# TCDS A17WE: Aerostar Aircraft Corporation - Type: Type certificate data sheet - Status: Current - Holder: Aerostar Aircraft Corporation - Revision: 23 - Revised: September 24, 2012 - Product: Aircraft, Small Airplane - Certification basis: Part 23, Part 36 - Registered aircraft: 58, by the registry models matched to it (OpenAirDocs) - Data sheet PDF: https://openairdocs.org/files/sha256/d4/67/d4673d93aa328a8410baaedc4cd2e9ae51e5b19cc45c19d6356e6abc893a5bbc - FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/ABBBB99FF89DC2ED86257A8B006EE54B.0001 - Page: https://openairdocs.org/tcds/A17WE ## Models (5) As the data sheet lists them. - PA-60-601P (Aerostar 601P) - PA-60-601 (Aerostar 601) - PA-60-602P (Aerostar 602P) - PA-60-600 (Aerostar 600) - PA-60-700P (Aerostar 700P) ## What the data sheet says From the PDF's text layer, line by line; tables lose their columns. The PDF is the record. ```text Page No. 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 Rev. No. 23 21 21 21 21 22 21 21 22 21 22 21 22 22 22 22 Page No. 17 Rev. No. 21 DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINSTRATION A17WE Revision 23 Aerostar PA-60-600 (Aerostar 600) PA-60-601 (Aerostar 601) PA-60-601P (Aerostar 601P) PA-60-602P (Aerostar 602P) PA-60-700P (Aerostar 700P) September 24, 2012 TYPE CERTIFICATE DATA SHEET NO. A17WE This data sheet, which is a part of Type Certificate A17WE, prescribes conditions and limitations under which the product for which the Type Certificate was issued meets the Airworthiness Requirements of the Federal Aviation Regulations. Holder of Type Certificate: Aerostar Aircraft Corporation 10555 Airport Drive Coeur d'Alene Airport Hayden Lake, ID 83835 I. Aerostar Model PA-60-600 (Aerostar 600) (Normal Category) Approved March 28, 1968 (See Note 2 & 4) Engines: Two Lycoming IO-540-G1B5, IO-540-K1F5, IO-540- K1J5 (with Bendix fuel injector servos 2524491- ); IO-540-S1A5 or IO-540-P1A5 (wit h Bendix fuel injector servos 2524491- ). NOTE: IO-540-S1A5 or IO-540-P1A5 engines are optional and installed per AAC Option 35. Fuel: 100/130 and 100LL minimum grade aviation gasoline Engine Limits: *2575 RPM. 29.5 in. Hg. MAP (290 HP) for all operations **2575 RPM, 29.5 in. Hg. MAP (290 HP) Maxi mum Continuous Power for takeoff, obstacle clearance, and emergency operations only. (No time limit.) 2520 RPM, 29.5 in. Hg. MAP (284 HP) Maximum Normal Operating Power for noise certification and fo r all other operations. (See "Noise Characteristics" paragraph) *For S/N 60-0001 thru 60-0714-7961221 **For S/N 60-0715-8061222 and subsequent Propeller Two Hartzell full-feathering propellers - HC-C3YR-2/C8468-8R or HC-C3YR-2UF/FC8468-8R. Propeller Limits (a) Pitch setting at 30 in. sta. Low 14° + 0.1°, High 18° -21° Feather 82.5° + 1.0° Diameter: 78 inches No cutoff for repairs permitted. (b) Spinners - Hartzell C-3258P (c) Propeller Governor - Hartzell F-6-5A , F-6-35, F-6-35Z, F-6-36, F-6-36Z, F-8-35, F-8-35Z, F-8-45, or F-8-45Z. A17WE 2 NOTE: If modified in accordance with AAC Option 64, Synchrophaser, Governor for right engine is F-8-35 or F- 8-35Z. If modified in accordance with AAC Op tion 150, Synchrophaser, Governor for right engine is F-8-45 or F-8-45Z. Airspeed Limits: (See Note 2) V ne- Never exceed 243 KCAS (280 MPH) V no- Max. structural cruising 217 KCAS (250 MPH) V a- Max. design maneuvering 163 KCAS (188 MPH) V fe- *Flaps extended 20° 156 KCAS (180 MPH) 45° 130 KCAS (150 MPH) - **Flaps extended 20° 174 KCAS (200 MPH) 45° 149 KCAS (172 MPH) V le-Max. gear extended 156 KCAS (180 MPH) V lo-Max gear retraction 130 KCAS (150 MPH) -Max gear extension 156 KCAS (180 MPH) *For S/N 60-0001 thru 60- 0014, 60-0015-26 thru 60-0056-128, 60-0130-057 thru 60-0355-127. The flap speeds for these S/N aircraft may be increased from 130 KCAS and 156 KCAS to 149 KCAS and 174 KCAS respectively when modified in accordance with AAC Option No. 131. **For S/N 60-0359-128 and subsequent. C.G. Range LANDING GEAR EXTENDED OR RETRACTED WEIGHT FWD (1) AFT (1) AIRFRAME S/N 4600 lbs. 157.66 (12.2% MAC) 166. 00 (25.5% MAC) (3) 60-0001 thru 4600 157.66 (12.2% MAC) 167. 88 (28.5% MAC) (3) 60-0824-8061236 5500 159.58 (15% MAC) 167.88 (28.5% MAC) 5500 159.58 (15% MAC) 166.00 (25.5% MAC) (2) (3) LANDING GEAR EXTENDED OR RETRACTED WEIGHT FWD (1) AFT (1) AIRFRAME S/N 4600 157.66 (12.2% MAC) 166. 00 (25.5% MAC) (3) 60-0833-8161237 4600 157.66 (12.2% MAC) 167. 88 (28.5% MAC) and subsequent 5500 159.58 (15% MAC) 167.88 (28.5% MAC) 5525 159.63 (15.1% MAC) 167.88 (28.5% MAC) 5500 159.58 (15% MAC) 166.00 (25.5% MAC) (2) (3) 5525 159.63 (15.1% MAC) 166. 00 (25.5% MAC) (2) (3) (1) Straight line variat ion between weight points. (2) For aircraft equipped for Flight into Known Icing AAC Option No. 196. (3) For aircraft with Aerostar Ki t 764 969V (ventral rudder) installed. Empty Weight NONE C.G. Range Maximum Weight 5525 lbs. MA X RAMP (60-0833-8161237 and subsequent). 5500 lbs. MAX. TAKEOFF 3 A17WE No. of Seats Crew or Fuselage Passenger Station 2 96 (CREW) 2 132 2 165* *When bench seat is fitted, three occupants may be accommodated provided that the maximum weight of 380 lbs. is not exceeded. See Flight Manual for loading instructions. Maximum Baggage (See Note 2) Rear compartment 240lbs. at (+245) Fuel Capacity Wing Total Capac ity (65 gals. each)........ 130 gals. Wing Total Usable ( 62 gals each)........... 124 gals. Fuselage Total C apacity............................ 43.5 gals. Fuselage Total Usable............................ 41.5 gals. Aircraft Total C apacity................................. 173.5 gals. Aircraft Total Usable................................. 165. 5 gals. (See Note 1 for unusable fuel) Oil Capacity Total Capacity tw o engines @ sta. +145.... 24 qts. Capacity each engine @ sta. +145.............. 12 qts. Usable each engi ne....................................... 9 1/4 qts. (See Note 1 for undrainable oil) Control Surface Movement Wing Flaps* Down 45 °+ 3° Main Surfaces Aileron** Up 25° + 1° Down 15° + 1° Elevator Up 30° + 1° Down 10° + 1° Rudder Right 30° + 1° Left 30° + 1° ***Right 35° + 1° - 0 ° Tabs (Main surface in neutral) Elevator Up 7°+ 1° Down 37° +9° - 1 ° Rudder Right 9° + 4° Left 37° + 4° - 1 ° - 1 ° *Flaps must be rigged so that at 20° flap setti ng, R.H. flap must not be more 1.0° lower or 4.0° above the L.H. flap. **Ailerons are rigged 2° down. Mo vements are measured from this neutral position. Elevator and rudder movements are m easured from a faired neutral position. ***For aircraft with Aerostar Kit 764 969V (ventral rudder) installed. Serial Numbers 60-0001 thru 60-0014, 60-0015- 26 thru 60-0056-128, 60-0130-057 thru 60-0933-8161262, Eligible 60-8261001 and subsequent. (See Note 4) A17WE 4 II Aerostar Model PA-60-601 (AEROSTAR 601) (Normal Category) Approved November 8, 1968. (See Note 2 and 4) Engines Two Lycoming IO-540-P1A5, IO-540-S1A5 or IO-540-G1B5 modified to incorporate turbochargers in accordance with RAJAY ST C SE6WE with Bendix fuel injector servos. 