master minimum equipment listfsims.faa.gov/wdocs/mmel/da 2000 r8.pdf · master minimum equipment...

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

Master Minimum Equipment List

Revision: 8 Date: 05/23/2012

Falcon DA-2000

Dassault Aviation

John K. Pinnow, Chairman Flight Operations Evaluation Board (FOEB)

Federal Aviation Administration Flight Standards Division

Seattle Aircraft Evaluation Group, SEA-AEG 1601 Lind Ave. S.W.

Renton, WA 98057-3356

Telephone: (425) 917-6600

FAX: (425) 917-6638

FEDERAL AVIATION ADMINISTRATION Page: I Revision: 8 MASTER MINIMUM EQUIPMENT LIST Date: 05/23/2012 FALCON 2000

SYSTEM PAGE REVISION DATE Table Of Contents I 8 05/23/2012 Highlights Of Change II 8 05/23/2012 Definitions (Operator Responsibility) III 8 05/23/2012 Preamble (Operator Responsibility) IV 8 05/23/2012 21 - Air Conditioning 1 to 9 8 05/23/2012 22 – Auto Flight 1 to 2 8 05/23/2012 23 - Communications 1 to 6 8 05/23/2012 24 – Electrical Power 1 to 2 8 05/23/2012 25 - Equipment Furnishings 1 to 10 8 05/23/2012 26 - Fire Protection 1 6 03/06/2007 27 - Flight Controls 1 to 6 8 05/23/2012 28 - Fuel 1 to 3 8 05/23/2012 29 - Hydraulic Power 1 to 2 8 05/23/2012 30 - Ice And Rain Protection 1 to 4 8 05/23/2012 31 – Indicating/Recording Systems 1 to 5 8 05/23/2012 32 - Landing Gear 1 to 5 8 05/23/2012 33 - Lights 1 to 6 8 05/23/2012 34 - Navigation 1 to 15 8 05/23/2012 35 - Oxygen 1 8 05/23/2012 36 - Pneumatic 1 to 2 8 05/23/2012 38 – Water/Waste 1 to 2 8 05/23/2012 45 – Central Maintenance Systems 1 8 05/23/2012 46 – Information Systems 1 7 04/08/2010 49 - Airborne Auxiliary Power 1 to 3 8 05/23/2012 52 - Doors 1 8 05/23/2012 73 – Engine Fuel & Control 1 to 2 8 05/23/2012 74 - Ignition 1 8 05/23/2012 77 – Engine Indicating 1 to 2 8 05/23/2012 78 – Engine Exhaust 1 8 05/23/2012 79 – Engine Oil 1 8 05/23/2012

FEDERAL AVIATION ADMINISTRATION Page: II Revision: 8 MASTER MINIMUM EQUIPMENT LIST Date: 05/23/2012 FALCON 2000

Highlights of Change

- The wording used for unpressurized flight is modified as “Flight is conducted in an unpressurized configuration.”

- The wording, “One/One or two/…” is replaced by, “One/Both/One or more.” - Computer fault codes are removed from the MMEL and placed in the Fault Guide

Dispatch Assistance (FGDA). The FGDA does NOT provide relief; however, it is a reference to assist the operator in locating relief found in the MMEL.

- Incorporated multiple Policy Letters.

Several all encompassing changes made in the previous revision remain in effect: 1. Log of Revisions and Control pages are incorporated into the Table of Contents. 2. Revision changes will be reflected for an entire ATA section vice by individual page. 3. The Definition section will reference the current Policy Letter vice reprinting the text. Operators are responsible for inclusion when developing individual Minimum Equipment Lists (MEL). Current Policy Letters may be found on the internet at www.opspecs.com. 4. The Preamble section will reference the current Policy Letter vice printing the text. Operators are responsible for using the appropriate 14 CFR Part Preamble when developing individual Minimum Equipment Lists (MEL). Current Policy Letters may be found on the internet at www.opspecs.com.

FEDERAL AVIATION ADMINISTRATION Page: III Revision: 8 MASTER MINIMUM EQUIPMENT LIST Date: 05/23/2012 FALCON 2000

For the Master Minimum Equipment List, Definitions addendum, refer to the current FAA Policy Letter PL-25, “Policy Concerning MMEL Definitions”, as well as, the current FAA Policy Letter PL-70, “Definitions Required in MELs”, as found on the Flight Standards Information Management System “FSIMS” website. FSIMS - Policy Letters

FEDERAL AVIATION ADMINISTRATION Page: IV Revision: 8 MASTER MINIMUM EQUIPMENT LIST Date: 05/23/2012 FALCON 2000

For the Master Minimum Equipment List, Preamble addendum, refer to the current FAA Policy Letter PL-34, “MMEL and MEL Preamble”, for operations under 14 CFR Parts 121, 125, 129, and 135, and FAA Policy Letter PL-36, “FAR Part 91 MEL Approval & Preamble”, for operations under 14 CFR Part 91, as found on the Flight Standards Information Management System “FSIMS” website. FSIMS - Policy Letters

U.S. DEPARTMENT OF TRANSPORTATION MASTER MINIMUM EQUIPMENT LIST

FEDERAL AVIATION ADMINISTRATION AIRCRAFT:

DA-2000 REVISION NO: 8 DATE: 05/23/2012

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 Digital Pressurization Controller

C 1 0 (M)(O) May be inoperative provided: a) UP-DN manual controller is

operative, b) Cabin visual and audio warnings

are operative , c) UP-DN manual controller is set to

the RH part of the white arc for take-off, and

d) DUMP mode is verified operative before each departure.

C 1 0 (O) May be inoperative provided:

a) Flight is conducted in an unpressurized configuration and,

b) EFIS fans are verified operative.

1) ARINC Input Data Bus Functions

C 3 - ||

2) Discrete Input Data

Functions C 2 0 |

|

2. UP-DN Manual Controller C 1 0 (O) May be inoperative provided:

a) Cabin digital pressurization controller is operative,

b) The UP-DN manual controller is set within the green index mark, and

c) DUMP mode is verified operative before each departure.


a) Flight is conducted in an unpressurized configuration, and





PAGE NO: 21-2





21 AIR CONDITIONING

3. Outflow Pressurization Valves

1) Electro Pneumatic

Outflow Valve C 1 0 (O) May be inoperative provided:

a) Aircraft is operated at 14,000 ft MSL or below,

b) Pneumatic Outflow valve is operative, and

c) EFIS fans are verified operative.

||

2) Pneumatic Outflow Valve C 1 0 (O) May be inoperative provided:


b) EFIS fans are verified operative. |

4. Triple Indicator

1) Cabin Altitude Indication C 1 0 (O) May be inoperative provided: a) Cabin differential pressure

indicator is operative, b) Cabin digital pressurization

controller is operative, and c) A chart to convert cabin

differential pressure to cabin altitude is provided to the crew.



b) EFIS fans are verified operative. (Continued)




PAGE NO: 21-3





21 AIR CONDITIONING

4. Triple Indicator (Cont’d)

2) Cabin Differential Pressure Indication

C 1 0 (O) May be inoperative provided: a) Cabin altitude indicator is

operative, and b) A chart to convert cabin altitude to

cabin differential pressure is provided to the crew.




3) Cabin Vertical Speed C 1 0 (O) May be inoperative provided cabin differential pressure indicator is operative.




5. “Cabin” Aural Warning C 1 0 (O) May be inoperative provided: a) CABIN warning light is operative, b) Cabin Digital Pressurization

Controller is verified operative, and

c) Cabin altitude remains at or below 8,000 ft.

|

6. CABIN Warning Light

and Aural Warning Test System

C 1 0 (M)(O) May be inoperative provided: a) Cabin Digital Pressurization

Controller is verified operative, and

b) CABIN warning light and aural warning are verified operative.

|




PAGE NO: 21-4





21 AIR CONDITIONING

7. CABIN Warning Light C 1 0 (O) May be inoperative provided: a) “CABIN” aural warning is

operative, b) Cabin Digital Pressurization

Controller is verified operative, c) Cabin altitude remains at or below

8,000 ft, and d) Warning light is deactivated if it

operates continuously.

||

8. Conditioning Pack (ECU) C 1 0 (O) May be inoperative provided:



9. Cold Conditioning Valves C 2 1 (M)(O) One may be inoperative provided:a) Related valve is secured in closed

position, and b) Flight level is limited to FL410 or

below.

|||||

C 2 0 (M)(O) Both may be inoperative provided:

a) Valves are secured in closed position,

b) Flight is conducted in an unpressurized configuration, and


||

|




PAGE NO: 21-5





21 AIR CONDITIONING

10. Hot Conditioning Valves C 2 1 (M)(O) One may be inoperative provided:a) Related valve is secured in

closed position, b) Manual air conditioning

interconnect valve is set in open position, and

c) Flight level is limited to FL410 or below.

||

|

C 2 0 (M)(O) Both may be inoperative provided:

a) Valves are secured in closed position,

b) Flight is conducted in an unpressurized configuration, and


||

11. Cabin Air Recirc Valve

C 1 0 (M) May be inoperative provided the valve is secured in closed position.

||

12. Jet Pump Valve C 1 0 (M)(O) May be inoperative provided:

a) Jet pump valve is verified in closed position,

b) Air Conditioning remains OFF on ground and in flight when TAS is below 300 kts,

c) Air Conditioning is switched AUTO in flight only when TAS is above 300 kts, and

d) EFIS fans are verified operative.

||




PAGE NO: 21-6





21 AIR CONDITIONING

13. Temperature Regulation (TCS) – AUTO mode

A 2 0 One or more may be inoperative provided:

a) MANUAL mode is operative, and b) Repairs are made within three

consecutive calendar days.

|

|

1) Engine Throttle Position Functions

A 2 1 One may be inoperative provided: a) Engine throttles are operative, andb) Repairs are made within three


||||

2) Computer Dialog

Functions (Cockpit and Cabin)

A 2 1 One may be inoperative provided: a) Repairs are made within three


|||

3) Compressor Overheat

Sensor Functions (Cockpit and Cabin)

A 2 1 One may be inoperative provided: a) TCS fault codes have been

considered, and b) Repairs are made within three


|||||

4) CREW and PAX Auto

Temperature Potentiometer Functions

C 2 0 |||

5) Cockpit and Cabin Duct

Temperature Sensor Functions

A 2 1 One may be inoperative provided: a) TCS fault codes have been

considered, and b) Repairs are made within two


|||||

(Continued)




PAGE NO: 21-7





21 AIR CONDITIONING

14. Temperature Regulation (TCS) MANUAL mode

C 1 0 (M)(O)May be inoperative provided: a) Flight is conducted in an

unpressurized configuration, and b) EFIS fans are verified operative.

