Airworthiness Directives; The Boeing Company Airplanes, 10441-10444 [2021-01851]
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Federal Register / Vol. 86, No. 33 / Monday, February 22, 2021 / Rules and Regulations
Subpart F—Farm Loan Programs Debt
Settlement
2. Amend § 761.403 by revising
paragraph (c)(3) to read as follows:
■
§ 761.403
General.
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(c) * * *
(3) The debtor’s account is involved
in a fiscal irregularity investigation in
which final action has not been taken or
the account shows evidence that a
shortage may exist and an investigation
will be requested.
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Steven Peterson,
Acting Administrator, Farm Service Agency.
[FR Doc. 2021–03186 Filed 2–19–21; 8:45 am]
BILLING CODE 3410–05–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2020–0459; Product
Identifier 2020–NM–049–AD; Amendment
39–21380; AD 2021–01–04]
RIN 2120–AA64
Airworthiness Directives; The Boeing
Company Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
The FAA is adopting a new
airworthiness directive (AD) for all The
Boeing Company Model 737 series
airplanes, excluding Model 737–100,
–200, –200C, –300, –400, and –500
series airplanes. This AD was prompted
by reports of cracked or completely
severed lugs in the upper aft corner stop
fitting assembly of the forward entry
door. This AD requires an inspection, a
measurement, or a records check of that
assembly to determine the part number,
and replacement if a certain part is
found. The FAA is issuing this AD to
address the unsafe condition on these
products.
SUMMARY:
This AD is effective March 29,
2021.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in this AD
as of March 29, 2021.
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;
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DATES:
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telephone 562–797–1717; internet
https://www.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 on the internet at
https://www.regulations.gov by
searching for and locating Docket No.
FAA–2020–0459.
Discussion of Final Airworthiness
Directive
Examining the AD Docket
You may examine the AD docket on
the internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2020–
0459; 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:
Michael Bumbaugh, Aerospace
Engineer, Airframe Section, FAA,
Seattle ACO Branch, 2200 South 216th
St., Des Moines, WA 98198; phone and
fax: 206–231–3522; email:
michael.bumbaugh@faa.gov.
SUPPLEMENTARY INFORMATION:
Aviation Partners Boeing stated that
the installation of winglets per
Supplemental Type Certificate (STC)
ST00830SE does not affect compliance
with the proposed actions.
The FAA agrees that the installation
of winglets per STC ST00830SE would
not affect the ability to replace the
affected stop fitting assembly with a
newly designed stop fitting assembly as
required by this AD. Operators of
airplanes with these winglets do not
need to request a ‘‘change in product’’
alternative method of compliance
(AMOC) approval as specified in 14 CFR
39.17. The FAA has redesignated
paragraph (c) of the proposed AD as
paragraph (c)(1) of this AD, and added
paragraph (c)(2) accordingly.
Discussion
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 series airplanes, excluding Model
737–100, –200, –200C, –300, –400, and
–500 series airplanes. The NPRM
published in the Federal Register on
June 3, 2020 (85 FR 34136). The NPRM
was prompted by reports of cracked or
completely severed lugs in the upper aft
corner stop fitting assembly of the
forward entry door. Analysis of the
design of the stop fitting assembly
revealed that undersized wall thickness
of the lug made it susceptible to fatigue
cracking, which may result in the
forward entry door being unable to
sustain limit load. In the NPRM, the
FAA proposed to require an inspection,
a measurement, or a records check of
that assembly to determine the part
number, and replacement if a certain
part-numbered assembly is installed.
The FAA is issuing this AD to address
cracked or completely severed lugs,
which could result in reduced structural
integrity of the forward entry door and
consequent rapid decompression of the
airplane.
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Comments
The FAA received comments from
four commenters. 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
Request for Compliance Actions at the
Component Level
Southwest Airlines (SWA) asked that
the compliance actions be reported at
the component level due to the
interchangeability of the forward entry
doors between the Model 737 NG and
737 MAX fleets.
The FAA infers that the commenter is
requesting that the AD’s applicability
point towards the component parts,
rather than the airplane. The FAA
acknowledges that the component most
likely to be rotated is the forward entry
door because doors are likely removed
with the stop fittings intact. However,
the FAA disagrees with changing the
applicability of this AD because the
unsafe condition is related to the stop
fitting assembly and an affected stop
fitting assembly may be installed on a
forward entry door of any airplane
identified in paragraph (c) of this AD. In
addition, paragraph (i) of this AD, ‘‘Parts
Installation Prohibition,’’ states that no
person may install a forward entry door
that has a stop fitting assembly with part
number (P/N) 141A6104–3 on any
airplane. The FAA used this language
because doors are often rotated among
aircraft with the stop fitting assembly
already installed. The FAA has therefore
determined that an airplane-level
applicability is appropriate and has not
changed this AD in this regard.
