482 Federal Register / Vol. 76, No. 3 / Wednesday, January 5, 2011 / Proposed Rules 

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, 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: 

Dassault-Aviation: Docket No. FAA–2010– 

1306; Directorate Identifier 2010–NM– 

112–AD. 

Comments Due Date 

(a) We must receive comments by February 

22, 2011. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to Dassault-Aviation 

Model FALCON 7X airplanes, certificated in 

any category, all serial numbers. 

Subject 

(d) Air Transport Association (ATA) of 

America Code 24: Electrical power. 

Reason 

(e) The mandatory continuing 

airworthiness information (MCAI) states: 

A design review has revealed a potential 

dormant failure of the Ram Air Turbine 

(RAT) heating system. If this failure occurs, 

it could lead to the freezing of the RAT 

mechanism and the consequent nondeployment of the RAT when needed. 

* * * * * 

Non-deployment of the RAT could result in 

insufficient electrical power to operate the 

fly-by-wire system, and subsequent loss of 

control of the airplane. 

Compliance 

(f) You are responsible for having the 

actions required by this AD performed within 

the compliance times specified, unless the 

actions have already been done. 

Actions 

(g) At the applicable times specified in 

paragraph (g)(1) or (g)(2) of this AD, do a 

functional test of the RAT heater using a 

method approved by either the Manager, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA; or the European 

Aviation Safety Agency (EASA) (or its 

delegated agent). Repeat the functional test of 

the RAT heater thereafter at the applicable 

time specified in paragraph (g)(1) or (g)(2) of 

this AD. If any functional test fails, before 

further flight, repair using a method 

approved by either the Manager, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA; or EASA (or its 

delegated agent). 

(1) For Falcon 7X airplanes on which 

modification M0305 has not been done and 

on which Dassault Service Bulletin 7X–018, 

dated March 6, 2009, has not been done: 

Within 650 flight hours after the effective 

date of this AD, do a functional test of the 

RAT heater and repeat the functional test of 

the RAT heater thereafter at intervals not to 

exceed 650 flight hours. 

(2) For Falcon 7X airplanes on which 

modification M0305 has been done or on 

which Dassault Service Bulletin 7X–018, 

dated March 6, 2009, has been done: Within 

1,900 flight hours after the effective date of 

this AD or after modification M0305 or 

Dassault Service Bulletin 7X–018, dated 

March 6, 2009, has been done, whichever 

occurs later, do a functional test of the RAT 

heater: Repeat the functional test of the RAT 

heater thereafter at intervals not to exceed 

1,900 flight hours. 

Note 1: Additional guidance for doing the 

functional test of the RAT heater required by 

paragraph (g) of this AD can be found in Task 

24–50–25–720–801, Functional Test of the 

RAT Heater, dated January 16, 2009, of the 

Dassault Falcon 7X Aircraft Maintenance 

Manual (AMM). 

FAA AD Differences 

Note 2: This AD differs from the MCAI 

and/or service information as follows: 

(1) The MCAI provides an option of 

inserting the MCAI into the Falcon 7X AMM 

Chapter 5–40, pending publication of the 

revised AMM Chapter 5–40. This AD does 

not have that option. 

(2) The MCAI requires doing the actions in 

accordance with Maintenance Task 24–50– 

25–720–801, Chapter 5–40, of the Dassault 

Falcon 7X AMM. However, this AD requires 

that the actions be done using a method 

approved by the FAA or EASA (or its 

delegated agent). 

Other FAA AD Provisions 

(h) The following provisions also apply to 

this AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Branch, ANM–116, 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: Tom Rodriguez, 

Aerospace Engineer, International Branch, 

ANM–116, Transport Airplane Directorate, 

FAA, 1601 Lind Avenue, SW., Renton, 

Washington 98057–3356; telephone (425) 

227–1137; fax (425) 227–1149. Before using 

any approved AMOC on any airplane to 

which the AMOC applies, notify your 

principal maintenance inspector (PMI) or 

principal avionics inspector (PAI), as 

appropriate, or lacking a principal inspector, 

your local Flight Standards District Office. 

The AMOC approval letter must specifically 

reference this AD. 

