Federal Register / Vol. 87, No. 17 / Wednesday, January 26, 2022 / Proposed Rules 3943 

(8) A participant may not withdraw 

funds directly from his or her mutual 

fund window account. To make a 

withdrawal, the participant must elect a 

fund transfer back to the TSP core funds 

as described in paragraph (b) of this 

section. Upon completion of such fund 

transfer, the participant may make a 

withdrawal in accordance with 5 CFR 

part 1650. 

(b) Fund transfers back to TSP core 

funds. A participant may elect to make 

a fund transfer to the TSP core funds 

from amounts invested in his or her 

mutual fund window account, subject to 

the following rules: 

(1) Fund transfers must be made in 

whole dollar increments (percentages 

are not permitted); 

(2) Amounts to be transferred from a 

participant’s mutual fund window 

account to the TSP core funds must first 

be transferred to the sweep money 

market fund. Subsequently, the 

participant may direct the investment of 

the transferred amounts into the TSP 

core funds; 

(3) Each fund transfer back to the TSP 

core funds from the mutual fund 

window account counts toward the 

monthly limit set forth in § 1601.32(b); 

except, however, that a participant may 

always elect a fund transfer from the 

mutual fund window account to the G 

Fund; and 

(4) Fund transfers are subject to the 

fees set forth in § 1601.53. 

(c) Forced transfers. The TSP record 

keeper will force a transfer from the 

participant’s mutual fund window 

account to the TSP core funds in the 

following situations, and subject to the 

following rules: 

(1) A forced transfer may occur if the 

balance invested in the TSP core funds 

is insufficient to cover: 

(i) Amounts necessary to comply with 

a court order, legal process, or levy 

described in 5 CFR part 1653; 

(ii) A beneficiary asset transfer; 

(iii) A required minimum 

distribution; 

(iv) A distribution of an account 

balance less than $200 described in 5 

CFR 1650.23; or 

(v) Any other payment or transfer that 

the Board is required by law to make 

from the participant’s TSP account 

balance; 

(2) The amount of the forced transfer 

shall be equal to the amount of the 

insufficiency described in paragraph 

(c)(1) of this section, plus $1,000; 

except, however, that if the participant’s 

mutual fund window account balance is 

less than $25,000, the entire mutual 

fund window account balance shall be 

transferred to the TSP core funds; 

(3) Forced transfers shall be 

liquidated from the participant’s mutual 

fund window account first from 

amounts held in the sweep money 

market fund; and then from amounts 

invested in mutual funds, beginning 

with the position with the highest 

balance; 

(4) Forced transfers from a 

participant’s mutual fund window 

account to the TSP core funds shall be 

invested according to the participant’s 

existing contribution allocation; and 

(5) The participant shall be 

responsible for any fees incurred as a 

result of the forced transfer. 

§ 1601.53 Fees. 

(a) The Board will allocate a portion 

of the TSP’s administrative expenses to 

mutual fund users by charging an 

annual fee of $55.00. The amount of this 

fee will be redetermined once every 

three years by multiplying the average 

mutual fund window account balance 

by the TSP administrative expense ratio, 

as of the date of redetermination. 

(b) The fee described in paragraph (a) 

of this section is in addition to any 

mutual fund window account 

maintenance fees, trading fees, and fees 

and expenses associated with the 

specific mutual fund(s) in which the 

participant chooses to invest. 

[FR Doc. 2022–01312 Filed 1–25–22; 8:45 am] 

BILLING CODE 6760–01–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2022–0015; Project 

Identifier AD–2021–00832–R] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: The FAA proposes to 

supersede Airworthiness Directive (AD) 

2020–23–05, which applies to certain 

Airbus Helicopters Model EC225LP 

helicopters. AD 2020–23–05 requires 

inspecting the control rod attachment 

yokes (yokes) of certain main rotor (M/ 

R) rotating swashplates (swashplates), 

establishing a life limit, a one-time 

inspection of stripped yokes, and 

applicable corrective actions. Since the 

FAA issued AD 2020–23–05, the FAA 

has determined that a revised 

compliance time is necessary for 

swashplates that have accumulated less 

than seven years since the date of 

manufacture and that clarification is 

necessary for the condition that 

concludes with a dye penetrant 

inspection of the yoke. This proposed 

AD would continue to require the 

actions in AD 2020–23–05, with a 

revised compliance time for a certain 

inspection. 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 March 14, 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 Airbus Helicopters, 

2701 North Forum Drive, Grand Prairie, 

TX 75052; phone: (972) 641–0000 or 

(800) 232–0323; fax (972) 641–3775; or 

at https://www.airbus.com/helicopters/ 

technical-services/support.html. You 

may view this service information 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. 

Examining the AD Docket 

You may examine the AD docket at 

https://www.regulations.gov by 

searching for and locating Docket No. 

