Airworthiness Directives; The Boeing Company Airplanes, 47255-47258 [2021-18069]
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Federal Register / Vol. 86, No. 161 / Tuesday, August 24, 2021 / Proposed Rules
17940 (79 FR 48018, August 15, 2014);
and AD 2018–19–28, Amendment 39–
19429 (83 FR 48935, September 28,
2018); and
■ b. Adding the following new AD:
Yabora˜ Indu´stria Aerona´utica S.A. (Type
Certificate Previously Held by Embraer
S.A.): Docket No. FAA–2021–0692; Project
Identifier MCAI–2020–01585–T.
(a) Comments Due Date
The FAA must receive comments on this
airworthiness directive (AD) by October 8,
2021.
(b) Affected ADs
(1) This AD replaces AD 2014–16–16,
Amendment 39–17940 (79 FR 48018, August
15, 2014) (AD 2014–16–16).
(2) This AD also replaces AD 2018–19–28,
Amendment 39–19429 (83 FR 48935,
September 28, 2018) (AD 2018–19–28).
(c) Applicability
This AD applies to all Yabora˜ Indu´stria
Aerona´utica S.A. (type certificate previously
held by Embraer S.A.) Model ERJ 190–100
STD, –100 LR, –100 ECJ, –100 IGW, –200
STD, –200 LR, and –200 IGW airplanes,
certificated in any category.
(d) Subject
Air Transport Association (ATA) of
America Code 54, Nacelles/pylons.
(e) Reason
This AD was prompted by reports of
bushing migration, loss of nut torque on the
engine pylon lower inboard and outboard
link fittings, a loose lower link assembly, and
damaged nuts, and the need to shorten the
compliance time for the modification of the
pylon lower link fitting attaching parts. The
FAA is issuing this AD to prevent loss of
integrity of the lower link fittings of the
engine pylon, which could lead to separation
of the engine from the wing.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
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(g) Requirements
For airplanes identified in Ageˆncia
Nacional de Aviac
¸a˜o Civil (ANAC) AD 2020–
06–02R02, effective November 30, 2020
(ANAC AD 2020–06–02R02): Except as
specified in paragraphs (h) and (i) of this AD,
comply with all required actions and
compliance times specified in, and in
accordance with, ANAC AD 2020–06–02R02.
(h) Exceptions to ANAC AD 2020–06–02R02
(1) Where ANAC AD 2020–06–02R02 refers
to its effective date, this AD requires using
the effective date of this AD.
(2) Where ANAC AD 2020–06–02R02 refers
to July 3, 2014, this AD requires using
September 2, 2014 (the effective date of AD
2014–16–16).
(3) Where ANAC AD 2020–06–02R02 refers
to April 25, 2017, this AD requires using
November 2, 2018 (the effective date of AD
2018–19–28).
(4) Paragraphs (y), ‘‘Alternative methods of
compliance (AMOCs),’’ and (z), ‘‘Material
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16:21 Aug 23, 2021
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incorporated by reference,’’ of ANAC AD
2020–06–02R02 do not apply to this AD.
(5) Where ANAC AD 2020–06–02R02
specifies ‘‘replace immediately,’’ this AD
requires replacing ‘‘before further flight.’’
(6) Paragraph (w), ‘‘Parts installation
prohibition,’’ of ANAC AD 2020–06–02R02
does not apply to this AD, except as specified
in paragraph (i) of this AD.
(i) Parts Installation Prohibition
As of September 2, 2014 (the effective date
of AD 2014–16–16), no person may install a
lock assembly identified in Embraer Service
Bulletin 190–54–0013, dated November 27,
2012; or Embraer Service Bulletin 190LIN–
54–0004, dated December 20, 2012; at the
inboard or outboard lower link fitting on any
airplane.
(j) Other FAA AD Provisions
The following provisions also apply to this
AD:
(1) Alternative Methods of Compliance
(AMOCs): The Manager, Large Aircraft
Section, 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 responsible Flight
Standards Office, as appropriate. If sending
information directly to the Large Aircraft
Section, International Validation Branch,
send it to the attention of the person
identified in paragraph (k)(2) of this AD.
