Airworthiness Directive · Amendment 39-21619 · Cabin equipment/furnishings
Airbus Helicopters Deutschland GmbH (AHD) Helicopters
This AD applies to Airbus Helicopters Deutschland GmbH (AHD) Model BO-105A, BO-105C, BO-105S, and BO-105LS A-3 helicopters, certificated in any category, as identified in European Aviation Safety Agency (now European Union Aviation Safety Agency) (EASA) AD 2015-0017 dated February 4, 2015 (EASA AD 2015-0017).
The FAA is adopting a new airworthiness directive (AD) for certain Airbus Helicopters Deutschland GmbH (AHD) Model BO-105A, BO- 105C, BO-105S, and BO-105LS A-3 helicopters. This AD was prompted by an uncommanded activation of the hoist cable cutter function on an MBB- BK117 C-1 helicopter, which prompted a design review of the BO105 hoist control grip with coiled cable. This AD requires inspections of the hoist control grip with coiled cable and deactivation of the hoist cutter function, as specified in a European Aviation Safety Agency (now European Union Aviation Safety Agency) (EASA) AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
Except as specified in paragraph (h) of this AD: Comply with all required actions and compliance times specified in, and in accordance with, EASA AD 2015-0017.
(1) Where EASA AD 2015-0017 refers to its effective date, this AD requires using the effective date of this AD.
(2) Where Note 1 of EASA AD 2015-0017 specifies a non-cumulative compliance time tolerance of 10% for certain required compliance times, this AD does not allow this tolerance.
(3) Where paragraph (1) of EASA AD 2015-0017 specifies a compliance time of “not to exceed 30 days”, this AD requires a compliance time of within 13 hours time-in-service.
(4) Where paragraph (4) of EASA AD 2015-0017 specifies a compliance time of “within 9 months”, this AD requires a compliance time of within 108 hours time-in-service.
(5) Where paragraph (5) of EASA AD 2015-0017 specifies a compliance time of “within 3 months”, this AD requires a compliance time of within 36 hours time-in-service.
(6) Where paragraph (3) of EASA AD 2015-0017 specifies replacing a part with a serviceable part, this AD requires removing the part from service.
(7) Where the service information referenced in EASA AD 2015-0017 specifies to use tooling, equivalent tooling may be used.
(8) Where the service information referenced in paragraph (2) of EASA AD 2015-0017 specifies a visual check of the control grip coiled cable, this AD requires, before next flight after the effective date of this AD involving a hoist operation, visually checking the control grip with coiled cable for mechanical damage including deformed or damaged switches, damaged housing, abrasion, cracks, and cuts. These visual checks may be performed by the owner/operator (pilot) holding at least a private pilot certificate and must be entered into the aircraft records showing compliance with this AD in accordance with 14 CFR 43.9(a)(1) through (4) and 14 CFR 91.417(a)(2)(v). The record must be maintained as required by 14 CFR 91.417, 121.380, or 135.439.
(9) Where EASA AD 2015-0017 refers to November 10, 2014, the effective date of EASA AD 2014-0235, this AD requires using the effective date of this AD.
(10) The “Remarks” section of EASA AD 2015-0017 does not apply to this AD.
