C210 Performance Specifications and Limitations
CESSNA TURBO 210L · Performance Data
Overview
This document provides performance specifications and limitations for the Cessna 210 series aircraft. It includes critical data on weight limits, engine specifications, fuel capacity, and various speed limitations. The figures are averages and may vary between different models within the Cessna 210 series. Pilots are advised to confirm specific performance and operating requirements in the Aircraft Flight Manual (AFM) before flying. The document serves as a reference for pilots to understand the operational capabilities and limitations of the aircraft, ensuring safe and efficient flight operations.
- Gross weight limits range from 3400 lbs to 4100 lbs.
- Maximum landing weight is between 3400 lbs and 3900 lbs.
- Engine power ranges from 285 BHP to 325 BHP depending on the model.
- Never Exceed Speed (Vne) is 175-225 knots.
- Clean stall speed (Vs) is 70-75 knots.
Document
Source
Originally published by www.aeroelectric.com. Sprinkle hosts a reference copy with an added summary, specifications and searchable full text.
Document details
- Type
- Performance Data
- Pages
- 4
- File size
- 54 KB
- Publisher
- www.aeroelectric.com
Specifications & performance
Extracted from this document.
Specifications
- Engine (hp)
- 325
- Engine model
- Lycoming IO-520 series
- Max speed (kt)
- 225
- Fuel capacity (gal)
- 87
- Max takeoff weight (lb)
- 4,100
Performance
- Max crosswind (kt)
- 15
- Stall speed clean (kt)
- 75
- Stall speed landing (kt)
- 65
V-speeds
- VX
- 75
- VY
- 90
- VNE
- 225
- VNO
- 210
- VSO
- 60
Weight & balance
- Baggage allowance (lb)
- 200
- Basic empty weight (lb)
- 2,150
- Max landing weight (lb)
- 3,900
- Max takeoff weight (lb)
- 4,100
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In this document
Structural Limitations
The document outlines the gross weight limits for take-off and landing, ranging from 3400 lbs to 4100 lbs. The maximum landing weight is specified as between 3400 lbs and 3900 lbs, while the standard empty weight varies from 2150 lbs to 2500 lbs. Baggage allowances are detailed, with a maximum of 120-200 lbs in the aft compartment and additional allowances for specific configurations.
Engine Specifications
The Cessna 210 is equipped with Lycoming engines, with maximum power outputs ranging from 285 BHP to 325 BHP depending on the engine model. The document specifies oil capacity requirements and fuel specifications, including a usable fuel capacity of 87 USG for standard tanks and 115 USG for optional long-range tanks.
Maximum Speeds
The document lists critical speed limitations, including a Never Exceed Speed (Vne) of 175-225 knots and a Maximum Structural Cruise Speed (Vno) of 170-210 knots. It also details flap limitation speeds and gear operating speeds, which vary by model.
Stall Speeds
Stall speeds are provided for clean and landing configurations, with clean stall speeds ranging from 70-75 knots and landing configuration stall speeds from 60-65 knots.
Performance for Normal Operations
Normal take-off procedures are outlined, including a recommended rotation speed of 55 knots and an acceleration speed of 90 knots after clearing obstacles. Climb speeds and approach speeds are also specified, ensuring pilots have clear guidance for various phases of flight.
Safety notes
- Always confirm performance and operating requirements in the AFM before flying.
- Do not operate on less than 7 quarts of oil for turbo engines.