Information may be emailed to: 9-AVS-AIR730-AMOC@faa.gov. Before using any
approved AMOC, notify your appropriate
principal inspector, or lacking a principal
inspector, the manager of the responsible
Flight Standards Office.
(2) Contacting the Manufacturer: For any
requirement in this AD to obtain instructions
from a manufacturer, the instructions must
be accomplished using a method approved
by the Manager, Large Aircraft Section,
International Validation Branch, FAA; or
ANAC; or ANAC’s authorized Designee. If
approved by the ANAC Designee, the
approval must include the Designee’s
authorized signature.
(3) Required for Compliance (RC): Except
as specified by paragraph (h) of this AD: For
service information that contains steps that
are labeled as Required for Compliance (RC),
the provisions of paragraphs (j)(3)(i) and (ii)
of this AD apply.
(i) The steps labeled as RC, including
substeps under an RC step and any figures
identified in an RC step, must be done to
comply with the AD. If a step or substep is
labeled ‘‘RC Exempt,’’ then the RC
requirement is removed from that step or
substep. An AMOC is required for any
deviations to RC steps, including substeps
and identified figures.
(ii) Steps not labeled as RC may be
deviated from using accepted methods in
accordance with the operator’s maintenance
or inspection program without obtaining
approval of an AMOC, provided the RC steps,
including substeps and identified figures, can
still be done as specified, and the airplane
can be put back in an airworthy condition.
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47255
(k) Related Information
(1) For ANAC AD 2020–06–02R02, contact
National Civil Aviation Agency (ANAC),
Aeronautical Products Certification Branch
(GGCP), Rua Dr. Orlando Feirabend Filho,
230—Centro Empresarial Aquarius—Torre
B—Andares 14 a 18, Parque Residencial
Aquarius, CEP 12.246–190—Sa˜o Jose´ dos
Campos—SP, BRAZIL, Tel: 55 (12) 3203–
6600; Email: pac@anac.gov.br. You may find
this IBR material on the ANAC website at
https://sistemas.anac.gov.br/certificacao/DA/
DAE.asp. For Embraer service information
identified in this AD, contact Embraer S.A.,
Technical Publications Section (PC 060), Av.
Brigadeiro Faria Lima, 2170—Putim—12227–
901 Sa˜o Jose dos Campos—SP—Brazil;
telephone +55 12 3927–5852 or +55 12 3309–
0732; fax +55 12 3927–7546; email distrib@
embraer.com.br; internet https://
www.flyembraer.com. For Embraer service
information identified in this AD that is
applicable to Yabora˜ Indu´stria Aerona´utica
S.A. Model ERJ 190–100 ECJ airplanes,
contact Embraer S.A., Technical Publications
Section (PC 560), Rodovia Presidente Dutra,
km 134, 12247–004 Distrito Eugeˆnio de
Melo—Sa˜o Jose´ dos Campos—SP—Brazil;
telephone +55 12 3927–0386; email distrib@
embraer.com.br; internet https://
www.mytechcare.embraer.com. You may
view this material 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. This
material may be found in the AD docket on
the internet at https://www.regulations.gov
by searching for and locating Docket No.
FAA–2021–0692.
(2) For more information about this AD,
contact Krista Greer, Aerospace Engineer,
Large Aircraft Section, International
Validation Branch, FAA, 2200 South 216th
St., Des Moines, WA 98198; telephone and
fax 206–231–3221; email krista.greer@
faa.gov.
Issued on August 18, 2021.
Gaetano A. Sciortino,
Deputy Director for Strategic Initiatives,
Compliance & Airworthiness Division,
Aircraft Certification Service.
[FR Doc. 2021–18110 Filed 8–23–21; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2021–0609; Project
Identifier AD–2021–00274–T]
RIN 2120–AA64
Airworthiness Directives; The Boeing
Company Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
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Federal Register / Vol. 86, No. 161 / Tuesday, August 24, 2021 / Proposed Rules
The FAA proposes to adopt a
new airworthiness directive (AD) for
certain The Boeing Company Model
737–300, –400, and –500 series
airplanes. This proposed AD was
prompted by an evaluation by the
design approval holder (DAH)
indicating that the frame splice between
certain stringers is subject to
widespread fatigue damage (WFD). This
proposed AD would require an
inspection of certain fuselage frame
splices for existing repairs, repetitive
inspections of certain fuselage frame
splices for cracking, and applicable oncondition actions. 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 October 8, 2021.
