flight standards information system (fsims) - …fsims.faa.gov/wdocs/mmel/dc-8 r45.pdfmcdonnell...

U.S. Department of Transportation Federal Aviation Administration Washington, D.C.

Master Minimum Equipment List Revision: 45 Date: January 8, 2010 McDONNELL DOUGLAS DC-8 SERIES 10 THROUGH SERIES 70 Thomas L. Witts Flight Operations Evaluation Board (FOEB) Federal Aviation Administration Long Beach Aircraft Evaluation Group (LGB-AEG) 3900 Paramount Blvd, Suite 100 Lakewood, CA 90712-4137 WWW.FAA.GOV/FSDO/LGBAEG Telephone: (562) 627-5272 FAX: (562) 627-5281

FEDERAL AVIATION ADMINISTRATION Page I Revision 45 MASTER MINIMUM EQUIPMENT LIST Date: 01/08/2010 DC-8

CONTENTS

SYSTEM PAGE(S) REVISION DATE Title page - 45 01/08/2010 Contents I 45 01/08/2010 Highlights of Change II Thru XI 45 01/08/2010 Definitions (Operator Responsibility) XII 45 01/08/2010 Preamble (Operator Responsibility) XIII 45 01/08/2010 21 - Air Conditioning 21-1 Thru 21-25 45 01/08/2010 22 - Auto Flight 22-1 Thru 22-6 45 01/08/2010 23 - Communications 23-1 Thru 23-17 45 01/08/2010 24 - Electrical Power 24-1 Thru 24-5 45 01/08/2010 25 - Equipment/Furnishings 25-1 Thru 25-14 45 01/08/2010 26 - Fire Protection 26-1 Thru 26-8 45 01/08/2010 27 - Flight Controls 27-1 Thru 27-4 45 01/08/2010 28 - Fuel 28-1 Thru 28-20 45 01/08/2010 29 - Hydraulic Power 29-1 Thru 29-3 44 05/20/2004 30 - Ice and Rain Protection 30-1 Thru 30-7 45 01/08/2010 31 - Indicating/Recording Systems 31-1 Thru 31-2 45 01/08/2010 32 - Landing Gear 32-1 Thru 32-4 45 01/08/2010 33 - Lights 33-1 Thru 33-6 45 01/08/2010 34 - Navigation 34-1 Thru 34-36 45 01/08/2010 35 - Oxygen 35-1 Thru 35-3 45 01/08/2010 36 - Pneumatic 36-1 Thru 36-5 45 01/08/2010 38 - Water/Waste 38-1 Thru 38-2 45 01/08/2010 46 - Information Systems 46-1 Thru 46-2 45 01/08/2010 49 - Airborne Auxiliary Power 49-1 Thru 49-1 45 01/08/2010 52 - Doors 52-1 Thru 52-6 45 01/08/2010 73 - Engine Fuel & Control 73-1 Thru 73-3 45 01/08/2010 74 - Ignition 74-1 Thru 74-1 43 12/15/1999 75 - Bleed Air 75-1 Thru 75-1 39b 10/18/1993 77 - Engine Indicating 77-1 Thru 77-3 43 12/15/1999 78 - Engine Exhaust 78-1 Thru 78-4 45 01/08/2010 79 - Engine Oil 79-1 Thru 79-2 43 12/15/1999 80 - Starting 80-1 Thru 80-1 39 04/26/1993 82 - Water Injection 82-1 Thru 82-1 39 04/26/1993

FEDERAL AVIATION ADMINISTRATION Page II Revision 45 MASTER MINIMUM EQUIPMENT LIST Date: 01/08/2010 DC-8

Highlights of Change

EFFECTIVE ABOVE DATE, the DC-8 Master Minimum Equipment List (MMEL) has been revised. Revision 45 introduces a new format. The changes in this revision were made to align with FAA policy letters, and improve consistency. All changes are reflected in the highlights of change listed below and are indicated by revision bars. Please replace ALL pages for a complete up-to-date MMEL. SEE NOTES BELOW FOR IMPORTANT INFORMATION ABOUT THIS REVISION. Retain this sheet with your MMEL until the next revision is issued. NOTE 1: Pages WILL NOT be itemized in a CONTROL PAGE for individual revisions. Rather, the ATA section will contain the applicable number of pages and revision number. Any changes to any item within the ATA section will result in the entire section receiving a revision number. To find any revised item within the section see the list below. NOTE 2: The “Table of Contents” has been replaced with a “Contents” page having System, Pages, and Revision Numbers. NOTE 3: The “Definitions” pages and “Preamble” pages have been removed. Operators must insert the applicable DEFINITIONS from current Policy Letter 25 and the applicable PREAMBLE from current Policy Letter 34 (Air Carriers) or Policy Letter 36 (Part 91 Operators) into their MEL.

Note: All references to FAR have been replaced with 14 CFR within the ATA Chapters for consistency. ATA System/Sequence Number Remarks

21 28 Radio Rack Cooling Valve

System

Revises proviso.

*** 59 EFIS Electronic Flight Display (EFD) Unit Cooling FANS

Removes “The” from item d) in second proviso.

*** 61-1 Supplemental Cockpit Air Conditioning and Heating Systems STC ST145CH System

Moves the word “provided” so that proviso reads better.

66 Flow Control Valves (NASI Flow Control Systems)

Revises proviso so that it reads better.

67 Hot Air Mix Valves (NASI Flow Control Systems)


70 Left (Cockpit), and Right (Cabin) Supply Duct Temperature Indicators (NASI Flow Control Systems STC SA466CH)


FEDERAL AVIATION ADMINISTRATION Page III Revision 45 MASTER MINIMUM EQUIPMENT LIST Date: 01/08/2010 DC-8

ATA System/Sequence Number Remarks

22 AUTO FLIGHT

1 Autopilot System Revises proviso and numbers Notes.

1-1 Autopilot System Control Wheel Disengage Switches

Revises item and adds relief per FAA PL-93, Revision 1.

1-3 Autopilot System Digital Air Data Computer (DADC)

Removes “(e.g. RVSM)” from proviso.

8-1e Autopilot Control Panel (Sperry) ALT Hold

Revises proviso.

9-2b Autopilot/Flight Guidance Control (Collins) Mode Select Panel Vertical Control Modes ALT

Revises proviso.

*** 10 Autopilot Disengage Audio Warning

Replaces “39,000 feet” with “FL 390”.

23 COMMUNICATIONS

2-1 Passenger Address System (PA) Passenger Configuration

Adds the word “function(s)” to Note per FAA PL-9, Revision 8.

*** 2-1a Lavatory Speakers Reformats item per FAA PL-9, Revision 8.

*** 2-2 Cargo Configuration (Courier/Supernumerary Address System)

Reformats item per FAA PL-9, Revision 8.

2-2a Lavatory Speakers Adds item per FAA PL-9, Revision 8.

3-1 VHF Comm Control Panels Revises title per FAA PL-95, Revision 1.

3-2 High Frequency (HF) Communications System

Revises item a) Per FAA PL-82, Revision 1. Revises item d) per FAA PL-106, Revision 3.

5-3 Audio Selector Panel Switches (VHF, ADF, HF, NAV, MKR, VOICE, RANGE SWITCHES)

Deletes “The” from proviso a).

*** 8 Selective Call Systems (SELCAL)

Revises item per FAA PL-117, Revision 0.

FEDERAL AVIATION ADMINISTRATION Page IV Revision 45 MASTER MINIMUM EQUIPMENT LIST Date: 01/08/2010 DC-8


*** 8-1 Channels Adds items per FAA PL-117, Revision 0.

13 Cockpit Voice Recorder (CVR)


*** 14 Emergency Locator Transmitters (ELT)


*** 15-1 Boom Microphones Cockpit Voice Recorder Equipped to Record Boom Microphone Per 14 CFR 121.359 (g), 135.151 (d) or 125.227 (e)


22-1b Flight Attendant Visual Alerting System

Adds (O) and revises verbiage in proviso b). Adds proviso c). Revises Note 1. Adds Note 2. All per FAA PL-9, Revision 8.

22-1c Flight Attendant Audio Alerting System

Adds (O) and revises verbiage in proviso b). Revises Note 1. Adds Note 2. All per FAA PL-9, Revision 8.

22-2b Courier/Supernumerary Visual Alerting System

Adds (O) and revises proviso. Adds proviso. Per FAA PL-9, Revision 8.

22-2c Courier/Supernumerary Audio Alerting System

Adds (O) and revises proviso. Adds Note to second proviso. All per FAA PL-9, Revision 8.

23 Handset System(s) Revises Title per FAA PL-9, Revision 8.

24 ELECTRICAL POWER

1-1a Generator and Constant Speed Drives (CSD) Units Brushless Generators Aircraft without STC SA7090NM to FREON System

Adds (M) and (O) to proviso.

1-1b Generator and Constant Speed Drives (CSD) Units Brushless Generators Aircraft with STC SA7090NM to FREON System

Adds (M) and (O) to proviso.

FEDERAL AVIATION ADMINISTRATION Page V Revision 45 MASTER MINIMUM EQUIPMENT LIST Date: 01/08/2010 DC-8


1-2a Generator and Constant Speed Drives (CSD) Units Brush Generators Aircraft without STC SA7090NM to FREON System

Adds (M) and (O) to proviso and revises proviso.

1-2b Generator and Constant Speed Drives (CSD) Units Brush Generators Aircraft with STC SA7090NM to FREON System

Adds (M) and (O) to proviso and revises proviso.

2 AC Voltage Regulators Revises proviso.

3 Current Transformers Revises proviso.

4 Generator Control Panels

Revises proviso.

5 Generator Relays (GR) Revises proviso.

*** 6-1 Push to Indicate Oil Temperature Display (Rise/Outlet) Function

Revises Note per FAA PL-82, Revision 1.

10 Frequency Meter Selector Switch Positions

Removes “One” from proviso.

10-2 Frequency Meter Selector Switch Positions


11 Voltmeter (AC) Selector Switch Positions


11-2 Voltmeter (AC) Selector Switch Positions


14 DC Loadmeters Adds “considered” to proviso.

25 EQUIPMENT/FURNISHINGS

5-1 Megaphones Passenger Configuration

Removes (M) from proviso per FAA PL-47, Revision 1. Removes “The” in proviso a).

6 “Fasten Seat Belt While Seated” Sign or Placard

Replaces the word “readable” with “visible” in the proviso per FAA PL-89, Revision 1.

FEDERAL AVIATION ADMINISTRATION Page VI Revision 45 MASTER MINIMUM EQUIPMENT LIST Date: 01/08/2010 DC-8


9-1-2 Primary Observer Seat (Including Associated Equipment)

Revises proviso a) per FAA PL-56, Revision 4.

9-1-3 Primary Observer Seat (Including Associated Equipment)

Removes “the” from proviso b) per FAA PL-56, Revision 4.

10 Cabin Emergency Flashlight and Holder (Flight Attendant Position)

Revises proviso for consistency.

11 Passenger Seat(s) Revises the repair category per FAA PL-79, Revision 6.

11-1 Recline Mechanism Revises the repair category and adds (M) to proviso per FAA PL-79, Revision 6.

11-1 Recline Mechanism Adds item per FAA PL-79, Revision 6.

11-3 Armrest Adds items per FAA PL-79, Revision 6.

*** 13 Non-Essential Equipment and Furnishings (NEF)


18 Emergency Medical Equipment

Revises and renumbers items per FAA PL-73, Revision 4.

20 Galley Waste Receptacles Access Door/Covers

Removes “The” from proviso a).

22 Overhead Storage Bin(s)/Cabin and Galley Storage Compartment/Closets

Revises and adds item per FAA PL-104, Revision 3.

*** 22-1 Storage Compartment Key Locks

Adds item per FAA PL-104, Revision 3.

26 FIRE PROTECTION

1 Portable Fire Extinguishers Removes “The” from proviso a).

8 Lavatory Smoke Detection Systems

Adds the word “Associated” to proviso b) per FAA PL-24, Revision 3.

9 Lavatory Fire Extinguisher Systems

Adds the word “Associated” to proviso b) and revises both Notes per FAA PL-24, Revision 3.

10 Cargo Compartment Fire Detection/Suppressions Systems

Revises item per FAA PL-102.

FEDERAL AVIATION ADMINISTRATION Page VII Revision 45 MASTER MINIMUM EQUIPMENT LIST Date: 01/08/2010 DC-8


27 FLIGHT CONTROLS

4-1 PTC Extend Warning Light and Mechanical Indicators Warning Light Push to Test Function

Replaces “flight” with “departure” in proviso.

13 Standby Rudder Accumulator Pressure Gauge

Replaces “flight” with “departure” in proviso.

28 FUEL

2-2 Alternate Tank Fuel Boost Pumps Series 10, 20, 30, 40, 50, and Models 61 and 71 Aircraft

Deletes duplicate verbiage.

*** 3 Center Auxiliary Fuel Tank Boost Pumps

Deletes duplicate nomenclature.

3-3 Center Auxiliary Fuel Tank Boost Pumps

Removes “The” from proviso c).

30 ICE AND RAIN PROTECTION

8 Scoop Anti-Ice System Adds (M) to proviso.

11-2 Engine Anti-Ice Valve Systems (Series 10 through 60)

Adds (M) to proviso.

13 Pitot HEATER INOP, HTR FAIL, and STALL WARNING ANTI-ICE Lights

Deletes the word “either” from item b) in the proviso.

31 INDICATING/RECORDING

SYSTEMS

2 Flight Data Recorder (FDR) System


32 Landing Gear

*** 6 Bogie Swivel Unlock Adds (M) to proviso.

11 Lamp Control Box for Mark III Anti-Skid System

Adds (O) to proviso.

12 Mark III Spoiler Control Unit Adds (O) to proviso.

FEDERAL AVIATION ADMINISTRATION Page VIII Revision 45 MASTER MINIMUM EQUIPMENT LIST Date: 01/08/2010 DC-8


33 LIGHTS

4 Passenger Lighted Information Signs

Revises item per FAA PL-123.

5-1 Red Anti-Collision Lights Individual Bulbs

Revises proviso.

6 Wing Illumination Lights Revises number installed per FAA PL-72, Revision 3.

34 NAVIGATION

15 Non-Stabilized Magnetic Compass

Removes the word “Standby” per FAA PL-10, Revision 1. Revises proviso to “are operative”.

15-1 Glareshield Mirrors Removes the word (Standby) in second proviso.

16-1-2 Flight Director Systems Go-Around (GA) Mode

Revises the Repair Category.

16-2-2 Flight Director Systems Go-Around Switch

Revises the Repair Category.

*** 23-3 VHF Navigation Systems (VOR, ILS) Glide Slope Indicators

Reformats proviso.

24 ATC Transponders and Automatic Altitude Reporting Systems


*** 24-1 Elementary and Enhanced Downlink Aircraft Reportable Parameters not Required by 14 CFR.


*** 24-2 ADS-B Squitter Transmissions


26 Radio Altimeter Systems Revises item to align with GPWS relief.

34 Terrain Awareness and Warning System (TAWS)

Revises item per FAA PL-54, Revision 10. Includes items for Class A, B, and C TAWS Equipment Required.

37-6 Distance Converter Deletes (M) from proviso.

40 Traffic Alert Collision Avoidance System (TCAS II)

Deletes (O) from second proviso.

FEDERAL AVIATION ADMINISTRATION Page IX Revision 45 MASTER MINIMUM EQUIPMENT LIST Date: 01/08/2010 DC-8

ATA System/Sequence Number

Remarks

40-2 Resolution Advisory (RA) Display System(s)

Deletes PL verbiage from nomenclature.

40-4 Audio Functions Adds item per FAA PL-32, Revision 7.

*** 40-5 Airspace Selection Function


*** 40-6 Dual Vertical Speed Indicator/Traffic and Resolution Advisory (VSI/TRA) Displays

Renumbered item due to the addition of items -40-4 and -40-5.

*** 41-1 Windshear Warning and Flight Guidance System (Reactive)

Revises items per FAA PL-67, Revision 3.

*** 41-2 Windshear Detection and Avoidance System (Predictive)

Revises items per FAA PL-67, Revision 3.

56 VOR/DME Tuning Select Function (Auto/Manual)

Removes “The” from proviso a) and b).

*** 66 Airspeed Bugs Internal Bug (All Except Collins STC SA8106SW)

Revises Repair Category.

*** 68-7 Select/Range (SEL/RNG) Controls


*** 69 Automatic Dependent Surveillance-Broadcast (ADS-B) System

Revises items per FAA PL-105.

35 OXYGEN

1-1 Crew Oxygen Bottles

Removes “All but one Bottle” verbiage in proviso.

3-2 Passenger Oxygen System

Adds relief.

5 Protective Breathing Equipment (PBE)

Adds (PBE) to nomenclature per FAA PL-43, Revision 1.

36 PNEUMATIC

1-2 Pressure Regulator Shutoff Valve (Series 10 through 60)


FEDERAL AVIATION ADMINISTRATION Page X Revision 45 MASTER MINIMUM EQUIPMENT LIST Date: 01/08/2010 DC-8


Remarks

38 WATER/WASTE

2 Lavatory Waste Systems (Including Wheelchair Accessible Lavatories)

Revises nomenclature and removes “system” from b) in second proviso per FAA PL-83, Revision 4.

46 INFORMATION SYSTEMS

*** 20-1 Electronic Flight Bag Systems (EFB)

Adds new Chapter for Information Systems. Adds relief for Electronic Flight Bag Systems (EFB).

49 AIRBORNE AUXILIARY

POWER

*** 2 Auxiliary Power Unit Pneumatic Power

Revises Repair Category to D.

*** 3 Auxiliary Power Unit Electrical Power Generating System

Revises Repair Category to D.

52 DOORS

6 Lower Compartment Doors Operating Mechanisms (Cargo/Air Conditioning/Accessory)

Replaces the word “flight” with “departure” in proviso a).

7 Main Cabin Exits/Slides (All Cargo Configuration)

Revises provisos per FAA PL-99, Revision 1.

*** 8 Enhanced Flight Deck Security Door Primary Locking System (14 CFR 25.795 Compliant) Passenger and Combi Aircraft Only


*** 9 Enhanced Flight Deck Security Door Secondary Locking System (14 CFR 25.795 Compliant) Passenger and Combi Aircraft Only


*** 10 Intrusion Resistant Cockpit Door

Adds item for STC STO1791CH NASI Cockpit Door.

10-1 Door Locking Solenoid


10-2 Door WARN Light


FEDERAL AVIATION ADMINISTRATION Page XI Revision 45 MASTER MINIMUM EQUIPMENT LIST Date: 01/08/2010 DC-8


Remarks

10-3 Door Bell Switch


10-4 Door Buzzer Adds item for STC STO1791CH NASI Cockpit Door. 73 ENGINE FUEL & CONTROL

2-1 Engine Fuel Filter Impending Bypass Indication System Indicator Reset Feature

Revises proviso a) per PL-82, Revision 1.

78 ENGINE EXHAUST

3 Ejector Systems Deletes duplicate nomenclature. Removes “The” from proviso b).

*** 4 Ejector Indicator Lights Adds (M) and the word “considered” to proviso.

FEDERAL AVIATION ADMINISTRATION Page XII Revision 45 MASTER MINIMUM EQUIPMENT LIST Date: 01/08/2010 DC-8

Definitions

Insert current Policy Letter 25 DEFINITIONS here.

FEDERAL AVIATION ADMINISTRATION Page XIII Revision 45 MASTER MINIMUM EQUIPMENT LIST Date: 01/08/2010 DC-8

Preamble

Insert current Policy Letter 34 or 36, as applicable, PREAMBLE here.

U.S. DEPARTMENT OF TRANSPORTATION MASTER MINIMUM EQUIPMENT LIST

FEDERAL AVIATION ADMINISTRATION AIRCRAFT:

DC-8 REVISION NO: 45 DATE: 01/08/2010

PAGE NO: 21-1

REPAIR CATEGORY 2. NUMBER INSTALLED

3. NUMBER REQUIRED FOR DISPATCH

1. SYSTEM, SEQUENCE NUMBERS & ITEM

4. REMARKS AND EXCEPTIONS

21 AIR CONDITIONING

1. ***

Cabin Turbo-Compressors (T/Cs)

1) Unpressurized Flight C 4 0 (O) May be inoperative provided:

a) When cabin differential pressure is less than 2 psi, Weather Radar, HF Radios, and ATC Transponder remain OFF, and

b) AFM performance penalties are applied.

2) Pressurized Flight C 4 3 (O) One may be inoperative provided

AFM Performance penalties are applied.

C 4 2 (O) Two may be inoperative provided:

a) One is operative on each side of the Pneumatic System, and

b) Flight is conducted at or below FL 240.

2. ***

Cabin Compressor Overspeed Controls

C - 0 May be inoperative provided associated Turbo-Compressor is considered inoperative and not used.

3. ***

Cabin Compressor RPM Indicators


4. ***

Cabin Compressor Overheat Lights





PAGE NO: 21-2





21 AIR CONDITIONING

5. ***

Cabin Compressor Recirculation Valves

D 4 0

6. Cabin Altitude Indicator C 1 0 (O) May be inoperative provided:

a) Cabin Differential Pressure indicator is operative, and

b) Flight crew is provided a chart to convert Cabin Differential Pressure to Cabin Altitude.

7. Cabin Differential

Pressure Indicator C 1 0 (O) May be inoperative provided:

a) Cabin Altitude Indicator is operative, and

b) Flight Crew is provided a chart to convert Cabin Altitude to Cabin Differential Pressure.

8. Cabin Rate of Climb

Indicator C 1 0 (O) May be inoperative provided:

a) Automatic Pressurization Control System is operative,

b) Cabin Differential Pressure Indicator is operative, and

c) Cabin Altitude Indicator is operative.

9. Cabin Altitude Warning

System C 1 0 May be inoperative provided aircraft

remains at or below 10,000 feet MSL.

10. Cabin Pressure Control System

1) Automatic C 1 0 (Continued)




PAGE NO: 21-3





21 AIR CONDITIONING

10. Cabin Pressure Control System (Cont’d)

2) Manual C 1 0 (M)(O) May be inoperative provided:

a) Cabin Pressure Control Valve is secured OPEN, and

b) Flight is conducted Unpressurized.

11. ***

Cabin Temperature Control System (FREON System)

1) Automatic D 1 0

2) Manual DELETED in Revision 38.

12. Cabin Air Temperature Indicating System

1) Passenger C 1 0

2) Cargo Configuration D 1 0

13. ***

Flight Deck Temperature Control System (FREON System)

1) Automatic D 1 0

2) Manual DELETED in Revision 38.




PAGE NO: 21-4





21 AIR CONDITIONING

14. ***

Cabin Heat Exchanger Exhaust Door Actuators

C 2 1 One may be inoperative provided associated FREON System is operative.

