TCDS A8EA

Page No. 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 Rev. No. 25 23 24 23 24 19 24 25 20 24 20 24 20 21 22 20 21 DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION A8EA Revision 25 Piper Aircraft, Inc PA-31P PA-31T PA-31T1 PA-31T2 PA-31T3 PA-31P-350 July 30, 2013 TYPE CERTIFICATE DATA SHEET NO. A8EA This data sheet which is a part of type certificate No. A8EA prescribes conditions and limitations under which the product for which the 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 A8EA to Piper Aircraft, Inc on August 7, 2006. I. - Model PA-31P (Pressurized Navajo), 6 - 8 PCLM (Normal Category). Approved November 26, 1969. Engine Two Lycoming TIGO-541-E series Fuel 100/130 minimum grade aviation gasoline Engine Limits 3200 r.p.m. (2133 propeller r.p.m.) 425 hp, from sea level to 15,000 ft. altitude. Full throttle operations at all altitudes. Maximum 45.5 inches Hg. manifold pressure. Propeller and Propeller Limits Hartzell Hub and Blade Models: HC-C3YN-2LU/JC9684-3R, HC-C3YN-2LUF/FJC9684-3R, or HC-C3YN-2LAUF/FJC9684-3R Pitch: High 85.7 ± 1° (Feathered) Diameter: 93.0” to 93.5” Propeller Governor 2 Woodward 210664 or 2 Woodward 210463 2 Woodward 210464 used when aircraft is equipped with Synchronizer 2 Woodward 210665 used when aircraft is equipped with Synchronizer. 2 Woodward 210772 used when aircraft is equipped with Synchronizer. A8EA Page 2 of 17 Airspeed Limits (CAS) *VNE (Never exceed) 283 mph (246 knots) *VNO (Maximum structural cruise) 230 mph (200 knots) VA (Maneuvering) Minimum weight - 6000 lb. 180 mph (156 knots) Maximum weight - 7800 lb. 198 mph (172 knots) VFE (Flaps extended) 15° Flaps - Takeoff range 200 mph (174 knots) Full flaps 150 mph (130 knots) VLO (Landing gear operating) Extend 180 mph (156 knots) Retract 150 mph (130 knots) VLE (Landing gear extended) 180 mph (156 knots) VMC (Minimum control speed) - 15° Flaps 95 mph (83 knots) *See NOTE 9 for variation of VNE and VNO at altitudes of 13,000 ft. and above. C.G. Range (Gear Extended) (+128.8) to (+137.0) at 7800 lb. (+125.0) to (+137.0) at 7200 lb. (+122.0) to (+137.0) at 6000 lb. or less Straight line variation between points given. 8000 7500 7000 6500 6000 5500 5000 115 120 125 130 135 140 C.G. Location (Inches Aft of Datum) 122 125 128.8 137 Aircraft Weight (lb.) Empty Weight C. G. Range None Maximum Weight 7800 lb. - Takeoff 7800 lb. - Landing No. of Seats 6 - 8 Seats (2 at +119.0, 2 at +166.0, 2 at +198.0) (2 optional: 1 at +229.0, 1 at +242.0) Maximum Baggage 400 lb. (200 lb. at +30, 200 lb. at +225) Fuel Capacity Total - 242 gallons 56 gallons at (+126.8) (Two wing tanks) 40 gallons at (+148.0) (Two wing tanks) 25 gallons at (+140.0) (Two nacelle tanks) See NOTE 1 for unusable fuel data. Oil Capacity 36 quarts at (+83.0) (4.5 gallons each engine - 5 quarts unusable each engine) Page 3 of 17 A8EA Control Surface Movements Aileron 24° Up 14° Down Aileron Tab 1 15° Up 20° Down (All measurements taken (Aileron Neutral) at trailing edge from Elevator 18° Up 20° Down neutral position) Elevator Tab 10° Up 25° Down (Elevator Neutral) Rudder 35° Right 35° Left Rudder Tab 35° Right 18° Left (Rudder Neutral) Flaps 40° Down Maximum Operating Altitude 29,000 feet pressure altitude Serial