COMMENTS DUE DATE
(a) The FAA must receive comments on this AD action by February 14, 2011.
AFFECTED ADS
(b) This AD supersedes AD 99-15-04 R1, Amendment 39-11747.
APPLICABILITY
(c) This AD applies to the following Piper Aircraft, Inc. (type certifi-
cate previously held by The New Piper Aircraft, Inc.) Models PA-46
-310P, PA-46-350P, and PA-46R-350T airplanes that:
(1) Are certificated in any category; and
(2) Equipped with a turbine inlet temperature (T.I.T.) system identified
in table 1 of this AD. Relief from this 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 T.I.T. gauge and probe.
GROUP 1--AIRPLANES PREVIOUSLY AFFECTED BY AD 99-15-04 R1
--------------------------------------------------------------------------
MODELS SERIAL NUMBERS (S/N)
--------------------------------------------------------------------------
PA-46-310P (Malibu)................... 46-8408001 through 46-8608067
and 4608001 through 4608140.
PA-46-350P (Malibu Mirage)............ 4622001 through 4622200 and
4636001 through 4636020.
--------------------------------------------------------------------------
GROUP 2--AIRPLANES NOT PREVIOUSLY AFFECTED BY AD 99-15-04 R1
--------------------------------------------------------------------------
MODELS SERIAL NUMBERS (S/N)
--------------------------------------------------------------------------
PA-46-350P (Malibu Mirage)............ 4636021 and subsequent.
PA-46R-350T (Matrix).................. 4692001 and subsequent.
--------------------------------------------------------------------------
TABLE 1 -- AFFECTED AIRPLANE MODELS AND CORRESPONDING AFFECTED LEWIS OR
TRANSICOIL PART NUMBERS (P/NS)
---------------------------------------------------------------------------------------------------
MODELS S/N INDICATION SYSTEM P/N PROBE P/N
---------------------------------------------------------------------------------------------------
PA-46-310P.. 46-8408001 through 46- Lewis T.I.T. analog 471-009 or 481-387.
8608067 and 4608001 indicators P/N 471-008.
through 4608140.
PA-46-350P.. 4622001 through 4622200 Lewis T.I.T. analog 481-389 or 481-392 or
and 4636001 through indicators P/N 471-008. 686-216 (preferred).
4636020.
PA-46-350P.. 4636021 through 4636374 Lewis T.I.T. digital 481-389 or 481-392 or
indicators P/N 548-811. 686-216 (preferred).
PA-46-350P.. 4636375 and subsequent. Avidyne Entegra or 686-216.
other Electronic
Flight Information
System (EFIS) display.
PA-46R-350T. 4692001 and subsequent. Avidyne Entegra or 686-216.
other EFIS display.
---------------------------------------------------------------------------------------------------
SUBJECT
(d) Joint Aircraft System Component (JASC)/Air Transport Association (ATA)
of America Code 77, Engine Indicating.
UNSAFE CONDITION
(e) This AD was prompted by field reports that indicated service accuracy
problems with the existing turbine inlet temperature system on certain
Models PA-46-310P, PA-46-350P, and PA-46R-350T airplanes. We are
issuing this AD 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.
COMPLIANCE
(f) For Group 1 airplanes: Comply with this AD within the compliance times
specified, unless already done.
TABLE 2--GROUP 1 AIRPLANES
[AIRPLANES PREVIOUSLY AFFECTED BY AD 99-15-04 R1]
--------------------------------------------------------------------------
ACTIONS COMPLIANCE PROCEDURES
--------------------------------------------------------------------------
(1) Clean and inspect the Within the next Follow Piper Airplane
turbine inlet temperature 100 hours time- Maintenance Manual
gauge and probe. in-service (TIS) PA-46-310P/PA-46-350P
after August 31, Part Number 761-783,
1999 (the Chapter 77-20-00,
effective date section A.(1)(d),
retained from AD pages 1 and 2; and
99-15-04). Piper Airplane
Maintenance Manual
PA-46-350P Part
Number 761-876,
Chapter 77-20-00,
section 1.C, pages 1
and 2, as
applicable.
