EP Sim

Engine Manufacturer

Lycombing

Engine Model

IO-360-B4A

Takeoff Power

180 HP

Max RPM

2700

Engine Displacement

361

Engine Type

Four Cylinder, Direct Drive, Horizontally Opposed with Fuel Injection

Number of Propellers

1

Number of Blades

2

Prop Manufacturer

Sensenich

Prop Diameter max and min

76

Prop Type

Fixed Pitch

Fuel Capacity

50 gal

Usable Fuel

48 gal

Fuel allowed

100 Green or 100ll Blue

Oil Capacity

8q

Oil Type

20W50

Max Ramp Weight Normal

2558

Max Ramp Weight Utility

2138

Max Takeoff Weight Normal

2550

Max Takeoff Weight Utility

2130

Max Landing Weight Normal

2550

Max Landing Weight Utility

2130

Max Baggage Weight Normal

200

Max Baggage Weight Utility

0

Wing Load

15.0 lbs per sq ft

Power Loading

14.2 lbs per hp

EGT

Exhaust Gas Temperatures

FFLOW

Fuel Flow

RPM

Propeller Speed

CAS

Calibrated Air Speed is corrected for position and instrument error

KCAS

Calibrated Airspeed in Knots

IAS

Indicated Airspeed is as shown on the airspeed indicator

KIAS

Indicated Airspeed in Knots

TAS

True Airspeed is CAS corrected for altitude, temperature, and compressibility

AFCS

Automatic Flight Control System

EIS

Engine Indication System

ESP

Electronic Stability and Protection

FDE

Fault Detection and Exclusion

FOB

Fuel On Board

GDL

Garmin Data Link

GFC

Garmin Flight Control Unit

GMA

Garmin Audio Panel

GSU

Garmin ADAHARS

GTX

Garmin Transponder

PFT

Preflight Test

SBAS

Satellite Based Augmentation System

TAWS

Terrain Awareness and Warning System

USP

Under Speed Protection

ARM

horizontal Distance from the relevance datum to the center of gravity

CG

Point at which an airplane would be suspended it would balance

CG ARM

The arm obtained by adding the airplanes individual moments and dividing the sum by the total weight

Datum

Imaginary vertical plane from which all horizontal distances are measured

Vo

Maximum operating Maneuvering Speed is the maximum speed at which application of full available aerodynamic control will not overstress the airplane.

VFE

Max Flap Extended

VNE

Never Exceed Speed

VNO

Max Structural Cruising Speed is the speed that should not be exceeded except in smooth air and then only with caution.

VS

Stalling Speed

VSO

Stalling Speed Landing Configuration

VX

Best Angle of Climb

VY

Best Rate of Climb

ISA

15 Celsius, 59 degrees, 29.92 inches hg

Pressure Altitude

Altitude measured from standard sea-level pressure by a pressure or barometric altimeter. It is the indicated pressure altitude corrected for position and instrument error. Errors are considered zero.

Max Continuous Power

Maximum power permissible continuously during flight.

Takeoff Power

Maximum power permissible for takeoff.

ADAHRS

Air data, attitude and heading reference system

CAS

Crew alerting system

EBD

Evolution backup display

EIS

Engine indication System

FDE

Fault Detection and Exclusion

SBAS

Satellite Based Augmentation System

FOB

Fuel on board

GDU

Garmin display unit

GEA

Garmin Engine/ airframe processing unit

GIA

Garmin Integrated avionics unit

GMU

Garmin magnetometer unit

GPS

Global Positioning System

Demonstrated Crosswind Velocity

The demonstrated crosswind velocity is velocity of the crosswind component for which adequate control of the airplane during takeoff and landing was actually demonstrated during certification tests.

Arm

The horizontal distance from the reference datum to the center of gravity of an item.

Center of Gravity

The point at which an airplane would balance if suspended. Its distance from the reference datum is found by dividing the total moment by the total weight of the airplane.

CG ARM

The arm obtained by adding the airplane’s individual moments and dividing the sum by the total weight.

CG LIMITS

The extreme center of gravity locations within which the airplane must be operated at a given weight.

Datum

An imaginary vertical plane from which all horizontal distances are measured for balance purposes.

Useful Load

Difference between takeoff weight, or ramp weight is applicable, and basic empty weight.

Propeller Tolerance @ ISA Conditions Formula

Vo = Vo max X sqr/ w/max w

MFD

Multifunction display

PFD

Primary flight display

Basic Empty Weight

Standard empty weight plus optional equipment

Standard Empty Weight

Weight of a standard airplane including unusable fuel, full operating fluids, and full oil

VNE SPEED

154

VNO SPEED

125

VO SPEED

113 and 98

Green Band

50-125

White Band

45-102

Yellow Band

125-154

Red Band

154

Tach Green Band

500-2700 rpm

Tach Red Line

2700 rpm

Oil temp green band

75-245 degrees

oil temp red line

245 degrees

Oil Pressure Minimum

25psi