Numbers Eligible 31P-1 through 31P-80 and 31P-7300110 through 31P-7730012 (See NOTE 7 and 8 for airworthiness certification eligibility in the United States). II. - Model PA-31T (Cheyenne/Cheyenne II), 6 - 9 PCLM (Normal Category), Approved May 3, 1972. Engine Two Pratt Whitney of Canada Ltd. PT6A-28 (TC No. E4EA) or Two Pratt & Whitney PT6A-28 (TC No. E2NE). Fuel If fuel PWA 522 is not available, Aviation Gasoline MIL-G-5572, all grades, may be used for maximum of 150 hours between overhauls. Oil UACL PT6 Service Bulletin No. 1 lists approved brand oils. Engine Limits (2200 r.p.m.) Static Sea Level Ratings PT6A-28 Shaft Horsepower Jet Thrust Equiv. Shaft hp Prop Shaft Speed Maximum Permissible Turbine Interstage Temp. (°C) Takeoff 620** 80 652 2200* 750 Maximum Cont. 620** 80 652 2200* 750 Strtg. Trans. (2 Sec.) 1090 Maximum Reverse 200 2068 Engine Limits (2000 r.p.m.) Static Sea Level Ratings PT6A-28, Special Configuration - Ref. Piper Drawing No. 51670 (See Equipment Items 13 and 17) Shaft Horsepower Jet Thrust Equiv. Shaft hp Prop Shaft Speed Maximum Permissible Turbine Interstage Temp. (°C) Takeoff 620** 80 652 2200* 750 Maximum Cont. 620** 80 652 2200* 750 Strtg. Trans. (2 Sec.) 1090 Maximum Reverse 200 1920 *See NOTE 6 **Available to ISA + 18°C Propeller and Propeller Limits Hartzell Hub and Blade Models: HC-B3TN-3B/T-10173-HB-8 or HC-B3TN-3B/T-10173-B-8 Pitch: High 87° ± 1° (Feathered), Low 20.2° at 30 in. station. Diameter: 93.0” to 93.5” Propeller Governor 2 Woodward 8210-003 Propeller Governors A8EA Page 4 of 17 Airspeed Limits VMO (Maximum operating - up to 12,000 ft.) 283 mph (246 knots) See VMO Chart for speeds above 12,000 ft. in Flight Manual VA (Maneuvering) Minimum weight - 5,195 lb. 168 mph (146 knots) Maximum weight - 9,000 lb. - up to 26,900 ft. 207 mph (180 knots) See VMO Chart for speeds above 26,900 ft. in Flight Manual VFE (Flaps extended) 15° flaps 200 mph (174 knots) Full flaps 165 mph (144 knots) VLO (Landing gear - operating) Extended 180 mph (156 knots) Retracted 150 mph (143 knots) VLE (Landing gear extended) 180 mph (156 knots) VMC (Minimum control speed) 110 mph (96 knots) C.G. Range (Gear Extended) (+131.9) to (+138.0) at 9000 lb. (S/N 31T-7400002 through 31T-7720069) (+129.6) to (+138.0) at 8500 lb. (S/N 31T-7400002 through 31T-8120104) (+126.0) to (+138.0) at 7170 lb. or less (S/N 31T-8020001 through 31T-8120104) (+125.0) to (+138.0) at 6800 lb. or less (S/N 31T-7400002 through 31T-7920094) Straight line variation between points given. 8000 7500 7000 6500 6000 5500 5000 115 120 125 130 135 140 C.G. Location (Inches Aft of Datum) 126.0 129.6 Aircraft Weight (lb.) 8500 9000 131.9 138.0 125.0 Empty Weight C. G. Range None Maximum Weight 9000 lb. - Takeoff 9000 lb. - Landing 9050 lb. - Ramp No. of Seats 6 - 8 (2 at +119.0, 2 at +166.0, 2 at +198.0) (2 Optional: 1 at +229.0, 1 at +242.0) Maximum Baggage 500 lb. (300 lb. at +30, 200 lb. at +255) Piper Kit No. 760 987 required for S/N 31T-7400002 through 31T-7520050 if more than 200 lb. forward baggage capacity is used. Page 5 of 17 A8EA Fuel Capacity 390 gallons maximum at (+138.9) 195 gallons when filled through wing tip filler (two wing tanks) or 346 gallons maximum at (+138.9) 173 gallons when filled