Airworthiness Directives; the Boeing Company Airplanes, 68384-68388 [2014-27069]
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Federal Register / Vol. 79, No. 221 / Monday, November 17, 2014 / Proposed Rules
(g) Repetitive Inspections for Crack
Indications at Stringers S–4R and S–4L,
Body Station (BS) 360 to BS 908
At the applicable time specified in Table
1 of paragraph 1.E., ‘‘Compliance,’’ of Boeing
Alert Service Bulletin 737–53A1319,
Revision 2, dated April 4, 2014: Do an
external eddy current inspection, or internal
eddy current and detailed inspections, for
crack indications at stringers S–4R and S–4L,
from body station (BS) 360 to BS 908, except
as provided by paragraph (h) of this AD, in
accordance with Part 1 of the
Accomplishment Instructions of Boeing Alert
Service Bulletin 737–53A1319, Revision 2,
dated April 4, 2014. Repeat the inspection(s)
thereafter at the applicable intervals specified
in Table 1 or Table 2, as applicable, of
paragraph 1.E., ‘‘Compliance,’’ of Boeing
Alert Service Bulletin 737–53A1319,
Revision 2, dated April 4, 2014. Either
inspection option may be used at any
repetitive inspection cycle.
(h) One-Time Inspections for Cracks at
Stringers S–4L and S–4R, BS 360 to BS 908
At the applicable time specified in Table
3 of paragraph 1.E., ‘‘Compliance,’’ of Boeing
Alert Service Bulletin 737–53A1319,
Revision 2, dated April 4, 2014, except as
required by paragraph (m) of this AD: Do
one-time internal detailed and eddy current
inspections for cracks at stringers S–4R and
S–4L, from BS 360 to BS 908, in accordance
with Part 2 of the Accomplishment
Instructions of Boeing Alert Service Bulletin
737–53A1319, Revision 2, dated April 4,
2014. Accomplishment of the inspections
required by this paragraph does not terminate
the repetitive inspections required by
paragraph (g) of this AD.
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(i) One-Time Inspections for Cracks at
Stringer S–4R, BS 908 to BS 1016
For airplanes identified as Group 2, 3, 5,
and 7 in Boeing Alert Service Bulletin 737–
53A1319, Revision 2, dated April 4, 2014: At
the applicable time specified in Table 4 of
paragraph 1.E., ‘‘Compliance,’’ of Boeing
Alert Service Bulletin 737–53A1319,
Revision 2, dated April 4, 2014, except as
required by paragraph (m) of this AD, do onetime internal detailed and eddy current
inspections for cracks at stringer S–4R, from
BS 908 to BS 1016, in accordance with Part
3 of the Accomplishment Instructions of
Boeing Alert Service Bulletin 737–53A1319,
Revision 2, dated April 4, 2014.
(j) Repetitive Inspections for Cracks at
Stringer S–4R, BS 908 to BS 1016
For airplanes identified as Group 2, 3, 5,
and 7 in Boeing Alert Service Bulletin 737–
53A1319, Revision 2, dated April 4, 2014: At
the applicable time specified in Table 5 of
paragraph 1.E., ‘‘Compliance,’’ of Boeing
Alert Service Bulletin 737–53A1319,
Revision 2, dated April 4, 2014, except as
required by paragraph (m) of this AD, do
external eddy current inspections, or internal
eddy current and detailed inspections, for
cracks at stringer S–4R, from BS 908 to BS
1016, in accordance with Part 4 of the
Accomplishment Instructions of Boeing Alert
Service Bulletin 737–53A1319, Revision 2,
dated April 4, 2014. Repeat the inspection(s)
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thereafter at the applicable intervals specified
in Table 5 of paragraph 1.E., ‘‘Compliance,’’
of Boeing Alert Service Bulletin 737–
53A1319, Revision 2, dated April 4, 2014.
Either inspection option may be used at any
repetitive inspection cycle.
(k) General Visual Inspection for Open
Pockets at Stringer S–4R, BS 908 to BS 1016
For airplanes identified as Group 1, 4, and
6 in Boeing Alert Service Bulletin 737–
53A1319, Revision 2, dated April 4, 2014: At
the applicable time specified in Table 6 of
paragraph 1.E., ‘‘Compliance,’’ of Boeing
Alert Service Bulletin 737–53A1319,
Revision 2, dated April 4, 2014, except as
required by paragraph (m) of this AD, do a
general visual inspection for open pockets of
the lower skin panel at stringer S–4R, from
BS 908 to BS 1016, in accordance with Part
5 of the Accomplishment Instructions of
Boeing Alert Service Bulletin 737–53A1319,
Revision 2, dated April 4, 2014. If any open
pocket is found, before further flight, inspect
and repair using a method approved in
accordance with the procedures specified in
paragraph (o) of this AD.
(l) Corrective Action
If any crack is found during any inspection
required by this AD: Before further flight,
repair using a method approved in
accordance with the procedures specified in
paragraph (o) of this AD. Accomplishment of
repairs approved in accordance with the
procedures specified in paragraph (o) of this
AD terminates the repetitive inspections
specified in paragraphs (g) and (j) of this AD
in the repaired areas only.
