Airworthiness Directives; The Boeing Company, 20834-20837 [2014-08320]
Download as PDF
<![CDATA[
20834
Federal Register / Vol. 79, No. 71 / Monday, April 14, 2014 / Proposed Rules
RApublications@baesystems.com; Internet:
https://www.baesystems.com/Businesses/
RegionalAircraft/. You may review copies of
the referenced service information at the
FAA, Small Airplane Directorate, 901 Locust,
Kansas City, Missouri 64106. For information
on the availability of this material at the
FAA, call (816) 329–4148.
Issued in Kansas City, Missouri, on April
7, 2014.
Timothy Smyth,
Acting Manager, Small Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 2014–08318 Filed 4–11–14; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2014–0194; Directorate
Identifier 2014–NM–022–AD]
RIN 2120–AA64
Airworthiness Directives; The Boeing
Company
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 737–600, –700,
–700C, –800, –900, and –900ER series
airplanes. This proposed AD was
prompted by reports of latently failed
fuel shutoff valves discovered during
fuel filter replacement. This proposed
AD would require revising the
maintenance or inspection program to
include new airworthiness limitations.
We are proposing this AD to detect and
correct latent failures of the fuel shutoff
valve to the engine, which could result
in the inability to shut off fuel to the
engine and, in case of certain engine
fires, an uncontrollable fire that could
lead to wing failure.
DATES: We must receive comments on
this proposed AD by May 29, 2014.
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
mstockstill on DSK4VPTVN1PROD with PROPOSALS
SUMMARY:
VerDate Mar<15>2010
16:59 Apr 11, 2014
Jkt 232001
p.m., Monday through Friday, except
Federal holidays.
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–
0194; 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–
2014–0194; Directorate Identifier 2014–
NM–022–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 have received reports of latently
failed fuel shutoff valves discovered
during fuel filter replacement.
Deficiencies in the valve actuator design
have resulted in latent failures of the
fuel shutoff valve to the engine. This
condition, if not detected and corrected,
could result in latent failures of the fuel
shutoff valve to the engine, which could
result in the inability to shut off fuel to
the engine and, in case of certain engine
fires, an uncontrollable fire that could
lead to wing failure.
PO 00000
Frm 00017
Fmt 4702
Sfmt 4702
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
revising the maintenance or inspection
program to include new airworthiness
limitations. The airworthiness
limitations would allow an operator to
perform the operational check as either
a maintenance action or a flightcrew
action. The flightcrew or maintenance
crew would monitor the engine spar
valve lights for a few seconds
immediately after moving the engine
fuel condition levers. Flightcrews can
perform this operational check while
starting the engine or while shutting
down the engine. Maintenance crews
can do this operational check as a
separate action that does not require
actual starting of the engine.
This proposed AD would require
revisions to certain operator
maintenance documents to include
these 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 (i) of this
proposed AD. The request should
include a description of changes to the
proposed inspections that will ensure
the continued operational safety of the
airplane.
Interim Action
We consider this proposed AD
interim action. The manufacturer is
currently developing a modification that
will address the unsafe condition
identified in this proposed AD. Once
this modification is developed,
approved, and available, we might
consider additional rulemaking.
Costs of Compliance
We estimate that this proposed AD
affects 1,244 airplanes of U.S. registry.
We estimate the following costs to
comply with this proposed AD:
E:\FR\FM\14APP1.SGM
14APP1
20835
Federal Register / Vol. 79, No. 71 / Monday, April 14, 2014 / Proposed Rules
ESTIMATED COSTS
Parts cost
Action
Labor cost
Incorporating Airworthiness Limitation.
Cost per
product
$0
$85
1 work-hour × $85 per hour = $85 ....................................................
Authority for this Rulemaking
Title 49 of the United States Code
specifies the FAA’s authority to issue
rules on aviation safety. Subtitle I,
section 106, describes the authority of
the FAA Administrator. Subtitle VII:
Aviation Programs, describes in more
detail the scope of the Agency’s
authority.
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 proposed
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,
Cost on U.S.
operators
$105,740
(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.
(b) Affected ADs
List of Subjects in 14 CFR Part 39
(e) Unsafe Condition
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
This AD was prompted by reports of
latently failed fuel shutoff valves discovered
during fuel filter replacement. We are issuing
this AD to detect and correct latent failures
of the fuel shutoff valve to the engine, which
could result in the inability to shut off fuel
to the engine and, in case of certain engine
fires, an uncontrollable fire that could lead to
wing failure.
