2002-05-04: Engine Mount Assembly

2002-05-04 SOCATA--Groupe AEROSPATIALE: Amendment 39-12672; Docket No. 2001-CE-41-AD; Supersedes AD 77-15-06, Amendment 39-2975. (a) What airplanes are affected by this AD? This AD affects the following airplane models and serial numbers that are certificated in any category and do not have a part number 892-51-0-035-0 engine mount assembly (or FAA-approved equivalent part number) installed: Model Serial No. 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, which could 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) Inspect the engine mount assembly for cracks. For airplanes previously affected by AD 77-15-06: inspect within the next 50 hours time-in-service (TIS) after the last inspection required by AD 77-15-06 or within the next 50 hours TIS after April 22, 2002 (the effective date of this AD), whichever occurs first, and thereafter at intervals not to exceed 50 hours TIS. For all other airplanes: inspect within the next 50 hours TIS after April 22, 2002 (the effective date of this AD) and thereafter at intervals not to exceed 50 hours TIS. In accordance with the Accomplishment Instructions section of Socata Service Bulletin SB 156-71, dated May2001. (2) If any crack is found during any inspection required by this AD that is less than 0.24 inches (6 mm) in length, repair the engine mounts assembly. If two repairs on the engine mount have already been performed, replace in accordance with paragraph (d)(3) 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. (3) 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, replace the engine mount assembly with part number 892-51-0-035-0 (or FAA-approved equivalent part number). Prior to further flight after the inspection in which the crack is found. Repetitive inspections are no longer required after this replacement In accordance with the maintenance applicable manual. (4) You may terminate the repetitive inspections of this AD after installing engine mount assembly, part number 892-51-0-035-0 (or FAA-approved equivalent part number At any time but it must be done prior to further flight if any of the criteria of paragraph (d)(3) are met. In accordance with the applicable maintenance manual. (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, 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, Small Airplane Directorate. (2) Alternative methods of compliance approved in accordance with AD 77-15-06, 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, Small Airplane 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 can get copies from SOCATA Groupe AEROSPATIALE, Customer Support, Aerodrome Tarbes- Ossun-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. You can look at 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 77-15-06, Amendment 39-2975. Note 2: The subject of this AD is addressed in French AD 2001- 400(A), dated September 19, 2001. (j) When does this amendment become effective? This amendment becomes effective on April 22, 2002.