Airworthiness Directives; The Boeing Company Airplanes, 58636-58638 [2019-23788]
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Federal Register / Vol. 84, No. 212 / Friday, November 1, 2019 / Proposed Rules
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Requirements
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, EASA AD 2019–
0167.
(h) Exception to EASA AD 2019–0167
The ‘‘Remarks’’ section of EASA AD 2019–
0167 does not apply to this AD.
(i) No Reporting Requirement
Although the service information
referenced in EASA AD 2019–0167 specifies
to submit certain information to the
manufacturer, and specifies that action as
‘‘RC’’ (required for compliance), this AD does
not include that requirement.
khammond on DSKJM1Z7X2PROD with PROPOSALS
(j) Other FAA AD Provisions
The following provisions also apply to this
AD:
(1) Alternative Methods of Compliance
(AMOCs): The Manager, International
Section, Transport Standards 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 International Section, send it
to the attention of the person identified in
paragraph (k)(2) of this AD. Information may
be emailed to: 9-ANM-116-AMOCREQUESTS@faa.gov. 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.
(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, International Section,
Transport Standards Branch, FAA; or EASA;
or Airbus SAS’s EASA Design Organization
Approval (DOA). If approved by the DOA,
the approval must include the DOAauthorized signature.
(3) Required for Compliance (RC): For any
service information referenced in EASA AD
2019–0167 that contains RC procedures and
tests: Except as required by paragraph (2) of
EASA AD 2019–0167 and paragraphs (i) and
(j)(2) of this AD, RC procedures and tests
must be done to comply with this AD; any
procedures or tests that are not identified as
RC are recommended. Those procedures and
tests that are not identified 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
procedures and tests identified as RC can be
done and the airplane can be put back in an
airworthy condition. Any substitutions or
changes to procedures or tests identified as
RC require approval of an AMOC.
VerDate Sep<11>2014
19:05 Oct 31, 2019
Jkt 250001
(k) Related Information
(1) For information about EASA AD 2019–
0167, contact the EASA, Konrad-AdenauerUfer 3, 50668 Cologne, Germany; telephone
+49 221 89990 6017; email ADs@
easa.europa.eu; internet
www.easa.europa.eu. You may find this
EASA AD on the EASA website at https://
ad.easa.europa.eu. You may view this
material 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.
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–2019–0861.
(2) For more information about this AD,
contact Sanjay Ralhan, Aerospace Engineer,
International Section, Transport Standards
Branch, FAA, 2200 South 216th St., Des
Moines, WA 98198; telephone and fax 206–
231–3223.
Issued in Des Moines, Washington, on
October 24, 2019.
Dionne Palermo,
Acting Director, System Oversight Division,
Aircraft Certification Service.
[FR Doc. 2019–23867 Filed 10–31–19; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2019–0719; Product
Identifier 2019–NM–137–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
787–8 airplanes. This proposed AD was
prompted by a report of failure of a wing
strut leak test due to a missing bolt on
the firewall. This proposed AD would
require a one-time leak test of the strut
upper spar areas for the left and right
wing struts, and corrective action if
necessary. 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 December 16,
2019.
ADDRESSES: You may send comments,
using the procedures found in 14 CFR
11.43 and 11.45, by any of the following
methods:
SUMMARY:
PO 00000
Frm 00003
Fmt 4702
Sfmt 4702
• 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 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.
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–
0719; 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: Tak
Kobayashi, Aerospace Engineer,
Propulsion Section, FAA, Seattle ACO
Branch, 2200 South 216th St., Des
Moines, WA 98198; phone and fax: 206–
231–3553; email: takahisa.kobayashi@
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–2019–0719; Product
Identifier 2019–NM–137–AD’’ at the
beginning of your comments. The
agency 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://
E:\FR\FM\01NOP1.SGM
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Federal Register / Vol. 84, No. 212 / Friday, November 1, 2019 / Proposed Rules
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.
Discussion
The FAA received a report indicating
failure of a wing strut leak test due to
a missing bolt on the firewall. Failure
during manufacture to install a bolt that
plugs a strut firewall penetration would
result in a hole in the firewall. This
condition, if not addressed, could allow
flammable fluid leakage in the strut
area. This leakage could overwhelm the
drainage provision, enter the engine
compartment, and result in an
uncontrollable engine fire and
consequent structural failure of the
wing.
Proposed AD Requirements
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.
Costs of Compliance
This proposed AD would require a
one-time leak test of the strut upper spar
areas for the left and right wing struts,
and corrective action if necessary.
