Federal Register / Vol. 86, No. 12 / Thursday, January 21, 2021 / Proposed Rules 6273 

(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: 

Rolls-Royce Deutschland Ltd & Co KG (Type 

Certificate previously held by RollsRoyce Deutschland GmbH, formerly 

BMW Rolls-Royce GmbH): Docket No. 

FAA–2020–1174; Project Identifier 

MCAI–2019–00135–E. 

(a) Comments Due Date 

The FAA must receive comments on this 

airworthiness directive (AD) by March 8, 

2021. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Rolls-Royce 

Deutschland Ltd & Co KG (RRD) (Type 

Certificate previously held by Rolls-Royce 

Deutschland GmbH, formerly BMW RollsRoyce GmbH) BR700–710A1–10, BR700– 

710A2–20 and BR700–710C4–11 model 

turbofan engines with a high-pressure turbine 

(HPT) stage 1 disk having a part number and 

serial number listed in Planning Information, 

paragraph 1.A., of RRD Alert NonModification Service Bulletin (NMSB) SB– 

BR700–72–A900659, Revision 1, dated 

November 5, 2019, installed. 

(d) Subject 

Joint Aircraft System Component (JASC) 

Code 7230, Turbine Engine Compressor 

Section. 

(e) Unsafe Condition 

This AD was prompted by an investigation 

by RRD, which revealed a quality escape 

during the HPT stage 1 disk rim cooling air 

hole manufacturing process. The FAA is 

issuing this AD to prevent failure of the HPT 

stage 1 disk. The unsafe condition, if not 

addressed, could result in the release of highenergy debris, damage to the airplane, and 

reduced control of the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Required Actions 

Before the affected HPT stage 1 disk 

exceeds 2,840 flight cycles (FCs) since new, 

or within 60 days after the effective date of 

this AD, whichever occurs later, but not to 

exceed 8 years after the effective date of this 

AD if using FCs, remove the affected HPT 

stage 1 disk from service and replace with a 

part eligible for installation. Guidance on 

replacing the HPT stage 1 disk can be found 

in the Accomplishment Instructions, 

paragraph 3.B., of RRD Non-Modification 

Service Bulletin (NMSB) SB–BR700–72– 

A900659, Revision 1, dated November 5, 

2019. 

(h) Installation Prohibition 

After the effective date of this AD, do not 

install any affected HPT stage 1 disk onto any 

engine. 

(i) Definition 

(1) For the purpose of this AD, a ‘‘part 

eligible for installation’’ is an HPT stage 1 

disk that is not listed in paragraph 1.A. of 

RRD NMSB SB–BR700–72–A900659, 

Revision 1, dated November 5, 2019. 

(j) 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 Related Information. You may 

email your request 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. 

(k) Related Information 

(1) For more information about this AD, 

contact Wego Wang, Aviation Safety 

Engineer, ECO Branch, FAA, 1200 District 

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

238–7134; fax: (781) 238–7199; email: 

wego.wang@faa.gov. 

(2) Refer to European Union Aviation 

Safety Agency (EASA) AD 2019–0299, dated 

December 10, 2019, for more information. 

You may examine the EASA AD in the AD 

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

searching for and locating it in Docket No. 

FAA–2020–1174. 

(3) For service information identified in 

this AD, contact Rolls-Royce Deutschland Ltd 

& Co KG, Eschenweg 11, Dahlewitz, 15827, 

Germany; phone: +49 0 33 7086 1200; email: 

rrd.techhelp@rolls-royce.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 (781) 238–7759. 

Issued on January 8, 2021. 

Lance T. Gant, 

Director, Compliance & Airworthiness 

Division, Aircraft Certification Service. 

[FR Doc. 2021–00672 Filed 1–19–21; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2020–1140; Project 

Identifier AD–2020–01009–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 

supersede Airworthiness Directive (AD) 

2017–14–13, which applies to certain 

The Boeing Company Model 737–600, 

–700, –700C, –800, –900, and –900ER 

series airplanes. AD 2017–14–13 

requires a torque check of the screws in 

the cover assembly of the heel rest for 

both the captain’s and the first officer’s 

rudder pedals, and corrective action if 

necessary. Since the FAA issued AD 

2017–14–13, operators have continued 

to find loose rudder pedal cover 

fasteners on previously inspected 

airplanes and airplanes outside the 

applicability of AD 2017–14–13. This 

proposed AD would require modifying 

the rudder pedal cover and shroud, and 

apply to all The Boeing Company Model 

737–600, –700, –700C, –800, –900, and 

–900ER series airplanes and Model 737– 

8 and 737–9 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 March 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 


jbell on DSKJLSW7X2PROD with PROPOSALS
6274 Federal Register / Vol. 86, No. 12 / Thursday, January 21, 2021 / Proposed Rules 

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 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–2020–1140. 