(2) Calibrate the turbine Within the next Follow Piper Airplane
inlet temperature system. 100 hours TIS Maintenance Manual
after August 31, PA-46-310P/PA-46-350P
1999 (the Part Number 761-783,
effective date Chapter 77-20-00,
retained from AD section A.(1)(g),
99-15-04). pages 3 and 4; and
Piper Airplane
Maintenance Manual
PA-46-350P Part
Number 761-876,
Chapter 77-20-00,
section 1.F, pages 2
through 4, as
applicable; or Piper
Service Bulletin No.
995C, dated November
17, 2009.
(3) If the turbine inlet Before further Follow Piper Airplane
temperature probe fails the flight after the Maintenance Manual
inspection required in cleaning and PA-46-310P/PA-46-350P
paragraph (f)(1) of this AD inspection Part Number 761-783,
and/or the turbine inlet required in Chapter 77-20-00,
temperature system indicator paragraph (f)(1) section A.(1)(f),
cannot be calibrated as and the page 2; and Piper
required in paragraph (f)(2) calibration Airplane Maintenance
of this AD, replace any required in Manual PA-46-350P
failed parts with a paragraph (f)(2) Part Number 761-876,
serviceable part listed in of this AD. Chapter 77-20-00,
table 1 of this AD as long as section 1.E., page
it has been inspected and 2, as applicable; or
properly calibrated. Piper Service
Bulletin No. 995C,
dated November 17,
2009.
(4) Incorporate the Within the next Not applicable.
information from Appendix 1 100 hours TIS
and Appendix 2, as after August 31,
applicable, of this AD into 1999 (the
the Emergency Procedures effective date
section of the pilot retained from AD
operating handbook (POH). 99-15-04).
This may be done by inserting
a copy of this AD into the
POH.
(5) Only install a part listed As of July 28, Not applicable.
in table 1 of this AD after 2000 (the
it has been inspected and effective date
properly calibrated. of AD 99-15-04
R1).
(6) Model PA-46-350P airplanes Upon accumulating For serial numbers
only: Replace the turbine 250 hours TIS on 4622001 through
inlet temperature probe with the currently 4622200: Follow
a new part number 481-389, installed Piper Airplane
481-392, or 686-216 probe turbine inlet Maintenance Manual
preferred). This action is temperature PA-46-310P/PA-46-
not required for Model PA-46- probe or within 350P Part Number 761-
310P. the next 100 783, Chapter 77-20-
hours TIS after 00, section
August 31, 1999 A.(1)(f), page 2; or
(the effective Piper Service
date retained Bulletin No. 995C,
from AD 99-15- dated November 17,
04), whichever 2009.
occurs later,
and thereafter
at intervals not
to exceed 250
hours TIS.
For serial numbers
4636001 through
4636020: Follow
Piper Airplane
Maintenance Manual
PA-46-350P Part
Number 761-876,
Chapter 77-20-00,
section 1.E., page
2: or Piper Service
Bulletin No. 995C,
dated November 17,
2009.
--------------------------------------------------------------------------
(g) For Group 2 airplanes: Comply with this AD within the compliance times
specified, unless already done.
TABLE 3--GROUP 2 AIRPLANES
[AIRPLANES NOT PREVIOUSLY AFFECTED BY AD 99-15-04 R1]
--------------------------------------------------------------------------
ACTIONS COMPLIANCE PROCEDURES
--------------------------------------------------------------------------
(1) Model PA-46-350P Within the next 100 Follow Piper
airplanes, S/Ns 4636021 hours TIS after the Airplane
through 4636374 only: Clean effective date of Maintenance Manual
and inspect the turbine this AD. PA-46-350P Part
inlet temperature gauge and Number 761-876,
probe. Chapter 77-20-00,
section 1.C, pages
1 and 2, as
applicable.
(2) Model PA-46-350P Before further Follow Piper Service
airplanes, S/Ns 4636021 flight after the Bulletin No. 995C,
through 4636374 only: If cleaning and dated November 17,
the turbine inlet inspection required 2009.
temperature probe fails the in paragraph (g)(1)
inspection required in and the calibration
paragraph (g)(1) of this AD required in
and/or the turbine inlet paragraph (g)(2) of
temperature system this AD.
indicator cannot be
calibrated as required in
paragraph (g)(2) of this
AD, replace any failed
parts with a serviceable
part listed in table 1 of
this AD as long as it has
been inspected and properly
calibrated.
