Federal Register / Vol. 65, No. 225 / Tuesday, November 21, 2000 / Rules and Regulations 69861

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

December 26, 2000.

Issued in Renton, Washington, on

November 9, 2000.

Donald L. Riggin,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 00–29376 Filed 11–20–00; 8:45 am]

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000–NM–52–AD; Amendment

39–11991; AD 2000–23–18]

RIN 2120–AA64

Airworthiness Directives; Learjet

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 60

airplanes, that requires inspecting the

routing of oxygen tubing to ensure that

there is adequate clamping of the tubing

and adequate clearance between the

tubing and electrical wiring or electrical

contacts, and taking corrective action, if

necessary. The actions specified by this

AD are intended to prevent electrical

arcing between the oxygen tubing and

an electrical source, which could result

in an oxygen fire.

DATES: Effective December 26, 2000.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of December

26, 2000.

ADDRESSES: The service information

referenced in this AD may be obtained

from Learjet, Inc., One Learjet Way,

Wichita, Kansas 67209–2942. 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 FAA,

Wichita Aircraft Certification Office,

1801 Airport Road, Room 100, MidContinent Airport, Wichita, Kansas; or

at the Office of the Federal Register, 800

North Capitol Street, NW., suite 700,

Washington, DC.

FOR FURTHER INFORMATION CONTACT:

Shane Bertish, Aerospace Engineer,

Systems and Propulsion Branch, ACE–

116W, FAA, Wichita Aircraft

Certification Office, 1801 Airport Road,

Room 100, Mid-Continent Airport,

Wichita, Kansas 67209; telephone (316)

946–4156; fax (316) 946–4407.

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 Learjet

Model 60 airplanes was published in

the Federal Register on August 8, 2000

(65 FR 48399). That action proposed to

require inspecting the routing of oxygen

tubing to ensure that there is adequate

clamping of the tubing and adequate

clearance between the tubing and

electrical wiring or electrical contacts.

That action also proposed to require

corrective action, if necessary.

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 58 airplanes

of the affected design in the worldwide

fleet. The FAA estimates that 40

airplanes of U.S. registry will be affected

by this AD, that it will take 1 work hour

per airplane to accomplish the required

inspection, and that the average labor

rate is $60 per work hour. There will be

no parts required. Based on these

figures, the cost impact of the required

inspection on U.S. operators is

estimated to be $2,400, or $60 per

airplane.

Should an operator be required to

adjust the clamping or the clearance of

the oxygen tubing, the FAA estimates

that it will take approximately 3 work

hours per airplane and that the average

labor rate is $60 per work hour. The cost

of required parts, such as clamps, nuts,

bolts, and washers, will be negligible.

Based on these figures, the cost impact

of adjusting the clamping or the

clearance of the tubing is estimated to

be $7,200, or $180 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,

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:

2000–23–18 Learjet: Amendment 39–11991.

Docket 2000–NM–52–AD.

69862 Federal Register / Vol. 65, No. 225 / Tuesday, November 21, 2000 / Rules and Regulations

Applicability: Model 60 airplanes, serial

numbers 104 through 168 inclusive;

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 (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 electrical arcing between the

oxygen tubing and an electrical source which

could result in an oxygen fire, accomplish

the following:

Inspection

(a) Within 60 days or 80 flight hours after

issuance of this AD, whichever occurs first,

perform a detailed visual inspection of the

oxygen tubing for adequate clamping and

adequate clearance from electrical wiring and

electrical contacts, in accordance with the

Accomplishment Instructions of Bombardier

Alert Service Bulletin (Learjet 60) SB A60–

35–2, dated November 4, 1999. If adequate

clamping and adequate clearance, as

specified in the service bulletin, are found,

no further action is required by this AD.

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.’’

Adjustment

(b) If clamping or clearance of the oxygen

tubing from electrical wiring or contacts is

not adequate as specified in Bombardier

Alert Service Bulletin (Learjet 60) SB A60–

35–2, dated November 4, 1999, the clamping

or the clearance must be adjusted, in

accordance with the Accomplishment

Instructions of the service bulletin.

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, Wichita

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, Wichita ACO.

Note 3: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Wichita 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 Bombardier Alert Service Bulletin

(Learjet 60) SB A60–35–2, dated November 4,

1999. 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 Learjet, Inc., One Learjet Way, Wichita,

Kansas 67209–2942. Copies may be inspected

at the FAA, Transport Airplane Directorate,

1601 Lind Avenue, SW., Renton,

Washington; or at the FAA, Wichita Aircraft

Certification Office, 1801 Airport Road,

Room 101, Mid-Continent Airport, Wichita,

Kansas; 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

December 26, 2000.

Issued in Renton, Washington, on

November 9, 2000.

Donald L. Riggin,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 00–29374 Filed 11–20–00; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000–NM–329–AD; Amendment

39–11988; AD 2000–23–16]

RIN 2120–AA64

Airworthiness Directives; Boeing

Model 747 Series Airplanes Powered

By Pratt & Whitney JT9D–3 and –7

Series Engines

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule; request for

comments.

SUMMARY: This amendment adopts a

new airworthiness directive (AD) that is

applicable to certain Boeing Model 747

series airplanes. This action requires

repetitive inspections and torque checks

of the hanger fittings and strut forward

bulkhead of the forward engine mount

and adjacent support structure, and

corrective actions, if necessary. This

action also provides for optional

terminating action for the repetitive

inspections and checks. This action is

necessary to detect and correct loose

fasteners and associated damage to the

hanger fittings and bulkhead of the

forward engine mount, which could

result in separation of the engine from

the airplane.

DATES: Effective December 6, 2000.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of December

6, 2000.

Comments for inclusion in the Rules

Docket must be received on or before

January 22, 2001.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, ANM–114,

Attention: Rules Docket No. 2000–NM–

329–AD, 1601 Lind Avenue, SW.,

Renton, Washington 98055–4056.

Comments may be inspected at this

location between 9 a.m. and 3 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-anmiarcomment@faa.gov. Comments sent

via fax or the Internet must contain

‘‘Docket No. 2000–NM–329–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.

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:

Tamara Anderson, Aerospace Engineer,

Airframe Branch, ANM–120S, FAA,

Seattle Aircraft Certification Office,

1601 Lind Avenue, SW., Renton,

Washington 98055–4056; telephone

(425) 227–2771; fax (425) 227–1181.

SUPPLEMENTARY INFORMATION: The FAA

has received reports indicating the

detection of loose fasteners of the

hanger fittings and strut forward

bulkhead of the forward engine mount.

In one occurrence, damage to a hanger

fitting also was detected. Such damage

has been attributed to loose fasteners of

the front spar bulkhead of the strut. The

fasteners may not have been fully

torqued, or the nuts may have bottomed

out on the bolt threads prior to full

clamp-up during fastener torque.