TCDS A20SO

Page No. 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 Rev. No. 12 10 7 9 7 10 7 10 10 5 9 12 13 12 12 DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION A20SO Revision 13 Piper Aircraft, Inc PA-31 PA-31-300 PA-31-325 PA-31-350 (See NOTE 7) January 26, 2022 TYPE CERTIFICATE DATA SHEET NO. A20SO This data sheet, which is a part of Type Certificate A20SO, 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 A20SO to Piper Aircraft, Inc on August 7, 2006. I. - Model PA-31 (Navajo), 6 - 8 PCLM (Normal Category), Approved February 24, 1966 (Reissued July 25, 1966, See NOTE 3). Engine 2 Lycoming TIO-540-A1A, TIO-540-A1B, TIO-540-A2A, or TIO-540-A2B (Applicable to S/N 31-2 through S/N 31-659 and S/N 31-661 through 31-751); or 2 Lycoming TIO-540-A2B (Applicable to S/N 31-660 with nacelle wing lockers only); or 2 Lycoming TIO-540-A2C (Applicable to S/N 31-712 through S/N 31-751 with nacelle wing lockers only and S/N 31-752 through S/N 31-8312019) See NOTE 4. Fuel 100/130 minimum grade aviation gasoline Engine Limits Applicable to S/N 31-2 through 31-751 (TIO-540-AIA, TIO-540-AIB, TIO-540-A2A, or TIO-540-A2B): 2,575 r.p.m., 310 hp. from sea level to 15,000 ft. altitude. Full throttle operations at all altitudes. Maximum 43 in. hg. manifold pressure cumulative total with automatic density control and altitude adjustment. Applicable to S/N 31-712 through 31-900, and 31-7300901 through 31-7912124 (TIO-540-A2C): 2,575 r.p.m., 310 hp. from sea level to 15,800 ft. altitude. Maximum 46.0 in. hg. manifold pressure cumulative total with automatic density control and altitude adjustment. Do not exceed the following manifold pressure limitations: 46.0 in. hg. manifold pressure at and below 15,800 ft. altitude, 31.0 in. hg. manifold pressure at 24,000 ft. altitude. Straight line variation between points given. Applicable to S/N 31-8012001 through 31-8312019 (TIO-540-A2C): Maximum continuous power 2,575 r.p.m. at 310 hp. from sea level to 15,800 ft. altitude. Maximum 46.0 in. hg. manifold pressure cumulative total with automatic density control and altitude adjustment. Do not exceed the following manifold pressure limitations: 46.0 in. hg. manifold pressure at and below 15,800 ft. altitude, 31.0 in. hg. manifold pressure at 24,000 ft. altitude. Straight line variation between points given. A20SO Page 2 of 15 Engine Limits Maximum normal operating power (continued) Do not exceed the following r.p.m. and manifold pressures: 2,400 r.p.m., 39.5 in. hg. manifold pressure at and below 19,700 ft. altitude, 2,400 r.p.m., 31.0 in. hg. manifold pressure at 24,000 ft. altitude. Straight line variation between points given. Propeller and Propeller Limits Hartzell Hub and Blade Models: Eligible on TI0-540-A1A, TI0-540-A1B engines only: HC-E2YK-2B/C8475-4 (2 Bld) HC-E2YK-2BT/C8475-4 (2 Bld) Eligible on TIO-540-AIA, TIO-540-AIB, TIO-540-A2A, TI0-540-A2B engines only: HC-E2YR-2B/C8475-4 (2 Bld) HC-E2YR-2BT/C8475-4 (2 Bld) HC-E2YR-2BTF/FC8475-4 (2Bld) Eligible on TIO-540-A2A, TI0-540-A2B, TI0-540-A2C egines only: HC-E3YR-2/C8468-6R (3 Bld) HC-E3YR-2T/C8468-6R (3 Bld) HC-E3YR-2A/C8468-6R (3 Bld) HC-E3YR-2AT/C8468-6R (3 Bld) Eligible on