Airworthiness Directives; The Boeing Company Airplanes, 39239-39241 [2019-17008]
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Federal Register / Vol. 84, No. 154 / Friday, August 9, 2019 / Proposed Rules
Applicability
As discussed above, these special
conditions are applicable to Boeing
Model 737 series airplanes. Should
Boeing apply at a later date for a change
to the type certificate to include another
model incorporating the same novel or
unusual design feature, these special
conditions would apply to that model as
well.
Conclusion
This action affects only one novel or
unusual design feature on one model
series of airplanes. It is not a rule of
general applicability.
List of Subjects in 14 CFR Part 25
Aircraft, Aviation safety, Reporting
and recordkeeping requirements.
Authority Citation
The authority citation for these
special conditions is as follows:
khammond on DSKBBV9HB2PROD with PROPOSALS
Authority: 49 U.S.C. 106(f), 106(g), 40113,
44701, 44702, 44704.
The Proposed Special Conditions
Accordingly, the Federal Aviation
Administration (FAA) proposes the
following special conditions as part of
the type certification basis for Boeing
Model 737 series airplanes.
In addition to the requirements of
§ 25.562, passenger seats incorporating
an inertia locking device (ILD) must
meet the following:
1. Level of Protection Provided by
ILD—It must be demonstrated by test
that the seats and attachments, when
subject to the emergency-landing
dynamic conditions specified in
§ 25.562, and with one ILD not
deployed, do not experience structural
failure that could result in:
a. Separation of the seat from the
airplane floor.
b. Separation of any part of the seat
that could form a hazard to the seat
occupant or any other airplane
occupant.
c. Failure of the occupant restraint or
any other condition that could result in
the occupant separating from the seat.
2. Protection Provided Below and
Above the ILD Actuation Condition—If
step-change effects on occupant
protection exist for impacts below and
above that at which the ILD deploys,
tests must be performed to demonstrate
that the occupant is shown to be
protected at any condition at which the
ILD does or does not deploy, up to the
maximum severity pulse specified by
§ 25.562. Test conditions must take into
account any necessary tolerances for
deployment.
3. Protection Over a Range of Crash
Pulse Vectors—The ILD must be shown
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Jkt 247001
to function as intended for all test
vectors specified in § 25.562.
4. Protection During Secondary
Impacts—The ILD activation setting
must be demonstrated to maximize the
probability of the protection being
available when needed, considering a
secondary impact that is above the
severity at which the device is intended
to deploy up to the impact loading
required by § 25.562.
5. Protection of Occupants other than
50th Percentile—Protection of
occupants for a range of stature from a
two-year-old child to a ninety-five
percentile male must be shown.
6. Inadvertent Operation—It must be
shown that any inadvertent operation of
the ILD does not affect the performance
of the device during a subsequent
emergency landing.
7. Installation Protection—It must be
shown that the ILD installation is
protected from contamination and
interference from foreign objects.
8. Reliability—The performance of the
ILD must not be altered by the effects of
wear, manufacturing tolerances, aging/
drying of lubricants, and corrosion.
9. Maintenance and Functional
Checks—The design, installation and
operation of the ILD must be such that
it is possible to functionally check the
device in place. Additionally, a
functional check method and a
maintenance check interval must be
included in the seat installer’s
instructions for continued airworthiness
(ICA) document.
10. Release Function—If a means
exists to release an inadvertently
activated ILD, the release means must
not introduce additional hidden failures
that would prevent the ILD from
functioning properly.
Issued in Des Moines, Washington, on
August 5, 2019.
Victor Wicklund,
Manager, Transport Standards Branch, Policy
and Innovation Division, Aircraft
Certification Service.
[FR Doc. 2019–17050 Filed 8–8–19; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2019–0583; Product
Identifier 2019–NM–063–AD]
RIN 2120–AA64
Airworthiness Directives; The Boeing
Company Airplanes
Federal Aviation
Administration (FAA), DOT.
AGENCY:
PO 00000
Frm 00029
Fmt 4702
Sfmt 4702
39239
Notice of proposed rulemaking
(NPRM).
ACTION:
The FAA proposes to adopt a
new airworthiness directive (AD) for
certain The Boeing Company Model
787–8 airplanes. This proposed AD was
prompted by a report of an escapement
from the wing spar terminal fitting
supplier indicating that the engineering
requirements provided by Boeing for
controlling machine mismatch were
incorrect for part faying surfaces, which
can result in a reduced fatigue
capability at the interface of the side of
body (SOB) rib. This proposed AD
would require repetitive inspections for
fatigue cracking and applicable oncondition actions for the SOB rib webs
where fastener locations attach the
terminal fittings. 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 September 23,
2019.
