2013-18-06: Main Rotor Control

Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: PART 39--AIRWORTHINESS DIRECTIVES 0 1. The authority citation for part 39 continues to read as follows: Authority: 49 U.S.C. 106(g), 40113, 44701. Sec. 39.13 [Amended] 0 2. The FAA amends Sec. 39.13 by adding the following new airworthiness directive (AD): 2013-18-06 Bell Helicopter Textron Canada Limited: Amendment 39- 17579; Docket No. FAA-2013-0400; Directorate Identifier 2009-SW-48- AD. (a) Applicability This AD applies to Model 206A, 206B, 206L, 206L-1, 206L-3, 206L- 4, 222, 222B, 222U, 230, 407, 427, and 430 helicopters as follows, certificated in any category. (1) Model 206A, Model 206B helicopters converted from Model 206A, and Model 206B with Bellcrank Assembly, part-number (P/N) 206- 001-526-001 or 206-001-538-009; Idler Link Assembly, P/N 206-010- 336-109; or Link Assembly, P/N 206-031-589-001, installed. (2) Model 206L, Model 206L-1, Model 206L-3, and Model 206L-4 with Idler Assembly, P/N 206-001-549-101; Bellcrank Assembly, P/N 206-001-552-001; or Link Assembly, P/N 206-010-336-109, installed. (3) Model 222 and Model 222B with (i) Cyclic Link Assembly, P/N 222-010-419-110; or (ii) Bellcrank Assembly Directional Controls, P/N 222-001-734- 001 or 222-001-736-005, installed. (4) Model 222U with (i) Cyclic Link Assembly, P/N 222-010-419-110; or (ii) Bellcrank Assembly Directional Controls, P/N 222-001-734- 001 or 222-001-736-005, installed. (5) Model 230 with (i) Fitting Assembly Engine Bipod Mount, P/N 230-060-113-101, 230-060-113-102, 230-060-114-101, or 230-060-114-102; Cyclic Link Assembly P/N 222-010-419-110; or (ii) Bellcrank Assembly Directional Controls, P/N 222-001-734- 001, or 222-001-736-005, installed. (6) Model 407 with (i) Bearing and Liner Assembly, P/N 406-010-417-101; Cyclic Mixer Follower Assembly, P/N 407-001-325-101; Bellcrank Assembly, P/ N 407-001-524-105, 407-001-524-109, 407-001-526-105, 407-001-526- 109, 407-001-528-101, or 407-001-528-105; or (ii) Beam Assembly, P/N 407-001-723-101, installed. (7) Model 427 with Swashplate Lateral Link Assembly (upper and lower bearing), P/N 427-001-021-101; Swashplate Longitudinal Link Assembly (upper and lower bearing), P/N 427-001-022-101; Transmission Mounted Longitudinal Bellcrank Assembly (pivot bearing), P/N 427-001-521-105/-109; Transmission Mounted Lateral Bellcrank Assembly (pivot bearing), P/N 427-001-520-109/-113; or Bearing and [[Page 56150]] Liner (lower drive link bearing), P/N 406-010-417-109, installed. (8) Model 427 with Tail Rotor Actuator Output Idler, P/N 427- 001-723-101, installed. (9) Model 430 with (i) Fitting Assembly Engine Bipod Mount, P/N 230-060-113-101, 230-060-113-102, 230-060-114-101, or 230-060-114-102; Bearing Assembly M/R Rotating Controls, P/N 430-010-449-101; Rod End Assembly Lift link, P/N 430-010-204-101 or 430-010-204-103, or (ii) Bellcrank Assembly Directional Controls, P/N 222-001-734- 001, or 222-001-736-005, installed. (b) Unsafe Condition This AD defines the unsafe condition as bearings that may not have been staked as required and may migrate out of their proper position and limit the functionality of the affected part. This condition could result in failure of a bearing and the lever assembly in which it is installed and subsequent loss of control of the helicopter. (c) Effective Date This AD becomes effective October 17, 2013. (d) Compliance You are responsible for performing each action required by this AD within the specified compliance time unless it has already been accomplished prior to that time. (e) Required Actions (1) Perform each action required by this AD within the compliance time for each part listed in the applicability paragraph of this AD as follows: (a)(1), (a)(2), (a)(6)(i), (a)(7), and (a)(8), within 10 hours time-in-service (TIS) or 30 days, whichever occurs first; (a)(3)(i), (a)(4)(i), (a)(5)(i), and (a)(9)(i), within 5 hours TIS or 30 days, whichever occurs first; (a)(3)(ii), (a)(4)(ii), (a)(5)(ii), and (a)(9)(ii) within 150 hours TIS or 12 months, whichever occurs first; and (a)(6)(ii) within 300 hours TIS or 12 months, whichever occurs first. (2) Using a 10X or higher power magnifying glass or using a boroscope, inspect each bearing and determine if the bearing has been properly staked for each part that contains a part serial number with a prefix of either ``TI'' or ``TIFS.'' (i) If a part does not contain a serial number, inspect the bearing of that part even if that part contains a supplier marking. (ii) If you cannot access the bearing while the part is installed on the helicopter to make a determination as to whether the bearing in the part is properly staked, remove the part and inspect the bearing using a 10X or higher power magnifying glass or using a boroscope. (iii) If you find a part that is not properly staked, replace the bearing or the assembly with an airworthy bearing or assembly before further flight. (f) Alternative Methods of Compliance (AMOCs) (1) The Manager, Safety Management Group, FAA, may approve AMOCs for this AD. Send your proposal to Sharon Miles, ASW-111, Aviation Safety Engineer, Rotorcraft Directorate, Regulations and Guidance Group, 2601 Meacham Blvd., Fort Worth, Texas 76137, telephone (817) 222-5110, email [email protected]. (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. (g) Additional Information (1) Bell Alert Service Bulletin (ASB) No. 206-09-122 for Models 206A and 206B; No. 206L-09-156 for Models 206L, 206L-1, 206L-3, and 206L-4; No. 222-09-107 for Models 222 and 222B; No. 222U-09-78 for Model 222U; No. 230-09-39 for Model 230; No. 407-09-88 for Model 407; No. 427-09-25 for Model 427; and No. 430-09-42 for Model 430, all dated April 7, 2009, which are not incorporated by reference, contain 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 the referenced service information at the FAA, Office of the Regional Counsel, Southwest Region, 2601 Meacham Blvd., Room 663, Fort Worth, Texas 76137. (2) The subject of this AD is addressed in Transport Canada Civil Aviation AD No. CF-2009-32, dated July 24, 2009, which may be reviewed in the AD docket on the Internet at http://www.regulations.gov. (h) Subject Joint Aircraft System/Component (JASC) Code: 6700 Rotorcraft Flight Controls and 6710 Main Rotor Control.