(3) All Group 2 airplanes: Upon accumulating Piper Service
Replace the turbine inlet 250 hours TIS on Bulletin No. 995C,
temperature probe with a the currently dated November 17,
new part number 686-216 installed turbine 2009.
probe. 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.
(4) All Group 2 airplanes: Within the next 100 Not applicable.
Incorporate the information hours TIS after the
from Appendix 2 of this AD effective date of
into the Emergency this AD.
Procedures section of the
POH. This may be done by
inserting a copy of this AD
into the POH.
(5) All Group 2 airplanes: As of the effective Not applicable.
Only install a part listed date of this AD.
in table 1 of this AD after
it has been inspected and
properly calibrated.
--------------------------------------------------------------------------
ALTERNATIVE METHODS OF COMPLIANCE (AMOCS)
(h)(1) The Manager, Atlanta Aircraft Certification Office, FAA, has the
authority to approve AMOCs for this AD, if requested using the
procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19,
send your request to your principal inspector or local Flight
Standards District Office, as appropriate. If sending information
directly to the manager of the ACO, send it to the attention of the
person identified in the Related Information section of this AD.
(2) Before using any approved AMOC, notify your Principal Maintenance Ins-
pector or Principal Avionics Inspector, as appropriate, or lacking a
principal inspector, your local Flight Standards District Office.
(3) AMOCs approved for AD 99-15-04 R1 are approved as AMOCs for this AD.
RELATED INFORMATION
(i) For more information about this AD, contact Darby Mirocha, Aerospace
Engineer, FAA, Atlanta Aircraft Certification Office, 1701 Columbia
Avenue, College Park, Georgia 30337; phone: (404) 474-5573; fax: (404)
474-5605; e-mail: darby.mirocha@faa.gov.
(j) For service information identified in this AD, contact Piper Aircraft,
Inc., 2926 Piper Drive, Vero Beach, Florida 32960; telephone: (772)
567-4361; fax: (772) 978-6573; Internet: http://www.piper.com/home/
pages/publications.cfm. You may review copies of the referenced
service information at the FAA, Small Airplane Directorate, 901 Locust
St., Kansas City, MO 64106. For information on the availability of
this material at the FAA, call (816) 329- 4148.
APPENDIX 1 TO DOCKET NO. FAA-2010-1295
MODEL PA-46-310P (MAILBU)--EMERGENCY PROCEDURES FOR THE PILOT'S OPERATING
HANDBOOK (POH)
(1) If the turbine inlet temperature indication fails or is suspected of
failure during takeoff, climb, descent, or landing, maintain FULL RICH
mixture to assure adequate fuel flow for engine cooling.
(2) If the turbine inlet temperature indication fails or is suspected of
failure 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.
APPENDIX 2 TO DOCKET NO. FAA-2010-1295
MODEL PA-46-350P (MALIBU MIRAGE) AND MODEL PA-46R-350T (MATRIX)--EMERGENCY
PROCEDURES FOR THE PILOT'S OPERATING HANDBOOK (POH)
(1) If the turbine inlet temperature indication fails or is suspected of
failure 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.
(2) If the turbine inlet temperature indication fails or is suspected of
failure 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.
Issued in Kansas City, Missouri on December 22, 2010. Earl Lawrence, Man-
ager, Small Airplane Directorate, Aircraft Certification Service.
DATES: We must receive comments on this proposed AD by February 14, 2011.
DEPARTMENT OF TRANSPORTATION
FEDERAL AVIATION ADMINISTRATION
14 CFR Part 39
[Docket No. FAA-2010-1295; Directorate Identifier 2010-CE-060-AD] RIN
2120-AA64
AIRWORTHINESS DIRECTIVES; Piper Aircraft, Inc. (Type Certificate Previous-
ly Held by The New Piper Aircraft, Inc.) Models PA-46-310P, PA-46-350P,
and PA-46R-350T Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
--------------------------------------------------------------------------
SUMMARY: We propose to supersede an existing airworthiness directive (AD)
that applies to certain Piper Aircraft, Inc. Models PA-46-310P and PA-46
-350P airplanes that are equipped with a Lewis or Transicoil turbine inlet
temperature (T.I.T.) gauge and associated probe. The existing AD currently
requires calibrating the T.I.T. system; replacing any T.I.T. system that
fails the calibration test; repetitively replacing the T.I.T. probe on
certain Model PA-46-350P airplanes; and inserting a copy of the AD into
the pilot's operating handbook (POH) for certain airplanes. Since we
issued that AD, the manufacturer has revised related service information
and added an airplane model to the list of affected airplanes. This
proposed AD would retain the actions required by AD 99-15-04 R1, add
certain Model PA-46R-350T airplanes to the Applicability section, expand
the applicability to include other T.I.T. systems, and incorporate new
service information. We are proposing this AD to prevent improper engine
operation caused by improperly calibrated T.I.T. indicators or defective
T.I.T. probes, which could result in engine damage/failure with consequent
loss of control of the airplane.
