15896 Federal Register / Vol. 87, No. 54 / Monday, March 21, 2022 / Proposed Rules 

§ 39.13 [Amended] 

■ 2. The FAA amends § 39.13 by adding 

the following new airworthiness 

directive: 

Leonardo S.p.a.: Docket No. FAA–2022– 

0282; Project Identifier MCAI–2021– 

01208–R. 

(a) Comments Due Date 

The FAA must receive comments on this 

airworthiness directive (AD) by May 5, 2022. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Leonardo S.p.a. Model 

AW169 helicopters, certificated in any 

category, as identified in European Union 

Aviation Safety Agency (EASA) AD 2021– 

0238, dated November 2, 2021 (EASA AD 

2021–0238). 

(d) Subject 

Joint Aircraft Service Component (JASC) 

Code: 2800, Aircraft Fuel System. 

(e) Unsafe Condition 

This AD was prompted by a report of 

blockage in a fuel tank vent line. The FAA 

is issuing this AD to detect and address the 

blockage. The unsafe condition, if not 

addressed, could result in dual engine 

flameout due to fuel starvation and a 

subsequent forced landing. 

(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 2021–0238. 

(h) Exceptions to EASA AD 2021–0238 

(1) Where EASA AD 2021–0238 requires 

compliance in terms of flight hours, this AD 

requires using hours time-in-service. 

(2) Where EASA AD 2021–0238 refers to its 

effective date, this AD requires using the 

effective date of this AD. 

(3) Where the service information 

referenced in paragraph (1) of EASA AD 

2021–0238 specifies recording the inspection 

outcome in the report in ANNEX A (of the 

service information), this AD does not 

require that action. 

(4) Where the service information 

referenced in paragraph (1) of EASA AD 

2021–0238 specifies inspecting ‘‘the left/right 

vent line for evidence of a partial or total 

Proseal obstruction,’’ this AD requires 

inspecting for a partial or total Proseal 

obstruction. 

(5) Where the service information 

referenced in EASA AD 2021–0238 specifies 

immediately contacting Leonardo Company 

Product Support Engineering and waiting for 

further instructions before proceeding if there 

is any Proseal obstruction in any fuel tank 

vent line, this AD does not require that 

action. 

(6) Where the service information 

referenced in paragraph (2) of EASA AD 

2021–0238 specifies to ‘‘carefully remove the 

Proseal obstruction by means of a suitable 

method,’’ this AD requires, before further 

flight, accomplishing repairs in accordance 

with a method approved by the Manager, 

General Aviation & Rotorcraft Section, 

International Validation Branch, FAA; or 

EASA; or Leonardo S.p.a. Helicopters’ EASA 

Design Organization Approval (DOA). If 

approved by the DOA, the approval must 

include the DOA-authorized signature. 

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

0238 specifies contacting Leonardo for 

approved corrective actions and 

accomplishing those instructions within the 

compliance time specified therein, this AD 

requires, before further flight, accomplishing 

repairs in accordance with a method 

approved by the Manager, General Aviation 

& Rotorcraft Section, International Validation 

Branch, FAA; or EASA; or Leonardo S.p.a. 

Helicopters’ EASA DOA. If approved by the 

DOA, the approval must include the DOAauthorized signature. 

(8) This AD does not mandate compliance 

with the ‘‘Remarks’’ section of EASA AD 

2021–0238. 

(i) No Reporting Requirement 

Although the service information 

referenced in EASA AD 2021–0238 specifies 

to submit certain information to the 

manufacturer, this AD does not include that 

requirement. 

(j) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, 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 local 

Flight Standards District Office, as 

appropriate. If sending information directly 

to the manager of the International Validation 

Branch, send it to the attention of the person 

identified in paragraph (k)(2) of this AD. 

Information may be emailed to: 9-AVS-AIR730-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. 

(k) Related Information 

(1) For EASA AD 2021–0238, 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 the 

EASA material on the EASA website at 

https://ad.easa.europa.eu. You may view this 

material at the FAA, Office of the Regional 

Counsel, Southwest Region, 10101 Hillwood 

Pkwy., Room 6N–321, Fort Worth, TX 76177. 

For information on the availability of this 

material at the FAA, call (817) 222–5110. 

