Federal Register / Vol. 76, No. 1 / Monday, January 3, 2011 / Proposed Rules 31 

are issuing this AD to prevent damage to the 

fuel pumps caused by electrical arcing that 

could introduce an ignition source in the fuel 

tank, 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. 

Replacement, Measurements and Test 

(g) For airplanes on which the actions 

specified in Boeing Alert Service Bulletin 

757–28A0078 or 757–28A0079, both dated 

July 16, 2008, have not been accomplished as 

of the effective date of this AD: Within 60 

months after the effective date of this AD, 

replace the power control relays for the fuel 

boost pumps and override pumps with new 

relays having a ground fault interrupt (GFI) 

feature; do applicable electrical bonding 

resistance measurements between the GFI 

relays and their installation panel to verify 

that applicable bonding requirements are 

met; and do an operational test to ensure 

correct operation, as specified in Boeing 

Service Bulletin 757–28A0078, Revision 1, 

dated August 24, 2010 (for Model 757–200, 

–200CB, and –200PF airplanes); or Boeing 

Service Bulletin 757–28A0079, Revision 1, 

dated August 24, 2010 (for Model 757–300 

airplanes). Do all actions in accordance with 

Part 1 of the Accomplishment Instructions of 

Boeing Service Bulletin 757–28A0078, 

Revision 1, dated August 24, 2010 (for Model 

757–200, –200CB, and –200PF airplanes); or 

Boeing Service Bulletin 757–28A0079, 

Revision 1, dated August 24, 2010 (for Model 

757–300 airplanes); except as required by 

paragraph (i) of this AD. 

Inspection 

(h) For airplanes on which the actions 

specified in Boeing Alert Service Bulletin 

757–28A0078 or 757–28A0079, both dated 

July 16, 2008, have been accomplished before 

the effective date of this AD: Within 60 

months after the effective date of this AD, do 

a general visual inspection to verify that each 

GFI installation screw has enough grip length 

to hold the screws in each nut plate; and do 

applicable electrical bonding resistance 

measurements between the GFI relays and 

their installation panel to verify that 

applicable bonding requirements are met. If 

the screw does not have enough grip length, 

before further flight, install a longer screw. 

Do all actions in accordance with Part 2 of 

the Accomplishment Instructions of Boeing 

Service Bulletin 757–28A0078, Revision 1, 

dated August 24, 2010 (for Model 757–200, 

–200CB, and –200PF airplanes); or Boeing 

Service Bulletin 757–28A0079, Revision 1, 

dated August 24, 2010 (for Model 757–300 

airplanes). 

Exception to the Service Information 

(i) The note in paragraph 3.B.12.i(5) of Part 

1 of the Accomplishment Instructions of 

Boeing Service Bulletins 757–28A0078 and 

757–28A0079, both Revision 1, both dated 

August 24, 2010, should read, ‘‘NOTE: The 

right override fuel boost pump PRESS light 

stays off when the pump switch is turned to 

OFF.’’ 

Paperwork Reduction Act Burden Statement 

(j) 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) 

(k)(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 

(l) For more information about this AD, 

contact Georgios Roussos, Aerospace 

Engineer, Systems and Equipment Branch, 

ANM–130S, Seattle ACO, FAA, 1601 Lind 

Avenue, SW., Renton, Washington 98057– 

3356; telephone (425) 917–6482; fax (425) 

917–6590. Or, e-mail information to 9-ANMSeattle-ACO-AMOC-Requests@faa.gov; email: Georgios.Roussos@faa.gov. 

(m) For 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. 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. 

Issued in Renton, Washington, on 

December 23, 2010. 

John P. Piccola, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2010–33129 Filed 12–30–10; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–1272; Directorate 

Identifier 2010–NM–226–AD] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Model 727, 727C, 727–100, 

727–100C, 727–200, and 727–200F 

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 replacing the existing 

unshielded fuel quantity indication 

system (FQIS) wire bundles with double 

shielded FQIS wire bundles, installing a 

new wire feed-through fitting, and 

grounding the wire shields, as 

applicable; and doing repetitive low 

frequency eddy current (LFEC) 

inspections for cracking of the fuselage 

skin, and corrective actions if necessary. 

