Federal Register / Vol. 75, No. 250 / Thursday, December 30, 2010 / Proposed Rules 82337 

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); and 

3. 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. 

We prepared a regulatory evaluation 

of the estimated costs to comply with 

this proposed AD and placed it in the 

AD docket. 

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: 

APEX Aircraft: Docket No. FAA–2010–1296; 

Directorate Identifier 2010–CE–063–AD. 

Comments Due Date 

(a) We must receive comments by February 

14, 2011. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to APEX Aircraft 

Model CAP 10 airplanes, all serial numbers, 

certificated in any category. 

Subject 

(d) Air Transport Association of America 

(ATA) Code 27: Flight Controls. 

Reason 

(e) The mandatory continuing 

airworthiness information (MCAI) states: 

A fatal accident occurred to a CAP 10C, in 

which the pilot lost control of the aeroplane. 

The following investigation has revealed 

that the probable cause of the accident was 

the improper locking of a turnbuckle (locking 

clip missing) of the flight control cables, and 

the subsequent inadvertent release of the 

pitchup control cable from the turnbuckle. 

For the above described reasons, this AD 

requires repetitive inspections to verify the 

correct installation of the turnbuckles of the 

flight control cables and, if foreseen by the 

applicable design configuration of the 

turnbuckles and found to be missing, to 

restore the locking clip and the safety wire. 

Actions and Compliance 

(f) Unless already done, do the following 

actions: 

(1) Within the next 2 months after the 

effective date of this AD: 

(i) If the turnbuckles are designed to be 

locked with locking clips and safety wire, 

verify that the locking clips are properly 

installed in the corresponding groove, that 

the safety wire of a minimum diameter of 0.8 

millimeter (mm) is correctly installed, and 

that there is no damage to the whole 

turnbuckle installation. 

(ii) For all other designs of turnbuckles, 

verify the correct installation of the safety 

locking devices. 

(iii) If any discrepancy is found during the 

inspection required by paragraph (f)(1)(i) or 

(f)(1)(ii) of this AD, before further flight, 

restore the correct turnbuckle installation in 

accordance with standard maintenance 

practice. 

(2) Repeat the inspection required by 

paragraph (f)(1)(i) or (f)(1)(ii) of this AD, as 

applicable to the turnbuckles design, and the 

associated corrective actions required by 

paragraph (f)(1)(iii) of this AD at intervals not 

to exceed 110 hours time-in-service or 13 

months since the last inspection, whichever 

occurs first. 

FAA AD Differences 

Note: This AD differs from the MCAI and/ 

or service information as follows: No 

differences. 

Other FAA AD Provisions 

(g) 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: Sarjapur Nagarajan, Aerospace 

Engineer, FAA, Small Airplane Directorate, 

901 Locust, Room 301, Kansas City, Missouri 

64106; telephone: (816) 329–4145; fax: (816) 

329–4090. 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 FAAapproved 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. 

(3) Reporting Requirements: For any 

reporting requirement in this AD, a federal 

agency may not conduct or sponsor, and a 

person is not required to respond to, nor 

shall a person be subject to a penalty for 

failure to comply with a collection of 

information subject to the requirements of 

the Paperwork Reduction Act unless that 

collection of information displays a current 

valid OMB Control Number. The OMB 

Control Number for this information 

collection is 2120–0056. Public reporting for 

this collection of information is estimated to 

be approximately 5 minutes per response, 

including the time for reviewing instructions, 

completing and reviewing the collection of 

information. All responses to this collection 

of information are mandatory. Comments 

concerning the accuracy of this burden and 

suggestions for reducing the burden should 

be directed to the FAA at: 800 Independence 

Ave., SW., Washington, DC 20591, Attn: 

Information Collection Clearance Officer, 

AES–200. 

Related Information 

(h) Refer to MCAI European Aviation 

Safety Agency (EASA) AD No.: 2010–0233, 

dated November 26, 2010, for related 

information. For service information related 

to this AD, contact Apex Aircraft, Bureau de 

Navigabilite ́, 1 route de Troyes, 21121 

DAROIS–France, telephone: (33) 380 35 65 

10; fax: (33) 380 35 65 15; email: apexaircraft.com. 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 

December 22, 2010. 