DATES: We must receive comments on this proposed AD by February 14, 2011.
ADDRESSES: You may send comments by any of the following methods:
Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the
instructions for submitting comments.
Fax: 202-493-2251.
Mail: U.S. Department of Transportation, Docket Operations, M-30, West
Building Ground Floor, Room W12-140, 1200 New Jersey Avenue, SE.,
Washington, DC 20590.
Hand Delivery: Deliver to Mail address above between 9 a.m. and 5 p.m.,
Monday through Friday, except Federal holidays.
For service information identified in this AD, contact Piper Aircraft,
Inc., 2926 Piper Drive, Vero Beach, Florida 32960; telephone: (772) 567-
4361; fax: (772) 978-6573; Internet: http://www.newpiper.com/company/
publications.asp. You may review copies of the referenced service
information at the FAA, Small Airplane Directorate, 901 Locust St., Kansas
City, Missouri 64106. For information on the availability of this material
at the FAA, call (816) 329-4148.
EXAMINING THE AD DOCKET
You may examine the AD docket on the Internet at http://www.regulations.
gov; or in person at the Docket Management Facility between 9 a.m. and 5
p.m., Monday through Friday, except Federal holidays. The AD docket
contains this proposed AD, the regulatory evaluation, any comments
received, and other information. The street address for the Docket Office
(phone: 800-647-5527) is in the ADDRESSES section. Comments will be
available in the AD docket shortly after receipt.
FOR FURTHER INFORMATION CONTACT: Darby Mirocha, Aerospace Engineer, FAA,
Atlanta Aircraft Certification Office, 1701 Columbia Avenue, College Park,
Georgia 30337; phone: (404) 474-5573; fax: (404) 474-5605; e-mail:
darby.mirocha@faa.gov.
SUPPLEMENTARY INFORMATION:
COMMENTS INVITED
We invite you to send any written relevant data, views, or arguments about
this proposed AD. Send your comments to an address listed under the
ADDRESSES section. Include "Docket No. FAA-2010-1295; Directorate Identif-
ier 2010-CE-060-AD" at the beginning of your comments. We specifically
invite comments on the overall regulatory, economic, environmental, and
energy aspects of this proposed AD. We will consider all comments received
by the closing date and may amend this proposed AD because of those
comments.
We will post all comments we receive, without change, to http://
www.regulations.gov, including any personal information you provide. We
will also post a report summarizing each substantive verbal contact we
receive about this proposed AD.
DISCUSSION
On May 17, 2000, we issued AD 99-15-04 R1, Amendment 39-11747 (65 FR
33745, May 25, 2000), for certain Piper Aircraft, Inc. (type certificate
previously held by The New Piper Aircraft, Inc.) Models PA-46-310P and PA
-46-350P airplanes that are equipped with a Lewis or Transicoil turbine
inlet temperature (T.I.T.) gauge and associated probe. That AD required
calibrating the T.I.T. system; replacing any T.I.T. system that fails the
calibration test; repetitively replacing the T.I.T. probe on Model PA-46
-350P airplanes; and inserting a copy of the AD into the Emergency
Procedures section of the POH for certain airplanes. That AD resulted from
field reports that indicated service accuracy problems with the existing
T.I.T. system on certain Piper Aircraft, Inc. Models PA-46-310P and PA-46
-350P. We issued that AD to prevent improper engine operation caused by
improperly calibrated T.I.T. indicators or defective T.I.T. probes, which
could result in engine damage/failure with consequent loss of control of
the airplane.
