minimum equipment list - crewserver1.piac.com.pk

MINIMUM EQUIPMENT LIST

ATR75

ISSUED BY

OPERATIONS ENGINEERING TECHNICAL DIVISION FLIGHT OPERATIONS PAKISTAN INTERNATIONAL FOD I TECH/ ATR75/ MEL I 01 SEP/2018 (NOT VALID FOR ETOPS AND CARGO CONFIGURATION)

INTENTIONALLY LEFT BLANK

ATA SYSTEM / DESCRIPTION PAGE DATE

LIST OF EFFECTIVE PAGES I / II JUN 2020

OPERATIONS ON NARROW RUNWAY III JUN 2020

APPLICABILITY PAGE IV JUN 2020

1 JUN 2020

2 JUN 2020

3 JUN 2020

4 JUN 2020

5 JUN 2020

6 JUN 2020

7 JUN 2020

8 JUN 2020

9 JUN 2020

21-1 JUN 2020

21-2 JUN 2020

21-3 JUN 2020

21-4 JUN 2020

21-5 JUN 2020

21-6 JUN 2020

22 AUTOMATIC FLIGHT CONTROL SYSTEM 22-1 JUN 2020

22-2 JUN 2020

22-3 JUN 2020

23-1 JUN 2020

23-2 JUN 2020

23-3 JUN 2020

23-4 JUN 2020

24-1 JUN 2020

24-2 JUN 2020

24-3 JUN 2020

24-4 JUN 2020

25-1 JUN 2020

25-2 JUN 2020

25-3 JUN 2020

25-4 JUN 2020

23 COMMUNICATIONS

PAKISTAN INTERNATIONAL AIRLINES MINIMUM EQUIPMENT LIST ATR75

INDEX/LIST OF EFFECTIVE PAGES (PIA REV 3.0)

PREAMBLE

21 AIR CONDITIONING

24 ELECTRICAL POWER

25 EQUIPMENT

25-4 JUN 2020

26-1 JUN 2020

26-2 JUN 2020

27-1 JUN 2020

27-2 JUN 2020

27-3 JUN 2020

27-4 JUN 2020

27-5 JUN 2020

27-6 JUN 2020

28-1 JUN 2020

28-2 JUN 2020

28-3 JUN 2020

28-4 JUN 2020

28-5 JUN 2020

29 HYDRAULIC SYSTEM 29-1 JUN 2020

29-2 JUN 2020

30-1 JUN 2020

30-2 JUN 2020

30-3 JUN 2020

30-4 JUN 2020

31 INSTRUMENTS 31-1 JUN 2020

31-2 JUN 2020

31-3 JUN 2020

31-4 JUN 2020

31-5 JUN 2020

31-6 JUN 2020

31-7 JUN 2020

32 LANDING GEAR 32-1 JUN 2020

32-2 JUN 2020

33-1 JUN 2020

33-2 JUN 2020

33-3 JUN 2020

33-4 JUN 2020

FIRE PROTECTION

27

26

FUEL SYSTEMS

30 ICE AND RAIN PROTECTION

FLIGHT CONTROLS

33 LIGHTS

28

PAGE - I / JUN 2020

ATA SYSTEM / DESCRIPTION PAGE DATE

34-1 JUN 2020

34-2 JUN 2020

34-3 JUN 2020

34-4 JUN 2020

34-5 JUN 2020

34-6 JUN 2020

35 OXYGEN 35-1 JUN 2020

35-2 JUN 2020

36 PNEUMATIC SYSTEM 36-1 JUN 2020

52 DOORS 52-1 JUN 2020

52-2 JUN 2020

52-3 JUN 2020

56 WINDOWS 56-1 JUN 2020

61 PROPELLER 61-1 JUN 2020

61-2 JUN 2020

61-3 JUN 2020

61-4 JUN 2020

73 ENGINE FUEL AND CONTROL 73-1 JUN 2020

73-2 JUN 2020

74 IGNITION 74-1 JUN 2020

75 AIR 75-1 JUN 2020

77 ENGINE INDICATING 77-1 JUN 2020

77-2 JUN 2020

79 OIL 79-1 JUN 2020

MMP (MAINTENANCE PART) Extracted from MMEL- 01-Dec

MMP (PIA ESTABLISHED MAINTENANCE

PROCEDURES)PIA MMP-1 Jun-20

NAVIGATION34

PAKISTAN INTERNATIONAL AIRLINES MINIMUM EQUIPMENT LIST ATR75

INDEX/LIST OF EFFECTIVE PAGES (PIA REV 3.0)

CAA APPROVAL NO. HQCAA/ DATED CAA APPROVAL NO. HQCAA/ DATED

PAGE - II / JUN 2020

(PIA Rev.3.0 as per DGAC approved MMEL Revision No 4.0 dated DEC 2019)

Ali Raza

Typewritten text

Ali Raza

Typewritten text

1076/021/FSAC/0944

Ali Raza

Typewritten text

06 JUL 2021

PAGE III ISSUED BY: OPERATIONS ENGINEERING JUN /2020

ATR75

OPERATIONS ON NARROW RUNWAY ________________________________________________________________ Runway having width less than 30 meters (98 ft) is defined as “NARROW RUNWAY”. Presently PIA ATR75 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 VI ISSUED BY: OPERATIONS ENGINEERING JUN/2020

ATR75

APPLICABILITY PAGE ________________________________________________________________ This page shows, for each ATR75 aircraft, the cross reference between

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

M.S.N REGISTRATION NUMBER

1000 AP – BKV 1037 AP – BKX 0994 AP – BKY 1029 AP – BKZ

This MEL is applicable to all the above aircraft.

Minimum Equipment List

JUN/2020________________________________________________ ___

Operations Engineering Page 1 of 9

PREAMBLE 1. GENERAL

1.1 The PCAA 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 the FAA/DGAC 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 PCAA. An operator’s MEL may differ in format

from the MMEL, but cannot be less restrictive than the MMEL. Based on the respective aircraft configuration, the operator will develops its own MEL and submit the same to DG PCAA 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 PCAA 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 equipments related to the airworthiness and the operating regulations of the aircraft not listed on the MMEL must be

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.


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Page 2 of 9 Operations Engineering

1.3 The MEL is intended to permit operation with inoperative items of equipment for a period of time until repairs can be 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 / Technical Log. 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 Dispatch/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. Dispatch/Release of airplane with more than one part missing from any one system is not allowed unless

specifically indicated in DDG/DDPG/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 DISPATCH OR NOT, contact Chief Pilot Technical (Operations) and Chief Engineer Quality Assurance

or their representatives for advice on telephone at Karachi. 1.6 WHEN USING THE MEL, COMPLIANCE WITH THE STATED INTENT

OF THE PREAMBLE, DEFINITIONS, THE CONDITIONS AND 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 FAA / DGAC – Master Minimum Equipment List copy of

which is attached as Annexure-1 to this Preamble.


JUN/2020________________________________________________ ___


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 & 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 Technical Log Slip. 3. RELEASE OF AIRCRAFT FROM MAINTENANCE BASE (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 efforts 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 A, B, C & D) is exceeded. 3.3 The Allowable Technical Deficiency Information will be sent to

stations along the route. The information shall be recognized by a standard prefix “AATD” (Aircraft Allowable Technical Deficiency),

Flt. No. and Aircraft Registration. This will always be sent by Manager Central Control, MCC.

3.4 For defects those are CF ex-base (Karachi or Islamabad as applicable) the status report will be sent to Flight Standards

Directorate, PCAA 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


JUN/2020


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 designated nominees. 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 then this is to be brought to

the notice of PCAA, Director Flight Standards (DFS) or his nominees by the Director Flight Operations (DFO) or Director Engineering &

Maintenance (DE&M) 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 PCAA.

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

period limitations given in MEL (in form of A, B, C & D) is NOT

covered under this authorization.

5. RELEASE OF AIRCRAFT WITH MEL COVERED DEFECTS ON EXPIRY OF TIME PERIOD LIMITATIONS GIVEN IN MEL

If repair interval requires more time than as described in relevant category of that particular inoperative system(s) or component(s),

deferred in accordance with the MEL, waiver from PCAA (Director Flight Standards or his nominees) shall be obtained. The waiver

shall be initiated by Engineering & Maintenance Department on a prescribed form and shall be signed by Director Engineering & Maintenance or his nominee then subsequently signed by Director

Flight Operations and or his nominee.

6. CREW RESPONSIBILITIES 6.1 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.

6.2 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.

6.3 The Pilot – in – Command will ensure that the appropriate crew

members are properly acquainted with any revision of procedures,

duties or limitations.


JUN/2020________________________________________________ ___


6.4 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 Headquarter. 6.5 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.

7. BALLAST: Only non-combustible material may be used as ballast.

(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 (If possible), the MEL must reflect the actual number

installed or an alternate means of configuration control approved by the DFS/DAW (PCAA)

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.

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.


JUN/2020


2. “Airplane Flight Manual” (AFM) is the document required for type

certification and approved by the responsible FAA/DGAC Aircraft Certification Office. The FAA/DGAC approved AFM for the specific

aircraft is listed on the applicable Type Certificate Data Sheet. 3. “As required by FAR/JAR” means that the listed item is subject to

certain provisions (restrictive or permissive) expressed in the FAR/JAR operating rules. The number of items required by the

FAR/JAR must be operative. Items installed that are in excess of the FAR/JAR 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 crewmembers and maintenance personnel of 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 (If Possible) or an

alternate means of configuration control approved by the DFS/DAW (PCAA).

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. “ER” refers to extended range operations of a two-engine airplane, which has a type design approval for ER operations and complies

with the provisions of Advisory Circular 120-42. Refer applicable circular by C.P. TECH.

8. “Federal Aviation Regulations” (FAR) means the applicable portions of the Federal Aviation Act and Federal Aviation Regulations.

