master minimum equipment list rev6.pdf · 2011. 7. 22. · federal aviation administration page: iv...

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

Master Minimum Equipment List

Revision: 6 Date: 07/18/2011

Falcon 50

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: II Revision: 6 MASTER MINIMUM EQUIPMENT LIST Date: 07/18/2011 FALCON 50

Table of Contents ATA SYSTEM PAGE -- Cover Page I -- Table of Contents II -- Control Page III, IV, V -- Highlights of Change VI -- Definitions VII -- Preamble VIII 21 Air Conditioning 21-1, THRU 8 22 Auto Flight 22-1, THRU 4 23 Communications 23-1, THRU 10 24 Electrical Power 24-1, THRU 3 25 Equipment/Furnishings 25-1, THRU 7 26 Fire Protection 26-1 27 Flight Controls 27-1, THRU 5 28 Fuel 28-1, THRU 4 29 Hydraulic Power 29-1, 2 30 Ice and Rain Protection 30-1, THRU 4 31 Indicating/Recording Systems 31-1, THRU 3 32 Landing Gear 32-1, THRU 3 33 Lights 33-1, THRU 4 34 Navigation 34-1, THRU 20 35 Oxygen 35-1, 36 Pneumatic 36-1, THRU 4 38 Water/Waste 38-1, 2 46 Information Systems 46-1 49 Airborne Auxiliary Power 49-1 52 Doors 52-1 56 Windows 56-1 73 Engine Fuel & Control 73-1, 2 74 Ignition 74-1 77 Engine Indicating 77-1, THRU 3 78 Engine Exhaust 78-1 79 Engine Oil 79-1, 2 80 Starting 80-1

FEDERAL AVIATION ADMINISTRATION Page: III Revision: 6 MASTER MINIMUM EQUIPMENT LIST Date: 07/18/2011 FALCON 50

Cover Page I 6 07/18/2011 Table of Contents II 6 07/18/2011 Control Page III 6 07/18/2011 Highlights of Change VI 6 07/18/2011 Definitions VII 6 07/18/2011 Preamble VIII 6 07/18/2011 ATA 21 21-1 6 07/18/2011 21-2 6 07/18/2011 21-3 6 07/18/2011 21-4 6 07/18/2011 21-5 6 07/18/2011 21-6 6 07/18/2011 21-7 6 07/18/2011 ATA 22 22-1 6 07/18/2011 22-2 6 07/18/2011 22-3 6 07/18/2011 22-4 6 07/18/2011 ATA 23 23-1 6 07/18/2011 23-2 6 07/18/2011 23-3 6 07/18/2011 23-4 6 07/18/2011 23-5 6 07/18/2011 23-6 6 07/18/2011 23-7 6 07/18/2011 23-8 6 07/18/2011 23-9 6 07/18/2011 23-10 6 07/18/2011 ATA 24 24-1 6 07/18/2011 24-2 6 07/18/2011 24-3 6 07/18/2011 ATA 25 25-1 6 07/18/2011 25-2 6 07/18/2011 25-3 6 07/18/2011 25-4 6 07/18/2011 25-5 6 07/18/2011 25-6 6 07/18/2011 25-7 6 07/18/2011 ATA 26 26-1 6 07/18/2011 ATA 27 27-1 6 07/18/2011 27-2 6 07/18/2011 27-3 6 07/18/2011 27-4 6 07/18/2011 ATA 28 28-1 6 07/18/2011 28-2 6 07/18/2011 28-3 6 07/18/2011 28-4 6 07/18/2011 ATA 29 29-1 6 07/18/2011

FEDERAL AVIATION ADMINISTRATION Page: IV Revision: 6 MASTER MINIMUM EQUIPMENT LIST Date: 07/18/2011 FALCON 50

29-2 6 07/18/2011 ATA 30 30-1 6 07/18/2011 30-2 6 07/18/2011 30-3 6 07/18/2011 30-4 6 07/18/2011 ATA 31 31-1 6 07/18/2011 31-2 6 07/18/2011 31-3 6 07/18/2011 ATA 32 32-1 6 07/18/2011 32-2 6 07/18/2011 32-3 6 07/18/2011 ATA 33 33-1 6 07/18/2011 33-2 6 07/18/2011 33-3 6 07/18/2011 33-4 6 07/18/2011 ATA 34 34-1 6 07/18/2011 34-2 6 07/18/2011 34-3 6 07/18/2011 34-4 6 07/18/2011 34-5 6 07/18/2011 34-6 6 07/18/2011 34-7 6 07/18/2011 34-8 6 07/18/2011 34-9 6 07/18/2011 34-10 6 07/18/2011 34-11 6 07/18/2011 34-12 6 07/18/2011 34-13 6 07/18/2011 34-14 6 07/18/2011 34-15 6 07/18/2011 34-16 6 07/18/2011 34-17 6 07/18/2011 34-18 6 07/18/2011 34-19 6 07/18/2011 34-20 6 07/18/2011 ATA 35 35-1 6 07/18/2011 ATA 36 36-1 6 07/18/2011 36-2 6 07/18/2011 36-3 6 07/18/2011 36-4 6 07/18/2011 ATA 38 38-1 6 07/18/2011

38-2 6 07/18/2011 ATA 46 46-1 6 07/18/2011 ATA 49 49-1 6 07/18/2011 ATA 52 52-1 6 07/18/2011

FEDERAL AVIATION ADMINISTRATION Page: V Revision: 6 MASTER MINIMUM EQUIPMENT LIST Date: 07/18/2011 FALCON 50

ATA 56 56-1 6 07/18/2011 ATA 73 73-1 6 07/18/2011 73-2 6 07/18/2011 ATA 74 74-1 6 07/18/2011 ATA 77 77-1 6 07/18/2011 77-2 6 07/18/2011 77-3 6 07/18/2011 ATA 78 78-1 6 07/18/2011 ATA 79 79-1 6 07/18/2011 79-2 6 07/18/2011 ATA 80 80-1 6 07/18/2011

FEDERAL AVIATION ADMINISTRATION Page: VI Revision: 6 MASTER MINIMUM EQUIPMENT LIST Date: 07/18/2011 FALCON 50

Highlights of Change General Changes - All wording as “operates normally” and “check to be operative” are reworded as

“is/are operative/verified operative” - All wording as “flight days” are re—worded as “consecutive calendar days” - Computer fault codes are deleted, and transferred to Fault Guide Dispatch

Assistance (FGDA) - Generic fault code items are added in MMEL. The purpose of the codes is to provide

the MMEL inputs which correspond to the FGDA outputs (for the fault codes cases where no item is considered inoperative).

- “EFIS FAN are verified operative” is added when the flight is conducted in an unpressurized configuration.

- Applicability to “A/C with TFE 7312-40 engines” is modified as “A/C with M2518 or SB280”

- “Before Takeoff” is replaced by “Before Departure’ when the check has to be performed before taxi.

- Various rewordings - Complete revision to all pages of MMEL. This is to accommodate the new format

where all pages of an ATA chapter are change when there are any changes anywhere in the chapter.

Specific Changes

ATA 21-1: Added proviso ATA 21-2: Added proviso ATA 21-3: Added proviso ATA 21-4-1: Added proviso ATA 21-4-2: Added (M) and proviso ATA 21-4-3: Added (M) and proviso ATA 21-5: Added (M) and proviso ATA 21-7: Added proviso ATA 21-8: Added (M) and proviso ATA 21-9: Added proviso ATA 24-2: Added (O) and proviso ATA 24-5: Added (M) ATA 24-8: Added (M) ATA 25-1-4: Added item ATA 25-4-5: Added item ATA 29-4: Added (M)(O) ATA 30-1-1: Added (O) ATA 30-1-2: Added (O) ATA 30-2-1: Added (M) ATA 30-8: Added (M) ATA 34-74: Removed (M) ATA 34-76: Added item

ATA 35-1: Added (M) ATA 38-2: Added proviso ATA 49-1: Added proviso ATA 52-1: Added proviso ATA 52-2: Added (M) ATA 73-3: Added proviso ATA 77-1: Added (O) ATA 77-2: Added (O) ATA 77-3: Added (O) ATA 77-9: Added item

FEDERAL AVIATION ADMINISTRATION Page: VII Revision: 6 MASTER MINIMUM EQUIPMENT LIST Date: 07/18/2011 FALCON 50

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

http://fsims.faa.gov/PICResults.aspx?mode=Publication&doctype=MMEL%20Policy%20letters�

FEDERAL AVIATION ADMINISTRATION Page: VIII Revision: 6 MASTER MINIMUM EQUIPMENT LIST Date: 07/18/2011 FALCON 50

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

http://fsims.faa.gov/PICResults.aspx?mode=Publication&doctype=MMEL%20Policy%20letters�

DEPARTMENT OF TRANSPORTATION MASTER MINIMUM EQUIPMENT LIST

FEDERAL AVIATION ADMINISTRATION AIRCRAFT:

FALCON 50 REVISION NO: 6 DATE: 7/18/2011

PAGE NO: 21-1

1. REPAIR CATEGORY 2. NUMBER INSTALLED

3. NUMBER REQUIRED FOR DISPATCH

SYSTEM SEQUENCE & NUMBERS

4. REMARKS AND EXCEPTIONS

21 AIR CONDITIONING

1. Automatic Pressure Controller 21-31-00

C 1 0 (M)(O) May be inoperative provided: a) UP-DN Manual Controller and

DUMP mode are verified operative before each flight,

b) Cabin visual and audio warning are verified operative, and

c) UP-DN Manual Controller is set to the RH part of the white arc for take-off.

||| |

C 1 0 (O) May be inoperative provided:

a) EFIS fans are verified operative, and

b) Flight is conducted in an unpressurized configuration.

|||

2. UP-DN Manual

Controller 21-31-00 C 1 0 (M)(O) May be inoperative provided:

a) Automatic Pressure Controller is verified operative,

b) DUMP mode is verified operative before each departure, and

c) Manual control is aligned with the green index mark.

| ||




|||




PAGE NO: 21-2





21 AIR CONDITIONING

3. Outflow Pressurization Valves 21-31-00

1) Electro Pneumatic

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

aircraft is operated at or below 14,000 feet MSL.

