2006-12-16: Structural testing of the cockpit door

2006-12-16 Bombardier, Inc. (Formerly de Havilland, Inc.): Amendment 39-14642. Docket No. FAA-2006-24411; Directorate Identifier 2006-NM- 033-AD. Effective Date (a) This AD becomes effective July 18, 2006. Affected ADs (b) None. Applicability (c) This AD applies to Bombardier Model DHC-8-102, -103, -106, - 201, -202, -301, -311, -314, and -315 airplanes, certificated in any category; serial numbers 003 through 557 inclusive; equipped with cockpit door installation part numbers (P/Ns) identified in Table 1 of this AD. Table 1.--Cockpit Door Installations Affected by This AD P/N Dash No.(s) 82510074 All. 82510294 All. 82510310 001 8Z4597 001 H85250010 All. 82510700 All. 82510704 All except 502 and 503. Unsafe Condition (d) This AD results from a report that, during structural testing of the cockpit door, the lower hinge block rotated and caused the mating hinge pin to disengage, and caused excessive door deflection. We are issuing this AD to prevent failure of a door attachment, which could result in uncontrolled release of the cockpit door under certain fuselage decompression conditions, and possible damage to the aircraft structure. 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. Modification (f) Within 24 months after the effective date of this AD, modify the cockpit door from a single-point attachment to a two-point attachment in accordance with the Accomplishment Instructions of the applicable service bulletin in Table 2 of this AD. Table 2.--Bombardier Service Bulletins Use this Bombardier service bulletin For airplane serial numbers 8 52 54, Revision A, dated November 5, 2004 003 through 451 inclusive, 453 through 463 inclusive, 465 through 489 inclusive, 491 through 505 inclusive, and 507. 8 52 58, dated May 12, 2004 452, 464, 490, 506, and 508 through 557 inclusive. Note 1: Bombardier Service Bulletin 8-52-54 refers to Bombardier Series 100/300 Modification Summary (Modsum) 8Q100859 as an additional source of service information for installing a hinge pin with a two-point attachment. Bombardier Service Bulletin 8-52-58 refers to Bombardier Series 100/300 Modsum 8Q900267 as an additional source of service information for reworking and installing the cockpit door, and reworking the lower hinge attachment to provide a downward-facing pin with a two-point attachment. Prior/Concurrent Requirements (g) Prior to or concurrently with the modification in paragraph (f) of this AD, do the applicable actions specified in Table 3 of this AD according to a method approved by either the Manager, New York Aircraft Certification (ACO), FAA; or Transport Canada Civil Aviation (TCCA) (or its delegated agent). One approved method is the applicable modification or Modsum listed in the "One approved methodfor doing these actions" column of Table 3 of this AD. Table 3.--Bombardier Service Bulletins For airplanes affected by Bombardier Service Bulletin That have these serial numbers Do these actions One approved method for doing these actions Rework the cockpit door emergency release. De Havilland Aircraft of Canada, Limited, Modification 8/2337. 8 52 54, Revision A, dated November 5, 2004. 003 through 407 inclusive, 409 through 412 inclusive, and 414 through 433 inclusive. Install a new label regarding alternate release of the door. De Havilland Aircraft of Canada, Limited, Modification 8/3339. Install the cockpit door Bombardier Series 100/300 Modsum 8Q200015. Install the cockpit door Bombardier Series 100/300 Modsum 8Q420101. 8 52 58, dated May 12, 2004 452, 464, 490, 506, and 508 through 557 inclusive. Install the cockpit door with a blow-out door panel. Bombardier Series 100/300 Modsum 8Q420143. Actions Done In Accordance With Previous Revision of Service Bulletin (h) Actions done before the effective date of this AD in accordance with Bombardier Service Bulletin 8-52-54, dated May 12, 2004, are acceptable for compliance with the corresponding requirements in paragraph (f) of this AD. Alternative Methods of Compliance (AMOCs) (i)(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) 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 (j) Canadian airworthiness directive CF-2005-34, dated August 29, 2005, also addresses the subject of this AD. Material Incorporated by Reference (k) You must use the Bombardier service informationidentified in Table 4 of this AD to perform the actions that are required by this AD, as applicable, unless the AD specifies otherwise. The Director of the Federal Register approved the incorporation by reference of these documents in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. 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. Table 4.--Material Incorporated by Reference Bombardier Service Bulletin Revisionlevel Date 8 52 54 A Nov. 5, 2004. 8 52 58 Original May 12, 2004.