Federal Register / Vol. 87, No. 35 / Tuesday, February 22, 2022 / Rules and Regulations 9429 

ESTIMATED COSTS * 

Action Labor cost Parts cost Cost per 

spoiler assembly 

Cost on U.S. 

operators 

Spoiler assembly replacement.70 work-hours × $85 per 

hour = $5,950.

$44,039 ............................. $49,989 ............................. $399,912 

* Each airplane contains two spoiler assemblies. 

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, 

and 

(2) Will not affect intrastate aviation 

in Alaska. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

Adoption of 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: 

2022–05–01 Learjet, Inc.: Amendment 39– 

21952; Docket No. FAA–2022–0144; 

Project Identifier AD–2022–00042–T. 

(a) Effective Date 

This airworthiness directive (AD) is 

effective March 9, 2022. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Learjet, Inc., Model 35, 

35A (C–21A), 36, 36A, 55, 55B, 55C, and 60 

airplanes, certificated in any category, with 

any spoiler assembly that meets any of the 

criteria identified in paragraph (c)(1) or (2) of 

this AD. 

(1) The spoiler assembly’s life limit was 

extended by Restored Aircraft Sales and 

Service, LLC. 

(2) The maintenance records related to the 

life limit for the spoiler assembly are missing 

or incomplete. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 5755, Spoilers. 

(e) Unsafe Condition 

This AD was prompted by a report 

indicating that a repair station performed a 

life extension program on spoiler assemblies 

that had reached or were close to reaching 

their life limit. The FAA is issuing this AD 

to prevent use of a spoiler assembly beyond 

its FAA-approved life limit, which could 

lead to undetected cracking and consequent 

failure or separation of the spoiler assembly, 

resulting in a reduction or complete loss of 

control of the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Spoiler Assembly Removal 

For each spoiler assembly identified in 

paragraph (c) of this AD: Remove the spoiler 

assembly from service before further flight. 

(h) Parts Installation Prohibition 

As of the effective date of this AD, no 

person may install, on any airplane, a spoiler 

assembly identified in paragraph (c) of this 

AD. 

(i) Special Flight Permit 

Special flight permits, as described in 14 

CFR 21.197 and 21.199, may be issued to 

operate the airplane to a location where the 

requirements of this AD can be 

accomplished, but concurrence by the 

Manager, Wichita ACO Branch, FAA, is 

required before issuance of the special flight 

permit. 

(j) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Wichita ACO 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 responsible Flight 

Standards 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 (k) of this 

AD. 

(2) Before using any approved AMOC, 

notify your appropriate principal inspector, 

or lacking a principal inspector, the manager 

of the responsible Flight Standards Office. 

(k) Related Information 

For more information about this AD, 

contact Tara Shawn, Aerospace Engineer, 

Airframe and Services Section, FAA, Wichita 

ACO Branch, 1801 Airport Road, Room 100, 

Wichita, KS 67209; phone: 316–946–4141; 

email: Tara.Shawn@faa.gov. 

(l) Material Incorporated by Reference 

None. 

Issued on February 16, 2022. 

Lance T. Gant, 

Director, Compliance & Airworthiness 

Division, Aircraft Certification Service. 

[FR Doc. 2022–03805 Filed 2–17–22; 11:15 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2021–1006; Project 

Identifier MCAI–2021–00700–T; Amendment 

39–21940; AD 2022–03–22] 

RIN 2120–AA64 

Airworthiness Directives; Airbus SAS 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 


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9430 Federal Register / Vol. 87, No. 35 / Tuesday, February 22, 2022 / Rules and Regulations 

ACTION: Final rule. 

SUMMARY: The FAA is superseding 

Airworthiness Directive (AD) 2019–26– 

01, which applied to certain Airbus SAS 

Model A350–941 and –1041 airplanes. 

AD 2019–26–01 required repetitive 

detailed inspections, and applicable 

corrective actions, and provided an 

optional modification that terminated 

the inspections. Since the FAA issued 

AD 2019–26–01, a determination was 

made that a related production 

modification was not properly installed 

on certain airplanes. This AD retains the 

requirements of AD 2019–26–01, and, 

for certain airplanes, adds a one-time 

detailed inspection of the modification 

for proper installation, and applicable 

corrective actions if necessary, as 

specified in a 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 March 29, 

2022. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of March 29, 2022. 