Full document text
C210 Performance Specifications and Limitations Performance figures given at MAUW and speeds in KIAS unless specified otherwise. Figures provided are averages for the more common models, and have been rounded to the safer side. Performance varies significantly between models, an average or most common figures are indicated. REMEMBER these figures may not correspond to those for your particular model, ALWAYS Confirm performance and operating requirements in the AFM before flying. Structural Limitations Gross weight (take-off and landing) 3400lbs - 4100lbs Maximum landing weight 3400lbs - 3900lbs Standard empty weight 2150lbs - 2500lbs Max Baggage allowance in aft compartment 120-200lbs Baggage on Folded down 5/6th seat 120lbs Rear Compartment with Seat Removed 50lbs Flight load factor (flaps up) +3.8g – -1.52g Flight load factor (flaps down) +2.0g – 0g Engine Specifications Max – 5 minutes only Max Continuous Engine (Lycoming IO-520 series) power 300BHP at 2850RPM 285BHP at 2700RPM Engine (Lycoming TSIO-520 series) power 310BHP at 2700RPM 285BHP at 2600rpm Engine (Lycoming TSIO-520 series) power 325BHP at 2700 rpm, (flat rated) maximum continuous Oil capacity 10Qts normally aspirated engines, 11Qts Turbo and External Filter engines Do not operate on less than 7Qts minimum Fuel Usable fuel Standard tanks 87USG/ 329litres/534lbs Optional Long range 115USG Fuel Optional Tip tanks Additional in each Tip Tank 16 USG/60 litres Filler cap qty 64USG/ 384lbs Landing Gear Pressure Main wheel tyre pressure 55 psi Nose wheel tyre pressure 50 psi or 88psi depending on type (refer manual) Nose Strut Pressure 90psi Maximum Speeds Never Exceed Speed, (Vne) 175-225kts (200-260mph) (top red line) Maximum structural cruise speed (Vno)* 170-210kts , (195-240mph) (top of green arc) Maximum demonstrated crosswind component** 15kts (20mph) Maximum manoeuvering speed (Va) 115-135 kts (135 – 155 mph) *May not be exceeded unless in smooth air conditions **Late models only Flap Limitation Speeds: Note: speeds vary significantly with models. Early models 0-10 degrees 140kts (160mph) (Placarded on Flap Lever) Early models 10-30 degrees 10-30 105kts (120mph) (top of white arc) Later models 0-10 degrees 0-10 150-160kts (175-185mph) (Placarded on Flap Lever) Later models 10-20 degrees 10-20 130kts (160mph) (Placarded on Flap Lever) Later models 20-30 degrees 20-30 115kts (120mph) (top of white arc) Gear Limitation Speeds Gear Operating 135-165kts (165-190mph) Depending on model Gear Down 135-200kts (165-230mph) Stall Speeds Stall speed, clean (Vs) 70-75kts (80-85mph) (bottom of green arc) Stall speed, landing config. (Vso) 60-65kts (70-75mph) (bottom of white arc) Performance for Normal Operations Takeoff Normal take-off, flaps up Raise nose at 55kts (60mph), Accelerate 90mph once obstacle cleared Short field take off, Flaps 10º 50ft 75kts, (85mph)* accelerate 80kts, (90mph) before retracting flaps Clear of Obstacles accelerate to Vy Fuel Placard – Takeoff Fuel flow 2850RPM 2700RPM Sea Level 144lbs/hr 138lbs/hr 4000ft 132lbs/hr 126lbs/hr 120lbs/hr 114lbs/hr 92kts (102mph) Sea level 97kts (109mph) 10,000ft Best Angle of Climb Speed (Vx) 75kts (90mph) Normal climb out speed Initial 90-100kts, (100-115mph) Enroute kts, (120-140mph) or as req'd for performance Normal approach flaps 30º 75-85kts, (90-100mph) Normal approach flaps up 80-90kts, (95-105mph) Short field landing 75kts, (90mph) * See more on short field performance and speeds in the Normal Operations section Speeds for Emergency Operation Engine Failure after take-off 85kts (100mph) Forced landing 3000lbs 75kts (85mph) flap up 3400lbs 80kts (90mph) flap up 3800lbs 85kts (100mph) flap up Precautionary landing 85kts (100mph) flap up 75kts (90mph) full flap Cruise Performance* (Continental IO520 series 300hp engines, C210 Centurion) Cruise at 5000ft pressure altitude 2400 RPM 23”MP, 148KTAS, 83lbs/hr Cruise at 10,000ft pressure altitude 2400RPM, 21”MP, 154KTAS, 79lbs/ hr Block Planning Figures** Block Cruises, recommended performance (Planning) 2400RPM, 23” or available MP 145kts TAS 60lt/hr / 100lbs/hr 4hours safe endurance+reserve Recommended Minimum Field Length (Planning) 700m Sea Level 900m Above 3000ft Density Altitude *Cruise figures provided from the pilots operating handbook should be used with a contingency factor, block cruises speed and fuel flow allow for contingency and for climb and descent, and are normally applied for planning purposes. **Where field/operations approach these margins performance figures should be consulted to confirm performance
What's in the CESSNA TURBO 210L TCDS
A Type Certificate Data Sheet (TCDS) is the FAA's record of what an aircraft type was approved as. It is the source of truth for weights, seating, fuel and the rules the design was certified against. Expand any line to see what it means.
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