Federal Register / Vol. 87, No. 92 / Thursday, May 12, 2022 / Rules and Regulations 29033 

(6) 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. 

(7) You may view this material that is 

incorporated by reference at the National 

Archives and Records Administration 

(NARA). For information on the availability 

of this material at NARA, email 

fr.inspection@nara.gov, or go to: https://

www.archives.gov/federal-register/cfr/ibrlocations.html. 

Issued on April 11, 2022. 

Lance T. Gant, 

Director, Compliance & Airworthiness 

Division, Aircraft Certification Service. 

[FR Doc. 2022–10140 Filed 5–11–22; 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; Amendment 

39–21972; AD 2022–06–06] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: The FAA is superseding 

Airworthiness Directive (AD) 2017–14– 

13, which applied to certain The Boeing 

Company Model 737–600, –700, –700C, 

–800, –900, and –900ER series 

airplanes. AD 2017–14–13 required 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. This AD was prompted by a 

report of an aborted takeoff because the 

rudder pedals were not operating 

correctly, and subsequent reports of 

loose rudder pedal cover fasteners on 

airplanes on which the actions required 

by AD 2017–14–13 were done and on 

additional airplanes that were not 

included in the applicability of AD 

2017–14–13. This AD requires 

modifying the rudder pedal cover and 

shroud assemblies, and applies to all 

The Boeing Company Model 737–600, 

–700, –700C, –800, –900, and –900ER 

series airplanes and Model 737–8 and 

737–9 airplanes. This AD also limits the 

installation of affected parts under 

certain conditions. The FAA is issuing 

this AD to address the unsafe condition 

on these products. 

DATES: This AD is effective June 16, 

2022. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of June 16, 2022. 

ADDRESSES: For service information 

identified in this final rule, 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 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 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 

final rule, any comments received, and 

other information. The address for 

Docket Operations is U.S. Department of 

Transportation, Docket Operations, 

M–30, West Building Ground Floor, 

Room W12–140, 1200 New Jersey 

Avenue SE, Washington, DC 20590. 

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: 

206–231–3548; email: douglas.tsuji@

faa.gov. 

SUPPLEMENTARY INFORMATION: 

Background 

The FAA issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to supersede AD 2017–14–13, 

Amendment 39–18957 (82 FR 33007, 

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

2017–14–13 applied to certain The 

Boeing Company Model 737–600, –700, 

–700C, –800, –900, and –900ER series 

airplanes. AD 2017–14–13 required 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. 

The NPRM published in the Federal 

Register on January 21, 2021 (86 FR 

6273). The NPRM was prompted by a 

report of an aborted takeoff because the 

rudder pedals were not operating 

correctly and subsequent reports of 

loose rudder pedal cover fasteners on 

airplanes on which the actions required 

by AD 2017–14–13 had been done. 

These reports demonstrated that the 

required torque checks were ineffective 

in guaranteeing fastener retention and 

that additional airplanes that had not 

been included in the applicability of AD 

2017–14–13 are also affected (i.e., all 

Model 737–8 and 737–9 airplanes; and 

Model 737–600, –700, –700C, –800, 

–900, and –900ER series airplanes, 

having line numbers 3556 and 

subsequent). In the NPRM, the FAA 

proposed to require modifying the 

rudder pedal cover and shroud 

assemblies with a new design that 

prevents the fasteners from backing out. 

The NPRM also proposed to limit the 

installation of affected parts under 

certain conditions, including 

modification of the cover or shroud 

assembly in accordance with the 

requirements of paragraph (h) of this 

AD. The FAA is issuing this AD to 

address cover assembly fasteners 

interfering with the operation of a 

rudder pedal. A fastener can back out 

and restrict rudder pedal motion and 

reduce differential braking control 

during takeoff or landing, which could 

cause a high-speed runway excursion. 