Examining the AD Docket 

You may examine the AD docket on 

the internet at https://

www.regulations.gov by searching for 

and locating Docket No. FAA–2020– 

1140; 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: 

Douglas Tsuji, Aerospace Engineer, 

Systems and Equipment Section, FAA, 

Seattle ACO Branch, 2200 South 216th 

St., Des Moines, WA 98198; phone and 

fax: 206–231–3548; email: 

douglas.tsuji@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 the ADDRESSES section. Include 

‘‘Docket No. FAA–2020–1140; Project 

Identifier AD–2020–01009–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 the 

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 the FAA receives about this 

proposed AD. 

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 the person identified 

in the FOR FURTHER INFORMATION

CONTACT section. 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 2017–14–13, 

Amendment 39–18957 (82 FR 33007, 

July 19, 2017) (‘‘AD 2017–14–13’’), for 

certain The Boeing Company Model 

737–600, –700, –700C, –800, –900, and 

–900ER series airplanes. AD 2017–14– 

13 requires a torque check of the screws 

in the cover assembly of the heel rest for 

both the captain’s and the first officer’s 

rudder pedals, and corrective action if 

necessary. AD 2017–14–13 resulted 

from a report of an aborted takeoff 

because the rudder pedals were not 

operating correctly. Investigation 

revealed a protruding screw in the 

rudder pedal heel rest adjacent to the 

pedals. The FAA issued AD 2017–14–13 

to address a protruding screw in the 

cover assembly of the heel rest of a 

rudder pedal. A protruding screw could 

restrict rudder pedal motion and reduce 

differential braking control during 

takeoff or landing, which could cause a 

high-speed runway excursion. 

Actions Since AD 2017–14–13 Was 

Issued 

Since the FAA issued AD 2017–14– 

13, operators have continued to find 

loose rudder pedal cover fasteners on 

previously inspected airplanes and on 

airplanes outside the applicability of the 

AD. The FAA has determined that this 

design issue is an unsafe condition that 

affects all The Boeing Company Model 

737–600, –700, –700C, –800, –900, and 

–900ER series airplanes and Model 737– 

8 and 737–9 airplanes. 

Related Service Information Under 1 

CFR Part 51 

The FAA reviewed Boeing Alert 

Requirements Bulletin 737–27A1313 

RB, Revision 1, dated June 24, 2020; and 

Boeing Alert Requirements Bulletin 

737–27A1314 RB, Revision 1, dated 

June 24, 2020. The service information 

describes procedures for modifying the 

captain’s and first officer’s rudder pedal 

cover and shroud assemblies. These 

documents are distinct since they apply 

to different airplane models. 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. 

FAA’s Determination 

The FAA is issuing this NPRM after 

determining the unsafe condition 

described previously is likely to exist or 

develop in other products of the same 

type design. 

Proposed AD Requirements 

This proposed AD would retain none 

of the requirements of AD 2017–14–13. 

This proposed AD would expand the 

applicability to include all The Boeing 

Company Model –600, –700, –700C, 

–800, –900, and –900ER series airplanes 

and Model 737–8 and 737–9 airplanes. 

This proposed AD would require 

accomplishment of the actions 

identified in Boeing Alert Requirements 

Bulletin 737–27A1313 RB, Revision 1, 

dated June 24, 2020; and Boeing Alert 

Requirements Bulletin 737–27A1314 

RB, Revision 1, dated June 24, 2020; 

described previously, except as 

discussed under ‘‘Differences Between 

this Proposed AD and the Service 

Information,’’ and 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–2020– 

1140. 

Differences Between This Proposed AD 

and the Service Information 

The effectivity of Boeing Alert 

Requirements Bulletin 737–27A1313 

RB, Revision 1, dated June 24, 2020, is 

limited to Model 737–8 and 737–9 

airplanes with certain line numbers. 

The effectivity of Boeing Alert 

Requirements Bulletin 737–27A1314 

RB, Revision 1, dated June 24, 2020, is 

limited to Model 737–600, 737–700, 

737–700C, 737–800, 737–900, and 737– 


jbell on DSKJLSW7X2PROD with PROPOSALS
Federal Register / Vol. 86, No. 12 / Thursday, January 21, 2021 / Proposed Rules 6275 

900ER series airplanes with certain line 

numbers. However, the applicability of 

this proposed AD includes all Boeing 

Model 737–600, –700, –700C, –800, 

–900, and –900ER series airplanes and 

Model 737–8 and 737–9 airplanes. 

