Airworthiness Directives; The Boeing Company Airplanes, 17480-17483 [2020-06459]
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Federal Register / Vol. 85, No. 61 / Monday, March 30, 2020 / Rules and Regulations
(i) Other FAA AD Provisions
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):
■
2020–04–17 Airbus SAS: Amendment 39–
19854; Docket No. FAA–2019–0865; Product
Identifier 2019–NM–158–AD.
(a) Effective Date
This AD is effective May 4, 2020.
(b) Affected ADs
None.
(c) Applicability
This AD applies to all Airbus SAS Model
A350–941 and –1041 airplanes, certificated
in any category.
(d) Subject
Air Transport Association (ATA) of
America Code 52, Doors.
(e) Reason
This AD was prompted by reports of
passenger door girt bar fitting assembly safety
hooks being stuck in the upward position.
The FAA is issuing this AD to address this
condition, which could lead to girt bar
disengagement from the girt bar fitting
assembly and consequent failure of the
passenger door slide deployment during an
emergency, possibly preventing safe
evacuation of the airplane.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
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(g) Requirements
Except as specified in paragraph (h) of this
AD: Comply with all required actions and
compliance times specified in, and in
accordance with, European Union Aviation
Safety Agency (EASA) AD 2019–0207, dated
August 22, 2019 (‘‘EASA AD 2019–0207’’).
(h) Exceptions to EASA AD 2019–0207
(1) Where EASA AD 2019–0207 refers to its
effective date, this AD requires using the
effective date of this AD.
(2) The ‘‘Remarks’’ section of EASA AD
2019–0207 does not apply to this AD.
(3) Paragraph (4) of EASA AD 2019–0207
specifies to report inspection results to
Airbus within a certain compliance time. For
this AD, report inspection results at the
applicable time specified in paragraph
(h)(3)(i) or (ii) of this AD.
(i) If the inspection was done on or after
the effective date of this AD: Submit the
report within 90 days after the conclusion of
the maintenance visit or check where the
inspection was completed.
(ii) If the inspection was done before the
effective date of this AD: Submit the report
within 90 days after the effective date of this
AD.
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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 (j) of this AD. Information may be
emailed to: 9-ANM-116-AMOC-REQUESTS@
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
2019–0207 that contains RC procedures and
tests: Except as required by paragraph (i)(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.
(4) Paperwork Reduction Act Burden
Statement: A federal agency may not conduct
or sponsor, and a person is not required to
respond to, nor shall a person be subject to
a penalty for failure to comply with a
collection of information subject to the
requirements of the Paperwork Reduction
Act unless that collection of information
displays a current valid OMB Control
Number. The OMB Control Number for this
information collection is 2120–0056. Public
reporting for this collection of information is
estimated to be approximately 1 hour per
response, including the time for reviewing
instructions, completing and reviewing the
collection of information. All responses to
this collection of information are mandatory
as required by this AD. Send comments
regarding this burden estimate or any other
aspect of this collection of information,
including suggestions for reducing this
burden to: Information Collection Clearance
Officer, Federal Aviation Administration,
10101 Hillwood Parkway, Fort Worth, TX
76177–1524.
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(j) Related Information
For more information about this AD,
contact Kathleen Arrigotti, Aerospace
Engineer, International Section, Transport
Standards Branch, FAA, 2200 South 216th
St., Des Moines, WA 98198; telephone and
fax 206–231–3218; email kathleen.arrigotti@
faa.gov.
(k) Material Incorporated by Reference
(1) The Director of the Federal Register
approved the incorporation by reference
(IBR) of the service information listed in this
paragraph under 5 U.S.C. 552(a) and 1 CFR
part 51.
(2) You must use this service information
as applicable to do the actions required by
this AD, unless this AD specifies otherwise.
(i) European Union Aviation Safety Agency
(EASA) AD 2019–0207, dated August 22,
2019.
(ii) [Reserved]
(3) For information about EASA AD 2019–
0207, 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.
(4) 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–2019–0865.
(5) You may view this material that is
incorporated by reference at the National
Archives and Records Administration
(NARA). For information on the availability
of this material at NARA, email fedreg.legal@
nara.gov, or go to: https://www.archives.gov/
federal-register/cfr/ibr-locations.html.
Issued on February 25, 2020.
Gaetano A. Sciortino,
Deputy Director for Strategic Initiatives,
Compliance & Airworthiness Division,
Aircraft Certification Service.
