Federal Register / Vol. 65, No. 102 / Thursday, May 25, 2000 / Rules and Regulations 33745

(f) The discharge of each cylinder shall be

done in accordance with the ‘‘Discharge

Procedure for the 74921G Cylinder’’ in

Eurocopter France Service Bulletin 05.66,

Revision 3, dated May 4, 1998; Eurocopter

France Service Bulletin 05.58, Revision 3,

dated May 4, 1998; or Eurocopter France

Service Bulletin 05.19, Revision 3, dated May

4, 1998. 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 American Eurocopter Corporation, 2701

Forum Drive, Grand Prairie, Texas 75053–

4005, telephone (972) 641–3460, fax (972)

641–3527. 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.

(g) This amendment becomes effective on

June 29, 2000.

Note 3: The subject of this AD is addressed

in Direction Generale De L’Aviation Civile

AD’s 80–062–041(A) R2, 80–063–030(A) R2,

and 80–061–028(A) R2, all dated July 15,

1998.

Issued in Fort Worth, Texas, on May 5,

2000.

Eric Bries,

Acting Manager, Rotorcraft Directorate,

Aircraft Certification Service.

[FR Doc. 00–12351 Filed 5–24–00; 8:45 am]

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 98–CE–112–AD; Amendment

39–11747; AD 99–15–04 R1]

RIN 2120–AA64

Airworthiness Directives; The New

Piper Aircraft, Inc., Models PA–46–

310P and PA–46–350P Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment revises

Airworthiness Directive (AD) 99–15–04,

which currently requires you to

calibrate, inspect, and repair or replace

portions of the turbine inlet temperature

system on all The New Piper Aircraft,

Inc. (New Piper) Models PA–46–310P

and PA–46–350P airplanes (different

actions for different airplane models).

Information reveals that the AD should

not apply to airplanes where the factory

installed turbine inlet temperature

gauge and associated probe have been

replaced through supplemental type

certificate (STC). This AD retains the

actions of AD 99–15–04, and restricts

the applicability accordingly. The

actions specified by this AD are

intended to prevent improper engine

operation caused by improperly

calibrated turbine inlet temperature

indicators or defective turbine inlet

temperature probes, which could result

in engine damage/failure with

consequent loss of control of the

airplane.

EFFECTIVE DATE: This AD becomes

effective on July 28, 2000.

ADDRESSES: You may examine

information related to this AD at FAA,

Central Region, Office of the Regional

Counsel, Attention: Rules Docket No.

98–CE–112–AD, 901 Locust, Room 506,

Kansas City, Missouri 64106.

FOR FURTHER INFORMATION CONTACT: Mr.

Donald J. Young, Aerospace Engineer,

FAA, Atlanta Aircraft Certification

Office, One Crown Center, 1895 Phoenix

Boulevard, Suite 450, Atlanta, Georgia

30349; telephone: (770) 703–6079;

facsimile: (770) 703–6097; e-mail

address: ‘‘Donald.Young@faa.gov’’.

SUPPLEMENTARY INFORMATION:

Events Leading to the Issuance of This

AD

Has FAA taken any action to this

point? Field reports that indicated

service accuracy problems with the

existing turbine inlet temperature

system on certain New Piper Models

PA–46–310P and PA–46–350P airplanes

caused FAA to issue AD 99–15–04,

Amendment 39–11223. This AD

currently requires you to accomplish the

following:

1. Calibrate the turbine inlet

temperature system to assure the

accuracy of the existing turbine inlet

temperature indicator and wiring on all

airplanes;

2. Repair or replace any turbine inlet

temperature system that fails the

calibration test on all airplanes;

3. Repetitively replace the turbine

inlet temperature probe on the Model

PA–46–350P airplanes; and

4. Insert a copy of the AD into the

Pilot’s Operating Handbook (POH) of

certain airplanes.

Since issuing AD 99–15–04, we have

received information to show that the

AD should not apply on airplanes where

the factory installed turbine inlet

temperature gauge and associated probe

were replaced through supplemental

type certificate (STC).