Because the affected captain’s and first 

officer’s rudder pedal cover and shroud 

assemblies are rotable parts, the FAA 

has determined that these parts could 

later be installed on airplanes that were 

initially delivered with acceptable 

rudder pedal cover and shroud 

assemblies, thereby subjecting those 

airplanes to the unsafe condition. The 

agency has confirmed with Boeing that 

the Accomplishment Instructions in 

Boeing Alert Requirements Bulletin 

737–27A1313 RB, Revision 1, dated 

June 24, 2020, and Boeing Alert 

Requirements Bulletin 737–27A1314 

RB, Revision 1, dated June 24, 2020, are 

applicable to the expanded group of 

airplanes. 

Costs of Compliance 

The FAA estimates that this proposed 

AD affects 2,048 airplanes of U.S. 

registry. The FAA estimates the 

following costs to comply with this 

proposed AD: 

ESTIMATED COSTS FOR REQUIRED ACTIONS

Action Labor cost Parts cost Cost per 

product 

Cost on U.S. 

operators 

Modifying rudder pedal shroud 

assemblies.

Up to 13 work-hours × $85 per hour = Up to $1,105 ..................... $5,560 Up to $6,665 .... Up to $13,649,920. 

The FAA has included all costs in its 

cost estimate. According to the 

manufacturer, however, some or all 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 has 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 that the proposed regulation: 

(1) Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866, 

(2) Will not affect intrastate aviation 

in Alaska, and 

(3) Will 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 

2017–14–13, Amendment 39–18957 (82 

FR 33007, July 19, 2017), and 

■ b. Adding the following new 

airworthiness directive: 

The Boeing Company: Docket No. FAA– 

2020–1140; Project Identifier AD–2020– 

01009–T. 

(a) Comments Due Date 

The FAA must receive comments on this 

airworthiness directive (AD) action by March 

8, 2021. 

(b) Affected ADs 

This AD replaces AD 2017–14–13, 

Amendment 39–18957 (82 FR 33007, July 19, 

2017) (AD 2017–14–13). 

(c) Applicability 

This AD applies to all The Boeing 

Company airplanes specified in paragraphs 

(c)(1) and (2) of this AD, certificated in any 

category. 

(1) Model 737–600, –700, –700C, –800, 

–900, and –900ER series airplanes. 

(2) Model 737–8 and 737–9 airplanes. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 27, Flight controls. 

(e) Unsafe Condition 

This AD was prompted by a report of an 

aborted takeoff because the rudder pedals 

were not operating correctly, and by 

additional reports of loose rudder pedal 

cover fasteners on previously inspected 

airplanes and on additional airplanes that 

were not included in the applicability of AD 

2017–14–13. The FAA is issuing this AD to 

address incorrectly installed cover assembly 

fasteners from interfering with the operation 

of a rudder pedal. An incorrectly installed 

fastener could restrict rudder pedal motion 

and reduce differential braking control 

during takeoff or landing, which could cause 

a high-speed runway excursion. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Determination of Modification Status 

For airplanes with an original 

airworthiness certificate or original export 

certificate of airworthiness issued before the 

effective date of this AD: Within 27 months 

after the date of issuance of the original 

airworthiness certificate or original export 

certificate of airworthiness, or within 27 

months after the effective date of this AD, 

whichever occurs later, determine whether 

the captain’s and first officer’s rudder pedal 

cover and shroud assemblies have been 

modified as specified in Boeing Alert 

Requirements Bulletin 737–27A1313 RB, 

Revision 1, dated June 24, 2020, or 737– 

27A1314 RB, Revision 1, dated June 24, 2020, 

as applicable, or by production equivalent. A 

review of airplane maintenance records is 

acceptable for this requirement if the 

modification status can be conclusively 

determined from that review. 

(h) Modification 

For airplanes that have not been modified 

as determined by paragraph (g) of this AD: At 


jbell on DSKJLSW7X2PROD with PROPOSALS
6276 Federal Register / Vol. 86, No. 12 / Thursday, January 21, 2021 / Proposed Rules 

the applicable times specified in the 

‘‘Compliance’’ paragraph of Boeing Alert 

Requirements Bulletin 737–27A1313 RB, 

Revision 1, dated June 24, 2020, or Boeing 

Alert Requirements Bulletin 737–27A1314 

RB, Revision 1, dated June 24, 2020, as 

applicable, except as specified by paragraph 

(i) of this AD, do all applicable actions 

identified in, and in accordance with, the 

Accomplishment Instructions of Boeing Alert 

Requirements Bulletin 737–27A1313 RB, 

Revision 1, dated June 24, 2020, or Boeing 

Alert Requirements Bulletin 737–27A1314 

RB, Revision 1, dated June 24, 2020, as 

applicable. 

