This section of the FEDERAL REGISTER

contains notices to the public of the proposed

issuance of rules and regulations. The

purpose of these notices is to give interested

persons an opportunity to participate in the

rule making prior to the adoption of the final

rules.

Proposed Rules Federal Register

69718

Vol. 65, No. 224

Monday, November 20, 2000

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000–NM–158–AD]

RIN 2120–AA64

Airworthiness Directives; Boeing

Model 747 Series Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Notice of proposed rulemaking

(NPRM).

SUMMARY: This document proposes the

supersedure of an existing airworthiness

directive (AD), applicable to all Boeing

Model 747 series airplanes, that

currently requires revising the Airplane

Flight Manual to include procedures to

prevent dry operation of the center wing

fuel tank override/jettison pumps and,

for certain airplanes, to prohibit

operation of the horizontal stabilizer

tank transfer pumps in-flight. That AD

was prompted by a report indicating

that several override/jettison fuel pumps

from the center wing tanks and main

tanks had been removed because circuit

breakers for the override/jettison fuel

pumps were tripped, or low pump

output pressure was indicated. For

certain airplanes, this action would

require installation of improved fuel

pumps, which would terminate the

requirements of the existing AD. This

proposal is prompted by new

information received from the fuel

pump manufacturer. The actions

specified by the proposed AD are

intended to prevent contact between the

rotating paddle wheel and the stationary

end plates within the center wing tank

override/jettison fuel pumps or

horizontal stabilizer tank transfer

pumps, which could cause sparks and/

or a hot surface condition and

consequent ignition of fuel vapor in the

center wing tank or horizontal stabilizer

tank during dry pump operation (no fuel

flowing).

DATES: Comments must be received by

January 4, 2001.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, ANM–114,

Attention: Rules Docket No. 2000–NM–

158–AD, 1601 Lind Avenue, SW.,

Renton, Washington 98055–4056.

Comments may be inspected at this

location between 9:00 a.m. and 3:00

p.m., Monday through Friday, except

Federal holidays. Comments may be

submitted via fax to (425) 227–1232.

Comments may also be sent via the

Internet using the following address: 9-

anm-nprmcomment@faa.gov. Comments

sent via fax or the Internet must contain

‘‘Docket No. 2000–NM–158–AD’’ in the

subject line and need not be submitted

in triplicate. Comments sent via the

Internet as attached electronic files must

be formatted in Microsoft Word 97 for

Windows or ASCII text.

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) 227–2686; fax (425) 227–1181.

SUPPLEMENTARY INFORMATION:

Comments Invited

Interested persons are invited to

participate in the making of the

proposed rule by submitting such

written data, views, or arguments as

they may desire. Communications shall

identify the Rules Docket number and

be submitted in triplicate to the address

specified above. All communications

received on or before the closing date

for comments, specified above, will be

considered before taking action on the

proposed rule. The proposals contained

in this action may be changed in light

of the comments received.

Submit comments using the following

format:

• Organize comments issue-by-issue.

For example, discuss a request to

change the compliance time and a

request to change the service bulletin

reference as two separate issues.

• For each issue, state what specific

change to the proposed AD is being

requested.

• Include justification (e.g., reasons or

data) for each request.

Comments are specifically invited on

the overall regulatory, economic,

environmental, and energy aspects of

the proposed rule. All comments

submitted will be available, both before

and after the closing date for comments,

in the Rules Docket for examination by

interested persons. A report

summarizing each FAA-public contact

concerned with the substance of this

proposal will be filed in the Rules

Docket.

Commenters wishing the FAA to

acknowledge receipt of their comments

submitted in response to this action

must submit a self-addressed, stamped

postcard on which the following

statement is made: ‘‘Comments to

Docket Number 2000–NM–158–AD.’’

The postcard will be date stamped and

returned to the commenter.

Availability of NPRMs

Any person may obtain a copy of this

NPRM by submitting a request to the

FAA, Transport Airplane Directorate,

ANM–114, Attention: Rules Docket No.

2000–NM–158–AD, 1601 Lind Avenue,

SW., Renton, Washington 98055–4056.

