Rule2022-09663
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
May 6, 2022
Effective
June 10, 2022
Issuing agencies
Transportation DepartmentFederal Aviation Administration
Abstract
The FAA is superseding Airworthiness Directive (AD) 2020-21- 17, which applied to all The Boeing Company Model 757 airplanes. AD 2020-21-17 required repetitive inspections for skin cracking and shim migration at the upper link drag fittings, diagonal brace cracking, and fastener looseness; and applicable on-condition actions. This AD was prompted by reports of bolt rotation in the engine drag fitting joint and fastener heads and cracks found in the skin of the fastener holes, and the need to reduce the compliance time for certain groups. This AD retains the requirements of AD 2020-21-17 with reduced compliance times for certain airplane groups. 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 88 (Friday, May 6, 2022)</title>
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[Federal Register Volume 87, Number 88 (Friday, May 6, 2022)]
[Rules and Regulations]
[Pages 26964-26966]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 2022-09663]
[[Page 26964]]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2021-0685; Project Identifier AD-2021-00432-T;
Amendment 39-22015; AD 2022-08-12]
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) 2020-21-
17, which applied to all The Boeing Company Model 757 airplanes. AD
2020-21-17 required repetitive inspections for skin cracking and shim
migration at the upper link drag fittings, diagonal brace cracking, and
fastener looseness; and applicable on-condition actions. This AD was
prompted by reports of bolt rotation in the engine drag fitting joint
and fastener heads and cracks found in the skin of the fastener holes,
and the need to reduce the compliance time for certain groups. This AD
retains the requirements of AD 2020-21-17 with reduced compliance times
for certain airplane groups. The FAA is issuing this AD to address the
unsafe condition on these products.
DATES: This AD is effective June 10, 2022.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in this AD as of June 10,
2022.
ADDRESSES: For service information identified in this final rule,
contact Boeing Commercial Airplanes, Attention: Contractual & Data
Services (C&DS), 2600 Westminster Blvd., MC 110-SK57, Seal Beach, CA
90740-5600; telephone 562-797-1717; internet <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-2021-0685.
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-2021-0685; 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: David Truong, Aerospace Engineer,
Airframe Section, FAA, Los Angeles ACO Branch, 3960 Paramount
Boulevard, Lakewood, CA 90712-4137; phone: 562-627-5224; email:
<a href="/cdn-cgi/l/email-protection#e18580978885cf9593948e8f86a1878080cf868e97"><span class="__cf_email__" data-cfemail="cda9acbba4a9e3b9bfb8a2a3aa8dabacace3aaa2bb">[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 2020-21-17, Amendment 39-21290 (85 FR
79418, December 10, 2020) (AD 2020-21-17). AD 2020-21-17 applied to all
The Boeing Company Model 757 airplanes. The NPRM published in the
Federal Register on September 9, 2021 (86 FR 50485). The NPRM was
prompted by reports of bolt rotation in the engine drag fitting joint
and fastener heads and cracks found in the skin of the fastener holes,
and the need to reduce the compliance time for certain groups. In the
NPRM, the FAA proposed to retain the requirements of AD 2020-21-17 with
reduced compliance times for certain airplane groups. The FAA is
issuing this AD to address cracking in the wing upper skin and forward
drag fittings, which could lead to a compromised upper link and reduced
structural integrity of the engine strut, and possible separation of a
strut and engine from the airplane during flight.
Discussion of Final Airworthiness Directive
Comments
The FAA received comments from the Air Line Pilots Association,
International (ALPA), Boeing, and FedEx who supported the NPRM without
change.
The FAA received additional comments from three commenters,
including Aviation Partners Boeing (APB), United Airlines (UAL), and
United Parcel Service (UPS). 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 accomplishing Supplemental Type Certificate (STC)
ST01518SE does not affect the actions specified in the proposed AD.
The FAA concurs with the commenter. The FAA has redesignated
paragraph (c) of the proposed AD as paragraph (c)(1) of this AD and
added paragraph (c)(2) 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 To Clarify Certain Figures in the Service Information
UAL requested clarification of Figures 21 and 22 for an open-hole
high frequency eddy current (HFEC) inspection as specified in Boeing
Alert Requirements Bulletin 757-57A0073 RB, Revision 2, dated March 1,
2021. UAL stated that in note (a) of Figures 21 and 22, it specifies to
``Do an open-hole HFEC inspection for any crack in accordance with 757
NDT [Non-Destructive Test] Manual Part 6, 51-00-16,'' at the ``Fastener
Holes and Drag Fitting.'' UAL also stated that this is different than
the inspection specified in note (a) of Figures 7 and 8 which specifies
to ``Do an open-hole HFEC inspection for any crack of the holes of
loose fasteners only in accordance with 757 NDT Manual Part 6, 51-00-
16'' at the ``Fastener Holes.''
UAL stated that the NDT manual references are the same in Figures 7
and 8, and Figures 21 and 22. UAL commented that Figures 7 and 8 are
used in Part 4 inspections (only at loose fastener hole locations found
at locations 11 through 18) of the service information; and Figures 21
and 22 are used in Part 8 inspections (inspections of all fastener
locations 11 through 18) of the service information. UAL commented that
it is not clear what the intent is of making step 1 in Figures 21 and
22 specify ``Fastener Holes'' and ``Drag Fitting,'' (listed as two
separate items) and if these are different inspections of the fastener
holes.
The FAA agrees to provide clarification. Part 4 inspections use
Figures 7 and 8 of the service information to inspect for any cracking,
and are an on-condition action required only for any fastener holes
that are found (during Part 2 inspections) to have loose fasteners in
the wing upper skin. Part 8 inspections use Figures 21 and 22 to
inspect for any cracking in the fastener holes of the upper wing skin
and drag fitting, and are required for all airplanes. Accomplishing an
open hole
[[Page 26965]]
HFEC inspection as a result of Condition 5 (which requires
accomplishing figures 7 and 8), meets the requirement of the open hole
HFEC inspection of fastener holes 11 through 18 for only the fastener
hole(s) inspected (as specified in note (a) of Tables 4 and 7 in the
Accomplishment Instructions of Boeing Alert Requirements Bulletin 757-
57A0073 RB, Revision 2, dated March 1, 2021). The open hole HFEC
inspection for any cracking of fastener holes 11 through 18 specified
in Figures 7 and 8 and Figures 21 and 22 are the same, however the
``Drag Fitting'' specified in Figures 21 and 22 is emphasized so the
drag fitting fastener holes are not missed when performing the open
hole HFEC inspection through the fastener hole shared between the upper
wing skin and drag fitting. Part 4 and Part 8 have different compliance
times and repetitive inspection intervals. The FAA has not changed this
AD in this regard.
Request To Include Previously Approved AMOCs
UPS requested that the FAA include previously approved AMOCs in the
proposed AD for AD 2018-16-05, Amendment 39-19345 (83 FR 38250, August
6, 2018) (AD 2018-16-05), which was superseded by AD 2020-21-17.
The FAA agrees with the request. AMOCs for AD 2018-16-05 that are
still applicable to the corresponding provisions of Boeing Alert
Requirements Bulletin 757-57A0073 RB, Revision 2, dated March 1, 2021,
which are required by paragraph (g) of this AD, are approved as AMOCs
for this AD. The FAA has added paragraph (j)(5) to this AD to include
AMOCs approved for AD 2018-16-05.
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 757-57A0073 RB,
Revision 2, dated March 1, 2021. This service information specifies
procedures for repetitive general visual and detailed inspections for
loose fasteners, skin cracking, and shim migration at the upper link
drag fittings, and for cracking in the diagonal brace and diagonal
brace fittings; repetitive open-hole high frequency eddy current
inspections for cracking of the fastener holes and loose bolt holes;
and applicable on-condition actions. On-condition actions include
installing the upper link and upper link pins; replacing drag fittings;
installing bolts, washers, and nuts; performing a torque check of
fasteners on the affected shims; trimming affected shims and applying
chemical conversion coating on the shims, fillet seal, and drag
fittings; and repairing cracks, migrated shims, mistorqued bolts, and
loose fasteners.
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 would affect 450 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
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Repetitive HFEC inspections...... 85 work-hours x $85 $0 $7,225 per $3,251,250 per
per hour = $7,225 inspection cycle. inspection cycle.
per inspection
cycle.
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The FAA has received no definitive data on which to base the cost
estimates for the on-condition actions 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 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) 2020-21-17, Amendment 39-21290
(85 FR 79418, December 10, 2020); and
0
b. Adding the following new AD:
2022-08-12 The Boeing Company: Amendment 39-22015; Docket No.
[[Page 26966]]
FAA-2021-0685; Project Identifier AD-2021-00432-T.
(a) Effective Date
This airworthiness directive (AD) is effective June 10, 2022.
(b) Affected ADs
This AD replaces AD 2020-21-17, Amendment 39-21290 (85 FR 79418,
December 10, 2020) (AD 2020-21-17).
(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 57, Wings.
(e) Unsafe Condition
This AD was prompted by reports of bolt rotation in the engine
drag fitting joint and fastener heads and cracks found in the skin
of the fastener holes, and the need to reduce the compliance time
for certain groups. The FAA is issuing this AD to address cracking
in the wing upper skin and forward drag fittings, which could lead
to a compromised upper link and reduced structural integrity of the
engine strut, and possible separation of a strut and engine from the
airplane during flight.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Required Actions
Except as specified by paragraph (h) of this AD: At the
applicable times specified in the ``Compliance'' paragraph of Boeing
Alert Requirements Bulletin 757-57A0073 RB, Revision 2, dated March
1, 2021, do all applicable actions identified in, and in accordance
with, the Accomplishment Instructions of Boeing Alert Requirements
Bulletin 757-57A0073 RB, Revision 2, dated March 1, 2021.
Note 1 to paragraph (g): Guidance for accomplishing the actions
required by this AD can be found in Boeing Alert Service Bulletin
757-57A0073, Revision 2, dated March 1, 2021, which is referred to
in Boeing Alert Requirements Bulletin 757-57A0073 RB, Revision 2,
dated March 1, 2021.
(h) Exceptions to Service Information Specifications
(1) Where Boeing Alert Requirements Bulletin 757-57A0073 RB,
Revision 2, dated March 1, 2021, uses the phrase ``the Original
Issue date of Requirements Bulletin 757-57A0073 RB,'' this AD
requires using September 10, 2018 (the effective date of AD 2018-16-
05, Amendment 39-19345 (83 FR 38250, August 6, 2018)).
(2) Where the Compliance Time columns of the tables in the
``Compliance'' paragraph of Boeing Alert Requirements Bulletin 757-
57A0073 RB, Revision 2, dated March 1, 2021, uses the phrase ``the
Revision 1 date of Requirements Bulletin 757-57A0073 RB date of this
service bulletin,'' this AD requires using January 14, 2021 (the
effective date of AD 2020-21-17).
(3) Where the Condition and Compliance Time columns of the
tables in the ``Compliance'' paragraph of Boeing Alert Requirements
Bulletin 757-57A0073 RB, Revision 2, dated March 1, 2021, uses the
phrase ``the Revision 2 date of Requirements Bulletin 757-57A0073
RB,'' this AD requires using the effective date of this AD.
(4) Where Boeing Alert Requirements Bulletin 757-57A0073 RB,
Revision 2, dated March 1, 2021, specifies contacting Boeing for
repair instructions: This AD requires doing the repair using a
method approved in accordance with the procedures specified in
paragraph (j) of this AD.
(i) Credit for Previous Actions
(1) This paragraph provides credit for the actions specified in
paragraph (g) of this AD, except for the open-hole high frequency
eddy current inspections at fastener locations 11-18, if those
actions were performed before the effective date of this AD using
Boeing Alert Requirements Bulletin 757-57A0073 RB, dated July 14,
2017.
(2) This paragraph provides credit for the actions specified in
paragraph (g) of this AD, if those actions were performed before the
effective date of this AD using Boeing Alert Requirements Bulletin
757-57A0073 RB, Revision 1, dated August 1, 2019. This service
information is not incorporated by reference in this AD.
(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 Related Information. Information may be emailed
to: <a href="/cdn-cgi/l/email-protection#10293d515e5d3d5c5151535f3d515d5f533d4275616575636463507671713e777f66"><span class="__cf_email__" data-cfemail="d7eefa96999afa9b96969498fa969a9894fa85b2a6a2b2a4a3a497b1b6b6f9b0b8a1">[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 for AD 2020-21-17 are approved as AMOCs for
the corresponding provisions of Boeing Alert Requirements Bulletin
757-57A0073 RB, Revision 2, dated March 1, 2021, that are required
by paragraph (g) of this AD.
(5) AMOCs approved for AD 2018-16-05, Amendment 39-19345 (83 FR
38250, August 6, 2018) are approved as AMOCs for the corresponding
provisions of Boeing Alert Requirements Bulletin 757-57A0073 RB,
Revision 2, dated March 1, 2021, that are required by paragraph (g)
of this AD.
(k) Related Information
(1) For more information about this AD, contact David Truong,
Aerospace Engineer, Airframe Section, FAA, Los Angeles ACO Branch,
3960 Paramount Boulevard, Lakewood, CA 90712-4137; phone: 562-627-
5224; email: <a href="/cdn-cgi/l/email-protection#0a6e6b7c636e247e787f65646d4a6c6b6b246d657c"><span class="__cf_email__" data-cfemail="c2a6a3b4aba6ecb6b0b7adaca582a4a3a3eca5adb4">[email protected]</span></a>.
(2) Service information identified in this AD that is not
incorporated by reference is available at the addresses specified in
paragraphs (l)(3) and (4) of this AD.
(l) Material Incorporated by Reference
(1) The Director of the Federal Register approved the
incorporation by reference (IBR) of the service information listed
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
(2) You must use this service information as applicable to do
the actions required by this AD, unless the AD specifies otherwise.
(i) Boeing Alert Requirements Bulletin 757-57A0073 RB, Revision
2, dated March 1, 2021.
(ii) [Reserved]
(3) For service information identified in this AD, contact
Boeing Commercial Airplanes, Attention: Contractual & Data Services
(C&DS), 2600 Westminster Blvd., MC 110-SK57, Seal Beach, CA 90740-
5600; telephone 562-797-1717; internet <a href="https://www.myboeingfleet.com">https://www.myboeingfleet.com</a>.
(4) You may view this service information at the FAA,
Airworthiness Products Section, Operational Safety Branch, 2200
South 216th St., Des Moines, WA. For information on the availability
of this material at the FAA, call 206-231-3195.
(5) You may view this service information that is incorporated
by reference at the National Archives and Records Administration
(NARA). For information on the availability of this material at
NARA, email <a href="/cdn-cgi/l/email-protection#b5d3c79bdcdbc6c5d0d6c1dcdadbf5dbd4c7d49bd2dac3"><span class="__cf_email__" data-cfemail="3f594d1156514c4f5a5c4b5650517f515e4d5e11585049">[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 April 7, 2022.
Lance T. Gant,
Director, Compliance & Airworthiness Division, Aircraft Certification
Service.
[FR Doc. 2022-09663 Filed 5-5-22; 8:45 am]
BILLING CODE 4910-13-P
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