1) CREW and PAX Manual

Temperature Potentiometer Functions

A 2 1 One may be inoperative provided repairs are made within three consecutive calendar days.

|||

15. Cabin Temperature

Remote Control C 1 0

16. Cabin Temperature

Indicator C 1 0

17. Pressure Control Valve

(Gasper Supply Valve) C 1 0 (M) May be inoperative provided the EFIS

fans are verified operative. |

18. EFIS Blowers C 4 3 (M) One may be inoperative provided the

cold air supply system is verified to provide an adequate airflow to the EFIS.

|

19. Nose Cone Blower C 1 0 (M) May be inoperative provided:

a) NOSE CONE OVH’T warning system is verified operative,

b) NOSE CONE OVH’T warning is not displayed , and

c) NOSE CONE pressurization system is verified operative.

20. Pilot Gaspers C 2 1

C 2 0 Both may be inoperative provided at least

one gasper remains in open position. |




PAGE NO: 21-8





21 AIR CONDITIONING

21. Cabin Pressurization Low Rate Control (M48)

C 1 0

22. ***

Cabin Duct Temperature Indication

C 1 0

23. “RECIRC ISOL” Caution

Light C 1 0 May be inoperative provided Cabin air

recirculation valve (item 21-11) is considered inoperative.

24. “ECU OVHT” Caution

Light C 1 0 May be inoperative provided the

conditioning pack (item 21-8) is considered inoperative.

25. “CREW” Amber Light C 1 0 (M) May be inoperative provided reading

the TCS fault codes is performed using the FCD before each departure.

|||

26. “PAX” Amber Light C 1 0 (M) May be inoperative provided reading

the TCS fault codes is performed using the FCD before each departure.

|||

27. ***

Glare Shield Cold Air Manual Control (M1992)

D 1 0




PAGE NO: 21-9





21 AIR CONDITIONING

28. Temperature Regulation System

C 1 0 (M)(O)May be inoperative provided: a) Flight is conducted in an

unpressurized configuration, and b) EFIS fans are verified operative.

||||||

1) Alarm Light Command

Functions (Auto Cockpit, Auto Cabin, and Manual Modes)

A 3 0 One or more may be inoperative provided repairs are made within three consecutive calendar days.

|||

2) Turbine Temperature

Control Functions (Auto and Manual Modes)

A 6 0 One or more may be inoperative provided repairs are made within two consecutive calendar days.

||||




PAGE NO: 22-1





22 AUTO FLIGHT

1. Autopilot Computer

1) AP Function C 1 0 (O) Except where en-route operations require its use, may be inoperative provided:

a) Approach minimums do not require its use, and

b) Flight time is limited to four hours.

|

||

NOTE: Any mode, which is operative,

may be used.

2) FD Function C 2 0 (O) One or more may be inoperative provided:

a) Approach minimums do not require its use,

b) Autopilot is not used, and c) Flight time is limited to two hours.

|

||

3) Yaw Damper C 1 0 (M)(O) May be inoperative provided:

a) Rudder is verified to be in the neutral position before each departure, and

b) “R” label on PFD in not displayed on the EFIS.

|

4) Mach Trim Function C 1 0 May be inoperative provided airspeed

does not exceed .80 Mach.

5) AP Warning Light C 1 0 (O) May be inoperative provided annunciation on EFIS and aural warning are verified operative.




PAGE NO: 22-2





22 AUTO FLIGHT

2. Autopilot Disengage Switches

C 2 1 (O) 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 (O) Both may be inoperative provided:

a) Autopilot is not used, and b) Flight time is limited to four hours.

|||

3. Go-Around Buttons C 2 1 (O) Copilot’s button may be inoperative. C 2 0 One or more may be inoperative provided

autopilot or flight director is not used below 1500 feet AGL.

|

4. Flight Control Panel

(FCP) C 1 0 (O) Except where en-route operations

require the use of ALT AP function, may be inoperative provided:

a) ASEL and course functions are verified operative before takeoff, and

b) Autopilot and flight director are considered inoperative.

|

|

5. Pitch or Roll Servomotors C 2 0 (O) Except where en-route operations

require the use of AP function, one or more may be inoperative provided:

a) Autopilot is not used, and b) Flight time is limited to four hours.

|||||




PAGE NO: 23-1





23 COMMUNICATIONS

1. Radio Tuning Unit (RTU) C 2 1 (O) Co-pilot RTU may be inoperative provided:

a) Tuning of the radios by FMS is operative, and

b) AFM limitations are observed.

2. Communications Systems (VHF or UHF)

D - - Any in excess of those required by FAR, and not powered by an Essential Bus or required for emergency procedures may be inoperative.

3. High Frequency (HF)

Communication System(s)

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

C - 1 (O) May be inoperative while conducting

operations that require two Long Range Communications Systems (LRCS) provided:

a) SATCOM Voice or Data Link operates normally,

b) Alternate procedures are established and used,

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

d) If SATCOM Voice is to be used over the intended route of flight, SATCOM Voice short codes (INMARSAT) or direct dial commercial numbers (IRIDIUM) must be available. If not available, prior coordination with appropriate ATS (FIR) facility is required.

| | | | | | | | |

NOTE: SATCOM is to be used only as a

backup to normal HF communications.




PAGE NO: 23-2





23 COMMUNICATIONS

4. Flight Deck Speakers C 2 0 One or more may be inoperative provided:

a) Procedures do not require the use of speakers, and

b) Associated headset for the inoperative side(s) is installed and is operative.

|

5. Headsets, Hand-held

Microphones C - - Any in excess of those required for flight

deck crewmembers (including official observer in observer’s seat) may be inoperative.

|

6. Audio Panels

1) Side Tone Pushbuttons C - 0

2) ADF Pushbuttons C - 1 C - - Any in excess of Radio Compass System

(ADF) required by FAR may be inoperative.

3) MKR Pushbuttons C - 1 C - - As required by FAR

4) FILT Pushbuttons C - 1 May be inoperative provided VHF Navigation Systems operates normally without filter functions.

|

5) SPK Pushbuttons C - - May be inoperative provided Flight Deck

Speakers (item 23-4) are considered inoperative.

6) ISOL Pushbuttons C - 0




PAGE NO: 23-4





23 COMMUNICATIONS

7. Public Address System

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 (audio and visual) system operates normally.

l l

NOTE: Any station function(s) that

operate normally may be used. C 1 0 (O) May be inoperative provided:

a) PA not required by FAR, and b) Alternate, normal and emergency

procedures, and/or operating restrictions are established and used.

NOTE: Any station function(s) that

operate normally may be used. a) Lavatory Speakers C - 0 (O) May be inoperative provided alternate

procedures are established and used.

2) Cargo Configuration D - 0 May be inoperative provided procedures do not require its use.

8. ***

SELCAL C - 0 May be inoperative provided alternate procedures are established and used.

||

D - 0 May be inoperative provided procedures

do not require its use. ||

9. Static Dischargers Deleted Rev 8 |




PAGE NO: 23-5





23 COMMUNICATIONS

10. ***

ACARS C - 0 May be inoperative provided alternate procedures are established and used.

11. ***

AFIS (VHF/SAT) C - 0

12. Cockpit Voice Recorder

System (CVR)

1) With Flight Data

Recorder (FDR) Installed A 1 0 May be inoperative provided:

a) Flight Data Recorder (FDR) operates normally, and

b) Repairs are made within three consecutive calendar days.

l

|*** Independent Power

Source C 1 0 l

l

2) Without Flight Data Recorder (FDR) Installed

A 1 0 May be inoperative provided repairs are made within three consecutive calendar days.

|

*** Independent Power Source

C 1 0 ll

3) For an operator other

than a holder of an air carrier or commercial operator certificate.

A 1 0 May be inoperative provided repairs are made in accordance with applicable FARs.

*** Independent Power Source

C 1 0 l l

13. ***

SATCOM D 1 0




PAGE NO: 23-6





23 COMMUNICATIONS

14. Boom Microphones

1) ***

Cockpit Voice Recorder Equipped to Record Boom Microphone per FAR 121.359(g), 135.151 (d) or 125.227 (e): With FDR Installed

A - 0 May be inoperative provided: a) Flight data recorder (FDR) is

operative, and b) Repairs are made within three

consecutive calendar days. |

2) Cockpit Voice Recorder

Equipped to Record Boom Microphone per FAR 121.359(g), 135.151 (d), or 125.227 (e): Without FDR installed

A - 0 May be inoperative provided repairs are made within three consecutive calendar days.

|

15. Emergency Locator

Transmitter (ELT)

Survival Type ELTs D - - Any in excess of those required by FAR

may be inoperative or missing. Fixed ELTs A - 0 May be missing provided repairs are

made within 90 consecutive calendar days.

||

A - 0 (M) May be inoperative provided:

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

consecutive calendar days

|

D - - Any in excess of those required by FAR

may be inoperative or missing. D - - (M) Any in excess of those required by

FAR may be inoperative provided system is deactivated.