9. “Joint Aviation Regulations” (JAR) means the applicable portions of

the Joint Aviation Act and Joint Aviation Regulations.

10. “Flight Day (Calendar Day)” means a 24 hour period (from

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

11. “Icing Conditions” means an atmospheric environment that may

cause ice to form on the aircraft or in the engine(s).


JUN/2020________________________________________________ ___


12. Alphabetical/Numerical symbol in column 4 indicates provisos (condition or limitation) that must be complied with for operation

with the listed item inoperative. 13. “Inoperative” means a system and/or component malfunctions 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. 14. “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 a part of the provisos.

15. 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 the inoperative system must be operative

unless relief is specifically authorized as per the MMEL).

16. “(M)” or “(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 Airline. Appropriate procedures are published

as part of the MEL as a separate section with name “MMP (MAINTENANCE PART) Extracted from MMEL.” In these procedures

where PIA established procedure is required to be used, “PIA established Maintenance procedure” part of this MEL is to be referred.

17. “(O)” or “(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 Airline. Appropriate procedures are published as part of the MEL.

Maintenance (M) and Operations (O) procedures are provided in MEL.


JUN/2020


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

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

20. “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.

21. “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.

22. “Passenger Convenience Items/Non Essential Equipment & Furnishing,(NEF)” 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.

23. A flight operated over water at a distance of more than 93 km ( 50

Nm ), or 30 min at normal cruising speed, whichever is the lesser,

away from land suitable for making an emergency landing, Refer to

ICAO Annex 6 parts II .

24. Not Applicable: means that item is not installed on PIA fleet or item is not applicable to PIA fleet.

25. Repair intervals: All users of an MEL approved under PCAA ANO-

007-FSXX-4.0 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:

Note: The letter designators are inserted adjacent to column 2.

CATEGORY A

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

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 were recorded at 10 am on January 26th, the three-day interval

would begin at midnight the 26th and end at midnight the 29th.


JUN/2020________________________________________________ ___


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 were recorded at 10 am on January 26th, the ten-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

log and/or record.

26. CCAS provides electronic massages refer to a system capable of providing different priority levels of system information messages (e.g. Warning, Caution, Advisory Status, and Maintenance). Any

airplane discrepancy message that affects dispatch ability will normally be at status message level (e. g. Advisory Status) or

higher.

27. Engine Indicating Crew Alerting System (EICAS), Electronic

Centralized Aircraft Monitoring System (ECAM) or similar systems that provide electronic messages refer to a system capable of

providing different priority levels of systems information messages (e.g. Warning, Caution, Advisory Status, and Maintenance). Any

airplane discrepancy message that affects dispatchability will normally be at status message level (e.g. Advisory Status) or higher.

28. “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 Chief Pilot 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 (PCAA). If the request results in review

and approval by the PCAA, the item becomes an MEL item rather than an administrative control item.

29. “Day of Discovery” is the calendar day an equipment / instrument

malfunction was recorded in the aircraft maintenance log and or

record. This day is excluded from the calendar days or flight days specified in the MMEL for the repair of an inoperative item of

equipment. This provision is applicable to all MEL items, i.e. categories “A, B, C, and D”.

PIA ATR 75 MINIMUM EQUIPMENT LIST

CH21 AIRCONDITIONING

Page 21-1(PIA REV 3.0)

JUN, 2020

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 VALVE

21-23-01A 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 FL170, 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)

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 comes 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.

MINIMUM FOR DISPATCH

ITEM

STANDARD EQUIPMENT




JUN, 2020



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

CONFIGURATIONNot Applicable

21-23-03P

Note

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

On ground only with aircraft network energized, the mechanic

ground call system is activated as extract fan is inoperative.

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 that:

(a) No combustible material is carried in any compartment.

(b) Outflow valves are 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 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

EXTRACT FAN -

PASSENGER

CONFIGURATION (O)

1PRESSURIZATION

SYSTEM - PASSANGER

CONFIGURATION

0C The pressurization system (automatic and manual modes) may

be inoperative for a non pressurized flight provided that outflow

valves are secured in open position if manual mode is

inoperative.

EXTRACT FAN -

PASSENGER

CONFIGURATION

● Select exhaust mode OVBD.

PRESSURIZATION SYSTEM

(O)




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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 6700

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

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) 4.8 5.4 5.8 5.9 6 6.35

21-31-04-02 CABIN PRESS

INDICATION - RATE


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)


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 6700

ALT (FT)

C21-31-03 ELECTROPNEUMATIC

OUTFLOW VALVE

1

1 0

AUTOMATIC

PRESSURIZATION

CONTROL

C21-31-01 0




JUN, 2020



ITEM

STANDARD EQUIPMENT

21-31-04-03 CABIN PRESS Indication -

Pressure


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)


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 6700

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 needed:

● MAN RATE knob………...……...…….…..MAN

● CAB PRESS MODE SEL ……...….…….MAN

● MAN RATE KNOB……...…MAX INCREASE

Note

Residual ∆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)



-5(PIA REV 3.0)

JUN, 2020



ITEM

STANDARD EQUIPMENT

21-51-01P PACK VALVE (O) As an in-flight failure could imply total loss of pressurization, fuel


the trip fuel.

Note


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


the trip fuel.

Note


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.

21-51-05 AUX AFT CARGO

VENTILATION VALVE

C 1 0 * May be inoperative provided that no combustible material is

carried in the associated compartment.

21-61-01 PACK AUTO

TEMPERATURE 21-61-01 A (A) C 2 1 * (O) One may be inoperative provided 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● 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

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

temperature control is operative. -OR-

TURBO FAN C

PACK AUTO

TEMPERATURE

CONTROL (O)

02




JUN, 2020



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 INDICATION

21-63-02A (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.

21-61-03 OVHT ALERT C 2 1


CH22 AUTOMATIC FLIGHT CONTROL SYSTEM


JUN, 2020


22-15-01 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 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 * (O) One or both may be inoperative.

See Operational procedure MOP.22.16-02P Touch Control Steering

(TCS) (O)

22-16-02P □ 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)

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 FUNCTION

22-18-01A Not Applicable

-OR-

ITEM

PITCH WHEEL

ADVISORY DISPLAY UNIT

(ADU) (O)


May be inoperative provided that one TCS is operative.1

STANDARD EQUIPMENT

C22-16-01 0

ETOPS Operations (A)

2C

ADVISORY DISPLAY UNIT

(ADU)

TOUCH CONTROL STEERING

(TCS) (O)

0




JUN, 2020


22-18-01B (B) B 1 0 * May be inoperative provided that ETOPS Operations are not conducted.

Note

1) Any mode which is operative may be uesd.

2) If AFCS Computer is inoperative Autopilot, Yaw

Damper, and Flight Director functions are lost.

Refer to Item 22-18-02 Flight Director Function

Refer to Item 22-18-03 Yaw Damper Function

22-18-02 C 1 0 * (O) May be inoperative.

Note

1) Any mode which is operative may be used.

2) If AFCS computer is inoperative Autopilot,

Yaw Damper,and Flight Director functions are lost.

Refer to Item 22-18-01 Autopilot Function

Refer to Item 22-18-03 Yaw Damper Function

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

22-18-02P □ If ASCB bus is lost, in addition to AFCB loss

VOR and ADF bearings display on the opposite side CRT,s are lost when

using EFIS reversion mode.

22-18-03 YAW DAMPER FUNCTION

22-18-03A RCU INOPERATIVE (A) A 1 0 * (O) May be inoperative provided that operations are limited to two flights.

Note

1) The Autopilot is inoperative Refer to Item 22-18-01

Autopilot Function.

2) If AFCS Computer is inoperative Autopilot,

Yaw Damper, and Flight Director functions are lost.


See Operational procedure MOP.22.18-03P Yaw Damper Function (O)

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

Note1) The Autopilot is inoperative Refer to Item 22-18-01

Autopilot Function.

2) If AFCS Computer is inoperative Autopilot,

Yaw Damper, and Flight Director functions are lost.


22-18-03P □ If RCU is inoperative

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

22-36-01 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)

YAW DAMPER FUNCTION (O)

FLIGHT DIRECTOR

FUNCTION

MODE ANNUNCIATOR (EADI)

FLIGHT DIRECTOR

FUNCTION (O)

STANDARD EQUIPMENT MINIMUM FOR DISPATCH

ITEM




JUN, 2020


22-36-02P □ 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

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 LIGHT

22-36-03A ETOPS OPERATIONS (A) Not Applicable

-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.22.18-01 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 PEW R 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

CHECK ASSOCIATED ALERTS

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

● STICK PUSHER pb…………….………..…….……..ON

● AIR BLEEDS ……………………………....….………ON

● RADAR ……………………………....….………AS RQD

22-36-04 GUIDANCE LIGHT Not Applicable

0-

AUTOPILOT DISCONNECT

AURAL ALERT (O)

May be inoperative.


ITEM


CONTROLS ON

MAINTENANCE PANELS

C


CH23 COMMUNICATIONS


JUN, 2020


23-11-01 HF SYSTEM - 1 1 Must be operative.

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.

Note

For 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:


(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:




1C 2

STANDARD EQUIPMENT

ITEM

(A)


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


Transfer switch

C 2 0 May be inoperative


Selector knob

C 2 1


Indication

C 2 1

23-22-01 SELCAL NOT APPLICABLE

23-24-01 ACARS NOT APPLICABLE

May be inoperative provided that frequency indication associated to

VHF 1 must be operative.

May be inoperative provided that frequency selector knob associated

to VHF 1 must be operative.


CH23 COMMUNICATIONS


JUN, 2020


MINIMUM FOR DISPATCH STANDARD EQUIPMENT

ITEM

* (O) May be inoperative provided that:

(a) Magaphone must be serviceable and used by Cabin attendants.

