Federal Register / Vol. 79, No. 41 / Monday, March 3, 2014 / Proposed Rules 11725 

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 AD: 

Alpha Aviation Concept Limited: Docket No. 

FAA–2014–0130; Directorate Identifier 

2014–CE–005–AD. 

(a) Comments Due Date 

We must receive comments by April 17, 

2014. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Alpha Aviation 

Concept Limited Model R2160 airplanes, 

serial numbers 001 through 378, certificated 

in any category. 

(d) Subject 

Air Transport Association of America 

(ATA) Code 74: Ignition. 

(e) Reason 

This AD was prompted by mandatory 

continuing airworthiness information (MCAI) 

originated by an aviation authority of another 

country to identify and correct an unsafe 

condition on an aviation product. The MCAI 

describes the unsafe condition as the metal 

screen shield over the ignition switch may 

ground out the ignition terminals. We are 

issuing this AD to prevent the ignition switch 

metal screen from grounding out the ignition 

switch terminals, which could cause the 

engine to shut down. 

(f) Actions and Compliance 

Unless already done, do the actions in 

paragraphs (f)(1) through (f)(3) of this AD: 

(1) Within the next 50 hours time-inservice after the effective date of this AD or 

within the next 3 months after the effective 

date of this AD, whichever occurs first, 

inspect the airplane ignition switch for the 

presence of a metal screen shield. Do the 

inspection following the Accomplishment 

Instructions in Alpha Aviation Service 

Bulletin AA–SB–24–002, Revision 0, dated 

January 2014. 

(2) If a metal screen is found during the 

inspection required in paragraph (f)(1) of this 

AD, before further flight, modify or replace 

the ignition switch following the 

Accomplishment Instructions in Alpha 

Aviation Service Bulletin AA–SB–24–002, 

Revision 0, dated January 2014. 

(3) As of the effective date of this AD, do 

not install an ignition switch with a metal 

screen shield. 

(g) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, Standards Office, 

FAA, has the authority to approve AMOCs 

for this AD, if requested using the procedures 

found in 14 CFR 39.19. Send information to 

ATTN: Karl Schletzbaum, Aerospace 

Engineer, FAA, Small Airplane Directorate, 

901 Locust, Room 301, Kansas City, Missouri 

64106; telephone: (816) 329–4123; fax: (816) 

329–4090; email: karl.schletzbaum@faa.gov. 

Before using any approved AMOC on any 

airplane to which the AMOC applies, notify 

your appropriate principal inspector (PI) in 

the FAA Flight Standards District Office 

(FSDO), or lacking a PI, your local FSDO. 

(2) Airworthy Product: For any requirement 

in this AD to obtain corrective actions from 

a manufacturer or other source, use these 

actions if they are FAA-approved. Corrective 

actions are considered FAA-approved if they 

are approved by the State of Design Authority 

(or their delegated agent). You are required 

to assure the product is airworthy before it 

is returned to service. 

(h) Related Information 

Refer to MCAI Civil Aviation Authority 

(CAA) AD DCA/R2000/42, dated January 29, 

2014, for related information. You may 

examine the MCAI on the Internet at http:// 

www.regulations.gov by searching for and 

locating Docket No. FAA–2014–0130. For 

service information related to this AD, 

contact Alpha Aviation, 59 Hautapu Road, 

RD 1, Cambridge 3493, New Zealand; 

telephone: +64 7 827 0528; fax: +64 7 929 

2878; Internet: www.alphaaviation.co.nz. 

You may review this 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 

February 21, 2014. 