(m) Service Information Exception
Where Boeing Alert Service Bulletin 737–
53A1319, Revision 2, dated April 4, 2014,
specifies a compliance time ‘‘after the
Revision 2 date of this service bulletin,’’ this
AD requires compliance within the specified
compliance time after the effective date of
this AD.
(n) Credit for Previous Actions
This paragraph provides credit for actions
required by paragraph (g) of this AD, if those
actions were performed before the effective
date of this AD using Boeing Alert Service
Bulletin 737–53A1319, dated April 4, 2011;
or Boeing Alert Service Bulletin 737–
53A1319, Revision 1, dated April 8, 2011.
Boeing Alert Service Bulletin 737–53A1319,
dated April 4, 2011, is incorporated by
reference in AD 2011–08–51, Amendment
39–16701 (76 FR 28632, May 18, 2011).
Boeing Alert Service Bulletin 737–53A1319,
Revision 1, dated April 8, is not incorporated
by reference in this AD.
(o) Alternative Methods of Compliance
(AMOCs)
(1) The Manager, Seattle Aircraft
Certification Office (ACO), 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 ACO, send it to the
attention of the person identified in
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paragraph (p)(1) of this AD. Information may
be emailed to: 9-ANM-Seattle-ACO-AMOCRequests@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
required by this AD if it is approved by the
Boeing Commercial Airplanes Organization
Designation Authorization (ODA) that has
been authorized by the Manager, Seattle
ACO, to make those findings. For a repair
method to be approved, the repair must meet
the certification basis of the airplane, and the
approval must specifically refer to this AD.
(4) AMOCs approved for AD 2011–08–51,
Amendment 39–16701 (76 FR 28632, May 18,
2011), are approved as AMOCs for the
corresponding provisions of paragraphs (g)
and (l) of this AD.
(p) Related Information
(1) For more information about this AD,
contact Wayne Lockett, Aerospace Engineer,
Airframe Branch, ANM–120S, FAA, Seattle
Aircraft Certification Office (ACO), 1601 Lind
Avenue SW., Renton, WA 98057–3356;
phone: 425–917–6447; fax: 425–917–6590;
email: wayne.lockett@faa.gov.
(2) For service information identified in
this AD, contact Boeing Commercial
Airplanes, Attention: Data & Services
Management, P. O. Box 3707, MC 2H–65,
Seattle, WA 98124–2207; telephone 206–
544–5000, extension 1; fax 206–766–5680;
Internet https://www.myboeingfleet.com. You
may view this referenced service information
at the FAA, Transport Airplane Directorate,
1601 Lind Avenue SW., Renton, WA. For
information on the availability of this
material at the FAA, call 425–227–1221.
Issued in Renton, Washington, on
November 5, 2014.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 2014–27070 Filed 11–14–14; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2014–0773; Directorate
Identifier 2014–NM–068–AD]
RIN 2120–AA64
Airworthiness Directives; the Boeing
Company Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
We propose to adopt a new
airworthiness directive (AD) for all The
Boeing Company Model 787–8
SUMMARY:
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Federal Register / Vol. 79, No. 221 / Monday, November 17, 2014 / Proposed Rules
airplanes. This proposed AD was
prompted by reports of a potential latent
failure of the valve actuator circuitry,
which was not identified during
actuator development. This proposed
AD would require replacing certain
engine and auxiliary power unit (APU)
fuel shutoff valve actuators with new
actuators, and would also require
revising the maintenance or inspection
program to include a new airworthiness
limitation into the Airworthiness
Limitations Section (ALS) of the
Instructions for Continued
Airworthiness (ICA). We are proposing
this AD to prevent latent failures of the
fuel shutoff valve actuators, which
could result in the inability to shut off
fuel to the engine or APU in the case of
an engine or APU fire. If the fuel cannot
be shut off to a fire, the engine or APU
fire could be uncontrollable, which
could lead to structural failure.
DATES: We must receive comments on
this proposed AD by January 2, 2015.
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 proposed AD, contact Boeing
Commercial Airplanes, Attention: Data
& Services Management, P.O. Box 3707,
MC 2H–65, Seattle, WA 98124–2207;
telephone 206–544–5000, extension 1;
fax 206–766–5680; Internet https://
www.myboeingfleet.com. You may view
this referenced service information at
the FAA, Transport Airplane
Directorate, 1601 Lind Avenue SW.,
Renton, WA. For information on the
availability of this material at the FAA,
call 425–227–1221.
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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–2014–
0773; or in person at the Docket
Management Facility between 9 a.m.
and 5 p.m., Monday through Friday,
except Federal holidays. The AD docket
contains this proposed AD, the
regulatory evaluation, any comments
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16:18 Nov 14, 2014
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received, and other information. The
street address for the Docket Office
(phone: 800–647–5527) is in the
ADDRESSES section. Comments will be
available in the AD docket shortly after
receipt.
FOR FURTHER INFORMATION CONTACT:
Rebel Nichols, Aerospace Engineer,
Propulsion Branch, ANM–140S, FAA,
Seattle Aircraft Certification Office,
1601 Lind Avenue SW., Renton, WA
98057–3356; phone: 425–917–6509; fax:
425–917–6590; email: Rebel.Nichols@
faa.gov.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite 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–
2014–0773; Directorate Identifier 2014–
NM–068–AD’’ at the beginning of your
comments. We specifically invite
comments on the overall regulatory,
economic, environmental, and energy
aspects of this proposed AD. We will
consider all comments received by the
closing date and may amend this
proposed AD because of those
comments.
