AIRBUSA380

ID: 2017-0131R1
Issue date: 2017-10-09
Effective date: 2017-10-09  
Source: EASA
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Landing Gear – Gravity Extension System – Inspection / Modification

EASA AD No.: 2017-0131R1


Airworthiness Directive
AD No.: 2017-0131R1
Issued: 09 October 2017
Note: This Airworthiness Directive (AD) is issued by EASA, acting in accordance with Regulation
(EC) 216/2008 on behalf of the European Union, 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 Regulation (EU) 748/2012, Part 21.A.3B. In accordance with Regulation (EU) 1321/2014 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 [Regulation (EU) 1321/2014 Annex I,
Part M.A.303] or agreed with the Authority of the State of Registry [Regulation (EC) 216/2008, Article 14(4) exemption].


Design Approval Holder’s Name: Type/Model designation(s):
AIRBUS A380 aeroplanes

Effective Date:
Revision 1: 09 October 2017
Original issue: 10 August 2017
TCDS Number(s): EASA.A.110
Foreign AD: Not applicable
Revision: This AD revises EASA AD 2017-0131 dated 27 July 2017.


ATA 32 – Landing Gear – Gravity Extension System – Inspection / Modification


Manufacturer(s):

Airbus

Applicability:

Airbus A380-841, A380-842 and A380-861 aeroplanes, all manufacturer serial numbers, except
those that have embodied Airbus modification (mod) 77381 in production.

Reason:

During a free-fall gravity landing gear (LG) extension of an A380 aeroplane, the left hand (LH) wing
LG failed to extend, remained in up-locked position in the LG bay and an associated alert was
initiated. Consequent investigation determined that the wiring of both channels, A and B, of the LG
gravity extension system, providing electrical signals to the LH wing LG Emergency Unlock Actuator
(EUA), were found damaged. Similar wiring damage was also detected on channel B of the right
hand (RH) wing LG up-lock EUA. The investigation concluded that the detected wiring failure mode
was provoked by fatigue degradation present in the wing LG gear up-lock areas. No fatigue
degradation of wiring was identified in the up-lock areas of nose LG, body LG and wing LG doors.

This condition, if not detected and corrected, could result in a failure of the wing LG emergency
gravity extension system, possibly preventing safe landing in case of a failure of the normal LG
extension system.


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EASA AD No.: 2017-0131R1

To address this potential unsafe condition, Airbus issued Alert Operators Transmission (AOT)
A32R009-16 to provide instructions for one-time inspection of EUAs fitted onto the LGs, up-locks of
LG doors and LG gravity extension on ground. The inspection results collected during
accomplishment of original issue of Airbus AOT A32R009-16 confirmed that the fatigue degradation
was present only on the wing LG up-lock EUA wiring. Consequently, Airbus issued Revision 01 of
Airbus AOT A32R009-16 providing instructions for repetitive inspections of wing LG up-lock EUA
wiring and retaining on ground LG gravity extension tests. Additionally, Airbus developed mod
77381, introducing improved attachments for harnesses connected to wing LG EUAs, available for
in-service aeroplanes through Airbus Service Bulletin (SB) A380-92-8103.

For the reasons described above, EASA issued AD 2017-0131 to require repetitive detailed
inspections (DET) of wing LG up-lock EUA wiring and functional tests of the wing LG gravity
extension system, accomplishment of applicable corrective action(s), and modification of the
electrical harness, which constitutes terminating action for the repetitive DET and functional tests.

After that AD was issued, it was determined that the safety intent of the AD can be achieved by
accomplishing a general visual inspection (GVI) in lieu of the more intensive examination
corresponding to DET. This AD is revised accordingly.

Required Action(s) and Compliance Time(s):

Required as indicated, unless accomplished previously:

Inspection(s):
(1) Within 6 months after aeroplane first flight or after accomplishment of the last wing LG up-lock
EUA wiring inspection and LG gravity extension test in accordance with the instructions of
Airbus AOT A32R009-16, as applicable, or within 30 days after 10 August 2017 [the effective
date of the original issue of this AD], whichever occurs later, and, thereafter, at intervals not to
exceed 6 months, accomplish concurrently the actions as required by paragraphs (1.1) and (1.2)
of this AD, in accordance with the instructions of Airbus AOT A32R009-16 Revision 01.

(1.1) A DET or GVI of wire harnesses connected to wing LG up-lock EUA.

(1.2) An on-ground wing LG gravity extension test.

Corrective Action(s):
(2) If, during any inspection or test as required by paragraph (1) of this AD, any discrepancy is
detected, before next flight, accomplish the applicable corrective action(s) in accordance with
the instructions of Airbus AOT A32R009-16 Revision 01.

Credit:
(3) Inspection(s), wing LG gravity extension test(s) and, depending on finding(s), corrective
action(s) on an aeroplane, accomplished before 10 August 2017 [the effective date of the
original issue of this AD] in accordance with the original issue of Airbus AOT A32R009-16, are
acceptable to comply with the initial inspection and LG gravity extension test as required by
paragraph (1) of this AD for that aeroplane.




TE.CAP.00110-006 © European Aviation Safety Agency. All rights reserved. ISO9001 Certified. Page 2 of 3
Proprietary document. Copies are not controlled. Confirm revision status through the EASA-Internet/Intranet.
An agency of the European Union
EASA AD No.: 2017-0131R1

Modification:
(4) Within 36 months after 10 August 2017 [the effective date of the original issue of this AD],
modify the wing LG EUA electrical harnesses in accordance with the instructions of Airbus SB
A380-92-8103.

Terminating Action:
(5) Modification of an aeroplane as required by paragraph (4) of this AD constitutes terminating
action for the repetitive inspections and wing LG gravity extension tests as required by
paragraph (1) of this AD for that aeroplane.

Ref. Publications:

Airbus AOT A32R009-16 original issue dated 22 November 2016, or Revision 01 dated 28 February
2017.

Airbus SB A380-92-8103 original issue dated 05 May 2017.

The use of later approved revisions of these documents is acceptable for compliance with the
requirements of this AD.

Remarks:
1. If requested and appropriately substantiated, EASA can approve Alternative Methods of
Compliance for this AD.

2. The original issue of this AD was posted on 14 June 2017 as PAD 17-078 for consultation until
12 July 2017. No comments were received during the consultation period.

3. Enquiries regarding this AD should be referred to the EASA Safety Information Section,
Certification Directorate. E-mail: ADs@easa.europa.eu.

4. For any question concerning the technical content of the requirements in this AD, please
contact: Airbus – EIANA (Airworthiness Office), Telephone: +33 562 110 253;
Fax: +33 562 110 307, E-mail: account.airworth-A380@airbus.com.




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This is a partial extract of the full document - please refer to the actual report for full information.
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