2) Pneumatic Outflow

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



|||

4. Triple Cabin Indicator

21-31-00

1) Cabin Altitude

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

a) Cabin Differential Pressure Indicator is verified operative,

b) Automatic Pressure Controller is verified operative, and

c) A chart to convert cabin pressure differential is provided to the crew.

| | |




|||

(Continued)




PAGE NO: 21-3





21 AIR CONDITIONING

4. Triple Cabin Indicator 21-31-00 (Cont’d)

2) Cabin Differential

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

a) Cabin Altitude Indicator is verified operative,

b) Automatic Pressure Controller is verified operative, and

c) A chart to convert cabin pressure differential to cabin altitude is provided to the crew.

|| |




|||

3) Cabin Vertical Speed C 1 0 (O)(M) May be inoperative provided:

a) Cabin Altitude Indicator is verified operative, and

b) Automatic Pressure Controller is verified operative.

|| |




|||




PAGE NO: 21-4





21 AIR CONDITIONING

5. Cabin Aural Warning 21-31-00

C 1 0 (O)(M) May be inoperative provided: a) Cabin Warning Light is verified

operative, and b) Automatic Pressure Controller

is verified operative.

||| |




|||

6. CABIN Warning Light

21-31-00 Refer to item 52-1

7. CABIN Light/Aural

Warning Test Circuit 21-31-00

C 1 0 (O) May be inoperative provided CABIN Light and Aural Warning are verified operative.

||




|||||

8. Environmental Control

Units (ECU’s) 21-31-00 C 2 1 (M) One may be inoperative provided:

a) Associated air conditioning valve is set in closed position, and

b) Isolation Valve is verified operative for pressurized flight.

|||| |




|||




PAGE NO: 21-5





21 AIR CONDITIONING

9. CABIN and CREW Bleed Air Control Valves 21-60-00

C 2 1 (M) One may be inoperative CLOSED.

C 2 0 (O) May be inoperative in the AUTO

position provided: a) Relevant Manual mode is

verified operative, b) OFF is selected for takeoff, c) ON is selected after completing

the second segment climb profile, and

d) CABIN Aural Warning and Warning Light are verified operative.

|| |

10. Baggage Compartment

Supply and Isolating Valves (BAG Switch) 21-24-00

C 2 0 (M) May be inoperative CLOSED provided baggage compartment remains empty.

11. Flightdeck Floor

Electric Heat Systems (FLOOR Switches) 21-61-00

C 2 0

12. Cockpit Gaspers 21-

22-00 C 2 1 One may be inoperative in the closed

position.

C 2 0 May be inoperative provided at least

one Gasper remains in open position.




PAGE NO: 21-6





21 AIR CONDITIONING

13. Temperature Control Systems 21-60-00

1) Manual Modes C 2 1 NOTE: ECU may be turned off, by

turning associated Cabin or Crew bleed air switch to OFF, if necessary.

2) Automatic Modes C 2 0 (O) May be inoperative provided

associated manual mode is verified operative.

|

14. ***

Cabin Temperature Remote Control Selector

C 1 0 May be inoperative provided the cockpit control for the cabin is operative.

||

15. Temperature Control

Valve Position Indicators 21-60-00

C 2 0

16. Cabin Temperature

Indicator 21-60-00 C 1 0

17. Nose Cone Ventilation

System 21-25-00 C 1 0 (M) May be inoperative provided:

a) Nose supply valve is verified operative, and

b) Ground operations do not exceed 30 minutes duration.

||

18. NOSE Supply Valve

21-25-00 C 1 0 (M) May be inoperative OPEN.

C 1 0 (M) May be inoperative CLOSED

provided the nose cone ventilation system is verified operative on the ground.

|




PAGE NO: 21-7





21 AIR CONDITIONING

19. Electrical Rack Blower 21-26-00

C 1 0 May be inoperative provided ground operations do not exceed 30 minutes duration.

20. ***

Toilet Compartment Blowers

1) Aft Toilet C 1 0

2) Fwd Toilet C 1 0

21. Cockpit Floor/ Windshield Diverter Levers 21-23-00

C 2 0 May be inoperative in the WINDSHIELD position.

22.

Cockpit Air Foot Warmers

C 2 0

23. ***

FLOOD DUCT System C 1 0 May be inoperative in the closed position.




PAGE NO: 22-1





22 AUTO FLIGHT

1. Autopilot System/ Autopilot Computer 22-00-00

|1) Non-EFIS Aircraft

a) AP Function B 1 0 May be inoperative provided enroute or approach procedures do not require its use.

NOTE: Any mode which functions

normally may be used.

b) Yaw Damper 22-14-00 C 1 0 (M) May be inoperative provided the

rudder actuator has been visually checked centered.

c) Mach Trim System 22-

20-00 C 1 0 May be inoperative provided airspeed

does not exceed .78 Mach when the autopilot is not engaged.

d) AP Caution Light 22-

12-00 B 1 0 May be inoperative provided the

autopilot is not used.

e) AP TRIM Caution Light

22-12-00 C 1 0 May be inoperative provided the

autopilot is used in stabilized cruise only.

f) MISTRIM Caution Light

22-12-00 C 1 0 (O) May be inoperative provided the

trim indicators are operative and are monitored during flight.

|

g) Control Wheel

Disengage Switches C 2 1 One may be inoperative provided

autopilot is not utilized at less than Initial Approach Altitude.

(Continued)




PAGE NO: 22-2





22 AUTO FLIGHT

1. Autopilot System/ Autopilot Computer 22-00-00 (Cont’d)

2) EFIS Aircraft |

a) AP Function B 1 0 May be inoperative provided enroute or approach procedures do not require its use.

b) FD Function C 2 0 May be inoperative provided approach

minimums do not require their use.

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

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

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

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

does not exceed .78 Mach.

e) AP Warning Light C 1 0 May be inoperative provided

annunciation on EFIS and aural warning are operative.

|

f) Autopilot 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.




PAGE NO: 22-3





22 AUTO FLIGHT

2. Yaw Damper 22-14-00 Incorporated into ATA 22 Item 1, Revision 3.

3. Mach Trim System 22-

20-00 Incorporated into ATA 22 Item 1,

Revision 3.

4. AP, AP TRIM and

MISTRIM Lights 22-12-00

Incorporated into ATA 22 Item 1-1), Revision 3.

5. ***

Aileron/Elevator/ Rudder Torque Indicators

1) Without APS-85

Autopilot C - 0

2) With APS-85 Autopilot C 2 0 May be inoperative provided Rudder

Torque Indicator is operative if Yaw Damper is used.

|

6. Go-Around Buttons C 2 1 Copilot’s button may be inoperative. C 2 0 May be inoperative provided autopilot

or flight director is not used below 1500 feet AGL.

7. ***

Flight Control Panel (FCP)

B 1 0 (O) May be inoperative provided: a) Enroute operations do not

require the use of ALT AP function,

b) ASEL and course functions are verified to operate normally before takeoff, and

c) Autopilot and flight director are considered inoperative and not used.




PAGE NO: 22-4





22 AUTO FLIGHT

8. ***

Pitch or Roll Servomotors

C 2 0 May be inoperative provided autopilot is considered inoperative and not used.




PAGE NO: 23-1





23 COMMUNICATIONS

1. Communication Systems (VHF and UHF) 23-20-00

D - - Any in excess of those required by FAR may be inoperative provided they are not powered by the Emergency AC Bus, Emergency DC Bus, Battery Bus, or the DC Transfer Bus and not required for Emergency Procedures.

1) VHF Comm. Control

Panels

a) Frequency Transfer

Light(s) C - 0

b) Frequency Transfer

Switch(es) C - 0

c) Frequency Selector

Knob(s) C - 2

d) Frequency Indicator(s) C - 2




PAGE NO: 23-2





23 COMMUNICATIONS

2. 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 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.

3. UHF System Moved to Item 1 (prior to Rev. 3.).




PAGE NO: 23-3





23 COMMUNICATIONS

4. Passenger Address System (PA) 23-30-00

1) Passenger

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

a) Alternate, Normal, Abnormal, 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) which

are operative may be used. |


a) PA not required by FAR, and b) Alternate, Normal, Abnormal,

and Emergency Procedures, and/or operating restrictions are established and used.

NOTE: Any station function(s) which

are operative may be used. |

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

alternate procedures are established and used.

(Continued)




PAGE NO: 23-4





23 COMMUNICATIONS

4. Passenger Address System (PA) 23-30-00

2) Cargo Configuration

(Courier/ Supernumerary Address System)

C 1 0 (O) May be inoperative provided alternate Normal, Abnormal and Emergency Procedures and/or operating restrictions are established and used.

D 1 0 May be inoperative provided

procedures do not require their use.

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



procedures do not require its use.

