CUSTOMER SERVICES DIRECTORATE

1 ROND POINT MAURICE BELLONTE

31707 BLAGNAC CEDEX FRANCE

TELEPHONE + 33 (0)5 61 93 33 33

ALERT OPERATORS TRANSMISSION - AOT

AOT ref: A32L003-14 Page 1 of 5 Date: 10 Mar 2014

© AIRBUS S.A.S. 2014. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT

SUBJECT: ATA 32 – MAIN LANDING GEAR (MLG) SIDESTAY UPPER CARDAN PIN INSPECTION

AIRCRAFT TYPE: A330, A340.

OUR REF.: A32L003-14 dated 10 Mar 2014.

1. AIRCRAFT AFFECTED

A330-200/300 and A340-200/300 fitted with:

- Basic MLG (PN 20125 series) with sidestay upper cardan pin PN 201267202

- Growth MLG (PN 20149 series) with sidestay upper cardan pin PN 201483202.

Note: aircraft fitted with Enhanced MLG (PN 10-210 series) are not subject to the inspection detailed 

in this AOT.

2. REFERENCED DOCUMENTATION

2.1 APPENDIX

- Appendix 1 MLG Sidestay cardan pin clearances

- Appendix 2 Inspection reporting sheet

- Appendix 3 Flow Chart

2.2 REFERENCES

- Ref. 1: AMM 32-11-16-420-053

- Ref. 2: IPC 32-11-18-01

- Ref. 3: MBD CMM 32-11-91, Figure 1

- Ref. 4: MBD CMM 32-12-07, Figure 1

- Ref. 5: AMM 32-11-18-000-801-A & 32-11-18-400-801-A

3. REASON

The purpose of this AOT is to request operators to accomplish an inspection on the MLG sidestay upper 

cardan pin.

3.1 FACTS

An A330 fitted with Basic MLG was rolling out after landing when it experienced a nose wheel steering 

fault (unrelated to the migration detailed in this document), which resulted in the crew stopping the 

aircraft on the taxiway after vacating the runway. 

Inspection identified that the RH MLG sidestay upper cardan pin (Ref. 2) had migrated out of position. 

The sidestay upper cardan nut and retainer were found in the landing gear bay detached from the upper 

cardan pin. The nut and the retainer were still bolted together.
CUSTOMER SERVICES DIRECTORATE

1 ROND POINT MAURICE BELLONTE

31707 BLAGNAC CEDEX FRANCE

TELEPHONE + 33 (0)5 61 93 33 33

ALERT OPERATORS TRANSMISSION - AOT

AOT ref: A32L003-14 Page 2 of 5 Date: 10 Mar 2014

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3.2 CONSEQUENCES

The loss of the sidestay cardan pin locking function (loss of nut) could lead to a complete migration of 

the sidestay upper cardan pin and a disconnection of the sidestay upper arm from the aircraft structure. 

This could therefore lead to a landing gear collapse.

3.3 AIM

The aim of this AOT is to request operators to:

- Perform a Detailed Inspection (DI) of the upper cardan pin and nut and retainer

- Perform a Gap check of the upper cardan pin and nut

The accomplishment of these inspections is requested on aircraft fitted with MLG sidestay upper cardan 

pins which have accumulated more than 8 years since first overhaul and which have not yet gone 

through their second overhaul, at the issue date of this AOT.

4. SHORT TERM ACTION

4.1 PLANNING AND MANPOWER

4.1.1 ACCOMPLISHMENT TIMESCALE

A330-200/300 and A340-200/300 fitted with MLG sidestay upper cardan pins PN 201267202 &

201483202 which have accumulated more than 8 years since first overhaul and which have not yet 

gone through their second overhaul, at the issue date of this AOT, are subject to the following 

inspections:

1. The accomplishment of the DI mentioned in Para 4.2.2.1 must be performed no later than 30 

days after the issuance of this AOT. 

2. Repeat the DI mentioned in Para 4.2.2.1 every 10 days until a gap check as per Para 4.2.2.2 

is performed.

3. Perform a gap check as mentioned in Para 4.2.2.2 no later than 4 months after issuance of 

this AOT.

When a gap check is performed, the results (including nil findings) must be reported to Airbus using 

the proforma provided in Appendix 2 of this AOT.

4.2 DESCRIPTION

4.2.1 ACCESS

The Detailed Inspection and the gap check called for in this AOT do not require special access, 

equipment, or aircraft jacking. 

4.2.2 INSPECTION REQUIREMENTS

- 4.2.2.1 Detailed Inspection:
CUSTOMER SERVICES DIRECTORATE

1 ROND POINT MAURICE BELLONTE

31707 BLAGNAC CEDEX FRANCE

TELEPHONE + 33 (0)5 61 93 33 33

ALERT OPERATORS TRANSMISSION - AOT

AOT ref: A32L003-14 Page 3 of 5 Date: 10 Mar 2014

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Carry out a DI of the Upper Cardan Pin and retainer and nut assembly, ensuring that there is 

no pin chrome visible inboard of the wing rear spar fitting lug, and that the nut and locking 

device (including bolts and washers), are still in place. There is no requirement to remove the 

nut, pin and retainer at this stage.

