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
15900 Federal Register / Vol. 87, No. 54 / Monday, March 21, 2022 / Proposed Rules 

• 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 EASA material that is proposed 

for 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 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 is 

also available at https://

www.regulations.gov by searching for 

and locating Docket No. FAA–2022– 

0283. 

Examining the AD Docket 

You may examine the AD docket at 

https://www.regulations.gov by 

searching for and locating Docket No. 

FAA–2022–0283; 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, the EASA AD, any comments 

received, and other information. The 

street address for Docket Operations is 

listed above. 

FOR FURTHER INFORMATION 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. 

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–2022–0283; Project Identifier 

MCAI–2021–01285–R’’ 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 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. Any 

commentary that the FAA receives that 

is not specifically designated as CBI will 

be placed in the public docket for this 

rulemaking. 

Background 

EASA, which is the Technical Agent 

for the Member States of the European 

Union, has issued EASA AD 2021–0259, 

dated November 17, 2021 and corrected 

November 22, 2021 (EASA AD 2021– 

0259), to correct an unsafe condition for 

Leonardo S.p.A. Helicopters, formerly 

Finmeccanica S.p.A, AgustaWestland 

S.p.A., Agusta S.p.A.; and 

AgustaWestland Philadelphia 

Corporation, formerly Agusta Aerospace 

Corporation, Model AB139 and AW139 

helicopters, all serial numbers. 

EASA advises that during a scheduled 

inspection of a Model AW139 

helicopter, a large crack was detected on 

the inner forward-right side of TGB 

fitting part number 3G5351A01151. 

EASA further advises that investigation 

results determined previous inspections 

on the inner-right side of the TGB fitting 

were accomplished without the use of a 

borescope. The FAA is proposing this 

AD to detect cracks on the TGB fitting. 

The unsafe condition, if not addressed, 

could result in crack propagation up to 

a critical length, reduced load capability 

of the TGB and tail rotor, and 

subsequent reduced control of the 

helicopter. See EASA AD 2021–0259 for 

additional background information. 

Related Service Information Under 1 

CFR Part 51 

EASA AD 2021–0259 specifies 

procedures, within the applicable 

compliance times, for a one-time 

borescope inspection of certain TGB 

fittings for a crack or any discrepancy, 

and replacement of an affected part with 

a new part as specified in the 

manufacturer’s service information. 

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. 

Other Related Service Information 

The FAA also reviewed Leonardo 

Helicopters Alert Service Bulletin 

No.139–686, dated November 8, 2021 

(ASB 139–686). This service 

information specifies procedures for 

borescope inspecting the right-hand and 

forward parts of certain TGB fittings for 

any cracks or damage and replacing the 

TGB fitting with a new one, if any 

cracks or damage are detected. ASB 

139–686 also specifies procedures for 

reporting inspection results if a crack or 

discrepancy is detected. 

FAA’s Determination 

These helicopters have been approved 

by EASA and are approved for operation 

in the United States. Pursuant to the 

FAA’s bilateral agreement with the 

European Union, EASA has notified the 

FAA about the unsafe condition 

described in its AD. The FAA is 

proposing this AD after evaluating all 

known relevant information and 

determining that the unsafe condition 

described previously is likely to exist or 

develop on other helicopters of the same 

type designs. 

Proposed AD Requirements in This 

NPRM 

This proposed AD would require 

accomplishing the actions specified in 

EASA AD 2021–0259, described 

previously, as incorporated by 

reference, except for any differences 

identified as exceptions in the 

regulatory text of this proposed AD and 

except as discussed under ‘‘Differences 

Between this Proposed AD and EASA 

AD 2021–0259.’’ 


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Explanation of Required Compliance 

Information 

In the FAA’s ongoing efforts to 

improve the efficiency of the AD 

process, the FAA developed a process to 

use some civil aviation authority (CAA) 

ADs as the primary source of 

information for compliance with 

requirements for corresponding FAA 

ADs. The FAA has been coordinating 

this process with manufacturers and 

CAAs. As a result, the FAA proposes to 

incorporate EASA AD 2021–0259 by 

reference in the FAA final rule. This 

proposed AD would, therefore, require 

compliance with EASA AD 2021–0259 

in its entirety through that 

incorporation, except for any differences 

identified as exceptions in the 

regulatory text of this proposed AD. 

Using common terms that are the same 

as the heading of a particular section in 

EASA AD 2021–0259 does not mean 

that operators need comply only with 

that section. For example, where the AD 

requirement refers to ‘‘all required 

actions and compliance times,’’ 

compliance with this AD requirement is 

not limited to the section titled 

‘‘Required Action(s) and Compliance 

Time(s)’’ in EASA AD 2021–0259. 

Service information referenced in EASA 

AD 2021–0259 for compliance will be 

available at https://www.regulations.gov 

by searching for and locating Docket No. 

FAA–2022–0283 after the FAA final 

rule is published. 

Differences Between This Proposed AD 

and EASA AD 2021–0259 

EASA AD 2021–0259 applies to 

Model AB139 and AW139 helicopters, 

all serial numbers, whereas this 

proposed AD would only apply to 

Model AB139 and AW139 helicopters 

with certain part-numbered TGB fittings 

installed. This proposed AD would not 

require compliance with paragraph (3) 

of EASA AD 2021–0259. 

Service information referenced in 

EASA AD 2021–0259 specifies that if 

any crack or damage is found, replace 

the damaged TGB fitting with a new 

one, whereas this proposed AD would 

require before further flight, removing 

the affected TGB fitting from service and 

replacing with an airworthy part. 

Costs of Compliance 

The FAA estimates that this AD, if 

adopted as proposed, would affect 129 

helicopters of U.S. Registry. Labor rates 

are estimated at $85 per work-hour. 

