A350 Line Maintenance Check List Instruction
A350
Line Maintenance
Check List Instruction
Version:
R 14
Date:
2023-10-23
1
A350 Line Maintenance Check List Instruction
Introduction
Line maintenance is an important part of aircraft airworthiness maintenance,
the quality of line maintenance is directly related to the airworthiness of aircraft,
but also an important guarantee of aircraft "safety, comfort, punctuality". In order
to applicable procedures and methods of airline maintenance of A350 aircraft
could be mastered for the maintenance, and improve the quality of airline
maintenance, the A350 line maintenance check list instruction is specially
compiled to further elaborate the inspection points and inspection risks of A350
pre-flight, short-stop and post-flight check list.
Due to the writing time is pressing and the editor's ability is limited, for the
omissions in this manual, please leaders and colleagues to criticize and correct.
Eastern Airline Technic CO.LTD
Engineering Dept.
In April 2020
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A350 Line Maintenance Check List Instruction
Line maintenance instructions inquiry mode
1、PC inquiry mode ： Log on ftp://172.28.36.56/ and enter the folder [LINE MAINTENANCE
CHECK INSTRUCTION MANUAL] to query the latest line maintenance instruction of each aircraft
model.
2、Mobile device inquiry mode：
Log in the [Palm East Airlines] APP, enter the [Maintenance] plate, click
on the [Job description], you can query the latest line maintenance
instruction of each aircraft model.
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A350 Line Maintenance Check List Instruction
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A350 Line Maintenance Check List Instruction
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A350 Line Maintenance Check List Instruction
A350 Line Maintenance Check List Instruction
I. Revision note....................................................................................................................................6
II. Refer to the file............................................................................................................................. 10
III. Work card filling requirements................................................................................................... 10
IV. General inspection requirements.................................................................................................11
V. General inspection item requirements.......................................................................................... 12
VI. Other instructions........................................................................................................................13
VII. External inspection.................................................................................................................... 14
(I) Inspection route....................................................................................................................14
(II) Details of each inspection item...........................................................................................15
VIII. Pre-Flight Check List............................................................................................................. 104
(I) Preliminary Item.................................................................................................................104
(II) Cockpit Inspection............................................................................................................ 104
(III) Cabin Inspection..............................................................................................................110
(IV) Release.............................................................................................................................111
(V) Close-up Item................................................................................................................... 111
IV. Transit Check List......................................................................................................................113
(I) Preliminary Item.................................................................................................................113
(II) Cockpit/Cabin Inspection................................................................................................. 113
(III) Servicing Procedure........................................................................................................ 113
(IV) Release.............................................................................................................................114
(V) Close-up Item................................................................................................................... 114
X. Stay-over Check List..................................................................................................................115
(I) Preliminary Item.................................................................................................................115
(II) Cockpit inspection............................................................................................................ 116
(III) Cabin Inspection..............................................................................................................141
(IV) Cargo inspection..............................................................................................................154
(V) Service work..................................................................................................................... 160
(VI) release..............................................................................................................................164
(VII) Close-up Items............................................................................................................... 164
ETOPS operation additional check................................................................................................. 165
(I) Engine Inspection...............................................................................................................165
(II) APU Inspection................................................................................................................. 165
(III) Cargo Inspection..............................................................................................................165
Appendix 1: aircraft antenna map...................................................................................................166
Appendix 2: list of ground service contacts and cover plates........................................................ 167
Appendix 3: tire damage replacement standard..............................................................................177
Appendix 4: common structural damage on airline routes.............................................................186
Appendix 5: Winding inspection of common fastener damage and defects.................................. 198
Appendix 6: Winding inspection of common seal damage and defects.........................................205
Appendix 7：Cold weather maintenance Tips........................................................................207
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A350 Line Maintenance Check List Instruction
I. Revision note
Revision
The revision
date
Major changes
R2
2021.01.29
1. Delete the statement "only applicable to ETOPS flights" in "
Other Instructions".
2. Delete the items that only involve ETOPS operation in
"Pre-flight Work Order", and add them into "Additional Work
Order for ETOPS Operation Route".
3. Delete the items in "Stay over Work Order" that only involve
ETOPS operation, and add them into "Additional Work Order
for ETOPS Operation Route".
4. Add "Additional Work Order for ETOPS Operation Lines".
R3
2021.06.16
1. Revision of Annex IV "Inspection of Common Damages and
Defects in Post-flight Winding".
2. Revision SO Check and record the pressure value of the
oxygen cylinder of the unit on the SD DOOR: the base station
shall ensure that the oxygen pressure is not less than
1200PSI.Non-base stations ensure that oxygen pressure is not
below the minimum required for planned flights.The minimum
standard for oxygen pressure required for planning flights is
according to Mel (O) 35-10-03A unit oxygen cylinders.
4. Add Detailed rules for each inspection item: 3. Right engine
and hanger area (1) Inspection steps for engine fan blade in
windmill state.
5. Add PF Cabin Inspection: 1. Confirm that there is no peculiar
smell in the cabin ( including seafood, lavatory smell, burnt
smell of equipment, etc ).
6. Add SO Cabin Inspection: 5. Confirm that there is no peculiar
smell in the cabin ( including seafood, lavatory smell, burnt
smell of equipment, etc ).
7. Add SO Cargo hold inspection: 5.Confirm that there is no
peculiar smell in the cargo (including seafood, sewage smell,
burnt smell of equipment, etc ).
8. Add for the work items related to aircraft configuration in
the route work list, the actual aircraft information in service
shall prevail.
R4
2021.09.22
1. Revision the "Clean the shock absorber sliding tube." To
"Clean the shock absorber sliding tube and grounding stud.".
And revise the relevant implementation requirements.
2. Add requirements of toilets servicing.
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R5
2022.01.27
1. Revision the General Inspection Item Requirements 1.
Fuselage skin inspection requirements.
2. Revision the requirements for radome inspection in External
Fuselage Inspection 1.2.
3. Revision the requirements for RVSM area skin inspection in
External Fuselage Inspection 1.4.
4. Revision the requirements for landing gear and doors
inspection in External Fuselage Inspection 1.5.
5. Revision the requirements for RVSM area skin inspection in
External Fuselage Inspection 2.4.
6. Revision the requirements for Inlet Cowl inspection in
External Fuselage Inspection 3.1.
7. Revision the requirements for Wings Inspection in External
Fuselage Inspection 4.1.
8. Revision the names of three certification in Pre-Flight Check
List II 2.2.
9. Revision the names of three certification in Stay-Over Check
List II 3.3.
10. Delete the requirements for the sign lights inspection in
Stay-Over Check List II 4.2.
11. Add Sign Lights Work in Stay-Over Check List II 4.3 and add
relevant implementation requirements.
12. Revision the requirements for the APU Oil Consumption
Calculation in Stay-Over Check List II 7.
13. Revision the requirements for the Crew Oxygen Pressure
Check in Stay-Over Check List II 8.
14. Revision “Cleaning the Landing Gear Shock Strut Mirror” to
“Cleaning the Landing Gear Shock Strut Mirror and Grounding
Pile” in Stay-Over Check List V 2, and revise the relevant
enforcement requirements.
15. Revision the APU Oil Consumption Calculation
requirements in ETOPS Operation Additional Check II.
16. Revision the Appendix 4: Common Structural Damage on
Airline Routes.
R6
2022.06.30
1. Revision the Pre-Flihgt check list（2） .2.2） .renamed the
certification.
2. Revision the Post-Flight check list （ 2 ） .3.3 ） ， the
requirement of clean the cockpit.
R7
2022.07.25
1. Revision the Pre-Flihgt check list（2）3）.the tire pressure
range of the NLG and MLG.
2. Add the Pre-Flight check list (3).2,Visual inspection of wing
upper surface visible area ( LH/RH ) through cabin windows.
Make sure there is no damage or no loosen/missing fastener.
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3. Add appendix 8. Examples of fastener damage.

R8
2022.10.28
1. Revised Appendix 4. Common Structural Damage of airline.
R9
2022.12.24
1. Amendment VIII, (I), "Remove and check the front/main
landing gear safety pins (5), plenum plates (8), multi-function
probe sleeves (3) and spare pitot sleeves (1) intact and place
them on the left front of the nose landing gear tire." For
"Remove and check the front/main landing gear safety pins (5),
plenum plates (8) (if installed), multi-function probe sleeves (3)
and spare pitot sleeves (1) intact, place on the left front of the
nose landing gear tire."
2. Revision 8, (IV) 4, "Check that the front/main landing gear
safety pins (5), plenum plates (8), multi-function probe sleeves
(3) and spare pitot tube sleeves (1) have been removed and are
in good condition." Check that the front/main landing gear
safety pins (5), plenum plates (8) (if installed), multi-function
probe sleeves (3) and spare pitot tube sleeves (1) have been
removed and are in good condition.
3. Revision 8 (IV) 5, "Place the front/main landing gear safety
pins (5), plenum plates (8), multi-function probe sleeves (3)
and spare pitot sleeves (1) in the designated position in the
cockpit." Put the front/main landing gear safety pins (5),
plenum plates (8) (if installed), multi-function probe sleeves (3)
and spare pitot sleeves (1) in the designated position in the
cockpit.
4. Revision X. (5) Service Work 1: Install hydrostatic plate (8),
multi-function probe sleeve (3) and spare pitot tube sleeve
(1)." Is "Install multi-function probe sleeve (3) and spare pitot
tube sleeve (1)."
R10
2023.01.03
1. Amended item VIII.(iv).1 "Complete pre-take-off checks in
accordance with the aircraft deicing/anti-icing program under
ground icing conditions." Is "Confirm that deicing/anti-icing
inspectors have completed the aircraft's exterior inspection
under ground icing conditions, and inform the crew of the
inspection results."
2. Amendment to Item IX.(iv).1 "Complete pre-take-off checks
in accordance with the aircraft deicing/anti-icing Program
under ground icing conditions." Is "Confirm that
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A350 Line Maintenance Check List Instruction
deicing/anti-icing inspectors have completed the aircraft's
exterior inspection under ground icing conditions, and inform
the crew of the inspection results."
Add item X. (iii) 3. 3) Execution requirement of "Emergency
Equipment in Place" "Check the distribution diagram of
emergency equipment to ensure that the quantity and location
of emergency equipment meet the requirements. Note: Pay
special attention to the extension, baby seat belt and other
common equipment check."
R11
2023.04.21
1. New way to inquire airline work order instruction.
2. Add X. (iii).4.2), NOTE Information: According to the
requirements of MEL, for the exit sign signal and the exit
position signal of the main channel, at most three
non-adjacent LED lights in each signal lamp can fail. It is
recommended to compare the external brightness of the signal
lights at different positions. If the LED lights are not on or the
signal lights are dim, remove the panel of the signal lights for
further
confirmation
and
processing.
(See
MP
A350-A-33-51-XX-01001-310A-A and MEL 33-50-04.)
3. Amend Appendix 4 "Common Damage and Defects in
Post-flight Winding Inspection" to "Common Damage and
Defects in Post-flight Winding Inspection".
4. Add Appendix 5, Winding Inspection of Common Fastener
Damage and Defects, and move the defects related to
fasteners in the original Appendix 4 to Appendix 5.
5. Add Appendix 6, Common Sealing Damage and Defects for
Inspection of Winding Machine, and move the defects related
to sealing in the original Appendix 4 to Appendix 6.