Discussion of Final Airworthiness 

Directive 

Comments 

The FAA received supportive 

comments from two commenters: Air 

Line Pilots Association, International 

(ALPA) and United Airlines (UAL). 

ALPA supported the NPRM without 

change. UAL supported the NPRM, but 

requested clarification regarding the 

method for part marking, as discussed 

later in this discussion. 

The FAA also received comments 

from Boeing, Aviation Partners Boeing, 

and Delta Air Lines (DAL). The 

following presents the comments 

received on the NPRM and the FAA’s 

response to each comment. 

Effect of Winglets on Accomplishment 

of the Proposed Actions 

Aviation Partners Boeing stated that 

the installation of winglets per 

Supplemental Type Certificate STC 

ST00830SE does not affect compliance 

with the proposed actions. 

The FAA agrees with the commenter. 

The installation of STC ST00830SE does 

not affect an operator’s ability to 

accomplish the actions required by this 

AD. The FAA has not changed this AD. 


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29034 Federal Register / Vol. 87, No. 92 / Thursday, May 12, 2022 / Rules and Regulations 

Request To Update the Service 

Information to the Latest Revision 

Boeing requested that the FAA require 

Boeing Requirements Bulletin 737– 

27A1314 RB, Revision 2, dated July 6, 

2021, because an individual airplane 

was omitted from the effectivity of the 

previous revision of the service bulletin 

(the NPRM proposed that operators do 

actions using Boeing Alert 

Requirements Bulletin 737–27A1314 

RB, Revision 1, dated June 24, 2020). 

The FAA agrees to require Boeing 

Requirements Bulletin 737–27A1314 

RB, Revision 2, dated July 6, 2021, 

because the individual airplane added 

to the effectivity of that service bulletin 

was already in the applicability of the 

proposed rule and therefore no change 

to the applicability of the final rule is 

necessary. 

Furthermore, Boeing Requirements 

Bulletin 737–27A1314 RB, Revision 2, 

dated July 6, 2021, does not add new 

actions or revise the existing actions 

specified in Boeing Alert Requirements 

Bulletin 737–27A1314 RB, Revision 1, 

dated June 24, 2020, which the NPRM 

proposed as a method of compliance for 

doing the actions required by this AD. 

The FAA has revised this AD to 

specify that required actions be done in 

accordance with Boeing Requirements 

Bulletin 737–27A1314 RB, Revision 2, 

dated July 6, 2021, as applicable, and to 

give credit for actions done in 

accordance with Boeing Alert 

Requirements Bulletin 737–27A1314 

RB, Revision 1, dated June 24, 2020. 

Request To Change Applicability of the 

Proposed AD 

Boeing requested that the 

applicability of the proposed AD be 

revised to match the effectivity defined 

in 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. 

Boeing stated that the shroud and cover 

do not meet the definition of ‘‘rotable 

parts’’ in the new configuration, because 

the parts are no longer interchangeable 

following modification and must also 

have the mating part (the part that 

attached to the aircraft structure) 

modified to be installed. Boeing also 

stated a ‘‘pre-modified part’’ cannot be 

installed on an airplane having the 

service bulletin modifications. Based on 

this non-interchangeability, Boeing does 

not consider these as rotable. 

The FAA disagrees with changing the 

applicability, as specified in paragraph 

(c) of this AD, because the FAA has 

determined there is a rotability issue. It 

is true that an original shroud assembly 

cannot be installed with an upper cover 

assembly modified as specified in the 

requirements bulletins identified in this 

AD, and conversely a shroud assembly 

modified as specified in the 

requirements bulletins cannot be 

installed with an original upper cover 

assembly. However, it is still physically 

possible to install an original shroud 

assembly and an original upper cover 

assembly (the combination with the 

unsafe condition) on an airplane not 

identified in the Boeing requirements 

bulletins. Therefore, no changes have 

been made to this AD regarding this 

request. 