2524477 - for S/N 61-0001 thru 61-0334-111* and 2524491 - for S/N 61-0342-112 and subsequent *These aircraft require P/N 2524491 Bendi x fuel injector servos when modified in accordance with AAC Option 93. Fuel 100/130 and 100LL minimum grade aviation gasoline. Engine Limits *2575 RPM, 29.5 in. Hg. MAP (290 HP) for all operations. **2575 RPM, 29.5 in. Hg. MAP ( 290 HP) Maximum Continuous Power for takeoff, obstacle clearance, and emergency operati ons only. (No time limit). 2475 RPM, 29.5 in. Hg. MAP (278 HP) Maximum Normal Operating Power for noise certification and fo r all other operations. (See "Noise Characteristics" paragragh). *For S/N 61-0001 thru 61-0714-7962143 and 62-001 **For S/N 61-0715-8062144 and subsequent. Propeller Two Hartzell full-feathering propellers - HC- C3YR-2/C8468-8R or HC-C3YR-2UF/FC8468-8R. Propeller Limits a.) Pitch settings at 30 in. sta. Low 14°+ 0.1°, High 18° -21° Feather 82.5°+ 1.0° Diameter: 78 inches No cutoff for repairs permitted. b.) Spinners - Hartzell C-3258P c.) Propeller Governor - Hartzell F-6-5A, F- 6-35, F-6-35Z, F-6-36, F-6-36Z, F-8-35, F-8- 35Z, F-8-45, F-8-45Z. NOTE: If modified in accordance with AAC Option 64, Synchrophaser, Governor for right engine is F-8-35 or F-8-35Z. If modified in accordance with AAC Option 150, Synchrophaser, Governor for right engine is F-8-45 or F-8-45Z. Airspeed Limits (See Note 2) V ne- Never exceed 243 KCAS (280 MPH) V no- Max. structural cruising 217 KCAS (250 MPH) Reduce V ne and Vno (5 MPH) 4 knots for each 1,000 feet above 24,000 feet. V a- Max. design maneuvering 167 KCAS (192 MPH) V fe- *Flaps extended 20° 156 KCAS (180 MPH) 45° 130 KCAS (150 MPH) - **Flaps extended 20° 174 KCAS (200 MPH) 45° 149 KCAS (172 MPH) V le-Max. gear extended 156 KCAS (180 MPH) V lo-Max gear retraction 130 KCAS (150 MPH) -Max gear extension 156 KCAS (180 MPH) 5 A17WE *For S/N 61-0001 thru 61-0352-114 and 62-001. The flap speeds for these S/N aircraft may be increased from 130 KCAS and 156 KCAS to 149 KCAS and 174 KCAS respectively when modified in accordance with AAC Option No. 131. **For S/N 61-0357-115 and subsequent. C.G. Range LANDING GEAR EXTENDED OR RETRACTED WEIGHT FWD (1) AFT (1) AIRFRAME S/N 4600 lbs. 157.66 (12.2% MAC) 166. 00 (25.5% MAC) (6) 61-0001 thru 4600 157.66 (12.2% MAC) 167.88 (28. 5% MAC) 61-0334-111 and 5700 160.03 (15.7% MAC) 167.88 ( 28.5% MAC) 62-001 5700 160.03 (15.7% MAC) 166. 00 (25.5% MAC) (5) (4) (6) 4600 157.66 (12.2% MAC) 166.00 (25.5% MAC) (6) 61-0342-112 thru 4600 157.66 (12.2% MAC) 167.88 (28.5% MAC) 61-0806-8062151 6000 160.67 (17% MAC) 167.88 (28.5% MAC) 6000 160.67 (17% MAC) 166.00 (25.5% MAC) (5) (2) (6) 4600 157.66 (12.2% MAC) 166. 00 (25.5% MAC) (6) 61-0838-8162152 4600 157.66 (12.2% MAC) 167.88 (28.5% MAC) and subsequent 6000 160.67 (17% MAC) 167.88 (28.5% MAC) 6025 160.72 (17.1% MAC) 167.88 (28.5% MAC) 6000 160.67 (17% MAC) 166.00 (25.5% MAC) (5) (6) 6025 160.72 (17.1% MAC) 166.00 (25.5% MAC) (5) (6) (1) Straight line va riation between points. (2) These S/N aircraft have AAC Option No. 93 incorporated into the production aircraft. (3) AAC Option No. 93 extends each wing tip 15 in ches and increases the permissible maximum weight from 5700 lbs. to 6000 lbs. (4) The maximum weight of these S/N aircraft may be increased to 6000 lbs. when modified in accordance with AAC Option No. 93. (5) For aircraft equipped for Flight into known Icing (AAC Option No. 196). (6) For aircraft with Aerostar Ki t 764 969V (ventral rudder) installed. Empty Weight None C.G. Range Maximum Weight 6025 lbs. MAX RAMP (S/N 61-0838-8162152 and subsequent) 6000 lbs. MAX TAKEOFF (S/N 61-0342-112 and subsequent) 5700 lbs. MAX TAKEOFF (S/N 61-0001 thru 61-0334-111and 62-001)* All weight over 5900 lbs. must be fuel in the wing. *The maximum weight of these S/N airc raft may be increased to 6000 lbs. when modified in accordance with AAC Option No. 93 which extends each wing tip 15 inches No. of seats Crew or Fuselage Passenger Station 2 96 (CREW) 2 132 2 165* *When bench seat is fitted, thr ee occupants may be accommodated provided the the maximum weight of 380 lbs. is not exceeded. See Flight Manual for loading i n s t r u c t i o n s . A17WE 6 Maximum Baggage (See Note 2) Rear Compartment 240 lbs. at (+245) Fuel Capacity Wing Total Capacit y (65 gals. each).......... 130 gals Wing Total Usable (62 gals. each)............ 124 gals Fuselage Total C apacity.............................. 43.5 gals Fuselage Total Usable................................ 41.5 gals Aircraft Total Capacity................................... 173. 5 gals Aircraft Tota l Usable................................... 165.5 gals (See Note1 for unusable fuel) Oil Capacity Total Capacity two engines @ sta. +145.. 24 qts. Capacity each engine @ st a. +145............ 12 qts. Usable each engi ne..................................... 9 1/4 qts. (See Note 1 for undrainable oil) Maximum Operating Altitude 30,000 feet Control Surface Movement Wing Flaps* Down 45 °+ 3° Main Surfaces Aileron** Up 25° + 1° Down 15° + 1° Elevator Up 30° + 1° Down 10° + 1° Rudder Right 30° + 1° Left 30° + 1° ***Right 35° +1° - 0 ° Tabs (Main surface in neutral) Elevator Up 7°+ 1° Down 37° +9° - 1 ° Rudder Right 9° + 4° Left 37° + 4° - 1 ° -1° *Flaps must be rigged so that at 20° flap se tting, R.H. flap must not be more than 1.0° lower or 4.0° above the L.H. flap. **Ailerons are rigged 2° down. Movements are measured from this neutral position. Elevator and rudder movements are measured from a faired neutral position. ***For aircraft with Aerostar Kit 764 969V (ventral rudder) installed. Serial Numbers Eligible 61-0001 thru 61-0002-19 thru 61-0070-129, 61-0132-071 thru 61-0880-8162157, 60-82620001 and subsequent and 62-0001-013. (See Note 4) III Aerostar Model PA-60-601P (AEROSTAR 601P) (Normal Category) Approved November 14, 1973 (See Note 2, 3, and 4) Engines Two Lycoming IO-540-P1A5, IO-540-S1A5 m odified to incorporate automatic controlled turbochargers in accordance with RAJAY ST C SE60WE with Bendix fuel injector servos 2524477- for S/N 61P-0157-001 thru 61P-0211-021* and 2524491- for S/N 61P-0213-022 thru S/N 61P-0455-176** o r Two Lycoming IO-540-P1A5, IO-540-S1A5 modifi ed to incorporate automatic controlled turbochargers in accordance with AEROSTAR ST C SE81WE with Bendix fuel injector servos 2524491- for S/N 61P-0456-177 and subsequent. 