R12
2023.05.30
1. The contents of the newly added "VIII. Pre-voyage Work
Order" (IV) Release "are described as follows: Verify that the
ELB device is set to airplane mode and placed in the ELB
storage box. (Aircraft equipped with ELBs)
2. Item contents in "(4) Release" in "9. Short Stop Work Order"
are added as follows: Verify that the ELB device is set to
airplane mode and placed in the ELB storage box. (Aircraft
equipped with ELBs)
3. Item contents in "(I) Project Preparation" in "X. Post-flight
Work Order" are added as follows: Check with the unit to
ensure that the ELB device is present. (Aircraft equipped with
ELBs)
4. Item contents in "(ii) Cockpit Inspection" in "X. Post-flight
work Order" are added as follows: Check that the ELB storage
box is in good condition and the charging function is normal.
(Aircraft equipped with ELBs)
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A350 Line Maintenance Check List Instruction
5. The item content of "(ii) Cockpit Inspection" in "X. Post-flight
work Order" is added as follows: Verify that the ELB charger
and charging cable are in place. (ELB-equipped aircraft) (Base
station only)"
6. Item contents in "(VI) Release" in "X. Post-flight Work Order"
are added as follows: Ensure that the ELB device is in good
condition and the remaining battery capacity is greater than
50%. Shut down the device and place it in the ELB storage box.
(Aircraft equipped with ELBs)
R13
2023.09.15
1. Add the Appendix 7：Cold weather maintenance Tips
2. Added reference manual links and requirements in (2).12.8)
of "7. Fuselage External Inspection".
3. Add the requirement to section 3, Passenger Cabin Checks
in the new "X. Post-flight Work Order": "For oxygen and fire
extinguisher bottles at 1L/R location, confirm that the display
head is positioned diagonally downward and easily reads the
values."
4. Revise the standard for checking the wear of short-stop
brakes when setting up the parking brake in (2) .5.5 of "VII.
External inspection of the airframe": When setting up the
parking brake, the length of the indicator pin should be more
than 0 mm.
R14
2023.10.23
1. Revise post-flight work Order, (ii).4.7, "Onboard EFB
Installed and powered off. Check that the three power
adapters are installed properly” to “Onboard EFB Installed and
powered off. Check that the power adapters are installed
properly”.
II. Refer to the file
1.
Maintenance Procedure (MP);
2.
Maintenance Planning Document (MPD);
3.
Maintenance industry standard (MSCA);
III. Work card filling requirements
1. The items must be completed and signed successively. In order to reduce the amount of
signature, the signature points of some projects were combination.
2. Fill in "N/A" of inapplicable record signature or select "not applicable" in e-sign field.
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A350 Line Maintenance Check List Instruction
3. For multiple projects with different applicability or execution under different
circumstances sharing a single signature point, as long as one of the projects is
applicable for execution, it is normally signed as applicable, (this signature indicates the
applicable executed and the non-applicable do not need to be executed).
4. Test data should be filled in the measured value, not "normal", "qualified" and other words.
5. The signature on the work card should be in full name, not in place of signature.
6. Items marked "signed by release personnel" in the signature bar shall be signed by release
personnel.
7. For non-electrical work card, the handwriting filled in maintenance records should be neat
and clear. In principle, it should not be altered. If it needs to be modified, the short
horizontal line should be crossed out, and the correct content should be filled in nearby,
and the name, date and reason for modification should be signed.
8. The work card should be filled in/signed at the work site.
IV. General inspection requirements
1. There are no rules on the order of inspection on the outside of the fuselage, the cockpit, the
cabin, the cargo compartment, the service work and other major items in the airline bill,
so they can be adjusted before and after according to the implementation of the work.
2. Only the inspection of the outside of the fuselage must be carried out in accordance with
the order specified in the inspection route around the machine. There is no order for the
specific small items in each area. It is ok to completely cover and not miss items during
the inspection in this area.If some areas are inconvenient for subsequent inspection due
to the situation of the corridor bridge, the boarding gate and the fuselage skin of the
relevant areas can be checked first, and then the complete inspection of the outside of
the fuselage can be carried out according to the normal inspection route around the
plane.If the inspection is interrupted for any reason, be sure to mark it and continue the
inspection of the outside of the aircraft from this area.
3. For the specific items in the inspection items such as cockpit, cabin, cargo hold and service
work, there is no order (except for those items that are in order logically, for example,
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A350 Line Maintenance Check List Instruction
the amount of lubricating oil must be checked before the calculation of sliding
consumption can be carried out), it can be adjusted before and after the work
implementation to ensure that no items are missing.
4. The general requirement for visual inspection is to inspect the visually visible portion of
the aircraft on the ground without the aid of ladders or platforms. If abnormalities are
found or suspected, a detailed visual inspection is required.
5. Detailed visual inspection is generally defined as: visual inspection of aircraft components,
structures and systems for damage, failure or non-compliance. In addition to normal
light sources, this level requires additional direct light sources if necessary.The examiner
may use a mirror, magnifying glass, or other tool to assist in the examination if
necessary. If necessary, clean the inspection area or open a nearby cover during the
inspection so that the inspector can get as close as possible to the inspection area for
inspection.
6. The outer inspection of the fuselage shall be combined by far and near, tangential and
vertical. The overall situation can be observed from the far position, and the external
defects of the aircraft can be checked from the far and near position. It is easier to find
defects such as surface pits by inspection along the tangential direction, while it is easier
to find surface cracks, scratches, lightning strikes and other damages by inspection along
the vertical direction.
7. If the abnormal situation is found during the inspection according to the airline work order,
the state assessment, troubleshooting and defects shall be carried out according to AMM
and other maintenance manuals.
V. General inspection item requirements
1. Fuselage skin: to ensure that the visible area of the skin without serious depainting, no
wrinkles, no bulging, no wind erosion, no pits, no scratches, no lighting strike, no cracks,
no rivet loose, no bird strikes and other defects.
2. Fasteners: check the fasteners loss or looseness for the belly of the fuselage, the lower
surface of the wings, and the cover plate of the pylon.
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3. Discharge hole/outlet: no leakage of abnormal liquid.If liquid leakage is found, it is
necessary to determine the nature of the liquid and the source of the liquid so as to
determine whether there is a need for troubleshooting.
4. Air intake/exhaust: no damage, no foreign body blockage.
5. Service cover plate: make sure that all service cover plates of the fuselage are closed and
locked when not in use, and the lock is flush. Check that there is no loose gap when the
cover plate is closed and fastened, and the hinge is in good condition and without
cracks.Be sure to close the cover after opening it.
6. Electrical circuit of the hydraulic pipeline in the landing gear area: there is no wear of the
hydraulic pipeline in the landing gear area, no leakage of the pipe joints, no wetting of
the hose, no distortion. No wear, no pollution, no loose plug.
7. Inspection of emergency equipment: the number of aircraft emergency equipment in
different configurations may be different. Check the equipment according to the aircraft
emergency equipment diagram and the marks in the region, confirm the corresponding
emergency equipment and place it in accordance with the regulations.If the quantity is
limited, the corresponding equipment shall be counted correctly; Check the status of
emergency equipment.
VI. Other instructions
1. For the work items involving aircraft configuration in the route work order, the actual
aircraft information in service shall prevail.
2. There are special requirements for some projects, as follows:
1) Apply only to projects executed by the base station
This project only needs to be executed at the base station, not at the non-base station.
2) Cold weather has special maintenance requirements
This project has special maintenance requirements in cold weather. Please refer to the
corresponding project requirements in the airline bill manual for details.
3) Not applicable to flight engineer
This program does not apply to flight engineer. There is no need to implement this
program for flight engineer.
4) Only applicable to flight engineer
This program is only applicable to flight engineer. No need to implement this program
for non-flight engineer.
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VII. External inspection
(I) Inspection route
1. This route from the right side of the plane to the left, a total of 12 station points.
2. Visual inspection is required continuously on the route.
3. Before inspection the aircraft should be in advance to understand the single aircraft
technical situation.
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(II) Details of each inspection item
1. Nose section and nose landing gear and wheel bay area
(2.1) area
(2.1) route
1) Fuselage, 1L cabin door and 1R cabin door no damage.
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 Airframe: no lightning strike, no dent, no scratch, no crack, no bird strike and other defects
in the skin of the visible area.
 Ref. A350-A-05-22-XX-00001-310A-A
General Visual Inspection of Upper Half of Fuselage (above Cabin Floor) (External
Surfaces Only)
 1L cabin door and 1R cabin door have no lightning strike, no pits, no damage, no corrosion,
no scratches, cracks, creases, etc.
 Ref. A350-A-05-28-XX-04001-310A-A
General Visual Inspection of the Passenger/Crew Doors, LH/RH (External Surfaces
Only)
2) Radome no damage, latch locked.
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 No serious missing paint, no lightning strikes, bird strike, pits, scratches or cracks.
 Radome latchs locked.
3) Side-slip probe (if installed), ice detection visual indicator, Stand-by pitot probe,
multi-function probe, AOA probe, ice detector probe, OAT no damage and blockage.
 Side-slip probe (three if installed), ice detection visual indicator (two), Stand-by pitot
probe (one), multi-function probe (three), AOA probe (one), ice detector probe (two)
clean, no FOD, no deformation, damage or cracking.
 Side-slip probe, Ref. A350-A-34-1X-XX-00003-310A-A.
 Ice indicator, left and right: no damage, deformation, missing coating, etc.
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A350 Line Maintenance Check List Instruction
 Stand-by pitot, multi-function probe, AOA probe (according to aircraft applicability),
Ref.MP A350-A-34-1X-XX-00003-310A-A or A350-A-34-1X-XX-00005-310A-A.
 Multi-functions probe and Stand-by pitot probe sample hole are no blockage and covering.
 Ice probe no loose, damaged, etc.
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 Check OAT sensor no damage or blockage.
4) Standby static port no blockage and no damage. Skin area inside of RVSM sensitive area
no damage and no wrinkled.
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 Clean static pressure hole (no FOD, no pollutants, no water, no ice, sampling hole
unobstructed)
 Static pressure hole is well installed, no lightning strike point (burn, stain, etc.), no
overheating blackening phenomenon.
 The skin in the RVSM area within the range of red and white Angle standard has no
damage, scratches, pits,wrinkles, deformation, etc., and the paint layer has no bubbling
and falling off.
 Ref. A350-A-34-1X-XX-00003-310A-A Inspection/Check of the Probe
or A350-A-34-1X-XX-00005-310A-A Inspection/Check of the Probes
5) There is no damage or leakage to wheel bay door, wheel well and landing gear area..
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 Post-flight, the front landing gear wheel door should be opened to inspect the inside of the
wheel compartment. Transit and pre-flight only check the wheel cabin parts in the visual
range.
 No oil leakage can be seen in the hydraulic pipeline inside the wheel well.
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 All parts of the landing gear are installed correctly, no external leakage, no damage, no
bird strike.
 The front wheel doors and follow-up doors (two) no pits, damage, strike points and bird
strike. The sealing strips are in good condition and there is no damage.
 The landing gear components no corrosion, no damage, no crack and no oil leakage.
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 The turning hydraulic assembly and locking assembly no oil leakage.
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 The front landing gear downlock spring no damage or crack.
 There is no damage to the electrical wiring protection layer in the landing gear area.
 Secure and clean access to the switch.
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A350 Line Maintenance Check List Instruction
 Ref. A350-A-05-27-10-00001-310A-A General Visual Inspection of Nose Landing Gear
(EWIS)
 Ref. A350-A-05-27-10-01001-310A-A General Visual Inspection of the NLG Forward Door,
LH/RH
 Ref. A350-A-05-27-10-02001-310A-A General Visual Inspection of the NLG Aft Door,
LH/RH
6) Shock strut sliding tube for correct extension, no damage and no leakage.
 The landing gear shock absorbers no external damage and the mirror cleaning no damage,
no oil leakage.
 The extension of shock absorber sliding tube no less than the width of one hand
before/after flight; The mirror does not compress to the bottom in transit.
