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MINIMUM EQUIPMENT LIST

ATR42-500

ISSUED BY

OPERATIONS ENGINEERING

TECHNICAL DIVISION FLIGHT OPERATIONS PAKISTAN INTERNATIONAL FODITECH/ATR42/MELI/03

FEB/2017 (NOT VALID FOR ETOPS AND CARGO CONFIGURATION)

ATA SYSTEM / DESCRIPTION PAGE DATE

LIST OF EFFECTIVE PAGES I / II FEB 2019OPERATIONS ON NARROW RUNWAY III FEB 2017APPLICABILITY PAGE IIIA FEB 2017

1 FEB 20172 FEB 20173 FEB 20174 FEB 20175 FEB 20176 FEB 20177 FEB 20178 FEB 20179 FEB 2017

21-1 SEP 201821-2 SEP 201821-3 SEP 201821-4 SEP 201821-5 SEP 201821-6 SEP 2018

22 AUTOMATIC FLIGHT CONTROL SYSTEM 22-1 SEP 201822-2 SEP 201822-3 SEP 201823-1 FEB 201923-2 SEP 201823-3 SEP 201823-4 SEP 201824-1 SEP 201824-2 SEP 201824-3 SEP 201824-4 SEP 201825-1 SEP 201825-2 SEP 201825-3 SEP 201825-4 SEP 2018

23 COMMUNICATIONS

PAKISTAN INTERNATIONAL AIRLINES MINIMUM EQUIPMENT LIST ATR42-500

INDEX/LIST OF EFFECTIVE PAGES (PIA REV 2.0A)

PREAMBLE

21 AIR CONDITIONING

24 ELECTRICAL POWER

25 EQUIPMENT

25-4 SEP 201826-1 FEB 201726-2 FEB 201727-1 SEP 201827-2 SEP 201827-3 SEP 201827-4 SEP 201827-5 SEP 201828-1 SEP 201828-2 SEP 201828-3 SEP 201828-4 FEB 201928-5 SEP 2017

29 HYDRAULIC SYSTEM 29-1 SEP 201829-2 SEP 201830-1 SEP 201830-2 SEP 201830-3 SEP 201830-4 SEP 2018

31 INSTRUMENTS 31-1 SEP 201831-2 SEP 201831-3 SEP 201831-4 SEP 201831-5 SEP 201831-6 SEP 201831-7 SEP 2018

32 LANDING GEAR 32-1 SEP 201832-2 FEB 201933-1 SEP 201833-2 SEP 201833-3 FEB 201933-4 FEB 2019

FIRE PROTECTION

27

26

FUEL SYSTEMS

30 ICE AND RAIN PROTECTION

FLIGHT CONTROLS

33 LIGHTS

28

PAGE - I / FEB 2019

ATA SYSTEM / DESCRIPTION PAGE DATE

34-1 FEB 201934-2 FEB 201934-3 FEB 201934-4 FEB 201934-5 SEP 201834-6 SEP 2018

35 OXYGEN 35-1 SEP 201735-2 SEP 2017

36 PNEUMATIC SYSTEM 36-1 SEP 201736-2 FEB 2017

52 DOORS 52-1 FEB 201952-2 FEB 201952-3 FEB 2019

56 WINDOWS 56-1 SEP 201861 PROPELLER 61-1 SEP 2018

61-2 SEP 201861-3 SEP 201861-4 SEP 2018

73 ENGINE FUEL AND CONTROL 73-1 SEP 201873-2 SEP 2018

74 IGNITION 74-1 SEP 201875 AIR 75-1 FEB 201777 ENGINE INDICATING 77-1 SEP 2018

77-2 SEP 201879 OIL 79-1 SEP 2018

NAVIGATION34

PAKISTAN INTERNATIONAL AIRLINES MINIMUM EQUIPMENT LIST ATR42-500

INDEX/LIST OF EFFECTIVE PAGES (PIA REV 2.0A)

CAA APPROVAL NO. HQCAA/1076/038/FSAC/3982 DATED 08-03-2019

PAGE - II / FEB 2019(PIA Rev.2.0A as per DGAC approved MMEL Revision No.2.0 dated 01-02-2018)

PAGE III ISSUED BY: OPERATIONS ENGINEERING FEB /2017

ATR42-500

OPERATIONS ON NARROW RUNWAY ________________________________________________________________ Runway having width less than 30 meters (98 ft) is defined as “NARROW RUNWAY”. Presently PIA ATR42-500 is being operated on the following airfields which come under the Narrow Runway category.

D.I. KHAN (23 m / 75 ft) GAWADAR (23 m / 75 ft) PANJGUR (23 m / 75 ft) SIBI (23 m / 75 ft)

PAGE IV

ISSUED BY: OPERATIONS ENGINEERING FEB/2017

ATR42-500

APPLICABILITY PAGE ________________________________________________________________ This page shows, for each ATR42-500 aircraft, the cross reference between

The manufacturing serial number (M.S.N) The registration number

M.S.N REGISTRATION NUMBER

645 AP – BHH 653 AP – BHI 659 AP – BHM 661 AP – BHN 665 AP – BHP

This MEL is applicable to all the above aircraft.

ATR42-500 Minimum Equipment List

Operations Engineering Page 1 of 9

PREAMBLE 1. GENERAL 1.1 The CAA Rules require that all equipment installed on an aircraft in

compliance with the Airworthiness Standards and the Operating Rules must be operative. However, the rules also permit the publication of a Minimum Equipment List (MEL) where compliance with certain equipment requirements is not necessary in the interest of safety under all operating conditions. Experience has shown that with the various levels of redundancy designed into aircraft, operation of every system or installed component may not be necessary when the remaining operative equipment can provide an acceptable level of safety. A Master Minimum Equipment List (MMEL) is developed by FAA or the Regulatory Body of the country of origin of the subject aircraft, with participation by the aviation industry, to improve aircraft utilization and thereby provide more convenient and economic air transportation for the public. This approved MMEL will include those items of equipment related to Airworthiness and operating regulations and other items of equipment which the regulatory body finds may be inoperative and yet maintain an acceptable level of safety by appropriate conditions and limitations; it does not contain obviously required items such as wings, flaps and rudders. The MMEL is the basis for development of individual operator’s MEL which takes into consideration the operator’s particular aircraft equipment configuration and operational conditions. Operator MELs for administrative control may include items not contained in the MMEL; however, relief for administrative control items must be approved by the DG CAA. An operator’s MEL may differ in format from the MMEL, but cannot be less restrictive than the MMEL. Based upon the respective aircraft configuration the operator will develop its own MEL and submit the same to DG CAA for approval together with the MMEL of the aircraft type. The individual operator’s MEL, when approved and authorized, permits operation of the aircraft with inoperative equipment covered by the MEL.

1.2 Equipment not required by the operation being conducted and

equipment in excess of CAA requirements are included in the MEL with appropriate conditions and limitations. The exposure to additional failures during continued operation with an operative system or component must also be considered in determining that an acceptable level of safety is being maintained. The MEL must not deviate from the Aircraft Flight Manual Limitations, Emergency Procedures or with Airworthiness Directives. It is important to remember that all equipment related to the airworthiness and the operating regulations of the aircraft not listed on the MMEL must be

FEB 17


Page 2 of 9 Operations Engineering

operative. Suitable conditions and limitations in the form of placards, maintenance procedures, crew operating procedures and other restrictions as necessary are specified in the MEL to ensure that an acceptable level of safety is maintained.

1.3 The MEL is intended to permit operation with inoperative items of

equipment for a period of time until repairs can accomplished. It is important that repairs be accomplished at the earliest opportunity. In order to maintain an acceptable level of safety and reliability the MMEL establishes limitations on the duration of and conditions for operation with inoperative equipment. The MEL provides for release of the aircraft for flight with inoperative equipment. When an item of equipment is discovered to be inoperative, it is reported by making an entry in the Aircraft Maintenance Record/logbook. The item is then either repaired or may be deferred as per the MEL. MEL conditions and limitations do not relieve the operator from determining that the aircraft is in condition for safe operation with items of equipment inoperative.

1.4 When these requirements are met, an Airworthiness Release,

Aircraft Maintenance Record/logbook entry, or other approved documentation is issued. Such documentation is required prior to operation with any item of equipment inoperative. Operators are responsible for exercising the necessary operational control to ensure that an acceptable level of safety is maintained. When operating with multiple inoperative items, the interrelationships between those items and the effect on aircraft operation and crew workload will be considered. Operators are to establish a controlled and sound repair program including the parts, personnel, facilities, procedures and schedules to ensure timely repair.

1.5 Despatch/Release of airplane with more than one item

unserviceable is not allowed if a simultaneous change in operating procedure for more than one major aircraft system would be necessary e.g. faults which require a change in electrical system operation and in hydraulic system operation would not be simultaneously permissible. Despatch/Release of airplane with more than one part missing from any one system is not allowed unless specifically indicated in CDL. Parts from different systems may be missing simultaneously, unless otherwise specified provided the limitation imposed by para 1.4 is not violated. WHENEVER DOUBT EXISTS TO DESPATCH OR NOT, contact General Manager Technical Operations and Chief Engineer Quality Assurance (QA) or their representatives for advice on telephone at Karachi.

1.6 WHEN USING THE MEL, COMPLIANCE WITH THE STATED INTENT

OF THE PREAMBLE, DEFINITIONS, AND THE CONDITIONS AND

FEB 17



LIMITATIONS SPECIFIED IN THE MEL IS REQUIRED. Definitions of various symbols, abbreviations etc. used in the MEL format is to be in line (with required approved alterations) with the Definitions as given in the Federal Aviation Administration – Master Minimum Equipment List copy of which is attached as Annexure-1 to this Preamble.

2. RELEASE OF AIRCRAFT FROM A TRANSIT STATION WITH DEFECTS COVERED UNDER MEL

2.1 In case where a defect is detected enroute, every endeavor should

be made to rectify it. Only in exceptional cases, where the defect cannot be justifiably rectified at the transit stations, and the same does not affect the safety of flight, it may be Carried Forward in the technical log for rectification at Base.

2.2 Effective monitoring of the Carried Forward (CF) defects shall be

carried out on continuous basis by Flight Operations and Engineering and Maintenance Departments on CARRIED FORWARD DEFECT MONITORING AND CONTROL (CFDM & C) SYSTEM.

2.3 Enough justification must be available if a snag is carried forward in

Technical Log. 2.4 CF defects shall be entered in the release Tech Log Slip. 3. RELEASE OF AIRCRAFT FROM KARACHI OR ISLAMABAD WITH

CARRIED FORWARD DEFECTS 3.1 Aircraft for which Base Maintenance facility exists at Karachi then

Karachi Airport will be considered as Base for this aircraft and Islamabad Airport will be considered as base for the aircraft for which Base Maintenance facility exists at Islamabad. All possible effort will be made when the aircraft lands at its base with a Carried Forward (CF) defect to rectify the same. Only in exceptional cases (but within the Repair Intervals as given in the definitions – Annexure – 1) the defect may be carried forward on the aircraft from its Base.

3.2 It will be Engineering responsibility to ensure that the aircraft is not

released on a flight when the time period limitation given in MEL (in form of ABC) is exceeded.

3.3 The Allowable Technical Deficiency Information will be sent to

stations along the route. The information shall be recognized by a FEB 17



standard prefix “AATD” (Aircraft Allowable Technical Deficiency, Flt. No. and Aircraft Registration). This will always be sent by MCC.

3.4 For defects that are CF ex-base (Karachi or Islamabad as

applicable) the status report will be sent to Flight Standards Directorate, CAA every 3 days.

4. RELEASE OF AIRCRAFT FROM OUTSTATION WITH DEFECT/

DEFECTS NOT COVERED UNDER MEL 4.1 Under normal circumstances no such release shall be allowed.

However, in extreme emergency, procedure as laid down in para 4.2 through 4.3 shall be followed to release aircraft under these circumstances.

4.2 If an aircraft at outstation is required to be released with defect /

defects to be carried forward which are not covered under MEL then the same is to be brought to the notice of Director Flight Operations and Director Engineering and Maintenance or their representatives. The above two Directors would jointly study the reported defect / defects and determine its impact on the safety of flight of the effected aircraft. If the aircraft is to be released for flight with the said defect / defects not rectified than this is to be brought to the notice of CAA (Director Flight Standards (DFS) or his representatives) by the Director Flight Operations or Director Engineering & Maintenance or their representatives that they have jointly arrived at the decision that the aircraft can be released and that clearance for the same may be accorded for the aircraft to return to the base. The aircraft is to be released only after obtaining the approval from the Civil Aviation Authority.

4.3 Release of aircraft with MEL covered defects on expiry of time

period limitations given in MEL (in form of ABC) is NOT covered under this authorization.

5. CREW RESPONSIBILITIES 5.1 The existence of this list does not in any way absolve the Captain

from ensuring that the aircraft is safe for particular flight from the time the aircraft departs.

5.2 Captain has to be aware of all Operational and Technical

consequences of the failure concerned and has to ensure that the faulty system component is adequately isolated or deactivated and placarded.

FEB 17



5.3 The Pilot – in – Command will ensure that the appropriated crewmembers are properly acquainted with any revision of procedures, duties or limitations.

5.4 The Captain has the authority to insist on the rectification of a

defect even though it is covered under MEL, irrespective of the decision from Operators Headquarters.

5.5 If Captain insists on rectification, Captain will star mark the defect

and put down his signature. Star marking will only be done by crew operating the out going flight.

(A N N E X U R E – 1) 1. SYSTEM DEFINITIONS

System numbers are based on the Air Transport Association (ATA) Specification Number 100 and items are numbered sequentially. a) “Item” (Column 1) means the equipment, system, component,

or function listed in the “Item” column. b) “Standard Equipment” (Column 2) is the number (quantity) of

items normally installed in the aircraft. This number represents the aircraft configuration considered in developing this MEL. Should the number be a variable (e.g. passenger cabin items) a number is not required. NOTE: When the MMEL shows a variable number installed,

the MEL must reflect the actual number installed or an alternate means of configuration control approved by the DFS/DAW (CAA)

c) “Minimum for Dispatch” (Column 3) is the minimum number

(quantity) of items required for operation provided the conditions specified in column 4 are met.

d) “Supplemental Procedure” (column 4) in this column includes a

statement either prohibiting or permitting operation with a specific number of items inoperative, provisos (conditions and limitations) for such operation, and appropriate notes.

FEB 17



e) A vertical bar (change bar) in the margin indicates a change, addition or deletion in the adjacent text for the current revision of that page only. The change bar is dropped at the next revision of that page.

2. “Airplane/Rotorcraft Flight Manual” (AFM/RFM) is the document

required for type certification and approved by the responsible FAA Aircraft Certification Office. The FAA approved AFM/RFM for the specific aircraft is listed on the applicable Type Certificate Data Sheet.

3. “As required by FAR” means that the listed item is subject to

certain provisions (restrictive or permissive) expressed in the Federal Aviation Regulations operating rules. The number of items required by the FAR must be operative. Items installed that are in excess of the FAR requirements may be permitted by the Operator’s MEL to be inoperative if not otherwise required by the MMEL.

4. “*” symbol in column 4 indicates the listed item if inoperative, must

be placarded to inform and remind the crew members and maintenance personnel the equipment condition.

NOTE: To the extent practical, placards should be located

adjacent to the control or indicator for the item affected however, unless otherwise specified placard wording and location will be determined by the operator.

5. “-” symbol in column 2 and/or column 3 indicates a variable

number (quantity) of the item installed. NOTE: Where the MMEL shows a variable number installed,

the MEL must reflect the actual number installed or an alternate means of configuration control approved by the DFS/DAW (CAA).

6. “Deleted” in the remarks column after a sequence item indicates

that the item was previously listed but is now required to be operative if installed in the Aircraft.

7. “Federal Aviation Regulations” (FAR) means the applicable portions of the Federal Aviation Act and Federal Aviation Regulations. 8. “Flight Day (Calendar day)” means a 24 hour period ( from

midnight to midnight ) either Universal Coordinated Time (UTC) or local time, as established by the operator, during which at least one flight is initiated for the affected aircraft.

FEB 17



9. “Icing Conditions” means an atmospheric environment that may cause ice to form on the aircraft or in the engine(s).

10. Alphabetical symbol in column 4 indicates provisos (condition or

limitation) that must be complied with for operation with the listed item inoperative.

11. “Inoperative” means a system and/or component’s malfunction to

the extent that it does not accomplish its intended purpose and/or is not consistently functioning normally within its approved operating limit(s) or tolerances.

12. “Notes” in column 4 provide additional information for crew member

or maintenance consideration. Notes are used to identify applicable material which is intended to assist with compliance, but do not relieve the Operator of the responsibility for compliance with all applicable requirements. Notes are not part of the provisos.

13. Inoperative components of an inoperative system: Inoperative items

which are components of a system which is inoperative are usually considered components directly associated with and having no other function than to support that system. (Warning/caution systems associated with inoperative system must be operative unless relief is specifically authorized as per the MMEL).

14. “(M)” symbol indicates a requirement for a specific maintenance

procedure which must be accomplished prior to operation with the listed item inoperative. Normally these procedures are accomplished by maintenance personnel; however, other personnel may be qualified and authorized to perform certain functions. Procedures requiring specialized knowledge or skill, or requiring the use of tools or test equipment should be accomplished by maintenance personnel. The satisfactory accomplishment of all maintenance procedures, regardless of who performs them is the responsibility of the Operator. Appropriate procedures are required to be published as part of the Operator’s manual or MEL.

15. “(O)” symbol indicates a requirement for a specific operations

procedure which must be accomplished in planning for and/or operating with the listed item inoperative. Normally these procedures are accomplished by the flight crew; however, other personnel may be qualified and authorized to perform certain functions. The satisfactory accomplishment of all procedures, regardless of who performs them is the responsibility of the Operator. Appropriate procedures are required to be published as part of the Operator’s manual or MEL. FEB 17



NOTE: The (M) and (O) symbols are required in the

Operator’s MEL unless otherwise authorized by the DFS/DAW CAA.

16. “Deactivated” and “Secured” means that the specified component

must be put into an acceptable condition for safe flight. An acceptable method of securing or deactivating will be established by the Operator.

17. “Visual Flight Rules” (VFR) is as defined in FAR Part 91. This

precludes a pilot from filling an Instrument Flight Rules (IFR) flight plan.

18. “Visual Meteorological Conditions” (VMC) means the atmospheric

environment is such that would allow a flight to proceed under the visual flight rules applicable to the flight. This does not preclude operating under Instrument Flight Rules.

19. “Visual Moisture” means an atmospheric environment containing

water in any form that can be seen in natural or artificial light; for example, clouds, fog, rain, sleet, hail or snow.

20. “Passenger Convenience Items” means those items related to

passenger convenience, comfort or entertainment such as, but not limited to, galley equipment, movie equipment, ash trays, stereo equipment, overhead reading lamps, etc

21. Flight “extended over water” means Aeroplanes flying more than 50

NM from shore line. Similarly Long range flight over water means Aeroplanes more than 30 minutes flying time or 100 NM from shore line which ever is less.

22. Not Applicable: means that item is not installed on PIA fleet or item is

not applicable to PIA fleet. 23. Repair intervals: All users of an MEL approved under FAR 121,

125, 129 and 135 must effect repairs of inoperative systems or components, deferred in accordance with the MEL, at or prior to the repair times established by the following letter designators:

CATEGORY A Items in this category shall be repaired within the time interval specified in the remarks column of the operator’s approved MEL.

FEB 17



CATEGORY B Items in this category shall be repaired within three (3) consecutive calendar days (72 hours), excluding the day the malfunction was recorded in the aircraft maintenance record/logbook. For example if it was recorded at 10 am on January 26th, the 3 day interval would begin at midnight the 26th and end at midnight the 29th. CATEGORY C Items in this category shall be repaired within ten (10) consecutive calendar days (240 hours), excluding the day the malfunction was recorded in the aircraft maintenance record/logbook. For example if it was recorded at 10 am on January 26th, the 10 day interval would begin at midnight the 26th and end at midnight February 5th. CATEGORY D Items in this category shall be repaired within one hundred and twenty (120) consecutive calendar days (2880 hours), excluding the day the malfunction was recorded in the aircraft maintenance record / logbook. THE LETTER DESIGNATORS ARE INSERTED ADJACENT TO COLUMN 2

24.“Administrative control item” means an item listed by the operator in

the MEL for tracking and informational purposes. It may be added to an operator’s MEL by approval of the General Manager Technical (Operations) / Chief Engineer (QA) provided no relief is granted, or provided conditions and limitations are contained in an approved document i.e. Structural Repair Manual, Airworthiness directive, etc. If relief other than that granted by an approved document is sought for an administrative control item, a request must be submitted to the DFS/DAW (CAA). If the request results in review and approval by the CAA, the item becomes an MEL item rather than an administrative control item.

FEB 17

PIA ATR 42‐500 MINIMUM EQUIPMENT LIST

CH21 AIRCONDITIONINGPage 21‐1(PIA REV 2.0)

SEP, 2018

SUPPLEMENTAL PROCEDURES

21-10-01 FLOW SELECTOR C 1 0 * May be inoperative provided that one mode (NORM or HIGH) is operative and used.

Note

Some smoke procedures request to select air flow HIGH. Nevertheless associated procedures efficiency has been demonstrated with air flow NORM.

21-22-01 RECIRCULATION FAN C 2 0 * May be inoperative.

21-23-01 OVERBOARD VALVE21-23-01A AUTOMATIC MODE (A) C 1 0 * (O) Automatic mode may be inoperative provided that:

(a) Manual mode is checked operative before each

departure,and

(b) Flight is conducted in order to maintain ∆P ≤ 1 PSI.

See Operational procedure MOP.21.23-01P Overboard Valve(O)

-OR-21-23-01B (B) C 1 0 * (M) May be inoperative provided that:

(a) It is deactivated, and

(b) Extended overwater flight is prohibited, and

(c) Flight level is limited to FL 170, and

(d) FLOW selector is considered inoperative, Refer to Item

21-10-01 MOP.21.10-01 Flow Selector

See Maintenance procedure MMP.21.23-01 Overboard Valve (M)

MINIMUM FOR DISPATCH

ITEM

STANDARD EQUIPMENT

21-23-01P Overboard Valve (O)

□ On ground before depaarture● OVBD VALVE SELECTOR SWITCH.……. FULL CLOSE

● OVBD VALVE…………………..CHECK FULLY CLOSED

● OVBD VALVE SELECTOR SWITCH.….….. FULL OPEN

● OVBD VALVE……………….……..CHECK FULLY OPEN

□ On ground, engine 1 not running● OVBD VALVE SELECTOR SWITCH….……FULL OPEN□ In flight or on ground, engine 1 running

● OVBD VALVE SELECTOR SWITCH………FULL CLOSE

□ If EXHAUST MODE come on amber and ∆P ≤ 1 PSI

● OVBD VALVE SELECTOR SWITCH…….…FULL OPENCAUTION

● Do not select OVBD VALVE OPEN if ∆P > 1 PSI.

21-23-02 UNDERFLOOR VALVE C 1 0 * (O) May be inoperative in closed position provided that: (a) Exhaust mode is selected OVBD , and

(b) Extended overwater flight is prohibited, and

(c) Flight level is limited to FL170.

See Operational procedure MOP.21.23-02P Underfloor Valve (O)

21-23-02P UNDERFLOOR VALVE (O) ● Select exhaust mode OVBD.Note

● Avoid leaving avionics selected ON for a long period

of time.



SEP, 2018



ITEM

STANDARD EQUIPMENT

21-23-03-01 C 1 0 * (O) May be inoperative provided that:

(a) Exhaust mode is selected OVBD , and

(b) Extended overwater flight is prohibited,and

(c) Flight level is limited to FL170.

