[Federal Register Volume 87, Number 130 (Friday, July 8, 2022)]
[Rules and Regulations]
[Pages 40710-40714]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2022-14490]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2021-1073; Project Identifier AD-2021-01252-T; 
Amendment 39-22090; AD 2022-13-04]
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) 2017-24-
10, which applied to certain The Boeing Company Model 757-200, -200PF, 
and -300 series airplanes. AD 2017-24-10 required repetitive 
inspections for any cracking of a certain fuselage frame inner chord; 
identification of the material of a certain fuselage frame inner chord 
for certain airplanes; and applicable corrective actions. This AD was 
prompted by reports of cracking found at a certain fuselage frame inner 
chord. This AD retains the requirements of AD 2017-24-10, adds 
airplanes, and requires new inspection types in certain areas, an 
expanded inspection area, additional inspections, and applicable 
corrective actions. The FAA is issuing this AD to address the unsafe 
condition on these products.

DATES: This AD is effective August 12, 2022.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of August 12, 
2022.
    The Director of the Federal Register approved the incorporation by 
reference of a certain other publication listed in this AD as of 
January 9, 2018 (82 FR 57343, December 5, 2017).

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-2021-1073.

Examining the AD Docket

    You may examine the AD docket at https://www.regulations.gov by 
searching for and locating Docket No. FAA-2021-1073; 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: Peter Jarzomb, Aerospace Engineer, 
Airframe Section, FAA, Los Angeles ACO Branch, 3960 Paramount 
Boulevard, Lakewood, CA 90712-4137; phone: 562-627-5234; email: 
[email protected].

SUPPLEMENTARY INFORMATION:

Background

    The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 
CFR part 39 to supersede AD 2017-24-10, Amendment 39-19114 (82 FR 
57343, December 5, 2017) (AD 2017-24-10). AD 2017-24-10 applied to 
certain The Boeing Company Model 757-200, -200PF, and -300 series 
airplanes. The NPRM published in the Federal Register on January 21, 
2022 (87 FR 3246). The NPRM was prompted by reports of cracking found 
at the fuselage station (STA) 1380 frame inner chord and by reports of 
new crack findings outside of the AD 2017-24-10 inspection area, which 
the existing inspections will not detect. In the NPRM, the FAA proposed 
to continue to require repetitive inspections for any cracking of a 
certain fuselage frame inner chord; identification of the material of a 
certain fuselage frame inner chord for certain airplanes; and 
applicable corrective actions. The NPRM also proposed to add airplanes 
and require new inspection types in

[[Page 40711]]

certain areas, an expanded inspection area, additional inspections, and 
applicable corrective actions. The FAA is issuing this AD to detect and 
correct such cracks, which could result in rapid decompression of the 
airplane and the inability to sustain loads required for continued safe 
flight and landing.

Discussion of Final Airworthiness Directive

Comments

    The FAA received comments from seven commenters. The Airline Pilots 
Association, International (ALPA), United Airlines, and two additional 
commenters supported the NPRM without change.
    The FAA received additional comments from Aviation Partners Boeing 
(APB), Delta Airlines (DAL), and FedEx Express (FedEx). 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

    APB stated that the installation of winglets per Supplemental Type 
Certificate (STC) ST01518SE does not affect compliance with the 
mandated actions in the proposed rule.
    The FAA agrees with the commenter. A review of the STC holders 
determined that airplanes with their winglets installed do not affect 
compliance with the proposed actions. Paragraph (c) of the proposed AD 
has been redesignated as paragraph (c)(1) of this AD, and paragraph 
(c)(2) has been added to this AD to state that installation of STC 
ST01518SE does not affect the ability to accomplish the actions 
required by this AD. Therefore, for airplanes on which STC ST01518SE is 
installed, a ``change in product'' alternative method of compliance 
(AMOC) approval request is not necessary to comply with the 
requirements of 14 CFR 39.17.