TI0-540-A2A, TI0-540-A2B, TI0-540-A2C engines only: HC-E3YR/2AF/FC8468-6R (3 Bld) HC-E3YR-2ATF/FC8468-6R (3 Bld) Pitch (2 Bld): High 81° ± 1.0° (feathered), Low 14.5° ± 0.1° at 30 in. station. Pitch (3 Bld): High 82° ± 1.0° (feathered), Low 13° ± 0.1° (TIO-540-A2A and TIO-540-A2B engines) or Low 13.2° ± 0.1° (TIO-540-A2C engines) at 30 in. station. Diameter: Not over 80 in., not under 78 in. No further reduction permitted. Propeller Governor 2 Hartzell F-6-24Z Propeller Governors or 2 Hartzell F-6-11S or F-6-11A Propeller Governors per Piper Drawing 24622-7 See Notes 13 & 14 Airspeed Limits (CAS) Applicable to all S/N: V NE (Never Exceed) 272 mph (236 knots) VNO (Max. Structural Cruise) 216 mph (188 knots) VFE (Flaps Extended) 40° 150 mph (130 knots) VMC (Minimum Control) 85 mph ( 74 knots) Applicable to S/N 31-2 through 31-711: VA (Maneuvering) 188 mph (163 knots) Applicable to S/N 31-712 through 31-900 and 31-7300901 through 31-8312019: VA (Maneuvering) 183 mph (159 knots) Applicable to S/N 31-2 through 31-900 and 31-7300901 through 31-7712106: VFE (Flaps Extended) 15° 175 mph (152 knots) VLO (Landing Gear Operating) Extension and Retraction 150 mph (130 knots) VLE (Landing Gear Extended) 150 mph (130 knots) Page 3 of 15 A20SO Airspeed Limits (CAS) Applicable to S/N 31-7812001 through 31-8312019: VFE (Flaps Extended) 25° 184 mph (160 knots) VLO (Landing Gear Operating) Extension 180 mph (156 knots) Retraction 150 mph (130 knots) VLE (Landing Gear Extended) 180 mph (156 knots) C.G. Range (Gear Extended) (+134.0) to (+138.0) at 6,500 lb. (+128.5) to (+138.0) at 6,000 lb. (+120.0) to (+138.0) at 4,800 lb. or less. Straight line variation between points given. Moment due to retracting landing gear: + 860 in.-lb. 7000 6500 6000 5500 5000 4500 115 125 130 135 140120 120 128.5 134 138 Aircraft Weight (lb.) C. G. Location (Inches aft of datum) Empty Weight C.G. Range None Maximum Weight 6,500 lb. - Takeoff; 6,200 lb. - Landing (S/N 31-2 through 31-711) 6,500 lb. - Takeoff or Landing (S/N 31-712 through 31-900 and 31-7300901 through 31-8312019) 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 +234.0) Maximum Baggage Without Nacelle Lockers: Total: 350 lb. Fuselage: 150 lb. at +43; 200 lb. at +255 With Nacelle Lockers: Total: 650 lb. Fuselage: 150 lb. at +43; 200 lb. at +255 Nacelle Lockers: 150 lb. each side at +168 Fuel Capacity Total - 192 gallons 56 gallons in each of 2 wing tanks at +126.8 40 gallons in each of 2 wing tanks at +148.0 See NOTE 1 for unusable fuel data. Oil Capacity Total - 6 gallons at (+77) (3 gallons each engine - 2 ¾ qt. unusable each engine) A20SO Page 4 of 15 Control Surface Movements Aileron (±1.0°) Up 24° Down 14° Aileron Tab (±1.0°) Up 15° Down 20° (All measurements taken at (Aileron neutral) trailing edge from neutral position) Elevator (±1.0°) Up 25° Down 20° Elevator Tab (±1.0°) Up 16° Down 29° (Elevator neutral) Rudder (±1.0°) Right 30° Left 30° Rudder Tab (±1.0°) Right 18° Left 40° (Rudder neutral) Flaps (±1.0°) Down 40° Maximum Operating Altitude 24,000 ft. pressure altitude Serial Numbers Eligible 31-2 through 31-900 and 31-7300901 through 31-8312019 (See NOTES 5 and 6 for airworthiness