68384 Federal Register / Vol. 79, No. 221 / Monday, November 17, 2014 / Proposed Rules 

(g) Repetitive Inspections for Crack 

Indications at Stringers S–4R and S–4L, 

Body Station (BS) 360 to BS 908 

At the applicable time specified in Table 

1 of paragraph 1.E., ‘‘Compliance,’’ of Boeing 

Alert Service Bulletin 737–53A1319, 

Revision 2, dated April 4, 2014: Do an 

external eddy current inspection, or internal 

eddy current and detailed inspections, for 

crack indications at stringers S–4R and S–4L, 

from body station (BS) 360 to BS 908, except 

as provided by paragraph (h) of this AD, in 

accordance with Part 1 of the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 737–53A1319, Revision 2, 

dated April 4, 2014. Repeat the inspection(s) 

thereafter at the applicable intervals specified 

in Table 1 or Table 2, as applicable, of 

paragraph 1.E., ‘‘Compliance,’’ of Boeing 

Alert Service Bulletin 737–53A1319, 

Revision 2, dated April 4, 2014. Either 

inspection option may be used at any 

repetitive inspection cycle. 

(h) One-Time Inspections for Cracks at 

Stringers S–4L and S–4R, BS 360 to BS 908 

At the applicable time specified in Table 

3 of paragraph 1.E., ‘‘Compliance,’’ of Boeing 

Alert Service Bulletin 737–53A1319, 

Revision 2, dated April 4, 2014, except as 

required by paragraph (m) of this AD: Do 

one-time internal detailed and eddy current 

inspections for cracks at stringers S–4R and 

S–4L, from BS 360 to BS 908, in accordance 

with Part 2 of the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

737–53A1319, Revision 2, dated April 4, 

2014. Accomplishment of the inspections 

required by this paragraph does not terminate 

the repetitive inspections required by 

paragraph (g) of this AD. 

(i) One-Time Inspections for Cracks at 

Stringer S–4R, BS 908 to BS 1016 

For airplanes identified as Group 2, 3, 5, 

and 7 in Boeing Alert Service Bulletin 737– 

53A1319, Revision 2, dated April 4, 2014: At 

the applicable time specified in Table 4 of 

paragraph 1.E., ‘‘Compliance,’’ of Boeing 

Alert Service Bulletin 737–53A1319, 

Revision 2, dated April 4, 2014, except as 

required by paragraph (m) of this AD, do onetime internal detailed and eddy current 

inspections for cracks at stringer S–4R, from 

BS 908 to BS 1016, in accordance with Part 

3 of the Accomplishment Instructions of 

Boeing Alert Service Bulletin 737–53A1319, 

Revision 2, dated April 4, 2014. 

(j) Repetitive Inspections for Cracks at 

Stringer S–4R, BS 908 to BS 1016 

For airplanes identified as Group 2, 3, 5, 

and 7 in Boeing Alert Service Bulletin 737– 

53A1319, Revision 2, dated April 4, 2014: At 

the applicable time specified in Table 5 of 

paragraph 1.E., ‘‘Compliance,’’ of Boeing 

Alert Service Bulletin 737–53A1319, 

Revision 2, dated April 4, 2014, except as 

required by paragraph (m) of this AD, do 

external eddy current inspections, or internal 

eddy current and detailed inspections, for 

cracks at stringer S–4R, from BS 908 to BS 

1016, in accordance with Part 4 of the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 737–53A1319, Revision 2, 

dated April 4, 2014. Repeat the inspection(s) 

thereafter at the applicable intervals specified 

in Table 5 of paragraph 1.E., ‘‘Compliance,’’ 

of Boeing Alert Service Bulletin 737– 

53A1319, Revision 2, dated April 4, 2014. 

Either inspection option may be used at any 

repetitive inspection cycle. 

(k) General Visual Inspection for Open 

Pockets at Stringer S–4R, BS 908 to BS 1016 

For airplanes identified as Group 1, 4, and 

6 in Boeing Alert Service Bulletin 737– 

53A1319, Revision 2, dated April 4, 2014: At 

the applicable time specified in Table 6 of 

paragraph 1.E., ‘‘Compliance,’’ of Boeing 

Alert Service Bulletin 737–53A1319, 

Revision 2, dated April 4, 2014, except as 

required by paragraph (m) of this AD, do a 

general visual inspection for open pockets of 

the lower skin panel at stringer S–4R, from 

BS 908 to BS 1016, in accordance with Part 

5 of the Accomplishment Instructions of 

Boeing Alert Service Bulletin 737–53A1319, 

Revision 2, dated April 4, 2014. If any open 

pocket is found, before further flight, inspect 

and repair using a method approved in 

accordance with the procedures specified in 

paragraph (o) of this AD. 