 If the extension of shock absorber sliding tube does not conform to the above regulations,
it may be in a situation that does not conform to the manual standards. According to
A350-A-32-21-XX-00001-310A-A, and corresponding maintenance work should be taken
as required.
 Ref. A350-A-32-21-XX-00001-310A-A General Visual Inspection of NLG Shock Strut
7) Wheels rim、the rotating interface-unit and tie bolts no damage and no missing.
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 No damage or crack on wheel rim.
 Fixed bolt in position, no damage, no loose, no loss.
 The inflatable valve and overpressure release plug are in place and properly insured.
 Wheel pressure sensor base nut and pin in position.
 Inflatable mouth cap is properly installed.
 The rotating interface component has no damage, good fixation, no missing parts, no
corrosion or crack on the surface.
 Dust cover screw is not loose.
 This project is MPD: 324100-00M02, Ref. A350-A-32-41-XX-01001-310A-A General
Visual Inspection (GVI) of the Wheels, Tires and Brakes
8) Tire wear, damage did not exceed the standard.
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 The tyre does not have the puncture injury to see the line, the block, the crack.
 The surface of the tyre is free from flammable material contamination (dust, flannelette,
chemicals, solvents, etc.).
 Ref. A350-A-32-41-XX-03001-310A-A Visual Inspection of the Wheels and Tires for
Wear and Damage
9) Takeoff and Taxi / Turn off lights lenses no damage.
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 Takeoff and Taxi / Turn off lights lenses: no cracks, damage, etc. As necessary to clean.
 The fixed clamp is not loose.
10) NLG wheel door lever no damage and secured.
2. Right forward fuselage and right wing root area
(2.2) Area
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(2.2) route
1) Fuselage、FWD cargo door and 2R cabin door no damage.
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 Fuselage: no lightning strike, no dent, no scratch, no crack, no bird strike and other defects
in the skin of the visible area.
 Ref. A350-A-05-22-XX-00001-310A-A
General Visual Inspection of Upper Half of Fuselage (above Cabin Floor) (External
Surfaces Only)
 FWD cargo door and 2R cabin door no lightning strikes, no pits, no damage, no corrosion,
no scratches, cracks, creases, etc.
 Cargo door:
When closed: 1. No scratches, no pits, no paint on the door frame.
2. Cargo compartment door handle mechanism is flush.
3. The cargo compartment door closing flag is flush with the door.
4. Cover the cargo compartment loading operation cover.
5. Cargo door switch cover plate is covered.
When opening:1. The sealing strip of the cabin door is clean and in good condition
without serious deformation.
2. No damage to hatch cover.
3. There is no oil leakage from the actuator cylinder of cargo
compartment door.
4. The inside of the door frame should be cleaned without sundries.
5. The door adjacent to the cargo hold is in good condition.
 Ref. A350-A-05-28-XX-04001-310A-A
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A350 Line Maintenance Check List Instruction
General Visual Inspection of the Passenger/Crew Doors, LH/RH (External Surfaces
Only)
 Ref. A350-A-05-28-XX-02001-310A-A
General Visual Inspection of the Forward and Aft Cargo-Compartment Doors and the
Bulk Cargo-Compartment Door (External Surfaces Only
 Ref. A350-A-05-28-20-00001-310A-A
General Visual Inspection of the Forward Cargo-Compartment Door, which includes
the Door Seal (but does not include the External Skin Surface)
2) Negative pressure valve in closed position.
 Visual inspection of the negative pressure valve, confirm that the negative pressure valve
in the closing position, valve flap no deformation.
3) Taxi Camera light lenses、Wing / Engine anti-ice lights lenses and Landing light lenses no
damage.
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 Taxi Camera light lenses、Wing / Engine anti-ice lights lenses and Landing light lenses: no
cracks, damage, etc.
4) The static ports no blockage and no damage. Skin area inside of RVSM sensitive area no
damage and no wrinkled
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 Clean static ports (no FOD, no pollutants, no water, no ice, unobstructed sampling hole )
 Static pressure hole is well installed, no lightning strike point (ablation, stain, etc.), no
overheating blackening phenomenon.
 The skin in the RVSM area within the range of red and white Angle standard has no
damage, lighting strike, scratches, pits, wrinkles and deformation etc., and the paint
layer has no bubbling and falling off.
 Ref. A350-A-34-1X-XX-00003-310A-A Inspection/Check of the Probe
or A350-A-34-1X-XX-00005-310A-A Inspection/Check of the Probes
5) Crew oxygen green discharge chip in place.
 Confirm that the green discharge chip in place. The yellow ring can be seen when the
green discharge disc in place is blown off. Ref. A350-A-35-12-XX-01001-04CA-A
6) IGGS outlet、LAV and galleys air extraction outlet 、pack air intakes and outlets、pack bay
ventilation air inlets and outlets and Conditioned service air system outlets no blockage.
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 Check that the IGGS outlet is not blocked and keep the area around the outlet clean
 Pack air intakes is no damage and no blockage
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
Pack air outlets is no damage
 LAV and galleys outlet is no damage and no blockage
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 Pack bay ventilation inlets is no damage and no blockage
 Servo air system outlets no blockage is no damage.
7) Ram air inlet flap is closed.
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 Make sure that Ram air inlet flap is closed and there is no external damage
8) Yellow hydraulic system and ground conditional service access panel no damage and
secured.
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 The panel locked secured, the surface is no damage.
9) The leading edge slat and lower surface no damage and no leakage
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 Visually inspect the leading edge slats for no external damage, ensuring no pits, no
deformation, no scratches, no cracks, no rivets loose, and no abnormal liquid leakage.If
structural damage such as pits is found, Ref. MP A350-A-57-41-61
 There is no leakage of fuel on the lower surface and the water valve of the big wing tank
3. Right engine and pylon area
(2.3)Area
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(2.3) route
1) Inlet cowl、Acoustic panels、T20 probe、Inlet cone、Fan blades、Engine inlet area、Fan
outlet acoustic panels、Fan Outlet Guide Vanes、Bypass area、Fan cowl、Thrust reverser、
Nacelle and pylon exterior surface and access panels no damage and no FOD.
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 Inspection confirmed no visible damage, bird strike, delamination, swelling and other
defects to the inlet cowl.
 Check 22 fan blades for no damage, no deformation, no FOD.
 Check and confirm that there is no visible damage or defect in the inlet cone, and the inlet
cone anti-icing rubber is in place and normal.
 Check to make sure the fan blade ring filling block is in place with no visible damage.
 Inlet cone with no sag.
 (Inlet cone inspection Ref. MP A350-A-72-21-61-001-310A-A General Visual Inspection
(GVI) of the Air Intake Fairing/Spinner)
 (Fan blade Inspection, Ref. MP A350-A-72-31-62-001-310A-A General Visual Inspection
(GVI) of the LP Compressor)
Note: If the engine blade is in the state of windmill during inspection, please follow the
following steps (choose one or the other):
(1) On the premise of ensuring the personal safety of maintenance personnel, put on
gloves, press the fan rectifier cone with both hands from both sides, and slowly reduce the
fan blade speed through friction resistance until visual inspection can be carried out.
Or (2) stop the rotation of the fan blades by covering the engine cover.
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 Check and confirm that the T20 probe is in place, and the probe is clean and in good
condition, without blocking, deformation or loosening.
 Check to make sure Acoustic layer is no damage.
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 Check and confirm no visible damage or defects in inlet port, Fan cowl, Thrust reverser
and Nacelle.
 Check to make sure the fan cowl and thrust reverser is locked, thrust reverser is in uplock
position.
 (Inlet cowl, fan cowl, thrust reverser, nacelle, exhaust nozzle and tailcone area. If any
damage is found, refer to the AIRCRAFT STRUCTURAL REPAIR manual in chapter
54 for inspection standards and handling measures.)
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
Check to make sure there is no damage to the engine inlet area and no FOD.
 Check no damage to fan outlet guide vanes
 Check and confirm that there is no foreign substance and no damage to the air passage in
the bypass area.
 Check the fan outlet acoustic board is not damaged
 Check there is no damage to the thrust reverser door
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 Check no damage to fan case A stem
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 Check the guide bar for no damage.
2) Exhaust nozzle and tailcone area、LPT6 blades and LPT Outlet Guide Vanes no damage no
metal deposition.
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3) Inlet cowl anti-ice exhaust and Engine ventilation grid no damage、no blockage.
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4) Oil filling port、Engine oil service access、Starter valve override access、Fan cowl and
Thrust reverser Latch Access Panels、Pressure Relief doors in place、closed and locked.
 Access panel is closed and locked.
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 Make sure oil filling port is closed and locked.
 Starter valve override access no damage, closed and locked.
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 Check and make sure Fan cowl and Thrust reverser Latch are closed and locked, no oil on
the joint.
5) Engine drain mast and Pylon drain no blockage、no leakage.
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 Engine drain mast no leakage. If there is liquid leakage, define the quality of the liquid and
check the leakage rate. Leakage standard reference MP A350-A -71-71-63-00001-360-A
-A Check of the Leakage Rates at the Drains Mast
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 Pylon drain no blockage、no leakage.
4. Right wing area
(2.4) Area
(2.4) Route
1) Wing leading/trailing edge、lower surfaces、wing tips、flap track fairings、jettison valve
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no damage and no leakage.
 Visually inspect leading edge slats, ailerons, flaps, wingtip flaps, flap track fairings, lower
surfaces and any panel no external damage, no pits, bird strikes, deformations, scratches,
cracks, loose rivets, and abnormal liquid leakage. If structural damage such as pits is
found,
refer
to
MP
A350-A-57-46-61-01001A-A
(2,3,4,5
slats),
A350-A-57-46-65-01001A-A (6,7 slats), MP A350-A-57-54-62-00001-661A-A (inner
flaps), MP A350-A-57-56-61-00001-661A-A (outer flaps), MP A350-A-57-61-61-61
(ailerons), MP A350-A-57-31-61 (wingtip flaps), MP A350-A-57-57 (flaps track fairing)
 Visually inspect all steering surfaces (slats, ailerons, flaps) to ensure no serious paint
missing, no lightning strike, no pits, no scratches, no cracks, no rivets loose, no
abnormal liquid leakage. If hydraulic oil leakage is found, refer to MP
A350-A-29-XX-XX-00ZZZ-360Z-A as standard.
 Visual inspection jettison valve no oil leakage, no external damage, and no deformation.
2) Navigation lights, strobe lights and taxi camera light lenses no damage.
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 Navigation lights, strobe lights and taxi camera light lenses: no cracks, damage, etc.
3) Static dischargers in place and no damage. ( Four items on wingtip )
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 No loss, no fork, no damage caused by lightning.
Note: Static dischargers is worn or damaged when the tip is not cylindrical.
 Reference: MP A350-A-23-61-XX-001-310A-A
4) Tank overpressure discharge chip are in place.
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 Check Tank overpressure discharge discs are in place, no damaged with light.
5) Surge tank air intake no blockage.
 Check the inlet is not blocked and the surface is not damaged
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 Check the drain valve and the lower surface for no fuel leakage.
6) Refueling station access door no damage，secured.
 Visual inspection the refueling service panel no damaged, locked and secured.
5. Right landing gear assembly and well area
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(2.5) area
(2.5) route
1) Landing gear door, wheel well, landing gear no damage and no leakage.
 The main landing gear door should be opened to inspect the inside of the wheel
compartment in stayover. There is no requirement to open the main landing gear wheel
door in pre-flight and transit, check the wheel compartment parts within the visual
range.
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 Main landing gear door and follow-up door are no pits, damage and lightning strike points.
The sealing strips are in place and no damage.
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 Hydraulic piping and components inside the wheel well visual area no leakage.
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 Landing gear components no damage.
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 Downlock spring of the main landing gear no damage.
 Electrical wiring protection layer in the landing gear area no damage.
