50232 Federal Register / Vol. 86, No. 171 / Wednesday, September 8, 2021 / Rules and Regulations 

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 part 39 of the Federal 

Aviation Regulations (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: 

■ a. Removing Airworthiness Directive 

2020–13–07, Amendment 39–21152 (85

FR 38312, June 26, 2020); and

■ b. Adding the following new 

airworthiness directive:

2021–17–12 Rolls-Royce Deutschland Ltd & 

Co KG (Type Certificate previously held 

by Rolls-Royce plc): Amendment 39– 

21695; Docket No. FAA–2021–0198; 

Project Identifier MCAI–2020–00950–E. 

(a) Effective Date

This airworthiness directive (AD) is

effective October 13, 2021. 

(b) Affected ADs

This AD replaces AD 2020–13–07,

Amendment 39–21152 (85 FR 38312, June 

26, 2020). 

(c) Applicability

This AD applies to Rolls-Royce

Deutschland Ltd & Co KG (RRD) (Type 

Certificate previously held by Rolls-Royce 

plc) Trent 1000–A, Trent 1000–A2, Trent 

1000–AE, Trent 1000–AE2, Trent 1000–C, 

Trent 1000–C2, Trent 1000–CE, Trent 1000– 

CE2, Trent 1000–D, Trent 1000–D2, Trent 

1000–G, Trent 1000–G2, Trent 1000–H, Trent 

1000–H2, Trent 1000–J2, Trent 1000–K2, and 

Trent 1000–L2 model turbofan engines with 

a fuel pump, part number (P/N) G5030FPU01 

or P/N TPS1000–05, installed. 

(d) Subject

Joint Aircraft System Component (JASC)

Code 7314, Engine Fuel Pump. 

(e) Unsafe Condition

This AD was prompted by the

manufacturer’s investigation into an 

unexpected reduction in fuel pump 

performance in certain high life fuel pumps 

and life-related wear-out of the internal 

components, which causes deterioration in 

fuel pump efficiency. The FAA is issuing this 

AD to prevent failure of the fuel pump, loss 

of engine thrust control and reduced control 

of the airplane. The unsafe condition, if not 

addressed, could result in failure of the fuel 

pump, loss of thrust control, and loss of the 

airplane. 

(f) Compliance

Comply with this AD within the

compliance times specified, unless already 

done. 

(g) Required Actions

Within the compliance time specified in

Planning Information, paragraph 1.D.2, of 

Rolls-Royce (RR) Alert Non-Modification 

Service Bulletin TRENT 1000 73–AK581, 

Revision 3, dated April 7, 2021 (the RR Alert 

NMSB), or within 30 days after the effective 

date of this AD, whichever occurs later, 

remove the fuel pump, P/N G5030FPU01 or 

P/N TPS1000–05, and replace it with a part 

eligible for installation. 

(h) Definition

For the purpose of this AD, a ‘‘part eligible

for installation’’ is a fuel pump with a P/N 

other than G5030FPU01 or TPS1000–05 or a 

fuel pump that has not exceeded the 

compliance time specified in Planning 

Information, paragraph 1.D.2, of the RR Alert 

NMSB. 

(i) Alternative Methods of Compliance

(AMOCs)

(1) The Manager, ECO 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 certification office, 

send it to the attention of the person 

identified in paragraph (j) of this AD. You 

may email your request to: ANE-AD-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

(1) For more information about this AD,

contact Kevin M. Clark, Aviation Safety 

Engineer, ECO Branch, FAA, 1200 District 

Avenue, Burlington, MA 01803; phone: (781) 

238–7088; fax: (781) 238–7199; email: 

kevin.m.clark@faa.gov. 

(2) Refer to European Union Aviation

Safety Agency (EASA) AD 2021–0006, dated 

January 7, 2021, for more information. You 

may examine the EASA AD in the AD docket 

at http://www.regulations.gov by searching 

for and locating Docket No. FAA–2021–0198. 

(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 the AD specifies otherwise. 

(i) Rolls-Royce (RR) Alert NonModification Service Bulletin TRENT 1000– 

73–AK581, Revision 3, dated April 7, 2021. 

(ii) [Reserved]

(3) For RR service information identified in

this AD, contact Rolls-Royce plc, P.O. Box 

31, Derby, DE24 8BJ, United Kingdom; 

phone: +44 (0)1332 242424; website: https:// 

www.rolls-royce.com/contact-us.aspx. 

