Federal Register / Vol. 87, No. 134 / Thursday, July 14, 2022 / Rules and Regulations 42063 

Revision 1, dated January 10, 2008; or BAE 

Systems (Operations) Limited Service 

Bulletin J41–28–013, Revision 2, dated July 

8, 2019; and, if incorrect clearances are 

found, before next flight, adjust clearances in 

accordance with BAE Systems (Operations) 

Limited Service Bulletin J41–28–013, 

Revision 1, dated January 10, 2008; or BAE 

Systems (Operations) Limited Service 

Bulletin J41–28–013, Revision 2, dated July 

8, 2019. As of the effective date of this AD, 

BAE Systems (Operations) Limited Service 

Bulletin J41–28–013, Revision 2, dated July 

8, 2019, must be used for the actions required 

by this paragraph. 

(3) Install additional electrical bonding of 

components within the LH and RH wings in 

accordance with paragraphs 2.B.(4) through 

2.B.(15) of the Accomplishment Instructions 

of BAE Systems (Operations) Limited Service 

Bulletin J41–28–013, Revision 1, dated 

January 10, 2008; or paragraphs 2.B.(4) and 

2.B.(6) through 2.B.(16) inclusive of BAE 

Systems (Operations) Limited Service 

Bulletin J41–28–013, Revision 2, dated July 

8, 2019. As of the effective date of this AD, 

BAE Systems (Operations) Limited Service 

Bulletin J41–28–013, Revision 2, dated July 

8, 2019, must be used for the actions required 

by this paragraph. 

(h) New Requirement of This AD: Replace 

Bolts and Washers Securing Crossfeed Valve 

Within 24 months after the effective date 

of this AD, install additional bonding leads 

on components within the dry bay at Rib 1 

on the airplane centerline and below the 

fuselage (around the crossfeed valve) and 

perform a resistance check in accordance 

with paragraph 2.B.(5) of BAE Systems 

(Operations) Limited Service Bulletin J41– 

28–013, Revision 2, dated July 8, 2019. 

(i) Other FAA AD Provisions 

(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 (j)(2) of this AD. 

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

approved AMOC, notify your appropriate 

principal inspector, or lacking a principal 

inspector, the manager of the responsible 

Flight Standards Office. 

(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 the 

Civil Aviation Authority (CAA); or BAE 

Systems (Operations) Limited’s CAA Design 

Organization Approval (DOA). If approved by 

the DOA, the approval must include the 

DOA-authorized signature. 

(j) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) CAA AD 

G–2021–0013, dated October 21, 2021, for 

related information. This MCAI may be 

found in the AD docket at https://

www.regulations.gov by searching for and 

locating Docket No. FAA–2022–0461. 

(2) For more information about this AD, 

contact Todd Thompson, Aerospace 

Engineer, Large Aircraft Section, 

International Validation Branch, FAA, 2200 

South 216th St., Des Moines, WA 98198; 

telephone and fax 206–231–3228; email 

todd.thompson@faa.gov. 

(3) Service information identified in this 

AD that is not incorporated by reference is 

available at the addresses specified in 

paragraphs (k)(5) and (6) of this AD. 

(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. 

(3) The following service information was 

approved for IBR on August 18, 2022. 

(i) BAE Systems (Operations) Limited 

Service Bulletin J41–28–013, Revision 2, 

dated July 8, 2019. 

(ii) [Reserved] 

(4) The following service information was 

approved for IBR on September 9, 2008 (73 

FR 45346, August 5, 2008). 

(i) BAE Systems (Operations) Limited 

Service Bulletin J41–28–013, Revision 1, 

dated January 10, 2008. 

(ii) [Reserved] 

(5) For service information identified in 

this AD, 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 https://

www.baesystems.com/Businesses/ 

RegionalAircraft/index.htm. 

(6) You may view this 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. 

(7) 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 June 27, 2022. 

Christina Underwood, 

Acting Director, Compliance & Airworthiness 

Division, Aircraft Certification Service. 

[FR Doc. 2022–14971 Filed 7–13–22; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2022–0454; Project 

Identifier MCAI–2021–01124–T; Amendment 

39–22106; AD 2022–14–01] 

RIN 2120–AA64 

Airworthiness Directives; Airbus SAS 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: The FAA is superseding 

Airworthiness Directive (AD) 2019–03– 

25, which applied to certain Airbus SAS 

Model Airbus SAS Model A318 series 

airplanes; Model A319–111, –112, –113, 

–114, –115, –131, –132, and –133 

airplanes; Model A320–211, –212, –214, 

–216, –231, –232, and –233 airplanes; 

and Model A321–111, –112, –131, –211, 

–212, –213, –231, and –232 airplanes. 