 Secure and clean access to the switch.
 Outer tube, strut, bogie, PTC, up and down torsion connecting rod, protective coating no
corrosion, no damage, no deformation, no crack, no wear, no scratch, no pits and burrs.
 The locking pin is firm and without damage.
 There is no damage or crack in the lock spring.
 The adjacent switch is clean, without damage, corrosion or loosening.
 There is no damage crack in the block of bogie.
 There is no leakage of hydraulic pipe and components in the wheel well.
 Follow - up hose without distortion, wear, leakage
 Ref. A350-A-05-27-30-00001-310A-A General Visual Inspection of Main Landing Gear
(EWIS)
 Ref. A350-A-05-27-30-02001-310A-A General Visual Inspection of the MLG Doors
(EWIS)
 Ref. A350-A-05-27-30-01001-310A-A General Visual Inspection of Cylinder Main
Landing Gear Door (EWIS)
 Ref. A350-A-05-27-30-03501-310A-A General Visual Inspection of Secondary Main
Landing Gear Door LH/RH (EWIS)
2) Shock absorber sliding tube correct extension no damage and no leakage.
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 There is no external damage to the landing gear shock absorbers, no damage to the mirror
cleaning, no leakage.
 The extension of shock absorber is no less than the width of one hand pre/post flight. The
mirror does not compress to the bottom in transit.
 When it is found that the extension does not conform to the above regulations, it means
that the Shock absorber sliding tube is in an incorrect condition. The front landing gear
must be checked according to A350-A-32-21-XX-00001-310A-A, and corresponding
maintenance work should be taken as required.
 Reference the A350-XX-02001-A-32-11-310-A-A
General Visual Inspection of MLG Shock Strut
3) Wheels rim、rotating interface-unit、brake cooling fan kit attached and tie bolts no damage
and no missing.
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 The item comes from MPD: 324100-00M02, Ref. A350-A-32-41-XX-01001-310A-A
General Visual Inspection (GVI) of the Wheels, Tires and Brakes
 Wheel rim no damage and crack.
 Fie bolt in position, no damage, no loose, no loss.
 The inflatable valve and overpressure release plug are in place and properly insured.
 Wheel pressure sensor base nut and pin in position.
 Inflatable mouth cap is properly installed.
 The rotating interface-unit has fixed, no damage, no missing parts, no corrosion or crack
on the surface.
 Dust cover screw is not loose.
 Brake cooling fan kit has no damage and is installed correctly, and its surface is free from
corrosion, crack and flammable material contamination (dust, flannelette, chemicals,
solvents, etc.).
4) Tire wear and damage not exceed limits.
 The item comes from MPD: 324100-00M02, Ref. A350-A-32-41-XX-01001-310A-A
General Visual Inspection (GVI) of the Wheels, Tires and Brakes
 The tire does not have the puncture to see the line, the block, the crack.
 The surface of the tire is free from flammable material contamination (dust, flannelette,
chemicals, solvents, etc.).
 Main tire maintenance inspection additional standard, see GCEB-2019-a350-32-203.
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5) The brake wear indicator not exceed limits..
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 This item comes from MPD: 324100-00M03, Ref, A350-A-32-41-XX-00001-310A-A
Visual Check of the Brake heat-pack wear-indicator
 Inspection standard for pre/post-flight brake wear: when setting park brake, the output of
indicator pin should be ≥0.5mm.
 Inspection standard for transit brake wear: when setting park brake, the output of indicator
pin is ＞0mm.
 When measuring the length of the wheel brake indicator pin is less than or equal to 1mm, it
is required to measure again after the brake temperature is less than 60 ℃.
6) Brake units no leakage and no damage.
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 This item comes from MPD: 324100-00M02-01, Ref.350-A-32-41-XX-01001-310A-A
General Visual Inspection (GVI) of the Wheels, Tires and Brakes
 Brake units no leakage, no damage, no corrosion, no cracks, no missing parts.
 Brake hub vent cap in position.
 There is no leakage in the brake actuator and the connected hydraulic self-sealing joint.
 No overheat crack on brake torque lever.
 Brake temperature sensor installed correctly, no signs of damage, plug installed correctly.
 Brake bolt in position, safety in position.
 No damage, no fracture, no oil contamination of brake disc.
6. Right rear fuselage area
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(2.6) area
(2.6) route
1) Fuselage, 3R cabin door, AFT cargo door and 4R cabin door no damage.
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 Visible area of the skin without lightning, no pits, no scratches, no cracks, no bird strikes
and other defects.
 3R cabin door, AFT cargo door and 4R cabin door no lightning strike, no pits, no damage,
no corrosion, no scratches, cracks, creases, etc.
 Cargo door:
When closed: 1. No scratches, no pits, no paint on the door frame.
2. Cargo door handle mechanism is flush.
3. The cargo compartment door closing flag is flush with the door.
4. Cover the cargo compartment loading operation cover.
5. Cargo door switch cover plate is covered.
When opening 1. The sealing strip of the cabin door is clean and in good condition
without serious deformation.
2. No damage to hatch cover.
3. There is no oil leakage from the actuator of cargo door.
4. The inside of the door frame should be cleaned without sundries.
5. The door adjacent to the cargo hold is in good condition.
 During short stoppage, the front door and threshold of the cargo hold should be checked
without damage or corrosion.
 Reference the A350 - A - 05-28 - XX - 04001-310 - A - A
General Visual Inspection ofthe Passenger/Crew Doors, LH/RH (External Surfaces
Only)
 Reference the A350 - A - 05-28 - XX - 02001-310 - A - A
General Visual Inspection of the Forward and Aft Cargo-Compartment Doors and
the Bulk Cargo-Compartment Door (External Surfaces Only)
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 Reference the A350-310 - A - A - 05-28-20-00001 - A
General Visual Inspection of the Forward Cargo-Compartment Door, which
includes the Door Seal (but does not include the External Skin Surface)
2) Ram air turbine doors are closed.
 Ram turbine access door 198PR and 1989 QR alignment
 The P-seal is well sealed and has no clearance
3) Potable water drain mast no dmage.
 Make sure that there is no leakage in the access panel of drinking water system and toilet
system
 Potable water service close to the cover without damage, locked.
7. Empennage and APU area
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(2.7) area
(2.7) route
1) THS and elevators, vertical stabilizer and rudder no damage and no leakage.
 Visually inspect all steering surfaces (elevator, stabilizer, rudder) to ensure that there is no
serious paint removal, no lightning strikes, no skin wrinkles, no pits, no scratches, no
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cracks, no rivets loose, and no abnormal fluid leakage. If hydraulic oil leakage is found,
refer to MP A350-A-29-XX-XX-00ZZZ-360Z-A as standard. For structural damage
such as pits, refer to MP A350-A-55-32-61-00001-661A-A, MP A350-A-55-12-7
1-05001-661A-A.
2) Navigation and strobe lights lenses no damage.
 Navigation and strobe lights lenses no damage no crack, damage, etc.
3) Static dischargers for no damaged and in place. ( Vertical stabilizer: 4; horizontal stabilizer:
7 for each side and totally 14 )
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 No loss, no fork, no damage caused by lightning.
Note: the discharge brush is worn or damaged when the tip is not cylindrical.
 Reference: MP A350-A-23-61-XX-001-310A-A
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4) APU drain no damage, no leakage.
 There was no abnormal leakage of liquid. If liquid leakage is found, it is necessary to
determine the nature of the liquid and the source of the liquid so as to determine whether
there is a need for darining.
5) APU overpressure door and access doors are closed and secured.
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A350 Line Maintenance Check List Instruction
 Make sure that the APU access door and nacelle lock locks are closed and flush when not
in use.
6) Exhaust for no damage, no blocked.
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 No wrinkles, no pits, no cracks, no lightning strikes, no bird strikes and other defects. No
foreign body blockage.
8. Left rear fuselage and bottom area
(2.8) area
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A350 Line Maintenance Check List Instruction
(2.8) route
1) Fuselage 、 bulk cargo door 、 4L cabin door 、 3L cabin door and tailstrike indication no
damage.
 No scratches on the door frame of bulk cargo door, no pits on the anti-scratch piece.
 Visible area of the skin without lightning, no pits, no scratches, no cracks, no bird strikes
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and other defects.
 No lightning strike, no pits, no damage, no corrosion, no scratches, cracks, creases, etc. for
4L cargo doors, front cargo doors and 3L cargo doors.
 Check the tailstrike indicator for no damage.
2) Waste tank service access panel and green hydraulic system service access panel no
damage and secured.
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3) Air extraction outlet 、 waster water drain mast 、 Outflow valve 、 LAV and galleys air
extraction outlet、Supplement cooling air intakes and outlets no blockage.
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4) Bilge drain port no leakage.
9. Left landing gear assembly and well area
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(2.9) arrea
(2.9) route
 Inspection criteria refer to "right landing gear assembly and well area (2.5)".
10. Left wing area
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(2.10) area
(2.10) route
 Inspection criteria refer to "right wing area (2.4)".
11. Left engine and pylon area
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(2.11) area
(2.11) route
 Check standard reference "right engine and pylon area (2.3)".
12. Left wing root, left forward fuselage and bottom area
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(2.12) area
(2.12) route
1) Wing leading edge and lower surface no damage and no leakage.
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 Visually inspect the leading edge slats for no external damage, ensuring no pits, no
deformation, no scratches, no cracks, no rivets loose, and no abnormal liquid leakage.If
structural damage such as pits is found, refer to MP A350-A-57-41-61
 There is no leakage of fuel on the lower surface and the drain valve of the wing tank
2) Landing light、Anti-collision light lenses、Wing/Engine scan lights lenses、Taxi Camera
light lenses and Camera no damage.
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 Landing light, anti-collision light lenses, wing/engine light lenses, taxi camera light lenses
no cracks, damage, etc.
3) Ground HP access PNL and wheel well door operation access PNL no damage and
secured.
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 Each service panel is closed and locked well when not in use, and the lock is even. Check
that there is no loose gap when the panel is closed and fastened, and the hinge is in good
condition and without cracks.Be sure to close the panel after opening it.
4) IGGS outlet 、 pack air intakes and outlets 、 MLG bay ventilation air inlets 、 pack bay
ventilation air inlets and outlets and conditioned service air system outlets no blockage.
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 Check that the IGGS outlet is not blocked and keep the area around the outlet clean
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5) Center tank fuel pump drain holes and Bilge drain holes no leak.
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6) Fuel drain mast and waste water drain mast no blockage.
 Make sure there is no blockage or leakage in fuel drain mast.
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7) LAV and galleys air extraction outlet、Avionics ventilation overboard valve and Outflow
Valve no blockage.
 Avionics ventilation valve, outflow valve, flashlight inspection is recommended at night.
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8) Mode S/TCAS antenna、radio altitude transmitting and receiving antenna、DME antenna、
Marker antenna and VHF antenna no damage.
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 The Mode S/TCAS antennas in position, no missing, sealant in good condition, no
mechanical damage (such as dents, deformations, cracks etc.), no erosion (such as paint
layer peeling).
 RA (transmission and reception) antennas in position, no missing, sealant in good
condition, no mechanical damage (such as dents, deformations, cracks etc.), no erosion
(such as paint layer peeling).
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 DME antennas in position, no missing, sealant in good condition, no mechanical damage
(such as dents, deformations, cracks etc.), no erosion (such as paint layer peeling). If
defects are found, handle according to MP A350-A-34-51-11-00001-282A-A.
 Marker antenna in position, no missing, sealant in good condition, no mechanical damage
(such as dents, deformations, cracks etc.), no erosion (such as paint layer peeling).
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 VHF antennas in position, no missing, sealant in good condition, no mechanical damage
(such as dents, deformations, cracks etc.), no erosion (such as paint layer peeling). If
defects are found, handle according to MP A350-A-23-12-11-00001-282A-A.
