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

Federal Register / Vol. 65, No. 212 / Wednesday, November 1, 2000 / Rules and Regulations 65259

the Federal Register as of March 23,

1999 (64 FR 10935, March 8, 1999).

FOR FURTHER INFORMATION CONTACT:

Scott Fung, Aerospace Engineer,

Airframe Branch, ANM–120S, FAA,

Seattle Aircraft Certification Office,

1601 Lind Avenue, SW., Renton,

Washington 98055–4056; telephone

(425) 227–1221; fax (425) 227–1181.

SUPPLEMENTARY INFORMATION: On

September 12, 2000, the Federal

Aviation Administration (FAA) issued

AD 2000–19–05, amendment 39–11906

(65 FR 56783, September 20, 2000),

which 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 one-time

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.

That AD was prompted by reports of

excessive high-frequency airframe

vibration during flight, with consequent

structural damage to the elevator tab,

elevator, and stabilizer. The actions

required by that AD are intended to

prevent detachment of an elevator tab

push rod due to a detached nut at either

end attachment of a push rod, which

could result in excessive high-frequency

airframe vibration during flight;

consequent structural damage to the

elevator tab, elevator, and horizontal

stabilizer; and reduced controllability of

the airplane.

Need for the Correction

Since the issuance of AD 2000–19–05,

the FAA has reviewed the wording in

paragraph (b) of that AD and finds that

there was an inadvertent error in the

compliance time. In the preamble of AD

2000–19–05, the FAA concurred with a

commenter’s request to extend the

compliance time in paragraph (b) from,

‘‘Within 12 months or 4,000 flight

cycles after the effective date of this AD,

whichever occurs first: * * *’’ to

‘‘Within 24 months or 4,000 flight

cycles after the effective date of this AD,

whichever occurs first: * * *’’

However, in the final rule the FAA

inadvertently retained the proposed

compliance time of ‘‘Within 12 months

* * *’’ This AD corrects the compliance

time for paragraph (b) of that AD to

read, ‘‘Within 24 months or 4,000 flight

cycles after the effective date of this AD,

whichever occurs first: * * *’’

Correction of Publication

This document corrects the error and

correctly adds the AD as an amendment

to § 39.13 of the Federal Aviation

Regulations (14 CFR 39.13).

The AD is reprinted in its entirety for

the convenience of affected operators.

The effective date of the AD remains

October 25, 2000.

Since this action only corrects an

error, which extends the compliance

time in that AD, it has no adverse

economic impact and imposes no

additional burden on any person.

Therefore, the FAA has determined that

notice and public procedures are

unnecessary.

List of Subject in 14 CFR Part 39

Air transportation, Aircraft, Aviation

safety, Incorporation by reference,

Safety.

Adoption of the Correction

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 [Corrected]

2. Section 39.13 is amended by

correctly adding the following

airworthiness directive (AD):

2000–19–05 Boeing: Amendment 39–11906.

Docket 99–NM–69–AD. Supersedes AD

99–05–15, Amendment 39–11063.

Applicability: Model 737–100, –200,

–200C, –300, –400, and –500 series airplanes;

line numbers 1 through 2939 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)(1) 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 detachment of an elevator tab

push rod due to a detached nut at either end

attachment of a push rod, which could result

in excessive high-frequency airframe

vibration during flight; consequent structural

damage to the elevator tab, elevator, and

horizontal stabilizer; and reduced

controllability of the airplane; accomplish

the following:

Restatement of Requirements of AD 99–05–

15

One-Time Inspection

(a) Within 90 days after March 23, 1999

(the effective date of AD 99–05–15,

amendment 39–11063): Perform a one-time

inspection of all attachment nuts at each end

of each elevator tab push rod to measure the

run-on torque values of the nuts, in

accordance with Boeing Alert Service

Bulletin 737–27A1205, dated August 28,

1997.

Corrective Actions

(1) If the run-on torque value of any end

attachment nut is within the limits specified

in the alert service bulletin, prior to further

flight, ensure that the final seating torque of

the attachment nuts is within the torque

values specified in the alert service bulletin.

(2) If the run-on torque value of any end

attachment nut is outside the limits specified

in the alert service bulletin, prior to further

flight, replace all existing bolts and

attachment nuts at each end of each elevator

tab push rod with new bolts and self-locking

castellated nuts that have cotter pins

installed as a secondary locking feature, in

accordance with Boeing Service Letter 737–

SL–27–118–D, dated December 17, 1999, and

ensure that the final seating torque of the

nuts is within the torque values specified in

the service letter.

Note 2: Accomplishment of the inspection

and ensuring adequate final seating torque

values prior to the effective date of this AD

in accordance with Boeing All-Base Telex M–

7272–97–0897, dated February 13, 1997, are

considered acceptable for compliance with

the actions specified in paragraphs (a) and

(a)(1) of this AD for only the forward

attachment nuts.

New Requirements of This AD

Replacement

(b) Within 24 months or 4,000 flight cycles

after the effective date of this AD, whichever

occurs first: Replace all existing bolts and

attachment nuts at the forward and aft end

attachment of each elevator tab push rod

with new bolts and self-locking castellated

nuts that have cotter pins installed as a

secondary locking feature, in accordance

with Boeing Service Letter 737–SL–27–118–

D, dated December 17, 1999.

