[Federal Register Volume 65, Number 102 (Thursday, May 25, 2000)]
[Rules and Regulations]
[Pages 33745-33748]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 00-13083]


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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: 
``<a href="/cdn-cgi/l/email-protection#34705b5a5558501a6d5b415a53745255551a535b42"><span class="__cf_email__" data-cfemail="90d4fffef1fcf4bec9ffe5fef7d0f6f1f1bef7ffe6">[email protected]</span></a>''.

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 currently-approved 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

[[Page 33746]]

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.


Sec. 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:

[[Page 33747]]

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

------------------------------------------------------------------------
       Compliance time               Action          In accordance with
------------------------------------------------------------------------
(i) Within the next 100       (A) Perform the       The PA-46-310P/350P
 hours time-in-service (TIS)   Turbine Inlet         Maintenance Manual,
 after August 31, 1999 (the    Temperature Gauge     Chapter 77-20-00
 effective date of the AD 99-  and Probe Cleaning    (section A.(1)(d),
 15-04).                       and Inspection.       pages 1 and 2).
                              (B) Accomplish the    The PA-46-310P/350P
                               Turbine Inlet         Maintenance Manual,
                               Temperature System    Chapter 77-20-00
                               Calibration.          (pages 3 and 4).
(ii) Prior to further flight  Repair or replace     Equipment
 after the above cleaning,     any failed parts      manufacturer
 inspection, and calibration.  (the turbine inlet    instructions and
                               temperature system    the applicable
                               indicator cannot be   maintenance manual.
                               calibrated or the
                               turbine inlet
                               temperature probe
                               fails the
                               inspection) with
                               serviceable parts
                               that are listed in
                               paragraph (e) of
                               this AD.
(iii) Within the next 100     (A) Incorporate the   Not applicable.
 hours TIS after August 31,    emergency
 1999 (the effective date of   procedures
 the AD 99-15-04), unless      presented in
 the applicable Pilot's        paragraph (g) of
 Operating Handbook (POH)      this AD into the
 revision is incorporated as   POH.
 presented in paragraph (f)   (B) This may be
 of this AD.                   accomplished by
                               inserting a copy of
                               this AD into the
                               POH..
(iv) As of July 28, 2000      Do not install one    Use the procedures
 (the effective date of this   of the affected       located in the
 AD).                          Lewis or Transicoil   previously
                               turbine inlet         referenced
                               temperature gauges    maintenance manual
                               or probes without     sections and pages.
                               assuring that it is
                               airworthy and
                               properly calibrated.
------------------------------------------------------------------------

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

------------------------------------------------------------------------
       Compliance time               Action          In accordance with
------------------------------------------------------------------------
(i) Within the next 100       (A) Perform the       For serial numbers
 hours TIS after August 31,    Turbine Inlet         4622001 through
 1999 (the effective date of   Temperature Gauge     4622200 and 4636001
 AD 99-15-04).                 and Probe Cleaning    through 4636020,
                               and Inspection.       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    For serial numbers
                               Turbine Inlet         4622001 through
                               Temperature System    4622200 and 4636001
                               Calibration.          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  Repair or replace     Equipment
 after the above cleaning,     any failed parts      manufacturer
 inspection, and calibration.  (the turbine inlet    instructions and
                               temperature system    the applicable
                               indicator cannot be   maintenance manual.
                               calibrated or the
                               turbine inlet
                               temperature probe
                               fails the
                               inspection) with
                               serviceable parts
                               that are listed in
                               paragraph (e) of
                               this AD.
(iii) Upon accumulating 250   Replace the turbine   Equipment
 hours TIS on the currently    inlet temperature     manufacturer
 installed turbine inlet       probe with a new      instructions and
 temperature probe or within   part number 481-389   the applicable
 the next 100 hours TIS        or 481-392 probe.     maintenance manual.
 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.
(iv) Within the next 100      (A) Incorporate the   Not applicable.
 hours TIS after August 31,    emergency
 1999 (the effective date of   procedures
 the AD 99-15-04), unless      presented in
 the applicable Pilot's        paragraph (g) of
 Operating Handbook (POH)      this AD into the
 revision is incorporated as   POH.
 presented in paragraph (f)   (B) This may be
 of this AD.                   accomplished by
                               inserting a copy of
                               this AD into the
                               POH..
(v) As of July 28, 2000 (the  Do not install one    Use the procedures
 effective date of this AD).   of the affected       located in the
                               Lewis or Transicoil   previously
                               turbine inlet         referenced
                               temperature gauges    maintenance manual
                               or probes without     sections and pages.
                               assuring that it is
                               airworthy and
                               properly calibrated.
------------------------------------------------------------------------

    (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.

[[Page 33748]]

    (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      471-008. This is the only
 Analog Indicator.                        indicator that has a zero
                                          adjustment screw.
(2) Lewis Turbine Inlet Temperature      548-811. Since this indicator
 Digital Indicator.                       does not have a zero
                                          adjustment screw, you must
                                          return it to the factory for
                                          adjustment or replacement.
(3) Lewis Turbine Inlet Temperature      471-009 for the Model PA-46-
 Probe.                                   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:

------------------------------------------------------------------------
                                                       Affected serial
              POH                  Revision/date           numbers
------------------------------------------------------------------------
VB-1200.......................  16/March 19, 1999..  46-8408001 through
                                                      46-8608067 and
                                                      4608001 through
                                                      4608007.
VB-1300.......................  13/February 25,      4608008 through
                                 1999.                4608140.
------------------------------------------------------------------------

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

------------------------------------------------------------------------
                                                       Affected serial
              POH                  Revision/date           numbers
------------------------------------------------------------------------
VB-1332.......................  16/November 14,      4622001 through
                                 1997.                4622200.
VB-1609.......................  1/November 21, 1997  463001 through
                                                      4636020.
VB-1602.......................  1/November 28, 1997  4636021 through
                                                      4636131.
VB-1446.......................  New/December 3,      4636132 through
                                 1997.                4636195.
VB-1710.......................  New/February 23,     All serial numbers
                                 1999.                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: ``<a href="/cdn-cgi/l/email-protection#30745f5e515c541e695f455e57705651511e575f46"><span class="__cf_email__" data-cfemail="82c6edece3eee6acdbedf7ece5c2e4e3e3ace5edf4">[email protected]</span></a>''.
    (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 
Secs. 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


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