# TCDS 3A10: Textron Aviation Inc. - Type: Type certificate data sheet - Status: Current - Holder: Textron Aviation Inc. - Revision: 64 - Revised: May 9, 2024 - Product: Aircraft, Small Airplane - Certification basis: Part 23, CAR 3 - Registered aircraft: 1,617, by the registry models matched to it (OpenAirDocs) - Data sheet PDF: https://openairdocs.org/files/sha256/ea/95/ea95ea69437e622fd0c2ee064af417315ffdf4fc1b3364c9320c00a24fb178fc - FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/DRSDOCID101191391220240528213712.0001 - Page: https://openairdocs.org/tcds/3A10 ## Models (23) As the data sheet lists them. - 310I - 310L - T310Q - 310P - T310R - T310P - 310A - 310R - E310J - 310Q - 310B - 310D - 310 - 310K - E310H - 310G - 310C - 310F - 310J - 310N - 310E - 310J-1 - 310H ## 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 17 Rev. No. 64 61 50 61 61 61 50 61 61 58 61 61 61 50 61 61 61 Page No. 18 19 20 21 22 23 24 25 26 27 28 29 30 31 32 33 34 Rev. No. 61 61 62 61 61 61 61 50 61 61 61 61 61 61 61 61 61 Page No. 35 36 37 38 39 40 41 42 43 44 Rev. No. 61 64 61 61 61 61 61 61 63 63 DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION 3A10 Revision 64 Textron Aviation 310 310J 310A (USAF U-3A) 310J-1 310B E310J 310C 310 K 310D 310L 310E (USAF U-3B) 310N 310F 310P 310G T310P 310H 310Q E310H T310Q 310I 310R T310R May 9, 2024 TYPE CERTIFICATE DATA SHEET NO. 3A10 This data sheet which is part of Type Certificate No. 3A10 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 Textron Aviation Inc. One Cessna Boulevard Wichita, KS 67215 Type Certificate Holder Record Cessna Aircraft Company transferred to Textron Aviation Inc. on July 29, 2015 I. Model 310 (Normal Categor y), Approved March 22, 1954 Engines 2 Continental O-470-B or O-470-M (installed per Cessna Dwg. 0850000, 0951560, 0851000 and 0851755) *Fuel Grade 100 or 100LL aviation gasoline *Engine Limits For all operations, 2600 r.p.m. (240 hp.) Propeller and 1. 2 full-feathe ring propeller installations Propeller Limits a. Hartzell hub HC82XF or HC-A2XF-2 with 68 lbs. ea. (-25) 8433 blades Diameter: not over 84 in., not under 78 in. Pitch settings at 30 in. sta.: low 12.5°, high 22.0°, feathered 82.0° b. Hydraulic governor, Woodward 210105, 210155, 4 lbs. ea. (-17) 210280, 210444, A210438, 210290 or C210355, McCauley DCFU290D1/T2, DCFU290D2/T2 c. Propeller spinner, Hartzell C- 888 dome with 4 lbs. ea. (-23) C-807-1 bulkhead or Cessna 0752006 dome with 0850300 bulkhead or Cessna 0850311 dome with 0850300 bulkhead or Cessna 0850313 dome with 0850300 bulkhead 3A10 2 Rev. 64 I. Model 310 (cont’d) *Airspeed Limits Maneuvering 159 m.p.h. (138 knots) (TIAS) Maximum structural cruising 200 m.p.h. (173 knots) Never exceed 246 m.p.h. (214 knots) Flaps extended 130 m.p.h. (113 knots) Landing gear extended 130 m.p.h. (113 knots) *C.G. Range (Landing (+36. 0) to (+41.5) at 4600 lbs. Gear Extended) (+33.9) to (+42.1) at 4240 lbs. (+32.0) to (+42.1) at 3900 lbs. or less Straight line variation between points given Empty Wt. C.G. Range None *Maximum Weight 4600 lbs. No. of Seats 5 (Std.) (2 at +37, 3 at +71). See Manufacturer's Weight and Balance data sheet for optional seating arrangements. Maximum Baggage 200 lbs. (+96) (See NOTE 2G for placard). Anti-Icing Fluid Capacity 4-1/2 qt. (7 lbs. at +47) Fuel Capacity 102 gal. (2 wing tip tanks, 51 gal. each at +35) (See NOTE 1 for data on system fuel) Oil Capacity 24 qt. (12 qt. in each engine at (0), 6 qt. unusable per engine) (See NOTE 1 for data on system oil) Control Surface Wing flaps Down 45° Movements Main surfaces Aileron Up 20° Down 20° Elevator Up 25° Down 15° Rudder Right 25° Left 25° Tabs (main surface in neutral) Aileron Up 20° Down 20° Elevator Up 20° Down 28° Rudder Right 20° Left 26° Serial Nos. Eligible 35000 through 35546. Delegation Option Manufacturer No. CE-1 authorized to issue airworthiness certificates for S/N 35216 through 35546 and approve repairs and alterations of airplanes S/N 35000 through 35546 under delegation option provisions of Part 21 of the Federal Aviation Regulations (FAR). II. Model 310A (USAF U-3A) (Normal Category), Approved April 9, 1957 Engines 2 Continental O-470-M *Fuel Grade 100 or 100LL aviation gasoline *Engine Limits For all operations, 2600 r.p.m. (240 hp.) Rev. 64 3 3A10 II. Model 310A (cont’d) Propeller and 1. 2 full-feathe ring propeller installations Propeller Limits a. Hartzell hub HC82XF-2 or HC-A2XF-2 with 68 lbs. ea. (-25) 8433 blades Diameter: not over 84 in., not under 78 in. Pitch settings at 30 in. sta.: low 12.5°, high 22.0°, feathered 82.0° b. Hydraulic governor, Woodward 210105, 210155, 4 lbs. ea. (-17) 210280, 210444, A210438, 210290 or C210355, McCauley DCFU290D1/T2, DCFU290D2/T2 c. Propeller spinner, Hartzell C-888 dome with 4 lbs. ea. (-23) C-807-1 bulkhead or Cessna 0752006 dome with 0850300 bulkhead or Cessna 0850311 dome with 0850300 bulkhead or Cessna 0850313 dome with 0850300 bulkhead *Airspeed Limits Maneuvering 164 m.p.h. (143 knots) (TIAS) Maximum structural cruising 200 m.p.h. (173 knots) Never exceed 248 m.p.h. (215 knots) Flaps extended 140 m.p.h. (122 knots) Landing gear extended 140 m.p.h. (122 knots) *C.G. Range (Landing (+37. 3) to (+42.1) at 4830 lbs. Gear Extended) (+32.0) to (+42.1) at 3900 lbs. or less Straight line variation between points given Empty Wt. C.G. Range None *Maximum Weight Landing 4600 lbs., takeoff 4830 lbs. No. of Seats 5 (Std.) (2 at +37, 3 at +71). See Manufacturer's Weight and Balance data sheet for optional seating arrangements. Maximum Baggage 200 lbs. (+96) (See NOTE 2G for placard). Anti-Icing Fluid Capacity 4-1/2 qt. (7 lbs.) (+47) Fuel Capacity 102 gal. (2 wing tip tanks, 51 gal. each at +35.0) (See NOTE 1 for data on unusable fuel) Oil Capacity 24 qt. (12 qt. in each engine at (0); 6 qt. unusable per engine) (See NOTE 1 for data on undrainable oil) Control Surface Wing flaps Down 45° Movements Main surfaces Aileron Up 20° Down 20° Elevator Up 25° Down 15° Rudder Right 25° Left 25° Tabs (main surface in neutral) Aileron Up 20° Down 20° Elevator Up 20° Down 28° Rudder Right 20° Left 26° Serial Nos. Eligible 38001 through 38161. Production Certificate No. 4 effective. Prior to civil certification U-3A airplanes must be modified in accordance with Cessna Dwg. 0800203 or Service Kit SK310-85, which may be obtained from the manufacturer. An Federal Aviation Agency (FAA) representative upon determination of compliance with the above-mentioned modification drawing may issue an airworthiness certificate. 3A10 4 Rev. 64 III. Model 310B (Normal Category), Approved May 23, 1957 Engines 2 Continental O-470-M *Fuel Grade 100 or 100LL aviation gasoline *Engine Limits For all operations, 2600 r.p.m. (240 hp.) Propeller and 1. 2 full-featheri ng propeller installations Propeller Limits a. Hartzell hub HC82XF-2 or HC-A2XF-2 with 68 lbs. ea. (-25) 8433 blades Diameter: not over 84 in., not under 78 in. Pitch settings at 30 in. sta.: low 12.5°, high 22.0°, feathered 82.0° b. Hydraulic governor, Woodward 210105, 210155, 4 lbs. ea. (-17) 210280, 210444, A210438, 210290 or C210355, McCauley DCFU290D1/T2, DCFU290D2/T2 c. Propeller spinner, Hartzell C- 888 dome with 4 lbs. ea. (-23) C-807-1 bulkhead or Cessna 0752006 dome with 0850300 bulkhead or Cessna 0850311 dome with 0850300 bulkhead or Cessna 0850313 dome with 0850300 bulkhead *Airspeed Limits Maneuvering 164 m.p.h. (143 knots) (TIAS) Maximum structural cruising 200 m.p.h. (173 knots) Never exceed 248 m.p.h. (215 knots) Flaps extended 140 m.p.h. (122 knots) Landing gear extended 140 m.p.h. (122 knots) *C.G. Range (Landing (+36. 6) to (+42.1) at 4700 lbs. Gear Extended) (+32.0) to (+42.1) at 3900 lbs. or less Straight line variation between points given Empty Wt. C.G. Range None *Maximum Weight Landing 4600 lbs., takeoff 4700 lbs. No. of Seats 5 (Std.) (2 at +37, 3 at +71). See Manufacturer's Weight and Balance data sheet for optional seating arrangements. Maximum Baggage 200 lbs. (+96) (See NOTE 2G for placard). Anti-Icing Fluid Capacity 4-1/2 qt. (7 lbs.) (+47) Fuel Capacity 102 gal. (2 wing tip tanks, 51 gal. each at +35.0) (See NOTE 1 for data on unusable fuel) Oil Capacity 24 qt. (12 qt. in each engine at (0), 6 qt. unusable per engine) (See NOTE 1 for data on undrainable oil) Control Surface Wing flaps Down 45° Movements Main surfaces Aileron Up 20° Down 20° Elevator Up 25° Down 15° Rudder Right 25° Left 25° Tabs (main surface in neutral) Aileron Up 20° Down 20° Elevator Up 20° Down 28° Rudder Right 20° Left 26° Rev. 64 5 3A10 III. Model 310B (cont’d) Serial Nos. Eligible 607, 35547, 35548, 35549, 35551 through 35771. Production Certificate No. 4 effective. IV. Model 310C (Normal Category ), Approved October 22, 1958 Engines 2 Continental IO-470-D *Fuel Grade 100 or 100LL aviation gasoline *Engine Limits For all operations, 2625 r.p.m. (260 hp.) Propeller and 1. 2 full-feathering 2-bladed propeller installations Propeller Limits a. Hartzell hub HC82XF-2 or HC-A2XF-2 with 68 lbs. ea. (-25) 8433 blades Diameter: not over 84 in., not under 78 in. Pitch settings at 30 in. sta.: low 13.5°, high 22.0°, feathered 82.0° b. Hydraulic governor, Woodward 210105, 210155, 4 lbs. ea. (-17) 210280, 210444, A210438, 210290 or C210355, McCauley DCFU290D1/T2, DCFU290D2/T2 c. Propeller spinner, Hartzell C- 888 dome with 4 lbs. ea. (-23) C-807-1 bulkhead or Cessna 0752006 dome with 0850300 bulkhead or Cessna 0850311 dome with 0850300 bulkhead or Cessna 0850313 dome with 0850300 bulkhead 2. 2 full feathering propeller installations a. McCauley hub D2AF36C48 with 90MF-10 blades 68 lbs. ea. (-25) Diameter: not over 80 in., not under 78 in. Pitch settings at 36 in. sta.: low 11°, feathered 77° b. Hydraulic governor, Woodward 210105, 210155, 4 lbs. ea. (-17) 210280, 210444, A210438, 210290 or C210355, McCauley DCFU290D1/T2, DCFU290D2/T2 c. Propeller spinner, McCauley Model D2840 4 lbs. ea. (-23) with D2878 bulkhead or Cessna 0850258 spinner with Cessna 0850257 bulkhead *Airspeed Limits Maneuvering 164 m.p.h. (143 knots) (TIAS) Maximum structural cruising 210 m.p.h. (183 knots) Never exceed 248 m.p.h. (215 knots) Flaps extended 140 m.p.h. (122 knots) Landing gear extended 140 m.p.h. (122 knots) *C.G. Range (Landing (+37. 3) to (+42.1) at 4830 lbs. Gear Extended) (+32.0) to (+42.1) at 3900 lbs. or less Straight line variation between points given Empty Wt. C.G. Range None *Maximum Weight Landing 4600 lbs., takeoff 4830 lbs. 3A10 6 Rev. 64 IV. Model 310C (cont’d) No. of Seats 5 (Std.) (2 at +37, 3 at +71). See Manufacturer's Weight and Balance data sheet for optional seating arrangements. Maximum Baggage 200 lb. (+96) (See NOTE 2G for placard). Anti-Icing Fluid Capacity 4-1/2 qt. (7 lbs.) (+47) Fuel Capacity 102 gal. (2 wing tip tanks, 51 gal. each at +35.0) (See NOTE 1 for data on unusable fuel) Oil Capacity 24 qt. (12 qt. in each engine at (-3.5), 6 qt. unusable per engine) (See NOTE 1 for data on undrainable oil) Control Surface Wing flaps Down 45° Movements Main surfaces Aileron Up 20° Down 20° Elevator Up 25° Down 15° Rudder Right 25° Left 25° Tabs (main surface in neutral) Aileron Up 20° Down 20° Elevator Up 10° Down 26° Rudder Right 0° Left 26° Serial Nos. Eligible 35550, 35772 through 35999, 39001 through 39031. Production Certificate No. 4 effective. V. Model 310D (Normal Category), Approved July 8, 1959 Engines 2 Continental IO-470-D *Fuel Grade 100 or 100LL aviation gasoline *Engine Limits For all operations, 2625 r.p.m. (260 hp.) Propeller and 1. 2 full-feathe ring propeller installations Propeller Limits a. Hartzell hub HC82XF-2 or HC-A2XF-2 with 68 lbs. ea. (-25) 8433 blades Diameter: not over 84 in., not under 78 in. Pitch settings at 30 in. sta.: low 13.5°, high 22.0°, feathered 82.0° b. Hydraulic governor, Woodward 210105, 210155, 4 lbs. ea. (-17) 210280, 210444, A210438, 210290 or C210355, McCauley DCFU290D1/T2, DCFU290D2/T2 c. Propeller spinner, Hartzell C- 888 dome with 4 lbs. ea. (-23) C-807-1 bulkhead or Cessna 0752006 dome with 0850300 bulkhead or Cessna 0850311 dome with 0850300 bulkhead or Cessna 0850313 dome with 0850300 bulkhead Rev. 64 7 3A10 V. Model 310D (cont’d) Propeller and 2. 2 full-feat hering propeller installations Propeller Limits (cont’d) a. McCauley hub D2AF 36C48 with 90MF-10 blades 68 lbs. ea. (-25) Diameter: not over 80 in., not under 78 in. Pitch settings at 36 in. sta.: low 11°, feathered 77° b. Hydraulic governor, Woodward 210105, 210155, 4 lbs. ea. (-17) 210280, 210444, A210438, 210290 or G210355 McCauley DCFU290D1/T2, DCFU290D2/T2 c. Propeller spinner, McCauley Model D2840 4 lbs. ea. (-23) with D2878 bulkhead or Cessna 0850258 spinner with Cessna 0850257 bulkhead *Airspeed Limits Maneuvering 164 m.p.h. (143 knots) (TIAS) Maximum structural cruising 210 m.p.h. (183 knots) Never exceed 248 m.p.h. (215 knots) Flaps extended 140 m.p.h. (122 knots) Landing gear extended 140 m.p.h. (122 knots) *C.G. Range (Landing (+37. 