33444 Federal Register / Vol. 65, No. 101 / Wednesday, May 24, 2000 / Rules and Regulations

Service Bulletin A300–53–0278, Revision 2,

dated November 10, 1995, is approved by the

Director of the Federal Register in accordance

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

(2) The incorporation by reference of the

Airbus service bulletins listed in Table 1 was

approved previously by the Director of the

Federal Register as of April 13, 1992 (57 FR

8257, March 9, 1992).

TABLE 1

Airbus service bulletin No. Revision

level Service bulletin date

A300–53–103 ........................................................................................................................................... 4 June 30, 1983.

A300–53–126 ........................................................................................................................................... 7 November 11, 1990.

A300–53–146 ........................................................................................................................................... 7 April 26, 1991.

A300–53–162 ........................................................................................................................................... 4 November 12, 1990.

A300–53–196 ........................................................................................................................................... 1 November 12, 1990.

A300–53–225 ........................................................................................................................................... 2 May 30, 1990.

Service Bulletin Change Notice 1.A. to A300–53–196 ............................................................................ (Original) February 4, 1991.

A300–53–226 ........................................................................................................................................... 4 November 12, 1990.

A300–53–226 ........................................................................................................................................... 5 September 7, 1991.

A300–53–278 ........................................................................................................................................... (Original) November 12, 1990.

A300–54–045 ........................................................................................................................................... 4 January 31, 1990.

A300–54–060 ........................................................................................................................................... 2 September 7, 1988.

Change Notice 2.A. to A300–54–060 ...................................................................................................... (Original) February 13, 1990.

A300–54–063 ........................................................................................................................................... 1 April 22, 1987.

Change Notice 1.A. to A300–54–063 ...................................................................................................... (Original) February 13, 1990.

A300–54–066 ........................................................................................................................................... 1 February 15, 1989.

Change Notice 1.A. to A300–54–066 ...................................................................................................... (Original) February 13, 1990.

(3) The incorporation by reference of the Airbus service bulletins listed in Table 2 was approved previously by the Director

of the Federal Register as of May 29, 1996 (61 FR 18661, April 29, 1996).

TABLE 2

Airbus service bulletin No. Revision

level Service bulletin date

A300–53–103 ........................................................................................................................................... 5 February 23, 1994.

A300–53–126 ........................................................................................................................................... 8 September 18, 1991.

A300–53–162 ........................................................................................................................................... 5 March 17, 1994.

A300–53–278 ........................................................................................................................................... 1 March 17, 1994.

A300–54–045 ........................................................................................................................................... 6 February 25, 1994.

A300–54–060 ........................................................................................................................................... 3 February 25, 1994.

A300–54–063 ........................................................................................................................................... 2 February 25, 1994.

A300–54–066 ........................................................................................................................................... 2 February 25, 1994.

A300–57–0194 ......................................................................................................................................... 2 August 19, 1993.

A300–57–166 ........................................................................................................................................... 3 July 12, 1993.

A300–57–0167 ......................................................................................................................................... 1 May 25, 1993.

A300–57–0168 ......................................................................................................................................... 3 November 22, 1993.

A300–57–0180 ......................................................................................................................................... 1 March 29, 1993.

A300–57–0185 ......................................................................................................................................... 1 March 8, 1993.

A300–54–0084 ......................................................................................................................................... (Original) April 21, 1994.

(4) Copies may be obtained from Airbus

Industrie, 1 Rond Point Maurice Bellonte,

31707 Blagnac Cedex, France. 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.

Note 7: The subject of this AD is addressed

in French airworthiness directives 93–154–

149(B), dated September 15, 1993, and 90–

222–116(B)R4, dated March 27, 1996.

(k) This amendment becomes effective on

June 28, 2000.

Issued in Renton, Washington, on May 8,

2000.

Vi L. Lipski,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 00–11948 Filed 5–23–00; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000–NM–75–AD; Amendment

39–11736; AD 2000–10–12]

RIN 2120–AA64

Airworthiness Directives; Boeing

Model 747–400 Series Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule; request for

comments.

