[Federal Register Volume 87, Number 147 (Tuesday, August 2, 2022)]
[Rules and Regulations]
[Pages 47093-47097]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2022-16605]



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 Rules and Regulations
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  Federal Register / Vol. 87, No. 147 / Tuesday, August 2, 2022 / Rules 
and Regulations  

[[Page 47093]]



DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2022-0884; Project Identifier AD-2022-00749-T; 
Amendment 39-22129; AD 2022-15-09]
RIN 2120-AA64


Airworthiness Directives; The Boeing Company Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule; request for comments.

-----------------------------------------------------------------------

SUMMARY: The FAA is superseding Airworthiness Directive (AD) 2019-23-
06, which applied to certain The Boeing Company Model 757-200, -200CB, 
and -300 series airplanes. AD 2019-23-06 required, depending on 
configuration, a general visual inspection for any previous repair, 
such as any reinforcing repair or local frame replacement repair, 
repetitive open hole high frequency eddy current (HFEC) inspections for 
any crack of the fuselage frame web fastener holes, on the left and 
right side of the airplane, and applicable on-condition actions. This 
AD was prompted by a determination that certain compliance times must 
be reduced. This AD requires the actions specified in AD 2019-23-06 
with reduced compliances times for certain actions. The FAA is issuing 
this AD to address the unsafe condition on these products.

DATES: This AD is effective August 17, 2022.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of August 17, 
2022.
    The Director of the Federal Register approved the incorporation by 
reference of certain other publications listed in this AD as of January 
13, 2020 (84 FR 67179, December 9, 2019).
    The FAA must receive comments on this AD by September 16, 2022.

ADDRESSES: You may send comments, using the procedures found in 14 CFR 
11.43 and 11.45, by any of the following methods:
     Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments.
     Fax: 202-493-2251.
     Mail: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE, Washington, DC 20590.
     Hand Delivery: Deliver to Mail address above between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
    For Boeing service information identified in this 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.
    For Aviation Partners Boeing service information identified in this 
final rule, contact Aviation Partners Boeing, 2811 South 102nd St., 
Suite 200, Seattle, WA 98168; phone: 206-830-7699; fax: 206-767-0535; 
email: [email protected]; internet: https://www.aviationpartnersboeing.com.x
    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-2022-
0884.

Examining the AD Docket

    You may examine the AD docket at https://www.regulations.gov by 
searching for and locating Docket No. FAA-2022-0884; 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 street address for the 
Docket Operations is listed above.

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 AD 2019-23-06, Amendment 39-19800 (84 FR 67179, 
December 9, 2019) (AD 2019-23-06), for certain The Boeing Company Model 
757-200, -200CB, and -300 series airplanes. AD 2019-23-06 required, 
depending on configuration, a general visual inspection for any 
previous repair, such as any reinforcing repair or local frame 
replacement repair, repetitive open HFEC inspections for any crack of 
the fuselage frame web fastener holes, on the left and right side of 
the airplane, and applicable on-condition actions. AD 2019-23-06 was 
prompted by reports of cracks initiating in the fuselage frame web at 
body station (STA) 1640. The FAA issued AD 2019-23-06 to address cracks 
initiating in the fuselage frame web at STA 1640, which, if not 
detected and corrected, could result in reduced structural integrity of 
the airplane.

Actions Since AD 2019-23-06 Was Issued

    Since the FAA issued AD 2019-23-06, severed fuselage frames were 
detected on three Model 757-200 airplanes before the 5,600 flight 
cycles compliance time allowed in AD 2019-23-06 for airplanes that have 
accomplished certain inspections. These incidents were detected on 
airplanes that had accumulated between 2,579 flight cycles and 3,311 
flight cycles since accomplishing those inspections with no crack 
findings. Boeing investigated the compliance times for the other 
affected airplane models and determined that the inspection interval 
for Model 757-200 airplanes converted to a special freighter (SF) 
configurations is also inadequate to detect cracks before they reach a 
critical length. Based on these findings, it was determined that 
certain compliance times must be revised to address the unsafe 
condition.
    For airplanes on which Aviation Partners Boeing (APB) blended or 
scimitar blended winglets are installed in accordance with Supplemental 
Type Certificate (STC) ST01518SE, APB and Boeing determined that the 
compliance times must also be reduced for the open HFEC inspection of 
the STA 1640 fuselage frame web fastener holes common to the S-14L and 
S-14R intercostal tee clip. In addition, it was determined that 
airplanes that have

