Federal Register / Vol. 70, No. 186 / Tuesday, September 27, 2005 / Rules and Regulations 56347 

flange of the jettison valve in accordance 

with the service bulletin and, whether a 

crack is found or not, before further flight, do 

the modification required by paragraph (i) of 

this AD. If no crack is found during the eddy 

current inspection, the inspected jettison 

valve may be reinstalled during the 

modification required by paragraph (i) of this 

AD. 

(2) If any crack is found during the detailed 

inspection: Before further flight, do the 

modification in paragraph (i) of this AD and 

do not reinstall the jettison valve. 

Note 1: For the purposes of this AD, a 

detailed inspection is: ‘‘An intensive 

examination of a specific item, installation, 

or assembly to detect damage, failure, or 

irregularity. Available lighting is normally 

supplemented with a direct source of good 

lighting at an intensity deemed appropriate. 

Inspection aids such as mirror, magnifying 

lenses, etc., may be necessary. Surface 

cleaning and elaborate procedures may be 

required.’’

Modification 

(i) At the applicable time specified in 

paragraph (g) or (h) of this AD: Modify the 

diameters of the six attachment holes in the 

wing bottom skin panel, and install a new 

fuel jettison valve, or reinstall a previously 

installed fuel jettison valve that has been 

inspected and found to have no crack in 

accordance with paragraph (h) of this AD. Do 

all actions in accordance with the service 

bulletin. 

Parts Installation 

(j) As of the effective date of this AD, no 

person may install, on any airplane, a fuel 

jettison valve, P/N HTE900169, unless it has 

been inspected and had corrective actions 

done in accordance with paragraphs (g) and 

(h) of this AD. 

Alternative Methods of Compliance 

(AMOCs) 

(k)(1) The Manager, ANM–116, Transport 

Airplane Directorate, FAA, has the authority 

to approve AMOCs for this AD, if requested 

in accordance with the procedures found in 

14 CFR 39.19. 

(2) Before using any AMOC approved in 

accordance with § 39.19 on any airplane to 

which the AMOC applies, notify the 

appropriate principal inspector in the FAA 

Flight Standards Certificate Holding District 

Office. 

Related Information 

(l) French airworthiness directive F–2004–

127, dated August 4, 2004, also addresses the 

subject of this AD. 

Material Incorporated by Reference 

(m) You must use Airbus Service Bulletin 

A330–57–3078, Revision 01, dated August 4, 

2004, to perform the actions that are required 

by this AD, unless the AD specifies 

otherwise. The Director of the Federal 

Register approved the incorporation by 

reference of this document in accordance 

with 5 U.S.C. 552(a) and 1 CFR part 51. 

Contact Airbus, 1 Rond Point Maurice 

Bellonte, 31707 Blagnac Cedex, France, for a 

copy of this service information. You may 

review copies at the Docket Management 

Facility, U.S. Department of Transportation, 

400 Seventh Street, SW., room PL–401, 

Nassif Building, Washington, DC; on the 

Internet at http://dms.dot.gov; or at the 

National Archives and Records 

Administration (NARA). For information on 

the availability of this material at the NARA, 

call (202) 741–6030, or go to http:// 

www.archives.gov/federal_register/ 

code_of_federal_regulations/ 

ibr_locations.html. 

Issued in Renton, Washington, on 

September 15, 2005. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 05–18910 Filed 9–26–05; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2005–22482; Directorate 

Identifier 2003–NM–009–AD; Amendment 

39–14291; AD 2005–19–26] 

RIN 2120–AA64 

Airworthiness Directives; BAE 

Systems (Operations) Limited Model 

ATP Airplanes and Model HS 748 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule; request for 

comments. 

SUMMARY: The FAA is adopting a new 

airworthiness directive (AD) for all BAE 

Systems (Operations) Limited Model 

ATP airplanes and Model HS 748 

airplanes. This AD requires doing a 

detailed inspection of the drain pipes of 

the fuel cross feed system and certain 

electrical cables for chafe damage; doing 

an inspection to determine the clearance 

between the cable loom and the cross 

feed drain pipe; and doing corrective 

actions if necessary. This AD results 

from a fire in the dry area of the wing 

due to severe chafe damage between an 

electrical cable and the fuel cross feed 

drain pipe. We are issuing this AD to 

prevent chafe damage of the electrical 

cable and fuel cross feed drain pipe that 

could lead to fuel leakage from the drain 

pipe and an ignition source from the 

electrical cable, which could result in a 

fire in the dry area of the airplane wing. 

DATES: This AD becomes effective 

October 12, 2005. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in the AD 

as of October 12, 2005. 

