aircrew weapons delivery manual (nonnuclear) b-52… 1b-52h-34-2-9... · t.o. 1b-52h-34-2-9 1 june...

T.O. 1B-52H-34-2-9

1 JUNE 1999CHANGE 11 – 1 JUNE 2006

AIRCREW WEAPONS DELIVERY MANUAL(NONNUCLEAR)B-52/AGM-86C/D

USAFSERIES

AIRCRAFTWEAPONSB-52/AGM-86C/D

THE BOEING COMPANYF34601-92-C-1116F34601-03-D-0066

This manual contains unverified procedures. Refer to the validation/verification statuspage(s) prior to performing any operation or maintenance procedure.

THIS PUBLICATION IS INCOMPLETE WITHOUT CLASSIFIED SUPPLEMENT T.O. 1B-52H-34-2-9-1.

SEE T.O. 0-1-CD-1 FOR CURRENT STATUS OF FLIGHT MANUALS, SAFETY SUPPLEMENTS, OPERATIONAL SUPPLEMENTS, ANDFLIGHT CREW CHECKLISTS.

COMMANDERS ARE RESPONSIBLE FOR BRINGING THIS PUBLICATION TO THE ATTENTION OF ALL AIR FORCE PERSONNELCLEARED FOR OPERATION OF SUBJECT AIRCRAFT.

DISTRIBUTION STATEMENT E – Distribution authorized to the Department of Defense Components only, due to Direct Military Support, 29October 1996. Other requests shall be referred to 327 BMSG/EN, Tinker AFB, OK 73145-3021.

WARNING –This document contains technical data whose export is restricted by the Arms Export Control Act (Title 22, U.S.C., Sec 2751, et seq.)or the Export Administration Act of 1979, as amended, Title 50, U.S.C., App. 2401 et seq. Violations of these export laws are subject to severecriminal penalties. Disseminate in accordance with provisions of DoD Directive 5230.25.

HANDLING AND DESTRUCTION NOTICE – Comply with distribution statement and destroy by any method that will prevent disclosure ofcontents or reconstruction of the document. Demil code D.

PUBLISHED UNDER AUTHORITY OF THE SECRETARY OF THE AIR FORCE

INSERT LATEST CHANGED PAGES. DESTROY SUPERSEDED PAGES.

*The asterisk indicates pages changed, added, or deleted by the current change.

Dates of issue for original and changed pages are:

NOTE: The portion of the text affected by the changes is indicated by avertical line in the outer margins of the page.

LIST OF EFFECTIVE PAGES

Upon receipt of the second and subsequent changes to this technical order, personnel responsible for maintaining this publication in currentstatus will ascertain that all previous changes have been received and incorporated. Action should be taken promptly if the publication isincomplete.

T.O. 1B-52H-34-2-9

A Change 11 USAF

ADDITIONAL COPIES OF THIS PUBLICATION MAY BE OBTAINED BY USAF ACTIVITIES IN ACCORDANCE WITH T.O. 00-5-1.

Technical orders are normally distributed promptly after printing. Date(s) shown on the title page (lower right corner) are for identification only. Theseare not distribution dates. Processing time sometimes causes distribution to only appear to have been delayed.

Original 0 1 Jun 99Change 1 1 Oct 99Change 2 1 Aug 00

Change 3 30 June 01Change 4 30 Nov 01Change 5 1 Mar 02

Change 6 1 Sep 02Change 7 1 Apr 03Change 8 1 Dec 03

Change 9 1 Dec 04Change 10 1 Jul 05Change 11 1 Jun 06

TOTAL NUMBER OF PAGES IN THIS PUBLICATION IS 288 CONSISTING OF THE FOLLOWING:

Page Change Page Change Page Change Page Change No. No. No. No. No. No. No. No.

* Title 11. . . . . . . . . . . . . . . . . . . . * A 11. . . . . . . . . . . . . . . . . . . . . .

V/VS-1 – V/VS-9 Added 10. . V/VS-10 Blank Added 10. . . . Flyleaf-1 9. . . . . . . . . . . . . . . . . Flyleaf-2 Blank 0. . . . . . . . . . . i 0. . . . . . . . . . . . . . . . . . . . . . . ii 4. . . . . . . . . . . . . . . . . . . . . . . iii – v 10. . . . . . . . . . . . . . . . . . . vi Blank 0. . . . . . . . . . . . . . . . . 1-1 10. . . . . . . . . . . . . . . . . . . . 1-2 Blank 0. . . . . . . . . . . . . . . . 1-3 10. . . . . . . . . . . . . . . . . . . . 1-4 – 1-6 7. . . . . . . . . . . . . . . .

* 1-6A – 1-6B 11. . . . . . . . . . . . . 1-6C – 1-6D 7. . . . . . . . . . . . . 1-6E – 1-6F Deleted 7. . . . . . 1-7 1. . . . . . . . . . . . . . . . . . . . . 1-8 0. . . . . . . . . . . . . . . . . . . . . 1-9 1. . . . . . . . . . . . . . . . . . . . . 1-10 – 1-11 0. . . . . . . . . . . . . . 1-12 7. . . . . . . . . . . . . . . . . . . . 1-13 – 1-20 10. . . . . . . . . . . . . 1-21 0. . . . . . . . . . . . . . . . . . . . 1-22 10. . . . . . . . . . . . . . . . . . . 1-23 – 1-27 0. . . . . . . . . . . . . . 1-28 6. . . . . . . . . . . . . . . . . . . . 1-29 0. . . . . . . . . . . . . . . . . . . .

* 1-30 – 1-31 11. . . . . . . . . . . . . 1-32 0. . . . . . . . . . . . . . . . . . . . 1-33 10. . . . . . . . . . . . . . . . . . . 1-34 0. . . . . . . . . . . . . . . . . . . . 1-35 2. . . . . . . . . . . . . . . . . . . . 1-36 Blank 0. . . . . . . . . . . . . . 1-37 10. . . . . . . . . . . . . . . . . . .

* 1-38 11. . . . . . . . . . . . . . . . . . .

1-39 – 1-40 10. . . . . . . . . . . . . 1-40A – 1-40B Added 10. . . . 1-41 0. . . . . . . . . . . . . . . . . . . .

* 1-42 11. . . . . . . . . . . . . . . . . . . 1-43 10. . . . . . . . . . . . . . . . . . .

* 1-44 11. . . . . . . . . . . . . . . . . . . 1-44A – 1-44D Added 10. . . . 1-45 – 1-46 10. . . . . . . . . . . . .

* 1-46A 11. . . . . . . . . . . . . . . . . . 1-46B 10. . . . . . . . . . . . . . . . . . 1-46C – 1-46D Added 10. . . . 1-47 – 1-56 10. . . . . . . . . . . . . 1-56A – 1-56B Deleted 10. . . 1-57 – 1-66 10. . . . . . . . . . . . . 1-66A – 1-66B 10. . . . . . . . . . . 1-66C Added 10. . . . . . . . . . . .

* 1-66D 11. . . . . . . . . . . . . . . . . . 1-66E Added 10. . . . . . . . . . . .

* 1-66F 11. . . . . . . . . . . . . . . . . . 1-66G – 1-66H Added 10. . . . 1-67 10. . . . . . . . . . . . . . . . . . .

* 1-68 11. . . . . . . . . . . . . . . . . . . 1-68A – 1-68D Added 10. . . . 1-69 – 1-70 10. . . . . . . . . . . . . 1-70A – 1-70B Added 10. . . . 1-71 – 1-72 10. . . . . . . . . . . . . 1-72A 10. . . . . . . . . . . . . . . . . . 1-72B 4. . . . . . . . . . . . . . . . . . . 1-73 0. . . . . . . . . . . . . . . . . . . .

* 1-74 11. . . . . . . . . . . . . . . . . . . 1-75 – 1-76 10. . . . . . . . . . . . . 1-76A – 1-76H Added 10. . . . 1-77 – 1-81 10. . . . . . . . . . . . . 1-82 0. . . . . . . . . . . . . . . . . . . . 1-83 – 1-84 10. . . . . . . . . . . . .

1-85 – 1-86 0. . . . . . . . . . . . . . 1-87 – 1-88 10. . . . . . . . . . . . . 1-89 0. . . . . . . . . . . . . . . . . . . . 1-90 10. . . . . . . . . . . . . . . . . . . 1-91 – 1-92 0. . . . . . . . . . . . . . 1-93 – 1-96 10. . . . . . . . . . . . . 1-97 Added 10. . . . . . . . . . . . . 1-98 Blank Added 10. . . . . . . . 2-1 – 2-3 10. . . . . . . . . . . . . . . 2-4 – 2-5 6. . . . . . . . . . . . . . . . 2-6 – 2-7 0. . . . . . . . . . . . . . . . 2-8 – 2-9 6. . . . . . . . . . . . . . . . 2-10 10. . . . . . . . . . . . . . . . . . . 2-10A – 2-10B 10. . . . . . . . . . . 2-11 – 2-14 10. . . . . . . . . . . . . 2-14A – 2-14B 10. . . . . . . . . . . 2-14C – 2-14D Added 10. . . . 2-15 – 2-16 10. . . . . . . . . . . . 2-17 – 2-19 7. . . . . . . . . . . . . . 2-20 6. . . . . . . . . . . . . . . . . . . . 2-21 – 2-22 9. . . . . . . . . . . . . .

* 2-23 11. . . . . . . . . . . . . . . . . . . 2-24 6. . . . . . . . . . . . . . . . . . . . 2-25 2. . . . . . . . . . . . . . . . . . . . 2-26 0. . . . . . . . . . . . . . . . . . . .

* 2-27 11. . . . . . . . . . . . . . . . . . . 2-28 2. . . . . . . . . . . . . . . . . . . . 2-29 0. . . . . . . . . . . . . . . . . . . . 2-30 3. . . . . . . . . . . . . . . . . . . . 2-31 0. . . . . . . . . . . . . . . . . . . . 2-32 2. . . . . . . . . . . . . . . . . . . . 3-1 4. . . . . . . . . . . . . . . . . . . . . 3-2 – 3-3 10. . . . . . . . . . . . . . . 3-4 7. . . . . . . . . . . . . . . . . . . . . 3-5 – 3-8 0. . . . . . . . . . . . . . . .

3-9 4. . . . . . . . . . . . . . . . . . . . . 3-10 Blank 0. . . . . . . . . . . . . . . 4-1 7. . . . . . . . . . . . . . . . . . . . . 4-2 10. . . . . . . . . . . . . . . . . . . . 4-2A Added 3. . . . . . . . . . . . . . 4-2B Blank Added 3. . . . . . . . 4-3 10. . . . . . . . . . . . . . . . . . . . 4-4 0. . . . . . . . . . . . . . . . . . . . . 5-1 0. . . . . . . . . . . . . . . . . . . . . 5-2 Blank 0. . . . . . . . . . . . . . . . 6-1 0. . . . . . . . . . . . . . . . . . . . . 6-2 Blank 0. . . . . . . . . . . . . . . . 7-1 10. . . . . . . . . . . . . . . . . . . . 7-2 0. . . . . . . . . . . . . . . . . . . . . 7-3 – 7-5 10. . . . . . . . . . . . . . . 7-6 9. . . . . . . . . . . . . . . . . . . . . 7-7 – 7-8 0. . . . . . . . . . . . . . . . 7-9 – 7-12 10. . . . . . . . . . . . . . 7-12A – 7-12B Deleted 7. . . . 7-13 – 7-16 Added 10. . . . . . . 7-17 – 7-18 10. . . . . . . . . . . . . 7-18A – 7-18F Deleted 10. . . 7-18G – 7-18H Deleted 7. . . . 7-19 – 7-24 10. . . . . . . . . . . . . 7-24A – 7-24B Deleted 7. . . . 7-25 – 7-34 10. . . . . . . . . . . . .

* 7-35 – 7-37 11. . . . . . . . . . . . . 7-38 – 7-46 10. . . . . . . . . . . . . 7-46A – 7-46B Deleted 10. . . 7-47 – 7-54 10. . . . . . . . . . . . . 7-55 – 7-66 Added 10. . . . . . . Glossary-1 – Glossary-2 10. . Glossary-3 Added 10. . . . . . . Glossary-4 Blank Added 10. . Index-1 – Index-4 10. . . . . . . .

CURRENT ABBREVIATED CHECKLIST

AGM-86C/D CALCM MISSILE Abbreviated Flight Crew Checklist T.O. 1B-52H-34-2-9CL-1 1 Jun 99 Change 9 1 Jun 06

T.O. NO. PTO CHANGE NO. – DATE

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BASIC DATE CHANGE NO. – DATE

This manual contains unverified procedures. Unverified procedures shall only be performed during verification, in accor-dance with TOs 00-5-1 and 00-5-3. Performance of unverified procedures may result in injury to personnel or damage toequipment.

WARNING

V/VS-1

T.O 1B-52H-34-2-9 1 JUN 99 CHANGE 10 1 JUL 05 AMI

TCTO Listings (P, PG v) 5/16/03 AB-52 Carrier Aircraft(P, PG 1-3) 5/16/03 AB-52 Carrier Aircraft(S, PG 1-3) 5/16/03 ACircuit Breaker Panels(F: 1-7, 2/3, PG 1-14) 5/16/03 AOAS Avionics System(P, PG 1-17) 5/16/03 AOAS Avionics System (OAS)Interface (S, PG 1-17) 5/16/03 ALocation/Station Selection(P, PG 1-18) 5/16/03 AEjector Unlock Consent(P, PG 1-18) 5/16/03 AWeapon Power Control Command(P, PG 1-18 – 1-19) 5/16/03 AReady-To-Launch Command(P, PG 1-19) 5/16/03 AManual Launch Command(P, PG 1-19) 5/16/03 AOAS/Missile Data Flow (F: 1-10, PG 1-22) 5/16/03 AMissile Jettison(S, PG 1-30) 5/16/03 AMissile Jettison Switch(P, PG 1-30) 5/16/03 APilot’s Jettison Controls andIndicators (F: 1-17, PG 1-31) 5/16/03 AStores Management Overlay(S, PG 1-37) 5/16/03 ASMO Initialization(P, PG 1-37) 5/16/03 ASMO Termination(P, PG 1-37 – 1-38) 2/01/03 ASMO Reconfiguration(P, PG 1-38) 5/16/03 AControls and Displays Commands(P, PG 1-38) 5/16/03 AOAS Power Control Panel Commands(P, PG 1-39) 5/16/03 A



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V/VS-2


Weapon Control Panel Commands(P, PG 1-39) 5/16/03 APilot’s Munitions Consent PanelCommands (P, PG 1-40) 5/16/03 APilot’s Bomb Bay and MissileJettison Control Switch (P, PG 1-40) 5/16/03 AIKB Commands(P, PG 1-40 –1-40A) 5/16/03 AMFD Displays(P, PG 1-40A) 5/16/03 ASMO MFD Displays(P, PG 1-40B) 5/16/03 APrime Mission Data(P, PG 1-40B) 5/16/03 AControl Function (CF) Displays(S, PG 1-42) 5/16/03 AWeapon Supervision Menu(P, PG 1-42) 5/16/03 AStrike Mode Command(P, PG 1-42) 5/16/03 APART SIM Mode Command(P, PG 1-42) 5/16/03 AFULL SIM Mode Command(P, PG 1-43) 5/16/03 ASMO Control Function Commands(F: 1-22, 1/2, PG 1-44) 5/16/03 ASMO Control Function Commands(F: 1-22, 2/2, PG 1-44A) 5/16/03 AControl Function Menu(F: 1-23, 1/2, PG 1-44B) 5/16/03 AControl Function Menu(F: 1-23, 2/2, PG 1-44C) 5/16/03 AWeapon Supervision Menu(F: 1-24, 1/2, PG 1-44D) 5/16/03 AWeapon Supervision Menu(F: 1-24, 2/2, PG 1-45) 5/16/03 ACALCM Supervision Menu(P, PG 1-46) 5/16/03 ACrypto Key Override Command(P, PG 1-46) 5/16/03 ACALCM Supervision Menu(F: 1-25, 1/2, PG 1-46A) 5/16/03 A



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V/VS-3


CALCM Supervision Menu(F: 1-25, 2/2, PG 1-46B) 5/16/03 AWeapon Erase Command CF-55F(P, PG 1-46C) 5/16/03 ACALCM Auto Targeting Mode CF-550(P, PG 1-46C) 5/16/03 AGo/No-Go Test CF-551(P, PG 1-46C) 5/16/03 ASystem Interface Test (SIT) CF-552(P, PG 1-46C) 5/16/03 AManual SAIR Command CF-553(P, PG 1-46C – 1-46D) 5/16/03 AClassified Data EraseCommand CF-555 (P, PG 1-46D) 5/16/03 AManual Target Command CF-556,nn(P, PG 1-46D) 5/16/03 AFlex Targeting SelectionCommand CF-557,nn (P, PG 1-47) 5/16/03 ACF-557,nn Flex Target Input Display(F: 1-26, 1/9, PG 1-48) 5/16/03 ACF-557,nn Flex Target Input Display(F: 1-26, 2/9, PG 1-49) 5/16/03 ACF-557,nn Flex Target Input Display(F: 1-26, 3/9, PG 1-50) 5/16/03 ACF-557,nn Flex Target Input Display(F: 1-26, 4/9, PG 1-51) 5/16/03 ACF-557,nn Flex Target Input Display(F: 1-26, 5/9, PG 1-52) 5/16/03 ACF-557,nn Flex Target Input Display(F: 1-26, 6/9, PG 1-53) 5/16/03 ACF-557,nn Flex Target Input Display(F: 1-26, 7/9, PG 1-54) 5/16/03 ACF-557,nn Flex Target Input Display(F: 1-26, 8/9, PG 1-55) 5/16/03 ACF-557,nn Flex Target Input Display(F: 1-26, 9/9, PG 1-56) 5/16/03 ADirect Targeting Input ScreenCF-558,nn (P, PG 1-57) 5/16/03 ACF-558 Direct Targeting Input Display(F: 1-27, 1/10, PG 1-58) 5/16/03 ACF-558 Direct Targeting Input Display(F: 1-27, 2/10, PG 1-59) 5/16/03 A



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CF-558 Direct Targeting Input Display(F: 1-27, 3/10, PG 1-60) 5/16/03 ACF-558 Direct Targeting Input Display(F: 1-27, 4/10, PG 1-61) 5/16/03 ACF-558 Direct Targeting Input Display(F: 1-27, 5/10, PG 1-62) 5/16/03 ACF-558 Direct Targeting Input Display(F: 1-27, 6/10, PG 1-63) 5/16/03 ACF-558 Direct Targeting Input Display(F: 1-27, 7/10, PG 1-64) 5/16/03 ACF-558 Direct Targeting Input Display(F: 1-27, 8/10, PG 1-65) 5/16/03 ACF-558 Direct Targeting Input Display(F: 1-27, 9/10, PG 1-66) 5/16/03 ACF-558 Direct Targeting Input Display(F: 1-27, 10/10, PG 1-66A) 5/16/03 ATarget/Retarget-All Command CF-559(P, PG 1-66B) 5/16/03 ASMO Menu (CF-62)(P, PG 1-66C) 5/16/03 AShutdown (CF-67)(P, PG 1-66D) 5/16/03 AECU PWR ORIDE (CF-68)(P, PG 1-66D) 5/16/03 ACF-6 FCP Supervision Menu(F: 1-28, 1/2, PG 1-66E) 5/16/03 ACF-6 FCP Supervision Menu(F: 1-28, 2/2, PG 1-66F) 5/16/03 ACF-62 SMO Load Menu(F: 1-29, 1/2, PG 1-66G) 5/16/03 ACF-62 SMO Load Menu(F: 1-29, 2/2, PG 1-66H) 5/16/03 AMission Supervision Menu (CF-8)(P, PG 1-67) 5/16/03 AB-52 Mission Data Load Display(CF-81) (P, PG 1-67) 5/16/03 AWeapon Group Selection Menu(P, PG 1-68) 5/16/03 ACF-8 Mission Supervision Menu(F: 1-30, 1/2, PG 1-68A) 5/16/03 ACF-8 Mission Supervision Menu(F: 1-30, 2/2, PG 1-68B) 5/16/03 A



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CF-81 Mission Data Load Display(F: 1-30A, 1/2, PG 1-68C) 5/16/03 ACF-81 Mission Data Load Display(F: 1-30A, 2/2, PG 1-68D) 5/16/03 ACF-82A, CF-82B, CF-82C Wpn GrpSelection Screen (F: 1-30B, PG 1-69) 5/16/03 ASend Targeting Data Command(P, PG 1-70) 5/16/03 ACF-DF AGM-86D Fuze Data InputDisp (F:1-30C, 1/5, PG 1-70A) 5/16/03 ACF-DF AGM-86D Fuze Data InputDisp (F:1-30C, 2/5, PG 1-70B) 5/16/03 ACF-DF AGM-86D Fuze Data InputDisp (F:1-30C, 3/5, PG 1-71) 5/16/03 ACF-DF AGM-86D Fuze Data InputDisp (F:1-30C, 4/5, PG 1-72) 5/16/03 ACF-DF AGM-86D Fuze Data InputDisp (F:1-30C, 5/5, PG 1-72A) 5/16/03 AFormat Displays(S, PG 1-74) 5/16/03 AStatus and Inventory Display(FRMT-7) (P, PG 1-74) 5/16/03 AWeapon Group Assignment Data Display (P, PG 1-75) 5/16/03 AStores Inventory Summary Display(FRMT-77) (P, PG 1-75) 5/16/03 AFormat Commands(F:1-32, PG 1-75) 5/16/03 AFormat Menu(F:1-33, 1/2, PG 1-76) 5/16/03 AFormat Menu(F:1-33, 2/2, PG 1-76A) 5/16/03 AFRMT-6 PME Status Display(F:1-34, 1/3, PG 1-76A) 5/16/03 AFRMT-6 PME Status Display(F:1-34, 2/3, PG 1-76B) 5/16/03 AFRMT-6 PME Status Display(F:1-34, 3/3, PG 1-76C) 5/16/03 AFRMT-7 and FRMT-7xy Status andInvent Disp (F:1-35, 1/5, PG 1-76D) 12/1/04 AFRMT-7 and FRMT-7xy Status andInvent Disp (F:1-35, 2/5, PG 1-76E) 12/1/04 A



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FRMT-7 and FRMT-7xy Status andInvent Disp (F:1-35, 3/5, PG 1-76F) 2/01/05 AFRMT-7 and FRMT-7xy Status andInvent Disp (F:1-35, 4/5, PG 1-76G) 2/01/05 AFRMT-7 and FRMT-7xy Status andInvent Disp (F:1-35, 5/5, PG 1-76H) 2/01/05 ACF-DF or CF-DB Wpn Grp Assign Data Disp (F:1-35A, 1/3, PG 1-77) 5/16/03 ACF-DF or CF-DB Wpn Grp Assign Data Disp (F:1-35A, 2/3, PG 1-78) 5/16/03 ACF-DF or CF-DB Wpn Grp Assign Data Disp (F:1-35A, 3/3, PG 1-79) 5/16/03 AFRMT-77 Stores Inventory SummaryDisp (F:1-35B, 1/2, PG 1-80) 5/16/03 AFRMT-77 Stores Inventory SummaryDisp (F:1-35B, 2/2, PG 1-81) 5/16/03 ACALCM Direct Target Program Disp(P, PG 1-83) 5/16/03 AWeapon Targeting Commands(P, PG 1-84) 5/16/03 ASMO Launch Point Program Display(F:1-39, 2/3, PG 1-87) 5/16/03 ASMO Launch Point Program Display(F:1-41, 1/5, PG 1-93) 5/16/03 ASMO Launch Point Program Display(F:1-41, 2/5, PG 1-94) 5/16/03 ASMO Launch Point Program Display(F:1-41, 3/5, PG 1-95) 5/16/03 ASMO Launch Point Program Display(F:1-41, 4/5, PG 1-96) 5/16/03 ASMO Launch Point Program Display(F:1-41, 5/5, PG 1-97) 5/16/03 AGeneral(P, PG 2-3) 5/16/03 ACALCM SMO Loading Checklist(PG 2-10) 5/16/03 AWeapon Check Checklist(PG 2-10 – 2-10B) 5/16/03 AMissile Power Application Checklist(PG 2-11 – 2-12) 2/01/05 ATarget/Retarget All Checklist(PG 2-14A – 2-14B) 5/16/03 A



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Mission Substitution Checklist(PG 2-15) 5/16/03 AManual Retargeting Checklist(PG 2-16) 5/16/03 AMissile Jettison Procedures (RN/N Reads) (PG 3-2) 5/16/03 AMissile Jettison Procedures (RN/N Reads) (Cont) (PG 3-3) 2/01/05 ATelemetry Power Transfer CommandCF-55C (P, PG 4-2) 2/01/05 ALaunch(P, PG 4-3) 5/16/03 ASMO Capabilities(P, PG 7-3) 5/16/03 AStrike Capabilities(P, PG 7-3) 5/16/03 AMIU Power Application(P, PG 7-4) 5/16/03 AMission Data(P, PG 7-9) 5/16/03 APreplanned Mission(P, PG 7-9) 5/16/03 AAutomatic Targeting Process(P, PG 7-10) 5/16/03 AManual Targeting Process(P, PG 7-11) 5/16/03 AWeapon Targeting Commands(P, PG 7-12) 5/16/03 AManual Target Command(P, PG 7-14) 5/16/03 ATarget/Retarget All Command(P, PG 7-14) 5/16/03 ATarget Location(P, PG 7-16) 5/16/03 AImpact Angle(P, PG 7-17) 5/16/03 AFlex Target Mission Data Entry(P, PG 7-18 – 7-20) 2/01/05 ADirect Target Data Entry(P, PG 7-20 – 7-22) 2/01/05 AIn-Range Determination(P, PG 7-25) 5/16/03 A



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Manual SAIR(P, PG 7-25 ) 5/16/03 ADirect SAIR(P, PG 7-27) 5/16/03 AAutomatic Retargeting(P, PG 7-31) 5/16/03 ALaunch Determination(P, PG 7-33) 5/16/03 AAuto Launch Determination(P, PG 7-33 – 7-34) 5/16/03 AMan Launch Determination(P, PG 7-34) 5/16/03 AManual Jettison(P, PG 7-36) 5/16/03 ASimulated Weapons(P, PG 7-38) 5/16/03 ATermination Of SIM Mode(P, PG 7-39) 5/16/03 ASIT/MIT and CF-552(P, PG 7-39) 5/16/03 AMissile/Station Master Faults(F: 7-9, 1/10, PG 7-42) 2/01/05 AMissile/Station Master Faults(F: 7-9, 2/10, PG 7-43) 2/01/05 AMissile/Station Master Faults(F: 7-9, 3/10, PG 7-44) 2/01/05 AMissile/Station Master Faults(F: 7-9, 4/10, PG 7-45) 2/01/05 AMissile/Station Master Faults(F: 7-9, 5/10, PG 7-46) 2/01/05 AMissile/Station Master Faults(F: 7-9, 6/10, PG 7-47) 2/01/05 AMissile/Station Master Faults(F: 7-9, 7/10, PG 7-48) 2/01/05 AMissile/Station Master Faults(F: 7-9, 8/10, PG 7-49) 2/01/05 AMissile/Station Master Faults(F: 7-9, 9/10, PG 7-50) 2/01/05 AMissile/Station Master Faults(F: 7-9, 10/10, PG 7-51) 2/01/05 AOAS/MIU Master Faults(F: 7-10, 1/8, PG 7-52) 2/01/05 A



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OAS/MIU Master Faults(F: 7-10, 2/8, PG 7-53) 2/01/05 AOAS/MIU Master Faults(F: 7-10, 3/8, PG 7-54) 2/01/05 AOAS/MIU Master Faults(F: 7-10, 4/8, PG 7-55) 2/01/05 AOAS/MIU Master Faults(F: 7-10, 5/8, PG 7-56) 2/01/05 AOAS/MIU Master Faults(F: 7-10, 6/8, PG 7-57) 2/01/05 AOAS/MIU Master Faults(F: 7-10, 7/8, PG 7-58) 2/01/05 AOAS/MIU Master Faults(F: 7-10, 8/8, PG 7-59) 2/01/05 ACALCM Advisories(F: 7-11, 1/5, PG 7-60) 2/01/05 ACALCM Advisories(F: 7-11, 2/5, PG 7-61) 2/01/05 ACALCM Advisories(F: 7-11, 3/5, PG 7-62) 2/01/05 ACALCM Advisories(F: 7-11, 4/5, PG 7-63) 2/01/05 ACALCM Advisories(F: 7-11, 5/5, PG 7-64) 2/01/05 ACF-557, CF-558, and FRMT-7Wpn Faults (F: 7-12, 1/2, PG 7-65) 5/16/03 ACF-557, CF-558, and FRMT-7Wpn Faults (F: 7-12, 2/2, PG 7-66) 5/16/03 AGlossary(S, PG Glossary 1 – Glossary3) 5/16/03 A

T.O. 1B-52H-34-2-9

Change 9 Flyleaf-1/(Flyleaf-2 blank)

STATUS OF SAFETY AND OPERATIONAL SUPPLEMENTS

This supplement status page is based on information available to the manual editor as of the date ofthis publication. The information may not be current as it must be updated by any subsequent supple-ment status pages and by reference to T.O. 0-1-CD-1.

SUPPLEMENTS IN THIS CHANGE

Number Date Short Title Section Affected

SS-3 (I) 15 Mar 2004 Effects of Buffers on CALCM C/D IIWeapon Navigation Solution

OUTSTANDING SUPPLEMENTS

Number Date Short Title Section Affected

T.O. 1B-52H-34-2-9

i

table of contents page

SECTION I DESCRIPTION 1-1

SECTION II NORMAL AIRCREW PROCEDURES 2-1

SECTION III EMERGENCY AIRCREW PROCEDURES 3-1

SECTION IV SUPPLEMENTARY DATA 4-1

SECTION V OPERATING LIMITATIONS 5-1

SECTION VI MISSION PLANNING 6-1

SECTION VII SYSTEMS OPERATION 7-1

GLOSSARY GLOSSARY-1

ALPHABETICAL INDEX INDEX-1

T.O. 1B-52H-34-2-9

ii Change 4

INTRODUCTION

SCOPE. This manual and classified T.O. 1B-52H-34-2-9-1 provide the system, procedural, andmissile performance information required to operate AGM-86C Conventional ALCM(CALCM) with the CALCM Stores Management Overlay (SMO), or the AGM-86C Conven-tional ALCM (CALCM) and the AGM-86D CALCM Penetrator with the CALCM PenetratorStores Management Overlay (SMO) This T.O. includes data for delivery of an AGM-86C/Dair-to-surface missile under all normal and the majority of abnormal conditions.

NOTE

This manual will be carried aboard the aircraft when AGM-86 C/DCALCM are loaded or when AGM-86 C/D CALCM training is per-formed. In addition, T.O. 1B-52H-34-2-9-1 will be carried whenAGM-86 C/D CALCM are loaded.

CONTENT. This manual contains descriptions and procedures relating to AGM-86C/D missilesand the B-52H carrier aircraft. Aircraft fuel system management with the missiles installedis given in the aircraft basic flight manuals. Aircraft performance with the pylons and mis-siles installed is given in the basic flight manual appendices.

CHECKLISTS. Abbreviated checklists for procedures in this manual are contained in theCALCM flightcrew checklist. This checklist is identified by a TO number identical to that ofthis manual except for the addition of the letters CL (checklist) and a suffix number 1.

ARRANGEMENT. This manual is divided into seven sections.

Section I, DESCRIPTION – Locates, identifies, and functionally describes the missile andaircraft components of concern to the aircrew in the delivery of an AGM-86C/D missile.

Section II, NORMAL AIRCREW PROCEDURES – Contains partially illustrated amplifiedchecklists for performance of normal aircrew missile delivery and ferry procedures from pre-flight through after landing, procedures applicable in the event a mission is aborted, and pro-cedures for declassifying mission data in the system. Procedures, techniques, and program-ming practice can be accomplished on any aircraft with OAS/AGM-86C/D equipment in-stalled.

Section III, EMERGENCY AIRCREW PROCEDURES – Contains missile and pylon jettisonprocedures. No attempt is made to regulate or define conditions under which a mission maybe aborted.

Section IV, SUPPLEMENTARY DATA – Contains information on operational test launch andjoint test launch systems and associated procedures.

Section V, OPERATING LIMITATIONS – Contains important missile and weapon systemlimitations that must be taken into account during planning and accomplishment of a mis-sion.

Section VI, MISSION PLANNING – Contains information on transportation of dangerousmaterial, inflight emergency notification, and inflight mission data changes that can be ac-complished by the flightcrew.

Section VII, SYSTEMS OPERATION – Contains additional material regarding the operationof the aircraft OAS/AGM-86C/D missile systems. Theory of guidance system operation, guid-ance performance, and malfunction analysis are included.

T.O. 1B-52H-34-2-9

Change 10 iii

PRECEDENCE. Compliance with procedures herein is mandatory. In all instances, only thoseoperations which are within the scope of the current applicable safety rules may be per-formed.

SAFETY POLICIES. The procedures in this manual reflect the latest applicable rules and poli-cies. Aircrew compliance with these procedures and policies is mandatory.

Mission planning shall provide maximum protection to friendly and neutral areas consistentwith operational requirements. Selection of launch point and type of maneuver shall beguided by the possible effect upon friendly or neutral areas of a missile guidance or controlsystem failure. Since launch point and type of maneuver are sufficiently flexible to allow forinflight decisions, aircrews shall be briefed concerning the potential disaster hazard tofriendly or neutral areas.

REFERENCES. The following publications, available to using commands, should be used togain more comprehensive information on subjects referred to in this technical order:

1B-52H-1 Flight Manual1B-52H-1-1 Flight Manual – Appendix 1, Performance Data1B-52H-1-12 Radar Navigator’s/Navigator’s Manual1B-52H-1-13 Electronic Warfare Officer’s Manual1B-52H-2-31GA-1 General Aircraft/Bomb Release System B-52H1B-52H-33-2-2 Nonnuclear Munitions Loading Procedures1B-52H-34-2-1 Aircrew Weapon Delivery Manual (Nonnuclear) B-521B-52H-34-2-5 Aircrew Weapon Delivery Manual (Nonnuclear) B-52/WCMD1B-52H-34-2-6 Aircrew Weapon Delivery Manual (Nonnuclear) B-52/JDAM1B-52H-34-2-7 Aircrew Weapon Delivery Manual (Nonnuclear) B-52/JSOW1B-52H-34-2-8 Aircrew Weapon Delivery Manual (Nonnuclear) B-52/JASSM1B-52H-34-2-9-1 Aircrew Weapon Delivery Manual (Nonnuclear) B-52/AGM-86C/D

Classified Supplement1B-52H-5 Basic Weight Checklist and Loading Data B-52H1-1M-34 Aircrew Weapons Delivery Manual (Nonnuclear) Standard VolumeJMEM Joint Munition Employment Manual

SAFETY AND OPERATIONAL SUPPLEMENTS. Information involving flightcrew safety and di-rectly pertaining to the information contained herein will be promptly forwarded to you bySafety Supplements issued against this manual. Safety Supplements covering loss of life willget to you in 48 hours by a message (called Interim Safety Supplements) and those concern-ing serious damage to equipment within 15 days by mail (in a formal printed form). Opera-tional information not involving safety but of an urgent nature will be forwarded to you byOperational Supplements issued against this manual. These will be forwarded by a message(interim) or by mail (formal), depending on the urgency of the information. Interim supple-ments are normally replaced by formal printed supplements at an early date. Formal printedsupplements are identified by red letters ‘‘SS’’ for safety supplements and black letters ‘‘OS’’for operational supplements printed around the borders of the pages. The currency of safetyand operational supplements affecting your manual can be determined by referring to theIndex of Bomber Aircraft Safety Supplements (T.O. 0-1-CD-1). The title block of each supple-ment and the title page of this manual should also be checked to determine the effect theymay have on existing supplements. You must remain constantly aware of the status of allsupplements – current supplements must be complied with, but there is no point in restrict-ing your operation by complying with a replaced or rescinded supplement. As a further aid, asupplement summary is included in this manual, following the A pages, for both safety andoperational supplements; however, this summary can only be as current as this manual.Safety and operational supplements will be filed in accordance with Section VI of the AirForce Technical Order System, T.O. 00-5-1.

T.O. 1B-52H-34-2-9

iv Change 10

WARNINGS, CAUTIONS, and NOTES. The following definitions apply to “Warnings,” “Cautions,” and “Notes” found throughout the manual.

Operating procedures, techniques, etc which could result in personalinjury or loss of life if not carefully followed.

Operating procedures, techniques, etc which could result in dam-age to equipment if not carefully followed.

NOTE An operating procedure, technique,etc which is considered essential toemphasize.

SHALL, WILL, SHOULD, and MAY. The following definitions apply to the words:

SHALL or WILL The instructions or procedures prefaced by ‘‘shall’’ or ‘‘will’’ are mandatory.

SHOULD Normally used to indicate a preferred but nonmandatory method ofaccomplishment.

MAY An acceptable or suggested means of accomplishment.

CHANGE SYMBOLS. Changes to existing material and addition of new material are indicatedby one of three types of symbols determined by the nature of the material affected. Text ma-terial utilizes a vertical line in the margin adjacent to the affected area. New illustrations(figures) utilize a vertical line in the outer margin of the page. Photographs and line draw-ings use a miniature pointing hand to highlight the affected area. Diagrams and schematicsutilize a grey tone (screening) to highlight the affected area. Change symbols are not used forblank space resulting from deletions, indexes, and tabular data where changes cannot beidentified, relocation of material, or correction of minor inaccuracies unless such correctionchanges the meaning.

RESPONSIBLE AGENCY. Every effort is made to keep this manual current. Review conferenceswith operating personnel and a constant review of reports assure inclusion of the latest datain this manual. Comments, corrections, and questions regarding this manual should be sub-mitted on AF Form 847 to your local standardization/evaluation unit and routed as directedby AFI 11-215 to the Flight Manual Manager, 327 BMSG/EN, Tinker AFB, Oklahoma73145-3021.

AIRCRAFT GROUP CODING. Certain modifications which have been completed do not includeall serialized aircraft in the models affected. Information pertaining to these aircraft is iden-tified by aircraft group coding symbols such as CS . Specific aircraft serialization withinthese groups is identified in the appropriate flight manual under a like coding in the ‘‘Air-craft Coding’’ pages.

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Change 10 v/(vi blank)

RETROFIT CODING. The following code symbols along with the words ‘‘Less’’ and ‘‘Plus’’ areused to distinguish information related to aircraft that have the described retrofit change in-corporated from that which is applicable to aircraft not yet retrofitted. This list contains onlyTCTO’s currently active. Those known to be completed are not included.

SYMBOL T.O. NO. TITLE

CS

1B-52H-753

1B-52H-756

⎧⎨⎩

Installation of Global Positioning System (GPS) on B-52HAircraft (ECP 0109)

Installation of Integrated Conventional Stores Management System (ICSMS)on B-52H Aircraft (ECP 0109)

[AMI] 1B-52H-830 Replacement of Ballistics Computer Set AN/AYQ-10 and Inertial NavigationSystem AN/ASN-136 on B-52H Aircraft.

T.O. 1B-52H-34-2-9

Change 10 1-1/(1-2 blank)

Description section I


PART 1 - B-52/CALCM SYSTEM DESCRIPTION 1-3

B-52/AGM-86 CONVENTIONAL AIR LAUNCHED CRUISE MISSILE(CALCM) WEAPON SYSTEM 1-3

B-52 CARRIER AIRCRAFT 1-3

AGM-86 MISSILE 1-3

AIRCRAFT COMMON STRATEGIC ROTARY LAUNCHER SYSTEM 1-7

PYLONS 1-7

AIRCRAFT ELECTRICAL SYSTEM 1-12

AIRCRAFT ENVIRONMENTAL CONTROL SYSTEM (ECS/MCS) 1-12

PART 2 - B-52 AVIONICS SYSTEM 1-17

OFFENSIVE AVIONICS SYSTEM (OAS) 1-17

OFFENSIVE AVIONICS SYSTEM (OAS) INTERFACE 1-17

OAS/MISSILE SYSTEM RELATED CONTROLS AND DISPLAYS 1-17

MISSILE JETTISON 1-30

PART 3 - CALCM OAS SOFTWARE AND DISPLAYS 1-37

STORES MANAGEMENT OVERLAY (SMO) 1-37

SMO MFD DISPLAYS 1-40B

RELEASE ADVISORY DISPLAYS 1-40B

PRIME MISSION DATA DISPLAYS 1-40B

CONTROL FUNCTION (CF) DISPLAYS 1-42

FORMAT (FRMT) DISPLAYS 1-74

SMO PROGRAM (PRGM) DISPLAY 1-83

T.O. 1B-52H-34-2-9

Change 10 1-3

PART 1 - B-52/CALCM SYSTEM DESCRIPTION

B-52/AGM-86 CONVENTIONAL AIRLAUNCHED CRUISE MISSILE (CALCM) WEAPON SYSTEM

The B-52/CALCM weapon system consists of aB-52H carrier aircraft, two underwing six-stationmissile pylons, an eight-station common strategicrotary launcher (CSRL) and up to 20 AGM-86CALCM. The full missile load may be carried forautomatic or manual launch against prepro-grammed targets.

B-52 CARRIER AIRCRAFT

The offensive avionics system (OAS) controls pro-gramming, prearming, and launching of missiles.The OAS also provides signal processing, storageavionics, control and display panels, missile super-vision, regulated dc power conversion, and monitorsenvironmental control equipment in the aircraft.The OAS interfaces with the carrier electricalsources, release circuit disconnect for pylon jettison,bomb tone scoring, and panel lighting. Primarymissile control and monitor is provided through theweapon control panel (WCP) and the multifunction-al displays (MFD).

CALCM power control, monitoring, and launch con-trol is provided via a Missile Interface Unit (MIU)Line Replaceable Unit (LRU) and the SMO in con-junction with existing Less [AMI] ICSMS, OASand Global Positioning System (GPS) hardware andthe Flight Management System (FMS) software;[AMI] AMI, OAS and GPS hardware, and FMS andCommon Stores Processing (CSP) software.

Less [AMI] The CALCM SMO executes in the B-52HAvionics Control Units (ACU) and is loaded into non-volatile memory in the ACUs from an external loadtape called the Operational Computer Program(OCP) Data Transfer Unit Cartridge (DTUC). TheCALCM SMO, in conjunction with the FMS, providesthe necessary CALCM weapon delivery functions forthe ACU to control, monitor and release CALCM mis-siles utilizing existing OAS/ICSMS/GPS equipment.The SMO will only be able to operate on weapons atlocations where the FMS has assigned the SMO. Eventhough the CALCM uses GPS for navigation, there isno GPS navigation data supplied from the aircraftGPS to the CALCM.

[AMI] The CALCM SMO executes in the B-52HAvionics Control Units (ACU) and is loaded into non-volatile memory in the ACUs from an external loadcartridge called the Operational Computer Program

(OCP) Data Transfer Cartridge (DTC). The CALCMSMO, in conjunction with the FMS, provides the nec-essary CALCM weapon delivery functions for theACU to control, monitor and release CALCM missilesutilizing existing OAS/AMI/GPS equipment. TheSMO will only be able to operate on weapons at loca-tions where the FMS has assigned the SMO. When se-lected as the secondary SMO, the SMO will be limitedto functions that can be performed without interfer-ing with the operation of the primary SMO. Eventhough the CALCM uses GPS for navigation, there isno GPS navigation data supplied from the aircraftGPS to the CALCM.

The pilot’s missile controls include an ejector racklock-unlock consent switch, a prearm-off switch, anoverhead panel jettison control switch, a pylon jetti-son consent switch, and a pylon jettison controlswitch.

AGM-86 MISSILE (CALCM)

The AGM-86 (figure 1-1) is a subsonic, turbofan-en-gine powered, winged missile. The missile is de-signed to deliver a conventional warhead in an air-to-ground mission with a very high degree of accu-racy at long range. During captive flight, the mis-sile’s flight surfaces (wings, fin, elevons), and en-gine inlet are carried in a stowed position. Afterlaunch the missile’s flight surfaces are deployedand the engine provides thrust within a few sec-onds. Computer controlled navigation, using a glob-al positioning system (GPS), directs the missile toits target.

AGM-86C MISSILE (CALCM C)

There are two versions of the AGM-86C, the Block0A and Block 1A missile. The Block 0A missile hasa 2000 pound class warhead. The Block 1A missilehas a 3000 pound class warhead.

The AGM-86C missiles have the GRIU/P GPS re-ceiver and computer co-processor supplementingthe missile computer in the INE. Additionally, theAGM-86C missiles have a GPS anti-jam system.

AGM-86D MISSILE (CALCM D)

The AGM-86D missile has a 1000 pound class pene-trator warhead. The AGM-86D also has the GRIU/PGPS receiver and computer co-processor that sup-plements the computer in the INE. Additionally, themissiles are outfitted with a GPS Anti-jam system.

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1-4 Change 7

MISSILE DIMENSIONS AND GROSS WEIGHT

Length: 20 feet 9 inches Span:Wings Folded 2 feet 3 inches Wings Extended 12 feet 0 inches Approximate Gross Weight:

3267 pounds (AGM-86C) 3280 Pounds (AGM-86D)

MISSILE SOFTWARE CLASSIFICATION

The CALCM missile software (OFS) is secret, andas a result anytime the missile has OFS loaded it isclassified as secret.

There are three methods for the operator to poweroff the missile. All three methods overwrite theGPS crypto keys. The OFS erasure and resultingmissile classification is discussed in the followingparagraphs:

1) Weapon Control Panel Power Off Command -When missile power off is commanded by the WCPor CF-E commands, OAS will initiate erasure of themission data by overwriting all mission data 1000times. Since power will be removed after approxi-mately 12 seconds, OAS will not complete the over-writing procedure, but the mission data will be un-usable. The missile OFS is not affected by this pro-cedure and the missile will remain SECRET.

2) Classified Data Erase Command CF-555 - Whencommanded OAS will initiate erasure of the mis-sion data by overwriting all mission data 1000

times. After 180 seconds (3 minutes) erasure iscomplete and missile power will be removed. Themissile OFS is not affected by this procedure andthe missile will remain SECRET.

3) Weapon Erase Command CF-55F - When com-manded OAS will initiate erasure of the missiondata by overwriting all mission data 1000 times fol-lowed by erasure of the missile OFS. After 240 sec-onds (4 minutes) erasure will be complete and mis-sile power will be removed. The missile OFS iserased and the missile is UNCLASSIFIED.

NOTE

CF-55F will erase all data from the missile,including the missile Operational FlightSoftware (OFS). The missile must be re-moved from the aircraft in order for thesoftware to be reloaded. CF-55F will erasemissile data from any selected powered mis-sile, including when the aircraft is on theground.

MISSILE ELECTRICAL SYSTEM

Missile power is furnished from the aircraft prior toand during the early part of the launch countdown.Missile battery power is initiated during launchcountdown by squib activation and paralleled withcarrier aircraft electronic power for approximately 2seconds following battery activate command. Allmissile power is provided by the missile engine-driven generator after launch.

1 FIN2 ELEVON3 TEMPERATURE PROBE COV-

ER *4 WARHEAD ARMING DEVICE

SAFEING PIN5 WING5A HARD TARGET SMART FUZE

(HTSF) ACCESS PANEL(AGM-86D)

6 ENGINE EXHAUST NOZZLECOVER

7 FUZE WELL (BLOCK 1A)8 FUZE WELL (BLOCK 0A)9 PAYLOAD BAY COVER10 PITOT-STATIC PROBE

COVER*

*MUST BE REMOVED BY AIR-CREW

T.O. 1B-52H-34-2-9

Change 7 1-5

Figure 1-1. Missile General Arrangement

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1-6 Change 7

MISSILE GUIDANCE AND CONTROL SYSTEM

The navigation/guidance system consists of the in-ertial navigation element (INE), radar altimeterelement (RAE), flight control element (FCE), the airdata element (ADE), the global positioning system(GPS) element, and in AGM-86C and AGM-86Dmissiles a computer co-processor (GRIU/P). TheINE and GRIU/P co-processor provides a central-ized processing and control function for missileflight and weapon operation. The INE receives datafrom the OAS before launch and inputs from theRAE, FCE, ADE, and GPS after launch.

NOTE

Selection of alternate as the prime naviga-tion mode with one or both INSs operation-al will result in some data being transferredfrom the alternate nav model to the missileswhich may cause a degraded launch.

Inertial Navigation

The inertial navigation element (INE), working intandem with the GRIU/P co-processor in AGM-86Cand AGM-86D missiles, provides control of all mis-sile functions including navigation, guidance, auto-pilot, event sequencing, and warhead arming andfuzing. The INE consists of an inertial referenceunit (IRU), air vehicle digital computer unit(ADCU), and a power conditioning unit (PCU). TheINE is cooled by the aircraft environmental systemduring captive flight and the missile environmentalsystem after launch. The IRU is an inertially stabi-lized platform that provides the ADCU with missileattitude reference and acceleration data for naviga-tion computations. The ADCU within the INE andco-processor in AGM-86C and AGM-86D missiles,performs computations required for missile control,navigation, and operation.

Global Positioning System (GPS)

A GPS receiver is installed in the missile to aid theINE in navigation. The GPS receiver is turned onat missile power application and begins its searchfor the GPS satellites after launch. The GPS is not

able to track the satellites until after launch due towing shielding of the GPS antenna prior to launch.The GPS provides position and velocity inputs tothe INE after the GPS begins tracking the satel-lites. The status of the GPS receiver cannot be mon-itored by the operator.

The AGM-86C and AGM-86D missiles have an anti-jam which significantly improves the missile resist-ance to GPS jamming.

Radar Altimeter

The missile uses a cruise missile radar altimeter(CMRA) for terrain following.

Air Data

The air data element (ADE) measures pitot pres-sure and static pressure, and provides this informa-tion to the INE.

MISSILE FLIGHT CONTROL SYSTEM

The flight control system consists of flight controlsystem electronics, the rate and acceleration sen-sors, and two elevon servos to maintain controlledflight.

MISSILE ENVIRONMENTAL CONTROL SYSTEM

The missile environmental control system main-tains temperatures within the missile and compo-nents. Prior to launch, cooling is provided for theinertial navigation element electronics by condi-tioned air from the aircraft.

MISSILE PROPULSION AND FUEL SYSTEM

An F107 WR 100 twin spool, turbofan engine is thepropulsion source for the missile. Engine start isaccomplished after launch by a start cartridge.

The missile fuel system is a sealed tank system us-ing JP-10 as the missile fuel. Low pressure bleedair is provided by the engine for the missile envi-ronmental control system and fuel tank pressuriza-tion.

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Change 11 1-6A

MISSILE ARMING SYSTEM

Warhead Arming Device (AGM-86C Missiles)

The Warhead Arm/Disarm Device (sheet 2, figure1-2) provides the control for the Warhead InterfaceUnit (WIU). A safeing pin (with streamer) is in-stalled in the Warhead Arm/Disarm Device duringground operation (see figure 1-1). Since external ac-cess to the safeing pin is provided, there is no needto remove panels or doors. An external window al-lows a visual check on the status of the WarheadArm/Disarm Device. Either an S for safe or an A forarmed will be seen in the window. If the WarheadArm/Disarm Device becomes armed during captivecarry an ordnance alarm (xy ORD ALARM) will bedisplayed as a Missile Master Fault. On the occur-rence of an ordnance alarm the OAS will send asafeing command to the Warhead Arm/Disarm De-vice and immediately power down the missile. SinceWarhead Prearm is not an operational function ofthe CALCM, execution of the OAS prearm functionresults in the setting of an OAS software switch tosatisfy the OAS launch requirements. Although theOAS provides for monitor and control of the safecircuits through the Warhead Arm/Disarm Device,the aircrew can not enable the Warhead Arm/Dis-arm Device; the missile computer performs thisfunction after launch. Sheet 2, figure 1-2 illustratesthe CALCM Fuzing Subsystem. At launch when theseparation switch closes, pulse load power is ap-plied to the missile computer. Closure of the separa-tion switch also completes the main bus circuitwhich provides main bus power from the generatorto the Warhead Arm/Disarm Device after enginestart. At the selected GPS Waypoint, the missilecomputer will issue an Arm Enable Commandwhich enables the Warhead Arm/Disarm Device. Ifthe selected GPS Waypoint is Waypoint 0, the mis-sile computer will delay 10 minutes before settingthe Arm Enable Command. The Arm 1 command isissued 1 second after the Arm Enable Command.After the Arm 1 command is issued, a time delaywithin the WIU prevents the application of fuzepower and the enabling of the Inertial/impact fuz-ing circuit for 35 seconds. The arm 1 command ap-plies power to the WIU and within 5 seconds (powerup time for the WIU) fuze power and turbine re-lease are applied to each fuze. Each fuze is manual-ly set to a 20 second arming delay time. The fuzingsystem is armed and ready to trigger within 25 sec-onds of the arm 1 command.

Warhead Arming Device (AGM-86D Missiles)

The Warhead Arm/Disarm Device (WAD) (sheet 3,figure 1-2) provides control and monitor interfacefor the Fuze Interface Unit (FIU). A safeing pin(with streamer) is installed in the WAD duringground operation (see figure 1-1). Since external ac-cess to the safeing pin is provided, there is no needto remove panels or doors. An external window al-lows a visual check on the status of the WAD. Ei-ther an S for safe or an A for armed will be seen inthe window. If the WAD becomes armed during cap-tive carry an ordnance alarm (xy ORD ALARM)will be displayed as a Missile Master Fault. On theoccurrence of an ordnance alarm the OAS will senda safeing command to the WAD and the FIU andimmediately power down the missile. Since War-head Prearm is not an operational function of theAGM-86D, execution of the OAS prearm functionresults in the setting of an OAS software switch tosatisfy the OAS launch requirements. Although theOAS provides for monitor and control of the safecircuits through the WAD, the aircrew can not en-able the WAD; the missile computer performs thisfunction after launch. Sheet 2 figure 1-2 illustratesthe AGM-86D Fuzing System. At launch when theseparation switch closes, pulse load power is ap-plied to the missile computer. Closure of the separa-tion switch also completes the main bus circuit thatprovides main load bus (MLB) from the generatorto the Warhead Arm/Disarm Device after enginestart. At the selected GPS way point, the inertialnavigation element (INE) will issue the Arm En-able Command that applies 28VDC Main Bus Pow-er to the Warhead Arm/Disarm Device and acti-vates the internal motor driven rotary switch. Oncethe motor driven rotary switch is in the armed posi-tion it enables several electrical output pathways.

The current monitor output voltage from the mis-sile generator is routed through a set of contacts inthe WAD that are interrupted by relay contacts inthe motor driven rotary switch controlled by theArm Enable signal. At the first arming waypointthe Arm enable signal is issued by the INE. Thisaction activates the motor driven rotary switch andallows the current monitor missile generator volt-age to be applied to the input of the FIU. The FIUwill use the frequency content of this signal to de-velop appropriate arming power for theFMU-159A/B Hard Target Smart Fuze (HTSF).

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1-6B Change 11

Application of the Arm 2 signal by the INE enablesa set of WAD relay contacts that allow MLB powerto be applied to the A3 ARM 2 and B3 ARM 2 out-puts of the WAD. The ARM 2 outputs from theWAD are used to provide 28VDC power to the fuzeinterface unit (FIU) and the hard target smartfuze’s serial data controller circuitry.

NOTE

The HTSF does not use 28VDC as armingpower. The HTSF requires a very specificsequence of events, not directly related tothe 28VDC power, to occur in order to arm.

Two serial interface standards are utilized for com-munications between the GRIU/P and the FIU andHTSF. The GRIU/P to FIU connection utilizes theEIA-485 serial interface standard (one differentialpair).

The GRIU/P to HTSF connection utilizes theEIA-422 serial interface standard (two differentialpairs). The WAD provides continuous, pass-throughelectrical connection between the GRIU/P to FIUand HTSF for these signal lines.

Impact Fuze (AGM-86C Missiles)

An impact fuze provides both an alternate as wellas backup fuzing to the missile computer inertialfuzing. The impact fuze is located in the nose of themissile and consists of three sensors connected tothe Warhead Arm/Disarm Device. The fuzing signaloccurs when the missile contacts the ground. Onimpact a fuze signal is generated in the WarheadArm/Disarm Device and input to the WIU whichprovides the Trigger signals to two warhead fuzes.The AGM-86C uses two FMU-139A/B fuzes.

Impact Fuze (AGM-86D Missiles)

The impact fuze is located in the nose of the missileand consists of three sensors connected to a signalconditioning circuit located inside the WarheadArm/Disarm (WAD) Device. For AGM-86D missileconfiguration the impact fuze is not connected tonor utilized by the hard target smart fuze in opera-tion. However, the impact fuze is left in circuit toprovide a needed load to the signal processing cir-cuitry in the WAD.

ARMING SEQUENCE, AGM-86D

The first arming waypoint is selected to be no closerthat 2 minutes from target impact. At this point theINE issues the Arm Enable signal. This signal en-ables Main Load Bus (MLB) power to the WAD andactivates the motor driven rotary switch internal tothe WAD. With the motor driven rotary switch en-gaged, the missile generator’s current monitor out-put voltage isapplied to the input of the FIU via theWAD.

The Arm 2 signal is issued by the INE to the WAD.The Arm 2 signal activates a set of relay contacts inthe WAD. Once activated 28VDC MLB power is ap-plied to the FIU and HTSF (FMU-159A/B).

The GRIU/P will pass the 24-bit arming word overthe EIA-485 serial data lines through the WAD andin to the FIU. The FIU reformats the 24-bit wordand passes it to the HTSF.

At this point the fuze has completed the commit toarm sequence and is ready for arming power to beapplied from the FIU. At a point approximately 1minute from the target, the GRIU/P will send a fi-nal arm command to the FIU that will then outputarming power to the HTSF. Within approximately10 to 20 seconds the HTSF is in the fully armedstate and awaiting target impact.

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Change 7 1-6C

AGM-86C MISSILE FUZING SYSTEM

Figure 1-2. CALCM Fuzing System (Sheet 1 of 2)

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1-6D Change 7

AGM-86D MISSILE FUZING SYSTEM

Figure 1-2. CALCM Fuzing System (Sheet 2 of 2)

All data on pages 1-6E and 1-6F (Deleted)

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Change 1 1-7

AIRCRAFT COMMON STRATEGIC ROTARYLAUNCHER SYSTEM

The Common Strategic Rotary Launcher (CSRL)(figure 1-3), attached to the tank deck structure inthe bomb bay, is capable of carrying eight missileson MAU-12 ejector racks. A missile interface unit(MIU) and a relay assembly are also installed onthe CSRL. A power drive unit on the forward yokeassembly provides launcher drive. Aircraft rightand left body hydraulic lines are connected to thelauncher hydraulic system. Either the left bodylauncher hydraulic pump power or the right bodyhydraulic system may be selected by the pilot forrotation of the launcher (figure 1-4). A brake is in-corporated with the power drive unit to maintainthe launcher in a selected position and to preventrotation with a low hydraulic pressure condition.Rotation is OAS controlled by the PDUC. Thelauncher can be manually positioned by commandsfrom the weapon control panel. With the system inthe AUTO mode, the launcher will automaticallyrotate to the desired launch position for the currentlaunch point when the aircraft enters SAIR. Inmanual launch mode, the launcher will automati-cally rotate to place the selected missile in launchposition after the Manual Launch button is pressed.Primary rotation power for the launcher is providedby an electric motor-driven hydraulic pumpmounted on the LH bomb bay aircraft structure.Secondary rotation power is through a solenoid se-lector hydraulic valve located on the RH bomb bayaircraft structure. The MIU is mounted at the for-ward end of the rotary tube. For more informationon launcher hydraulic system, refer to T.O.1B-52H-1.

POWER DRIVE UNIT CONTROL (PDUC) POWERSWITCH

The PDUC power switch (figure 1-5), a two-positionswitch marked ON- -OFF, located on the RH equip-ment rack in the lower compartment, provides pow-er to the rotary launcher PDU. The PDUC circuitbreaker is also on the switch panel.

PDUC Power Application

If the CSRL PDUC power switch is in the ON posi-tion when OAS Master Power is applied, power willbe applied to the PDUC. Even though there is nosoftware status of the CSRL PDUC power switch,the PDUC is statused, so when OAS Master Poweris applied, if the PDUC does not respond, fault indi-cations will be displayed on FRMT-6. Upon powerapplication the PDUC will automatically perform

internal initializations for a maximum of five sec-onds. Any faults detected will be set by the PDUCat the completion of initialization and will be indi-cated on FRMT-6. In addition a PDUC MasterFault message will be displayed on the MFD andLNCHR will be displayed on FRMT-7.

NOTE

Launcher faults may occur if the PDUC ispowered on after the SMO is loaded. Manu-al rotation of the launcher may be requiredto clear the faults and allow automaticlauncher rotation capability.

PYLONS

The pylons (figure 1-6) attach to pylon adapters onthe underside of each wing between the fuselageand the inboard engine pods. The pylon providessupporting structure and wing interface for sixMAU-12 ejector racks, three forward and three aft.Internal cables route power and signals betweenthe missile interface unit (MIU), relay assembly, sixejector racks, and six missile station umbilical con-nectors. An environmental air ducting system dis-tributes conditioned air to and from the pylon MIUand to each of six missile stations. The pylons canbe jettisoned separately or simultaneously, with orwithout missiles attached using the pylon jettisoncontrol switches on the pilot’s overhead panel.

LOCK-UNLOCK CONTROL

Lock and unlock control of the MAU-12 ejectorracks is accomplished by use of the pilot’s consentpanel LOCK-UNLOCK and WCP LOCK-UNLOCKswitches. Ejector unlock power is provided from the28 volt dc missile essential bus. When the ordnanceenable relay is energized, ejector unlock power isrouted through the switching units to each missileejector. When the unlock command is received fromthe avionics control unit (ACU), the MIU sendsejector unlock power to the missile ejector.

MAU-12 EJECTOR RACK

A MAU-12 ejector rack is installed at each missilestation for suspension and ejection of a missile. Theelectrical connector carries control and monitoringsignals to and from the rack. Rack unlock and arm-ing is performed by application of 28 volt dc to therack solenoids. The rack has provisions for installa-tion of a ground safeing pin. At the pylon ejectors,an access cover must be removed from the fairing togain access to the ground safety pin hole.