Steven W. Thompson, 

Acting Manager, Small Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2014–04549 Filed 2–28–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0128; Directorate 

Identifier 2013–NM–133–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 The 

Boeing Company Model airplanes 

equipped with Rolls-Royce Trent 800 

series engines. This proposed AD was 

prompted by reports of in-flight 

separation of the aft plug from the 

forward plug, which are the two parts of 

the turbine exhaust plug assembly. This 

proposed AD would require installation 

of a serviceable turbine exhaust plug 

assembly (for certain airplanes), and a 

general visual inspection (for certain 

airplanes) to determine the diameter of 

the bolt used at the forward and aft plug 

interface, and applicable corrective 

actions. We are proposing this AD to 

prevent separation of the forward plug 

from the aft plug of the turbine exhaust 

plug assembly, which could result in 

parts departing the airplane and hitting 

the empennage or hitting a person on 

the ground, and destabilizing the 

airplane during a critical flight phase; 

parts remaining on a runway could 

cause damage to another airplane. 

DATES: We must receive comments on 

this proposed AD by April 17, 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 

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11726 Federal Register / Vol. 79, No. 41 / Monday, March 3, 2014 / Proposed Rules 

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; 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: 

Kevin Nguyen, Aerospace Engineer, 

Propulsion Branch, ANM–140S, Seattle 

Aircraft Certification Office (ACO) FAA, 

1601 Lind Avenue SW., Renton, WA 

98057–3356; phone: (425) 917–6501; 

fax: (425) 917–6590; email: 

kevin.nguyen@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– 

2014–0128; Directorate Identifier 2013– 

NM–133–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 of in-flight 

separation of the aft plug from the 

forward plug, which are the two parts of 

the turbine exhaust plug assembly. A 

subsequent investigation showed that 

some of the interface bolts were found 

loose or missing. The turbine exhaust 

plug assembly was sent for analysis and 

it was found that the remaining bolts 

had less than the necessary minimum 

run-on torque value. It was also found 

that the operator of the analyzed turbine 

exhaust plug assembly had 

disassembled it a minimum of three 

times during maintenance actions. 

Repeated assembly and disassembly 

causes the locking property of the nut 

on the nutplate to wear out and 

subsequently let the bolts become loose 

or removed in service. This condition, if 

not corrected, could result in parts 

departing the airplane and hitting the 

empennage or hitting a person on the 

ground, and destabilizing the airplane 

during a critical flight phase; parts 

remaining on a runway could cause 

damage to another airplane. 

Relevant Service Information 

We reviewed Boeing Special 

Attention Service Bulletin 777–78– 

0051, Revision 3, dated August 23, 

2012. For information on the procedures 

and compliance times, see this service 

information at http:// 

www.regulations.gov by searching for 

Docket No. FAA 2014–0128. 

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 these same 

type designs. 

Proposed AD Requirements 

This proposed AD would require 

installation of a serviceable turbine 

exhaust plug assembly (for certain 

airplanes), and a general visual 

inspection (for certain airplanes) to 

determine the diameter of the bolt used 

at the forward and aft plug interface, 

and applicable corrective actions. 

The phrase ‘‘corrective actions’’ is 

used in this proposed AD. ‘‘Corrective 

actions’’ are actions that correct or 

address any condition found. Corrective 

actions in an AD could include, for 

example, repairs. 

Differences Between the Proposed AD 

and the Service Information 

The applicability of the proposed AD 

and the effectivity of Boeing Special 

Attention Service Bulletin 777–78– 

0051, Revision 3, dated August 23, 

2012, both include Model 777 airplanes 

equipped with Rolls-Royce Trent 800 

series engines. Boeing Special Attention 

Service Bulletin 777–78–0051, Revision 

3, dated August 23, 2012, however, is 

further limited to airplanes with line 

numbers before line position 470. 

Because we have determined that these 

engines are interchangeable among the 

Model 777 airplane fleet, this proposed 

AD would apply to all line positions of 

Model 777 airplanes equipped with 

Rolls-Royce Trent 800 engines, and 

would prohibit installation of nonserviceable turbine exhaust plug 

assemblies on any affected airplane. 

