AD 2008-13-01 Airworthiness Directives; Fokker Model F27 Mark 050 Airplanes

Models named: F27 Mark 050. Read the applicability below — it usually turns on serial or part numbers too.

This AD applies to Fokker Model F27 Mark 050 airplanes, certificated in any category, all serial numbers.

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 3 of 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 be NDT-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, if a 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, 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 Mandatory Continuing Airworthiness Information (MCAI) Dutch Airworthiness Directive NL-2005-015, dated November 30, 2005, and the service bulletins identified in Table 1 of this AD 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. Issued in Renton, Washington, on June 26, 2008. Dionne Palermo, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E8-15711 Filed 7-16-08; 8:45 am] BILLING CODE 4910-13-P

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 3 of 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 be NDT-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, if a 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, 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 Mandatory Continuing Airworthiness Information (MCAI) Dutch Airworthiness Directive NL-2005-015, dated November 30, 2005, and the service bulletins identified in Table 1 of this AD 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. Issued in Renton, Washington, on June 26, 2008. Dionne Palermo, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E8-15711 Filed 7-16-08; 8:45 am] BILLING CODE 4910-13-P