3182 Federal Register / Vol. 87, No. 14 / Friday, January 21, 2022 / Rules and Regulations 

(4) Before installing the main driveshaft 

following paragraph (g)(3) of this AD, and 

with the engine adapter installed in the end 

of the engine output shaft, inspect the 

alignment of the main driveshaft installation 

between the transmission input drive quill 

coupling and the engine output shaft adapter 

by following ‘‘6–24. Alignment—Main 

Driveshaft,’’ paragraphs c. through g. on 

pages 6–21 through 6–23, including ‘‘Figure 

6–7. Transmission Positioning for Driveshaft 

Alignment’’ on page 6–2 (Figure 6–7), and 

‘‘Figure 6–8. Tool Application—Use of 

Alignment Tool Set (T47)’’ on page 6–3 

(Figure 6–8), of TM 55–1520–210–23–1 C 42. 

If there is misalignment, before further flight, 

adjust the alignment by following ‘‘6–24. 

Alignment—Main Driveshaft,’’ paragraphs h. 

through j. on page 6–23, including Figure 6– 

7 and Figure 6–8, of TM 55–1520–210–23–1 

C 42. 

(5) Within 300 hours TIS after the effective 

date of this AD, and thereafter within 

intervals not to exceed 300 hours TIS, with 

the main driveshaft installed, accomplish the 

actions in paragraphs (g)(3)(i) through (iv) of 

this AD. 

(6) As an optional terminating action for 

the requirements of this AD, you may install 

KAflex main driveshaft P/N SKCP3303–1. 

(7) As an option to accomplishing the 

actions by following the specified portions in 

TM 55–1520–210–23–1 C 42 in paragraphs 

(g)(3) and (4) of this AD, you may accomplish 

the actions by following those specified 

portions in Headquarters, Department of the 

Army, Aviation Unit and Intermediate 

Maintenance Instructions Army Model UH– 

1H/V/EH–1H/X Helicopters, Technical 

Manual TM 55–1520–210–23–1, Change No. 

47, dated September 20, 2005 (TM 55–1520– 

210–23–1 C 47), and disregard exceptions to 

refer to Figure 1 and see Figure 2 to the 

introductory text of paragraph (g)(3) of this 

AD, instead refer to ‘‘Figure 6–12.2. Main 

Driveshaft Installation & Removal Tool’’ and 

see ‘‘Figure 6–12.3. Work Aid Tool Installed 

on Main Driveshaft,’’ on page 6–27 of TM 55– 

1520–210–23–1 C 47 as instructed in TM 55– 

1520–210–23–1 C 47. 

(h) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, DSCO 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 (i) of this AD. 

Information may be emailed to: 9-ASW-190- 

COS@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 

For more information about this AD, 

contact Ameet Shrotriya, Aerospace 

Engineer, Delegation Oversight Section, 

DSCO Branch, Compliance & Airworthiness 

Division, FAA, 10101 Hillwood Pkwy., Fort 

Worth, TX 76177; telephone (817) 222–5525; 

email ameet.shrotriya@faa.gov. 

(j) 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) Headquarters, Department of the Army, 

Aviation Unit and Intermediate Maintenance 

Instructions Army Model UH–1H/V/EH–1H/ 

X Helicopters, Technical Manual TM 55– 

1520–210–23–1, Change No. 42, dated April 

14, 2003: 

(A) ‘‘Figure 4–9. Engine Air Inlet Filter 

Installation,’’ page 4–16; 

(B) Page 4–17; 

(C) ‘‘Figure 6–7. Transmission Positioning 

for Driveshaft Alignment,’’ page 6–2; 

(D) ‘‘Figure 6–8. Tool Application—Use of 

Alignment Tool Set (T47),’’ page 6–3; and 

(E) Pages 6–21 through 6–24. 