ADDRESSES: For the material 

incorporated by reference (IBR) in this 

AD, contact the EASA, KonradAdenauer-Ufer 3, 50668 Cologne, 

Germany; telephone +49 221 8999 000; 

email ADs@easa.europa.eu; internet 

www.easa.europa.eu. You may view this 

IBR material 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 in 

the AD docket on the internet at https:// 

www.regulations.gov by searching for 

and locating Docket No. FAA–2021– 

1006. 

Examining the AD Docket 

You may examine the AD docket at 

https://www.regulations.gov by 

searching for and locating Docket No. 

FAA–2021–1006; 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 mandatory continuing 

airworthiness information (MCAI), 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: Dan 

Rodina, Aerospace Engineer, 

International Section, Transport 

Standards Branch, FAA, 2200 South 

216th St., Des Moines, WA 98198; 

telephone and fax 206–231–3225; email 

dan.rodina@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Background 

EASA, which is the Technical Agent 

for the Member States of the European 

Union, has issued EASA AD 2021–0141, 

dated June 15, 2021 (EASA AD 2021– 

0141) (also referred to as the MCAI), to 

correct an unsafe condition for certain 

Airbus SAS Model A350–941 and –1041 

airplanes. 

The FAA issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to supersede AD 2019–26–01, 

Amendment 39–21023 (85 FR 4199, 

January 24, 2020) (AD 2019–26–01). AD 

2019–26–01 applied to certain Airbus 

SAS Model A350–941 and –1041 

airplanes. The NPRM published in the 

Federal Register on November 18, 2021 

(86 FR 64416). The NPRM was 

prompted by reports of sealant bead 

damage caused by rotation of the 

attachment fitting bearing assembly of a 

trimmable horizontal stabilizer (THS) 

and a determination that a related 

production modification was not 

properly installed on certain airplanes. 

The NPRM proposed to retain the 

requirements of AD 2019–26–01, and, 

for certain airplanes, proposed to add a 

one-time detailed inspection of the 

modification for proper installation, and 

applicable corrective actions if 

necessary, as specified in EASA AD 

2021–0141. 

The FAA is issuing this AD to address 

possible water ingress due to sealant 

bead damage, which could result in 

corrosion damage in the aluminum 

corner fitting. This condition, if not 

addressed, could lead to detachment 

and loss of the THS, possibly resulting 

in loss of control of the airplane and 

injury to persons on the ground. See the 

MCAI for additional background 

information. 

Discussion of Final Airworthiness 

Directive 

Comments 

The FAA received a comment from 

the Air Line Pilots Association, 

International (ALPA), who supported 

the NPRM without change. 

Conclusion 

The FAA reviewed the relevant data, 

considered the comment received, and 

determined that air safety requires 

adopting this AD as proposed. Except 

for minor editorial changes, this AD is 

adopted as proposed in the NPRM. 

None of the changes will increase the 

economic burden on any operator. 

Accordingly, the FAA is issuing this AD 

to address the unsafe condition on these 

products. 

Related Service Information Under 1 

CFR Part 51 

EASA AD 2021–0141 describes 

procedures for repetitive detailed 

inspections for damage of the fillet 

sealant and corrosion on aluminum in 

the lower and upper corner fittings and 

bearing assembly attachment interface at 

frame (FR) 102, left-hand and right-hand 

sides, and an optional modification 

(application of new corrosion protection 

in the THS upper and lower attachment 

fitting bearing assembly) that would 

eliminate the need for the repetitive 

inspections. EASA AD 2021–0141 also 

describes procedures for a one-time 

detailed inspection of the modification 

of the lower and upper corner fittings 

and bearing assembly attachment 

interface at FR 102, left-hand and righthand sides (Airbus production 

modification 113102) for discrepancies 

(including missing sealant bead, cracks 

in the sealant bead, and corrosion on the 

affected bearing zone) and corrective 

actions (including, but not limited to, a 

check for grease, a check for cracks in 

the sealant bead, applying sealant, 

torqueing the bearing nut, inspecting for 

corrosion on the affected bearing zone, 

applying corrosion preventative 

compound and actions to address 

missing grease and corrosion). This 

material is reasonably available because 

the interested parties have access to it 

through their normal course of business 

or by the means identified in the 

ADDRESSES section. 

