Commonwealth legislation

AD/R22/29 - Main Rotor Pitch Link

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legislative instrument

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This Airworthiness Directive requires owners/operators of certain Robinson R22 helicopters (S/N 0580–0644, and R22s overhauled/repaired or fitted with A258-1/‑2/‑3 parts from RHC between 15 Aug 1986 and 7 May 1987) to inspect main rotor pitch links for cracks before the next flight after 16 June 1987 and to replace affected fittings per RHC Service Bulletin No.57.

Operators bear inspection and replacement costs; CASA mandates compliance and the RHC bulletin prescribes the method. Pilots may perform and must certify inspections; any crack found requires replacement before further flight.

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AD/R22/29 - Main Rotor Pitch Link

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

SCHEDULE OF AIRWORTHINESS DIRECTIVES

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Robinson R22 Series Helicopters

AD/R22/29 Main Rotor Pitch Link 8/87 TX

Applicability: All R22 helicopters S/N 0580 through S/N 0644. All R22 helicopters overhauled or repaired at RHC completed between 15 August 1986 and 7 May 1987. R22 helicopters fitted with pitch link parts A258-1 -2, or -3, received from RHC between 15 August 1986 and 7 May 1987.

Requirement: 1. Inspect main rotor pitch links for cracks in accordance with Part A of RHC S.B. No. 57.

Replace fittings in accordance with Part B of RHC S.B. No. 57.

Compliance: 1. Prior to next flight after 16 June 1987, and each flight thereafter until Part B is accomplished.

Note 1. If cracks are found, perform Part B of RHC S.B. No. 57 prior to any further flight.

Note 2. This inspection may be accomplished by the pilot in command in which case he shall enter and certify for this A.D. in col. 2 part 3 of the Maintenance Release on each occasion.

Within the next 10 flight hours or by 15 July 1987 whichever occurs first.

Background: Flaws have been found in the material used during a production run of the A258-2 and A258-3 pitch link components. These flaws produce lengthwise cracks in the parts and, if allowed to progress, these cracks could lead to failure of the pitch link and loss of control of the helicopter.

Source text

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

1 AD/R22/29 - Main Rotor Pitch Link