Airworthiness Directives; Airbus Helicopters Deutschland GmbH (AHD) Helicopters

[Federal Register Volume 86, Number 131 (Tuesday, July 13, 2021)]
[Rules and Regulations]
[Pages 36633-36635]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2021-14778]



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Federal Register / Vol. 86, No. 131 / Tuesday, July 13, 2021 / Rules 
and Regulations

[[Page 36633]]



DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2021-0308; Project Identifier MCAI-2020-00594-R; 
Amendment 39-21619; AD 2021-13-14]
RIN 2120-AA64


Airworthiness Directives; Airbus Helicopters Deutschland GmbH 
(AHD) Helicopters

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

-----------------------------------------------------------------------

SUMMARY: 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.

DATES: This AD is effective August 17, 2021.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of August 17, 
2021.

ADDRESSES: For material incorporated by reference (IBR) in this AD, 
contact the EASA, Konrad-Adenauer-Ufer 3, 50668 Cologne, Germany; 
telephone +49 221 8999 000; email [email protected]; internet 
www.easa.europa.eu. You may find this material on the EASA website at 
https://ad.easa.europa.eu. You may view this material at the FAA, 
Office of the Regional Counsel, Southwest Region, 10101 Hillwood Pkwy., 
Room 6N-321, Fort Worth, TX 76177. For information on the availability 
of this material at the FAA, call (817) 222-5110. It is also available 
in the AD docket on the internet at https://www.regulations.gov by 
searching for and locating Docket No. FAA-2021-0308.

Examining the AD Docket

    You may examine the AD docket on the internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2021-
0308; or in person at Docket Operations between 9 a.m. and 5 p.m., 
Monday through Friday, except Federal holidays. The AD docket contains 
this final rule, any comments received, and other information. The 
address for Docket Operations is U.S. Department of Transportation, 
Docket Operations, M-30, West Building Ground Floor, Room W12-140, 1200 
New Jersey Avenue SE, Washington, DC 20590.

FOR FURTHER INFORMATION CONTACT: Blaine Williams, Aerospace Engineer, 
Cabin Safety & Environmental Systems Section, Los Angeles ACO Branch, 
Compliance & Airworthiness Division, 3960 Paramount Blvd., Lakewood, CA 
90712; telephone (562) 627-5371; email [email protected].

SUPPLEMENTARY INFORMATION:

Background

    The EASA, which is the Technical Agent for the Member States of the 
European Union, has issued EASA AD 2015-0017, dated February 4, 2015 
(EASA AD 2015-0017), to correct an unsafe condition for certain Airbus 
Helicopters Deutschland GmbH Model BO105 A, BO105 C, BO105 D, BO105 S, 
and BO105 LS A-3 helicopters.
    The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 
CFR part 39 by adding an AD that would apply to certain Model BO-105A, 
BO-105C, BO-105S, and BO-105LS A-3 helicopters. The NPRM published in 
the Federal Register on April 19, 2021 (86 FR 20341). The NPRM 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. The NPRM proposed to 
require accomplishing the actions specified in EASA AD 2015-0017, 
described previously, as incorporated by reference, except for any 
differences identified as exceptions in the regulatory text of this 
proposed AD and except as discussed under ``Differences Between this AD 
and the EASA AD.''
    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. See the EASA AD for additional 
background information.

Discussion of Final Airworthiness Directive

Comments

    The FAA gave the public the opportunity to participate in 
developing this final rule. The FAA received no comments on the NPRM or 
on the determination of the cost to the public.

Conclusion

    The FAA reviewed the relevant data and determined that air safety 
and the public interest require adopting this final rule as proposed in 
the NPRM.