Note 3: Replacements accomplished prior

to the effective date of this AD in accordance

65260 Federal Register / Vol. 65, No. 212 / Wednesday, November 1, 2000 / Rules and Regulations

with Boeing Service Letter 737–SL–27–118–

A, dated November 14, 1997; 737–SL–27–

118–B, dated April 14, 1999; or 737–SL–27–

118–C, dated May 19, 1999; are considered

acceptable for compliance with paragraphs

(a)(2) and (b) of this AD.

Alternative Methods of Compliance

(c)(1) 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.

(2) Alternative methods of compliance,

approved previously in accordance with AD

99–05–15, amendment 39–11063, are

considered to be approved as alternative

methods of compliance with paragraph (a) of

this AD only.

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 §§ 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 737–

27A1205, dated August 28, 1997, and Boeing

Service Letter 737–SL–27–118–D, dated

December 17, 1999.

(1) 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).

(2) The incorporation by reference of

Boeing Alert Service Bulletin 737–27A1205,

dated August 28, 1997, was approved

previously by the Director of the Federal

Register as of March 23, 1999 (64 FR 10935,

March 8, 1999).

(3) 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.

(f) The effective date of this amendment

remains October 25, 2000.

Issued in Renton, Washington, on October

24, 2000.

Donald L. Riggin,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 00–27791 Filed 10–31–00; 8:45 am]

BILLING CODE 4910–13–P

DEPARTMENT OF COMMERCE

Office of the Secretary

15 CFR Part 6

[Docket No.: 001024293–0293–01]

RIN 0690–AA31

Civil Monetary Penalties; Adjustment

for Inflation

AGENCY: Office of the Secretary,

Commerce.

ACTION: Final rule.

SUMMARY: This final rule is being issued

to adjust each civil monetary penalty

provided by law within the jurisdiction

of the Department of Commerce (the

Department). The Federal Civil

Penalties Inflation Adjustment Act of

1990, as amended by the Debt

Collection Improvement Act of 1996,

requires the head of each agency to

adjust its civil monetary penalties for

inflation no later than October 23, 1996,

and at least once every four years

thereafter. These inflation adjustments

will apply only to violations that occur

after the effective date of this rule.

DATES: This rule is effective November

1, 2000.

ADDRESSES: Office of Financial

Management, Department of Commerce,

14th and Constitution Avenue, MS

6827, Washington, DC 20230.

FOR FURTHER INFORMATION CONTACT: Lisa

Casias, 202–482–0766.

SUPPLEMENTARY INFORMATION: The

Federal Civil Penalties Inflation

Adjustment Act of 1990, (Pub. L. 101–

410), provided for the regular evaluation

of civil monetary penalties to ensure

that they continued to maintain their

deterrent value and that penalty

amounts due to the Federal Government

were properly accounted for and

collected. On April 26, 1996, the

Federal Civil Penalties Inflation

Adjustment Act of 1990 was amended

by the Debt Collection Improvement Act

of 1996 (Pub. L. 104–134) to require

each agency to issue regulations to

adjust its civil monetary penalties

(CMP) for inflation at least every four

years. The amendment further provides

that any resulting increases in a CMP

due to the inflation adjustment should

apply only to the violations that occur

subsequent to the date of the

publication in the Federal Register of

the increased amount of the CMP. The

first inflation adjustment of any penalty

shall not exceed ten percent of such

penalty.

On October 24, 1996, the Commerce

Department published in the Federal

Register a schedule of CMP adjusted for

inflation as required by law. In one

instance, the initial CMP inflation

adjustment was zero, and was published

accordingly. In two cases the adjustment

was nine percent. All other CMP

adjusted at that time were increased by

the ten percent maximum amount. In

the October 24, 1996, publication, the

following then existing CMP were not

included:

15 U.S.C. 5408 (b)(1), Fastener Quality

Act

16 U.S.C. 1174 (b), Fur Seal Act

Amendments of 1983

16 U.S.C. 1385 (e), Dolphin Protection

Consumer Information Act

16 U.S.C. 2465 (a), Antarctic Protection

Act of 1990

16 U.S.C. 4016 (b)(1)(B), Fish and

Seafood Promotion Act of 1986

16 U.S.C. 5010 (a), North Pacific

Anadromous Stocks Act of 1992

16 U.S.C. 5103 (b)(2), Atlantic Coastal

Fisheries Cooperative Management

Act

16 U.S.C. 5507 (a), High Seas Fishing

Compliance Act of 1995

16 U.S.C. 5606 (b), Northwest Atlantic

Fisheries Convention Act of 1995

22 U.S.C. 1978 (e), Fishermen’s

Protective Act of 1967

By this publication CMP are again

being adjusted for inflation as

prescribed by law. In the case of those

CMP listed above that were not

previously adjusted, the CMP

adjustment in this document is subject

to the initial inflation adjustment

limitation of ten percent, and each is

being adjusted by that amount. Next, in

the October 24, 1996, publication, the

CMP included in the Atlantic Striped

Bass Conservation Act (16 U.S.C. 1851

Note (Sec. 5)(c)(1)), was adjusted from

$1,000 to $1,100. Thus, it is no longer

subject to the ten percent limitation for

first time adjustments. However, in

1997, this CMP was legislatively

changed to be the same amount as the

CMP established in the MagnusonStevens Fishery Conservation and

Management Act (16 U.S.C. 1858(a)),

which in 1997 was $110,000. As a

consequence, the CMP for the Atlantic

Striped Bass Conservation Act is being

adjusted in this publication from the