Airworthiness Directives; The Boeing Company Airplanes, 58257-58260 [2024-15827]
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Federal Register / Vol. 89, No. 138 / Thursday, July 18, 2024 / Rules and Regulations
the integral rear center tank during the
time required for evacuation. The
applicant’s showing must also
demonstrate that the design provides
sufficient time for a safe evacuation of
all occupants after the initiation of an
external fuel-fed ground fire.
Issued in Kansas City, Missouri, on July 12,
2024.
Patrick R. Mullen,
Manager, Technical Policy Branch, Policy and
Standards Division, Aircraft Certification
Service.
[FR Doc. 2024–15853 Filed 7–17–24; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2023–2395; Project
Identifier AD–2023–00767–T; Amendment
39–22773; AD 2023–12–09]
RIN 2120–AA64
Airworthiness Directives; The Boeing
Company Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
The FAA is superseding
Airworthiness Directive (AD) 2022–08–
12, which applies to all The Boeing
Company Model 757 airplanes. AD
2022–08–12 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, a determination that certain drag
fittings may be made of alternate
materials, which could result in reduced
structural integrity of the engine strut,
and a determination that additional
inspections and revised compliance
times are needed. This AD retains the
requirements of AD 2022–08–12 with
revised compliance times for certain
actions and requires adding inspections
for existing repairs and applicable on
condition actions. The FAA is issuing
this AD to address the unsafe condition
on these products.
DATES: This AD is effective August 22,
2024.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in this AD
as of August 22, 2024.
ADDRESSES:
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SUMMARY:
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AD Docket: You may examine the AD
docket at regulations.gov under Docket
No. FAA–2023–2395; 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.
Material Incorporated by Reference:
• For Boeing service information
incorporated by reference in this AD,
contact Boeing Commercial Airplanes,
Attention: Contractual & Data Services
(C&DS), 2600 Westminster Blvd., MC
110–SK57, Seal Beach, CA 90740–5600;
telephone 562–797–1717; website
myboeingfleet.com.
• You may view this service
information at the FAA, Airworthiness
Products Section, Operational Safety
Branch, 2200 South 216th St., Des
Moines, WA. For information on the
availability of this material at the FAA,
call 206–231–3195. It is also available at
regulations.gov under Docket No. FAA–
2023–2395.
FOR FURTHER INFORMATION CONTACT:
Wayne Ha, Aviation Safety Engineer,
FAA, 2200 South 216th St., Des Moines,
WA 98198; telephone 562–627–5238;
email wayne.ha@faa.gov.
SUPPLEMENTARY INFORMATION:
Background
The FAA issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 to supersede AD 2022–08–12,
Amendment 39–22015 (87 FR 26964,
May 6, 2022) (AD 2022–08–12). AD
2022–08–12 applied to all The Boeing
Company Model 757 airplanes. The
NPRM published in the Federal
Register on December 21, 2023 (88 FR
88271). 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 require
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. The FAA issued
AD 2022–08–12 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.
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58257
Actions Since AD 2022–08–12 Was
Issued
Since the FAA issued AD 2022–08–
12, it was determined that drag fittings
made of alternate materials have
possibly been installed on some
configurations, which could result in
reduced structural integrity of the
engine strut. The FAA has determined
that additional inspections and revised
compliance times are needed to
maintain structural integrity. Although
this AD does not explicitly restate the
requirements of AD 2022–08–12, this
AD would retain all requirements of AD
2022–08–12. Those requirements are
referenced in the service information
identified previously, which, in turn, is
referenced in paragraph (g) of this AD.
Discussion of Final Airworthiness
Directive
Comments
The FAA received comments from
The Boeing Company, who supported
the NPRM without change.
The FAA received additional
comments from five commenters,
including Aviation Partners Boeing,
Delta Air Lines, UPS Airlines, United
Airlines, and FedEx Express. 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
Aviation Partners Boeing has
reviewed the NPRM and has determined
that the incorporation of STC
ST01518SE for installation of blended
or scimitar blended winglets does not
affect compliance with the mandated
actions in the proposed rule. Boeing
does not have delegation to approve
repairs in areas affected by the scimitar
blended winglet configuration of STC
ST01518SE. Therefore, Boeing will not
be able to use Organization Designation
Authorization (ODA) approval in
paragraph (j)(3) of this AD to make an
alternative method of compliance
(AMOC) finding on behalf of the FAA
for alternative inspections and
corrective actions in areas affected by
the scimitar blended winglet
configuration of STC ST01518SE. The
operators of scimitar blended winglet
airplanes subject to this AD should be
aware that approval of any alternative
inspections and corrective actions as an
AMOC to the final rule will only be
obtainable from the FAA through the
means described in paragraph (j)(1) of
this AD.
The FAA agrees. The FAA has not
changed this AD in this regard.
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Federal Register / Vol. 89, No. 138 / Thursday, July 18, 2024 / Rules and Regulations
Requests for Revising AMOCs
Paragraphs (j)(4) Through (j)(6) of the
Proposed Rule
Delta Air Lines, FedEx, UPS Airlines,
and United Airlines requested revising
AMOCs paragraphs (j)(4), (j)(5), and
(j)(6) of the proposed rule. Delta Air
Lines stated that restrictions of
paragraphs (j)(4) through (j)(6) of the
proposed rule would put an extreme
and unnecessary burden on Model 757
operators. FedEx was concerned that
paragraphs (j)(4) and (j)(5) of the
proposed rule would prevent continued
operation of the affected airplanes until
new AMOC approvals could be
obtained. UPS Airlines requested
revising paragraphs (j)(4), (j)(5), and
(j)(6) of the proposed rule to accept
AMOCs issued after March 1, 2021.
United Airlines stated that paragraphs
(j)(4) through (j)(6) of the proposed rule
contains exception for previously
approved AMOCs for locations at the
wing skin and drag fittings at the upper
link drag fittings (fasteners 1–18) that
will affect the aircraft operations until
new AMOC is received, or new
inspection is accomplished.
The FAA agrees with the commenters.
The FAA has determined that
paragraphs (j)(4), (j)(5), and (j)(6) of the
proposed rule are not required. The
FAA has determined that the
Compliance Tables 19 and 20 of
Revision 3 of the Boeing Alert
Requirements Bulletin 757–57A0073 RB
address all existing repairs and existing
drag fitting replacement with universal
fitting. The FAA has removed
paragraphs (j)(4), (j)(5), and (j)(6) of the
proposed rule accordingly.
Request To Not Reduce Inspection
Compliance Times Under Certain
Circumstances
UPS Airlines proposed that the
inspection compliance times for some
configurations that installed upper link
drag fitting made of optional materials
be reduced only if this condition has
been confirmed by visual inspection
and/or maintenance records review.
The FAA acknowledges UPS Airlines’
concern. However, the FAA does not
agree with the proposed request because
UPS Airlines did not submit sufficient
data to substantiate that the proposed
actions would provide an acceptable
level of safety. Under the provisions of
paragraph (j) of this AD, the FAA will
consider requests for approval of
alternative actions and compliance
times if sufficient data are submitted to
substantiate that the change would
provide an acceptable level of safety.
This AD has not been changed regarding
this proposed request.
Request for Revising Paragraphs (h)(1)
Through (h)(4) of the Proposed Rule
UPS Airlines also requested to revise
paragraphs (h)(1) through (h)(4) of the
proposed rule from ‘‘Where the
Compliance Time columns of the
tables’’ to ‘‘Where the Compliance Time
columns and notes of the tables.’’ UPS
Airlines explained that both
Compliance Time columns and notes in
the tables are referred to Boeing Alert
Requirements Bulletin 757–57A0073
RB.
The FAA agrees to revise from
‘‘Where the Compliance Time columns
of the tables’’ to ‘‘Where the Compliance
Time columns and notes of the tables’’
for paragraphs (h)(2), (h)(3), and (h)(4) of
this AD, because the notes in
compliance tables refer to ‘‘On or after
the Revision 1 date of Boeing Alert
Requirements Bulletin 757–57A0073
RB.’’ Paragraph (h)(2) of this AD refers
to the phrase ‘‘the Revision 1 date of
Boeing Alert Requirements Bulletin
757–57A0073 RB,’’ paragraph (h)(3) of
this AD refers to the phrase ‘‘the
Revision 2 date of Boeing Alert
Requirements Bulletin 757–57A0073
RB,’’ and paragraph (h)(4) of this AD
refers to the phrase ‘‘the Revision 3 date
of Boeing Alert Requirements Bulletin
757–57A0073 RB.’’ However, the FAA
does not agree to revise paragraph (h)(1)
of this AD, because the notes in the
compliance tables only refer to ‘‘On or
after the Revision 1 date of Boeing Alert
Requirements Bulletin 757–57A0073
RB.’’ The original issue date of Boeing
Alert Requirements Bulletin 757–
57A0073 RB is not included for
paragraph (h)(1) of this AD. The FAA
has not changed paragraph (h)(1) of this
AD. The FAA has revised paragraphs
(h)(2), (h)(3), and (h)(4) of this AD
accordingly.
Conclusion
The FAA reviewed the relevant data,
considered any comments received, and
determined that air safety requires
adopting this AD as proposed.
Accordingly, the FAA is issuing this AD
to address the unsafe condition on these
products. 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 3, dated May 5, 2023. This
service information specifies procedures
for a general visual inspection or
records check of the wing upper skin at
the drag fitting attachment holes for any
existing repair; 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
(HFEC) inspections for cracking of the
fastener holes and loose bolt holes; and
applicable on-condition actions. Oncondition actions include performing an
ultrasonic inspection for cracks at any
repaired upper wing skin location;
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
affects 496 airplanes of U.S. registry.
The FAA estimates the following costs
to comply with this AD:
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ESTIMATED COSTS
Action
Labor cost
Repetitive HFEC inspections
(retained actions from AD
2022-08-12).
New actions ............................
85 work-hours × $85 per hour
= $7,225 per inspection
cycle.
Up to 4 work-hours × $85 per
hour = Up to $340.
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Parts cost
Fmt 4700
Cost per product
Cost on U.S.
operators
$0
$7,225 per inspection cycle ...
$3,583,600 per inspection
cycle.
$0
Up to $340 .............................
Up to $168,640.
Sfmt 4700
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Federal Register / Vol. 89, No. 138 / Thursday, July 18, 2024 / Rules and Regulations
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.
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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
1. The authority citation for part 39
continues to read as follows:
■
Authority: 49 U.S.C. 106(g), 40113, 44701.
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§ 39.13
[Amended]
2. The FAA amends § 39.13 by:
a. Removing Airworthiness Directive
(AD) 2022–08–12, Amendment 39–
22015 (87 FR 26964, May 6, 2022); and
■ b. Adding the following new AD:
■
■
2023–12–09 The Boeing Company:
Amendment 39–22773; Docket No.
FAA–2023–2395; Project Identifier AD–
2023–00767–T.
(a) Effective Date
This airworthiness directive (AD) is
effective August 22, 2024.
(b) Affected ADs
This AD replaces AD 2022–08–12,
Amendment 39–22015 (87 FR 26964, May 6,
2022) (AD 2022–08–12).
(c) Applicability
This AD applies to all The Boeing
Company Model 757–200, PF, –200CB, and
–300 series airplanes, certificated in any
category.
(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, a determination that
certain drag fittings may be made of alternate
materials, which could result in reduced
structural integrity of the engine strut, and a
determination that additional inspections
and revised compliance times are needed.
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 3, dated May 5, 2023, do all
applicable actions identified in, and in
accordance with, the Accomplishment
Instructions of Boeing Alert Requirements
Bulletin 757–57A0073 RB, Revision 3, dated
May 5, 2023.
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 3, dated
May 5, 2023, which is referred to in Boeing
Alert Requirements Bulletin 757–57A0073
RB, Revision 3, dated May 5, 2023.
(h) Exceptions to Service Information
Specifications
(1) Where the Compliance Time columns
of the tables in the ‘‘Compliance’’ paragraph
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58259
of Boeing Alert Requirements Bulletin 757–
57A0073 RB, Revision 3, dated May 5, 2023,
use 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))’’ (AD 2018–16–05).
(2) Where the Compliance Time columns
and notes of the tables in the ‘‘Compliance’’
paragraph of Boeing Alert Requirements
Bulletin 757–57A0073 RB, Revision 3, dated
May 5, 2023, use the phrase ‘‘the Revision 1
date of Requirements Bulletin 757–57A0073
RB,’’ this AD requires using ‘‘January 14,
2021 (the effective date of AD 2020–21–17,
Amendment 39–21290 (85 FR 79418,
December 10, 2020))’’ (AD 2020–21–17).