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Federal Register / Vol. 86, No. 33 / Monday, February 22, 2021 / Rules and Regulations
Request for Clarification of Compliance
Time
SWA asked for clarification of the
reference in paragraph (g) of the
proposed AD to the applicable times
specified in the ‘‘Compliance’’
paragraph of Boeing Alert Requirements
Bulletin 737–52A1180 RB, dated
January 24, 2020. SWA asked if once it
is determined that a P/N 141A6104–3
fitting is installed on a door through
records or survey, the fitting must be
replaced before further flight or whether
it can be replaced at a later date as long
as the door is still within its required
compliance time per the referenced
service information.
‘‘Table 1: Forward Entry Door Number
7 Stop Fitting Assembly Inspection’’ of
Paragraph 3., ‘‘Compliance’’ of Boeing
Service Bulletin 737–52A1180, dated
January 24, 2020, gives the compliance
time for replacing the P/N 141A6104–3
fitting if found. The compliance time is
before 10,000 total flight cycles on the
forward entry door, or within 5,000
forward entry door flight cycles after the
original issue date of Boeing Alert
Requirements Bulletin 737–52A1180
RB, dated January 24, 2020, whichever
occurs later. However, under paragraph
(h) of this AD, the date for determining
compliance time is the effective date of
this AD, and not the issue date of the
bulletin. Therefore, the FAA clarifies
that if the compliance time has not yet
been reached, then the fitting does not
need to be replaced before further flight.
The FAA has not changed this AD in
this regard.
tkelley on DSKBCP9HB2PROD with RULES
Request To Change Parts Installation
Prohibition Paragraph
SWA asked that the FAA reword
paragraph (i) of the proposed AD to
require compliance with the service
information before installation of the
fitting instead of prohibiting installation
of the fitting.
The intent of paragraph (i) of this AD
is to prohibit installation of an affected
part on an airplane with a compliance
time for this prohibition related to the
airplane configuration and whether the
actions specified in Boeing Alert
Requirements Bulletin 737–52A1180
RB, dated January 24, 2020, must be
accomplished on that airplane. The
FAA has not made the changes
requested by the commenter. However,
the FAA has revised paragraph (i) of this
AD to clarify that, for any airplane
required to accomplish the actions
required by paragraph (g) of this AD, the
parts installation prohibition does not
take effect until the applicable actions
required by paragraph (g) of this AD
have been accomplished on that
airplane. For airplanes having an
original airworthiness certificate or
original export certificate of
airworthiness dated after the effective
date of this AD, the parts installation
prohibition continues to be applicable
as of the effective date of this AD.
Request for Correction of Error in
Service Information
AIRDO requested the FAA correct an
error in the service information
incorporated by reference in paragraph
(g) of the proposed AD. AIRDO noted
that page 13 of Boeing Alert
Requirements Bulletin 737–52A1180
RB, dated January 24, 2020, refers to the
procedures in ‘‘SB 747–52A1180’’ when
the correct reference is ‘‘SB 737–
52A1180.’’
The FAA agrees with the commenter’s
request. The FAA has added paragraph
(h)(3) of this AD to clarify the correct
service information reference.