Discussion

On December 15, 1998, the FAA

issued AD 98–25–52, amendment 39–

10957 (63 FR 71214, December 24,

1998), applicable to all Boeing Model

747 series airplanes, to require revising

the Airplane Flight Manual to include

procedures to prevent dry operation of

the center wing fuel tank override/

jettison pumps and, for certain

airplanes, to prohibit operation of the

horizontal stabilizer tank transfer

pumps in-flight. That action was

prompted by a report indicating that

several override/jettison fuel pumps

from the center wing tanks and main

tanks had been removed because circuit

breakers for the override/jettison fuel

pumps were tripped, or low pump

output pressure was indicated. The

requirements of that AD are intended to

prevent contact between the rotating

paddle wheel and the stationary end

plates within the center wing tank

override/jettison fuel pumps or

horizontal stabilizer tank transfer

pumps due to excessive wear of the

pump shaft carbon thrust bearing,

which could cause sparks and/or a hot

surface condition and consequent

ignition of fuel vapor in the center wing

tank or horizontal stabilizer tank during

dry pump operation (no fuel flowing).

Federal Register / Vol. 65, No. 224 / Monday, November 20, 2000 / Proposed Rules 69719

Actions Since Issuance of Previous Rule

In the preamble to AD 98–25–52, the

FAA indicated that the actions required

by that AD were considered ‘‘interim

action’’ and that further rulemaking

action was being considered. The FAA

now has determined that further

rulemaking action is indeed necessary,

and this proposed AD follows from that

determination.

Since the issuance of AD 98–25–52,

the FAA has received information from

the fuel pump manufacturer indicating

that it has now determined the cause of

the premature wear of the thrust carbon

bearings of the center wing tank

override/jettison fuel pumps, and the

horizontal stabilizer tank transfer

pumps. The thrust washer located in the

pump shaft thrust bearing was coated

with aluminum oxide, applied using a

plasma spray method, and investigation

revealed that this method has a life limit

of less than 500 flight hours. Further

investigation revealed that aluminum

oxide coating applied to the thrust

washer using a D-gun spray method has

a life limit of more than 15,000 flight

hours.

During operation at normal fuel pump

rotation speeds (7,000 to 8,000 RPM),

the steel-to-steel contact may produce

sparks or hot spots sufficient to ignite

fuel vapor from the center wing tank or

horizontal stabilizer tank, when the

pump is running dry. The center wing

fuel tank pumps on 747–400 series

airplanes are normally operated until

the fuel in the tank is exhausted and the

pump inlet is uncovered, exposing the

fuel pump to dry or partially dry

operation for a period of time during

each flight when the center wing tank is

used. The horizontal stabilizer tank on

747–400 series airplanes uses the same

pumps and is also run out dry each time

it is used. Replacement of the existing

pumps with improved pumps having

the correct thrust washers installed

enhances airplane safety in that it

eliminates the possibility that pumps

with bad washers will be operated when

the pump is running dry.

Explanation of Requirements of

Proposed Rule

Since an unsafe condition has been

identified that is likely to exist or

develop on other products of this same

type design, the proposed AD would

supersede AD 98–25–52 to continue to

require revising the Airplane Flight

Manual to include procedures to

prevent dry operation of the center wing

fuel tank override/jettison pumps and,

for certain airplanes, to prohibit

operation of the horizontal stabilizer

tank transfer pumps in-flight. For

certain airplanes, the proposed AD also

would require the installation of

improved fuel pumps, which would

terminate the requirements of the

existing AD.

Cost Impact

There are approximately 1,100 Model

747 series airplanes of the affected

design in the worldwide fleet. The FAA

estimates that 250 airplanes of U.S.

registry would be affected by this

proposed AD.

The AFM revisions that are currently

required by AD 98–25–52 take

approximately 1 work hour per airplane

to accomplish, at an average labor rate

of $60 per work hour. Based on these

figures, the cost impact of the currently

required actions on U.S. operators is

estimated to be $15,000, or $60 per

airplane.

The replacements that are proposed in

this new AD action would take

approximately 25 work hours per

airplane to accomplish, at an average

labor rate of $60 per work hour.

Required parts would be provided by

the manufacturer at no cost to the

operators. Based on these figures, the

cost impact of the proposed

requirements of this AD on U.S.

operators is estimated to be $375,000, or

$1,500 per airplane.

The cost impact figures discussed

above are based on assumptions that no

operator has yet accomplished any of

the proposed requirements of this AD

action, and that no operator would

accomplish those actions in the future if

this AD were not adopted. The cost

impact figures discussed in AD

rulemaking actions represent only the

time necessary to perform the specific

actions actually required by the AD.

These figures typically do not include

incidental costs, such as the time

required to gain access and close up,

planning time, or time necessitated by

other administrative actions.

Regulatory Impact

The regulations proposed herein

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. Therefore,

it is determined that this proposal

would not have federalism implications

under Executive Order 13132.

For the reasons discussed above, I

certify that 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) if

promulgated, 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. A copy of the draft

regulatory evaluation prepared for this

action is contained in the Rules Docket.