(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 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.


FLIGHT DECK TO FLIGHT

DECK

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

Hand Microphone

23-44-01-03 B 1 0 * (O) May be inoperative provided that:

(a) Passenger Address is operative, and

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

INTERPHONE SYSTEM

(FLIGHT DECK TO CABIN -

CABIN TO FLIGHT DECK )

PASSENGER ADDRESS

SYSTEM - Cargo Configuration

0A 1PASSENGER ADDRESS

SYSTEM - Passenger

Configuration

23-31-01-01


operate normally.

(C) Flight deck door automatic locking system 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 May be inoperative provided that:



operate normally.


CABIN TO CABINC 1 0 * (O) May be inoperative provided Operational procedure is fallowed.

See Operational provedure MOP.23.44-01P Interphone System Cabin to

Cabin (O)


CABIN TO CABIN (O)

May be inoperative provided passanger address system operates

normally and cabin crew is briefed accordingly.


INTERPHONE SYSTEM



(O)


CH23 COMMUNICATIONS


JUN, 2020



ITEM

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)

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.


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 stations may be inoperative.

-OR-

23-44-01-07B (B) C 1 0 * (O) 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)


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


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.

0C 123-44-02 CABIN CHIME SYSTEM


SEAT BELT AND SMOKING

SIGNS)


CH23 COMMUNICATIONS


JUN, 2020



ITEM

One may be inoperative provided that the associated boom set

(headset function) is operative for 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.

*

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

2 0

1 1

2 1

C

C

C

HEADSET

COCKPIT LOUDSPEAKER

BOOM SET

May be inoperative.

-

0

0

3

2

2C

C

23-71-01 COCKPIT VOICE RECORDER

23-50-05

23-50-03 HAND MICROPHONE

23-51-01 PUSH-TO-TALK (PTT)

SWITCH ON WHEEL

23-50-02

23-50-04


CH24 ELECTRICAL POWER


JUN, 2020


* 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)

See Maintenance procedure MMP.24.22-01 ACW Generation (Generator and

(or) Related GCU ) (M)

STANDARD EQUIPMENT

ITEM

24-21-01 AC INVERTER

ACW GENERATION

(GENERATOR AND (OR)

RELATED GCU)

0


0

A 2

B

1

C 2

1

24-22-01P ACW GENERATION

(GENERATOR AND (OR)

RELATED GCU) (O)

Refer To AFM-DEV.2.2.01.1 Dispatch with One ACW Generstor

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 (BTC) (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

ACW GENERATION BUS

TIE CONTACTOR (BTC)

One may be inoperative provided that ACW BTC operates normally.1C 224-22-02 ACW GEN FAULT ALERT

ACW GENERATION BUS

TIE CONTACTOR (BTC) (O)




JUN, 2020


STANDARD 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 ELEC PWR panel (29VU)

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

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

On MAIN ELEC PWR panel● Check that the following cau6on lights are switched ON:

1) BATTERY ARROWS,

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,

24-30-01 DC GENERATION

(GENERATOR AND (OR)

RELATED GCU)

One or both may be inoperative.

1A 2

0C 224-22-04 ACW BUS OFF ALERT

DC GENERATION

(GENERATOR AND (OR)

RELATED GCU) (O)

- VHF 1,

- FUEL QTY indicator ,

- FLAPS POSITION indicator

On MAIN ELEC PWR panel

● 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 s6ll supplied:

- VHF 1,

- FUEL QTY indicator ,

- FLAPS POSITION indicator

On MAIN ELEC PWR panel

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 lights are switched ON.

Note

After the test, the flight crew must set operative DC GEN to ON

position.




JUN, 2020


STANDARD EQUIPMENT

ITEM


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 DC TRANSFORMER

RECTIFIER UNIT (TRU) (O)

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

● 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

* One may be inoperative provided that DC Bus Tie Contactor is

operative.

1C 224-32-01 DC GEN FAULT ALERT




JUN, 2020


STANDARD EQUIPMENT

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 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 Electrical Power Indicator

(Left Hand Panel)

C 1 0 May be inoperative.


CONTROLS ON

MAINTENANCE PANELS


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

DC GENERATION BUS TIE

CONTACTOR (BTC) (O)

24-32-02 DC GENERATION BUS TIE

CONTACTOR (BTC)

MAINTENANCE PANELS


CH25 EQUIPMENT


JUN, 2020


25-11-01 B 2 0 * 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 visual restrictions

to the flight crew.

25-13-15 SEAT POSITION SINGHT

GAUGE (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 station.

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


25-21-01 1REQUIRED CABIN B 2

STANDARD EQUIPMENT

ITEM

FLIGHT CREW SEAT -

VERTICAL AND RECLINE

ADJUSTMENTS

* (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.

Note

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


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)

25-21-01 1REQUIRED CABIN

ATTENDANT SEAT

B 2


CH25 EQUIPMENT


JUN, 2020



ITEM

25-21-01P One seat or seat assembly may be inoperative, provided that :

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



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

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:




seat most suitable to the crew, 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


NON-REQUIRED CABIN

ATTENDANT SEAT

REQUIRED CABIN

ATTENDANT SEAT (O)


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)

25-21-02P One seat assembly may be inoperative provided that:


(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 access to

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.

NON-REQUIRED CABIN

ATTENDANT SEAT (O)


CH25 EQUIPMENT


JUN, 2020



ITEM

Note

A seat with an inoperative or missing seat belt is

considered inoperative .

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

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 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)

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

GALLEY WAST

COMPARTMENT FLAPPER

DOOR

PASSENGER SEAT -

PASSENGER SEATS

ARMRESTS

introduction into compartment.

See Operatinal procedure MOP.25.33-01P Galley Wast Compartment

Flapper Door (O)

25-33-01P GALLEY WAST

COMPARTMENT FLAPPER

DOOR (O)

Cabin attendants to physically eusure that sufficient galley wast

receptacles are available to accommodate all wast that may be

generateed on a flight.

25-40-01 CABIN FLASHLIGHT Each Crew member (cockpit and cabin) shall carry a Flashlight, 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 * May be inoperative provided that:

(a) Toilet wast receptacle is empty, and

(b) Toilet door is closed locked and placarded,

INOPERATVE DO NOT ENTER.

LAVATORY WAST

COMPARTMENT FLAPPER

DOOR


CH25 EQUIPMENT


JUN, 2020



ITEM

Note

Tiolet may be used and/or inspected by crew members

25-50-01 VIDEO SYSTEM IN CABIN

25-50-01A (A) D 1 0 * (O) (M) May be inoperative provided that:

(a) All screen are checked locked in up position for the

flight, and

(b) Operational porcedure is followed uesd for pax briefing.

See Operatinal procedure MOP.25.50-01P Vedio System in Cabin (O)

See Maintenance procedure MMP.25.50-01 Vedio System in Cabin (M)

-OR-

25-50-01B (B) D 1 1 Individual screens way be inoperative provided cabin crew will do pax

briefing

25-50-01P VIDEO SYSTEM IN CABIN Passenger address system is used by cabin crew for pax briefing.

25-54-23 CARGO RESTRAINT SYSTEM D 5 0 * May be inoperative or missing provided relevant section of the cargo

compartment remains empty.

25-60-01 ELT-EMERGENCY LOCATOR

TRANSMITTER

2 2 Both must be Operative

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

25-64-01 CRASH AXES OR

CROWBARS

1 1 Part of Emergency Equipment

CROWBARS

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


CH26 FIRE PROTECTION


JUN, 2020


*

One or both may be inoperative.

26-12-03 ENG 2 NAC OVHT C 1 0 * May be inoperative provided that hotel mode operation is limited

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 CONFIGURATIONNOT APPLICABLE

26-15-05 AUX AFT COMPT AGENT

DISCH LIGHTNOT APPLICABLE

26-15-06 AUX AFT CARGO BOTTLE

EXTINGUISHERNOT APPLICABLE

26-17-01-01

26-17-01-01A (A) C 1 0 * May be inoperative provided that:

26-12-02 FUEL SO LIGHT

(INTEGRATED IN CL)

C 2

TOILET SMOKE DETECTION

SYSTEM - PASSENGER

CONFIGURATION


3 One may be inoperative provided that the affected loop is

selected OFF.

STANDARD EQUIPMENT

*

ITEM

26-12-01 FIRE DETECTION LOOP C 4

0

C 1 0 * May be inoperative provided that:

(a) Toilet waste receptacle is empty, and

(b) Toilet door is closed locked and placarded

“INOPERATIVE DO NOT ENTER” .

(c) Toilet is not used for storage of any inflammable or

combustible materials.

(d) Flight is a non revenue flight.

Note

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

-OR-

26-17-01-01B (B) B 1 0 (O) (M) May be inoperative provided that:

(a) Toilet waste receptacle fire-extinguishing system is

verified operative, and

(b) Cabin crew is advised to check periodically absence

of smoke in affected lavatory.

See Operational procedure Toilet Smoke Detection System -

Passenger Configuration (O)

See Maintenance procedure Toilet Smoke Detection System -

Passenger Configuration (M)


CH26 FIRE PROTECTION


JUN, 2020



ITEM

26-17-01-01P TOILET SMOKE DETECTION

SYSTEM - PASSENGER

CONFIGURATION (O)

Cabin crew is advised to ensure lavatory is visited regularly during the

entire flight duration and the occasional usage of toilet by passengers.

Toilet should not be used for stowage of any inflammable or

combustible materials.

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

(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

AGENT DISCH LIGHTS

(ENGINE) (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 days.

See Maintenance procedure MMP.26.21-01 AGENT DISCH Light

(Engine) (M)

26-30-01 CABIN HAND FIRE

EXTINGUISHER3 3

Part of Emergency Equipment

(ENGINE)


CH27 FLIGHT CONTROLPage 27‐1(PIA REV 3.0)

JUN, 2020


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 twoflights.