ACTIONS SINCE EXISTING AD WAS ISSUED
Since we issued AD 99-15-04 R1, the manufacturer has revised related
service information and has added an airplane model to the list of
affected airplanes. We have also determined that the scope of this
proposed AD goes beyond only airplanes equipped with Lewis or Transicoil
gauges and/or probes.
RELEVANT SERVICE INFORMATION
We reviewed Piper Aircraft, Inc. Service Bulletin No. 995C, dated November
17, 2009. The service information describes procedures for calibrating the
T.I.T. system and replacing the probe.
FAA'S DETERMINATION
We are proposing this AD because we evaluated all the relevant information
and determined the unsafe condition described previously is likely to
exist or develop in other products of the same type design.
PROPOSED AD REQUIREMENTS
This proposed AD would retain the requirements of AD 99-15-04 R1. This
proposed AD would also add certain Model PA-46R-350T airplanes to the
Applicability section, expand the applicability to include other T.I.T.
systems, and incorporate new service information.
COSTS OF COMPLIANCE
We estimate that this proposed AD affects 898 airplanes of U.S. registry.
We estimate the following costs to comply with this proposed AD:
ESTIMATED COSTS
---------------------------------------------------------------------------------------------------
COST PER COST ON U.S.
ACTION LABOR COST PARTS COST PRODUCT OPERATORS
---------------------------------------------------------------------------------------------------
Clean and inspect the turbine 1 work-hour x $85 Not applicable. $85 $85 x 780 affected
inlet temperature gauge and per hour = $85. airplanes =
probe for certain Models PA-46- $66,300.
310P and PA-46-350P airplanes.
Calibrate the turbine inlet 4 work-hours x $85 Not applicable. 340 $340 x 427 affected
temperature gauge for certain per hour = $340. airplanes =
Models PA-46-310P and PA-46-350P $145,180.
airplanes.
Incorporate emergency procedures 1 workhour x $85 Not applicable. 85 $85 x 898 affected
into POH. per hour = $85. airplanes =
$76,330.
---------------------------------------------------------------------------------------------------
The requirements of this proposed AD add no additional economic burden
other than the addition of an airplane model to the Applicability section.
We estimate the following costs to do any necessary replacements that
would be required based on the results of the proposed inspection. We have
no way of determining the number of aircraft that might need these
replacements:
ON-CONDITION COSTS
--------------------------------------------------------------------------
COST PER
ACTION LABOR COST PARTS COST PRODUCT
--------------------------------------------------------------------------
Replace probe....... 1 work-hour x $85 $384 $469
per hour = $85.
--------------------------------------------------------------------------
AUTHORITY FOR THIS RULEMAKING
Title 49 of the United States Code specifies the FAA's authority to issue
rules on aviation safety. Subtitle I, Section 106, describes the authority
of the FAA Administrator. Subtitle VII, Aviation Programs, describes in
more detail the scope of the Agency's authority.
We are issuing this rulemaking under the authority described in Subtitle
VII, Part A, Subpart III, Section 44701, "General requirements." Under
that section, Congress charges the FAA with promoting safe flight of civil
aircraft in air commerce by prescribing regulations for practices,
methods, and procedures the Administrator finds necessary for safety in
air commerce. This regulation is within the scope of that authority
because it addresses an unsafe condition that is likely to exist or devel-
op on products identified in this rulemaking action.
REGULATORY FINDINGS
We have determined that this proposed AD would not have federalism
implications under Executive Order 13132. This proposed AD would 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.
For the reasons discussed above, I certify that the proposed regulation:
(1) Is not a "significant regulatory action" under Executive Order 12866,
(2) Is not a "significant rule" under the DOT Regulatory Policies and Pro-
cedures (44 FR 11034, February 26, 1979),
(3) Will not affect intrastate aviation in Alaska, and
(4) 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.
LIST OF SUBJECTS IN 14 CFR PART 39
Air transportation, Aircraft, Aviation safety, Incorporation by reference,
Safety.
THE PROPOSED AMENDMENT
Accordingly, under the authority delegated to me by the Administrator, the
FAA proposes to amend 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. The FAA amends Sec. 39.13 by removing airworthiness directive (AD) 99
-15-04 R1, Amendment 39-11747 (65 FR 33745, May 25, 2000), and adding
the following new AD: