This section of the FEDERAL REGISTER

contains regulatory documents having general

applicability and legal effect, most of which

are keyed to and codified in the Code of

Federal Regulations, which is published under

50 titles pursuant to 44 U.S.C. 1510.

The Code of Federal Regulations is sold by

the Superintendent of Documents.

Rules and Regulations Federal Register

36633 

Vol. 86, No. 131 

Tuesday, July 13, 2021 

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 ADs@

easa.europa.eu; 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 

blaine.williams@faa.gov. 

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 


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36634 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 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-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 43.9(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 workhour 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 

■ 1. The authority citation for part 39 

continues to read as follows: 

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

§ 39.13 [Amended] 

■ 2. The FAA amends § 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-inservice. 

(4) Where paragraph (4) of EASA AD 2015– 

0017 specifies a compliance time of ‘‘within 


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Federal Register / Vol. 86, No. 131 / Tuesday, July 13, 2021 / Rules and Regulations 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: 9-AVS-AIR730-AMOC@faa.gov. 

(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 

blaine.williams@faa.gov. 

(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 ADs@easa.europa.eu; 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 fedreg.legal@

nara.gov, 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] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2020–1033; Project 

Identifier MCAI–2020–01393–R; Amendment 

39–21622; AD 2021–13–17] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: The FAA is superseding 

Airworthiness Directive (AD) 2017–17– 

01, which applied to certain Airbus 

Helicopters Model AS332L2 and 

EC225LP helicopters. AD 2017–17–01 

required repetitive inspections of the 

main rotor blade (MRB) attachment 

pins. This AD continues to require the 

repetitive inspections of the MRB 

attachment pins, and also requires 

repetitive measurement of the 

attachment pin chamfer at certain 

intervals after corrosion removal, as 

specified in a European Aviation Safety 

Agency (now European Union Aviation 

Safety Agency) (EASA) AD, which is 

incorporated by reference. This AD was 

prompted by the FAA’s determination 

that it is necessary to measure the 

attachment pin chamfer after corrosion 

removal, that replacement of an 

attachment pin after four corrosion 

removals is no longer necessary, and 

that all Airbus Helicopters Model 

AS332L2 and EC225LP helicopters are 

affected by the unsafe condition. 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; phone: +49 

221 8999 000; email: ADs@

easa.europa.eu; 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–2020–1033. 

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–2020– 

1033; 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: 

Katherine Venegas, Aviation Safety 

Engineer, Cabin Safety, Mechanical and 

Environmental Systems Section, Los 

Angeles ACO Branch, FAA, 3960 

Paramount Boulevard, Lakewood, CA 

90712–4137; phone: 562–627–5353; 

email: katherine.venegas@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Background 

The EASA, which is the Technical 

Agent for the Member States of the 


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