21634 Federal Register / Vol. 65, No. 79 / Monday, April 24, 2000 / Rules and Regulations

submitted will be available, both before

and after the closing date for comments,

in the Rules Docket for examination by

interested persons. A report that

summarizes each FAA-public contact

concerned with the substance of this AD

will be filed in the Rules Docket.

Commenters wishing the FAA to

acknowledge receipt of their comments

submitted in response to this rule must

submit a self-addressed, stamped

postcard on which the following

statement is made: ‘‘Comments to

Docket Number 2000–NM–88–AD.’’ The

postcard will be date stamped and

returned to the commenter.

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.

The FAA has determined that this

regulation is an emergency regulation

that must be issued immediately to

correct an unsafe condition in aircraft,

and that it is not a ‘‘significant

regulatory action’’ under Executive

Order 12866. It has been determined

further that this action involves an

emergency regulation under DOT

Regulatory Policies and Procedures (44

FR 11034, February 26, 1979). If it is

determined that this emergency

regulation otherwise would be

significant under DOT Regulatory

Policies and Procedures, a final

regulatory evaluation will be prepared

and placed in the Rules Docket. A copy

of it, if filed, 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:

2000–08–08 Boeing: Amendment 39–11694.

Docket 2000–NM–88–AD.

Applicability: Model 737–600, –700, and

–800 series airplanes; certificated in any

category; line numbers 1 through 321

inclusive.

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 failure of the keel beam

structure, accomplish the following:

Inspection

(a) Prior to the accumulation of the total

number of flight cycles specified by Table 1,

‘‘Compliance Thresholds,’’ as applicable, of

Boeing Service Bulletin 737–57–1253, dated

December 16, 1999; or within 60 days after

the effective date of this AD, whichever

occurs later: Perform a one-time highfrequency eddy current inspection to detect

cracking of the rear spar stiffeners that are

located at the left and right buttock lines 6.15

of the wing center section, in accordance

with the service bulletin.

(1) If no cracking is detected in either

stiffener: Prior to further flight, install the

preventive modification on that stiffener, in

accordance with the service bulletin.

(2) If any cracking is found in either

stiffener, prior to further flight, repair that

stiffener in accordance with a method

approved by the Manager, Seattle Aircraft

Certification Office (ACO), FAA, Transport

Airplane Directorate; or in accordance with

data meeting the type certification of the

airplane approved by a Boeing Company

Designated Engineering Representative (DER)

who has been authorized by the Manager,

Seattle ACO, to make such findings. For a

repair method to be approved by the

Manager, Seattle ACO, as required by this

paragraph, the Manager’s approval letter

must specifically reference 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

ACO. 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 2: 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 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) Except as required by paragraph (a)(2)

of this AD, the actions shall be done in

accordance with Boeing Service Bulletin

737–57–1253, dated December 16, 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 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.

(e) This amendment becomes effective on

May 9, 2000.

Issued in Renton, Washington, on April 14,

2000.

Charles D. Huber,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 00–9895 Filed 4–21–00; 8:45 am]

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 99–SW–28–AD; Amendment

39–11691; AD 2000–08–05]

RIN 2120–AA64

Airworthiness Directives; Agusta

Model A109C and A109K2 Helicopters

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment supersedes

an existing airworthiness directive (AD),

applicable to Agusta Model A109C and

A109K2 helicopters, that currently

requires removing the main rotor pitch

control link assemblies, measuring the

radial play of each upper and lower

spherical rod-end bearing (bearing), and

replacing any unairworthy bearing. This

amendment requires replacing the pitch

control link assembly with an assembly

that has increased durability and wear

resistance. This amendment is

prompted by reports of increased

helicopter vibration caused by wear of

Federal Register / Vol. 65, No. 79 / Monday, April 24, 2000 / Rules and Regulations 21635

bearings on certain pitch control link

assemblies. The actions specified by this

AD are intended to eliminate the need

for recurring bearing inspections and to

prevent failure of a bearing, increased

helicopter vibration, and subsequent

reduced controllability of the helicopter.

DATES: Effective May 30, 2000.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of May 30,

2000.

ADDRESSES: The service information

referenced in this AD may be obtained

from Agusta, 21017 Cascina Costa di

Samarate (VA), Via Giovanni Agusta

520, telephone (0331) 229111, fax (0331)

229605–222595. This information may

be examined at the FAA, Office of the

Regional Counsel, Southwest Region,

2601 Meacham Blvd., Room 663, Fort

Worth, Texas; or at the Office of the

Federal Register, 800 North Capitol

Street, NW., suite 700, Washington, DC.

