Airworthiness Directives; The Boeing Company, 20834-20837 [2014-08320]

Download as PDF 20834 Federal Register / Vol. 79, No. 71 / Monday, April 14, 2014 / Proposed Rules RApublications@baesystems.com; Internet: http://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 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 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 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: 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 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. 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 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: 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 http://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 http:// 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 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-
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 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:

[[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