22122 Federal Register / Vol. 87, No. 72 / Thursday, April 14, 2022 / Rules and Regulations 

2020–0270, or within 90 days after the 

effective date of this AD, whichever occurs 

later. 

(5) The provisions specified in paragraph 

(4) of EASA AD 2020–0270 do not apply to 

this AD. 

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

2020–0270 does not apply to this AD. 

(7) For all airplanes identified in paragraph 

(c) of this AD: Where the Note for Item 

274000–00004–1–E of Section 4–1 in the 

service information referenced in EASA AD 

2020–0270 specifies ‘‘NBB carbon disc 

replacement’’ instructions, for this AD, 

replace the text ‘‘NBB carbon disc 

replacement can be accomplished in 

accordance with SB A320–27–1242 or VSB 

47145–27–17,’’ with ‘‘NBB carbon disk 

replacement must be accomplished in 

accordance with SB A320–27–1242.’’ 

(n) New Provisions for Alternative Actions 

and Intervals 

After the existing maintenance or 

inspection program has been revised as 

required by paragraph (l) of this AD, no 

alternative actions (e.g., inspections) or 

intervals are allowed unless they are 

approved as specified in the provisions of the 

‘‘Ref. Publications’’ section of EASA AD 

2020–0270. 

(o) Terminating Action for Certain 

Requirements of AD 2020–21–10 

Accomplishing the actions required by this 

AD terminates the airworthiness limitations 

section (ALS) limitation task 274000–00004– 

1–E for the THSA, as required by paragraph 

(i) of AD 2020–21–10. 

(p) Additional 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 

identified in paragraph (q)(1) 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 

2016–17–12 are approved as AMOCs for the 

corresponding provisions of paragraphs (g) 

through (j) 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): Except 

as required by paragraph (p)(2) of this AD, if 

any service information contains procedures 

or tests that are identified as RC, those 

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. 

(q) Related Information 

(1) For more information about this AD, 

contact Sanjay Ralhan, Aerospace Engineer, 

Large Aircraft Section, International 

Validation Branch, FAA, 2200 South 216th 

St., Des Moines, WA 98198; telephone and 

fax 206–231–3223; email sanjay.ralhan@

faa.gov. 

(2) For UTC Aerospace Systems service 

information identified in this AD that is not 

incorporated by reference, contact Collins 

Aerospace, Product Support Department 13, 

Avenue de L’Eguillette—Saint-Ouen 

L’Aumone, Boite Postale 7186 95056 Cergy 

Pontoise Cedex, France; telephone 1–877– 

808–7575; email crc@collins.com; internet 

https://www.collinsaerospace.com/support. 

(r) 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. 

(3) The following service information was 

approved for IBR on May 19, 2022. 

(i) European Union Aviation Safety Agency 

(EASA) AD 2020–0270, dated December 7, 

2020. 

(ii) [Reserved] 

(4) The following service information was 

approved for IBR on September 30, 2016 (81 

FR 58823, August 26, 2016). 

(i) Airbus Service Bulletin A320–27–1242, 

Revision 01, dated February 4, 2016. 

(ii) [Reserved] 

(5) For EASA AD 2020–0270, 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. 

(6) For Airbus service information, contact 

Airbus SAS, Airworthiness Office—EIAS, 

Rond-Point Emile Dewoitine No: 2, 31700 

Blagnac Cedex, France; telephone +33 5 61 

93 36 96; fax +33 5 61 93 44 51; email 

account.airworth-eas@airbus.com; internet 

https://www.airbus.com. 

(7) 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. 

(8) 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 March 18, 2022. 

Lance T. Gant, 

Director, Compliance & Airworthiness 

Division, Aircraft Certification Service. 

[FR Doc. 2022–07859 Filed 4–13–22; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2022–0400; Project 

Identifier AD–2022–00179–E; Amendment 

39–22009; AD 2022–08–06] 

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) CF34– 

8C and CF34–8E model turbofan 

engines. This AD was prompted by an 

‘‘Engine Degraded’’ message received inflight from the Engine Indicating and 

Crew Alerting System (EICAS), and a 

subsequent investigation by the 

manufacturer that revealed corrosion of 

the variable geometry (VG) system 

actuator, which can cause the full 

authority digital engine control (FADEC) 

software to command and lock the 

engine at idle until it is restarted. This 

AD requires performing a rotational 

torque check on the actuating linkage 

assembly and, depending on the results 

of the rotational torque check, 

replacement of the compressor inlet 

guide vane (IGV) outer shroud bushing 

and vane spindle bushing with parts 

eligible for installation. This AD also 

requires reporting the results of the 

rotational torque check to GE. The FAA 

is issuing this AD to address the unsafe 

condition on these products. 