(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: 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 

(i) Refer to MCAI EASA Airworthiness 

Directive 2010–0033, dated March 3, 2010, 

for related information. 

Issued in Renton, Washington, on 

December 27, 2010. 

Jeffrey E. Duven, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2010–33334 Filed 1–4–11; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–1304; Directorate 

Identifier 2010–NM–254–AD] 

RIN 2120–AA64 

Airworthiness Directives; Fokker 

Services B.V. Model F.28 Mark 1000, 

2000, 3000, and 4000 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 


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Federal Register / Vol. 76, No. 3 / Wednesday, January 5, 2011 / Proposed Rules 483 

product. The MCAI describes the unsafe 

condition as: 

* * * under certain conditions, an ignition 

source may develop in the wing tank vapour 

space, due to insufficient clearance between 

the wiring along the Fuel Quantity Tank 

Units (FQTU’s) and the local reinforcing 

structure around the upper skin cut-out. 

This condition, if not corrected, in 

combination with flammable fuel vapours, 

could result in a wing tank explosion and 

consequent loss of the aeroplane. 

* * * * * 

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 22, 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 W12–140, 1200 New Jersey 

Avenue, SE., Washington, DC, between 

9 a.m. and 5 p.m., Monday through 

Friday, except Federal holidays. 

For service information identified in 

this proposed AD, contact Fokker 

Services B.V., Technical Services Dept., 

P.O. Box 231, 2150 AE Nieuw-Vennep, 

the Netherlands; telephone +31 (0)252– 

627–350; fax +31 (0)252–627–211; email technicalservices.fokkerservices

@stork.com; Internet http:// 

www.myfokkerfleet.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 

street address for the Docket Operations 

office (telephone (800) 647–5527) is in 

the ADDRESSES section. Comments will 

be available in the AD docket shortly 

after receipt. 

FOR FURTHER INFORMATION CONTACT: Tom 

Rodriguez, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue, SW., Renton, 

Washington 98057–3356; telephone 

(425) 227–1137; fax (425) 227–1149. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 

this proposed AD. Send your comments 

to an address listed under the 

ADDRESSES section. Include ‘‘Docket No. 

FAA–2010–1304; Directorate Identifier 

2010–NM–254–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 based on 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 European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Community, has issued EASA 

Airworthiness Directive 2010–0156, 

dated August 3, 2010 (referred to after 

this as ‘‘the MCAI’’), to correct an unsafe 

condition for the specified products. 

The MCAI states: 

* * * The FAA has published Special 

Federal Aviation Regulation (SFAR) 88, and 

the [Joint Aviation Authorities] JAA has 

published Interim Policy INT/POL/25/12. 

The design review conducted by Fokker 

Services on the Fokker F28 type design in 

response to these regulations revealed that, 

under certain conditions, an ignition source 

may develop in the wing tank vapour space, 

due to insufficient clearance between the 

wiring along the Fuel Quantity Tank Units 

(FQTU’s) and the local reinforcing structure 

around the upper skin cut-out. 

This condition, if not corrected, in 

combination with flammable fuel vapours, 

could result in a wing tank explosion and 

consequent loss of the aeroplane. 

For the reasons described above, this AD 

requires a one-time [detailed] inspection to 

investigate if a clearance of 3 mm (0.12 inch) 

or more is available between the FQTU 

probes wiring and the surrounding 

reinforcement structure of the wing upper 

skin and corrective rework actions, 

depending on findings. 

You may obtain further information by 

examining the MCAI in the AD docket. 

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. 

The Joint Aviation Authorities (JAA) 

has issued a regulation that is similar to 

SFAR 88. (The JAA is an associated 

body of the European Civil Aviation 

Conference (ECAC) representing the 

civil aviation regulatory authorities of a 

number of European States who have 

agreed to co-operate in developing and 

implementing common safety regulatory 

standards and procedures.) Under this 

regulation, the JAA stated that all 

members of the ECAC that hold type 

certificates for transport category 


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484 Federal Register / Vol. 76, No. 3 / Wednesday, January 5, 2011 / Proposed Rules 

airplanes are required to conduct a 

design review against explosion risks. 