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 on the internet
at https://www.regulations.gov by
searching for and locating Docket No.
FAA–2021–0609.
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SUMMARY:
Examining the AD Docket
You may examine the AD docket at
https://www.regulations.gov by
searching for and locating Docket No.
FAA–2021–0609; 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:
Wayne Ha, Aerospace Engineer,
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Airframe Section, FAA, Los Angeles
ACO Branch, 3960 Paramount
Boulevard, Lakewood, CA 90712–4137;
phone: 562–627–5238; fax: 562–627–
5210; email: wayne.ha@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–2021–0609; Project Identifier AD–
2021–00274–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
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 Wayne Ha, Aerospace
Engineer, Airframe Section, FAA, Los
Angeles ACO Branch, 3960 Paramount
Boulevard, Lakewood, CA 90712–4137;
phone: 562–627–5238; fax: 562–627–
5210; email: wayne.ha@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.
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Background
Fatigue damage can occur locally, in
small areas or structural design details,
or globally, in widespread areas.
Multiple-site damage is widespread
damage that occurs in a large structural
element such as a single rivet line of a
lap splice joining two large skin panels.
Widespread damage can also occur in
multiple elements such as adjacent
frames or stringers. Multiple-site
damage and multiple-element damage
cracks are typically too small initially to
be reliably detected with normal
inspection methods. Without
intervention, these cracks will grow,
and eventually compromise the
structural integrity of the airplane. This
condition is known as WFD. It is
associated with general degradation of
large areas of structure with similar
structural details and stress levels. As
an airplane ages, WFD will likely occur,
and will certainly occur if the airplane
is operated long enough without any
intervention.
An FAA final rule (‘‘Aging Airplane
Program: Widespread Fatigue Damage;’’
75 FR 69746, November 15, 2010)
became effective on January 14, 2011,
and amended 14 CFR parts 25, 26, 121,
and 129 (commonly known as the WFD
rule). The WFD rule requires certain
actions to prevent structural failure due
to WFD throughout the operational life
of certain existing transport category
airplanes and all of these airplanes that
will be certificated in the future. DAHs
of existing and future airplanes subject
to the WFD rule are required to establish
a limit of validity (LOV) of the
engineering data that support the
structural maintenance program.
Operators affected by the WFD rule may
not fly an airplane beyond its LOV,
unless an extended LOV is approved.
The WFD rule does not require
identifying and developing maintenance
actions if the DAHs can show that such
actions are not necessary to prevent
WFD before the airplane reaches the
LOV. Many LOVs, however, do depend
on accomplishment of future
maintenance actions. As stated in the
WFD rule, any maintenance actions
necessary to reach the LOV will be
mandated by airworthiness directives
through separate rulemaking actions.
In the context of WFD, this action is
necessary to enable DAHs to propose
LOVs that allow operators the longest
operational lives for their airplanes, and
still ensure that WFD will not occur.
This approach allows for an
implementation strategy that provides
flexibility to DAHs in determining the
timing of service information
development (with FAA approval),
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while providing operators with certainty
regarding the LOV applicable to their
airplanes.
The FAA has received a report
indicating that cracking is occurring in
the frame splice doubler and may occur
in the upper frame at the upper frame
splice between stringer S–13 and S–14
on Boeing Model 737–300, –400, and
–500 airplanes at multiple frame
locations. The doubler cracking and
possible upper frame cracking at the
frame splice between stringer S–13 and
S–14 are the result of fatigue, caused by
combined cyclic loading from fuselage
pressurization and flight loads. The
FAA is issuing this AD to address upper
frame cracking common to the frame
splice between stringer S–13 and S–14,
which could interact with stringer S–14
skin lap splice lower fastener row
cracking in lower skin, and result in an
uncontrolled decompression of the
airplane and loss of structural integrity.