9) The static ports no blockage and no damage. Skin area inside of RVSM sensitive area no
damage and no wrinkled
 Clean static port (no foreign substance attached, no pollutants, no water, no ice,
unobstructed sampling hole and no foreign matter)
 Static port is well installed, no lightning strike point (ablation, stain, etc.), no overheating
blackening phenomenon.
 The skin in the RVSM area within the range of red and white Angle standard has no
damage, wrinkle, deformation, etc., and the paint layer has no bubbling and falling off.
 Refer to A350-A-34-1X-XX-00003-310A-A Inspection/Check of the Probe
Or A350-A-34-1X-XX-00005-310A-A Inspection/Check of the Probes
10) Fuselage and 2L cabin door no damage.

Fuselage: no lightning strike, no dent, no scratch, no crack, no bird strike and other
defects in the skin of the visible area.
 Reference the A350-A-05-22-XX-00001-310-A-A
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General Visual Inspection of Upper Half of Fuselage (above Cabin Floor) (External
Surfaces Only)
 2L cabin door no lightning strike, no pits, no damage, no corrosion, no scratches, cracks,
creases, etc.
 Reference the A350-A-05-28-XX-04001-310-A-A
General Visual Inspection ofthe Passenger/Crew Doors, LH/RH (External Surfaces
Only)
11) Crew oxygen green discharge chip in place.
 Confirm that the green release piece is in place. The yellow ring can be seen when the
green release sheet is blown off.
13. Close the nose and main landing gear doors.
 Stay over requirements
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VIII. Pre-Flight Check List
(I) Preliminary Item
1. Remove and check the Nose/Main landing gear safety pins（5）、the static
ports（8）(if installed）、MFP（3） and standby pitot probe（1） in good
condition, put to left front of nose gear wheel.
(II) Cockpit Inspection
1. Confirm the fault recorded on the technical log book and cabin log book
completed. View the system messages show on the ECAM and do
corrective actions as required and record it.
 Check the technical log book for pilot failure information. If so, take corrective action as
required or reserve it on condition and record it in the technical record book.
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 Check the cabin log book for failure information recorded by the purser. If so, take
corrective action as required or reserve it on condition and record it in the cabin log
book.
 Check whether the PFR and ECAM display failure information and maintenance
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information.If so, take corrective action as required or reserve it on condition and record
it in the technical record book.
2. Confirm whether there has any Defered defect that is open in the aircraft
technical status folder. Confirm whether there has an item released
according to MEL/CDL in the previous three flight segments in tech log
book. Verify the effectiveness of MEL/CDL terms and execute the "M"
procedure as required, and sign on the tech log book.
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3. General visual inspection cockpit
1) The panels, display units and windows cleanliness.
2) Check three Certificates (Standard Airworthiness Certificate, Certificate of Civil Aircraft
Registration, Aircraft Station License) are in good condition
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 Standard Airworthiness Certificate, Certificate of Civil Aircraft Registration, Aircraft
Station License in place, no damage, no pollution.
4. Check the pressure of tires through the SD WHEEL page, service and
record pressure as necessary. ( Special maintenance requirements in cold
weather)
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 This item comes from MPD: 324100-00M01, referring to MP
A350-A-32-41-XX-00001-340A-A Check of the Tire Pressures
 Make sure that each tyre is cold before measuring the air pressure.It normally takes two
hours for the tyre to cool down after the last run.
 Each charge must be charged to the upper limit of the pressure value.
 The following wheel pressure standard is the cold tire value, if the tire pressure is not
within the normal working range, as required service (air discharge/inflation) :
Front wheels: 181-186 PSI main wheels: 255-260 PSI
 Refer to the following table to perform the corresponding maintenance work for the wheel
in different tire pressure range, refer to: A350-A-32-41-XX-00001-340A-A
NLG pressure
MLG pressure
Tire status/necessary steps
Less than 142 psi
Less than 199 psi
Replace the corresponding low-pressure
wheel assembly. If the wheel rotates at
low pressure, replace the adjacent wheels
on the same wheel shaft.
142 psi to 159 psi
199 psi to 222 psi
Replace the corresponding low-voltage
wheel assembly and check the adjacent
wheels on the same wheel shaft. Replace
as needed.
160 psi to 167 psi
223 psi to 235 psi
The corresponding low-pressure wheel
components were inflated to 260 psi, the
maintenance base was monitored and
measured again the next day. If the
low-pressure continued, the machine was
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replaced.
168 psi to 177 psi
235 psi to 248 psi
Inflate the corresponding low-pressure
wheel assembly into the upper limit of the
normal tire pressure range: 186 psi for the
front wheel and 260 psi for the main
wheel.
177 psi to 186 psi
248 psi to 260 psi
Normal tire pressure, no maintenance
required.
More than 186 psi
More than 260 psi
Use the tire gauge to measure again, if the
pressure value is unchanged, then vent to
the upper limit of the normal tire pressure
range.
 Cold weather maintenance requirements (ambient temperature below 0 ° C)：
Caution: When the ambient temperature is below 0 ℃, there is a risk of valve core
leakage after performing tire pressure service, which may cause damage to the
aircraft/system.
Caution: It is prohibited to use MIL-PRF-25567E Type I leak detector when the ambient
temperature is lower than 0 ° C to perform leakage inspection.Mil-prf-25567e Type I leak
detector is at risk of icing at temperatures below 0 ° C and ice cleaning may cause damage to
aircraft/systems.
(1) Mil-PRF-25567E Type II leak detector is recommended to perform leakage test after
tire pressure service.
(2) If mil-PRF-25567E-Type II leakage test is not available, anti-ice liquid can be used
temporarily instead of performing leakage test.The valve core and surrounding parts should be
cleaned after the test to prevent the residual anti-ice liquid.
(III)
Cabin Inspection
1. Confirm that there is no peculiar smell in the cabin ( including seafood,
lavatory smell, burnt smell of equipment, etc )
 Confirm that there is no peculiar smell in the cabin ( including seafood, lavatory smell,
burnt smell of equipment, etc ).report any peculiar smell and abnormal situation in time.
 If found seafood peculiar smell, check and find the source of peculiar smell, timely report.
 If there is lavatory peculiar smell, check and find the source of peculiar smell, and report in
time.
 If burnt smell of equipment is found, check and find the source of smell, and troubleshoot
the equipment as required.
2. Visual inspection of wing upper surface visible area ( LH/RH ) through
cabin windows. Make sure there is no damage or no loosen/missing
fastener.
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(IV)
Release
1. If aircraft is at icing condition on the ground ， comfirm the De-icing &
Anti-icing check list performed and inform the pilots.
 Ground freezing conditions: the outside air temperature below 5 ℃ , there are visible
moisture (rain, snow, sleet and ice crystals, the fog and visibility less than 1.5 km, etc.)
or in the water, snow, ice or snow on the runway of the meteorological conditions, or the
outside air temperature under 10 ℃, ambient temperature at or below the dew point of
the meteorological conditions.
3. Inspect all wheel wells, ensure there is no foreign object and person.
 Make sure the wheel well door control handle is in the open position, the safety pin is
inserted and locked, and the control handle is not movable.
 Do not pressurize the hydraulic system in the cockpit while inspecting the wheel well.
4. Check and make sure the Nose/Main landing gear safety pins（5）、the static
ports（8）(if installed）、MFP（3） and standby pitot probe（1） are
removed and integrated.
5. After handover with the crew, put the downlock pins（5）、the static ports
（8）(if installed）、MFP（3） and standby pitot probe covers （1）to
the appointed position in the cockpit.
6. Make sure Pre-flight List has been accomplished,release person singed off
on the Aircraft TECH Log Book.
7. Make sure that the ELB device has been set to flight mode and placed in
the ELB storage box.(aircraft equipped with ELB)
(V) Close-up Item
1. Checking around the aircraft before towing or engine run, make sure:
1) All cabin doors、cargo compartment doors and service panels are properly closed.
2) No leakage at portable water、waste water and refuel panel no leakage.
3) NO FOD within engine inlet cowls.
4) The airplane is not damaged by the ground equipment/vehicle.
5) NO FOD in the aircraft parking area.
 Not applicable to flight engineer
2. Checking around the aircraft before closing passenger doors, make sure:
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1) Portable water，waste water and refuel panel properly closed and no leakage.
2) NO FOD within engine inlet cowls.
 Not applicable to flight engineer
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IV. Transit Check List
(I) Preliminary Item
1. Confirm there is no FOD at aircraft parking area before the aircraft comes
in.
 Not applicable to flight engineer
 Confirm there is no FOD (such as vehicles, equipment, personnel, etc.) at aircraft parking
area before 10 minute of the aircraft comes in. If there is a covered bridge at the stand,
the covered bridge shall be within the designated area.
(II) Cockpit/Cabin Inspection
1. Review technical log book、cabin log book、PFR and the system warning
maintenance information show on the ECAM and do corrective actions
as required and record it.
2. Confirm whether there has any Defered defect that is open in the aircraft
technical status folder. Confirm whether there has an item released
according to MEL/CDL in the previous three flight segments in tech log
book. Verify the effectiveness of MEL/CDL terms and execute the "M"
procedure as required, and sign on the tech log book.
3. The onboard EFBs and power adapters in place.
4. Check engine oil quantity on SD ENG page between 30 and 45 minutes
after engine shutdown. If the oil quantity is less than 16.5 QTS，service
the oil level to the FULL mark（QTS）(0.5 QTS precision).
 Applicable for non-ETOPS flight only
 When the oil quantity is less than 16.5 QTS in transit, the engine oil service should be
carried out. Service the oil level to the FULL (QTS) scale of the observation window of
the oil tank.
 If engine grease is refilled, make sure the oil cover is properly closed.
 Oil type: oil service using Eastman 2197 oil (ETO 2197 or BP 2197)
 (The sliding loss standard refers to MP A350-A-71-XX-XX-05001-398A-A The Engine
Operating Limits)
(III)
Servicing Procedure
1) Clean the shock absorber sliding tube.（Only applicable to the base station）
 Refer to GCEB-2019-a350-32-202, A350 landing gear mirror cleaning and lubrication
service requirements.
 Refer to MP A350-A-32-11-XX-001-250A-A Cleaning of the MLG
And MP A350-A-32-21-XX-001-250A-A Cleaning of the NLG
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(IV)
Release
1. If aircraft is at icing condition on the ground ， comfirm the De-icing &
Anti-icing check list performed and inform the pilots.
 Ground freezing conditions: the outside air temperature below 5 ℃ , there are visible
moisture (rain, snow, sleet and ice crystals, the fog and visibility less than 1.5 km, etc.)
or in the water, snow, ice or snow on the runway of the meteorological conditions, or the
outside air temperature under 10 ℃, ambient temperature at or below the dew point of
the meteorological conditions.
2. Make sure Transit List has been accomplished, release person singed off on
the Aircraft TECH Log Book.
3. Make sure that the ELB device has been set to flight mode and placed in
the ELB storage box.(aircraft equipped with ELB)
(V) Close-up Item
1. Checking around the aircraft before towing or engine run, make sure:
1) All cabin doors, cargo compartment doors and service panels are properly closed.
2) No leakage at portable water, waste water and refuel panel no leakage
3) NO FOD within engine inlet cowls.
4) The airplane is not damaged by the ground equipment/vehicle.
5) NO FOD in the aircraft parking area.
 Not applicable to flight engineer
2. Checking around the aircraft before closing passenger doors, make sure:
1) Portable water，waste water and refuel panel properly closed and no leakage.
2) NO FOD within engine inlet cowls.
 Not applicable to flight engineer
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X. Stay-over Check List
(I) Preliminary Item
1. Confirm there is no FOD at aircraft parking area before the aircraft comes
in.