PAGE NO: 24-1





24 ELECTRICAL POWER

1. DC Voltmeter C 2 1 (O) RH voltmeter may be inoperative provided:

a) Ammeter of the associated DC generating system is operative, and

b) RH BUS TIED, LH BUS ISOL, GEN 1 and GEN 2 caution lights are verified operative.

||||

2. Battery Temperature

Indicating System

1) Temperature Indication C 1 0 (O) May be inoperative provided:

a) Both lights on the indicator and the HOT BAT light are operative, and

b) Battery blower is verified operative.

|||

2) Indicator’s Amber and

Red Lights C 2 1 (O) One may be inoperative provided:

a) Battery temperature indicator is operative,

b) Remaining indicator light and HOT BAT light are operative, and

c) Battery blower is verified operative.

||

||

3. Battery Blower C 1 0 (M)(O) May be inoperative provided the

HOT BAT monitoring system is verified operative.

|

4. BUS TIED Light C 1 0 (O) May be inoperative provided the ESS

bus tie circuit and the voltmeters are operative.

5. LH BUS ISOL Light C 1 0 (O) May be inoperative provided the

LH/ESS bus tie circuit and voltmeters are operative.




PAGE NO: 24-2





24 ELECTRICAL POWER

6. GEN Lights C 2 1 (O) One may be inoperative provided: a) Voltmeter and ammeter of the

associated DC generating system are operative, and

b) Generator output current is closely monitored during flight.

7. ***

Emergency Power Supply System (Communications Auxiliary Power)

C - 0




PAGE NO: 25-1





25 EQUIPMENT/ FURNISHINGS

1. Pilot Seat(s)

1) Vertical Adjustment C 2 0 (M)(O) One or more may be inoperative provided:

a) Seat is secured at the individual crewmember’s requirements,

b) Fore-aft adjustment is operative, and

c) The associated “CREW SEATS” C/B is pulled and collared.

|

2) Armrests C 4 0 (M)(O) One or more may be inoperative

provided: a) Affected armrest is in the up

position or removed, and b) Seat is acceptable to the affected

crewmember.

|

3) Recline Adjustment C 2 0 (M)(O) One or more may be inoperative

provided: a) Seat is secured at a position

acceptable to the affected crewmember, and

b) Seat is able to move full Fore and Aft on its track.

|

4) Headrests C 2 0 (O) Headrest fairing only may be

damaged provided: a) Headrest structure is verified

adequate, and b) Seat is acceptable to the affected

crewmember.




PAGE NO: 25-2






2. Rudder Pedal

Adjustment C 2 0 (M) One or more may be inoperative

provided: a) Adjustments can be secured in a

position that suits individual pilot(s) requirements, and

b) Position of pedal(s) permits normal full flight control movement.

|

3. Not Used




PAGE NO: 25-3






4. Passenger Seat(s) C - - (O) 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 seat(s) 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 C - - (M) May be inoperative and seat occupied

provided seat is secured in the up-right position.

|

2) Armrests C - - May be inoperative 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.

(Continued)




PAGE NO: 25-4






4. Passenger Seat(s)

(Cont’d)

3) 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.

4) ***

Electrical/Electronic Systems/Components

C - - (M) May be inoperative and seat occupied provided associated component(s) is deactivated.

5) Swivel Mechanism C - - May be inoperative and seat occupied

provided: a) Associated seat does not block an

emergency exit, b) Associated seat does not restrict

any passenger from access to main aisle, and

c) Associated seat remains in the take-off position for take-off and landing.

6) Forward/Aft Tracking

Mechanism C - - May be inoperative and seat occupied

provided: a) Associated seat does not block an

emergency exit, b) Associated seat does not restrict

any passenger from access to main aisle, and

c) Associated seat remains in the take-off position for take-off and landing.

(Continued)




PAGE NO: 25-5






4. Passenger Seat(s)

(Cont’d)

7) Headrests C - - May be inoperative, and seat occupied,

provided the associated passenger seat is in takeoff position.

5. Observer Seat(s) |

1) Forward Observer Seat (Including Associated Equipment)

A 1 0 (M)(O) 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 consecutive calendar days.

|

| A 1 0 (M)(O) May be inoperative provided:

a) Forward Observer’s Seat is available with the required minimum safety equipment (safety belt and oxygen) and acceptable to the FAA for the performance of official duties, and

b) Repairs are made within two consecutive calendar days. |

NOTE 1: These provisos are intended to

provide for occupancy of the above seat by an FAA inspector when the minimum safety equipment (oxygen and safety belt) is functional and the inspector determines the 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 observer seat.

(Continued) |




PAGE NO: 25-6






5. Observer Seat(s)

(Cont’d) |

|

1) Forward Observer Seat (Including Associated Equipment) (Cont’d)

NOTE 3: When not occupied, the observer seat must be stowed so as to not impede egress from the cockpit. |


than a holder of an air carrier or commercial operator certificate

D - 0 NOTE: The pilot-in-command will determine if the minimum safety equipment is functional for other persons authorized to occupy any observer seat.

||||

6. Emergency Locator

Transmitter (ELT) Item transferred to ATA 23, MMEL REV7 |

|

7. ***

Passenger Convenience/NEF Items

|

*** Non –Essential

Equipment & 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 operators (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 NEF items.

|

|

||




PAGE NO: 25-7






8. ***

Flight Phone D - 0

9. Lavatory Door Ashtrays

1) Airplanes With More Than One Lavatory Door Ashtray Installed

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

|

2) Airplanes With Only One

Lavatory Door Ashtray Installed

A 1 0 May be missing provided it is replaced within three consecutive calendar days. |

10. ***

Cockpit Smoke Vision System (CSVS) (STC # SA00892LA)

D - 0 May be inoperative or missing provided procedures do not require its use.

ll

11. Aircraft Ladders

1) Forward/Aft Service

Compartment Ladders C 2 0 (M) May be removed or inoperative in the

stowed position.

2) ***

Portable Ladder

D - 0 May be removed or inoperative in the stowed position.

12. Exterior Baggage Door C 1 0 (M) May be inoperative provided Door is

verified closed and secure prior to each departure.




PAGE NO: 25-8






13. Baggage Compartment

Shelves

1) Shelf Stowage Straps D 2 0 One or more may be inoperative or

removed provided the shelves remain in the down position.

|||

2) Shelf Support Straps D 4 0 One or more may be inoperative or

removed provided the associated shelf remains in the stowed (up) position and is not used.

|

3) Shelves D 2 0 One or more may be removed or

inoperative provided the shelf remains in the stowed (up) position and is not used.

|

14. Overwater Equipment

(Flotation Devices/Rafts) D - - Any in excess of those required by FAR

may be inoperative or missing.

15. Crewmember Flashlight Holder Assemblies (Including Flashlight)

C - - May be inoperative or missing provided crewmember has a flashlight of equivalent characteristics readily available.

16. Cockpit Convenience

Items - - Refer to item 25-7

17. Keyed Locks C - 0 (O) May be inoperative provided the associated door, compartment, or cap is verified secure prior to each departure.

18. ***

Galley-to-Cabin Sliding Door (“Pocket” Door)

D 1 0 (M) May be inoperative provided the door is secured in open position using an acceptable means.




PAGE NO: 25-9






19. 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 1 flight. l


may be incomplete, missing, or inoperative.

20. 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







PAGE NO: 25-10






21. First Aid Kit (FAK) and/or

Associated Equipment A - - (O) If more than one is required by FAR,

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







PAGE NO: 26-1





26 FIRE PROTECTION

1. Hand Fire Extinguishers D - - Any in excess of those required by FAR may be inoperative or missing provided:

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

b) Required distribution is maintained.

2. ***

AFT Lavatory and LH Crew Closet Smoke Detectors (M1620)

D 2 - Any in excess of those required by FAR may be inoperative or missing.




PAGE NO: 27-1





27 FLIGHT CONTROLS

1. T/O CONFIG Warning Light

C 1 0 (O) May be inoperative provided the aural warning is verified operative. |

2. Horizontal Stabilizer

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

a) Stabilizer is verified to be between the two takeoff reference marks before each departure,

b) Stabilizer trim is operative, c) T/O CONFIG warning system is

verified operative, d) Horizontal Stabilizer Trim Audio

Warning is operative, and e) Touch and go training maneuvers

are prohibited.

|||

3. Horizontal Stabilizer Trim

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

a) Stabilizer trim is verified operative,b) T/O CONFIG warning system is

verified operative, c) Horizontal stabilizer position

indicator is verified operative, andd) Autopilot is not used.

|

|

|

4. Elevator Arthur Variable

Bellcrank B 1 0 (M) May be inoperative provided:

a) PITCH FEEL circuit breaker is pulled and collared,

b) Arthur Bellcrank low speed position is verified prior to departure,

c) Airspeed does not exceed 260 KIAS/. 76 Mach, and

d) Stabilizer is verified to be between the two takeoff reference marks before each departure.

NOTE: For A/C with SN < 62, Arthur

Variable Bellcrank low speed position is to be verified with engines running.




PAGE NO: 27-2





27 FLIGHT CONTROLS

5. PITCH FEEL Caution Light

B 1 0 (M)(O) May be inoperative provided: a) Arthur Bellcrank low speed

position is verified before departure,

b) Airspeed does not exceed 260 KIAS/ .76 Mach, and

c) AFM limitations are observed.

