Airworthiness Directives; The Boeing Company Airplanes, 8207-8209 [2020-02863]
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Federal Register / Vol. 85, No. 30 / Thursday, February 13, 2020 / Proposed Rules
Okfuskee
Okmulgee
Ottawa
Pawnee
Pushmataha
Sequoyah
Washington
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[FR Doc. 2020–02833 Filed 2–12–20; 8:45 am]
BILLING CODE 6325–39–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2020–0095; Product
Identifier 2019–NM–192–AD]
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
747–8 and 747–8F series airplanes. This
proposed AD was prompted by an
evaluation by the design approval
holder (DAH) indicating that the skin
lap joints at certain stringers are subject
to widespread fatigue damage (WFD).
This proposed AD would require
modifying the left and right side lap
joints of the fuselage skin, repetitive
post-modification inspections 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 March 30, 2020.
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
jbell on DSKJLSW7X2PROD with PROPOSALS
SUMMARY:
VerDate Sep<11>2014
17:36 Feb 12, 2020
Jkt 250001
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,
Transport Standards 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–2020–0095.
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–2020–0095; 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, the regulatory
evaluation, 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: Bill
Ashforth, Senior Aerospace Engineer,
Airframe Section, FAA, Seattle ACO
Branch, 2200 South 216th St., Des
Moines, WA 98198; phone and fax: 206–
231–3520; email: bill.ashforth@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 the ADDRESSES section. Include
‘‘Docket No. FAA–2020–0095; Product
Identifier 2019–NM–192–AD’’ at the
beginning of your comments. The FAA
specifically invites comments on the
overall regulatory, economic,
environmental, and energy aspects of
this NPRM. The FAA will consider all
comments received by the closing date
and may amend this NPRM because of
those comments.
The FAA will post all comments,
without change, to https://
www.regulations.gov, including any
personal information you provide. The
FAA will also post a report
summarizing each substantive verbal
contact the agency receives about this
proposed AD.
Discussion
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
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Sfmt 4702
8207
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.
The FAA’s WFD final rule (75 FR
69746, November 15, 2010) became
effective on January 14, 2011. 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. For
existing and future airplanes subject to
the WFD rule, the rule requires that
DAHs 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 (75 FR 69746,
November 15, 2010) 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),
while providing operators with certainty
regarding the LOV applicable to their
airplanes.
The FAA received an evaluation by
the DAH indicating that the skin lap
joints at stringers S–6 and S–23 for
Model 747–8 series airplanes, and
stringers S–6, S–23 and S–44 for Model
747–8F series airplanes, are subject to
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Federal Register / Vol. 85, No. 30 / Thursday, February 13, 2020 / Proposed Rules
WFD as a result of cyclic pressurization
of the fuselage. Any fatigue cracking of
the lap joints of the fuselage skin could
go undetected and grow in length. This
condition, if not addressed, could result
in sudden decompression and reduced
structural integrity of the airplane.
Related Service Information Under 1
CFR Part 51
The FAA reviewed Boeing Alert
Requirements Bulletin 747–53A2895
RB, dated September 12, 2019. This
service information describes
procedures for modifying the left and
right side lap joints of the fuselage skin,
repetitive post-modification internal
detailed and surface high frequency
eddy current (HFEC) inspections for
cracking, and applicable on-condition
actions. On-condition actions include
repair. This service information is
reasonably available because the
interested parties have access to it
through their normal course of business
or by the means identified in the
ADDRESSES section.
FAA’s Determination
The FAA is proposing this AD
because the FAA evaluated all the
relevant information and determined
the unsafe condition described
previously is likely to exist or develop
in other products of the same type
design.
Proposed AD Requirements
This proposed AD would require
accomplishment of the actions
identified in Boeing Alert Requirements
Bulletin 747–53A2895 RB, dated
September 12, 2019, described
previously, 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–2020–
0095.
Explanation of Requirements Bulletin
The FAA worked in conjunction with
industry, under the Airworthiness
Directive Implementation Aviation
Rulemaking Committee (AD ARC), to
enhance the AD system. One
enhancement is a process for annotating
which steps in the service information
are ‘‘required for compliance’’ (RC) with
an AD. Boeing has implemented this RC
concept into Boeing service bulletins.
