2003-04-02: Inspection Opening in Wing

2003-04-02 Apex Aircraft (Avions Mudry et Cie previously held type certificate A36EU): Amendment 39-13050; Docket No. 2002-CE-04-AD; Supersedes AD 98-12-10, Amendment 39-10566, and AD 99-21-23, Amendment 39-11368. (a) What airplanes are affected by this AD? This AD affects Model CAP 10B airplanes, all serial numbers, that are certificated in any category. (b) Who must comply with this AD? Anyone who wishes to operate any of the airplanes identified in paragraph (a) of this AD must comply with this AD. (c) What problem does this AD address? The actions specified by this AD are intended to provide the flight information necessary to the pilot so that excessive speed is not used during aerobatic maneuvers and to detect and correct structural cracks in the wing spar, which could result in the wing separating from the airplane. Such failure could lead to loss of control of the airplane. (d) What actions must I accomplish to address this problem? To address this problem, you must accomplish the following: Actions Compliance Procedures (1) For CAP 10 B airplanes, all serial numbers through 263, install a permanent inspection opening in the No. 1 wing rib. Inspection openings are incorporated during production for airplanes having a serial number of 264 or higher. Within the next 100 hours time-in-service (TIS) after July 23, 1993 (the effective date of AD 93-10-11, which was superseded by AD 98-12-10), unless already accomplished. In accordance with Avions Mudry Service Bulletin CAP10B No. 16 ATA (57-004), dated April 27, 1992. (2) For all airplanes, accomplish the following: (i) Restrict the load factors limitation to +5 & -3 G's. (ii) Restrict the entry speed for performing flick maneuvers to 86 knots through the incorporation of the following information into the CAP 10B flight manual: "The never-exceed airspeed for positive or negative flick maneuvers is 160 km/h (86 knots)." (iii) Fabricate a placard that incorporates thefollowing words (using at least 1/8-inch letters) 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)". Within the next 25 hours TIS after April 4, 2003 (the effective date of this AD). Accomplish the limitations of paragraphs (d)(2)(i) and (d)(2)(ii) of this AD by inserting a copy of the AD into the Limitations Section of the CAP 10B flight manual. 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 accomplish this flight manual insertion and the placard requirements of paragraph (d)(2)(iii) of this AD. Make an entry into the aircraft records showing compliance with these portions of the AD in accordance with section 43.9 of the Federal Aviation Regulations (14 CFR 43.9). (3) Inspect the upper wing spar cap, the main wing spar undersurface, and the landing gear attachment blocks for cracks. Initially inspect all areas within the next 55 hours TIS after April 4, 2003 (the effective date of this AD). 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. In accordance with APEX Aircraft CAP10B-Upper spar cap inspection Document No. 1000913GB, Revision No. 00, dated February 4, 2002; APEX Aircraft CAP10B-Landing gear attachment blocks inspection Document No. 1000914GB, Revision No. 00, dated February 4, 2002; and APEX Aircraft CAP10B-Main spar undersurface inspection Document No. 1000915GB, Revision No. 00, dated February 4, 2002. (4) If cracks are found during any inspection required in paragraph (d)(3) of this AD, accomplish the following: (i) Obtain a repair scheme from the manufacturer through the FAA at the address specified in paragraph (f) of this AD; (ii) Incorporate this repair scheme; and (iii) The repair scheme will indicate whether or not you may raise the load factor limits. Obtain and incorporate the repair scheme prior to further flight after the inspection in which the cracks are found. Continue to inspect as specified in paragraph (d)(3) of this AD. In accordance with the repair scheme obtained from APEX Aircraft, Direction Technique, Route de Troyes, F21121, Darois, France. Obtain this repair scheme through the FAA at the address specified in paragraph (f) of this AD. (5) If no cracks are found during the initial inspection required in paragraph (d)(3) of this AD, you may raise load factor limits back to +6 & -4.5 G's. Prior to further flight