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1-8

1 LAUNCHER MIU2 EJECTOR RACK3 GROUND

OPERATION SAFETY SWITCHPIN

Figure 1-3. Launcher Configuration

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Change 1 1-9

Figure 1-4. Launcher Hydraulic System

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1-10

NO.CONTROL-INDICATOR FUNCTION

1 PDUC Power Switch The PDUC power switch, a two-position switch marked ON- -OFF pro-vides power to the rotary launcher PDUC. The PDUC circuit breaker isalso on the switch panel. In the ON position, the PDUC allows rotation ofthe CSRL on either the launcher hydraulic system or the RH BODY hy-draulic system, as applicable. In the OFF position, the CSRL will not ro-tate. Since there is no software status of the CSRL PDUC power switch,it is assumed power will be available when OAS Master Power is applied.If the PDUC does not respond, fault indications will be displayed onFRMT-6.

NOTE

Launcher faults may occur if the PDUC is powered on after theSMO is loaded. Manually commanded rotation of the launchermay be required to clear the faults and allow automatic launcherrotation capability.

Figure 1-5. PDUC Power Switch

A65467

GROUND SAFETYLOCKPIN HOLE

SWAYBRACES(4)

ELECTRICALRECEPTACLE

30 IN. HOOK

EJECTORFOOT

SENSING SWITCHPLUNGER

CARTRIDGERETAINERS

IN FLIGHT SAFETYLOCKOUT BOLT

CENTERARMINGSOLENOID

EJECTORFOOT

30 IN. HOOK

2

1

MAU 12

3

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1-11

1 D DOOR (6)2 PYLON EJECTOR ACCESS DOOR (6)3 MAU-12 EJECTOR RACK (6)

Figure 1-6. Pylon Configuration

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1-12 Change 7

MAU-12 ELECTRO-EXPLOSIVE DEVICE (EED) POWER

EED power is internally routed to an ordnance en-able relay in the power distribution box (PDB). Therelay contacts are closed when both pilot and navi-gator have issued an unlock command and the AIUhas issued the critical power-on signal. EED powerdistribution from the MIU is controlled by the AIUfor launch and jettison.

AIRCRAFT ELECTRICAL SYSTEM

Primary system power is 400 Hz ac furnished fromengines No. 1, 3, 5, and 7 generator power boxes.Power is distributed from buses in the main genera-tor power boxes (forward wheel well) and from thesecondary buses located in the aircraft. Aircraft dcpower is furnished primarily for system control.Aircraft power is removed from the missile duringlaunch countdown after missile battery power isswitched to the missile circuitry. The OAS No. 1and 2 circuit breakers located on the right forwardBNS circuit breaker panel (figure 1-7) are thesource for control power for the OAS and missilesystems. Essential power, fill-in power for criticalavionics and missile navigation functions, pylonsand ejectors unlock power, and power for electro-ex-plosive devices are distributed from the power dis-tribution box in the forward wheel well. Figure 1-8lists related circuit breakers and their locations.

AIRCRAFT ENVIRONMENTAL CONTROLSYSTEM (ECS/MCS)

The aircraft environmental control system suppliesconditioned air to the missiles through the missileconditioning subsystem (MCS) which ensures mis-sile temperature is maintained within a normal op-erating range. The system will operate when Mis-sile Interface Unit (MIU) power is applied and thecabin air conditioning system is on. The system iscomposed of two distinct circuits. The temperaturecontrol circuit consists of a heat exchanger, hot andcold air modulating valves, ECS/MCS temperaturecontroller, missile circuit temperature sensor, andram air inlet temperature sensor. The missile aircircuit consists of a fan, fan differential pressureswitch, pressure regulator, missile overtemperatureswitch, two wing leading edge bypass valves, andfour pylon breakaway valves. Both circuits containducting for routing air and wiring required for oper-ation and control of the system. The missile circuitfan circulates conditioned air through a closed loopto the wing and bomb bay missiles. The air is cooledor heated to the desired temperature as it flowsthrough the heat exchanger core. The missile cir-cuit air temperature is monitored by a sensor in-

stalled in the heat exchanger outlet duct. Ambienttemperature is sensed by the ram air inlet tempera-ture sensor. These signals allow the controller to de-termine the three modes of operation for the MCSsystem: warmup mode, normal heating mode, andnormal cooling mode.

The MCS controller adjusts airflow through the hotor cold air modulating valves to provide the re-quired missile supply air temperatures. The rightwing ram airscoop provides cooling air to the mis-sile dc power supplies installed in a rack immedi-ately aft of the heat exchanger. Self-sealing valvesat the pylon interface assure conditioned air is notlost into the atmosphere after the pylon is jetti-soned or when no pylon is installed. After pylonseparation or when no pylons are installed, theleading edge bypass valves open allowing supply airto return to complete the cooling loop. Proper opera-tion of the missile environmental control system iscontinuously monitored. Improper operation of thesystem is indicated when a reverse video environ-mental control unit (ECU) appears on the MFD.Fan failure, as sensed by the fan differential pres-sure switch, missile circuit air temperature above140°F or below 46°F, missile circuit temperaturesensor failure, or ram air inlet temperature sensorfailure will generate this display. Also, an overheatcondition, as sensed by the missile circuit overtem-perature switch, will cause the fan to shut downand result in a fault indication on the MFD. TheECS/MCS controller incorporates a built-in-test(BIT) feature which allows isolation of defectivecomponents. The system requires 28 volt dc for con-trol and 118/205 volt ac 400 Hz power for majorcomponent operation.

An ECU fault will not shutdown poweredMIUs and missiles. Therefore, consider-ation should be given to the potential ofMIU overheat conditions.

ANTI-ICING AND PRESSURIZATION

Anti-icing of the ram airscoop, located in the rightwing leading edge, is accomplished with bleed airsupplied by engines 3 and 4. Valve operating powerfor bleed air is from the RH AIR SCOOP ANTI-ICEcircuit breaker on the right forward dc power panel.A valve open relay is enabled from the pilot’sengine, nacelle and scoops anti-ice switch when thesquat switch relay contacts are closed. The anti-icevalve is closed by system pressure when electricalpower is removed.

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Change 10 1-13

PILOT’S CIRCUIT BREAKER PANEL (TYPICAL)

RIGHT FORWARD BNS CIRCUIT BREAKER PANEL (TYPICAL)

Figure 1-7. Circuit Breaker Panels (Sheet 1 of 3)

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1-14 Change 10

Less [AMI] LEFT FORWARD BNS CIRCUIT BREAKER PANEL (TYPICAL)

[AMI] LEFT FORWARD BNS CIRCUIT BREAKER PANEL (TYPICAL)


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Change 10 1-15

RIGHT S/V FILTER BOX CIRCUIT BREAKER PANEL


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1-16 Change 10

CIRCUIT

CIRCUITBREAKER

NOMENCLATUREAMPERERATING LOCATION TYPE FUNCTION

MISSILEJETTISON

JETTISONPOWER

15 Right fwd BNSoverhead CBpanel

DC Pilot’s jettisonswitch power

NORMALRELEASE


DC Ejector unlockconsent

JETTISONCONTROL


DC Jettison controlpower

WEAPONCONTROL PANEL

2.5 Right S/V filter boxCB panel

DC Weapon controlpanel power

ARMAMENTINTERFACE UNIT

2.5 Right S/V filter boxCB panel

DC Controls EED dis-tribution powerand WCP power

GAM-72 GEAR JETTI-SON & AGM-69A

5 Pilot’s CircuitBreaker Panel

DC Bomb Door LimitSafety Switchesfor jettison se-quence

PYLONJETTISON

WEAPONCONTROL PANEL

2.5 Left FWD BNSoverhead CBpanel

DC Pylon lock-unlockconsent power

WEAPONCONTROL PANEL

2 Right S/V filter boxCB panel

DC Weapon controlpanel power

LEFT PYLON JETTI-SONCONTROL

10 Pilot’s CB panel DC Left pylon jettisonpower

RIGHT PYLONJETTISONCONTROL

10 Pilot’s CB panel DC Right pylon jetti-son power

CSRL PDUC 2.5 Navigator’s sidepanel

DC PDUC control boxpower

ARMAMENTINTERFACE UNIT

2.5 Right S/V filler boxCB panel

DC Controls EED dis-tribution powerand WCP power

GAM-72 GEAR JETTI-SON & AGM-69A

5 Pilot’s CircuitBreaker Panel

DC Pylon Jettison

Figure 1-8. Circuit Protection

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Change 10 1-17

PART 2 - B-52 AVIONICS SYSTEM

OFFENSIVE AVIONICS SYSTEM (OAS)

The B-52 Offensive Avionics System (OAS) is acomputer controlled electronics system providingnearly automatic navigation and missile delivery byuse of computers programmed by Less [AMI] mag-netic tapes, [AMI] data transfer cartridges, con-taining the flight computer program and missiondata information. The OAS provides present posi-tion, speed, direction, pitch and roll data, accelera-tion, altitude, Planned Time of Arrival (PTA), andupdate and reference data to the missile for missilenavigation computations. For information on OASnavigation, refer to the applicable flight manual.Figure 1-9 shows the location of the CALCM re-lated controls at switches at the Pilots’ station.

OFFENSIVE AVIONICS SYSTEM (OAS) INTERFACE

Less [AMI] The B-52 Integrated ConventionalStores Management System (ICSMS) provides OAScontrol for release of CALCM weapons. The ICSMSoperational computer program consists of a GroundMaintenance Computer Program (GMCP) andFlight Computer Program (FCP). The GMCP is notdiscussed. The FCP consists of the flight manage-ment system (FMS) and stores management over-lay (SMO). The CALCM SMO is used for CALCMpower application, alignment, targeting, andlaunch functions.

Less [AMI] The CALCM SMO software controlsCALCM weapon functions. The Navigation andWeapon Delivery (NAWD) ACU executes the navi-gation and weapon delivery functions for the SMO.The Controls and Displays (CAD) ACU executes thecontrols and displays function along with a majorityof the BIT (Built In Test) processing.

[AMI] The B-52 OAS provides control for program-ming and release of CALCM. The operational com-puter program consists of a Ground MaintenanceComputer Program (GMCP) and Flight ComputerProgram (FCP). The GMCP is not discussed. TheFCP consists of the Flight Management System(FMS), Common Stores Processing (CSP), andCALCM Stores Management Overlay (CALCMSMO). For further information regarding OAS andbasic SMO functions, refer to T.O. 1B-52H-1-12.

[AMI] The OAS provides the capability for control-ling and monitoring more than one type of weaponsystem at a time. This is accomplished by the CSPand loading multiple weapon SMOs. Currently, onlythe JASSM SMO may be loaded with the CALCM

SMO. With the CALCM and JASSM SMOs loaded,MIU/WIU power, environmental conditioning andmonitor capabilities are available to all the CALCMand JASSM weapons. However, all other weaponfunctions are available only to those weapons con-trolled by the Primary SMO.

• [AMI] With CALCM designated as the Prima-ry SMO (CF-62x), all CALCM weapon functions areavailable. The CALCM can be powered, aligned,monitored, targeted, ranged, launched and jetti-soned.

• [AMI] If the CALCM SMO is not the PrimarySMO, only MIU power, heating and monitoringfunctions (FRMT 7A, 7B, 7C and 77) are availablefor the missiles.

OAS/WEAPON SYSTEM RELATED CONTROLS AND DISPLAYS

Operator controls and displays for weapon releasesystem control are located at the pilots’ and naviga-tors’ stations. The munitions consent panel is lo-cated at the pilots’ station. The WCP, OAS powercontrol panel, keyboards, MFD, and computer con-trol panel are located at the navigators’ station. Seefigure 1-10 for OAS/weapon data flow.

Pilot’s Munitions Consent Panel

The pilot’s munitions consent panel (figure 1-11)contains the PREARM-OFF and LOCK-UNLOCKswitches. The panel provides unlock consent forpowering the weapon ejectors. The PREARM func-tion of the pilot’s switch is not used with theCALCM SMO. The LOCK-UNLOCK switch isguarded in the LOCK position.

Weapon Control Panel

The Weapon Control Panel (WCP) (figure 1-12), lo-cated on the navigator’s front panel, provides con-trols for weapon power application, weapon powerremoval, weapon jettison, or weapon abort. TheWCP is also used to clear master faults and manu-ally rotate the CSRL launcher. The PYLON UN-LOCK and PA ENBL switches are not used or rec-ognized by the CALCM SMO.

LOCATION/STATION SELECTION

Weapons are selected with the LOCATION (LP, RP,and BAY) and STATION (1, 2, 3, 4, 5, 6, 7, 8, andALL) switches. The WCP PYLON location switchesare enabled only when the associated MIU is pow-ered and has completed startup and initialization.

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1-18 Change 10

The BAY location switch is enabled anytime theOAS is operational, although the launcher rotatecommand is the only command recognized when theBAY MIU is off. The WCP station switches are en-abled only when one or more locations have beenselected. If no location is selected when either theALL station switch or an individual station switchhas been selected, the advisory message LOCA-TION?? will be displayed on each MFD. If an inval-id location (not loaded with a CALCM) is selectedthe advisory X: LOCATION (X = L - Left Pylon, R-Right Pylon, or B - Bay) will be displayed on eachMFD. If an invalid station (7 or 8 at a pylon LOCA-TION) is selected, the advisory Less [AMI] STA-TION??, [AMI] CALCM STATION??, will be dis-played on each MFD.

Location and station selection is required for thefollowing commands:

• Power application.• Power removal.• Selective jettison.• Prearm (Ready-To-Launch).• Safe.• Launcher Rotation (bay only).• Mission data erase.• Manual targeting.• Direct targeting.• Telemetry power ON.• Telemetry power OFF.• Telemetry power transfer.• Weapon erase.

Launcher rotation, manual targeting, direct target-ing and telemetry commands require that only onelocation and station is selected.

Once a weapon command is entered, the locationswitch(es) will be extinguished.

EJECTOR UNLOCK CONSENT

Ejector unlock consent is provided using the WCPNUCLEAR UNLOCK - LOCK switch figure 1-12 andthe pilot’s unlock consent switch (UNLOCK - LOCK)on the Pilots Munitions Consent Panel, figure 1-11.Both of these switches are required to be in the UN-LOCK position to allow weapon release from the air-craft via either a launch or jettison. If either the WCPunlock consent switch or the pilot’s unlock consentswitch are not in the UNLOCK position, Electro-Ex-plosive Device (EED) power will not be available atthe ejectors and ejector squib fire cannot be accompli-shed. When the WCP unlock consent switch and thepilot’s unlock consent switch are in opposite positions(one UNLOCK and one LOCK) the release consentmaster fault UNLOCK CONSENT is displayed oneach MFD. If the switches are then placed in the sameposition while the fault is displayed, the master fault

will be removed automatically. The fault can also beacknowledged by the Navigator/Radar Navigator bypressing the master fault acknowledge switch, MSTRFAULT, on the WCP.

If automatic or manual launch is commanded whenejector unlock enables are not present, the advisorymessage Less [AMI] LCD ENTRY INHB, [AMI]CALCM LCD ENTRY will be displayed on each MFD.

WEAPON POWER CONTROL COMMAND

The weapon power switch is used by the SMO, inconjunction with the location and station switchesto command CALCM missile power ON and OFF toselected CALCMs. The weapon power switch is en-abled only when one or more stations are selected.If the weapon power switch is momentarily placedin the OFF position, the SMO will remove powerfrom the selected CALCM(s) which are not inlaunch countdown. If the weapon power switch ismomentarily placed in the ON position, while thecarrier is providing valid inertial navigation data,the SMO will apply power to the selectedCALCM(s) for which power is not inhibited. Whenreleased, the weapon power switch returns to theneutral position. A power command will be pro-cessed only for the selected stations and then onlyfor those stations where a CALCM is present.

Since an ALCM has the same umbilical as a CALCM,the primary means to prevent the control of an ALCMby the CALCM SMO is through detection of a commu-nication failure when the ALCM fails to recognize theCALCM critical data request control word sent by theCALCM SMO during weapon power ON. The SMOwill declare a transient fatal fault for this condition.

The advisory message Less [AMI] LOC/STA??,[AMI] CALCM LOC/STA??, will be displayed whenweapon power is commanded ON or OFF if any ofthe following conditions are true.

• No location/station is selected on the WCP.• Individual stations are selected on a pylon or

launcher and both the ejector and umbilical statusat one or more of those stations show that aCALCM is not present or for a weapon commandedOFF and is in launch countdown.

• All stations on a pylon or launcher are selectedusing the ALL switch and both the ejector and umbili-cal status at all stations show that no CALCMs arepresent at those locations or for a weapon commandedOFF the only CALCM present is in launch count-down. If all stations are selected and if one or moreCALCMs are present on a selected pylon or launcher,the command will be processed only for thoseCALCMs that are present and not in launch count-down. No advisory message will be displayed unlessthere are no CALCMs at another selected location.

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Change 10 1-19

If the desired warm-up time for a CALCM has notelapsed since heater power was applied and if warm-up override is not commanded with a CF-55E com-mand, the advisory message Less [AMI] WARMUP/GYRO WAIT, [AMI] CALCM WARMUP, will be dis-played on each MFD when a command to apply powerto that station is entered.

Power is inhibited for CALCMs which have a per-manent fatal or safety critical fault. The advisorymessage(s) Less [AMI] WARMUP/GYRO WAIT,[AMI] CALCM GYRO WAIT, will be displayed oneach MFD when a command to apply power toCALCM(s) that have not had a fifteen second cooldown period since gyro spindown, or have not hadan eight minute cool down period since a shutdownwithout gyro spindown.

READY-TO-LAUNCH (RTL) COMMAND

The PREARM/SAFE switch is used to provide WCPcontrol of CALCM missiles to be launched. Whenmomentarily placed in the PREARM position forvalid selected location(s) and station(s) which havepower applied, the RTL status will indicate RDY onFRMT-7 and the weapon can be automatically ormanually launched when other launch prerequisiteconditions are satisfied. When the switch is momen-tarily placed in the SAFE position for valid selectedlocation(s) and station(s) which have power applied,or if no PREARM command has been given the RTLstatus will indicate SAF on FRMT-7 and weaponlaunch is inhibited. RTL is a prerequisite to launch.

The advisory message Less [AMI] LOC/STA??,[AMI] CALCM LOC/STA??, will be displayed whenRTL or Safe is commanded and any of the followingconditions are true.

• No location/station is selected on the WCP.• Individual stations are selected on a pylon or

launcher and at least one of the selected CALCMsis not powered ON.

• All stations on a pylon or launcher are selectedusing the ALL switch and no CALCM at that locationis powered ON. If all stations are selected and if oneor more CALCMs are powered ON on a selected pylonor launcher, the command will be processed only forthose CALCMs that are powered ON. No advisorymessage will be displayed unless there are noCALCMs powered ON at another selected location.

MISSILE LAUNCH MODE SELECT COMMAND

The LNCH MODE (AUTO - MAN) switch is used toselect between the automatic or manual launchmodes. When a weapon is in launch countdownchanging a weapon from automatic to manuallaunch mode will cause the weapon to enter alaunch countdown hold. This command may be en-

tered any time direct launch mode is not active andthe command is not weapon dependent. The se-lected launch mode will be illuminated on theswitch. SMO Processing will cause the launch modeto change from automatic to manual if a bay weap-on is hung during a launch or jettison. The launchmode can be returned to automatic by use of thelaunch mode select switch, if this occurs.

MANUAL LAUNCH COMMAND

The MAN LNCH switch is used to initiate launch ofa CALCM missile from the pylon or launcher asso-ciated with the current cruise missile launch pointwhen in manual launch mode. It is also used tolaunch a Direct Targeted CALCM when PRGM-Dn(n) is active. A bay manual launch can be se-lected regardless of where the launcher position is,but LCD will not start until the weapon is withinone position of down. In manual launch mode, entryof a manual launch command will cause a CALCMassociated with the next weapon event to enterlaunch countdown if the launch prerequisite condi-tions discussed in Section VII under MISSILELAUNCH have been met.

The switch light will be illuminated when thelaunch command is accepted and extinguished atthe completion of the launch sequence or if manuallaunch is deselected. If the manual launch switch isdepressed while it is illuminated (i.e. a manuallaunch has already been initiated), manual launchis deselected and the light will extinguish. If LCDhas not started when this occurs, no launch is initi-ated. If LCD has started when this occurs, a LCDhold occurs which lasts until the manual launchswitch is pressed again or the hold timer expires. Ifthe CALCM associated with the next weapon eventis not ready to be launched when the launch switchis momentarily depressed, the switch input will beignored.

If either the WCP unlock consent switch or the pi-lot’s missile consent switch are not in the UNLOCKposition when launch is commanded, the ejector un-lock enables will not be present, so the commandwill not be processed and the advisory messageLess [AMI] LCD ENTRY INHB, [AMI] CALCMLCD ENTRY, will be displayed on each MFD.

The advisory message Less [AMI] LOC/STA??,[AMI] CALCM LOC/STA??, will be displayed whenmanual launch is commanded and the followingconditions are true.

• The current destination is not a cruise missilelaunch point or there are no CALCMs associatedwith the cruise missile launch point.

• PRGM-Dnn is not entered to select a directtargeted weapon.

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1-20 Change 10

LAUNCHER ROTATE COMMAND

The WCP LCHR ROTATE switch commands rota-tion of the launcher to the currently selected weap-on in the bay. In order to use this command, thelaunch mode must be manual, only one station inthe bay must be selected, and the launcher cannotbe carrying out a previously commanded launcherrotate command. The LCHR ROTATE switch willremain illuminated until the launcher has stoppedrotating.

The command will be ignored if not in manuallaunch mode or if the launcher is carrying out apreviously commanded launcher rotate command.Launcher rotation commanded by a launch or jetti-son command takes precedence over a manual rota-tion request and it will be ignored.

WEAPON CONTROL PANEL ABNORMAL PROCEDURES

An advisory WCP on the MFD indicates malfunc-tion on the WCP. The operator will use CF-E (figure1-31) to back up actions accomplished on the WCP.This will allow the operator to work around certainfailures of the WCP and OAS power control panel.

NOTE

With a total WCP failure prior to accom-plishing hardwired functions, weapon re-lease is not possible.

CF-E may be used in conjunction with an opera-tional WCP and OAS power panel to operate thesystem. The operators may use keyboard entries toperform functions mechanized on these panels atany time regardless of the panels go/no-go status.The OAS will treat the keyboard command as if ithad originated from the WCP or OAS power panel.The lock-unlock function is not available on theCF-E backup. The display is laid out in basicallythe same arrangement as the panel. To accomplisha backup action for the malfunctioning panelswitch, the operator enters CF-E and the symbolsassociated with the switch on the keyboard in thesame sequence that normal switch operation wouldoccur. See CF-E this section for further discussionof the CF-E functions.

Bomb Tone Scoring Switch

The SMO controls the Bomb Tone Scoring cutoff atweapon release (launch) for each powered onCALCM. The Bomb Tone Scoring master switch,figure 1-13 is located at the Radar Navigator’s sta-tion and begins TONE operation when the switch ismomentarily placed in the INITIATE position. The

Bomb Tone Scoring master switch can also be usedto end TONE operation by momentarily placing theswitch in the CUTOFF position. The Bomb ToneScoring master switch must be used to initiate thetone prior to each launch or the cutoff commandfrom the SMO will be ignored.

OAS Power Control Panel

The OAS power control panel (figure 1-14) locatedon the navigators’ front panel provides power con-trol for the OAS and the MIU (Missile InterfaceUnit). All legends are backlighted green whenpower is on. The MIU switches which commandpower to the MIU are alternate action pushbuttonsand will remain latched if the MIU loses power or isshut down by the OAS. The light in the switch issoftware controlled and will go out when MIUpower is removed regardless of switch position. Toreapply power to the MIU when they have beenshut down by other than the operator, the switchmust be pressed and released to reset the switchand then pressed a second time to reapply MIUpower.

Keyboard

The keyboards (figure 1-15) located at the naviga-tor’s and radar navigator’s stations, provide inter-face with the control of the OAS and weapon sys-tem. The keyboard and MFD provide operator in-terface with the weapons through the selection offormat (FRMT), control function (CF), program(PRGM), and modify (MDFY) commands. The selec-tion of FRMT results in the display of a specificOAS and weapon data presentation on the selectedMFD. Control function selection results in displayof a specific OAS data display or initiates the entryinto a specific operating mode. If WCP switchesmalfunction, the navigator or radar navigator canselect CF-E which provides a display of the WCPswitches and the MIU power switches.

MULTIFUNCTION DISPLAYS

The multifunction display (MFD) (figure 1-16) is aCRT display unit. The MFD displays scan con-verted radar video, electro-optical viewing system(EVS) video, and alphanumeric mission data. TwoMFDs are located at the navigator’s station and twoat the radar navigator’s station.

MFD DISPLAY FIGURES

In the MFD display figures in this T.O., the itemsmodifiable by the operator or the SMO are repre-sented in the display explanations as lower case(non-capital) letters. The labels which are not modi-fiable are presented in all capital letters.

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1-21

1 MUNITIONS CONSENT PANEL2 BOMB BAY AND MISSILE JETTISON CONTROL

PANEL

3 PYLON JETTISON CONTROL PANEL4 PYLON JETTISON CONSENT PANEL5 PILOT CIRCUIT BREAKER PANEL

Figure 1-9. Pilot’s Station CALCM Related Controls and Switches (Typical)

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1-22 Change 10

Figure 1-10. OAS/Missile Data Flow

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1-23

PILOT’S LEFT SIDE PANEL

Figure 1-11. Pilot’s Munitions Consent Panel

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1-24

NAVIGATOR’S FRONT PANEL

NO. CONTROL/INDICATOR FUNCTION

1 WEAPON JETTISONSELECT (SEL) Switch

Spring-loaded to NORM (off) position. Used with unlock consent from pilot’smissile consent panel and WCP nuclear lock-unlock switch.

SEL - Jettisons missiles selected on location and station switches.

2 NUCLEAR PREARM SAFESwitch

Three position, spring-loaded to neutral (N).

PREARM - When momentarily placed to PREARM, changes the status of themissiles selected by WCP location and station switches to Ready To Launch(RDY). SAFE - When momentarily placed to SAFE, with a LOCATION and STATIONselected, removes RDY status from the selected missiles.

Figure 1-12. Weapon Control Panel (Sheet 1 of 2)

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1-25


3 STATION Switches Used with location switches to select individual Bay missile stations (1through 8), pylon missile stations (1 through 6) or all (ALL) stations at theselected location for missile operational functions

4 WEAPON POWER (WPNPWR) Switch

Three position, spring-loaded to neutral (N).

ON - Commands power be applied to the missiles selected by the location andstation switches on the WCP.

OFF - Commands power be removed from the missiles selected by the WCP.

5 NUCLEAR CAUTION (NUCCAUTN) Light

Not used with the CALCM SMO.

6 MASTER FAULT (MSTRFAULT) Light

Indicates a fault has occurred and more information is available on the MFD.Pressing acknowledges receipt of message, turns light off, and erases mes-sage.

7 LAMP TEST Switch When pressed all panel lights will come on.

8 MISSILE MANUAL LAUNCHSwitch

Starts the missile launch countdown if SAIR exists. Light will remain on untilmissile has been launched.

9 MISSILE LAUNCH MODESwitch

Alternately selects automatic (AUTO) or manual (MAN) launch mode andturns on respective light. Light also indicates OAS selected launch mode. MANoverrides auto and enables manual launch switch.

10 LAUNCHER ROTATE (LCHRROTATE) Switch

Used in manual launch mode to position selected BAY missile in launch posi-tion. The light remains on until the missile is in the commanded position.

11 LOCATION Switches Used with station select switches to select missiles for missile operation functions

LP (Left Pylon) - selects left pylon missiles.

RP (Right Pylon) - selects right pylon missiles.

BAY (Bay) - selects bay missiles.

12 NUCLEAR PREARM ENABLE Switch

Not used with the CALCM SMO.

13 NUCLEAR LOCK-UNLOCKSwitch

Guarded two position switch used with pilot’s consent to lock and unlock mis-sile ejectors.

14 PYLON LOCK-UNLOCKSwitch

Guarded two position lever lock switch gives consent to jettison missile pylons.

Figure 1-12. Weapon Control Panel (Sheet 2 of 2)

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1-26

BOMB TONE SCORING PANEL


1 Bomb TONE ON Light A tone-on indicator light located on the bomb tone scoring panel is illumi-nated when the bomb tone scoring system has been energized.

2 Bomb Tone Scoring Switch The switch provides a means of energizing the bomb tone scoring systemand has INITIATE- -NORMAL- -CUTOFF positions The switch is spring-loaded to the unmarked NORMAL position. Actuating this switch momen-tarily to INITIATE position will energize the circuit, causing the tone-on in-dicator light to illuminate and both UHF radio sets to transmit a steadytone provided both UHF radio sets are turned on. Actuating this switchmomentarily to CUTOFF position will deenergize the circuit, causing thebomb tone indicator light to go out and the tone transmission to stop.

Figure 1-13. Bomb Tone Scoring Panel

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1-27

NAVIGATOR’S FRONT PANEL


1 LAMP TEST Switch Tests all lights on the Power Control Panel.

2 MISSILE INTERFACE UNITSwitches

MIU/LP - Commands power to the left pylon missile interface unit and missile heaters.

MIU/BAY - Commands power to the bay missile interface unit and missile heaters

MIU/RP - Commands power to the right pylon missile interface unit and missile heaters.

NOTE

• There is a delay of up to 15 seconds for an ON indication changefollowing power application/removal commanded by the operator.

• If MIU power is lost or removed by OAS, the MIU power switchwill not automatically reset, and therefore must be pushed andreleased once to reset the switch manually, then pressed a sec-ond time to reapply power to the MIU.

• The MIU power off sequence requires 15 seconds to allow mis-siles to power down and an additional 5 seconds for the MIU topower off before power is actually removed from the MIU and thelight indication goes out.

3 MASTER POWER Switch ON (light on) sends master power to:• OAS• Weapon Control Panel• Armament Interface Unit (AIU)• Electro-Explosive Device (EED) power after MIU power is ON. • Ejector Unlock power• Enable MIU Power switches• Enable missile power

For all other functions, refer to the applicable flight manual.

Figure 1-14. OAS Power Control Panel

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1-28 Change 6

MISSILE RELATED KEYS AND SWITCHES


1 0 - 9 Keys Enter the respective number in the data/command to be transferred. Whenused in conjunction with upper corner key, gives N, S, E, W, +, -, and comma(,).

2 ENTER Key Completes the operator sequence. When pressed, data/commands will betransferred to OAS and displayed on MFD.

3 Message (MSG) Switch Acknowledges an existing message after being displayed on all four MFDs.

4 Crosshair On Target Key Used to designate the crosshair position.

5 A - F Keys Enter respective letter in data/command to be transferred.

6 Return (RTN) Key Places the MFD cursor to the first operator-changeable position in the row des-ignated.

7 Backspace (←) and Advance(→) Keys

Keys move the cursor on the MFD to the left and right respectively.

8 Upper Corner (UC) Key When pressed, the number keys enter the symbols in the upper left corner ofthe key.

9 Display Select Keys (4) PRGM displays current event program or selected event program.

CF displays OAS mode supervision menu or initiates entry into specific OASmode.

MDFY initiates operator changes to MFD displayed data.

FRMT displays video and/or data

10 L MFD and R MFD SelectionSwitches

Select either MFD for display of data inputs from the keyboard

Figure 1-15. Integrated Keyboard (IKB)

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1-29

TYPICAL MFD RADAR NAVIGATOR’S AND NAVIGATOR’S FRONT PANELS

CRITICAL DESIGNATION/LAUNCH EVENT DATAOR

OAS SUPERVISORY MENUS, MISSION DATA TABLES,AND WEAPON/PME STATUS

OAS ADVISORY DATA AREA

KEYBOARD DATA INPUTSMASTER FAULT MESSAGES NUCLEAR CAUTION MESSAGE PME FAULT MESSAGES

QUESTIONS REQUIRING YES - NO RESPONSEOAS ADVISORY MESSAGES AND SELECTED WEAPON STATION STATUS

PRIME MISSION DATA (PMD)

GENERAL DISPLAY ARRANGEMENT

Figure 1-16. Multifunction Display

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1-30 Change 11

MISSILE JETTISON

[AMI] The crew can command the SMO to jettisonMIU controlled weapons at locations controlled bythe SMO, when the SMO is primary and the MIUsat the selected locations are on.

MISSILE JETTISON SWITCH

Missile jettison is accomplished using the naviga-tor’s weapon jettison select switch on the WCP orthe pilots’ Bomb Bay & Missile jettison controlswitch (figure 1-17). The WCP jettison switch al-lows the navigator to selectively jettison one ormore missiles by selecting the location and stationswitches on the WCP. Pressing the pilots’ Bomb Bay& Missile jettison control switch jettisons all weap-ons Less [AMI] on the aircraft, [AMI] controlled bythe primary SMO. In order to jettison CALCMs,OAS must be operating, the respective MIU mustbe powered, and, for CSRL missiles, PDUC powermust be applied. The missile jettison system is il-lustrated in figure 1-18.

• The pilots’ Bomb Bay & Missile JettisonControl switch jettisons all GWD and ac-tive/primary SMO controlled weaponsloaded on the aircraft and will only be usedas a backup to jettison by the Radar Navi-gator. If jettison is commanded using the pi-lots’ Bomb Bay & Missile Jettison Controlswitch, all GWD weapons and, with OASoperating and MIUs/WIUs powered, all ac-tive/primary SMO controlled weapons willbe jettisoned. Proper separation clearancebetween weapons and between weaponsand aircraft cannot be ensured.

• The radar navigator’s Bomb Bay Jettisonswitch is excluded from operation with theCALCM SMO, however, a malfunction inthe jettison system could enable the switch,making it function in the same manner asthe pilots’ Bomb Bay & Missile jettisonswitch.

• Selectively jettisoning pylon missiles usingthe Pilots’ Bomb Bay & Missile JettisonControl switch, while attempting to retaininternal CSRL weapons by pulling BombDoor Control Valve circuit breakers is notauthorized. If jettison is attempted in thisfashion, the jettison command will remain

in the OAS even until all statused weaponshave been jettisoned. Resetting the BombDoor Control Valve circuit breakers willcause the bomb bay doors to open, whichwill complete the jettison sequence causingall internal CSRL weapons to be jettisoned.Once selective jettison is commanded usingthe pilots’ switch, the only way to clear theresident jettison command from the OASwithout jettisoning the weapons is by shut-ing down OAS (CF-67).

• Jettison of missiles from the aft inboard py-lon stations is inhibited if bomb doors arenot closed and latched.

• The CALCM SMO has no interlocks pre-venting jettison on the ground. With unlockconsent, and power applied to the OAS andthe WIU, actuation of jettison switcheswhile on the ground will result in weaponjettison.

NOTE

• With a total WCP failure prior to accom-plishing hardwired functions, missilelaunch or jettison, and pylon jettison is notpossible.

• If unlock enables are not present for theMIU from which the weapon is being jetti-soned, when jettison is commanded, theweapon will be powered down (if poweredon) for the associated MIU, and the masterfault NO UE will be displayed on eachMFD.

• If a multiple CALCM jettison is command-ed, some of the weapons may not have a jet-tison or hung release advisory displayed atthe bottom of the MFD. This is attributedto timing differences between the jettisonand the advisory display update rate.

• [AMI] If the primary SMO is not assignedto the selected jettison location(s) on theWCP when using the jettison select switch,or to all locations when using the pilots’Bomb Bay & Missile jettison control switch,an advisory message X: JETT INHIB is dis-played, where X is the location B, L, or Rfor bay, left pylon, or right pylon respective-ly. Select jettison location for which theSMO is primary or change the primarySMO for the desired locations and reaccom-plish.

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Change 11 1-31

NOTE

[AMI] BOMB BAY AND MISSILE JETTISON CONTROL switch jettisons all weapons controlled by the primary SMO.

Figure 1-17. Pilot’s Jettison Controls and Indicators

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1-32

Figure 1-18. Missile Jettison System

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Change 10 1-33

PYLON JETTISON

PYLON JETTISON CONTROL SWITCH

Pylon jettison is accomplished by using the pilot’spylon jettison control switches (figure 1-19) afterunlock consent is given and the release circuits dis-connect is connected. Unlock consent between thenavigator and pilot must exist by use of the naviga-tor’s pylon lock-unlock switch on the WCP, and thepilot’s pylon jettison consent panel switches. A bar-ber pole indication on the pylon locked indicatormeans the pylon is not locked. When the ready lighton the pilot’s pylon jettison control panel comes on,the pylon is ready for jettison. EED power for pylonjettison is supplied by the Noninterrupted DC(NDC) power supply. The NDC power supply ispowered any time at least one MIU is powered. Seefigure 1-20 for pylon jettison system.

Do not jettison pylon any time there aremissiles loaded unless the flight safety ofthe aircraft is in jeopardy.

Do not reposition the pylon jettison consentswitch(es) after the pylons have been jetti-soned. Damage to the pylon lock-unlock ac-tuator could occur.

NOTE

• Even though pylon(s) indicate unlocked(barber pole) and READY, pylon jettisonwill not occur unless EED power is avail-able from the NDC power supply. At leastone MIU must be powered in order for theNDC power supply to supply EED power.

• With total WCP failure prior to accomplish-ing hardwired functions, pylon jettison isimpossible.

RELEASE CIRCUITS DISCONNECT (RCD)

The release circuits disconnect (figure 1-19), whenconnected, completes the pylon jettison circuits. TheRCD is enclosed and has a transparent plexiglassprotective door. The plug and receptacle can be con-nected, or disconnected by pulling the T-handleafter the protective door has been opened.

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1-34

Figure 1-19. Pylon Jettison Controls and Indicators

T.O. 1B-52H-34-2-9


Figure 1-20. Pylon Jettison System

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Change 10 1-37

PART 3 - CALCM OAS SOFTWARE AND DISPLAYS

STORES MANAGEMENT OVERLAY (SMO)

The OAS controls the programming, targeting,alignment, and launch CALCMs using the flightcomputer program (FCP). The FCP consists of theflight management system (FMS), stores manage-ment overlay (SMO), and [AMI] Common StoresProcessing (CSP). The FMS controls navigation, ra-dar, controls and displays, and supports the Con-ventional Air Launched Cruise Missile (CALCM)SMO. The CALCM SMO contains all weapon con-trol and delivery functions required with CALCMs.[AMI] The CSP incorporates common stores/weap-on capabilities and provides multi-SMO operation.

The SMO menu can be displayed to allow the oper-ator to select the appropriate SMO. Up to 10 SMOscan be listed on control function CF-62, the SMOLoad Menu. Functions performed by the SMO in-clude weapon control processing, simulation pro-cessing, and controls and displays processing. Toperform its required functions, the SMO interfaceswith existing aircraft weapon system components,the OAS sources of navigation, steering, controlsand displays processing, mission data, and with theglobal positioning system (GPS) hardware.

SMO INITIALIZATION

Less [AMI] The SMO is automatically initializedand begins execution immediately upon beingloaded into the ACUs. The procedure for loadingthe SMO into the ACUs is equivalent to loading anyother ICSMS SMO. The SMO, if it exists on theOCP DTUC, is identified on the CF-62 Menu by thelabel CALCM followed by optional version informa-tion. The SMO is loaded by operator enteringCF-62,n, where n is the line number with theCALCM label. The advisory message SMO LOADCMPLT is displayed on each MFD followingcompletion of a SMO load.

[AMI] SMO load and primary SMO selection aredescribed in T.O. 1B-52H-1-12, Section 1, OffensiveAvionics System. SMO titles are selected from theSMO load menu (CF-62) and loaded by position (LP,BAY, RP). Selected SMOs appear at the top of theSMO Load Menu by position in blinking video whileloading. The SMO titles convert to normal videowhen loading is complete and appear as bright un-derlined video when selected as the primary SMO.

[AMI] With CALCM designated as the PrimarySMO (CF-62x), all CALCM weapon functions areavailable. The CALCM can be powered, aligned,monitored, targeted, ranged, launched and jetti-soned.

[AMI] If the CALCM SMO is not the PrimarySMO, only MIU power, heating and monitoringfunctions (FRMT-7A, 7B, 7C and 77) are availablefor the missiles.

[AMI] If the CALCM SMO is currently the PrimarySMO and will become a secondary SMO the selectionprocess will be inhibited if any process is active thatcan’t be accomplished in the secondary SMO mode.

In order to obtain an accurate Time of Launch Er-ror (TLE) for preplaned CALCM missions (directtargeted CALCMs use TLE of zero), the followingFMS data is needed:

• The Universal Time Coordinate (UTC).• The Planned Time of Arrival (PTA) Reference

for a designated destination.• The Planned Time of Arrival on FRMT-10 for

a designated destination.

Both values are input on the FMS Startup Menu(CF-61) display, with the inputs validated by theFMS. The UTC needs to be entered only once. How-ever, the PTA Reference for a designated destina-tion should be entered each time a B-52 mission isloaded and before the first launch at a launch point.(Updating the PTA reference for each launch pointis recommended.) The SMO does not need to beloaded prior to entering this data.

NOTE

• For proper missile mission timing, plannedmissile launch time must be entered intoCF-61, Line 3, PTA REF time.

• The hours field of the PTA Reference ac-cepts an input up to 48, allowing update ofplanned arrival times past midnight of thecurrent date.

SMO TERMINATION

SMO execution can be terminated in either of thefollowing Less [AMI] three ([AMI] two) ways.

Less [AMI] Another SMO can be loaded into theACUs, using CF-62,n a SMO load initialization pro-cess which terminates execution of and overwritesthe SMO. With this method, FMS will continue tobe executed. The SMO will inhibit the command toterminate execution if any MIU is powered ON. TheSMO will delay compliance with the SMO load re-quest until all outstanding SMO faults have beenrecorded and DTU Input/Output is complete (if anFDRC is installed).

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1-38 Change 11

Less [AMI] A CF-64 command will immediatelyhalt FMS and SMO processing and erase processormemory. The INSs, WCE and weapons will not bepowered off and can not be powered off until theFMS and SMO are reloaded.

[AMI] The operator can command the FMS to un-load the SMO as described in T.O. 1B-52H-1-12,Section 1, Offensive Avionics System. With thismethod, FMS will continue to be executed. TheSMO will delay compliance with the command toterminate execution until the SMO has removedpower from the WCE and all outstanding faultshave been recorded.

A CF-67 command can be entered by the operatorwhich halts execution of all software loaded into theACUs (FMS and any loaded SMO(s)). The SMO willdelay compliance with the shutdown request untilall outstanding SMO faults have been recorded andfor as long as it takes to power down all WCE thatis powered ON.

SMO RESTART

The method of restarting the SMO is dependentupon the method which terminated SMO execution.The three methods are described below.

If SMO execution was terminated by loading anotherSMO into the ACUs, the SMO must be reloaded intothe ACUs as described in SMO INITIALIZATION.

If SMO execution was terminated by enteringCF-67, the FMS and the SMO can be restarted bydepressing the PROC SYNC button on the CSCP, ifACU memory has not been erased.

If SMO execution was terminated by enteringCF-64 or CF-67 with a memory erase, there is noSMO restart capability without reloading the FMSand the SMO.

SMO RECONFIGURATION

Less [AMI] SMO capabilities and processes are af-fected when reconfiguration occurs (i.e. the Hot SpareACU takes over the functions of the CAD or NAWDACU). SMO operation is suspended until its functionscan be taken over by a new processor. The FMS showsreconfiguration has occurred by displaying advisorymessages indicating reconfiguration load status. TheFMS loads the SMO Reconfiguration Load first, thenthe FMS Reconfiguration Load from the load DTUC.The advisories displayed by the FMS for a successfulReconfiguration Load should be as follows:

• SMO RCNFG LDG• SMO RCNFG COMPLT• FMS RCNFG LDG• FMS RCNFG COMPLT

Less [AMI] All SMO functions are currently resi-dent in the Hot Spare ACU, so there is no SMO Re-configuration Load required as part of the reconfi-guration process, even though the FMS reports that

one occurred. However, some SMO functions mayrely on non-resident FMS functions and have towait for the FMS Reconfiguration Load to completebefore they can operate.

[AMI] SMO capabilities and processes are affectedwhen reconfiguration occurs (i.e. the secondaryACU takes over the functions of the primary ACU).SMO operation is suspended until its functions canbe taken over by the other processor. Some opera-tions will continue and some abort. The followingSMO processes are or may be affected by reconfi-guration:

• Flex targeting data modification aborts andhas to be restarted.

• Direct targeting data modification aborts andhas to be restarted.

• The missile launch process aborts and has tobe restarted.

• The store jettison process aborts and has to berestarted.

• Fuze data modification aborts and has to berestarted.

• MIU power application might abort and haveto be restarted.

• CALCM power application might abort andhave to be restarted.

• The manual targeting of a CALCM mightabort and have to be restarted.

• The flex targeting of a CALCM might abortand have to be restarted.

• The direct targeting of a CALCM might abortand have to be restarted.[AMI] All SMO displays remain on the MFD theywere on prior to reconfiguration although modifica-tion of data will be inhibited for the flex, direct, andfuze data input screens because all targeting pro-cesses are aborted. After reconfiguring, the SMOwill display the CALCM CLAPAR LD advisory.

If the condition and status of the data in the ACUsis in question after reconfiguration, it is recom-mended that the crew reload any, or all, of the fol-lowing:

• FMS• CALCM SMO• B-52 Mission

Controls and Displays (C&D) Commands

Reconfiguration aborts or interrupts various SMOprocesses, and therefore may require SMO C&D com-mands to be re-entered after reconfiguration occurs torestart them, or to ensure that SMO controlled condi-tions are set as desired. All SMO C&D commands con-tinue to function and are available for entry immedi-ately after a reconfiguration occurs. Less [AMI] Somecommands will wait until FMS RCNFG COMPLT isdisplayed before being carried out, or the commandmay have to wait to be issued until after FMS RCNFGCOMPLT is displayed.

T.O. 1B-52H-34-2-9

Change 10 1-39

OAS POWER CONTROL PANEL COMMANDS

Less [AMI] It is not necessary to wait for FMS Re-configuration Load to complete before using theswitches on the Power Control panel. If the MIU ispowering on when reconfiguration occurs, the pow-er on sequence aborts. The appropriate switchneeds to be set to the OUT position then set back tothe IN position to restart the MIU power-on processif this happens. If the MIU is already on, it shouldstay on.

NOTE

If the MIU is powering down when reconfi-guration occurs, it will immediately indicatethat it is off, as will any powered-on weap-ons for the MIU. It will be necessary to waitfor 8 minutes of gyro cool-down time priorto weapon power application for any weap-on powered down in this manner.

[AMI] It is necessary to wait for reconfiguration tocomplete before using the switches on the PCP. Ifthe MIU is powering on when reconfiguration oc-curs, and the power-on sequence aborts, then theappropriate switch needs to be set to the non-de-pressed position then set back to the depressedposition to restart the power-on process for thatlocation.

WEAPON CONTROL PANEL (WCP) COMMANDS

Less [AMI] It is not necessary to wait for FMS Re-configuration Load to complete before using theswitches on the WCP.

• Reconfiguration causes the launch mode to beset to manual. Auto launch mode can be selectedafterwards.

• Reconfiguration will abort launch, if in pro-gress. If a manual launch was in progress, themanual launch command will have to be reissuedusing the MAN LNCH switch. If an automaticlaunch was in progress, then launch can be contin-ued by reselecting automatic launch mode using thelaunch mode select switch.

• Reconfiguration clears all location/stationselections. They must be reselected.

• CALCMs in power-on sequence that have notstarted coarse alignment are powered off and re-quire reapplication of missile power. Since the mis-sile does not immediately initiate spindown, an 8minute cool down period is required before weaponpower application will be allowed.

• CALCMs in power off sequence (during MIUoff) when reconfiguration occurs will immediatelyindicate being off afterwards. Since a completespindown does not occur, an 8 minute cool-down pe-riod is required prior to weapon power application.The WPN PWR switch can be used to power weap-ons off, if desired, at any time after reconfigurationoccurs.

• The launcher rotation light remains as it wasprior to reconfiguration, and should be available foruse immediately after reconfiguration. A rotationcommanded prior to reconfiguration should contin-ue to the commanded position.

• The MSTR FAULT switch should be availableimmediately after reconfiguration occurs. Its lightwill be as it was prior to reconfiguration, unlessfaults are detected, in which case it will be illumi-nated.

• The NUCLEAR LOCK-UNLOCK switch posi-tion is not affected by reconfiguration.

• It is not necessary to wait for FMS Reconfi-guration Load to complete to use WPN JETTISONswitch. However, since reconfiguration aborts jetti-son, any weapons that did not jettison need to bereselected and the jettison switch toggled again.

[AMI] It is necessary to wait for reconfiguration tocomplete before using the switches on the WCP.

• Reconfiguration clears all Location/Stationselections. They must be reselected.

• If a Weapon Power On or Off request was in-progress when a reconfiguration occurred, the opera-tor must check via SMO MFD display(s) for the cur-rent weapon power status, to determine if a WeaponPower On or Off request needs to be reissued. If aCALCM powers down because of reconfiguration, thestore power control switch will need to be used to pow-er it back on. However, there may be an eight minutewait required to ensure gyro spindown has occurred.

• If a Weapon Prearm or Safe request was in-progress when a reconfiguration occurred, the oper-ator must check via SMO MFD display(s) for thecurrent weapon prearm/safe status, to determine ifa Prearm or Safe request needs to be reissued.

• If a Weapon Selective Jettison request was inprogress when a reconfiguration occurred, the oper-ator must check via SMO MFD display(s) for thecurrent weapon jettison status, to determine if aWeapon Selective Jettison request needs to be reis-sued. Since reconfiguration aborts the jettison pro-cess, the selected jettison switch or the switch onthe BMJCP may have to be pressed again to com-plete jettison.

• The Launcher Rotation light remains as it wasprior to reconfiguration, unless it was illuminatedand the SMO requests CSP to extinguish it (e.g. therotation was aborted due to reconfiguration).

• Reconfiguration causes the Launch Mode to beset to manual.

T.O. 1B-52H-34-2-9

1-40 Change 10

• The Manual Launch light remains as it wasprior to reconfiguration, unless it was illuminatedand the SMO requests CSP to extinguish it (e.g. thelaunch was aborted due to reconfiguration). Sincereconfiguration aborts the launch process, if it wasprior to ejector squib firing, the manual launchswitch or the launch mode switch must be pressedagain to complete launch.

• The Nuclear Unlock/Lock switch position isnot affected by reconfiguration. The Unlock Con-sent status remains as it was prior to reconfigura-tion.

• The Nuclear Prearm Enable/Off switch posi-tion is not affected by reconfiguration. The PrearmConsent status remains as it was prior to reconfi-guration.

• The Nuclear Caution switch remains as it wasprior to reconfiguration, unless it was extinguishedand nuclear caution messages were issued followingreconfiguration, then it will be illuminated.

• The Master Fault switch remains as it wasprior to reconfiguration, unless it was extinguishedand master fault messages were issued followingreconfiguration, then it will be illuminated.

PILOT’S MUNITIONS CONSENT PANEL COMMANDS (PMCP)

Less [AMI] It is not necessary to wait for FMS Re-configuration Load to complete before using theLOCK-UNLOCK switch on the Pilot’s MunitionsConsent Panel nor is its position affected by reconfi-guration.

[AMI] It is necessary to wait for reconfiguration tocomplete before using the switches on the Pilot’sMunitions Consent Panel. The Unlock Consentstatus remains as it was prior to reconfiguration,and the Prearm Consent status remains as it wasprior to reconfiguration.

PILOT’S BOMB BAY AND MISSILE JETTISONCONTROL (BMJCP) SWITCH COMMANDS

Less [AMI] It is not necessary to wait for FMS Re-configuration Load to complete before using the pi-lot’s bomb bay and missile jettison control switch.However, since reconfiguration aborts jettison, theswitch must be pressed again to complete jettison.

[AMI] It is necessary to wait for reconfiguration tocomplete before using the pilot’s bomb bay and mis-sile jettison control switch. If a Jettison All requestwas in progress when a reconfiguration occurred,the operator (navigator) must check via SMO MFDdisplay(s) for the current jettison status, to deter-

mine if a Jettison request needs to be reissued.Since reconfiguration aborts the jettison process,this switch on the BMJCP or the selected jettisonswitch on the WCP may have to be pressed again tocomplete jettison.

IKB COMMANDS

Less [AMI] It is not necessary to wait for FMS Re-configuration Load to complete before using theswitches on the IKB. Certain SMO commands mayneed to be re-issued if their processes were abortedby the reconfiguration and some may require FMSReconfiguration Load to complete. Unless listed be-low, all SMO IKB commands are available for useimmediately after reconfiguration occurs, subject totheir normal prerequisite conditions.

Less [AMI] All display requests should be availableimmediately after reconfiguration occurs.

• Reconfiguration aborts Flex Targeting and Di-rect Targeting data input. The command sequenceto continue the aborted targeting data input pro-cess must be reissued. However, the last data fieldentered on the Flex or Direct Targeting Input Dis-plays (MDFY-nn) may not be processed properly ifreconfiguration occurs shortly after entry. There-fore, it is advisable to re-enter that field againwhen resuming the Flex or Direct Targeting Datainput that was in progress when reconfiguration oc-curred.

Less [AMI] All weapon targeting commands shouldbe available:

• Immediately after CAD reconfiguration oc-curs.

• Immediately after FMS Reconfiguration Loadcompletes when NAWD reconfiguration occurs.

• Since Targeting aborts because of reconfigura-tion, Manual Targeting (CF-556,nn) and Send Tar-geting Data (CF-DD) commands may need to be re-issued to ensure they are properly carried out. Forthe Send Targeting Data (CF-DD) command to bereissued, the Flex or Direct Targeting it was associ-ated with must first be restarted.

• If the Target/Retarget All (CF-559) commandwas active before reconfiguration, it will pick upwhere it left off automatically once it establishesthat conditions are set to continue, or if desired, thecommand may be reissued to start targeting overagain.

• Although it is immediately available for use,the Exit Targeting Mode command (CF-DE) doesnot need to be used if Flex or Direct Targeting DataInput was active when reconfiguration occurred.

T.O. 1B-52H-34-2-9

Change 10 1-40A

[AMI] It is necessary to wait for reconfiguration tocomplete before using the switches on the IKB. AllCommand Menu display request commands, Sys-tem Status display request commands, and SystemControl commands should be available for use im-mediately after reconfiguration occurs. The opera-tional (Strike/Sim) mode and the ECU Override re-main as they were prior to reconfiguration. CertainCSP IKB commands may need to be reissued iftheir processes were aborted by the reconfiguration:

• If automatic targeting was actively targetinga CALCM when reconfiguration occurred, the retar-get all command need only be reissued if reconfi-guration somehow disrupted the assigning ofCALCMs to targets in the preferred launch se-quence. Otherwise, automatic targeting will startback up on its own.

• If manual targeting was active when reconfi-guration occurred, the manual targeting commandmay need to be reissued to ensure the CALCM istargeted correctly.

• If flex targeting data input was active, includ-ing the fuze data input screen when applicable,when reconfiguration occurred, the flex targetingcommand must be reissued to continue enteringflex targeting and/or fuze data.

• If direct targeting data input was active, in-cluding the fuze data input screen when applicable,when reconfiguration occurred, the direct targetingcommand must be reissued to continue entering di-rect targeting and/or fuze data.

• If flex or direct targeting data was being sentto a CALCM when reconfiguration occurred, the ap-propriate targeting command must be reissuedprior to reissuing the send targeting data commandto ensure the CALCM was targeted correctly.

MFD DISPLAYS

When reconfiguration occurs, some SMO functionsare affected and can cause data that is displayed onthe PCP, the WCP, and the MFDs to change. To as-certain the current conditions after a reconfigura-tion occurs the following displays should be re-viewed to verify settings and conditions are as de-sired.

Less [AMI] :

• Control Function (CF) menu• Weapon Supervision Menu (CF-5)• CALCM Supervision Menu (CF-55)• FCP Supervision Menu (CF-6)• PME Status Display (FRMT-6)• Status and Inventory Display (FRMT-7)• Launch Point Program Display (PRGM)

[AMI] :

• Control Function Menu (CF-) for the currentoperational (Strike/Sim) mode.

• Weapon Supervision Menu (CF-5) for the current operational (Strike/Sim) mode.

• FCP Supervision Menu (CF-6) for the currentECU Override status.

• PME Status Display (FRMT-6).• Stores Summary Display (FRMT-77).

The following displays may be reviewed if theywere being used prior to reconfiguration to verifysettings and conditions are as desired.

• WCP Backup Display (CF-E)• Flex Targeting Input screen (CF-557,nn)• Direct Targeting Input screen (CF-558,nn)

Less [AMI] FMS Reconfiguration Load Fails

If the FMS Reconfiguration Load did not occur afterthe NAWD fails, due to a bad load DTUC or theload DTUC is not having been mounted or selected,SMO targeting functions will be affected as follows:

• Auto targeting will cease to operate• Manual Targeting (CF-556,nn) will result in a

TGT XFER ABORT advisory for any weapon, re-gardless of whether it was previously targeted ornot

• Flex Targeting (CF-557,nn) and the ensuingCF-DD, Send Data command) will function onlywith those weapons that are already targeted toCALCM launch points

• Direct Targeting (CF-558,n(n) and the ensuingCF-DD, Send Data command) will function onlywith those weapons that are already targeted, orhave indicated they have received GPS Initializa-tion Data. Weapons that have indicated they havereceived GPS Initialization Data can only be DirectTargeted.

T.O. 1B-52H-34-2-9

1-40B Change 10

SMO MFD DISPLAYS

Displays can be requested on each MultifunctionDisplay (MFD) which contain SMO data and areused to interface with the operator for CALCM op-erations. Several of the displays are defined andupdated primarily by the FCP for which the SMOprovides additional data for display. Some of thedisplays are completely unique to SMO operationfor which the SMO provides all of the data. The fol-lowing displays are affected wholly or in part by theSMO:

• Release Advisory Display• CF Control Function• CF-5 Weapon Supervision Menu• CF-55 CALCM Supervision Menu• CF-557,nn Flex Target Input Display• CF-558,nn Direct Target Input Display for

Direct Target Dn• CF-6 FCP Supervision Menu• CF-61 FCP Initialization Display• CF-62 SMO Load Menu• CF-67 FCP Termination Display• CF-8 Mission Supervision Menu• CF-81 [AMI] Mission Data Load

Display• CF-82 [AMI] CALCM Group Selection

Menu• CF-DF Fuze Data Input Display when

entered from the Flex or DirectTarget Displays

• CF-DF or [AMI] CALCM Group AssignCF-DB ment Display when entered

from CALCM Status & Inventory Display

• CF-E Weapon Control Panel BackupDisplay

• FRMT- Format Menu• FRMT-1 Radar Display Data• FRMT-2 Radar Display Data with PMD• FRMT-4 EVS Display Data• FRMT-5 EVS Full Display Data• FRMT-6 PME Status Display• FRMT-7 CALCM Status and Inventory

Display• FRMT-7xy CALCM Status and Inventory

Display with Selected StationStatus

• FRMT-10 Destination Table Display• FRMT-10,nn Destination Table Display

for destination nn

• PRGM,nn CALCM Launch Point ProgramDisplay

• PRGM, Dnn CALCM Direct Target Program Display

RELEASE ADVISORY DISPLAY

When weapons are declared launched, jettisoned,aborted or hung, the Location/Station number andthe appropriate status of each affected weapon willbe shown as a Weapon Release advisory as indi-cated in figure 1-21. The Weapon Release Advisorydisplay will be shown on the bottom of the displayon all MFDs. There is no operator command tocause the Weapon Release advisory to be displayed.Once displayed, the data will remain on the MFDsfor approximately five seconds after the release orattempted release of the last weapon in thesequence. The Weapon Release Advisory is also dis-played when an abort to one or more weaponsoccurs.

NOTE

If a multiple weapon jettison is commanded,some of the weapons may not have a jetti-son or hung release advisory displayed.This is attributed to timing differences be-tween the jettison and the advisory displayupdate rate.

PRIME MISSION DATA

Less [AMI] The prime mission data is displayedanytime a MFD is displaying CF-61, CF-67, CF-E,FRMT-2, FRMT-4, FRMT-5, FRMT-6, FRMT-8,FRMT-9, FRMT-10, or a PRGM display.

[AMI] Prime mission data (PMD) displays aircraftlocation, flight parameters, and mission parametersto monitor mission performance. Either Full or Par-tial PMD is displayed at the top of most MFDs. SeeT.O. 1B-52H-1-12 for a further description of PMD.The SMO produces a one line PMD when FRMT-7is entered. The one line PMD only displays time-to-go to current destination, steering heading errorwith associated course correction arrow, and time ofday.

The SMO provides the destination label for the cur-rent destination when the destination is a CALCMlaunch point.

T.O. 1B-52H-34-2-9

1-41

WINDOW DISPLAY FUNCTION

1 xy Location and station of each weapon launched.

x = B for Bay stations, L for Left pylon stations, and R for Right pylon stations.

y = Station number - Bay 1, 2, 3, 4, 5, 6, 7, or 8.Pylon 1, 2, 3, 4, 5, or 6

The location and station of the weapon launched will be displayed in window 1and will be displayed for 5 seconds. If multiple jettison from pylons occurs,some messages may be skipped due to display timing.

2 AWAY_

HUNG_

ABORT

JETT_

The weapon was successfully launched.

The weapon umbilical and/or ejector status indicate that the weapon was notreleased.

A weapon abort was commanded.

The weapon was successfully jettisoned.

Figure 1-21. Release Advisory Display

T.O. 1B-52H-34-2-9

1-42 Change 11

CONTROL FUNCTION (CF) DISPLAYS

SMO Control Function (CF) commands are listed infigure 1-22. Pressing the CF key on the IKB willdisplay the CF MENU display (figure 1-23). Muchof the data displayed on the Control Function Menuis related to FMS and will not be discussed in thisT.O. The SMO related items are included in thisT.O. Operations are listed below:

• 5 WPN SUPV indicates a CF-5 command canbe used to request the Weapon Supervision Menu.The current operational SMO mode (i.e., STRIKE,PART SIM, FULL SIM, or Less [AMI] PLUS CT)is displayed in the adjacent window.

