FROM : AIRBUS CUSTOMER SERVICES TOULOUSE

ALL OPERATORS TELEX - ALL OPERATORS TELEX

SUBJECT: ATA29 - HYDRAULIC POWER - Inspection of electrical feeder 

cables

and Green hydraulic system electrical motor pump pressure hoses at 

frame

54, for Eaton (formerly Vickers) configuration.

OUR REF: AOT A310-29A2101 Rev 01 dated 12 April 2011

OUR PREVIOUS REF: AOT A310-29A2101 dated 09 November 2010

0.REASON FOR REVISION

The purpose of this AOT revision is to inform operators that:

. It is anticipated that an EASA Airworthiness Directive (AD) will 

render

this AOT inspection mandatory.

. The in-flight use of the Green EMPs is forbidden and will have to be

highlighted by a locally manufactured placard to be installed in the

cockpit with recording in the log book. This is applicable until the 

AOT ́s

requirement for inspection (and repair, if necessary) is completed.

.Due to AOT ́s reported findings, additional inspections, underneath the

clamps securing the electrical conduits, are requested.

Accomplishment of this revision is also necessary on aircraft having

already been inspected as per previous AOT issue.

The revised paragraphs are indicated by: **BEG.REV** and **END.REV**.

1.AIRCRAFT AFFECTED

All A310-200/-300 aircraft equipped with Eaton (Formerly Vickers) 

Hydraulic

Electrical Motor Pump (EMP) models.

2.REFERENCED DOCUMENTATION

REF.1: Airbus Service Information Letter (SIL) N° 29-047 (Rev 01 

February

1993).

REF.2: Airbus Modification N° 10017 S20254 (Prevent chafing between

electrical conduits and Green EMP FIN 11GE hydraulic pressure hose).

REF.3: Airbus mandatory Service Bulletin (SB) A310-29-2036 (Rev 03 June

2006).

REF.4: IPC 29-21-03 Figure 1 (Green EMP installation - Pre REF 2 Airbus

Modification and pre-REF.3 Airbus SB).

REF.5: IPC 29-21-03 Figure 1C (Green EMP installation - Post REF 2 

Airbus

Modification or post-REF.3 Airbus SB).
REF.6: IPC 24-92-03 Figure 17 (Green EMP electric feeder cable 

installation

at Frame 54 zone 147).

REF.7: AMM 20-23-11 Paragraph 7.Permitted damage and defects on 

flexible

hydraulic hoses.

REF.8: ESPM 20-53-21 Repair of standard cables (Damage check and repair

procedures).

REF.9: ESPM 20-53-31 Repair of convoluted conduits (Damage check and 

repair

procedures).

**BEG.REV**

REF.10: AOT A310-29A2102 dated 12 April 2011 for similar one time 

visual

inspection of the Parker (formerly Abex) installation condition.

3.REASON

3.1 FACTS

While preparing the aircraft, an A310-300 equipped with Eaton (formerly

Vickers) Green EMPs, for towing from the hangar, the two Green EMPs 

were

selected ON to close the MLG Doors. Then when the Green/Blue and

Green/Yellow Power Transfer Units (PTUs) were selected ON to retract 

the

Flaps/Slats, a large hydraulic haze (sprayed fluid) with a burnt 

electrical

smell came from the LH MLG wheel well bay. The electrical aircraft 

network

was switched off.

The left hand forward side area of the belly fairing was covered with

hydraulic spray while the equipment, electrical harnesses and 

connectors

showed signs of high temperature exposure.

The leak was coming from the Green EMP FIN 11GE pressure line with

insulation damage on one cable of the electrical feeder cables for 

Green

EMP FIN 12GE, in the area of the hydraulic leak. As the leak and cable

insulation damage are the only visible evidences, it is supposed that

hydraulic spray combined with possible electrical arcing might be the

source of the reported damage.

This aircraft was delivered early 1993 with the REF.2 Airbus 

Modification

embodied. This Modification was issued to avoid past event of chafing

between electrical conduits and hydraulic pressure hose.

3.2 CONSEQUENCES

Due to the proximity of both the Green EMP hydraulic pressure hose and

electrical feeder cables, if damage occurs to the feeder cable with, at 

the

same time, leakage at the hydraulic pressure hose, it might result in 

the

reported event.

