[Federal Register Volume 89, Number 61 (Thursday, March 28, 2024)]
[Proposed Rules]
[Pages 21446-21450]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2024-06522]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2024-0769; Project Identifier AD-2023-00556-T]
RIN 2120-AA64


Airworthiness Directives; The Boeing Company Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD) 
for certain The Boeing Company Model 777 airplanes. This proposed AD 
was prompted by a report indicating multiple findings of cracks in the 
fuselage skin common to the underwing longeron (UWL). This proposed AD 
would require external or internal (depending on configuration) 
inspections for any cracking of the left and right side fuselage skin 
common to the UWL, and applicable on-condition actions. The FAA is 
proposing this AD to address the unsafe condition on these products.

DATES: The FAA must receive comments on this proposed AD by May 13, 
2024.

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 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.
    AD Docket: You may examine the AD docket at regulations.gov under 
Docket No. FAA-2024-0769; 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.
    Material Incorporated by Reference:
     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; website 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 
regulations.gov by searching for and locating Docket No. FAA-2024-0769.

FOR FURTHER INFORMATION CONTACT: Luis Cortez-Muniz, Aviation Safety 
Engineer, FAA, 2200 South 216th St., Des Moines, WA 98198; phone: 206-
231-3958; email: [email protected].

SUPPLEMENTARY INFORMATION:

Comments Invited

    The FAA invites you to send any written relevant data, views, or 
arguments about this proposal. Send your comments to an address listed 
under ADDRESSES. Include ``Docket No. FAA-2024-0769; Project Identifier 
AD-2023-00556-T'' at the beginning of your comments. The most helpful 
comments reference a specific portion of the proposal, explain the 
reason for any recommended change, and include supporting data. The FAA 
will consider all comments received by the closing date and may amend 
this proposal because of those comments.
    Except for Confidential Business Information (CBI) as described in 
the following paragraph, and other information as described in 14 CFR 
11.35, the FAA will post all comments received, without change, to 
regulations.gov, including any personal information you provide. The 
agency will also post a report summarizing each substantive verbal 
contact received about this NPRM.

Confidential Business Information

    CBI is commercial or financial information that is both customarily 
and actually treated as private by its owner. Under the Freedom of 
Information Act (FOIA) (5 U.S.C. 552), CBI is exempt from public 
disclosure. If your comments responsive to this NPRM contain commercial 
or financial information that is customarily treated as private, that 
you actually treat as private, and that is relevant or responsive to 
this NPRM, it is important that you clearly designate the submitted 
comments as CBI. Please mark each page of your submission containing 
CBI as ``PROPIN.'' The FAA will treat such marked submissions as 
confidential under the FOIA, and they will not be placed in the public 
docket of this NPRM. Submissions containing CBI should be sent to Luis 
Cortez-Muniz Aviation Safety Engineer, FAA, 2200 South 216th St., Des 
Moines, WA 98198; phone: 206-231-3958; email: [email protected]. Any commentary that the FAA receives that is not 
specifically designated as CBI will be placed in the public docket for 
this rulemaking.

Background

    The FAA has received reports indicating multiple findings of cracks 
in the fuselage skin common to the UWL on all series of Boeing Model 
777 airplanes. The crack findings were made during UWL replacement or 
accomplishing Boeing Service Bulletins 777-53-0084 or 777-53-0087, or 
Boeing Requirements Bulletin 777-57A0122 RB. In many of the fuselage 
skin crack reports, the UWL was reported not damaged. The found 
fuselage skin cracks were hidden externally by the UWL, and internally 
by fuselage frames and stringers. The fuselage skin cracks were found 
on airplanes with as few as 2,000 total flight cycles and 18,000 total 
flight hours. These fuselage skin cracks were determined to be caused 
by cold work surface upset that is not removed from the mating parts 
and high joint load transfer or significant local bending stresses at 
critical fastener locations. These conditions, if not addressed, could 
result in an inability of a principal structural element (PSE) to 
sustain limit load, leading to reduced structural integrity of the 
airplane and possible loss of control of the airplane.
    Boeing has issued Boeing Alert Requirements Bulletin 777-53A0100

[[Page 21447]]

RB, dated March 16, 2023, to address the identified unsafe condition.