3) to (+42.1) at 4830 lbs. Gear Extended) (+32.0) to (+42.1) at 4060 lbs. or less Straight line variation between points given Empty Wt. C.G. Range None Maximum Weight Landing 4600 lbs., takeoff 4830 lbs. No. of Seats 5 (Std.) (2 at +37, 3 at +71). See Manufacturer's Weight and Balance data sheet for optional seating arrangements. Maximum Baggage 200 lbs. (+96) (See NOTE 2G for placard). Anti-Icing Fluid Capacity 4-1/2 qt. (7 lbs.) (+47) Fuel Capacity 102 gal. (2 wing tip tanks, 51 gal. each at +35.0) (See NOTE 1 for data on unusable fuel) Oil Capacity 24 qt. (12 qt. in each engine at (-3.5), unusable 6 qt. per engine) (See NOTE 1 for data on undrainable oil) Control Surface Wing flaps Down 45° Movements Main surfaces Aileron Up 20° Down 20° Elevator Up 25° Down 15° Rudder Right 25° Left 25° (Parallel to W.L.) Tabs (main surface in neutral) Aileron Up 20° Down 20° Elevator Up 10° Down 26° Rudder Right 17° Left 22° (Parallel to W.L.) Serial Nos. Eligible 39032 through 39264. Production Certificate No. 4 effective. Prior to original certification of S/N 39265 through 39299, an FAA representative must perform a detailed inspection for workmanship, materials and conformity with the approved technical data and a check of the flight characteristics. 3A10 8 Rev. 64 VI. Model 310E (USAF U-3B) (Normal Category), Approved September 21, 1959 Engines 2 Continental IO-470-D *Fuel Grade 100 or 100LL aviation gasoline *Engine Limits For all operations, 2625 r.p.m. (260 hp.) Propeller and 1. 2 full-feathe ring propeller installations Propeller Limits a. Hartzell hub HC82XF-2 or HC-A2XF-2 with 68 lbs. ea. (-25) 8433 blades Diameter: not over 84 in., not under 78 in. Pitch settings at 30 in. sta.: low 13.5°, high 22.0°, feathered 82.0° b. Hydraulic governor, Woodward 210105, 210155, 4 lbs. ea. (-17) 210280, 210444, A210438, 210290 or C210355 McCauley DCFU290D1/T2, DCFU290D2/T2 c. Propeller spinner, Hartzell C- 888 dome with 4 lbs. ea. (-23) C-807-1 bulkhead or Cessna 0752006 dome with 0850300 bulkhead or Cessna 0850311 dome with 0850300 bulkhead or Cessna 0850313 dome with 0850300 bulkhead 2. 2 full-feathering propeller installations a. McCauley hub D2AF36C48 with 90MF-10 blades 68 lbs. ea. (-25) Diameter: not over 80 in., not under 78 in. Pitch settings at 36 in. sta.: low 11°, feathered 77° b. Hydraulic governor, Woodward 210105, 210155, 4 lbs. ea. (-17) 210280, 210444, A210438, 210290 or C210355 McCauley DCFU290D1/T2, DCFU290D2/T2 c. Propeller spinner, McCauley Model D2840 4 lbs. ea. (-23) with D2878 bulkhead or Cessna 0850258 spinner with Cessna 0850257 bulkhead *Airspeed Limits Maneuvering 167 m.p.h. (145 knots) (TIAS) Maximum structural cruising 210 m.p.h. (183 knots) Never exceed 252 m.p.h. (218 knots) Flaps extended 140 m.p.h. (122 knots) Landing gear extended 140 m.p.h. (122 knots) *C.G. Range (Landing (+38. 3) to (+41.6) at 4990 lbs. Gear Extended) (+35.6) to (+42.1) at 4600 lbs. (+32.0) to (+42.1) at 4060 lbs. or less Straight line variation between points given Empty Wt. C.G. Range None *Maximum Weight Landing 4750 lbs., takeoff 4990 lbs. No. of Seats 5 (Std.) (2 at +37, 3 at +71). See Manufacturer's Weight and Balance data sheet for optional seating arrangements. Maximum Baggage 200 lbs. (+96) (See NOTE 2G for placard). Anti-Icing Fluid Capacity 4-1/2 qt. (7 lbs.) (+47) Rev. 64 9 3A10 VI. Model 310E (cont’d) Fuel Capacity 102 gal. (2 wing tip tanks, 51 gal. each at +35.0) (See NOTE 1 for data on unusable fuel) Oil Capacity 24 qt. (12 qt. in each engine at (-3.5), 6 qt. unusable per engine) (See NOTE 1 for data on undrainable oil) Control Surface Wing flaps Down 45° Movements Main surfaces Aileron Up 20° Down 20° Elevator Up 25° Down 15° Rudder Right 25° Left 25° (Parallel to W.L.) Tabs (main surface in neutral) Aileron Up 20° Down 20° Elevator Up 10° Down 26° Rudder Right 17° Left 22° (Parallel to W.L.) Serial Nos. Eligible 35912A, 310M0001 through 310M0036. Production Certificate No. 4 effective. Prior to original certification U-3B airplanes must be modified in accordance with Cessna Dwg. 0800203 or Service Kit SK310-85, which may be obtained from the manufacturer. An FAA representative upon determination of compliance with the above-mentioned modification drawing may issue an airworthiness certificate. VII. Model 310F (Normal Category), Approved July 25, 1960 Engines 2 Continental IO-470-D *Fuel Grade 100 or 100LL aviation gasoline *Engine Limits For all operations, 2625 r.p.m. (260 hp.) Propeller and 1. 2 full-feathe ring propeller installations Propeller Limits a. Hartzell hub HC82XF-2 or HC-A2XF-2 with 68 lbs. ea. (-25) 8433 blades Diameter: not over 84 in., not under 78 in. Pitch settings at 30 in. sta.: low 13.5°, high 22.0°, feathered 82.0° b. Hydraulic governor, Woodward 210105, 210155, 4 lbs. ea. (-17) 210280, 210444, A210438, 210290, or C210355 McCauley DCFU290D1/T2, DCFU290D2/T2 c. Propeller spinner, Hartzell C888 dome with 4 lbs. ea. (-23) C-807-1 bulkhead or Cessna 0752006 dome with 0850300 bulkhead or Cessna 0850311 dome with 0850300 bulkhead or Cessna 0850313 dome with 0850300 bulkhead 2. 2 full-feathering propeller installations a. McCauley hub D2AF36C48 with 90MF-10 blades 68 lbs. ea. (-25) Diameter: not over 80 in., not under 78 in. Pitch settings at 36 in. sta.: low 11°, feathered 77° 3A10 10 Rev. 64 VII. Model 310F (cont’d) Propeller and b. Hydraulic governor, Woodward 210105, 210155, 4 lbs. ea. (-17) Propeller Limits (cont’d) 210280, 210444, A210438, 210290 or C210355, McCauley DCFU290D1/T2, DCFU290D2/T2 c. Propeller spinner, McCauley Model D2840 4 lbs. ea. (-23) with D2878 bulkhead or Cessna 0850258 spinner with Cessna 0850257 bulkhead *Airspeed Limits Maneuvering 164 m.p.h. (143 knots) (TIAS) Maximum structural cruising 210 m.p.h. (183 knots) Never exceed 248 m.p.h. (215 knots) Flaps extended 140 m.p.h. (122 knots) Landing gear extended 140 m.p.h. (122 knots) *C.G. Range (Landing (+37. 3) to (+42.1) at 4830 lbs. Gear Extended) (+32.0) to (+42.1) at 4060 lbs. or less Straight line variation between points given. Empty Wt. C.G. Range None *Maximum Weight Landing 4600 lbs., takeoff 4830 lbs. No. of Seats 5 (Std.) (2 at +37, 3 at +71). See Manufacturer's Weight and Balance data sheet for optional seating arrangements. Maximum Baggage 200 lbs. (+96) (See NOTE 2G for placards) Anti-Icing Fluid Capacity 4-1/2 qt. (7 lbs.) (+47) Fuel Capacity 102 gal. (2 wing tip tanks, 51 gal. each at +35.0) (See NOTE 1 for data on unusable fuel) Oil Capacity 24 qt. (12 qt. in each engine at (-3.5), 6 qt. unusable per engine) (See NOTE 1 for data on undrainable oil) Control Surface Wing flaps Down 45° Movements Main surfaces Aileron Up 20° Down 20° Elevator Up 25° Down 15° Rudder Right 25° Left 25° (Parallel to W.L.) Tabs (main surface in neutral) Aileron Up 20° Down 20° Elevator Up 10° Down 26° Rudder Right 17° Left 22° (Parallel to W.L.) Serial Nos. Eligible 310-0001 through 310-0016, 310-0018 through 310-0156. Production Certificate No. 312 effective. Prio r to original certification of each aircraft, an FAA representative must perform a detailed inspection for workmanship, materials and conformity with the approved technical data and a check of the flight characteristics. Rev. 64 11 3A10 VIII. Model 310G (Normal Category), Approved October 2, 1961 Engines 2 Continental IO-470-D *Fuel Grade 100 or 100LL aviation gasoline *Engine Limits For all operations, 2625 r.p.m. (260 hp.) Propeller and 1. 2 full-feathe ring propeller installations Propeller Limits a. Hartzell hub HC82XF-2 or HC-A2XF-2 with 68 lbs. ea. (-25) 8433 blades Diameter: not over 84 in., not under 78 in. Pitch settings at 30 in. sta.: low 13.5°, high 22.0°, feathered 82.0° b. Hydraulic governor, Woodward 210105, 210155, 4 lbs. ea. (-17) 210280, 210444, A210438, 210290 or C210355, McCauley DCFU290D1/T2, DCFU290D2/T2 c. Propeller spinner, Hartzell C- 888 dome with 4 lbs. ea. (-23) C-807-1 bulkhead or Cessna 0752006 dome with 0850300 bulkhead or Cessna 0850311 dome with 0850300 bulkhead or Cessna 0850313 dome with 0850300 bulkhead 2. 2 full-feathering propeller installations a. McCauley hub D2AF36C48 with 90MF-10 blades 68 lbs. ea. (-25) Diameter: not over 80 in., not under 78 in. Pitch settings at 36 in. sta.: low 11°, feathered 77° b. Hydraulic governor, Woodward 210105, 210155, 4 lbs. ea. (-17) 210280, 210444, A210438, 210290 or C210355, McCauley DCFU290D1/T2, DCFU290D2/T2 c. Propeller spinner, McCauley M odel D2840 with 4 lbs. ea. (-23) D2878 bulkhead or Cessna 0850 spinner with Cessna 0850257 bulkhead *Airspeed Limits Maneuvering 167 m.p.h. (145 knots) (TIAS) Maximum structural cruising 210 m.p.h. (183 knots) Never exceed 252 m.p.h. (218 knots) Flaps extended 140 m.p.h. (122 knots) Landing gear extended 140 m.p.h. (122 knots) *C.G. Range (Landing (+38. 3) to (+41.6) at 4990 lbs. Gear Extended) (+35.6) to (+42.1) at 4600 lbs. (+32.0) to (+42.1) at 4060 lbs. or less Straight line variation between points given Empty Wt. C.G. Range None *Maximum Weight Landing 4750 lbs., takeoff 4990 lbs. No. of Seats 5 (Std.) (2 at +37, 3 at +71). See Manufacturer's Weight and Balance data sheet for optional seating arrangements. Maximum Baggage 200 lbs. (+96) (See NOTE 2G for placard) Anti-Icing Fluid Capacity 4-1/2 qt. (7 lb.) (+47) 3A10 12 Rev. 64 VIII. Model 310G (cont’d) Fuel Capacity 102 gal. (2 wing tip tanks, 51 gal. each at +35.0) (See NOTE 1 for data on unusable fuel) Oil Capacity 24 qt. (12 qt. in each engine at (-3.5), 6 qt. unusable per engine) (See NOTE 1 for data on undrainable oil) Control Surface Wing flaps Down 45° Movements Main surfaces Aileron Up 20° Down 20° Elevator Up 25° Down 15° Rudder Right 25° Left 25° (Parallel to W.L.) Tabs (main surface in neutral) Aileron Up 20° Down 20° Elevator Up 10° Down 26° Rudder Right 17° Left 22° (Parallel to W.L.) Serial Nos. Eligible 310G0001 through 310G0156. Production Certificate No. 312 effective. IX. Model 310H (Normal Category), Approved July 19, 1962 Engines 2 Continental IO-470-D *Fuel Grade 100 or 100LL aviation gasoline *Engine Limits For all operations, 2625 r.p.m. (260 hp.) Propeller and 1. 2 full-feathe ring propeller installations Propeller Limits a. Hartzell hub HC82XF-2 or HC-A2XF-2 68 lbs. ea. (-25) with 8433 blades Diameter: not over 84 in., not under 78 in. Pitch settings at 30 in. sta.: low 13.5°, high 22.0°, feathered 82.0° b. Hydraulic governor, Woodward 210105, 4 lbs. ea. (-17) 210155, 210280, 210444, A210438, 210290 or C210355; McCauley DCFU290D1/T2, DCFU290D2/T2 c. Propeller spinner, Hartzell C-888 dome 4 lbs. ea. (-23) with C-807-1 bulkhead or Cessna 0752006 dome with 0850300 bulkhead or Cessna 0850311 dome with 0850300 bulkhead or Cessna 0850313 dome with 0850300 bulkhead 2. 2 full-feathering propeller installations a. McCauley hub D2AF36C48 with 90MF-10 blades 68 lbs. ea. (-25) Diameter: not over 80 in., not under 78 in. Pitch settings at 36 in. sta.: low 11°, feathered 77° b. Hydraulic governor, Woodward 210105, 210155, 4 lbs. ea. (-17) 210280, 210444, A210438, 210290 or C210355, McCauley DCFU290D1/T2, DCFU290D2/T2 c. Propeller spinner, McCauley Model D2840 4 lbs. ea. (-23) with D2878 bulkhead or Cessna 0850258 spinner with Cessna 0850257 bulkhead Rev. 64 13 3A10 IX. Model 310H *Airspeed Limits Maneuvering 167 m.p.h. (145 knots) (TIAS) Maximum structural cruising 210 m.p.h. (183 knots) Never exceed 254 m.p.h. (220 knots) Flaps extended 140 m.p.h. (122 knots) Landing gear extended 140 m.p.h. (122 knots) *C.G. Range (Landing (+37. 3) to (+42.2) at 5100 lbs. Gear Extended) (+34.7) to (+42.7) at 4700 lbs. (+32.0) to (+42.7) at 4300 lbs. or less Straight line variation between points given Empty Wt. C.G. Range None *Maximum Weight Landing 5100 lbs., takeoff 5100 lbs. No. of Seats 5 (Std.) (2 at +37, 3 at +71). See Manufacturer's Weight and Balance data sheet for optional seating arrangements. Maximum Baggage 200 lbs. (+96), 80 lbs. per side on floor (+124) or 60 lbs. in upper rack (+124). (See NOTE 2G for placard) Fuel Capacity 102 gal. (2 wing tip tanks, 51 gal. each at +35.0) (See NOTE 1 for data on unusable fuel) Oil Capacity 24 qt. (12 qt. in each engine at (-3.5), 6 qt. unusable in each engine) (See NOTE 1 for data on undrainable oil) Control Surface Wing flaps Down 45° Movements Main surfaces Aileron Up 20° Down 20° Elevator Up 25° Down 15° Rudder Right 25° Left 25° (Parallel to W.L.) Tabs (main surface in neutral) Aileron Up 20° Down 20° Elevator Up 10° Down 26° Rudder Right 17° Left 22° (Parallel to W.L.) Serial Nos. Eligible 310H0001 through 310H0148. Production Certificate No. 312 effective. X. Model E310H (Normal Category), Approved January 17, 1963 Engines 2 Continental IO-470-D *Fuel Grade 100 or 100LL aviation gasoline *Engine Limits For all operations, 2625 r.p.m. (260 hp.) 3A10 14 Rev. 64 X. Model E310H (cont’d) Propeller and 1. 2 full-feathe ring propeller installations Propeller Limits a. Hartzell hub HC82XF-2 or HC-A2XF-2 with 68 lbs. ea. (-24) 8433 blades Diameter: not over 84 in., not under 78 in. Pitch settings at 30 in. sta.: low 13.5°, high 22.0°, feathered 82.0° b. Hydraulic governor, Woodward 210105, 210155, 4 lbs. ea. (-17) 210280, 210444, A210438, 210290 or C210355 McCauley DCFU290D1/T2, DCFU290D2/T2 c. Propeller spinner, Hartzell C- 888 dome with 4 lbs. ea. (-23) C-807-1 bulkhead or Cessna 0752006 dome with 0850300 bulkhead or Cessna 0850311 dome with 0850300 bulkhead or Cessna 0850313 dome with 0850300 bulkhead 2. 