(l) Corrective Action 

If any crack is found during any inspection 

required by this AD: Before further flight, 

repair using a method approved in 

accordance with the procedures specified in 

paragraph (o) of this AD. Accomplishment of 

repairs approved in accordance with the 

procedures specified in paragraph (o) of this 

AD terminates the repetitive inspections 

specified in paragraphs (g) and (j) of this AD 

in the repaired areas only. 

(m) Service Information Exception 

Where Boeing Alert Service Bulletin 737– 

53A1319, Revision 2, dated April 4, 2014, 

specifies a compliance time ‘‘after the 

Revision 2 date of this service bulletin,’’ this 

AD requires compliance within the specified 

compliance time after the effective date of 

this AD. 

(n) Credit for Previous Actions 

This paragraph provides credit for actions 

required by paragraph (g) of this AD, if those 

actions were performed before the effective 

date of this AD using Boeing Alert Service 

Bulletin 737–53A1319, dated April 4, 2011; 

or Boeing Alert Service Bulletin 737– 

53A1319, Revision 1, dated April 8, 2011. 

Boeing Alert Service Bulletin 737–53A1319, 

dated April 4, 2011, is incorporated by 

reference in AD 2011–08–51, Amendment 

39–16701 (76 FR 28632, May 18, 2011). 

Boeing Alert Service Bulletin 737–53A1319, 

Revision 1, dated April 8, is not incorporated 

by reference in this AD. 

(o) 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 (p)(1) 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. 

(3) An AMOC that provides an acceptable 

level of safety may be used for any repair 

required by this AD if it is approved by the 

Boeing Commercial Airplanes Organization 

Designation Authorization (ODA) that has 

been authorized by the Manager, Seattle 

ACO, to make those findings. For a repair 

method to be approved, the repair must meet 

the certification basis of the airplane, and the 

approval must specifically refer to this AD. 

(4) AMOCs approved for AD 2011–08–51, 

Amendment 39–16701 (76 FR 28632, May 18, 

2011), are approved as AMOCs for the 

corresponding provisions of paragraphs (g) 

and (l) of this AD. 

(p) Related Information 

(1) For more information about this AD, 

contact Wayne Lockett, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, Seattle 

Aircraft Certification Office (ACO), 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

phone: 425–917–6447; fax: 425–917–6590; 

email: wayne.lockett@faa.gov. 

(2) For service information identified in 

this AD, contact Boeing Commercial 

Airplanes, Attention: Data & Services 

Management, P. O. Box 3707, MC 2H–65, 

Seattle, WA 98124–2207; telephone 206– 

544–5000, extension 1; fax 206–766–5680; 

Internet https://www.myboeingfleet.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. 

Issued in Renton, Washington, on 

November 5, 2014. 

Jeffrey E. Duven, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2014–27070 Filed 11–14–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0773; Directorate 

Identifier 2014–NM–068–AD] 

RIN 2120–AA64 

Airworthiness Directives; the Boeing 

Company Airplanes 

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 787–8 

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Federal Register / Vol. 79, No. 221 / Monday, November 17, 2014 / Proposed Rules 68385 

airplanes. This proposed AD was 

prompted by reports of a potential latent 

failure of the valve actuator circuitry, 

which was not identified during 

actuator development. This proposed 

AD would require replacing certain 

engine and auxiliary power unit (APU) 

fuel shutoff valve actuators with new 

actuators, and would also require 

revising the maintenance or inspection 

program to include a new airworthiness 

limitation into the Airworthiness 

Limitations Section (ALS) of the 

Instructions for Continued 

Airworthiness (ICA). We are proposing 

this AD to prevent latent failures of the 

fuel shutoff valve actuators, which 

could result in the inability to shut off 

fuel to the engine or APU in the case of 

an engine or APU fire. If the fuel cannot 

be shut off to a fire, the engine or APU 

fire could be uncontrollable, which 

could lead to structural failure. 

DATES: We must receive comments on 

this proposed AD by January 2, 2015. 

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. 