through wing tip filler (two wing tanks) See NOTE 1 for unusable fuel data. Oil Capacity 26 quarts at (+91.8) (13 quarts each engine - 3 quarts unusable each engine) Control Surface Movements Aileron 24° Up 14° Down Aileron Tab 1 15° Up 20° Down (All measurements taken at (Aileron Neutral) trailing edge from neutral Elevator 16° Up 20° Down position) Elevator Tab 1 1° Up 36° Down (Elevator Neutral) Rudder 35° Right 35° Left (Rudder Neutral) Flaps 40° Down Maximum Operating Altitude 29,000 ft. pressure altitude 31,000 ft. pressure altitude (S/N 31T-8020001 through 31T-8120104) Serial Numbers Eligible 31T-7400002 through 31T-7400018; and 31T-7520001 through 31T-8120104 Note: For the serial number range specified (31T-7520001 through 31T-8120104, only serial numbers with the following format are eligible; 31T-XX20XXX where X is a number between zero (0) and nine (9) inclusive. The characters “31T” and “20” must appear in the positions shown. For example, 31T-7820055 is a valid serial number for model PA-31T, but serial number 31T-7804010 is not. (See NOTE 7 and 8 for airworthiness certification eligibility in the United States). III. - Model PA-31T1 (Cheyenne I/IA), 6 - 7 PCLM (Normal Category), Approved March 6, 1978. Engine Two UACL PT6A-11 Fuel If fuel PWA 522 is not available, Aviation Gasoline MIL-G-5572, all grades, may be used for maximum of 150 hours between overhauls. Oil UACL PT6 Service Bulletin No. 1 lists approved brand oils. Engine Limits Static Sea Level Ratings PT6A-11 Shaft Horsepower Jet Thrust Equiv. Shaft hp Prop Shaft Speed Maximum Permissible Turbine Interstage Temp. (°C) Takeoff 500** 70 528 2200* 700 Maximum Cont. 455** 65 481 2000* 685 Strtg. Trans. (2 Sec.) 1090 Maximum Reverse 200 2068 *See NOTE 6 **Available to ISA + 18°C Propeller and Propeller Limits Hartzell Hub and Blade Models: HC-B3TN-3B/T10173B-8 HC-B3TN-3B/T-10173K-8 for S/N 31T-8304001 through 31T-8304003, and 31T-1104004 through 31T-1104017 Pitch: High 87° (Feathered), Low 20.2° at 30 in. station. Diameter: 93.0” to 93.5” Propeller Governor 2 Woodward 8210-003 or 8210-035 Propeller Governors A8EA Page 6 of 17 Airspeed Limits (CAS) VMO (Maximum operating -without tip tanks) 265 mph (230 knots) VMO (Maximum operating - with tip tanks - 283 mph (246 knots) up to 9,500 ft.) (For speeds above 9,500 ft., see Flight Manual) VA (Maneuvering - without tip tanks) Minimum weight - 5,195 lb. 168 mph (146 knots) Maximum weight - 8,700 lb. - up to 207 mph (180 knots) 24,600 ft. (For speeds above 24,600 ft., see Flight Manual.) VA (Maneuvering - with tip tanks) Minimum weight - 5,195 lb. 168 mph (146 knots) Maximum weight - 8,700 lb.--up to 207 mph (180 knots) 27,700 ft. (For speeds above 27,700 ft., see Flight Manual.) VFE (Flaps extended) 15° Flaps 200 mph (174 knots) Full Flaps 165 mph (143 knots) VLO (Landing gear - operating) Extend 180 mph (156 knots) Retract 165 mph (143 knots) VLE (Landing gear extended) 180 mph (156 knots) VMC (Minimum control speed) 104 mph (90 knots) C.G. Range (Gear Extended) (+130.5) to (+136.0) at 8700 lb. (+129.6) to (+136.0) at 8500 lb. (+126.5) to (+136.0) at 7200 lb. or less Straight line variation between points given. 