thµntrnentoffran5{xx1ation - supplemental type certificate€¦ · 1 1500-1260-001 overhead umt...

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Thµntrnentoffran5{XX1ation - FeooalA viationAdministration

Supplemental Type Certificate .,;fl'~ ST00129SE

Rockwell Collins Aerospace and Electronics, Inc. 27300 SW Parkway Avenue Wilsonville, OR 97070

~ dud,~ IA, d, ~ t:htjmfod,~~,m:d d, ~ ,vu/~

~ aJ ~~meet; d, ~dvze.i; ~ g/!J11,v1 25 g/d, Federal Aviation

~-&npl,nd!J11~-~ W~A'.wnk·

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A13NM

Bombardier, Inc (deHav1lland)

DHC-8 Serres 100, 200, and 300• •see Type Certificate Data Sheet for FAA approved models

9JeJ~tMg/d, ~9JeJtjm W~.· Installation of the Head-Up Display Guidance System, Model 2800, in accordance with Flight Dynamics Master Drawing Lrst 9701-0868, Revrsron W, dated September 18, 2001, or later FAA approved revIsrons

~ ,vu/ Wu,uukiM.1: Approval of !hrs change in type desrgn applies to the above models of aircraft only Thrs change has only been demonstrated to be acceptable for use in operations associated wrth Category I and Category II Landrng Mrnrma as defined in FAA Advrsory Circular 120-29, Category Illa Landing Minrma as defined in FAA Advisory Circular 120-28C and takeoffs in low vrsrbrlity condrtrons as defined in JAA AWO Subpart 4 Thrs approval should not be extended to other aircraft of these models on whrch other previously approved modrficatrons are incorporated unless rt Is determined that the relatIonshIp between thrs change and any of those other previously approved modrfrcatrons, includrng changes in type desrgn, wrll introduce no adverse effect upon the arrworthiness of that aircraft A copy of thrs certrfrcate, Continuation Sheet, and FAA approved Flight Manual Supplement must be marntained as part of the permanent records for the modified aircraft

(See Page 3 for addrtronal Lrmrtatrons and CondrtIons)

9%id cv'ifoai;- mu/ d, ;~ ~ u;.lid ii d, l'adil fo~;,la/'/',em,.zu,. u,. #a adi/

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Iifac, g/ ~=· Iifau g/ ,:,;ua,u,e. ·

March 26, 1993

September 29, 1994

Iifau,.,,,,ued· Aprrl 16, 2003, January 21, 2010

Iifau umended· 12/23/93, 12/3/01, 4/16/03

(S1gnat11re) Actrng Manager, Seattle Aircraft

Certrficatron Office (Title)

Any alteration of this certificate 1s punishable by a fme of not exceedmg $1,000, or 1mpnsonment not exceedmg 3 years, or both

This certificate may be transferred m accordance with FAR 21 47

FAA FORM 8110-2(10-68)

,, ~

Deµn1mentoffransportation - FederalA viationAdminist:ratioo

Supplemental Type Certificate (Continuation Sheet)

./ft~ ST00129SE

Rockwell Collins Aerospace and Electronics, Inc Flight Dynamics D1v1s1on

Reissued. April 16, 2003, January 21, 2010 Amended. 12/23/97, 12/3/01, 4/16/03

The 300 model has not been evaluated for operational approval under 14 CFR part 121 579 (c) and 121 651 (c) and (d). Before any US. registered aircraft of this type can operate under Part 121, it must demonstrate operational suitability in accordance with the above Advisory Circulars and criteria or other means acceptable to the Administrator

If the holder agrees to permit another person to use this Certificate to alter the product, the holder shall give the other person written evidence of that permission

-END-

Any alterat,on ofth1s certificate Is punishable by a fine of not exceedmg $1,000, or,mpnsonment not exceedmg 3 years, or both

FAA FORM 8110-2-1 (10-69) This certificate may be transferred m accordance with FAR 21 47

PAGE 3 OF 3 PAGES

I' .

l

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m111tt Gtutifttate ./f'unz.le,. ST00129SE Flight Dynamics 16600 SW 72nd Avenue Portland, OR 97224

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~@~a'~-u de~:1;-e?"~ uyf!Jl',vl' 25 uyfde Federal Aviation

..9i'epaMIOll.1.

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A13NM

Bombardier Inc. (deHavilland)

DHC-8 Series 100, 200 and 300* •see Type Certificate Data Sheet for FAA approved models

gtJ.1an;-,t'«Hl, uyf de~ g,:,1~ %'~: Installation of the Head-Up Display Guidance System, Model 2800, In accordance with Flight Dynamics Master Drawing List 9701-0868, Revision W, dated September 18, 2001, or later FAA approved revisions .

.:ltmit'al'IOll.1 r:v,a' Wwuu:tlOlld .· Approval of this change In type design applies to the above models of aircraft only. This change has only been demonstrated to be acceptable for use In operations associated with Category I and category II Landing Minima as defined in FAA Advisory Circular 120-29, Category Illa Landing Minima as defined in FAA Advisory Circular 120-28C and takeoffs in low visibility conditions as defined in JAA AWO Subpart 4. This approval should not be extended to other aircraft of these models on which other previously approved modifications are incorporated unless it is determined that the relationship between this change and any of those other previously approved modifications, including changes in type design, will introduce no adverse effect upon the airworthiness of that aircraft. A copy of this certificate, continuation sheet and FAA approved Flight Manual Supplement must be maintained as part of the permanent records for the modified aircraft.

fi'k u,t~ r:vu¥ de :1,.y~ dat'a udid i$ d. /adi$ fo ~J,fd/;-emau,, iA #,,l'u.n,;i/' :I~ :I~~ IN'a ~hn, dz/',, i$ ~e ,:,1rJl'.dM,/p d. .W~l'n,,t',p,o/d, sr~.w~.w~~

March 26, 1993

September 29, 1994 S}ffat,, ~- 12/23/97; 12/03/01

gnatme) Acting Manager, Seattle Aircraft

Certification Office ([Ille/

Any alteration of Ibis certificate is pum'shable by a fine of 1101 e'<ceedmg $1,000. or imprisonment not exceed mg 3 years, or both

This certificate may be trn11sferred Ill accordance w1t/J FAR 2 J .47.

,, II_Uiestern·, Engineenng Department ~ ~ I 275 Palmer Road N E AVlONICS Calgary, Alberta T2E 7G4

(403) 250-2644

ENGINEERING ORDER 60605-410, Revision 2

Head-Up Guidance System (HGS) and Inertial Reference System (IRS)

Installation - Full Provisions and Activation

Model (s): de Havilland DHC-8-300

Aircraft Registration: {J E - L rP --=-=-------':._:_ ________ _

Aircraft Serial Number: --~I'_r_L'I ________ _ ..

Date Revision 2: December 10, 2001

Prepared By:

Reviewed By:

The drawings spec1ficat1ons descnpt1ons, and other technical data attached hereto are property and covenant to Western Avionics Inc and constitute secrets for purposes of Trade Secret and Freedom of Information Acts No disclosure to others, either 1n Canada or abroad or reproduction of any part of the 1nformat1on supphed 1s to be made, except by written authonzat1on from Western Av1omcs

Copynght © 2000 Western Avionics

60605-410, Rev 2 Page 1 of 30

., 2:,0--2644

RECORD OF REVISIONS

REV. PAGES REVISIONS DATE APPROVED

AFFECTED BY

- - Initial Issue March 21, 2000 S. Harke

Deleted step 3 13

1 4, 7 to 10, and Moved steps 29,312, and 3 14 May 11, 2000 M Jaques 25 to 30 Changed wording steps 310,311,316

Added Step 5 1 and Appendix E

Changed wording in Section A

2 3, and 11 to 14 Changed HGS Computer PIN December 10, 2001 ,, Changed Appendix A reference '

60605-410, Rev 2 Page 2 of 30

A.

B.

' .)

WESTERN AVIONICS ENGINEERING ORDER# 60605-410

APPLICABILITY

This Engineenng Order provides the detailed installation instructions to incorporate the -301

configuration (Dash 8-300 HGS With Complete Retrofit Kit) as defined on Flight Dynamics MDL

9701-0868

BACKGROUND

A new Flight Dynamics (FD) Model 2800 HUD Guidance System (HGS) will be installed in the

aircraft A mounting bracket and the HGS computer will be installed under the floor between X400-

420 and the Drive Electronic Umt (DEU) will be installed above the wardrobe. In order to display the

HGS information, the Overhead Unit (OHU), Holographic Combiner, HGS Control Panel (HCP),

Remote Airspeed Select Unit (RASU) and HGS Annunciator will be installed in the aircraft cockpit

C. DESCRIPTION

a. The Flight Dynamics Model 2800 HUD Guidance System consists of the following Line Replaceable

Units (LRU's).

Item Part Number Descnpt1on Quantity

1 1500-1260-001 Overhead Umt (OHU) 1

2 1500-1290-002 HGS Control Panel (HCP) 1

3 1500-1300-003 HGS Computer (HGC) 1

4 1500-1320-002 Remote Airspeed Select Umt (RASU) 1

5 1500-1330-001 Drive Electronics Umt (DEU) 1

6 1500-1350-003 Combiner 1

7 1500-1360-002 Annunciator Panel 1

60605-410. Rev 2 Page 3 of 30

b The Honeywell Laseref IV Inertial Reference System consists of the following Line Replaceable Units

(LRU's)

Item Part Number Description Quantity

1 HG2001GD03 Inertial Reference Unit (IRU) 1

2 CG1042AB03 Mode Select Unit (MSU) 1

Flight Dynamics drawing 1000-0280 (lnstallabon, HGS MDL 2800, DHC8) provides an overview of

the installed components and their locations

D. MATERIALS REQUIRED

E.

F.

The Cable Assemblies required to perform this modification are contained In Western Avionics

Mod1ficabon Kit# 60605-401-001. This kit contains Flight Dynamics' Kit# 1000-0280-301 with some

pre-assembly work performed to minimize aircraft downtime The installer Is responsible to supply

consumables and standard shop supplies

The LRUs Idenbfied In Section C above are not contained in the modification kit, and must be

procured separately

APPROVAL

The Flight Dynamics Model 2800 HUD Guidance System installation completed as per this

Eng1neenng Order, Is approved under FAA STC ST00129SE

LABOUR

The 1nstallat1on of the Model 2800 HUD Guidance System will take approximately 500 man-hours to

complete This esbmate Is for direct labor performed by an experienced crew, and 1t doesn't include

planning, fam1hanzation, access, or lost time

60605-410, Rev 2 Page 4 of 30

" G. WEIGHT AND BALANCE CHANGES

Table 1: WEIGHT AND BALANCE

STATION. WEIGHT MOMENT ITEM (inches) (pounds) (inch pounds)

Overhead Unit 93 00 27 00 2511 00

Combiner 75 20 600 451 20

DEU 136 00 8.00 1088 00

HGS Computer 414 50 2600 10777 00 ,, HCP 9600 3.00 288 00

HGS Annunciator Panel 49.20 1.00 4920

RASU 96.00 3 00 288 00

IRU 284.00 17.10 485640

MSU 6000 1 00 6000

HGS Structural & Wiring Provisions 242.55 61.80 14989.80

IRS Structural & Wiring Provisions 261 00 32 50 8499 00

TOTALS 186.40 43857 60

H. ELECTRICAL LOAD CHANGES

fl Table 2: 115 VAC INSTALLATION

ITEM VA POWER FACTOR BUS CONNECTED

DEU 57.5VA 09 Left 115 VAC Bus

HGS/DEU Cooling 506VA 08 Left 115 VAC Bus

,, . : ! ~ ,., Table 3!'28:VDC 'tNStALLAT!ON . ;,• •• '1 •1, •• r i C ~· .

. ·· .. J'., .{. :- .. ::· lTi:M ·.CURRENT · BUS:CONNECTED

OHU 1.00 Amos 28 VDC Left Main Bus

HGS 5.80Amns 28 VDC Left Essential Bus

IRU 1.96Amos 28 VDC Left Essential Bus

'" 60605-410, Rev 2 Page 5 of 30

--·- _, ••• t --~------...-

Engineeri .. , rtment- · ;.,;;,.;, .. ,,._ ...... ,.;.;.,.. -=-. "" :""F;--~, - ,if+ -~f, -., ,,:&r~~·--

,.

AVIONICS 275 Palmer Koad N.E

Calgary, Alberta T2E 7G4 - ' _, '

---

(403) 250-2644

" I.