3.3 AIM

This AOT is to request:
- Installation of a locally manufactured placard in the cockpit 

forbidding

the in-flight use of the Green EMPs,

- Recording in the logbook of this requirement to not operate the Green

EMPs in flight,

- A one-time visual inspection to verify the correct installation and

condition (With repair if necessary) of

. The hydraulic pressure hoses (REF.4 or REF.5 IPC figure),

. The electrical conduits, feeder cables (REF.6 IPC figure),

. The associated clamping devices at Frame 54 as well as the electrical

conduits, feeder cables (REF.6 IPC figure) underneath the clamps. This

requires removal of the concerned clamps,

This is applicable to all A310-200 / -300 with Eaton (formerly Vickers) 

EMP

models fitted, whatever their installation configuration i.e. with or

without the REF 2 Airbus Modification and / or REF 3 Airbus SB 

embodied.

4.SHORT TERM ACTION

4.1 PLANNING AND MANPOWER

The AOT ́s requirements described in paragraph 4.2 have to be carried 

out at

the next convenient opportunity e.g. during a night stop,

. Within 15 calendar days from the issue date of the AOT Rev 01 for

installation in the cockpit of a locally manufactured placard 

forbidding

the in-flight use of the Green EMPs, with recording in the logbook,

. Within 500 FH or 4 months whichever comes first, from the issue date 

of

the AOT Rev 01 for the inspection and repair, if necessary. The 

estimated

manpower for inspection without findings is about 2.00 hours.

-It is anticipated that this AOT will be rendered mandatory by an EASA

Airworthiness Directive (AD).

4.2 AOT ́s REQUIREMENTS

a) INSTALLATION IN THE COCKPIT OF A LOCALLY MANUFACTURED SELF-ADHESIVE

PLACARD WITH RECORDING IN THE LOGBOOK

(1) Install on the "HYD PWR" overhead panel 427VU, a locally 

manufactured

self-adhesive placard forbidding the in-flight use of the Green EMPs 

(P/BSW

FIN 14GE - "ELEC PUMPS").

As a proposal, the placard could be as follows:

. With the below wording and letters of about 2 to 3 mm height on a 

selfadhesive placard size of 45 mm width and 10 mm height,

DO NOT USE GREEN

ELEC PUMPS IN FLIGHT

. With placard installed on or above the "ELEC PUMPS" push button 

switch of

"HYD PWR" overhead panel 427VU,

(2) Make an entry in the logbook to record, as per above placard, that 
the

in-flight use of the Green EMPs is forbidden. Also mention that this

limitation is applicable until AOT ́s requirement for inspection (and

repair, if necessary) is completed as per AOT ́s paragraph 4.2.b).

Once AOT ́s requirement is completed (inspection and repair, if 

necessary),

remove the placard from the cockpit and clear the associated logbook 

entry.

b) INSPECTION / REPAIR / REPLACEMENT

(1) Preparation for the inspection / replacement procedure

- Make sure that the aircraft is electrically grounded (AMM 24-00-00 

Page

Block 301).

- De-energize the aircraft electrical circuits (AMM 24-41-00 Page Block

301).

- Open the LH main landing gear (MLG) door (AMM 32-12-11 Page Block 

301).

- Put the access platform in position in zone 147.

- Depressurize the Green hydraulic system (AMM 29-10-00 Page Block 

301).

(2) Inspection / replacement procedure

With reference to REF.3 Airbus SB (Figures on pages 13, 14 and 15)

reflecting the two possible in-service installation configurations of 

the

Green EMP hydraulic pressure hoses, electrical conduits and feeder 

cables,

perform the following inspection with repair and/or replacement if

required:

*For aircraft of pre-REF.2 Airbus Modification and pre REF 3 Airbus SB

configuration, identified as "BEFORE" on REF.3 Airbus SB (Figures on

pages 13 and 15) and reflected also on REF.4 IPC figure,

 - Inspect at "C" location (Figure page 15 "BEFORE" 

configuration),

the

 clamps, the electrical conduits, the feeder cables and the 

hydraulic

 pressure hoses for correct condition and installation.

 o Remove clamps securing the electrical conduits 

(Figure

page 15

 "BEFORE" configuration), check condition of the 

clamping

device

 as well as of the electrical conduits to ensure there 

are

no

 damage,

 - If damage is found on the electrical conduits, check the 

condition

of

 the electrical feeder cables,

 - If chafing marks or damage beyond allowable limits are 

apparent

 replace or repair the affected parts (Hydraulic pressure hoses,
 Electrical conduits, feeder cables, clamps).

 o For permissible damage and defects on hydraulic 

hoses, see

REF

 7 AMM procedure.

 o For repair of electrical conduit and feeder cable, 

see REF

8

 and REF.9 ESPM procedures.

