[Federal Register Volume 79, Number 71 (Monday, April 14, 2014)]
[Proposed Rules]
[Pages 20834-20837]
[FR Doc No: 2014-08320]

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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).

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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 http://www.regulations.gov. Follow the instructions for submitting comments.
     Fax:<PHONE_NUMBER>.
     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 http://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:<PHONE_NUMBER>) 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:<PHONE_NUMBER>; email<EMAIL_ADDRESS>
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 http://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:

                                                 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
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          AWL Number                  Task            Interval        Applicability           Description
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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:

                                                                                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.

                                                                                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).
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(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<EMAIL_ADDRESS>    (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:<PHONE_NUMBER>; fax:<PHONE_NUMBER>; email:
<EMAIL_ADDRESS>

    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