CUSTOMER SERVICES DIRECTORATE

1 ROND POINT MAURICE BELLONTE

31707 BLAGNAC CEDEX FRANCE
TELEPHONE + 33 (0)5 61 93 33 33

A L E R T O P E R A T O R S T R A N S M I S S I O N

- A O T

AOT ref: 24L001-13 Rev 01 Page 1 of 4 Date: 06 Mar 2014 SUBJECT: ATA 24 – INSPECTION FOR LOCKING OF CONTACTS ON GCU-CSMG CONNECTOR 1XE-A

OUR REF.: A24L001-13 Rev 01 dated 06 Mar 2014.

OUR PREV. REF.: A24L001-13 dated 25 Jul 2013.

0. REASON FOR REVISION

This AOT is revised to update the AMM tasks indicated by Ref /E/, /F/ and /G/.

It is to be noted that the above mentioned changes do not affect the technical content of this AOT.

The revised paragraphs are indicated between **BEG. REV** and **END REV**.

1. AIRCRAFT AFFECTED

All A330 and A340 aircraft up to MSN 1391, except MSN 925, 1382.

**BEG. REV**

2. REFERENCED DOCUMENTATION

Ref /A/ - A330 MPD 242400-01-2

Ref /B/ - A330 MPD 242400-01-3

Ref /C/ - A340 MPD 242400-01-1 & 242400-01-2

Ref /D/ - A330 & A340 AMM 24-24-34-000-801-A

Ref /E/ - A330 & A340 AMM 24-24-00-710-801-A

Ref /F/ - A330 & A340 AMM 24-24-00-710-803-A

Ref /G/ - A330 & A340 AMM 24-42-00-862-801-A

Ref /H/ - A330 & A340 AMM 24-24-34-400-801-A

Ref /J/ - ESPM 20-33-45

Ref /K/ - ESPM 20-25-41

Ref /L/ - ESPM 20-44-11

Ref /M/ - ESPM 20-48-21

Ref /N/ - ESPM 20-33-44

Ref /P/ - A330 & A340 TSM 24-24-00 PB201

**END REV**.CUSTOMER SERVICES DIRECTORATE

1 ROND POINT MAURICE BELLONTE

31707 BLAGNAC CEDEX FRANCE
TELEPHONE + 33 (0)5 61 93 33 33

A L E R T O P E R A T O R S T R A N S M I S S I O N

- A O T

AOT ref: 24L001-13 Rev 01 Page 2 of 4 Date: 06 Mar 2014 3. REASON

It has been found during aircraft production that so me contacts of GCU-CSM/G (Generator Control Unit - Constant Speed Motor / Generator) connector 1XE-A might not be correctly locked in position.

3.1 FACTS During pre-delivery testing of one recently manufactured A330 aircraft, the operational test (Ref /E/) of the

CSM/G was not successful.

Troubleshooting revealed that three contacts of the connector 1XE-A were not properly locked into the

connector.

An investigation of all other production aircraft availabl e at that time revealed other cases of the same issue.

3.2 CONSEQUENCES A badly locked contact could result in a loss of continuity and lead to the non-operation of the CSM/G.

An operational test of the CSM/G is performed every 75FH (Ref /A/) (50FH for ETOPS beyond 180 minutes, Ref /B/) on A330 and every 800FH for A340 (Ref /C/). However, due to the risk of potential intermittent electrical contact (which might allow the system to operate successfully on ground during the test but not in fli ght due to loss of contact continuity), it is requested to perform a one-time inspection as described by this AOT.

3.3 AIMThe aim of this AOT is to provide instructions to perform a one-time inspection and, if necessary, correctly reengage the contacts of connector 1XE-A.

4. SHORT TERM ACTION

4.1 PLANNING AND MANPOWER

4.1.1 ACCOMPLISHMENT TIMESCALE Operators are requested to perform the one-time inspecti on and, if necessary, the corrective action described paragraph 4.2, on all aircraft affected by this AOT within 1000FH of the reception of this AOT.

