Federal Register / Vol. 86, No. 161 / Tuesday, August 24, 2021 / Proposed Rules 47255 

17940 (79 FR 48018, August 15, 2014); 

and AD 2018–19–28, Amendment 39– 

19429 (83 FR 48935, September 28, 

2018); and 

■ b. Adding the following new AD: 

Yabora ̃ Indu ́ stria Aerona ́utica S.A. (Type 

Certificate Previously Held by Embraer 

S.A.): Docket No. FAA–2021–0692; Project 

Identifier MCAI–2020–01585–T. 

(a) Comments Due Date 

The FAA must receive comments on this 

airworthiness directive (AD) by October 8, 

2021. 

(b) Affected ADs 

(1) This AD replaces AD 2014–16–16, 

Amendment 39–17940 (79 FR 48018, August 

15, 2014) (AD 2014–16–16). 

(2) This AD also replaces AD 2018–19–28, 

Amendment 39–19429 (83 FR 48935, 

September 28, 2018) (AD 2018–19–28). 

(c) Applicability 

This AD applies to all Yabora ̃ Indu ́ stria 

Aerona ́utica S.A. (type certificate previously 

held by Embraer S.A.) Model ERJ 190–100 

STD, –100 LR, –100 ECJ, –100 IGW, –200 

STD, –200 LR, and –200 IGW airplanes, 

certificated in any category. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 54, Nacelles/pylons. 

(e) Reason 

This AD was prompted by reports of 

bushing migration, loss of nut torque on the 

engine pylon lower inboard and outboard 

link fittings, a loose lower link assembly, and 

damaged nuts, and the need to shorten the 

compliance time for the modification of the 

pylon lower link fitting attaching parts. The 

FAA is issuing this AD to prevent loss of 

integrity of the lower link fittings of the 

engine pylon, which could lead to separation 

of the engine from the wing. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Requirements 

For airplanes identified in Ageˆncia 

Nacional de Aviac ̧a ̃o Civil (ANAC) AD 2020– 

06–02R02, effective November 30, 2020 

(ANAC AD 2020–06–02R02): Except as 

specified in paragraphs (h) and (i) of this AD, 

comply with all required actions and 

compliance times specified in, and in 

accordance with, ANAC AD 2020–06–02R02. 

(h) Exceptions to ANAC AD 2020–06–02R02 

(1) Where ANAC AD 2020–06–02R02 refers 

to its effective date, this AD requires using 

the effective date of this AD. 

(2) Where ANAC AD 2020–06–02R02 refers 

to July 3, 2014, this AD requires using 

September 2, 2014 (the effective date of AD 

2014–16–16). 

(3) Where ANAC AD 2020–06–02R02 refers 

to April 25, 2017, this AD requires using 

November 2, 2018 (the effective date of AD 

2018–19–28). 

(4) Paragraphs (y), ‘‘Alternative methods of 

compliance (AMOCs),’’ and (z), ‘‘Material 

incorporated by reference,’’ of ANAC AD 

2020–06–02R02 do not apply to this AD. 

(5) Where ANAC AD 2020–06–02R02 

specifies ‘‘replace immediately,’’ this AD 

requires replacing ‘‘before further flight.’’ 

(6) Paragraph (w), ‘‘Parts installation 

prohibition,’’ of ANAC AD 2020–06–02R02 

does not apply to this AD, except as specified 

in paragraph (i) of this AD. 

(i) Parts Installation Prohibition 

As of September 2, 2014 (the effective date 

of AD 2014–16–16), no person may install a 

lock assembly identified in Embraer Service 

Bulletin 190–54–0013, dated November 27, 

2012; or Embraer Service Bulletin 190LIN– 

54–0004, dated December 20, 2012; at the 

inboard or outboard lower link fitting on any 

airplane. 