[FR Doc. 2020–06480 Filed 3–27–20; 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; Amendment
39–19876; AD 2020–05–26]
RIN 2120–AA64
Airworthiness Directives; The Boeing
Company Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
The FAA is adopting a new
airworthiness directive (AD) for certain
SUMMARY:
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Federal Register / Vol. 85, No. 61 / Monday, March 30, 2020 / Rules and Regulations
The Boeing Company Model 787–8
airplanes. This AD was prompted by a
report of failure of a wing strut leak test
due to a missing bolt on the firewall.
This AD requires 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 issuing
this AD to address the unsafe condition
on these products.
DATES: This AD is effective May 4, 2020.
ADDRESSES: For service information
identified in this final rule, 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.
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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 final rule,
the regulatory evaluation, any
comments received, and other
information. The address for Docket
Operations is U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue SE,
Washington, DC 20590.
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:
Discussion
The FAA issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 by adding an AD that would
apply to certain The Boeing Company
Model 787–8 airplanes. The NPRM
published in the Federal Register on
November 1, 2019 (84 FR 58636). The
NPRM was prompted by a report of
failure of a wing strut leak test due to
a missing bolt on the firewall. The
NPRM proposed to 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 issuing this AD to address
a hole in the firewall, which could
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allow flammable fluid to leak from the
strut compartment to the engine
compartment when the drainage
provision is overwhelmed. Flammable
fluid leakage into the engine
compartment could result in an
uncontrollable engine fire and
consequent structural failure of the
wing.
Comments
The FAA gave the public the
opportunity to participate in developing
this final rule. The following presents
the comments received on the NPRM
and the FAA’s response to each
comment.
Support for the NPRM
Two commenters, Patrick Imperatrice
and Seth Stewart, indicated support for
the NPRM.
Request To Change the Unsafe
Condition
Boeing asked that the current
language for the unsafe condition
specified in the proposed AD, which
states, in part, ‘‘. . . which could allow
flammable fluid leakage in the strut
area. This leakage could overwhelm the
drainage provision, enter the engine
compartment . . .’’ be changed to ‘‘. . .
which could allow flammable fluid to
leak from the strut compartment to the
engine core compartment . . . .’’
Boeing stated that the hole in the
firewall due to a missing bolt does not
affect the drain provision from the strut
system tubing shroud. Boeing added
that a missing bolt does create an
unintended drain path from the strut
flammable fluid compartment to the
engine core compartment fire zone.
The FAA agrees with the commenter’s
request for the reason provided. The
FAA has revised the Discussion section
and paragraph (e) of this AD to include
the suggested language.
Request To Clarify Certain Language
Boeing asked that the language
specified in paragraph (g)(2) of the
proposed AD, be changed from ‘‘strut
upper spar (strut areas . . .)’’ to
‘‘systems tubing shroud (area . . .).’’
Boeing stated that the water must be
applied in the systems tubing shroud,
not to the strut upper spar. Boeing
added that the strut upper spar between
the forward and mid-vapor barriers is a
dry bay, but the systems tubing shroud
is a flammable leakage zone.
The FAA agrees with the commenter’s
request to clarify the language to be
consistent with Boeing’s terminology.
This procedure is also provided in the
Boeing 787 Aircraft Maintenance
Manual (AMM), specified as additional
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17481
guidance in this AD. The FAA has
revised paragraph (g)(2) of this AD as
suggested by the commenter.
Request To Remove Leak Test
Requirement
Boeing asked that the FAA remove the
leak test required by paragraph (g) of the
proposed AD and either require or
include an option for a visual inspection
for proper installation of the bolt on the
firewall, as specified in planned Boeing
Service Bulletin 787–54A0021–I001.
Boeing stated that paragraph (e) of the
proposed AD specified that the unsafe
condition was caused by a missing bolt
that plugs a penetration on the strut
firewall. Boeing added that a visual
inspection done using the planned
Boeing service information will verify
the proper installation of the bolt, and
ensure firewall integrity, in addition to
less maintenance time than a leak test,
resulting in lower costs for the airlines.
Boeing also stated that the service
bulletin is scheduled for release in June
2020, and will include instructions to
inspect for a missing bolt, as well as
corrective action to correctly install a
missing bolt and perform a leak test to
ensure proper drainage.