To address this issue, we issued a

notice of proposed rulemaking (NPRM)

to revise AD 99–15–04. This NPRM was

published in the Federal Register on

November 5, 1999 (64 FR 60383). The

NPRM proposed to continue to require

you to accomplish all the actions that

AD 99–15–04 currently requires. Those

airplanes that do not have a Lewis or

Transicoil Turbine Inlet Temperature

Gauge and associated probe installed,

and where this system was replaced in

accordance with an STC, would be

excluded from the AD. Relief from the

AD is available only if the gauge and

probe are replaced through STC and not

if a second turbine inlet temperature

gauge was installed while retaining the

Lewis or Transicoil gauge and probe.

Was the public invited to comment on

the NPRM? The FAA invited interested

persons to participate in the making of

the amendment. A summary of the

comments and FAA’s responses follows:

Comment Issue No. 1: Provide

Justification for Indefinite Life of

Probes Installed Through STC

What is the commenter’s concern?

One commenter requests an explanation

on how FAA determined that the

turbine inlet temperature gauge and

associated probe would last indefinitely

if installed through STC.

What is FAA’s response to the

concern? Our intent of this AD is not to

life limit the turbine inlet temperature

system. We are issuing the AD to assure

that the system is calibrated correctly

and assure that certain parts of this

system are checked and replaced

accordingly. We have not received any

service history or other evidence of

problems with those systems installed

in accordance with an STC. We also

have not received any evidence of

inadequate maintenance instructions for

any system installed in accordance with

an STC. If an unsafe condition develops

on airplanes with these systems

installed per STC, we will issue an AD

against airplanes with that specific

configuration.

We are not changing the AD as a

result of this comment.

Comment Issue No. 2: Provide Specific

STC Numbers and Holders

What are the commenter’s concerns?

One commenter requests that FAA

include a list of STC numbers and

holders of those STC’s that provide

relief from this AD. This commenter

also points out that relief should also be

given if New Piper (the manufacturer)

develops a new turbine temperature

inlet system since we are allowing relief

for any STC, whether currentlyapproved or approved in the future.

What is FAA’s response to the

concerns? We have elected not to

provide a list of STC’s that provide

relief because the FAA having to revise

the AD every time a new STC was

developed and certificated would make

tracking of this AD action confusing and

impractical. We acknowledge that New

33746 Federal Register / Vol. 65, No. 102 / Thursday, May 25, 2000 / Rules and Regulations

Piper could develop a system that could

be eligible for relief from the actions in

this AD. In this case, New Piper could

request an alternative method of

compliance to the AD. If we approve,

then New Piper could include a

statement in the maintenance

instructions that installation of such a

system is considered an alternative

method of compliance to the AD per a

specific FAA letter, or FAA could revise

the AD to exclude such systems.

We are not changing the AD as a

result of this comment.

Comment Issue No. 3: Include Piper

Service Bulletin No. 995A in the AD

What is the commenter’s concern?

One commenter requests that FAA

reference Piper Service Bulletin No.

995A, dated April 26, 1996, in the AD.

What is FAA’s response to the

concern? Piper Service Bulletin No.

995A, dated April 26, 1996, contains

information related to the subject of this

AD. However, if you comply with this

service bulletin, you have not

accomplished all of the actions required

by the AD. Therefore, we are not

mandating compliance with the service

bulletin. Instead we are including the

following statement in the AD: ‘‘Piper

Service Bulletin 995A, dated April 26,

1996, contains information related to

the subject matter of this AD.’’

The FAA’s Determination

What is FAA’s final determination on

this issue? After careful review of all

available information related to the

subject presented above, we have

determined that air safety and the

public interest require the adoption of

the rule as proposed except for the

following:

—the addition of the statement that

Piper Service Bulletin No. 995A

contains information related to the

subject matter of this AD; and

—minor editorial corrections.

How does the addition and

corrections affect the AD? We have

determined that the addition and minor

corrections will not change the meaning

of the AD and will not add any

additional burden upon the public than

was already proposed.

Cost Impact

How many airplanes does this AD

impact? We estimate that this AD will

affect 580 airplanes in the U.S. registry.

What is the cost impact of the affected

airplanes on the U.S. Register? We

estimate 4 workhours per airplane to

accomplish the calibration at an average

labor rate of $60 an hour. Based on these

figures, we estimate the cost impact of

the calibration on U.S. operators at

$139,200, or $240 per airplane.