This proposed AD also would require 

revising the maintenance program to 

incorporate certain airworthiness 

limitations. This proposed AD was 

prompted by fuel system reviews 

conducted by the manufacturer. We are 

proposing this AD to increase the level 

of protection from lightning strikes and 

prevent the potential of ignition sources 

inside fuel tanks, which, in combination 

with flammable fuel vapors, could result 

in fuel tank explosions and consequent 

loss of the airplane. 

DATES: We must receive comments on 

this proposed AD by February 17, 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 


srobinson on DSKHWCL6B1PROD with PROPOSALS
32 Federal Register / Vol. 76, No. 1 / Monday, January 3, 2011 / 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, Washington 98124– 

2207; telephone 206–544–5000, 

extension 1; fax 206–766–5680; e-mail 

me.boecom@boeing.com; Internet 

https://www.myboeingfleet.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: 

Louis Natsiopoulos, Aerospace 

Engineer, Systems and Equipment 

Branch, ANM–130S, FAA, Seattle 

Aircraft Certification Office, 1601 Lind 

Avenue, SW., Renton, Washington 

98057–3356; telephone (425) 917–6478; 

fax (425) 917–6590; e-mail: 

elias.natsiopoulos@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– 

2010–1272; Directorate Identifier 2010– 

NM–226–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 fuel tank explosions and consequent 

loss of the airplane. 

A safety assessment has determined 

that shielding was not provided for the 

FQIS wire bundles. Unshielded wire 

bundles could result in a reduced level 

of protection against a lightning strike 

which could be a potential ignition 

source for the fumes in the fuel tanks. 

This condition, if not corrected, could 

result in fuel tank explosions and 

consequent loss of the airplane. 

Relevant Service Information 

We reviewed Boeing Service Bulletin 

727–28–0131, dated August 18, 2010. 

The service information describes 

procedures for the following: 

• For airplanes in Groups 1, 12, 13, 

and 14: Replacing the FQIS wire 

bundles between the fitting and ground 

brackets at the pressure seal and the 

tank connectors on the wing tanks with 

double shielded wire bundles; installing 

a new wire feed-through fitting and 

ground brackets for the wires at the 

pressure seal, and ground brackets at the 

wing tank connectors; and grounding 

the wire shields at the pressure seal 

feed-through fitting and ground brackets 

and at the tank connector brackets. 

• For airplanes in Groups 2 through 

11 and 15 through 49: Replacing the 

FQIS wire bundles between the pressure 

seal and the volumetric top-off (VTO) 

connectors with double shielded wire 

bundles and working the ground wires 

at the VTO connectors. 

• For all airplanes: Doing repetitive 

LFEC inspections for cracking in the 

fuselage skin on the left and right sides 

of the airplane, and contacting Boeing 

for repair instructions and doing the 

repair if necessary. 

We have also reviewed Section 9 of 

the Boeing 727–100/200 Airworthiness 

Limitations (AWLs), D6–8766–AWL, 

Revision August 2010. Sub-Section D of 

Section 9 of the Boeing 727–100/200 

Airworthiness Limitations (AWLs), D6– 

8766–AWL describes AWLs for fuel 

tank systems, including the following 

fuel system AWLs: 

• AWL No. 28–AWL–18 which is a 

check of the fuel quantity indicating 

system (FQIS)—out-tank wiring 

lightning shield to ground termination, 

applicable to all Model 727–100 and 

–200 airplanes that have incorporated 

Boeing Service Bulletin 727–28–0131. 