 Not applicable to flight engineer
 Confirm there is no FOD (such as vehicles, equipment, personnel, etc.) at aircraft parking
area before 10 minute of the aircraft comes in. If there is a covered bridge at the stand,
the covered bridge shall be within the designated area.
2. Communicate with flight crew to confirm ELB device is in place. (aircraft
equipped with ELB)
3. Install nose and main landing gear safety pins（5）.
Open the nose and main landing gear door and install the GDO handle
safety pin.
 Make sure the landing gear door control handle is in the open position, the safety pin is
inserted and locked, and the control handle is not movable.
 Do not pressurize the hydraulic system in the cockpit while inspecting the wheel well.
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(II) Cockpit inspection
1. Review technical log book 、 PFR and the system warning maintenance
information show on the ECAM and do corrective actions as required
and record it.
 Review technical log book for pilot failure information. If so, take corrective action as
required or reserve it on condition and record it in the technical log book.
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 Review technical log book 、
PFR and the system warning maintenance
information show on the ECAM. If so, take corrective action as required or reserve
it on condition and record it in the technical log book.
2. Confirm whether there has any Defered defect that is open in the aircraft
technical status folder. Confirm whether there has an item released
according to MEL/CDL in the previous three flight segments in tech log
book. Verify the effectiveness of MEL/CDL terms and execute the "M"
procedure
as required, and sign on the tech log book.
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3. General visual inspection cockpit
1) The windshield and wiper no damage,.
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 Visual inspect the windshield from the inside to make sure there are no cracks, scratches,
bubbles, burns, discoloration, layer, etc.
 The windshield wipers are properly connected and fitted to the windshield without
damage.
2) Make sure the windshield and instrument panel are clean.
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3) Cockpit seat cushion covers and its hard decorative surface(armrest, seat back, etc.) ，
sliding tables of CAPT and F/O, side and rear decorative plate of center pedesta.
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Clean procedure：
（i）Use a vacuum cleaner to clean the cushion covers.
（ii）Dip the textile lint free cotton in clean water and wring dry to clean and dry the hard
decorative surface of the cockpit seat(armrest, seat back, etc.), the sliding table of CAPT and
F/O, side and rear decorative plate of center pedestal.
Note: As necessary, use aircraft interior aqueous cleaner(08ACA1/AMS1550) or equivalent
alternative products, textile lint free cotton and clean water to clean the obstinate dirt area and
dry, ensure no residual detergent.
4) Each crew side console, including the surface (upper and side) and its storage space, data
box, garbage box, cup holder and other internal space
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Clean procedure：
（i）Use a vacuum cleaner as necessary to clean the storage space, data box, garbage box, cup
holder and other internal space.
（ii）Dip the textile lint free cotton in clean water and wring dry to clean and dry each area.
Note: As necessary, use aircraft interior aqueous cleaner(08ACA1/AMS1550) or equivalent
alternative products, textile lint free cotton and clean water to clean the obstinate dirt area and
dry, ensure no residual detergent.
5) Cockpit door, sidewall and internal of right rear closet
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Clean procedure：
（i）Dip the textile lint free cotton in clean water and wring dry to clean and dry each area.
Note: As necessary, use aircraft interior aqueous cleaner(08ACA1/AMS1550) or equivalent
alternative products, textile lint free cotton and clean water to clean the obstinate dirt area and
dry, ensure no residual detergent.
6) Windshield and side windshield lower platform
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Clean procedure：
（i）Dip the textile lint free cotton in clean water and wring dry to clean and dry each area.
Note: As necessary, use aircraft interior aqueous cleaner(08ACA1/AMS1550) or equivalent
alternative products, textile lint free cotton and clean water to clean the obstinate dirt area and
dry, ensure no residual detergent.
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7) Cockpit floor(including pedal aera of CAPT and F/O)
Clean procedure：
（i）Use a vacuum cleaner to clean the floor.
（ii）Dip the textile lint free cotton in clean water and wring dry to clean and dry the pedal
aera of CAPT and F/O.
Note: As necessary, use aircraft interior aqueous cleaner(08ACA1/AMS1550) or equivalent
alternative products, textile lint free cotton and clean water to clean the obstinate dirt area and
dry, ensure no residual detergent.
8) Crew handset in position.(Totally 4)
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9) Check three Certificates (Standard Airworthiness Certificate, Certificate of Civil Aircraft
Registration, Aircraft Station License) are in good condition.
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 Standard Airworthiness Certificate, Certificate of Civil Aircraft Registration, Aircraft
Station License in place, no damage, no pollution.
10) Confirm the two reserve coils printer papers in position.
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 Only applicable to the base station.
11) Five each labels of Deferred defect warning card and Do not use in place.
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 Only applicable to the base station.
12) Emergency equipment in position.
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 Confirm that there is no missing emergency equipment in the cockpit according to the
"emergency equipment drawing" located in the cockpit reserved fault folder.
13) Portable fire extinguish bottle pressure and in the right range.
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 Portable fire extinguish: make sure the gauge is in the green zone;
Refer to MP TASK A350-A-26-24-AA-001-310A-A.
4. Operation check
1) CVR test is normal.
 Reference: MP A350-A-23-71-XX-04001-320A-A
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2) Navigation lights, Taxi/Take-off, Runway turn off, Wing flood, beacon, strobe lights,
landing lights and camera normal condition.
 Confirm that Navigation lights, Taxi/Take-off, Runway turn off, Wing flood, beacon,
strobe lights, landing lights and camera normal condition. Overhead panel 215VM light
zone, respectively push the external light switch.
3) Logo light Work
 Aircraft Landing Gear in daytime hours, no need to check logo lights.
 Daytime hours definition: the time between sunrise and sunset.
 Refer MP A350-A-33-47-13-00001-720A-A (Logo lights)
4) Cockpit lights and legend normal operation.
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 Confirm that the cockpit lights and legend are operating normally, refer to MP
A350-A-33-13-XX-00001-320A-a and MP A350-A-33-14-XX-00001-320A-A
 Emergency flashlight normal operating.
 On the SD HYD PAGE, check fluid level of Green and Yellow hydraulic, as necessary as
refill.
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 The onboard EFBs are in place and switch off, power adapters is in place.
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5. Confirm ELB storage box in good condition and the charging function is
good.(aircraft equipped with
ELB)
6. Confirm the ELB charger and charging cable are in place.(aircraft
equipped with ELB)(Only applicable to the base station)
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 The ELB charger and charging cable are stored under the fourth observer seat in the
cockpit.
7. Check the engine oil level through oil tank sight glass between 30 and 45
minutes after engine shutdown, and service the oil level to the FULL
mark（QTS）(0.5 QTS precision).
 If oil is filled, make sure the oil cover is properly closed.
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 Oil type: oil service using Eastman 2197 oil (ETO 2197 or BP 2197)
8. Calculate engine oil consumption rate.
 Calculation method of oil consumption rate: the amount of oil added this time is divided
by the total flight hours from the oil added last time to this time (the time recorded in the
flight log book).
 The aircraft cannot perform ETOPS flights if the oil consumption rate is 0.3 QTSs per hour
or more.
 (The oil consumption standard refers to MP A350-A-71-XX-XX-05001-398A-A The
Engine Operating Limits)
9. On SD APU PAGE check the APU“LOW OIL LEVEL message ,if
necessary, refill the oil:
 Check the APU "OIL LVL LO" information on the SD APU display page:
(1) if there is "OIL LVL LO" information: add it with Eastman 2389 (ETO 2389 or BP
2389) (add it with a measuring cup, accurate to 0.1 QTS) to the full scale and record the added
amount in the work order and aircraft technical log book, and calculate the OIL consumption
rate.
(2) if there is no "OIL LVL LO" information, ETOPS filghts can be performed.
 Lubricating oil consumption rate = lubricating oil replenishment/hours of use of APU
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Hours of use of APU = time of use of APU between two refillings of lubricating oil.
 Lubricating oil addition record is available in SAP system “ Engine/APU lubricating oil
consumption Query (Transaction code: ZPMR009)” module.
 If the oil consumption rate is greater than or equal to 0.12 and less than 0.33 QTSs/h, APU
oil shall be added to the full scale before each ETOPS flight.
 If the oil consumption rate is greater than or equal to 0.33 QTSs/h, reserved the APU.
 This work needs the release personnel to fill in and sign.
10. On the SD DOOR page system display ， check the crew oxygen bottle
pressure：
A. The base station ensures that the oxygen pressure is not lower than 1200PSI.
 If the unit oxygen pressure shown on the SD DOOR page is lower than 1200PSI, then
enter the ACMS to check the pressure value of each oxygen cylinder, and replace all
oxygen cylinders lower than 1200PSI, refer to MP A350-A-35-1X-XX-001-310A-A.
 If the crew oxygen cylinder pressure fails to meet the pressure standard specified in the
post-flight check list working order due to lack of aviation materials, NRC can be
opened for monitoring and the repair period is set as 3 calendar days when the oxygen
pressure of the unit is no less than 1050PSI.
B. The non-base station ensures that the oxygen pressure is not lower than
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700PSI.
 The SD DOOR page shows that the critical value at which the oxygen pressure of the crew
appears in a half amber box is 700PSI.
(III)
Cabin Inspection
1. Review cabin log book and the system warning maintenance information
show on the FAP and do corrective actions as required and record it.
 Check the cabin log book for system waning maintenance information recorded by the
purser. If so, take corrective action as required or reserve it on condition and record it in
the cabin log book.
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 Check the FAP panel for system waning maintenance information, and if so, take
corrective action as required or reserve it on condition and record it in the cabin log
book.
2. Switch off main power of IFE on FAP in cabin
 Switch off FAP power.
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3. General Visual Inspection cabin area
1) Windows, passenger doors 、 emergency exits 、 galleys 、 lavatory 、 FCRC and CCRC
equipment in position and no damage.
 Windows no damaged.
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 Make sure sidewall, ceiling and slide cover/trim of passenger door/emergency exits are in
position and not missing. Toilet/cabinet door in normal condition. There is no
abnormality in the crew/cabin crew rest compartment (including stairwell).
2) Visual inspection of wing upper surface visible area ( LH/RH ) through cabin windows.
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Make sure there is no damage or no loosen/missing fastener.
3) Emergency equipment in position.
 Check the emergency equipment distribution diagram to ensure that the number and
location of the emergency equipment meet the requirements.
 Note: Pay special attention to the extension, baby seat belt and other common equipment
check.
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 Confirm that there is no missing emergency equipment in the cabin according to the
"emergency equipment drawing" in the cockpit reserved fault folder.
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4) Portable fire extinguish and portable oxygen bottle pressure in the right range.
 This work includes the portable fire extinguish and portable oxygen bottle in FCRC 、
CCRC and cabin.
 For oxygen and fire extinguisher bottles at 1L/R location, confirm that the display head is
positioned diagonally downward and easily reads the values.
 Portable fire extinguish: make sure the gauge is in the green zone;
Refer to MP TASK A350-A-26-24-XX-001-310A-A.
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 Portable oxygen bottle: make sure the indicator head gauge is in the green zone;
Refer to MP A350-A-35-3XX -XX-02001-310A-A.
5)Door Escape Slide Inflation Reservoir Pressure Gauge in green band
 Confirm escape slide inflation reservoir pressure gauge in the green zone, MP
A350-A-25-62-XX-001-310A-A
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4. Operation check
1) Cabin, Galley and lavatory lights illuminate.
 Confirm lavatory lights illuminate, MP A350-A-33-24-XX-001-320A-A.
2) Emergency light illuminate
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 Make sure the emergency lights illuminate. Refer to the MP
A350-XX-04001-A-33-51-320-A-A.