after the initial inspection required in paragraph (d)(3) of this AD in which no cracks were found. Not applicable. Note 1: The service information specified in paragraph (d)(3) of this AD is available on CD-ROM from the manufacturer. You may contact them at the address and phone number in paragraph (h) of this AD. (e) Can I comply with this AD in any other way? (1) You may use an alternative method of compliance or adjust the compliance time if: (i) Your alternative method of compliance provides an equivalent level of safety; and (ii) The Standards Office Manager, Small Airplane Directorate, approves your alternative. Submit your request through an FAA Principal Maintenance Inspector, who may add comments and then send it to the Standards Office Manager. (2) Alternative methods of compliance approved in accordance with AD 98-12-10 and AD 99-21-23, which are superseded by this AD, are not approved as alternative methods of compliance with this AD. Note 2: This AD applies to each airplane identified in paragraph (a) of this AD, regardless of whether it has been modified, altered, or repaired in the area subject to the requirements of this AD. For airplanes that have been modified, altered, or repaired so that the performance of the requirements of this AD is affected, the owner/operator must request approval for an alternative method of compliance in accordance with paragraph (e) of this AD. The request should include an assessment of the effect of the modification, alteration, or repair on the unsafe condition addressed by this AD; and, if you have not eliminated the unsafe condition, specific actions you propose to address it. (f) Where can I get information about any already-approved alternative methods of compliance? Contact S.M. Nagarajan, Aerospace Engineer, FAA, Small Airplane Directorate, 901 Locust, Room 301, Kansas City, Missouri 64106; telephone: (816) 329-4145; facsimile: (816) 329-4090. (g) What if I need to fly the airplane to another location to comply with this AD? The FAA can issue a special flight permit under Secs. 21.197 and 21.199 of the Federal Aviation Regulations (14 CFR 21.197 and 21.199) to operate your airplane to a location where you can accomplish the requirements of this AD. (h) Are any service bulletins incorporated into this AD by reference? (1) Actions required by this AD must be done in accordance with Avions Mudry Service Bulletin CAP10B No. 16 (ATA 57-004), dated April 27, 1992; APEX Aircraft CAP10B-Upper spar cap inspection Document No. 1000913GB, Revision No. 00, dated February 4, 2002; APEX Aircraft CAP10B-Landing gear attachment blocks inspection Document No. 1000914GB, Revision No. 00, dated February 4, 2002; and APEX Aircraft CAP10B-Main spar undersurface inspection Document No. 1000915GB, Revision No. 00, dated February 4, 2002. (i) The Director of the Federal Register approved this incorporation by reference of APEX Aircraft CAP10B-Upper spar cap inspection Document No. 1000913GB, Revision No. 00, dated February 4, 2002; APEX Aircraft CAP10B-Landing gear attachment blocks inspection Document No. 1000914GB, Revision No. 00, dated February 4, 2002; and APEX Aircraft CAP10B-Main spar undersurface inspection Document No. 1000915GB, Revision No. 00, dated February 4, 2002, under 5 U.S.C. 552(a) and 1 CFR part 51. (ii) The Director of the Federal Register previously approved the incorporation by reference of Avions Mudry Service Bulletin CAP10B No. 16 (ATA 57-004), dated April 27, 1992, as listed in the regulations as of July 23, 1993 (58 FR 31342, June 2, 1993). (2) You may get copies from APEX AIRCRAFT, Direction Technique, Route de Troyes, F21121 Darois, France; telephone: +33 (380) 356 510; facsimile: +33 (380) 356 515. You may view copies at the FAA, Central Region, Office of the Regional Counsel, 901 Locust, Room 506, Kansas City, Missouri, or at the Office of the Federal Register, 800 North Capitol Street, NW, suite 700, Washington, DC. (i) Does this AD action affect any existing AD actions? This amendment supersedes AD 98-12-10, Amendment 39-10566 and AD 99-21-23, Amendment 39-11368. Note 3: The subject of this AD is addressed in French AD Number 2001-616(A) R1, datedMay 29, 2002. (j) When does this amendment become effective ? This amendment becomes effective on April 4, 2003.