2 full-feathering propeller installations a. McCauley hub D2AF36C48 with 90MF-10 blades 68 lbs. ea. (-25) Diameter: not over 80 in., not under 78 in. Pitch settings at 36 in. sta.: low 11°, feathered 77° b. Hydraulic governor, Woodw ard 210105, 4 lbs. ea. (-17) 210155, 210280, 210444, A210438, 210290 or C210355; McCauley DCFU290D1/T2, DCFU290D2/T2 c. Propeller spinner, McCauley Model D2840 4 lbs. ea. (-23) with D2878 bulkhead or Cessna 0850258 spinner with Cessna 0850257 bulkhead *Airspeed Limits Maneuvering 167 m.p.h. (145 knots) (TIAS) Maximum structural cruising 210 m.p.h. (183 knots) Never exceed 254 m.p.h. (220 knots) Flaps extended 140 m.p.h. (122 knots) Landing gear extended 140 m.p.h. (122 knots) *C.G. Range (Landing (+36. 6) to (+42.3) at 4990 lbs. Gear Extended) (+34.7) to (+42.7) at 4700 lbs. (+32.0) to (+42.7) at 4300 lbs. or less Straight line variation between points given Empty Wt. C.G. Range None *Maximum Weight Landing 4990 lbs., takeoff 4990 lbs. No. of Seats 5 (Std.) (2 at +37, 3 at +71). See Manufacturer's Weight and Balance data sheet for optional seating arrangements. Maximum Baggage 200 lbs. (+96), 60 lbs. upper r ack (+124), and 80 lbs. per side on floor (+124). (See NOTE 2G for placard) Fuel Capacity 102 gal. (2 wing tip tanks, 51 gal. each at +35.0) (See NOTE 1 for data on unusable fuel) Oil Capacity 24 qt. (12 qt. in each engine at (-3.5), 6 qt. unusable per engine) (See NOTE 1 for data on undrainable oil) Rev. 64 15 3A10 X. Model E310H (cont’d) Control Surface Wing flaps Down 45° Movements Main surfaces Aileron Up 20° Down 20° Elevator Up 25° Down 15° Rudder Right 25° Left 25° (Parallel to W.L.) Tabs (main surface in neutral) Aileron Up 20° Down 20° Elevator Up 10° Down 26° Rudder Right 17° Left 22° (Parallel to W.L.) Serial Nos. Eligible All Model 310H's (Section IX), 310H0001 through 310H0148. Production Certificate No. 312 effective. XI. Model 310I (Normal Category), Approved December 20, 1963 Engines 2 Continental IO-470-U *Fuel Grade 100 or 100LL aviation gasoline *Engine Limits For all operations, 2625 r.p.m. (260 hp.) Propeller and 1. 2 full-feathe ring propeller installations Propeller Limits a. McCauley hub D2AF 34C52, blades 80GF 60 lbs. ea. (-25) Diameter: not over 80 in., not under 78 in. Pitch settings at 30 in. sta.: low 13.8°, feathered 80.5° b. Hydraulic governor, Woodward 210105, 210155, 4 lbs. ea. (-17) 210280, 210444, A210438, 210290 or C210355, McCauley DCFU290D1/T2, DCFU290D2/T2 c. Propeller spinner, Cessn a 0850326 dome 4 lbs. ea. (-23) with 0850257 bulkhead and 0850330 support *Airspeed Limits Maneuvering 170 m.p.h. (148 knots) (TIAS) Maximum structural cruising 210 m.p.h. (183 knots) Never exceed 254 m.p.h. (220 knots) Flaps extended 140 m.p.h. (122 knots) Landing gear extended 140 m.p.h. (122 knots) *C.G. Range (Landing (+37. 3) to (+42.9) at 5100 lbs. Gear Extended) (+43.6) at 4700 lbs. (+32.0) to (+43.6) at 4300 lbs. or less Straight line variation between points given Empty Wt. C.G. Range None *Maximum Weight Landing 5100 lbs., takeoff 5100 lbs. No. of Seats 5 (Std.) (2 at +37, 3 at +71). See Manufacturer's Weight and Balance data sheet for optional seating arrangements. Maximum Baggage 200 lbs. (+96), 80 lbs. per si de on floor (+124), 120 lbs. per nacelle (+63) Fuel Capacity 102 gal. (2 wing tip tanks, 51 gal. each at +35.0) (See NOTE 1 for data on system fuel) 3A10 16 Rev. 64 XI. Model 310I (cont’d) Oil Capacity 24 qt. (12 qt. in each engine at (-3.5), 6 qt. unusable per engine) (See NOTE 1 for data on system oil) Control Surface Wing flaps Down 35° Movements Main surfaces Aileron Up 20° Down 20° Elevator Up 16.5° Down 15° Rudder Right 25° Left 25° (Parallel to W.L.) Tabs (main surface in neutral) Aileron Up 20° Down 20° Elevator Up 10° Down 26° Rudder Right 17° Left 22° (Parallel to W.L.) Serial Nos. Eligible 310I0001 through 310I0200. Production Certificate No. 312 effective. XII. Model 310J (Normal Category), Approved September 3, 1964 Engines 2 Continental IO-470-U *Fuel Grade 100 or 100LL aviation gasoline *Engine Limits For all operations, 2625 r.p.m. (260 hp.) Propeller and 1. 2 full-feathe ring propeller installations Propeller Limits a. McCauley hub D2AF34C 65, blades 84JF-3 62 lbs. ea. (-28) or McCauley hub D2AF34C81, blades 84JF-3 Diameter: not over 81 in., not under 79 in. Pitch settings at 30 in. sta.: low 12.8°, feathered 82.6° b. Hydraulic governor, Woodward 210105, 210155, 4 lbs. ea. (-17) 210280, 210290, C210355, A210438, 210444; McCauley DCFU290D1/T2, DCFU290D2/T2 c. Propeller spinner, Cessna 0855030-12 dome 4 lbs. ea. (-23) with 0855030-14 and -15 bulkhead and 0855030-3 support *Airspeed Limits Maneuvering 170 m.p.h. (148 knots) (TIAS) Maximum structural cruising 210 m.p.h. (183 knots) Never exceed 254 m.p.h. (220 knots) Flaps extended 140 m.p.h. (122 knots) Landing gear extended 140 m.p.h. (122 knots) *C.G. Range (Landing (+37. 3) to (+43.1) at 5100 lbs. Gear Extended) (+43.6) at 4700 lbs. (+32.0) to (+43.6) at 4300 lbs. or less Straight line variation between points given Empty Wt. C.G. Range None *Maximum Weight Landing 5100 lbs., takeoff 5100 lbs. No. of Seats 5 (Std.) (2 at +37, 3 at +71). See Manufacturer's Weight and Balance data sheet for optional seating arrangements. Maximum Baggage 200 lbs. (+96), 80 lbs. per si de on floor (+124), 120 lbs. per nacelle (+63) Rev. 64 17 3A10 XII. Model 310J (cont’d) Fuel Capacity 102 gal. (2 wing tip tanks, 51 gal. each at +35.0) (See NOTE 1 for data on unusable fuel) Oil Capacity 24 qt. (12 qt. in each engine at (-3.5), 6 qt. unusable per engine) (See NOTE 1 for data on undrainable oil) Control Surface Wing flaps Down 35° Movements Main surfaces Aileron Up 20° Down 20° Elevator Up 16.5° Down 15° Rudder Right 25° Left 25° (Parallel to W.L.) Tabs (main surface in neutral) Aileron Up 20° Down 20° Elevator Up 10° Down 26° Rudder Right 17° Left 22° (Parallel to W.L.) Serial Nos. Eligible 310J0001 through 310J0200. Production Certificate No. 312 effective. XIII. Model 310J-1 (Utility Category), Approved November 30, 1964 Engines 2 Continental IO-470-U *Fuel Grade 100 or 100LL aviation gasoline *Engine Limits For all operations, 2625 r.p.m. (260 hp.) Propeller and 1. 2 full-feathe ring propeller installations Propeller Limits a. McCauley hub D2AF34C 71, blades 84JF-3 61 lbs. ea. (-25) Diameter: not over 81 in., not under 79 in. Pitch settings at 30 in. sta.: low 11.4°, feathered 83.0° b. Hydraulic governor, Woodward 210105, 210155, 4 lbs. ea. (-17) 210280, 210290, C210355, 210438, 210444; McCauley DCFU290D1/T2, DCFU290D2/T2 c. Propeller spinner, Cessna 0850326 dome with 4 lbs. ea. (-23) 0850257 bulkhead and 0855030 support *Airspeed Limits Maneuvering 183 m.p.h. (159 knots) (TIAS) Maximum structural cruising 210 m.p.h. (183 knots) Never exceed 272 m.p.h. (236 knots) Flaps extended 140 m.p.h. (122 knots) Landing gear extended 140 m.p.h. (122 knots) *C.G. Range (Landing (+37. 7) to (+43.1) at 5150 lbs. Gear Extended) (+43.6) at 4750 lbs. (+32.0) to (+43.6) at 4300 lbs. or less Straight line variation between points given Empty Wt. C.G. Range None *Maximum Weight Landing 5150 lbs., takeoff 5150 lbs. No. of Seats 4 (2 at +37, 2 at +68) Maximum Baggage 200 lbs. (+96) , 120 lbs. per nacelle (+63) 3A10 18 Rev. 64 XIII. Model 310J-1 (cont’d) Fuel Capacity 102 gal. (2 wing tip tanks, 51 gal. each at +35.0) (See NOTE 1 for data on unusable fuel) Oil Capacity 24 qt. (12 qt. in each engine at (-3.5), 6 qt. unusable per engine) (See NOTE 1 for data on undrainable oil) Control Surface Wing flaps Down 35° Movements Main surfaces Aileron Up 20° Down 20° Elevator Up 16.5° Down 15° Rudder Right 25° Left 25° (Parallel to W.L.) Tabs (main surface in neutral) Aileron Up 20° Down 20° Elevator Up 10° Down 26° Rudder Right 17° Left 22° (Parallel to W.L.) Serial Nos. Eligible 310J0001 through 310J0200. Production Certificate No. 312 effective. XIV. Model E310J (Normal Category), Approved March 15, 1965 Engines 2 Continental IO-470-U *Fuel Grade 100 or 100LL aviation gasoline *Engine Limits For all operations, 2625 r.p.m. (260 hp.) Propeller and 1. 2 full-feathe ring propeller installations Propeller Limits a. McCauley hub D2AF34C 65, blades 84JF-3 62 lbs. ea. (-28) or McCauley hub D2AF34C81, blades 84JF-3 Diameter: not over 81 in., not under 79 in. Pitch settings at 30 in. sta.: low 12.8°, feathered 82.6° b. Hydraulic governor, Woodward 210105, 210155, 4 lbs. ea. (-17) 210280, 210290, C210355, A210438, 210444; McCauley DCFU290D1/T2, DCFU290D2/T2 c. Propeller spinner, Cessna 0855030-12 dome 4 lbs. ea. (-23) with 0855030-14 and -15 bulkhead and 0855030-3 support *Airspeed Limits Maneuvering 170 m.p.h. (148 knots) (TIAS) Maximum structural cruising 210 m.p.h. (183 knots) Never exceed 254 m.p.h. (220 knots) Flaps extended 140 m.p.h. (122 knots) Landing gear extended 140 m.p.h. (122 knots) *C.G. Range (Landing (+36. 6) to (+43.1) at 4990 lbs. Gear Extended) (+43.6) at 4700 lbs. (+32.0) to (+43.6) at 4300 lbs. or less Straight line variation between points given Empty Wt. C.G. Range None *Maximum Weight Landing 4990 lbs., takeoff 4990 lbs. No. of Seats 5 (Std.) (2 at +37, 3 at +71). See Manufacturer's Weight and Balance data sheet for optional seating arrangements. Rev. 64 19 3A10 XIV. Model E310J (cont’d) Maximum Baggage 200 lbs. (+96), 80 lbs. per side on floor (+124) 120 lbs. per nacelle (+63) Fuel Capacity 102 gal. (2 wing tip tanks, 51 gal. each at +35.0) (See NOTE 1 for data on unusable fuel) Oil Capacity 24 qt. (12 qt. in each engine at (-3.5), 6 qt. unusable per engine). (See NOTE 1 for data on undrainable oil) Control Surface Wing flaps Down 35° Movements Main surfaces Aileron Up 20° Down 20° Elevator Up 16.5° Down 15° Rudder Right 25° Left 25° (Parallel to W.L.) Tabs (main surface in neutral) Aileron Up 20° Down 20° Elevator Up 10° Down 26° Rudder Right 17° Left 22° (Parallel to W.L.) Serial Nos. Eligible 310J0001 throug h 310J0200 (same as Section XII). Production Certificate No. 312 effective. XV. Model 310K (Normal Category), Approved October 20, 1965 Engines 2 Continental IO-470-V or IO-470-VO *Fuel Grade 100 or 100LL aviation gasoline *Engine Limits For all operations, 2625 r.p.m. (260 hp.) Propeller and 1. 2 full-feathering 2-bladed propeller installations Propeller Limits a. McCauley hub D2AF34C 81, blades 84JF-3 62 lbs. ea. (-25) Diameter: not over 81 in., not under 78 in. Pitch settings at 30 in. sta.: low 12.8°, feathered 82.5° b. Hydraulic governor, Woodw ard 210105, 4 lbs. ea. (-17) 210155, 210280, 210290, C210355, A210438, 210444; 210446, A210449; McCauley DCFU290D1/T2, DCFU290D2/T2 c. Propeller spinner, Cessna 0855030-12 dome 4 lbs. ea. (-23) with 0855030-14 and -15 bulkhead and 0855030-3 support 2. 2 full-feathering 3-bl aded propeller installations a. McCauley hub D3AF32C80, blades 82NC-4 79 lbs. ea. (-25) Diameter: not over 78 in., not under 74 in. Pitch settings at 30 in. sta.: low 12.5°, feathered 81.3° b. Hydraulic governor, Woodw ard 210105, 4 lbs. ea. (-17) 210155, 210280, 210290, C210355, A210438, 210444, 210446, A210449; McCauley DCFU290D1/T2, DCFU290D2/T2 c. Propeller spinner, 3-bladed , McCauley 4 lbs. ea. (-23) D-3651 dome with D-3652 bulkhead 3A10 20 Rev. 64 XV. Model 310K (cont’d) *Airspeed Limits Maneuvering 170 m.p.h. (148 knots) (CAS) Maximum structural cruising 210 m.p.h. (183 knots) Never exceed 257 m.p.h. (224 knots) Flaps extended 35° 140 m.p.h. (122 knots) Landing gear extended 140 m.p.h. (122 knots) *C.G. Range (Landing (+38. 0) to (+43.1) at 5200 lbs. Gear Extended) (+43.6) at 4800 lbs. (+32.0) to (+43.6) at 4300 lbs. or less Straight line variation between points given Empty Wt. C.G. Range None *Maximum Weight Landing 5200 lbs., takeoff 5200 lbs. No. of Seats 5 (Std.) (2 at +37, 3 at +71). See Manufacturer's Weight and Balance data sheet for optional seating arrangements Maximum Baggage 200 lbs. (+96), 80 lbs. per side on floor (+124) 120 lbs. per nacelle (+63) Fuel Capacity 102 gal. (2 wing tip tanks, 51 gal. each at +35.0) (See NOTE 1 for data on system fuel) Oil Capacity 24 qt. (12 qt. in each engine at (-3.5), 6 qt. unusable per engine) (See NOTE 1 for data on system oil) Control Surface Wing flaps Down 35° Movements Main surfaces Aileron Up 20° Down 20° Elevator Up 16.5° Down 15° Rudder Right 25° Left 25° (Parallel to W.L.) Tabs (main surface in neutral) Aileron Up 20° Down 20° Elevator Up 10° Down 26° Rudder Right 17° Left 22° (Parallel to W.L.) Serial Nos. Eligible 310K0001 through 310K0245. Production Certificate No. 312 effective. XVI. Model 310L (Normal Category), Approved September 20, 1966 Engines 2 Continental IO-470-V or IO-470-VO *Fuel Grade 100 or 100LL aviation gasoline *Engine Limits For all operations, 2625 r.p.m. (260 hp.) Propeller and 1. 2 full-feathe ring propeller installations Propeller Limits a. McCauley hub D2AF 34C81, blades 84JF-3 62 lbs. ea. (-25) Diameter: not over 81 in., not under 78 in. Pitch settings at 30 in. sta.: low 12.8°, feathered 82.5° b. Hydraulic governor, Woodw ard A210438, 4 lbs. ea. (-17) 210444, 210446, A210449; McCauley DCFU290D1/T2, DCFU290D2/T2 Rev. 64 21 3A10 XVI. Model 310L (cont’d) Propeller and c. Propeller spinner, Ce ssna 0855030-12 dome 4 lbs. ea. (-23) Propeller Limits (cont’d) with 0855030-14 and -15 bulkhead and 0855030-3 support 2. 