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).

-----------------------------------------------------------------------

SUMMARY: This document proposes to adopt a new airworthiness directive

(AD) that would apply to all The New Piper Aircraft, Inc. (Piper)

Models PA-46-310P and PA-46-350P airplanes. The proposed AD would

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

proposed AD would also 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 proposed AD is the result of field reports that indicate

service accuracy problems with the existing turbine inlet temperature

system. 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 May 21, 1999.

ADDRESSES: Submit comments in triplicate to 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. 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.

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 1558, 601 E. 12th Street, Kansas

City, Missouri 64106.

Discussion

The FAA has received several reports that indicate service accuracy

problems with the existing turbine inlet temperature system on Piper

Models PA-46-310P and PA-46-350P airplanes. In particular, an accident

report cited turbine inlet temperature probe inaccuracy as a

contributing factor.

In addition, 9 airplanes were randomly checked for turbine inlet

temperature system accuracy. Six of these airplanes revealed turbine

inlet temperature system inaccuracy (60 degrees to 110 degrees low at

the 1,750-degree test point). More extensive analysis of these systems

reveals the following:

--The turbine inlet temperature probe used on the Model PA-46-310P

airplanes (part number 471-990) when calibrated correctly is accurate

and durable; and

--The turbine inlet temperature probe used on the Model PA-46-350P

airplanes (part number 481-392) when calibrated correctly is accurate,

but not durable.

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 turbine inlet temperature systems on all Piper Models PA-46-310P

and PA-46-350P airplanes should be calibrated to assure the accuracy of

[[Page 13935]]

the existing turbine inlet temperature indicator and wiring;

--the turbine inlet temperature probe used on the Model PA-46-350P

airplanes (part number 481-392) should be replaced every 250 hours

time-in-service (TIS); and

--AD action should be taken 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 FAA is proposing AD action. The

proposed AD would 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 proposed AD would also 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.

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.

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 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 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:

The New Piper Aircraft, Inc.: 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

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

[[Page 13936]]

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; and

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

do not have the applicable POH revision incorporated as follows:

----------------------------------------------------------------------------------------------------------------

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 all serial numbers beginning with 4636132.

----------------------------------------------------------------------------------------------------------------

(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 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).

(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 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) All persons affected by this directive may obtain copies of

the document referred to herein upon request to The New Piper

Aircraft, Inc., Customer Services, 2926 Piper Drive, Vero Beach,

Florida 32960; or may examine this document at the FAA, Central

Region, Office of the Regional Counsel, Room 1558, 601 E. 12th

Street, Kansas City, Missouri 64106.

Issued in Kansas City, Missouri, on March 12, 1999.

Michael Gallagher,

Manager, Small Airplane Directorate, Aircraft Certification Service.

[FR Doc. 99-6975 Filed 3-22-99; 8:45 am]

BILLING CODE 4910-13-U