(3) Where the Compliance Time columns
and notes of the tables in the ‘‘Compliance’’
paragraph of Boeing Alert Requirements
Bulletin 757–57A0073 RB, Revision 3, dated
May 5, 2023, use the phrase ‘‘the Revision 2
date of Requirements Bulletin 757–57A0073
RB,’’ this AD requires using ‘‘June 10, 2022
(the effective date of AD 2022–08–12).’’
(4) Where the Compliance Time columns
and notes of the tables in the ‘‘Compliance’’
paragraph of Boeing Alert Requirements
Bulletin 757–57A0073 RB, Revision 3, dated
May 5, 2023, use the phrase ‘‘the Revision 3
date of Requirements Bulletin 757–57A0073
RB,’’ this AD requires using the effective date
of this AD.
(5) Where Boeing Alert Requirements
Bulletin 757–57A0073 RB, Revision 3, dated
May 5, 2023, 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.
(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
January 14, 2021 (the effective date of AD
2020–21–17) 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 June
10, 2022 (the effective date of AD 2022–08–
12) using Boeing Alert Requirements Bulletin
757–57A0073 RB, Revision 1, dated August
1, 2019.
(3) 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 2, dated March 1, 2021.
(j) Alternative Methods of Compliance
(AMOCs)
(1) The Manager, AIR–520, Continued
Operational Safety 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,
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Federal Register / Vol. 89, No. 138 / Thursday, July 18, 2024 / Rules and Regulations
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: AMOC@
faa.gov.
(2) Before using any approved AMOC,
notify your appropriate principal inspector,
or lacking a principal inspector, the manager
of the responsible Flight Standards Office.
(3) An AMOC that provides an acceptable
level of safety may be used for any repair,
modification, or alteration required by this
AD if it is approved by The Boeing Company
Organization Designation Authorization
(ODA) that has been authorized by the
Manager, AIR–520, Continued Operational
Safety Branch, FAA, to make those findings.
To be approved, the repair method,
modification deviation, or alteration
deviation must meet the certification basis of
the airplane, and the approval must
specifically refer to this AD.
(k) Related Information
(1) For more information about this AD,
contact Wayne Ha, Aviation Safety Engineer,
FAA, 2200 South 216th St., Des Moines, WA
98198; telephone 562–627–5238; email
wayne.ha@faa.gov.
(2) Service information identified in this
AD that is not incorporated by reference is
available at the address specified in
paragraph (l)(3) of this AD.
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(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 3, dated May 5,
2023.
(ii) [Reserved]
(3) 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; website myboeingfleet.com.
(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 material at the
National Archives and Records
Administration (NARA). For information on
the availability of this material at NARA,
visit www.archives.gov/federal-register/cfr/
ibr-locations or email fr.inspection@nara.gov.
Issued on June 14, 2024.
Peter A. White,
Deputy Director, Integrated Certificate
Management Division, Aircraft Certification
Service.
[FR Doc. 2024–15827 Filed 7–17–24; 8:45 am]
BILLING CODE 4910–13–P
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2024–0232; Project
Identifier MCAI–2023–00353–R; Amendment
39–22758; AD 2024–10–12]
RIN 2120–AA64
Airworthiness Directives; Bell Textron
Canada Limited Helicopters
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
The FAA is adopting a new
airworthiness directive (AD) for certain
Bell Textron Canada Limited Model 407
helicopters. This AD was prompted by
a report that a certain part-numbered
fuel system standpipe assembly
(standpipe) may have sharp edges at the
interval weld joints due to a quality
escape during the manufacturing
process. This AD requires inspecting
certain fuel system parts and, depending
on the inspection results, taking
corrective actions and performing a fuel
quantity gauging system calibration.
Depending on the results of the fuel
quantity gauging system calibration, this
AD requires performing additional
corrective actions and repeating the fuel
quantity gauging system calibration. The
FAA is issuing this AD to address the
unsafe condition on these products.
DATES: This AD is effective August 22,
2024.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in this AD
as of August 22, 2024.
