EASA AD No.: 2012-0233

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EASA AIRWORTHINESS DIRECTIVE

AD No.: 2012-0233

Date: 07 November 2012

Note: This Airworthiness Directive (AD) is issued by EASA, acting in accordance with Regulation 

(EC) No 216/2008 on behalf of the European Community, its Member States and of the 

European third countries that participate in the activities of EASA under Article 66 of that 

Regulation.

This AD is issued in accordance with EU 748/2012, Part 21.A.3B. In accordance with EC 2042/2003 Annex I, Part M.A.301, the 

continuing airworthiness of an aircraft shall be ensured by accomplishing any applicable ADs. Consequently, no person may operate an 

aircraft to which an AD applies, except in accordance with the requirements of that AD, unless otherwise specified by the Agency [EC 

2042/2003 Annex I, Part M.A.303] or agreed with the Authority of the State of Registry [EC 216/2008, Article 14(4) exemption].

Design Approval Holder’s Name:

AIRBUS

Type/Model designation(s):

A300 aeroplanes

TCDS Number: France No 145

Foreign AD: Not applicable

Supersedure: None

ATA 05 Time Limits / Maintenance Checks – Ageing System Maintenance –

Airworthiness Limitations – Introduction

Manufacturer(s): Airbus (formerly Airbus industries)

Applicability: A300 aeroplane models, all serial numbers

Reason: The results of the Extended Service Goal (ESG) exercise for A300 series 

aeroplanes (75 000 flight hours (FH) or 48 000 flight cycles (FC), whichever 

occurs first) identified certain operational tests as Airworthiness Limitation Items 

(ALI), necessary to ensure the safety objectives for aeroplanes which have 

accumulated or exceeded 60 000 FH.

These ALI are not fully new, since all nine tasks derive from existing 

Maintenance Planning Document (MPD) tasks. Consequently, the intervals of 

those nine tasks can no longer be escalated or retained at an interval higher 

than that specified in this AD for each task.

Failure to comply with these tasks within the established maximum intervals 

could be detrimental to the safety of the affected aeroplanes.

For the reasons described above, this AD requires the implementation of nine 

specific operational ALI test for aeroplanes which have accumulated or 

exceeded 60 000 FH. 

In addition, Airbus performed an analysis of the impacts of ESG activities on 

A300 series aeroplanes and, based on the results, this AD publishes an 

operational life of 75 000FH or 48 000FC, whichever occurs first, applicable to

A300 system installations.

Effective Date: 21 November 2012
EASA AD No.: 2012-0233

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Required Action(s) 

and Compliance

Time(s):

Required as indicated, unless accomplished previously.

(1) Before exceeding 60 000 FH accumulated by the aeroplane, or within 90 

days after the effective date of this AD, whichever occurs later, verify that 

the ALI as listed in Appendix 1 of this AD are being accomplished within 

the intervals as specified in Appendix 1 of this AD, as applicable. If any ALI 

interval is currently included in the approved Aircraft Maintenance 

Programme (AMP) at an interval exceeding the value specified in Appendix 

1 of this AD, the AMP must be revised accordingly.

(2) After the verification as required by paragraph (1) of this AD, within the 

applicable interval, accomplish each ALI task as specified in Appendix 1 of 

this AD.

Note: Credit may be taken for the last accomplishment of these Aircraft 

Maintenance Manual (AMM) or MPD tasks to claim initial compliance with the 

requirements of paragraph (2) of this AD.

(3) Compliance with the requirements of paragraph (2) of this AD can be 

demonstrated by:

(3.1) Revising as follows the approved AMP, on the basis of which the 

operator or the owner ensures the continuing airworthiness of each 

operated aeroplane:

Incorporate all ALIs specified in Appendix 1 of this AD, including 

each applicable (not to exceed) interval,

and

(3.2) Complying with the approved AMP described in paragraph (3.1) of 

this AD.

(4) Do not operate any A300 series aeroplanes beyond 75 000FH or 48 

000FC, whichever occurs first.

Ref. Publications: A300 MPD Revision 30, dated 01 April 2010.

A300 AMM at latest revision, as applicable for each operator.

Remarks: 1. If requested and appropriately substantiated, EASA can approve 

Alternative Methods of Compliance for this AD.

2. This AD was posted on 13 April 2012 as PAD 12-029 for consultation until 

11 May 2012. The Comment Response Document can be found at 

http://ad.easa.europa.eu.

3. Enquiries regarding this AD should be referred to the Safety Information 

Section, Executive Directorate, EASA. E-mail: ADs@easa.europa.eu.

4. For any question concerning the technical content of the requirements in 

this AD, please contact AIRBUS SAS – EIAW (Airworthiness Office, 

Telephone: + 33 5 61 18 41 39, Fax: + 33 5 61 93 44 51).
EASA AD No.: 2012-0233

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Appendix 1 – Not-To-Exceed Intervals Of New Airworthiness Limitation Items 

MPD Task No. Task description Interval

(not to 

exceed)

AMM ref.

273311 0503 1

ARTIFICIAL FEEL – ELEVATOR - Operational 

test of pitch artificial feel by comparing 

qualitatively operating loads in high speed and 

low speed configurations (with each individual 

hydraulic system).

2 500 FH 273300/501

273313 0503 1

COMPUTER-ARTIFICIAL FEEL - Operational test 

of artificial feel "pitch feel" and "rudder travel" 

monitoring circuits (warning light test and 

indicating system test).

3 500 FH 272300/501

and

273300/501

222100 0503 1

YAW DAMPER - Operational test to verify correct 

operation of mechanical control between yaw 

damper system 2 and the rudder.

80 FH 222100/501

222600 0503 1

YAW DAMPER - Operational test to verify correct 

operation of mechanical control between yaw 

damper system 2 and the rudder.

80 FH 222600/501

272411 0503 1

SERVO CONTROL – RUDDER - Operational test 

of rudder servo controls (with individual hydraulic 

system) by moving Right Hand (RH) rudder pedal 

full forward and visually observe that rudder 

moves to the right. Check that rudder travel is 

confirmed on the flight control position indicator. 

Release RH pedal. Repeat above test by moving 

Left Hand rudder pedal.

250 FH 271400/501

275400 0503 1

FLAP ASYMMETRY - Operational test of flap 

asymmetry monitoring circuit, (incl. solenoid 

operation). 

500 FH 275400/501

275400 0503 2

FLAP PRESSURE-OFF BRAKE - Operational 

test of pressure-off brake.

1 000 FH 275400/501

278300 0503 1

SLAT ASYMMETRY - Operational test of slat 

asymmetry monitoring circuit.

500 FH 278300/501

278300 0503 2

SLAT PRESSURE-OFF BRAKE - Operational 

test of pressure-off brake.

1 000 FH 278300/501