See Operational procedure MOP.21.23-03P Extract Fan - Passenger Configuration (O)

21-23-03-02 EXTRACT FAN -CARGO CONFIGURATION NO GO

21-23-03P EXTRACT FAN - PASSENGER CONFIGURATION (O)

● Select exhaust mode OVBD.

Note

Avoid leaving avionics selected ON for a long period of time.

21-30-01-01 * (O) (M)

See Operational procedurue MOP.21.30-01P Pressurization System (O)

See Maintenance procedurue MMP.21.30-01 Pressurization System (M)

21-30-01-02 PRESSURIZATION SYSTEM CARGO CONFIGURATION

C 1 0 * (O) (M) The pressurization system (automatic and manual modes) may be inoperative for a non pressurized flight provided

1PRESSURIZATION SYSTEM - PASSANGER CONFIGURATION

0C The pressurization system (automatic and manual modes) may be inoperative for a non pressurized flight provided that outflow valve is secured in open position if manual is inoperative.

EXTRACT FAN -PASSENGER CONFIGURATION

- CARGO CONFIGURATION may be inoperative for a non pressurized flight provided that:(a) No combustible material is carried in any compartment.

(b) Outflow valve is secured in open position if manual

mode is inoperative.

See Opetation procedure MOP.21.30-01P Pressurization System (O)

See Maintenance procedure MMP.21.30-01 Pressurization System (M)

21-30-01P PRESSURIZATION SYSTEM (O) Unpressurized flight

Limitation

Maximum operating altitude……….....……….10000 ft

Normal Procedures

□ If manual mode is operative

● OVBD VALVE……………….………….FULL OPEN

● CAB PRESS MODE SEL…………………..….MAN

● MAN RATE knob………………..…MAX INCREASE

● BLEED VALVE………………………...………....ON

Note

Control aircraft vertical speed to take into account passenger comfort.

□ If manual mode is inoperative

● MAINTENANCE PROCUDURE ……..……..APPLY



SEP, 2018



ITEM

STANDARD EQUIPMENT

* (O)May be inoperative for a pressurized flight provided that:

(a) Manual pressurization is operative, and

(b) ALT, RATE and DIFF indications are operative.

See Operational procedure MOP.21.31-01P Automatic pressurization Control (O)

21-31-01P AUTOMATIC PRESSURIZATION CONTROL (O)

● Set cabin altitude manually based on table below (∆P = 6 PSI)

FL 140 170 200 220 240 250

TARGET CAB ALT (ft) 2500 3300 4200 5200 6200 6800

21-31-02 DESCENT RATE SELECTOR

C 1 0 * May be inoperative.

* (M) May be inoperative provided that:

(a) It is secured in closed position, and

(b) Flight is conducted with manual pressurization:

Refer to Item 21-31-01 Automatic pressurization Control.

See maintenance procedure MMP.21.31-03 Electropneumatic Outflow Valve (M)

21-31-04-01 CABIN PRESS Indication - ALT

AUTOMATIC PRESSURIZATION CONTROL

C21-31-01 01

1 0C21-31-03 ELECTROPNEUMATIC OUTFLOW VALVE

CABIN PRESS indicator - ALT Indication

C 1 0 * (O) May be inoperative provided that DIFF indication is operative.

See Operational procedure MOP.21.31-04-01P CABIN PRESS Indication - ALT (O)

21-31-04-01P CABIN PRESS Indication - ALT (O)

CABIN PRESS Indicator - ALT Indication (O)

● Check DIFF based on table below

FL 140 170 200 220 240 250

TARGET (PSI) 3.5 4.6 5.7 5.9 6 6.35

21-31-04-02 CABIN PRESS INDICATION -RATECABIN PRESS Indicator - RATE Indication

C 1 0 * (O) May be inoperative provided that ALT indication is operative.

See Operatinal procedure MOP.21.31-04-02P CABIN PRESS Indication-RATE (O)

21-31-04-02P CABIN PRESS Indication RATE (O)CABIN PRESS Indicator - RATE Indication (O)

● Check cabin altitude based on table below (DIFF = 6 PSI):

FL 140 170 200 220 240 250

TARGET CAB 2500 3300 4200 5200 6200 6800 ALT (FT)



SEP, 2018



ITEM

STANDARD EQUIPMENT

21-31-04-03 CABIN PRESS Indication - Pressure

CABIN PRESS Indicator - DIFF Indication

C 1 0 * (O) May be inoperation provided that ALT indication is operative.

See Operational procedure MOP.21.31-04-03P CABIN PRESS Indication - Pressure (O)

21-31-04-03P CABIN PRESS Indication - pressure (O)CABIN PRESS Indicator - DIFF Indication (O)

Check cabin aititude based on table below (DIFF = 6 PSI):

FL 140 170 200 220 240 250

TARGET CAB 2500 3300 4200 5200 6200 6800 ALT (ft)

21-31-05 DITCH FUNCTION C 1 0 * May be inoperative.

21-31-06 INDICATIONS AND CONTROLS ON MAINTENANCE PANELS

C - 0 May be inoperative.

21-35-01 DUMP FUNCTION C 1 0 * (O) May be inoperative provided that manual pressurization is operative.See Operational procedure MOP.21.35-01 DUMP Function (O)

21-35-01P DUMP FUNCTION (O) □ Incase of rapid depressurization of the aircraft is ( ) p pneeded:● MAN RATE knob………...……...…….…..MAN

● CAB PRESS MODE SEL ……...….…….MAN

● MAN RATE KNOB……...…MAX INCREASENoteResidual ∆P may be cancelled using the cockpit

communcation door.

21-50-01 PACK C 2 1 * (O) One may be inoperative provided that flight level is limited to FL170.

See Operational procedure MOP.21.50-01P Pack (O)

21-50-01P PACK (O) As an in-flight failure could imply total loss of pressurization, fuel consumption at FL 100 must be taken into account to compute the trip fuel.

Note

With a pack selected OFF, engine torque parameter of the related side will increase.● PL (Affected engine) …… ADJUST TO OTHER ENGINE

21-51-01 PACK VALVE C 2 1 * (O) (M) One may be inoperative provided that :

(a) It is secured closed, and

(b) Associated pack is considered inoperative: Refer to Item 21-50-01 Pack.

See Operational procedure MOP.21.51-01P Pack Valve (O)

See Maintenance procedure MMP.21.51-01 Pack Valve (M)



SEP, 2018



ITEM

STANDARD EQUIPMENT

21-51-01P PACK VALVE (O) As an in-flight failure could imply total loss of pressurization, fuel consumption at FL 100 must be taken into account to compute the trip fuel.

NoteWith a pack selected OFF, engine torque parameter of the related side will increase.● PL (Affected engine) …… ADJUST TO OTHER ENGINE

21-51-02 PACK FAULT ALERT C 2 1 * (O) One may be inoperative provided that associated pack is considered inoperative: Refer to item 21-50-1 Pack.

See Operational procedure MOP.21.51-02P Pack Fault Alert (O)

21-51-02P PACK FAULT ALERT (O) As an in-flight failure could imply total loss of pressurization, fuel consumption at FL 100 must be taken into account to compute the trip fuel.

NoteWith a pack selected OFF, engine torque parameter of the related side will increase.● PL (Affected engine) …… ADJUST TO OTHER ENGINE

21-51-03 COOLING FAN

* May be inoperative provided that:

(a) Affected pack is not used on ground, and

(b) Cruise level is chosen to allow a 150 kt minimum

IAS with one engine inoperative.

02TURBO FAN C

21-51-05 AUX AFT CARGO VENTILATION VALVE

C 1 0 * May be inoperative provided that no combustible marerial is carried in the associated compartment.

21-61-01 PACK AUTO TEMPERATURE CONTROL

21-61-01 A (A) C 2 1 * (O) One may be inoperative provided that associated pack MAN temperature control is operative.

See Operational Procedure MOP.21.61-01P Pack AUTO Temperature Control (O)

-OR-

21-61-01B (B) C 2 1 * One may be inoperative provided that associated pack is considered inoperative: Refer to Item 21-50-01 Pack

21-61-01P PACK AUTO TEMPERATURE CONTROL (O) ● TEMP SEL (affected side) …………………...……… MAN

● Adjust manually the associated pack discharge

temperature to obtain the same duct indication

as the opposite pack.

21-61-02 PACK MAN TEMPERATURE CONTROL

21-61-02A (A) C 2 1 * One may be inoperative provided that associated pack AUTO temperature control is operative.

-OR-



SEP, 2018



ITEM

STANDARD EQUIPMENT

21-61-02B (B) C 2 1 * One may be inoperative provided that associated pack is considered inoperative:

Refer to item 21-50-1 Pack

* (O) One may be inoperative provided that associated DUCT indication is operative.

See Operational procedure MOP.21-61-03P OVHT Alert (O)

21-61-03P OVHT ALERT (O) ● Moniter and maintain DUCT induction below 92 ᴼC/200 ᴼF.

21-63-01-01 COMPT Temp - FLIGHT DECK INDICATION


21-63-01-02 COMPT TEMP - CABIN INDICATIONS


21-63-02 DUCT INDICATION21-63-02A (A) C 2 0 * May be inoperative provided that AUTO temperature control is

operative for the associated zones.

‐OR‐

21-63-02B (B) C 2 0 * May be inoperative provided that COMPT indication and MAN temperature control are operative for the associated zones.

121-61-03 OVHT ALERT C 2


CH22 AUTOMATIC FLIGHT CONTROL SYSTEMPage 22‐1(PIA REV 2.0)

SEP, 2018


22-15-01 ADVISORY DISPLAY UNIT (ADU)

A 1 0 * (O) May be inoperative provided that:

(a) Both mode annunciators (on EADI)

are operative, and(b) Flight director only is used, and(c) ALT SEL is not used, and(d) Operations are limited to two calendar day.

See Operational procedure MOP.22.15-01P Advisory Display Unit (ADU) (O)

22-15-01P ADVISORY DISPLAY UNIT (ADU) (O)

The use of automatic pilot is forbidden.

Flight director is usable with the following restrictions:

● Turn ALT knob fully to the left, to avoid undue alerts.

● NAV , APP, BC , GA flight director modes are

available.

*

22-16-02 TOUCH CONTROL STEERING (TCS)

* (O) One or both may be inoperative.

See Operational procedure MOP.22.16-02P Touch Control Steering (TCS) (O)

22-16-02P TOUCH CONTROL STEERING (TCS) (O) □ Prior to any manual control movement:

● AUTOPILOT ………………………...… DISENGAGE

22-16-03 COUPLING FUNCTION PUSHBUTTON

C 1 0 * (O) May be inoperative provided the Pilot Flying is on the selected side.See Operational procedure MOP.22.16-03P Coupling Function Pushbutton (O)

ITEM

PITCH WHEEL


May be inoperative provided that one TCS is operative.1

STANDARD EQUIPMENT

C22-16-01 0

2C 0

Pushbutton (O)

22-16-03P COUPLING FUNCTION PUSHBUTTON (O)

In flight autopilot remains coupled to the side selected before pushbutton failure.FOR a new dispatch, it will be automatically coupled to the LH side after being energized.

22-16-04 AUTOPILOT QUICK DISCONNECT PUSHBUTTON (Quick Release Control)

22-16-04A (A) C 2 1 * (M) One may be inoperative provided that the Pilot flying side autopilot quick disconnect pushbuttion is operative.

See Maintenance procedure MMP.22.16-04 Autopilot Quick Disconnect (Quick Release Control) (M)

-OR-22-16-04B (B) C 2 0 * One or both may be inoperative provided that autopilot is

considered inoperative and not used. Refer to item 22-18-01 Autopilot Function.

22-18-01 AUTOPILOT FUNCTION22-18-01A * May be inoperative provided that Operations are limited to

one calander day. -OR-

1AETOPS Operations (A) 0


CH22 AUTOMATIC FLIGHT CONTROL SYSTEM‐2(PIA REV 2.0)

SEP, 2018


22-18-01B (B) B 1 0 * May be inoperative provided that ETOPS Operations are notconducted.NoteAny mode which is operative may be uesd.

22-18-02 FLIGHT DIRECTOR FUNCTION

C 1 0 * (O) May be inoperative.

NoteAny mode which is operative may be used.

See Operational procedure MOP.22.18-02P Flight Director Function (O)

22-18-02P FLIGHT DIRECTOR FUNCTION (O)

□ If ASCB bus is lost, in addition to AFCS loss

VOR and ADF bearings display on the opposite side CRT,s are lost when using EFIS reversion mode.

22-18-03 YAW DAMPER FUNCTION22-18-03A (A) A 1 0 * (O) May be inoperative provided that operations are limited to

two flights.NoteThe Autopilot is inoperative, Refer to Item 22-18-01 MOP.22.18-01 Autopilot Function.See Operational procedure MOP.22.18-03P Yaw Damper Function(O)

-OR-

22-18-03B (B) B 1 0 * May be inoperative provided that RCU is operative.

NoteThe Autopilot is inoperative, Refer to Item 22-18-01 MOP.22.18-01 Autopilot Function.

22-18-03P YAW DAMPER FUNCTION □ If RCU is inoperative

STANDARD EQUIPMENT MINIMUM FOR DISPATCH

ITEM

22-18-03P YAW DAMPER FUNCTION (O)

□ If RCU is inoperative

● PF will keep his feet on the pedals to be ready to control rudder.

22-36-01 MODE ANNUNCIATOR (EADI)

C 2 0 * One or both may be inoperative.

22-36-02 AUTOPILOT DISCONNECT AURAL ALERT

22-36-02A (A) B 1 0 * May be inoperative provided that autopilot function is not used.

-OR-

22-36-02B (B) B 1 0 * (O) May be inoperative provided that both AP OFF lights are checked operative prior to each departure.

See Operational procudure MOP.22.36-02P Autopilot Disconnect Aural Alet (O)

22-36-02P AUTOPILOT DISCONNECT AURAL ALERT (O)

□ On Ground, aircraft powered (EXT PWR or HOTEL Mode)

● AVIONICS VENT EXHAUST MODE……...……NORM

● STICK PUSHER pb ……….……………………...OFF

● AIR BLEEDS ……………………………….………OFF

● RADAR ……………………………………………..OFF

● WEIGHT ON WHEELS ( F/O maintenance panel)..…FLT

● AP …………………………………...………..ENGAGE

● YD ……………………………………….………….OFF


CH22 AUTOMATIC FLIGHT CONTROL SYSTEMPage 22‐3(PIA REV 2.0)

SEP, 2018


CHECK ASSOCIATED ALERTS

● WEIGHT ON WHEELS (F/O maintenance panel)

……….………………………………………..…NORM

● STICK PUSHER pb .…………………..…………..ON

● AIR BLEEDS ……………………………..…………ON

● RADAR …………………………….…...……..AS RQD

22-36-03 AP OFF LIGHT22-36-03A ETOPS OPERATIONS (A) A 2 0 *

One or both may be inoperative provided that:

(a) Autopilot function is not used, and

(b) Operations are limited to one flight , and

Refer to Item 22-18-01 MOP.18-01 Autopilot function -OR-22-36-03B (B) B 2 0 * One or both may be inoperative provided that:

(a) ETOPS operations are not conducted, and

(b) Autopilot function is not used.

Refer to Item 22-18-01 MOP.18-01 Autopilot function -OR-22-36-03C (C) C 2 1 * (O) One may be inoperative provided that:


(b) Associated aural alert is checked operative prior

to each departure.

See Operational procedure MOP.22.36-03P AP OFF light (O)

22-36-03P AP OFF LIGHT (O)□ On Ground, aircraft powered (EXT PEWR or Hotel Mode)

● AVIONICS VENT EXHAUST MODE …..…..……NORM

● STICK PUSHER pb OFF


ITEM

● STICK PUSHER pb……….…………………...…...OFF

● AIR BLEEDS …………………………...…...………OFF

● RADAR …………………………...………..………..OFF

● WEIGHT ON WHEELS ( F/O maintenance panel)…….FLT

● AP …………………………………...…….…..ENGAGE

● YD ……………………………………………..…….OFF

CHECK ASSOCIATED ALERTS● WEIGHT ON WHEELS ( F/O maintenance panel)……..FLT

● STICK PUSHER pb…………….………..…….……..ON

● AIR BLEEDS ……………………………....….………ON

● RADAR ……………………………....….………AS RQD

22-36-04 GUIDANCE LIGHT Not Applicable

May be inoperative.22-70-04 INDICATIONS AND CONTROLS ON MAINTENANCE PANELS

C 0-


CH23 COMMUNICATIONSPage 23‐1(PIA REV 2.0 A)

FEB, 2019


23-11-01 HF SYSTEM C 1 0 Any in excess of those required for the intended route may beinoperative.

23-12-01-01 VHF SYSTEM

23-12-01-01A * May be inoperative when flying VFR over routes navigated by visual reference to landmarks provided that:(a) VHF1 is operative, and

(b) The regulations applicable to the aerodrome(s) intended to be used do not require two VHF to be operative.NoteFor all routes, consider the need for ACAS.

-OR-23-12-01-01B (B) B 2 1 * (O) May be inoperative when flying IFR or VFR over routes not

navigated by visual reference to landmarks, provided that:(a) VHF1 is operative, and

(b) Where regulations applicable to the space(s) and procedure(s) to be flown require two VHF to be operative, permission is obtained from the relevant Air Navigation Service Provider(s), prior to each flight.

Note

1) For all routes, consider the need for ACAS.2) (O) to agree with the Air Navigation Service Provider(s) on the rules and procedures applicable in case of total VHF COM failure.

See Operational procedure MOP.23.12-01-01P VHF System (O)

23-12-01-01P VHF SYSTEM (O) May be inoperative when flying IFR, or VFR over routes not navigated by visual reference to landmarks, provided that:

(a) VHF1 is operative, and


12C

STANDARD EQUIPMENT

ITEM

(A)

(b) Where regulations applicable to the space(s) and procedure(s) to be flown require two VHF to be operative, permission is obtained from the relevant Air Navigation Service Provider(s), prior to each flight.

Note

1) For all routes, consider the need for ACAS.

2) (O) to agree with the Air Navigation Service Provider(s) on the rules and procedures applicable in case of total VHF COM failure.

23-12-01-02 VHF System - Frequency Transfer Light

C 2 0 May be inoperative

23-12-01-03 C 2 0 May be inoperative

23-12-01-04 VHF System - Frequency Selector knob

C 2 1

23-12-01-05 VHF System - Frequency Indication

C 2 1

23-22-01 SELCAL NOT APPLICABLE

23-24-01 ACARS NOT APPLICABLE

VHF System ‐ Frequency

Transfer switch

May be inoperative provided that frequency selector knob associated to VHF 1 must be operative.

May be inoperative provided that frequency indication associated to VHF 1 must be operative.


CH23 COMMUNICATIONSPage 23‐2(PIA REV 2.0)

SEP, 2018


STANDARD EQUIPMENT

ITEM


23-24-02 ACARS Printer NOT APPLICABLE

* (O) May be inoperative provided that:

(a) Alternate normal, abnormal and emergency procedures and/or operating restrions are established and used, and(b) Operations are limited to three calendar days or three flights whichever occurs first.

See Operational procedure MOP.23.31-01-01P Passenger Address System - Passenger Confiuration (O)

23-31-01-02 PASSENGER ADDRESS SYSTEM - Cargo Configuration

NOT APPLICABLE

23-31-01P PASSENGER ADDRESS SYSTEM - Passenger Configuration (O)

Magaphone must be serviceable and used by Cabin attendants.

23-44-01-01 INTERPHONE SYSTEM - GROUND CALL HORN

C 1 0 (O) May be inoperative.

See operational procedure MOP.23.44-01-01P Interphone System Ground Call Horn (O)

23-44-01-01P INTERPHONE SYSTEM - GROUND CALL HORN (O)

May be inoperative provided visual signals are used for communication.

23-44-01-02 INTERPHONE SYSTEM - FLIGHT DECK TO FLIGHT DECK

* Refer to Audio Control Panel and Refer to Headset, and Refer to Hand Microphone

23-44-01-03 INTERPHONE SYSTEM

PASSENGER ADDRESS SYSTEM - Passenger Configuration

23-31-01-01 A 1 0

(FLIGHT DECK TO CABIN - CABIN TO FLIGHT DECK ) B 1 0 * (O) May be inoperative provided that:

(a) Passenger Address is operative, and

(b) Alternate normal and abnormal and emergency procedures are established and used, and

(C) Flight deck door automatic locking system (if installed) is verified to operate normally.

See Operational procedure MOP.23.44-01-03P Interphone System (Flight Deck to Cabin - Cabin to Flight Deck) (O)

23-44-01-03P INTERPHONE SYSTEM (FLIGHT DECK TO CABIN - CABIN TO FLIGHT DECK ) (O) May be inoperative provided that:


(b) Flight deck door automatic locking system (if installed) is verified to operate normally.

23-44-01-05 INTERPHONE SYSTEM (FLIGHT CREW TO GROUND - GROUND TO FLIGHT CREW)

C 1 0 * (O) May be inoperative provided that alternate normal and abnormal and emergency procudurees are established and used.

See Operational procedure MOP.23.44-01-05P Interphone System (Flight Crew to Ground - Ground to Flight Crew) (O)



SEP, 2018


STANDARD EQUIPMENT

ITEM


23-44-01-05P INTERPHONE SYSTEM (FLIGHT CREW TO GROUND - GROUND TO FLIGHT CREW) (O)

May be inoperative provided visual signals are used for communication.

23-44-01-06 INTERPHONE SYSTEM - ALERTING SYSTEM

23-44-01-06A (A) C 1 0 * Visual signal may be inoperative on the flight deck.

-OR-

23-44-01-06B (B) C 1 0 * Both visual and aural signals may be inoperative in the cabin provided that Passenger Address is operative from the flight deck.

23-44-01-07 INTERPHONE SYSTEM - HANDSETS

23-44-01-07(A) (A) C 1 0 * Handsets at non-required statins may be inoperative.

-OR-

23-44-01-07B (B) C 1 0 * One handset may be inoperative provided that aiternate procedures are established and used to compensate for the loss of PA and interphone function at the affected station.

See Operational procedure MOP.23.44-01-07P Interphone System - Handsets (O)

23-44-01-07P INTERPHONE SYSTEM - HANDSETS (O)

Cabin handset may be inoperative provided the following procedure is used to compensate for the loss of PA and interphone function.For PA : Cabin crew may use cockpit hand microphone.

For Interphone : Cabin crew shell physically visit cockpit receiving cabin chime.

(O) May be inoperative provided that:


(b) Alternate normal and abnormal and emergency procedures are established and used.

See Operational procedure MOP.23.44-02P Cabin Chime System (Flight Deck to Cabin - Seat Belt and Smoking Signs) (O)

23-44-02P CABIN CHIME SYSTEM (FLIGHT DECK TO CABIN - SEAT BELT AND SMOKING SIGNS) (O)

When necessary, flight crew must directly inform the cabin crew member that SIGNS are ON.

23-50-01 AUDIO CONTROL PANEL C 2 2 * May be inoperative provided that CAPT and F/O panels are operative except VOICE ONLY key which may be inoperative.

One may be inoperative provided that the associated boom set (headset function) is operativefor each crew member on flight deck duty.

One or more may be inoperative provided that the associated boom set is operative for each crew member on flight deck duty.

One may be inoperative provided that the associated hand mike and headset are operative for each crew member on flight deck duty.

23-44-02

23-50-03 HAND MICROPHONE

CABIN CHIME SYSTEM (FLIGHT DECK TO CABIN - SEAT BELT AND SMOKING SIGNS)

23-50-02 HEADSET

23-50-04 BOOM SET 3 -

2 1C

2 0

C

C

C 1 0



SEP, 2018


STANDARD EQUIPMENT

ITEM


*

One or both may be inoperative, provided that:

(a) INT sw / RAD sw on ACP are operative, and

(b) RAD PTT SW on Nose Wheel Steering Control

Handwheel is operative, and

(c) There is no permanent/constant radio transmission.

