Airworthiness Directive · Amendment 39-15340 · Rotorcraft servo system
Eurocopter France Model AS 355 F2 and AS 355 N Helicopters
This AD applies to Eurocopter Model AS 355 F2 and AS 355 N helicopters, all serial numbers, certificated in any category.
We are adopting a new airworthiness directive (AD) for Eurocopter France Model AS 355 F2 and AS 355 N helicopters. This AD results from mandatory continuing airworthiness information (MCAI) originated by an aviation authority to identify and correct an unsafe condition on an aviation product. The European Aviation Safety Agency, the Technical Agent for France, with which we have a bilateral agreement, states in the MCAI:
Unless already done, do the following:
(1) Within the next 10 hours time-in-service (TIS), determine the part number (P/N) and the compatibility of the load compensator lever (compensator level) and the hydraulic actuator assembly (hydraulic actuator) in accordance with the Accomplishment Instructions, paragraphs 2.B.1. through 2.B.2.c. of Eurocopter AS 355 Emergency Alert Service Bulletin No. 67.00.29, Revision 1, April 27, 2007 (ASB).
Note: Instead of inspecting the rotorcraft, a review of the helicopter maintenance records along with any other applicable data (rotorcraft logbook, components list, etc.) is acceptable if each P/N can be positively determined from that review.
(2) For helicopters, Pre-Mod 072065, with an incompatible hydraulic actuator, P/N 355A75-1370-01 or P/N 355A75-1370-03, and compensator lever, P/N 355A27-0082-00:
(i) If the helicopter has NOT been operated with compensator lever, P/N 355A27-0082-00, installed, replace the compensator lever before further flight with an airworthy compensator lever, P/N 355A27-0072-00.
(ii) If the helicopter has been operated with compensator lever, P/N 355A27-0082-00, installed, within the next 10 hours time-in-service (TIS):
(A) Remove the load compensator assembly and the compensator lever, measure the diameters of the bores, inspect the swivel bearings, replace the specified hydraulic actuator components and the incompatible compensator lever and install the load compensator assembly in accordance with the applicable steps in the Accomplishment Instructions, paragraph 2.B.3.b. of the ASB.
(B) If the diameter of a bore is greater than the tolerances specified in the applicable steps in the Accomplishment Instructions, paragraph 2.B.3.b., of the ASB, replace each part that contains an out-of-tolerance bore diameter with an airworthy part that contains a bore diameter that is within the specified tolerances.
(3) For helicopters, Post-MOD 072065, with an incompatible hydraulic actuator, P/N 355A75-1370-02 or P/N 355A75-1370-04, and compensator lever, P/N 355A27-0072-00:
(i) If the helicopter has NOT been operated with compensator lever, P/N 355A27-0072-00, installed, replace the compensator lever before further flight with an airworthy compensator lever, P/N 355A27-0082-00.
(ii) If the helicopter has been operated with compensator lever, P/N 355A27-0072-00, installed, within the next 10 hours TIS, replace the compensator lever with an airworthy compensator lever, P/N 355A27-0082-00, and inspect the bolts in accordance with the applicable steps in the Accomplishment Instructions, paragraph 2.B.3.b.of the ASB.
(f) No person shall install a:
(1) Load compensator lever, P/N 355A27-0082-00, on any Model AS 355 N or AS 355 F2 helicopter Pre-MOD 072065, with hydraulic actuator assembly, P/N 355A75-1370-01 or P/N 355A75-1370-03; or a
(2) Load compensator lever, P/N 355A27-0072-00, on any Model AS 355 N or AS 355 F2 helicopter Post-MOD 072065, with hydraulic actuator assembly, P/N 355A75-1370-02 or P/N 355A75-1370-04.
The requirements of this AD must be accomplished within 10 hours TIS after the effective date of this AD. The MCAI requires accomplishment before next flight. Additionally, this AD requires that components with bore diameters outside the tolerances specified in the ASB be replaced with airworthy components with bore diameters within the specified tolerances instead of contacting the manufacturer for a “suitable repair solution.”
(i) The following provisions also apply to this AD:
(1) Alternative Methods of Compliance (AMOCs): The Manager, Safety Management Group, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. Send information to ATTN: Ed Cuevas, Aviation Safety Engineer, FAA, Rotorcraft Directorate, Safety Management Group, Fort Worth, Texas 76193-0111, telephone (817) 222-5355, fax (817) 222-5961.
(2) Airworthy Product: Use only FAA-approved corrective actions. Corrective actions are considered FAA-approved if they are approved by the State of Design Authority (or their delegated agent) if the State of Design has an appropriate bilateral agreement with the United States. You are required to assure the product is airworthy before it is returned to service.
(3) Reporting Requirements: For any reporting requirement in this AD, under the provisions of the Paperwork Reduction Act, the Office of Management and Budget (OMB) has approved the information collection requirements and has assigned OMB Control Number 2120-0056.