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–2019–0583.
SUMMARY:
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–2019–
0583; or in person at Docket Operations
between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
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39240
Federal Register / Vol. 84, No. 154 / Friday, August 9, 2019 / Proposed Rules
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:
Allen Rauschendorfer, Aerospace
Engineer, Airframe Section, FAA,
Seattle ACO Branch, 2200 South 216th
St., Des Moines, WA 98198; phone and
fax: 206–231–3528; email:
Allen.Rauschendorfer@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–2019–0583; Product
Identifier 2019–NM–063–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
received, 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 received about this proposed
AD.
Discussion
The FAA received a report of an
escapement from the wing spar terminal
fitting supplier indicating that the
engineering requirements provided by
Boeing for controlling machine
mismatch were incorrect for part faying
surfaces, which can result in a reduced
fatigue capability at the interface of the
SOB rib. The engineering-defined
machined mismatch requirement of
0.001 inch was incorrectly documented
as 0.010 inch. Inspection of parts
internal to Boeing production found
machine mismatch on faying surfaces
exceeding the 0.001-inch requirement.
This condition, if not addressed, could
result in undetected fatigue cracks.
Undetected fatigue cracks can grow to
weaken primary wing structure where it
cannot sustain limit load, which could
adversely affect the structural integrity
of the airplane.
Related Service Information Under 1
CFR Part 51
The FAA reviewed Boeing Alert
Requirements Bulletin B787–81205–
SB570036–00 RB, Issue 001, dated
December 14, 2018. The service
information describes procedures for
repetitive high frequency eddy current
or ultrasonic inspections for fatigue
cracking and applicable on-condition
actions for the SOB rib webs where
fastener locations attach the terminal
fittings. 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 agency 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 B787–81205–SB570036–00 RB,
Issue 001, dated December 14, 2018,
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–2019–
0583.
Costs of Compliance
The FAA estimates that this proposed
AD affects 1 airplane of U.S. registry.
The FAA estimates the following costs
to comply with this proposed AD:
khammond on DSKBBV9HB2PROD with PROPOSALS
ESTIMATED COSTS FOR REQUIRED ACTIONS
Action
Labor cost
Inspection ...............
Up to 32 work-hours × $85 per
hour = Up to $2,720 per inspection cycle.
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.
According to the manufacturer, some
or all of the costs of this proposed AD
may be covered under warranty, thereby
reducing the cost impact on affected
individuals. The FAA does not control
warranty coverage for affected
individuals. As a result, the FAA has
included all known costs in our cost
estimate.
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
VerDate Sep<11>2014
16:41 Aug 08, 2019
Jkt 247001
Parts cost
$960
Cost per product
Cost on U.S. operators
Up to $3,680 per inspection cycle
Up to $3,680 per inspection
cycle.
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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Fmt 4702
Sfmt 4702
This proposed AD is issued in
accordance with authority delegated by
the Executive Director, Aircraft
Certification Service, as authorized by
FAA Order 8000.51C. In accordance
with that order, issuance of ADs is
normally a function of the Compliance
and Airworthiness Division, but during
this transition period, the Executive
Director has delegated the authority to
issue ADs applicable to transport
category airplanes and associated
appliances to the Director of the System
Oversight Division.
Regulatory Findings
The FAA determined that this
proposed AD would not have federalism
implications under Executive Order
13132. This proposed AD would not
E:\FR\FM\09AUP1.SGM
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Federal Register / Vol. 84, No. 154 / Friday, August 9, 2019 / Proposed Rules
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.
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–
2019–0583; Product Identifier 2019–
NM–063–AD.
(a) Comments Due Date
The FAA must receive comments by
September 23, 2019.
(b) Affected ADs
None.
khammond on DSKBBV9HB2PROD with PROPOSALS
(c) Applicability
This AD applies to The Boeing Company
Model 787–8 airplanes, certificated in any
category, as identified in Boeing Alert
Requirements Bulletin B787–81205–
SB570036–00 RB, Issue 001, dated December
14, 2018.
(d) Subject
Air Transport Association (ATA) of
America Code 57, Wings.