This material may be found in the AD docket 

at https://www.regulations.gov by searching 

for and locating Docket No. FAA–2022–0282. 

(2) For more information about this AD, 

contact Andrea Jimenez, Aerospace Engineer, 

COS Program Management Section, 

Operational Safety Branch, Compliance & 

Airworthiness Division, FAA, 1600 Stewart 

Ave., Suite 410, Westbury, NY 11590; 

telephone (516) 228–7330; email 

andrea.jimenez@faa.gov. 

Issued on March 10, 2022. 

Lance T. Gant, 

Director, Compliance & Airworthiness 

Division, Aircraft Certification Service. 

[FR Doc. 2022–05590 Filed 3–18–22; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2022–0160; Project 

Identifier AD–2022–00009–E] 

RIN 2120–AA64 

Airworthiness Directives; CFM 

International, S.A. Turbofan Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: The FAA proposes to adopt a 

new airworthiness directive (AD) for 

certain CFM International, S.A. (CFM) 

LEAP–1A model turbofan engines. This 

proposed AD was prompted by reports 

of two in-flight shutdowns (IFSDs) and 

subsequent investigation by the 

manufacturer that revealed cracks in the 

high-pressure turbine (HPT) rotor stage 

1 blades. This proposed AD would 

require initial and repetitive borescope 

inspections (BSIs) of the HPT rotor stage 

1 blades and HPT stator stage 1 nozzle 

set. Depending on the results of the 

BSIs, this proposed AD would require 

either additional BSIs at reduced 

intervals or replacement of the HPT 

rotor stage 1 blades or HPT stator stage 

1 nozzle set. This proposed AD would 

also require sending the inspection 

results to CFM if any unserviceable 

finding is found. The FAA is proposing 

this AD to address the unsafe condition 

on these products. 

DATES: The FAA must receive comments 

on this proposed AD by May 5, 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 


khammond on DSKJM1Z7X2PROD with PROPOSALS
Federal Register / Vol. 87, No. 54 / Monday, March 21, 2022 / Proposed Rules 15897 

p.m., Monday through Friday, except 

Federal holidays. 

For service information identified in 

this NPRM, contact CFM International, 

S.A., Aviation Operations Center, 1 

Neumann Way, M/D Room 285, 

Cincinnati, OH 45125; phone: (877) 

432–3272; email: aviation.fleetsupport@

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. 

Examining the AD Docket 

You may examine the AD docket at 

https://www.regulations.gov by 

searching for and locating Docket No. 

FAA–2022–0160; 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 

NPRM, any comments received, and 

other information. The street address for 

Docket Operations is listed above. 

FOR FURTHER INFORMATION CONTACT: 

Mehdi Lamnyi, Aviation Safety 

Engineer, ECO Branch, FAA, 1200 

District Avenue, Burlington, MA 01803; 

phone: (781) 238–7743; email: 

Mehdi.Lamnyi@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

The FAA invites you to send any 

written relevant data, views, or 

arguments about this proposal. Send 

your comments to an address listed 

under ADDRESSES. Include ‘‘Docket No. 

FAA–2022–0160; Project Identifier AD– 

2022–00009–E’’ at the beginning of your 

comments. The most helpful comments 

reference a specific portion of the 

proposal, 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 proposal 

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 NPRM. 

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 NPRM 

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 NPRM, 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 

NPRM. Submissions containing CBI 

should be sent to Mehdi Lamnyi, 

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. 

Background 

The FAA received reports of two 

single-engine IFSDs on airplanes 

powered by LEAP–1A model turbofan 

engines, operating extensively in the 

Middle East and North Africa (MENA) 

region. A post-flight BSI of the HPT 

module revealed that the engine failures 

were due to cracks in the HPT rotor 

stage 1 blades. After investigation, the 

manufacturer determined that engines 

operating in the MENA region are 

susceptible to accelerated HPT rotor 

stage 1 blade deterioration and airfoil 

distress due to the build-up of dust. 

This unsafe condition, if not addressed, 

could result in failure of the engine, inflight shutdown, loss of thrust control, 

and loss of the airplane. 

FAA’s Determination 

The FAA is issuing this NPRM after 

determining that the unsafe condition 

described previously is likely to exist or 

develop on other products of the same 

type design. 

