Airworthiness directives › 2016-02-06
AD 2016-02-06 Airworthiness Directives; Bell Helicopter Textron Canada Limited
Applicability*9
This AD becomes effective February 2, 2016.
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
The subject of this AD is addressed in Transport Canada AD CF-2016-01, dated January 5, 2016. You may view the Transport Canada AD on the Internet at http://www.regulations.gov by searching for and locating it in Docket No. FAA-2016-2068.
Unsafe condition
(1) For T/R link P/N 429-012-112-101 and 429-012-112-103, within 10 hours time-in-service (TIS): (i) Remove each T/R link assembly. Prior to cleaning the T/R link bearing bores, using 10X or higher power magnification, inspect each T/R link bearing bore for aluminum oxide corrosion extruding from between the roll staked lip of the bearing outer race and the link bearing bore. Aluminum oxide corrosion appears as a white crystalline material in contrast with the black finish and any accumulated soot. An example of this corrosion is shown in Figure 1 of Bell Helicopter Alert Service Bulletin 429-15-26, dated December 7, 2015 (ASB 429-15-26). (ii) If there is any aluminum oxide corrosion, replace the T/R link before further flight. (iii) If there is no aluminum oxide corrosion, clean each T/R link bearing bore with isopropyl alcohol and inspect for pitting. (A) If there is any pitting, replace the T/R link before further flight. (B) If there is no pitting, apply corrosion preventative sealant by following the Accomplishment Instructions, paragraph 5. of Part I, of ASB 429-15-26. (2) For all T/R links listed in paragraph (a) of this AD, within 50 hours TIS and thereafter at intervals not to exceed 50 hours TIS, using 10X or higher power magnification, inspect each T/R link bearing bore for missing corrosion preventative sealant. If any corrosion preventative sealant is missing, perform the actions in paragraph (e)(1)(i) through (e)(1)(iii) of this AD before further flight. (3) Do not install T/R link P/N 429-012-112-101 or -103 on any helicopter before complying with the actions in paragraph (e)(1) of this AD.
Affected ADs
This AD defines the unsafe condition as failure of a T/R link. This condition could result in loss of T/R flight control and subsequent loss of control of the helicopter.
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