4.1.2 MANPOWER The estimated time to perform the inspection, repair (if necessary), gain access and close up is 1 MH. The estimated time to perform the test is 0.3 MH

4.2 DESCRIPTION

4.2.1 ACCESS AND JOB SET-UP Do the Job Set-Up procedure as specified in paragraphs 2 and 3 of the AMM task Ref /D/ (Removal of the CSM/G Generator Control Unit (GCU) (1XE)).CUSTOMER SERVICES DIRECTORATE

1 ROND POINT MAURICE BELLONTE

31707 BLAGNAC CEDEX FRANCE
TELEPHONE + 33 (0)5 61 93 33 33

A L E R T O P E R A T O R S T R A N S M I S S I O N

- A O T

AOT ref: 24L001-13 Rev 01 Page 3 of 4 Date: 06 Mar 2014 4.2.2 INSPECTION PROCEDURE AND TESTS: The inspection procedure will apply to the following list of wires: Wire n°2424-0138B (1XE-A, cavity E) Wire n°2424-0138R (1XE-A, cavity D) Wire n°2424-0145B (1XE-A, cavity J) Wire n°2424-0145R (1XE-A, cavity G) Wire n°2424-0145Y (1XE-A, cavity H) Wire n°2424-0207 (1XE-A, cavity F)

• Disconnect the electrical connector 1XE-A. • As required, remove cable tie/lacing tape from the electrical harness to facilitate inspection. • As per Ref /J/, unscrew the connector backshell 1XE-A1. • As per Ref /K/, gently pull individually each of the listed connector’s wire. • If any contacts are found incorrectly engaged in the conn ector, inspect them before next flight for traces of arcing or overheating damage. • If no arcing or overheating damage is found, then before next flight, re-engage the contacts per Ref /M/ and test by pulling to ensure that the contacts stay correctly engaged. • If arcing or overheating damage is found, then before next flight: i. Replace all affected contacts per Ref /M/ and, if necessary, the connector per Ref /L/. ii. Inspect the receptacle contacts of the GCU-CSM/G (1XE) for traces of arcing or overheating damage. In case of findings, before next flight, replac e the GCU-CSM/G in accordance with Ref /D/ and Ref /H/ if necessary. • Record any contacts which have been found incorrectly engaged or damaged. These findings should be reported as requested in paragraph 7 of this AOT. • As per Ref /J/, re-install the connector backshell 1XE-A1. • As per Ref /N/, re-install cable ties/lacing tape.

• Make sure that the electrical connector is clean and in the correct condition.

• Re-connect the electrical connector 1XE-A.

Remove the safety clip and the tag and close the circuit breaker opened with Ref /D/.

OPERATIONAL TEST: • Do the operational test of the GCU-CSM/G from the CMC(s) (Ref /F/). • Do the operational test of the emergency generation system (Ref /E/). • If either of the two operational tests is not successful, refer to TSM task Ref /P/.

CLOSE-UP:

• Make sure that the work area is clean and clear of tools and other items.

• Close the access door 811. • Remove the access platform. • De-energize the ground service network (Ref /G/).CUSTOMER SERVICES DIRECTORATE

1 ROND POINT MAURICE BELLONTE

31707 BLAGNAC CEDEX FRANCE
TELEPHONE + 33 (0)5 61 93 33 33

A L E R T O P E R A T O R S T R A N S M I S S I O N

- A O T

AOT ref: 24L001-13 Rev 01 Page 4 of 4 Date: 06 Mar 2014 4.3 SPARES AND TOOLING No specific spares and tooling are necessary

5. FURTHER INFORMATION

5.1 FOLLOW-UP PLAN No follow-up of this AOT is planned.

5.2 IMPACTED DOCUMENTATION No documentation changes are planned as a result of this AOT.

6. AOT APPROVAL

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

It is anticipated that the instructions contained in this AOT will be rendered mandatory by the Airworthiness

Authorities.

7. REPORTING

Questions about this AOT and inspection results with or without findings are to be sent to Airbus Customer Services engineering as soon as possible, af ter the AOT application, to the attention of:

Ciaran MCCORMACK Electrical Power Generation & Lighting Systems Airbus Customer Services Engineering – SEEA5

CUSTOMER SERVICES Phone: +33 (0)5 82 05 58 17 Fax: +33 (0)5 61 93 44 25

Mailto: ciaran.mccormack@airbus.com

Best Regards,

Jean-Luc MOUYSSET Philippe GOURDON
VICE PRESIDENT ENGINEERING SUPPORT VICE PRESIDENT A330/A340 PROGRAMME

CUSTOMER SERVICES CUSTOMER SERVICES