2 full-feathering 3-bl aded propeller installations a. McCauley hubs D3AF32C80, blades 82NC-4 79 lbs. ea. (-25) Diameter: not over 78 in., not under 74 in. Pitch settings at 30 in. sta.: low 12.5°, feathered 81.3° b. Hydraulic governor, Woodw ard A210438, 4 lbs. ea. (-17) 210444, 210446, A210449; McCauley DCFU290D1/T2, DCFU290D2/T2 c. Propeller spinner, 3-bladed , McCauley 4 lbs. ea. (-23) D-3651 dome with D-3652 bulkhead *Airspeed Limits Maneuvering 170 m.p.h. (148 knots) (CAS) Maximum structural cruising 210 m.p.h. (183 knots) Never exceed 257 m.p.h. (224 knots) Flaps extended 35° 160 m.p.h. (139 knots) Landing gear extended 160 m.p.h. (139 knots) *C.G. Range (Landing (+38. 0) to (+43.1) at 5200 lbs. Gear Extended) (+43.6) at 4800 lbs. (+32.0) to (+43.6) at 4300 lbs. or less Straight line variation between points given Empty Wt. C.G. Range None *Maximum Weight Landing 5200 lbs., takeoff 5200 lbs. No. of Seats 5 (Std.) (2 at +37, 3 at +71). See Manufacturer's Weight and Balance data sheet for optional seating arrangements Maximum Baggage 200 lbs. (+96), 80 lbs. per si de on floor (+124), 120 lbs. per nacelle (+63) Fuel Capacity 102 gal. (2 wing tip tanks, 51 gal. each at +35.0) or 143 gal. (2 wing tip tanks , 51 gal. each at +35.0) and 2 auxiliary tanks 20.5 gal. each at +47.0) or 183 gal. (2 wing tip tanks, 51 ga l. each at +35.0, 2 auxiliary tanks, 20 gal. each at +47.0, and 2 wing locker transfer tanks, 20.0 gal. each at +49.0). (See NOTE 1 for data on system fuel) Oil Capacity 24 qt. (12 qt. in each engine at (-3.5), 6 qt. unusable per engine) (See NOTE 1 for data on system oil) Control Surface Wing flaps Down 35° Movements Main surfaces Aileron Up 20° Down 20° Elevator Up 16.5° Down 15° Rudder Right 25° Left 25° (Parallel to W.L.) Tabs (main surface in neutral) Aileron Up 20° Down 20° Elevator Up 10° Down 26° Rudder Right 17° Left 22° (Parallel to W.L.) Serial Nos. Eligible 310L0001 through 310L0207. Production Certificate No. 312 effective. 3A10 22 Rev. 64 XVII. Model 310N (Normal Catego ry), Approved August 22, 1967 Engines 2 Continental IO-470-V or IO-470-VO *Fuel Grade 100 or 100LL aviation gasoline *Engine Limits For all operations, 2625 r.p.m. (260 hp.) Propeller and 1. 2 full-feathe ring propeller installation Propeller Limits a. McCauley hub D2AF34C81, blades 84JF-3 Diameter: not over 81 in., not under 78 in. Pitch settings at 30 in. sta.: low 12.8°, feathered 82.5° b. Hydraulic governor, Woodward 210446, 210444, A210438 or A210449; McCauley DCFU290D1/T2, DCFU290D2/T2 c. Propeller spinner, Cessna 0855030-12 dome with 0855030-14 and -15 bulkhead and 0855030-3 support 2. 2 full-feathering 3-bl aded propeller installation a. McCauley hub D3AF32C80, blades 82NC-4 Diameter: not over 78 in., not under 74 in. Pitch settings at 30 in. sta.: low 12.5°, feathered 81.3° b. Hydraulic governor, Woodward 210446, 210444, A210438 or A210449; McCauley DCFU290D1/T2, DCFU290D2/T2 c. Propeller spinner, 3-blades, McCauley D-3651 dome with D-3652 bulkhead *Airspeed Limits Maneuvering 170 m.p.h. (148 knots) (CAS) Maximum structural cruising 210 m.p.h. (183 knots) Never exceed 257 m.p.h. (224 knots) Flaps extended 35° 160 m.p.h. (139 knots) Landing gear extended 160 m.p.h. (139 knots) *C.G. Range (Landing (+38. 0) to (+43.1) at 5200 lbs. Gear Extended) (+43.6) at 4800 lbs. (+32.0) to (+43.6) at 4300 lbs. or less Straight line variation between points given Empty Wt. C.G. Range None *Maximum Weight Landing 5200 lbs., takeoff 5200 lbs. No. of Seats 5 (Std.) (2 at +37, 3 at +71). See Manufacturer's Weight and Balance data sheet for optional seating arrangements. Maximum Baggage 200 lbs. (+96), 80 lbs. per side on floor (+124), 120 lbs. per nacelle (+63) Fuel Capacity 102 gal. (2 wing tip tanks, 51 gal. each at +35.0) or 143 gal. (2 wing tip tanks, 51 gal. each at +35.0 and 2 auxiliary tanks 20.5 gal. each at +47.0) or 183 gal. (2 wing tip tanks, 51 gal. each at +35.0 and 2 auxiliary tanks 20.5 gal. ea ch at +47.0, and 2 wing locker tanks, 20.0 gal. each at +49.0) (See NOTE 1 for data on system fuel) Rev. 64 23 3A10 XVII. Model 310N (cont’d) Oil Capacity 24 qt. (12 qt. in each engine at (-3.5), 6 qt. unusable per engine) (See NOTE 1 for data on system oil) Control Surface Wing flaps Down 35° Movements Main surfaces Aileron Up 20° Down 20° Elevator Up 16.5° Down 15° Rudder Right 25° Left 25° (Parallel to W.L.) Tabs (main surface in neutral) Aileron Up 20° Down 20° Elevator Up 10° Down 26° Rudder Right 17° Left 22° (Parallel to W.L.) Serial Nos. Eligible 310N0001 through 310N0198. Production Certificate No. 312 effective. XVIII. Model 310P (Normal Category), Approved August 30, 1968 Engines 2 Continental IO-470-VO *Fuel Grade 100 or 100LL aviation gasoline *Engine Limits For all operations, 2625 r.p.m. (260 hp.) Propeller and 1. 2 full-feathering 2-bladed propeller installation Propeller Limits a. McCauley hub D2AF34C71, blades 84JF-3 Diameter: not over 81 in., not under 78 in. Pitch settings at 30 in. sta.: low 12.8°, feathered 82.6° b. Hydraulic governor, Woodward 210446, 210444, A210438 or A210499; McCauley DCF290D1/T2, DCFU290D1/T2, DCFS290D1/T2, DCFUS290D2/T2, DCF290D2/T2, DCFU290D2/T2, DCFS290D2/T2, DCFUS290D2/T2, DCFS290D7/T2, DCFUS290D7/T2 or DCFUS290D13/T2 c. Propeller spinner, McCauley D3935 dome with D3923 bulkhead and 0855030-3 support 2. 2 full-feathering 3- bladed propeller installation a(1) McCauley hub 3AF32C87, blades 82NC-4. Diameter: not over 78 in., not under 74 in. Pitch settings at 30 in sta.: Low 12.5 o, feathered 81.3o or a(2) McCauley hub 3AF32C504, with 82NEA-5.5 blades. Diameter: not over 76.5 in., not under 74 in. Pitch settings at 30 in. sta.: low 13.0°, feathered 81.7° b. Hydraulic governor, Woodward 210446, 210444, A210438 or A210499; McCauley DCF290D1/T2, DCFU290D1/T2, DCFS290D1/T2, DCFUS290D2/T2, DCF290D2/T2, DCFU290D2/T2, DCFS290D2/T2, DCFUS290D2/T2, DCFS290D7/T2, DCFUS290D7/T2 or DCFUS290D13/T2 c. Propeller spinner, McCauley D3651 dome and D3925 bulkhead with 3AF32C87 hub or McCauley D7185 spinner assembly with 3AF32C504 hub 3A10 24 Rev. 64 XVIII. Model 310P (cont’d) *Airspeed Limits Maneuvering 170 m.p.h. (148 knots) (CAS) Maximum structural cruising 210 m.p.h. (183 knots) Never exceed 257 m.p.h. (224 knots) Flaps extended 35° 160 m.p.h. (139 knots) Landing gear extended 160 m.p.h. (139 knots) *C.G. Range (Landing (+38. 0) to (+43.1) at 5200 lbs. Gear Extended) (+43.6) at 4800 lbs. (+32.0) to (+43.6) at 4300 lbs. or less Straight line variation between points given Empty Wt. C.G. Range None *Maximum Weight Landing 5200 lbs., takeoff 5200 lbs. No. of Seats 5 (Std.) (2 at +37, 3 at +71). See Manufacturer's Weight and Balance data sheet for optional seating arrangements Maximum Baggage 200 lbs. (+96), 80 lbs. per side on floor (+124) 120 lbs. per nacelle (+63) Fuel Capacity 102 gal. (2 wing tip tanks, 51 gal. each at +35.0) or 143 gal. (2 wing tip tanks, 51 gal. each at +35.0 and 2 auxiliary tanks, 20.5 gal. each at +47.0) or 183 gal. (2 wing tip tanks, 51 gal. each at +35.0, 2 auxiliary tanks, 20.5 gal. each at +47.0 and 2 wing lo cker tanks, 20.5 gal. each at +49.0) (See NOTE 1 for data on system fuel) Oil Capacity 6 gal. (3 gal. in each engine at (-3.5), unusable 1.5 gal. per engine) (See NOTE 1 for data on system oil) Control Surface Wing flaps Down 35° Movements Main surfaces Aileron Up 20° Down 20° Elevator Up 16.5° Down 15° Rudder Right 25° Left 25° (Parallel to W.L.) Tabs (main surface in neutral) Aileron Up 20° Down 20° Elevator Up 10° Down 26° Rudder Right 17° Left 22° (Parallel to W.L.) Serial Nos. Eligible 310P0001 through 310P0240. Production Certificate No. 312 effective. XIX. Model T310P (Turbo-System 310P) (Nor mal Category), Approved August 30, 1968 Engines 2 Continental TSIO-520-B or TSIO-520-BB *Fuel Grade 100 or 100LL aviation gasoline Rev. 64 25 3A10 XIX. Model T310P (cont’d) *Engine Limits For all operations, 2700 r.p.m. (285 hp., 32 in. Hg MP) (Critical altitude is 16,000 ft. in standard atmosphere) Maximum Altitude Allowable MP Sea level 32.0 in. Hg 16,000 ft. 32.0 in. Hg 18,000 ft. 30.7 in. Hg 20,000 ft. 29.0 in. Hg 22,000 ft. 26.4 in. Hg 24,000 ft. 24.3 in. Hg 26,000 ft. 22.2 in. Hg 28,000 ft. 20.2 in. Hg 30,000 ft. 18.5 in. Hg 32,000 ft. 17.0 in. Hg Propeller and 1. 2 full-feathering 2-bladed propeller installations Propeller Limits a. McCauley Hub D2AF34C71 with 84JF-3 blades Diameter: not over 81 in., not under 79 in. Pitch settings at 30 in. sta.: low 13.3°, feathered 82.7° b. Hydraulic governor Woodward B210446, A210529, B210444 or C210439; McCauley DCFS290D1/T3, DCFUS290D1/T3, DCFS290D2/T3, DCFUS290D2/T3, DCFS290D7/T3, DCFUS290D7/T3 or DCFUS290D13/T3 c. Propeller spinner McCauley D3800 dome with D3818 bulkhead 2. 2 full-feathering 3-bl aded propeller installations a. McCauley hubs 3AF32C87 with 82NC-4 blades or McCauley hubs 3AF32C504 with 82NEA-4 blades Diameter: not over 78 in., not under 74 in. Pitch settings at 30 in. sta.: low 13.0°, feathered 82.6° b. Hydraulic governor Woodward B210446, A210529, B210444 or C210439; McCauley DCFS290D1/T3, DCFUS290D1/T3, DCFS290D2/T3, DCFUS290D2/T3, DCFS290D7/T3, DCFUS290D7/T3 or DCFUS290D13/T3 c. Propeller spinner McCauley D3534 dome with D3796 bulkhead *Airspeed Limits Maneuvering 170 m.p.h. (148 knots) CAS) Maximum structural cruising 210 m.p.h. (183 knots) Never exceed 257 m.p.h. (224 knots) Flaps extended 35° 160 m.p.h. (139 knots) Landing gear extended 160 m.p.h. (139 knots) *C.G. Range (Landing (+38. 0) to (+43.1) at 5400 lbs. Gear Extended) (+43.6) at 5000 lbs. (+32.0) to (+43.6) at 4500 lbs. or less Straight line variation between points given Empty Wt. C.G. Range None 3A10 26 Rev. 64 XIX. Model T310P (cont’d) *Maximum Weight Landing 5400 lbs., takeoff 5400 lbs. No. of Seats 5 (Std.) (2 at +37, 3 at +71). See Manufacturer's Weight and Balance data sheet for optional seating arrangements. Maximum Baggage 200 lbs. (+96), 80 lbs. per side on floor (+124) 120 lbs. per nacelle (+63) Fuel Capacity 102 gal. (2 wing tip tanks, 51 gal. each at +35.0) or 143 gal. (2 wing tip tanks, 51 gal. each at +35.0 and 2 auxiliary tanks, 5 gal. each at +47.0) or 183 gal. (2 wing tip tanks, 51 gal. each at +35.0, 2 auxiliary tanks 20.5 gal. ea ch at .0 and 2 wing locker tanks, 20.5 gal. each at +49.0) (See NOTE 1 for data on system fuel) Oil Capacity 6.5 gal. (3.25 ga l. in each engine at (-3.5), unusable 1.5 gal. per engine) (See NOTE 1 for data on system oil) Control Surface Wing flaps Down 35° Movements Main surfaces Aileron Up 20° Down 20° Elevator Up 16.5° Down 15° Rudder Right 29.3° Left 29.3° (Parallel to W.L.) Tabs (main surface in neutral) Aileron Up 20° Down 20° Elevator Up 10° Down 26° Rudder Right 17° Left 22° (Parallel to W.L.) Serial Nos. Eligible 310P0001 through 310P0240. Production Certificate No. 312 effective. XX. Model 310Q (Normal Category ), Approved August 20, 1969 Engines 2 Continental IO-470-VO *Fuel Grade 100 or 100LL aviation gasoline *Engine Limits For all operations, 2625 r.p.m. (260 hp.) Propeller and 1. 2 full-feathering 2-bladed propeller installations Propeller Limits a. McCauley hubs D2AF34C71, blades 84JF-3 Diameter: not over 81 in., not under 78 in. Pitch settings at 30 in. sta.: low 12.8°, feathered 82.6° b. Hydraulic governor, Woodward 210444, 210446, A210438, A210499; McCauley DCF290D1/T2, DCFU290D1/T2, DCFS290D1/T2, DCFUS290D1/T2, DCF290D2/T2, DCFU290D2/T2, DCFS290D2/T2, DCFUS290D2/T2, DCFS290D7/T2, DCFUS290D7/T2 or DCFUS290D13/T2 c. Propeller spinner, McCauley D3935 dome with D3923 bulkhead and 0855030-3 support Rev. 64 27 3A10 XX. Model 310Q (cont’d) Propeller and 2. 2 full-feathering 3-bladed propeller installations Propeller Limits a(1) McCauley hubs 3AF32C87, blades 82NC-4 (cont’d) Diameter: Not over 78 in., not under 74 in. Pitch settings at 30 in. sta.: low 12.5 o, feathered 81.3o or a(2) McCauley hubs 3AF32C504, with 82NEA-5.5 blades Diameter: not over 76.5 in., not under 74 in. Pitch settings at 30 in. sta.: low 13.0°, feathered 81.7° b. Hydraulic governor, Woodward 210444, 210446, A210438 or A210499; McCauley DCF290D1/T2, DCFU290D1/T2, DCFS290D1/T2, DCFUS290D1/T2, DCF290D2/T2, DCFU290D2/T2, DCFS290D2/T2, DCFUS290D2/T2, DCFS290D7/T2, DCFUS290D7/T2 or DCFUS290D13/T2 c. Propeller spinner, McCauley D3651 dome and D3925 bulkhead with 3AF32C87 hub or McCauley D7185 spinner assembly with 3AF32C504 hub *Airspeed Limits S/N 310Q0001 through 310Q0845 (CAS) Maneuvering 170 m.p.h. (148 knots) Maximum structural cruising 210 m.p.h. (183 knots) Never exceed 257 m.p.h. (224 knots) Flaps extended 15° 180 m.p.h. (157 knots) Flaps extended 35° 160 m.p.h. (139 knots) Landing gear extended 160 m.p.h. (139 knots) *Airspeed Limits S/N 310Q0901 through 310Q1160 Maneuvering 148 knots (170 m.p.h.) Maximum structural cruise 183 knots (210 m.p.h.) Never exceed 224 knots (257 m.p.h.) Flaps extended 15° 160 knots (184 m.p.h.) Flaps extended 35° 140 knots (161 m.p.h.) Landing gear extended 140 knots (161 m.p.h.) *C.G. Range (Landing (+37. 