AD/A320/181 Engine Forward Bolt Mount (Cth)

AIRWORTHINESS DIRECTIVE

For the reasons set out in the background section, the CASA delegate whose signature appears below issues the following Airworthiness Directive (AD) under subregulation 39.001(1) of CASR 1998.  The AD requires that the action set out in the requirement section (being action that the delegate considers necessary to correct the unsafe condition) be taken in relation to the aircraft or aeronautical product mentioned in the applicability section: (a) in the circumstances mentioned in the requirement section; and (b) in accordance with the instructions set out in the requirement section; and (c) at the time mentioned in the compliance section.

Airbus Industrie A319, A320 and A321 Series Aeroplanes

AD/A320/181 Engine - Forward Bolt Mount 9/2005

Applicability:

Airbus A319-131, A319-132, A319-133, A320-232, A320-233, A321-131, A321-231 and A321-232 aircraft models, all aircraft serial numbers that are powered by IAE V2500 series engine with the following engine serial numbers:

V10002, V10008, V10009, V10010, V10012, V10013, V10015, V10017, V10019, V10020, V10021, V10023, V10024, V10025, V10027, V10030, V10031, V10032, V10034, V10043, V10044, V10045, V10046, V10048, V10049, V10050, V10051, V10056, V10057, V10058, V10059, V10060, V10063, V10064, V10065, V10066, V10068, V10070, V10072, V10073, V10074, V10076, V10077, V10078, V10081, V10082, V10083, V10085, V10086, V10087, V10090, V10091, V10092, V10094, V10095, V10097, V10098, V10099, V10105, V10106, V10108, V10109, V10110, V10115, V10129, V10133, V10140, V10143, V10144, V10146, V10150, V10153, V10157, V10158, V10159, V10162, V10163, V10165, V10167, V10170, V10171, V10182, V10183, V10189, V10191, V10197, V10212, V10213, V10214, V10215, V10217, V10218, V10222, V10224, V10225, V10226, V10227, V10232, V10233, V10239, V10244, V10248, V10280, V10281, V10288, V10289, V10291, V10292, V10302, V10304, V10305, V10306, V10308, V10311, V10316, V10317, V10319, V10323, V10327, V10333, V10345, V10350, V10351, V10353, V10354, V10357, V10358, V10359, V10365, V10367, V10368, V10372, V10373, V10374, V10376, V10377, V10378, V10388, V10390, V10394, V10395, V10402, V10406, V10409, V10419, V10428, V10444, V10484, V10511, V10545, V10592, V10602, V10640, V10707, V10740, V10747, V10769, V10770, V10842, V10847, V10989, V11111, V11116, V11162, V11181, V11185, V11262, V11307, V11311, V11345, V11346, V11437, V11438,

V10022, V10029, V10038, V10041, V10047, V10052, V10053, V10054, V10062, V10067, V10069, V10071, V10075, V10088, V10089, V10104, V10121, V10131, V10133, V10135, V10137, V10138, V10139, V10141, V10142, V10164, V10166, V10186, V10206, V10238, V10240, V10245, V10246, V10283, V10414, V10416, V10443, V10479, V10522, V10598, V10599, V10664, V10665, V10684, V10709, V10755, V10765, V10796.

Requirement:

1.    Perform a detailed inspection of the forward engine mount primary load path components and apply all necessary corrective actions in accordance with Airbus All Operator Telex (AOT) A320-71A1036 revision 1.  Accomplishment of A320 MPD check reference 712111-03 or engine shop visit are equivalent if already done within less than 2250 flight cycles before the effective date of this AD.

2.    Remove and reinstall the bolts attaching the engine forward mount to the engine, in accordance, with AOT A320-71A1036 revision 1.

Note:  DGAC AD UF-2005-117 and Airbus AOT A320-71A1036 revision 1 refers.

Compliance:

1.    a.     For aircraft powered by V2530-A5 or V2533-A5 engines - within 5 days from the effective date of this Directive.

b.    For aircraft powered by V2522-A5, V2524-A5 or V2527-A5 engines - within 10 days from the effective date of this Directive.

2.    Within 2250 flight cycles from accomplishment of detailed inspection as specified in paragraph 1 of this Directive, or during the next engine shop visit, whichever occurs first.

This Airworthiness Directive becomes effective on 1 September 2005.

Background:

An engine shop has confessed that during incorporation of Airbus Service Bulletin A320-71-1021, mandated by Airworthiness Directive (AD) 98-293-118(B), they have been applying an incorrect torque to the bolts Part Number 275B0307-7H attaching the engine forward mount to the engine.  The effect of the lower torque values used on the bolts is a reduction in fatigue life.  The bolts are part of a secondary thrust load path that is only active upon failure of the primary thrust load path.  The aim of this AD is to check the integrity of the primary load path and to re-install the forward mount bolts with correct torque level.

David Villiers
Delegate of the Civil Aviation Safety Authority

20 July 2005