INSTALLATION INSTRUCTIONS

STEP WORK STEPS MECH

1 Aircraft Preparation

1 1 Ensure aircraft has dual radio albmeters installed If required, install a second

radio altimeter system in accordance with de Hav1lland Maintenance Manual ~7-i.A chapter 34-42-02 using FD kit 9762-0800-001 pnor to incorporation of this .,V:,

mod1ficat1on

1 2 Ensure aircraft has been retrofitted for dual VIR-33 Navigation Receivers If :t:~ required, incorporate de HavIlland SB 8-34-166 pnor to incorporation of this

mod1ficat1on

1,3 Ensure aircraft has at least a single UNS-1C Flight Management System {<'....il\ installed If required, install FMS pnor to IncorporatIon of this mod1ficat1on 70 ,, 1 4 Remove the cockpit seats and cockpit floor access paneL Perform Fhgtit Deck t~ Preparations in accordance with FD documents 9701-0896 secbon 4 1 and

9701-0897 secbon 4_ 1

Remove Engine and Copilot Instrument Panels Remove all equipment In 1 5 --~j

forward and aft center consoles

1.6 Remove the passenger seats on the nght side of the aircraft forward of FS f~,J<

420_ Remove the passenger seats at FS 593 5 (last row)_ This will provide

soace for the Internal Taraet Board "2--0

1 7 Remove the center aisle and nght side carpeting and floorboards -~

1 8 Remove wardrobe to access avionics terminal strips ¾~ 1 9 Remove extenor front access panels 121AL and 121 BL (Ref MM 6-40-10) ~?-,>

-?O

2 Structural Provisions

2.1 Install the HGS computer tray in accordance with FD document 9701-0902 1,,v,~s, sec 4 Install ground strap In accordance with FD drawing 9762-0730 Note 4

2.2 Perform bonding test on HGS computer ground strap installed in previous

step The bond should have a resistance of equal to or less than 5 mIlhohms p s.

Resistance :?\ _2 ~ m.l\. "''' ft

2,3 Install the IRU shelf in accordance with FD document 9701-0899 section 4 2 /. ·'T~ '-

Install ground strap in accordance with FD drawing 9762-0769 Note 9

24 Perform bonding test on IRU ground strap installed In previous step The bond

should have a resistance of equal to or less than 5 mlihohms

Resistance I .zc m ./\ P.'> ,ail'\

25 Install the DEU provIsIons in accordance with FD document 9701-0902 fi-£v\ section 5

2.6 Dnll a #10 hole In a convenient location on the rear side flange of the DEU ,(.,,--J ~s.

mounting tray and install ground strap to airframe ground d.

27 Perform bonding test on DEU ground strap installed In previous step The

bond should have a resistance of equal to or less than 5 m1lhohms

fs Resistance 1.'lt, m.JL 1c/A

't '":I• -

INSP

~ 44 :ll

~ ;i 44 %.e 44

• t/4 'l! • 44

• -u ~J

U- ~~·i

~ ,. 44

u.e~~.., -~

1/~

ue 44 "'

r/f{!Jn~" /~ ~ • 44 .,.,o~~

C<,- ;r :YJ • 44 ~,· ., -·., '£'-.--,_,._ ~-.,\

u0 ,• 44 ....

60605-41 o_ Rev 2 Page 6 of 30

-STEP WORK STEPS MECH INSP

2.8 If additional center console space Is required to accommodate the three new rJ/ft v~ controls, install center console extension in accordance with de HavIlland SB

8-53-72 or equivalent • •

29 Modify First Officer's Instrument Panel for HGS Annunciators In accordance _,{µ,,<,('39 .

El with FD drawing 9762-0764 sheet 2

2 10 Install the overhead structural modIficat1ons in accordance with FD document 4f.-,ut,81$· '

9701-0896 ~-

2 11 Install the HGS PDU (Pilot Display Unit) In accordance with FD document ~~ -9701-0897

NOTE:

The installation of the PDU requires that the aircraft not be

exposed to sudden wind currents or movement. Do this phase of ,, the installation in a closed hangar while potting POU hardpoints.

The aircraft must not be boarded for 4 hours after potting to allow

for cure. Nonnal maintenance operations may continue after 4

hours of cure time. Interior trim panels must be fitted with LRUs

properly installed for a correct fit. Install and fit interior trim panels

in coniunction with Section 4, Equipment Installation.

3 Wiring Provisions

3 1 Modify the pilot's upper and lower cIrcuIt breaker panels referencing FD f S u.e i 44

drawings 9762-0767 and 9762-0768 Install cIrcuIt breakers in locations "70J,. . "' identified on Western Avionics Wire Diagram 60605-001 and 60605-002 -

32 Prepare IRU Cable Assembly 60605-402-001 for installation and terminate In -~

{,{_ (i44 "•

accordance with Western Avionics Wire Diagram 60605-002 \.i'J... .,.,. ..

33 Prepare MSU Cable Assembly 60605-409-001 for 1nstallat1on and terminate in . Jt~ U[i~"·~.-~

accordance with Western Avionics Wire Diagram 60605-002 ,• 44 \.-., ......

34 Prepare HGS Computer Cable Assembly 60605-403-001 for 1nstallat1on and f--~ •u rt' terminate in accordance with Western Avionics Wire Diagram 60605-001. ·?..J · 44 ·- -

3.5 Install DEU Cable Assembly 60605-404-001 in DEU Tray and terminate In \L-5 Uri 44:,

accordance with Western Avionics Wire Diagram 60605-001 and Appendix B ·?0-z)< \t+n~~

36 Prepare CHU/Combiner Cable Assembly 60605-405-001 for installation and ~ u0 terminate In accordance with Western Avionics Wire Diagram 60605-001 and " "

·-?'v~ .• 44

Append1xC "tolfr.' ..

37 Prepare HCP Cable Assembly 60605-406-001 for installation and terminate in _,;t~ urr~i accordance with Western Avionics Wire Diagram 60605-001 and Appendix C ,,

38 Prepare RASU Cable Assembly 60605-407-001 for installation and terminate (2f a r~r«;i in accordance with Western Avionics Wire Diagram 60605-001 .--7D~ \!'4-ortt."'

39 Install and terminate remaining loose wires from Cable Assembly 60605-408- ~ CL~ 001 in accordance with Western Avionics Wire Diagram 60605-001 ---P~

3 10 Install two new grounding studs adJacent to the combiner and overhead unit in ~-zi,, u..{." .• 44

the upper cockpit structure Refer to Dash-8 MM 20-09-06 .,:7--0 .'\t"'o'-""""'

3 11 Attach a ground strap (MS25038-2BB or equivalent) to each of the new .,;:-~ u. r."' " 1 44

ground studs Refer to notes 22 and 23 of FD drawing 1000-0280 v..:,;,_.,

3 12 Perform a continuity test on all installed wInng Ensure all ground terminations fh u. ........... ~,..0.

" " have good connection to airframe ground .~-:.J,, • 44 "

"-i' ~ ...

-

f)

60605-410, Rev 2 Page 7 of 30

,, - ~- -STEP WORK STEPS MECH INSP

313 Without any LRU's installed, perform a power check on the following systems

by setting the cIrcuIt breakers listed below and checking for proper voltage on x-S-J\ the corresponding pins Open circuit breaker and confirm power Is removed --7-0

Circuit Br<>aker Voltane Pins Checked Bu

3445-P101C !;½ IRU 1 28VDC 21Hl&81L1 ·'? D -:z..,'-. U-

3445-P101C -~~ 7 /H\ & 8 /L\ 0 3445-P101C ~ 10 IHI & 11 IL\

•

3434-P501-C <?'

"' HGS 28VDC 2 IHI & 3 IL\ -7'<>';},

3434-T1 "7~~ 1 /Hl & 5 IL\

3434-P401 ~ A /Hl & B /L\ '2Z>u\

3434-P701 -'7~, 1 /H\ & 2 IL\

3434-P801 .,;~~ 14VDC 1 /H\ & 2 IL\

3434-P201 ~-OHU 28VDC 52 (HI & 24 IL1

-7t)~

3434-P301-C \?<-,-

HGSDEU 115VAC 2 IHI & 4 IL\ < ?-o-:?..},

3434-P350 J~ HGSCOOLING 115VAC E CH\ & BIL\

3434-T1 ~ 7 /H\ & 8 IL\ --vo

3434-P501-A -~~ HGS 26VAC D9 IH\ & E9 IL\

3434-P501-B \>. D9 /HI & E9 IL\ ·7>v~

RAD CONS 5VDC 3445-P201 e~ Panel Lights Lighting S /H\ & T /Ll -Z--"

Dimmer 3434-P401 (2-7 -:J. P /H\ & SIL\ "7 1)

3434-P701 ~J 3(H\&11IL\

f)

60605-410, Rev 2 Page 8 of 30

,--1 ·1 L..>\., ... _ , ,, -STEP WORK STEPS MECH INSP

4 Equipment Installation

4.1 Install the HGS Control Panel 1n the aft pedestal 1n accordance with FD (2$ ?£.

drawmg 1000-0280 /tr 0 0 I 0 ..-z;,-~

P/N /'5&0- I ~9o - Oo ~.f( S/N· 93~¥ "'

42 Install the Combiner Put the combiner on the ahgnment pins on the sill beam U-

pad Tighten the three capbve bolts and torque to 83 ± 5 inch pounds (9 4 ± ~-Jr 0 0 6 Nm) Use a 7/16 inch (11 mm) tool Attach the grounding strap to the ~

combiner with a 10-32 screw and torque the screw to 30 ± 5 inch pounds (3 4 44 •

±0 6 Nm) /vi oO I

PIN. lj?JV- /)$0-()0/ )I S/N: I.J.Sly' ,, 43 Perform bonding test on combmer ground strap installed 10 previous step. The t) bond should have a resistance of equal to or less than 0 005 ohms

I -St> M .I\.

p ·;.

Resistance

~

l -:.14

4.4 Install the Overhead Unit Fully support the OHU on the OHU mounbng U-brackets. Tighten the three captive bolts and torque to 83 ± 5 inch pounds (9.4 !~ ± 0 6 Nm) Use a 7/16 inch (11 mm) tool Attach the grounding strap to the •Alii)

stud adJacent to the aft mounting point with a 10-32 self-locking hex nut ii 44

Torque the nut to 30 ± 5 inch pounds (3 4 ± 0.6 Nm). "'"ofr.."""

NOTE:

The overhead unit must be fully supported until the three bolts are

tightened. Refer to the warning label on the unit.

PIN r5tJo-/J.6v ·tx2.(Tl SIN [:).6 06

45 Perform bonding test on OHU ground strap installed in previous step The t) bond should have a resistance of equal to or less than 0 005 ohms P.5 ~

Resistance· ' . "t 2 TY'> .f\. j DIA -

46 Install RASU adapter plate 1n accordance with FD drawing 9762-0773-201 ~..µ,-:ih

~ 47 Install the RASU in accordance with FD document 9701-0905

~ / l 44

P/N· (S-Oo - ('3_,;0-Oo).. L?- S/N l;:J5'6k ,,~~"i,

4.8 Install the HGS Annunciator Panel 1n the co-pilot's instrument panel location in Ct<- 11-A,i

accordance with FD drawing 9762-0764 sheet 2 ~ i 44

/7(}0- \¾6- 00,-. l 't0;,°1 1'.,,o °' ..,.,,.

PIN SIN·

49 Install the Dnve Electronics Umt 1n its appropnate tray above the wardrobe

!'~ U-0 Make sure that the appropnate coohng system 1s in operation for the DEU ii 44

/500-1330-ooLt I J 'f 5 ;;;_. "'ltolf'."""

P/N· SIN.

410 Install the HGS Computer 1n 1ts tray located below the passenger cabin floor in

~ tL

accordance with FD drawing 1000-0280 Make sure that the appropnate •• cooling system 1s 1n operation

s

i~"'-,:,,

[5"00-{Joo·oo3 ti [;}795 PIN

SIN

60605-410, Rev 2 Page 9 of 30

( 403) 250-2644

STEP WORK STEPS MECH INSP

4 11 Install the IRU on the shelf ~ ~ /:1_ 6 Joo(_ 4 I) o ] 44

~ l_o ~9 I 7 <7-'D --zl,; • P/N S/N

4 12 Install the MSU In the aft pedestal flW{J i ~'__<;,~ ~ P/N C6 /0 lf__) .. A-1!,0 5 SIN OJ-0738/3 /J'D

5 Testing

5 1 Configure FMS 1 ARING Port 6 for "HS429 IRS1" m accordance with the ~L;, U,,.;: 19a

UNS-1C FMS Technical Manual Use the Configuration Module Programming

.,JD~ i' 44

Procedure appropriate to the software version installed m the aircraft Section ~Aro$" ...

5 A, Q, and U for software version 601 xi 701 x are contained In Appendix E

for reference use.

5.2 Perform the IRU/AHRS alignment in accordance with FD document 9701-'?'O~ ~"~i~

0899 section 4 4 or 4 5.

5.3 Complete Installation Checkout Procedure FD Document Number 9851-0723, '2,0 U.1r44 fl section 3, HGS Functional Tests ,.-JV~ ''t•o1t'.,,

54 For certification of first installation on a new aircraft model, complete 1 (r-.c;J\ ,.,/ff~ Installation Checkout Procedure FD Document Number 9851-0723, section 4, CL i144t Electromagnetic Interference (EMI) Tests /J-0 .,4to,;ft_~

NOTE: ~? C/4-0 If Head-Up Guidance System is to be de-activated (to wiring

if • • 44 ~

provisions only), omit the remaining steps and perform Western .-71)~ -t+o°'""'

Avionics Enaineerina Order #60605-411.

