Airworthiness Directives; The New Piper Aircraft, Inc. Models PA- 46-310P and PA-46-350P Airplanes

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 98-CE-112-AD]

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: Notice of proposed rulemaking (NPRM).

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SUMMARY: This document proposes to revise Airworthiness Directive (AD)

99-15-04, which currently requires calibrating the turbine inlet

temperature system to assure the accuracy of the existing turbine inlet

temperature indicator and wiring on all The New Piper Aircraft, Inc.

(Piper) Models PA-46-310P and PA-46-350P airplanes, and repairing or

replacing any turbine inlet temperature system that fails the

calibration test. AD 99-15-04 also requires repetitively replacing the

turbine inlet temperature probe on the Model PA-46-350P airplanes, and

inserting a copy of the AD into the Pilot's Operating Handbook (POH) of

certain airplanes. Since AD 99-15-04 became effective, the Federal

Aviation Administration (FAA) has determined 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). The proposed AD retains the

actions of AD 99-15-04, and restricts the applicability accordingly.

The actions specified by the proposed 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.

DATES: Comments must be received on or before January 4, 2000.

ADDRESSES: Submit comments in triplicate to the FAA, Central Region,

Office of the Regional Counsel, Attention: Rules Docket No. 98-CE-112-

AD, Room 506, 901 Locust, Kansas City, Missouri 64106. Comments may be

inspected at this location between 8 a.m. and 4 p.m., Monday through

Friday, holidays excepted.

Service information that applies to the proposed AD may be obtained

from The New Piper Aircraft, Inc., Customer Services, 2926 Piper Drive,

Vero Beach, Florida 32960. This information also may be examined at the

Rules Docket at the address above.

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.Y[email protected]''.

SUPPLEMENTARY INFORMATION:

Comments Invited

Interested persons are invited to participate in the making of the

proposed 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 above. All

communications received on or before the closing date for comments,

specified above, will be considered before taking action on the

proposed rule. The proposals contained in this notice may be changed in

light of the comments received.

[[Page 60384]]

Comments are specifically invited on the overall regulatory,

economic, environmental, and energy aspects of the proposed 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 concerned

with the substance of this proposal will be filed in the Rules Docket.

Commenters wishing the FAA to acknowledge receipt of their comments

submitted in response to this notice must submit a self-addressed,

stamped postcard on which the following statement is made: ``Comments

to Docket No. 98-CE-112-AD.'' The postcard will be date stamped and

returned to the commenter.

Availability of NPRMs

Any person may obtain a copy of this NPRM by submitting a request

to the FAA, Central Region, Office of the Regional Counsel, Attention:

Rules Docket No. 98-CE-112-AD, Room 506, 901 Locust, Kansas City,

Missouri 64106.

Discussion

AD 99-15-04, Amendment 39-11223 (64 FR 37669, July 13, 1999),

currently requires the following:

--calibrating the turbine inlet temperature system to assure the

accuracy of the existing turbine inlet temperature indicator and wiring

for all Piper Models PA-46-310P and PA-46-350P airplanes, and repairing

or replacing any turbine inlet temperature system that fails the

calibration test;

--repetitively replacing the turbine inlet temperature probe on the

Model PA-46-350P airplanes; and

--inserting a copy of this AD into the POH of airplanes that do not

have a certain POH revision incorporated.

AD 99-15-04 was the result of field reports that indicated service

accuracy problems with the existing turbine inlet temperature system on

the affected airplanes.

The actions specified in AD 99-15-04 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.

Actions Since Issuance of Previous Rule

Since AD 99-15-04 became effective, the FAA has determined that the

AD should not apply to airplanes that do not have a Lewis or Transicoil

Turbine Inlet Temperature Gauge and associated probe installed, where

this system was replaced in accordance with a supplemental type

certificate (STC). 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.

The FAA's Determination

After examining the circumstances and reviewing all available

information related to the incidents described above, the FAA has

determined that:

--the actions of AD 99-15-04 should be revised to exclude those

airplanes that do not have a Lewis or Transicoil turbine inlet

temperature gauge and associated probe installed and the system was

replaced through STC; and

--additional AD action should be taken to continue 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.