A copy of it may be obtained by

contacting the Rules Docket at the

location provided under the caption

ADDRESSES.

List of Subjects in 14 CFR Part 39

Air transportation, Aircraft, Aviation

safety, Safety.

The Proposed Amendment

Accordingly, pursuant to the

authority delegated to me by the

Administrator, the Federal Aviation

Administration proposes to amend part

39 of the Federal Aviation Regulations

(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. Section 39.13 is amended by

removing amendment 39–10957 (63 FR

71214, December 24, 1998), and by

adding a new airworthiness directive

(AD), to read as follows:

Boeing: Docket 2000–NM–158–AD.

Supersedes AD 98–25–52, amendment

39–10957.

Applicability: All Model 747 series

airplanes, certificated in any category.

Note 1: This AD applies to each airplane

identified in the preceding applicability

provision, regardless of whether it has been

modified,altered, or repaired in the area

subject to the requirements of this AD. For

airplanes that have been modified, altered, or

repaired so that the performance of the

requirements of this AD is affected, the

owner/operator must request approval for an

alternative method of compliance in

accordance with paragraph (d)(1) of this AD.

The request should include an assessment of

the effect of the modification, alteration, or

repair on the unsafe condition addressed by

this AD; and, if the unsafe condition has not

been eliminated, the request should include

specific proposed actions to address it.

Compliance: Required as indicated, unless

accomplished previously.

To prevent contact between the rotating

paddle wheel and the stationary end plates

within the center wing tank override/jettison

fuel pumps or horizontal stabilizer tank

transfer pumps due to excessive wear of the

pump shaft carbon thrust bearing, which can

cause sparks and/or a hot surface condition

and consequent ignition of fuel vapor in the

center wing tank or horizontal stabilizer tank

during dry pump operation (no fuel flowing),

accomplish the following:

69720 Federal Register / Vol. 65, No. 224 / Monday, November 20, 2000 / Proposed Rules

Restatement of Requirements of AD 98–25–

52

Airplane Flight Manual (AFM) Revisions

(a) Within 7 days after December 29, 1998

(the effective date of AD 98–25–52,

amendment 39–10957), revise the

Limitations Section of the FAA-approved

AFM to include the following procedures.

This may be accomplished by inserting a

copy of this AD into the AFM.

‘‘For Model 747–400 series airplanes

equipped with a horizontal stabilizer tank,

operation of the horizontal stabilizer tank

transfer pumps is prohibited in flight.

A tripped circuit breaker of a center wing

tank override/jettison pump or a tripped

circuit breaker of a horizontal stabilizer tank

transfer pump must not be reset until the

associated fuel pump has been inspected for

damage and any damage has been repaired.

The center wing tank override/jettison

pumps must be operated in accordance with

either option 1 or option 2 below.

Option 1

If the center wing tank override/jettison

pumps are required for flight, the center tank

must contain a minimum of 17,000 pounds

(7,700 kilograms) at engine start. The fuel

quantity indicating system of the center wing

tank must be operative to dispatch with

center wing tank fuel intended for use in the

flight.

Select both center wing tank override/

jettison pump switches off at or before the

fuel quantity of the center wing tank reaches

7,000 pounds (3,200 kilograms). Note: On

Model 747–400 series airplanes, the ‘‘FUEL

OVRD CTR L’’ and ‘‘FUEL OVRD CTR R’’

engine indication and crew alerting system

(EICAS) messages will be displayed with the

switches off.

The center wing tank override/jettison

pumps may be operated with less than 7,000

pounds of fuel in the center wing tank if

required to address an emergency (such as

fuel jettison or low fuel quantity).

Option 2

If the center wing tank override/jettison

pumps are required for flight, the center tank

must contain a minimum of 50,000 pounds

(22,700 kilograms) at engine start. The fuel

quantity indicating system of the center wing

tank must be operative to dispatch with

center wing tank fuel intended for use in the

flight.

Select both center wing tank override/

jettison pump switches off at or before center

wing tank fuel quantity reaches 3,000 pounds

(1,400 kilograms).

The center wing tank override/jettison

pumps may be operated with less than 3,000

pounds of fuel in the center wing tank if

required to address an emergency (such as

fuel jettison or low fuel quantity).’’

New Requirements of This AD

Determination of Correct Thrust Washer

(b) For airplanes having center wing fuel

tank override/jettison pumps and, if

installed, horizontal stabilizer tank transfer

pumps, and all pumps meet the criteria

specified in paragraph (b)(1), (b)(2), or (b)(3)

of this AD (i.e., the correct thrust washer is

installed), no further action is required by

this AD.