The FAA acknowledges the
commenter’s request, but does not agree
to revise this AD. The leak test required
by this AD provides a practical means
to address the unsafe condition, and this
method is adequate since the service
information is not yet approved or
available. The FAA may not require any
document that does not yet exist in an
AD. In general terms, the FAA is
required by Office of the Federal
Register (OFR) regulations for approval
of materials incorporated by reference,
as specified in 1 CFR 51.1(f), to either
publish the service document contents
as part of the actual AD language; or
submit the service document to the OFR
for approval as referenced material, in
which case the FAA may only refer to
such material in the text of an AD. Since
no service information for the visual
inspection has been provided to the
FAA, the agency is unable to evaluate or
approve an inspection method. The
FAA finds that delaying this action is
inappropriate in light of the identified
unsafe condition. If service information
for this inspection becomes available
later, it may be submitted to the FAA for
approval of an alternative method of
compliance under the provisions of
paragraph (h) of this AD. The FAA has
not changed this AD in this regard.
Request To Clarify a Procedure
Boeing asked that the FAA add the
language ‘‘remove the tubing shroud
cover’’ to the end of paragraph (g)(1) of
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Federal Register / Vol. 85, No. 61 / Monday, March 30, 2020 / Rules and Regulations
the proposed AD to clarify the
procedure. Boeing stated that if the
tubing shroud cover is not removed,
water cannot be poured into the systems
tubing and side shroud areas.
The FAA partially agrees with the
commenter’s request. The FAA
determined that only the steps
necessary for properly accomplishing
the leak test—not the general steps
necessary to prepare for the test—are
included in the AD requirements. For
additional guidance, Note 1 to
paragraph (g) of this AD provides
information related to the procedures in
the applicable section of the Boeing 787
AMM. That section includes all relevant
general steps for accomplishing the
required leak test. Therefore, the FAA
has not changed this AD in this regard.
Request for Correction of a Paragraph
Identifier
Boeing stated that there are two
paragraph identifiers that are identical.
Boeing noted that paragraph identifier
(g)(5)(ii) of the proposed AD is repeated,
and the second paragraph identifier
should be (g)(5)(iii).
The FAA agrees with the commenter
and has corrected the paragraph
identifier accordingly.
Conclusion
The FAA reviewed the relevant data,
considered the comments received, and
determined that air safety and the
public interest require adopting this
final rule with the changes described
previously and minor editorial changes.
The FAA has determined that these
minor changes:
• Are consistent with the intent that
was proposed in the NPRM for
addressing the unsafe condition; and
• Do not add any additional burden
upon the public than was already
proposed in the NPRM.
The FAA also determined that these
changes will not increase the economic
burden on any operator or increase the
scope of this final rule.
Costs of Compliance
The FAA estimates that this AD
affects 2 airplanes of U.S. registry. The
agency estimates the following costs to
comply with this 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 required 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
Parts cost
1 work-hour × $85 per hour = $85 .................................................................
Minimal ...................................................................
Authority for This Rulemaking
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Cost per
product
Labor cost
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
This AD will not have federalism
implications under Executive Order
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13132. This AD will 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 that this AD:
(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.
$85
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):
■
2020–05–26 The Boeing Company:
Amendment 39–19876; Docket No.
FAA–2019–0719; Product Identifier
2019–NM–137–AD.
(a) Effective Date
This AD is effective May 4, 2020.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
(b) Affected ADs
Adoption of the Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as
follows:
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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None.
(c) Applicability
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Federal Register / Vol. 85, No. 61 / Monday, March 30, 2020 / Rules and Regulations
(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
to leak from the strut compartment to the
engine compartment when the drainage
provision is overwhelmed. Flammable fluid
leakage into the engine compartment could
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.
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(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 systems tubing shroud (area 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.
(iii) 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)
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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 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: 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 that is not incorporated by reference,
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.
(j) Material Incorporated by Reference
None.
Issued on March 10, 2020.
Lance T. Gant,
Director, Compliance & Airworthiness
Division, Aircraft Certification Service.
[FR Doc. 2020–06459 Filed 3–27–20; 8:45 am]
BILLING CODE 4910–13–P
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17483
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2019–0438; Product
Identifier 2019–NM–033–AD; Amendment
39–19875; AD 2020–05–25]
RIN 2120–AA64
Airworthiness Directives; The Boeing
Company Airplanes
Federal Aviation
Administration (FAA), DOT.
AGENCY:
ACTION:
Final rule.
The FAA is adopting a new
airworthiness directive (AD) for all The
Boeing Company Model 757–200,
–200PF, –200CB, and –300 series
airplanes. This AD was prompted by a
report that during a maintenance check
an operator discovered cracking of the
aft cargo compartment frames in the
station 1460 frame web and inner chord
between certain stringers. This AD
requires an inspection of the fuselage
frames for any existing repair, repetitive
surface high frequency eddy current
(HFEC) inspections of the fuselage
frames with a cargo liner support
channel for any cracking, and applicable
on-condition actions. The FAA is
issuing this AD to address the unsafe
condition on these products.