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

-OR-

27-20-02B YAW DAMPER FUNCTION C 1 0 * May be inoperative provided that Yaw damper function is


ITEM

27 20 02B YAW DAMPER FUNCTION OPERATIVE (B)

C 1 0 * May be inoperative provided that Yaw damper function isoperative 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 speedis limited to 185 kt.

-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 ▪ 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 approx.

30 s and check rudder travel no longer limited.

▪ In Flight

● During an acceleration, select manually HI SPD

when reaching 185 kt.

● During a deceleration, select manually LO SPD

when reaching 180 kt .

TRAVEL LIMITER UNIT (TLU) (O)

RUDDER RELEASABLE CONTROL UNIT (O)



JUN, 2020



ITEM

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)

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 approx 30 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 INDICATOR

B 1 0 * (O) May be inoperative provided that elevator tabs are visuallychecked operative 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 the trim from nose down to nose up for 13 s .

Note

● This procedure sets the pitch trim to a conservative position for any CG inside the operational CG envelope.A TOCG in the center of the operational CG envelope is recommended in order to reduce the efforts of the pilot during the rotation.



JUN, 2020



ITEM

27-36-01 STICK 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

● MINIMUM MANEUVER OPERATING SPEED………..

…………………………………………….….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 ▪ During Preliminary Cockpit Preparation

● TCAS……………………………..……………....TA ONLY

● STICK PUSHER/SHAKER pb …..……….…………..ON● 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

27-36-03 INDICATIONS AND CONTROLS ON MAINTENANCE PANELS


STICK PUSHER ACTUATOR (O)



JUN, 2020



ITEM

27-37-01 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 AFM Deviation Guide.

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

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


Ferry Flight (A)

PITCH ELEVATORS COUPLING SYSTEM

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


(a) Flaps are checked in retracted position, and


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 (O) Refer to AFM.DEV.02.4 Dispatch With Flaps Retracted.


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

FLAPS CONTROL SYSTEM



JUN, 2020



ITEM

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 ● 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



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

FLAPS POSITION INDICATOR (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 thespoilers is checked prior to each departure and monitoredthroughout 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.



JUN, 2020



ITEM

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 SYSTEMS


JUN, 2020


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.

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 C 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 (O)

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

STANDARD EQUIPMENT

ITEM


ELECTRICAL FUEL PUMP

28-21-02P Limitations

Flight 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 730 kg

(1 609 lb).

▪ During Preliminary Cockpit Preparation

● FUEL X FEED…………...………...…....CHECK X LINE

● 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 …………………………..…….…IN LINE

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

TURN OFF

ELECTRICAL FUEL PUMP

(O)


CH28 FUEL SYSTEMS


JUN, 2020


STANDARD EQUIPMENT

ITEM


● FUEL X FEED ………………………………………..OFF

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

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

(There is no cockpit indication as Circuit breaker

of the pump is pulled)

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

(It is necessary to wait several minutes)

● FUEL X FEED ……………………….…CHECK X LINE

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

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

□ Before affected engine start

● FUEL X FEED …………….…………...………...IN LINE

□ 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 ……………………………………X LINE

● 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.

JET PUMP (AND

ASSOCIATED MOTIVE

FLOW VALVE)

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


(b) Fule X FEED valve is operative, and

(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.

Note

The "FUEL LO LVL" may be triggered in case of feeder tank jet

pump malfunction on aircraft fitted with the secondary low level

detection.

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)

FEEDER TANK JET PUMP


CH28 FUEL SYSTEMS


JUN, 2020


STANDARD EQUIPMENT

ITEM


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 730 kg

(1 609 lb).

● 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 See Maintenance procedure MMP.28.25-01-01 Refueling control

Panel - Refueling control Panel (M)

28-25-01-02 C 1 0 * (M) May be inoperative provided that manual refueling is performed.

See 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.

TANK TEMPERATURE

INDICATION

REFUELING CONTROL

PANAL - FUEL

PRESELECTOR


CH28 FUEL SYSTEMS


JUN, 2020


STANDARD EQUIPMENT

ITEM


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

(O)

28-41-01P Note

Refer to LIM.5.70.4.2 Fuel Temperature , for temperature limitation.

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


(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.

Note

1) In addition to the cockpit FUEL QTY INDICATION, the

preselected quantity and the repeated fuel quantity

indications on the refueling panel must be placarded

inoperative

2) 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)

TANK TEMPERATURE

INDICATION (O)

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), Maintain 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:


(b) Associated alert is processed by CCAS .

(O) (M) One may be inoperative provided that:


(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

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


CH28 FUEL SYSTEMS


JUN, 2020


STANDARD EQUIPMENT

ITEM


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

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

28-42-03P 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 3.0)

JUN, 2020


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

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


ITEM

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 (Central Instrument Panel)

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 3.0)

JUN, 2020



ITEM

29-32-02-02 PRESSURE INDICATION - BRAKE ACCU INDICATION (Central Instrument Panel)

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 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 Al t (O)

MAIN HYDRAULIC PUMP OVHT ALERT

Alert (O)

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

The DC AUX pump is set to OFF.


CH30 ICE AND RAIN PROTECTION


JUN, 2020


30-11-01 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 - B 1 0 * May be inoperative provided that:



conditions.

30-11-03-01 PNEUMATIC DE-ICING -

ENG-AIRFRAME MODE

SELECTOR - (FAST-SLOW)

MODE30-11-03-01A (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 -

AFR AIR BLEED FAULT

LIGHT

B 1 0 * (O) May be inoperative provided that AIRFRAME FAULT light is

checked operative.

See Operational procedure MOP.30.11-04P Pneumatic de-icnig - AFR

AIR BLEED FAULT Light (O)

30-11-04P With Bleed Supply :

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

● DE ICING AIRFREAM…………………………………….ON


ITEM

PNEUMATIC DE-ICING - DE-

ICE PRESSURE

REGULATING AND SHUT

OFF VALVE

PNEUMATIC DE-ICING -

AFR AIR BLEED FAULT

LIGHT (O)● DE ICING AIRFREAM…………………………………….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 C 2 1 * One may be inoperative, provided that:

(a) ETOPS Operation are not conducted, and


conditions.


ENGINE DE ICING (OR ANTI

ICING) BOOTS SYSTEM




JUN, 2020



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:



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

(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)


ENG-AIRFRAME DE ICING

BOOTS FAULT ALERT

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


-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.




JUN, 2020



ITEM

30-60-02 WINDOW HEATING - SIDE

WINDOW30-60-02A (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 - Side

Windows 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 ● 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.

WINDOW HEATING - SIDE

WINDOWS FAULT LIGHT

(O)

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 PROPELLER ANTI-ICING

SYSTEM 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)




JUN, 2020



ITEM

30-61-02P 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



PROPELLER FAULT ALERT

C 2 0 * One or both may be inoperative provided that aircraft is not

operated into known or forecast icing conditions.


PROPELLER MODE SEL

AUTO

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

30-65-01-01 WINDSHIELDS WIPERS -

WIPERSC 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.

Note

1 : 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.


HIGH SPEED FUNCTION

PROPELLER ANTI-ICING

ON LIGHT (O)

HIGH SPEED FUNCTION

(FAST)30-65-01-02A (A) C 2 0 * One or both may be inoperative provided that the associated low

speed function is operative.


LOW SPEED FUNCTION

(SLOW)

30-65-01-03A (A) C 2 0 * One or both may be inoperative provided that the associated high

speed function is operative.


CONTROLS ON

MAINTENANCE PANELS


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 1 1 NO GO

Note

Refer 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



CH31 INSTRUMENTS


JUN, 2020


31-21-01 CLOCK C 2 1 * One may be inoperative provided that:

Note

On 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

Note

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-DFDR

Note


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

Refer to item 77-13-01 TQ Indicator

Note


ITEM

MPC - DMU - FLIGHT

RECORDING FUNCTIONS

(DATE, TIME AND FLIGHT

NUMBER)


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

MULTI FUNCTION

COMPUTER (MFC) MODULE

1A


CH31 INSTRUMENTS


JUN, 2020



ITEM

(f) Aircraft is not operated into known or forecast

icing conditions if de-icing OVRD system is

inoperative, and

(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

ADC instruments are lost.

● PUSH IN C/B INV 2 .

Following warnings have to be tested prior to the first

flight of the 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

MULTI FUNCTION


1A (O)

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.

FLAPS UNLOCK TEST

● SET FLAPS 15.

● On RH maintenance panal , 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.


CH31 INSTRUMENTS


JUN, 2020



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)


● 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

CAPT ADC connected instruments operate normally - F/O

MFC FUNCTION COMPUTER

(MFC) MODULE 2A

MFC MODULE COMPUTER

(MFC) MODULE 2A (O)

CAPT ADC connected instruments operate normally - F/O

ADC instruments are lost.


Following warnings have to be tested prior to the first

flight of the 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 WAN rotary selector to NORM FLT.

● Clear ICING AOA light.


CH31 INSTRUMENTS


JUN, 2020



ITEM

● GUST LOCK engaged.

FLAPS UNLOCK TEST

● SET FLAPS 15.

● On RH maintenanace panel, depress and maintain

FLAPS UNLOCK PTT.


passes over the selected position minus 3 ᴼ on the

flaps position indicator.

● SET FLAPS AS RQD.


● 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 PUSHED OUT

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

● EXHAUST MODE……………..…..……….…NORM


(a) Aircraft is not operated on narrow runways

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

MULTI FUNCTION

COMPUTER (MFC) MODULES

1B


(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


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)


CH31 INSTRUMENTS


JUN, 2020



ITEM


● OVBD VALVE ………………………...FULL OPEN

● PACK 1 ………………………………………...OFF● PULL C/B INV 1 and check AC STBY BUS

is supplied.