23-70-01 FLIGHT CREW COMPARTMENT DOOR SURVEILLANCE SYSTEM

NOT APPLICABLE

23-71-01 COCKPIT VOICE RECORDER

23-50-05

23-51-01 PUSH-TO-TALK (PTT) SWITCH ON WHEEL

COCKPIT LOUDSPEAKER

C

C

2 0

1 1

2 1 May be inoperative.


CH24 ELECTRICAL POWERPage 24‐1(PIA REV 2.0)

SEP, 2018


* Inverter # 2 only may be inoperative, provided that:

(a) The flight is conducted in day VMC only, and

(b) AP use is prohibited below 1000 ft AGL, and

(c) Operations are limited to not more than two calendar

days , and(d) TLU manual mode is operative.

24-21-02 AC INV FAULT ALERT * (O) May be inoperative provided that affected inverter is checked operative prior to each departure.

See Operational procedure MOP.24.21-02P AC INV FAULT ALERT (O)

24-21-02P AC INV FAULT ALERT (O) ● After engines start, select BTC ISOL.● Check no amber light or flag on instruments come on.

24-21-03 AC GENERATION BUS TIE RELAY (BTR)

* May be inoperative provided that DC generation Bus Tie Contactor is considered inoperative.Refer to item 24-32-02 DC Generation Bus Tie Contactor (BTC)

24-21-04 AC BUS OFF ALERT C 2 0 * One or both may be inoperative.

24-22-01 B 2 1 * (O) (M) One may be inoperative provided that:

(a) HYD AUX pump is operative, and

(b) Operations are conducted in compliance with applicable

AFM Deviation Guide.

See Operational procedure MOP.24.22-01P ACW Generation (Generator and (or) Related GCU ) (O)

S M i t d MMP 24 22 01 ACW G ti (G t

1

ACW GENERATION (GENERATOR AND (OR) RELATED GCU)

A 2

B

1

C 2 0


0

STANDARD EQUIPMENT

ITEM

24-21-01 AC INVERTER

See Maintenance procedure MMP.24.22-01 ACW Generation (Generator and (or) Related GCU ) (M)

24-22-01P ACW GENERATION (GENERATOR AND (OR) RELATED GCU) (O)

Refer To AFM-DEV.2.2.01.1 Dispatch with One ACW Generator Channel Inoperative

*

24-22-03 B 1 0 * (O) May be inoperative in the ISOL position, provided that:

(a) Both ACW generator channels are operative, and

(b) HYD X FEED pb is operative and is selected ON

before take off, then OFF during cruise and

reselected ON before landing.

See Operational procedure MOP.24.22-03P ACW Generation Bus Tie Contactor (O)

24-22-03P ● Open hydraulic X FEED before take off● Close it after flaps retraction● Open it in approach● Close it after landing

Note

Two-engine taxi is recommended

24-22-02 ACW GEN FAULT ALERT C 2

ACW GENERATION BUS TIE CONTACTOR

ACW GENERATION BUS TIE CONTACTOR (O)

1 One may be inoperative provided that ACW BTC operates normally.



SEP, 2018


MINIMUM FOR DISPATCHSTANDARD EQUIPMENT

ITEM

*

* (O) May be inoperative, provided that:

(a) ETOPS Operations are not conducted, and (b) TRU is checked operative prior to each departure, and(c) Two engines taxi is performed, and(d) Aircraft does not line up until 6 min elapsed after operative generator comes on line, and(e) Operations are limited to two calendar days .See Operational procedure MOP.24.30-01P DC Generation (Generator and (or) Related GCU) (O)

24-30-01P Check of remaining generator feeder integrity:

6 min are necessary to establish the temperature difference

between the feeders if one line is broken.

So aircraft should not line up unit 6 min elapsed after operative

generator comes on line.

Operational test of TRU :During the test, the ACW electrical network must be available

(The AC GPU connacted or ACW generators running)

●Checking are performed only on Main Electrical Panel (left

hand panel)● Switch OFF DC EXTERNAL POWER pb (if selected ON)

● Switch OFF DC GEN 1 pb & DC GEN 2 pb (if selected ON).

On Main Electrical Panal

● Check that the following cau on lights are switched ON:

1) BATTERY ARROWS,

24-22-04 ACW BUS OFF ALERT

DC GENERATION (GENERATOR AND (OR) RELATED GCU)

A 2

0C 2

DC GENERATION (GENERATOR AND (OR) RELATED GCU) (O)

One or both may be inoperative.

124-30-01

2) Both BUS OFF,

3) INVERTER 2 FAULT,

4) Both DC BUS OFF,

5) SHED LEGEND OF DC SVCE/UTLY BUS

● Check that the following systems are supplied:

‐ VHF 1,

‐ FUEL QTY indicator ,

‐ FLAPS POSITION indicator


● Press the TRU pb ; then check that:

‐ The TRU pb is switched ON,

‐ TRU ARROW caution light is switched ON,

‐ The BATTERIES ARROWS caution lights are not illuminated,

‐ The UNDV legend of OVRD/UNDV pb is not illuminated.

● Check that the BATTERY AMMETER shows zero load either if

BAT sw is placed in EMER or MAIN position.

● Check that the following systems are s ll supplied:

‐ VHF 1,

‐ FUEL QTY indicator ,

‐ FLAPS POSITION indicator




SEP, 2018



ITEM

switched off the TRU pb ; then check that:

‐ The TRU pb is not illuminated,

‐ The TRU ARROW caution light is not illuminated,

‐ The BATTERIES ARROWS caution light are switched ON.

24-30-02 DC TRANSFORMER RECTIFIER UNIT (TRU)

B 1 0 * (O) May be inoperative provided that ETOPS Operations are not conducted.

See Operational procudure MOP.24.30-02P DC Transformer Rectifier Unit (TRU) (O)

24-30-02P In case of DUAL DC GEN LOSS the following procedure has to be applied:

● DC GEN 1 AND 2 ………………….OFF THEN ON□ If no generator recovered● LAND ASAP, flight under IMC must be limited to 30 min

● BAT sw ………………………………….……….OVRD

Note

If after a restart , a DC GEN becomes operative, set BAT sw to ON.

● CAPT EHSI …………….…….……………………..OFF

● MAN RATE knob .………………..…………9 O'CLOCK

● CAB PRESS MODE SEL …………..……….….…MAN

● ATC (VHF 1 or HF or HF 2) ………………..…..NOTIFY

● MIN CAB LT ……………………………....…………OFF

Note

NAV lights sw set to ON is necessary to provide IEP illumination.

● STICK PUSHER / SHAKER ………………………..OFF

● STICK PUSHER/SHAKER FAULT procedure ….APPLY

DC TRANSFORMER RECTIFIER UNIT (TRU) (O)

● SIDE WINDOWS ANTI-ICING …………….………..OFF

AVIONICS VENT EXHAUST MODE………………..OVBD

● ADC sw ………………….………....……SET TO ADC 1

● ATC sw ……………….…………...……..SET TO ATC 1

● TLU ………………….….……...… MAN MODE LO SPD

□ WHEN TLU LO SPD illuminates

● TLU………………………………….………..…… AUTO

CAUTION

● Avoid large rudder input if IAS above 180 kt

● MAIN BATTERY CHARGE ( on LH maintenance panel ) ………….…………..…….…….………………… CHECK

● BUS EQUIPMENT LISTS ………..………...… CHECK

□ if STBY UNDV light illuminates

● STBY BUS ...… For approach, OVRD only when necessary

□ Before descent

● PAX INSTRUCTIONS ………..USE PASSENGER ADDRESS

□ At touch down

● IDLE GATE LEVER ………………………….…….PULL

*24-32-01 C 2 One may be inoperative provided that DC Bus Tie Contactor is operative.

1DC GEN FAULT ALERT



SEP, 2018



ITEM

* (O) May be inoperative in the ISOL position provided that:

(a) Both DC generator channels are operative, and (b) DC BUS OFF lights are operative, and

(c) Both inverters are operative.

See Operational procedure MOP.24.32-02P DC Generation Bus Tie Contactor (BTC) (O)

24-32-02P DC GENERATION BUS TIE CONTACTOR (BTC) (O) Note

Two-engine taxi is recommended.

CAUTION

● While aircraft is on ground, if LH DC generator fails, then automatic pressurization digital controller supplied by DC BUS 1 is lost. Therefore, both outflow valves will close, and aircraft will be pressurized. In this case, use manual pressurization to depressurize the aircraft.

*

24-32-04 DC BUS OFF ALERT C 2 0 * One or both may be inoperative.

* May be inoperative.

24-46-01 DC EXTERNAL POWER CONNECTION SYSTEM


24-69-01 DC AMP INDICATOR (Left Hand Panel)

C 1 0 May be inoperative.

24-77-01 INDICATIONS AND C - 0 May be inoperative

24-32-02 DC GENERATION BUS TIE CONTACTOR (BTC)

24-41-01 AC EXTERNAL POWER CONNECTION SYSTEM

May be inoperative in the OFF position.0

C 1 0

24-32-03 DC SVCE & UTLY BUS CONTROL SYSTEM

C 1

0B 1




CH25 EQUIPMENTPage 25‐1(PIA REV 2.0)

SEP, 2018


25-11-01 FLIGHT CREW SEAT - VERTICAL AND RECLINE ADJUSTMENTS

B 2 2 * Vertical and recline adjustments may be inoperative provided that:

(a) Associated seat is secured or locked in a position

acceptable to the flight crew member, and(b) Horizontal adjustment is operative for each flight crew member.

Note

1) A seat with an inoperative or missing seat belt harness

is considered inoperative.

2) If an inoperative armrest will hinder an emergency

evacuation or any other flight duties, it should

be removed.

25-11-02 FLIGHT DECK OBSERVER SEAT

D 1 0 * May be inoperative provided that the seat is correctly stowed.

Note

A seat with an inoperative or missing seat belt or harness is considered inoperative.

25-13-11 SUNVISORS D 2 0 May be inoperative or missing provided there are no visualrestrictions to the flight crew

25-13-15 EYE LOCATOR C 1 0 May be missing

25-13-17 CHART HOLDER C 4 2 May be inoperative or missing provided one is available in each

STANDARD EQUIPMENT

ITEM


25 13 17 CHART HOLDER C 4 2 May be inoperative or missing provided one is available in eachstation.

* (O) (M) One seat or seat assembly may be inoperative, provided that:

(a) Inoperative seat or seat assembly is not occupied,

and

(b) Cabin attendant displaced by inoperative seat occupies

the adjacent cabin attendant seat or the passenger

seat most suitable to perform assigned duties, and

(c) Passenger Address is operative and used to

communicate with displaced cabin attendant, and

(d) One cabin attendant occupies a seat with a

direct access to the communication system, and

(e) Folding type seat is stowed and secured in the

retracted position, and

(f) Where a passenger seat is assigned to the displaced

cabin attendant it is placarded "FOR CABIN

ATTENDANT USE ONLY", and

(g) Alternate normal, abnormal and emerency procedures

are setablished / approved and used for

displaced cabin attendant.

25-21-01 1REQUIRED CABIN ATTENDANT SEAT

B 2



SEP, 2018


STANDARD EQUIPMENT

ITEM


Note

1) A seat with an inoperative or missing seat belt or harness is considered inoperative.

2) This requirement does not preclude use of passenger seats by cabin attendants carried in excess of the required cabin attendant.

See Operational procedure MOP.25.21-01P Required Cabin Attendant Seat (O)

See Maintenance procedure MMP.25.21-01 Required Cabin Attendant Seat (M)

25-21-01P REQUIRED CABIN ATTENDANT SEAT (O) One seat or seat assembly may be inoperative, provided that :

(a) Inoperative seat or seat assembly is not occupied,

and(b) Cabin attendant displaced by inoperative seat occupies

the adjacent cabin attendant seat or the passenger

seat most suitable to perform assigned duties, and

(c) Passenger Address is operative and used to

communicate with displaced cabin attendant, and

(d) One cabin attendant occupies a seat with a

direct access to the communication system, and

(e) Folding type seat is stowed and secured in the


(f) Where a passenger seat is assigned to the displaced(f) Where a passenger seat is assigned to the displaced

cabin attendant it is placarded "FOR CABIN

ATTENDANT USE ONLY".

25-21-02 C 2 0 * (O) (M) One seat or seat assembly may be inoperative provided that:

(a) Inoperative seat or seat assembly is not occupied, and

(b) Alternate normal, abnormal and emergency procedures

are established / approved and used for displaced

cabin attendant, and

(c) Folding type seat is stowed and secured in the


(d) Where a passenger seat is assigned to the displaced

cabin attendant it is placarded : FOR

CABIN ATTENDANT USE ONLY.

Note

A seat with an inoperative or missing seat belt or harness is considered inoperative.

See Operational procedure MOP.25.21-02P Non-Required Cabin Attendant Seat (O)

See Maintenance procedure MMP.25.21-02 Non-Required Cabin Attendant Seat (M)

NON-REQUIRED CABIN ATTENDANT SEAT



SEP, 2018


STANDARD EQUIPMENT

ITEM


25-21-02P One seat assembly may be inoperative provided that:(a) Inoperative seat or seat assembly is not occupied, and

(b) Alternate normal, abnormal and emergency procedures

are established / approved and used for displaced

cabin attendant, and

(c) Folding type seat is stowed and secured in the

retraced position, and

(d) Where a passenger seat is assigned to the displaced

cabin attendant it is placarded : FOR

CABIN ATTENDANT USE ONLY.

25-31-01-01 PASSENGER SEATS D 48 - * (M) One or more may be inoperative provided that :

(a) Inoperative seat does not block an emergency exit, and

(b) Inoperative seat does not restrict any passenger from

the main aircraft aisle, and

(c) Affected seat(s) are blocked and placarded

"DO NOT OCCUPY" , and(d) Any damage is checked not detrimental to adjacent passenger safety.NoteA seat with an inoperative or missing seat belt is

considered inoperative .

See Meintanance procedure MMP.25.31-01-01 Passenger Seats (M)

NON-REQUIRED CABIN ATTENDANT SEAT (O)

25-31-01-02 PASSENGER SEAT - UNDERSEAT BAGGAGE RESTRAINING BARS

NOT APPLICABLE

25-31-01-02P PASSENGER SEAT - UNDERSEAT BAGGAGE RESTRAINING BARS (O)

Brief cabin crew about affected seats position.

25-31-01-03 PASSENGER SEAT - PASSENGER SEATS ARMRESTS

D 48 - (M) May be inoperative or damaged and the affected seat occupied provided that:

(a) The affected armrest does no block an emergency exit, and(b) The affected armrest is not in such position that is

restricts any passengers from access to the aircraft

aisle, and

(c) Any damage is checked not detrimental to adjacent

passenger safety, and

(d) Recline function is checked operative.

See Maintenance procedure MMP.25.31-01-03 Passenger Seats - Passenger Seat Armrests (M)



SEP, 2018


STANDARD EQUIPMENT

ITEM


25-33-01 C 1 0 (O) May be inoperative provided that:

(a) Container is empty, and

(b) Container access is secured to prevent waste

introduction into compartment.

See Operatinal procedure MOP.25.33-01P Galley Waste Compartment Flapper Door (O)

25-33-01P GALLEY WASTE COMPARTMENT FLAPPER DOOR (O)

Cabin attendants to physically eusure that sufficient galley waste receptacles are available to accommodate all waste that may be generateed on a flight.

25-40-01 TORCHES Each Crew member (cockpit and cabin) shall carry a tarch, that is in good working order, having at least two size "D" cells, readily accessible to crew members when seated at their designated stations.

25-41-01 EXTERIOR LAVATORY DOOR ASHTRAY

NOT APPLICABLE

25-41-02 INTERIOR LAVATORY DOOR ASHTRAY

NOT APPLICABLE

25-45-01 PORTABLE PROTECTIVE BREATHING EQUIPMENT

2 2 Part of Emergency Equipment

25-45-21 C 1 0 * May be inoperative provided that:

(a) Toilet waste receptacle is empty, and

(b) T il t d i l d l k d d l d d

GALLEY WASTE COMPARTMENT FLAPPER DOOR

LAVATORY WASTE COMPARTMENT FLAPPER DOOR

(b) Toilet door is closed locked and placarded, INOPERATVE DO NOT ENTER.

Notetiolet may be used and/or inspected by crew members

25-54-23 CARGO RESTRAINT SYSTEM

D 5 0 * May be inoperative or missing provided relevant section of thecargo compartment remains empty.

25-60-01 ELT-EMERGENCY LOCATOR TRANSMITTER

1) SURVIVAL TYPE 1 1 Part of Emergency Equipment

2) IMPACT TYPE 1 1 Part of Emergency Equipment

25-62-01 MEGAPHONES 1 1 Part of Emergency Equipment

25-64-01 CRASH AXES OR CROWBARS

1 1 Part of Emergency Equipment

25-64-02 LIFE JACKETS - - One life jacket for each person on board must be operative.

DOOR


CH26 FIRE PROTECTIONPage 26‐1(PIA REV 0.0)

FEB, 2017


*

One or both may be inoperative.

26-12-03 ENG 2 NAC OVHT C 1 0 * May be inoperative provided that hotel mode operation islimited to a maximum tailwind component of 10 kt.

26-12-04 ENG 1 NAC OVHT NOT APPLICABLE

26-15-01-01 CARGO SMOKE ALERT - PASSENGER CONFIGURATION

C 2 0 * May be inoperative provided that no combustible material is carried in the associated compartment.

26-15-01-02 CARGO SMOKE ALERT - CARGO CONFIGURATION

NOT APPLICABLE

26-15-05 AUX AFT COMPT AGENT DISCH LIGHT

NOT APPLICABLE

26-15-06 AUX AFT CARGO BOTTLE EXTINGUISHER

NOT APPLICABLE

26-17-01-01 TOILET SMOKE DETECTION SYSTEM - PASSENGER CONFIGURATION

C 1 0 *May be inoperative provided that:


3 One may be inoperative provided that the affected loop isselected OFF.

STANDARD EQUIPMENT

*

ITEM

26-12-01 FIRE DETECTION LOOP C 4

026-12-02 FUEL SO LIGHT (INTEGRATED IN CL)

C 2

CONFIGURATION(a) Toilet waste receptacle is empty, and

(b) Toilet door is closed locked and placarded

“INOPERATIVE DO NOT ENTER” .

Note

Toilet may be used and/or inspected only by crew members.

26-17-01-02 TOILET SMOKE DETECTION SYSTEM - CARGO CONFIGURATION

NOT APPLICABLE

.26-18-01 AFT CARGO (CURTAIN -

DOOR) NOT APPLICABLE

26-19-01 AFT SMOKE DETECTION FANS

26-19-01A (A) C 2 1 One may be inoperative provided that the remaining fan is checked operative before each departure.

-OR-

26-19-01B (B) C 2 0 One or both may be inoperative provided that:

(a) Tiolet waste receptacle is empty, and

(b) Toilet door is closed locked and placarded

“INOPERATIVE DO NOT ENTER”,and


CH26 FIRE PROTECTIONPage 26‐2(PIA REV 0.0)

FEB, 2017


MINIMUM FOR DISPATCH STANDARD EQUIPMENT

ITEM

(c) No combustible material is carried in the AFT

cargo compartment.

Note

Toilet may be used and/or inspected only by crew members.

26-21-01 A 4 2 * (M) One or two may be inoperative provided that:

(a) Affected light(s) are not on the same engine fire panel, and

(b) Respective extinguisher bottle pressure is checked

on the direct reading gauge prior to first flight of

each day, and

(c) Operations are limited to two calendar daysSee Maintenance procedure MMP.26.21-01 AGENT DISCH Light (Engine) (M)

26-30-01 HAND FIRE EXTINGUISHER

1) WATER GLYCOL 1 1 Part of Emergency Equipment

2) HALON 1 1 Part of Emergency Equipment

AGENT DISCH LIGHTS (ENGINE)


CH27 FLIGHT CONTROLPage 27‐1(PIA REV 2.0)

SEP, 2018


27-20-01 RUDDER DAMPER C 1 0 * (O) May be inoperative provided that for taxi and take off:

(a) Maximum crosswind is limited to 15 kt, and

(b) Maximum total wind is limited to 30 kt.

See Operational procedure MOP.27.20-01P Rudder Damper (O)

27-20-01P RUDDER DAMPER (O) Pilot Flying and Pilot Non Flying must keep their feet on the pedals during all the taxi phases in order to avoid rudder excessive movements.pilot flying will avoid large pedal movements during take off run and landing and will prefer nose wheel steering use.

27-20-02 RUDDER RELEASABLE CENTERING UNIT (RCU)

27-20-02A (A) A 1 0 * (O) May be inoperative provided that operations are limited to two flights.

See operational procedure MOP.27.20-02P Rudder Releasable Control Unit (O)

-OR-27-20-02B YAW DAMPER FUNCTION

OPERATIVE (B)C 1 0 * May be inoperative provided that yaw damper function is operative and

used throughtout the flight .

27-20-02P □ If the Yaw damper is inoperative

Pilot flying will keep his feet on the pedals to be ready to controlrudder.

27-23-01 TRAVEL LIMITER UNIT (TLU)

27-23-01A (A) C 1 0 * May be inoperative in the low speed position provided that speed islimited to 195 kt.

OR


ITEM

RUDDER RELEASABLE CONTROL UNIT (O)

-OR-

27-23-01B AUTOMATIC MODE (B) C 1 0 * (O) May be inoperative provided that manual mode is operative.

See Operational procedure MOP.27.23-01P Travel limiter Unit (TLU) (O)

27-23-01P TRAVEL LIMITER UNIT (TLU) (O) ▪ During Cockpit preparation

● Select manually HI SPD and check alert is generated

after 25 s : master caution, single chime, FLT CTL on

CAP and TLU FAULT light. Check rudder travel limited.

● Select LO SPD and check alert stops after 15 s and

check rudder travel no longer limited.▪ In Flight

● During an acceleration, select manually HI SPD

when reaching 195 kt.

● During a deceleration, select manually LO SPD

when reaching 190 kt .

27-23-02 TLU FAULT LIGHT C 1 0 * (O) May be inoperative provided that the aural alert and Master Caution and associated FLT CTL alert on CAP are checked operative prior to each flight .

See Operational procedure MOP.27.23-02P TLU FAULT Light (O)



SEP, 2018



ITEM

27-23-02P TLU FAULT LIGHT (O) ▪ During Cockpit preparation

● Select manually HI SPD and check alert is generated

after 25s: master caution, single chime, FLT CTL on CAP.

Check rudder travel limited.

● Select LO SPD and Check alert stops after 15 s

and check rudder travel no longer limited.

▪ In Flight● During an acceleration, select manually HI SPD


● During an deceleration, select manually LO SPD


27-25-01 YAW TRIM POSITION INDICATOR

A 1 0 * May be inoperative provided that:

(a) Yaw trim system operates normally, and

(b) Rudder trim tab is visually verified in neutral position

before each departure, and

(c) Yaw damper and/or auto pilot are not used until the

aircraft has been fully trimmed, and

(d) Operations are limited to three calendar days.

27-32-01 PITCH TRIM ROCKING LEVERS

B 2 1 * One may be inoperative provided that standby pitch trim is operative.

27-32-02 STANDBY PITCH TRIM C 1 0 * May be inoperative provided that both pitch trim rocking levers are operative.

27 35 01 PITCH TRIM POSITION B 1 0 * (O) M b i ti id d th t l t t b i ll h k d27-35-01 PITCH TRIM POSITION INDICATOR

B 1 0 * (O) May be inoperative provided that elevator tabs are visually checkedoperative and positioned neutral prior to departure.

