Federal Register / Vol. 75, No. 239 / Tuesday, December 14, 2010 / Proposed Rules 77793 

alternative methods of compliance with the 

corresponding requirements of this AD. 

Compliance time extensions approved 

previously in accordance with AD 2000–11– 

06 are not approved as alternative methods 

of compliance for the compliance times 

required by paragraph (l) of this AD. 

Issued in Renton, Washington, on 

November 15, 2010. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2010–31371 Filed 12–13–10; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–1158; Directorate 

Identifier 2010–NM–125–AD] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Model 747 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 

747 airplanes. The existing AD currently 

requires repetitive inspections to detect 

damage of the sleeving and wire 

bundles of the boost pumps of the 

numbers 1 and 4 main fuel tanks, and 

of the auxiliary tank jettison pumps (if 

installed); replacement of any damaged 

sleeving with new sleeving; and repair 

or replacement of any damaged wires 

with new wires. For airplanes on which 

any burned wires are found, the existing 

AD also requires an inspection to detect 

damage of the conduit, and replacement 

of any damaged conduit with a 

serviceable conduit. This proposed AD 

would reduce the initial compliance 

time and repetitive inspection interval 

in the existing AD. This proposed AD 

results from fleet information indicating 

that the repetitive inspection interval in 

the existing AD is too long because 

excessive chafing of the sleeving 

continues to occur much earlier than 

expected between scheduled 

inspections. We are proposing this AD 

to detect and correct abrasion of the 

Teflon sleeving and wires in the 

bundles of the fuel boost pumps for the 

numbers 1 and 4 main fuel tanks and of 

the auxiliary tank jettison pumps (if 

installed), which could result in 

electrical arcing between the wires and 

aluminum conduit and consequent fire 

or explosion of the fuel tank. 

DATES: We must receive comments on 

this proposed AD by January 28, 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 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 

(telephone 800–647–5527) is in the 

ADDRESSES section. Comments will be 

available in the AD docket shortly after 

receipt. 

FOR FURTHER INFORMATION CONTACT: Jon 

Regimbal, Aerospace Engineer, 

Propulsion Branch, ANM–140S, FAA, 

Seattle Aircraft Certification Office, 

1601 Lind Avenue SW., Renton, 

Washington 98057–3356; telephone 

(425) 917–6506; fax (425) 917–6590. 

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–2010–1158; Directorate Identifier 

2010–NM–125–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 

On December 9, 1997, we issued AD 

97–26–07, Amendment 39–10250 (62 

FR 65352, December 12, 1997), for all 

Model 747 airplanes. That AD currently 

requires repetitive inspections to detect 

damage of the sleeving and wire 

bundles of the boost pumps of the 

numbers 1 and 4 main fuel tanks, and 

of the auxiliary tank jettison pumps (if 

installed); replacement of any damaged 

sleeving with new sleeving; and repair 

or replacement of any damaged wires 

with new wires. For airplanes on which 

any burned wires are found, that AD 

also requires an inspection to detect 

damage of the conduit, and replacement 

of any damaged conduit with a 

serviceable conduit. That AD resulted 

from reports of chafing of the sleeving. 

We issued that AD to detect and correct 

abrasion of the Teflon sleeving and 

wires in the bundles of the fuel boost 

pumps for the numbers 1 and 4 main 

fuel tanks and of the auxiliary tank 

jettison pumps (if installed), which 

could result in electrical arcing between 

the wires and the aluminum conduit 

and consequent fire or explosion of the 

fuel tank. 

Actions Since Existing AD Was Issued 

Since we issued AD 97–26–07, we 

received fleet information from the 

manufacturer indicating that excessive 

chafing of the sleeving continues to 

occur much earlier than expected 

between scheduled inspections. Due to 

that fact, the manufacturer has revised 

the service information to reduce the 

repetitive inspection intervals. 

