Airworthiness Directive · Amendment 39-16063 · Eurocopter France (ECF) Model AS332C, AS332L, AS332L1, AS332L2, SA330F, SA330G, and SA330J Helicopters
Eurocopter France (ECF) Model AS332C, AS332L, AS332L1, AS332L2, SA330F, SA330G, and SA330J Helicopters
This AD applies to Model AS332C, AS332L, AS332L1, AS332L2, SA330F, SA330G, and SA330J helicopters with a main rotor blade (blade) de-icing system distributor retaining clamp (clamp), part number (P/N) 225000-18454, or P/N D18454, installed, certificated in any category.
We are adopting a new airworthiness directive (AD) for the specified ECF helicopters. This AD results from a mandatory continuing airworthiness information (MCAI) AD issued by the European Aviation Safety Agency (EASA), the Technical Agent for the aviation authority of France. The MCAI AD states there have been two cases of failure of the screw that secures the main rotor blade (blade) deicing system distributor retaining clamp (clamp). Analysis revealed that these failures were the result of insufficient clearance of the screw and the clamp assembly causing the screw to bend and also by some screws having nonconforming material hardness. Also, some of the screw heads were missing a lock-wiring hole preventing the use of lock-wiring between the screw head and the nut. These actions are intended to detect failure of the clamp attachment screw leading to damage to the main or tail rotor blades and risk to persons on the ground by impact from a departed screw or clamp.
Inspect each clamp within 50 hours time-in-service (TIS), without exceeding 3 months, for each clamp with an attachment screw that is not welded to the barrel, or within 20 hours TIS, without exceeding 1 month, for each clamp with an attachment screw that is welded to the barrel as follows, unless already accomplished:
(1) Remove the clamp from the distributor, as depicted in Figure 2 and by following paragraph 2.B.2.a. of the Accomplishment Instructions, in Eurocopter Emergency Alert Service Bulletin No. 30.00.66, Revision 1, dated August 21, 2008 (ASB 332) for the Model AS332 C, C1, L, L1 helicopters or Eurocopter Emergency Alert Service Bulletin No. 30.20, Revision 1, dated August 21, 2008 (ASB 330) for the Model SA330 J, F, and G helicopters.
Note: The service bulletin references 3 documents: No. 30.00.66 for Model AS332 helicopters, No. 30.00.26 for Model AS532 helicopters, and No. 30.20 for Model SA330 helicopters. This AD does not reference No. 30.00.26 because the Model AS532 helicopters are not type certificated in the United States. 14 CFR part 39 only allows the FAA to issue ADs against type certificated products.
(2) Measure the clearance between the screw head and the clamp as depicted in Figure 1 and by following paragraph 2.B.2.b. of the Accomplishment Instructions of ASB 332 or ASB 330, as appropriate for your model helicopter. If the clearance is less than 1 millimeter, rework the clamp until the clearance is between 1 and 2 millimeters.
(3) Inspect the screw for a crack and for a safety-wire hole in the head of the screw as depicted in Figure 2 and by following paragraph 2.B.2.c. of the Accomplishment Instructions of ASB 332 or ASB 330, as appropriate for your model helicopter.
(i) If there is a crack in the screw, before further flight, replace the screw.
(ii) If there is no safety-wire hole in the head of the screw, before further flight, either replace the screw with a screw having a safety wire hole or drill a hole as depicted in Figure 2, Detail D, of either ASB 332 or ASB 330, as appropriate for your model helicopter.
(4) If there is a P/N on the clamp, vibro-engrave the letter “V” after the P/N on the band of the clamp, as depicted in Detail G of Figure 4 of either ASB 332 or ASB 330, as appropriate for your model helicopter. If there is no P/N marked on the clamp, vibro-engrave the letter “V” on the band of the clamp near to the screw head.
(5) Safety the clamp as shown in Figure 3 of either ASB 332 or ASB 330, as appropriate for your model helicopter.
We refer to the actions required by the AD as inspections rather than checks.
Alternative Methods of Compliance (AMOCs): The Manager, Safety Management Group, ATTN: DOT/FAA Southwest Region, J. R. Holton, Jr., ASW-112, Aviation Safety Engineer, Rotorcraft Directorate, 2601 Meacham Blvd., Fort Worth, Texas 76137, telephone (817) 222-4964, fax (817) 222-5961, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19.
