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 

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: 

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Federal Register / Vol. 79, No. 71 / Monday, April 14, 2014 / Proposed Rules 20835 

ESTIMATED COSTS

Action Labor cost Parts cost Cost per 

product 

Cost on U.S. 

operators 

Incorporating Airworthiness Limitation.1 work-hour × $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. 

§ 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. 

(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, –700C, 

–800, –900, and 

–900ER series airplanes.

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: 

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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 

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. 

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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 

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 

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 

DEPARTMENT OF TRANSPORTATION 

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 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: 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– 

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 

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