6. Roll Trim Control System C 1 0 (M)(O) May be inoperative provided: a) Roll Trim is verified in neutral

position, b) Rudder trim system is operative , c) TRIM AILERON circuit breaker is

pulled and collared, d) Fuel quantity indicators are

operative, and e) Fuel imbalance is limited to 500

lbs or less.

|

7. Roll Trim Position

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

a) Roll trim control system is operative,

b) The two control surfaces are verified to be in the same position,

c) Fuel quantity indicators are operative, and

d) Fuel imbalance is limited to 500 lbs or less.

|

8. AIL ZERO Light B 1 0 (M)(O) May be inoperative provided it is

verified before each departure that the left and right ailerons are in the same position when roll trim is set to zero.




PAGE NO: 27-3





27 FLIGHT CONTROL

9. Aileron Arthur Variable Bellcrank

C 1 0 (M)(O) May be inoperative provided: a) Roll control forces are verified to

be in low speed configuration before each departure,

b) AIL FEEL circuit breaker is pulled and collared, and

c) AFM limitations are observed.

10. Arthur AIL FEEL Caution Light

C 1 0 (O) May be inoperative provided the roll control forces are verified in the low speed configuration before each departure.

11. Rudder Trim Control

System A 1 0 (M) May be inoperative provided:

a) Rudder trim is verified in neutral position before each departure,

b) Aileron trim system is operative, c) TRIM RUDDER circuit breaker is

pulled and collared, d) Fuel quantity indicators are

operative, e) Fuel imbalance is limited to 500

lbs or less, and f) Repairs are made within two


12. Rudder Trim Position Indicator

C 1 0 (M)(O) May be inoperative provided Rudder Trim is verified in the neutral position before each departure.

13. Emergency Slat

Extension (EMERG SLATS)

B 1 0 (O) May be inoperative provided: a) Normal control is verified

operative before each departure, and

b) AFM limitations are observed.




PAGE NO: 27-4





27 FLIGHT CONTROLS

14. Slat Configuration Panel

1) Green Light B 1 0 (O) May be inoperative provided: a) Position of the slats and the

control are verified in agreement before each departure,

b) T/O CONFIG warning system is verified operative,

c) Wing anti-ice lights are operative, and

d) Amber (In Transit) Light is operative.

|

2) Amber Light C 1 0 (O) May be inoperative provided AFM

limitations are observed.

15. STALL Aural Warning C 2 1 (M)(O) One may be inoperative provided:a) Both automatic slat extension

systems are verified operative before each departure,

b) Automatic ignition systems are verified operative before each departure, and

c) Slat configuration panel is operative.

|

|||||

16. STALL Test A 2 1 One may be inoperative provided:

a) Slats are extended with the normal control at speeds below 180 KIAS,

b) Slat configuration panel is operative,

c) AUTO SLATS light is operative, and

d) Repairs are made within two consecutive calendar days. |




PAGE NO: 27-5





27 FLIGHT CONTROLS

17. AUTO SLATS Light C 1 0 May be inoperative provided: a) Airspeed does not exceed 270

KIAS, b) Slats are extended with normal

control at speeds below 180 KIAS, and

c) The slat configuration panel is operative.

18. FLAPS ASYM Light C 1 0 (M)(O) May be inoperative provided:

a) Flap asymmetry protection system is verified operative, and

b) Flap symmetry is verified before each departure.

|

19. AIRBRAKE Light B 1 0 (M)(O) May be inoperative provided:

a) Airbrakes are verified operative, b) Airbrakes are verified in the

retracted position for each departure,

c) STALL tests are verified operative before each departure, and

d) T/O CONFIG warning system is verified operative.

||

|

20. ***

PITCH AFU Heating System

D 1 0 (M) May be inoperative provided it is secured.

||

1) PITCH AFU OVERHEAT

Magnetic Indicator D 1 0 Magnetic indicator (MINELCO) may be

tripped provided the PITCH AFU Heating System (item 27-20.) is considered inoperative.

|

|

2) PITCH AFU HEAT TEST

Light D 1 0 (M) May be inoperative provided PITCH

AFU OVERHEAT Minelco is not tripped red.

D 1 0 May be inoperative provided PITCH AFU

Heating System (item 27-20.) is considered inoperative.

||




PAGE NO: 27-6





27 FLIGHT CONTROLS

21. Servo-Actuator Integrated Anti-Flutter Functions

A 8 7 (M) One may be inoperative for three flights or 10 flight hours, whichever occurs first, provided the associated servo-actuator is verified before each flight. |




PAGE NO: 28-1





28 FUEL

1. Booster Pumps Deleted Rev. 3.

2. XTK Valve Deleted Rev. 3.

3. XBP Crossfeed Valves Deleted Rev. 3.

4. Gauging System (EIED)

1) Channels C 2 1 (M)(O) One channel may be

inoperative provided: a) Fuel quantity is determined by

other acceptable means, b) Fuel Flow/Fuel Used indicators

are operative, c) LEVEL and LO FUEL lights are

verified operative, d) Warning panel is operative, and e) Partial fueling selector is not

used.

|

5. LEVEL Lights C 2 0 (O) One or more may be inoperative

provided: a) Gauging system is operative,

and b) LO FUEL lights are verified

operative.

| |

6. LO FUEL Lights B 2 1 (O) One may be inoperative provided:

a) Gauging system is operative, and

b) LEVEL lights are verified operative.

|

7. Fuel Temperature

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

a) Flights are planned with outside temperature above ISA -20degreesC, and

b) Initial fuel temperature is above -30 degrees C




PAGE NO: 28-2





28 FUEL

8. Pressure fueling System

C 1 0 (O) May be inoperative OFF provided cockpit FUELING amber light is operative.

1) Vent Valves C - 0 (M) May be inoperative provided:

a) Affected vent valve(s) is(are) manually operated prior/after refueling,

b) If STOP FUELING red indicator light remains lighted after opening of the vent valves, gravity refueling is used, and

c) Cockpit FUELING caution light is operative and is extinguished after closing sequence.

2) Refueling valves A 2 1 (M)(O) One may be inoperative

provided: a) Inoperative Refueling Valve is

verified in closed position, b) Gravity refueling is used, and c) Repairs are made within three


| |

3) Fuel High Level

Detection System A 1 0 May be inoperative provided:

a) Full refueling is not used, b) Cockpit fuel quantity indications

are operative and are checked during refueling operation, and

c) Repairs are made within three consecutive calendar days.

|

4) Refueling Gauging

System C - 0 May be inoperative provided:

a) FULL lights are operative, and b) Partial refueling is not used.

|




PAGE NO: 28-3





28 FUEL

9. FUELING Light C 1 0 (M) May be inoperative provided: a) Both fueling panel access doors

are verified closed, b) Fuel tanks are verified properly

pressurized with engines running,

c) Defueling valve is verified closed, and

d) The DEFUELING switch remains in the OFF position.

|| |

10. Fuel Quantity

Management Computer (FQMC) Channels

A 2 1 (M)(O) One Channel may be inoperative provided:

a) It is verified that the fault comes from the fuel system,

b) Remaining computer Channel is verified operative, and


|

1) Magnetic Indicator

Driver Functions A 2 0 One or more may be inoperative

provided: a) FQMC fault codes have been

considered before each departure, and

b) Repairs are made within three consecutive calendar days

|||||||

2) Pulse Input Built-In

Tests C 2 0 (O) One or more may be inoperative

provided: a) FQMC fault codes have been

considered, b) Fuel Flow, Fuel Used and QTY

indications are operative and consistent, and

c) Fuel indications are monitored during the flight.

|||||||||




PAGE NO: 29-1





29 HYDRAULIC POWER

1. PUMP .. HYDR# Caution Lights

C 3 2 (O) One may be inoperative provided: a) Standby hydraulic pump is

verified operative before engine start,

b) Associated hydraulic system pressure indicator is verified operative and is monitored during flight, and

c) ST BY PUMP and HYDR#2 ISOL caution lights are verified operative.

| |||

2. System 1 or 2

Pressure Indicators (EIED)

C 2 1 (O) One may be inoperative provided: a) Standby hydraulic pump is

verified operative before engine start,

b) Associated hydraulic system PUMP indicator light(s) is/are verified operative, and

c) ST BY PUMP and HYDR#2 ISOL caution lights are verified operative.

||||

3. HYDR TK PRESS

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

a) Both hydraulic pressure indicators are verified operative,

b) Hydraulic system pressure is monitored during flight, and

c) AFM procedures are applied.

|

4. Tank 1 Fluid Level

Indicator (EIED) C 1 0 (M) May be inoperative provided the

tank fluid level is verified before engine start.




PAGE NO: 29-2





29 HYDRAULIC POWER

5. ST BY PUMP Light C 1 0 (M)(O) May be inoperative provided: a) Standby pump selector valve is

secured in the No. 2 system position, and

b) Standby pump is verified operative before engine start.

6. Hydraulic Accumulator

Pressure Indicators C - 0 (M) May be inoperative provided an

alternate procedure to verify accumulator pressure is established and used.

7. Main Hydraulic

Accumulators C 2 1 System No. 1 Accumulator may be

inoperative.

8. ***

Thrust Reverser Hydraulic Accumulators

C 2 0 One or more may be inoperative provided associated Thrust Reverser System (item 78-1) is considered inoperative.

| |

9. Hydraulic Filter

Clogging Indicators C 9 8 (M) One indicator may be tripped red

provided It is reset once during the 10-days period and is verified to remain reset before each flight during the rectification interval.




PAGE NO: 30-1





30 ICE AND RAIN PROTECTION

1. Wing Anti-Icing System C 1 0 (O) May be inoperative provided:

a) Airplane is not operated in the known or forecast icing conditions, and

b) Wing anti-ice valve is verified in the closed position.