5. Cockpit Speakers 23-

50-00 C 2 0 May be inoperative provided:

a) Procedures do not require their use, and

b) Headsets are installed and are operative.

||

6. Headsets,

Microphones 23-50-00 D - - Any in excess of those required for

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

7. Audio Selector (Or

Control) Panels 23-50-00

Incorporated into Item 23-1, Communication Systems, Rev. 3.

8. Microphones 23-50-00 Incorporated into Item 23-6, Rev. 3.




PAGE NO: 23-5





23 COMMUNICATIONS

9. Cockpit Voice Recorder System (CVR)

1) With FDR Installed A 1 0 May be inoperative provided:

a) Flight data recorder (FDR) is operative, and

b) Repairs are made within three flight days.

||

2) Without FDR Installed A 1 0 May be inoperative provided repairs

are made within three flight days.

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.

10. Static Dischargers 23-

60-00 C 19 16 Three may be damaged or missing

provided damage is limited to not more than two on each wing, horizontal, or vertical tail surface.

11. Air Phone Moved to ATA 25, Item 8, Rev. 1.

12. ***

Selective Call System (SELCAL)

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

D - 0 May be inoperative provided


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


D - 0 May be inoperative provided





PAGE NO: 23-6





23 COMMUNICATIONS

13. ***

Automatic Cabin Briefer

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

14. Boom Microphones

(CVR With Flight Data

Recorder Installed)

1) Cockpit Voice

Recorder Equipped to Record Boom Microphones per FAR 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 FAR may be inoperative.

(CVR Without Flight

Data Recorder Installed)

1) Cockpit Voice

Recorder Equipped to Record Boom Microphone per FAR 121.359(g), 135.151(d), or 125.227(e)

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

2) ***

Cockpit Voice Recorder Not Equipped to Record Boom Microphones

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




PAGE NO: 23-7





23 COMMUNICATIONS

15. ***

Radio Master Switch C - 0 May be inoperative provided the O’RIDE is operative.

|

16. ***

AFIS System (VHF/SAT)




17. ***

SATCOMM D - 0 Any in excess of those required by FAR may be inoperative.

C - - (O) May be inoperative for operations

requiring two Long Range Communication Systems (LRCS) provided two HF Systems are installed and are operative.

|




PAGE NO: 23-8





23 COMMUNICATIONS

18. ***

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

19. ***

Radio Tuning Unit (RTU)

C 2 1 (O) One may be inoperative provided radio tuning function of the FMS is verified operative.

||

20. Alerting System (Audio/

Visual)

1. Flight Deck Call Visual

Alerting System B 1 0 May be inoperative provided Flight

Deck Audio Alerting System is operative.

||

NOTE: Flight Deck Audio Alerting

System must always is operative. |

(Continued)




PAGE NO: 23-9





23 COMMUNICATIONS

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

2. Flight Attendant Visual

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

a) Public Address System (PA) is operative,

b) If Visual Alerting System is used for Lavatory Smoke Detector Alerting, an alternate Lavatory Smoke Detector Alerting System (Audio or Visual) is installed and is operative, and

c) Alternate procedures for contacting Flight Attendants are established and used.

|| ||

NOTE 1: Passenger to Flight Attendant

Call System is considered a Passenger Convenience Item.

NOTE 2: Any Visual Alerting Function

which is operative may be used. |

(Continued)




PAGE NO: 23-10





23 COMMUNICATIONS

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

3. Flight Attendant Audio

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

a) Public Address System (PA) is operative,

b) If affected Audio Alerting System is used for Lavatory Smoke Detector Alerting, an alternate Lavatory Smoke Detector Alerting System (Audio or Visual) is installed and is operative, and

c) Alternate procedures for contacting Flight Attendants are established and used.

|| |

NOTE 1: Passenger to Flight Attendant

Call System is considered a Passenger Convenience Item.

NOTE 2: Any Audio Alerting Function

which is operative may be used. |




PAGE NO: 24-1





24 ELECTRICAL POWER

1. Inverters (A/C with 3 inverters installed) 24-20-00

B 3 2 (O) One may be inoperative provided the remaining two are operative.

|

2. AC Voltmeter 24-20-00 C 1 0 (O) May be inoperative provided AC 1

and AC 2 Caution Lights are verified operative.

|||

3. AC 1 and AC 2 Caution

Lights 24-30-00 C 2 0 May be inoperative provided the

voltmeter, and flags in the navigation instruments are operative, and are closely monitored during flight.

|

4. Batteries 24-30-00 DELETED REVISION No 3.

5. Battery Blower 24-30-00

C 1 0 (O) May be inoperative provided HOT BOT Warning system is verified operative.

|||

6. BAT 1/BAT 2 Caution

Lights 24-30-00 C 2 1 (O) One may be inoperative provided:

a) Voltage and charging current of each battery is verified operative before each departure, and

b) Voltmeter and ammeter of the associated DC generating system and battery overheat sensing system are closely monitored during flight.

||




PAGE NO: 24-2





24 ELECTRICAL POWER

7. Battery Temperature Indicating System 24-30-00

1) Meter Indicators C 2 1 (O) One may be inoperative provided

associated battery warning lights are verified operative.

|

2) Amber/Red Indicator

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

both temperature indicators and master caution “HOT BAT” warning light are verified operative.

|

8. Generators C 3 2 (O)Either Generator #1 or #2 may be

inoperative provided the bus tie system is verified operative.

| |

9. GEN Caution Lights C 3 2 One may be inoperative provided:

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

b) Engine start is manually discontinued at 50% N2, and

c) Generator current is closely monitored during flight.

|

C 3 2 One may be inoperative provided

associated generator is inoperative.

10. DC Ammeter DELETED REVISION No 1.

11. DC Voltmeters C 2 1 One may be inoperative provided:

a) Generator lights and ammeter of the associated generating system are operative, and

b) BUS TIED warning light is operative.

|||

12. DC Bus-Tie Circuit DELETED REVISION No 2.




PAGE NO: 24-3





24 ELECTRICAL POWER

13. BUS TIED Caution Light

C 1 0 May be inoperative provided bus tie circuit and voltmeters are verified operative.

||

14. ***

Aux Battery D 1 0




PAGE NO: 25-1





25 EQUIPMENT/ FURNISHINGS

1. Pilot’s Seats

1) Vertical Adjustments C 2 0 (M) May be inoperative provided: a) Seat is secured at the individual

crewmember’s requirements, b) Fore-aft adjustment is

operative, and c) Associated circuit breakers are

pulled and collared.

||

2) Armrests C 4 0 (M) May be inoperative provided:

a) Affected armrest is in the up position or removed, and

b) Seat is acceptable to the affected crew member.

3) Recline Adjustment C 2 0 (M) May be inoperative provided:

a) Seat is secured at a position acceptable to the affected crew member, and

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

4) Headrests C 2 0 (M) One or more headrest fairing may

be damaged provided: a) Headrest structure is verified

adequate, and b) Seat is secured at a position

acceptable to the affected crew member.

|||||||

2. Rudder Pedal

Adjustments Moved to ATA 27 Item 17, Rev. 2.

3. Crewmember Shoulder

Harness DELETED REVISION No 1.




PAGE NO: 25-2






4. Passenger Seats 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) is 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 D - - (M) May be inoperative and seat occupied provided seat is secured in the full up-right position.

C - - (M) May be inoperative and seat

occupied provided seat is immovable in the full up-right position

2) Arm Rests C - - May be inoperative or missing and seat

occupied provided: a) Arm rest does not block an

Emergency Exit, b) Arm rest does not restrict any

passenger from access to the main aircraft aisle, and

c) For and armrest with a recline mechanism, seat is secured in the upright position.

|

(Continued)




PAGE NO: 25-3






4. Passenger Seats

(Cont’d)

3) ***

Swivel Mechanism C - - May be inoperative provided: a) Associated seat does not block

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.

4) ***

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 and used to alert Cabin Crew of inoperative Restraining Bar.

5) Headrests C - - One or more may be jammed in takeoff

position. ||

5. 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 inoperative or missing provided

repairs are made within 90 days.

D - - Any in excess of those required by FAR

may be inoperative or missing.




PAGE NO: 25-4






6. Forward Observer Seat

(Including Associated Equipment)

A 1 0 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 1 0 May be inoperative provided:

a) Required minimum safety equipment (safety belt and oxygen) is available,

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

a) Repairs are made within two flight 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. NOTE 3: When not occupied, the observer seat must be stowed so as to not impede egress from the cockpit.

Observer Seat Not

Required by FAR (Including associated equipment)

D - 0 Refer to NOTE 2 above.




PAGE NO: 25-5






7.

Passenger Convenience/NEF Items

*** Passenger Convenience Items (Expires on April 30, 2008)

DELETED REVISION No 6 |

*** 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 considered NEF items.

8. ***

Air Phone D 1 0

9. Exterior Lavatory Door

Ashtrays

1) Airplanes with more

than one Exterior Lavatory Door Ashtrays Installed

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

2) Airplanes with only one

Exterior Lavatory Door Ashtrays Installed

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




PAGE NO: 25-6






10. Cockpit Convenience

Items Refer to item 25-7.

11. Overwater Equipment

(Flotation Devices/ Rafts)

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

12. Crewmember

Flashlight Holder Assemblies (Including Flashlight)

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

13. ***

Security System D 1 0

14. 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 with-in 3 flight cycles.

D - - Any in excess of those required by

FAR may be incomplete, missing, or inoperative.