The Proposed Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA proposes to amend 14 CFR part
39 as follows:
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by adding
the following new airworthiness
directive (AD):
The Boeing Company: Docket No. FAA–
2014–0194; Directorate Identifier 2014–
NM–022–AD.
(a) Comments Due Date
We must receive comments by May 29,
2014.
None.
(c) Applicability
This AD applies to all The Boeing
Company Model 737–600, –700, –700C,
–800, –900, and –900ER series airplanes,
certificated in any category.
(d) Subject
Joint Aircraft System Component (JASC)
Code 2823, Fuel Selector/Shut-off Valve.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Revision of Maintenance or Inspection
Program
Within 30 days after the effective date of
this AD, revise the maintenance or inspection
program, as applicable, to add airworthiness
limitation number 28–AWL–MOV, 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.
The initial compliance time for
accomplishing the actions specified in 28–
AWL–MOV is within 7 days after
accomplishing the maintenance or inspection
program revision required by this paragraph.
FIGURE 1 TO PARAGRAPH (G) OF THIS AD: ENGINE SHUT-OFF VALVE (FUEL SPAR VALVE) POSITION INDICATION
OPERATIONAL CHECK
Task
Interval
Applicability
28–AWL–MOV .............
mstockstill on DSK4VPTVN1PROD with PROPOSALS
AWL Number
ALI ................
DAILY ...........
737–600, –700, –700C,
–800, –900, and
–900ER series airplanes.
VerDate Mar<15>2010
16:59 Apr 11, 2014
Jkt 232001
PO 00000
Frm 00018
Fmt 4702
Sfmt 4702
Description
Engine Shut-Off Valve (Fuel Spar Valve) Position Indication Operational Check.
Concern: The MOV actuator design can result in airplanes
operating with a failed MOV actuator that is not reported.
A latently failed MOV actuator could 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 one of the following operational checks of the Fuel
Spar Valve position indication (unless checked by the
flight crew in a manner approved by the principal operations inspector):
A. Operational Check during engine shutdown:
E:\FR\FM\14APP1.SGM
14APP1
20836
Federal Register / Vol. 79, No. 71 / Monday, April 14, 2014 / Proposed Rules
FIGURE 1 TO PARAGRAPH (G) OF THIS AD: ENGINE SHUT-OFF VALVE (FUEL SPAR VALVE) POSITION INDICATION
OPERATIONAL CHECK—Continued
mstockstill on DSK4VPTVN1PROD with PROPOSALS
AWL Number
Task
Interval
Applicability
Description
1. Do all operational checks of the left engine fuel spar
valve actuator.
a. As the ENG 1 START LEVER on the CONTROL
STAND is moved to the CUTOFF position, verify the
SPAR VALVE CLOSED indication light on the OVERHEAD PANEL for No.1 Engine changes from OFF to
BRIGHT then DIM.
b. If the test fails, (bright light fails to illuminate), before further flight, repair faults as required (refer to Boeing airplane maintenance manual (AMM) 28–22–11).
2. Do an operational check of the right engine fuel spar
valve actuator.
a. As the ENG 2 START LEVER on the CONTROL
STAND is moved to the CUTOFF position, verify the
SPAR VALVE CLOSED indication light on the OVERHEAD PANEL for No. 2 Engine changes from OFF to
BRIGHT then DIM.
b. If the test fails, (bright light fails to illuminate), before further flight, repair faults as required (refer to Boeing AMM
28–22–11).
B. Operational check during engine start.
1. Do an operational check of the left engine fuel spar
valve actuator.
a. As the ENG 1 START LEVER on the CONTROL
STAND is moved to the IDLE position, verify the SPAR
VALVE CLOSED indication light on the OVERHEAD
PANEL for No. 1 Engine changes from DIM to BRIGHT
then OFF.
b. If the test fails, (bright light fails to illuminate), before further flight, repair faults as required (refer to Boeing AMM
28–22–11).
2. Do an operational check of the right engine fuel spar
valve actuator.
a. As the ENG 2 START LEVER on the CONTROL
STAND is moved to the IDLE position, verify the SPAR
VALVE CLOSED indication light on the OVERHEAD
PANEL for No. 2 Engine changes from DIM to BRIGHT
then OFF.
b. If the test fails, (bright light fails to illuminate), before further flight, repair faults as required (refer to Boeing AMM
28–22–11).
C. Operational check without engine operation.
1. Make sure No. 1 and No. 2 Engine FIRE switches on
the Aft Electronic Panel are in the NORMAL (IN) position.
2. Make sure No. 1 and No. 2 Engine Start Switches on
the Forward Overhead Panel, are in the OFF or AUTO
position.