For service information identified in 

this proposed AD, contact Boeing 

Commercial Airplanes, Attention: Data 

& Services Management, P.O. Box 3707, 

MC 2H–65, Seattle, WA 98124–2207; 

telephone 206–544–5000, extension 1; 

fax 206–766–5680; Internet https://

www.myboeingfleet.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– 

0773; 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– 

2014–0773; Directorate Identifier 2014– 

NM–068–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 received reports on Model 787 

airplanes of a potential latent failure of 

the valve actuator circuitry, which was 

not identified during actuator 

development. The fuel shutoff valve 

actuator circuit design provides 

common input power through microswitches to both the motor and position 

indications. The latent failure condition 

has the potential for a stuck microswitch, which could lead to a 

disagreement between the valve 

command and position indication. If a 

command is sent to change the valve 

position and one of the internal microswitches is stuck in the depressed state, 

power would immediately provide 

indication that the valve transitioned to 

its commanded state, when the motor 

actually never received power to rotate. 

This condition, if not corrected, could 

result in the inability to shut off fuel to 

the engine or APU in the case of an 

engine or APU fire. If the fuel cannot be 

shut off to a fire, the engine or APU fire 

could be uncontrollable, which could 

lead to structural failure. 

Relevant Service Information 

We reviewed Boeing Service Bulletin 

B787–81205–SB280015–00, Issue 002, 

dated June 19, 2014. For information on 

the procedures and compliance times, 

see this service information at http://

www.regulations.gov by searching for 

Docket No. FAA–2014–0773. 

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 

airplanes with certain part number 

shutoff valves to revise the maintenance 

or inspection program to add 

airworthiness limitation number 28– 

AWL–ACT, ‘‘Engine and APU Shut-Off 

Valve Actuator Test.’’ This proposed AD 

would also require accomplishing the 

actions specified in the service 

information described previously, 

except as discussed under ‘‘Difference 

Between this Proposed AD and the 

Service Information.’’ 

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 (k) of this 

proposed AD. The request should 

include a description of changes to the 

required inspections that will ensure the 

continued operational safety of the 

airplane. 

Explanation of ‘‘RC’’ Steps in Service 

Information 

The FAA worked in conjunction with 

industry, under the Airworthiness 

Directives Implementation Aviation 

Rulemaking Committee, to enhance the 

AD system. One enhancement was a 

new process for annotating which steps 

in the service information are required 

for compliance with an AD. 

Differentiating these steps from other 

tasks in the service information is 

expected to improve an owner’s/

operator’s understanding of crucial AD 

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68386 Federal Register / Vol. 79, No. 221 / Monday, November 17, 2014 / Proposed Rules 

requirements and help provide 

consistent judgment in AD compliance. 

The actions specified in the service 

information described previously 

include steps that are labeled as RC 

(required for compliance) because these 

steps have a direct effect on detecting, 

preventing, resolving, or eliminating an 

identified unsafe condition. 

As noted in the specified service 

information, steps labeled as RC and all 

subordinate steps must be done to 

comply with the proposed AD. 

However, steps that are not labeled as 

RC are recommended. Those steps that 

are not labeled as RC may be deviated 

from, done as part of other actions, or 

done using accepted methods different 

from those identified in the service 

information without obtaining approval 

of an AMOC, provided the steps labeled 

as RC can be done and the airplane can 

be put back in a serviceable condition. 

Any substitutions or changes to steps 

labeled as RC will require approval of 

an alternative method of compliance. 

Differences Between This Proposed AD 

and the Service Information 

Although Boeing Service Bulletin 

B787–81205–SB280015–00, Issue 002, 

dated June 19, 2014, describes installing 

engine fuel shutoff valve and APU fuel 

shutoff valve actuators having part 

number (P/N) 53–0037, this proposed 

AD would prohibit installing valves 

having P/N 53–0037, and require 

installing certain other valves. We have 

coordinated this difference with Boeing. 

The applicability of this proposed AD 

includes all Model 787–8 airplanes, 

which differs from the effectivity of the 

service information referenced 

previously. The parts are rotable, 

therefore, this proposed AD includes all 

Model 787–8 airplanes. 

Costs of Compliance 

We estimate that this proposed AD 

affects 6 airplanes of U.S. registry. 

We estimate the following costs to 

comply with this proposed AD: 

ESTIMATED COSTS

Action Labor cost Parts cost Cost per 

product 

Cost on U.S. 

operators 

Maintenance program revision ....................... 1 work-hour × $85 per hour = $85 ................. $0 $85 $510 

Engine and APU fuel shutoff valve actuator 

replacement.

10 work-hours × $85 per hour = $850 ........... 0 850 5,100 

According to the manufacturer, some 

of the costs of this proposed AD may be 

covered under warranty, thereby 

reducing the cost impact on affected 

individuals. We do not control warranty 

coverage for affected individuals. As a 

result, we have included all costs in our 

cost estimate. 