Related Service Information Under 1 CFR Part 51

    For Model BO105 C, BO105 D, BO105 S, and BO105 LS A-3 helicopters, 
EASA AD 2015-0017 specifies to perform an initial and recurring 
inspections of the hoist control grip with coiled cable of the hoist 
and depending on the results, replacing the hoist control grip with 
coiled cable with a serviceable part. EASA AD 2015-0017 also specifies 
to replace any hoist control grip with coiled cable that has exceeded 
10 years since first installation or since last overhaul and to 
deactivate the cable cutter function in accordance with referenced 
service information.
    EASA AD 2015-0017 also specifies to not operate the hoist on any of 
the Model BO105 A, BO105 D, variant BO105 D, and BO105 DS helicopters. 
For Model BO105 helicopters, except for BO105 D, variant BO105 D, and 
BO105 DS helicopters, EASA specifies to amend the helicopter flight 
manual (FM) to incorporate the temporary revision as specified in Table 
1 of the EASA AD.
    This material is reasonably available because the interested 
parties have access to it through their normal course

[[Page 36634]]

of business or by the means identified in the ADDRESSES section.

Differences Between This AD and the EASA AD

    Where EASA AD 2015-0017 refers to its effective date, this AD 
requires using the effective date of the FAA AD. Where EASA AD 2015-
0017 specifies this unsafe condition for Airbus Helicopters Deutschland 
GmbH Model BO105 A, BO105 C, BO105 D, BO105 S, and BO105 LS A-3 
helicopters, this AD does not include Model BO-105 D helicopters, 
because this model is not FAA type-certificated. Where EASA AD 2015-
0017 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-in-service 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 43.9(a)(1) through (4) and 91.417(a)(2)(v). 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 FAA's standard maintenance regulations.

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 work-hour and parts cost $1,956 for an 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 FAA's 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 Agency's 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:

PART 39--AIRWORTHINESS DIRECTIVES

0
1. The authority citation for part 39 continues to read as follows:

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


Sec.  39.13  [Amended]

0
2. The FAA amends Sec.  39.13 by adding the following new airworthiness 
directive:

2021-13-14 Airbus Helicopters Deutschland GmbH (AHD): Amendment 39-
21619; Docket No. FAA-2021-0308; Project Identifier MCAI-2020-00594-
R.

(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 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).

(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 MBB-BK117 C-1 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 2015-0017.

(h) Exceptions to 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

[[Page 36635]]

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.

(i) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, International Validation Branch, FAA, has the 
authority to approve AMOCs for this AD, if requested using the 
procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, 
send your request to your principal inspector or local Flight 
Standards District Office, as appropriate. If sending information 
directly to the manager of the International Validation Branch, send 
it to the attention of the person identified in paragraph (j) of 
this AD. Information may be emailed to: [email protected].
    (2) Before using any approved AMOC, notify your appropriate 
principal inspector, or lacking a principal inspector, the manager 
of the local flight standards district office/certificate holding 
district office.

(j) Related Information

    For more information about this AD, contact Blaine Williams, 
Aerospace Engineer, Cabin Safety & Environmental Systems Section, 
Los Angeles ACO Branch, Compliance & Airworthiness Division, 3960 
Paramount Blvd., Lakewood, CA 90712; telephone (562) 627-5371; email 
[email protected].

(k) Material Incorporated by Reference

    (1) The Director of the Federal Register approved the 
incorporation by reference (IBR) of the service information listed 
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
    (2) You must use this service information as applicable to do 
the actions required by this AD, unless this AD specifies otherwise.
    (i) European Aviation Safety Agency (EASA) AD 2015-0017, dated 
February 4, 2015.
    (ii) [Reserved]
    (3) For EASA AD 2015-0017, contact the EASA, Konrad-Adenauer-
Ufer 3, 50668 Cologne, Germany; telephone +49 221 8999 000; email 
[email protected]; internet www.easa.europa.eu. You may find this 
EASA AD on the EASA website at https://ad.easa.europa.eu.
    (4) You may view this service information at the FAA, Office of 
the Regional Counsel, Southwest Region, 10101 Hillwood Pkwy., Room 
6N-321, Fort Worth, TX 76177. For information on the availability of 
this material at the FAA, call (817) 222-5110. This material may be 
found in the AD docket on the internet at https://www.regulations.gov by searching for and locating Docket No. FAA-
2021-0308.
    (5) You may view this material that is incorporated by reference 
at the National Archives and Records Administration (NARA). For 
information on the availability of this material at NARA, email 
[email protected], or go to https://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued on June 16, 2021.
Lance T. Gant,
Director, Compliance & Airworthiness Division, Aircraft Certification 
Service.
[FR Doc. 2021-14778 Filed 7-12-21; 8:45 am]
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