Relevant Service Information 

We have reviewed Boeing Alert 

Service Bulletin 747–28A2204, Revision 

3, dated March 11, 2010. The service 

information reduces the initial 

compliance time and repetitive 

inspection interval for detecting damage 

WReier-Aviles on DSKGBLS3C1PROD with PROPOSALS

77794 Federal Register / Vol. 75, No. 239 / Tuesday, December 14, 2010 / Proposed Rules 

of the sleeving and wire bundles of the 

boost pumps of the numbers 1 and 4 

main fuel tanks, and of the auxiliary 

tank jettison pumps (if installed) 

specified in Boeing Service Bulletin 

747–28A2204, Revision 1, dated 

October 30, 1997. Revision 1 of this 

service bulletin was referred to in AD 

97–26–07 as the appropriate source of 

service information for accomplishing 

the specified actions. The actions 

described in Revision 3 of this service 

bulletin are essentially the same as 

those described in Revision 1 of this 

service bulletin. 

FAA’s Determination and Requirements 

of the Proposed AD 

We have evaluated all pertinent 

information and identified an unsafe 

condition that is likely to develop on 

other airplanes of the same type design. 

For this reason, we are proposing this 

AD, which would supersede AD 97–26– 

07 and would retain the requirements of 

the existing AD at reduced compliance 

times. 

Change to Existing AD 

This proposed AD would retain all 

requirements of AD 97–26–07. Since AD 

97–26–07 was issued, the AD format has 

been revised, and certain paragraphs 

have been rearranged. As a result, the 

corresponding paragraph identifiers 

have changed in this proposed AD, as 

listed in the following table: 

REVISED PARAGRAPH IDENTIFIERS

Requirement in AD 

97-26-07 

Corresponding 

requirement in 

this proposed 

AD 

paragraph (a) ..................... paragraph (g). 

paragraph (b) ..................... paragraph (h). 

paragraph (c) ..................... paragraph (i). 

paragraph (d) ..................... paragraph (j). 

paragraph (e) ..................... paragraph (k). 

paragraph (f) ...................... paragraph (l). 

paragraph (g) ..................... paragraph (m). 

Costs of Compliance 

There are about 772 airplanes of the 

affected design in the worldwide fleet. 

This proposed AD would affect about 

215 airplanes of U.S. registry. The new 

requirements of this proposed AD add 

no additional economic burden. The 

current costs for this proposed AD are 

repeated below for the convenience of 

affected operators. 

The actions that are required by AD 

97–26–07 and retained in this proposed 

AD take about 4 work-hours per 

airplane, at an average labor rate of $85 

per work-hour. Based on these figures, 

the estimated cost of the currently 

required actions is $73,100, or $340 per 

airplane, per inspection cycle. 

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 

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 that the 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. 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. 

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 

removing Amendment 39–10250 (62 FR 

65352, December 12, 1997) and adding 

the following new AD: 

The Boeing Company: Docket No. FAA– 

2010–1158; Directorate Identifier 2010– 

NM–125–AD. 

Comments Due Date 

(a) The FAA must receive comments on 

this AD action by January 28, 2011. 

Affected ADs 

(b) This AD supersedes AD 97–26–07, 

Amendment 39–10250. 

Applicability 

(c) This AD applies to all The Boeing 

Company Model 747–100, –100B, –100B 

SUD, –200B, –200C, –200F, –300, –400, 

–400D, –400F, 747SR, and 747SP series 

airplanes, certificated in any category. 

Subject 

(d) Air Transport Association (ATA) of 

America Code 28: Fuel. 

Unsafe Condition 

(e) This AD results from fleet information 

indicating that the repetitive inspection 

interval in the existing AD is too long 

because excessive chafing of the sleeving 

continues to occur much earlier than 

expected between scheduled inspections. 

The Federal Aviation Administration is 

issuing this AD to detect and correct abrasion 

of the Teflon sleeving and wires in the 

bundles of the fuel boost pumps for the 

numbers 1 and 4 main fuel tanks and of the 

auxiliary tank jettison pumps (if installed), 

which could result in electrical arcing 

between the wires and aluminum conduit 

and consequent fire or explosion of the fuel 

tank. 

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. 