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 

■ 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. Amend § 39.13 by adding the 

following new airworthiness directive 

(AD): 

The Boeing Company: Docket No. FAA– 

2014–0773; Directorate Identifier 2014– 

NM–068–AD. 

(a) Comments Due Date 

We must receive comments by January 2, 

2015. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to all The Boeing 

Company Model 787–8 airplanes, certificated 

in any category. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 28, Fuel. 

(e) Unsafe Condition 

This AD was prompted by a report of an 

error in the valve actuator design. We are 

issuing this AD to prevent latent failures of 

the fuel shutoff valve actuators, which could 

result in the inability to shut off fuel to the 

engine or APU in the case of an engine or 

APU fire. If the fuel cannot be shut off to a 

fire the engine or APU fire could be 

uncontrollable which could lead to structural 

failure. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Maintenance or Inspection Program 

Revision 

Within 30 days after the effective date of 

this AD, revise the maintenance or inspection 

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Federal Register / Vol. 79, No. 221 / Monday, November 17, 2014 / Proposed Rules 68387 

program, as applicable, to add airworthiness 

limitation number 28–AWL–ACT, 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. 

This may be accomplished by inserting a 

copy of airworthiness limitation number 28– 

AWL–ACT into the maintenance or 

inspection program, as applicable. For the 

airplanes identified in the applicability note 

of airworthiness limitation number 28–AWL– 

ACT, the initial compliance time for 

accomplishing the actions specified in figure 

1 to paragraph (g) of this AD is within 10 

days after accomplishment of the 

maintenance or inspection program revision 

required by this paragraph. When the engine 

and APU fuel shutoff valve actuators have 

been replaced as required by paragraph (i) of 

this AD, the airworthiness limitation number 

28–AWL–ACT required by this paragraph 

may be removed from the maintenance or 

inspection program, as applicable. 

FIGURE 1 TO PARAGRAPH (g) OF THIS AD: ENGINE AND APU SHUT-OFF VALVE ACTUATOR TEST

AWL No. Task Interval Applicability Description 

28–AWL–ACT ......... ALI ........................... 10 Days NOTE ........ ALL NOTE ............... Engine and APU Shut-Off Valve Actuator Test. 

Concern: The fuel shutoff valve actuator design can 

result in airplanes operating with a failed fuel 

shutoff actuator that is not reported. A latently 

failed fuel shutoff actuator would 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 the following tests in accordance with Boeing Service Bulletin B787–81205–SB280015–00, 

Issue 002, dated June 19, 2014. 

1. Do PART 1: ENGINE FUEL SHUTOFF VALVE 

ACTUATOR TEST as described in Boeing Service Bulletin B787–81205–SB280015–00, Issue 

002, dated June 19, 2014. 

a. If the left engine fuel shutoff valve actuator has 

Part Number 53–0037, perform the left engine 

fuel shutoff valve actuator test. 

b. If the right engine fuel shutoff valve actuator 

has Part Number 53–0037, perform the right 

engine fuel shutoff valve actuator test. 

c. If either test fails, repair faults as required 

(refer to Boeing Airplane Maintenance Manual 

28–22–02). 

2. Do PART 2: APU FUEL SHUTOFF VALVE ACTUATOR TEST as described in Boeing Service 

Bulletin B787–81205–SB280015–00, Issue 002, 

dated June 19, 2014. 

a. If the APU fuel shutoff valve actuator has part 

number 53–0037, perform the APU fuel shutoff 

valve actuator test. 

b. If the test fails, before further flight requiring 

APU availability, repair If the test fails, before 

further flight requiring APU availability, repair 

faults as required (refer to Boeing Airplane 

Maintenance Manual 28–25–03). 

NOTE: Dispatch may be permitted per MMEL 28– 

25–03 if APU is not required for flight. 

INTERVAL NOTE: Not required on days when the 

airplane is not used in revenue service. Must be 

done before further flight if it has been 10 or 

more calendar days since last inspection 

APPLICABILITY NOTE: This AWL applies to airplanes with Eaton Aerospace Ltd fuel shutoff 

valve actuators having Part Number 53–0037 installed at the engine or APU spar shutoff location. 

(h) No Alternative Actions and Intervals 

Except as specified in paragraph (i) of this 

AD: 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 (k) of this AD. 

(i) Replacement 

Within 36 months after the effective date 

of this AD, replace the engine and APU fuel 

shutoff valve actuators having part number 

(P/N) 53–0037 with P/N 53–0049, in 

accordance with Part 5 or Part 6 of the 

Accomplishment Instructions of Boeing 

Service Bulletin B787–81205–SB280015–00, 

Issue 002, dated June 19, 2014, as applicable. 