Request To Limit the Applicability
American Airlines (AA) and AIRDO
requested the FAA limit the
applicability of the proposed AD to the
line numbers (L/Ns) identified in the
effectivity of Boeing Alert Service
Bulletin 737–52A1180, dated January
24, 2020. AA stated that because the
aircraft illustrated parts catalog (IPC)
does not allow for the unsafe part to be
installed on aircraft beyond L/N 1075,
or on the door assemblies allowed to be
installed on aircraft beyond L/N 1075,
including all Model 737–600, –700,
–700C, –800, –900, and –900ER series
airplanes in the applicability of the
proposed AD is unnecessarily
redundant. AIRDO stated Boeing has not
allowed operators to install P/Ns
141A6104–3, 141A6150–1, 141A6150–
2, and 141A6100–678 on airplanes other
than those with L/N 1–1075 per the IPC
and related drawings. AIRDO also stated
that if the fitting or the door assembly
must be replaced, operators will check
the IPC and drawing to confirm if the
affected part number can be used on the
specific airplane. AIRDO stated that
based on this general protocol, even
though the fitting and door assembly are
physically interchangeable, a suspected
fitting and door assembly cannot be
installed on airplanes having L/N 1076
and subsequent.
The FAA does not agree with the
requests to limit the applicability. Both
the stop fitting assemblies and the doors
they are installed on are physically
interchangeable among the airplane
models listed in the applicability of this
AD. The FAA has determined it is
necessary to ensure these rotable parts
will not be introduced on other
airplanes by including these airplanes
in the applicability of this AD.
Therefore, the FAA has not changed this
AD in this regard.
Conclusion
The FAA reviewed the relevant data,
considered the 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 in these
products. Except for the 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 737–52A1180
RB, dated January 24, 2020. The service
information specifies procedures for an
inspection, a measurement, or a records
check of the upper aft corner stop fitting
assembly to determine the part number,
and applicable on-condition actions.
The on-condition action is to replace the
affected stop fitting assembly with a
newly designed stop fitting assembly
that has improved wall thickness and
strength. This service information is
reasonably available because the
interested parties have access to it
through their normal course of business
or by the means identified in the
ADDRESSES section.
Costs of Compliance
The FAA estimates that this AD
affects 1,075 airplanes of U.S. registry.
The FAA estimates the following costs
to comply with this AD:
ESTIMATED COSTS FOR REQUIRED ACTIONS
Action
Labor cost
Inspection and part replacement ..
Up to 4 work-hours × $85 per hour = Up to $340 ...
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Parts cost
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$4,640
E:\FR\FM\22FER1.SGM
Cost per
product
Cost on U.S.
operators
Up to $4,980 ....
Up to $5,353,500.
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Federal Register / Vol. 86, No. 33 / Monday, February 22, 2021 / Rules and Regulations
The FAA has included all known
costs in the cost estimate. According to
the manufacturer, however, some or all
of the costs of this AD may be covered
under warranty, thereby reducing the
cost impact on affected operators.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by adding
the following new airworthiness
directive:
■
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.
2021–01–04 The Boeing Company:
Amendment 39–21380; Docket No.
FAA–2020–0459; Product Identifier
2020–NM–049–AD.
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.
(d) Subject
Air Transport Association (ATA) of
America Code 52, Doors.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
tkelley on DSKBCP9HB2PROD with RULES
Authority: 49 U.S.C. 106(g), 40113, 44701.
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:
■
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(a) Effective Date
This airworthiness directive (AD) is
effective March 29, 2021.
(b) Affected ADs
None.
(c) Applicability
(1) This AD applies to all The Boeing
Company Model 737 series airplanes,
excluding Model 737–100, –200, –200C,
–300, –400, and –500 series airplanes,
certificated in any category.
(2) Installation of Supplemental Type
Certificate (STC) ST00830SE does not affect
the ability to accomplish the actions required
by this AD. Therefore, for airplanes on which
STC ST00830SE 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.
(e) Unsafe Condition
This AD was prompted by reports of
cracked or completely severed lugs in the
stop fitting assembly of the forward entry
door. The FAA is issuing this AD to address
such cracking or severing, which could result
in reduced structural integrity of the forward
entry door and consequent rapid
decompression of the airplane.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Required Actions
For airplanes having a date of issuance of
the original airworthiness certificate or date
of issuance of the original export certificate
of airworthiness on or before the effective
date of this AD: Except as specified by
paragraph (h) of this AD, at the applicable
times specified in the ‘‘Compliance’’
paragraph of Boeing Alert Requirements
Bulletin 737–52A1180 RB, dated January 24,
2020, do all applicable actions identified in,
and in accordance with, the Accomplishment
Instructions of Boeing Alert Requirements
Bulletin 737–52A1180 RB, dated January 24,
2020.