55 Perform pre-closing mspecbon and complete Conformity Inspection ~~.p;,j,_ :1! f~:, 56 Close up all affected areas of the aircraft {-~ \l(J\ /l{f! E"r~. Ji: 44 g ,z.,,, C,,!,- .,.,_.., ...

6 Documentation

61 Revise aircraft Weight and Balance to include data m Paragraph G ~\!\ 11/H- ~:it ·~ <b'7v¾. t,(.. • 44 , .

62 Revise aircraft Electrical Load Analysis to include data in Paragraph H ~l!\ zS\- l'/ff' W 44 1 (20'/1! t-L-··~

63 Make appropriate logbook entries and complete Conformity Certificate Form ~~"'~ fVfl~J (TC Form 24-0045, FAA Form 337, or equivalent)

64 Insert Airplane Flight Manual Supplement, FD Document Number 9701-0904, ~~~ ii-t,iJ Rev B or latter approved revIsIon into the aircraft flight manual

65 Insert Maintenance Manual Supplement, FD Document Number 9661-0050, ~Coi.J "'II!"~ 44) Rev 4 or latter approved revIsIon into the aircraft maintenance manual it,(_. .,..,.,0,,., ...

60605-410, Rev 2 Page 10 of 30

1-lu .!644

,, J. APPt~ ,!!,,Ll

fl

The following are attached for reference purposes, as noted in the above report

Appendix A

FD Report # 9762-0660, Rev1s1on C, Section 3 - Requirement

Appendix B

FD Report# 9712-0052. RevIs1on F, Section 5 4 - DEU Connector Installation

Appendix C

FD Report# 9712-0052, RevIs1on F, Secbon 5 5 - OHU and HCP Connector lnstallabon

Appendix D

ASCB Tenminabon

Appendix E

UNS-1C FMS Technical Manual, Report Number 34-60-07, dated July 30, 1996, Section 5A, a, and U,

Configuration Module Programming Procedure

K REFERENCES

1

2

Federal Av1at1on Regulation Advisory Circular, Acceptable Methods, T echmques, and Practices -

Aircraft Inspection and Repair, AC 43.13-1B, dated September 8, 1998

Federal AvIatIon Regulation Advisory Circular, Acceptable Methods, Techniques, and Practices -

Aircraft Alterations, AC 43 13-2A, Change 2, dated 10/30/89.

60605-410, Rev 2 Page 11 of 30

n 60605-4 10, Rev 2

(403) 250-2644

APPENDIX A

FD Report# 9762-0660, Revision C Section 3 - Requirement

Page 12 of 30

"' cl

cj

(4Li3J 250-2644

3. REQUIREMENT

No single failure In the HG$ winng and/or LRUs shall cause a fault or degradation in both the #1 and #2 airplane systems when installed to provide CAT Ill operations.

3.1. Documentation

Airplane wiring and maintenance documentation must show the appropriate wire separation for the HGS wiring as stated In section 4, as well as the appropnate 1mplementat1on as stated In section 5. This separation is applicable over the life of the aircraft while the HGS is operational for CAT Ill operations.

3.2. Separation Definitions

3.2.1. Existing Aircraft Wiring

3.2.2.

3.2.2.1.

Existing aircraft wiring is defined as the winng In the airplane Installed m accordance with production drawings, service bulletins, or engineering orders prior to the HGS installation, or any newly installed wIrtng not associated with the HGS wiring identified below.

HGS Wiring

HGS wiring Is defined as all wiring required to install and connect the HGS components to the existing aircraft systems in accordance with Flight Dynamics HGS wiring documents for CAT Ill operations. This wiring is defined by the following groups.

#1 Sensor Wiring

The #1 sensor wiring are those wires associated with the primary sensor inputs {localizer, glideslope, radio altitude, etc.) to the HGS required for CAT Ill as identified by the Flight Dynamics HGS wiring documents. '

3.2.2.2. #2 Sensor Wiring

The #2 sensor wiring are those wires associated with the secondary sensor inputs (localizer, glideslope, radio altitude, etc.) lo the HGS required for CAT Ill as Ident1fied by the Flight Dynamics HGS wiring documents.

CI 3.2.2.3. #3 Sensor Wiring (when applicable)

3.2.2.4.

The #3 sensor wiring are those wires associated with third source sensor inputs (attitudes, localizer and glideslope) to the HGS required for CAT ill as identified by the Flight Dynamics HGS wiring documents.

Interconnect Wiring

The HGS interconnect wmng are those wires associated with the HGS which provide the interconnect between the HGS LRU's as identified by the Flight Dynamics HGS wirmg documents

Use or disclosure of th,s mformat1on 1s subJect to the restrictmn of the proprietary notice.

DAAWINO/DOCUMENT NUMBEA

9762-0660 1 AEV~ION

FLIGHT DYNAMICS

Flight Dynamics Portland, Oregon I Page8oi 12

A COUJHS.;,(A,ISE" COMPANY

60605-410, Rev 2 Page 13 of 30

"

C

C

,+O'

EXISTING AIRCRAFT WIRING HGS WIRING

' I BLUE TIES

B WMl-4321-22 I OR

WMl-4322-22

A50 -~0---11i- 'o/002-9678-22

-----;,.'-,(>,::-:71- W002-9679-22 I I 'ASI

PRIMARY

"''" SECTION

HGS COMPUTER

, , I

34-22-12111 ::,,,

:112. SPACING

1 OR SLEEVING

YELLOW TIES

NUMBERS ARE FOR ILLUSTRATION ONLY

Figure 1

A I-<>----<

SLE£V'ING

Signal Separation Example #1

PRIMA.RY INP\JT

HGS COMPUTER

SECOt-0.l.RY INPUT

-----------------------i--------------------112 • OR SLEEVING

/" ' "'--~ EXISTING A/C WIRING v"

Figure 2

Signal Separation Example #2

f1 SENSORS

HGS LRU 5

Use or disclosure of th,s mformat,on 1s subJect to the restnct1on of the proprietary notice.

FLIGHT DYNAMICS .\ COlU"'S-IC.\/SEII COl>IP.\IIY

60605-410, Rev 2

Flight Dynamics Portland, Oregon

DRAWlNCIOOCUMENT NUMBER

9762-0660

REVISION

C

Page 11 of 12

Page 14 of 30

I)

60605-410, Rev 2

APPENDIX B

FD Report# 9712-0052, Revision F

Section 5.4 - DEU Connector Installation

Page 15 of 30

() 5.4. DEU Connector Installation

The DEU has a specially designed EMI connector backshell Care must be taken to maintain the

EMI protection This procedure shows how to assemble the DEU connector

Observe that the DEU Cable connector 1s already partially wired

STEP ACTION

1 The DEU backshell connector has a two-piece connector case, screws and washers, and

associated hardware Make sure that all items are available

2 Identify all wires that will be going into the backshell and connector. Stnp off the insulation

to expose wiring and shielding for the first 1 75 inches of wire ,

3 Pin all the wires for the connector as shown by the wmng diagrams.

4 Each maJor wire cluster for the openings of the backshell should be apparent after

pinning Roll back the shielding for each wire to the outside of the respective bundle

5. In preparabon for assembly of the other half of the backshell, loosely tie wrap the shields

against the main cable bundle This will give a clear area for the backshell connectors to

mate together

6 Arrange the cables into three maier groups Assemble the two connector EMI backshell

halves with the four screws and washers over these groups, routing the appropriate

bundle into the correct flange

Rubber Gasket

• :) • . "'-"'-

60605-410, Rev 2 Page 16 of 30

•

•

7.

(403) e26 )

Attach the L J connector to the backshells with the four screws and washers. Slide three wire bundle overbra1ds onto the three flanges at the back of the backshell and . secure the overbra1ds with the three hose clamps as was done on the HGS computer connector

8 Attach the connector and backshell to the mount tray with the four connector mount screws If conductive epoxy was used for the EMI gasket, wait at least 3 hours before doing this to allow the epoxy to cure The connector installation 1s now complete .

60605-410, Rev 2 Page 17 of 30

\- j, _.)l - ....

,

I)

"'

APPENDIXC

,...., FD Report# 9712-0052, Revision F

Section 5.5 - OHU and HCP Connector Installation

Iii\

,....,

60605-410, Rev 2 Page 18 of 30

ns.s. OHU and HCP EMI Connector Installation

,,

"

· The OHU and HCP EMI connection 1s an integral part of the connector backshe/1 This procedure defines

how the EMI shielding 1s to be applies to this connector

STEP ACTION

1 Shde the EMI backshell components (Figure C-1) over the cable bundle Stnp off approximately

1 5 inches of wire insulation to expose the sh1eld1ng of each wire

2 Roll the shielding back as was done on the previous HGS computer and DEU connectors to clear

the shields away from the ends of the wires Pin each appropriate wire and insert into the

connector as shown by the w1nng diagram.

LARGE RF\ RING

SLEEVE /

CABLE CLAMP

WIRE SEAL RING

CONNECTOR

SMALL RF\ RING

Figure C-1 EMI Backshe/1 Assembly

3 Set the wire seal nng on the rear face of the connector Secure 1t with the sleeve

60605-410, Rev 2

SLEEVE SMALL RFI RING

-LA~CE RFI

RING

OVERALL SYIELO

Figure C-2 EMI RFI Ring

Page 19 of 30

() 4

5

6

" 7

Put the shield of each individually shielded wire and wire pair Ins1de the small EMI ring. t--old the

shields back over the nng

The overall braid used to cover the wire Is too large to fit inside the connector, therefore install a

small section of EMI shielding tape (PIN 9300-0875-001) from end of backshell forward to the

sleeve Ensure there are at three layers of shielding tape used

Put the cable EMI shielding tape inside the large EMI nng Fold the shielding tape back over the

nng.

SLEEVE

SMALL RF1 RING

LARGE RF! RING

OVER.r.ll SHIELD

Figure C-3 Securing EMI Shields

Thread the cable clamp onto the sleeve Make sure that the shielding tape ends appear at the

rear of the cable clamp.

8 Tnm the excess shielding tape as needed Attach the strain relief to the cable clamp Ensure the

overall braid ends Just outside the cable clamp

60605-410, Rev 2 Page 20 of 30

y ·- -

•

-APPENDIXD

ASCB Termination

•

• -" ··---Pagei1 of30

f)

•

A.

B.

(403) 250-L644

Wiring Practices

In order to ensure proper functioning and operations of the dIgItal data network It Is essential that the general guidelines hsted below are followed at all times dunng the fabrication and assembly of the electrical wiring harness 1 All stub lead terminations shall be made using 22 guage PTFE (Teflon) msulabon wire as

follows.

• MIL-W-16878/4-22-9 (White) for white cable wire

• MIL-W-16878/4-22-2 (Red) for brown cable wire

2 Match the length of stub leads to within ± 0 02 inches at all termInatIons 3 The maximum length of unshielded wire ends at each termination shall not exceed 3 inches 4 The ASCB transmIssIon Imes shall be connected In a daisy chqm fashion between user sub

systems 5 The cable length between users shall not be less than 24 mches'and In order to facilitate

repair or rework of the wiring harness, It is recommended that a minimum of 6 inches excess length be provided between each sub-system

6 All data bus winng shall run separately from general avionic and electrical cables

Connector/ Feed Through Termination

Connector and Feed Through terminations are typically used to interconnect individual cable assemblies In the winng harness 1 Refer to Figure D-1 for a general descnptIon of the typical wmng diagram schematic.

I

/3

14

II' I

'I

/£24 ----2£24

Figure D-1 WInng Diagram Schematic

60605-410, Rev 2 Page 22 of 30

()

C.

2

(403) 250-2644

Refer to FIg1 , ~ D-2 for a general descnption of the assembled termination and

recommended sequence of assembly

1-4----- 3" max -----,

-~It-- Max difference m lead length= 0 2"

Stub leads M83519/l-2 Solder Sleeve

M22759/34-22-9 Max length= 6"

~OTE

0

End of Slueld

M83519/l-3 Solder Sleeve

= Recommended sequence of assembl)'

Figure D-2 General Assembly Arrangement

Sub-System Termination

Sub-system terminations are used to interconnect individual components In the AFCS In a daisy

chain fashion

1. Refer to Figure D-3 for a general descnption of the typical winng diagram schematic

2

Figure D-3 Wiring Diagram Schematic

60605-410, Rev 2 Page 23 of 30

fl

n

2

3

Refer to Figure D-4 for a general description of the assembled termination and

recommended sequence of assembly

Stub Leads

3" max

difference m lead h=02"

M83519/l-2 Solder Sleeve

End of Shields

NOTE

--

NAS 1744-4 Solder Sleeve

Q = Recommended Sequence of Assembl)'

Figure D-4 General Assembly Arrangement

/

60605-410, Rev 2 Page 24 of 30

60605-410, Rev 2

{' ,) ,.,0-2644

APPENDIX E

UNS-1C FMS Technical Manual

Section 5A, Q, and U


Page 25 of 30

INVSlSAL"AVIONICS SYSTEMS CORPORATION

UNS-1 C FUGHT MANAGEMENT SYSTEM TECHNICAL MANUAL

{601.X} {701.X}

5. Configuration Module Programming Procedures {601.X} {701.X}

Refer to Description and Operation for general information about use of the UNS-IC FMS That section

introduces the hne select keys, keyboard, and display features

On multiple UNS-IC 1nsta1lat1ons, the following procedures must be repeated for each UNS-IC Program the

Configuration Module as follows:

A. Starting the UNS-1C FMS

With power applied to the aircraft, press [ON/OFF DIM] key on the umt After about a,five second wann-up,

self test will begin with the self test page displayed and test will proceed The display will look hke tlus dunng

the database portion of the self test.