Costs of Compliance 

The FAA estimates that this AD 

affects 15 airplanes of U.S. registry. The 

FAA estimates the following costs to 

comply with this AD: 


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Federal Register / Vol. 87, No. 35 / Tuesday, February 22, 2022 / Rules and Regulations 9431 

ESTIMATED COSTS FOR REQUIRED ACTIONS

Action Labor cost Parts cost Cost per 

product 

Cost on U.S. 

operators 

Retained actions from AD 2019-26-01 ........... 30 work-hours × $85 per hour = $2,550 ........ $0 $2,550 $38,250 

New actions .................................................... 32 work-hours × $85 per hour = $2,720 ........ 0 2,720 40,800 

The FAA has received no definitive 

data that enables the agency to provide 

cost estimates for the corrective actions 

(including repair) specified in this AD. 

ESTIMATED COSTS OF OPTIONAL ACTIONS

Labor cost Parts cost Cost per 

product 

34 work-hours × $85 per hour = $2,890 ................................................................................................................. $0 $2,890 

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: 

■ a. Removing Airworthiness Directive 

(AD) 2019–26–01, Amendment 39– 

21023 (85 FR 4199, January 24, 2020); 

and 

■ b. Adding the following new AD: 

2022–03–22 Airbus SAS: Amendment 39– 

21940; Docket No. FAA–2021–1006; 

Project Identifier MCAI–2021–00700–T. 

(a) Effective Date 

This airworthiness directive (AD) is 

effective March 29, 2022. 

(b) Affected ADs 

This AD replaces AD 2019–26–01, 

Amendment 39–21023 (85 FR 4199, January 

24, 2020) (AD 2019–26–01). 

(c) Applicability 

This AD applies to Airbus SAS Model 

A350–941 and –1041 airplanes, certificated 

in any category, as identified in European 

Union Aviation Safety Agency (EASA) AD 

2021–0141, dated June 15, 2021 (EASA AD 

2021–0141). 

(d) Subject 

Air Transport Association (ATA) of 

America Code 53, Fuselage. 

(e) Reason 

This AD was prompted by reports of 

sealant bead damage caused by rotation of 

the attachment fitting bearing assembly of a 

trimmable horizontal stabilizer (THS) and a 

determination that a related production 

modification was not properly installed on 

certain airplanes. The FAA is issuing this AD 

to address possible water ingress due to 

sealant bead damage, which could result in 

corrosion damage in the aluminum corner 

fitting. This condition, if not addressed, 

could lead to detachment and loss of the 

THS, possibly resulting in loss of control of 

the airplane 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 2021–0141. 

(h) Exceptions to EASA AD 2021–0141 

(1) Where EASA AD 2021–0141 refers to 

February 21, 2018 (the effective date of EASA 

AD 2018–0037), this AD requires using 

February 28, 2020 (the effective date of FAA 

AD 2019–26–01). 

(2) Where EASA AD 2021–0141 refers to its 

effective date, this AD requires using the 

effective date of this AD. 

(3) The ‘‘Remarks’’ section of EASA AD 

2021–0141 does not apply to this AD. 

(i) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, Large Aircraft 

Section, 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 responsible Flight 

Standards Office, as appropriate. If sending 

information directly to the Large Aircraft 

Section, International Validation Branch, 

send it to the attention of the person 


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9432 Federal Register / Vol. 87, No. 35 / Tuesday, February 22, 2022 / Rules and Regulations 

identified in paragraph (j) of this AD. 

Information may be emailed to: 9-AVS-AIR730-AMOC@faa.gov. 

(i) Before using any approved AMOC, 

notify your appropriate principal inspector, 

or lacking a principal inspector, the manager 

of the responsible Flight Standards Office. 

(ii) AMOCs approved previously for AD 

2019–26–01 are approved as AMOCs for the 

corresponding provisions of EASA AD 2021– 

0141 that are required by paragraph (g) of this 

AD. 

(2) Contacting the Manufacturer: For any 

requirement in this AD to obtain instructions 

from a manufacturer, the instructions must 

be accomplished using a method approved 

by the Manager, Large Aircraft Section, 

International Validation Branch, FAA; or 

EASA; or Airbus SAS’s EASA Design 

Organization Approval (DOA). If approved by 

the DOA, the approval must include the 

DOA-authorized signature. 