DATES: AD is effective April 29, 2022. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of April 29, 2022. 

The FAA must receive comments on 

this AD by May 31, 2022. 


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Federal Register / Vol. 87, No. 72 / Thursday, April 14, 2022 / Rules and Regulations 22123 

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@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– 

0400. 

Examining the AD Docket 

You may examine the AD docket at 

https://www.regulations.gov by 

searching for and locating Docket No. 

FAA–2022–0400; 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: 

Scott Stevenson, Aviation Safety 

Engineer, ECO Branch, FAA, 1200 

District Avenue, Burlington, MA 01803; 

phone: (781) 238–7132; email: 

Scott.M.Stevenson@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Background 

On August 11, 2021, a Bombardier 

CRJ1000 airplane, powered by GE 

CF34–8C5 model turbofan engines, 

experienced an in-flight engine 

shutdown that resulted in a diversion. 

The manufacturer’s investigation found 

that this airplane was parked outdoors 

for extended lengths of time within 10 

miles (16 km) from a saltwater coastline, 

causing corrosion to develop on the 

CF34–8C5 engines’ compressor VG 

actuator rod, seizure of the rod end 

bearing, and fracture of the rod end. 

Based on the manufacturer’s 

investigation, on November 4, 2021, the 

FAA issued Emergency AD 2021–23–51 

(followed by publication in the Federal 

Register on December 14, 2021, as a 

Final Rule, Request for Comments (86 

FR 70969)), which requires performing 

an inspection of the master compressor 

VG actuator and slave compressor VG 

actuator on certain GE CF34–8C and 

CF34–8E model turbofan engines and, 

depending on the results of the 

inspection, replacement of the part with 

a part eligible for installation. 

Since the FAA issued AD 2021–23– 

51, the manufacturer determined that 

two additional in-flight events occurred 

that were related to this unsafe 

condition. On September 7, 2021 and 

October 26, 2021, two Bombardier CRJ– 

900 airplanes powered by GE CF34–8C5 

model turbofan engines received 

‘‘Engine Degraded’’ messages from the 

EICAS during flight. A subsequent 

investigation by the manufacturer found 

that these engines were operated 

infrequently over the past 2 years, with 

one engine showing corrosion findings 

after being stored approximately 45 

miles (72 km) from a saltwater coastline, 

and another engine showing corrosion 

findings after being installed on an 

airplane parked for over 250 days. The 

manufacturer’s investigation concluded 

that engines stored outdoors for 250 or 

more days are at risk of the excessive 

corrosion build up, with the risk 

increasing if the engines were stored 

outdoors in close proximity to a 

saltwater coastline. These conditions 

caused corrosion to develop between 

the high-pressure compressor case and 

vane bushings, increasing the VG 

actuation loads and slowing the VG 

response. As a result, the VG command 

and actual positions exceeded 

acceptable disagreement parameters, 

triggering an EICAS ‘‘Engine Degraded’’ 

message. In response to the ‘‘Engine 

Degraded’’ message, all versions of the 

full authority digital engine control 

(FADEC) software on GE CF34–8E 

engines, and FADEC software earlier 

than Version 6.60 on GE CF34–8C 

engines automatically reduces the 

engine to idle and locks the throttle 

until the engine is shut down and 

restarted. This condition, if not 

addressed, could result in failure of one 

or more engines, loss of engine thrust 

control, and reduced control of the 

airplane. The FAA is issuing this AD to 

address the unsafe condition on these 

products. 

FAA’s Determination 

The FAA is issuing this AD because 

the agency has determined the unsafe 

condition described previously is likely 

to exist or develop in other products of 

the same type design. 

Related Service Information Under 1 

CFR Part 51 

The FAA reviewed GE CF34–8C 

Service Bulletin (SB) 72–0356 R00 and 

GE CF34–8E SB 72–0244 R00, both 

dated February 15, 2022. These SBs 

specify procedures for performing a onetime rotational torque check of the 

actuating linkage assembly, 

differentiated by engine model, to 

identify possible interface corrosion or 

seizure on the compressor case, 

compressor IGV outer shroud bushing, 

vane spindle bushing, compressor stator 

IGV variable vane, compressor stator 

stage 1 variable vane, compressor stator 

stage 2 variable vane, compressor stator 

stage 3 variable vane, and compressor 

stator stage 4 variable vane. These SBs 

also specify instructions for operators to 

report the rotational torque check 

results to GE. This service information 

is reasonably available because the 

interested parties have access to it 

through their normal course of business 

or by the means identified in 

ADDRESSES. 

