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Piper Cherokee 160

Aircraft Specs & Performance


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Aircraft Specs
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General Info
Category Single Engine Piston
Seating
Crew + Typical Seating / Maximum Seating. For example, 2 + 6 / 9 indicates that the aircraft requires two pilots, there are six seats in the typical cabin configuration and the aircraft is certified for up to 9 passenger seats.

A six place single or multi-engine is shown as 1 + 5 / 5 indicating that one pilot is required and there are five other seats available for passengers in a normal cabin configuration.

See Guide To Specs for more info.
1 + 3 / 3
Top Speed
The top speed as determined by the manufacturer under optimal conditions and flown by an expert test pilot.

This speed will vary from aircraft to aircraft based on equipment, flight conditions and pilot abilities.
120 kts
Max Range
Max Range as indicated by the manufacturer under optimal conditions.

See Cruise & Mission performance for examples of range capabilities.
440 NM
URL www.piper.com
Weights & Dimensions
Weights:
Basic Operating Weight
Empty Weight (EW) is shown for Piston powered airplanes.

Basic Operating Weight (BOW) is shown for turbine powered airplanes. BOW is the empty weight of the aircraft, plus 200 lbs for each required crewmember. This does not include unusable fuel and oil.

BOW is based on the average EW for current production aircraft and is interpolated as accurate as possible for out of production aircraft. For Ultra Long Range aircraft, Crew = 3 pilots and 1 cabin attendant.

Please see the Guide To Specifications for more detail.
1,575 lbs 714.41 kg
Max Payload
Jet & Turboprop Aircraft - Zero fuel weight minus Basic Operating Weight (BOW).

For piston engine airplanes, weight shown here is calculated by subtracting 200 pounds from the Useful Load for the pilot and supplies. (Useful Load minus Pilot @ 200 lbs = Max Payload).
625 lbs 283.50 kg
Passenger Payload
Based on 180 pounds per occupant for Piston aircraft and 200 pounds per occupant for turbine engine airplanes.

If the passenger payload exceeds the maximum payload, we use the maximum payload weight.

Pilots and crew are not counted as occupants.
540 lbs 244.94 kg
Useful Load 825 lbs 374.21 kg
Avail. Payload/Max Fuel
The maximum ramp weight minus the tanks full weight, (not to exceed zero fuel weight) minus Basic Operating Weight.

For light aircraft, it is the Max Payload minus the full fuel weight.
574 lbs 260.36 kg
Avail. Fuel/Max Payload
Jet & Turboprop Aircraft - Maximum Ramp Weight minus Basic Operating Weight, not to exceed Zero Fuel Weight or maximum fuel capacity.
14.17 gal / 85 lbs 53.63 L / 38.56 kg
Max Fuel 36.00 gal / 216 lbs 136.27 L / 97.98 kg
Usable Fuel 34.00 gal / 204 lbs 128.70 L / 92.53 kg
Wing Loading
Is computed using the Max Takeoff Weight (MTOW) divided by the total wing area.
15.00 lbs / ft2 22.32 kg / m2
Power Loading
Power Loading is calculated using the Max Takeoff Weight (MTOW) divided by total rated thrust / horsepower.
13.30 lbs / hp 6.03 kg / hp
Max Ramp Weight
The maximum allowable weight of the aircraft to be considered airworthy including fuel required for taxi.

Max ramp, takeoff and landing weights may be the same for light aircraft that only have a certificated max takeoff weight.
2,400 lbs 1,088.62 kg
Max Takeoff Weight
(MTOW) The maximum weight that the aircraft has shown to meet all airworthiness requirements. MTOW is fixed and does not vary with altitude or air temperature.

Max ramp, takeoff and landing weights may be the same for light aircraft that on may only have a certificated max takeoff weight.
2,400 lbs 1,088.62 kg
Max Landing Weight
Max Landing Weight is determined by structural limits and is the maximum weight for an aircraft to land.

Max ramp, takeoff and landing weights may be the same for light aircraft that on may only have a certificated max takeoff weight.
2,400 lbs 1,088.62 kg
External Dimensions
External length, height and span dimensions are provided for use in determining hangar and or tie-down space requirements.
Length 23 ft 6 in 7.16 m
Height 7 ft 4 in 2.24 m
Wingspan 30 ft 0 in 9.14 m
Wing Area 160.00 ft2 48.77 m2
Baggage Capacity
Interior Volume
Volume of internal baggage compartment and typical weight capacity.
17 ft3 5.18 m3
Interior Weight 200 lbs 90.72 kg

Performance Specs
Speeds
Top Speed
The top speed as determined by the manufacturer under optimal conditions and flown by an expert test pilot.

This speed will vary from aircraft to aircraft based on equipment, flight conditions and pilot abilities.
120 kts
Cruise Speed
Crusie Speed as determined by the manufacturer under optimal conditions and flown by an expert test pilot.

This speed will vary from aircraft to aircraft based on equipment, flight conditions and pilot abilities.
109 kts
Max Range
Max Range as indicated by the manufacturer under optimal conditions.

See Cruise & Mission performance for examples of range capabilities.
440 NM
V Speeds:
Speed Vso 58 kts
Speed Vs 50 kts
Speed Vx 64 kts
Speed Vy 74 kts
Speed Va 112 kts
Takeoff Distances
Is the shortest ground distance, measured in feet, for an aircraft to accelerate and liftoff. Where applicable, takeoff distance is computed for airplanes to clear a 50' obstruction.

Aviation regulations, (for large aircraft) require the takeoff distance to be less than, or equal to the available runway length, both with and without an engine failure assumed.
Sea Level, ISA 1,750 ft 533.40 m
Accelerated Stop Distances
The distance of runway length needed for an aircraft to accelerate to rotation speed and then come to a complete stop if unable or the decision is made to abort the takeoff. The distance is shown for multi-engine piston and turboprop airplanes.

Takeoff Field Length (TOFL), which is the greater of the one-engine inoperative (OEI) takeoff distance or the accelerated stop distance is shown for Part 23 and 25 airplanes. If the accelerated stop and the OEI are equal, the TOFL is the balanced field length.
Sea Level, ISA 1,400 ft 426.72 m
Climb Performance / Ceilings
Climb 700 fpm 213.36 mpm
Min. To Altitude
Provides an indication of overall climb performance, especially if the aircraft has an all-engine service ceiling well above sample top-of-climb altitudes shown here and in the cruise section of performance specs. The all-engine time to climb to a specific altitude is shown, based on type of aircraft, departing at Max Total Operating Weight (MTOW) from a sea level, standard day airport.

We provide the all engine time to climb to specific altitudes based on the type of aircraft.

10,000 feet for normally aspirated (non turbocharged) single and multi engine piston aircraft, pressurized single engine piston and non pressurized turboprop; 25,000 feet for pressurized single and multiengine turboprops; 37,000 feet for turbofan powered aircraft.

The data is published as time-to-climb in minutes to the designated altitude. Exp: If it takes 9 minutes to climb to 10,000 feet, it will be shown as 9 / 10,000.
28 min / 10,000 ft 28 min / 3,048.00 m
Certified Ceiling
Maximum allowable operating altitude determined by airworthiness authorities.
13,000 ft 3,962.40 m
Cruise Performance at 7,000 ft
Speed / Power 114 kts / 75 %
Fuel Flow 9.00 gal / 54 lbs 34.08 L / 24.50 kg
Range 288 NM
Altitude 7,000 ft 2,133.60 m
Payload / Fuel
560 lbs / 254.01 kg / 0.00 lb/gal 0.00 kg/L

ClassG and MyWings are registered
service marks of ClassG, LLC.