PAGE NO: 25-7






15. 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

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

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

16. 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

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

D - - Any in excess of those required by FAR

may be incomplete, missing, or inoperative




PAGE NO: 26-1





26 FIRE PROTECTION

1. Fire Extinguisher Discharge Indicator Discs 26-11-00

C - - (M) May be missing provided associated gauge reading is verified adequate once each flight day.

2. ***

APU Fire Extinguisher 26-20-00

C 1 0 May be inoperative provided APU is considered inoperative.


procedures do not require APU use.

3. ***

APU Fire Warning System 26-11-00

C 1 0 May be inoperative provided APU is considered inoperative.


procedures do not require APU use.

4 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.




PAGE NO: 27-1





27 FLIGHT CONTROLS

1. Aileron and Elevator Arthur Q Units 27-10-00

B 2 0 (M)(O) May be inoperative provided: a) Arthur Q units are in the low

speed position, and b) Airspeed remains at or below

260 KIAS/Mach .76, and c) Autopilot is not used.

2. Q-UNIT Caution Light

27-10-00 B 1 0 (M)(O) May be inoperative provided:

a) Arthur Q units are in the low speed position, and

b) Airspeed remains at or below 260 KIAS/Mach .76, and

c) Autopilot is not used.

3. Aileron Trim Indicator

27-10-00 C 1 0 (M)(O) May be inoperative provided

before each departure: a) Aileron Trim System is

operative, and b) Roll Trim is verified to be in the

neutral position, and Aileron control surfaces are verified to be in the same position.

||

4. Aileron Emergency

Trim Indicator 27-10-00 C 1 0 (M)(O) May be inoperative provided

emergency trim system is verified to be in the neutral position.

5. Rudder Trim Indicator

27-20-00 C 1 0 (M) May be inoperative provided before

each departure: a) Rudder Control System is

verified operative, and b) Rudder Trim is verified to be in

the neutral position.

|




PAGE NO: 27-2





27 FLIGHT CONTROLS

6. Horizontal Stabilizer Position Indicator 27-20-00

C 1 0 (M)(O) May be inoperative provided: a) Stabilizer trim is operative, b) Stabilizer is verified to be in the

recommended position for takeoff before each departure, and

c) T/O CONFIG Warning System is verified operative.

|||| |

7. T/O CONFIG Warning

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

T/O CONFIG warning system is installed and is verified operative.

|

8. Stabilizer Trim Aural

Motion Detector C 1 0 DELETED REVISION No 3.

9. FLAP ASYM Light C 1 0 (M)(O) May be inoperative provided:

a) Flap asymmetry protection system is verified operative, and

b) Flap setting is verified symmetrical before each departure.

| |

10. AIR BRAKE Light B 1 0 (O) May be inoperative provided:

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

retracted position for each departure, and

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

| |||

11. Emergency Control

System (EMERG SLATS Switch)

C 1 0 (O) May be inoperative provided normal control system is verified operative.

|




PAGE NO: 27-3





27 FLIGHT CONTROLS

12. Slat Configuration Panel

B 1 0

1) Green Light (O) May be inoperative provided:

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

b) Position of the slats and the control are verified in agreement before each departure,

c) Wing anti-ice lights is operative, and

d) Red (In Transit) Light is operative.

|| | ||

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

Limitations are observed.

13. Automatic Slat

Extension Systems DELETED REVISION No 3.

14. STALL Test A 2 1 (O) One may be inoperative provided:

a) Slats are extended by the normal method for all flight at speeds below 200 KIAS,

b) Slat configuration panel is operative,

c) AUTO SLATS light is operative, and

d) Repairs are made within two flight days.

|||

15. Stall Warning B 1 0 (O) May be inoperative provided:

a) Both the automatic slat extension and the automatic ignition system are verified operative, and

b) Slats configuration panel is operative.

| |




PAGE NO: 27-4





27 FLIGHT CONTROLS

16. AUTO SLAT Light C 1 0 (O) May be inoperative provided: a) Airspeed does not exceed 270

KIAS, b) Slats are extended by the

normal method for all flight at speeds below 180 KIAS, and

c) Slat configuration panel is operative.

||

17. Rudder Pedal

Adjustments 27-20-00 C 2 0 (M)(O) 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.




PAGE NO: 28-1





28 FUEL

1. Booster Pumps 28-20-00

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

a) Feeder tank pressurization is verified before each departure,

b) Crossfeed valves are not opened until climb is established, and

c) Associated BOOST circuit breaker is pulled and collared.

|

2. Transfer Pumps (XFR)

28-13-00 C 3 2 (M)(O) One may be inoperative

provided: a) Wing tank pressurization and

wing tank-to-feeder tank transfer due to differential pressure are verified before each departure,

b) Appropriate adjustments are made in flight planning for potentially unusable fuel,

c) Transfer intercom valves are verified operative, and

d) Relevant XFR PMP circuit breaker is pulled and collared.

| ||

3. Crossfeed Valves (X-

FEED) 28-13-00 C 2 1 (M)(O) One may be inoperative

provided: a) It is secured in CLOSED

position, b) All booster pumps, transfer

intercom valves and associated fuel quantity indication system are verified operative, and

c) Associated circuit breaker is pulled and collared.

| || |||




PAGE NO: 28-2





28 FUEL

4. Transfer Intercom Systems (XFR INTERCOM) 28-13-00

C 2 0 May be inoperative provided all three transfer system, crossfeed valves and associated fuel quantity indication systems are operative.

|

5. Pressure Fueling

System 28-14-00 C 1 0 May be inoperative provided:

a) Cockpit FUELING caution light is operative and is extinguished, and

b) All fuel quantity systems are operative.

|| ||

NOTE: Complete filling of center tank

may not be possible.

1) Refueling Vent Valves C 3 0 (M) May be inoperative during open

sequence provided: a) Non fully open vent valve(s) is

(are) manually open, 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 extinguishes after closing sequence.

|

| C 3 0 (M) May be inoperative during closing

sequence provided: a) Non fully closed vent valve(s) is

(are) manually closed, and b) Cockpit FUELING caution light

is operative and extinguishes after closing sequence.

|




PAGE NO: 28-3





28 FUEL

6. Fuel QTY Indication Systems 28-40-00

C 3 2 (O) One may be inoperative provided: a) Single point fueling system

ONLY is used for refueling, b) Fuel quantity is verified

adequate before each takeoff, c) Fuel Used counter functions are

operative, and d) All REAR tank indicating

systems are operative.

|| |

7. LO FUEL Caution Light

28-40-00 B 1 0 (M) May be inoperative provided:

a) Fuel gauging systems in REAR position is operative,

b) REAR tank quantity system is monitored closely during flight, and

c) Light must be deactivated if steady illumination occurs.

|

8. ***

Fuel Temperature Indicator

C 1 0 (O) May be inoperative provided: a) Boost pumps, transfer systems

and engine crossfeed are operative, and

b) Operations are conducted at a TAT at least 3 Degrees C above the fuel freeze point.

||

9. ***

Fuel Burn/Gross Weight Totalizer

C 1 0

10. ***

Emergency Fuel Transfer System

C 1 0

11. FUELING Caution

Light C 1 0 (M) May be inoperative provided before

each departure it is verified that: a) Fueling panel access door is

closed, b) Fuel tanks pressurization is

verified, and c) Defueling valve is verified

closed.

|||




PAGE NO: 28-4





28 FUEL

12. Fuel Flow Meters B 3 2 One may be inoperative provided all other engine instruments and the fuel quantity indicating systems are operative.

||




PAGE NO: 29-1





29 HYDRAULIC POWER

1. HYDR PUMP 1, 2, or 3 Caution Lights 29-30-00

C 3 2 (O) One may be inoperative provided associated hydraulic pressure indicator is verified operative.

|

2. Hydraulic Pressure

System 1 or System 2 Indications (Analogue or EIED ) 29-30-00

C 2 1 (O) One may be inoperative provided: a) All pump lights of the

associated system is verified operative, and

b) Standby pump operation is verified operative before each departure.

|| |

3. Hydraulic Reservoir 1

or 2 Fluid Quantity Indications (Analogue or EIED ) 29-11-00

C 2 1 (O) May be inoperative provided: a) Fluid quantity is visually verified

adequate before each departure, and

b) Associated hydraulic pressure indication and pump caution light are verified operative.

| |

4. Tank Pressure Caution

Light(s) (TK.P1, TK.P2 or HYD TK PRESS)

C - 0 (M)(O) May be inoperative provided: a) All hydraulic pressure

indications are operative, b) Hydraulic Pressure indications

are closely monitored during flight, and,

c) If Hydraulic pressure is fluctuating the airplane remains at or below FL 200.

|




PAGE NO: 29-2





29 HYDRAULIC POWER

5. Standby Pump Caution Light 29-30-00

C 1 0 (M)(O) May be inoperative provided: a) Standby pump is verified

operative before departure, b) Selector handle is aft

compartment is secured in the flight position,

c) Standby pump is turned OFF during cruise flight, and

d) Standby pump is turned ON during takeoff, approach, or upon failure of the No. 2 hydraulic system pump.

||

6. No. 1 System

Accumulator 29-11-00 C 1 0

7. Main System

Accumulator Pressure Indicators 29-11-00

C 2 0 (M) May be inoperative provided an alternate procedure to verify accumulator pressure is established and used.

1) No. 1 System

Accumulator Pressure Indicator

C 1 0 May be inoperative provided associated accumulator is considered inoperative.