See Operational procedure MOP.27.35-01P Pitch Trim Position Indicator (O)

27-35-01P PITCH TRIM POSITION INDICATOR (O)

● During TAXI Check list run the trim from nose up to nose down: from the trim position where the whooler stops, run trim from the nose down to nose up for 13 s .

27-36-01STICK SHAKER ACTUATOR

27-36-01A Ferry Flight (A) A 2 1 * (O) One may be inoperative for one Ferry Flight provided that MFC modules 1B and 2B are operative.See Operational procedure MOP.27.36-01P Stick Shaker Actuator (O)

27-36-01P STICK SHAKER ACTUATOR (O) ▪ During Preliminary Cockpit Preparation

● TCAS ………..………….……………...….....…....TA ONLY

Limitations▪ During approach



SEP, 2018



ITEM

● MINIMUM MANEUVER OPERATING SPEEDS ……

…………………………..…………INCREASE BY 10kt

● LDG DIST………...………..……..…MULTIPLY BY 1.13

27-36-02 STICK PUSHER ACTUATOR

27-36-02A Ferry Flight (A) A 1 0 * (O) (M) May be inoperative for one Ferry Flight only, provided that MFC modules 1B and 2B are operative.

See Operational procedure MOP.27.36-02P Stick Pusher Actuator (O)

See Maintenance procedure MMP.27.36-02 Stick Pusher Actuator (M)

27-36-02P STICK PUSHER ACTUATOR (O) ▪ During Preliminary Cockpit Preparation

● TCAS……………………………..……………....TA ONLY

● Stick pusher/shaker pb ………………….…………..OFF● CONTROL COLUMN & WHEEL….………………………

……………………………...CHECK FREE MOVEMENT

● STICH PUSHER/SHAKER FAULT LIGHT….…...……….

……………………………………………..…CHECK OFF

Note

If control column is stuck, refer to Maintenance Porcedure (disassembling of strick pusher).Refer to MMP.27.36-02 Stick pusher Actuator (M)

Perform stick Shakers test:

● WARN Selector……..…STICK PUSHER/SHAKER YES

Limitations

▪ During approch

● MINIMUM MANEUVER OPERATING SPEEDS……..

…………………………..………..INCREASE BY 10 kt

LDG DIST………..…………...……….MULTIPLY BY 1.13



27-37-01 PITCH ELEVATORS COUPLING SYSTEM

27-37-01A Ferry Flight (A) A 1 0 * (O) (M) May be inoperative provided that:

(a) Operations are limited to one Ferry Flight, and

(b) Operations are conducted in compliance with applicable


See Operational procedure MOP.27.37-01P Pitch Elevators Coupling System (O)

See Maintenance procedure MMP.27.37-01 Pitch Elevators Coupling System (M)

27-37-01P PITCH ELEVATORS COUPLING SYSTEM (O) Refer to AFM.DEV.02.16.01.1 Flight with Pitch Elevators Disconnected



SEP, 2018



ITEM

27-37-02 ELEVATORS CLUTCH RECONDITIONING DEVICE

27-37-02 A A 1 0 * (O) May be inoperative provided that:

(a) Pitch disconnect alarm comes on steady, and

(b) Operations are limited to one Ferry Flight, and

(c) Operations are conducted in compliance with applicable


See Operational procedure MOP.27.37-02P Elevators Clutch Reconditioning Device (O)

-OR-27-37-02B (B) D 1 0 * (M) May be inoperative provided that:

(a) The elevator clutch reconditioning device is

deactivated, and

(b) Steep Slope Approach is prohibited ( > 4.5° ).

See Maintenance procedure MMP.27.37-02 Elevators Clutch Reconditioning Device (M)

27-37-02P ELEVATORS CLUTCH RECONDITIONING DEVICE (O)

Refer to AFM.Dev.02.16.01.1 Flight with Pitch Elevators Disconnected

27-51-01 A 1 0 * (O) May be inoperative provided that:

(a) Flaps are checked in retracted position, and

(b) Operations are conducted in compliance with

applicable AFM Deviation Guide, and

(c) Operations are limited to two flights .

See Operational procedure MOP.27.51-01P Flaps Control System (O)

27-51-01P FLAPS CONTROL SYSTEM Refer to AFM DEV 02 4 Dispatch With Flaps Retracted

FLAPS CONTROL SYSTEM

Ferry Flight (A)

27 51 01P FLAPS CONTROL SYSTEM (O)

Refer to AFM.DEV.02.4 Dispatch With Flaps Retracted.


(a) Flaps position visual check is made prior to take

off and in flight, and

(b) Operations are limited to two calendar days .

See Operational procedure MOP.27.55-01P Flaps Position indicator (O)

27-55-01P FLAPS POSITION INDICATOR (O) ● Check visually flaps position at each configuration

change.

27-55-02 FLAPS UNLOCK WARNING A 1 0 * May be inoperative provided that flaps control system is considered inoperative:

Refer to Item .27-51-01 MOP.51-01 Flaps Control System.

27-61-01 SPOILER CONTROL SYSTEM

B 1 0 * (O) (M) May be inoperative provided that:

(a) Spoilers are secured in retracted position, and


applicable AFM Deviation Guide.

FLAPS POSITION INDICATOR



SEP, 2018



ITEM

See Operational procedure MOP.27.61-01P Spoiler Control System (O)

See Maintenance procedure MMP.27.61-01 Spoiler Control System (M)

27-61-01P SPOILER CONTROL SYSTEM (O)

Refer to AFM.DEV.02.3 Dispatch With Spoilers Control System Inoperative

27-65-01 SPOILER POSITION INDICATING SYSTEM

C 1 0 * May be inoperative provided that proper functioning of the spoilers ischecked prior to each departure and monitored throughout the flight.

27-70-01-01 GUST LOCK SYSTEM - AILERON

C 1 0 * (O) (M) May be inoperative provided that the tailwind during parking does not exceed 40 Kt.

Note

Propeller brake is not available.

See Operational procedure MOP.27.70-01-01P GUST LOCK System - Aileron (O)

See maintenanace procedure MMP.27.70-01-01 GUST LOCK System - Aileron (M)

27-70-01-01P GUST LOCK SYSTEM - AILERON (O)

Take special care for parking and taxi (wind effects)

27-70-01-02 GUST LOCK SYSTEM - ELEVATOR C 1 0 (O)(M) May be inoperative.

Note

Propeller Brake is not available.

See Operational procedure MOP.27.70‐01‐02P GUST LOCK System ‐

Elevator (O)

See Maintenance procedure MMP.27.70‐01‐02 GUST LOCK System ‐

Elevator (M)

27-70-01-02P GUST LOCK SYSTEM - ELEVATOR (O)

Take special care for parking taxi (wind effects)

27-70-02 AIL LOCK LIGHT A 1 0 May be inoperative provided that operations are limited to two flights.


CH28 FUEL SYSTEMSPage 28‐1(PIA REV 2.0)

SEP, 2018


28-21-01 FEED LO PR LIGHT B 2 1 * (O) One may be inoperative provided that:

(a) Associated alert is processed by the CCAS, and

(b) Associated pump is operative.

See Operational procedure MOP.28.21-01P FEED LO PR Light (O)

28-21-01P FEED LO PR LIGHT (O) During Cockpit Preparation

● RH and LH PUMPS……….......................CHECK ON

● FUEL light on CAP ……….…. CHECK TURN OFF

● AFFECTED SIDE PUMP ………..………SELECT OFF

● C/B FUEL FEED/AFFECTED SIDE ENGINE / CTL &

CAUT…….……………………….……………...…RESET

● FUEL LIGHT ON CAP……...….……………….CHECK

● AFFECTED SIDE PUMP …………….....SELECT ON

● ASSOCIATED ALERTS…………..CHECK TURN OFF

28-21-02 ELECTRICAL FUEL PUMPC 2 1 * (O) (M) One may be inoperative provided that:

(a) ETOPS operations are not conducted,and

(b) Fuel X FEED valve is check operative, and

(c) Associated jet pump (and motive flow valve) is

operative.

See Operational procedure MOP.28.21-02P Electrical Fuel Pump

STANDARD EQUIPMENT

ITEM


p p p(O)

See Maintenance procedure MMP.28.21-02 Electrical Fuel Pump (M)

28-21-02P LimitationsFlight planning must take into account engine failure in the inoperative pump side as X FEED would not be possible. Flight time from suitable alternate must not exceed 45 min with one engine operating (elapse time before reaching maxi fuel unblance).Maximum certified fuel unbalance must never be exceeded 550 kg (1 212 lb).▪ During Preliminary Cockpit Preparation● FUEL X FEED…………...………...….……CHECK OFF

● FUEL PUMP (on affected side)……………………..OFF● FUEL PUMP(on operative side)………………………ON

● ENG FEED LO PR (on operative side)………....CHECK

TURN OFF

● ENG FEED LO PR (on affected side) ….……...CHECK

REMAINS ON

● FUEL X FEED …………………………..…….………ON

● ENG FEED LO PR (on affected side)…….…...CHECK

TURN OFF● FUEL X FEED ………………………………………..OFF

ELECTRICAL FUEL PUMP (O)



SEP, 2018


STANDARD EQUIPMENT

ITEM


● FUEL PUMP (on operative side) ……..………….…OFF

● ENG FEED LO PR 1+2……...........CHECK TURN ON

● FUEL PUMP (on operative side)..………….…AS RQD

□ Before affected engine start

● FUEL X FEED ………………………...………………ON

□ After affected engine start

● FUEL PUMP(on affected side).………..…….……...ON

Note

This enables motive flow valve and then jet pump to be operative.

● FUEL X FEED ………………………………………..OFF

● ENG FEED LO PR…………….CHECK REMAINS OFF

28-21-03 PUMP RUN LIGHT C 2 0 * One or both may be inoperative provided that:


(b) Associated electrical pumps are operative.

28-21-04 C 2 1 * One may be inoperative provided that:

(a) Fuel X FEED valve is operative, and

(b) Associated electrical pump is operative.

28-21-05 C 2 1 One may be inoperative provided that:

(a) ETOPS operations are conducted, and

(b) Fule X FEED valve is operative, and

FEEDER TANK JET PUMP

JET PUMP (AND ASSOCIATED MOTIVE FLOW VALVE)

(c) Both associated electrical pumps are operative, and

(d) Both fuel quantity indication systems are operative,

and

(e) Fuel quantity unusable in each tank is raised from

20 kg / 44 Ib to 130 kg / 287 Ib . Refueling must be

done accordingly.

28-23-01 X FEED VALVE C 1 0 * (O) May be inoperative provided that:


(b) X FEED valve is checked in closed position, and

(c) Both fuel quantity indications are operative.

See Operational procedure MOP.28.23-01P X FEED Valve (O)

28-23-01P X FEED VALVE (O) Limitations

Flight planning must take into account engine failure as X FEED would not be possible.

Flight time from suitable alternate must not exceed 45 min with one engine operating (elapse time before reaching maxi fuel unbalance).

● Dispatch without any asymmetry.Maximum certified fuel unbalance must never be exceeded 550 kg (1 212 lb).



SEP, 2018


STANDARD EQUIPMENT

ITEM


● When selecting RH PUMP ON, check ENG 2 FEED LO PR light turned off and ENG 1 FEED LO PR light remains illuminated.

28-23-02 X FEED FLOW BAR C 1 0 * (O) May be inoperative provided that:

(a) X FEED valve is checked in closed position, and

(b) Both fuel quantity indications are operative.

See Operational procedure MOP.28.23-02P X FEED Flow Bar (O)

28-23-02P X FEED FLOW BAR (O) ● When selecting RH PUMP ON, check ENG 2 FEED LO PR light extinguishes and ENG 1 FEED LO PR light remains illuminated.

28-23-03 FUEL X FEED MEMO LIGHT


28-25-01-01 REFUELING CONTROL PANAL

C 1 0 * (M) May be inoperative provided that gravity refueling is performed.See Maintenance procedure MMP.28.25-01-01 Refueling control Panel - Refueling control Panel (M)

28-25-01-02 REFUELING CONTROL PANAL - FUEL PRESELECTOR

C 1 0 * (M) May be inoperative provided that manual refueling is performed.

See Maintenance procedure MMP.28.25-01-02 Refueling ControlSee Maintenance procedure MMP.28.25 01 02 Refueling Control Panal - Fuel Preselector (M)

28-25-02 Pressure Refueling Cap A 1 0 (M) May be inoperative provided that:

(a) Refuel valves are confirmed closed, and

(b) There is no leakage from the refuel coupling, and

(c) Operations are limited to three calender days .

See Maintenance procedure MMP.28.25-02 Pressure Refueling Cap (M)

28-26-01 LP VALVE POSITION INDICATOR

C 2 0 * One or both may be inoperative.

28-41-01 C 1 0 * (O) May be inoperative

Note

OAT has to be used.

See Operational procedure MOP.28.41-01P Tank Temperature Indication (O)

28-41-01P NoteRefer to LIM.5.70.4.2 Fuel Temperature , for temperature limitation.

TANK TEMPERATURE INDICATION

TANK TEMPERATURE INDICATION (O)


CH28 FUEL SYSTEMSPage 28‐4(PIA REV 2.0A)

FEB, 2019


STANDARD EQUIPMENT

ITEM


28-42-01 FUEL QTY INDICATION C 2 1 * (O) (M) One may be inoperative provided that:

(a) ETOPS Operations are not conducted, and

(b) The associated FU indication is operative, and

(c) The opposite side Fuel LO LVL alert is checked operative, and(d) The use of preselected quantity is prohibited

during refueling, and(e) The associated tank fuel quantity is checked using

manual (magnetic) indicators after each refueling.

Note1) In addition to the cockpit FUEL QTY INDICATION, the preselected quantity and the repeated fuel quantity indications on the refueling panel must be placarded inoperative2) if the Fuel LO LVL alert is triggered on affected side due to Fuel Quantity Indication inoperative: Refer to MOP.28.42-03 Fuel LO LVL Alert.

See Operatinal procudure MOP.28.42-01P Fuel QTY Indication (O)

See Maintenance procudure MMP.28.42-01 Fuel QTY Indication (M)

28-42-01P FUEL QTY INDICATION (O)

● In case of suspected fuel leak or fuel unbalanec (an excessive aileron trim indication may help for detection), M i t i X FEED l CLOSEDMaintain X FEED valve CLOSED.

● Monitor fuel consumption using Fuel Flow/Fuel Used indicator.

28-42-02 FUEL LO LVL LIGHT C 2 0 * One or both may be inoperative provided that:

(a) ETOPS operations are not conducted, and(b) Associated alert is processed by CCAS .

(O) (M) One may be inoperative provided that:(a) ETOPS operations are not conducted, and(b) The associated FU indication is operative, and(c) The opposite side Fuel LO LVL alert is checked operative, and(d) The opposite side Fuel Quantity Indication is operative, and(e) The associated tank fuel quantity is checked using

manual (magnetic) indicators after each refueling.

Note

if fuel Quantity Indication on affected side is inoperative: Refer to Item 28-42-01 MOP.28.42-01 Fuel QTY Indication

See Operational procedure MOP.28.42-03P Fuel LO LVL Alert (O)

See Maintenance procedure MMP.28.42-03 Fuel LO LVL Alert (M)

28-42-03 FUEL LO LVL ALERT B 2 1



SEP, 2017


STANDARD EQUIPMENT

ITEM


28-42-03P FUEL LO LVL ALERT (O) ● X FEED valve must be maintained closed in all cases.

● In case of Fuel LO LVL on opposite side, LAND ASAP.

● Monitor fuel consumption using Fuel Flow/Fuel Used

indicator.

28-42-04 FUEL QTY TEST SYSTEM C 1 0 * May be inoperative.

* All may be inoperative.4 028-43-01 MANUAL (MAGNETIC) INDICATORS

C


CH29 HYDRAULIC SYSTEMPage 29‐1(PIA REV 2.0)

SEP, 2018


29-11-01 MAIN HYD PUMP C 2 1 * (O) (M) One may be inoperative provided that:

(a) X FEED valve is open, and

(b) Both ACW GEN are operative, and

(c) ACW BTC is operative, and(d) DC AUX pump operates normally, and(e) Hydraulic fluid QTY is checked prior to each

departure, and(f) Aircraft is not operated on narrow runways (width

< 30 m (98 ft))

See Operatinal procedure MOP.29.11-01P Main Hyd Pump (O)

See Maintenance procuedure MMP.29.11-01 Main HYD Pump (M)

29-11-01P MAIN HYD PUMP (O) Two-engine taxi is recommended.

29-11-02 DC AUX PUMP C 1 0 * May be inoperative provided that aircraft is not operated on narrow runways (width < 30 m (98ft))

29-21-01 X FEED VALVE C 1 0 * (M) May be inoperative provided that

(a) X FEED Valve is in the closed position.

(b) Hydraulic fluid QTY is checked prior to each departure

S M i d d MMP 29 11 01 M i HYD P (M)


ITEM

See Manienance procedude MMP.29.11-01 Main HYD Pump (M)

29-31-01 LO LVL ALERT C 2 1 * (O) (M) One may be inoperative proviede that:

(a) Hydraulic fluid QTY is checked prior to each

departure, and

(b) X FEED valve is not used in flight.

See Operatinal procedure MOP.29.31-01P LO LVL Alert (O)

See Maintenance procedure MMP.29.11-01 Main HYD Pump (M)

29-31-01P LO PR ALERT (O) ● Monitor associated HYD SYS pressure indication throughout the flight.

29-32-01-01 LO PR ALERT - MAIN HYD PUMP

C 2 1 * (O) One may be inoperative provided that the associated HYD SYS pressure indication is operative.

See Operatinal procedure MOP.29.32-01-01P LO PR Alert - Main HYD Pump (O)

29-32-01-01P LO PR ALERT - MAIN HYD PUMP (O)

● Monitor associated HYD SYS pressure indication throughout the flight.

29-32-01-02 LO PR ALERT - AUX HYD PUMP

C 1 0 * May be inoperative provided that the BLUE HYD SYS pressure indication is operative.

29-32-02-01 PRESSURE INDICATION - HYD SYS INDICATION

C 2 0 * One or both may be inoperative provided that the associated LO PR alert is operative.


CH29 HYDRAULIC SYSTEMPage 29‐2(PIA REV 2.0)

SEP, 2018



ITEM

29-32-02-02 PRESSURE INDICATION - BRAKE ACCU INDICATION

C 1 0 * May be inoperative provided that the brake accumulator pressure is checked on the hydraulic bay indication prior to each flight.

29-32-03 ACCUMULATORS PRESSURE INDICATOR (HYDRAULIC BAY)

C 3 0 All may be inoperative.

29-33-01 MAIN HYDRAULIC PUMP OVHT ALERT

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

(a) The associated pump is considered inoperative, and

(b) The other main hydraulic pump and associted

OVHT alert is operative

Refer to item 29-11-01 MAIN HYD Pump

See Operational MOP.29.33-01P Main Hydraulic Pump OVHT Alert (O)

29-33-01P MAIN HYDRAULIC PUMP OVHT ALERT (O)

During the cockpit preparation, the associated main hydraulic pump is set to OFF.

29-33-02 DC AUX PUMP OVHT ALERT

C 1 0 * (O) May be inoperative provided that the pump is considered inoperative.Refer to item 29- 11-02DC AUX Pume

See Operational procedure MOP.29.33-02P DC AUX Pump OVHT Alert (O)

29-33-02P DC AUX PUMP OVHT ALERT (O)

The DC AUX pump is set to OFF.


CH30 ICE AND RAIN PROTECTIONPage 30‐1(PIA REV 2.0)

SEP, 2018


30-11-01 PNEUMATIC DE-ICING - DE-ICE PRESSURE REGULATING AND SHUT OFF VALVE C 2 1 * One may be inoperative in closed position provided that:


(b) Aircraft is not operated into known or forecast icing conditions

30-11-02 PNEUMATIC DE-ICING - AIRFRAME DE-ICING BOOTS SYSTEM B 1 0 * May be inoperative provided that:


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

30-11-03-01 PNEUMATIC DE-ICING - ENG-AIRFRAME MODE SELECTOR - (FAST-SLOW) MODE

30-11-03-01A (A) C 1 0 * May be inoperative provided that MODE SEL AUTO is operative.

-OR-

30-11-03-01B (B) C 1 0 * May be inoperative provided that aircraft is not operated into known or forecast icing conditions when mode FAST is inoperative.

30-11-03-02 PNEUMATIC DE-ICING - ENG-AIRFRAME MODE SELECTOR - OVRD MODE


30 11 04 PNEUMATIC DE ICING B 1 0 * (O) M b i ti id d th t AIR FRAME FAULT li ht i


ITEM

30-11-04 PNEUMATIC DE-ICING - AFR AIR BLEED FAULT LIGHT

B 1 0 * (O) May be inoperative provided that AIR FRAME FAULT light is checked operative.

See Operational procedure MOP.30.11-04P Pneumatic de-icnig - AFR AIR BLEED FAULT Light (O)

30-11-04P PNEUMATIC DE-ICING - AFR AIR BLEED FAULT LIGHT (O)

With Bleed Supply :

● AFR AIR BLEED………….…………………...…CHECK ON

● DE-ICING AIR FREAM…………………………………….ON

● AIRFRAME FAULT light…………....CHECK TURNED OFF

● AFR AIR BLEED……………………………………….…OFF

● AIRFRAME FAULT light……………..CHECK TURNED ON

● AFR AIR BLEED………………………………………..…ON

30-11-05 PNEUMATIC DE-ICING - DE ICING AIRFRAME MEMO LIGHT


30-11-06 PNEUMATIC DE-ICING - MODE SEL AUTO

C 1 0 * May be inoperative provided that MAN mode is operative.

30-21-01 PNEUMATIC DE-ICING - ENGINE DE ICING (OR ANTI ICING) BOOTS SYSTEM C 2 1 * One may be inoperative, provided that:

(a) ETOPS Operation are not conducted, and(b) Aircraft is not operated into known or forecast icing conditions.



SEP, 2018



ITEM

30-21-02 B 3 0 * All may be inoperative provided that:


(b) Associated device is considered inoperative, and

(c) Aircraft is not operated into known or forecast

icing conditions.

30-30-01 PROBE HEATING - PITOT B 3 2 * One may be inoperative provided that:


(b) Aircraft is not operated into known or forecast icing

conditions.

30-30-02 PROBE HEATING - STATIC B 6 5 * One may inoperative provided that both STBY are operative.

30-31-01 PROBE HEATING - TAT B 2 1 * (O) May be inoperative provided ADC associated with valid TAT is selected.

See Operational procedure MOP.30.31-01P Probe heating - TAT (O)

30-31-02P PROBE HEATING - TAT (O) ● Select ADC associated to valid TAT probe.

TAT heating loss may affect FDAU Torque computation.

● Crosscheck with tables.

30-31-02 PROBE HEATING - ALPHA B 2 1 * One may be inoperative provided that aircraft is not operated into known or forecast icing conditions.

30-31-03 PROBE HEATING - ALERT B 10 6 * (M) May be inoperative provided that:

(a) Two pitot alerts are operative, and

(b) Two static alerts are operative, and

(c) One TAT alert is operative, and

PNEUMATIC DE-ICING - ENG-AIRFRAME DE ICING BOOTS FAULT ALERT

(d) One alpha alert is operative, and

(e) Heating system associated to failed alerts are

checked operative prior to each departure.

See Maintenance procedure MMP.30.31-03 Alert (M)

30-53-01 HORN ANTI-ICING SYSTEM A 2 1 * May be inoperative provided that:


(b) Aircraft is not operated into known or forecast

icing conditions, and (c) Operations are limited to three calendar days.

30-53-02 HORN ANTI-ICING FAULT ALERT

A 2 1 * One may be inoperative provided that associated devices must be considered inoperative: Refer to Item 30-53-01 MOP.30.53-01 Horn Anti-icing System

30-60-01 WINDOW HEATING - WINDSHIELD

30-60-01A (A) C 2 1 * One may be inoperative provided that aircraft is not operated into known or forecast icing conditions.

