97-22-06 AIRBUS INDUSTRIE: Amendment 39-10177. Docket 96-NM-155-AD.
Applicability: All Model Airbus Model A300, A310, and A300-600 series airplanes, certificated in any category.
NOTE 1: This AD applies to each airplane identified in the preceding applicability provision, regardless of whether it has been modified, altered, or repaired in the area subject to the requirements of this AD. For airplanes that have been modified, altered, or repaired so that the performance of the requirements of this AD is affected, the owner/operator must request approval for an alternative method of compliance in accordance with paragraph (c) of this AD. The request should include an assessment of the effect of the modification, alteration, or repair on the unsafe condition addressed by this AD; and, if the unsafe condition has not been eliminated, the request should include specific proposed actions to address it.
Compliance: Required as indicated, unless accomplished previously.To detect and correct corrosion of the ram air turbine (RAT) uplock pin/shaft and needle that could result in failure of the RAT to deploy and subsequent loss of emergency hydraulic power to the flight controls in the event that power is lost in both engines, accomplish the following:
(a) Prior to the accumulation of 30 months since the date of manufacture, or within 3 months after the effective date of this AD, whichever occurs later: Accomplish the requirements of paragraphs (a)(1) and (a)(2) of this AD in accordance with Airbus Service Bulletin A300-29-0108, dated April 1, 1996 (for Model A300 series airplanes); A310-29-2076, dated April 1, 1996 (for Model A310 series airplanes); or A300-29-6037, dated April 1, 1996 (for Model A300-600 series airplanes); as applicable. Thereafter, repeat these actions at intervals not to exceed 30 months.
(1) Perform a RAT extension test on the ground, in accordance with the procedures specified in the Maintenance Manual.
(2) Disassemble and remove the uplock mechanism of the RAT and perform a visual inspection of the uplock mechanism to detect corrosion, in accordance with the applicable service bulletin.
NOTE 2: For the purposes of this AD, the RAT uplock mechanism includes both the lever assembly and uplock unit.
(i) If no corrosion is detected: Prior to further flight, clean and lubricate the uplock mechanism and its associated parts, reinstall the assembly, and perform a retraction/extension/retraction of the RAT, in accordance with the applicable service bulletin.
(ii) If any corrosion is detected in any part of the uplock mechanism, prior to further flight, accomplish either paragraph (a)(2)(ii)(A) or (a)(2)(ii)(B) of this AD in accordance with the applicable service bulletin.
(A) Replace the uplock mechanism with a new part and perform a retraction/extension/retraction of the RAT, in accordance with the applicable service bulletin. Or
(B) Clean and lubricate the uplock mechanism and its associated parts. Within 30 days following accomplishment of this cleaning and lubrication, replace the uplock mechanism with a new part and perform a retraction/extension/retraction of the RAT.
(b) Initial accomplishment of the actions required by paragraph (a) of this AD that have been performed in accordance with Airbus All Operator Telex (AOT) 29-16, Revision 01, dated January 10, 1996, is considered acceptable for compliance with the initial RAT extension test and an initial visual inspection as required by paragraph (a) of this AD. However, the first repetitive inspection, as required by paragraph (a) of this AD, must be performed within 30 months after that RAT extension test and visual inspection were conducted, and repeated thereafter at intervals not to exceed 30 months.
(c) An alternative method of compliance or adjustment of the compliance time that provides an acceptable level of safety may be used if approved by the Manager, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate. Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, Standardization Branch, ANM-113.
NOTE 3: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Standardization Branch, ANM-113.
(d) Special flight permits may be issued in accordance with sections 21.197 and 21.199 of the Federal Aviation Regulations (14 CFR 21.197 and 21.199) to operate the airplane to a location where the requirements of this AD can be accomplished.
(e) The actions shall be done in accordance with Airbus Service Bulletin A300-29- 0108, dated April 1, 1996; Airbus Service Bulletin A310-29-2076, dated April 1, 1996; or Airbus Service Bulletin A300-29-6037, dated April 1, 1996; as applicable. This incorporation by reference was approved by the Director of the FederalRegister in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Copies may be obtained from Airbus Industrie, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC.
NOTE 4: The subject of this AD is addressed in French airworthiness directive 95-163-182 (B) R2, dated June 5, 1996.
(f) This amendment becomes effective on December 2, 1997.