7 A17WE *These aircraft require P/N 2524491 Bendix fuel injector servos when modified in accordance with AAC Option 93. **These aircraft incorporate turbochargers per AAC STC SE81WE when modified in accordance with AAC Option 155. Fuel 100/130 and 100LL minimum grade aviation gasoline Engine Limits *2575 RPM, 29.5 in. Hg. MAP (290 HP) for all operations. **2575 RPM, 29.5 in. Hg. MAP (290 HP) Maximum Continuous Power for takeoff, obstacle clearance, and emergency operati ons only. (No time limit). 2475 RPM, 29.5 in. Hg. MAP (278 HP) Maximum Normal Operating Power for noise certification and for all other operations. (No time limit) (See "Noise Characteristics" paragraph). *For S/N 61P-0157-001 thru 61P-0714-7963345 **For S/N 61P-0715-8063346 and subsequent Propeller Two Hartzell full-feathering propellers - HC-C3YR-2/C8468-8R or HC-C3YR-2UF/FC8468-8R Propeller Limits a.) Pitch settings at 30 in. sta. Low 14°+ 0.1°, High 18°-21° Feather 82.5°+ 1.0° Diameter: 78 inches No cutoff for repairs permitted b.) Spinners - Hartzell C-3258P c.) Propeller Governor - Hartzell F-6-5A, F-6- 35, F-6-35Z, F-6-36, F-6-36Z, F-8-35, F-8-35Z, F-8- 45, F-8-45Z. NOTE: If modified in accordance with AAC Option 64, Synchrophaser, Governor for right engine is F-8-35 or F-8-35Z. If modified in accordance with AAC Option 150, Synchrophaser, Governor for right engine is F-8-45 or F-8-45Z. Airspeed Limits (See Note 2) V ne- Never exceed 243 KCAS (280 MPH) V no- Max. structural cruising 217 KCAS (250 MPH) Reduce V ne and Vno (5 MPH) 4 knots for each 1,000 feet above 24,000 feet. V a- Max. design maneuvering 163 KCAS (188 MPH) V fe- *Flaps extended 20° 156 KCAS (180 MPH) 45° 130 KCAS (150 MPH) - **Flaps extended 20° 174 KCAS (200 MPH) 45° 149 KCAS (172 MPH) V le-Max. gear extended 156 KCAS (180 MPH) V lo-Max gear retraction 130 KCAS (150 MPH) -Max gear extension 156 KCAS (180 MPH) *For S/N 61P-0157-001 thru 61P -0354-109. The flap speeds for these S/N aircraft may be increased from 150 MPH CAS and 180 MPH CAS to 172 MPH CAS and 200 MPH CAS respectively when modified in accordance with AAC Option No. 131. **For S/N 61P-0356-128 and subsequent. A17WE 8 C. G. Range LANDING GEAR EXTENDED OR RETRACTED WEIGHT FWD (1) AFT (1) AIRFRAME S/N 4600 lbs. 157.66 (12.2% MAC) 166. 00 (25.5% MAC) (6) 61P-0157-001 thru 4600 157.66 (12.2% MAC) 167.88 ( 28.5% MAC) 61P-0211-021; 5700 160.03 (15.7% MAC) 167.88 (28.5% MAC) 5700 160.03 (15.7% MAC) 166. 00 (25.5% MAC) (5) (4) (6) 4600 157.66 (12.2% MAC) 166.00 (25.5% MAC) (6) 61P-0213-022 thru 4600 157.66 (12.2% MAC) 167.88 ( 28.5% MAC) 61P-0825-8063433; LANDING GEAR EXTENDED OR RETRACTED WEIGHT FWD (1) AFT (1) AIRFRAME S/N 6000 160.67 (17% MAC) 167.88 (28.5% MAC) 6000 160.67 (17% MAC) 166.00 (25.5% MAC) (5) (2) (6) 4600 lbs. 157.66 (12.2% MAC) 166.00 (25.5% MAC) (6) 61P-0826-8163434 4600 157.66 (12.2% MAC) 167.88 ( 28.5% MAC) and subsequent 6000 160.67 (17% MAC) 167.88 (28.5% MAC) 6025 160.72 (17.1% MAC) 167.88 (28.5% MAC) 6000 160.67 (17% MAC) 166.00 (25.5% MAC) (5) (6) 6025 160.72 (17.1% MAC) 166.00 (25.5% MAC) (5) (6) (1) Straight line va riation between points. (2) These S/N aircraft have AAC Option No. 93 incorporated into the production aircraft (3) AAC Option No. 93 extends each wing tip 15 in ches and increases the permissible maximum weight from 5700 lbs. to 6000 lbs. (4) The maximum weight of these S/N aircraft may be increased to 6000 lbs. when modified in accordance with AAC Option No. 93. (5) For aircraft equipped for Flight In to Known Icing (AAC Option No. 196). (6) For aircraft with Aerostar Ki t 764 969V (ventral rudder) installed. Empty Weight None C.G. Range Maximum Weight 6025 lbs. MAX RAMP (S/N 61P-0826-8163434 and subsequent) 6000 lbs. MAX TAKEOFF (S/N 61P-0213-022 and subsequent) 5700 lbs. MAX TAKEOFF (S/N 61P-0157-001 thru 61P-0211-021)* All weight over 5900 lbs. must be fuel in the wing. *The maximum weight may be increased from 5700 lbs. to 6000 lbs. when modified in accordance with AAC Option No. 93 which extends each wing tip 15 inches. Number of Seats Crew or Fuselage Passenger Station 2 9 6 ( c r e w ) 2 132 2 165* *When bench seat is fitted, three occupants may be accommodated provided that the maximum weight of 380 lbs. is not exceeded. See Flight Manual for loading instructions. 9 A17WE Maximum Baggage (See Note 2 ) Rear compartment 240 lbs. at (+245). Fuel Capacity Wing Total Capacit y (65 gals. each).......... 130 gals Wing Total Usable (62 gals. each)............ 124 gals Fuselage Total C apacity.............................. 43.5 gals Fuselage Total Usable................................. 41. 5 gals Aircraft Total C apacity................................ 173.5 gals Aircraft Tota l Usable................................. 165.5 gals (See Note 1 for unusable fuel) Oil Capacity Total Capacity two engines @ sta. +145... 24 qts Capacity each engine @ sta. +145............ 12 qts Usable each engi ne................................... 9 1/4 qts (See Note 1 for undrainable oil) Maximum Operating Altitude 25,000 feet (30,000 feet when equipped with AAC Option 262, and 264.) Maximum Cabin Operating Pressure 4.25 PSI (5.50 PSI when equipped with AAC Option 262.) Control Surface Movement Wing Flaps* Down 45 °+ 3° Main Surfaces Aileron** Up 25° + 1° Down 15° + 1° Elevator Up 30° + 1° Down 10° + 1° Rudder Right 30° + 1° Left 30° + 1° ***Right 35° + 1° - 0 ° Tabs (Main surface in neutral) Elevator Up 7°+ 1° Down 37° +9° - 1 ° Rudder Right 9° +4° Left 37° +4° - 1 ° - 1 ° *Flaps must be rigged so that at 20° flap setting, the R.H. flap must not be more than 1.0° lower or 4.0° above the L.H. flap. **Ailerons are rigged 2° down. Movements are measured from this neutral position. Elevator and rudder mo vements are measured from a faired neutral position. ***For aircraft with Aerostar Kit 764 969V (ventral rudder) installed Serial Numbers Eligible 61P-0157-001 thru 61P-0860-8163455, 60-8263001 and subsequent. (See Note 4) IV - Aerostar Model PA-60-602P (AEROSTAR 602P) (Normal Category) Approved October 30,1980 (See Note 2, 3, & 4) Engines Two Lycoming IO-540-AA1A5 engines incorpor ating Bendix fuel injector servos Bendix P/N 2524846-1 and automatically controlled tur bochargers Aerostar Kits P/N 300076-515 (LH engine) and P/N 300076-517 (RH engine). Fuel 100/130 and 100LL minimum grade aviation gasoline. Engine Limits 2425 RPM, 37 in. Hg. MAP (290 HP) for all operations. Propeller Two Hartzell full-feathering propellers - HC-C3YR-2UF/FC8468-8R, or HC-C3YR-2/C8468-8R A17WE 10 Propeller Limits a.) Pitch settings at 30 in. sta. Low 15.9°+ 0.1°, High 18°-21° Feather 82.5°+ 1.0° Diameter: 78 in. No cutoffs for repairs permitted b.) Spinners - Hartzell C-3258P c.) Propeller Governor - Hartzell F-6-60Z, F-8-60Z. NOTE: If Modified in accordance with AAC Option #150, Synchrophaser, Governor for right engine is F-8-60Z. Airspeed Limits (See Note 2) (KCAS). V ne- Never exceed 