PAGE NO: 30-1





30 ICE AND RAIN PROTECTION

1. Wing Anti-Ice System

30-10-00

1) A/C Without SB F50-

0225 or M1844 C 1 0 (M)(O) May be inoperative provided:

a) Flight is not operated into known or forecast icing conditions, and

b) Both wing anti-icing valves are in the closed position.

||

2) A/C With SB F50-0225

or M1844 C 1 0 (M)(O) May be inoperative provided:

a) Flight is not operated into known or forecast icing conditions, and

b) The wing anti-icing valve is in the closed position.

||

2. NORM Wing Anti-Ice

Valve 30-10-00

1) A/C Without SB F50-

0225 or M1844 C 1 0 (M) May be inoperative in closed

position provided the STBY anti-ice valve is operative.

|||

2) A/C With SB F50-0225

or M1844 C 1 0 (O) May be inoperative in closed

position provided the flight is not operated into known or forecast icing conditions.

|

3. ST BY Wing Anti-Ice

Valve (A/C Without SB F50-0225 or M1844) 30-10-00

C 1 0 (M) May be inoperative in closed position provided the NORM anti-ice valve is operative.

|




PAGE NO: 30-2






4. Wing or Engine Anti-

Ice Indicating Systems 30-20-00

C 4 3 (O) One may be inoperative provided the associated anti-ice system is verified operative before each departure.

||

5. ***

Windshield Defogging Blower System 30-41-00

C 1 0 May be inoperative provided windshield heating systems are operative.

||

6. Windshield Heating

Systems 30-41-00 C 2 1 (O) One may be inoperative provided:

a) Windshield diverter air or blower defogging system is operative, and

b) Departure is not made into known precipitation, or into known or forecast icing conditions.

||

7. Side and Rear Flight

Deck Windows Heating System 30-41-00

C 1 0

8. Windshield Heat XFR

Light 30-41-00 C 1 0 (M) May be inoperative provided

temperature control, transfer systems and heating networks are verified operative.

| ||

9. Windshield Wipers 30-

43-00 C 2 0 (O) May be inoperative provided the

airplane is not operated in precipitation within 5 nautical miles of the airport of takeoff or intended landing.

10. Static Port Heating

Systems 30-31-00 B 2 1 (O) One may be inoperative for day

VMC provided airplane is not operated in visible moisture of known or forecast icing conditions.




PAGE NO: 30-3






11. Angle-of-Attack Sensor

Heating Systems 30-31-00

C 2 1 (O) One may be inoperative provided flight is not operated in known or forecast icing conditions.

12. Pitot/Static System

Heat Indicator Lights (L. PITOT or R. PITOT) 30-31-00

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

a) Associated heating system is verified operative before each departure, and

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

|

13. ***

Angle of Attack Heating System (Speed Indexes)

C 1 0 (O) May be inoperative provided flight is not operated in known or forecast icing conditions.

14. TAT Probe Heat

(Rosemont) C 1 0 (O) May be inoperative provided

airplane is not operated in known or forecast conditions.




PAGE NO: 30-4






15. Engine Anti-Ice System

30-20-00

1) Engine #1 and Engine

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

provided: a) Flight is not operated into

known or forecast icing conditions.

b) Corresponding anti-ice valve is set to closed position, and

c) Engine #2 and S-Duct anti-ice system are operative.

|

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

a) Flight is not operated into known of forecast icing conditions,

b) Engine #2 anti-ice valve is set to closed position, and

c) Engine #1 and #3 anti-ice systems are operative.

|

3) S-Duct Anti-Ice C 1 0 (M)(O) May be inoperative provided:

a) Flight is not operated into known or forecast icing conditions,

b) S-Duct anti-ice valve is set to closed position, and

c) Engine #1 and #3 anti-ice systems are operative.

|




PAGE NO: 31-1





31 INDICATING/ RECORDING SYSTEMS

1. Flight Data Recorder

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

FAR 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 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 airplane 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 flight days.

|

1) FDR Recording

Parameters required by FAR

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

is operative, and b) Repairs are made within three

flight 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. Flight Data Recorder

System (FDR) (Cont'd)

3) For an operator other

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 applicable FARs.

2. Clock with Sweep

Second Hand (or equivalent)

C - 1 One may be inoperative at either the pilot’s or copilot’s station.

3. ***

TAS Indicator C 1 0

4. ***

Cabin Data Indicator (TAS, TAT, OAT, ALT)

D 1 0

5. SAT/TAT/TAS

Indications C - 0

1) TAS Indications C - 0




PAGE NO: 31-3






6. ***

Bleed Air System Computer (BASC) Magnetic Indicators (Minelco) (Cockpit Maintenance Panel) (A/C with M2518 or SB280)

||

1) Red Indication B 2 0 (M) Aircraft may be dispatched with

computer magnetic indicators Red provided BASC is considered inoperative.

2) White Indication B 2 0 (M) Aircraft may be dispatched with

computer magnetic indicators failed White provided BASC is considered inoperative.




PAGE NO: 32-1





32 LANDING GEAR

1. Landing Gear Selector Flashing Light 32-60-00

C 1 0 May be inoperative provided the landing gear position indicators and warning horn are verified operative.

|

2. Aural Warning 32-60-

00 DELETED REVISION No 2.

3. Emergency/ Park

Brake 32-45-00 DELETED REVISION No 3.

4. #2P.BK light

(Steady Illumination) C 1 0 (O) May be inoperative provided:

a) T/O CONFIG warning system is verified operative, and

b) Parking brake pressure input to T/O CONFIG warning system is verified before each flight.

|| |

5. Anti-Skid System 32-

40-00

1) Dry Runways C 1 0 (O) May be inoperative provided:

a) Applicable AFM take-off and landing limitations and performance decrements are applied, and

b) T/O CONFIG warning system is verified operative before each departure.

|

(Continued)




PAGE NO: 32-2





32 LANDING GEAR

5. Anti-Skid System 32-40-00 (Cont’d)

2) Wet Runways C 1 0 (O) May be inoperative provided:

a) Operations are limited to utilization of PFCO or grooved runways,

b) Thrust Reverser is operative, c) Acceptable Performance Data

from an Analysis of the Accelerate Stop Capability on Wet Runway Surfaces is developed and used,

d) The Cross Wind Component for both departure and arrival runways is forecast to be 15 knots or less,

e) Acceptable Performance Data Report is referenced in the Operator’s Minimum Equipment List (MEL) by Report Name., Number, Revision Number, and Acceptance Date,

f) Performance Data Report assumes that Reverse Thrust action is terminated at 60 knots, and

g) Wet Runway Landing Operations are conducted in accordance with available Landing Performance Data in the AFM.

| |




PAGE NO: 32-3





32 LANDING GEAR

6. Nose Wheel Steering System

A 1 0 (M)(O) May be inoperative provided: a) Nose Wheel is verified free to

caster, b) Anti-Skid is operative, c) Airplane is not operated to or

from an airport with standing water or contamination on the runways,

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

e) Repairs are made within two flight days.

| |

7. Brake Pressure

Accumulator Low Pressure Indication (Flashing #2P.BK Light or BRAKE ACCU Warning Light)

C 1 0 (M) May be inoperative provided: a) Parking brake accumulator

pressure is verified adequate once each flight day, and

b) There is no leakage of nitrogen of the emergency braking system.




PAGE NO: 33-1





33 LIGHTS

1. Flight Deck and Instrument Panel Lighting Systems

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 crew member’s eyes, and

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

2. Passenger Cabin

Normal Lighting System

C - - Individual lights may be inoperative 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.




PAGE NO: 33-2





33 LIGHTS

3. Passenger Notice System (“No Smoking/Fasten Seat Belt” Signs)

C - - (O) ”No Smoking/Fasten Seat Belt” signs may be inoperative and the associated passenger seat(s) may be occupied provided:

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

b) An acceptable procedure is used to notify passengers when seat belts must be fastened or smoking is prohibited.

||

4. Aft Compartment

Lighting System 33-30-00

C 1 0

5. Landing Lights C 2 1 One may be inoperative for night

operations provided the taxi light is operative.

||

C 2 0 May be inoperative for day operations.

6. Taxi Light C 1 0 May be inoperative for night operations provided both landing lights is operative.

||





PAGE NO: 33-3





33 LIGHTS

7. Position Lights 33-41-00

1) Rear Navigation Light C 1 0 May be inoperative for day operations.

2) RH and LH Navigation Lights (A/C Without M2327 or SB F50-338)


3) RH and LH Navigation

Lights (A/C With M2327 or SB F50-338)

C 4 2 One may be inoperative on each side. |


8. Anti-collision Lights (Fuselage/ Vertical Fin) 33-41-00

C 2 0 May be inoperative provided wingtip/tail strobes are operative.

|

9. Wingtip/Tail Strobe

Lights 33-41-00 C 3 0 May be inoperative for day operations.

C 3 0 May be inoperative for night operations

provided anti-collision light is operative. |

10. Exterior Emergency

Lighting Systems C 3 0 May be inoperative for day operations.




PAGE NO: 33-4





33 LIGHTS

11. Windshield Ice Detection Light 33-50-00


C 1 0 May be inoperative for night operations

provide a portable lamp/light of suitable capacity is available when operating into known or forecast icing conditions.

12. ***

Wing Illumination Lights 33-41-00

C 2 0 (O) May be inoperative provided ground de-icing procedures do not require their use.