3. Do an operational check of the left engine fuel spar
valve actuator.
a. Move ENG 1 START LEVER on the CONTROL STAND
to the IDLE position and wait 10 seconds.
NOTE: It is normal under this test condition for the ENG
VALVE CLOSED indication light on the OVERHEAD.
PANEL to transition from DIM to BRIGHT and stay
BRIGHT.
b. Move ENG 1 START LEVER on the CONTROL STAND
to the CUTOFF position.
c. Verify the SPAR VALVE CLOSED indication light on the
OVERHEAD PANEL for No. 1 Engine changes from
OFF to BRIGHT then DIM.
d. If the test fails, (bright light fails to illuminate), before further flight, repair faults as required (refer to Boeing AMM
28–22–11).
4. Do an operational check of the right engine fuel spar
valve actuator.
a. Move ENG 2 START LEVER on the CONTROL STAND
to the IDLE position and wait 10 seconds.
VerDate Mar<15>2010
16:59 Apr 11, 2014
Jkt 232001
PO 00000
Frm 00019
Fmt 4702
Sfmt 4702
E:\FR\FM\14APP1.SGM
14APP1
Federal Register / Vol. 79, No. 71 / Monday, April 14, 2014 / Proposed Rules
20837
FIGURE 1 TO PARAGRAPH (G) OF THIS AD: ENGINE SHUT-OFF VALVE (FUEL SPAR VALVE) POSITION INDICATION
OPERATIONAL CHECK—Continued
AWL Number
Task
Interval
Applicability
Description
NOTE: It is normal under this test condition for the ENG
VALVE CLOSED indication light on the OVERHEAD
PANEL to transition from DIM to BRIGHT and stay
BRIGHT.
b. Move ENG 2 START LEVER on the CONTROL STAND
to the CUTOFF position.
c. Verify the SPAR VALVE CLOSED indication light on the
OVERHEAD PANEL for No. 2 Engine changes from
OFF to BRIGHT then DIM.
d. If the test fails, (bright light fails to illuminate), before further flight, repair faults as required (refer to Boeing AMM
28–22–11).
(h) No Alternative Actions and Intervals
DEPARTMENT OF TRANSPORTATION
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 (i)(1) of
this AD.
(i) 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 (j) 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.
(j) Related Information
mstockstill on DSK4VPTVN1PROD with PROPOSALS
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.
Issued in Renton, Washington, on April 4,
2014.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 2014–08320 Filed 4–11–14; 8:45 am]
BILLING CODE 4910–13–P
VerDate Mar<15>2010
16:59 Apr 11, 2014
Jkt 232001
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2014–0230; Directorate
Identifier 2013–NM–242–AD]
RIN 2120–AA64
Airworthiness Directives; Airbus
Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
We propose to adopt a new
airworthiness directive (AD) for certain
Airbus Model A300–600 series
airplanes. This proposed AD was
prompted by reports of cracking found
in the pylon box, which was due to the
stresses resulting from the pressure
applied by the engines’ thrust reverser
cowl bumpers. This proposed AD would
require repetitive high frequency eddy
current (HFEC) inspections for cracking,
and replacement of all fittings if
necessary. Replacement of all fittings
would terminate the repetitive HFEC
inspections. We are proposing this AD
to detect and correct cracks of the pylon
rib 5, which could result in reduced
structural integrity of the airplane.
DATES: We must receive comments on
this proposed AD by May 29, 2014.
ADDRESSES: You may send comments 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: U.S. Department of
Transportation, Docket Operations, M–
SUMMARY:
PO 00000
Frm 00020
Fmt 4702
Sfmt 4702
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue SE.,
Washington, DC, between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays.
For service information identified in
this proposed AD, contact Airbus SAS,
Airworthiness Office—EAW, 1 Rond
Point Maurice Bellonte, 31707 Blagnac
Cedex, France; telephone +33 5 61 93 36
96; fax +33 5 61 93 44 51; email
account.airworth-eas@airbus.com;
Internet https://www.airbus.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–
0230; 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 Operations
office (telephone (800) 647–5527) is in
the ADDRESSES section. Comments will
be available in the AD docket shortly
after receipt.