AD Requirements 

This AD requires performing a 

rotational torque check on the actuating 

linkage assembly and, depending on the 

results of the rotational torque check, 

replacement of the compressor IGV 

outer shroud bushing and vane spindle 

bushing with parts eligible for 

installation. This AD also requires 

reporting the results of the rotational 

torque check to GE. 

Interim Action 

The FAA considers this AD to be an 

interim action. The inspection reports 

that are required by this AD will enable 

the manufacturer to obtain better insight 

into the nature, cause, and extent of the 

corrosion, and eventually to develop 

final action to address the unsafe 

condition. Once final action has been 

identified, the FAA might consider 

further rulemaking. 

Justification for Immediate Adoption 

and Determination of the Effective Date 

Section 553(b)(3)(B) of the 

Administrative Procedure Act (APA) (5 

U.S.C. 551 et seq.) authorizes agencies 

to dispense with notice and comment 

procedures for rules when the agency, 

for ‘‘good cause,’’ finds that those 

procedures are ‘‘impracticable, 

unnecessary, or contrary to the public 

interest.’’ Under this section, an agency, 

upon finding good cause, may issue a 

final rule without providing notice and 

seeking comment prior to issuance. 


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22124 Federal Register / Vol. 87, No. 72 / Thursday, April 14, 2022 / Rules and Regulations 

Further, section 553(d) of the APA 

authorizes agencies to make rules 

effective in less than thirty days, upon 

a finding of good cause. 

An unsafe condition exists that 

requires the immediate adoption of this 

AD without providing an opportunity 

for public comments prior to adoption. 

The FAA has found that the risk to the 

flying public justifies foregoing notice 

and comment prior to adoption of this 

rule. The FAA considers corrosion of 

the VG system actuator to be an urgent 

safety issue. Performance of a rotational 

torque check of the actuating linkage 

assembly will detect excessive corrosion 

build up on the VG system actuator. 

This rotational torque check is 

necessary to prevent failure of one or 

more engines, loss of engine thrust 

control, and reduced control of the 

airplane. Engines installed on airplanes 

parked outdoors for 250 or more days 

are at risk of excessive corrosion build 

up. The risk of the excessive corrosion 

build up increases if the engines are 

stored outdoors in close proximity to a 

saltwater coastline. For affected engines 

installed on airplanes that were parked 

outdoors within 10 miles of a saltwater 

coastline, a rotational torque check on 

the actuating linkage assembly must be 

accomplished within 30 flight hours or 

5 calendar days after the effective date 

of this AD. For affected engines 

installed on airplanes that were parked 

outdoors within 50 miles of a saltwater 

coastline, a rotational torque check of 

the actuating linkage assembly must be 

accomplished within 200 FHs or 35 

calendar days after the effective date of 

this AD. Additionally, for all other 

affected engines installed on airplanes 

that were parked outdoors, the 

rotational torque check on the actuating 

linkage assembly must be accomplished 

before exceeding 880 FHs. According to 

fleet data, 880 FHs is approximately 100 

calendar days. For affected engines with 

an actuating linkage assembly that does 

not pass the rotational torque check, this 

AD requires replacement of the 

compressor IGV outer shroud bushing 

and vane spindle bushing before further 

flight. Accordingly, notice and 

opportunity for prior public comment 

are impracticable and contrary to the 

public interest pursuant to 5 U.S.C. 

553(b)(3)(B). 

In addition, the FAA finds that good 

cause exists pursuant to 5 U.S.C. 553(d) 

for making this amendment effective in 

less than 30 days, for the same reasons 

the FAA found good cause to forego 

notice and comment. 

Comments Invited 

The FAA invites you to send any 

written data, views, or arguments about 

this final rule. Send your comments to 

an address listed under ADDRESSES. 

Include ‘‘Docket No. FAA–2022–0400 

and Project Identifier AD–2022–00179– 

E’’ at the beginning of your comments. 

The most helpful comments reference a 

specific portion of the final rule, explain 

the reason for any recommended 

change, and include supporting data. 

The FAA will consider all comments 

received by the closing date and may 

amend this final rule because of those 

comments. 