UNS - 1C

AJICIAFT IDENTIFICATION

E3 CPU PASS E3 RAM PASS

E3 DATABASE E3 E3 E3

E3---------~E3

If the self tests detect a fault precluding use of the system, then this page wdl identify the failed test. In this

case refer to Maintenance. Checkout. and Troubleshooting.

If the self-tests detect no faults precludmg use of the system, then the COPYRIG!IT page will appear bnefly

followed by the tniualization page (INIT 1/1)

Push [SL) to Initialize the UNS-1C. The posrt10n, date, and time do not matter.

60605-410. Rev 2

POS !NIT t / I IIMSG

B IN1T1Al ,o, DATE 31-MAY-91

ID 8 N 32 07, I

W 110 66.4

UTC 14,41

E3 ITANDAID/EXTENDED NAY DATAIAIE IXPIIII

8 U-JUN-98 PEIF DI -------

B.,__:,~~::,AC::,C:;;E:,:P_;T~F_;;M_;;C_;_YE:.•;;__.:.B.:,0..:,1_.::,0 <./~

Push [MSG] to display the message(s). Push [MSG] or RETURN [SR] to return to the lmt1alizat1on page

Push [1 RJ to highlight the DATE field Push [4) [SJ (6) [7J [8) (9) and then push [ENTER]

34-60-07 Page 475 July 30, 1996

Page 26 of 30

3.4.1 Inertial Reference Umt (IRU)/ ~7-7<:,z....\, Attitude Heading Reference System (AHRS)

3.4.2 Flight Management System (FMS) ~ 7-oi.JI.

3 4.3 Automatic Fhght Control System (AFCS) \-7 --J.t?}

3.4.4 Nav1gat1on (NA V) ~'7-cti\

~ 1 ,;; n~.;·•,,1 _!\. , .. ~"~:1 C-:im;-1_•1 cr l\lo l :1..,d "!,:. ~ ~0 A._'!:JC~ 0 7-u ::-..'\

3 4.6 Electromc Fhght Instrument System (EFIS) (Aircraft 0 //0,__.'\ Config. Dependant)

3.4.7 Remote Airspeed Select Umt (RASU) I..½ ).--c '.:?...j'<

3.4 8 Instrument Remote Controller (!RC) e__,:,, ·ro-z..,\.

349 Radio Altimeter No. I and No.2 (RAD ALT) \'2.f;, z.,., 2 .. ),

3.4.10 Flap Position (FLAP POS) ~ "7'.-o::.....l>..

3.4.11 Discretes (DISCRETES) ~:A.>0

3.4.12 Global Positioning System ( GPS) \:.£.. ,"°'t--_]\

3.5 Flight Compartment Lights t...__s-=-:..A-

3 6 Captam 's Speaker (24.-z..<>-:zj\,

3.7 IRS Shutdown ~-=-,_A

EM!DATA(FormB3)

~:The EM I tests are necessary to be done on the ~ \i"" r first installation aircraft of each model.

/1.,A.:-z),.

•-i_.lffl-: All da'.:l'eets co111p~ete

, 1:g.. ~-

" t " \111rk,

.. ' _,

NOTE:AJI data sheets and . eek.lists are to be kept as ~.

a part of the aircraft'records.

A/CS/N:

.. -- _f'~_,;....... ___ ·--Revision 0

4.7 Navigation No se1ecteo course ~\t< @7-ve::.i changes

No LOC changes - I-if~ ~?,.,_,\ No G/S changes r.._\ I !>.c f:--;':,7,-, ~

4.8 Distance Measuring Equipment No distance changes N\~ ~..,:

- 4.9 Automatic Direction Fmding No pomter changes ~;:"). f...S.it21 '1- IU r-\Ul0p11Ul No control column or I"\). \~c2-:

wheel movements

4 11 Ground Proximity Warnmg No HGS changes l'-1 i ~ - I

System ~<,}.,

4. 12 VHF Commun1cat10ns No HGS changes ~It.. '"½ ' µ <-"L~""'

Pilot's & First Officer's No audio mterference "' l,t,_ ~di

Freq.

4 13 Windshield Wipers and No HGS changes ~lA f.S z.;,·zl

Windshield Anti-Ice

4.14 External Lights No HGS changes t!)L -\ 'i,:'.?,.,zc·L1

4 15 Flight Compartment Lights No HGS changes NI,:\ eh ,·<-z\

4 16 Aircraft Generator Power No HGS changes t--i l -l\ (2h ,...-,l il

NoHGSmode ti\;',, p'7ytJ2 changes

4.17 IRS Shutdown None l'J lr\ ~ '7,..v2.J

• , t'l"------Ma-y-2,-2-0_0_1 __ _ ------------- Page_BL ..

Rev1s1on D

---------------

••• $4 ~ . -:;_·;;.; [.:"" --,

·n ,,\;J,.. ..fic"15' . -----·~ ...... -_" 4,,

fi\i.,f,)~ ~·- - ._,. -• ~- ,

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_, -:~ ~;-- -:..:-'' ~ '

,-_ . 'j -

: c ·,~4t,:;:;: - ... -~:, • .,, ~9 't' -~ .

SERIAL NllMBER

HGSL PART NUMBER MOD t }fi-~-~

Computer·,· · ' \9)0 - \;co- Cu3, \.!i \~ 2-

Control Panel 15)0- (-Z., 'lC - (/Cf~ \ '2,7,16~· l ' Overhead Unit (7{)0-l'2.f:O- 00\ -J\ l 7--wf, > -

Combiner j;"QQ- \z_;x)-'90 \\-\, \'2-6\~ ~ • DEU J 5CC - l-i, 7,(1- t:C \\;:. \ "2.-~-:Z- l\-' RASU ) SlX)- \ >ffeJ- On1.--~ \ 2-S~(, -?,-Annunciator Panel 1t;uO - \. ¼o- ocZ.. ,~o~, '?-

•

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··-·---Ma-y-2-,2-00_1 ____ _ ---- -----=---------- £age.BJ. Rev1s1on D --------- ___ ., ____ ... -'-...

{Jj JAR-145 MOT-No 1-01, FAR-AUXY103F Austrian Airlines, Oesterre1chs91e Luftverkehrs AG

0 JAR-145 MOT-No 1-30 Tyrolean Airways - Tiroler-Luftfahrt GmbH Workorder Rev 0

1111 111111111111111 II Ill 1rcraft/ J Cust.:

1 iJ A32

LTf

L B77 U CRJ 0 OHS [l ER4 CJ F70

Maintenance Workorder 03069209

r::; MOS Date Issued by ATA 3069209 0 A33 0 A34 D B73 [1 B76

P/N

1'3RD I

cj COMP ~ /, '1, Ill(

I Flt No

ID Vf,er 1 )4 --1Fr~;- ~of --

1 i Sin If.//./

Mam! C Sched

Statistics ,- -----------

~ Struct Damage ~ Insurance -------- [lCanm ' Proiect: S / N LJ Tech lrreg LJ Warranty

MEL Ref MEL Interval I I- ' HIL , n Flt Deck Info ' [ • Cabin Info 1-:J soc Clssslftcation

- -- -- -- -T -- -- -- -+ - ______ __L ____ -- - -

~ ~ @12,i; I '._' F B req __ _ i ~ AOG Risk _ __I OR AB/TB/BS/GR/HU~LS/RTR/0 ___ _

OPS Re ortin Text any avaUable Fault Codes, Messages, Observations either in Descnpbon- or Action Text ~='--='==--'-='-==-"===-======-===:::__::::_:_::::=_:_:::-'_ ____________ _

- _ __Q_ifJ.L +"'-ded. _b1,r-1'-J _jj_(;._s_ _,:,,,._J_f:_-<IL,,.f_,:s.'--· __________________ _ _ L,.._k/L ru:__.,,_(Jffl/ _.,_,.L _L£7'k.±L _L:__- _u_(_::_1_ ~ 'Jl.{-.2_g_2_, -- -- - -- -- - - - -- - -

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Area Date ID

• _j~5G"...,.U.':!> __ ,\,tc,5,, O:tl ,,J . _S~' _ II tl._'l- __ ~C..C..· _ _ __ _

~ ~--> ~'-I I ~1-~ "-'" L_ __ - -- ---- -- -+---+---+-- -- --- -- -- -- - -- -- -------1---J ___ , - -- -

L. __ ?,_.1;;,,,c.;.,.,.._,__,.,o=-._,,li,.,.,.__ ~ .. s "f\,1,-)t., -;-1 ~..., "''- 'i'E,Si' .. u.:.. . - cf:=. - -i- I

':l).:)c- ft: _j'iS t--_ .. ~t.~ t-_f/..li,_y_,_ ~-t--1~~"?-H_ 1-. _____

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r-=--_-_~-------- ______________ -------1---t---i--- -- ~-=-I I I

---,,£-- - -- - -- ----- -- -------4---------l--- +- -- --- -------- -- -- --:-- --t-- :-- - - - -

-----------1___[_ ________ - -- --t : ---------- --1-- - ---- -- -- -- - I .---t-- ----

I

----1--- -- ---- - 1-- - ------r---------1------- +- -

Sign

[] PIG for MEL Dispatch

I ,-- --,------- --_ _ j_ ____ _ ------ --

L-

I This aircraft or airframe tdenblied above was repaired and inspected in accordance wrth current Regulations of the Federal Av1at1on Admm1strat1on and 1s approved for return to service

_ The undersigned for the Austnan Airlines FAR 145 Approved Repair Station, Certtficale Number AUXY 103F at Austnan Alrtmes Technical Base A-1300 Vienna Airport, Austna, Europe

/

•

-•

•

iyrolean

Engineering Order: 8-3/34/287 Subject: Head-up guidance system, Flight Dynamics model 2800,

system activation, STC ST00129SE, ACG.21NE.046 TYROLEAN AIRWAYS, Tiroler Luftfahrt GmbH, Furstenweg 190, A-6020 Innsbruck

WEIGHT & BALANCE CHANGES

Item

Description In Out

LRU's:

X HGS computer

X Overhead unit

X Drive electronics unit

X HGS combiner

X HGS control panel

X Rem. airspeed select unit

X Mode annunciator panel

X Inertial reference unit

X Mode selector unit

X RASU panel assy

Misc:

X Blanking plates

Totals

Total Weight & Balance Change

Remarks· Weight [lbs] Arm (inches] Moment [lbin/1000]

TE-ProJect number. 990072 Rev 0, 14-01-2003

DHC-8/300 We1ciht Chancie

Removed (-l Weiciht Arm Moment Weiciht

26 0

- ~7.0/

80

60

30

30

1.0

17.1

1.0

Negl

Negl

0 0 0 92.1 =:> 0

92.1

- 21.0

~AL (;>-I

(w !THov7 OHV.)

Form 2016

Added(+ Arm Moment

414.5 10 78

93.0 ,/ 2.51 ~ 1J 136.0 1.09

75.2 0.45

960 0.29

96.0 0.29

492 0.05

284.0 4.86

96.0 0.10

221 28 2042 0 0 221.71 20.42

- ~-S-1

,<1'.12 I "'.)._ 'l I

Page6 of6

.;

·..!

· ·• SENDcBERICHT •• ·

DRUCKZE IT 03 . 05 . '04 22 : 36 I D : TYROLEAN TECHN I K

TI MER=--: --

DAT . START MODE Nr . ZEIT 883 03.05 22:35 S

FcHLERH . SEITE=

iyrolean technik

INNOCPVO

Attn.: Hr. Wieser

Fax No: 0512 - 2222 9010

From: INNTPVO / ... .. .

