TCDS A25SO

Page No. 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 19 20 Rev. No. 42 16 34 35 24 23 36 41 38 38 29 37 41 36 41 35 38 36 38 39 Page No. 21 22 23 24 25 Rev. No. 41 41 38 42 41 DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION A25SO Revision 42 Piper PA-46-310P PA-46-350P PA-46-500TP PA-46R-350T PA-46-600TP PA-46-701TP February 16, 2026 TYPE CERTIFICATE DATA SHEET NO. A25SO This data sheet, which is part of Type Certificate No. A25SO, prescribes conditions and limitations under which the product for which type certificate was issued meets the airworthiness requirements of the Federal Aviation Regulations. Type Certificate Holder: Piper Aircraft, Inc. 2926 Piper Drive Vero Beach, Florida 32960 Type Certificate Holder Record The New Piper Aircraft, Inc transferred TC A25SO to Piper Aircraft, Inc on August 7, 2006. I. - Model PA-46-310P (Malibu), 6 PCLM (Normal Category), Approved September 27, 1983. Engine Teledyne Continental, TC No. E8CE, Model TSI0-520-BE Fuel 100/100LL minimum grade aviation gasoline Engine Limits For all operations: 2600 RPM and 38" Hg MAP (310 HP), sea level to 24,000 ft. 2600 RPM and 35" Hg MAP above 24,000 ft. 2400 RPM and 31" Hg MAP maximum when leaned to 50  F lean of peak, any altitude. Propeller and Propeller Limits Hartzell, TC No. P-920, Hub BHC-C2YF-1BF, Blade F8052 ( ) Pitch: High 38.0   1, Low 16.0  0.2 at 30" station. Diameter: Not over 80", not under 78". Spinner: Hartzell D-4810 or D-4810P. Governor: Hartzell Model E-5-2. Airspeed Limits VNE (Never Exceed) 203 KIAS V NO (Maximum Structural Cruise) 173 KIAS V A (Maneuvering 4100 lb.) 135 KIAS V A (Maneuvering 2450 lb.) 103 KIAS V FE (Maximum Flaps Extended) 120 KIAS V LO (Maximum Landing Gear Operation) Extension 170 KIAS Retraction 130 KIAS V LE (Maximum Landing Gear Extended) 200 KIAS A25SO Page 2 of 25 C.G. Range (Gear Extended) WT. FWD. LIMIT AFT LIMIT (LB.) IN. AFT OF DATUM IN. AFT OF DATUM 4100 143.3 in. 147.1 in. 3680 136.1 in. 147.1 in. 2450 or less 130.7 in. 147.1 in. Empty Weight C.G. Range None Maximum Weight Ramp : 4118 lb. Takeoff : 4100 lb. Landing : 3900 lb. No. of Seats 6 (2 at +135.5, 2 at +177.0, 2 at +218.75) Maximum Baggage 100 lb. at (+88.6) (Fwd.) 100 lb. at (+248.23) (Aft) Fuel Capacity 122 gals. at (+150.31) (2 wing tanks) See NOTE 1 for data on system fuel. Oil Capacity 8 qts. at (+53.5) See NOTE 1 for data on system oil. Maximum Operating Altitude 25,000 ft. Maximum Cabin Operating Pressure Differential 5.5 PSID Control Surface Movements Ailerons (1) Up 18 Down 18 Elevator (.5) Up 23.5 Down 14.5  Rudder (+1, -0) Left 26 Right 30 Elevator (+0, -1) Down 24.5 Up 19 Trim Tab (Elevator Neutral) Wing Flaps S/N 46-8408001 to 46-8508109 Up 0 (1) Down 35 (+0, -1) Wing Flaps S/N 46-8608001 and up Up 0 (1) Down 35 (1) Manufacturer's Serial Numbers 46-8408001 through 46-8408087, 46-8508001 through 46-8508109, 46-8608001 through 46-8608067, 4608001 through 4608140. II. - Model PA-46-350P (Malibu Mirage), 6 PCLM (Normal Category), Approved August 30, 1988. Engine Textron Lycoming, TC No. E14EA, Model TIO-540-AE2A Fuel 100/100LL mínimum grade aviation gasoline Engine Limits For all operations: 2500 RPM and 42.0" Hg MAP (350 HP), sea level to 20,600 ft. 42 - 1.6" Hg MAP decrease per each 1000 ft. altitude increase, 20,600 ft. to 25,000 ft. Propeller and Propeller Limits Hartzell, TC No. P42GL, Hub HC-I2YR-1BF, Blade F8074 (standard 2 blade-Serial Numbers 4622001 through 4622200 and 4636001 through 4636195) Pitch: High 40.5   0.5 Low 17.6  0.2 at 30" station. Diameter: Not over 80", not under 79". Spinner: Hartzell A-2298-3P. Governor: Hartzell Model V-5-2 or V-11-1 The following limitation is applicable to the two-bladed aluminum propeller installation: A25SO Page 3 of 25 Do not exceed 36” MAP below 2400 RPM Do not exceed 32” MAP below 2300 RPM Hartzell, TC No. P33EA, Hub HC-I3YR-1E, Blade 7890K, 3-blade, Serial Numbers 4636132 and up Pitch: High 38.7°  0.5 Low 13.65  0.15 at 30" station. Diameter: 80" Spinner: Hartzell D-6750P. Governor: Hartzell Model V-5-2 or V-11-1 Hartzell, TC No. P33EA, Hub HC-I3Y1R-1N, Blade N7605C+2, or N7605CK+2, 3- blade, Serial Numbers 4636460, 4636463 and up Pitch: High 38.0°  1.0 Low 14.0  0.2 at 30" station. Diameter: 80" Spinner: Hartzell D-6750-1P. Governor: Hartzell Model V-5-2, V-11-1 or S-1-30 Airspeed Limits VNE (Never Exceed) 198 KIAS V NO (Maximum Structural Cruise) 168 KIAS V A (Maneuvering 4340 lb.) (S/N 4636196 & up) 133 KIAS V A (Maneuvering 4300 lb.) 133 KIAS V A (Maneuvering 2450 lb.) 100 KIAS V FE (Maximum Flaps Extended) 116 KIAS V LO (Maximum Landing Gear Operation) Extension 165 KIAS Retraction 126 KIAS V LE (Maximum Landing Gear Extended) 195 KIAS C.G. Range (Gear Extended) WT. FWD. LIMIT AFT LIMIT (LB.) IN. AFT OF DATUM IN. AFT OF DATUM 4300 (4340) 143.3 in. (144.1 in) 147.1 in. 4100 (4123) 139.1 in. (139.6 in) 147.1 in. 4000 137.0 in. 146.5 in. 2450 130.7 in. 137.6 in 2400 130.7 in. 137.3 in. Note: Numbers in parentheses apply to serial numbers 4636196 and up. Empty Weight C.G. Range None Maximum Weight Ramp : 4318 lb. (4358 lb.) Takeoff : 4300 lb. (4340 lb.) Landing : 4100 lb. (4123 lb.) Note: Numbers in parentheses apply to serial numbers 4636196 and up. No. of Seats 6 (2 at +135.5, 2 at +177.0, 2 at +218.75) Maximum Baggage 100 lb. at (+88.6) (Fwd.) 100 lb. at (+248.23) (Aft) Fuel Capacity 122 gals. at (+150.31) (2 wing tanks) See NOTE 1 for data on system fuel. Oil Capacity 12 qts. at (+53.5) See NOTE 1 for data on system oil. Maximum Operating Altitude 25,000 ft. A25SO Page 4 of 25 Maximum Cabin Operating Pressure Differential 5.5 PSID (+0.1, -0.15) Control Surface Movements Ailerons (1) Up 18 Down 18 Elevator (0.5) Up 23.5 Down 14.5 Rudder (+1, -0) Left 26 Right 30 Elevator Trim Tab (+0, -1) (Elevator Neutral) Down 24.5 Up 19 Wing Flaps Up 0 (1) Down 10 (2) 20 (+2, -0) 36 (+0, -1) Manufacturer's Serial Numbers 4622001 through 4622200, and 4636001 and up. III. – Model PA-46-500TP (Malibu Meridian), 6PCLM (Normal Category), Approved September 27, 2000. Engine Pratt & Whitney Canada, PT6A-42A (per PWC Build Specifications BS1011, BS1192 or BS1430) Fuel Jet A and A-1 fuels conforming to Pratt & Whitney Specification 522 or Service Bulletin 3044, CPW204. (Fuels shall conform to the specification as listed or to subsequent revisions thereto.) MIL-DTL-85470 Fuel System Icing Inhibitor or equivalent must