Federal Register / Vol. 65, No. 212 / Wednesday, November 1, 2000 / Rules and Regulations 65257

TABLE 1—Continued

Engine serial no. HPT module

configuration HPT hardware Reconfigure at or prior to—

V10221 ................................................. Z Low Flow Blades: Pre SB72–0242 ..................................

High Flow Duct Assembly: Post SB72–0241

Towel Bar Seals, P/N 2A0530: Installed

Next shop visit.

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, Engine

Certification Office (ECO). Operators shall

submit their requests through an appropriate

FAA Principal Maintenance Inspector, who

may add comments and then send it to the

Manager, ECO.

Note 2: Information concerning the

existence of approved alternative methods of

compliance with this airworthiness directive,

if any, may be obtained from the ECO.

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 aircraft to a

location where the requirements of this AD

can be accomplished.

Incorporation by Reference

(d) The restoration to type design must be

done in accordance with International Aero

Engines AOW 1053, Issue 2, dated June 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 International Aero Engines AG, 400

Main Street, East Hartford, CT 06108;

telephone: (860) 565–5515; fax (860) 565–

5510. Copies may be inspected at the FAA

New England Region, Office of the Regional

Counsel, 12 New England Executive Park,

Burlington, MA, or at the Office of the

Federal Register, 800 North Capitol Street,

NW., suite 700, Washington, DC.

Effective Date of This AD

(e) This amendment becomes effective on

December 6, 2000.

Issued in Burlington, Massachusetts, on

October 23, 2000.

David A. Downey,

Assistant Manager, Engine and Propeller

Directorate, Aircraft Certification Service.

[FR Doc. 00–27632 Filed 10–31–00; 8:45 am]

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000–NM–132–AD; Amendment

39–11950; AD 2000–22–04]

RIN 2120–AA64

Airworthiness Directives; Learjet

Model 45 Series Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD),

applicable to certain Learjet Model 45

series airplanes, that requires repetitive

application of grease to the rotating disk

assembly of the nose landing gear squat

switch mechanism. Application of

grease to the squat switch assembly is

necessary to prevent moisture

contamination and subsequent

formation of ice. Such ice formation

could result in bending or damaging of

the nose landing gear squat switch

assembly, which could drive the nose

wheel to an uncommanded angle

against the force of the steering system.

This condition, if not corrected, could

result in the airplane departing from the

runway at high speeds during landing.

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.

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 Equipment Branch, ACE–

116W, FAA, Small Airplane Directorate,

Wichita Aircraft Certification Office,

1801 Airport Road, Room 100, MidContinent 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 45 series airplanes was published

in the Federal Register on June 27, 2000

(65 FR 39578). That action proposed to

require repetitive application of grease

to the rotating disk assembly of the nose

landing gear squat switch mechanism.

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.

Interim Action

This is considered to be interim

action. The manufacturer has advised

that it currently is developing a

modification that will positively address

the unsafe condition addressed by this

AD. Once this modification is

developed and approved, and parts are

available, the FAA may consider

additional rulemaking.

Cost Impact

There are approximately 69 Learjet

Model 45 series airplanes of the affected

design in the worldwide fleet. The FAA

estimates that 45 airplanes of U.S.

registry will be affected by this AD, that

it will take approximately 1 work hour

per airplane to accomplish the required

actions, and that the average labor rate

is $60 per work hour. Based on these

figures, the cost impact of the AD on

U.S. operators is estimated to be $2,700,

or $60 per airplane, per application.

The cost impact figure discussed

above is based on assumptions that no

operator has yet accomplished any of

65258 Federal Register / Vol. 65, No. 212 / Wednesday, November 1, 2000 / Rules and Regulations

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:

2000–22–04 Learjet: Amendment 39–11950.

Docket 2000–NM–132–AD.

Applicability: Model 45 series airplanes,

serial numbers 45–001 through 45–114

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 (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 the airplane from departing the

runway at high speeds during landing due to

bending and damage to the squat switch

assembly of the nose landing gear,

accomplish the following:

Application of Grease

(a) Within 30 days after the effective date

of this AD, apply grease to the rotating disk

assembly of the squat switch mechanism of

the nose wheel in accordance with

Bombardier Aerospace Service Information

Letter SIL 32–016, dated March 30, 2000.

Thereafter, repeat this application at intervals

not to exceed 30 days.

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, 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 2: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Wichita ACO.

Special Flight Permit

(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 application of grease shall be done

in accordance with Bombardier Aerospace

Service Information Letter SIL 32–016, dated

March 30, 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 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 100, Mid-Continent Airport, Wichita,

Kansas; 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 6, 2000.

Issued in Renton, Washington, on October

23, 2000.

Donald L. Riggin,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 00–27630 Filed 10–31–00; 8:45 am]

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 99–NM–69–AD; Amendment

39–11906; AD 2000–19–05]

RIN 2120–AA64

Airworthiness Directives; Boeing

Model 737–100, –200, –200C, –300,

–400, and –500 Series Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule; correction.

SUMMARY: This document corrects

information in an existing airworthiness

directive (AD) that applies to certain

Boeing Model 737–100, –200, –200C,

–300, –400, and –500 series airplanes.

That AD supersedes AD 99–05–15,

amendment 39–11063, to require a onetime inspection of the attachment nuts

at each end attachment of the elevator

tab push rods to measure run-on torque

values, and corrective actions, if

necessary. That AD also requires

replacement of all existing bolts and

attachment nuts at the forward and aft

end attachment of each elevator tab

push rod with new bolts and selflocking castellated nuts with cotter pins.

This document corrects an inadvertent

error regarding the compliance time for

certain requirements of that AD. This

correction is necessary to provide an

adequate compliance time for the

replacement of certain parts.

DATES: Effective October 25, 2000.

The incorporation by reference of

Boeing Service Letter 737–SL–27–118–

D, dated December 17, 1999, was

approved previously by the Director of

the Federal Register as of October 25,

2000 (65 FR 56783, September 20,

2000).

The incorporation by reference of

Boeing Alert Service Bulletin 737–

27A1205, dated August 28, 1997, was

approved previously by the Director of