Explanation of the Provisions of the Proposed AD

Since an unsafe condition has been identified that is likely to

exist or develop in other Piper Models PA-46-310P and PA-46-350P

airplanes of the same type design, the proposed AD would revise AD 99-

15-04. The proposed AD would continue to require calibrating the

turbine inlet temperature system to assure the accuracy of the existing

turbine inlet temperature indicator and wiring on all affected

airplanes, and repairing or replacing any turbine inlet temperature

system that fails the calibration test. The proposed AD would also

require repetitively replacing the turbine inlet temperature probe on

the Model PA-46-350P airplanes, and inserting a copy of the AD into the

POH of certain airplanes. Those airplanes that do not have a Lewis or

Transicoil Turbine Inlet Temperature Gauge and associated probe

installed, 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.

Cost Impact

The FAA estimates that 580 airplanes in the U.S. registry would be

affected by the proposed calibration, that it would take approximately

4 workhours per airplane to accomplish the proposed calibration, and

that the average labor rate is approximately $60 an hour. Based on

these figures, the total cost impact of the proposed calibration on

U.S. operators is estimated to be $139,200, or $240 per airplane.

The FAA estimates that it would take approximately 1 workhour per

airplane to accomplish the proposed initial turbine inlet temperature

probe replacement, and that the average labor rate is approximately $60

an hour. Parts cost approximately $518. Based on these figures, the

total cost impact of the proposed replacement on U.S. operators is

estimated to be $335,240, or $578 per airplane. These figures only take

into account the initial replacement and do not take into account the

cost of subsequent repetitive replacements. The FAA has no way of

determining the number of replacements each owner/operator will incur

over the life of the affected airplanes.

The cost impact of the proposed AD is the same as that specified in

AD 99-15-04. The only difference between AD 99-15-04 and the proposed

AD is the exemption of certain airplanes from the proposed AD if they

have a certain turbine inlet temperature gauge and associated probe

installed.

Regulatory Impact

The regulations proposed herein would not have substantial direct

effects 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, in

accordance with Executive Order 12612, it is determined that this

proposal would not have sufficient federalism implications to warrant

the preparation of a Federalism Assessment.

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) if promulgated,

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 copy of the draft regulatory evaluation

prepared for this action has been placed in the Rules Docket. A copy of

it may be obtained by contacting the Rules Docket at the

[[Page 60385]]

location provided under the caption ADDRESSES.

List of Subjects in 14 CFR Part 39

Air transportation, Aircraft, Aviation safety, Safety.

The Proposed Amendment

Accordingly, pursuant to the authority delegated to me by the

Administrator, the Federal Aviation Administration proposes to amend

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 USC 106(g), 40113, 44701.

Sec. 39.13 [Amended]

2. Section 39.13 is amended 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:

The New Piper Aircraft, Inc.: Docket No. 98-CE-112-AD; Revises AD

99-15-04, Amendment 39-11223.

Applicability: Models PA-46-310P and PA-46-350P airplanes, all

serial numbers, certificated in any category. (See paragraph (f) of

this AD for configurations that would exclude airplanes from the

applicability of this AD).

Note 1: This AD applies to each airplane 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 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 (i) 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 in the body of this AD, unless

already accomplished.

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, accomplish

the following:

(a) For all affected airplanes (Models PA-46-310P and PA-46-

350P), within the next 100 hours time-in-service (TIS) after August

31, 1999 (the effective date of AD 99-15-04), accomplish the Turbine

Inlet Temperature Gauge and Probe Cleaning and Inspection, and

Turbine Inlet Temperature System Calibration, as follows:

(1) For Model PA-46-310P airplanes: Perform the Turbine Inlet

Temperature Gauge and Probe Cleaning and Inspection in accordance

with the PA-46-310P/350P Maintenance Manual, Chapter 77-20-00

(section A.(1)(d), pages 1 and 2); and accomplish the Turbine Inlet

Temperature System Calibration in accordance with the PA-46-310P/

350P Maintenance Manual, Chapter 77-20-00 (pages 3 and 4); and

(2) For Model PA-46-350P airplanes, serial numbers 4622001

through 4622200 and 4636001 through 4636020: Perform the Turbine

Inlet Temperature Gauge and Probe Cleaning and Inspection in

accordance with the PA-46-350P Maintenance Manual, Chapter 77-20-00

(section 1.C, page 1); and accomplish the Turbine Inlet Temperature

System Calibration in accordance with the PA-46-350P Maintenance

Manual, Chapter 77-20-00 (section 1.I., pages 4 through 7).