Other Relevant Rulemaking

    AD 2023-17-14, Amendment 39-22541 (88 FR 60111, August 31, 2023) 
(AD 2023-17-14) requires repetitive inspections for cracking of the 
left and right side ring chords, repair angles, front spar lower 
chords, and front spar webs (depending on configuration) common to the 
UWL located at station (STA) 1035; modification of the front spar lower 
chord for some airplanes; repetitive post-modification inspections; and 
applicable on-condition actions, as specified in Boeing Alert 
Requirements Bulletin 777-57A0122 RB, dated October 8, 2021; and 
requires a maintenance records review of previously modified airplanes 
for the procedures used during that modification, and applicable 
corrective actions. Boeing Alert Requirements Bulletin 777-53A0100 RB, 
dated March 16, 2023, specifies that the modification in Boeing Alert 
Requirements Bulletin 777-57A0122 RB should be done before further 
flight if cracking is found during certain inspections. Therefore, this 
proposed AD, which mandates Boeing Alert Requirements Bulletin 777-
53A0100 RB, dated March 16, 2023, might require that the modification 
be done prior to the compliance time for that modification as specified 
in AD 2023-17-14. For airplanes on which a front spar lower chord 
modification specified in Boeing Alert Requirements Bulletin 777-
57A0122 RB is done as part of the requirements of paragraph (g) of this 
proposed AD, the modification requirements of paragraph (g) of AD 2023-
17-14 are terminated for the applicable side (left or right) on which 
the modification was done.
    AD 2019-11-02, Amendment 39-19648 (84 FR 28722, June 20, 2019) (AD 
2019-11-02) requires repetitive inspections of the left and right side 
UWLs and applicable on-condition actions as specified in Boeing Alert 
Service Bulletin 777-53A0081, Revision 2, dated March 29, 2019. The 
accomplishment of the longeron modification specified in Boeing Service 
Bulletin 777-53-0084, Revision 2, dated December 9, 2020, or Boeing 
Service Bulletin 777-53-0087, Revision 1, dated March 4, 2020; or the 
front spar lower chord modification specified in Boeing Alert 
Requirements Bulletin 777-57A0122 RB, dated October 8, 2021; which must 
be done if cracking is found during certain inspections specified in 
Boeing Alert Requirements Bulletin 777-53A0100 RB, dated March 16, 
2023, terminates the inspection requirements of paragraph (g) of AD 
2019-11-02 for the applicable side (left or right) on which the 
modification was done.

FAA's Determination

    The FAA is issuing this NPRM after determining that the unsafe 
condition described previously is likely to exist or develop on other 
products of the same type design.

Related Service Information Under 1 CFR Part 51

    The FAA reviewed Boeing Alert Requirements Bulletin 777-53A0100 RB, 
dated March 16, 2023. This service information specifies procedures for 
external or internal (depending on configuration) detailed and 
ultrasonic or surface high frequency eddy current (HFEC) inspections 
for any cracking of the left and right side fuselage skin common to the 
UWL, and applicable on-condition actions. On-condition actions include, 
among other things, modification of the fuselage skin, and post-
modification inspections and applicable corrective actions (repairs of 
cracking). Compliance times for on-condition actions depend on 
inspection type, inspection findings, and modification status. Initial 
compliance times for post-modification inspections range from within 
10,000 flight cycles or 50,000 flight hours, whichever occurs first 
after the modification; and within 30,000 flight cycles, 90,000 flight 
hours, or before the result of a certain total flight cycle and total 
flight hour equation, whichever occurs first after the modification. 
The repetitive intervals range from 8,000 flight cycles or 25,000 
flight hours, whichever occurs first, to 11,000 flight cycles or 56,000 
flight hours, whichever occurs first. Repairs of cracking found during 
post-modification inspections are to be accomplished before further 
flight.
    The FAA also reviewed Boeing Multi Operator Message MOM-MOM-24-
0054-01B, dated January 26, 2024. This service information specifies 
corrections for Boeing Alert Requirements Bulletin 777-57A0122 RB, 
dated October 8, 2021, that address a non-destructive test manual 
(NDTM) error, fastener callout errors, inadequate cap seal 
instructions, figure orientation errors, minimum gap errors, missing 
fasteners on certain figures, affected groups missing from certain 
figures, and typographical errors.
    This service information is reasonably available because the 
interested parties have access to it through their normal course of 
business or by the means identified in ADDRESSES.

Proposed AD Requirements in This NPRM

    This proposed AD would require accomplishing the actions specified 
in the service information already described 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 regulations.gov under Docket No. FAA-
2024-0769.

