Document ID: chunk:federal_register_of_legislation:F2005L02089:body:0:p2
Version: federal_register_of_legislation:F2005L02089
Segment Type: other
Provision Reference: 
Character Range: 3116–4751

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