8000 7500 7000 6500 6000 5500 5000 115 120 125 130 135 140 C.G. Location (Inches Aft of Datum) 126.5 129.6 Aircraft Weight (lb.) 8500 9000 130.5 136.0 Empty Weight C. G. Range None Maximum Weight 8700 lb. - Takeoff 8700 lb. - Landing 8750 lb. - Ramp No. of Seats 31T-7804001 through 31T-8104073 and 31T-8104101: 6 - 7 Seats (2 at +119.0, 2 at +166.0, 2 at +198.0) (2 optional, 1 at +229.0) 31T-8304001 through 31T-8304003, 31T-1104004 through 31T-1104017: 6 - 7 Seats (2 at +116.96 to +121.09) (2 at +149.85 to +172.85) (2 at +196.50 to +212.35) (1 at +232.60 to +240.50) Page 7 of 17 A8EA Maximum Baggage 31T-7804001 through 31T-8104073 and 31T-8104101: 500 lb. (300 lb. at +30, 200 lb. at +255) 31T-8304001 through 31T-8304003, and 31T-1104004 through 31T-1104017: 500 lb. (300 lb. at +37, 200 lb. at +260.0) Fuel Capacity (Standard) 308 gallons maximum at (+138.9) 154 gallons (two wing tanks) when filled through nacelle filler. Fuel Capacity (including optional tip tanks) 390 gallons maximum at (+138.9) 195 gallons (two wing tanks) when filled through wing tip filler. or 346 gallons maximum at (+138.9) 173 gallons (two wing tanks) when filled through nacelle filler. 31T-8304001 through 31T-8304003, and 31T-1104004 through 31T-1104017: 374 gallons maximum at (+138.3) 187 gallons (two wing tanks) when filled through nacelle filler. or 336 gallons maximum at (+138.3) 168 gallons (two wing tanks) when filled through nacelle filler. See NOTE 1 for unusable fuel data. Oil Capacity 26 quarts at (+91.8) (13 quarts each engine - 3 quarts unusable each engine) Control Surface Movements Aileron 24° Up 14° Down Aileron Tab 1 15° Up 20° Down (All measurements taken at (Aileron Neutral) trailing edge from neutral Elevator 16° Up 20° Down position) Elevator Tab 1° Up 36° Down (Elevator Neutral) Rudder 35° Right 35° Left Rudder Tab 20° Right 45° Left (Rudder Neutral) Flaps 40° Down Maximum Operating Altitude 29,000 ft. pressure altitude Serial Numbers Eligible 31T-7804001 through 31T-8104073; 31T-8104101; 31T-8304001 through 31T-8304003; and 31T-1104004 through 31T-1104017 Note: only serial numbers with the following format are eligible: 31T-XX04XXX where X is a number between zero (0) and nine (9) inclusive. The characters “31T” and “04” must appear in the posit ions shown. For example, 31T-7804010 is a valid serial number for model PA -31T1, but serial number 31T-7820055 is not. (See NOTE 7 and 8 for airworthiness certification eligibility in the United States). IV. - Model PA-31T2 (Cheyenne IIXL), 6 - 10 PCLM (Normal Category), Approved February 12, 1981. Engine 2 UACL PT6A-135 Fuel If fuel PWA 522 is not available, Aviation Gasoline MIL-G-5572, all grades, may be used for maximum of 150 hours between overhauls (See PWA Service Bulletin No. 1244). A8EA Page 8 of 17 Oil CPW 202 or PWA 521 Type II (See PWA PT6 Service Bulletin No. 1001 for approved brands.) Engine Limits Static Sea Level Ratings PT6A-135 Shaft Horsepower Torque ft-lb. Prop Shaft Speed Maximum Permissible Turbine Interstage Temp. (°C) Takeoff 620** 1714 1900* 805 Maximum Cont. 620*** 1714 1900* 805 Strtg. Trans. (2 Sec.) 1090 Maximum Reverse 200 655 1815 805 *See NOTE 11 **Available to ISA +23°C ***Available to ISA +24°C Propeller and Propeller Limits Hartzell Hub and Blade Models: HC-B3TN-3B/T10178B-8R