This section of the FEDERAL REGISTER

contains regulatory documents having general

applicability and legal effect, most of which

are keyed to and codified in the Code of

Federal Regulations, which is published under

50 titles pursuant to 44 U.S.C. 1510.

The Code of Federal Regulations is sold by

the Superintendent of Documents. Prices of

new books are listed in the first FEDERAL

REGISTER issue of each week.

Rules and Regulations Federal Register

21851

Vol. 66, No. 85

Wednesday, May 2, 2001

DEPARTMENT OF ENERGY

Office of Energy Efficiency and

Renewable Energy

10 CFR Part 490

RIN 1904–AB00

Alternative Fuel Transportation

Program; Biodiesel Fuel Use Credit

AGENCY: Office of Energy Efficiency and

Renewable Energy, Department of

Energy (DOE).

ACTION: Final rule, completion of

regulatory review.

SUMMARY: In accordance with the

memorandum of January 20, 2001, from

the Assistant to the President and Chief

of Staff, entitled ‘‘Regulatory Review

Plan,’’ published in the Federal Register

on January 24, 2001 (66 FR 7702), DOE

temporarily delayed for 60 days (66 FR

8746, February 2, 2001) the effective

date of the final rule entitled

‘‘Alternative Fuel Transportation

Program; Biodiesel Fuel Use Credit’’

published in the Federal Register on

January 11, 2001 (66 FR 2207). DOE has

now completed its review of that

regulation, and does not intend to

initiate any further rulemaking action to

modify its provisions.

DATES: The effective date of the rule

amending 10 CFR part 490 published at

66 FR 2207, January 11, 2001, and

delayed at 66 FR 8746, February 2,

2001, is confirmed as April 13, 2001.

FOR FURTHER INFORMATION CONTACT:

David Rodgers, Office of Energy

Efficiency and Renewable Energy, (202)

586–9118, david.rodgers@hq.doe.gov.

Issued in Washington, DC on April 24,

2001.

Spencer Abraham,

Secretary of Energy.

[FR Doc. 01–10771 Filed 5–1–01; 8:45 am]

BILLING CODE 6450–01–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000–NM–147–AD; Amendment

39–12207; AD 2001–09–02]

RIN 2120–AA64

Airworthiness Directives; Boeing

Model 777–200 Series Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD),

applicable to certain Boeing Model 777–

200 series airplanes, that requires

replacement of certain existing bushings

of the aft trunnion of the outer cylinder

of the main landing gear (MLG) with

new bushings, and replacement of

grease in an undercut on the aft

trunnion, if necessary. The actions

specified by this AD are intended to

prevent stress corrosion cracking and

consequent fracture of the aft trunnion

of the outer cylinder of the MLG, which

could result in collapse of the MLG.

This action is intended to address the

identified unsafe condition.

DATES: Effective June 6, 2001.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of June 6,

2001.

ADDRESSES: The service information

referenced in this AD may be obtained

from Boeing Commercial Airplane

Group, P.O. Box 3707, Seattle,

Washington 98124–2207. This

information may be examined at the

Federal Aviation Administration (FAA),

Transport Airplane Directorate, Rules

Docket, 1601 Lind Avenue, SW.,

Renton, Washington; or at the Office of

the Federal Register, 800 North Capitol

Street, NW., suite 700, Washington, DC.

FOR FURTHER INFORMATION CONTACT: Stan

Wood, Aerospace Engineer, Airframe

Branch, ANM–120S, FAA, Seattle

Aircraft Certification Office, 1601 Lind

Avenue, SW., Renton, Washington

98055–4056; telephone (425) 227–2772;

fax (425) 227–1181.

SUPPLEMENTARY INFORMATION: A

proposal to amend part 39 of the Federal

Aviation Regulations (14 CFR part 39) to

include an airworthiness directive (AD)

that is applicable to certain Boeing

Model 777–200 series airplanes was

published in the Federal Register on

December 29, 2000 (65 FR 82959). That

action proposed to require replacement

of certain existing bushings of the aft

trunnion of the outer cylinder of the

main landing gear (MLG) with new

bushings, and replacement of grease in

an undercut on the aft trunnion, if

necessary.