-OR-30-60-01B (B) C 2 1 * One may be inoperative provided that both side windows heating

are operative.

-OR-30-60-01C (C) C 2 0 * May be inoperative provided that:

(a) Both packs are operative, and


icing conditions.(c) Both side windows heating are operative.



SEP, 2018



ITEM

30-60-02 WINDOW HEATING - SIDE WINDOW

30-60-02A (A) C 2 1 * RH side window heating may be inoperative.

-OR-30-60-02B (B) C 2 1 * LH side window heating may be inoperative provided that flight

is not conducted into known or forecast icing conditions. -OR-30-60-02C (C) C 2 0 * Both may be inoperative provided that:

(a) Flight is not conducted into known or forecast icing conditions, and(b) Both windshields heating are operative, and(c) Both ACW GEN are operative.

30-60-03 WINDOW HEATING - SIDE WINDOWS FAULT LIGHT

C 1 0 * (O) May be inoperative provided that associated alert is checked operative.See Operational procedure MOP.30.60-3P Window Heating - SideWindows Fault Light (O)

-OR-C 1 0 * May be inoperative provided that both side window heating are

considered inoperative (Refer to Item 30-60-02MOP.30.60-02 Window Heating - Side Window)

30-60-03P WINDOW HEATING - SIDE WINDOWS FAULT LIGHT (O)

● SIDE WINDOWS pb…………...…….………..…….ON

● C/B ANT/DE ICING/WSHLD HTG R IND L/SIDE

WDO/L CTL…………….……………………….…..PULL

● MC light + SC + ANT ICING light on CAP….....CHECK

● C/B ANT/DE ICING/WSHLD HTG R IND L/SIDE

WDO/L CTL..……………………….…………….PRESS

● SIDE WINDOWS pb…………………………...…....OFF

30-60-04 WINDOW HEATING - WINDSHIELD HTG FAULT LIGHT

30-60-04A (A) C 2 1 * (O) One may be inoperative provided that respective heating system is checked operative prior to each departure.

See Operational procudure MOP.30.60-04P Window hearting - WINDSHIELD HTG FAULT LIGHT (O)

-OR-30-60-04B (B) C 2 1 * One may be inoperative provided that associated windshield

heating is considered inoperative.Refer to Item 30-60-01MOP.30.60-01 Window heating - windshield

30-60-04P WINDOW HEATING - WINDSHIED HTG FAULT LIGHT (O)

● Check by hand the correct functioning of the respective heating system.

30-61-01 C 2 0 * One or both may be inoperative provided that:


(b) Aircraft is not operated into know or forecast icing

conditions

30-61-02 PROPELLER ANTI ICING ON LIGHT

C 2 0 * (O) May be inoperative provided that FAULT alert is operative.

See Operational procedure MOP.30.61-02P Propeller Anti-icing ON Light (O)

PROPELLER ANTI-ICING SYSTEM



SEP, 2018



ITEM

30-61-02P PROPELLER ANTI-ICING ON LIGHT (O)

While engines are running with CL at AUTO

● ACW genera on ……………………………………………………OFF

● PROP ANTI‐ICING affected ………………………….……….ON

● FAULT alert……………………………..……CHECK GENERATED

● PROP ANTI‐ICING affected ……..…….……………AS RQRD

● ACW genera on……………………………………………………ON

30-61-03 PROPELLER ANTI-ICING - PROPELLER MODE SELECTOR

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

30-61-04 PROPELLER ANTI-ICING - PROPELLER FAULT ALERT

C 2 0 * One or both may be inoperative provided that aircraft is not operated into known or forecast icing conditions.

30-61-05 PROPELLER ANTI-ICING - PROPELLER MODE SEL AUTO

C 1 0 * May be inoperative provided that MAN MODE is operative.

30-65-01-01 WINDSHIELDS WIPERS - WIPERS

C 2 0 * One or both may be inoperative provided that:

(a) No precipitation is forecasted during a period from

one hour before until one hour after the estimated time of

departure and arrival at the take-off and

destination aerodromes.

(b) Affected wipers are not part of the equipment required for the intended operations.

Note1 : Takeoff and destination aerodromes include any take-off and destination alternate aerodromes required by the operational rules.

2: Check Flight Manual for minimum required equipment for CAT II approaches and low visibility take off.

30-65-01-02 WINDSHIELDS WIPERS - HIGH SPEED FUNCTION (FAST)

30-65-01-02A (A) C 2 0 * One or both may be inoperative provided that the associated lowspeed function is operative.

30-65-01-03 WINDSHIELDS WIPERS - LOW SPEED FUNCTION (SLOW)

30-65-01-03A (A) C 2 0 * One or both may be inoperative provided that the associated highspeed function is operative.



30-80-01 ICE DETECTION SYSTEM B 1 0 * (M) May be inoperative provided that:(a) The aircraft is not operated into known or forecast icing conditions, and(b) The ice detection system is deactivated.

See Maintenance procedure MMP.30.80-01 Ice Detection System (M)

30-80-03 ICE EVIDENCE PROBE IEP B 1 1 NO GONoteRefer to Item 33-49-02MOP.33.49-02 IEP Light

30-80-04 ICING AOA LIGHT C 1 0 * May be inoperative provided that aircraft is not operated into known or forecast icing conditions.


CH31 INSTRUMENTSPage 31‐1(PIA REV 2.0)

SEP, 2018


31-21-01 CLOCK C 2 0 * May be inoperative provided that an accurate timepiece is operative on the flight deck indicating the time in hours, minutes and seconds.

NoteOn the basis that the required timepiece(s) does not need to be approved, an accurate pilot's wristwatch that indicates hours, minutes and seconds would be acceptable.

31-31-01-01 MPC - APM FAULT ONLY C 1 0 * (O) May be inoperative.

See Operation procedure MOP.31.31-01-01P MPC - APM FAULT ONLY (O)

31-31-01-01P MPC - APM FAULT ONLY (O) ● APM ………………………………………………….OFF

● ICE CONDITION : MONITOR

● IAS & V/S : MONITOR

31-31-01-02

* Refer to Item 31-32-01 Digital Flight Data Recorder - DFDR

No parameter acquisition.

31‐31‐01‐03 MPC ‐ DMU ‐ Maintenance

function


31‐31‐01‐04 MPC ‐ AFDAU ‐ ‐ * Refer to item 31-32-01 digital flight data recoder-DFDRNote

No parameter acquisition.

31‐31‐02 FDAU * Refer to item 31-32-01 Dgital Flight Data Rcorder - DFDR and


ITEM

MPC - DMU - FLIGHT RECORDING FUNCTIONS (DATE, TIME AND FLIGHT NUMBER)

g gRefer to item 77-13-01 TQ Indicator NoteNo parameter acquisition.

31-32-01 DIGITAL FLIGHT DATA RECORDER - DFDR

1 1

31-32-02 AIDS NOT APPLICABLE

31-32-03 QAR NOT APPLICABLE

31-48-01-01 A 1 0 * (O) May be inoperative provided that:

(a) OVBD valve manual mode is operative, and

(b) RH pack is operative, and

(c) AC BTC is operative, and

(d) INV 2 is operative, and

(e) Following warnings are tested prior to the first

flight of the day :

- Flaps UNLOCK

- Stick pusher inhibition

(f) Aircraft is not operated into known or forecast

icing conditions if de-icing OVRD system is

inoperative, and

MULTI FUNCTION COMPUTER (MFC) MODULE 1A



SEP, 2018



ITEM

(g) MFC 1B, MFC 2A,and MFC 2B are operative, and

(h) Operations are limited to two calendar days.

See Operational procedure MOP.31.48-01-01P Multi Function Computer (MFC) Module 1A (O)

31-48-01-01P □ During cockpit preparation● FWD COMPT door must be visually checked

locked closed prior to each departure.

● FWD cargo door must be manually activated.

● DESELECT DC SVCE / UTLY BUS in case of LH single DC GEN operation on ground.

● PULL C/B INV 2 and check AC STBY BUS is supplied.NoteCAPT ADC connected instruments operate normally - F/O ADCinstruments are lost.● PUSH IN C/B INV 2 .Following warnings have to be tested prior to the first flight ofthe day:● Provide blue HYD PRESS.STICK PUSHER INHIBITION TEST● Seelect HORNS anti-icing ON then OFF.● Disegage GUST LOCK.● On LH maintenance panel , set WARN rotary selector to STICK PUSHER TEST 2● Depress and maintain PTT .● On LH maintenance panel , CHECK CH 2 light is illuminated.● Check RH stick Shaker and stall warning are activated.● Check STICK PUSHER/SHAKER FAULT light is illuminated after 5 s.

MULTI FUNCTION COMPUTER (MFC) MODULE 1A (O)

● Check STICK PUSHER is not activated after 10 s.● Set WARN rotary selector to NORM FLT.● Clear ICING AOA light.● GUST LOCK engaged.FLAPS UNLOCK TEST● SET FLAPS 15.● On RH maintenance panel , depress and maintain FLAPS UNLOCK PTT.● Check warning is activated when the flaps position passes over the selected position minus 3 ᴼ on the Flaps Position indicator.● SET FLAPS AS RQD .□ When one engine running

● Select de icing OVRD mode and visually check boots

inflation.

● Select de icing OVRD mode to NORM position.

● Refer to module equipment list and note missing

functions.



SEP, 2018



ITEM


(a) Flight level is limited to FL 170 and

(b) OVBD valve manual mode is operative, and

(c) LH pack is operative, and

(d) AC BTC is operative, and

(e) INV 1 is operative, and

(f) Following warnings are tested prior to the first

flight of the day :

- Flaps UNLOCK

- Stick pusher inhibition

(g) Aircraft is not operated into known or forecast

icing conditions if de icing OVRD system is

inoperative, and

(h) MFC 1A, MFC 1B, and MFC 2B are operative, and

(i) Operations are limited to two calendar days.

See Operational procedure MOP.31.48-01-02P Multi Fuction Computer (MFC) Module 2A (O)

31-48-01-02P □ During cockpit preparation

● OVBD VALVE…………………………..FULL OPEN

● Pilot emergency hatch must be visually checked

locked closed prior to each departure.

● As extract fan is lost, avoid leaving avionicse selected

ON for a long period of time.

● DESELECT DC SVCE / UTLY BUS in case of

RH single DC GEN operation on ground.

● PULL C/B INV 1 and check AC STBY BUS is supplied.

Note

MULTI FUNCTION COMPUTER (MFC) MODULE 2A

MULTI FUNCTION COMPUTER (MFC) MODULE 2A (O)

Note

CAPT ADC connected instruments operate normally - F/O ADCinstruments are lost.● PUSH IN C/B INV 1 .

Following warnings have to be tested prior to the first flight ofthe day:● Provide blue HYD PRESS.

STICK PUSHER INHIBITION TEST

● Seelect HORNS anti-icing ON then OFF.

● Disengage GUST LOCK.

● On LH maintenance panel , set WARN rotary

selector to STICK PUSHER TEST 1

● Depress and maintain PTT .

● On LH maintenance panel , CHECK CH 1 light

is illuminated.

● Check LH stick shaker and stall warning are activated.

● Check STICK PUSHER/SHAKER FAULT light is

illuminated after 5 s .

● Check STICK PUSHER is not activated after 10 s .

● Set WARN rotary selector to NORM FLT.

● Clear ICING AOA light.

● GUST LOCK engaged.



SEP, 2018



ITEM

FLAPS UNLOCK TEST

● SET FLAPS 15.

● On RH maintenanace panel , depress and maintain

FLAPS UNLOCK PTT. ● Check warning is activated when the flaps position

passes over the selected position minus 3 ᴼ on the

flaps position indicator.

● SET FLAPS AS RQD.

□ When one engine running

● Restore DC SVCE / UTLY BUS.

● Select de icing OVRD mode and visually check boots

inflation.

● Select de icing OVRD mode to NORM position.


functions.

● Amend normal in-flight check list as follows:

□ A er take off

● IDLE GATE POSITION ……..CHECK PUSHED IN

● OVBD VALVE ……….…...………….……….AUTO

● EXHUAST MODE……..………..…….………OVBD

□ A er landing

● IDLE GATE POSITION ….…CHECK PULLED OUT

● OVBD VALVE ……..……..……..……..FULL OPEN

● EXHAUST MODE……………..…..……….…NORM


(a) Acraft is not operative on narrow runways

(width < 30 m (98ft)) and

MULTI FUNCTION COMPUTER (MFC) MODULES 1B

(width < 30 m (98ft)), and (b) OVBD valve manual mode is operative, and

(c) RH pack is operative, and


(e) All brakes are operative, and

(f) All alerts and warnings are operative, and

(g) Landing gear is left down for 1 min after take off

except in case of emergency, and

(h) A minimum turn around of 20 min must be observed, and

(i) Aircraft is not operated into known or forecast

icing conditions if de icing OVRD system is inoperative, and

(j) MFC 1A, MFC 2A, and MFC 2B are operative, and

(k) Operations are limited to two calender days.

See Operation procedure MOP.31.48-01-03P Multi Function Computer (MFC) Module 1B (O)

31-48-01-03P □ During cockpit preparation● OVBD VALVE ………………………...FULL OPEN● PACK 1 ………………………………………...OFF● PULL C/B INV 1 and check AC STBY BUS is supplied.

MULTI FUNCTION COMPUTER (MFC) MODULES 1B (O)



SEP, 2018



ITEM

Note

CAPT ADC connected instaruments operate normally - F/O ADC instrument are lost.● PUSH IN C/B INV 1 .


● Select de-icing OVRD mode and visually check boots

infiation.● Select de-icing OVRD mode to NORM position.

● Refer to module equipment list and note missing functions.● Amend normal in-flight check list as follows:

□ Before take off

● PACK 2 ………………………………………..OFF

□ After take off

Note

Landing gear must be left down for 1 minute after take off

for cooling except in case of emergency.

● PACKS ………………………...…….....…...……ON

● OVBD VALVE…………………...…….FULL CLOSE

□ After landing

● OVBD VALVE ……………………..……FULL OPEN

● PACK 1 ……………..…………...…………..…...OFF

CAUTION

● Before opening any door, PACK 1 and 2 must be selected OFF and cockpit communication hatch must be opened.Note

In case of in-flight failure of MFC module 2B, no aural alert will be generated.Therefore the crew must moniter MC lightTherefore, the crew must moniter MC light.


(a) Aircraft is not operated on narrow runways

(width < 30 m (98ft)) ,and

(b) OVBD valve manual mode is operative, and

(c) LH pack is operative, and


(e) All brakes are operative, and

(f) All alerts and warnings are operative, and

(g) Landing gear is left down for 1 minute after

take off except in case of emergency, and

(h) A minimum turn around of 20 minutes must be

observed, and

(i) Hotel mode is not used, and

(j) Aircraft is not operated into known or forecast

icing conditions if de icing OVRD system is

inoperative, and

(k) MFC 1A, MFC 1B, and MFC 2A are operative, and

(l) Operations are limited to two calendar days.

See Operational procedure MOP.31.48-01-04P Multi Function Computer (MFC) Module 2B (O)

MULTI FUNCTION COMPUTER (MFC) MODULE 2B



SEP, 2018



ITEM

31-48-01-04P □ During cockpit preparation

● OVBD VALVE ……………...………...…….FULL OPEN

● PACK 2 ………………………..…………..…OFF


● Select de-icing OVRD mode and visually check

boots inflation.

● Select de-icing OVRD mode to NORM position.


functions.

● Amend normal in-flight check list as follows:

□ Before take off

● PACK 1 …………………………………….OFF

□ After take off

● PACKS …….…………..…….………………ON

● OVBD VALVE …....………....…FULL CLOSE

□ After landing

● OVBD VALVE …………….………FULL OPEN

● PACK 2………………………………………OFF

CAUTION● Before opening any door, PACK 1 and 2 must be selected OFF and cockpit communication hatch must be opened.Note

In case of in-flight failure of MFC module 1B, no aural alert will be generated. Therefore, the crew must monitor MC light.

31-48-06 MFC MODULE FAULT LIGHT A 4 3 * One may be inoperative provided that associated module is considered inoperative. Refer to item 31-48-01-01 MOP.31.48-01-

MULTI FUNCTION COMPUTER (MFC) MODULE 2B (O)

01 Multi Function Computer (MFC) Module 1A. Refer to Item 31-48-01-02 MOP.31.48-01-02 Multi Function Computer (MFC) Module 2A Refer to Item 31-48-01-03 MOP.31.48-01-03 Multi Function Computer (MFC) Module 1B Refer to Item 31-48-01-04 MOP.31.48-01-04 Multi Function Computer (MFC) Module 2B

31-53-02 C 2 1 * (O) One may be inoperative provided that:(a) The aural warnings are operative, and(b) All warning lights on the CAP panel are operative.

See Operational procedure MOP.31.53-02P Master Warning (MW) Light and Associated Cancel Function (O)

31-53-02P MASTER WARNING (MW) LIGHT AND ASSOCIATED CANCEL FUNCTION (O)

The crew must closely monitor the Crew Alerting panel.

31-53-03 C 2 1 * (O) One may be inoperative provided that:

(a) The aural caution is operative, and

(b) All caution lights on the CAP panel are operative.

See Operational procedure MOP.31.53-03P Master Caution (MC) Light and Associated Cancel Function (O)

MASTER WARNING (MW) LIGHT AND ASSOCIATED CANCEL FUNCTION

MASTER CAUTION (MC) LIGHT AND ASSOCIATED CANCEL FUNCTION



SEP, 2018



ITEM

31-53-03P MASTER CAUTION (MC) LIGHT AND ASSOCIATED CANCEL FUNCTION (O)

The crew must closely monitor the Crew Alerting panel.

31-53-04-01 CREW ALERTING PANEL CAP - WARNING LIGHT

31-53-04-01A (A) A - - * (a) FLAPS UNLOCK light may be inoperative

provided that flaps are considered inoperative.

Refer to item 27-51-01 Flaps Control System

(b) EXCESS CAB ALT light may be inoperative provided

that flight level is limited to FL 100.

(c) Operations are limited to three calendar days.

31-53-04-02 CREW ALERTING PANEL CAP - OTHER LIGHTS OR FUNCTIONS

A - 0 * May be inoperative provided that operations are limited to three calendar days.

31-53-05 EMER AUDIO CANCEL C 1 0 * May be inoperative.

31-53-06 TO CONFIG TEST B 1 0 * May be inoperative.

31-60-05-02 SINGLE MCDU Refer to Global Positioning System

31-60-05-03 SINGLE MCDU WITH MPC C 1 0 * Refer to item 31-32-01 Digital Flight Data Recorder - DFDR

Note

Flight recording functions (Date, time and flight number) are not available.

31-60-05-04 SINGLE MCDU WITH MPC AND FDFP

C 1 0 * Refer to Item 34-58-01 Global Postitioning System

Note

Flight recording functions (Data, time and flight number) are operative on FDEP.

31-60-05-05 DUAL MCDU NOT APPLICABLE




CH32 LANDING GEARPage 32‐1(PIA REV 2.0)

SEP, 2018


32-31-01 ANTI RETRACTION SYSTEM (LEVER LATCH)


32-31-02 LANDING GEAR LEVER INTEGRATED RED LIGHT



(a) Operations are limited to two calendar days.

(b) ETOPS operations are not conducted, and

(c) Operations are performed with landing gear down, and

(d) Operations are conducted in compliance with


See Operational procedure Landing Gear Retraction System and Uplocking System (O)

32-31-03PRefer to DEV.2.13.01.1 Dispatch with Landing Gear Down

32-42-01 WHEEL BRAKE C 4 3 * (O) (M) One may be inoperative provided that:

(a) Anti-skid system is operative, and

(b) Affected brake is deactivated , and(c) Operations are conducted in complicable AFM

Deviation Guide.

See Operational procedure MOP.32.42-01P Wheel Break (O)


ITEM

LANDING GEAR RETRACTION SYSTEM AND UPLOCKING SYSTEM

LANDING GEAR RETRACTION SYSTEM AND UPLOCKING SYSTEM (O)

p p ( )

See maintenance procedure MMP.32.42-01 Wheel Break (M)

32-42-01P WHEEL BRAKE (O) Refer to DEV.2.5.01.1 Dispatch with One Wheel Brake Deactivated or Removed.

32-42-02 ANTI SKID SYSTEM C 1 0 * (O) May be inoperative provided that operations are conducted in compliance with applicable AFM Deviation Guide.

See Operational procedure MOP.32.42-02P Anti-skid System (O)

32-42-02P ANTI SKID SYSTEM (O) Refer to DEV.02.6.01.1 Dispatch with Antiskid System Inoperative.

32-42-03 BRK TEMP ALERT C 1 0 * May be inoperative provided that:

(a) Landing gear is left down for 1 min after take off except in case of emergency, and

(b) A minimum turn around of 20 min is observed.

32-45-01 A 1 0 * May be inoperative provided that:

(a) The parking brake system is operative, and

(b) Operations are limited to three calendar days.

PRKG BRK (PARK BRK LIGHT ON CAP)


CH32 LANDING GEARPage 32‐2(PIA REV 2.0A)

FEB, 2019



ITEM

32-51-01 NOSE WHEEL STEERING C 1 0 * (O) May be inoperative provided that:

(a) Centering function is not affected, and

(b) All brakes are operative, and(c) Maximum crosswind component is limited to

15 kt, and

(d) Aircraft is not operated on narrow runways

(width < 30 m (98 ft))

See Operational procedure MOP.32.51-01P Nose Wheel Steering (O)

32-51-01P NOSE WHEEL STEERING (O) Maximum demonstrated crosswind component for take off and landing is 15 kt

● Apply asymmetrical thrust and differen al braking for taxi

and line up as required.

● Avoid sharp turns while using brakes.

32-61-01 LANDING GEAR POSITION INDICATING SYSTEM

B 2 1 * (O) May be inoperative.

See Operational procedure MOP.32.61-01P Landing Gear Position Indicating Systems (O)

32-61-01P LANDING GEAR POSITION INDICATING SYSTEM (O)

If OVHD panel is affected, some failure case may generate LDG GEAR NOT DN Alerts.

As soon as three green are illuminated on one panel, gear is down.if Primary or Secondary Landing gear indication system is not operative. The illumination of the Green System "LO PR" amber light on the HYD PWR overhead panel will be inhibited when the landing gear control lever is in Down Position.


CH33 LIGHTSPage 33‐1(PIA REV 2.0)

SEP, 2018


33-10-01 COCKPIT LIGHTS C - - May be inoperative provided that:

(a) Sufficient lighting to illuminate all instruments, controls and placards is assured, and(b) RH dome and STBY instruments integrated lights are operative.

33-10-02-01 CABIN LIGHTS -PASSENGER CONFIGURATION

C - 9 One or more may be inoperative provided that:

(a) 9 Operating ceiling lights are regularly

distributed within the cabin, and

(b) Lighting must be sufficient for cabin attendant

to perform its duties.

33-10-02-02 CABIN LIGHTS - CARGO CONFIGURATION

NOT APPLICABLE

33-16-01-01 ANN LIGHT - TEST FUNCTION

A 1 0 * (O) May be inoperative provided that operations are limited to two calendar days.

See Operational procedure MOP.33-16-01-01P ANN Light - Test Function (O)

33-16-01-01P ANN LIGHT - TEST FUNCTION (O)

Following warnings have to be tested before the first flight of the day, to check red lights illumination.

PITCH DISCONNECT / SMK / EXCESS CAB ALT / EXCESS ∆P

● The SELECTOR on the LH maintenance panel has

to be used:

● Set the SELECTOR to the function to be tested.

Depress TEST PTT pb


ITEM

● Depress TEST PTT pb.● Check the associated warnings are generated:CRC,

MW light flashing red and associated local red

light if applicable is come on.

● After the test of all the functions, set SELECTOR

to NORM FLT.

LANDING GEAR NOT DOWN● On LH MAINTENANCE panel , set the SELECTOR to

LDG GEAR NOT DOWN.

● Set PL to FI or FLAPS 35.

● Depress TEST PTT pb.

● Check the warnings: CRC , MW light flashing red and

LDG GEAR NOT DOWN light on CAP comes on.

TO CONFIG● Depress TO CONFIG TEST pb while at least one out

of the following four conditions is not met:

● Pitch trim set in the TO range.

● FLAPS set to 15ᴼ

● PWR MGT set to TO.

● RUD TLU green light come on.

● Check the warnings: CRC , MW light flashing red and

TO CONFIG light on CAP comes on.


CH33 LIGHTSPage 33‐2(PIA REV 2.0)

SEP, 2018



ITEM

FLAPS UNLOCK● Set FLAPS 15.

● Depress and maintain FLAPS UNLK PTT pb on

RH maintenance panel.

● Check warning is activated when the flaps position

passes over the selected position minus 3ᴼ on

the flaps position indicator.33-16-01-02 ANN LIGHT - DIM FUNCTION33-16-01-02A NIGHT OPERATIONS (A) B 1 0 * May be inoperative for Night operations. -OR-

33-16-01-02B DAYLIGHT OPERATIONS (B) C 1 0 * May be inoperative for Daylight operations.

33-16-02 NO SMKG OR NO DEVICE MEMO LIGHT


33-16-03 SEAT BELTS MEMO LIGHT C 1 0 * May be inoperative.

33-26-01 CABIN SIGNS C - 0 * May be inoperative provided that:

(a) Passenger address system is operative and is used to

advise passengers and cabin attendant when seat belts

should be fastened and smoking or use of personal

electronic devices are prohibited, and

(b) Cabin attendant call and interphone are operative.

NoteFor Cargo Operations,no MEL item entry is applicable as the system is not required.

33-31-01 NOSE WHEEL WELL LIGHT C 1 0 May be inoperative.

33-34-01 CARGO BAY LIGHT C - 0 May be inoperative.

33-37-01 MAIN WHEEL WELL LIGHT C 2 0 One or both may be inoperative.

33-41-01 NAV LIGHTS SYSTEM C 1 0 * May be inoperative for daylight operation.

33-42-01 LAND LIGHT33‐42‐01A NIGHT OPERATIONS (A) C 2 1 * One may be inoperative for Night operations provided that one

Landing light is operative. - OR-

33-42-01B DAYLIGHT OPERATIONS (B) C 2 0 * May be inoperative for Daylight Operations.

33-43-01 STROBE LIGHT D 3 0 * One or more STROBE lights may be inoperative provided all BEACON lights are operative.

33-46-01 TAXI AND TO LIGHT33-46-01A NIGHT OPERATIONS (A) C 2 0 * One or both may be inoperative for Night Operations provided

that one LAND light is operative. -OR-

33-46-01B Daylight Operations (B) C 2 0 * One or may be inoperative for Daylight Operations.

33-47-01 LOGO LIGHTS D 2 0 * One or both may be inoperative.


CH33 LIGHTSPage 33‐3(PIA REV 2.0A)

FEB, 2019



ITEM

33-48-01 BEACON LIGHT33-48-01A NIGHT OPERATIONS (A) C 2 1 * (O) One may be inoperative provided all STROBE lights are

operative.

See Operation procedure MOP.33-48-01P BEACON Light (O)

-OR-33-48-01B DAYLIGHT OPERATIONS (B) C 2 1 * (O) One or both may be inoperative for Daylight Operations

provided that all STROBE lights are operative.NoteIf the center fuselage BEACON light is inoperative, alternative procedures must be developed and used when aircraft is on ground with engine (s) running.

See Operations procedure MOP.33.48-01P BEACON Light (O)

33-48-01P BEACON LIGHT (O) ● One may be inoperative provided that all STROBE lights are operative.

33-49-01 WING INSPECTION LIGHTS

33-49-01 A NIGHT OPERATIONS (A) B 2 1 * One may be inoperative for Night Operations provided that flight is not conducted into known or forecast icing conditions.

-OR-

33-49-01B DAYLIGHT OPERATIONS (B) C 2 0 * One or both may be inoperative for Daylight Operations.

33-49-02 IEP LIGHT33-49-02A NIGHT OPERATIONS (A) B 1 0 (O) May be inoperative provided that the Flight is not conducted

into known or forecast icing conditiions.

See Operational procedure MOP.33.49-02P IEP Light (O)

-OR-

33 49 02B DAYLIGHT OPERATIONS (B) C 1 0 M b i ti f D li ht O ti33-49-02B DAYLIGHT OPERATIONS (B) C 1 0 May be inoperative for Daylight Operations.

33-49-02P IEP LIGHT (O) ● In case of inadvertent icing conditions encountered, keep

the anti-icing systems activated until the end of the Flight (Icing AOA illuminated).

33-50-01 EMER EXIT (DISARM) LIGHT C 1 0 * May be inoperative provided that EMER EXIT light system isoperative and armed prior to each departure.

33-50-02-01 C - - One or more photoluminescent tape portion may be inoperative provided that:(a) No more than one meter of photoluminescent is

inoperative on each strip,and

(b This inoperative part is neither facing nor

continuous to an emergency exit.

NOTEFor Cargo Operations, no MEL item entry is applicable as the system is not required.

33-50-03 CEILING EMERGENCY LIGHTING

B 4 3 May be inoperative provided that a maximum of one in four consecutive overhead emergency lights may be inoperative.

NOTEFor Cargo Operations, no MEL item entry is applicable as the system is not required.

PHOTO LUMINESCENT FLOOR PROXIMITY EMERGENCY ESCAPE PATH MARKING TAPE


CH33 LIGHTSPage 33‐4(PIA REV 2.0A)

FEB, 2019



ITEM

33-50-04 EMERGENCY EXIT SIGNS

33-50-04 A 10 9 * One may be inoperative provided that associated exit is considered inoperative.Refer to Item 52-21-01-01 Emergency Exit (Including Passenger-Crew Doors, but Excluding Flight Deck Emergency Exits) - Passenger or Combi Configuration.NoteFor Corgo Operations, no MEL item entry is applicable as the system is not required, and the emergency exit lights of the issues accessible by the crew members must be operative.

- OR -

33-50-04 C 10 10 * Up to 50% of the bulbs / LEDS may be inoperative in one or

more signs provided that the sign remains legible.NoteFor Corgo Operations, no MEL item entry is applicable as the system is not required, and the emergency exit lights of the issues accessible by the crew members must be operative.

33-50-05 EMERGENCY EXIT HANDLE LIGHTING

A 2 1 * One may be inoperative provided that associated emergency exits is considered inoperative.Refer to Item 52-21-01-01 MOP.52.21.01-01 Emergency Exit (Including Passenger-Crew Doors,Service Door but Excluding Flight Deck Emergency Exits) - Passenger or Combi Configuration

33-51-01 EXTERIOR EMER LIGHTS

33-51-01A NIGHT OPERATIONS (A) B 4 3 For Night Operations, Refer to Item 52-21-01-01 Emergency Exit (Including Passenger - Crew Doors, but Excluding Flight Deck Emergency Exits) Passenger or Combi ConfigurationDeck Emergency Exits) - Passenger or Combi Configuration

NoteFor Corgo Operations, no MEL item entry is applicable as the system is not required, and the emergency exit lights of the issues accessible by the crew members must be operative.

-OR-

33-51-01B DAYLIGHT OPERATIONS (B) B 4 3 One light may be inoperative for Daylight Operations only.

Note

For Corgo Operations, no MEL item entry is applicable as the system is not required, and the emergency exit lights of the issues accessible by the crew members must be operative.


CH34 NAVIGATIONPage 34‐1(PIA REV 2.0A)

FEB, 2019


34-11-01 AIR DATA COMPUTER (ADC)

34-11-01A ETOP OPERATONS (A) A 2 1 * (O) The ADC # 2 only may be inoperative provided that:


(b) The autopilot use is prohibited below 1000 ft AGL, and

(c) Operations are limited to two flights, and(d) TLU manual mode is operative.

See Operational procedure MOP.34.11-01P Air Data Computer (ADC) (O)

-OR-34-11-01B (B) A 2 1 * (O) The ADC # 2 only may be inoperative, provided that:


(b) ETOPS operations are not conducted, and(c) The autopilot use is prohibited below 1000 ft AGL, and

(d) Operations are limited to two calender days , and

(e) TLU manual mode is operative.

See Operational procedure MOP.34.11-01P Air Data Computer (ADC) (O)

34-11-01P ● ADC switching must be set to valid ADC

TLU manual mode check:● Select HI SPD and check alert is generated after 25 s : MC ,

SC , FLT CTL on CAP and TLU FAULT light.

● Check rudder travel is limited.

● Select AUTO and check alert stops after 15 s.

● Check rudder travel is not limited.

34-12-02 STBY ALTIMETER C 1 1 * Vibrator may be inoperative.


ITEM

AIR DATA COMPUTER (ADC) (O)

34-12-03 MAIN ALTIMETERS34-12-03A ETOPS OPERATIONS (A) A 2 1 * One may be inoperative provided that:


(b) Standby altimeter is fully operative, and

(c) CAPT main altimeter is operative, and

(d) Operations are limited to two calendar days. -OR-34-12-03B (B) A 2 1 * One may be inoperative provided that:


(b) ETOPS operations are not conducted, and

(c) Standby altimeter is fully operative, and

(d) Operations are limited to two calender days .

34-13-01-01 AIRSPEED INDICATOR - SPEED INDICATION

34-13-01-01A ETOPS OPERATIONS (A) A 3 2 * One may be inoperative provided that:

(a) Standby airspeed indicator is operative, and

(b) CAPT speed indicator is operative, and

(c) Operations are limited to two calendar days.

-OR-

34-13-01-01B (B) A 3 2 * One may be inoperative provided that:


(b) Standby airspeed indicator is operative, and




FEB, 2019



ITEM

34-13-01-02 AIRSPEED INDICATOR - SPEED SELECTOR

C 2 0 * (O) One or both may be inoperative.

See Operational procedure MOP.34.13-01-02P Airspeed indicator - Speed Selector (O)

34-13-01-02P AIRSPEED INDICATOR - SPEED SELECTOR (O)

● FAST/SLOW indication on the EADI is lost.

34-14-01 VERTICAL SPEED C 2 1 * One may be inoperative.

34-15-01-01 (TAT-SAT-TAS INDICATOR) - TAS INDICATION


34-15-01-02 (TAT-SAT-TAS INDICATOR) - TEMPERATURE INDICATION

C 2 0 * (O) One or both may be inoperative.

See Operational procedure MOP.34.15-01-02P (TAT-SAT-TAS Indicator) - Temperature Indication (O)

34-15-01-02P Aircraft must be considered as flying in icing conditions as soon asvisible moisture is encountered regardless of temperature.

If anti-icing and/or de-icing systems need to be used, mode FASTonly must be switched ON.

34-15-01-03 (TAT-SAT-TAS INDICATOR) - SAT SWITCHING


34-16-01 B 1 0 * (O) May be inoperative provided that:

(a) Autopilot altitude hold mode is operative, and (b) Both main altimeters are operative, and (c) The altitude alerting system is not part of the required

equipment for intended operations

(TAT-SAT-TAS INDICATOR) - TEMPERATURE INDICATION (O)

ALTITUDE ALERTING SYSTEM

equipment for intended operations.

See Operational procedure MOP.34.16-01P Altitude Alerting System (O)

34-16-01P ● In FlightFlight crew should check on altimeters that there is no altitude excursion.● During climd, descent and altitude capture phasesFlight crew must ensure strict adherence to standardized callouts.

34-20-01 AHRS 2 2 * Any in excess of 2 may be in inoperative.

34-21-02 ADC SWITCH B 1 0 * May be inoperative provided that associated ADC is operative.

34-21-03 ADC SWITCH FAULT LIGHT C 1 0 * May be inoperative provided that both ADC are operative.

34-26-01 SLIP-SKID INDICATOR C 2 1 * One may be inoperative provided that:(a) The Slip/Skid indicator on the Pilot Flying side must be operative, and (b) Primary attitude indications are operative on Pilot Flying side.

ALTITUDE ALERTING SYSTEM (O)



FEB, 2019



ITEM

34-27-01 STANDBY HORIZON 1 1 * Any in Excess of one may be inoperative.

34-29-01 RMI

34-29-01A ETOPS OPERATION (A) C 2 1 * One may be inoperative provided that:

(a) Respective information is available on adjacent EHSI , and (b) RMI #2 is operative.

-OR-34-29-01B (B) C 2 1 * One may be inoperative provided that:


(b) Respective information is available on adjacent EHSI.

34-33-01 MARKER BEACON SYSTEM

34-33-01A (A) C 2 0 *

-OR-34-33-01B (B) D 2 0 * One or more may be inoperative for flight in accordance with VFR.

34-36-01 ILS34-36-01A (A) C 2 0 One or both may be inoperative for IFR operations, provided that

approaches and missed approaches are not based on ILS only on the airports required to be selected for the intended flight route.

-OR-34-39-01B (B) D 2 0 One or both may be inoperative for flight in accordance with VFR .

34-41-01 WEATHER RADAR C 1 0 * May be inoperative provided that weather reports or forecast available to the Captain indicate that cumulo-nimbus clouds or other potentially

One or more may be inoperative for IFR operations provided that approaches and missed approaches are not based on marker beacon only on the airports required to be selected for the intended flight route.

p p yhazardous weather conditions which could be detected by the system in working order are unlikely to be encountered on the intended flight route.

34-41-02 RADOME BONDING ADHESIVE TAPES

C 8 7 One may be inoperative provided that flight is not conducted into known or forecasted cumulo-nimbus, thunderstorm or sandstom for the intended flight route.

34-42-01 B 1 0 * (O) One or more may be inoperative provided that: (a) GPWS is turned OFF, Refer to Item 34-48-02-01MOP.34.48-02-01

Ground Proximity Warning System - GPWS, and

(B) ACAS is set to STBY, Refer to Item 34-57-01-01 MOP.34.57-01-01 Airborne Collision Avoidance System - ACAS System.

See Operational procedure MOP.34.42-01P Radio Altimeter System (O)

34-42-01P ▪ During Final Cockpit Prepration● GPWS…………………………………………………………OFF● TCAS…………………………………………………………STBY

▪ During Descent Preparation● ARRIVAL BRIEFING………………..……..ANNOUNCE STICK

PUSHER INHIBITION BELOW 500 FT AGL INOPERATIVE

34-48-02-01 GROUND PROXIMITY WARNING SYSTEM - GPWS

1 1 NO GO AS PER PCAA POLICY

RADIO ALTIMETER SYSTEM (O)

RADIO ALTIMETER SYSTEM



FEB, 2019



ITEM

34-50-01 NAVIGATION SYSTEMS (VOR-DME-ADF)

VORA C 2 1 * (O) One may be inoperative provided that:

(a) Both ADF and DME are Operative or alternative approved

equipment giving equivalent or enhanced navigation

capability is operative, and

(b) Operational procedures, are not based only on VOR signals.

B A 2 O (O) One or both may be inoperative for a maximum of 5 flights provided that: (a) Two additional items of equipment giving equivalent

navigation capability are operative, and

(b) The flight can proceed safely, including approach phase using

the other operative navigation systems.

DMEA B 2 0 (O) One or both may be inoperative, provided that the affected DME is not

required for the intended flight routes and approach procedures to be performed.NoteThe approach procedure(s) intended to be flown are at the airports specified in the operational flight plan.

B C 2 0 One or both may be inoperative provided that navigation procedures for the intended flight routes are not dependant upon the use off affected DME.

ADFA B 2 0 (O) One or more may be inoperative, provided that alternate approved

navigation equipment is operative and used.

B C 2 0 One or more may be inoperative, provided that navigation procedures for the intended flight route to be flown are not dependant upon the use of affected ADF.

34-50-01P NAVIGATION SYSTEMS (VOR-DME-ADF) (O)

(Same as Supplemental procedures)

34-52-01 A 2 0 * May be inoperative for a maximum of 5 flights provided that:

(a) Flight is conducted under VFR over routes navigated

by reference to visual landmarks, and

(b) Permission is obtained from the Air Navigation Service

Provider(s) along the route or any planned diversion.

34-52-02 SSR TRANSPONDER SYSTEM - MODE S FUNCTION

34-52-02A (A) D 2 0 Any in excess of those required for the intended route may be inoperative.Note1) Altitude reporting, provided by an ATC Mode S Transponder, is

required for ACAS II OPERATION. Refer to Item 34-57-01-01 Airborne Collision Avoidance System - ACAS2) Elementary Surveillance (ELS) function is required in European

Mode S designated airspace.

SSR TRANSPONDER SYSTEM - MODE AC FUNCTIONS


CH34 NAVIGATIONPage 34‐5(PIA REV 2.0)

SEP, 2018



ITEM

34-52-03 SSR TRANSPONDER SYSTEM - ENHANCED SURVEILLANCE FUNCTION

C 2 0 One or more Downlinked Aircraft Parameters which provide Enhanced Surveillance may be inoperative when required for the intended route.

34-52-04 SSR TRANSPONDER SYSTEM - EXTENDED SQUITTER TRANSMISSION FUNCTION

NOT APPLICABLE

34-57-01-01 AIRBORNE COLLISION AVOIDANCE SYSTEM - ACAS SYSTEM

1 1 NO GO AS PER PCAA POLICY

34-57-01-02 AIRBORNE COLLISION AVOIDANCE SYSTEM - COMBINE TA AND RA DUAL DISPLAY

C 2 1 (O) May be inoperative on the non flying pilot side provided that TA and RA elements and audio functions are operative on the flying pilot side.

See Operational procedure MOP.34.57-01-02P airborne Collision Avoidance System - Combine TA and RA Dual Display (O)

34-57-01-02P May be inoperative on the non flying pilot side provided TA and RA elements and audio functions are operative on the flying pilot side.

The associated C/B ACAS is pulled for ACAS deactivation.

34-57-01-03 AIRBORNE COLLISION AVOIDANCE SYSTEM - RESOLUTION ADVISORY (RA) DISPLAY SYSTEM

34-57-01-03A (A) C 2 1 (O) One may be inoperative on the non-flying pilot side.

AIRBORNE COLLISION AVOIDANCE SYSTEM - COMBINE TA AND RA DUAL DISPLAY (O)

( ) (O) y p y g p

See Operational procedure MOP.34.57-01-03P Airborne Collision Avoidance System - Resolution Advisory (RA) Display System (O)

-OR-

34-57-01-03B (B) C 2 0 (O) One or more may be inoperative provided that:

(a) All Traffic Alert (TA) display elements and audio

functions are operative, and

(b) TA only mode is selected by the crew.

See Operational procedure MOP.34.57-01-03P Airborne Collision Avoidance System - Resolution Advisory (RA) Display System (O)

34-57-01-03P One or both may be inoperative provided that:(a) All Traffic Alert (TA) display elements and audio functions are operative, and(b) TA only mode is selected by the crew.The associated C/B ACAS is pulled for ACAS deacativation.

34-57-01-04 C 2 0 (O) One or more may be inoperative provided that all installed RA display and audio functions are operative.

See Operational procedure MOP.34.57-01-04P Airborne Collision Avoidance System - Traffic Alert (TA) Display System (O)

34-57-01-04P AIRBORNE COLLISION AVOIDANCE SYSTEM -TRAFFIC ALERT (TA) DISPLAY SYSTEM (O)

● One or more may be inoperative provided that all installed RA display and audio functions are operative.

AIRBORNE COLLISION AVOIDANCE SYSTEM -TRAFFIC ALERT (TA) DISPLAY SYSTEM

AIRBORNE COLLISION AVOIDANCE SYSTEM - RESOLUTION ADVISORY (RA) DISPLAY SYSTEM (O)


CH34 NAVIGATIONPage 34‐6(PIA REV 2.0)

SEP, 2018



ITEM

34-58-01 C 1 0 * (O) May be inoperative provided that:

(a) The navigation systems required for each segment of the intended flight route are operative, and(b) Alternate procedures are astablished and used, where applicable, and

(c) For ETOPS Operations, GPS/GNSS # 1 is operative.

Note

1) Dependent TAWS is inoperative, Refer to Item 34-48-02-05

MOP.34.48-02-05 Ground proximity Warning System - Terrain

Awareness and Warning System (TAWS) (Where required)

2) GNSS parameters are no longer available for Transponder

System, Refer to Item 34-52-03MOP.34.52-03 SSR

Transponder System - Enhanced Surveillance Function and

Refer to MOP.34.52-04 SSR Transponder System - Extended

Squitter Transmission Function.See Operational procedure MOP.34.58-01P GPS-GNSS (O)

34-58-01P May be inoperative provided that:

(a) Not required by the flight rules, and

(b) Status and suitability of navigation facilities used to define route

flight are verified by dispatch (refer jeppesen Chart Notams), and

(c) Approch navigation redios are verified to be properly tuned

and identified.

34-61-02 NAVIGATION DATABASE C 1 1 May be out of currency provided current aeronautical charts are used to verify navigation fixes before dispatch.

34-70-01 EFIS - SG C 2 0 * One or both may be inoperative in normal position.

34 70 02 ATT HDG C 2 0 * O b th b i ti i l iti

GPS-GNSSGLOBAL POSITIONING SYSTEM

GPS-GNSSGLOBAL POSITIONING SYSTEM (O)

34-70-02 ATT - HDG C 2 0 * One or both may be inoperative in normal position.

34-70-03 VOR - ILS C 2 0 * One or both may be inoperative in normal position.

34-71-01 C 4 3 * (O) One may be inoperative provided that CAPT EADI is operative.

See Operational procedure MOP.34.71-01P Electronic Flight Instrument System (EFIS) Display (O)

-OR-B 4 2 * (O) Two may be inoperative provided that:

(a) The flight is conducted in day VMC only, and(b) ETOPS Operations are not conducted, and

(c) They are not on the same side.

See Operational procedure MOP.34.71-01P Electronic Flight Instrument System (EFIS) Display (O)

34-71-01P ● Select OFF the affected EFIS display in order to recover composite mode on the non affected screen.

34-71-02 SYMBOL GENERATOR UNIT (SGU)

A 2 1 * SGU 2 only may be inoperative provided that:


(b) ETOPS Operations are not conducted, and

(c) Operations are limited to two calender days .



ELECTRONIC FLIGHT INSTRUMENT SYSTEM (EFIS) DISPLAY (O)

ELECTRONIC FLIGHT INSTRUMENT SYSTEM (EFIS) DISPLAY


CH35 OXYGENPage 35‐1(PIA REV 1.0)

SEP, 2017


35-11-01 LO PR ALERT B 1 0 * May be inoperative provided that maximum altitude is limited to 10 000 ft pressure altitude.

35-13-01 FLIGHT DECK PRESSURE INDICATION

B 1 0 * May be inoperative provided that oxygen pressure is checked on the bottle direct reading gauge prior to each departure.

35-13-02 OBSERVER SEAT OXYGEN MASK

C 1 0 * May be inoperative provided that observer seat is not occupied.

-OR-

C 1 0 * May be inoperative provided that maximum altitude is limited to 10 000 ft.

35-15-01 BOTTLE GAUGE B 1 0 * May be inoperative provided that flight deck pressure indication is operative.

35-20-01 PASSENGER OXYGEN SYSTEM - PASSENGER CONFIGURATION

B 1 0 * (O) May be inoperative provided that maximum altitude is limited to 10 000 ft pressure altitude.

See Operational procedure MOP.35.20-01P Passenger Oxygen System - Passenger Configuration (O)

35-20-01P PASSENGER OXYGEN May be inoperative provided that maximum altitude is limited to


ITEM

SYSTEM - PASSENGER CONFIGURATION (O)

10 000 ft pressure altitude.

