2011-22-05 R1: Tail rotor control system

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 removing Airworthiness Directive (AD) 2011-22-05, Amendment 39-16847 (76 FR 70046, November 10, 2011), and adding the following new AD: 2011-22-05 R1 Airbus Helicopters (Type Certificate Previously Held by Eurocopter France) (Airbus Helicopters): Amendment 39-17765; Docket No. FAA-2011-1158; Directorate Identifier 2010-SW-018-AD. (a) Applicability This AD applies to Airbus Model AS350B, B1, B2, B3, BA, C, D, D1; and Model AS355E, F, F1, F2, N, and NP helicopters; with tail rotor (T/R) pitch control rod (control rod), part number (P/N) 350A33-2100-00, -01, -02, -03, -04; P/N 350A33-2121-00, -01, -02;P/ N 350A33-2143-00; or P/N 350A33-2145-00 or -01, installed; certificated in any category. (b) Unsafe Condition This AD defines the unsafe condition as excessive play in the control rod. This condition could result in failure of a T/R control rod, loss of T/R control, and subsequent loss of control of the helicopter. (c) Affected ADs This AD revises AD 2011-22-05, Amendment 39-16847 (76 FR 70046, November 10, 2011). (d) Effective Date This AD becomes effective April 17, 2014. (e) 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. (f) Required Actions (1) Within 30 hours time-in-service (TIS) and, if no bearing play is detected, thereafter at intervals not to exceed 30 hours TIS, place the T/R pedals in the neutral position. If the helicopter is fitted with a T/R load compensator, discharge the accumulator asdescribed in the rotorcraft flight manual. Check the control rod bearing (bearing) for play on the helicopter, by observation and feel, by slightly moving the T/R blade in the flapping axis while monitoring the bearing for movement. See the following Figure 1 to Paragraph (f) of this AD. The actions required by this paragraph may be performed by the owner/operator (pilot) holding at least a private pilot certificate, and must be entered into the helicopter maintenance records showing compliance with this AD in accordance with 14 CFR 43.9(a)(1)-(4) and 14 CFR 91.417(a)(2)(v). The record must be maintained as required by 14 CFR 91.417, 121.380, or 135.439. BILLING CODE 4910-13-P [[Page 14171]] [GRAPHIC] [TIFF OMITTED] TR13MR14.000 (2) If a pilot or mechanic detects play in the bearing, before the next flight, a mechanic must remove the control rod from the helicopter, and using a dial indicator, measure the bearing wear according to the following and as shown in Figures 2and 3 to Paragraph (f) of this AD: [[Page 14172]] [GRAPHIC] [TIFF OMITTED] TR13MR14.001 [[Page 14173]] [GRAPHIC] [TIFF OMITTED] TR13MR14.002 BILLING CODE 4910-13-C (i) Remove the control rod from the helicopter. (ii) Mount the control rod in a vise as shown in Figure 2 to Paragraph (f) of this AD. (iii) Using a dial indicator, take axial play readings by moving the spherical bearing in the direction F (up and down) as shown in Figure 2 to Paragraph (f) of this AD. (iv) Install a bolt through the bearing and secure it with a washer and nut to provide a clamping surface when the bearing is clamped in a vise. (v) Mount the control rod and bearing in a vise as shown in Figure 3 to Paragraph (f) of this AD. (vi) Using a dial indicator, take radial play measurements by moving the control rod in the direction F as shown in Figure 3 to Paragraph (f) of this AD. (vii) Record the hours of operation on each control rod. (viii) If the radial play exceeds 0.008 inch or axial play exceeds 0.016 inch, replace the control rod with an airworthy control rod before further flight. (ix) If the radial and axial play are within limits, reinstall the control rod. (x) Thereafter, at intervals not to exceed 30 hours TIS, remove the control rod and measure the bearing play with a dial indicator in accordance with paragraph (f)(2) of this AD. (g) Alternative Methods of Compliance (AMOCs) (1) The Manager, Safety Management Group, FAA, may approve AMOCs for this AD. Send your proposal to: Robert Grant, Aviation Safety Engineer, Safety Management Group, FAA, 2601 Meacham Blvd., Fort Worth, Texas 76137; telephone (817) 222-5110; email robert.grant@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. (h) Additional Information (1) Eurocopter Alert Service Bulletin (ASB) No. 05.00.60 and ASB No. 05.00.56, both Revision 0, and both dated December 9, 2009, which are not incorporated by reference, contain additional information about the subject of this AD. For service information identified in this AD, contact Airbus Helicopters, Inc., 2701 N. Forum Drive, Grand Prairie, TX 75052; telephone (972) 641-0000 or (800) 232-0323; fax (972) 641-3775; or at http://www.airbushelicopters.com/techpub. You may review a copy of the 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 the European Aviation Safety Agency (EASA) AD No. 2010-0006, dated January 7, 2010. You may view the EASA AD on the Internet at http://www.regulations.gov in Docket No. FAA-2011-1158.[[Page 14174]] (i) Subject Joint Aircraft Service Component (JASC) Code: 6720, Tail rotor control system.