PARTNER

22229010

SPEI CH $/E GES. CODE SEITE SE!TE ZEIT

1 l / 0 00 ·29·• OK-F

TY R OLEAN AlRWAYS Tiroler LufIfahrI • GmbH ,echr.ical Department

Furstenweg 190, A-6026 Innsbruck. AUSTR IA Phone: .,.43 (0 )5 12 / 22 22 • o·

Fax: +43 (0 )512 / 28 01 o~

Rei. No.: --------Date:

Pages: 1

E-Mail: Exi. 1811

; _ -;::::;;•.,,:;: - :=;;;111 ic _ _ ,::r _ _ _ _ . _c_,__:-,i:: - -- ---------- --------- --- - - -==---=-----a:=-=:s;===-c: If ourfax is illegible or if you do not receive all of the pages please call: ~43 (0)512/22 22-1811

_f:.Jbjact: W eigth & Balance Changes 0ash 8 :,

Ple.ise be advicsd on following ·weight & Balance Changes·:

A ircraft : LT?, h . ;, Scheduled tor: t).3/ OS/0((

Reference Description

- -·-··-··---------- - ---- -----

Weigth Arm (Lbs) (Inch)

Moment (Lbs"'ln/1000)

.li_£"( __ _

- ------ - - - --- ------- -------- ---- ------- - ---- ·- ·- ·

------- - --- ---- - - --- ~- ---------- --- -- --

- - -·------- · - - ··-- ·- --- ·--, -- ----- -- - ·

- -- ---·- - - ----- ~- - -

··- ---- --- - -- - ----- -- - - ----- - - - - -- --- ·-· - ····------ ------- -- ------ ---------- ·- - ··-- ·- · - ·- --- -

·- :1111,= --- --------------- - -------- --- - - - - - --- =:a--··-- - •==r=-- ----=- -.;.=:= ===:;=:--- -:s,:a";::: _ _ _ .. ·- · H1nwei~· 1. Nicl'lt angctuhrt;, ooer "lchi durchgetuhrte Andtirungen eintr~oen !l2w austr~1cnen. - ---· 2. Uberschrif t mil 3·Lanercod;,. Uriters~hnlt. Flouzeugkannze,~ngn, Datum uM MAR Numm~, erQanzi;,n 3. Fax abschicken 4. Die Faxbastiitigu,,g d9r MWO oder dljm Aft1~11stlericn1 oe,t,;.gsn.

re )lcM / 1.sa 10IR2I010600

·-t

RCFD 9851-0723 Installation Checkout Procedure HGS® Model 2800

3 HGS Functional Tests The HGS functional tests make sure that each HGS LRU works correctly.

Rockwell Collins

Fli ht D namics

Do these tests from the flight compartment after the HGS LRU's are properly connected and all required power is applied. See Appendix A for specific data and procedures associated with the HGS test functions for the sensor displays, fault recording and fault reporting. The results arc recorded on Form B-2 in Appendix B.

The functional tests are arranged in the order that follows:

Table 1 HGS Functional Tests

Step Number Step Title

3. 1 HGS Test Setup

3.2 HGS System Test

3.3 HGS LRU Tests

3.3. 1 HGS Computer, DEU, OHU and Combiner

3.3.2 HGS Control Panel (HCP)

3.3.3 HGS Remote Airspeed Select Unit (RASU)

3.3.4 HGS Annunciator Panel

3.4 HGS Sensor Input Tests

3.4.1 inertial Reference Unit (JRU)/ Attitude Heading Reference System (AHRS)

3.4.2 Flight Management System (FMS)

3.4.3 Automatic Flight Control System (AFCS)

3.4.4 Navigation (NA V)

3.4 .5 Digital Air Data Computer No. I and No.2 (DADC)

3.4.6 Electronic Flight Instrument System (EFIS) (Aircraft Config. Dependant)

3.4.7 Remote Airspeed Select Unit (RASU)

3.4.8 Instrument Remote Controller (IRC)

3.4.9 Radio Altimeter No. I and No.2 (RAD ALT)

3.4.10 Flap Position (FLAP POS)

3.4. 11 Discretes (DISCRETES)

3.4. 12 Global Posit ioning System (GPS)

3.5 Flight Compartment Lights

3.6 Captain 's Speaker

3.7 JRS Shutdown

May 2, 2001 Page 3

Revision D

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Fli ht D nam1cs

32 . HGSS t ,ys em T est Test Step Test Procedure

r v Make sure step 3 I 1s completed.

2 Push the HCP TEST pushbutton

__,,,/ NOTE: All HGS Built-in-Test functions are done in the first 3-4 seconds of the system test.

NOTE: HCP STBY display shows a fault code if one or more faults are logged.

3

~ Push the HCP TEST pushbutton agam.

May 2, 2001

Desired Results

HCP TEST pushbutton hght comes on.

HCP MODE display lme shows TEST.

HCP FAULT hght comes on for the first 3-4 seconds of the test and then off.

HGS ANNUNCIATOR Panel Lights -(First Officer Instrument Panel) Red hght comes on (APCH WRN). Green hghts on as red hght goes out (AIJI and FLARE) Green hghts (2) stay on durmg test selection.

Combiner shows the HGS TEST MENU.

HCP TEST pushbutton hght goes off.

HCP FAULT hght comes on momentarily then goes off.

HGS ANNUNCIATOR Panel Lights -Red hght comes back on, then all red and green h ghts go off.

Normal HCP and Combmer displays return.

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Rev1s1on D

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Fli ht D nam1cs

3.3.1 HGS Com uter, DEU, OHU and Combmer (contmued)

T St est ep T p est d roce ure

_)--- Remove the Combiner ambient light sensor cover.

J,- Stow the Combiner

JD Extend the Combmer.

V""'l I Push the HCP TEST pushbutton.

i./12 Push the HCP mode switch until:

13 Carefully push and pull the Combiner lens i...------ frame area until:

3.3.2 HGS Control Panel (HCP)

Test Step Test Procedure

I Push and hold the HCP TEST pushbutton for

v-- a mm1mum of 4 seconds to start the HCP DISPLAY TEST

NOTE: The HCP ELV light is on at the same time the HCP ELY display line is on.

NOTE: The HCP G/S pushbutton light, FAULT light, CLR pushbutton light and TEST pushbutton lights are on when the HCP G/S display line is on.

NOTE: The four step test cycle repeats until the HCP TEST pushbutton is pushed again.

,__;;.-- Push the HCP TEST pushbutton.

3 Cover the HCP ambient hght sensor (see Figure 2).

I...---" NOTE: HCP display area mtensity

change also depends on ambient light conditions, and the change may he very slight.

May 2, 2001

D . dR es1re esu ts

Combiner display mtenstty mcreases.

HCP STBY display !me shows fault code CMBBI

Combiner shows the HGS TEST DISPLAY agam

Combmer shows the pnor mode m use.

HCP MODE display hne shows VMC.

Combiner shows ALIGN HUD mtermlltently with Combmer movement. When the Combmer is m the correct position, the ALIGN HUD message does not show.

Desired Results

HCP MODE display !me comes on for 2 seconds, then goes off.

Next, HCP STBY display !me comes on for 2 seconds, then goes off.

Next, HCP EL V display line comes on for 2 seconds, then goes off. The EL V pushbutton light comes on for 2 seconds.

Next, HCP G/S display hne comes on for 2 seconds, then goes off. The G/S pushbutton light, FAULT light, CLR pushbutton light, and TEST pushbutton hght all come on for 2 seconds.

Combiner shows the pnor mode is use

HCP display area intensity decreases

Page 7

Rev1s1on D


Rockwell Z:eH:¼intt"t

3.3.2 HGS Control Panel (HCP) (contmued)

Test Step

12 .,_/

Test Procedure

Use the HCP keypad to enter a new reference glideslope angle.

Push the HCP MODE pushbutton

Tum the center panel hght control on the overhead panel.

Fli ht D nam1cs

Desired Results

HCP G/S lme shows each entry as It is made

HCP G/S Imes shows the new G/S value, the HCP MODE lme changes to the mode shown on left side of the STBY line and the Combiner changes to the new mode.

The HCP hghtplate hght mtens1ty changes as the control is turned

3.3.3 HGS Remote Airsoeed Select Unit (RASU)


Push the HCP TEST pushbutton.

-- 2 Push the HCP DIM - pushbutton untli:

1,/"3 Push the HCP ENTER pushbutton.

4 Push the HCP DIM - pushbutton untli: -...,..,,-

...__../2 Push the HCP ENTER pushbutton

6 Compare the RASU selected airspeed value ../ with the SEL A/S data line displayed value.

7 Tum the RASU selected airspeed knob

v ..., 8 Push the HCP TEST pushbutton.

/ Tum the center panel hght control on the overhead panel.

3.3 4 HGS Annunciator Panel . Test Step Test Procedure

I,./'"] Set the CAUT/ADVSY hghts BRT/DlM switch to BRT and release the switch.

2 Set the CAUT/ADVSY lights test switch to \....,,-"'" the ADVSY position.

..--, Set the CAUT/ADVSY hghts BRT/DIM switch to DIM and release the switch.

J Release the CAUT/ADVSY lights test switch

May 2, 2001

Desired Results

HCP TEST pushbutton h ght comes on Combiner shows the HGS TEST MENU

The Combiner caret symbol 1s on the same !me as the SENSOR DAT Ahne

Combiner shows the SENSOR MENU page.

On the Combiner SENSOR DAT A page RASU 1s selected.

Combiner shows the RASU DAT A page

Combiner and RASU values are the same.

Combiner value changes as the RASU selected airspeed number changes

Cornbmer shows the prior mode m use .

lntens1ty of the RASU display and panel lamps change as the control is turned.

Desired Results

Instrument panel caution hghts come on bnght

The three HGS annunciator panel hghts come on.

The three HGS annunciator panel hghts dim.

The three HGS annunciator panel lights go off

Page 9

Revision D

, RCFD 9051-0723 Installation Checkout Procedure HGS® Model 2800

Rockwell r.:,11,;~;~g,

Fli ht D namics

3.4.3 Automatic Flight Control System (AFCS)

WARNING: ENGAGEMENT OF THE AFCS MAY CAUSE CONTROL SURFACE AND CONTROL COLUMN MOVEMENT. KEEP ALL PERSONNEL AND EQUIPMENT CLEAR OF THE CONTROL SURFACES AND CONTROL COLUMNS TO PREVENT PERSONAL INJURY.


\/1 Push the HCP DIM - pushbutton until

2 Push the HCP ENTER pushbutton.

-----..,./) Push the HCP DIM - pushbutton until:

4 Open the two WOW SYS I and the two ._,..--WOW SYS 2 circuit breakers.

......-:5 Release the pedestal-mounted gust lock .

6 Push the flight guidance controller AP

----- pushbutton.

J Push the Captam's or First Officer's advisory display panel R AFCS pushbutton.

J-- Push the Captam's or F1Tst Officer's control column A/P disconnect switch.

~ Close the two WOW SYS I and the two WOW SYS 2 circuit breakers

l/10 Engage the pedestal-mounted gust lock.

(../f'l Push the HCP CLR pushbutton

May 2, 2001

Desired Results

The Combiner caret symbol is on AFCS hne.

Combiner shows the AFCS DAT A page (see Appendix A).

Combmer shows the AP STATUS data !me.

The flight guidance controller AP left light comes on.

Combiner column I AP STATUS data !me changes from OFF to ON.

The tlight guidance controller AP left light goes off and the AP nght hght comes on.

Combmer column I AP STATUS data !me changes from ON to OFF and column 2 AP STATUS data hne changes from OFF to ON

The autopilot system disengages.

The flight gmdance controller AP right hght goes out.

Combmer column 2 AP STATUS data line changes from ON to OFF.

Combmer shows the SENSOR MENU page

Page 11

Rev1s1on D

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, RCFD ~951-0723 Installation Checkout Procedure HGS® Model 2800

Fli ht D mimics

3.4.4 Navi,wtion (NAY) (continue)

Test Step Test Procedure Desired Results 13 On the Captam's aud,o panel, push the MKR ~ control.

14 On the center console, set the MARKER ,._/ SENS No I switch to HI

'--9 Set the 40 IL near the marker beacon antenna.

16 Setthe401L MODE switch to MKR XTL Captain's outer marker (OM) (blue color) .__....,., and the tone select switch to the 400 light comes on and the Combiner column I position. OUTER MKR data ]me changes from OFF to

ON

17 Set the 401 L tone select switch to the 1300 Captam's middle marker (MM) (amber color) (._..,--" position. hght comes on and the Combiner column I

MIDDLE MKR data ]me changes from OFF to ON.

18 Set the 4011. tone select switch to the 3000 Captain's mner marker (IM) (white color) ~ position. hght comes on and the Combmer column I

INNER MKR data line changes from OFF to ON

' 12... Push the HCP CLR pushbutton. Combmer shows the SENSOR MENU page.

3.4.5 Di11ital Air Data Comuuter No.I and No. 2(0 AD C ) Test Step Test Procedure

\,.),-"'" Push the HCP DIM - pushbutton until:

~ Push the HCP ENTER pushbutton.

'--3--"' Compare the Captam's barometric altimeter to the Combmer column I BARO ALT data lme.

~- On the Captain's barometnc all!meter, tum the BARO set knob

~ Repeat above steps 3 and 4 with the First Officer's ADC system and Combmer column 2.

May 2. 2001

Desired Results

The Combiner caret symbol 1s on the DADC lme

Combmer shows the DADC DATA page(see Appendix A).

Captam' s barometnc altimeter and Combmer column I BARO ALT numbers are the same ±30 feet. -Li-t. Captam 's barometric altimeter and Combiner column I BARO ALT numbers are the same ±30 feet. - 'Z.St. . First Officer's ADC system operates the same as the Captam's system.

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Page 13 Rev1s1on 0

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, RCFD 9351-0723 lnstallat1on Checkout Procedure HGS® Model 2800

Rockwell Ci!:t;;J,ns:

3.4.8

Test Step

\..,./1

\.,/ 2

.___..,,-3 ........-4

3.4 9

Test Step

.__,..)

1....--"2

~

4 \....---

L,..-5-

May 2, 2001

Fli ht D namics

Instrument Remote Controller (IRC)

Test Procedure Desired Results

Push the HCP DIM - pushbutton until: The Combmer caret symbol 1s on the !RC lme.

