Document ID: chunk:federal_register_of_legislation:F2006B06442:body:0
Version: federal_register_of_legislation:F2006B06442
Segment Type: other
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COMMONWEALTH OF AUSTRALIA (Civil Aviation Regulations 1998), PART 39 - 105 CIVIL AVIATION SAFETY AUTHORITY
 SCHEDULE OF AIRWORTHINESS DIRECTIVES

 Robinson R22 Series Helicopters

 AD/R22/38
 Amdt 1

 Tail Rotor Gearbox Output Shaft Key 2/96

            Applicability: All R22 helicopters fitted with a tail rotor gearbox that was overhauled or manufactured by Robinson Helicopter Company prior to 8 June 1992.

            FAA AD 95-23-05 lists gearbox serial numbers that are exempt from the requirements of this AD.

            Note: Copies of FAA AD 95-23-05 are available from CASA Airworthiness District Offices.

             Requirement: 1. Unless previously accomplished in accordance with the requirements of the original issue of AD/R22/38, install alignment dots in accordance with the technical requirements of paragraph (a) of FAA AD 95-23-05.

2.    Inspect for misalignment of the "alignment dots" in accordance with the technical requirements of paragraph (b) of FAA AD 95-23-05.

3.    Verify the existence of both the input and output shaft keys in accordance with the technical requirements of paragraph (c) of FAA AD 95-23-05. This is terminating action for the daily preflight checks in Requirement 2.

            Note: FAA AD 95-23-05 supersedes FAA AD 94-17-07.

 Compliance: Effective date 1 February 1995;

              1. Unless previously accomplished, before further flight.

             2.    Prior to the first flight of each day.

            Note: The Pilot in Command may carry out and certify in the Maintenance Release for the daily preflight checks required by this Directive as part of the daily preflight inspection.

3.    Within the next 100 hours time in service (TIS) after the effective date of this Directive or at the next annual inspection, whichever occurs first.

            Background: The manufacturer has received reports of two tail rotor gearboxes which were assembled without the key required to prevent the output gear from rotating on the output shaft. In one case the slippage occurred on the ground while in the other case a forced landing, which damaged the helicopter, resulted.

            This amendment requires the additional action to disassemble the tail rotor gear box assembly in order to verify the installation of the key.