ADDRESSES:
AD Docket: You may examine the AD
docket at regulations.gov under Docket
No. FAA–2024–0232; 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.
Material Incorporated by Reference:
• For Bell material, contact Bell
Textron Canada Limited, 12,800 Rue de
l’Avenir, Mirabel, Quebec J7J 1R4,
Canada; phone 1–450–437–2862 or 1–
800–363–8023; fax 1–450–433–0272;
email productsupport@bellflight.com; or
at bellflight.com/support/contactsupport.
SUMMARY:
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• You may view this material at the
FAA, Office of the Regional Counsel,
Southwest Region, 10101 Hillwood
Pkwy., Room 6N 321, Fort Worth, TX
76177. For information on the
availability of this material at the FAA,
call (817) 222–5110. It is also available
at regulations.gov under Docket No.
FAA–2024–0232.
FOR FURTHER INFORMATION CONTACT:
Michael Hughlett, Aviation Safety
Engineer, FAA, 1600 Stewart Avenue,
Suite 410, Westbury, NY 11590; phone:
(817) 222–5889; email:
michael.Hughlett@faa.gov.
SUPPLEMENTARY INFORMATION:
Background
The FAA issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 by adding an AD that would
apply to Bell Textron Canada Limited
Model 407 helicopters, serial numbers
54832 through 54931 inclusive, 54933
through 54939 inclusive, and 54942
through 54954 inclusive, with a certain
part-numbered fuel system standpipe
assembly installed. The NPRM
published in the Federal Register on
February 20, 2024 (89 FR 12792). The
NPRM was prompted by Transport
Canada AD CF–2023–11, dated February
23, 2023 (Transport Canada AD CF–
2023–11), issued by Transport Canada,
which is the aviation authority for
Canada. Transport Canada AD CF–
2023–11 states that, due to a quality
escape, standpipe part number (P/N)
407–062–032–103 may have been
delivered with sharp edges at the
internal weld joints.
In the NPRM, the FAA proposed to
require, with the standpipe removed,
inspecting its interior for any sharp
edges on each internal weld joint. If
there are any sharp edges on any weld
joint, the NPRM proposed to require
deburring the edges, ensuring not to
exceed a certain depth into the tube.
The NPRM then proposed to require
removing all sanding residue and
applying a chemical film to any bare
metal surfaces. The NPRM also
proposed to require, with the harness
assembly removed, inspecting the
harness assembly connectors for any
mechanical damage and corrosion to the
electrical pins, and inspecting the
insulation tubing and wires of the
harness assembly for any crack and
chafing. Depending on these results, the
NPRM proposed to require replacing the
harness assembly.
If the harness assembly was required
to be replaced as a result of the
proposed AD requirements, the NPRM
proposed to require performing a fuel
quantity gauging system calibration.
E:\FR\FM\18JYR1.SGM
18JYR1
]]>Agencies
[Federal Register Volume 89, Number 138 (Thursday, July 18, 2024)]
[Rules and Regulations]
[Pages 58257-58260]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2024-15827]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2023-2395; Project Identifier AD-2023-00767-T;
Amendment 39-22773; AD 2023-12-09]
RIN 2120-AA64
Airworthiness Directives; The Boeing Company Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: The FAA is superseding Airworthiness Directive (AD) 2022-08-
12, which applies to all The Boeing Company Model 757 airplanes. AD
2022-08-12 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,
a determination that certain drag fittings may be made of alternate
materials, which could result in reduced structural integrity of the
engine strut, and a determination that additional inspections and
revised compliance times are needed. This AD retains the requirements
of AD 2022-08-12 with revised compliance times for certain actions and
requires adding inspections for existing repairs and applicable on
condition actions. The FAA is issuing this AD to address the unsafe
condition on these products.
DATES: This AD is effective August 22, 2024.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in this AD as of August 22,
2024.
ADDRESSES:
AD Docket: You may examine the AD docket at regulations.gov under
Docket No. FAA-2023-2395; 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.
Material Incorporated by Reference:
For Boeing service information incorporated by reference
in this AD, contact Boeing Commercial Airplanes, Attention: Contractual
& Data Services (C&DS), 2600 Westminster Blvd., MC 110-SK57, Seal
Beach, CA 90740-5600; telephone 562-797-1717; website
myboeingfleet.com.