Restatement of Requirements of AD 96–26– 

06, Amendment 39–9870 

Inspections/Repair or Replace if Necessary 

(g) Perform an initial inspection to detect 

damage of the sleeving and wire bundles of 

the forward and aft boost pumps of the 

numbers 1 and 4 main fuel tanks, and of the 

wire bundles of the auxiliary tank jettison 

pumps (if installed), in accordance with 

Boeing Service Bulletin 747–28A2204, dated 

December 19, 1996, or Revision 1, dated 

October 30, 1997; or Boeing Alert Service 

Bulletin 747–28A2204, Revision 3, dated 

March 11, 2010, at the time specified in 

paragraph (g)(1) or (g)(2) of this AD, as 

applicable. After the effective date of this AD, 

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Federal Register / Vol. 75, No. 239 / Tuesday, December 14, 2010 / Proposed Rules 77795 

only Revision 3 of Boeing Alert Service 

Bulletin 747–28A2204 may be used. 

(1) For airplanes having line numbers 001 

through 432 inclusive: Inspect within 120 

days after January 21, 1997 (the effective date 

of AD 96–26–06, amendment 39–9870, which 

was superseded by AD 97–26–07). 

(2) For airplanes having line numbers 433 

and subsequent: Inspect at the later of the 

times specified in paragraphs (g)(2)(i) or 

(g)(2)(ii) of this AD. 

(i) Prior to the accumulation of 20,000 

flight cycles or 60,000 flight hours, 

whichever occurs first; or 

(ii) Within 120 days after December 29, 

1997 (the effective date of AD 97–26–07). 

(h) Repeat the inspection required by 

paragraph (g) of this AD at intervals not to 

exceed 20,000 flight cycles or 60,000 flight 

hours since the last inspection, whichever 

occurs first, until the first inspection required 

by paragraph (n) of this AD has been 

accomplished. 

(i) If any damaged sleeving is found, prior 

to further flight, replace the sleeving with 

new sleeving, in accordance with Boeing 

Service Bulletin 747–28A2204, dated 

December 19, 1996, or Revision 1, dated 

October 30, 1997; or Boeing Alert Service 

Bulletin 747–28A2204, Revision 3, dated 

March 11, 2010. After the effective date of 

this AD, only Revision 3 of Boeing Alert 

Service Bulletin 747–28A2204 may be used. 

(j) If any damaged wire is found, prior to 

further flight, repair or replace the wire with 

a new wire, in accordance with Boeing 

Service Bulletin 747–28A2204, dated 

December 19, 1996, or Revision 1, dated 

October 30, 1997; or Boeing Alert Service 

Bulletin 747–28A2204, Revision 3, dated 

March 11, 2010. After the effective date of 

this AD, only Revision 3 of Boeing Alert 

Service Bulletin 747–28A2204 may be used. 

(k) If any burned wire is found, prior to 

further flight, perform an inspection to detect 

damage of the conduit, in accordance with 

Boeing Service Bulletin 747–28A2204, dated 

December 19, 1996, or Revision 1, dated 

October 30, 1997; or Boeing Alert Service 

Bulletin 747–28A2204, Revision 3, dated 

March 11, 2010. If any damage is found, prior 

to further flight, replace the conduit with a 

serviceable conduit, in accordance with 

Boeing Service Bulletin 747–28A2204, dated 

December 19, 1996, or Revision 1, dated 

October 30, 1997; or Boeing Alert Service 

Bulletin 747–28A2204, Revision 3, dated 

March 11, 2010. After the effective date of 

this AD, only Revision 3 of Boeing Alert 

Service Bulletin 747–28A2204 may be used. 

(l) For airplanes having line numbers 433 

and subsequent: Within 14 days after 

accomplishing the initial inspection required 

by paragraph (g) of this AD, submit a report 

of any damaged sleeving (i.e., holes, breaks, 

cuts, splits), damaged wire (i.e., worn or 

cracked insulation, exposed conductor, 

indication of arcing/burning), or damaged 

conduit to the Manager, Seattle Aircraft 

Certification Office (ACO), FAA, Transport 

Airplane Directorate, 1601 Lind Avenue, 

SW., Renton, WA 98057–3356; fax (425) 227– 

1181. The report shall include the 

information specified in paragraphs (l)(1), 

(l)(2), (l)(3), (l)(4), and (l)(5) of this AD. 