(j) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, Large Aircraft 

Section, International Validation Branch, 

FAA, has the authority to approve AMOCs 

for this AD, if requested using the procedures 

found in 14 CFR 39.19. In accordance with 

14 CFR 39.19, send your request to your 

principal inspector or responsible Flight 

Standards Office, as appropriate. If sending 

information directly to the Large Aircraft 

Section, International Validation Branch, 

send it to the attention of the person 

identified in paragraph (k)(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 

ANAC; or ANAC’s authorized Designee. If 

approved by the ANAC Designee, the 

approval must include the Designee’s 

authorized signature. 

(3) Required for Compliance (RC): Except 

as specified by paragraph (h) of this AD: For 

service information that contains steps that 

are labeled as Required for Compliance (RC), 

the provisions of paragraphs (j)(3)(i) and (ii) 

of this AD apply. 

(i) The steps labeled as RC, including 

substeps under an RC step and any figures 

identified in an RC step, must be done to 

comply with the AD. If a step or substep is 

labeled ‘‘RC Exempt,’’ then the RC 

requirement is removed from that step or 

substep. An AMOC is required for any 

deviations to RC steps, including substeps 

and identified figures. 

(ii) Steps not labeled 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 RC steps, 

including substeps and identified figures, can 

still be done as specified, and the airplane 

can be put back in an airworthy condition. 

(k) Related Information 

(1) For ANAC AD 2020–06–02R02, contact 

National Civil Aviation Agency (ANAC), 

Aeronautical Products Certification Branch 

(GGCP), Rua Dr. Orlando Feirabend Filho, 

230—Centro Empresarial Aquarius—Torre 

B—Andares 14 a 18, Parque Residencial 

Aquarius, CEP 12.246–190—Sa ̃o Jose ́ dos 

Campos—SP, BRAZIL, Tel: 55 (12) 3203– 

6600; Email: pac@anac.gov.br. You may find 

this IBR material on the ANAC website at 

https://sistemas.anac.gov.br/certificacao/DA/ 

DAE.asp. For Embraer service information 

identified in this AD, contact Embraer S.A., 

Technical Publications Section (PC 060), Av. 

Brigadeiro Faria Lima, 2170—Putim—12227– 

901 Sa ̃o Jose dos Campos—SP—Brazil; 

telephone +55 12 3927–5852 or +55 12 3309– 

0732; fax +55 12 3927–7546; email distrib@

embraer.com.br; internet http:// 

www.flyembraer.com. For Embraer service 

information identified in this AD that is 

applicable to Yabora ̃ Indu ́ stria Aerona ́utica 

S.A. Model ERJ 190–100 ECJ airplanes, 

contact Embraer S.A., Technical Publications 

Section (PC 560), Rodovia Presidente Dutra, 

km 134, 12247–004 Distrito Eugeˆnio de 

Melo—Sa ̃o Jose ́ dos Campos—SP—Brazil; 

telephone +55 12 3927–0386; email distrib@

embraer.com.br; internet https:// 

www.mytechcare.embraer.com. 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 on 

the internet at https://www.regulations.gov 

by searching for and locating Docket No. 

FAA–2021–0692. 

(2) For more information about this AD, 

contact Krista Greer, Aerospace Engineer, 

Large Aircraft Section, International 

Validation Branch, FAA, 2200 South 216th 

St., Des Moines, WA 98198; telephone and 

fax 206–231–3221; email krista.greer@

faa.gov. 

Issued on August 18, 2021. 

Gaetano A. Sciortino, 

Deputy Director for Strategic Initiatives, 

Compliance & Airworthiness Division, 

Aircraft Certification Service. 

[FR Doc. 2021–18110 Filed 8–23–21; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2021–0609; Project 

Identifier AD–2021–00274–T] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 


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47256 Federal Register / Vol. 86, No. 161 / Tuesday, August 24, 2021 / Proposed Rules 

SUMMARY: The FAA proposes to adopt a 

new airworthiness directive (AD) for 

certain The Boeing Company Model 

737–300, –400, and –500 series 

airplanes. This proposed AD was 

prompted by an evaluation by the 

design approval holder (DAH) 

indicating that the frame splice between 

certain stringers is subject to 

widespread fatigue damage (WFD). This 

proposed AD would require an 

inspection of certain fuselage frame 

splices for existing repairs, repetitive 

inspections of certain fuselage frame 

splices for cracking, and applicable oncondition actions. 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 October 8, 2021. 