Request for an Exception for a Certain STC

    FedEx noted that its fleet of Boeing Model 757-200 series airplanes 
was converted to a configuration similar to the Boeing Model 757-200SF 
per VT Mobile Aerospace Engineering (VT MAE) STC ST03562AT, and those 
airplanes are no longer configured as passenger airplanes. Per the VT 
MAE STC ST03562AT, certain areas of the airplane are not altered, but 
are subject to Boeing Model 757-200SF loads. The FAA infers that the 
certain areas the commenter referred to is the fuselage STA 1380 frame 
inner chord. As a result, FedEx requested the VT MAE STC ST03562AT be 
included as a new exception in paragraph (k) of this AD to the 
requirements of paragraph (j) of this AD, similar to Model 757-200 
Special Freighter STC ST00916WI-D, as specified in Boeing Alert 
Requirements Bulletin 757-53A0118 RB, dated October 22, 2021.
    The FAA agrees with the commenter for the reasons provided. 
Paragraph (k)(3) has been added to this AD to state that where Boeing 
Alert Requirements Bulletin 757-53A0118 RB, dated October 22, 2021, 
allows an approved web repair accomplished in accordance with 757-200 
SRM 53-00-07 Repair 4 for ``757-200 Special Freighter STC ST00916WI-D 
only,'' this AD also approves those repairs for VT MAE STC ST03562AT.

Request To Change Compliance Time

    FedEx requested that paragraphs (g), (h), and (i) of the proposed 
AD (retained from AD 2017-24-10) be retained only until the effective 
date of this final rule, at which point the new requirements of this 
AD, as specified in paragraphs (j), (k), and (l) of this AD would be 
the only requirements of this AD. FedEx pointed to the unsafe condition 
statement in paragraph (e) of the proposed AD as justification, 
emphasizing the phrase ``. . . new crack findings outside of the AD 
2017-24-10 inspection area, which the existing inspections will not 
detect.'' FedEx noted that the exception specified in paragraph (k)(1) 
of this AD would remain unchanged.
    The FAA does not agree with the commenter. This AD is issued to 
address new cracking that has been found outside of the inspection area 
of AD 2017-24-10, and that AD's inspections will not detect the new 
cracking. Operators that have performed the initial eddy current 
inspections required by AD 2017-24-10 need to continue to inspect 
affected airplanes at the applicable repetitive interval in order to 
maintain the damage tolerance capability of the affected structure. If 
the FAA were to not retain the requirements of AD 2017-24-10 until the 
terminating action required by paragraph (l) of this AD is performed, 
that would allow the affected airplanes to continue flying beyond the 
repetitive inspection interval. If those repetitive eddy current 
inspections are not performed, an undetected crack could result in the 
inability of a principal structural element to sustain limit loads, 
which could adversely affect the structural integrity of the airplane. 
No change has been made to this final rule.

Request for an Additional AMOC

    FedEx requested that paragraph (m)(4) of the proposed AD be updated 
to reflect the language in Notes (a) and (b) of Tables 1 and 2 of 
Boeing Alert Requirements Bulletin 757-53A0118 RB, dated October 22, 
2021, which FedEx believes should allow additional AMOCs. FedEx 
observed that paragraph (m)(4) of the proposed AD states that AMOCs 
approved previously for AD 2017-24-10 are not approved as AMOCs for 
this AD. In expressing its disagreement with that statement, FedEx 
observed that those Notes state that if any existing repair is found 
and meets either one of the conditions stated in the Notes, the repair 
is still approved and meets the requirements for accomplishing the 
action specified in Boeing Alert Requirements Bulletin 757-53A0118 RB, 
dated October 22, 2021. FedEx asserts that the referenced notes are 
governed by paragraph (j) of the proposed AD, and paragraph (k) of the 
proposed AD does not provide any exceptions for the referenced notes. 
In conclusion, FedEx asserted that paragraph (m)(4) of the proposed AD 
is in conflict with Notes (a) and (b) of Tables 1 and 2 of Boeing Alert 
Requirements Bulletin 757-53A0118 RB, dated October 22, 2021. As a 
result, FedEx requests that paragraph (m)(4) of the final rule be 
updated to reflect the language in the referenced notes.
    The FAA does not agree with the commenter. FedEx asserted that a 
repair that meets either one of the conditions stated in Notes (a) and 
(b) of Tables 1 and 2 of Boeing Alert Requirements Bulletin 757-53A0118 
RB, dated October 22, 2021, is approved and meets the requirements for 
accomplishing the actions specified in that service information. FedEx 
further asserts that such a repair is therefore in conflict with 
paragraph (m)(4) of the proposed AD. These assertions are incorrect. 
For airplanes with repairs that meet either one of the conditions 
stated in Notes (a) and (b) of Tables 1 and 2 of Boeing Alert 
Requirements Bulletin 757-53A0118 RB, dated October 22, 2021, the 
inspections specified in that service information are still required, 
but at a different inspection threshold than the threshold for 
airplanes that do not have an approved repair installed in the 
inspection area. Therefore, Notes (a) and (b) of Tables 1 and 2 of 
Boeing Alert Requirements Bulletin 757-53A0118 RB, dated October 22, 
2021, are not in conflict with paragraph (m)(4) of this AD. AMOCs 
previously approved for AD 2017-24-10 do not address the unsafe 
condition identified in this final rule (cracks initiating in the STA 
1380 frame web), and therefore cannot be approved as AMOCs for this 
final rule. If the existing AMOCs were to be