SUMMARY:
DATES:
This AD is effective May 4, 2020.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in this AD
as of May 4, 2020.
For service information
identified in this final rule, 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.
It is also available on the internet at
https://www.regulations.gov by
searching for and locating Docket No.
FAA–2019–0438.
ADDRESSES:
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]]>Agencies
[Federal Register Volume 85, Number 61 (Monday, March 30, 2020)]
[Rules and Regulations]
[Pages 17480-17483]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2020-06459]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2019-0719; Product Identifier 2019-NM-137-AD; Amendment
39-19876; AD 2020-05-26]
RIN 2120-AA64
Airworthiness Directives; The Boeing Company Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule.
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SUMMARY: The FAA is adopting a new airworthiness directive (AD) for
certain
[[Page 17481]]
The Boeing Company Model 787-8 airplanes. This AD was prompted by a
report of failure of a wing strut leak test due to a missing bolt on
the firewall. This AD requires 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 issuing this AD to address the unsafe condition
on these products.
DATES: This AD is effective May 4, 2020.
ADDRESSES: For service information identified in this final rule,
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 final rule, the regulatory evaluation, any comments received, and
other information. The address for Docket Operations is U.S. Department
of Transportation, Docket Operations, M-30, West Building Ground Floor,
Room W12-140, 1200 New Jersey Avenue SE, Washington, DC 20590.
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:
Discussion
The FAA issued a notice of proposed rulemaking (NPRM) to amend 14
CFR part 39 by adding an AD that would apply to certain The Boeing
Company Model 787-8 airplanes. The NPRM published in the Federal
Register on November 1, 2019 (84 FR 58636). The NPRM was prompted by a
report of failure of a wing strut leak test due to a missing bolt on
the firewall. The NPRM proposed to 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 issuing this AD to address a hole in the firewall, which
could allow flammable fluid to leak from the strut compartment to the
engine compartment when the drainage provision is overwhelmed.
Flammable fluid leakage into the engine compartment could result in an
uncontrollable engine fire and consequent structural failure of the
wing.
Comments
The FAA gave the public the opportunity to participate in
developing this final rule. The following presents the comments
received on the NPRM and the FAA's response to each comment.
Support for the NPRM
Two commenters, Patrick Imperatrice and Seth Stewart, indicated
support for the NPRM.
Request To Change the Unsafe Condition
Boeing asked that the current language for the unsafe condition
specified in the proposed AD, which states, in part, ``. . . which
could allow flammable fluid leakage in the strut area. This leakage
could overwhelm the drainage provision, enter the engine compartment .
. .'' be changed to ``. . . which could allow flammable fluid to leak
from the strut compartment to the engine core compartment . . . .''
Boeing stated that the hole in the firewall due to a missing bolt does
not affect the drain provision from the strut system tubing shroud.
Boeing added that a missing bolt does create an unintended drain path
from the strut flammable fluid compartment to the engine core
compartment fire zone.
The FAA agrees with the commenter's request for the reason
provided. The FAA has revised the Discussion section and paragraph (e)
of this AD to include the suggested language.
Request To Clarify Certain Language
Boeing asked that the language specified in paragraph (g)(2) of the
proposed AD, be changed from ``strut upper spar (strut areas . . .)''
to ``systems tubing shroud (area . . .).'' Boeing stated that the water
must be applied in the systems tubing shroud, not to the strut upper
spar. Boeing added that the strut upper spar between the forward and
mid-vapor barriers is a dry bay, but the systems tubing shroud is a
flammable leakage zone.
The FAA agrees with the commenter's request to clarify the language
to be consistent with Boeing's terminology. This procedure is also
provided in the Boeing 787 Aircraft Maintenance Manual (AMM), specified
as additional guidance in this AD. The FAA has revised paragraph (g)(2)
of this AD as suggested by the commenter.
Request To Remove Leak Test Requirement
Boeing asked that the FAA remove the leak test required by
paragraph (g) of the proposed AD and either require or include an
option for a visual inspection for proper installation of the bolt on
the firewall, as specified in planned Boeing Service Bulletin 787-
54A0021-I001. Boeing stated that paragraph (e) of the proposed AD
specified that the unsafe condition was caused by a missing bolt that
plugs a penetration on the strut firewall. Boeing added that a visual
inspection done using the planned Boeing service information will
verify the proper installation of the bolt, and ensure firewall
integrity, in addition to less maintenance time than a leak test,
resulting in lower costs for the airlines. Boeing also stated that the
service bulletin is scheduled for release in June 2020, and will
include instructions to inspect for a missing bolt, as well as
corrective action to correctly install a missing bolt and perform a
leak test to ensure proper drainage.