Boeing Special Attention Service 

Bulletin 777–78–0051, Revision 3, dated 

August 23, 2012, does not specify a 

compliance time for accomplishing one 

of the corrective actions. In Table 2 of 

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

Special Attention Service Bulletin 777– 

78–0051, Revision 3, dated August 23, 

2012, the condition ‘‘Only 1⁄4 inch 

diameter bolts are found installed at all 

33 locations forward and aft plug 

interface’’ has a corrective action to 

‘‘reidentify the forward and aft plug’’ 

with a compliance time of ‘‘none.’’ 

However, in paragraph (g)(2) of this 

proposed AD, the compliance time is 

‘‘before further flight’’ for doing all 

applicable corrective actions, which 

includes reidentifying the forward and 

aft plug. 

Boeing Special Attention Service 

Bulletin 777–78–0051, Revision 3, dated 

August 23, 2012, specifies to contact the 

manufacturer for instructions on how to 

repair certain conditions, but this 

proposed AD would require repairing 

those conditions in one of the following 

ways: 

• In accordance with a method that 

we approve; or 

• Using data that meet the 

certification basis of the airplane, and 

that have been approved by the Boeing 

Commercial Airplanes Organization 

Designation Authorization (ODA) whom 

we have authorized to make those 

findings. 

Costs of Compliance 

We estimate that this proposed AD 

affects 35 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. 41 / Monday, March 3, 2014 / Proposed Rules 11727 

ESTIMATED COSTS

Action Labor cost Parts cost Cost per 

product 

Cost on U.S. 

operators 

Installation ............................... 5 work-hours × $85 per hour = $425 ..................................... $0 $425 $14,875 

General visual inspection ....... 2 work-hours × $85 per hour = $170 ..................................... 0 170 5,950 

We estimate the following costs to do 

any necessary replacements that would 

be required based on the results of the 

proposed inspection. We have no way of 

determining the number of aircraft that 

might need this replacement: 

ON-CONDITION COSTS

Action Labor cost Parts cost Cost per 

product 

Replacement (replacing the 3⁄16 inch bolts with 1⁄4

inch bolts).

5 work-hours × $85 per hour = $425 ........................... $0 $425 

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– 

2014–0128; Directorate Identifier 2013– 

NM–133–AD. 

(a) Comments Due Date 

We must receive comments by April 17, 

2014. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to The Boeing Company 

Model 777–200, –200LR, –300, –300ER, and 

777F series airplanes; certificated in any 

category; equipped with Rolls-Royce Trent 

800 series engines. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 78, Engine Exhaust. 

(e) Unsafe Condition 

This AD was prompted by reports of inflight separation of the aft plug from the 

forward plug, which are the two parts of the 

turbine exhaust plug assembly. We are 

issuing this AD to prevent separation of the 

forward plug from the aft plug of the turbine 

exhaust plug assembly, which could result in 

parts departing the airplane and hitting the 

empennage or hitting a person on the ground, 

and destabilizing the airplane during a 

critical flight phase; parts remaining on a 

runway could cause damage to another 

airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Installation and General Visual 

Inspection 

At the applicable time specified in 

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

Special Attention Service Bulletin 777–78– 

0051, Revision 3, dated August 23, 2012, 

except as provided by paragraph (i) of this 

AD, do the applicable actions specified in 

paragraphs (g)(1), (g)(2), and (g)(3) of this AD, 

in accordance with the Accomplishment 

Instructions of Boeing Special Attention 

Service Bulletin 777–78–0051, Revision 3, 

dated August 23, 2012. 

(1) For airplanes identified as Group 1, 

Configuration 1, in Boeing Special Attention 

Service Bulletin 777–78–0051, Revision 3, 

dated August 23, 2012: Install a serviceable 

turbine exhaust plug assembly. 

(2) For airplanes identified as Group 1, 

Configurations 2 and 3, in Boeing Special 

Attention Service Bulletin 777–78–0051, 

Revision 3, dated August 23, 2012: Do a 

general visual inspection to determine the 

diameter of the bolt used at the forward and 

aft plug interface, and before further flight, 

do all applicable corrective actions. 