Comments

Interested persons have been afforded

an opportunity to participate in the

making of this amendment. Due

consideration has been given to the

comments received.

Request To Delete Airplane With Line

Number (L/N) 1

One commenter requests that the

Boeing Model 777 series airplane having

L/N 1 be removed from the applicability

section of the proposed rule. The

commenter states that the main landing

gear on that airplane was reworked prior

to airplane delivery, and the outer

cylinders with the final configuration of

the aft trunnion were installed. The

commenter adds that this rework was

done at the manufacturer per Boeing

Production Revision Record 61571, part

G95. Such rework meets the intent of

Boeing Service Bulletin 777–32–0003,

dated October 9, 1997, which was

specified in the applicability section of

the proposed rule.

The FAA concurs with the

commenter. The FAA has determined

that this airplane was retained by the

manufacturer until delivery to an

operator at the end of the year 2000. The

following changes have been made to

the final rule: The applicability and cost

impact sections have been revised

accordingly; paragraph (a)(3) of the final

rule has been revised to remove the

reference to the airplane having L/N 1;

and Note 3, which specified, ‘‘For the

purposes of this AD, the airplane having

L/N 1 is considered to have the

configuration of a Group 1 airplane,’’

has been removed.

Revised Service Information

The same commenter states that,

subsequent to issuance of the proposed

rule, Boeing Alert Service Bulletin 777–

32A0025, Revision 1, dated March 8,

2001, was submitted to the FAA for

approval. (The original issue of the

21852 Federal Register / Vol. 66, No. 85 / Wednesday, May 2, 2001 / Rules and Regulations

service bulletin was referenced in the

proposal as the appropriate source of

service information for accomplishment

of the specified actions.) The

commenter adds that the revised

bulletin contains additional inspection

requirements for operators that used a

specific corrosion-inhibiting compound

when incorporating the referenced

service bulletin. The commenter notes

that when the final rule is released it

should reference the revised service

bulletin.

The FAA concurs with the

commenter. Since the issuance of the

proposed rule, the FAA has approved

Revision 1 of the service bulletin. The

service bulletin was revised in order to

delete a certain corrosion-inhibiting

compound specified in the original

issue that, in certain conditions, has

been found to promote corrosion.

Documentation received from the

manufacturer shows that compound was

used on only 3 of the 25 airplanes

affected by this final rule, and those

airplanes are scheduled to be reworked

using the revised service bulletin. The

final rule has been revised to require

accomplishment of the specified actions

per Revision 1 only. A new Note 3 has

been added to the final rule to give

credit for airplanes that applied the

correct corrosion-inhibiting compound

per the original service bulletin.

Conclusion

After careful review of the available

data, including the comments noted

above, the FAA has determined that air

safety and the public interest require the

adoption of the rule with the changes

previously described. The FAA has

determined that these changes will

neither increase the economic burden

on any operator nor increase the scope

of the AD.

Cost Impact

There are approximately 25 airplanes

of the affected design in the worldwide

fleet. The FAA estimates that 11

airplanes of U.S. registry will be affected

by this AD, that it will take

approximately 36 work hours per

airplane to accomplish the required

actions, and that the average labor rate

is $60 per work hour. Required parts

will cost approximately $13,228 per

airplane. Based on these figures, the cost

impact of the AD on U.S. operators is

estimated to be $169,268, or $15,388 per

airplane.

The cost impact figure discussed

above is based on assumptions that no

operator has yet accomplished any of

the 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 adopted herein 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. Therefore, it is

determined that this final rule does not

have federalism implications under

Executive Order 13132.

For the reasons discussed above, I

certify that this action (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. A final evaluation has

been prepared for this action and it is

contained in the Rules Docket. A copy

of it may be obtained from the Rules

Docket at the location provided under

the caption ADDRESSES.

List of Subjects in 14 CFR Part 39

Air transportation, Aircraft, Aviation

safety, Incorporation by reference,

Safety.

Adoption of the Amendment

Accordingly, pursuant to the

authority delegated to me by the

Administrator, the Federal Aviation

Administration amends 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

adding the following new airworthiness

directive:

2001–09–02 Boeing: Amendment 39–12207.

