F2008L00725
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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
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Horizontal
Stabiliser Rear Spar Splice Fitting
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4/2008
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Applicability:
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All Model 1124 and 1124A aircraft, all
serial numbers.
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Requirement:
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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.
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Compliance:
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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.
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This Amendment becomes effective on 10
April 2008.
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Background:
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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.
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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.
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David Villiers
Delegate of the Civil Aviation Safety Authority
28 February 2008
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