(3) For airplanes listed in paragraph (c) of 

this AD that are not listed in the ‘‘Effectivity’’ 

section of Boeing Special Attention Service 

Bulletin 777–78–0051, Revision 3, dated 

August 23, 2012: Do a general visual 

inspection to determine if a serviceable 

turbine exhaust plug assembly is installed. If 

a serviceable turbine exhaust plug assembly 

is not installed, before further flight, install 

a serviceable turbine exhaust plug assembly. 

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11728 Federal Register / Vol. 79, No. 41 / Monday, March 3, 2014 / Proposed Rules 

(h) Definition of Serviceable Assembly 

For purposes of this AD, an acceptable 

serviceable turbine exhaust plug assembly 

must meet the conditions specified in 

paragraph (h)(1) or (h)(2) of this AD. 

(1) A new assembly with part number 

314W5520–22. 

(2) A serviceable assembly as defined in 

the Accomplishment Instructions of Boeing 

Special Attention Service Bulletin 777–78– 

0051, Revision 3, dated August 23, 2012; 

except, for any assembly on which the 

actions specified in Part 2 or Part 3 of the 

Accomplishment Instructions of Boeing 

Special Attention Service Bulletin 777–78– 

0051, Revision 3, dated August 23, 2012, are 

done, and Boeing Special Attention Service 

Bulletin 777–78–0051, Revision 3, dated 

August 23, 2012, specifies to contact Boeing 

for repair instructions, this AD requires 

repair before further flight using a method 

approved in accordance with the procedures 

specified in paragraph (k) of this AD. 

(i) Exception to Service Information 

Specifications 

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

Boeing Special Attention Service Bulletin 

777–78–0051, Revision 3, dated August 23, 

2012, specifies a compliance time ‘‘after the 

Revision 3 date of this service bulletin,’’ this 

AD requires compliance within the 

applicable time after the effective date of this 

AD. 

(j) Parts Installation Limitation 

As of the effective date of this AD, only a 

serviceable turbine exhaust plug assembly 

may be installed on any airplane. 

(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 (m) 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. 

(l) Related Information 

(1) For more information about this AD, 

contact Kevin Nguyen, Aerospace Engineer, 

Propulsion Branch, ANM–140S, Seattle 

Aircraft Certification Office (ACO) FAA, 1601 

Lind Avenue SW., Renton, Washington 

98057–3356; phone: (425) 917–6501; fax: 

(425) 917–6590; email: kevin.nguyen@

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 February 

24, 2014. 

Jeffrey E. Duven, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2014–04568 Filed 2–28–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0122; Directorate 

Identifier 2014–NM–002–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 certain 

The Boeing Company Model 737–600, 

–700, –700C, –800, and –900 series 

airplanes. This proposed AD was 

prompted by reports in which a single, 

undetected, erroneous radio altimeter 

output caused the autothrottle to enter 

landing flare retard mode prematurely 

on approach. This proposed AD would 

require removing certain autothrottle 

computers and installing a new or 

reworked autothrottle computer. We are 

proposing this AD to prevent a single, 

undetected, erroneous radio altimeter 

output from causing premature 

autothrottle landing flare retard and 

subsequent loss of automatic speed 

control, which could result in loss of 

control of the airplane. 

DATES: We must receive comments on 

this proposed AD by April 17, 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. 

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 98057. For information on 

the availability of this material at the 

FAA, call 425–227–2112. 

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– 

0122; 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: 

Marie Hogestad, Aerospace Engineer, 

Systems and Equipment Branch, ANM– 

130S, FAA, Seattle Aircraft Certification 

Office, 1601 Lind Avenue SW., Renton, 

WA 98057–3356; phone: 425–917–6418; 

fax: 425–917–6590; email: 

marie.hogestad@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– 

2014–0122; Directorate Identifier 2014– 

NM–002–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 

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