Federal Register / Vol. 65, No. 221 / Wednesday, November 15, 2000 / Rules and Regulations 68875

Issued in Fort Worth, Texas, on November

2, 2000.

Mark R. Schilling,

Acting Manager, Rotorcraft Directorate,

Aircraft Certification Service.

[FR Doc. 00–29050 Filed 11–14–00; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000–NE–03–AD; Amendment

39–11981; AD 2000–23–11]

RIN 2120–AA64

Airworthiness Directives; Rolls-Royce

Spey 555–15, –15H, –15N, and –15P

Turbofan Engines

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD),

applicable to Rolls-Royce (RR) plc. Spey

555–15, –15H, –15N, and –15P turbofan

engines, that requires modification of

the low pressure (LP) turbine stage 2

nozzle guide vane (NGV) support ring

seal assembly. This amendment is

prompted by two instances of disk drive

arm damage. In both cases, heavy

damage to the stage 1 LP turbine-tostage 2 LP turbine disk drive arm

occurred as a result of an out-of-balance

condition following the failure of a stage

2 LP turbine blade. The actions

specified by this AD are intended to

prevent damage to the disk drive arm

which could result in loss of stage 1 LP

turbine-to-stage 2 LP turbine disk drive,

a turbine overspeed condition, and

possible uncontained disk failure and

damage to the airplane.

DATES: Effective date December 20,

2000. The incorporation by reference of

certain publications listed in the rule is

approved by the Director of the Federal

Register as of December 20, 2000.

ADDRESSES: The service information

referenced in this AD may be obtained

from Rolls-Royce plc, PO Box 31, Derby,

England, DE248BJ; telephone No. 011–

44–1332–242–424; FAX No. 011–44–

1332–245–418. This information may be

examined at the Federal Aviation

Administration (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.

FOR FURTHER INFORMATION CONTACT:

James Lawrence, Aerospace Engineer,

Engine Certification Office, FAA, Engine

and Propeller Directorate, 12 New

England Executive Park, Burlington, MA

01803–5299; telephone No. 781–238–

7176; fax No. 781–238–7199.

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 Rolls-Royce (RR)

plc. Spey 555–15, –15H, –15N, and

–15P turbofan engines was published in

the Federal Register on July 7, 2000 (65

FR 41884). That action proposed to

require modification of the low pressure

(LP) turbine stage 2 nozzle guide vane

(NGV) support ring seal assembly in

accordance with Service Bulletin (SB)

No. Sp 72–1063, dated May 1999.

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.

Economic Impact

There are approximately 310 engines

of the affected design in the worldwide

fleet. The FAA estimates that 60 engines

installed on aircraft of U.S. registry

would be affected by this AD. It will

take approximately 2.0 work hours per

engine to accomplish the proposed

actions. The average labor rate is $60

per work hour. Since this action is a

rework of existing parts, there is no

required parts cost. Based on these

figures, the FAA estimates the total cost

impact of the proposed AD on U.S.

operators to be $7,200.

Regulatory Impact

This proposed rule does not have

federalism implications, as defined in

Executive Order No. 13132, because it

would 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.

Accordingly, the FAA has not consulted

with state authorities prior to

publication of this proposed rule.

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

Code of Federal 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:

2000–23–11 Rolls-Royce: Amendment 39–

11981. Docket 2000–NE–03–AD.

Applicability: Rolls-Royce (RR) plc. Spey

555–15, –15H, –15N, and –15P turbofan

engines. These engines are installed on but

not limited to Fokker F.28 Mark series

airplanes.

Note 1: This airworthiness directive (AD)

applies to each engine 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 engines 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 disk drive arm

which could result in loss of stage 1 LP

turbine-to-stage 2 LP turbine disk drive, a

turbine overspeed condition and possible

uncontained disk failure, and damage to the

airplane, do the following:

Rework Instructions

(a) Within three years after the effective

date of this AD, rework the low pressure (LP)

turbine stage 2 nozzle guide vane (NGV)

support ring seal assembly in accordance

with paragraphs 2.A. through 2.C. of the

Accomplishment Instructions of RR service

68876 Federal Register / Vol. 65, No. 221 / Wednesday, November 15, 2000 / Rules and Regulations

bulletin (SB) No. Sp 72–1063, dated May

1999.

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 request 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.