D 2 1 May be inoperative provided affected

Door remains fully OPEN.

15. ***

Air Conditioning Temperature Diverter Valve

C 1 0 May be inoperative provided ambient temperature is less than 85 degrees F.

16. Recirculation Fans C - 0

17. ***

FREON Systems

1) Ambient Temperature

Less than 85 Deg. F C 2 0

2) Ambient Temperatures

Exceeding 85 Deg. F C 2 0 Both may be inoperative provided

alternate cooling source is available and used to cool the aircraft to at least 85 degrees F.

a) Left System C 1 0 May be inoperative provided:

a) Diverter Valve is operative, b) Aircraft is cooled to

85 degrees F or less, and c) Right System is operative.

b) Right System C 1 0 May be inoperative provided:

a) Aircraft is cooled to 85 degrees F or less, and

b) Left System is operative.




PAGE NO: 21-5





21 AIR CONDITIONING

18. ***

FREON Compressor Air Shutoff Valves

C 2 0 (O) May be inoperative provided associated FREON compressor is considered inoperative and not used.

19. ***

FREON System Temperature Saturation Indicators

C 2 0 (O) May be inoperative provided: a) FREON Compressor

Overspeed Trim relay is operative,

b) High FREON Pressure Shutoff Switch is operative,

c) High Oil Temperature Warning light is operative, and

d) Low Oil Pressure Switch is operative.

20. ***

FREON System Temperature Superheat Indicators


Overspeed Trim relay is operative,

b) High FREON Pressure Shutoff Switch is operative,

c) HIGH Oil Temperature Warning light is operative, and

d) Low Oil Pressure Switch is operative.

21. ***

FREON Compressor Oil Overheat Lights

C 2 0 (O) May be inoperative provided associated FREON Compressor is considered inoperative and not used.

22. ***

FREON Condensers C 2 0 May be inoperative provided associated FREON Compressor is considered inoperative and not used.




PAGE NO: 21-6





21 AIR CONDITIONING

22. FREON Condensers (Cont’d)

1) FREON Condenser Air

Selector Valves C 2 0 (M) May be inoperative provided:

a) Valve is secured in the Flight Position, and

b) Associated FREON system is used only in flight.

23. ***

FREON Condenser Fans

C 2 0 May be inoperative provided associated FREON Compressor is not used on the ground.

24. ***

FREON Condenser Exhaust Door Actuators

C 2 0 May be inoperative provided associated FREON Compressor is considered inoperative and not used.

25. ***

FREON Evaporators C 2 0 May be inoperative provided associated FREON Compressor is considered inoperative and not used.

26. ***

Aft Cargo Compartment Blower

D 1 0

27. Radio Rack Blower C 1 0 May be inoperative provided:

a) Venturi Valve Set to provide cooling,

b) Weather Radar, Transponder, and HF transmitter are not used on the ground,

c) Ground operation of remaining Radio Compartment Equipment is limited to 30 minutes,

(Continued)




PAGE NO: 21-7





21 AIR CONDITIONING

27. Radio Rack Blower (Cont’d)

d) One Radar System may be in STANDBY and selected ON less than 5 minutes before takeoff, and

e) One HF transmitter may be used on the ground for no more than two 20 second transmissions at approximately 3 minute intervals.

NOTE: All equipment may be turned

ON after takeoff.

28. Radio Rack Cooling

Valve System C 1 0 (M) May be inoperative provided

Venturi Valve Set to provide cooling. ||

29. Radio Rack Blower

Indicating Light C 1 0 May be inoperative provided Radio

Rack Blower is considered inoperative.

1) ***

Reset Function C 1 0 May be inoperative provided Radio Rack Blower is considered inoperative.

30. Radio Rack Blower

Differential Pressure Switch

C 1 0 (M) May be inoperative provided Cooling Valve is secured OPEN.

31. ***

Recirculation Fan Unloader Valve

C 1 0 May be inoperative provided Recirculation Fan Stall Warning Lights are operative.




PAGE NO: 21-8





21 AIR CONDITIONING

32. ***

Recirculating Fan Stall Warning Lights

C - 0 May be inoperative provided associated Recirculation Fan is considered inoperative and not used.

D - 1 May be inoperative provided

associated Recirculation Fan is not considered inoperative and not used.

33. ***

Forward Cargo Compartment Temperature Switch

D 1 0

34. ***

FREON Compressor Low Oil Pressure Warning Lights

C 2 0 May be inoperative provided associated Freon Evaporator Inlet and Outlet Temperature Indicator is operative.

35. ***

FREON Compressor Overspeed Warning Lights

C 2 0 May be inoperative provided associated Freon Evaporator Inlet and Outlet Temperature Indicator is operative.

36. ***

FREON Controller Power Available Lights

C 2 0

37. ***

FREON Evaporator Inlet and Outlet Temperature Indicators


Overspeed Warning Light System is operative, and

b) FREON Compressor low Oil Pressure Warning Light is operative.




PAGE NO: 21-9





21 AIR CONDITIONING

38. ***

Air Conditioning Packs C 2 1 (M)(O) One may be inoperative provided:

a) Associated Flow Control Valve is secured CLOSED, and

b) Aircraft remains at or below FL250.

C 2 0 (M)(O) May be inoperative provided:

a) Both Flow Control Valves are secured CLOSED,

b) Flight is conducted Unpressurized, and

c) Appropriate AFM Limitations are applied.

39. Air Conditioning Pack

Air Cycle Machines C 2 1 One may be inoperative provided Heat

Exchanger Cooling is operative for affected Pack.

40. PACK Flow Control

Valves C 2 0 May be inoperative provided

associated Air Conditioning Pack is considered inoperative and not used.

1) Variable Flow Rate

Function (Cargo Configuration)

C 2 1 (M) May be inoperative provided: a) Min Flow is available for

associated Air Conditioning Pack, and

b) Pack Flow Control Valve is verified to close.

41. PACK Trip Systems C 2 1 One may be inoperative provided:

a) Associated Compressor Discharge Temperature Indicator is operative, and

b) Associated Pack Temperature indicating System is operative.

(Continued)




PAGE NO: 21-10





21 AIR CONDITIONING

41. PACK Trip Systems (Cont’d)

C 2 1 One may be inoperative provided

affected Pack is considered inoperative and not used.

42. PACK Cooling Fans C 2 0 May be inoperative provided affected

Pack is operated only when in flight.

43. PACK Fan Inlet Door Actuators

C 2 0 May be inoperative provided: a) Affected Door is failed

CLOSED, and b) Associated Pack is operated

only when in flight. C 2 0 May be inoperative provided affected

Door is failed OPEN.

44. PACK Cooling Door Systems (Ram Air Exit)

C 2 1 One may be inoperative provided: a) Both Packs are operative, b) Affected Pack is operated only

when in flight, and c) Associated Pack Trip System is

operative. C 2 0 (M) May be inoperative provided

affected systems are secured full OPEN.

45. ***

PACK Cooling Door Position Indicators

C 2 0 May be inoperative provided: a) Associated Pack Trip System is

operative, and b) Associated Pack Compressor

Temperature Indicator is operative.

(Continued)




PAGE NO: 21-11





21 AIR CONDITIONING

45. ***

PACK Cooling Door Position Indicators (Cont’d)

D 2 0 May be inoperative provided

associated Pack Cooling Doors are positioned fully OPEN.

46. PACK Compressor

Discharge Temperature Indicators

C 2 0 May be inoperative provided associated Pack Trip System is operative.

47. ***

PACK Temperature Indicating Systems

1) Pack Temperature C - 0 May be inoperative provided

associated Pack Trip System is operative.

2) Cabin Supply D - 0

3) Lower Cargo Compartment

D - 0

48. PACK Temperature

(Mix) Valves C 2 0 May be inoperative provided

associated Pack is considered inoperative and not used.

49. PACK Mix Valve

Position Indicating Systems

C 2 0

50. Cabin Temperature

Control Systems (PACK)

C 1 0 May be inoperative provided Right Air Conditioning Pack is considered inoperative and not used.

(Continued)




PAGE NO: 21-12





21 AIR CONDITIONING

50. Cabin Temperature Control Systems (PACK) (Cont’d)

1) Manual Control C 1 0 May be inoperative provided automatic

control system is operative.

2) Automatic Control D 1 0 May be inoperative provided Manual Control System is operative.

51. Cockpit Temperature

Control System (PACK)

C 1 0 May be inoperative provided Left Air Conditioning Pack is considered inoperative and not used.

1) Manual Control C 1 0 May be inoperative provided Automatic

Control System is operative.

2) Automatic Control D 1 0 May be inoperative provided Manual Control System is operative.

52. Supply Duct Overheat

Systems (PACK) C 2 1 One may be inoperative provided:

a) Associated Pack Trip System is operative, and

b) Associated Pack Temperature Indicating System is operative.

53. Ram/Fan Diverter

Valves (PACK) C 2 0 May be inoperative provided:

a) Affected Valve is set to admit Ram Air, and

b) Affected Air Conditioning pack is operated in flight only.

(Continued)




PAGE NO: 21-13





21 AIR CONDITIONING

53. Ram/Fan Diverter Valves (PACK) (Cont’d)

1) Right Valve C 1 0 May be inoperative provided:

a) Affected Valve is set to admit FAN Air, and

b) Affected Air Conditioning Pack is operated on the ground only.

54. ***

Water Separator Anti Ice Systems

C 2 1 One may be inoperative provided: a) Affected Pack Mix Valve

Position Indicator is operative, and

b) Pack Mix Valve is operated in Manual Control and controlled such that the Mix Valve indicator remains between 11 and 3 O’clock.

55. ***

EFIS Display Unit Cooling Fans (STC SA2304SO)

C 5 4 One may be inoperative provided: a) Outside Air Temperature is

below 100 degrees F and operational ground time is limited to 30 minutes or less, and

b) All Symbol Generator Cooling Fans are operative.

56. ***

EFIS Symbol Generator Cooling Fans (STC SA2304SO)

C 3 2 One may be inoperative provided: a) Outside Air Temperature is

below 100 degrees F and operational ground time is limited to 30 minutes or less, and

b) All Display Unit Cooling Fans are operative.




PAGE NO: 21-14





21 AIR CONDITIONING

57. Freon Condenser Air Selector Valves

Moved to 21-22 in Rev. 39

58. INU Cooling Fan Fail

Annunciator (STC SA8106SW)

C 2 0 (M) May be inoperative provided associated fan operation is verified prior to each departure.

59. ***

EFIS Electronic Flight Display (EFD) Unit Cooling FANS (STC SA8106SW)

C 4 2 Two may be inoperative provided: a) One is operative on each side,

and b) OAT is at or below

45 degrees C (113 degrees F) for ground operation.

C 4 2 Two may be inoperative provided:

a) One is operative on each side, b) OAT is above 45 degree C (113

degrees F) for ground operation,

c) At least one air conditioning pack is on for ground operations, and

d) Recirculating fan is on for ground operations.

|


a) One is operative on each side, and

b) OAT is greater than 45 degrees C (113 degrees F) for ground operations of 20 minutes or less.

60. EFIS Cooling Fan Fail

Annunciator Lights (STC SA8106SW)

C 4 0 (M) May be inoperative provided associated fan is verified operative prior to each departure.




PAGE NO: 21-15





21 AIR CONDITIONING

61. ***

Supplemental Cockpit Air Conditioning and Heating Systems (STC ST145CH, STC SA1360GL, STC SA1421GL)

1) STC ST145CH System C 1 0 May be inoperative for aircraft not

equipped with air conditioning packs, provided an alternate cooling source is used to cool the cockpit to 85 degrees F.

|||||

D 1 0 May be inoperative provided:

a) For aircraft not equipped with air conditioning packs, an alternate cooling source is used to cool the cockpit to 85 degree F., and

b) Air conditioning and heat operate only through ground control relay.

a) Heat Function C 1 0 (O) May be inoperative provided HEAT

HI/HOT and HEAT LO/WARM are not used.

D 1 0 (O) May be inoperative provided:

a) HEAT HI/HOT and HEAT LO/WARM are not used, and


(Continued)




PAGE NO: 21-16





21 AIR CONDITIONING

61. ***

Supplemental Cockpit Air Conditioning and Heating Systems (STC ST145CH, STC SA1360GL, STC SA1421GL) (Cont’d)

1) STC ST145CH System

(Cont’d)

b) Air Conditioning

(Cooling) Function C 1 0 (O) May be inoperative provided for

aircraft not equipped with air conditioning packs, an alternate cooling source is used to cool the cockpit to 85 degree F.


a) AC HI and/or AC LO are not required to cool the cockpit to 85 degrees F, and

b) Air conditioning and heat operation are only through the ground control relay.

c) Fan Speed LO Setting C 1 0 (O) May be inoperative provided Fan

LO setting is not required to cool cockpit to 85 degrees F.


a) Fan LO Setting is not required to cool cockpit to 85 degrees F, and


(Continued)




PAGE NO: 21-17





21 AIR CONDITIONING

61. ***


1) STC ST145CH System

(Cont’d)

d) Fan Speed HI Setting C 1 0 (O) May be inoperative provided:

a) Fan HI setting is not required to cool cockpit to 85 degrees F, and

b) Heat mode is not used. D 1 0 (O) May be inoperative provided:

a) Fan HI setting is not required to cool cockpit to 85 degrees F,

b) Heat mode is not used, and c) Air conditioning and heat

operate only through the ground control relay.

e) Condensate Pump D 1 0 (Continued)




PAGE NO: 21-18





21 AIR CONDITIONING

61. ***


2) STC SA1360GL

System C 1 0 May be inoperative provided an

alternate cooling source is used to cool the cockpit to 85 degrees F.

a) Fan Speed LO Setting C 1 0 (O) May be inoperative provided Fan

LO setting is not required to cool cockpit to 85 degrees F.

b) Fan Speed HI Setting C 1 0 (O) May be inoperative provided Fan HI

setting is not required to cool cockpit to 85 degrees F.

c) Evaporator Fans STC

SA1360GL C 2 0 Both may be inoperative provided

associated evaporator(s) is not used.

3) Electric Heating System STC SA1421GL

D 1 0

62. ***

Cold Air Pressure Regulator Valve

C 1 0 May be inoperative provided Equipment Cooling does not require its use.

63. Cockpit Individual Air

Outlets (Eyeballs) D - 0




PAGE NO: 21-19





21 AIR CONDITIONING

64. Flight Compartment Overhead Air Diffuser(s) Controls

C - 0 (M) May be inoperative provided affected Air Diffuser(s) is secured open.

65. NASI Flow Control

Systems (STC SA466CH)

C 2 0 (M)(O) both Left and Right Systems may be inoperative provided:

a) Both Flow Control Valves are secured closed,

b) Flight is conducted in an Approved Unpressurized Configuration, and

c) Appropriate AFM Limitations, Procedures, and performance adjustments are applied.

1) Left Flow Control

System C 1 0 (M)(O) May be inoperative provided:

a) Right Flow Control System is operative,

b) Left Flow Control Valve is secured closed,

c) Temperature Diverter Valve is operative, and

d) Aircraft remains at or below FL 250.

2) Right Flow Control

System C 1 0 (M)(O) May be inoperative provided:

a) Left Flow Control System is operative,

b) Right Flow Control Valve is secured closed, and

c) Aircraft remains at or below FL 250.

66. Flow Control Valves

(NASI Flow Control Systems) (STC SA466CH)

C 2 0 (M)(O) May be inoperative provided: a) Both Flow Control Valves are

secured closed,

|||

(Continued)




PAGE NO: 21-20





21 AIR CONDITIONING

66. Flow Control Valves (NASI Flow Control Systems) (STC SA466CH) (Cont’d)

b) Flight is conducted in an

Approved Unpressurized Configuration, and


1) Left Flow Control Valve C 1 0 (M)(O) May be inoperative provided:


b) Left Flow Control Valve is secured closed,

c) Temperature Diverter Valve is operative, and


2) Right Flow Control

Valve C 1 0 (M) May be inoperative provided:


b) Right Flow Control Valve is secured closed, and

c) Aircraft remains at or below FL 250.

3) Variable Flow Control

Functions (Cargo Configuration)

C 2 1 (M) One may be inoperative provided associated Flow Control Valve is verified to be operative.

(Continued)




PAGE NO: 21-21





21 AIR CONDITIONING

67. Hot Air Mix Valves (NASI Flow Control Systems) (STC SA466CH)


secured closed, b) Flight is conducted in an



|

1) Left Hot Air Mix Valve C 1 0 (M)(O) May be inoperative provided:


b) Right Hot Air Mix Valve is operative,

c) Left Flow Control Valve is secured closed,

d) Temperature Diverter Valve is operative, and

e) Aircraft remains at or below FL 250.

2) Right Hot Air Mix Valve C 1 0 (M)(O) May be inoperative provided:


b) Left Hot Air Mix Valve is operative,

c) Right Flow Control Valve is secured closed, and


68. Cabin Temperature

Control System (NASI Flow Control Systems) (STC SA466CH)

C 1 0 (M)(O) May be inoperative provided: a) Left Flow Control System is

operative, b) Right Flow Control Valve is

secured closed, and

(Continued)




PAGE NO: 21-22





21 AIR CONDITIONING

68. Cabin Temperature Control System (NASI Flow Control Systems) (STC SA466CH) (Cont’d)

c) Aircraft remains at or below

FL 250.

1) Cabin Manual Control Function

C 1 0 May be inoperative provided Automatic Cabin Temperature Control Function is operative.

2) Cabin Automatic

Control Function D 1 0 (O) May be inoperative provided:

a) Manual Cabin Temperature Control function is operative,

b) Right Supply Duct Temperature Indicator is operative,

c) Right Supply Duct Overtemperature System is operative, and

d) Procedures are established and used to regulate Cabin Temperature manually.

69. Cockpit Temperature

Control System (NASI Flow Control Systems STC SA466CH)

C 1 0 (M)(O) May be inoperative provided: a) Right Flow Control System is

operative, b) Left Flow Control Valve is

secured closed, c) Temperature Diverter Valve is

operative, and d) Aircraft remains at or below

FL 250. (Continued)




PAGE NO: 21-23





21 AIR CONDITIONING

69. Cockpit Temperature Control System (NASI Flow Control Systems STC SA466CH) (Cont’d)

1) Cockpit Manual

Temperature Control Function

C 1 0 May be inoperative provided Cockpit Automatic Temperature Control Function is operative.

2) Cockpit Automatic

Temperature Control Function

D 1 0 May be inoperative provided: a) Cockpit Manual Temperature

Control function is operative, b) Left Supply Duct Temperature

Indicator is operative, c) Left Supply Duct Over

temperature System is operative, and

d) Procedures are established and used to regulate Cockpit Temperature manually.

70. Left (Cockpit), and

Right (Cabin) Supply Duct Temperature Indicators (NASI Flow Control Systems STC SA466CH)


secured closed, b) Flight is conducted in an



|

(Continued)




PAGE NO: 21-24





21 AIR CONDITIONING

70. Left (Cockpit), and Right (Cabin) Supply Duct Temperature Indicators (NASI Flow Control Systems STC SA466CH) (Cont’d)

1) Left (Cockpit) Supply

Duct Temperature Indicator

C 2 1 May be inoperative provided: a) Right (Cabin) Supply Duct

Temperature Indicator is operative,

b) Left (Cockpit) Automatic Temperature Control Function is operative,

c) Left (Cockpit) Supply Duct Over temperature Protection System is operative, and

d) Temperature Diverter Valve is operative.

2) Right (Cabin) Supply

Duct Temperature Indicator

C 2 1 May be inoperative provided: a) Left (Cockpit) Supply Duct

Temperature Indicator is operative,

b) Right (Cabin) Automatic Temperature Control function is operative, and

c) Left (Cockpit) Supply Duct Over temperature Protection System is operative.




PAGE NO: 21-25





21 AIR CONDITIONING

71. Left (Cockpit) and Right (Cabin) Supply Duct Over Temperature Protection Systems (NASI Flow Control Systems STC SA466CH)

C 2 0 (M)(O) Both Left and Right systems may be inoperative provided.

a) Both Flow Control Valves are secured closed,

b) Flight is conducted in an Approved Unpressurized configuration, and


1) Left (Cockpit) Supply

Duct Over temperature Protection System

C 1 0 (M)(O) May be inoperative provided: a) Right Flow Control System is

operative, b) Right (Cabin) Supply Duct Over

temperature Protection System is operative,

c) Left Flow Control Valve is secured closed,

d) Temperature Diverter Valve is operative, and

e) Aircraft remains at or below FL 250.

2) Right (Cabin) Supply

Duct Over temperature Protection System

C 1 0 (M)(O) May be inoperative provided: a) Left Flow Control System is

operative, b) Left (Cockpit) Supply Duct Over

temperature Protection System is operative,

c) Right Flow Control Valve is secured closed, and





PAGE NO: 22-1





22 AUTO FLIGHT

1. Autopilot System B 1 0 May be inoperative provided enroute operations and/or approach minimums do not require its use.

|||

NOTE 1: Any mode which functions

normally may be used. |

NOTE 2: See AFM for use of autopilot

as an alternate stability device when PTC is inoperative.

|

1) Control Wheel

Disengage Switches C 2 1 One may be inoperative provided:

a) Autopilot is not used below 1,500 feet AGL, and

b) Approach minimums do not require the use of the autopilot.

|||||

B 2 0 May be inoperative provided autopilot

is not used. ||

2) Autopilot Transfer

Switch C 1 0

3) Digital Air Data

Computer (DADC) (STC ST09336SC)

C 1 0 May be inoperative except where enroute operations require its use.

|

2. Yaw Damper C 1 0

3. Comparator Unit C 1 0 (Continued)




PAGE NO: 22-2





22 AUTO FLIGHT

4. ***

Auto Throttle D 1 0

5. ***

Auto Throttle Speed Command System

D 1 0 May be inoperative provided Auto Throttle is considered inoperative and not used.

6. ***

EFIS Altitude Preselector

C 1 0 May be inoperative provided: a) Autopilot and Flight Director

functions are not used for altitude selection or capture, and

b) Altitude Alert Function is operative.

7. Yaw Damper

Annunciator C 2 0

8. Autopilot Control Panel

(Sperry)

1) Pitch Selector Modes

a) ***

Mach Hold D 1 0

b) ***

IAS Hold D 1 0

c) ***

Glide Path Extend D 1 0

d) ***

Pitch Damp C 1 0

e) ALT Hold B 1 0 May be inoperative provided:

a) Altitude Alert Function is operative, and

b) Enroute operations and/or approach minimums do not require its use.

|||||

(Continued)




PAGE NO: 22-3





22 AUTO FLIGHT

8. Autopilot Control Panel (Sperry) (Cont’d)

2) NAV Selector Mode

a) ***

AUX NAV D 1 0 As required by 14 CFR.

b) Heading Selector B 1 0

c) LOC/VOR C 1 0 May be inoperative provided approach minimums do not require its use.

d) ILS C 1 0 May be inoperative provided approach

minimums do not require its use.

e) ALT Hold Moved to item 22-8-1, Revision 44.