Related Service Information Under 1 

CFR Part 51 

The FAA reviewed CFM Service 

Bulletin (SB) LEAP–1A–72–00–0461– 

01A–930A–D, Issue 002–00, dated 

December 21, 2021. This SB specifies 

procedures for performing a BSI of the 

HPT rotor stage 1 blades and HPT stator 

stage 1 nozzle set for LEAP–1A model 

turbofan engines operating in the MENA 

region, performing all applicable 

corrective actions, and reporting any 

unserviceable results to CFM. 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. 

Proposed AD Requirements in This 

NPRM 

This proposed AD would require 

initial and repetitive BSIs of the HPT 

rotor stage 1 blades and HPT stator stage 

1 nozzle set and, depending on the 

results of the inspections, additional 

BSIs at reduced intervals or replacement 

of the HPT rotor stage 1 blades or HPT 

stator stage 1 nozzle set. This proposed 

AD would also require a BSI of the HPT 

rotor stage 1 blades and HPT stator stage 

1 nozzle set installed on the sister 

engine of the same airplane if certain 

criteria are met. This proposed AD 

would also require sending the 

inspection results to CFM if any 

unserviceable finding is found. 

Differences Between This Proposed AD 

and the Service Information 

The Accomplishment Instructions, 

paragraphs 5.E.(1)(g)2 and 5.E.(1)(g)3, of 

CFM SB LEAP–1A–72–00–0461–01A– 

930A–D, Issue 002–00, dated December 

21, 2021, specify removing one engine 

if certain conditions exist, whereas this 

proposed AD would require 

replacement of the HPT rotor stage 1 

blades or HPT stator stage 1 nozzle set 

if certain conditions exist. 

Interim Action 

The FAA considers that this proposed 

AD would be an interim action. The 

inspection reports that would be 

required by this proposed AD will 

enable the manufacturer to obtain better 

insight into the nature, cause, and 

extent of the cracking, and eventually to 

develop final action to address the 

unsafe condition. Once final action has 

been identified, the FAA might consider 

additional rulemaking. 

Costs of Compliance 

The FAA estimates that this AD, if 

adopted as proposed, would affect 0 

engines installed on airplanes of U.S. 

registry. 

The FAA estimates the following 

costs to comply with this proposed AD: 


khammond on DSKJM1Z7X2PROD with PROPOSALS
15898 Federal Register / Vol. 87, No. 54 / Monday, March 21, 2022 / Proposed Rules 

ESTIMATED COSTS

Action Labor cost Parts cost Cost per 

product 

Cost on U.S. 

operators 

BSI the HPT rotor stage 1 blades and HPT stator 

stage 1 nozzle set.

4 work-hours × $85 per hour = $340 ... $0 $340 $0 

The FAA estimates the following 

costs to do any necessary reporting and 

replacements that would be required 

based on the results of the proposed 

inspections. The agency has no way of 

determining the number of airplanes 

that might need these replacements. 

ON-CONDITION COSTS

Action Labor cost Parts cost Cost per 

product 

Replace the HPT rotor stage 1 blades ........................ 150 work-hours × $85 per hour = $12,750 .................. $988,200 $1,000,950 

Replace the HPT stator stage 1 nozzle set ................. 24 work-hours × $85 per hour = $2,040 ...................... 701,460 703,500 

BSI the HPT rotor stage 1 blades and HPT stator 

stage 1 nozzle set (on the sister engine).

4 work-hours × $85 per hour = $340 ........................... 0 340 

Report BSI results to CFM ........................................... 1 work-hour × $85 per hour = $85 ............................... 0 85 

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 current 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 take 

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 

The FAA determined that this 

proposed AD would not have federalism 

implications under Executive Order 

13132. This proposed AD would 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 this proposed regulation: 

(1) Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866, 

(2) Would not affect intrastate 

aviation in Alaska, and 

(3) Would 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 Proposed Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA proposes to amend 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: 

CFM International, S.A.: Docket No. FAA– 

2022–0160; Project Identifier AD–2022– 

00009–E. 

(a) Comments Due Date 

The FAA must receive comments on this 

airworthiness directive (AD) by May 5, 2022. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to CFM International, S.A. 

