This section of the FEDERAL REGISTER

contains notices to the public of the proposed

issuance of rules and regulations. The

purpose of these notices is to give interested

persons an opportunity to participate in the

rule making prior to the adoption of the final

rules.

Proposed Rules Federal Register

17198 

Vol. 87, No. 59 

Monday, March 28, 2022 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2022–0380; Project 

Identifier MCAI–2021–01178–T] 

RIN 2120–AA64 

Airworthiness Directives; Airbus SAS 

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 Airbus SAS Model A330–200 

series airplanes, Model A330–200 

Freighter series airplanes, and Model 

A330–300 series airplanes. This 

proposed AD was prompted by a 

determination that certain service 

information specified in AD 2018–20– 

19 contained instructions that could be 

misleading, resulting in a necessary 

inspection not being accomplished on 

certain airplanes. This proposed AD 

would require a rototest for certain 

modified airplanes for any crack around 

the right-side upper and lower bulk 

door support or door latch fitting holes 

at certain bulk cargo door frames, or 

repetitive inspections for any crack at 

certain fittings, and on-condition 

actions, as specified in a European 

Union Aviation Safety Agency (EASA) 

AD, which is proposed for incorporation 

by reference. 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 12, 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 material that will be 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. 

Examining the AD Docket 

You may examine the AD docket at 

https://www.regulations.gov by 

searching for and locating Docket No. 

FAA–2022–0380; 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 mandatory continuing 

airworthiness information (MCAI), any 

comments received, and other 

information. The street address for 

Docket Operations is listed above. 

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 206–231–3229; email 

vladimir.ulyanov@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–2022–0380; Project Identifier 

MCAI–2021–01178–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 

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 Vladimir Ulyanov, 

Aerospace Engineer, Large Aircraft 

Section, FAA, International Validation 

Branch, 2200 South 216th St., Des 

Moines, WA 98198; telephone and fax 

206–231–3229; email vladimir.ulyanov@

faa.gov. Any commentary that the FAA 

receives which 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 2021–0233, 

dated October 27, 2021 (EASA AD 

2021–0233) (also referred to as the 

MCAI), to correct an unsafe condition 

for certain Airbus SAS Model A330–200 

series airplanes, Model A330–200 

Freighter series airplanes, and Model 

A330–300 series airplanes. 

This proposed AD was prompted by 

a determination that tartaric sulfuric 

anodizing (TSA)/chromic acid 

anodizing (CAA) surface treatment in 

the door fitting attachment holes leads 

to a detrimental effect on fatigue 

behavior; and that certain service 

information specified in AD 2018–20– 

19, Amendment 39–19453 (83 FR 

52126, October 16, 2018) (AD 2018–20– 

19) contains instructions that could be 

misleading, resulting in a necessary 

inspection not being accomplished on 

certain airplanes. The potentially 


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Federal Register / Vol. 87, No. 59 / Monday, March 28, 2022 / Proposed Rules 17199 

misleading instructions are for an 

optional action, and apply only to 

model A330–200, A330–200 Freighter, 

and A330–300 airplanes, therefore this 

AD does not propose to supersede AD 

2018–20–19. The FAA is proposing this 

AD to address possible fatigue cracks in 

the bulk cargo door frames, caused by 

TSA/CAA surface treatment in frame 

(FR) 67 and FR 69 bulk cargo door frame 

attachment holes. Cracks in the bulk 

cargo door frames can cause the in-flight 

loss of a bulk cargo door, damage to the 

airplane, and subsequent reduced 

control of the airplane. See the MCAI for 

additional background information. 

AD 2018–20–19 superseded AD 2017– 

16–07, Amendment 39–18984 (82 FR 

41874, September 5, 2017) (AD 2017– 

16–07), and applies to certain Airbus 

SAS Model A330–200 series airplanes, 

Model A330–200 Freighter series 

airplanes, Model A330–300 series 

airplanes, Model A340–200 series 

airplanes, and Model A340–300 series 

airplanes. AD 2018–20–19 was 

prompted by a determination that only 

airplanes having manufacturer serial 

numbers (MSNs) 0400 through 1779 

inclusive are affected by TSA/CAA 

surface treatment in the door fitting 

attachment holes, and that airplanes 

having MSNs 0001 through 0399 

inclusive were excluded from AD 2017– 

16–07. AD 2018–20–19 requires new 

inspections of certain attachment holes 

for residual surface treatment and 

cracking, and corrective action if 

necessary; and provides an optional 

terminating action for the inspections. 

Since AD 2018–20–09 was issued, it 

was determined that the service bulletin 

used for the optional modification on 

certain airplanes, Airbus Service 

Bulletin A330–53–3275, dated 

September 8, 2017, contained 

instructions that could be misleading. 