Based on these numbers, the FAA 

estimates the following costs to comply 

with this proposed AD. 

Borescope inspecting the TGB fitting 

for a crack and any discrepancy (i.e., 

damage) would take about 4 work-hours 

for an estimated cost of $340 per 

helicopter and $43,860 for the U.S. fleet. 

Replacing the TGB fitting with an 

airworthy TGB fitting would take about 

36 work-hours and parts would cost 

about $6,650 for an estimated cost of 

$9,710 per replacement. 

The FAA has included all known 

costs in its cost estimate. According to 

the manufacturer, however, some of the 

costs of this proposed AD may be 

covered under warranty, thereby 

reducing the cost impact on affected 

operators. 

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: 

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

0283; Project Identifier MCAI–2021– 

01285–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 

AB139 and AW139 helicopters, certificated 

in any category, with an affected part as 

identified in European Union Aviation Safety 

Agency (EASA) AD 2021–0259, dated 

November 17, 2021, and corrected November 

22, 2021 (EASA AD 2021–0259). 

(d) Subject 

Joint Aircraft Service Component (JASC) 

Code: 5300, Fuselage Structure. 

(e) Unsafe Condition 

This 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. The FAA is issuing this AD to 

detect cracks on the TGB fitting. The unsafe 

condition, if not addressed, could result in 

crack propagation up to a critical length, 

reduced load capability of the TGB and tail 

rotor, and subsequent reduced control of the 

helicopter. 

(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 2021–0259. 

(h) Exceptions to EASA AD 2021–0259 

(1) Where EASA AD 2021–0259 requires 

compliance in terms of flight hours (FH), this 

AD requires using hours time-in-service. 

(2) Where EASA AD 2021–0259 refers to its 

effective date, this AD requires using the 

effective date of this AD. 

(3) Where paragraph (1) of EASA AD 2021– 

0259 specifies ‘‘inspect, using a borescope, 


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15902 Federal Register / Vol. 87, No. 54 / Monday, March 21, 2022 / Proposed Rules 

the affected part in accordance with the 

instructions of Section 3 Part I of the ASB,’’ 

for this AD replace ‘‘in accordance with the 

instructions of Section 3 Part I of the ASB’’ 

with ‘‘in accordance with the 

Accomplishment Instructions, Section 3 Part 

I, paragraphs 5. through 5.5 of the ASB.’’ 

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

0259 specifies ‘‘if, during the inspection as 

required by paragraph (1) this AD, a crack or 

any discrepancy is detected, replace the 

affected part in accordance with the 

instructions of Section 3 Part II of the ASB,’’ 

this AD requires before further flight, 

removing the TGB fitting from service and 

replacing with an airworthy part, if any crack 

or discrepancy is detected. For this AD, 

discrepancies include damage, which 

includes scratches and dents on the outer 

surfaces of the forward and right-hand sides 

of the TGB fitting above the horizontal row 

of fastener holes. The instructions specified 

in paragraph (2) of EASA AD 2021–0259 are 

for reference only and are not required for the 

replacement required by this paragraph. 

(5) Where paragraph (4) of EASA AD 2021– 

0259 allows (re)installing an affected part 

provided it is inspected as required by 

paragraph (1) of EASA AD 2021–0259, for 

this AD, the inspected part cannot be 

(re)installed if any crack or discrepancy is 

detected. 

(6) This AD does not mandate compliance 

with paragraph (3) of EASA AD 2021–0259. 

(7) This AD does not mandate compliance 

with the ‘‘Remarks’’ section of EASA AD 

2021–0259. 

(i) Special Flight Permit 

Special flight permits may be issued in 

accordance with 14 CFR 21.197 and 21.199, 

provided no passengers are onboard. 

(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 2021–0259, 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 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–2022–0283. 

(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. 2022–05588 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–2022–0103; Project 

Identifier AD–2021–00977–T] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Airplanes 

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 The Boeing Company Model 777 

airplanes. This proposed AD was 

prompted by reports of discrepancies 

between the center wing tank (CWT) 

fuel quantity, as indicated by the fuel 

quantity indicating system (FQIS), and 

the refueling truck uploaded fuel 

amount, followed by certain engineindicating and crew-alerting system 

(EICAS) messages. This proposed AD 

would require installing new software 

in the fuel quantity processor unit 

(FQPU), or replacing the FQPU with one 

that includes new software, depending 

on airplane configuration; and doing a 

software version check and FQPU 

operational check. This proposed AD 

would also prohibit the installation of 

certain FQPUs on certain airplanes. 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 

p.m., Monday through Friday, except 

Federal holidays. 

For service information identified in 

this NPRM, contact Boeing Commercial 

Airplanes, Attention: Contractual & Data 

Services (C&DS), 2600 Westminster 

Blvd., MC 110–SK57, Seal Beach, CA 

90740–5600; telephone 562–797–1717; 

internet https://

www.myboeingfleet.com. You may view 

this referenced service information at 

the FAA, Airworthiness Products 

Section, Operational Safety Branch, 

2200 South 216th St., Des Moines, WA. 

For information on the availability of 

this material at the FAA, call 206–231– 

3195. It is also available at https://

www.regulations.gov by searching for 

and locating Docket No. FAA–2022– 

0103. 

Examining the AD Docket 

You may examine the AD docket at 

https://www.regulations.gov by 

searching for and locating Docket No. 

FAA–2022–0103; 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: 

Kevin Nguyen, Aerospace Engineer, 

Propulsion Section, FAA, Seattle ACO 

Branch, 2200 South 216th St., Des 

Moines, WA 98198; phone and fax: 206– 

231–3555; email: kevin.nguyen@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–2022–0103; Project Identifier AD– 

2021–00977–T’’ 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 


khammond on DSKJM1Z7X2PROD with PROPOSALS