Commonwealth legislation

AD/B767/124 - Wing Front Spar Pitch Load Fittings

In ForceCTH

Jurisdiction

Commonwealth

Collection

legislative instrument

Plain English Summary

6/10 complexity

This AD requires Boeing 767 aircraft (line numbers 1–663) operators to inspect wing front‑spar pitch‑load fittings per FAA AD 2000‑12‑17 and Boeing Service Bulletin 767‑57‑0053 Rev 2 to detect fatigue cracks. Inspections are initial and repetitive from 7 September 2000; specified Boeing structural modifications end the inspection requirement.

Operators pay for inspections and any modifications; the CASA delegate enforces compliance and recognises the listed Boeing SBs as terminating action. The AD follows a structural fatigue analysis showing nacelle loads exceed the original design loads.

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Current sections

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AIRWORTHINESS DIRECTIVE

View image in the official source

View image in the official source
For the reasons set out in the background section, the CASA delegate whose signature appears below issues the following Airworthiness Directive (AD) under subregulation 39.1 (1) of CAR 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.

AD/B767/124 Wing Front Spar Pitch Load F

AD/B767/124 Wing Front Spar Pitch Load Fittings 9/2000

Applicability: Model 767 series aircraft, line numbers 1 through 663.

Requirement: Inspect in accordance with the technical requirements of FAA AD 2000-12-17 Amdt 39-11795.

Note: Boeing Service Bulletin 767-57-0053 Revision 2 refers.

Compliance: As specified in the Requirement document for the initial and repetitive inspection requirements, with a revised effective date of 7 September 2000.

Note: Modification of the nacelle strut and wing structure in accordance with Boeing Service Bulletin (SB) 767-54-0080, SB 767-54-0081, or SB 767-54-0082, as

applicable, and, accomplishment of the lug bore inspections and insurance cut of the pitch load fitting in accordance with SB 767-57-0053 Revision 2; constitutes terminating action for the inspection requirements of this Directive.

This Airworthiness Directive becomes effective on 7 September 2000.

Background: The FAA requires certain actions in response to a structural fatigue analysis that shows that the operational loads of the nacelle are higher than the loads used during the initial design of the Model 767 aircraft. The required actions are intended to detect and correct fatigue cracking in the pitch load fittings of the wing front spar.

Signature of David Villiers, Delegate of the Civil Aviation Safety Authority.

David Alan Villiers

Delegate of the Civil Aviation Safety Authority 14 July 2000

View image in the official source

The above AD is notified in the Commonwealth of Australia Gazette on 9 August 2000

Source text

Sourced from the Federal Register of Legislation (legislation.gov.au), CC BY 4.0.

AIRWORTHINESS DIRECTIVE AIRWORTHINESS DIRECTIVE

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 39.1 (1) of CAR 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.

AD/B767/124 Wing Front Spar Pitch Load F AD/B767/124 Wing Front Spar Pitch Load Fittings 9/2000

AD/B767/124 Wing Front Spar Pitch Load Fittings 9/2000

Applicability: Model 767 series aircraft, line numbers 1 through 663.

Requirement: Inspect in accordance with the technical requirements of FAA AD 2000-12-17 Amdt 39-11795.

Note: Boeing Service Bulletin 767-57-0053 Revision 2 refers.

Compliance: As specified in the Requirement document for the initial and repetitive inspection requirements, with a revised effective date of 7 September 2000.

Note: Modification of the nacelle strut and wing structure in accordance with Boeing Service Bulletin (SB) 767-54-0080, SB 767-54-0081, or SB 767-54-0082, as

This Airworthiness Directive becomes effective on 7 September 2000.

David Alan Villiers

Delegate of the Civil Aviation Safety Authority 14 July 2000

The above AD is notified in the Commonwealth of Australia Gazette on 9 August 2000