• 6 FCP SUPV, indicates a CF-6 command canbe used to request the FCP Supervision Menu.

• 8 MSN SUPV, indicates a CF-8 command canbe used to request the Mission Supervision Menu.

• E WCP BACKUP indicates a CF-E commandcan be used to request the WCP Backup display.

WEAPON SUPERVISION MENU (CF-5)

The Weapon Supervision Menu, commanded byCF-5, has the following functions:

• 50 STRIKE indicates a CF-50 command can beused to select STRIKE mode.

• 51 PART SIM indicates a CF-51 command canbe used to select PART SIM from STRIKE mode.

• 52 FULL SIM indicates a CF-52 command canbe used to select FULL SIM from STRIKE mode.

• Less [AMI] 55 CALCM SUPV indicates aCF-55 command can be used to select the CALCMSupervision Menu.

• [AMI] 55 CALCM SUPV indicates a CF-55command can be used to select the CALCM Super-vision Menu when CALCM is designated the prima-ry SMO. The alternate CALCM supervision displaycommands, CF-5x (where x = A for left pylon, B forbay, and C for right pylon), can be used at any timeto select the CALCM Supervision Menu, but thecommands are only valid if the SMO is assigned tothe corresponding location.

• 59 BAY DOORS identifies the operator com-mand to open and close the bomb bay doors (Notpertinent to operation of the SMO).

When the Weapon Supervision Menu is displayed,the current SMO mode (i.e., STRIKE, FULL SIM,or [AMI] PART SIM) is displayed, similar to theControl Function Menu (CF-).

STRIKE Mode Command (CF-50)

Less [AMI] Operator entry of CF-50 will commandthe SMO from either SIM mode into STRIKE mode.If the command is entered while the SMO is inSTRIKE mode or PLUS CT mode, it will be ignored.

The SMO will reject a CF-50 command and displayit in reverse video when the operational mode isFULL SIM or PART SIM and the MIUs are beingsimulated in the ON condition. The SMO will rejecta CF-50 command and display it in reverse video ifsimulated power is applied to any MIU, Go/No-Gotest option is active or SIT (System Interface Test)option is active.

[AMI] Operator entry of CF-50 will command theweapon system from SIM mode into STRIKE mode.If the command is entered while the weapon systemis in STRIKE mode, it will be ignored. The CF-50command will be rejected and displayed in reversevideo if any of the following is true:

• Simulated Go/No-Go test mode is active.• Simulated SIT mode is active.• Simulated power is applied to either MIU or

to any weapon.

After SIM mode is exited by commanding STRIKEmode, the B-52 mission data and the SMO must be re-loaded to guarantee proper operation of the system.

PART SIM Mode Command (CF-51)

Less [AMI] Operator entry of CF-51 will commandthe SMO from STRIKE mode into PART SIM mode.If the command is entered while the SMO is inPART SIM mode, it will be ignored. The SMO willreject a CF-51 command and display it in reversevideo under the following conditions:

• Power is applied to any MIU.• Operational mode is FULL SIM.• The B-52 mission tape payload type indicates

a war mission.• The MIUs have previously been powered ON

and any ejector was in the unlocked state.• Either SIT or Go/No-Go Testing mode is active.

[AMI] Operator entry of CF-51 will command theweapon system from STRIKE mode into PART SIMmode. If the command is entered while the weaponsystem is in PART SIM mode, it will be ignored.The CSP will reject a CF-51 command and displayit in reverse video if any of the following is true:

• The system is in FULL SIM mode.• Mission data is for an operational (STRIKE)

mission.• Power is applied to an MIU or to any weapon.• Actual Go/No-Go test mode is active.• Actual SIT mode is active.• 28 VDC T/R Power Discrepancy fault exists.• AIU Communication fault exists.• Any CALCM ejector is in the unlock state as de-

termined from previously having MIU power applied.

T.O. 1B-52H-34-2-9

Change 10 1-43

FULL SIM Mode Command (CF-52)

Less [AMI] Operator entry of CF-52 will commandthe SMO from STRIKE mode into FULL SIM mode.If the command is entered while the SMO is inFULL SIM mode, it will be ignored. The SMO willreject a CF-52 command and display it in reversevideo under the following conditions:

• Power is applied to any MIU.• Operational mode is PART SIM.• The B-52 mission tape payload type indicates

a war mission.• The MIUs have previously been powered ON

and any ejector was in the unlocked state.• Either SIT or Go/No-Go Testing mode is active.

[AMI] Operator entry of CF-52 will command theweapon system from STRIKE mode into FULL SIMmode. If the command is entered while the weaponsystem is in FULL SIM mode, it will be ignored.

The CSP will reject a CF-52 command and displayit in reverse video if any of the following is true:

• The system is in PART SIM mode.• The loaded B-52 mission is an operational

(strike/war) mission.• Power is applied to either MIU or to any weap-

on.• Actual Go/No-Go test mode is active.• Actual SIT mode is active.• 28 VDC T/R Power Discrepancy fault exists.• AIU Communication fault exists.• Any CALCM ejector is in the unlock state as de-


FULL SIM mode operation is described in SectionVII. The operational mode is displayed on ControlFunction Menu, Weapon Supervision Menu, andCALCM Supervision Menu.

T.O. 1B-52H-34-2-9

1-44 Change 11

COMMAND DESCRIPTION

CF Control Function Menu Request

CF-5 Weapon Supervisory Menu Request

CF-5x [AMI] CALCM Supervision Menu Request (Displays CALCM Supervision Menu, CF-55,when CALCM SMO controls location x)

CF-50 STRIKE Mode Command

CF-51 PART SIM Mode Command

CF-52 FULL SIM Mode Command

CF-55 CALCM Supervision Menu Request

CF-550 [AMI] Auto Target Enable/disable Command

CF-55A* Telemetry Power On Command for Selected CALCM

CF-55B* Telemetry Power Off Command for Selected CALCM

CF-55C* Telemetry Power Transfer Command for Selected CALCM

CF-55D Crypto Key Override Command

CF-55E Warm-Up Override Command

CF-55F** Weapon Erase Command for selected CALCM

CF-550 [AMI] Automatic Target On/Off Command

CF-551 Go/No-Go Test Command (MAINTENANCE ONLY)

CF-552 SIT Command (MAINTENANCE ONLY)

CF-553 Manual SAIR Command for Current Launch Point

CF-554 Automatic Retargeting On/Off Command

CF-555** Classified Data Erase Command

CF-556,nn* Manual Targeting of a Selected CALCM to the Mission Associated with Cruise MissileLaunch Point nn

CF-557,nn Flex Target Input Display Request for Launch Point nn

CF-558,nn* Direct Target Input Display Request for Selected CALCM with Direct Target Designa-tion of Dnn.

CF-559 Manually Initiated Targeting or Retargeting of All Available CALCMs

CF-6 FCP Supervision Menu Request

CF-61 FCP Initialization Display Request

CF-62 SMO Load Menu Request

CF-62,n Less [AMI] SMO Load Command for SMO Menu No. n

CF-62x [AMI] Primary SMO Selection Command by SMO Location x

CF-64 Classified Data Erase Command

CF-65 SMO Mission Event Recording Command

CF-66 Clear PME Faults Command

CF-67 OAS Shutdown Command

CF-68 ECU Fault Override Command

Figure 1-22. SMO Control Function (CF) Commands (Sheet 1 of 2)

T.O. 1B-52H-34-2-9

Change 10 1-44A

COMMAND DESCRIPTION

CF-8 Mission Supervision Menu Request

CF-81,n Read B-52 Sortie Mission Data Command for Mission No. n

CF-82x [AMI] Weapon Group Selection Menu Request for SMO Loaded at Location x

CF-82,nn or n [AMI] CALCM Weapon Group Selection Command for Weapon Group No. nn or n.

CF-DB Page Backward from the AGM-86D Fuze Data Screen to the Flex or Direct Target Dis-play

[AMI] Previous Sortie Command when entered from B-52 Mission Data Load Display,CF-81

[AMI] Page Backward to Previous CALCM Group Selection Menu when entered fromCALCM Group Selection Menu

[AMI] Page to CALCM Status and Inventory Display when entered from WeaponGroup Assignment Data Display

CF-DD Send Data for Flex/Direct Targeting

CF-DE Exit Flex/Direct Targeting

CF-DF Page Forward to the AGM-86D Fuze Data Screen from Flex or Direct Target Displays

[AMI] Next Sortie Command when entered from B-52 Mission Data Load Display,CF-81

[AMI] Page Forward to Next CALCM Group Selection Menu when entered fromCALCM Group Selection Menu

[AMI] Page to CALCM Status and Inventory Display when entered from WeaponGroup Assignment Data Display

CF-E Weapon Control Panel Backup Display Command

CLR-D Exit Direct Launch Mode Command

* Only one location and station can be selected if multiple locations and/or stations are selected, the command is displayed in reverse video and LOC/STA?? advisory displayed.** Multiple locations/stations can be selected.

Figure 1-22. SMO Control Function (CF) Commands (Sheet 2 of 2)

T.O. 1B-52H-34-2-9

1-44B Change 10

CF CONTROL FUNCTION MENU

Less [AMI]

[AMI]

1 N 1 SUPV2 N - 2 SUPV3 AL TER SUPV4 NAV R F5 WPN SUPV6 F P SUPV7 STE R SUPV8 MSN SUPV

EF RNMP BACKUP

E

E

II

B41011

WCP BACKUP

CF MENU

F -- - - - C

C

-

1

UU

PMD

Figure 1-23. Control Function (CF) Menu (Sheet 1 of 2)

T.O. 1B-52H-34-2-9

Change 10 1-44C

CF CONTROL FUNCTION MENU

WINDOW DISPLAY MODI-FIABLE

FUNCTION

1 STRIKE NO Operational mode is STRIKE.

PART SIM Operational mode is Part Simulation.

FULL SIM Operational mode is FULL Simulation.

Less [AMI] PLUS CT Operational mode is Plus Count.

Figure 1-23. Control Function (CF) Menu (Sheet 2 of 2)

T.O. 1B-52H-34-2-9

1-44D Change 10

CF-5 WEAPON SUPERVISION MENU

Less [AMI]

[AMI]

5 WPN SUPV

5A5 9 BAY DOORS 2

- - - - CF - 5

B41012

PMD

5B5C

L P WPN SUPVBAY WPN SUPVRP WPN SUPV

15 0 STR I KE5 PAR T S5 2 FUL L S

II MM1

333

5 5 CAL CM SUPV

Figure 1-24. CF-5 Weapon Supervision Menu (Sheet 1 of 2)

T.O. 1B-52H-34-2-9

Change 10 1-45


FUNCTION

1 Operational Mode NO

STRIKE Operational mode is STRIKE.




2 Bomb Bay Door Status

NO

OPEN AIU door status indicates bay doors are open.

CLSD AIU door status indicates bay doors are closed.

UNLTCHD AIU door status indicates bay doors are not opened and not closed.

UNLTCHD(Reverse Video)

AIU door status indicates bay doors are both opened and closed.

3 [AMI] SMO ID NO

24 Character SMO ID SMO is loaded for the respective location (A=Left Pylon, B=Bay,C=Right Pylon) but is not the Primary SMO.

24 Character SMO ID(Bright UnderlinedVideo)

SMO is loaded for the respective location (A=Left Pylon, B=Bay,C=Right Pylon) and is the Primary SMO.

Blank SMO is not loaded for the respective location (A=Left Pylon, B=Bay,C=Right Pylon) but is not the Primary SMO.

Figure 1-24. CF-5 Weapon Supervision Menu (Sheet 2 of 2)

T.O. 1B-52H-34-2-9

1-46 Change 10

CALCM Supervision Menu (CF-55)

The CALCM Supervision menu, commanded byCF-55 ([AMI] CF-55, CF-5A, CF-5B, and CF-5C), isshown in figure 1-25. CF-55 displays the currentSMO status and lists CF commands associated withCALCM operations. When the CALCM SupervisionMenu is displayed, the current SMO mode (i.e.,STRIKE or SIM) is displayed just as on the ControlFunction Menu (CF-) and the Weapon SupervisionMenu (CF-5).

[AMI] Commands CF-5A, CF-5B, and CF-5C willdisplay the same CALCM Supervision menu when-ever the CALCM SMO is loaded at the respectiveleft pylon, bay, or right pylon location. UnlikeCF-5A, CF-5B, and CF-5C commands, the CF-55command displays the CALCM Supervision menuonly when CALCM is designated as the primarySMO. Although CF-5A, CF-5B, and CF-5C com-mands are operable, whichever SMO is prime, ifCALCM is loaded but not prime, none of the optionson the CALCM Supervision menu, CF-550 throughCF-559 and CF-55A through CF-F,x,y are available.

The control function commands that are unique tothe SMO are of the form CF-55x where x representsany of several digits or alpha characters which mayor may not be followed by a comma and other dig-it(s) or alpha characters. The CALCM SupervisionMenu displays the control function commands ofthis form that are accepted by the SMO and thefunction commanded by each. In addition to identi-fying the CF-55x commands, the CALCM Supervi-sion Menu (CF-55) also identifies other SMO com-mands not identified on other CALCM displays.

TELEMETRY POWER COMMANDS (CF-55A,CF-55B, AND CF-55C)

Discussion of the telemetry power commands(CF-55A, CF-55B, and CF-55C) is contained in Sec-tion IV.

CRYPTO KEY OVERRIDE COMMAND CF-55D

Operator entry of CF-55D while the Crypto Keyoverride is inactive, which is the initial condition,will command the SMO to activate the Crypto Keyoverride option, removing targeting and launch re-strictions due to lack of Crypto Keys. Once active,the Crypto Key override option will become inactiveonly if the SMO is reloaded or if a logoff is com-manded and the system is restarted. Entry ofCF-55D again after activating the override will beignored. If the override is not active, targeting will

not occur unless valid Crypto Keys are available,and weapons will not be launched unless CryptoKeys are verified in the weapon GPS receiver. Theoverride will apply to all CALCMs. The current sta-tus of the Crypto Key override option is displayedon the CALCM Supervision screen figure 1-25. TheSMO will reject a CF-55D command to activate theCrypto Key override option, removing targeting andlaunch restrictions due to lack of Crypto Keys anddisplay the command in reverse video if anotherSMO confirmation message is active.

Prior to initiating crypto key override the SMO willseek confirmation by displaying the question KEYORIDE? YES/NO. A YES response will result incrypto key override being initiated, while a NO re-sponse will terminate the request. After Less[AMI] 60 seconds, [AMI] 120 seconds, the defaultresponse of NO will be assumed.

WARM UP OVERRIDE COMMAND CF-55E

Prior to accepting a command for missile electronicpower application, the SMO will ensure missileheater power has been applied for forty minutes toallow the missile electronic components to warmup. Missile heater power is applied to each missileat each location following MIU power applicationand initialization. Missile heater power is removedfrom each missile at each location during the MIUshutdown process. Operator entry of CF-55E whilethe warmup override is inactive, which is the initialcondition, will command the SMO to activate thewarm up override option and to ignore the mini-mum CALCM heater power ON time for all mis-siles. If the command is entered when the overrideoption is active, the missile warm up override op-tion will become inactive. The current status of themissile warm up override option is displayed in ad-jacent to the command on the CALCM SupervisionMenu (CF-55) figure 1-25.

NOTE

• Warm up timer (CF-55E) will not be by-passed for initial MIU operation.

• MIU power must be on for 40 minutes be-fore missile power can be applied, unlesstimer override command is entered. CF-55Ewill override approximately 35 minutes ofthe 40 minutes warm-up time when ex-treme cold conditions are present. Evenwith CF-55E entered, missile power will notbe accepted if missile INE platform temper-ature is not within limits.

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Change 11 1-46A

CF-55 CALCM SUPERVISION MENULess [AMI]

(CF-55, CF-5A, CF-5B, CF-5C)[AMI]

* Only one location and station can be selected if multiple locations and/or stations are selected, the command is displayed in reverse video and LOC/STA?? advisory displayed.** Multiple locations/stations can be selected.

Figure 1-25. CF-55 CALCM Supervision Menu (Sheet 1 of 2)

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1-46B Change 10


FUNCTION

1 Operational Mode NO

STRIKE Operational mode is STRIKE.




2 GO/NOGO Test Status NO

ON (Bright) Go/No-Go test is commanded and in progress. (Maintenance Function)

OFF (Bright) Go/No-Go test is not commanded.

3 SIT Test Status NO

ON (Bright) SIT test is commanded and in progress. (Maintenance Function)

OFF (Bright) SIT test is not commanded.

4 Auto Retarget Status NO

ON (Bright) Auto retarget function is commanded.

OFF (Bright) Auto retarget function is not commanded.

5 Crypto Key OverrideStatus

NO

ON (Bright) Crypto key override, which inhibits launch restrictions due to lack ofcrypto keys, is active.

OFF (Bright) Crypto key override is not commanded.

6 Warmup OverrideStatus

NO

ON (Bright) Warmup override, which inhibits missile electronic power applicationdue to sufficient missile heater warmup time.

OFF (Bright) Warmup override is not commanded.

7 [AMI] Auto TargetStatus

NO

ON (Bright) Auto target function is commanded.

OFF (Bright) Auto target function is not commanded.

NOTE

Aircrew members will not command CF-551 or CF-552 with actual missiles onboard unless required to verity DTUC/DTCcontents. Entry of CF-551 with missiles powered will cause all missiles to power down at the end of the Go/No-Go test.

Figure 1-25. CF-55 CALCM Supervision Menu (Sheet 2 of 2)

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Change 10 1-46C

WEAPON ERASE COMMAND CF-55F

Operator entry of CF-55F will result in weaponmission data and the CALCMs operational flightsoftware (OSF) being erased for the weapon(s) se-lected on the WCP. The SMO will ignore the com-mand for any selected CALCMs that are off or go-ing off. The SMO will reject a CF-55F command toinitiate weapon erase and display the command inreverse video if any of the following conditions ex-ist:

• At least one location and station is not selected.

• A single selected weapon is in launch countdown.

• Less [AMI] Another SMO confirmation mes-sage is active.

Prior to initiating weapon erase the SMO will seekconfirmation by displaying the question WEAPONOFS ERASE? YES/NO. A YES response will resultin weapon erase being initiated, while a NO re-sponse will terminate the request. After Less[AMI] 60 seconds, [AMI] 120 seconds, the defaultresponse of NO will be assumed.

NOTE

• Use of CF-55F and CF-555 is unrestricted af-ter authorization from higher headquarters.

• CF-55F will erase all data from the missile,including the missile Operational Flight Soft-ware (OFS). The missile must be removedfrom the aircraft in order for the software tobe reloaded. CF-55F will erase missile datafrom any selected powered missile, includingwhen the aircraft is on the ground.

[AMI] CALCM Auto Targeting Mode CF-550

Operator entry of CF-550 toggles between command-ing the Auto Targeting mode ON and OFF. The auto-matic targeting process has the SMO assigningCALCMs to CALCM launch points and downloadingthe appropriate weapon mission into the primaryCALCM assigned and its backups. Since other target-ing processes cannot be commanded for a CALCM un-til it has been initially targeted with an actual or de-fault weapon, each CALCM must successfully com-plete the automatic targeting process first. The cur-rent status of the Auto Target mode is displayed on theCALCM Supervision Menu (CF-55, CF-5A, CF-5B,CF-5C). The initial condition is OFF which inhibitsautomatic targeting from occurring.

Go/No-Go Test CF-551

Entry of CF-551 will command the SMO to activatethe Go/No-Go Test function. When active, Go/No-Go

Test tests can be performed on operationalCALCMs. The SMO will reject a CF-551 commandand display it in reverse video if the SIT mode is ac-tive or Less [AMI] the SIM mode is active ([AMI]any MIU has power applied). The SMO will displaya GO/NOGO CMPLT advisory message when thetest for all CALCMs for which powered was com-manded. Entry of CF-551 prior to test completionwill exit the Go/No-Go Test function.

NOTE

Aircrew members will not command CF-551or CF-552 with missiles on board unless re-quired to verify DTUC/DTC contents. Entryof CF-551 with missiles powered will cause allmissiles to power down at the end of the Go/No-Go test.

System Interface Test (SIT) CF-552

SIT performs a checkout of WCE, weapon interface,and missile(s). Entry of CF-552 will command theSMO to activate the SIT function. When active, SITtests can be performed on operational CALCMs.The SMO will reject a CF-552 command and dis-play it in reverse video if the aircraft is not on theground, if the Go/No-Go Test is active, or Less[AMI] SIM mode is active ([AMI] any MIU haspower applied). Entry of CF-552 prior to SITcompletion will exit the SIT Test function.

NOTE

Aircrew members will not command CF-551or CF-552 with missiles on board. Entry ofCF-551 with missiles powered will cause allmissiles to power down at the end of the Go/No-Go test.

Manual SAIR Command CF-553

Operator entry of CF-553 will result in manualSAIR mode being initiated for the weapon associat-ed with the current cruise missile launch point.When Manual SAIR is entered the launch modewill automatically change to manual. The SMO willreject a CF-553 command to initiate manual SAIRand display the command in reverse video if any ofthe following conditions exist:

• The current destination is not a cruise missilelaunch point.

• No weapon is targeted to the current cruisemissile launch point.

• A direct target is selected as the current weap-on event.

• Weapon is in launch countdown sequence.• Less [AMI] Another SMO confirmation mes-

sage is active.

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1-46D Change 10

Prior to entering Manual SAIR the SMO will seekconfirmation by displaying the question MANUALSAIR? YES/NO on the bottom of the MFD. A YESresponse will result in manual SAIR being initi-ated, while a NO response will terminate the re-quest. After Less [AMI] 60 seconds, [AMI] 120 sec-onds, the default response of NO will be assumed.

Manual SAIR will remain active until one of the fol-lowing occurs:

• A weapon release.• The launch mode is changed to automatic.• Entry into direct launch mode.• Three minutes have elapsed since entry into

manual SAIR mode.• The operator issues a Fly-to command, or nor-

mal destination sequencing occurs. Normal se-quencing is inhibited as long as a missile is tar-geted to the launch point and SAIR conditions arevalid. Sequencing will occur when all three of thefollowing have occurred

1) The aircraft has flown within 1 nm of thelaunch point.2) The aircraft has flown within 0.1 nm of thelaunch point, or is no longer within 1 nm of the launch point.3) The aircraft is no longer in SAIR or no missile is targeted to the launch point.

Automatic Retargeting Enable Command CF-554

Operator entry of CF-554, while the automatic re-targeting function is inhibited, which is the initialcondition, will cause automatic retargeting to be ac-tive. If the command is entered while the automaticretarget function is active, automatic retargetingwill become inhibited. The current status of auto-matic retargeting, whether it is active or inactive, isdisplayed in the window adjacent to the commandon the CALCM Supervision Menu (CF-55) and onthe Program screen.

Classified Data Erase Command CF-555

Operator entry of CF-555 will result in classifieddata erase mode being initiated for the weapon(s)selected on the WCP. The SMO will ignore the com-mand for any selected CALCM that is off or goingoff. The SMO will reject a CF-555 command to initi-ate classified data erase and display the commandin reverse video if any of the following conditionsexist:

• At least one valid location and station is notselected.

• A single selected weapon is in launch count-down.

• Less [AMI] Another SMO confirmation mes-sage is active.

Prior to initiating classified data erase the SMOwill seek confirmation by displaying the questionCLSF DATA ERASE? YES/NO. A YES responsewill result in the mission data set, including cryptokeys, being erased from the weapon memory. A NOresponse will terminate the request. After Less[AMI] 60 seconds, [AMI] 120 seconds, the defaultresponse of NO will be assumed.

NOTE

• Use of CF-55F and CF-555 is unrestrictedafter authorization from higher headquar-ters.

• CF-555 erases mission data only. The mis-sile OFS remains loaded and as a result themissile still contains software classified SE-CRET. The CALCM can have power reap-plied and made ready for launch after usingthe CF-555 command.

Manual Target Command CF-556,nn

Operator entry of CF-556,nn with a single weaponlocation and station selected on the WCP will causethe mission associated with the cruise missilelaunch point nn to be loaded in the selected weaponand up to two available backup weapons. The SMOwill reject a CF-556,nn command to send targetingdata and display the command in reverse video ifany of the following conditions exist:

• [AMI] Another SMO is designated as primary.• [AMI] The selected weapon group is not avail-

able.• nn is not a valid cruise missile launch point

number.• A single weapon location and station has not

been selected.• There is no CALCM at the selected location/

station.• The warhead type for the cruise missile

launch point number does not match the warheadtype of the single weapon selected.

• Any CALCM is in launch count down.• Another targeting mode is in progress.• Less [AMI] The loaded sortie mission does not

identify a MIU in the stores table that is associatedwith the single weapon selected.

• The CALCM selected is OFF or going OFF.• The single weapon selected has not received

GPS initialization data.• Mission data transfer is in progress.

NOTE

If the launch point being manually targetedis the current destination, automatic se-quencing to the next destination will be in-hibited while in-range.

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Change 10 1-47

Flex Targeting Selection Command CF-557,nn

Operator entry of CF-557,nn where nn is the cruisemissile launch point number, will cause the FlexTargeting Input display, figure 1-26, to be dis-played. This display is used to flex off of anyCALCM mission steering waypoint to a operatorentered target location. The launch point number,its associated missile location/station, and Less[AMI] the DTUC checksum or [AMI] CALCMweapon group are shown at the top of the display.

Less [AMI] All digital input fields will be initial-ized to zero at SMO load. Before the data can besent to the weapon the operator must enter eachnon-zero data item.

Flex targeting data entry is initiated by entering aMDFY-n command (where n is the line number ofthe desired line to modify). The operator will thenenter the requested information and press ENTER.When ENTER is pressed, range checks will be pro-vided for all data on the line being modified and thefirst out-of-range entry on a line will be reversehighlighted. Once an entry has been reverse high-lighted it stays reverse highlighted even when cor-rect data is entered. To remove the reverse high-light, the MDFY-n command for that line (or a dif-ferent line if desired) must be used and all data forthat line re-entered.

NOTE

If the latitude or longitude fields become re-verse highlighted, the arrow keys on theIKB must be used to skip over the degree,minute, and decimal delimiters because itwill no longer happen automatically).

If the data is valid, it is copied from the commandline that was modified. When the operator has com-pleted a line or wishes to modify another line,MDFY-n can be entered to modify the same or dif-ferent line. The process of entering MDFY-n, thenthe data, then pressing ENTER is repeated until alllines have valid data on them. Once all requireddata has been entered, the selected CALCM can beretargeted with the entered data by issuing the CF-DD command.

Less [AMI] The DTUC Checksum on line 1 allowsverification that the launch point’s CALCM missionbeing flexed came from the appropriate CALCMweapon DTUC. Checksums must be provided to theaircrew by the mission planners.

A message for AGM-86Ds has been added at thebottom of the display above the CF-DD prompt.This message, CF-DF PAGE FORWARD, directs theoperator to select CF-DF for the AGM-86D FuzeData Display.

The available backup weapons will be flexed auto-matically when the CF-DD command is issued. Un-til the CF-DD command is issued, the operator canre-enter data on any modifiable line by reselectingthat line using the MDFY-n command as before.

During the Flex targeting process the operator cancommand display of an additional flex targeting inputdisplay by entering CF-557. After the CF-DD or CF-DE command is issued, Flex targeting will be termi-nated, the entered data will remain displayed and theoperator must reenter CF-557,nn to flex target anoth-er weapon. If the operator changes displays such thatFlex targeting screens are no longer displayed, Flextargeting will be terminated and the entered data willbe stored for display on a subsequent Flex targetingcommand. The operator may review Flex targetingdata for a weapon previously targeted by enteringCF-557,nn for that launch point.

The SMO will reject a CF-557,nn command and dis-play the command in reverse video if any of the fol-lowing conditions exist:

• [AMI] The CALCM SMO is not the primarySMO.

• nn is not a valid CALCM launch point number.• There is no CALCM associated with the speci-

fied launch point.• Flex target modification is active for another

launch point.

The CF-557,nn and CF-557 commands will be re-jected and reverse highlighted for the following:

• Mission data transfer is in progress.• Another targeting mode is in progress.• Launch countdown is in progress for any mis-

sile.

The CF-557,nn, CF-557, and CF-DF commands willbe rejected and reverse highlighted for the following:

• The CALCM associated with the launch pointis off or powering off.

The CF-557 and CF-DF commands will be rejectedand reverse highlighted for the following:

• Flex targeting mode is in progress.

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1-48 Change 10

CF-557,nn FLEX TARGET INPUT DISPLAY FOR LAUNCH POINT nn Less [AMI]

[AMI]

Figure 1-26. CF-557,nn Flex Target Input Display For Launch Point nn (Sheet 1 of 9)

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Change 10 1-49


FUNCTION

1 Launch Point No. NO

nn (Bright Underlined) Selected launch point number.

(blank) Flex targeting not active.

2 Location/Station NO

xy (Bright Underlined) Location(x) and station (y) of the weapon of associated weapon.

(blank) Flex targeting not active & flex screen displayed.

x = B for Bay location, L for left pylon location, and R for right pylon locationy = Station number 1, 2, 3, 4, 5, 6, 7, or 8 for Bay; 1, 2, 3, 4, 5, or 6 for pylons.

3 Less [AMI] DTUCChecksum

NO

nnnn (Bright) NO DTUC checksum in hexadecimal format, in the range of 0000 to FFFF.

4 Target Latitude YES

Less [AMI]add°mm ss.sss[AMI] add°mm.mmm(Bright)

Target latitude in Less [AMI] degrees, minutes, seconds and thousandthsof a second, [AMI] degrees, minutes and thousandths of minutes.

a= N for north and S for south. Valid input range = N/S 90°

Less [AMI] N00°0000.000[AMI] N00°00.000(Bright)

Awaiting Data Input or valid zero input.

5 Target Longitude YES

Less [AMI]addd°mm ss.sss[AMI] addd°mm.mmm(Bright)

Target longitude in Less [AMI] degrees, minutes, seconds and thousandthsof a second, [AMI] degrees, minutes and thousandths of minutes..

a= E for east and W for west. Valid input range = Less [AMI] E 180° 00 00.000 thru

W 179° 59 59.999 [AMI] E 180°00.000 through W 179°59.999.

Less [AMI] E000°0000.000[AMI] E000°00.000(Bright)


6 Target Elevation YES

nnnnn (Bright) Target elevation (MSL): -1300 to 29030 in feet.

00000 (Bright) Awaiting Data Input, or valid zero target elevation.

7 Pre-target SteeringWaypoint

YES

nn (Bright) CALCM steering waypoint to be used as the pre-target waypoint.Valid input range = 2 to JMAX-3. Where JMAX-3 is the planned pre-target waypoint.

00 Awaiting Data Input.


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1-50 Change 10


FUNCTION

8 JMAX-3 NO

nn JMAX-3, Where JMAX-3 is the planned pre-target waypoint.

9 Burst Altitude YES

nnnn (Bright) Height of burst altitude AGL in feet.Valid input range = 0 to 5000.

0000 Awaiting Data Input, or valid zero target altitude.

n (Bright) SWP to Target Mach speed index.Valid input range = 0 to 4.

0 (Bright) Awaiting Data Input, or valid zero input.

10 Steering Waypoint toTarget Mach Index

YES



11 Flight Mode Code YES

n (Bright) Flight mode from the SWP to the target(0 = Baro Hold, 1 = Terrain Following).


12 Flight Mode NO

TF When flight mode is Terrain Following.

BH When flight mode is Baro Hold.

13 Flight Altitude YES

nnnnn (Bright) Flight altitude from the SWP to TMIP in feet. Valid input range = -1000 to 50000 MSL when flight mode is Baro Hold or = 0 to 8000 AGL when flight mode is Terrain Following .

00000 (Bright) Awaiting data input, or valid zero input.

14 Less [AMI] Flight ModeAltitude Reference

NO

AGL When flight mode is Terrain Following.

MSL When flight mode is Baro Hold.

[AMI] Flight Mode Alti-tude Range

NO

(0 – 8000 FT AGL) When flight mode is Terrain Following.

(-1000 – 50000 MSL) When flight mode is Baro Hold.


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Change 10 1-51


FUNCTION

15 Line 7 NO

7 When flight mode is Terrain Following or flight altitude trajectory mode onCF-558 is Terrain Following.

(blank) When flight mode is not Terrain Following.

16 Barometric Hold Backup Altitude

NO

BH BKUP ALT When flight mode is Terrain Following.


17 Backup Altitude YES

nnnnn (Bright) Backup altitude in feet (SWP to TMIP).Valid input range = -1000 to 50000 MSL when flight mode is Terrain Fol-lowing.

00000 (Bright) Awaiting data input, or valid zero input when flight mode is Terrain Fol-lowing.

(blank) When flight mode is Baro Hold.

18 Less [AMI] Backup Altitude Reference

NO

FT MSL, TF Only When flight mode is Terrain Following.


[AMI] Backup AltitudeRange

(-1000 – 50000MSL) When flight mode is not Terrain Following.

19 Rollover Flag YES

n (Bright) Valid inputs: 0= OFF, 1 = ON.

20 Less [AMI] ImpactAngle

YES

nn (Bright) Impact Angle in whole degrees. Valid input range accepted by OAS is 00to 80.

AGM-86C - If rollover mode is not selected the input range which will beaccepted by the missile is 00 to 50. If rollover mode is selected, the inputwhich will be accepted by the missile is 70. If a value greater than 50 isused for a push over or a value other than 70 is used for a rollover themissile will NoGo.

AGM-86D - If rollover mode is not selected the input range which will beaccepted by the missile is 00 to 50. If rollover mode is selected, the inputrange which will be accepted by the missile is 50 to 70. If a value be-tween 70 to 80 is entered the missile will use 70. If a value outside thepushover or rollover limitations is entered the missile will accept the val-ues and may unsuccessfully attempt to achieve the commanded angle.



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1-52 Change 10


FUNCTION

20 [AMI] Impact Angle YES

nn (Bright) Impact angle in degrees. Valid input range = 0 to 80 for Warhead 2(Penetrator) when Rollover Flag = 0 or 1. Valid input range = 0 to 50 forWarhead 1 (Blast/Frag) when Rollover Flag = 0. Valid input = 70 for War-head 1 when Rollover Flag = 1.


(blank) Awaiting data input.

21 PAGE FORWARD Msg NO

CF-DF PAGE FORWARD(Underlined)

Page forward to Fuze Data screen (CF-DF) when the missile is anAGM-86D.

(blank) Missile not an AGM-86D.


xy (Bright Underlined) Location(x) and station (y) of the weapon of associated weapon. x = B for Bay location, L for left pylon location, and R for right pylon locationy = Station number 1, 2, 3, 4, 5, 6, 7, or 8 for Bay; 1, 2, 3, 4, 5, or 6 for pylons.

23 Store Type NO

P Store is present but unidentified.

C CALCM is present .

C (Bright Underlined) CALCM is present with OTL power on.

X Store is not present at the specified location/station.

(blank) MIU is not powered.

24 Warhead Type NO

n (Bright) Weapon warhead type provided by missile data (1 = Blast/Frag, 2 =Penetrator).

(blank) Warhead type has not been received from the missile.


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Change 10 1-53


FUNCTION

25 CALCM Status NO

OF CALCM electronic power is off.

ON CALCM electronic power is on.

CA CALCM is coarse aligning.

TA (Reverse) Transfer Alignment maneuver is required.

AL CALCM is aligned.

GO CALCM is aligned, GPS receiver is initialized, and Crypto Keys are veri-fied (if keyed mission).

Less [AMI] PL [AMI] CL CALCM plus ct launch is currently active when not in either SIM mode.

AW CALCM launch (captive carry mode not active) has successfully oc-curred.

JT CALCM jettison has successfully occurred.

HG (Reverse) CALCM is hung.

NG (Reverse) CALCM permanent fatal fault has occurred, power is off and reapplicationof power is inhibited.

[AMI] ER CALCM Erase is active.

(blank) No CALCM at this station or MIU power is off.

26 Ready To Launch Status

NO

SAF Weapon has not been provided operator consent for launch from theSAFE/PREARM switch.

RDY Weapon has been provided operator consent for launch from the SAFE/PREARM switch.


27 Flex/Direct Target Indication

NO

F (Bright Underlined) Weapon has been flex targeted.

F Flex targeted weapon has been launched.

D (Bright Underlined) Weapon has been direct targeted.

D Direct targeted weapon has been launched.

(blank) No CALCM at this station, it is not flex or direct targeted, or MIU power is off.

28 Targeting Status NO

nn Primary mission of a weapon has launch point or direct target nn defined,or Weapon has been launched at launch point or direct target nn.

nn (Bright Underlined) Primary mission of a weapon has launch point or direct target nn definedand the weapon is targeted.


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1-54 Change 10


FUNCTION

28 Targeting Status (Cont)

G GPS initialization data has been loaded into the weapon, but no missionis assigned.

R CALCM indicates it is ready to receive mission data.

(blank) MIU power is off, CALCM power is off, or weapon is not a CALCM.

29 MISSILE FAULTS (Reverse)

NO SEE SECTION VII.

30 Ordnance Alarm Status NO

ALARM (Reverse) Ordnance Alarm fault indication has been received for selected CALCM.

SAFE No ordnance alarm fault indication has been received for selectedCALCM.

(blank) No CALCM selected or MIU is powered off.

31 Ejector Status NO

LOCKD Ejector is locked for selected CALCM.

UNLOCKD Ejector is unlocked for selected CALCM.

UNKNOWN(Reverse)

Ejector status cannot be determined (Illegal ejector status) for the selected CALCM.

(blank) No CALCM present or selected, or MIU is powered off.

32 OTL Payload Status NO

OTL (Bright Underlined)

Weapon has OTL payload.

(blank) Payload type is not identified as OTL, no CALCM selected, or MIU ispowered off.

33 OTL Power Status NO

BATT OTL instrumentation power is on CALCM battery power for selectedCALCM.

CARR OTL instrumentation power is on carrier power for selected CALCM.

UNKN (Reverse) OTL instrumentation power has indeterminate status for selectedCALCM.

OFF OTL instrumentation power is off for selected CALCM.



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Change 10 1-55


FUNCTION

34 Command DestructStatus

NO

C/D (Bright Underlined) Missile has command destruct (flight termination) receiver installed.

(blank) Missile does not have command destruct (flight termination) receiverinstalled.

35 Flight Termination System Status

NO

SAFE Flight termination system is disable for selected CALCM.

ARMD (Reverse) Flight termination system is enabled for selected CALCM.


36 CALCM INS Temp Fault NO

TEMP (Reverse) CALCM INS platform temperature NO-GO for the selected CALCM.

(blank) No fault detected or MIU is powered off.

37 CALCM Altimeter Fault NO

ALTM (Reverse) CALCM Radar Altimeter (RA) No-Go or Radar Altimeter Equipment(RAE) No-Go for the selected CALCM.


38 CALCM INS Fault NO

INS (Reverse) CALCM INS Z-Velocity No-Go or INS Alignment No-Go for the selectedCALCM.


39 Backup Location/Station

NO

xy (Bright Underlined) Location(x) and station (y) of the backup for selected CALCM.


(blank) No backups for selected CALCM or no CALCM selected or MIU is powered off.

40 CALCM WeaponGroup ID

NO

28 Characters (Bright) CALCM Weapon Group ID associated with weapon mission being flexed.

41 Manual SAIR Range NO

nnn Maximum manual launch range in NM. Valid range = 20 - 300 NM.


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1-56 Change 10


FUNCTION

42 Lower Impact AngleLimit

NO

00 Lower range value for Impact Angle for Warhead Type 2 (Penetrator) withRollover Flag = 0 or 1.

00 Lower range value for Impact Angle for Warhead Type 1 (Blast/Frag) withRollover Flag = 0.


43 Upper Impact AngleLimit

NO

80 Upper range value for Impact Angle for Warhead Type 2 (Penetrator) withRollover Flag = 0 or 1.

50 Upper range value for Impact Angle for Warhead Type 1 (Blast/Frag) withRollover Flag = 0.



All data on pages 1-56A and 1-56B (Deleted)

T.O. 1B-52H-34-2-9

Change 10 1-57

Direct Targeting Input Screen CF-558,nn

Operator entry of CF-558,nn, with a single weaponlocation and station selected on the WCP will causethe Direct Targeting Input screen, figure 1-27, to bedisplayed for direct target Dnn. This screen is usedto direct target a CALCM to a operator entered tar-get. The direct target designation and the missilelocation/station are displayed in figure 1-27 next tothe screen title in windows 1 and 2. All digital in-put fields will be initialized to zero at SMO load.

Direct Targeting data entry is initiated by enteringa MDFY-n command (where n is the line number ofthe desired line to modify). The operator will thenenter the requested information and press ENTER.When ENTER is pressed, range checks will be pro-vided for all data on the line being modified and thefirst out-of-range entry on a line will be reversehighlighted. Once an entry has been reverse high-lighted it stays reverse highlighted even when cor-rect data is entered. To remove the reverse highlight, the MDFY-n command for that line (or a dif-ferent line if desired) must be used and all data forthat line re-entered. (Special note: If the latitude orlongitude fields become reverse highlighted, the ar-row keys on the IKB must be used to skip over thedegree, minute, and decimal delimiters because itwill no longer happen automatically).

If the data is valid, it is copied from the commandline that was modified. When the operator has com-pleted a line or wishes to modify another line,MDFY-n can be entered to modify the same or dif-ferent line. The process of entering MDFY-n, thenthe data, then pressing ENTER is repeated until alllines have valid data on them.

The CF-DF command is used to page forward to theAGM-86D Fuze Data Display when the missile isan AGM-86D (figure 1-30C).

Once all required data has been entered, the se-lected CALCM can be retargeted with the entereddata by issuing the CF-DD command. The availablebackup weapons will be direct targeted automati-cally when the CF-DD command is issued. Until theCF-DD command is issued, the operator can reen-ter data on any modifiable line by reselecting thatline using the MDFY-n command as before. Duringthe direct targeting process the operator can com-mand display of an additional direct targeting input

display by entering CF-558. After the CF-DD orCF-DE command is issued, direct targeting will beterminated, the data entered will be saved as thedefault, and the operator must reenter CF-558,nnwith another single weapon location and station se-lected to direct target another weapon. If the Navi-gator and Radar Navigator change displays, suchthat direct targeting screens are no longer dis-played, direct targeting will be terminated and theentered data will be stored for display on the follow-ing direct targeting command. The operator may re-view Direct Targeting data for a weapon previouslytargeted by selecting the location and station of theweapon and entering CF-558,nn for the direct tar-get designator.

The SMO will reject a CF-558,nn command and dis-play the command in reverse video if any of the fol-lowing conditions exist:


• A single weapon location and station has notbeen selected.

• Direct target modification is active for anotherCALCM.

• Direct target modification is active for anotherdirect target number.

• The direct target number is assigned to a dif-ferent CALCM than the one designated by theWCP.

• nn is not a valid CALCM direct target number.• The selected CALCM has not received GPS in-

itialization data.

The CF-558,nn and CF-558 commands will be re-jected and reverse highlighted for the following:

• Mission data transfer is in progress.• Another targeting mode is in progress.• Launch countdown is in progress for any mis-

sile.

The CF-558,nn, CF-558, and CF-DF commands willbe rejected and reverse highlighted for the following:

• The CALCM associated with the direct targetis off or going off.

The CF-558, and CF-DF commands will be rejectedand reverse highlighted for the following:

• Direct targeting is not active.

T.O. 1B-52H-34-2-9

1-58 Change 10

CF-558, nn DIRECT TARGET INPUT DISPLAY FOR DIRECT TARGET nn Less [AMI]

[AMI]

Figure 1-27. CF-558, nn Direct Target Input Display For Direct Target nn (Sheet 1 of 10)

T.O. 1B-52H-34-2-9

Change 10 1-59


FUNCTION

1 Direct Target No. NO

Dnn (Bright Under-lined)

Direct target designation number.Valid range D1 to D20

(blank) Direct Targeting not active.


xy (Bright Underlined) Location(x) and station (y) of the weapon of associated weapon.

(blank) Flex Targeting is not active and the Flex screen is displayed or Direct target-ing not active and direct screen displayed.


3 Target Latitude (Bright) YES

Less [AMI]add°mm ss.sss[AMI] add°mm.mmm

Target latitude in Less [AMI] degrees, minutes, seconds and thousandthsof a second, [AMI] degrees, minutes and thousandths of minutes. a= N for north and S for south.

Valid input range = N/S 90°Less [AMI] N00°0000.000[AMI] N00°00.000


4 Target Longitude(Bright)

YES

Less [AMI]addd°mm ss.sss[AMI] addd°mm.mmm

Target longitude in Less [AMI] degrees, minutes, seconds and thousandthsof a second, [AMI] degrees, minutes and thousandths of minutes. a= E for east and W for west.

Valid input range = Less [AMI] E 180° 00 00.000 thru W 179° 59 59.999 [AMI] E 180°00.000 through W 179°59.999.

Less [AMI] E000°0000.000[AMI] E000°00.000


5 Target Elevation YES

nnnnn (Bright) Target elevation (MSL): –1300 to 29030 in feet.

00000 (Bright) Awaiting Data Input, or valid zero target elevation.

6 Target Approach Azi-muth

YES

nnn (Bright) Target approach azimuth in degrees (True).Valid input range = 0 to 359 orDAA for direct approach.

000 Awaiting Data Input or valid zero input.

7 Burst Altitude YES

nnnn (Bright) Height of burst altitude AGL in feet.Valid input range = 0 to 5000.

0000 Awaiting Data Input, or valid zero target altitude.

8 SWP Mach Speed Index YES

n (Bright) Launch to SWP Mach speed index.Valid input range = 0 to 4.



T.O. 1B-52H-34-2-9

1-60 Change 10


FUNCTION


n (Bright) Flight altitude trajectory mode from Launch to the SWP(0 =Baro Hold, 1 = Terrain Following).


10 Flight Mode NO

TF When flight altitude trajectory mode is Terrain Following.

BH When flight altitude trajectory mode is Baro Hold.

11 Launch to SWP Flight Altitude

YES

nnnnn (Bright) Flight altitude from Launch to SWP in feet. Valid input range = -1000 to 50000 MSL when flight mode is Baro Hold or = 0 to 8000 AGL when flight mode is Terrain Following.



NO



[AMI] Flight Mode Altitude Range

NO



13 Line 7 NO

7 When flight mode on CF-558 is Terrain Following.



NO




nnnnn (Bright) Backup altitude in feet (Launch to SWP). Valid input range = -1000 to50000 MSL when flight mode is Terrain Following.




T.O. 1B-52H-34-2-9

Change 10 1-61


FUNCTION

16 Less [AMI] Backup Al-titude Reference

NO



[AMI] Flight Mode Altitude Range

NO

(-1000 – 50000 MSL) When flight mode is Terrain Following.


17 Steering Waypoint toTarget Mach Index

YES



18 Steering Waypoint toTarget Distance

YES

nn (Bright) Distance selection from SWP to the target. Valid input range = 30 to 99 NM.

00 Awaiting Data Input.


n (Bright) Flight mode from the SWP to the target(0 = Baro Hold, 1 = Terrain Following).


20 Flight Mode NO

TF When flight mode is Terrain Following.

BH When flight mode is Baro Hold.

21 SWP to TargetFlight Altitude

YES

nnnnn (Bright) Flight mode altitude from the SWP to the target in feet. Valid input range = -1000 to 50000 MSL when flight mode is Baro Hold or = 0 to 8000 AGL when flight mode is Terrain Following.



NO




T.O. 1B-52H-34-2-9

1-62 Change 10


FUNCTION

22 [AMI] Flight Mode Alti-tude Range (Cont)

NO



23 Line 12 NO

12 When flight mode is Terrain Following.



NO




nnnnn (Bright) Backup altitude in feet (SWP to the target).Valid input range = -1000 to 50000 MSL when flight mode is Terrain Following.

00000 (Bright) Awaiting data input, or valid zero input when flight mode is Terrain Following.


26 Less [AMI] Backup Al-titude Reference

NO



[AMI] Backup AltitudeRange

NO

(-1000 – 50000MSL) When flight mode is not Terrain Following.

27 Rollover Flag YES

n (Bright) Rollover Flag. Valid inputs 0= OFF, 1 = ON.


T.O. 1B-52H-34-2-9

Change 10 1-63


FUNCTION

28 Impact Angle YES Impact Angle in whole degrees. Valid input range accepted by OAS is 00 to80.

Less [AMI]nn (Bright)

AGM-86C - If rollover mode is not selected (0 displayed in window 27) theinput range which will be accepted by the missile is 00 to 50. If rollover modeis selected (1 displayed in window 27) the input which will be accepted bythe missile is 70. If a value greater than 50 is used for a push over or a valueother than 70 is used for a rollover the missile will NoGo.

AGM-86D - If rollover mode is not selected (0 displayed in window 27) theinput range which will be accepted by the missile is 00 to 50. If rollover modeis selected (1 displayed in window 27) the input range which will be acceptedby the missile is 50 to 70. If a value between 70 to 80 is entered the missilewill use 70. If a value outside the pushover or rollover limitations is enteredthe missile will accept the values and may unsuccessfully attempt to achievethe commanded angle.


[AMI] nn (Bright)

Impact angle in degrees. Valid input range = 0 to 80 for Warhead 2(Penetrator) when Rollover Flag = 0 or 1. Valid input range = 0 to 50 forWarhead 1 (Blast/Frag) when Rollover Flag = 0. Valid input = 70 for War-head 1 when Rollover Flag = 1.


29 PAGE FORWARD Msg NO

CF-DF PAGE FORWARD(Underlined)

Page forward to Fuze Data screen (CF-DF) when the missile is anAGM-86D.

(blank) Missile not an AGM-86D.




T.O. 1B-52H-34-2-9

1-64 Change 10


FUNCTION

31 Store Type NO






32 Warhead Type NO



33 CALCM Status NO














34 Ready To Launch Status

NO





T.O. 1B-52H-34-2-9

Change 10 1-65


FUNCTION


NO





(blank) No CALCM at this station, it is not flex or direct targeted, or MIU power isoff.




G_ GPS initialization data has been loaded into the weapon, but no missionis assigned.

R_ CALCM indicates it is ready to receive mission data.



NO SEE SECTION VII.








UNKNOWN(Reverse)




T.O. 1B-52H-34-2-9

1-66 Change 10


FUNCTION












NO




NO

SAFE Flight termination system is disabled for selected CALCM.




TEMP (Reverse) CALCM INS platform temperature No-Go for the selected CALCM.



ALTM (Reverse) CALCM CMRA No-Go or RAE No-Go for the selected CALCM.



T.O. 1B-52H-34-2-9

Change 10 1-66A


FUNCTION



(blank) No fault detected or MIU is powered off ([AMI] or weapon is powered off,selected store is not a CALCM, no store selected or weapon has beenreleased).


NO



(blank) No backups for selected CALCM or no CALCM selected or MIU is poweredoff.

48 Lower Impact AngleLimit

NO

00 Lower range value for Impact Angle for Warhead Type 2 (Penetrator) withRollover Flag = 0 or 1.



49 Upper Impact AngleLimit

NO

80 Upper range value for Impact Angle for Warhead Type 2 (Penetrator) withRollover Flag = 0 or 1.




T.O. 1B-52H-34-2-9

1-66B Change 10

Target/Retarget All Command CF-559

Initial operator entry of CF-559 will result in thetargeting of all CALCMs which have power appliedand their available backups in order of the pre-ferred launch sequence until either all availableweapons have unique primary missions or allunique missions have been exhausted from theCALCM Mission DTUC/DTC. If after targeting hasbeen completed and for any reason a CALCM be-comes available that is not targeted and a CALCMlaunch point is not targeted, the CALCM and anyavailable backups will be targeted automaticallywithout need for reissuing the CF-559 command.The CF-559 command must be issued and targetingcompleted prior to commanding any other weapontargeting options. If after all cruise missile missionshave been exhausted, and there remain CALCMswhich have not been targeted, GPS initializationdata will be sent so that other targeting functionscan be performed on those weapons. EnteringCF-559 after targeting has been initiated will clearthe existing mission to weapon assignments and re-target all available weapons beginning with thecurrent destination. The SMO will reject a CF-559command to send targeting data and display thecommand in reverse video if any of the followingconditions exist:

• A B-52 mission has not been loaded.• Automatic targeting is not enabled.• Another targeting mode is in progress (exclud-

ing automatic retargeting).• Less [AMI] Another SMO confirmation mes-

sage is active.

Prior to initiating targeting or retargeting of allCALCMs, the SMO will seek confirmation by dis-playing the question TGT/RETGT ALL? YES/NO. AYES response will result in targeting being initi-ated, while a NO response will terminate the re-quest. After Less [AMI] 60 seconds, [AMI] 120 sec-onds, the default response of NO will be assumed.

One of the following conditions must be met prior toissuing the CF-559 command or targeting will notoccur and the command will have to be re-issuedonce one of the conditions is met.

If the IU is on:• Almanac data is resident in the IU.• Crypto key data is resident in the IU if Crypto

Key Override has not been selected.

If the IU is off and a B-52 sortie DTUC/DTC withGPS data is available:

• Almanac data is resident in the DTUC/DTC.• Crypto key data is resident in DTUC/DTC if

Crypto Key Override has not been selected. (Thecurrent date, CF-61 line 4, must be within theCrypto Key start and End date in the DTUC/DTC.

T.O. 1B-52H-34-2-9

Change 10 1-66C

FCP SUPERVISION MENU (CF-6)

The FCP Supervision Menu, commanded by CF-6,is shown in figure 1-28. Much of the data displayedon the FCP Supervision Menu is related to FMSand will not be discussed herein. However, theitems which regard SMO operation are:

FMS Startup Menu (CF-61)

CF-61 commands OAS startup. The procedure forstarting up the OAS is the same as for any otherOAS startup and is contained in T.O. 1B-52H-1-12.Data on the FMS Startup Menu (CF-61) is enteredin order to process data for CALCMs with pre-planed missions (direct targeted CALCMs do notuse this data). Operator entry of CF-61 will requestthe FMS Startup Menu display. The MDFY-n com-mand is then used to enter the required data inlines 1 and 3. MDFY-1 allows the entry of the UTCused as the clock time for the flight system.MDFY-3 allows the entry of the Planned Time ofArrival (PTA), and the destination it applies to,used to determine a time of launch deviation errorsent to the missile during LCD to adjust missilecruise speed.

This data must be entered prior to launching thefirst CALCM associated with a launch point. Thedata must be loaded after each B-52 mission load.The entered PTA is used to compute a delta valuethat will be applied to the planned PTAs for eachdestination.

Less [AMI] SMO Menu (CF-62)

The 62 SMO Load Menu, figure 1-29, indicates aCF-62 command can be used to request the displayof the SMOs available on the OCP DTUC. Operatorentry of CF-62,n will result in an FMS display ofthe SMOs available on the OCP DTUC (figure1-29). Operator entry of CF-62,n will result in theFMS loading the SMO indicated by n. The SMOwill reject a CF-62,n command to have the FMSload a new SMO and display the command inreverse video if any MIU has power applied. TheSMO will delay a CF-62,n command to have theFMS load a new SMO until the SMO has completednecessary fault processing and DTU Input/Outputif a Flight Data Record Cartridge DTUC isinstalled.

The SMO is automatically initialized and begins exe-cution immediately upon loading the SMO into theACUs. The procedure for loading the CALCM into theACUs is equivalent to loading any other SMO. TheCALCM, if it exists on the OCP DTUC, is identifiedby CALCM followed by optional version informationon the CF-62 menu. The status message SMO LOADCMPLT will be displayed on each MFD followingcompletion of a SMO load. The procedure for loadingthe CALCM, (the same as for loading any other SMO)is contained in T.O. 1B-52H-1-12.

[AMI] SMO Menu (CF-62)

SMO Load Menu (CF-62) (figure 1-29) allows the op-erator to select and load a SMO for left pylon, bay, orright pylon. The primary SMO is selected from theSMO’s loaded on left pylon, bay, or right pylon.

With the CF-62 menu displayed the operator willenter MDFY-11 to copy the following text to the bot-tom of the MFD for modification:

11 SMO LOAD LP__ BAY__ RP__

The operator will then enter the number of the de-sired SMO into the field that corresponds to thelocation that the SMO is to control and press theENTER key. The location: LP (left pylon), BAY, orRP (right pylon) is defined by the cursor which canbe moved using the arrow keys on the IKB.

To select a SMO as the primary SMO, Operator willenter CF-62x where x is either A, B or C to selectthe SMO that controls the left pylon, bay or rightpylon, respectively.

The procedure for loading the SMO, (the same asfor loading any other SMO) is contained in T.O.1B-52H-1-12.

CLSF MEM Erase (CF-64)

CF-64 commands erase of OAS classified memoryin the ACUs. The INS, WCE, and weapons will notbe powered off when CF-64 is commanded, but theFMS and SMO will immediately halt execution.Unlike the CF-67 command, there is no delay to al-low the SMO to record outstanding faults or powerdown all WCE and missiles. The procedure for era-sing the OAS classified memory is the same as con-tained in T.O. 1B-52H -1-12.

T.O. 1B-52H-34-2-9

1-66D Change 11

Data Record (CF-65)

CF-65 DATA RECORD indicates a CF-65 commandcan be used to record mission event data. When aSMO is loaded, the weapon modes, ranges, safe con-ditions and pertinent information is recorded alongwith FMS mission event data. Operator entry ofCF-65 will result in a DTUC/DTC recording of navi-gation and mission parameters and weapon modeswitches.

Erase PME Faults (CF-66)

CF-66 ERASE PME FAULTS indicates a CF-66command can be used to erase fault indicationsthat are no longer valid from the PME Status Dis-play (FRMT-6). The SMO will indicate to the FMSwhich of its fault indications should be erased. Op-erator entry of CF-66 will result in erasure of allpast fault indications shown on the PME StatusDisplay (FRMT-6, figure 1-34). Any faults for theMIUs, PDUC, and ECU will be cleared. Any exist-ing faults will cause a fault recording and the faultindication will continue to be displayed in reversevideo.

Shutdown (CF-67)

CF-67 SHUTDOWN indicates a CF-67 commandcan be used to shutdown FMS and SMO processingin the ACUs. Operator entry of CF-67 will result inthe shutdown of the FMS and SMO. The SMO willdelay compliance of the shutdown request until alloutstanding SMO faults have been recorded (Less[AMI] if an FDRC is installed) and until powerdown of all WCE and weapons is complete. The pro-cedure for shuting down the OAS with the CALCMloaded is the same as for any other shutdown and iscontained in T.O. 1B-52H-1-12.

ECU PWR ORIDE (CF-68)

Less [AMI] CF-68 ECU PWR ORIDE indicates aCF-68 command can be used to override faults asso-ciated with unavailability of Environmental ControlUnit (ECU) power. The current state of the overrideis displayed (ON or OFF). The SMO will not reject aCF-68 command.

[AMI] CF-68 ECU PWR ORIDE serves as an ON-OFF toggle for Environmental Control Unit (ECU)fault override. Only when the override is OFF canan ECU or ECU PWR Master Fault message be

displayed when applicable (See Section 7). The OASprovides the current state of the override to theSMO. The current state of the override is displayed(ON or OFF) on the FCP Supervision Menu (CF-6).

During MIU power on and initialization, the ECU,which supplies cooling air to the MIUs, is com-manded on. If aircraft status indicates ECU poweris not available when commanded, the MIU poweron process is terminated. Additionally, if an Envi-ronmental No-Go fault is detected from the ECU amaster fault will be displayed unless the operatoractivates the ECU fault override option.

Operator entry of CF-68 will command the OAS toactivate the ECU fault override option and ignoreany ECU faults. If an Environmental No-Go fault isdetected, an ECU master fault will be displayed. IfMIU and/or weapon power application is inhibitedbecause of a fault, the CF-68 command can beentered prior to re-applying MIU power and theECU fault will be ignored. The OAS will not reject aCF-68 command.

While in ECU fault override, the MIU may be oper-ated using a 30 minute on, 15 minute off, 30 minuteon cycle.

With an ECU fault present, damage toequipment may occur if MIU power remainson continuously as a result of selecting ECUPWR ORIDE.

Less [AMI] The ECU fault override option willbecome inactive only if the SMO is reloaded or if alogoff is commanded and the system is restarted.The current status of the ECU fault overrideoption, whether it is active or inactive, is displayed(ON or OFF) on the FCP Supervision Menu (CF-6)next to the 68 ECU PWR ORIDE menu item.

[AMI] If enabled, ECU power override can be dis-abled with a second entry of CF-68. If an ECU faultis still in effect, the operator will be given 1 minuteto recommand ECU power override with anotherCF-68 entry, otherwise weapon and WIU power willbe removed. A system logoff and restart of the sys-tem will also de-activate ECU power override.

T.O. 1B-52H-34-2-9

Change 10 1-66E

CF-6 FCP SUPERVISION MENULess [AMI]

B43136

66 1 STARTUP6 2 SMO MENU

6 4 CL SF MEM ERASE6 5 DATA RECORD6 6 ERASE PME FAUL TS6 7 SHUTDOWN6 8 ECU PWR OR I DE 4

CF − 6

FCP SUPV

PMD

[AMI]

6 FCP SUPV6 1 STARTUP

6666

4567

CDES

LARH

STAU

FAST

ED

MR

O

EEPW

MCMN

OE

ER

RASEDF AUL TS

− − − −CF - 6

B42827

6 2 SMO MENU

SMO :

PMD

6 9 SHUTDOWNA PR I MARY ACU6 9 SHUTDOWNB SECONDA Y A

FCP APPL I CAT I ONS

2 3

2 3

2 3

2 3

2 3

2 3

2 3

2 3

2 3

R CU

1PR I MARY

6 8 ECU PWR OR I DE 4

Figure 1-28. CF-6 FCP Supervision Menu (Sheet 1 of 2)

T.O. 1B-52H-34-2-9

1-66F Change 11


FUNCTION

1 Primary SMO Title NO

24 Character Label Primary SMO title.

2 FCP Application Title NO

24 Character Label Title of each non-SMO FCP application (FMS, CSP, and ODI) successfullyloaded into ACU memory.

24 Character Label (Blinking Video)

Title of each non-SMO FCP application (FMS, CSP, and ODI) that is in theprocess of being loaded into ACU memory.