13. Baggage Compartment

Light 33-30-00 C 1 0

14. ***

LOGO Light System D 1 0

15. ***

Pulse Light System (Landing & Logo Lights)

D 1 0 |

16. ***

Pylon Lights D 2 0




PAGE NO: 34-1





34 NAVIGATION

1. Total Air Temperature Indicator 34-14-00

Deleted, Revision 3.

2. Mach Indications 34-

14-00 C 2 1 (O) One may be inoperative provided

the VMO/MMO aural warning is operative.

||

3. Vertical Speed

Indicators C 2 1 One may be inoperative for day VMC

flight operations only.

4. Altimeters DELETED REVISION No 1.

5. Airspeed Indicators DELETED REVISION No 1.

6. Air Data Computer 34-13-00

DELETED REVISION No 3.

7. VMO/MMO Aural

Warnings 34-13-00 B - 0 (O) May be inoperative provided:

a) Both Mach/Airspeed indicators are operative, and

b) AFM VMO/MMO limitations are applied.

|

8. VMO/MMO Aural

Warning Test System 34-15-00

C 1 0

9. Altitude Alerting

Preselector System 34-15-00

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 FAR.




PAGE NO: 34-2





34 NAVIGATION

10. Radio Altimeter System 34-43-00

A - 0 (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 flight days.

11. Bank-and-Pitch

Indicators (Horizon Indicator)


12. Standby Bank-and-

Pitch Indicator 34-21-00 (Except aircraft with Collins Pro Line 4 installed by STC ST00231WI-D or Collins Pro Line 21 STC ST01052WI-D)

C - 0 Any in excess of those required by FAR may be inoperative

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.

13. Attitude Transfer

System 34-21-00 C - 0 May be inoperative provided pilot and

copilot have independent attitude sources.

14. Flight Director Systems

(Computed Commands) 34-23-00

C 2 0 May be inoperative provided approach minimums do not require their use.

15. Horizontal Situation

Indicator (HIS) (Course Deviation Indication) 34-23-00





PAGE NO: 34-3





34 NAVIGATION

16. Instrument Compartment Warning System 34-24-00

C - 0 May be inoperative provided approach minimums do not require its use.

17. Excessive Deviation

Indication Lights 34-24-00

C - 0 May be inoperative provided approach minimums do not require its use.

18. Stabilized Heading

Indication System DELETED REVISION No 1.

19. Compass Transfer

System C - 0

20. ***

Remote Magnetic Indicator (RMI) 34-22-00

C - -




PAGE NO: 34-4





34 NAVIGATION

21. Non-stabilized Magnetic Compass 34-22-00

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 during 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.

|

22. ***

Angle-of-Attack Indicator 34-10-00

C 1 0

23. VHF NAV Receiver

Transfer 34-51-00 C - 0

24. Distance Measuring

Equipment (DME) 34-52-00





PAGE NO: 34-5





34 NAVIGATION

25. Marker Beacon Receiver 34-32-00

C - - May be inoperative provided approach minimums do not require its use.

26. Automatic Direction

Finder (ADF) 34-53-00 C - - As required by FAR.

27. Inertial Navigation

System (INS) 34-00-00 Moved to item 34-62, Rev. 2.

28. ***

Radar Navigation System

C 1 0

29. Flight Management

System C - 0 (O)Except where operations require

their use, may be inoperative provided IRS, if installed, are initialized by alternate means.

1) Navigation Data

Bases/Data Banks C - - (O) 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 tuned and identified.

30. Vertical Navigation

System (VNAV) C - 0




PAGE NO: 34-6





34 NAVIGATION

31. 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) May be inoperative provided:


a) Repairs are made within two flight days.

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

31. 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) operates normally.

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

31. Class B TAWS Equipment Required

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


c) Repairs are made within two 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.


a) Advisory callout not required by FAR, and

b) Alternate procedures are established and used

e) ***

Windshear Mode (Reactive)


(Continued)




PAGE NO: 34-9





34 NAVIGATION

31. 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

31. Class C TAWS

Equipment

*** TAWS/GPWS C 1 0 (O) May be inoperative provided


NOTE: Any mode that is operative may

be used. |

32. Weather Radar 34-41-

00 C - - As required by FAR.

33. ***

Radar Auto-Inhibit C 1 0 (O) May be inoperative provided: a) Primary Radar Indicator is

operative, and b) Radar is selected OFF or STBY

during ground operations.

||

34. ***

Angular/ Linear Deviation VOR Selectors

C 2 0 May be inoperative provided at least one VOR system is operative in the angular mode.

|




PAGE NO: 34-10





34 NAVIGATION

35. ***

EHSI Annunciation Display 34-01-00

1) Selected Heading C 2 1

2) Selected Course C 2 1 (O) One may be inoperative provided navigation does not require its use.

3) Bearing Pointers C 4 0 May be inoperative provided adjacent

RMI(s) are operative. |

4) DME Display C 2 0 As required by FAR.

5) Groundspeed/ Time To Go

C 2 0

6) ARC Mode C 2 0 NOTE: Weather radar requirements

must be considered if both ARC modes are inoperative.

7) Elapsed Time/TAS C 2 0

8) Wind Speed C 2 0

36. VLF/OMEGA Navigation Receiver

Incorporated into item 34-62 in Rev. 2. Effective Revision 3, VLF/Omega Navigation Receivers have deleted from the MMEL.

37. ***

Microwave Landing System (MLS)

C - - As required by FAR.




PAGE NO: 34-11





34 NAVIGATION

38. ATC Transponder/Automatic Altitude Reporting 34-54-00

B - 0 May be inoperative provided: a) Enroute operations do not

require its use, and b) Prior approval is obtained from

ATC facilities having jurisdiction over the planned route of flight.

D - - Any in excess of those required by

FAR may be inoperative.

39. ***

Voice Advisory/ Flight Profile Advisory

C 1 0

40. ***

Symbol Generators 34-01-00

C 3 2 (O) One may be inoperative provided each pilot’s EFIS is driven by an independent symbol generator unit which is operative.

|

41. Standby Altimeter (A/C

Without EFIS) 34-12-00

B 1 0 May be inoperative for day VMC only.

42. ***

Multifunction Display (MFD) (Radar) 34-90-01

C 1 0 May be inoperative provided: a) Procedures do not require its

use, and b) When required, at least one

radar display is operative.

|




PAGE NO: 34-12





34 NAVIGATION

43. ***

IRS NO AIR Warning Light (LASEREF MSU)

C - 0 (M) May be inoperative provided: a) Filter is checked for absence of

contamination and b) Cooling fan is operative.

|

C - 0 May be inoperative provided IRS is

considered inoperative.

44. Glide Slope Receiver Moved to ATA 34 Item 56, Rev. 3.

45. LORAN System Moved to item 34-62, Rev. 2.

46. Navigation Data Bank Incorporated into ATA 34 Item 29,

Revision 3.

47. ***

Storm Scope/Lightning Sensor

C - 0

48. Windshear Detection

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

a) Alternate procedures are established and used,

b) Windshear Warning and Guidance System (GPWS function) is installed and is operative.

||



b) Takeoffs and landings are not conducted in known or forecast windshear conditions.

49. ***

NAV/COM Preselect Tuning Functions

C - - May be inoperative provided direct tuning mode is installed and is operative for each associated unit.

||

50. ***

NAV/COM/ADF/XPNDR Memory Channels

C - 0 May be inoperative provided manual tuning is operative.

|




PAGE NO: 34-13





34 NAVIGATION

51. ***

NAV/COM/ADF/XPNDR Digital Frequency Selector/LCD/LED Display Units

C - 1 May be inoperative on one pilot side only provided:

a) Manual remote tune or dual FMS/CDU tune capability operates normally, and

b) All digital Frequency Selector/LCD/LED display units on opposite pilot side are operative.

||

52. ***

IRS (Compass) Transfer System

C - 0 May be inoperative provided compass information remains in the normal (onside) selector.

53. Traffic Alert and

Collision Avoidance System

1) TCAS I 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


(Continued)




PAGE NO: 34-14





34 NAVIGATION

53. Traffic Alert and Collision Avoidance System (Cont’d)

2) TCAS II B - 0 (M) May be inoperative provided:

a) System is deactivated and secured, and


C - 0 (M) May be inoperative provided:

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

secured, and c) Enroute or approach


a) ***

Combined Traffic Alert (TA) and Resolution Advisory (RA) Dual Display System(s)

C 2 1 May be inoperative on the non-flying pilot’s side provided:

a) TA and RA visual display is operative on the flying pilot’s side, and

b) TA and RA audio function is operative on the flying pilot’s side.

(Continued)




PAGE NO: 34-15





34 NAVIGATION

53. Traffic Alert and Collision Avoidance System (Cont’d)

b) Resolution Advisory

(RA) Display System(s) C 2 1 May be inoperative on the non-flying

pilot side. C - 0 (O) May be inoperative provided:

a) All Traffic Alert (TA) visual display and audio functions are operative

b) TA Only Mode is selected by the crew, and

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

c) Traffic Alert (TA)

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

a) RA visual display and audio functions are operative, and


d) Audio Functions B 1 0 May be inoperative provided enroute or

approach procedures do not require use of TCAS.

e) ***

Airspace Selection Function

C - 0

54. Attitude and Heading

System(s) (IRS, INS, AHRS, DG/VG)

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




PAGE NO: 34-16





34 NAVIGATION

55. ***

EADI Annunciators/ Displays 34-20-00

1) Fast/Slow Indications C 2 0 (M) May be inoperative provided

airspeed information is removed from display by an acceptable procedure.

|

2) Flight Director

Command Bars C 2 0 May be inoperative provided:

a) Approach minimums do not require their use, and

b) Erroneous Flight Director information is removed from pilots’ view.

3) Radio Altitude C 2 0 May be inoperative provided approach


4) ILS Deviation C 2 0 As required by FAR.

5) Marker Beacon Indications

C 2 0 As required by FAR.

6) Composite (COMP)

Mode C 2 1

7) Airspeed B 2 0 (M) May be inoperative provided


(Continued)




PAGE NO: 34-17





34 NAVIGATION

55. ***

EADI Annunciators/ Displays 34-20-00 (Cont’d)

8) Speed Trend C 2 0 (M) May be inoperative provided


9) Mach Indication C 2 0 (M) May be inoperative provided


10) Accel/ Decel Indication C 2 0

11) DH Set C 2 0 May be inoperative provided approach


56. ***

VHF Navigation System (VOR/ILS)

C - 0 As required by FAR.

57. ***

Global Positioning System (GPS)

Moved to ATA 34 Item 62, Rev. 3.

58. ***

Standby Airspeed Indicator (Pneumatic)

C 1 0 May be inoperative for day VMC flight only.

59. ***

Standby Airspeed Altimeter (Pneumatic)


60. ***

Standby Mach Airspeed Indicator


C 1 0 May be inoperative provided both normal mach indicators are operative.




PAGE NO: 34-18





34 NAVIGATION

61. ***

Attitude Heading Reference System (AHRS)

Moved to ATA 34 Item 54, Rev. 3.

62. ***

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


63. ***

Traffic Collision Avoidance Device (TCAD)

C - 0 (M)(O) May be inoperative provided system is deactivated.

64. ***

Airborne Flight Information System (AFIS)

Moved to ATA 23, Item 16, Rev. 3.

65. Turn and Bank

Indicators

1) ***

Rate of Turn Indicators C 2 1

C 2 0 May be inoperative provided Standby

Horizon indicator is operative. |

66. ***

Co-Pilot Standby Instrument System

C 1 0

67. ***

DDRMI C - 0




PAGE NO: 34-19





34 NAVIGATION

68. ***

Display Controller Panels (DCP)

A 2 1 (O) Except where Enroute operations require their use, may be inoperative provided:

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


| ||

69. ***

Reversion Switch Panels (RSP)

B 2 0 May be inoperative provided: a) Both Display Controller Panels

(DCP) is operative, and b) No reversion is selected.

|

70. ***

Air Data Reference Panels (ARP)

B 2 1 (O)Co-pilot position IAS/MACH function may be inoperative.

71. ***

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

72. ***

Primary Flight Display (PFD) Indications)

1) IAS Trend Vector C 2 0

2) Long Accel/Mach C 2 0

3) Wind C 2 0

73. ***

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




PAGE NO: 34-20





34 NAVIGATION

74. ***

Electronic Flight Instrument System (EFIS) Displays (Except aircraft with Collins Pro Line 4 installed by STC ST00231WI-D or M1924 or SB-280 or M2518 or Collins Pro Line 21 installed by STC ST01052WI-D)

A 4 3 (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 flight days.

| | ||||

NOTE 1: In case of a second MFD

failure in flight, TCAS and EGPWS situation awareness are not available.

NOTE 2: In case of a second MFD

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

75. ***

Electronic Checklist System


76 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 are considered inoperative. Refer to item 34.29

||||




PAGE NO: 35-1





35 OXYGEN

1. Passenger Oxygen System

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

a) Manual deployment is verified operative, and

b) Airplane remains at or below FL 250.

| ||

C 1 0 May be inoperative provided the airplane remains at or below 10,000 feet.

1) Passenger Service

Units C - - (M) One or more passenger service

units may be inoperative provided: a) Associated seats are placarded

and blocked to prevent occupancy, and

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

|

2) Cargo Only

Configuration D 1 0

2. Crew Portable Oxygen

Units (Bottle and Masks)


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

4. Portable Oxygen System





PAGE NO: 36-1





36 PNEUMATIC

1. HP1, HP2, and HP3 Bleed Air Valves


a) Affected valve is deactivated in the closed position,

b) Associated BLEED AIR- HP switch remains in the OFF position, and

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

||

2. ISOLATION Valve C 1 0 (M)(O) May be inoperative provided:

a) Valve is deactivated in the closed position,

b) ISOL rotary switch remains is ISOL position, and


3. Pressure Regulating

Valve (PRV) (Non-BASC equipped A/C only)

C 1 0 (O) May be inoperative in the CLOSED position only, provided Cabin Pressure is closely monitored closely at lower power settings.

4. ***

ISOLATION Rotary Switch (A/C With M2518 or SB280)

Deleted revision 4 |

5. ***

ISOL Caution Light (Overhead Panel) (A/C With M2518 or SB280)

C 1 0 (M)(O) May be inoperative provided: a) ISOL rotary switch remains in

ISOL position, b) ISOLATION valve is

deactivated in the closed position, and


|




PAGE NO: 36-2





36 PNEUMATIC

6. ***

APU BLEED AIR Valve C 1 0 (M) May be inoperative provided: a) Valve is deactivated in the

closed position, and b) APU is used for electrical power

only.

7. ***

APU BLEED AIR Switch

C 1 0 (M) May be inoperative provided: a) Switch remains in OFF position, b) APU BLEED AIR valve is


c) APU is used for electrical power only.

8. ***

BLEED APU Caution Light

C 1 0 (M) May be inoperative provided: a) APU BLEED AIR switch

remains in OFF position, b) APU BLEED AIR valve is


c) APU is used for electrical power only.

9. ***

Cockpit Air Conditioning Temperature Probe (A/C With SB-280 or M2518)

C 1 0 (M) May be inoperative provided: a) Cockpit conditioning valve is


b) Airplane remains at or below flight level 410.

||

10. ***

Wing Anti-Ice Temperature Probe (A/C With SB-280 or M2518)

C 1 0 (O) May be inoperative provided airplane is not operated in known or forecast icing conditions.

||




PAGE NO: 36-3





36 PNEUMATIC

11. ***

S-Duct Anti-Icing Temperature Probe (A/C With SB-280 or M2518)

C 1 0 (M)(O) May be inoperative provided: a) Passenger cabin conditioning

valve is deactivated in the closed position,

b) Air supply interconnect valve is manually open,

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

d) Airplane remains at or below flight level 410.

||

12. ***

Engine #1, #2, and #3 Bleed Overheat Probes (A/C With SB-280 or M2518)


a) All other temperature probes are operative,

b) Associated HP bleed air valve remains in the OFF position, and


||

13. ***

Wing Pressure Transmitter (A/C With M2518 or SB280)

C 1 0 (M)(O) May be inoperative provided: a) S-Duct pressure transmitter is

operative, and b) Airplane is not operated in


||

14. ***

S-Duct Pressure Transmitter (A/C With M2518 or SB280)

C 1 0 (M)(O) May be inoperative provided: a) Wing pressure transmitter is

operative, b) #1 and #3 engine anti-ice

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


|| |




PAGE NO: 36-4





36 PNEUMATIC

15. ***

BASC (Bleed Air System Computer) (A/C With M2518 or SB280)

B 1 0 (M)(O) May be inoperative provided: a) HP bleed and Anti-Ice valves

are verified closed, b) Airplane is not operated in

known or forecast icing conditions,

c) EFIS fans are verified operative, and

d) Flight is conducted in an unpressurized configuration

|| |

1) BASC Fault Codes

(A/C With M2518 or SB280)

|

a) Type C C - - May be displayed.

Note: the BASC fault code Type C covers the following fault codes after troubleshooting using FGDA document: - 405 : ADC2 Reading Failure - 406 : ADC1 Reading Failure - 409: TC Sensor Failure - 419: Pressure Sensor Drift - 435: Minelco Ouput Failure - 501: Pressure Sensor Drift - 505: TC' Sensor Failure - 532: ADC2 Reception Failure - 533: ADC1 Reception Failure - 534: Minelco Output Failure

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




PAGE NO: 38-1





38 WATER/WASTE

1. Portable Water System(s)

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

operates normally may be used.

(M) May be inoperative provided:

a) System is drained, and b) Procedures are established and

used to ensure that system is not serviced.

2. 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 a

unpressurized configuration, b) EFIS fans are verified

operative, c) Placard is installed on toilet

door with "DO NOT USE TOILET" inscription,

d) Draining port plug is verified to be in locked position, and

e) Repairs are made within three consecutive calendar days.

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

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

a) After manually operating the drain valve in closed position, it is checked there is no water leak at the drain valve, and

b) Repairs are made within three consecutive calendar days.

|||||||




PAGE NO: 38-2





38 WATER/WASTE

3. 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. |

(M) Associated lavatory system(s) may

be inoperative provided: a) Associated components are

deactivated or isolated to prevent leaks,

b) The Pilot-in-Command determines whether the flight duration is acceptable with 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





46 NEW TECHNOLOGY

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 |

D - 0 May be inoperative provided procedures

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.



*** 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 from the aircraft, and

b) Alternate procedures are established and used.

D - 0 (M) May be inoperative provided:

a) Associated EFB and hardware is secured by an alternate means or removed from the aircraft, and

b) procedures do not require its use.




PAGE NO: 49-1





49 AIRBORN AUXILIARY POWER

1. ***

Auxiliary Power Unit C 1 0 (M) May be inoperative or removed provided:

a) APU fuel shut-off valve is secured closed,

b) APU inlet door is verified closed.

c) APU circuit breaker is pulled and collared.

| ||



2. ***

APU Fault Detection Indicator

C 1 0 (M) May be inoperative provided APU is considered inoperative and not used.



