2008-23-02: Aft engine mounting

2008-23-02 Saab Aircraft AB: Amendment 39-15723. Docket No. FAA- 2008-0115; Directorate Identifier 2007-NM-240-AD. Effective Date (a) This airworthiness directive (AD) becomes effective December 22, 2008. Affected ADs (b) None. Applicability (c) This AD applies to Saab Model SAAB 2000 airplanes, certificated in any category, serial number 004 through 063. Subject (d) Air Transport Association (ATA) of America Code 71: Powerplant. Reason (e) The mandatory continuing airworthiness information (MCAI) states: One Part Number (P/N) LM-219-92 Centre Bracket from a P/N LM- 219-SA28 Aft Engine Mounting assembly was found to be cracked while installed on the aircraft. This reduces the effectiveness of the mounting assembly and could eventually cause it to fail. EASA Airworthiness Directive (AD) was issued to require inspection and rework in order to make the centre bracket less sensitive to external damage that may result in a crack.This AD, superseding AD 2007-0204, has been issued to introduce an alternative repeatable inspection procedure. A failed mounting assembly, if not corrected, could result in loss of the engine. The corrective actions include an inspection to determine if there are any sharp edges on the aft engine mounting assembly; repetitive visual inspections, or a combination of visual and fluorescent penetrant inspection, for cracking of the center bracket of the aft engine mounting assembly for both engines; rework of sharp edges; replacement of the aft engine mounting assemblies; and re-identification of engine mounting assemblies and reworked center bracket. Actions and Compliance (f) Unless already done, do the following actions. (1) Within 1,000 flight hours after the effective date of this AD, do visual inspections of both the aft engine mounting assemblies to find if the center bracket is correct (no sharp edges) from the manufacturer. (2) If no sharp edge is found duringthe inspection required by paragraph (f)(1) of this AD, before further flight, inspect to determine if the aft engine mounting assembly and center bracket are identified with a "-1,'' and before further flight re-identify the parts that are not identified with a "-1,'' in accordance with the Accomplishment Instructions of Saab Service Bulletin 2000-71-025, dated June 13, 2007. Following the re-identification, no further action is required by this AD for airplanes on which no sharp edge is found during the inspection required by paragraph (f)(1) of this AD. (3) If any sharp edge is found during the inspection required by paragraph (f)(1) of this AD, before further flight, do the action in paragraph (f)(3)(i) or (f)(3)(ii) of this AD in accordance with the Accomplishment Instructions of Saab Service Bulletin 2000-71-025, dated June 13, 2007. (i) Do a general visual inspection for cracking of the center bracket of both of the aft engine mounting assemblies, with the bracket on thewing, and repeat the inspection thereafter at intervals not to exceed 250 flight hours until the action required by paragraph (f)(4) of this AD is accomplished. (ii) Do general visual and penetrant inspections for cracking of the center bracket of both of the aft engine mounting assemblies, with the bracket off the wing. Note 1: For the purposes of this AD, a general visual inspection is: "A visual examination of an interior or exterior area, installation, or assembly to detect obvious damage, failure, or irregularity. This level of inspection is made from within touching distance unless otherwise specified. A mirror may be necessary to ensure visual access to all surfaces in the inspection area. This level of inspection is made under normally available lighting conditions such as daylight, hangar lighting, flashlight, or droplight and may require removal or opening of access panels or doors. Stands, ladders, or platforms may be required to gain proximity to the area being checked.'' (4) At the applicable time in paragraph (f)(4)(i) or (f)(4)(ii) of this AD, do the applicable actions in those paragraphs in accordance with the Accomplishment Instructions of Saab Service Bulletin 2000-71-025, dated June 13, 2007. Doing the applicable action terminates the repetitive inspection requirements of paragraph (f)(3)(i) of this AD. (i) If no cracking is found during any inspection required by paragraph (f)(3) of this AD: Within 4,000 flight hours after the effective date of this AD, rework the center bracket, and re- identify the aft engine mounting assembly and center bracket. (ii) If any cracking is found during any inspection required by paragraph (f)(3) of this AD, before further flight, replace the aft engine mounting assembly with an assembly and bracket identified with a "-1'' part number. (5) Actions done before the effective date of this AD in accordance with Saab Service Bulletin 2000-71-023, Revision 01, dated June 13, 2007, are acceptable forcompliance with the corresponding requirements of paragraph (f)(3) of this AD. FAA AD Differences Note 2: This AD differs from the MCAI and/or service information as follows: Although the MCAI or service information allows further flight after cracks are found during compliance with the required action, paragraph (f)(4) of this AD requires that you replace a cracked aft engine mounting assembly before further flight. Other FAA AD Provisions (g) The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, International Branch, ANM-116, Transport Airplane Directorate, 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: Shahram Daneshmandi, Aerospace Engineer, International Branch, ANM- 116, Transport Airplane Directorate, FAA, 1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425) 227-1112; fax (425) 227-1149. Before usingany approved AMOC on any airplane to which the AMOC applies, notify your appropriate principal inspector (PI) in the FAA Flight Standards District Office (FSDO), or lacking a PI, your local FSDO. (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 assure 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. Related Information (h) Refer to MCAI European Aviation Safety Agency Airworthiness Directive 2008-0068, dated April 11, 2008; and Saab ServiceBulletin 2000-71-025, dated June 13, 2007; for related information. Material Incorporated by Reference (i) You must use Saab Service Bulletin 2000-71-025, dated June 13, 2007, to do the actions required by this AD, unless the AD specifies otherwise. (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 service information identified in this AD, contact Saab Aircraft AB, SAAB Aircraft Product Support, S-581.88, Link[ouml]ping, Sweden; telephone 011 46 13 18 5591; fax 011 46 13 18 4874; e-mail http://[email protected]; Internet http://www.saabgroup.com. (3) You may review copies at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or 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.