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 737–53A1388
RB, dated October 27, 2020. This service
information specifies procedures for a
general visual inspection (GVI) of the
fuselage frame splices between stringer
S–13 and S–14 station (STA) 360 to STA
520 and STA 727A to STA 907 for
existing repairs, repetitive inspections
of the fuselage frame splices between
stringer S–13 and S–14 from STA 360 to
STA 520 and STA 727A to STA 907 for
cracking, and applicable on-condition
actions. On-condition actions include
an open hole high frequency eddy
current (HFEC) inspection for cracking
at all fastener hole locations where a
fastener was removed due to finding a
cracked doubler, repair, or replacement.
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–
0609.
Costs of Compliance
The FAA estimates that this AD, if
adopted as proposed, would affect 66
airplanes of U.S. registry. The FAA
estimates the following costs to comply
with this proposed AD:
ESTIMATED COSTS
Action
Labor cost
Repetitive Inspections ...
Up to 267 work-hours × $85 per hour = Up to
$22,695 inspection cycle.
2 work-hours × $85 per hour = $170 .................
GVI ................................
The FAA has received no definitive
data on which to base the cost estimates
for the on-condition actions specified in
this proposed AD.
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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.
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Cost per
product
Parts cost
$0
0
Up to $22,695 per inspection cycle.
$170 .............................
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.
Cost on U.S.
operators
Up to $1,497,870 per
inspection cycle.
$11,220.
The Proposed Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA proposes to amend 14 CFR part
39 as follows:
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
■
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by adding
the following new airworthiness
directive:
■
The Boeing Company: Docket No. FAA–
2021–0609; Project Identifier AD–2021–
00274–T.
(a) Comments Due Date
The FAA must receive comments on this
airworthiness directive (AD) by October 8,
2021.
List of Subjects in 14 CFR Part 39
(b) Affected ADs
None.
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
(c) Applicability
This AD applies to The Boeing Company
Model 737–300, –400, and –500 series
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airplanes, certificated in any category, as
identified in Boeing Alert Requirements
Bulletin 737–53A1388 RB, dated October 27,
2020.
(d) Subject
Air Transport Association (ATA) of
America Code 53, Fuselage.
(e) Unsafe Condition
This AD was prompted by an evaluation by
the design approval holder (DAH) indicating
that the frame splice between stringer S–13
and S–14 is subject to widespread fatigue
damage (WFD). The FAA is issuing this AD
to address upper frame cracking common to
the frame splice between stringer S–13 and
S–14, which could interact with stringer S–
14 skin lap splice lower fastener row
cracking in lower skin and result in an
uncontrolled decompression of the airplane
and loss of structural integrity.
(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 737–53A1388 RB,
dated October 27, 2020, do all applicable
actions identified in, and in accordance with,
the Accomplishment Instructions of Boeing
Alert Requirements Bulletin 737–53A1388
RB, dated October 27, 2020.
Note 1 to paragraph (g): Guidance for
accomplishing the actions required by this
AD can be found in Boeing Alert Service
Bulletin 737–53A1388, dated October 27,
2020, which is referred to in Boeing Alert
Requirements Bulletin 737–53A1388 RB,
dated October 27, 2020.
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(h) Exceptions to Service Information
Specifications
(1) Where Boeing Alert Requirements
Bulletin 737–53A1388 RB, dated October 27,
2020, uses the phrase ‘‘the Original Issue date
of Requirements Bulletin 737–53A1388 RB,’’
this AD requires using ‘‘the effective date of
this AD,’’ except where Alert Requirements
Bulletin 737–53A1388 RB, dated October 27,
2020, uses the phrase ‘‘the Original Issue date
of Requirements Bulletin 737–53A1388 RB,’’
in a note or flag note.
(2) Where Boeing Alert Requirements
Bulletin 737–53A1388 RB, dated October 27,
2020, specifies contacting Boeing for repair
instructions or for alternative inspections:
This AD requires doing the repair, or doing
the alternative inspections and applicable oncondition actions 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, 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
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Standards Office, as appropriate. If sending
information directly to the manager of the
certification office, send it to the attention of
the person identified in Related Information.