be used in the fuel in the amount up to 0.15% by volume. Oil (Engine & Gearbox) PWC PT6 Engine Service Bulletin No. 3001 lists approved brand oils. Engine Limits Takeoff and max continuous power 500 SHP Compressor Turbine Speed (Ng) 39000 RPM (104%)* Propeller Speed (Np) 2205 RPM* * See Note 5 Propeller and Propeller Limits Hartzell, T.C. No. P10NE, Hub HC-E4N-3Q, Blade E8501B-3.5 Pitch: Low 19.0  + 0.1at 30” station. Diameter: Not over 82.5”, not under 81.5”. Spinner: Hartzell D-630-5P Governor: Woodward Model 210 638 or Woodward Model 210 695 Airspeed Limits V MO (Maximum Operating Speed) 188 KIAS VO (Operating Maneuvering Speed) 127 KIAS VFE (Flaps Extended Speed for 10 Flaps) 168 KIAS VFE (Flaps Extended Speed for 20 Flaps) 135 KIAS VFE (Flaps Extended Speed for 36 Flaps) 118 KIAS VLO (Maximum Landing Gear Operation) Extension 168 KIAS Retraction 129 KIAS VLE (Maximum Landing Gear Extended) 168 KIAS C.G. Range For airplanes S/N 4697001, 4697003 through 4697156: WT. (LB.) FWD LIMIT IN. AFT OF DATUM AFT LIMIT IN. AFT OF DATUM 4892 140.22 in. 147.10 in. 4850 140.06 in. 147.10 in. 4100 137.23 in. 147.10 in. 3508 135.00 in. 143.67 in 3000 135.00 in. 140.75 in A25SO Page 5 of 25 For airplanes S/N 4697157 and up and earlier airplanes having Kit 767-360 installed: WT. (LB.) FWD LIMIT IN. AFT OF DATUM AFT LIMIT IN. AFT OF DATUM 5134 141.13 in. 147.10 in. 5092 140.97 in. 147.10 in. 4892 140.22 in. 147.10 in. 4850 140.06 in. 147.10 in. 4100 137.23 in. 147.10 in. 3508 135.00 in. 143.67 in. 3000 135.00 in. 140.75 in. Empty Weight C.G. Range None Maximum Weight RAMP (LB.) TAKEOFF (LB.) LANDING (LB.) MZFW (LB.) For airplanes S/N 4697001, 4697003 through 4697156: 4892 4850 4850 For airplanes S/N 4697157 and up and earlier airplanes having Kit 767-360 installed: 5134 5092 4850 4850 No. of Seats 6 (2 at +135.5, 2 at 177.0, 2 at 218.75) Maximum Baggage 100 lbs. at (+248.23) Fuel Capacity 173 gallons at (+148.75) (2 wing tanks) 170 gallons (1140 lbs.) useable See Note 1 for data on system fuel. Oil Capacity 12 quarts at (+77.76) See Note 1 for data on system oil. Maximum Operating Altitude 30,000 ft. OAT Operating Limitation For airplanes S/N 4697001, 4697003 through 4697173: +46 C (+115ºF) maximum -34C (-30ºF) minimum with Jet-A -41C (-42ºF) minimum with Jet A-1 For airplanes S/N 4697174 and up and S/N 4697001, 4697003 through 4697158 having Piper Kit 767-380 installed and S/N 4697159 through 4697173 having Piper Kit 767-381 installed: +46C (+115ºF) maximum -54C (-65ºF) minimum Minimum Fuel Temperature For airplanes S/N 4697159 and up and S/N 4697001, 4697003 through 4697158 having Piper Kit 767-380 installed: -34C (-30ºF) minimum for starting with Jet-A/A-1 -34C (-30ºF) minimum in-flight with Jet-A -41C (-42ºF) minimum inflight with Jet A-1 NOTE: When a mixture of Jet A and Jet A-1 is present in the fuel tanks, the Jet A minimum fuel temperature limits must be observed. Maximum Cabin Operating Pressure Differential 5.5 PSID (+0.1, -0.15) Control Surface Movements Aileron (+ 1 ) Up 18 Down 18  Elevator (+.5 ) Up 23.5  Down 14.5  Elevator Trim Tab (+0 ,-1) Up 19  Down 24.5  (Elevator Neutral) A25SO Page 6 of 25 Rudder (+1 -0) Left 26  Right 30  Rudder Trim Tab (+1 ) Left 13.5  Right 13  (Rudder Neutral) Wing Flaps Up 0  (+1) Down 10  (+2) 20  (+2,-0) 36  (+0,-1) Manufacturer’s Serial Numbers 4697001, 4697003 and up IV. - Model PA-46R-350T (Malibu Matrix), 6 PCLM (Normal Category), Approved October 26, 2007. Engine Textron Lycoming, TC No. E14EA, Model TIO-540-AE2A Fuel 100/100LL mínimum grade aviation gasoline Engine Limits For all operations: 2500 RPM and 42.0" Hg MAP (350 HP), sea level to 20,600 ft. 42 - 1.6" Hg MAP decrease per each 1000 ft. altitude increase, 20,600 ft. to 25,000 ft. Propeller and Propeller Limits Hartzell, TC No. P33EA, Hub HC-I3YR-1E, Blade 7890K or 7890B, 3-blade Pitch: High 38.7°  0.5 Low 13.65  0.15 at 30" station. Diameter: 80" Spinner: Hartzell D-6750P. Governor: Hartzell Model V-11-1 Hartzell, TC No. P33EA, Hub HC-I3Y1R-1N, Blade N7605+2 or N7605K+2, or N7605C+2, or N7605CK+2 3-blade, Serial Numbers 4692123 and up Pitch: High 38.0°  1.0 Low 14.0  0.2 at 30" station. Diameter: 80" Spinner: Hartzell D-6750-1P. Governor: Hartzell Model V-11-1 or S-1-30 Airspeed Limits VNE (Never Exceed) 198 KIAS V NO (Maximum Structural Cruise) 168 KIAS V A (Maneuvering 4340 lb.) 133 KIAS V A (Maneuvering 2900 lb.) 108 KIAS V FE (Maximum Flaps Extended for 10°) 165 KIAS V FE (Maximum Flaps Extended for 20°) 130 KIAS V FE (Maximum Flaps Extended for 36°) 116 KIAS V LO (Maximum Landing Gear Operation) Extension 165 KIAS Retraction 126 KIAS V LE (Maximum Landing Gear Extended) 195 KIAS C.G. Range (Gear Extended) WT. FWD. LIMIT AFT LIMIT (LB.) IN. AFT OF DATUM IN. AFT OF DATUM 4340 144.1 in 147.1 in. 4123 139.6 in 147.1 in. 4000 137.0 in. 146.5 in. 2900 132.5 in. 140.2 in Empty Weight C.G. Range None Maximum Weight Ramp : 4358 lb. Takeoff : 4340 lb. Landing : 4123 lb. A25SO Page 7 of 25 No. of Seats 6 (2 at +135.5, 2 at +177.0, 2 at +218.75) Maximum Baggage 100 lb. at (+88.6) (Fwd.) 100 lb. at (+248.23) (Aft) Fuel Capacity 122 gals. at (+150.31) (2 wing tanks) See NOTE 1 for data on system fuel. Oil Capacity 12 qts. at (+53.5) See NOTE 1 for data on system oil. Maximum Operating Altitude 25,000 ft. Control Surface Movements Ailerons (1) Up 18 Down 18 Elevator (0.5) Up 23.5 Down 14.5  Rudder (+1, -0) Left 26 Right 30 Elevator Trim Tab (+0, -1) (Elevator Neutral) Down 24.5 Up 19 Wing Flaps Up 0 (1) Down 10 (2) 20 (+2, -0) 36 (+0, -1) Manufacturer's Serial Numbers 4692001 through 4692214 V. – Model PA-46-600TP (M600), 6PCLM (Normal Category), Approved June 16, 2016. Engine Pratt & Whitney Canada, PT6A-42A (per PWC Build Specification BS1322 or BS1415) Fuel Jet A and A-1 fuels conforming to Pratt & Whitney Specification 522 or Service Bulletin 3044, CPW204. (Fuels shall conform to the specification as listed or to subsequent revisions thereto.) MIL-DTL-85470 Fuel System Icing Inhibitor or equivalent must be used in the fuel in the amount up to 0.15% by volume. Oil (Engine & Gearbox) PWC PT6 Engine Service Bulletin No. 3001 lists approved brand oils. Engine Limits Takeoff and max continuous power 600 SHP Compressor Turbine Speed (Ng) 39000 RPM (104%)* Propeller Speed (Np) 2205 RPM* * See Note 5 Propeller and Propeller Limits Hartzell, T.C. No. P10NE, Hub HC-E4N-3Q, Blade E8501K-3.5*1 Pitch: Low 19.0  + 0.1at 30” station. Diameter: Not over 82.5”, not under 81.5”. Spinner: Hartzell D-630-5P Governor: Woodward Model 210695 Hartzell, T.C. No. P00015CH, Hub 5D3-N338A1, Blade 78D01B Pitch: Low 17.7  + 0.1at 30” station Feather 83.2  + 0.5at 30” station Reverse -11.0 + 0.5at 30” station Diameter: 82.5 inches (No additional reduction permitted) Spinner: Hartzell Standard: 106917(P) or Light Weight: 105951(P) Governor: Woodward Model 210695 Airspeed Limits V MO (Maximum Operating Airspeed) 250 KCAS M MO (Maximum Operating Mach) 0.55 M VO (Maximum Operating Maneuvering Speed) 6000 lbs 151 KCAS 3750 lbs 119 KCAS VFE (Flaps Extended Speed for T/O Flaps) Flaps Extended Speed for T/O Flaps 145 KCAS Flaps Extended Speed for LND Flaps 108 KCAS VLE (Maximum Landing Gear Extended) 168 KCAS A25SO Page 8 of 25 VLO (Maximum Landing Gear Operation) V LOE Extension 168 KCAS V LOR Retraction 128 KCAS C.G. Range For airplanes S/N 4698001 and up: WT. (LB.) FWD LIMIT IN. AFT OF DATUM AFT LIMIT IN. AFT OF DATUM 6050 144.00 in. 146.00 in. 6000 144.00 in. 146.00 in. 5850 141.26 in 146.00 in. 5800 141.15 in. 146.00 in. 4850 139.05 in. 146.00 in. 3925 137.00 in 142.40 in 3500 137.00 in 140.00 in Empty Weight C.G. Range None Maximum Weight RAMP (LB.) TAKEOFF (LB.) LANDING (LB.) MZFW (LB.) For airplanes S/N 4698001 and up: 6050 6000 5800 4850 No. of Seats 6 (1 at +140.6, 1 at 141.8, 2 at 171.9, 2 at 223.8) Maximum Baggage 100 lbs. at (+248.23) Fuel Capacity 263.2 gallons at (+148.90) (2 wing tanks) 260 gallons (1742 lbs.) useable See Note 1 for data on system fuel. Oil Capacity 12 quarts at (+77.76) See Note 1 for data on system oil. Maximum Operating Altitude 30,000 ft. OAT Operating Limitation +46 C (+115ºF) maximum -54C (-65ºF) minimum Minimum Fuel Temperature -34 C (-30ºF) minimum for starting with Jet-A/A-1 -34C (-30ºF) minimum in-flight with Jet-A -41C (-42ºF) minimum inflight with Jet A-1 NOTE: When a mixture of Jet A and Jet A-1 is present in the fuel tanks, the Jet A minimum fuel temperature limits must be observed. Maximum Cabin Operating Pressure Differential 5.5 PSID (+0.1, -0.15) Control Surface Movements Aileron (+ 1) Up 24.7 Down 20 Elevator (+.5) Up 13  Down   Elevator Trim Tab (+0,-1) Up 19 Down  (Elevator Neutral) Rudder (+1-0) Left 20 Right 30 Rudder Trim Tab (+1) Left 13.5 Right 13 (Rudder Neutral) Wing Flaps Up 0 (+1) Down 15 (+1) 35 (+1) Manufacturer’s Serial Numbers 4698001, 4698004 and up A25SO Page 9 of 25 VI. – Model PA-46-701TP (M700), 6PCLM (Normal Category), Approved February 29, 2024. Engine Pratt & Whitney Canada, PT6A-52 (per PWC Build Specification BS1435) Fuel Jet A and A-1 fuels conforming to Pratt & Whitney Specification 522 or Service Bulletin 3044, CPW204. (Fuels shall conform to the specification as listed or to subsequent revisions thereto.) MIL-DTL-85470 Fuel System Icing Inhibitor or equivalent must be used in the fuel in the amount up to 0.15% by volume. Oil (Engine & Gearbox) PWC PT6 Engine Service Bulletin No. 13001 lists approved brand oils. Engine Limits Takeoff and max continuous power 700 SHP Compressor Turbine Speed (Ng) 39000 RPM (104.1%) Propeller Speed (Np) 2205 RPM* * See Note 8 Propeller and Propeller Limits Hartzell, T.C. No. P00015CH, Hub 5D3-N338A1, Blade 78D01B Pitch: Low 17.7  + 0.1at 30” station Feather 83.2  + 0.5at 30” station Reverse -11.0 + 0.5at 30” station Diameter: 82.5 inches (No additional reduction permitted) Spinner: Hartzell 105951(P) Governor: Woodward Model 210695 Airspeed Limits V MO (Maximum Operating Airspeed) 250 KCAS M MO (Maximum Operating Mach) 0.55 M VO (Maximum Operating Maneuvering Speed) 6000 lbs 151 KCAS 3750 lbs 119 KCAS VFE (Flaps Extended Speed for T/O Flaps) Flaps Extended Speed for T/O Flaps 145 KCAS Flaps Extended Speed for LND Flaps 108 KCAS VLE (Maximum Landing Gear Extended) 168 KCAS VLO (Maximum Landing Gear Operation) V LOE Extension 168 KCAS V LOR Retraction 128 KCAS C.G. Range For airplanes S/N 46020001 and up: WT. (LB.) FWD LIMIT IN. AFT OF DATUM AFT LIMIT IN. AFT OF DATUM 6050 144.00 in. 146.00 in. 6000 144.00 in. 146.00 in. 5850 141.26 in 146.00 in. 5800 141.15 in. 146.00 in. 5050 139.49 in. 146.00 in. 3925 137.00 in 142.40 in 3500 137.00 in 140.00 in Empty Weight C.G. Range None Maximum Weight RAMP (LB.) TAKEOFF (LB.) LANDING (LB.) MZFW (LB.) For airplanes S/N 46020001 and up: 6050 6000 5800 5050 No. of Seats 6 (1 at +140.6, 1 at 141.8, 2 at 171.9, 2 at 223.8) A25SO Page 10 of 25 Maximum Baggage 100 lbs. at (+248.23) Fuel Capacity 263.2 gallons at (+148.90) (2 wing tanks) 260 gallons (1742 lbs.) useable See Note 1 for data on system fuel. Oil Capacity 12 quarts at (+77.76) See Note 1 for data on system oil. Maximum Operating Altitude 30,000 ft. OAT Operating Limitation +46 C (+115ºF) maximum -54C (-65ºF) minimum Minimum Fuel Temperature -34 C (-30ºF) minimum for starting with Jet-A/A-1 -34C (-30ºF) minimum in-flight with Jet-A -41C (-42ºF) minimum in-flight with Jet A-1 NOTE: When a mixture of Jet A and Jet A-1 is present in the fuel tanks, the Jet A minimum fuel temperature limits must be observed. Maximum Cabin Operating Pressure Differential 5.5 PSID (+0.1, -0.15) Control Surface Movements Aileron (+ 1) Up 24.7 Down 20 Elevator (+.5) Up 13  Down   Elevator Trim Tab (+0,-1) Up 19 Down  (Elevator Neutral) Rudder (+1-0) Left 20 Right 30 Rudder Trim Tab (+1) Left 25 Right 13 (Rudder Neutral) Wing Flaps Up 0 (+1) Down 15 (+1) 35 (+1) Manufacturer’s Serial Numbers 46020001 and up DATA PERTINENT TO ALL MODELS Datum 100 in. forward pressure bulkhead. Leveling Means Top or bottom fuselage at B.L. 0 (constant section). Certification Basis Type Certificate No. A25SO issued September 27, 1983. Date of application for Type Certificate, August 22, 1979. PA-46-310P and PA-46-350P: FAR Part 23, effective February 1, 1965, as amended by Amendment 23-25, effective March 6, 1980; FAR 25.783(e) as amended by Amendment 25-54, effective October 14, 1980; FAR 25.831(c) and (d) as amended by Amendment 25-41, effective September 1, 1977; and FAR 36, Appendix F through Amendment 36-15, effective May 6, 1988 when equipped with 2 blade propeller or FAR 36, Appendix G through Amendment 36-16, effective December 18, 1988 when equipped with optional 3 blade propeller. No equivalent safety findings. Special Conditions No. 23-ACE-53, Docket No. 082CE. For PA-46-350P aircraft equipped with Piper factory installed Avidyne Entegra system (See Piper Report VB-1954), the additional certification basis for installation specific items only is: FAR 23.1529 as amended by Amendment 23-26, effective 14 October 1980; FAR 23.1523 as amended by Amendment 23-34, effective 17 February 1987; FAR 23.1322, 23.1331, 23.1357 (a)(2), (b), (c), (d) as amended by Amendment 23-43, effective 10 May 1993; FAR 23.305, 23.613, 23.773 (a)(2), 23.1525, 23.1549 (a) as amended by Amendment 23-45, effective 7 September 1993; FAR 23.301, 23.337 (a)(1), (b)(1), 23.341 (a), 23.473, A25SO Page 11 of 25 23.561 (b)(3), (e), 23.571 (a), 23.607, 23.611, as amended by Amendment 23-48, effective 11 March 1996; FAR 23.1303 (a), (b), (f), 23.1307, 23.1309 (a), (a)(1), (a)(2), (b),(e), 23.1311 (a)(2), (a)(3), (a)(4), (a)(5), (a)(6), (a)(7), (b), (c), 23.1321 (a), (c), (d), (e), 23.1323 (a), (c), 23.1329, 23.1351 (a)(1), (a)(2)(i), (b)(2), (b)(3), 23.1353 (d), (h), 23.1359 (c), 23.1365 (a), (b), (d), (e), (f), 23.1431 (a), (b) as amended by Amendment 23-49, effective 11 March 1996; FAR 23.1325 (a), (b)(1), (b)(2)(ii), (b)(3), (c), (e), 23.1543 (b), (c), 23.1545 (a), (b)(3), (b)(4), (c), 23.1555 (a), (b), 23.1563, 23.1581 (a), (b)(2), (b)(3), (f), 23.1583 (m), 23.1585 (j) as amended by Amendment 23-50, effective 11 March1996; FAR 23.777 (a), (b), 23.1337 as amended by Amendment 23-51, effective 11 March 1996; FAR 23.1305 (a)(1), (a)(2), (a)(3), (b)(2), (b)(3), (b)(4), (b)(5), (b)(6)(i) as amended by Amendment 23-52, effective 25 July 1996; Special Condition for HIRF (Docket # CE215, Special Condition 23- 154-SC), January 7, 2005. Eligible Serial Numbers: 4636375 and up. For the PA-46-350P Mirage aircraft equipped with Hartzell propeller HC-I3Y1R- 1N/N7605C+2, or N7605CK+2 (See Piper Report VB-2132) the additional certification basis for installation specific items only is: FAR 23.905 (a), (b), (d) as amended by Amendment 23-43, effective 10 May 1993; 23.907 as amended by Amendment 23-59, effective 24 October 2008; and FAR 36, Appendix G through Amendment 36-28, dated 3 February 2006. Eligible Serial Numbers: 4636460, 4636463 & up. For PA-46-350P aircraft equipped with Piper factory installed Garmin G1000 system and GFC 700 AFCS (See Piper Drawing 106800), the additional certification basis for installation specific items only as amended by Amendment 23-59 dated December 23, 2008, is: 14 CFR 23.23 14 CFR 23.25 14 CFR 23.251 14 CFR 23.301 (a), (b), (c) 14 CFR 23.305 14 CFR 23.337 14 CFR 23.341 (a), (c) 14 CFR 23.397 (a) 14 CFR 23.473 14 CFR 23.561 (a), (b)(3), (e) 14 CFR 23.607 14 CFR 23.611 14 CFR 23.613 14 CFR 23.677 (b), (d) 14 CFR 23.773 (a) (1), (a)(2) 14 CFR 23.777 (a), (b), (d) 14 CFR 23.841 (b)(5), (6) 14 CFR 23.867 14 CFR 23.1141 (a), (b), (c), (d) 14 CFR 23.1303 (a), (b), (c), (f) 14 CFR 23.1305 (a) (1), (a)(2), (a)(3), (b)(2), (b)(4)(i), (b)(5), (b)(6)(i) 14 CFR 23.1307 14 CFR 23.1308 (a)(l), (a)(2), (a)(3), (b), (c) 14 CFR 23.1309 (a)(I), (a)(2), (b), (c), (e) 14 CFR 23.1311 (a) (1), (a)(2), (a)(3), (a)(4), (a)(5), (a)(6), (a)(7), (b), (c) 14 CFR 23.1321 (a), (c), (d)(5), (e) 14 CFR 23.1322 (a), (b), (c), (d), (e) 14 CFR 23.1323 (a), (c) 14 CFR 23.1325 (a), (b)(I), (b)(2)(ii) 14 CFR 23.1326