243 KCAS (280 MPH) V no- Max. structural cruising 217 KCAS (250 MPH) Reduce V ne and Vno (5 MPH) 4 knots for each 1,000 feet above 24,000 feet. V a- Max. design maneuvering 167 KCAS (192 MPH) V fe- *Flaps extended 20° 174 KCAS (200 MPH) 45° 149 KCAS (172 MPH) V le-Max. gear extended 156 KCAS (180 MPH) V lo-Max gear retraction 130 KCAS (150 MPH) -Max gear extension 156 KCAS (180 MPH) C. G. Range LANDING GEAR EXTENDED OR RETRACTED WEIGHT FWD (1) AFT (1) AIRFRAME S/N 4600 lbs. 157.66 (12.2% MAC) 166.00 (25.5% MAC) 62P-0750-8165001, 6000 160.67 (17% MAC) 166.00 ( 25.5% MAC) 62P-0861-8165002 6029 160.72 (17.1% MAC) 166.00 ( 25.5% MAC) and subsequent (1) Straight line va riation between points. Empty Weight None C.G. Range Maximum Weight 6029 lbs. MAX RAMP 6000 lbs. MAX TAKEOFF Number of Seats Crew or Fuselage Passenger Station 2 9 6 ( c r e w ) 2 132 2 165* *When bench seat is fitted, three occupants may be accommodated provided that the maximum weight of 380 lbs. is not exceeded. See Flight Manual for loading instructions. Maximum Baggage (See Note 2) Rear compartment 240 lbs. at (+245). 11 A17WE Fuel Capacity Wing Total Capacit y (65 gals. each).......... 130 gals Wing Total Usable (62 gals. each)............ 124 gals Fuselage Total C apacity.............................. 43.5 gals Fuselage Total Usable................................. 41. 5 gals Aircraft Total C apacity................................ 173.5 gals Aircraft Total Usable................................. 165. 5 gals (See Note 1 for unusable fuel) Oil Capacity 12 qts. per engine (9.25 qts. per engine usable) (See Note 1 for undrainable oil). Maximum Operating Altitude 25,000 feet (30,000 feet when equipped with AAC Options 262, and 264.) Maximum Cabin Operating Pressure 4.25 PSI (5.50 PSI when equipped with AAC Option 262.) Control Surface Movement Wing Flaps* Down 45 °+ 3° Main Surfaces Aileron** Up 25° + 1° Down 15° + 1° Elevator Up 30° + 1° Down 10° + 1° Rudder Right 30° + 1° Left 30° + 1° ***Right 35° + 1° - 0 ° Tabs (Main surface in neutral) Elevator Up 7°+ 1° Down 37° +9° - 1 ° Rudder Right 9° + 4° Left 37° + 4° - 1 ° - 1 ° *Flaps must be rigged so that at 20° flap setting R.H. flap must not be more than 1.0° lower or 4.0° above the L.H. flap. **Ailerons are rigged 2° down. Movements are measured from this neutral position. Elevator and rudder mo vements are measured from a faired neutral position. ***For aircraft with Ae rostar Kit 764 969 V (ventral rudder) installed. Serial Numbers Eligible 62P-0750-8165001, 62P-0861-8165002 thru 62P-0932-8165055, 60-8265001 and subsequent. (See Note 4) V-Model PA-60-700P (AEROSTAR 700P) (Normal Category) Approved May 24, 1983. (See Notes 2 & 3) Same as PA-60-602P except engines, propellers, ma ximum weights, increase zero fuel weight, flight envelope shifted forward, added elevator gap seals, elevator bob weight, cowl flaps, stall warning system, increase span on elevator and rudder trim tabs, and other minor changes. Engines 1 Lycoming LTIO-540-U2A and 1 TIO- 540 U2A engine incorporating Bendix fuel injector servos Bendix P/N 2549056 and automatically controlled turbochargers Aerostar Kits P/N 300154-1 (L H engine) and P/N 300154-501 (RH engine). Fuel 100/130 and 100LL minimum aviation gasoline. Engine Limits 2500 RPM, 42 in. Hg. MAP (350 HP) Sea level to 16,500 feet. A17WE 12 Propeller Two Hartzell full-feathering propellers - HC-C3YR-2LUF/FJC7451 (b) (Left Side) HC-C3YR-2UF/FC7451 (b) (Right Side) Propeller Limits a.) Pitch setting at 30 in. sta. Low 15.9° + 0.2° Feather 80° + 1.0° Diameter: 76 in. max, 75 in. min. b.) Spinners - Hartzell D-4816P c.) Propeller Governor - Hartzell F-6-63LZ (Left) Hartzell F-6-63Z (Right) Note: If modified in accordance with AAC Option 220, Synchrophaser, Governor for right engine is F-8-63Z Airspeed Limits (See Note 2) (KIAS) V ne- Never exceed 244 KIAS (281 MPH) V no- Max. structural cruise 215 KIAS (248 MPH) Reduce V ne and Vno 4 knots for each 1,000 feet above 24,000 feet. V a- Max. design maneuvering 160 KIAS (184 MPH) V fe- flaps extended 20° 188 KIAS (217 MPH) 45° 148 KIAS (170 MPH) V le- Max. landing gear extended 153 KIAS (176 MPH) V lo- Max. landing gear operation Extension 153 KIAS (176 MPH) Retraction 140 KIAS (161 MPH) C.G. Range LANDING GEAR EXTENDED OR RETRACTED WEIGHT (LBS.) FWD (1) AFT (1) SERIAL NUMBER 4250 lbs 157.00 (11.17% MAC) 165.00 (23.9% MAC) 5400 157.00 (11.17% MAC) 165.00 (23.9% MAC) 60-8223001, ` 6000 160.20 (16.3% MAC) 165.00 (23.9% MAC) 60-8423001 6315 161.70 (18.7% MAC) 165. 00 (23.9% MAC) and subsequent (1) Straight line variation between points. Mo ment change due to retracting landing gear (-206 in. lbs.). Empty Weight C.G. Range None Maximum weight 6356 lbs. Max. Ramp. 6315 lbs. Max. Takeoff 6000 lbs. Max. Landing Number of Seats Crew or Fuselage Passenger Station 2 9 6 ( c r e w ) 2 132 2 165* * When bench seat is fitted, thr ee occupants may be accommodated provided that the maximum wei ght of 380 lbs. is not exceeded. See Flight Manual for loading instructions. 13 A17WE Maximum Baggage (See Note 2 & 6) Rear compartment 240 lbs. at (+245). Fuel Capacity Wing Total Capacit y (65 gals. each).......... 130 gals Wing Total Usable (62 gals. each)............ 124 gals Fuselage Total C apacity.............................. 43.5 gals Fuselage Total Usable................................. 41. 5 gals Aircraft Total Capacity................................... 173. 5 gals Aircraft Tota l Usable................................... 165.5 gals (See Note 1 for unusable fuel) Oil Capacity 12 qts. per engine (9.25 qts. per engine usable) (See Note 1 for undrainable oil.) Maximum Operating Altitude 25,000 feet (30,000 feet when equipped with AAC Options 262, and 264) Maximum Cabin Operating Pressure 4.25 PSI (5. 50 PSI when equipped with AAC Option 262). Control Surface Movement Wing Flaps* Down 45° + 3° Main Surfaces Ailerons** Up 25° + 1° Down 15° + 1° Elevator Up 29° + 1°, -0° Down 11° + 1°, -0° Rudder Right 30° + 1° Left 30° + 1° Tabs (Main Surface in Neutral) Elevator Up 7° + 1° Down 37° + 9°, -1° Rudder Right 24° + 2°, -1° Left 20° + 2°, -1° *Flaps must be rigged so that at 20° flap setting, the right and left flaps agree within + 1° of each other. **Ailerons are rigged 2° down. Movements are measured from this neutral position. Elevator and rudder movements ar e measured from a faired neutral position. Serial Numbers Eligible 60-8223001, 60-8423001 and up. Data Pertinent to All Models Datum F.S. 0.00 at 150.00 in. forward of wing L.E. Leveling Means Across and along floor seat tracks (use bubble scale) Certification Basis Models PA-60-600, PA-60-601, PA-60-601P, PA-60-602P FAR Part 23 effective February 1, 1965 wi th Amendments 23-1 through 23-6 effective August 1, 1967. In addition, aircraft modified with Aerostar Kit 764 969V (ventral rudder) comply with the following paragraphs: 23.207 of Amendment 7 and 23.201, 23.203 and 23.205 of Amendment 14. No exemptions. Compliance with ice protection requirem ents has been shown in accordance with FAR 23.1091 of Amendment 23-7 effective August 13, 1969; FAR 23.929 and 23.1419 of Amendment 23-14 effective November 19, 1973; FAR 23.1093 and 23.1193 of Amendment 23-18 effective March 17, 1977; and FAR 23. 