Note

CAPT ADC connected instaruments operate normally - F/O

ADC instrument are lost.



● Select de-icing OVRD mode and visually check boots

infiation.

● Select de-icing OVRD mode to NORM position.


functions.


□ Before take off

● PACK 2 ………………………………………..OFF

□ After take off

Note

Landing gare 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..

MULTI FUNCTION

COMPUTER (MFC) MODULES

1B (O)

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 light.


(a) Aircraft is not operated on narrow runways

(width < 30 m (98ft)) ,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 min must be

observed, and

(i) Hotel mode is not used, and

MULTI FUNCTION


2B


CH31 INSTRUMENTS


JUN, 2020



ITEM

(j) Aircraft is not operated into known or forecast


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)


● OCBD 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.


□ Before take off

● PACK 1 …………………………………….OFF

□ After take off

● PACKS …………….…..…….………………ON

● OCBD VALVE …....………....…FULL CLOSE

□ After landing

● OVBD VALVE …………….………FULL OPEN

● PACK 2………………………………………OFF

CAUTION


MULTI FUNCTION


2B (O)


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-

01-01 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)

MASTER WARNING (MW)

LIGHT AND ASSOCIATED

CANCEL FUNCTION


CH31 INSTRUMENTS


JUN, 2020



ITEM

31-53-02P MASTER WARNING (MW)


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)

31-53-03PThe crew must closely monitor the Crew Alerting panel.

31-53-04-01 CREW ALERTING PANEL

CAP - WARNING LIGHT31-53-04-01A (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.

MASTER CAUTION (MC)


CANCEL FUNCTION (O)

MASTER CAUTION (MC)


CANCEL FUNCTION

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.


CONTROLS ON

MAINTENANCE PANELS



CH32 LANDING GEAR


JUN, 2020


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)

32-31-03P LANDING GEAR

RETRACTION SYSTEM AND

UPLOCKING SYSTEM (O)

Refer 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



See Operational procedure MOP.32.42-01P Wheel Break (O)

See maintenance procedure MMP.32.42-01 Wheel Break (M)


ITEM

LANDING GEAR

RETRACTION SYSTEM AND

UPLOCKING SYSTEM

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 GEAR


JUN, 2020



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 differential 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.when the landing gear control lever is in Down Position.


CH33 LIGHTS


JUN, 2020


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.

-OR-

C - 0 May be inoperative for daylight operations.

33-10-02-01 C - 14 One or more may be inoperative provided that:

(a) 14 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:


ITEM

CABIN LIGHTS -PASSENGER

CONFIGURATION

to be used:

● Set the SELECTOR to the function to be tested.

● 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 30.

● 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 15 ᴼ .

● 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.

FLAPS UNLOCK

● Set FLAPS 15.

● Depress and maintain FLAPS UNLK PTT pb on

RH maintenance panel.


CH33 LIGHTS


JUN, 2020



ITEM


passes over the selected position minus 3 ᴼ on

the flaps position indicator.

33-16-01-02 ANN LIGHT - DIM FUNCTION

33-16-01-02A 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.

Note

For 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.33-37-01 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 LIGHT

33-42-01A NIGHT OPERATIONS (A) 2 2 * Must be 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 that all

BEACON lights are operative.

33-46-01 TAXI AND TO LIGHT

33-46-01A 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.

33-48-01 BEACON LIGHT

33-48-01A NIGHT OPERATIONS (A) C 2 1 * (O) One may be inoperative for Night Operations provided that all

STROBE lights are operative.

See Operation procedure MOP.33-48-01P BEACON Light (O)


CH33 LIGHTS


JUN, 2020



ITEM

-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.

Note

If 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.

NOTE

If right Wing Inspection Light is inoperative, Hotel mode is prohibited.

-OR-

33-49-01B DAYLIGHT OPERATIONS (B) C 2 0 * One or both may be inoperative for Daylight Operations.

33-49-02 IEP LIGHT

33-49-02A 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 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 is

operative 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.

NOTE

For 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.

NOTE

For Cargo operations, no MEL item entry is applicable as the system

is not required.

33-50-04 EMERGENCY EXIT SIGNS C 10 10 * Up to 50% of the bulbs / LEDS may be inoperative in one or more

signs provided that the sign remains legible.

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.

PHOTO LUMINESCENT FLOOR

PROXIMITY EMERGENCY

ESCAPE PATH MARKING TAPE


CH33 LIGHTS


JUN, 2020



ITEM

33-50-05 EMERGENCY EXIT HANDLE

LIGHTING

A 2 1 * One may be inoperative provided that associated emergency exits is


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 ConfigurationNote




-OR-

33-51-01B DAYLIGHT OPERATIONS (B) B 4 3 One light may be inoperative for Daylight Operations only.

Note





CH34 NAVIGATION


JUN, 2020


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 2 1 * Vibrator may be inoperative.

34-12-03 MAIN ALTIMETERS

34-12-03A ETOPS OPERATIONS (A) A 2 1 * Altimeter #2 may be inoperative provided that:



ITEM

AIR DATA COMPUTER (ADC) (O)


(b) Operations are limited to two calendar days .

-OR-

34-12-03B (B) A 2 1 * One may be inoperative provided that:

(a) Operations are limited to two calendar days,

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

(c) ETOPS operations are not conducted.

34-13-01-01 MAIN AIRSPEED INDICATOR -

SPEED INDICATION34-13-01-01A ETOPS OPERATIONS (A) A 2 1 * Airspeed Indicator #2 may be inoperative provided that operations are

limited to two calendar days.

-OR-34-13-01-01B (B) A 2 1 * One may be inoperative provided that:

(a) Operations are limited to two calendar days, and

(b) ETOPS operations are not conducted.

34-13-01-02 C 2 0 * (O) One or both may be inoperative.

See Operational procedure MOP.34.13-01-02P Airspeed indicator - Speed Selector

(O)

AIRSPEED INDICATOR - SPEED

SELECTOR


CH34 NAVIGATION


JUN, 2020



ITEM

34-13-01-02P AIRSPEED INDICATOR - SPEED

SELECTOR (O)

● FAST/SLOW indication on the EADI is lost.

34-14-01 VERTICAL SPEED INDICATOR C 2 1 * One may be inoperative.

Refer to Item 34-57-01-02 Airborne Collision Avoidance System- Combine TA

and RA Dual Display

34-15-01-01 (TAT-SAT-TAS INDICATOR) - TAS

INDICATION


34-15-01-02 C 2 0 * (O) One or both may be inoperative provided that SAT is available on GNSS

progress page.

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 as visible

moisture is encountered regardless of temperature.

If anti-icing and/or de-icing systems need to be used, mode FAST only must

be switched ON.

34-15-01-03 (TAT-SAT-TAS INDICATOR) - SAT

SWITCHING


34-16-01 ALTITUDE ALERTING SYSTEM 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.

See Operational procedure MOP.34.16-01P Altitude Alerting System (O)

34-16-01P ● In Flight

Flight crew should check on altimeters that there is no altitude excursion.

(TAT-SAT-TAS INDICATOR) -

TEMPERATURE INDICATION

(TAT-SAT-TAS INDICATOR) -

TEMPERATURE INDICATION (O)

ALTITUDE ALERTING SYSTEM (O)

Flight crew should check on altimeters that there is no altitude excursion.

● During climd, descent and altitude capture phases

Flight crew must ensure strict adherence to standardized callouts.

34-20-01 AHRS 2 2 Must be operative.

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.

34-27-01 STANDBY HORIZON 1 1 Must be operative.

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.


CH34 NAVIGATION


JUN, 2020



ITEM

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 ILS

34-36-01A (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 hazardous

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

forecast 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 34-48-02-01

Ground Proximity Warning System - GPWS, and

(b) ACAS is set to STBY, Refer to Item 34-57-01-01

Airborne Collision Avoidance System - ACAS System.

See Operational procedure MOP.34.42-01P Radio Altimeter System (O)

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.

RADIO ALTIMETER SYSTEM

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 to

34-48-02-06

GROUND PROXIMITY WARNING

SYSTEM - GPWS

1 1NO GO AS PER PCAA POLICY

34-50-01 NAVIGATION SYSTEMS (VOR-

DME-ADF)

VOR

A 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.

RADIO ALTIMETER SYSTEM (O)


CH34 NAVIGATION


JUN, 2020



ITEM

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.

DME

A 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.

Note

The 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.

ADF

A 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 NOT APPLICABLE

34-52-02 D 2 1 Any in excess of those required for the intended route may be inoperative.

SSR TRANSPONDER SYSTEM -

MODE AC FUNCTIONS

SSR TRANSPONDER SYSTEM -

Note

1) 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 - ACAS

2) Elementary Surveillance (ELS) function is required in European

Mode S designated airspace.

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.

-OR-

D 2 0 One or more Downlinked Aircraft Parameters which provide Enhanced

Surveillance may be inoperative when not required for the intended route.

34-52-04 SSR TRANSPONDER SYSTEM -

EXTENDED SQUITTER

TRANSMISSION FUNCTION NOT APPLICABLE

MODE S FUNCTION


CH34 NAVIGATION


JUN, 2020



ITEM

34-57-01-01 AIRBORNE COLLISION

AVOIDANCE SYSTEM - ACAS

SYSTEM

1 1 NO GO AS PER PCAA POLICY

34-57-01-02 C 2 1 (O) One 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 The associated C/B of ACAS TA and RA dual display is pulled for deactivation

AND Vertical Speed Indicator will also be considered inoperative.

Refer to item 34-14-01 Vertical Speed Indicator.

