A320 - AMM Reference

• Installation of the Aircraft Protection Equipment iaw amm 10-11-00-555-013-A
• Removal of the Aircraft Protection Equipment iaw amm 10-11-00-555-014-A 

It is not necessary to do all the scheduled maitenance task immediately during the storage/parking period. But you must do them all before the next flight.

(This job included AMM 12-14-32-614-003-A Functional Check of MLG Shock Absorber Charge Pressure)

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-> within limit

-> Do the Hydraulic Replenishment of the MLG Two-Stage Shock Absorber iaw amm 12-12-32-611-008-A before 50 cycles (Aircraft on Jacks).

-> Do the Hydraulic Replenishment of the MLG Two-Stage Shock Absorber iaw amm 12-12-32-611-008-A (Aircraft on Jacks).

Full AMM: 12-13-79-610-002-A Check oil level and replenish Check Pop Out Indicator of EMCD (Electrical Master Chip Detector)

Full AMM: 12-14-32-614-001-A

-> Do the functional check of the MLG shock-absorber fluid-level iaw amm 12-12-32-611-004.

-> Do the functional check of the MLG shock-absorber fluid-level before the aircraft completes five flight cycles, iaw amm 12-12-32-611-004.

-> Do the functional check of the MLG shock-absorber charge-pressure at the next available maintenance check, iaw amm 12-14-32-614-003.

Out of limit,

or

is less than 48 mm when the ambient temperature is between 0 deg.C and 30 deg.C

or

is less than 72 mm, when the ambient temperature is more than 30 deg.C .

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or

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-> within limit

-> Check and adjust nitrogen pressure on both filling ports (first make sure than bottom one has more then 261 psi compare to upper one).

-> Functional Check of the MLG Shock Absorber Charge-Pressure and Nitrogen Filling (Aircraft on Jacks).

Full AMM: 12-15-38-613-001-A

Full AMM: 12-24-38-680-001-A

Full AMM: 12-31-38-660-001-A

Ful AMM: 12-31-71-660-001-A

Replace the bonding lead at the next maintenance visit, before 6 months, 1000 Flight Hours (FH) or 1000 flight cycles, whichever occurs first

if the bonding lead is broken or if more than 25% of the strands are damaged (less than 75% not damaged)

NOTE: Cargo doors need resistance check for deferral

IPC

For Bonding lead at cargo door actuator IPC 52-36-04-08D

Crew door IPC 52-13-04-04E

Bite test via MCDU (4min)

- AFS Test

- Softwares checking

Full AMM: 22-96-00-710-001-A

*

Full AMM: 23-73-00-740-005-B Interface and Power-Up Test of the Cabin Intercommunication Data System (CIDS) through the CFDS

MCDU:

1. Push the SYSTEM REPORT/TEST line select key
2. Push the COM related line select key.
3. Push the CIDS1(2) related line select key.
4. Push the SYSTEM TESTS related line select key
5. Push the "INTERFACE + POWER-UP TEST" line select key

During the inspection, if you cannot replace the bonding leads that are broken or damaged, the installations that follow are satisfactory: * a.) xxx * b.) xxx * Replace all the remaining broken or damaged bonding leads in less than 24 months or 7500 flight hours or 5000 flight cycles (the one that occurs first). *

*

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*

20-28-00-200-001-A Detailed Inspection of Bonding Leads on Access Panels, Doors and Movable Surfaces

NOTE:  CHOOSE THE LEFT OR THE RIGHT VARIANT OF SPRING PART NUMBER IS DEPENDING TO THE SEAT ORIENTATION.

Full amm for jumpseat change: 25-22-41-04 Installation of the Wall-Mounted Cabin Attendant Seat (CAS)

Visual Check of Cargo Compartment Decompression, Lining, Floor Panels and Ventilation Extraction Duct

2 x SFCC (Slat and Flap Control Computer)

Full amm: TASK 27-51-00-740-002-A BITE Test of the Slat and Flap Control Computers (Flap System)

2 x SFCC (Slat and Flap Control Computer)

TASK 27-81-00-740-002-A BITE Test of the Slat and Flap Control Computers (Slat System)

The flight control computers consists of two Elevator Aileron Computers (ELACs), three Spoiler Elevator Computers (SECs), and two Flight Augmentation Computers (FACs).

• Installation of the Safety Devices on the Landing Gears iaw amm 32-00-00-481-001-A
• Removal of the Safety Devices on the Landing Gears iaw amm 32-00-00-081-001-A

A319/320 tighten 220-70-110 lbt/ft A321 tighten 320-0-160 lbt/ft

tighten 160-0-80 lbt/ft

Tighten 160 lbf.ft

Lamp P/N: 8GH005597-12

33-51-38-400-002-A Instalation of the Battery of the Emmergency Power Supply Unit (EPSU) * C/B: H06 H05 V07 * Do the operational ccheck of the EPSU thru the Bite check * 33-51-38-400-001-A Instalation of the Emmergency Power Supply Unit (EPSU)

Pneumatic system operation is controlled and monitored by two bleed monitoring computers (BMCs).

iaw AMM can be deferred with inspection every 50FC. After 550 FC, install the new rubbing strip.

PN: can be found in SRM 52-13-00-04-A

Needed: Adhesive at Neopren base (05JBC9), Polysulfide Sealent (06AAB1), Rubbing strip

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Starter limit:

Note: max D on the leading edge is 8,6mm

Note: reworking on leading edge: Min radius 15x deept, min lenght 10x deept.

Note: amm 72-21-00-210-009-A (Inspection of Fan Rotor Blades) .

Note: amm 72-21-00-320-003-A (Blending of the Fan Rotor Blades).

Job Set-up:

• Fadec GND PWR to ON
• Push all the fuel Pumps
• Set the three OFF/NAV/ATT selector switches to NAV.
• Open C/Bs 1 and 2 HP FUEL SOV (LOC: A01, A02)
• Start test on MCDU
• ENG MODE selector to NORM
• ENG MASTER control switch to ON
• FADEC TEST REPORT comes into view
• Return from test
• ENG MASTER lever to OFF
• ECU reset by ENG MASTER control switch to ON then OFF
• Retur A/C to initial config

Job Set-up:

• FADEC GND PWR ON
• Set the three OFF/NAV/ATT selector switches to NAV.
• START THE TEST
• MODE CRANK/NORM/IGN/START selector switch is set to NORM
• ENG MASTER 1(2) lever to ON
• RETURN FROM TEST
• Reset ECU by ENG MASTER control switch to ON then OFF
• Return A/C to initial config

***if more

***monitor at 750 flight cycles / 4 calendar months (whichever the earliest), or repair Ref. NSRM 543000 (51563), Rep.No.12.