As a result, the special detailed 

inspection (rototest inspection) that was 

intended to be accomplished prior to 

accomplishing the optional 

modification may not have been 

accomplished on all airplanes. This 

proposed AD would therefore require a 

rototest for any crack around the holes 

at the holes of the upper and lower door 

support fittings of FR67 and FR69 on 

the right hand side and the holes at door 

latch fittings of FR69 on the right hand 

side, or repetitive detailed inspections 

for cracks of the frame around the 

fittings, or high frequency eddy current 

(HFEC) and ultrasonic inspections of the 

upper door supper fitting holes and 

rototests of the lower door fitting holes 

of the door latch fittings at FR69, and 

on-condition actions. 

These proposed actions would be 

required for Airbus SAS Model A330– 

200 series airplanes, Model A330–200 

Freighter series airplanes, and Model 

A330–300 series airplanes, MSN 1 

through 1779 inclusive, on which 

Airbus Service Bulletin A330–53–3275 

was embodied, except those airplanes 

on which during the embodiment of that 

service bulletin the rototest inspection 

was accomplished with no defect 

detected or any defects corrected, as 

applicable, as specified in Airbus 

Service Bulletin A330–53–3275. 

Related Service Information Under 1 

CFR Part 51 

EASA AD 2021–0233 specifies 

procedures for a rototest for any crack 

around the holes at the upper and lower 

door support fittings of frame (FR)67 

and FR69 right hand side and the holes 

at door latch fitting of FR69 right hand 

side; or repetitive detailed inspections 

of the frame around the fittings, or 

HFEC and ultrasonic inspections of the 

upper door supper fitting holes and 

rototests of the lower door fitting holes 

of the door latch fittings at FR69 for any 

crack; and on-condition actions. Oncondition actions include installing new 

(never installed on an airplane) bushes 

to the latch fittings of FR69 and repair, 

and a rototest of the support fittings and 

the frame holes at FR67. 

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. 

FAA’s Determination 

These products have been approved 

by the aviation authority of another 

country and are approved for operation 

in the United States. Pursuant to the 

FAA’s bilateral agreement with the State 

of Design Authority, it has notified the 

FAA of the unsafe condition described 

in the MCAI referenced above. The FAA 

is issuing this NPRM after determining 

that the unsafe condition described 

previously is likely to exist or develop 

in other products of these same type 

designs. 

Proposed AD Requirements in this 

NPRM 

This proposed AD would require 

accomplishing the actions specified in 

EASA AD 2021–0233 described 

previously, except for any differences 

identified as exceptions in the 

regulatory text of this proposed AD. 

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 2021–0233 by 

reference in the FAA final rule. This 

proposed AD would, therefore, require 

compliance with EASA AD 2021–0233 

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 2021–0233 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 2021–0233. 

Service information required by EASA 

AD 2021–0233 for compliance will be 

available at https://www.regulations.gov 

by searching for and locating Docket No. 

FAA–2022–0380 after the FAA final 

rule is published. 

Costs of Compliance 

The FAA estimates that this proposed 

AD would affect 109 airplanes of U.S. 

registry. The FAA estimates the 

following costs to comply with this 

proposed AD: 

ESTIMATED COSTS FOR REQUIRED ACTIONS

Labor cost Parts cost Cost per product Cost on U.S. 

operators 

Up to 15 work-hours × $85 per hour = $1,275 ........... $0 Up to $1,275 ............................................................... Up to $138,975. 


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17200 Federal Register / Vol. 87, No. 59 / Monday, March 28, 2022 / Proposed Rules 

The FAA estimates the following 

costs to do any necessary on-condition 

action that would be required based on 

the results of any required or optional 

actions. The FAA has no way of 

determining the number of aircraft that 

might need this on-condition action: 

ESTIMATED COSTS OF ON-CONDITION ACTIONS

Labor cost Parts cost Cost per 

product 

3 work-hours × $85 per hour = $255 ...................................................................................................................... $1,915 $2,340 

The FAA has received no definitive 

data on which to base the cost estimates 

for the repairs specified in this proposed 

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 

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: 

Airbus SAS: Docket No. FAA–2022–0380; 

Project Identifier MCAI–2021–01178–T. 

(a) Comments Due Date 

The FAA must receive comments on this 

airworthiness directive (AD) by May 12, 

2022. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to the Airbus SAS 

airplanes identified in paragraphs (c)(1) 

through (3) of this AD, certificated in any 

category, as identified in European Union 

Aviation Safety Agency (EASA) AD 2021– 

0233, dated October 27, 2021 (EASA AD 

2021–0233). 

(1) Model A330–201, –202, –203, –223, and 

–243 airplanes. 