Information may be emailed to: 9-ANMLAACO-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, 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.
Havilland Aircraft of Canada Limited
Model DHC–8–401 and –402 airplanes.
This proposed AD was prompted by
reports of a possible hard contact
between the #2 top high level sensor
(HLS) terminal screw head and the #6
outer wing fuel access panel stiffener
flange. This proposed AD would require
removing and replacing or reworking
the #6 outer wing fuel access panel
assembly. 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 October 8, 2021.
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
(j) Related Information
https://www.regulations.gov. Follow the
(1) For more information about this AD,
instructions for submitting comments.
contact Wayne Ha, Aerospace Engineer,
• Fax: 202–493–2251.
Airframe Section, FAA, Los Angeles ACO
• Mail: U.S. Department of
Branch, 3960 Paramount Boulevard,
Transportation, Docket Operations,
Lakewood, CA 90712–4137; phone: 562–627–
M–30, West Building Ground Floor,
5238; fax: 562–627–5210; email: wayne.ha@
Room W12–140, 1200 New Jersey
faa.gov.
Avenue SE, Washington, DC 20590.
(2) For service information identified in
• Hand Delivery: Deliver to Mail
this AD, contact Boeing Commercial
address above between 9 a.m. and 5
Airplanes, Attention: Contractual & Data
Services (C&DS), 2600 Westminster Blvd.,
p.m., Monday through Friday, except
MC 110–SK57, Seal Beach, CA 90740–5600;
Federal holidays.
telephone 562–797–1717; internet https://
For service information identified in
www.myboeingfleet.com. You may view this
this NPRM, contact De Havilland
referenced service information at the FAA,
Aircraft of Canada Limited, Q-Series
Airworthiness Products Section, Operational
Technical Help Desk, 123 Garratt
Safety Branch, 2200 South 216th St., Des
Boulevard, Toronto, Ontario M3K 1Y5,
Moines, WA. For information on the
Canada; telephone 416–375–4000; fax
availability of this material at the FAA, call
416–375–4539; email thd@
206–231–3195.
dehavilland.com; internet https://
Issued on July 26, 2021.
dehavilland.com. You may view this
Lance T. Gant,
service information at the FAA,
Director, Compliance & Airworthiness
Airworthiness Products Section,
Division, Aircraft Certification Service.
Operational Safety Branch, 2200 South
[FR Doc. 2021–18069 Filed 8–23–21; 8:45 am]
216th St., Des Moines, WA. For
BILLING CODE 4910–13–P
information on the availability of this
material at the FAA, call 206–231–3195.
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2021–0694; Project
Identifier MCAI–2021–00305–T]
RIN 2120–AA64
Airworthiness Directives; De Havilland
Aircraft of Canada Limited (Type
Certificate Previously Held by
Bombardier, Inc.) Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
The FAA proposes to adopt a
new airworthiness directive (AD) for De
SUMMARY:
PO 00000
Frm 00017
Fmt 4702
Sfmt 4702
Examining the AD Docket
You may examine the AD docket at
https://www.regulations.gov by
searching for and locating Docket No.
FAA–2021–0694; 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:
Thomas Niczky, Aerospace Engineer,
Avionics and Electrical Systems
Section, FAA, New York ACO Branch,
1600 Stewart Avenue, Suite 410,
Westbury, NY 11590; telephone 516–
228–7347; fax 516–794–5531; email 9avs-nyaco-cos@faa.gov.
SUPPLEMENTARY INFORMATION:
E:\FR\FM\24AUP1.SGM
24AUP1
]]>Agencies
[Federal Register Volume 86, Number 161 (Tuesday, August 24, 2021)]
[Proposed Rules]
[Pages 47255-47258]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2021-18069]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2021-0609; Project Identifier AD-2021-00274-T]
RIN 2120-AA64
Airworthiness Directives; The Boeing Company Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
[[Page 47256]]
SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD)
for certain The Boeing Company Model 737-300, -400, and -500 series
airplanes. This proposed AD was prompted by an evaluation by the design
approval holder (DAH) indicating that the frame splice between certain
stringers is subject to widespread fatigue damage (WFD). This proposed
AD would require an inspection of certain fuselage frame splices for
existing repairs, repetitive inspections of certain fuselage frame
splices for cracking, and applicable on-condition actions. 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 October 8,
2021.