24 Character Label (Reverse Video)

Title of each non-SMO FCP application (FMS, CSP, and ODI) that failed tosuccessfully load into ACU memory.

3 FCP Application Ver-sion/Revision

NO

6 Character Label Version/revision identifier of the associated FCP application.

4 ECU Power OverrideSwitch

NO

ON ECU power override is commanded.

OFF ECU power override is not commanded.

With an ECU fault present, damage to equipment may occur if MIU powerremains on as a result of selecting ECU PWR ORIDE. While in ECU poweroverride, the MIU may be operated using a 30 minute on, 15 minute off,30 minute on cycle.

Figure 1-28. CF-6 FCP Supervision Menu (Sheet 2 of 2)

T.O. 1B-52H-34-2-9

Change 10 1-66G

CF-62 SMO LOAD MENULess [AMI]

[AMI]

Figure 1-29. CF-62 SMO Load Menu (Sheet 1 of 2)

T.O. 1B-52H-34-2-9

1-66H Change 10


FUNCTION

1 SMO Title NO

24 Character Label(Blinking Video)

Title of the SMO assigned to the corresponding location while the SMOis being loaded.

24 Character Label Title of the SMO assigned to the corresponding location after the SMOhas been successfully loaded and the SMO is not the Primary SMO.

24 Character Label(Bright Underline)

Title of the SMO assigned to the corresponding location and that SMO isthe Primary SMO.

24 Character Label(Reverse Video)

Title of the SMO assigned to the corresponding location if the SMO hasfailed.

(Blank) No SMO is assigned to the corresponding location.

2 DTC SMO Title NO

24 Character Label Title of each SMO load module that is resident on the DTC.

(Blank) All SMO titles resident on the DTC have been displayed.

3 Version/RevisionIdentifier

NO

6 Character Label SMO Version/revision identifier.

(Blank) All SMO version/revision identifiers have been displayed.

4 SMO Menu No. YES

nn Number associated with the SMO that is assigned to the correspondinglocation and either loading of that SMO has not completed or the other twoassigned SMOs are not compatible. Displayed as an integer with a lead-ing blank.

nn(Reverse Video)

Number associated with the SMO that is assigned to the correspondinglocation and that SMO is not compatible with another assigned SMO.

(Blank) Displayed prior to a command to load a SMO at the corresponding loca-tion and after successful or unsuccessful completion of the SMO load.

Figure 1-29. CF-62 SMO Load Menu (Sheet 2 of 2)

T.O. 1B-52H-34-2-9

Change 10 1-67

MISSION SUPERVISION MENU (CF-8)

Less [AMI] The Mission Supervision Menu, com-manded by CF-8, is shown in figure 1-30. Much of thedata displayed on the Mission Supervision Menu is re-lated to the flight management system and is con-tained in T.O. 1B-52H-1-12. The SMO operation item,CALCM MSN DATA will be displayed, followed by theweapon group ID from the loaded weapon DTUC.

[AMI] The Mission Supervision Menu, commandedby CF-8, is shown in figure 1-30. The screen dis-plays the sortie, mission, and weapon group by loca-tion (left pylon, bay, and right pylon) loaded in theOAS. A further description of this menu is con-tained in T.O. 1B-52H-1-12.

Less [AMI] Read B-52 Sortie Mission Data Command(CF-81,n)

Operator entry of CF-81,n will initiate reading ofB-52 Mission n data. Before mission data can beloaded, the SMO must perform a Mission File For-mat check. If the Mission File Format is not inICSMS format or the operational mode is PLUS CT(Plus Count) and any MIUs are powered on or flex,direct or manual targeting are currently active theSMO will inhibit loading of the mission data andthe command will be displayed in reverse video.Loading a B-52 mission causes CALCMs targeted tolaunch points to be untargeted from the current as-signments and targeted to CALCM launch points inaccordance with the newly loaded mission.

NOTE

Telemetry power commands only functionwhen an OTL or an OTL PLUS CT missionis loaded. Removing telemetry power ishighly recommended prior to loading a non-OTL mission.

If the mission data that is loaded does not identify aMIU as the stores management interface unit at alocation where missiles were previously targeted,those missiles will not be able to be targeted by anytargeting process. The missiles will remain poweredand can be retargeted if a mission is loaded with aMIU as the stores management interface unit atthat location.

[AMI] B-52 Mission Data Load Display (CF-81)

The B-52 Mission Data Load Display (CF-81), fig-ure 1-25A, displays the primary SMO, loaded sor-tie, mission and primary SMO weapon group, num-ber of sorties available on the DTC, and a list ofmissions available for each sortie. The display alsoprovides the capability of selecting and loading thesortie and mission.

NOTE

The resident sortie and mission windows atthe top of the CF-81 display will remain blankor display the previously loaded sortie andmission identifiers until a mission/new mis-sion is loaded.

The operator can select a sortie from one of threeways, Either CF-DF to select the next sortie, CF-DB to select the previous sortie, or MDFY-1, enterthe desired sortie number and press the ENTERkey. The selected sortie number will be displayedalong with the sortie title and the associated mis-sions will be listed below them.

Operator entry of CF-81,n will initiate reading ofB-52 mission n data. The CALCM SMO will cause thecommand to be rejected and reverse highlighted if thecurrently loaded carrier mission is a Captive Carrymission and any MIU has power applied.

NOTE

Manual Targeting, Direct Targeting, or Auto-matic Targeting, if active, will be terminatedwhen a valid CF-81,n command is entered.

For an in-depth discussion of mission data opera-tions see MISSION DATA in Section VII.

T.O. 1B-52H-34-2-9

1-68 Change 11

[AMI] Weapon Group Selection Menu (CF-82A, CF-82B,CF-82C)

Operator entry of a CF-82x will display the CALCMWeapon Group Selection Menu, figure 1-30B, whenthe CALCM SMO is loaded at location x where x= Afor left pylon, B for bay, or C for right pylon. The Weap-on Group Selection Menu shows the sortie, missionand weapon group (for the SMO loaded at location x)currently loaded into the OAS. The display also de-picts the number of weapon groups available and alisting of the weapon groups.

There can be up to 72 available CALCM weapongroups on a DTC. The CF-82A, B, or C displays canshow a maximum of nine weapon groups at a time.CF-DF and CF-DB commands are used to page for-ward or back to the page containing the desired weap-on group.

The operator can select and load a weapon groupinto the OAS with a CF-82,nn or CF-82,n com-mand, where nn or n represents the weapon groupnumber as shown on the CF-82A, B, or C display.

NOTE

• Although CF-82A, CF-82B, and CF-82C aredepicted as LP, BAY, and RP WPNGROUPs, CF-82A, CF-82B, and CF-82Crepresent all the CALCM SMO controlledweapons. A CF-82,nn or CF-82,n commandfrom either the CF-82A, CF-82B, or CF-82Cdisplay will load the selected (nn or n)weapon group for all the CALCMs.

• The CF-82,nn and CF-82,n commands willbe ignored, if CF-82A, CF-82B, or CF-82Cis not displayed on the current MFD.

T.O. 1B-52H-34-2-9

Change 10 1-68A

CF-8 MISSION SUPERVISION MENULess [AMI]

[AMI]

- - - - CF - 8

B40816

B 5 2 DATA2S T I EORS ENTI DRE

S ENTI DRE B− 5 2 DATA 3

8 MSN SUPV

8 1

8 2 A L P WPN GRP8 2B BAY WPN GRP8 2C RP WPN GRP

SELECTED WEAPON GROUP

PMD

4

4

4

Figure 1-30. CF-8 Mission Supervision Menu (Sheet 1 of 2)

T.O. 1B-52H-34-2-9

1-68B Change 10


FUNCTION

1 Missile Mission ID NO

28 Character ASCII ID Missile mission data tape label.

(blank) When no missile DTUC is installed; title on mission data tape contains allblanks.

2 Sortie Title NO

28 Characters Title of the sortie loaded into the ACU.

(blank) No mission is loaded into the ACU or mission data load is in progress.

3 Mission Title NO

28 Characters Title of the mission loaded into the ACU.

4 Weapon Group Title NO

28 Characters Title of the weapon group assigned to the associated location (LP, Bay,RP).

28 Characters(Bright UnderlinedVideo)

Title of the weapon group assigned to the associated location (LP, Bay,RP). The SMO associated with the weapon group is primary.

Figure 1-30. CF-8 Mission Supervision Menu (Sheet 2 of 2)

T.O. 1B-52H-34-2-9

Change 10 1-68C

CF-81 MISSION DATA LOAD DISPLAY[AMI]


FUNCTION

1 Primary SMO Title NO

24 Character Label Primary SMO title.

2 Sortie Title NO

28 Character Label Title of the sortie from which the ACU resident mission was loaded.

(Blank) No mission is loaded into the ACU or mission data load is in progress.

3 Mission Title NO

28 Character Label Title of the mission loaded into the ACU.

(Blank) No mission is loaded into the ACU or mission data load is in progress.

4 PRIMARY SMOGROUP(Bright Underlined Video)

NO The text, PRIMARY SMO GROUP, will appear when a weapon grouphas been loaded for the primary SMO.

(Blank) No weapon group has been loaded for the primary SMO.

5 Primary SMO WeaponGroup

NO

28 Character Label Title of the weapon group loaded for the primary SMO.

(Blank) No weapon group has been loaded for the primary SMO.

Figure 1-30A. CF-81 Mission Data Load Display (Sheet 1 of 2)

T.O. 1B-52H-34-2-9

1-68D Change 10


FUNCTION

6 Sortie No. Select YES

n Selected sortie number (1 - 8).

7 DTC Sortie Count NO

0 No DTC is installed or no sorties are resident on the DTC.

n Number of sorties resident on the DTC that is installed.

8 Selected Sortie No. NO

n Selected sortie number (1-8).

9 Selected Sortie Title NO

28 Character Label Title of selected sortie on the DTC.

(Blank) No DTC is available.

10 DTC Mission Title NO

28 Character Label Title of each mission data file resident in the DTC for the selected sortie.

(Blank) No DTC is available.

Figure 1-30A. CF-81 Mission Data Load Display (Sheet 2 of 2)

T.O. 1B-52H-34-2-9

Change 10 1-69

CF-82A, CF-82B, CF-82C WEAPON GROUP SELECTION SCREEN[AMI]


FUNCTION


28 Character Label Title of the sortie resident in the ACU.


2 Selected Mission Title NO

28 Character Label Title of the mission resident in the ACU.


3 Selected WeaponGroup

NO

28 Character Label Title of the weapon group loaded into the ACU for the selected location.

(blank) No weapon group loaded into the ACU for the selected location.

4 Number of WeaponGroups Available

YES

n or nn Number of CALCM weapon groups available to load.

5 Weapon GroupNumber

NO

n or nn CALCM weapon group number.

6 Weapon GroupTitle

NO

28 Character Label CALCM weapon group title.

Figure 1-30B. CF-82A, CF-82B, CF-82C Weapon Group Selection Menu

T.O. 1B-52H-34-2-9

1-70 Change 10

AGM-86D FUZE DATA DISPLAY PAGE BACK COMMAND(CF-DB)

Displayed on the AGM-86D Fuze Data Input Dis-play (figure 1-30C), the message CF-DB = PAGEBACKWARD prompts the operator to key in CF-DBto command return to the previous targeting screenfrom the AGM-86D Fuze Data Input Display.

SEND TARGETING DATA COMMAND (CF-DD)

When flex or direct targeting screens are displayedand all required data has been entered, operatorentry of CF-DD will command the SMO to send theinput targeting data to the selected weapon andany backups associated with that weapon. TheSMO will reject a CF-DD command to send target-ing data and display the command in reverse videoif any of the following conditions exist:

• The Flex or Direct targeting screen is not onthe selected MFD.

• All required data has not been successfully entered.

• Flex or Direct targeting is not active.• [AMI] The CALCM assigned to the launch

point being flex or direct targeted is in LCD.

NOTE

• When CF-DD is entered the affected missilewill be considered untargeted (indicated byremoval of the underline in the targetingstatus) and cannot be launched until thetargeting data has been transferred to theCALCM.

• If the launch point being manually targetedis the current destination and has aCALCM already assigned to it, sequencingto the next destination will be inhibitedwhile in-range.

• [AMI] If the launch point being flex tar-geted is the current destination, sequencingto the next location will be inhibited whilein-range during the data transfer to the se-lected CALCM.

EXIT TARGETING MODE COMMAND (CF-DE)

When flex or direct targeting screen(s) are dis-played, Operator entry of CF-DE will exit the flexor direct targeting input displays without sendingflex or direct targeting data to the CALCM and itsbackups. The SMO will reject a CF-DE command toterminate flex or direct targeting and display thecommand in reverse video if an active flex or directtargeting screen is not on the selected MFD.

AGM-86D FUZE DATA INPUT DISPLAY COMMAND(CF-DF)

The Fuze Data Input Display (figure 1-30C) forAGM-86D missiles is commanded by CF-DF froman active Flex or Direct Targeting Input display(CF-557,nn or CF-558,nn). The Fuze Data Inputdisplay is used to review the fuze settings for theAGM-86D associated with the current target. Thedefault settings are contained in figure 1-30C. Theoperator may change the settings or accept the de-fault values.

The command will be rejected and reverse high-lighted if any of the following conditions exist:

• Neither flex or direct target modification is ac-tive.

• The CALCM associated with the direct targetis off or going off.

• The CALCM associated with the direct targetis not a warhead type 2 (penetrator).

• The data for the active targeting operation isnot valid.

WEAPON CONTROL PANEL BACKUP DISPLAY (CF-E)

CF-E, shown in figure 1-31, can be used by the op-erator to enter weapon commands in lieu of enter-ing the commands via the WCP. Input of commandsusing CF-E is contained in Section III of T.O.1B-52H-1-12.

NOTE

When any MIU power command is issuedusing a PCP/WCP backup display command(CF-E9A, CF-E9B, or CF-E9C), the corre-sponding PCP/MIU switches are deacti-vated until the enable hardware switchcommand, CF-E9D, has been entered.

T.O. 1B-52H-34-2-9

Change 10 1-70A

CF-DF AGM-86D FUZE DATA INPUT DISPLAY


FUNCTION

1 Targeting Type NO

FLEX Flex Targeting type.

DIR Direct Targeting type.

2 Direct Target Indication NO

D (Bright Underlined) Direct Targeting is active.

(blank) Direct Targeting is not active.

3 Launch Point/DirectTarget Number

NO

nn (Bright Underlined) Valid values 01-99 for Launch Point and 10-20 for Direct Target.

n_ Direct Target Number Valid values 1-9.

(blank) Neither Flex nor Direct Targeting is not active.

4 Fuze Mode YES

n Valid inputs 1=Void, 2=Solid, and 3=DOB. Default value of 1 (Void).

Figure 1-30C. CF-DF AGM-86D Fuze Data Input Display (Sheet 1 of 5)

T.O. 1B-52H-34-2-9

1-70B Change 10


FUNCTION

5 Number of Events YES

nn Valid range = 1 to 15. Default value of 01.

6 Backup Depth of Burial YES

nnn Valid range = 0 to 262 feet. Default value of 0 feet.

7 Fuze Function Distance YES

nnn Valid range of 0 to 262 feet. Default value of 6 feet.

8 Time After Impact YES

nnn Valid range = 0 to 255 milliseconds. Default value of 250 milliseconds.

9 Impact Velocity YES

nnnn Valid range of 492–1509 Feet per Second.Default value of 1299 Feet per Second.



11 Store Type NO


C CALCM is present.




12 Warhead Type NO




T.O. 1B-52H-34-2-9

Change 10 1-71


FUNCTION

13 CALCM Status NO













14 Ready To Launch Sta-tus

NO





NO










T.O. 1B-52H-34-2-9

1-72 Change 10


FUNCTION

16 Targeting Status (Cont)





NO SEE SECTION VII.








UNKNOWN(Reverse)












T.O. 1B-52H-34-2-9

Change 10 1-72A


FUNCTION

21 OTL Power Status(Cont)

NO




NO




NO

SAFE Flight termination system is disabled for selected CALCM.







ALTM (Reverse) CALCM Radar Altimeter (RA) No-Go or Radar Altimeter Equipment(RAE) No-Go for the selected CALCM.






NO



(blank) No backups for selected CALCM or no CALCM selected or MIU is powered off.


PMD

WPN JET TSEL =EE 1

PWR− − − −− − −W I UL P / =E 9A

/RP =E 9CEN HW SWCH=E 9D

− − − − − L AUNCH− − − − −/ MODE =E 7

=ECD =E 1 1

WPN PWRON =E 6 AOF F =E 6B

ENTER E 3’ ’ THEN ENTER ’ ’A TO SEL ECT OR 0 TO CL EAR’ ’− LOCAT I ON− − + − − − − − −STAT I ON− − − − − − − = E 3

− − − −CF −E

2

2

1

1

45 6

7

8 10 11 1 2 3 4 5 6 7 8

13 13 13 13 13

12

A60606

/ 21 =E 9BAYB

3

=E 1 0

SAF = 2BE EPRE = 2AA ERM

9

13

T.O. 1B-52H-34-2-9

1-72B Change 4

CF-E WEAPON CONTROL PANEL BACKUP DISPLAY


FUNCTION

1 ON (Bright Underlined) NO MIU power is on.

ON MIU power is off.

2 OFF (Bright Underlined)

NO MIU power is off.

OFF MIU power is on.

3 LCHRROT (Bright Underlined)

NO Launcher is rotating.

LCHRROT

Launcher is not rotating.

4 MSTRFAULT (Bright Underlined)

NO A master fault is displayed.

MSTRFAULT

A master fault is not displayed.

Figure 1-31. CF-E Weapon Control Panel Backup Display (Sheet 1 of 2)

T.O. 1B-52H-34-2-9

1-73


FUNCTION

5 AUTO (Bright Underlined)

NO Launch mode is automatic.

AUTO Launch mode is manual.

6 MAN (Bright Underlined )

NO Launch mode is manual.

MAN Launch mode is automatic.

7 MAN LAUNCH (Bright Underlined )

NO Manual launch has been commanded and launch is in progress.

MAN LAUNCH

Manual launch has not been commanded or has completed.

8 LP (Bright Underlined) NO Left pylon is selected.

LP Left pylon is not selected.

9 BAY (Bright Underlined)

NO Bay location is selected.

BAY Bay location is not selected.

10 RP (Bright Underlined) NO Right pylon is selected.

RP Right pylon is not selected.

11 ALL (Bright Underlined)

NO ALL station switch is selected.

ALL ALL station switch is not selected.

12 Station Number 1 Thru 8 (Bright Underlined )

NO Station is selected.

Station Number 1 Thru 8

Station is not selected.

13 A YES CF-E3 was the last command entered and the corresponding location orstation is currently selected. When ‘A’ is displayed, the location/stationidentifier above it will be displayed in bright/underline (B/U) video.

0 CF-E3 was the last command entered and the corresponding location orstation is not selected. When ‘0’ is displayed, the location/station identifierabove it will be displayed in normal (N) video.

(blank) CF-E3 was not the last command entered or corresponding location orstation is not currently selected.

Figure 1-31. CF-E Weapon Control Panel Backup Display (Sheet 2 of 2)

T.O. 1B-52H-34-2-9

1-74 Change 11

FORMAT (FRMT) DISPLAYS

The FRMT display displays the format menu shownin figure 1-33. FRMT-6 PME Status, FRMT-7 Weap-on Data, ([AMI] FRMT-7A LP Weapon Data,FRMT-7B Bay Weapon Data, FRMT-7C RP WeaponData, and FRMT-77 Stores Summary), FRMT-9Fixpoint Table, and FRMT-10 DEST/OAP table dis-plays are applicable to CALCM operations. Opera-tor entry of FRMT will cause the Format Menu tobe displayed on the selected MFD at the stationwhere the command was entered. The Format com-mands are shown in figure 1-32.

RADAR/ELECTRO - OPTICAL VIEWING SYSTEM (EVS)DISPLAYS

Discussion of the Radar and EVS displays, com-manded by FRMT-1, FRMT-2, FRMT-4, or FRMT-5,is contained in T.O. 1B-52H-1-12. The CALCM willprovide the destination label for these displayswhen the destination is a CALCM launch point.

PME STATUS DISPLAY (FRMT-6)

Figure 1-34 shows FRMT-6, the PME Status dis-play. Much of the data displayed on the PME Statusdisplay is common OAS equipment and is containedin T.O. 1B-52H-1-12. The following items areCALCM specific:

• Left Pylon, Right Pylon, and Bay MIU LRUsand their communication status.

• Power Drive Unit Control (PDUC), PDU,Launcher, and their communication status.

• ECU status.• PMD.

Operator entry of FRMT-6 will cause the PME Sta-tus display to be displayed on the selected MFD atthe station where the command was entered.

STATUS AND INVENTORY DISPLAY (FRMT-7)

The Status and Inventory display, commanded byFRMT-7 ([AMI] FRMT-7, FRMT-7A, FRMT-7B andFRMT-7C), is displayed by the SMO as depicted inFigure 1-35. This display is used to view WCE,weapon and ejector status data.

NOTE

• [AMI] FRMT-7 will display the Status and In-ventory display for the primary weapon SMOonly. If CALCM is not selected as the primarySMO, operator entry of FRMT-7A LP Weapondata, FRMT-7B Bay Weapon data, orFRMT-7C RP Weapon data will display all theCALCM weapons when the CALCM SMO isassigned to the corresponding location.

• [AMI] Although designated as left, bay, andright pylon weapon data displays,FRMT-7A, FRMT-7B, and FRMT-7C willdisplay all the CALCM weapons in thesame format as FRMT-7.

The items which can be reviewed on the CALCMStatus And Inventory display are listed as follows.

• Weapon identification.• Weapon warhead type.• Weapon status.• Ready-to-Launch status.• Targeting status.• Flex/direct targeting indicator.• Weapon faults.• Left, right, and bay MIU fault indications.• ECU fault indication.• Launcher fault indication.• Bay door fault indication.• Armament Interface Unit (AIU) fault

indication.• Launcher station.• Crypto Key availability status.• [AMI] DTC access indication during target

data retrieval.

Status and Inventory Display Request with SelectedStation Status (FRMT-7xy)

The Selected Station Status Display commanded byentry of FRMT-7xy, where x is the weapon location(A = Left Pylon, B = Bay and C = Right Pylon), andy is the weapon station (1 - 6 for the pylons and 1 -8 for the bay), is an augment to the CALCM Statusand Inventory display and is displayed by the SMOas depicted in figure 1-35. The CALCM SelectedStation Status Display also augments the Flex andDirect Targeting Input screens as depicted in fig-ures 1-26 and 1-27. This display is contained in theadvisory data area as shown in figure and is used toview detailed information about a particular wea-pon. The additional information displayed is listedas follows.

• Weapon identification.• Weapon warhead type.• Weapon status.• Ready-to-Launch status.• Targeting status.• Flex/direct targeting indicator.• Weapon faults.• Weapon location and station.• Ordnance alarm status.• Ejector status.• OTL status in windows.• Command/Destruct status.• Weapon fault indications for temperature,altimeter, and Inertial Navigation System (INS).• Location/Station and availability of backupweapons.

T.O. 1B-52H-34-2-9

Change 10 1-75

[AMI] Weapon Group Assignment Data Display(CF-DF or CF-DB From FRMT-7, 7A, 7B, 7C or 7xy)

The CALCM Group Assignment Data display (figure1-35A), is requested by paging forward (CF-DF) orbackward (CF-DB) from the Weapon Status and In-ventory displays (FRMT-7, 7A, 7B, 7C or 7xy). Inaddition to common FRMT-7 data, such as stationnumber, weapon type/subtype, and the launch point/target identifier, the CALCM Group AssignmentData display provides the weapon group id, selectedsortie, and selected B-52 mission. Paging forwardfrom FRMT-7 7A, 7B, 7C or 7xy, the CALCM GroupAssignment Data displays are presented in the orderof assigned CALCM locations; Left Pylon, Bay, RightPylon and back to the starting FRMT-7,7A, 7B, 7C or7xy display. Paging backward from the FRMT-7, 7A,7B, 7C or 7xy will present the CALCM Group Assign-ment Data displays in the reverse sequence.

NOTE

Although not displayed (overwritten withCALCM xy data), CF-DF and CF-DB com-mands are available on the FRMT-7xy dis-play, allowing the operator to request theCALCM Group Assignment Data displays.

[AMI] Stores Inventory Summary Display (FRMT-77)

Operator entry of FRMT-77 displays the Stores In-ventory Summary (figure 1-35B). The Stores Inven-tory Summary display provides generic store/weap-on information for all locations. All data on this dis-play is controlled by the CSP and none of the datafields are modifiable.

DESTINATION TABLE DISPLAY (FRMT-10,nn)

The destination table display, commanded byFRMT-10,nn is shown in figure 1-36. The SMO willprovide the destination label for the current or se-lected destination and the subsequent destinationas depicted in figure 1-36 when they are CALCMlaunch points. Entry of FRMT-10,nn will cause thedestination table display to be displayed on the se-lected MFD where the command was entered. Mod-ification of the current destination will not be per-mitted for a CALCM launch point (CALCMLP).

COMMAND DESCRIPTION

FRMT Format Menu Request.

FRMT-6 PME Status Display Request.

FRMT-7 CALCM Status and Inventory Display Request. ([AMI] Only when CALCM is primary SMO)

FRMT-7A [AMI] CALCM Status and Inventory Display Request.

FRMT-7B [AMI] CALCM Status and Inventory Display Request.

FRMT-7C [AMI] CALCM Status and Inventory Display Request.

FRMT-7xy CALCM Status and Inventory Display Request with Selected Station xy.

FRMT-77 [AMI] Stores Inventory Summary Display

FRMT-10,nn Destination Table Display. nn = current or selected destination

CF-DF or CF-DB FromFRMT-7, 7A, 7B, 7C or 7xy[AMI]

Weapon Group Assignment Data Display Request.

Figure 1-32. Format Commands

T.O. 1B-52H-34-2-9

1-76 Change 10

FRMT (FORMAT) MENULess [AMI]

MRF T MENU1 DRR2 RDR+PMD3 EVS4 EVS+PMD5 EVS FUL L6 PME STATUS7 WPN DATA8 MERG DATA9 XPT TBL

1 0

FRMT

TBL

+ XH POS I T I ON

PMD

A36687

EFEST OAPD /

[AMI]

FRMT MENU1 RDR2 RDR+PMD3 EVS4 EVS+PMD5 EVS FUL L6 PME STATUS

8 EMERG DATA9 F XPT TBL

1 0 DEST / OAP TBL

− −FRMT -

B41020

PMD

7 A L P WPN DATA7B BAY WPN DATA7C RP WPN DATA

+ XH POS I T I ON

DISPLAY IDENTIFIER(TYPICAL LOCATION ALL DISPLAY)

7 7 STORES SUMMARY

1

2

22

Figure 1-33. FRMT (Format) Menu (Sheet 1 of 2)

T.O. 1B-52H-34-2-9

Change 10 1-76A


FUNCTION

1 7 PRIMARYWEAPON DATA

NO A SMO is primary.

(blank) No SMO is primary.

2 CALCM SMO ID NO

28 Characters CALCM SMO is loaded at the respective location (LP, BAY, or RP).

28 Characters(Bright Underlined Video)

CALCM SMO is loaded at the respective location and it is the primarySMO.

(blank) No SMO is loaded at the respective location.

Figure 1-33. FRMT (Format) Menu (Sheet 2 of 2)

FRMT-6 PME STATUS DISPLAYLess [AMI]

PMD

BUS PME FL T BUS PME FL T BUS PME FL T BUS PME FL T

ACU A DEU R I U CD I UACU B RSC AHRS CSCPACU C RVR RDR RNMP

RNKB WCPDTU 1DTUDTUDTU

234

12

I MEI ME

NKB

I UGPSSAURPKBNPKB

PDUCA I U

RA

ECU

DVSE I U

− −FRMT − 6

B M I ULR

M I UM I U

1 2 3

3

1 2 31 2

A60609

1 233

PDU 3L NCR 3

ROOD

Figure 1-34. FRMT-6 PME Status Display (Sheet 1 of 3)

T.O. 1B-52H-34-2-9

1-76B Change 10

FRMT-6 PME STATUS DISPLAY [AMI]

PMD

BUS PME FL T BUS PME FL T BUS PME FL T BUS PME FL T

DEU R I U CD I URSC AHRS CSCPRVR RDR RNMPRNKB WCP

DTR 1DTR 2

12

I NUI NU

NKB

I UGPSSAUNPKB

A I URA

ECU

DVSE I U

− −FRMT - 6

3

B42829

ROOD

21

3

33

FC

CF - DF =PAGE FWD CF - DB=PAGE BACK

BAY1 2

33

33

1 2 3 1 2 3

456

8 8

7

L P RP

1 2


FUNCTION

1 Device Bus A Test NO

A The corresponding device has failed bus test as a remote terminal on bus A since the last time faults were cleared (CF-66), but is currentlypassing the bus A test.

A(Reverse Video)

The corresponding device is currently failing bus A test.

(blank) The corresponding device has not failed bus test as a remote terminal onbus A since the last time faults were cleared.

2 Device Bus C Test NO

C The corresponding device has failed bus test as a remote terminal on bus C since the last time faults were cleared (CF-66), but is currentlypassing the bus C test.

C(Reverse Video)

The corresponding device is currently failing bus C test.

(blank) The corresponding device has not failed bus test as a remote terminal onbus C since the last time faults were cleared.


T.O. 1B-52H-34-2-9

Change 10 1-76C


FUNCTION

3 Device Fault NO

X The corresponding device has failed since the last time faults werecleared (CF-66), but is currently not faulted.

X(Reverse Video)

The corresponding device is currently faulted.

(blank) The corresponding device has not failed since the last time faults werecleared.

4 Bay MIU Assignment NO

MIU MIU is assigned to the Bay Location. The fault fields apply to the MIU.

(blank) No MIU is assigned to the Bay Location.

5 Bay PDUC Assignment NO

PDUC PDUC is assigned to the Bay Location. The fault fields apply to the PDUC.

(blank) No PDUC is assigned to the Bay Location.

6 Bay PDU Assignment NO

PDU PDUC/PDU is assigned to the Bay Location. The fault fields apply to thePDU.

(blank) No PDUC/PDU is assigned to the Bay Location.

7 Bay CSRL Assignment NO

CSRL CSRL is assigned to the Bay Location. The fault fields apply to the CSRL.

(blank) No CSRL is assigned to the Bay Location.

8 MIU Pylon Assignment NO

MIU MIU is assigned to the designated Pylon Location. The fault fields applyto the MIU.

(blank) No MIU is assigned to the Pylon Location.


T.O. 1B-52H-34-2-9

1-76D Change 10

FRMT-7 AND FRMT-7xy STATUS AND INVENTORY DISPLAYLess [AMI]

[AMI]

1 / 1

2 1 5 2

3 2 6 3

4 3 7 4

5 4 8 5

6 6

− −FRM x y

ORDE J BKUPS

/

21

3

4 5

6

78

LP 2 BAY 1 BAY 5

RP 1

LP 3

LP 4

LP 5

LP 6

BAY 2 BAY 6

BAY 3 BAY 7

BAY 4 BAY 8

RP 2

RP 3

RP 4

RP 5

RP 6

10 11 12

9

10 13 14 10

15 4 5 7 168 17

18 1920 21

2223 24

25 25

B42830

3 6

SELECTED STATION STATUS

26

2T - 7

On L i n PMDe e

NOTE

• Details of the LEFT 1 station inventory display are shown, the other station datadisplays are identical.

• The Selected Station data at the bottom of the screen is displayed for FRMT-7xy.

Figure 1-35. FRMT-7 and FRMT-7xy Status and Inventory Display (Sheet 1 of 5)

T.O. 1B-52H-34-2-9

Change 10 1-76E


FUNCTION

1 Crypto Key Status NO

NO KEYS Crypto keys are not available and crypto key override is commanded.

NO KEYS (Reverse ) Crypto keys are not available and crypto key override is not commanded.

(blank) Crypto keys are available or retrieval of crypto keys has not yet occurred.

2 Store NO






3 Warhead Type NO

n (Bright) Weapon warhead type provided by missile data. (range 1 through 9 andA through F)

0 = Test.1 = Blast/Frag.2 = Penetrator.3 - 9 and A - F not assigned.


4 CALCM Status NO







Less [AMI] PL [AMI] CL CALCM plus count launch is currently active and not in either SIM mode.








T.O. 1B-52H-34-2-9

1-76F Change 10


FUNCTION

5 Ready To Launch Sta-tus

NO

SAF Weapon has not been provided Nav/RNav consent for launch from theSAFE/PREARM switch.

RDY Weapon has been provided Nav/RNav consent for launch from theSAFE/PREARM switch.



NO







nn Primary mission of a weapon has launch point or direct target n(n) de-fined, or Weapon has been launched at launch point or direct target n(n).

nn (Bright Underlined) Primary mission of a weapon has launch point or direct target n(n) de-fined and the weapon is targeted.





NO SEE SECTION VII.

9 Launcher Down Station NO

[x] Launcher station in the down position, updated once per second whenthe launcher is rotating. x = 1 - 8.

[x] (Reverse Video) Launcher station in the down position, updated once per second whenthe launcher is rotating. x = 1 - 8. Indexing mode is incorrect or PDUCcommunication lost.

(blank) Unable to determine launcher position.

10 MIU Fault Status NO

MIU (Reverse) A MIU communication failure or a MIU fault indication has been detectedwhich precludes missile launch for CALCMs communicating through that MIU.

(blank) The above condition does not exist.

11 ECU Fault Status NO

ECU (Reverse) A ECU fault indication has been detected.

(blank) The above condition has not been detected.


T.O. 1B-52H-34-2-9

Change 10 1-76G


FUNCTION

12 LNCHR Fault Status NO

LNCHR (Reverse) A launcher fault has been detected.

(blank) A launcher fault has not been detected.

13 Bay Door Fault Status NO

DOORS (Reverse) A bay door fault has been detected.

(blank) A bay door fault has not been detected.

14 AIU Fault Status NO An AIU fault has been detected.

AIU (Reverse) An AIU fault has been detected.

(blank) An AIU fault has not been detected.








LOCKD Ejector is locked for the selected CALCM.

UNLOCKD Ejector is unlocked for the selected CALCM.

UNKNOWN(Reverse)





CALCM has OTL payload.

(blank) Payload is not identified as an OTL, no CALCM is selected, or MIU is off.








T.O. 1B-52H-34-2-9

1-76H Change 10


FUNCTION


NO




NO

SAFE Flight termination system is disable for selected CALCM.



22 CALCM INSTemp Fault Status

NO



23 CALCM AltimeterFault Status

NO

ALTM (Reverse) CALCM CMRA No-Go or RAE No-Go for the selected CALCM.


24 CALCM INS Fault Sta-tus

NO



25 BackupLocation/Station

NO



(blank) No backups for selected CALCM, no CALCM selected or MIU powered off.

26 [AMI] DTC AccessStatus

NO

DTC (Blinking) SMO is accessing DTC.

DTC (Reverse Video) DTC access fault has occurred.

(blank) No DTC Access Fault is occurring and no DTC access fault has oc-curred.


T.O. 1B-52H-34-2-9

Change 10 1-77

CF-DF OR CF-DB FROM FRMT-7, 7A, 7B, OR 7CWEAPON GROUP ASSIGNMENT DATA DISPLAY

[AMI]


FUNCTION

1 CALCM Location NO

_LP Displayed weapon assignment data is for the left pylon.

BAY Displayed weapon assignment data is for the bomb bay.

_RP Displayed weapon assignment data is for the right pylon.


28 Character Label ID of sortie loaded into ACU.

(Blank) No sortie is loaded into ACU.

3 Selected Mission Title NO

28 Character Label ID of B-52 mission loaded into ACU.

(Blank) No B-52 mission is loaded in ACU.

Figure 1-35A. CF-DF or CF-DB Weapon Group Assignment Data Display (Sheet 1 of 3)

T.O. 1B-52H-34-2-9

1-78 Change 10


FUNCTION

4 Store Status NO

P Store present but unidentified.

C CALCM is present.

C (Bright UnderlinedVideo)

CALCM is present with OTL power on.

X Store is not present.

(blank) MIU power is off or (for group assignment only) Stations 7 and 8 do not existwhen pylon locations are selected or (for selected station status only) nostore is selected.

5 Warhead Type NO

n Weapon warhead type as provided from CALCM. (1 = Blast/Frag, 2 = Penetrator)

(blank) One of the following conditions exist:1. MIU power is off. 2. For group assignment only, Stations 7 and 8 do not exist when pylon loca-tions are selected.3. For selected station status only, no store is selected.4. Store is not a CALCM.5. Warhead type has not been received from CALCM at this station.


F (Bright UnderlinedVideo)

CALCM has been flex targeted.

F Flex targeted CALCM has been launched.

D (Bright UnderlinedVideo)

CALCM has been direct targeted.

D Direct targeted CALCM has been launched.

(blank) One of the following conditions exist:1. CALCM has been powered on, but not flex or direct targeted.2. MIU power is off.3. CALCM power is off.4. Store is not a CALCM.5. For group assignment only, Stations 7 and 8 do not exist when pylon loca-tions are selected.6. For selected station status only, no store is selected.

7 Launch Point/DirectTarget

NO

nn (Bright UnderlinedVideo)

Primary mission of a weapon has launch point or direct target n(n) definedand the weapon is targeted.

nn Primary mission of a weapon has launch point or direct target n(n) definedand the weapon has been launched.


T.O. 1B-52H-34-2-9

Change 10 1-79


FUNCTION

7 (Cont) G GPS initialization data has been loaded into the weapon, but no mission isassigned.


(blank) One of the following conditions exist:1. CALCM has been powered on, but has not yet been targeted.2. MIU power is off.3. CALCM power is off.4. Store is not a CALCM.5. For group assignment only, Stations 7 and 8 do not exist when pylon loca-tions are selected.6. For selected station status only, no store is selected.

8 Bay Station 7 NO

7 Display is for the bay. This is blank when a pylon is selected.

(blank) Pylon is selected.

9 Bay Station 8 NO

8 Display is for the bay. This is blank when a pylon is selected.

(blank) Pylon is selected.

10 Selected WeaponGroup

NO

28 Characters ID of weapon group, loaded into ACU and used for targeting data.

(Blank) No targeting data is currently assigned to the weapon.


T.O. 1B-52H-34-2-9

1-80 Change 10

FRMT-77 STORES INVENTORY SUMMARY DISPLAY [AMI]

− −FRMT

B42831

1 1 11 2 3 4 5

2

3

4

5

6

7

8

2 3 4 5

2 3 4 5

2 3 4 5

2 3 4 5

2 3 4 5

2 3 4 5

2 3 4 5

3 4 521

2

3

4

5

6

7

8

2 3 4 5

- 7 7

2 3 4 5

2 3 4 5

2 3 4 5

2 3 4 5

2 3 4 5

2 3 4 5

321 4 5

2

3

4

5

6

7

8

2 3 4 5

2 3 4 5

2 3 4 5

2 3 4 5

2 3 4 5

2 3 4 5

2 3 4 5

PMD


FUNCTION

1 SMO Title NO

17 Characters SMO title assigned to the location (truncated to 17 characters).

17 Characters (BrightUnderlined Video)

Primary SMO title (truncated to 17 characters)

(blank) No SMO assigned to the Location.

2 Weapon Type NO

aa Weapon type as provided by the loaded aircraft mission data (No SMOloaded at the location or the SMO cannot confirm the actual weapontype). For CALCM, aa = C1 (Blast/Frag warhead) or C2 (Penetrator war-head)

aa (Bright UnderlinedVideo)

Weapon type as provided by the loaded aircraft mission data, that hasbeen confirmed by the SMO with aircraft mission data.

aa (Reverse Video) Weapon type as provided by the loaded aircraft mission data, that has notbeen confirmed by the SMO with aircraft mission data.

(blank) Weapon data is not being provided by loaded aircraft mission data or noaircraft mission data is loaded.

Figure 1-35B. FRMT-77 Stores Inventory Summary Display(Sheet 1 of 2)

T.O. 1B-52H-34-2-9

Change 10 1-81


FUNCTION

3 Weapon Status NO

aa Two-digit weapon status (e.g. ON, OF, CA, AL, GO) as provided by theparticular weapon SMO. Refer to the applicable weapon manual for de-tails of display.

(blank) No SMO assigned to the location, or no weapon status has been providedby the SMO.

4 Direct Target/Launch Point

NO

nn or Dn Launch point number (nn) or direct target number (Dn) assigned as pro-vided by the SMO. Refer to the applicable weapon manual for details ofdisplay.

(blank) No SMO assigned to the location, or no direct target or launch point hasbeen provided by the SMO.

5 Time To In-Range NO

mm Time-to-go to In-Range as provided by the SMO that is 10 minutes orgreater (up to 60 minutes). Refer to the applicable weapon manual for de-tails of display.

m:ss Time-to-go to In-Range as provided by the SMO, that is less than 10 min-utes. And, highlight mode as provided by the SMO. Refer to the applicableweapon manual for details of display.

(blank) No SMO assigned to the location, or no time to In-Range provided by theSMO, or SMO has decided it is not applicable.

Figure 1-35B. FRMT-77 Stores Inventory Summary Display(Sheet 2 of 2)

P DM

1234

−OAP 1

234

NNNN

N30000

7 4 1 . 9 9o

o

o

o

o

0 0 . 0 00 0 . 0 00 0 . 0 00 0 . 0 0

EEEE

W 9 7 17 . 9 80000

0000

0000

.

.

.

.

0000

0000

o

o

o

o

o

1 4 9 0 ’’’’’

0000

0000

0 : 0 4 : 5 9

1234

OAP 1234

NNNN

N30000

8 2 4 . 0 0o

o

o

o

o

0 0 . 0 00 0 . 0 00 0 . 0 00 0 . 0 0

EEEE

W 9 8 4 7 . 9 80000

0000

0000

.

.

.

.

0000

0000

o

o

o

o

o

1 5 2 0 ’’’’’

0000

0000

0 : 1 9 : 5 9

− −FRMT 0

DESTINATIONSEQUENCE NO.

A60611DESTINATION SEQUENCE NO.

,

1

1

1

T.O. 1B-52H-34-2-9

1-82

FRMT-10,nn DESTINATION TABLE DISPLAY


FUNCTION

1 CALCMLP NO CALCM launch point

Figure 1-36. FRMT-10,nn Destination Table Display

T.O. 1B-52H-34-2-9

Change 10 1-83

SMO PROGRAM (PRGM) DISPLAY

The SMO PRGM commands are listed in figure1-37. The CALCM launch point program display,commanded by PRGM- or PRGM-nn, is displayedby the SMO as depicted in figure 1-38 (Current AndNext Destination Not a CALCM Launch Point), fig-ure 1-39 (Auto SAIR When Current or Next Des-tination is a CALCM Launch Point), figure 1-40(Manual SAIR When Current Destination is aCALCM Launch Point), and figure 1-41 (DirectLaunch Mode). Using the PRGM- command causesthe FMS to display the current destination at thetop of the screen and the next destination at thebottom. Using the PRGM-nn command, where nn isa destination number from 1 to 99, causes the FMSto display the current destination at the top of thescreen and the destination indicated by nn, even ifit is the same as the current destination, at the bot-tom. This display is used to view launch informa-tion about the weapon associated with a CALCMlaunch point when it is the current destination, orwhen it is the next destination if the current des-tination is not a CALCM launch point.

The CALCM launch point program display onlyprovides launch information for the current or thenext destination, as applicable, and not the selecteddestination. Information included in the display islisted below. The second item below is displayed onthe program display regardless of whether the cur-rent or next destination is a CALCM launch point,although blanks will be displayed in windowswhere no direct targets have been designated.

• Cruise missile launch point mnemonic for thecurrent destination and the next or selected des-tination when the respective destination is aCALCM launch point.

• Direct targeting status for up to twenty weapons.

• SAIR mode, status, range (manual SAIR), andtime to go (automatic ranging).

• Unsafe condition.• Automatic retargeting enable status.• Location and station of weapon to be

launched.• Launch countdown timer, manual launch re-

quirements, and launch countdown hold timer.• Magnetic course to cruise missile first way-

point (manual SAIR).• Bay door status.• PMD.

CALCM DIRECT TARGET PROGRAM DISPLAY

The CALCM direct target program display, com-manded by PRGM-Dnn, where nn is the direct tar-get number (1-20), and is displayed by the SMO asdepicted in figure 1-41. Using the PRGM-Dnn com-mand causes the FMS to display the current des-tination at the top of the screen and the next des-tination at the bottom. This display is used to viewlaunch information about the weapon associatedwith a CALCM direct target nn.

Information included in the display is listed below.Direct targeting status for up to twenty weapons isalways displayed on the program display, althoughblanks will be displayed for windows where no di-rect targets have been designated.

• Cruise missile launch point mnemonic for thecurrent destination and the next or selected des-tination when the respective destination is aCALCM launch point.

• Direct targeting status for up to twenty weap-ons.

• SAIR mode, status, and range.• Unsafe condition.• Automatic retargeting enable status.• Location and station of weapon to be

launched.• Launch countdown timer, manual launch re-

quirements, and launch countdown hold timer.• Pre-target Steering Waypoint turn angle.• Magnetic course to pre-target steering way-

point.• Bay door status.• PMD.

The SMO will reject a PRGM-Dnn command anddisplay it in reverse video under the following con-ditions:

• Invalid direct target designation is selected.• A weapon is in launch countdown.• [AMI] The CALCM SMO is not primary.

Once Direct Launch Mode is activated, it will re-main active until one of the following occurs:

• The associated weapon is launched.• Clear direct launch mode is commanded.• There is no longer a valid CALCM assigned to

the active direct target, Dnn.

Exit Direct Launch Mode.

Operator entry of CLR-D will exit Direct LaunchMode that was entered by Operator entry of PRGM-Dnn. If not in Direct Launch Mode when CLR-D isentered, the command will be displayed in reversevideo.

T.O. 1B-52H-34-2-9

1-84 Change 10

WEAPON TARGETING COMMANDS

Before any CALCMs can be launched, the Operatormust initiate the transfer of targeting informationto the missile from the weapon DTUC/DTC. Afterinitial targeting of the CALCMs, the Operator can

1) Reinitiate targeting of all weapons,2) Manually target a CALCM to a specified launchpoint,3) Modify a mission by using the Flex targeting op-tion, or4) Direct target a CALCM.

The commands to carry out these processes are de-scribed in the following paragraphs. For all target-ing commands the targeting information will alsobe provided for up to two backup weapons, if avail-able. After a mission is targeted to a primary weap-on and available backups, there can be no newbackup weapons added for that mission without re-initiating targeting or manually targeting the mis-sion (options 1 and 2 above).

COMMAND DESCRIPTION

PRGM-,nn Launch Point Program Display

PRGM-Dnn Direct Target Program Display

CLR-D Exit Direct Launch Mode

Figure 1-37. SMO Program Commands

T.O. 1B-52H-34-2-9

1-85

SMO LAUNCH POINT PROGRAM DISPLAY (PRGM)(CURRENT AND NEXT DESTINATION IS NOT A CALCMLP)


FUNCTION

1 Direct Target Number Direct Target Number nn= 1 to 20.

Dnn Direct target has been assigned to weapon and target data is loaded andverified, where nn = 1 to 20 from left to right across screen.

Dnn (Blinking) PRGM-Dnn is entered, where nn = 1 to 20 from left to right acrossscreen.

Dnn (BrightUnderlined)

Direct target is in range, where nn = 1 to 20 from left to right acrossscreen.

Dnn (BrightUnderlined Blinking)

Direct target is in range and PRGM-Dnn is entered, where nn = 1 to 20from left to right across screen.

(blank) No weapons are assigned to the direct target or all assigned weaponshave been released.

Figure 1-38. SMO Launch Point Program Display (PRGM)

T.O. 1B-52H-34-2-9

1-86

SMO LAUNCH POINT PROGRAM DISPLAY (PRGM) (AUTO SAIR)(CURRENT OR NEXT DESTINATION IS A CALCMLP)


FUNCTION

1 CALCMLP NO Current destination is a CALCM launch point.

2 Direct Target Number

Dnn

Direct Target Number nn= 1 to 20.Direct target has been assigned to weapon and target data is loaded andverified, where nn = 1 to 20 from left to right across screen.







Figure 1-39. SMO Launch Point Program Display (PRGM)(Auto SAIR) (Sheet 1 of 3)

T.O. 1B-52H-34-2-9

Change 10 1-87


FUNCTION

3 SAIR NO CALCM is not within range and no launch restrictions exist.

SAIR (Bright Underlined)

CALCM is within range and no launch restrictions exist.

SAIR (Reverse Blinking)

Safe launch restrictions exist.

(blank) No CALCM is associated with the current and next destinations and di-rect launch mode is not active.

4 mm:ss NO When automatic SAIR is active, time to go to SAIR is displayed in min-utes and seconds when greater than 00:00. If time to go exceeds 59:59then 59:59 is displayed.Display range = 00:01 through 59:59

[AMI] FAR Either (1) Manual is active and the carrier is too far from the missile’s firstwaypoint to launch or (2) Direct SAIR is active and the carrier is too farfrom the target to launch.

[AMI] CLOSE Direct SAIR is active and carrier is too close to the target to load.

(blank) One of the following conditions exist:1. Automatic SAIR is active and time to go to SAIR is less than 00:002. [AMI] Direct SAIR is active and carrier is in range.3. [AMI] Manual SAIR is active and carrier is in range.4. Less [AMI] Direct or Manual SAIR is active.5. There is no current event.

5 BRG CHG (ReverseBlinking)

NO During direct launch mode, steer point turn angle exceeds CALCM capa-bility for selected direct target.

CLIMB (ReverseBlinking)

Aircraft altitude too low for safe release.

LEVL_OFF (ReverseBlinking)

Aircraft Z velocity and/or Z acceleration is too high for safe release.

ACCEL (ReverseBlinking)

Aircraft true airspeed is too slow for safe release.

PITCH (ReverseBlinking)

Aircraft pitch angle or pitch rate is unsafe for release.

ROLL (ReverseBlinking)

Aircraft bank angle or roll rate is unsafe for release.

YAW (ReverseBlinking)

Aircraft yaw rate is unsafe for release.

(blank) No Launch Restrictions Exist, or no CALCM is associated with the cur-rent and next destinations and direct launch mode is not active.

6 AUTO RETGT (BrightUnderlined)

NO Current or next destination is a CALCM launch point or direct launchmode is active.

(blank) None of the above.


T.O. 1B-52H-34-2-9

1-88 Change 10


FUNCTION

7 ON NO Auto retargeting is enabled, not inhibited and either backup is launchablewhen the current or next destinations are a CALCM launch point or directlaunch mode is active.

ON (Reverse) The current or next destination is a CALCM launch point or direct launchmode is active and auto retargeting is enabled, but inhibited becauseboth backups for the weapon associated with the next weapon event arenot launchable.

OFF Auto retargeting mode is disabled and the current or next destination is aCALCM launch point or direct launch mode is active.


8 xy NO Location and station of associated weapon when the current or next destina-tion is a CALCM launch point or direct launch mode is active.


(blank) (Reverse) Current or next destination is a CALCM launch point and no weapon isassigned.

(blank) Current or next destination is not a CALCM launch point.

9 MAN LNCH MODE(Bright)

NO Manual launch mode but not in launch countdown when the current ornext destination is a CALCM launch point or direct launch mode is active.

COUNTDOWN x (Bright)

Launch countdown. x equals time to go in seconds (1 thru 5 seconds).

HOLD xx Launch countdown hold is active where xx is countdown seconds in hold(1 thru 45 seconds).


10 BBD (Bright Underlined)



11 OPEN NO Bomb bay doors are open and current or next destination is a CALCMlaunch point or direct launch mode is active.

CLSD Bomb bay doors are closed and current or next destination is a CALCMlaunch point or direct launch mode is active.

DOORS (Reverse) Door fault is detected and current or next destination is a CALCM launchpoint or direct launch mode is active.

UNLTCH Door status is indeterminate and current or next destination is a CALCMlaunch point or direct launch mode is active.


12 CALCMLP NO Next or selected destination is a CALCM launch point.


T.O. 1B-52H-34-2-9

1-89

SMO LAUNCH POINT PROGRAM DISPLAY (PRGM)(MANUAL SAIR)(CURRENT DESTINATION IS A CALCMLP)


FUNCTION

1 CALCMLP NO Current destination is a CALCM launch point.


Dnn

Direct Target Number nn= 1 to 20.Direct target has been assigned to weapon and target data is loaded andverified, where nn = 1 to 20 from left to right across screen.







Figure 1-40. SMO Launch Point Program Display (PRGM)(Manual SAIR) (Sheet 1 of 4)

T.O. 1B-52H-34-2-9

1-90 Change 10


FUNCTION

3 MAN NO Manual SAIR mode and not in range.

MAN (Bright Underlined)

Manual SAIR mode and safe and in range.

MAN (Reverse Blinking)

Manual SAIR mode and safe launch restrictions exist.

(blank) MAN SAIR is not active.

4 SAIR NO CALCM is not within range and no launch restrictions exist.






5 BRG CHG (ReverseBlinking)

NO During direct launch mode, steer point turn angle exceeds CALCM capa-bility for selected direct target.














6 AUTO RETGT (BrightUnderlined)




T.O. 1B-52H-34-2-9

1-91


FUNCTION

7 ON NO Auto retargeting is enabled, not inhibited and either backup is launchablewhen the current or next destinations are a CALCM launch point or directlaunch mode is active.




8 xy NO Location and station of associated weapon when the current or next destina-tion is a CALCM launch point or direct launch mode is active.


(blank) (Reverse) Current or next destination is a CALCM launch point and no weapon isassigned.


9 MAN LNCH MODE(Bright)

Manual launch mode but not in launch countdown when the current ornext destination is a CALCM launch point or direct launch mode is active.



HOLD xx Launch countdown hold is active where xx is countdown seconds in hold(1 thru 45 seconds).


10 SAIR RNG NO Direct launch mode or manual SAIR is active, range data is available,and not in range.

SAIR RNG (Bright Underlined)

Direct launch mode or manual SAIR is active, range data is available,and in range.

SAIR RNG (Reverse) Direct launch mode or manual SAIR is active and range data is not avail-able.

(blank) Direct launch mode or manual SAIR is not active.

11 xxx NO Distance from A/C present position along ground track to enter SAIRRange boundary in NM for selected weapon in direct or manual SAIRmode.(xxx = 999 for range >= 999).

xxx (Bright Underlined) Distance from A/C present position along ground track to exit SAIRRange boundary in NM for selected weapon in direct or manual SAIRmode.(xxx = 999 for range >= 999).



T.O. 1B-52H-34-2-9

1-92


FUNCTION

12 MC (Bright Underlined) NO Direct launch mode or manual SAIR is active and data is available forcalculations.

MC (Reverse) Direct launch mode or manual SAIR is active and data is not available forcalculations.


13 xxx° NO Magnetic course from A/C present position to calculated pre-target steer-ing waypoint for active direct launch mode. Magnetic course from A/Cpresent position to first cruise missile waypoint in manual SAIR mode.Display range = 0 to 359 degrees.


14 BBD (Bright Underlined)



15 OPEN NO Bomb bay doors are open and current or next destination is a CALCMlaunch point or direct launch mode is active.





16 CALCMLP NO Next or selected destination is a CALCM launch point.


T.O. 1B-52H-34-2-9

Change 10 1-93

SMO LAUNCH POINT PROGRAM DISPLAY (PRGM)(DIRECT TARGET LAUNCH MODE)


FUNCTION

1 Destination Type NO

CALCMLP Current destination is a CALCM launch point.


Dnn

NODirect target nn has been assigned to weapon and target data is loadedand verified, where nn = 1 to 20 from left to right across screen.


Direct target nn is in range, where nn = 1 to 20 from left to right acrossscreen.


Figure 1-41. SMO Launch Point Program Display (PRGM) (Direct Target) (Sheet 1 of 5)

T.O. 1B-52H-34-2-9

1-94 Change 10


FUNCTION

3 MAN/DIR Mode NO

MAN Manual SAIR mode and not in range.

MAN (Bright Underlined)

Manual SAIR mode and safe and in range.

MAN (Reverse Blinking)

Manual SAIR mode and safe launch restrictions exist.

DIR Direct Launch mode and not in range.

DIR (Bright Underlined)

Direct Launch mode and safe and in range.

DIR (Reverse Blinking)

Direct Launch mode and safe launch restrictions exist.

(blank) Neither Manual SAIR nor Direct Launch modes are active.

4 SAIR Status NO

SAIR CALCM is not within range and no launch restrictions exist.






5 Launch Restrictions NO

BRG CHG (ReverseBlinking)

During direct launch mode, steer point turn angle exceeds CALCM capa-bility for selected direct target.














Figure 1-41. SMO Launch Point Program Display (PRGM)(Direct Target) (Sheet 2 of 5)

T.O. 1B-52H-34-2-9

Change 10 1-95


FUNCTION

6 Auto Retarget StatusLabel

NO

AUTO RETGT (BrightUnderlined)

Current or next destination is a CALCM launch point or direct launchmode is active.


7 Auto Retarget Status NO

ON Auto retargeting is enabled, not inhibited and either backup is launchablewhen the current or next destinations are a CALCM launch point or directlaunch mode is active.




8 [AMI] Flex/Direct Tar-get Indicator

NO

F CALCM for current weapon event has been flex targeted.

D CALCM for current weapon event has been direct targeted.

(blank) Either there is no current weapon event or the CALCM for the currentweapon event has not been flexed or direct targeted.

9 [AMI] Launch Point/Direct Target Number

NO

nn Launch point or direct target number for CALCM assigned to currentweapon event.

(blank) There is no current weapon event.

10 Weapon Location/Station

NO

xy Location and station of associated weapon when the current or next destina-tion is a CALCM launch point or direct launch mode is active.


(blank)(Reverse Video)

Current or next destination is a CALCM launch point and no weapon isassigned.



T.O. 1B-52H-34-2-9

1-96 Change 10


FUNCTION

11 Launch Mode NO

MAN LNCH MODE(Bright)

Manual launch mode but not in launch countdown when the current ornext destination is a CALCM launch point or direct launch mode is active.



HOLD xx Launch countdown hold is active where XX is countdown seconds in hold(1 thru 45 seconds).


12 [AMI] Auto Launcher Rotation Status

NO

AUTOROT INHIB (Reverse Video)

Auto launcher rotation is inhibited.

(blank) Auto launcher rotation is not inhibited.

13 ∆ BRG Label NO

∆ BRG (Bright Underlined)

PRGM-Dnn is entered.


14 Steering WaypointTurn Angle

NO

xnnn° Direct launch mode is active and the absolute value of the pre-targetsteering waypoint turn angle is less than or equal to 150o, where x = R for positive angle; L for negative. nnn = abs value of turn angle.

xnnn° (Reverse) Direct launch mode is active and the absolute value of the pre-targetsteering waypoint turn angle is not less than or equal to 150o, where x = R for positive angle; L for negative. nnn = abs value of turn angle.

(blank) Direct launch mode is not active.

15 SAIR Range Status NO

SAIR RNG Direct launch mode or manual SAIR is active, range data is available,and not in range.

SAIR RNG (Bright Underlined)

Direct launch mode or manual SAIR is active, range data is available,and in range.

SAIR RNG (Reverse) Direct launch mode or manual SAIR is active and range data is not avail-able.



T.O. 1B-52H-34-2-9



FUNCTION

16 Distance to SAIREntry/Exit

NO

xxx Distance from A/C present position along ground track to enter SAIRRange boundary in NM for selected weapon in direct or manual SAIRmode.(xxx = 999 for range >= 999).

xxx (Bright Underlined) Distance from A/C present position along ground track to exit SAIRRange boundary in NM for selected weapon in direct or manual SAIRmode.(xxx = 999 for range >= 999).


17 Mag Course Label NO

MC (Bright Underlined) Direct launch mode or manual SAIR is active and data is available forcalculations.

MC (Reverse) Direct launch mode or manual SAIR is active and data is not available forcalculations.


18 Mag Course to Weapon Waypoint

NO

xxx° Magnetic course from A/C present position to calculated pre-target steer-ing waypoint for active direct launch mode. Magnetic course from A/Cpresent position to first cruise missile waypoint in manual SAIR mode.Display range = 0 to 359 degrees.


19 Bomb Bay Door Label NO

BBD (Bright Underlined)

Current or next destination is a CALCM launch point or direct launchmode is active.


20 Bomb Bay Door Status NO

OPEN Bomb bay doors are open and current or next destination is a CALCMlaunch point or direct launch mode is active.





21 CALCMLP Label NO

CALCMLP Next or selected destination is a CALCM launch point.


T.O. 1B-52H-34-2-9

Change 10 2-1

Normal Aircrew Procedures section II


GENERAL 2-3

PREFLIGHT PROCEDURES 2-3

BEFORE EXTERIOR INSPECTION (RN/N) 2-3

EXTERIOR INSPECTION (RN/N) 2-3

PYLONS 2-3

BOMB BAY INTERIOR 2-6

INTERIOR INSPECTION 2-9

AFTER ENGINE START (Power and Cooling Air Available) 2-10

Less [AMI] CALCM SMO LOADING (N) 2-10

[AMI] CALCM SMO LOADING (N) 2-10

WEAPON CHECK (RN) 2-10

CALCM INFLIGHT PROCEDURES 2-11

MISSILE POWER APPLICATION (N) 2-11

MISSILE TARGETING (N) 2-13

Less [AMI] TARGET/RETARGET ALL 2-13

[AMI] TARGET/RETARGET ALL 2-14A

AUTO RETARGET INHIBIT/ENABLE 2-14C

Less [AMI] MISSION SUBSTITUTION (INDIVIDUAL MISSILES) 2-14D

[AMI] MISSION SUBSTITUTION (INDIVIDUAL MISSILES) 2-15

MANUAL RETARGETING (INDIVIDUAL MISSILES) 2-16

FLEX TARGETING (INDIVIDUAL MISSILES) 2-17

DIRECT TARGETING (INDIVIDUAL MISSILES) 2-18

T.O. 1B-52H-34-2-9

2-2 Change 10


LAUNCH PROCEDURES 2-19

MISSILE PREPARATION FOR LAUNCH 2-19

MISSILE LAUNCH (N) 2-21

LAUNCH ABORT/MISSION ABORT/RETAINED MISSILE(S) 2-27

PRELANDING PROCEDURES 2-29

BEFORE DESCENT 2-29

AFTER LANDING PROCEDURES 2-29

AFTER PARKING 2-29

GROUND SAFEING PROCEDURES (PYLON MISSILES) (RN/N) 2-30

GROUND SAFEING PROCEDURES (BAY MISSILES) (RN/N) 2-31

GROUND SIT/MIT PROCEDURES 2-32

T.O. 1B-52H-34-2-9

Change 10 2-3

GENERAL

Detailed operating procedures for CALCM missilesare contained in this section.