1) Green Light (overhead

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

a) The wing anti-icing check is found satisfactory, and

b) ANTI-ICE caution light (warning panel) is operative.

2. Engine Anti-Icing

Systems B 2 1 (O) One may be inoperative provided:

a) Airplane is not operated in known or forecast icing condition, and

b) Engine anti-icing valve is verified in the closed position.

1) Green Lights

(overhead panel) C 2 0 (O) One or more may be inoperative

provided: a) The engine anti-icing system

check is found satisfactory, b) ANTI-ICE caution light (warning

panel) is operative.

| |

2) Engine T2 Probe Anti-

Icing Systems B 2 1 (O) One may be inoperative provided:

a) Related engine anti-icing system is set to OFF, and

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

||||||




PAGE NO: 30-2






3. ANTI-ICE Light

(Caution Panel) C 1 0 (O) May be inoperative provided the

Anti-Ice overhead panel related lights are verified operative and are monitored during flight.

||

4. Windshield DE-FOG

Systems C 2 0 One or more may be inoperative

provided both the pilots and copilots windshield heating systems are operative.

|

5. Windshield Wipers C 2 0 One or more may be inoperative or

missing provided: a) Airplane is not operated in

precipitation within five nautical miles of the airport of takeoff or intended landing, and

b) Approach minimums do not require its use

|

B 2 1 (M) One may be inoperative in non-rest

position provided: a) Airplane is not operated in

precipitation within five nautical miles of the airport of takeoff or intended landing,

b) Pilot flying is on the non affected side,

c) Airplane is operated with a maximum speed of 215 kt, and

d) Associated circuit breaker is pulled and collared.

6. Windshield Heating

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

a) Remaining side is operative, b) Windshield DE-FOG systems

are verified operative, and c) Airplane is not operated in

known or forecast icing conditions.

| ||




PAGE NO: 30-3






7. XFR Light C 1 0 (M)(O) May be inoperative provided

a) Temperature controller, controller transfer system and heating networks are verified operative, and

b) Windshield DE-FOG systems are verified operative.

| ||

8. Side and Rear Flight

Deck Windows Heating C 1 0

9. Pitot Probe Heating

Systems B 3 2 (O) Either the Pilot’s or Copilot’s

system may be inoperative for day VMC provided the airplane is not operated in visible moisture or in known or forecast icing conditions.

10. Normal Static Port

Heating Systems B 2 1 (O) One may be inoperative provided:

a) Airplane is not operated in known or forecast icing conditions, and

b) RVSM operations are not planned.

11. Angle of Attack Probe

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

a) Airplane is not operated in the known or forecast icing conditions,

b) Stall 1 and 2 tests are operative,

c) Pitot probe heating systems are operative, and

d) Normal static port heating system is operative.

||||||




PAGE NO: 30-4






12. LH PROBES, RH

PROBES, STB-BY PITOT Heater Lights

B 3 2 (M)(O) One may be inoperative provided:

a) Associated heater is verified operative before each departure, and

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

13. TAT Probe Heating

System B 1 0 (O) May be inoperative provided

airplane is not operated in known or forecast icing conditions.

14. ***

Brake Heating System D 1 0 (M)(O) May be inoperative provided: a) Brake Heating Valves are

secured in closed position, and b) Brake Heating System

(WINGS-BRK position overhead panel) is not used.

15. ***

Ice Detection System (M1893)

D 1 0 (M) May be inoperative provided the ICE DETECTOR circuit breaker is pulled and collared.

|||

1) ICE Light (cyan) D 1 0 May be inoperative provided ice

detection system (item 30-15.) is considered inoperative.

|

2) FAIL Light (white) D 1 0 May be inoperative provided ice

detection system (item 30-15.) is considered inoperative.

|




PAGE NO: 31-1





31 INDICATING/ RECORDING SYSTEMS

1. Digital Flight Data

Recorder (DFDR) System

C - - Any in excess of those required by FAR may be inoperative.

Includes FDR function of Combined Voice and Flight Data Recorder (CVFDR)

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

operative, b) Airplane is not dispatched from a

designated airport as listed in the operator’s MEL unless:

1. The FDR failure occurs after pushback but prior to takeoff, or

2. FDR repair was attempted but was not successful.

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

d) Repairs are made within three consecutive calendar days.

|||| | |

1) FDR Recording

Parameters required by FAR

A - - Up to three (3) recording parameters may be inoperative provided:

a) Cockpit Voice Recorder (CVR) operates normally, and

b) Repairs are made within 20 calendar days.

| |||

2) FDR Recording

Parameters not required by FAR

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

(Continued)




PAGE NO: 31-2






1. Digital Flight Data

Recorder (DFDR) System (cont'd)


than a holder of an air carrier or commercial operator certificate.

C - 1 Any in excess of those required by FAR may be inoperative.

A - 0 May be inoperative provided repairs

are made in accordance with FARs.

2. Clocks C 2 - Any in excess of those required by

FAR may be inoperative at either the pilot or copilot station.

3. Engine Indication

Electronic Display (EIED)

B 3 2 (O) The lower display may be inoperative provided:

a) No displayed parameter has failed,

b) Remaining EIEDs manual reconfiguration is verified operative, and

c) Associated warning lights are operative.

|

1) Display Link Functions C 6 - |




PAGE NO: 31-3






4. Computer Magnetic

Indicator (Minelco) B 7 - One or more may be failed white or

tripped red provided related computer(s) is(are) considered inoperative.

||||

5. Hydraulic Magnetic Indicator (Minelco)

B 8 - One or more may be failed white or tripped red provided the fault is not confirmed and comes from the indicating system.

||||

6. ***

Master Warning/ Master Caution Lights System (Mod 298)

C 1 0

7. Engine Indication

Electronic Display (EIED) Fault Message(s)

Deleted Rev. 8. |

8. ***

Quick Access Recorder (QAR) (SB227 or Mod 1896)

C 1 0 May be inoperative provided no Digital Flight Data Recorder (DFDR) or Flight Data Acquisition Unit (FDAU) fault is reported on the Flight Data Entry Panel (FDEP).

C 1 0 May be inoperative provided the DFDR

is considered inoperative. ||




PAGE NO: 31-4






9. Overhead Panel

Switch / Indicator Bulbs or LED

|||

1) EXT PWR Switch

Lights (Electrical Area) C 4 2 One or more bulbs may be inoperative. |

|

2) START/STOP Switch

Lights (APU Area) C 4 2 One or more bulbs may be inoperative. |

| A 4 0 One or more bulbs may be inoperative

provided: a) APU is considered inoperative,

and b) Repairs are made within two


||||||

3) MASTER Switch Lights

(APU Area) C 4 2 One or more bulbs may be inoperative. |

| A 4 0 One or more bulbs may be inoperative

provided: a) APU is considered inoperative,



||||||

(Continued)




PAGE NO: 31-5






9. Overhead Panel

Switch / Indicator Bulbs or LED (Cont’d)

4) LH AV MASTER

Switch Lights (Circuit Breaker Area)

|||

a) S/N 173 and below C 4 2 One or more bulbs may be inoperative. |

b) S/N 174 and above C 8 4 One or more LED may be inoperative. |

5) RH AV MASTER Switch Lights (Circuit Breaker Area)

|||

a) S/N 173 and below C 4 2 One or more bulbs may be inoperative. |

b) S/N 174 and above C 8 4 One or more LED may be inoperative. |

6) XTK Amber Indicator Lights (Fuel Area)

B 2 1 (O) One bulb may be inoperative provided fuel interconnection valve monitoring is verified operative.

|||

7) X-BP Amber Indicator

Lights (Fuel Area) B 2 1 (O) One bulb may be inoperative

provided crossfeed units monitoring is verified operative.

|||

8) ISOL Amber Indicator

Lights (Air Conditioning Area)

B 2 1 (O) One bulb may be inoperative provided air isolation valve monitoring is verified operative.

|||

9) PAX Amber Indicator

Lights (Air Conditioning Area)

B 2 1 (O) One bulb may be inoperative provided TCS is operative in both AUTO and MAN modes.

|||

10) CREW Amber

Indicator Lights (Air Conditioning Area)

B 2 1 (O) One bulb may be inoperative provided TCS is operative in both AUTO and MAN modes.

|||




PAGE NO: 32-1





32 LANDING GEAR

1. L/G Handle Flashing Light

C 1 0 (O) May be inoperative provided: a) L/G configuration panel is

operative, and b) GEAR aural warning is verified

operative.

|

2. Nose Wheel Steering

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

a) NOSE WHL 1 and NOSE WHL 2 circuit breakers are pulled and collared,

b) Nose Wheel is verified free to caster,

c) Nose Wheel Steering is not used,

d) Two braking systems are verified operative,

e) Airplane is not operated to or from an airport with standing water or contamination on the runways,

f) Thrust reverser system is not used,

g) Operations are limited to crosswinds of 10KTS or less, and

h) Repairs are made within two consecutive calendar days.

|||| |||| || |

3. BRAKE ACCU Light C 1 0 (M) May be inoperative provided the

park brake accumulator pressure is verified adequate once each flight day.




