2010-20-01: Wings

2010-20-01 GROB-WERKE: Amendment 39-16435; Docket No. FAA-2010-0926; Directorate Identifier 2010-CE-024-AD. Effective Date (a) This airworthiness directive (AD) becomes effective October 12, 2010. Affected ADs (b) None. Applicability (c) This AD applies to Model G120A airplanes, all serial numbers, certificated in any category. Subject (d) Air Transport Association of America (ATA) Code 57: Wings. Reason (e) GROB Aircraft AG has been informed that flap ribs P/N 120A- 1053 and 120A-1054 have been found cracked during regular maintenance. Structural failure of the ribs may cause failure of the middle flap support which may lead to flap asymmetry due to excessive flap deformation and ultimately could result in reducing the controllability of the aeroplane. Pending further investigation on the root source for the cracks, including review of the original proofs of compliance, temporary limitations for flap operations established until terminating action development. EASA AD 2010-0065-E required a repetitive inspection of the RH and LH flap ribs. EASA AD 2010-0065-E is superseded as a terminating action has been developed by Grob Aircraft AG. This AD, which supersedes EASA AD 2010-0065-E retaining its requirements, additionally requires accomplishment of repair N[deg] 1121-017 and modification N[deg] 1121-018 for aeroplanes on which cracks have been found or accomplishment of modification N[deg] 1121-018 only for aeroplanes on which no crack has been found. Actions and Compliance (f) Unless already done, do the following actions: (1) Before further flight after October 12, 2010 (the effective date of this AD), and repetitively thereafter before the first flight of each day, inspect the right hand (RH) and left hand (LH) flap ribs for cracks following GROB Aircraft AG Service Bulletin No.: ASB1121-113/1, Accomplishment Instructions, PART A, dated May 18, 2010. (2) If no crack is found during any inspection required in paragraph (f)(1) of this AD, before further flight, you must comply with the following conditions until the Repair Instructions in GROB Aircraft AG Repair Instruction No. RI-1121-018, dated May 18, 2010, are done: (i) Reduction of the airplane's maximum flap deflection to the "TAKE-OFF'' position and reduction of the maximum flaps extended speed VFE to 114 knots indicated airspeed (KIAS); (ii) Modification of the placard part number (P/N) 120A- 7000.113E to show reduced flap deflection of "TAKE-OFF'' position and maximum flaps extended speed VFE of 114 KIAS, and (iii) Insertion into the limitations section of the airplane flight manual and/or pilots operating handbook an amendment showing that the Temporary Maximum Flap Position is TAKE-OFF and the Maximum Flap Extended Speed is 114 KIAS. (3) If no crack is found during any inspection required in paragraph (f)(1) of this AD, within the next 12 months after the effective date of this AD, modify the LH and RHflap ribs following GROB Aircraft AG Repair Instruction No. RI-1121-018, dated May 18, 2010 and GROB Aircraft AG Service Bulletin No.: ASB1121-113/1, Accomplishment Instructions, PART B, dated May 18, 2010. (4) If a crack is found during any inspection required in paragraph (f)(1) of this AD, before further flight, repair the applicable flap rib(s) following GROB Aircraft AG Repair Instruction No. RI-1121-017, dated April 1, 2010; GROB Aircraft AG Repair Instruction No. RI-1121-018, dated May 18, 2010; and GROB Aircraft AG Service Bulletin No.: ASB1121-113/1, Accomplishment Instructions, PART B, dated May 18, 2010. (g) You may at any time complete GROB Aircraft AG Repair Instruction No. RI-1121-017, dated April 1, 2010, and GROB Aircraft AG Service Bulletin No. ASB1121-113/1, Accomplishment Instructions, PART B, dated May 18, 2010, to terminate the repetitive inspection required in paragraph (f)(1) of this AD, and to terminate the conditions required by paragraphs (f)(2) of thisAD. This repair must be done before further flight if cracks are found as required in paragraph (f)(4) of this AD. FAA AD Differences Note: This AD differs from the MCAI and/or service information as follows: The MCAI allows flight with known cracks for up to 100 hours time-in-service. FAA policy is to not allow further flight with known cracks in critical structure. We require that if any cracks are found, before further flight, the crack must be repaired following the applicable GROB service information. Other FAA AD Provisions (h) 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: Greg Davison, Aerospace Engineer, FAA, Small Airplane Directorate, 901 Locust, Room 301, Kansas City, Missouri 64106; telephone: (816) 329-4130; 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 (i) Refer to MCAI European Aviation Safety Agency (EASA) AD No.: 2010-0140, dated July 2, 2010; GROB Aircraft AG Repair Instruction No. RI-1121-017, dated April 1, 2010; GROB Aircraft AG Repair Instruction No. RI-1121-018, dated May 18, 2010; and GROB Aircraft AG Service Bulletin No.: ASB1121-113/1, dated May 18, 2010, for related information. Material Incorporated by Reference (j) You must use GROB Aircraft AG Repair Instruction No. RI- 1121-017, dated April 1, 2010; GROB Aircraft AG Repair Instruction No. RI-1121-018, dated May 18, 2010; and GROB Aircraft AG Service Bulletin No.: ASB1121-113/1, dated May 18, 2010, 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 GROB Aircraft AG, Lettenbachstrasse 9, 86874 Tussenhausen-Mattsies, Germany; telephone: +49 (0) 8268-998-0; fax: +49 (0) 8268-998-200; e-mail productsupport@grob-aircraft.com;Internet: http://www.grob- aircraft.eu/service-and-support/g-120/documentation/service- bulletins.html. (3) You may review copies of the service information incorporated by reference for this AD at the FAA, Central Region, Office of the Regional Counsel, 901 Locust, Kansas City, Missouri 64106. For information on the availability of this material at the Central Region, call (816) 329-3768. (4) You may also review copies of the service information incorporated by reference for this AD 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.