3) to (+43.1) at 5300 lbs. Gear Extended) (+43.6) at 4900 lbs. (+32.0) to (+43.6) at 4500 lbs. or less Straight line variation between points given Empty Wt. C.G. Range None *Maximum Weight Landing 5300 lbs. - Takeoff 5300 lbs. No. of Seats 5 (Std.) (2 at +37, 3 at +71). See Manufacturer's Weight and Balance data sheet for optional seating arrangements Maximum Baggage 200 lbs. (+96), 80 lbs. per side on floor (+124), 120 lbs. per nacelle (+63) 3A10 28 Rev. 64 XX. Model 310Q (cont’d) Fuel Capacity Tank Capacity (Gal.) Usable(Gal.) Moment Arm S/N 310Q0001 through 310Q1160 LH tip tank 51 50 +35 RH tip tank 51 50 +35 LH aux. tank (40 gal. opt) 20.5 20 +47 RH aux. tank (40 gal. opt) 20.5 20 +47 LH wing locker tank 20.5 20 +49 RH wing locker tank 20.5 20 +49 S/N 310Q0601 through 310Q1160 LH aux. tank (63 gal. opt) 32 31.5 +47 RH aux. tank (63 gal. opt) 32 31.5 +47 (See NOTE 1 for data on unusable fuel) Oil Capacity 6 gallons (3 gal. in each engine at (-3.5), unusable 1.5 gal. each engine) (See NOTE 1 for data on undrainable oil) Control Surface Wing flaps Down 35° Movements Main surfaces Aileron Up 20° Down 20° Elevator Up 16.5° Down 15° Rudder Right 25° Left 25° (Parallel to W.L.) Tabs (main surface in neutral) Aileron Up 20° Down 20° Elevator Up 10° Down 26° Rudder Right 17° Left 22° (Parallel to W.L.) Serial Nos. Eligible 310Q0001 through 310Q1160. Production Certificate No. 312 effective XXI. Model T310Q (Turbo-System 310Q) (Nor mal Category), Approved August 20, 1969 Engines 2 Continental TSIO-520-B or TSIO-520-BB *Fuel Grade 100 or 100LL aviation gasoline *Engine Limits For all operations, 2700 r.p.m. (285 hp., 32 in. Hg MP) Critical altitude is 16,000 ft. in standard atmosphere. Maximum Altitude Allowable MP Sea level 32.0 in. Hg 16,000 ft. 32.0 in. Hg 18,000 ft. 30.7 in. Hg 20,000 ft. 29.0 in. Hg 22,000 ft. 26.4 in. Hg 24,000 ft. 24.3 in. Hg 26,000 ft. 22.2 in. Hg 28,000 ft. 20.2 in. Hg 30,000 ft. 18.5 in. Hg 32,000 ft. 17.0 in. Hg Rev. 64 29 3A10 XXI. Model T310Q (cont’d) Propeller and 1. 2 full-feathering 2-bladed propeller installations Propeller Limits a. McCauley Hub D2AF34C71 with 84JF-3 blades Diameter: not over 81 in., not under 79 in. Pitch settings at 30 in. sta.: low 13.3°, feathered 82.7° b. Hydraulic governor, Woodward B210446, A210529; McCauley DCFS290D1/T3, DCFUS290D1/T3, DCFS290D2/T3, DCFUS290D2/T3, DCFS290D7/T3, DCFUS290D7/T3 or DCFUS290D13/T3 c. Propeller spinner, McCauley D3800 dome with D3818 bulkhead 2. 2 full-feathering 3-bl aded propeller installations a. McCauley hubs 3AF32C87 with 82NC-4 blades or McCauley hubs 3A F32C504 with 82NEA-4 blades Diameter: not over 78 in., not under 74 in. Pitch settings at 30 in. sta.: low 13.0°, feathered 82.6° b. Hydraulic governor Woodward A210529, B210446; McCauley DCFS290D1/T3, DCFUS290D1/T3, DCFS290D2/T3, DCFUS290D2/T3, DCFS290D7/T3, DCFUS290D7/T3 or DCFUS290D13/T3 c. Propeller spinner McCauley D3534 dome with D3796 bulkhead *Airspeed Limits S/N 310Q0001 through 310Q0845 (CAS) Maneuvering 172 m.p.h. (150 knots) Maximum structural cruising 210 m.p.h. (183 knots) Never exceed 261 m.p.h. (227 knots) Flaps extended 15° 180 m.p.h. (157 knots) Flaps extended 35° 160 m.p.h. (139 knots) Landing gear extended 160 m.p.h. (139 knots) S/N 310Q0901 through 310Q1160 Maneuvering 150 knots (172 m.p.h.) Maximum structural crui sing 183 knots (210 m.p.h.) Never exceed 227 knots (261 m.p.h.) Flaps extended 15° 160 knots (184 m.p.h.) Flaps extended 35° 140 knots (161 m.p.h.) Landing gear extended 140 knots (161 m.p.h.) *C.G. Range (Landing (+38.7) to (+43.1) at 5500 lbs. (takeoff) Gear Extended) (+38.0) to (+43.2) at 5400 lbs. (landing) (+43.6) at 5100 lbs. (+32.0) to (+43.6) at 4500 lbs. or less Straight line variation between points given Landing gear retracted moment change: +848 in. lbs. Empty Wt. C.G. Range None *Maximum Weight Landing 5400 lbs., takeoff 5500 lbs. No. of Seats 5 (Std.) (2 at +37, 3 at +71). See Manufacturer's Weight and Balance data sheet for optional seating arrangements. 3A10 30 Rev. 64 XXI. Model T310Q (cont’d) Maximum Baggage 200 lbs. (+96), 80 lbs. per side on floor (+124) 120 lbs. per nacelle (+63) Fuel Capacity Tank Capacity (Gal.) Usable (Gal.) Moment Arm S/N 310Q0001 through 310Q1160 LH tip tank 51 50 +35 RH tip tank 51 50 +35 LH aux. tank (40 gal. opt) 20.5 20 +47 RH aux. tank (40 gal. opt) 20.5 20 +47 LH wing locker tank 20.5 20 +49 RH wing locker tank 20.5 20 +49 S/N 310Q0601 through 310Q1160 LH aux. tank (63 gal. opt) 32 31.5 +47 RH aux. tank (63 gal. opt) 32 31.5 +47 (See NOTE 1 for data on unusable fuel) Oil Capacity 6.5 gal. (3.25 ga l. in each engine at (-3.5), usable 1.75 gal. ea. engine) (See NOTE 1 for data on undrainable oil) Control Surface Wing flaps Down 35° Movements Main surfaces Aileron Up 20° Down 20° Elevator Up 16.5° Down 15° Rudder Right 29.3° Left 29.3° (Parallel to W.L.) Tabs (main surface in neutral) Aileron Up 20° Down 20° Elevator Up 10° Down 26° Rudder Right 17° Left 22° (Parallel to W.L.) Serial Nos. Eligible 310Q0001 through 310Q1160. Production Certificate No. 312 effective. XXII. Model 310R (Normal Catego ry), Approved August 15, 1974 Engines S/N 310R0001 through 310R1434 2 Continental IO-520-M or IO-520-MB S/N 310R1501 through 310R2140 2 Continental IO-520-MB *Fuel Grade 100 or 100LL aviation gasoline *Engine Limits For all operations, 2700 r.p.m. (285 hp.) Propeller and 1. 2 full-feathering 3-bladed propeller installations Propeller Limits a(1) McCauley hubs 3AF32C87, blades 82NC-5.5 Diameter: Not over 76.5 in., not under 74.5 in. Pitch settings at 30 in. sta.: Low 13.9 o, feathered 81.7o or a(2) McCauley hubs 3AF32C504, with 82NEA-5.5 blades Diameter: not over 76.5 in., not under 76.0 in. Pitch settings at 30 in. sta.: low 13.9°, feathered 81.7° Rev. 64 31 3A10 XXII. Model 310R (cont’d) Propeller and b. S/N 310R0001 through 310R0330 Propeller Limits (cont’d) Hydraulic governor Woodward A210529, B210444, B210446 or C210439; McCauley DCF290D 2/T3, DCFS290D2/T3, DCFU290D2/T3, DCFUS290D2/T3, DCF290D7/ T3, DCFS290D7/T3, DCFU290D7/T3, DCFUS290D7/T3, DCFU290D13/T3 or DCFUS290D13/T3 S/N 310R0501 through 310R1004 Hydraulic governor Woodward B210444, C210439; McCauley DCF290D2/T3, DCFU290D2/T3, DCFS290D4/T3, DCFS290D5/T3, DCFUS290D4/T3, DCFUS290D5/ T3, DCF290D7/T3, DCFUS290D7/T3, DCFS290D7/T3, DCFS290D8/T3 , DCFUS290D7/T3, DCFUS290D8/T3, DCFU290D13/T3, DCFUS290D13/T3 or DCFUS290D12/T3 S/N 310R01201 through 310R2140 Hydraulic governor Woodward B210444, C210439; McCauley DCF290D2/T3, DCFU290D2/T3, DCFS290D4/T3, DCFS290D5/T3, DCFUS290D4/T3, DCFUS290D6/T3, DCF290D7/T3, DCFU290D7/T3, DCFS290D7/T3, DCFS290D8/T3 , DCFUS290D7/T3, DCFUS290D8/T3, DCFU290D13/T3, DCFUS290D13/T3 or DCFUS290D12/T3 c. Propeller spinner, McCauley D3534 dome with D3796 bulkhead or D-5212 dome with D-5214 bulkhead. *Airspeed Limits S/N 310R0001 through 310R0330 (CAS) Maneuvering 150 knots (172 m.p.h.) Maximum structural crui sing 183 knots (210 m.p.h.) Never exceed 227 knots (261 m.p.h.) Flaps extended 15° 160 knots (184 m.p.h.) Flaps extended 35° 140 knots (161 m.p.h.) Landing gear extended 140 knots (161 m.p.h.) (IAS) S/N 310R0501 through 310R2140 Maneuvering 148 KIAS (170 m.p.h.) Maximum structural cruising 181 KIAS (208 m.p.h.) Never exceed 223 KIAS (257 m.p.h.) Flaps extended 15° 158 KIAS (182 m.p.h.) Flaps extended 35° 139 KIAS (160 m.p.h.) Landing gear extended 138 KIAS (159 m.p.h.) *C.G. Range (Landing (+38.7) to (+43.1) at 5500 lbs. (takeoff) Gear Extended) (+38.0) to (+43.2) at 5400 lbs. (landing) (+43.6) at 5100 lb. (+32.0) to (+43.6) at 4500 lbs. or less Straight line variation between points given Landing gear retracted moment change: +782 in. lbs. Empty Wt. C.G. Range None *Maximum Weight S/N 310R0001 through 310R1004 Landing 5400 lbs., takeoff 5500 lbs. S/N 310R1201 through 310R2140 Landing 5400 lbs., ramp 5535 lb., takeoff 5500 lbs. No. of Seats 5 (Std.) (2 at +37, 3 at +71). See Manufacturer's Weight and Balance data sheet for optional seating arrangements 3A10 32 Rev. 64 XXII. Model 310R (cont’d) Maximum Baggage 200 lbs. (+96), 80 lbs. per side on floor (+124), 120 lbs. per nacelle (+63), 350 lb. nose (-31) Fuel Capacity Capacit y Usable Moment Tan k (Gal) (Gal) Arm LH tip tan k 51 50 +35 RH ti p tank 51 50 +35 LH aux. tank (40 gal. opt) 20.5 20 +47 RH aux. tank (40 gal. opt) 20.5 20 +47 LH aux. tank (63 gal. opt) 32 31.5 +47 RH aux. tank (63 gal. opt) 32 31.5 +47 LH wing locker tank 20.5 20 +49 RH win g locker tank 20.5 20 +49 (See NOTE 1 for data on unusable fuel) Oil Capacity 6.5 gal. (3.25 ga l. in each engine at (-3.5), usable 1.75 gal. ea. engine) (See NOTE 1 for data on undrainable oil) Control Surface Wing flaps Down 35° Movements Main surfaces Aileron Up 20° Down 20° Elevator Up 16.5° Down 15° Rudder Right 29.3° Left 29.3° (Parallel to W.L.) Tabs (main surface in neutral) Aileron Up 20° Down 20° Elevator Up 10° Down 26° Rudder Right 17° Left 22° (Parallel to W.L.) Serial Nos. Eligible 310R0001 through 310R2140. Production Certificate No. 312 effective. XXIII. Model T310R (Turbo-System 310R) (Nor mal Category), Approved August 15, 1974 Engines S/N 310R0001 through 310R1434 2 Continental TSIO-520-B or TSIO-520-BB S/N 310R1501 through 310R2140 2 Continental TSIO-520-BB *Fuel Grade 100 or 100LL aviation gasoline *Engine Limits For all operations, 2700 r.p.m. (285 hp. 32 in. Hg MP) Critical altitude is 16,000 ft. in standard atmosphere Maximum Altitude Allowable MP Sea level 32.0 in. Hg 16,000 ft. 32.0 in. Hg 18,000 ft. 30.7 in. Hg 20,000 ft. 29.0 in. Hg 22,000 ft. 26.4 in. Hg 24,000 ft. 24.3 in. Hg 26,000 ft. 22.2 in. Hg 28,000 ft. 20.2 in. Hg 30,000 ft. 18.5 in. Hg 32,000 ft. 17.0 in. Hg Rev. 64 33 3A10 XXIII. Model T310R (cont’d) Propeller and 1. 2 full-feathering 3-bladed propeller installations Propeller Limits a. McCauley hubs 3AF32C87 with 82NC-4 blades or McCauley hubs 3AF32C504 with 82NEA-4 blades Diameter: not over 78 in., not under 74 in. Pitch settings at 30 in. sta.: low 13.0°, feathered 82.6° b. S/N 310R0001 through 310R0330 Hydraulic governor Woodward A210529, B210446; McCauley DCFS290D2/T3, DCFUS290D2/T3, DCFS290D7/T3, DCFUS290D7/T3 or DCFUS290D13/T3 S/N 310R0501 through 310R1004 Hydraulic governor McCauley DCFS290D4/T3, DCFS290D5/T3, DCFUS290D4/T3, DCFUS290D5/T3, DCFS290D7/T3, DCFS290D8/T3, DCFUS290D7/T3, DCFUS290D8/T3, DCFUS290D13/T3 or DCFUS290D12/T3 S/N 310R1201 through 310R2140 Hydraulic governor McCauley DCFS290D4/T3, DCFS290D6/T3, DCFUS290D4/T3, DCFUS290D6/T3, DCFS290D7/T3, DCFS290D8/T3, DCFUS290D7/T3, DCFUS290D8/T3, DCFUS290D13/T3 or DCFUS290D12/T3 c. Propeller spinner McCauley D3534 dome with D3796 bulkhead *Airspeed Limits S/N 310R0001 through 310R0330 (CAS) Maneuvering 150 knots (172 m.p.h.) Maximum structural crui sing 183 knots (210 m.p.h.) Never exceed 227 knots (261 m.p.h.) Flaps extended 15° 160 knots (184 m.p.h.) Flaps extended 35° 140 knots (161 m.p.h.) Landing gear extended 140 knots (161 m.p.h.) (IAS) S/N 310R0501 through 310R2140 Maneuvering 148 KIAS (170 m.p.h.) Maximum structural cruising 181 KIAS (208 m.p.h.) Never exceed 223 KIAS (257 m.p.h.) Flaps extended 15° 158 KIAS (182 m.p.h.) Flaps extended 35° 139 KIAS (160 m.p.h.) Landing gear extended 138 KIAS (159 m.p.h.) *C.G. Range (Landing (+38.7) to (+43.1) at 5500 lbs. (takeoff) Gear Extended) (+38.0) to (+43.2) at 5400 lbs. (landing) (+43.6) at 5100 lbs. (+32.0) to (+43.6) at 4500 lbs. or less Straight line variation between points given Landing gear retracted moment change: +782 in. lbs. Empty Wt. C.G. Range None 3A10 34 Rev. 64 XXIII. Model T310R (cont’d) *Maximum Weight S/N 310R0001 through 310R1004 Landing 5400 lbs., takeoff 5500 lbs. S/N 310R1201 through 310R2140 Landing 5400 lbs., ramp 5535 lbs., takeoff 5500 lbs. No. of Seats 5 (Std.) (2 at +37, 3 at +71). See Manufacturer's Weight and Balance data sheet for optional seating arrangements. Maximum Baggage 200 lbs. (+96), 80 lbs. per side on floor (+124) 120 lbs. per nacelle (+63), 350 lb. nose (-31) Fuel Capacity Capacity Usable Moment Tank (Gal) (Gal) Arm LH tip tank 51 50 +35 RH tip tank 51 50 +35 LH aux. tank (40 gal. opt) 20.5 20 +47 RH aux. tank (40 gal. opt) 20.5 20 +47 LH aux. tank (63 gal. opt) 32 31.5 +47 RH aux. tank (63 gal. opt) 32 31.5 +47 LH wing locker tank 20.5 20 +49 RH wing locker tank 20.5 20 +49 (See NOTE 1 for data on unusable fuel) Oil Capacity 6.5 gal. (3.25 ga l. in each engine at (-3.5), usable 1.75 gal. ea. engine) (See NOTE 1 for data on undrainable oil) Control Surface Wing flaps Down 35° Movements Main surfaces Aileron Up 20° Down 20° Elevator Up 16.5° Down 15° Rudder Right 29.3° Left 29.3° (Parallel to W.L.) Tabs (main surface in neutral) Aileron Up 20° Down 20° Elevator Up 10° Down 26° Rudder Right 17° Left 22° (Parallel to W.L.) Serial Nos. Eligible 310R0001 through 310R2140. Production Certificate No. 312 effective. Rev. 64 35 3A10 Data Pertinent to All Models Datum Forward face of fuselage bulkhead forward of rudder pedals. *Leveling Means Models 310Q, 310R, T310R: External splice plate on left side of fuselage under the windows. External leveling screws at F.S. 59.10 and F.S. 88.90 additional Certification Basis: Models 310, 310A, 310B, 310C, 310D, 310E, 310F