Request for Definition of ‘‘Production 

Equivalent’’ 

Boeing and DAL requested that the 

FAA revise paragraph (g) of the 

proposed AD to further define what 

constitutes a ‘‘production equivalent.’’ 

DAL asked if certain part numbers and 

subsequent part numbers that are fully 

interchangeable can be installed. Boeing 

stated that more guidance is needed for 

operators on how to verify that the 

change is incorporated on production 

airplanes that have been delivered. 

Boeing stated that for airplanes 

modified by Boeing, operators do not 

have a corresponding maintenance 

record and that delivery records may be 

used for verification of production 

equivalent. 

The FAA agrees with the request. The 

NPRM did not provide a definition of a 

‘‘production equivalent,’’ which need 

not be further modified. Paragraph (g) of 

this AD has been revised to include the 

following information: ‘‘A production 

equivalent can be determined by its 

upper cover assembly part numbers (P/ 

Ns 251A3122–15 (pilot) and 251A3122– 

16 (first officer), or later approved part 

numbers) and shroud assembly part 

numbers (P/Ns 233A2319–5 or –6, or 

later approved part numbers, used for 

both pilot and first officer).’’ 

Request for Re-Identification of 

Modified Housing and Shrouds 

DAL requested that the service 

information be revised. DAL stated that 

modified housing and shrouds should 

be re-identified with a new dash 

number instead of with the service 

bulletin number. DAL stated that 

configuration control could be an issue 

if the pre- and post-modification parts 

were to share a common part number. 

The commenter asserted that in an 

aircraft on ground or ‘‘AOG’’ situation 

(such as when a maintenance issue 

prevents the airplane from departing 

from an airport until the issue is 

resolved), the operator could find out 

too late that a part brought to the 

airplane is unmodified and is, therefore, 

restricted for installation, which could 

lead to an operational delay to allow for 

part modification prior to returning the 

aircraft to service. DAL argued that a 

new, unique part number would 

eliminate that risk. 

The FAA disagrees with the requested 

change. The FAA acknowledges that 

parts are typically identified by part 

numbers, and that continued use of the 

same part number for both modified and 

unmodified parts could make it difficult 

for operators to keep track of them. 

However, the FAA disagrees with reidentifying modified parts with a new 

dash number, because some operators 

have already modified their airplanes 

using the existing service information 

and imposing this additional 

requirement would necessitate work 

unrelated to addressing the unsafe 

condition. Furthermore, waiting for 

revised service information that 

incorporates the identification of new 

dash numbers would delay the issuance 

of this AD. After this AD is issued, 

operators could coordinate with the 

manufacturer to create a unique new 

part number for parts modified in 

accordance with the service 

information, and the manufacturer 

could propose installation of the new 

part number as an alternative method of 

compliance (AMOC) to this AD. This 

AD has not been changed with regard to 

this request. 

Request To Allow Part Marking by 

Hand Lettering 

DAL requested a change in paragraph 

(i) of the proposed AD to specify either 

rubber stamp or hand lettering, because 

hand lettering is an acceptable alternate 

method of part marking for the affected 

part. DAL also stated that the 

manufacturer agrees hand lettering is an 

acceptable alternative to the rubber 

stamp method. In addition, UAL 

requested that the FAA clarify the part 

marking in the required for compliance 

(RC) step of the service information that 

refers to the standard overhaul practices 

manual (SOPM). UAL stated that the 

SOPM includes a note referring to 

alternate marking methods (i.e., hand 

lettering instead of rubber stamp). 

The FAA disagrees with the request to 

modify paragraph (i) of this AD because 

the service information does not specify 

the method by which the part marking 

must be applied. This AD requires that 

part marking must be done. However, 

the method of part marking is not 

mandated, as the service information 

refers to the SOPM. The use of the ‘‘refer 

to’’ indicates the SOPM is guidance on 

how to do the part marking. The SOPM 


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Federal Register / Vol. 87, No. 92 / Thursday, May 12, 2022 / Rules and Regulations 29035 

specifies using a rubber stamp and 

allows for hand lettering as an 

alternative action so operators may use 

either method or may use an accepted 

alternative. This AD has not been 

changed regarding this request. 