Push the HCP ENTER pushbutton. Combiner <hows the lRC DATA page (see Appendix A),

On the Combmer, look at the two data Imes Combmer shows the two lines VAL.

Push the HCP CLR pushbutton Combmer shows the SENSOR MENU page,

Radio Altimeter No 1 and No 2 (RAD ALT) . Test Procedure

Push the HCP DIM - pushbutton until:

Push the HCP ENTER pushbutton

On the No. I Radio Altimeter umt, tum the zero adjust control

NOTE: Set the No.1 and No.2 radio altimeters zero indications as close as possible to the same value.

On the No.2 Radm Altimeter umt, turn the zero adjust control,

NOTE: Set the No.1 and No.2 radio altimeter's zero indications as close as possible to the same value.

Push the HCP CLR pushbutton.

Desired Results

The Combmer caret symbol ,s on the RAD ALT !me .

Combiner shows the RAD ALT DAT A page (see Appendix A)

Combiner RAD ALT DAT A page column I RAD ALT data !me value reads as close to zero as possible.

Combmer RAD ALT DATA page column I RAD ALT data !me shows 00 ±5 feet and VAL. 'T 2-ft Combmer RAD ALT DAT A page column 2 RAD ALT data line value reads as close to zero as poss1ble.

Combmer RAD ALT DAT A page column 2 RAD ALT data line shows 00 ±5 feet and VAL. r1, fL Combiner shows the SENSOR MENU page.

Page 15

Revision 0

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RCFD 9$51-0723 Installation Checkout Procedure HGS® Model 2800

Rockwell .tt?~!f;rus

35 . Fr htC l!!I t ompar men t L" ht 1g s Test Step Test Procedure

J- Tum the Captain's map hght knob.

.._,_>- Set the DOME hght switch to ON .

36 . C t . ' S ap a1n s ,pea k er Test Step Test Procedure

J-' Select a local tower or ATIS frequency on #I VHF COMM radto and select the VHF-I mike and audio on the Captain's audio control panel.

3.7 IRS Shutdown Test Step Test Procedure

I When the IRS 1s no longer needed, turn I..._.,.-- the MSU switch to the OFF pos1t10n

before the aircraft power 1s removed.

May 2, 2001

Fli ht D nam1cs

Desired Results

The Captain's map hght intensity changes as the knob 1s turned

The Captain's dome light comes on.

Desired Results

Make sure the Captain's speaker ts clear with enough volume and the speaker mutes when Captain's mike 1s keyed.

Desired Results

The MSU ALIGN light is off before the aircraft power 1s removed.

Page 17

Rev1s1on D

I. Approving National Aviation 2 -3. Form Tracking Number:

Authority/Country: .

AUTHORIZED RELEASE CERTIFICATE UNITED STATES

FAAFonn8130-3,AIRWORTHINESSAPPROVAL TAG ot..,,, 1t SC20376 4 Orgamzat,on Name and Address: ROCKWELL COLLINS FLIGHT DYNAMICS SERVICE CENTER 5. Work Order/Contract/Invoice

16655 SW 72ND A VE, SUITE 200 542344 •• Number:

Portland, OR 97224 l 0. APR. 21l/U W0068204 6. Item: 7. Descrintion: 8. Part Number: 9. Eli•ibilitv:• I 0. fluantitv: II. Serial/Batch Number: 12. Status/Work:

1 OVERHEAD UNIT 1500-1260-001 TBVBV 1 11282 REPAIRED INSTALLER

13. Remarks:

REFER TO ATTACHED SERVICE MEMORANDUM# SC20376 FOR SERVICE DETAILS. ITEM #1 REFERENCED ABOVE WAS SERVICE p/t, 9851-11747 ITEM #1 THE FOLLOWING AIRWORTHINESS DIRECTIVE (S) WERE COMPLIED WITH: N/A ITEM #1 ABOVE WAS SERVICEfl IN ACCORDANCE WITH ENGINEERING ORDER No. NIA ITEM #1 THE FOLLOWING SERVICE BULLETINS WERE INSTALLED: NIA

CERTIFIES THAT THE WORK SPECIFIED IN BLOCK 12/13 WAS CARRIED OUT IN ACCORDANCE WITH JAR 145 AND WITH RESPECT TO THAT WORK THE AIRCRAFT COMPONENT IS CONSIDERED READY FOR RELEASE TO SERVICE UNDER JAA ACCEPTANCE CERTIFICATE NUMBER: JAA.4445

14. Certifies the items identified abv\-e were 1udnufa.ct1..1rt:tl i11 cunfonu.ity tu: 19. 0 14 CFR 43.9 Return to ~ervice [8J Ot.ner regulauon spet:1hed m Block 13

D Approved design data and are in condition for safe operation. Certifies that unless otherwise specified in block 13, the work identified in Block 12

D Non-approved design data specified in Block 13. and described in Block 13 was accomplished in accordance with Title 14, Code of Federal Regulations, part 43 and in respect to that work, the items are approved for return to service.

15. Authorized Signature: 16. ApprovaVAuthorization No.: 20. Authorized Signature: 21. ApprovaVCertificate No.:

7 '0J7 F2DR018N ( .,.,,/J~.., .,:,. - //

17. Name (Typed or Printed): 18. Date: , ,ii,. Name (T)pedeinted): 23. Date (m/d/y): ,., JULIA JOHNSON April 13, 2004

I '

User/Installer Responsibilities It is important to understand that the existence of this doc:11ment alone does not automatically constitute authm ity to install the part/component/assembly.

Where the user/installer performs work in accordance witn the national regulations of an airworthiness authority different tha 1 the airworthiness authority of the country specified in Block 1, it is essential that the user/installer ensures that his/her airworthiness accepts parts/components/assemblies from thf airworthiness authority of tht· country specified in Blockl.

Statements in Blocks 14 and 19 do not constitute installatmn certificatmn. In all cases, aircraft maintenance records must contain an installation certification issued in accordance with the national regulations by the user/mstaller before the aircraft may be flown.

FAA Form 8130-3 (6-01) *Installer must cross-check ehg1b1hty with applicable technical data NSN· 0052-00-012-9005

OS JAR-145 MOT-No 1-01, FAR-AUXY103F VO JAR-i'45 MOT-No 1-30 r--·

Workorder Rev 0 Austrian A1rl1nes, Oesterre1chsche Luftverkehrs AG Tyrolean Airways - Tiroler Lufttahrt GmbH ··------------t

Aircraft' L TP Gust.: Maintenance Workorder [qj \81 0A32 D B77 0MD8

iilllllllltJ I ~ ~ Date OA33 OCRJ 03RD

fJA34 0DH8 0COMP 01.Nov2003 Issued by ATA ID VBUI I 34-30

D Pirep D Mamt

~ Sched

No.2015882 uB73 0ER4 Flt No. From D 876 D F70

f.;.,·N D Canni Proiect

S/N

MEL Ref MEL Interval 0HIL

Toi Sin INN

D Flt Deck Info

Statistics

D Struct Damage D Tech lrreg

D Cabin Info

(Side 1 of 2)

D Insurance D Warranty

I OSDC

Classlt:~at1on ~ffil[g[Q] 0 F B req 0 AOG Risk OR ABrTB/BS/GR/HUI/LS/RTR/O

OPS Reporting Text

List~ lV available Fault Codes, Messaoes, Observations either in Descrlot1on- or Action Text

PERFORM INSTALLATION OF HEAD-UP GUIDANCE SYSTEM AND INERTIAL REFERENCE SYSTEM (PROVISIONS ONLY) ACC. EOS-3/34/286.

:si-.::IN:.=:S,e..T:..:.A=L=L.,_,A~Tl:..::::Oc:.:N:....:.A..:.::C=C=·-=S_,_TC=-=S-'-T=00=0=6=5S'E=-T,_,O=-=B=E_,_P=E=R'-FO=R=M=E=D=-=B_,_Y_,_A=V=M"-AX=-'--P--=E"'-R=S=O'-'-'N""N=E=L.'------1 ;;: NOTE: W&B CHANGE!!

Jf------------------------------------------------1

t\_,.rcratt Log ~ t;ntryreq If Taskcard Finding reoort Task No

Enter Maintenance Action into Technical Aircraft Log I Zone I I Area I Date ID Sign

-

't----------;;,...<:/'----------------j---+--+-----1 1- / r-------/-,,,"'-------------+-----1--+-----1

Reference D EOS-3/34/286 Type/ No: W,F,C 0,1,M

Valid Ext Codes Corrb1nat1on of GT/ Groundtune MP/ ManlXlwer TOI Tool HA/ Hannar PW/ Pa=rwork PR/ Part uest and CH/ Ch e IC/ lnco ete ISi lnsuff1c1ent NA/ Not avail WR/ Wrona

Transfer Due Date TAH TAC Prio Ext. Codes ID Sign

D PIG for MEL Dispatch

17.Nov.2003 3 SDT VBUG

~Adrnnistrat1on Workorder, no Maintenance Release reQuired

D This a1rcraN or airframe 1dent1fied above was repaired and inspected 1n accordance W1\h current Regulations of the Federal Av1at1on Adrnnistrallon and 1s approved for return to service The undersigned for the Austnan Airlines FAR 145 Approved Repair Station, Cert1l1cate Number AUXY 103F at Austnan Alrl1nes Technical Base A-1300 Vienna AJrport, Austna, Europe

, ~ Certifies that the work spec1f1ed excepl as otherwise spec1f1ed was earned out 1n accordance with JAR-145 and m respect to that work the aircraft/aircraft component 1s considered ready for releese

0)

It SOMCO /' o,l Approval No O OS JAR-145 MOT-No 1-01 ~ VO JAR-145 MOT-No 1-30 0 Othe "x._ l<>r: ""'l. ,

i,,elease Release 'Time UTC 'Last Flt No._ /Release( lo i\ Dbl~ns~ r~1

/

s'"'°;., o,:,_"_ ,, \';;;1 ;/ sts ~ iJ:l/>,j;,i pnnted by VZEC on Fnday, the 14 November 2003 at 08 32 out of database prod_vo hosted on amosp vie aua com ' procuded by WYM'll''C.MOS corn I

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Engineering Order: 8-3/34/286 Subject: Head-up guidance system, Flight Dynamics model 2800, and Inertial Reference System Honeywell Laserref IV,

Installation of provisions, STC ST00065SE Approval page/ List of effective pages TYROLEAN AIRWAYS, Tiroler Luftfahrt AG, F0rstenweg 190, A-6020 Innsbruck

List of effective pages for revision 0: Reference

LEP

EffectivIty Page

E.O.

Compliance record

Approval for revision O: Notes

Page

1

1

1 ·2 3 4 5 6

1

Revision status Date

17-04-2000

17-04-2000

17-04-2000 17-04-2000 17-04-2000 17-04-2000 17-04-2000 17-04-2000

17-04-2000

For approval of previous revisions, refer to the list of effective pages of the previous revision. For regulation compliance, refer to compliance record CRB-3/34/286. Remarks·

Prepared by: TE-A Graf Approved by:

Distributionlist: Tyrolean TP-Schichtleiterburo (E.O. & drawings)

TS-AVI (E.O. & drawings) J TE-Original file

ACG ..I FL-ZERT (all effective pages)

TE-ProJect number 990072 Rev. 0, 17-04-2000 Form 2016 Page 1 of 1

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Effectivity:


and Inertial Reference System Honeywell Laserref IV, Installation of provisions, STC ST00065SE

Effectivity Page TYROLEAN Al RWA YS, nroler Luftfahrt AG, Furstenweg 190, A-6020 Innsbruck

DH-8-300Q series aircraft, model 311 & 314 Note· This installation is compatible for aircraft equipped with flight compartment sunvisors P/N RDHS-300-1 (rework of sunvisors covered in STC)

For all lill marked A/C the compatibility to this Engineering Order has been checked.

X X X X X X X X X X

I A/CS/NI

268 317 345 351 355

340 370 400 423

438 442 466 481 483 485 527 531 553 554

4014 4015 4026 4027

TE-Project number: 990072 Rev 0, 17-04-2000

A/C Registration A/C model

OE-LLH Dash-8/106 OE-LLJ Dash-8/106 OE-LLG Dash-8/106 OE-LLF Dash-8/106 OE-LLE Dash-8/106

OE-LLZ Dash-8/314 OE-LLY Dash-8/314 OE-LTD Dash-8/314 OE-LTF Dash-8/314

OE-LTG Dash-8/314O OE-LTH Dash-8/314Q OE-LTI Dash-8/314Q OE-LTJ Dash-8/314Q OE-LTK Dash-8/314Q OE-LTL Dash-8/314Q OE-LTM Dash-8/314O OE-LTN Dash-8/314O OE-LTO Dash-8/314O OE-LTP Dash-8/314O

OE-LGA Dash-8/402O OE-LGB Dash-8/402O OE-LGC Dash-8/402O OE-LGD Dash-8/402O

Form 2016 Page 1 of 1

"-'"''11 ... 11 .. 6'"''""' --~-...... ~- - __ -_..,,,,. • ..,.."'"" ~_...,....- .. -

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Effectivity:



TYROLEAN AIRWAYS, T1roler Luftfahrt AG, Forstenweg 190, A-6020 Innsbruck

DH-8-300Q series aircraft, model 311 & 314

Reason:

Note. This installat1on 1s compatible for aircraft equipped with flight compartment sunvisors P/N RDHS-300-1 (rework of sunv1sors covered m STC)

To install provisions for a Flight Dynamics head-up guidance system model 2800, and for a Honeywell Laserref IV inertial reference system

Description:

Mechanical and wiring provisions for the HGS Model 2800 system and for the Honeywell Laserref IV inertial reference system will be installed according Flight Dynamics STC no. ST00065SE which has been validated by the ACG. This results in a .no hazard" installation, with wiring to the circuit breakers disconnected, capped and stowed, and circuit breakers pulled and clipped All HGS LRU's (HGS control panel, combiner, overhead unit, remote airspeed select unit, drive electronics unit, mode annunciator panel, HGS computer), and the inertial reference unit with mode selector unit, are removed (or disconnected & placarded inoperative) for the provisions-installation.