CAR 3 dated November 1, 1949, as amended by 3-1 through 3-10. Models 310G, 310H, E310H, 310I, 310J, 310J-1, E310J, 310K, 310L, 310N, 310P, T310P CAR 3 dated November 1, 1949, as amended by 3-1 through 3-10 and Sections 3.109, 3.111, 3.112, 3.115, 3.118 and 3.120 of CAR 3 dated May 15, 1956, as amended by 3-2 and 3-5. Models 310Q, T310Q CAR 3 dated November 1, 1949, as amended by 3-1 through 3-10, Sections 3.109, 3.111, 3.112, 3.115, 3.118, 3.118, 3.120 and 3.688 of CAR 3 dated May 15, 1956, as amended by 3-2, 3-5 and 3-8. Models 310R, T310R CAR 3 dated November 1, 1949, as amended by 3-1 through 3-10 and Sections 3.109, 3.111, 3.112, 3.115, 3.118, 3.120 and 3.688 of CAR 3 dated May 15, 1956, as amended by 3-2, 3-5 and 3-8; and Sections 23.161 and 23.171 through 23.181 of FAR 23 dated February 1, 1965, as amended by 23-1 through 23-7, and 23.1327 as amended through 23-23. Model 310R/T310R, S/N 310R0801 through 310R2140 In addition to the above certification basis, compliance with ice protection has been demonstrated in accordance with FAR 23.1419 of Amendment 23-14 effective December 20, 1973, when ice protection equipment is installed in accordance with the Pilot's Operating Handbook and Factory Kit (FK) No. 194. Model 310R/T310R, S/N 310Q0901 through 310Q1160 Markings, placards and manuals are primarily in knots instead of m.p.h. as required by CAR 3, but permitted by FAR 23, Amendment 23-7. Model 310R/T310R, S/N 310R0501 through 310R2140 Findings of equivalent level of safety were made for CAR 3.757 and 3.778(a). Model 310R/T310R, S/N 310R1801 through 310R2140 In addition to the above certification basis, compliance with noise certification requirements has been demonstrated in accordance with FAR 36 dated December 1, 1969, as amended through 36-10. Application for type certificate dated April 9, 1952. Type Certificate No. 3A10 issued March 22, 1954. Model 310A and subsequent certificated under delegation option procedures. Production Basis: Production Certificates Nos. 4 and 312 (refer to "S/N eligible for applicability"). Delegation Option Manufacturer Nos. CE-1 and CE-3 authorized to issue airworthiness certificates under delegation option provisions of Part 21 of the FAR. Effective February 15, 1985, and on, Production Certificate No. 4 is applicable to all spares production. 3A10 36 Rev. 64 Data Pertinent to All Models 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. (a) Models 310C, 310D, 310E, 310F, 310G, 310H, E310H, 310I, 310J, 310J-1, E310J, 310K: Airspeed Indicator, Cessna Dwg. 0813604 or CM 2640 or complying with TSO-C2, (b) Model 310L: Airspeed I ndicator, Cessna Dwg. CM 3301-4. (c) Models 310N, 310P: Airspeed Indicator, Cessna Dwg. CM-3301-6. (d) Model T310P: Airspeed Indicator, Cessna Dwg. CM 3301-2. (e) Model 310Q, S/N 310Q0001 through 310Q0845: Airspeed Indicator, Cessna Dwg. C661040-0102. (f) Model T310Q, S/N 310Q0001 through 310Q0845: Airspeed Indicator, Cessna Dwg. C661040-0103. (g) Model 310Q, S/N 310Q0901 through 310Q1160: Airspeed Indicator, Cessna Dwg. C661040-0202. (h) Model T310Q, S/N 310Q0901 through 310Q1160: Airspeed Indicator, Cessna Dwg. C661040-0203. (i) Models 310R, S/N 310R0001 through 310R0330, T310R, S/N 310R0001 through 310R0330: Airspeed Indicator, Cessna Dwg. C661040-0208. (j) Models 310R, S/N 310R0501 through 310R2140, T310R, S/N 310R0501 through 310R2140: Airspeed Indicator, Cessna Dwg. C661040-0209. 2. (a) Models 310G, 310H, E310H, 310I , 310J, 310J-1, E310J: Safe Flight Stall Warning Indicator (Model 146-5), 24v. (b) Models 310K, 310L, 310N, 310P, T310P, 310Q, T310Q, 310R, T310R, or as modified by MEB- 34-05, Models 310Q, T310Q, 310R, T310R: Safe Flight Stall Warning Indicator (Model 285), 24v. (c) Models 310Q and T310Q: Safe Fli ght Stall Warning Indicator (Model 285), or Angle of Attack Indicator System, Cessna Dwg. 0800302. NOTE 1. Current weight and ba lance report including list of equipment included in certificated empty weight, and loading instructions when necessary, must be provided for each aircraft at the time of original certification. The certificated empty weight and corresponding center of gravity location must include undrainable oil (not included in oil capacity) and unusable fuel (not included in fuel capacity) as follows: Fuel 6 lbs. at (+44) 310, 310A, 310B Oil 1 lb. at (+ 0) 310, 310A, 310B Fuel 12 lbs. at (+44) 310C, 310D, 310E, 310F, 310G, 310H, E310H, 310I, 310J, 310J-1, E310J, 310K, 310L, 310N, 310P, T310P, 310Q, T310Q, 310R, T310R Oil l lb. at (-3.5) 310C, 310D, 310E, 310F, 310G, 310H, E310H, 310I, 310J, 310J-1, E310J, 310K, 310L, 310N, 310P, T310P, 310Q, T310Q, 310R, T310R Models 310, 310A, 310B, 310C, 310D, 310E, 310F, 310G, 310H, E310H, 310I, 310J, E310J, 310J-1, 310K: When two 15.5 gal. auxiliary fuel ta nks are installed, an additional 6 lbs. of unusable fuel at (+47) must be included. Models 310L, 310N, 310P, T310P, 310Q, T310Q, 310R, T 310R: When two 20.5 gal. auxiliary fuel tanks are installed, an additional 6 lbs. of unusable fuel at (+47) must be included. Models 310L, 310N, 310P, T310P, 310Q, T310Q, 310R, T310R : When two 20.5 gal. wing locker fuel tanks are installed, an additional 6 lbs. of unusable fuel at (+58) must be included. Models 310Q and T310Q S/N 310Q0601 through 310Q1160, 310R and T310R: When two 32 gal. auxiliary fuel tanks are installed, an additional 6 lbs. of unusable fuel at (+47) must be included. Rev. 64 37 3A10 Data Pertinent to All Models NOTE 2. Model 310R/T310R, S/N 310R1501 through 310R2140: The placards specified in the F AA Approved AFM must be displayed. Models 310, 310A, 310B, 310C, 310D, 310E, 310F, 310G, 310H, E310H, 310I, 310J, 310J-1, E310J, 310K, 310L, 310N, 310P, T310P, 310Q, T310Q, 310R S/N 310R0001 through 310R1434, T310R S/N 310R0001 through 310R1434, the following placards must be displayed as indicated: 1. "Operation Limits" (On Circuit Breaker Panel) a. Models 310, 310A, 310B, 310C, 310D, 310E, 310F, 310G, 310H, 310I, 310J, E310J, 310K, 310L, 310N, 310P, T310P, 310Q, T310Q, 310R S/N 310R0001 through 310R1004, T310R S/N 310R0001 through 310R1004: "This airplane must be operated as a normal category airplane in compliance with the operating limitations as stated in the form of placards, markings and manuals (Pilot's Check List)." b. Model 310J-1: "This airplane must be oper ated as a normal or utility category airplane compliance with the operating limitations as st ated in the form of placards, markings and manuals (Pilot's Check List)." 2. a. Models 310, 310A, 310B, 310C, 310D, 310E , 310F, 310G, 310H, 310I, 310J, E310J, 310K, 310L, 310N, 310P, T310P, 310Q, T310Q, 310R S/N 310R0001 through 310R1004, T310R S/N 310R0001 through 310R1004: "No acrobatic maneuvers including spins approved." b. Model 310J-1: "Intentional spins prohibited; Approved Maneuvers Ma ximum Safe Entry Speed Lazy Eights 160 m.p.h. (CAS) Steep Turns 160 m.p.h. (CAS) Chandelles 160 m.p.h. (CAS)" 3. a. Model 310: "Minimum speed for si ngle engine operation 95 mph. (TIAS)" b. Models 310A, 310B: "Minimum speed for single engine operation 84 mph. (TIAS) c. Model 310C: "Minimum speed for single engine operation 86 mph. (TIAS)" d. Models 310D, 310F: "Minimum speed for single engine operation 83 mph. (TIAS)" e. Model 310E: "Minimum speed for si ngle engine operation 88 mph. (TIAS)" f. Model 310G: "Minimum speed for single engine operation 84 mph. (CAS)" g. Models 310H, E310H: “M inimum speed for single engine operation 90 mph. (CAS)" h. Models 310I, 310J, 310J-1, E310J, 310K, 310L: "Minimum speed for single engine operation 85 mph. (CAS)" i. Models 310N, 310P: "Minimum speed for single engine operation 85 mph. (CAS)" 4. a. Model T310P: "Minimum single engine control speed 90 mph. (CAS)" b. Model 310Q S/N 310Q0001 through 310Q0845: "Minimum single engine control speed 86 mph. (CAS)" c. Model T310Q S/N 310Q0001 through 310Q0845: "Minimum single engine control speed 94 mph. (CAS)" d. Model 310Q S/N 310Q0901 through 310Q1160: "Minimum single engine control speed 75 knots (CAS)" e. Models T310Q S/N 310Q0901 through 310Q1160, 310R, S/N 310R0001 through 310R0330, T310R S/N 310R0001 through 310R0330: "Minimum single engine control speed 81 knots (CAS)" f. Models 310R S/N 310R0501 through 310R1004, T310R S/N 310R0501 through 310R1004: "Air Minimum Control Speed, 80 KIAS" 3A10 38 Rev. 64 Data Pertinent to All Models NOTE 2 (cont’d) 5. a. Model 310: "Maximum g ear extended speed 130 mph. (CAS)" b. Models 310A, 310B, 310C, 310D, 310E, 310F: "Maximum gear extended speed 140 mph. (CAS)" c. Models 310G, 310H, E 310H, 310I, 310J, 310J-1, E310J, 310K: "Maximum gear extended speed 140 mph. (CAS)" d. Models 310L, 310N, 310P, T310 P, 310Q S/N 310Q0001 through 310Q0845, T310Q S/N 310Q0001 through 310Q0845: "Max imum gear extended speed 160 mph. (CAS)" e. Models 310Q S/N 310Q0901 through 310Q 1160, T310Q S/N 310Q0901 through 310Q1160, 310R S/N 310R0001 through 310R0330, T310R S/N 310R0001 through 310R0330: "Maximum gear extended speed 140 knots (CAS)" f. Models 310R S/N 310R0501 through 310R1004, T310R S/N 310R0501 through 310R1004: "Maximum gear operating speed: 138 KIAS" g. Models 310R S/N 310R0501 through 310R1004, T310R S/N 310R0501 through 310R1004: "Maximum gear extended speed: 138 KIAS" 6. a. Model 310J-1:"Maximum maneuvering speed 183 mph. (CAS)" 7. a. Models 310R S/N 310R1201 thr ough 310R2140, T310R S/N 310R1201 through 310R2140: (1) "This airplane must be operated as a normal category airplane in compliance with the operating limitations stated in the form of placards, markings and handbooks (Pilot's Checklist)" (2) "No acrobatic maneuvers, including spins, approved" (3) "Air minimum control speed: 80 KIAS" (4) "Maximum gear operating speed: 138 KIAS" (5) "Maximum gear extended speed: 138 KIAS" (6) "Maximum flap extended speed 15°: 158 KIAS" (7) "Maximum flap extended speed 35°: 139 KIAS" (8) "Maximum maneuvering speed: 148 KIAS" (9) "This airplane is approved for day/night VFR conditions. It’s approved for day/night IFR conditions and flights into icing conditions if the proper optional equipment is installed and operational." IDLE POWER STALL SPEEDS (KIAS) Angle of Ban k Configuration 0° 20° 40° 60° Gear Up - Flaps Up 79 82 91 112 Gear Down - Flaps Down 15° 77 79 88 109 Gear Down - Flaps Down 35° 72 74 82 101 7. On the Instrument Panel a. "Open defrost or cabin air during heater operation." b. "T & B Test" "Heater Overheat" c. Model 310: "Flap Max. Speed Deflection (TIAS) MPH 15° 160 15° - 45° 130" d. Models 310A, 310B, 310C , 310D, 310E, 310F, 310G, 310H, E310H: "Flap Max. Speed Deflection (TIAS) MPH* 15° 160 15° - 45° 140" *(Substitute ‘CAS’ for ‘TIA S’ on Models 310G, 310H, E310H) Rev. 64 39 3A10 Data Pertinent to All Models NOTE 2 (cont’d) e. Models 310I, 310J, 310J-1, E310J: "Flap Max. Speed Deflection** (CAS) MPH 15° 160 15° - 35° 140" **(as noted on position indicator) f. Model 310K: "Flap Max. Speed Deflection** (CAS) MPH 15° 180 15° - 35° 140" **(as noted on position indicator) g. Models 310L, 310N, 310P, T3 10P, 310Q, S/N 310Q0001 through 310Q0845, T310Q, S/N 310Q0001 through 310Q0845: "Flap Max. Speed Deflection** (CAS) MPH 15° 180 15° - 35° 160" **(as noted on position indicator) h. Models 310Q, S/N 310Q0901 through 310Q1160; T310Q, S/N 310Q0901 through 310Q1160, 310R, S/N 310R0001 through 310R0330; T310R, S/N 310R0001 through 310R0330: "Flap Max. Speed Deflection** (CAS) Knots 15° 160 15° - 35° 140" **(as noted on position indicator) i. Models 310R, S/N 310R0501 through 310R2140; T310R, S/N 310R0501 through 310R2140: "Flap Max. Flap Deflection** Ext. Speed 15° 158 KIAS 15° - 35° 138 KIAS" **(as noted on position indicator) j. Models 310L, 310N, 310P, T310P, 310Q, T310Q, 310R/T310R, S/N 310R0001 through 310R0735: If nacelle fuel transfer tanks are installed: "20 gal. - empty - LH - ON - RH - OFF – fuel transfer - 20 gal k. Models 310I, 310J, 310K, 310L, 310N, 310P , 310Q: If AK 310-212 is installed: "Aircraft Gross Weight limited to 4990 lb. See Owner's Manual Supplement No. D919-13." l. Model 310R: If AK 310-233 is installed: "Aircraft Gross Weight limited to 4990 lbs. See Owner's Manual Supplement No. D1524-13." m. Models T310P, T310Q: If AK 310-220 is installed: "Aircraft Gross Weight limited to 4990 lbs. See Owner's Ma nual Supplement No. D1502-13." n. Model T310R: If AK 310-234 is installed: "Aircraft Gross Weight limited to 4990 lbs. See Owner's Manual Supplement No. D1525-13." o. Models 310Q, T310Q S/N 310Q0601 th rough 310Q1160; 310R, T310R: If Oxygen System is installed: "U se Blue Oxygen connector only." p. Models 310R/T310R, S/N 310R0501 through 310R2140: If fuel low level warning is installed: "L - Low Fuel - R" 3A10 40 Rev. 64 Data Pertinent to All Models NOTE 2 (cont’d) q. Models 310R/T310R S/N 310R0801 through 310R1004: If propeller synchrophaser is installed: (1) Near phasing knob and switch: "PHASING-SYNC-OFF" "MUST BE OFF FOR TAKEOFF, LDG AND ONE ENG. OPER." (2) Near phasing light: "PROP-SYNC" r. Models 310R/T310R S/N 310R1201 through 310R2140: If propeller synchrophaser is installed: (1) Near phasing knob and switch: "PHASING - OFF" "MUST BE OFF FOR TAKEOFF, LDG AND ONE ENGINE OPER" (2) Near phasing light: "PROP - SYNC" 8. On Foul Weather Window a. Models 310, 310A, 310B, 310C, 310D, 310E, 310F, 310G, 310H, E310H, 310I, 310J, 310J-1, E310J: "Do not open above 130 mph." 9. On Emergency Exits a. On left emergency exit (1) Models 310, 310A, 310B, 310C, 310D , 310E, 310F, 310G, 310H, E310H, 310I, 310J, 310J-1, E310J, 310K, 310L, 310 N, 310P/T310P, 310Q/T310Q, S/N 310Q0001 through 310Q0291: "Emergency Exit - pull ring - push window out." (2) Models 310Q/T310Q, S/N 310Q 0401 through 310Q1160; 310R/T310R, S/N 310R0001 through 310R0735: "Emergency Exit - Pull Handle - Push bottom of window out with sustained force." (3) Models 310R/T310R, S/N 310R0801 through 310R2140: "EMERGENCY EXIT - PULL HANDLE - PUSH WINDOW OUT" (4) Models 310L, S/N 310L0075 thr ough 310L0207; 310N, 310P, T310P, 310Q, T310Q, 310R/T310R, S/N 310R0001 through 310R0735: "Emergency window release pull." b. On right emergency exit (1) Models 310G, S/N 310G0080 thr ough 310G0156; 310H, E310H, 310I, 310J, 310J-1, E310J: "Emergency Exit - force to open." 10. On Control Lock a. "Control Lock - remove before starting engines." 