Pitch: High 88.2° ± .5° (Feathered); Low 20.2° ± 1°; Reverse -11° ± 5° at 30 in. station. Diameter: 93.0” to 93.5” Propeller Governor 2 Woodward 8210-003 Propeller Governors Airspeed Limits (CAS) VMO (Maximum operating - up to 12,000 ft.) 283 mph (246 knots) (For speeds above 12,000 ft., see Flight Manual) VA (Maneuvering) Minimum weight - 5,704 lb. 176 mph (153 knots) Maximum weight - 9,474 lb. - up to 25,300 ft. 215 mph (187 knots) (See VMO chart for speeds above 25,300 ft. in Flight Manual) VFE (Flaps extended) 15° Flaps 200 mph (174 knots) Full Flaps 166 mph (144 knots) VLO (Landing gear operating) Extend 180 mph (156 knots) Retract 165 mph (143 knots) VLE (Landing gear extended 200 lb. at (+255)) 180 mph (156 knots) (Nitrogen system) 138 mph (120 knots) VMC (Minimum control speed) 110 mph (96 knots) Page 9 of 17 A8EA C.G. Range (Gear Extended (+124.0) to (+136.0) at 5850 lb. and less (+129.5) to (+136.0) at 9474 lb. Straight line variation between points given. Location of datum is 137.0 inches forward of the main spar centerline. 8000 7500 7000 6500 6000 5500 5000 115 120 125 130 135 140 C.G. Location (Inches Aft of Datum) 124.0 129.5 Aircraft Weight (lb.) 8500 9000 136.09500 Empty Weight C. G. Range None Maximum Weight 9474 lb. - Takeoff 9000 lb. - Landing 9540 lb. - Ramp 7600 lb. - Maximum Zero Fuel Weight No. of Seats 6 - 8 Seats (2 at +95.0, 2 at +142.6 (aft facing)) (2 at +165.9 (fwd facing)) (2 at +196.5, or 1 at +229.0 and 1 at +242.0) 6 - 8 Seats (2 at +95.0) (2 at +130.9) (2 at +165.9) (1 at +229.0) (1 at +242.0) 6 - 10 Seats * (2 at +95.0) (2 at +130.9) (2 at +165.6) (2 at +196.5) (1 at +229.0) (1 at +242.0) *For aircraft modified per Piper Dwg. No. 02252. See Equipment Item No. 23. Maximum Baggage 500 lb. (300 lb. at +3) (200 lb. at +255) A8EA Page 10 of 17 Fuel Capacity 390 gallons maximum at (+138.9) 195 gallons (two wing tanks) when filled through wing tip filler. or 346 gallons maximum at (+138.9) 173 gallons (two wing tanks) when filled through nacelle filler. See NOTE 1 for unusable fuel data. Control Surface Movements Aileron 24° Up 14° Down Aileron Tab 15° Up 20° Down (All measurements taken at (Aileron Neutral) trailing edge from neutral Elevator 16° Up 20° Down position) Elevator Tab 1° Up 36° Down (Elevator Neutral) Rudder 35° Right 35° Left Rudder Tab 20° Right 45° Left (Rudder Neutral) Flaps 40° Down Maximum Operating Altitude 31,000 ft. pressure altitude Serial Numbers Eligible 31T-8166001 through 31T-8166076, and 31T-1166001 through 31T-1166008 (See NOTE 7 and 8 for airworthiness certification eligibility in the United States). V. - Model PA-31T3 (T-1040), 9 - 11 PCLM (Normal Category), Approved February 25, 1982. Engine Two UACL PT6A-11 Fuel If fuel PWA 522 is not available, Aviation Gasoline MIL-G-5572, all grades, may be used for maximum of 150 hours between overhauls. Oil UACL PT6 Service Bulletin 1 lists approved brand oils. Engine Limits Static Sea Level Ratings PT6A-11 Shaft Horsepower Jet Thrust Equiv. Shaft hp Prop Shaft Speed Maximum Permissible Turbine Interstage Temp. (°C) Takeoff 500** 70 528 2200* 700 Maximum Cont. 500** 70 528 2200* 700 Strtg. Trans. (2 Sec.) 1090 Maximum Reverse 200 2112 *See NOTE 6. **Available to ISA + 18°C Propeller and