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 on the internet 

at https://www.regulations.gov by 

searching for and locating Docket No. 

FAA–2021–0609. 

Examining the AD Docket 

You may examine the AD docket at 

https://www.regulations.gov by 

searching for and locating Docket No. 

FAA–2021–0609; 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: 

Wayne Ha, Aerospace Engineer, 

Airframe Section, FAA, Los Angeles 

ACO Branch, 3960 Paramount 

Boulevard, Lakewood, CA 90712–4137; 

phone: 562–627–5238; fax: 562–627– 

5210; email: wayne.ha@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–2021–0609; Project Identifier AD– 

2021–00274–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 Wayne Ha, Aerospace 

Engineer, Airframe Section, FAA, Los 

Angeles ACO Branch, 3960 Paramount 

Boulevard, Lakewood, CA 90712–4137; 

phone: 562–627–5238; fax: 562–627– 

5210; email: wayne.ha@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 

Fatigue damage can occur locally, in 

small areas or structural design details, 

or globally, in widespread areas. 

Multiple-site damage is widespread 

damage that occurs in a large structural 

element such as a single rivet line of a 

lap splice joining two large skin panels. 

Widespread damage can also occur in 

multiple elements such as adjacent 

frames or stringers. Multiple-site 

damage and multiple-element damage 

cracks are typically too small initially to 

be reliably detected with normal 

inspection methods. Without 

intervention, these cracks will grow, 

and eventually compromise the 

structural integrity of the airplane. This 

condition is known as WFD. It is 

associated with general degradation of 

large areas of structure with similar 

structural details and stress levels. As 

an airplane ages, WFD will likely occur, 

and will certainly occur if the airplane 

is operated long enough without any 

intervention. 

An FAA final rule (‘‘Aging Airplane 

Program: Widespread Fatigue Damage;’’ 

75 FR 69746, November 15, 2010) 

became effective on January 14, 2011, 

and amended 14 CFR parts 25, 26, 121, 

and 129 (commonly known as the WFD 

rule). The WFD rule requires certain 

actions to prevent structural failure due 

to WFD throughout the operational life 

of certain existing transport category 

airplanes and all of these airplanes that 

will be certificated in the future. DAHs 

of existing and future airplanes subject 

to the WFD rule are required to establish 

a limit of validity (LOV) of the 

engineering data that support the 

structural maintenance program. 

Operators affected by the WFD rule may 

not fly an airplane beyond its LOV, 

unless an extended LOV is approved. 

The WFD rule does not require 

identifying and developing maintenance 

actions if the DAHs can show that such 

actions are not necessary to prevent 

WFD before the airplane reaches the 

LOV. Many LOVs, however, do depend 

on accomplishment of future 

maintenance actions. As stated in the 

WFD rule, any maintenance actions 

necessary to reach the LOV will be 

mandated by airworthiness directives 

through separate rulemaking actions. 

In the context of WFD, this action is 

necessary to enable DAHs to propose 

LOVs that allow operators the longest 

operational lives for their airplanes, and 

still ensure that WFD will not occur. 

This approach allows for an 

implementation strategy that provides 

flexibility to DAHs in determining the 

timing of service information 

development (with FAA approval), 


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Federal Register / Vol. 86, No. 161 / Tuesday, August 24, 2021 / Proposed Rules 47257 

while providing operators with certainty 

regarding the LOV applicable to their 

airplanes. 

The FAA has received a report 

indicating that cracking is occurring in 

the frame splice doubler and may occur 

in the upper frame at the upper frame 

splice between stringer S–13 and S–14 

on Boeing Model 737–300, –400, and 

–500 airplanes at multiple frame 

locations. The doubler cracking and 

possible upper frame cracking at the 

frame splice between stringer S–13 and 

S–14 are the result of fatigue, caused by 

combined cyclic loading from fuselage 

pressurization and flight loads. The 

FAA is issuing this AD to address upper 

frame cracking common to the frame 

splice between stringer S–13 and S–14, 

which could interact with stringer S–14 

skin lap splice lower fastener row 

cracking in lower skin, and result in an 

uncontrolled decompression of the 

airplane and loss of structural integrity. 