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 on the internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2021-
0609.
Examining the AD Docket
You may examine the AD docket at https://www.regulations.gov by
searching for and locating Docket No. FAA-2021-0609; 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: Wayne Ha, Aerospace Engineer, Airframe
Section, FAA, Los Angeles ACO Branch, 3960 Paramount Boulevard,
Lakewood, CA 90712-4137; phone: 562-627-5238; fax: 562-627-5210; 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-2021-0609; Project Identifier
AD-2021-00274-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 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 Wayne
Ha, Aerospace Engineer, Airframe Section, FAA, Los Angeles ACO Branch,
3960 Paramount Boulevard, Lakewood, CA 90712-4137; phone: 562-627-5238;
fax: 562-627-5210; 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
Fatigue damage can occur locally, in small areas or structural
design details, or globally, in widespread areas. Multiple-site damage
is widespread damage that occurs in a large structural element such as
a single rivet line of a lap splice joining two large skin panels.
Widespread damage can also occur in multiple elements such as adjacent
frames or stringers. Multiple-site damage and multiple-element damage
cracks are typically too small initially to be reliably detected with
normal inspection methods. Without intervention, these cracks will
grow, and eventually compromise the structural integrity of the
airplane. This condition is known as WFD. It is associated with general
degradation of large areas of structure with similar structural details
and stress levels. As an airplane ages, WFD will likely occur, and will
certainly occur if the airplane is operated long enough without any
intervention.
An FAA final rule (``Aging Airplane Program: Widespread Fatigue
Damage;'' 75 FR 69746, November 15, 2010) became effective on January
14, 2011, and amended 14 CFR parts 25, 26, 121, and 129 (commonly known
as the WFD rule). The WFD rule requires certain actions to prevent
structural failure due to WFD throughout the operational life of
certain existing transport category airplanes and all of these
airplanes that will be certificated in the future. DAHs of existing and
future airplanes subject to the WFD rule are required to establish a
limit of validity (LOV) of the engineering data that support the
structural maintenance program. Operators affected by the WFD rule may
not fly an airplane beyond its LOV, unless an extended LOV is approved.
The WFD rule does not require identifying and developing
maintenance actions if the DAHs can show that such actions are not
necessary to prevent WFD before the airplane reaches the LOV. Many
LOVs, however, do depend on accomplishment of future maintenance
actions. As stated in the WFD rule, any maintenance actions necessary
to reach the LOV will be mandated by airworthiness directives through
separate rulemaking actions.
In the context of WFD, this action is necessary to enable DAHs to
propose LOVs that allow operators the longest operational lives for
their airplanes, and still ensure that WFD will not occur. This
approach allows for an implementation strategy that provides
flexibility to DAHs in determining the timing of service information
development (with FAA approval),
[[Page 47257]]
while providing operators with certainty regarding the LOV applicable
to their airplanes.
The FAA has received a report indicating that cracking is occurring
in the frame splice doubler and may occur in the upper frame at the
upper frame splice between stringer S-13 and S-14 on Boeing Model 737-
300, -400, and -500 airplanes at multiple frame locations. The doubler
cracking and possible upper frame cracking at the frame splice between
stringer S-13 and S-14 are the result of fatigue, caused by combined
cyclic loading from fuselage pressurization and flight loads. The FAA
is issuing this AD to address upper frame cracking common to the frame
splice between stringer S-13 and S-14, which could interact with
stringer S-14 skin lap splice lower fastener row cracking in lower
skin, and result in an uncontrolled decompression of the airplane and
loss of structural integrity.