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. 

Relevant Service Information 

Fokker Services B.V. has issued 

Fokker Service Bulletin SBF28–57–097, 

Revision 1, dated June 10, 2010. The 

actions described in this service 

information are intended to correct the 

unsafe condition identified in the 

MCAI. 

FAA’s Determination and Requirements 

of This Proposed AD 

This product has been approved by 

the aviation authority of another 

country, and is approved for operation 

in the United States. Pursuant to our 

bilateral agreement with the State of 

Design Authority, we have been notified 

of the unsafe condition described in the 

MCAI and service information 

referenced above. We are proposing this 

AD because we evaluated all pertinent 

information and determined an unsafe 

condition exists and is likely to exist or 

develop on other products of the same 

type design. 

Differences Between This AD and the 

MCAI or Service Information 

We have reviewed the MCAI and 

related service information and, in 

general, agree with their substance. But 

we might have found it necessary to use 

different words from those in the MCAI 

to ensure the AD is clear for U.S. 

operators and is enforceable. In making 

these changes, we do not intend to differ 

substantively from the information 

provided in the MCAI and related 

service information. 

We might also have proposed 

different actions in this AD from those 

in the MCAI in order to follow FAA 

policies. Any such differences are 

highlighted in a Note within the 

proposed AD. 

Costs of Compliance 

Based on the service information, we 

estimate that this proposed AD would 

affect about 2 products of U.S. registry. 

We also estimate that it would take 

about 6 work-hours per product to 

comply with the basic requirements of 

this proposed AD. The average labor 

rate is $85 per work-hour. Based on 

these figures, we estimate the cost of the 

proposed AD on U.S. operators to be 

$1,020, or $510 per product. 

In addition, we estimate that any 

necessary follow-on actions would take 

about 21 work-hours and require parts 

costing $0, for a cost of $1,785 per 

product. We have no way of 

determining the number of products 

that may need these actions. 

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); 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: 

Fokker Services B.V.: Docket No. FAA– 

2010–1304; Directorate Identifier 2010– 

NM–254–AD. 

Comments Due Date 

(a) We must receive comments by February 

22, 2011. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to Fokker Services B.V. 

Model F.28 Mark 1000, 2000, 3000, and 4000 

airplanes, certificated in any category, all 

serial numbers. 

Subject 

(d) Air Transport Association (ATA) of 

America Code 57: Wings. 

Reason 

(e) The mandatory continuing 

airworthiness information (MCAI) states: 

* * * under certain conditions, an ignition 

source may develop in the wing tank vapour 

space, due to insufficient clearance between 

the wiring along the Fuel Quantity Tank 

Units (FQTU’s) and the local reinforcing 

structure around the upper skin cut-out. 

This condition, if not corrected, in 

combination with flammable fuel vapours, 

could result in a wing tank explosion and 

consequent loss of the aeroplane. 

* * * * * 

Compliance 

(f) You are responsible for having the 

actions required by this AD performed within 

the compliance times specified, unless the 

actions have already been done. 

Detailed Inspection and Corrective Actions 

(g) At the next scheduled opening of the 

fuel tanks, but not later than 84 months after 

the effective date of this AD, do a detailed 

inspection for minimum clearance of the gap 

between the FQTU wiring harness and the 

outer wing FQTU hole reinforcement 

structure, in accordance with the 

Accomplishment Instructions of Fokker 

Service Bulletin SBF28–57–097, Revision 1, 

dated June 10, 2010. 

(h) If during the inspection required by 

paragraph (g) of this AD, the minimum 

clearance is found to be insufficient, as 

defined in the Accomplishment Instructions 

of Fokker Service Bulletin SBF28–57–097, 

Revision 1, dated June 10, 2010, before 

further flight, rework the surrounding 

structure to remove the possibility of an 

ignition source, in accordance with the 


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Federal Register / Vol. 76, No. 3 / Wednesday, January 5, 2011 / Proposed Rules 485 

Accomplishment Instructions of Fokker 

Service Bulletin SBF28–57–097, Revision 1, 

dated June 10, 2010. 