FOR FURTHER INFORMATION CONTACT: Dan
Rodina, Aerospace Engineer,
International Branch, ANM–116,
Transport Airplane Directorate, FAA,
1601 Lind Avenue SW., Renton,
Washington 98057–3356; telephone
(425) 227–2125; fax (425) 227–1149.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written
relevant data, views, or arguments about
this proposed AD. Send your comments
E:\FR\FM\14APP1.SGM
14APP1
]]>Agencies
[Federal Register Volume 79, Number 71 (Monday, April 14, 2014)]
[Proposed Rules]
[Pages 20834-20837]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2014-08320]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2014-0194; Directorate Identifier 2014-NM-022-AD]
RIN 2120-AA64
Airworthiness Directives; The Boeing Company
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 737-600, -700, -700C, -800, -900, and -900ER
series airplanes. This proposed AD was prompted by reports of latently
failed fuel shutoff valves discovered during fuel filter replacement.
This proposed AD would require revising the maintenance or inspection
program to include new airworthiness limitations. We are proposing this
AD to detect and correct latent failures of the fuel shutoff valve to
the engine, which could result in the inability to shut off fuel to the
engine and, in case of certain engine fires, an uncontrollable fire
that could lead to wing failure.
DATES: We must receive comments on this proposed AD by May 29, 2014.
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.
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-
0194; 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-2014-0194;
Directorate Identifier 2014-NM-022-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 have received reports of latently failed fuel shutoff valves
discovered during fuel filter replacement. Deficiencies in the valve
actuator design have resulted in latent failures of the fuel shutoff
valve to the engine. This condition, if not detected and corrected,
could result in latent failures of the fuel shutoff valve to the
engine, which could result in the inability to shut off fuel to the
engine and, in case of certain engine fires, an uncontrollable fire
that could lead to wing failure.
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 revising the maintenance or
inspection program to include new airworthiness limitations. The
airworthiness limitations would allow an operator to perform the
operational check as either a maintenance action or a flightcrew
action. The flightcrew or maintenance crew would monitor the engine
spar valve lights for a few seconds immediately after moving the engine
fuel condition levers. Flightcrews can perform this operational check
while starting the engine or while shutting down the engine.
Maintenance crews can do this operational check as a separate action
that does not require actual starting of the engine.
This proposed AD would require revisions to certain operator
maintenance documents to include these 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 (i) of this proposed AD. The request should
include a description of changes to the proposed inspections that will
ensure the continued operational safety of the airplane.
Interim Action
We consider this proposed AD interim action. The manufacturer is
currently developing a modification that will address the unsafe
condition identified in this proposed AD. Once this modification is
developed, approved, and available, we might consider additional
rulemaking.
Costs of Compliance
We estimate that this proposed AD affects 1,244 airplanes of U.S.
registry.
We estimate the following costs to comply with this proposed AD:
[[Page 20835]]
Estimated Costs
----------------------------------------------------------------------------------------------------------------
Parts Cost per Cost on U.S.
Action Labor cost cost product operators
----------------------------------------------------------------------------------------------------------------
Incorporating Airworthiness Limitation.. 1 work-hour x $85 per hour = $85 $0 $85 $105,740
----------------------------------------------------------------------------------------------------------------
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 proposed 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
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]
2. The FAA amends Sec. 39.13 by adding the following new
airworthiness directive (AD):
The Boeing Company: Docket No. FAA-2014-0194; Directorate Identifier
2014-NM-022-AD.
(a) Comments Due Date
We must receive comments by May 29, 2014.
(b) Affected ADs
None.
(c) Applicability
This AD applies to all The Boeing Company Model 737-600, -700, -
700C, -800, -900, and -900ER series airplanes, certificated in any
category.
(d) Subject
Joint Aircraft System Component (JASC) Code 2823, Fuel Selector/
Shut-off Valve.
(e) Unsafe Condition
This AD was prompted by reports of latently failed fuel shutoff
valves discovered during fuel filter replacement. We are issuing
this AD to detect and correct latent failures of the fuel shutoff
valve to the engine, which could result in the inability to shut off
fuel to the engine and, in case of certain engine fires, an
uncontrollable fire that could lead to wing failure.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Revision of Maintenance or Inspection Program
Within 30 days after the effective date of this AD, revise the
maintenance or inspection program, as applicable, to add
airworthiness limitation number 28-AWL-MOV, 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. The initial compliance time for
accomplishing the actions specified in 28-AWL-MOV is within 7 days
after accomplishing the maintenance or inspection program revision
required by this paragraph.
Figure 1 to Paragraph (g) of this AD: Engine Shut-Off Valve (Fuel Spar Valve) Position Indication Operational
Check
----------------------------------------------------------------------------------------------------------------
AWL Number Task Interval Applicability Description
----------------------------------------------------------------------------------------------------------------
28-AWL-MOV.................... ALI............. DAILY........... 737-600, -700, - Engine Shut-Off Valve
700C, -800, - (Fuel Spar Valve)
900, and -900ER Position Indication
series Operational Check.
airplanes.