1416 of Amendment 23-23 effective December 1, 1978 when AAC Option No. 196 is installed. For Model 602P, compliance with engine coo ling requirments has been shown in accordance with FAR 23.1041 of Amendment 23-7 e ffective August 13, 1969 and 23.1043 of Amendment 23-21 effective Januar y 6, 1978 applied per 21.101 (b). A17WE 14 SFAR 27 EPA Regulation Part 87, effective February 7, 1973. Application for Type Ce rtificate dated June 22, 1967. Reference Engine Lycoming IO-540- Type Certificate Data Sheet No. 1E4. FAR Part 36 "Noise Standard" Amendment s 36-1 through 36-9 effective April 3, 1978. For Models 601P and 602P Special Conditi on No. 23-48-WE-15 dated February 7, 1973 (pertaining to doors and exits, and oxygen system). Model PA-60-700P FAR Part 23 effective February 1, 1965, as amended by Amendments 23-1 through 23-6, and the following Amendments: FAR 23.75,23.207, 23.909, 23.1041, 23.1091, 23.1563 of Amendment 7; FAR 23.201, 23.203,23.205, 23.1435, of Amendment 14; FAR 23.1143 of Amendment 17; FAR 23.901, 23.959, 23.1093, 23.1193, 23.1305 of Amendment 18; FAR 23.1301, 23.1351, 23. 1357, of Amendment 20; FAR 23.1043, 23.1047, 23.1583, and 23.1585, of Amendment 21. In addition, when the aircraft is fitted with optional equipment and approved for flight into known icing, the following regulations apply: FAR 23.929, 23.1419 of Amendment 14; FAR 23.1325 of Amendment 20; and FAR 23.1416 of Amendment 23. No exemptions. No equivalent safety findings. FAR Part 36 "Noise Standard" Amendment s 36-1 through 36-12 effective April 1, 1981. Special Condition No. 23-48-WE-15 amended February 23, 1983 (Pertaining to doors and exits, and oxygen system). Production Basis None. Spare parts only are produced under license. Equipment The basic required equipm ent as prescribed in the applicable Airworthiness Regulations (See Certification Basis) must be inst alled in the aircraft for certification. In addition, the following items of equipment are required. Airplane Flight Manual REPORT MODEL AIRFRAME SEQUENCE NUMBERS VB-1201 600 0001 through 0560. VB-1202 600 0561 through 0714. VB-1203 600 0715 through 0825. VB-1204 600 0826 and up. VB-1205 601 0001 through 0341 when Option 93 (Gross Weight Increase) is not installed. VB-1206 601 0001 through 0341 when Option 93 (Gross Weight Increase) is installed and 0342 through 0560. VB-1207 601 0561 through 0714. VB-1208 601 0715 through 0825. VB-1209 601 0826 and up. VB-1210 601P 0157 through 0212 when Option 93 (Gross Weight Increase) or 155 (Higher Altitude Turbo Installation) is not installed. 15 A17WE VB-1211 601P 0157 through 0212 when Option 93 (Gross Weight Increase) is installed and Option 155 (Higher Altitude Turbo Installation) is not installed and 0213 through 0455 when Option 155 (Higher Altitude Turbo Installation) is not installed. VB-1212 601P 0157 through 0212 when Option 93 (Gross Weight Increase) and 155 (Higher Altitude Turbo Installation) are installed, 0213 through 0455 when Option 155 (Higher Altitude Turbo Installation) is installed and 0456 through 0560. VB-1213 601P 0561 through 0714. VB-1214 601P 0715 through 0825. VB-1215 601P 0826 and up. Pilot's Operating Handbook/Airplane Flight Manual VB-1190 602P Aircraft serial numbers 60-8165001 through 60- 8365021. VB-1220 700P 60-8223001 and 60-8423001 and up. The approved types of operation were estab lished during the Type Certification and are valid ` only when the required equipment specified in the Required Operating Equipment List of the FAA Approved Airplane Manual is installed and operating. Noise Characteristics: The corrected noise le vel of the Models 600/601/601P is 80.0 dBA at the Maximum Normal Operating Power at 2520 RPM (Model 600) and 2475 RPM (Model s 601/601P) (top of the green arc on the RPM indicator). A 2.4 dBA (Model 600) and 1.4 dBA (Model s 601/601P) credit was also allowed for the takeoff and climb performance at a takeoff gross we ight of 5500 pounds (Model 600) and 6000 pounds (Models 601/601P). The corrected noise level of the Model 602P is 79.4 dBA at Maximum continuous Power at 2425 RPM. A 2.5 dBA credit was also allowed for the takeoff and climb performance at a takeoff gross weight of 6000 pounds. The noise level stated abov e has been verified by and approved by the Federal Aviation Administration in noise le vel test flights conducted in accordance with FAR 36, "Noise Standards : Aircraft Type and Airworthiness Certification." The aircraft noise is in compliance with FAR 36 noise standards applicable to this type. The corrected noise level of the Model 700P is 78. 8 dBA at the Maximum Normal Operating Power at 2500 RPM. A 2.0 dBA credit was also allowed for the tak eoff and climb performance at a takeoff gross weight of 6315 pounds. The noise level stated above has been approv ed by the Federal Aviation Administration in noise level test flights conducted in accordance with FAR 36, "Noise Standards : Aircraft Type and Airworthiness Certification." The aircraft noise is in compliance with FAR 36 noise standards applicable to this type. Note 1. Current weight and balance report including list of equipment included in certificated empty weight, and loading instructions, when necessary, must be provi ded for each aircraft at the time of original certificaton. The certified empty weight and corresponding center of gravity locations must include undrainable system oil of 7.5 lbs. at (+145) and unusable fuel of 24 lbs. at (+204.4). The full amount of usable fuel is based on the airplane sitting on a level ramp, laterally level, and longitudinally level (approx imately 1 1/2° nose up) with each tank fueled to 0.6 in. below filler neck. NOTE: The wing tanks are extremely sensitiv e to attitude and if not level, they cannot be fueled to the full usable capacity. A17WE 16 Note 2. All required placards listed in the limitations section of the AFM must be installed in the appropriate locations. The following placards must be placed in clear view of the pilot. (1) This airplane must be operated as a norma l category airplane in compliance with the operating limitations stated in the form of placards, markings, and manuals. (2) This airplane approved for day/night VFR /IFR non-icing flight when equipped in accordance with the Airplane Flight Manual. No acrobatic maneuvers, including spins, approved. (3) For airplanes equipped with AAC Option No. 196: This airplane approved for day/night VFR/IFR icing flight when equipped in accor dance with the Airplane Flight Manual. No acrobatic maneuvers, including spins, approved. Note 3. Life Limitations (Model 601P, 602P and 700P Only). P / N Item Service Life Limits Hours 824007 Cabin Window 16000 210038-501 Windshield 4860 210807 Cabin Windows and Windshield 13,200 when equipped with AAC Option 262 210807 Cabin Windows and Windshield 9,900 when equipped with AAC Options 262 and 264 Note 4. The change to the model designation and se rial number format are shown in (1) and (2) below: (1) For aircraft up to and incl uding 60-0933-8161262, 61-0880-8162157, 61P-0860-8163455 and 62P-0932-8165055, the original Aerostar Model 600 series designation and serial number format is as follows: (a) The first two digits or two digi ts plus letter indicates the model number: (1) 60 denotes Model 600 (2) 61 denotes Model 601 (3) 61P denotes Model 601P (4) 62P denotes Model 602P (b) The last dash number of the airplane se rial number indicates the factory airframe number, model year and Piper Model Code. (c) The largest number of the second or th ird set of numbers is always the airframe number. If there are only two sets of numbers, the second set of numbers indicates the model sequence number. (d) If the last numbers are more than four digi ts, the first digits indicate the model year, the second, two digits indicate a Piper Model Code, and the last three digits indicate the model sequence number. (2) For aircraft subsequent to seri al numbers 60-0933-8161262, 61-0880-8162157, 61P-0860- 8163455, and 62P-0932-8165055, the model designations have been changed from Ted Smith Aerostar Models 600, 601, 601P,and 602P to Piper Models PA-60-600, PA-60-601, PA-60- 601P, and PA-60-602P, repectively. All data rela ting to the designations 600, 601, 601P, and 602P are also applicable to the new designati ons. Also effective with this change, the serial number format is as follows: 60-XXYYZZZ (a) The first two digits (60) indica te the basic type certificate designations. (b) The second two digits (XX) indicate the year model. 17 A17WE (c) The third two digits (YY) indicate the Piper model code: (1) 61 denotes PA-60-600 (2) 62 denotes PA-60-601 (3) 63 denotes PA-60-601P (4) 65 denotes PA-60-602P (5) 23 denotes PA-60-700P (d) The final three digits (ZZZ) indica te the model sequence number in the given model year. NOTE 5. The following aircraft were the last seri al numbers manufactured at Santa Maria, California: Model S / N PA-60-600 60-0933-8161262 PA-60-601 61-0880-8162157 PA-60-601P 61P-0860-8163455 PA-60-602P 62P-0932-8165055 NOTE 6. When the optional 40 gallon fu selage fuel tank is installed per AAC STC SA5492SW, the amount of aft baggage that can be carried must be reduced to comply with the baggage placard part No. NAYAK 35049-20. .....END..... ``` ## ADs (40, in force first) - [AD 2023-09-09](https://openairdocs.org/ad/2023-09-09): Exhaust Turbine System (Recip) · Aerostar PA-60-600 (Aerostar 600), PA-60-601 (Aerostar 601), PA-60-601P (Aerostar 601P) and 292 more. Effective Jul 17, 2023 - [AD 2022-03-15](https://openairdocs.org/ad/2022-03-15): Fuel Quantity Indicator · Garmin G3X Touch Electronic Flight Instrument System (STC SA01899WI or SA02658SE). Effective Mar 21, 2022 - [AD 2020-24-10](https://openairdocs.org/ad/2020-24-10): Flight Controls · Aerostar PA-60-601P (Aerostar 601P), PA-60-602P (Aerostar 602P) and PA-60-700P (Aerostar 700P). Effective Jan 22, 2021 - [AD 2006-12-07](https://openairdocs.org/ad/2006-12-07): ECi cylinder assemblies · Aerostar AEIO-320-D1B, AEIO-320-D2B, AEIO-320-E1A and 386 more. Effective Jul 11, 2006 - [AD 2005-18-20](https://openairdocs.org/ad/2005-18-20): "FASTprop" propeller de-icers · Hartzell PHC-C3YF-1RF/F8468A(B,K)-8R constant speed propeller (STC SA00718LA or 17 others). Effective Oct 14, 2005 - [AD 2005-01-19](https://openairdocs.org/ad/2005-01-19): Mode S transponders · GARMIN International GTX 330D, GTX 330, GTX 33D and 830 more. Effective Feb 23, 2005 - [AD 2003-22-01](https://openairdocs.org/ad/2003-22-01): Auxiliary fuel transfer pumps · Aerostar PA-60-600 (Aerostar 600), PA-60-601 (Aerostar 601), PA-60-601P (Aerostar 601P) and 2 more. Effective Nov 17, 2003 - [AD 2002-24-07](https://openairdocs.org/ad/2002-24-07): Roto-Master and Rajay scavenge pumps · Aerostar PA-60-601 (Aerostar 601), PA-60-601P (Aerostar 601P), PA-60-602P (Aerostar 602P) and 1 more. Effective Jan 17, 2003 - [AD 2001-10-09](https://openairdocs.org/ad/2001-10-09): Automatic Flight Control Systems · Aerostar PA-60-700P (Aerostar 700P), 208, 208B and 15 more. Effective Jun 15, 2001 - [AD 2001-08-10](https://openairdocs.org/ad/2001-08-10): Main Landing Gear Lower Side Brace Assemblies · Aerostar PA-60-600 (Aerostar 600), PA-60-601 (Aerostar 601), PA-60-601P (Aerostar 601P) and 2 more. Effective Jun 12, 2001 - [AD 98-24-29](https://openairdocs.org/ad/98-24-29): Wing Upper Spar Cap · Aerostar PA-60-600 (Aerostar 600), PA-60-601 (Aerostar 601), PA-60-601P (Aerostar 601P) and 2 more. Effective Jan 8, 1999 - [AD 98-04-23](https://openairdocs.org/ad/98-04-23): AFM - Limitations Section - Icing · Aerostar PA-60-600 (Aerostar 600), PA-60-601 (Aerostar 601), PA-60-601P (Aerostar 601P) and 2 more. Effective Mar 13, 1998 - [AD 95-23-11](https://openairdocs.org/ad/95-23-11): Upper And Lower Horizontal Flanges · Aerostar PA-60-600 (Aerostar 600), PA-60-601 (Aerostar 601), PA-60-601P (Aerostar 601P) and 1 more. Effective Nov 30, 1995 - [AD 94-15-13](https://openairdocs.org/ad/94-15-13): Nose Landing Gear Drag Link Assembly · Aerostar PA-60-600 (Aerostar 600), PA-60-601 (Aerostar 601), PA-60-601P (Aerostar 601P) and 2 more. Effective Sep 12, 1994 - [AD 93-13-08](https://openairdocs.org/ad/93-13-08): Torque Links · Aerostar PA-60-600 (Aerostar 600), PA-60-601 (Aerostar 601), PA-60-601P (Aerostar 601P) and 2 more. Effective Aug 20, 1993 - [AD 91-23-16](https://openairdocs.org/ad/91-23-16): Manifold Pressure Operations · Aerostar PA-60-700P (Aerostar 700P). Effective Dec 20, 1991 - [AD 90-01-02](https://openairdocs.org/ad/90-01-02): Service Bulletin 920 - Fire Prevention · Aerostar PA-60-600 (Aerostar 600), PA-60-601 (Aerostar 601), PA-60-601P (Aerostar 601P) and 2 more. Effective Mar 1, 1990 - [AD 89-03-04](https://openairdocs.org/ad/89-03-04): Cabin Door · Aerostar PA-60-600 (Aerostar 600), PA-60-601 (Aerostar 601), PA-60-601P (Aerostar 601P) and 2 more. Effective Feb 24, 1989 - [AD 88-25-02](https://openairdocs.org/ad/88-25-02): Engine Fluid-Carrying Hoses · Aerostar PA-60-601 (Aerostar 601), PA-60-601P (Aerostar 601P), PA-60-602P (Aerostar 