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. 

56350 Federal Register / Vol. 70, No. 186 / Tuesday, September 27, 2005 / Rules and Regulations 

FOR FURTHER INFORMATION CONTACT: 

Sulmo Mariano, Aerospace Engineer, 

Propulsion Branch, ANM–140S, FAA, 

Seattle Aircraft Certification Office, 

1601 Lind Avenue, SW., Renton, 

Washington 98055–4056; telephone 

(425) 917–6501; fax (425) 917–6590. 

SUPPLEMENTARY INFORMATION: 

Examining the Docket 

You may examine the airworthiness 

directive (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 street address stated in the 

ADDRESSES section. 

Discussion 

The FAA issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to include an AD that would 

apply to all Boeing Model 707 airplanes, 

and all Boeing Model 720 and 720B 

series airplanes. That NPRM was 

published in the Federal Register on 

April 1, 2005 (70 FR 16767). That NPRM 

proposed to require 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. 

Comments 

We provided the public the 

opportunity to participate in the 

development of this AD. We have 

considered the comments received. 

Support for the AD 

One commenter supports the AD. 

Request to Change Airplane Flight 

Manual (AFM) Wording to be Similar to 

Other AFMs 

The commenter, the airplane 

manufacturer, requests that we revise 

the wording for the AFM revision that 

is specified in paragraph (f) of the 

NPRM. The commenter states that the 

wording should be changed to agree 

with the wording in an FAA-approved 

AFM, and to be similar to the AFM 

wording for other Boeing airplane 

models. 

We agree with the commenter. The 

wording in the AFM revision should 

agree with the previously approved 

AFM and be similar to the AFM 

wording for other Boeing airplane 

models. These changes will reduce 

confusion and provide the greatest 

clarity for the AFM revision. We have 

revised paragraph (f) of the final rule to 

include the commenter’s requested 

changes. However, operators that have 

previously incorporated the information 

in Approval Reference Number 045151 

of the Boeing Model 707 AFM, dated 

December 6, 2004, are not required to 

change the AFM. That exclusion is 

noted in revised wording in paragraph 

(g) of the final rule that emphasizes 

previous accomplishment of this 

revision. 

Request to Include Sentences for 

Ground Operations and Flight 

Operations in AFM Revision 

The same commenter requests that we 

revise the first paragraph of the AFM 

revision specified in paragraph (f) of the 

NPRM to include two sentences 

regarding resetting the circuit breaker: 

one for the flight case and one for the 

ground case. The commenter states that 

the proposed change in wording would 

allow the circuit breaker to be reset 

during ground operations after 

maintenance has determined it is safe to 

do so. The commenter states that the 

proposed change is currently provided 

in most flightcrew operations manuals 

(FCOMs). 

We do not agree with the commenter. 

We met with the commenter on June 30, 

2005, to discuss this comment and our 

response to it. During the meeting we 

discussed the fact that the AFM 

provides limitations for flightcrews to 

follow during flight operations. The 

proposed change to the AFM would put 

the flightcrew in the role of 

maintenance by allowing the flightcrew 

to reset a tripped circuit breaker during 

ground operations. It is more 

appropriate to incorporate ground 

limitations (and warnings) in the 

airplane maintenance manual (AMM) 

rather than the AFM, to ensure that 

these procedures are done by 

maintenance personnel. We also 

discussed that the procedures in the 

FAA-approved AFM take priority over 

the FCOM, which is not FAA-approved. 

During the meeting, the commenter 

stated that, if the proposed changes are 

not made, it would revise the FCOM to 

prohibit resetting the fuel pump circuit 

breakers both in-flight and on the 

ground. We are considering additional 

rulemaking to revise the Airworthiness 

Limitations section of the AMM to 

ensure that maintenance does not reset 

the circuit breaker until it is safe to do 

so. We have not changed the final rule 

in this regard. 

Explanation of Change in Applicability 

We have revised the applicability of 

the AD to identify the model 

designations as published in the most 

recent type certificate data sheet for the 

affected models. 

