Airworthiness directives › 2005-21-03
AD 2005-21-03 Airworthiness Directives; Bell Helicopter Textron Canada Model 206A, A-1, B, B-1, L, L-1, L-3, L-4 Helicopters
Models named: 206A, A-1, B, B-1, L, L-1, L-3, L-4. Read the applicability below — it usually turns on serial or part numbers too.
Applicability*9
Model 206A, A-1, B, B-1, L, L-1, L-3, L-4 helicopters, with tail rotor blade (blade), part number (P/N) 206-016-201-131, serial numbers with a prefix of “CS” and 4820 through 4845, installed, certificated in any category.
Compliance
Required as indicated, unless accomplished previously. To prevent loss of a blade, loss of tail rotor control, and subsequent loss of control of the helicopter, accomplish the following: (a) Before the first flight of each day, clean each blade and visually check the blade root doublers for an edge void or de-bond on both sides of each blade as depicted in Figure 1 of this AD. An owner/operator (pilot), holding at least a private pilot certificate, may perform this visual check and must enter compliance with this paragraph into the helicopter maintenance records by following 14 CFR sections 43.11 and 91.417(a)(2)(v). BILLING CODE 4910-13-P ER17OC05.000 BILLING CODE 4910-13-C (b) If an edge void or a de-bond is found, before further flight, replace the blade with an airworthy blade with a serial number other than those to which this AD applies. (c) Within 100 hours time-in-service, replace all affected, serial-numbered blades with airworthy blades with a serial number other than those to which this AD applies. Note 1: Bell Helicopter Textron Alert Service Bulletin Nos. 206-04-101 and 206L-04-131, both dated September 13, 2004, pertain to the subject of this AD. (d) Replacing an affected, serial-numbered blade with an airworthy blade without an affected serial number contained in the applicability section of this AD constitutes terminating action for the requirements of this AD for that blade. (e) 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 Safety Management Group, Rotorcraft Directorate, FAA, for information about previously approved alternative methods of compliance. (f) Special flight permits may be issued in accordance with 14 CFR 21.197 and 21.199 to operate the helicopter to a location where the blade may be replaced provided that no doubler edge void or de-bond is found during any check or inspection. (g) This amendment becomes effective on November 21, 2005. Note 2: The subject of this AD is addressed in Transport Canada, Canada AD No. CF-2004-25, dated November 23, 2004. Issued in Fort Worth, Texas, on October 7, 2005. David A. Downey, Manager, Rotorcraft Directorate, Aircraft Certification Service. [FR Doc. 05-20677 Filed 10-14-05; 8:45 am] BILLING CODE 4910-13-P
Read the original on the Federal Register →
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The directive text above is reproduced from the Federal Register, a work of the United States government and in the public domain. The separation into applicability, compliance and required actions is TrackAD's.*1