Document ID: chunk:federal_register_of_legislation:F2017L00910:body:0
Version: federal_register_of_legislation:F2017L00910
Segment Type: other
Provision Reference: 
Character Range: 0–2536

AIRWORTHINESS DIRECTIVE
On the commencement date specified below, and for the reasons set out in the background section, the CASA delegate whose signature appears below repeals Airworthiness Directive (AD) AD/CFM56/15 Amdt 1 and issues the following AD under subregulation 39.001 (1) of CASR 1998 and subsection 33 (3) of the Acts Interpretation Act 1901. The AD requires that the action set out in the requirement section (being action that the delegate considers necessary to correct an 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.

CFM International Turbine Engines - CFM56 Series
AD/CFM56/15 Amdt 2  Fuel Filter Cover Attachment Inspection  14/2017

Applicability:  CFM International (CFMI) CFM56-3, -3B & -3C engines.
Requirement:       1. Inspect fuel filter cover attachment hardware in accordance with CFMI Service Bulletin CFM56-3 73-126 Revision 1 as in force at the time of issue of this AD.
                   2. Modify the engine driven fuel pump to provide improved filter cover retention in accordance with CFMI Service Bulletin CFM 56-3 73-A129 as in force at the time of issue of this AD.
                Note 1:  DGAC 1999-245(B)R1 also refers.
                Note 2: Compliance with Requirement 2 constitutes terminating action for this AD.
Compliance:        1. Unless previously accomplished, no later than the next A check after the effective date of this AD.
                   2. No later than the date of commencement of this AD.
                Note 3:  Compliance with both requirements in AD/CFM56/15 Amdt 1 constitutes compliance with this AD.
                This AD commences on 19 July 2017.
Background:     The fuel filter cover is secured with six bolts torqued in helicoil inserts. Loose inserts have been discovered in two aircraft which have resulted in heavy fuel loss in flight.
                The original issue of this AD became effective on 7 October 1999.
                Amendment 1 of this AD required modification of the engine driven pump to provide an improved fuel filter cover retention design.
                Amendment 2 of this AD is issued to correct a minor typographical error in the DGAC AD number referenced in Note 1 of this AD.

Ben Wilson
Delegate of the Civil Aviation Safety Authority
7 July 2017