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Airworthiness directives › 2016-01-15

AD 2016-01-15 Airworthiness Directives; Agusta S.p.A. Helicopters

2016-02-25
2016-01-21
39-18374
FAA-2015-1935
Airframe
—

Applicability*9

This AD becomes effective February 25, 2016.

Compliance

Special flight permits are prohibited.

Required actions

(1) The Manager, Safety Management Group, FAA, may approve AMOCs for this AD. Send your proposal to: Robert Grant, Aviation Safety Engineer, Safety Management Group, Rotorcraft Directorate, FAA, 10101 Hillwood Pkwy., Fort Worth, TX 76177; telephone (817) 222-5110; 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.

Unsafe condition

(1) Within 30 hours time-in-service (TIS) and thereafter at intervals not to exceed 300 hours TIS, using a light, inspect all visible surfaces of the left hand subfloor frame, right hand subfloor frame, and middle subfloor frame at station (STA) 2105 for a crack as shown in Figures 10 through 13 of AgustaWestland Bollettino Tecnico No. 139-311, Revision B, dated June 4, 2014 (BT 139-311). (2) If there is a crack, before further flight, install frame STA 2105 retromod part number (P/N) 3G5306P47211 by following the Compliance Instructions, Part II, paragraphs 7 through 7.10. of BT 139-311. (3) If there are no cracks, within 1200 hours TIS, install frame STA 2105 retromod P/N 3G5306P47211 by following the Compliance Instructions, Part II, paragraphs 7 through 7.10. of BT 139-311. (4) Installing frame STA 2105 retromod P/N 3G5306P47211 terminates the repetitive inspection requirements in paragraph (e)(1) of this AD.

Affected ADs

This AD defines the unsafe condition as a crack in a subfloor frame. This condition could result in failure of the pilot and co-pilot pedal support frame and subsequent loss of control of the helicopter.

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