(e) Unsafe Condition
This AD was prompted by a report of an
escapement from the wing spar terminal
fitting supplier indicating that the
engineering requirements provided by Boeing
for controlling machine mismatch were
incorrect for part faying surfaces, which can
result in a reduced fatigue capability at the
interface of the side of body (SOB) rib. The
VerDate Sep<11>2014
15:57 Aug 08, 2019
Jkt 247001
FAA is issuing this AD to address fatigue
cracks in the left and right SOB rib webs
common to the front and rear wing spar
terminal fittings. Undetected fatigue cracks
can grow to weaken primary wing structure
where it cannot sustain limit load, which
could adversely affect the 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 B787–81205–
SB570036–00 RB, Issue 001, dated December
14, 2018, do all applicable actions identified
in, and in accordance with, the
Accomplishment Instructions of Boeing Alert
Requirements Bulletin B787–81205–
SB570036–00 RB, Issue 001, dated December
14, 2018.
Note 1 to paragraph (g): Guidance for
accomplishing the actions required by this
AD can be found in Boeing Alert Service
Bulletin B787–81205–SB570036–00, Issue
001, dated December 14, 2018, which is
referred to in Boeing Alert Requirements
Bulletin B787–81205–SB570036–00 RB, Issue
001, dated December 14, 2018.
(h) Exception to Service Information
Specifications
Where Boeing Alert Requirements Bulletin
B787–81205–SB570036–00 RB, Issue 001,
dated December 14, 2018, 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 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.
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39241
(j) Related Information
(1) For more information about this AD,
contact Allen Rauschendorfer, Aerospace
Engineer, Airframe Section, FAA, Seattle
ACO Branch, 2200 South 216th St., Des
Moines, WA 98198; phone and fax: 206–231–
3528; email: Allen.Rauschendorfer@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 in Des Moines, Washington, on July
26, 2019.
Michael Kaszycki,
Acting Director, System Oversight Division,
Aircraft Certification Service.
[FR Doc. 2019–17008 Filed 8–8–19; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2019–0602; Product
Identifier 2019–NM–016–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
supersede Airworthiness Directive (AD)
2010–26–01, which applies to certain
The Boeing Company Model 777–200
series airplanes. AD 2010–26–01
requires installing a new insulation
blanket on the latch beam firewall of
each thrust reverser (T/R) half. Since AD
2010–26–01 was issued, the agency
received a report that the T/R affected
by AD 2010–26–01 has the potential to
be installed on airplanes outside of the
applicability of that AD. This proposed
AD would retain the requirements of
2010–26–01. This proposed AD would
also add airplanes to the applicability.
For those airplanes, this proposed AD
would require an inspection to
determine if the installed T/R has an
affected part number and, if an affected
part number is found, installation of a
new insulation blanket. The FAA is
proposing this AD to address the unsafe
condition on these products.
SUMMARY:
E:\FR\FM\09AUP1.SGM
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]]>Agencies
[Federal Register Volume 84, Number 154 (Friday, August 9, 2019)]
[Proposed Rules]
[Pages 39239-39241]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2019-17008]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2019-0583; Product Identifier 2019-NM-063-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 787-8 airplanes. This proposed AD
was prompted by a report of an escapement from the wing spar terminal
fitting supplier indicating that the engineering requirements provided
by Boeing for controlling machine mismatch were incorrect for part
faying surfaces, which can result in a reduced fatigue capability at
the interface of the side of body (SOB) rib. This proposed AD would
require repetitive inspections for fatigue cracking and applicable on-
condition actions for the SOB rib webs where fastener locations attach
the terminal fittings. 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 September
23, 2019.
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-2019-0583.
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-2019-
0583; or in person at Docket Operations between 9 a.m. and 5 p.m.,
Monday through Friday, except Federal holidays.
[[Page 39240]]
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: Allen Rauschendorfer, Aerospace
Engineer, Airframe Section, FAA, Seattle ACO Branch, 2200 South 216th
St., Des Moines, WA 98198; phone and fax: 206-231-3528; 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-2019-0583;
Product Identifier 2019-NM-063-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 received, 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 received about this proposed AD.
Discussion
The FAA received a report of an escapement from the wing spar
terminal fitting supplier indicating that the engineering requirements
provided by Boeing for controlling machine mismatch were incorrect for
part faying surfaces, which can result in a reduced fatigue capability
at the interface of the SOB rib. The engineering-defined machined
mismatch requirement of 0.001 inch was incorrectly documented as 0.010
inch. Inspection of parts internal to Boeing production found machine
mismatch on faying surfaces exceeding the 0.001-inch requirement. This
condition, if not addressed, could result in undetected fatigue cracks.