FAA–2022–0015; 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 European Union Aviation 

Safety Agency (EASA) AD, any 

comments received, and other 

information. The street address for 

Docket Operations is listed above. 

FOR FURTHER INFORMATION CONTACT: Hal 

Jensen, Aerospace Engineer, Operational 

Safety Branch, Compliance & 

Airworthiness Division, FAA, 950 

L’Enfant Plaza N SW, Washington, DC 

20024; phone: (202) 267–9167; email: 

hal.jensen@faa.gov. 

SUPPLEMENTARY INFORMATION: 


khammond on DSKJM1Z7X2PROD with PROPOSALS
3944 Federal Register / Vol. 87, No. 17 / Wednesday, January 26, 2022 / Proposed Rules 

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–2022–0015; Project Identifier AD– 

2021–00832–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 Hal Jensen, Aerospace 

Engineer, Operational Safety Branch, 

Compliance & Airworthiness Division, 

FAA, 950 L’Enfant Plaza N SW, 

Washington, DC 20024; phone: (202) 

267–9167; email: hal.jensen@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 

The FAA issued AD 2020–23–05, 

Amendment 39–21321 (85 FR 73604, 

November 19, 2020), (AD 2020–23–05), 

for certain Airbus Helicopters Model 

EC225LP helicopters. AD 2020–23–05 

requires inspecting the yokes of certain 

swashplates, establishing a life limit, a 

one-time inspection of stripped yokes, 

and applicable corrective actions. AD 

2020–23–05 was prompted by a crack in 

a swashplate yoke, which could result 

in failure of the yoke, loss of M/R 

control, and subsequent loss of control 

of the helicopter. 

EASA AD 2019–0074, dated March 

28, 2019 (EASA AD 2019–0074), was 

issued by EASA, which is the Technical 

Agent for the Member States of the 

European Union, to supersede EASA 

AD 2017–0191R2, dated December 15, 

2017 (EASA AD 2017–0191R2). EASA 

AD 2019–0074 followed Airbus 

Helicopters revising Emergency Alert 

Service Bulletin (EASB) No. 05A051, 

Revision 1, dated November 16, 2017, to 

Revision 2, dated February 26, 2019, to 

establish a life limit (also called a 

service life limit) of 12 years for the 

swashplate and add a reporting 

requirement if there is a crack or 

corrosion in a yoke. EASA advises that 

additional analysis determined that it is 

necessary to introduce the new life limit 

for the affected swashplates. 

Accordingly, EASA AD 2019–0074 

retains the requirements of EASA AD 

2017–0191R2 and adds a life limit and 

a reporting requirement. 

Actions Since AD 2020–23–05 Was 

Issued 

Since the FAA issued AD 2020–23– 

05, the FAA has determined that a 

revised compliance time is necessary for 

swashplates that have accumulated less 

than seven years since the date of 

manufacture. This revised compliance 

time matches the compliance time 

specified in EASA AD 2019–0074. The 

FAA has also determined that 

paragraphs (g)(3)(i) and (g)(4)(iii)(A) of 

this AD need clarification regarding 

when it is necessary to do a dye 

penetrant inspection of the yoke. 

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 design. 

Related Service Information Under 1 

CFR Part 51 

The FAA reviewed one document that 

co-publishes two Airbus Helicopters 

EASB identification numbers: EASB No. 

05A051 for Model EC225LP helicopters 

and EASB No. 05A046 for non-FAA 

type-certificated Model EC725AP 

helicopters, each Revision 2 and dated 

February 26, 2019. This service 

information specifies inspections for 

swashplate part number (P/N) 332A31– 

3074–00 and P/N 332A31–3074–01. 

This service information specifies 

procedures for a repetitive inspection of 

the yokes for a crack and a one-time 

inspection of the stripped yokes for 

corrosion and a crack. If in doubt about 

whether there is a crack, this service 

information specifies performing a 

nondestructive inspection. This service 

information also specifies touching up 

the swashplate with varnish if there is 

corrosion, removing any damage within 

allowable limits, and refinishing the 

yokes. If there is a crack in a yoke, this 

service information specifies replacing 

the swashplate. This service information 

also specifies a life limit of 12 years 

since the date of manufacture for the 

swashplates and reporting requirements 

if a crack or corrosion is discovered. The 

Director of the Federal Register 

approved EASB No. 05A051, Revision 2, 

dated February 26, 2019, for 

incorporation by reference as of 

December 24, 2020 (85 FR 73604, 

November 19, 2020). EASB No. 05A046, 

Revision 2, dated February 26, 2019, is 

not incorporated by reference in this 

AD. 

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 the ADDRESSES section. 

Proposed AD Requirements in This 

NPRM 

This proposed AD would retain all of 

the requirements of AD 2020–23–05. 

