Airworthiness Directive · Amendment 39-11732 · Eurocopter France Model SA-365N1, AS-365N2, and SA-366G1 Helicopters
Eurocopter France Model SA-365N1, AS-365N2, and SA-366G1 Helicopters
Superseded. A later AD replaced this one: AD 2003-08-53. Comply with the one in force.
Model SA-365N1, AS-365N2, and SA-366G1 helicopters, with a tail rotor blade, part number (P/N) 365A33-2131, 365A12-0010, or 365A12-0020, all dash numbers, installed, certificated in any category.
Note 1: This AD applies to each helicopter identified in the preceding applicability provision, regardless of whether it has been otherwise modified, altered, or repaired in the area subject to the requirements of this AD. For helicopters that have been modified, altered, or repaired so that the performance of the requirements of this AD is affected, the owner/operator must request approval for an alternative method of compliance in accordance with paragraph (f) of this AD. The request should include an assessment of the effect of the modification, alteration, or repair on the unsafe condition addressed by this AD; and if the unsafe condition has not been eliminated, the request should include specific proposed actions to address it.
This amendment adopts a new airworthiness directive (AD) that applies to Eurocopter France Model SA-365N1, AS-365N2, and SA-366G1 helicopters and requires conducting inspections of each tail rotor blade for bonding separation, measuring the clearance between the tip of each tail rotor blade and the circumference of the air duct, and replacing the blade if necessary. This amendment is prompted by an inflight incident in which the tail rotor blades were significantly damaged due to bonding separation. The actions specified by this AD are intended to prevent damage to a tail rotor blade, loss of tail rotor control, and subsequent loss of control of the helicopter.
To prevent damage to a tail rotor blade (blade), loss of tail rotor control, and subsequent loss of control of the helicopter:
(a) Within 10 hours time-in-service (TIS) and thereafter prior to the first flight of each day, conduct the following visual inspection of each blade (see Figure 1):
(1) Zone A: If a blister is detected on the blade suction face, conduct a tapping test inspection on the whole blade for bonding separation. If bonding separation or a crack is found, replace the blade with an airworthy blade before further flight.
(2) Zone B: If a crack, wrinkling, or a blister is found, replace the blade with an airworthy blade before further flight.
(b) Within 10 hours TIS, conduct a tapping test inspection on each blade. If there is bonding separation, replace the blade with an airworthy blade before further flight.
Note 2: Revisions 5 of Eurocopter France Service Bulletins 05.09 and 05.00.17, both dated December 18, 1998, pertain to the subject of this AD.
(c) Thereafter, at intervals not to exceed 25 hours TIS or every 50 cycles (each takeoff and landing equals 1 cycle), whichever occurs first, conduct a tapping test inspection for bonding separation on all blades with a serial number (S/N) less than 18912, and blades, P/N 365A12-0020-00 or 365A12-0020-01, with a S/N equal to or greater than 18912. If bonding separation or a crack is found, replace the blade with an airworthy blade before further flight.
(d) Thereafter, at intervals not to exceed 100 hours TIS or 200 cycles, whichever occurs first, conduct a tapping test inspection for bonding separation on blades, P/N 365A12-0020-02 or 365A12-0020-03. If bonding separation or a crack is found, replace the blade with an airworthy blade before further flight.
(e) Within 10 hours TIS, and thereafter at intervals not to exceed 100 hours TIS or 200 cycles, whichever occurs first, measure the blade-to-air duct clearance. If the clearance is less than 3 mm, replace the blade with an airworthy blade before further flight.