Except for Confidential Business 

Information (CBI) as described in the 

following paragraph, and other 

information as described in 14 CFR 

11.35, the FAA will post all comments 

received, without change, to https://

www.regulations.gov, including any 

personal information you provide. The 

agency will also post a report 

summarizing each substantive verbal 

contact received about this final rule. 

Confidential Business Information 

CBI is commercial or financial 

information that is both customarily and 

actually treated as private by its owner. 

Under the Freedom of Information Act 

(FOIA) (5 U.S.C. 552), CBI is exempt 

from public disclosure. If your 

comments responsive to this AD contain 

commercial or financial information 

that is customarily treated as private, 

that you actually treat as private, and 

that is relevant or responsive to this AD, 

it is important that you clearly designate 

the submitted comments as CBI. Please 

mark each page of your submission 

containing CBI as ‘‘PROPIN.’’ The FAA 

will treat such marked submissions as 

confidential under the FOIA, and they 

will not be placed in the public docket 

of this AD. Submissions containing CBI 

should be sent to Scott Stevenson, 

Aviation Safety Engineer, ECO Branch, 

FAA, 1200 District Avenue, Burlington, 

MA 01803. Any commentary that the 

FAA receives which is not specifically 

designated as CBI will be placed in the 

public docket for this rulemaking. 

Regulatory Flexibility Act 

The requirements of the Regulatory 

Flexibility Act (RFA) do not apply when 

an agency finds good cause pursuant to 

5 U.S.C. 553 to adopt a rule without 

prior notice and comment. Because FAA 

has determined that it has good cause to 

adopt this rule without prior notice and 

comment, RFA analysis is not required. 

Costs of Compliance 

The FAA estimates that this AD 

affects 617 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 

Rotation torque check of actuating linkage assembly .. 2 work-hours × $85 per hour = $170 $0 $170 $104,890 

Report results of rotational torque check ...................... 1 work-hour × $85 per hour = $85 .. 0 85 52,445 

The FAA estimates the following 

costs to do any necessary replacement 

that would be required based on the 

results of the rotational torque check. 

The agency has no way of determining 

the number of aircraft that might need 

these replacements: 

ON-CONDITION COSTS

Action Labor cost Parts cost Cost per 

product 

Replace compressor IGV outer shroud bushing and 

vane spindle bushing.

2 work-hours × $85 per hour = $170 ........................... $25,622 $25,792 


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Federal Register / Vol. 87, No. 72 / Thursday, April 14, 2022 / Rules and Regulations 22125 

Paperwork Reduction Act 

A federal agency may not conduct or 

sponsor, and a person is not required to 

respond to, nor shall a person be subject 

to a penalty for failure to comply with 

a collection of information subject to the 

requirements of the Paperwork 

Reduction Act unless that collection of 

information displays a currently valid 

OMB Control Number. The OMB 

Control Number for this information 

collection is 2120–0056. Public 

reporting for this collection of 

information is estimated to be 

approximately 1 hour per response, 

including the time for reviewing 

instructions, searching existing data 

sources, gathering and maintaining the 

data needed, and completing and 

reviewing the collection of information. 

All responses to this collection of 

information are mandatory. Send 

comments regarding this burden 

estimate or any other aspect of this 

collection of information, including 

suggestions for reducing this burden to: 

Information Collection Clearance 

Officer, Federal Aviation 

Administration, 10101 Hillwood 

Parkway, Fort Worth, TX 76177–1524. 

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. 

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: 

2022–08–06 General Electric Company: 

Amendment 39–22009; Docket No. 

FAA–2022–0400; Project Identifier AD– 

2022–00179–E. 

(a) Effective Date 

This airworthiness directive (AD) is 

effective April 29, 2022. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to General Electric 

Company (GE) CF34–8C1, CF34–8C5, CF34– 

8C5A1, CF34–8C5A2, CF34–8C5A3, CF34– 

8C5B1, CF34–8E2, CF34–8E2A1, CF34–8E5, 

CF34–8E5A1, CF34–8E5A2, CF34–8E6, and 

CF34–8E6A1 model turbofan engines 

installed on an airplane that has accumulated 

250 or more parked days outdoors within the 

24 months prior to the effective date of this 

AD. 

(d) Subject 

Joint Aircraft System Component (JASC) 

Code 7230, Turbine Engine Compression 

Section. 