[[Page 47094]]

been converted from a passenger to freighter configuration using VT 
Mobile Aerospace Engineering (MAE) Inc. STC ST03562AT must use the 
reduced compliance times because the configuration is identical to 
airplanes converted to The Boeing Company Model 757-200 special 
freighter airplanes using Boeing STC ST00916WI-D.

FAA's Determination

    The FAA is issuing this AD because the agency has determined the 
unsafe condition described previously is likely to exist or develop in 
other products of the same type design.

Related Service Information Under 1 CFR Part 51

    The FAA reviewed Boeing Alert Requirements Bulletin 757-53A0112 RB, 
Revision 1, dated June 17, 2022. This service information specifies 
procedures for, depending on configuration, a general visual inspection 
for any previous repair, such as any reinforcing repair or local frame 
replacement repair, repetitive open hole HFEC inspections for any crack 
of the fuselage frame web fastener holes, on the left and right side of 
the airplane, and applicable on-condition actions. On-condition actions 
include installation of fasteners, oversizing of fastener holes, and 
repair. These documents are distinct since they apply to different 
airplane models in different configurations.
    This AD also requires Aviation Partners Boeing Alert Service 
Bulletin AP757-53-002, Revision 3 dated August 14, 2019; and Boeing 
Alert Requirements Bulletin 757-53A0112 RB, dated November 16, 2018; 
which the Director of the Federal Register approved for incorporation 
by reference as of January 13, 2020 (84 FR 67179, December 9, 2019).
    This service information is reasonably available because the 
interested parties have access to it through their normal course of 
business or by the means identified in the ADDRESSES section.

AD Requirements

    Although this AD does not explicitly restate the requirements of AD 
2019-23-06, this AD retains all of the requirements of AD 2019-23-06. 
Those requirements are referenced in the service information identified 
previously, which, in turn, is referenced in paragraph (g) of this AD. 
This AD reduces certain compliance times for certain actions. This AD 
requires accomplishment of the actions identified in the service 
information described previously, except for any differences identified 
as exceptions in the regulatory text of this AD.
    For information on the procedures and compliance times, see Boeing 
Alert Requirements Bulletin 757-53A0112 RB, Revision 1, dated June 17, 
2022, at https://www.regulations.gov by searching for and locating 
Docket No. FAA-2022-0884.

Justification for Immediate Adoption and Determination of the Effective 
Date

    Section 553(b)(3)(B) of the Administrative Procedure Act (APA) (5 
U.S.C. 551 et seq.) authorizes agencies to dispense with notice and 
comment procedures for rules when the agency, for ``good cause,'' finds 
that those procedures are ``impracticable, unnecessary, or contrary to 
the public interest.'' Under this section, an agency, upon finding good 
cause, may issue a final rule without providing notice and seeking 
comment prior to issuance. Further, section 553(d) of the APA 
authorizes agencies to make rules effective in less than thirty days, 
upon a finding of good cause.
    An unsafe condition exists that requires the immediate adoption of 
this AD without providing an opportunity for public comments prior to 
adoption. The FAA has found that the risk to the flying public 
justifies forgoing notice and comment prior to adoption of this rule 
because the FAA received reports of severed fuselage frames at STA 1640 
detected on airplanes prior to the 5,600 flight cycles compliance time 
allowed in AD 2019-23-06 for airplanes that have accomplished certain 
inspections. Cracks initiating in the fuselage frame web at STA 1640, 
if not detected and corrected, could result in reduced structural 
integrity of the airplane and loss of controllability of the airplane. 
Furthermore, failure of the No. 4 passenger door surround structure 
(frame) at STA 1640 due to cracks could lead to explosive 
decompression. Accordingly, notice and opportunity for prior public 
comment are impracticable and contrary to the public interest pursuant 
to 5 U.S.C. 553(b)(3)(B).
    In addition, the FAA finds that good cause exists pursuant to 5 
U.S.C. 553(d) for making this amendment effective in less than 30 days, 
for the same reasons the FAA found good cause to forgo notice and 
comment.