(CFM) LEAP–1A23, LEAP–1A24, LEAP– 

1A24E1, LEAP–1A26, LEAP–1A26CJ, LEAP– 

1A26E1, LEAP–1A29, LEAP–1A29CJ, LEAP– 

1A30, LEAP–1A32, LEAP–1A33, LEAP– 

1A33B2, and LEAP–1A35A model turbofan 

engines with an installed high-pressure 

turbine (HPT) rotor stage 1 blade, having part 

number (P/N) 2747M92P01, P/N 

2553M91G03, P/N 2553M91G05, P/N 

2553M91G06, P/N 2553M91G07, or P/N 

2553M91G08 that has accumulated more 

than 800 Middle East and North Africa 

(MENA) takeoffs. 

(d) Subject 

Joint Aircraft System Component (JASC) 

Code 7250, Turbine Section. 

(e) Unsafe Condition 

This AD was prompted by reports of two 

in-flight shutdowns and subsequent 

investigation by the manufacturer that 

revealed cracks in the HPT rotor stage 1 

blades. The FAA is issuing this AD to 

prevent failure of the HPT rotor stage 1 


khammond on DSKJM1Z7X2PROD with PROPOSALS
Federal Register / Vol. 87, No. 54 / Monday, March 21, 2022 / Proposed Rules 15899 

blades. The unsafe condition, if not 

addressed, could result in failure of the 

engine, in-flight shutdown, loss of thrust 

control, and loss of the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Required Actions 

(1) Group 1 Engines: Borescope Inspection 

(BSI) of HPT Rotor Stage 1 Blades and HPT 

Stator Stage 1 Nozzle Set 

For Group 1 engines with an affected HPT 

rotor stage 1 blade installed: 

(i) Within 100 flight cycles (FCs) after 

accumulating 800 MENA takeoffs on the HPT 

rotor stage 1 blade, before the HPT rotor stage 

1 blade accumulates 1,750 cycles since new 

(CSN), or within 100 FCs after the effective 

date of this AD, whichever occurs later, 

perform an initial BSI of the HPT rotor stage 

1 blades and HPT stator stage 1 nozzle set in 

accordance with the Accomplishment 

Instructions, paragraphs 5.E.(1)(c) and 

5.E.(1)(d), of CFM Service Bulletin LEAP– 

1A–72–00–0461–01A–930A–D, Issue 002–00, 

dated December 21, 2021 (the SB). 

(ii) Thereafter, at intervals not to exceed 

150 FCs since the last BSI, perform a 

repetitive BSI of the HPT rotor stage 1 blades 

and HPT stator stage 1 nozzle set in 

accordance with the Accomplishment 

Instructions, paragraphs 5.E.(1)(c) and 

5.E.(1)(d), of the SB. 

(2) Group 2 Engines: BSI of HPT Rotor Stage 

1 Blades and HPT Stator Stage 1 Nozzle Set 

For Group 2 engines with an affected HPT 

rotor stage 1 blade installed: 

(i) Within 100 FCs after accumulating 800 

MENA takeoffs on the HPT rotor stage 1 

blade, before the HPT rotor stage 1 blade 

accumulates 2,600 CSN, or within 100 FCs 

after the effective date of this AD, whichever 

occurs later, perform an initial BSI of the 

HPT rotor stage 1 blades and HPT stator stage 

1 nozzle set in accordance with the 

Accomplishment Instructions, paragraphs 

5.E.(1)(c) and 5.E.(1)(d), of the SB. 

(ii) Thereafter, at intervals not to exceed 

300 FCs since the last BSI, perform a 

repetitive BSI of the HPT rotor stage 1 blades 

and HPT stator stage 1 nozzle set in 

accordance with the Accomplishment 

Instructions, paragraphs 5.E.(1)(c) and 

5.E.(1)(d), of the SB. 

(3) BSI Results Disposition 

Based on the results of the BSI required by 

paragraph (g)(1) or (2) of this AD, as 

applicable, either re-inspect or replace the 

HPT rotor stage 1 blades or HPT stator stage 

1 nozzle set using the criteria, compliance 

times, and procedures referenced in the 

Accomplishment Instructions, paragraph 

5.E.(1)(f), of the SB. 