Note 1 to paragraph (h): Guidance for 

accomplishing the actions required by 

paragraph (h) of this AD can be found in 

Boeing Alert Service Bulletin 737–27A1313, 

Revision 1, dated June 24, 2020, and Boeing 

Alert Service Bulletin 737–27A1314, 

Revision 1, dated June 24, 2020, which are 

referred to in Boeing Alert Requirements 

Bulletin 737–27A1313 RB, Revision 1, dated 

June 24, 2020, and Boeing Alert 

Requirements Bulletin 737–27A1314 RB, 

Revision 1, dated June 24, 2020, respectively. 

(i) Exception to Service Information 

Specifications 

Where Boeing Alert Requirements Bulletin 

737–27A1313 RB, Revision 1, dated June 24, 

2020, and Boeing Alert Requirements 

Bulletin 737–27A1314 RB, Revision 1, dated 

June 24, 2020, use the phrase ‘‘the original 

issue date of’’ each Requirements Bulletin for 

compliance, this AD requires using the 

effective date of this AD. 

(j) Credit for Previous Actions 

This paragraph provides credit for the 

actions specified in paragraph (h) of this AD, 

if those actions were performed before the 

effective date of this AD using Boeing Alert 

Requirements Bulletin 737–27A1313 RB, 

dated March 18, 2020, or Boeing Alert 

Requirements Bulletin 737–27A1314 RB, 

dated March 18, 2020. 

(k) Parts Installation Limitation 

(1) For airplanes with an original 

airworthiness certificate or original export 

certificate of airworthiness issued after the 

effective date of this AD: As of the effective 

date of this AD, no person may install a 

captain’s or first officer’s rudder pedal cover 

or shroud assembly on any airplane, unless 

the cover or shroud assembly has been 

modified in accordance with the 

requirements of paragraph (h) of this AD. 

(2) For airplanes with an original 

airworthiness certificate or original export 

certificate of airworthiness issued prior to the 

effective date of this AD: After the 

modification required by paragraph (h) of 

this AD has been done, no person may install 

a captain’s or first officer’s rudder pedal 

cover or shroud assembly on any airplane, 

unless the cover or shroud assembly has been 

modified in accordance with the 

requirements of paragraph (h) of this AD. 

Reinstallation of a rudder pedal cover or 

shroud assembly that has not been modified 

in accordance with paragraph (h) of this AD 

but has been removed for other maintenance 

is allowed. 

(l) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Seattle 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 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 (m)(1) of 

this AD. Information may be emailed to: 9- 

ANM-Seattle-ACO-AMOC-Requests@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. 

(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, Seattle 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. 

(4) AMOCs approved previously for AD 

2017–14–13 are not approved as AMOCs for 

the corresponding provisions of this AD. 

(5) For service information that contains 

steps that are labeled as Required for 

Compliance (RC), the provisions of 

paragraphs (l)(5)(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. 

(m) Related Information 

(1) For more information about this AD, 

contact Douglas Tsuji, Aerospace Engineer, 

Systems and Equipment Section, FAA, 

Seattle ACO Branch, 2200 South 216th St., 

Des Moines, WA 98198; phone and fax: 206– 

231–3548; email: douglas.tsuji@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 December 17, 2020. 

Lance T. Gant, 

Director, Compliance & Airworthiness 

Division, Aircraft Certification Service. 

[FR Doc. 2021–01161 Filed 1–19–21; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2020–0587; Product 

Identifier 2020–NM–086–AD] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Supplemental notice of 

proposed rulemaking (SNPRM); 

reopening of comment period. 

SUMMARY: The FAA is revising an earlier 

proposal for all The Boeing Company 

Model 737–100, –200, –200C, –300, 

–400, and –500 series airplanes. This 

action revises the notice of proposed 

rulemaking (NPRM) by reducing the 

compliance time for certain airplanes. 

The FAA is proposing this 

airworthiness directive (AD) to address 

the unsafe condition on these products. 

Since these actions would impose an 

additional burden over that in the 

NPRM, the FAA is reopening the 

comment period to allow the public the 

chance to comment on these changes. 

DATES: The comment period for the 

NPRM published in the Federal 

Register on July 28, 2020 (85 FR 45355), 

is reopened. 

The FAA must receive comments on 

this SNPRM by March 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 Boeing service information 

identified in this SNPRM, contact 

Boeing Commercial Airplanes, 

Attention: Contractual & Data Services 


jbell on DSKJLSW7X2PROD with PROPOSALS