Earl Lawrence, 

Manager, Small Airplane Directorate, Aircraft 

Certification Service. 

[FR Doc. 2010–32966 Filed 12–29–10; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–1271; Directorate 

Identifier 2010–NM–187–AD] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Model 777–200, –300, and 

–300ER Series 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 

products listed above. This proposed 

AD would require installing an auto 

shutoff feature for the center override/ 

jettison fuel pumps, and installing 

power control circuitry for the center 


srobinson on DSKHWCL6B1PROD with PROPOSALS
82338 Federal Register / Vol. 75, No. 250 / Thursday, December 30, 2010 / Proposed Rules 

override/jettison and main jettison fuel 

pumps. This proposed AD would also 

require installing new software in the 

electrical load management system 

(ELMS) electronics units in certain 

power management panels; installing 

airplane information management 

system 2 (AIMS–2) software in the 

AIMS–2 hardware; and making certain 

wiring changes. This proposed AD was 

prompted by results from fuel system 

reviews conducted by the manufacturer. 

We are proposing this AD to prevent the 

potential of ignition sources inside fuel 

tanks, which, in combination with 

flammable fuel vapors, could result in a 

fuel tank explosion and consequent loss 

of the airplane. 

DATES: We must receive comments on 

this proposed AD by February 14, 2011. 

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: Deliver to Mail 

address above between 9 a.m. and 

5 p.m., Monday through Friday, except 

Federal holidays. 

For Boeing service information 

identified in this proposed AD, contact 

Boeing Commercial Airplanes, 

Attention: Data & Services Management, 

P.O. Box 3707, MC 2H–65, Seattle, 

Washington 98124–2207; telephone 

206–544–5000, extension 1; fax 206– 

766–5680; e-mail 

me.boecom@boeing.com; Internet 

https://www.myboeingfleet.com. For GE 

Aviation service information identified 

in this proposed AD, contact GE 

Aviation, Customer Services— 

Clearwater, P.O. Box 9013, Clearwater, 

Florida 33758; telephone 727–539– 

1631; fax 727–539–0680; e-mail 

cs.support@ge.com. You may review 

copies of the referenced service 

information at the FAA, Transport 

Airplane Directorate, 1601 Lind 

Avenue, SW., Renton, Washington. 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: 

Georgios Roussos, Aerospace Engineer, 

Systems and Equipment Branch, ANM– 

130S, FAA, Seattle Aircraft Certification 

Office, 1601 Lind Avenue, SW., Renton, 

Washington 98057–3356; telephone 

(425) 917–6482; fax (425) 917–6590; 

e-mail: Georgios.Roussos@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– 

2010–1271; Directorate Identifier 2010– 

NM–187–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 

The FAA has examined the 

underlying safety issues involved in fuel 

tank explosions on several large 

transport airplanes, including the 

adequacy of existing regulations, the 

service history of airplanes subject to 

those regulations, and existing 

maintenance practices for fuel tank 

systems. As a result of those findings, 

we issued a regulation titled ‘‘Transport 

Airplane Fuel Tank System Design 

Review, Flammability Reduction and 

Maintenance and Inspection 

Requirements’’ (66 FR 23086, May 7, 

2001). In addition to new airworthiness 

standards for transport airplanes and 

new maintenance requirements, this 

rule included Special Federal Aviation 

Regulation No. 88 (‘‘SFAR 88,’’ 

Amendment 21–78, and subsequent 

Amendments 21–82 and 21–83). 

Among other actions, SFAR 88 

requires certain type design (i.e., type 

certificate (TC) and supplemental type 

certificate (STC)) holders to substantiate 

that their fuel tank systems can prevent 

ignition sources in the fuel tanks. This 

requirement applies to type design 

holders for large turbine-powered 

transport airplanes and for subsequent 

modifications to those airplanes. It 

requires them to perform design reviews 

and to develop design changes and 

maintenance procedures if their designs 

do not meet the new fuel tank safety 

standards. As explained in the preamble 

to the rule, we intended to adopt 

airworthiness directives to mandate any 

changes found necessary to address 

unsafe conditions identified as a result 

of these reviews. 

