Airworthiness Directives; The Boeing Company Airplanes, 73706-73708 [2021-28181]
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Federal Register / Vol. 86, No. 246 / Tuesday, December 28, 2021 / Proposed Rules
(j) Parts Installation Prohibition
As of the effective date of this AD, no
person may install on any helicopter a
FADEC identified in paragraph (c) of this AD
(affected FADEC part).
Note 2 to paragraph (j): Removal of an
affected FADEC part from a helicopter and
reinstallation of that same affected FADEC
part on the same helicopter during the same
maintenance visit is not considered ‘‘install’’
as specified in paragraph (j) of this AD.
(k) Special Flight Permits
(l) Alternative Methods of Compliance
(AMOCs)
(1) The Manager, International Validation
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 International Validation
Branch, send it to the attention of the person
identified in paragraph (m)(1) of this AD.
Information may be emailed to: 9-AVS-AIR730-AMOC@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.
khammond on DSKJM1Z7X2PROD with PROPOSALS
(m) Related Information
(1) For more information about this AD,
contact Andrea Jimenez, Aerospace Engineer,
COS Program Management Section,
Operational Safety Branch, Compliance &
Airworthiness Division, FAA, 1600 Stewart
Ave., Suite 410, Westbury, NY 11590;
telephone (516) 228–7330; email
andrea.jimenez@faa.gov.
(2) For Airbus Helicopters service
information identified in this AD, contact
Airbus Helicopters, 2701 N Forum Drive,
Grand Prairie, TX 75052; telephone (972)
641–0000 or (800) 232–0323; fax (972) 641–
3775; or at https://www.airbus.com/
helicopters/services/technical-support.html.
For Safran Turbomeca service information
identified in this AD, contact Safran
Helicopter Engines, S.A., 64511 Bordes,
France; phone: +33 (0) 5 59 74 45 11. You
may view this referenced service information
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.
(3) The subject of this AD is addressed in
European Union Aviation Safety Agency
(EASA) AD 2021–0195, dated August 20,
2021. You may view the EASA AD on the
internet at https://www.regulations.gov in
Docket No. FAA–2021–1166.
21:04 Dec 27, 2021
[FR Doc. 2021–28132 Filed 12–27–21; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
Special flight permits may be issued to
operate the helicopter to a location where the
actions specified in this AD can be
performed, provided no passengers are
onboard.
VerDate Sep<11>2014
Issued on December 21, 2021.
Lance T. Gant,
Director, Compliance & Airworthiness
Division, Aircraft Certification Service.
Jkt 256001
[Docket No. FAA–2021–1020; Project
Identifier AD–2021–00864–T]
RIN 2120–AA64
Airworthiness Directives; The Boeing
Company Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
The FAA proposes to adopt a
new airworthiness directive (AD) for
certain The Boeing Company Model 777
airplanes. This proposed AD was
prompted by a report of the loss of the
nuts at all four fastener locations
common to the outboard flap inboard
support rear spar attachment fittings,
which affects the retention feature of the
fasteners and leaves the fasteners
susceptible to migrating out of the joint.
This proposed AD would require
repetitive detailed inspections for
discrepancies of the fasteners and shim
of the wing rear spar at certain outboard
flap supports, a detailed inspection for
damage of the shim, flap support
mechanism, and wing lower skin;
installing new fasteners and shims; and
repair or replacement of damaged parts.
The FAA is proposing this AD to
address the unsafe condition on these
products.
DATES: The FAA must receive comments
on this proposed AD by February 11,
2022.
ADDRESSES: 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.
SUMMARY:
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For service information identified in
this NPRM, 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 referenced 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 https://
www.regulations.gov by searching for
and locating Docket No. FAA–2021–
1020.
Examining the AD Docket
You may examine the AD docket at
https://www.regulations.gov by
searching for and locating Docket No.
FAA–2021–1020; 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
NPRM, any comments received, and
other information. The street address for
Docket Operations is listed above.
