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; Amendment 39-11223; AD 99-15-04]

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.

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SUMMARY: This amendment adopts a new airworthiness directive (AD) that

applies to all The New Piper Aircraft, Inc. (Piper) Models PA-46-310P

and PA-46-350P airplanes. This AD requires calibrating the turbine

inlet temperature system to assure the accuracy of the existing turbine

inlet temperature indicator and wiring for all of the applicable

airplanes, and repairing or replacing any turbine inlet temperature

system that fails the calibration test. This AD also requires

repetitively replacing the turbine inlet temperature probe on the Model

PA-46-350P airplanes, and inserting a copy of this AD into the Pilot's

Operating Handbook of certain airplanes. This AD is the result of field

reports that indicate service accuracy problems with the existing

turbine inlet temperature system. 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.

DATES: Effective August 31, 1999.

ADDRESSES: 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 Aviation Administration (FAA), Central Region, Office of the

Regional Counsel, Attention: Rules Docket No. 98-CE-112-AD, Room 1558,

601 E. 12th Street, 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.Y[email protected]''.

SUPPLEMENTARY INFORMATION:

[[Page 37670]]

Events Leading to the Issuance of This AD

A proposal to amend part 39 of the Federal Aviation Regulations (14

CFR part 39) to include an AD that would apply to all Piper Models PA-

46-310P and PA-46-350P airplanes was published in the Federal Register

as a notice of proposed rulemaking (NPRM) on March 23, 1999 (64 FR

13934). The NPRM proposed to require calibrating the turbine inlet

temperature system to assure the accuracy of the existing turbine inlet

temperature indicator and wiring for all of the applicable airplanes,

and repairing or replacing any turbine inlet temperature system that

fails the calibration test. The NPRM also proposed to require

repetitively replacing the turbine inlet temperature probe on the Model

PA-46-350P airplanes, and inserting a copy of this AD into the Pilot's

Operating Handbook of certain airplanes.

The NPRM was the result of field reports that indicate service

accuracy problems with the existing turbine inlet temperature system.

Interested persons have been afforded an opportunity to participate

in the making of this amendment. Due consideration has been given to

the one comment received.

Comment Disposition

The commenter provides reference to other POH revisions than those

referenced in the AD. The commenter recommends that the FAA incorporate

these into the final rule.

The FAA concurs and has revised the final rule accordingly.

No comments were received regarding the FAA's estimate of the cost

impact upon the public.

The FAA's Determination

After careful review of all available information related to the

subject presented above, the FAA has determined that air safety and the

public interest require the adoption of the rule as proposed except for

minor editorial corrections. The FAA has determined that these 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

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

affected by the calibration, that it will take approximately 4

workhours per airplane to accomplish the calibration, and that the

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

figures, the total cost impact of the calibration on U.S. operators is

estimated to be $139,200, or $240 per airplane.

The FAA estimates that it will take approximately 1 workhour per

airplane to accomplish the 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 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.

Regulatory Impact

The regulations adopted herein will 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 final

rule does 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) 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 final evaluation prepared for this

action is contained in the Rules Docket. A copy of it may be obtained

by contacting the Rules Docket at the location provided under the

caption ADDRESSES.

List of Subjects in 14 CFR Part 39

Air transportation, Aircraft, Aviation 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.

Sec. 39.13 [Amended]

2. Section 39.13 is amended by adding a new airworthiness directive

(AD) to read as follows:

99-15-04 The New Piper Aircraft, Inc.: Amendment 39-11223; Docket

No. 98-CE-112-AD.

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

serial numbers, certificated in any category.

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 (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 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 the

effective date of this AD, 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: 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).

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

[[Page 37671]]

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 481-392 for the 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 the effective date of this

AD, 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 one of the same part number.

(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

the effective date of this AD, 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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(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) 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 Sec. 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).

(g) Special flight permits may be issued in accordance with

Secs. 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.

(h) 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. The request shall be

forwarded through an appropriate FAA Maintenance Inspector, who may

add comments and then send it to the Manager, Atlanta ACO.

Note 3: Information concerning the existence of approved

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

obtained from the Atlanta ACO.

(i) 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 1558, 601 E.

12th Street, Kansas City, Missouri 64106

(j) This amendment becomes effective on August 31, 1999.

Issued in Kansas City, Missouri, on July 2, 1999.

Marvin R. Nuss,

Acting Manager, Small Airplane Directorate, Aircraft Certification

Service.

[FR Doc. 99-17678 Filed 7-12-99; 8:45 am]

BILLING CODE 4910-13-U