2003-06-07: Engine Mount Assembly

2003-06-07 Socata-Groupe Aerospatiale: Amendment 39-13095; Docket No. 2002-CE-49-AD; Supersedes AD 2002-05-04, Amendment 39-12672. (a) What airplanes are affected by this AD? This AD affects the following airplane models and serial numbers that are certificated in any category: Model Serial Nos. MS 892A-150 All serial numbers. MS 892E-150 All serial numbers. MS 893A All serial numbers. MS 893E All serial numbers. MS 894A 1005 through 2204 equipped with kit OPT8098 9037. MS 894E 1005 through 2204 equipped with kit OPT8098 9037. Rallye 150T All serial numbers. Rallye 150ST All serial numbers. (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 detect and correct cracks in the engine mount assembly. Such a condition could cause the engine mount assembly to fail, whichcould result in 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) Replace any part number 892-51-0-035-0 engine mount assembly with an FAA-approved assembly that is not part number 892-51-0-035-0. Within the next 50 hours time-in-service (TIS) after May 16, 2003 (the effective date of this AD). In accordance with the applicable maintenance manual. (2) Inspect the engine mount assembly for cracks. Initially inspect at whichever of the following occurs later: after accumulating 50 hours TIS after engine mount assembly installation; within the next 20 hours TIS after May 16, 2003 (the effective date of this AD); or at the next inspection required by AD 2002-05-04. Repetitively inspect thereafter at intervals not to exceed 50 hours TIS. In accordance with the Accomplishment Instructions section of Socata Service Bulletin SB 156-71, dated May 2001. (3) If any crack is found during any inspection required by paragraph (d)(2) of this AD that is less than 0.24 inches (6 mm) in length, repair the engine mount assembly. If two repairs on the engine mount have already been performed, repair in accordance with paragraph (d)(4) of this AD. Prior to further flight after the inspection in which the crack is found. In accordance with the Accomplishment Instructions section of Socata Service Bulletin SB 156-71, dated May 2001. (4) If any crack is found during any inspection required by this AD that is 0.24 inches (6 mm) or longer in length, or if any crack is found and two repairs on the engine mount have already been performed: (i) Obtain a repair scheme from the manufacturer through the FAA at the address specified in paragraph (f) of this AD; and (ii) Incorporate this repair scheme. Prior to further flight after the inspection in which the crack is found. In accordance with the repair scheme obtained from SocataGroupe Aerospatiale, Customer Support, Aerodrome TarbesOssun-Lourdes, BP 930-F65009 Tarbes Cedex, France; or the Product Support Manager, Socata-Groupe Aerospatiale, North Perry Airport, 7501 Pembroke Road, Pembroke Pines, Florida 33023. Obtain this repair scheme through the FAA at the address specified in paragraph (f) of this AD. (5) Do not install on any airplane engine mount assembly part number 892-51-0-035-0. As of May 16, 2003 (the effective date of this AD). Not applicable. (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 Manager, Standards Office, 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 Manager, Standards Office. (2) Alternative methods of compliance approved in accordance with AD 2002-05-04, which is superseded by this AD, are not approved as alternative methods of compliance with this AD. Note 1: 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 Karl Schletzbaum, Aerospace Engineer, FAA, SmallAirplane Directorate, 901 Locust, Room 301, Kansas City, Missouri 64106; telephone: (816) 329-4146; 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 sections 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? Actions required by this AD must be done in accordance with Socata Service Bulletin SB 156-71, dated May 2001. The Director of the Federal Register approved this incorporation by reference under 5 U.S.C. 552(a) and 1 CFR part 51. You may get copies from Socata Groupe Aerospatiale, Customer Support, Aerodrome Tarbes-Ossun-Lourdes, BP 930-F65009 Tarbes Cedex, France; telephone: 011 33 5 62 41 73 00; facsimile: 011 33 5 62 41 76 54; or the Product Support Manager, Socata-Groupe Aerospatiale, North Perry Airport, 7501 Pembroke Road, Pembroke Pines, Florida 33023; telephone: (954) 894-1160; facsimile: (954) 964-4141. 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. Note 2: The subject of this AD is addressed in French AD 2001-400(A), dated September 19, 2001; and French AD 1978-205(A) R1, dated September 19, 2001. (i) Does this AD action affect any existing AD actions? This amendment supersedes AD 2002-05-04, Amendment 39-12672. (j) When does this amendment become effective? This amendment becomes effective on May 16, 2003.