Airworthiness directives › 2013-16-20
AD 2013-16-20 Airworthiness Directives; Eurocopter Deutschland GmbH (ECD) Helicopters
Applicability*9
This AD becomes effective September 27, 2013.
Compliance
(1) The Manager, Safety Management Group, FAA, may approve AMOCs for this AD. Send your proposal to: Jim Grigg, Manager, Rotorcraft Directorate, 2601 Meacham Blvd., Fort Worth, TX 76137, telephone (817) 222-5110, email Jim.Grigg@faa.gov. (2) For operations conducted under 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
(1) For service information identified in this AD, contact American Eurocopter Corporation, 2701 N. Forum Drive, Grand Prairie, TX 75052, telephone (972) 641-0000 or (800) 232-0323, fax (972) 641-3775, or at http://www.eurocopter.com/techpub. You may review the referenced service information at the FAA, Office of the Regional Counsel, Southwest Region, 2601 Meacham Blvd., Room 663, Fort Worth, Texas 76137. (2) The subject of this AD is addressed in European Aviation Safety Agency (EASA) AD No. 2010-0248, dated November 26, 2010. You may view the EASA AD at http://www.regulations.gov in Docket No. FAA-2013-0020.
Unsafe condition
Within 300 hours time-in-service: (1) Inspect the rigging of the power-boosted control system, referencing Figure 1 of Eurocopter Alert Service Bulletin ASB MBB BK117 C-2-67A-012, Revision 0, dated September 20, 2010 (ASB). Ensure the piston of the longitudinal actuator (right-hand side) is held in the fully extended position and the piston of the lateral actuator (left-hand side) is held in the fully retracted position against the mechanical stop. Also, ensure the gauge block is clamped between the sliding sleeve and the support tube. (2) Insert the rigging wedges with the 25.4 degree (item 8 of Figure 1 of the ASB) and 19.5 degree (item 7 of Figure 1 of the ASB) markings in the “A” side of the guide grooves of the rigging device (item 3 of Figure 1 of the ASB). (3) If the gap between the rigging wedges (items 7 and 8 of Figure 1 of the ASB) and the inner sleeves (item 9 of Figure 1 of the ASB) is closed, the rigging is correct. (4) If there is a nonparallel gap between the rigging wedges (items 7 and 8 of Figure 1 of the ASB) and the inner sleeves (item 9 of Figure 1 of the ASB), the rigging is not correct. Perform a rigging procedure.
Affected ADs
This AD defines the unsafe condition as movement of the longitudinal main rotor actuator piston after shut-down of the external pump drive, during rigging of the main rotor controls, causing an incorrect rigging result. This condition could impair freedom of movement of the upper controls and subsequently reduce control of the helicopter.
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