(e) Unsafe Condition 

This AD was prompted by an ‘‘Engine 

Degraded’’ message received in-flight from 

the Engine Indicating and Crew Alerting 

System (EICAS), and a subsequent 

investigation by the manufacturer that 

revealed corrosion of the variable geometry 

(VG) system actuator. The FAA is issuing this 

AD to detect corrosion of the VG system 

actuator. The unsafe condition, if not 

addressed, could result in failure of one or 

more engines, loss of engine thrust control, 

and reduced control of the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Required Actions 

(1) Torque Check: CF34–8C Model Turbofan 

Engines With Full Authority Digital Engine 

Control (FADEC) Software (SW) Below 

Version 6.60, and All Affected CF34–8E 

Model Turbofan Engines 

(i) If the affected engine is installed on an 

airplane that was parked less than or equal 

to 10 miles from a saltwater coastline for 250 

or more parked days, within 30 flight hours 

(FHs) or 5 calendar days, whichever occurs 

first after the effective date of this AD, 

perform a rotational torque check of the 

actuating linkage assembly. If an airplane has 

two affected engines installed while parked 

less than or equal to 10 miles from a 

saltwater coastline for 250 or more parked 

days, operators may perform the rotational 

torque check of the actuating linkage 

assembly on the second engine before the 

second engine exceeds 440 FHs after the 

effective date of this AD. 

(ii) For affected engines not requiring the 

performance of a rotational torque check by 

paragraph (g)(1)(i) of this AD, if the affected 

engine is installed on an airplane that was 

parked less than or equal to 50 miles from 

a saltwater coastline for 250 or more parked 

days, within 200 FHs or 35 calendar days, 

whichever occurs first after the effective date 

of this AD, perform a rotational torque check 

of the actuating linkage assembly. If an 

airplane has two affected engines installed 

while parked less than or equal to 50 miles 

from a saltwater coastline for 250 or more 

parked days, operators may perform the 

rotational torque check of the actuating 

linkage assembly on the second engine before 

the second engine exceeds 880 FHs after the 

effective date of this AD. 

(iii) For affected engines not requiring the 

performance of a rotational torque check by 

paragraphs (g)(1)(i) or (g)(1)(ii) of this AD, 

before exceeding 880 FHs after the effective 

date of this AD, perform a rotational torque 

check of the actuating linkage assembly. If an 

airplane has two affected engines installed, 

operators may perform the rotational torque 

check of the actuating linkage assembly on 

the second engine before the second engine 

exceeds 1,680 FHs after the effective date of 

this AD. 

(2) Torque Check: CF34–8C Model Turbofan 

Engines With FADEC SW Version 6.60 or 

Above Installed on an Airplane That Is in 

Service as of the Effective Date of This AD 

(i) If the affected engine is installed on an 

airplane that was parked less than or equal 

to 10 miles from a saltwater coastline for 250 

or more parked days, within 200 FHs or 35 

calendar days, whichever occurs first after 

the effective date of this AD, perform a 

rotational torque check of the actuating 

linkage assembly. If an airplane has two 

affected engines installed while parked less 

than or equal to 10 miles from a saltwater 

coastline for 250 or more parked days, 

operators may perform the rotational torque 

check of the actuating linkage assembly on 

the second engine before the second engine 


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22126 Federal Register / Vol. 87, No. 72 / Thursday, April 14, 2022 / Rules and Regulations 

exceeds 880 FHs after the effective date of 

this AD. 

(ii) For affected engines not requiring the 

performance of a rotational torque check by 

paragraph (g)(2)(i) of this AD, if the affected 

engine is installed on an airplane that was 

parked less than or equal to 50 miles from 

a saltwater coastline for 250 or more parked 

days, before exceeding 440 FHs after the 

effective date of this AD, perform a rotational 

torque check of the actuating linkage 

assembly. If an airplane has two affected 

engines installed while parked less than or 

equal to 50 miles from a saltwater coastline 

for 250 or more parked days, operators may 

perform the rotational torque check of the 

actuating linkage assembly on the second 

engine before the second engine exceeds 880 

FHs after the effective date of this AD. 

(iii) For affected engines not requiring the 

performance of a rotational torque check by 

paragraphs (g)(2)(i) or (g)(2)(ii) of this AD, 

before exceeding 880 FHs after the effective 

date of this AD, perform a rotational torque 

check of the actuating linkage assembly. If an 

airplane has two affected engines installed, 

operators may perform the rotational torque 

check of the actuating linkage assembly on 

the second engine before the second engine 

exceeds 1,680 FHs after the effective date of 

this AD. 