Costs of Compliance

    The FAA estimates that this AD, if adopted as proposed, would 
affect 272 airplanes of U.S. registry. The FAA estimates the following 
costs to comply with this proposed AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                 Cost on U.S.
             Action                    Labor cost         Parts cost      Cost per product        operators
----------------------------------------------------------------------------------------------------------------
External or internal inspections  Up to 21 work-hours              $0   $1,785 per           $485,520 per
                                   x $85 per hour =                      inspection cycle.    inspection cycle.
                                   $1,785 per
                                   inspection cycle.
----------------------------------------------------------------------------------------------------------------

    The FAA estimates the following costs to do any necessary on-
condition actions that would be required based on the results of the 
proposed inspection. The agency has no way of determining the number of 
aircraft that might need these actions:

[[Page 21448]]



                                               On-Condition Costs
----------------------------------------------------------------------------------------------------------------
                 Action                           Labor cost            Parts cost         Cost per product
----------------------------------------------------------------------------------------------------------------
Modification............................  420 work-hours x $85 per           $40,620  $76,320.
                                           hour = $35,700.
Post-modification inspections...........  46 work-hours x $85 per                  0  3,910 per inspection
                                           hour = $3,910 per                           cycle.
                                           inspection cycle.
----------------------------------------------------------------------------------------------------------------

    The FAA has received no definitive data on which to base the cost 
estimates for the on-condition repairs specified in this proposed AD.
    The FAA has included all known 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 determined that this proposed AD would not have federalism 
implications under Executive Order 13132. This proposed AD would not 
have a substantial direct effect on the States, on the relationship 
between the national Government and the States, or on the distribution 
of power and responsibilities among the various levels of government.
    For the reasons discussed above, I certify this proposed 
regulation:
    (1) Is not a ``significant regulatory action'' under Executive 
Order 12866,
    (2) Would not affect intrastate aviation in Alaska, and
    (3) Would not have a significant economic impact, positive or 
negative, on a substantial number of small entities under the criteria 
of the Regulatory Flexibility Act.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

The Proposed Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA proposes to amend 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

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

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


Sec.  39.13  [Amended]

0
2. The FAA amends Sec.  39.13 by adding the following new airworthiness 
directive:

The Boeing Company: Docket No. FAA-2024-0769; Project Identifier AD-
2023-00556-T.

(a) Comments Due Date

    The FAA must receive comments on this airworthiness directive 
(AD) by May 13, 2024.

(b) Affected ADs

    This AD affects AD 2023-17-14, Amendment 39-22541 (88 FR 60111, 
August 31, 2023) (AD 2023-17-14).

(c) Applicability

    This AD applies to The Boeing Company Model 777-200, -200LR, -
300, -300ER, and 777F series airplanes, certificated in any 
category, as identified in Boeing Alert Requirements Bulletin 777-
53A0100 RB, dated March 16, 2023.

(d) Subject

    Air Transport Association (ATA) of America Code 53, Fuselage.

(e) Unsafe Condition

    This AD was prompted by a report indicating multiple findings of 
cracks in the fuselage skin common to the underwing longeron (UWL). 
The FAA is issuing this AD to address fuselage skin cracking caused 
by cold work surface upset that is not removed from the mating parts 
and high joint load transfer or significant local bending stresses 
at critical fastener locations. The unsafe condition, if not 
addressed, could result in an inability of a principal structural 
element (PSE) to sustain limit load, leading to reduced structural 
integrity of the airplane and possible loss of control of the 
airplane.

(f) Compliance

    Comply with this AD within the compliance times specified, 
unless already done.

(g) Required Actions

    Except as specified by paragraph (h) of this AD: At the 
applicable times specified in the ``Compliance'' paragraph of Boeing 
Alert Requirements Bulletin 777-53A0100 RB, dated March 16, 2023, do 
all applicable actions identified in, and in accordance with, the 
Accomplishment Instructions of Boeing Alert Requirements Bulletin 
777-53A0100 RB, dated March 16, 2023.
    Note 1 to paragraph (g): Guidance for accomplishing the actions 
required by this AD can be found in Boeing Alert Service Bulletin 
777-53A0100, dated March 16, 2023, which is referred to in Boeing 
Alert Requirements Bulletin 777-53A0100 RB, dated March 16, 2023.
    Note 2 to paragraph (g): Guidance for accomplishing certain on-
condition actions required by paragraph (g) of this AD can be found 
Boeing Service Bulletin 777-53-0084 Revision 2, dated December 9, 
2020; Boeing Service Bulletin 777-53-0087 Revision 1, dated March 4, 
2020; and Boeing Alert Requirements Bulletin 777-57A0122 RB, dated 
October 8, 2021.