602P) and 1 more. Effective Dec 26, 1988 - [AD 88-21-05](https://openairdocs.org/ad/88-21-05): Exhaust Systems (STC SA980NM) · Aerostar PA-60-600 (Aerostar 600), PA-60-601 (Aerostar 601), PA-60-601P (Aerostar 601P) and 2 more. Effective Nov 6, 1988 - [AD 87-21-01](https://openairdocs.org/ad/87-21-01): Fuel Filler Openings · Aerostar PA-60-600 (Aerostar 600), PA-60-601 (Aerostar 601), PA-60-601P (Aerostar 601P) and 14 more. Effective Nov 2, 1987 - [AD 87-07-09](https://openairdocs.org/ad/87-07-09): Exhaust System Components · Aerostar PA-60-600 (Aerostar 600), PA-60-601 (Aerostar 601), PA-60-601P (Aerostar 601P) and 2 more. Effective May 15, 1987 - [AD 85-23-07](https://openairdocs.org/ad/85-23-07): Autopilot Systems · Aerostar PA-60-700P (Aerostar 700P), 172L, 172P and 37 more. Effective Jan 27, 1986 - [AD 83-14-07 R3](https://openairdocs.org/ad/83-14-07-R3): Limitations Section -- CG Limit · Aerostar PA-60-600 (Aerostar 600), PA-60-601 (Aerostar 601), PA-60-601P (Aerostar 601P) and 1 more. Effective Nov 25, 1983 - [AD 80-18-03](https://openairdocs.org/ad/80-18-03): Fuel Pressure System · Aerostar PA-60-601 (Aerostar 601) and PA-60-601P (Aerostar 601P). Effective Oct 6, 1980 - [AD 80-19-14](https://openairdocs.org/ad/80-19-14): Horizontal/Vertical Stabilizer · Aerostar PA-60-600 (Aerostar 600), PA-60-601 (Aerostar 601) and PA-60-601P (Aerostar 601P). Effective Sep 25, 1980 - [AD 80-17-04](https://openairdocs.org/ad/80-17-04): Fuel Flow Transducers · Aerosonic Fuel Flow Transducers, PA-60-600 (Aerostar 600), PA-60-601 (Aerostar 601) and 9 more. Effective Aug 13, 1980 - [AD 80-12-14](https://openairdocs.org/ad/80-12-14): Engine Fire · Aerostar PA-60-600 (Aerostar 600), PA-60-601 (Aerostar 601) and PA-60-601P (Aerostar 601P). Effective Jun 19, 1980 - [AD 79-01-05](https://openairdocs.org/ad/79-01-05): Fuel Starvation · Aerostar PA-60-600 (Aerostar 600), PA-60-601 (Aerostar 601) and PA-60-601P (Aerostar 601P). Effective Dec 27, 1979 - [AD 79-18-10](https://openairdocs.org/ad/79-18-10): Cabin Door Latching Mechanism · Aerostar PA-60-600 (Aerostar 600) and PA-60-601 (Aerostar 601). Effective Aug 29, 1979 - [AD 79-08-05](https://openairdocs.org/ad/79-08-05): Engine Nacelles · Aerostar PA-60-600 (Aerostar 600), PA-60-601 (Aerostar 601) and PA-60-601P (Aerostar 601P). Effective May 24, 1979 - [AD 78-18-05](https://openairdocs.org/ad/78-18-05): Wing Tank Fuel Quantity Indicator · Aerostar PA-60-600 (Aerostar 600), PA-60-601 (Aerostar 601) and PA-60-601P (Aerostar 601P). Effective Sep 13, 1978 - [AD 74-25-02](https://openairdocs.org/ad/74-25-02): Electrical Attitude And Directional Gyros · Aerostar PA-60-600 (Aerostar 600), PA-60-601 (Aerostar 601) and PA-60-601P (Aerostar 601P) with STC SA2336WE or SA2367WE. Effective Dec 4, 1974 - [AD 70-23-04](https://openairdocs.org/ad/70-23-04): Wing Flap Tracks · Aerostar PA-60-600 (Aerostar 600) and PA-60-601 (Aerostar 601). Effective Aug 23, 1971 - [AD 71-17-07](https://openairdocs.org/ad/71-17-07): Wing Flap Attachment Rib · Aerostar PA-60-600 (Aerostar 600) and PA-60-601 (Aerostar 601). Effective Aug 23, 1971 - [AD 71-10-02](https://openairdocs.org/ad/71-10-02): Overvoltage Relay Ground · Aerostar PA-60-600 (Aerostar 600) and PA-60-601 (Aerostar 601). Effective May 14, 1971 - [AD 71-05-06](https://openairdocs.org/ad/71-05-06): Main Landing Gear · Aerostar PA-60-600 (Aerostar 600) and PA-60-601 (Aerostar 601). Effective Apr 5, 1971 - [AD 71-02-05](https://openairdocs.org/ad/71-02-05): Main Cabin Door Lock Pins · Aerostar PA-60-600 (Aerostar 600) and PA-60-601 (Aerostar 601). Effective Jan 23, 1971 - [AD 70-25-09](https://openairdocs.org/ad/70-25-09): Microphone Jack Connection · Aerostar PA-60-600 (Aerostar 600) and PA-60-601 (Aerostar 601). Effective Dec 18, 1970 - [AD 70-23-05](https://openairdocs.org/ad/70-23-05): Fuel Pressure Indicators · Aerostar PA-60-600 (Aerostar 600) and PA-60-601 (Aerostar 601). Effective Nov 16, 1970 ## Registered aircraft by registry model (OpenAirDocs) - [Piper PA-60-602P](https://openairdocs.org/model/piper-pa-60-602p): 31 aircraft (registry code 7106015) - [Piper PA-60-700P](https://openairdocs.org/model/piper-pa-60-700p): 17 aircraft (registry code 7106023) - [Piper PA-60-601P](https://openairdocs.org/model/piper-pa-60-601p): 9 aircraft (registry code 7106016) - [Piper AEROSTAR 600](https://openairdocs.org/model/piper-aerostar-600): 1 aircraft (registry code 7104100) - [Aerostar PA-60-601](https://openairdocs.org/model/aerostar-pa-60-601): 0 aircraft (registry code 7106017) ## STCs approved under this data sheet (251, first 50) - [STC SA02571SE](https://openairdocs.org/stc/SA02571SE): Installation of Garmin G500/G600 TXi Integrated Avionics System (Primary Flight Display, Multi-Function Display, and Engine Indicating System Display).. Garmin International Inc. - [STC SA01800SE](https://openairdocs.org/stc/SA01800SE): Fabrication and installation of new or replacement of existing instrument panel lights dimmer control.. TCW Technologies, LLC - [STC SA01861SE](https://openairdocs.org/stc/SA01861SE): Fabrication and installation of Landing Light Controller. TCW Technologies, LLC - [STC SA12428CH](https://openairdocs.org/stc/SA12428CH): Installation of the Lycoming Engines Electronic Ignition System (EIS). Lycoming Engines, An Operating Division of AVCO Corporation - [STC SA04837NY](https://openairdocs.org/stc/SA04837NY): Installation of AeroLED's Holdings, LLC., position lights, navigation lights, strobe lights and beacon lights. AeroLED's Holdings, LLC - [STC SA12406WI](https://openairdocs.org/stc/SA12406WI): Installation of a Garmin AXIS Flight Display System. Garmin International Inc. - [STC SA02636SE](https://openairdocs.org/stc/SA02636SE): Installation of Garmin GPS 175 Navigation System and GNX 375 Navigation System with ADS-B In/Out Transponder.. Garmin International Inc. - [STC SA02019SE-D](https://openairdocs.org/stc/SA02019SE-D): Installation of Garmin Model GTN 625/635/650; 725/750 Navigation System. Garmin International Inc. - [STC SA01147WI](https://openairdocs.org/stc/SA01147WI): Installation of Concorde FLA or VRSLA series batteries in Piper Light Airplanes.. Concorde Battery Corporation - [STC SA02738CH](https://openairdocs.org/stc/SA02738CH): Installation of L-3 Communications Avionics Systems. Acron Aviation Inc. - [STC SA04046CH PAGE 1](https://openairdocs.org/stc/SA04046CH%20PAGE%201): Installation of L-3 GENESIS (TM) Electronic Standby Instrument System (ESI-500/MAG-500). Acron Aviation Inc. - [STC SA04378CH](https://openairdocs.org/stc/SA04378CH): Installation of an engine modified per STC SE04349CH. SureFly Partners Ltd. - [STC SA02386AK](https://openairdocs.org/stc/SA02386AK): Replacement of existing landing and/or taxi light reflector and