AD 2017-10-12 Airworthiness Directives; Airbus Helicopters

This AD becomes effective August 15, 2017.

Compliance with Airbus Helicopters Emergency Alert Service Bulletin (EASB) No. 53.01.47, and EASB No. 53A001, both Revision 4, and both dated September 27, 2011, before the effective date of this AD is considered acceptable for compliance with the initial inspections specified in paragraphs (e)(1) and (e)(2) of this AD, but does not constitute terminating action for the repetitive inspections required by this AD.

(1) The Manager, Safety Management Group, FAA, may approve AMOCs for this AD. Send your proposal to: David Hatfield, Aviation Safety Engineer, Safety Management Group, Rotorcraft Directorate, FAA, 10101 Hillwood Pkwy, Fort Worth, TX 76177; telephone (817) 222-5116; email 9-ASW-FTW-AMOC-Requests@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) Within 15 hours time-in-service (TIS) and thereafter at intervals not to exceed 15 hours TIS, visually inspect the IGB fairing and the left- and right-hand attachment supports for a crack as shown in Figure 2 of Airbus Helicopters Emergency Alert Service Bulletin (EASB) No. 53.01.47, Revision 5, dated March 9, 2015 (EASB No. 53.01.47) or EASB No. 53A001, Revision 5, dated March 9, 2015 (EASB No. 53A001), as appropriate for your model helicopter. (i) If there is a crack in an attachment support, replace the attachment support. (ii) If there is a crack in the fairing, replace the IGB fairing with IGB fairing P/N 332A24-0322-00 in accordance with the Accomplishment Instructions, paragraph 3.B.2, of Airbus Helicopters Service Bulletin No. AS332-53.01.78, Revision 0, dated March 9, 2015 (SB No. AS332-53.01.78) or Service Bulletin No. EC225-53-041, Revision 0, dated March 9, 2015 (SB No. EC225-53-041), as appropriate for your model helicopter. (2) For helicopters with IGB fairing P/N 332A24-0303-05XX or P/N 332A24-0303-06XX, within 15 hours TIS and thereafter at intervals not to exceed 15 hours TIS, visually inspect for a crack in the fairing gutter as shown in Figure 1 of EASB No. 53.01.47 or EASB No. 53A001. If there is a crack in the fairing gutter: (i) Inspect for interference and separation of the fairing gutter. If there is any interference between the gutter and the tail rotor inclined drive shaft tube, replace the tail rotor inclined drive shaft tube. If there is any interference between the gutter and a hydraulic pipe, repair or replace the hydraulic pipe. If there is any interference between the gutter and the flight controls, repair the flight controls in accordance with FAA-approved procedures. If there is any separation of the gutter, remove the gutter. (ii) Replace the IGB fairing with IGB fairing P/N 332A24-0322-00 in accordance with the Accomplishment Instructions, paragraph 3.B.2, of SB No. AS332-53.01.78 or SB No. EC225-53-041. (3) Within 150 hours TIS, replace the IGB fairing P/N 332A24-0303-05XX, 332A24-0303-06XX, 332A08-1391-00, or 332A08-1391-01 with IGB fairing P/N 332A24-0322-00 in accordance with the Accomplishment Instructions, paragraph 3.B.2, of SB No. AS332-53.01.78 or SB No. EC225-53-041. (4) Replacing the IGB fairing with IGB fairing P/N 332A24-0322-00 is terminating action for the repetitive inspections required by this AD. (5) Do not install an IGB fairing P/N 332A24-0303-05XX, P/N 332A24-0303-06XX, P/N 332A08-1391-00, or P/N 332A08-1391-01 on any helicopter.

This AD defines the unsafe condition as detachment of the angle section of an IGB and subsequent interference between an IGB fairing and tail rotor inclined drive shaft. This condition could result in failure of a tail rotor drive shaft, loss of the tail rotor drive, and subsequent loss of control of the helicopter.