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 Boeing Alert 

Requirements Bulletin 737–53A1388 

RB, dated October 27, 2020. This service 

information specifies procedures for a 

general visual inspection (GVI) of the 

fuselage frame splices between stringer 

S–13 and S–14 station (STA) 360 to STA 

520 and STA 727A to STA 907 for 

existing repairs, repetitive inspections 

of the fuselage frame splices between 

stringer S–13 and S–14 from STA 360 to 

STA 520 and STA 727A to STA 907 for 

cracking, and applicable on-condition 

actions. On-condition actions include 

an open hole high frequency eddy 

current (HFEC) inspection for cracking 

at all fastener hole locations where a 

fastener was removed due to finding a 

cracked doubler, repair, or replacement. 

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 

accomplishing the actions specified in 

the service information already 

described except for any differences 

identified as exceptions in the 

regulatory text of this proposed AD. For 

information on the procedures and 

compliance times, see this service 

information at https://

www.regulations.gov by searching for 

and locating Docket No. FAA–2021– 

0609. 

Costs of Compliance 

The FAA estimates that this AD, if 

adopted as proposed, would affect 66 

airplanes of U.S. registry. The FAA 

estimates the following costs to comply 

with this proposed AD: 

ESTIMATED COSTS

Action Labor cost Parts cost Cost per 

product 

Cost on U.S. 

operators 

Repetitive Inspections ... Up to 267 work-hours × $85 per hour = Up to 

$22,695 inspection cycle.

$0 Up to $22,695 per inspection cycle.Up to $1,497,870 per 

inspection cycle. 

GVI ................................ 2 work-hours × $85 per hour = $170 ................. 0 $170 ............................. $11,220. 

The FAA has received no definitive 

data on which to base the cost estimates 

for the on-condition actions 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: 

The Boeing Company: Docket No. FAA– 

2021–0609; Project Identifier AD–2021– 

00274–T. 

(a) Comments Due Date 

The FAA must receive comments on this 

airworthiness directive (AD) by October 8, 

2021. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to The Boeing Company 

Model 737–300, –400, and –500 series 


lotter on DSK11XQN23PROD with PROPOSALS1
47258 Federal Register / Vol. 86, No. 161 / Tuesday, August 24, 2021 / Proposed Rules 

airplanes, certificated in any category, as 

identified in Boeing Alert Requirements 

Bulletin 737–53A1388 RB, dated October 27, 

2020. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 53, Fuselage. 

(e) Unsafe Condition 

This AD was prompted by an evaluation by 

the design approval holder (DAH) indicating 

that the frame splice between stringer S–13 

and S–14 is subject to widespread fatigue 

damage (WFD). The FAA is issuing this AD 

to address upper frame cracking common to 

the frame splice between stringer S–13 and 

S–14, which could interact with stringer S– 

14 skin lap splice lower fastener row 

cracking in lower skin and result in an 

uncontrolled decompression of the airplane 

and loss of structural integrity. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Required Actions 

Except as specified by paragraph (h) of this 

AD: At the applicable times specified in the 

‘‘Compliance’’ paragraph of Boeing Alert 

Requirements Bulletin 737–53A1388 RB, 

dated October 27, 2020, do all applicable 

actions identified in, and in accordance with, 

the Accomplishment Instructions of Boeing 

Alert Requirements Bulletin 737–53A1388 

RB, dated October 27, 2020. 

Note 1 to paragraph (g): Guidance for 

accomplishing the actions required by this 

AD can be found in Boeing Alert Service 

Bulletin 737–53A1388, dated October 27, 

2020, which is referred to in Boeing Alert 

Requirements Bulletin 737–53A1388 RB, 

dated October 27, 2020. 