[[Page 40712]]

approved as AMOCs for this final rule, then the inspections specified 
in Boeing Alert Requirements Bulletin 757-53A0118 RB, dated October 22, 
2021, would not be required on airplanes with a previously approved 
AMOC. If these inspections are not accomplished, cracks initiating in 
the frame web could grow undetected, which could result in the 
inability of a principal structural element to sustain limit loads, 
which could adversely affect the structural integrity of the airplane. 
No change has been made to this final rule.

Request for a New Exception To Omit Reinstallation of the Guide Track 
Fitting as a Required for Compliance Action

    Delta requested that the FAA modify paragraph (k) of the proposed 
AD to include a new exception that omits Figure 6 from Boeing Alert 
Requirements Bulletin 757-53A0118 RB, dated October 22, 2021. Delta 
recognized that the proposed AD seeks to mitigate cracking at the 
fuselage STA 1380 frame inner chord by detecting and repairing such 
cracks as described in paragraph (e) of the proposed AD. However, Delta 
contends that reinstallation of the guide track fitting in accordance 
with Figure 6 of Boeing Alert Requirements Bulletin 757-53A0118 RB, 
dated October 22, 2021, does nothing to mitigate the unsafe condition 
and is a close access step. Open access steps in accordance with Boeing 
Alert Requirements Bulletin 757-53A0118 RB, dated October 22, 2021, 
including removal of the guide track fitting in Figure 2, and other 
close access steps in accordance with Part 2, are not contained in 
Boeing Alert Requirements Bulletin 757-53A0118 RB, dated October 22, 
2021.
    The FAA does not agree with the commenter. The root cause for the 
cracking in the STA 1380 frame inner chord and web under the roller 
guide track fitting is attributed to the out-of-plane bending stress 
induced from a mis-rigging condition of the No. 2 cargo door, which 
allows the roller pin on the lower cargo door to contact the roller 
guide track fitting. Figure 6 provides instructions on how to properly 
re-rig the roller guide track fitting and the No. 2 cargo door to 
prevent the contact between the roller pin and the roller guide track 
fitting, eliminating the out-of-plane bending loads on the STA 1380 
frame. No change has been made to this final rule.

Conclusion

    The FAA reviewed the relevant data, considered any comments 
received, and determined that air safety requires adopting this AD as 
proposed. Except for minor editorial changes, and any other changes 
described previously, this AD is adopted as proposed in the NPRM. None 
of the changes will increase the economic burden on any operator.

