AD 2007-18-05 Airworthiness Directives; Societe de Motorisations Aeronautiques (SMA) SR305-230 and SR305-230-1 Reciprocating Engines

This AD applies to Societe de Motorisations Aeronautiques (SMA) SR305-230 and SR305-230-1 reciprocating engines with exhaust collector assembly part number (P/N) SF01080014-0. These engines are installed on, but not limited to, Cessna 182 series airplanes modified to supplemental type certificate AS03302AT. Reason (d) Several occurrences of cracks on the exhaust collector assembly have been reported in service. Failure of the engine primary exhaust can lead to a loss of engine manifold pressure and may result in a loss of engine power. In some recent occurrences, cracking has appeared near the weld of the Turbine Inlet Temperature (TIT) probe support. This eventually led to an open hole in the exhaust collector assembly. The resulting loss of engine power was not compatible with the continuation of the flight and an immediate landing was necessary. We are issuing this AD to prevent failure of the engine primary exhaust, which could result in loss of engine power and inability to maintain safe flight. Actions and Compliance Initial Inspection (e) Unless already done, do the following actions. (1) Within 30 hours time-since-new (TSN), visually inspect the exhaust collector assembly, P/N SF01080014-0 in the area of the TIT probe mount weld for cracks. (2) Before further flight, replace exhaust collector assemblies found cracked with a serviceable part. Repetitive Inspections (3) Within 10 hours time-since-last inspection (TSLI), repeat the actions specified in paragraph (e)(1) and (e)(2) of this AD. Replace Exhaust Collector Assembly (4) Within 50 hours TSN, replace the exhaust collector assembly with a serviceable part. Continuing Action (5) Continue to inspect and replace exhaust collector assemblies as specified in paragraphs (e)(1) through (e)(4) of this AD. Definitions (6) For the purpose of this AD, a serviceable exhaust collector assembly is a new exhaust collector assembly, or an exhaust collector assembly with fewer than 50 operating hours and no cracks. FAA AD Differences (f) This AD differs from the Mandatory Continuing Airworthiness Information (MCAI) and/or service information as follows: (1) We require the initial inspection within 30 hours TSN instead of at 30 hours TSN. (2) We require the repetitive inspections within 10 hours TSLI instead of at 40 hours TSN. (3) We define a serviceable part. Other FAA AD Provisions (g) Alternative Methods of Compliance (AMOCs): The Manager, Engine Certification Office, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. (h) Special Flight Permits: We will allow a special flight permit to comply with paragraph (e)(4) of this AD. Related Information (i) Refer to MCAI EASA Airworthiness Directive 2007-0127, dated May 7, 2007, and SMA Service Bulletin SB-01-78-78-001, dated March 27, 2007, for related information. (j) Contact Christopher Spinney, Aerospace Engineer, Engine Certification Office, FAA, Engine & Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803; e-mail: christopher.spinney@faa.gov ; telephone (781) 238-7175; fax (781) 238-7199 for more information about this AD. Material Incorporated by Reference (k) None. Issued in Burlington, Massachusetts, on September 11, 2007. Francis A. Favara, Manager, Engine and Propeller Directorate, Aircraft Certification Service. [FR Doc. E7-18412 Filed 9-20-07; 8:45 am] BILLING CODE 4910-13-P