Comments Invited

    The FAA invites you to send any written data, views, or arguments 
about this final rule. Send your comments to an address listed under 
ADDRESSES. Include ``Docket No. FAA-2022-0884 and Project Identifier 
AD-2022-00749-T'' at the beginning of your comments. The most helpful 
comments reference a specific portion of the final rule, 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 final rule because of those comments.
    Except for Confidential Business Information (CBI) as described in 
the following paragraph, and other information as described in 14 CFR 
11.35, the FAA will post all comments received, without change, to 
https://www.regulations.gov, including any personal information you 
provide. The agency will also post a report summarizing each 
substantive verbal contact received about this final rule.

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 AD 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 AD, 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 AD. Submissions containing CBI should be sent to 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]. Any commentary that the FAA 
receives that is not specifically designated as CBI will be placed in 
the public docket for this rulemaking.

Regulatory Flexibility Act

    The requirements of the Regulatory Flexibility Act (RFA) do not 
apply when an agency finds good cause pursuant to 5 U.S.C. 553 to adopt 
a rule without prior notice and comment. Because the FAA has determined 
that it has good cause to adopt this rule without notice and comment, 
RFA analysis is not required.

Costs of Compliance

    The FAA estimates that this AD affects 419 airplanes of U.S. 
registry. The FAA estimates the following costs to comply with this AD:

[[Page 47095]]



                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                 Cost on U.S.
              Action                    Labor cost        Parts cost      Cost per product        operators
----------------------------------------------------------------------------------------------------------------
General Visual Inspection          1 work-hours x $85               $0  $85................  $35,615.
 (retained actions from AD 2019-    per hour = $85.
 23-06).
Open Hole HFEC Inspection          35 work-hours x $85               0  $2,975 per           $1,246,525 per
 (retained actions from AD 2019-    per hour = $2,975                    inspection cycle.    inspection cycle.
 23-06).                            per inspection
                                    cycle.
----------------------------------------------------------------------------------------------------------------

    The FAA estimates the following costs to do any necessary 
installation of fasteners and oversizing of fastener holes that would 
be required based on the results of the inspection. The FAA has no way 
of determining the number of aircraft that might need these 
installations:

                                               On-Condition Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                     Cost per
                    Action                                 Labor cost               Parts cost        product
----------------------------------------------------------------------------------------------------------------
Installation of fasteners and oversizing of     1 work-hour x $85 per hour = $85              $0             $85
 fastener holes.
----------------------------------------------------------------------------------------------------------------

    The FAA has received no definitive data on which to base the cost 
estimates for the repairs specified in this AD.
    The reduced compliance times specified in this AD add no additional 
economic burden.

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, and
    (2) Will not affect intrastate aviation in Alaska.

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) 2019-23-06, Amendment 39-19800 
(84 FR 67179, December 9, 2019); and
0
b. Adding the following new AD:

2022-15-09 The Boeing Company: Amendment 39-22129; Docket No. FAA-
2022-0884; Project Identifier AD-2022-00749-T.

(a) Effective Date

    This airworthiness directive (AD) is effective August 17, 2022.

(b) Affected ADs

    This AD replaces AD 2019-23-06, Amendment 39-19800 (84 FR 67179, 
December 9, 2019) (AD 2019-23-06).

(c) Applicability

    This AD applies to The Boeing Company Model 757-200, -200CB, and 
-300 series airplanes, certificated in any category, as identified 
in Boeing Alert Requirements Bulletin 757-53A0112 RB, Revision 1, 
dated June 17, 2022.

