Airworthiness directives › 2012-10-01
AD 2012-10-01 Airworthiness Directives; Bell Helicopter Textron Canada Limited Helicopters
Applicability*9
This AD becomes effective June 29, 2012.
Compliance
(1) The Manager, Safety Management Group, FAA, may approve AMOCs for this AD. Send your proposal to: Sharon Miles, Aviation Safety Engineer, Regulations and Policy Group, Rotorcraft Directorate, FAA, 2601 Meacham Blvd., Fort Worth, Texas 76137; telephone (817) 222-5110; email sharon.y.miles@faa.gov. (2) For operations conducted under a 14 CFR part 119 operating certificate or under 14 CFR part 91, subpart K, we suggest that you notify your principal inspector, or lacking a principal inspector, the manager of the local flight standards district office or certificate holding district office, before operating any aircraft complying with this AD through an AMOC.
Required actions
The subject of this AD is addressed in Transport Canada AD CF-2010-32, dated September 30, 2010.
Unsafe condition
(1) Within 150 hours time-in-service (TIS) or 90 days, whichever occurs first, replace the tailboom attachment hardware (attachment hardware) as follows: (i) Remove the left upper bolt, washers, and nut. (ii) Install a new bolt, part number (P/N) NAS627-27; washer, P/N 140-007-29S25E6; washer(s), P/N NAS1149G0732P; and new nut, P/N 42FLW-720 in accordance with paragraphs 5.a) through 5.d) of the Accomplishment Instructions in BHTC Alert Service Bulletin No. 427-10-31, dated March 1, 2010 (ASB). (iii) Run the nut onto the threads of the mating bolt with a torque wrench and measure the existing tare torque. Any bolt and nut used must have a minimum tare torque value of 14 inch/lbs. (iv) Torque the nut in accordance with paragraphs 5.f) and 5.g) of the ASB. (v) Coat the bolt head, nut, and washers with appropriate corrosion preventive compound to seal the joint. (vi) At each remaining attachment location, remove the bolt, washers, and nut, and install the attachment hardware in accordance with paragraphs (e)(1)(ii) through (e)(1)(v) of this AD. (2) After installation of the new attachment hardware, at intervals of not less than 1 hour TIS but not exceeding 5 hours TIS, determine the torque of each nut until the torque stabilizes at each attachment location. Thereafter, at intervals not to exceed 300 hours TIS, determine the torque of each nut. When determining the torque, it is acceptable to use the minimum tare torque of 14 inch/lbs (1.58 Nm) added to the minimum torque range of 550-560 inch/lbs (62.1 to 63.3 Nm). If you remove corrosion preventative compound during the torquing, recoat the bolt head, nut, and washers with appropriate corrosion preventive compound to seal the joint.
Affected ADs
This AD defines the unsafe condition as an over-torque of the tailboom attachment bolt (bolt). This condition could result in bolt failure, loss of the tailboom, and subsequent loss of control of the helicopter.
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