Commonwealth legislation

AD/CESSNA 120/3 - Elevator Spar Web Hinges

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Commonwealth

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legislative instrument

Plain English Summary

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This AD requires owners/operators of Cessna 120 and 140 aircraft (serials 8001–13780) to inspect the elevator spar web at the hinge for fatigue cracks and to either fit reinforcing channels or replace the spar depending on crack length. (Applicability; Requirement.)

Compliance must occur within 100 flight hours or 12 months after 15 May 2003 and then every 100 hours until channels are fitted. Owners pay for inspections, parts and any spar replacement; CASA issued the directive under CASR subreg 39.1(1). (Compliance; first paragraph.)

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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 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.

Cessna 120 and 140 Series Aeroplanes

AD/CESSNA 120/3 Elevator Spar Web Hinges

AD/CESSNA 120/3 Elevator Spar Web Hinges 5/2003

Applicability: Model 120 and 140 aircraft, serial numbers 8001 through 13780.

Requirement: Inspect the elevator spar web at the hinges for fatigue cracks. The cracks start either at the rivets or at an edge of the fitting and progress around the fitting, until the elevator breaks loose from the hinge fitting.

If cracks are less than 0.5-inch in length, install a reinforcing channel, Cessna part number 0434151 (outboard hinge) or 0434152 (inboard hinge), on the aft side of the spar with the flanges riveted between the spar flanges and the skin with two

AN 455AD3 rivets per flange. Use four AN 442AD4 to attach each fitting to the spar web and reinforcing channel.

If cracks are more than 0.5-inch in length, replace the spar and add reinforcing channels.

Note: FAA AD 47-43-05 and Cessna Service Letter No.46 refer.

Compliance: Within 100 hours time in service or 12 months after 15 May 2003, whichever occurs first, and thereafter at intervals not to exceed 100 hours time in service; until reinforcing channels are ins talled at all hinge fittings.

This Airworthiness Directive becomes effective on 15 May 2003.

Background: The FAA requires inspections of the elevator spar webs for fatigue cracks.

View image in the official source

David Alan Villiers

Delegate of the Civil Aviation Safety Authority 4 April 2003

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 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.

Cessna 120 and 140 Series Aeroplanes

AD/CESSNA 120/3 Elevator Spar Web Hinges AD/CESSNA 120/3 Elevator Spar Web Hinges 5/2003

AD/CESSNA 120/3 Elevator Spar Web Hinges 5/2003

Applicability: Model 120 and 140 aircraft, serial numbers 8001 through 13780.

AN 455AD3 rivets per flange. Use four AN 442AD4 to attach each fitting to the spar web and reinforcing channel.

If cracks are more than 0.5-inch in length, replace the spar and add reinforcing channels.

Note: FAA AD 47-43-05 and Cessna Service Letter No.46 refer.

This Airworthiness Directive becomes effective on 15 May 2003.

Background: The FAA requires inspections of the elevator spar webs for fatigue cracks.

David Alan Villiers

Delegate of the Civil Aviation Safety Authority 4 April 2003