(d) Subject

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

(e) Unsafe Condition

    This AD was prompted by reports of cracks initiating in the 
fuselage frame web at body station (STA) 1640 and a determination 
that certain compliance times must be reduced due to severed 
fuselage frames reported at earlier flight cycles. The FAA is 
issuing this AD to address cracks initiating in the fuselage frame 
web at STA 1640, which, if not detected and corrected, could result 
in reduced structural integrity of the airplane and loss of 
controllability of the airplane. Furthermore, failure of the No. 4 
passenger door surround structure (frame) at STA 1640 due to cracks 
could lead to explosive decompression.

(f) Compliance

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

(g) Required Actions

    (1) For all airplanes except those identified in paragraphs 
(g)(2) through (4) of this AD: Except as specified by paragraph (h) 
of this AD, at the applicable times specified in the ``Compliance'' 
paragraph of Boeing Alert Requirements Bulletin 757-53A0112 RB, 
Revision 1, dated June 17, 2022, do all applicable actions 
identified in, and in accordance with, the Accomplishment 
Instructions of Boeing Alert Requirements Bulletin 757-53A0112 RB, 
Revision 1, dated June 17, 2022.
    Note 1 to paragraph (g): Guidance for accomplishing the actions 
required by this AD can be found in Boeing Alert Service Bulletin 
757-53A0112, Revision 1, dated June 17, 2022, which is referred to 
in Boeing Alert Requirements Bulletin 757-53A0112 RB, Revision 1, 
dated June 17, 2022.
    (2) Except as specified by paragraph (h) of this AD: For 
airplanes on which Aviation Partners Boeing blended or scimitar 
blended winglets are installed in accordance with Supplemental Type 
Certificate (STC) ST01518SE, at the applicable times specified

[[Page 47096]]

in paragraph 1.E., ``Compliance'' of Aviation Partners Boeing Alert 
Service Bulletin AP757-53-002, Revision 3, dated August 14, 2019, do 
all applicable actions identified in, and in accordance with, the 
Accomplishment Instructions of Boeing Alert Requirements Bulletin 
757-53A0112 RB, dated November 16, 2018.
    (3) Except as specified by paragraph (h) of this AD: For Group 1 
airplanes that have been converted from a passenger to freighter 
configuration using VT Mobile Aerospace Engineering (MAE) Inc. STC 
ST03562AT, at the applicable times specified for Group 2 airplanes 
in the ``Compliance'' paragraph of Boeing Alert Requirements 
Bulletin 757-53A0112 RB, Revision 1, dated June 17, 2022, do all 
applicable Group 2 actions, as identified in, and in accordance 
with, the Accomplishment Instructions of Boeing Alert Requirements 
Bulletin 757-53A0112 RB, Revision 1, dated June 17, 2022.
    (4) Except as specified by paragraph (h) of this AD: For Group 4 
airplanes that have been converted from a passenger to freighter 
configuration using VT MAE Inc. STC ST03562AT, at the applicable 
times specified for Group 5 airplanes in the ``Compliance'' 
paragraph of Boeing Alert Requirements Bulletin 757-53A0112 RB, 
Revision 1, dated June 17, 2022, do all applicable Group 5 actions 
as identified in, and in accordance with, the Accomplishment 
Instructions of Boeing Alert Requirements Bulletin 757-53A0112 RB, 
Revision 1, dated June 17, 2022.