11. On Floor Between Front Seats a. (1) Models 310, 310A, 310B, 310C, 310D, 310E, 310F, 310G, 310H, E310H, 310I, 310J, 310J-1, E310J: "Left engine 50 gal. - left on tank - right on tank - both off." (2). Models 310K, 310L, 310N, 310P, T310P, 310Q, T310Q, 310R, T310R: "Left main 50 gal. - right main 50 gal. - left engine off." (3) Models 310, 310A, 310B, 310C, 310D , 310E, 310F, 310G, 310H, E310H, 310I, 310J, 310J-1, E310J: "Right engine 50 gal. - left on tank - right on tank - both off." (4) Models 310K, 310L, 310N, 310P, T310P, 310Q, T310Q, 310R, T310R: "Left main 50 gal. – right main 50 gal. - right engine off." b. (1) "Set fuel selector valve to left main tank for left engine and right main tank for right engine for takeoff, landing and all normal operation." (2) Models 310, 310A, 310B: "Takeoff and land with fuel boost pumps on. To extend gear manually, pull out crank to engage and turn clockwise to extend. Caution: push button and stow crank before operating electrically." (3) Models 310C, 310D, 310E, 310F, 310G, 310H , E310H: "Takeoff and land with auxiliary pumps on. Use full rich mixture and auxiliary pumps when switching fuel pumps. To extend gear manually, pull out crank to engage and turn clockwise to extend. Caution: push button and stow crank before operating electrically." (4) Models 310I, 310J, 310J-1, E310J: "Tak eoff and land with auxiliary pumps on. Use full rich mixture and auxiliary pumps on 'low' when switching tanks. To extend gear manually, pull out crank to engage and tu rn clockwise to extend. Caution: push button and stow crank before operating electrically." Rev. 64 41 3A10 Data Pertinent to All Models NOTE 2 (cont’d) (5) Models 310K, 310L, 310N, 310P, T310P, 310Q, T310Q, 310R, T310R: "Takeoff and land with auxiliary fuel pumps on. Use full rich mixture and auxiliary fuel pumps on 'low' when switching fuel tanks. (Feel fo r detent.) To extend gear manually, pull out crank to engage and turn clockwise. CAUTION: - Gear switch should be in neutral before operating manual system. - Push button and stow crank before operating electrically." c. (1) Models 310L, S/N 310L0050 th rough 310L0207; 310N, 310P/T310P, 310R/T310R, S/N 310R0001 through 310R0330: If optiona l nacelle transfer tanks are installed – "Use main tank for takeoff, landing and emergency." "Takeoff and land with auxiliary fuel pumps on." "Use full rich mixture and auxiliary fu el pumps on 'low' when switching fuel tanks." (a) "Operate on main tanks until fu el quantity is less than 30 gal. per tank." (b) "Transfer wing locker fuel while operating on main tanks in straight and level flight." (c) "Turn transfer pumps off when lights illuminate." (d) "Use fuel cross feed system to balance main fuel quantities if one wing locker tank does not transfer or if a single wing locker tank is installed." (e) "Switch to auxiliary tanks when main fuel is again less than 30 gal. per tank." "To extend gear manually, pull out crank to engage and turn clockwise." CAUTION: - Gear switch should be in neutral before operating manual system. - Push button and stow crank before operating electrically." d. (1) Models 310R/T310R, S/N 310R0501 through 310R2140: If optional nacelle transfer tanks are installed - "Set fuel selector va lves to left main tank for left engine and right main tank for right engine in takeoff, landing and emergency." "Takeoff and land with auxiliary fuel pumps ON." "Use full rich mixture and auxiliary fuel pumps on 'low' when switching fuel tanks." (a) "Operate on main tanks until fuel quantity is less than 180 lbs./tank." (b) "Transfer wing locker fuel to ma in tanks in straight and level flight only." (c) "Turn transfer pumps OFF when lights illuminate." (d) "Operate on auxiliary tanks only when main tank is again less than 180 lbs./tank." "To extend gear manually pull out crank to engage and turn clockwise." CAUTION: - Gear switch should be in neutral before operating manual system. - Push button and stow crank before operating electrically." 12. Baggage a. On baggage door (1) Models 310A, 310B, 310C, 310D, 310E, 310F, 310G: "Maximum capacity – 200 lbs. See weight and balance data for detailed loading instructions." (2) Models 310H, E310H, 310I, 310J, 310J-1, E310J): "Maximum capacity - 200 lbs. Sta. 85 - 110 - see weight and balance data for detailed loading instructions." b. Models 310H, E310H: On upper baggage wall, Sta. 132 (1) "Maximum baggage capacity - 60 lbs. - see weight and balance data for detailed loading instructions." c. Models 310H, 310I, 310J, 310J-1, E 310J: On lower baggage wall, Sta. 132 (full width baggage area) (1) "Maximum baggage capacity - 160 lb s. Sta. 110 - 132 - see weight and balance data for detailed loading instructions." d. Models 310H, E310H: On lower bagga ge wall, Sta. 132 (alternate baggage area) (1) "Maximum baggage capacity - 80 lbs. Sta. 110 – 132. See weight and balance data for detailed loading instructions." 3A10 42 Rev. 64 Data Pertinent to All Models NOTE 2 (cont’d) e. Models 310I, 310J, 310J-1, E310J, 310K, 310L, 310N, 310P, T310P, 310Q, T310Q, 310R, T310R: On each wing locker door (1) "Maximum baggage 120 lbs." (2) If wing locker transfer tanks are installed, "Maximum baggage 40 lbs." f. Models 310K, 310L, 310N, 310P, T310P, 310Q, T310Q, 310R, T310R: On baggage door (1) "Sta. 89 to Sta. 109 - 200 lbs., Sta. 109 to Sta. 132 - 160 lbs. See Weight and Balance data for detailed loading instructions." g. Models 310R, T310R: On aft baggage retainer in nose. (1) "Maximum baggage XX.X. Maximum capacity 350 lbs. less XX.X optional equipment." 13. Adjacent to Fuel Strainer a. "Fuel strainer - drain daily. NOTE: if water is observed at the fuel strainer, fuel tank sumps and cross feed lines must be drained." 14. Omitted 15. When auxiliary tanks are installed, replac e placard 2F on floor between front seats with the following placard: a. (1) Models 310, 310A, 310B, 310C, 310D, 310E, 310F, 310G, 310H, E310H, 310I, 310J, 310J-1, E310J: "Left engine - 50 gal. left main - 15 gal. left auxiliary – 50 gal. right main - left engine off." (2) Model 310K: "Left main 50 gal. - le ft auxiliary 15 gal. - right main 50 gal. - left engine off." (3) Models 310L, 310N, 310P, T310P, 310Q , T310Q, 310R, T310R: "Left main 50 gal. - left auxiliary 20 gal. - right main 50 gal. - left engine off." b. (1) Models 310, 310A, 310B, 310C, 310D, 310E, 310F, 310G, 310H, E310H, 310I, 310J, 310J-1, E310J: "Right engine - 50 gal. left main - 15 gal. right auxiliary – 50 gal. right main - right engine off." (2) Model 310K: "Left main 50 gal. - ri ght auxiliary 15 gal. - right main 50 gal. - right engine off." (3) Models 310L, 310N, 310P, T310P, 310Q , T310Q, 310R, T310R: "Left main 50 gal. - right auxiliary 20 gal. - righ t main 50 gal. - right engine off." c. Models 310, 310A, 310B: (1) "Use main tanks for takeoff, landing and first 30 minutes of flight." (2) "Set fuel selector valves to left ta nk for left engine and right tank for right engine in takeoff, landing and all normal operation." (3) "Takeoff and land with fuel boost pump on." (4) "To extend gear manually, pull out cra nk to engage and turn clockwise to extend. Caution: push button and stow crank before operating electrically." d. Models 310C, 310D , 310E, 310F, 310G, 310H, E310H: (1) "Use main tanks for takeoff, landing and first 60 minutes of flight." (2) "Set fuel selector valves to left engine and right tank for right engine in takeoff, landing and all normal operation." (3) "Takeoff and land with auxiliary fuel pumps on. Use full rich mixture and auxiliary pumps when switching fuel tanks." (4) "To extend gear manually, pull out cra nk to engage and turn clockwise to extend. Caution: push button and stow crank before operating electrically." Rev. 64 43 3A10 Data Pertinent to All Models NOTE 2 (cont’d) e. (1) Models 310I, 310J, 310J-1, E310J: "S et fuel selector valve to left main tank for left engine and right main tank for right engine for takeoff, landing and all normal operation." (2) Models 310K, 310L, 310N, 310P, T310P, 310Q, T310Q, 310R, T310R: "Set fuel selector valve to left main tank for left engine and right main tank for right engine for takeoff, landing and emergency." (3) Models 310I, 310J, 310J-1, E310 J, 310K, 310L, 310N, 310P, T310P, 310Q, T310Q, 310R, T310R: "Use main tanks for ta keoff, landing and first 60 minutes of flight." (4) Models 310I, 310J, 310J-1, E310 J, 310K, 310L, 310N, 310P, T310P, 310Q, T310Q, 310R, T310R: "Takeoff and load with auxiliary fuel pumps on. Use full rich mixture and auxiliary fuel pumps on 'low' when switching fuel tanks." (Feel for detent.) (5) Models 310I, 310J, 310J-1, E310J: "To extend gear manually, pull out crank to engage and turn clockwise. Cauti on: push button and stow crank before operating electrically." (6) Models 310K, 310L, 310N, 310P, T310P, 310Q, T310Q, 310R, T310R: "To extend gear manually, pull out crank to engage and turn clockwise. Caution: (a) Gear switch should be in neutral before operating manual system. (b) Push button and stow crank before operating electrically." f. Models 310Q and T310Q S/N 310Q0601 through 310Q1160, 310R, T310R (63 gal. auxiliary fuel system): (1) "Left main 50 gal. - left auxiliary 31.5 gal. - right main 50 gal. - left engine off." (2) "Right main 50 gal. - right auxiliary 31.5 gal. - left main 50 gal. - right engine off." (3) "Set fuel selector valve to left main tank for left engine and right main tank for right engine in takeoff, landing and emergency." (4) "Use main tanks for takeoff, landing and first 90 minutes of flight." (5) "Takeoff and land with auxiliary fuel pumps on. Use full rich mixture on 'low' when switching fuel ta nks. (Feel for detent.)" (6) "To extend gear manually, pull out crank to engage and turn clockwise. Caution: (a) Gear switch should be in neutral before operating manual system. (b) Push button and stow crank before operating electrically." 16. On engine control pedestal: a. Models 310R/T310R, S/N 310R0801 through 310R2140: If nacelle fuel transfer tanks are installed - "FUEL TRANSFER - 20 GAL - L - R - L ON R - EMPTY - OFF" NOTE 3. The following information sh all be provided in the form of markings, placards or manuals (Pilot's Check List): 1. Maximum takeoff flap setting 15°. 2. Maximum positive maneuvering load factor +3.8 g, flaps up; +2.0g, flaps extended, except for Model 310J-1 which has a load factor of +4.8g, flaps up. 3. Models 310, 310A, 310B, 310C, 310D, 310E, 31 0F, 310G, 310H, E310H, 310I, 310J, 310J-1, E310J, 310K, 310L, 310N, 310P, T310P: Maximum loss of altitude during normal stall recovery is 400 ft. and maximum pitch in power-off stall is 45°. 4. Loading schedule for the Model 310 airplane. 