FOR FURTHER INFORMATION CONTACT: Luis
Cortez, Aerospace Engineer, Airframe
Section, FAA, Seattle ACO Branch, 2200
South 216th St., Des Moines, WA 98198;
phone and fax: (206) 231–3958; email:
Luis.A.Cortez-Muniz@faa.gov.
SUPPLEMENTARY INFORMATION:
Comments Invited
The FAA invites you to send any
written relevant data, views, or
arguments about this proposal. Send
your comments to an address listed
under ADDRESSES. Include ‘‘Docket No.
FAA–2021–1020; Project Identifier AD–
2021–00864–T’’ at the beginning of your
comments. The most helpful comments
reference a specific portion of the
proposal, explain the reason for any
recommended change, and include
supporting data. The FAA will consider
all comments received by the closing
date and may amend this proposal
because of those comments.
Except for Confidential Business
Information (CBI) as described in the
following paragraph, and other
information as described in 14 CFR
11.35, the FAA will post all comments
received, without change, to https://
www.regulations.gov, including any
personal information you provide. The
agency will also post a report
summarizing each substantive verbal
contact received about this NPRM.
Confidential Business Information
CBI is commercial or financial
information that is both customarily and
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Federal Register / Vol. 86, No. 246 / Tuesday, December 28, 2021 / Proposed Rules
actually treated as private by its owner.
Under the Freedom of Information Act
(FOIA) (5 U.S.C. 552), CBI is exempt
from public disclosure. If your
comments responsive to this NPRM
contain commercial or financial
information that is customarily treated
as private, that you actually treat as
private, and that is relevant or
responsive to this NPRM, it is important
that you clearly designate the submitted
comments as CBI. Please mark each
page of your submission containing CBI
as ‘‘PROPIN.’’ The FAA will treat such
marked submissions as confidential
under the FOIA, and they will not be
placed in the public docket of this
NPRM. Submissions containing CBI
should be sent to Luis Cortez, Aerospace
Engineer, Airframe Section, FAA,
Seattle ACO Branch, 2200 South 216th
St., Des Moines, WA 98198; phone and
fax: (206) 231–3958; email:
Luis.A.Cortez-Muniz@faa.gov. Any
commentary that the FAA receives
which is not specifically designated as
CBI will be placed in the public docket
for this rulemaking.
Background
The FAA has received a report of the
loss of the nuts at all four fastener
locations common to the outboard flap
inboard support rear spar attachment
fittings, which affects the retention
feature of the fasteners and leaves the
fasteners susceptible to migrating out of
the joint. These conditions, if not
addressed, could result in the inability
of the outboard flap support to sustain
limit load, and potential loss of the
outboard flap. Loss of the fastener
retention feature in the rear spar
attachment may lead to a severed joint
at the forward attachment point, leading
to separation of the support fitting.
Contact with the airplane from a
departed outboard flap or support fitting
could cause damage and consequent
reduced controllability and reduced
structural integrity of the airplane.
FAA’s Determination
The FAA is issuing this NPRM after
determining that the unsafe condition
described previously is likely to exist or
develop on other products of the same
type design.
Related Service Information Under 1
CFR Part 51
The FAA reviewed Boeing Alert
Requirements Bulletin 777–57A0123
RB, dated July 8, 2021. This service
information specifies procedures for
repetitive detailed inspections for
discrepancies (missing nuts, loose nuts,
thread protrusion, shim migration, and
gapping between the shim and wing
lower skin or between the shim and flap
support fitting) of the fasteners and
shim of the wing rear spar at outboard
73707
flap support numbers 1, 2, 7, and 8, a
detailed inspection for damage of the
shim, flap support mechanism, and
wing lower skin; installing new
fasteners and shims; and repair or
replacement of damaged parts.
Installation of the new fasteners and
shim would eliminate the need for the
repetitive inspections. 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.
