Airworthiness Directives; General Electric Company Turbofan Engines, 3182-3184 [2022-01141]

Download as PDF 3182 Federal Register / Vol. 87, No. 14 / Friday, January 21, 2022 / Rules and Regulations jspears on DSK121TN23PROD with RULES1 (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-190COS@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 VerDate Sep<11>2014 16:23 Jan 20, 2022 Jkt 256001 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 PO 00000 Frm 00008 Fmt 4700 Sfmt 4700 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 Federal Aviation Administration (FAA), DOT. ACTION: Final rule. AGENCY: 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. SUMMARY: DATES: This AD is effective February 25, 2022. 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. ADDRESSES: 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 E:\FR\FM\21JAR1.SGM 21JAR1 3183 Federal Register / Vol. 87, No. 14 / Friday, January 21, 2022 / Rules and Regulations 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: jspears on DSK121TN23PROD with RULES1 ESTIMATED COSTS Action Labor cost Revise ALS of Engine Manual and the operator’s existing approved CAMP. 2 work-hours × $85 per hour = $170 ............. Cost per product Parts cost $0 Cost on U.S. operators $170 $37,400 Authority for This Rulemaking Regulatory Findings The Amendment 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. 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. Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: VerDate Sep<11>2014 16:23 Jan 20, 2022 Jkt 256001 List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. PO 00000 Frm 00009 Fmt 4700 Sfmt 4700 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. E:\FR\FM\21JAR1.SGM 21JAR1 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 BILLING CODE 4910–13–P Federal Aviation Administration (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 jspears on DSK121TN23PROD with RULES1 [FR Doc. 2022–01141 Filed 1–20–22; 8:45 am] DEPARTMENT OF TRANSPORTATION Joint Aircraft System Component (JASC) Code 7120, Engine Mount Section. 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. VerDate Sep<11>2014 Issued on January 14, 2022. Lance T. Gant, Director, Compliance & Airworthiness Division, Aircraft Certification Service. 16:23 Jan 20, 2022 Jkt 256001 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 Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: 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@ SUMMARY: PO 00000 Frm 00010 Fmt 4700 Sfmt 4700 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 E:\FR\FM\21JAR1.SGM 21JAR1

Agencies

[Federal Register Volume 87, Number 14 (Friday, January 21, 2022)]
[Rules and Regulations]
[Pages 3182-3184]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2022-01141]


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

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: [email protected]; 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

[[Page 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: 
[email protected].

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 left-hand 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
----------------------------------------------------------------------------------------------------------------
                                                                                     Cost per      Cost on U.S.
                Action                         Labor cost           Parts cost        product        operators
----------------------------------------------------------------------------------------------------------------
Revise ALS of Engine Manual and the     2 work-hours x $85 per                $0            $170         $37,400
 operator's existing approved CAMP.      hour = $170.
----------------------------------------------------------------------------------------------------------------

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:

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.

[[Page 3184]]

(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 
left-hand 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: [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.

(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: [email protected].

(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