2009-09-02 Bombardier, Inc. (Formerly de Havilland, Inc.): Amendment 39-15888. Docket No. FAA-2009-0361; Directorate Identifier 2009-NM- 046-AD.
Effective Date
(a) This airworthiness directive (AD) becomes effective May 6, 2009.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Bombardier Model DHC-8-400, DHC-8-401, and DHC-8-402 series airplanes; certificated in any category, serial numbers 4001, 4003, and subsequent.
Subject
(d) Air Transport Association (ATA) of America Code 32: Landing gear.
Reason
(e) The mandatory continued airworthiness information (MCAI) states:
Several reports have been received on failures of the aft hinge of the main landing gear (MLG) forward stabilizer brace. Laboratory examinations have found that the fatigue cracks were initiated from the dowel pin hole at the aft hinge lug of the MLG forward stabilizer brace where the stop bracket is attached. Failure of the stabilizer brace could result in thecollapse of the main landing gear.
Actions and Compliance
(f) Unless already done, do the following actions:
(1) At the applicable time specified in paragraph (f)(1)(i), (f)(1)(ii), (f)(1)(iii), or (f)(1)(iv) of this AD: Perform non- destructive inspections for damage of the MLG forward stabilizer brace assemblies part number (P/N) 46401-7, in accordance with Bombardier Repair Drawing 8/4-32-099, Issue 1, dated March 10, 2009; and Goodrich Service Concession Request 026-09, Revision B, dated March 10, 2009. Repeat the inspection thereafter at intervals not to exceed 2,000 flight cycles.
(i) For airplanes with MLG forward stabilizer braces that have accumulated 12,000 or more total flight cycles as of the effective date of this AD: Inspect within 50 flight cycles after the effective date of this AD.
(ii) For airplanes with MLG forward stabilizer braces that have accumulated 9,000 or more total flight cycles but fewer than 12,000 total flight cycles as of the effectivedate of this AD: Inspect before the accumulation of 12,050 total flight cycles, or within 500 flight cycles after the effective date of this AD, whichever occurs earlier.
(iii) For airplanes with MLG forward stabilizer braces that have accumulated 4,500 or more total flight cycles but fewer than 9,000 total flight cycles as of the effective date of this AD: Inspect before the accumulation of 9,500 total flight cycles, or within 1,500 flight cycles after the effective date of this AD, whichever occurs earlier.
(iv) For airplanes with MLG forward stabilizer braces that have accumulated fewer than 4,500 total flight cycles as of the effective date of this AD: Inspect before the accumulation of 6,000 total flight cycles.
(2) If any damage is found during any inspection required by paragraph (f)(1) of this AD, before further flight, do all applicable corrective actions in accordance with Goodrich Service Concession Request 026-09, Revision B, dated March 10, 2009, except as provided by paragraphs (f)(3), (f)(4), (f)(5), and (f)(6) of this AD.
(3) For airplanes on which step 24. of Goodrich Service Concession Request 026-09, Revision B, dated March 10, 2009, has been done: Within 1,200 flight cycles after the effective date of this AD, rework the MLG forward stabilizer brace, and except for airplanes on which the rework has been done, within 600 flight cycles after the effective date of this AD do a detailed visual inspection for damage of the stabilizer brace apex lugs, in accordance with Goodrich Service Concession Request 026-09, Revision B, dated March 10, 2009. If any damage is found, repair before further flight in accordance with Section C of Goodrich Service Concession Request 026-09, Revision B, dated March 10, 2009.
(4) At the applicable time specified in paragraph (f)(4)(i), (f)(4)(ii), or (f)(4)(iii) of this AD, replace the forward stabilizer brace assembly, in accordance with Goodrich Service Concession Request 026-09, Revision B, dated March10, 2009.
(i) For airplanes on which cracking is found during any inspection required by this AD, and the cracking exceeds the limit specified in Section C of Goodrich Service Concession Request 026- 09, Revision B, dated March 10, 2009: Replace the assembly before further flight.
(ii) For airplanes on which any cracking is found after the rework specified in Section C of Goodrich Service Concession Request 026-09, Revision B, dated March 10, 2009: Replace the assembly before further flight.
(iii) For airplanes on which no cracking is found after the rework specified in Section C of Goodrich Service Concession Request 026-09, Revision B, dated March 10, 2009: Replace the assembly within 2,700 flight cycles after doing the rework.
(5) If foreign object damage is found during any inspection required by this AD, or if damage is found to a forward stabilizer brace lug or stop bracket retention hole apex bushing, before further flight, repair using a method approved by either the Manager, New York Aircraft Certification Office, ANE-170, FAA; or Transport Canada Civil Aviation (TCCA) (or its delegated agent).
(6) If any crack is found during the visual inspection under 10X magnification, repair before further flight, in accordance with Goodrich Service Concession Request 026-09, Revision B, dated March 10, 2009.
