This section of the FEDERAL REGISTER

contains regulatory documents having general

applicability and legal effect, most of which

are keyed to and codified in the Code of

Federal Regulations, which is published under

50 titles pursuant to 44 U.S.C. 1510.

The Code of Federal Regulations is sold by

the Superintendent of Documents. Prices of

new books are listed in the first FEDERAL

REGISTER issue of each week.

Rules and Regulations Federal Register

691

Vol. 65, No. 4

Thursday, January 6, 2000

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 99–NE–39–AD; Amendment 39–

11497; AD 99–27–16]

RIN 2120–AA64

Airworthiness Directives; CFE

Company Model CFE738–1–1B

Turbofan Engines

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD),

applicable to CFE Company Model

CFE738–1–1B turbofan engines. This

AD requires, on certain engines

identified by serial numbers: a one-time

visual inspection of Stage 2 high

pressure turbine (HPT) aft cooling plates

for nicks, dents, and scratches, and if

present, dimensional inspection of

indentation depth; repair, if indentation

is within acceptable limits, and, if

necessary, replacement with serviceable

parts. This AD also requires inspection

for raised metal on the Stage 2 HPT

rotor disk post aft surface that mates

with the Stage 2 HPT aft cooling plate,

and removal of the raised metal, if

present. This amendment is prompted

by reports of Stage 2 HPT aft cooling

plates that were dented during the

assembly of the cooling plate to the

Stage 2 disk due to raised metal on the

stage 2 HPT disk post aft mating surface.

The actions specified by this AD are

intended to prevent aft HPT cooling

plate failure, which could result in an

uncontained engine failure and damage

to the airplane.

DATES: Effective February 10, 2000.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of February

10, 2000.

ADDRESSES: The service information

referenced in this AD may be obtained

from CFE Company, Data Distribution,

MS 64–03/2101–201, PO Box 29003

Phoenix, AZ 85038–9003; telephone

(602) 365–2493, fax (602) 365–5577.

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:

Keith Mead, Aerospace Engineer,

Engine Certification Office, FAA, Engine

and Propeller Directorate, 12 New

England Executive Park, Burlington, MA

01803–5299; telephone (781) 238–7744,

fax (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 certain CFE

Company Model CFE738–1–1B turbofan

engines was published in the Federal

Register on September 28, 1999 (64 FR

52259). That action proposed to require,

on certain engines identified by serial

numbers: a one-time visual inspection

of Stage 2 high pressure turbine (HPT)

aft cooling plates for nicks, dents, and

scratches, and if present, dimensional

inspection of indentation depth; repair,

if indentation is within acceptable

limits, and, if necessary, replacement

with serviceable parts. This Ad also

requires inspection for raised metal on

the Stage 2 HPT rotor disk post aft

surface that mates with the Stage 2 HPT

aft cooling plate, and removal of the

raised metal, if present. That action was

prompted by reports of Stage 2 HPT aft

cooling plates that were dented during

the assembly of the cooling plate to the

Stage 2 disk due to raised metal on the

stage 2 HPT disk post aft mating surface.

That condition, if not corrected, could

result in aft HPT cooling plate failure,

which could result in an uncontained

engine failure and damage to the

airplane.

No Comments Received

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 Analysis

There are approximately 72 engines of

the affected design in the worldwide

fleet. The FAA estimates that 48 engines

installed on aircraft of US registry will

be affected by this AD, that it will take

approximately 4 work hours per engine

to accomplish the required inspection if

the inspection does not take place

during scheduled maintenance, and that

the average labor rate is $60 per work

hour. Required parts cost approximately

$1,536 per engine. Based on these

figures, the total cost impact of the AD

on US operators is estimated to be

$106,560.

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 (EO) 13132.