PAGE NO: 32-2





32 LANDING GEAR

4. Braking and Steering Control Units (BSCU)

A 2 1 (M)(O) Right braking system may be inoperative provided:

a) RH (#2) BSCU is deactivated and secured by an acceptable procedure,

b) BRAKES warning light is verified operative and is extinguished,

c) No messages related to Weight-on-Wheel system is present on E.I.E.D,

d) Hydraulic indication and warning are operative,

e) Standby hydraulic pump is verified operative before engine start,

f) AHS#1 and AHS#2 are operative,

g) Park brake accumulator pressure is verified adequate,

h) Nose wheel steering is operative,

i) AFM limitations are observed, and

j) Repairs are made within two consecutive calendar days.

| |

1) Main Gear Contact

Functions A 4 3 (O) One may be inoperative provided:

a) No message relevant to Weight-On-Wheel system is reported on EIED,

b) Front gear contact functions are operative,

c) Landing distance is increased by 10%, and

d) Repairs are made within two consecutive calendar days.

||||||||||




PAGE NO: 32-3





32 LANDING GEAR

4. Braking and Steering Control Units (BSCU) (Cont’d)

|||

2) Front Gear Contact

Functions A 2 1 (O) One may be inoperative provided:

a) No message relevant to Weight-On-Wheel system is reported on EIED,

b) Main gear contact functions are operative,

c) Thrust Reverser System is considered inoperative (item 78-1)

d) Landing distance is increased by 10%, and

e) Repairs are made within two consecutive calendar days.

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

3) NWS Functions C 2 1 |

4) AHS Data Functions C 4 3 One may be inoperative provided landing distance is increased by 10%.

||

5) Gear Handle Functions C 2 1 One may be inoperative provided

landing Gear retraction System is operative.

|||




PAGE NO: 32-4





32 LANDING GEAR

5. Configuration Panel

1) LH L/G Green Indicator Lights

B 2 1 (O) One bulb may be inoperative provided Gear aural warning is verified operative.

|

2) RH L/G Green

Indicator Lights B 2 1 (O) One bulb may be inoperative

provided Gear aural warning is verified operative.

|

3) Nose L/G Green


provided Gear aural warning is verified operative.

|

4) LH L/G Red Indicator

Lights B 2 1 (O) One bulb may be inoperative

provided Gear Handle Light Flashing is operative.

5) RH L/G Red Indicator

Lights B 2 1 (O) One bulb may be inoperative


6) Nose L/G Red






PAGE NO: 32-5





32 LANDING GEAR

6. Landing Gear Retraction System

A 1 0 (M)(O) May be inoperative for three flights or two calendar days, whichever occurs first, provided:

a) No abnormal L/G configuration panel indications displayed during last previous flight before failure occurred,

b) L/G configuration panel is operative,

c) Landing gears are down and locked,

d) Main landing gear doors are closed,

e) Landing Gear handle was not jammed in down position during the flight where the failure occurred,

f) Landing Gear handle is placarded in down position by a “DO NOT ACTUATE” red placard,

g) EGPWS (item 34-18) is considered inoperative,

h) Right Braking System is operative,

i) No BSCU fault code occurred during the flight prior to the flight that the failure occurred,

j) Aircraft is not operated in known or forecast icing conditions,

k) RVSM operations are not planned,

l) APU is operative, m) Landing distance is increased

by 10%, and n) AFM limitations are observed.

| |

NOTE: BSCU fault code(s) 315, 333,

415, 433 may be displayed. ||




PAGE NO: 33-1





33 LIGHTS

1. Flight Deck and Instrument Panel Lighting Systems

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

a) Not on emergency bus, b) Sufficient to clearly illuminate all

required instruments, controls, and other devices for which it is provided,

c) Position so that direct rays are shielded from flight crew member’s eyes, and

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

|||

NOTE 1: Individual button/switch lights and/or annunciations/indications are excluded from this relief. NOTE 2: Unaided operation (without NVGs) may be permitted with inoperative NVG supplemental lights; cracked or missing filters.

||| ||||

2. Passenger Cabin Normal Lighting System

C 1 - Individual lights may be inoperative or missing provided:

a) Inoperative lights do not exceed 50 percent of the total installed,

b) Cabin emergency lighting system is operative, and

c) Cabin lighting is sufficient for flight crew to perform required duties.

3. Forward and Rear

Compartments, and Nose Cone Lights

C 3 0

4. Baggage

Compartment Light C 1 0




PAGE NO: 33-2





33 LIGHTS

5. Fuel Area Lights

1) Pressure Fueling Bay Lights

C - 0 May be inoperative provided natural or alternate lighting is adequate.

2) Refueling Area Light

(M982) C 1 0

6. Landing Lights C 2 1 One may be inoperative provided taxi

light is operative.

C 2 0 Both may be inoperative for day

operations. |

1) ***

Pulse Light System C 1 0

7. Taxi Light C 1 0 May be inoperative provided both

Landing lights are operative.

C 1 0 May be inoperative for day operations.

8. Navigation Lights

1) Without M1401 or SB F2000-181

C 3 0 One or more may be inoperative for day operations.

|

2) ***

With M1401 or SB F2000-181

C 5 0 One or more may be inoperative for day operations.

|

C 5 3 One or more may be inoperative

provided at least one light is operative at each position.

|




PAGE NO: 33-3





33 LIGHTS

9. Red ANTICOL Light(s)

1) Single Light System

(S/N 52 and Below 4LX)

B 1 0 (O) May be inoperative provided WHITE ANTICOL lights are verified operative.

|

2) Dual Light System

(S/N 53 and Above 4LX and 6LX)

C 2 1

B 2 0 (O) Both may be inoperative provided

WHITE ANTICOL lights are verified operative.

||

10. White ANTICOL

Lights C 3 0 One or more may be inoperative

provided red ANTICOL light(s) is/are operative.

|

11. Wing Ice Detection

Lights C 2 1

C 2 0 Both may be inoperative for day

operations. |

C 2 0 Both may be inoperative for night

operations provided a portable light/lamp of adequate capacity is available for use in icing conditions.

|

C 2 0 Both may be inoperative for night

operations provided airplane is not operated in known or forecast icing conditions.

|

12. Exterior Emergency

Lighting System C 1 0 May be inoperative for day operations.




PAGE NO: 33-4





33 LIGHTS

13. Passenger Notice System (“No Smoking/Fasten Seat Belt/Return to Cabin” Signs

C - - (M)(O) One or more “No Smoking/Fasten Seat Belt/Return to Cabin” signs may be inoperative, provided the affected passenger seat(s), cabin attendant seat(s), or lavatory is blocked and placarded “DO NOT OCCUPY”.

C - - (O) If one or more “No Smoking/Fasten

Seat Belt/Return to Cabin” signs are inoperative, the affected passenger seat(s), cabin attendant seat(s), or lavatory may be occupied provided:

a) Passenger Address System is operating normally and can be heard clearly throughout the cabin during flight, and

b) An acceptable procedure is used to notify passengers when seat belts must be fastened, smoking is prohibited, and passengers should return to cabin from the lavatory.

1) Cockpit Switch Lights C 2 0 (O) Illuminated feature of the cockpit

No Smoking/ Fasten Seat Belt lighted switch may be inoperative provided:

a) Public Address System audio feedback is operative, and

b) Cabin No Smoking/Fasten Seat Belt lights are operative.

14. ***

Logo Lights (M1129 or M1746)

D - 0

15. Pylon Lights C - 0

16. ***

Chartholder Lightings (M1426)

D 2 0




PAGE NO: 33-5





33 LIGHTS

17. Interior Emergency Lighting

||

1) Floor Emergency

Escape Path Lights A - - One or more may be inoperative

provided: a) Emergency escape path lights

adjacent to passenger door and over-wing emergency exit are operative,

b) Other interior emergency lights are operative, and


||||||||||

C - 0 May be inoperative without passenger

on board. ||

2) Bulkhead Exit Sign C - - May be inoperative provided no seat

behind the bulkhead is occupied. ||

3) Pilot and Copilot

Emergency Dome Light bulbs

C 4 3 One bulb may be inoperative. |||

4) ***

Passenger Dome Lights (Mod. M3553)

D 2 0 ||

5) Passenger Door |

a) Exit Signs C 2 0 One or more may be inoperative without passenger on board.

||




PAGE NO: 33-6





33 LIGHTS

5) Passenger Door (Cont’d)

||

b) Opening Instruction

Sign C 1 0 May be inoperative without passenger

on board. ||

c) Spotlights C 2 1 One may be inoperative. | C 2 0 Both may be inoperative without

passenger on board. ||

6) Overwing Emergency

Exit |

|

a) Exit Signs C 2 0 One or more may be inoperative without passenger on board.

||

b) Handle Light C 1 0 May be inoperative without passenger

on board. ||

c) Opening Instruction

Sign C 1 0 May be inoperative without passenger

on board. ||




PAGE NO: 34-1





34 NAVIGATION

1. Display Controller Panels (DCP)

A 2 1 Co-pilot position may be inoperative provided:

a) Associated Reversion switch panel (RSP) is operative, and


| |

2. Reversion Switch

Panels (RSP) B 2 0 (O) One or more may be inoperative

provided: a) Both DCP’s are operative, and b) No reversion is selected.

|

3. Air Data Reference

Panels (ARP) B 2 1 (O) Co-pilot position IAS/MACH

function may be inoperative.

4. VHF Navigation

Systems (VOR/ILS) C - - As required by FAR.

5. Attitude and Heading

Reference System (AHRS) (IRS)

D - 2 Any in excess of the two required to independently power the Pilot’s and Copilot’s systems may be inoperative.

6. Altitude Alerting

System A 1 0 (O) Except where Enroute operations

required its use, may be inoperative provided:

a) Autopilot with altitude hold is operative, and


|

7. Not Used




PAGE NO: 34-2





34 NAVIGATION

8. VMO/MMO Aural Warnings

C 2 1 (O) One may be inoperative provided: a) Both Mach/airspeed indicators

are verified operative, and b) AFM VMO/MMO limitations are

observed.

| |

9. Stand-by Instruments

1) Stand-by Horizon Indicator (S/N 69 and below without Mod. M1578 or M1678)

B 1 0 (O) May be inoperative provided: a) Operations are conducted in

day VMC only, b) Non-stabilized magnetic

compass is operative, c) Standby airspeed indicator or

standby airspeed indication is operative,

d) Standby altimeter or standby altitude indication is operative, and

e) Operations are not conducted into known or forecast VFR-On-Top conditions.