Proposed AD Requirements in this
NPRM
This proposed AD would require
accomplishing the actions specified in
the service information already
described, except for any differences
identified as exceptions in the
regulatory text of this proposed AD. For
information on the procedures and
compliance times, see this service
information at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2021–
1020.
Costs of Compliance
The FAA estimates that this AD, if
adopted as proposed, would affect 280
airplanes of U.S. registry. The FAA
estimates the following costs to comply
with this proposed AD:
ESTIMATED COSTS
Action
Labor cost
Detailed inspections ...........................
39 work-hours × $85 per hour =
$3,315.
Up to 37 work-hours × $85 per hour
= Up to $3,145.
Inspect for damage, install fasteners/
shim, replace damaged parts.
The FAA has received no definitive
data on which to base the cost estimates
for the on-condition repairs specified in
this proposed AD.
khammond on DSKJM1Z7X2PROD with PROPOSALS
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
VerDate Sep<11>2014
21:04 Dec 27, 2021
Jkt 256001
Parts cost
Cost per product
Cost on U.S. operators
$0
$3,315 ....................
1,920
Up to $5,065 ..........
$928,200 per inspection
cycle.
Up to $1,418,200.
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
The FAA determined that this
proposed AD would not have federalism
implications under Executive Order
13132. This proposed AD would 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 this proposed regulation:
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(1) Is not a ‘‘significant regulatory
action’’ under Executive Order 12866,
(2) Would not affect intrastate
aviation in Alaska, and
(3) Would 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 Proposed Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA proposes to amend 14 CFR part
39 as follows:
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Federal Register / Vol. 86, No. 246 / Tuesday, December 28, 2021 / Proposed Rules
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.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by adding
the following new airworthiness
directive:
■
The Boeing Company: Docket No. FAA–
2021–1020; Project Identifier AD–2021–
00864–T.
(a) Comments Due Date
The FAA must receive comments on this
airworthiness directive (AD) by February 11,
2022.
(b) Affected ADs
None.
(c) Applicability
This AD applies to The Boeing Company
Model 777–200, –200LR, –300, –300ER, and
777F series airplanes, certificated in any
category, as identified in Boeing Alert
Requirements Bulletin 777–57A0123 RB,
dated July 8, 2021.
(d) Subject
Air Transport Association (ATA) of
America Code 57, Wings.
(e) Unsafe Condition
This AD was prompted by a report of the
loss of the nuts at all four fastener locations
common to the outboard flap inboard support
rear spar attachment fittings, which affects
the retention feature of the fasteners and
leaves the fasteners susceptible to migrating
out of the joint. The FAA is issuing this AD
to address the resulting inability of the
outboard flap support to sustain limit load,
and potential loss of the outboard flap. Loss
of the fastener retention feature in the rear
spar attachment may lead to a severed joint
at the forward attachment point, leading to
separation of the support fitting, which could
cause damage and consequent reduced
controllability and reduced structural
integrity of the airplane.
khammond on DSKJM1Z7X2PROD with PROPOSALS
(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 777–57A0123 RB,
dated July 8, 2021, do all applicable actions
identified in, and in accordance with, the
Accomplishment Instructions of Boeing Alert
Requirements Bulletin 777–57A0123 RB,
dated July 8, 2021.
Note 1 to paragraph (g): Guidance for
accomplishing the actions required by this
AD can be found in Boeing Alert Service
Bulletin 777–57A0123, dated July 8, 2021,
which is referred to in Boeing Alert
Requirements Bulletin 777–57A0123 RB,
dated July 8, 2021.
VerDate Sep<11>2014
21:04 Dec 27, 2021
Jkt 256001
(h) Exceptions to Service Information
Specifications
(1) Where the Compliance Time columns
of the tables in the ‘‘Compliance’’ paragraph
of Boeing Alert Requirements Bulletin 777–
57A0123 RB, dated July 8, 2021, use the
phrase ‘‘the original issue date of
Requirements Bulletin 777–57A0123 RB,’’
this AD requires using the effective date of
this AD.
