2008-09-02: Upper spar flange inspection

2008-09-02 APEX Aircraft: Amendment 39-15482; Docket No. FAA-2008- 0196; Directorate Identifier 2008-CE-002-AD. Effective Date (a) This airworthiness directive (AD) becomes effective May 27, 2008. Affected ADs (b) This AD supersedes AD 2003-04-02, Amendment 39-13050. Applicability (c) This AD applies to Model CAP 10B airplanes, serial numbers (SNs) 01, 02, 03, 04, and 1 through 282, certificated in any category, that have not been fitted with a replacement wood/carbon wing following application of major change 000302. Subject (d) Air Transport Association of America (ATA) Code 57: Wings. Reason (e) The mandatory continuing airworthiness information (MCAI) states: Further to a new fracture in flight of a CAP 10B wing in June 2003, the investigation in process seems to point out that a wrong application of CAP 10B Service Bulletin No. 16 (CAP 10B-57-004) would lead to the impossibility of detecting the potential spar damage while performing the Type Certificate holder upper spar flange inspection. The MCAI requires you to check that the No. 1 wing rib has been modified, comply with load factors and operating limitations, and do repetitive inspections of the upper and lower spar flanges and landing gear attachment blocks. Actions and Compliance (f) Unless already done, do the following actions: (1) For Model CAP 10B airplanes with SNs 01, 02, 03, 04, and 1 through 263, within the next 100 hours time-in-service (TIS) after July 23, 1993 (the compliance date retained from AD 2003-04-02), unless already done, install a permanent inspection opening in the No. 1 wing rib following Avions Mudry Service Bulletin CAP10B No. 16, dated April 27, 1992. Inspection openings are incorporated during production for airplanes having a serial number of 264 or higher. (2) For all affected airplanes, initially inspect the upper wing spar cap, the main wing spar undersurface, and the landing gear attachment blocks for cracks within the next 55 hours TIS after April 4, 2003 (the compliance date retained from AD 2003-04-02) following APEX Aircraft Document No. 1000913GB, dated February 4, 2002; APEX Aircraft Document No. 1000914GB, dated February 4, 2002; and APEX Aircraft Document No. 1000915GB, dated February 4, 2002. Repetitively inspect the upper wing spar cap and the main wing spar undersurface thereafter at intervals not to exceed 55 hours TIS. Repetitively inspect the landing gear attachment blocks thereafter at intervals not to exceed 1,000 hours TIS. (3) For all affected airplanes, before further flight if any cracks are found during any inspection required in paragraph (f)(2) of this AD, do the following: (i) Obtain a repair scheme from the manufacturer through the FAA at the address specified in paragraph (h)(1) of this AD; (ii) Incorporate this repair scheme; and (iii) Continue to inspect as specified in paragraph (f)(2) of this AD. (4) For all affected airplanes, unless already done, do the following actions: (i) Load factors limitation: Before further flight, as of May 27, 2008 (the effective date of this AD), the load factors limitation for solo flight is +5 and -3.5 Gs and when 2 persons are on board is +4.3 and -3.5 Gs. (ii) Flick (snap roll) maneuvers speed limitation: Before further flight, as of May 27, 2008 (the effective date of this AD), for positive and negative flick maneuvers, the airspeed limitation is 160 km/hour (86 knots). (5) For all affected airplanes, before further flight after May 27, 2008 (the effective date of this AD), fabricate a placard: (i) Incorporate the following words (using at least \1/8\-inch letters) in the placard and install this placard on the instrument panel within the pilot's clear view: "THE NEVER EXCEED AIRSPEED FOR POSITIVE OR NEGATIVE FLICK MANEUVERS IS 160 KM/H (86 KNOTS). THE LOAD FACTORS LIMITATION FOR SOLO FLIGHT IS +5 AND -3.5 Gs AND WHEN 2 PERSONS ARE ON BOARD IS +4.3 AND -3.5 Gs.'' (ii) The owner/operator holding at least a private pilot certificate as authorized by section 43.7 of the Federal Aviation Regulations (14 CFR 43.7) may fabricate the placard required in paragraph (g)(3)(i) of this AD. Make an entry into the aircraft records showing compliance with this portion of the AD in accordance with section 43.9 of the Federal Aviation Regulations (14 CFR 43.9). FAA AD Differences Note: This AD differs from the MCAI and/or service information as follows: This AD does not include the requirement from the MCAI to route the request to operate beyond the load factors limitation and flick (snap roll) maneuvers speed limitation through the Direction G[eacute]n[eacute]rale de L'Aviation Civile (DGAC). You may make this request to the FAA following paragraph (h)(1) of this AD. 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: Sarjapur Nagarajan, Aerospace Engineer, FAA, Small Airplane Directorate, 901 Locust, Room 301, Kansas City, Missouri 64106; telephone: (816) 329-4145; 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 (44U.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 French AD 2003-375(A), dated October 1, 2003; Avions Mudry & CIE Service Bulletin CAP 10B No. 16, dated April 27, 1992, APEX Aircraft Document No. 1000913GB, dated February 4, 2002; APEX Aircraft Document No. 1000914GB, dated February 4, 2002; and APEX Aircraft Document No. 1000915GB, dated February 4, 2002, for related information. Material Incorporated by Reference (j) You must use Avions Mudry & CIE Service Bulletin CAP 10B No. 16, dated April 27, 1992; APEX Aircraft Document No. 1000913GB, dated February 4, 2002; APEX Aircraft Document No. 1000914GB, dated February 4, 2002; and APEX Aircraft Document No. 1000915GB, dated February 4, 2002, 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 APEX Aircraft Document No. 1000913GB, dated February 4, 2002; APEX Aircraft Document No. 1000914GB, dated February 4, 2002; and APEX Aircraft Document No. 1000915GB, dated February 4, 2002, under 5 U.S.C. 552(a) and 1 CFR part 51. (2) On July 23, 1993 (58 FR 31342, June 2, 1993), the Director of the Federal Register previously approved the incorporation by reference of Avions Mudry & CIE Service Bulletin CAP 10B No. 16, dated April 27, 1992. (3) For service information identified in this AD, contact APEX Aircraft, Bureau de Navigabilit[eacute], 1, route de Troyes, 21121 DAROIS--France; telephone: +33 380 35 65 10; fax +33 380 35 65 15; e-mail: airworthiness@apex-aircraft.com; Internet: http://www.apex- aircraft.com. (4) 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.