9. Autopilot/Flight Guidance Control (Collins) STC SA8106SW

1) Mode Select Panel

Lateral Control Modes

a) HDG C 2 1 B 2 0

b) NAV C 2 0

c) ½ Bank C 2 0 (Continued)




PAGE NO: 22-4





22 AUTO FLIGHT

9. Autopilot/Flight Guidance Control (Collins) STC SA8106SW (Cont’d)


Lateral Control Modes (Cont’d)

d) APPR C 2 0 May be inoperative provided approach



Vertical Control Modes C 2 0 May be inoperative provided approach


a) CLIMB C 2 0

b) ALT C 2 1 B 2 0 May be inoperative provided:

a) Altitude Alert Function is operative, and

b) Enroute operations and/or approach minimums do not require its use.

||||||

c) DESCENT C 2 0

d) SPEED C 2 0

e) PERFORM C 2 0

f) SYNCRONIZE C 2 0 (Continued)




PAGE NO: 22-5





22 AUTO FLIGHT

9. Autopilot/Flight Guidance Control (Collins) STC SA8106SW (Cont’d)


Vertical Control Modes (Cont’d)

g) Commanded/Set

Speed Bug (airspeed indicator inner bug)

C 2 0 May be inoperative provided alternate speed indications and speed set controls are available for each bug.

C 2 0 May be inoperative provided

associated auto flight modes (SPEED, DESCENT and CLIMB) are considered inoperative.


Switch lights

a) Captain C 8 4 May be inoperative provided selected

mode is annunciated on the associated EADI.

b) First Officer C 8 4 May be inoperative provided selected

mode is annunciated on the associated EADI.

4) Autopilot Panel

Turbulence Mode C 1 0




PAGE NO: 22-6





22 AUTO FLIGHT

10. ***

Autopilot Disengage Audio Warning

A 1 0 May be inoperative provided: a) Approach minimums do not

require its use, b) PTC is operative, and c) Repairs are made within

3 flight days.

A 1 0 May be inoperative provided:

a) Approach minimums do not require its use,

b) Flight Mach Number does not exceed 0.78,

c) Flight altitude does not exceed FL 390, and

d) Repairs are made within 3 flight days.

|




PAGE NO: 23-1





23 COMMUNICATIONS

1. Flight Deck Speakers C - 0 May be inoperative provided procedures do not require its use.

2. Passenger Address

System (PA)

1) Passenger

Configuration B 1 0 (O) May be inoperative provided:

a) Alternate, normal and emergency procedures, and/or operating restrictions are established and used, and

b) Flight Attendant alerting system (audio and visual) is operative.

NOTE: Any station function(s) that is

operative may be used.

C 1 0 (O) May be inoperative provided:

a) PA not required by 14 CFR, and

b) Alternate, normal and emergency procedures, and/or operating restrictions are established and used.


operative may be used. ||

a) ***

Lavatory Speakers C - 0 (O) May be inoperative provided alternate procedures are established and used.

|||

(Continued)




PAGE NO: 23-2





23 COMMUNICATIONS

2. Passenger Address System (PA) (Cont’d)

2) ***

Cargo Configuration (Courier/ Supernumerary Address System)

C 1 0 May be inoperative provided alternate, normal and emergency procedures, and/or operating restrictions are established and used.

||||


procedures do not require its use.

a) Lavatory Speakers C 1 0 (O) May be inoperative provided

alternate procedures are established and used.

|||


procedures do not require its use. ||

3. Communications

Systems (HF, VHF, UHF)

D - - Any in excess of those required by 14 CFR may be inoperative provided it is not powered by the emergency AC bus, Emergency DC Bus, Battery Bus, Battery Direct Bus, or the DC Transfer Bus and not required for emergency procedures.

1) VHF Comm

Control Panels |

|

a) Frequency Transfer Light

C - 0

b) Frequency Transfer

Switch C - 0

c) Frequency Selector

Knob C - 2

d) Frequency Indication C - 2 (Continued)




PAGE NO: 23-3





23 COMMUNICATIONS

3. Communications Systems (HF, VHF, UHF) (Cont’d)

2) High Frequency (HF)

Communications System

D - - Any in excess of those required by 14 CFR may be inoperative.

C - 1 (O) May be inoperative while

conducting operations that require two LRCS provided:

a) SATCOM Voice or Data Link is operative,

b) Alternate procedures are established and used,

c) SATCOM coverage is available over the intended route of flight, and

d) If Inmarsat codes are not available while using SATCOM voice, prior coordination with the appropriate ATS facility is required.

|| |||||

NOTE: SATCOM is to be used only as

a backup to normal HF communications unless otherwise authorized by the appropriate ATS facilities.




PAGE NO: 23-4





23 COMMUNICATIONS

4. Crewmember Interphone System(s)

C 2 1

1) Passenger

Configuration

a) Flight Deck to Cabin,

Cabin to Flight Deck Functions

B - - (O) May be inoperative provided: a) Flight deck to cabin and cabin

to flight deck interphone functions are operative on at least fifty percent of the cabin handsets, and

b) Alternate communications procedures between the affected Flight Attendants station(s) are established and used.


operative may be used.

b) Cabin to Cabin Function

B 2 0 (O) May be inoperative provided alternate communications procedures between the affected flight attendants stations are established and used.


operative may be used. (Continued)




PAGE NO: 23-5





23 COMMUNICATIONS

4. Crewmember Interphone System(s) (Cont’d)

1) Passenger

Configuration (Cont’d)

b) Cabin to Cabin

Function (Cont’d)

B - - (O) May be inoperative provided:

a) Cabin to cabin interphone functions are operative on at least fifty percent of the cabin handsets, and

b) Alternate communications procedures between the affected flight attendants station(s) are established and used.


operative may be used. (Continued)




PAGE NO: 23-6





23 COMMUNICATIONS


1) Passenger


c) Flight Deck to Ground

Function

1) Large Turbojet

Powered Airplanes Operating Under Part 121

C 1 0 (O) Flight interphone flight deck to ground/ground to flight deck function may be inoperative provided:

a) Alternate procedures are established and used, and

b) Nose gear/forward fuselage service interphone jack is operative.

C 1 0 (O) Service interphone flight deck to

ground/ground to flight deck function may be inoperative provided:


b) Nose gear/forward fuselage flight interphone jack is operative.

B - 0 (O) May be inoperative provided


(Continued)




PAGE NO: 23-7





23 COMMUNICATIONS


1) Passenger



Function (Cont’d)

2) All Other

Aircraft/Operations C - 0 (O) May be inoperative provided




2) Cargo Configuration

a) Flight Deck to Cabin, Cabin to Flight Deck Functions

C 1 0 (O) May be inoperative provided alternate, normal and emergency procedures, and/or operating restrictions are established and used.



b) Cabin to Cabin Function

D 1 0

(Continued)




PAGE NO: 23-8





23 COMMUNICATIONS



(Cont’d)


Function

1) Large Turbojet

Powered Airplanes Operating Under Part 121

C 1 0 (O) Flight interphone flight deck to ground/ground to flight deck function may be inoperative provided:


b) Nose gear/forward fuselage service interphone jack is operative.

C 1 0 (O) Service interphone flight deck to

ground/ground to flight deck function may be inoperative provided:


b) Nose gear/forward fuselage flight interphone jack is operative.

B - 0 (O) May be inoperative provided


(Continued)




PAGE NO: 23-9





23 COMMUNICATIONS



(Cont’d)


Function (Cont’d)

2) All Other

Aircraft/Operations C - 0 (O) May be inoperative provided




5. Audio Selector Panels D - - Any in excess of those required for flight deck crewmembers (including official observer in Forward Observers Seat) may be inoperative.

1) Audio Selector Panel

R/T Function of Receive/Transmit and Intercom Switch

C - - May be inoperative provided a separate push-to-talk (PTT) switch is operative at that crew station.


Amplifier C - - One amplifier associated each panel

may be inoperative provided one amplifier remains operative at each crew station.

(Continued)




PAGE NO: 23-10





23 COMMUNICATIONS

5. Audio Selector Panels (Cont’d)


Switches (VHF, ADF, HF, NAV, MKR, VOICE, RANGE SWITCHES)

C - - One switch on each audio selector panel may be inoperative provided:

a) Flight interphone function is operative, and

b) Alternate procedures for monitoring and identifying radios are established and used.

|

6. ***

Service Interphone System

Moved to item 23-4, Revision 44.

7. ***

Flight Attendants Interphone System

Moved to item 23-4, Revision 44.

8. ***

Selective Call Systems (SELCAL)

C - 0 (O) May be inoperative provided alternate procedures are established and used.

|||



1) Channels C - 0 (O) May be inoperative provided


|||



9. Static Dischargers DELETED in revision 38. NOTE: See CDL

10. Passenger Entertainment Equipment

DELETED, Included Passenger Convenience Items in Chapter 25.




PAGE NO: 23-11





23 COMMUNICATIONS

11. Operator And Passenger Convenience Communications Equipment

DELETED, Included in Passenger Convenience Items in Chapter 25.

12. ***

ARINC Communications Addressing and Reporting System (ACARS)

C 1 0 (O) May be inoperative provided alternate procedures are established and used.



13. Cockpit Voice

Recorder (CVR) A 1 0 May be inoperative provided:

a) Flight Data Recorder (FDR) is operative, and

b) Repairs are made within three flight days.

|||||

14. ***

Emergency Locator Transmitters (ELT)

||

1) Survival Type ELTs D - - Any in excess of those required by 14

CFR may be inoperative or missing. ||

2) Fixed ELTs A - 0 (M) May be inoperative provided:

a) System is deactivated, and b) Repairs are made within 90

days.

||||

A - 0 May be missing provided repairs are

made within 90 days. ||

D - - (M) Any in excess of those required by

14 CFR may be inoperative provided system is deactivated.

|||

D - - Any in excess of those required by 14

CFR may be missing. ||




PAGE NO: 23-12





23 COMMUNICATIONS

15. Boom Microphones

1) ***

Cockpit Voice Recorder Equipped to Record Boom Microphone Per 14 CFR 121.359 (g), 135.151 (d) or 125.227 (e)

A - 0 May be inoperative provided: a) Flight Data Recorder (FDR) is

operative, and b) Repairs are made within three

flight days.

|||

2) Cockpit Voice

Recorder Not Equipped to Record Boom Microphone

D - 0 Any in excess of those required by 14 CFR may be inoperative.

3) Mask/Boom

Microphone Selector SW

D - 0 As required by 14 CFR.

16. VHF COMM Control

Panel Frequency Display Test

C 2 0 (O) May be inoperative provided alternate procedures are established to determine proper frequency.

17. VHF COMM Active

Channel Light Moved to item 23-3a), rev. 43.

18. VHF Communications

Control Panel A/B Transfer Switch

Moved to item 23-3b), rev. 43.

19. VHF Communications

Dual Control Panel Frequency Selector

Moved to item 23-3c), rev. 43.




PAGE NO: 23-13





23 COMMUNICATIONS

20. ***

Dual Tone Multifrequency Microphone (DTMF) (Telephone Dialing Feature)

D - 0 May be inoperative provided: a) Voice Mode is operative, and b) Procedures do not require its

use.

D - 0 (O) May be inoperative provided:

a) Voice Mode is operative, and b) Alternate procedures are

established and used.

21. ***

Mechanic Call System D 1 0 (O) May be inoperative provided: a) System is not required for INS

NO COOLING Warning, b) System is not required for APU

Fire Warning, and c) Alternate procedures are


22. Alerting System

(Audio/Visual)

1) Passenger

Configuration

a) Flight Deck Call Visual

Alerting System B 1 0 May be inoperative provided the flight

deck audio alerting system is operative.

NOTE: Flight Deck audio alerting must

always be operative.

(Continued)




PAGE NO: 23-14





23 COMMUNICATIONS

22. Alerting System (Audio/Visual) (Cont’d)

b) Flight Attendant Visual

Alerting System B 1 0 (O) May be inoperative provided:

a) PA System is operative, and b) If affected visual alerting

system is used for Lavatory Smoke Detector Alerting, an alternate lavatory smoke detector alert (audio or visual) is installed and is operative, and

c) Alternate procedures for contacting flight attendants are established and used.

|||||||||||

NOTE 1: Passenger to Attendant Call

System is considered Non-Essential Equipment and Furnishing (NEF).

|||

NOTE 2: Any visual alerting system

function(s) that is operative may be used.

|||

c) Flight Attendant Audio

Alerting System B - 0 (O) May be inoperative provided:

a) PA System is operative, and b) If affected audio alerting system

is used for Lavatory Smoke Detector Alerting, an alternate lavatory smoke detector alert (visual or audio) is installed and is operative, and

c) Alternate procedures for contacting flight attendants are established and used.

|||||||||||

NOTE 1: Passenger to Attendant Call

System is considered Non-Essential Equipment and Furnishing (NEF).

|||

(Continued)




PAGE NO: 23-15





23 COMMUNICATIONS


c) Flight Attendant Audio

Alerting System (Cont’d)

NOTE 2: Any audio alerting system

function(s) that is operative may be used.

|||


a) Flight Deck Call Visual Alerting System

B 1 0 May be inoperative provided the flight deck audio alerting system is operative.


Courier/Supernumerary compartment remains unoccupied.

b) Courier/

Supernumerary Visual Alerting System

B 1 0 (O) May be inoperative provided: a) Courier/supernumerary address system is operative, and b) Alternate procedures are


|||||


courier/supernumerary compartment remains unoccupied.

|||

NOTE: Any visual alerting system

function(s) that are operative may be used.

|||




PAGE NO: 23-16





23 COMMUNICATIONS



(Cont’d)

c) Courier/Supernumerary

Audio Alerting System B 1 0 (O) May be inoperative provided:

a) Courier/supernumerary address system is operative, and

b) Alternate procedures are established and used.

||||||


courier/supernumerary compartment remains unoccupied.

|||

NOTE: Any audio alerting system

function(s) that operates normally may be used.

|||

23. Handset System(s) |

1) Passenger

Configuration

a) Flight Deck C - 0 (O) May be inoperative provided:

a) Flight Deck to cabin communication is operative and,




(Continued)




PAGE NO: 23-17





23 COMMUNICATIONS

23. Handset Systems (Cont’d)

1) Passenger


b) Cabin B - - (O) May be inoperative provided:

a) Fifty percent of cabin handsets are operative,

b) On wide-body airplanes, one handset must be operative at each pair of exit doors, and

c) Alternate communications procedures between the affected Flight Attendants station(s) are established and used.

NOTE 1: An operative handset at an

inoperative flight attendant seat shall not be counted to satisfy the fifty percent requirement.

NOTE 2: Any handset(s) function(s)

that is operative may be used.


a) Flight Deck C - 0 May be inoperative provided flight deck to courier/supernumerary communication is operative.



b) Courier/ Supernumerary

D - 1


Courier/Supernumerary compartment remains unoccupied.




PAGE NO: 24-1





24 ELECTRICAL POWER

1. Generator and Constant Speed Drives (CSD) Units

1) Brushless Generators

a) Aircraft without STC SA7090NM to FREON System

C 4 3 (M)(O) One may be inoperative provided:

a) Bus-tie system is operative, b) Remaining Generators are

operated in parallel, and c) AFM Limitations are applied.

|

b) Aircraft with STC

SA7090NM To FREON System

B 4 3 (M)(O) One may be inoperative provided:

a) Bus-Tie System is operative, b) Remaining Generators are

operated in parallel, and c) AFM Limitations are applied.

|

2) Brush Generators

a) Aircraft without STC SA7090NM to FREON System

C 4 3 (M)(O) One may be inoperative provided:

a) Aircraft is restricted to Domestic Operations as defined in 14 CFR 119.3.

b) Remaining Generators are operated in parallel, and

c) AFM Limitations are applied.

||||||

b) Aircraft with STC SA7090NM To FREON System

B 4 3 (M)(O) One may be inoperative provided:

a) Aircraft is restricted to Domestic Operations as defined in 14 CFR 119.3.

b) Remaining Generators are operated in parallel, and

c) AFM Limitations are applied.

||||||




PAGE NO: 24-2





24 ELECTRICAL POWER

2. AC Voltage Regulators C 4 3 One may be inoperative provided the associated Generator is not used.

|

3. Current Transformers C 28 21 Seven may be inoperative provided the

associated Generator is not used. ||

4. Generator Control

Panels C 4 3 One may be inoperative provided

associated Generator is not used. |

5. Generator Relays (GR) C 4 3 One may be inoperative provided

associated Generator is not used. |

6. CSD Temperature

Indications C 4 2

1) ***

Push to Indicate Oil Temperature Display (Rise/Outlet) Function

C 1 0 NOTE: Any Indication that is operative may be used.

||

7. CSD Low Oil Quantity

and Pressure Warning Lights

C 4 2

1) ***

Low Oil Quantity Warning Function

D 4 0

8. Generator Paralleling

System C 1 0 May be inoperative provided all four

generators are operative.




PAGE NO: 24-3





24 ELECTRICAL POWER

9. Transformer Rectifier (TR) Units

C 4 3 (M) One may be inoperative provided all DC buses (including relays) are operative.

10. Frequency Meter

Selector Switch Positions

C - - (M) May be inoperative provided associated Generator is not used.

||

C - - (O) May be inoperative provided:

a) Four Generators are operative, b) Generators are operated in

parallel, c) Voltmeter is operative for the

affected position, and d) Loadmeter is operative for the

affected position.

|

11. Voltmeter (AC)

Selector Switch Positions

C - - May be inoperative provided the associated Generator is not used.

||

C - - (O) May be inoperative provided:

a) Four Generators are operative, b) Generators are operated in

parallel, c) Frequency Meter is operative

for the affected position, and d) Loadmeter is operative for the

affected position.

|

12. Voltmeter (DC) C 1 0 (M) May be inoperative provided:

a) DC Bus Tie and Battery voltage are checked before each departure, and

b) DC Loadmeters are operative.




PAGE NO: 24-4





24 ELECTRICAL POWER

13. AC Loadmeters C 4 3

14. DC Loadmeters C 4 3 (M) One may be inoperative provided associated Transformer Rectifier (TR) is considered inoperative.

|

15. Battery System DELETED in revision 34.

16. External Power System

1) External Power C 1 0 (M) May be inoperative provided:

a) External Power Transformer rectifier Circuit Breaker is pulled and collared,

b) External Power Protection Fuses are removed from the External Power Protection panel,

c) External Power Receptacle is placarded “DO NOT CONNECTED EXTERNAL POWER”, and

d) Accepted battery start procedures are used.

2) Ground Service Switch

and Relay C 1 0 May be inoperative provided Relay is

positioned for OPEN CIRCUIT.

NOTE: “OPEN CIRCUIT” denotes that

in placing the ground service switch from OFF to GROUND SERVICE will not energize the auxiliary hydraulic pump power and the number 4 main cabin bus.

17. Bus Tie Relays (AC) DELETED in revision 34.

18. Bus Fail Lights DELETED in revision 34.




PAGE NO: 24-5





24 ELECTRICAL POWER

19. ***

Fine Frequency Controls

C 4 0

20. ***

Generator Fail Lights D 4 0

21. ***

Generator Overload Light

D 1 0 May be inoperative provided AC Loadmeters are operative.

22. Generator Unparalleled

Caution Lights C 4 3 (O) One may be inoperative provided:

a) All four Generators are operative,

b) Loadmeter for associated Generator is operative, and

c) Associated generator is selected onto the tie bus through use of the preferential circuit before paralleling Generators.

23. CSD Air and Oil Heat

Exchangers C 4 3 One may be inoperative provided

associated CSD is disconnected.




PAGE NO: 25-1





25 EQUIPMENT/ FURNISHINGS

1. ***

Lower Compartment Viewer

D 1 0

2. ***

Pressurized Water System Compressor

D 1 0

3. Crewmember Shoulder

Harness D - - Any in excess of those required for

flight deck crewmembers (including official observer in Forward Observers Seat) may be inoperative.

4. Flight Attendant Seats

(Single or Dual Position)

1) Required Flight

Attendant Seats B - - (M)(O) One seat or assembly (dual

position) may be inoperative provided: a) Affected seat position or seat

assembly is not occupied, b) Flight Attendant(s) displaced by

inoperative seat(s) occupies either an adjacent flight attendant seat or the Passenger Seat most accessible to the inoperative seat(s), so as to most effectively perform assigned duties,

c) Alternate operations procedures are established and used as published in crewmember manuals,

d) Folding type seat stows automatically or secured in the RETRACTED position, and

e) Passenger Seat assigned to Flight Attendant is placarded “FOR FLIGHT ATTENDANT USE ONLY”.




PAGE NO: 25-2







(Single or Dual Position) (Cont’d)

1) Required Flight

Attendant Seats (Cont’d)

NOTE 1: An automatic folding seat that

will not stow automatically is considered inoperative.

NOTE 2: A seat position with an

inoperative or missing restraint system is considered inoperative.

NOTE 3: Individual operators, when

operating with inoperative seats, will consider the locations and combinations of seats to ensure that the proximity to exits and distribution requirements of the applicable 14 CFR are met.

NOTE 4: If one side of a dual seat

assembly is inoperative and a flight attendant is displaced to the adjacent seat, the adjacent seat must operate normally.




PAGE NO: 25-3







(Single or Dual Position) (Cont’d)

2) Excess Flight

Attendant Seats C - - (M) May be inoperative provided:

a) Affected seat or seat assembly is not occupied, and

b) Folding type seat is stowed or secured in the RETRACTED position.

NOTE 1: An automatic folding seat that

will not stow automatically is considered inoperative.

NOTE 2: A seat position with an

inoperative or missing lap belt is considered inoperative.

3) All Cargo Configuration D - - May be inoperative provided affected

seat assembly is not occupied.

5. Megaphones

1) Passenger Configuration

D - - Any in excess of those required by 14 CFR may be inoperative or missing provided:

a) Inoperative megaphone is removed from the passenger cabin, and

b) Required distribution is maintained.

|| |

2) ***

Cargo Configuration D - 0




PAGE NO: 25-4






6. “Fasten Seat Belt

While Seated” Sign or Placard

C - - One or more signs or placards may be illegible or missing provided a legible sign or placard is visible from each occupied passenger seat.

||||

7. ***

Onboard Weight and Balance System

D - 0 (M) May be inoperative provided affected equipment is appropriately secured.