5. Maximum loss of altitude during normal stall reco very is 500 ft. for Model 310Q and 300 ft. for Model T310Q. 6. Maximum loss of altitude during normal stall recovery is 300 ft. for Model 310R and T310R. 3A10 44 Rev. 64 Data Pertinent to All Models NOTE 4. Special Accessory Kits for Foreign Certification 1. Models 310I, 310J, 310K, 310 L, 310N, 310P, 310Q: Aircraft with Accessory Kit AK 310-212 installed are restricted to operations at gross weights of 49 90 lbs. or less. The model designation will be altered by adding the prefix letter "E." 2. Model 310R: Aircraft with Accessory Kit AK 310-233 installed are restricted to operations at gross weights of 4990 lbs. or less. The model designati on will be altered by adding the prefix letter "E." 3. Models T310P, T310Q: Aircra ft with Accessory Kit AK 310-220 installed are restricted to operations at gross weights of 4990 lbs. or less. The model designation will be altered by adding the prefix letter "E." 4. Model T310R: Aircraft with Accessory Kit AK 310-234 installed are restricted to operations at gross weights of 4990 lbs. or less. The model designation will be altered by adding the prefix letter "E." NOTE 5. McCauley Propellers with 3AF32C87 or 3AF32C504 hubs may be interchanged in any combination. In addition to the placards specified above, the prescribed operating limitations indicated by an asterisk (*) under Sections I through XXIII of this data sheet must also be displayed by permanent markings. ----------- END ---------- ``` ## ADs (44, 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 2023-10-02](https://openairdocs.org/ad/2023-10-02): Indicating/Recording System, Navigation · Boeing 18, 23, 35 and 1,060 more. Effective May 26, 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 2016-17-08](https://openairdocs.org/ad/2016-17-08): Elevator Tab Control System · Textron 310, 310A, 310B and 46 more. Effective Sep 12, 2016 - [AD 2014-03-03](https://openairdocs.org/ad/2014-03-03): Placards and Markings · Cessna 310, 310A, 310B and 37 more. Effective Apr 7, 2014 - [AD 2005-25-08](https://openairdocs.org/ad/2005-25-08): Electronic Flight Information System (EFIS) · B-N Group BN-2A, 172, 180 and 22 more. Effective Jan 23, 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 2004-25-16 R1](https://openairdocs.org/ad/2004-25-16-R1): Fuel regulator shutoff valve · Bombardier CL-215-1A10, CL-215-6B11 (CL-215T Variant), CL-215-6B11 (CL-415 Variant) and 64 more. Effective Jun 20, 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 2004-21-05](https://openairdocs.org/ad/2004-21-05): B-Seires Combustion Heaters · Bombardier CL-215-1A10, CL-215-6B11 (CL-215T Variant), CL-215-6B11 (CL-415 Variant) and 41 more. Effective Nov 19, 2004 - [AD 98-21-21 R1](https://openairdocs.org/ad/98-21-21-R1): Electric Inflatable Door Seals · Cessna 17-30, 17-30A, 17-31 and 267 more. Effective May 1, 2000 - [AD 2000-01-16](https://openairdocs.org/ad/2000-01-16): Exhaust System · Cessna 320, 320-1, 320A and 28 more. Effective Feb 15, 2000 - [AD 98-25-02](https://openairdocs.org/ad/98-25-02): Top-mounted Antenna · Bell Helicopter Textron Canada 407, 172, 172A and 243 more. Effective Dec 22, 1998 - [AD 98-14-03](https://openairdocs.org/ad/98-14-03): Transponders · Cessna 172, 172A, 172B and 230 more. Effective Aug 16, 1998 - [AD 98-04-28](https://openairdocs.org/ad/98-04-28): AFM - Limitations Section - Icing · Cessna 310R, 335, 340A and 12 more. Effective Mar 13, 1998 - [AD 97-16-10](https://openairdocs.org/ad/97-16-10): Filters · Cessna 310R, T310R, 36 and 17 more. Effective Sep 18, 1997 - [AD 97-01-13](https://openairdocs.org/ad/97-01-13): Fuel, Oil and Hydraulic Hoses · Cessna 150, 150A, 150B and 232 more. Effective Feb 3, 1997 - [AD 96-12-22](https://openairdocs.org/ad/96-12-22): Full Flow Engine Oil Adapter · Bellanca CH-300 Pacemaker, 120, 140 and 361 more. Effective Jul 31, 1996 - [AD 90-02-13](https://openairdocs.org/ad/90-02-13): Main Landing Gear · Cessna 310, 310A, 310B and 40 more. Effective Feb 5, 1990 - [AD 87-21-02 R1](https://openairdocs.org/ad/87-21-02-R1): Fuel Filler Openings · Cessna 310D, 310E, 310F and 41 more. Effective Jun 16, 1989 - [AD 70-03-04 R1](https://openairdocs.org/ad/70-03-04-R1): Turbosupercharger Turbine Housing · Cessna 320D, 320E, 320F and 8 more. Effective Mar 28, 1987 - [AD 76-08-02 R2](https://openairdocs.org/ad/76-08-02-R2): Wing Tip Nose Cap · Cessna 310, 310A, 310B and 41 more. Effective Jan 31, 1983 - [AD 81-19-04](https://openairdocs.org/ad/81-19-04): Hose Assembly · Rajay Hose Assemblies, 500A, 500B and 87 more. Effective Sep 17, 1981 - [AD 72-14-08 R1](https://openairdocs.org/ad/72-14-08-R1): Flexible Hose Assemblies · Cessna 310, 310A, 310B and 33 more. Effective Sep 4, 1981 - [AD 81-15-03](https://openairdocs.org/ad/81-15-03): Engine Inlet Air Filters · Replace existing engine induction air filter (Brackett Aero Filters STC SA693CE or SA71GL). Effective Jul 20, 1981 - [AD 80-13-14](https://openairdocs.org/ad/80-13-14): Fuel Flow Transducer · Cessna 310R, 335, 340A and 4 more. Effective Jul 22, 1980 - [AD 78-05-06](https://openairdocs.org/ad/78-05-06): Flexible Fuel Cells · Cessna 180, 182, 185 and 98 more. Effective Jun 30, 1978 - [AD 78-11-05](https://openairdocs.org/ad/78-11-05): Autopilot Actuator · Cessna 210M, 310R, 340A and 9 more. Effective Jun 5, 1978 - [AD 76-04-03](https://openairdocs.org/ad/76-04-03): ARC PA-500A Actuators · Cessna 172L, 172M, 177B and 43 more. Effective Feb 26, 1976 - [AD 75-23-07](https://openairdocs.org/ad/75-23-07): Emergency Exit Window · Cessna 310Q, 310R, T310Q and 1 more. Effective Nov 13, 1975 - [AD 75-12-07](https://openairdocs.org/ad/75-12-07): Governors · Cessna 310P, 310Q and Governors. Effective Jun 6, 1975 - [AD 74-20-08](https://openairdocs.org/ad/74-20-08): Fire Procedures Checklist · Cessna 310, 310A and 310B. Effective Oct 1, 1974 - [AD 74-20-01](https://openairdocs.org/ad/74-20-01): Main Landing Gear Trunnion · Cessna 310Q, 340, 402B and 2 more. Effective Sep 25, 1974 - [AD 74-08-01](https://openairdocs.org/ad/74-08-01): Autopilot Servo Actuators · Aircraft Radio Autopilot Servo Actuators, 172L, 172M and 29 more. Effective Apr 9, 1974 - [AD 73-25-01](https://openairdocs.org/ad/73-25-01): Heater Fuel Pump Relay Relocation · Cessna 310I. Effective Dec 10, 1973 - [AD 73-07-07](https://openairdocs.org/ad/73-07-07): Fuel Hoses & Electrical Wiring Chafing · Cessna 310C, 310D, 310E and 19 more. Effective Apr 6, 1973 - [AD 73-01-02](https://openairdocs.org/ad/73-01-02): Alternate Air System · Cessna 310N, 310P and 310Q. Effective Jan 5, 1973 - [AD 72-03-07](https://openairdocs.org/ad/72-03-07): Landing Gear Failure · Cessna 310, 310A, 310B and 30 more. Effective Feb 9, 1972 - [AD 69-15-09](https://openairdocs.org/ad/69-15-09): Fuel Starvation · Cessna 310, 310A, 310B and 6 more. Effective Jul 25, 1969 - [AD 69-12-03](https://openairdocs.org/ad/69-12-03): Fuel Crossfeed Lines · Cessna 310, 310A, 310B and 4 more. Effective Jun 10, 1969 - [AD 57-04-01](https://openairdocs.org/ad/57-04-01): Aileron Hinge · Cessna 310, 310A, 310B and 15 more - [AD 69-14-01](https://openairdocs.org/ad/69-14-01): Fuel Starvation · Cessna 310G, 310H, 310I and 22 more - [AD 2016-07-24](https://openairdocs.org/ad/2016-07-24) (historical): Elevator Tab Control System · Textron 310, 310A, 310B and 46 more. Effective Apr 26, 2016 - [AD 75-23-08 R5](https://openairdocs.org/ad/75-23-08-R5) (historical): Engine Exhaust System · Cessna Aircraft Company, The 320 Model or Series (all), 340 Model or Series (all), 401 Model or Series (all) and 12 more. Effective Nov 4, 1986 ## Registered aircraft by registry model (OpenAirDocs) - [Cessna 310R](https://openairdocs.org/model/cessna-310r): 361 aircraft (registry code 2074245) - [Cessna 310Q](https://openairdocs.org/model/cessna-310q): 277 aircraft (registry code 2074242) - [Cessna T310R](https://openairdocs.org/model/cessna-t310r): 140 aircraft (registry code 2074246) - [Cessna 310](https://openairdocs.org/model/cessna-310): 103 aircraft (registry code 2074202) - [Cessna 310K](https://openairdocs.org/model/cessna-310k): 78 aircraft (registry code 2074228) - [Cessna 310L](https://openairdocs.org/model/cessna-310l): 62 aircraft (registry code 2074230) - [Cessna 310P](https://openairdocs.org/model/cessna-310p): 61 aircraft (registry code 2074238) - [Cessna 310I](https://openairdocs.org/model/cessna-310i): 60 aircraft (registry code 2074224) - [Cessna 310J](https://openairdocs.org/model/cessna-310j): 59 aircraft (registry code 2074226) - [Cessna 310C](https://openairdocs.org/model/cessna-310c): 58 aircraft (registry code 2074210) - [Cessna 310D](https://openairdocs.org/model/cessna-310d): 56 aircraft (registry code 2074212) - [Cessna 310N](https://openairdocs.org/model/cessna-310n): 55 aircraft (registry code 2074234) - [Cessna T310Q](https://openairdocs.org/model/cessna-t310q): 50 aircraft (registry code 2074244) - [Cessna 310B](https://openairdocs.org/model/cessna-310b): 45 aircraft (registry code 2074208) - [Cessna 310F](https://openairdocs.org/model/cessna-310f): 41 aircraft (registry code 2074216) - [Cessna 310G](https://openairdocs.org/model/cessna-310g): 41 aircraft (registry code 2074218) - [Cessna 310H](https://openairdocs.org/model/cessna-310h): 33 aircraft (registry code 2074220) - [Cessna T-310P](https://openairdocs.org/model/cessna-t-310p): 16 aircraft (registry code 2074240) - [Cessna 310A](https://openairdocs.org/model/cessna-310a): 14 aircraft (registry code 2074204) - [Cessna 310E](https://openairdocs.org/model/cessna-310e): 6 aircraft (registry code 2074214) - [Cessna E310H](https://openairdocs.org/model/cessna-e310h): 1 aircraft (registry code 2074222) - [Cessna 310-J1](https://openairdocs.org/model/cessna-310-j1): 0 aircraft (registry code 2073014) ## STCs approved under this data sheet (471, 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 SA01844WI](https://openairdocs.org/stc/SA01844WI): Installation of Garmin GFC 600 Automatic Flight Control System. Garmin International Inc. - [STC SA02279AT](https://openairdocs.org/stc/SA02279AT): Installation of a Boom Beam bulb, starter, and ballast. Whelen Aerospace Technologies - [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 SA04652CH](https://openairdocs.org/stc/SA04652CH): To allow use of 100R grade aviation fuel meeting Swift Fuel, LLC specification. Swift Fuels LLC - [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 SA800EA](https://openairdocs.org/stc/SA800EA): Installation of Whelen Anti-Collision, Position, or Anti-Collision/Position Light System, and applicable associated power supplies. Whelen Aerospace Technologies - [STC SA00079NY](https://openairdocs.org/stc/SA00079NY): Installation of Airwolf remote mounted engine oil filter kit AFC-K008 on single and multi engine fixed wing light aircraft incorporating Teledyne Continental reciprocating engines of 450 horsepower or less.. Airwolf Filter Corporation - [STC SA02511SE](https://openairdocs.org/stc/SA02511SE): Installation of replacement fuel quantity indicator sending unit(s). CiES Inc. - [STC SA5581SW](https://openairdocs.org/stc/SA5581SW): Installation of ALCOR true-flow/ totalizer system. Alcor LLC - [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 SA04568CH](https://openairdocs.org/stc/SA04568CH): Installation of the uAvionix tailBeaconX, a tail mounted position light with integrated Automatic Dependent Surveillance - Broadcast (ADS-B) Out and 1090MHz Mode-S transponder functionality. uAvionix Corporation - [STC SA02658SE](https://openairdocs.org/stc/SA02658SE): Installation of Garmin GI 275 Multi-Function Display System. Garmin International Inc. - [STC SA00040LB](https://openairdocs.org/stc/SA00040LB): Installation of a modified exhaust tail pipe.. Aerospace Welding Minneapolis Inc. - [STC SA02532AT](https://openairdocs.org/stc/SA02532AT): Installation of subject Michelin tires on appropriate aircraft. For Michelin 5, 6, 8, and 10-inch rim diameter tires on General Aviation Aircraft.. Michelin North America Inc. - [STC SA181SO](https://openairdocs.org/stc/SA181SO): Installation of Turbosupercharged Continental IO-470- U engines. TALCO Aviation - [STC SA2383WE](https://openairdocs.org/stc/SA2383WE): Installation of turbocharged Continental IO-470-D engine. TALCO Aviation - [STC SA294SO](https://openairdocs.org/stc/SA294SO): Installation of turbocharged Continental I0-470-D engines. S. TALCO Aviation - [STC SA348WE](https://openairdocs.org/stc/SA348WE): Installation of air induction system in accordance with FAA Sealed Rajay Drawing list No. RJ1039.. TALCO Aviation - [STC SA385WE](https://openairdocs.org/stc/SA385WE): Installation of turbocharged Lycoming IO-540-A1A5 engines. TALCO Aviation - [STC SA574WE](https://openairdocs.org/stc/SA574WE): Installation of landing gear position mirror on left wing tip tank. TALCO Aviation - [STC SA97SO](https://openairdocs.org/stc/SA97SO): A, B, or C of turbocharged Continental IO-470-D engines.. TALCO Aviation - [STC SA02019WI](https://openairdocs.org/stc/SA02019WI): Installation of the Trig Avionics TX56, TX56A, TX57, or TX57A VHF Nav-Com Radio.. Peregrine - [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 SA1686WE](https://openairdocs.org/stc/SA1686WE): Installation of Vibration Isolation Products (VIP) engine mount P/Ns VIP 50525-1 and VIP 50545-1 on various aircraft as shown on FAA Approved Model List (AML) No. SA1686WE.. FTG, Inc. - [STC SA111GL](https://openairdocs.org/stc/SA111GL): Install Cleveland conversion kit P/N 199-64.. Kaman Corporation Aircraft Wheel and Brake LLC - [STC SA01967WI](https://openairdocs.org/stc/SA01967WI): Use of GAMI G100UL High Octane Unleaded Avgas. General Aviation Modifications Inc. - [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 SA04466NY](https://openairdocs.org/stc/SA04466NY): Installation of an externally mounted exhaust silencer system. ACC Columbia Jet Service GmbH - [STC SA4222SW](https://openairdocs.org/stc/SA4222SW): Mount collision avoidance lights in engine nacelle.. Johnson Aviation Products - [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 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 SA04182NY](https://openairdocs.org/stc/SA04182NY): Installation of BendixKing KA 310 Autopilot Adapter. Honeywell International Inc - [STC SA02426AK](https://openairdocs.org/stc/SA02426AK): Approval of the FreeFlight FDL-978-TX ADS-B system installed. FreeFlight Systems All 471: https://openairdocs.org/tcds/3A10/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.