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Federal Register / Vol. 86, No. 131 / Tuesday, July 13, 2021 / Rules and Regulations
of business or by the means identified in the ADDRESSES section.
Differences Between This AD and the EASA AD
Where EASA AD 20150017 refers to its effective date, this AD requires using the effective date of the FAA AD. Where EASA AD 20150017 specifies this unsafe condition for Airbus Helicopters Deutschland GmbH Model BO105 A, BO105 C, BO105 D, BO105 S, and BO105 LS A3 helicopters, this AD does not include Model BO105 D
helicopters, because this model is not FAA type-certificated. Where EASA AD
20150017 specifies replacing an affected part, this AD requires removing the part from service. Where the service information referenced in the EASA AD
refers to calendar time for certain actions, this AD uses hours time-inservice instead. The EASA AD allows a tolerance to certain compliance times, whereas this AD does not. The EASA
AD requires using service information to accomplish the preflight checks of the control grip with coil cable, whereas this AD requires visually checking the condition of the control grip and coiled cable for mechanical damage including deformed or damaged switches, damaged housing, abrasion, cracks, and cuts instead. The owner/operator pilot may perform the required visual checks but must enter compliance with the applicable paragraph of this AD in the helicopter maintenance records in accordance with 14 CFR 43.9a1
through 4 and 91.417a2v. A pilot may perform these checks because they only involve visually checking affected control grips with coiled cable. This action can be performed equally well by a pilot or a mechanic. This check is an exception to the FAAs standard maintenance regulations.

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Interim Action The FAA considers this AD interim action. If final action is later identified, the FAA might consider further rulemaking then.
Costs of Compliance The FAA estimates that this AD
affects 20 helicopters of U.S. Registry.
Labor rates are estimated at $85 per work-hour. Based on these numbers, the FAA estimates that operators may incur the following costs in order to comply with this AD.
Inspecting the hoist control grip with coiled cable takes up to one quarter work-hour for an estimated cost of $21
per helicopter and $420 for the U.S.
fleet, per inspection cycle. Replacing the hoist control grip takes about 1 workhour and parts cost $1,956 for an
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estimated cost of $2,041 per helicopter.
Replacing the coiled cable takes about 2
work-hours and parts cost $1,858 for an estimated cost of $2,028 per helicopter.
Deactivation of the cable cutter function takes about 1 work hour and parts cost about $26 for an estimated cost $111 per hoist control grip.
Authority for This Rulemaking Title 49 of the United States Code specifies the FAAs authority to issue rules on aviation safety. Subtitle I, section 106, describes the authority of the FAA Administrator. Subtitle VII:
Aviation Programs, describes in more detail the scope of the Agencys authority.
The FAA is issuing this rulemaking under the authority described in Subtitle VII, Part A, Subpart III, Section 44701: General requirements. Under that section, Congress charges the FAA
with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce.
This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action.
Regulatory Findings This AD will not have federalism implications under Executive Order 13132. This AD will not have a substantial direct effect on the States, on the relationship between the national government and the States, or on the distribution of power and responsibilities among the various levels of government.
For the reasons discussed above, I
certify that this AD:
1 Is not a significant regulatory action under Executive Order 12866, 2 Will not affect intrastate aviation in Alaska, and 3 Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety.
The Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows:

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PART 39AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:

Authority: 49 U.S.C. 106g, 40113, 44701.
39.13

Amended
2. The FAA amends 39.13 by adding the following new airworthiness directive:

20211314 Airbus Helicopters Deutschland GmbH AHD: Amendment 3921619; Docket No. FAA20210308;
Project Identifier MCAI202000594R.
a Effective Date This airworthiness directive AD is effective August 17, 2021.
b Affected ADs None.
c Applicability This AD applies to Airbus Helicopters Deutschland GmbH AHD Model BO105A, BO105C, BO105S, and BO105LS A3
helicopters, certificated in any category, as identified in European Aviation Safety Agency now European Union Aviation Safety Agency EASA AD 20150017 dated February 4, 2015 EASA AD 20150017.
d Subject Joint Aircraft System Component JASC
Code: 2500, Cabin Equipment/Furnishings.
e Reason This AD was prompted by uncommanded activation of the hoist cable cutter function on an MBBBK117 C1 helicopter which prompted a design review of the BO105 hoist control grip with coiled cable. The FAA is issuing this AD to prevent uncommanded cutting of the hoist cable and subsequent injury to persons being lifted by the hoist and injury to persons on the ground.
f Compliance Comply with this AD within the compliance times specified, unless already done.
g Requirements 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 20150017.
h Exceptions to EASA AD 20150017
1 Where EASA AD 20150017 refers to its effective date, this AD requires using the effective date of this AD.
2 Where Note 1 of EASA AD 20150017
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-inservice.
4 Where paragraph 4 of EASA AD 2015
0017 specifies a compliance time of within
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