In evaluating these design reviews, we 

have established four criteria intended 

to define the unsafe conditions 

associated with fuel tank systems that 

require corrective actions. The 

percentage of operating time during 

which fuel tanks are exposed to 

flammable conditions is one of these 

criteria. The other three criteria address 

the failure types under evaluation: 

Single failures, single failures in 

combination with a latent condition(s), 

and in-service failure experience. For all 

four criteria, the evaluations included 

consideration of previous actions taken 

that may mitigate the need for further 

action. 

We have determined that the actions 

identified in this AD are necessary to 

reduce the potential of ignition sources 

inside fuel tanks, which, in combination 

with flammable fuel vapors, could result 

in a fuel tank explosion and consequent 

loss of the airplane. 

Results of a safety assessment 

revealed that there is a small risk of an 

ignition source in a fuel tank if a center 

override/jettison fuel pump or a main 

jettison fuel pump continues to run 

when there is no fuel at the pump inlet, 

or when the pumps are commanded to 

stop running (commanded off) and they 

remain on. When a pump runs after the 

fuel level goes below the pump inlet, 

there is a small risk that the pump can 

cause an ignition source in the fuel tank 

from an overheat condition, electrical 

arcs, or frictional sparks. This condition, 

if not corrected, could result in a fuel 

tank explosion and consequent loss of 

the airplane. 

Relevant Service Information 

We reviewed Boeing Service Bulletin 

777–28A0047, Revision 5, dated 

September 20, 2010. That service 

information describes procedures for 

installing a new P301 panel on the left 

side of the airplane, installing a new 

P302 panel on the right side of the 

airplane, and changing the wiring; and 

performing certain bonding resistance 

measurements and reworking the 

airplane installation to verify that 


srobinson on DSKHWCL6B1PROD with PROPOSALS
Federal Register / Vol. 75, No. 250 / Thursday, December 30, 2010 / Proposed Rules 82339 

certain bonding requirements are met if 

necessary. 

Boeing Service Bulletin 777– 

28A0047, Revision 5, dated September 

20, 2010, specifies prior or concurrent 

accomplishment of the following service 

bulletins: 

• Boeing Service Bulletin 777– 

28A0040, Revision 1, dated March 18, 

2010, which describes procedures for 

installing new software in the ELMS 

electronics units in the P110, P210, and 

P310 power management panels. 

• Boeing Special Attention Service 

Bulletin 777–31–0097, Revision 3, dated 

February 22, 2007, which describes 

procedures for installing AIMS–2 

software in the AIMS–2 hardware. 

• GE Aviation Service Bulletin 

5000ELM–28–456, Revision 1, dated 

January 7, 2010, which describes 

procedures for changing the wiring of 

the ELMS P110 left power management 

panel. 

• GE Aviation Service Bulletin 

6000ELM–28–457, Revision 1, dated 

January 7, 2010, which describes 

procedures for changing the wiring of 

the ELMS P210 right power 

management panel. 

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 

accomplishing the actions specified in 

the service information described 

previously, except as discussed under 

‘‘Differences Between the Proposed AD 

and the Service Information.’’ 

Differences Between the Proposed AD 

and the Service Information 

Boeing Special Attention Service 

Bulletin 777–31–0097, Revision 3, dated 

February 22, 2007, specifies a 

compliance time of 60 months. This AD 

requires a 36-month compliance time to 

install the AIMS–2 software upgrade. 

This difference has been coordinated 

with the manufacturer. 

Costs of Compliance 

We estimate that this proposed AD 

will affect 2 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 

Installation: Groups 1 and 2, Configuration 2 149 work-hours × $85 per hour = $12,665 .... $15,719 $28,384 .......... $56,768. 

Installation: Groups 1 and 2, Configuration 1 2 work-hours × $85 per hour = $170 ............. 15,719 $15,889 .......... $31,778. 

Concurrent requirement: Install ELMS software.3 work-hours × $85 per hour = $255 ............. 0 $255 ............... $510. 

Concurrent requirement: Upgrade AIMS2 

software.

Up to 2 work-hours × $85 per hour = Up to 

$170.

0 Up to $170 ..... Up to $340. 

Concurrent requirement: P110 wiring 

changes.

3 work-hours × $85 per hour = $255 ............. 1,164 $1,419 ............ $2,838. 

Concurrent requirement: P210 wiring 

changes.

3 work-hours × $85 per hour = $255 ............. 1,164 $1,419 ............ $2,838. 