We will post all comments we
receive, without change, to https://
www.regulations.gov, including any
personal information you provide. We
will also post a report summarizing each
substantive verbal contact we receive
about this proposed AD.
Discussion
We received reports on Model 787
airplanes of a potential latent failure of
the valve actuator circuitry, which was
not identified during actuator
development. The fuel shutoff valve
actuator circuit design provides
common input power through microswitches to both the motor and position
indications. The latent failure condition
has the potential for a stuck microswitch, which could lead to a
disagreement between the valve
command and position indication. If a
command is sent to change the valve
position and one of the internal microswitches is stuck in the depressed state,
power would immediately provide
indication that the valve transitioned to
its commanded state, when the motor
actually never received power to rotate.
This condition, if not corrected, could
result in the inability to shut off fuel to
the engine or APU in the case of an
engine or APU fire. If the fuel cannot be
shut off to a fire, the engine or APU fire
could be uncontrollable, which could
lead to structural failure.
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68385
Relevant Service Information
We reviewed Boeing Service Bulletin
B787–81205–SB280015–00, Issue 002,
dated June 19, 2014. For information on
the procedures and compliance times,
see this service information at https://
www.regulations.gov by searching for
Docket No. FAA–2014–0773.
FAA’s Determination
We are proposing this AD because we
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
airplanes with certain part number
shutoff valves to revise the maintenance
or inspection program to add
airworthiness limitation number 28–
AWL–ACT, ‘‘Engine and APU Shut-Off
Valve Actuator Test.’’ This proposed AD
would also require accomplishing the
actions specified in the service
information described previously,
except as discussed under ‘‘Difference
Between this Proposed AD and the
Service Information.’’
This proposed AD would require
revisions to certain operator
maintenance documents to include new
inspections. Compliance with these
inspections is required by section
91.403(c) of the Federal Aviation
Regulations (14 CFR 91.403(c)). For
airplanes that have been previously
modified, altered, or repaired in the
areas addressed by these inspections, an
operator might not be able to
accomplish the inspections described in
the revisions. In this situation, to
comply with 14 CFR 91.403(c), the
operator must request approval of an
alternative method of compliance
(AMOC) in accordance with the
provisions of paragraph (k) of this
proposed AD. The request should
include a description of changes to the
required inspections that will ensure the
continued operational safety of the
airplane.
Explanation of ‘‘RC’’ Steps in Service
Information
The FAA worked in conjunction with
industry, under the Airworthiness
Directives Implementation Aviation
Rulemaking Committee, to enhance the
AD system. One enhancement was a
new process for annotating which steps
in the service information are required
for compliance with an AD.
Differentiating these steps from other
tasks in the service information is
expected to improve an owner’s/
operator’s understanding of crucial AD
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Federal Register / Vol. 79, No. 221 / Monday, November 17, 2014 / Proposed Rules
requirements and help provide
consistent judgment in AD compliance.
The actions specified in the service
information described previously
include steps that are labeled as RC
(required for compliance) because these
steps have a direct effect on detecting,
preventing, resolving, or eliminating an
identified unsafe condition.
As noted in the specified service
information, steps labeled as RC and all
subordinate steps must be done to
comply with the proposed AD.
However, steps that are not labeled as
RC are recommended. Those steps that
are not labeled as RC may be deviated
from, done as part of other actions, or
done using accepted methods different
from those identified in the service
information without obtaining approval
of an AMOC, provided the steps labeled
as RC can be done and the airplane can
be put back in a serviceable condition.
Any substitutions or changes to steps
labeled as RC will require approval of
an alternative method of compliance.
Differences Between This Proposed AD
and the Service Information
Although Boeing Service Bulletin
B787–81205–SB280015–00, Issue 002,
dated June 19, 2014, describes installing
engine fuel shutoff valve and APU fuel
shutoff valve actuators having part
number (P/N) 53–0037, this proposed
AD would prohibit installing valves
having P/N 53–0037, and require
installing certain other valves. We have
coordinated this difference with Boeing.
The applicability of this proposed AD
includes all Model 787–8 airplanes,
which differs from the effectivity of the
service information referenced
previously. The parts are rotable,
therefore, this proposed AD includes all
Model 787–8 airplanes.
Costs of Compliance
We estimate that this proposed AD
affects 6 airplanes of U.S. registry.
We estimate the following costs to
comply with this proposed AD:
ESTIMATED COSTS
Action
Labor cost
Maintenance program revision .......................
Engine and APU fuel shutoff valve actuator
replacement.
1 work-hour × $85 per hour = $85 .................
10 work-hours × $85 per hour = $850 ...........
According to the manufacturer, some
of the costs of this proposed AD may be
covered under warranty, thereby
reducing the cost impact on affected
individuals. We do not control warranty
coverage for affected individuals. As a
result, we have included all costs in our
cost estimate.
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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.
We are 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
We 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
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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) Is not a ‘‘significant rule’’ under
the DOT Regulatory Policies and
Procedures (44 FR 11034, February 26,
1979),
(3) Will not affect intrastate aviation
in Alaska, and
(4) 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.