 NOTE: According to MEL requirements, for exit sign signal and exit position signal of
main channel, up to three non-adjacent LED lights in each signal lamp can fail. It is
recommended to compare the external brightness of the signal lights at different
positions. If the LED lights are not on or the signal lights are dim, remove the panel of
the signal lights for further confirmation and processing. (See MP
A350-A-33-51-XX-01001-310A-A and MEL 33-50-04.)
3) Emergency flashlight operating.
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4) No Smoking, Reading light and Fasten Seat Belt signs illuminate
 Visual inspection no smoking light illuminate, no light failure.
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 Confirm that the reading light illuminate, MP A350-A-33-25-XX-001-320A-A
5. Confirm that there is no peculiar smell in the cargo ( including seafood,
sewage smell, burnt smell of equipment, etc ).
 Confirm that there is no peculiar smell in the cabin ( including seafood, lavatory smell,
burnt smell of equipment, etc ).report any peculiar smell and abnormal situation in time.
 If seafood peculiar smell is found, inspect and look for the source of peculiar smell, clean
the source of odour, and clean the contaminated area with water and detergent as needed
to remove odour. Refer to MP A350-A-51-78-16-00001-25BA-A
 If toilet peculiar smell is found, check and find the source of peculiar smell. Clean the
contaminated area with clean water and detergent as needed to remove odour. Refer to
MP A350-a-12-21-12-03001-200a-a. Repair toilet assemblies and sewer lines as needed.
 If burnt smell of equipment is found, check and find the source of smell, and troubleshoot
the equipment as required.
(IV)
Cargo inspection
1. Check cargo compartment light illuminate
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 Confirm that cargo compartment light illuminate, refer to MP
A350-A-33-34-XX-001-320A-A
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2. Clean cargo compartment
 Clean the front, rear and bulk cargo floor with vacuum or broom.
 Dry cleaning: ensure the cargo compartment is clean. If any dirt is found, clean it
immediately with a broom and vacuum.
 Note: do not touch the drive motor to prevent burns or motor rotation injuries.
 Do not use a metal scraper to remove unwanted material. The metal scraper can damage
the surface of the parts.
 Wet cleaning: especially if liquid spills after loading of chemicals, seafood, poultry, etc.,
use a mop or cloth to remove the water in the compartment immediately and completely.
3. General Visual Inspection cargo compartment area, including:
1) Cargo door welt, Linings, floor panels, decompression panels, ceiling panels, pedal, baffle,
access doors cargo door seal and nets no damage.
 No damage or corrosion to door jamb. The adjacent switch or block intact, no deformation,
no pollution.
 The inside seal of the cargo door jamb is completely and in place, no damage, no missing,
no scratch, no incision, no puncture, no corrosion, etc.
 There are no serious craters, cracks or corrosion on the floor inside the cargo compartment.
 There is no damage to the side wall, no falling off of the ceiling, no blocking in the air
outlets, and no defect in the tape between the cargo bulkheads.
 Cargo nets in position, no damage, complete lock.
2) PDU、guides and roller in place and no damage.
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 PDU roller in position, no damage, no excessive wear.
 Cargo rail in position, no damage.
 The ball is in good condition, no missing, no crack, no damage.
3) Discharge nozzle no damage and no blockage.
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 Make sure the nozzles of fire extinguish in cargo compartment are not blocked.
4. Operating check Cargo loading system.
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 Power check the status of cargo loading system. The rolling rods, PDU and ball bearings
should function normally and be repaired as required.
 Do not touch PDU: Be careful when you perform maintenance task, do not touch PDU
until it cools completely. Hot PDU can injury you. During operation, the parts are turned
to prevent injury.
5. Confirm that there is no peculiar smell in the cargo ( including seafood,
sewage smell, burnt smell of equipment, etc ).
 Confirm that there is no peculiar smell in the cargo hold (including seafood, sewage odor,
burnt smell of equipment, etc.), report any abnormal odor and abnormal situation in time
and deal with it in time.
 If seafood peculiar smell is found, inspect and look for the source of peculiar smell, clean
the source of odour, and clean the contaminated area with water and detergent as needed
to remove odour. Refer to MP A350-A-51-78-16-00001-25BA-A
 If sewage peculiar smell is found, check and find the source of peculiar smell, clean the
source of odor, clean the contaminated area with clean water and detergent as needed to
remove the odor, refer to MP A350-A-51-78-18-00001-250A-A, repair the sewage line
as needed.
 If burnt smell of equipment is found, check and find the source of smell, and troubleshoot
the equipment as required.
(V) Service work
1. Install the MFP（3）and standby pitot probe（1）
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2. Ensure toilets are serviced as required. Drain off water in potable
water system and close service panel. ( Special maintenance
requirements in cold weather)
 Select the WATER/WASTE button on the FAP panel to confirm that the sewage tank is
empty.
 To perform potable water discharge service, refer to MP A350-A-38-1X-XX-00001-220A-A.
 Cold weather maintenance requirements (ambient temperature below 0 ° C) :
Caution: When ambient temperatures are below 0 ° C, there is a risk that the water
system will freeze and cause damage to aircraft systems/components.
Note: Discharge the drinking water tank as soon as possible after landing.
(1) After confirming that all the drinking water has been discharged, close the discharge
valve, use a clean and non-fluffing cloth to dry the discharge outlet and plug the cover, and
cover the plug cover of the discharge outlet.
(2) Dry the drainage service panel and the surrounding bonding surface with a clean,
non-fuzz cloth, and close the drainage service panel.
(3) Ensure that all faucets, toilets, coffee makers and water heaters in the kitchen and
toilet are fully discharged.
3. Clean the shock absorber sliding tube and grounding stud.
(1) Clean the shock absorber sliding tube
 Reference GCEB - 2019 - the A350-32-202, MP A350-A-32-11-XX-00001-250A-A Cleaning
of the MLG and MP A350-A-32-21-XX-00001-250A-a Cleaning of the NLG Maintenance
personnel shall use non-flapping cloth (MAT.14SBA1) to soak the anhydrous cleaner
(Mat.08BBB1 or MAT.08BAA9) to clean the mirror surface of the landing gear damping
prop, and use non-flapping cloth (Mat.14SBA1) to soak the hydraulic oil (MAT.: 02EBA1,
US Army Grade No. : Mil-prf-87257) lubricated landing gear shock strut mirror.
(2) Clean the ground stud
 Use a clean, lint-free cloth (MAT.14SBA1) to clean the ground stud. If there is oil on the
ground pile, use a clean, lint-free cloth (Mat.14sBA1) to soak P-D-680(MAT.08BBB1) to
clean the ground pile and dry it with a clean cloth.
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 Note: The tooling department has purchased relevant A350 landing gear pre-moisten wipe
paper sets as recommended by GCEB-2019-A350-32-202. Maintenance personnel can
use PN: 15-5-680-HX (multi-functional solvent dry cleaning pre-moistening wipe paper)
to clean the landing gear mirror and ground pile, and then use PN15-5-87257-HX (A350
landing gear pre-moistening wipe paper) to lubricate the landing gear mirror.
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(VI)
release
1. Make sure Stay-over List has been accomplished, release person singed off
on the Aircraft TECH Log Book
(VII)
Close-up Items
1. Make sure all systems have been put back to its normal condition ,turn off
electric network and disconnect external power as required .
 Reference:
Ref.MP A350-A-24-41-XX-00001-561A-energize the
External Power Receptacle 1
Ref.MP A350-A-24-41-XX-00001-561B-A-De-energize
External Power Receptacle 2
Ref.MP A350-A-24-41-XX-00001-561C-A-De-energize
External Power Receptacles 1 and 2
Ref.MP A350-A-24-41-XX-00001-561E-A-De-energize
the APU
Aircraft Electrical Circuits from
the Aircraft Electrical Circuits from
the Aircraft Electrical Circuits from
the Aircraft Electrical Circuits from
2. Carry out a final walk around inspection, make sure:
1) All cabin doors, cargo doors, windows and panels are properly closed. Remove all ground
equipment and tools.（Special maintenance needed in cold weather）
 Do not close the drain cover when the drain valve is manually held in the open position
under freezing conditions.
2) Portable water, waste water and refuel panel no leakage.
3) The airplane is not damaged by the ground equipment/vehicle.
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ETOPS operation additional check
(I) Engine Inspection
1. Service the oil level to the FULL mark（QTS）(0.5 QTS precision) between
30 and 45 minutes after engine shutdown and calculate engine oil
consumption rate.
 Before an ETOPS flight, oil is added to a FULL scale (QTS) (accurate to 0.5 QTS).
 The aircraft cannot perform ETOPS flights if the lubricating oil consumption rate is 0.3
QTSs per hour or more.
 Calculation method of sliding consumption rate: the amount of lubricating oil added this
time is divided by the total flight hours from the last time the lubricating oil was added
to this time (the time recorded in the flight log book shall prevail).
 If engine grease is added, make sure the oil cover is properly closed.
 Oil type: oil service using Eastman 2197 oil (ETO 2197 or BP 2197)
 (The oil consumption standard refers to MP A350-A-71-XX-XX-05001-398A-A The
Engine Operating Limits)
(II) APU Inspection
1.On SD APU PAGE check the APU“LOW OIL LEVEL message ,if
necessary, refill the oil:
 Check the APU "OIL LVL LO" information on the SD APU display page:
(1) if there is "OIL LVL LO" information: refill Eastman 2389 (ETO 2389 or BP 2389) (fill
it with a measuring cup, accurate to 0.1 QTS) to the full scale and record the added amount in
the check list and technical log book, and calculate the OIL consumption rate.
(2) if there is no "OIL LVL LO" information, ETOPS filghts can be performed.
 Lubricating oil consumption rate = lubricating oil replenishment/hours of use of APU
Hours of use of APU = time of use of APU between two refillings of lubricating oil.
 Lubricating oil addition record is available in SAP system “ Engine/APU lubricating oil
consumption Query (Transaction code: ZPMR009)” module.
 If the oil consumption rate is greater than or equal to 0.12 and less than 0.33 QTSs/h, APU
oil shall be added to the full scale before each ETOPS flight.
 If the oil consumption rate is greater than or equal to 0.33 QTSs/h, keep the APU.
 Oil type: oil service using Eastman 2197 oil (ETO 2197 or BP 2197)
(III) Cargo Inspection
1.Cargo door jamb, Linings, floor panels, decompression panels, ceiling panels, foot steps,
partition walls access doors and cargo door seal no damage.
 This work only applies to ETOPS flights.
2.Make sure the cargo door seal is good condition before closing cargo doors.
 This work only applies to ETOPS flights.
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Appendix 1: aircraft antenna map
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Appendix 2: list of ground service contacts and cover plates
Item
1
2
3
4
FIN
N/A
122 AR
N/A
193 CB 194 CR
5
193 KB
6
7
8
9
10
11
12
13
14
15
16
17
18
194 KB
415 BR (425BR)
415 AL (425AL)
415 AL (425AL)
523 EB 623 EB
543 CB (643 CB)
543 DB (643 DB)
N/A
197 LB
197 KB
164 AR
171 AL
316 BR
Description
Nose landing gear touchdown
External-Power Receptacle
Oxygen system
Low-Pressure Ground-Connector
Door
High-Pressure Ground-Connector
Door
Yellow Ground Service Panel Door
Engine Oil Service Panel
Starting Oil Service Panel
VFG Oil Service Panel
Refuel/Defuel Door
Tank overpressure release indicator
Surge Tank Intake Panel
Main landing gear touchdown
Green Ground Service Panel Door
Refuel/Defuel Panel Door
Portable-Water Service-Panel
Waste-Water Service-Panel
APU Oil Service Panel
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1. NLG touchdown
2. External-Power Receptacle
3. Oxygen system
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4. Low-Pressure Ground-Connector Door
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5. High-Pressure Ground-Connector Door
6. Yellow Ground Service Panel Door
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7. Engine Oil Service Panel
8. Starting Oil Service Panel
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9. VFG Oil Service Panel
10. Refuel/Defuel Door
11. Tank overpressure release indicator
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12. Surge Tank Intake Panel
13. Main landing gear touchdown
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14. Green Ground Service Panel Door
15. Refuel/Defuel Panel Door
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16. Portable-Water Service-Panel
17. Waste-Water Service-Panel
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18. APU Oil Service Panel
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Appendix 3: tire damage replacement standard
 The standard for wheel replacement shall refer to MP TASK
A350-A-32-41-XX-03001-310A-A. The following contents shall be further explained and
supplemented.In case of any discrepancy between the following contents and the
contents of EB-2019-A350-32-203, the EB requirements shall prevail.