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. The FAA amends § 39.13 by adding 

the following new airworthiness 

directive (AD): 

The Boeing Company: Docket No. FAA– 

2010–1271; Directorate Identifier 2010– 

NM–187–AD. 

Comments Due Date 

(a) We must receive comments by February 

14, 2011. 

Affected ADs 

(b) None. 

Applicability 

(c) The Boeing Company Model 777–200, 

–300, and –300ER series airplanes; 

certificated in any category; as identified in 

Boeing Service Bulletin 777–28A0047, 

Revision 5, dated September 20, 2010. 

Subject 

(d) Joint Aircraft System Component 

(JASC)/Air Transport Association (ATA) of 

America Code 28, Fuel. 


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82340 Federal Register / Vol. 75, No. 250 / Thursday, December 30, 2010 / Proposed Rules 

Unsafe Condition 

(e) This AD was prompted by results from 

fuel system reviews conducted by the 

manufacturer. We are issuing this AD to 

prevent the potential of ignition sources 

inside fuel tanks, which, in combination with 

flammable fuel vapors, could result in a fuel 

tank explosion and consequent loss of the 

airplane. 

Compliance 

(f) Comply with this AD within the 

compliance times specified, unless already 

done. 

Installation 

(g) For airplanes in Groups 1 and 2, 

Configuration 2, as identified in Boeing 

Service Bulletin 777–28A0047, Revision 5, 

dated September 20, 2010: Within 36 months 

after the effective date of this AD, install a 

new P301 panel on the left side of the 

airplane, install a new P302 panel on the 

right side of the airplane, and change the 

wiring, in accordance with the 

Accomplishment Instructions of Boeing 

Service Bulletin 777–28A0047, Revision 5, 

dated September 20, 2010. 

(h) For airplanes in Groups 1 and 2, 

Configuration 1, as identified in Boeing 

Service Bulletin 777–28A0047, Revision 5, 

dated September 20, 2010: Within 36 months 

after the effective date of this AD, perform 

bonding resistance measurements and rework 

the airplane installation if necessary, 

depending on airplane configuration, in 

accordance with the Accomplishment 

Instructions of Boeing Service Bulletin 777– 

28A0047, Revision 5, dated September 20, 

2010. 

Concurrent Requirements 

(i) Prior to or concurrently with 

accomplishing the requirements of paragraph 

(g) of this AD, do the actions in paragraphs 

(i)(1), (i)(2), (i)(3), and (i)(4) of this AD. 

(1) Install new software in the electrical 

load management system (ELMS) electronics 

units in the P110, P210, and P310 power 

management panels, in accordance with the 

Accomplishment Instructions of Boeing 

Service Bulletin 777–28A0040, Revision 1, 

dated March 18, 2010. 

(2) Install airplane information 

management system 2 (AIMS–2) software in 

the AIMS–2 hardware, in accordance with 

the Accomplishment Instructions of Boeing 

Special Attention Service Bulletin 777–31– 

0097, Revision 3, dated February 22, 2007. 

(3) Modify the P110 left power 

management panel by incorporating wiring 

changes, in accordance with the 

Accomplishment Instructions of GE Aviation 

Service Bulletin 5000ELM–28–456, Revision 

1, dated January 7, 2010. 

(4) Modify the P210 right power 

management panel by incorporating wiring 

changes, in accordance with the 

Accomplishment Instructions of GE Aviation 

Service Bulletin 6000ELM–28–457, Revision 

1, dated January 7, 2010. 

Credit for Actions Accomplished in 

Accordance With Previous Service 

Information 

(j) Installations done before the effective 

date of this AD in accordance with Boeing 

Alert Service Bulletin 777–28A0040, dated 

April 13, 2007, are acceptable for compliance 

with the requirements of paragraph (i)(1) of 

this AD. 

(k) Installations done before the effective 

date of this AD in accordance with Boeing 

Service Bulletin 777–28A0047, Revision 3, 

dated June 11, 2009; or Revision 4, dated 

May 20, 2010; are acceptable for compliance 

with the requirements of paragraphs (g) and 

(h) of this AD. 