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Cost per
product
Parts cost
$0
0
§ 39.13
Cost on U.S.
operators
$85
850
$510
5,100
[Amended]
2. Amend § 39.13 by adding the
following new airworthiness directive
(AD):
■
The Boeing Company: Docket No. FAA–
2014–0773; Directorate Identifier 2014–
NM–068–AD.
(a) Comments Due Date
We must receive comments by January 2,
2015.
(b) Affected ADs
None.
(c) Applicability
This AD applies to all The Boeing
Company Model 787–8 airplanes, certificated
in any category.
(d) Subject
Air Transport Association (ATA) of
America Code 28, Fuel.
(e) Unsafe Condition
This AD was prompted by a report of an
error in the valve actuator design. We are
issuing this AD to prevent latent failures of
the fuel shutoff valve actuators, which could
result in the inability to shut off fuel to the
engine or APU in the case of an engine or
APU fire. If the fuel cannot be shut off to a
fire the engine or APU fire could be
uncontrollable which could lead to structural
failure.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Maintenance or Inspection Program
Revision
Within 30 days after the effective date of
this AD, revise the maintenance or inspection
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Federal Register / Vol. 79, No. 221 / Monday, November 17, 2014 / Proposed Rules
program, as applicable, to add airworthiness
limitation number 28–AWL–ACT, by
incorporating the information specified in
figure 1 to paragraph (g) of this AD into the
Airworthiness Limitations Section of the
Instructions for Continued Airworthiness.
This may be accomplished by inserting a
copy of airworthiness limitation number 28–
AWL–ACT into the maintenance or
inspection program, as applicable. For the
airplanes identified in the applicability note
of airworthiness limitation number 28–AWL–
ACT, the initial compliance time for
accomplishing the actions specified in figure
1 to paragraph (g) of this AD is within 10
days after accomplishment of the
68387
maintenance or inspection program revision
required by this paragraph. When the engine
and APU fuel shutoff valve actuators have
been replaced as required by paragraph (i) of
this AD, the airworthiness limitation number
28–AWL–ACT required by this paragraph
may be removed from the maintenance or
inspection program, as applicable.
FIGURE 1 TO PARAGRAPH (g) OF THIS AD: ENGINE AND APU SHUT-OFF VALVE ACTUATOR TEST
AWL No.
Task
Interval
Applicability
Description
28–AWL–ACT .........
ALI ...........................
10 Days NOTE ........
ALL NOTE ...............
Engine and APU Shut-Off Valve Actuator Test.
Concern: The fuel shutoff valve actuator design can
result in airplanes operating with a failed fuel
shutoff actuator that is not reported. A latently
failed fuel shutoff actuator would prevent fuel
shut off to an engine. In the event of certain engine fires, the potential exists for an engine fire to
be uncontrollable.
Perform the following tests in accordance with Boeing Service Bulletin B787–81205–SB280015–00,
Issue 002, dated June 19, 2014.
1. Do PART 1: ENGINE FUEL SHUTOFF VALVE
ACTUATOR TEST as described in Boeing Service Bulletin B787–81205–SB280015–00, Issue
002, dated June 19, 2014.
a. If the left engine fuel shutoff valve actuator has
Part Number 53–0037, perform the left engine
fuel shutoff valve actuator test.
b. If the right engine fuel shutoff valve actuator
has Part Number 53–0037, perform the right
engine fuel shutoff valve actuator test.
c. If either test fails, repair faults as required
(refer to Boeing Airplane Maintenance Manual
28–22–02).
2. Do PART 2: APU FUEL SHUTOFF VALVE ACTUATOR TEST as described in Boeing Service
Bulletin B787–81205–SB280015–00, Issue 002,
dated June 19, 2014.
a. If the APU fuel shutoff valve actuator has part
number 53–0037, perform the APU fuel shutoff
valve actuator test.
b. If the test fails, before further flight requiring
APU availability, repair If the test fails, before
further flight requiring APU availability, repair
faults as required (refer to Boeing Airplane
Maintenance Manual 28–25–03).
NOTE: Dispatch may be permitted per MMEL 28–
25–03 if APU is not required for flight.
INTERVAL NOTE: Not required on days when the
airplane is not used in revenue service. Must be
done before further flight if it has been 10 or
more calendar days since last inspection
APPLICABILITY NOTE: This AWL applies to airplanes with Eaton Aerospace Ltd fuel shutoff
valve actuators having Part Number 53–0037 installed at the engine or APU spar shutoff location.
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(h) No Alternative Actions and Intervals
Except as specified in paragraph (i) of this
AD: After accomplishment of the
maintenance or inspection program revision
required by paragraph (g) of this AD, no
alternative actions (e.g., inspections) or
intervals may be used unless the actions or
intervals are approved as an alternative
method of compliance (AMOC) in
accordance with the procedures specified in
paragraph (k) of this AD.
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(i) Replacement
Within 36 months after the effective date
of this AD, replace the engine and APU fuel
shutoff valve actuators having part number
(P/N) 53–0037 with P/N 53–0049, in
accordance with Part 5 or Part 6 of the
Accomplishment Instructions of Boeing
Service Bulletin B787–81205–SB280015–00,
Issue 002, dated June 19, 2014, as applicable.
When all the engine and APU fuel shutoff
valve actuators have been replaced as
required by this paragraph, the airworthiness
limitation number 28–AWL–ACT required by
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paragraph (g) of this AD may be removed
from the maintenance or inspection program,
as applicable.
