2007-01-11: Flight compartment door

2007-01-11 Bombardier, Inc. (Formerly de Havilland, Inc.): Amendment 39-14883. Docket No. FAA-2006-25904; Directorate Identifier 2006-NM- 077-AD. Effective Date (a) This AD becomes effective March 5, 2007. Affected ADs (b) This AD supersedes AD 99-08-04. Applicability (c) This AD applies to Bombardier Model DHC-8-100, -200 and -300 series airplanes, certificated in any category; equipped with a flight compartment door installation having part number (P/N) 82510074-(*), 82510294-(*), 82510310-001, 8Z4597-001, H85250010-(*), 82510700-(*), or 82510704-(*); except P/Ns 82510704-502 and 82510704-503. Note 1: (*) denotes all dash numbers. Unsafe Condition (d) This AD results from a determination that certain cockpit doors are no longer subject to the existing requirements. We are issuing this AD to prevent failure of the alternate release mechanism of the flight compartment door, which could delay or impede the evacuation of the flightcrew during anemergency. This failure also could result in the flightcrew not being able to assist passengers in the event of an emergency. Compliance (e) You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done. Restatement of Requirements of Ad 99-08-04 With Revised Procedures Modification (f) Except as required by paragraph (g) of this AD: Within 90 days after May 12, 1999 (the effective date of AD 99-08-04), 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; or Revision `H,' dated September 9, 2004. After the effective date of this AD, only Revision `H' may be used for accomplishing the modification. (g) For airplanes on which the modification required by paragraph (f) of this AD was done before the effective date of this AD in accordance with Bombardier Service Bulletin S.B. 8-52-39, dated August 30, 1996; or Revision `A,' dated October 31, 1996: Within 90 days after the effective date of this AD, do the modification required by paragraph (f) of this AD in accordance with Bombardier Service Bulletin 8-52-39, Revision `H,' dated September 9, 2004. Inspection (h) Within 800 flight hours after doing the modification required by paragraph (f) or (g) of this AD, as applicable: 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 `D,' dated February 27, 1998; or Revision `H,' dated September 9, 2004. After the effective date of this AD, only Revision `H' may be used for accomplishing the inspection. (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. Credit for Actions Accomplished Previously (i) Modifications and inspections done before the effective date of this AD in accordance with Bombardier Service Bulletin S.B. 8-52- 39, Revision `B,' dated July 4, 1997; Revision `C,' dated August 1, 1997; Revision `E,' dated May 10, 1999; Revision `F,' dated February 4, 2000; or Revision `G,' dated May 17, 2001; are considered acceptable for compliance with the modification and inspections required by this AD. Alternative Methods of Compliance (AMOCs) (j)(1) The Manager, New York Aircraft Certification Office, FAA, has the authority to approve AMOCs for this AD, if requested in accordance with the procedures found in 14 CFR 39.19. (2) AMOCs approved previously in accordance with AD 99-08-04 are approved as AMOCs for the corresponding provisions of paragraphs (f), (g), (h), and (i) of this AD. (3) Before using any AMOC approved in accordance with Sec. 39.19 on any airplane to which the AMOC applies, notify the appropriate principal inspector in the FAA Flight Standards Certificate Holding District Office. Related Information (k) Canadian airworthiness directive CF-1996-20R4, dated August 10, 2005, also addresses the subject of this AD. Material Incorporated by Reference (l) You must use Bombardier Service Bulletin S.B. 8-52-39, Revision `D,' dated February 27, 1998; and Bombardier Service Bulletin 8-52-39, Revision `H,' dated September 9, 2004; as applicable, to perform the actions that are required by this AD, unless the AD specifies otherwise. (1) The Director of the Federal Register approved the incorporation by reference of Bombardier Service Bulletin 8-52-39, Revision `H,' dated September 9, 2004, in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. (2) On May 12, 1999 (64 FR 16803, April 7, 1999), the Director of the Federal Register approved the incorporation by reference of Bombardier Service Bulletin S.B. 8-52-39, Revision `D,' dated February 27, 1998. (3) Contact Bombardier, Inc., Bombardier Regional Aircraft Division, 123 Garratt Boulevard, Downsview, Ontario M3K 1Y5, Canada, for a copy of this service information. You may review copies at the Docket Management Facility, U.S. Department of Transportation, 400 Seventh Street, SW., Room PL-401, Nassif Building, Washington, DC; on the Internet at http://dms.dot.gov; or at the National Archives and Records Administration (NARA). For information on the availability of this material at the NARA, call (202) 741-6030, or go to http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html .