We estimate 1 workhour per airplane

to accomplish the initial turbine inlet

temperature probe replacement at an

average labor rate of $60 an hour. Parts

cost approximately $518. We estimate

the cost impact of the replacement on

U.S. operators at $335,240, or $578 per

airplane.

What about repetitive actions? These

figures only take into account the initial

replacement and do not take into

account the cost of subsequent

repetitive replacements. We have no

way of determining the number of

replacements each owner/operator will

incur over the life of the affected

airplanes.

What is the cost impact difference

between this AD and AD 99–15–04? The

cost impact of this AD is the same as

that specified in AD 99–15–04. The only

difference between AD 99–15–04 and

this AD is the exemption of certain

airplanes from this AD if a certain

turbine inlet temperature gauge and

associated probe is installed.

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

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 on a

substantial number of small entities

under the criteria of the Regulatory

Flexibility Act. A copy of the final

evaluation prepared for this action is

contained in the Rules. We have placed

a copy of the final regulatory evaluation

prepared for this action in the Rules

Docket. You may obtain a copy of it at

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, under 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. FAA amends Section 39.13 by

removing Airworthiness Directive (AD)

99–15–04, Amendment 39–11223 (64

FR 37699, July 13, 1999), and adding a

new AD to read as follows:

99–15–04 R1 The New Piper Aircraft, Inc.:

Amendment 39–11747; Docket No. 98–

CE–112–AD; Revises AD 99–15–04,

Amendment 39–11223.

(a) What airplanes are affected by this AD?

This AD applies to Models PA–46–310P and

PA–46–350P airplanes, all serial numbers,

that are:

(1) Certificated in any category; and

(2) Equipped with a Lewis or Transicoil

Turbine Inlet Temperature Gauge and

associated probe installed. Relief from the

AD is available only if the gauge and probe

are replaced through STC and not if a second

turbine inlet temperature gauge was installed

while retaining the Lewis or Transicoil gauge

and probe.

(b) Who must comply with this AD?

Anyone who wishes to operate any of the

above airplanes on the U.S. Register must

comply with this AD.

(c) What problem does this AD address?

The actions required in this AD are intended

to detect and correct improperly calibrated

turbine inlet temperature indicators or

defective turbine inlet temperature probes.

This condition, if not detected and corrected,

could result in improper engine operation

and engine damage/failure with consequent

loss of control of the airplane.

(d) What must I do to address this

problem? To address this problem, you must

accomplish the following actions:

Federal Register / Vol. 65, No. 102 / Thursday, May 25, 2000 / Rules and Regulations 33747

(1) For the Model PA–46–310P airplanes:

Compliance time Action In accordance with

(i) Within the next 100 hours time-in-service

(TIS) after August 31, 1999 (the effective

date of the AD 99–15–04).

(A) Perform the Turbine Inlet Temperature

Gauge and Probe Cleaning and Inspection.

The PA–46–310P/350P Maintenance Manual,

Chapter 77–20–00 (section A.(1)(d), pages

1 and 2).

(B) Accomplish the Turbine Inlet Temperature

System Calibration.

The PA–46–310P/350P Maintenance Manual,

Chapter 77–20–00 (pages 3 and 4).

(ii) Prior to further flight after the above cleaning, inspection, and calibration.Repair or replace any failed parts (the turbine

inlet temperature system indicator cannot

be calibrated or the turbine inlet temperature probe fails the inspection) with serviceable parts that are listed in paragraph (e) of

this AD.

Equipment manufacturer instructions and the

applicable maintenance manual.

(iii) Within the next 100 hours TIS after August

31, 1999 (the effective date of the AD 99–

15–04), unless the applicable Pilot’s Operating Handbook (POH) revision is incorporated as presented in paragraph (f) of this

AD.

(A) Incorporate the emergency procedures

presented in paragraph (g) of this AD into

the POH.

(B) This may be accomplished by inserting a

copy of this AD into the POH.

Not applicable.

(iv) As of July 28, 2000 (the effective date of

this AD).

Do not install one of the affected Lewis or

Transicoil turbine inlet temperature gauges

or probes without assuring that it is airworthy and properly calibrated.

Use the procedures located in the previously

referenced maintenance manual sections

and pages.