We must receive comments on this 

AD by November 28, 2005. 

ADDRESSES: Use one of the following 

addresses to submit comments on this 

AD. 

• DOT Docket Web site: Go to 

http://dms.dot.gov and follow the 

instructions for sending your comments 

electronically. 

• Government-wide rulemaking Web 

site: Go to http://www.regulations.gov 

and follow the instructions for sending 

your comments electronically. 

• Mail: Docket Management Facility; 

U.S. Department of Transportation, 400 

Seventh Street SW., Nassif Building, 

room PL–401, Washington, DC 20590. 

• Fax: (202) 493–2251. 

• Hand Delivery: Room PL–401 on 

the plaza level of the Nassif Building, 

400 Seventh Street SW., Washington, 

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

through Friday, except Federal holidays. 

Contact British Aerospace Regional 

Aircraft American Support, 13850 

Mclearen Road, Herndon, Virginia 

20171, for service information identified 

in this AD. 

FOR FURTHER INFORMATION CONTACT: 

Todd Thompson, Aerospace Engineer, 

International Branch, ANM–116, FAA, 

Transport Airplane Directorate, 1601 

Lind Avenue, SW., Renton, Washington 

98055–4056; telephone (425) 227–1175; 

fax (425) 227–1149. 

SUPPLEMENTARY INFORMATION: 

Discussion 

The Civil Aviation Authority (CAA), 

which is the airworthiness authority for 

the United Kingdom, notified us that an 

unsafe condition may exist on all BAE 

Systems (Operations) Limited Model 

ATP airplanes and Model HS 748 

airplanes. The CAA advises that an 

operator reported finding a fire in the 

dry area of the wing on a Model ATP 

airplane before takeoff. Severe chafe 

damage between an electrical cable and 

the drain pipe of the fuel cross feed 

system caused a small leakage of fuel 

from the drain pipe. Electrical sparks 

from the damaged electrical cable most 

likely ignited the fuel leakage. Chafe 

damage of the electrical cable and fuel 

cross feed drain pipe, if not prevented, 

could result in a fire in the dry area of 

the airplane wing. 

The fuel cross feed pipe drain on 

certain Model ATP airplanes is identical 

to those on the affected Model HS 748 

airplanes. Therefore, all of these models 

may be subject to the same unsafe 

condition. 

Relevant Service Information 

BAE Systems (Operations) Limited 

has issued Alert Service Bulletin ATP–

56348 Federal Register / Vol. 70, No. 186 / Tuesday, September 27, 2005 / Rules and Regulations 

A28–021, Revision 1, dated September 

26, 2002 (for Model ATP airplanes); and 

Alert Service Bulletin HS748–A28–44, 

dated September 26, 2002 (for Model HS 

748 airplanes). The service bulletins 

describe procedures for accomplishing 

the following actions: 

• Inspecting the cross feed drain pipe 

of the left and right wings between the 

fuel drain valve and the cross feed drain 

pipe for chafe damage, and doing the 

corrective action if necessary. The 

corrective action is replacing the cross 

feed drain pipe with a new drain pipe 

if material is lost from the wall 

thickness. If a replacement drain pipe is 

unavailable, the corrective action is 

removing the drain pipe and blanking 

the cross feed stub pipe. 

• Inspecting the electrical cables on 

the terminal block of the left and right 

wings for chafe damage, and doing 

corrective actions if necessary. The 

corrective action is to replace the 

electrical wire with new electrical wire, 

if insulation has been lost; and to 

replace any damaged protective 

convoluted or spiral tubing with new 

tubing. 

• Checking the clearance between the 

cable loom and the cross feed drain pipe 

on the left and right wings, and doing 

corrective actions if necessary. The 

corrective action is re-routing the cable 

loom for adequate clearance of the cross 

feed drain pipe. 

Accomplishing the actions specified 

in the service information is intended to 

adequately address the unsafe 

condition. The CAA mandated the 

service information and issued British 

airworthiness directives 001–09–2002 

and 002–09–2002 to ensure the 

continued airworthiness of these 

airplanes in the United Kingdom. 

FAA’s Determination and Requirements 

of This AD 

These airplane models manufactured 

in the United Kingdom and are type 

certificated for operation in the United 

States under the provisions of section 

21.29 of the Federal Aviation 

Regulations (14 CFR 21.29) and the 

applicable bilateral airworthiness 

agreement. Pursuant to this bilateral 

airworthiness agreement, the CAA has 

kept the FAA informed of the situation 

described above. We have examined the 

CAA’s findings, evaluated all pertinent 

information, and determined that we 

need to issue an AD for products of this 

type design that are certificated for 

operation in the United States. 