8. ***

Galley Equipment DELETED, included in Passenger Convenience Items.

9. Primary Observer Seat

(Including Associated Equipment)

A - - May be inoperative provided: a) A Passenger Seat in the

Passenger Cabin is made available to an FAA Inspector for the performance of official duties, and

b) Repairs are made within two flight days.

A - - May be inoperative provided:

a) Secondary observer’s seat is available to the FAA inspector for performance of official duties, and


|||||

A - - May be inoperative provided:

a) Required minimum safety equipment (Safety Belt and Oxygen) is available,

b) Seat is acceptable to the FAA Inspector for performance of official duties, and

c) Repairs are made within two flight days.

|




PAGE NO: 25-5






9. Primary Observer Seat

(Including Associated Equipment) (Cont’d)

NOTE 1: These provisos are intended

to provide for occupancy of the above Seats by an FAA Inspector when the minimum Safety Equipment (Oxygen and Safety Belt) is functional and the Inspector determines conditions to be acceptable.

NOTE 2: The Pilot in Command will

determine if the minimum Safety Equipment is functional for other persons authorized to occupy any Observers Seat(s).

1) ***

Lumbar Support C - - May be inoperative provided the Seat is acceptable to an FAA Inspector for the performance of official duties.

2) ***

Recline System B - - May be inoperative provided: a) Seat is fixed in an upright

position, and b) Seat is acceptable to an FAA

Inspector for the performance of official duties.

3) ***

Thigh Support(s) C - - May be inoperative provided the Seat is acceptable to an FAA Inspector for the performance of official duties.

4) ***

Arm Rest(s) C - - (M) May be inoperative provided: a) Seat is acceptable to an FAA

Inspector for performance of official duties, and

b) Affected Arm Rest(s) are stowed in the retracted position.




PAGE NO: 25-6






10. Cabin Emergency

Flashlight and Holder (Flight Attendant Position)

C - - May be inoperative provided crewmember assigned to the associated position has a flashlight of equivalent characteristics readily available.

|||||

11. Passenger Seat(s) D - - May be inoperative provided:

a) Seat does not block an Emergency Exit,

b) Seat does not restrict any passenger from access to the main aircraft aisle, and

c) The affected seat(s) are blocked and placarded “DO NOT OCCUPY”.

|

NOTE 1: A seat with an inoperative

seat belt is considered inoperative.

NOTE 2: Inoperative seats do not

affect the required number of Flight Attendants.

NOTE 3: Affected seat(s) may include

the seat(s) behind and/or adjacent outboard seats.

1) Recline Mechanism D - - (M) May be inoperative and seat

occupied provided seat is secured in the full upright position.

|||

D - - May be inoperative and seat occupied

provided seat back is immovable in full upright position.

|||




PAGE NO: 25-7






11. Passenger Seat(s)

(Cont’d)

2) Underseat Baggage

Restraining Bars C - - (O) May be inoperative provided:

a) Baggage is not stowed under seat with inoperative restraining bar,

b) Associated seat is placarded “DO NOT STOW BAGGAGE UNDER THIS SEAT”, and

c) Procedures are established to alert Cabin Crew of inoperative restraining bar.

3) Armrest |

a) Armrest with Recline Mechanism

D - - (M) May be inoperative or missing and seat occupied provided:

a) Armrest does not block an Emergency Exit,

b) Armrest does not restrict any passenger from access to the main aircraft aisle, and

c) If armrest is missing, seat is secured in the full upright position.

||||||||||

b) Armrest without

Recline Mechanism D - - May be inoperative or missing and seat

occupied provided. a) Armrest does not block an

Emergency Exit, and b) Armrest does not restrict any

passenger from access to the main aircraft aisle.

|||||||

12. Lavatory Equipment DELETED, included in Passenger

Convenience Items. Rev 42 See Ch 38.




PAGE NO: 25-8






13. ***

Non-Essential Equipment and Furnishings(NEF)

- 0 May be inoperative, damaged or missing provided that the item(s) is deferred in accordance with the operator’s NEF deferral program. The NEF program, procedures and processes are outlined in the operator’s (insert name) Manual. (M) and (O) procedures, if required, must be available to the flight crew and included in the operator’s appropriate document.

|||||||||||

NOTE: Exterior lavatory door ash trays

are not considered NEF items. ||

14. ***

Courier Seat(s) and Seat Lap Belt(s)

D - - (M) May be inoperative provided: a) Seat(s) is not required for the

operation conducted, b) Affected Seat(s) is appropriately

secured or deactivated so that it does not block Emergency Egress to an Aisle or Exit, and

c) Affected Seat(s) is blocked using an accepted procedure and placarded “DO NOT OCCUPY”.

1) ***

Recline System(s) D - - (M) May be inoperative provided the affected Seat(s) is secured in the upright position.

2) ***

Arm Rest(s) D - - (M) May be inoperative provided affected Arm Rest(s) is stowed in the retracted position.

15. Flotation Devices D - - Any in excess of those required by

14 CFR may be inoperative.




PAGE NO: 25-9






16. ***

Additional Observer Seat(s) (Including Associated Equipment)

D 1 0 (M) May be inoperative provided affected Seat(s) is secured or deactivated so that it does not block Emergency Egress to an Aisle or Exit.

NOTE: The Pilot-in-Command will

determine if the minimum Safety Equipment is functional for persons authorized to occupy any Observers Seat(s).

1) ***

Lumbar Support(s) D - 0

2) ***

Recline System(s) D - 0 (M) May be inoperative, and Seat(s) occupied, provided Seat(s) is secured in upright position.

3) ***

Thigh Support(s) D 1 0

4) ***

Arm Rest(s) D - 0 (M) May be inoperative provided affected Arm Rest(s) are stowed in retracted position.

17. Flight Crew Seats

1) ***

Lumbar Support(s) C - 0 May be inoperative provided Seat(s) is acceptable to the affected Crewmember(s).

2) ***

Recline System(s) A - 0 (M) May be inoperative provided: a) Seat(s) is secured in an upright

position acceptable to the affected Crewmember(s), and


(Continued)




PAGE NO: 25-10






17. Flight Crew Seats

(Cont’d)

3) ***

Thigh Support(s) C - 0 May be inoperative provided Seat is acceptable to the affected crewmember(s).

4) ***

Arm Rest(s) B - - (M) May be inoperative provided: a) Affected Arm Rest(s) is stowed

in the retracted position, and b) Seat(s) is acceptable to the

affected Crewmember(s).

18. Emergency Medical

Equipment |

|

1) Automatic External Defibrillator (AED) and/or Associated Equipment

A - 0 (O) May be incomplete, missing or inoperative provided:

a) AED is resealed in a manner that will identify it as a unit that can not be mistaken for a fully serviceable unit, and

b) Repairs or replacements are made within 3 flight cycles.

||||||||

D - - Any in excess of those required by 14

CFR may be incomplete, missing, or inoperative.

|||

2) Emergency Medical Kit

(EMK) and/or Associated Equipment

A - 0 (O) May be incomplete, missing or inoperative provided:

a) EMK is resealed in a manner that will identify it as a unit that can not be mistaken for a fully serviceable unit, and


||||||||

(Continued)




PAGE NO: 25-11






18. Emergency Medical

Equipment (Cont’d)

2) Emergency Medical Kit (EMK) and/or Associated Equipment (Cont’d)

D - - Any in excess of those required by

14 CFR may be incomplete, missing, or inoperative.

|||

3) First Aid Kit (FAK)

and/or Associated Equipment

A - - (O) If more than one is required by 14 CFR, only one of the required first aid kits may be incomplete, missing or inoperative provided:

a) FAK is resealed in a manner that will identify it as a unit that can not be mistaken for a fully serviceable unit, and


||||||||||

D - - Any in excess of those required by

14 CFR may be incomplete, missing, or inoperative.

|||

19. Exterior Lavatory Door

Ashtrays

1) Airplanes With More

Than One Exterior Lavatory Door Ashtray Installed

A - - One may be missing provided it is replaced within 10 calendar days.

(Continued)




PAGE NO: 25-12






19. Exterior Lavatory Door

Ashtrays (Cont’d)

2) Airplanes With Only

One Exterior Lavatory Door Ashtray Installed

A 1 0 May be missing provided it is replaced within 3 calendar days.

20. Galley Waste

Receptacles Access Door/Covers

C - - (M)(O) May be inoperative provided: a) Container is empty and the

access is secured to prevent waste introduction into the compartment, and

b) Procedures are established to ensure that sufficient galley waste receptacles are available to accommodate all waste that may be generated on a flight.

|

21. Cargo Restraint

Systems C - - (M) May be inoperative, or missing

providing acceptable cargo loading limits from an approved source, i.e., an Approved Cargo Loading Manual, Cargo Handling Manual, or Weight and Balance Document are observed.

C - - May be inoperative, or missing

provided cargo compartment remains empty.




PAGE NO: 25-13






22. Overhead Storage

Bin(s)/Cabin and Galley Storage Compartment/ Closets

C - - (M) May be inoperative provided: a) Procedures are established to

secure compartment CLOSED, b) Associated bin or compartment

is prominently placarded DO NOT USE,

c) Any emergency equipment located in affected compartment is considered inoperative, and

d) Affected compartment is not used for storage of any item(s) except for those permanently affixed.

||||||||||||||

NOTE: If no partitions are installed, the

entire overhead storage compartment is considered one bin or compartment.

|||

C - - (M) (O) May be inoperative provided:

a) Affected door(s) is removed, b) Associated bin or compartment

is not used for storage of any items, except those permanently affixed,

c) Associated bin or compartment is prominently placarded

DO NOT USE, d) Procedures are established and

used to alert crew members and passengers of inoperative bins, and

e) Passengers are briefed that associated bin or compartment is not used.

||||||||||||||||

(Continued)




PAGE NO: 25-14






22. Overhead Storage

Bin(s)/Cabin and Galley Storage Compartment/ Closets (Cont’d)

NOTE 1: If no partitions are installed,

the entire overhead storage compartment is considered one bin or compartment.

||||

NOTE 2: Any emergency equipment

located in the associated compartment (permanently affixed) is available for use.

||||

1) ***

Storage Compartment Key Locks

D - 0 (M) May be inoperative in the unlocked position provided doors can be secured by other means.

|||

23. Main Cabin/Galley

Entry Door Restraining Straps

D - 0 (O) May be inoperative or missing provided alternate procedures are established and used.




PAGE NO: 26-1





26 FIRE PROTECTION

1. Portable Fire Extinguishers

D - - Any in excess of those required by 14 CFR may be inoperative or missing provided:

a) Inoperative fire extinguisher is tagged inoperative, removed from the installed location, and placed out of sight so it can not be mistaken for a functional unit, and

b) Required distribution is maintained.

|

2. Engine Fire Detection

System

1) Fire Detector Function DELETED in revision 38.

2) Cockpit Test Feature C 1 0 (M) May be inoperative provided an alternate procedure is established and used to assure integrity of the system once each flight day.

3) ***

Dual Loop System (Including Loop Selector Switches)

C 8 4 (M)(O) One complete loop (A or B) one each engine may be inoperative provided remaining Loop is operative.

3. Firewall Shut-off

Systems DELETED in revision 34.




PAGE NO: 26-2





26 FIRE PROTECTION

4. Power Plant Fire Extinguisher Agent Low Pressure Light

1) Squib Test Function DELETED in revision 38.

2) Low Pressure Function C - - (M) May be inoperative provided an alternate procedure is established to ensure system cylinder pressure is normal once each flight day.

5. Short Discriminator

Warning Lights (Series 60 and 70)

C 4 0

6. ***

Main Deck Cargo Compartment Smoke Detectors

C - - May be inoperative provided appropriate AFM Limitations and Procedures are applied.

7. Engine Fire Warning

System

1) Engine Compartment

Fire Warning Light (Fire Shutoff Lever Handle)

DELETED in revision 38.

2) Master Fire Warning

Light (Pilots Glareshield)


(Continued)




PAGE NO: 26-3





26 FIRE PROTECTION

7. Engine Fire Warning System (Cont’d)

3) Master Repeater Fire

Warning Light (F/E Panel

C 1 0

8. Lavatory Smoke

Detection Systems C - - (M)(O) For each lavatory, the lavatory

smoke detection system may be inoperative provided:

a) Lavatory waste receptacle is empty,

b) Associated lavatory door is locked CLOSED and placarded, “INOPERATIVE – DO NOT ENTER”, and

c) Lavatory is used only by crewmembers.

|

NOTE 1: These provisos are not

intended to prohibit lavatory use or inspections by crewmembers.

NOTE 2: Lavatory Smoke Detection

System is not required for all-cargo operations.

9. Lavatory Fire

Extinguisher System C - - For each lavatory, the Lavatory Fire

Extinguisher System may be inoperative provided Lavatory Smoke Detector System is operative.

(Continued)




PAGE NO: 26-4





26 FIRE PROTECTION

9. Lavatory Fire Extinguisher Systems (Cont’d)

C - - (M)(O) For each lavatory, the lavatory

fire extinguisher system may be inoperative provided:

a) Lavatory waste receptacle is empty,

b) Associated lavatory door is locked CLOSED and placarded, “INOPERATIVE – DO NOT ENTER”, and

c) Lavatory is used only by crewmembers.

|

NOTE 1: These provisos are not

intended to prohibit lavatory use or inspections by crewmembers.

|

NOTE 2: A Lavatory Fire Extinguisher

System is not required for all-cargo operations.

|

10. Cargo Compartment

Fire Detection/ Suppressions Systems

C - 0 (O) May be inoperative provided procedures are established and used to ensure the associated compartment remains empty, or is verified to contain only empty cargo handling equipment, ballast (ballast may be loaded in ULDs), and/or Fly Away Kits.

|||||||

NOTE 1: Operator MELs must define

which items are approved for inclusion in the Fly Away Kits, and which materials can be used as ballast.

||||

NOTE 2: (ALL Cargo Aircraft Only)

Class E cargo compartments require only the installation of smoke or fire detection systems (not suppression).

||||




PAGE NO: 26-5





26 FIRE PROTECTION

10. Cargo Compartment Fire Detection/ Suppression Systems (Cont’d)

1) Lower Cargo

Compartment Smoke Detection System STC ST00746LA-D, STC ST00984LA-D

a) Smoke Detectors One inoperative in

each compartment. No messages annunciated on the MX display

C - - (O) One smoke detector in each compartment may be inoperative provided the System OK indicator on the control display unit (CDU) is illuminated.

NOTE: If a detector is inoperative or

has a low battery, the MX indicator will also be illuminated.

(Continued)




PAGE NO: 26-6





26 FIRE PROTECTION


1) Lower Cargo

Compartment Smoke Detection System STC ST00746LA-D, STC ST00984LA-D (Cont’d)

a) Smoke Detectors

(Cont’d)

More than one

inoperative in each compartment. MX display message of: Models 62,62F FWD INOP AFT INOP Models 61, 61F, 63, 63F, 71, 71F, 73, 73F FWD A INOP, FWD B INOP, AFT C INOP, AFT D INOP

C - 0 (O) More than one detector may be inoperative in each compartment provided:

a) SYS OK light on CDU is illuminated, and

b) Procedures are established and used to ensure the associated compartment remains empty, or is verified to contain only empty cargo handling equipment, ballast (ballast may be loaded in ULDs), and/or Fly Away Kits.

NOTE 1: Operator MELs must define

which items are approved for inclusion in the Fly Away Kits, and which materials can be used as ballast.

(Continued)




PAGE NO: 26-7





26 FIRE PROTECTION


1) Lower Cargo

Compartment Smoke Detection System STC ST-00746LA-D, STC ST00984LA-D (Cont’d)

a) Smoke Detectors

(Cont’d)

NOTE 2: Class E cargo compartments

require only the installation of smoke or fire detection systems (not suppression).

Low Battery C - 0 (O) Battery Voltage may be low

provided the SYS OK light on the CDU is illuminated.

NOTE: The MX light on the CDU will

remain illuminated.

b) All other faults annunciated by MX display.

C - 0 (O) May be displayed provided the SYS OK light on the CDU is illuminated.

c) F/Es Lower Cargo Fire

Light C 1 0 May be inoperative provided Lower

Cargo Fire Light on the CDU is operative.

(Continued)




PAGE NO: 26-8





26 FIRE PROTECTION


1) Lower Cargo

Compartment Smoke Detection System STC ST00746LA-D, STC ST00984LA-D (Cont’d)

d) MX Display Pixels C - - Up to three non-consecutive pixels per

display section may be inoperative provided the display remains readable.

e) MX Test Switch B 1 0

f) MX Setup Switch C 1 0

2) Suppression Control Units (SCU) Models 62, 62F (STC ST00984LA-D)

C 2 0 May be inoperative provided procedures are established and used to ensure the lower cargo compartments remain empty, or are verified to contain only empty cargo handling equipment, ballast, (ballast may be loaded in ULDs), and/or Fly Away Kits.

NOTE: Class E cargo compartments

require only the installation of smoke or fire detection systems (not suppression).




PAGE NO: 27-1





27 FLIGHT CONTROLS

1. Stabilizer Trim Systems

1) Stabilizer Trim

Hydraulic System DELETED in revision 38.

2) Stabilizer Alternate

Trim System DELETED in revision 38.

3) Control Wheel

Stabilizer Trim Switches

C 2 1 One may be inoperative provided: a) Pilot Flying has an operative

Control Wheel Stabilizer Trim Switch, and

b) Suitcase handle control and alternate trim system are operative.

2. Pitch Trim

Compensator (PTC) System

C 1 0 May be inoperative provided flight is conducted in accordance with applicable AFM Limitations and Procedures.

3. Pitch Trim

Compensator Actuator C 1 0 (M) May be inoperative provided

Actuator is deactivated FULLY retracted, or substitute fixed link, equivalent to a retracted actuator, is installed.

4. PTC Extend Warning

Light and Mechanical Indicators

C 2 0 May be inoperative provided PTC is considered inoperative.

1) Warning Light Push to

Test Function C 1 0 (M) May be inoperative provided PTC

System, including Warning Light, is verified to be operative before each departure.

|




PAGE NO: 27-2





27 FLIGHT CONTROLS

5. Horizontal Stabilizer Indicator


6. Flap Position Indicator

Pointers C 2 1 (O) One may be inoperative provided

visual check of flap position is accomplished before each departure.

7. Takeoff Function

Warning Horn DELETED in revision 34.

8. Wing Slot Door

Indicator Light System C 1 0 (O) May be inoperative provided:

a) A visual check of wing slot position is made after flap and slot positions are selected for takeoff,

b) Flaps and slots are not moved after the check until after takeoff, and

c) Landing speed and distance are increased to account for the slots in the CLOSED position for landing.

NOTE: If buffeting occurs above 250

KIAS and it cannot be determined that the slots are closed, observe maximum speed of 280 KIAS/M .80. If the aircraft is operated with slot(s) open at speeds in excess of 230 KIAS/M .46, a complete inspection of the slot doors, door mechanism and supporting structures shall be accomplished prior to the next departure.




PAGE NO: 27-3





27 FLIGHT CONTROLS

9. Elevator Position Indicator

C 1 0 (O) May be inoperative provided proper elevator operation is verified in accordance with Airworthiness Directive 78-01-15.

10. Stabilizer In-Motion

Warning System C 1 0 May be inoperative provided PTC is

operative.

11. Ground Spoiler

Automatic Actuation System

C 1 0 May be inoperative provided: a) Manual System is operative,

and b) AFM performance limitations

are observed.

NOTE: AFM Limitations for some noise

abatement STCs require the Ground Spoiler Automatic Actuation System be operative for dispatch.

12. ***

Elevator Outboard Dampers

D 2 0 (M) May be inoperative provided: a) Elevator Outboard Dampers are

disconnected, and b) Associated “Operating Links”

are removed using an accepted maintenance procedure.

13. Standby Rudder

Accumulator Pressure Gauge

C 1 0 (M) May be inoperative provided, before each departure, adequate Accumulator Precharge Pressure is verified by an acceptable alternate procedure.

|




PAGE NO: 27-4





27 FLIGHT CONTROLS

14. Spoiler Accumulator Pressure Gauge

C 1 0 (M) May be inoperative provided adequate accumulator precharge pressure is verified once each flight day by an acceptable alternate procedure.

15. Standby Rudder Pump

Operating Light Push to Test Function

C 1 0 (M) May be inoperative provided Rudder Pump Operating Light is verified to be operative before each departure.

16. Rudder HI Indicator

Light STC SA8106SW C 1 0 May be inoperative provided Airspeed

is limited to 300 IAS knots when the yaw damper is engaged.




PAGE NO: 28-1





28 FUEL

1. Main Tank Fuel Boost Pumps

1) Series 10, 20, 30 and

40 Aircraft C 4 3 (O) One may be inoperative provided:

a) Fuel Tank Temperature Indicator System is operative,

b) Fuel Temperature does not exceed 21 degrees C, and

c) Flight remains at or below FL300.

2) Series 50, 60, and 70

Aircraft DELETED in revision 38.

2. Alternate Tank Fuel

Boost Pumps

1) All Models C - 0 May be inoperative provided:

a) Associated Fuel Tank remains empty, and

b) AFM fuel balance and distribution limitations are observed.

2) Series 10, 20, 30, 40,

50, and Models 61 and 71 Aircraft

C 4 3 One may be inoperative provided: a) All other systems of the

associated fuel tank and its related main tank are operative,

b) All Fuel Quantity Indicators are operative for Tanks containing fuel,

(Continued)




PAGE NO: 28-2





28 FUEL

2. Alternate Tank Fuel Boost Pumps (Cont’d)

2) Series 10, 20, 30, 40,

50, and Models 61 and 71 Aircraft (Cont’d)

c) Sufficient fuel is carried to provide 2,000 pounds fuel in excess of that (including reserves) required for the flight,

d) Fuel temperature at takeoff is not in excess of 21 degrees C,

e) At or above FL300 thrust does not exceed Maximum Cruise thrust while using fuel from associated Alternate Tank, and

f) Last 500 pounds fuel is not used in associated Alternate Tank.

|

3) Models 62, 63, 72, and

73 Aircraft C 2 1 One may be inoperative provided:

a) All other systems of the associated fuel tank and its related main tank are operative,

b) All fuel Quantity Indicators are operative for Tanks containing fuel,

(Continued)




PAGE NO: 28-3





28 FUEL

3) Models 62, 63, 73, and 73 Aircraft (Cont’d)

c) Sufficient fuel is carried to

provide 2,000 pounds fuel in excess of that (including reserves) required for the flight,

d) Fuel temperature at takeoff is not in excess of 21 degrees C,

e) At or above FL300 thrust does not exceed Maximum Cruise Thrust while using fuel from associated Alternate Tank, and

f) Last 500 pounds fuel is not used in associated Alternate Tank.