The step procedures are the call-response type inwhich code letters appear after each response to in-dicate which member of the crew is to accomplish

that step. Identification symbols are used after eachresponse, except when the entire checklist is accom-plished by a single crewmember, such as pilot ornavigator. Code letters are as follows: (P) pilot, (CP)copilot, (N) navigator, and (RN) radar navigator.

NOTE

[AMI] On missions with mixed weapons loads, the CALCM SMO mustbe loaded and selected as the primary SMO in order to power, align,target, range and launch CALCMs.

PREFLIGHT PROCEDURES

NOTE

When missiles are aboard, check the AFTO Form 781 for an entry indi-cating a weapons preflight was accomplished. The wing weapons offi-cer, alternate wing weapons officer or a designated representative willperform a complete weapons and bomb bay preflight during the main-tenance post-load checks.

BEFORE EXTERIOR INSPECTION (POWER OFF) (RN/N)

1. Jettison Power & Jettison Control Circuit Breakers – Out

2. Pilot’s Munitions Consent Panel: (RN)

a. LOCK-UNLOCK Switch – Guard closed

3. PYLON JETTISON CONSENT Switches (2) – Guards closed

4. Weapon Control Panel: (N)

a. PYLON LOCK-UNLOCK Switch – Guard closed

b. WPN JETTISON Switch – Guard closed

c. NUCLEAR LOCK-UNLOCK Switch – Guard closed

5. Proceed to aircraft EXTERIOR INSPECTION (POWER OFF) checklist (step 1) (RN/N)

EXTERIOR INSPECTION (POWER OFF) (RN/N)

PYLONS

1. Pylons and Pylon Missiles:

a. Pylon General Condition – Checked

Check general appearance of pylon for surface damage or irregularities. Ensure pylon accesspanels are secure. Check for evidence of fuel drainage or leakage from wing tanks or fuel fittings.

T.O. 1B-52H-34-2-9

2-4 Change 6

b. Pylon Jettison Safeing Pin – Check removed

c. AGM-86C/D Missiles – Checked

(1) Warhead Arming Device Safety Pin & Streamer – Checked removed

Check the Warhead Arming Device safeing pin is removed and the status indicator is SAFE(a white “S” on a green background)

NOTE

Omit Warhead Arming Device check if OTL payload is installed.

(2) Pitot-Static Probe Cover & Streamers – Checked removed

(3) Temperature Sensor Cover and Streamer – Checked removed

On AGM-86C missiles, if the gag rod is extended on the FMU-139A/Bfuzes, assume the fuze is armed.

(4) (AGM-86C) Payload Fuze Safeing Pins & Tags – Checked removed

(5) (AGM-86C) Fuze Settings – As briefed

Verify fuzes are set as briefed by the Wing Air Weapons Officer.

(6) Absence of Missile Fuel Leaks – Checked

d. MAU-12 Ejector Rack Ground Safety Lock Pins – Checked removed

T.O. 1B-52H-34-2-9

Change 6 2-5

If the Warhead Arming Device indicates armed (a black “A” on a redbackground) assume the fuze is armed.

2. All Safeing/Safety Pins – Counted and stowed (P-CP-RN-N)

Check that all safeing, safety pins, and streamers are stowed aboard aircraft. Check that there are12 MAU-12 ejector rack ground safety lock pins, two pylon jettison safeing pins and one WarheadArming Device safeing pin for each missile. For AGM-86C missiles there should also be two payloadfuze safeing pins for each missile.

T.O. 1B-52H-34-2-9

2-6

BOMB BAY INTERIOR

• The bomb door actuator struts must be disconnected before enteringthe bomb bay if power is applied to the aircraft.

• Do not perform operations on the launcher or missiles without firstinstalling the ground operation safety pin. Injury to personnel couldresult.

1. CSRL & Bay Weapons: (RN-N)

a. Launcher General Condition – Checked

Ejector cable plug supports will be installed at those weapon stations without an ejector. Checkenvironmental, electrical, and hydraulic connections secure. Check for evidence of hydraulic leak-age. With a CSRL installed, the environmental control lines on the launcher U tube assemblymust be removed and the lines capped.

b. Ground Operation Safety Switch Pin – Check installed

When installed, the pin prevents the launcher from rotating. The CSRL ground operation safety pin must be installed from the top side down to prevent inadvertent removal of the pin.

c. Uplock Indicator – Checked seated

T.O. 1B-52H-34-2-9

2-7

d. PDU Spline – Engaged and pin seated

If the PDU Spline is not engaged, the launcher will not rotate.

e. Overtravel Indicator – Checked locked

f. Downlock Indicator – Checked down

T.O. 1B-52H-34-2-9

2-8 Change 6

g. MAU-12 Ejector Safeing Mechanism – Check red indicator showing

Visually check indicator on safeing mechanism indicates red.

h. AGM-86C/D Missiles – Checked

(1) Warhead Arming Device Safety Pin & Streamer – Checked removed

Check the Warhead Arming Device safeing pin is removed and the status indicator is SAFE(a white “S” on a green background)

NOTE

Omit Warhead Arming Device check if OTL payload is installed.

(2) Pitot-Static Probe Cover & Streamers – Checked removed

(3) Temperature Sensor Cover and Streamer – Checked removed

On AGM-86C missiles, if the gag rod is extended on the FMU-139A/Bfuzes, assume the fuze is armed.

(4) (AGM-86C) Payload Fuze Safeing Pins & Tags – Checked removed

(5) (AGM-86C) Fuze Settings – As briefed

Verify fuzes are set as briefed by the Wing Air Weapons Officer.

(6) Absence of Missile Fuel Leaks – Checked

i. Ground Operation Safety Switch Pin – Check removed (RN-N)

T.O. 1B-52H-34-2-9

Change 6 2-9

If the Warhead Arming Device indicates armed (a black “A” on a redbackground) assume the fuze is armed.

2. Missile Ram Air Shutoff Valve – Checked open, forward position (forward right wheel well) (RN/N)

3. All Safeing/Safety Pins – Counted and stowed (P-CP-RN-N)

Check that safety pins and streamers for all missiles are counted and stowed aboard the aircraft.Check that there is one ground operation safety switch pin and one Warhead Arming Device safeingpin for each missile. For AGM-86C missiles there should also be two payload fuze safeing pins foreach missile.

4. Bomb Doors – Closed (alert only)

Ensure the bomb bay doors are closed prior to departing the aircraft.

INTERIOR INSPECTION

1. PDUC Power Switch - ON (If required)

Turn the PDUC power switch ON only if a CSRL is installed and is to be rotated.

2. Release Circuits Connected Light - Tested (RN)

T.O. 1B-52H-34-2-9

2-10 Change 10

AFTER ENGINE START (Power and Cooling Air Available)

Less [AMI] CALCM SMO LOADING (N)NOTE

Accomplish the SMO load after OAS is on, processors are loaded, theIU is on and loaded, GPS Keys are loaded (if required), and the B-52Mission DTUC is loaded in the DTU cavity with power applied.

1. B-52 Mission DTUC in DTU Cavity With Power On - Checked

CALCM mission classified parameters are contained on the B-52 Mission DTUC and are loaded with-in the first two minutes after SMO load is complete. It is important to ensure the proper B-52 Mis-sion DTUC remains installed until the CALCM SMO displays the CLAPAR LOADED message.

2. CF-62, n CALCM SMO – Entered

Ensure the proper CALCM SMO for the type/block CALCMs is selected for loading.

[AMI] CALCM SMO LOADING (N)

Load SMO and designate the CALCM SMO as primary in accordance with OAS Log-On in OAS,EVS, and RADAR TURN-ON CHECKLIST of T.O. 1B-52H-1-12.

WEAPON CHECK (RN/N)

NOTE

For proper operation, the CALCM requires GPS almanac data to be less thantwo weeks old to be considered valid. Since the primary source of almanacdata for the missile is the B-52 GPS Interface Unit, which retrieves the datafrom the GPS receiver’s non-volatile memory, the crew should ensure that theGPS receiver contains the current almanac data prior to applying missilepower (28 vdc #1) to any CALCM. If the GPS almanac data age is unknown,or the GPS IU has not been operated within the last two weeks, the crewshould accomplish steps 1 through 4.

1. GPS Power – On (if required) (N)

Apply power to the GPS and GPS IU in accordance with GPS Power Turn-on in OAS, EVS, andRADAR TURN-ON CHECKLIST of T.O. 1B-52H-1-12.

Wait a minimum of 12.5 minutes after the receiver indicates tracking of satellites. This allows thereceiver to complete the initialization process and store current almanac data in its non-volatilememory.

2. GPS Power – Cycle (if required) (N)

Cycle GPS IU power. This causes the IU to retrieve the almanac data from the GPS receiver.

3. GPS Crypto Keys – Load (if required) (N)

Load weekly crypto keys into the IU in accordance with GPS Initialization OAS, EVS, AND RADARTURN-ON CHECKLIST of T.O. 1B-52H-1-12.

4. Less [AMI] CALCM SMO (CF-62,n) – Reload (if required) (N)

T.O. 1B-52H-34-2-9

Change 10 2-10A

WEAPON CHECK (Cont)

4. [AMI] CALCM SMO – Reload and designate as primary (if required) (N)

a. CF-62 – Entered (if applicable)

(1) MDFY-11 – Entered

(2) SMO Number(s) – EnteredEnter desired SMO number for each location: LP (Left Pylon), Bay, and RP (Right Pylon).The cursor indicates which location is being loaded. Use the arrow keys to move the cursorto the desired location.

(3) Primary SMO – SelectEnter CF-62x command where x is the location (A - Left Pylon, B - Bay, C - Right Pylon)of the SMO to be assigned as primary.

5. Simulation Mode - Entered (if applicable) (RN)

NOTE

With no MIUs on board, omit steps a. and b.

a. MIU Power Switches - ON (MIU loaded stations)To enable the simulation mode, the following conditions must be met: (1) A B52 mission withthe OTL mission word indicating OTL or TF, must be loaded; (2) No MIUs are powered on and(3) If an MIU was previously powered on, none of the ejectors on that MIU have an unlockedstatus. If any of the above conditions is not met, the simulation mode cannot be entered andCF-51 or CF-52 will not be accepted. SIMULATION MODES cannot be entered with weaponson board that do not have OTL or TF mission words.

b. MIU Power Switches - Off (MIU loaded stations)Simulation modes cannot be entered with MIU power on.

c. CF-51 or CF-52 - EnteredThe system must be in STRIKE (CF 50) mode to enter simulation mode.

6. Weapon Status Check (RN)

a. FRMT-7 – Entered

• Due to overheating of the Non-Interruptible Direct Current (NDC) power sup-ply, MIU operation on the ground without cooling air being supplied directly tothe right wing root is limited to 2 minutes.

• To reapply MIU power on the ground without cooling air being supplied tothe right wing root, a minimum cool down period (power off) of 20 minutesis required between power applications.

b. MIU Power Switches – ONApply MIU power to missile loaded locations only.

T.O. 1B-52H-34-2-9

2-10B Change 10

WEAPON CHECK (Cont)

c. Missile Status – C_OF (all missiles)Status windows for each missile will be blank before MIU power is turned ON and will showC_OF/ while MIU power is ON and will return to blank when MIU power is turned OFF. Checkfor OAS/Missile related faults; transient faults are possible. FRMT-7 information should matchaircraft weapon load exactly. If not, call qualified personnel.

If a MASTER FAULT indication is present, turn MIU power off. Callqualified personnel. DO NOT REAPPLY POWER.

NOTE

A transient reverse highlighted MIU and/or ECU MASTER FAULTmay appear on the MFD during MIU PWR application. Acknowledgethe fault by pressing the MSTR FAULT button on the WCP. If the samefault reappears, turn MIU power off and call qualified personnel.

d. MIU & Missile Master Faults Not Present – CheckedFRMT-7 information should match aircraft weapon load exactly. If not, call qualified personnel.

e. MIU Power Switches – Off

AFTER TAKEOFF (RN)

1. MIU POWER Switches - ON

a. If missiles are to be simulated, simulation mode entry checklist shall be accomplished beforesimulated MIU power can be applied.

NOTE

A transient reverse highlighted MIU and/or ECU MASTER FAULTmay appear on the MFD during MIU PWR application. Acknowledgethe fault by pressing the MSTR FAULT button on the WCP. If the samefault reappears, refer to Malfunction Analysis in Section VII and takeappropriate action.

T.O. 1B-52H-34-2-9

Change 10 2-11

CALCM INFLIGHT PROCEDURES

MISSILE POWER APPLICATION (N)

If missile power is removed for any reason, wait at least 15 seconds be-fore reapplying power or a GPS failure could occur.

NOTE

• Missile power is inhibited until one OAS INS/INU is on.

• For improved missile INE accuracy, missiles should not be powereduntil OAS INS/INU 1 or 2 have completed four fixes or have a 30 min-ute GPS inertial alignment. Carrier aircraft INS position and driftrates are critical and should be maintained at the lowest possible val-ues before missile power is applied.

• Missiles may be powered individually, in groups, or all simultaneously.

• If missile power is removed 15 seconds must have elapsed before mis-sile power can be reapplied to the powered down missiles. If missilepower is lost or was removed during caging (ON displayed on FRMT-7missile status) 8 minutes must elapse before missile power can bereapplied.

• The aircrew should attempt to maintain straight and level non-turningflight for 10 minutes after missile power application or until TAL re-quired message appears. If turns are performed during this period ex-pect possible degraded missile performance.

• [AMI] To ensure the preferred launch sequence is properly followed,CF-550 (Automatic Targeting) should not be enabled until all CALCMswith power applied show R in the Mission Data window on the CALCMStatus and Inventory Display (FRMT-7).

1. [AMI] CALCM SMO – Primary (CF-62x), if not previously accomplished

2. Less [AMI] Cruise Missile Tape DTU Cavity Power – Checked Off

Power will remain off until all cruise missiles have completed coarse alignment.

3. Relay Circuit Breakers – In (N) (Bomb bay launches only)

4. [AMI] CF-55 – Entered

The AUTO TGT status is displayed on CF-55.

5. [AMI] CF-550, AUTO TGT – Check OFF

T.O. 1B-52H-34-2-9

2-12 Change 10

MISSILE POWER APPLICATION (N) (Cont)

6. MIU Power (AGM-86 Loaded Locations) – Check ON

NOTE

• Warm up timer (CF-55E) will not be bypassed for initial MIU powerapplication.

• MIU power must be on for 40 minutes before missile power can beapplied, unless CF-55E, warmup timer override command is entered.CF-55E will override approximately 35 minutes of the 40 minutewarmup time when extreme cold conditions are not present. Even withCF-55E entered, missile power will not be accepted if missile INE plat-form temperature is not within limits.

• Actual MIU power cannot be applied or removed when in simulationmode (CF-51 or CF-52). Actuation of MIU power switch in simulationmode will result in simulated application of MIU power.

• The MIU power off sequence requires 15 seconds to allow missiles topower down and an additional 5 seconds for the MIU to power off be-fore the MIU light indication goes out.

7. FRMT-7 – Entered

8. Missile Status – C_OF

9. Launcher Hydraulic Control Switch (CSRL Installed) – Check ON PRIMARY (if required) (P)

10. PDUC Power Switch (CSRL Installed) – Check ON, circuit breaker in (if required) (N)

11. GAM-72 GEAR JETTISON & AGM-69A Circuit Breaker – Checked in (P)

This circuit breaker provides the power to the AIU bomb bay door OPEN monitor circuit.

12. Desired Location(s) & Station(s) First Group of Missiles – Selected

NOTE

• If a mixed load of AGM-86C and AGM-86D missiles is being carried,each missile type must be powered and targeted separately. Each missi-le group must contain only one type missile; AGM-86C Blast/Frag(Type 1 Warhead), or AGM-86D Penetrator (Type 2 Warhead).

• Coordinate with the EW Officer to ensure ALQ-155 and ALT-28 trans-mitters are in standby or are not transmitting in the affected bandslisted in T.O. 1B-52H-30-4-1, Operating Limitations, Section V (for ex-ternal pylon missiles only)

13. Weapon Power Switch – ON (1 second)

14. Missile Status – CnON/SAF____ Monitored

The hexadecimal number code for the warhead type FRMT-7 is displayed and the missile status changesfrom OF to ON. When the missile enters coarse alignment the ON changes to CA. The targeting statusis initially blank. When the targeting status indicates R, the missile is ready for targeting.

Ensure the OAS time and date are correct. Incorrect time and date willcause DATA faults during missile BIT and could degrade missile accuracy.

T.O. 1B-52H-34-2-9

Change 10 2-13

MISSILE TARGETING (N)

To ensure GPS data initialization, a G, launch point number, or directtarget designator must be present next to the applicable missile loca-tion on FRMT 7 prior to Manual or Direct Targeting a missile.

NOTE

• It can take up to 2 minutes to target/retarget each missile.

• In order to target cruise missile launch points correctly, the currentdestination must be the first launch point desired to be targeted, or adestination that precedes it.

LESS [AMI] TARGET/RETARGET ALL

NOTE

• Use this checklist to ensure missiles are launched in their preferredlaunch sequence.

• If a mixed load of AGM-86C and AGM-86D missiles is being carried,each missile type must be targeted separately. Each targeting groupmust contain only one type missile; AGM-86C Blast/Frag (Type 1 War-head), or AGM-86D Penetrator (Type 2 Warhead).


Missile targeting status must be a R or have received targeting data before the missile will accepta mission. If missile status is OF, ON, or NG, the missile will be bypassed in the targeting sequence.

2. First Group of Missiles Ready to Receive Mission Data – R or nn Verified

Missiles ready to receive mission data not previously targeted will display a R in the targeting statusportion at the end of the missile status block. Missiles previously targeted will display nn (CALCMlaunch point number) in the targeting status portion at the end of the missile status block.

3. First Missile Group Cruise Missile Mission DTUC – Check installed DTU

Even though the resident DTUC is removed, all missiles will still retain the removed DTUCs target-ing information.

4. FLY-TO nn – Entered (N)

nn = A destination prior to the first CMLP that the aircraft is targeting. The OAS will target missilesagainst the first group of CMLPs it detects after nn.

5. Cruise Missile Mission DTU Cavity Power – On

Cruise Missile Mission DTUC must be powered prior to sending missile mission data to the missile(s).

6. CF-559 – Entered

When all functional missiles indicate ready to receive mission data, initiate targeting using thetarget/retarget all command (CF-559).

7. TGT/RETGT ALL? – YES selected, if applicable

T.O. 1B-52H-34-2-9

2-14 Change 10

Less [AMI] TARGET/RETARGET ALL (Cont)

8. Missile Targeting Status of First Missile Group – Verified

The first powered missile in the preferred launch sequence which is ready to receive mission data(R displayed if not previously targeted or nn displayed if previously targeted) will change to a newnn (where nn is the next CALCM launch point). Subsequent powered missiles in the preferredlaunch sequence R (displayed if not previously targeted) will change to the next nn (where nn is thenext CALCM launch point). If previously targeted, targeting status will change to G (GPS initializa-tion data has been loaded in the missile) then to nn (where nn is the next CALCM launch point).Backup missiles will be displayed in the respective station status display. Only missiles at locationswith a MIU as the Stores Management Interface Unit in the loaded B-52 Mission can be targeted.

9. Cruise Missile Mission DTU Cavity Power – Off

10. First Missile Group Cruise Missile Mission DTUC – Removed from DTU

Even though the resident DTUC is removed, all powered missiles will still retain the removedDTUCs targeting information.

NOTE

If a mixed load of AGM-86C and AGM-86D missiles is being carried ac-complish steps 11 through 18 to power and target second group of missiles.

11. Desired Location(s) & Station(s) of Second Group of Missiles – Selected



The hexadecimal number code for the warhead type FRMT-7 is displayed and the missile statuschanges from OF to ON. When the missile enters coarse alignment the ON changes to CA. Thetargeting status is initially blank.

14. Second Missile Group of Missiles Ready to Receive Mission Data – R or nn Verified


15. Second Group Cruise Missile Mission DTUC – Check installed DTU

16. Cruise Missile Mission DTU Cavity Power – On

Cruise Missile Mission DTUC must be powered prior to sending missile mission data to the second group of missiles.

17. Missile Targeting Status of Second Missile Group – Verified

The first powered missile in the second missile group in the preferred launch sequence which isready to receive mission data (R displayed if not previously targeted) will change to a new nn (wherenn is the next CALCM launch point). Subsequent powered missiles in the second missile group inthe preferred launch sequence with an R displayed will change to the next nn (where nn is the nextCALCM launch point). Only missiles at locations with a MIU as the Stores Management InterfaceUnit in the loaded B-52 Mission can be targeted.

18. Cruise Missile Mission DTU Cavity Power – As Required

T.O. 1B-52H-34-2-9

Change 10 2-14A

[AMI] TARGET/RETARGET ALL

NOTE

• Use this checklist to ensure missiles are launched in their preferredlaunch sequence.

• If a mixed load of AGM-86C and AGM-86D missiles is being carried,each missile type must be targeted separately. Each targeting groupmust contain only one type missile; AGM-86C Blast/Frag (Type 1 War-head), or AGM-86D Penetrator (Type 2 Warhead).


Missile targeting status must be a R or have received targeting data before the missile will accepta mission. If missile status is OF, ON, or NG, the missile will be bypassed in the targeting sequence.

2. First Group of Missiles Ready to Receive Mission Data – R or nn Verified


3. FLY-TO nn – Entered (N)

nn = A destination prior to the first CMLP that the aircraft is targeting. The OAS will target missilesagainst the first group of CMLPs it detects after nn.

4. CALCM Weapon Group – Select (if required)

a. CF-82x – Entered

x is the location (A = Left Pylon, B = Bay, C = Right Pylon) where the CALCM SMO is loaded.

b. CF-82,n – Entered

n or nn is the desired weapon group number.



6. CF-550, AUTO TGT – ON

The CF-550 command toggles AUTO TGT to ON.


When all functional missiles indicate ready to receive mission data, initiate targeting using thetarget/retarget all command (CF-559).

8. TGT/RETGT ALL? – YES selected, if applicable

9. Missile Targeting Status of First Missile Group – Verified

The first powered missile in the preferred launch sequence which is ready to receive mission data(R displayed if not previously targeted or nn displayed if previously targeted) will change to a newnn (where nn is the next CALCM launch point). Subsequent powered missiles in the preferredlaunch sequence R (displayed if not previously targeted) will change to the next nn (where nn is thenext CALCM launch point). If previously targeted, targeting status will change to G (GPS initializa-tion data has been loaded in the missile) then to nn (where nn is the next CALCM launch point).Backup missiles will be displayed in the respective station status display. Only missiles at locationswith a MIU as the Stores Management Interface Unit in the loaded B-52 Mission can be targeted.

T.O. 1B-52H-34-2-9

2-14B Change 10

[AMI] TARGET/RETARGET ALL (Cont)



11. CF-550, AUTO TGT – OFF

The CF-550 command toggles AUTO TGT to OFF.

NOTE

If a mixed load of AGM-86C and AGM-86D missiles is being carried ac-complish steps 12 through 20 to power and target second group of missiles.

12. Desired Location(s) & Station(s) of Second Group of Missiles – Selected



The hexadecimal number code for the warhead type FRMT-7 is displayed and the missile statuschanges from OF to ON. When the missile enters coarse alignment the ON changes to CA. Thetargeting status is initially blank.

15. Second Missile Group of Missiles Ready to Receive Mission Data – R or nn Verified











19. Missile Targeting Status of Second Missile Group – Verified

The first powered missile in the second missile group in the preferred launch sequence which isready to receive mission data (R displayed if not previously targeted) will change to a new nn (wherenn is the next CALCM launch point). Subsequent powered missiles in the second missile group inthe preferred launch sequence with an R displayed will change to the next nn (where nn is the nextCALCM launch point). Only missiles at locations with a MIU as the Stores Management InterfaceUnit in the loaded B-52 Mission can be targeted.

20. CF-550, AUTO TGT – As Required

T.O. 1B-52H-34-2-9

Change 10 2-14C

AUTO RETARGET INHIBIT/ENABLE


2. AUTO RETGT Status – Checked

Check AUTO RETGT Status on the CALCM Supervision menu (CF-55) for desired status (AUTORETGT = YES/NO).

3. CF-554 – Entered (If a change in status is desired)

4. AUTO RETGT Status – Checked

Check AUTO RETGT Status on the CALCM Supervision menu (CF-55) for desired status (AUTORETGT = YES/NO).

T.O. 1B-52H-34-2-9

2-14D Change 10

Less [AMI] MISSION SUBSTITUTION (INDIVIDUAL MISSILES)

Do not enter CF-559 during or after accomplishment of the missionsubstitution checklist. Entry of CF-559 can result in targeting informa-tion being programmed into the wrong missile.

To ensure GPS data initialization, a G, launch point number, or directtarget designator must be present next to the applicable missile loca-tion on FRMT-7 prior to Manual or Direct Targeting a missile.

NOTE

This checklist will be used when directed to change (swap) DTUCs.

1. Auto Retarget CF-554 – OFF (all powered missiles)


Ensure all missiles are targeted with the resident DTUCs missions. The launch point sequence num-bers should all be underlined.

3. Resident DTUC – Removed from DTU

Even though the resident DTUC is removed, all missiles will still retain the removed DTUCs target-ing information.

4. New DTUC – Inserted in DTU and DTU power applied

Inserting the new DTUC will not change targeting information. The OAS will, however, read themission identifier for the new DTUC and display it on the CF-8 display.

5. New Target Data – Inserted as directed

Use the Manual Retargeting checklist to selectively retarget those missiles directed to be retargeted.

NOTE

Repeat steps 3, 4, and 5, if additional DTUCs are required to beswapped.

T.O. 1B-52H-34-2-9

Change 10 2-15

[AMI] MISSION SUBSTITUTION (INDIVIDUAL MISSILES)

Do not enter CF-559 during or after accomplishment of the missionsubstitution checklist. Entry of CF-559 can result in targeting informa-tion being programmed into the wrong missile.


NOTE

This checklist will be used when directed to change weapon groups.

1. Auto Retarget CF-554 – OFF (all powered missiles)


Ensure all missiles are targeted with the resident weapon group. The launch point sequence num-bers should all be underlined.



4. CF-550, AUTO TGT – OFF

The CF-550 command toggles AUTO TGT to OFF.










8. New Target Data – Inserted as directed

Use the Manual Retargeting checklist to selectively retarget those missiles directed to be retargeted.

NOTE

Repeat steps 3 through 8, if additional weapon groups are required.

T.O. 1B-52H-34-2-9

2-16 Change 10

MANUAL RETARGETING (INDIVIDUAL MISSILES)


NOTE

• Verify that targeting has been commanded and is complete.

• The operator can manually retarget only a powered missile providedthe selected missile is not in a launch countdown, mission data transferis not in progress to the selected missile, and the loaded B-52 Missionhas a MIU as the weapon interface unit for the selected missile.

• When selectively retargeting any missile the operator should exercisediscretion so as to avoid a non-optimum launch sequence.

• Less [AMI] Always ensure the CALCM DTUC associated with the mis-sion to be targeted is resident in the DTU.

• [AMI] Always ensure the proper weapon group is selected.

1. FRMT-7xy – Entered

Check missile power status of missile to be targeted where x = Location, y = Station.

2. LOCATION & STATION – Selected

3. CF-556,nn – Entered

This command loads the mission for CALCM launch point nn into the selected missile.

4. Target Load Status – Checked

When the target load has been verified by the OAS, the assigned CALCM launch point sequencenumber (nn) in the missile status on FRMT-7 will change to nn.

NOTE

Repeat steps 1 through 4 for each additional missile required to bemanually targeted.

T.O. 1B-52H-34-2-9

Change 7 2-17

FLEX TARGETING (INDIVIDUAL MISSILES)

To ensure GPS data initialization, a launch point number must be pres-ent next to the applicable missile location on FRMT 7 prior to flex tar-geting a missile.

NOTE


• The operator can flex target only a powered missile provided the se-lected missile is not in a launch countdown and mission data transferis not in progress.





This command displays the Flex Targeting screen for CALCM launch point nn.

3. Flex Targeting Data – Entered

4. AGM-86D Fuze Data (CF-DF) - Entered, if required

5. CF-DD SEND DATA – Entered

Sends Flex Targeting Data to the CALCM.

6. PTA Reference Time – Update on FRMT 10 for affected missile(s).


When the flex target load has been verified by the OAS, the assigned CALCM launch point sequencenumber (nn) in the missile status on FRMT-7 will change to Fnn.

NOTE

• Enter a new PTA Reference Time (as directed) in the flex targetedCMLP line(s) on FRMT 10 before launching flex targeted missile(s). Donot change the directed PTA Reference Time on line 3 of CF-61.

• Repeat steps 1 through 7 for each additional missile required to be flextargeted.

T.O. 1B-52H-34-2-9

2-18 Change 7

DIRECT TARGETING (INDIVIDUAL MISSILES)

To ensure GPS data initialization, a G or a launch point number mustbe present next to the applicable missile location on FRMT 7 prior toflex targeting a missile.

NOTE


• The operator can direct target only a powered missile provided the se-lected missile is not in a launch countdown, mission data transfer isnot in progress, and the loaded B-52 Mission has a MIU as the weaponinterface unit for the selected missile.




2. LOCATION & STATION – Selected


This command displays the Direct Targeting screen for direct target nn.

4. Direct Targeting Data – Entered

5. AGM-86D Fuze Data (CF-DF) - Entered, if required

6. CF-DD SEND DATA – Entered

Sends Direct Targeting Data to the CALCM.


When the direct target load has been verified by the OAS, the assigned CALCM launch point se-quence number (nn) in the missile status on FRMT-7 will change to Dnn.

NOTE

Repeat steps 1 through 7 for each additional missile required to bedirect targeted.

T.O. 1B-52H-34-2-9

Change 7 2-19

LAUNCH PROCEDURES

MISSILE PREPARATION FOR LAUNCH

NOTE

• Perform this checklist no later than 30 minutes prior to the HEW, tothe launch point, or not later than 30 minutes prior to descent (lowaltitude launch).

• The RN will monitor the MPL and ensure completion of all items.

• It is imperative that the following steps be completed in sequence.

• For proper missile timing, planned missile launch time must be enteredinto CF-61, Line 3. PTA reference time on CF-61 only needs to be up-dated for the first missile in a launch stream.

1. Cabin Pressurization – COMBAT (if applicable) (CP)

2. Personal Locator Beacon Lanyards – Notify crew to set as required (RN/N)

Mission requirements will dictate the configuration of the personal locator beacon lanyard.

3. Exterior Lights – As briefed (P)

4. Walkway Lights Circuit Breakers – Out (RN)

5. Normal Release, Jettison Power, and Relay Circuit Breakers – In (RN)

6. FRMT-7 – Entered (N)

7. Missile Power – Check ON (N)

8. Missile Status – Checked Cnaa/SAF_nn

aa Status may be GO, TA, AL, or CA.

9. Location & Station (Missiles To Be Launched) – Selected (N)

NOTE

• All missiles can be declared “Ready to Launch” (RDY) simultaneouslyby selecting the LP, RP, and BAY location switches and the ALL stationswitch.

• Repeat steps 9 thru 11 if missiles are to be declared “Ready to Launch”(RDY) individually or in groups.

T.O. 1B-52H-34-2-9

2-20 Change 6

MISSILE PREPARATION FOR LAUNCH (Cont)

10. PREARM-SAFE Switch – PREARM (1 second) (N)

11. Missile Status – Checked Cnaa/RDY (N)

aa status may be GO, TA, AL, or CA/RDY.

12. Missile Targeting/Retargeting Checklist – Accomplished (N) (As required)

13. PTA REF Time (CF-61) – Set (N) (As required)

PTA reference time is not required for direct targeting.

14. Master Fault Lights – Off (N)

15. Munitions Consent Panel LOCK-UNLOCK Switch – UNLOCK (P)

16. NUCLEAR LOCK-UNLOCK Switch – UNLOCK (N)

T.O. 1B-52H-34-2-9

Change 9 2-21

MISSILE LAUNCH (N)

• The aircraft must maintain straight and level flight for a period of 5seconds before to 5 seconds after missile launch. This is to prevent thepossibility of aircraft and missile collision.

• The mission plan for flight of aircraft after AGM-86C/D missile launchmust be followed to ensure safe separation distance of aircraft frommissile when the missile becomes armed.

• Changing the launch mode, while the missile is in launch countdown,will place the weapon in a hold and may result in a weapon abort. At2 seconds before release the CALCM battery is squibbed and any abortpast this point is fatal to the missile (cannot be used again on the sameflight). During any launch countdown, if either the launch mode ormanual launch switch is pressed, a hold occurs:

• Before the battery squib command, a 45 second hold is entered. If themanual launch switch is pressed before the 45 seconds expires, thelaunch countdown will continue. If the manual launch switch is notpressed before the 45 seconds expires, the launch countdown abortsand the weapon is powered off with a transient fatal fault (weapon canbe used on the same flight).

• After the battery squib command, a 10 second hold is entered. If themanual launch switch is pressed before the 10 seconds expires, thelaunch countdown continues. If the manual launch switch is notpressed before the 10 seconds expires, the launch countdown abortsand the weapon is powered off with a permanent fatal fault (weaponcannot be used on the same flight).

NOTE

• To achieve system alignment accuracy, complete a transfer alignmentmaneuver within 2 to 30 minutes of launch.

• If a targeted missile is powered down due to a fault while in SAIR, theSMO will assign the secondary or tertiary weapon (if available) withthe mission of the powered down missile. The secondary and tertiaryweapons are the next weapons in the preferred launch sequence avail-able for targeting. This will occur only if automatic retargeting hasbeen enabled, check Auto Retarget status on CF-55 (YES = Enabled,NO = Inhibited).

• Missile launch from the aft inboard pylon stations is inhibited if bombdoors are not closed and latched.

T.O. 1B-52H-34-2-9

2-22 Change 9

MISSILE LAUNCH (Cont)

1. Transfer Alignment Maneuver – Accomplished, if required (N-P) (figure 2-1)

2. HAC/LAC – Accomplished (RN)

B-52 Operators must be aware that the Inertial/GPS aided munitionsuse the transfer alignment data (latitude, longitude, altitude, etc.) ofthe aircraft prime navigation model. Buffers are not incorporated/transferred to the Inertial/GPS aided munitions. This navigation trans-fer applies to a prime navigation model with, or without, GPS aiding.Failure to recognize this condition may result in weapons impactingother than the intended target or failing to release due to LAR consid-erations. Refer to MAJCOM or Theater specific guidance for degradedweapon release ROE.

NOTE

HAC/LAC must be accomplished within 30 minutes to one hour prior toAGM-86C/D missile launch if the OAS is not in GPS inertial navigationmode.

3. Missile Launch Mode Switch – AUTO/MAN, as required (N)

4. PTA REF (CF-61) or PTA on FRMT 10 for each CMLP – Verified (N/A for Direct Tgt) (N-RN)

PTA reference time is not required for direct targeting.

NOTE

FRMT 10 planned time of arrival times will change if PTA REF (CF-61)is subsequently modified.

5. PRGM – Entered (N)

The program current event should be displayed to allow monitoring of all missile conditions.

NOTE

• SAIR information will be displayed anytime the current or next des-tination is a CALCM launch point or while in Direct Launch mode.

• With AUTO selected, missile launch will be initiated automaticallywhen the aircraft passes the closest point of approach to the launchpoint provided the launch point is determined to be in range and safelaunch checks are satisfied.

• Procedurally, manual launch requires display of the in-range launchpoint (PRGM display) so that the operator may monitor a steady SAIRindication, and actuate the manual launch switch.

6. FLY TO nn – Entered (N) (Not applicable for Direct SAIR Launch)

nn = CALCM launch point number. Dnn is displayed as the current weapon event for direct SAIR launch.The SAIR mode/status indicates SAIR. The time to go to SAIR is displayed in minutes and seconds.AUTO RETGT status as required is displayed.

T.O. 1B-52H-34-2-9

Change 11 2-23


7. MANUAL SAIR, If Required:

a. CF-553 – Entered

b. MANUAL SAIR? YES/NO – YES (N)

The manual SAIR question must be answered within 60 seconds or the system will assume NO.If answered YES, a manual SAIR timer begins running for 3 minutes. If no launch occurs, theOAS will automatically exit the manual SAIR mode when the timer expires.

The SAIR mode/status changes from SAIR to MAN SAIR. The Time To Go to SAIR changes to blank.Manual SAIR range is displayed as SAIR RNG xxx (xxx= range to enter SAIR).The range to exit SAIR xxx is displayed The launch mode/launch countdown status displays MAN LNCH MODE.AUTO RETGT status as required is displayed. Magnetic course to the first CALCM waypoint is displayed as MCxxx°.

7. DIRECT SAIR, If Required:

PRGM-Dnn – Entered

The Direct Targeting status displays DnnThe SAIR mode/status changes from SAIR to DIR SAIR.The Time To Go to SAIR changes to blank.Direct SAIR range is displayed as SAIR RNG xxx (xxx = range to enter SAIR).The range to exit SAIR xxx is displayedThe launch mode/launch countdown status displays MAN LNCH MODE.Pretarget steering waypoint data is displayed as �BRG xnn�AUTO RETGT status as required is displayed.Magnetic course to the first steering waypoint is displays as MCxxx�

8. Carrier Aircraft Position & Heading – Checked (N-RN)

Carrier aircraft must be within SAIR footprint on the chart provided and aircraft heading must be within±30 degrees of the programmed launch heading to ensure the missile reaches its first waypoint.

9. Automatic Launch (Automatic Launch Point Ranging SAIR Only):

a. SAIR Indication – SAIR

As the aircraft enters SAIR, the SAIR changes to SAIR and the time to go decreases to zeroand then becomes blank. A blinking reverse video SAIR indicates the launch is inhibitedbecause aircraft Mach number/altitude, or attitude is out of limits for missile launch. Theaction to correct the out-of-limits condition will also be displayed in reverse video.

b. Launch Countdown – Monitored

Maintain straight and level flight. If the missile enters a launch countdown hold and thecondition causing the hold is not corrected, the launch countdown hold timer (45-second) orTA launch countdown hold timer (approximately 5.6 to 13 seconds) will expire. If the 45-sec-ond launch countdown hold timer has expired, the launch countdown will be terminated. Ifthe TA launch countdown hold timer has expired, due to limited missile battery life (approxi-mately 5.6 to 13 seconds), the launch countdown will be terminated and the missile will bedeclared NO-GO and powered down.

c. Missile AWAY Indication – Notify crew

d. Bomb Doors (Launcher Missiles Only) – Closed

T.O. 1B-52H-34-2-9

2-24 Change 6


9. Manual Launch:

a. Auto SAIR Indication – Steady (N)

As the aircraft enters SAIR, the SAIR changes to SAIR and the time to go decreases to zeroand then becomes blank. A blinking reversed video SAIR indicates the launch is inhibited be-cause aircraft Mach number/altitude, or attitude is out of limits for missile launch. The actionto correct the out-of- limits condition will also be displayed in reverse video.

a. MAN SAIR Indication – Steady (N)

As the aircraft enters SAIR, the MAN SAIR changes to MAN SAIR and the SAIR RNG changesto SAIR RNG. A blinking reversed video MAN SAIR indicates the launch is inhibited becauseaircraft Mach number/altitude, or attitude is out of limits for missile launch. The action to correctthe out-of- limits condition will also be displayed in reverse video.

a. DIR SAIR Indication – Steady (N)

As the aircraft enters SAIR, the DIR SAIR changes to DIR SAIR and the SAIR RNG changesto SAIR RNG. A blinking reversed video DIR SAIR indicates the launch is inhibited becauseaircraft Mach number/altitude, or attitude is out of limits for missile launch. The action to correctthe out-of- limits condition will also be displayed in reverse video.

NOTE

If ∆BRG is in reverse video and a missile left turn is required at SWP(∆BRG = Lnnn°), fly the aircraft on a mag course to SWP plus 30° . If∆BRG is in reverse video and a missile right turn is required at SWP(∆BRG = Rnnn°), fly the aircraft on a mag course to SWP minus 30°.

T.O. 1B-52H-34-2-9

Change 2 2-25


9.a.

b. Location & Station (Bay, x) (Manual Launch CSRL Missiles Only) – Selected (N)

Accomplish when approaching SAIR (approximately 60 to 50 seconds SAIR TTG for AutomaticLaunch Point Ranging SAIR, or 30 to 25 NM for MAN SAIR or DIR SAIR).

c. CSRL LCHR ROTATE Switch – Pressed, light on (N)

Ensure selected missile station rotates to the down (launch) position.

d. Missile Manual Launch Switch (When in SAIR) – Pressed, light on (N)

e. Launch Countdown – Monitored (N)

Maintain straight and level flight. If the missile enters a launch countdown hold and the condi-tion causing the hold is not corrected, the launch countdown hold timer (45-second) or TA launchcountdown hold timer (approximately 5.6 to 13 seconds) will expire. If the 45-second launchcountdown hold timer has expired, the launch countdown will be terminated. If the TA launchcountdown hold timer has expired, due to limited missile battery life (approximately 5.6 to 13seconds), the launch countdown will be terminated and the missile will be declared NO-GO andpowered down.

f. Missile AWAY Indication – Notify crew (N)

g. Bomb Doors (Launcher Missiles Only) – Closed (N)

T.O. 1B-52H-34-2-9

2-26

NOTE

• Heading changes shown are nominal values.• Time on each leg starts at rollout.• The minimum TAL maneuver consists of one turn that meets the time requirements

shown below.• One complete TAL consists of three heading changes.• Two TALs, each on opposite sides of track, result in smaller navigation errors.

NOTE

• Perform coordinated turn within limits shown to accomplish missile fine alignmenttransfer.

• Maneuvers of less than 6 seconds duration will not be recognized by the computer.• A minimum of 1 minute of straight and level flight is required after the TAL prior

to starting any reverse direction maneuver in order not to nullify any effects of thefirst TAL.

Figure 2-1. Guidance Transfer Alignment Maneuver

T.O. 1B-52H-34-2-9

Change 11 2-27

LAUNCH ABORT/MISSION ABORT/RETAINED MISSILE(S)

NOTE

• Accomplish this checklist on mixed load mission when changing be-tween weapon types ([AMI] non Multi-SMO capable weapon types).However, if mission requirements dictate, the classified data erase maybe delayed to follow the sortie’s last weapon/bomb release.

• On mixed load missions when changing between CALCM-C andCALCM-D weapons, only steps 1. through 5. and 12. are required. Theremaining steps may be delayed to follow the sortie’s last CALCMlaunch.

• The Master Fault light will come on and remain on, and the corre-sponding fault message will be displayed on the MFD any time thereis a disagreement between the pilot and navigator unlock switches.

1. NUCLEAR LOCK-UNLOCK Switch – LOCK (N)

2. Missile Launch Mode Switch – MAN (N)

3. Missile Manual Launch Switch – Light off (N)

4. For further launch attempts – Go to MISSILE PREPARATION FOR LAUNCH CHECKLIST step 15.

NOTE

Accomplish the remaining steps for mission abort only if no furtherlaunches are to be attempted and weapons are retained aboard the air-craft.

5. FRMT-7 – Entered (N)

NOTE

• RDY missiles must always be manually safed.

• All missiles can be safed, or erased, or powered down simultaneouslyby selecting the ALL station switch.

• Repeat steps 6 thru 11 if missiles are safed, erased, and/or powereddown individually or in groups.

6. Location & Station Of Missile(s) To Be Safed – Selected (N)

7. PREARM-SAFE Switch – SAFE (1 second) (N)

Missile ready to launch status should change from RDY to SAF.

8. Location & Station Of Missile(s) To Be Erased – Selected (if required) (N)

NOTE

If either type of classified data erase is accomplished the missiles willbe powered down by the SMO at the end the erase process. Thereforepowering down (steps 10 and 11) is not required for those missiles.

T.O. 1B-52H-34-2-9

2-28 Change 2

9. Classified Data Erase (CF-555) or Weapon Data Erase (CF-55F) – Entered (if required) (N)

When Classified Data Erase CF-555 is commanded OAS will initiate erasure of the mission data byoverwriting all mission data 1000 times. After 180 seconds (3 minutes) erasure is complete andmissile power will be removed. The missile OFS is not affected by this procedure and the missilewill remain SECRET.

When Weapon Erase CF-55F is commanded OAS will initiate erasure of the mission data by over-writing all mission data 1000 times followed by erasure of the missile OFS. After 240 seconds (4minutes) erasure will be complete and missile power will be removed. The missile OFS is erased andthe missile is UNCLASSIFIED.

NOTE

• Use of CF-55F and CF-555 is unrestricted after authorization fromhigher headquarters.

• CF-55F will erase all data from the missile, including the missile Op-erational Flight Software (OFS). The missile must be removed from theaircraft in order for the software to be reloaded. CF-55F will erase mis-sile data from any selected powered missile, including when the air-craft is on the ground.

10. Location & Station Of Missile(s) To Be Powered Off – Selected, if required (N)

11. Weapon Power Switch – OFF (1 second) (N)

Missile status should indicate CnOF/SAF___.

12. Munitions Consent Panel LOCK-UNLOCK Switch – LOCK (N-P)

T.O. 1B-52H-34-2-9

2-29

PRELANDING PROCEDURES

NOTE

MIU and missile power must be removed inflight due to the lack of ramair for the MCS.

BEFORE DESCENT

1. Launcher – Positioned (if required) (N)

If a no-go missile is aboard, position that missile to the launch position to facilitate removal byground crew.

2. Launcher Hydraulic Control Switch – OFF (P)

3. MIU Power Switches – Off (N)

4. Missile Safety Check:

NOTE

Missile aboard, complete the following safety check.

a. Pilot’s Munitions Consent Panel LOCK-UNLOCK Switch – LOCK, guard closed (P)

b. Weapon Control Panel: (N)

(1) NUCLEAR LOCK-UNLOCK Switch – LOCK, guard closed

(2) PYLON LOCK-UNLOCK Switch – LOCK, guard closed

(3) Weapon Jettison Switch – NORM, guard closed

AFTER LANDING PROCEDURES

AFTER PARKING

1. PDUC Power Switch – OFF (N)

2. Missiles Aboard & Qualified Personnel Not Available – Accomplish GROUND SAFEING PROCEDURES checklist (N/RN)

T.O. 1B-52H-34-2-9

2-30 Change 3

GROUND SAFEING PROCEDURES (PYLON MISSILES) (RN/N)

Missile release system safeing procedures must be accomplished by the navigator and radar navigator if qu-alified maintenance personnel are not available. Safe the missile systems by performing the following proce-dures:

1. Weapon Control Panel:

a. NUCLEAR LOCK-UNLOCK Switch – LOCK, guard closed

b. PYLON LOCK-UNLOCK Switch – LOCK, guard closed

2. Pitot-Static Probe Covers – Installed

3. Temperature Sensor Covers – Installed

T.O. 1B-52H-34-2-9

2-31

GROUND SAFEING PROCEDURES (BAY MISSILES) (RN/N)

Missile release system safeing procedures must be accomplished by the navigator and radar navigator if qu-alified maintenance personnel are not available. Safe the missile systems by performing the following proce-dures:

1. Weapon Control Panel NUCLEAR LOCK-UNLOCK Switch – LOCK, guard closed

2. MIU-BAY Power Switch – OFF

3. OAS Master Power Switch – OFF

4. Rotary Launcher Hydraulic Control Switch – OFF (P)

NOTE

Electrical and hydraulic power must be available to accomplish theseprocedures.

5. Bomb Bay Doors – OPEN

6. FWD EMER VALVE, FWD MAIN VALVE, AFT MAIN VALVE & RELAYS Circuit Breakers (Rt FwdBNS Circuit Breaker Panel) – Pulled

The bomb bay door actuator struts must be disconnected before enter-ing the bomb bay if power is applied to the aircraft.

7. Bomb Bay Door Actuator Struts – Disconnected

Launcher ground operation safety switch pin must be installed throughthe switch from the top side down to prevent inadvertent removal ofthe pin.

8. Launcher Ground Operation Safety Switch Pin – Installed

9. Bomb Bay Doors – CLOSED

T.O. 1B-52H-34-2-9

2-32 Change 2

GROUND SIT/MIT PROCEDURES

1. BEFORE EXTERIOR (POWER OFF) & EXTERIOR INSPECTION Checklists - Completed

2. INTERIOR INSPECTION Checklist - Completed

3. External Power & Cooling Air - Available

NOTE

• Qualified maintenance personnel must be available when this proce-dure is used to ensure proper electrical and cooling air requirementsare met.

• When missile power is applied for ground tests, a wing root fan is re-quired. If ambient temperature is above 90° F, use a cooling cart tosupply ram air to the NDC power supplies and air inlet receptacle.

• If ambient temperature is below 90° F, ram air scoop fan assembly maybe used in lieu of a cooling cart.

• If a cooling cart is used when ambient temperature is below 90° F,apply discharge air at full delivery airflow. Compressor should not beused unless it is necessary to prevent discharge air exceeding 100° F.

4. AFTER ENGINE START Checklist - Completed

• Do not close the bomb bay doors when a wing root fan is installed. Thepower cord is routed into the bomb bay and will be damaged if thedoors are closed.

• When performing missile maintenance test (SIT/MIT) or operationaltargeting checks, the OAS must contain an accurate date and time onCF 61.

5. Aircraft INSs - Onor

CF 552 - Entered (as directed by mission requirements)

6. MISSILE POWER APPLICATION & MISSILE TARGETING Checklists - Accomplished

NOTE

Weapon power must be applied to each location separately. If weaponpower is applied to all locations simultaneously, the OAS may shut-down.

7. Normal Missile and OAS Shutdown Procedures - Accomplish after missile targeting is complete.

T.O. 1B-52H-34-2-9

Change 4 3-1

Emergency Aircrew Procedures section III



MISSILE JETTISON PROCEDURES 3-1

PYLON JETTISON 3-3

PYLON JETTISON PROCEDURES 3-3

NOTIFICATION PROCEDURES – DANGEROUS MATERIALS 3-7

FIREFIGHTING AND EVACUATION CRITERIA 3-9

MISSILE JETTISON

MISSILE JETTISON PROCEDURES (RN/N READS)

• Jettison of AGM-86 missiles, or pylon with missiles installed, is prohib-ited below 3500 feet above surface unless flight safety of the aircraftis in jeopardy.

• The CALCM SMO has no interlocks preventing jettison on the ground.With unlock consent, and power applied to the OAS and the MIU, ac-tuation of jettison switches while on the ground will result in weaponjettison.

NOTE

• Jettison of missiles from the aft inboard pylon stations is inhibited ifbomb doors are not closed and latched.

• With total WCP failure prior to accomplishing hardwired functions,missile jettison or pylon jettison is not possible.

• Jettison is independent of missile electrical or hydraulic subsystemsand can occur at any aircraft altitude, speed, or attitude, but must haveboth OAS and MIU power on.

• See figure 3-1 for launch/jettison release sequence, figure 3-2 for pylonmissile jettison restrictions, and refer to T.O. 1B-52H-34-2-9-1 SectionIII for jettison airspeed envelope limits.

• The navigator will record the coordinates, time and descriptive locationof jettisoned weapons for later use by appropriate authorities.

T.O. 1B-52H-34-2-9

3-2 Change 10

MISSILE JETTISON PROCEDURES (RN/N READS) (Cont)

1. Command Post – Contacted (if practical) (P)

2. Impact Area – Cleared (if practical) (P-CP-RN)

Clear both visually and by radar to maximum extent possible.

3. OAS Master Power – ON (N)

4. Processors – Loaded (N)

NOTE

OAS and CALCM SMO loaded ([AMI] as the primary SMO) and operating is re-quired to enable jettison.

5. [AMI] CALCM SMO – Loaded and designated as Primary SMO (N)

6. MIU Power Switches – ON (location of missile(s) to be jettisoned) (N)

7. Jettison Control & Jettison Power Circuit Breakers (2) – In (N)

8. Normal Release Circuit Breaker – In (N)

9. Launcher Hydraulic Control Switch (Bay Missiles) – ON PRIMARY (P)

10. Pilot’s Munitions Consent Panel LOCK-UNLOCK Switch – UNLOCK (P)

11. NUCLEAR LOCK-UNLOCK Switch – UNLOCK (N)

NOTE

• If “BAY ALL” is selected, missiles will be jettisoned in order 1 thru 8if missile 1, 2, 3, or 4 was in release position at the time of jettison.If 5, 6, 7, or 8 was in release position, the missiles will be jettisonedin reverse order 8 thru 1.

• If the launcher fails to rotate to place the command missile in jettisonposition, manually command the launcher to rotate to the proper jetti-son position. If it still will not rotate, ejector unlock consent must beremoved within 60 seconds of the jettison command to prevent OASfrom powering down all other launcher missiles.

12. Location & Station (Missiles To Be Jettisoned) – Selected (N)

13. WCP Weapon Jettison Select Switch – Select (1 second) (N)

T.O. 1B-52H-34-2-9

Change 10 3-3

MISSILE JETTISON PROCEDURES (RN/N READS) (Cont)

NOTE

Accomplish step 14 only if the pilot jettison control switch is used tojettison missiles.

14. Pilots’ Bomb Bay & Missile Jettison Control Switch – Pressed (P)

• Selectively jettisoning pylon missiles using the Pilots’ Bomb Bay & Mis-sile Jettison Control switch, while attempting to retain internal CSRLweapons by pulling Bomb Door Control Valve circuit breakers is notauthorized. If jettison is attempted in this fashion, the jettison com-mand will remain in the OAS even until all statused weapons havebeen jettisoned. Resetting the Bomb Door Control Valve circuit break-ers will cause the bomb bay doors to open, which will complete thejettison sequence causing all internal CSRL weapons to be jettisoned.Once selective jettison is commanded using the pilots’ switch, the onlyway to clear the resident jettison command from the OAS without jetti-soning the weapons is by shuting down OAS (CF-67).

• The Pilots’ Bomb Bay & Missile jettison control switch jettisons allweapons Less [AMI] loaded on the aircraft, [AMI] controlled by theprimary SMO, and will only be used if jettison by the WCP and CF-Eis impossible. If jettison is commanded using the pilots’ switch, Less[AMI] all weapons will be jettisoned, [AMI] all weapons controlled bythe primary SMO will be jettisoned, and proper separation clearancebetween weapons or between weapons and aircraft cannot be ensured.

PYLON JETTISON

Pylons can be jettisoned, with or without missiles, by use of pylon jettison control switches on the pilot over-head panel. These switches marked LH and RH can be used individually or simultaneously to jettison thepylons after the pylon ready lights come on.

Jettison of pylons with missiles loaded is prohibited below 3500 feetabove surface unless the flight safety of the aircraft is in jeopardy.

NOTE

With total WCP Failure prior to accomplishing hardwired functions,pylon jettison is impossible.

PYLON JETTISON PROCEDURES (RN/N READS)

1. Command Post – Contacted (if practical) (P)

2. LEFT/RIGHT PYLON JETTISON CONTR Circuit Breakers – In (P)

3. Impact Area – Cleared (if practical) (P-CP-RN)

Clear both visually and by radar to maximum extent possible.

4. OAS Master Power – ON (N)

5. Processors – Loaded (N)

T.O. 1B-52H-34-2-9

3-4 Change 7

PYLON JETTISON PROCEDURES (RN/N READS) (Cont)

6. MIU Power – ON (N)

NOTE

• Even though pylon(s) indicate unlocked (barber pole) and READY, py-lon jettison will not occur unless EED power is available from the NDCpower supply. At least one MIU must be powered in order for the NDCpower supply to supply EED power.

• Steps 7 thru 10 must be accomplished if RDY or powered missiles areon pylons to be jettisoned.

7. Location & Station – Selected (LP, RP as required and ALL) (N)

8. PREARM-SAFE Switch – SAFE (1 second) (N)

9. Location & Station – Selected (LP, RP as required and ALL) (N)

10. Weapon Power Switch – OFF (1 second) (N)

11. Release Circuits Disconnect – Connected, light on (RN)

12. WCP PYLON LOCK-UNLOCK Switch – UNLOCK (N)

13. Pylon Jettison Consent Panel LEFT/RIGHT Switch(es) – Switch actuated, barber pole indications (P)

NOTE

Two to 10 seconds after the pylon jettison consent switch is actuated,the READY light on the pylon jettison control panel will come on.

14. Pylon Jettison Control Panel READY Light(s) – On (P)

15. Pylon Jettison Control Switch(es) – Press (P)

When pylon(s) separate, the respective READY light will go out.

16. LEFT/RIGHT PYLON JETTISON CONTR Circuit Breaker for Jettisoned Pylon – Out (P)

Do not reposition the pylon jettison consent switch(es) after the pylonshave been jettisoned, as damage to the pylon lock/unlock actuator couldoccur.

17. Release Circuits – Disconnected (RN)

7

65

4

3

21

8

A37739

CENTER

OUTBOARD INBOARD

CENTER

OUTBOARD INBOARD

CENTER

OUTBOARDINBOARD

CENTER

OUTBOARDINBOARD

RIGHT PYLONLEFT PYLON

CSRL LAUNCH/JETTISONSEQUENCEAFT VIEW

LOOKING FORWARD

8

5

12 10

4 6

6 41 25

79 11

3

321 21 3

54 6

T.O. 1B-52H-34-2-9

3-5

PREFERRED LAUNCH SEQUENCEAND JETTISON SEQUENCE

PYLON STATION NUMBER/OAS STA-TION NUMBER. USED WHEN SE-LECTING SPECIFIC MISSILES VIATHE WCP OR OAS DISPLAYS (SEEFIGURES 1-5 AND 1-12).

NOTE

SINGLE PYLON PREFERREDLAUNCH SEQUENCE AND JET-TISON SEQUENCE WILL BE:FORWARD INBOARD, OUT-BOARD AND THEN CENTER,FOLLOWED BY: AFT CENTER,OUTBOARD AND THEN IN-BOARD.

NOTE

• THE AUTOMATIC LAUNCH OR JETTISON SEQUENCE IS OAS CONTROLLEDFOR MAINTAINING OPTIMUM CG LOCATION, SAFETY, AND EXTERNAL MIS-SILE DRAG INDEX. THE SEQUENCE IS ALTERNATED BETWEEN LEFT ANDRIGHT PYLONS AS SHOWN.

• DURING COMPUTER JETTISON OF ALL MISSILES, PYLON MISSILES WILL BEEJECTED AT 1/2 SECOND INTERVALS, EXCEPT THE AFT INBOARD POSI-TIONS WILL BE EJECTED AT 1-1/2 SECOND INTERVALS TO ALLOW GREAT-ER CLEARANCE TO PREVENT COLLISION WITH THE OTHER AFT INBOARDMISSILE.

Figure 3-1. Pylon Missile Preferred Launch/Jettison Release Sequence

A37740

IND

ICA

TE

D P

RE

SS

UR

E A

LTIT

UD

E

100

0 F

T.

50

40

30

20

10

0200 220 240 260 280 300 320

0.3 0.4 0.5 0.6 0.7 0.8 0.9

50

40

30

20

10

0

50

40

30

20

10

0

IND

ICA

TE

D P

RE

SS

UR

E A

LTIT

UC

E −

100

0FT

.

INDICATED AIRSPEED KNOTS

INDICATED MACH NUMBER

T.O. 1B-52H-34-2-9

3-6

DATE: AUGUST 1981DATA BASIS: ESTIMATED

CONDITIONS: TWO AGM-86CPYLONS LOADED WITH AGM-86CMISSILES AS SHOWN.

Figure 3-2. B-52H/CALCM Loaded Pylon Jettison Restrictions

T.O. 1B-52H-34-2-9

3-7

NOTIFICATION PROCEDURES – DANGEROUS MATERIALS

Procedures for alerting the fire department andother base support elements for aircraft carryingdangerous materials are as follows:

DEFINITION OF TERMS

Definitions of some of the terms used in communi-cations are as follows:

• Dangerous Materials: Any material that isflammable, corrosive, an oxidizing agent, explosive,toxic, radioactive, nuclear, unduly magnetic, or bio-logically infective or any other material that (be-cause of its quantity, properties, or packaging) mayendanger human life or property.

• Firefighting Time: A period that begins whenthe material becomes enveloped in flames and ter-minates when the material can be expected to deto-nate, deflagrate, or begin burning.

• Withdrawal Distance: The minimum permissi-ble distance, between firefighters, rescue, and/ornonessential personnel and the site of the accident(fire/detonation), without protective barricades.

• Department of Transportation (DOT) Classifica-tions: Classifications established by DOT for handl-ing dangerous materials in transit. They defineclasses of dangerous materials.

• Inert Devices: Devices containing no dangerousmaterial but closely resembling nuclear or explosiveitems that are classified as dangerous.

• Net Explosive Weight (NEW): The actual (orhigh explosive equivalent) weight of explosive sub-stances contained within a munition/weapon to beused when applying quantity – distance criteria orother standards.

AIRCRAFT COMMANDER’S RESPONSIBILITIES

The aircraft commander must ensure that crewmembers thoroughly understand the operationalmission requirements and procedures governing thedangerous materials to be airlifted. The aircrewwill comply with applicable backup and emergencyinflight notification procedures, plan flight routes toavoid overflight of heavily populated or otherwisecritical areas, and refuse to accept any ATC clear-ance that, in the aircraft commander’s judgment,would interfere with operational necessity or flightsafety. For each flight ‘‘Dangerous Cargo,’’ ‘‘InertDevices,’’ or both (as appropriate) will be entered inthe ‘‘Remarks’’ section of the DD Form 175 or ‘‘Oth-er Information’’ section of the DD Form 1801 (ICAOFlight Plan) unless prohibited by regulations gov-erning the area of operation.