35-20-02 PASSENGER OXYGEN SYSTEM - CARGO CONFIGURATION

NOT APPLICABLE

35-20-03 PASSENGER SERVICE UNIT

B 12 - * (O) (M) One or more passenger service units may be inoperative provided that:

(a) Affected seats are blocked and placarded to prevent occupancy, and

(b) Units are operative for all operative passenger seats,

toilet compartment and cabin attendant location.

See Operational procedure MOP.35.20-03P Passenger Service Unit (O)

See Maintanance procedure MMP.35.20-03 Passenger Service Unit (M)

35-20-03P PASSENGER SERVICE UNIT (O)

One or more passenger service units may be inoperative provided that:(a) Affected seats are blocked and placarded to prevent

occupancy, and


CH35 OXYGENPage 35‐2(PIA REV 1.0)

SEP, 2017



ITEM

(b) Units are operative for all operative passenger seats,

toilet compartment and cabin attendant location.

35-35-01 PORTABLE OXYGEN BOTTLE

D 2 1 * (O) (M) Any in excess of that required may be inoperative or missing provided that each inoperative equipment is placarded inoperative removed from the installed location and placed out of sight so it cannot be mistaken for functional unit.

See Oerational procedure MOP.35.35-01P Portable Oxygen Bottle (O)

See Maintenance procedure MMP.35.35-01 Portable Oxygen Bottle (M)

35-35-01P PORTABLE OXYGEN BOTTLE (O)

One may be inoperative or missing provided that each inoperative equipment is placarded inoperative removed from the installed location and placed out of sight so it cannot be mistaken for functional unit.


CH36 PNEUMATIC SYSTEMPage 36‐1(PIA REV 0.0)

SEP, 2017


36-11-01 HP VALVE C 2 1 * (M) One may be inoperative provided that it is deactivated.

See Maintenance procedure MMP.36.11-01 HP Valve (M)

36-11-02-01 BLEED VALVE - PASSENGER CONFIGURATION C 2 1 * (O) (M) One may be inoperative provided that:

(a) In case of BLEED LEAK a maintenance action is due

to close X BLEED.

Refer to Item 36-11-04 Ground X Feed Valve

(b) It is secured closed, and

(c) Flight level is limited to FL 170.

See Operational procedure MOP.36.11-02P BLEED Valve (O)

See Maintenance procedure MMP.36.11-02 BLEED Valve (M)

36-11-02-02 BLEED VALVE - CARGO CONFIGURATION

C 2 1 * (O) (M) One may be inoperative provided that:

(a) In case of BLEED LEAK a maintenance action is due

to close X BLEED.

Refer to Item 36-11-04 Ground X Feed Valve

(b) It is secred closed, and

(c) Flight level is to FL 170.

See Operational procedure MOP.36.11-02P BLEED Valve (O)


ITEM

See Maintenance procedure MMP.36.11-02P BLEED Valve (M)

36-11-02-02P BLEED VALVE (O) As an in-flight failure could imply total loss of pressurization,fuel consumption at FL 100 must be taken into account to compute the trip fuel.LIMITATIONS

• LARGE RAPID POWER CHANGE : AVOID

36-11-03 BLEED FAULT ALERT

36-11-03A (A)C 2 1 * One may be inoperative provided that associated pack FAULT

alert is operative. -OR-

36-11-03B (B) C 2 1 * One may be inoperative provided that associated bleed valve is considered inoperative and selected OFF:Refer to Item 36-11-02-01Bleed Valve - Passenger Configuration , or Refer to Item 36-11-02-02BLEED Valve - Cargo Configuration

36-11-04 GROUND X FEED VALVE C 1 0 * (M) May be inoperative provided that it is secured closed.

See Maintenance procedure MMP.36.11-04 Ground X Feed Valve (M)

36-11-05 GROUND X FEED VALVE OPEN ALERT

C 1 0 * (M) May be inoperative provided that X valve is checked closed.


CH36 PNEUMATIC SYSTEMPage 36‐2(PIA REV 0.0)

FEB, 2017



ITEM

See Maintenance procedure MMP.36.11-04 Ground X Feed ValveOPEN Alert (M)

36-11-06 OVHT ALERT C 2 1 * One may be inoperative provided that associated bleed valve is

considered inoperative and selected OFF.Refer to Item 36-11-02-01 BLEED Valve - Passenger Configuration , or Refer to Item 36-11-02-02 BLEED Valve - Cargo Configuration

36-22-01 LEAK ALERT C 2 1 * One may be inoperaetive provided that associated bleed valve is considered inoperative and selected OFF. Refer to Item 36-11-02-01 BLEED Valve - Passenger Configuration , or refer to Item 36-11-02-02 BLEED Valve - Cargo Configuration




CH52 DOORSPage 52‐1(PIA REV 2.0 A)

FEB, 2019


52-11-01 DOOR ALERT SYSTEM B 1 0 * (M) May be inoperative provided that affected doors are checked locked closed prior to each flight.

See Maintenanace proccedure MMP.52.11-01 Door Alert System (M)

52-11-02 SECONDARY HANDRAIL C 1 0 * May be inoperative provided that the rail is secured in retracted position or removed.

52-12-01 PASSENGER DOOR TORQUE TUBE

52-12-01A FERRY FLIGHT (A) A 1 0 * May be inoperative for one ferry flight to a base where repair is possible provided that:

(a) Ground personnel assistance for opening and closing

operation is available, and

(b) Door is not operated from inside the aircraft

(except in case of emergency), and

(c) It is checked that nobody is right below the door during the

the operation, and

(d) All possibly concerned personnel are informed

about the unbalanced condition.

52-21-01-01 EMERGENCY EXIT (INCLUDING PASSENGER-CREW DOORS, SERVICE DOOR, BUT EXCLUDING

4 4


ITEM

FLIGHT DECK EMERGENCY EXITS)-PASSENGER OR COMBI CONFIGURATION

52-21-01-02 EMERGENCY EXIT (INCLUDING PASSENGER-CREW DOORS, SERVICE DOOR BUT EXCLUDING FLIGHT DECK EMERGENCY EXITS)-CARGO CONFIGURATION

NOT APPLICABLE

52-31-01 CARGO DOOR MOTOR ACTUATOR

52-31-01A (A) C 1 0 (M) May be inoperative provided that an approved mechanical device (crank) installed in the aircraft is used for cargo door operation.

See Maintenance procedure MMP.52.31-01 Cargo Door Motor Actuator (M)

-OR-

52-31-01B (B) C 1 0 An alternate way is defined to load/unload the forwad cargo.

52-31-02 CARGO DOOR CONTROL SYSTEM

C 1 0 * May be inoperative provided that cargo door is visually checked locked closed.



FEB, 2019



ITEM

52-31-03 AUX AFT CARGO DOOR (CLASS "C")

NOT APPLICABLE

52-42-01 SERVICE DOOR HOLD OPEN DEVICE

C 1 0 May be inoperative provided that service door is maintained in closed position.Refer to item 52-21-01-01MOP.52.21-01-01 Emergency Exit (including Passenger-Crew Doors, Service Door, but Excluding Flight Deck Emergency Exits) - Passenger or Combi Configuration

52-50-01-01 COCKPIT DOOR LOCKING SYSTEM

C 1 0 * (O) May be inoperative provided that the complete system is deactivated.See Operational procedure MOP.52.50-01-01P Cockpit Door Locking System (O)

52-50-01-01P ● Move the manual lock bolt(s), to CLOSE position.

Note

When the door is locked with the manual bolt (s), the emergency access to the cockpit is unavailable.Two crew members are mandatory to stay in the cockpit permanently.Note

Any part of the CDLS may be inoperative provided that the complete system is deactivated in the unlocked position and is not required by operational regulations for the intended flight.

A 1 0 M b i ti id d th t ti li it d t t

COCKPIT DOOR LOCKING SYSTEM (O)

COCKPIT DOOR LOCKING52‐50‐01‐02 A 1 0 * (O) May be inoperative provided that operations are limited to two calendar days .

See Operational procedure MOP.52-50-01-02P Cockpit Door Locking System - System (control Unit, Toggle Switch, Lights on Control Panel, Buzzer) (O)

52-50-01-02P ● Move the manual lock bolt(s) to CLOSE position.

NoteWhen the door is locked with the manual bolt(s), emergency access to the cockpit is unavailable.Two crew members are mandatory to stay in the cockpit permanently.NoteAny part of the CDLS may be inoperative provided that the complete system is deactivated in the unlocked position and is not required by operational regulations for the intended flight.

52-50-01-03 COCKPIT DOOR LOCKING SYSTEM - CALL PUSHBUTTON ON DOOR CALL PANEL

C 1 0 * May be inoperative provided that the crew members interphone is operative.

COCKPIT DOOR LOCKING SYSTEM - SYSTEM (CONTROL UNIT, TOGGLE SWITCH, LIGHTS ON CONTROL PANAL,BUZZER) (O)

COCKPIT DOOR LOCKING SYSTEM - SYSTEM (CONTROL UNIT, TOGGLE SWITCH, LIGHTS ON CONTROL PANAL,BUZZER)



FEB, 2019



ITEM

52-50-01-04 C 1 0 * (O) May be inoperative provided that the crew members interphone is operative.

See Operational procedure MOP.52.50-01-04P Cockpit Door Locking System - EMER Pushbutton on Door Call Panel (O)

52-50-01-04P ● Move the manual lock bolt(s), to CLOSE position.

Note

When the door is locked with the manual bolt(s), emergency access to the cockpit is unavailable.Two crew members are mandatory to stay in the cockpit permanently.Note

Any part of the CDLS may be inoperative provided that thecomplete system is deactivated in the unlocked position and isnot required by operational regulations for the intended flight.

52-50-01-05 COCKPIT DOOR LOOKING SYSTEM - OPEN LIGHT ON DOOR CALL PANEL


52-50-01-06 COCKPIT DOOR LOOKING SYSTEM - DENY LIGHT ON DOOR CALL PANEL

C 1 0 * May be inoperative provided that the crew membersinterphone is operative.

COCKPIT DOOR LOCKING SYSTEM - EMER PUSHBUTTON ON DOOR CALL PANEL

COCKPIT DOOR LOCKING SYSTEM - EMER PUSHBUTTON ON DOOR CALL PANEL (O)


CH56 WINDOWSPage 56‐1(PIA REV 2.0)

SEP, 2018


56-11-01 WINDSHIELD (INCLUDING MAIN WINDSHIELD, FWD AND AFT WINDOWS)

56-11-01A (A) A 6 6 (M) Structural damages may be present provided:

(a) Flight is conducted unpressurized, and

(b) Vision through affected cockpit windshield is

acceptable to the pilot, and

(c) Operations are limited to one calendar day.

NoteA cockpit window with minor damages, as described in Refer to SRM 56-10-00 , is considered operative, but the vision through this cockpit window must be acceptable to the pilot.See Maintenance procedure MMP.56.11-01 Windshield (Including Main Windshield, FWD and AFT Windows) (M)

-OR-

56-11-01B (B) C 6 6 (M) External ply may be cracked, provided that vision through affected cockpit windshield is acceptable to the pilot.

NoteA cockpit window with minor damages, as described in Refer to SRM 56-10-00 , is considered operative, but the vision through this cockpit window must be acceptable to the pilot.See Maintenance procedure MMP.56.11-01 Windshield (I l di M i Wi d hi ld FWD d AFT Wi d ) (M)


ITEM

(Including Main Windshield, FWD and AFT Windows) (M)

56-21-01-01 A - - (M) One or more cabin windows may be cracked provided that:

(a) Flight is conducted unpressurized, and

(b) Operations are limited to one calendar day.

See Maintenance procedure MMP.56.21-01 Passenger Compartment Window (M)

56-21-01-02 PASSENGER COMPARTMENT WINDOW - CARGO CONFIGURATION

NOT APPLICABLE

PASSENGER COMPARTMENT WINDOW - PASSENGER CONFIGURATION

PIA ATR 42‐500 MINIMUM EQUIPMENT LISTCH61 PROPELLER

Page 61‐1(PIA REV 2.0)

SEP, 2018


61-21-02 PEC CHANNEL A 4 2 * (O) Two may be inoperative provided that:

(a) One channel is operative on each engine, and(b) Reversers are not used when operated on narrow

runways (width < 30 m (98 ft)), and


See Operational Procedure MOP.61.21-02P PEC Channel (O)

61-21-02P PEC CHANNEL (O) On the engin affected by a PEC SGL CH light illuminated :

Other channel test :

Engine not running - PL on GI - CL on FUEL SO

● Set WOW on FLT position on RH Maintenance panel

● Advance CL to AUTO

● Check PEC FAULT illuminates after 30 s

● Retard CL to FUEL SO.

● Check PEC FAULT extinguishes after 30 s

● Set WOW on NORM position on RH Maintenance panel

Overspeed governor test:

Enine running - PL slighly above FI - CL on AUTO _ Make sure NP is above 77 %● Select PEC to OFF

● Slowly advance PL up to reach NP = 102.5 %

● Increase TQ by 5 % and check NP unchanged.


ITEM

● Retard PL to GI.

● Select PEC to ON and check PEC OFF extinguishes.

Note

Low pitch stop is automatically checked when propeller isunfeathered.

61-21-04 PEC SGL CH LIGHT A 2 0 * (O) May be inoperative provided that:

(a) PEC channel is considered inoperative on affected

engine: Refer to Item 61-21-02MOP.61.21-02 PEC

Channel ,and

(b) Operations are limited to two calender days.

See Operational procedure MOP.61.21.04P PEC SGL CH Light (O)

61-21-04P PEC SGL CH LIGHT (O) Refer to MOP.61.21-02P PEC Channel (O)

61-21-06 C 2 0 (O) May be inoperative provided that both CL are set to 100% OVRDNote

If affected side can not be identified, both PIU should be considered as inoperative.

See Operational procedure MOP.61.21-06P PIU and Associated Propeller Speed Selection (O)

PIU AND ASSOCIATED PROPELLER SPEED SELECTION



SEP, 2018



ITEM

61-21-06P During Preliminary Cockpit Preparation check:

□ Before each affected engine start● PL ………………………………………..….………….GI

● CL ………………………………………….……FUEL SO

● WOW SWITCH…………………………….………...FLT

● CL……………………………………………...……AUTO

AFTER 30 s

● PEC FAULT LIGHT………………….CHECK TURN ON

● CL……………………………………………....FUEL SO

● PEC…………………………………………….…RESET

● PEC FAULT LIGHT………..………CHECK TURN OFF

● WOW SWITCH…………………………….…….NORM

During propeller unfeathering

● SGL CH INDICATION………………CHECK TURN ON

● SGL CH INDICATION……………..CHECK TURN OFF

61-22-02-01 ATPCS C 1 0 * (O) One may be inoperative provided that:

(a) AFU is operative



See Operational procedure MOP.61.22-02-01P ATPCS (O)

61 22 02 01P ATPCS (O) Refer to DEV 2 12 01 1 Dispatch with ATPCS Off

PIU AND ASSOCIATED PROPELLER SPEED SELECTION (O)

61-22-02-01P ATPCS (O) Refer to DEV.2.12.01.1 Dispatch with ATPCS Off.

61-22-02-02 UPTRIM FUNCTION C 2 0 * (O) May be inoperative provided that:

(a) Autofeather is checked operative before each take off, and


applicable AFM Deviation Guide

See Operational procedure MOP.61.22-02-02P Uptrim Function (O)

61-22-02-02P UPTRIM FUNCTION (O) Refer to AFM - DEV.2.11.1.1 DISPATCH WITH UPTRIM FUNCTION INOPERATIVE

61-22-02-03 AUTOFEATHER FUNCTION

C 2 0 * (O) May be inoperative provided that:

(a) AFU is operative, and

(b) EEC/uptrim is operative, and



See Operational procedure MOP.61.22-02-03P Autofeather Function (O)

61-22-02-03P AUTOFEATHER FUNCTION(O)

Refer to DEV.02.7.01.1 Dispatch with Autofeather System Inoperative.

61-22-03 ATPCS ARM LIGHT C 1 0 * May be inoperative provided that ATPCS is considered inoperative.



SEP, 2018



ITEM

661-22-04 UPTRIM LIGHT C 2 0 * (O) One or more may be inoperative provided that uptrim is

consider inoperative.Refer to item 61-22-02 MOP.61.22-02-02 Uptrim Function

See Operational procedure MOP.61.22-04P Uptrim Light (O)

61-22-04P UPTRIM LIGHT (O) See Operational procedure MOP.61.22-02-02P Uptrim Function (O)

61-42-01 NP INDICATIONS

NP INDICATOR

61-42-01 (A) C 2 2 * (M) Either pointer or counter may be inoperative on each indicator provided that associated PROP anti icing is checked operative.See maintenance procedure MMP.61.42-01 NP Indications (M)

-OR-

61‐42‐01B (B) C 2 1 * (O) One may be inoperative, provided that :



icing conditions.

See Operational procedure MOP.61.42-01P NP Indications (O)

61-42-01P NP INDICATIONS (O) ● Either pointer or counter may be inoperative on eachNP INDICATOR (O) indicator provided that associated PROP anti icing is checked

operative.● One may be inoperative, provided that :



icing conditions.

61-45-01 LO PITCH CAUTION LIGHT C 2 0 * (O) May be inoperative provided that neither reverser is used at landing.See Operational procedure MOP.61.45-01P LO PITCH CAUTION Light (O)

61-45-01P Limitations

● REVERSE 1+ 2 : PROHIBITEDNormal Procedures

● If PL is on GI and CL is advanced from FTR to AUTO

● TQ : MONITOR < 10 %

61-50-01 PROPELLER BRAKE C 1 0 * (M) May be inoperativeNote

Hotel mode is not available.

See Maintenance procedure MMP.61.50-01 Propeller Brake (M)

61-51-01 PROP BRAKE UNLK C 1 0 * May be inoperative provided that propeller brake is removed after deactivation Refer to Item 61-50-1 Propeller Brake

LO PITCH CAUTION LIGHT (O)



SEP, 2018



ITEM

61-51-02 PROP BRK LOCAL AND MEMO LIGHT

61-51-02A (A) C 2 1 * One may be inoperative

-OR-

61-51-02B (B) C 2 0 * One or both may be inoperative provided that propeller brake is not used.

61-51-03 PROP BRK READY LIGHT C 1 0 * (O) May be inoperative provided that propeller brake is not used.

See Operational procedure MOP.61.51-03P PROP BRK Ready Light (O)

61-51-03P □ if propeller brake releasing is needed

● BLUE HYD PRESS……...………….CHECK 3000 PSI

● PROP BRK…………………………………...RELEASE

● UNLOCK LIGHT….....CHECK EXTINGUISHES AFTER 6 S

□ If prop brk WARNING IS ACTIVATED

CL…………………………………….…………….FUEL SO

61-60-01 INDICATION AND CONTROLS ON MAINTENANCE PANELS

C - 0 All may be inoperative.

PROP BRK READY LIGHT (O)


CH73 ENGINE FUEL AND CONTROLPage 73‐1(PIA REV 2.0)

SEP, 2018


73-13-01 IDLE GATE FAIL ALERT C 1 0 * (O) May be inoperative.

See Operational procedure MOP.73.13-01P IDLE Gate FAIL Alert (O)

73-13-01P IDLE GATE FAIL ALERT (O) Normal Procedures□ AFTER TAKEOFF

● IDLE GATE lever………..……CHECK PUSHED IN□ AT LANDING

● IDLE GATE lever……...…...CHECK PULLED OUT

73-15-01 FUEL HEATER73-15-01A C 2 0 * (M) May be inoperative provided that:

(a) Fuel anti-icing additives meets the engine

manufacturer'e specification, and

(b) Engine oil level is checked before the first flight of

each day.

See Maintenance procedure MMP.73.15-01 Fuel Heater (M)

-OR-

C 2 0 * May be inoperative provided that flight can be conducted in atmospheric conditions above 0 ° SAT

-OR-

73-15-01B HIGH FUEL TEMPERATURE REPORTED (B)

C 2 0 * May be inoperatIve provided that no fault in other fuel systems (ATA 28) is reported or is under MEL dispatch.

73-23-01 PWR MGT ROTARY SELECTOR

A 2 1 * (O) One may be inoperative provided that operations are limited to two calendar days.


ITEM

LOW FUEL TEMPERATURE REPORTED (A)

See Operational procedure MOP.73.23-01P PWR MGT Rotary Selector (O)

73-23-01P PWR MGT ROTARY SELECTOR (O)

□ IF One rotary selector stuck in TO position

● CL 1 + 2, for the whole flight……..…....…100% OVRD

□ For CLIMB and CRUISE

● Valid rotary selector…………....…CLIMB / CRUISE

● TQ affected side….According to the non affected one

□ One rotary selector stuck in MCT position

● ATPCS is lost: Refer to ATPCS (and Associated Test) (O).

● CL 1 + 2, for the whole flight………...…100% OVRD

● For TAKE OFF

● Inhibit CONFIG WARNIING BY depressing

WARNIING pb when applying power.

Note

● CAP light will not extinguish.

□ CLIMB AND CRUISE

● Valid rotary selector…………...….CLIMB / CRUISE

● TQ affected side.…...According to the non affected one

□ One rotary selector stuck in CLB or CRZ or

CRZ 1 position

● ATPCS is lost: Refer to ATPCS (and Associated Test) (O).

● For TAKE OFF

● CL 1 + 2 ……………………..…………100% OVRD


CH73 ENGINE FUEL AND CONTROLPage 73‐2(PIA REV 2.0)

SEP, 2018



ITEM

● Inhibit CONFIG WARNIING by depressing WARNING

pb when applying power.

Note

● CAP light will not extinguish.

● For CLIMB and CRUISE

● Valid rotary selector…………..….CLIMB / CRUISE

● CL 1 + 2 ………….………………..…...……...AUTO

● TQ affected side….…According to the non affected one

● For Final APPROACH

● CL 1 + 2 ……………….………..………100% OVRD

73-23-02 ENGINE CONTROL EEC A 2 1 * (O) One may be inoperative provided that:

(a) The DC HYD pump is operative, and

(b) The Associated pack and bleed valve are

operative, and


AFM Deviation Guide, and

(d) The Operations are limited to two calendar days .

See Operational procedure MOP.73.23-02P Engine Control (O)

73-23-02P ENGINE CONTROL (O)

EEC (O) Refer to DEV.2.8.01.1 Dispatch with EEC OFF

73-31-01 FUEL FLOW INDICATION B 2 1 * One may be inoperative.

73-31-02 FUEL USED C 2 1 * One may be inoperative provided that associated tank FUEL QTY indicator is operative.

73-34-01 FUEL CLOG ALERT A 2 1 * One may be inoperative provided that:(a) Associated engine parameters are monitored during

the flight, and

(b) Operations are limited to one calendar day and

aircraft does not depart an airport where repair or

replacement may be carried out.

73-35-01 FUEL TEMPERATURE INDICATION

C 2 0 * May be inoperative provided that associated fuel heater is considered inoperative: Refer to Item 73-15-01 Fuel Heater


C - 0 May be inoperative


CH74 IGNITIONPage 74‐1(PIA REV 2.0)

SEP, 2018


74-21-01 A 4 2 * Any in excess of two may be inoperative provided that:

(a) Operations are limited to three calendar days, and

(b) ETOPS Operations are not conducted, and

(c) One is operating on each engine and used.

74-31-01-02 IGN MEMO LIGHT C 1 0 * May be inoperative.


ITEM

IGNITION SYSTEM (A or B)


CH75 AIRPage 75‐1(PIA REV 0.0)

FEB, 2017


75-20-01 HBV DISCHARGE FLAPPERNOT APPLICABLE


ITEM


CH77 ENGINE INDICATINGPage 77‐1(PIA REV 2.0)

SEP, 2018


77-00-02 AFU B 2 1 * (O) (M) One may be inoperative provided that:


(b) AFU is deactivated, and

(c) ATPCS is considered inoperative, and

(d) Operations are conducted in compliance with applicable AFM Deviation Guide.

