2008-13-01 Fokker Services B.V.: Amendment 39-15564. Docket No. FAA- 2008-0639; Directorate Identifier 2007-NM-003-AD.
Effective Date
(a) This airworthiness directive (AD) becomes effective August 1, 2008.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Fokker Model F27 Mark 050 airplanes, certificated in any category, all serial numbers.
Subject
(d) Air Transport Association (ATA) of America Code 71: Powerplant.
Reason
(e) The mandatory continued airworthiness information (MCAI) states:
During scheduled X-ray inspections of Fokker 50 (F27 Mark 050) engine mounting frames, welding defects were discovered. In two forward frames and one aft frame, defects were found in a total of 4 weld locations. Investigation showed that during manufacture of the frames, when the tubes were welded to the end fittings, unintentional sideways movement of the electric arc resulted in some welds running beside the borderline for a part of thetube circumference. Where a weld runs beside the borderline, there is no connection between tube and end fitting for that part of the circumference, directly affecting the structural integrity of the engine mounting frame connections. The defective welding process appears to have happened at some of the welds in an unknown number of engine mounting frames. This condition, if not corrected, could lead to failure of the engine mounting frame in cases where multiple welds are severely affected, potentially resulting in in-flight loss of an engine. Since an unsafe condition had been identified that may exist on aircraft of the same type design, Airworthiness Directive NL-2005-007 was issued to require * * * a one-time inspection for improper welds. The [MCAI supersedes Airworthiness Directive NL- 2005-007 and] further specifies the criteria and compliance times for the follow-up NDT (non-destructive test) inspection and repair or replacement of engine mounting frames, as necessary.
Corrective action includes contacting Fokker for repair instructions and repair.
Actions and Compliance
(f) Unless already done, do the following actions.
(1) Within 2 months after the effective date of this AD, inspect the engine mounting frames to identify those that have any sideways deviations in the welds, in accordance with Part 3 of the Accomplishment Instructions of Fokker Service Bulletin SBF50-71-048, dated May 30, 2005. When deviations are found that are less than or equal to 2.0 mm, no further action is required on that frame and the aircraft may be returned to service.
(2) When, during the inspection required by paragraph (f)(1) of this AD, deviations are found that are greater than 2.0 mm but less than or equal to 2.5 mm on any of the welds of the engine mounting frame, except those of tubes 7, 8, and 12 of the rear frame: Within 12 months after the effective date of this AD, NDT (non-destructive test) inspect the affected frame tubes in accordance with Part 3of the Accomplishment Instructions of Fokker Service Bulletin SBF50-71- 049, dated October 25, 2005.
(3) When, during the inspection required by paragraph (f)(1) of this AD, deviations are found that are greater than 2.5 mm but less than or equal to 3.0 mm on any of the welds of the engine mounting frame, except those of tubes 7, 8, and 12 of the rear frame: Within 9 months after the effective date of this AD, NDT-inspect the affected frame tubes in accordance with Part 3 of the Accomplishment Instructions of Fokker Service Bulletin SBF50-71-049, dated October 25, 2005.
(4) When, during the inspection required by paragraph (f)(1) of this AD, deviations are found that are greater than 3.0 mm but less than or equal to 3.5 mm on any of the welds of the engine mounting frame, except those of tubes 7, 8, and 12 of the rear frame: Within 6 months after the effective date of this AD, NDT-inspect the affected frame tubes in accordance with Part 3 of the Accomplishment Instructions of Fokker Service Bulletin SBF50-71-049, dated October 25, 2005.
(5) When, during the inspection required by paragraph (f)(1) of this AD, deviations are found that are greater than 3.5 mm but less than or equal to 5.0 mm on any of the welds of the engine mounting frame, except those of tubes 7, 8, and 12 of the rear frame: Within 3 months after the effective date of this AD, NDT-inspect the affected frame tubes in accordance with Part 3 of the Accomplishment Instructions of Fokker Service Bulletin SBF50-71-049, dated October 25, 2005.
(6) When, during the inspection required by paragraph (f)(1) of this AD, deviations are found that are greater than 2.0 mm but less than or equal to 5.0 mm on tubes 7, 8, and 12 of the rear frame: Within 3 months after the effective date of this AD, NDT-inspect the affected frame tubes in accordance with Part 3 of the Accomplishment Instructions of Fokker Service Bulletin SBF50-71-049, dated October 25, 2005.
(7) Within 7 days after doing any NDT-inspection required by this AD, or within 30 days after the effective date of this AD, whichever occurs later, report all findings to Fokker Services B.V., Technical Services Dept., P.O. Box 231, 2150 AE Nieuw-Vennep, the Netherlands.
(8) Within 30 days after reporting in accordance with paragraph (f)(7) of this AD, or within 30 days after the effective date of this AD, whichever occurs later, repair any frame deviation in accordance with a method approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA, or by the European Aviation Safety Agency (EASA) (or its designated agent).