34-58-01 C 1 0 * (O) One or more may be inoperative provided that:

(a) The navigation systems required for each segment of the

intended flight route are operative, and

(b) Not required by the flight rules, and

(c) Status and suitability of navigation facilities uesd to define route

flight are verified by dispatach (refer jeppesen Chart Notams), and

(d) Approch navigation radios are verified to be properly tuned

and identified, and

(e) SAT is available on TAT-SAT-TAS indicator.

Note

1) If GPS #1 is operative, TAWS is inoperative, Refer to Item

34-48-02-05Ground proximity Warning System -Terrain Awareness

and Warning System (TAWS)

2) If GPS #1 is inoperative, GNSS parameters are no longer

available for Transponder System, Refer to Item 34-52-03

SSR Transponder System - Enhanced Surveillance Function

GPS-GNSS

GLOBAL POSITIONING SYSTEM

(O)

AIRBORNE COLLISION AVOIDANCE

SYSTEM - COMBINE TA AND RA

DUAL DISPLAY (O)

AIRBORNE COLLISION

AVOIDANCE SYSTEM - COMBINE

TA AND RA DUAL DISPLAY

See Operational procedure MOP.34.58-01P GPS-GNSS (O)

34-58-01P (a) Status and suitability of navigation facilities uesd to define route

flight are verified by dispatach (refer jeppesen Chart Notams), and

(b) Approach navigation radios are verified to be properly tuned

and identified.

34-61-02 NAVIGATION DATABASE C 1 0 May be inoperative for the intended route where conventional (non- RNAV )

navigation is sufficient, provided that:

34-61-02A (A) (a) Current aeronautical information (e.g. charts) is available for the

entire route and for the airports intended to be used, and

(b) Navigation database information is disregarded.

Note

Database which is out of date is considered to be inoperative.

34-61-02B B NOT APPLICABLE

34-61-02C C A 1 0 May be inoperative for a maximum of 10 calendar days provided that:

(a) Area Navigation ( RNAV ) departure, arrival and approach

procedures do not depend on the data amended in the current

database cycle, and

GPS-GNSS

GLOBAL POSITIONING SYSTEM

(O)


CH34 NAVIGATION


JUN, 2020



ITEM

(b) Before each flight , current aeronautical information is used

to verify the database Navigation Fixes, the coordinates,

frequencies, status (as applicable) and suitability of Navigation

Facilities required for the intended route, and

(c) Radio navigation aids, which are required to be flown

for departure, arrival and approach procedures and

which have been amended in the current database cycle,

are manually tuned and identified.

Note


34-61-02D D A 1 0 May be inoperative for a maximum of 10 calendar days provided that:

(a) Conventional (Non- RNAV ) departure, arrival and approach

procedures, when available, or ANSP assistance are used

as an alternative to RNAV procedures which have been

amended in the current database cycle, and

(b) Before each flight , current aeronautical information is used

to verify the database Navigation Fixes, the coordinates,

frequencies, status (as applicable) and suitability of

Navigation Facilities required for the intended route, and

(c) Radio navigation aids, which are required to be flown

for departure, arrival and approach procedures and

which have been amended in the current database cycle,

are manually tuned and identified.

Note


34-70-01 EFIS - SG SWITCHING

PUSHBUTTON

C 2 0 * One or both may be inoperative in normal position.

34-70-02 ATT - HDG SWITCHING

PUSHBUTTON

C 2 0 * One or both may be inoperative in normal position.

34-70-03 VOR - ILS SWITCHING Pushbutton 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:


(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 ELECTRONIC FLIGHT

INSTRUMENT SYSTEM (EFIS)

DISPLAY (O)

● Select OFF affected EFIS display in order to recover composite mode on

the non affected screen.

34-71-02 A 2 1 * SGU 2 only may be inoperative provided that:



(c) Operations are limited to two calender days .

34-76-01 INDICATIONS AND CONTROLS ON

MAINTENANCE PANELS


SYMBOL GENERATOR UNIT (SGU)

ELECTRONIC FLIGHT

INSTRUMENT SYSTEM (EFIS)

DISPLAY


CH35 OXYGEN


JUN, 2020


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


See Operational procedure MOP.35.20-01P Passenger Oxygen

System - Passenger Configuration (O)

35-20-01P PASSENGER OXYGEN

SYSTEM - PASSENGER

CONFIGURATION (O)

May be inoperative provided that maximum altitude is limited


35-20-02 PASSENGER OXYGEN

SYSTEM - CARGO

NOT APPLICABLE


ITEM

SYSTEM - CARGO

CONFIGURATION

35-20-03 PASSENGER SERVICE

UNIT

B 35 0 * (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 Maintenance 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 OXYGEN


JUN, 2020



ITEM

(b) Units are operative for all operative passenger seats,

toilet compartment and cabin attendant location.

35-35-01 PORTABLE OXYGEN

BOTTLE

D 2 - * (O) (M) Any in excess of that required (as given in note below) may

be inoperative or missing provided that each inoperative

equipment is placarded inoperative and removed from the

installed location and placed out of sight so it cannot be

mistaken for functional unit.

Note

Requirement is :

1 bottle for upto 50 cabin occupants, and

2 bottles for upto 100 cabin occupants

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.

35-65-01 TOOL OXYGEN MANUAL

RELEASE

C 4 3 * One may be inoperative.


CH36 PNEUMATIC SYSTEM


JUN, 2020


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 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

NOT APPLICABLE

36-11-02P 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.

Note

With one bleed INOP, whilst on ground, with both engines

running, the crossfeed valve remains open with the associated

X FEED indicator illuminated.

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.


ITEM

BLEED VALVE -

PASSENGER

CONFIGURATION

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 FEED valve is checked

closed.

See Maintenance procedure MMP.36.11-05 Ground X Feed Valve

OPEN 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


CH36 PNEUMATIC SYSTEM


JUN, 2020



ITEM

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


CONTROLS ON

MAINTENANCE PANELS



CH52 DOORSPage 52‐1(PIA REV 3.0)

JUN, 2020


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 operation, and

(d) All possibly concerned personnel are informed

about the unbalanced condition


ITEM

about the unbalanced condition.

52-21-01-01 EMERGENCY EXIT (INCLUDING PASSENGER-CREW DOORS, SERVICE DOOR, BUT EXCLUDING FLIGHT DECK EMERGENCY EXITS)-PASSENGER OR COMBI CONFIGURATION

2 2

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.



JUN, 2020



ITEM

52-31-02 CARGO DOOR CONTROL SYSTEM

C 1 0 * May be inoperative provided that cargo door is visually checked locked closed.


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 ConfigurationOrRefer to item 52-21-01-02MOP.52.21-01-02 Emergency Exit (including Passenger-Crew Doors, Service Door, but Excluding Flight Deck Emergency Exits) - Cargo Configuration

52-50-01-01 COCKPIT DOOR LOCKING SYSTEM

B 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)

AUX AFT CARGO DOOR (CLASS "C")

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.

52‐50‐01‐02 A 1 0 * (O) May be inoperativeprovided that operations are limited to two

calendar day .

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.

COCKPIT DOOR LOCKING SYSTEM - SYSTEM (CONTROL UNIT, TOGGLE SWITCH, LIGHTS ON CONTROL PANAL,BUZZER) (O)

COCKPIT DOOR LOCKING SYSTEM (O)

COCKPIT DOOR LOCKING SYSTEM - SYSTEM (CONTROL UNIT, TOGGLE SWITCH, LIGHTS ON CONTROL PANAL,BUZZER)



JUN, 2020



ITEM

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.

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.

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.

COCKPIT DOOR LOCKING SYSTEM - EMER PUSHBUTTON ON DOOR CALL PANEL (O)

COCKPIT DOOR LOCKING SYSTEM - EMER PUSHBUTTON ON DOOR CALL PANEL

p yNote

Any part of the CDLS may be inoperative provided that thecomplete system is deactivated in the unlocked position andis not required by operational regulations for the intendedflight.

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.


CH56 WINDOWSPage 56‐1(PIA REV 3.0)

JUN, 2020


56-11-01 WINDSHIELD (INCLUDING MAIN WINDSHIELD, FWD AND AFT WINDOWS)

56-11-01A (A) A 6 6 (O) (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 damaged cockpit window must be assessed in accordance with Structural Repair Manual Refer to SRM 56-10-00. If it is assessed as acceptable bymaintenance personnel, the vision through this cockpit window must also be assessed as being acceptable by the pilot.

See Operational procedure MOP.56.11-01P Windshield (Including Main Windshield, FWD and AFT Windows) (O)

See Maintenance procedure MMP.56.11-01 Windshield (Including M i Wi d hi ld FWD d AFT Wi d ) (M)


ITEM

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 (Including Main Windshield, FWD and AFT Windows) (M)

56-11-01P WINDSHIELD (INCLUDING MAIN WINDSHIELD, FWD AND AFT WINDOWS) (O)

Refer to 21-30-01P Pressurization System (O) to conduct unpressurized flight.

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


CH61 PROPELLER


JUN, 2020


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

(c) Operations are limited to two calendar days.

See Operational Procedure MOP.61.21-02P PEC Channel (O)

61-21-02P PEC CHANNEL (O) On the engine affected by a PEC SGL CH light illuminated :

Other channel test :

Engine not running - PL on GI - CL on FUEL S.O.

● Set WOW on FLT position on RH Maintenance panel

● Advance CL to AUTO

● Check PEC FAULT illuminates after 30 s

● Retard CL to FUEL S.O.

● Check PEC FAULT extinguishes after 30 s

● Set WOW on NORM position on RH Maintenance panel

Overspeed governor test:

Engine running - PL above FI - CL on AUTO - Make sure NP is above

77 %

● Select PEC to OFF

● Slowly advance PL up to reach NP = 102.5 % +/- 1 %.

● Increase TQ by 5 % and check NP unchanged.

● Retard PL to GI.