(2) For the Model PA–46–350P airplanes:

Compliance time Action In accordance with

(i) Within the next 100 hours TIS after August

31, 1999 (the effective date of AD 99–15–04).

(A) Perform the Turbine Inlet Temperature

Gauge and Probe Cleaning and Inspection.

For serial numbers 4622001 through 4622200

and 4636001 through 4636020, utilize the

PA–46–350P Maintenance Manual, Chapter

77–20–00 (section 1.C, page 1).

For all serial numbers beginning with

4636021, utilize the PA–46–350P Maintenance Manual, Chapter 77–20–00 (section

1.C, page 1).

(B) Accomplish the Turbine Inlet Temperature

System Calibration.

For serial numbers 4622001 through 4622200

and 4636001 through 4636020, utilize the

PA–46–350P Maintenance Manual, Chapter

77–20–00 (section 1.I, pages 4 through 7).

For all serial numbers beginning with

4636021, calibration is not required.

(ii) Prior to further flight after the above cleaning, inspection, and calibration.Repair or replace any failed parts (the turbine

inlet temperature system indicator cannot

be calibrated or the turbine inlet temperature probe fails the inspection) with serviceable parts that are listed in paragraph (e) of

this AD.

Equipment manufacturer instructions and the

applicable maintenance manual.

(iii) Upon accumulating 250 hours TIS on the

currently installed turbine inlet temperature

probe or within the next 100 hours TIS after

August 31, 1999 (the effective date of AD

99–15–04), whichever occurs later, and

thereafter at intervals not to exceed 250

hours TIS.

Replace the turbine inlet temperature probe

with a new part number 481–389 or 481–

392 probe.

Equipment manufacturer instructions and the

applicable maintenance manual.

(iv) Within the next 100 hours TIS after August

31, 1999 (the effective date of the AD 99–

15–04), unless the applicable Pilot’s Operating Handbook (POH) revision is incorporated as presented in paragraph (f) of this

AD.

(A) Incorporate the emergency procedures

presented in paragraph (g) of this AD into

the POH.

(B) This may be accomplished by inserting a

copy of this AD into the POH.

Not applicable.

(v) As of July 28, 2000 (the effective date of

this AD).

Do not install one of the affected Lewis or

Transicoil turbine inlet temperature gauges

or probes without assuring that it is airworthy and properly calibrated.

Use the procedures located in the previously

referenced maintenance manual sections

and pages.

(3) Operators of the Model PA–46–350P

airplanes with over 150 hours TIS on the

currently installed turbine inlet temperature

probe will have to replace the probe as

required in paragraph (d)(2)(iii) of this AD. In

this case, the operator may want to

accomplish the replacement prior to the

Turbine Inlet Temperature Gauge and Probe

Cleaning and Inspection, and Turbine Inlet

Temperature System Calibration.

33748 Federal Register / Vol. 65, No. 102 / Thursday, May 25, 2000 / Rules and Regulations

(e) What are the part numbers of the replacement parts referenced in paragraph (d)(2)(ii) of this AD?

Equipment name and manufacturer Part No.

(1) Lewis Turbine Inlet Temperature Analog Indicator ............................ 471–008. This is the only indicator that has a zero adjustment screw.

(2) Lewis Turbine Inlet Temperature Digital Indicator .............................. 548–811. Since this indicator does not have a zero adjustment screw,

you must return it to the factory for adjustment or replacement.

(3) Lewis Turbine Inlet Temperature Probe ............................................. 471–009 for the Model PA–46–310P airplanes and 481–389 or 481–

392 for the Model PA–46–350P airplanes.

(f) What are the POH revisions that can be incorporated instead of the emergency procedures that this AD requires?

(1) For operators of the Model PA–46–310P airplanes:

POH Revision/date Affected serial numbers

VB–1200 .................. 16/March 19, 1999 ................................................................ 46–8408001 through 46–8608067 and 4608001 through

4608007.

VB–1300 .................. 13/February 25, 1999 ............................................................ 4608008 through 4608140.

(2) For operators of the Model PA–46–350P airplanes:

POH Revision/date Affected serial numbers

VB–1332 .................. 16/November 14, 1997 .......................................................... 4622001 through 4622200.