Clarification of Alternative Method of 

Compliance (AMOC) Paragraph 

We have revised this action to clarify 

the appropriate procedure for notifying 

the principal inspector before using any 

approved AMOC on any airplane to 

which the AMOC applies. 

Conclusion 

We have carefully reviewed the 

available data, including the comments 

received, and determined that air safety 

and the public interest require adopting 

the AD with the changes described 

previously. We have determined that 

these changes will neither increase the 

economic burden on any operator nor 

increase the scope of the AD. 

Costs of Compliance 

There are about 225 airplanes of the 

affected design in the worldwide fleet. 

The following table provides the 

estimated costs for U.S. operators to 

comply with this AD. 

ESTIMATED COSTS

Action Work hours Average labor 

rate per hour Parts Cost per airplane 

Number of 

U.S.-registered 

airplanes 

Fleet cost 

Revising AFM ........................................ 1 $65 None ................. $65 90 $5,850 

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. 

Federal Register / Vol. 70, No. 186 / Tuesday, September 27, 2005 / Rules and Regulations 56351 

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 this AD: 

(1) Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866; 

(2) Is not a ‘‘significant rule’’ under 

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 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, 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): 

2005–20–02 Boeing: Amendment 39–14295. 

Docket No. FAA–2005–20785; 

Directorate Identifier 2005–M–002–AD. 

Effective Date 

(a) This AD becomes effective November 1, 

2005. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to all Boeing Model 

707–100 long body, –200, –100B long body, 

and –100B short body series airplanes; Model 

707–300, –300B, –300C, and –400 series 

airplanes; and Model 720 and 720B series 

airplanes; certificated in any category. 

Unsafe Condition 

(d) 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. 

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. 

Airplane Flight Manual (AFM) Revisions 

(f) Within 30 days after the effective date 

of this AD: Revise the Limitations section of 

the Boeing 707 AFM to include the following 

information. This may be done by inserting 

a copy of this AD into the AFM. Thereafter, 

operate the airplane in accordance with the 

limitations specified in these AFM revisions. 

‘‘Fuel Pumps 

For ground and flight operations, a fuel 

pump circuit breaker which has tripped must 

not be reset. 

Center Tank Fuel Pumps 

Center tank fuel pumps must be ‘OFF’

unless personnel are available in the flight 

deck to monitor low pressure lights. 

Each center tank fuel pump switch must be 

positioned to ‘OFF’ without delay when the 

respective center tank fuel pump low 

pressure light illuminates.’’

Note 1: When information identical to that 

in paragraph (f) of this AD has been included 

in the general revision of the AFM, the 

general revision may be inserted into the 

AFM, and the copy of this AD may be 

removed from the AFM. 

Actions Accomplished Previously 

(g) Incorporation of the information in 

Approval Reference Number 045151 of the 

Boeing Model 707 Airplane Flight Manual 

before the effective date of this AD is 

considered acceptable for compliance with 

the corresponding action specified in this 

AD. 

Alternative Methods of Compliance 

(AMOCs) 

(h)(1) The Manager, Seattle Aircraft 

Certification Office, 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. 

(3) 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. 

Material Incorporated by Reference 

(i) None. 

Issued in Renton, Washington, on 

September 16, 2005. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 05–19140 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–2005–20627; Directorate 

Identifier 2004–NM–39–AD; Amendment 39–

14290; AD 2005–19–25] 

RIN 2120–AA64 

Airworthiness Directives; Boeing 

Model 737–100, –200, –200C, –300, 

–400, and –500 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 certain 

Boeing Model 737–100, –200, –200C, 

–300, –400, and –500 series airplanes. 

This AD requires repetitive eddy current 

inspections for cracks of the 

countersunk rivet holes in the lower 

lobe, adjacent to the radio altimeter 

cutouts; additional inspections, for 

certain airplanes, for cracks and/or 

corrosion; and further investigative and 

corrective action if any crack is found. 

This AD also provides an optional 

terminating action for the repetitive 

inspections. This AD results from 

reports of cracks in the fuselage skin of 

the lower lobe. We are issuing this AD 

to detect and correct fatigue cracks of 

the countersunk rivet holes, which 

could result in cracks of the fuselage