(Continued)




PAGE NO: 34-3





34 NAVIGATION

9. Stand-by Instruments (Cont’d)

2) Secondary Flight

Display System (SFDS) (S/N 70 and above with Mod. M1578 or M1678)

a) Attitude Flag B 1 0 (O) May be displayed provided:

a) Operations are conducted in day VMC only,

b) Non-stabilized magnetic compass is operative,

c) Standby airspeed indicator or standby airspeed indication is operative,

d) Standby altimeter or standby altitude indication is operative, and

e) Operations are not conducted into known or forecast VFR-On-Top conditions.

b) LOC Flag C 1 0

c) LOC Flag with B/C Label

C 1 0

d) G/S Flag C 1 0

10. Non-Stabilized Magnetic (Standby) Compass

B 1 0 May be inoperative provided any combination of three gyro (or INS (IRU)) stabilized compass systems are operative.

|

(Continued)




PAGE NO: 34-4





34 NAVIGATION

10. Non-Stabilized Magnetic (Standby) Compass (Cont’d)

B 1 0 May be inoperative provided:

a) Any combination of two gyro (or INS (IRU)) compass systems is operative, and

b) Airplane is operated with dual independent navigation capability and under positive radar control by ATC during the enroute flight phase.

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, operative, and used in conjunction with approved free gyro navigation techniques.

1) Compass Lighting B 1 0 May be inoperative provided the non-

stabilized magnetic (standby) compass (Item 34-10) is considered inoperative.

||

C 1 0 May be inoperative for day operations

11. ***

DDRMI/BDRMI C - 0

12. Marker Beacon

System C - 0 As required by FAR |

13. Distance Measuring

Equipment (DME) D - - As required by FAR.

14. Radio Compass

System (ADF) C - - As required by FAR.




PAGE NO: 34-5





34 NAVIGATION

15. Weather Radar System

C 1 - As required by FAR.

16. Weather Radar

Control Panel

1) A/C without Mod.

M878 or M1174 C 1 0 May be inoperative provided the

weather radar (item 34-15) is considered inoperative.

2) ***

A/C with Mod. M878 or M1174

D 2 1 One may be inoperative.

C 2 0 Both may be inoperative provided the

weather radar (item 34-15) is considered inoperative.

|

17. Radio Altimeter A - 0 (M)(O) May be inoperative provided:

a) Dispatch deviation for GPWS is observed,

b) Approach minimums or operating procedures do not require its use, and

c) Repairs are made within two consecutive calendar days.

||




PAGE NO: 34-6





34 NAVIGATION

18. Class A TAWS Equipment Required

1) GPWS A 1 0 (O) May be inoperative provided:

a) Alternate procedures are established and used, and


a) Modes 1 Thru 4 A 4 0 (O) One or more may be inoperative

provided: a) Alternate procedures are

established and used, and b) Repairs are made within two


|

|

b) Test Mode A 1 0 May be inoperative provided:

a) GPWS is considered inoperative, and


c) Glideslope Deviation (s)

(Mode 5) C - 1

B - 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 FAR, and

b) Alternate procedures are established and used.

(Continued)




PAGE NO: 34-7





34 NAVIGATION

18. 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) are 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: 34-8





34 NAVIGATION

18. Class B TAWS Equipment Required

1) GPWS A 1 0 (O) May be inoperative provided:



a) Modes 1 & 3 A 2 0 (O) One or more may be inoperative

provided: a) Alternate procedures are

established and used, and a) Repairs are made within two


|

|

b) Test Mode A 1 0 May be inoperative provided: a) GPWS is considered inoperative,



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 FAR, and

b) Alternate procedures are established and used.

e) ***

Windshear Mode (Reactive)

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

(Continued)




PAGE NO: 34-9





34 NAVIGATION

18. 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 (RAAS)

C 1 0

Class C TAWS

Equipment

*** 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.




PAGE NO: 34-10





34 NAVIGATION

19. Traffic Alert Collision Avoidance System (TCAS)

1) TCAS System B - 0 (M) May be inoperative provided:

a) System is deactivated and secured, and

b) Enroute or approach procedures do not require its use.

C - 0 (M) May be inoperative provided:

a) Not required by FAR, b) System is deactivated and

secured, and c) Enroute or approach

procedures do not require its use.

2) ***

Combined TA and RA Dual Displays

C 2 1 One may be inoperative on the non-flying pilot side provided TA and RA elements and audio functions are operative on the flying pilot side.

3) Resolution Advisory

(RA) Display System(s)

C 2 1 One may be inoperative on the non-flying pilot side.

C - 0 May be inoperative provided:

a) All Traffic Alert (TA) display elements and voice command 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.

(Continued)




PAGE NO: 34-11





34 NAVIGATION

19. Traffic Alert Collision Avoidance System (TCAS) (Cont’d)

4) TA Display

System(s) C - 0 (O) May be inoperative provided:

a) all installed RA displays and audio functions are operative, and

b) Enroute or approach procedures do not require its use.

5) Audio Functions B 1 0 (O) May be inoperative provided

enroute or approach procedures do not require use of TCAS.

6) ***

Airspace Selection Function

C - 0

20. ***

Long Range Navigation Systems (INS, GPS, Loran, Etc.)

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

21. ***

Laser Track C - 0 (O) May be inoperative provided IRS can be initialized by FMS.

ll

22. Flight Management

System (FMS) C - 0 (O) May be inoperative provided IRS

are initialized by alternate means. ll

23. Windshear System C - 0 (O) May be inoperative provided

alternate procedures are established and used.




PAGE NO: 34-12





34 NAVIGATION

24. ATC Transponders and Automatic Altitude Reporting Systems

B - 0 May be inoperative provided: a) Operations do not require its

use, and 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

FAR may be inoperative. |

1) ***

Elementary and Enhanced Downlink Aircraft Reportable Parameters not Required by FAR

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.

llllll

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.

llllll

25. Primary Flight Display (PFD) Indications

1) IAS Trend Vector C 2 0

2) Long Accel/Mach C 2 0

3) Wind C 2 0




PAGE NO: 34-14





34 NAVIGATION

26. Multi-Function Display (MFD) Indications

1) Wind C 2 0

2) TAS C 2 0

3) GS C 2 0

4) SAT/TAT C 2 1

27. ***

Head-Up Display (HUD) System

D 1 0 May be inoperative provided procedures do not require its use.

NOTE: Any mode, which is operative,

may be used.

28. Electronic Flight

Instrument System (EFIS) Displays

A 4 3 (M)(O) Copilot MFD#2 may be inoperative provided:

a) Reversion Switch Panels (RSP) are operative,

b) Display Controller Panels (DCP) are operative,

c) Stand-by instrument(s) is/are operative, and

d) Repairs are made within three consecutive calendar days.

|

NOTE 1: In case of a second MFD

failure in flight, TCAS and EGPWS situation awareness are inoperative.

NOTE 2: In case of a second MFD

failure in flight, FMS MFD flight plan depictions are not available; FMS flight plan legs displayed on FMS CDU’s remain functional including FD/AP coupling.




PAGE NO: 34-15





34 NAVIGATION

29. Navigation Databases

C - - (O) May be out of currency provided: a) Current aeronautical charts are

used to verify navigation fixes before 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 verified to be properly tuned and identified.

30. Electronic Check List

System (Mod 1049) C 1 0 (O) May be inoperative provided

alternate procedures are established and used.

31. ***

Speed indexers (M255)

D 2 0

32. Navigation

Databases Data Loader

C 1 0 May be inoperative provided Navigation Databases are not out of currency.

C 1 0 May be inoperative provided

Navigation Databases (item 34-29) are considered out of currency.




PAGE NO: 35-1





35 OXYGEN

1. Passenger Oxygen System

C 1 0 (M)(O) Automatic presentation system may be inoperative provided:

a) Manual deployment is operative,

b) Cabin warnings are verified operative, and

c) Airplane remains at or below FL 250.

||

C 1 0 (M)(O) One or more passenger service

units may be inoperative without flight restrictions provided:

a) Associated seats are placarded and blocked to prevent occupancy, and

b) Units are operative at all usable lavatory and flight attendant locations.

C 1 0 (O) May be inoperative provided the

airplane remains at or below 10,000 feet.

1) Cargo Only

Configuration D 1 0

2. Portable Oxygen

System D - - Any in excess of those required by the

FAR may be inoperative.

3. First Aid Oxygen C - - As required by FAR.




PAGE NO: 36-1





36 PNEUMATIC

1. Engine Bleed Valves B 2 1 (M)(O) One may be inoperative provided:

a) Engine bleed valve is in closed position,

b) The Anti-Ice caution light is operative,

c) APU is verified operative before each departure, and

d) Airplane is not operated in known or forecast icing conditions.

2. Left Engine Starting

Valve A 1 0 (M)(O) May be inoperative provided:

a) Valve is closed by an acceptable procedure after engine start,

b) Right engine starting valve is operative,

c) APU is verified operative before each departure,

d) All engine booster pumps are verified operative,

e) Fuel system cross-feed is verified operative,

f) Wing tank pressurization is verified with engines running,

g) JP4 or JET B fuel is not used, h) Bus tie system and BUS TIE

caution lights are operative, i) Airplane is not operated in

known or forecast icing conditions, and

j) Repairs are made within two consecutive calendar days.

| | |

NOTE: In flight, associated engine

restart is only possible using ENGINES-WINDMILLING AIRSTART procedure.