certification eligibility in the United States). II. - Model PA-31-300 (Navajo), 6 - 8 PCLM (Normal Category), Approved June 12, 1967. Engine 2 Lycoming IO-540-M1A5 Fuel 100/130 minimum grade aviation gasoline Engine Limits For all operations, 2700 r.p.m. (300 hp) "Do not exceed 23 in. manifold pressure below 2,250 r.p.m." Propeller and Propeller Limits Hartzell Hub and Blade Models: HC-E2YR-2B/C8475A-4 HC-E2YR-2BT/C8475A-4 HC-E2YR-2BTF/FC8475A-4 Pitch: High 81° ± 1.0° (feathered), Low 12.5° ± 0.1° at 30 in. station. Diameter: Not over 80 in., not under 78 in. No further reduction permitted. Propeller Governor 2 Hartzell F-6-15A Propeller Governors Airspeed Limits (CAS) V NE (Never Exceed) 272 mph (236 knots) VNO (Max. Structural Cruise) 216 mph (188 knots) VA (Maneuvering) 188 mph (163 knots) VFE (Flaps Extended) 40° 150 mph (130 knots) VLO (Landing Gear Operating) 150 mph (130 knots) VLE (Landing Gear Extended) 150 mph (130 knots) VMC (Minimum Control) 85 mph ( 74 knots) Page 5 of 15 A20SO C.G. Range (Gear Extended) (+132.0) to (+138.0) at 6,000 lb. (+120.0) to (+138.0) at 4,800 lb. or less. Straight line variation between points given. Moment due to retracting landing gear: + 860 in.-lb. 6500 6000 5500 5000 4500 115 125 130 135 140120 132 138 Aircraft Weight (lb.) C. G. Location (Inches aft of datum) Empty Weight C.G. Range None Maximum Weight 6,000 lb. 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 +234.0) Maximum Baggage Total: 400 lb. (200 lb. at +43, 200 lb. at +255) Fuel Capacity Total: 192 gallons 56 gallons in each of 2 wing tanks at +126.8 40 gallons in each of 2 wing tanks at +148.0 See NOTE 1 for unusable fuel data. Oil Capacity Total - 6 gallons at (+77) (3 gallons each engine - 2 ¾ qt. unusable each engine) Control Surface Movements Aileron (±1.0°) Up 24° Down 14° Aileron Tab (±1.0°) Up 15° Down 20° (All measurements taken at (Aileron neutral) trailing edge from neutral position) Elevator (±1.0°) Up 25° Down 20° Elevator Tab (±1.0°) Up 16° Down 29° (Elevator neutral) Rudder (±1.0°) Right 30° Left 30° Rudder Tab (±1.0°) Right 18° Left 40° (Rudder neutral) Flaps (±1.0°) Down 40° Maximum Operating Altitude 24,000 ft. pressure altitude Serial Numbers Eligible 31-2 through 31-900 and 31-7300901 through 31-8312019 (See NOTES 5 and 6 for airworthiness certification eligibility in the United States). A20SO Page 6 of 15 III. - Model PA-31-350 (Chieftain), and (T-1020), 6 - 11 PCLM (Normal Category), Approved May 3, 1972. Engine 1 Lycoming TIO-540-J2BD (Chieftain, S/N 31-5001 through 31-5004 and 31-7305005 through 31-8452024) 1 Lycoming LTIO-540-J2BD (Chieftain, S/N 31-5001 through 31-5004 and 31-7305005 through 31-8452024) 1 Lycoming TIO 540-J2B (T1020, S/N 31-8253001 through 31-8553002) 1 Lycoming LTIO-540-J2B (T1020, S/N 31-8253001 through 31-8553002) Fuel 100/130 minimum grade aviation gasoline Engine Limits Applicable to S/N 31-5001 through 31-5004 and 31-7305005 through 31-7952250: 2,575 r.p.m., 350 hp. from sea level to 15,000 ft. altitude. Full throttle operations at all altitudes. Maximum 49 inches hg. manifold pressure cumulative total with automatic density control and altitude adjustment. Do not exceed the following manifold pressure limitations: 49.0 inches hg. manifold pressure at and below 15,000 ft. altitude, 44.3 inches hg. manifold pressure at 22,300 ft., 40.5 inches hg. manifold pressure at 24,000 ft. altitude. Straight line variation between points given. Applicable to S/N 31-8052001 through 31-8553002: Maximum continuous power 2,575 r.p.m., 350 hp. from sea level to 15,000 ft. altitude. Full throttle operations at all altitudes. Maximum 49 inches hg. manifold pressure cumulative total with automatic density control and altitude adjustment. Do not exceed the following manifold pressure limitations: 49.0 inches hg. manifold pressure at and below 15,000 ft. altitude, 44.3 inches hg. manifold pressure at 22,300 ft., 40.5 inches hg. manifold pressure at 24,000 ft. altitude. Straight line variation between points given. Maximum normal operating power Do not exceed the following r.p.m. and manifold pressures: 2,400 r.p.m., 40.0 inches hg. manifold pressure at and below 18,700 ft. altitude, 2,400 r.p.m., 31.0 inches hg. manifold pressure at 24,000 ft. altitude. Straight line variation between points given. Propeller and Propeller Limits Hartzell Hub and Blade Models: Eligible on TIO-540-J2BD engine: HC-E3YR-2A/C8468-6R HC-E3YR-2AT/C8468-6R HC-E3YR-2AF/FC8468-6R HC-E3YR-2ATF/FC8468-6R Eligible on LTIO-540-J2BD engine: HC-E3YR-2ALT/JC8468-6R HC-E3YR-2AL/JC8468-6R HC-E3YR-2ALF/FJC8468-6R HC-E3YR-2ALTF/FJC8468-6R Eligible on TIO-540-J2B engine: HC-E3YR-2ATF/FC8468-6R Eligible on LTIO-540-J2B engine: HC-E3YR-2ALTF/FJC8468-6R Pitch: High 82° ± 1.0° (feathered), Low 13.4° ± 0.1° at 30 in station. Diameter: Not over 80 in., not under 78 in. No further reduction permitted. Propeller Governor 1 Hartzell F-6-24LZ and 1 Hartzell F-6-24Z Propeller Governors See Notes 8, 9 & 10 Page 7 of 15 A20SO Airspeed Limits (CAS) Applicable to all S/N: V NE (Never Exceed) 272 mph (236 knots) VNO (Max. Structural Cruise) 216 mph (187 knots) VA (Maneuvering) 186 mph (162 knots) VFE (Flaps Extended) 40° 150 mph (130 knots) VMC (Minimum Control) 90 mph ( 78 knots) Applicable to S/N 31-5001 through 31-5004 and 31-7305005 through 31-7752201: VFE (Flaps Extended) 15° 175 mph (152 knots) VLO (Landing Gear Operating) Extension and Retraction 150 mph (130 knots) VLE (Landing Gear Extended) 150 mph (130 knots) Applicable to S/N 31-7852001 through 31-8553002: VFE (Flaps Extended) 25° 184 mph (160 knots) VLO (Landing Gear Operating) Extension 180 mph (156 knots) Retraction 150 mph (130 knots) VLE (Landing Gear Extended) 180 mph (156 knots) C.G. Range (Gear Extended) (+126.0) to (+135.0) at 7,000 lb. (+122.0) to (+135.0) at 6,200 lb. (+120.0) to (+135.0) at 5,200 lb. or less Straight line variation between points given. Moment due to retracting landing gear: + 860 in.-lb. 115 125 130 135 140120 6500 6000 5500 5000 4500 7000 120 122 126 135 Aircraft Weight (lb.) C. G. Location (Inches aft of datum) Empty Weight C.G. Range None Maximum Weight 7,000 lb. - Takeoff; 7,000 lb. - Landing No. of Seats 2 seats at +95.0 6 optional (2 at +132/137 (reversed), 2 at +195.0, 1 at +229.0, 1 at +242.0) 8 optional (2 at +132.0, 2 at +163.5, 2 at +195.0, 1 at +229.0, 1 at +242.0) 9 optional (T1020, S/N 31-8253001 through 31-8553002: 2 at +130.9, 2 at +164.6, 2 at +193.6, 1 at +222.6, 2 at +253.5) A20SO Page 8 of 15 Maximum Baggage Total: 700 lb. Fuselage: 200 lb. at +19.0 200 lb. at +255 Nacelle Lockers: 150 lb. each side at +168.0 Chieftain, S/N 31-5001 through 31-5004 and 31-7305005 through 31-8452024: With optional nacelle fuel tanks Total: 500 lb. Fuselage: 200 lb. at +19.0 200 lb. at +255 Nacelle Lockers: 50 lb. each side at +192.0 T1020, S/N 31-8253001 through 31-8553002: Total: 600 lb. Fuselage: 200 lb. at +23.0 100 lb. at +268 Nacelle Lockers: 150 lb. each side at +168.0 Fuel Capacity T1020, S/N 31-8253001 through 31-8553002: Total - 112 gallons 56 gallons in each of 2 wing tanks at +126.8 Chieftain, S/N 31-5001 through 31-5004 and 31-7305005 through 31-8452024: Total - 192 gallons 56 gallons in each of 2 wing tanks at +126.8 40 gallons in each of 2 wing tanks at +148.0 Chieftain, S/N 31-5001 through 31-5004 and 31-7305005 through 31-8452024: With optional nacelle fuel tanks Total - 246 gallons 56 gallons in each of 2 wing tanks at +126.8 27 gallons in each of 2 nacelle tanks at +142.8 40 gallons in each of 2 wing tanks at +148.0 See NOTE 1 for unusable fuel data. Oil Capacity Total - 6 gallons at (+77) (3 gallons each engine - 2 ¾ qt. unusable each engine) Control Surface Movements Aileron (±1.0°) Up 24° Down 14° Aileron Tab (±1.0°) Up 15° Down 20° (All measurements taken at (Aileron neutral) trailing edge from neutral position) Elevator (±1.0°) Up 16° Down 20° Elevator Tab (±1.0°) Up 9° Down 36° (Elevator neutral) Rudder (±1.0°) Right 30° Left 30° Rudder Tab (±1.0°) Right 18° Left 40° (Rudder neutral) Flaps (±1.0°) Down 40° Maximum Operating Altitude 24,000 ft. pressure altitude Serial Numbers Eligible 31-5001 through 31-5004 and 31-7305005 through 31-8553002 (See NOTES 5 and 6 for airworthiness certification eligibility in the United States). Page 9 of 15 A20SO IV. - Model PA-31-325 (Navajo C/R), 6 - 8 PCLM (Normal Category), Approved May 31, 1974. Engine 1 Lycoming TIO-540-F2BD 1 Lycoming LTIO-540 F2BD Fuel 100/130 minimum grade aviation gasoline Engine Limits Applicable to S/N 31-7400990, 31-7512001 through 31-7912124: Maximum continuous power 2,575 r.p.m., 325 hp. from sea level to 14,000 ft. altitude, maximum 49.0 in. hg. manifold pressure cumulative total with automatic density control and altitude adjustment. Do not exceed the following manifold pressure limitations: 49.0 in. hg manifold pressure at and below 14,000 ft. altitude, 31.0 in. hg manifold pressure at 25,000 ft altitude. Straight line variation between points given. Applicable to S/N 31-8012001 through 31-8312019: Maximum continuous power 2,575 r.p.m., 325 hp. from sea level to 14,000 ft. altitude, maximum 49.0 in. hg. manifold pressure cumulative total with automatic density control and altitude adjustment. Do not exceed the following manifold pressure limitations: 49.0 in. hg manifold pressure at and below 14,000 ft. altitude, 31.0 in. hg manifold pressure at 24,000 ft. altitude. Straight line variation between points given. Maximum normal operating power Do not exceed the following r.p.m. and manifold pressures: 2,400 r.p.m., 