[Federal Register Volume 64, Number 133 (Tuesday, July 13, 1999)]
[Rules and Regulations]
[Pages 37669-37671]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 99-17678]
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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.Young@faa.gov''.
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
