Rule2022-27751
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
December 22, 2022
Effective
January 26, 2023
Issuing agencies
Transportation DepartmentFederal Aviation Administration
Abstract
The FAA is adopting a new airworthiness directive (AD) for all The Boeing Company Model 737-100, -200, -200C, -300, -400, and -500 series airplanes. This AD was prompted by a report indicating that a crack was found in one of the holes of the wing rear spar lower chord at the main landing gear (MLG) aft fitting at a certain wing buttock line (WBL). This AD requires repetitive open hole high frequency eddy current (HFEC) inspections or surface HFEC and ultrasonic (UT) inspections for cracking of the wing rear spar lower chord at the MLG aft fitting at a certain WBL, and applicable on-condition 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 245 (Thursday, December 22, 2022)</title>
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[Federal Register Volume 87, Number 245 (Thursday, December 22, 2022)]
[Rules and Regulations]
[Pages 78530-78532]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 2022-27751]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2022-1061; Project Identifier AD-2022-00441-T;
Amendment 39-22271; AD 2022-25-15]
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 adopting a new airworthiness directive (AD) for all
The Boeing Company Model 737-100, -200, -200C, -300, -400, and -500
series airplanes. This AD was prompted by a report indicating that a
crack was found in one of the holes of the wing rear spar lower chord
at the main landing gear (MLG) aft fitting at a certain wing buttock
line (WBL). This AD requires repetitive open hole high frequency eddy
current (HFEC) inspections or surface HFEC and ultrasonic (UT)
inspections for cracking of the wing rear spar lower chord at the MLG
aft fitting at a certain WBL, and applicable on-condition actions. The
FAA is issuing this AD to address the unsafe condition on these
products.
DATES: This AD is effective January 26, 2023.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in this AD as of January 26,
2023.
ADDRESSES:
AD Docket: You may examine the AD docket at <a href="http://regulations.gov">regulations.gov</a> under
Docket No. FAA-2022-1061; 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:
<bullet> 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="http://myboeingfleet.com">myboeingfleet.com</a>.
<bullet> 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="http://regulations.gov">regulations.gov</a> under Docket No. FAA-2022-1061.
FOR FURTHER INFORMATION CONTACT: Wayne Ha, Aerospace Engineer, Airframe
Section, FAA, Los Angeles ACO Branch, 3960 Paramount Boulevard,
Lakewood, CA 90712-4137; phone: 562-627-5238; email: <a href="/cdn-cgi/l/email-protection#5c2b3d25323972343d1c3a3d3d723b332a"><span class="__cf_email__" data-cfemail="a0d7c1d9cec58ec8c1e0c6c1c18ec7cfd6">[email protected]</span></a>.
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 all The Boeing Company
Model 737-100, -200, -200C, -300, -400, and -500 series airplanes. The
NPRM published in the Federal Register on September 8, 2022 (87 FR
54922). The NPRM was prompted by a report indicating that a crack was
found in one of the holes of the wing rear spar lower chord at the MLG
aft fitting at WBL 157 on a Model 737-400 airplane. In the NPRM, the
FAA proposed to require repetitive open hole HFEC inspections or
surface HFEC and UT inspections for cracking of the wing rear spar
lower chord at the MLG aft fitting at a certain WBL, and applicable on-
condition actions. The FAA is issuing this AD to address cracking in
the rear spar lower chord at a fastener common to the MLG aft support
fitting. This condition, if not addressed, could result in the
inability of the rear spar lower chord to sustain limit loads,
resulting in reduced structural integrity of the airplane and possible
loss of control of the airplane.
Discussion of Final Airworthiness Directive
Comments
The FAA received comments from The Air Line Pilots Association,
International (ALPA), who supported the NPRM without change. The FAA
received comments from an individual that were outside the scope of
this rulemaking.
The FAA received an additional comment from Boeing. The following
[[Page 78531]]
presents the comment received on the NPRM and the FAA's response.
Effect of Winglets on Accomplishment of the Proposed Actions
Aviation Partners Boeing stated that accomplishing Supplemental
Type Certificate (STC) ST01219SE 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
ST01219SE does not affect the ability to accomplish the actions
required by this AD. Therefore, for airplanes on which STC ST01219SE 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 a Correction to Paragraph (h) of This AD
Boeing requested that a reference to ``paragraph (h) of this AD''
within paragraph (h) of this AD be corrected to read ``paragraph (i) of
this AD.'' Boeing noted that the reference should be to the exceptions
stated in paragraph (i) of this AD.
The FAA agrees with the request to correct the error. The reference
to ``paragraph (h) of this AD'' within paragraph (h) of this AD has
been corrected to read ``paragraph (i) of this AD.''
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 737-57A1353 RB,
dated February 10, 2022. This service information specifies procedures
for repetitive open hole HFEC inspections or surface HFEC and UT
inspections for cracking, and applicable on-condition actions. On-
condition actions include installing fasteners and repair. 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 69 airplanes of U.S.
registry. The FAA estimates the following costs to comply with this AD:
Estimated Costs
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Cost on U.S.
Action Labor cost Parts cost Cost per product operators
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Open hole HFEC inspection........ 30 work-hours x $85 $0 $2,550 per Up to $175,950 per
per hour = $2,550 inspection cycle. inspection cycle.
per inspection
cycle.