Note 1 to paragraph (g): Guidance for
accomplishing the actions required by this
AD can be found in Boeing Alert Service
Bulletin 737–52A1180, dated January 24,
2020, which is referred to in Boeing Alert
Requirements Bulletin 737–52A1180 RB,
dated January 24, 2020.
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10443
(h) Exceptions to Service Information
Specifications
(1) Where Boeing Alert Requirements
Bulletin 737–52A1180 RB, dated January 24,
2020, uses the phrase ‘‘the original issue date
of Requirements Bulletin 737–52A1180 RB,’’
this AD requires using ‘‘the effective date of
this AD.’’
(2) Where Boeing Alert Requirements
Bulletin 737–52A1180 RB, dated January 24,
2020, specifies contacting Boeing for repair
instructions: This AD requires doing the
repair before further flight using a method
approved in accordance with the procedures
specified in paragraph (j) of this AD.
(3) Where the heading in Table 1 of the
Accomplishment Instructions in Boeing Alert
Requirements Bulletin 737–52A1180 RB,
dated January 24, 2020, identifies ‘‘SB 747–
52A1180,’’ the correct reference for this AD
is ‘‘SB 737–52A1180.’’
(i) Parts Installation Prohibition
No person may install a stop fitting
assembly with part number 141A6104–3 or a
forward entry door that has a stop fitting
assembly with part number 141A6104–3, on
any airplane, as of the applicable time
specified in paragraph (i)(1), (2), or (3) of this
AD.
(1) For airplanes having an original
airworthiness certificate or original export
certificate of airworthiness dated after the
effective date of this AD: As of the effective
date of this AD.
(2) For airplanes on which it is determined
a stop fitting assembly with part number
141A6104–3 is not installed, as required by
paragraph (g) of this AD: After accomplishing
the inspection, records check, or
measurement required by paragraph (g) of
this AD.
(3) For airplanes on which it is determined
a stop fitting assembly with part number
141A6104–3 is installed, as required by
paragraph (g) of this AD: After accomplishing
the replacement required by paragraph (g) of
this AD.
(j) Alternative Methods of Compliance
(AMOCs)
(1) The Manager, Seattle 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 local Flight Standards
District 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: 9ANM-Seattle-ACO-AMOC-Requests@faa.gov.
(2) Before using any approved AMOC,
notify your appropriate principal inspector,
or lacking a principal inspector, the manager
of the local flight standards district office/
certificate holding district 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, Seattle ACO Branch, FAA, to make
those findings. To be approved, the repair
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Federal Register / Vol. 86, No. 33 / Monday, February 22, 2021 / Rules and Regulations
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 Michael Bumbaugh, Aerospace
Engineer, Airframe Section, FAA, Seattle
ACO Branch, 2200 South 216th St., Des
Moines, WA 98198; phone and fax: 206–231–
3522; email: michael.bumbaugh@faa.gov.
(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
737–52A1180 RB, dated January 24, 2020.
(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 https://
www.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 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 fedreg.legal@nara.gov, or go to: https://
www.archives.gov/federal-register/cfr/ibrlocations.html.
Issued on December 28, 2020.
Lance T. Gant,
Director, Compliance & Airworthiness
Division, Aircraft Certification Service.
[FR Doc. 2021–01851 Filed 2–19–21; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
tkelley on DSKBCP9HB2PROD with RULES
[Docket No. FAA–2020–1109; Product
Identifier 2020–NM–067–AD; Amendment
39–21383; AD 2021–01–07]
RIN 2120–AA64
Airworthiness Directives; The Boeing
Company Airplanes
Federal Aviation
Administration (FAA), DOT.
AGENCY:
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Final rule; request for
comments.
ACTION:
The FAA is adopting a new
airworthiness directive (AD) for certain
The Boeing Company Model 737–700
series airplanes. This AD requires
repetitive testing to verify correct
operation of the smoke clearance mode
of the equipment cooling system and
low pressure environmental control
system, and corrective actions if
necessary. This AD also requires
installing new relays and changing the
wiring to the environmental control
system, among other actions. This AD
was prompted by a determination that a
repetitive test is needed to assess the
components on airplanes equipped with
a certain air distribution system
configuration. The FAA is issuing this
AD to address the unsafe condition on
these products.
SUMMARY:
This AD is effective March 9,
2021.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in this AD
as of March 9, 2021.
The FAA must receive comments on
this AD by April 8, 2021.