● Select PEC to ON and check PEC OFF extinguishes.

Note

Low pitch stop is automatically checked when propeller is


ITEM

Low pitch stop is automatically checked when propeller is

unfeathered.

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% OVRD

Note

If affected side cannot 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


CH61 PROPELLER


JUN, 2020



ITEM

61-21-06P During Preliminary Cockpit Preparation check:

□ Before each affected engine start

● PL ………………………………………..….………….GI

● CL ………………………………………….…FUEL S.O.

● WOW SWITCH…………………………….………...FLT

● CL……………………………………………...……AUTO

AFTER 30 s

● PEC FAULT LIGHT………………….CHECK TURN ON

● CL……………………………………………..FUEL S.O.

● 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.

61-22-02-02 UPTRIM FUNCTION C 2 0 * (O) May be inoperative provided that:

PIU AND ASSOCIATED

PROPELLER SPEED

SELECTION (O)

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 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 AFM DEV.02.7.01.1 Dispatch with Autofeather System

Inoperative.

AUTOFEATHER

FUNCTION


CH61 PROPELLER


JUN, 2020



ITEM

61-22-03 ATPCS ARM LIGHT C 1 0 * May be inoperative provided that ATPCS is considered inoperative.

61-22-04 UPTRIM LIGHT C 2 0 * (O) One or more may be inoperative provided that uptrim is consider

inoperative.

Refer to Item 61-22-02-02MOP.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)

NP INDICATOR (O)

● Either pointer or counter may be inoperative on each indicator

provided that associated PROP anti icing is checked operative.

● One may be inoperative, provided that :



icing conditions.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 : PROHIBITED

Normal 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 inoperative

Note

Hotel mode is not available.

See Maintenance procedure MMP.61.50-01 Propeller Brake (M)

LO PITCH CAUTION LIGHT

(O)


CH61 PROPELLER


JUN, 2020



ITEM

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

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 S.O.

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 3.0)

JUN, 2020


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 PUSHED 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 Fule 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.


ITEM

LOW FUEL TEMPERATURE

REPORTED (A)

( ) ( ) p p

73-23-01 PWR MGT ROTARY SELECTOR

A 2 1 * (O) One may be inoperative provided that operations are limited to two calendar days.

See Operational procedure MOP.73.23-01P PWR MGT Rotary Selector (O)

73-23-01P □ 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 go off.

□ 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).

PWR MGT ROTARY SELECTOR (O)


CH73 ENGINE FUEL AND CONTROLPage 73‐2(PIA REV 3.0)

JUN, 2020



ITEM

● For TAKE OFF

● CL 1 + 2 ………………………..…………100% OVRD

● Inhibit CONFIG WARNIING by depressing WARNING

pb when applying power.

Note

● CAP light will not go off.

● 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

73-60-01 INDICATIONS AND CONTROLS ON MAINTENANCE PANELS

C - 0 May be inoperative


CH74 IGNITIONPage 74‐1(PIA REV 3.0)

JUN, 2020


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


(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 3.0)

JUN, 2020


75-20-01 HBV DISCHARGE FLAPPER NOT APPLICABLE


ITEM


CH77 ENGINE INDICATINGPage 77‐1(PIA REV 3.0)

JUN, 2020


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


See Operational procedure MOP.77.00-02P AFU (O)

See Maintenance procedure MMP.77.00-02 AFU (M)

77-00-02P Refer to AFM-AFM DEV.02.12.01.1 Dispatch with ATPCS Off.

77‐11‐01‐01 NH INDICATIONS C 4 2 * Either pointer or counter may be inoperative on each indicator.

77-11-01-02 NH INDICATOR C 2 1 * (O) One Indicator (pointer and counter) may be inoperative provided that:(a) ETOPS Operations are not conducted, and

(b) Both engines TQ indicator and NP indicator are

operative.

See Operational Procedure MOP.77.11-01P NH Indicator (O)


ITEM

AFU (O)

77-11-01P NH INDICATOR (O) ● When starting affected engine, select CL FTR 5 s after

START pb has been depressed.

77-11-02 NL INDICATOR C 2 0 * One may be inoperative provided that associated NH indicator is operative and monitored.

77-13-01-01 TQ INDICATIONS - DIGITAL COUNTER

C 2 2 * (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 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


See Operational procedure MOP.77.13-01P TQ Indications (O)

TQ INDICATIONS - POINTER & DIGITAL COUNTER


CH77 ENGINE INDICATINGPage 77‐2(PIA REV 3.0)

JUN, 2020



ITEM

77-13-01P TQ INDICATIONS - POINTER AND DIGITAL COUNTER (O)

Refer to AFM.DEV.02.10.01.1 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 QRH

PER.2.Torque Value)

77-20-01 ITT INDICATOR C 4 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.

77 60 01 INDICATION AND C 0 May be inoperative

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 3.0)

JUN, 2020


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

(c) e o p essu e s o to ed t oug out t e g t

PIA ATR 75 MINIMUM EQUIPMENT LIST (MAINTENANCE PART)

PIA ESTABLISHED MAINTENANCE PROCUDURE

(PIA REV 3.0)

JUN, 2020

MAINTENANCE PROCEDURES

The affected seat is to be secured in retracted and /or stowed position and ensured that the

seat will not be used.

Ref. AMM JIC: TASK ATR-A-25-21-20-02001-720A-A , SUBTASK 252120-10200070001

(3) Put the seat in the stowed position.

In order to C/F the aft cabin attendant seat, ensure it in Upright/locked position.

The affected seat is to be secured in retracted and /or stowed position and ensured that the

seat will not be used.

Ref. AMM JIC: TASK ATR-A-25-21-20-02001-720A-A , SUBTASK 252120-10200070001

(3) Put the seat in the stowed position.

In order to C/F the aft cabin attendant seat, ensure it in Upright/locked position.

25-45-01 PORTABLE PROTECTIVE

BREATHING EQUIPMENT

NOT APPLICABLE As this item can not be carried forwad as per MEL item description.

25-50-01 VIDEO SYSTEM IN CABIN

25-50-01A This is to be ensured that screens are locked in up position.

Ref. AMM JIC: TASK ATR-A-23-36-XX-00001-320A-A, SUBTASK2336XX-50000010001

(e) Put the switches in OFF position.

(f) On the video cabin command unit , push CTRL and PAX keys at the same time,

then switch off the video cabin command unit when all the video cabin screens

are in stowed position.

26-17-01-01

26-17-01-01B (B) Visually inspect fire extinguisher assembly for the waste bin in the Toilet

compartment for its servicebility.

Ref. AMM JIC: TASK ATR-A-26-25-20-00001-281A-A, SUBTASK 262520-60000020001

“(2) Examine the general condition of the discharge tubes”

26-30-01 CABIN HAND FIRE

EXTINGUISHER

NOT APPLICABLE As this item can not be carried forwad as per MEL item description.

28-25-02 This is to be ensured that:

(a) Refuel valve is closed, and

(b) No fuel leakage is observed from refuel coupling.


C. Check of Refuel/Defuel Valve

(1) During refueling or defueling operation:

(a) Do a check of the refuel/defuel valve for correct operation.

(b) Do a leakage check ATR-A-25-25-20-00001-740A-A, SUBTASK 252520-

20000020004

35-20-03 This is to be ensured that:

(a) Passenger service Unit is locked in secured position, and

(b) Affected seats are blocked and placarded to prevent occupancy.


A. Closing of the PSU Module (New Look Cabin)

35-35-01 PORTABLE OXYGEN

BOTTLE

This is to be ensured that non-required bottle is removed and placed out of sight.


TOILET SMOKE DETECTION

SYSTEM - PASSENGER

CONFIGURATION

AUX AFT CARGO DOOR

(CLASS "C")

PRESSURE REFUELING

CAP

PASSENGER SERVICE UNIT

ITEM

25-21-01 REQUIRED CABIN

ATTENDANT SEAT

25-21-02 NON-REQUIRED CABIN

ATTENDANT SEAT

PIA MMP-1

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 / 75 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 / 75 TOCMMEL Table of Content Page n°02

21-23-01 Overboard Valve (M)_c9d14da0-8abf-4344-9450-e16f722ac43b 3.4

ALL

▶ Overboard Ventilation Valve De-energizationRefer to JIC 21-23-22-DAR-10000 PART 1 / MP ATR-A-21-23-20-00ZZZ-560Z-A, setting thevalve 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 1.11

ALL

▶ Electropneumatic Outflow Valve and Pneumatic Outflow Valve Blockage in Open PositionRefer to JIC 21-31-20-DEA-10000 / MP ATR-A-21-31-20-00ZZZ-560Z-A.

21-31-03 Electropneumatic Outflow Valve (M)_7d3d4f46-f8f7-4688-b716-4c30dc900c11 2.1

ALL

Refer to JIC 213122-DEA-10000 / MP ATR-A-21-31-20-01ZZZ-560Z-A.

21-51-01 Pack Valve (M)_005e5080-471c-4e69-bfa1-74072375cf49 2.2

ALL

Refer to JIC 21-11-51-DEA-10000 / MP ATR-A-21-11-50-00ZZZ-560Z-A.

MAINTENANCE PARTMMP.21

PK / 75 ATA 21 AIR CONDITIONINGMMEL Page n°01

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PK / 75 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 / 75 ATA 22 AUTOMATIC FLIGHT CONTROL SYSTEMMMEL Page n°01

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PK / 75 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 / 75 ATA 24 ELECTRICAL POWERMMEL Page n°01

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PK / 75 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


25-50-01 Video System in Cabin (M)_1e924511-1aaa-4227-b753-ef586c70ac1f 0.1

ALL



PK / 75 ATA 25 EQUIPMENTMMEL Page n°01

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PK / 75 ATA 25 EQUIPMENTMMEL Page n°02

26-17-01-01 Toilet Smoke Detection System (if installed) - PassengerConfiguration (M)Toilet Smoke Detection System (if installed) – Passenger Configuration (M)_8fca2fb3-1a6b-4897-814c-4551d6050a0f 0.3

ALL

PROCEDURE TO BE DEVELOPED IN THE OPERATOR'S MELTo provide instructions to verify/test the agent bottle of the lavatory waste receptacle fire-extinguishing system.

