[Federal Register Volume 87, Number 92 (Thursday, May 12, 2022)]
[Rules and Regulations]
[Pages 29033-29037]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2022-10178]


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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.

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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: 
<a href="/cdn-cgi/l/email-protection#dcb8b3a9bbb0bdaff2a8afa9b6b59cbabdbdf2bbb3aa"><span class="__cf_email__" data-cfemail="44202b31232825376a3037312e2d042225256a232b32">[email protected]</span></a>.

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.

[[Page 29034]]

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 re-identifying 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

[[Page 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     Up to 13 work-         $5,560  Up to $6,665...........  Up to $13,649,920.
 cover and shroud assemblies.   hours x $85 per
                                hour = Up to
                                $1,105.
----------------------------------------------------------------------------------------------------------------

    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

0
1. The authority citation for part 39 continues to read as follows:

    Authority:  49 U.S.C. 106(g), 40113, 44701.

[[Page 29036]]

Sec.  39.13  [Amended]

0
2. The FAA amends Sec.  39.13 by:
0
a. Removing Airworthiness Directive 2017-14-13, Amendment 39-18957 (82 
FR 33007, July 19, 2017); and
0
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: <a href="/cdn-cgi/l/email-protection#f7cedab6b9badaa4929683839b92dab6b4b8dab6bab8b4daa592868292848384b7919696d9909881"><span class="__cf_email__" data-cfemail="b98094f8f7f494eadcd8cdcdd5dc94f8faf694f8f4f6fa94ebdcc8ccdccacdcaf9dfd8d897ded6cf">[email protected]</span></a>.
    (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: <a href="/cdn-cgi/l/email-protection#81e5eef4e6ede0f2aff5f2f4ebe8c1e7e0e0afe6eef7"><span class="__cf_email__" data-cfemail="b8dcd7cddfd4d9cb96cccbcdd2d1f8ded9d996dfd7ce">[email protected]</span></a>.

(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;

[[Page 29037]]

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 <a href="/cdn-cgi/l/email-protection#f99f8bd790978a899c9a8d909697b997988b98d79e968f"><span class="__cf_email__" data-cfemail="f89e8ad691968b889d9b8c919796b896998a99d69f978e">[email protected]</span></a>, 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


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