DATES:
You may send comments,
using the procedures found in 14 CFR
11.43 and 11.45, by any of the following
methods:
• Federal eRulemaking Portal: Go to
https://www.regulations.gov. Follow the
instructions for submitting comments.
• Fax: 202–493–2251.
• Mail: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue SE,
Washington, DC 20590.
• Hand Delivery: Deliver to Mail
address above between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays.
For service information identified in
this final rule, contact Boeing
Commercial Airplanes, Attention:
Contractual & Data Services (C&DS),
2600 Westminster Blvd., MC 110–SK57,
Seal Beach, CA 90740–5600; telephone
562–797–1717; internet https://
www.myboeingfleet.com. 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 on the internet at
https://www.regulations.gov by
searching for and locating Docket No.
FAA–2020–1109.
ADDRESSES:
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Examining the AD Docket
You may examine the AD docket on
the internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2020–
1109; or in person at Docket Operations
between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
The AD docket contains this final rule,
any comments received, and other
information. The street address for
Docket Operations is listed above.
Comments will be available in the AD
docket shortly after receipt.
FOR FURTHER INFORMATION CONTACT:
Susan L. Monroe, Aerospace Engineer,
Cabin Safety and Environmental
Systems Section, FAA, Seattle ACO
Branch, 2200 South 216th St., Des
Moines, WA 98198; phone and fax: 206–
231–3570; email: susan.l.monroe@
faa.gov.
SUPPLEMENTARY INFORMATION:
Discussion
The FAA has determined that a
repetitive test is needed to assess the
components on airplanes equipped with
a certain air distribution system
configuration. A review by Boeing
found that there was no maintenance
procedure available to assess the
components used to reconfigure the air
distribution system to the cargo fire
mode. Without the repetitive test,
failures of components could be latent
for extended periods. This condition, if
not addressed, could result in latent
failures of the equipment cooling system
and low pressure environmental control
system, which, in combination with a
cargo fire event, could result in smoke
in the flight deck and/or main cabin,
and possible loss of aircraft control.
Other Related Rulemaking
The FAA issued AD 2016–04–06,
Amendment 39–18400 (81 FR 9756,
February 26, 2016) (AD 2016–04–06),
applicable to all The Boeing Company
Model 737–600, –700, –700C, –800,
–900, and –900ER series airplanes. That
AD requires doing repetitive testing to
verify correct operation of the
equipment cooling system and low
pressure environmental control system,
and corrective actions if necessary. That
AD also requires, for certain airplanes,
installing new relays and changing the
wiring to the environmental control
system. That AD was prompted by a
determination that a repetitive test is
needed to inspect the components on
airplanes equipped with a certain air
distribution system configuration. The
actions required by that AD are
intended to address latent failures of the
equipment cooling system and low
E:\FR\FM\22FER1.SGM
22FER1
]]>Agencies
[Federal Register Volume 86, Number 33 (Monday, February 22, 2021)]
[Rules and Regulations]
[Pages 10441-10444]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2021-01851]
=======================================================================
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2020-0459; Product Identifier 2020-NM-049-AD; Amendment
39-21380; AD 2021-01-04]
RIN 2120-AA64
Airworthiness Directives; The Boeing Company Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule.
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SUMMARY: The FAA is adopting a new airworthiness directive (AD) for all
The Boeing Company Model 737 series airplanes, excluding Model 737-100,
-200, -200C, -300, -400, and -500 series airplanes. This AD was
prompted by reports of cracked or completely severed lugs in the upper
aft corner stop fitting assembly of the forward entry door. This AD
requires an inspection, a measurement, or a records check of that
assembly to determine the part number, and replacement if a certain
part is found. The FAA is issuing this AD to address the unsafe
condition on these products.
DATES: This AD is effective March 29, 2021.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in this AD as of March 29,
2021.
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 https://www.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 on
the internet at https://www.regulations.gov by searching for and
locating Docket No. FAA-2020-0459.
Examining the AD Docket
You may examine the AD docket on the internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2020-
0459; 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: Michael Bumbaugh, Aerospace Engineer,
Airframe Section, FAA, Seattle ACO Branch, 2200 South 216th St., Des
Moines, WA 98198; phone and fax: 206-231-3522; email:
[email protected].