Concern: The MOV actuator
design can result in
airplanes operating with
a failed MOV actuator
that is not reported. A
latently failed MOV
actuator could 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 one of the
following operational
checks of the Fuel Spar
Valve position indication
(unless checked by the
flight crew in a manner
approved by the principal
operations inspector):
A. Operational Check
during engine shutdown:
[[Page 20836]]
1. Do all operational
checks of the left engine
fuel spar valve actuator.
a. As the ENG 1 START
LEVER on the CONTROL
STAND is moved to the
CUTOFF position, verify
the SPAR VALVE CLOSED
indication light on the
OVERHEAD PANEL for No.1
Engine changes from OFF
to BRIGHT then DIM.
b. If the test fails,
(bright light fails to
illuminate), before
further flight, repair
faults as required (refer
to Boeing airplane
maintenance manual (AMM)
28-22-11).
2. Do an operational check
of the right engine fuel
spar valve actuator.
a. As the ENG 2 START
LEVER on the CONTROL
STAND is moved to the
CUTOFF position, verify
the SPAR VALVE CLOSED
indication light on the
OVERHEAD PANEL for No. 2
Engine changes from OFF
to BRIGHT then DIM.
b. If the test fails,
(bright light fails to
illuminate), before
further flight, repair
faults as required (refer
to Boeing AMM 28-22-11).
B. Operational check
during engine start.
1. Do an operational check
of the left engine fuel
spar valve actuator.
a. As the ENG 1 START
LEVER on the CONTROL
STAND is moved to the
IDLE position, verify the
SPAR VALVE CLOSED
indication light on the
OVERHEAD PANEL for No. 1
Engine changes from DIM
to BRIGHT then OFF.
b. If the test fails,
(bright light fails to
illuminate), before
further flight, repair
faults as required (refer
to Boeing AMM 28-22-11).
2. Do an operational check
of the right engine fuel
spar valve actuator.
a. As the ENG 2 START
LEVER on the CONTROL
STAND is moved to the
IDLE position, verify the
SPAR VALVE CLOSED
indication light on the
OVERHEAD PANEL for No. 2
Engine changes from DIM
to BRIGHT then OFF.
b. If the test fails,
(bright light fails to
illuminate), before
further flight, repair
faults as required (refer
to Boeing AMM 28-22-11).
C. Operational check
without engine operation.
1. Make sure No. 1 and No.
2 Engine FIRE switches on
the Aft Electronic Panel
are in the NORMAL (IN)
position.
2. Make sure No. 1 and No.
2 Engine Start Switches
on the Forward Overhead
Panel, are in the OFF or
AUTO position.
3. Do an operational check
of the left engine fuel
spar valve actuator.
a. Move ENG 1 START LEVER
on the CONTROL STAND to
the IDLE position and
wait 10 seconds.
NOTE: It is normal under
this test condition for
the ENG VALVE CLOSED
indication light on the
OVERHEAD.
PANEL to transition from
DIM to BRIGHT and stay
BRIGHT.
b. Move ENG 1 START LEVER
on the CONTROL STAND to
the CUTOFF position.
c. Verify the SPAR VALVE
CLOSED indication light
on the OVERHEAD PANEL for
No. 1 Engine changes from
OFF to BRIGHT then DIM.
d. If the test fails,
(bright light fails to
illuminate), before
further flight, repair
faults as required (refer
to Boeing AMM 28-22-11).
4. Do an operational check
of the right engine fuel
spar valve actuator.
a. Move ENG 2 START LEVER
on the CONTROL STAND to
the IDLE position and
wait 10 seconds.
[[Page 20837]]
NOTE: It is normal under
this test condition for
the ENG VALVE CLOSED
indication light on the
OVERHEAD PANEL to
transition from DIM to
BRIGHT and stay BRIGHT.
b. Move ENG 2 START LEVER
on the CONTROL STAND to
the CUTOFF position.
c. Verify the SPAR VALVE
CLOSED indication light
on the OVERHEAD PANEL for
No. 2 Engine changes from
OFF to BRIGHT then DIM.
d. If the test fails,
(bright light fails to
illuminate), before
further flight, repair
faults as required (refer
to Boeing AMM 28-22-11).
----------------------------------------------------------------------------------------------------------------
(h) No Alternative Actions and Intervals
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 (i)(1) of this AD.
(i) 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 (j) 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.
(j) Related Information
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.
Issued in Renton, Washington, on April 4, 2014.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2014-08320 Filed 4-11-14; 8:45 am]
BILLING CODE 4910-13-P
