Malibu Mirage

PERFORMANCE SPECIFICATIONS

ENGINE
Manufacturer
Model
Horsepower
Number of Cylinders

Lycoming
TIO-540-AE2A
350 hp
6

PROPELLER
Manufacturer
Number of Blades
Type

Hartzell
3
Constant Speed

WEIGHTS
Maximum Takeoff Weight
Standard Empty Equipped Weight (b and c)
Standard Useful Load (a)

4340 lbs/1969 kg
3120 lbs/1415 kg
1220 lbs/553 kg

DIMENSIONS
Wing Span
Length
Height
Wing Area
Cabin Length
Cabin Width
Cabin Height
HEADROOM (Seat to Ceiling)
Front Seats
Middle Seats
Rear Seats

43 ft/13.1 m
28.9 ft/8.8 m
11.3 ft/3.4 m
175 ft²/16.25 m²148 in/375.9 cm
49.5 in/125.7 cm
47.0 in/119.4 cm

38 in/96.5 cm
38 in/96.5 cm
37 in/94.0 cm

FUEL and OIL CAPACITY
Usable Fuel
Oil Capacity

BAGGAGE
Forward Compartment Capacity
Aft Compartment Capacity

120 gallons/454 liters
12 quarts/ 11.4 liters

100 lbs/45.4 kgs
100 lbs/45.4 kgs

MAXIMUM SPEED
TAS at mid-cruise weight
CRUISING SPEEDS
High Speed Cruise Power (TAS)
(Mid cruise weight, optimum altitude)
CRUISING RANGE
Long Range Cruise Power(IAS)
Cruising range includes 45 minute fuel reserve at long range power plus allowance for fuel used during taxi, take-off, climb at MCP, cruise at stated mixture and descent.

220 knots/408 km/h

213 knots/408 km/h

1345 nm/2491 km

STALL SPEED
Flaps Down Full 36 °
SERVICE CEILING
100fpm
MAX DIFFERENTIAL PRESSURE
5.5 psid
TAKE-OFF DISTANCE
Ground Roll
Over 50 ft Obstacle (Flaps 20° Gross Weight)
LANDING DISTANCE
Ground Roll
Total over 50 ft Obstacle

58 knots/107 km/h

25,000 ft+/7620 m+

1,090 ft/332 m
2,090 ft/637 m

1,020 ft/311 m
1,960 ft/597 m

a. Standard useful load is maximum takeoff weight minus standard equipped weight.
b. The standard empty weight and standard equipped weight are the same.
c. Standard equipped aircraft.

25,000 ft is the maximum approved altitude.

Malibu Mirage
PERFORMANCE SPECIFICATIONS
ENGINE Manufacturer Model Horsepower Number of Cylinders	Lycoming TIO-540-AE2A 350 hp 6
PROPELLER Manufacturer Number of Blades Type	Hartzell 3 Constant Speed
WEIGHTS Maximum Takeoff Weight Standard Empty Equipped Weight (b and c) Standard Useful Load (a)	4340 lbs/1969 kg 3120 lbs/1415 kg 1220 lbs/553 kg
DIMENSIONS Wing Span Length Height Wing Area Cabin Length Cabin Width Cabin Height HEADROOM (Seat to Ceiling) Front Seats Middle Seats Rear Seats	43 ft/13.1 m 28.9 ft/8.8 m 11.3 ft/3.4 m 175 ft²/16.25 m²148 in/375.9 cm 49.5 in/125.7 cm 47.0 in/119.4 cm 38 in/96.5 cm 38 in/96.5 cm 37 in/94.0 cm
FUEL and OIL CAPACITY Usable Fuel Oil Capacity BAGGAGE Forward Compartment Capacity Aft Compartment Capacity	120 gallons/454 liters 12 quarts/ 11.4 liters 100 lbs/45.4 kgs 100 lbs/45.4 kgs
MAXIMUM SPEED TAS at mid-cruise weight CRUISING SPEEDS High Speed Cruise Power (TAS) (Mid cruise weight, optimum altitude) CRUISING RANGE Long Range Cruise Power(IAS) Cruising range includes 45 minute fuel reserve at long range power plus allowance for fuel used during taxi, take-off, climb at MCP, cruise at stated mixture and descent.	220 knots/408 km/h 213 knots/408 km/h 1345 nm/2491 km
STALL SPEED Flaps Down Full 36 ° SERVICE CEILING 100fpm MAX DIFFERENTIAL PRESSURE 5.5 psid TAKE-OFF DISTANCE Ground Roll Over 50 ft Obstacle (Flaps 20° Gross Weight) LANDING DISTANCE Ground Roll Total over 50 ft Obstacle	58 knots/107 km/h *25,000 ft+/7620 m+ 1,090 ft/332 m 2,090 ft/637 m 1,020 ft/311 m 1,960 ft/597 m
a. Standard useful load is maximum takeoff weight minus standard equipped weight. b. The standard empty weight and standard equipped weight are the same. c. Standard equipped aircraft. *25,000 ft is the maximum approved altitude.