(7) Before the accumulation of 6,000 total flight cycles on the MLG forward stabilizer braces, or within 600 flight hours after the effective date of this AD, whichever occurs later: Do a detailed visual inspection for cracking of both MLG forward stabilizer braces and do all applicable liquid penetrant inspections for cracking, in accordance with Bombardier Q400 All Operator Message 338, dated February 23, 2009. Repeat the inspection thereafter at intervals not to exceed 600 flight hours. If any cracking is found during any inspection required by this paragraph, repair before further flight in accordance with Bombardier Repair Drawing 8/4-32-099, Issue 1, dated March 10, 2009; and Goodrich Service Concession Request 026- 09, Revision B, dated March 10, 2009.
(8) Submit a report of all findings of the inspections required by paragraph (f)(1) of this AD to the Bombardier Technical Help Desk, e-mail: thd.qseries@aero.bombardier.com; fax: (416) 375-4539; telephone: (416) 375-4000; at the applicable time specified in paragraph (f)(8)(i) or (f)(8)(ii) of this AD. The report must include the information specified in sheets 3 and 4 of Bombardier Repair Drawing 8/4-32-099, Issue 1, dated March 10, 2009.
(i) If the inspection was done on or after the effective date of this AD: Submit the report within 10 days after the inspection.
(ii) If the inspection was accomplished prior to the effective date of this AD: Submit the report within 10 days after the effective date of this AD.
FAA AD Differences
Note: This AD differs from the MCAI and/or service information as follows: No differences.
Other FAA AD Provisions(g) The following provisions also apply to this AD:
(1) Alternative Methods of Compliance (AMOCs): The Manager, New York Aircraft Certification Office, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. Send information to ATTN: Jon Hjelm, Aerospace Engineer, Airframe and Propulsion Branch, ANE-171, FAA, New York Aircraft Certification Office, 1600 Stewart Avenue, Suite 410, Westbury, New York 11590; telephone (516) 228-7323; fax (516) 794- 5531. Before using any approved AMOC on any airplane to which the AMOC applies, notify your principal maintenance inspector (PMI) or principal avionics inspector (PAI), as appropriate, or lacking a principal inspector, your local Flight Standards District Office. The AMOC approval letter must specifically reference this AD.
(2) Airworthy Product: For any requirement in this AD to obtain corrective actions from a manufacturer or other source, use these actions if they are FAA-approved. Corrective actions are considered FAA-approved if they are approved by the State of Design Authority (or their delegated agent). You are required to ensure the product is airworthy before it is returned to service.
(3) Reporting Requirements: For any reporting requirement in this AD, under the provisions of the Paperwork Reduction Act, the Office of Management and Budget (OMB) has approved the information collection requirements and has assigned OMB Control Number 2120- 0056.
(4) Special Flight Permits: 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 airplane can be modified (if the operator elects to do so), provided that, within 10 flight cycles after detection of the discrepancy that requires repair, operators perform a detailed visual inspection for cracking of both MLG forward stabilizer braces and do all applicable non-destructive inspections (eddy current or visual liquid penetrant inspections) for cracking, in accordance with Bombardier Q400 All Operator Message 338, dated February 23, 2009; and repair any cracking before further flight in accordance with Goodrich Service Concession Request 026-09, Revision B, dated March 10, 2009.
Related Information
(h) Refer to MCAI Canadian Emergency Airworthiness Directive CF- 2009-11, dated March 13, 2009; Bombardier Q400 All Operator Message 338, dated February 23, 2009; Bombardier Repair Drawing 8/4-32-099, Issue 1, dated March 10, 2009; and Goodrich Service Concession Request 026-09, Revision B, dated March 10, 2009; for related information.
Material Incorporated by Reference
(i) You must use Bombardier Q400 All Operator Message 338, dated February 23, 2009; Bombardier Repair Drawing 8/4-32-099, Issue 1, dated March 10, 2009; and Goodrich Service Concession Request 026- 09, Revision B, dated March 10, 2009; as applicable; to do the actions required by this AD, unless the AD specifies otherwise. (The issue date of Bombardier Q400 All Operator Message 338, dated February 23, 2009; and Bombardier Repair Drawing 8/4-32-099, Issue 1, dated March 10, 2009; is specified only on the first page of the documents.) Goodrich Service Concession Request 026-09, Revision B, dated March 10, 2009, contains the following effective pages:
Page No.
Revision level shown on page
Date shown on page
1-8
B
March 5, 2009
9-22
B
March 10, 2009
(1) The Director of the Federal Register approved the incorporation by reference of this service information under 5 U.S.C. 552(a) and 1 CFR part 51.
(2) For Bombardier service information identified in this AD, contact Bombardier, Inc., 400 C[ocirc]te-Vertu Road West, Dorval, Qu[eacute]bec H4S 1Y9, Canada; telephone 514-855-5000; fax 514-855- 7401; e-mail thd.qseries@aero.bombardier.com; Internet http:// www.bombardier.com. For Goodrich service information identified in this AD, contact Goodrich Corporation, Landing Gear, 1400 South Service Road, West Oakville L6L 5Y7, Ontario, Canada; telephone 905- 825-1568; e-mail jean.breed@goodrich.com; Internet http:// www.goodrich.com/TechPubs.
(3) You may review copies of the service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington. For information on the availability of this material at the FAA, call 425-227-1221 or 425-227-1152.
(4) You may also review copies of the service information that is incorporated by reference at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202-741-6030, or go to: http:// www.archives.gov/federal_register/code_of_federal_regulations/ ibr_locations.html.