Refer to JIC 26-25-21-DVI-10000 / MP ATR-A-26-25-20-00ZZZ-281Z-A

26-21-01 AGENT DISCH Light (Engine) (M)_8a68d305-478e-467f-a323-13901c4e48d4 1.1

ALL

Refer to JIC 26-21-00-CHK-10000 / MP ATR-A-26-21-XX-00ZZZ-362Z-A.

26-30-01 Cabin Hand Fire Extinguisher (M)_40cdb9c3-c5d6-4383-9f7d-40aed12a2fc5 REV 1.1

ALL



PK / 75 ATA 26 FIRE PROTECTIONMMEL Page n°01

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PK / 75 ATA 26 FIRE PROTECTIONMMEL Page n°02

27-36-02 Stick Pusher Actuator (M)_3eecb395-eda6-41b3-85e5-034caca2bc7f 2.1

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 / MP ATR-A-27-36-30-00ZZZ-520Z-A.

27-37-01 Pitch Elevators Coupling System (M)_10fb71a0-490f-47ef-ad74-04ffc3380bb0 1.4

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 JIC 55-10-00-DVI-10000 / MP ATR-A-55-1X-

XX-01ZZZ-310Z-A) 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 JIC 27-31-43-DAR-10005 /

MP ATR-A-27-31-40-00ZZZ-560Z-A).

27-37-02 Elevators Clutch Reconditioning Device (M)_3eadb632-6fd1-4835-962c-468bd8edb389 1.2

ALL

Refer to JIC 27-31-43-DAR-10000 / MP ATR-A-27-31-40-01ZZZ-560Z-A.

27-61-01 Spoiler Control System (M)_fb265fd3-e2c1-44ed-85dd-15483137bdb1 1.1

ALL

Refer to JIC 27-61-00-DAR-10000 / MP ATR-A-27-61-XX-00ZZZ-560Z-A.

27-70-01-01 GUST LOCK System - Aileron (M)_525c9fe4-e2d9-4519-ab78-6f012a0825aa 0.2

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).


PK / 75 ATA 27 FLIGHT CONTROLSMMEL Page n°01

cont'd…

▶ Display warning notice in the flight compartment prohibiting operation of gust lockcontrol

▶ Open access panel 533AB (633AB) then 544AB (644AB).▶ Retract the actuator, if necessary, by means of an ALLEN KEY▶ Check the clearance (8 mm +/- 3 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 4.0

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)_99a64439-8dc8-46f3-a74c-eb6824519201 1.5

ALL

Gravity RefuelingRefer to JIC 12-11-28-FLG-10000 / MP ATR-A-12-11-28-00ZZZ-211Z-A.

28-25-01-02 Refueling Control Panel - Fuel Preselector (M)_5501a39e-3cb5-4827-b8b6-3f70f149d1d7 2.1

ALL

Manual RefuelingRefer to JIC 12-11-00-FLG-10025 / MP ATR-A-12-11-XX-01ZZZ-211Z-A.

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 3.1

ALL

Refer to JIC 12-11-00-FLG-10025 / MP ATR-A-12-11-XX-01ZZZ-211Z-A for manual refueling.Refer to JIC 12-11-28- CHK-10000 / MP ATR-A-12-11-28-00ZZZ-310Z-A for checking fuellevel using manual (magnetic) indicators.Refer to JIC 28-42-72-FUT-10020 / MP ATR-A-28-42-70-04ZZZ-340Z-A (FUNCTIONAL TESTOF FEEDER TANK LOW LEVEL SENSOR) to check the opposite side Fuel LO LVL alert.

28-42-03 Fuel LO LVL Alert (M)_22f45eed-a07f-427b-9a34-89c33e35d405 REV 2.0

ALL

Refer to JIC 12-11-28-CHK-10000 / MP ATR-A-12-11-28-00ZZZ-310Z-A for checking fuellevel using manual (magnetic) indicators.Refer to JIC 28-42-72-FUT-10020 / MP ATR-A-28-42-70-04ZZZ-340Z-A (FUNCTIONAL TESTOF FEEDER TANK LOW LEVEL SENSOR) to check Fuel LO LVL alert on opposite side.


PK / 75 ATA 28 FUEL SYSTEMMMEL Page n°01

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PK / 75 ATA 28 FUEL SYSTEMMMEL Page n°02

29-11-01 Main HYD Pump (M)_ab380eee-7d0a-44f3-a7ee-b1be718dd591 1.1

ALL

Refer to JIC 29-00-00-CHK-10000 / MP ATR-A-29-XX-XX-00ZZZ-281Z-A to check the level ofhydraulic fluid.


PK / 75 ATA 29 HYDRAULIC SYSTEMMMEL Page n°01

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PK / 75 ATA 29 HYDRAULIC SYSTEMMMEL Page n°02

30-31-03 Probe Heating Alert (M)_3bf43848-129e-4600-aff1-2c382e47b3ea 1.2

ALL

Refer to JIC 34-11-11-CHK-10000 / MP ATR-A-34-11-10-00ZZZ-366Z-A to check pitot probesheating 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 / 75 ATA 30 ICE AND RAIN PROTECTIONMMEL Page n°01

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PK / 75 ATA 30 ICE AND RAIN PROTECTIONMMEL Page n°02

32-42-01 Wheel Brake (M)_fdc0d835-aa00-4a37-8812-52e1b14c3649 1.4

ALL

For deactivation, Refer to JIC 32-42-50-REM-10000 / MP ATR-A-32-42-50-00ZZZ-560Z-A.

NoteDispatch is not possible with wheel brake removed.


PK / 75 ATA 32 LANDING GEARMMEL Page n°01

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PK / 75 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 / 75 ATA 35 OXYGENMMEL Page n°01

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PK / 75 ATA 35 OXYGENMMEL Page n°02

36-11-01 HP Valve (M)_3a543cb7-7d35-4c6a-bbc9-a0dfa8532991 3.1

ALL


36-11-02 BLEED Valve (M)_072d6b42-fa3d-4d82-b2c4-e09a02a9a4f6 2.1

ALL


36-11-04 Ground X Feed Valve (M)_4a428ad2-c6c5-4b4a-ad1c-a513435a0a79 3.1

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 / 75 ATA 36 PNEUMATIC SYSTEMMMEL Page n°01

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PK / 75 ATA 36 PNEUMATIC SYSTEMMMEL Page n°02

52-11-01 Door Alert System (M)_903169b9-1c9d-48ec-b8ef-9be412397f77 1.1

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.

NoteApplicable only for Flight Compartment Overhead Hatch

52-31-01 Cargo Door Motor Actuator (if installed) (M)_2f1320b2-1f49-48c5-b8f2-7e37153dd67d 1.1

ALL

Refer to JIC 52-31-00-OAC-10010 / MP ATR-A-52-31-XX-01ZZZ-520Z-A.

52-31-03 AUX AFT Cargo Door (Class C) (if installed) (M)_9252df6d-cda0-4ca2-bb8c-0765699ad6b3 0.1

ALL



PK / 75 ATA 52 DOORSMMEL Page n°01

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PK / 75 ATA 52 DOORSMMEL Page n°02

56-11-01 Windshield (Including Main Windshield, FWD and AFTWindows) (M)Windshield (Including Main Windshield, FWD and AFT Windows) (M)_7994d8cc-8ab8-4d82-a4ae-88a6c91614a9 2.2

ALL

Refer to SRM 56.10.00&Electropneumatic Outflow Valves Blockage in Open PositionRefer to JIC 21-31-20-DEA-10000 / MP ATR-A-21-31-20-00ZZZ-560Z-A.

56-21-01 Passenger Compartment Window (M)_7014e4d1-e26f-4ab5-b9ba-d4376f27f035 0.1

ALL

Refer to SRM 56.21.00


PK / 75 ATA 56 WINDOWSMMEL Page n°01

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PK / 75 ATA 56 WINDOWSMMEL Page n°02

61-42-01 NP Indications (M)NP Indicator (M)_a2d2d5b9-7434-4337-8bcd-70a5ff8ad40d 1.1

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Refer to JIC 30-61-00-OPT-10010 / MP ATR-A-30-61-XX-01ZZZ-320Z-A to check PROP anti-icing is operative.

61-50-01 Propeller Brake (M)_16596579-b13e-4857-b280-ed0a5b5119eb 1.2

ALL



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73-15-01 Fuel Heater (M)_aac38c02-1445-4e54-b369-8ca32a41d4cb REV 3.2

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■ 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 - Anti-icing Additives Table).

Check of oil level:▶ Open left hinged cowl (435AL or 445AL).▶ Check that oil level is to “FULL”.▶ Close cowl(s).


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77-00-02 AFU (M)_b252952d-9060-49a8-ad89-178a93850faf 0.1

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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 1.0

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▶ 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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79-32-01 Oil TEMP Indication (M)_f348196e-0287-41fa-90c0-f7a0fa5dda5b 1.1

ALL

Refer to JIC 12-13-79-CHK-10000 / MP ATR-A-12-13-79-00ZZZ-310Z-A.

79-33-01 Oil Pressure Indication (M)_7d0e2028-dd38-4874-b89b-ae58b01d1832 1.1

ALL

Refer to JIC 79-34-00-OPT-10000 / MP ATR-A-79-34-XX-00ZZZ-320Z-A.


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minimum equipment list - crewserver1.piac.com.pk

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