Related Service Information Under 1 CFR Part 51

    The FAA reviewed Boeing Alert Requirements Bulletin 757-53A0118 RB, 
dated October 22, 2021. This service information specifies procedures 
for a general visual inspection or a maintenance records check of the 
STA 1380 frame for any repair, and repetitive surface high frequency 
eddy current (HFEC) inspections of the STA 1380 frame inner chord and 
frame web for any cracking, repetitive sub-surface low frequency eddy 
current (LFEC) inspections of the STA 1380 frame inner chord for any 
cracking, and applicable corrective actions. Corrective actions include 
repair.
    This AD also requires Boeing Alert Service Bulletin 757-53A0101, 
dated November 8, 2016, which the Director of the Federal Register 
approved for incorporation by reference as of January 9, 2018 (82 FR 
57343, December 5, 2017).
    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 affect 477 airplanes of U.S. 
registry. The FAA estimates the following costs to comply with this AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                Cost on U.S.
              Action                     Labor cost       Parts cost    Cost per product          operators
----------------------------------------------------------------------------------------------------------------
Surface HFEC inspection (retained   5 work-hours x $85            $0  $425 per inspection   $202,725 per
 actions from AD 2017-24-10).        per hour = $425 per               cycle.                inspection cycle.
                                     inspection cycle.
Identify the material (retained     Up to 2 work-hours x           0  Up to $170..........  Up to $81,090.
 actions from AD 2017-24-10).        $85 per hour = $170.
General visual inspection (new      6 work-hours x $85             0  $510................  $243,270.
 proposed action).                   per hour = $510.
Surface frame inner chord HFEC      Up to 10 work-hours            0  Up to $850 per        Up to $405,450 per
 inspection (new proposed action).   x $85 per hour =                  inspection cycle.     inspection cycle.
                                     $850 per inspection
                                     cycle.
Sub-surface frame inner chord LFEC  Up to 6 work-hours x           0  Up to $510 per        Up to $243,270 per
 inspection (new proposed action).   $85 per hour = $510               inspection cycle.     inspection cycle.
                                     per inspection
                                     cycle.
Surface HFEC frame web inspection   Up to 6 work-hours x           0  Up to $510 per        Up to $243,270 per
 (new proposed action).              $85 per hour = $510               inspection cycle.     inspection cycle.
                                     per inspection
                                     cycle.
----------------------------------------------------------------------------------------------------------------

    The FAA has received no definitive data on which to base the cost 
estimates for the on-condition repairs specified in this AD.

Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to 
issue rules on aviation safety. Subtitle I, section 106, describes the 
authority of the FAA Administrator. Subtitle VII: Aviation Programs, 
describes in more detail the scope of the Agency's authority.
    The FAA is issuing this rulemaking under the authority described in 
Subtitle VII, Part A, Subpart III, Section 44701: General requirements. 
Under that section, Congress charges the FAA with promoting safe flight 
of civil aircraft in air commerce by prescribing regulations for 
practices, methods, and procedures the Administrator finds necessary 
for safety in air commerce. This regulation is within the scope of that 
authority because it addresses an unsafe condition that is likely to 
exist or develop on products identified in this rulemaking action.

Regulatory Findings

    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

[[Page 40713]]

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.


Sec.  39.13  [Amended]

0
2. The FAA amends Sec.  39.13 by:
0
a. Removing Airworthiness Directive (AD) 2017-24-10, Amendment 39-19114 
(82 FR 57343, December 5, 2017); and
0
b. Adding the following new AD:

2022-13-04 The Boeing Company: Amendment 39-22090; Docket No. FAA-
2021-1073; Project Identifier AD-2021-01252-T.

(a) Effective Date

    This airworthiness directive (AD) is effective August 12, 2022.

(b) Affected ADs

    This AD replaces AD 2017-24-10, Amendment 39-19114 (82 FR 57343, 
December 5, 2017) (AD 2017-24-10).

(c) Applicability

    (1) This AD applies to all The Boeing Company Model 757-200, -
200PF, -200CB, and -300 series airplanes, certificated in any 
category.
    (2) Installation of Supplemental Type Certificate (STC) 
ST01518SE does not affect the ability to accomplish the actions 
required by this AD. Therefore, for airplanes on which STC ST01518SE 
is installed, a ``change in product'' alternative method of 
compliance (AMOC) approval request is not necessary to comply with 
the requirements of 14 CFR 39.17.

(d) Subject

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

(e) Unsafe Condition

    This AD was prompted by reports of cracking found at the 
fuselage station (STA) 1380 frame inner chord and by reports of new 
crack findings outside of the AD 2017-24-10 inspection area, which 
the existing inspections will not detect. The FAA is issuing this AD 
to detect and correct such cracks, which could result in rapid 
decompression of the airplane and the inability to sustain loads 
required for continued safe flight and landing.