(1) Verify the serial number on the pump

data plate. The first four digits of the pump

serial number represent the month and year

of manufacture (e.g., 0697 indicates a pump

manufactured in June 1997). If the serial

number date code indicates that the pump

was manufactured prior to July 1996, or after

November 1998, and if the operator can

determine that the pump was not overhauled

or repaired after July 31, 1996, then the pump

has the correct thrust washer installed. If the

pump was overhauled or repaired after July

31, 1996, and the operator has maintenance/

overhaul records showing that the thrust

washer was not replaced, or was replaced

with the correct thrust washer, as specified

in paragraph (c) of this AD, then the pump

has the correct thrust washer installed.

(2) For airplanes having a date of

manufacture prior to July 1996, if the

operator can determine that the pump was

not overhauled or repaired after July 31,

1996; and the pump was not replaced with

a new pump manufactured between July

1996 and November 1998, then the pump has

the correct thrust washer installed. If the

pump was overhauled or repaired after July

31, 1996, and the operator has maintenance/

overhaul records showing that the thrust

washer was not replaced, or was replaced

with the correct thrust washer, as specified

in paragraph (c) of this AD, then the pump

has the correct thrust washer installed.

(3) For airplanes having pumps installed

containing a serial number on the pump data

plate with the suffix ‘‘P,’’ the pump has the

correct thrust washer installed.

Terminating Action

(c) For airplanes that do not meet the

requirements specified in paragraph (b)(1),

(b)(2), or (b)(3) of this AD; or if the serial

number on the pump data plate of any fuel

pump cannot be determined: Within 24

months after the effective date of this AD,

replace the applicable center wing fuel tank

override/jettison pumps and horizontal

stabilizer tank transfer pumps with Crane

Hydro-Aire fuel pumps having a thrust

washer, part number 60–06561, with a date

code of 9848 (‘‘98’’ indicates the year 1998,

and ‘‘48’’ indicates the 48th week in 1998),

or higher, etched on the outside diameter of

the thrust washer. Accomplishment of this

paragraph terminates the requirements of

paragraph (a) of this AD.

Alternative Methods of Compliance

(d)(1) An alternative method of compliance

(AMOC) or adjustment of the compliance

time that provides an acceptable level of

safety may be used if approved by the

Manager, Seattle Aircraft Certification Office

(ACO), FAA. Operators shall submit their

requests through an appropriate FAA

Principal Operations Inspector or Principal

Maintenance Inspector, as applicable, who

may add comments and then send it to the

Manager, Seattle ACO.

(2) With the exception of FAA AMOC letter

to Boeing (No. 98–140–437, dated December

9, 1998), AMOC’s approved previously in

accordance with AD 98–25–52, amendment

39–10957, are approved as alternative

methods of compliance with paragraph (a) of

this AD.

Note 2: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Seattle ACO.

Special Flight Permits

(e) Special flight permits may be issued in

accordance with sections 21.197 and 21.199

of the Federal Aviation Regulations (14 CFR

21.197 and 21.199) to operate the airplane to

a location where the requirements of this AD

can be accomplished.

Issued in Renton, Washington, on

November 13, 2000.

Donald L. Riggin,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 00–29498 Filed 11–17–00; 8:45 am]

BILLING CODE 4910–13–P

ENVIRONMENTAL PROTECTION

AGENCY

40 CFR Part 52

[TX–114–2–7480; FRL–6904–2]

Approval and Promulgation of Air

Quality State Implementation Plans

(SIP); Texas: Control of Gasoline

Volatility

AGENCY: Environmental Protection

Agency (EPA).

ACTION: Proposed rule.

SUMMARY: We, the EPA, propose to fully

approve a State Implementation Plan

(SIP) revision submitted by the State of

Texas establishing a low-Reid Vapor

Pressure (RVP) fuel requirement for

gasoline distributed in 95 counties in

the eastern and central parts of Texas.

Texas developed this fuel requirement

to reduce emissions of volatile organic

compounds (VOC) as part of the State’s

strategy to achieve the National

Ambient Air Quality Standard (NAAQS)

for ozone in the Houston and DallasFort Worth nonattainment areas. We are

approving Texas’ fuel requirements into

the SIP because we found that the fuel

requirement is in accordance with the

requirements of the Clean Air Act (the

Act) as amended in 1990 and is

necessary for these nonattainment areas

to achieve the ozone NAAQS.

DATES: Comments should be received on

or before December 20, 2000.

ADDRESSES: Written comments on this

action should be addressed to Mr.

Thomas H. Diggs, Chief, Air Planning

Section, at the EPA Regional Office

listed below. Copies of the documents

relevant to this action are available for

public inspection during normal

business hours at the following