(ii) Headquarters, Department of the Army, 

Aviation Unit and Intermediate Maintenance 

Instructions Army Model UH–1H/V/EH–1H/ 

X Helicopters, Technical Manual TM 55– 

1520–210–23–1, Change No. 47, dated 

September 20, 2005: 

(A) ‘‘Figure 4–9. Engine Air Inlet Filter 

Installation,’’ page 4–16; 

(B) Page 4–17; 

(C) ‘‘Figure 6–7. Transmission Positioning 

for Driveshaft Alignment,’’ page 6–2; 

(D) ‘‘Figure 6–8. Tool Application—Use of 

Alignment Tool Set (T47),’’ page 6–3; 

(E) Pages 6–21 through 6–24; and 

(F) ‘‘Figure 6–12.2. Main Driveshaft 

Installation & Removal Tool’’ and ‘‘Figure 6– 

12.3. Work Aid Tool Installed on Main 

Driveshaft,’’ page 6–27. 

(3) For service information identified in 

this AD, contact U.S. Army Materiel 

Command Logistics Data Analysis Center 

(USAMC LDAC), ATTN: Equipment 

Publication Control Officers (EPCOs), 

Building 3305, Redeye Road, Redstone 

Arsenal, AL 35898–7466; telephone (256) 

955–7716 or 1–866–211–3367; email 

usarmy.redstone.ldac.mbx.logetm@mail.mil; 

or at https://enterprise.armyerp.army.mil. 

(4) You may view this service information 

at 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. 

(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 December 10, 2021. 

Lance T. Gant, 

Director, Compliance & Airworthiness 

Division, Aircraft Certification Service. 

[FR Doc. 2022–00991 Filed 1–20–22; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2021–0949; Project 

Identifier AD–2021–00115–E; Amendment 

39–21915; AD 2022–02–18] 

RIN 2120–AA64 

Airworthiness Directives; General 

Electric Company Turbofan Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: The FAA is adopting a new 

airworthiness directive (AD) for all 

General Electric Company (GE) CF6– 

80C2A1, CF6–80C2A2, CF6–80C2A3, 

CF6–80C2A5, CF6–80C2A5F, and CF6– 

80C2A8 model turbofan engines with an 

installed left-hand rear mount link 

assembly, part number (P/N) 

1846M23G01. This AD was prompted 

by the manufacturer reducing the life 

limit for the affected left-hand rear 

mount link assembly. This AD requires 

revising the airworthiness limitations 

section (ALS) of the existing engine 

maintenance manual and the operator’s 

existing approved continuous 

airworthiness maintenance program 

(CAMP). The FAA is issuing this AD to 

address the unsafe condition on these 

products. 

DATES: This AD is effective February 25, 

2022. 

ADDRESSES: For service information 

identified in this final rule, contact 

General Electric Company, 1 Neumann 

Way, Cincinnati, OH 45215; phone: 

(513) 552–3272; email: 

aviation.fleetsupport@ae.ge.com; 

website: https://www.ge.com. 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 (817) 222– 

5110. It is also available at https://

www.regulations.gov by searching for 

and locating Docket No. FAA–2021– 

0949. 

Examining the AD Docket 

You may examine the AD docket at 

https://www.regulations.gov by 

searching for and locating Docket No. 

FAA–2021–0949; 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 


jspears on DSK121TN23PROD with RULES1
Federal Register / Vol. 87, No. 14 / Friday, January 21, 2022 / Rules and Regulations 3183 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE, 

Washington, DC 20590. 

FOR FURTHER INFORMATION CONTACT: 

Scott Stevenson, Aviation Safety 

Engineer, ECO Branch, FAA, 1200 

District Avenue, Burlington, MA 01803; 

phone: (781) 238–7132; fax: (781) 238– 

7199; email: Scott.M.Stevenson@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 all GE CF6–80C2A1, CF6– 