(4) You may view this service information

at the FAA, Airworthiness Products Section, 

Operational Safety Branch, 1200 District 

Avenue, Burlington, MA 01803. For 

information on the availability of this 

material at the FAA, call (781) 238–7759. 

(5) You may view this service information

that is incorporated by reference at the 

National Archives and Records 

Administration (NARA). For information on 

the availability of this material at NARA, 

email: fr.inspection@nara.gov, or go to: 

https://www.archives.gov/federal-register/cfr/ 

ibr-locations.html. 

Issued on August 12, 2021. 

Lance T. Gant, 

Director, Compliance & Airworthiness 

Division, Aircraft Certification Service. 

[FR Doc. 2021–19279 Filed 9–7–21; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2021–0539; Project 

Identifier 2018–SW–048–AD; Amendment 

39–21719; AD 2021–19–01] 

RIN 2120–AA64 

Airworthiness Directives; Bell Textron 

Canada Limited Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: The FAA is adopting a new 

airworthiness directive (AD) for certain 

Bell Textron Canada Limited Model 

206, 206A, 206A–1 (OH–58A), 206B, 

206B–1, 206L, 206L–1, 206L–3, 206L–4, 

222, 222B, 222U, 230, 407, 427, 429, 

and 430 helicopters. This AD was 

prompted by a report of a shoulder 

harness seat belt comfort clip (comfort 

clip) interfering with the seat belt inertia 

reel. This AD requires removing each 

comfort clip from service, inspecting the 

shoulder harness seat belt for any rip 

and abrasion, and removing any 

shoulder harness seat belt from service 

that has a rip or abrasion. The FAA is 

issuing this AD to address the unsafe 

condition on these products. 

DATES: This AD is effective October 13, 

2021. 

ADDRESSES: For service information 

identified in this final rule, contact Bell 

Textron Canada Limited, 12,800 Rue de 

l’Avenir, Mirabel, Quebec J7J1R4; 

telephone 1–450–437–2862 or 1–800– 

363–8023; fax 1–450–433–0272; email 

productsupport@bellflight.com; or at 

https://www.bellflight.com/support/ 


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Federal Register / Vol. 86, No. 171 / Wednesday, September 8, 2021 / Rules and Regulations 50233 

contact-support. You may view the 

referenced 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. 

Examining the AD Docket 

You may examine the AD docket at 

https://www.regulations.gov by 

searching for and locating Docket No. 

FAA–2021–0539; 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, the Transport Canada AD, any 

comments received, and other 

information. The street 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: 

Steven Warwick, Aerospace Engineer, 

Certification Section, Fort Worth ACO 

Branch, FAA, 10101 Hillwood Pkwy., 

Fort Worth, TX 76177; telephone (817) 

222–5225; email Steven.R.Warwick@

faa.gov. 

SUPPLEMENTARY INFORMATION: 

Background 

The FAA issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 by adding an AD that would 

apply to Bell Textron Canada Limited 

Model 206, 206A, 206A–1 (OH–58A), 

206B, 206B–1, 206L, 206L–1, 206L–3, 

206L–4, 222, 222B, 222U, 230, 407, 427, 

429, and 430 helicopters with a comfort 

clip installed; or that have been 

modified per Supplemental Type 

Certificate (STC) SH2073SO 

(installation of shoulder harness 

restraint system) or STC SH2751SO 

(installation of a passenger shoulder 

harness restraint system). 

The NPRM published in the Federal 

Register on July 6, 2021 (86 FR 35410). 

In the NPRM, the FAA proposed to 

require, within 25 hours time-in-service 

(TIS) after the effective date of the 

proposed AD, removing from service 

each comfort clip and inspecting each 

shoulder harness seat belt for a rip and 

abrasion. If there is a rip or abrasion, the 

NPRM proposed to require removing the 

shoulder harness seat belt from service 

before further flight. The NPRM also 

proposed to prohibit installing a comfort 

clip on any helicopter as of the effective 

date of the proposed AD. 