SUMMARY: This amendment adopts a

new airworthiness directive (AD),

applicable to certain Boeing Model 747–

Federal Register / Vol. 65, No. 101 / Wednesday, May 24, 2000 / Rules and Regulations 33445

400 series airplanes. This action

requires repetitive inspections to detect

damage or deflection of the crew rest

heat exchanger, and follow-on actions, if

necessary. This amendment is prompted

by reports of cracking and buckling of

the front edge of the crew rest heat

exchanger on several airplanes. The

actions specified in this AD are

intended to detect and correct damage

or deflection of the crew rest heat

exchanger, which could result in

jamming of the rudder or elevator

control cables, and consequent reduced

controllability of the airplane.

DATES: Effective June 8, 2000.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of June 8,

2000.

Comments for inclusion in the Rules

Docket must be received on or before

July 24, 2000.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, ANM–114,

Attention: Rules Docket No. 2000–NM–

75–AD, 1601 Lind Avenue, SW.,

Renton, Washington 98055–4056.

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 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.

FOR FURTHER INFORMATION CONTACT:

Barbara Mudrovich, Aerospace

Engineer, Systems and Equipment

Branch, ANM–130S, FAA, Transport

Airplane Directorate, Seattle Aircraft

Certification Office, 1601 Lind Avenue,

SW., Renton, Washington 98055–4056;

telephone (425) 227–2983; fax (425)

227–1181.

SUPPLEMENTARY INFORMATION: The FAA

has received reports indicating that

cracking and buckling of the forward

edge of the crew rest heat exchanger has

been found on several airplanes.

Investigation revealed that certain heat

exchangers were manufactured with

material that is too thin. On one

airplane, the heat exchanger buckled

and bulged enough to make contact with

the rudder and elevator cables located

below the heat exchanger. Such contact

between the heat exchanger and the

rudder and elevator control cables could

eventually dislodge pieces of the heat

exchanger or adjacent fasteners.

Dislodged pieces or fasteners could

cause a jam of the rudder or elevator

control cables. This condition, if not

corrected, could result in reduced

controllability of the airplane.

Explanation of Relevant Service

Information

The FAA has reviewed and approved

Boeing Alert Service Bulletin 747–

21A2412, dated January 20, 2000. The

alert service bulletin describes

procedures for repetitive general visual

inspections to detect damage or

deflection of the crew rest heat

exchanger, and follow-on actions, if

necessary. If damage or deflection is

found, follow-on actions include

replacement of the affected heat

exchanger with a new heat exchanger,

and measurement of the thickness of

material of the discrepant heat

exchanger. If the thickness of the

material is within certain limits, the

alert service bulletin specifies that the

discrepant heat exchanger should be

returned to Boeing.

Explanation of Requirements of the

Rule

Since an unsafe condition has been

identified that is likely to exist or

develop on other airplanes of the same

type design, this AD is being issued to

detect and correct cracking or buckling

of the crew rest heat exchanger, which

could result jamming of the rudder or

elevator control cables, and consequent

reduced controllability of the airplane.

This AD requires accomplishment of the

actions specified in the alert service

bulletin described previously, except as

discussed below.

Difference Between This AD and the

Alert Service Bulletin

Operators should note that there is a

typographical error in the

Accomplishment Instructions on page

10 of the alert service bulletin. Item G.

under the heading ‘‘Inspection and

Replacement of the Heat Exchanger (All

Airplanes)’’ reads, ‘‘If the material

thickness is between 0.028—0.034

inches[,] send the damaged heat

exchanger and your inspection results to

Boeing.’’ The number ‘‘0.034’’ should

read ‘‘0.038.’’ ‘‘NOTE 3’’ has been

included in this AD for clarification of

this point.

Interim Action

This is considered to be interim

action until final action is identified, at

which time the FAA may consider

further rulemaking.

Cost Impact

None of the airplanes affected by this

action are on the U.S. Register. All

airplanes included in the applicability

of this rule currently are operated by

non-U.S. operators under foreign

registry; therefore, they are not directly

affected by this AD action. However, the

FAA considers that this rule is

necessary to ensure that the unsafe

condition is addressed in the event that

any of these subject airplanes are

imported and placed on the U.S.

Register in the future.

Should an affected airplane be

imported and placed on the U.S.

Register in the future, it would require

approximately 1 work hour to

accomplish the required inspection, at

an average labor rate of $60 per work

hour. Based on these figures, the cost

impact of this AD would be $60 per

airplane, per inspection cycle.

Determination of Rule’s Effective Date

Since this AD action does not affect

any airplane that is currently on the

U.S. register, it has no adverse economic

impact and imposes no additional

burden on any person. Therefore, prior

notice and public procedures hereon are

unnecessary and the amendment may be

made effective in less than 30 days after

publication in the Federal Register.

