AD/CESSNA 120/3 - Elevator Spar Web Hinges (Cth)

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

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 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.