Airworthiness directives › 2017-15-13
AD 2017-15-13 Airworthiness Directives; Bell Helicopter Textron Canada Limited
Applicability*9
This AD becomes effective August 31, 2017.
Compliance
(1) The Manager, Safety Management Group, FAA, may approve AMOCs for this AD. Send your proposal to: Matt Fuller, Senior Aviation Safety Engineer, Safety Management Group, Rotorcraft Directorate, FAA, 10101 Hillwood Pkwy., Fort Worth, TX 76177; telephone (817) 222-5110; email 9-ASW-FTW-AMOC-Requests@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
(1) Bell 429 Maintenance Manual BHT-429-MM-1, Volume 1, Chapter 4, Revision 9, dated January 6, 2012, which is not incorporated by reference, contains additional information about the subject of this AD. For service information identified in this AD, contact Bell Helicopter Textron Canada Limited, 12,800 Rue de l'Avenir, Mirabel, Quebec J7J1R4; telephone (450) 437-2862 or (800) 363-8023; fax (450) 433-0272; or at http://www.bellcustomer.com/files/. You may review a copy of the service information at the FAA, Office of the Regional Counsel, Southwest Region, 10101 Hillwood Pkwy, Room 6N-321, Fort Worth, TX 76177. (2) The subject of this AD is addressed in Transport Canada AD No. CF-2014-28, dated August 19, 2014. You may view the Transport Canada AD on the Internet at http://www.regulations.gov in Docket No. FAA-2017-0174.
Unsafe condition
Before further flight, determine the accumulated retirement index number (RIN) for each part and remove it from service if it has reached or exceeded its life limit as follows. Thereafter, remove each part from service on or before reaching its life limit. For purposes of this AD, a run-on landing is defined as a landing with forward ground travel of the helicopter greater than 3 feet (0.91 m) with weight on skids. (1) For Skid Tube Assembly part number (P/N) 429-700-101, 429-700-102, and 429-030-586-107: 16,000 RIN. Count 1 RIN for each landing; count 81 RIN for each run-on landing; and count 117 RIN for each autorotation landing. (2) For Forward Crosstube Assembly P/N 429-712-101: 10,000 RIN. Count 1 RIN for each landing; count 50 RIN for each run-on landing; and count 118 RIN for each autorotation landing. (3) Aft Crosstube Assembly P/N 429-723-108: 30,000 RIN. Count 1 RIN for each landing; count 32 RIN for each run-on landing; and count 186 RIN for each autorotation landing.
Affected ADs
This AD defines the unsafe condition as a landing gear part remaining in service beyond its fatigue life. This condition could result in failure of a landing gear part, failure of a landing gear skid, and subsequent loss of control of the helicopter during takeoff or landing.
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