Credit for Actions Accomplished in 

Accordance With Previous Service 

Information 

(i) Inspections accomplished before the 

effective date of this AD according to Fokker 

Service Bulletin SBF28–57–097, dated May 

6, 2010, are considered acceptable for 

compliance with the requirements of 

paragraph (g) of this AD. 

FAA AD Differences 

Note 1: This AD differs from the MCAI 

and/or service information as follows: No 

differences. 

Other FAA AD Provisions 

(j) The following provisions also apply to 

this AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Branch, ANM–116, Transport Airplane 

Directorate, 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: Tom Rodriguez, 

Aerospace Engineer, International Branch, 

ANM–116, Transport Airplane Directorate, 

FAA, 1601 Lind Avenue, SW., Renton, 

Washington 98057–3356; telephone (425) 

227–1137; fax (425) 227–1149. Information 

may be e-mailed to: 9-ANM-116-AMOCREQUESTS@faa.gov. Before using any 

approved AMOC on any airplane to which 

the AMOC applies, notify your principal 

maintenance inspector (PMI) or principal 

avionics inspector (PAI), as appropriate, or 

lacking a principal inspector, your local 

Flight Standards District Office. The AMOC 

approval letter must specifically reference 

this AD. 

(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. 

(3) Reporting Requirements: 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 

(k) Refer to MCAI European Aviation 

Safety Agency (EASA) Airworthiness 

Directive 2010–0156, dated August 3, 2010; 

and Fokker Service Bulletin SBF28–57–097, 

Revision 1, dated June 10, 2010; for related 

information. 

Issued in Renton, Washington, on 

December 28, 2010. 

Jeffrey E. Duven, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2010–33337 Filed 1–4–11; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–1305; Directorate 

Identifier 2010–NM–074–AD] 

RIN 2120–AA64 

Airworthiness Directives; Lockheed 

Martin Corporation/Lockheed Martin 

Aeronautics Company Model 382, 

382B, 382E, 382F, and 382G Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: The FAA proposes to 

supersede an existing airworthiness 

directive (AD) that applies to all Model 

382, 382B, 382E, 382F, and 382G 

airplanes. The existing AD currently 

requires revising the FAA-approved 

maintenance program by incorporating 

new airworthiness limitations for fuel 

tank systems to satisfy Special Federal 

Aviation Regulation No. 88 

requirements. That AD also requires the 

accomplishment of certain fuel system 

modifications, the initial inspections of 

certain repetitive fuel system limitations 

to phase in those inspections, and repair 

if necessary. This proposed AD would 

correct certain part number references, 

add an additional inspection area, and 

for certain airplanes, require certain 

actions to be re-accomplished according 

to revised service information. This 

proposed AD results from a report of 

incorrect accomplishment information 

in the service information cited by the 

existing AD. We are proposing this AD 

to prevent the potential for ignition 

sources inside fuel tanks caused by 

latent failures, alterations, repairs, or 

maintenance actions, 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 22, 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 W12–140, 1200 New Jersey 

Avenue, SE., Washington, DC 20590, 

between 9 a.m. and 5 p.m., Monday 

through Friday, except Federal holidays. 

For service information identified in 

this proposed AD, contact Lockheed 

Martin Corporation/Lockheed Martin 

Aeronautics Company, Airworthiness 

Office, Dept. 6A0M, Zone 0252, Column 

P–58, 86 S. Cobb Drive, Marietta, 

Georgia 30063; telephone 770–494– 

5444; fax 770–494–5445; e-mail 

ams.portal@lmco.com; Internet http:// 

www.lockheedmartin.com/ams/tools/ 

TechPubs.html. 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 

(telephone 800–647–5527) is in the 

ADDRESSES section. Comments will be 

available in the AD docket shortly after 

receipt. 

FOR FURTHER INFORMATION CONTACT: Neil 

Duggan, Aerospace Engineer, 

Propulsion and Services Branch, ACE– 

118A, FAA, Atlanta Aircraft 

Certification Office, 1701 Columbia 

Avenue, College Park, GA 30337; 

telephone (404) 474–5576; fax (404) 

474–5606. 

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 


srobinson on DSKHWCL6B1PROD with PROPOSALS