Therefore, we are issuing this AD to 

prevent chafe damage of the electrical 

cable and fuel cross feed drain pipe that 

could lead to fuel leakage from the drain 

pipe and an ignition source from the 

electrical cable, which could result in a 

fire in the dry area of the airplane wing. 

This AD requires accomplishing the 

actions specified in the service 

information described previously. 

Costs of Compliance 

None of the airplanes affected by this 

action are on the U.S. Register. All 

airplanes affected by this AD are 

currently operated by non-U.S. 

operators under foreign registry; 

therefore, they are not directly affected 

by this AD action. However, we 

consider this AD necessary to ensure 

that the unsafe condition is addressed if 

any affected airplane is imported and 

placed on the U.S. Register in the future. 

If an affected airplane is imported and 

placed on the U.S. Register in the future, 

the required inspections would take 

about 2 work hours per airplane, at an 

average labor rate of $65 per work hour. 

Based on these figures, the estimated 

cost of the AD would be $130 per 

airplane. 

FAA’s Determination of the Effective 

Date 

No airplane affected by this AD is 

currently on the U.S. Register. 

Therefore, providing notice and 

opportunity for public comment is 

unnecessary before this AD is issued, 

and this AD may be made effective in 

less than 30 days after it is published in 

the Federal Register. 

Comments Invited 

This AD is a final rule that involves 

requirements that affect flight safety and 

was not preceded by notice and an 

opportunity for public comment; 

however, we invite you to submit any 

relevant written data, views, or 

arguments regarding this AD. Send your 

comments to an address listed in the 

ADDRESSES section. Include ‘‘Docket No. 

FAA–2005–22482; Directorate Identifier 

2003–NM–009–AD’’ at the beginning of 

your comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of the AD that might suggest a 

need to modify it. 

We will post all comments we 

receive, without change, to http:// 

dms.dot.gov, including any personal 

information you provide. We will also 

post a report summarizing each 

substantive verbal contact with FAA 

personnel concerning this AD. Using the 

search function of that Web site, anyone 

can find and read the comments in any 

of our dockets, including the name of 

the individual who sent the comment 

(or signed the comment on behalf of an 

association, business, labor union, etc.). 

You may review the DOT’s complete 

Privacy Act Statement in the Federal 

Register published on April 11, 2000 

(65 FR 19477–78), or you may visit 

http://dms.dot.gov. 

Examining the Docket 

You may examine the AD docket on 

the Internet at http://dms.dot.gov, or in 

person at the Docket Management 

Facility office between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. The Docket 

Management Facility office (telephone 

(800) 647–5227) is located on the plaza 

level of the Nassif Building at the DOT 

street address stated in the ADDRESSES

section. Comments will be available in 

the AD docket shortly after the Docket 

Management System receives them. 

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 have determined that this AD will 

not have federalism implications under 

Executive Order 13132. This AD will 

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 that the 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 

Federal Register / Vol. 70, No. 186 / Tuesday, September 27, 2005 / Rules and Regulations 56349 

this AD and placed it in the AD docket. 

See the ADDRESSES section for a location 

to examine the regulatory evaluation. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

Adoption of the Amendment 

■ Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA amends 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 Federal Aviation 

Administration (FAA) amends § 39.13 

by adding the following new 

airworthiness directive (AD): 

2005–19–26 BAE Systems (Operations) 

Limited (Formerly British Aerospace 

Regional Aircraft): Amendment 39–

14291. Docket No. FAA–2005–22482; 

Directorate Identifier 2003–NM–009–AD. 

Effective Date 

(a) This AD becomes effective October 12, 

2005. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to all BAE Systems 

(Operations) Limited Model ATP airplanes 

and Model HS 748 series 2A and series 2B 

airplanes, certificated in any category. 

Unsafe Condition 

(d) This AD results from a fire in the dry 

area of the wing due to severe chafe damage 

between an electrical cable and the fuel cross 

feed drain pipe. We are issuing this AD to 

prevent chafe damage of the electrical cable 

and fuel cross feed drain pipe that could lead 

to fuel leakage from the drain pipe and an 

ignition source from the electrical cable, 

which could result in a fire in the dry area 

of the airplane wing. 

Compliance 

(e) 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 Inspections 

(f) Within 48 hours after the effective date 

of this AD, do the actions specified in 

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

in accordance with the Accomplishment 

Instructions of BAE Systems (Operations) 

Limited Alert Service Bulletin ATP–A28–

021, Revision 1, dated September 26, 2002 

(for Model ATP airplanes); or BAE Systems 

(Operations) Limited Alert Service Bulletin 

HS748–A28–44, dated September 26, 2002 

(for Model HS 748 airplanes); as applicable. 

