Federal Register / Vol. 65, No. 88 / Friday, May 5, 2000 / Rules and Regulations 26121

Accordingly, under the authority of 5

U.S.C. 5343, the interim rule (64 FR

61769) amending 5 CFR part 532

published on November 15, 1999, is

adopted as final with no changes.

Office of Personnel Management.

Janice R. Lachance,

Director.

[FR Doc. 00–11198 Filed 5–4–00; 8:45 am]

BILLING CODE 6325–01–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 99–NE–46–AD; Amendment 39–

11714; AD 2000–09–05]

RIN 2120–AA64

Airworthiness Directives; Allison

Engine Company AE 3007 Series

Turbofan Engines

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD) that is

applicable to certain Allison Engine

Company AE 3007 series turbofan

engines. This AD would require removal

of certain cone shafts from service

before exceeding new cyclic life limits

and replacement with serviceable parts.

This amendment is prompted by

additional testing and low cycle fatigue

(LCF) life analysis that substantiate

lower cyclic lives than originally

determined. The actions specified by

this AD are intended to prevent LCF

failure of cone shafts, which could

result in an uncontained engine failure

and damage to the aircraft.

DATES: Effective date July 5, 2000.

ADDRESSES: 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.

FOR FURTHER INFORMATION CONTACT: John

Tallarovic, Aerospace Engineer, Chicago

Aircraft Certification Office, FAA, Small

Airplane Directorate, 2300 East Devon

Avenue, Des Plaines, IL 60018;

telephone (847) 294–8180, fax (847)

294–7834.

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 Allison Engine

Company AE 3007A, AE 3007A1, AE

3007A1/1, AE 3007A1/2, AE 3007A1/3,

AE 3007A1P, and AE 3007C turbofan

engines was published in the Federal

Register on October 12, 1999 (64 FR

55196). That action proposed to require

the removal of certain cone shafts, P/Ns

23050728 and 23070729, from service

prior to the accumulation of new cyclic

life limits, depending on engine model.

Comments Received

Interested persons have been afforded

an opportunity to participate in the

making of this amendment. Due

consideration has been given to the

comments received.

Increase Cone Shaft Life Limits for AE

3007A and AE 3007C Engines

The manufacturer requests that the

FAA increase the cone shaft life limits

for the AE 3007A and AE 3007C engines

from 7,500 cycles each to 9,500 cycles

and 14,500 cycles respectively. At the

time the NPRM was issued, the cone

shaft low cycle fatigue analysis for these

engines was not available, and the FAA

proposed lower, more conservative shaft

life limits. The analysis has since been

completed and the manufacturer

requests that the life limits be increased.

The FAA agrees. The methodology

used to determine the lives for these

engine models has been approved by the

FAA and is consistent with that used to

determine critical part lives for other

engines already in service (AE 3007A1,

AE 3007A1/1, and AE 3007A1/2).

Therefore, the cone shaft life limits for

the AE 3007A and AE3007C engines

should be increased to 9,500 cycles for

the AE 3007A engine and to 14,500

cycles for the AE 3007C engine.

Accordingly, new paragraphs (a), (b),

and (c) in the final rule are substituted

for proposed paragraph (a), and the

proposed paragraphs (b) through (g)

become paragraphs (d) through (i) in the

final rule.

Increase Cone Shaft Life Limits for AE

3007A1/3 and AE 3007A1P Engines

One commenter requests that the FAA

increase the cone shaft life limits for the

AE 3007A1/3 and AE 3007A1P engines

from 3,500 cycles and 2,400 cycles,

respectively, to 7,500 cycles each. The

commenter suggests that the cone shaft

life of the AE 3007A1/3 and AE

3007A1P engines should be increased to

match those of the AE 3007A1, AE

3007A1/1, and AE 3007A1/2 engines for

two reasons:

• The turbomachinery hardware is

the same for all the engine models

referenced above. The primary

difference between the models is the

engine control software.

• A significant operational aspect of

this group of engines is the ability to

easily maintain fleet readiness by

changing the engine model with an

engine control software change.

The FAA does not agree. When new

data from tests or analysis suggests that

component low cycle fatigue lives need

to be reduced, different approaches may

be taken, depending on the

circumstances. If there are significant

numbers of affected engines in the field

(e.g. AE 3007A, AE 3007A1, AE

3007A1/1, AE 3007A1/2, and AE 3007C

models), a life management program is

developed that allows the users some

operational flexibility while

maintaining an acceptable level of risk

for the fleet. If there is a very small

number of affected engines in the field,

the FAA prefers a life management

program structured on the lifing

methodology intended for original

certification of the engine design. For

the AE 3007A1/3 and AE 3007A1P

engines, therefore, the FAA has

determined to use the original FAA

approved lifing methodology.

Increase Cone Shaft Life Limits for AE

3007A3 Engines

One commenter requests that the FAA

increase the cone shaft life limits for the

AE 3007A3 engines.

The FAA does not agree. This engine

model was not included in the NPRM

and is beyond the scope of this AD.

