Airworthiness directives › 2006-17-51
AD 2006-17-51 Airworthiness Directives; Agusta S.p.A. Model AB139 Helicopters
Models named: AB139. Read the applicability below — it usually turns on serial or part numbers too.
Applicability*9
Model AB139 helicopters, with tailpipe assembly left hand, part number (P/N) 3G7800L00131 and right hand, P/N 3G7800L00231, installed, certificated in any category.
Compliance
Required as indicated, unless accomplished previously. To prevent a fire due to the structure in the cowling area overheating, separation of part of each tailpipe assembly, and subsequent loss of control of the helicopter, do the following: (a) Before further flight, and thereafter at intervals not to exceed 25 hours time-in-service, access the rear areas of each tailpipe assembly by removing the rear cowlings. (1) Visually inspect each tailpipe assembly inside the cowling for a crack. Note 1: Bollettino Tecnico No. 139-069, dated August 11, 2006 (BT), pertains to the subject of this AD. Note 2: Aircraft Maintenance Publication (AMP) AB139 pertains to the subject of this AD. (2) Inspect the structure surrounding each tailpipe assembly for overheating. If you find areas of overheating, inspect for heat damage to the surrounding structure. Inspect for overheating in the area of each tailpipe assembly outside the cowling. Inspect the internal part of each tailpipe assembly in the areas depicted in Areas A, Figure 1, of this AD. ER01SE06.042 (i) Clean the end of each tailpipe assembly with a cloth. While applying slight pressure on it, inspect for a crack using a flashlight. (ii) Inspect each tailpipe assembly toward the centerline of the helicopter for a crack using a flashlight. (iii) Inspect each tailpipe assembly toward the outboard side of the helicopter for a crack using a mirror and a flashlight. (3) If you find a crack, before further flight, replace the tailpipe assembly with an airworthy tailpipe assembly. (b) To request a different method of compliance or a different compliance time for this AD, follow the procedures in 14 CFR 39.19. Contact the Manager, Safety Management Group, FAA, ATTN: Ed Cuevas, Aviation Safety Engineer, Fort Worth, Texas 76193-0111, telephone (817) 222-5355, fax (817) 222-5961, for information about previously approved alternative methods of compliance. Note 3: The subject of this AD is addressed in the European Aviation Safety Agency (EASA) AD 2006-0242-E, dated August 11, 2006. Note 4: This AD differs from the BT and the EASA AD in that the BT and EASA AD allow repairs of certain cracks in each tailpipe assembly. (c) This amendment becomes effective on September 18, 2006, to all persons except those persons to whom it was made immediately effective by Emergency AD 2006-17-51 issued August 15, 2006, which contained the requirements of this amendment. Issued in Fort Worth, Texas, on August 24, 2006. David A. Downey, Manager, Rotorcraft Directorate, Aircraft Certification Service. [FR Doc. E6-14548 Filed 8-31-06; 8:45 am] BILLING CODE 4910-13-P
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