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.

Federal Register / Vol. 65, No. 88 / Friday, May 5, 2000 / Rules and Regulations 26123

The service information referenced in

this AD may be obtained from MD

Helicopters Inc., Attn: Customer

Support Division, 4555 E. McDowell

Rd., Mail Stop M615–GO48, Mesa,

Arizona 85215–9797, telephone 1–800–

388–3378 or 480–346–6387, datafax

480–346–6813. This information may be

examined at the FAA, Office of the

Regional Counsel, Southwest Region,

2601 Meacham Blvd., Room 663, Fort

Worth, Texas 76137; or at the Office of

the Federal Register, 800 North Capitol

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

FOR FURTHER INFORMATION CONTACT:

Elizabeth Bumann, Aviation Safety

Engineer, FAA, Los Angeles Aircraft

Certification Office, 3960 Paramount

Blvd., Lakewood, California 90712–

4137, telephone (562) 627–5265; fax

(562) 627–5210.

SUPPLEMENTARY INFORMATION: This

amendment adopts a new airworthiness

directive (AD) applicable to MDHI

Model 369D, 369E, 500N, and 600N

helicopters with certain analog/digital

TOT indicators installed. This action

requires repetitive testing of the TOT

indicating system to verify correct

calibration and to take corrective actions

if necessary. This amendment is

prompted by seven reports of erroneous

TOT readings, up to 100 degrees Celsius

low. This amendment is also prompted

by two reports of incorrect wiring

harness terminal lugs on the

thermocouple wiring. Reports indicated

that some of the TOT readings did not

agree with the engine Electronic Control

Unit (ECU) and some readings were

found to be 4 degrees Celsius to 17

degrees Celsius low. The actions

specified in this AD are intended to

prevent erroneous TOT indications,

which could prevent the flight crew

from detecting that an engine

temperature limitation has been

exceeded. This condition, if not

corrected, could result in damage to

critical engine components, loss of

engine power, and a subsequent forced

landing.

The FAA has reviewed MDHI Service

Bulletins SB369D–199, SB369E–093,

SB500N–019 (for Model 369D, 369E,

and 500N helicopters) and SB600N–026

(for Model 600N helicopters), both

dated January 11, 2000. These service

bulletins describe procedures for

calibration testing of the TOT indicating

system and corrective actions if

necessary. The corrective actions

include inspecting TOT wire harness

terminal lugs, connector pins, and

sockets to verify correct material and

installation; retesting the TOT

indicating system; and replacing any

unairworthy part with an airworthy

part. For Model 600N helicopters, Part

III of the service bulletin also describes

procedures for verifying the electronic

control unit (ECU) TOT calibration.

Since an unsafe condition has been

identified that is likely to exist or

develop on other MDHI model

helicopters of these same type designs,

this AD is being issued to prevent an

erroneous TOT indication, damage to

critical engine components, loss of

engine power, and a subsequent forced

landing. The actions are required to be

accomplished in accordance with the

service bulletins described previously,

except as discussed in the following

paragraphs. The short compliance time

involved is required because the

previously described critical unsafe

condition can adversely affect the

engine, causing a loss of engine power

and a subsequent forced landing of the

helicopter. Therefore, initial testing of

the TOT indicating system to verify

correct calibration is required within the

next 50 hours time-in-service (TIS) or on

or before June 15, 2000, whichever

occurs earlier, and this AD must be

issued immediately.

This AD is an interim action. The

manufacturer has advised that it

currently is developing a modification

that will permanently address the

unsafe condition.

The service bulletins specify certain

serial numbered helicopters with the

affected analog/digital TOT indicator

installed. The FAA has determined that

any Model 369D, 369E, 500N, and 600N

helicopter may have the analog/digital

TOT indicator, part number (P/N)

369D24513–1 or P/N 9A3420, installed,

since the helicopter manufacturer has

not developed a modification to correct

the unsafe condition. Even subsequently

manufactured Model 369D, 369E, 500N,

and 600N helicopters may have these

analog/digital TOT indicators installed.

The service bulletins recommend

accomplishing the TOT system

calibration test within 100 hours TIS.

The FAA has determined that a 100-

hour TIS compliance time would not

address the unsafe condition in a timely

manner. In developing an appropriate

compliance time for this AD, the FAA

considered not only the manufacturer’s

recommendation, but the degree of

urgency associated with addressing the

unsafe condition, the average utilization

of the affected fleet, and the time

necessary to perform the test. In light of

all these factors, the FAA finds a

compliance time within the next 50

hours TIS or on or before June 15, 2000,

whichever occurs first, for initiating the

required test is an appropriate interval

of time that affected helicopters can

operate without compromising safety.

Additionally, the FAA has

determined that long-term continued

operational safety will be better assured

by repetitive testing of the TOT

indicating system at intervals not to

exceed 300 hours TIS, rather than a onetime test, because of reports that the

system calibration may shift with

service time. A one-time test may not

provide the degree of safety assurance

necessary to ensure that the TOT

indicator is properly calibrated over

time.

Since a situation exists that requires

the immediate adoption of this

regulation, it is found that notice and

opportunity for prior public comment

hereon are impracticable, and that good

cause exists for making this amendment

effective in less than 30 days.

The FAA estimates that 566

helicopters will be affected by this

proposed AD, that it will take

approximately 0.5 work hour to

accomplish the test, and that the average

labor rate is $60 per work hour. The

manufacturer has represented in the

service bulletins that parts will be

provided at no cost to the operator.