Incorrect Model Designation

The NPRM incorrectly specifies the

AE 3007A1/P engine. This designation

should read ‘‘AE 3007A1P.’’ This has

been corrected in the final rule.

Conclusion

After careful review of the available

data, including the comments noted

above, the FAA has determined that air

safety and the public interest require the

adoption of the rule with the changes

described previously. The FAA has

determined that these changes will

neither increase the economic burden

on any operator nor increase the scope

of the AD.

Economic Analysis

There are approximately 598 engines

of the affected design in the worldwide

fleet. The FAA estimates that 364

engines installed on aircraft of U.S.

registry will be affected by this AD, that

it will take approximately 150 work

hours per engine to accomplish the

required actions, and that the average

labor rate is $60 per work hour.

Required parts will cost approximately

$3,921 per engine. Based on these

figures, the total cost impact of the AD

on U.S. operators is estimated to be

$4,703,244.

26122 Federal Register / Vol. 65, No. 88 / Friday, May 5, 2000 / Rules and Regulations

Regulatory Impact

This rule does not have federalism

implications, as defined in Executive

Order 13132, because it does 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

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 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, 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:

2000–09–05 Allison Engine Company:

Amendment 39–11714; Docket 99–NE–

46–AD.

Applicability: Allison Engine Company

Models AE 3007A, AE 3007A1, AE 3007A1/

1, AE 3007A1/2, AE 3007A1/3, AE 3007A1P,

and AE 3007C turbofan engines, with cone

shafts, part numbers (P/Ns) 23050728 and

23070729, installed. These engines are

installed on but not limited to EMBRAER

EMB–135 and EMB–145 series and Cessna

750 (Citation X) 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 (h)

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 low cycle fatigue failure of cone

shafts, which could result in an uncontained

engine failure and damage to the aircraft,

accomplish the following:

Removal From Service

(a) For Allison Engine Company model AE

3007A engines, remove cone shafts from

service prior to accumulating 9,500 cyclessince-new (CSN) and replace with

serviceable parts.

(b) For Allison Engine Company model AE

3007C engines, remove cone shafts from

service prior to accumulating 14,500 CSN

and replace with serviceable parts.

(c) For Allison Engine Company models

AE 3007A1, AE 3007A1/1, and AE 3007A1/

2 engines, remove cone shafts from service

prior to accumulating 7,500 CSN and replace

with serviceable parts.

(d) For Allison Engine Company model AE

3007A1/3 engines, remove cone shafts from

service prior to accumulating 3,500 CSN and

replace with serviceable parts.

(e) For Allison Engine Company model AE

3007A1P engines, remove cone shafts from

service prior to accumulating 2,400 CSN and

replace with serviceable parts.

New Life Limits

(f) Paragraphs (a), (b), (c), (d) and (e) of this

AD establish new, lower life limits for cone

shafts, P/Ns 23050728 and 23070729.

(g) Except for the provisions of paragraph

(h) of this AD, no cone shafts, P/Ns 23050728

and 23070729, may remain in service

exceeding the life limits established in

paragraphs (a), (b), (c), (d) and (e) of this AD.

Alternative Method of Compliance

(h) 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, Chicago

Aircraft Certification Office (ACO). Operators

shall submit their requests through an

appropriate FAA Principal Maintenance

Inspector, who may add comments and then

send it to the Manager, Chicago ACO.

Note 2: Information concerning the

existence of approved alternative methods of

compliance with this airworthiness directive,

if any, may be obtained from the Chicago

ACO.

Ferry Flights

(i) No special flight permits will be issued.

Effective Date

(j) This amendment becomes effective on

July 5, 2000.

Issued in Burlington, Massachusetts, on

April 27, 2000.

David A. Downey,

Assistant Manager, Engine and Propeller

Directorate, Aircraft Certification Service.

[FR Doc. 00–11177 Filed 5–4–00; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000–SW–02–AD; Amendment

39–11708; AD 2000–08–22]

RIN 2120–AA64

Airworthiness Directives; MD

Helicopters Inc. Model 369D, 369E,

500N, and 600N Helicopters

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule; request for

comments.

SUMMARY: This amendment adopts a

new airworthiness directive (AD)

applicable to MD Helicopters Inc.

(MDHI) Model 369D, 369E, 500N, and

600N helicopters with certain analog/

digital turbine outlet temperature (TOT)

indicators installed. This action requires

repetitive calibration testing of the TOT

indicating system and corrective actions

if necessary. This amendment is

prompted by seven reports of erroneous

TOT readings and two reports of

incorrect wiring harness terminal lugs

on the thermocouple wiring. The

actions specified in this AD are

intended to prevent an erroneous TOT

indication, damage to critical engine

components, loss of engine power, and

a subsequent forced landing.

DATES: Effective May 22, 2000.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of May 22,

2000.

Comments for inclusion in the Rules

Docket must be received on or before

July 5, 2000.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Office of the

Regional Counsel, Southwest Region,

Attention: Rules Docket No. 2000-SW–

02, 2601 Meacham Blvd., Room 663,

Fort Worth, Texas 76137. You may also

send comments electronically to the

Rules Docket at the following address:

9-asw-adcomments@faa.gov.