Commonwealth legislation

AD/B717/8 - Upper Centre Fuselage Longerons

In ForceCTH

Jurisdiction

Commonwealth

Collection

legislative instrument

Plain English Summary

3/10 complexity

This AD requires owners/operators of Boeing 717-200 aeroplanes with fuselage numbers 5001–5056 to modify the upper centre fuselage longeron-to-frame installation (including fabricating and fitting support angles and doublers) in accordance with Boeing Service Bulletin 717-53-0001. The Commonwealth delegate issued the directive under subregulation 39.1(1) of CASR 1998 to address FAA-identified risk of fatigue cracking that could reduce fuselage structural integrity. Operators must comply before 30,000 total flight cycles or within 10 years after 7 August 2003, whichever is earlier.

JSON API

Deep dive

Want the full deep dive?

Zoe can write the in-depth analysis on top of the summary above: how it works, who it affects and what each part actually does.

Current sections

Direct links to the current provisions in AD/B717/8 - Upper Centre Fuselage Longerons.

AIRWORTHINESS DIRECTIVE

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 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.

View image in the official source

Boeing 717 Series Aeroplanes

AD/B717/8 Upper Centre Fuselage Longeron

AD/B717/8 Upper Centre Fuselage Longerons 8/2003

Applicability: Model 717-200 aircraft, manufacturer’s fuselage numbers 5001 through 5056.

Requirement: Modify the longeron to frame installation of the upper centre fuselage between stations Y=655.000 and Y=813.000, at longerons L-5L to L-5R (includes fabrication of the angles and installation of support angles and doublers) in accordance with Boeing Service Bulletin 717-53-0001, dated 20 March 2001.

Note: FAA AD 2003-10-08 Amdt 39-13153 refers.

Compliance: Before the accumulation of 30,000 total flight cycles or within 10 years after 7 August 2003, whichever occurs first.

This Airworthiness Directive becomes effective on 7 August 2003.

Background: The FAA requires certain actions to prevent fatigue cracking of the longerons of the upper centre fuselage. Such cracking could result in reduced structural integrity of the fuselage.

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

David Punshon

Delegate of the Civil Aviation Safety Authority 26 June 2003

View image in the official source

The above AD is notified in the Commonwealth of Australia Gazette on 16 July 2003.

Source text

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

AIRWORTHINESS DIRECTIVE AIRWORTHINESS DIRECTIVE

AIRWORTHINESS DIRECTIVE

Boeing 717 Series Aeroplanes

AD/B717/8 Upper Centre Fuselage Longeron AD/B717/8 Upper Centre Fuselage Longerons 8/2003

AD/B717/8 Upper Centre Fuselage Longerons 8/2003

Applicability: Model 717-200 aircraft, manufacturer’s fuselage numbers 5001 through 5056.

Note: FAA AD 2003-10-08 Amdt 39-13153 refers.

Compliance: Before the accumulation of 30,000 total flight cycles or within 10 years after 7 August 2003, whichever occurs first.

This Airworthiness Directive becomes effective on 7 August 2003.

Background: The FAA requires certain actions to prevent fatigue cracking of the longerons of the upper centre fuselage. Such cracking could result in reduced structural integrity of the fuselage.

David Punshon

Delegate of the Civil Aviation Safety Authority 26 June 2003

The above AD is notified in the Commonwealth of Australia Gazette on 16 July 2003.