3. ***

Center Auxiliary Fuel Tank Boost Pumps

C 2 0 (M)(O) May be inoperative provided: a) Affected Center Auxiliary

Booster Pump(s) are deactivated,

b) Remaining Fuel is verified using an accepted procedure,

c) Operating Zero Fuel Weight plus fuel in the associated Auxiliary Tank does not exceed the maximum allowable Zero Fuel Weight, and

(Continued)




PAGE NO: 28-4





28 FUEL

3. ***

Center Auxiliary Fuel Tank Boost Pumps (Cont’d)

d) The airplane is loaded to

ensure that it is within CG Limits at all times during the flight with the fuel in the Center Wing and Forward Aux Tanks.

D 2 0 (M)(O) May be inoperative provided:

a) Fuel is not carried in the center wing or forward auxiliary tanks,

b) Center wing and forward auxiliary tanks are verified empty before each flight, and

c) Affected center auxiliary boost pump(s) are deactivated.

C 2 1 (M)(O) One may be inoperative

provided: a) Affected Center Auxiliary

Booster Pump is deactivated, b) Operating Zero Fuel Weight

plus fuel in the associated Auxiliary Tank(s) does not exceed the maximum allowable Zero Fuel Weight,

|

(Continued)




PAGE NO: 28-5





28 FUEL

3. Center Auxiliary Fuel Tank Boost Pumps (Cont’d)

c) Airplane is loaded to ensure

that it is within CG Limits at all times during the flight with the center wing and forward aux tanks either empty or at their initial loading, and

d) The quantity in the remaining tanks must be adequate to reach an alternate destination should the remaining pump fail.

|

4. Reservoir Feed Pumps C 4 3 (O) One may be inoperative provided:

a) Sufficient fuel is carried to provide 2,000 pounds fuel in excess of that (including reserves) required for the flight, and

b) Fuel is managed so that no less than 2000 pounds fuel is in the associated tank at any time.

5. Reservoir Feed Pump

Low Pressure Caution Lights

C 4 3 One may be inoperative provided associated Reservoir Feed Pump is inoperative.

C 4 2 Two may be inoperative provided all

reservoir Feed Pumps are operative.




PAGE NO: 28-6





28 FUEL

6. ***

Fuel Pump Pressure Caution Lights (Main Engine Pump Low Differential)

D - 0

7. Fuel Level Control

Valve Systems (Tank Fuel Level Control System and Associated Fuel Level Pilot Valve and Control Valve Switch)

1) All Tanks C - 0 (O) May be inoperative provided:

a) Affected Valve is OPEN, b) Associated Tank Fill Valve is

operative, c) Fuel Quantity Indicator for

affected tanks are operative, and

d) Fuel Level is controlled manually.

2) Main Tanks C 4 3 (M)(O) One may be inoperative

provided: a) Affected valve is verified

CLOSED, b) Associated Main Tank Fill Valve

is secured and placarded CLOSED, and

c) All Main Tank Fuel Quantity Indicators are operative.

(Continued)




PAGE NO: 28-7





28 FUEL

7. Fuel Level Control Valve Systems (Tank Fuel Level Control System and Associated Fuel Level Pilot Valve and Control Valve Switch) (Cont’d)

3) Alternate Tanks (Series

10, 20, 30, 40, 50 and Models 61 and 71)

C 4 3 (M) One may be inoperative provided: a) Affected valve is CLOSED, b) Associated Alternate Tank Fill

Valve is secured and placarded CLOSED, and

c) Alternate procedure is established and used to verify Alternate Tank Fuel Quantity before each departure.

4) ***

Auxiliary Tanks C - - (M) One may be inoperative provided: a) Affected Valve is CLOSED, b) Associated Auxiliary Tank Fill

Valve is secured and placarded CLOSED, and

c) An Alternate procedure is established and used to verify Auxiliary Tank Fuel Quantity before each departure.

D - - (M) May be inoperative provided

associated Fuel Tank is verified empty.




PAGE NO: 28-8





28 FUEL

8. Fuel Pressure Indicators

C 4 3 (M) One may be inoperative provided: a) Associated Fuel Systems

(including Feed Pump, Feed Pump Low Pressure Warning, Tank Boost Pump and Engine Driven Boost Pump) are operative, and

b) Associated Engine Fuel Flow Indicator is operative.

9. Fuel Dump System C 1 0 May be inoperative provided:

a) Takeoff Gross Weight is less than 105 percent of certificated Maximum Landing Weight, and

b) En route engine out performance does not require fuel dumping.

1) Electric Mode C 1 0 May be inoperative provided Manual

Fuel Dump System is operative.

10. Fuel Tank Quantity Totalizer

C 1 0

1) ***

Repeater D 1 0

11. Fuel Quantity

Indicating Systems

1) Main Tank Indicators C 4 3 (M)(O) One may be inoperative

provided: a) Automatic Fuel Level Control

System including Lights and fuel Flow indicators for the associated engine are operative,

(Continued)




PAGE NO: 28-9





28 FUEL

11. Fuel Quantity Indicating Systems (Cont’d)

1) Main Tank Indicators

(Cont’d)

b) With one indicator inoperative,

fuel quantity in the associated tank is verified using an alternate procedure (such as dripsticking)

c) With more than one Fuel Quantity Indicator inoperative on the aircraft, fuel quantity in all fueled tanks is verified using an alternate procedure (such as dripsticking), and

d) A Fuel Log is used.

2) Alternate Tank Indicators

a) (Series 10, 20, 30, 40,

50 and models 61 and 71)

C 4 2 (M)(O) Two Alternate Tank indicators may be inoperative provided:

a) Automatic Fuel Level Control System including Lights and fuel Flow indicators for the associated engines are operative,

b) No more than one indicator is inoperative on symmetrically opposite tanks,

(Continued)




PAGE NO: 28-10





28 FUEL


2) Alternate Tank

Indicators (Cont’d)

a) (Series 10, 20, 30, 40,

50 and models 61 and 71) (Cont’d)

c) No more than one Indicator is inoperative within each Engine Tank System,

d) With one Fuel Quantity indicator inoperative, Fuel Quantity in the associated tank is verified using an alternate procedure (such as dripsticking)

e) With more than one Fuel Quantity indicator inoperative, on the aircraft, Fuel Quantity in all fueled tanks is verified using an alternate procedure (Such as dripsticking), and

f) A Fuel Log is used.

b) (Models 62, 63, 72, 73) C 2 1 (M)(O) One Alternate Tank indicator may be inoperative provided:

a) Automatic Fuel Level Control system including Lights and fuel Flow indicators for the associated engine are operative,

b) No more than one Indicator is inoperative within each Engine Tank System,

(Continued)




PAGE NO: 28-11





28 FUEL


2) Alternate Tank

Indicators (Cont’d)

b) (Models 62, 63, 72, 73)

(Cont’d) c) With one indicator inoperative,

fuel quantity in the associated tank is verified using an alternate procedure (such as dripsticking)

d) With more than one Fuel Quantity indicator inoperative on the aircraft, fuel quantity in all fueled tanks is verified using an alternate procedure (such as dripsticking), and

e) A Fuel Log is used.

c) All Series C - 0 May be inoperative provided: a) Associated Alternate Tanks are

fueled symmetrically, b) Associated Alternate Fuel

Tanks are not used, and c) Associated Main Tank Fuel

Quantity Indicator(s) are operative.

D - 0 May be inoperative provided:

a) Associated Alternate Tanks remain empty, and

b) Associated Alternate Tanks are verified empty after each refueling.

(Continued)




PAGE NO: 28-12





28 FUEL


3) Center Wing Auxiliary

Fuel Tank Quantity Indicating System

C 1 0 (M) May be inoperative provided an alternate procedure is established to verify Fuel Quantity before each departure.

D 1 0 (M) May be inoperative provided the

associated fuel tank remains empty and is verified empty.

4) Leading Edge Auxiliary

Fuel Tank Indicating System

C 1 0 (M) May be inoperative provided an alternate procedure is established to verify Fuel Quantity before each departure.

D 1 0 (M) May be inoperative provided the

associated fuel tank is verified empty.

5) Fuel Quantity Gauge Set Indices (Bugs) (Includes Set Knob and Fuel Quantity Indicator Index Switch)

a) Main Tanks C 4 3 (M)(O) One may be inoperative

provided: a) Affected Set Index Switch is

failed to Fill Valve CLOSED, b) Affected Main Tank Fill Valve is

secured CLOSED, and c) All Main Tank Fuel Quantity

Indicators are operative. (Continued)




PAGE NO: 28-13





28 FUEL

5) Fuel Quantity Gauge Set Indices (Bugs) (Includes Set Knob and Fuel Quantity Indicator Index Switch) (Cont’d)

a) Main Tanks (Cont’d) C 4 0 (O) May be inoperative provided:

a) Affected Set Index Valve Switch is failed to Fill Valve OPEN,

b) All main Tank fuel Quantity Indicators are operative,

c) Fuel tank Quantity can be controlled manually, and

d) Associated Fuel Level Control Valve is operative.

b) Alternate Tanks (All

Models) C - 0 (O) May be inoperative provided:


b) Fuel Tank Quantity level can be controlled manually during refueling or transfer, and

c) Associated Fuel Level Control Valve is operative.

(Continued)




PAGE NO: 28-14





28 FUEL


c) Alternate Tanks (Series

10, 20, 30, 40, 50 and Models 61 and 71)

C 4 3 (M) One may be inoperative provided: a) Affected Set Index Switch is

failed to Fill Valve CLOSED, b) Alternate Tank Fill Valve is

secured and placarded CLOSED, and

c) Alternate procedures are established to verify Alternate Tank Fuel Quantity before each departure.

d) Auxiliary Tanks C - 0 (O) May be inoperative provided:


b) Fuel Tank Quantity level can be controlled manually during refueling or transfer, and


(Continued)




PAGE NO: 28-15





28 FUEL


d) Auxiliary Tanks

(Cont’d) C - 0 (M) May be inoperative provided:

a) Affected Set Index Switch is failed to Fill Valve CLOSED,

b) Auxiliary Tank Fill Valve is secured and placarded CLOSED, and

c) Alternate procedures are established to verify Auxiliary Tank Fuel Quantity before each departure.

D - 0 (M) May be inoperative provided the

Affected Fuel Tank is verified empty.

12. Center Wing Auxiliary Fuel Tank Quantity Indicating System

MOVED to item 28-11.

13. Leading Edge Auxiliary

Fuel Tank Indicating System

MOVED to item 28-11.




PAGE NO: 28-16





28 FUEL

14. Fuel Tank Temperature Indicating System

C 1 0 (O) May be inoperative provided Ram Air Temperature (RAT) or Total Air Temperature (TAT) Indicator is operative.

C 1 0 (O) May be inoperative provided

alternate procedures are established to preclude fuel going below AFM minimum temperature.

15. Pressure Fueling

System C 1 0 (M) May be inoperative provided

alternate fueling procedures are established and used.

16. Main Tank Fill Valve C 4 3 (M) One may be inoperative provided:

a) Inoperative Main Tank Fill Valve is secured CLOSED, and

b) All Main Tank Quantity Indicators are operative.

C 4 3 (M) One may be inoperative provided:

a) Inoperative Main tank Fill Valve is secured OPEN,

b) All Main tank Quantity Indicators are operative, and





PAGE NO: 28-17





28 FUEL

17. Alternate Tank Fill Valves

1) Series 10 through 50

and Models 61, 61F, 71, and 71F Aircraft

C 4 3 (M) One may be inoperative provided: a) Alternate Tank Fill Valve is

secured CLOSED after fueling, and

b) An alternate procedure is established and used to verify Alternate Tank Fuel quantity before each departure.

2) Models 62, 62F, 63,

63F, 72, 72F, 73 and 73F


18. ***

Auxiliary Tank Fill Valves

C - - (M) May be inoperative provided: a) Affected Valve is secured

CLOSED, and b) An alternate procedure is

developed and used to verify Auxiliary Tank fuel quantity before each departure.

D - - (M) May be inoperative provided the

Associated Fuel tank is verified empty.

19. Auto Fill Lights and Test System

C - 0 May be inoperative provided Fuel Quantity Indicators are operative for tanks associated with inoperative Lights.




PAGE NO: 28-18





28 FUEL

20. ***

Engine Fuel Temperature Indicating System

D 4 1 Three may be inoperative provided: a) Operative System is associated

with an inboard engine, and b) Associated Generator and CSD

are operative. D 4 0 May be inoperative provided Tank Fuel

Temperature is less than 80 degrees F before each takeoff.

21. Outboard Alternate

Fuel Tank Low Level Lights


and Models 61, 61F, 71 and 71F aircraft

C 2 0 May be inoperative provided associated Fuel Quantity Indicators are operative.

C 2 0 May be inoperative provided

associated Fuel Tank remains empty.

2) Models 62, 62F, 63, 63F, 72, 72F, 73, and 73F


22. Outboard Main Fuel

Tank Low Level Lights (Models 62, 62F, 63, 63F, 72, 72F, 73, and 73F)

C 2 1 One may be inoperative provided: a) Associated Tank Fuel Quantity

Indicating system is operative, and

b) Associated Fuel level Control Valve Indicating (Blue) Light is operative.




PAGE NO: 28-19





28 FUEL

23. Centerwing Sump and Crossfeed Manifold Scavenge Pump System (Models 62, 62F, 63, 63F, 72, 72F, 73, and 73F)

D 1 0 May be inoperative provided: a) Operating Zero Fuel Weight

plus 262 pounds does not exceed the maximum allowable Zero Fuel Weight, and

b) Scavenged Fuel is not required for the flight.

24. Dripsticks (Mag. Sticks) C - 0 (M) May be inoperative provided

alternate procedures are established and used to verify fuel quantity in associated tanks.

C - 0 May be inoperative provided

associated Fuel Tank remains empty.

25. ***

Refueling Control Panel Quantity Indicators

D - 0 (M) May be inoperative provided alternate procedures are established to verify fuel quantity in associated tank.

26. ***

Refueling Control Panel Crossfeed Caution Light (Amber)

D 1 0

27. Pressure Refueling

Adapter Caps C 4 2 (M) Two may be inoperative or missing

provided: a) Refueling receptacle is free of

contamination before each refueling,

b) No leakage exists after refueling, and

c) All Fuel Tank Quantity Indicators are operative.




PAGE NO: 28-20





28 FUEL

28. Tank Selector Valves A 4 3 (M)(O) One may be inoperative provided:

a) Valve is secured in Main “To Engine”,

b) Fuel in associated Alternate Tank is not required for the Flight, and

c) Repair is made within three Flight Days.

29. Alternate Tank Refill

Systems (No. 1 and No. 4 Refill Switches and Refill Solenoids) (Models 62, 62F, 63, 63F, 72, 72F, 73 and 73F)

C 2 0 (M) May be inoperative provided: a) Associated Tank Fill Valve is

operative, and b) Alternate procedures are

established and used to maintain fuel level.

NOTE: If normal fuel management can

not be regained, reduce aircraft speed to 260 KIAS or .75M until AFM Fuel Management Schedule is reestablished.

30. ***

Backup Fuel Transfer (Models 73, 73F with STC ST00069BO)

C 2 0 (O) May be inoperative provided: a) Associated Backup Fuel

Transfer Switch is OFF, and b) Associated fuel tank level can

be controlled manually during refueling or transfer.




PAGE NO: 29-1





29 HYDRAULIC POWER

1. Engine Driven Pump Bypass Feature


2. Filter and Relief Valve DELETED in revision 34.

3. System Pressure Gauge


4. Auxiliary Electric Pump DELETED in revision 34.

5. Oil Temperature Indicator

C 1 0 May be inoperative provided Over Temperature Caution Light is operative.

6. Over Temperature

Caution Light C 1 0 May be inoperative provided oil

temperature Indicator is operative.

7. Hydraulic Oil Quantity Indicating System

1) Hydraulic Oil Quantity

Gauge C 1 0 (M) May be inoperative provided:

a) Hydraulic Reservoir Low Quantity Indication Light is installed and operative,

b) Emergency Low Level Warning Indication is operative,

c) Hydraulic oil Temperature Indicator is operative, and

d) Hydraulic Reservoir is checked for proper quantity before each departure.

2) Hydraulic Oil Low

Quantity Light D 1 0 May be inoperative provided Hydraulic

Oil Quantity Gauge is operative.




PAGE NO: 29-2





29 HYDRAULIC POWER

8. Brake Pressure Gauge DELETED in revision 34.

9. ***

Engine Driven Pump Low Pressure Caution Lights

D 2 0

10. ***

Thrust Reverser Auxiliary Pump

C 1 0

11. ***

Auxiliary Pump Surge Damper

C 1 0

1) Pressure Gauge C 1 0 (M) May be inoperative provided

adequate Accumulator Precharge Pressure is verified once each flight day using an acceptable alternate procedure.

12. ***

Empennage Accumulator (Horizontal Stabilizer and Rudder System)

C 1 0

13. ***

Reservoir Low Pressure Light (Series 60 and 70)

C 1 0 (O) May be inoperative provided Reservoir Air Pressure is verified from the left Main Wheel Well gauge before each departure.

14. Hydraulic System

Pressure Indicators C - 1

15. ***

Nose Wheel Steering Hydraulic Pressure Gauge

D 1 0




PAGE NO: 29-3





29 HYDRAULIC POWER

16. Rudder HI Indicator Light STC #SA8106SW

Moved to chapter 27, Revision 43.

17. General System

Accumulator Pressure Gauge

C 1 0 (M) May be inoperative provided adequate Accumulator Precharge Pressure is verified before each flight using an acceptable alternate procedure.




PAGE NO: 30-1






1. Horizontal Stabilizer

De-Icing System C 1 0 (O) May be inoperative provided

aircraft is not operated in known or forecast icing conditions.

2. Wing De-Icing System C 1 0 (O) May be inoperative provided


3. Airfoil De-Icing Timers C 2 1 C 2 0 (O) May be inoperative provided


4. Pitot Heaters

1) Captains, First Officers, and (if installed) Alternate Pitot Heater(s)

B - - (O) One may be inoperative provided aircraft is not operated in known or forecast icing conditions.

2) ***

FDR Pitot Heater A 1 0 May be inoperative provided: a) All remaining Pitot Tube

Heaters are operative, b) Cockpit Voice Recorder (CVR)

is operative, and c) Repairs are made within three

flight days.

5 Windshield Electric Heating System

C 1 0 May be inoperative provided flight is conducted in accordance with applicable AFM Limitations.




PAGE NO: 30-2






6. Windshield Rain

Removal (Air) Systems C 2 0 May be inoperative provided aircraft is

not operated in precipitation within 5 Nautical Miles of the airport of takeoff or intended landing

7. ***

Rain Repellent System C 1 0

8. Scoop Anti-Ice System C 1 0 (M) May be inoperative provided:

a) Scoop anti-ice valves are verified closed,

b) Pitot Line Heaters are operative on aircraft with Air Conditioning Packs, and

c) Aircraft is not operated in known or forecast icing conditions.

|

9. ***

Engine Inlet Duct Ice Detector

D 1 0

10. Stall Warning

Transducer Anti-Ice System

C 1 0 May be inoperative provided aircraft is not operated in known or forecast icing conditions.

11. Engine Anti-Ice Valve

Systems (Series 10 through 60)

C 12 4 (M)(O) Eight may be inoperative provided:

a) One engine valve is operative on each engine,

b) Inoperative valves are secured OPEN,

c) Cockpit Placards state which Valves are inoperative,

(Continued)




PAGE NO: 30-3







Systems (Series 10 through 60) (Cont’d)

d) Performance decrements are

used in accordance with the appropriate AFM,

e) Associated Guide Valves are inspected before each departure for cracks or distortion caused by excessive heat, and

f) Entire flight, including ground operation, is conducted with outside air temperatures of 50 degrees F or less.

NOTE: System consists of two engine

and one cowl anti-ice valve

C 12 11 (M) One may be inoperative provided:

a) Affected Valve is secured CLOSED, and

b) Aircraft is not operated in known or forecast icing conditions.

|

12. ***

Static Port Heaters D 10 0




PAGE NO: 30-4






13. Pitot HEATER INOP,

HTR FAIL, and STALL WARNING ANTI-ICE Lights

B - 0 (M) May be inoperative provided: a) Associated Probe Heaters are

verified operative before each departure, and

b) On aircraft with Air Conditioning Packs associated Pitot Line Heaters are verified operative before each departure.

|

B - 0 (M) May be inoperative provided:

a) Associated Probe Heaters are verified operative before each departure, and

b) On aircraft with Air Conditioning Packs associated Pitot Line Heaters are considered inoperative.

14. ***

Windshield Over and Under Temperature Indicating Detector

D 1 0

15. ***

Tail Deicing Timer Override Switch

D 1 0

16. ***

Drain Mast Heaters C - 0 (M) May be inoperative provided: a) Associated lavatory, galley, and

service center basins are not used, and

b) Associated Lavatory Doors are secured CLOSED.

(Continued)




PAGE NO: 30-5






16. Drain Mast Heaters

(Cont’d)

D - 0 (M) May be inoperative provided:

a) Associated lavatory, galley, and service center basins are deactivated, and

b) Associated water shutoff valves are CLOSED.

17. ***

Total Air Temperature Heater

C 1 0 May be inoperative provided aircraft is not operated in known or forecast icing conditions.

18. Pitot Heater Ammeter C 1 0 (M) May be inoperative provided:

a) All associated Heaters are verified operative before each departure, and

b) All Pitot Heater Lights are operative.


Lights (Series 70) C 4 3 (O) One may be inoperative provided

alternate procedures are established and used to verify valve movement and position.

20. Engine Cowl Anti-Ice

Valves (Series 70) C 4 3 (M) One may be inoperative provided:

a) Affected Valve is secured CLOSED, and


C 4 0 (M) May be inoperative provided:

a) Affected Valves are secured OPEN,

(Continued)




PAGE NO: 30-6






20. Engine Cowl Anti-Ice

Valves (Series 70) (Cont’d)

b) Associated Pneumatic Pressure

Regulator, 9th Stage Regulator Valve and Bleed Air Control Systems are operative, and

c) Appropriate AFM Performance decrements are applied.

21. ***

Pitot Line Heaters B 3 2 (O) One may be inoperative provided: a) Aircraft is not operated in known

or forecast icing conditions, b) Scoop Anti-Ice system is

operative. B 3 0 (O) May be inoperative provided:

a) Temperature at the Departure airport is above 0 degrees C, or if visible moisture exists, above 6 degrees C,

b) Forecast at the arrival airport is forecast above 6 degrees C,

c) All Pitot Line Sumps are drained before each departure, and

d) Scoop Anti-Ice System is operative and ON whenever Ram Air Temperature is 6 degrees C or less.




