EASA AD No.: 20 14

- 0166

TE. CAP.0011 0

- 00 3 © European Aviation Safety Agency. All rights reserved. 1 / 4 Proprietary document. Copies are not controlled. Confirm revision status through the EASA

- Internet/Intranet. 

## EASA AIRWORTHINESS DIRECTIVE

AD No

. : 20 14 - 0166

Date : 16 July 2014

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 ope rate 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): A319, A320 and A321 aeroplanes

TCDS Number: EASA.A.064

F oreign AD: Not applicable Supersedure: This AD supersedes DGAC France AD F

- 2003

- 434 dated 10 December 2003 (EASA

approval 2003

- 1436)

.



### ATA 52 Door s – Main Landing Gear Door Actuator Fitting s – Inspection /

Replacement

Manufacturer(s): Ai rbus (formerly Airbus Industrie ) Applicability: Airbus A319

- 111, A319

- 112, A319

- 113, A319

- 114, A319

- 115, A319

- 131, A319

- 132, A319

- 133, A320

- 211, A320

- 212, A320

- 214, A320

- 215, A320

- 216, A320

- 231, A320

- 232, A320

- 233, A321

- 111, A321

- 112, A321

- 131, A321

- 211, A321

- 212, A321

- 213, A321

- 231 and A321

- 232 aeroplanes, all manufacturer serial numbers

. Reason: On one A320 aeroplane , it was reported that one of the main landing gear (MLG) doors could not be closed . Investigations revealed the rupture of the actuator fitting at the actuator attachment area on t he door side. The MLG door is attached to the aeroplane by 2 hinge fittings. This condition , if not corrected , could, u nder certain circumstances , lead to detach ment of a MLG door from the aeroplane, possibly resulting in damage to the aeroplane , and/or injury to persons on the ground. Prompted by these findings, DGAC France issued AD 1999

- 243

- 133 (later revised to R1 ) , to requ ir e a MLG door actuator fitting inspect ion for cracks and to check the grain direction on a batch of aeroplanes

. Subsequently, DGAC France issued AD 2000

- 257

- 149 , retaining the requirement of DGAC France AD 1999

- 243

- 133 R1, which was superseded, to requ ir e an inspection of the lower part of the MLG door actuator fitting. A fter that AD was issued, a dditional in vestigation s revealed that damage could also appear on the nerve area, in the upper part of the MLG door actuator fitting inEASA AD No.: 20 14

- 0166

TE. CAP.0011 0

- 00 3 © European Aviation Safety Agency. All rights reserved. 2 / 4 Proprietary document. Copies are not controlled. Confirm revision status through the EASA

- Internet/Intranet. the area of the hinge. Consequently, DGAC France issued AD F

- 2003

- 434 (EASA approval 2003

- 1436) , retaining the requirement s of DGAC France AD 2000

- 257

- 149 , which was superseded, to require additional repetitive inspection s

. That AD also included an optional terminating action, by replacing the MLG door actuator fitting s in accordance with the instructions of Airbus Service Bulletin (SB) A320

- 52

- 1073. Since that AD was issued, i n the frame work of the extended service goal campaign, it has been decided to make replacement of the MLG door actua tor fitting s a required modification

. For th e reasons describe d above, this AD retains the requirements of DGAC France AD F

- 2003

- 434 , which is superseded , and requires replacement of the MLG door actuator fitting s with new monoblock fittings , which constitutes terminating action for the repetitive inspections

. Effective Date: 30 July 2014
Required A ction(s) and Compliance Time(s) : Required as indicated, unless accomplished previously: Restatement of the requirement s of DGAC France AD F
- 2003 - 434 : (1) For aeroplane s equipped with MLG door fitting s Part Number ( P/N ) D52880224 000/001 that were installed at the time of aeroplane first delivery on MLG door s with serial number s (S/N) as specified in T able 1 of this AD , w ithin 500 flight hours (FH) from the last inspection in accordance with the instructions of Airbus SB A320

- 52A1086 Revision 01 , and , thereafter , at interval s not exceeding 500 FH , accomplish a h igh f requency e ddy c urrent (HFEC ) inspection in accordance with the instructions of Airbus SB A320

- 52A1086 R evision 0 1.
Table 1

– MLG Door s Location S/N
L H 1206 to 1237 inclusive , 1239 to 1247 inclusive , and

1249 to 1251 inclusive
R H 1208 to 1239 inclusive , 1241 to 1249 inclusive , and

1251

(2) If, during any HFEC inspection as required by paragraph (1) of this AD, any crack is found , within the compliance time ( threshold ) specified in Airbus SB A320

- 52A1086 R evision 0 1 , replace the MLG door actuator fitting s in accordance with the instruction s of Airbus SB A320

- 52

- 1073 R evision 05

. (3) If, during any HFEC inspection as required by paragraph (1) of this AD, no crack is detected, accomplish a l ow f requency e ddy c urrent (LFEC) inspection to determine the grain direction of the raw material of each actuator fitting in accordance with the instructions of Airbus SB A320

- 52A1086 R evision 0 1

. (3.1) If , during the LFEC inspection as required by paragraph (3) of this AD, the grain direction of the raw material of the fitting is found to be correct , the repetitive inspections of paragraph (1) of this AD can be terminated. (3.2) If , during the LFEC inspection as required by paragraph (3) of this AD, the grain direction of the raw material of the fitting is found to be in correct , continue the HFEC inspecti on s as required by paragraph (1) of this AD or, before ne x t flight , replace the MLG door actuator fitting s in accordance with the instructions of Airbus SB A320

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- 1073 Revision 05

.EASA AD No.: 20 14

- 0166

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- 00 3 © European Aviation Safety Agency. All rights reserved. 3 / 4 Proprietary document. Copies are not controlled. Confirm revision status through the EASA