(4) Conditional Inspection of the Sister 

Engine on the Same Airplane 

(i) Based on the BSI results disposition 

required by paragraph (g)(3) of this AD, if reinspection or replacement of the HPT rotor 

stage 1 blades or HPT stator stage 1 nozzle 

set is required within 50 FCs based on the 

criteria, compliance times, and procedures 

referenced in the Accomplishment 

Instructions, paragraph 5.E.(1)(f), of the SB, 

then perform the actions required in 

paragraph (g)(4)(ii) of this AD. 

(ii) Within 5 FCs after performing the 

inspection required by paragraph (g)(1) or (2) 

of this AD, as applicable, either inspect or 

replace the HPT rotor stage 1 blades or HPT 

stator stage 1 nozzle set on the sister engine 

using the procedures and compliance times 

in the Accomplishment Instructions, 

paragraph, 5.E.(1)(g), of the SB. Where the SB 

specifies to remove the engine, this AD 

requires replacement of the HPT rotor stage 

1 blades or HPT stator stage 1 nozzle set, as 

applicable. 

(5) Reporting Requirements 

If, during any inspection required by 

paragraph (g)(1), (2), (3), or (4) of this AD, as 

applicable, any HPT unserviceable finding is 

found on an engine as identified in the 

Accomplishment Instructions, paragraph 

5.E.(1)(f) of the SB, within 30 days of 

performing the inspection, report the HPT 

unserviceable finding to CFM in accordance 

with the Accomplishment Instructions, 

paragraph 5.E.(1)(f)1, of the SB. 

Note 1 to paragraph (g): The 

Accomplishment Instructions in paragraph 

5.E.(1)(f) of the SB reference applicable 

aircraft maintenance manual tasks for 

procedures and compliance times for the 

actions required by paragraphs (g)(3) through 

(5) of this AD. 

(h) Definitions 

(1) Group 1 engines are CFM LEAP–1A29, 

LEAP–1A29CJ, LEAP–1A30, LEAP–1A32, 

LEAP–1A33, LEAP–1A33B2, and LEAP– 

1A35A model turbofan engines. 

(2) Group 2 engines are CFM LEAP–1A23, 

LEAP–1A24, LEAP–1A24E1, LEAP–1A26, 

LEAP–1A26CJ, and LEAP–1A26E1 model 

turbofan engines. 

(3) For the purpose of this AD, a ‘‘MENA 

takeoff’’ is any takeoff accomplished in the 

MENA region, as defined in the Planning 

Information, paragraph 3.D., of the SB. 

(4) For the purpose of this AD, ‘‘sister 

engine’’ refers to the other engine installed 

on the same airplane. 

(i) 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 (j)(1) of this AD and 

email 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. 

(j) Related Information 

(1) For more information about this AD, 

contact Mehdi Lamnyi, Aviation Safety 

Engineer, ECO Branch, FAA, 1200 District 

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

238–7743; email: Mehdi.Lamnyi@faa.gov. 

(2) For service information identified in 

this AD, contact CFM International, S.A., 

Aviation Operations Center, 1 Neumann 

Way, M/D Room 285, Cincinnati, OH 45125; 

phone: (877) 432–3272; email: 

aviation.fleetsupport@ge.com. You may view 

this referenced 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. 

Issued on March 10, 2022. 

Lance T. Gant, 

Director, Compliance & Airworthiness 

Division, Aircraft Certification Service. 

[FR Doc. 2022–05524 Filed 3–18–22; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2022–0283; Project 

Identifier MCAI–2021–01285–R] 

RIN 2120–AA64 

Airworthiness Directives; Leonardo 

S.p.a. Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: The FAA proposes to adopt a 

new airworthiness directive (AD) for 

certain Leonardo S.p.a. Model AB139 

and AW139 helicopters. This proposed 

AD was prompted by a large crack 

detected on the tail gearbox (TGB) 

fitting during a scheduled inspection 

and the determination that certain TGB 

fittings are required to be inspected by 

the use of a borescope. This proposed 

AD would require a one-time borescope 

inspection of certain part-numbered 

TGB fittings, and depending on the 

inspection results, removing the affected 

part from service and replacing with an 

airworthy part, as specified in a 

European Union Aviation Safety Agency 

(EASA) AD, which is proposed for 

incorporation by reference (IBR). The 

FAA is proposing this AD to address the 

unsafe condition on these products. 

DATES: The FAA must receive comments 

on this proposed AD by May 5, 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. 


khammond on DSKJM1Z7X2PROD with PROPOSALS