(h) Exceptions to Service Information 

Specifications 

(1) Where Boeing Alert Requirements 

Bulletin 737–53A1388 RB, dated October 27, 

2020, uses the phrase ‘‘the Original Issue date 

of Requirements Bulletin 737–53A1388 RB,’’ 

this AD requires using ‘‘the effective date of 

this AD,’’ except where Alert Requirements 

Bulletin 737–53A1388 RB, dated October 27, 

2020, uses the phrase ‘‘the Original Issue date 

of Requirements Bulletin 737–53A1388 RB,’’ 

in a note or flag note. 

(2) Where Boeing Alert Requirements 

Bulletin 737–53A1388 RB, dated October 27, 

2020, specifies contacting Boeing for repair 

instructions or for alternative inspections: 

This AD requires doing the repair, or doing 

the alternative inspections and applicable oncondition actions using a method approved 

in accordance with the procedures specified 

in paragraph (i) of this AD. 

(i) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Los Angeles ACO 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 manager of the 

certification office, send it to the attention of 

the person identified in Related Information. 

Information may be emailed to: 9-ANMLAACO-AMOC-Requests@faa.gov. 

(2) Before using any approved AMOC, 

notify your appropriate principal inspector, 

or lacking a principal inspector, the manager 

of the responsible Flight Standards Office. 

(3) An AMOC that provides an acceptable 

level of safety may be used for any repair, 

modification, or alteration required by this 

AD if it is approved by The Boeing Company 

Organization Designation Authorization 

(ODA) that has been authorized by the 

Manager, Los Angeles ACO Branch, FAA, to 

make those findings. To be approved, the 

repair method, modification deviation, or 

alteration deviation must meet the 

certification basis of the airplane, and the 

approval must specifically refer to this AD. 

(j) Related Information 

(1) For more information about this AD, 

contact Wayne Ha, Aerospace Engineer, 

Airframe Section, FAA, Los Angeles ACO 

Branch, 3960 Paramount Boulevard, 

Lakewood, CA 90712–4137; phone: 562–627– 

5238; fax: 562–627–5210; email: wayne.ha@

faa.gov. 

(2) For service information identified in 

this AD, 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. 

Issued on July 26, 2021. 

Lance T. Gant, 

Director, Compliance & Airworthiness 

Division, Aircraft Certification Service. 

[FR Doc. 2021–18069 Filed 8–23–21; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2021–0694; Project 

Identifier MCAI–2021–00305–T] 

RIN 2120–AA64 

Airworthiness Directives; De Havilland 

Aircraft of Canada Limited (Type 

Certificate Previously Held by 

Bombardier, Inc.) 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 De 

Havilland Aircraft of Canada Limited 

Model DHC–8–401 and –402 airplanes. 

This proposed AD was prompted by 

reports of a possible hard contact 

between the #2 top high level sensor 

(HLS) terminal screw head and the #6 

outer wing fuel access panel stiffener 

flange. This proposed AD would require 

removing and replacing or reworking 

the #6 outer wing fuel access panel 

assembly. 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 October 8, 2021. 

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 De Havilland 

Aircraft of Canada Limited, Q-Series 

Technical Help Desk, 123 Garratt 

Boulevard, Toronto, Ontario M3K 1Y5, 

Canada; telephone 416–375–4000; fax 

416–375–4539; email thd@

dehavilland.com; internet https://

dehavilland.com. You may view this 

service information at the FAA, 

Airworthiness Products Section, 

Operational Safety Branch, 2200 South 

216th St., Des Moines, WA. For 

information on the availability of this 

material at the FAA, call 206–231–3195. 

Examining the AD Docket 

You may examine the AD docket at 

https://www.regulations.gov by 

searching for and locating Docket No. 

FAA–2021–0694; 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: 

Thomas Niczky, Aerospace Engineer, 

Avionics and Electrical Systems 

Section, FAA, New York ACO Branch, 

1600 Stewart Avenue, Suite 410, 

Westbury, NY 11590; telephone 516– 

228–7347; fax 516–794–5531; email 9- 

avs-nyaco-cos@faa.gov. 

SUPPLEMENTARY INFORMATION: 


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