In an effort to further improve the
quality of ADs and AD-related Boeing
service information, a joint process
improvement initiative was worked
between the FAA and Boeing. The
initiative resulted in the development of
a new process in which the service
information more clearly identifies the
actions needed to address the unsafe
condition in the ‘‘Accomplishment
Instructions.’’ The new process results
in a Boeing Requirements Bulletin,
which contains only the actions needed
to address the unsafe condition (i.e.,
only the RC actions).
Explanation of Compliance Time
The compliance time for the
replacement specified in this proposed
AD for addressing WFD was established
to ensure that discrepant structure is
replaced before WFD develops in
airplanes. Standard inspection
techniques cannot be relied on to detect
WFD before it becomes a hazard to
flight. The FAA will not grant any
extensions of the compliance time to
complete any AD-mandated service
bulletin related to WFD without
extensive new data that would
substantiate and clearly warrant such an
extension.
Costs of Compliance
The FAA estimates that this proposed
AD affects 14 airplanes of U.S. registry.
The FAA estimates the following costs
to comply with this proposed AD:
ESTIMATED COSTS FOR REQUIRED ACTIONS *
Action
Labor cost
Parts cost
Cost per product
Modification of S–6 and
S–23.
Post-mod inspection of
S–6 and S–23.
Modification of S–44 .....
Post-mod inspection of
S–44.
1,856 work-hours × $85 per hour = $157,760 ...
*
$157,760 ......................
$2,208,640.
68 work-hours × $85 per hour = $5,780 per inspection cycle.
1,216 work-hours × $85 per hour = $103,360 ...
28 work-hours × $85 per hour = $2,380 per inspection cycle.
$0
$5,780 per inspection
cycle.
$103,360 ......................
$2,380 per inspection
cycle.
$80,920 per inspection
cycle.
$1,447,040.
$33,320 per inspection
cycle.
*
$0
Cost on U.S. operators
* The FAA has received no definitive data that would enable the agency to provide parts cost estimates for the modifications specified in this
proposed AD.
The FAA has received no definitive
data that would enable the agency to
provide cost estimates for the oncondition actions specified in this
proposed AD.
jbell on DSKJLSW7X2PROD 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
VerDate Sep<11>2014
17:36 Feb 12, 2020
Jkt 250001
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
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Sfmt 4702
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) 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.
E:\FR\FM\13FEP1.SGM
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Federal Register / Vol. 85, No. 30 / Thursday, February 13, 2020 / Proposed Rules
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 (AD):
■
The Boeing Company: Docket No. FAA–
2020–0095; Product Identifier 2019–
NM–192–AD.
(a) Comments Due Date
The FAA must receive comments by March
30, 2020.
(b) Affected ADs
None.
(c) Applicability
This AD applies to The Boeing Company
Model 747–8 and 747–8F series airplanes,
certificated in any category, as identified in
Boeing Alert Requirements Bulletin 747–
53A2895 RB, dated September 12, 2019.
(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 skin lap joints at certain stringers are
subject to widespread fatigue damage (WFD).
The FAA is issuing this AD to address
undetected fatigue cracks, which could result
in sudden decompression and reduced
structural integrity of the airplane.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
jbell on DSKJLSW7X2PROD with PROPOSALS
(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 747–53A2895 RB,
dated September 12, 2019, do all applicable
actions identified in, and in accordance with,
the Accomplishment Instructions of Boeing
Alert Requirements Bulletin 747–53A2895
RB, dated September 12, 2019.
Note 1 to paragraph (g): Guidance for
accomplishing the actions required by this
AD can be found in Boeing Alert Service
Bulletin 747–53A2895, dated September 12,
2019, which is referred to in Boeing Alert
Requirements Bulletin 747–53A2895 RB,
dated September 12, 2019.
VerDate Sep<11>2014
17:36 Feb 12, 2020
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8209
(h) Exception to Service Information
Specifications
DEPARTMENT OF TRANSPORTATION
Where Boeing Alert Requirements Bulletin
747–53A2895 RB, dated September 12, 2019,
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 (i) of this AD.
Federal Aviation Administration
(i) Alternative Methods of Compliance
(AMOCs)
Airworthiness Directives; The Boeing
Company Airplanes
(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 (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 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
method, modification deviation, or alteration
deviation must meet the certification basis of
the airplane, and the approval must
specifically refer to this AD.
AGENCY:
(j) Related Information
(1) For more information about this AD,
contact Bill Ashforth, Senior Aerospace
Engineer, Airframe Section, FAA, Seattle
ACO Branch, 2200 South 216th St., Des
Moines, WA 98198; phone and fax: 206–231–
3520; email: bill.ashforth@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,
Transport Standards 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 February 7, 2020.