Docket 2000–NM–147–AD.

Applicability: Model 777–200 series

airplanes; line numbers (L/N) 2 through 29

inclusive, except L/N’s 10, 14, and 18;

certificated in any category; except those on

which the outer cylinder of the main landing

gear (MLG) has been replaced in accordance

with Boeing Service Bulletin 777–32–0003,

dated October 9, 1997.

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 (c) 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 stress corrosion cracking and

consequent fracture of the aft trunnion of the

outer cylinder of the MLG, which could

result in collapse of the MLG, accomplish the

following:

Replacement of Bushings

(a) Within 5 years and 300 days since date

of manufacture of the airplane, or within 1

year after the effective date of this AD,

whichever occurs later, replace bushings in

the aft trunnion of the outer cylinder with

new bushings by doing paragraphs (a)(1),

(a)(2), (a)(3), and (a)(4) of this AD; as

applicable; in accordance with Boeing Alert

Service Bulletin 777–32A0025, Revision 1,

dated March 8, 2001.

(1) Remove bushings in the aft trunnion of

the outer cylinder of the MLG.

(2) Perform a one-time detailed visual

inspection of the aft trunnion area for

corrosion or other damage.

(3) For airplanes listed in Group 1 of the

service bulletin: Replace grease in the

undercut of the aft trunnion with corrosioninhibiting compound.

(4) Install new bushings with corrosioninhibiting compound.

Note 2: For the purposes of this AD, a

detailed visual inspection is defined as: ‘‘An

intensive visual examination of a specific

structural area, system, installation, or

assembly to detect damage, failure, or

irregularity. Available lighting is normally

supplemented with a direct source of good

lighting at intensity deemed appropriate by

the inspector. Inspection aids such as mirror,

magnifying lenses, etc., may be used. Surface

cleaning and elaborate access procedures

may be required.’’

Corrective Action

(b) If any corrosion or other damage is

found during the inspection required by

paragraph (a)(2) of this AD: Prior to further

flight, repair in accordance with Boeing Alert

Service Bulletin 777–32A0025, Revision 1,

dated March 8, 2001; except, where the

service bulletin specifies to contact Boeing

for instructions, prior to further flight, repair

in accordance with a method approved by

the Manager, Seattle Aircraft Certification

Federal Register / Vol. 66, No. 85 / Wednesday, May 2, 2001 / Rules and Regulations 21853

Office (ACO), FAA; or in accordance with

data meeting the type certification basis of

the airplane approved by a Boeing Company

Designated Engineering Representative (DER)

who has been authorized by the Manager,

Seattle ACO, to make such findings. For a

repair method to be approved by the

Manager, Seattle ACO, as required by this

paragraph, the approval letter must

specifically reference this AD.

Note 3: Prior accomplishment of

paragraphs (a) and (b) of this AD, as specified

in Boeing Alert Service Bulletin 777–

32A0025, dated April 6, 2000; using BMS 3–

27 or Cor-Ban 27L corrosion-inhibiting

compound; is acceptable for compliance with

the applicable actions required by this AD.

Alternative Methods of Compliance

(c) An alternative method of compliance or

adjustment of the compliance time that

provides an acceptable level of safety may be

used if approved by the Manager, Seattle

ACO. Operators shall submit their requests

through an appropriate FAA Principal

Maintenance Inspector, who may add

comments and then send it to the Manager,

Seattle ACO.

Note 4: 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

(d) 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.

Incorporation by Reference

(e) Except as provided by paragraph (b) of

this AD: The actions shall be done in

accordance with Boeing Alert Service

Bulletin 777–32A0025, Revision 1, dated

March 8, 2001. This incorporation by

reference was approved by the Director of the

Federal Register in accordance with 5 U.S.C.

552(a) and 1 CFR part 51. Copies may be

obtained from Boeing Commercial Airplane

Group, P.O. Box 3707, Seattle, Washington

98124–2207. Copies may be inspected at the

FAA, Transport Airplane Directorate, 1601

Lind Avenue, SW., Renton, Washington; or at

the Office of the Federal Register, 800 North

Capitol Street, NW., suite 700, Washington,

DC.