See Operational procedure MOP.77.00-02P AFU (O)

See Maintenance procedure MMP.77.00-02 AFU (M)

77-00-02P AFU (O) Refer to AFM-AFM DEV.02.12.01.1 Dispatch with ATPCS Off.

77-11-01 NH INDICATOR

77-11-01A (A) C 2 2 * Either pointer or counter may be inoperative on each indicator.

-OR-

77-11-01B (B) C 2 1 * (O) One may be inoperative provided that:


(b) Both engines TQ indicator and NP indicator are

operative.

See Operational Procedure MOP.77.11-01 P NH Indicator (O)

77-11-01P NH INDICATOR (O) ● When starting affected engine, select CL FTR 5 s after

S


ITEM

START pb has been depressed.

77-11-02 NL INDICATOR C 2 1 * One may be inoperative provided that associated NH indicator is operative and monitored.

77-13-01-01 TQ INDICATIONS - DIGITAL COUNTER

C 2 0 * (M) One or both Digital counters may be inoperative provided that:(a) Both EECs are operative and,

(b) HBV is checked operative.

NOTE

When only a TQ Pointer is inoperative AFU is considered inoperative and dispatch must be done under Refer to Item 77-00-02 MOP.77.00-02 AFU.

See Maintenance procedure MMP.77.13-01 TQ Indications (M)

77-13-01-02 TQ INDICATIONS - POINTER & DIGITAL COUNTER

C 4 2 * (O) Both Pointer and Digital counter on the same ENG may be inoperative provided that:


(b) ATPCS checked operative, and

(c) Both EECs are operative, and

(d) All NH and NP Indications are operative, and

(e) Operations are conducted in compliance with

applicable AFM Deviation guide.


CH77 ENGINE INDICATINGPage 77‐2(PIA REV 2.0)

SEP, 2018



ITEM

See Operational procedure MOP.77.13-01P TQ Indications (O)

77-13-01P TQ INDICATIONS - POINTER AND DIGITAL COUNTER (O)

Refer to AFM.DEV.02.11.01.1 Dispatch with One TQ Indication Inoperative (O).

77-14-01 TQ TARGET INDICATION C 2 0 (O) One or Both may be inoperative.

See Operational procedure MOP.77.14-01P TQ Target Indication (O)

77-14-01P □ If one TQ target indication is inoperative● TQ TARGET (affected side) : USE OPERATIVE TARGET

INDICATION

□ If both TQs target indication are inoperative

TQ TARGET 1+2: USE TQ TABLE (Refer to

Torque Value)

77-20-01 ITT C 2 2 * Either pointer or counter may be inoperative on each indicator.

77-21-01 EXCESSIVE ITT ALERT A 2 0 * May be inoperative provided that:

(a) Associated ITT indicator is operative and

monitored throughout the flight, and

(b) Operations are limited to three calendar days.

TQ TARGET INDICATION (O)

77-60-01 INDICATION AND CONTROL ON MAINTENANCE PANELS

C - 0 May be inoperative


CH79 OIL Page 79‐1(PIA REV 2.0)

SEP, 2018


79-32-01 B 2 1 * (M) One may be inoperative provided that:

(a) The affected engine oil level is checked before the first

flight of each day, and

(b) The associated fuel temperature gauge is operative and

monitored throughout the flight, and

(c) The associated oil pressure gauge is operative and

monitored throughout the flight.

See Maintanance procedure MMP.79.32-01 Oil TEMP Indication (M)

79-33-01 OIL PRESSURE INDICATION B 2 1 * (M) One may be inoperative provided that the associated ENG OIL CAP alert is checked operative.

See Maintanance procedure MMP.79.33-01 Oil Pressure Indication (M)

79-34-01 ENG OIL CAP ALERT A 2 1 * May be inoperative provided that:

(a) Operations are limited to three calendar days, and(b) The associated pressure indicator is operative, and (c) The oil pressure is monitored throughout the flight.


ITEM

OIL TEMPERATURE INDICATION

MAINTENANCE PARTATA 21 AIR CONDITIONING MMP.21

ATA 22 AUTOMATIC FLIGHT CONTROL SYSTEM MMP.22

ATA 24 ELECTRICAL POWER MMP.24

ATA 25 EQUIPMENT MMP.25

ATA 26 FIRE PROTECTION MMP.26

ATA 27 FLIGHT CONTROLS MMP.27

ATA 28 FUEL SYSTEM MMP.28

ATA 29 HYDRAULIC SYSTEM MMP.29

ATA 30 ICE AND RAIN PROTECTION MMP.30

ATA 32 LANDING GEAR MMP.32

ATA 35 OXYGEN MMP.35

ATA 36 PNEUMATIC SYSTEM MMP.36

ATA 52 DOORS MMP.52

ATA 56 WINDOWS MMP.56

MMELMMP.

PK / 45 TOCMMEL Table of Content Page n°01

ATA 61 PROPELLERS MMP.61

ATA 73 ENGINE FUEL AND CONTROL MMP.73

ATA 77 ENGINE INDICATING MMP.77

ATA 79 OIL MMP.79

MMELMMP.

PK / 45 TOCMMEL Table of Content Page n°02

21-23-01 Overboard Valve (M)_c9d14da0-8abf-4344-9450-e16f722ac43b REV 2.1

ALL

▶ Overboard Ventilation Valve De-energizationRefer to JIC 21-23-22 DAR 10000 PART 1, setting the valve open in intermediate position.

Note▶ Avoid leaving avionics selected ON for a long period of time.

21-30-01 Pressurization System (M)_9d253ad8-5e40-4e1c-8a23-c91c4a1c5990 0.1

ALL

▶ Electropneumatic Outflow Valves Blockage in Open PositionRefer to JIC 21.31.20 DNZ 10000 .

21-31-03 Electropneumatic Outflow Valve (M)_7d3d4f46-f8f7-4688-b716-4c30dc900c11 REV 1.2

ALL

Refer to JIC 213122-DEA-10000.

21-51-01 Pack Valve (M)_005e5080-471c-4e69-bfa1-74072375cf49 REV 1.1

ALL


MAINTENANCE PARTMMP.21

PK / 45 ATA 21 AIR CONDITIONINGMMEL Page n°01

PAGE

INTENTIONALLY

LEFT BLANK


PK / 45 ATA 21 AIR CONDITIONINGMMEL Page n°02

22-16-04 Autopilot Quick Disconnect (Quick Release Control) (M)_1ddfbf8b-09e0-463c-b139-edc6ba282b19 0.1

ALL

Procedure to follow to check override means on ground:▶ AVIONICS VENT EXHAUST MODE............................... ............................... NORM▶ STICK PUSHER............................................... ............................................... OFF▶ AIR BLEEDS....................................................................................................OFF▶ RADAR..................................................... ..................................................... OFF▶ Switch WOW on Flight position, angle of attack probes positioned in normal angle of

attack. (horizontal position).▶ Engage the autopilot by pressing AP pb on FGCP .▶ Check that the AP disconnection is operative by pressing the non affected

Quick Release Control pb .Check the other AP disconnection means ( AP must be engaged before each actions ):▶ Normal pitch trim rocker on captain control wheel (nose up and nose down).▶ Normal pitch trim rocker on first officer control wheel (nose up and nose down).▶ Stand by pitch trim rockers (up and down).▶ Push, then pull on captain control wheel (repeat the same actions on first officer control

wheel).▶ Force on rudder pedals (only on a captain or first officer side) : one time left and one

time right.▶ Press on YD pb .


PK / 45 ATA 22 AUTOMATIC FLIGHT CONTROL SYSTEMMMEL Page n°01

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PK / 45 ATA 22 AUTOMATIC FLIGHT CONTROL SYSTEMMMEL Page n°02

24-22-01 ACW Generation (Generator and (or) Related GCU) (M)_458eede6-649e-441c-9106-f91c355d50a1 2.0

ALL

This procedure has to be performed before the next flight following the ACW generatorchannels fault triggering to detect a mechanical damage (bearing failure...).▶ Perform a visual inspection of the failed alternator:▶ Look for overheating and/or presence of debris/chips in the alternator-cooling outlet.▶ Check for unusual noise from the alternator by manually rotating the propeller.

■ If check satisfactory:▶ Repeat this inspection on a daily basis until the ACW generator failure is repaired.

■ If check not satisfactory:▶ Replace the failed ACW generator before flight.


PK / 45 ATA 24 ELECTRICAL POWERMMEL Page n°01

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PK / 45 ATA 24 ELECTRICAL POWERMMEL Page n°02

25-21-01 Required Cabin Attendant Seat (M)_838138ae-7284-44d6-83d9-c3fbfc2cb90b 0.1

ALL

PROCEDURE TO BE DEVELOPED IN THE OPERATOR'S MELto follow corresponding MMEL 25 conditions.

25-21-02 Non-Required Cabin Attendant Seat (M)_bbb5763e-8759-49c1-b98f-acd4224ba618 0.1

ALL


25-31-01-01 Passenger Seats (M)_5d640f44-649c-4874-82fb-9eda73fd2f8e 2.0

ALL

Identify the affected seat(s) and prohibit the use of the affected seat(s) by a placard “DO NOTOCCUPY”.Visual inspection is performed to check for any apparent sharp edge.

25-31-01-02 Passenger Seats - Underseat Baggage Restraining Bars (M)_1f1c1d02-1dc3-4b22-90b3-9df872178591 0.1

ALL

Visual inspection is performed to check for any apparent sharp edge.

25-31-01-03 Passenger Seats - Passenger Seat Armrests (M)_29f4493a-ff74-44c5-9f25-b65c6c4ed687 0.1

ALL

Recline function is checked operative.Visual inspection is performed to check for any apparent sharp edge.

25-45-01 Portable Protective Breathing Equipment (M)Portable Protective Breathing Equipment (If Applicable) (M)_69afe408-5fd3-4722-bb29-51dfc40e3451 0.1

ALL



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PK / 45 ATA 25 EQUIPMENTMMEL Page n°02

26-21-01 AGENT DISCH Light (Engine) (M)_8a68d305-478e-467f-a323-13901c4e48d4 0.1

ALL

Refer to JIC 26.21.00 CHK 10000 .

26-30-01 Hand Fire Extinguisher (M)_40cdb9c3-c5d6-4383-9f7d-40aed12a2fc5 0.1

ALL



PK / 45 ATA 26 FIRE PROTECTIONMMEL Page n°01

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PK / 45 ATA 26 FIRE PROTECTIONMMEL Page n°02

27-36-02 Stick Pusher Actuator (M)_3eecb395-eda6-41b3-85e5-034caca2bc7f 1.3

ALL

■ If control column is stuckStick Pusher Deactivation▶ Open, secure and tag C/B FLT CTL / STICK PUSHER / PWR SPLY

Stick Pusher Actuator RemovalRefer to JIC 27.36.31 RAI 10000 .

27-37-01 Pitch Elevators Coupling System (M)_51d4b7ef-4eeb-4631-85a0-76f49c83c850 2.0

ALL

■ If "PITCH DISCONNECT" warning light comes ON steady on CAP and pitch couplingsystem is disconnected in flight▶ Perform visual inspection as per (Refer to AMM 55-10-00-DVI-10000) before next flight.

■ If "PITCH DISCONNECT" warning light comes ON steady on CAP and pitch couplingsystem is disconnected on ground▶ No maintenance action is required before the Ferry Flight

■ If "PITCH DISCONNECT" warning light is flashing on CAP▶ Deactivate the elevator reconditioning device as per(Refer to AMM JIC 27.31.43 DAR

10005 ).

27-37-02 Elevators Clutch Reconditioning Device (M)_e256dacc-9552-4152-998f-fece9230b7be NEW 0.1

ALL

Refer to JIC 27.31.43 DAR 10000 .

27-61-01 Spoiler Control System (M)_fb265fd3-e2c1-44ed-85dd-15483137bdb1 0.1

ALL

Refer to JIC 27.61.00 DAR 10000 .

27-70-01-01 GUST LOCK System - Aileron (M)_e78e9311-320c-4a6e-8935-d0b577e7c1c2 1.1

ALL

Deactivation of aileron gust lock systemNoteThis task is to be performed on the both sides.

▶ Place GUST LOCK lever on "OFF" position.▶ Open, safety and tag the following breaker: FLT CTL /GUST LOCK AIL (10CE).▶ Display warning notice in the flight compartment prohibiting operation of gust lock control▶ Open access panel 533AB (633AB) then 544AB (644AB).


PK / 45 ATA 27 FLIGHT CONTROLSMMEL Page n°01

cont'd…

▶ Retract the actuator, if necessary, by means of an ALLEN KEY▶ Check the clearance (7 mm +/- 2 mm) between the cam and the rocking lever▶ Close C/B 10CE and make sure that gust lock actuators do not engage inadvertently.▶ Open, secure and tag C/B 10CE .▶ Make certain that working area is clear and clean of tools and miscellaneous items▶ Close access doors▶ Remove warning notice in the flight compartment▶ Place GUST LOCK lever on "ON" position.▶ Rotate PILOT HANDWHEEL to the right to reach aileron stop▶ Install tool P/N S0003024900000 between the PILOT HANDWHEEL and the STEERING

HANDWHEEL

Note▶ The tool shall be removed and stored before leaving the parking; the ailerons shall

be kept on the stops manually during the taxiing operations.

Perform a daily inspection of Aileron hinge fitting stops (on RH and LH )▶ Install notice prohibiting operation of flight controls in flight compartment.▶ Install access platform.▶ Remove fairing 555AB or 655AB according to aileron to be inspected.

Note▶ LH and RH wings aileron hinge fitting stops must be inspected.

▶ Manually move the aileron until reaching the upper stop.▶ Perform a Detailed Visual Inspection of aileron center fitting, aileron control fitting and

lower stop as per Refer to NDTM 51-90-00 . In case of findings, contact ATR prior anyaction.

▶ Manually move the aileron until reaching the lower stop.▶ Perform a Detailed Visual Inspection of aileron center fitting, aileron control fitting and

upper stop as per Refer to NDTM 51-90-00 . In case of findings, contact ATR prior anyaction.

▶ Install fairing 555AB or 655AB.▶ Remove warning notices and access platform.



cont'd…

cont'd…

27-70-01-02 GUST LOCK System - Elevator (M)_c3332d43-1a4f-4792-aea9-5c6cd1180c3a 0.1

ALL

▶ Perform a daily inspection of elevator hinge fitting stops (on RH and LH )▶ Install notice prohibiting operation of flight controls in flight compartment.▶ Install access platform.▶ Remove access panels 333CB and 343CB.▶ Maintain elevators in full nose up position (trailing edge upward).▶ Perform a Detailed Visual Inspection of elevators inboard hinge fittings and stops as per

Refer to NDTM 51-90-00 . In case of findings, contact ATR prior any action.▶ Install access panels 333CB and 343CB.▶ Remove warning notices and access platform.



cont'd…

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28-21-02 Electrical Fuel Pump (M)_9c7aaae8-a5ee-4383-a8e8-2bcfb15a4cbe REV 2.2

ALL

Open, secure and tag C/B FUEL / FUEL FEED / ENG 1 (2) / ELEC PUMP (121 VU).

28-25-01-01 Refueling Control Panel - Refueling Control Panel (M)Refueling Control Panel - Refueling Control Panel (M)_99a64439-8dc8-46f3-a74c-eb6824519201 0.2

ALL

Gravity RefuelingRefer to JIC 12-11-28 FLG 10000.

28-25-01-02 Refueling Control Panel - Fuel Preselector (M)_5501a39e-3cb5-4827-b8b6-3f70f149d1d7 1.2

ALL

Manual RefuelingRefer to JIC 12-11-00 FLG 10025.

28-25-02 Pressure Refueling Cap (M)_793ec7bd-bb6d-4efa-94e7-1e7adf9d02b4 0.1

ALL

PROCEDURE TO BE DEVELOPED IN THE OPERATOR'S MELTo be defined by operator to follow corresponding MMEL 28 conditions.

28-42-01 Fuel QTY Indication (M)_46e901b1-b423-4ec2-a229-8631d6772404 2.0

ALL

Refer to JIC 12-1100 FLG 10025 for manual refueling.Refer to JIC 12-11-28 CHK 10000 for checking fuel level using manual (magnetic) indicators.Refer to JIC 28-42-72 FUT 10020 (FUNCTIONAL TEST OF FEEDER TANK LOW LEVELSENSOR) to check the opposite side Fuel LO LVL alert.

28-42-03 Fuel LO LVL Alert (M)_22f45eed-a07f-427b-9a34-89c33e35d405 0.1

ALL

Refer to JIC 12-11-28 CHK 10000 for checking fuel level using manual (magnetic) indicators.Refer to JIC 28-42-72 FUT 10020 (FUNCTIONAL TEST OF FEEDER TANK LOW LEVELSENSOR) to check Fuel LO LVL alert on opposite side.


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PK / 45 ATA 28 FUEL SYSTEMMMEL Page n°02

29-11-01 Main HYD Pump (M)_ab380eee-7d0a-44f3-a7ee-b1be718dd591 0.1

ALL

Refer to JIC 290000 CHK 10000 to check the level of hydraulic fluid.


PK / 45 ATA 29 HYDRAULIC SYSTEMMMEL Page n°01

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PK / 45 ATA 29 HYDRAULIC SYSTEMMMEL Page n°02

30-31-03 Alert (M)_3bf43848-129e-4600-aff1-2c382e47b3ea 0.1

ALL

Refer to JIC 341111CHK10000 to check pitot probes heating resistance.

30-80-01 Ice Detection System (M)_8a280089-2d57-48bd-9dff-ca41ec409075 0.2

ALLEASA - APPROVED

▶ Pull C/B ANTI/DE ICING/ ICE DET, secured and tagged.


PK / 45 ATA 30 ICE AND RAIN PROTECTIONMMEL Page n°01

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PK / 45 ATA 30 ICE AND RAIN PROTECTIONMMEL Page n°02

32-42-01 Wheel Brake (M)_1abbd2d4-76b3-4cc1-a600-997e570457bc 0.1

ALL

For deactivation, Refer to JIC 32.42.50 REM 100000 .For removal, Refer to JIC 32.42.55 RAI 10000 .


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PK / 45 ATA 32 LANDING GEARMMEL Page n°02

35-20-03 Passenger Service Unit (M)_759795e3-377e-49ff-9656-157216075fdb 0.1

ALL


35-35-01 Potable Oxygen Bottle (M)_0d1f4bb8-0268-45e2-a0f8-eccbc218d5c9 0.1

ALL



PK / 45 ATA 35 OXYGENMMEL Page n°01

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PK / 45 ATA 35 OXYGENMMEL Page n°02

36-11-01 HP Valve (M)_3a543cb7-7d35-4c6a-bbc9-a0dfa8532991 REV 2.2

ALL


36-11-02 BLEED Valve (M)_072d6b42-fa3d-4d82-b2c4-e09a02a9a4f6 REV 1.2

ALL

Refer to JIC 361162-DEA-10000

36-11-04 Ground X Feed Valve (M)_4a428ad2-c6c5-4b4a-ad1c-a513435a0a79 REV 2.2

ALL


36-11-05 Ground X FEED VALVE OPEN Alert (M)_32836591-804b-4c2b-91e4-0c99cf71c337 0.1

ALL

Check of crossfeed valve:Location: under passenger compartment, access doors 231DF and 231EF.

▶ Open, safety and tag the following circuit breaker on panel 121VU: 33HA AIR BLEED/XFEED.

▶ Open access doors 231DF and 231EF.▶ Check that mechanical indicator shows closed.▶ Close access doors.▶ Install placard.


PK / 45 ATA 36 PNEUMATIC SYSTEMMMEL Page n°01

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PK / 45 ATA 36 PNEUMATIC SYSTEMMMEL Page n°02

52-11-01 Door Alert System (M)_903169b9-1c9d-48ec-b8ef-9be412397f77 0.1

ALL

▶ Check that flight compartment overhead hatch is closed:

▶ Manually operate handle to ensure the shoot bolt operates normally.▶ Close and latch the hatch.▶ Verify the handle is flush in the closed position.

52-31-01 Cargo Door Motor Actuator (if installed) (M)_2f1320b2-1f49-48c5-b8f2-7e37153dd67d 0.1

ALL

Refer to JIC 52.31.00 OAC 10010 .

52-31-03 AUX AFT Cargo Door (Class C) (if installed) (M)_9252df6d-cda0-4ca2-bb8c-0765699ad6b3 0.1

ALL



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PK / 45 ATA 52 DOORSMMEL Page n°02

56-11-01 Windshield (Including Main Windshield, FWD and AFTWindows) (M)_7994d8cc-8ab8-4d82-a4ae-88a6c91614a9 REV 1.2

ALL

Refer to SRM 56.10.00

56-21-01 Passenger Compartment Window (M)_7014e4d1-e26f-4ab5-b9ba-d4376f27f035 0.1

ALL

Refer to SRM 56.21.00


PK / 45 ATA 56 WINDOWSMMEL Page n°01

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61-42-01 NP Indications (M)NP Indicator (M)_a2d2d5b9-7434-4337-8bcd-70a5ff8ad40d 0.1

ALL

Refer to JIC 30.61.00 OPT 10010 to check PROP anti-icing is operative.

61-50-01 Propeller Brake (M)_16596579-b13e-4857-b280-ed0a5b5119eb 0.1

ALL

Refer to JIC 61.51.67. DNZ 10000 .


PK / 45 ATA 61 PROPELLERSMMEL Page n°01

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PK / 45 ATA 61 PROPELLERSMMEL Page n°02

73-15-01 Fuel Heater (M)_aac38c02-1445-4e54-b369-8ca32a41d4cb REV 2.2

ALL

■ If TOO LOW TEMPFuel anti icing additive for all fuel (JET A, JET A1, JP5, RT, TS1):

To be added in compliance with Engine Maintenance Manual (Refer to EngineMaintenance Manual 72-00-00 Table 9).

Check of oil level:▶ Open left hinged cowl (435AL or 445AL).▶ Check that oil level is to “FULL”.▶ Close cowl(s).


PK / 45 ATA 73 ENGINE FUEL AND CONTROLMMEL Page n°01

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PK / 45 ATA 73 ENGINE FUEL AND CONTROLMMEL Page n°02

77-00-02 AFU (M)_b252952d-9060-49a8-ad89-178a93850faf 0.1

ALL

This task is performed to deactivate the AFU and then to avoid an untimely autofeatherin flight:▶ Open " C/B ENG CTL/ENG 1 (2) / AFU "▶ Open " C/B ENG CTL/ENG 1 (2) / FEATH CTL & AFU "▶ Open nacelle cowling left side.▶ Disconnect AFU connector▶ Secure and cap electrical connectors.▶ Close nacelle cowling.▶ Close C/B .

77-13-01 TQ Indications (M)TQ Indicator (M)_b26003ed-386e-45d4-90a2-0d9884d87e64 REV 1.0

ALL

▶ In case of dashes (---) on counter, check that no EEC fault code 39 ( HBV ) is recorded.Dispatch with inoperative HBV is not allowed.


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PK / 45 ATA 77 ENGINE INDICATINGMMEL Page n°02

79-32-01 Oil TEMP Indication (M)_f348196e-0287-41fa-90c0-f7a0fa5dda5b 0.1

ALL

Refer to JIC 12.13.79 CHK 10000

79-33-01 Oil Pressure Indication (M)_7d0e2028-dd38-4874-b89b-ae58b01d1832 0.1

ALL

Refer to JIC 79.34.00 OPT 10000


PK / 45 ATA 79 OILMMEL Page n°01

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PK / 45 ATA 79 OILMMEL Page n°02

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