Gaetano A. Sciortino,
Deputy Director for Strategic Initiatives,
Compliance & Airworthiness Division,
Aircraft Certification Service.
[FR Doc. 2020–02863 Filed 2–12–20; 8:45 am]
BILLING CODE 4910–13–P
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14 CFR Part 39
[Docket No. FAA–2020–0096; Product
Identifier 2019–NM–211–AD]
RIN 2120–AA64
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
The FAA proposes to
supersede Airworthiness Directive (AD)
2016–07–28, which applies to all The
Boeing Company Model DC–9–81 (MD–
81), DC–9–82 (MD–82), DC–9–83 (MD–
83), and DC–9–87 (MD–87) airplanes,
and Model MD–88 airplanes. AD 2016–
07–28 requires repetitive eddy current
high frequency (ETHF) inspections for
any cracking in the left and right side
center wing lower skin, and repair if any
crack is found. Since the FAA issued
AD 2016–07–28, the FAA has
determined it is necessary to expand the
inspection area to include adjacent
stringers with similar stress levels and
to perform an inspection with increased
sensitivity for crack detection. This
proposed AD would retain certain
requirements of AD 2016–07–28,
expand the inspection area, and require
new inspections. 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 March 30, 2020.
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
SUMMARY:
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]]>Agencies
[Federal Register Volume 85, Number 30 (Thursday, February 13, 2020)]
[Proposed Rules]
[Pages 8207-8209]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2020-02863]
=======================================================================
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2020-0095; Product Identifier 2019-NM-192-AD]
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 747-8 and 747-8F series airplanes.
This proposed AD was prompted by an evaluation by the design approval
holder (DAH) indicating that the skin lap joints at certain stringers
are subject to widespread fatigue damage (WFD). This proposed AD would
require modifying the left and right side lap joints of the fuselage
skin, repetitive post-modification inspections 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 March 30,
2020.
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, Transport
Standards 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-2020-0095.
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-
0095; 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, the regulatory evaluation, 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: Bill Ashforth, Senior Aerospace
Engineer, Airframe Section, FAA, Seattle ACO Branch, 2200 South 216th
St., Des Moines, WA 98198; phone and fax: 206-231-3520; 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 the ADDRESSES section. Include ``Docket No. FAA-2020-0095;
Product Identifier 2019-NM-192-AD'' at the beginning of your comments.
The FAA specifically invites comments on the overall regulatory,
economic, environmental, and energy aspects of this NPRM. The FAA will
consider all comments received by the closing date and may amend this
NPRM because of those comments.
The FAA will post all comments, without change, to https://www.regulations.gov, including any personal information you provide.
The FAA will also post a report summarizing each substantive verbal
contact the agency receives about this proposed AD.
Discussion
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.
The FAA's WFD final rule (75 FR 69746, November 15, 2010) became
effective on January 14, 2011. 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. For existing and
future airplanes subject to the WFD rule, the rule requires that DAHs
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 (75 FR 69746, November 15, 2010) 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), while providing operators with
certainty regarding the LOV applicable to their airplanes.
The FAA received an evaluation by the DAH indicating that the skin
lap joints at stringers S-6 and S-23 for Model 747-8 series airplanes,
and stringers S-6, S-23 and S-44 for Model 747-8F series airplanes, are
subject to
[[Page 8208]]
WFD as a result of cyclic pressurization of the fuselage. Any fatigue
cracking of the lap joints of the fuselage skin could go undetected and
grow in length. This condition, if not addressed, could result in
sudden decompression and reduced structural integrity of the airplane.
Related Service Information Under 1 CFR Part 51
The FAA reviewed Boeing Alert Requirements Bulletin 747-53A2895 RB,
dated September 12, 2019. This service information describes procedures
for modifying the left and right side lap joints of the fuselage skin,
repetitive post-modification internal detailed and surface high
frequency eddy current (HFEC) inspections for cracking, and applicable
on-condition actions. On-condition actions include repair. This service
information is reasonably available because the interested parties have
access to it through their normal course of business or by the means
identified in the ADDRESSES section.
FAA's Determination
The FAA is proposing this AD because the FAA evaluated all the
relevant information and determined the unsafe condition described
previously is likely to exist or develop in other products of the same
type design.
Proposed AD Requirements
This proposed AD would require accomplishment of the actions
identified in Boeing Alert Requirements Bulletin 747-53A2895 RB, dated
September 12, 2019, described previously, 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-2020-0095.