SUPPLEMENTARY INFORMATION:
Discussion
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 series airplanes, excluding Model 737-100, -200, -200C, -300,
-400, and -500 series airplanes. The NPRM published in the Federal
Register on June 3, 2020 (85 FR 34136). The NPRM was prompted by
reports of cracked or completely severed lugs in the upper aft corner
stop fitting assembly of the forward entry door. Analysis of the design
of the stop fitting assembly revealed that undersized wall thickness of
the lug made it susceptible to fatigue cracking, which may result in
the forward entry door being unable to sustain limit load. In the NPRM,
the FAA proposed to require an inspection, a measurement, or a records
check of that assembly to determine the part number, and replacement if
a certain part-numbered assembly is installed.
The FAA is issuing this AD to address cracked or completely severed
lugs, which could result in reduced structural integrity of the forward
entry door and consequent rapid decompression of the airplane.
Discussion of Final Airworthiness Directive
Comments
The FAA received comments from four commenters. 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 stated that the installation of winglets
per Supplemental Type Certificate (STC) ST00830SE does not affect
compliance with the proposed actions.
The FAA agrees that the installation of winglets per STC ST00830SE
would not affect the ability to replace the affected stop fitting
assembly with a newly designed stop fitting assembly as required by
this AD. Operators of airplanes with these winglets do not need to
request a ``change in product'' alternative method of compliance (AMOC)
approval as specified in 14 CFR 39.17. The FAA has redesignated
paragraph (c) of the proposed AD as paragraph (c)(1) of this AD, and
added paragraph (c)(2) accordingly.
Request for Compliance Actions at the Component Level
Southwest Airlines (SWA) asked that the compliance actions be
reported at the component level due to the interchangeability of the
forward entry doors between the Model 737 NG and 737 MAX fleets.
The FAA infers that the commenter is requesting that the AD's
applicability point towards the component parts, rather than the
airplane. The FAA acknowledges that the component most likely to be
rotated is the forward entry door because doors are likely removed with
the stop fittings intact. However, the FAA disagrees with changing the
applicability of this AD because the unsafe condition is related to the
stop fitting assembly and an affected stop fitting assembly may be
installed on a forward entry door of any airplane identified in
paragraph (c) of this AD. In addition, paragraph (i) of this AD,
``Parts Installation Prohibition,'' states that no person may install a
forward entry door that has a stop fitting assembly with part number
(P/N) 141A6104-3 on any airplane. The FAA used this language because
doors are often rotated among aircraft with the stop fitting assembly
already installed. The FAA has therefore determined that an airplane-
level applicability is appropriate and has not changed this AD in this
regard.
[[Page 10442]]
Request for Clarification of Compliance Time
SWA asked for clarification of the reference in paragraph (g) of
the proposed AD to the applicable times specified in the ``Compliance''
paragraph of Boeing Alert Requirements Bulletin 737-52A1180 RB, dated
January 24, 2020. SWA asked if once it is determined that a P/N
141A6104-3 fitting is installed on a door through records or survey,
the fitting must be replaced before further flight or whether it can be
replaced at a later date as long as the door is still within its
required compliance time per the referenced service information.
``Table 1: Forward Entry Door Number 7 Stop Fitting Assembly
Inspection'' of Paragraph 3., ``Compliance'' of Boeing Service Bulletin
737-52A1180, dated January 24, 2020, gives the compliance time for
replacing the P/N 141A6104-3 fitting if found. The compliance time is
before 10,000 total flight cycles on the forward entry door, or within
5,000 forward entry door flight cycles after the original issue date of
Boeing Alert Requirements Bulletin 737-52A1180 RB, dated January 24,
2020, whichever occurs later. However, under paragraph (h) of this AD,
the date for determining compliance time is the effective date of this
AD, and not the issue date of the bulletin. Therefore, the FAA
clarifies that if the compliance time has not yet been reached, then
the fitting does not need to be replaced before further flight. The FAA
has not changed this AD in this regard.
Request To Change Parts Installation Prohibition Paragraph
SWA asked that the FAA reword paragraph (i) of the proposed AD to
require compliance with the service information before installation of
the fitting instead of prohibiting installation of the fitting.
