Federal Aviation Administration (FAA), DOT.
Notice of proposed rulemaking (NPRM).
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.
We must receive comments on this proposed AD by February 14, 2011.
You may send comments by any of the following methods:
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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:
You may examine the AD docket on the Internet at
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:
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
We will post all comments we receive, without change, to
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.
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.
We reviewed Piper Aircraft, Inc. Service Bulletin No. 995C, dated
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.
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.
We estimate that this proposed AD affects 898 airplanes of U.S. registry.
We estimate the following costs to comply with this proposed AD:
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:
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 develop on products identified in this rulemaking action.
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 Procedures (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.
Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety.
Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 14 CFR part 39 as follows:
1. The authority citation for part 39 continues to read as follows:
49 U.S.C. 106(g), 40113, 44701.
2. The FAA amends § 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:
(a) The FAA must receive comments on this AD action by February 14, 2011.
(b) This AD supersedes AD 99–15–04 R1, Amendment 39–11747.
(c) This AD applies to the following Piper Aircraft, Inc. (type certificate previously held by The New Piper Aircraft, Inc.) Models PA–
(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.
(d) Joint Aircraft System Component (JASC)/Air Transport Association (ATA) of America Code 77, Engine Indicating.
(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.
(f) For Group 1 airplanes: Comply with this AD within the compliance times specified, unless already done.
(g) For Group 2 airplanes: Comply with this AD within the compliance times specified, unless already done.
(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 Inspector 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.
(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:
(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:
(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.
(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.