Explanation of Requirements Bulletin
The FAA worked in conjunction with industry, under the
Airworthiness Directive Implementation Aviation Rulemaking Committee
(AD ARC), to enhance the AD system. One enhancement is a process for
annotating which steps in the service information are ``required for
compliance'' (RC) with an AD. Boeing has implemented this RC concept
into Boeing service bulletins.
In an effort to further improve the quality of ADs and AD-related
Boeing service information, a joint process improvement initiative was
worked between the FAA and Boeing. The initiative resulted in the
development of a new process in which the service information more
clearly identifies the actions needed to address the unsafe condition
in the ``Accomplishment Instructions.'' The new process results in a
Boeing Requirements Bulletin, which contains only the actions needed to
address the unsafe condition (i.e., only the RC actions).
Explanation of Compliance Time
The compliance time for the replacement specified in this proposed
AD for addressing WFD was established to ensure that discrepant
structure is replaced before WFD develops in airplanes. Standard
inspection techniques cannot be relied on to detect WFD before it
becomes a hazard to flight. The FAA will not grant any extensions of
the compliance time to complete any AD-mandated service bulletin
related to WFD without extensive new data that would substantiate and
clearly warrant such an extension.
Costs of Compliance
The FAA estimates that this proposed AD affects 14 airplanes of
U.S. registry. The FAA estimates the following costs to comply with
this proposed AD:
Estimated Costs for Required Actions *
----------------------------------------------------------------------------------------------------------------
Cost on U.S.
Action Labor cost Parts cost Cost per product operators
----------------------------------------------------------------------------------------------------------------
Modification of S-6 and S-23... 1,856 work-hours x $85 * $157,760.......... $2,208,640.
per hour = $157,760.
Post-mod inspection of S-6 and 68 work-hours x $85 per $0 $5,780 per $80,920 per
S-23. hour = $5,780 per inspection cycle. inspection cycle.
inspection cycle.
Modification of S-44........... 1,216 work-hours x $85 * $103,360.......... $1,447,040.
per hour = $103,360.
Post-mod inspection of S-44.... 28 work-hours x $85 per $0 $2,380 per $33,320 per
hour = $2,380 per inspection cycle. inspection cycle.
inspection cycle.
----------------------------------------------------------------------------------------------------------------
* The FAA has received no definitive data that would enable the agency to provide parts cost estimates for the
modifications specified in this proposed AD.
The FAA has received no definitive data that would enable the
agency to provide 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) 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.
[[Page 8209]]
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 (AD):
The Boeing Company: Docket No. FAA-2020-0095; Product Identifier
2019-NM-192-AD.
(a) Comments Due Date
The FAA must receive comments by March 30, 2020.
(b) Affected ADs
None.
(c) Applicability
This AD applies to The Boeing Company Model 747-8 and 747-8F
series airplanes, certificated in any category, as identified in
Boeing Alert Requirements Bulletin 747-53A2895 RB, dated September
12, 2019.
(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 skin lap joints at certain
stringers are subject to widespread fatigue damage (WFD). The FAA is
issuing this AD to address undetected fatigue cracks, which could
result in sudden decompression 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 747-53A2895 RB, dated September 12,
2019, do all applicable actions identified in, and in accordance
with, the Accomplishment Instructions of Boeing Alert Requirements
Bulletin 747-53A2895 RB, dated September 12, 2019.
Note 1 to paragraph (g): Guidance for accomplishing the actions
required by this AD can be found in Boeing Alert Service Bulletin
747-53A2895, dated September 12, 2019, which is referred to in
Boeing Alert Requirements Bulletin 747-53A2895 RB, dated September
12, 2019.
(h) Exception to Service Information Specifications
Where Boeing Alert Requirements Bulletin 747-53A2895 RB, dated
September 12, 2019, 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 (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 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 (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 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
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 Bill Ashforth,
Senior Aerospace Engineer, Airframe Section, FAA, Seattle ACO
Branch, 2200 South 216th St., Des Moines, WA 98198; phone and fax:
206-231-3520; 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, Transport Standards 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 February 7, 2020.
Gaetano A. Sciortino,
Deputy Director for Strategic Initiatives, Compliance & Airworthiness
Division, Aircraft Certification Service.
[FR Doc. 2020-02863 Filed 2-12-20; 8:45 am]
BILLING CODE 4910-13-P