BACKUP NOTIFICATION PROCEDURES

If the ETE is less than 1 hour or if other known cir-cumstances will preclude timely receipt of informa-tion, the aircraft commander will contact the baseof intended landing by priority telephone and pro-vide tactical call sign, ETA, DOT class of dangerousmaterial aboard, DOD quantity-distance class(when applicable), NEW (total weight in pounds ofall DOT Class A and Class B explosives on board),withdrawal distance and firefighting time (if as-signed), request for special handling (if required),inert devices (when applicable) and line numbersand quantities (if applicable).

INFLIGHT NOTIFICATION PROCEDURES

At least 30 minutes (or as soon thereafter as practi-cal) before the ETA, the aircraft commander willcontact the base operations dispatcher, control tow-er, approach control, or other agency specified inthe applicable FLIP announcing that they havedangerous material and to verify receipt of arrivalnotification If advance notice has not been received,request that the information stated in backup noti-fication procedures, be relayed to the military baseoperations or civil airport manager to pass to appro-priate base support elements (Example: ‘‘Bird 51,ETA – 1200Z, DOT Class A explosives, DOD class7, ‘‘NEW’’ four zero pounds, four zero zero zero feet,3 minutes, request isolated parking, four each M-XXX bombs in bomb bay. Please relay immediatelyto fire department and other base support ele-ments.’’)

T.O. 1B-52H-34-2-9

3-8

INFLIGHT EMERGENCY NOTIFICATION PROCEDURES(WORLD WIDE)

Under inflight emergency conditions or for un-scheduled landings, the aircraft commander will in-form the appropriate Air Traffic Control Facility ofthe nature of the emergency, intentions, and, aspracticable, the information as stated in backup no-tification procedures. (Example: ‘‘Bird 51, 60 mileseast of intended landing base – Nest AFB, No. 1and 2 engines out; six personnel, forward section ofaircraft; have dangerous cargo in bomb bay of air-craft, four zero pounds of DOT class A explosives; ifexplosives become enveloped in flames, detonationmay be expected after 3 minutes; withdrawal dis-tance is 4000 feet; 10,000 gallons of fuel remaining,apply emergency procedures accordingly.’’)

Inert Devices

If inert devices are carried, the radio call will besimilar to inflight emergency notification proce-dures (world wide), identifying the devices as inert,that they present no hazard, and including theamount of fuel remaining. (Example: ‘‘Bird 51, 60

miles east of intended landing base – Next AFB,No. 1 and 2 engines shut down, six personnel for-ward compartment, inert cargo in bomb bay of air-craft; no hazard; 10,000 gallons fuel remaining; ap-ply emergency procedures accordingly.’’)

CONUS Civil Airports

When aircraft must land at a CONUS civil airportwhich has no control tower, information in inflightemergency notification procedures (world wide), asapplicable, will be furnished to the nearest FAAFlight Service Station.

Aircraft Ditching/Abandonment

If the aircraft must be ditched or abandoned, thenavigator should record the coordinates and de-scriptive location of abandoned cargo for later useby appropriate authorities.

Safe Jettison

Jettison procedures and restrictions are in the frontof this section.

T.O. 1B-52H-34-2-9


FIREFIGHTING AND EVACUATION CRITERIA

These emergency procedures consist of actions totake if munitions are involved in a fire. The aircrewshould be thoroughly familiar with these instruc-tions.

Aircraft fires involving conventional munitions can-not be definitized to any one set of circumstancesand environmental conditions. This precludes de-velopment of reliable standardized test criteria andreliable specific item firefighting and withdrawaltimes. The conclusion to be reached from availabledata is that a munitions reaction to fire is a func-tion of case thickness and type of explosive fillerwhich can be varied by environmental conditions.Since the circumstances of a fire cannot be pre-dicted, specific item by item firefighting and with-drawal times cannot be determined with any degreeof reliability.

Normally, aircraft fire involving munitions occursunder a set of circumstances wherein it is impossi-

ble to know immediately the specific missile, bomb,or CBU model number. Such information is abso-lutely essential for specific firefighting and with-drawal times. Therefore, these times are presentedfor family groups only; i.e., bombs, CBU’s, missile,etc.

• Bombs: See T.O. 1B-52H-34-2-1• CBUs: See T.O. 1B-52H-34-2-1• Missiles: Missiles normally react in a propul-sion, detonation, or both between +45 seconds and2 minutes. A propulsion hazard (missile flight) ex-ists within 45 seconds and a major hazard to envi-ronment and firefighting capability exists after 1minute. Approach the fire, if necessary, from theside of the aircraft.

The firefighting guidance provided in AFI 91-201will be utilized in all instances. There is no specificwithdrawal time assigned to items which do notalign into one of the family groups mentionedabove.

NOMENCLATURE WITHDRAWAL TIMEWITHDRAWAL DISTANCE (FT) FIRE

NONESSENTIAL PERSONNEL SYMBOL

AGM-86C 2 - 4 MINUTES 4000’ 1

AGM-86D TBD MINUTES TBD’ 1

Figure 3-3. Fire Fighting and Evacuation Criteria

T.O. 1B-52H-34-2-9

Change 7 4-1

Supplementary Data section IV


OPERATIONAL TEST LAUNCH SYSTEM 4-1

PLUS COUNT MODE 4-3

OPERATIONAL TEST LAUNCH SYSTEM

OTL FUNCTIONS

The operational test launch (OTL) system is used toevaluate the performance of the B52/CALCM sys-tem, and provide actual launch training for aircrewpersonnel. No special equipment is installed on theaircraft to provide for control and monitoring dur-ing captive flight. Special equipment is installed onthe OTL missile to provide for control and monitor-ing during flight, and control, monitoring, andemergency termination after launch. The missilereceives test range verification of telemetry whileon carrier power prior to launch. Launch of an OTLmissile is accomplished using the normal launch se-quence. Operational test launch data is displayedon the selected MFD by the CALCM SMO.

MISSILE OTL EQUIPMENT

The AGM-86C missile OTL equipment consists of amodified nontactical instrumentation kit (MNTIK).The kit is installed in the missile payload bay, andother components are installed on the missile. TheMNTIK instrumentation package provides instru-mentation links with the test range for the purposeof monitoring and evaluating missile performance.These functions are accomplished by MNTIK sub-systems. A radar beacon and the high accuracymultiple object tracking system (HAMOTS) are

used for tracking purposes, and a telemetry subsys-tem transmits data on missile system performancefor correlation with ground tracking data. Theflight termination system (FTS) has both a com-manded and a fail-safe flight termination mode.Loss of a fail-safe tone for 60 seconds automaticallyprovides a termination mode. For flight terminationa drogue chute is deployed and a squib operatedfuel shutoff valve is activated.

REMOTE COMMAND CONTROL SYSTEM

A Remote Command Control (RCC) system can con-trol an OTL configured AGM-86C missile. This isessential when flying outside a test range to pro-vide a flight termination and collision avoidance ca-pability. Missile flightpath can be offset left, right,up, or down by command and then restored to origi-nal flightpath or manually flown to the desired areafor flight termination. A fail-safe tone is also pro-vided continuously and its absence for 60 secondswill automatically terminate missile flight.

NOTE

Once the RCC system is used in the manualmode, the missile cannot be returned to nor-mal flight.

T.O. 1B-52H-34-2-9

4-2 Change 10

OTL CAPABILITIES.

This paragraph describes any differences in theSMO capabilities when conducting OTL as opposedto being in normal STRIKE mode. The following areimplemented by the SMO as part of the OTL pro-cess.

• OTL Instrumentation power control• Monitor OTL faults.

1. Instrumentation power fail.2. Flight term enable.3. OTL battery timer expired.4. Armed solenoid fault in OTL.

For each OTL master fault, a recording will be gen-erated and weapon power will be removed. The onlyexception to this is when instrumentation powerfails prior to battery activate when the only affect isto terminate LCD.

IKB Commands

IKB commands associated with OTL are found onthe CALCM Supervision Menu and are described inthe following subparagraphs. These commands canbe issued regardless of CALCM power state (i.e.,CALCM can be ON or OFF). If the commands areissued while the selected CALCM is OFF, they willbe carried out when the CALCM is powered ON.The result in the OTL power status is what wouldresult if the commands were issued with theCALCM ON.

TELEMETRY POWER ON COMMAND CF-55A

Operator entry of CF-55A will result in turningOTL instrumentation power ON for the selectedweapon. The SMO will reject a CF-55A command toturn OTL instrumentation power ON and displaythe command in reverse video if any of the follow-ing conditions exist.

• One location and station is not selected.• Not in OTL mode of operation (i.e. sortie mis-

sion is not a test launch).• There are two weapons with telemetry power

already on carrier power.

The SMO will ignore a CF-55A command to turnOTL instrumentation power ON for a selectedweapon where OTL power is ON.

TELEMETRY POWER OFF COMMAND CF-55B

Operator entry of CF-55B will result in turningOTL instrumentation power OFF for the selected

weapon. The SMO will reject a CF-55B command toturn OTL instrumentation power OFF and displaythe command in reverse video if any of the follow-ing conditions exist.

• One location and station is not selected• Not in OTL mode of operation (i.e. sortie mis-

sion is not a test launch).

The SMO will ignore a CF-55B command to turnOTL instrumentation power OFF for a selectedweapon where OTL power is OFF.

TELEMETRY POWER TRANSFER COMMANDCF-55C

Operator entry of CF-55C will result in the transferof OTL instrumentation power from carrier powerto the weapon OTL battery for the selected weaponwhere carrier OTL instrumentation power is ap-plied. Operator entry of CF-55C will result in thetransfer of OTL instrumentation power from theweapon OTL battery to carrier power for the se-lected weapon where weapon OTL battery power isapplied. The SMO will ignore a CF-55C commandto transfer OTL instrumentation power if carrierand missile instrumentation power are both OFF.The SMO will reject a CF-55C command to transferOTL instrumentation power and display the com-mand in reverse video if any of the following condi-tions exist;

• One location and station is not selected.• Not in OTL mode of operation (i.e. sortie mis-

sion is not a test launch).• Less [AMI] Operational mode is PLUS CT.• [AMI] A Captive Carry mission is loaded.• If transfer is from battery to carrier, there are

two weapons with telemetry power already on car-rier power.

NOTE

OTL battery power only lasts a total of 11minutes 55 seconds. While OTL batterypower can be turned OFF, if it is turnedback on, the life expectancy for that batteryis reduced by the amount of time it was pre-viously on. Once the time expires, theCALCM powers down with a permanent fa-tal fault. Also, while any number ofCALCMs can have OTL battery power on atthe same time, only the first four will havetheir battery time checked for expirationand fault reporting. If SMO is reloaded,four more CALCMs can have their timerschecked.

T.O. 1B-52H-34-2-9

Change 3 4-2A/(4-2B blank)

CSRL CARRIAGE OF CALCM MISSILES WITHA TEST INSTRUMENTATION KIT(TIK)

CALCM mass properties differ from operationalmissiles when they have a Test Instrumentation Kit(TIK) added. The Center of Gravity limits areshown in figure 4-0A. Acceptable weight and CG

combinations fall below and to the right of thecurve. Figure 4-0A is suitable for test missiles hav-ing a CG at Water Line (WL) 98.40 or above. Due tolauncher torque limits, CSRL missile carriage is re-stricted to two adjacent missiles if no other missilesare symmetrically loaded.

Figure 4-0A CSRL Carriage CG Limitations

T.O. 1B-52H-34-2-9

Change 10 4-3

PLUS COUNT MODE

This paragraph describes the SMO capabilitieswhen the PLUS CT function is active. Entry intoCaptive Carry/PLUS CT mode is determined by theSMO when the loaded sortie mission has theunique PLUS CT identifier and its payload type in-dicates “OTL”. There is no crew action required toenter PLUS CT mode other than loading a sortiemission with the previously mentioned characteris-tics. PLUS CT missile control is the same as forOTL Capabilities, and includes Simulation Capabil-ities when in either simulation mode, with excep-tions discussed in the following paragraphs.

Less [AMI] MODE INDICATIONS

When Plus Count mode is active, PLUS CT is dis-played in the WPN SUPV window on the ControlFunction Menu (CF-) and the Weapon SupervisionMenu (figure CF-5), and in the CALCM SUPV win-dow on the CALCM Supervision Menu (CF-55).

LAUNCH

Only one CALCM will be in captive carry launch(i.e. providing steering meter data to the SMO) atone time during PLUS CT. Safe launch restrictionswill not inhibit a captive carry launch. When a

CALCM is in captive carry launch, the missile sta-tus window will display Less [AMI] PL, [AMI] CL,instead of AW, unless either SIM mode is active.

FLIGHT COMMAND INDICATOR

The SMO receives roll steering data from theCALCM after its captive launch which is processedinto FCI (figure 4-1) prompts for the pilot. The pilotcan fly the aircraft to follow the CALCM’s flightpath by keeping the roll error, (displayed on theheading error indicator) as small as possible. Thisinformation will continue to be supplied until themissile is powered OFF, either manually or auto-matically (due to a fault). Targeting is inhibitedwhile steering meter data is supplied to the SMO.

TERMINATION OF PLUS CT MODE

PLUS CT mode can be terminated by loading in amission that does not have the unique PLUS CTidentifier and/or its payload type does not indicateOTL. However, a different mission can only beloaded after powering down all MIUs and CALCMs.

JETTISON IN PLUS CT MODE

CALCMs can be jettisoned while in PLUS CT Modeusing the same procedures as STRIKE missiles.

T.O. 1B-52H-34-2-9

4-4

Flight Command Indicator

1 HEADING ERROR INDICATOR


1 Heading Error Indicator For CALCM captive carriage, the heading error indicator displays the an-gular difference between the CALCM roll steering command and the air-craft roll angle.

Figure 4-1. Flight Command Indicator

T.O. 1B-52H-34-2-9

5-1/(5-2 blank)

Operating Limitations section V


AIRCRAFT AVIONICS LIMITS ON LAUNCH 5-1

SPEED RESTRICTIONS FOR PYLON MISSILE SEPARATION 5-1

MISSILE LEVEL FLIGHT LIMITS FOR MISSILE SEPARATION 5-1

AIRCRAFT AVIONICS LIMITS ON LAUNCH

Instantaneous values of level flight limits are com-pared to OAS preprogrammed inputs, and if out oftolerance, result in a missile countdown hold. Theindication is displayed as COUNTDOWN and SAIRin reverse blinking video and the out-of-limits con-dition in reverse video on the selected MFD.

The aircraft will maintain straight andlevel flight for a period of 5 seconds beforeto 5 seconds after missile launch. This is toprevent the possibility of aircraft/missilecollision.

SPEED RESTRICTIONS FOR PYLON MISSILESEPARATION

JETTISON ENVELOPE LIMITS

Refer to T.O. 1B-52H-34-2-9-1 Section III.

LAUNCH ENVELOPE LIMITS

Refer to T.O. 1B-52H-34-2-9-1 Section V.

MISSILE LEVEL FLIGHT LIMITS FOR MISSILESEPARATION

The OAS determines the missile level flight limitsfor safe separation and launch by comparing mis-sile outputs to preprogrammed inputs. The OASpreprogrammed inputs include:• Pitch attitude, roll rate, angle and rate• Acceleration, lateral and normal• Vertical velocity• Aircraft/missile clearance limits

Launch inhibit is determined prior to enteringlaunch countdown and 45 second launch countdownhold is determined immediately before battery acti-vate command. TA launch countdown hold (approx.5.6 to 13 seconds) can occur after battery activationand before last transmission.

T.O. 1B-52H-34-2-9

6-1/(6-2 blank)

Mission Planning section VI


TRANSPORTATION OF HAZARDOUS MATERIAL 6-1

INFLIGHT MISSION DATA CHANGES 6-1

TRANSPORTATION OF HAZARDOUS MATERIAL

Prior to any flight involving transportation of weap-ons, the aircraft commander must make sure thatall crewmembers have a thorough understanding ofclearance procedures, communications, security re-quirements, inflight normal and emergency notifi-cation procedures, and safety jettison procedures.

CLEARANCE PROCEDURES

1. The flight will be planned to minimize flyingover metropolitan areas (cities over 100,000population). During flight, if a clearance con-taining noise abatement procedures is re-ceived that in the judgment of the aircraftcommander would interfere with operationalnecessity or flight safety, it will be refused.

2. “Hazardous Cargo” or “Inert Cargo” or both(as appropriate) will be entered in the re-marks section of the DD Form 175.

3. For flights to or from areas outside the CON-US or if any portion of a flight requires com-pliance with ICAO rules, clearance proce-dures as listed in the USAF Foreign Clear-ance Guide and Special Weapons OverflightGuide will be followed. No reference will bemade to “Hazardous Cargo” in the remarkssection of DD Form 175 or during landing atthe scheduled landing base.

COMMUNICATIONS SECURITY

Strict communication security procedures will befollowed at all times. If, in the aircraft commander’sjudgment, an emergency condition requires an im-mediate emergency landing and a choice must bemade between communications security and flightsafety, safety will take precedence. Disclosure ofclassified information to the extent necessary toavoid compromising flight safety must be acceptedas an condition of military service. The judgment ofthe aircraft commander on such cases is not subjectto after-the-fact debate or review.

NORMAL NOTIFICATION PROCEDURES

It is the responsibility of the major command con-cerned to ensure all required information is trans-mitted to departure and destination (primary/alter-nate) bases far enough in advance to ensure ade-quate preparation before the departure/arrival ofaircraft carrying “hazardous cargo”. If the ETE isless than 1 hour or if other known circumstanceswill preclude timely receipt of information, the air-craft commander will notify the base of first in-tended landing by telephone that he has hazardouscargo on board, his ETA, and the applicable linenumbers for his cargo. EXAMPLE: “Hasty 46 willarrive at your base at 1200 ZULU with hazardouscargo, 4 each line number 11 and 12 each line num-ber 171.”

INFLIGHT MISSION DATA CHANGES

See “Missile Targeting/Retargeting” Section VII.

T.O. 1B-52H-34-2-9

Change 10 7-1

Systems Operation section VII


AIRCRAFT OAS/CALCM OPERATION 7-2

SMO CAPABILITIES 7-3

MISSION DATA 7-9

SAFE LAUNCH DETERMINATION 7-24

IN-RANGE DETERMINATION 7-25

AUTOMATIC RETARGETING 7-31

MISSILE LAUNCH 7-33


SIMULATION 7-38

BOMB TONE SCORING 7-39

SIT/MIT AND CF-552 7-39

MALFUNCTION ANALYSIS 7-40

ERROR MESSAGES 7-40

T.O. 1B-52H-34-2-9

7-2

AIRCRAFT OAS/CALCM OPERATIONOAS/MISSILE POWER

OAS master power switch controls the applicationof power to the following:

• OAS.• Weapon Control Panel (WCP).• Armament Interface Unit (AIU).• Ejector Unlock Power Circuitry.• Enable Missile Power.• Enable MIU Power Switches.

MIU power switches (MIU/LP, MIU BAY, & MIU/RP) provide:

• MIU Power.• Missile Heater Power.• Enable Missile Power.• MAU-12 Electro-Explosive Device (EED) Power

Circuitry.

AIU interfaces the OAS with:

• Environmental Control Units (aircraft and mis-sile).

• Power Distribution Box (PDB).• Radar Altimeter.• Bomb Tone Scoring System.

Circuit Breakers:

Pilot’s Circuit Breaker Panel• LEFT PYLON JETTISON CONTROL circuit

breaker provides power to the left pylon jettisoncontrol switch.

• RIGHT PYLON JETTISON CONTROL circuitbreaker provides power to the right pylon jetti-son control switch.

• GAM-72 GEAR JETTISON & AGM-69A circuitbreaker provides power to the Bomb Bay LimitSafety switches and the AIU bomb door OPENmonitor circuit.

Left Forward BNS Overhead Breaker Panel

• CONTROLS AND DISPLAYS - WPN CONT PNLcircuit breaker provides control and displaypower to the weapons control panel.

Right Forward BNS Overhead Circuit BreakerPanel

• NORMAL RELEASE circuit breaker providespower to the pilot’s munitions consent panel lock-unlock switch.

• JETTISON POWER circuit breaker providesmissile jettison power to the pilot’s and radarnavigator’s missile jettison controls

Right-Hand S/V Filter Box Circuit Breaker Panel

• WCP circuit breaker provides power to the weap-on control panel.

• AIU circuit breaker provides power to the arma-ment interface unit.

Navigator’s Side Panel

• CSRL PDUC circuit breaker provides power tothe PDUC control box.

T.O. 1B-52H-34-2-9

Change 10 7-3

SMO CAPABILITIES

The SMO capabilities, responses to operator com-mands and general operation procedures are de-scribed in the following paragraphs and are struc-tured around the operational time line as follows.

• MIU and PDUC power.• Applying missile power.• Selecting a target/mission for launch.• Ranging on the selected target.• Launching CALCMs.• Jettisoning missiles.

NOTE

[AMI] In order to accomplish any of the sixfunctions listed above, the CALCM SMOmust be designated as the primary SMO(CF-62x).

Commands, Menus and displays will sometimes beidentified by the command which invokes them. Forexample, ECU Power Override will be referred to asCF-68.

STRIKE CAPABILITIES

When the SMO is loaded, it is initialized intoSTRIKE mode. The operator can verify the current-ly active SMO mode, whether STRIKE, FULL SIM,PART SIM, or Less [AMI] PLUS CT, on either theCF- Menu, the CF-5 Menu or the CF-55 Menu. Ifthe SMO is currently in either SIM mode, STRIKEmode can be commanded by entering CF-50. If theSMO is currently in PLUS CT mode, STRIKE modecan be entered by loading a non-Captive Carry mis-sion. If in FULL SIM or PART SIM mode, the SMOwill reject a CF-50 command and display it in re-verse video if simulated power is applied to anyMIU.

WEAPON CONTROL EQUIPMENT MONITOR AND POW-ER CONTROL

The Weapon Control Equipment (WCE), which con-sists of the AIU, ECU, PDUC (for bay weapons),and MIUs, must have power applied to enable theoperator to apply power to control and release anymissiles. The AIUs function is to control the ap-plication of power to the ECU and MIUs, and to

control the bay doors. The ECUs function is to sup-ply conditioned air to the MIUs and all loadedCALCMs. The PDUC function is to control rotationof the rotary launcher for bay weapons. The MIUsprovide data conditioning, monitoring and control,ejector rack monitor and control, weapon discretes,missile status, and power application to the mis-sile(s). AIU power is applied when OAS masterpower is turned on. ECU and MIU power are all ap-plied when the operator commands MIU power onvia the PCP. PDUC power is applied when the oper-ator commands CSRL PDUC power ON via theCSRL PDUC Control Box.

WCE Status

The operator can review the operational status ofthe AIU, ECU, PDUC, bay MIU (B MIU), left pylonMIU (L MIU), and right pylon MIU (R MIU) usingthe PME Status display (FRMT-6). The SMO com-municates with these LRUs via the 1553 data busesA and C. FRMT-6 shows AIU, MIU and PDUC Abus and C bus communication status and AIU,ECU, MIU and PDUC failure status. If the textfields (A, C, or X) are blank, then no failures haveoccurred for that WCE since startup, or the lasttime the FMS fault reset command was entered. Ifa MIU or PDUC A bus communication failure hasoccurred, an A will be displayed for the PDUC, bayMIU, left MIU, or right MIU. If a MIU or PDUC Cbus communication failure has occurred, a C will bedisplayed for the PDUC, bay MIU, left MIU, orright MIU. If an LRU failure has occurred, an Xwill be displayed for the ECU, PDUC, bay MIU, leftMIU, or right MIUs, respectively. In a similar man-ner, FMS will display an A or a C next to AIU if anAIU A bus or C bus communication failure has oc-curred and an X next to AIU if an AIU failure hasoccurred. When text is displayed, it indicates that afailure has occurred and whether it currently existsor not. If a failure occurred and currently exists, thetext (A, C or X) will be displayed in reverse video. Ifa failure occurred and does not currently exist, thetext (A, C or X) will be displayed in normal video.To clear unwanted data from FRMT-6, the operatorcan enter the FMS fault reset command, CF-66, todelete the display of all failures which no longer ex-ist. When the CF-66 command is entered, all failuretext displayed in normal video will be blanked andany text displayed in reverse video will remain.

T.O. 1B-52H-34-2-9

7-4 Change 10

The AIU, ECU, MIU, and PDUC failure status isalso displayed on the CALCM Status and Inventorydisplay (FRMT-7). AIU will be displayed in reversevideo if the AIU has failed. ECU will be displayedin reverse video if the ECU has failed. MIU will bedisplayed in reverse video the respective MIU, if ei-ther MIU communication or the MIU have failed.LNCHR will be displayed in reverse video if eitherPDUC communication or the PDUC have failed.DOORS will be displayed in reverse video if thedoors have failed. Each display will be removed ifthe associated failure status clears. ECU, MIU,LNCHR, PDUC, and WCP Master faults and Advi-sories will be displayed at the bottom of the MFD.

MIU

The MIU interfaces with the avionics processor(AP) receiving commands and transmitting missilestatus via the data bus. It also interfaces with theWCP, the switching unit, and the power distribu-tion box (PDB). The MIU provides missile squib cir-cuit actuation commands, release squib circuit com-mands, ejector unlock signals, power control toswitching unit, fault detection, performs analog todigital conversion, and analog measurement for theAP. Upon receipt of MIU power on command, theOAS issues an ECU power command through theAIU to maintain equipment temperature within op-erational limits

MIU Power Application

MIU power is applied using the MIU POWERswitches on the OAS Power Control Panel. Whenthe operator presses a power switch, the switchlatches in the depressed position, power is appliedto the MIU for the selected location and that LRUwill be initialized, and the light in the switch comeson.

If a fault is detected during power on, the MIUpower-ON sequence will be terminated, the ap-propriate fault will be displayed and any powerswhich have been applied will be removed. However,if ECU Power Override is currently active, the SMOwill not declare an ECU ac Power fault regardlessof ECU ac power availability ([AMI] or an ECUfault), and continue with the power-ON sequence.The power-ON sequence takes less than 24 seconds.The operator can verify completion of the MIU pow-

er-on sequence by viewing FRMT-7. When the se-quence is complete, the following display changeswill occur on FRMT-7 next to each MIU stationnumber:

A. The Store window will change from blank to ei-ther P, C, or X to identify the type of weapon pres-ent at the station or blank to indicate that no weap-on is present.

1. P will appear if the ejector and umbilical sta-tus show a weapon is present at the station andthe weapon is not known to be CALCM.

2. C will appear if the ejector and umbilical sta-tus show a weapon is present at the station andumbilical status indicates the weapon is aCALCM/ALCM. (Since there is no way to obtainpositive weapon identification between anALCM and a CALCM at the umbilical, aCALCM will be assumed.)

3. X will appear if the ejector or umbilical sta-tus shows no weapon is present at the station.

B. The CALCM Status window for each station willchange from blank to OF or NG, when a weapon ispresent to indicate weapon status.

1. OF will be displayed to indicate weapon elec-tronic power is not applied at the station when aCALCM is present.

2. NG will be displayed if a permanent fatalfault has occurred for the missile and a releaseof that missile has not been attempted.

3. Nothing will be displayed when there is nostore present.

C. The Ready To Launch Status window will dis-play SAF if a CALCM is present and the WCPPREARM/SAFE switch is in SAFE. If no CALCM ispresent, the window will remain blank.

D. The Station Fault window below the station linewill display a fault indication if a CALCM is pres-ent and if any faults have been detected at the sta-tion. All faults are listed and described in at theend of this section. If no CALCM is present, thewindow will remain blank.

T.O. 1B-52H-34-2-9

Change 10 7-5

PDUC Power Application

PDUC power will be applied when the operatortoggles the CSRL PDUC power switch to the ONposition on the CSRL PDUC Control Box. If theCSRL PDUC power switch is in the ON positionwhen OAS Master Power is applied, power will beapplied to the PDUC. Even though there is no soft-ware status of the CSRL PDUC power switchthrough the SMO, the PDUC is statused, so whenthe operator depresses the OAS Master PowerSwitch, if the PDUC does not respond, fault indica-tions will be displayed on FRMT-6. Upon power ap-plication the PDUC will automatically perform in-ternal initializations for a maximum of five se-conds. Any faults detected will be set by the PDUCat the completion of initialization. If after five sec-onds, communication cannot be established withthe PDUC, a Double MUX Error will be indicatedon the PME Status Display (FRMT-6) with a re-verse highlight A, a reverse highlight C, and a re-verse highlight X. In addition a PDUC MasterFault message will be displayed at the bottom ofthe MFD and LNCHR will be displayed on theWeapon Status and Inventory Display (FRMT-7).

Five seconds after communication is established, ifthe PDUC Controller Reset Bit indicates PDUC in-itialization failed, a PDUC fault will be indicated onthe PME Status Display (FRMT-6) with a reversehighlight X on FRMT-6. In addition, a PDUC Mas-ter Fault message will be displayed at the bottom ofthe MFD and LNCHR will be displayed in the laun-cher fault window of the Weapon Status and Inven-tory Display (FRMT-7). If PDUC CommunicationFaults previously existed, they will be displayed innormal video on FRMT-6 unless an actual fault ispresent.

NOTE

Launcher faults may occur if the PDUC ispowered on after the SMO is loaded. Manu-ally commanded rotation of the launchermay be required to clear the faults and al-low automatic launcher rotation capability.

WCE Power Removal

MIU power is removed when the operator pressesthe MIU POWER switch (MIU/LP, MIU/BAY orMIU/RP) on the PCP a second time allowing it toreset to the outward position. Power is then re-moved from the respective MIU along with theweapon power for any weapons which have powerapplied at that location. No faults will be displayedduring MIU power removal.

The operator can verify completion of the MIU pow-er removal sequence by viewing FRMT-7 and/or thePCP. When the sequence is complete, the selectedMIU POWER switch will no longer be illuminatedand all data contained in the windows on FRMT-7for each station at that MIU location will beblanked within 3 seconds.

The PDUC is powered down when the operatortoggles the CSRL Power Control switch to OFF.PDUC Communication Faults will be displayed inreverse video on FRMT-6.

WEAPON MONITOR AND POWER CONTROL

After applying power to a MIU, weapon electronicpower can be commanded ON for any missile(s) atthat location from the WCP. Weapon electronic pow-er will not be applied under the following condi-tions:

A. Umbilical status indicates weapon is not aCALCM/ALCM.

B. A permanent fatal fault has occurred for theweapon on a previous power cycle.

C. A weapon OFS erase has occurred on a previouspower cycle.

D. An ECU AC Power fault is active and ECU Pow-er Override is not commanded.

Missile power must be applied to enable the SMOto verify the warhead type and the operational sta-tus of the missile(s), to initiate alignment of theCALCM INE, and to transmit targeting and mis-sion data to the missile(s) prior to launch.

T.O. 1B-52H-34-2-9

7-6 Change 9

Weapon/Ejector Status

The operator can view the operational status ofeach CALCM missile and station ejector via theCALCM Status and Inventory display (FRMT-7).The CALCM Status and Inventory display showsmissile presence, missile power, missile state, mis-sile faults and targeting status for each station ateach MIU location where power is applied (baylauncher and left and right pylon). The station sta-tus windows are grouped together for each station.The station number is displayed immediately to theleft of missile presence window.

The text and associated indications for station sta-tus on the CALCM Status and Inventory displayare delineated in the following subparagraphs. Allof these fields will be blank for each station wherethe MIU does not have power applied at that loca-tion. If no weapon is present an X will be displayedto indicate the store is missing, and all other win-dows will be blank. If a weapon type is unknown allwindows except presence window will be blank. Thepresence window will display P to indicate a store ispresent but unidentified.

WEAPON PRESENCE

The weapon presence window on the CALCM Sta-tus and Inventory display indicates what the SMObelieves to be present at the umbilical based on thedata available from the ejector and MIU.

WEAPON WARHEAD TYPE.

The weapon warhead type field on the CALCM Sta-tus and Inventory display indicates the warheadtype status received from the CALCM missile atthat location and station. The weapon warheadtype will be a hexadecimal value from 0 through 9or A through F. 1 is used for a blast-frag warheadand 2 is used for a penetrator warhead.

WEAPON STATUS.

The weapon status field on the CALCM Status andInventory display indicates the status of theCALCM missile at that location and station.

READY TO LAUNCH (RTL) STATUS.

The RTL status on the CALCM Status And Inven-tory display indicates if RTL permission has beenprovided each weapon. The default status, dis-played when weapon power is turned ON, is SAF(safe). The operator must command Prearm, indi-cated by RTL, for each CALCM before it can belaunched. The operator can, at any time, commandSAF to prevent selected CALCMs from being laun-ched. Prearm Enable does not need to be command-ed to use the Prearm/Safe switch on the WCP.

TARGETING STATUS

The targeting status field on the CALCM StatusAnd Inventory display indicates, R, when a CALCMis ready to receive a mission. Once targeting beginsfor the CALCM, the launch point, nn (or Direct Tar-get Designation) is displayed. The launch pointnumber or direct target designation will be under-lined when the mission has been loaded into theCALCM. If no weapon mission is available for aCALCM, GPS initialization data will be loaded intothe weapon and indicated with a G. After theCALCM has been launched, the launch point, nn(or direct target), is displayed.

FLEX/DIRECT TARGETING INDICATION

The flex/direct targeting indication field on theCALCM Status and Inventory display indicateswhether the weapon has been flex or direct targe-ted. The flex targeting indication, F, will be dis-played if flex targeting has been performed. The di-rect target indication, D, will be displayed if directtargeting has been performed, otherwise the fieldwill be blank. After launch, this field will retain theappropriate targeting indication.

WEAPON FAULTS

The weapon fault field on the CALCM Status andInventory display indicates any CALCM missilefaults that are present. The highest priority faultwill be displayed in the field if more than one faultexists. The weapon fault indicators which are dis-played are provided at the end of this section.CALCM temperature, altimeter, and INS faults, ifthey exist, are displayed for a selected CALCM inwindows at the bottom of the MFD in the SelectedStation Status Advisory area on FRMT-7xy.

T.O. 1B-52H-34-2-9

7-7

ORDNANCE ALARM STATUS

The ordnance alarm status on the CALCM StatusAnd Inventory display in the Selected Station Sta-tus Advisory area is displayed when a MIU is pow-ered ON and FRMT-7xy is entered.

EJECTOR STATUS

The ejector status on the CALCM Status And In-ventory display in the Selected Station Status Advi-sory area is displayed when a MIU is powered ONand FRMT-7xy is entered.

OTL POWER STATUS

OTL is displayed as a label with OTL power statusin the Selected Station Status Advisory area ofFRMT-7xy when the MIU for the selected MIU ispowered ON, the mission is identified as OTL.

COMMAND DESTRUCT (C/D) STATUS

C/D is displayed as a label with the command de-struct status is displayed in the Selected StationStatus Advisory area of FRMT-7xy when a weaponis powered ON and the mission is identified asOTL.

BACKUP WEAPON TARGETING STATUS

The backup weapon targeting status is displayed inthe Selected Station Status Advisory area onFRMT-7xy when a weapon is powered ON.

WEAPON POWER APPLICATION

Missile electronic power will be applied when theoperator presses the desired Location (left, bay and/or right) and Station (1 through 6 for the pylonsand 1 through 8 for the bay or ALL) switches on theWCP and momentarily moves the MSL PWR switchto the ON position. Subsequently, power will be ap-plied to the selected missile(s) and they will be in-itialized.

If the SMO is unable to complete missile power ap-plication sequence it will be terminated for thatmissile, the appropriate fault will be displayed andany missile power which has been applied to thatmissile will be removed. The operator can verifycompletion of the missile electronic power applica-tion sequence by viewing FRMT-7. When the se-quence is complete, the following display changeswill occur within 3 seconds on FRMT-7 next to eachselected MIU station number where power was ap-plied:

A. A hexadecimal number between 0 and F (inclu-sive) will be displayed to indicate warhead type forthe CALCM.

B. The missile status will change from OF to ON toindicate weapon electronic power is available at thestation. This status will change to CA while theweapon is coarse and fine aligning, to TA after finealignment complete to indicate a transfer align-ment maneuver is required, to AL when fine align-ment and transfer alignment maneuver have com-pleted (if the GPS receiver is already initialized sta-tus will change from TA to GO), and to GO whenthe missile is both aligned and the GPS receiver isinitialized.

T.O. 1B-52H-34-2-9

7-8

C. The consent for launch window will display SAFto indicate ready-to-launch consent has not beenprovided. Once the operator have given ready-to-launch consent this status will change to RDY.

D. The mission data window will be blank untilmissile status displays CA, at which time it willcheck for the ready to receive mission data indica-tion so that R can be displayed to indicate theCALCM is ready to receive a mission.

E. The station fault window will display a fault in-dication if any missile faults have been detected atthe station.

The following limitations apply to weapon powerapplication:

• The associated MIU must have power appliedand be initialized.

• At least one weapon station selected must bevalid.

• At least one selected weapon station musthave no power applied.

• The weapon(s) selected must be present.• The weapon(s) selected must have a C in pres-

ence window.• The weapons selected must not have any per-

manent fatal faults. If a fatal fault exists for a mis-sile, NG will be displayed in reverse video. A weap-on erase is considered a permanent fatal fault.

NOTE

• If weapon power is automatically removedbecause of a COMM NO GO or a 42-SCAGE master fault, or if weapon power iscommanded off during caging (i.e., weaponstatus on FRMT-7 shows ON), weapon pow-er should not be applied for 8 minutes.

• If the MIU is powering down when reconfi-guration occurs, it will immediately indicatethat it is off, as will any powered-on weap-ons for the MIU. It will be necessary to waitfor 8 minutes of gyro cool-down time priorto weapon power application for any weap-on powered down in this manner.

WEAPON POWER REMOVAL

Missile electronic power will be removed when theoperator depresses the desired Location (left, bayand/or right) and Station (1 through 6 for the py-lons and 1 through 8 for the bay or ALL) switcheson the WCP and momentarily moves the MSL PWRswitch to the OFF position. Subsequently, powerwill be removed from the selected CALCM(s).

The operator can verify completion of the missileelectronic power OFF sequence by viewing FRMT-7.The following display changes will occur on FRMT-7next to each selected location/station:

• The missile status window will display ON un-til electronic power is removed (approximately 15seconds).

• The missile status window will change to OFindicating weapon electronic power is not availableat the station.

• The station fault window will display a faultindication if any missile faults have been detectedat the station.

• The remaining windows on the station linewill be blanked.

The following limitations apply to weapon power re-moval:

• At least one selected weapon location/stationmust be valid.

• At least one selected weapon station musthave power applied.

• A selected station with launch countdown inprogress will be launched, not powered down.

Missile electronic power is also removed from allweapons at a location when the MIU power at thatlocation is removed. The preceding limitations onweapon power removal do not apply when associat-ed with MIU power removal.

T.O. 1B-52H-34-2-9

Change 10 7-9

MISSION DATA

Less [AMI] Prior to launching a CALCM, missiondata must be provided from a valid CALCM weaponDTUC. After this has been performed, the CALCMmission may be modified using Flex targeting in-puts or the CALCM may be direct targeted. If theoperator enters an invalid command through theIKB, the command will be displayed in reverse vi-deo. If the operator inputs invalid data values, theaffected data fields will be displayed in reverse vi-deo. The details are described in the following para-graphs.

[AMI] Prior to launching a CALCM, weapon mis-sion data must be provided to the CALCM from avalid CALCM weapon group on a DTC or from op-erator entered data to target or initialize it. Weaponmission data can only be loaded to a CALCM whilethe SMO is primary. Once a CALCM is targeted orinitialized, it will retain that weapon mission datauntil it is powered off or targeted again. The target-ing process can be monitored on the Stores Summa-ry display (FRMT-77), the Weapon Status and In-ventory display (FRMT-7), or the CALCM GroupAssignment display (CF-DF from FRMT-7). Onlyone CALCM can be the primary weapon targeted toa launch point at any time. The following subpara-graphs describe the types of weapon mission datamanagement controlled by the SMO.

MISSION TYPES

The SMO supports three types of weapon missions:

• Preplanned mission.• Flex targeted mission.• Direct targeted mission.

Less [AMI] Preplanned Mission

Each CALCM must be targeted from the weaponDTUC prior to availability for launch. This is initi-ated by the operator entering CF-559 when a B-52mission containing CALCM launch points is loadedand a CALCM weapon DTUC is available. Thelaunch points are assigned to the CALCM missiles(which have power applied) with the indicatedmatching warhead type, in the order of the pre-ferred launch sequence (see section III). (To ensurethat the preferred launch sequence is properly fol-lowed, CF-559 should not be entered until allCALCMs with power applied show R in the missiondata window FRMT-7). The mission associated withthe launch point is loaded into the primary weaponand up to two backup weapons, with the same war-head type as the primary weapon, so they will beready for launch in the event the primary weaponfails. During mission load, the launch point numberfor the mission being loaded will be displayed inbright video on the CALCM Status and Inventorydisplay for that weapon. After mission load is com-plete, the launch point number will be displayed inbright underline video for that weapon. Only oneCALCM can be the primary weapon targeted to alaunch point at any time. After initial targeting hascompleted for a CALCM, it can be manually tar-geted with a different mission from the CALCMweapon DTUC by selecting a single location andstation combination on the WCP and enteringCF-556,nn, where nn is the CALCM launch pointdesired for the selected missile. Up to two availablebackups will also receive the new targeting data.Figure 7-1 illustrates an example of mission(launch point) assignments for multiple warheadtypes.

[AMI] Preplanned Mission

Preplanned mission data is provided on the DTCalong with the B-52 missions that have CALCMlaunch points in them. Preplanned mission data isloaded into CALCMs from the DTC by either auto-matic targeting or manual targeting. Figure 7-1 il-lustrates an example of mission (launch point) as-signments for multiple warhead types.

T.O. 1B-52H-34-2-9

7-10 Change 10

[AMI] AUTOMATIC TARGETING PROCESS

The automatic targeting process has the SMO assign-ing CALCMs to CALCM launch points and download-ing the appropriate weapon mission into the primaryCALCM assigned and its backups. Since other target-ing processes cannot be commanded for a CALCM un-til it has been initially targeted with an actual or de-fault weapon mission, each CALCM must successful-ly complete the automatic targeting process first. Au-tomatic targeting occurs when all of the following con-ditions are satisfied:

a. A B-52 mission containing CALCM launchpoints is loaded.

b. The corresponding weapon event table forCALCMs is loaded.

c. The DTC from which the above data was loadedis available to the SMO.

d. The weapon groups defined in the weapon eventtable are on the available DTC.

e. The CALCMs to be targeted have power ap-plied. For a CALCM with power applied to betargeted there must be at least one launch pointin the loaded B-52 mission that has the samewarhead type associated with it.

f. Automatic targeting is enabled. If not enabled,the Nav/RNav can enable automatic targetingusing CF-550. To ensure that the preferredlaunch sequence is properly followed, CF-550should not be entered until all CALCMs withpower applied show R in the Targeting Statuswindow on the Weapon Status and Inventorydisplay.

NOTE

The above is the preferred sequence ofevents for the automatic targeting processso CALCMs are assured to be targeted inpreferred launch sequence, especially forthe initial targeting process. However, theevents can occur in any order and automat-ic targeting will begin once the last eventoccurs, regardless of which event that is.

Automatic targeting looks for CALCM launchpoints in the loaded B-52 mission, starting with thecurrent destination and proceeding through the endof the mission. CALCMs, with the same warheadtype as the launch point being processed, are as-signed to the found launch points in the order of thepreferred launch sequence. The weapon mission as-sociated with the found launch point is loaded intothe primary CALCM and up to two backupCALCMs, which have the same warhead type asthe primary CALCM. This allows the backups to be

immediately ready for launch in the event the pri-mary weapon fails and automatic re-targeting is en-abled. If there are more CALCMs available thanlaunch points, the remaining CALCMs will be ini-tialized using the first available weapon mission forthat warhead type identified by the weapon eventtable. If there is no weapon mission identified bythe loaded B-52 mission for a CALCM with a partic-ular warhead type, it cannot be targeted or initial-ized by automatic targeting. If there are morelaunch points than available CALCMs with match-ing warhead types, the excess launch points will re-main untargeted by the automatic targeting pro-cess. All other targeting processes are inhibitedwhile this process occurs.

Once automatic targeting completes for the current-ly powered on CALCMs other targeting processescan be initiated. Meanwhile, automatic targetingwill continually look forward from the current des-tination for any CALCM launch points that do nothave a CALCM assigned to them. Whether such alaunch point is found or not, automatic targetingwill still look for any CALCMs that have not beenassigned as the primary for a launch point. If botha launch point and an unassigned CALCM with amatching warhead type are found, the CALCM willbe targeted to the launch point. If an unassignedand un-initialized CALCM is found but there is nomatching launch point, the CALCM will be initial-ized if there is an available default weapon mission.If no unassigned CALCMs with the appropriatewarhead type are found for a found launch pointand no un-initialized CALCMs that have an avail-able default weapon mission available are found,the cycle of looking for launch points and compat-ible CALCMs begins again. This ensures that anyCALCMs that are powered on after the initial auto-matic targeting process completes and are compat-ible with the currently loaded B-52 mission will ei-ther be targeted or initialized.

The automatic targeting process can be suspendedby the SMO being made secondary or by using theCF-550 command un-enable it.

Unless inhibited by another targeting process, auto-matic targeting can be restarted at any time, evenif a previously initiated automatic targeting processhas not completed, by using the CF-559 commandor by loading a B-52 mission. This will cause allcurrently targeted CALCMs to be untargeted andthus available for possible assignment to anyCALCM launch points found from the current des-tination onward.

T.O. 1B-52H-34-2-9

Change 10 7-11

Figure 7-1. Auto Targeting Scheme

[AMI] MANUAL TARGETING PROCESS

The manual targeting process assigns a selectedCALCM to a selected CALCM launch point andloads the weapon mission designated by the se-lected launch point from a selected weapon groupinto the selected CALCM. The weapon group is se-lected using the CF-82,n(n) command. If the se-lected CALCM launch point already has a CALCMassigned to it, the weapon group that provided theweapon mission the currently assigned CALCMwas targeted with can be viewed on the CALCMGroup Assignment display (CF-DF from FRMT-7).The CALCM is selected using the WCP in conjunc-tion with the CF-556,n(n) command, which uses thevalue of n(n) to select the CALCM launch point. Ifthe command is accepted, the SMO will first untar-get any assigned CALCM and its backups from theselected CALCM launch point. This primaryCALCM, if it exists, will now be considered to haveonly default initialization data loaded and willtherefore be evaluated by automatic targeting (af-

ter manual targeting completes) for assignment toany compatible CALCM launch point that does nothave a primary CALCM assigned. The SMO willnext untarget the selected CALCM and its backupsif it was assigned to a CALCM launch point or di-rect targeted. The SMO then retrieves the appropri-ate preplanned weapon mission from the selectedweapon group on the available DTC and loads itinto the selected CALCM and up to two availablebackups.

All targeting processes, including another manualtarget, are inhibited while this process occurs. Oncethe manual targeting process completes, the inhibitis released for initiating all targeting processes.

NOTE

The preferred launch sequence may be cir-cumvented through the use of manual tar-geting.

T.O. 1B-52H-34-2-9

7-12 Change 10

Flex Targeted Mission

The CALCM assigned to a CALCM launch pointmay have the terminal portion of its preplannedmission modified using the flex targeting process.The backup weapons targeted to the same launchpoint, if any, will have their missions modified also.This is initiated by the operator entering CF-557,nnwhere nn is the launch point of the weapon missionbeing modified. The Flex targeting screen will bedisplayed on the selected MFD with the launchpoint number and the location and station of theCALCM targeted to that launch point number dis-played. The targeting data will be sent to theCALCM associated with the selected launch point,and any backups, when all fields have been modi-fied and the operator enters the CF-DD command.After the CALCM accepts the targeting data, F willbe displayed for that weapon on the CALCM Statusand Inventory display (FRMT-7).

NOTE

• Because flex targeting changes the terminalportion of the CALCM mission, prior tolaunch, the PTA Reference Time for theCALCM launch point(s) being flexed shouldbe updated (as directed) on FRMT-10 to ac-count for the missile route change. Do notchange the mission commander directedPTA on line 3 of CF-61, as this may causeconfusion, while accomplishing launch pro-cedures for combinations of originally tar-geted and flex targeted missiles.

• Entering a PTA Ref Time (CF-61) will changeall aircraft mission PTAs on FRMT-10, there-fore, do not re-enter a PTA Ref Time on CF-61after modifying CMLP PTAs on FRMT-10.

Direct Targeted Mission

A CALCM can be targeted to fly directly to an oper-ator entered target location (Direct Approach Azi-muth (DAA) mode) or to fly to a operator enteredtarget location at a operator entered Target Ap-proach Azimuth as shown in Figure 7-2. The Pre-target Steering Waypoint (SWP) will be calculatedso that the CALCM can accomplish the maneuver.After a weapon mission or GPS initialization data

is loaded in a CALCM, indicated with bright under-lined text or a G in the mission data window forthat weapon on FRMT-7, the CALCM may be directtargeted. This is initiated by the operator selectingone weapon location/station on the WCP and enter-ing CF-558,nn where nn is the direct target numberin the desired direct target designation Dnn. TheDirect targeting screen, will be displayed on the se-lected MFD with direct target designation and loca-tion/station of the CALCM selected. The targetingdata will be sent to the selected CALCM, and itsbackups, when all fields have been modified andthe operator enters the CF-DD command. After theCALCM accepts the targeting data a direct targetdesignation D1 through D20 will be displayedFRMT-7 and the PRGM display.

WEAPON TARGETING COMMANDS

Less [AMI] Before any CALCMs can be launched,the operator must initiate the transfer of targetinginformation to the missile from the weapon DTUC.

[AMI] Prior to launching a CALCM, weapon mis-sion data must be provided to the CALCM from avalid CALCM weapon group on a DTC or from op-erator entered data to target or initialize it. Weaponmission data can only be loaded to a CALCM whilethe SMO is primary. Once a CALCM is targeted orinitialized, it will retain that weapon mission datauntil it is powered off or targeted again.

After initial targeting of the CALCMs, the operatorcan 1) re-initiate targeting of all weapons, 2) manu-ally target a CALCM to a specified launch point, 3)modify a mission by using the Flex targeting op-tion, or 4) Direct target a CALCM. The commandsto carry out these processes are described in the fol-lowing paragraphs. For all targeting commands thetargeting information will also be provided for up totwo backup weapons, if available. After a mission istargeted to a primary weapon and available back-ups, there can be no new backup weapons added forthat mission without reinitiating targeting ormanually targeting the mission (options 1 and 2above).

T.O. 1B-52H-34-2-9

Change 10 7-13

AGM-86C and AGM-86D MISSILES

Figure 7-2. Direct Target Trajectory

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7-14 Change 10

Manual Target Command

Entry of CF-556,nn with a single weapon locationand station selected on the WCP will cause the mis-sion associated with the cruise missile launch pointnn to be loaded in the selected weapon and up totwo available backup weapons. The SMO will rejecta CF-556,nn command to send targeting data anddisplay the command in reverse video if any of thefollowing conditions exist:


• [AMI] The selected weapon group is not avail-able.

• nn is not a valid cruise missile launch pointnumber.

• A single weapon location and station has notbeen selected.

• There is no CALCM at the selected location/station.

• The warhead type for the cruise missilelaunch point number does not match the warheadtype of the single weapon selected.

• Any CALCM is in launch count down.• Another targeting mode is in progress.• Less [AMI] The loaded sortie mission does not

identify a MIU in the stores table that is associatedwith the single weapon selected.

• The CALCM selected is OFF or going OFF.• The single weapon selected has not received

GPS initialization data.• Mission data transfer is in progress.

NOTE

If the launch point being manually targetedis the current destination and has aCALCM already assigned to it, auto se-quencing to the next destination will be in-hibited while in-range.

Target/Retarget All Command

Less [AMI] Initial Entry of CF-559 will result inthe targeting of all CALCMs which have power ap-plied and their available backups in order of thepreferred launch sequence until either all availableweapons have unique primary missions or allunique missions have been exhausted from theCALCM DTUC. If after targeting has been com-pleted and for any reason a CALCM becomes avail-able that does not have a primary target and aCALCM launch point does not have a CALCM as-signed to it, the CALCM and any available backupswill be targeted automatically without need for re-issuing the CF-559 command. The CF-559 com-

mand must be issued and targeting completed priorto commanding any other weapon targeting option-s. If after all cruise missile missions have been ex-hausted, and there remain CALCMs which havenot been targeted, GPS initialization data will besent so that other targeting functions can be per-formed on those weapons. Entering CF-559 aftertargeting has been initiated will clear the existingmission to weapon assignments and retarget allavailable weapons.

[AMI] The Retarget All command, CF-559, will re-sult in the untargeting of all currently targetedCALCMs in preparation for the automatic targetingprocess to retarget them.

The SMO will reject a CF-559 command to sendtargeting data and display the command in reversevideo if any of the following conditions exist:

• A B-52 mission has not been loaded.• Another targeting mode is in progress (exclud-

ing automatic retargeting).• [AMI] Automatic targeting is not available.• Less [AMI] Another SMO confirmation mes-

sage is active.

Prior to initiating targeting or retargeting of allCALCMs, the SMO will seek confirmation by dis-playing the question TGT/RETGT ALL? YES/NO. AYES response will result in targeting being initi-ated, while a NO response will terminate the re-quest. After Less [AMI] 60 seconds [AMI] 120 sec-onds, the default response of NO will be assumed.

One of the following conditions must be met prior toissuing the CF-559 command or targeting will notoccur and the command will have to be re-issuedonce one of the conditions is met:

• Less [AMI] The IU is on.1. Almanac data is resident in the IU.2. Crypto key data is resident in the IU ifCrypto Key Override is Off.

• Less [AMI] The IU is off and a B-52 sortieDTUC with GPS data is available.

1. Almanac data is resident in the DTUC.2. Crypto key data is resident in the IU ifCrypto Key Override is Off (the current date,CF-61 line 4, must be within the Crypto Keystart and end date in the DTUC).

• [AMI] Almanac data is available from theFMS.

• [AMI] Crypto key data is available from theFMS, if Crypto Key Override is OFF.

T.O. 1B-52H-34-2-9

Change 10 7-15

Send Targeting Data Command

When flex or direct targeting screens are displayedand all required data has been entered, Entry ofCF-DD will command the SMO to send the inputtargeting data and any fuze data to the selectedweapon and any backups associated with thatweapon. The SMO will reject a CF-DD command tosend targeting data and display the command in re-verse video if any of the following conditions exist:

• The Flex or Direct Targeting display or associ-ated Fuze Data Input display is not on the selectedMFD.

• All required data has not been successfully en-tered.

• Flex or Direct targeting is not active.• The CALCM assigned as primary to the

CALCM launch point being flex or direct targetedis in LCD.

If the launch point being flex targeted is the cur-rent destination, sequencing to the next destinationwill be inhibited while in-range during the datatransfer to the selected CALCM.

Exit Targeting Mode Command

When flex or direct targeting screen(s) are dis-played, Entry of CF-DE will command the SMO toterminate flex or direct targeting. The SMO will re-ject a CF-DE command to terminate flex or directtargeting and display the command in reverse videoif the following conditions exist:

• The Flex or Direct Targeting display or associ-ated Fuze Data Input display is not on the selectedMFD.

• Flex or Direct targeting is not active.

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7-16 Change 10

MISSION DATA ITEMS

The items which must be defined for a flex or directtargeted mission are discussed in the followingparagraphs. Unless otherwise indicated the itemsapply to both flex and direct targeting.

Target Location

The target location is the geographical position andelevation which the missile is to attack.

The position entry fields on CF-557 and CF-558 are:

• Less [AMI] Latitude in degrees, minutes, sec-onds, and thousandths of seconds in the TGT POSwindow.

• Less [AMI] Longitude in degrees, minutes,seconds, and thousandths of seconds in the TGTPOS window.

• [AMI] Latitude in degrees, minutes, and thou-sandths of minutes in the TGT POS window.

• [AMI] Longitude in degrees, minutes, andthousandths of minutes in the TGT POS window.

• Elevation in feet in in the TGT POS window.

Flex SWP Number (Flex Only)

The flex steering waypoint (SWP) is the pre-planned waypoint in a CALCM mission which willbe used as the pre-target waypoint. This is the lastpre-planned waypoint number in the mission datathe CALCM will fly to before flying to the TMIPand the flexed target location.

Target Approach Azimuth (Direct Only)

The target approach azimuth window on CF-558 isthe true course from the SWP to the target in degrees.

Burst Altitude

Burst Altitude window is the height in feet abovethe target at which the warhead will detonate.

Mach Index

The Mach index is a numerical input which is usedto set the CALCM’s airspeed from launch to SWP,(Direct Only) and from SWP to target.

Rollover Flag

The rollover flag is a numerical input which setsthe terminal maneuver to Modified Push Over(MPO) or rollover. A entry of zero (0) commandsMPO (rollover off) and an entry of one (1) com-mands rollover. If the validity check fails, the modi-fiable field will be reverse video.

Distance from SWP to Target (Direct Only)

The distance from the SWP to the target is enteredin nautical miles.

Flight Altitude Trajectory Mode

The flight altitude trajectory mode defines theflight altitude mode for the CALCM mission. Thereare two segments of the flight which have the flightaltitude trajectory mode defined, from launch toSWP for direct targeted missions and from SWP totarget for both direct and flex targeted missions.There are two flight altitude trajectory modes se-lectable:

• Barometric Hold Altitude (display field set to0). The CALCM will fly at a constant barometricaltitude.

• Terrain Following Altitude (display field set to1). The CALCM will follow the terrain attemptingto maintain a constant height above the ground.

Launch Point to Pre-target Steering Waypoint Altitude(Direct Only)

The launch point to pre-target steering waypoint al-titude is the altitude in feet for the CALCM to flyfrom the launch point to the pre-target steeringwaypoint. When the launch to SWP flight altitudetrajectory mode is barometric hold the launch pointto pre-target steering waypoint altitude is a MSLaltitude. When the launch to SWP flight altitudetrajectory mode is terrain following the launchpoint to pre-target steering waypoint altitude is anAGL altitude. This must be entered after thelaunch to SWP flight altitude trajectory mode is se-lected.

The trajectory altitude windows on the direct tar-geting screen will display BH and MSL, respective-ly, when the launch to SWP flight altitude trajecto-ry mode is barometric hold and TF and AGL, re-spectively, when the flight altitude trajectory modefrom launch to SWP is terrain following.

Launch to SWP Barometric Hold Backup Altitude (Direct Only)

The launch to SWP barometric hold backup altitudeis used when terrain following flight altitude trajec-tory mode from launch to SWP is selected and theCALCM radar altimeter fails. The input is alwaysMSL altitude, in feet, but can only be entered if ter-rain following flight altitude trajectory mode fromlaunch to SWP is selected.

T.O. 1B-52H-34-2-9

Change 10 7-17

SWP to Target Altitude

The SWP to target altitude the flight mode windowis the altitude in feet for the CALCM to fly from theSWP to the target. When the flight altitude trajec-tory mode from SWP to target is barometric holdthe SWP to target altitude is a MSL altitude. Whenthe flight altitude trajectory mode from SWP to tar-get is terrain following the SWP to target altitude isan AGL altitude. This must be entered after theflight altitude trajectory mode from SWP to targetis selected.

The flight mode windows on the flex and direct tar-geting screen will display BH and MSL, respective-ly, when the selected SWP to target flight altitudetrajectory mode is barometric hold and TF andAGL, respectively, when the selected SWP to targetflight altitude trajectory mode is terrain following.

Impact Angle

The target impact angle displayed is the angle be-tween the CALCM trajectory and the horizontalplane at the target area. Less [AMI] The impactangle is given in degrees with the values rangingfrom 0 to 80 degrees. If the validity check fails, themodifiable field will be reverse video.

NOTE

• Less [AMI] Even though the OAS will ac-cept entries between 00 and 80 degrees, theAGM-86C missiles have their own valid pa-rameters. If a value outside of these limitsis entered, when CF-DD is commanded, themissile will be faulted, a xy:MSN DATAmessage will be displayed and the missilewill be powered off. Power reapplication willbe inhibited for eight minutes. TheAGM-86C 0A/1A missile valid input is asfollows:

If rollover mode is not selected the inputrange which will be accepted by the missileis 00 to 50. If rollover mode is selected theonly input which will be accepted by themissile is 70. If a value other than 00 to 50for pushover or other than 70 for a rolloveris used, the missile will NoGo.

• Less [AMI] AGM-86D - If rollover mode isnot selected the input range which will beaccepted by the missile is 00 to 50. If rollov-er mode is selected the input range whichwill be accepted by the missile is 50 to 70.If a value between 70 to 80 is entered themissile will use 70. If a value more than 50

for pushover or less than 50 for rollover isentered the missile will accept the valueand may unsuccessfully attempt to achievethe commanded angle.

• [AMI] The impact angle valid inputs de-pend on the rollover value and the warheadtype of the CALCM assigned to the launchpoint. When the rollover value is 0 and thewarhead type of the CALCM is 1, the validinputs are 00 to 50 degrees. When the rol-lover value is 1 and the warhead type of theCALCM is 1, the only valid input is 70 de-grees. When the rollover value is 0 or 1 andthe warhead type of the CALCM is 2, thevalid inputs are 00 to 80 degrees. This isthe angle between the CALCM terminaltrajectory and the horizontal plane at thetarget area. The value is 00 when the SMOis first loaded.

SWP to Target Barometric Hold Backup Altitude

The SWP to target barometric hold backup altitude,is used when terrain following flight altitude trajec-tory mode from SWP to target is selected and theCALCM radar altimeter fails. The input is alwaysMSL altitude, in feet, but can only be entered if ter-rain following SWP to target flight altitude trajecto-ry mode is selected.