(f) Compliance

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

(g) Retained Inspection for Group 1 Airplanes, With No Changes

    This paragraph restates the requirements of paragraph (g) of AD 
2017-24-10, with no changes. For Group 1 airplanes as identified in 
Boeing Alert Service Bulletin 757-53A0101, dated November 8, 2016: 
At the applicable time specified in paragraph 1.E., ``Compliance,'' 
of Boeing Alert Service Bulletin 757-53A0101, dated November 8, 
2016; except as specified in paragraph (i)(1) of this AD, do a 
surface high frequency eddy current (HFEC) inspection for any 
cracking of the fuselage STA 1380 frame inner chord, and do all 
applicable corrective actions, in accordance with the Accomplishment 
Instructions of Boeing Alert Service Bulletin 757-53A0101, dated 
November 8, 2016; except as specified in paragraph (i)(2) of this 
AD. Do all applicable corrective actions before further flight. 
Repeat the surface HFEC inspection, thereafter, at the times 
specified in paragraph 1.E., ``Compliance,'' of Boeing Alert Service 
Bulletin 757-53A0101, dated November 8, 2016.

(h) Retained Inspection for Group 2 Airplanes, With No Changes

    This paragraph restates the requirements of paragraph (h) of AD 
2017-24-10, with no changes. For Group 2 airplanes as identified in 
Boeing Alert Service Bulletin 757-53A0101, dated November 8, 2016: 
At the applicable time specified in paragraph 1.E., ``Compliance,'' 
of Boeing Alert Service Bulletin 757-53A0101, dated November 8, 
2016, except as specified in paragraph (i)(1) of this AD, identify 
the material of the fuselage STA 1380 frame inner chord, in 
accordance with the Accomplishment Instructions of Boeing Alert 
Service Bulletin 757-53A0101, dated November 8, 2016.
    (1) If the fuselage STA 1380 frame inner chord material 2024-T42 
aluminum alloy is found during any identification required by 
paragraph (h) of this AD: No further action is required by this 
paragraph for that airplane.
    (2) If the fuselage STA 1380 frame inner chord material 7075-T73 
aluminum alloy is found during any identification required by the 
introductory text of paragraph (h) of this AD: Before further 
flight, do a surface HFEC inspection for any cracking of the 
fuselage STA 1380 frame inner chord, and do all applicable 
corrective actions, in accordance with the Accomplishment 
Instructions of Boeing Alert Service Bulletin 757-53A0101, dated 
November 8, 2016; except as specified in paragraph (i)(2) of this 
AD. Do all applicable corrective actions before further flight. 
Repeat the surface HFEC inspection thereafter at the times specified 
in paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 
757-53A0101, dated November 8, 2016.

(i) Retained Exceptions to the Service Information, With No Changes

    This paragraph restates the requirements of paragraph (i) of AD 
2017-24-10, with no changes.
    (1) Where Boeing Alert Service Bulletin 757-53A0101, dated 
November 8, 2016, specifies a compliance time ``after the original 
issue date of this service bulletin,'' this AD requires compliance 
within the specified compliance time after January 9, 2018 (the 
effective date of AD 2017-24-10).
    (2) Where Boeing Alert Service Bulletin 757-53A0101, dated 
November 8, 2016, specifies to contact Boeing for appropriate action 
and identifies that action as ``RC'' (Required for Compliance): 
Before further flight, repair the crack using a method approved in 
accordance with the procedures specified in paragraph (m) of this 
AD.

(j) New Required Actions

    Except as specified by paragraph (k) of this AD: At the 
applicable times specified in the ``Compliance'' paragraph of Boeing 
Alert Requirements Bulletin 757-53A0118 RB, dated October 22, 2021, 
do all applicable actions identified in, and in accordance with, the 
Accomplishment Instructions of Boeing Alert Requirements Bulletin 
757-53A0118 RB, dated October 22, 2021.
    Note 1 to paragraph (j): Guidance for accomplishing the actions 
required by this AD can be found in Boeing Alert Service Bulletin 
757-53A0118, dated October 22, 2021, which is referred to in Boeing 
Alert Requirements Bulletin 757-53A0118 RB, dated October 22, 2021.

