EASA AD No : 2011-0155

EASA Form 110 Page 1/3 

## EASA AIRWORTHINESS DIRECTIVE

AD No.: 2011-0155

Date: 25 August 2011

Note: This Airworthiness Directive (AD) is issued b y EASA, acting in accordance with Regulation (EC) No 216/2008 on behalf of the European Communit y, its Member States and of the European third countries that participate in the ac tivities of EASA under Article 66 of that Regulation.

This AD is issued in accordance with EC 1702/2003, Part 21A.3B. In accordance with EC 2042/2003 Annex I, Part M.A.301, the continuing airworthiness of an aircraft shall be en sured by accomplishing any applicable ADs. Conseque ntly, no person may operate an aircraft to which an AD applies, except in accordan ce with the requirements of that AD, unless otherwi se 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, A rticle 14(4) exemption]. 

### Type Approval Holder’s Name:
AIRBUS Type/Model designation(s): A318, A319, A320 and A321 aeroplanes

TCDS Number: EASA.A.064

Foreign AD: Not applicable

Supersedure: This AD supersedes EASA AD 2006-0203 d ated 11 July 2006.



### ATA 05 Time Limits and Maintenance Checks

– Fuel Airworthiness Limitations – ALS Part 5 – Amendment

Manufacturer(s): Airbus (formerly Airbus Industrie)

Applicability: Airbus A318-111, A318-112, A318-121, A318-122, A319-111, A319-112, A319-113, A319-114, A319-115, A319-131, A319-132, A 319-133, A320-111, A320-211, A320-212, A320-214, A320-215, A320-216, A 320-231, A320-232, A320-233, A321-111, A321-112, A321-131, A321-211, A 321-212, A321-213, A321-231 and A321-232 aeroplane models, all manufac turer serial numbers

Reason: The airworthiness limitations are currently published in the Airbus A318/A319/ A320/A321 Airworthiness Limitations Section (ALS). The Fuel Airworthiness Limitations (FAL) are specif ied in Airbus A318/A319/ A320/A321 FAL Document reference 95A.1931/05, which is approved by the European Aviation Safety Agency (EASA) and referenc ed in the Airbus A318/ A319/A320/A321 ALS Part 5. The issue 4 of Airbus A318/A319/A320/A321 FAL Docum ent introduces more restrictive maintenance requirements and/or airwort hiness limitations. Failure to comply with these more restrictive maintenance r equirements and airworthiness limitations contained in this documen t constitutes an unsafe condition. This AD retains the requirement of EASA AD 2006-020 3, which is superseded, and requires the implementation of the new or more restrictive maintenance requirements and/or airworthiness limitations as sp ecified in Airbus A318/A319/A320/A321 FAL Document issue 4.

