Commonwealth legislation

AD/B767/159 Amdt 1 - Vertical Fin to Body Section 48 Attachment

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Commonwealth

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legislative instrument

Plain English Summary

6/10 complexity

This amendment requires inspections, earlier compliance, revised torque settings, and eventual replacement of vertical‑fin‑to‑body attachment nuts and bolts on specified Boeing 767‑200/‑300 aircraft. It follows FAA findings that corroded H‑11 steel barrel nuts fractured after inadequate sealant—weakening the fin attachment—and directs operators to follow FAA AD 2003‑10‑11 and Boeing service bulletins.

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Current sections

Direct links to the current provisions in AD/B767/159 Amdt 1 - Vertical Fin to Body Section 48 Attachment.

AD/B767/159 Amdt 1 - Vertical Fin to Body Section 48 Attachment

COMMONWEALTH OF AUSTRALIA (Civil Aviation Safety Regulations 1998), PART 39 - 105 CIVIL AVIATION SAFETY AUTHORITY

SCHEDULE OF AIRWORTHINESS DIRECTIVES

View image in the official source

AIRWORTHINESS DIRECTIVE

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For the reasons set out in the background section, the CASA delegate whose signature appears below revokes Airworthiness Directive (AD) AD/B767/159 and issues the following AD under subregulation 39.1 (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.

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Boeing 767 Series Aeroplanes

AD/B767/159

Amdt 1

Vertical Fin to Body Section 48 Attachment 9/2003

Applicability: Model 767-200 and -300 series aircraft, line numbers 1 through 574.

Requirement: Inspect in accordance with the technical requirements of FAA AD 2003-10-11 Amdt 39-13156.

Note: Boeing Service Bulletin (SB) 767-53-0085, SB 767-53A0085 Revision 1, SB 767-53A0085 Revision 2, and SB 767-53A0085 Revision 3 refer.

Compliance: As specified in the Requirement document, with a revised effective date of 4 September 2003.

This Amendment becomes effective on 4 September 2003.

Background: The FAA received several reports of corroded and/or broken vertical fin to body section 48 attachment barrel nuts on certain Model 767-200 and -300 aircraft. Further investigation revealed that the broken barrel nuts fractured due to stress corrosion cracks that started at corrosion pits. Examination of the vertical fin attachment bolts showed inadequate sealant on the bolt threads and shank. Reduced structural integrity of the vertical fin attachment joint could result in loss of the vertical fin and consequent loss of controllability of the aircraft.

Amendment 1 is issued in response to a new FAA AD which reduces compliance time for the inspections, changes the torque specification, and mandates eventual replacement of all H-11 steel alloy barrel nuts and bolts with Inconel nuts and bolts.

The original issue of this Airworthiness Directive became effective on 27 December 2001.

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

David Villiers

View image in the official sourceDelegate of the Civil Aviation Safety Authority 22 July 2003

The above AD is notified in the Commonwealth of Australia Gazette on 13 August 2003.

Page 1 of 1

Source text

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

1 AD/B767/159 Amdt 1 - Vertical Fin to Body Section 48 Attachment

COMMONWEALTH OF AUSTRALIA (Civil Aviation Safety Regulations 1998), PART 39 - 105 CIVIL AVIATION SAFETY AUTHORITY

SCHEDULE OF AIRWORTHINESS DIRECTIVES

AIRWORTHINESS DIRECTIVE

Boeing 767 Series Aeroplanes

AD/B767/159

Amdt 1

Vertical Fin to Body Section 48 Attachment 9/2003

Applicability: Model 767-200 and -300 series aircraft, line numbers 1 through 574.

Requirement: Inspect in accordance with the technical requirements of FAA AD 2003-10-11 Amdt 39-13156.

Note: Boeing Service Bulletin (SB) 767-53-0085, SB 767-53A0085 Revision 1, SB 767-53A0085 Revision 2, and SB 767-53A0085 Revision 3 refer.

Compliance: As specified in the Requirement document, with a revised effective date of 4 September 2003.

This Amendment becomes effective on 4 September 2003.

The original issue of this Airworthiness Directive became effective on 27 December 2001.