 - If not already done, install on the upper hydraulic pressure 

hose

 length (Green EMP FIN 11GE) a spiralex band (Spiral trip) ref

 NSA849000T125 as per REF.1 Airbus SIL or apply the REF.3 Airbus 

SB.

 Make sure that the installation is in accordance with REF.3 

Airbus

SB

 "BEFORE" configuration (Figures on pages 13 and 15) and REF.4 

IPC

figure.

 For information, REF.3 Airbus SB was mandated by EASA AD N°

2006-0285R1

 dated November 13, 2006.

*For aircraft of post-REF.2 Airbus Modification or post-REF.3 Airbus SB

configuration, identified as "AFTER" on REF.3 Airbus SB (Figures on

pages 14 and 15) and reflected on REF.5 IPC figure,

 - Inspect at "C" location (Figure page 15 "AFTER" 

configuration),

the

 clamps, the spacer, the electrical conduits, the feeder cables 

and

 hydraulic pressure hoses for correct condition and 

installation.

 o Remove clamps securing the electrical conduits 

(Figure

page 15

 "AFTER" configuration), check condition of the 

clamping

device

 as well as of the electrical conduits to ensure there 

are

no

 damage,

 - If damage is found on the electrical conduits, check the 

condition

of

 the electrical feeder cables,

 - If chafing marks or damage beyond allowable limits are 

apparent

 replace or repair the affected parts (Hoses, Electrical 

conduits,

 feeder cables, clamps, spacer).

 o For permissible damage and defects on hydraulic 

hoses, see

REF

 7 AMM procedure.
 o For repair of electrical conduit and feeder cable, 

see REF

8

 and REF.9 ESPM procedures.

 - Make sure that the installation is in accordance with REF 3 

Airbus

SB

 "AFTER" configuration (Figures on pages 14 and 15) and REF 5 

IPC

 figure.

 **END.REV**

(3) Test

If hydraulic hoses, Green EMP electrical plug(s) and / or electrical 

feeder

cables have been disconnected for repair or replacement, do an 

operational

test of the Green EMPs as per AMM 29-21-00 Page Block 501.

(4) Close-up

-Make sure that the work areas are clean and clear of tools and other

items.

-Remove the access platform.

-Close the main landing gear (MLG) door LH (AMM 32-12-11 Page Block 

301).

4.3 MATERIAL AND TOOLING

For details about the material for both installation configurations, 

you

can refer to

-REF.3 Airbus SB (Page 7) for components.

-REF.4 IPC 29-21-03 figure 1 for pre-Airbus SB and pre-Airbus 

Modification

configuration.

-REF.5 IPC 29-21-03 figure 1C for post-Airbus SB or post-Airbus

Modification configuration.

-REF.6 IPC 24-92-03 Figure 17 for electrical conduits, feeder cables

installation.

5.FURTHER ACTION

An improvement of the clamping of the electrical conduits and hydraulic

pressure hoses is being reviewed. The solution is expected to be 

available

(Airbus Service Bulletin) by second half of 2012. For your information, 

as

the reported chafing phenomenon is a long term process, with the 

current

AOT ́s inspection requirement enough time will remain for implementation 

of

the forthcoming solution, Airbus Service Bulletin.

6.AOT APPROVAL

The technical content of this AOT has been approved under EASA Design
Organization Approval EASA.21J.031.

**BEG.REV**

7.ACKNOWLEDGEMENT / REPORTING

7.1 ACKNOWLEDGMENT

Operators are requested to acknowledge receipt of this AOT within 48 

hours

after receipt to:

Mlle Laetitia BONNET, SEEL

Phone number: +33 (0)5 67 19 24 40

Fax number: +33 (0)5 61 93 32 73

E-mail: Laetitia.bonnet@airbus.com

This acknowledgement can be made through the Airbus field service 

office

where available.

7.2 QUESTIONS / REPORTING

Questions regarding this AOT and inspection results, with or without

findings, are to be sent (See in below note the requested information) 

to

Airbus Customer Services Engineering as soon as possible after the AOT

application, to the attention of:

Mr. Georges GENIN SEEL4

Phone number: +33 (0)5 61 93 49 29

Fax number: +33 (0)5 61 93 32 73

E-mail: georges.genin@airbus.com

Note:

-Aircraft MSN.

-Any previous issues on parts / installation to be inspected by this 

AOT.

-Implementation date of mandatory REF 3 Airbus SB.

-If any, detailed description of the findings with, if possible, 

pictures

of the affected parts / installation.

-If any, detailed which parts have been repaired or replaced,

**END.REV**

Best regards,

E. VAN AELST

VICE PRESIDENT A300 PROGRAMME

CUSTOMER SERVICES DIRECTORATE