Commonwealth legislation

AD/B737/155 - Elevator Hinge Plates

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Jurisdiction

Commonwealth

Collection

legislative instrument

Plain English Summary

3/10 complexity

This Airworthiness Directive requires operators of Boeing 737-600, -700 and -800 aircraft (line numbers 1–84) to inspect elevator hinge plates per FAA AD 2001-06-08 and Boeing Service Bulletin 737-55-1067. Inspections must be done before 7,000 total flight cycles or within 90 days of 9 August 2001, then every 4,000 cycles until an optional terminating modification is carried out. It addresses reported fatigue cracking that could detach the elevator; operators bear the inspection, maintenance and modification costs and scheduling burden.

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Current sections

Direct links to the current provisions in AD/B737/155 - Elevator Hinge Plates.

AIRWORTHINESS DIRECTIVE

View image in the official source

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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.

Boeing 737 Series Aeroplanes

AD/B737/155 Elevator Hinge Plates 8/2001

Applicability: Model 737-600, -700, and -800 series aircraft, with line numbers 1 through 84. Requirement: Action in accordance with the technical requirements of FAA AD 2001-06-08 Amdt

39-12155.

Note: Boeing Service Bulletin 737-55-1067 refers.

Compliance: Before the accumulation of 7,000 total flight cycles or within 90 days after 9 August 2001, whichever occurs later; thereafter at intervals not to exceed 4,000 flight cycles, until accomplishment of optional terminating action specified in Part II of Boeing Service Bulletin 737-55-1067.

This Airworthiness Directive becomes effective on 9 August 2001.

Background: Fatigue cracking of the elevator hinge plates has been reported. Such cracking could lead to loss of attachment of the elevator to the horizontal stabiliser, and consequent reduced controllability of the aircraft.

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

David Alan Villiers

Delegate of the Civil Aviation Safety Authority 26 June 2001

View image in the official source

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.

Boeing 737 Series Aeroplanes