Airworthiness directives › 2014-13-04
AD 2014-13-04 Airworthiness Directives; Columbia Helicopters, Inc. (Type Certificate Previously Held by Boeing Defense & Space Group) Helicopters
Applicability*9
This AD becomes effective July 15, 2014.
Compliance
(1) The Manager, Seattle Aircraft Certification Office, FAA, may approve AMOCs for this AD. Send your proposal to: 9-ANM-Seattle-ACO-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.
Required actions
Joint Aircraft Service Component (JASC) Code: 5400 and 6210 Nacelle/Pylon Structure and Main Rotor Blades.
Unsafe condition
(1) Within 50 hours time-in-service (TIS): (i) Clean and inspect each fore and aft rotor blade for a defect, damage, or a disbond in accordance with the Accomplishment Instructions, paragraph 3.A.(1)(b) through 3.A.(2)(b), of Columbia Helicopters, Inc., Service Bulletin No. 234-62-0008, Revision 1, dated December 6, 2013 (SB 234-62-0008). (ii) Using a metallic coin or tap hammer, tap inspect each rotor blade trailing edge for defect, damage, or a disbond in accordance with the Accomplishment Instructions, paragraph 3.B.(1) through 3.B.(2)(e) and Figures 1 and 2 of SB 234-62-0008. (iii) If there is any defect, damage, or a disbond, repair the blade before further flight. If the defect, damage, or disbond is beyond acceptable limits, replace the blade before further flight. (2) Within 50 hours TIS and thereafter at intervals not to exceed 100 hours TIS, inspect the aft pylon at the station 534 and 594 tension attachment fittings as follows: (i) Dye-penetrant inspect the aft pylon at the attachment fitting for a crack as shown in Figures 1, 2, and 3 and by following the Detailed Special Inspection-Dye Penetrant Method, paragraph 2.A.(2) through 2.G.(1), of Columbia Helicopters, Inc. Service Bulletin No. 234-54-0004, Revision 0, dated November 22, 2013 (SB 234-54-0004). (ii) If there is a crack, before further flight, repair or replace the aft pylon. Figures 2, 3, 4, and 5 of SB 234-54-0004 contain examples of a crack. (3) Do not install an aft pylon or a rotor blade until the requirements of paragraphs (e)(1) and (e)(2) of this AD are accomplished.
Affected ADs
This AD defines the unsafe condition as fatigue failure of aft pylon fitting attach structure combined with aft rotor blade damage. This condition could result in failure of a fore or aft rotor blade, vibration, overload of the aft pylon structure at the pylon attach fittings, departure of the aft pylon, and subsequent loss of control of the helicopter.
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