The NPRM was prompted by 

Transport Canada AD CF–2018–16, 

dated June 14, 2018 (Transport Canada 

AD CF–2018–16), issued by Transport 

Canada, which is the aviation authority 

for Canada, to correct an unsafe 

condition for all serial-numbered Bell 

Helicopter Textron Canada Limited 

(now Bell Textron Canada Limited) 

Model 206, 206A, 206A–1, 206B, 206B– 

1, 206L, 206L–1, 206L–3, 206L–4, 222, 

222B, 222U, 230, 407, 427, 429 and 430 

helicopters. Transport Canada advises 

that Bell Helicopter Textron Canada 

Limited delivered comfort clips with 

some helicopters, and that these comfort 

clips, which were also sold as spare 

parts or accessories, were intended to 

improve occupant comfort by reducing 

shoulder harness tension. However, 

Transport Canada advises the comfort 

clip may interfere with the shoulder 

harness inertia reel, preventing the 

harness from locking and resulting in 

injury to the occupant during an 

emergency landing. To prevent this 

unsafe condition, Transport Canada AD 

CF–2018–16 requires, within 25 hours 

air time or 10 days, whichever occurs 

first, determining if the comfort clips are 

installed. If the comfort clips are 

installed, Transport Canada AD CF– 

2018–16 requires removing them from 

service within 100 hours air time or 30 

days, whichever occurs first, and 

inspecting each shoulder harness seat 

belt for damage and replacing any 

shoulder harness seat belt that has 

damage that exceeds allowable limits 

before further flight. Transport Canada 

AD CF–2018–16 also prohibits the 

installation of any comfort clip on any 

helicopter. 

Discussion of Final Airworthiness 

Directive 

Comments 

The FAA received no comments on 

the NPRM or on the determination of 

the costs. 

Conclusion 

These helicopters have been approved 

by the aviation authority of Canada and 

are approved for operation in the United 

States. Pursuant to the FAA’s bilateral 

agreement with Canada, Transport 

Canada, its technical representative, has 

notified the FAA of the unsafe condition 

described in its AD. The FAA reviewed 

the relevant data and determined that 

air safety requires adopting this AD as 

proposed. Accordingly, the FAA is 

issuing this AD to address the unsafe 

condition on these helicopters. 

Related Service Information 

The FAA reviewed the following Bell 

Helicopter Alert Service Bulletins 

(ASBs), each dated January 11, 2016: 

• ASB 222–15–112 for Model 222, 

222B, and 222U helicopters with serial 

numbers (S/N) 47006 through 47089, 

47131 through 47156, and 47501 

through 47574 (ASB 222–15–112); 

• ASB 230–15–46 for Model 230 

helicopters with S/N 23001 through 

23038; 

• ASB 407–15–111 for Model 407 

helicopters with S/N 53000 through 

53900, 53911 through 54166, and 54300 

through 54599; 

• ASB 427–15–39 for Model 427 

helicopters with S/N 56001 through 

56084, 58001 and 58002 (ASB 427–15– 

39); 

• ASB 429–15–27 for Model 429 

helicopters with S/N 57001 through 

57259 (ASB 429–15–27); and 

• ASB 430–15–56 for Model 430 

helicopters with S/N 49001 through 

49129. 

The FAA also reviewed the following 

Bell Helicopter ASBs, both Revision A 

and both dated February 5, 2016: 

• ASB 206–15–133 for Model 206A/B 

and TH–67 helicopters with S/N 4 

through 4690 and 5101 through 5313 

(ASB 206–15–133); and 

• ASB 206L–15–175 for Model 206L, 

206L–1, 206L–3, and 206L–4 helicopters 

with S/N 45001 through 45153, 46601 

through 46617, 45154 through 45790, 

51001 through 51612, and 52001 

through 52455 (ASB 206L–15–175). 

All of the ASBs specify removing all 

variants of comforts clips from all seat 

belt assemblies. ASB 222–15–112, ASB 

427–15–39, and ASB 429–15–27 also 

specify that although the helicopter 

models to which these ASBs apply were 

not affected by the original design at the 

time of certification and delivery of the 

helicopter, the affected parts may have 

been installed post-delivery to end 

owners/operators of those helicopters. 

ASB 206–15–133 and ASB 206L–15– 

175 also specify that helicopters that 

have been modified per STC SH2073SO 

(installation of shoulder harness 

restraint system) are affected and 

therefore included in the ASB 

applicability. 

ASB 206L–15–175 also specifies that 

helicopters that have been modified per 

STC SH2751SO (installation of a 

passenger shoulder harness restraint 

system) are affected and therefore 

included in the ASB applicability. 

