AD 2008-09-01 Airworthiness Directives; Alpha Aviation Design Limited (Type Certificate No. A48EU Previously Held by APEX Aircraft and AVIONS PIERRE ROBIN) Model R2160 Airplanes

Models named: R2160. Read the applicability below — it usually turns on serial or part numbers too.

This AD applies to Model R2160 airplanes, serial numbers 001 through 378, certificated in any category.

Unless already done, do the following actions: (1) Disassemble the wings from the fuselage and inspect the wing structure and assembly components using instruction No. 1 in Robin Aviation Service Bulletin No. 123, revision 3, dated December 23, 1999. If any defects are found, repair following Robin Aviation Service Bulletin No. 123, revision 3, dated December 23, 1999. Use the following compliance times for the inspection: (i) For airplanes with less than 4,000 hours time-in-service (TIS): When the airplane reaches a total of 3,500 hours TIS or within the next 100 hours TIS after May 27, 2008 (the effective date of this AD), whichever occurs later, and thereafter at intervals not to exceed 750 hours TIS. (ii) For airplanes with 4,000 hours TIS or more that have not complied with the special instruction in paragraph E of Avions Pierre Robin Service Bulletin No. 123, revision 2, dated November 14, 1995: Within the next 100 hours TIS after May 27, 2008 (the effective date of this AD) and thereafter at intervals not to exceed 750 hours TIS. (iii) For airplanes with 4,000 hours TIS or more that have complied with the special instruction in paragraph E of Avions Pierre Robin Service Bulletin No. 123, revision 2, dated November 14, 1995: Within the next 750 hours TIS after May 27, 2008 (the effective date of this AD) and thereafter at intervals not to exceed 750 hours TIS. (2) When the airplane reaches a total of 3,500 hours TIS with original wing-to-fuselage bolts installed or 3,500 hours TIS of an airplane since new bolts have been installed or within the next 100 hours TIS after May 27, 2008 (the effective date of this AD), whichever occurs later, do a non-destructive inspection of the wing-to-fuselage retaining bolts and replace any bolts that do not pass this inspection following instruction No. 2 in Robin Aviation Service Bulletin No. 123, revision 3, dated December 23, 1999. Thereafter, repetitively inspect wing-to-fuselage retaining bolts and replace any bolts that do not pass this inspection every 750 hours TIS following instruction No. 2 in Robin Aviation Service Bulletin No. 123, revision 3, dated December 23, 1999. Note 1: The requirement for a 3,500-hour inspection is a time since new or time since installation (that is, the TIS of new bolts). (3) Within the next 50 hours TIS after re-assembling the wing and thereafter at intervals not to exceed 100 hours TIS, inspect the wing-to-fuselage retaining bolts for correct torque settings following instruction No. 3 in Robin Aviation Service Bulletin No. 123, revision 3, dated December 23, 1999. The required torque value is 22 ft-lb with nut part number 95.24.39.010. Tighten to 16 ft-lb (pre-loading) and then torque from 16 to 22 ft-lb. FAA AD Differences Note 2: 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, Standards 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: Karl Schletzbaum, Aerospace Engineer, FAA, Small Airplane Directorate, 901 Locust, Room 301, Kansas City, Missouri 64106; telephone: (816) 329-4146; fax: (816) 329-4090. 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 (44 U.S.C. 3501 et seq. ), 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 Civil Aviation Authority AD DCA/R2000/28, dated September 28, 2006, and Robin Aviation Mandatory Service Bulletin No. 123, revision 3, dated December 23, 1999, for related information. Material Incorporated by Reference (i) You must use Robin Aviation Mandatory Service Bulletin No. 123, revision 3, dated December 23, 1999, 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 Alpha Aviation, Ingram Road, Hamilton Airport, RD 2, Hamilton 2021, New Zealand; telephone: 011 64 7 843 7070; fax: 011 64 7 843 8040; Internet: http://www.alphaaviation.co.nz . (3) You may review copies at the FAA, Central Region, Office of the Regional Counsel, 901 Locust, Room 506, Kansas City, Missouri 64106; 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 . Issued in Kansas City, Missouri, on April 11, 2008. James E. Jackson, Acting Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. E8-8509 Filed 4-21-08; 8:45 am] BILLING CODE 4910-13-P