MISSION DATA ENTRY

These paragraphs describe the methods and proce-dures that the operator can use when enteringCALCM mission data for flex and direct targets.When out of range values are entered, the invaliddata field will be displayed in reverse video whenthe ENTER key is pressed. Modification of missiondata is not allowed for a CALCM that has enteredlaunch countdown.

Flex Target Mission Data Entry

Operator entry of CF-557,nn, where nn is the cruisemissile launch point number, will cause the Flex tar-geting screen to be displayed. This screen is used toflex off of any CALCM mission steering waypoint toa operator entered target location. The launch pointnumber and the missile location and station are dis-played. The selected station status advisory displayfor the primary weapon associated with the launchpoint will be displayed. The operator must modifyeach applicable data entry location before the datacan be sent to the selected weapon and its backups. Adescription of data entry for each element follows.

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7-18 Change 10

A. Flex target position entry is initiated by enter-ing a MDFY-1 command. The target position linewill be displayed at the command line initially asfollows:

Less [AMI] 1 TGT POS N00o00’00.000 E000o00’00.00000000(FT)

[AMI] 1 TGT POS N00o00.000 E000o00.000 00000(FT)

The operator will then enter WGS-84 values for tar-get latitude, longitude and elevation and press EN-TER. Latitude valid inputs include direction North(N) or South (S) followed by Less [AMI] degrees from0 to 90, minutes from 00 to 59, and seconds from00.000 to 59.999, [AMI] degrees from 0 to 90 and min-utes 00.000 to 59.999. The total value of latitude, com-puted as degrees + minutes + seconds, cannot exceed90. Longitude valid inputs include direction East (E)or West (W) followed by Less [AMI] degrees from 0 to180, minutes from 00 to 59, and seconds from 00.000to 59.999, Less [AMI] degrees from 0 to 180 and min-utes from 00.000 to 59.999. The total value of longi-tude, computed as degrees + minutes + seconds, can-not exceed 180. Elevation valid inputs include from–1300 to 29030 feet. When out of range values are in-put for more than one field at one time, only the firstfield out of range will be displayed in reverse videowhen the ENTER key is pressed. When an in rangevalue is input for that field, the next out of range fieldwill be displayed in reverse video when the ENTERkey is pressed.

B. The flex steering waypoint number entry is initi-ated by entering a MDFY-2 command. The flexsteering waypoint number line will be displayed atthe command line as follows:

2 FLEX SWP NUMBER 00 (2 – xx)

The operator will then enter the value for flexsteering waypoint number and press ENTER. Flexsteering waypoint number valid inputs includefrom 2 to xx, where xx is the planned pre-targetwaypoint number of the mission being flexed. If therange check fails, the modifiable field will be re-verse highlighted.

C. The burst altitude entry is initiated by enteringa MDFY-3 command. The burst altitude line will bedisplayed at the command line as follows:

3 BURST ALT 0000 (0 – 5000 FT AGL)

The operator will then enter the value for burst al-titude and press ENTER. Burst altitude valid in-puts include from 0 to 5000 feet. If the range checkfails, the modifiable field will be reverse highligh-ted. This value will be ignored if targeting a

CALCM with a warhead type 2, which uses the fuzedata entries to determine when to detonate.

D. The SWP to target Mach index entry is initiatedby entering a MDFY-4 command. The SWP to tar-get Mach index line will be displayed at the com-mand line as follows:

4 SWP-TGT MACH INDEX 0 (0 – 4)

The operator will then enter the value for SWP totarget Mach index and press ENTER. SWP to tar-get Mach index valid inputs include from 0 to 4. Ifthe range check fails, the modifiable field will be re-verse highlighted.

E. The flight altitude trajectory mode from SWP totarget entry is initiated by entering a MDFY-5 com-mand. The flight altitude trajectory mode fromSWP to target line will be displayed at the com-mand line as follows:

5 FLIGHT MODE 0 (0=BH; 1=TF)

The operator will then enter the value for flight al-titude trajectory mode from SWP to target andpress ENTER. Flight altitude trajectory mode fromSWP to target valid inputs include 0 (barometrichold) and 1 (terrain following). If the range checkfails, the modifiable field will be reverse high-lighted.

F. The SWP to target altitude entry is initiated byentering a MDFY-6 command. This input must bemade after flight altitude trajectory mode fromSWP to target input. It will be zeroed out each timethe flight altitude trajectory mode from SWP to tar-get is entered. If the flight altitude trajectory modeis terrain following, the SWP to target altitude linewill be displayed at the command line as follows:

6 TF ALT 0000 (0 – 8000 FT AGL)

The operator will then enter the value for SWP totarget altitude and press ENTER. SWP to target al-titude valid AGL inputs include from 0 to 8000 feet.If the range check fails, the modifiable field will bereverse highlighted.

If the flight altitude trajectory mode is barometrichold, the SWP to target altitude line will be dis-played at the command line as follows:

6 BH ALT 00000 (-1000 – 50000 FT AGL)

The operator will then enter the value for SWP totarget altitude and press ENTER. SWP to target al-titude valid MSL inputs include from –1000 to50000 feet. If the range check fails, the modifiablefield will be reverse highlighted.

All data on pages 7-18A through 7-18F (Deleted)

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Change 10 7-19

G. When the flight altitude trajectory mode fromSWP to target is terrain following, the SWP to tar-get barometric hold backup altitude entry is initi-ated by entering a MDFY-7 command. This inputmust be made after flight altitude trajectory modefrom SWP to target input. The command line isonly displayed when the flight altitude trajectorymode is terrain following, and starts out zeroedeach time a 1 is entered for the SWP-TGT flightmode. The SWP to target barometric hold backupaltitude line will be displayed at the command lineas follows:

7 BH BKUP ALT 00000 (-1000 – 50000 FT AGL)

The operator will then enter the value for SWP totarget barometric hold backup altitude and pressENTER. SWP to target barometric hold backup al-titude valid inputs include from –1000 to 50000feet. If the range check fails, the modifiable fieldwill be reverse highlighted. operator entry ofMDFY-7 when the flight altitude trajectory modefrom SWP to target is barometric hold will result inreverse highlight of the command.

H. The rollover entry is initiated by entering aMDFY-8 command. The rollover line will be dis-played at the command line as follows:

8 ROLLOVER 0 (0=OFF; 1=ON)

The operator will then enter the value for rollover andpress ENTER. Valid rollover input is 0 or 1. A entryof zero (0) commands MPO (rollover off) and an entryof one (1) commands rollover on. If the validity checkfails the modifiable field will be reverse highlighted.

I. The impact angle entry is initiated by entering aMDFY-9 command. The impact angle line will bedisplayed at the command line as follows:

9 IMPACT ANGLE 00 (0 – 80 DEG)

The operator will then enter the value for impactangle and press ENTER. Impact angle valid inputsrange from 0 to 80 degrees (See note below). If thevalue check fails the modifiable field will be reversehighlighted.

NOTE

• Less [AMI] Even though the OAS will acceptentries between 00 and 80 degrees, theAGM-86C missile have their own valid pa-rameters. If a value outside of these limitsis entered, when CF-DD is commanded, the

missile will be faulted, a xy:MSN DATAmessage will be displayed and the missilewill be powered off. Power reapplication willbe inhibited for eight minutes. TheAGM-86C missile valid input is as follows:


• Less [AMI] AGM-86D - If rollover mode isnot selected the input range which will beaccepted by the missile is 00 to 50. If rollov-er mode is selected the input range whichwill be accepted by the missile is 50 to 70.If a value between 70 to 80 is entered themissile will use 70. If a value more than 50for pushover or less than 50 for rollover isentered the missile will accept the valueand may unsuccessfully attempt to achievethe commanded angle.

• [AMI] The impact angle valid inputs dependon the rollover value and the warhead typeof the CALCM assigned to the launch point.When the rollover value is 0 and the war-head type of the CALCM is 1, the valid in-puts are 00 to 50 degrees. When the rollovervalue is 1 and the warhead type of theCALCM is 1, the only valid input is 70 de-grees. When the rollover value is 0 or 1 andthe warhead type of the CALCM is 2, thevalid inputs are 00 to 80 degrees. This isthe angle between the CALCM terminaltrajectory and the horizontal plane at thetarget area. The value is 00 when the SMOis first loaded.

J. [AMI] The manual SAIR range entry is initiatedby entering a MDFY-10 command to copy themanual SAIR range data to the MFD modificationline. The cursor will be under the manual SAIRrange field. The operator will then enter the valuefor the manual SAIR range and press ENTER.

[AMI] 10 MANUAL SAIR RANGE 000 (20 – 300 NM)

The manual SAIR range valid points depend on theweapons being flex targeted. The SMO will acceptvalues for this field between 20 and 300 NM.

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7-20 Change 10

The operator can re-enter data on any line by rese-lecting that line using the MDFY-n command as be-fore. Once data entry is complete, the entered datawill be sent to the CALCM associated with thelaunch point and its backups by operator entry ofthe CF-DD. If any required line has not been modi-fied when CF-DD is entered, the command will bereverse highlighted. After the data is sent to theweapons, the data will be retained as the initialvalues for the next Flex targeted weapon. (FLEXSWP number will be set to zero if the retained val-ue is greater than the value of the pre-target way-point number for the next Flex targeted weapon).The operator can recall flex targeting data sent tothe weapon at anytime by entering CF-557,nn forthe launch point.

[AMI] If the launch point being flex targeted is as-signed to a CALCM with a warhead type of 2, theNav/RNav may need to use the CF-DF command toenter fuze data prior to sending the data to theCALCM to flex its mission.

NOTE

[AMI] If the launch point being flex tar-geted is assigned to a CALCM with a war-head type of 2, the Nav/RNav can enter theCF-DD command without going to the fuzedata input screen since the fuze data de-faults are always valid. This could result inthe incorrect fuze data values being sent tothe CALCM if the Nav/RNav does not checkthe values prior to issuing the CF-DD com-mand.

[AMI] The CF-DE command may be used to exitflex targeting data entry without sending the flexdata to the CALCM, and its backups, associatedwith the launch point being flex targeted.

Direct Target Data Entry

Operator selection of one weapon location and sta-tion followed by entry of CF-558,nn will cause theDirect targeting screen to be displayed for the di-rect target designation Dnn. This screen is used todirect target the CALCM to a operator entered tar-get location. The direct target designation and theselected missile location/station are displayed alongwith the selected station status advisory display forthe primary weapon selected. The operator mustmodify each applicable data entry location beforethe data can be sent to the weapon.

[AMI] The only field that can have invalid data dis-played when the screen first appears on a MFD af-ter the SMO is loaded is the SWP to target distance(see below). Since the initial values for the rest ofthe fields are already valid and the default valuesfor direct target operations after the first one arewhat was last entered or retrieved from an existingdirect target, the data displayed on the screen isvalid even without being modified and can be sentto the selected CALCM and its backups as soon asthe screen is displayed, as long as the SWP to tar-get distance is also valid.

A discussion of data entry of each element follows.

A. Direct target position entry is initiated by enter-ing a MDFY-1 command. Direct target positionentry is similar to Flex target position entry andwill not be repeated here.

B. The target approach azimuth entry is initiatedby entering a MDFY-2 command. The target ap-proach azimuth line will be displayed at the com-mand line as follows:

2 TGT APPR AZ 000 (DAA = DIRECT, 0 – 359o)

The operator will then enter the value for target ap-proach azimuth and press ENTER. Target approachazimuth valid inputs include from 0 to 359 degreesor DAA. If the range check fails, the modifiablefield will be reverse highlighted.

C. Burst altitude entry is initiated by entering aMDFY-3 command. Burst altitude entry is similarto flex burst altitude entry and will not be repeatedhere.

D. The launch to SWP Mach index entry is initi-ated by entering a MDFY-4 command. The launchto SWP Mach index entry is similar to flex SWP totarget Mach index entry and will not be repeatedhere.

E. The flight altitude trajectory mode from launchto SWP entry is initiated by entering a MDFY-5command. The flight altitude trajectory mode fromlaunch to SWP entry is similar to flex flight alti-tude trajectory mode from SWP to target entry andwill not be repeated here.

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Change 10 7-21

F. The Launch to SWP altitude entry is initiatedby entering a MDFY-6 command. This input mustbe made after any flight altitude trajectory modefrom launch to SWP input. It will be zeroed outeach time the launch to SWP flight altitude trajec-tory mode is entered. If the launch to SWP flight al-titude trajectory mode is terrain following, theLaunch to SWP altitude line will be displayed atthe command line as follows:

6 TF ALT 0000 (0 – 8000 FT AGL)

The operator will then enter the value for Launchto SWP altitude and press ENTER. Launch to SWPaltitude valid AGL inputs include from 0 to 8000feet. If the range check fails the modifiable fieldwill be reverse highlighted.

If the launch to SWP flight altitude trajectory modeis barometric hold, the Launch to SWP altitude linewill be displayed at the command line as follows:

6 BH ALT 00000 (-1000 – 50000 FT AGL)

G. The launch to SWP barometric hold backup alti-tude entry is initiated by entering a MDFY-7 com-mand. This input must be made after flight altitudetrajectory mode from launch to SWP input. Thecommand line is only displayed when the launch toSWP flight altitude trajectory mode is terrain fol-lowing, and starts out zeroed each time a 1 is en-tered for the LNCH-SWP flight mode. The launchto SWP barometric hold backup altitude line will bedisplayed at the command line as follows:

7 BH BKUP ALT 00000 (-1000 – 50000 FT AGL)

The operator will then enter the value for launch toSWP barometric hold backup altitude and pressENTER. Launch to SWP barometric hold backupaltitude valid inputs include from –1000 to 50000feet. If the range check fails, the modifiable fieldwill be reverse highlighted. operator entry ofMDFY-7 when the flight altitude trajectory modefrom launch to SWP is barometric hold will resultin reverse highlight of the command.

H. The SWP to target Mach index entry is initiatedby entering a MDFY-8 command. The SWP to tar-get Mach index entry is identical to flex SWP to tar-get Mach index entry and will not be repeated here.

I. The SWP to target distance index entry is initi-ated by entering a MDFY-9 command. The SWP totarget distance line will be displayed at the com-mand line as follows:

9 DIST 00 (30 – 99 NM)

The operator will then enter the value for SWP totarget distance and press ENTER. SWP to targetdistance valid inputs include from 30 to 99 nauticalmiles. If the range check fails, the modifiable fieldwill be reverse highlighted.

J. The flight altitude trajectory mode from SWP totarget entry is initiated by entering a MDFY-10command. The flight altitude trajectory mode fromSWP to target entry is similar to flex flight altitudetrajectory mode from SWP to target entry and willnot be repeated here.

K. The SWP to target altitude entry is initiated byentering a MDFY-11 command. The SWP to targetaltitude entry is similar to flex SWP to target alti-tude entry and will not be repeated here.

L. The SWP to target barometric hold backup alti-tude entry is initiated by entering a MDFY-12 com-mand. The SWP to target barometric hold backupaltitude entry is similar to flex SWP to target baro-metric hold backup altitude entry and will not berepeated here.

M. The rollover entry is initiated by entering aMDFY-13 command. The rollover entry is similar toflex rollover entry:

13 ROLLOVER 0 (0=OFF; 1=ON)

The operator will then enter the value for rolloverand press ENTER. Valid rollover input is 0 or 1. Aentry of zero (0) commands MPO (rollover off) andan entry of one (1) commands rollover on. If the va-lidity check fails the modifiable field will be reversehighlighted.

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7-22 Change 10

N. The impact angle entry is initiated by entering aMDFY-14 command. The impact angle line will bedisplayed at the command line as follows:

14 IMPACT ANGLE 00 (0 – 80 DEG)

The operator will then enter the value for impactangle and press ENTER. Impact angle valid inputsrange from 0 to 80 degrees (See note below). If thevalue check fails the modifiable field will be reversehighlighted.

NOTE

• Less [AMI] Even though the OAS will acceptentries between 00 and 80 degrees, theAGM-86C missile have their own valid pa-rameters. If a value outside of these limitsis entered, when CF-DD is commanded, themissile will be faulted, a xy:MSN DATAmessage will be displayed and the missilewill be powered off. Power reapplication willbe inhibited for eight minutes. TheAGM-86C missile valid input is as follows:


• Less [AMI] AGM-86D - If rollover mode isnot selected the input range which will beaccepted by the missile is 00 to 50. If rollov-er mode is selected the input range whichwill be accepted by the missile is 50 to 70.If a value between 70 to 80 is entered themissile will use 70. If a value more than 50for pushover or less than 50 for rollover isentered the missile will accept the valueand may unsuccessfully attempt to achievethe commanded angle.

• [AMI] The impact angle valid inputs dependon the rollover value and the warhead typeof the CALCM assigned to the launch point.When the rollover value is 0 and the war-head type of the CALCM is 1, the valid in-

puts are 00 to 50 degrees. When the rollovervalue is 1 and the warhead type of theCALCM is 1, the only valid input is 70 de-grees. When the rollover value is 0 or 1 andthe warhead type of the CALCM is 2, thevalid inputs are 00 to 80 degrees. This isthe angle between the CALCM terminaltrajectory and the horizontal plane at thetarget area. The value is 00 when the SMOis first loaded.

The operator can re-enter data on any line by rese-lecting that line using the MDFY-n command as be-fore. Once data entry is complete, the entered datawill be sent to the selected CALCM and its backupsby issuing the CF-DD command. If any requiredline has not been modified when CF-DD is entered,the command will be reverse highlighted. After thedata is sent to the weapon, the data will be retainedas the initial values for the next direct targetedweapon. Thereafter, the operator needs to modifyonly those parameters which are different to directtarget another weapon. The operator can recall di-rect targeting data sent to the weapon at anytimeby entering the location and station and CF-558,nnfor the direct target designation.

[AMI] If the launch point being direct targeted isassigned to a CALCM with a warhead type of 2, theNav/RNav may need to use the CF-DF command toenter fuze data prior to sending the data to theCALCM.

NOTE

[AMI] If the launch point being direct tar-geted is assigned to a CALCM with a war-head type of 2, the Nav/RNav can enter theCF-DD command without going to the fuzedata input screen since the fuze data de-faults are always valid. This could result inthe incorrect fuze data values being sent tothe CALCM if the Nav/RNav does not checkthe values prior to issuing the CF-DD com-mand.

[AMI] The CF-DE command may be used to exit di-rect targeting data entry without sending the directtarget data to the CALCM, and its backups, associ-ated with the launch point being direct targeted.

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Change 10 7-23

FUZE DATA ENTRY (AGM-86D MISSILES ONLY)

The operator can re-enter data on any line by rese-lecting that line using the MDFY-n command as be-fore. When the weapon is an AGM-86D, the opera-tor may enter a CF-DF command to display thefuze data. Once data entry is complete, the entereddata will be sent to the selected AGM-86D and itsbackups by issuing the CF-DD command. If any re-quired line has not been modified when CF-DD orCF-DF is entered, the command will be reversehighlighted. After the data is sent to the missile,the data will be retained as the initial values forthe next direct targeted weapon. Thereafter, the op-erator needs to modify only those parameters whichare different to direct target another AGM-86D.The operator can recall direct targeting data sent tothe missile at anytime by entering the location andstation and CF-558,n(n) for the direct target desig-nation.

To display the Fuze Data Input AGM-86D Display,the operator enters a CF-DF command from eitherCF-557 (Flex Targeting) or CF-558 (Direct Target-ing) screen. An AGM-86D must be the currently se-lected weapon. The selected station status advisorydisplay for the primary weapon selected will be dis-played. The operator may modify any data entrylocation before sending the data to the weapon.

A. Fuze mode entry is initiated by entering aMDFY-1 command.

1 FUZE MODE 1 (1=VOID; 2=SOLID; 3=DOB)

The operator will then enter the value for FuzeMode and press ENTER. Fuze Mode valid inputsinclude 1 for Function on Void, 2 for Function onLayer, or 3 for Depth of Burial. If the validity checkfails, the modifiable field will be reverse high-lighted.

B. Number of Events entry is initiated by enteringa MDFY-2 command.

2 NUM EVENTS 01 (1 – 15)

The operator will then enter the value for Numberof Events and press ENTER. Number of Events val-id inputs include from 1 to 15. If the range checkfails, the modifiable field will be reverse high-lighted.

C. Backup DOB entry is initiated by entering aMDFY-3 command.

3 BACKUP DOB 000 (0 – 262 FEET)

The operator will then enter the value for BackupDOB and press ENTER. Backup DOB valid inputsinclude from 0 to 262 feet. This value is ignored iffuze mode is DOB. If the range check fails, the mod-ifiable field will be reverse highlighted.

D. Fuze Function Distance entry is initiated by en-tering a MDFY-4 command.

4 FUNCTION DISTANCE 000 (0 – 262 FEET)

The operator will then enter the value for FunctionDistance and press ENTER. Function Distance val-id inputs include from 0 to 262 feet. This indicatesthe minimum distance the CALCM should travelafter impact before it should try to detonate. Thevalue is 006 when the SMO is first loaded. If therange check fails, the modifiable field will be re-verse highlighted.

E. Time After Impact entry is initiated by enteringa MDFY-5 command.

5 TIME AFTER IMPACT 250 (0 – 255 MILLISECS)

The operator will then enter the value for Time Af-ter Impact and press ENTER. Time After Impactvalid inputs include from 0 to 255 milliseconds. Ifthe range check fails, the modifiable field will be re-verse highlighted.

F. Impact Velocity entry is initiated by entering aMDFY-6 command.

6 IMPACT VELOCITY 1299 (492 – 1509 FT/SEC)

The operator will then enter the value for ImpactVelocity and press ENTER. Impact Velocity validinputs include from 492 to 1509 Feet per second. Ifthe range check fails, the modifiable field will be re-verse highlighted.

The operator can re-enter data on any line by rese-lecting that line using the MDFY-n command as be-fore. Once data entry is complete, the entered datawill be sent to the selected AGM-86D and its back-ups by issuing the CF-DD command. Entering aCF-DB command will return to the previous Flex orDirect Targeting screen. The CF-DE command isused to exit fuze data entry and the associated flexor direct target direct entry without sending thedata to the CALCM and its backups associated withthe flex or direct target data entry screen.

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7-24 Change 10

SAFE LAUNCH DETERMINATION

Safe launch checks are made to verify that at launchthe CALCM will not re-contact the airplane after sep-aration or the CALCM is not launched in adverseflight conditions which are beyond its capability to re-cover. Safe launch checks include checks for altitude,dynamic pressure, roll, pitch, pitch rate, normal ac-celeration, and vertical velocity. In Direct LaunchMode the pre-target steering waypoint turn angle isalso checked to verify the CALCM can accomplish theturn from the pre-target steering waypoint to the tar-get. When any safe launch check is not met a safelaunch restriction is imposed so that the CALCM isnot launched and the PRGM screen will display whatcorrective action is required.

ALTITUDE AND PRESSURE CHECKS

The following altitude and dynamic pressure checksare made to verify a safe launch can be accom-plished:

A. MSL altitude must exceed preplanned minimumlaunch altitude.

B. Dynamic Pressure must exceed minimum valuesof pressure (400 psf) from the altitude - pressurecurves of the B-52 to CALCM.

C. AGL altitude must exceed safe launch altitudefrom the altitude - pressure curves of the B-52 toCALCM.

Altitude checks (A or C above) or pressure checksfailure (B above) will result in a CALCM safelaunch restriction and in display of CLIMB or AC-CEL, respectively on the PRGM screen.

Level Flight Checks

The following level flight checks are made to verifya safe launch can be accomplished:

A. The predicted roll angle cannot exceed ±10degrees.

B. The predicted pitch angle cannot exceed ±10 de-grees.

C. The pitch rate must be within both of the follow-ing:

1. ±5 degrees per second

2. –1.5 multiplied by the predicted pitch angle±12.5 degrees per second

Level flight checks failure will result in a CALCMsafe launch restriction and in display of ROLL (Aabove) or PITCH (B or C above) on the PRGMscreen.

ACCELERATION AND VERTICAL VELOCITY CHECKS

The following acceleration and vertical velocitychecks are made to verify a safe launch can be ac-complished:

A. The lateral acceleration cannot exceed ±.25 g.

B. The normal acceleration cannot be less than –.5 g and cannot be more than 2 gs.

C. The vertical velocity must be within limits.

Acceleration and vertical velocity checks failure willresult in a CALCM safe launch restriction and indisplay of YAW (A above) or LEVL OFF (B or Cabove) on the PRGM screen.

PRE-TARGET STEERING WAYPOINT TURN ANGLE (DI-RECT LAUNCH MODE ONLY)

The pre-target steering waypoint turn angle will bedisplayed on the CALCM Direct Target Programdisplay to inform the operator of the pre-targetsteering waypoint turn angle the missile will haveto perform if launched from the current aircraftposition. If Direct Launch Mode is active, ∆ BRG inbright underline video and the pre-target steeringwaypoint turn angle in degrees will be displayed onPRGM. The pre-target steering waypoint turnangle will be displayed in normal video if it is lessthan or equal to the maximum allowed turn angle.The waypoint turn angle will be displayed in re-verse video if it is more than the maximum allowedturn angle, and a BRG CHG release restriction willbe displayed on the CALCM Direct Target Programdisplay CF-558. When ∆ BRG indicates the missilemust take an excessive left turn, the turn can be re-duced by flying counterclockwise around the SWP.Similarly, an excessive right turn can be reduced byflying clockwise around the SWP.

NOTE

• When the release restriction BRG CHG isdisplayed, the aircraft is outside the in-range boundary.

• If ∆BRG is in reverse video and a missileleft turn is required at SWP (∆BRG =Lnnn°), fly the aircraft on a mag course toSWP plus 30° . If ∆BRG is in reverse videoand a missile right turn is required at SWP(∆BRG = Rnnn°), fly the aircraft on a magcourse to SWP minus 30°.

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Change 10 7-25

IN-RANGE DETERMINATION

When the B-52 is flying to a cruise missile launchpoint, or when a CALCM has been direct targeted,In-Range calculations are performed to determinewhen the missile can be launched. [AMI] TheCALCM SMO must be primary for this to occur.

[AMI] A CALCM EVENT advisory will be dis-played in normal video when CALCM SMO is sec-ondary and the carrier mission indicates the air-craft is 25 minutes from a mission planned CALCMlaunch point. A CALCM EVENT master fault willbe displayed in reverse video when the CALCMSMO is secondary and the aircraft is 20 minutesaway from a mission planned CALCM launch point.

RANGING MODES

There are three ranging modes:• Automatic launch point ranging.• Manual SAIR.• Direct SAIR.

Automatic launch point ranging and manual SAIRare only performed when flying to a cruise missilelaunch point. Direct SAIR is performed for everyCALCM that has been direct targeted.

Automatic Launch Point Ranging

Automatic launch point ranging is performed any-time the B-52 is flying to a CALCM launch pointand manual SAIR or Direct Launch Mode is not ac-tive. Automatic launch point range is the distancefrom the airplane position to the current launchpoint. Time-to-go to the launch point is calculatedas the range divided by the ground speed. The auto-matic launch point range indications are displayedon the PRGM screen. When the time-to-go to thelaunch point is less than 3 minutes When In-Rangeis detected and the CALCM associated with thelaunch point is in the bay, launcher rotation will beautomatically commanded to position that CALCMin the down position.

Manual SAIR

Manual SAIR is initiated when the operator entersCF-553. Manual SAIR ranging is performed fromthe airplane position to the first waypoint on theCALCM mission. The manual SAIR range indica-tions are displayed on the PRGM screen and indi-cate Manual SAIR mode, along track distance toSAIR entry or exit, and magnetic course to the firstwaypoint on the CALCM mission. When range to

the first waypoint on the CALCM mission is lessthan the maximum manual SAIR launch range,RLIM, In-Range indications are displayed. Less[AMI] RLIM is read in from the B-52 Sortie MissionDTUC. [AMI] The position of the first steeringwaypoint point in the weapon mission assigned tothe current CALCM launch point and the rangelimit are obtained from the weapon event dataloaded by the SMO as its part of a carrier missiondata load.

To ensure the missile in manual SAIR will reachthe first CALCM waypoint, the carrier aircraftmust be in the manual SAIR footprint (figure 7-3),within the charted area provided in the missionpackage, and the carrier aircraft heading must bewithin 30 degrees either side of the programmedlaunch heading.

MANUAL SAIR COMMAND

Entry of CF-553 will result in manual SAIR modebeing initiated for the weapon associated with thecurrent cruise missile launch point. When ManualSAIR is entered the launch mode will automaticallychange to manual. The SMO will reject a CF-553command to initiate manual SAIR and display thecommand in reverse video if any of the followingconditions exist.

• The current destination is not a cruise missilelaunch point.

• No weapon is targeted to the current cruisemissile launch point.

• Direct targeting mode is enabled.• Weapon is in launch countdown sequence.• Another SMO confirmation message is active.

Prior to entering Manual SAIR the SMO will seekconfirmation by displaying the question MANUALSAIR? YES/NO on MFD. A yes response will resultin MAN SAIR being initiated, while a NO responsewill terminate the request. After Less [AMI] 60seconds, [AMI] 120 seconds, the default response ofNO will be assumed.

Manual SAIR will remain active until one of the fol-lowing occurs:

• A weapon release.• The launch mode is changed to automatic.• Entry into direct launch mode.• Three minutes have elapsed since entry into

manual SAIR mode.• The operator issues a Fly-to command.

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7-26 Change 10

Figure 7-3. Manual SAIR Footprint

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Change 10 7-27

Direct SAIR

Direct SAIR is initiated whenever a CALCM hasbeen Direct Targeted. Direct SAIR ranging is per-formed from the airplane position through the pre-target steering waypoint (SWP) to the target. Thedirect target ranging geometry for an operator en-tered target azimuth is shown in figure 7-4. The di-rect target ranging geometry for flying direct ap-proach azimuth is shown in figure 7-5. In range sta-tus is indicated for all Direct Targeted CALCMs onthe CALCM PRGM display or the CALCM DirectTarget program display PRGM-Dnn. When the op-erator enters PRGM-Dnn where nn is a direct tar-get designation the direct SAIR indications are dis-played for the selected Direct Target on the DirectTarget Program screen to indicate Direct LaunchMode, along track distance to SAIR entry or exit,and magnetic course to the pre-target steering way-point. The boundary to which SAIR range is deter-mined depends upon the ground track of the air-plane and location in relation to the SAIR region.Example scenarios are depicted in figure 7-6 withthe corresponding SAIR Range and Delta Bearingindications for the Direct Target Program Display.When the aircraft is inside the SAIR region, In-Range indications are displayed. Once direct SAIRis activated, it will remain active until no CALCMsare Direct Targeted.

[AMI] For every defined direct target, an in or outof range indication will appear on the PRGM dis-play when the SMO is primary. If the SMO is notprimary, a SMO unique message will be displayedon all MFDs whenever a direct target determines itis in-range.

SAFE AND IN-RANGE INDICATION

The SAIR status for missile launches is provided onthe PRGM display. SAIR is displayed in differentvideo modes to indicate whether or not launch re-strictions exist, and whether or not the aircraft iswithin missile flight range of the selected targetwhen no restriction exists. SAIR indications areshown below.

SAIR VIDEO INDICATION CORRECTIVEACTION

Reverse/BlinkingHighlight

1) At least onelaunch restric-tion exists

Perform aircraftmaneuvers as indi-cated on the Pro-gram display

Normal 1) Missile flightrange to thetarget is greaterthan the maxi-mum range ofthe missile

2) No launch re-strictions exist

Fly aircraft towardslaunchpoint

Bright/UnderlineHighlight

1) Missile flightrange to thetarget is withinthe maximumrange of themissile

2) No launch re-strictions exist

N/A

Blank 1) Not flying toCALCM launchpoint and not indirect launchmode

N/A

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7-28 Change 10

AGM-86C AND AGM-86D MISSILES

Figure 7-4. Direct Target Ranging Geometry When The Target Approach Azimuth Is Defined

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Change 10 7-29

AGM-86C AND AGM-86D MISSILES

Figure 7-5. Direct Target Ranging Geometry When Flying Direct Approach Azimuth To The Target

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7-30 Change 10

EXAMPLENO

∆ BEARING SAIRRANGE

MAGNETICCOURSE

EXAMPLENO

∆ BEARING SAIRRANGE

MAGNETICCOURSE

1 L 105 75 70 9 R 180 65 145

2 L 125 999 90 10 R 155 999 170

3 L 115 50 80 11 R 170 130 155

4 L 130 65 95 12 L 120 999 85

5 R 115 175 210 13 R 55 125 270

6 R 20 45 305 14 R 180 85 145

7 R 150 999 175 15 L 177 350 148

8 L 170 50 135

Figure 7-6. Direct Target Ranging Examples

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Change 10 7-31

AUTOMATIC RETARGETING

Less [AMI] Automatic retargeting will be per-formed under the following conditions:

• Automatic retargeting is enabled.• The current destination is a CALCM launch

point or Direct Launch Mode is active.• The aircraft is In-Range based upon the cur-

rent SAIR mode.• The primary or secondary backup weapon is

launchable, as determined below:1. Weapon is targeted to the same CALCMlaunch point or direct target as the weapon thatfailed to launch.2. Weapon is not off or powering off.3. Weapon is verified as a CALCM.4. Weapon has received at least two fine alignupdate data blocks.5. Avionics Test is complete.6. Weapon is not hung.7. GPS receiver is initialized with data.8. Missile must be RDY.• If a weapon fails and results in power down or

the weapon is determined hung after LCD and doesnot reside on the CSRL.

[AMI] Automatic retargeting mission data selectioncan only occur when all of the following conditionsare satisfied for at least one of the assigned backupCALCMs:

• Automatic retargeting is enabled.• The CALCM currently assigned as the prima-

ry for the current weapon event fails due to somefault that will cause that CALCM to power down.

• The aircraft is in–range for the current weap-on event, as determined by the current rangingmode.

• There is at least one CALCM, assigned as abackup for the current weapon event, that is readyto launch.

1. The backup CALCM has received at least twofine align updates.2. Avionics test is complete for the backupCALCM.3. GPS receiver for the backup CALCM is ini-tialized with data.

When automatic retargeting occurs, the missionswill be re-assigned to the appropriate backup weap-ons (the next available weapon with the same war-head type in the preferred launch sequence at thetime targeting occurred). The new mission assign-ments can be viewed for each weapon on the Weap-on Status and Inventory display. The backup weap-on status for a mission can be viewed by selectingthe primary CALCM assigned to the mission on theselected station status display. If the launch modeis manual and automatic retargeting is performeddue to a failed launch, the operator must press thelaunch button to launch the backup.

No mission data transfer is required for automaticretargeting to occur. Since, during initial targeting(automatic, manual, flex, or direct), each mission isloaded into a primary weapon and up to two avail-able backup weapons. This allows the automatic re-targeting process to be nearly instantaneous. Anexample of the automatic retargeting process isshown in figure 7-7. The example is for a multiple(two) warhead type scenario.

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7-32 Change 10

Figure 7-7. CALCM Auto-Retarget due to L3 Fail

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Change 10 7-33

MISSILE LAUNCH

The missile launch process, including the means forcontrolling, suspending and stopping a missilelaunch, as well as launch command restrictions aredescribed in the following paragraphs.

Changing the launch mode, while the missileis in launch countdown, will place the weaponin a hold and may result in a weapon abort. At2 seconds before release the CALCM batteryis squibbed and any abort past this point is fa-tal to the missile (cannot be used again on thesame flight). During any launch countdown,if either the launch mode or manual launchswitch is pressed, a hold occurs:

• Before the battery squib command, a 45second hold is entered. If the manuallaunch switch is pressed before the 45seconds expires, the launch countdownwill continue. If the manual launchswitch is not pressed before the 45 sec-onds expires, the launch countdownaborts and the weapon is powered offwith a transient fatal fault (weapon canbe used on the same flight).

• After the battery squib command, a 10second hold is entered. If the manuallaunch switch is pressed before the 10seconds expires, the launch countdowncontinues. If the manual launch switchis not pressed before the 10 seconds ex-pires, the launch countdown aborts andthe weapon is powered off with a per-manent fatal fault (weapon cannot beused on the same flight).

LAUNCH DETERMINATION

A launch determination involves checking condi-tions to ensure the LCD process can begin when theSMO is directed to initiate LCD. There are two dif-ferent methods of directing the SMO to initiateLCD, automatic and manual.

AUTOMATIC MISSILE LAUNCH DETERMINATION

When the launch mode is automatic, LCD will beinitiated by the SMO when the aircraft reaches theclosest point of approach to the CALCM launchpoint provided the launch determination conditionslisted below are satisfied.

• Safe launch conditions exist.• The CALCM is in range for the current weap-

on event.• The CALCM passes the following launchable

checks:1. CALCM is targeted.2. CALCM is not off or powering off.3. Weapon is verified as a CALCM.4. CALCM has received at least two fine alignupdates.5. Avionics Test is complete.6. CALCM is not hung.7. GPS receiver is initialized with data.8. CALCM has no transient fatal or higherpriority faults.9. CALCM is not jettisoned or away.10. Gyro spindown command has not been is-sued.11. Instrumentation power for the weapon isset as indicated for the following launch types.

a) Non-OTL launch – Instrumentationpower is off.b) OTL launch – Instrumentation power ison missile.c) PLUS CT launch – Instrumentationpower is on carrier.

• Unlock consent has been given.• RTL consent has been given.• If CALCM to be launched is in the bay:

1. Doors are not in an unlatched condition.2. Less [AMI] Launcher is within one posi-tion of down.3. Less [AMI] Launcher is in position iflauncher faults exist.4. [AMI] Launcher is in position and notmoving.

If any of the conditions are not, LCD entry is inhib-ited and a [AMI] CALCM LCD ENTRY advisory,Less [AMI] LCD ENTRY INHB advisory, is dis-played on all MFDs.

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7-34 Change 10

If the conditions are not satisfied when the aircraftreaches the closest point of approach to the launchpoint, a [AMI] CALCM LCD ENTRY advisory, Less[AMI] LCD ENTRY INHB advisory, is displayed onall MFDs informing the crew that LCD is inhibited.Also, the SMO will inhibit automatic destination se-quencing and the aircraft will stay on the samecourse it approached the CALCM launch point at.The aircraft will remain on this course for up tothree minutes, while the SMO waits for the condi-tions to be satisfied. If the conditions are satisfiedprior to the end of three minutes, LCD will be initi-ated. If not, the SMO will release the inhibit to au-tomatic destination sequencing and the CALCMwill not be launched, although it will still be tar-geted to the CALCM launch point. In this lattercase, the SMO could try to launch the CALCMagain if the CALCM launch point is made the cur-rent destination again by the operator.

MANUAL MISSILE LAUNCH DETERMINATION

When the launch mode is manual, LCD will be ini-tiated by depressing the manual launch switch onthe WCP provided the launch determination condi-tions are satisfied. If in automatic ranging mode,the aircraft must also be flying to the CALCMlaunch point associated with the CWE to initiateLCD when the manual launch switch is depressed.If the conditions are not satisfied when the manuallaunch switch is depressed, a [AMI] CALCM LCDENTRY advisory, Less [AMI] LCD ENTRY INHBadvisory, will be displayed on all MFDs informingthe crew that LCD is inhibited. The launch mode isalways manual when either manual ranging modeor direct launch mode is active.

When in automatic ranging mode and manuallaunch mode, the manual launch switch can be de-pressed up to three minutes past the launch point.The SMO will inhibit automatic destination se-quencing and the aircraft will remain on the courseit approached the launch point at until the CALCMis launched, the in-range boundary is exited, ormanual destination sequencing is commanded.

If the manual launch switch is pressed again whileLCD is in progress for a manual launch, a LCDhold will occur. The LCD will resume if the manuallaunch switch is pressed once again.

MISSILE LAUNCH PROCESS

• The launch countdown initialization block willbe sent to the CALCM to provide the following in-formation:

1. Launch mode (i.e., Operational, Plus Count,or Aborted).

2. The set of mission data to use (i.e., 1, 2, or 3)corresponding to what is currently the primarymission for the weapon.3. If the CALCM is on a launcher or pylon.• If the CALCM is in the bay the bay doors will

be opened. The bay door status on the PRGM dis-play will indicate UNLTCH when the doors areopening and will indicate OPEN when the doors arefully opened. DOORS will be displayed in reversevideo if the doors fail to open when commanded anda door failure is indicated.

• Perform Flight Control Element (FCE) and AirData Element (ADE) tests.

• Safe launch tests are performed to verify thesafe launch conditions have not been violated. Ifany safe launch condition fails the message for thatcondition will be displayed on the PRGM display. Ifthe launch is a bay launch, the bay door status isalso checked, with its condition displayed as pre-viously described.

• Electro-Explosive Device power is turned ON,battery activation is enabled, and the missile bat-tery squib is fired if it is safe to launch. If the mis-sile to be launched is in the bay, the bay doors mustindicate OPEN or these actions will not be com-manded.

• Terminate the alignment process and issueprelaunch navigation data.

1. Navigation initialization data.(a) Carrier position in terms of direction cosines.

2. Free flight alignment data.(a) Carrier Kalman filter state vector elements.(b) Carrier Kalman filter covariance elements.

3. Free flight initialization data.(a) Carrier wind velocities.(b) Carrier ground velocities.(c) Carrier vertical velocity.(d) Carrier altitude.(e) Air density.(f) Speed of sound.(g) Time of launch error.

• Remove carrier electronic power from theweapon.

• Verify weapon battery power.• Perform safe separation test for the CALCM.• Remove heater power from the relay assembly.• Unlock the ejectors, arm the ejector solenoids,

and squib the missile ejectors.• Activate heater power to the relay assembly.

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Change 11 7-35

• Command bomb scoring tone cut off and re-cord weapon scoring information on the flightDTUC/DTC when release processing is complete forthe missile.

• Close the bay doors if bay weapon is not hung.The bay door status on the PRGM display will indi-cate UNLTCH when the doors begin to close andwill indicate CLSD when the doors are fully closed.DOORS will be displayed in reverse highlight if thedoors fail to close when commanded and FMS indi-cates a door failure. Check for and display CALCMrelease advisory in the release advisory display.

NOTE

In automatic launch mode, if a bay launchwas aborted due to a bay door fault and theweapon is not powered down, successfullyclosing (clearing the fault) the bay doorscould cause launch countdown to restart ifstill in SAIR.

• When CALCM release processing is completethe following changes will appear on the WeaponStatus and Inventory Display FRMT-7:

1. The missile status for the launched CALCMwill indicate AW, if the missile is away, (PL,[AMI] CL, if in captive carry mode), or HG ifhung.2. The presence window will change to X indi-cating no weapon is present.3. Ready To Launch and Missile Fault Windowswill go blank.

The information displayed on the Selected StationStatus display (FRMT-7xy), will be identical to thesame windows displayed at the location and stationfor that weapon on FRMT-7.

• When CALCM release processing for a launch iscomplete the Weapon Release advisory, is displayedon each MFD that does not have the Selected StationStatus display. The Weapon Release advisory will re-main displayed for five seconds, and then be removedfrom each MFD. Any advisory previously displayedwill not be re-displayed. Removal of the Weapon Re-lease advisory will not remove any other advisory.

1. The SMO displays the location and station xyof the Weapon Release advisory for the launchedmissile.2. The SMO determines if the missile has beensuccessfully launched or is hung and displaysAWAY or HUNG next to the missile location andstation.• If the operator issues a Fly-to command while

in LCD, the CALCM will still attempt launch pro-vided no launch restrictions or SAIR exit cause anabort to the launch process.

If a CALCM that failed to launch (HUNG) was inthe bay the following will occur:

• Launch mode will be commanded to manual,but the operator can command it to automatic.

• Automatic launcher rotation for launch will beinhibited.

• Bay doors will remain open, but can be closedusing the bay door command.

LAUNCH COUNTDOWN HOLD

The missile launch sequence will be suspended be-fore the selected missile has been launched if any ofthe following conditions occur:

• Safe launch checks fail (excluding pre-targetsteering waypoint).

• Weapon Ready/Safe status (controlled by thePrearm/Safe switch) indicates Safe.

• Ejector unlock enables are not present.• For bay launch only, the bay doors are not

open or the weapon to be launched is not in thedown position on the CSRL when it is time forweapon release.

• The launch mode is changed to manual fromautomatic.

• Manual launch has been deselected via themanual launch switch.

During launch countdown, hold display indicationsinclude the following:

• PRGM screen will display a failed launchedcondition in reverse highlight if safe launch checksfail.

• If safe launch checks fail, PRGM screen willdisplay SAIR in blinking reverse video

• PRGM screen will display HOLD xx, where xxis the allowable time remaining in launch count-down hold, in seconds.

• If ejector unlock enables are not present NOUE master fault will be displayed for the CALCMin LCD.

The launch countdown will be re-entered when thehold conditions listed above are not present and thelaunch mode is changed from manual to automatic(not available if direct launch mode is active) ormanual launch is initiated.

The launch countdown will be terminated when ei-ther of the following conditions exist.

• The 45 second hold timer has elapsed.• Expiration of the variable hold timer after bat-

tery activate. The variable hold time represents theapproximate time the CALCM battery is usable.The usable range is approximately 5.6 to 13 sec-onds, based on the aircraft altitude.

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7-36 Change 11

LAUNCH COUNTDOWN TERMINATION

The missile launch sequence will be terminated be-fore the selected missile has been launched if any ofthe following conditions occur:

• Detection of a fault that requires power to beremoved from the CALCM in launch countdown.

• Detection of a MIU fault that requires removalof power from the MIU at the location of theCALCM in launch countdown.

• Expiration of the launch countdown hold timer.• Exiting in-range boundary prior to ejector

squib.

The following provides a summary of the activitieswhich are required or will occur following abnormallaunch sequence termination.

• An abort message will be issued to theCALCM in launch countdown.

• Commands will be issued to remove all powerfrom the weapon, except in the case of the expiredlaunch countdown hold timer and battery activatewas not accomplished.

• When a MIU fault occurs that requires MIUpower to be removed, commands will be issued toremove all power from all CALCMs at the affectedMIU location prior to removing power from theMIU.

• If prerequisite conditions are satisfied, auto-matic retargeting will occur and a backup CALCMwill be launched in place of the unlaunchable weap-on, if in automatic launch mode.

• An abort release advisory will be displayed forthe CALCM whose launch was abnormally termina-ted. If the abort occurred after battery activate, anabort master fault and abort status will be dis-played also.

MISSILE JETTISON

The crew can command the SMO to jettison MIUcontrolled weapons at locations controlled by theSMO ([AMI] when the SMO is primary) and theMIUs at the selected locations are on. The crew canuse either the WPN Jettison switch on the WCP orthe pilots’ Bomb Bay & Missile Jettison Controlswitch.

• The pilots’ Bomb Bay & Missile JettisonControl switch jettisons all GWD and ac-tive/primary SMO controlled weaponsloaded on the aircraft and will only be usedas a backup to jettison by the Radar Navi-

gator. If jettison is commanded using the pi-lots’ Bomb Bay & Missile Jettison Controlswitch, all GWD weapons and, with OASoperating and MIUs/WIUs powered, all ac-tive/primary SMO controlled weapons willbe jettisoned. Proper separation clearancebetween weapons and between weaponsand aircraft cannot be ensured.

• Using the pilot’s Bomb Bay and Missile Jet-tison Control switch will cause the baydoors to open immediately. This is a hard-ware command and beyond the capability ofthe SMO to control. Having the bay doorsopen will inhibit jettison of the aft inboardstores on the pylons, if they were among thevalid selections for jettison by the SMO.

The pilots’ jettison switch will jettison all GWD andprimary/active SMO controlled weapons loaded onthe aircraft. If the WCP WPN Jettison switch isused, the jettison of CALCMs is controlled by theSMO and the process is as follows:

• Operator selects Location and Station of mis-sile(s) to be jettisoned on the WCP.

• Operator moves WPN Jettison switch to theSEL position.

1. If any bay weapons are among the weaponsto be jettisoned, the launcher will be commandedto the position of the weapon to be jettisonedthat is closest to the launcher end position (1 or8) that is closest to the launcher’s current downposition. (i.e., If weapons 6 and 7 are to be jetti-soned, and the launcher currently has position 4down, 1 is closer than 8 and position 6 will bejettisoned first. If position 5 is currently down, 8is closer than 1 and position 7 will be jettisonedfirst.)

2. The SMO determines which of the selectedweapons is first in the preferred jettison se-quence to start the jettison process. Pylon weap-ons will be jettisoned before bay weapons.

3. The selected weapon is powered down if ON.(steps 4 through 11 occur after the weapon ispowered down.)

NOTE

If jettison aborts for a CALCM after it ispowered down it will require an eight min-ute cool down period prior to being able topower it back up, if needed.

T.O. 1B-52H-34-2-9

Change 11 7-37

4. Prior to steps 5, 6, and 7, the following occurs:

• The master fault NO UE, associated withthe MIU controlling the weapon being jettisoned, will be displayed if ejector unlockenables are not present, and jettison will beaborted for weapons at that MIU.• An ACU transient will cause the weapon currently being jettisoned to abort the jettisonprocess• If the MIU controlling the weapon is powered down, jettison of all weapons controlled by that MIU will be aborted.• Jettison of the aft inboard weapons (left 6

or right 4) will be inhibited if the bay doorsare open.

5. For Bay weapon jettison, the SMO will checkfor door and launcher faults and if a fault(s) ex-ist, will not open the doors and will abort the jet-tison.

6. The SMO commands ejector unlock. Jettisonof the current weapon will abort if the MIU criti-cal function very fails.

7. The SMO commands ejector squib fire. Jetti-son of the current weapon will abort if the MIUcritical function very fails.

8. The SMO performs a scoring recording on theflight DTUC/DTC for the jettisoned missile.There is no scoring recording for aborted jettisonattempts.

9. The SMO determines if the missile has beensuccessfully jettisoned or is hung and either dis-plays JETT or HUNG for the jettisoned missilein on the Weapon release advisory along withthe location and station.

The Weapon Release advisory is requested on allMFDs that are not displaying the Selected Sta-tion Status Display. The Weapon Release adviso-ry will remain displayed for 5 seconds after thelast missile is jettisoned. The advisory area ofeach MFD where the Weapon Release advisory

is displayed will then be blanked. The SMO dis-plays the appropriate location and station forthe latest jettisoned missile on the CALCM re-lease advisory.

10. The Weapon Station Status will be update toreflect the change in missile status. The pres-ence window will display X to indicate no weap-on is present, and the weapon status windowwill display JT or HG based upon determinationof the success or failure of the jettison attempt.

11. The SMO repeats steps 3. through 10. untilall the selected weapons have been jettisoned.

12. If the bay doors were opened by jettison,they will be commanded closed as long as a bayCALCM was not hung during a jettison attempt.

If a weapon that failed to jettison (HUNG) was inthe bay the following will occur:

• Any existing jettison requests for the bay willbe cleared.

• Launch mode will be commanded to manual,but the operator can command it to automatic.

• Automatic launcher rotation for launch will beinhibited.

• Bay doors will remain open but can be closedusing the bay door command.

To continue bay jettisons, the jettison commandmust be reissued.

NOTE

• If a multiple CALCM jettison is command-ed, some of the weapons may not have a jet-tison or hung release advisory displayed.This is attributed to timing differences be-tween the jettison and the advisory displayupdate rate.

• There is no indication of an aborted jettisonother than the weapons still displayingpresent on FRMT-7.

T.O. 1B-52H-34-2-9

7-38 Change 10

SIMULATION

This paragraph describes any differences in theSMO capabilities when in PART SIM and FULLSIM modes as opposed to being in STRIKE mode.Entry into either ground maintenance mode (SIT orGo/No-Go) while either SIM mode is active is inhi-bited. PART SIM and FULL SIM will present thesame displays and responses to commands to thecrew as STRIKE mode does. In FULL SIM therewill be no data transmitted between the SMO andthe PDUC or MIUs. In PART SIM there will be nodata transmitted between the SMO and the MIUs.Therefore, actual responses to commands andWCE, weapon, and processing status’s are not avai-lable. The following concepts are implemented bythe SMO as part of the simulation process.

• No faults are declared for any simulated WCEor CALCMs.

• Times similar to STRIKE will be used to deter-mine when to display the results of WCE and mis-sile simulated responses and status’s. In general,simulated weapon alignment times will be shorterthan those of real weapons.

• The time line for normal launch or jettisonwill be followed and the appropriate display infor-mation provided.

• Operation of the launcher will not be simu-lated in PART SIM.

• Operation of the bay doors will not be simu-lated in either PART SIM or FULL SIM.

• Data will be formatted and transmitted to theAIU as needed.

• Initial status of simulated weapons will beSafe, Flight termination is not enabled, ordnancealarm is not indicated, ejector lock/unlock status islock, weapon power is OFF.

• Entering LCD is inhibited if operator ejectorunlock consent is not given.

• Weapons can only be declared No-Go if a LCDhold timer has expired.

PART SIM mode is commanded by entering CF-51from STRIKE mode. FULL SIM mode is command-ed by entering CF-52 from STRIKE mode. The op-erator can verify the currently active SMO mode byviewing any of the following Menus or displays:Control Function Menu, the Weapon SupervisionMenu, or the CALCM Supervision Menu.

PART SIM MODE COMMAND

Entry of CF-51 will command the SMO fromSTRIKE mode into PART SIM mode. If the com-mand is entered while the SMO is in PART SIMmode, it will be ignored. The SMO will reject a

CF-51 command and display it in reverse video un-der the conditions listed below.

• The system is in FULL SIM mode.• Mission data is not available.• Stores table is not loaded.• Mission data is for an operational (STRIKE)

mission.• Power is applied to either MIU or to any weapon.• Actual Go/No-Go test mode is active.• Actual System Integrity Test (SIT) test mode

is active.• 28 VDC T/R Power Discrepancy fault exists.• AIU Communication fault exists.• Any CALCM ejector is in the unlock state as de-


FULL SIM MODE COMMAND

Entry of CF-52 will command the SMO fromSTRIKE mode into FULL SIM mode. If the com-mand is entered while the SMO is in FULL SIMmode, it will be ignored. The SMO will reject aCF-52 command and display it in reverse video un-der the conditions listed following.

• The system is in PART SIM mode.• Mission data is not available.• Stores table is not loaded.• The B-52 mission that is loaded indicates an

operational (strike/war) mission or a timeline in-tegration (TLI) mission.

• Power is applied to either WIU or to any weapon.• Actual Go/No-Go test mode is active.• Actual System Integrity Test (SIT) test mode

is active.• 28 VDC T/R Power Discrepancy fault exists.• AIU Communication fault exists.• Any CALCM ejector is in the unlock state as de-


SIMULATED WEAPONS

Weapons to be simulated will be as defined in thestores table from the loaded sortie mission data.The weapon configuration can be viewed on theCALCM Status and Inventory display after the as-sociated simulated MIUs are turned on. Less[AMI] Simulated weapons require a real CALCMweapon DTUC to be mounted in order to do autoand manual targeting. [AMI] Preplanned weaponmission data must available and read from the DTCin order to do automatic or manual targeting.

SIMULATED MIU RESPONSES

Since no actual data is sent to or received from theMIUs, simulated commands will be used for status-ing only.

T.O. 1B-52H-34-2-9

Change 10 7-39

LAUNCHER OPERATION

FULL SIM simulates the launcher operation. PARTSIM uses the actual launcher, when it is present onthe aircraft.

Simulated Launcher Operation

Initial position of simulated launcher will be 1 uponentry into FULL SIM with CALCMs assigned inthe bay. Simulated movement between positionswill take place as commanded. Launcher commandswill simulate being carried out and status’s will bethe expected values for those commands.

Real Launcher Operation

Initial position of the actual launcher (if present)upon entry into PART SIM will be its actual posi-tion. All launcher control commands will be actual-ly carried out and actually statused.

GPS INITIALIZATION IN SIM MODE

GPS data will be retrieved from the IU or the sortiemission DTUC/DTC only to determine its availabil-ity.

SIMULATED LAUNCH IN SIM MODE

Simulated launch is still subject to all proceduresand constraints of a STRIKE launch (i.e. ECU over-ride, targeting complete for weapon to be launched,SAIR, etc.). Minimum launch interval betweensuccessive launches of two or more CALCMs will be5 seconds. If the Safe Release Conditions processingindicates a LCD hold should be entered, a hold willoccur until the hold conditions cease or the holdtimer elapses. Simulated CALCMs will be given alaunch status of AWAY on the CALCM Release Ad-visory when launched.

TERMINATION OF SIM MODE

Either SIM mode can only be terminated when allsimulated MIUs are OFF, and the operator com-mands CF-50 (STRIKE).

When either SIM mode is terminated, the status ofWCE and CALCM conditions are returned to theiractual status and any simulated states conflictingwith them are reset to reflect that actual status.

[AMI] After SIM mode is exited by commandingSTRIKE mode, the B-52 mission data and the SMOmust be reloaded to guarantee proper operation ofthe system.

BOMB TONE SCORING

The SMO controls Bomb Tone Scoring cutoff atweapon launch for each CALCM. The Bomb ToneScoring switch begins tone operation when momen-tarily placed to the INITIATE position, and will endthe tone if momentarily placed to the CUTOFFposition. The Bomb Tone Scoring switch must beused to initiate the tone prior to each launch or theSMO cutoff command will be ignored.

SIT/MIT AND CF-552

Various operational requirements dictate aircrewvalidation of Less [AMI] missile DTUCs, [AMI]DTC, and missile targeting ability. The use ofCF-552 during ground operations in conjunctionwith a maintenance run Systems Interface Test/Missile Interface Test (SIT/MIT) will allow targetdata to be loaded into missiles. The SIT/MIT en-ables maintenance crews to check the aircraft andmissile system without the B-52 INSs being pow-ered on. The SIT/MIT allows missiles to be poweredon, aligned, and targeted while on the ground. SeeSection II for the SIT/MIT checklist.

T.O. 1B-52H-34-2-9

7-40 Change 10

MALFUNCTION ANALYSIS

STATUS ONLY MONITORS

Status only monitors are used by the OAS to pro-vide data for other OAS functions.

Store Present

The store present monitor is used by OAS to displaythe C (CALCM) in the missile status block onFRMT-7. If a P is displayed, a store is present, butcannot be identified. If the store present monitor fora particular station is absent or in error, the OAScannot identify the type missile and therefore can-not properly process the missile functions or com-mands for that station. The OAS displays an xySTORE?? master fault for a store present statusfault.

Cage Complete Failure (Transient Fatal Fault)

The OAS uses the platform cage complete status toinitiate coarse alignment of the missile INS. If mis-sile platform cage complete status is not received bythe OAS processor 42 seconds after the coarse aligncommand has been sent, the OAS initiates a tran-sient fatal fault and removes power from the mis-sile. The missile status indication on FRMT-7 willgo from ON to OF (off) without indicating CA andthe OAS will display an XY 42S CAGE masterfault.

Coarse Align Complete

Coarse alignment status is used to initiate finealignment and to change missile status display. If acoarse align complete status is not received by theOAS 10 minutes after coarse align began, the OASwill display XY 10 MIN CA master fault.

ERROR MESSAGES

MASTER FAULTS

The SMO Master Faults are identified in Figure 7-9and 7-10. Master faults are an indication of WCE orCALCM failures. The FMS will display MasterFaults in reverse video at the bottom left hand endof the MFD (figure 7-8). When the faulted device isa MIU or a CALCM, the text that is displayed willbe preceded by a location or location and stationidentifier. The text for MIU faults that are not asso-ciated with a specific station will be preceded byBAY, LP, or RP identifying the faulted device loca-tion as the left pylon, bay or right pylon, respective-ly. CALCM faults and MIU faults that are associat-ed with a specific location will be preceded by alocation and station identifier of the form xy, wherex will be B, L, or R to identify the location, and y

will be the station number, 1 - 8 for the bay or 1 - 6for the pylons.

When a Master Fault occurs the following correc-tive actions may be taken by the crew:

• Power re-application can be commanded bythe operator when power is removed from a faulteddevice, however, if the SMO has determined thatpower should not be re-applied because of the fail-ure, the SMO will not respond to the command toapply power.

• The operator can override an ECU or ECUPOWER fault with the CF-68 ECU PWR ORIDEcommand to allow MIU and weapon power applica-tion.

With an ECU fault present, damage toequipment may occur if MIU power remainson as a result of selecting ECU Power Over-ride. While in ECU Power Override, theMIU may be operated using a 30 minute on,15 minute off, 30 minute on cycle.

• The operator can override a KEY VRFY No-Goand initiate targeting and/or launch of a CALCMwithout Crypto Keys by commanding the CF-55DCrypto Key Override command. There are four types of SMO master faults. Thefour types are described as follows:

Safety Critical (SC)

Safety critical faults present a safety threat to per-sonnel and/or the aircraft. The SMO will removepower from the faulted device immediately and in-hibit re-application of power by the operator.

Permanent Fatal (PF)

The SMO will remove power from the faulted deviceand inhibit re-application of power by the operator.

Transient Fatal (TF)

The SMO will remove power from the faulted device.Re-application of power by the operator is allowed.However, if missile power is removed prior to cagecomplete (weapon status shows CA), wait 8 minutesbefore attempting to reapply missile power. AnyCALCM or station transient fatal fault which occursafter battery activate has been commanded to thatmissile will be treated as a permanent fatal fault.

Non Fatal (NF)

The SMO will not remove power from the faulteddevice.

T.O. 1B-52H-34-2-9

Change 10 7-41

ADVISORIES

The CALCM Advisories are identified in figure7-11. Advisories are an indication to the operator ofan abnormality which may affect mission perfor-mance. The FMS will display Advisories at the bot-tom right hand of MFD. OAS Advisories are foundin Section III of T.O. 1B-52H-1-12.

CF-557, CF-558, AND FRMT-7 MISSILE FAULTS

The missile faults displayed in the individual sta-tion and selected station windows on CF-557,CF-558, and FRMT-7 are listed in figure 7-12.

Figure 7-8. FRMT-7 Fault Indications

T.O. 1B-52H-34-2-9

7-42 Change 10

MISSILE/STATION MASTER FAULTSFAULT INDICATION CODING:

• x = L (Left Pylon), R (Right Pylon), B (Bomb Bay)• y = Station Numbers 1 thru 8 (Bay), 1 thru 6 (Pylon)

FAULTINDICATION

FAULTCATEGORY

POSSIBLECAUSE

SYSTEMRESPONSE

OPERATORACTION

10-MIN CA Transient Fatal Missile did not completecoarse alignment withinrequired 10 minutes.