The FAA estimates that this proposed
AD would affect 2 airplanes of U.S.
registry. The agency estimates the
following costs to comply with this
proposed AD:
ESTIMATED COSTS FOR REQUIRED ACTIONS
Labor cost
Parts cost
Cost per
product
Cost on U.S.
operators
3 work-hours × $85 per hour = $255 ..........................................................................................
$0
$255
$510
The FAA estimates the following
costs to do any necessary on-condition
action that would be required based on
the results of any proposed actions. The
FAA has no way of determining the
number of aircraft that might need this
on-condition action:
ESTIMATED COSTS OF ON-CONDITION ACTION
Labor cost
Parts cost
Cost per
product
1 work-hour × $85 per hour = $85 .............................................
Minimal .......................................................................................
$85
khammond on DSKJM1Z7X2PROD with PROPOSALS
Authority for This Rulemaking
Title 49 of the United States Code
specifies the FAA’s authority to issue
rules on aviation safety. Subtitle I,
section 106, describes the authority of
the FAA Administrator. Subtitle VII:
Aviation Programs, describes in more
detail the scope of the Agency’s
authority.
The FAA is issuing this rulemaking
under the authority described in
Subtitle VII, Part A, Subpart III, Section
44701: ‘‘General requirements.’’ Under
that section, Congress charges the FAA
with promoting safe flight of civil
aircraft in air commerce by prescribing
regulations for practices, methods, and
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
VerDate Sep<11>2014
19:05 Oct 31, 2019
Jkt 250001
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
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.
PO 00000
Frm 00004
Fmt 4702
Sfmt 4702
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–
2019–0719; Product Identifier 2019–
NM–137–AD.
(a) Comments Due Date
The FAA must receive comments by
December 16, 2019.
(b) Affected ADs
None.
(c) Applicability
This AD applies to The Boeing Company
Model 787–8 airplanes, certificated in any
category, line numbers 6, 11, 17, 19, 20, 21,
23, 25 through 30 inclusive, and 32 through
38 inclusive.
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Federal Register / Vol. 84, No. 212 / Friday, November 1, 2019 / Proposed Rules
(d) Subject
Air Transport Association (ATA) of
America Code 54, Nacelles/Pylons.
(e) Unsafe Condition
This AD was prompted by a report of
failure of a wing strut leak test due to a
missing bolt on the firewall. The FAA is
issuing this AD to address a hole in the
firewall, which could allow flammable fluid
leakage in the strut area. This leakage could
overwhelm the drainage provision, enter the
engine compartment, and result in an
uncontrollable engine fire and consequent
structural failure of the wing.
khammond on DSKJM1Z7X2PROD with PROPOSALS
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Leak Test and Corrective Action
Within 12 months after the effective date
of this AD: Do a one-time leak (functional)
test of the strut upper spar areas for the left
and right wing struts, by doing the actions
specified in paragraphs (g)(1) through (5) of
this AD. A review of airplane maintenance
records is acceptable in lieu of this test if it
can be conclusively determined from that
review that the leak test was previously
accomplished and successfully completed.
(1) Put a plug in the strut forward drain
outlet (this drain outlet is labeled as ‘‘pylon
strut’’). Put an empty container below the
strut forward drain outlet to collect water
drained through this outlet.
(2) Apply 381 to 387 fluid ounces (11.3 to
11.4 liters) of water in 2.5 to 3.5 minutes, to
the strut upper spar (strut areas between the
forward and mid-vapor barriers).
(3) Make sure that no leakage occurred
after doing the action specified in paragraph
(g)(2) of this AD.
(4) Remove the plug from the strut forward
drain outlet and make sure that the water is
drained through the strut forward drain
outlet only.
(5) After 3 minutes from accomplishing the
action specified in paragraph (g)(4) of this
AD, measure the water collected in the
container, and do the applicable actions
specified in paragraphs (g)(5)(i) through (iii)
of this AD.
(i) If leaks were found, do corrective action
before further flight using a method approved
in accordance with the procedures specified
in paragraph (h) of this AD.
(ii) If no leaks were found and less than
354 fluid ounces (10.5 liters) of water is
collected in the container, do corrective
action before further flight using a method
approved in accordance with the procedures
specified in paragraph (h) of this AD.
(ii) Before further flight after
accomplishing any corrective action required
by paragraph (g)(5)(i) or (ii) of this AD, repeat
the actions specified in paragraphs (g)(1)
through (5) of this AD until successful
completion of the test (i.e., no leaks are found
and 354 fluid ounces (10.5 liters) of water or
more is measured in the container).
