Cessna 310R

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In the FlightDecide app since 2026-07-16. Reviewed 2026-09-28. 6 of 7 tables from the handbook. Anything marked “Not yet verified against the handbook” comes from FlightDecide's earlier library and hasn't been checked against the printed page.

Cessna 310R preflight numbers at a glance: max gross weight 5500 lb, typical useful load 2000 lb, 163 gal usable fuel, cruise up to about 205 KTAS (reference figure at 10,000 ft, standard day). 6 of the 7 performance tables below are read from the published POH/AFM and cite their figure and page; treat the ones marked “Not yet verified against the handbook” as estimates. Use them for planning and study, and confirm against the POH for your specific serial number before flight.

Cessna 310R specs and key numbers

Not yet verified against the handbook

Cessna 310R V-speeds

Not yet verified against the handbook

Knots indicated (KIAS) unless the POH states otherwise. Speeds vary by model year and serial; the placarded speeds and your POH govern.

Cessna 310R cruise performance

Not yet verified against the handbook

Source not verified: the library's record cites no handbook page for these rows. True airspeed and fuel flow depend on altitude, power setting, temperature, and leaning technique.

Standard-day (ISA) rows shown, sampled across the POH table for readability; the FlightDecide app carries the full digitized table, including non-standard temperatures.

How much runway does a Cessna 310R need?

Handbook figures at 5500 lb, 0 ft pressure altitude, 20 °C. Real-world technique, wind, surface, and density altitude move these substantially, so apply your own margin (many pilots use 1.5× the book number) and run the numbers for the actual conditions.

See how density altitude stretches these distances on a hot day.

Takeoff distance

Full throttle and 2700 RPM before brake release, mixtures leaned for field elevation, wing flaps up, cowl flaps open, level hard surface dry runway

Source: Pilot's Operating Handbook, Cessna Aircraft Company, 1976 Model 310R · P/N D1528-4-13 · Figure 5-10 (Sheet 2 of 2) · Normal Takeoff Distance · page 5-23

from the handbook   extrapolated beyond the handbook

• If full power is applied without brakes set, distances apply from the point where full power is applied.
• Decrease distance 7% for each 10 knots headwind.
• Increase distance 5% for each 2 knots tailwind.
• Increase total distance 7.9% for operation on a firm dry sod runway.
• Takeoff speed to the 50 foot obstacle: 92 KIAS at 5500 lb, 88 KIAS at 5100 lb, 85 KIAS at 4700 lb, 81 KIAS at 4300 lb.
• These are the 20, 30 and 40 degree C columns, which are sheet 2 of the figure. Sheet 1 (printed page 5-22, PDF page 132) prints -20, -10, 0 and 10 degree C for the same four weights and eleven altitudes and is not carried here.
• The 5500 lb block stops at 9000 ft. The handbook prints a 10,000 ft row for it (5410/7640 at 20 C, 5880/8720 at 30 C, 6390/10,270 at 40 C), but 10,270 is printed with a thousands separator that the extractor's numeric pattern does not accept, which would leave a half-read pair, so that row is clipped out of the sheet rather than published half-read. The other three weights carry their 10,000 ft rows.

Landing distance

Throttles idle, landing gear down, wing flaps 35 deg, cowl flaps closed, level hard surface runway, maximum braking effort

Source: Pilot's Operating Handbook, Cessna Aircraft Company, 1976 Model 310R · P/N D1528-4-13 · Figure 5-26 (Sheet 2 of 2) · Normal Landing Distance · page 5-43

from the handbook   extrapolated beyond the handbook

• Increase distance by 25% of the ground run for operation on a firm sod runway.
• If it is necessary to land with wing flaps up, increase the approach speed 12 knots above the normal approach speed and expect total landing distance to increase by 35%.
• Decrease total distances by 3% for each 4 knots headwind. For tailwinds up to 10 knots, increase total distances by 5% for each 2 knots of wind.
• Speed at the 50 foot obstacle: 93 KIAS at 5400 lb, 89 KIAS at 5000 lb, 86 KIAS at 4600 lb, 82 KIAS at 4200 lb.
• The landing weights stop at 5400 lb because that is the maximum landing weight printed under WEIGHT LIMITS on printed page 2-5 (PDF page 25). 5500 lb is the takeoff limit.
• These are the 20, 30 and 40 degree C columns, which are sheet 2 of the figure. Sheet 1 (printed page 5-42, PDF page 152) prints -20, -10, 0 and 10 degree C for the same four weights and eleven altitudes and is not carried here.

Rate of climb

2500 RPM and 24.5 inches Hg, landing gear up, wing flaps up, cowl flaps as required, 120 KIAS, mixtures at the recommended fuel flow. The handbook footnotes this figure "above 5200 feet, use full throttle": below that height the engines are throttled to hold 24.5 inches, so power stays put while drag falls with the air, and the rate of climb RISES with altitude up to about 5000 ft before falling away

Source: Pilot's Operating Handbook, Cessna Aircraft Company, 1976 Model 310R · P/N D1528-4-13 · Figure 5-15 · Rate-of-Climb - Cruise Climb · page 5-29

from the handbook

• Above 5200 feet, use full throttle.
• This is the CRUISE climb, at 2500 RPM and 120 KIAS, not the maximum-rate climb. It is the only rate of climb this handbook prints as a table. Rate-of-Climb Maximum Climb (Figure 5-14, printed page 5-28) and Rate-of-Climb Single Engine (Figure 5-16, printed page 5-30) are both carpet charts of curves, so neither can be transcribed here. Cruise climb is the slower of the two, so a climb figure read from this table is never higher than the maximum-climb figure the same handbook publishes.
• Rate of climb RISES from sea level to 5000 ft in every column of this table, then falls. That is the aeroplane, not a misread: at a fixed 24.5 inches Hg the engines make more power as exhaust back pressure drops, up to the roughly 5200 ft full-throttle altitude named in the conditions. The extractor's monotonicity check expects a climb table to fall in both axes, so it reports 102 altitude-direction reversals on this figure. All 102 sit in the sea level to 5000 ft band, the temperature direction is clean everywhere, and every cell was checked against the printed page.

Stall speeds

Throttles idle, 5500 lb gross weight. Gear up at flaps 0 deg; gear down at flaps 15 deg and 35 deg

Source: Pilot's Operating Handbook, Cessna Aircraft Company, 1976 Model 310R · P/N D1528-4-13 · Figure 5-8 · Stall Speeds · page 5-20

• Maximum altitude lost during a stall is 300 feet. (page 5-20)
• Maximum pitch in power-off stall is 10°. (page 5-20)

Common Questions

Plan a flight in this aircraft

Reference data for planning and study: approximate, and not a substitute for the FAA-approved AFM/POH for your specific aircraft, an official weather briefing, or your judgment as pilot in command (14 CFR 91.3). Source: Cessna 310R Pilot's Operating Handbook, Cessna Aircraft Company Data synced from the FlightDecide aircraft library on 2026-09-28.