AD 2003-08-53 Airworthiness Directives; Eurocopter France Model SA-365N1, AS365-N2, AS 365 N3, and SA-366G1 Helicopters

Models named: SA-365N1, AS365-N2, AS 365 N3, SA-366G1. Read the applicability below — it usually turns on serial or part numbers too.

Model SA-365N1, AS365-N2, AS 365 N3, and SA-366G1 helicopters, with a tail rotor blade (blade), part number 365A33-2131-all dash numbers; 365A12-0010-all dash numbers; or 365A12-0020-00, -01, -02, or -03; installed, certificated in any category.

Required as indicated, unless accomplished previously. To prevent failure of a blade, loss of tail rotor control, and subsequent loss of control of the helicopter, accomplish the following: (a) Within 10 hours time-in-service (TIS) and thereafter before the first flight of each day, visually check each blade for a crack, blister, or wrinkling. An owner/operator (pilot), holding at least a private pilot certificate, may perform the visual check and must enter compliance into the aircraft maintenance records in accordance with 14 CFR sections 43.11 and 91.417(a)(2)(v)). See Figure 1 as follows: BILLING CODE 4910-13-P ER05JN03.000 BILLING CODE 4910-13-C (b) If a crack, blister, or wrinkling is found as a result of the visual check, accomplish the following before further flight (see Figure 1 of this AD): (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. (i) For blades, P/N 365A33-2131-all dash numbers, 365A12-0010-all dash numbers, and 365A12-0020-00, and -01, if bonding separation or a crack is found, replace the blade with an airworthy blade before further flight. (ii) For blades, P/N 365A12-0020-02, and -03, if bonding separation exceeds 900 mm 2 in a 30 x 30 mm square or if there is a crack, 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. (c) Within 10 hours TIS, conduct a tapping test inspection on each blade. If there is bonding separation that exceeds the criteria in paragraphs b(1)(i) and b(1)(ii) of this AD, replace the blade with an airworthy blade before further flight. Note 1: Edition No. 1, Revision No. 0, of Eurocopter France Service Bulletin Nos. 05.09 and 05.00.17, both dated April 16, 2003, pertain to the subject of this AD. (1) 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. (2) Thereafter, at intervals not to exceed 25 hours TIS, conduct a tapping test inspection for bonding separation on blades, P/N 365A12-0020-02 or 365A12-0020-03, in Zone A as depicted in Figure 1 of this AD. (i) If bonding separation exceeds the criteria specified in paragraph (b)(1)(ii) of this AD or if a crack is found, replace the blade with an airworthy blade before further flight. (ii) If bonding separation is present and within tolerance of the criteria specified in paragraph (b)(1)(ii) of this AD, conduct a tapping test before the first flight of the day and as often as necessary during the day ensuring that the TIS between tapping tests does not exceed 10 hours TIS between tapping tests. (iii) Within 25 hours TIS after the discovery of skin debonding in Zone A, remove and replace the blade with an airworthy blade. (3) 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, in Zone B as depicted in Figure 1 of this AD. If a crack, wrinkling, or a blister is found, replace the blade with an airworthy blade before further flight. (d) 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. (e) For blades, P/N 365A12-0020-02 or 365A12-0020-03, with a S/N equal to or greater than 32944, except for S/N 32963 through 33091, S/N 33116 through 33187, or S/N 33232 through 33319: (1) Within 10 hours TIS, replace blades with 150 or more hours TIS with an airworthy blade. (2) On or before 160 hours TIS, replace blades with less than 150 hours TIS with an airworthy blade. (f) This AD revises the Limitations section of the maintenance manual by establishing a 160-hour TIS life limit for blades, P/N 365A12-0020-02 and 365A12-0020-03, with a S/N equal to or greater than 32944, except for S/N 32963 through 33091, S/N 33116 through 33187, and S/N 33232 through 33319. (g) To request a different method of compliance or a different compliance time for this AD, follow the procedures in 14 CFR 39.19. Contact the Regulations Group, Rotorcraft Directorate, FAA, for information about previously approved alternative methods of compliance. (h) This amendment becomes effective on June 20, 2003, to all persons except those persons to whom it was made immediately effective by Emergency AD 2003-08-53, issued April 23, 2003, which contained the requirements of this amendment. Note 2: The subject of this AD is addressed in Direction Generale De L'Aviation Civile (France) AD Nos. T2003-155(A) and T2003-156(A), both dated April 17, 2003. Issued in Fort Worth, Texas, on May 28, 2003. David A. Downey, Manager, Rotorcraft Directorate, Aircraft Certification Service. [FR Doc. 03-14134 Filed 6-4-03; 8:45 am] BILLING CODE 4910-13-P