Request To Change To Allow 

Installation of New Housing 

DAL requested a change to correct 

certain discrepancies in Boeing Alert 

Service Bulletin 737–27A1314, Revision 

1, dated June 24, 2020. In the non-RC 

sections ‘‘Work Package 1, Part 2: 

Installation, Test and Close Access’’ and 

‘‘Work Package 2, Part 2: Installation, 

Test and Close Access,’’ DAL asked for 

a change in wording of the proposed AD 

to indicate that a ‘‘new or changed’’ 

upper cover assembly could be 

installed. The commenter explained that 

the work instructions allow either 

Option 1 (modify then reinstall existing 

housing) or Option 2 (install new 

housing). 

The FAA disagrees with the request. 

While the non-RC work instructions in 

Boeing Alert Service Bulletin 737– 

27A1314, Revision 1, dated June 24, 

2020, accurately describe the allowable 

installations, changing the AD would 

not be warranted because the indicated 

sections are not within Boeing Alert 

Requirements Bulletin 737–27A1314 

RB, Revision 2, dated July 6, 2021 (or 

within Revision 1, dated June 24, 2020). 

‘‘Work Package 1, Part 2: Installation, 

Test and Close Access’’ and ‘‘Work 

Package 2, Part 2: Installation, Test and 

Close Access,’’ of Boeing Alert Service 

Bulletin 737–27A1314, Revision 2, 

dated July 6, 2021, are for reference 

only. The manufacturer may choose to 

update this section of the service 

information in a future revision, but this 

section does not affect compliance with 

this AD. Operators can use either option 

as specified in Boeing Alert 

Requirements Bulletin 737–27A1314 

RB, Revision 2, dated July 6, 2021. This 

AD has not been changed regarding this 

request. 

Clarification of Parts Installation 

Prohibition 

Paragraphs (k)(1) and (2) of the 

proposed AD specified the parts 

installation prohibition for airplanes 

with an original airworthiness 

certificate or original export certificate 

of airworthiness issued after the 

effective date of this AD and prior to the 

effective date of this AD. However, 

airplanes with an original airworthiness 

certificate or original export certificate 

of airworthiness issued on the effective 

date of this AD were not identified in 

either paragraph. The FAA has revised 

paragraph (k)(1) of this AD to include 

the parts installation prohibition for 

airplanes with an original airworthiness 

certificate or original export certificate 

of airworthiness issued on or after the 

effective date of this AD. 

Conclusion 

The FAA reviewed the relevant data, 

considered the comments received, and 

determined that air safety requires 

adopting the requirements of this AD. 

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 2, dated July 

6, 2021. The service information 

describes procedures for modifying the 

captain’s and first officer’s rudder pedal 

cover and shroud assemblies. 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. 

Costs of Compliance 

The FAA estimates that this AD 

affects 2,048 airplanes of U.S. registry. 

The FAA estimates the following costs 

to comply with this AD: 

ESTIMATED COSTS FOR REQUIRED ACTIONS

Action Labor cost Parts cost Cost per 

product 

Cost on U.S. 

operators 

Modifying the rudder pedal cover and 

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 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 

This AD will not have federalism 

implications under Executive Order 

13132. This AD will 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 this AD: 

(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 Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA amends 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. 


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29036 Federal Register / Vol. 87, No. 92 / Thursday, May 12, 2022 / Rules and Regulations 

§ 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 AD: 

2022–06–06 The Boeing Company: 

Amendment 39–21972; Docket No. 

FAA–2020–1140; Project Identifier AD– 

2020–01009–T. 

(a) Effective Date 

This airworthiness directive (AD) is 

effective June 16, 2022. 