Undetected fatigue cracks can grow to weaken primary wing structure
where it cannot sustain limit load, which could adversely affect the
structural integrity of the airplane.
Related Service Information Under 1 CFR Part 51
The FAA reviewed Boeing Alert Requirements Bulletin B787-81205-
SB570036-00 RB, Issue 001, dated December 14, 2018. The service
information describes procedures for repetitive high frequency eddy
current or ultrasonic inspections for fatigue cracking and applicable
on-condition actions for the SOB rib webs where fastener locations
attach the terminal fittings. 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 agency 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 B787-81205-SB570036-00
RB, Issue 001, dated December 14, 2018, 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-2019-0583.
Costs of Compliance
The FAA estimates that this proposed AD affects 1 airplane 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
----------------------------------------------------------------------------------------------------------------
Inspection.................... Up to 32 work-hours $960 Up to $3,680 per Up to $3,680 per
x $85 per hour = Up inspection cycle. inspection cycle.
to $2,720 per
inspection cycle.
----------------------------------------------------------------------------------------------------------------
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.
According to the manufacturer, some or all of the costs of this
proposed AD may be covered under warranty, thereby reducing the cost
impact on affected individuals. The FAA does not control warranty
coverage for affected individuals. As a result, the FAA has included
all known costs in our cost estimate.
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.
This proposed AD is issued in accordance with authority delegated
by the Executive Director, Aircraft Certification Service, as
authorized by FAA Order 8000.51C. In accordance with that order,
issuance of ADs is normally a function of the Compliance and
Airworthiness Division, but during this transition period, the
Executive Director has delegated the authority to issue ADs applicable
to transport category airplanes and associated appliances to the
Director of the System Oversight Division.
Regulatory Findings
The FAA determined that this proposed AD would not have federalism
implications under Executive Order 13132. This proposed AD would not
[[Page 39241]]
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.
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-2019-0583; Product Identifier
2019-NM-063-AD.
(a) Comments Due Date
The FAA must receive comments by September 23, 2019.
(b) Affected ADs
None.
(c) Applicability
This AD applies to The Boeing Company Model 787-8 airplanes,
certificated in any category, as identified in Boeing Alert
Requirements Bulletin B787-81205-SB570036-00 RB, Issue 001, dated
December 14, 2018.
(d) Subject
Air Transport Association (ATA) of America Code 57, Wings.
(e) Unsafe Condition
This AD was prompted by a report of an escapement from the wing
spar terminal fitting supplier indicating that the engineering
requirements provided by Boeing for controlling machine mismatch
were incorrect for part faying surfaces, which can result in a
reduced fatigue capability at the interface of the side of body
(SOB) rib. The FAA is issuing this AD to address fatigue cracks in
the left and right SOB rib webs common to the front and rear wing
spar terminal fittings. Undetected fatigue cracks can grow to weaken
primary wing structure where it cannot sustain limit load, which
could adversely affect the 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 B787-81205-SB570036-00 RB, Issue 001,
dated December 14, 2018, do all applicable actions identified in,
and in accordance with, the Accomplishment Instructions of Boeing
Alert Requirements Bulletin B787-81205-SB570036-00 RB, Issue 001,
dated December 14, 2018.
Note 1 to paragraph (g): Guidance for accomplishing the actions
required by this AD can be found in Boeing Alert Service Bulletin
B787-81205-SB570036-00, Issue 001, dated December 14, 2018, which is
referred to in Boeing Alert Requirements Bulletin B787-81205-
SB570036-00 RB, Issue 001, dated December 14, 2018.
(h) Exception to Service Information Specifications
Where Boeing Alert Requirements Bulletin B787-81205-SB570036-00
RB, Issue 001, dated December 14, 2018, 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 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 Allen
Rauschendorfer, Aerospace Engineer, Airframe Section, FAA, Seattle
ACO Branch, 2200 South 216th St., Des Moines, WA 98198; phone and
fax: 206-231-3528; 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 in Des Moines, Washington, on July 26, 2019.
Michael Kaszycki,
Acting Director, System Oversight Division, Aircraft Certification
Service.
[FR Doc. 2019-17008 Filed 8-8-19; 8:45 am]
BILLING CODE 4910-13-P