This proposed AD would require 

inspecting the yokes of certain 

swashplates, compliance with the 

established life limit, and a one-time 

inspection of stripped yokes. This 

proposed AD would also include a 

revised compliance time for the initial 

visual inspection of the yokes on 

swashplates that have accumulated less 

than seven years since the date of 

manufacture; and clarification that dye 

penetrant inspection of the yoke is 

required before further flight if no 

cracks are detected visually during the 

visual inspection. This proposed AD 

would require accomplishing the 

actions specified in the service 

information described previously, 

except as discussed under ‘‘Differences 

Between this Proposed AD and the 

EASA AD or Service Information.’’ 


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Federal Register / Vol. 87, No. 17 / Wednesday, January 26, 2022 / Proposed Rules 3945 

Differences Between This Proposed AD 

and the EASA AD or Service 

Information 

EASB No. 05A051, Revision 2, dated 

February 26, 2019 requires performing a 

non-destructive inspection only if there 

is doubt whether there is a crack. 

Instead, this proposed AD would 

require a visual inspection and if no 

cracks are visually detected, would 

require a non-destructive inspection. 

The EASA AD specifies instructions 

for reporting inspection results; this 

proposed AD would not. 

Costs of Compliance 

The FAA estimates that this AD, if 

adopted as proposed, would affect 28 

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. The new 

requirements of this proposed AD add 

no additional economic burden. 

ESTIMATED COSTS FOR REQUIRED ACTIONS

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

operators 

Determination of the manufacture date of 

the swashplate.

0.5 work-hour × $85 per hour = $43 ....... $0 $43 ......................... $1,204. 

Inspecting the yokes ................................. 0.25 work-hour × $85 per hour = $21 per 

inspection cycle.

0 $21 per inspection 

cycle.

$588 per inspection 

cycle. 

Removing grease, stripping the yokes, 

and inspecting the stripped yokes.

8 work-hours × $85 per hour = $680 ...... 0 $680 ....................... $19,040. 

Creating a life limit record ........................ 1 work-hour × $85 per hour = $85 .......... 0 $85 ......................... $2,380. 

The FAA estimates the following 

costs to do any necessary on-condition 

actions that would be required based on 

the results of any required actions. The 

FAA has no way of determining the 

number of aircraft that might need these 

on-condition actions: 

ESTIMATED COSTS OF ON-CONDITION ACTIONS

Action Labor cost Parts cost Cost per 

product 

Removing any corrosion or repairing damage within 

the allowable limit.

3 work-hours × $85 per hour = $255 ........................... $0 $255 

Replacing the swashplate ............................................ 6 work-hours × $85 per hour = $510 ........................... 85,661 86,171 

Dye-penetrant inspection .............................................. 6 work-hours × $85 per hour = $510 ........................... 50 560 

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, 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: 

■ a. Removing Airworthiness Directive 

2020–23–05, Amendment 39–21321 (85 

FR 73604, November 19, 2020); and 

■ b. Adding the following new 

airworthiness directive: 

Airbus Helicopters: Docket No. FAA– 

2022–0015; Project Identifier AD–2021– 

00832–R. 

(a) Comments Due Date 

The FAA must receive comments on this 

airworthiness directive (AD) action by March 

14, 2022. 

(b) Affected ADs 

This AD replaces AD 2020–23–05, 

Amendment 39–21321 (85 FR 73604, 

November 19, 2020) (AD 2020–23–05). 

(c) Applicability 

This AD applies to Airbus Helicopters 

Model EC225LP helicopters, certificated in 

any category, with a main rotor (M/R) 

rotating swashplate (swashplate) part number 


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3946 Federal Register / Vol. 87, No. 17 / Wednesday, January 26, 2022 / Proposed Rules 

(P/N) 332A31–3074–00 or P/N 332A31– 

3074–01 installed. 

(d) Subject 

Joint Aircraft Service Component (JASC) 

Code: 6230, Main Rotor Mast/Swashplate. 

(e) Unsafe Condition 

This AD was prompted by a crack in a 

swashplate control rod attachment yoke 

(yoke). The FAA is issuing this AD to detect 

and correct a crack in a yoke. The unsafe 

condition, if not addressed, could result in 

failure of the yoke, loss of M/R control, and 

subsequent loss of control of the helicopter. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Required Actions 

Before further flight, review Appendix 4.A. 

of Airbus Helicopters Emergency Alert 

Service Bulletin No. 05A051, Revision 2, 

dated February 26, 2019 (EASB 05A051) to 

determine the date of manufacture of the 

swashplate. 

(1) If the swashplate has accumulated 12 or 

more years since the date of manufacture, 

remove from service the swashplate. 

(2) If the swashplate has accumulated less 

than 12 years since the date of manufacture, 

create a component history card or 

equivalent record indicating a life limit of 12 

years since the date of manufacture. 