(2) Model A330–223F and –243F airplanes. 

(3) Model A330–301, –302, –303, –321, 

–322, –323, –341, –342, and –343 airplanes. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 53, Fuselage. 

(e) Unsafe Condition 

This AD was prompted by a determination 

that tartaric sulfuric anodizing (TSA)/ 

chromic acid anodizing (CAA) surface 

treatment in the door fitting attachment holes 

leads to a detrimental effect on fatigue 

behavior; and that certain service information 

specified in AD 2018–20–19 contains 

instructions that could be misleading, 

resulting in a necessary inspection not being 

accomplished on certain airplanes. The FAA 

is issuing this AD to address possible fatigue 

cracks in the bulk cargo door frames, caused 

by TSA/CAA surface treatment in frame (FR) 

67 and FR 69 cargo door frame attachment 

holes. Cracks in the bulk cargo door frames 

can cause the in-flight loss of a bulk cargo 

door, damage to the airplane, and subsequent 

reduced control 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 2021–0233. 

(h) Exceptions to EASA AD 2021–0233 

(1) Where EASA AD 2021–0233 refers to its 

effective date, this AD requires using the 

effective date of this AD. 

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

2021–0233 does not apply to this AD. 

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

0233 specifies to ‘‘accomplish those 

instructions accordingly’’ if discrepancies are 

detected, for this AD a discrepancy is any 

crack, and if any cracking is detected, 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. 

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

0233 specifies to ‘‘contact Airbus for 

approved repair instructions,’’ for this AD 

use ‘‘accomplish corrective actions in 

accordance with the instructions of the SB 

and contact the Manager, Large Aircraft 

Section, International Validation Branch, 

FAA; or EASA; or Airbus SAS’s EASA DOA 

for approved repair instructions. If approved 

by the DOA, the approval must include the 

DOA-authorized signature’’ 

(5) Although the service information 

referenced in EASA AD 2021–0233 specifies 

to do a check of the aircraft records for 

accomplishment of certain service 

information, and specifies that action as 

‘‘RC,’’ (required for compliance), this AD 

does not include that requirement. 

(6) Where the Applicability section of 

EASA AD 2021–0233 refers to ‘‘defects,’’ for 

this AD ‘‘defects’’ are cracks. 

(i) No Reporting Requirement 

Although the service information 

referenced in EASA AD 2021–0233 specifies 

to submit certain information to the 

manufacturer, this AD does not include that 

requirement. 


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(j) 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 (k)(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 

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 paragraphs (h)(3) and (4), (i), 

and (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 

(1) For EASA AD 2021–0233, 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. 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. This 

material may be found in the AD docket at 

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

and locating Docket No. FAA–2022–0380. 

(2) 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 206–231–3229; email 

vladimir.ulyanov@faa.gov. 

Issued on March 22, 2022. 

Lance T. Gant, 

Director, Compliance & Airworthiness 

Division, Aircraft Certification Service. 

[FR Doc. 2022–06392 Filed 3–25–22; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2022–0294; Project 

Identifier MCAI–2021–00550–R] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Helicopters Deutschland GmbH (AHD) 

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 all 

Airbus Helicopters Deutschland GmbH 

(AHD) Model MBB–BK117 A–1, MBB– 

BK117 A–3, MBB–BK117 A–4, MBB– 

BK117 B–1, MBB–BK117 B–2, MBB– 

BK117 C–1, MBB–BK117 C–2, and 

MBB–BK117 D–2 helicopters. This 

proposed AD was prompted by the 

FAA’s determination that aging of the 

elastomeric material of certain tension 

torsion straps (TT-Straps), during the 

period since manufacturing date up to 

first flight on a helicopter, may affect its 

structural characteristics. This proposed 

AD would require the replacement of 

certain TT-Straps, implementation of 

storage life limits for TT-Straps, a 

prohibition on installing certain TTStraps and conditions for installation of 

certain other TT-Straps, 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 12, 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 EASA material that is proposed 

for IBR in this AD, contact EASA, 

Konrad-Adenauer-Ufer 3, 50668 

Cologne, Germany; phone: +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. The EASA material 

is also available at https://

www.regulations.gov by searching for 

and locating Docket No. FAA–2022– 

0294. 

Examining the AD Docket 

You may examine the AD docket at 

https://www.regulations.gov by 

searching for and locating Docket No. 

FAA–2022–0294; 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: 

Kristi Bradley, Program Manager, COS 

Program Management Section, 

Operational Safety Branch, Compliance 

& Airworthiness Division, FAA, 10101 

Hillwood Pkwy., Fort Worth, TX 76177; 

phone: (817) 222–5110; email: 

kristin.bradley@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–2022–0294; Project Identifier 

MCAI–2021–00550–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 


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