The intent of paragraph (i) of this AD is to prohibit installation
of an affected part on an airplane with a compliance time for this
prohibition related to the airplane configuration and whether the
actions specified in Boeing Alert Requirements Bulletin 737-52A1180 RB,
dated January 24, 2020, must be accomplished on that airplane. The FAA
has not made the changes requested by the commenter. However, the FAA
has revised paragraph (i) of this AD to clarify that, for any airplane
required to accomplish the actions required by paragraph (g) of this
AD, the parts installation prohibition does not take effect until the
applicable actions required by paragraph (g) of this AD have been
accomplished on that airplane. For airplanes having an original
airworthiness certificate or original export certificate of
airworthiness dated after the effective date of this AD, the parts
installation prohibition continues to be applicable as of the effective
date of this AD.
Request for Correction of Error in Service Information
AIRDO requested the FAA correct an error in the service information
incorporated by reference in paragraph (g) of the proposed AD. AIRDO
noted that page 13 of Boeing Alert Requirements Bulletin 737-52A1180
RB, dated January 24, 2020, refers to the procedures in ``SB 747-
52A1180'' when the correct reference is ``SB 737-52A1180.''
The FAA agrees with the commenter's request. The FAA has added
paragraph (h)(3) of this AD to clarify the correct service information
reference.
Request To Limit the Applicability
American Airlines (AA) and AIRDO requested the FAA limit the
applicability of the proposed AD to the line numbers (L/Ns) identified
in the effectivity of Boeing Alert Service Bulletin 737-52A1180, dated
January 24, 2020. AA stated that because the aircraft illustrated parts
catalog (IPC) does not allow for the unsafe part to be installed on
aircraft beyond L/N 1075, or on the door assemblies allowed to be
installed on aircraft beyond L/N 1075, including all Model 737-600, -
700, -700C, -800, -900, and -900ER series airplanes in the
applicability of the proposed AD is unnecessarily redundant. AIRDO
stated Boeing has not allowed operators to install P/Ns 141A6104-3,
141A6150-1, 141A6150-2, and 141A6100-678 on airplanes other than those
with L/N 1-1075 per the IPC and related drawings. AIRDO also stated
that if the fitting or the door assembly must be replaced, operators
will check the IPC and drawing to confirm if the affected part number
can be used on the specific airplane. AIRDO stated that based on this
general protocol, even though the fitting and door assembly are
physically interchangeable, a suspected fitting and door assembly
cannot be installed on airplanes having L/N 1076 and subsequent.
The FAA does not agree with the requests to limit the
applicability. Both the stop fitting assemblies and the doors they are
installed on are physically interchangeable among the airplane models
listed in the applicability of this AD. The FAA has determined it is
necessary to ensure these rotable parts will not be introduced on other
airplanes by including these airplanes in the applicability of this AD.
Therefore, the FAA has not changed this AD in this regard.
Conclusion
The FAA reviewed the relevant data, considered the 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 in these products. Except for the 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 737-52A1180 RB,
dated January 24, 2020. The service information specifies procedures
for an inspection, a measurement, or a records check of the upper aft
corner stop fitting assembly to determine the part number, and
applicable on-condition actions. The on-condition action is to replace
the affected stop fitting assembly with a newly designed stop fitting
assembly that has improved wall thickness and strength. This service
information is reasonably available because the interested parties have
access to it through their normal course of business or by the means
identified in the ADDRESSES section.
Costs of Compliance
The FAA estimates that this AD affects 1,075 airplanes of U.S.
registry. The FAA estimates the following costs to comply with this AD:
Estimated Costs for Required Actions
----------------------------------------------------------------------------------------------------------------
Action Labor cost Parts cost Cost per product Cost on U.S. operators
----------------------------------------------------------------------------------------------------------------
Inspection and part Up to 4 work- $4,640 Up to $4,980......... Up to $5,353,500.
replacement. hours x $85 per
hour = Up to
$340.
----------------------------------------------------------------------------------------------------------------
[[Page 10443]]
The FAA has included all known costs in the cost estimate.
According to the manufacturer, however, some or all of the costs of
this AD may be covered under warranty, thereby reducing the cost impact
on affected operators.
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 adding the following new airworthiness
directive:
2021-01-04 The Boeing Company: Amendment 39-21380; Docket No. FAA-
2020-0459; Product Identifier 2020-NM-049-AD.
(a) Effective Date
This airworthiness directive (AD) is effective March 29, 2021.