(j) Parts Installation Prohibition
As of the effective date of this AD, no
person may install a motor operated valve
actuator having P/N 53–0037 on any airplane
in the following locations: Engine fuel
shutoff valve, APU fuel shutoff valve,
crossfeed valve, and defuel/isolation valve.
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(k) Alternative Methods of Compliance
(AMOCs)
DEPARTMENT OF TRANSPORTATION
(1) The Manager, Seattle Aircraft
Certification Office (ACO), 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 ACO, send it to the
attention of the person identified in
paragraph (l)(1) of this AD. Information may
be emailed to: 9-ANM-Seattle-ACO-AMOCRequests@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) If the service information contains steps
that are labeled as RC (Required for
Compliance), those steps and all subordinate
steps must be done to comply with this AD;
any steps that are not labeled as RC are
recommended. Those steps that are not
labeled as RC may be deviated from, done as
part of other actions, or done using accepted
methods different from those identified in
the specified service information without
obtaining approval of an AMOC, provided
the steps labeled as RC can be done and the
airplane can be put back in a serviceable
condition. Any substitutions or changes to
steps labeled as RC require approval of an
AMOC.
Federal Aviation Administration
(l) Related Information
mstockstill on DSK4VPTVN1PROD with PROPOSALS
(1) For more information about this AD,
contact Rebel Nichols, Aerospace Engineer,
Propulsion Branch, ANM–140S, FAA, Seattle
Aircraft Certification Office, 1601 Lind
Avenue SW., Renton, WA 98057–3356;
phone: 425–917–6509; fax: 425–917–6590;
email: Rebel.Nichols@faa.gov.
(2) For service information identified in
this AD, contact Boeing Commercial
Airplanes, Attention: Data & Services
Management, P.O. Box 3707, MC 2H–65,
Seattle, WA 98124–2207; telephone 206–
544–5000, extension 1; fax 206–766–5680;
Internet https://www.myboeingfleet.com. You
may view this referenced service information
at the FAA, Transport Airplane Directorate,
1601 Lind Avenue SW., Renton, WA. For
information on the availability of this
material at the FAA, call 425–227–1221.
Issued in Renton, Washington, on
November 5, 2014.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 2014–27069 Filed 11–14–14; 8:45 am]
BILLING CODE 4910–13–P
VerDate Sep<11>2014
16:18 Nov 14, 2014
Jkt 235001
14 CFR Part 39
[Docket No. FAA–2014–0774; Directorate
Identifier 2013–NM–154–AD]
RIN 2120–AA64
Airworthiness Directives; the Boeing
Company Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
We propose to supersede
Airworthiness Directive (AD) 2006–22–
15, which applies to all Boeing Model
747–100, 747–100B, 747–100B SUD,
747–200B, 747–200C, 747–200F, 747–
300, 747–400, 747–400D, 747–400F,
747SR, and 747SP series airplanes. AD
2006–22–15 currently requires
repetitive inspections for cracking of
certain panel webs and stiffeners of the
nose wheel well (NWW), and corrective
actions if necessary. AD 2006–22–15
also requires replacing certain panels
with new panels, which terminates the
repetitive inspections. Since we issued
AD 2006–22–15, we received reports of
fatigue cracking in the panel webs and
stiffeners of the NWW prior to the
inspection threshold of AD 2006–22–15.
This proposed AD would reduce a
compliance time and add certain
inspections and repair if necessary. We
are proposing this AD to prevent fatigue
cracking of the NWW side and top
panels, which could result in a NWW
depressurization event severe enough to
reduce the structural integrity of the
fuselage.
SUMMARY:
We must receive comments on
this proposed AD by January 2, 2015.
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 proposed AD, contact Boeing
Commercial Airplanes, Attention: Data
& Services Management, P.O. Box 3707,
DATES:
PO 00000
Frm 00013
Fmt 4702
Sfmt 4702
MC 2H–65, Seattle, WA 98124–2207;
telephone 206–544–5000, extension 1;
fax 206–766–5680; Internet https://
www.myboeingfleet.com. You may view
this referenced service information at
the FAA, Transport Airplane
Directorate, 1601 Lind Avenue SW.,
Renton, WA. For information on the
availability of this material at the FAA,
call 425–227–1221.
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–2014–
0774; or in person at the Docket
Management Facility between 9 a.m.
and 5 p.m., Monday through Friday,
except Federal holidays. The AD docket
contains this proposed AD, the
regulatory evaluation, any comments
received, and other information. The
street address for the Docket Office
(phone: 800–647–5527) is in the
ADDRESSES section. Comments will be
available in the AD docket shortly after
receipt.
FOR FURTHER INFORMATION CONTACT: Bill
Ashforth, Aerospace Engineer, Airframe
Branch, ANM–120S, FAA, Seattle
Aircraft Certification Office (ACO), 1601
Lind Avenue SW., Renton, WA 98057–
3356; phone: 425–917–6432; fax: 425–
917–6590; email: Bill.Ashforth@faa.gov.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written
relevant data, views, or arguments about
this proposed AD. Send your comments
to an address listed under the
ADDRESSES section. Include ‘‘Docket No.