(h) Exceptions to Service Information Specifications

    (1) Where the Condition and Compliance Time columns of the 
tables in the ``Compliance'' paragraph of Boeing Alert Requirements 
Bulletin 757-53A0112 RB, Revision 1, dated June 17, 2022, use the 
phrase ``the original issue date of Requirements Bulletin 757-
53A0112 RB,'' this AD requires using ``January 13, 2020 (the 
effective date of AD 2019-23-06).''
    (2) Where the Condition and Compliance Time columns of the 
tables in the ``Compliance'' paragraph of Boeing Alert Requirements 
Bulletin 757-53A0112 RB, Revision 1, dated June 17, 2022, use the 
phrase ``the Revision 1 date of Requirements Bulletin 757-53A0112 
RB,'' this AD requires using ``the effective date of this AD.''
    (3) Where Boeing Alert Requirements Bulletin 757-53A0112 RB, 
Revision 1, dated June 17, 2022, 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 (j) of this 
AD.
    (4) Where the Condition and Compliance Time columns of the 
tables in the ``Compliance'' paragraph of Aviation Partners Boeing 
Alert Service Bulletin AP757-53-002, Revision 3, dated August 14, 
2019, use the phrase ``the original issue date of this service 
bulletin,'' this AD requires using ``January 13, 2020 (the effective 
date of AD 2019-23-06).''
    (5) Where Aviation Partners Boeing Alert Service Bulletin AP757-
53-002, Revision 3, dated August 14, 2019, 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 (j) of this 
AD.
    (6) For Group 1 airplanes, as identified in Aviation Partners 
Boeing Alert Service Bulletin AP757-53-002, Revision 3, dated August 
14, 2019, with less than 34,500 total flight cycles as of the 
effective date of this AD that have accomplished any eddy current 
inspection specified in Revision 1 or Revision 2 of Aviation 
Partners Boeing Alert Service Bulletin AP757-53-001 with no cracking 
found and have not accomplished any inspection specified in Revision 
2 or Revision 3 of Aviation Partners Boeing Alert Service Bulletin 
AP757-53-002: The compliance time for the initial open hole high 
frequency eddy current (HFEC) inspection of the STA 1640 fuselage 
frame web fastener holes common to the S-14L and S-14R intercostal 
tee clip for any crack is at the applicable time specified in 
paragraph (h)(6)(i) or (ii) of this AD, whichever occurs later.
    (i) Within 1,200 flight cycles after the most recent inspection 
was done in accordance with Revision 1 or Revision 2 of Aviation 
Partners Boeing Alert Service Bulletin AP757-53-001.
    (ii) Within 500 flight cycles after the effective date of this 
AD not to exceed 5,600 flight cycles after the most recent 
inspection was done in accordance with Revision 1 or Revision 2 of 
Aviation Partners Boeing Alert Service Bulletin AP757-53-001.
    (7) For Group 1 airplanes, as identified in Aviation Partners 
Boeing Alert Service Bulletin AP757-53-002, Revision 3, dated August 
14, 2019, with 34,500 total flight cycles or more as of the 
effective date of this AD that have accomplished any eddy current 
inspection in accordance with Revision 1 or Revision 2 of Aviation 
Partners Boeing Alert Service Bulletin AP757-53-001 with no cracking 
found and have not accomplished any inspection specified in Revision 
2 or Revision 3 of Aviation Partners Boeing Alert Service Bulletin 
AP757-53-002: The compliance time for the initial open hole HFEC 
inspection of the STA 1640 fuselage frame web fastener holes common 
to the S-14L and S-14R intercostal tee clip for any crack is at the 
applicable time specified in paragraph (h)(7)(i) or (ii) of this AD, 
whichever occurs later:
    (i) Within 1,200 flight cycles after the most recent eddy 
current inspection was done in accordance with Revision 1 or 
Revision 2 of Aviation Partners Boeing Alert Service Bulletin AP757-
53-001.
    (ii) Prior to the accumulation of 35,000 total flight cycles, or 
within 30 days after the effective date of this AD, whichever occurs 
later.
    (8) For Group 3 airplanes, as identified in Aviation Partners 
Boeing Alert Service Bulletin AP757-53-002, Revision 3, dated August 
14, 2019, that as of the effective date of this AD have accomplished 
any eddy current inspection in accordance with Revision 1 or 
Revision 2 of Aviation Partners Boeing Alert Service Bulletin AP757 
53-001, with no cracking found: The compliance time for the initial 
open hole HFEC inspection of the STA 1640 fuselage frame web 
fastener holes common to the S-14L and S-14R intercostal tee clip 
for any crack is at the applicable time specified in paragraph 
(h)(8)(i) or (ii) of this AD, whichever occurs later.
    (i) Within 1,350 flight cycles after the most recent eddy 
current inspection was done as specified in Revision 1 or Revision 2 
of Aviation Partners Boeing Alert Service Bulletin AP757-53-001.
    (ii) Within 500 flight cycles after the effective date of this 
AD not to exceed 3,250 flight cycles after the most recent 
inspection was done in accordance with Revision 1 or Revision 2 of 
Aviation Partners Boeing Alert Service Bulletin AP757-53-001.