80C2A2, CF6–80C2A3, CF6–80C2A5, 

CF6–80C2A5F, and CF6–80C2A8 model 

turbofan engines with an installed lefthand rear mount link assembly, P/N 

1846M23G01. The NPRM published in 

the Federal Register on November 5, 

2021 (86 FR 61086). The NPRM was 

prompted by a report from the 

manufacturer reducing the life limit for 

the affected left-hand rear mount link 

assembly. The left-hand rear mount link 

assembly was redesigned and certified 

in 1999, and the FAA subsequently 

issued AD 2000–12–08 (65 FR 39536, 

June 27, 2000), mandating the 

replacement of the affected left-hand 

rear mount link assembly with a part 

eligible for installation. Later, analysis 

from the aircraft manufacturer of stress 

loads in their extended service goal 

mission profile revealed loads during 

the take-off phase that were not 

included at certification. These 

additional loads result in a reduced life 

limit on the left-hand rear mount link 

assembly. In the NPRM, the FAA 

proposed to require revising the ALS of 

the GE CF6–80C Engine Manual, 

GEK92451, as applicable to each 

affected engine model, and the 

operator’s existing approved CAMP to 

incorporate a reduced life limit for the 

affected left-hand rear mount link 

assembly, P/N 1846M23G01. The FAA 

is issuing this AD to address the unsafe 

condition on these products. 

Discussion of Final Airworthiness 

Directive 

Comments 

The FAA received comments from 

one commenter, FedEx Express, who 

supported the NPRM without change. 

Conclusion 

The FAA reviewed the relevant data, 

considered the comments received, and 

determined that air safety requires 

adopting the AD as proposed. 

Accordingly, the FAA is issuing this AD 

to address the unsafe condition on these 

products. Except for minor editorial 

changes, including the removal of the 

reference to GE CF6–80C2 Engine 

Manual, GEK92451, this AD is adopted 

as proposed in the NPRM. 

Related Service Information 

The FAA reviewed GE CF6–80C2 

Temporary Revision (TR) 05–0276, 

dated July 13, 2021 (GE TR 05–0276), 

and GE CF6–80C2 TR 05–0277, dated 

July 9, 2021 (GE TR 05–0277). GE TR 

05–0276 and GE TR 05–277 provide the 

new life limit to be updated into the 

ALS, for the affected left-hand rear 

mount link assembly, in the existing 

engine maintenance manual. 

Costs of Compliance 

The FAA estimates that this AD 

affects 220 engines installed on 

airplanes of U.S. registry. 

The FAA estimates the following 

costs to comply with this AD: 

ESTIMATED COSTS

Action Labor cost Parts cost Cost per 

product 

Cost on U.S. 

operators 

Revise ALS of Engine Manual and the operator’s existing approved CAMP.2 work-hours × $85 per hour = $170 ............. $0 $170 $37,400 

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: 

2022–02–18 General Electric Company: 

Amendment 39–21915; Docket No. 

FAA–2021–0949; Project Identifier AD– 

2021–00115–E. 

(a) Effective Date 

This airworthiness directive (AD) is 

effective February 25, 2022. 

(b) Affected ADs 

None. 


jspears on DSK121TN23PROD with RULES1
3184 Federal Register / Vol. 87, No. 14 / Friday, January 21, 2022 / Rules and Regulations 

(c) Applicability 

This AD applies to General Electric 

Company (GE) CF6–80C2A1, CF6–80C2A2, 

CF6–80C2A3, CF6–80C2A5, CF6–80C2A5F, 

and CF6–80C2A8 model turbofan engines 

with an installed left-hand rear mount link 

assembly, part number (P/N) 1846M23G01. 

(d) Subject 

Joint Aircraft System Component (JASC) 

Code 7120, Engine Mount Section. 

(e) Unsafe Condition 

This AD was prompted by a report from 

the manufacturer on an updated analysis of 

stress loads during take-off, which revealed 

a stress increase with take-off phase loads 

that were not included at certification. The 

FAA is issuing this AD to lower the life limit 

of the left-hand rear mount link assembly and 

prevent the failure of the engine mount 

system. The unsafe condition, if not 

addressed, could result in separation of the 

engine from the airplane and loss of the 

airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Required Actions 

Within 180 days after the effective date of 

this AD, revise the airworthiness limitations 

section of the existing engine maintenance 

manual, and the operator’s existing approved 

continuous airworthiness maintenance 

program, by reducing the life limit of the lefthand rear mount link assembly, P/N 

1846M23G01, from 50,000 flight cycles (FCs) 

to 23,800 FCs. 

(h) 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 ECO Branch, send it to 

the attention of the person identified in 

paragraph (i) 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. 