- Internet/Intranet. (4) For aeroplanes equipped with MLG door fitting s P/N D52880224 000/001 or P/N D52880235 000/001 , w ithin 400 f light c ycles (FC) after 2 0 December 2003 [ the effective date of DGAC France AD F

- 2003

- 434 ] , or before exceeding 9 000 FC since aeroplane first flight , whichever occurs later, and , thereafter , at interval s not exceeding 800 FC, accomplish a HFEC inspection in both hinge and nerve area s in accordance with the instructions of Airbus SB A320

- 52

- 1096 R evision 0 2

. (5) If, during any HFEC inspection as required by paragraph (4) of this AD, any crack is found on the hinge area , or on the nerve area, within the compliance time (threshold) specified in Airbus SB A320

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- 1096 Revision 02 , replace the MLG door actuator fitting s in accordance with the instruction s of Airbus SB A320

- 52

- 1073 R evision 05

. (6) If, during any HFEC inspection as required by paragraph (4) of this AD, any crack is found on both hinge and nerve area s , before next flight, replace the affected fitting (s) in accordance with the instructions of Airbus SB A320

- 52

- 1096 R evision 0 2 or , within the compliance time (threshold) specified in Airbus SB A320

- 52

- 1096 Revision 02 , replace the MLG door actuator fitting s in accordance with the instruction s of Airbus SB A320

- 52

- 1073 R evision 05. (7) Inspections and corrective actions , accomplished before the effective date of this AD in accordance with the instructions of Airbus SB A320

- 52

- 1096 Revision 01 are acceptable to comply with the initial requirements of paragraph s (4) and (6) of this AD

. New requirements of this AD : ( 8 ) For all aeroplanes equipped with MLG door fitting s with a P/N as listed in T able 2 of this AD, b efore exceeding 48 000 FC or 96 000 FH , whichever occurs later since aeroplane first flight , replace the MLG door actuator fitting s in accordance with the instruction s of Airbus SB A320

- 52

- 1073 Revision 05

. Table 2

– MLG Door Actuator Fittings P/N
D52880102000 D52880102 00 1 D52880220000 D52880220 00 1 D52880224000 D52880224 00 1 D52880235000 D52880235 00 1
( 9 ) Modification of an aeroplane, prior to the effective date of this AD in accordance with the instructions of Airbus SB A320

- 52

- 1073 (at any revision) is acceptable to comply with the requirements of paragraph ( 8 ) of this AD for that aeroplane. ( 10 ) An aeroplane on which Airbus modification (mod) 24903 , or mod 25372, or mod 36979 has been embodied in pro duction is not affected by the requirements of this AD, except as specified below, provided that no MLG door actuator fitting with a P/N as listed in Table 2 of this AD has been reinstalled on that aeroplane since first flight. Paragraph ( 13 .1) of this AD remains applicable to post

- mod 24903 , post

mod 25372 and post

- mod 36979 aeroplanes

. (11) Modification of an aeroplane in accordance with the instructions of Airbus SB A320

- 52

- 1073 (at any revision) to in stall fittings with P/N D52880246002EASA AD No.: 20 14

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- 00 3 © European Aviation Safety Agency. All rights reserved. 4 / 4 Proprietary document. Copies are not controlled. Confirm revision status through the EASA

- Internet/Intranet. and P/N D52880246003 is acceptable to comply with the requirements of paragraph (8) of this AD for that aeroplane

. ( 12 ) Modification of an aeroplane as required by paragraph (2) or (5) or (8) of this AD, as applicable, or as specified in paragraph (3 .2) or (6) of this AD , as applicable, constitutes terminating action for the repetitive inspection s required by this AD for t hat aeroplane

. ( 13 ) Do not install on an y aeroplane a MLG door actuator fitting with a P/N as listed in T able 2 of this AD , as required by paragraph ( 13 .1) or ( 13 .2) of this AD, as applicable

. ( 13 .1) For an aeroplane that, on the effective date of this AD, ha s fitting s installed with a P/N not listed in Table 2 of this AD : From the effective date of this AD. ( 1 3 .2) For an aeroplane that, on the effective date of this AD, has fittings installed with a P/N as listed in Table 2 of this AD: After modification of the aeroplane as required by paragraph ( 2 ) or (5) or ( 8 ) of this AD, or as specified in paragraph (3 .2 ) or ( 6 ) of this AD. ( 1 4 ) Modification of an aeroplane by installing a version (P/N) of the MLG door actuator fitting approved after the effective date of this AD is equal to compliance with the requirements of paragraph ( 8 ) of this AD for that aeroplane , provided the conditions , as specified in paragraphs (14.1) and (14.2) of this AD, are met. ( 1 4 .1) The MLG door actuator fitting (P/N) must be approved by EASA, or approved under Airbus DOA; and ( 1 4 .2) The modification must be accomplished in accordance with instructions approved by EASA, or approved under Airbus DOA.
Ref. Public ations: Airbus SB A320

- 52

- 1073 original issue dated 02 February 1996, or Revision 01 dated 26 April 1996, or Revision 02 dated 07 April 1997, or Revision 03 dated 01 October 1998, or Revision 04 dated 10 August 1999, or R evision 0 5 dated 28 September 2006

. Airbus SB A320

- 52A1086 R evision 0 1 dated 10 September 1999

. Airbus SB A320

- 52

- 1096 Revision 01 dated 23 October 2003, or R evision 02 dated 12 July 2006

. The u se 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. This AD was posted on 04 June 2014 as PAD 14

- 0 93 for consultation until 02 July 2014 . 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 conte nt of the requirements in this AD, please contact: AIRBUS

– Airworthiness Office

– EIAS; Fax +33 5 61 93 44 51; E

- mail: account.airworth

- eas@airbus.com

.