AD Amdt-39-11747 - Airworthiness Directives; The New Piper Aircraft, Inc., Models PA-46-310P and...

Type	Manufacturer	Model	Details
aircraft	Piper	Various	Airworthiness Directives; The New Piper Aircraft, Inc., Models PA-46-310P and PA-46-350P Airplanes

Unsafe Condition

Improperly calibrated turbine inlet temperature indicators or defective turbine inlet temperature probes could result in engine damage/failure with consequent loss of control of the airplane.

AI-generated summary from the source AD text. Verify against the official source before acting.

Required Actions

Calibrate the turbine inlet temperature system to assure accuracy of the existing turbine inlet temperature indicator and wiring. Repair or replace any turbine inlet temperature system that fails the calibration test. Repetitively replace the turbine inlet temperature probe on Model PA-46-350P airplanes. Insert a copy of the AD into the Pilot's Operating Handbook (POH) of certain airplanes.

AI-generated summary from the source AD text. Verify against the official source before acting.

Compliance Time

Before further flight

AI-generated summary from the source AD text. Verify against the official source before acting.

Affected Aircraft

The New Piper Aircraft, Inc., Models PA-46-310P and PA-46-350P airplanes, all serial numbers, 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.

AI-generated summary from the source AD text. Verify against the official source before acting.

Federal Register Abstract

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.

Document Text

Show stored source text (verify against official source)

[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 [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 00-13083]

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

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&#160;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&#160;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

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

Applicability

Unsafe Condition

Required Actions

Compliance Time

Affected Aircraft

Federal Register Abstract

Document Text