99-15-04: Turbine Inlet Temperature System Calibration

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 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: POH Revision/Date Affected serial numbers VB-1200 16/March 19, 1999 46-8408001 through 46-8608067 and 4608001 through 4608007 VB-1300 13/February 25, 1999 4608008 through 4608140 (2) For those operators of the Model PA-46-350P airplanes that do not have the applicable POH revision incorporated as follows: POH Revision/Date Affected serial numbers 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 (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 section 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 sections 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.