When all the engine and APU fuel shutoff 

valve actuators have been replaced as 

required by this paragraph, the airworthiness 

limitation number 28–AWL–ACT required by 

paragraph (g) of this AD may be removed 

from the maintenance or inspection program, 

as applicable. 

(j) Parts Installation Prohibition 

As of the effective date of this AD, no 

person may install a motor operated valve 

actuator having P/N 53–0037 on any airplane 

in the following locations: Engine fuel 

shutoff valve, APU fuel shutoff valve, 

crossfeed valve, and defuel/isolation valve. 

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68388 Federal Register / Vol. 79, No. 221 / Monday, November 17, 2014 / Proposed Rules 

(k) 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 (l)(1) 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. 

(3) If the service information contains steps 

that are labeled as RC (Required for 

Compliance), those steps and all subordinate 

steps must be done to comply with this AD; 

any steps that are not labeled as RC are 

recommended. Those steps that are not 

labeled as RC may be deviated from, done as 

part of other actions, or done using accepted 

methods different from those identified in 

the specified service information without 

obtaining approval of an AMOC, provided 

the steps labeled as RC can be done and the 

airplane can be put back in a serviceable 

condition. Any substitutions or changes to 

steps labeled as RC require approval of an 

AMOC. 

(l) Related Information 

(1) 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. 

(2) For service information identified in 

this AD, contact Boeing Commercial 

Airplanes, Attention: Data & Services 

Management, P.O. Box 3707, MC 2H–65, 

Seattle, WA 98124–2207; telephone 206– 

544–5000, extension 1; fax 206–766–5680; 

Internet https://www.myboeingfleet.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. 

Issued in Renton, Washington, on 

November 5, 2014. 

Jeffrey E. Duven, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2014–27069 Filed 11–14–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0774; Directorate 

Identifier 2013–NM–154–AD] 

RIN 2120–AA64 

Airworthiness Directives; the Boeing 

Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to supersede 

Airworthiness Directive (AD) 2006–22– 

15, which applies to all Boeing Model 

747–100, 747–100B, 747–100B SUD, 

747–200B, 747–200C, 747–200F, 747– 

300, 747–400, 747–400D, 747–400F, 

747SR, and 747SP series airplanes. AD 

2006–22–15 currently requires 

repetitive inspections for cracking of 

certain panel webs and stiffeners of the 

nose wheel well (NWW), and corrective 

actions if necessary. AD 2006–22–15 

also requires replacing certain panels 

with new panels, which terminates the 

repetitive inspections. Since we issued 

AD 2006–22–15, we received reports of 

fatigue cracking in the panel webs and 

stiffeners of the NWW prior to the 

inspection threshold of AD 2006–22–15. 

This proposed AD would reduce a 

compliance time and add certain 

inspections and repair if necessary. We 

are proposing this AD to prevent fatigue 

cracking of the NWW side and top 

panels, which could result in a NWW 

depressurization event severe enough to 

reduce the structural integrity of the 

fuselage. 

DATES: We must receive comments on 

this proposed AD by January 2, 2015. 

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. 

For service information identified in 

this proposed AD, contact Boeing 

Commercial Airplanes, Attention: Data 

& Services Management, P.O. Box 3707, 

MC 2H–65, Seattle, WA 98124–2207; 

telephone 206–544–5000, extension 1; 

fax 206–766–5680; Internet https://

www.myboeingfleet.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– 

0774; 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: Bill 

Ashforth, Aerospace Engineer, Airframe 

Branch, ANM–120S, FAA, Seattle 

Aircraft Certification Office (ACO), 1601 

Lind Avenue SW., Renton, WA 98057– 

3356; phone: 425–917–6432; fax: 425– 

917–6590; email: Bill.Ashforth@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 

this proposed AD. Send your comments 

to an address listed under the 

ADDRESSES section. Include ‘‘Docket No. 

FAA–2014–0774; Directorate Identifier 

2013–NM–154–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 

On October 25, 2006, we issued AD 

2006–22–15, Amendment 39–14812 (71 

FR 64884, November 6, 2006), for all 

Boeing Model 747–100, 747–100B, 747– 

100B SUD, 747–200B, 747–200C, 747– 

200F, 747–300, 747–400, 747–400D, 

747–400F, 747SR, and 747SP series 

mstockstill on DSK4VPTVN1PROD with PROPOSALS