39.5 in. hg manifold pressure at and below 19,700 ft.. altitude, 2,400 r.p.m., 31.0 in. hg manifold pressure at 24,000 ft. altitude. Straight line variation between points given. Propeller and Propeller Limits Hartzell Hub and Blade Models: HC-E3YR-2AF/FC8468-6R (Eligible on TIO-540-F2BD engines) HC-E3YR-2ATF/FC8468-6R HC-E3YR-2ATF/FC8468-7R HC-E3YR-2ALTF/FJC8468-6R (Eligible on LTIO-540-F2BD engines) HC-E3YR-2ALF/FJC8468-6R HC-E3YR-2ALTF/FJC8468-7R Pitch: High 82° ± 1.0° (feathered), Low 13.2° ± 0.1° at 30 in station. Diameter: Not over 80 in., not under 78 in. No further reduction permitted. Propeller Governor 2 Hartzell F-6-24Z Propeller Governors See Notes 11 & 12 Airspeed Limits (CAS) Applicable to all S/N: V NE (Never Exceed) 272 mph (236 knots) VNO (Max. Structural Cruise) 216 mph (188 knots) Above 21,000 ft. reduce VNO speed 3 mph per 1,000 ft. VA (Maneuvering) 183 mph (159 knots) VFE (Flaps Extended) 40° 150 mph (130 knots) VMC (Minimum Control) 85 mph ( 74 knots) Applicable to S/N 31-7400990, 31-7512001 through 31-7712106: VFE (Flaps Extended) 15° 175 mph (152 knots) VLO (Landing Gear Operating) Extension and Retraction 150 mph (130 knots) VLE (Landing Gear Extended) 150 mph (130 knots) A20SO Page 10 of 15 Airspeed Limits (CAS) Applicable to S/N 31-7812001 through 31-8312019: VFE (Flaps Extended) 25° 184 mph (160 knots) VLO (Landing Gear Operating) Extension 180 mph (156 knots) Retraction 150 mph (130 knots) VLE (Landing Gear Extended) 180 mph (156 knots) C.G. Range (Gear Extended) (+134.0) to (+138.0) at 6,500 lb. (+128.5) to (+138.0) at 6,000 lb. (+121.4) to (+138.0) at 5,000 lb. or less Straight line variation between points given. Moment due to retracting landing gear: + 860 in.-lb. 115 125 130 135 140120 6500 6000 5500 5000 4500 Aircraft Weight (lb.) 121.4 128.5 134 138 C. G. Location (Inches aft of datum) Empty Weight C.G. Range None Maximum Weight 6,500 lb. - Takeoff or 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 +234.0) Maximum Baggage Total: 650 lb. Fuselage: 150 lb. at +43.0 200 lb. at +255 Nacelle Lockers: 150 lb. each side at +168.0 With optional nacelle fuel tanks. Total: 450 lb. Fuselage: 150 lb. at +43.0 200 lb. at +255.0 Nacelle Lockers: 50 lb. each side at +192.0 Fuel Capacity Total - 192 gallons 56 gallons in each of 2 wing tanks at +126.8 40 gallons in each of 2 wing tanks at +148.0 With optional nacelle fuel tanks. Total - 246 gallons 56 gallons in each of 2 wing tanks at +126.8 27 gallons in each of 2 nacelle tanks at +142.8 40 gallons in each of 2 wing tanks at +148.0 See NOTE 1 for unusable fuel data. Oil Capacity Total - 6 gallons at (+77) (3 gallons each engine - 2 3/4 qt. unusable each engine) Page 11 of 15 A20SO Control Surface Movements Aileron (±1.0°) Up 24° Down 14° Aileron Tab (±1.0°) Up 15° Down 20° (All measurements taken at (Aileron neutral) trailing edge from neutral position) Applicable to S/N 31-7400990, 31-7512001 through 31-7912124: Elevator (±1.0°) Up 20° Down 20° Elevator Tab (±1.0°) Up 1° Down 40° (Elevator neutral) Applicable to S/N 31-8012001 through 31-8312019: Elevator (±1.0°) Up 20° Down 20° Elevator Tab (±1.0°) Up 5° Down 40° (Elevator neutral) Rudder (±1.0°) Right 30° Left 30° Rudder Tab (±1.0°) Right 18° Left 40° (Rudder neutral) Flaps (±1.0°) Down 40° Maximum Operating Altitude 24,000 ft. pressure altitude. Serial Numbers Eligible 31-7400990, and 31-7512001 through 31-8312019 (See NOTES 5 and 6 for airworthiness certification eligibility in the United States). 