You may view this service information at the FAA,
Airworthiness Products Section, Operational Safety Branch, 2200 South
216th St., Des Moines, WA. For information on the availability of this
material at the FAA, call 206-231-3195. It is also available at
regulations.gov under Docket No. FAA-2023-2395.
FOR FURTHER INFORMATION CONTACT: Wayne Ha, Aviation Safety Engineer,
FAA, 2200 South 216th St., Des Moines, WA 98198; telephone 562-627-
5238; email [email protected].
SUPPLEMENTARY INFORMATION:
Background
The FAA issued a notice of proposed rulemaking (NPRM) to amend 14
CFR part 39 to supersede AD 2022-08-12, Amendment 39-22015 (87 FR
26964, May 6, 2022) (AD 2022-08-12). AD 2022-08-12 applied to all The
Boeing Company Model 757 airplanes. The NPRM published in the Federal
Register on December 21, 2023 (88 FR 88271). 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 require 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. The FAA issued
AD 2022-08-12 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.
Actions Since AD 2022-08-12 Was Issued
Since the FAA issued AD 2022-08-12, it was determined that drag
fittings made of alternate materials have possibly been installed on
some configurations, which could result in reduced structural integrity
of the engine strut. The FAA has determined that additional inspections
and revised compliance times are needed to maintain structural
integrity. Although this AD does not explicitly restate the
requirements of AD 2022-08-12, this AD would retain all requirements of
AD 2022-08-12. Those requirements are referenced in the service
information identified previously, which, in turn, is referenced in
paragraph (g) of this AD.
Discussion of Final Airworthiness Directive
Comments
The FAA received comments from The Boeing Company, who supported
the NPRM without change.
The FAA received additional comments from five commenters,
including Aviation Partners Boeing, Delta Air Lines, UPS Airlines,
United Airlines, and FedEx Express. 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
Aviation Partners Boeing has reviewed the NPRM and has determined
that the incorporation of STC ST01518SE for installation of blended or
scimitar blended winglets does not affect compliance with the mandated
actions in the proposed rule. Boeing does not have delegation to
approve repairs in areas affected by the scimitar blended winglet
configuration of STC ST01518SE. Therefore, Boeing will not be able to
use Organization Designation Authorization (ODA) approval in paragraph
(j)(3) of this AD to make an alternative method of compliance (AMOC)
finding on behalf of the FAA for alternative inspections and corrective
actions in areas affected by the scimitar blended winglet configuration
of STC ST01518SE. The operators of scimitar blended winglet airplanes
subject to this AD should be aware that approval of any alternative
inspections and corrective actions as an AMOC to the final rule will
only be obtainable from the FAA through the means described in
paragraph (j)(1) of this AD.
The FAA agrees. The FAA has not changed this AD in this regard.
[[Page 58258]]
Requests for Revising AMOCs Paragraphs (j)(4) Through (j)(6) of the
Proposed Rule
Delta Air Lines, FedEx, UPS Airlines, and United Airlines requested
revising AMOCs paragraphs (j)(4), (j)(5), and (j)(6) of the proposed
rule. Delta Air Lines stated that restrictions of paragraphs (j)(4)
through (j)(6) of the proposed rule would put an extreme and
unnecessary burden on Model 757 operators. FedEx was concerned that
paragraphs (j)(4) and (j)(5) of the proposed rule would prevent
continued operation of the affected airplanes until new AMOC approvals
could be obtained. UPS Airlines requested revising paragraphs (j)(4),
(j)(5), and (j)(6) of the proposed rule to accept AMOCs issued after
March 1, 2021. United Airlines stated that paragraphs (j)(4) through
(j)(6) of the proposed rule contains exception for previously approved
AMOCs for locations at the wing skin and drag fittings at the upper
link drag fittings (fasteners 1-18) that will affect the aircraft
operations until new AMOC is received, or new inspection is
accomplished.
The FAA agrees with the commenters. The FAA has determined that
paragraphs (j)(4), (j)(5), and (j)(6) of the proposed rule are not
required. The FAA has determined that the Compliance Tables 19 and 20
of Revision 3 of the Boeing Alert Requirements Bulletin 757-57A0073 RB
address all existing repairs and existing drag fitting replacement with
universal fitting. The FAA has removed paragraphs (j)(4), (j)(5), and
(j)(6) of the proposed rule accordingly.