(3) For Model PA-46-350P airplanes, all serial numbers beginning

with 4636021: Perform the Turbine Inlet Temperature Gauge and Probe

Cleaning and Inspection in accordance with the PA-46-350P

Maintenance Manual, Chapter 77-20-00 (section 1.C, page 1).

Note 2: 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 (c) 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.

(b) For all affected airplanes (Models PA-46-310P and PA-46-

350P), if the results of paragraph (a) of this AD cannot be met (the

turbine inlet temperature system indicator cannot be calibrated or

the turbine inlet temperature probe fails the inspection), prior to

further flight, repair or replace the failed parts with serviceable

parts of the following part numbers:

(1) Lewis Turbine Inlet Temperature Analog Indicator, part

number 471-008.

(2) Lewis Turbine Inlet Temperature Digital Indicator, part

number 548-811.

(3) Turbine Inlet Temperature Probe, part number 471-009 for the

Model PA-46-310P airplanes and part number 481-389 or 481-392 for

the Model PA-46-350P airplanes.

(4) Only the Lewis Turbine Inlet Temperature Analog Indicator

(referenced in paragraph (b)(1) of this AD) has a zero adjustment

screw. The Lewis Turbine Inlet Temperature Digital Indicator

(referenced in paragraph (b)(2) of this AD) must be returned to the

factory for adjustment or replacement.

(c) For the Model PA-46-350P airplanes, 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

part number 481-392 turbine inlet temperature probe with a new part

number 481-389 or 481-392 probe.

(d) For the operators of the airplanes presented in paragraphs

(d)(1) and (d)(2) of this AD, within the next 100 hours TIS after

August 31, 1999 (the effective date of AD 99-15-04), incorporate the

emergency operation procedures specified in paragraph (e) of this AD

for when a turbine inlet temperature system failure occurs while in-

flight by inserting a copy of this AD into the applicable Pilots'

Operating Handbook/Airplane Flight Manual (AFM/POH):

(1) For all operators of the Model PA-46-310P airplanes that do

not have the applicable POH revision incorporated as follows:

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POH Revision/Date Affected serial numbers

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VB-1200............................... 16/March 19, 1999........ 46-8408001 through 46-8608067 and 4608001 through 4608007.

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

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(2) For those operators of the Model PA-46-350P airplanes that

do not have the applicable POH revision incorporated as follows:

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POH Revision/Date Affected serial numbers

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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.

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[[Page 60386]]

(e) The following are emergency operation procedures for when a

turbine inlet temperature system failure occurs while in-flight:

(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.

(f) This AD does not apply to any airplane that does not have a

Lewis or Transicoil Turbine Inlet Temperature Gauge and associated

probe installed, where this system was replaced in accordance with a

supplemental type certificate (STC). 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.

(g) Inserting a copy of this AD into the applicable POH/AFM as

required by paragraph (d) of this AD may be performed by the owner/

operator holding at least a private pilot certificate as authorized

by section 43.7 of the Federal Aviation Regulations (14 CFR 43.7),

and must be entered into the aircraft records showing compliance

with paragraph (d) of this AD in accordance with section 43.9 of the

Federal Aviation Regulations (14 CFR 43.9).

(h) 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 requirements of this AD can be accomplished.

(i) An alternative method of compliance or adjustment of the

initial or repetitive compliance times that provides an equivalent

level of safety may be approved by the Manager, Atlanta Aircraft

Certification Office (ACO), One Crown Center, 1895 Phoenix

Boulevard, Suite 450, Atlanta, Georgia 30349.

(1) The request shall be forwarded through an appropriate FAA

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 considered approved as alternative methods of

compliance for this AD.

Note 3: Information concerning the existence of approved

alternative methods of compliance with this AD, if any, may be

obtained from the Atlanta ACO.

(j) Service information that applies to this AD may be obtained

from The New Piper Aircraft, Inc., Customer Services, 2926 Piper

Drive, Vero Beach, Florida 32960. This information may also be

examined at the Federal FAA, Central Region, Office of the Regional

Counsel, Attention: Rules Docket No. 98-CE-112-AD, Room 506, 901

Locust, Kansas City, Missouri 64106.

(k) This amendment revises AD 99-15-04, Amendment 39-11223.

Issued in Kansas City, Missouri, on October 27, 1999.

Marvin R. Nuss,

Acting Manager, Small Airplane Directorate, Aircraft Certification

Service.

[FR Doc. 99-29057 Filed 11-4-99; 8:45 am]

BILLING CODE 4910-13-U