34090 Federal Register / Vol. 66, No. 124 / Wednesday, June 27, 2001 / Rules and Regulations

Incorporation by Reference

(e) The actions shall be done in accordance

with Airbus Service Bulletin A300–28–0080,

dated September 28, 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 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 3: The subject of this AD is addressed

in French airworthiness directive 2000–455–

322(B), dated November 15, 2000.

Effective Date

(f) This amendment becomes effective on

August 1, 2001.

Issued in Renton, Washington, on June 19,

2001.

Kalene C. Yanamura,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 01–15936 Filed 6–26–01; 8:45 am]

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000–NM–339–AD; Amendment

39–12288; AD 2001–13–08]

RIN 2120–AA64

Airworthiness Directives; Dornier

Model 328–300 Series Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD),

applicable to certain Dornier Model

328–300 series airplanes, that requires

replacing the brake assemblies with

modified brake assemblies. The actions

specified by this AD are intended to

prevent overheating of the brakes,

which could result in cracked pistons

and consequent leakage and burning of

the hydraulic fluid. This action is

intended to address the identified

unsafe condition.

DATES: Effective August 1, 2001.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of August 1,

2001.

ADDRESSES: The service information

referenced in this AD may be obtained

from Fairchild Dornier, Dornier

Luftfahrt GmbH, P.O. Box 1103, D–

82230 Wessling, Germany. This

information may be examined at these

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: Dan

Rodina, Aerospace Engineer,

International Branch, ANM–116, FAA,

Transport Airplane Directorate, 1601

Lind Avenue, SW., Renton, Washington

98055–4056; telephone (425) 227–2125;

fax (425) 227–1149.

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 Dornier

Model 328–300 series airplanes was

published in the Federal Register on

May 4, 2001 (66 FR 22484). That action

proposed to require replacing the brake

assemblies with modified brake

assemblies.

Comments

Interested persons have been afforded

an opportunity to participate in the

making of this amendment. No

comments were submitted in response

to the proposal or the FAA’s

determination of the cost to the public.

Conclusion

The FAA has determined that air

safety and the public interest require the

adoption of the rule as proposed.

Cost Impact

The FAA estimates that 8 airplanes of

U.S. registry will be affected by this AD,

that it will take approximately 9 work

hours per airplane to accomplish the

required actions, and that the average

labor rate is $60 per work hour.

Required parts will be provided at the

manufacturer at no cost to operators.

Based on these figures, the cost impact

of the AD on U.S. operators is estimated

to be $4,320, or $540 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:

2001–13–08 Dornier Luftfahrt GmbH:

Amendment 39–12288. Docket 2000–

NM–339–AD.

Applicability: Model 328–300 series

airplanes, certificated in any category, serial

numbers 3105 through 3144 inclusive, 3146,

3148, 3151 through 3154 inclusive, 3158, and

3159.

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

Federal Register / Vol. 66, No. 124 / Wednesday, June 27, 2001 / Rules and Regulations 34091

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 overheating of the brakes,

which could result in cracked pistons and

consequent leakage and burning of the

hydraulic fluid, accomplish the following:

Brake Piston Replacement

(a) Within 7 weeks after the effective date

of this AD, replace the left and right brake

assemblies having part number (P/N)

AHA2227–2 with modified brake assemblies

having P/N AHA2227–3, in accordance with

Dornier Service Bulletin SB–328J–32–029,

Revision 1, dated August 4, 2000.

Note 2: Replacement of the brake

assemblies prior to the effective date of this

AD in accordance with Dornier Service

Bulletin SB–328J–32–029, dated June 14,

2000, is also acceptable for compliance with

the requirements of paragraph (a) of this AD.

Spares

(b) As of the effective date of this AD, no

person may install a brake assembly having

P/N AHA2227–2 on any airplane.

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,

International Branch, ANM–116, Transport

Airplane Directorate, FAA. Operators shall

submit their requests through an appropriate

FAA Principal Maintenance Inspector, who

may add comments and then send it to the

Manager, International Branch, ANM–116.

Note 3: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the International Branch,

ANM–116.

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 Dornier Service Bulletin SB–328J–32–

029, Revision 1, dated August 4, 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

FAIRCHILD DORNIER, DORNIER Luftfahrt

GmbH, P.O. Box 1103, D–82230 Wessling,

Germany. 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 4: The subject of this AD is addressed

in German airworthiness directive 2000–288,

dated September 21, 2000.

Effective Date

(f) This amendment becomes effective on

August 1, 2001.

Issued in Renton, Washington, on June 19,

2001.

Kalene C. Yanamura,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 01–15935 Filed 6–26–01; 8:45 am]

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000–NM–308–AD; Amendment

39–12287; AD 2001–13–07]

RIN 2120–AA64

Airworthiness Directives; Boeing

Model 737–300, 737–400, 737–500,

737–600, 737–700, 737–800, 757–200,

757–200PF, 757–200CB, and 757–300

Series Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD),

applicable to certain Boeing Model 737–

300, 737–400, 737–500, 737–600, 737–

700, 737–800, 757–200, 757–200PF,

757–200CB, and 757–300 series

airplanes. This AD requires a test of the

two electrical circuits that close the fuel

shutoff valve on the wing spar, and

repair, if necessary. This action is

necessary to prevent inability to shut off

the flow of fuel to an engine after an

uncontained engine failure, which

could result in a fire spreading to other

parts of the airplane. This action is

intended to address the identified

unsafe condition.

DATES: Effective August 1, 2001.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of August 1,

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:

Kathrine Rask, Aerospace Engineer,

Propulsion Branch, ANM–140S, FAA,

Seattle Aircraft Certification Office,

1601 Lind Avenue, SW., Renton,

Washington 98055–4056; telephone

(425) 227–1547; 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 737–300, 737–400, 737–500,

737–600, 737–700, 737–800, 757–200,

757–200PF, 757–200CB, and 757–300

series airplanes was published in the

Federal Register on December 29, 2000

(65 FR 82957). That action proposed to

require a test of the two electrical

circuits that close the fuel shutoff valve

on the wing spar, and repair, if

necessary.

Explanation of New Relevant Service

Information

The FAA has reviewed and approved

Boeing Service Bulletin 737–28–1164,

Revision 1, dated May 10, 2001, which

describes procedures for a one-time test

of the two electrical circuits that close

the fuel shutoff valve on each wing spar

to determine if there is continuity, and

location and repair of any discontinuity.

The procedures described in Revision 1

of the service bulletin are essentially

similar to those described in the original

issue of the service bulletin, dated

August 24, 2000, which was listed in

the proposed rule as the appropriate

source of service information for Boeing

Model 737–300, 737–400, and 737–500

series airplanes. Revision 1 merely

corrects the location of two electrical

connectors. Accomplishment of the

actions specified in Revision 1 of the

service bulletin is intended to

adequately address the identified unsafe

condition.

In consideration of this new service

information, the FAA has revised

paragraph (a) of this final rule to refer

to Boeing Service Bulletin 737–28–1164,

Revision 1, in addition to the original

issue of the service bulletin, as an

acceptable source of service information

for accomplishment of paragraph (a) on

Boeing Model 737–300, –400, and –500

series airplanes.

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.