PAGE NO: 30-7






22. ***

Anti-Ice and De-Ice Advisory Light

D 1 0

23. Outer Wing Pneumatic

Duct Valve C 2 0 (M) May be inoperative provided:

a) Affected Valve is closed, b) Wing Deice System is

considered inoperative and not used, and

c) Aircraft is not operated in known or forecast icing conditions.




PAGE NO: 31-1





31 INDICATING/ RECORDING SYSTEMS

1. Clock (Cockpit) D - 1 Any in excess of those required by


1) Elapsed Time

Chronometer Display C 2 0

2) Chronometer Switches

– Date Set Start/Stop Features

C 2 0

2. Flight Data Recorder

(FDR) System C - - Any in excess of those required by 14

CFR may be inoperative. |

A - 0 May be inoperative provided:

a) Cockpit Voice Recorder (CVR) is operative,

b) Airplane is not dispatched from a designated airport listed in the operator’s MEL unless: 1. The FDR failure occurs

after pushback but prior to takeoff, or

2. The FDR repair was attempted but was not successful.

c) In those cases where repair is attempted but not successful, the aircraft may be dispatched on a flight or series of flights until the next designated airport where repairs must be accomplished prior to dispatch, and

| | |

(Continued)




PAGE NO: 31-2





31 INDICATING/ RECORDING SYSTEMS

2. Flight Data Recorder

(FDR) System (Cont’d)

d) Repairs are made within three

flight days. |

1) FDR Recording

Parameters Required by 14 CFR

A - - May be inoperative provided: a) Cockpit Voice Recorder (CVR)

is operative, and b) Repairs are made within 20

calendar days.

2) FDR Recording

Parameters Not Required by 14 CFR

A - - May be inoperative provided repairs are made prior to completion of the next heavy maintenance visit.

3) ***

Flight Data Recorder Air Data Computer

A 1 0 May be inoperative provided: a) Cockpit Voice Recorder (CVR)

System is operative, and b) Repair is made within three

flight days.

3. Cockpit Voice

Recorder (CVR) System

MOVED to ATA Chapter 23.

4. Elapsed Time

Chronometer Display MOVED to Item 31-1.

5. Chronometer Switches

– Date Set Start/Stop Features

MOVED to Item 31-1.




PAGE NO: 32-1





32 LANDING GEAR

1. Wheel Brake Anti-Skid System

C 1 0 (O) May be inoperative provided: a) Appropriate AFM Limitations,

Procedures, and Performance adjustments are applied.

b) Operations on other than dry surfaces are conducted in accordance with FAA approved Supplemental Performance Data in report # 2003-01 Revision dated 4/06/04.

c) Operations based on FAA approved Supplemental Data Reports must include the Following: 1) Takeoffs are limited to

utilization of PFCO or grooved runways,

2) All Thrust reverses operate normally, and

3) Crosswind components for takeoff to be 15 knots or less.

NOTE: AFM Limitations for some Noise

Abatement STCs require the Wheel Brake Anti-skid System be Operative for Takeoff and Landing.

2. Parking Brake DELETED in revision 34.

3. Landing Gear Warning and Indicating System Including Horn


4. Air Brake Pressure

Gauge (Cockpit) DELETED in revision 34.




PAGE NO: 32-2





32 LANDING GEAR

5. Air Brake Pressure Gauge (Wheel Well)

C 1 0

6. ***

Bogie Swivel Unlock C 2 0 (M) May be inoperative provided: a) Bogie Beam Swivel is

deactivated and Locked, b) Appropriate Limits Placard and

Indicator is provided in the cockpit, and

c) Nose wheel angle is limited to 50 degrees (40 degrees for DC-8F) in turn.

|

7. ***

Landing Gear Pin Caution Light

C 1 0

8. Main Gear Door

Warning Light (Fwd Instrument Panel)

C - 0 (M) May be inoperative provided: a) An approved alternate Main

Landing Gear Door Warning Light is installed and operative,

b) It is verified that the Main Gear Doors will close and the door latches will engage in the flight latch position, and

c) Affected light is OFF.

9. Main Landing Gear

Visual Downlock Indicators

C 2 0 May be inoperative provided aircraft is configured for all-cargo operations.

10. ***

Skid Control Monitor Panel for Mark III Anti-Skid System

C 1 0




PAGE NO: 32-3





32 LANDING GEAR

11. Lamp Control Box For Mark III Anti-Skid System

C 1 0 (O) May be inoperative provided appropriate AFM Limitations and Performance Data are applied.

|

12. Mark III Spoiler Control

Unit C 1 0 (O) May be inoperative provided

appropriate AFM Limitations and Performance Data are applied.

|

13. ***

Alternate Main Landing Gear Door Warning Light System

D 1 0 May be inoperative provided Main Gear Door Warning System Light is operative.


Door Uplatch Systems A - 0 May be inoperative provided:

a) Landing Gear Door Warning Light is operative,

b) Aircraft is not operated in excess of 230 KIAS or Mach 0.65, and

c) Repair is made within two flight days.

15. Brake Accumulator

Pressure Gauge (Wheel Well)

C - 0 (M) May be inoperative provided adequate Accumulator Precharge Pressure is verified before each flight using an acceptable alternate procedure.


Uplatch System A - 0 (M) May be inoperative provided:

a) Gear Not Latched Light is operative,

b) Door Not Latched/Doors Light is installed and operative,

c) Main Gear Door engagement and latching in Flight Latch Position is verified, and

d) Repairs are made within two flight days.

(Continued)




PAGE NO: 32-4





32 LANDING GEAR

16. Main Landing Gear Uplatch System (Cont’d)

A - 0 (O) May be inoperative provided:

a) Flight Plan Fuel Burn is based on Gear Down Performance,

b) Aircraft is not operated in excess of 230 KIAS or Mach.65 and,

c) Repairs are made within two flight days.




PAGE NO: 33-1





33 LIGHTS

1. Cockpit and Instrument Lighting System

C - - Individual lights may be inoperative provided remaining lights are:

a) Sufficient to clearly illuminate all required instruments, controls, and other devices for which it is provided,

b) Positioned so that direct rays are shielded from flight crewmembers eyes, and

c) Lighting configuration and intensity is acceptable to the flight crew.

2. Cabin Interior

Illumination Systems C - - May be inoperative provided:

a) Cabin emergency lighting is operative,

b) Sufficient lighting is operative for crew to perform required duties, and

c) Lighting configuration at dispatch is acceptable to the flight crew.

3. Cargo Compartment

Light Systems

1) Upper Cargo

Compartment D 1 0

2) Lower Cargo

Compartment D 1 0




PAGE NO: 33-2





33 LIGHTS

4. Passenger Lighted Information Signs

C - - (M) May be inoperative provided: a) Associated passenger seat or

lavatory is not occupied from which a passenger lighted information sign is not readily legible, and

b) Associated seat or lavatory must be blocked and placarded DO NOT OCCUPY NOTE: These provisos are not intended to prohibit lavatory use or inspections by crewmembers.

|||||||||||||||

C - - (O) May be inoperative and associated

passenger seat or lavatory may be occupied provided:

a) PA System operates normally, and

b) PA System is used to notify passengers and cabin crew when associated sign(s) are placed ON or OFF.

|||||||||

1) All Cargo

Supernumerary/Courier Area Lighted Information Signs

C - - (O) May be inoperative provided alternate procedures are established and used to notify couriers/supernumeraries when associated sign(s) are placed ON or OFF.

||||||

5. Red Anti-Collision

Lights C 2 0 May be inoperative provided aircraft is

not operated at night.

C 2 0 May be inoperative provided aircraft is

equipped with operative White High Intensity Strobe Lights.




PAGE NO: 33-3





33 LIGHTS

5. Red Anti-Collision Lights (Continued)

1) Individual Bulbs C - - Individual bulbs or units may be

inoperative provided operations are conducted in compliance with 14 CFR 91.205.

||||

6. Wing Illumination

Lights C - 0 (O) May be inoperative provided

Ground De-Icing Procedures do not require their use.

|

7. Landing Lights C 4 3 C 4 0 May be inoperative provided aircraft is


1) Wing Landing Light

Retract Function C 2 0 (M) May be inoperative provided:

a) Associated Landing light is considered inoperative, and

b) Associated Landing Light is secured RETRACTED.

(Continued)




PAGE NO: 33-4





33 LIGHTS

7. Landing Lights (Continued)

1) Wing Landing Light

Retract Function (Continued)

C 2 0 (M) May be inoperative provided: a) Associated Landing Light is

secured EXTENDED, b) Performance limited weights

are reduced by value shown for each extended light:

SERIES 10 THROUGH 40 AIRCRAFT

CONDITION: REDUCE GROSS WEIGHT BY: Takeoff (-) 1.20% En Route (-) 3820 pounds Landing (-) 0.35% SERIES 50 AND 60 AIRCRAFT Takeoff (-) 0.85% En Route (-) 2900 pounds Landing (-) 0.35% SERIES 70 AIRCRAFT Takeoff (-) 0.45% En Route (-) 0.85% And

c) Takeoff speeds and maximum pressure height for acceleration only are determined using actual weight plus the weight penalty.

NOTE: See AFM Appendix CDL for

method to apply performance limited weight reductions.




PAGE NO: 33-5





33 LIGHTS

8. Ground Flood Lights (Runway Turnoff Lights)

C 2 0

9. Position Lights (Wing

Tip and Tail)

1) Single Bulb Installation C 4 0 May be inoperative provided aircraft is


2) Dual Bulb Installation C - - May be inoperative provided each position contains an operative bulb.

C - 0 May be inoperative provided aircraft is


10. Passenger Cabin Emergency Lighting System

DELETED in Revision 38.

11. Maintenance Flood

Light Systems (Nose and Main Wheel Wells)

D - 0

12. Master Warning Light DELETED in Revision 38.

13. ***

Exterior Emergency Illumination System

C 1 0 May be inoperative provided aircraft is not operated at night.




PAGE NO: 33-6





33 LIGHTS

14. ***

Floor Proximity Emergency Escape Path Marking System Lights

C - 0 (M) Individual lights may be inoperative provided FAA approved minimum acceptable lighting levels specified in one of the following documents are complied with:

a) FAA Engineering Approval letter.

b) FAA approved report of the Type Design holder.

c) Limitations and conditions section of the applicable Supplemental Type Certificate (STC).

d) An FAA approved report incorporated in the Master Drawing List for the Applicable STC.

15. ***

Logo Lights D - 0

16. ***

White High Intensity Strobe Lights (Anti Collision)

C - - May be inoperative provided aircraft is not operated at night.

C - - May be inoperative provided aircraft

Red Anti-Collision Light System is operative.

17. ***

Master Caution Light System

B 1 0 (M)(O) May be inoperative provided: a) All Caution Lights monitored by

the Master Caution Light for operative systems, (except Fire Agent Low) are located on the Flight Engineers Panel,

b) All affected Caution Lights are verified to be operative before each flight, and

c) Alternate monitoring procedures are established and used.




PAGE NO: 34-1





34 NAVIGATION

1. ***

True Airspeed Indicator C - 0 NOTE: Other systems such as OMEGA, FMS, AHRS, and DFGS may be affected.

2. ***

Navigators Indicated Airspeed Indicator

D - 0

3. Mach Indication

System(s) (Separate Mach Indicator or Mach Indication of a combined Mach/Airspeed Indicator)

C - 1 (O) May be inoperative provided: a) An independent Indicated

Airspeed Indicator is operative in each Pilots Panel,

b) Above FL 258 the Pilot Flying has an operative Mach Indicator, and

c) Mach and Airspeed Overspeed Warning System is operative.

d) For inoperative components requiring Mach restrictions, alternate procedures for determining Mach are established and used.

1) Reminder Bug (Inner

Bug) Superceded by new Item 34-66,

Revision 41.

4. Mach and Airspeed Overspeed Warning System

B 1 0 (O) May be inoperative provided: a) Both Mach Indicators are

operative, and b) The following Speed Limitations

are observed: Mmo= 0.82 Mach above FL258 Vmo= 340 KIAS below FL258.




PAGE NO: 34-2





34 NAVIGATION

5. ***

Altimeter C - 2 Any in excess of those required by 14 CFR may be inoperative.

1) ***

Reminder Bugs (Internal or External)

C - 0 (O) May be inoperative or missing provided alternate procedures are established and used.

6. ***

Altimeter Vibrators

1) Pneumatic Altimeters C - 0 One may be inoperative provided VMC

conditions exist at the departure and arrival airports.

2) Servo Electric-

Pneumatic Altimeters C - - (O) May be inoperative provided:

a) Associated Altimeter Servo Mode is operative, and

b) Associated Altimeter remains in the Servo Mode.

3) Standby Altimeter

(Pneumatic) C - - May be inoperative provided a Servo-

Electric Altimeter is installed and operative as part of each Pilots basic “T” instrument group.

C - - May be inoperative provided a Servo-

Electro-Pneumatic Altimeter is installed and operating in the Servo Mode as part of each Pilots basic “T” instrument group.

7. ***

Navigators Rate-of-Climb Indicator

D - 0

8. ***

Static Air Temperature (SAT) Indicators

D - 0 May be inoperative provided Ram Air Temperature or Total Air Temperature Indicator is operative.




PAGE NO: 34-3





34 NAVIGATION

9. ***

Ram Air Temperature (RAT) and Total Air Temperature (TAT) Indicators

D - 0 May be inoperative provided Static Air Temperature Indicator, Total Air Temperature Indicator, or Ram Air Temperature Indicator is operative.

10. Horizon Indicators DELETED in revision 34.

11. Attitude System

Sensors (Vertical, gyro, AHRS, IRS, etc.)

D - 2 May be inoperative provided independent Primary Attitude information is available on each pilot’s panel.

12. ***

Angle of Attack Indicating Systems

C - 0 May be inoperative provided system is not required for stall warning.

13. Turn and Slip

Indicators

1) Slip Indication C 2 0 May be inoperative provided Slip

Indications are provided in each pilots Basic “T”.

2) Turn Indication C 2 1 C 2 0 May be inoperative provided Standby

Attitude Gyro is installed and operative.

14. Compass System Sensors (Directional gyro, AHRS, IRS, etc.)

D - 2 May be inoperative provided: a) Both Directional Compass

Systems are operative from independent sources, and

b) Each pilots panel has independent heading information.




PAGE NO: 34-4





34 NAVIGATION

15. Non-Stabilized Magnetic Compass

B 1 0 (O) May be inoperative provided any combination of three Gyro or INS (IRU) Stabilized Compass Systems are operative.

|

B 1 0 (O) May be inoperative provided:

a) Any combination of two gyro or INS (IRU) Stabilized Compass Systems are operative, and

b) Airplane is operated with dual independent Navigation capability and under Positive Radar Control by ATC on the enroute portion of the flight.

|

B 1 0 (O) May be inoperative for flights that

are entirely within areas of magnetic unreliability provided at least two Stabilized Directional Gyro Systems are installed, are operative, and used in conjunction with Approved free gyro navigation techniques.

| |

1) Glareshield Mirrors C 2 1 One may be inoperative provided the

mirror located at the Compass is operative.

B 2 0 May be inoperative provided Non-

Stabilized Magnetic Compass is considered inoperative.

|




PAGE NO: 34-5





34 NAVIGATION

16. Flight Director Systems C - 0 May be inoperative provided approach minimums do not require its use.

1) Go-Around (GA) Mode C - 0 (O) May be inoperative provided



procedures do not require its use. |

2) Go-Around Switch C - 0 (O) May be inoperative provided




3) Flight Director Mode

Select Panel Modes (Collins FGS-80, STC SA 1915SO, SA2304SO)

a) ALT C 2 0 May be inoperative provided Altitude

Alert function is operative.

b) LRN C 2 0

c) HDG C 2 0

d) APPR C 2 0 May be inoperative provided approach minimums do not require its use.

e) NAV C 2 0 May be inoperative provided approach


(Continued)




PAGE NO: 34-6





34 NAVIGATION

16. Flight Director Systems (Cont’d)

4) Mode Select Panel Gull

Wing Indicator Lights (Collins FGS-80 STC SA1915SO, SA2304SO)

a) Captains C 12 2 All Gull Wing indicator lights, except

Pitch mode, may be inoperative provided selected mode is annunciated on the associated EADI.

b) First Officer C 12 2 All Gull Wing indicator lights, except

Pitch Mode, may be inoperative provided selected mode is annunciated on the associated EADI.

17. Distance Measuring

Equipment (DME) Systems





PAGE NO: 34-7





34 NAVIGATION

18. Marker Beacon System C 1 0 May be inoperative provided approach procedures do not require its use.

19. ***

Doppler Navigation Systems


20. ***

Inertial Navigation Systems

1) All Except Litton LTN92 D - - Any in excess of those required by


a) Navigational Information

C - -

b) Nav Data Base C - - May be out of currency provided:

a) Current aeronautical charts are used to verify navigation fixes prior to dispatch,

b) Procedures are established and used to verify status and suitability of navigation facilities used to define route of flight, and

c) Approach navigation radios are manually turned and identified.

2) Litton LTN92 D - - Any of those in excess of 14 CFR may

be inoperative. (Continued)




PAGE NO: 34-8





34 NAVIGATION

20. ***

Inertial Navigation Systems (Cont’d)

2) Litton LTN92 (Cont’d)

a) Navigational Accuracy and Information (excessive drift rates or residual ground speed) when INS is the Primary Attitude and/or Heading Source

C - - (O) May be inoperative while system is used only for attitude and/or heading source provided:

a) The system is aligned and operative in NAV mode. (not ATT REF),

b) No INS warning annunciations or instrument flags are displayed,

c) Both pilots pitch, roll and heading indications agree within comparator limits, and

d) System is not used for navigation.

b) Functions Reference

by “Delayed Maintenance Action/Malfunction” Messages

C - - May be inoperative provided external systems which receive INS data associated with the message(s) are considered inoperative.

D - - May be inoperative provided no

external systems are affected. (Continued)




PAGE NO: 34-9





34 NAVIGATION

20. ***



c) Catalog(s) World Wide Data Base, Custom Catalog, Crew Catalog

C - - (O) May be out of currency provided: a) Current aeronautical charts are

used to verify navigation fixes prior to dispatch,


c) Approach navigation radios are manually tuned and identified.

d) INS Update/No

Updates Annunciators D - 0 May be inoperative provided:

a) RNAV approach procedures are not used, and

b) Update status is verified on the CDU.

e) CDU Offset Light C - - May be inoperative provided

associated INS is not used in crosstrack offset unless a remote offset light is installed and operative.

(Continued)




PAGE NO: 34-10





34 NAVIGATION

20. ***



f) CDU Alert Light C - - May be inoperative provided associated CDU is monitored for distance and time to next way point (Flight Plan page) or a remote Alert light is installed and operative.

g) CDU Edge Light C - - May be inoperative provided area

lighting illumination is acceptable to the flight crew.

h) CDU Dimming C - - May be inoperative provided the

display is legible and acceptable to the flight crew.

i) CDU Display

Segments C - - May be inoperative provided

corresponding segment on other CDU is operative.

j) MSU Align Light C - - May be inoperative provided Align

count down on CDU Status page changes from “ALIGN” to “NAV”.

k) MSU Detent to NAV C - - (M) May be inoperative provided switch

is secured in NAV position to prevent accidental turn off.

l) MSU Edge Light C - - May be inoperative provided area

lighting illumination is acceptable to the flight crew.

(Continued)




PAGE NO: 34-11





34 NAVIGATION

20. ***



m) INS Crossfill C - - May be inoperative provided flight data is entered into each INS.

n) Wind Display C - -

o) RNAV Mode D - - May be inoperative provided enroute operations do not require its use.

p) Triple Mix D - - May be inoperative provided enroute

operations do not require its use.

q) GPS updating D - - May be inoperative provided enroute operations do not require its use.

r) RNAV Position

Updating D - - May be inoperative provided enroute

operations do not require its use.

s) TMIX Position Updating

D - - May be inoperative provided enroute operations do not require its use.

t) CDU Message Check

ADC (from ADC to INS)

C - - NOTE: Wind and RNAV may be inoperative without ADC data.

u) Approach Mode C - - May be inoperative provided approach

procedures do not require its use. (Continued)




PAGE NO: 34-12





34 NAVIGATION

20. ***



v) Autopilot Coupling C - - May be inoperative provided approach procedures do not require its use.

21. ***

Weather Radar System C - - As required by 14 CFR.

1) Contour C 1 0

2) Map C 1 0

3) Test C 1 0 (O) May be inoperative provided an alternate means is developed and used to verify the system is operative.

4) Automatic Gain Control C 1 0 May be inoperative provided radar can

be manually tuned to receive satisfactory radar returns.

5) Stabilization C 1 0 (M) May be inoperative provided:

a) Tilt Control is operative. b) Antenna is verified to scan in a

horizontal plane with the tilt at zero degrees.

c) Place DMI placard adjacent to indicator stating “STAB INOP”.

6) Turbulence Detection D 1 0 (Continued)




PAGE NO: 34-13





34 NAVIGATION

21. ***

Weather Radar System (Cont’d)

7) Display C - - As required by 14 CFR.

22. Automatic Direction Finding (ADF) Systems


23. VHF Navigation

Systems (VOR, ILS) D - - Any in excess of those required by

14 CFR may be inoperative, provided they are not powered by an Emergency Bus, or equivalent, and are not required to accomplish an Emergency Procedure.

1) ***

Self Test Feature C - 0 (O) May be inoperative provided alternate procedures are established and used.



2) ***

Expanded Localizer Indicator (In ADI)

C - - May be inoperative provided approach minimums do not require its use.

D - - May be inoperative provided


3) ***

Glide Slope Indicators C - 2 (O) May be inoperative provided at least one Glide Slope Indicator is operative in each Pilots Basic “T”.

|||

C - 0 May be inoperative provided approach





PAGE NO: 34-14





34 NAVIGATION

24. ATC Transponders and Automatic Altitude Reporting Systems

B - 0 May be inoperative provided: a) Operations do not require its

use. b) Prior to flight, approval is

obtained from ATC facilities having jurisdiction over the planned route of flight.

|||||||

D - 1 Any in excess of those required by

14 CFR may be inoperative. |

1) ***

Elementary and Enhanced Downlink Aircraft Reportable Parameters not Required by 14 CFR

A - 0 May be inoperative provided: a) Operations do not require its

use, and b) Repairs are made prior to

completion of the next heavy maintenance visit.

||||||

2) ***

ADS-B Squitter Transmissions

A - 0 May be inoperative provided: a) Operations do not require its

use, and b) Repairs are made prior to

completion of the next heavy maintenance visit.

||||||

25. LORAN “C” Navigation

Systems D - - Any in excess of those required by





PAGE NO: 34-15





34 NAVIGATION

26. Radio Altimeter Systems

A - 0 (O) May be inoperative provided: a) Approach minimums or

operating procedures do not require its use, and


|||||||

1) ***

Rising Runway Display in ADI

D - 0 May be inoperative provided procedures do not require its use.