(d) The rework shall be done in accordance

with the following Rolls-Royce service

bulletin: (SB) No. Sp 72–1063, dated May

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 Rolls-Royce plc, PO Box 31, Derby,

England, DE248BJ; telephone No. 011–44–

1332–242–424; fax No. 011–44–1332–245–

418. 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 20, 2000.

Issued in Burlington, Massachusetts, on

November 6, 2000.

Donald Plouffe,

Acting Manager, Engine and Propeller

Directorate, Aircraft Certification Service.

[FR Doc. 00–28960 Filed 11–14–00; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000–NM–104–AD; Amendment

39–11977; AD 2000–23–07]

RIN 2120–AA64

Airworthiness Directives; Airbus Model

A300, A300–600, and A310 Series

Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment supersedes

an existing airworthiness directive (AD),

applicable to certain Airbus Model

A300 and all Model A300–600 and

A310 series airplanes, that currently

requires performing a pitch trim system

test to detect any continuity defect in

the autotrim function, and follow-on

corrective actions, if necessary. This

amendment requires repetitive

inspections of the autotrim function to

detect such defects, and corrective

actions, if necessary. This amendment

also expands the applicability to

include additional airplanes. This

amendment is prompted by issuance of

mandatory continuing airworthiness

information by a foreign civil

airworthiness authority. The actions

specified by this AD are intended to

prevent a sudden change in pitch due to

an out-of-trim condition combined with

an autopilot disconnect, which could

result in reduced controllability of the

airplane.

DATES: Effective December 20, 2000.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of December

20, 2000.

ADDRESSES: The service information

referenced in this AD may be obtained

from Airbus Industrie, 1 Rond Point

Maurice Bellonte, 31707 Blagnac Cedex,

France. 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:

Norman B. Martenson, Manager,

International Branch, ANM–116, FAA,

Transport Airplane Directorate, 1601

Lind Avenue, SW., Renton, Washington

98055–4056; telephone (425) 227–2110;

fax (425) 227–1149.

SUPPLEMENTARY INFORMATION: A

proposal to amend part 39 of the Federal

Aviation Regulations (14 CFR part 39)

by superseding AD 2000–02–04,

amendment 39–11522 (65 FR 3799,

January 25, 2000), which is applicable

to certain Airbus Model A300 and all

Model A300–600 and A310 series

airplanes, was published in the Federal

Register on June 12, 2000 (65 FR 36801).

The action proposed to supersede AD

2000–02–04 to continue to require

performing a pitch trim system test to

detect any continuity defect in the

autotrim function, and follow-on

corrective actions, if necessary. The

action also proposed to require

repetitive inspections of the autotrim

function to detect such defects, and

corrective actions, if necessary.

Comments

Interested persons have been afforded

an opportunity to participate in the

making of this amendment. Due

consideration has been given to the

comments received.

Request To Revise Applicability

The manufacturer, Airbus, requests

that the applicability of the proposed

AD be revised to exclude Model A300–

600 series airplanes on which Airbus

Modification 12277 has been

accomplished during production. In

addition, since the issuance of the

proposed AD, the Direction Ge ́ne ́rale de

l’Aviation Civile (DGAC), which is the

airworthiness authority for France,

issued French airworthiness directive

2000–115–304(B) R2, dated July 12,

2000, as revised by Erratum, dated

August 9, 2000, to exclude those

airplanes from the applicability. The

FAA concurs with the commenter’s

request, and has revised the

applicability of this final rule

accordingly.

Request To Revise Reporting

Requirement

The Air Transport Association (ATA)

of America, on behalf of one of its

members, requests that the reporting

requirement specified in the proposed

AD be revised to require that inspection

findings be reported to Airbus on a

monthly basis, rather than 10 days

following each inspection. The

commenter states that since any

necessary corrective actions would

occur immediately as a result of the

inspection findings, monthly reporting

would not affect the safe operation of

the airplane. For certain airlines,

monthly reporting would greatly

simplify the administrative tasks

associated with ongoing reporting.

The FAA concurs partially. The FAA

agrees that corrective actions, if

necessary, would be required prior to

further flight; therefore, extension of the

compliance time in question will not

affect the safe operation of the airplane.

However, the FAA considers that

requiring report submittals on a

monthly basis could lead to possible

misinterpretation as to the specific

deadline for submission of each report.

In light of this, the FAA has revised

the final rule to require submission of

each report within 30 days after

accomplishing each inspection (for

inspections accomplished after the

effective date of this AD), or within 30

days after the effective date of the AD

(for inspections accomplished prior to

the effective date of this AD). Operators

are provided with additional time to