VB–1609 .................. 1/November 21, 1997 ............................................................ 463001 through 4636020.

VB–1602 .................. 1/November 28, 1997 ............................................................ 4636021 through 4636131.

VB–1446 .................. New/December 3, 1997 ......................................................... 4636132 through 4636195.

VB–1710 .................. New/February 23, 1999 ......................................................... All serial numbers beginning with 4636196.

(g) What are the emergency procedures

referenced in paragraphs (d)(1)(iii) and

(d)(2)(iv) of this AD?

(1) For Model PA–46–310P airplanes:

(i) If the turbine inlet temperature

indication fails during takeoff, climb,

descent, or landing, maintain FULL RICH

mixture to assure adequate fuel flow for

engine cooling.

(ii) If the turbine inlet temperature

indication fails after cruise power has been

set, maintain cruise power setting and lean

to 6 gallons per hour (GPH) fuel flow above

that specified in the Power Setting Table in

Section 5 of the AFM/POH. Continually

monitor engine cylinder head and oil

temperatures to avoid exceeding temperature

limits.

(2) For Model PA–46–350P airplanes:

(i) If the turbine inlet temperature

indication fails during takeoff, climb, descent

or landing, set power per the POH Section 5

Power Setting Table and then lean to the

approximate POH Power Setting Table fuel

flow plus 4 GPH.

(ii) If the turbine inlet temperature

indication fails after cruise power has been

set, maintain the power setting and increase

indicated fuel flow by 1 GPH. Continually

monitor engine cylinder head and oil

temperatures to avoid exceeding temperature

limits.

(h) Did The New Piper Aircraft, Inc.

develop service information related to this

subject? Piper Service Bulletin 995A, dated

April 26, 1996, contains information that

related to the subject matter of this AD.

However, if you comply with this service

bulletin, you have not accomplished all of

the actions required by the AD. Therefore, we

are not mandating compliance with the

service bulletin.

(i) Can the pilot accomplish the action?

Anyone who holds at least a private pilot

certificate, as authorized by section 43.7 of

the Federal Aviation Regulations (14 CFR

43.7), may insert a copy of this AD into the

POH, as required by this AD. You must make

an entry into the aircraft records that shows

compliance with this AD, in accordance with

section 43.9 of the Federal Aviation

Regulations (14 CFR 43.9).

(j) Can I comply with this AD in any other

way? You may use an alternative method of

compliance or adjust the compliance time if:

(1)(i) Your alternative method of

compliance provides an equivalent level of

safety; and

(ii) The Manager, Atlanta Aircraft

Certification Office (ACO), approves your

alternative. Submit your request through an

FAA Principal Maintenance Inspector, who

may add comments and then send it to the

Manager, Atlanta ACO.

(2) Alternative methods of compliance

approved in accordance with AD 99–15–04

are approved as alternative methods of

compliance for this AD.

Note: This AD applies to each airplane

identified in paragraph (a) of this AD,

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 (j)

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 you have not

eliminated the unsafe condition, specific

actions you propose to address it.

(k) Where can I get information about any

already-approved alternative methods of

compliance? Contact Donald Young,

Aerospace Engineer, Atlanta Aircraft

Certification Office, One Crown Center, 1895

Phoenix Boulevard, Suite 450, Atlanta,

Georgia 30349; telephone: (770) 703–6079;

facsimile: (770) 703–6097; e-mail address:

‘‘Donald.Young@faa.gov’’.

(l) What if I need to fly the aircraft to

another location to comply with this AD? The

FAA can issue a special flight permit under

§§ 21.197 and 21.199 of the Federal Aviation

Regulations (14 CFR 21.197 and 21.199) to

operate your aircraft to a location where you

can accomplish the requirements of this AD.

(m) Does this AD action affect any existing

AD actions? This amendment revises AD 99–

15–04, Amendment 39–11223.

(n) When does this amendment become

effective? This amendment becomes effective

on July 28, 2000.

Issued in Kansas City, Missouri, on May

17, 2000.

Michael Gallagher,

Manager, Small Airplane Directorate, Aircraft

Certification Service.

[FR Doc. 00–13083 Filed 5–24–00; 8:45 am]

BILLING CODE 4910–13–P