PAGE NO: 36-2





36 PNEUMATIC

3. Right Engine Starting Valve

A 1 0 (M)(O) May be inoperative provided: a) Valve is closed by an

acceptable procedure after engine start,

b) Left engine starting valve is operative,

c) APU is verified operative before departure,

d) All engine booster pumps are verified operative,

e) Fuel system cross-feed is verified operative,

f) Wing tank pressurization is verified with engines running,

g) JP4 or JET B fuel is not used, h) Airplane is not operated in

known or forecast icing conditions, and

i) Repairs are made within two consecutive calendar days.

| | |

NOTE: In flight, associated engine

restart is only possible using ENGINES-WINDMILLING AIRSTART procedure.




PAGE NO: 38-1





38 WATER / WASTE

1. Rear Toilet Drain Valve

A 1 0 May be inoperative in closed position provided repairs are made before next toilet drain pan draining operation.

A 1 0 (M)(O) May be inoperative in open

position provided: a) Flight is conducted in an

unpressurized configuration, b) Toilet is not used, c) A placard is installed on the

toilet door with "DO NOT USE TOILET" inscription,

d) Draining port plug is verified to be LOCKED,

e) EFIS fans are verified operative, and

f) Repairs are made within three consecutive calendar days.

|


position provided: a) After manually operating the

drain valve in closed position, it is checked there is no water leak at the drain valve, and


|




PAGE NO: 38-2





38 WATER / WASTE

2. ***

Front Toilet Drain Valve (Mod. M1235 or M2282)

A 1 0 May be inoperative in closed position provided repairs are made before next toilet drain pan draining operation.

||


position provided: a) Flight is conducted in an

unpressurized configuration, b) Toilet is not used, c) A placard is installed on the

toilet door with "DO NOT USE TOILET" inscription,

d) Draining port plug is verified to be LOCKED,

e) EFIS fans are verified operative, and

f) Repairs are made within three consecutive calendar days.

|




PAGE NO: 45-1





45 CENTRAL MAINTENANCE SYSTEMS

|||

1. Maintenance Diagnostic

Computer (MDC) C 1 0 May be inoperative provided, if required

by procedures, alternate procedures are established and used.

|||




PAGE NO: 46-1





46 INFORMATION SYSTEMS

1. ***

Electronic Flight Bag Systems (EFBs)

*** Class 3 EFBs C - - (O) May be inoperative provided alternate

procedures are established and used. NOTE: Any function, program or

document which is operative may be used.


do not require its use.

*** Data Connectivity (Class 2)

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



*** Power Connection (Class 1 and 2)

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






PAGE NO: 49-1





49 AIRBORNE AUXILIARY POWER

1. Auxiliary Power Unit

(APU) A 1 0 (O) May be inoperative provided:

a) JP4 or JET B fuel is not used, b) AFM limitations are observed, c) L/G Retraction System is

operative. d) Operations are limited to day

VMC only, and e) Repairs are made within two


|

2. APU Starter

Generator C 1 0 (O) May be inoperative in the electrical

generator function mode.

3. APU Inlet Door A 1 0 (M)(O) May be inoperative provided:

a) APU Door is secured in the closed position by appropriate tool,

b) APU (item 49-1) is considered inoperative, and


| |

A 1 0 (M)(O) May be jammed for one flight

provided: a) APU door is secured in other

than closed position, b) APU (item 49-1) is considered

inoperative, and c) AFM procedures are observed.

|




PAGE NO: 49-2






4. APU Indications

1) N1, EGT, OVSP A 3 0 (O) One or more may be inoperative provided:

a) APU (item 49-1) is considered inoperative, and


| | |

2) OIL Level A 1 0 (M) May be inoperative for 40 flights

hours provided APU oil quantity is verified within the first three flights of the rectification interval.

||||

5. APU DOOR

Indication C 1 0 (M) May be inoperative provided it is

verified that the fault is in the indicating system.

A 1 0 (M) May be inoperative provided:

a) APU (item 49-1) is considered inoperative, and


| |

6. APU Oil Level Test

System (OIL LEVEL Light on EIED and APU Oil Test Button on Maintenance Panel)

A 1 0 May be inoperative provided OIL Level is considered inoperative (item 49-4.2).

||

7. APU FAULT Caution

Light A 1 0 (M) May be inoperative provided:

a) APU (item 49-1) is considered inoperative and not used,

b) APU inlet door is checked in closed position, and


| |




PAGE NO: 49-3






8. APU GEN Caution

Light A 1 0 (M)(O) May be inoperative provided:

a) APU GEN Switch remains off, b) APU (item 49-1) is considered

inoperative and not used, and c) Repairs are made within two


| |

9. APU Bleed Valve A 1 0 (M)(O) May be inoperative provided:

a) APU Is operated on ground for electrical power and engine start only,

b) APU is shut down after engine start,

c) APU Bleed Valve is manually closed after engine start,

d) APU is not used during flight, e) Operations are limited to day

VMC only, and f) Repairs are made within two


| |




PAGE NO: 52-1





52 DOORS

1. Door Warning Light System

C 1 0 (O) May be inoperative provided it is verified that the doors are closed and locked before each departure.

2. ***

Electric Main Entrance Door Motor System (S/N 138 and above or with Mod. M1378)

C 1 0 (M) May be inoperative provided Door is verified to manually open and close freely.

||

3. Roller Micro

Switches (Baggage Compartment)

C 2 0 (O) One or more may be inoperative provided the mechanism is verified in closed position.

|||

4. Latch Detectors

(Baggage Compartment)

C 2 0 O) One or more may be inoperative provided the mechanism is verified in closed position.

|||




PAGE NO: 73-1





73 ENGINE FUEL & CONTROL

1. Engine FADEC

System |

|

1) Short Time Dispatch Fault

A - - Only one engine may be affected provided:

a) FADEC fault codes have been considered,

b) EIED “class 3 Fault Combination” does not appear,

c) Reliability monitoring data are submitted to the engine manufacturer in accordance with the engine Type Certificate Data Sheet note, and

d) Repairs are made within 40 flight hours or 30 consecutive calendar days, whichever comes first.

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

2) Long Time Dispatch

Fault A - - Only one engine may be affected

provided: a) FADEC fault codes have been

considered, b) EIED “class 3 Fault

Combination” does not appear, c) Reliability monitoring data are

submitted to the engine manufacturer in accordance with the engine Type Certificate Data Sheet note, and

d) Repairs are made within 350 flight hours.

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




PAGE NO: 73-2





73 ENGINE FUEL & CONTROL

2. APR Caution Light A 1 0 (O) May be inoperative provided:

a) APR O’RIDE button is pressed before take-off and landing,

b) All EIED’s are operative, c) Amber Arc’s on ITT display are

operative, and d) Repairs are made within two

flight days.

3. Mach Hold Functions

(A/C with Mod 613) D 1 0

4. Mach Hold Switch

Green Lights (A/C with Mod 613)

D 2 0 (M) One or more may be inoperative provided Mach Hold function (item 73-3) is considered inoperative.

|

5. SYNC switch C 1 0 May be stuck or broken in the OFF

position.

6. Impending Fuel Filter

Bypass EIED Functions

A 2 1 One may be inoperative for one flight. |||




PAGE NO: 74-1





74 IGNITION

1. Igniters Plugs C 4 3 (O) One may be inoperative provided: a) All FADECs are operative, b) Only one engine has a detected

ground start light-off fault (Class 3 MSG no light-off), and

c) AFM procedures are complied with.

2. Holding Start

Function C 2 0 One or more may be inoperative

provided starting is performed by depressing the start button for 9 seconds maximum.

|




PAGE NO: 77-1





77 ENGINE INDICATING

1. EIED Indications

(Middle Display)

1) Fuel Flow B 2 1 One may be inoperative provided all

other engine indications and the associated fuel quantity indication system are operative.

2) Fuel Used C 2 0 One or both may be inoperative

provided the associated Fuel Flow and Fuel Quantity Indications are operative.

2. EIED Indications

(Bottom Display)

1) N1 Vibration C 2 0

2) N2 Vibration C 2 0

3) Oil Pressure C 2 1 (O) One may be inoperative provided the associated OIL low pressure warning light and oil temperature indication are verified operative.

|

3. Engine Vibration

Computer C 2 1 |




PAGE NO: 77-2





77 ENGINE INDICATING

4. ENG OIL FILTER

CLOGGING Indication (EIED)

B 2 1 (M) One may be inoperative provided: a) OIL lights are operative at

engine start, b) OIL TEMP indications are

normal, c) OIL PRESS indications are

normal, and d) Associated FQMC fault codes

(812/913 LH) or (813/912 RH) are not present on the FCD.




PAGE NO: 78-1





78 ENGINE EXHAUST

1. Thrust Reverser System

C 2 0 (M) One or more may be inoperative provided:

a) No damage to the Thrust Reverser system exists which would adversely affect operation of the airplane, and

b) Both Thrust Reversers are deactivated and locked in the closed (forward thrust) position by use of safety pins.

|

2. THRUST

REVERSER 1 THRUST REVERSER 2 Caution Lights

C 2 0 (M) One or more may be inoperative provided:

a) It is verified that the fault is in the indicating system only, and

b) Both thrust reversers are deactivated and locked in the closed (forward thrust) position by use of safety pins.

|




PAGE NO: 79-1





79 ENGINE OIL

1. Magnetic Chip Detector System

A 2 1 (M) One may be inoperative or showing erroneous chip detection provided:

a) Associated magnetic chip detector is inspected and found acceptable in accordance with the Engine Light Maintenance Manual, and

b) Repairs are made in accordance with Engine Light Maintenance Manual within three flight days.

2. Engine Oil Level

Indication (EIED3, Maintenance Page)

C 2 0 (M) One or more may be inoperative provided oil tank level of associated engine is verified adequate before each departure.

||||

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