(h) Exceptions to Service Information Specifications

    (1) Where the Compliance Time columns of the tables in the 
``Compliance'' paragraph of Boeing Alert Requirements Bulletin 777-
53A0100 RB, dated March 16, 2023, use the phrase ``the original 
issue date of Requirements Bulletin 777-53A0100 RB,'' this AD 
requires using the effective date of this AD.
    (2) Where Boeing Alert Requirements Bulletin 777-53A0100 RB, 
dated March 16, 2023, and any service information referenced in 
Boeing Alert Requirements Bulletin 777-53A0100 RB, dated March 16, 
2023, specifies contacting Boeing for repair instructions: This AD 
requires doing the repair using a method approved in accordance with 
the procedures specified in paragraph (j) of this AD.
    (3) Where any service information referenced in Boeing Alert 
Requirements Bulletin 777-53A0100 RB, dated March 16, 2023, 
specifies applying a cap seal (sealant) to a fastener, fastener 
head, and fastener threads and collars, for this AD, during 
application of any cap seal to a fastener, fastener head, or 
fastener threads and collars, the cap seal must be applied using a 
cap sealing procedure with thickness greater than or equal to the 
dimensions given in Figure 1 to paragraph (h)(3) of this AD.

[[Page 21449]]

Figure 1 to Paragraph (h)(3)--Cap Sealing Dimensions (all Dimensions 
are in Inches)
[GRAPHIC] [TIFF OMITTED] TP28MR24.025

    (4) Where Boeing Alert Requirements Bulletin 777-53A0100 RB, 
dated March 16, 2023, specifies doing actions ``in accordance with 
Revision 2 of Boeing Service Bulletin 777-53-0084,'' for this AD, 
where flagnote (f) of Figure 7 and Figure 22 of that referenced 
service information (``Revision 2 of Boeing Service Bulletin 777-53-
0084'') includes a sealant callout of Boeing Material Specification 
(BMS) 5-45 or an optional BMS 5-95, only BMS 5-45 is allowed.
    (5) Where Boeing Alert Requirements Bulletin 777-53A0100 RB, 
dated March 16, 2023, specifies doing actions ``in accordance with 
Revision 1 of Boeing Service Bulletin 777-53-0087,'' for this AD, 
where flagnote (f) of Figure 13 and Figure 49 of that referenced 
service information (``Revision 1 of Boeing Service Bulletin 777-53-
0087'') includes a sealant callout of BMS 5-45 or an optional BMS 5-
95, only BMS 5-45 is allowed.
    (6) Where Boeing Alert Requirements Bulletin 777-53A0100 RB, 
dated March 16, 2023, specifies doing actions ``in accordance with 
the original issue of Boeing Alert Requirements Bulletin 777-57A0122 
RB,'' for this AD, the exceptions specified in paragraph (h)(6)(i) 
through (v) of this AD apply to that referenced service information 
(``the original issue of Boeing Alert Requirements Bulletin 777-
57A0122 RB'') and the corrections identified in Boeing Multi 
Operator Message MOM-MOM-24-0054-01B, dated January 26, 2024, apply 
to that referenced service information.
    (i) Where the ``Compliance'' paragraph of the referenced service 
information identifies ``Tables 1 through 50,'' the correct number 
of tables is Tables 1 through 54.
    (ii) The referenced service information does not specify the 
application of cap seals to underwing longeron fasteners, fastener 
heads, and fastener threads and collars for the airplane groups and 
configurations identified in paragraphs (h)(6)(ii)(A) through (D) of 
this AD. For those airplane groups and configurations, the 
application of a cap seal to the underwing longeron fasteners at the 
locations identified in Figures 81 and 144 is required during 
installation of the underwing longeron and must be applied using a 
cap sealing procedure with thickness greater than or equal to the 
dimensions given in Figure 1 to paragraph (h)(3) of this AD.
    (A) Groups 7 and 8, Configurations 5 through 8, on the left 
side.
    (B) Group 9, Configurations 1 and 2, on the left side.
    (C) Groups 7 and 8, Configurations 2, 6, 10, and 14, on the 
right side.
    (D) Group 9, Configurations 1 and 3, on the right side.
    (iii) For any inspection that may require the removal of 
fastener cap seals, if the cap seal is removed, a cap seal of BMS 5-
45 sealant must be reapplied using a cap sealing procedure with a 
thickness equal to or greater than the dimensions specified in 
Figure 1 to paragraph (h)(3) of this AD before further flight after 
completion of the inspection.
    (iv) The referenced service information does not require the 
restoration of any sealant removed to accomplish high frequency eddy 
current and ultrasonic inspections external to the fuel tank in 
Figures 1, 7, 11, and 17. Following completion of any inspection 
required by those figures, replacement of the sealant described in 
paragraph (h)(6)(iv)(A) and repair of the sealant described in 
paragraph (h)(6)(iv)(B) of this AD, as applicable, is required.
    (A) Where any sealant was removed from the heads of fasteners, 
before further flight, cover and fillet seal the fasteners using BMS 
5-45 or BMS 5-95 sealant.
    Note 3 to paragraph (h)(6)(iv)(A): Guidance for accomplishing 
the actions required by paragraph (h)(6)(iv)(A) of this AD can be 
found in the Boeing Standard Overhaul Practices Manual (SOPM) 
section 20-50-19.
    (B) Following any sealant replacement required by paragraph 
(h)(6)(iv)(A) of this AD, where any secondary fuel barrier coating 
was removed, before further flight, repair the secondary fuel 
barrier using BMS 5-81 sealant.
    Note 4 to paragraph (h)(6)(iv)(B): Guidance for accomplishing 
the actions required by paragraph (h)(6)(iv)(B) of this AD can be 
found in Boeing Model 777 Aircraft Maintenance Manual (AMM) section 
28-11-00.
    (v) The Effectivity of the referenced service information does 
not include Boeing Model 777F series airplanes having line numbers 
1713, 1717, 1720, and 1724 through 1742 inclusive. For those 
airplanes the applicable actions for Group 6 must be done.