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. A20SO issued March 6, 1978, (originally issued February 24, 1966, under Type Certificate A8EA) 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-31-350: FAR 23.75(a), 23.77, 23.145, 23.161, 23.175(d), and 23.1527 as amended by Amendment 23-7, effective September 14, 1969. Model PA-31-325: FAR 23.75(a), 23.77(a), 23.145, 23.161, 23.175(a), 23.175(b), 23.175(c), 23.175(d), and 23.1527 as amended by Amendment 23 -7, effective September 14, 1969. Model PA-31 and PA-31-325 (S/N 31-8012001 through 31-8312019), and Model PA-31-350 (S/N 31-8052001 through 31-8553002): FAR 36 as amended by Amendments 1 through 6, effective January 24, 1977. Compliance with ice protection requirements have been demonstrated in accordance with FAR 23.1419 as amended by Amendment 23-14, effective December 20, 1973, when ice protection equipment is installed in accordance with the airplane equipment list. A20SO Page 12 of 15 Certification Basis Model PA-31-350 (S/N 31-7652124 through 31-7952250): (continued) Compliance with ice protection requirements have been demonstrated in accordance with FAR 23.1419 as amended by Amendment 23-14, effective December 20, 1973, when ice protection equipment is installed in accordance with Piper Drawing 71983. Production Basis Approved for manufacture of spare parts only under Production Certificate Number 206. Equipment The basic required equipment as prescribed in the applicable airworthiness regulations (see Certification Basis) must be installed in the aircraft for certification. In addition, the following items of equipment are required: 1. D.O.A. No. EA-1 Approved Airplane Flight Manual per PAC Report No. 1362 for Model PA-31, S/N 31-2 through 31-659, 31-661 through 31-711. 2. D.O.A. No. EA-1 Approved Airplane Flight Manual per PAC Report No. 1470 for Model PA-31-300, S/N 31-2 through 31-511. 3. D.O.A. No. EA-1 Approved Airplane Flight Manual per PAC Report No. 1655 for Model PA-31, S/N 31-712 through 31-751. 4. D.O.A. No. EA-1 Approved Airplane Flight Manual per PAC Report No. 1653 for Model PA-31 with nacelle wing lockers and TIO-540-A2B engines, Serial Number 31-660. 5. D.O.A. No. EA-1 Approved Airplane Flight Manual per PAC Report No. 1686 for Model PA-31 with nacelle wing lockers and TIO-540-A2C engines, Serial Number 31-712 through 31-751. 6. D.O.A. No. EA-1 Approved Airplane Flight Manual per PAC Report No. 1702 for Model PA-31, S/N 31-752 through 31-900 and 31-7300901 through 31-7612110. 7. D.O.A. No. EA-1 Approved Airplane Flight Manual per PAC Report No. 1750 for Model PA-31-350, S/N 31-5001 through 31-5004 and 31-7305005 through 31-7652176. 8. D.O.A. No. EA-1 Approved Airplane Flight Manual per PAC Report No. 1860 for Model PA-31-325, S/N 31-7300932 through 31-7612110. 9. D.O.A. No. EA-1 Approved Pilot's Operating Handbook per PAC Report