(2) Where Boeing Alert Requirements
Bulletin 777–57A0123 RB, dated July 8,
2021, specifies contacting Boeing for repair
instructions: This AD requires doing the
repair using a method approved in
accordance with the procedures specified in
paragraph (i) of this AD.
(i) 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 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 (j)(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 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, Seattle 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.
(j) Related Information
(1) For more information about this AD,
contact Luis Cortez, Aerospace Engineer,
Airframe Section, FAA, Seattle ACO Branch,
2200 South 216th St., Des Moines, WA
98198; phone and fax: (206) 231–3958; email:
Luis.A.Cortez-Muniz@faa.gov.
(2) 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. You may view this
referenced 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.
Issued on December 2, 2021.
Lance T. Gant,
Director, Compliance & Airworthiness
Division, Aircraft Certification Service.
[FR Doc. 2021–28181 Filed 12–27–21; 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–2021–1078; Project
Identifier MCAI–2020–01574–R]
RIN 2120–AA64
Airworthiness Directives; Bell Textron
Canada Limited Helicopters
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
The FAA proposes to adopt a
new airworthiness directive (AD) for
certain Bell Textron Canada Limited
Model 429 helicopters. This proposed
AD was prompted by in-service reports
of the loss of display and subsequent
recovery of certain display units (DUs).
This proposed AD would require
revising the existing rotorcraft flight
manual supplement (RFMS) for your
helicopter and disabling the traffic alert
and collision avoidance system (TCAS)
POP–UP feature for certain DUs. The
FAA is proposing this AD to address the
unsafe condition on these products.
DATES: The FAA must receive comments
on this proposed AD by February 11,
2022.
SUMMARY:
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 between 9 a.m. and 5 p.m.,
Monday through Friday, except Federal
holidays.
For service information identified in
this NPRM, contact Bell Textron Canada
Limited, 12,800 Rue de l’Avenir,
Mirabel, Quebec J7J 1R4, Canada;
telephone 1–450–437–2862 or 1–800–
363–8023; fax 1–450–433–0272; email
productsupport@bellflight.com; or at
https://www.bellflight.com/support/
contact-support. You may view this
service information 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.
ADDRESSES:
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]]>Agencies
[Federal Register Volume 86, Number 246 (Tuesday, December 28, 2021)]
[Proposed Rules]
[Pages 73706-73708]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2021-28181]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2021-1020; Project Identifier AD-2021-00864-T]
RIN 2120-AA64
Airworthiness Directives; The Boeing Company Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD)
for certain The Boeing Company Model 777 airplanes. This proposed AD
was prompted by a report of the loss of the nuts at all four fastener
locations common to the outboard flap inboard support rear spar
attachment fittings, which affects the retention feature of the
fasteners and leaves the fasteners susceptible to migrating out of the
joint. This proposed AD would require repetitive detailed inspections
for discrepancies of the fasteners and shim of the wing rear spar at
certain outboard flap supports, a detailed inspection for damage of the
shim, flap support mechanism, and wing lower skin; installing new
fasteners and shims; and repair or replacement of damaged parts. The
FAA is proposing this AD to address the unsafe condition on these
products.
DATES: The FAA must receive comments on this proposed AD by February
11, 2022.
ADDRESSES: 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 NPRM, 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 referenced 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 https://www.regulations.gov by searching for and locating Docket No. FAA-2021-
1020.
Examining the AD Docket
You may examine the AD docket at https://www.regulations.gov by
searching for and locating Docket No. FAA-2021-1020; 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 NPRM, any comments
received, and other information. The street address for Docket
Operations is listed above.
FOR FURTHER INFORMATION CONTACT: Luis Cortez, Aerospace Engineer,
Airframe Section, FAA, Seattle ACO Branch, 2200 South 216th St., Des
Moines, WA 98198; phone and fax: (206) 231-3958; email: [email protected].