AD 2019–03–25 required repetitive 

inspections of the center and outer wing 

box lower stiffeners and panels at a 

certain junction on the left- and righthand sides for any cracking, and repair 

if necessary. AD 2019–03–25 also 

provided an optional modification, 

which would terminate the repetitive 

inspections. This AD was prompted by 

a determination that, for certain 

airplanes, the compliance time for the 

initial inspection is inadequate and 

must be revised. This AD continues to 

require the actions specified in AD 

2019–03–25 with revised compliance 

times for certain airplanes and 

additional actions for certain airplanes, 

and expands the applicability, as 

specified in a European 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 August 18, 

2022. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of August 18, 2022. 

ADDRESSES: For material incorporated 

by reference (IBR) in this AD, 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 material on the EASA website 

at https://ad.easa.europa.eu. You may 

view this material at the FAA, 

Airworthiness Products Section, 

Operational Safety Branch, 2200 South 


jspears on DSK121TN23PROD with RULES1
42064 Federal Register / Vol. 87, No. 134 / Thursday, July 14, 2022 / Rules and Regulations 

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 at 

https://www.regulations.gov by 

searching for and locating Docket No. 

FAA–2022–0454. 

Examining the AD Docket 

You may examine the AD docket at 

https://www.regulations.gov by 

searching for and locating Docket No. 

FAA–2022–0454; 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: 

Vladimir Ulyanov, Aerospace Engineer, 

Large Aircraft Section, FAA, 

International Validation Branch, 2200 

South 216th St., Des Moines, WA 98198; 

telephone and fax 206–231–3223; email 

Vladimir.Ulyanov@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Background 

EASA, which is the Technical Agent 

for the Member States of the European 

Union, has issued EASA AD 2021–0228, 

dated October 12, 2021 (EASA AD 

2021–0228) (also referred to as the 

MCAI), to correct an unsafe condition 

for certain Airbus SAS Model A318 

series airplanes; Model A319–111, –112, 

–113, –114, –115, –131, –132, and –133 

airplanes; Model A320–211, –212, –214, 

–215, –216, –231, –232, and –233 

airplanes; and Model A321–111, –112, 

–131, –211, –212, –213, –231, and –232 

airplanes. Model A320–215 airplanes 

are not certificated by the FAA and are 

not included on the U.S. type certificate 

data sheet; this AD therefore does not 

include those airplanes in the 

applicability. 

The FAA issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to supersede AD 2019–03–25, 

Amendment 39–19577 (84 FR 8805, 

March 12, 2019) (AD 2019–03–25). AD 

2019–03–25 applied to certain Airbus 

SAS Model A318 series airplanes; 

Model A319–111, –112, –113, –114, 

–115, –131, –132, and –133 airplanes; 

Model A320–211, –212, –214, –216, 

–231, –232, and –233 airplanes; and 

Model A321–111, –112, –131, –211, 

–212, –213, –231, and –232 airplanes. 

The NPRM published in the Federal 

Register on April 11, 2022 (87 FR 

21044). The NPRM was prompted by a 

determination that, for certain airplanes, 

the compliance time for the initial 

inspection is inadequate and must be 

revised and additional actions are 

required. The NPRM proposed to 

continue to require the actions specified 

in AD 2019–03–25 with revised 

compliance times for certain airplanes 

and additional actions for certain 

airplanes, and proposed to expand the 

applicability, as specified in EASA AD 

2021–0228. 

The FAA is issuing this AD to address 

the loss of pre-tension in the fasteners, 

which could affect the structural 

integrity of the airplane. See the MCAI 

for additional background information. 

Discussion of Final Airworthiness 

Directive 

Comments 

The FAA received a comment from 

United Airlines who supported the 

NPRM without change. 

Additional Changes Made to This AD 

The FAA has added paragraph (i) to 

this AD to specify that reporting is not 

required, and redesignated subsequent 

paragraphs accordingly. The FAA has 

also removed the Paperwork Reduction 

Act portion of this AD, as it is no longer 

relevant. The FAA did not intend to 

require reporting and these revisions 

clarify that intent. 

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 2021–0228 specifies 

procedures for repetitive internal and 

external SDIs (ultrasonic inspections) of 

the center and outer wing box lower 

stiffeners and panels at the level of rib 

1 junction on the left- and right-hand 

sides for any cracking, and repair if 

necessary; and additional actions (reprotection of the inspected area at the 

lower panel at rib1 junction at the leftand right-hand sides) for airplanes on 

which certain service information was 

used. EASA AD 2021–0228 also 

specifies procedures for an optional 

modification, which would terminate 

the repetitive inspections. 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 765 airplanes of U.S. registry. 

The FAA estimates the following costs 

to comply with this AD: 

ESTIMATED COSTS FOR REQUIRED ACTIONS

Action Labor cost Parts 

cost 

Cost per 

product Cost on U.S. operators 

Retained actions from 2019–03–25 ............................... 51 work-hours × $85 per 

hour = $4,335.