Based on these figures, the total cost

impact of the AD on U.S. operators is

estimated to be $16,980, per test cycle

for the entire fleet.

Comments Invited

Although this action is in the form of

a final rule that involves requirements

affecting flight safety and, thus, was not

preceded by notice and an opportunity

for public comment, comments are

invited on this rule. Interested persons

are invited to comment on this rule by

submitting such written data, views, or

arguments as they may desire.

Communications should identify the

Rules Docket number and be submitted

in triplicate to the address specified

under the caption ADDRESSES. All

communications received on or before

the closing date for comments will be

considered, and this rule may be

amended in light of the comments

received. Factual information that

supports the commenter’s ideas and

suggestions is extremely helpful in

evaluating the effectiveness of the AD

action and determining whether

additional rulemaking action would be

needed.

Comments are specifically invited on

the overall regulatory, economic,

environmental, and energy aspects of

the rule that might suggest a need to

modify the rule. All comments

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

26124 Federal Register / Vol. 65, No. 88 / Friday, May 5, 2000 / Rules and Regulations

concerned with the substance of this AD

will be filed in the Rules Docket.

Commenters wishing the FAA to

acknowledge receipt of their mailed

comments submitted in response to this

rule must submit a self-addressed,

stamped postcard on which the

following statement is made:

‘‘Comments to Docket No. 2000–SW–

02–AD.’’ The postcard will be date

stamped and returned to the

commenter.

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 a new airworthiness directive to

read as follows:

AD 2000–08–22 MD Helicopters Inc.:

Amendment 39–11708, Docket No.

2000–SW–02–AD.

Applicability: Model 369D, 369E, and

500N helicopters, with analog/digital turbine

outlet temperature (TOT) indicator, part

number (P/N) 369D24513–1, installed; and

Model 600N helicopters, with analog/digital

TOT indicator, P/N 9A3420, 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 (f) 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 an erroneous TOT indication,

damage to critical engine components, loss of

engine power, and a subsequent forced

landing, accomplish the following:

(a) For Model 369E, 369D, and 500N

helicopters: Within the next 50 hours timein-service (TIS) or on or before June 15, 2000,

whichever occurs first; test the TOT

indicating system to verify correct calibration

in accordance with the Accomplishment

Instructions, Part I, of MD Helicopters, Inc.

(MDHI) Service Bulletin SB369D–199,

SB369E–093, SB500N–019, dated January 11,

2000 (SB). Thereafter, repeat the test at

intervals not to exceed 300 hours TIS.

(b) If during any test required by paragraph

(a) of this AD the TOT indicator readings for

the tester setting temperatures in Table 1,

Part I, of the SB are not within the indicator

reading range, before further flight, perform

the actions in the Accomplishment

Instructions, Part I, paragraph (6)(b) of the

SB.

(c) For Model 600N helicopters: Within the

next 50 hours TIS or on or before June 15,

2000, whichever occurs first; test the TOT

indicating system, including the electronic

control unit (ECU) TOT sensing system, to

verify correct calibration in accordance with

the Accomplishment Instructions, Part I, of

MDHI SB600N–026, dated January 11, 2000

(SB 600N). Thereafter, repeat the test at

intervals not to exceed 300 hours TIS.

(d) If during any calibration test required

by paragraph (c) of this AD the TOT indicator

readings for the tester setting temperatures in

Table 1, Part I, of SB 600N, are not within

the indicator reading range, before further

flight, perform the actions in the

Accomplishment Instructions, Part I,

paragraph (7)(b) of SB 600N.

(e) If during any test required by paragraph

(c) of this AD the Full Authority Digital

Electronic Control (FADEC) maintenance laptop terminal does not indicate ECU TOT

within (5 degrees Celsius of the tester setting

in Table 1, Part I, of SB 600N, before further

flight, perform the actions in the

Accomplishment Instructions, Part III, of the

SB 600N.

(f) 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, Los

Angeles Aircraft Certification Office.

Operators shall submit their requests through

an FAA Principal Maintenance Inspector,

who may concur or comment and then send

it to the Manager, Los Angeles Aircraft

Certification Office.

Note 2: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Los Angeles Aircraft

Certification Office.

(g) 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.

(h) The tests shall be done in accordance

with MD Helicopters Inc. Service Bulletin

SB369D–199, SB369E–093, SB500N–019 for

Model 369D, 369E, and 500N helicopters and

Service Bulletin SB600N–026 for Model

600N helicopters, both dated January 11,

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 MD Helicopters Inc., Attn: Customer

Support Division, 4555 E. McDowell Rd.,

Mail Stop M615–GO48, Mesa, Arizona

85215–9797, telephone 1–800–388–3378 or

480–346–6387; datafax 480–346–6813.

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.

(i) This amendment becomes effective on

May 22, 2000.

Issued in Fort Worth, Texas, on April 18,

2000.

Mark R. Schilling,

Acting Manager, Rotorcraft Directorate,

Aircraft Certification Service.

[FR Doc. 00–11058 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–NM–99–AD; Amendment

39–11713; AD 2000–07–51]

RIN 2120–AA64

Airworthiness Directives; McDonnell

Douglas Model 717–200 Series

Airplanes

AGENCY: Federal Aviation

Administration, DOT.