Migrated upper cardan pin.

- 4.2.2.2 Gap check:

WARNING: MAKE SURE THAT THE SAFETY DEVICES AND THE WARNING NOTICES 

ARE IN A 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 INJURE PERSONS.

(a) Ensure that no gap exists between wing rear spar fitting lugs (outboard & inboard lugs) 

and their installed bush flanges (no bush migration). Refer to Appendix 1 and report in 

Appendix 2.

(b) Measure MLG Cardan Pin clearance dimensions X plus Y, which must be no greater than 

0.6 mm (0.0236 in.). Take largest gap measured at 3 points circumferentially. Refer to 

Appendix 1 or to Ref.1 Fig ‘Cardan Pin - Clearances’ SHEET 1.

(c) Repeat Gap check on the opposite side landing gear.

(d) Record all measurements.

(e) Report findings including measured gap dimensions (refer to Appendix 2)

Example:

Dim X (maximum gap measured between head of cardan pin and bush = 0.2 mm

Dim Y (maximum gap measured between nut and bush) = 0.35mm

Total Gap = Dim X + Dim Y = 0.55mm. 

Recorded gap measurement = 0.55mm.
CUSTOMER SERVICES DIRECTORATE

1 ROND POINT MAURICE BELLONTE

31707 BLAGNAC CEDEX FRANCE

TELEPHONE + 33 (0)5 61 93 33 33

ALERT OPERATORS TRANSMISSION - AOT

AOT ref: A32L003-14 Page 4 of 5 Date: 10 Mar 2014

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4.2.3 FINDINGS

For the DI:

- If pin chrome found visible inboard of the wing rear spar fitting lug: Before next flight, replace 

the cardan pin assembly (in accordance with Ref.5). Report to Airbus within 30 days.

For the Gap check:

- If measured gap (X+Y) is ≥ 1.5 mm: Before next flight, replace the cardan pin assembly (in 

accordance with Ref.5). Report to Airbus within 30 days.

- If measured gap (X+Y) is >0.6 mm but <1.5 mm: Before next flight, provide Airbus with the 

following information:

o Completed proforma provided in Appendix 2 of this AOT

o Photographs of cardan pin head/wing/bush interfaces and nut/bush/wing 

interfaces( if possible provide ‘macro level’ detail shots of nut and pin face)

o Movement Traceability Sheet (MTS) for the affected cardan pin

The aircraft can then continue operations for a 30 days grace period whilst Airbus review the 

information provided. Airbus will consult with the operator during this grace period to request 

specific actions in the event that the findings are judged to be abnormal.

- If measured gap (X+Y) is ≤ 0.6 mm: report gap to Airbus within 30 days. No further action 

required.

When a gap check is performed, the results (including nil findings) must be reported to Airbus using 

the proforma provided in Appendix 2 of this AOT.

4.3 SPARES AND TOOLING

In case of part’s replacement, please refer to Ref.2 for procurable part numbers.

In addition, refer to the applicable MBD CMM as follows:

- For Basic MLG: refer to Ref.3

- For Growth MLG: refer to Ref.4

Should spares be required, they will be available from MBD local distribution centres and allocated on a 

case by case basis.

5. FURTHER INFORMATION

It is anticipated that this AOT will be rendered mandatory by issuance of an EASA Airworthiness 

Directive (AD).

6. AOT APPROVAL

The technical content of this document is approved under the authority of DOA nr. EASA.21J.031.

7. REPORTING
CUSTOMER SERVICES DIRECTORATE

1 ROND POINT MAURICE BELLONTE

31707 BLAGNAC CEDEX FRANCE

TELEPHONE + 33 (0)5 61 93 33 33

ALERT OPERATORS TRANSMISSION - AOT

AOT ref: A32L003-14 Page 5 of 5 Date: 10 Mar 2014

© AIRBUS S.A.S. 2014. ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT

Questions about this AOT and inspection results with or without findings are to be sent to Airbus 

Customer Services engineering as soon as possible after the AOT application, to the attention of:

Philippe KERANGUEVEN

Customer Services – SEEL1

Phone : +33 (0) 5 67 19 18 42

Fax : +33 (0) 5 67 19 12 05

Email: philippe.kerangueven@airbus.com

Best Regards,

Jean-Luc MOUYSSET

VICE PRESIDENT ENGINEERING SUPPORT

CUSTOMER SERVICES

Philippe GOURDON

VICE PRESIDENT A330/A340 PROGRAMME

CUSTOMER SERVICES DIRECTORATE