$0 $4,335 $25,860 (516 airplanes). 

New additional actions .................................................... 13 work-hours × $85 per 

hour = $1,105.

0 1,105 Up to $845,325 (Up to 765 

airplanes). 

The FAA has received no definitive 

data that enables the agency to provide 

cost estimates for the repair specified in 

this AD. 

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 


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Federal Register / Vol. 87, No. 134 / Thursday, July 14, 2022 / Rules and Regulations 42065 

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) 2019–03–25, Amendment 39– 

19577 (84 FR 8805, March 12, 2019); 

and 

■ b. Adding the following new AD: 

2022–14–01 Airbus SAS: Amendment 39– 

22106; Docket No. FAA–2022–0454; 

Project Identifier MCAI–2021–01124–T. 

(a) Effective Date 

This airworthiness directive (AD) is 

effective August 18, 2022. 

(b) Affected ADs 

This AD replaces AD 2019–03–25, 

Amendment 39–19577 (84 FR 8805, March 

12, 2019) (AD 2019–03–25). 

(c) Applicability 

This AD applies to Airbus SAS Model 

A318–111, –112, –121, and –122 airplanes; 

Model A319–111, –112, –113, –114, –115, 

–131, –132, and –133 airplanes; Model 

A320–211, –212, –214, –216, –231, –232, and 

–233 airplanes; and Model A321–111, –112, 

–131, –211, –212, –213, –231, and –232 

airplanes; certificated in any category; as 

identified in European Aviation Safety 

Agency (EASA) AD 2021–0228, dated 

October 12, 2021 (EASA AD 2021–0228). 

(d) Subject 

Air Transport Association (ATA) of 

America Code 57, Wings. 

(e) Unsafe Condition 

This AD was prompted by a report that 

taperloks used in the wing-to-fuselage 

junction at rib 1 were found to be noncompliant with the applicable specification, 

resulting in a loss of pre-tension in the 

fasteners; and a determination that, for 

certain airplanes, the compliance time for the 

initial inspection is inadequate and must be 

revised and additional actions are required. 

The FAA is issuing this AD to address the 

loss of pre-tension in the fasteners, which 

could affect the structural integrity of the 

airplane. 

(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 2021–0228. 

(h) Exceptions to EASA AD 2021–0228 

(1) Where EASA AD 2021–0228 refers to its 

effective date, this AD requires using the 

effective date of this AD. 

(2) Where paragraph (3) of EASA AD 2021– 

0228 specifies to ‘‘contact Airbus for 

approved repair instructions’’ if any damage 

(cracking) is found, for this AD, if any 

cracking is found, the cracking must be 

repaired before further flight 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) The ‘‘Remarks’’ section of EASA AD 

2021–0228 does not apply to this AD. 

(i) No Reporting Requirement 

Although the service information 

referenced in EASA AD 2021–0228 specifies 

to submit certain information to the 

manufacturer, this AD does not include that 

requirement. 

(j) Additional 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 

identified in paragraph (k) of this AD. Before 

using any approved AMOC, notify your 

appropriate principal inspector, or lacking a 

principal inspector, the manager of the 

responsible Flight Standards Office. 

(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 (j)(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. 

(k) Related Information 

For more information about this AD, 

contact Vladimir Ulyanov, Aerospace 

Engineer, Large Aircraft Section, FAA, 

International Validation Branch, 2200 South 

216th St., Des Moines, WA 98198; telephone 

and fax 206–231–3223; email 

Vladimir.Ulyanov@faa.gov. 

(l) 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 2021–0228, dated October 12, 

2021. 

(ii) [Reserved] 

(3) For EASA AD 2021–0228, 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 


jspears on DSK121TN23PROD with RULES1
42066 Federal Register / Vol. 87, No. 134 / Thursday, July 14, 2022 / Rules and Regulations 

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 June 22, 2022. 

Ross Landes, 

Deputy Director for Regulatory Operations, 

Compliance & Airworthiness Division, 

Aircraft Certification Service. 

[FR Doc. 2022–14969 Filed 7–13–22; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2022–0385; Project 

Identifier MCAI–2021–00786–E; Amendment 

39–22117; AD 2022–14–12] 

RIN 2120–AA64 

Airworthiness Directives; GE Aviation 

Czech s.r.o. (Type Certificate 

Previously Held by WALTER Engines 

a.s., Walter a.s., and MOTORLET a.s.) 