Missile power isremoved.

1. Acknowledge MF.2. Verify missile power status.3. Attempt to re-apply missile

power.

42-S CAGE Transient Fatal Missile did not completeplatform cage within re-quired 42 seconds.


1. Acknowledge MF.2. Verify missile power status.3. Wait 8 minutes then

attempt to re-apply missilepower.

ABORT Permanent Fatal Launch countdownabort after battery activation.

Missile power isremoved, re-applica-tion is inhibited, andmissile battery poweris depleted.

1. Acknowledge MF.2. Verify missile power status.3. Accomplish LAUNCH ABORT Checklist.

A/D Transient Fatal 1. Analog/Digital (A/D)Converter accuracyNo-Go

2. A/D ConverterUpdate No-Go


1. Acknowledge MF.2. Verify missile power status.3. If missile power was

removed prior to cagecomplete (weapon statusindicates CA), wait 8minutes before proceeding.

4. Attempt to re-apply missilepower.

AIR DATA Transient Fatal 1. Missile outside airtemperature fault.

2. Air Data computerfault.

Missile power is removed.




Figure 7-9. Missile/Station Master Faults (Sheet 1 of 10)

T.O. 1B-52H-34-2-9

Change 10 7-43

MISSILE/STATION MASTER FAULTS (Cont)

FAULTINDICATION

FAULTCATEGORY

POSSIBLECAUSE

SYSTEMRESPONSE

OPERATORACTION

BATTERY Transient Fatal Uncommanded CALCMbattery activate status.

Missile power isremoved, missilebattery power maybe depleted.




CARR INS Transient Fatal B-52 INS/INU failure. Missile power isremoved.

1. Acknowledge MF.2. Verify missile power

status.3. Recycle aircraft INS/INU.4. If missile power was


5. Attempt to re-apply missilepower when INS/INU datais available.

C/D ARMD Permanent Fatal OTL flight terminationsystem malfunction.



status.3. Do not re-apply missile power until resolution of the discrepancy.

CMU Transient Fatal Computer memory unitfault.


1. Acknowledge MF2. Verify missile power

status.3. If missile power was

removed prior to cagecomplete (weapon statusindicates CA), wait 8minutes before proceeding


Do not re-apply power until resolution of the discrepancy


T.O. 1B-52H-34-2-9

7-44 Change 10


FAULTINDICATION

FAULTCATEGORY

POSSIBLECAUSE

SYSTEMRESPONSE

OPERATORACTION

COMM NOGO Transient Fatal Missile communicationNo-Go.

1. Missile power isremoved.

2. If fault occurred after LCD, the LCD will beaborted andweapon power inhibited.

1. Acknowledge MF.2. Wait 8 minutes then

attempt to re-applyCALCM power.

3. If fault persists, verifypower is removed.

4. If fault occurs during launch countdown,

accomplish LAUNCHABORT Checklist.

EJECTOR Transient Fatal 1. Ejector fails tounlock whencommanded.

2. Ejector unlocked when not

commanded.3. Ejector locked when

not commanded.4. Solenoid does not

arm when in OTLmode.


2. Launch Count- down will be terminated.

3. Missile powerre-application inhibited, if fault occurs during LCD.

1. Acknowledge MF.2. Verify missile power status.3. If cause 1 or 3 occurred

prior to missile batteryactivate and prior to cagecomplete (weapon statusindicates CA), wait 8minutes before proceeding

4. If fault occurs during launch countdown,

accomplish LAUNCH ABORT Checklist.

Non Fatal Solenoid does not armwhen in Strike mode.

None. Acknowledge MF.

EMP Transient Fatal Electromagnetic Pulse(EMP) event detected.

OAS, MIU, andCALCM weaponpower is removed.

1. Wait until EMP clears.2. Re-apply OAS and MIU

power.3. If missile power was



FCE Transient Fatal 1. Flight Control Element (FCE) fault.

2. Ready to receivemission data No-Go.

The SMO will removepower from the faulteddevice.

1. Acknowledge MF.2. If missile power was




T.O. 1B-52H-34-2-9

Change 10 7-45


FAULTINDICATION

FAULTCATEGORY

POSSIBLECAUSE

SYSTEMRESPONSE

OPERATORACTION

FCE ENBL Transient Fatal Flight Control Element(FCE) enable fault.

The SMO will removepower from the faulteddevice.




FCS Transient Fatal Missile Flight ControlSystem (FCS) No-Go.





GPS NOGO Transient Fatal CALCM GPS ReceiverNo-Go. CALCM GPS Receiver Interface Unit(GRIU) may be faulty.





HUNG Permanent Fatal Missile failed to release. 1. Missile declaredNo-Go.

2. If the hung missile is in the bay:

A. Launch modewill be set to manual.B. Multiple jettisonrequest will be terminated for remaining weapons.C. Bay doors willremain open.

1. Acknowledge MF.2. Accomplish LAUNCH

ABORT/MISSION ABORT/RETAINED MISSILE(S) Checklist.


T.O. 1B-52H-34-2-9

7-46 Change 10


FAULTINDICATION

FAULTCATEGORY

POSSIBLECAUSE

SYSTEMRESPONSE

OPERATORACTION

INE Transient Fatal 1. Inertial Navigation Element (INE) output fault.

2. Inertial Navigation serial data bus fault.

3. Inertial Navigation Element platform fault.





INE HTR Transient Fatal Inertial Navigation Element (INE) platformheater fault.





INE RELAY Transient Fatal Inertial Navigation Element (INE) relayfault.





INE TEMP Transient Fatal Inertial Navigation Element (INE) platformtemperature fault.


1. Acknowledge MF.2. Verify missile power status.3. A restart may be possible

after 1/2 hour of stabilizedtemperature.


All data on pages 7-46A and 7-46B (Deleted)

T.O. 1B-52H-34-2-9

Change 10 7-47


FAULTINDICATION

FAULTCATEGORY

POSSIBLECAUSE

SYSTEMRESPONSE

OPERATORACTION

INIT DATA Transient Fatal Almanac Loaded No-Go.


1. Acknowledge MF.2. Verify validity of Almanac

data from IU or Less [AMI] Mission DTUC,[AMI] Sortie Mission DTC,if IU off.

3. If missile power was removed prior to cagecomplete (weapon statusindicates CA), wait 8minutes before proceeding

4. Attempt to re-apply missile power.5. If fault persists:

A. Reload SMO.B. Load valid almanac data into IU.C. Re-apply power to MIU and weapons.

INS Transient Fatal 1. CALCM INSalignment fault.

2. CALCM INS Z velocity fault.



status.3. Check aircraft Prime INU

alignment. 4. If missile power was

removed prior to cage complete (weapon status indicates CA), wait 8 minutes before proceed-ing.

5. Attempt to re-apply missile power.

KEY VRFY Non Fatal CALCM Crypto KeyVerify Fail.

1. SMO will not remove power from faulted device.

2. Invalid keys resident in IU.

3. Invalid keys resident in Less [AMI] DTUC,[AMI] Sortie DTC.

1. Acknowledge MF.2. Verify validity of crypto key

data from IU (orLess [AMI] DTUC,[AMI] Sortie DTC, if IU is off).

3. If keys are requiredfor mission: A. Cycle missile power .B. After missile targets,verify fault status. C. If fault persists,reload SMO, load validkey data into IU, and apply power to MIU and weapons.

4. If keys are not requiredfor mission:Enable Crypto Key Override and ignore fault.


T.O. 1B-52H-34-2-9

7-48 Change 10


FAULTINDICATION

FAULTCATEGORY

POSSIBLECAUSE

SYSTEMRESPONSE

OPERATORACTION

MSL NOGO Transient Fatal Missile Separation Armfailure.





MSL PWR Transient Fatal Missile electronic, hy-draulic, or instrumenta-tion power discrepancy.





MSN DATA Transient Fatal 1. CALCM CMU power on No-Go.

2. Mission load complete No-Go.

3. CALCM Checksum No-Go.

4. Almanac data loadchecksum failure.

5. Critical mission data valid No-Go


2. If launch in progress:A. Launch will beaborted.B. Missile powerwill be removed.C. Power reapplication will be inhibited.

3. CALCM mission data may be invalid.

1. Acknowledge MF.2. If fault occurred during

launch countdown accomplish LAUNCHABORT Checklist.

3. If missile power was removed prior to cagecomplete (weapon statusindicates CA), wait 8minutes before proceeding.

4. Attempt to re-applymissile power.

5. Determine Less [AMI]DTU, [AMI] DTC status,from FRMT-6.

6. Re-attempt B-52 MissionData load.


T.O. 1B-52H-34-2-9

Change 10 7-49


FAULTINDICATION

FAULTCATEGORY

POSSIBLECAUSE

SYSTEMRESPONSE

OPERATORACTION

MSN ERASE Transient Fatal Mission erasecomplete.

Missile power isremoved. Missile can-not be launched due tolack of valid mission.

1. Acknowledge MF.2. Verify missile power status.3. Attempt to reload missile

mission.4. Determine Less [AMI]

DTU, [AMI] DTC, status from FRMT-6.

5. Reinstall Less [AMI] Missile Mission DTUC intodifferent DTU cavity andreload mission,[AMI] DTC into differentDTR and reload mission.

NTIK BATT Permanent Fatal 12 minute NTIK batterypower timer expired.

1. Missile power is removed.

2. Missile power re-application is inhibited.

1. Acknowledge MF.2. Verify missile power status.

NO FUZE Transient Fatal Fuze not connected(AGM-86D only).

1. Missile power is removed.

2. Missile power re-application is permitted.




NOT LOCKDNOT LOCKD Transient Fatal Ejector locked statuscannot be determined.

Missile power is removed.



4. Do not re-apply power untilresolution of discrepancy.

ORD ALARM Safety Critical 1. INE relays not inSAFE position.

2. Separation lanyardswitch has beentriggered.

3. WAD is not SAFE.

1. Missile power removed immediately.

2. Missile power reapplication is inhibited.

1. Acknowledge MF.2. Verify missile power status.3. Do not re-apply power until resolution of

the discrepancy.

Do not re-apply power until resolution of the discrepancy


T.O. 1B-52H-34-2-9

7-50 Change 10


FAULTINDICATION

FAULTCATEGORY

POSSIBLECAUSE

SYSTEMRESPONSE

OPERATORACTION

OTL PWR Non Fatal OTL power is not in thecommanded state.

1. Launch count-down entry is inhibited.

2. Enters launch holdif launch is in progress.

1. Acknowledge MF.2. Verify OTL power status.3. Cycle OTL power.

OVERFLOW Transient Fatal 1. CALCM data overflow No-Go.

2. Invalid missile mission loaded.





5. Load different mission into missile.

RAE Non Fatal Missile Radar AltimeterEquipment (RAE) failure.

1. Terrain followingmode will be inhibited duringmissile free-flight.

2. Launch will beallowed.

1. Acknowledge MF.2. Wait until cage complete

(weapon status indicates CA) then cycle missile power if missile mission requires terrain following.

STORE?? Non Fatal 1. Missile umbilical monitor disagreeswith mission data.

2. Missile warheadtype disagrees withmission data.

1. Power will not beapplied to the weapon with a non CALCM/ALCMumbilical type indication.

2. Weapon will nottarget if the storestable MIU information in invalid.

1. Acknowledge MF.2. Cycle MIU power.3. Less [AMI] Verify correct

mission has been loaded.4. [AMI] Verify correct

sortie/mission has beenloaded.

TIME OUT Permanent Fatal After Battery Activate Launch Hold Timer expired.

1. Launch is aborted.2. Missile power is

removed. 3. Missile will be

declared No-Go.

1. Acknowledge MF.2. Verify missile No-Go.3. Accomplish LAUNCH ABORT Checklist.4. If in-flight, perform mission

event recording (CF-65)

UNCMD REL Transient Fatal Uncommanded release. The SMO will re-move power to storelocation.

1. Acknowledge MF.2. Accomplish LAUNCH

ABORT/MISSIONABORT/RETAINED MISSILE(S) Checklist.

3. If in-flight, perform missionevent recording (CF-65).


T.O. 1B-52H-34-2-9

Change 10 7-51


FAULTINDICATION

FAULTCATEGORY

POSSIBLECAUSE

SYSTEMRESPONSE

OPERATORACTION

UNCMD UL Transient Fatal 1. Ejector unlockedwhen not commanded.

2. Ejector failed tolock when commanded.


1. Acknowledge MF.2. Select ejector unlock on

pilot’s consent panel andWCP.


4. Re-apply power to affectedmissile.

5. Perform normal launchprocedures, if applicable.

WPN ERASE Permanent Fatal Insufficient OFS incomputer memory

The SMO will removepower from the missileand inhibit re-applica-tion of power.

1. Acknowledge MF.2. Verify missile power status

WPN PRSNT Non Fatal Ejector and umbilical status disagree aboutweapon presence.

Missile may beunusable.

1. Acknowledge MF.2. Verify missile power status3. Cycle MIU and missile

power.4. If fault persists, verify

missile power is removed.


T.O. 1B-52H-34-2-9

7-52 Change 10

OAS/MIU MASTER FAULTS

FAULTINDICATION

FAULTCATEGORY

POSSIBLECAUSE

SYSTEMRESPONSE

OPERATORACTION

AIU Non Fatal 1. AIU communications failure.

2. AIU terminal failure.3. Interruptible Direct

Current (IDC) power enable discrepancy (uncommanded ON or OFF).

May result in any or allof the following:1. Loss of ECU power

control. 2. Loss of MIU

power control.3. Missiles cannot be

powered, launched,or jettisoned.

4. Loss of OAS control of bay doors.

5. RBS tone cutoff willnot occur

6. Loss of jettison capability..

1. Acknowledge MF.2. Check circuit breaker on

auxiliary BNS and S/Vfilter box circuit breakerpanels. Pull and resetif necessary.

3. Verify status of MIU power and weapon power.

AIU 28 VDC Non Fatal 28 VDC missile powerdiscrepancy for bay, leftpylon, or right pylon.

May result in any or allof the following:1. Unable to apply

MIU essential (ESS) power.

2. Unable to applystore 28VDC #1power.

1. Acknowledge MF.2. Verify status of MIU and weapon power.3. Check circuit breaker on

auxiliary BNS and S/Vfilter box circuit breakerpanels. Pull and resetif necessary.

BAY EED PWR(Same actions/re-sponses for LPand RP EEDPWR)

Non Fatal or Transient Fatal

28 VDC EED power notin commanded state; onwhen commanded off oroff when commandedon.

1. During launch orjettison if power is not present when requested, a nonfatal fault will occurand the MIU willremain on, howeverthe launch or jettisonsequence will beaborted.

2. If EED power ispresent when not commanded, atransient fatal faultwill occur and powerwill be removed fromthe missiles and theMIU.

1. Acknowledge MF.2. Accomplish LAUNCH ABORT Checklist.3. Cycle MIU power.4. Re-apply power to the MIU,

if removed.5. Accomplish normal launch

procedures, if desired.6. If EED power is present when not desired fault

persists, verify that CALCMand MIU power is removed.

BAY ESS PWR(Same actions/re-sponses for LPand RP ESSPWR)

Non Fatal orTransient Fatal

1. 28 VDC ESS power on when commanded

off.2. 28 VDC ESS power

is off when commanded on.

1. For cause 1, a NonFatal fault will occurand the MIU willremain on.

2. For cause 2, a Transient Fatal faultwill occur andmissile and MIU willbe removed.

1. Acknowledge MF.2. If missile and MIU power

remains on, cycle missile and MIU power.

3. If missile and MIU power were removed, re-apply power.

4. Accomplish normal launchprocedures.

5. If the fault resulted in a launch abort, accomplish

LAUNCH ABORTchecklist.

6. If cause 2 persists, verify MIU power removed.

Figure 7-10. OAS/MIU Master Faults (Sheet 1 of 8)

T.O. 1B-52H-34-2-9

Change 10 7-53

OAS/MIU MASTER FAULTS (Cont)

FAULTINDICATION

FAULTCATEGORY

POSSIBLECAUSE

SYSTEMRESPONSE

OPERATORACTION

BAY MIU(Same actions/responses for LPor RP MIU)

Non Fatal or

Transient Fatal

Non Fatal1. First time MIU Critical

Command Register Fault.

2. MIU BIT fault.3. First time MIU Critical

Verify fault.

Transient Fatal1. Two consecutive MIU

communication failures.

2. MIU end-around test failure.

3. MIU Not Reset fault. 4. MIU Not Clear fault.5. Second MIU Critical

Command Register fault.

6. Second MIU Critical Verify fault.

7. MIU terminal failure.

Non Fatal Fault - None

Transient Fatal -MIU and missile powerremoved. No missilefunctions including jet-tison or launch may beaccomplished ataffected location.

1. Acknowledge MF.2. Re-apply MIU power if

removed.

NOTE

MIU power switch must bepressed and released toreset and then pressedagain to re-apply MIUpower.If fault clears, CF-54 canbe entered to overrideapproximately 35 minutesof the 40 minute MIUwarmup time.

3. If fault persists, verifyMIU power is removed.


•

•

.

BAY NO UE(Same actions/re-sponses for LPand RP NO UE)

Non Fatal MIU unlock enable notpresent during autolaunch mode when inSAIR, during LCD orwhen jettison has beencommanded.

Launch and jettisoninhibited.

1. Acknowledge MF.2. Command lock then

unlock onpilot’s missile consentpanel and WCP.

3. If fault remains:A. Set Pilot and WCP consent switches to LOCK.B. Remove missile power C. Cycle MIU power.

D. Set pilot and WCP consent switches to UNLOCK.

4. Accomplish normal launchprocedures.

5. If fault persists, accomplish LAUNCH ABORT Checklist.

BAY UNCMDDRVR(Same actions/re-sponses for LPand RP UNCMDDRVR)

Non Fatal orTransient Fatal

Driver status of truewhen not commanded.

Non FatalFirst time - None Transient Fatal Second time - Poweris removed from MIUand CALCM.

1. Acknowledge MF.2. If LCD abort , accomplish

LAUNCH ABORT checklist.3. Re-apply MIU power.4. If fault persists, verify MIU

power is removed.5. If missile power was

removed prior to cage complete (weapon status indicates CA), wait 8minutes before attempting to re-apply missile power.


T.O. 1B-52H-34-2-9

7-54 Change 10


FAULTINDICATION

FAULTCATEGORY

POSSIBLECAUSE

SYSTEMRESPONSE

OPERATORACTION

BAY UNCMD UE(Same actions/re-sponses for LPand RP UNCMDUE)

Non Fatal During MIU power onsequence, unlock en-able is present when notcommanded.

1. Uncommanded ejector unlock.

2. Ejector fails to lock.

1. Acknowledge MF.2. Remove MIU power.3. Re-apply MIU power.4. If fault persists, do not

attempt live launch.5. Ensure launch mode is

manual.

CALCM EVENT[AMI]

Transient Fatal The CALCM SMO issecondary and aCALCM missionplanned launch point iswithin 20 minutes of theaircraft.

Weapon for missionplanned launch point isnot targeted.

1. Acknowledge MF.2. Make the CALCM SMO

primary.3. Power on and target

weapons.

CALCM MSNDATA??[AMI]

Non Fatal No Mission data or noMIUs in the storestable.

Missiles will not target or launch.

1. Acknowledge MF.2. Verify valid CALCM sortie

mission is loaded.3. Reload valid sortie mission

CALCM NO CLAPAR[AMI]

Non Fatal No Classified Parame-ters loaded.

No SAIR ranging canbe accomplished, as aresult missiles will notbe launched.

1. Acknowledge MF.2. Retarget the affected

missiles.

CALCM SMO/MSN[AMI]

Non Fatal The CALCM SMO isnot in the SMO ID list inthe Stores Table.

Weapons will not target or launch.

1. Acknowledge MF.2. Verify valid CALCM

sortie mission is loaded.3. Reload valid sortie

mission.

CALCM WPNDATA??[AMI]

Non Fatal 1. DTC read error whileretrieving weapon data.

2. DTC not available during manual targeting.

Weapon mission datais not available.

1. Acknowledge MF.2. Verify correct DTC is

installed and selected.3. Confirm DTC status on

FRMT-6.4. Remove and reinstall DTC

in same DTR.5. Remove and reinstall DTC

in other DTR.

DOORS Non Fatal Bay Door malfunction. Temporarily inhibits au-tomatic launch/jettison from CSRL.

1. Acknowledge MF.2. Confirm doors status on

CF-5.3. Check MISCELLANEOUS

-GAM-72 GEAR JETTI-SON & AGM69A circuitbreaker on Pilot’s CircuitBreaker Panel. Pull and reset, if required.

4. Attempt to open doors using CF-59 (if not in LCD) or the RN BOMB DOOR CONTROL switch.

5. Attempt to open doors using Pilot’s BOMB DOORS control switch.


T.O. 1B-52H-34-2-9

Change 10 7-55


FAULTINDICATION

FAULTCATEGORY

POSSIBLECAUSE

SYSTEMRESPONSE

OPERATORACTION

ECU Non Fatal ECU environmental No-Go and ECU PowerOverride is off. May becaused by the following:

1. ECU fault2. Insufficient airflow.3. Low engine power

settings.4. Transient failure

during climb ordescent.

5. Icing conditions.

1. Weapon temperatureor airflow out of limits

could cause degradedweapon performanceand weaponmalfunctions.

2. MIU could overheatand shutdown.

NOTE

Fault displayed andrecorded every 30minutes, as long asthe fault is present.

With an ECU fault pres-ent, damage to equip-ment may occur if MIUpower remains on as aresult of selecting ECUPower Override. Whilein ECU Power Over-ride, the MIU may beoperated using a 30minute on, 15 minuteoff, 30 minute on cycle.

1. Acknowledge MF.2. If low airflow, increase

power on engines 3 and 4.Abort on ground, if faultdoes not clear.

3. Close air outlet knobs anddecrease cabintemperature. Abort onground, if fault does notclear.

4. Verify pilot’s cabin pressuremaster switch is in ECS.

5. In potential icing conditionscheck pilot’s anti-icing isON. Descending may clearMaster Fault.

6. If ECU fault cannot beisolated and/or cleared,and override is desired,CF-68 commands ECUPWR ORIDE.

7. If ECU fault cannot becleared, and if ECU PWRORIDE is not desired,remove power from theMIU and weapons as soonas possible after receivingthe fault.


T.O. 1B-52H-34-2-9

7-56 Change 10


FAULTINDICATION

FAULTCATEGORY

POSSIBLECAUSE

SYSTEMRESPONSE

OPERATORACTION

ECU PWR Non Fatal ECU AC power discrep-ancy (uncommanded onor off) and ECU Overrideis OFF.

NOTE

Fault displayed andrecorded every 30minutes, as long asthe fault is present.

Loss of cooling air toMIU.1. If fault occurs prior toMIU power on, the MIUand weapons cannot bepowered on.2. If the fault occurs af-ter MIU power on, theweapons cannot bepowered on.

With an ECU fault pres-ent, damage to equip-ment may occur if MIUpower remains on as aresult of selecting ECUPower Override. Whilein ECU Power Over-ride, the MIU may beoperated using a 30minute on, 15 minuteoff, 30 minute on cycle.

1. Acknowledge MF.2. Check MIU and weapon

status.3. If fault override is desired,

enter CF-68 to activateECU Power Override.

4. If fault cannot be cleared, and ECU Power Overrideis not desired, removepower from weapons andMIUs within two minutesof receiving fault.


T.O. 1B-52H-34-2-9

Change 10 7-57


FAULTINDICATION

FAULTCATEGORY

POSSIBLECAUSE

SYSTEMRESPONSE

OPERATORACTION

LNCHR Non Fatal 1. PDS Rotation fault.2. PDUC subsystem

failure.3. Launcher moving

fault.4. Launcher position

discrepancy.

PDUC reset/initializa-tion performed.

1. Acknowledge MF.2. Switch to right body

system and attempt manual rotation.

3. Cycle PDUC power in an attempt to clear fault

4. Attempt to rotate CSRL using the WCP.

5. Recycle OAS, if required.

LP EED PWR(See BAY EEDPWR)

Transient Fatal SEE BAY EED PWR.

LP ESS PWR(See BAY ESSPWR)

Transient Fatal SEE BAY ESS PWR.

LP MIU(See BAY MIU)

Transient Fatal SEE BAY MIU.

LP NO UE(See BAY NO UE)

Non Fatal SEE BAY NO UE.

LP UNCMDDRVR(See BAY UNCMD DRVR)

Non Fatal SEE BAY UNCMD DRVR.

LP UNCMD UE(See BAY UNCMD UE)

Non Fatal SEE BAY UNCMD UE.

MSN DATA??Less [AMI]

Non Fatal No Mission data or noMIUs in the stores table.


1. Acknowledge MF.2. Verify valid CALCM sortie

mission is loaded.3. Reload valid sortie mission.4. Reinstall Missile Mission

DTUC into different DTUcavity and reload mission.

NO CLAPARLess [AMI]

Non Fatal No Classified Parame-ters loaded.

No SAIR ranging canbe accomplished, as aresult missiles will notbe launched.

1. Acknowledge MF.2. Retarget the affected

missiles.


T.O. 1B-52H-34-2-9

7-58 Change 10


FAULTINDICATION

FAULTCATEGORY

POSSIBLECAUSE

SYSTEMRESPONSE

OPERATORACTION

PDU Non Fatal CSRL PDU fault. 1. Launcher cannot berotated.

2. Launch countdown terminated if targeted weapon isnot in the 6 O’clockposition.

3. Additional launchesand jettison of bay missiles may be inhibited.

1. Acknowledge MF.2. Recycle PDUC power

switch.3. Attempt to rotate CSRL

using WCP switches. 4. Recycle OAS, if required.

PDUC Non Fatal 1. PDUC communica-tions failure.

2. PDUC initialization fault.

3. Indexing mode discrepancy.

4. PDUC fault.5. Out of indexed

position fault.

1. Launcher cannot berotated.terminated.

2. Launch countdown terminated if targeted weapon isnot in the 6 O’clockposition.

3. Additional launchesand jettison of Bay missiles may be inhibited.

1. Acknowledge MF.2. Switch to right body

system and attempt manual rotation.

3. Recycle PDUC power switch.

4. Recycle OAS if required.

RP EED PWR(See BAY EEDPWR)

Transient Fatal SEE BAY EED PWR.

RP ESS PWR(See BAY ESSPWR)

Transient Fatal SEE BAY ESS PWR.

RP MIU(See BAY MIU)

Transient Fatal SEE BAY MIU.

RP NO UE(See BAY NO UE)

Non Fatal SEE BAY NO UE.

RP UNCMDDRVR(See BAY UNCMD DRVR)

Non Fatal SEE BAY UNCMD DRVR.

RP UNCMD UE(See BAY UNCMD UE)

Non Fatal SEE BAY UNCMD UE.


T.O. 1B-52H-34-2-9

Change 10 7-59


FAULTINDICATION

FAULTCATEGORY

POSSIBLECAUSE

SYSTEMRESPONSE

OPERATORACTION

SMO/MSNLess [AMI]

Non Fatal The CALCM SMO isnot in the SMO ID list inthe Stores Table.


1. Acknowledge MF.2. Install CALCM

SMO DTUC.3. Load CALCM SMO.4. Insert correct mission

DTUC.5. Load correct mission.

UNLOCK CONSENT

Non Fatal Pilot’s consent panellock/unlock and WCPnuclear lock/unlockswitches are not inagreement.

1. Ejector will not unlock.

2. CALCM weapon launch is not possible.

1. Acknowledge MF.2. Check PMCP Lock/Unlock

switch and WCP nuclear Lock/Unlock switches for disagreement.

3. Align switches4. If fault persists, remove

weapon power and cycle MIU power.

5. If fault clears, proceed with normal launch procedures.

WPN DTUCLess [AMI]

Non Fatal 1. Weapon DTUC read error.

2. Weapon DTUC not installed during manual targeting.

Weapon mission datais not available.

1. Acknowledge MF.2. Verify correct weapon

DTUC is installed and selected.

3. Confirm DTU status on FRMT-6.

4. Remove and re-seat weapon mission DTUC.

5. Re-install DTUC in alternate DTU cavity.


T.O. 1B-52H-34-2-9

7-60 Change 10

CALCM ADVISORIES

FAULTINDICATION

POSSIBLECAUSE

SYSTEMRESPONSE

OPERATORACTION

GPS DATA ADVISORIES

ALMANAC DATALess [AMI]

Almanac data retrieval for weapons tar-geted from the IU or DTUC failed.

Missiles will not target.

1. Verify IU or sortie DTUC containsvalid almanac data.

2. Reissue CF-559 command.

ALMANACLOADEDLess [AMI]

Almanac data has been loaded fromthe IU or from the B-52 Mission DTUCfor targeting.

None.

CALCM ALMANACLD[AMI]

Almanac data retrieval for CALCMweapon targeting from the IU or DTCfailed.

Weapons will nottarget or launch.

Verify IU or DTC contains valid almanac data then reissue CF-559command.

CALCM CRYPTOKEY[AMI]

CALCM Crypto Key Override is not commanded and Crypto Key data retrieval failed.


1. Verify IU or DTC contains valid Crypto Key data.

2. Enter Crypto Key data.3. Command Crypto Key

Override.4. Reissue CF-559 command.

CALCM GPS LOADED[AMI]

Almanac data has been retrieved fromFMS for targeting.

Normal Operation. Acknowledge advisory message.

CKEY ALERT Daily B-52 Crypto Key data will expirein two hours.


1. Determine expected mission time remaining.

2. If keys are valid through the re-mainder of the mission, continue.

3. If keys will expire prior to missioncompletion, update keys through the IUPKB.

CRYPTO KEYSLess [AMI]

CALCM Crypto Key Override is not commanded and Crypto Key data retrieval failed.


1. Verify IU or DTUC contains valid Crypto Key data.

2. Enter Crypto Key data.3. Command Crypto Key Override.4. Reissue CF–559 command.

DAILY KEY 1. Crypto Keys are not valid for the current date.

2. An incorrect date was input on CF-61.


1. Verify correct date input on CF-61.

2. If available, input current keys through the IUPKB.

GPS DATA GPS navigation data is unreasonableor not valid.


1. Verify IU or Less [AMI] sortie DTUC, [AMI] DTC,contains validCrypto Key data.

2. Enter Crypto Key data. 3. Command Crypto Key Override. 4. Re-issue CF-559 command.

GPS LOADEDLess [AMI]

Crypto key and Almanac data havebeen loaded from the IU or from theB-52 Mission DTUC for targeting, orCrypto Key Override is commandedand almanac data has been loadedfrom the IU or from the B-52 missionDTUC for targeting.

None.

Figure 7-11. CALCM Advisories (Sheet 1 of 5)

T.O. 1B-52H-34-2-9

Change 10 7-61

CALCM ADVISORIES (Cont)

FAULTINDICATION

POSSIBLECAUSE

SYSTEMRESPONSE

OPERATORACTION

GPS DATA ADVISORIES (Cont)

INSUF KEYS Insufficient Crypto Keys to satisfy mis-sion duration.


1. Verify determine mission duration from the GPS Crypto Key page atthe IUPKB.

2. If the mission duration is equal toone day, continue.

3. If the mission duration is greater than one day, reenter a mission duration of one day through the IUPKB crypto key page.

KEYS LOADED Crypto key data has been loaded fromthe IU or from the B-52 Mission DTUCfor targeting.

None.

ZEROIZE FAIL The attempt to erase B-52 Crypto Keydata failed.

Missiles will nottarget or launch.

1. Re-select GPS zeroize at the IUCP.

2. Treat IU and GPS receiver as crypto classified.

LOCATION/STATION ADVISORIES

B: LOCATION[AMI]

The Bay location select switch was se-lected, but no SMO is assigned to thatlocation.

Command will notbe processed.

Deselect Bay Switch.

CALCM CLAPAR LD[AMI]

Classified parameters have beenloaded so ranging can occur.


CALCM GYROWAIT[AMI]

Gyro spin–down timer has not expiredafter powering CALCM off.

Power on commandwill be ignored.

Wait until GYRO spin-down timer expires.

CALCM LOC/STA??[AMI]

An invalid selection of a location and/orstation is used for a command.

Command not processed.

Select only stations that have a CALCM present.

CALCM STATION??[AMI]

Invalid station select switch was pressed.

Command not processed.

Select a valid station (7 and 8 are not valid stations on the left and right pylons).

CALCM WARMUP[AMI]

CALCM warm–up timer has not expired, warm–up override is not enabled and power application is commanded.

Power on commandwill be ignored.

Command warm-up override or waituntil warm-up timer expires.

CAPTIVE CARRY(Normal Video)

A captive carry mission has beenloaded and/or PLUS CT mode be-comes active after MIUs are powereddown.


CAPTIVE CARRY(Reverse Video)

A captive carry B-52 mission load hasbeen attempted with MIUs powered on.

Captive Carry launchwill not be per-formed.

Load operational mission or powerdown the MIUs.

CLAPAR LOADEDLess [AMI]

Classified parameters have beenloaded so that ranging can occur.

None.


T.O. 1B-52H-34-2-9

7-62 Change 10


FAULTINDICATION

POSSIBLECAUSE

SYSTEMRESPONSE

OPERATORACTION

LOCATION/STATION ADVISORIES (Cont)

L: LOCATION[AMI]

The Left Pylon location select switchwas selected, but no SMO is assignedto that location.


Deselect Left Pylon Switch.

LOCATION?? A station switch was selected with nolocation selected or an operation wasattempted without designating a location on the WCP.


Select a location before selecting astation.

LOC/STA??Less [AMI]

An invalid selection of a location and/orstation is used for a command.


Select only stations that have aCALCM present.

PDU Hydraulic Backup System change. Normal operation ismaintained

1. Manually rotate the launcher toverify launcher rotate capability.

2. Monitor launcher rotation status.

R: LOCATION[AMI]

The Right Pylon location select switchwas selected, but no SMO is assignedto that location.


Deselect Right Pylon Switch.

STATION??Less [AMI]

An invalid station select switch (7 or 8for pylon weapons) was selected, or anoperation was attempted without des-ignating a Station on the WCP.


Select a valid station.

B-52 mission data does not identify aweapon that is compatible with theSMO.

Load a B-52 mission that identifiescompatible weapons.

WARMUP/GYROWAITLess [AMI]

1. CALCM 40 minute warm-up timer has not expired.2. CALCM 15 second Gyro spindown timer has not expired.3. CALCM 8 minute gyro cool down

time has not expired.

Power on commandwill be ignored formissiles with the ad-visory.

1. Apply missile power after warm-up timer expires.

2. Apply power to missile after therequired 15 second or 8 minute time required after missile powerremoval.

x: JETT INHIB[AMI]

A jettison request was issued for a loca-tion where the SMO is not Primary.

Weapon jettisoncannot be accom-plished until thatweapon’s SMO is primary.

Make the location’s SMO Primaryand re-issue the command .


T.O. 1B-52H-34-2-9

Change 10 7-63


FAULTINDICATION

POSSIBLECAUSE

SYSTEMRESPONSE

OPERATORACTION

MISCELLANEOUS ADVISORIES

CALCM ABORTXFR[AMI]

Targeting of a CALCM is in progressand any of the following occur:1. Weapon is being powered off for

any reason.2. Weapon’s MIU is being powered

down for any reason.3. Weapon Serial communication

error (Double MUX error).4. Critical Mission data transfer error

(Copy check failure).5. Almanac data transfer error (Check-

sum check failure).6. Aircraft Time or Crypto Key data

transfer error (Echo check failure).7. Weapon DTC not mounted when

manual targeting requested (accompanied by a CALCM WPN DATA?? fault).

8. Weapon DTC data read failure (accompanied by a CALCM WPN DATA?? fault).

Attempted targetingdid not complete.

1. Reenter targeting for the affected CALCM (refer to FRMT-7 display to determine affected CALCM).

2. Ensure DTC is installed.3. Verify power status of weapons

and MIUs.

CALCM EVENT[AMI]

The CALCM SMO is secondary and aCALCM mission planned launch pointis within 25 minutes of the aircraft.

Weapon for missionplanned launchpoint is not targeted.

1. Make the CALCM SMO primary.2. Power on weapons.

CALCM LCD ENTRY[AMI]

1. OTL instrumentation power stateincorrect.

2. Unlock enables are not present.

3. Weapon fatal fault exists.4. Weapon is safe.5. Bay doors are unlatched

(if bay launch).6. Launcher fault and launcher is not

in position (if bay launch).

Weapon will not enter launch count-down.

1. Set OTL instrumentation power state correctly.

2. Ensure Pilot and Navigator consent switches are both in the unlock position.

3. Select different weapon to launch.4. Place weapon into ready.5. Attempt manual door command

(CF-59) to open doors.6. Attempt manual launcher rotation

to position launcher.

CALCM TAL REQD[AMI]

Transfer Alignment Maneuver requiredfor powered on CALCMs.

Perform transfer alignment maneuver.

LCD ENTRY INHBLess [AMI]

1. OTL instrumentation power stateincorrect.

1. Set OTL instrumentation power state correctly.

2. Unlock enables are not present. 2. Ensure Pilot and navigator consent switches are both in the

unlock position.3. Weapon fatal faults exist. 3. Select different weapon to

launch.4. Weapon is safe. 4. Place weapon into ready.5. Bay doors are unlatched (if bay

launch).5. Attempt manual door command (CF-59) to get doors open.

6. Launcher fault and launcher is notin position (if bay launch).

6. Attempt manual launcher rotation to position launcher.


T.O. 1B-52H-34-2-9

7-64 Change 10


FAULTINDICATION

POSSIBLECAUSE

SYSTEMRESPONSE

OPERATORACTION

MISCELLANEOUS ADVISORIES (Cont)

SMO LDREQUIREDLess [AMI]

New destination requires a SMO to beloaded.

1. Determine if the destination is the desired destination.

2. Load/reload the SMO.

SMO RCNFG FAILLess [AMI]

Reconfiguration of the SMO was unsuccessful.

1. Ensure OCP DTUC is installed2. Determine DTU status from

FRMT-6.3. Reload SMO.

STORES DATA FAIL[AMI]

A failure occurred while CSP was loading the Stores Data from the DTC.

Stores Data will notbe available for theSMO.

Ensure the DTC is properly insertedin the DTR.

TAL REQDLess [AMI]

Transfer Alignment Maneuver requiredfor powered on CALCM(s).

Perform transfer alignment maneuver.

TARGET XFRABORTLess [AMI]

Targeting of a CALCM is in progressand any of the following occur:1. Weapon is being powered off for

any reason.2. Weapon’s MIU is being powered

down for any reason.3. Weapon Serial Communication

error (Double MUX error).4. Critical Mission data transfer error

(Copy check failure).5. Almanac data transfer error

(Checksum check failure).6. Aircraft Time or Crypto Key data

transfer error (Echo check failure).7. Weapon DTUC not mounted when

manual targeting requested (accompanied by a WPN DTUC fault).

8. Weapon DTUC data read failure(accompanied by a WPN DTUCfault).

Requested targetcommand did notcomplete.

1. Retry Targeting the affectedCALCM (refer to FRMT-7 displayto determine affected CALCM).

2. Ensure CALCM mission DTUCis installed and selected.

3. Verify power status of missilesand MIUs.

STATUS MESSAGES

GO/NOGO COMPLT[AMI]

The Go/No-Go Test has been com-pleted for all missiles that have hadpower applied.

Acknowledge advisory message.

SIT COMPLT[AMI]

The System Interface Test has beencompleted for all missiles that havehad power applied.

Acknowledge advisory message.


T.O. 1B-52H-34-2-9

Change 10 7-65

CF-557, CF-558, AND FRMT-7 WEAPON FAULTS

MESSAGE FAULT CATEGORY

CAUSE

ABORT____ Permanent Fatal Launch countdown aborted after battery activated.

A/D______ Transient Fatal A/D converter accuracy No-Go.A/D converter update No-Go.

AIR_DATA_ Transient Fatal Air data equipment failure.

BATTERY__ Transient Fatal Battery activated with power off.

Less [AMI] CARR_INS_ Transient Fatal Carrier INS failure.

[AMI] CARR_INU_ Transient Fatal Carrier INU failure.

C/D_ARMD_ Transient Fatal Flight termination enable failure.

CMU______ Transient Fatal Computer memory unit failure.

COMM_NOGO Transient Fatal Communications fault.

EJECTOR__ Transient Fatal 1. Uncommanded lock or ejector fails to unlock.2. Armed solenoid failed when in OTL mode.

EMP______ Transient Fatal EMP event detected by weapon.

FCE______ Transient Fatal 1. Flight control element fault.2. Ready to Rec. Mission Data No-Go.

FCE_ENBL_ Transient Fatal Flight control element enable fault.

FCS______ Transient Fatal Flight control equipment failure.

GPS_NOGO_ Transient Fatal GPS receiver No-Go.

HUNG_____ Permanent Fatal Hung store.

INE_RELAY Transient Fatal INE relay failure.

INE______ Transient Fatal Platform No-Go/INE output No-Go/INE serial data bus failure.

INE_HTR__ Transient Fatal Platform heater No-Go.

INE_TEMP_ Transient Fatal Platform temperature No-Go.

INIT_DATA Transient Fatal Almanac data not received.

INS______ Transient Fatal INS alignment failure or Z-velocity No-Go.

KEY_VRFY_ Non Fatal Crypto key verify fail in GPS receiver.

MSL_NOGO_ Transient Fatal Separation Arm failure.

MSL_PWR__ Transient Fatal Weapon electronic power discrepancy.

MSN_DATA_ Transient Fatal 1. Data checksum error.2. Mission Data Valid error.3. Primary Mission Load Complete No-Go.4. Go/No-Go Test CMU power on No-Go.

MSN_ERASE Transient Fatal Mission data erase performed.

NO_FUZE Transient Fatal Fuze not connected for penetrator.

Figure 7-12. CF-557, CF-558, and FRMT-7 Weapon Faults (Sheet 1 of 2)

T.O. 1B-52H-34-2-9

7-66 Change 10

CF-557, CF-558, AND FRMT-7 WEAPON FAULTS (Cont)

MESSAGE FAULT CATEGORY

CAUSE

NOT_LOCKD Transient Fatal Illegal ejector status; both locked or unlocked or neither locked or un-locked.

NTIK_BATT Permanent Fatal OTL battery timer exceeds 12 minutes.

OTL_PWR__ Non Fatal Uncommanded instrumentation power on/off.

ORD_ALARM Safety Critical Ordnance alarm.

OVERFLOW_ Transient Fatal Data overflow.

RAE______ Non Fatal Radar altimeter equipment failure.

STORE??__ Non Fatal Store table discrepancy.

TIME_OUT_ Permanent Fatal Hold timer for post battery activate has expired.

UNCMD_UL_ Transient Fatal 1. Uncommanded ejector unlock.2. Fails to lock.

UNCMD_REL Transient Fatal Uncommanded Release.

WPN_ERASE Permanent Fatal Weapon erase performed.

WPN_PRSNT Non Fatal Store present monitors disagree.

42-S_CAGE Transient Fatal INE failed to cage in 42 seconds.

10-MIN_CA Transient Fatal INE failed to coarse align in 10 minutes.

(Blank) 1. MIU power is off.2. Store is not a CALCM.3. No CALCM or station faults at this station.4. For selected station status, no store is selected.

Figure 7-12. CF-557, CF-558, and FRMT-7 Weapon Faults (Sheet 2 of 2)

T.O. 1B-52H-34-2-9

Change 10 Glossary-1

GLOSSARY

AC Alternating CurrentACC AccelerateACU Avionics Control Unit (Avionics

Processor)ADCU Air Data ElementADE Air Data ElementAGL Above Ground LevelAGM Air-to-Ground MissileAIU Armament Interface UnitALT AltitudeALTR AlternateAMI Avionics Midlife ImprovementANT AntennaAP Avionics ProcessorAPU Avionics Processor UnitARMD Armed (Prearmed on FRMT 7)AUTO AutomaticAUX AuxiliaryBARO BarometricBATT BatteryBAY Bomb BayBH Barometric HoldBIT Built-In-TestBMJCP Bombbay & Missile Jettison

Control PanelC&D Controls And DisplaysCA Coarse AlignmentCAD Controls And DisplaysCAL CalibrateCALCM Conventional Air Launched

Cruise MissileCB Circuit BreakerC/D Command/DestructCD Control DisplayCDIU Control Display Interface UnitCEP Circular Error ProbabilityCF Control FunctionCLSD ClosedCLSF ClassifiedCMPTR ComputerCOM CommunicationsCRT Cathode Ray TubeCSP Common Stores ProcessingCSRL Common Strategic Rotary

LauncherCWE Current Weapon EventDAA Direct Approach AzimuthDAS Damage Assessment Strike

DC Direct CurrentDEU Display Electronics UnitDOB Depth of BurialDPLR DopplerDSBL DisableD/T Destination/TargetDTC Data Transfer CartridgeDTU Data Transfer UnitDTUC Data Transfer Unit CartridgeDVS Doppler Velocity SystemECU Environmental Control UnitEED Electro-Explosive DeviceEMERG EmergencyENBL EnableETA Explosive Transfer Assembly

(OTL)FA Fine AlignFCE Flight Control ElementFCI Flight Command IndicatorFCP Flight Computer ProgramFCS Flight Control SystemFIU Fuze Interface UnitFLT FlightFMS Flight Management SystemFRMT FormatFWD ForwardFXPT FixpointG & C Guidance and ControlGPS Global Positioning SystemGRIU/P GPS Receiver UnitGS GroundspeedHA Absolute AltitudeHA True AltitudeHAC High Altitude CalibrationHDG HeadingHT Terrain ElevationHTR HeaterHTSF Hard Target Smart FuzeHUNG Hung MissileHV High VoltageICSMS Integrated Conventional Stores

Management SystemIEU Interface Electronic UnitIKB Integrated KeyboardIND IndicatorINE Inertial Navigation EquipmentINS Inertial Navigation Set/SystemIRU Inertial Reference Unit

T.O. 1B-52H-34-2-9

Glossary-2 Change 10

GLOSSARY (Cont)

JETT JettisonJTA Joint Test AssemblyJTU Joint Test UnitKLM Kalman FilterLAC Low Altitude CalibrationLAT LatitudeLCD Launch CountdownLH Left-HandLKD LockedLNCH LaunchLOC LocationLOCKD LockedLONG LongitudeLP Left PylonLRU Line Replaceable UnitLSC Linear Shaped Charge (OTL)MAL MalfunctionMAN ManualMAX MaximumMCU Multiplexer Conversion UnitMDFY ModifyMEM MemoryMIU Missile Interface UnitMFD Multifunction DisplayMGMT ManagementMIL STD Military StandardMIU Missile Interface UnitMNTIK Modified Nontactical Instrumen-

tation KitMP Memory PointMPO Modified Push OverMSG MessageMSL Mean Sea LevelMSN MissionMSTR MasterNAV Navigator, NavigationNAWC Navigation and Weapon ControlNAWD Navigation and Weapon DeliveryNF Non FatalNG No-GoNKB Navigator KeyboardNM Nautical MileNTIK Nontactical Instrumentation KitNUC NuclearNUC SLU Nuclear Station Logic UnitOAS Offensive Avionics SystemOC Operational ComputerOCP Operational Computer ProgramOF OffOPER Operator/Operate

ORIDE OverrideOTL Operational Test LaunchPCP Power Control PanelPDB Power Distribution BoxPDU Power Drive UnitPDUC Power Drive Unit ControlPF Permanent FatalPLUS CT Plus CountPMCP Pilot’s Munitions Consent PanelPMD Prime Mission DataPME Prime Mission EquipmentPNL PanelPOS PositionPP Present PositionPRGM ProgramPROC ProcessorPTA Planned Time of ArrivalPWR PowerRA Radar AltimeterRAE Radar Altimeter ElementRCD Release Circuits DisconnectRCDR RecorderRCVR ReceiverRDR RadarRDY ReadyREF ReferenceRG Range (Ground)RH Right-HandRIU Radar Interface UnitRN Radar NavigatorRNG RangeRNKB Radar Navigator KeyboardRNMP Radar Navigator Management

PanelRP Right PylonRTL Ready To LaunchSAF Safe Arm Fuse SystemSAIR Safe and In RangeSC Safety CriticalSEL SelectSIM SimulateSIT System Interface TestSMO Stores Management OverlaySUPV SupervisionS/V Survivability/VulnerabilitySW SwitchSWP Pre-target Steering Waypoint

(Flex Targeting)SYNC Synchronization

T.O. 1B-52H-34-2-9

Change 10 Glossary-3/(Glossary-4 blank)

GLOSSARY (Cont)

TA Transfer AlignmentTA Temperature Altitude Time (3.0 to

10.5 second CALCM battery life)TAL Transfer Alignment ManeuverTAS True AirspeedTC Terrain ClearanceTCS Terrain Clearance SensorTEMP TemperatureTF Transient Fatal/Terrain FollowingTGT TargetTH True HeadingTK TrackTR Transformer-RectifierTRANS TransferTRK TrackTRNG TrainingTTG Time to GoUC Upper CornerUCT Universal Coordinated TimeUL Upper LeftUR Upper Right

UNCMD UncommandedUNLK UnlockUTC Universal Time CoordinateV VelocityVAC/vac Volts Alternating CurrentVAR VariableVDC/vdc Volts Direct CurrentVFR Visual Flight RulesVRCDR Video RecorderVG Vertical GyroscopeVV Vertical VelocityV/v VoltsWAD Warhead Arm DeviceWCE Weapon Control EquipmentWCP Weapon Control PanelWCS Weapon Control SystemWGS-84 World Geodetic System (1984)WPN WeaponWPN JETT Weapon JettisonW/V Wind/VelocityXFR Transfer

T.O. 1B-52H-34-2-9

Change 10 Index-1

INDEX

*DENOTES ILLUSTRATION

Page

AAcceleration and Vertical Velocity Checks 7-24Advisories, CALCM 7-41, 7-60*After Engine Start 2-10After Landing Procedure 2-29After Parking 2-29AGM-86 Missile 1-3AGM-86D Fuze Data Display, CF-DF

1-70, 1-70A*Aircraft

Common Strategic Rotary LauncherSystem 1-7

Electrical System 1-12Environmental Control System 1-12OAS/CALCM Operation 7-2

Aircrew Procedures, Emergency 3-1Aircrew Procedures, Normal 2-1Altitude and Pressure Checks 7-24Analysis, Malfunction, OAS/Missile 7-40Anti-icing and Pressurization 1-12Application, Missile Power – Navigator,

Inflight Procedures 2-11Arrangement, Missile General 1-5*Automatic Retargeting 7-31Auto Targeting Scheme 7-11*Avionics Limits on Launch, Aircraft 5-1

B

B-52 Mission Data Load Display CF-81 1-67, 1-68C*

B-52/AGM-86 Conventional Air Launched CruiseMissile (CALCM) Weapon System 1-3

B-52/CALCM Loaded Pylon Jettison Restrictions 3-6*

B-52 Avionics System 1-17B-52 Carrier Aircraft 1-3Before Descent, Prelanding Procedures 2-29Before Exterior Inspection (Power Off)

Preflight Procedures 2-3Bomb Tone Scoring 1-26*, 7-39

Page

C

CALCM Advisories 7-60*CALCM Auto-Retarget Due To L3 Fail 7-32*CALCM Fuzing System 1-6C*CALCM Group Assignment

Data Display, CF-DF 1-75, 1-77*CALCM OAS Software and Displays 1-37CALCM SMO 1-37Carrier Aircraft, B-52 1-3Control Function (CF) Displays 1-42Control Function (CF) Menu 1-44B*CF-DD, Send Targeting Data Command 1-70CF-DE, Exit Targeting Mode Command 1-70CF-DF, AGM-86D Fuze Data Display 1-70, 1-70A*CF-DF, CALCM Group Assignment

Data Display 1-75, 1-77*CF-E, Weapon Control Panel Backup

Display 1-70, 1-72B*CF-5 Weapon Supervision Menu 1-42, 1-44D*CF-55 CALCM Supervision Menu 1-46, 1-46A*CF-557 CALCM Flex Target Input Display

for Launch Point nn 1-47, 1-48*CF-557, CF-558, and FRMT-7

Weapon Faults 7-65*CF-558, nn Direct Target Input Display

for Direct Target nn 1-57, 1-58*CF-6, FCP Supervision Menu 1-66C, 1-66E*CF-62, SMO Load Menu 1-66C, 1-66G*CF-8 Mission Supervision 1-67, 1-68A*CF-81 B-52 Mission Data

Load Display 1-68, 1-68C*CF-82A, CF-82B, CF-82C Weapon

Group Selection Menu 1-68, 1-69*Circuit Breaker Panels 1-13*Circuit Protection 1-16*Configuration, Launcher 1-8*Configuration, Pylon 1-11*Control and Guidance System, Missile 1-6Controls and Indicators, Pilot’s Jettison 1-31*Controls and Indicators, Pylon Jettison 1-34*Control Panel, OAS Power 1-20, 1-27*Control Panel, Weapon 1-17, 1-24*Control System, Aircraft Environmental 1-12Control System, Missile Environmental 1-6CSRL Carriage CG Limitations 4-2A*CSRL Carriage of CALCM Missiles with a Test

Instrumentation Kit 4-2A

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Index-2 Change 10

Page

D

Data Changes, Inflight Mission 6-1Descent, Before, Prelanding Procedures 2-29Destination Table Display FRMT-10 1-75, 1-82*Direct Target Ranging Examples 7-30*Direct Targeting Input Screen

CF-558,nn 1-57, 1-58*Direct Target Ranging Geometry 7-28*, 7-29*Direct Target Trajectory 7-13*Display, CF-5 Weapon Supervision 1-42, 1-44D*Display, CF-8 Mission Supervision 1-67, 1-68A*Display (CF-E), Weapon Control Panel

Backup 1-70, 1-72B*Display (FRMT-7), Weapon Status and

Inventory 1-74, 1-76D*Display, Multifunction 1-20, 1-29*

EEED Power 1-12Ejector Rack, MAU-12 1-7Electrical

System, Aircraft 1-12System, Missile 1-4

Emergency Aircrew Procedures 3-1Environmental Control System, Aircraft 1-12Environmental Control System, Missile 1-6Error Messages 7-40Exterior Inspection, Preflight Procedures 2-3

FFaults, Master 7-40Faults, Missile/Station Master 7-42*Faults, OAS/MIU Master 7-52*FCP Supervision Menu CF-6 1-66C, 1-66E*Firefighting And Evacuation Criteria 3-9*Flex Targeting Selection Command

CF-557,nn 1-47, 1-48*Flight Command Indicator 4-4*Flight Control System, Missile 1-6Flight Limits for Missile Separation,

Missile Level 5-1Format Commands 1-75*Format (FRMT) Displays 1-74, 1-76*

FRMT-6, PME Status Display 1-74, 1-76A*FRMT-7, Status and Inventory

Display 1-74, 1-76D*FRMT-7xy, Status and Inventory

Display Request 1-74, 1-76D*FRMT-77, Stores Inventory Summary

Display 1-75, 1-80*FRMT-10, Destination Table

Display 1-75, 1-82*

Page

FRMT-7 Fault Indications 7-65*Fuze Data Display, CF-DF 1-70, 1-70A*Fuze Data Entry 7-23

GGlossary Glossary-1Ground Safeing Procedures (Bay Missiles) –

Navigator and Radar Navigator 2-31Ground Safeing Procedures (Pylon Missiles) –

Navigator and Radar Navigator 2-30Guidance and Control System, Missile 1-6Guidance Transfer Alignment Maneuver 2-26*

HHazardous Material, Transportation of 6-1

I

InflightMission Data Changes 6-1Procedures 2-11

In-Range Determination 7-25Ranging Modes 7-25Safe and In-Range Indication 7-27

Interior Inspection, Preflight Procedures 2-9Integrated Keyboard (IKB) 1-28*

JJettison

Controls and Indicators, Pilot’s 1-31*Pylon Controls and Indicators 1-34*Missile 1-30, 3-1, 7-36Procedures, Missile 3-1Procedures, Pylon 3-3Pylon 1-33, 3-3System, Missile 1-32*System, Pylon 1-33, 1-35*

KKeyboard, Integrated (IKB) 1-20, 1-28*

LLaunch

Abort 2-27Procedures 2-19System, Operational Test Launch (OTL) 4-1

Launcher Configuration 1-8*Launcher Hydraulic System 1-9*Limitations, Operating 5-1Limits On Launch, Aircraft Avionics 5-1Lock-Unlock Control 1-7

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Change 10 Index-3

Page

M

Malfunction Analysis 7-40Manual SAIR Footprint 7-26*Master Faults 7-40MAU-12 Ejector Rack 1-7Missile

Arming System 1-6AData Flow 1-22*Dimensions and Gross Weight 1-4Electrical System 1-4Environmental Control System 1-6Faults 7-42*Flight Control System 1-6General Arrangement 1-5*Guidance and Control System 1-6Jettison 1-30, 7-36Jettison Procedures 3-1Jettison Switch 1-30Jettison System 1-32*Launch 7-33Level Flight Limits for Missile

Separation 5-1OTL Equipment 4-1Power Application 2-11Propulsion and Fuel System 1-6Pylon Jettison Restrictions 3-6*Software Classification 1-4

Missile/Station Master Faults 7-42*Mission

Abort/Launch Abort 2-27Data 7-9Data Entry 7-17Data Items 7-16Data Changes, Inflight 6-1Planning 6-1Supervision (CF-8) 1-67, 1-68A*Types 7-9

Multifunction Display 1-20, 1-29*Munitions Consent Panel, Pilot’s 1-17, 1-23*

NNormal Aircrew Procedures 2-1Notification Procedures

Dangerous Materials 3-7

Page

O

OAS Power Control Panel 1-27*OAS/CALCM Operation, Aircraft 7-2OAS/Missile Data Flow 1-22*OAS/MIU Master Faults 7-52*OAS/Weapon System Related

Controls And Displays 1-17Offensive Avionics System (OAS) 1-17Offensive Avionics System (OAS)

Interface 1-17Operating Limitations 5-1Operation, Aircraft OAS/CALCM 7-2Operational Test Launch (OTL) System 4-1OTL Capabilities 4-2OTL Functions 4-1

PPilot’s Jettison Controls and Indicators 1-31*Pilot’s Munitions Consent Panel 1-17, 1-23*Pilots’ Station CALCM Related

Controls and Switches (Typical) 1-21*Planning, Mission 6-1Plus Count Mode 4-3Power

Application, Missile 2-11Drive Unit Control (PDUC)

Power Switch 1-7, 1-10*Preflight

Interior Inspection 2-9Procedures Before Exterior Inspection 2-3Procedures Exterior Inspection 2-3

Prelanding Procedures 2-29Pre-Target Steering Waypoint Turn Angle

(Direct Launch Only) 7-24Prime Mission Data 1-40BProcedures

After Engine Start 2-10After Landing 2-29After Parking 2-29Emergency Aircrew 3-1Inflight 2-11Launch 2-19Launch Abort/Mission Abort 2-27Missile Jettison 3-1Missile Launch 2-21Normal Aircrew 2-1Notification, Dangerous Materials 3-7Preflight 2-3Prelanding 2-29Pylon Jettison 3-3

T.O. 1B-52H-34-2-9

Index-4 Change 10

Page

Program Commands, SMO 1-84*Program (PRGM) Display 1-83, 1-85*Protection, Circuit 1-16*Pylon

Jettison Restrictions 3-6*Configuration 1-11*Description 1-7Jettison 1-33, 3-3Jettison Procedures 3-3Jettison Controls and Indicators 1-34*Jettison Control Switch 1-33Jettison System 1-35*Lock-Unlock Control 1-7MAU-12 Electro-explosive Device

(EED) Power 1-12MAU-12 Ejector Rack 1-7Missile Preferred Launch/Jettison

Release Sequence 3-5*Missile Separations, Speed

Restrictions 5-1

RRack, MAU-12 Ejector 1-7Ranging Modes 7-25Release Advisory Display 1-40B, 1-41*Release Circuits Disconnect (RCD) 1-33Remote Command Control System 4-1

S

Safe Launch Determination 7-24Simulation 7-38Speed Restrictions for Pylon Missile

Separations 5-1SIT/MIT and CF-552 1-46C, 7-39SIT/MIT Procedures (Ground) 2-32SMO, CALCM 1-37SMO

Capabilities 7-3Control Function Commands 1-44*Initialization 1-37Launch Point Program Display (PRGM) 1-85*Launch Point Program Display

(PRGM) (Auto SAIR) 1-86*Launch Point Program Display

(PRGM) (Direct Target) 1-93*Launch Point Program Display

(PRGM) (Manual SAIR) 1-89*MFD Displays 1-40BProgram Commands 1-84*Reconfiguration 1-38Restart 1-38Strike Capabilities 7-3Termination 1-37Weapon Control Equipment Monitor

and Power Control 7-3

Page

Stores Inventory Summary Display 1-75, 1-80*Supplementary Data 4-1System

Aircraft Electrical 1-12Aircraft Environmental Control 1-12Missile Arming 1-6AMissile Electrical 1-4Missile Environmental Control 1-6Missile Guidance and Control 1-6Missile Jettison 1-30, 1-32*Missile Propulsion and Fuel System 1-6Operational Test Launch 4-1Operations 7-1Pylon Jettison 1-33, 1-35*

TTransportation of Hazardous Material 6-1Transfer Alignment Maneuver 2-26*

WWeapon Control Panel 1-17, 1-24*Weapon Control Panel Backup

Display (CF-E) 1-70, 1-72B*Weapon Faults CF-557, CF-558, FRMT-7 7-65*Weapon Group Assignment Data Display

(CF-DF) 1-75, 1-77*Weapon Group Selection Menu

(CF-82A, CF-82B, CF-82C) 1-68, 1-69*Weapon Monitor And Power Control 7-5Weapon Power Application 7-7Weapon Power Removal 7-8Weapon Status and Inventory

Display (FRMT-7) 1-74, 1-76D*Weapon System, B-52/AGM-86C (CALCM) 1-3Weapon Supervision Menu CF-5 1-42, 1-44D*Weapon Targeting Commands 7-12

aircrew weapons delivery manual (nonnuclear) b-52… 1b-52h-34-2-9... · t.o. 1b-52h-34-2-9 1 june...

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