Effective Date: 08 September 2011EASA AD No : 2011-0155

EASA Form 110 Page 2/3 Required Action(s) and Compliance Time(s): Required as indicated, unless previously accomplish ed: (1) Re-statement of the requirements of EASA AD 2006-02 03 : Within 3 months after 19 July 2006 [the effective date of AD 2006-0203], comply with all applicable maintenance requirements and associated airworthiness limitations included in Airbus A318/A 319/A320/A321 FAL Document reference 95A.1931/05 at issue 1. For aeroplanes whose first flight occurred before 19 July 2006 [the effective date of EASA AD 2006-0203], the first acc omplishment of tasks 281800-01-1 and 281800-02-1 must be performed withi n 72 months after 19 July 2006 [the effective date of EASA AD 2006-02 03].
Note 1 : The use of later approved issues of Airbus A318/A 319/A320/A321 FAL Document reference 95A.1931/05 is acceptable fo r compliance with the requirements of paragraph (1) of this AD. (2) Within 6 months after the effective date of thi s AD, comply with all applicable maintenance requirements and associated airworthiness limitations included in Airbus A318/A319/A320/A321 FAL Document reference 95A.1931/05 at issue 4, except for the li fe limitation and associated replacement requirement for the ASM iden tified by P/N in Table 1 of this AD.
Note 2 : Refer to paragraph (3.3) of this AD for the life limitation and associated replacement requirement for the ASM. (3) Specific tasks and compliance times : (3.1) For aeroplanes whose first flight occurred be fore 19 July 2006 [the effective date of EASA AD 2006-0203], the first acc omplishment of tasks 281800-01-1 and 281800-02-1 must be performed no later than 18 July 2012. (3.2) Depending on aeroplane configuration, the fir st accomplishment of tasks 470000-01-1, 470000-02-1, 470000-03-1, 470000 -04-1 and 470000-05-1, must be calculated, either: (3.2.1) From the aeroplane first flight for aeropla nes on which Airbus modification 38062 or 38195 has been embodie d in production, or (3.2.2) From the in-service installation of the Fue l Tank Inerting System in accordance with the instructions of Airbu s SB A320-47-1001, or SB A320-47-1002, or SB A320-47-100 3, or SB A320-47-1004, or SB A320-47-1006, or SB A320-47-1007. (3.2.3) Although Airbus A318/A319/A320/A321 FAL Doc ument reference 95A.1931/05 issue 4 does not refer to the SB A320-47-1006 and SB A320-47-1007, the tasks apply a s follows: Tasks 470000-01-1 and 470000-02-1 apply to aeroplan es in post-SB A320-47-1007 configuration, Task 470000-03-1 applies to aeroplanes in post-SB A 320- 47-1006 and pre-SB A320-47-1007 configuration, Task 470000-04-1 applies to aeroplanes in post-modi fication 38195 and pre-SB A320-47-1007 configuration, Task 470000-05-1 applies to aeroplanes in post-SB A 320- 47-1007 and pre-modification 151529 (SB A320-47-100 5) configuration. (3.3) Replace each ASM, as specified in Table 1 of this AD, upon reaching the 27 000 flight hours (FH) life limitation (compo nent time), with aEASA AD No : 2011-0155

EASA Form 110 Page 3/3 serviceable ASM.
Table 1 ASM P/N Affected Aeroplane Configuration
P/N 2060017-101 Post-modification 38062, or Post-SB A320-47-1002, or Post-SB A320-47-1004, or Post-SB A320-47-1007
P/N 2060017-102 Post-modification 152033, or Post-SB A320-47-1011

(4) Compliance with the requirements of paragraph ( 2) of this AD can be demonstrated by: (4.1) Revising, unless accomplished previously, the approved Aircraft Maintenance Programme from which the Operator or th e Owner ensures the continuing airworthiness of each operat ed aeroplane, as follows: Incorporate all maintenance requirements and assoc iated airworthiness limitations specified in paragraph (2 ) of this AD,
and (4.2) Complying with the approved Aircraft Maintena nce Programme described in paragraph (4.1) of this AD.
Note 3 : For aeroplanes maintained, modified, altered and/ or repaired in accordance with Instructions for Continued Airworth iness (ICA) published by Airbus, there are no parallel required actions t o update those ICA. These documents include all information necessary t o help the Operator/Owner to demonstrate compliance with the r equirements of this AD. For other aeroplanes, operators/owners may not be able to demonstrate compliance with the requirements of thi s AD. In such cases, the operator/owner must seek guidance from the Nati onal Authority of the State of Registry of the aeroplane.

Ref. Publications: AIRBUS A318/A319/A320/A321 FAL D ocument reference 95A.1931/05 issue 4, approved by EASA on 26 August 2010. The use of later approved variations or revisions o f this document is acceptable for compliance with the requirements of this AD.

Remarks: 1. If requested and appropriately substantiated, EA SA can approve Alternative Methods of Compliance for this AD. 2. This AD was posted on 11 May 2011 as PAD 11-050 for consultation until 08 June 2011 and republished as PAD 11-050R1 on 21 July 2011 and officially closed for comments on 04 August 2011. T he Comment Response Document can be found at http://ad.easa.europa.eu/

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

. 4. For any question concerning the technical conten t of the requirements in this AD, please contact: AIRBUS – Airworthiness Off ice – EIAZA; E-mail: als@airbus.com

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