• AWL No. 28–AWL–19 which is a 

critical design configuration control 

limitation (CDCCL) that specifies to do 

a check of the FQIS—out-tank wiring 

lightning shield to ground termination, 

following any FQIS out-tank wire 

bundle replacement, wire bundle shield 

repair or shield path to ground 

reconnection, applicable to all Model 

727–100 and –200 airplanes that have 

incorporated Boeing Service Bulletin 

727–28–0131. 


srobinson on DSKHWCL6B1PROD with PROPOSALS
Federal Register / Vol. 76, No. 1 / Monday, January 3, 2011 / Proposed Rules 33 

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 

accomplishing the actions specified in 

the service information described 

previously, except as discussed under 

‘‘Differences Between Proposed Rule 

and Service Bulletin.’’ 

Differences Between Proposed Rule and 

Service Bulletin 

Although Boeing Service Bulletin 

727–28–0131, dated August 18, 2010, 

specifies that operators may contact the 

manufacturer for disposition of certain 

repair conditions, this proposed AD 

would require operators to repair those 

cracks using a method approved by the 

FAA. 

Costs of Compliance 

We estimate that this proposed AD 

will affect 566 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 .................. Between 86 and 247 work-hours × $85 per 

hour = Between $7,310–$20,995.1

Between $16,191 and 

$34,712.1

Between $23,501 and 

$55,707.1

Up to $27,195,925.2

Inspection ................... 2 work-hours × $85 per hour = $170 per inspection cycle.0 ................................. 170 ............................. 96,220 per inspection 

cycle. 

Maintenance Program 

Revision.

1 work-hour × $85 per hour = $85 ................. 0 ................................. 85 ............................... 48,110. 

1 Depending on configuration. 

2The cost on U.S. operators is based on configuration and number of airplanes in that configuration. 

We have received no definitive data that 

would enable us to provide a cost 

estimate for the on-condition action 

specified in this proposed AD. 

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– 

2010–1272; Directorate Identifier 2010– 

NM–226–AD. 

Comments Due Date 

(a) We must receive comments by February 

17, 2011. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to The Boeing 

Company Model 727, 727C, 727–100, 727– 

100C, 727–200, and 727–200F series 

airplanes, all variable numbers, certificated 

in any category. 

Note 1: This AD requires revisions to 

certain operator maintenance documents to 

include new inspections. Compliance with 

these inspections is required by 14 CFR 

91.403(c). For airplanes that have been 

previously modified, altered, or repaired in 

the areas addressed by these inspections, the 

operator may 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 for an 

alternative method of compliance according 

to paragraph (l) of this AD. The request 

should include a description of changes to 

the required inspections that will ensure the 

continued operational safety of the airplane. 

Subject 

(d) Joint Aircraft System Component 

(JASC)/Air Transport Association (ATA) of 

America Code 28, Fuel. 

Unsafe Condition 

(e) This AD was prompted by fuel system 

reviews conducted by the manufacturer. We 

are issuing this AD to increase the level of 

protection from lightning strikes and prevent 

the potential of ignition sources inside fuel 

tanks, which, in combination with flammable 

fuel vapors, could result in fuel tank 

explosions and consequent loss of the 

airplane. 

Compliance 

(f) Comply with this AD within the 

compliance times specified, unless already 

done. 


srobinson on DSKHWCL6B1PROD with PROPOSALS
34 Federal Register / Vol. 76, No. 1 / Monday, January 3, 2011 / Proposed Rules 

Installation 

(g) Within 60 months after the effective 

date of this AD, install double shielded fuel 

quantity indicating system (FQIS) wire 

bundles, install a new wire feed-through 

fitting, and ground the wire shields, as 

applicable, in accordance with Part 1 of the 

Accomplishment Instructions of Boeing 

Service Bulletin 727–28–0131, dated August 

18, 2010. 

Repetitive Inspections 

(h) At the applicable times specified in 

paragraphs (h)(1) or (h)(2) of this AD, do low 

frequency eddy current (LFEC) inspections 

for cracking of the fuselage skin, in 

accordance with Part 2 of the 

Accomplishment Instructions of Boeing 

Service Bulletin 727–28–0131, dated August 

18, 2010. 