3. APU N1 or T5

Indications C 1 0 (M) May be inoperative provided APU

is verified operative. |






PAGE NO: 52-1





52 DOORS

1. Door Warning Light

1) CABIN (on A/C where cabin light indicates high cabin altitude or doors open)

C 1 0 (M) May be inoperative provided: a) Cabin altitude aural warning

feature is verified operative, b) Before departure, each of the

cabin and exterior doors are verified closed and latched.

c) In flight, cabin altitude is closely monitored to ensure that it remains below 8,000 feet, and

d) Warning Light which remains illuminated is deactivated.

|

C 1 0 (M)(O) Cabin altitude function may be

inoperative provided: a) EFIS fans are verified

operative, and b) Flight is conducted in an

unpressurized configuration.

||

2) ***

DOORS

C 1 0 (M) May be inoperative provided it is verified that each of the cabin and exterior doors are closed and latched before each departure.

|




PAGE NO: 56-1





56 WINDOWS

1. Cockpit Windows (Glass)





PAGE NO: 73-1





73 ENGINE FUEL & CONTROL

1. Fuel Flow Meters 73-

30-00 A/C with TFE 731-3 engines only)

B 3 2 One may be inoperative provided: a) All remaining engine

instruments are operative, b) ITT, N1 and N2 indicators are

compared with those of the other engines, and

c) Fuel Used counter and Total Fuel Used/GW meter are not used.

| |

2. Engine

Synchronization System

C 1 0 May be inoperative provided Engine Synchronization remains OFF.

3. Engine Computers

(CMPTR 1, 2, 3) |

|

1) A/C with TFE 731-3 engines

B 3 2 (M)(O) Automatic mode of one computer may be inoperative provided:

a) Test to verify correct operation of the overspeed protection system of corresponding engine is performed in accordance with AFM annex 5,

b) Airplane is operated in accordance with instruction of AFM annex 5,

c) No other dispatch inoperative item or configuration deviation concerning powerplant or performance exists,

d) Associated ENG computer is operated in manual mode, and

e) Thrust Reverser is deactivated and secured in the stowed position if ENG Computer 2 is operated in manual mode.

|| ||||||

(Continued)




PAGE NO: 73-2





73 ENGINE FUEL & CONTROL

3. Engine Computers

(CMPTR 1, 2, 3) (Cont’d)

2) A/C with M2518 or

SB280 B 3 2 (M)(O) Automatic mode of one

computer may be inoperative provided: a) Test to verify correct operation

of the overspeed protection system of corresponding engine is performed in accordance with AFM annex 5A,

b) Airplane is operated in accordance with instruction of AFM annex 5A,

c) No other dispatch inoperative item or configuration deviation concerning powerplant or performance exists,

d) Associated ENG computer is operated in manual mode, and

e) Thrust Reverser is deactivated and secured in the stowed position if ENG Computer 2 is operated in manual mode.

|| | | ||||||




PAGE NO: 74-1





74 IGNITION

1. Ignition Indications (IGN Lights or IGN Label on EIED) 74-10-00

C 3 2 (O) One may be inoperative provided the automatic ignition system is verified operative.

||

2. Automatic Ignition

Systems (AOA Activated) 74-10-00


a) Manual ignition system is verified operative,

b) AIR START function is operative,

c) AIR START position is selected for takeoff, approach, landing and rough air penetration, and

d) AFM limitations are applied.

|

3. Ignition Selector

Switches 74-10-00 C 3 2 (O) One GRD START position may be

inoperative provided: a) Associated engine AIR START

position is operative, and b) Switch is returned to GRD

START position after each ground start.

|

4. Igniter Plugs C 6 5 One may be inoperative provided all

other powerplant systems are operative.

||




PAGE NO: 77-1





77 ENGINE INDICATING

1. N1 Indications 77-10-00

1) Digital Readouts

A/C with TFE 731-3 engines)

C 3 0


SB280 C 3 2 (O) One may be inoperative provided:

a) All N2, ITT and fuel flow indications are operative,

b) Associated DEEC is operative in AUTO mode, and

c) Associated EDC is operative.

|||| |

2. N2 Indications 77-11-

00

1) (A/C with TFE 731-3

engines) C 3 2 One may be inoperative provided N1

and Fuel Flow indicators for the associated engine are operative.

|



a) All N1, ITT and fuel flow indications are operative,

b) Associated DEEC is operative in AUTO mode,

c) Associated EDC is operative, and

d) During starting, the power lever is moved to idle at the first indication of N1.

|||| |




PAGE NO: 77-2






3. ITT Indications 77-22-00

1) Digital readout (A/C

with TFE 731-3 engines)

C 3 0 ITT Digital readout may be inoperative if ITT pointer is operative.

|



a) N1, N2, ITT and fuel flow indications are operative,

b) Associated DEEC is operative in AUTO mode, and

c) Associated EDC is operative.

|||| |

4. Fuel Flow Indications

(A/C with M2518 or SB280)

B 3 2 One may be inoperative provided all other engine indications and the associated fuel quantity indication system are operative.

|||

5. Fuel Used Indications


C 3 2 One may be inoperative provided the associated Fuel Flow and Fuel Quantity Indications are operative.

||

6. N1 Vibration Indication


C 3 0 ||

7. N2 Vibration Indication (A/C with M2518 or SB280)

C 3 0

|8. Engine Vibration

Monitoring Computer (EVMC) (A/C with M2518 or SB280)

C 3 0

|




PAGE NO: 77-3






9. Engine Instrument Electronic Displays (EIED) (A/C with M2518 or SB280)

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

a) No display parameter has failed,

b) Remaining EIED manual reconfiguration is operative,

c) Associated warning lights are operative,

d) SAT is considered as the fuel temperature, and

e) ALL DEEC are operative in auto mode.

| ||| |

1) EIED Fault Messages |

a) Type C C - - May be displayed. Note: the EIED fault messages Type C covers the following fault messages after troubleshooting using FGDA document: - UP_DISP/LINK_FROM_MID_DISP_ LOSS - UP_DISP/LINK_FROM_LOW_DISP_ LOSS - MID_DISP/LINK_FROM_UP_DISP_ LOSS - MID_DISP/LINK_FROM_LOW_ DISP_LOSS - LOW_DISP/LINK_FROM_UP_DISP_ LOSS - LOW_DISP/LINK_FROM_MID-DISP_LOSS

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

10 Oil Pressure Indication

(EIED) Deleted revision 4. Refer to item 79-5




PAGE NO: 78-1





78 ENGINE EXHAUST

1. Thrust Reverser System 78-30-00

C 1 0 (M)(O) May be inoperative provided: a) No damage to the thrust

reverser system exists which would adversely affect operation of the airplane,

b) Reverser is deactivated and secured in the stowed position by use of the safety pin,

c) All braking systems are operative, and

d) Reverser Unlock Light that remains illuminated must be deactivated.

||

2. DEPLOYED Green

Light C - 0 May be inoperative provided Thrust

Reverser is considered inoperative Refer to item 78-1

|||

3. TRANSIT Amber Light C - 0 May be inoperative provided Thrust


|||

4. REVERSER UNLOCK

Warning Light C 1 0 May be inoperative provided Thrust


|||




PAGE NO: 79-1





79 ENGINE OIL

1. OIL 1, 2, or 3, Caution Lights (Oil Pressure and Chip Detectors - TFE731-3 engine aircraft ONLY) 79-30-00

C 3 2 (M) One may be inoperative provided: a) Malfunction is verified to be in

the Warning System, b) Associated magnetic plugs are

visually checked for evidence of metal chips or clogging prior to the first flight of each day,

c) Associated Oil Pressure and Oil Temperature Indicators are operative and are monitored closely during flight, and

d) Caution Light which remains illuminated is deactivated.

||

2. Oil Pressure Indicator DELETED REVISION No 1.

3. CHIP DET SYSTEM (Yellow Lights on EIED) (A/C with M2518 or SB280)

A 3 2 (M) One may be inoperative or showing erroneous illumination provided:

a) Associated magnetic chip detector is visually checked free of metal particles prior to the first flight of the day, and


||

4. OIL 1, 2, and 3

Warning Lights (A/C with M2518 or SB280)

C 3 2 One may be inoperative provided: a) Associated Oil Pressure

Indicator on EIED is operative and is closely monitored during flight,

b) Associated Oil Temperature Indication on EIED is operative and is closely monitored during flight, and

c) A Warning Light which remains illuminated is deactivated.

|| |




PAGE NO: 79-2





79 ENGINE OIL

5. OIL Pressure Indications (EIED) (A/C with M2518 or SB280)

C 3 2 One may be inoperative provided: a) Associated OIL Warning Light

on Warning Panel is operative, and

b) Associated Oil Temperature Indication on EIED is operative and is closely monitored during flight.

|| |

6. OIL Temperature

Indications (EIED) (A/C with M2518 or SB280)

C 3 2 One may be inoperative provided: a) Associated OIL Warning Light

on Warning Panel is operative, and

b) Associated Oil Pressure Indication on EIED is operative and is closely monitored during flight.

||||




PAGE NO: 80-1





80 STARTING

1. Automatic Starter Cutout Features 80-00-00

C 3 2 (O) One may be inoperative provided starter is disengaged manually at 50% N2 during engine start.

master minimum equipment list rev6.pdf · 2011. 7. 22. · federal aviation administration page: iv...

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