(i) Related Information 

For more information about this AD, 

contact Scott Stevenson, Aviation Safety 

Engineer, ECO Branch, FAA, 1200 District 

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

238–7132; fax: (781) 238–7199; email: 

Scott.M.Stevenson@faa.gov. 

(j) Material Incorporated by Reference 

None. 

Issued on January 14, 2022. 

Lance T. Gant, 

Director, Compliance & Airworthiness 

Division, Aircraft Certification Service. 

[FR Doc. 2022–01141 Filed 1–20–22; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2021–0725; Project 

Identifier MCAI–2020–01402–T; Amendment 

39–21882; AD 2021–26–23] 

RIN 2120–AA64 

Airworthiness Directives; Bombardier, 

Inc., Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: The FAA is superseding 

Airworthiness Directive (AD) 2017–22– 

06, which applied to certain 

Bombardier, Inc., Model CL–600–2B16 

(601–3A, 601–3R, and 604 Variants) 

airplanes. AD 2017–22–06 required 

repetitive inspections for fuel leakage at 

the engine and auxiliary power unit 

(APU) fuel pumps, and related 

investigative and corrective actions if 

necessary. This AD retains the 

requirements of AD 2017–22–06, and 

requires an inspection of the APU, 

repair if necessary, and modification of 

the engine electrical fuel pump (EFP) 

installation. This AD also adds airplanes 

to the applicability. This AD was 

prompted by reports of fuel leaks from 

the electrical connectors and conduits of 

the engine and APU EFP cartridge/ 

canister, and the development of 

additional actions to address the root 

cause of the fuel leaks. The FAA is 

issuing this AD to address the unsafe 

condition on these products. 

DATES: This AD is effective February 25, 

2022. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of February 25, 2022. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain other publications listed in 

this AD as of November 30, 2017 (82 FR 

49498, October 26, 2017). 

ADDRESSES: For service information 

identified in this final rule, contact 

Bombardier Business Aircraft Customer 

Response Center, 400 Coˆte-Vertu Road 

West, Dorval, Que ́bec H4S 1Y9, Canada; 

telephone 514–855–2999; email ac.yul@

aero.bombardier.com; internet https://

www.bombardier.com. You may view 

this referenced service information at 

the FAA, Airworthiness Products 

Section, Operational Safety Branch, 

2200 South 216th St., Des Moines, WA. 

For information on the availability of 

this material at the FAA, call 206–231– 

3195. It is also available on the internet 

at https://www.regulations.gov by 

searching for and locating Docket No. 

FAA–2021–0725. 

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– 

0725; 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: 

Steven Dzierzynski, Aerospace 

Engineer, Avionics and Electrical 

Systems Section, FAA, New York ACO 

Branch, 1600 Stewart Avenue, Suite 

410, Westbury, NY 11590; telephone 

516–228–7367; fax 516–794–5531; email 

9-avs-nyaco-cos@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

Transport Canada Civil Aviation 

(TCCA), which is the aviation authority 

for Canada, has issued TCCA AD CF– 

2016–32R4, dated October 13, 2020 

(TCCA AD CF–2016–32R4); and TCCA 

AD CF–2020–38, dated October 13, 2020 

(TCCA AD CF–2020–38); (also referred 

to as the Mandatory Continuing 

Airworthiness Information, or the 

MCAI), to correct an unsafe condition 

for certain Bombardier, Inc., Model CL– 

600–2B16 (601–3A, 601–3R, and 604 

Variants) airplanes. You may examine 

the MCAI in the AD docket on the 

internet at https://www.regulations.gov 

by searching for and locating Docket No. 

FAA–2021–0725. 

The FAA issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to supersede AD 2017–22–06, 

Amendment 39–19086 (82 FR 49498, 

October 26, 2017) (AD 2017–22–06). AD 

2017–22–06 applied to certain 

Bombardier, Inc., Model CL–600–2B16 

(601–3A, 601–3R, and 604 Variants) 

airplanes. The NPRM published in the 

Federal Register on September 8, 2021 

(86 FR 50291). The NPRM was 


jspears on DSK121TN23PROD with RULES1