(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 subsequent 

reports of loose rudder pedal cover fasteners 

on airplanes on which the actions required 

by AD 2017–14–13 were done and on 

additional airplanes that were not included 

in the applicability of AD 2017–14–13. The 

FAA is issuing this AD to address cover 

assembly fasteners interfering with the 

operation of a rudder pedal. A fastener can 

back out and 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 2, dated July 6, 2021; 

as applicable, or has a production equivalent. 

A production equivalent can be determined 

by its upper cover assembly part numbers (P/ 

Ns 251A3122–15 (pilot) and 251A3122–16 

(first officer), or later approved part numbers) 

and shroud assembly part numbers (P/Ns 

233A2319–5 or –6, or later approved part 

numbers, used for both pilot and first officer). 

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 

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 2, dated July 6, 2021, 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 2, dated July 6, 2021; 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 2, dated July 6, 2021; 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 2, dated July 6, 2021; 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 2, dated 

July 6, 2021, 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; Boeing Alert 

Requirements Bulletin 737–27A1314 RB, 

dated March 18, 2020; or Boeing Alert 

Requirements Bulletin 737–27A1314 RB, 

Revision 1, dated June 24, 2020. 

(k) Parts Installation Limitation 

(1) For airplanes with an original 

airworthiness certificate or original export 

certificate of airworthiness issued on or 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) of this 

AD. Information may be emailed to: 9-ANMSeattle-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. 

(m) Related Information 

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: 206–231– 

3548; email: douglas.tsuji@faa.gov. 

(n) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 

(IBR) of the service information listed in this 

paragraph under 5 U.S.C. 552(a) and 1 CFR 

part 51. 

(2) You must use this service information 

as applicable to do the actions required by 

this AD, unless the AD specifies otherwise. 

(i) Boeing Alert Requirements Bulletin 

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

2020. 

(ii) Boeing Alert Requirements Bulletin 

737–27A1314 RB, Revision 2, dated July 6, 

2021. 

(3) 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; 


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telephone 562–797–1717; internet https://

www.myboeingfleet.com. 

(4) 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. 

(5) You may view this service information 

that is incorporated by reference at the 

National Archives and Records 

Administration (NARA). For information on 

the availability of this material at NARA, 

email fr.inspection@nara.gov, or go to: 

https://www.archives.gov/federal-register/cfr/ 

ibr-locations.html. 

Issued on March 10, 2022. 

Lance T. Gant, 

Director, Compliance & Airworthiness 

Division, Aircraft Certification Service. 

[FR Doc. 2022–10178 Filed 5–11–22; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2021–0870; Project 

Identifier MCAI–2021–00644–T; Amendment 

39–22007; AD 2022–08–04] 

RIN 2120–AA64 

Airworthiness Directives; Airbus SAS 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: The FAA is adopting a new 

airworthiness directive (AD) for all 

Airbus SAS Model A300 series 

airplanes. This AD was prompted by a 

determination that new or more 

restrictive airworthiness limitations are 

necessary. This AD requires revising the 

existing maintenance or inspection 

program, as applicable, to incorporate 

new or more restrictive airworthiness 

limitations, as specified in a European 

Union Aviation Safety Agency (EASA) 

AD, which is incorporated by reference. 

The FAA is issuing this AD to address 

the unsafe condition on these products. 

DATES: This AD is effective June 16, 

2022. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of June 16, 2022. 

ADDRESSES: For material 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 IBR material on the EASA 

website at https://ad.easa.europa.eu. 

You may view this IBR 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. 

It is also available in the AD docket on 

the internet at https://

www.regulations.gov by searching for 

and locating Docket No. FAA–2021– 

0870. 

Examining the AD Docket 

You may examine the AD docket at 

https://www.regulations.gov by 

searching for and locating Docket No. 