(l) Installations done before the effective 

date of this AD in accordance with Boeing 

Special Attention Service Bulletin 777–31– 

0097, dated March 30, 2006; Revision 1, 

dated August 10, 2006; or Revision 2, dated 

October 26, 2006; are acceptable for 

compliance with the requirements of 

paragraph (i)(2) of this AD. 

Paperwork Reduction Act Burden Statement 

(m) A Federal agency may not conduct or 

sponsor, and a person is not required to 

respond to, nor shall a person be subject to 

a penalty for failure to comply with a 

collection of information subject to the 

requirements of the Paperwork Reduction 

Act unless that collection of information 

displays a current valid OMB Control 

Number. The OMB Control Number for this 

information collection is 2120–0056. Public 

reporting for this collection of information is 

estimated to be approximately 5 minutes per 

response, including the time for reviewing 

instructions, completing and reviewing the 

collection of information. All responses to 

this collection of information are mandatory. 

Comments concerning the accuracy of this 

burden and suggestions for reducing the 

burden should be directed to the FAA at: 800 

Independence Ave., SW, Washington, DC 

20591, Attn: Information Collection 

Clearance Officer, AES–200. 

Alternative Methods of Compliance 

(AMOCs) 

(n)(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 the 

Related Information section of this AD. 

Information may be e-mailed to: 9-ANMSeattle-ACO-AMOC-Requests@faa.gov. 

(2) Before using any approved AMOC, 

notify your Principal Maintenance Inspector 

or Principal Avionics Inspector, as 

appropriate, or lacking a principal inspector, 

your local Flight Standards District Office. 

Related Information 

(o) For more information about this AD, 

contact Georgios Roussos, Aerospace 

Engineer, Systems and Equipment Branch, 

ANM–130S, FAA, Seattle Aircraft 

Certification Office, 1601 Lind Avenue, SW., 

Renton, Washington 98057–3356; telephone 

(425) 917–6482; fax (425) 917–6590; e-mail: 

Georgios.Roussos@faa.gov. 

(p) For Boeing service information 

identified in this AD, contact Boeing 

Commercial Airplanes, Attention: Data & 

Services Management, P.O. Box 3707, MC 

2H–65, Seattle, Washington 98124–2207; 

telephone 206–544–5000, extension 1; fax 

206–766–5680; e-mail 

me.boecom@boeing.com; Internet https:// 

www.myboeingfleet.com. For GE Aviation 

service information identified in this AD, 

contact GE Aviation, Customer Services— 

Clearwater, P.O. Box 9013, Clearwater, 

Florida 33758; telephone 727–539–1631; fax 

727–539–0680; e-mail cs.support@ge.com. 

You may review copies of the referenced 

service information at the FAA, Transport 

Airplane Directorate, the FAA, 1601 Lind 

Avenue, SW., Renton, Washington. For 

information on the availability of this 

material at the FAA, call 425–227–1221. 

Issued in Renton, Washington, on 

December 17, 2010. 

Ali Bahrami, 

Manager,Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2010–33000 Filed 12–29–10; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF COMMERCE 

Foreign-Trade Zones Board 

15 CFR Part 400 

[Docket No. 090210156–0416–01] 

RIN 0625–AA81 

Foreign-Trade Zones in the United 

States 

AGENCY: Foreign-Trade Zones Board, 

International Trade Administration, 

Commerce. 

ACTION: Proposed rule; request for 

comments. 

SUMMARY: The Foreign-Trade Zones 

Board (the Board) proposes to amend its 

regulations, and invites public comment 

on these proposed amendments. 

Through this action, the Board proposes 

to amend the substantive and 

procedural rules for the authorization of 

Foreign-Trade Zones (FTZs or zones) 

and the regulation of zone activity. The 

purpose of zones as stated in the 

Foreign-Trade Zones Act (FTZ Act or 

the Act) is to ‘‘expedite and encourage 

foreign commerce, and other purposes.’’ 

The regulations proposed here provide 

the legal framework for accomplishing 

this purpose in the context of evolving 

U.S. economic and trade policy, and 

economic factors relating to 

international competition. The changes 

are comprehensive and the proposed 

action constitutes a major revision. 

These revisions encompass changes 

related to manufacturing and valueadded activity, as well as new rules 

designed to address compliance with 

the Act’s requirement for a grantee to 


srobinson on DSKHWCL6B1PROD with PROPOSALS