Differences Between This AD and the 

Transport Canada AD 

This AD requires removing the 

comfort clip and inspecting the 

shoulder harness seat belt within 25 

hours TIS; Transport Canada AD CF– 

2018–16 requires inspecting for the 

presence of a comfort clip at 25 hours 

air time, or 10 days, whichever occurs 

first, and then requires removing the 

comfort clip, if installed. Transport 


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50234 Federal Register / Vol. 86, No. 171 / Wednesday, September 8, 2021 / Rules and Regulations 

Canada AD CF–2018–16 requires 

inspecting the shoulder harness seat belt 

for any damage that exceeds allowable 

limits within 100 hours air time or 30 

days, whichever occurs first, whereas 

this AD requires the inspection within 

25 hours TIS and removing any 

shoulder harness seat belt from service 

before further flight if there is any rip or 

abrasion. 

Transport Canada AD CF–2018–16 

applies to all serial-numbered Model 

206, 206A, 206A–1, 206B, 206B–1, 

206L, 206L–1, 206L–3, 206L–4, 222, 

222B, 222U, 230, 407, 427, 429 and 430 

helicopters, whereas this AD applies to 

Model 206, 206A, 206A–1, 206B, 206B– 

1, 206L, 206L–1, 206L–3, 206L–4, 222, 

222B, 222U, 230, 407, 427, 429, and 430 

helicopters with a comfort clip installed 

or helicopters that have been modified 

per STC SH2073SO (installation of 

shoulder harness restraint system) or 

STC SH2751SO (installation of a 

passenger shoulder harness restraint 

system). 

Costs of Compliance 

The FAA estimates that this AD 

affects 2,347 helicopters of U.S. 

Registry. Labor rates are estimated at 

$85 per work-hour. Based on these 

numbers, the FAA estimates the 

following costs to comply with this AD. 

Removing each comfort clip will take 

about 0.5 work-hour for an estimated 

cost of $43 per clip and up to $807,368 

for the U.S. fleet. 

Replacing a shoulder harness seat 

belt, if required, will take about 1 workhour and parts will cost about $250 per 

shoulder harness seat belt, for an 

estimated cost of $335 per replacement. 

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 helicopters 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: 

2021–19–01 Bell Textron Canada Limited: 

Amendment 39–21719; Docket No. 

FAA–2021–0539; Project Identifier 

2018–SW–048–AD. 

(a) Effective Date 

This airworthiness directive (AD) is 

effective October 13, 2021. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Bell Textron Canada 

Limited Model 206, 206A, 206A–1 (OH– 

58A), 206B, 206B–1, 206L, 206L–1, 206L–3, 

206L–4, 222, 222B, 222U, 230, 407, 427, 429, 

and 430 helicopters, certificated in any 

category: 

(1) With a shoulder harness seat belt 

comfort clip (comfort clip) installed; or 

(2) That have been modified per 

Supplemental Type Certificate (STC) 

SH2073SO (installation of shoulder harness 

restraint system) or STC SH2751SO 

(installation of a passenger shoulder harness 

restraint system). 

(d) Subject 

Joint Aircraft Service Component (JASC) 

Code: 2500 Cabin Equipment/Furnishings. 

(e) Unsafe Condition 

This AD defines the unsafe condition as a 

comfort clip interfering with the seat belt 

inertia reel, which could prevent the seatbelt 

from locking and result in injury to the 

occupant during an emergency landing. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Required Actions 

(1) Within 25 hours time-in-service after 

the effective date of this AD: 

(i) Remove each comfort clip from service. 

(ii) Inspect each shoulder harness seat belt 

for a rip and abrasion. If there is a rip or any 

abrasion, before further flight, remove the 

shoulder harness seat belt from service. 

(2) As of the effective date of this AD, do 

not install any comfort clip on any 

helicopter. 

(h) 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 (i)(1) 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. 

(i) Related Information 

(1) For more information about this AD, 

contact Steven Warwick, Aerospace 

Engineer, Certification Section, Fort Worth 

ACO Branch, FAA, 10101 Hillwood Pkwy., 

Fort Worth, TX 76177; telephone (817) 222– 

5225; email Steven.R.Warwick@faa.gov. 

(2) The subject of this AD is addressed in 

Transport Canada AD CF–2018–16, dated 

June 14, 2018. You may view the Transport 

Canada AD on the internet at https://

www.regulations.gov in the AD Docket in 

Docket No. FAA–2021–0539. 

(j) Material Incorporated by Reference 

None. 

Issued on August 31, 2021. 

Gaetano A. Sciortino, 

Deputy Director for Strategic Initiatives, 

Compliance & Airworthiness Division, 

Aircraft Certification Service. 

[FR Doc. 2021–19244 Filed 9–7–21; 8:45 am] 

BILLING CODE 4910–13–P 


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