SUPPLEMENTARY INFORMATION:
Comments Invited
The FAA invites you to send any written relevant data, views, or
arguments about this proposal. Send your comments to an address listed
under ADDRESSES. Include ``Docket No. FAA-2021-1020; Project Identifier
AD-2021-00864-T'' at the beginning of your comments. The most helpful
comments reference a specific portion of the proposal, explain the
reason for any recommended change, and include supporting data. The FAA
will consider all comments received by the closing date and may amend
this proposal because of those comments.
Except for Confidential Business Information (CBI) as described in
the following paragraph, and other information as described in 14 CFR
11.35, the FAA will post all comments received, without change, to
https://www.regulations.gov, including any personal information you
provide. The agency will also post a report summarizing each
substantive verbal contact received about this NPRM.
Confidential Business Information
CBI is commercial or financial information that is both customarily
and
[[Page 73707]]
actually treated as private by its owner. Under the Freedom of
Information Act (FOIA) (5 U.S.C. 552), CBI is exempt from public
disclosure. If your comments responsive to this NPRM contain commercial
or financial information that is customarily treated as private, that
you actually treat as private, and that is relevant or responsive to
this NPRM, it is important that you clearly designate the submitted
comments as CBI. Please mark each page of your submission containing
CBI as ``PROPIN.'' The FAA will treat such marked submissions as
confidential under the FOIA, and they will not be placed in the public
docket of this NPRM. Submissions containing CBI should be sent to Luis
Cortez, Aerospace Engineer, Airframe Section, FAA, Seattle ACO Branch,
2200 South 216th St., Des Moines, WA 98198; phone and fax: (206) 231-
3958; email: [email protected]. Any commentary that the FAA
receives which is not specifically designated as CBI will be placed in
the public docket for this rulemaking.
Background
The FAA has received a report of the loss of the nuts at all four
fastener locations common to the outboard flap inboard support rear
spar attachment fittings, which affects the retention feature of the
fasteners and leaves the fasteners susceptible to migrating out of the
joint. These conditions, if not addressed, could result in the
inability of the outboard flap support to sustain limit load, and
potential loss of the outboard flap. Loss of the fastener retention
feature in the rear spar attachment may lead to a severed joint at the
forward attachment point, leading to separation of the support fitting.
Contact with the airplane from a departed outboard flap or support
fitting could cause damage and consequent reduced controllability and
reduced structural integrity of the airplane.
FAA's Determination
The FAA is issuing this NPRM after determining that the unsafe
condition described previously is likely to exist or develop on other
products of the same type design.
Related Service Information Under 1 CFR Part 51
The FAA reviewed Boeing Alert Requirements Bulletin 777-57A0123 RB,
dated July 8, 2021. This service information specifies procedures for
repetitive detailed inspections for discrepancies (missing nuts, loose
nuts, thread protrusion, shim migration, and gapping between the shim
and wing lower skin or between the shim and flap support fitting) of
the fasteners and shim of the wing rear spar at outboard flap support
numbers 1, 2, 7, and 8, a detailed inspection for damage of the shim,
flap support mechanism, and wing lower skin; installing new fasteners
and shims; and repair or replacement of damaged parts. Installation of
the new fasteners and shim would eliminate the need for the repetitive
inspections. 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.
Proposed AD Requirements in this NPRM
This proposed AD would require accomplishing the actions specified
in the service information already described, except for any
differences identified as exceptions in the regulatory text of this
proposed AD. For information on the procedures and compliance times,
see this service information at https://www.regulations.gov by
searching for and locating Docket No. FAA-2021-1020.
Costs of Compliance
The FAA estimates that this AD, if adopted as proposed, would
affect 280 airplanes of U.S. registry. The FAA estimates the following
costs to comply with this proposed AD:
Estimated costs
----------------------------------------------------------------------------------------------------------------
Cost on U.S.
