AD/A320/224 - Hydraulic Power - Ram Air Turbine Georotor Pump

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 39.001(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. Airbus Industrie A319, A320 and A321 Series Aeroplanes AD/A320/224 Hydraulic Power - Ram Air Turbine Georotor Pump 7/2008 Applicability: AIRBUS A318, A319, A320 and A321 aircraft, equipped with HAMILTON SUNDSTRAND (formerly DOWTY) Ram Air Turbine (RAT) Part Number (P/N) 680203037 with a Serial Number (S/N) between 0101 and 0354 inclusive. Aircraft having received AIRBUS modification 27189 in production or AIRBUS Service Bulletin (SB) A320-29-1100 in service, and without having received AIRBUS modification 28413 in production, are not affected by the requirements of this AD. Requirement: 1. Identify the P/N and S/N of the RAT in accordance with AIRBUS SB A320-29-1122 or later NAA Approved revision. 2. If the S/N is included in the affected batch, replace the gerotor pump assembly, re-identify the RAT and report to Airbus. 3. If the S/N is not included in the affected batch, no further action is required. Note: EASA AD 2008-0034 dated 21 February 2008 refers. Compliance: Before 31 May 2009 unless previously accomplished. This Airworthiness Directive becomes effective on 3 July 2008. Background: In-service experience has shown that a fracture of the gerotor pump of the A320 RAT may occur. This may lead to the non-operation of the RAT in case of an in-flight deployment. The Non-Deployment or Non-Pressurization of the RAT, associated with a double engine failure or a total loss of normal electrical power generation constitutes an unsafe condition. This AD mandates the replacement of the affected gerotor pump assembly, which will provide the required im proved reliability of the RAT. The implementation of this modification was originally managed by an AIRBUS monitoring campaign. However the rate of installation of the modification by operators has not met the predicated target. As such and to ensure continued compliance with the certification requirements it is considered necessary to require compliance by use of AD. James Coyne Delegate of the Civil Aviation Safety Authority 22 May 2008