(1) Do a detailed inspection of the cross 

feed drain pipe of the left and right wings 

between the fuel drain valve and the cross 

feed pipe for chafe damage. Before further 

flight, do any corrective action if applicable. 

(2) Do a detailed inspection of the 

electrical cable between the terminal block 

and fuel boost pump of the left and right 

wings for chafe damage. Before further flight, 

do any corrective action if applicable. 

(3) Do an inspection to determine the 

clearance between the cable loom and the 

cross feed drain pipe on the left and right 

wings. Before further flight, do any corrective 

action if applicable. 

No Reporting Requirement 

(g) Although the service bulletin referenced 

in this AD specifies to submit certain 

information to the manufacturer, this AD 

does not include that requirement. 

Special Flight Permit 

(h) Prohibited. 

Alternative Methods of Compliance 

(AMOCs) 

(i)(1) The Manager, International Branch, 

ANM–116, Transport Airplane Directorate, 

FAA, has the authority to approve AMOCs 

for this AD, if requested in accordance with 

the procedures found in 14 CFR 39.19. 

(2) Before using any AMOC approved in 

accordance with 14 CFR 39.19 on any 

airplane to which the AMOC applies, notify 

the appropriate principal inspector in the 

FAA Flight Standards Certificate Holding 

District Office. 

Related Information 

(j) British airworthiness directives 001–09–

2002 and 002–09–2002 also address the 

subject of this AD. 

Material Incorporated by Reference 

(k) You must use BAE Systems 

(Operations) Limited Alert Service Bulletin 

ATP–A28–021, Revision 1, dated September 

26, 2002; or BAE Systems (Operations) 

Limited Alert Service Bulletin HS748–A28–

44, dated September 26, 2002; as applicable, 

to perform the actions that are required by 

this AD, unless the AD specifies otherwise. 

The Director of the Federal Register approved 

the incorporation by reference of these 

documents in accordance with 5 U.S.C. 

552(a) and 1 CFR part 51. Contact British 

Aerospace Regional Aircraft American 

Support, 13850 Mclearen Road, Herndon, 

Virginia 20171, for a copy of this service 

information. You may review copies at the 

Docket Management Facility, U.S. 

Department of Transportation, 400 Seventh 

Street SW., room PL–401, Nassif Building, 

Washington, DC; on the Internet at http:// 

dms.dot.gov; or at the National Archives and 

Records Administration (NARA). For 

information on the availability of this 

material at the NARA, call (202) 741–6030, 

or go to http://www.archives.gov/ 

federal_register/code_of_federal_regulations/ 

ibr_locations.html. 

Issued in Renton, Washington, on 

September 15, 2005. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 05–18909 Filed 9–26–05; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2005–20785; Directorate 

Identifier 2005–NM–002–AD; Amendment 

39–14295; AD 2005–20–02] 

RIN 2120–AA64 

Airworthiness Directives; Boeing 

Model 707 Airplanes, and Boeing 

Model 720 and 720B Series Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: The FAA is adopting a new 

airworthiness directive (AD) for all 

Boeing Model 707 airplanes, and all 

Boeing Model 720 and 720B series 

airplanes. This AD requires revising the 

Limitations section of the airplane flight 

manual (AFM). The AFM revisions 

include instructions for monitoring the 

low pressure lights for the center tank 

fuel pumps, and a statement prohibiting 

the resetting of a tripped circuit breaker 

for a fuel pump in any tank. This AD 

results from fuel system reviews 

conducted by the manufacturer. We are 

issuing this AD to prevent dry operation 

of the fuel pumps in the center fuel 

tank, which could result in high 

temperatures or sparks inside the fuel 

tank, ignition of fuel vapors, and 

consequent fire or explosion. We are 

also issuing this AD to prohibit the 

resetting of a tripped circuit breaker for 

a fuel pump in any tank, which could 

allow an electrical fault to override the 

protective features of the circuit breaker, 

and result in sparks inside the fuel tank, 

ignition of fuel vapors, and consequent 

fire or explosion. 

DATES: This AD becomes effective 

November 1, 2005. 

ADDRESSES: You may examine the AD 

docket on the Internet at http:// 

dms.dot.gov or in person at the Docket 

Management Facility, U.S. Department 

of Transportation, 400 Seventh Street 

SW., Nassif Building, room PL–401, 

Washington, DC. 

Contact Boeing Commercial 

Airplanes, PO Box 3707, Seattle, 

Washington 98124–2207, for service 

information identified in this AD.