The FAA acknowledges the commenter's request, but does not agree to
revise this AD. The leak test required by this AD provides a practical
means to address the unsafe condition, and this method is adequate
since the service information is not yet approved or available. The FAA
may not require any document that does not yet exist in an AD. In
general terms, the FAA is required by Office of the Federal Register
(OFR) regulations for approval of materials incorporated by reference,
as specified in 1 CFR 51.1(f), to either publish the service document
contents as part of the actual AD language; or submit the service
document to the OFR for approval as referenced material, in which case
the FAA may only refer to such material in the text of an AD. Since no
service information for the visual inspection has been provided to the
FAA, the agency is unable to evaluate or approve an inspection method.
The FAA finds that delaying this action is inappropriate in light of
the identified unsafe condition. If service information for this
inspection becomes available later, it may be submitted to the FAA for
approval of an alternative method of compliance under the provisions of
paragraph (h) of this AD. The FAA has not changed this AD in this
regard.
Request To Clarify a Procedure
Boeing asked that the FAA add the language ``remove the tubing
shroud cover'' to the end of paragraph (g)(1) of
[[Page 17482]]
the proposed AD to clarify the procedure. Boeing stated that if the
tubing shroud cover is not removed, water cannot be poured into the
systems tubing and side shroud areas.
The FAA partially agrees with the commenter's request. The FAA
determined that only the steps necessary for properly accomplishing the
leak test--not the general steps necessary to prepare for the test--are
included in the AD requirements. For additional guidance, Note 1 to
paragraph (g) of this AD provides information related to the procedures
in the applicable section of the Boeing 787 AMM. That section includes
all relevant general steps for accomplishing the required leak test.
Therefore, the FAA has not changed this AD in this regard.
Request for Correction of a Paragraph Identifier
Boeing stated that there are two paragraph identifiers that are
identical. Boeing noted that paragraph identifier (g)(5)(ii) of the
proposed AD is repeated, and the second paragraph identifier should be
(g)(5)(iii).
The FAA agrees with the commenter and has corrected the paragraph
identifier accordingly.
Conclusion
The FAA reviewed the relevant data, considered the comments
received, and determined that air safety and the public interest
require adopting this final rule with the changes described previously
and minor editorial changes. The FAA has determined that these minor
changes:
Are consistent with the intent that was proposed in the
NPRM for addressing the unsafe condition; and
Do not add any additional burden upon the public than was
already proposed in the NPRM.
The FAA also determined that these changes will not increase the
economic burden on any operator or increase the scope of this final
rule.
Costs of Compliance
The FAA estimates that this AD affects 2 airplanes of U.S.
registry. The agency estimates the following costs to comply with this
AD:
Estimated Costs for Required Actions
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Cost per Cost on U.S.
Labor cost Parts cost product operators
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3 work-hours x $85 per hour = $255........................... $0 $255 $510
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The FAA estimates the following costs to do any necessary on-
condition action that would be required based on the results of any
required 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
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Cost per
Labor cost Parts cost product
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1 work-hour x $85 per hour = $85.. Minimal............. $85
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Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, section 106, describes the
authority of the FAA Administrator. Subtitle VII: Aviation Programs,
describes in more detail the scope of the Agency's authority.
The FAA is issuing this rulemaking under the authority described in
Subtitle VII, Part A, Subpart III, Section 44701: ``General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.
Regulatory Findings
This AD will not have federalism implications under Executive Order
13132. This AD will 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 that this AD:
(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.
Adoption of the Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA amends 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]
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2. The FAA amends Sec. 39.13 by adding the following new airworthiness
directive (AD):
2020-05-26 The Boeing Company: Amendment 39-19876; Docket No. FAA-
2019-0719; Product Identifier 2019-NM-137-AD.
(a) Effective Date
This AD is effective May 4, 2020.
(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 17483]]
(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 to leak from the strut compartment to the engine compartment
when the drainage provision is overwhelmed. Flammable fluid leakage
into the engine compartment could 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 systems tubing shroud (area 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.
(iii) 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 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 that is not
incorporated by reference, 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.
(j) Material Incorporated by Reference
None.
Issued on March 10, 2020.
Lance T. Gant,
Director, Compliance & Airworthiness Division, Aircraft Certification
Service.
[FR Doc. 2020-06459 Filed 3-27-20; 8:45 am]
BILLING CODE 4910-13-P