(3) Required for Compliance (RC): For any 

service information referenced in EASA AD 

2021–0141 that contains RC procedures and 

tests: Except as required by paragraph (i)(2) 

of this AD, RC procedures and tests must be 

done to comply with this AD; any procedures 

or tests that are not identified as RC are 

recommended. Those procedures and tests 

that are not identified as RC may be deviated 

from using accepted methods in accordance 

with the operator’s maintenance or 

inspection program without obtaining 

approval of an AMOC, provided the 

procedures and tests identified as RC can be 

done and the airplane can be put back in an 

airworthy condition. Any substitutions or 

changes to procedures or tests identified as 

RC require approval of an AMOC. 

(j) Related Information 

For more information about this AD, 

contact Dan Rodina, Aerospace Engineer, 

International Section, Transport Standards 

Branch, FAA, 2200 South 216th St., Des 

Moines, WA 98198; telephone and fax 206– 

231–3225; email dan.rodina@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 Union Aviation Safety Agency 

(EASA) AD 2021–0141, dated June 15, 2021. 

(ii) [Reserved] 

(3) For EASA AD 2021–0141, contact 

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 material 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. 

(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 

fr.inspection@nara.gov, or go to: https://

www.archives.gov/federal-register/cfr/ibrlocations.html. 

Issued on January 28, 2022. 

Lance T. Gant, 

Director, Compliance & Airworthiness 

Division, Aircraft Certification Service. 

[FR Doc. 2022–03633 Filed 2–18–22; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2022–0101; Project 

Identifier AD–2021–01456–E; Amendment 

39–21949; AD 2022–04–07] 

RIN 2120–AA64 

Airworthiness Directives; General 

Electric Company Turbofan Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule; request for 

comments. 

SUMMARY: The FAA is adopting a new 

airworthiness directive (AD) for certain 

General Electric Company (GE) GEnx– 

1B64, –1B64/P1, –1B64/P2, –1B67, 

–1B67/P1, –1B67/P2, –1B70, –1B70/75/ 

P1, –1B70/75/P2, –1B70/P1, –1B70/P2, 

–1B70C/P1, –1B70C/P2, –1B74/75/P1, 

–1B74/75/P2, –1B76/P2, –1B76A/P2, 

GEnx–2B67, –2B67B, and –2B67/P 

model turbofan engines. This AD was 

prompted by an in-flight shutdown 

(IFSD) of an engine and subsequent 

investigation by the manufacturer that 

revealed an improperly torqued fuel 

metering unit (FMU) bypass valve (BPV) 

plug. This AD requires a shim check 

inspection of the FMU BPV plug and, 

depending on the results of the 

inspection, replacement of the FMU. 

The FAA is issuing this AD to address 

the unsafe condition on these products. 

DATES: This AD is effective March 9, 

2022. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of March 9, 2022. 

The FAA must receive comments on 

this AD by April 8, 2022. 

ADDRESSES: You may send comments, 

using the procedures found in 14 CFR 

11.43 and 11.45, by any of the following 

methods: 

• Federal eRulemaking Portal: Go to 

https://www.regulations.gov. Follow the 

instructions for submitting comments. 

• Fax: (202) 493–2251. 

• Mail: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE, 

Washington, DC 20590. 

• Hand Delivery: Deliver to Mail 

address above between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

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–2022– 

0101. 

Examining the AD Docket 

You may examine the AD docket at 

https://www.regulations.gov by 

searching for and locating Docket No. 

FAA–2022–0101; 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 street address for 

the Docket Operations is listed above. 

FOR FURTHER INFORMATION CONTACT: 

Alexei Marqueen, Aviation Safety 

Engineer, ECO Branch, FAA, 1200 

District Avenue, Burlington, MA 01803; 

phone: (781) 238–7178; email: 

Alexei.T.Marqueen@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Background 

On July 20, 2021, a Boeing model 

747–8F airplane, powered by GEnx– 

2B67/P model turbofan engines, flying 

from Hong Kong to Dubai, experienced 

N1 overspeed and fire warnings that 

resulted in an IFSD and air turnback 

(ATB) to Hong Kong. After landing, the 

engine reignited and emergency crews 

extinguished the fire. The investigation 

led by the National Transportation 

Safety Board found several fuel system 

leaks including at the FMU supply 

pressure (P1) BPV pressure port with a 

loose FMU BPV plug safety cabled in 

place. Because a safety cable was in 

place, the investigation concluded that 

the FMU BPV plug might not have been 

torqued properly during production or 

during an engine shop visit. During the 

investigation, GE discovered that 

another operator, operating a Boeing 


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