(9) When, during the inspection required by paragraph (f)(1) of this AD, deviations are found exceeding 5 mm, before further flight, report the inspection findings to Fokker Services B.V., Technical Services Dept., P.O. Box 231, 2150 AE Nieuw-Vennep, the Netherlands, and repair any such deviation in accordance with a method approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA, or by EASA (or its designated agent).
(10) Except as provided by paragraphs (f)(10)(i), (f)(10)(ii), (f)(10)(iii), (f)(10)(iv), and (f)(10)(v) of this AD, as of the effective date of this AD, no person may install an engine mounting frame having part number F8200-035-427/-441/-451/-463 (forward frames); F8200-035-425/-443 (A-frames); or F8200-035-403/-439/-449/- 461 (rear frames), as a replacement part, unless it has been inspected and found to have deviations less than or equal to 2.0 mm, in accordance with the requirements of Fokker Component Service Bulletin F8200-035-71-10, dated May 30, 2005.
(i) Any frame inspected in accordance with Fokker Component Service Bulletin F8200-035-71-10, and found to have any deviation greater than 2.0 mm but less than or equal to 2.5 mm on any tube, except tubes 7, 8, and 12 of the rear frame, is acceptable for installation. However, if a frame is installed in accordance with this paragraph, it must beNDT-inspected within 12 months after the installation, in accordance with Part 3 of the Accomplishment Instructions of Fokker Service Bulletin SBF50-71-049, dated October 25, 2005.
(ii) Any frame inspected in accordance with Fokker Component Service Bulletin F8200-035-71-10, and found to have any deviation greater than 2.5 mm but less than or equal to 3.0 mm on any tube, except tubes 7, 8, and 12 of the rear frame, is acceptable for installation. However, if a frame is installed in accordance with this paragraph, it must be NDT-inspected within 9 months after the installation, in accordance with Part 3 of the Accomplishment Instructions of Fokker Service Bulletin SBF50-71-049, dated October 25, 2005.
(iii) Any frame inspected in accordance with Fokker Component Service Bulletin F8200-035-71-10, and found to have any deviation greater than 3.0 mm but less than or equal to 3.5 mm on any tube, except tubes 7, 8, and 12 of the rear frame, is acceptable for installation. However, ifa frame is installed in accordance with this paragraph, it must be NDT-inspected within 6 months after the installation, in accordance with Part 3 of the Accomplishment Instructions of Fokker Service Bulletin SBF50-71-049, dated October 25, 2005.
(iv) Any frame inspected in accordance with Fokker Component Service Bulletin F8200-035-71-10, and found to have any deviation greater than 3.5 mm but less than or equal to 5.0 mm on any tube, except tubes 7, 8, and 12 of the rear frame, is acceptable for installation. However, if a frame is installed in accordance with this paragraph, it must be NDT-inspected within 3 months after the installation, in accordance with Part 3 of the Accomplishment Instructions of Fokker Service Bulletin SBF50-71-049, dated October 25, 2005.
(v) Any tube 7, 8, or 12 of the rear frame, inspected in accordance with Fokker Component Service Bulletin F8200-035-71-10, and found to have any deviation greater than 2.0 mm but less than or equal to 5.0 mm, is acceptable for installation. However, if a frame is installed in accordance with this paragraph, it must be NDT-inspected within 3 months after the installation, in accordance with Part 3 of the Accomplishment Instructions of Fokker Service Bulletin SBF50-71-049, dated October 25, 2005.
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, International Branch, ANM-116, 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: Tom Rodriguez, Aerospace Engineer, International Branch, ANM-116, Transport Airplane Directorate, FAA, 1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425) 227-1137; fax (425) 227-1149. Before using any approved AMOC on any airplane to which the AMOC applies, notifyyour 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 Mandatory Continuing Airworthiness Information (MCAI) Dutch Airworthiness Directive NL-2005-015, dated November 30, 2005, and the service bulletins identified in Table 1 of thisAD for related information.
Table 1.--Service Information
Fokker Service Bulletin
Date
Component Service Bulletin F8200-035-71-10
May 30, 2005
Component Service Bulletin F8200-035-71-11
October 25, 2005
Service Bulletin SBF50-71-048
May 30, 2005
Service Bulletin SBF50-71-049
October 25, 2005
Material Incorporated by Reference
(i) You must use the service information specified in Table 2 of this AD to do the actions required by this AD, as applicable, 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 Fokker Services B.V., Technical Services Dept., P.O. Box 231, 2150 AE Nieuw-Vennep, the Netherlands.
(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/cfr/ibr- locations.html.
Table 2.--Material Incorporated by Reference
Service Bulletin
Date
Fokker Component Service Bulletin F8200-035-71-10
May 30, 2005
Fokker Service Bulletin SBF50-71-048
May 30, 2005
Fokker Service Bulletin SBF50-71-049
October 25, 2005