Effective Date

(f) This amendment becomes effective on

June 6, 2001.

Issued in Renton, Washington, on April 20,

2001.

Donald L. Riggin,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 01–10465 Filed 5–1–01; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2001–NM–115–AD; Amendment

39–12215; AD 2001–09–10]

RIN 2120–AA64

Airworthiness Directives; McDonnell

Douglas Model MD–11 Series

Airplanes Equipped With Pratt &

Whitney Model PW4400 Series Engines

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule; request for

comments.

SUMMARY: This amendment supersedes

an existing airworthiness directive (AD),

applicable to all McDonnell Douglas

Model MD–11 series airplanes equipped

with Pratt & Whitney Model PW4400

series engines, that currently requires

revising the Airplane Flight Manual

(AFM) to advise the flight crew of

applicable operational limits. This

amendment corrects a typographical

error in one paragraph of the existing

AD that resulted in a reference to an

incorrect engine fan blade which is not

subject to the requirements of that

paragraph. The actions specified in this

AD are intended to ensure that the flight

crew is informed of applicable

limitations in airplane performance, and

to prevent reduced acceleration and

climb performance relative to

performance data in the AFM, which

could result in the airplane overrunning

the end of the runway during takeoff or

landing, or impacting obstacles or

terrain. This action is intended to

address the identified unsafe condition.

DATES: Effective May 17, 2001.

Comments for inclusion in the Rules

Docket must be received on or before

July 2, 2001.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, ANM–114,

Attention: Rules Docket No. 2001–NM–

115–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-iarcomment@faa.gov. Comments

sent via fax or the Internet must contain

‘‘Docket No. 2001–NM–115–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.

Information pertaining to this

amendment may be examined at the

FAA, Transport Airplane Directorate,

1601 Lind Avenue, SW., Renton,

Washington; or at the FAA, Los Angeles

Aircraft Certification Office, 3960

Paramount Boulevard, Lakewood,

California.

FOR FURTHER INFORMATION CONTACT:

Philip C. Kush, Aerospace Engineer,

Propulsion Branch, ANM–140L, FAA,

Los Angeles Aircraft Certification

Office, 3960 Paramount Boulevard,

Lakewood, California 90712–4137;

telephone (562) 627–5263; fax (562)

627–5210.

SUPPLEMENTARY INFORMATION: On April

3, 2001, the FAA issued AD 2001–07–

08, amendment 39–12173 (66 FR 18527,

April 10, 2001), applicable to all

McDonnell Douglas Model MD–11

series airplanes equipped with Pratt &

Whitney Model PW4400 series engines.

That AD requires revising the Airplane

Flight Manual (AFM) to advise the flight

crew of applicable operational limits.

That action was prompted by the FAA’s

finding that the operational limits

specified in the Limitations Section of

the AFM for McDonnell Douglas Model

MD–11 series airplanes equipped with

Pratt & Whitney Model PW4400 series

engines do not adequately list the

performance correction sections in the

AFM; and reports that Pratt & Whitney

Model PW4400 series engines with

certain early-production fan blades

(Phase 0/1, FB2B), as installed on

certain McDonnell Douglas Model MD–

11 series airplanes, do not produce the

amount of thrust indicated in the AFM.

The actions required by that AD are

intended to ensure that the flight crew

is informed of applicable limitations in

airplane performance, and to prevent

reduced acceleration and climb

performance relative to performance

data in the AFM, which could result in

the airplane overrunning the end of the

runway during takeoff or landing, or

impacting obstacles or terrain.

Actions Since Issuance of Previous Rule

Since the issuance of AD 2001–07–08,

the FAA has found a typographical error

in paragraph (b) of that AD. Paragraph

(b) requires a revision of the

Performance Section of the AFM to

address a shortfall in the amount of

thrust produced by certain engines

equipped with certain early-production

fan blades. That paragraph states that it

applies to ‘‘airplanes with Pratt &

Whitney Model PW4460 or PW4462

engines with FB2C [fan blades]