(b) Affected ADs
None.
(c) Applicability
(1) This AD applies to all The Boeing Company Model 737 series
airplanes, excluding Model 737-100, -200, -200C, -300, -400, and -
500 series airplanes, certificated in any category.
(2) Installation of Supplemental Type Certificate (STC)
ST00830SE does not affect the ability to accomplish the actions
required by this AD. Therefore, for airplanes on which STC ST00830SE
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 52, Doors.
(e) Unsafe Condition
This AD was prompted by reports of cracked or completely severed
lugs in the stop fitting assembly of the forward entry door. The FAA
is issuing this AD to address such cracking or severing, which could
result in reduced structural integrity of the forward entry door and
consequent rapid decompression of the airplane.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Required Actions
For airplanes having a date of issuance of the original
airworthiness certificate or date of issuance of the original export
certificate of airworthiness on or before the effective date of this
AD: Except as specified by paragraph (h) of this AD, at the
applicable times specified in the ``Compliance'' paragraph of Boeing
Alert Requirements Bulletin 737-52A1180 RB, dated January 24, 2020,
do all applicable actions identified in, and in accordance with, the
Accomplishment Instructions of Boeing Alert Requirements Bulletin
737-52A1180 RB, dated January 24, 2020.
Note 1 to paragraph (g): Guidance for accomplishing the actions
required by this AD can be found in Boeing Alert Service Bulletin
737-52A1180, dated January 24, 2020, which is referred to in Boeing
Alert Requirements Bulletin 737-52A1180 RB, dated January 24, 2020.
(h) Exceptions to Service Information Specifications
(1) Where Boeing Alert Requirements Bulletin 737-52A1180 RB,
dated January 24, 2020, uses the phrase ``the original issue date of
Requirements Bulletin 737-52A1180 RB,'' this AD requires using ``the
effective date of this AD.''
(2) Where Boeing Alert Requirements Bulletin 737-52A1180 RB,
dated January 24, 2020, specifies contacting Boeing for repair
instructions: This AD requires doing the repair before further
flight using a method approved in accordance with the procedures
specified in paragraph (j) of this AD.
(3) Where the heading in Table 1 of the Accomplishment
Instructions in Boeing Alert Requirements Bulletin 737-52A1180 RB,
dated January 24, 2020, identifies ``SB 747-52A1180,'' the correct
reference for this AD is ``SB 737-52A1180.''
(i) Parts Installation Prohibition
No person may install a stop fitting assembly with part number
141A6104-3 or a forward entry door that has a stop fitting assembly
with part number 141A6104-3, on any airplane, as of the applicable
time specified in paragraph (i)(1), (2), or (3) of this AD.
(1) For airplanes having an original airworthiness certificate
or original export certificate of airworthiness dated after the
effective date of this AD: As of the effective date of this AD.
(2) For airplanes on which it is determined a stop fitting
assembly with part number 141A6104-3 is not installed, as required
by paragraph (g) of this AD: After accomplishing the inspection,
records check, or measurement required by paragraph (g) of this AD.
(3) For airplanes on which it is determined a stop fitting
assembly with part number 141A6104-3 is installed, as required by
paragraph (g) of this AD: After accomplishing the replacement
required by paragraph (g) of this AD.
(j) Alternative Methods of Compliance (AMOCs)
(1) The Manager, Seattle 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 local Flight Standards District
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 local flight standards district office/certificate holding
district 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, Seattle
ACO Branch, FAA, to make those findings. To be approved, the repair
[[Page 10444]]
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 Michael
Bumbaugh, Aerospace Engineer, Airframe Section, FAA, Seattle ACO
Branch, 2200 South 216th St., Des Moines, WA 98198; phone and fax:
206-231-3522; email: [email protected].
(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 737-52A1180 RB, dated
January 24, 2020.
(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 https://www.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 service information that is incorporated
by reference at the National Archives and Records Administration
(NARA). For information on the availability of this material at
NARA, email [email protected], or go to: https://www.archives.gov/federal-register/cfr/ibr-locations.html.
Issued on December 28, 2020.
Lance T. Gant,
Director, Compliance & Airworthiness Division, Aircraft Certification
Service.
[FR Doc. 2021-01851 Filed 2-19-21; 8:45 am]
BILLING CODE 4910-13-P
