99-08-04: Flight Compartment Door

99-08-04 BOMBARDIER, INC. (Formerly de Havilland, Inc.): Amendment 39-11109. Docket 97-NM-04-AD. Applicability: Model DHC-8-100, -200, and -300 series airplanes having serial numbers 3 and subsequent; 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 prevent failure of the alternate release mechanism of the flight compartment door, which could delay or impede the evacuation of the flightcrew and passengers during an emergency, accomplish the following: (a) Within 90 days after the effective date of this AD, modify the lower hinge assembly and main door latch (Modification 8/2337) of the flight compartment door, in accordance with Bombardier Service Bulletin S.B. 8-52-39, Revision `D,' dated February 27, 1998. NOTE 2: Modification of the flight compartment door accomplished prior to the effective date of this AD in accordance with Bombardier Service Bulletin S.B. 8-52-39, dated August 30, 1996; Revision `A,' dated October 31, 1996; Revision `B,' dated July 4, 1997; or Revision `C,' dated September 1, 1997; is considered acceptable for compliance with the modification required by paragraph (a) of this AD. (b) Within 800 flight hours after accomplishment of the modification required by paragraph (a) of this AD, inspect the hinge areas around the hinge pin holes of the flight compartment door for wear, in accordance with Bombardier Service Bulletin S.B. 8-52-39, Revision `C,' dated September 1, 1997, or Revision `D,' dated February 27, 1998. (1) If no wear is detected, or if the wear is less than or equal to 0.020 inch in depth, repeat the inspection thereafter at intervals not to exceed 800 flight hours. (2) If any wear is detected and its dimension around the hinge pin holes is less than 0.050 inch and greater than 0.020 inch in depth, prior to further flight, perform the applicable corrective actions specified in the service bulletin. Repeat the inspection thereafter at intervals not to exceed 800 flight hours. (3) If any wear is detected and its dimension around the hinge pin holes is greater than or equal to 0.050 inch in depth, prior to further flight, replace the worn hinges with new hinges in accordance with the service bulletin. Repeat the inspection thereafter at intervals not to exceed 800 flight hours. Alternative Methods of Compliance (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, New York Aircraft Certification Office (ACO), FAA, Engine and Propeller Directorate. Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, New York ACO. NOTE 3: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the New York ACO. Special Flight Permits (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. Incorporation by Reference(e) The actions shall be done in accordance with Bombardier Service Bulletin S.B. 8-52-39, Revision `C,' dated September 1, 1997, and Bombardier Service Bulletin S.B. 8- 52-39, Revision `D,' dated February 27, 1998; as applicable. 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 Bombardier, Inc., Bombardier Regional Aircraft Division, Garratt Boulevard, Downsview, Ontario M3K 1Y5, Canada. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW, Renton, Washington; or at the FAA, Engine and Propeller Directorate, New York Aircraft Certification Office, 10 Fifth Street, Third Floor, Valley Stream, New York; 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 Canadian airworthiness directive CF- 96-20R2, dated July 16, 1997. (f) Thisamendment becomes effective on May 12, 1999.