Approval:

Approval of this E.O. has been done in accordance with VHB 03-09-03.

Compliance:

On operaters own discretion.

"' Manpower: Approximately 8 full days downtime will be required to accomplish this modification. The installation will be performed by Avmax Inc personnel (Avmax is a JAR-145 approved/accepted organ1zat1on) which has been contracted by Tyrolean Airways.

Detailed manhour breakdown: Access: (Tyrolean personnel)

Structures and Wirings (Contracted personnel):

Close out: (Tyrolean personnel)

20 Mhrs

2 shifts (12 hours each), teams of 3-4 persons (approx. 500 Mhrs total)

25 Mhrs

This estimate 1s for labor performed by an experienced crew and ~ does not include set-up, planmng, fam1harizat1on, cure time, part fabncat1on, tool aqu1s1t1on or lost time

TE-ProJect number: 990072 Rev. 0, 17-04-2000 Form 2016 Page 1 of 6

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TYROLEAN AIRWAYS, Tiroler LuftfahrtAG, Furstenweg 190, A-6020 Innsbruck

Material Information/Parts required: Item Qty (per A/Cl P/N 1 1ea 60605-401-001

Description Mod-Kit

Remarks pre-assembled

Kit 1s supplied with a .certificate of conformity". Kit is pre-assembled 1n accordance with instructions contained in STC SA00065SE using the approved parts specified in the STC. Detailed kit content

Item Qty (per A/Cl 1 1ea 2 1ea 3 1ea 4 1ea

P/N 1000-0280-301 26006092-101 26012423-105 26000790-101

Descnpt1on HGS installation kit IRU mounting rack IRU DC blower kit IRU fan filter

Above mentioned parts are supplied with JAR-form-one or equivalent

The following_ additional g_arts are reg_uired: Item Qty ( per A/C) P/N Description 1 AR blanking plates 2 AR Alodine 1201 Conversion coating 3 AR F19Type2 Epoxy primer 4 AR EC2216B/A Adhesive 5 AR MS o.oos· dia. Micro balloons 6 AR EA9371 A/B Adhesive, structural 7 AR FR7010 Adhesive, DHMSA6 09 8 AR 495 Superbonder, Loctite 9 AR 242-21 Threadlocker, Loctite 10 AR PR1422B1/2 Sealant 11 AR PR1431G Sealant 12 AR RTV128 Sealant 13 AR RC609 Retainer compound 14 AR 76456 Primer, two part 15 1ea 8CK0673-001 Mod-Kit

Remarks Flight Dynamics Honeywell Honeywell Honeywell

Remarks self-made MIL-C-5541 MIL-P-23377 Gray or equivalent Hysol or E934 or equivalent or equivalent or equivalent or equivalent or equivalent Loctite Loctite Structural mod

The following_ 12.arts are LRU's and are reg_uired for installation checkout on/"t_ (no Q_ermanent installation):

Item Qty (12er A/Cl 1 1ea 2 1ea 3 1ea 4 1ea 5 1ea 6 1ea 7 1ea 8 1ea 9 1ea

TE-Project number: 990072 Rev. 0, 17-04-2000

P/N Descri1;1t1on Remarks 1500-1300-002 HGS computer Rockwell Collins 1500-1260-001 Overhead unit Rockwell Collins 1500-1330-001 Drive electronics unit Rockwell Collins 1500-1350-001 HGS combiner Rockwell Collins 1500-1290-002 HGS control panel Rockwell Collins 1500-1320-002 Rem airspeed select unit Rockwell Collins 1500-1360-002 Mode annunciator panel Rockwell Collins HG2001GD03 Laserref IV IRU Honeywell CG1042AB03 Mode selector unit Honeywell

Form 2016 Page 2 of6

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Engineering Order: 8-3/34/286 Subject: Head-up guidance system, Flight Dynamics modE:I 2800,


TYROLEAN AIRWAYS, Tiroler Luftfahrt AG, Fllrstenweg 190, A-6020 Innsbruck

Special Tools Required:

To be supplied by Tyrolean:

Milliohm Meter VOR/ILS test set Pilot static test set and test fittings Theodolite Tripod

To be supplied by Avmax:

Boresight Alignment Registration Tool BART Aircraft Mounting and Alignment Tool AMAT

Weight & Balance:

Results: Weight: Arm: Moment:

For calculations, refer to sheet no 6.

Publications affected:

N/A

94.3 lbs 249.1 in 23.49 lbin/1000

(Manual revisions will be issued at a later date upon activation of the HGS system) Electrical Load Data:

NIA (All wiring installed is provisions only)

Stress Analysis:

Refer to STC ST00065SE.

Accomplishment Instructions:

• It is only possible to install parts/components (.mod-kit") for which a JAR Form One (or equivalent) has been issued by the STC holder (Note: The STC holder is Flight Dynamics. During incoming inspection at Tyrolean it has to be ensured that an appropriate certificate from the STC holder is available). Exemptions to this rule is granted for:

TSO approved parts called up in the STC paperwork may be obtained directly from the manufacturer In this case the part certification Is done in relation to the applicable TSO number. Self-made parts which are defined as .self-made" in the STC paperwork Certification of such parts is done through the 145 organisation which installs the STC modification.

TE-Project number: 990072 Rev O. 17-04-2000 Form 2016 Page 3 of6



TYROLEAN AIRWAYS, Tiroler LuftfahrtAG, F0rstenweg 190, A-6020 Innsbruck

When parts are pre-assembled in accordance with instructions contained in STC SA00065SE using the approved parts specified in the STC, a cerificate of conformity has to be issued. See .material information". • For installation or replacement of STC approved parts/components, it is only possible to install original STC parts/components. That means, it is not possible to install equivalent parts/components (different partnumber) from the aircraft manufacturer.

Notes: Structural provisions for head up guidance system (8CK0673-001) are a pre-requisite and shall be installed in reference to BRAD service bulletin (supplied with mod kit).

1. Jack up and level aircraft as per AMM (if required for later alignment of avionic ~ equipment).

~emove the following parts for access (Refer to AMM): - Instrument panels (copilot & engine) - All equipment in fwd and aft center console

Flightdeck floor panels as required Cabin seats as required Cabin floor panels as required All equipment in avionics rack Wardrobe assy Exterior front access panels 121AL & 121BL > Carry out installation of provisions only for HGS / IRS in accordance with STC ST00065SE.

Refer to the following documents. - Flight Dynamics Installation drawing list, document no. 9701-0868 rev.Tor later approved revision.

Western Avionics Engineering Order 60605-410 (Installation - Full Provisions and Activation) Western Avionics Engineering Order 60605-411 (De-Activation to Provisions Only)

Remarks·

This step will be accomplished and signed off by Avmalii:' Inc. personnel. All LRU's have to be removed after installation check-out. However, LRU's which remain installed (for example if no appropriate blanking plate is available) must be disconnected, placarded inoperative and considered in the W&B calculation (See page 6)

All wiring to the HGS/IRS circuit breakers shall disconnected, capped and stowed, and circuit breakers shall be pulled and clipped - Cockpit center console layout remains unchanged until final activation of HGS system.

TE-Project number 990072 Rev 0, 17-04-2000 Form 2016 Page 4 of6



TYROLEAN AIRWAYS, Tiroler LuftfahrtAG, F0rstenweg 190, A-6020 Innsbruck

- When doing the Electromagnetic Interference Test (EMI) according the FD Installation checkout procedure 9851-0723 (first aircraft only), it is also required to perform a test with the Dynamic Propeller Balancer Chadwick-Helmuth 8500C (refer Tyrolean E.0. 8-GEN/61/160), to ensure there is no electromagnetic interference between HGS and prop balancer. Record results on FD Form B-3 .EMI data sheet".

~Reinstall all parts previously removed for access. Carry out function checks as required . ._....6-" Remove aircraft from jacks (if required). f 6. Make appropriate entries in the W&B manual (refer to W&B information). L7. Write .EO 8-3/34/286 - Head-up guidance system, Flight Dynamics model 2800, and Inertial Reference System Honeywell Laserref IV, Installation of provisions, STC ST00065SE - accomplished." into the appropriate logbooks.

Maintenance:

No additional maintenance requirements.

Reference Documents: FAA STC ST00065SE (Provisions installation) FAA STC ST00129SE (Fully operational installation)

Flight Dynamics Document Number 9701-0868 (Installation Drawing List) incl. all related documentation issued by Flight Dynamics Flight Dynamics Document Number 9661-0050 (System Maintenance Manual 34-32-00)

Western Avionics Document Number 60605-900 (Mod Data Summary) incl. all related documentation 1sued by Western Avionics (Engineering Order 60605-410 Installation-Full provisions and activation) (Engineering Order 60605-411 De-Activation to Provisions only) (Engineering Order 60605-412 Reactivation)

TE-Project number: 990072 Rev. 0, 17-04-2000 Form 2016 Page 5 of6

Engineering Order: 8-3/34/286 ~ 1Yrolean Subject: Head-up guidance system, Flight Dynamics model 2800,


TYROLEAN AIRWAYS, Tiroler Luftfahrt AG, FOrstenweg 190, A-6020 Innsbruck

Weight & Balance calculations:

WEIGHT & BALANCE CHANGES .,

Item

Description In Out

LRU's:

MGS GGrAfl\ller

O>,erheae llRit

l:lrive eleclreRics llRil

MGS GGrAlliR0F

MGS G9RIF9I !)aRel

Rem. airspeee select llRII

Meee aRRURGiater !)Snel

lneFlial relerence llnit

Meee selector llRlt

Provisions·

X HGS structural & wiring prov X IRU structural & wiring prov,

Misc·

X Blanking plates

Totals

Total Weight & Balance Change

Remarks: Weight [lbs] Arm (inches] Moment [lbin/1000]

TE-Project number: 990072 Rev 0, 17-04-2000

DHC-8/300

Weicht Chance Removed 1-

Weicht Arm Moment Weicht

2e,O

~

M

&c-0

~

~

4.,Q

~

4,-0

61 80

32 50

negl.

94 30

=> 94.30

J

Form 2016

Added(+ Arm Moment

444-5 W-78

ll3--0 ~

~ 4.-09 73,2 GA-a 9e-Q ~

9e-Q ~

~ ~

:.84.0 Mis

00-0 0,00

242 55 14 99

261 00 8.49

249.10 2349

249.10 23.49 V

Page 6 of 6

•

•

:,_,._;f_ -· -~-----· .- -

ENGINEERING ORDER 60605-411, Revision 2

Head-Up Guidance System (HGS) and Inertial Reference System (IRS)

De-Activation to Provisions Only

Model (s): de Havilland DHC-8-300

Aircraft Registration: __ {2.u-1£~----=Lc...,Ti'--'--p ______ _

Aircraft Serial Number: ~ ~</ --~--~-----------Date Revision 2: December 10, 2001

Prepared By:

Reviewed By:

The drawings, specifications, descnpttons. and other technical data attached hereto are property and covenant to Western Av1omcs Inc and constitute secrets for purposes of Trade Secret and Freedom of Information Ads No drsclosure to others, either 1n Canada or

____ a~~a~, o~ repr~ue!•.on of.any part of _the ·~!~~:t~n supplled~o be ~a~~· ~xce~! ~n authonzat~_from ~estem ~~~~

Copyright© 2000 Western Av1omcs

-·00605-411, Rev 2 Page 1 of 11

-•. ,~.: ~,+:.i ;·.· .. ~~~ -.th" ,, .' :., _ "'- ,, f~f." I 4fi,~ ,, ,.,J,, _,-, ~'t - " . -

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cng,neerlng7Jepaffinenl--275 Palmer Road N.E. -- ------- ---~ --- -Calgary. Alberta T2E 7G4 (403) 250-2644

-.... ' • ' A

~

..;.:-~·--: ~ ~. ,-_~ .. ~t., '' -,~1 .. :,~ -~- ' ,..,,,'( ,,, - . ,. -~1-'••! w~·u·1l~f-'7'"" .. -, .,_;~, ' -- . ,,. ~--: ' ,.,, ~ ..., .... ~_ ·- ,;;' ~, ,~ ~ ,y-..J','"

RECORD OF REVISIONS

REV. I

1 I

2 I

' .