Surface HFEC/UT inspections...... 4 work-hours x $85 0 $340 per inspection Up to $23,460 per
per hour = $340 cycle. inspection cycle.
per inspection
cycle.
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The FAA estimates the following costs to do any necessary fastener
installations that would be required based on the results of the
inspection. The agency has no way of determining the number of aircraft
that might need these installations:
On-Condition Costs
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Cost per
Action Labor cost Parts cost product
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Install fasteners............................ 1 work-hour x $85 per hour = * $0 $85
$85.
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* The FAA has no definitive data on the parts costs for fasteners.
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 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.
[[Page 78532]]
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 adding the following new airworthiness
directive:
2022-25-15 The Boeing Company: Amendment 39-22271; Docket No. FAA-
2022-1061; Project Identifier AD-2022-00441-T.
(a) Effective Date
This airworthiness directive (AD) is effective January 26, 2023.
(b) Affected ADs
None.
(c) Applicability
(1) This AD applies to all The Boeing Company Model 737-100, -
200, -200C, -300, -400, and -500 series airplanes, certificated in
any category.
(2) Installation of Supplemental Type Certificate (STC)
ST01219SE does not affect the ability to accomplish the actions
required by this AD. Therefore, for airplanes on which STC ST01219SE
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 a report indicating that a crack was
found in one of the holes of the wing rear spar lower chord at the
main landing gear (MLG) aft fitting at wing buttock line (WBL) 157.
The FAA is issuing this AD to address cracking in the rear spar
lower chord at a fastener common to the MLG aft support fitting.
This condition, if not addressed, could result in the inability of
the rear spar lower chord to sustain limit loads, resulting in
reduced structural integrity of the airplane and possible loss of
control of the airplane.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Required Actions for Group 1 Airplanes
For airplanes identified as Group 1 in Boeing Alert Requirements
Bulletin 737-57A1353 RB, dated February 10, 2022: Within 120 days
after the effective date of this AD, inspect the airplane and do all
applicable on-condition actions using a method approved in
accordance with the procedures specified in paragraph (j) of this
AD.
(h) Required Actions for Group 2 and Group 3 Airplanes
For airplanes identified as Group 2 and Group 3 in Boeing Alert
Requirements Bulletin 737-57A1353 RB, dated February 10, 2022:
Except as specified by paragraph (i) of this AD, at the applicable
times specified in the ``Compliance'' paragraph of Boeing Alert
Requirements Bulletin 737-57A1353 RB, dated February 10, 2022, do
all applicable actions identified in, and in accordance with, the
Accomplishment Instructions of Boeing Alert Requirements Bulletin
737-57A1353 RB, dated February 10, 2022.
Note 1 to paragraph (h): Guidance for accomplishing the actions
required by this AD can be found in Boeing Alert Service Bulletin
737-57A1353, dated February 10, 2022, which is referred to in Boeing
Alert Requirements Bulletin 737-57A1353 RB, dated February 10, 2022.
(i) Exceptions to Service Information Specifications
(1) Where the Compliance Time columns of the tables in the
``Compliance'' paragraph of Boeing Alert Requirements Bulletin 737-
57A1353 RB, dated February 10, 2022, use the phrase ``the original
issue date of Requirements Bulletin 737-57A1353 RB,'' this AD
requires using ``the effective date of this AD.''
(2) Where Boeing Alert Requirements Bulletin 737-57A1353 RB,
dated February 10, 2022, 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.
(j) Alternative Methods of Compliance (AMOCs)
(1) The Manager, Los Angeles ACO Branch, FAA, has the authority
to approve AMOCs for this AD, if requested using the procedures
found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your
request to your principal inspector or responsible Flight Standards
Office, as appropriate. If sending information directly to the
manager of the certification office, send it to the attention of the
person identified in paragraph (k) of this AD. Information may be
emailed to: <a href="/cdn-cgi/l/email-protection#ffc6d2beb1b2d2b3bebebcb0d2beb2b0bcd2ad9a8e8a9a8c8b8cbf999e9ed1989089"><span class="__cf_email__" data-cfemail="330a1e727d7e1e7f7272707c1e727e7c701e6156424656404740735552521d545c45">[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.
(k) Related Information
For more information about this AD, contact Wayne Ha, Aerospace
Engineer, Airframe Section, FAA, Los Angeles ACO Branch, 3960
Paramount Boulevard, Lakewood, CA 90712-4137; phone: 562-627-5238;
email: <a href="/cdn-cgi/l/email-protection#1364726a7d763d7b72537572723d747c65"><span class="__cf_email__" data-cfemail="d8afb9a1b6bdf6b0b998beb9b9f6bfb7ae">[email protected]</span></a>.
(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 737-57A1353 RB, dated
February 10, 2022.
(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="http://myboeingfleet.com">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, <a href="/cdn-cgi/l/email-protection#3f594d1156514c4f5a5c4b5650517f515e4d5e11585049"><span class="__cf_email__" data-cfemail="0365712d6a6d70736660776a6c6d436d6271622d646c75">[email protected]</span></a>, or go to: <a href="http://www.archives.gov/federal-register/cfr/ibr-locations.html">www.archives.gov/federal-register/cfr/ibr-locations.html</a>.
Issued on November 30, 2022.
Christina Underwood,
Acting Director, Compliance & Airworthiness Division, Aircraft
Certification Service.
[FR Doc. 2022-27751 Filed 12-21-22; 8:45 am]
BILLING CODE 4910-13-P
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