Propeller Limits Hartzell Hub and Blade Models: HC-B3TN-3B/T-10173B-8 Pitch: High 87° ± 1° (Feathered), Low 20.2° at 30 in. station. Diameter: 93.0” to 93.5” Propeller Governor 2 Woodward 8210-003 or 8210-035 Propeller Governors Page 11 of 17 A8EA Airspeed Limits (CAS) VMO (Maximum operating - up to 12,000 ft.) 265 mph (230 knots) (See VMO chart for speeds above 12,000 ft. in Flight Manual) VA (Maneuvering) Minimum weight - 4924 lb. 166 mph (144 knots) Maximum weight - 9000 lb. 210 mph (183 knots) (Up to 23,600 ft., see VMO chart for speeds above 23,600 ft. in Flight Manual) VFE (Flaps extended) 15° flaps 200 mph (174 knots) Full flaps 165 mph (143 knots) VLO (Landing gear operating) Extend 180 mph (156 knots) Retract 165 mph (143 knots) VLE (Landing gear extended) 180 mph (156 knots) VMC (Minimum control speed) 103 mph (90 knots) C.G. Range (Gear Extended) (+128.5) to (+135.0) at 9000 lb. (+120.0) to (+135.0) at 5200 lb. or less Straight line variation between points given. 7500 7000 6500 6000 5500 5000 4500 115 120 125 130 135 140 C.G. Location (Inches Aft of Datum) 120.0 128.5 Aircraft Weight (lb.) 8000 8500 135.09000 Empty Weight C.G. Range None Maximum Weight 9000 lb. - Takeoff 9000 lb. - Landing 9050 lb. - Ramp 7600 lb. - Maximum Zero Fuel Weight No. of Seats 9 - 11 Seats (2 at +95.0, 2 at +130.9, 2 at +164.6, 2 at +193.6, 1 at +222.6, 2 at +253.5) A8EA Page 12 of 17 Maximum Baggage Standard Total 700 lb. With Optional Cargo Pod 1050 lb. Fuselage 300 lb. at (+13) 100 lb. at (+268) Nacelle Lockers 150 lb. each side at (+182) Cargo Pod 350 lb. See Supplement 8 to Airplane Flight Manual - Piper Report 2297 for data concerning C.G. Minimum Zero Fuel Weight for loading Nacelle Lockers - 5066 lb. Fuel Capacity (Standard) 300 gallons maximum at (+135.9) (150 gallons each wing) See NOTE 1 for unusable fuel data. Oil Capacity 26 quarts at (+91.8) (13 quarts each engine - 3 quarts unusable each engine) Control Surface Movements Aileron 24° Up 14° Down Aileron Tab 1 15° Up 20° Down (All measurements taken at (Aileron Neutral) trailing edge from neutral Elevator 16° Up 20° Down position) Elevator Tab 1° Up 36° Down (Elevator Neutral) Rudder 35° Right 35° Left Rudder Tab 20° Right 45° Right (Rudder Neutral) Flaps 40° Down Maximum Operating Altitude 24,000 ft. pressure altitude Serial Numbers Eligible 31T-8275001 through 31T-8475001, and 31T-5575001 VI. - Model PA-31P-350 (Mojave), 6 - 7 PCLM (Normal Category), Approved June 9, 1983. Engine Two Lycoming TIO-LTIO-540V2AD Fuel 100 or 100LL minimum grade aviation gasoline Engine Limits 2600 r.p.m., 42 in. Hg., 350 hp. to 18,000 ft. Above 18,000 ft., 2600 r.p.m., reduce manifold pressure to 33.6 in. Hg. at 25,000 ft. (Straight line variation between 18,000 ft. and 25,000 ft.) Propeller and Propeller Limits Hartzell Hub and Blade Models: HC-I3YR-2UF/FC7854 or HC-I3YR-2UF/FC7854K (Left) HC-I3YR-2LUF/FJC7854 or HC-I3YR-2LUF/FJC7854K (Right) Pitch: High 16.5° to 19.5°; Low 12.5° ± 0.1°; Feather 80° ± 0.5° at 30 in. station. Diameter: 80 in. No reduction permitted. Propeller Governor 1 Hartzell Model V-1 1 Hartzell Model V-1L Page 13 of 17 A8EA Airspeed Limits (CAS) VNE (Never exceed- up to 12,264 ft.) 271 mph (236 knots) For speeds above 12,264 feet, see