For the reasons discussed above, I

certify that this action (1) is not a

‘‘significant regulatory action’’ under EO

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

692 Federal Register / Vol. 65, No. 4 / Thursday, January 6, 2000 / Rules and Regulations

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:

99–27–16 CFE Company: Amendment 39–

11497. Docket 99–NE–39–AD.

Applicability: CFE Model CFE738–1–1B

turbofan engines, serial numbers (S/Ns)

105267 through 105339, inclusive. These

engines are installed on but not limited to

Dassault-Breguet Falcon 2000 series aircraft.

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 aft HPT cooling plate failure,

which could result in an uncontained engine

failure and damage to the airplane,

accomplish the following:

Inspections and Follow-On Actions

(a) At the next engine shop visit after the

effective date of this AD where the HPT

assembly is sufficiently disassembled to

afford access to the Stage 2 HPT aft cooling

plate, but not later than 4500 part cyclessince-new (CSN), accomplish the following

in accordance with CFE Alert Service

Bulletin (ASB) No. CFE738–A72–8031,

Revision 1, dated June 23, 1999, as follows:

(1) Inspect the stage 2 HPT aft cooling plate

for nicks, dents, and scratches on surface D

in accordance with the requirements of ASB

No. CFE738–A72–8031, paragraph 2.B.(1).

(2) Repair those stage 2 HPT aft cooling

plates with indentation less than 0.003 inch

deep in accordance with ASB No. CFE738–

A72–8031. paragraph 2.B.(1).

(3) Remove from service prior to further

flight those stage 2 HPT aft cooling plates

that have nicks, dents, and/or scratches that

exceed the acceptance limits in accordance

with ASB No. CFE738–A72–8031 paragraph

2.B.(1), and replace with serviceable parts.

(4) Inspect the stage 2 HPT rotor disk post

aft mating surface for raised metal, and

remove raised metal if present in accordance

with ASB No. CFE738–A72–8031, paragraph

2.B.(2).

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.

Ferry Flights

(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 inspection requirements

of this AD can be accomplished.

Incorporation by Reference

(d) The actions required by this AD shall

be done in accordance with the following

CFE ASB:

Document No. Revision Pages Date

CFE738–A72–8031 .......................................................................................................................................... 1 ............. 1 June 23, 1999.

Original .. 2–5 May 17, 1999.

Total pages: 5.

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 CFE Company, Data Distribution, MS

64–03/2101–201, P.O. , PO Box 29003

Phoenix, AZ 85038–9003; telephone (602)

365–2493, fax (602) 365–5577. 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.

(e) This amendment becomes effective on

February 10, 2000.

Issued in Burlington, Massachusetts, on

December 29, 1999.

Jay J. Pardee,

Manager, Engine and Propeller Directorate,

Aircraft Certification Service.

[FR Doc. 00–133 Filed 1–5–00; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 99–NE–62–AD; Amendment 39–

11496; AD 99–27–15]

RIN 2120–AA64

Airworthiness Directives; General

Electric Company GE90 Series

Turbofan 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 General Electric

Company GE90 series turbofan engines.

This action requires visually inspecting

Ps3 and P3B sense lines and full

authority digital engine control (FADEC)

Ps3 and P3B sensing ports and fittings,

cleaning Ps3 and P3B fittings and

sensing ports, purging the Ps3 and P3B

systems of moisture, and, if necessary,

blending of high metal, nicks, burrs, or

scratches on Ps3 and P3B fitting threads.

This amendment is prompted by seven

reports of loss of thrust control due to

corruption of the signals to the FADEC

caused by water freezing in the Ps3

sensing system. The actions specified in

this AD are intended to prevent loss of

thrust control due to corruption of the

Ps3 and P3B signals to the FADEC

which if it occurs in a critical phase of

flight, could result in loss of aircraft

control.

DATES: Effective January 11, 2000.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of January 11,

2000.

Comments for inclusion in the Rules

Docket must be received on or before

March 6, 2000.

ADDRESSES: Submit comments to the

Federal Aviation Administration (FAA),

New England Region, Office of the

Regional Counsel, Attention: Rules

Docket No. 99–NE–62–AD, 12 New

England Executive Park, Burlington, MA