
[Federal Register Volume 79, Number 43 (Wednesday, March 5, 2014)]
[Proposed Rules]
[Pages 12431-12434]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2014-04898]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2014-0126; Directorate Identifier 2013-NM-236-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 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 April 21, 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: 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 http://www.regulations.gov by searching for and locating Docket No. FAA-2014-
0126; 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-2014-0126; 
Directorate Identifier 2013-NM-236-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.

[[Page 12432]]

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 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 590 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
----------------------------------------------------------------------------------------------------------------
Incorporating Airworthiness         1 work-hour x $85 per                  $0              $85          $50,150
 Limitation.                         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 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-2014-0126; Directorate Identifier 
2013-NM-236-AD.

(a) Comments Due Date

    We must receive comments by April 21, 2014.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to all The Boeing Company Model 757-200, -200PF, 
-200CB, and -300 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 numbers 28-AWL-ENG and 28-AWL-APU, by 
incorporating the information specified in Figure 1 and Figure 2 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 Figure 1 
and Figure 2 to paragraph (g) of this AD is within 7 days after 
accomplishing the

[[Page 12433]]

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 No.          Task       Interval     Applicability                       Description
----------------------------------------------------------------------------------------------------------------
28-AWL-ENG.......  ALI......  DAILY........  ALL............  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 shutoff 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 an operational check of the left engine fuel
                                                               spar valve actuator.
                                                              a. As the L FUEL CONTROL switch on the quadrant
                                                               control stand is moved to the CUTOFF position,
                                                               verify the left SPAR VALVE disagreement light on
                                                               the quadrant control stand illuminates and then
                                                               goes off.
                                                              b. If the test fails (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 R FUEL CONTROL switch on the quadrant
                                                               control stand is moved to the CUTOFF position,
                                                               verify the right SPAR VALVE disagreement light on
                                                               the quadrant control stand illuminates and then
                                                               goes off.
                                                              b. If the test fails (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 L FUEL CONTROL switch on the quadrant
                                                               control stand is moved to the RUN position,
                                                               verify the left SPAR VALVE disagreement light on
                                                               the quadrant control stand illuminates and then
                                                               goes off.
                                                              b. If the test fails (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 R FUEL CONTROL switch on the quadrant
                                                               control stand is moved to the RUN position,
                                                               verify the right SPAR VALVE disagreement light on
                                                               the quadrant control stand illuminates and then
                                                               goes off.
                                                              b. If the test fails (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 all fuel pump switches on the
                                                               Overhead Panel are in the OFF position.
                                                              2. If the APU is running, open and collar the L
                                                               FWD FUEL BOOST PUMP (C00372) circuit breaker on
                                                               the Main Power Distribution Panel.
                                                              3. Make sure LEFT and RIGHT ENG FIRE switches on
                                                               the Aft Aisle Stand are in the NORMAL (IN)
                                                               position.
                                                              4. Make sure L and R Engine Start Selector
                                                               Switches on the Overhead Panel are in the OFF
                                                               position.
                                                              5. Do an operational check of the left engine fuel
                                                               spar valve actuator.
                                                              a. Move L FUEL CONTROL switch on the quadrant
                                                               control stand to the RUN position and wait 10
                                                               seconds.
                                                              NOTE: It is normal under this test condition for
                                                               the ENG VALVE disagreement light on the quadrant
                                                               control stand to stay illuminated.
                                                              b. Move L FUEL CONTROL switch on the quadrant
                                                               control stand to the CUTOFF position.
                                                              c. Verify the left SPAR VALVE disagreement light
                                                               on the quadrant control stand illuminates and
                                                               then goes off.
                                                              d. If the test fails (light fails to illuminate),
                                                               before further flight, repair faults as required
                                                               (refer to Boeing AMM 28-22-11).
                                                              6. Do an operational check of the right engine
                                                               fuel spar valve actuator.
                                                              a. Move R FUEL CONTROL switch on the quadrant
                                                               control stand to the RUN position and wait 10
                                                               seconds.
                                                              NOTE: It is normal under this test condition for
                                                               the ENG VALVE disagreement light on the quadrant
                                                               control stand to stay illuminated.
                                                              b. Move R FUEL CONTROL switch on the quadrant
                                                               control stand to the CUTOFF position.
                                                              c. Verify the right SPAR VALVE disagreement light
                                                               on the quadrant control stand illuminates and
                                                               then goes off.
                                                              d. If the test fails, (light fails to illuminate),
                                                               before further flight, repair faults as required
                                                               (refer to Boeing AMM 28-22-11).
                                                              7. If the L FWD FUEL BOOST PUMP circuit breaker
                                                               was collared in step C.2., remove collar and
                                                               close.
----------------------------------------------------------------------------------------------------------------


[[Page 12434]]


           Figure 2 to Paragraph (g) of This AD: APU Fuel Valve Position Indication Operational Check
----------------------------------------------------------------------------------------------------------------
     AWL No.          Task       Interval     Applicability                       Description
----------------------------------------------------------------------------------------------------------------
28-AWL-APU.......  ALI......  10 DAYS......  ALL............  APU Fuel 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 shutoff to the APU.
                                                               In the event of certain APU fires, the potential
                                                               exists for an APU fire to be uncontrollable.
                                                              Perform the operational check of the APU Fuel
                                                               Valve position indication (unless checked by the
                                                               flight crew in a manner approved by the principal
                                                               operations inspector).
                                                              A. Operational check of the APU Fuel Valve
                                                               position indication
                                                              1. If the APU is running, unload and shut down the
                                                               APU using standard practices.
                                                              2. Make sure the APU FIRE switch on the Aft Aisle
                                                               Stand is in the NORMAL (IN) position.
                                                              3. Make sure there is at least 700 lbs (300 kgs)
                                                               of fuel in the Left Main Tank.
                                                              4. Move APU Selector switch on the Overhead Panel
                                                               to the ON position and wait 10 seconds.
                                                              5. Move APU Selector switch on the Overhead Panel
                                                               to the OFF position.
                                                              6. Verify the APU FAULT light on the Overhead
                                                               Panel illuminates and then goes off.
                                                              7. If the test fails (light fails to illuminate),
                                                               before further flight requiring APU availability,
                                                               repair faults as required (refer to Boeing AMM 28-
                                                               25-11).
                                                              NOTE: Dispatch may be permitted per MMEL 28-25-02
                                                               if APU is not required for flight.
----------------------------------------------------------------------------------------------------------------

(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 February 21, 2014.
John P. Piccola,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2014-04898 Filed 3-4-14; 8:45 am]
BILLING CODE 4910-13-P