FAA–2014–0774; Directorate Identifier
2013–NM–154–AD’’ at the beginning of
your comments. We specifically invite
comments on the overall regulatory,
economic, environmental, and energy
aspects of this proposed AD. We will
consider all comments received by the
closing date and may amend this
proposed AD because of those
comments.
We will post all comments we
receive, without change, to https://
www.regulations.gov, including any
personal information you provide. We
will also post a report summarizing each
substantive verbal contact we receive
about this proposed AD.
Discussion
On October 25, 2006, we issued AD
2006–22–15, Amendment 39–14812 (71
FR 64884, November 6, 2006), for all
Boeing Model 747–100, 747–100B, 747–
100B SUD, 747–200B, 747–200C, 747–
200F, 747–300, 747–400, 747–400D,
747–400F, 747SR, and 747SP series
E:\FR\FM\17NOP1.SGM
17NOP1
]]>Agencies
[Federal Register Volume 79, Number 221 (Monday, November 17, 2014)]
[Proposed Rules]
[Pages 68384-68388]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2014-27069]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2014-0773; Directorate Identifier 2014-NM-068-AD]
RIN 2120-AA64
Airworthiness Directives; the Boeing Company Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: We propose to adopt a new airworthiness directive (AD) for all
The Boeing Company Model 787-8
[[Page 68385]]
airplanes. This proposed AD was prompted by reports of a potential
latent failure of the valve actuator circuitry, which was not
identified during actuator development. This proposed AD would require
replacing certain engine and auxiliary power unit (APU) fuel shutoff
valve actuators with new actuators, and would also require revising the
maintenance or inspection program to include a new airworthiness
limitation into the Airworthiness Limitations Section (ALS) of the
Instructions for Continued Airworthiness (ICA). We are proposing this
AD to prevent latent failures of the fuel shutoff valve actuators,
which could result in the inability to shut off fuel to the engine or
APU in the case of an engine or APU fire. If the fuel cannot be shut
off to a fire, the engine or APU fire could be uncontrollable, which
could lead to structural failure.
DATES: We must receive comments on this proposed AD by January 2, 2015.
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 proposed AD, contact
Boeing Commercial Airplanes, Attention: Data & Services Management,
P.O. Box 3707, MC 2H-65, Seattle, WA 98124-2207; telephone 206-544-
5000, extension 1; fax 206-766-5680; Internet https://www.myboeingfleet.com. You may view this referenced service information
at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW.,
Renton, WA. For information on the availability of this material at the
FAA, call 425-227-1221.
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-2014-
0773; or in person at the Docket Management Facility between 9 a.m. and
5 p.m., Monday through Friday, except Federal holidays. The AD docket
contains this proposed AD, the regulatory evaluation, any comments
received, and other information. The street address for the Docket
Office (phone: 800-647-5527) is in the ADDRESSES section. Comments will
be available in the AD docket shortly after receipt.
FOR FURTHER INFORMATION CONTACT: Rebel Nichols, Aerospace Engineer,
Propulsion Branch, ANM-140S, FAA, Seattle Aircraft Certification
Office, 1601 Lind Avenue SW., Renton, WA 98057-3356; phone: 425-917-
6509; fax: 425-917-6590; email: Rebel.Nichols@faa.gov.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite 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-2014-0773;
Directorate Identifier 2014-NM-068-AD'' at the beginning of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of this proposed AD. We
will consider all comments received by the closing date and may amend
this proposed AD because of those comments.
We will post all comments we receive, without change, to https://www.regulations.gov, including any personal information you provide. We
will also post a report summarizing each substantive verbal contact we
receive about this proposed AD.
Discussion
We received reports on Model 787 airplanes of a potential latent
failure of the valve actuator circuitry, which was not identified
during actuator development. The fuel shutoff valve actuator circuit
design provides common input power through micro-switches to both the
motor and position indications. The latent failure condition has the
potential for a stuck micro-switch, which could lead to a disagreement
between the valve command and position indication. If a command is sent
to change the valve position and one of the internal micro-switches is
stuck in the depressed state, power would immediately provide
indication that the valve transitioned to its commanded state, when the
motor actually never received power to rotate. This condition, if not
corrected, could result in the inability to shut off fuel to the engine
or APU in the case of an engine or APU fire. If the fuel cannot be shut
off to a fire, the engine or APU fire could be uncontrollable, which
could lead to structural failure.
Relevant Service Information
We reviewed Boeing Service Bulletin B787-81205-SB280015-00, Issue
002, dated June 19, 2014. For information on the procedures and
compliance times, see this service information at https://www.regulations.gov by searching for Docket No. FAA-2014-0773.
FAA's Determination
We are proposing this AD because we 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 airplanes with certain part number
shutoff valves to revise the maintenance or inspection program to add
airworthiness limitation number 28-AWL-ACT, ``Engine and APU Shut-Off
Valve Actuator Test.'' This proposed AD would also require
accomplishing the actions specified in the service information
described previously, except as discussed under ``Difference Between
this Proposed AD and the Service Information.''
This proposed AD would require revisions to certain operator
maintenance documents to include new inspections. Compliance with these
inspections is required by section 91.403(c) of the Federal Aviation
Regulations (14 CFR 91.403(c)). For airplanes that have been previously
modified, altered, or repaired in the areas addressed by these
inspections, an operator might not be able to accomplish the
inspections described in the revisions. In this situation, to comply
with 14 CFR 91.403(c), the operator must request approval of an
alternative method of compliance (AMOC) in accordance with the
provisions of paragraph (k) of this proposed AD. The request should
include a description of changes to the required inspections that will
ensure the continued operational safety of the airplane.