Unless already done, do the following actions: (1) Disassemble the wings from the fuselage and inspect the wing structure and assembly components using instruction No. 1 in Robin Aviation Service Bulletin No. 123, revision 3, dated December 23, 1999. If any defects are found, repair following Robin Aviation Service Bulletin No. 123, revision 3, dated December 23, 1999. Use the following compliance times for the inspection: (i) For airplanes with less than 4,000 hours time-in-service (TIS): When the airplane reaches a total of 3,500 hours TIS or within the next 100 hours TIS after May 27, 2008 (the effective date of this AD), whichever occurs later, and thereafter at intervals not to exceed 750 hours TIS. (ii) For airplanes with 4,000 hours TIS or more that have not complied with the special instruction in paragraph E of Avions Pierre Robin Service Bulletin No. 123, revision 2, dated November 14, 1995: Within the next 100 hours TIS after May 27, 2008 (the effective date of this AD) and thereafter at intervals not to exceed 750 hours TIS. (iii) For airplanes with 4,000 hours TIS or more that have complied with the special instruction in paragraph E of Avions Pierre Robin Service Bulletin No. 123, revision 2, dated November 14, 1995: Within the next 750 hours TIS after May 27, 2008 (the effective date of this AD) and thereafter at intervals not to exceed 750 hours TIS. (2) When the airplane reaches a total of 3,500 hours TIS with original wing-to-fuselage bolts installed or 3,500 hours TIS of an airplane since new bolts have been installed or within the next 100 hours TIS after May 27, 2008 (the effective date of this AD), whichever occurs later, do a non-destructive inspection of the wing-to-fuselage retaining bolts and replace any bolts that do not pass this inspection following instruction No. 2 in Robin Aviation Service Bulletin No. 123, revision 3, dated December 23, 1999. Thereafter, repetitively inspect wing-to-fuselage retaining bolts and replace any bolts that do not pass this inspection every 750 hours TIS following instruction No. 2 in Robin Aviation Service Bulletin No. 123, revision 3, dated December 23, 1999. Note 1: The requirement for a 3,500-hour inspection is a time since new or time since installation (that is, the TIS of new bolts). (3) Within the next 50 hours TIS after re-assembling the wing and thereafter at intervals not to exceed 100 hours TIS, inspect the wing-to-fuselage retaining bolts for correct torque settings following instruction No. 3 in Robin Aviation Service Bulletin No. 123, revision 3, dated December 23, 1999. The required torque value is 22 ft-lb with nut part number 95.24.39.010. Tighten to 16 ft-lb (pre-loading) and then torque from 16 to 22 ft-lb. FAA AD Differences Note 2: 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, Standards 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: Karl Schletzbaum, Aerospace Engineer, FAA, Small Airplane Directorate, 901 Locust, Room 301, Kansas City, Missouri 64106; telephone: (816) 329-4146; fax: (816) 329-4090. 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 (44 U.S.C. 3501 et seq. ), 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 Civil Aviation Authority AD DCA/R2000/28, dated September 28, 2006, and Robin Aviation Mandatory Service Bulletin No. 123, revision 3, dated December 23, 1999, for related information. Material Incorporated by Reference (i) You must use Robin Aviation Mandatory Service Bulletin No. 123, revision 3, dated December 23, 1999, 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 Alpha Aviation, Ingram Road, Hamilton Airport, RD 2, Hamilton 2021, New Zealand; telephone: 011 64 7 843 7070; fax: 011 64 7 843 8040; Internet: http://www.alphaaviation.co.nz . (3) You may review copies at the FAA, Central Region, Office of the Regional Counsel, 901 Locust, Room 506, Kansas City, Missouri 64106; 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 . Issued in Kansas City, Missouri, on April 11, 2008. James E. Jackson, Acting Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. E8-8509 Filed 4-21-08; 8:45 am] BILLING CODE 4910-13-P