Comments Invited

Although this action is in the form of

a final rule and was not preceded by

notice and opportunity for public

comment, comments are invited on this

rule. Interested persons are invited to

comment on this 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 under the caption

ADDRESSES. All communications

received on or before the closing date

for comments will be considered, and

this rule may be amended in light of the

comments received. Factual information

that supports the commenter’s ideas and

suggestions is extremely helpful in

evaluating the effectiveness of the AD

action and determining whether

additional rulemaking action would be

needed.

Comments are specifically invited on

the overall regulatory, economic,

environmental, and energy aspects of

the rule that might suggest a need to

modify the 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 that

summarizes each FAA-public contact

concerned with the substance of this AD

will be filed in the Rules Docket.

Commenters wishing the FAA to

acknowledge receipt of their comments

submitted in response to this rule must

33446 Federal Register / Vol. 65, No. 101 / Wednesday, May 24, 2000 / Rules and Regulations

submit a self-addressed, stamped

postcard on which the following

statement is made: ‘‘Comments to

Docket Number 2000–NM–75–AD.’’ The

postcard will be date stamped and

returned to the commenter.

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:

2000–10–12 Boeing: Amendment 39–11736.

Docket 2000–NM–75–AD.

Applicability: Model 747–400 series

airplanes, line numbers 1 through 1205

inclusive, certificated in any category, and

equipped with dual crown skin heat

exchangers.

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 detect and correct damage or deflection

of the crew rest heat exchanger, which could

result in jamming of the rudder or elevator

control cables, and consequent reduced

controllability of the airplane, accomplish

the following:

Repetitive Inspections

(a) Within 1,200 flight hours or 90 days

after the effective date of this AD, whichever

occurs first, perform a general visual

inspection of the crew rest heat exchanger to

detect deflection or damage, in accordance

with Boeing Alert Service Bulletin 747–

21A2412, dated January 20, 2000. Repeat the

inspection thereafter at intervals not to

exceed 2,500 flight hours.

Note 2: For the purposes of this AD, a

general visual inspection is defined as: ‘‘A

visual examination of an interior or exterior

area, installation, or assembly to detect

obvious damage, failure, or irregularity. This

level of inspection is made under normally

available lighting conditions such as

daylight, hangar lighting, flashlight, or droplight, and may require removal or opening of

access panels or doors. Stands, ladders, or

platforms may be required to gain proximity

to the area being checked.’’

Corrective Action

(b) If any damage or deflection is detected

during any inspection required by paragraph

(a) of this AD, prior to further flight, replace

the discrepant heat exchanger with a new

heat exchanger, and measure the thickness of

the material of the discrepant heat exchanger,

in accordance with Boeing Alert Service

Bulletin 747–21A2412, dated January 20,

2000. If the material is greater than or equal

to 0.028 inches thick but less than or equal

to 0.038 inches thick (≥ 0.028 but ≤ 0.038

inches thick), send the damaged heat

exchanger and inspection results to the

Manager of Service Bulletin Engineering,

Boeing Commercial Airplane Group, P.O.

Box 3707, Seattle, Washington 98124.

Note 3: There is a typographical error in

the Accomplishment Instructions on page 10

of the alert service bulletin. Item G. under the

heading ‘‘Inspection and Replacement of the

Heat Exchanger (All Airplanes)’’ reads, ‘‘If

the material thickness is between 0.028—

0.034 inches[,] send the damaged heat

exchanger and your inspection results to

Boeing.’’ The number ‘‘0.034’’ should read

‘‘0.038.’’

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

Aircraft Certification Office (ACO), FAA,

Transport Airplane Directorate. 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) The actions shall be done in accordance

with Boeing Alert Service Bulletin 747–

21A2412, dated January 20, 2000. 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 8, 2000.

Issued in Renton, Washington, on May 15,

2000.

Donald L. Riggin,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 00–12671 Filed 5–22–00; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF ENERGY

Federal Energy Regulatory

Commission

18 CFR Part 388

[Docket No. RM00–8–000; Order No. 640]

Revision of Public Reference Room

Procedures for Record Requests

May 17, 2000.

AGENCY: Federal Energy Regulatory

Commission.

ACTION: Final rule.

SUMMARY: The Federal Energy

Regulatory Commission is updating its

regulation at part 388 governing fees for

paper copies of records available in its