FOR FURTHER INFORMATION CONTACT:

Shep Blackman, Aerospace Engineer,

FAA, Rotorcraft Directorate, Rotorcraft

Standards Staff, 2601 Meacham Blvd.,

Fort Worth, Texas 76137, telephone

(817) 222–5296, fax (817) 222–5961.

SUPPLEMENTARY INFORMATION: A

proposal to amend part 39 of the Federal

Aviation Regulations (14 CFR part 39)

by superseding AD 99–02–09,

Amendment 39–11000 (64 FR 2559),

which is applicable to Agusta Model

A109C and A109K2 helicopters, was

published in the Federal Register on

January 12, 2000 (65 FR 1838). That

action proposed to require replacing

main rotor pitch link assemblies with

assemblies that have increased

durability and wear resistance.

Interested persons have been afforded

an opportunity to participate in the

making of this amendment. No

comments were received on the

proposal or the FAA’s determination of

the cost to the public. The FAA has

determined that air safety and the

public interest require the adoption of

the rule as proposed.

The FAA estimates that 3 helicopters

of U.S. registry will be affected by this

AD, that it will take approximately 7

work hours per helicopter to accomplish

the required actions, and that the

average labor rate is $60 per work hour.

Required parts will cost approximately

$2,200 per helicopter. Based on these

figures, the total cost impact of the AD

on U.S. operators is estimated to be

$7,860.

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

removing Amendment 39–11000 (64 FR

2559), and by adding a new

airworthiness directive (AD),

Amendment 39–11691, to read as

follows:

AD 2000–08–05 Agusta S.p.A.: Amendment

39–11691. Docket No. 99–SW–28–AD.

Supersedes AD 99–02–09, Amendment

39–11000, Docket No. 97–SW–55–AD.

Applicability: Model A109C and A109K2

helicopters, with main rotor pitch control

link assemblies, part number (P/N) 109–

0110–71–103 or –105, installed, certificated

in any category.

Note 1: This AD applies to each helicopter

identified in the preceding applicability

provision, regardless of whether it has been

otherwise modified, altered, or repaired in

the area subject to the requirements of this

AD. For helicopters 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 before further flight,

unless accomplished previously.

To prevent failure of a main rotor pitch

control link rod-end spherical bearing,

increased vibration level, and subsequent

reduced controllability of the helicopter,

accomplish the following:

(a) Rework each main rotor pitch control

link assembly, P/N 109–0110–71–103 or

–105, and reidentify as pitch control link

assembly, P/N 109–0110–71–107, in

accordance with the Compliance Instructions

of Agusta Bollettino Tecnico 109K–10 or

109–103, both dated November 22, 1995, as

applicable.

(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, Regulations

Group, Rotorcraft Directorate, FAA.

Operators shall submit their requests through

an FAA Principal Maintenance Inspector,

who may concur or comment and then send

it to the Manager, Regulations Group.

Note 2: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Regulations Group.

(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 helicopter

to a location where the requirements of this

AD can be accomplished.

(d) The modification shall be done in

accordance with the Compliance Instructions

of Agusta Bollettino Tecnico 109K–10 or

109–103, both dated November 22, 1995.

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 Agusta, 21017 Cascina Costa di

Samarate (VA), Via Giovanni Agusta 520,

telephone (0331) 229111, fax (0331) 229605–

222595. Copies may be inspected at the FAA,

Office of the Regional Counsel, Southwest

Region, 2601 Meacham Blvd., Room 663, Fort

Worth, Texas; or at the Office of the Federal

Register, 800 North Capitol Street, NW., suite

700, Washington, DC.

(e) This amendment becomes effective on

May 30, 2000.

Note 3: The subject of this AD is addressed

in Registro Aeronautico Italiano (Italy) AD’s

95–332, dated December 15, 1995, and 95–

334, dated December 18, 1995.

Issued in Fort Worth, Texas, on April 11,

2000.

Henry A. Armstrong,

Manager, Rotorcraft Directorate, Aircraft

Certification Service.

[FR Doc. 00–9817 Filed 4–21–00; 8:45 am]

BILLING CODE 4910–13–P