C - 0 (O) May be inoperative provided


2) ***

Decision Height (DH) Annunciation System(s)

C - 0 May be inoperative provided approach minimums and operating procedures do not require its use.

27. Navigation and

Instrument Warning Monitor, or Comparator System

C 1 0 May be inoperative provided approach minimums do not require its use.

NOTE: Auto throttle and Auto Pilot

disconnect annunciations are required parts of an operative Auto Pilot or Auto Throttle System

28. ***

Instrument Warning System (Gables)

C 1 0

29. ***

Kollsman Interpreted Flight Instrument System (KIFIS) and Central Air Data Computer (CADC) System

C 1 0 May be inoperative provided one altimeter at each pilot station is operative as a standard barometric altimeter.




PAGE NO: 34-16





34 NAVIGATION

1) ***

Test Switches (Flight Deck)

C - 0 (M) May be inoperative provided an alternate procedures for testing the System are established and used.

30. Mach/Airspeed

Overspeed Warning Light

B 1 0 May be inoperative provided Mach/Airspeed Overspeed Aural Warning System is operative.

31. ***

CAT II Mode Annunciator

C 1 0 May be inoperative provided system approach minimums do not require its use.

32. Standby Attitude

Indicator C - 0 May be inoperative provided not

required by 14 CFR.

B - 0 May be inoperative provided:

a) Operations are conducted in Day VMC only, and

b) Operations are not conducted into known or forecast over the Top conditions.

33. Altitude Alerting

System A - 0 (O) May be inoperative provided:

a) Autopilot with Altitude Hold is operative,

b) Enroute operations do not require its use, and

c) Repairs are made within three flight days.

C - 0 May be inoperative provided it is not

required by 14 CFR.




PAGE NO: 34-17





34 NAVIGATION

34. Terrain Awareness and Warning System (TAWS)

|||

-01 Class A TAWS

Equipment Required |

|

1) GPWS A 1 0 (O) May be inoperative provided: a) Alternate procedures are

established and used, and b) Repairs are made within two (2)

flight days.

|

a) Modes 1 – 4 A 4 0 (O) May be inoperative provided:



|

b) Test Mode A 1 0 May be inoperative provided:

a) GPWS is considered inoperative, and


|

c) Glide Slope

Deviation(s) (Mode 5) C - 1 |

| B - 0 |

d) ***

Advisory Callouts B - 0 (O) May be inoperative provided alternate procedures are established and used.

|


a) Advisory callout not required by 14 CFR, and


|||||




PAGE NO: 34-18





34 NAVIGATION

34. Terrain Awareness and Warning System (TAWS) (Cont’d)

-01 Class A TAWS

Equipment Required (Cont’d)

e) ***

Windshear Mode (Reactive)

B 1 0 (O) May be inoperative provided alternate procedures are established and used.

|||

NOTE: Operator’s alternate procedures

should include reviewing windshear avoidance and windshear recovery procedures.

||||



b) Windshear Detection and Avoidance System (Predictive) is operative.

||||||

2) Terrain System –

Forward looking Terrain Avoidance (FLTA) and Premature Descent Alert (PDA) Functions

B 1 0 (O) May be inoperative provided alternate procedures are established and used.

||||||

3) ***

Terrain Displays C - 1 ||

B - 0 |

4) ***

Runway Awareness & Advisory System (RAAS)

C 1 0 |||

(Continued)




PAGE NO: 34-19





34 NAVIGATION TAWS (Cont’d)

-02 Class B TAWS Equipment Required

||

1) GPWS A 1 0 (O) May be inoperative provided:


b) Repairs are made within two (2) flight days.

|||||

a) Modes 1 & 3 A 2 0 (O) May be inoperative provided:



|||||

b) Test Mode A 1 0 May be inoperative provided:

a) GPWS is considered inoperative , and


|||||

c) ***

Modes 2, 4 & 5 C 3 0 ||

d) ***

Advisory Callouts

B - 0 (O) May be inoperative provided alternate procedures are established and used.

|||

C - 0 (O) May be inoperative provided:

a) Advisory callout not required by 14 CFR, and


|||||

e) ***

Windshear Mode (Reactive)

C 1 0 (O) May be inoperative provided alternate procedures are established and used.

|||

(Continued)




PAGE NO: 34-20





34 NAVIGATION TAWS (Cont’d) Class B TAWS

Equipment Required (Cont’d)

2) Terrain System –

Forward Looking Terrain Avoidance (FLTA) and Premature Descent Alert (PDA) Functions

B 1 0 ||||||

3) ***

Terrain Displays C - 0 ||

4) ***

Runway Awareness & Advisory System (RASS)

C 1 0 |||

-03 Class C TAWS

Equipment |

|

1) ***

TAWS/GPWS C 1 0 (O) May be inoperative provided alternate procedures are established and used.

|||

NOTE: Any mode that is operative may

be used. ||

35. ***

Speed Control Indicator

D 1 0

36. ***

OMEGA/VLF Navigation System


1) TAS (Omega System) C - - (Continued)




PAGE NO: 34-21





34 NAVIGATION

36. ***

OMEGA/VLF Navigation System (Cont’d)

2) Aux Nav (Steering to

Autopilot) C - 0

3) Heading (Input to

Omega) C - 0

4) Course Deviation

(Signal to HSI/CDI) C - 0 May be inoperative provided course

deviation is available on another indicator (e.g. Omega CDU).

5) Navigation Databases C - 0 (O) May be out of currency provided:

a) Current aeronautical charts are used to verify navigation fixes prior to dispatch,



6) Flight Plan Crossload

Capability D - 0

7) Night Vision D - 0

8) Wind Direction D - 0

9) Wind Speed D - 0

10) Ground Speed D - 0

11) Track D - 0

12) Grid Nav. D - 0




PAGE NO: 34-22





34 NAVIGATION

37. ***

Long Range Navigation System (FMS/GPS)


1) Data Transfer Unit C 1 0

2) Data Base C - - (O) May be out of currency provided: a) Current aeronautical charts are

used to verify navigation fixes prior to dispatch,



3) Aux. NAV C 1 0 (O) May be inoperative provided

autopilot coupling is not required.

4) TAS/ALT Input C - 0 (O) May be inoperative provided: a) Crossfill function is operative,

and b) Approach minimums do not

require its use.

5) Heading Input C - 0 (O) May be inoperative provided Crossfill function or Manual input is operative.

(Continued)




PAGE NO: 34-23





34 NAVIGATION

37. ***

Long Range Navigation System (FMS/GPS) (Cont’d)

6) Distance Converter C 2 1 May be inoperative provided Leg

distance is available through the CDU. |

7) Fuel Flow Counters C 4 0 (O) May be inoperative provided Fuel

Quantity Indicators are used.

8) System Status

Annunciator Panel C 2 1 May be inoperative provided CDU

displays Status Messages.

38. ***

Flight Performance Management System

D 1 0 May be inoperative provided operation does not require its use.

39. ***

Electronic Flight Instrument Systems (EFIS)

1) Symbol Generator

(Display Processor) C 3 2 One may be inoperative provided each

pilot station EFIS displays operate independently.

2) Navigation

Concentrator (Analog to Digital Converter)

C 3 2 One may be inoperative provided associated Symbol Generator is considered inoperative.

3) Multifunction Display

Unit C 1 0 May be inoperative provided Weather

Radar information can be displayed at a pilot station.

(Continued)




PAGE NO: 34-24





34 NAVIGATION

39. ***

Electronic Flight Instrument Systems (EFIS) (Cont’d)

C 1 0 May be inoperative provided Weather

Radar is considered inoperative.

40. Traffic Alert Collision

Avoidance System (TCAS II)

B - 0 (M) May be inoperative provided: a) System is deactivated and

secured, and b) Enroute or approach


C - 0 (M) May be inoperative provided:

a) Not required by 14 CFR b) System is deactivated and

secured, and c) Enroute or approach


|

1) ***

Combined Traffic Alert (TA) and Resolution Advisory (RA) Dual Display System(s)

C 2 1 May be inoperative on the non-flying pilots side provided:

a) TA and RA visual display is operative on the flying pilot side, and

b) TA and RA audio function is operative on the flying pilot side.

2) Resolution Advisory

(RA) Display System(s) C 2 1 May be inoperative on the non-flying

pilots side. |

(Continued)




PAGE NO: 34-25





34 NAVIGATION

40. ***

Traffic Alert Collision Avoidance System (TCAS II) (Cont’d)

2) Resolution Advisory

(RA) Display System(s) (Cont’d)

|


a) Traffic Alert (TA) visual display and audio functions are operative, and

b) TA only mode is selected by the crew, and

c) Enroute or approach procedures do not require its use.

3) Traffic Alert Display

System(s) C - 0 (O) May be inoperative provided:

a) RA visual display and audio functions are operative, and

b) Enroute or approach procedures do not require its use.

4) Audio Functions B 1 0 May be inoperative provided enroute or

approach procedures do not require use of TCAS.

|||

5) ***

Airspace Selection Function

C - 0 ||

6) ***

Dual Vertical Speed Indicator/Traffic and Resolution Advisory (VSI/TRA) Displays (STC STO 1738CH)

B 2 0 (O) Both may be inoperative provided: a) Both primary vertical speed

indicators are operative, and b) TCAS systems is deactivated

and secured.

|

(Continued)




PAGE NO: 34-26





34 NAVIGATION

40. ***

Traffic Alert Collision Avoidance System (TCAS II) (Cont’d)

6) ***

Dual Vertical Speed Indicator/Traffic and Resolution Advisory (VSI/TRA) Display (STC STO 1738CH) (Cont’d)

C 2 1 (O) One VSI/TRA display may be

inoperative provided: a) Both primary vertical speed

indicators are operative, and b) Operative TCAS (VSI/TRA)

display is on the flying pilot side.

41. ***

Wind Shear Detection Systems

1) Windshear Warning

and Flight Guidance System (Reactive)

B - 0 (O) May be inoperative provided alternate procedures are established and used. NOTE: Operator’s alternate procedures should include reviewing windshear avoidance and windshear recovery procedures.

|||||||



b) Windshear Detection and Avoidance System (Predictive) is operative.

|||

(Continued)




PAGE NO: 34-27





34 NAVIGATION

41. ***

Wind Shear Detection Systems (Cont’d)

2) Windshear Detection

and Avoidance System (Predictive)

B - 0 (O) May be inoperative provided alternate procedures are established and used. NOTE: Operator’s alternate procedures should include reviewing windshear avoidance and windshear recovery procedures.

|||||||



b) Windshear Warning and Guidance System (Reactive) is operative.

|||

42. ***

Total Air Temperature Indicators

D - 0 May be inoperative provided any RAT or SAT Indication is operative.

43. ***

EFIS Source Select Switches

1) Display Mode C 2 0 May be inoperative provided

associated EADI and EHSI are not in composite mode.

2) ATT/HDG C 2 1 One may be inoperative provided:

a) Both pilots have independent sources for Attitude and Heading reference, and

b) Affected switch is not operated in flight.

(Continued)




PAGE NO: 34-28





34 NAVIGATION

43. ***

EFIS Source Select Switches (Cont’d)

3) Air Data Computers

(ADC) C 2 1 One may be inoperative provided:

a) Both pilots have Air Data Information from Independent sources, and

b) Affected Switches are not operated in flight.

4) EFIS Display

Processor Unit (DPU) Source Select Switch Light

C 2 0 (M) Switch or Light in switch may be inoperative provided:

a) Display is selected to an ON SIDE source, and

b) Both DPUs are operative, and c) Switch is not moved inflight.

44. GPWS Press to Test

Switches Moved to item 34-34-2a, Revision 44.

45. Glide Slope Inhibit

Switch/Light Moved to item 34-34-3a, Revision 44.

46. Vertical Speed

Indicator Reminding Marker (bug)

C 2 0 May be inoperative provided both vertical speed indicators are operative.

47. Bearing Distance

Indicator (BDI) Instrument

C 2 0 May be inoperative provided: a) EHSIs are operative and

powered from independent sources, and

b) Bearing distance and azimuth can be displayed on each EHSI.




PAGE NO: 34-29





34 NAVIGATION

48. Enroute Approach Switch Light

C 2 0

49. Update/No Update

Indicator Light C 2 0 May be inoperative provided RNAV

procedures are not used. C 2 0 May be inoperative provided Update

status can be verified on INS CDU

50. EFIS Display Control Panel Course Preselected (CRS/PRE) Switch

C 2 1

51. EFIS Display Control

Panel Course Active (CRS/ACT) Switch

C 2 1 May be inoperative provided: a) Associated active course is

displayed on the EHSI, and b) Preselected and course transfer

switches are operative.

52. EFIS Display Control Panel Bearing Mode Selector Display (BRG) Switch System

C 2 0 Both may be inoperative provided: a) BDI is operative, and b) Approach minimums do not

require its use.

53. EFIS Air Speed Annunciator Indication (EADI)

C 2 0

54. Windshear Guidance

Switchlight Annunciator Light

C 2 0 May be inoperative provided windshear guidance can be cancelled by actuating the affected switchlight.

55. VOR NAV Control

Panel Frequency Display Test Switch

C 2 0 May be inoperative provided panel displays correct frequency.




PAGE NO: 34-30





34 NAVIGATION

56. VOR/DME Tuning Select Function (Auto/Manual)

C 2 0 May be inoperative provided: a) Radio can be tuned manually,

and b) Auto function is not required by

RNAV.

| |

57. EFIS MAX Airspeed

Warning EFIS Display in EADI

C 2 0

58. Comparator Reset

System C 2 0 May be inoperative provided the

associated comparator is inoperative and approach minimums do not require its use.

59. EFIS EHSI DME

Display C - - As required by 14 CFR.

60. EFIS HSI ARC Map

Format Display Select Switch

Moved to 34-68-8 in revision 42.

61. VSI Push to Test

System C 2 0 May be inoperative provided an

alternate means is used to test system.

62. Instrument Annunciator

Test Switch C 1 0 May be inoperative provided operation

can be determined by alternate means.

63. EFIS Weather Radar

Control Panel C 1 0 As required by 14 CFR.

1) Test Function C 1 0 May be inoperative provided radar is

not required.

(Continued)




PAGE NO: 34-31





34 NAVIGATION

63. EFIS Weather Radar Control Panel (Cont’d)

1) Test Function (Cont’d) C 1 0 (M) May be inoperative provided

alternate procedures are established verifying its operation.

2) Turbulence Mode C 1 0

3) Gain Control C 1 0

4) MAP Mode C 1 0

64. Nav Display Transfer Switch

C - - (M) May be inoperative provided VOR/ILS data is verified to be available on the HSI.

65. ***

Trim Spirit Level D 1 0 (M) May be inoperative provided alternate procedures, including, if appropriate, alternate Refueling procedures, are established and used.




PAGE NO: 34-32





34 NAVIGATION

66. ***

Airspeed Bugs

1) ***

Externally Mounted (Reminder Bugs)

a) On Captains Airspeed

Indicator C - 1 (O) All but one may be inoperative, or

missing, provided: a) Inoperative bugs which

erroneously indicate normally marked Speeds (i.e. V1, Vr, V2, Vapp, Vref, etc.) are removed or masked, and

b) Alternate Speed Referencing Procedures are established and used.

b) On First Officers

Airspeed Indicator C - 1 (O) All but one may be inoperative, or

missing, provided: a) Inoperative Bugs which

erroneously indicate normally marked Speeds (i.e. V1, Vr, V2, Vapp, Vref, etc.) are removed or masked, and

b) Alternate Speed Referencing procedures are established and used.

2) Internal Bug (All

Except Collins STC SA8106SW)

C - 0 (O) May be inoperative provided alternate procedures are established and used.






PAGE NO: 34-33





34 NAVIGATION

67. ***

EFIS Course Heading Panel (CHP) (STC SA8106SW)

1) Course Control (CRS

Ctl) Functions C 2 0 May be inoperative provided

associated primary course needle is operative and can be controlled by the course knob.

2) Course Direct Control

(Push CRS Direct) Functions

C 2 0

3) Elapsed Time (ET)

Functions C 2 0

4) Heading Sync (Push

HDG SYNC) Functions C 2 0

68. ***

EFIS Display Control Panel (DCP) (STC SA8106SW)

1) Course Preselect

(CRS PRE) Functions C 2 0

2) Course Active (CRS

ACT) Functions C 2 1 (O) One may be inoperative provided:

a) Associated active course is displayed on the EHSI, and

b) Associated preselect and course transfer functions are operative.




PAGE NO: 34-34





34 NAVIGATION

68. ***

EFIS Display Control Panel (DCP) (STC SA8106SW) (Cont’d)

3) Bearing (BRG)

Functions C 2 0 May be inoperative provided:

a) Associated RMI bearing pointer is operative, and

b) Approach minimums do not require its use.

4) Course Transfer (CRS

XFR) Functions C 2 0

5) Radar (RDR) Switches C 2 1 One may be inoperative provided radar

information can be displayed on the operative system.

C 2 0 May be inoperative provided weather

radar is considered inoperative.

6) DIM Functions C 4 2 One may be inoperative on each DCP

Provided display brightness is acceptable to the flight crew.

(Continued)




PAGE NO: 34-35





34 NAVIGATION

68. ***

EFIS Display Control Panel (DCP) (STC SA8106SW) (Cont’d)

7) Select/Range

(SEL/RNG) Controls |

a) Select Functions C 2 0 (O) May be inoperative provided:

a) Appropriate navigation sensor is selected in the active mode, and

b) Associated RMI bearing pointers are operative.

b) Range Functions C 2 0

8) EFIS Mode Selectors (ARC, MAP, HSI)

C 2 0 Both may be inoperative provided one unit provides arc mode and the switch is not moved during flight.

69. ***

Automatic Dependent Surveillance- Broadcast (ADS-B) System

D - 0 May be inoperative provided it is not required by 14 CFR.

|

NOTE: If ADS-B is installed in lieu of or

as a replacement for 14 CFR required equipment, the repair category in the operators MEL will be the same as that of the 14 CFR required equipment.

|||||




PAGE NO: 34-36





34 NAVIGATION

69. ***

Automatic Dependent Surveillance- Broadcast (ADS-B) System (Cont’d)

1) Cockpit Display and

Traffic Information (CDTI)

D - 0 NOTE: Cockpit Display Traffic Information (CDTI) display of data from other aircraft systems may be used.

|||

2) CDTI Control Panel D - 0 May be inoperative provided:

a) Flight ID can be set, and b) Screen display is acceptable to

the flight crew.

3) Data Link

Transmitter(s) D - 0 NOTE: In some aircraft the Data Link

Transmission is an integral part of the transponder and relief is provided in that section.

||||

4) Data Link Receivers D - 0

5) ADS-B Applications D - 0 |




PAGE NO: 35-1





35 OXYGEN

1. Oxygen System and Supply

B - - As required by 14 CFR.

NOTE: Refer to AFM for Crew

Protective requirements.

1) Crew Oxygen Bottles B - 1 (O) May be inoperative provided:

a) Courier Oxygen Bottle is installed and available to Flight Deck crewmembers, and

b) Before each departure Oxygen supply is verified to be adequate for all crewmembers and additional occupants for the planned duration of the flight.

|

2) ***

Courier Oxygen Bottle C - 0 May be inoperative provided: a) Contents of the Bottle(s) is not

required to meet Oxygen requirements of planned flight, and

b) Courier Seats are not occupied.

C - 0 May be inoperative provided:

a) Contents of the Bottle(s) is not required to meet Oxygen requirements of planned flights, and

b) An Approved alternate means of Courier Oxygen supply is installed and available to Couriers.




PAGE NO: 35-2





35 OXYGEN

2. Passenger Oxygen Mask Access Door Latches (Automatic Door Opening Feature and Door Latch)

C - - May be inoperative provided: a) Associated Passenger Service

Unit (PSU) is operative, and b) Associated Passenger Seats

are Blocked.

C - - May be inoperative provided Flight

remains at or below FL250.

3. Passenger Oxygen

System B 1 0 (O) May be inoperative provided:

a) Flight is not conducted on routes with a Minimum En Route Altitude in excess of 14,000 feet MSL,

b) All Air Conditioning and Pressurization Systems are operative,

c) Flight remains at or below FL250,

d) Portable Oxygen Units capable of delivering 2 liters per minute for 30 minutes are provided for at least 10 percent of the passengers, and

e) Alternate Passenger Briefing is developed and used for this operation.

C 1 0 May be inoperative provided flight is

conducted at or below 10,000 feet MSL.

|||




PAGE NO: 35-3





35 OXYGEN

4. Portable Oxygen Dispensing Units

D - - Any in excess of those required by 14 CFR may be unserviceable provided:

a) Required distribution of serviceable bottles is maintained throughout the aircraft, and

b) Bottles not properly serviced are replaced, serviced, or removed at the next available maintenance facility.

5. Protective Breathing

Equipment (PBE) D - - Any in excess of those required by

14 CFR may be inoperative. ||




PAGE NO: 36-1





36 PNEUMATIC

1. Pressure Regulator and Shutoff Valves

1) Pressure Regulator

Shutoff Valve (Series 10 through 60)

C 4 3 (M) One may be inoperative provided: a) Affected Valve is secured

CLOSED, and b) Aircraft is not flown in known or

forecast icing conditions.

C 4 2 (M) Two may be inoperative provided:

a) Affected valve(s) is secured CLOSED,

b) One valve is operative on each side,

c) Aircraft is not flown in known or forecast icing conditions, and

d) Approach and landing is not made in known or forecast moderate or heavy precipitation.

|2) Pressure Regulator

Valve (Series 70) C 4 2 (M)(O) Two may be inoperative

provided: a) One valve is operative on each

side, b) Associated HI stage valve is

secured closed, c) Procedures are established and

used to CLOSE the associated Bleed Air Shutoff Valve after engine start,

(Continued)




PAGE NO: 36-2





36 PNEUMATIC

1. Pressure Regulator and Shutoff Valves (Cont’d)

2) Pressure Regulator

Valve (Series 70) (Cont’d)

d) Associated engine anti-ice valve

is fixed closed, and e) Aircraft is not flown in known or

forecast icing conditions.

3) Bleed Air Shutoff Valves (Series 70)


4) High Pressure 16th

Stage Shutoff Valve (Models 61 Modified With STC #ST00266AT, 62, 62F, 63, and 63F)

C 4 2 (M) Two may be inoperative provided: a) Affected valve is secured

CLOSED, b) At least one valve is operative

on each side, c) Pressure Regulator and Shutoff

Valve on the other engine on that side is operative, and

d) Aircraft is not flown in known or forecast icing conditions.


