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Piper Clipper

Aircraft Specs & Performance


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Aircraft Specs
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General Info
Category Antique / Classic
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.
102 kts
Max Range
Max Range as indicated by the manufacturer under optimal conditions.

See Cruise & Mission performance for examples of range capabilities.
410 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.
850 lbs 385.55 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).
600 lbs 272.16 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 800 lbs 362.87 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.
384 lbs 174.18 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.
10.00 gal / 60 lbs 37.85 L / 27.22 kg
Max Fuel 30.00 gal / 180 lbs 113.56 L / 81.65 kg
Usable Fuel 29.50 gal / 177 lbs 111.67 L / 80.29 kg
Wing Loading
Is computed using the Max Takeoff Weight (MTOW) divided by the total wing area.
11.20 lbs / ft2 16.67 kg / m2
Power Loading
Power Loading is calculated using the Max Takeoff Weight (MTOW) divided by total rated thrust / horsepower.
14.30 lbs / hp 6.49 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.
1,650 lbs 748.43 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.
1,650 lbs 748.43 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.
1,650 lbs 748.43 kg
External Dimensions
External length, height and span dimensions are provided for use in determining hangar and or tie-down space requirements.
Length 20 ft 1 in 6.12 m
Height 6 ft 2 in 1.88 m
Wingspan 29 ft 6 in 8.99 m
Wing Area 148.00 ft2 45.11 m2
Baggage Capacity
Interior Weight 50 lbs 22.68 kg
Engine / Propeller
Engine Info
Manufacturer Textron Lycoming
Model O-235
Engine Piston
Fuel Type 100LL
Thrust / Horse Power
Is the takeoff rated pounds of thrust for jet/turbofan aircraft and horsepower for propeller driven aircraft.

If an engine is flat rated, enabling it to produce take off rated output at higher than International Standard Day Atmospheric conditions (ISA), ambient temperature, the flat rating limit is shown as ISA +XX'C. Highly flat rated engines, typically provide substantially improved high-density altitude and high-altitude cruise performance.
112
Number of Cylinders 4
Inspection Interval
The longest scheduled hourly major maintenance interval for the engine, either Time Before Overhaul (TBO), or Compressor Zone Inspection (CZI). OC (on condition) is shown only for engines that have "on condition" repair or replacement parts maintenance. On Condition repair or replacement parts maintenance is performed when an inspector deems it necessary rather than after a pre-specified hourly use.
2

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.
102 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.
97 kts
Max Range
Max Range as indicated by the manufacturer under optimal conditions.

See Cruise & Mission performance for examples of range capabilities.
410 NM
V Speeds:
Speed Vso 45 kts
Speed Vs 45 kts
Speed Vx 65 kts
Speed Vy 71 kts
Speed Va 94 kts
Speed Vno 102 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 2,000 ft 609.60 m
Landing Distances
Is the shortest distance an aircraft can descend, land and come to a complete stop. Where applicable, landing distance is computed for airplanes to clear a 50' obstruction. For larger aircraft, a mid-weight mission is used for computation.
Sea Level, ISA 1,600 ft 487.68 m
Climb Performance / Ceilings
Climb 600 fpm 182.88 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.
20 / 10,000 min / ft 20 / 10,000 min / m
Certified Ceiling
Maximum allowable operating altitude determined by airworthiness authorities.
11,000 ft 3,352.80 m
Cruise Performance at 5,000 ft
Recommended
Speed / Power 97 kts / 75 %
Fuel Flow 7.00 gal / 42 lbs 26.50 L / 19.05 kg
Range 330 NM
Altitude 5,000 ft 1,524.00 m

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