bulbs with Light Emitting Diode (LED) lighting systems. AeroLED's Holding LLC - [STC SA02658SE](https://openairdocs.org/stc/SA02658SE): Installation of Garmin GI 275 Multi-Function Display System. Garmin International Inc. - [STC SA4827NM](https://openairdocs.org/stc/SA4827NM): Installation of exhaust system. Aerospace Welding Minneapolis Inc. - [STC SA02019WI](https://openairdocs.org/stc/SA02019WI): Installation of the Trig Avionics TX56, TX56A, TX57, or TX57A VHF Nav-Com Radio.. Peregrine - [STC SA01435LA](https://openairdocs.org/stc/SA01435LA): Installation of engines modified with Firewall Forward Technologies LLC modified camshaft. Centri-Lube Technologies LLC - [STC SA04192NY](https://openairdocs.org/stc/SA04192NY): KFD 900 Primary Flight Display System Additional Functions. Honeywell International Inc - [STC SA00756DE](https://openairdocs.org/stc/SA00756DE): Installation of Automatic Dependent Surveillance Broadcast (ADS-B) Out Equipment using a Trig Avionics TT22 Transponder and an approved Global Positioning System (GPS) Position Sensor. Peregrine - [STC SA11137SC](https://openairdocs.org/stc/SA11137SC): Installation of Plane-Power ALT-FLX alternator. Hartzell Engine Technologies, LLC - [STC SA02010WI](https://openairdocs.org/stc/SA02010WI): Installation of the Mid-Continent Instruments & Avionics MD23 FLEX Custom Function Display (CFD). Mid-Continent Instruments and Avionics - [STC SA35GL](https://openairdocs.org/stc/SA35GL): Install Cleveland Acft Products wheel and brake conversion kit, P/N 199-51.. Kaman Corporation Aircraft Wheel and Brake LLC - [STC SA02203AK](https://openairdocs.org/stc/SA02203AK): Installation of FlightLogic Synthetic Vision Electronic Flight Information System (EFIS-SV).. Genesys Aerosystems Inc. - [STC SA02444AK](https://openairdocs.org/stc/SA02444AK): Approval of the L-3 Communications NGT 9000/9000R ADS-B system installed. ADS-B Technologies LLC - [STC SA04452NY](https://openairdocs.org/stc/SA04452NY): Installation of MT-Propeller Entwicklung GmbH model MTV-14-B-C-F/CF(L)188-30g 4-blade, constant speed, full feathering propellers and spinners. MT- Propeller Entwicklung GmbH - [STC SA01818WI](https://openairdocs.org/stc/SA01818WI): Installation of Garmin G5 Electronic Flight Instrument. Garmin International Inc. - [STC SA09856AC](https://openairdocs.org/stc/SA09856AC): Installation of BendixKing Aerowave 100 In-flight Data Link System for non-essential, non-required aircraft Cabin Systems & Equipments. Honeywell International Inc (Bendix King) - [STC SA09902AC](https://openairdocs.org/stc/SA09902AC): Installation of BendixKing KFD 900 Flight Display System. Honeywell International Inc. (Bendix King) - [STC SA11174SC PAGE 1](https://openairdocs.org/stc/SA11174SC%20PAGE%201): Installation of BendixKing by Honeywell KSN 770 and KSN 765 WAAS LPV approach capable nav/comm systems. Honeywell International Inc (Bendix King) - [STC SA02265SE](https://openairdocs.org/stc/SA02265SE): Installation of a camera housing. Airborne Sensor LLC - [STC SA02430SE](https://openairdocs.org/stc/SA02430SE): Fabrication and installation of a camera housing. Airborne Sensor LLC - [STC SA10822SC](https://openairdocs.org/stc/SA10822SC): Installation of EFD1000 Primary Flight Display. Aspen Avionics Inc. - [STC SA00401BO](https://openairdocs.org/stc/SA00401BO): Installation of a SkyTrax100B UAT receiver. Avidyne Corporation - [STC SA04181NY](https://openairdocs.org/stc/SA04181NY): Installation of the KFC 230 Aerocruze Automatic Flight Control System. Honeywell International Inc - [STC SA04182NY](https://openairdocs.org/stc/SA04182NY): Installation of BendixKing KA 310 Autopilot Adapter. Honeywell International Inc - [STC SA4472NM](https://openairdocs.org/stc/SA4472NM): Installation of inflatable door seal.. The Flight Shop Inc - [STC SA09764DS](https://openairdocs.org/stc/SA09764DS): Installation of an S-TEC 01326 Digital Flight Control System (DFCS). S-TEC Corporation - [STC SA10236SC](https://openairdocs.org/stc/SA10236SC): Installation of a GDC 31 Roll Steering Converter. DAC International Inc - [STC SA02268CH](https://openairdocs.org/stc/SA02268CH): Installation of Airwolf Filter Corp. Air Oil Separator. Airwolf Filter Corporation - [STC SA1777CE-D](https://openairdocs.org/stc/SA1777CE-D): Installation of KAP 150 two-axis or KFC 150 two-axis flight control system with optional third (yaw) axis and optional KAP 297B Vertical Speed and Altitude Selector.. Honeywell International Inc - [STC SA1184CE](https://openairdocs.org/stc/SA1184CE): Installation of King KFC 200 2 axis(3 optional) Flight Control System with King KCS 55 (or -55A) compass and a King KI 255 (or -256) Flight Command Indicator or a KG 258 Attitude Horizon Gyro with a KC 292 Mode Controller.. Honeywell International Inc - [STC SA1530CE-D](https://openairdocs.org/stc/SA1530CE-D): Installation of King KAS 297 altitude selector option. Honeywell International Inc - [STC SA01714WI](https://openairdocs.org/stc/SA01714WI): Installation of a Garmin transponders: (a) GTX 330/330D/33/33D with ADS-B Out functionality; (b) GTX 335/335R/345/345R with ADS-B Out and In functionality; or (c) GTX 335R/345R with ADS-B Out functionality in select airplanes installed with G950/G1000 systems.. Garmin International Inc - [STC SA03286CH](https://openairdocs.org/stc/SA03286CH): Install an electronic engine ignition system. Electroair Acquisition Corporation - [STC SA04032CH](https://openairdocs.org/stc/SA04032CH): Install rocker switch assemblies. Electroair Acquisition Corporation - [STC SA2207WE](https://openairdocs.org/stc/SA2207WE): Installation of electrically-driven Freon air-conditioning system. Air Comm Corporation - [STC SA00344BO PAGE 1](https://openairdocs.org/stc/SA00344BO%20PAGE%201): Installation of Parmetheus Plus LED PAR36 and PAR46 taxi and landing lights.. Whelen Aerospace Technologies - [STC SA00744DE](https://openairdocs.org/stc/SA00744DE): Installation of the Automatic Dependent Surveillance Broadcast (ADS-B) Out Equipment using a Trig Avionics TT31 Transponder and an approved position sensor. Peregrine - [STC SA00765DE](https://openairdocs.org/stc/SA00765DE): Installation of Automatic Dependent Surveillance Broadcast (ADS-B) Out functionality using the BendixKing KT74 Transponder and qualified position sensor. Peregrine - [STC SA04165NY](https://openairdocs.org/stc/SA04165NY): Installation of Latitude Technologies Skynode S200 Satcom system must be performed. Latitude Technologies Corporation All 251: https://openairdocs.org/tcds/A17WE/stcs.md --- OpenAirDocs.org is an independent research project of [Contrail Labs](https://contraillabs.com/). It is not affiliated with the FAA or the NTSB. Source documents are U.S. government works in the public domain.