Explanation of ``RC'' Steps in Service Information
The FAA worked in conjunction with industry, under the
Airworthiness Directives Implementation Aviation Rulemaking Committee,
to enhance the AD system. One enhancement was a new process for
annotating which steps in the service information are required for
compliance with an AD. Differentiating these steps from other tasks in
the service information is expected to improve an owner's/operator's
understanding of crucial AD
[[Page 68386]]
requirements and help provide consistent judgment in AD compliance. The
actions specified in the service information described previously
include steps that are labeled as RC (required for compliance) because
these steps have a direct effect on detecting, preventing, resolving,
or eliminating an identified unsafe condition.
As noted in the specified service information, steps labeled as RC
and all subordinate steps must be done to comply with the proposed AD.
However, steps that are not labeled as RC are recommended. Those steps
that are not labeled as RC may be deviated from, done as part of other
actions, or done using accepted methods different from those identified
in the service information without obtaining approval of an AMOC,
provided the steps labeled as RC can be done and the airplane can be
put back in a serviceable condition. Any substitutions or changes to
steps labeled as RC will require approval of an alternative method of
compliance.
Differences Between This Proposed AD and the Service Information
Although Boeing Service Bulletin B787-81205-SB280015-00, Issue 002,
dated June 19, 2014, describes installing engine fuel shutoff valve and
APU fuel shutoff valve actuators having part number (P/N) 53-0037, this
proposed AD would prohibit installing valves having P/N 53-0037, and
require installing certain other valves. We have coordinated this
difference with Boeing.
The applicability of this proposed AD includes all Model 787-8
airplanes, which differs from the effectivity of the service
information referenced previously. The parts are rotable, therefore,
this proposed AD includes all Model 787-8 airplanes.
Costs of Compliance
We estimate that this proposed AD affects 6 airplanes of U.S.
registry.
We estimate the following costs to comply with this proposed AD:
Estimated Costs
----------------------------------------------------------------------------------------------------------------
Cost per Cost on U.S.
Action Labor cost Parts cost product operators
----------------------------------------------------------------------------------------------------------------
Maintenance program revision.......... 1 work-hour x $85 per $0 $85 $510
hour = $85.
Engine and APU fuel shutoff valve 10 work-hours x $85 per 0 850 5,100
actuator replacement. hour = $850.
----------------------------------------------------------------------------------------------------------------
According to the manufacturer, some of the costs of this proposed
AD may be covered under warranty, thereby reducing the cost impact on
affected individuals. We do not control warranty coverage for affected
individuals. As a result, we have included all 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.
We are 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
We 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) Is not a ``significant rule'' under the DOT Regulatory Policies
and Procedures (44 FR 11034, February 26, 1979),
(3) Will not affect intrastate aviation in Alaska, and
(4) 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. Amend Sec. 39.13 by adding the following new airworthiness
directive (AD):
The Boeing Company: Docket No. FAA-2014-0773; Directorate Identifier
2014-NM-068-AD.
(a) Comments Due Date
We must receive comments by January 2, 2015.
(b) Affected ADs
None.
(c) Applicability
This AD applies to all The Boeing Company Model 787-8 airplanes,
certificated in any category.
(d) Subject
Air Transport Association (ATA) of America Code 28, Fuel.
(e) Unsafe Condition
This AD was prompted by a report of an error in the valve
actuator design. We are issuing this AD to prevent latent failures
of the fuel shutoff valve actuators, which could result in the
inability to shut off fuel to the engine or APU in the case of an
engine or APU fire. If the fuel cannot be shut off to a fire the
engine or APU fire could be uncontrollable which could lead to
structural failure.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Maintenance or Inspection Program Revision
Within 30 days after the effective date of this AD, revise the
maintenance or inspection
[[Page 68387]]
program, as applicable, to add airworthiness limitation number 28-
AWL-ACT, by incorporating the information specified in figure 1 to
paragraph (g) of this AD into the Airworthiness Limitations Section
of the Instructions for Continued Airworthiness. This may be
accomplished by inserting a copy of airworthiness limitation number
28-AWL-ACT into the maintenance or inspection program, as
applicable. For the airplanes identified in the applicability note
of airworthiness limitation number 28-AWL-ACT, the initial
compliance time for accomplishing the actions specified in figure 1
to paragraph (g) of this AD is within 10 days after accomplishment
of the maintenance or inspection program revision required by this
paragraph. When the engine and APU fuel shutoff valve actuators have
been replaced as required by paragraph (i) of this AD, the
airworthiness limitation number 28-AWL-ACT required by this
paragraph may be removed from the maintenance or inspection program,
as applicable.
Figure 1 to Paragraph (g) of This AD: Engine and APU Shut-Off Valve Actuator Test
--------------------------------------------------------------------------------------------------------------------------------------------------------
AWL No. Task Interval Applicability Description
--------------------------------------------------------------------------------------------------------------------------------------------------------
28-AWL-ACT..................... ALI............................ 10 Days NOTE................... ALL NOTE....................... Engine and APU Shut-
Off Valve Actuator
Test.