Request To Not Reduce Inspection Compliance Times Under Certain
Circumstances
UPS Airlines proposed that the inspection compliance times for some
configurations that installed upper link drag fitting made of optional
materials be reduced only if this condition has been confirmed by
visual inspection and/or maintenance records review.
The FAA acknowledges UPS Airlines' concern. However, the FAA does
not agree with the proposed request because UPS Airlines did not submit
sufficient data to substantiate that the proposed actions would provide
an acceptable level of safety. Under the provisions of paragraph (j) of
this AD, the FAA will consider requests for approval of alternative
actions and compliance times if sufficient data are submitted to
substantiate that the change would provide an acceptable level of
safety. This AD has not been changed regarding this proposed request.
Request for Revising Paragraphs (h)(1) Through (h)(4) of the Proposed
Rule
UPS Airlines also requested to revise paragraphs (h)(1) through
(h)(4) of the proposed rule from ``Where the Compliance Time columns of
the tables'' to ``Where the Compliance Time columns and notes of the
tables.'' UPS Airlines explained that both Compliance Time columns and
notes in the tables are referred to Boeing Alert Requirements Bulletin
757-57A0073 RB.
The FAA agrees to revise from ``Where the Compliance Time columns
of the tables'' to ``Where the Compliance Time columns and notes of the
tables'' for paragraphs (h)(2), (h)(3), and (h)(4) of this AD, because
the notes in compliance tables refer to ``On or after the Revision 1
date of Boeing Alert Requirements Bulletin 757-57A0073 RB.'' Paragraph
(h)(2) of this AD refers to the phrase ``the Revision 1 date of Boeing
Alert Requirements Bulletin 757-57A0073 RB,'' paragraph (h)(3) of this
AD refers to the phrase ``the Revision 2 date of Boeing Alert
Requirements Bulletin 757-57A0073 RB,'' and paragraph (h)(4) of this AD
refers to the phrase ``the Revision 3 date of Boeing Alert Requirements
Bulletin 757-57A0073 RB.'' However, the FAA does not agree to revise
paragraph (h)(1) of this AD, because the notes in the compliance tables
only refer to ``On or after the Revision 1 date of Boeing Alert
Requirements Bulletin 757-57A0073 RB.'' The original issue date of
Boeing Alert Requirements Bulletin 757-57A0073 RB is not included for
paragraph (h)(1) of this AD. The FAA has not changed paragraph (h)(1)
of this AD. The FAA has revised paragraphs (h)(2), (h)(3), and (h)(4)
of this AD accordingly.
Conclusion
The FAA reviewed the relevant data, considered any comments
received, and determined that air safety requires adopting this AD as
proposed. Accordingly, the FAA is issuing this AD to address the unsafe
condition on these products. 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 3, dated May 5, 2023. This service information specifies
procedures for a general visual inspection or records check of the wing
upper skin at the drag fitting attachment holes for any existing
repair; 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 (HFEC)
inspections for cracking of the fastener holes and loose bolt holes;
and applicable on-condition actions. On-condition actions include
performing an ultrasonic inspection for cracks at any repaired upper
wing skin location; 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 affects 496 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
----------------------------------------------------------------------------------------------------------------
Repetitive HFEC inspections 85 work-hours x $85 $0 $7,225 per $3,583,600 per
(retained actions from AD per hour = $7,225 inspection cycle. inspection cycle.
2022[dash]08[dash]12). per inspection
cycle.
New actions...................... Up to 4 work-hours $0 Up to $340......... Up to $168,640.
x $85 per hour =
Up to $340.
----------------------------------------------------------------------------------------------------------------
[[Page 58259]]
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) 2022-08-12, Amendment 39-22015
(87 FR 26964, May 6, 2022); and
0
b. Adding the following new AD:
2023-12-09 The Boeing Company: Amendment 39-22773; Docket No. FAA-
2023-2395; Project Identifier AD-2023-00767-T.
(a) Effective Date
This airworthiness directive (AD) is effective August 22, 2024.
(b) Affected ADs
This AD replaces AD 2022-08-12, Amendment 39-22015 (87 FR 26964,
May 6, 2022) (AD 2022-08-12).