Note 1 to paragraph (g): Additional
guidance for performing the leak (functional)
test can be found in Boeing Model 787
Aircraft Maintenance Manual (AMM), 54–
65–01, Strut Spar—Upper—Functional Test.
VerDate Sep<11>2014
19:05 Oct 31, 2019
Jkt 250001
(h) 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 (i)(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.
(i) Related Information
(1) For more information about this AD,
contact Tak Kobayashi, Aerospace Engineer,
Propulsion Section, FAA, Seattle ACO
Branch, 2200 South 216th St., Des Moines,
WA 98198; phone and fax: 206–231–3553;
email: takahisa.kobayashi@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. For information on
the availability of this material at the FAA,
call 206–231–3195.
Issued in Des Moines, Washington, on
October 24, 2019.
Dionne Palermo,
Acting Director, System Oversight Division,
Aircraft Certification Service.
[FR Doc. 2019–23788 Filed 10–31–19; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2019–0827; Product
Identifier 2019–SW–014–AD]
RIN 2120–AA64
Airworthiness Directives; Airbus
Helicopters (Type Certificate
Previously Held by Eurocopter France)
Helicopters
Federal Aviation
Administration (FAA), DOT.
AGENCY:
PO 00000
Frm 00005
Fmt 4702
Sfmt 4702
Notice of proposed rulemaking
(NPRM).
ACTION:
The FAA proposes to
supersede Airworthiness Directive (AD)
2011–12–07 for Eurocopter France (now
Airbus Helicopters) Model SA–365C,
SA–365C1, SA–365C2, SA–365N, SA–
365N1, AS–365N2, AS 365 N3, and SA–
366G1 helicopters. AD 2011–12–07
currently requires repetitively
inspecting the adhesive bead between
the bushings and the Starflex star
(Starflex) arms and the Starflex arm
ends. Since the FAA issued AD 2011–
12–07, Airbus Helicopters has
developed an improved Starflex. This
proposed AD would retain the
requirements of AD 2011–12–07 and
revise the Applicability paragraph by
omitting helicopters with the improved
Starflex installed. 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 December 31,
2019.
ADDRESSES: You may send comments by
any of the following methods:
• Federal eRulemaking Docket: Go to
https://www.regulations.gov. Follow the
online instructions for sending your
comments electronically.
• Fax: 202–493–2251.
• Mail: Send comments to the U.S.
Department of Transportation, Docket
Operations, M–30, West Building
Ground Floor, Room W12–140, 1200
New Jersey Avenue SE, Washington, DC
20590–0001.
• Hand Delivery: Deliver to the
‘‘Mail’’ address between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays.
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–
0827; 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 proposed
AD, the European Aviation Safety
Agency (EASA) AD, the economic
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 service information identified in
this proposed rule, contact Airbus
Helicopters, 2701 N Forum Drive, Grand
Prairie, TX 75052; telephone (972) 641–
0000 or (800) 232–0323; fax (972) 641–
3775; or at https://
www.helicopters.airbus.com/website/
en/ref/Technical-Support_73.html. You
E:\FR\FM\01NOP1.SGM
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]]>Agencies
[Federal Register Volume 84, Number 212 (Friday, November 1, 2019)]
[Proposed Rules]
[Pages 58636-58638]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2019-23788]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2019-0719; Product Identifier 2019-NM-137-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 failure of a wing strut leak test due to a
missing bolt on the firewall. This proposed AD would require a one-time
leak test of the strut upper spar areas for the left and right wing
struts, and corrective action if necessary. 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 December
16, 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 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.
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-
0719; 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: Tak Kobayashi, Aerospace Engineer,
Propulsion Section, FAA, Seattle ACO Branch, 2200 South 216th St., Des
Moines, WA 98198; phone and fax: 206-231-3553; 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-2019-0719;
Product Identifier 2019-NM-137-AD'' at the beginning of your comments.
The agency 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:/
/
[[Page 58637]]
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.
Discussion
The FAA received a report indicating failure of a wing strut leak
test due to a missing bolt on the firewall. Failure during manufacture
to install a bolt that plugs a strut firewall penetration would result
in a hole in the firewall. This condition, if not addressed, could
allow flammable fluid leakage in the strut area. This leakage could
overwhelm the drainage provision, enter the engine compartment, and
result in an uncontrollable engine fire and consequent structural
failure of the wing.
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 a one-time leak test of the strut
upper spar areas for the left and right wing struts, and corrective
action if necessary.
