Rule2022-14490
Airworthiness Directives; The Boeing Company Airplanes
Primary source
Metadata and text below are from the Federal Register, a public-domain U.S. government work. Always verify the official published version before relying on it for any legal matter.
Published
July 8, 2022
Effective
August 12, 2022
Issuing agencies
Transportation DepartmentFederal Aviation Administration
Abstract
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.
Full Text
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<title>Federal Register, Volume 87 Issue 130 (Friday, July 8, 2022)</title>
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[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 [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[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 <a href="https://www.myboeingfleet.com">https://www.myboeingfleet.com</a>. 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
<a href="https://www.regulations.gov">https://www.regulations.gov</a> by searching for and locating Docket No.
FAA-2021-1073.
Examining the AD Docket
You may examine the AD docket at <a href="https://www.regulations.gov">https://www.regulations.gov</a> 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:
<a href="/cdn-cgi/l/email-protection#bdcdd8c9d8cf93d7dccfc7d2d0dffddbdcdc93dad2cb"><span class="__cf_email__" data-cfemail="2b5b4e5f4e5905414a59514446496b4d4a4a054c445d">[email protected]</span></a>.
SUPPLEMENTARY INFORMATION:
Background
The FAA issued a notice of proposed rulemaking (NPRM) to amend 14
CFR part 39 to supersede AD 2017-24-10, 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: <a href="/cdn-cgi/l/email-protection#dfe6f29e9192f2939e9e9c90f29e92909cf28dbaaeaabaacabac9fb9bebef1b8b0a9"><span class="__cf_email__" data-cfemail="043d29454a4929484545474b2945494b47295661757161777077446265652a636b72">[email protected]</span></a>.
(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: <a href="/cdn-cgi/l/email-protection#d0a0b5a4b5a2febab1a2aabfbdb290b6b1b1feb7bfa6"><span class="__cf_email__" data-cfemail="a9d9ccddccdb87c3c8dbd3c6c4cbe9cfc8c887cec6df">[email protected]</span></a>.
(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 <a href="https://www.myboeingfleet.com">https://www.myboeingfleet.com</a>.
(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 <a href="/cdn-cgi/l/email-protection#0d6b7f2364637e7d686e796462634d636c7f6c236a627b"><span class="__cf_email__" data-cfemail="e78195c98e8994978284938e8889a789869586c9808891">[email protected]</span></a>, or go to: <a href="https://www.archives.gov/federal-register/cfr/ibr-locations.html">https://www.archives.gov/federal-register/cfr/ibr-locations.html</a>.
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
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</html>Indexed from Federal Register on July 8, 2022.
This is legal information, not legal advice. Laws vary by jurisdiction and change frequently. Always verify current law with official sources and consult a licensed attorney in your jurisdiction for advice on your specific situation.