Flight Manual VNO (Maximum structural cruise speed) 215 mph (187 knots) VA (Maneuvering speed at maximum gross weight) 188 mph (164 knots) VFE (Flaps extended) 15° 184 mph (160 knots) Full flaps 150 mph (130 knots) VLO (Landing gear operating) Extend 180 mph (156 knots) Retract 150 mph (130 knots) VLE (Landing gear extended) 180 mph (156 knots) VMC (Minimum control speed) 85 mph (74 knots) C.G. Range (Gear Extended) (+126.4) to (+134.5) at 7200 lb. (+123.0) to (+134.5) at 5600 lb. or less (+126.5) to (+134.5) at 7245 lb. ramp weight Straight line variation between points given. 7000 6000 5000 120 124 128 132 136 C.G. Location (Inches Aft of Datum) Aircraft Weight (lb.) 123.0 126.4 134.5 Empty Weight C.G. Range None Maximum Weight 7200 lb. - Takeoff 7000 lb. - Landing 7245 lb. - Ramp 6700 lb. - Maximum Zero Fuel Weight No. of Seats 6 - 7 Seats (2 at +116.96 to +121.09) (2 at +149.85 to +162.60) (2 at +196.50 to +212.35) (1 at +232.60 to +240.50) Maximum Baggage Total - 680 lb. Fuselage - 300 lb. at +37.0 200 lb. at +260.40 Nacelle Lockers, 90 lb. each side at +180.00 A8EA Page 14 of 17 Fuel Capacity 242 gallons maximum at (+134.9) (12.5 gallons each wing) See NOTE 1 for unusable fuel data. Oil Capacity 26 quarts at (+77.5) (13 quarts each side) 13 quarts unusable at (+77.5) (6.5 quarts each side) Control Surface Movements Aileron (± 1°) 24° Up 14° Down Aileron Tab (± 1°) 15° Up 20° Down (All measurements taken at (Aileron Neutral) trailing edge from neutral Elevator (± 1°) 16° Up 20° Down position) Elevator Tab (± 1°) 9° Up 36° Down (Elevator Neutral) Rudder (+ 0°, - 1°) 30° Left 30° Right Rudder Tab (± 1°) 40° Left 18° Right (Rudder Neutral) Flaps (± 1°) 40° Down Maximum Operating Altitude 25,000 ft. pressure altitude Serial Numbers Eligible 31P-8414001 through 31P-8414050. DATA PERTINENT TO ALL MODELS Datum 137 inches forward of the main spar centerline. Leveling Means Top of two rivnuts on right side of nose near access door. Certification Basis Type Certificate No. A8EA issued February 24, 1966, reissued June 25, 1966 and October 25, 1972, obtained by the manufacturer under the delegation option authorization. Date of Type Certificate application March 15, 1962. CAR 3 effective May 15, 1956, through Amendment 3-8, effective December 18, 1962; and FAR 23.205, 23.1545, 23.1563 and 23.1585 as amended by Amendment 23-3, effective November 11, 1965; and FAR 23.1557(c) as amended by Amendment 23-7, effective September 14, 1969. Eastern Region Engineering and Manufacturing Branch letter of December 6, 1965, addresses the showing of equivalent safety with regard to CAR 3.682, 3.771 and 3.772. In addition: Model PA-31T: Special Conditions Nos. 23-3-EA-1 Docket No. 9245 including Amendment No. 1 and AEA-210 letter of November 11, 1971, and FAR 23.991 as amended by Amendment 23-7, effective September 14, 1969. Model PA-31T1: Special Conditions No. 23-3-EA-1 Docket No. 9245 including Amendment No. 1 and AEA-210 letter of November 11, 1971, as amended by AEA-210 letter of February 1, 1978, referring to Amendment 23-14 and FAR 23.991 as amended by Amendment 23-7, effective September 14, 1969, and SFAR 27 (Fuel Venting). Model PA-31T2: Special Conditions No. 23-3-EA-1 Docket No. 9245 including