AD 95-08-07 Airworthiness Directives; Airbus Model A310 Series Airplanes

Models named: A310 series. Read the applicability below — it usually turns on serial or part numbers too.

All Model A310 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 use the authority provided in paragraph (e) to request approval from the FAA. This approval may address either no action, if the current configuration eliminates the unsafe condition; or different actions necessary to address the unsafe condition described in this AD. Such a request should include an assessment of the effect of the changed configuration on the unsafe condition addressed by this AD. In no case does the presence of any modification, alteration, or repair remove any airplane from the applicability of this AD.

Required as indicated, unless accomplished previously. To prevent impeding evacuation during an emergency due to seized bearings on the lower shaft of the mechanism inside the emergency exit door, which would make the door control handle difficult to lift, accomplish the following: (a) Within 60 days after the effective date of this AD, measure the amount of force required to move the interior control handle of the emergency exit doors to, in accordance with Airbus All Operators Telex (AOT) 52 08, Revision 1, dated December 1, 1994. (b) If the force required to move the interior control handle of the door is equal to or does not exceed 20 daN (45 foot-pounds), no further action is required by this paragraph for that door. (c) If the force required to move the interior control handle of the door exceeds 20 daN (45 foot-pounds), prior to further flight, perform a full functional test of the emergency exit doors to measure the amount of force required to open the doors, in accordance with the AOT. (1) If the force required to open the door is equal to or does not exceed 20 daN (45 foot-pounds), no further action is required by this paragraph for that door. (2) If the force required to open the door exceeds 20 daN (45 foot-pounds), prior to further flight, perform a visual inspection to detect discrepancies of the mechanism inside the door, in accordance with the AOT. (i) If no discrepancy is found, prior to further flight, replace seized bearings with new or serviceable bearings, in accordance with the AOT. (ii) If any discrepancy is found, prior to further flight, repair the discrepancy in accordance with a method approved by the Manager, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate. (d) Within 10 days after accomplishing the inspection required by paragraph (a) of this AD, submit a report of the findings of discrepancies to the Airbus Industrie, Engineering Services, Attention: Mr. R. Filaquier, AI/SE E121, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France. Information collection requirements contained in this regulation have been approved by the Office of Management and Budget (OMB) under the provisions of the Paperwork Reduction Act of 1980 (44 U.S.C. 3501 et seq) and have been assigned OMB Control Number 2120-0056. (e) 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. Operators shall submit their requests through [[Page 19157]] an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, Standardization Branch, ANM-113. Note 2: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Standardization Branch, ANM-113. (f) Special flight permits may be issued for non-revenue bearing flights in accordance with Secs. 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. (g) The measurements, functional test, inspections, and replacement shall be done in accordance with Airbus All Operators Telex 52 08, Revision 1, dated December 1, 1994. This incorporation by reference was approved by the Director of the Federal Register 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. (h) This amendment becomes effective on May 2, 1995. Issued in Renton, Washington, on April 5, 1995. S.R. Miller, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 95-8822 Filed 4-14-95; 8:45 am] BILLING CODE 4910-13-U