Information collection requirements 

contained in this regulation have been 

approved by the Office of Management and 

Budget (OMB) under the provisions of the 

Paperwork Reduction Act of 1980 (44 U.S.C. 

3501 et seq.) and have been assigned OMB 

Control Number 2120–0056. 

(1) The airplane serial number. 

(2) The total hours’ time-in-service 

accumulated on the airplane. 

(3) The total number of flight cycles 

accumulated on the airplane. 

(4) A description of any damage found. 

(5) The location of where the damaged part 

was installed. 

(m) For airplanes having line numbers 433 

and subsequent: Within 14 days after 

accomplishing the initial inspection required 

by paragraph (g) of this AD, submit any 

damaged part to the Manager, Seattle ACO. 

The damaged part shall be tagged to include 

the information specified in paragraphs (l)(1), 

(l)(2), (l)(3), (l)(4), and (l)(5) of this AD. 

Additionally, operators shall align the inner 

sleeving, outer sleeving, and wire as installed 

in the airplane, and secure the sleeving and 

wiring in place by taping or other means 

when submitting the damaged part to the 

Manager, Seattle ACO. Information collection 

requirements contained in this regulation 

have been approved by the OMB under the 

provisions of the Paperwork Reduction Act of 

1980 (44 U.S.C. 3501 et seq.) and have been 

assigned OMB Control Number 2120–0056. 

New Reduced Inspection Intervals 

Repetitive Inspections 

(n) Do the next inspection required by 

paragraph (h) of this AD at the time specified 

in paragraph (n)(1) or (n)(2) of this AD, as 

applicable, in accordance with Boeing Alert 

Service Bulletin 747–28A2204, Revision 3, 

dated March 11, 2010. Repeat the inspection 

thereafter at intervals not to exceed 15,000 

flight hours. Accomplishing the initial 

inspection in this paragraph ends the 

repetitive inspection requirements of 

paragraph (h) of this AD. 

(1) For airplanes on which the inspection 

required by paragraph (g) of this AD has been 

done as of the effective date of this AD: Do 

the inspection at the earlier of the times 

specified in paragraph (n)(1)(i) and (n)(1)(ii) 

of this AD. 

(i) Within 15,000 flight hours after the most 

recent inspection, or within 6,000 flight 

hours after the effective date of this AD, 

whichever occurs later. 

(ii) Within 20,000 flight cycles or 60,000 

flight hours after the most recent inspection 

required by paragraph (g) or (h) of this AD, 

whichever occurs first. 

(2) For airplanes on which the inspection 

required by paragraph (g) of this AD has not 

been done as of the effective date of this AD: 

Do the inspection before the accumulation of 

15,000 total flight hours, or within 6,000 

flight hours after the effective date of this AD, 

whichever occurs later. 

Paperwork Reduction Act Burden Statement 

(o) 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) 

(p)(1) The Manager, Seattle ACO, 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: Jon 

Regimbal, Aerospace Engineer, Propulsion 

Branch, ANM–140S, FAA, Seattle Aircraft 

Certification Office, 1601 Lind Avenue, SW., 

Renton, Washington 98057–3356; telephone 

(425) 917–6506; fax (425) 917–6590. 

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

(2) To request a different method of 

compliance or a different compliance time 

for this AD, follow the procedures in 14 CFR 

39.19. 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. 

(3) AMOCs approved previously in 

accordance with AD 97–26–07, Amendment 

39–10250, are approved as alternative 

methods of compliance with the 

corresponding requirements of this AD. 

Compliance time extensions approved 

previously in accordance with AD 97–26–07, 

are not approved as alternative methods of 

compliance for the compliance times 

required by paragraph (n) of this AD. 

Issued in Renton, Washington, on 

November 15, 2010. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2010–31375 Filed 12–13–10; 8:45 am] 

BILLING CODE 4910–13–P 

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