Action Labor cost Parts cost Cost per product operators
----------------------------------------------------------------------------------------------------------------
Detailed inspections............. 39 work-hours x $85 $0 $3,315............. $928,200 per
per hour = $3,315. inspection cycle.
Inspect for damage, install Up to 37 work-hours 1,920 Up to $5,065....... Up to $1,418,200.
fasteners/shim, replace damaged x $85 per hour =
parts. Up to $3,145.
----------------------------------------------------------------------------------------------------------------
The FAA has received no definitive data on which to base the cost
estimates for the on-condition repairs specified in this proposed 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
The FAA determined that this proposed AD would not have federalism
implications under Executive Order 13132. This proposed AD would 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 this proposed
regulation:
(1) Is not a ``significant regulatory action'' under Executive
Order 12866,
(2) Would not affect intrastate aviation in Alaska, and
(3) Would 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 Proposed Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA proposes to amend 14 CFR part 39 as follows:
[[Page 73708]]
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:
The Boeing Company: Docket No. FAA-2021-1020; Project Identifier
AD-2021-00864-T.
(a) Comments Due Date
The FAA must receive comments on this airworthiness directive
(AD) by February 11, 2022.
(b) Affected ADs
None.
(c) Applicability
This AD applies to The Boeing Company Model 777-200, -200LR, -
300, -300ER, and 777F series airplanes, certificated in any
category, as identified in Boeing Alert Requirements Bulletin 777-
57A0123 RB, dated July 8, 2021.
(d) Subject
Air Transport Association (ATA) of America Code 57, Wings.
(e) Unsafe Condition
This AD was prompted by a report of the loss of the nuts at all
four fastener locations common to the outboard flap inboard support
rear spar attachment fittings, which affects the retention feature
of the fasteners and leaves the fasteners susceptible to migrating
out of the joint. The FAA is issuing this AD to address the
resulting inability of the outboard flap support to sustain limit
load, and potential loss of the outboard flap. Loss of the fastener
retention feature in the rear spar attachment may lead to a severed
joint at the forward attachment point, leading to separation of the
support fitting, which could cause damage and consequent reduced
controllability and reduced structural integrity of the airplane.
(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 777-57A0123 RB, dated July 8, 2021, do
all applicable actions identified in, and in accordance with, the
Accomplishment Instructions of Boeing Alert Requirements Bulletin
777-57A0123 RB, dated July 8, 2021.
Note 1 to paragraph (g): Guidance for accomplishing the actions
required by this AD can be found in Boeing Alert Service Bulletin
777-57A0123, dated July 8, 2021, which is referred to in Boeing
Alert Requirements Bulletin 777-57A0123 RB, dated July 8, 2021.
(h) Exceptions to Service Information Specifications
(1) Where the Compliance Time columns of the tables in the
``Compliance'' paragraph of Boeing Alert Requirements Bulletin 777-
57A0123 RB, dated July 8, 2021, use the phrase ``the original issue
date of Requirements Bulletin 777-57A0123 RB,'' this AD requires
using the effective date of this AD.
(2) Where Boeing Alert Requirements Bulletin 777-57A0123 RB,
dated July 8, 2021, specifies contacting Boeing for repair
instructions: This AD requires doing the repair using a method
approved in accordance with the procedures specified in paragraph
(i) of this AD.
(i) 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 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 (j)(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, Seattle
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.
(j) Related Information
(1) For more information about this AD, contact Luis Cortez,
Aerospace Engineer, Airframe Section, FAA, Seattle ACO Branch, 2200
South 216th St., Des Moines, WA 98198; phone and fax: (206) 231-
3958; email: [email protected].
(2) 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. You may view this referenced 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.
Issued on December 2, 2021.
Lance T. Gant,
Director, Compliance & Airworthiness Division, Aircraft Certification
Service.
[FR Doc. 2021-28181 Filed 12-27-21; 8:45 am]
BILLING CODE 4910-13-P