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 737-53A1388 RB,
dated October 27, 2020. This service information specifies procedures
for a general visual inspection (GVI) of the fuselage frame splices
between stringer S-13 and S-14 station (STA) 360 to STA 520 and STA
727A to STA 907 for existing repairs, repetitive inspections of the
fuselage frame splices between stringer S-13 and S-14 from STA 360 to
STA 520 and STA 727A to STA 907 for cracking, and applicable on-
condition actions. On-condition actions include an open hole high
frequency eddy current (HFEC) inspection for cracking at all fastener
hole locations where a fastener was removed due to finding a cracked
doubler, repair, or replacement.
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-2021-0609.
Costs of Compliance
The FAA estimates that this AD, if adopted as proposed, would
affect 66 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
----------------------------------------------------------------------------------------------------------------
Repetitive Inspections......... Up to 267 work-hours x $0 Up to $22,695 per Up to $1,497,870
$85 per hour = Up to inspection cycle. per inspection
$22,695 inspection cycle.
cycle.
GVI............................ 2 work-hours x $85 per 0 $170.............. $11,220.
hour = $170.
----------------------------------------------------------------------------------------------------------------
The FAA has received no definitive data on which to base the cost
estimates for the on-condition actions 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:
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-2021-0609; Project Identifier AD-
2021-00274-T.
(a) Comments Due Date
The FAA must receive comments on this airworthiness directive
(AD) by October 8, 2021.
(b) Affected ADs
None.
(c) Applicability
This AD applies to The Boeing Company Model 737-300, -400, and -
500 series
[[Page 47258]]
airplanes, certificated in any category, as identified in Boeing
Alert Requirements Bulletin 737-53A1388 RB, dated October 27, 2020.
(d) Subject
Air Transport Association (ATA) of America Code 53, Fuselage.
(e) Unsafe Condition
This AD was prompted by an evaluation by the design approval
holder (DAH) indicating that the frame splice between stringer S-13
and S-14 is subject to widespread fatigue damage (WFD). The FAA is
issuing this AD to address upper frame cracking common to the frame
splice between stringer S-13 and S-14, which could interact with
stringer S-14 skin lap splice lower fastener row cracking in lower
skin and result in an uncontrolled decompression of the airplane and
loss of structural integrity.
(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 737-53A1388 RB, dated October 27, 2020,
do all applicable actions identified in, and in accordance with, the
Accomplishment Instructions of Boeing Alert Requirements Bulletin
737-53A1388 RB, dated October 27, 2020.
Note 1 to paragraph (g): Guidance for accomplishing the actions
required by this AD can be found in Boeing Alert Service Bulletin
737-53A1388, dated October 27, 2020, which is referred to in Boeing
Alert Requirements Bulletin 737-53A1388 RB, dated October 27, 2020.
(h) Exceptions to Service Information Specifications
(1) Where Boeing Alert Requirements Bulletin 737-53A1388 RB,
dated October 27, 2020, uses the phrase ``the Original Issue date of
Requirements Bulletin 737-53A1388 RB,'' this AD requires using ``the
effective date of this AD,'' except where Alert Requirements
Bulletin 737-53A1388 RB, dated October 27, 2020, uses the phrase
``the Original Issue date of Requirements Bulletin 737-53A1388 RB,''
in a note or flag note.
(2) Where Boeing Alert Requirements Bulletin 737-53A1388 RB,
dated October 27, 2020, specifies contacting Boeing for repair
instructions or for alternative inspections: This AD requires doing
the repair, or doing the alternative inspections and applicable on-
condition actions using a method approved in accordance with the
procedures specified in paragraph (i) of this AD.
(i) Alternative Methods of Compliance (AMOCs)
(1) The Manager, Los Angeles ACO Branch, FAA, has the authority
to approve AMOCs for this AD, if requested using the procedures
found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your
request to your principal inspector or responsible Flight Standards
Office, as appropriate. If sending information directly to the
manager of the certification office, send it to the attention of the
person identified in Related Information. Information may be emailed
to: [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, 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.
(j) Related Information
(1) 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; fax: 562-627-5210; 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 July 26, 2021.
Lance T. Gant,
Director, Compliance & Airworthiness Division, Aircraft Certification
Service.
[FR Doc. 2021-18069 Filed 8-23-21; 8:45 am]
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