Turboprop Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: The FAA is adopting a new 

airworthiness directive (AD) for certain 

GE Aviation Czech s.r.o. (GEAC) 

M601D–11, M601E–11, M601E–11A, 

M601E–11AS, M601E–11S, and M601F 

model turboprop engines. This AD was 

prompted by the absence of life limits 

for propeller shaft part number (P/N) 

M601–6081.6 in the airworthiness 

limitations section (ALS) of the 

applicable GEAC M601 Engine Shop 

Manual. This AD was also prompted by 

a report that operators may not have 

been provided with enough data to 

determine the accumulated life of 

certain propeller shafts. For M601F 

model turboprop engines, this AD 

requires removal and replacement of the 

propeller shaft before the propeller shaft 

accumulates 12,000 flight hours (FHs) 

since first installation on an engine, or 

before accumulating 350 FHs after the 

effective date of this AD, whichever 

occurs later, with a part eligible for 

installation. For M601D–11, M601E–11, 

M601E–11A, M601E–11AS, and 

M601E–11S model turboprop engines, 

this AD requires calculation of the 

accumulated life of the propeller shaft 

and, depending on the number of 

accumulated FHs removal and 

replacement of the propeller shaft with 

a part eligible for installation. The FAA 

is issuing this AD to address the unsafe 

condition on these products. 

DATES: This AD is effective August 18, 

2022. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of August 18, 2022. 

ADDRESSES: For service information 

identified in this final rule, contact GE 

Aviation Czech s.r.o., Beranovy ́ch 65, 

199 02 Praha 9, Letnˇ any, Czech 

Republic; phone: +420 222 538 111. 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– 

0385. 

Examining the AD Docket 

You may examine the AD docket at 

https://www.regulations.gov by 

searching for and locating Docket No. 

FAA–2022–0385; 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: 

Barbara Caufield, Aviation Safety 

Engineer, ECO Branch, FAA, 1200 

District Avenue, Burlington, MA 01803; 

phone: (781) 238–7146; email: 

barbara.caufield@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 certain GEAC M601D–11, 

M601E–11, M601E–11A, M601E–11AS, 

M601E–11S, and M601F model 

turboprop engines. The NPRM 

published in the Federal Register on 

April 01, 2022 (87 FR 19029). The 

NPRM was prompted by the absence of 

life limits for propeller shaft P/N M601– 

6081.6 in the ALS of the applicable 

GEAC M601 Engine Shop Manual. The 

NPRM was also prompted by a report 

that operators may not have been 

provided with enough data to determine 

the accumulated life of certain propeller 

shafts. For M601F model turboprop 

engines, the NPRM proposed to require 

removal and replacement of the 

propeller shaft with a part eligible for 

installation before the propeller shaft 

accumulates 12,000 FHs since first 

installation on an engine, or before 

accumulating 350 FHs after the effective 

date of this AD, whichever occurs later. 

For M601D–11, M601E–11, M601E– 

11A, M601E–11AS, and M601E–11S 

model turboprop engines, the NPRM 

proposed to require calculation of the 

accumulated life of the propeller shaft 

and, depending on the number of 

accumulated FHs, removal and 

replacement of the propeller shaft with 

a part eligible for installation. The FAA 

is issuing this AD to address the unsafe 

condition on these products. 

The European Union Aviation Safety 

Agency (EASA), which is the Technical 

Agent for the Member States of the 

European Union, has issued EASA AD 

2021–0154, dated July 1, 2021 (referred 

to after this as ‘‘the MCAI’’), to address 

the unsafe condition on these products. 

The MCAI states: 

It has been determined that the life limit 

for the propeller shaft P/N M601–6081.6 is 

not published in the applicable ALS for 

M601 engines. In addition, it has also been 

reported that some data, which can be used 

to determine the accumulated life of certain 

propeller shafts, may have not been provided 

to operators, so the propeller shaft life limit 

may not have been implemented correctly. 

These conditions, if not corrected, may 

lead to failure of a propeller shaft, possibly 

resulting in detachment of the propeller and 

consequent damage to the engine and/or the 

aircraft, and reduced control of the 

aeroplane. 

To address this potential unsafe condition, 

GEAC issued the original issue of the ASB, 

providing applicable instructions, and EASA 

issued AD 2021–0052 to require 

implementation of the applicable life limit 

and replacing each propeller shaft with a 

serviceable propeller shaft. 

Since that [EASA] AD was issued, 

additional data, which can be used to 

determine the accumulated life of certain 

propeller shafts, and to support an extended 

compliance time for Group 1 engines, has 

been made available; GEAC revised 

accordingly the ASB (now at revision 02). 

For the reasons described above, this 

[EASA] AD partially retains the requirements 

of EASA AD 2021–0052, which is 

superseded, introducing updated affected 

population and different compliance times. 

You may obtain further information 

by examining the MCAI in the AD 

docket at https://www.regulations.gov 

by searching for and locating Docket No. 

FAA–2022–0385. 


jspears on DSK121TN23PROD with RULES1