(i) Terminating Action for AD 2023-17-14

    For airplanes on which a front spar lower chord modification 
specified in Boeing Alert Requirements Bulletin 777-57A0122 RB is 
done as part of the requirements of paragraphs (g) and (h)(6) of 
this AD, the modification requirements of paragraph (g) of AD 2023-
17-14 are terminated for the applicable side (left or right) on 
which the modification was done.

(j) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, AIR-520, Continued Operational Safety Branch, 
FAA, has the

[[Page 21450]]

authority to approve AMOCs for this AD, if requested using the 
procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, 
send your request to your principal inspector or responsible Flight 
Standards Office, as appropriate. If sending information directly to 
the manager of the Continued Operational Safety Branch, send it to 
the attention of the person identified in paragraph (k)(1) of this 
AD. Information may be emailed to: [email protected].
    (2) Before using any approved AMOC, notify your appropriate 
principal inspector, or lacking a principal inspector, the manager 
of the responsible Flight Standards Office.
    (3) An AMOC that provides an acceptable level of safety may be 
used for any repair, modification, or alteration required by this AD 
if it is approved by The Boeing Company Organization Designation 
Authorization (ODA) that has been authorized by the Manager, AIR-
520, Continued Operational Safety 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.

(k) Related Information

    (1) For more information about this AD, contact Luis Cortez-
Muniz, Aviation Safety Engineer, FAA, 2200 South 216th St., Des 
Moines, WA 98198; phone: 206-231-3958; email: [email protected].
    (2) Service information identified in this AD that is not 
incorporated by reference is available at the addresses specified in 
paragraph (l)(3) of this AD.

(l) 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 777-53A0100 RB, dated 
March 16, 2023.
    (ii) Boeing Multi Operator Message MOM-MOM-24-0054-01B, dated 
January 26, 2024.
    (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; telephone 562-797-1717; website myboeingfleet.com.
    (4) 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.
    (5) You may view this material at the National Archives and 
Records Administration (NARA). For information on the availability 
of this material at NARA, visit www.archives.gov/federal-register/cfr/ibr-locations or email [email protected].

    Issued on March 22, 2024.
Victor Wicklund,
Deputy Director, Compliance & Airworthiness Division, Aircraft 
Certification Service.
[FR Doc. 2024-06522 Filed 3-27-24; 8:45 am]
BILLING CODE 4910-13-P