(c) Applicability
This AD applies to all The Boeing Company Model 757-200, PF, -
200CB, and -300 series airplanes, certificated in any category.
(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, a determination that certain drag fittings
may be made of alternate materials, which could result in reduced
structural integrity of the engine strut, and a determination that
additional inspections and revised compliance times are needed. 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 3, dated May 5,
2023, do all applicable actions identified in, and in accordance
with, the Accomplishment Instructions of Boeing Alert Requirements
Bulletin 757-57A0073 RB, Revision 3, dated May 5, 2023.
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 3, dated May 5, 2023, which is referred to in
Boeing Alert Requirements Bulletin 757-57A0073 RB, Revision 3, dated
May 5, 2023.
(h) Exceptions to Service Information Specifications
(1) Where the Compliance Time columns of the tables in the
``Compliance'' paragraph of Boeing Alert Requirements Bulletin 757-
57A0073 RB, Revision 3, dated May 5, 2023, use 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))'' (AD
2018-16-05).
(2) Where the Compliance Time columns and notes of the tables in
the ``Compliance'' paragraph of Boeing Alert Requirements Bulletin
757-57A0073 RB, Revision 3, dated May 5, 2023, use the phrase ``the
Revision 1 date of Requirements Bulletin 757-57A0073 RB,'' this AD
requires using ``January 14, 2021 (the effective date of AD 2020-21-
17, Amendment 39-21290 (85 FR 79418, December 10, 2020))'' (AD 2020-
21-17).
(3) Where the Compliance Time columns and notes of the tables in
the ``Compliance'' paragraph of Boeing Alert Requirements Bulletin
757-57A0073 RB, Revision 3, dated May 5, 2023, use the phrase ``the
Revision 2 date of Requirements Bulletin 757-57A0073 RB,'' this AD
requires using ``June 10, 2022 (the effective date of AD 2022-08-
12).''
(4) Where the Compliance Time columns and notes of the tables in
the ``Compliance'' paragraph of Boeing Alert Requirements Bulletin
757-57A0073 RB, Revision 3, dated May 5, 2023, use the phrase ``the
Revision 3 date of Requirements Bulletin 757-57A0073 RB,'' this AD
requires using the effective date of this AD.
(5) Where Boeing Alert Requirements Bulletin 757-57A0073 RB,
Revision 3, dated May 5, 2023, 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.
(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 January 14, 2021 (the effective date
of AD 2020-21-17) 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
June 10, 2022 (the effective date of AD 2022-08-12) using Boeing
Alert Requirements Bulletin 757-57A0073 RB, Revision 1, dated August
1, 2019.
(3) 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 2, dated March 1, 2021.
(j) Alternative Methods of Compliance (AMOCs)
(1) The Manager, AIR-520, Continued Operational Safety 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,
[[Page 58260]]
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, AIR-
520, Continued Operational Safety Branch, FAA, to make those
findings. To be approved, the repair method, modification deviation,
or alteration deviation must meet the certification basis of the
airplane, and the approval must specifically refer to this AD.
(k) Related Information
(1) For more information about this AD, contact Wayne Ha,
Aviation Safety Engineer, FAA, 2200 South 216th St., Des Moines, WA
98198; telephone 562-627-5238; email [email protected].
(2) Service information identified in this AD that is not
incorporated by reference is available at the address specified in
paragraph (l)(3) of this AD.
(l) Material Incorporated by Reference
(1) The Director of the Federal Register approved the
incorporation by reference (IBR) of the service information listed
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
(2) You must use this service information as applicable to do
the actions required by this AD, unless the AD specifies otherwise.
(i) Boeing Alert Requirements Bulletin 757-57A0073 RB, Revision
3, dated May 5, 2023.
(ii) [Reserved]
(3) 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; website myboeingfleet.com.
(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 material at the National Archives and
Records Administration (NARA). For information on the availability
of this material at NARA, visit www.archives.gov/federal-register/cfr/ibr-locations or email [email protected].
Issued on June 14, 2024.
Peter A. White,
Deputy Director, Integrated Certificate Management Division, Aircraft
Certification Service.
[FR Doc. 2024-15827 Filed 7-17-24; 8:45 am]
BILLING CODE 4910-13-P