(i) Credit for Previous Actions

    (1) This paragraph provides credit for actions specified in 
paragraphs (g)(1), (3), and (4) of this AD, if those actions were 
performed before the effective date of this AD using Boeing Alert 
Requirements Bulletin 757-53A0112 RB, dated November 16, 2018.
    (2) This paragraph provides credit for the actions specified in 
paragraph (g)(2) of this AD, if those actions were performed before 
the effective date of this AD using Aviation Partners Boeing Alert 
Service Bulletin AP757-53-002, Revision 2, dated April 11, 2019.

(j) 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 (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, 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 for AD 2019-23-06 are approved as AMOCs for 
the corresponding provisions of Boeing Alert Requirements Bulletin 
757-53A0112 RB, dated November 16, 2018; and Aviation Partners 
Boeing Alert Service Bulletin AP757-53-002, Revision 3, dated August 
14, 2019; that are required by paragraph (g)(2) of this AD.
    (5) AMOCs approved for AD 2019-23-06 are approved as AMOCs for 
the

[[Page 47097]]

corresponding provisions of Boeing Alert Requirements Bulletin 757-
53A0112 RB, Revision 1, dated June 17, 2022, that are required by 
paragraphs (g)(1), (3), and (4) of this AD, except AMOCs for 
airplanes converted to the special freighter (SF) configuration by 
Boeing STC ST00916WI-D or from a passenger to freighter 
configuration using VT MAE Inc. STC ST03562AT are not approved as 
AMOCs for this AD.

(k) Related Information

    (1) 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].
    (2) For service information identified in this AD, contact 
Boeing Commercial Airplanes, Attention: Contractual & Data Services 
(C&DS), 2600 Westminster Blvd., MC 110-SK57, Seal Beach, CA 90740-
5600; telephone 562-797-1717; internet https://www.myboeingfleet.com. You may view this referenced service 
information at the FAA, Airworthiness Products Section, Operational 
Safety Branch, 2200 South 216th St., Des Moines, WA. For information 
on the availability of this material at the FAA, call 206-231-3195.
    (3) Service information identified in this AD that is not 
incorporated by reference is available at the addresses specified in 
paragraphs (l)(5), (6), and (7) 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.
    (3) The following service information was approved for IBR on 
August 17, 2022.
    (i) Boeing Alert Requirements Bulletin 757-53A0112 RB, Revision 
1, dated June 17, 2022.
    (ii) [Reserved]
    (4) The following service information was approved for IBR on 
January 13, 2020 (84 FR 67179, December 9, 2019).
    (i) Aviation Partners Boeing Alert Service Bulletin AP757-53-
002, Revision 3 dated August 14, 2019.
    (ii) Boeing Alert Requirements Bulletin 757-53A0112 RB, dated 
November 16, 2018.
    (5) For Boeing 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) For Aviation Partners Boeing service information identified 
in this AD, contact Aviation Partners Boeing, 2811 South 102nd St., 
Suite 200, Seattle, WA 98168; phone: 206-830-7699; fax: 206-767-
0535; email: [email protected]; internet: https://www.aviationpartnersboeing.com.
    (7) 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.
    (8) 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 July 15, 2022.
Gaetano A. Sciortino,
Deputy Director for Strategic Initiatives, Compliance & Airworthiness 
Division, Aircraft Certification Service.
[FR Doc. 2022-16605 Filed 7-29-22; 4:15 pm]
BILLING CODE 4910-13-P