Document ID: chunk:federal_register_of_legislation:F2008L00725:body:0
Version: federal_register_of_legislation:F2008L00725
Segment Type: other
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Character Range: 0–2723

AIRWORTHINESS DIRECTIVE
On the effective date specified below, and for the reasons set out in the background section, the CASA delegate whose signature appears below revokes Airworthiness Directive (AD) AD/IAI-W/9 Amdt 2 and issues the following 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.

Israel Aircraft Industries 1123 and 1124 (Westwind) Series Aeroplanes
AD/IAI-W/9 Amdt 3  Horizontal Stabiliser Rear Spar Splice Fitting  4/2008

Applicability:  All Model 1124 and 1124A aircraft, all serial numbers.
Requirement:       1. Inspect in accordance with Israel Aircraft Industries Service Bulletin (SB)
                   1124-55-020 Revision 2, or later Israel CAA approved revision.

                   2. If no cracking is evident, repeat the inspection.

                If cracks are detected, before further flight, replace the splice fitting with a serviceable fitting in accordance with SB 1124-55-021 Revision 3, or later Israel CAA approved revision.

                Note 1:  Incorporation of a Titanium Splice Fitting part number WW4453005-509 (MOD AFC2081) in accordance with the Aircraft Maintenance Manual (AMM) constitutes terminating action for the requirements of this Directive.  The considerably longer inspection interval for modified aircraft is included in Chapter 5 of the AMM.

                Note 2:  Israel CAA AD 85-001 R3 refers.
Compliance:        1. Within 75 flight hours after 10 April 2008, unless inspected within the last 225 flight hours since compliance with the previous issue of this Directive.

                   2. Inspect at intervals not to exceed 300 flight hours; until a titanium splice fitting (MOD AFC2081) is installed.
                This Amendment becomes effective on 10 April 2008.
Background:     Cracks have been found in the splice fitting (hinge assembly) P/N 453005-501 on several aircraft.

                Amendment 2 reduced the inspection interval from 600 to 300 flight hours.

   Amendment 3 is issued in response to a revision of the related CAA AD, which introduces a strengthened aft spar splice fitting made of titanium.  There is no additional work required by this issue of the Directive.

David Villiers
Delegate of the Civil Aviation Safety Authority

28 February 2008