MLG (LH) Shock Absorber Does Not Extend

TASK 32-31-00-810-869-A
MLG (LH) Shock Absorber Does Not Extend

WARNING: MAKE SURE THAT THE GROUND SAFETY-LOCKS ARE IN POSITION ON THE LANDING GEAR. MOVEMENT OF THE LANDING GEAR CAN CAUSE INJURY TO PERSONS AND DAMAGE TO THE AIRCRAFT AND/OR EQUIPMENT.

WARNING: PUT THE SAFETY DEVICES AND THE WARNING NOTICES IN POSITION BEFORE YOU START A TASK ON OR NEAR:

THE FLIGHT CONTROLS
THE FLIGHT CONTROL SURFACES
THE LANDING GEAR AND THE RELATED DOORS
COMPONENTS THAT MOVE.

MOVEMENT OF COMPONENTS CAN KILL OR CAUSE INJURY TO PERSONS AND/OR CAN CAUSE DAMAGE TO THE EQUIPMENT.

1. Possible Causes

MLG (LH) proximity sensor and target clearances
MLG (LH) torque link damper assembly
landing gear torque link excessive play
MLG sliding tube.
charge pressure of the main landing gear (LH) shock absorber
fluid level of the MLG (LH) shock absorber

2. Job Set-up Information
A. Referenced Information

REFERENCE	DESIGNATION
AMM 07-11-00-581-001	Lifting for Aircraft Maintenance Operations
AMM 12-12-32-611-004	Check of MLG Shock Absorber Fluid Level
AMM 12-14-32-614-003	Check of MLG Shock Absorber Charge Pressure
AMM 24-41-00-861-002	Energize the Aircraft Electrical Circuits from the External Power
AMM 31-32-00-860-009	Procedure to Get Access to the SYSTEM REPORT/TEST/L/G Page
AMM 32-11-00-200-001	General Visual Inspection of the Main Landing Gear
AMM 32-11-00-200-008	Detailed Inspection of Main Landing Gear, Sliding Tube (Twin Wheel), Brake Attachment Flange, Upper and Lower Torque Links, Upper and Lower Torque Link...
AMM 32-11-27-200-001	Check of MLG Torque Links for Excessive Play
AMM 32-11-27-210-001	Detailed Inspection of the Torque-Link Damper-Assemblies
AMM 32-31-00-720-002	Functional Test of the Normal Extension and Retraction of the Landing Gear
AMM 32-31-73-200-001	Inspection of the MLG Proximity Sensor and Target Clearances

3. Fault Confirmation
Subtask 32-31-00-860-101-A

A. Procedure
(1) Do a check of the post flight report. The fault messages that follow are related to the components installed:
(a) If a Crane LGCIU PN 80-178-0X-8801X (where X equals 2 or 3) and interlink connection (MOD 39303) is installed:

CFDS message 'L LG SHOCK ABSORBER(2501GM)' and E/W message 'L/G SHOCK ABSORBER FAULT' are shown.

(b) For all other configurations (for example, if an ULTRA LGCIU PN 664700500A4X (where X equals A, B, C or D) or a CRANE LGCIU (without interlink connection (MOD 39303)) is installed):

CFDS messages 'L L/G EXT PROX SNSR 21GA TGT POS', 'L L/G EXT PROX SNSR 23GA TGT POS' and 'L/G SHOCK ABSORBER FAULT' are shown.

(c) If there was a report of a hard or a hard overweight landing on the last flight:
1 Do the Fault Isolation from Para. 4. A. (1).
(d) If there was not a report of a hard or a hard overweight landing on the last flight:
1 Do the Fault Isolation from Para. 4. A. (4).
(2) If one or more message(s) that follow is(are) shown during ground maintenance, with no ECAM warning shown:

NOTE: The fault messages are related to the components installed.

NOTE: The Fault Confirmation that follows is only applicable to LGCIU PN 80-178-0X-8801X.

(a) If a CRANE LGCIU PN 80-178-0X-8801X (where X equals 2 or 3) and interlink connection (MOD 39303) is installed:

CFDS message 'L LG SHOCK ABSORBER(2501GM)' is shown.

(b) If a CRANE LGCIU PN 80-178-0X-8801X (where X equals 2 or 3) and interlink connection (MOD 39303) is not installed:

CFDS message(s) 'L LG EXT PROX SNSR 21GA TGT POS' and/or 'L LG EXT PROX SNSR 23GA TGT POS' is(are) shown.

(c) Do the steps that follow:
1 Get access to the SYSTEM REPORT/TEST L/G page AMM 31-32-00-860-009:
a If you cannot get access to the SYSTEM REPORT/TEST L/G page:

Make sure that the aircraft electrical circuits are energized with an external power supply AMM 24-41-00-861-002. If external power is not available, go to Para. 4. A.

2 Select the applicable LGCIU.
3 Select trouble shooting data (TSD).
4 The TSD shows 1X00 on word 4:

1 shows the aircraft on ground
X is not applicable
00 shows the BITE recording command from the CFDS was null.

5 Refer to Table 1.

Table 1

! Word 1! Word 2! Word 3! Word 4! Word 5!

! XXXX ! XXXX ! XXXX ! 1X00 ! XXXX !

! XXXX ! XXXX ! XXXX ! XXXX ! XXXX !

NOTE: This fault can occur with one L/G lifted off the ground and the aircraft electrical power on.

6 This shows that the fault has occurred on the ground. It can be ignored if maintenance on the MLG shock absorbers was done before. If no maintenance was done on the MLG shock absorbers, do the Fault Isolation from Para. 4. A. (1).

4. Fault Isolation
Subtask 32-31-00-810-127-A

A. Procedure

NOTE: If there was a report of a hard or a hard overweight landing on the last flight, a check must be done. This will make sure that there is no internal damage to the L/G.

(1) Lift the aircraft on jacks AMM 07-11-00-581-001:
(a) Make sure that:

The shock absorber extends smoothly and continuously
Make sure that dimension H is between 496.7 mm (19.5551 in.) and 500.5 mm (19.7047 in.), AMM 12-14-32-614-003.

(2) If the shock absorber does not extend smoothly and continuously, or dimension H is more than the limits specified in Para. 4. A. (1):
(a) You must speak to Airbus before the next flight.
(3) If no fault is found continue the Fault Isolation.

NOTE: The procedure that follows, gives the information necessary to identify mechanical faults related to the MLG (LH) shock absorber.

(4) Do the inspection/check of the main gear (LH) AMM 32-11-00-200-001.
(5) Do the inspection of the MLG (LH) proximity sensor and target clearances AMM 32-31-73-200-001.
(6) Do the detailed inspection of the MLG (LH) torque link damper assembly AMM 32-11-27-210-001.
(7) Do the check of the landing gear torque link excessive play AMM 32-11-27-200-001.
(8) Do the detailed inspection of the MLG sliding tube. AMM 32-11-00-200-008.
(9) Do the check of the charge pressure of the main landing gear (LH) shock absorber AMM 12-14-32-614-003.
(10) Do the check of the fluid level of the MLG (LH) shock absorber AMM 12-12-32-611-004.
(11) Correct the faults found.
(12) Do the functional test of the normal extension and retraction of the landing gear AMM 32-31-00-720-002.

[Rev.8 from Aug 2018] 2026.04.04 04:40:14 UTC