PAGES I REVISIONS AFFECTED

'

3 to 11

3

Initial Issue· • " •• ' .,,.

Reworded Section F and steps 2 2, and 123

Added Step 3 1, and Appendix A

I Changed STC Approval number

L

'/ •"- __ ..:._ -- •--i>a -~-- ·-· • ,_

11 ~!:' • ,,_ - ... -~ ~ 4~-~.-,.f.;~...i,.,.l,,,U-'Oc ,-:- _,,_ ";,::: :- _":!,"?,":--""i~"t"--y~.-.. ,. ... _ .::;•-- --~-

DATE APPROVED RY _,_ -·-Apnl5,2000 S Harke I .,

/ May 11, 2000 / M Jaques

I December 10, 2001

. ,

...... Elam 1:ngineenng Department - -- - ---1::: 'iu- - _275 Palmer Road NE~--AVIONICS Calgary, Alberta T2E 7G4

(403) 250-2644

WESTERN AVIONICS ENGINEERING ORDER# 60605-411

A. APPLICABILITY

--::~---;-:,r:~J'.L!,..lifiiljji,!i;,,eenngOrder ii appiicabie to de Havriland 0HQi.#ien~ a~rcraft-wrth HG-~S-in_s_ta_ll_ed-iii-. -- ---~-• accordance with Western Avionrcs Engrneenng Order 60605-41 O

B.

• C.

D.

E.

F.

• G.

BACKGROUND

Western Avronrcs Engineering Order 60605-410 rnstalls all HGS/IRS components and must be rncorporated prior to accomplrshrng thrs engrneenng order

DESCRIPTION

Flrght Dynamics drawing 100~280 (lnstallabon, HGS MDL 2800, DHC8) provrdes an overview of the rnstalled components and their locabons. This Engineering Order removes the HGS/IRS LRUs and de-activates the Head-Up Guidance system to winng provrsrons only

MATERIALS REQUIRED

This modIficatron requires only standard shop supplies and hardware to complete

APPROVAL

The Flight Dynamics Model 2800 HUD Guidance System structural and wmng provision installation completed as per this Engineering Order, rs approved under FAA STC ST00129SE.

LABOUR

., The de-activation of the Model 2800 HUD Guidance System to Provisions Only will take • -approximately 10 man-hours to complete. This estimate is for direct labor performed by an

experienced crew, and it doesn't include planning, familrarization,_access, or lost time.

WEIGHT AND BALANCE CHANGES

• The_f9llowing Werght & Balance changes occur when modifying the't)HC-8 Series 300 aircraft for HGS Provrs1ons Only. ·

-.~ •• -. cl'igineenng-rrepartmenr ~ 21 .:aa.1 I 275 Palmer Road N.E A V I O . . WM j- Calgary:Alberta'Tie-7G4

( 403) 250-2644

H. INSTALLATION INSTRUCTIONS

STEP WORK STEPS MECH INSP 1 Circuit Breaker Panel

1. . :4-'"·~MifeuiH>reakers on ~ pilot's '11PJ)er and lower ~-:::: ;,,.,t~ c circuit breaker pane(· Cap anc1 Stow wires from circurt breakers as shown \' below Reference WA drawing 60605-001 and 60505-002 .-z~ Upper Circuit Breaker Panel·

Label Location Wire HGS G1 3434-271-20 RD OHU F3 3434-021-20 HGSDEU E9 3434-201-20RD ' HGSCOOLING D9 3434-203-20RD and

3434-205-20RD

Lower Circuit Breaker Panel.

Label Location Wore HGS 01 3434-001-16 and

3434-005-16 IRUNo 1 R1 3445-028-20

2 Equipment Removal 2 1 Remove the HGS Control Panel, stow connector and install blanking plate.

PIN. {,l)0-/Jq0-0{)J /( SIN /J-: 2.2 Remove the Combiner and stow connector, and ground strap

PIN: SIN. 2.3 Remove the Overhead Unit and stow connectors, and ground strap.

j•-1.i:,J ••

PIN: I SIN 12~06 2.4 Remove the RASU, stow connector and install blanking plate

PIN· /,,c/0- {3.JO-Q;).:).LJ__ SIN

25 Remove the MSO, stow connector and install blanking plate

. -~-----·Engo~ Oepartn ,ent 275 Palmer Road N E Calga,y," Alberta 't2E ffl4 (403) 250-2644

STEP WORK STEPS MECH 27 Remove the Dnve Electronics Unit ~>

• PIN l~-/]Jo-&o/ ~ SIN /')t/>.l- ~ . 2-.~ f--Rem~, - .. '·.tihi ••• .. - -- 1,--~-- ~> - :. . ~-~··

PIN (_5l'JtJ -/3otJ-{)()],J SIN L;;. 7fr --?R>J., 29 Remove the IRU

,J:¾ fl4:Jo&L4{)0J tl <tJ2f2qJ 1 PIN SIN

3 Tesbng : 3.1 Configure FMS 1 ARING Port 6 for "HS429 IRS1" on accordance with t~e

J;~ UNS-1C FMS Technical Manual Use the Configuration Module Programming Procedure appropriate to the software version installed in the aircraft Section 5 A, Q, and U for software version 601 xi 701.x are contained in Appendix A for reference use.

3.2 Perform pre-closing inspec!Jon and complete Conformity Inspection -~Jr 3.3 Close up all affected areas of the aircraft. ~~

4 Documentation 4 1 Revise aircraft Weight and Balance to include data in Paragraph G %~ 42 Make appropnate logbook entnes and complete Conformity Certificate Form

~2J~ (TC Form 24-0045, FAA Form 337, or equivalent)

I. APPENDICES • . . The following are attached for reference purposes, as notec! in the above report:

Appendix A

UNS-1,C FMS Technical Manual, Report Number 34-60-07, dated July 30, 1996, Section SA, Q, and U, Configuration Module Programming Procedure

J. REFERENCES

1 ., 4.-t:r ... .:.. • • ' ~

' .

~ • •

. r::r· t',t . • «· . ~+a~~

~:) X"+or:1t" ...

Us~ '" .. t~ 44 ~ ~~

u ,~IIAl;-0

i 44 \.,, ...

u ~7% i !H

"'~If!_,:..-

~

u (Ii' 44 :J ~1".gjll)

X,\c~~:\ :~ , .. t: '.:!.~~

-Weste111 ~i;:i~~=:--•- Ai A I cafgary, Alberta '1'2E ~

•

•

(403) 250-2644

. '

.. ,J\i,~. ·19 • ..

APPENDIX A

UNS-1C FMS Technical Manual Section 5A, Q, and U


·- t>H -~. ~,1., .... ,~,

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------ --stern --E--ngmeeAng-Depa,tmenl---t: 2.., 275 Palmer Road NE --.!--- -.AVIO~Jcs Calga~lberffi l 2E /<.5J,'·

(403) 250-2644

UNVBlSAL"AVIONICS SYSTEMS CORPORATION

UNS-1 C FUGHT MANAGEMENT SYSTEM TECHNICAL MANUAL . - {601 ;X} {701.X}

> .

5. Configuration Module Programming Procedures {601.X} {701.X}

A.

Refer to Dtscnphon and Opt ration for general mfonnauon about use of the UNS-1 C FMS. That section introduces the hne select keys, keyboard, and display features.

On multiple UNS-IC mstallauons, the following procedures must be repeated for each UNS-IC Program the Configuration Module as follows:

Starting the UNS-1C FMS

With power apphed to the aircraft. press [ON/OFF DIM] key on the unit. After about •five second warm-up. self test will begm with the self test page displayed and test will proceed. The display will look hke this dunng the database portion of the self test.

UNS - IC

AIRCRAFT IDENTIFICATION

CPU RAM DATABASE

PASS PASS

If the self tests detect a fault precluchng use of the system, then this page will identify the failed test. In this case refer to Maintenance, Checkou~ and Troubleshooting.

If the self-tests detect no faults precluding use of the system, then the COPYRIGHT page will appear brie0y followed by the iniualization page (!NIT 1/1 ).

Puah [SL] lo lnttlalize the UNS-IC. The position. date, and time do not matter.

- : .,

POS INIT

UtTIAl POI ID N 32 ·07. I

1/ I INSG DATE

31-MAY-II UTC

14 ,u W 111 65.4 ITANDAID/EXTENDED NAV DA~AIAIE EXPIIII II-JUN-II

'PEIF DI --------ACCEPT FMC VEI

P-ush [MSGl to ilisplay lhe message(s). Push [MSG] or~ETURN (SR] 10 return to the lnoliallzatlorl page.

10 1. D Push [IR] to highlight the DATE field. Puah [4) [5] (6) [7J [8] (9) and then push [ENTER]

•

•

--- - -=- ---- --- -- --

Push [DATA) to show the DATA 115 page.

DATA t/6

-JEPPESEN -PILOT

"'""'MAINT [SR) to show the Mamlenance page;

.. ,,

-PERF

-DISK

-HOLD POS

Push CONFIG [1L) to show the First Configuration page .

MAINT-

MAINT t/1

-CONFIG MAINT LOGCLEAR LOG-

RETURN-

EDIT (1 A) must be pushed once, on th,s or a later page, belore you can change the configuration. The display will change to:

EDIT CONFIQ STORE CONF-

The changes you make performing these contiguration procedure& are not eflective until you store them. You should enter all required configuration changes before pushlng STORE CONF- [1 R~ H you push STORE CONF- [t RJ before making all required changes,

~ than you will haw to wall while Iha oystam restans ltaeH •

Push display (1 L) to show CONFIQ I/ 2

-DISPLAY EDIT-the DISPLAY CONFIG page. ~ --FMS CONFIG

-OISCRETES

-ARINC

-CSOB

ANALOG

ASCBAIR DATA

RETURN-

--- - ~-~--------- - --------- ------

60605--41-1, ~--

. " < •

34-60-07 Page 476 July 30, 1996

- Pa9e8of11

. ,._,

"

On the first Configuration.page, push ARINC (4LJ to -show the -ARINC Options page.

Push RECEIVE (1 L) to show the first ARINC Receiw page. Then verify or set each of the ARINC Receive inputs.

Push IBANSMIT (2LJ to Show the first ARINC Transmit page. Then verily or set each of the ARINC Transmit outputs.

Push 561 TRANSMIT [3LJ to show the first A561 XMIT page. Then verily or set each of the ARtNC 561 options.

-·

,.;.,:_; NOTE: ' , X ~

561 TRANSMIT wi!l,not show unless.,, "' , .. , , .,. ' the UNS-1C is equipped with an , - , : , ANALOG board, PIN 1017-XX-XlX.; __ ,,,,.

or 1017-XX-XSX.

ARINC OPT 1 /1 EDIT CONFIQ

-RECEIVE STORE CONF-13 13 -TRANSMIT

13 -6 8 t TRANSMIT

13 l3=------....!R~E2,;TU~R!,!N!:;--.c,

13

When you have -Wied or configured an ARINC Inputs and OUtputs, push RETURN [5A] to show the first Configuration Page.

_,4L --~4f,.,,.~t-, .... :.-.... :-··-·-~----- - ___ --,JL

34-60-07 Page 498.5 July 30, 1996

--- -- .60605--411,Belt.2~--- ----- ·--- ---- --------- - -

Push the Une select key for any ARINC Input you want to change. Fill in the appropriate Item number and then push [ENTER). ·

Repeat Step O for an remaining ARINC Inputs you want to change.

If your UNS-lC is PIN 1017-XX-X2X, then 11 is equipped with two ARINC Boards. Push [NEXT] to show the second ARINC Options Page.

Perform Steps O and 8 for all ARINC Inputs you want to change.

' .t.-_-

,.... -

See Note 2 ' l.' \,Mtf,:.,r if'

i B B

'' ""' ., - - - ,,_ EXAMPLE FOR FMS #1, ,., •. 1. '""''"''' ,i,.,, .

ARING RCV 1/1 PORTO EDIT CONFIG LS GPSI 81 STORE CONF-roar 1 ro1T 5 LS GPS2 B1 NO SENSQR PORT 2 POIT 6 429 GPOSS HS429 IRS 1 PORT 3 PORT 7 NO SENSOR CROSSFILL 1 PORT 4

8"-l>H:.:;S::,;4:,:2a,:9:...:l.::R,::S..::,3 __ _,::R,::E.:_TU::,R::,;N---::.;.,~

.. , When you have verified or configured all ARINC Inputs, push RETURN (SR) to show the ARINC Options Page.

NOTES: 1 . When performing the inrtlal configuration of ARINC receive ports, select the NO SENSOR option for ail ports inltlally. This will allow all possible port Input devices to be displayed in the selection list for each port. Once a sensor is selected for a particular port, 11 will not shOw up as an option for any other ports.

2. The UNS-1 C GPS is internally connected to Port O. It should therefore be configured as the onside GPS, i.e., for FMS #1 configure Porto to "LS GPSl 81 "; for FMS #2 configure Port Oto "LS GPS2 81 "; for FMS #3 configure Porto to 'LS GPS3 Bl".

34-60-07

., •. ,, Page 498.6

July 30, 1996

-- -Pege10 of++--·--··