Costs of Compliance
The FAA estimates that this proposed AD would affect 2 airplanes of
U.S. registry. The agency estimates the following costs to comply with
this proposed AD:
Estimated Costs for Required Actions
----------------------------------------------------------------------------------------------------------------
Cost per Cost on U.S.
Labor cost Parts cost product operators
----------------------------------------------------------------------------------------------------------------
3 work-hours x $85 per hour = $255........................... $0 $255 $510
----------------------------------------------------------------------------------------------------------------
The FAA estimates the following costs to do any necessary on-
condition action that would be required based on the results of any
proposed actions. The FAA has no way of determining the number of
aircraft that might need this on-condition action:
Estimated Costs of On-Condition Action
------------------------------------------------------------------------
Cost per
Labor cost Parts cost product
------------------------------------------------------------------------
1 work-hour x $85 per hour = Minimal............... $85
$85.
------------------------------------------------------------------------
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
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-2019-0719; Product Identifier
2019-NM-137-AD.
(a) Comments Due Date
The FAA must receive comments by December 16, 2019.
(b) Affected ADs
None.
(c) Applicability
This AD applies to The Boeing Company Model 787-8 airplanes,
certificated in any category, line numbers 6, 11, 17, 19, 20, 21,
23, 25 through 30 inclusive, and 32 through 38 inclusive.
[[Page 58638]]
(d) Subject
Air Transport Association (ATA) of America Code 54, Nacelles/
Pylons.
(e) Unsafe Condition
This AD was prompted by a report of failure of a wing strut leak
test due to a missing bolt on the firewall. The FAA is issuing this
AD to address a hole in the firewall, which could allow flammable
fluid leakage in the strut area. This leakage could overwhelm the
drainage provision, enter the engine compartment, and result in an
uncontrollable engine fire and consequent structural failure of the
wing.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Leak Test and Corrective Action
Within 12 months after the effective date of this AD: Do a one-
time leak (functional) test of the strut upper spar areas for the
left and right wing struts, by doing the actions specified in
paragraphs (g)(1) through (5) of this AD. A review of airplane
maintenance records is acceptable in lieu of this test if it can be
conclusively determined from that review that the leak test was
previously accomplished and successfully completed.
(1) Put a plug in the strut forward drain outlet (this drain
outlet is labeled as ``pylon strut''). Put an empty container below
the strut forward drain outlet to collect water drained through this
outlet.
(2) Apply 381 to 387 fluid ounces (11.3 to 11.4 liters) of water
in 2.5 to 3.5 minutes, to the strut upper spar (strut areas between
the forward and mid-vapor barriers).
(3) Make sure that no leakage occurred after doing the action
specified in paragraph (g)(2) of this AD.
(4) Remove the plug from the strut forward drain outlet and make
sure that the water is drained through the strut forward drain
outlet only.
(5) After 3 minutes from accomplishing the action specified in
paragraph (g)(4) of this AD, measure the water collected in the
container, and do the applicable actions specified in paragraphs
(g)(5)(i) through (iii) of this AD.
(i) If leaks were found, do corrective action before further
flight using a method approved in accordance with the procedures
specified in paragraph (h) of this AD.
(ii) If no leaks were found and less than 354 fluid ounces (10.5
liters) of water is collected in the container, do corrective action
before further flight using a method approved in accordance with the
procedures specified in paragraph (h) of this AD.
(ii) Before further flight after accomplishing any corrective
action required by paragraph (g)(5)(i) or (ii) of this AD, repeat
the actions specified in paragraphs (g)(1) through (5) of this AD
until successful completion of the test (i.e., no leaks are found
and 354 fluid ounces (10.5 liters) of water or more is measured in
the container).
Note 1 to paragraph (g): Additional guidance for performing the
leak (functional) test can be found in Boeing Model 787 Aircraft
Maintenance Manual (AMM), 54-65-01, Strut Spar--Upper--Functional
Test.
(h) 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 (i)(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.
(i) Related Information
(1) For more information about this AD, contact Tak Kobayashi,
Aerospace Engineer, Propulsion Section, FAA, Seattle ACO Branch,
2200 South 216th St., Des Moines, WA 98198; phone and fax: 206-231-
3553; 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. For information on the availability of this
material at the FAA, call 206-231-3195.
Issued in Des Moines, Washington, on October 24, 2019.
Dionne Palermo,
Acting Director, System Oversight Division, Aircraft Certification
Service.
[FR Doc. 2019-23788 Filed 10-31-19; 8:45 am]
BILLING CODE 4910-13-P