Concern: The fuel
shutoff valve
actuator design can
result in airplanes
operating with a
failed fuel shutoff
actuator that is
not reported. A
latently failed
fuel shutoff
actuator would
prevent fuel shut
off to an engine.
In the event of
certain engine
fires, the
potential exists
for an engine fire
to be
uncontrollable.
Perform the
following tests in
accordance with
Boeing Service
Bulletin B787-81205-
SB280015-00, Issue
002, dated June 19,
2014.
1. Do PART 1: ENGINE
FUEL SHUTOFF VALVE
ACTUATOR TEST as
described in Boeing
Service Bulletin
B787-81205-SB280015
-00, Issue 002,
dated June 19,
2014.
a. If the left
engine fuel
shutoff valve
actuator has Part
Number 53-0037,
perform the left
engine fuel
shutoff valve
actuator test.
b. If the right
engine fuel
shutoff valve
actuator has Part
Number 53-0037,
perform the right
engine fuel
shutoff valve
actuator test.
c. If either test
fails, repair
faults as
required (refer
to Boeing
Airplane
Maintenance
Manual 28-22-02).
2. Do PART 2: APU
FUEL SHUTOFF VALVE
ACTUATOR TEST as
described in Boeing
Service Bulletin
B787-81205-SB280015
-00, Issue 002,
dated June 19,
2014.
a. If the APU fuel
shutoff valve
actuator has part
number 53-0037,
perform the APU
fuel shutoff
valve actuator
test.
b. If the test
fails, before
further flight
requiring APU
availability,
repair If the
test fails,
before further
flight requiring
APU availability,
repair faults as
required (refer
to Boeing
Airplane
Maintenance
Manual 28-25-03).
NOTE: Dispatch may
be permitted per
MMEL 28-25-03 if
APU is not required
for flight.
INTERVAL NOTE: Not
required on days
when the airplane
is not used in
revenue service.
Must be done before
further flight if
it has been 10 or
more calendar days
since last
inspection
APPLICABILITY NOTE:
This AWL applies to
airplanes with
Eaton Aerospace Ltd
fuel shutoff valve
actuators having
Part Number 53-0037
installed at the
engine or APU spar
shutoff location.
--------------------------------------------------------------------------------------------------------------------------------------------------------
(h) No Alternative Actions and Intervals
Except as specified in paragraph (i) of this AD: After
accomplishment of the maintenance or inspection program revision
required by paragraph (g) of this AD, no alternative actions (e.g.,
inspections) or intervals may be used unless the actions or
intervals are approved as an alternative method of compliance (AMOC)
in accordance with the procedures specified in paragraph (k) of this
AD.
(i) Replacement
Within 36 months after the effective date of this AD, replace
the engine and APU fuel shutoff valve actuators having part number
(P/N) 53-0037 with P/N 53-0049, in accordance with Part 5 or Part 6
of the Accomplishment Instructions of Boeing Service Bulletin B787-
81205-SB280015-00, Issue 002, dated June 19, 2014, as applicable.
When all the engine and APU fuel shutoff valve actuators have been
replaced as required by this paragraph, the airworthiness limitation
number 28-AWL-ACT required by paragraph (g) of this AD may be
removed from the maintenance or inspection program, as applicable.
(j) Parts Installation Prohibition
As of the effective date of this AD, no person may install a
motor operated valve actuator having P/N 53-0037 on any airplane in
the following locations: Engine fuel shutoff valve, APU fuel shutoff
valve, crossfeed valve, and defuel/isolation valve.
[[Page 68388]]
(k) Alternative Methods of Compliance (AMOCs)
(1) The Manager, Seattle Aircraft Certification Office (ACO),
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 ACO, send it to the
attention of the person identified in paragraph (l)(1) of this AD.
Information may be emailed to: 9-ANM-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) If the service information contains steps that are labeled
as RC (Required for Compliance), those steps and all subordinate
steps must be done to comply with this AD; any steps that are not
labeled as RC are recommended. Those steps that are not labeled as
RC may be deviated from, done as part of other actions, or done
using accepted methods different from those identified in the
specified service information without obtaining approval of an AMOC,
provided the steps labeled as RC can be done and the airplane can be
put back in a serviceable condition. Any substitutions or changes to
steps labeled as RC require approval of an AMOC.
(l) Related Information
(1) For more information about this AD, contact Rebel Nichols,
Aerospace Engineer, Propulsion Branch, ANM-140S, FAA, Seattle
Aircraft Certification Office, 1601 Lind Avenue SW., Renton, WA
98057-3356; phone: 425-917-6509; fax: 425-917-6590; email:
Rebel.Nichols@faa.gov.
(2) For service information identified in this AD, contact
Boeing Commercial Airplanes, Attention: Data & Services Management,
P.O. Box 3707, MC 2H-65, Seattle, WA 98124-2207; telephone 206-544-
5000, extension 1; fax 206-766-5680; Internet https://www.myboeingfleet.com. You may view this referenced service
information at the FAA, Transport Airplane Directorate, 1601 Lind
Avenue SW., Renton, WA. For information on the availability of this
material at the FAA, call 425-227-1221.
Issued in Renton, Washington, on November 5, 2014.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2014-27069 Filed 11-14-14; 8:45 am]
BILLING CODE 4910-13-P
