31836 Federal Register / Vol. 66, No. 114 / Wednesday, June 13, 2001 / Rules and Regulations

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 (b) 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 a crack in the hydraulic line,

leading to heavy leakage in hydraulic system

‘‘B,’’ which could impair the functioning of

the airplane’s flaps, roll spoilers, inner

ground spoilers, and nose wheel steering,

accomplish the following:

Replacement

(a) Within 45 days from the effective date

of this AD: Remove the hydraulic hose

having part number (P/N) 001D291A2050010

between the main pump 50DA and the

pulsation damper, and replace it with a new

hose having P/N 001D291A1102000, in

accordance with Dornier Service Bulletin

SB–328J–29–040, dated June 8, 2000.

Alternative Methods of Compliance

(b) 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 2: 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

(c) 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

(d) The actions shall be done in accordance

with Dornier Service Bulletin SB–328J–29–

040, dated June 8, 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 3: The subject of this AD is addressed

in German airworthiness directive 2000–378,

dated December 14, 2000.

Effective Date

(e) This amendment becomes effective on

July 18, 2001.

Issued in Renton, Washington, on June 4,

2001.

Donald L. Riggin,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 01–14532 Filed 6–12–01; 8:45 am]

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000–NM–268–AD; Amendment

39–12258; AD 2001–12–03]

RIN 2120–AA64

Airworthiness Directives; Boeing

Model 767–300 Series Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD),

applicable to certain Boeing Model 767–

300 series airplanes, that requires a onetime general visual inspection to find

chafing and determine adequate

clearance of certain wire bundles in the

ceiling panel near the main passenger

door, and corrective actions. The actions

specified by this AD are intended to

prevent damage to the wires in the

bundles due to contact between the

bundles and the adjacent ceiling

support bracket. Such damage could

result in electrical arcing, smoke, or fire

in the cabin, and failure of certain

systems essential to safe flight and

landing of the airplane. This action is

intended to address the identified

unsafe condition.

DATES: Effective July 18, 2001.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of July 18,

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:

Elias Natsiopoulos, Aerospace Engineer,

ANM–130S, FAA, Seattle Aircraft

Certification Office, 1601 Lind Avenue,

SW., Renton, Washington 98055–4056;

telephone (425) 227–1279; 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 767–300 series airplanes was

published in the Federal Register on

March 9, 2001 (66 FR 14094). That

action proposed to require a one-time

general visual inspection to find chafing

and determine adequate clearance of

certain wire bundles in the ceiling panel

near the main passenger door, and

corrective actions.

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

There are approximately 135 Model

767–300 series airplanes of the affected

design in the worldwide fleet. The FAA

estimates that 53 airplanes of U.S.

registry will be affected by this AD.

It will take approximately 1 work

hour per airplane to accomplish the

required inspection, at an average labor

rate of $60 per work hour. Based on

these figures, the cost impact of the

inspection required by this AD on U.S.

operators is estimated to be $3,180, or

$60 per airplane.

It will take approximately 2 work

hours per airplane to accomplish the

required repair or replacement, at an

average labor rate of $60 per work hour.

Based on these figures, the cost impact

of the repair or replacement required by

this AD on U.S. operators is estimated

to be $6,360, or $120 per airplane.

The cost impact figures discussed

above are 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,

Federal Register / Vol. 66, No. 114 / Wednesday, June 13, 2001 / Rules and Regulations 31837

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:

2001–12–03 Boeing: Amendment 39–12258.

Docket 2000–NM–268–AD.

Applicability: Model 767–300 series

airplanes, as listed in Boeing Alert Service

Bulletin 767–33A0085, Revision 2, dated

December 7, 2000, 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 (b) 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 damage to the wires in certain

wire bundles due to contact between the

bundles and the adjacent ceiling support

bracket, which could result in electrical

arcing, smoke, or fire in the cabin, and failure

of certain systems essential to safe flight and

landing of the airplane, accomplish the

following:

One-Time Inspection/Corrective Actions

(a) Accomplish the requirements in

paragraphs (a)(1) and (a)(2) of this AD, as

applicable, at the times specified.

(1) Within 6 months after the effective date

of this AD: Do a one-time general visual

inspection to find chafing and determine

adequate clearance of the wire bundles above

the F4/G2 galley, per Figure 1 or Figure 3, as

applicable, of the Accomplishment

Instructions of Boeing Alert Service Bulletin

767–33A0085, Revision 2, dated December 7,

2000.

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 find obvious

damage, failure, or irregularity. This level of

inspection is made under normally available

lighting conditions such as daylight, hangar

lighting, flashlight, or drop-light 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.’’

(2) If chafing and/or inadequate clearance

is found: Before further flight, repair or

replace damaged wires in the wire bundles;

install a bracket assembly on the wire bundle

support bracket; install nut spacer plates; and

re-route the wire bundles away from the

ceiling support bracket, as applicable, as

specified by and per Figure 2 or Figure 3, as

applicable, of the Accomplishment

Instructions of the alert service bulletin.

Note 3: Accomplishment of the one-time

inspection and corrective actions before the

effective date of this AD per Boeing Alert

Service Bulletin 767–33A0085, dated May

11, 2000; or Revision 1, dated August 31,

2000, is considered acceptable for

compliance with paragraph (a) of this AD.

Alternative Methods of Compliance

(b) 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.

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

(c) Special flight permits may be issued in

accordance with §§ 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

(d) The actions shall be done in accordance

with Boeing Alert Service Bulletin 767–

33A0085, Revision 2, dated December 7,

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

(e) This amendment becomes effective on

July 18, 2001.

Issued in Renton, Washington, on June 4,

2001.

Donald L. Riggin,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 01–14531 Filed 6–12–01; 8:45 am]

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000–NM–128–AD; Amendment

39–12257; AD 2001–12–02]

RIN 2120–AA64

Airworthiness Directives; Learjet

Model 55 Series Airplanes and Model

60 Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD),

applicable to certain Learjet Model 55

series airplanes and Model 60 airplanes,

that requires replacement of the brake

valve adjustment screw with a new

improved screw, and for certain

airplanes, it would also require

installation of a new brake valve lever

stop. The actions specified by this AD

are intended to prevent bottoming of the

valve components before contact of the

brake valve lever with the stop, which