1. Tire wear standard (Stay-Over)
1)
Check the decorative line inside the machine tire leather machine. If the groove of the
decorative line on the side wall is found to be worn from top to bottom with no more
than 4 grooves left, it shall be replaced with appropriate opportunity for inspection.
Note: The definition of wear up to 4 remaining grooves is: 1st groove has been worn out, the
rib on the 2nd groove begins to wear out.
2)
Near the area above the decorative line on the side wall of the tire of the inspection
machine, if it is found that the continuous and dense tearing block in the circumferential
direction of the area above the decorative line is about to be worn to the tire structure
layer, the wheel shall be replaced immediately.
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3)
Check the area near the top of the decorative line on the side wall of the tire skin of the
machine. If it is found that the area above the decorative line is worn in a circumferential
strip or is accompanied by local tear, then the tread rubber layer has been worn through to
the structural layer of the tire body, and the wheel should be replaced immediately.
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4)
Check the tire skin and tire shoulder area. If the tire shoulder area is found to be corrugated
or with texture, it will be worn to the line layer of kevlar anti-pring, and the wheel should
be replaced immediately.
2. Tire damage standard
 If the airline finds tire damage, it will be treated according to corresponding AMM. If the
following tire defect or damage is found, it shall be replaced before the next flight.
（1）Replacement standard for tread damage
1) Tread rib bottom laceration
 The tread rib develops rubber cracking at the base of the "wall" surface of the groove and
develops expansion at the base of the rib.The crack expansion at the bottom of rib
groove will lead to rubber drop of tread, rib spalling and even flaking of tread layer.If
crack expansion is found at rib root, replace wheel immediately.
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2) Tread "V" cut
 This "V" cut is usually caused when the aircraft lands on a runway with a drain groove and
the tyre is cut on the edge of the groove while running at high speed.Replace the wheel
if (1) the anti-puncture line is found exposed and injured or (2) the cut is found to
traverse the entire central rib or (3) the cut is found to cross the tread line exposing
more than 5 cm2 or (4) the deep tread line is found to be exposed at more than 1
place.
3) Tread rib spalling
 Rib exfoliation is a partial or complete circumferential exfoliation of a tread rib, usually
due to a tread puncture.If the tread has transverse puncture, which is deeper than the
tread groove or extends across the groove, then replace the wheel.
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4) Cracks at the bottom of tread groove
 Straight line cracks at the bottom of the tread grooves may be due to environmental
erosion (e.g., oxidation) of the rubber material, tire fatigue, or low air pressure.Replace
the wheel if the crack leads to exposure of the anti-damage line layer or the crack
extends to the bottom of the adjacent rib.Tires with slight grooves and cracks can
continue to be installed and used.
5) Tread pollution erosion
 Brake hydraulic oils, fuels, tar, solvents, chemicals and hydrocarbons can degrade tire
rubber materials.If the above problem is found, remove the contaminant immediately
with industrial alcohol (as environmental conditions permit), or clean it directly with
soapy water.If the rubber drum/material comparison in the corresponding area is
abnormal after the cleaning, the wheel will be replaced and the marking will be
notified to the engineering department.
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6) Tread bulge
 Tread bumps indicate layering or damage to the tire structure and require replacement of
the wheel.
（2）Replacement standard for side wall damage
1) Side wall damage
 Damage to the side wall is usually caused by external damage. If the cord at the side wall
is exposed or damaged, replace the wheel.
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2) Side wall crack - circumferential crack
 The circumferential crack in the side wall of the tire is caused by the expansion and
expansion of the tire body at the side wall during the low-pressure load operation of
the tire. If the crack depth exceeds 2mm, the wheel shall be replaced.
3) Weathering erosion or radial crack of the wall
 Lateral wall weathering and radial cracks are caused by environmental oxidation of the
tire or prolonged exposure to direct sunlight (ultraviolet). Low-pressure operation of
the tire will accelerate the cracks.If there is a line at the crack, replace the wheel.
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4) The position of the tire wall, the inner wall creases
 The inner wall creases are typically caused by the transition deformation of the tire, which
also indicates the low pressure of the tire during operation.If the inner wall of the
corrugate tire is found, it shall be replaced with the coaxial wheel at the same time. The
coaxial wheel information shall be notified to the engineering department.
3. Tire structure and terminology
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Appendix 4: common structural damage on airline routes
1. Lightning damage
 Common locations:
 Common damage examples：
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Example:
Lighting damage Start the lighting check program
MP A350-A-05-51-18-00001-282A-A
And MP A350-A-05-51-18-02001-282A-A.
Inspection of the radome:
Refer MP A350-A-53-15-73-00001-661A-A
Or MP A350-A-53-15-73-00002-661A-A
Check the external grille of the inlet cone:
Refer ASR A350-A-54-10-82-09001-661A-A
For the inspection of the wing tip:
Refer to ASR A350-A-57-31-61-09001-661A-A
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2. Pit damage
 Common locations:
 Common damage examples:
襟翼下表面凹坑
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Example:
Inspection of metal skin pits on the section 11 of the fuselage:
Refer ASR A350-A-53-11-61-07001-661A-A
For the inspection of the inner flaps pits:
Refer ASR A350-A-57-54-61-00003-661A-A
Or ASR A350-A-57-54-61-00003-661A-A
Or ASR A350-A-57-54-61-00003-661A-A
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3. Bird strike
 Common locations:
 Common damage examples:
Engine Blade bird strike
Engine Inlet Cone bird strike
Radome Bird strike
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Wing bird strike
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Wing bird strike
Example:
For Engine fan blade inspection:
Refer to MP A350-A-72-31-62-00001-310A-A
Check for pit in front ring:
Refer to ASR A350-A-54-10-61-01001-661A-A
Or ASR A350-A-54-10-61-01002-661A-A
Check for the radome:
Refer to ASR A350-A-53-15-73-00001-661A-A
Or ASR A350-A 53-15-73-00002-661A-A
Or ASR A350-A-53-15-73-01001-661A-A
Or ASR A350-A-53-15-73-01002-661A-A
Or ASR A350-A-53-15-73-00001-662A-A
Inspection of No.1 slat (Droop nose) pits:
Refer to ASR A350-A-57-41-61-08001-661A-A
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4. GSE FOD
 Common locations:
Passenger elevator car collision
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Loading truck collision
Example:
For impact damage of section 11 of the fuselage:
Refer ASR A350-A-53-11-61-06001-661A-A
For the replacement of front/rear cargo door operating panel:
Refer LM 52-42-72
Or LM52-42-73
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5. Scratch damage
 Common locations:
 Common damage examples:
Example:
For static ports scratches:
Refer MP A350-A-34-1X-XX-00003-310A-A
Or MP A350-A-34-1X-XX-00005-310A-A
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6. Erosion damage
 Common locations:
 Common damage examples:
Example:
Inspection of wind erosion of the radome:
Refer ASR A350-A-53-15-73-00001-661A-A
Or ASR A350-A-53-15-73-00002-661A-A
Inspection of wind erosion of the inlet cone ring:
Refer ASR A350-A-54-10-82
Inspection of wind erosion of the flap fairing:
Refer ASR A350-A-57-57-XX
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7. An example of special damage to lower fairing
Example:
Inspection of the belly fairing cover plate:
Refer to A350-A-53-35-70-06002-661A-A
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Appendix 5: Winding inspection of common fastener damage and
defects
1. Examples of fastener damage
 MLG area：
1. Missing or loosen fastening screw for uplock roller.
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2. Engine area exampls
1.The tip of the fan blade is ablated
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2. The muffler board at the rear of the fan blade is damaged
3.The glass fiber is missing on the surface of the internal fixation structure, and the carbon fiber
layer is not damaged, and there is no delamination and degumming
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4.NEP engine fan sheath anti-wear strip wear
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3. Pylon area example
1. Fasteners are missing in the hanger area.
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4. Fastener paint loss
1. A large area of paint is lost on the nail head of the fastener on the lower surface of the big
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wing
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Appendix 7: Winding inspection of common seal damage and
defects
1.Damage of seal
1.All hinge doors in landing gear area are sealed
2.Cracked or missing or worn door seals on various hinges in the landing gear area
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3.The cargo door frame seal was cracked after being hit
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Appendix 6：Cold weather maintenance Tips
1、Terms and relevant definitions
(A) Deicing: refers to the operation procedure of removing frost, ice and snow attached to
the surface of the aircraft in order to provide a clean appearance of the aircraft.
(B) Anti-icing: means a preventive procedure that provides protection against the
formation of frost, ice and snow on certain surfaces of the aircraft for a limited period.
(C) Hold time: is the estimated time during which the deicing/anti-icing solution can
prevent frost, ice and snow from forming on the aircraft's protected surface.
(D) Beginning of winter: it means that the average daily temperature is below 10 ° C for
five consecutive days in meteorology.
(E) Special weather in winter: it refers to special cold wave weather such as blizzard and
freezing rain.
(F) Winter snow and ice weather: refers to moderate snow and above snow, freezing rain
and other weather.
(G) Ground icing conditions: In general, it refers to the meteorological conditions where the
external atmospheric temperature is below 5°C, there is visible moisture (such as rain, snow,
sleet, ice crystal, fog and visibility is less than 1.5 km, etc.) or there is water, snow, ice or
snow on the runway, or the meteorological conditions where the external atmospheric
temperature is below 10 °C and the external temperature is at or below the dew point.
2、Cold weather maintenance tips
(A) Pre-flight power-on in cold weather: When the temperature is lower than or equal to
-5℃, the APU should be started or the ground power supply and air conditioning should be
connected at least 60 minutes in advance before departure.
When the temperature is lower than or equal to -15℃, the APU should be started or the ground
power supply and air conditioning should be connected at least 90 minutes in advance before
departure.
When the temperature is lower than or equal to -25℃, the APU should be started or the ground
power supply and air conditioning should be connected at least 120 minutes in advance before
departure.
(B) In the case of icing on the surface of the aircraft, when electricity is needed (starting the
APU, connecting the air conditioning, etc.), the icing at the APU inlet valve, outlet valve,
ventilation inlet and outlet door of the electronic cabin must be cleared first. Prevent the
aircraft during power-on process, due to the above parts after ice movement caused by
jamming or damage.
(C) In freezing rain weather, avoid using APUs in freezing rain.
If you need to use the APU, check the condition of the APU air inlet before starting the APU,
remove foreign objects, and monitor the APU air inlet during the use of the APU.
If the APU air inlet is frozen, the APU should be closed as soon as possible to avoid ice entering
the APU and damaging the APU blades.
(D) In extreme cold weather, in winter, airline workers shall ensure sufficient inspection time
during PRE-FLT, STAYOVER and TRANSIT, and shall not shorten the working time because of
cold weather.
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In winter, the northern sunshine time is short, in the morning and evening when the illumination
conditions cannot meet the requirements of visual inspection of aircraft, the flashlight must be
used to supplement the illumination.
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