(1) For Model 727, 727–100, 727–100C, 

and 727C series airplanes: Before the 

accumulation of 45,000 total flight cycles, or 

within 8,000 flight cycles after the effective 

date of this AD, whichever occurs later. 

Repeat the inspections thereafter at intervals 

not to exceed 8,000 flight cycles. 

(2) For Model 727–200 and 727–200F 

series airplanes: Before the accumulation of 

45,000 total flight cycles, or within 16,000 

flight cycles after the effective date of this 

AD, whichever occurs later. Repeat the 

inspections thereafter at intervals not to 

exceed 16,000 flight cycles. 

(i) If any cracking is found during any 

inspection required by paragraph (h) of this 

AD: Before further flight, repair the crack in 

accordance with a method approved by the 

Manager, Seattle Aircraft Certification Office 

(ACO), FAA. 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. 

Maintenance Program Revision 

(j) Before or concurrently with doing the 

actions required by paragraph (g) of this AD, 

or within 30 days after the effective date of 

this AD, whichever occurs later: Revise the 

maintenance program by incorporating 

airworthiness limitations (AWL) No. 28– 

AWL–18 and 28–AWL–19 in Section D of 

Section 9 (‘‘AIRWORTHINESS 

LIMITATIONS—FUEL SYSTEMS’’) of the 

Boeing 727–100/200 Airworthiness 

Limitations (AWLs) Document, 

D6–8766–AWL, Revision August 2010. The 

initial compliance time for AWL No. 28– 

AWL–18 is within 10 years after the 

accomplishment of paragraph (g) of this AD, 

or within 10 years after the effective date of 

this AD, whichever occurs later. 

No Alternative Inspections, Inspection 

Intervals, or Critical Design Configuration 

Control Limitations (CDCCLs) 

(k) After accomplishing the action 

specified in paragraph (j) of this AD, no 

alternative inspections, inspection intervals, 

or CDCCLs may be used unless the 

inspections, intervals, or CDCCLs are 

approved as an Alternative Method of 

Compliance (AMOC) in accordance with the 

procedures specified in paragraph (l) of this 

AD. 

Alternative Methods of Compliance 

(AMOCs) 

(l)(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 

(m) For more information about this AD, 

contact Louis Natsiopoulos, Aerospace 

Engineer, Systems and Equipment Branch, 

ANM–130S, FAA, Seattle Aircraft 

Certification Office, 1601 Lind Avenue, SW., 

Renton, Washington 98057–3356; telephone 

(425) 917–6478; fax (425) 917–6590; e-mail: 

elias.natsiopoulos@faa.gov. 

(n) For 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. 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. 

Issued in Renton, Washington, on 

December 17, 2010. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2010–33002 Filed 12–30–10; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–1275; Directorate 

Identifier 2010–NM–091–AD] 

RIN 2120–AA64 

Airworthiness Directives; Airbus Model 

A310 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 results from 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: 

DGAC [Direction Ge ́ne ́rale de l’Aviation 

Civile] France Airworthiness Directive (AD) 

1992–106–132(B) * * * was issued to 

require a set of inspection- and modification 

tasks which addressed JAR/FAR [Joint 

Aviation Regulation/Federal Aviation 

Regulation] 25–571 requirements related to 

damage-tolerance and fatigue evaluation of 

structure. * * *. 

* * * * * 

The unsafe condition is reduced 

structural integrity of the wings. The 

proposed AD would require actions that 

are intended to address the unsafe 

condition described in the MCAI. 

DATES: We must receive comments on 

this proposed AD by February 17, 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: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–40, 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— 

EAW (Airworthiness Office), 1 Rond 

Point Maurice Bellonte, 31707 Blagnac 

Cedex, France; telephone +33 5 61 93 36 

96; fax +33 5 61 93 44 51; e-mail 

account.airworth-eas@airbus.com; 

Internet http://www.airbus.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 Operations office 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 


srobinson on DSKHWCL6B1PROD with PROPOSALS