Thereafter, continue to record the life limit 

of the swashplate on its component history 

card or equivalent record and remove from 

service any swashplate before accumulating 

12 years since the date of manufacture. 

(3) For each swashplate that has 

accumulated less than 7 years since the date 

of manufacture, within 15 hours time-inservice (TIS) or 7 days, whichever occurs first 

after the effective date of this AD, and 

thereafter at intervals not to exceed 15 hours 

TIS or 7 days, whichever occurs first, until 

the swashplate accumulates 7 years since the 

date of manufacture, visually inspect each 

yoke for a crack, paying particular attention 

to the areas shown in Details B, C, and D of 

Figure 1 of EASB 05A05. 

(i) If no cracks are visually detected, before 

further flight, perform a dye penetrant 

inspection of the yoke for a crack. 

(ii) If there is a crack on a yoke, before 

further flight, remove from service the 

swashplate. 

(4) For each swashplate that has 

accumulated 7 or more years, but less than 

12 years, since the date of manufacture, 

within 100 hours TIS: 

(i) Remove the grease from areas (E), (F), 

(G), (H), (J), and (K) of each yoke as shown 

in Details B, C, and D of Figure 1 of EASB 

05A051. Using a plastic spatula, strip areas 

(E), (F), (G), (H), (J), and (K) of each yoke as 

shown in Details B, C, and D of Figure 1 of 

EASB 05A051. Do not use a metal tool to 

strip any area of a yoke. 

(ii) Inspect areas (E), (F), (G), (H), (J) and 

(K) of each yoke as shown in Details B, C, 

and D of Figure 1 of EASB 05A051 for 

corrosion, pitting, and loss of material. 

(A) If there is any corrosion less than 

0.0078 in. (0.2 mm), before further flight, 

remove the corrosion and apply varnish 

(Vernelec 43022 or equivalent) to the surface 

of areas (E), (F), (G), (H), (J) and (K). 

(B) If there is any pitting or loss of material 

of less than 0.0078 in. (0.2 mm), before 

further flight, remove the damage by sanding 

with sandpaper 200/400 or 330. 

(C) If there is any corrosion, pitting, or loss 

of material of 0.0078 in. (0.2 mm) or greater, 

before further flight, remove from service the 

swashplate. 

(iii) Visually inspect each yoke for a crack, 

paying particular attention to the areas 

shown in Details B, C, and D of Figure 1 of 

EASB 05A051. 

(A) If there are no cracks, before further 

flight, perform a dye penetrant inspection of 

the yoke for a crack. 

(B) If there is a crack on a yoke, before 

further flight, remove from service the 

swashplate. 

(h) Credit for Previous Actions 

If you performed the actions in paragraph 

(g)(4) of this AD before the effective date of 

this AD using Airbus Helicopters Emergency 

Alert Service Bulletin No. 05A051, Revision 

1, dated November 16, 2017, you have met 

the requirements of paragraph (g)(4) of this 

AD. 

(i) 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 (j)(1) 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. 

(j) Related Information 

(1) For more information about this AD, 

contact Hal Jensen, Aerospace Engineer, 

Operational Safety Branch, Compliance & 

Airworthiness Division, FAA, 950 L’Enfant 

Plaza N SW, Washington, DC 20024; phone: 

(202) 267–9167; email: hal.jensen@faa.gov. 

(2) For service information identified in 

this AD, contact Airbus Helicopters, 2701 

North Forum Drive, Grand Prairie, TX 75052; 

phone: (972) 641–0000 or (800) 232–0323; fax 

(972) 641–3775; or at https://

www.airbus.com/helicopters/services/ 

technical-support.html. You may view this 

referenced service information 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. 

(3) The subject of this AD is addressed in 

European Union Aviation Safety Agency 

(EASA) AD 2019–0074, dated March 28, 2019 

(EASA AD 2019–0074). You may view the 

EASA AD on the internet at https://

www.regulations.gov in Docket No. FAA– 

2022–0015. 

Issued on January 20, 2022. 

Lance T. Gant, 

Director, Compliance & Airworthiness 

Division, Aircraft Certification Service. 

[FR Doc. 2022–01440 Filed 1–25–22; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2021–1169; Project 

Identifier AD–2021–01011–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 

737–800 series airplanes. This proposed 

AD was prompted by the determination 

that insufficient sealing may allow 

water to enter the lower lobe electronic 

equipment (EE) bay through the main 

deck floor structure at the rigid cargo 

barrier (RCB), which could cause 

damage to EE bay line replacement units 

(LRUs) in the E5 rack. This proposed 

AD would require detailed inspections 

for the presence and condition of 

sealant at certain locations and 

applicable on-condition actions. This 

proposed AD would also require 

replacing the moisture barrier tape at a 

certain location, replacing the weather 

seal at a certain location, and installing 

seat track fillers. 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 March 14, 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