Stage Regulator and Shutoff Valve (Series 70)

C 4 2 (M) Two may be inoperative provided: a) Affected valve is secured

CLOSED, b) At least one valve is operative

on each side, (Continued)




PAGE NO: 36-3





36 PNEUMATIC

1. Pressure Regulator and Shutoff Valves (Cont’d)


Stage Regulator and Shutoff Valve (Series 70) (Cont’d)

c) Pressure Regulator on the other

engine on that side is operative, and

d) Aircraft is not flown in known or forecast icing conditions.

2. ***

Manifold Under Temperature Indicating System

D 1 0 May be inoperative provided Pneumatic Temperature Gauges are operative.

3. Manifold Temperature

Gages C 2 1 One may be inoperative provided:

a) Affected Gauge has an approved crossover system, and

b) Both Manifold Temperatures can be monitored.

4. Low Pressure Valves

(8th, 9th, or 12th Stage Bleed) (Series 10 through 60)

C 4 3


a) One Valve is operative on each side, and

b) Takeoff is not into precipitation or icing conditions.

(Continued)




PAGE NO: 36-4





36 PNEUMATIC

5. Three Position Bleed Switches – Low Pressure Function


and Models 61 and 61F (Except 61 Models Modified with STC ST00266AT)

C 4 0

2) Models 62, 62F, 63,

63F and Series 70 DELETED in revision 38.

6. Bleed Air Heat

Exchangers (Including Temperature Control System)

1) Series 10 Through 60 C 4 0 (O) May be inoperative provided

associated Pressure Regulator and Shutoff Valve is CLOSED for takeoff and climb.

2) Series 70 C 4 3 (O) One may be inoperative provided:

a) Associated Bleed Air shutoff Valve is CLOSED after engine start, and





PAGE NO: 36-5





36 PNEUMATIC

7. Pneumatic Pressure Relief Valves (Series 10 through 60)

C 4 2 (M) Two may be inoperative provided: a) Affected Valves are secured

CLOSED, b) Associated Shutoff (On-Off

Selector) Valve is operated or secured CLOSED, and

c) One Pneumatic Pressure Relief Valve is operative on each side.

8. Combustion Starter

System C 1 0

9. Manifold Pressure

Indications C 2 1

10. Manifold Under

Pressure Warning Systems

1) Aircraft with Turbo-

Compressors C 2 1 One may be inoperative provided

associated Manifold Pressure Indication is operative.

2) Aircraft with Air

Conditioning Packs C 2 0




PAGE NO: 38-1





38 WATER/WASTE

1. Potable Water Systems

C - - (M) Individual components may be inoperative provided:

a) Associated components are deactivated or isolated, and

b) Associated System components are verified not to have leaks.

NOTE: Any portion of the system which

is operative may be used.

C - - (M) May be inoperative provided:

a) System is drained, and b) Procedures are established to

ensure that system is not serviced.

2. Lavatory Waste

Systems (Including Wheelchair Accessible Lavatories)

C - - (M) Individual components may be inoperative provided:

a) Associated components are deactivated or isolated, and

b) Associated system components are verified not to have leaks.

||||

NOTE: Any portion of the system which

is operative may be used.

(Continued)




PAGE NO: 38-2





38 WATER/WASTE

2. Lavatory Waste Systems (Including Wheelchair Accessible Lavatories) (Cont’d)

C - - (M) Associated lavatory system(s) may

be inoperative provided: a) Associated components are

deactivated or isolated to prevent leaks,

b) The pilot-in-command will determine if flight duration is acceptable with a FWD lavatory unusable, and

c) Associated lavatory door(s) is secured closed and placarded, “INOPERATIVE – DO NOT ENTER”.

|

NOTE: These provisos are not

intended to prohibit inspections by crewmembers.




PAGE NO: 46-1






20-1 ***

Electronic Flight Bag Systems (EFBs)

1) ***

Class 3 EFBs C - - (O) May be inoperative provided alternate procedures are established and used.

|||

NOTE: Any function, program or

document which operates normally may be used.

|||



2) ***

Class 2 EFB ||

a) Data Connectivity

(Class 2) C - - (O) May be inoperative provided


|||



b) Power Connection



|||



c) Mounting Device

(Class 2) C - 0 (M)(O) May be inoperative provided:

a) Associated EFB and hardware is secured by an alternate means or removed, and


|||||||




PAGE NO: 46-2






20-1 Electronic Flight Bag

Systems (EFBs) (Cont’d)

c) Mounting Device

(Class 2) (Cont’d) D - 0 (M) May be inoperative provided:

a) Associated EFB and hardware is secured by an alternate means or removed, and

b) Procedures do not require its use.

|||||||

3) ***

Class 1 EFB ||

a) Power Connection



|||



||




PAGE NO: 49-1





49 AIRBORNE AUXILIARY POWER

1. ***

Auxiliary Power Unit D - 0

2. ***

Auxiliary Power Unit Pneumatic Power

D - 0 |

3. ***

Auxiliary Power Unit Electrical Power Generating System

D - 0 |




PAGE NO: 52-1





52 DOORS

1. Door Warning Light System (Except Main Cabin Cargo Door)

C 1 0 (M) May be inoperative provided it is verified by visual inspection that the associated Doors are CLOSED and LOCKED.

NOTE: Belly Door is closed if aircraft

can be pressurized before takeoff.

2. Main Cabin Cargo Door Warning Light Systems

1) Dual Light System

(Installed In Accordance With S/B 52-76)

C 2 1 One may be inoperative provided: a) Visual inspection verifies that

door is CLOSED and that Lockpin is properly positioned or the pin can be visually inspected from within the cabin,

b) Operative Indicating system Test verifies system is operative, and

c) Cargo Door Hydraulic System is independent of or can be isolated from the main hydraulic system.

2) Single Light System DELETED in revision 38. (Continued)




PAGE NO: 52-2





52 DOORS

2. Main Cabin Cargo Door Warning Light Systems (Cont’d)

3) ***

Dual Light System (Installed in Accordance with STC ST01116CH, STC ST01244CH, STC ST01245CH)

C 2 1 (M) One may be inoperative provided: a) Visual inspection verifies that

the cargo Door and Vent Door are CLOSED and Cargo Door locked, visual indicator flag is properly positioned,

b) Operative indicating system test verifies the system is operative, and

c) Cargo Door in Transit Light is operative.

NOTE: Vent Door Warning may be

illuminated.

4) ***

In Transit Light (STC ST01116CH, STC ST01244CH, STC ST01245CH)

C 1 0 (M) May be inoperative provided: a) Visual inspection verifies that

the Cargo Door is CLOSED, and

b) Vent Door Warning Light system is operative.

3. Main Cabin Cargo

Door Vent Door Electrical Function

B 1 0 (M) May be inoperative provided: a) Vent Door is manually CLOSED

using an accepted procedure, b) Latch Activating Shaft and Lock

Pin Handle are verified locked, and

c) Vent Door Warning Light system is operative.

NOTE: These provisions of AD 89-17-

01 remain applicable.




PAGE NO: 52-3





52 DOORS

4. Main Cabin Cargo Door Vent Warning Lights

1) (STC SA1614GL,

Installation Document Nav-DC8-1 Rev. L and Subsequent, or Installations Incorporating both SB-92-01R1 And SB-92-03R1

C 2 1

2) ***

STC ST01116CH STC ST01244CH STC ST01245CH

C 1 0 (M) May be inoperative provided: a) Visual inspection verifies that

the Cargo Door and Vent Door are CLOSED and Cargo Door Lock visual indicator flag is properly position, and

b) A and B Cargo Door warning systems are operative.


a) Visual inspection verifies that the Cargo Door and Vent Door are CLOSED and Cargo Door lock visual indicator flag is properly positioned,

b) A or B Cargo Door warning system is operative, and

c) Cargo Door in Transit light is operative.




PAGE NO: 52-4





52 DOORS

5. Service Doors and Rear Entrance Door Hold Open Feature

C - - (M) May be inoperative provided: a) Door is not required as an

Emergency Exit, and b) Door is secured when in the

Open position.

6. Lower Compartment

Doors Operating Mechanisms (Cargo/Air Conditioning/ Accessory)

D - - (M) May be inoperative provided: a) Associated Door is visually

verified CLOSED and LOCKED before each departure, and

b) Door Open Warning system is operative.

|

7. Main Cabin

Exits/Slides (All Cargo Configuration

C - 0 All Slides in the cargo area except L1/R1 may be inoperative or slide missing without restriction.

|||

B - 1 L1 may be inoperative or slide missing

provided R1 is operative. ||

B - 1 R1 may be inoperative or slide missing

provided L1 is operative. ||

B - 0 May be inoperative or slide missing

provided: a) Only essential crew members

including official observer in the observers seat are allowed on the flight, and

b) An alternate means of egress is available.

||




PAGE NO: 52-5





52 DOORS

8. ***

Enhanced Flight Deck Security Door Primary Locking System (14 CFR 25.795 Compliant) Passenger and Combi Aircraft Only

|||||

1) Decompression

Function Dependant on Primary Door Locking System

A 1 0 (M)(O) May be inoperative provided: a) Primary locking system is

deactivated, b) Secondary locking system is

operative and is used to lock the door,

c) Alternate procedures are established and used for locking and unlocking the door using the secondary locking system, and

d) Repairs are made within two flight days.

|||||||||||||

2) Decompression

Function Independent of Primary Door Locking System

C 1 0 (M)(O) May be inoperative provided: a) Primary locking system is

deactivated, b) Secondary locking system is

operative and is used to lock the door, and

c) Alternate procedures are established and used for locking and unlocking the door using the secondary locking system.

|||||||||||

9. ***

Enhanced Flight Deck Security Door Secondary Locking System (14 CFR 25.795 Compliant) Passenger and Combi Aircraft Only

C 1 0 May be inoperative provided primary locking system is operative.

||||||




PAGE NO: 52-6





52 DOORS

10. ***

Intrusion Resistant Cockpit Door (NASI STC STO1791CH)

C 1 0 (M)(O) May be inoperative provided: a) Alternate security procedures

are established and used per 14 CFR, and

b) Door must be secured open prior to departure.

||||||

1) Door Locking Solenoid C 1 0 (M)(O) May be inoperative provided:

a) Door can be locked and unlocked manually, and


|||||

2) Door WARN Light C 1 0 (M)(O) May be inoperative provided:

a) Normal lock functions are verified operative, and

b) Door buzzer is operative.

|||||

3) Door Bell Switch C 1 0 (M)(O) May be inoperative provided:

a) Door electronic control system is deactivated.

b) Door can be locked and unlocked manually, and

c) Alternate procedures are established and used.

|||||||

4) Door Buzzer C 1 0 |




PAGE NO: 73-1





73 ENGINE FUEL & CONTROL

1. Power Management

Controls (PMC) (Aircraft With CFM 56-2C Engines)

C 4 3 One may be inoperative provided: a) Affected Power Management

Control (PMC) is switched OFF, and

b) Aircraft is operated in accordance with AFM, Appendix XVIII.

2. ***

Engine Fuel Filter Impending Bypass Indication System (Series 70)

C 1 0 (M) May be inoperative provided: a) Engine Fuel Filters are checked

to verify no Fuel contamination is present, and

b) FILTER BYPASS Lights erroneously displayed are deactivated.

1) Engine Fuel Filter

Impending Bypass Indication System Indicator Reset Feature

C 1 0 (O) May be inoperative provided: a) Engine Fuel Filter Impending

bypass Indication System is operative, and

b) Alternate FUEL BYPASS Light Illuminated Procedures are established and used.

||

NOTE: May be inoperative for an

inoperative Engine Fuel Filter Impending Bypass Indication System.

2) FILTER BYPASS

Lights C 4 0 (M) May be inoperative provided:

a) Associated Engine(s) Fuel Filter(s) is checked to verify no Fuel contamination is present, and

b) Affected Light(s) is deactivated.




PAGE NO: 73-2






3. Fuel Flow Indicating

Systems

1) Series 10 Through 60 B 4 3 One may be inoperative provided:

a) Fuel Quantity Indicating Systems for the associated Main and Alternate Fuel Tanks are operative, and

b) Associated N1 and N2 Indicating Systems are operative.

2) Series 70 B 4 3 One may be inoperative provided Fuel

Quantity indicating Systems for the associated Main and Alternate Fuel Tanks are operative.

3) ***

Dual Displays (All Models)

a) Pointers C 4 3 One may be inoperative provided:

a) Associated EPR (P&W Engines only), N1, and N2 Indicators are operative, and

b) Associated Main Fuel Tank Indicators are operative.

b) Digital Displays C 4 0 May be inoperative provided the

associated pointer is operative. (Continued)




PAGE NO: 73-3






3. Fuel Flow Indicating

Systems (Cont’d)

3) ***

Dual Displays (All Models) (Cont’d)

c) Dual Channel Power

Supply (Models 62, 63, 72, and 73)

B 2 1 (M) One channel may be inoperative provided:

a) All Main and Alternate Fuel Quantity Indicating Systems are operative,

b) All N1 and N2 indicating Systems are operative, and

c) Fuel Flow Power Selector Switch is placarded and secured in the operative position.

4. ***

Fuel Used Indicators D - 0




PAGE NO: 74-1





74 IGNITION

1. Fuel Shutoff Lever Ignition Switches

C 4 0 (O) May be inoperative provided alternate procedures are developed and used to start associated engine.

2. Ignition Timer Systems C 4 0

3. Ignition Override System


4. ***

Continuous Ignition C 4 0 (M) May be inoperative provided Ignition Override System is verified operative.

5. Ignition Systems (A

and B)

1) Models 62 and 63 C 8 7

2) Series 70 C 8 6



DC-8 REVISION NO: 39 b DATE: 10/18/1993

PAGE NO: 75-1





75 BLEED AIR

1. Jet Pump Systems for Engine Compartment Ventilation, Engine Oil Cooler Air Flow and Blowaway Jet (All P&W Powered Models, except 61 modified with STC #ST00266AT, 62, 62F, 63 and 63F)

C 4 0 (M)(O) May be inoperative provided: a) Appropriate EPR Correction is

made for Engines with Shutoff Valve secured OPEN, and

b) Engines with Shutoff Valve secured CLOSED are operated at idle when taxiing, except for excursions of 10 seconds or less to 1.2 EPR or less.

2. Fan Air Bleed for

ENGINE Compartment Ventilation, Jet Pump System for CSD Oil Cooler Air flow, and Blowaway Jet (Models 61 Modified with STC #ST00266AT, 62, 62F, 63, and 63F)

C 4 0 (M)(O) May be inoperative provided: a) Appropriate EPR Correction is

made for Engines with Shutoff Valve secured OPEN, and

b) Engines with Shutoff Valve Secured CLOSED are operated at idle when taxiing, except for excursions of 10 seconds of less to 1.2 EPR or less.




PAGE NO: 77-1





77 ENGINE INDICATING

1. Engine Pressure Ratio (EPR) (Or PT-7) Systems

1) Intermix With JT3D-3B

and JT3D-7 Engines DELETED in revision 38.

2) All Aircraft Except

Intermix A 4 3 (M)(O) One may be inoperative

provided: a) Associated N1, N2 and fuel flow

are operative, and b) Aircraft does not exceed 40

flight hours before repair is completed.

2. ***

N1 Overspeed Caution Lights

D 4 0

3. Fuel Flow Meter (F/F),

Tachometer (N1), Tachometer (N2), (Except Series 70)


4. Exhaust Gas

Temperature Indicators (EGT)

1) ***

Digital Counters B 4 0

2) ***

Maximum Limit Pointers

B 4 0

3) ***

Memory System B 1 0




PAGE NO: 77-2






5. ***

Vibration Indicator System

D 1 0 (M) May be inoperative provided maintenance procedures do not require its use.

6. N1 Indicating Systems

1) Series 70 DELETED in revision 38.

2) Series 10 through 60. B 4 3 (O) One may be inoperative provided: a) Associated EPR, N2 and Fuel

Flow Indicating Systems are operative, and

b) Alternate procedures for setting engine power are established and used.

7. N2 Indicating Systems

1) Series 70 B 4 3 (O) One may be inoperative provided associated N1, Fuel Flow Indicating Systems, and PMC are operative.

2) Series 10 through 60 B 4 3 One may be inoperative provided

associated N1 and Fuel Flow Indicating systems are operative.

3) Digital Display C 4 0 May be inoperative provided the N2

pointer is operative.

8. ***

N2 Engine Acceleration Rate Monitors (EARM)

D 4 0




PAGE NO: 77-3






9. PT2 Probe Heater (all Aircraft Except Intermix)

A 4 3 (M)(O) One may be inoperative provided:

a) EPR is considered inoperative, b) Associated N1, N2, and fuel

flow are operative, and c) Aircraft does not exceed 40

flight hours before repair is complete.




PAGE NO: 78-1





78 ENGINE EXHAUST

1. Thrust Brake Systems C 4 2 (M) Two may be inoperative provided: a) Affected Thrust Brake Systems

are on symmetrical engines, b) Affected Thrust Brakes are

secured for forward thrust.

2. Thrust Brake Position

Lights (Series 10 Through 60)

C 4 3 (M) One may be inoperative provided: a) Associated thrust Brake System

is functionally checked through its full cycle and visually verified to be STOWED before each departure, and

b) Thrust Brake is not used before each takeoff.

C 4 2 Two may be inoperative provided

associated Thrust Brake Systems are inoperative.

3. Ejector Systems C 4 2 (M) May be inoperative provided:

a) Affected ejectors are secured RETRACTED, AND

b) Affected Reverser (Thrust Brake) is considered inoperative.


a) Affected Ejectors are secured extended,

b) Affected ejector does not impair Thrust Brake operation,

c) AFM Performance is followed for the number of extended ejectors, and

d) Appropriate Cruise performance decrement is used.

| |




PAGE NO: 78-2





78 ENGINE EXHAUST

4. ***

Ejector Indicator Lights C 4 3

C 4 0 (M) May be inoperative provided

associated Ejector System is considered inoperative.

| |

5. Thrust Brake Sleeve

and Fan Cascade Cover Doors (Series 50 and Models 61 and 61F, except 61 models modified with STC #ST00266AT)

C - - (M) May be inoperative provided: a) Affected Doors are secured,

and b) Associated Thrust Brake

system is considered inoperative.

6. Blocker Doors (Series

70) C 32 16 (M) Sixteen may be inoperative

provided: a) Associated Thrust Reverser is

considered inoperative and not used, and

b) Affected Doors are secured STOWED and verified STOWED before each departure.




PAGE NO: 78-3





78 ENGINE EXHAUST

7. Thrust Reverser Actuator Locks (Series 70)

C 16 12 (M) Four may be inoperative provided: a) No more than two Thrust

Reverser Actuator Locks are inoperative on affected Thrust Reverser, and

b) Affected Thrust Reversers are secured (bolted) STOWED.

8. Reverse Thrust

Indicating Systems (Models 71, 71F)

C 4 2 Two may be inoperative provided the associated Thrust Reverser Brake System is considered inoperative and not used.


a) Throttle interlock system for the associated Thrust Reverser Brake is verified operative, and

b) Reverse Unlock Indicator for associated Thrust Reverser Brake is operative.

9. Reverse Thrust

Indicating Systems (Models 72, 72F, 73, 73F and 71F modified by STC SA8106SW)

C 4 2 Two may be inoperative provided the associated Thrust Reverser Brake System is considered inoperative and not used.

1) Reverser Deployed

Function (Continuous Mode)

C 4 0 (M) May be inoperative provided: a) Throttle interlock system for the

associated Thrust Reverser Brake is verified operative, and

b) Reverse Unlock Indication (Flashing mode of light) for associated Thrust Reverser is operative.




PAGE NO: 78-4





78 ENGINE EXHAUST

10. Thrust Reverser Accumulator Pressure Gauges

1) Series 10 Through 40 C 1 0 (M) May be inoperative provided

adequate Accumulator Precharge Pressure is confirmed once each flight day by an acceptable alternate method.

2) Models 62, 63, and

Series 70 C 2 0 (M) Both may be inoperative provided

adequate Accumulator Precharge Pressure is confirmed once each flight day by an acceptable alternate method.




PAGE NO: 79-1





79 ENGINE OIL

1. Oil Quantity Indicating Systems

B 4 3 (M) One may be inoperative provided: a) Associated Oil Tank Quantity is

verified properly serviced before each departure,

b) There is no evidence of above normal oil consumption or leakage, and

c) Oil Pressure Indicating, Low Oil Pressure Indicating and Oil Temperature Indicating Systems are operative.

2. ***

Manual Oil Temperature Regulating Systems (Oil Cooler Door Actuator and Controls)

C 4 3 One may be inoperative provided: a) Associated Oil Cooler Door

remains with a 1.5 inch gap throughout each flight, and

b) Associated Engine Oil Temperature does not exceed 110 degrees C during ground operation.

3. Oil Temperature

Indicating System DELETED in revision 34.

4. Oil Pressure Indicating

System DELETED in revision 34.

5. ***

Automatic Oil Temperature Regulating Systems

C 4 0

6. Oil Low Pressure

Indicating Light Systems

B 4 3 One may be inoperative provided associated Oil Pressure, Oil Temperature and Oil Quantity indicating Systems are operative.




PAGE NO: 79-2





79 ENGINE OIL

7. ***

Oil filter Differential Pressure Indicating Systems

1) Series 10 Through 60 B 4 0 (M) May be inoperative provided:

a) Affected System is verified inoperative,

b) Associated Filter Screen is checked in accordance with AD 61-24-1, and

c) Associated Disconnect Plug is removed from the Filter Bypass Switch and STOWED.

2) Series 70 B 4 0 (M) May be inoperative provided:

a) Affected System is verified inoperative,

b) Both the Supply and Scavenge Red Pop Up Button Filter Differential Pressure Indicators are visually checked before each departure and Scavenge Filters are checked each flight day, and

c) Associated Disconnect Plug is removed from the Filter Bypass Switch and STOWED.




PAGE NO: 80-1





80 STARTING

1. ***

Starter Air Shutoff Valve Indicating Lights

C - 0 (O) May be inoperative provided alternate procedures are established and used to verify start valve operation and position.

2. Start Valves C 4 3 (O) One may be inoperative provided

procedures are established and used for manually opening and closing affected valve during engine start.




PAGE NO: 82-1





82 WATER INJECTION

1. ***

Water Injection System D 1 0 May be inoperative provided affected system is not required for aircraft performance.

flight standards information system (fsims) - …fsims.faa.gov/wdocs/mmel/dc-8 r45.pdfmcdonnell...

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