(k) New Exceptions to Service Information Specifications

    (1) Where the Compliance Time column of the tables in the 
``Compliance'' paragraph of Boeing Alert Requirements Bulletin 757-
53A0118 RB, dated October 22, 2021, uses the phrase ``the original 
issue date of the Requirements Bulletin 757-53A0118 RB,'' this AD 
requires using ``the effective date of this AD.''
    (2) Where Boeing Alert Requirements Bulletin 757-53A0118 RB, 
dated October 22, 2021, specifies contacting Boeing for repair 
instructions or for alternative inspections: This AD requires doing 
the repair, or doing the alternative inspections and applicable on-
condition actions using a method approved in accordance with the 
procedures specified in paragraph (m) of this AD.
    (3) Where Boeing Alert Requirements Bulletin 757-53A0118 RB, 
dated October 22, 2021, states that 757-200 SRM 53-00-07 Repair 4 is 
for ``757-200 Special Freighter STC ST00916WI-D only,'' for this AD, 
757-200 SRM 53-00-07 Repair 4 is for ``757-200 Special Freighter STC 
ST00916WI-D and VT Mobile Aerospace Engineering (VT MAE) 
Supplemental Type Certificate (STC) ST03562AT only.''

[[Page 40714]]

(l) Terminating Action for Certain Inspections

    Accomplishment of the applicable initial inspections and 
corrective actions specified in the Accomplishment Instructions of 
Boeing Alert Requirements Bulletin 757-53A0118 RB, dated October 22, 
2021, terminates the inspections required by paragraphs (g) and (h) 
of this AD.

(m) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, Los Angeles ACO Branch, FAA, has the authority 
to approve AMOCs for this AD, if requested using the procedures 
found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your 
request to your principal inspector or responsible Flight Standards 
Office, as appropriate. If sending information directly to the 
manager of the certification office, send it to the attention of the 
person identified in paragraph (n) 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, Los 
Angeles ACO Branch, FAA, to make those findings. To be approved, the 
repair method, modification deviation, or alteration deviation must 
meet the certification basis of the airplane, and the approval must 
specifically refer to this AD.
    (4) AMOCs approved previously for AD 2017-24-10 are not approved 
as AMOCs with this AD.
    (5) Except as specified by paragraph (i) of this AD: For service 
information that contains steps that are labeled as Required for 
Compliance (RC), the provisions of paragraphs (m)(5)(i) and (ii) of 
this AD apply.
    (i) The steps labeled as RC, including substeps under an RC step 
and any figures identified in an RC step, must be done to comply 
with the AD. If a step or substep is labeled ``RC Exempt,'' then the 
RC requirement is removed from that step or substep. An AMOC is 
required for any deviations to RC steps, including substeps and 
identified figures.
    (ii) Steps not labeled as RC may be deviated from using accepted 
methods in accordance with the operator's maintenance or inspection 
program without obtaining approval of an AMOC, provided the RC 
steps, including substeps and identified figures, can still be done 
as specified, and the airplane can be put back in an airworthy 
condition.

(n) Related Information

    For more information about this AD, contact Peter Jarzomb, 
Aerospace Engineer, Airframe Section, FAA, Los Angeles ACO Branch, 
3960 Paramount Boulevard, Lakewood, CA 90712-4137; phone: 562-627-
5234; email: [email protected].

(o) 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 this AD specifies otherwise.
    (3) The following service information was approved for IBR on 
August 12, 2022.
    (i) Boeing Alert Requirements Bulletin 757-53A0118 RB, dated 
October 22, 2021.
    (ii) [Reserved]
    (4) The following service information was approved for IBR on 
January 9, 2018 (82 FR 57343, December 5, 2017).
    (i) Boeing Alert Service Bulletin 757-53A0101, dated November 8, 
2016.
    (ii) [Reserved]
    (5) For service information identified in this AD, contact 
Boeing Commercial Airplanes, Attention: Contractual & Data Services 
(C&DS), 2600 Westminster Blvd., MC 110-SK57, Seal Beach, CA 90740-
5600; telephone 562-797-1717; internet https://www.myboeingfleet.com.
    (6) 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.
    (7) 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 [email protected], or go to: https://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued on June 13, 2022.
Christina Underwood,
Acting Director, Compliance & Airworthiness Division, Aircraft 
Certification Service.
[FR Doc. 2022-14490 Filed 7-7-22; 8:45 am]
BILLING CODE 4910-13-P


