AD 2015-11-06

This AD applies to Model EC 155B, EC155B1, SA-365N, SA-365N1, AS-365N2, AS 365 N3, and SA-366G1 helicopters, except helicopters with modification (MOD) 0767B65 installed, certificated in any category.

This AD defines the unsafe condition as inadvertent locking and unlocking of the collective pitch lever, which could result in subsequent loss of control of the helicopter.

This AD supersedes AD 2013-18-01, Amendment 39-17574 (78 FR 56599, September 13, 2013).

This AD becomes effective July 13, 2015.

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.

Within 50 hours time-in-service:

(1) For Model EC 155B and EC155B1 helicopters:

(i) Lock the collective pitch lever, and using a spring scale, measure the load (G) required to unlock the pilot's collective pitch lever as depicted in Figure 1, Detail B of Eurocopter Alert Service Bulletin (ASB) No. 67A007, Revision 1, dated February 25, 2009 (ASB 67A007).

(ii) If the collective pitch lever unlocks at a load less than 11 deca Newtons (daN) (24.7 lbs) or greater than 14 daN (31.5 lbs), before further flight, adjust the collective pitch lever restraining tab (F) using the oblong holes.

(iii) Set the collective pitch lever to the “low pitch” position and hold it in this position, without forcing it downwards.

(iv) Measure the clearance (J1) between the locking pin of the collective pitch lever (C) and the L-section of the restraining tab (F) as depicted in Figure 1, Detail A of ASB 67A007.

(v) If the clearance between the locking pin of the collective pitch lever and the L-section of the restraining tab is less than 3 millimeters (mm), before further flight, remove the restraining tab, clamp the restraining tab (F) in a vice with soft jaws, and gradually apply a load (H) to ensure a clearance of 3 mm or more, as depicted in Figure 1, Detail K of ASB 67A007.

(2) For Model SA-365N, SA-365N1, AS-365N2, and AS 365 N3 helicopters:

(i) Completely loosen the friction, lock the collective pitch lever, and using a spring scale, measure the load (G) required to unlock the pilot's collective pitch lever as depicted in Figure 1, Detail B of Eurocopter ASB No. 67.00.10, Revision 1, dated February 25, 2009 (ASB 67.00.10).

(ii) If the collective pitch lever unlocks at a load less than 5 daN (11.3 lbs) or greater than 14 daN (31.5 lbs), before further flight, adjust the collective pitch lever restraining tab (F) using the oblong holes and adjust the collective link rods as described in the Accomplishment Instructions, paragraph 2.B.4., of ASB 67.00.10.

(iii) Set the collective pitch lever to the “low pitch” position and hold it in this position, without forcing it downwards.

(iv) Tighten the friction lock and measure the clearance (J1) between the locking pin of the collective pitch lever (C) and the L-section of the restraining tab (F) as depicted in Figure 1, Detail A of ASB 67.00.10.

(v) If the clearance between the locking pin of the collective pitch lever and the L-section of the restraining tab is less than 3 mm, before further flight, remove the restraining tab, clamp the restraining tab (F) in a vice with soft jaws, and gradually apply a load (H) to ensure a clearance of 3 mm or more, as depicted in Figure 1, Detail K, of ASB 67.00.10.

(3) For Model SA-366G1 helicopters:

(i) Completely loosen the friction, lock the collective pitch lever, and using a spring scale, measure the load (G) required to unlock the pilot's collective pitch lever as depicted in Figure 1, Detail B of Eurocopter ASB No. 67.05, Revision 1, dated February 25, 2009 (ASB 67.05).

(ii) If the collective pitch lever unlocks at a load less than 5 daN (11.3 lbs) or greater than 14 daN (31.5 lbs), before further flight, adjust the collective pitch lever restraining tab (F) using the oblong holes and adjust the collective link rods as described in the Accomplishment Instructions, paragraph 2.B.4., of ASB 67.05.

(iii) Set the collective pitch lever to the “low pitch” position and hold it in this position, without forcing it downwards.

(iv) Tighten the friction lock and measure the clearance (J1) between the locking pin of the collective pitch lever (C) and the L-section of the restraining tab (F) as depicted in Figure 1, Detail A, of ASB 67.05.

(v) If the clearance between the locking pin of the collective pitch lever and the L-section of the restraining tab is less than 3 mm, before further flight, remove the restraining tab, clamp the restraining tab (F) in a vice with soft jaws, and gradually apply a load (H) to ensure a clearance of 3 mm or more, as depicted in Figure 1, Detail K, of ASB 67.05.

(1) The Manager, Safety Management Group, FAA, may approve AMOCs for this AD. Send your proposal to: Matt Wilbanks, Aviation Safety Engineer, Regulations and Policy Group, Rotorcraft Directorate, FAA, 2601 Meacham Blvd., Fort Worth, Texas 76137; telephone (817) 222-5110; email matt.wilbanks@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.

(1) Eurocopter Alert Service Bulletin (ASB) No. 67.00.12, Revision 0, dated February 25, 2009; ASB No. 67.07, Revision 0, dated February 25, 2009; and ASB No. 67-009, Revision 1, dated July 19, 2010, which are not incorporated by reference, contain additional information about this AD. For service information identified in this AD, contact Airbus Helicopters, Inc., 2701 N. Forum Drive, Grand Prairie, Texas 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 European Aviation Safety Agency (EASA) AD No. 2011-0154, dated August 22, 2011. You may view the EASA AD on the Internet at http://www.regulations.gov in Docket No. FAA-2014-0464.

Joint Aircraft Service Component (JASC) Code: 6710, Main Rotor Control.

(1) The Director of the Federal Register approved the incorporation by reference (IBR) of the service information listed in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.

(2) You must use this service information as applicable to do the actions required by this AD, unless the AD specifies otherwise.

(3) The following service information was approved for IBR on October 18, 2013, (78 FR 56599, September 13, 2013).

(i) Eurocopter Alert Service Bulletin No. 67.00.10, Revision 1, dated February 25, 2009.

(ii) Eurocopter Alert Service Bulletin No. 67.05, Revision 1, dated February 25, 2009.

(iii) Eurocopter Alert Service Bulletin No. 67A007, Revision 1, dated February 25, 2009.

(4) For Eurocopter service information identified in this AD, contact Airbus Helicopters, Inc., 2701 N. Forum Drive, Grand Prairie, Texas 75052; telephone (972) 641-0000 or (800) 232-0323; fax (972) 641-3775; or at http://www.airbushelicopters.com/techpub.

(5) You may view this service information at FAA, Office of the Regional Counsel, Southwest Region, 2601 Meacham Blvd., Room 663, Fort Worth, Texas 76137. For information on the availability of this material at the FAA, call (817) 222-5110.

(6) You may view this service information that is incorporated by reference at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call (202) 741-6030, or go to: http://www.archives.gov/federal-register/cfr/ibr-locations.html.