(3) Torque Check: All Affected Engines That 

Are Not currently in Service 

If the affected engine is installed on an 

airplane that was parked outdoors for 250 or 

more parked days within the 24 months prior 

to re-entering service, or if the engine was 

off-wing and stored outdoors for 250 or more 

days within the 24 months prior to reentering 

service, before further flight, perform a 

rotational torque check of the actuating 

linkage assembly. 

(4) Replacement of the Compressor Inlet 

Guide Vane (IGV) Outer Shroud Bushing and 

Vane Spindle Bushing 

If the actuating linkage assembly does not 

pass any rotational torque check required by 

paragraphs (g)(1) through (3) of this AD, 

before further flight, remove the compressor 

IGV outer shroud bushing and vane spindle 

bushing and replace with a zero cycles since 

new compressor IGV outer shroud bushing 

and vane spindle bushing. 

(5) Service Information for Performance of 

the Rotational Torque Check and 

Replacement of the Compressor IGV Outer 

Shroud Bushing and Vane Spindle Bushing 

Use the Accomplishment Instructions, 

paragraph 3.A.(1)(c), of GE CF34–8C Service 

Bulletin (SB) 72–0356 R00 or GE CF34–8E SB 

72–0244 R00, both dated February 15, 2022, 

as applicable to the engine model, to perform 

the actions required by paragraphs (g)(1) 

through (4) of this AD. 

(h) Reporting Requirements 

Within 10 days after performing the 

rotational torque check required by 

paragraphs (g)(1) through (3) of this AD, in 

accordance with paragraph 3.A.(1)(c), of GE 

CF34–8C SB 72–0356 or GE CF34–8E SB 72– 

0244, send your inspection report form, 

pictures, or report findings to GE at 

aviation.fleetsupport@ge.com. 

(i) Definition 

(1) For the purpose of this AD, a ‘‘parked 

day’’ is 24 consecutive hours without engine 

operation. 

(2) For the purpose of this AD, ‘‘outdoors’’ 

is any location that is not environmentally 

controlled, including any nonenvironmentally controlled facility. 

(j) Special Flight Permit 

Special flight permits are prohibited. 

(k) 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 (l) of this AD and 

email it 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. 

(l) 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; email: Scott.M.Stevenson@faa.gov. 

(m) 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) GE CF34–8C Service Bulletin (SB) 72– 

0356 R00, dated February 15, 2022. 

(ii) GE CF34–8E SB 72–0244 R00, dated 

February 15, 2022. 

(3) For GE service information identified in 

this AD, contact General Electric Company, 

1 Neumann Way, Cincinnati, OH 45215; 

phone: (513) 552–3272; email: 

aviation.fleetsupport@ge.com; website: 

https://www.ge.com. 

(4) You may view this service information 

at 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. 

(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 April 4, 2022. 

Lance T. Gant, 

Director, Compliance & Airworthiness 

Division, Aircraft Certification Service. 

[FR Doc. 2022–08037 Filed 4–11–22; 4:15 pm] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2021–1013; Project 

Identifier MCAI–2020–01530–T; Amendment 

39–21980; AD 2022–06–14] 

RIN 2120–AA64 

Airworthiness Directives; BAE 

Systems (Operations) Limited 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: The FAA is superseding 

Airworthiness Directive (AD) 2017–12– 

08, which applied to all BAE Systems 

(Operations) Limited Model BAe 146– 

100A, –200A, and –300A airplanes; and 

Model Avro 146–RJ70A, 146–RJ85A, 

and 146–RJ100A airplanes. AD 2017– 

12–08 required revising the 

maintenance or inspection program, as 

applicable, to incorporate new or 

revised structural inspection 

requirements. This AD requires revising 

the existing maintenance or inspection 

program, as applicable, to incorporate 

new or more restrictive airworthiness 

limitations. This AD was prompted by 

a determination that new or more 

restrictive airworthiness limitations are 

necessary. The FAA is issuing this AD 

to address the unsafe condition on these 

products. 

DATES: This AD is effective May 19, 

2022. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of May 19, 2022. 

ADDRESSES: For service information 

identified in this final rule, contact BAE 

Systems (Operations) Limited, Customer 

Information Department, Prestwick 

International Airport, Ayrshire, KA9 

2RW, Scotland, United Kingdom; 

telephone +44 1292 675207; fax +44 

1292 675704; email RApublications@

baesystems.com; internet http://

www.baesystems.com/Businesses/ 

RegionalAircraft/index.htm. You may 

view this referenced service information 

at the FAA, Airworthiness Products 

Section, Operational Safety Branch, 


lotter on DSK11XQN23PROD with RULES1