FAA–2021–0870; 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 

final rule, the mandatory continuing 

airworthiness information (MCAI), any 

comments received, and other 

information. The address for Docket 

Operations is U.S. Department of 

Transportation, Docket Operations, 

M–30, West Building Ground Floor, 

Room W12–140, 1200 New Jersey 

Avenue SE, Washington, DC 20590. 

FOR FURTHER INFORMATION CONTACT: Dan 

Rodina, Aerospace Engineer, Large 

Aircraft Section, International 

Validation Branch, FAA, 2200 South 

216th St., Des Moines, WA 98198; 

telephone and fax 206–231–3225; email 

dan.rodina@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Background 

EASA, which is the Technical Agent 

for the Member States of the European 

Union, has issued EASA AD 2021–0134, 

dated June 1, 2021 (EASA AD 2021– 

0134) (also referred to as the Mandatory 

Continuing Airworthiness Information, 

or the MCAI), to correct an unsafe 

condition for all Airbus SAS Model 

A300 series airplanes. 

The FAA issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 by adding an AD that would 

apply to all Airbus SAS Model A300 

series airplanes. The NPRM published 

in the Federal Register on October 7, 

2021 (86 FR 55749). The NPRM was 

prompted by a determination that new 

or more restrictive airworthiness 

limitations are necessary. The NPRM 

proposed to require revising the existing 

maintenance or inspection program, as 

applicable, to incorporate new or more 

restrictive airworthiness limitations, as 

specified in EASA AD 2021–0134. 

The FAA is issuing this AD to prevent 

reduced structural integrity of the 

airplane. See the MCAI for additional 

background information. 

Discussion of Final Airworthiness 

Directive 

Comments 

The FAA received a comment from 

the Air Line Pilots Association, 

International (ALPA) who supported the 

NPRM without change. 

The FAA received an additional 

comment from UPS Airlines. The 

following presents the comment 

received on the NPRM and the FAA’s 

response. 

Request To Reference Related 

Rulemaking 

UPS Airlines stated that paragraph (b) 

of the proposed AD does not refer to any 

affected ADs. UPS Airlines added that 

this is in contrast to NPRM MCAI– 

2021–00385–T, dated August 9, 2021 

(Docket No. FAA–2021–0617 (86 FR 

43440, August 9, 2021)), which also 

would individually mandate an 

airworthiness limitations section (ALS) 

Variation document without 

superseding prior rulemaking. UPS 

Airlines noted that in paragraph (b) of 

that NPRM, the current ALS Part 2 

rulings are identified as affected by the 

proposed rule. UPS Airlines proposed to 

include in paragraph (b) of this 

proposed AD the applicable existing 

mandatory ruling(s) for the A300 ALS 

Part 2, Revision 3, and subsequent 

released variations (the FAA notes the 

existing requirements for incorporating 

the A300 ALS Part 2, Revision 3 are in 

AD 2018–19–17, Amendment 39–19417 

(83 FR 48207, September 24, 2018) (AD 

2018–19–17)). 

The FAA agrees with the commenter’s 

request. By definition, an ‘‘affected AD’’ 

is one where all or part of the 

requirements of that AD is affected by 

the new AD. Affected ADs are provided 

in paragraph (b) of AD actions solely for 

information. Paragraph (h)(2) of this AD 

states that the new limit of validity 

(LOV) required by this AD replaces the 

LOVs required by AD 2018–19–17. 

Therefore, the FAA has revised 

paragraph (b) of this AD to refer to AD 

2018–19–17. 

Clarification for Paragraph (h)(2) of the 

Proposed AD 

Paragraph (h)(2) of the proposed AD 

incorrectly specifies the date for Airbus 

A300 ALS, Part 2, Revision 03, as 

‘‘March 16, 2021.’’ The correct date is 

August 28, 2017. Paragraph (h)(2) of this 

AD has been revised to refer to the 

correct date. 

Conclusion 

The FAA reviewed the relevant data, 

considered the comments received, and 

determined that air safety requires 


khammond on DSKJM1Z7X2PROD with RULES