Section 2 - Limitations

Section 2 includes operating limitations instrument markings and basic placards necessary for safe operation of P2012 aircraft, its engines, standard systems and equipment.

SPEED

Speed Limitations

The following table addresses the airspeed limitations and their operational significance:

Airspeed Indicator Markings

POWERPLANT

Engines

• MANUFACTURER: Lycoming

• MODEL: TEO-540-C1A

• TYPE: Direct - drive six - cylinder, horizontally opposed, turbocharged, air-cooled engine equipped with electronic fuel injection, electronic ignition, down exhaust.

Propellers

• MANUFACTURER: MT Propeller

• MODEL: MTV-14-B-C-F/CF195-30

• TYPE: 4 wood/composite blades with metal leading edge fully featherable.

• DIAMETER: 1950 mm / 6 ft 4.77 in

Powerplant Limitations

Following list reports the operating limitations for installed engines:

1. Maximum Continuous Power: 375hp @ 2575rpm

2. Maximum Cylinder Head Temperature: 500°F

3. Maximum Turbine Inlet Temperature: 1650°F

4. Maximum Oil Temperature: 245°F

5. Oil Pressure:

   • Minimum for idle: 25 psi

   • Minimum normal: 55 psi

   • Maximum normal: 95 psi

   • Maximum for starting and warm-up: 115 psi

6. Fuel Pressure:

   • Minimum: 44 psi

   • Maximum: 72 psi

Avionics System Instrument Markings

FUEL

• 2 TANKS: 375 litres each one (99 US gallons)

• MAXIMUM CAPACITY: 750 litres (198 US gallons)

• USABLE FUEL: 364 litres each one (96 US gallons)

• APPROVED FUEL: 100 or 100LL (Aviation Grade)

• MAXIMUM FUEL UNBALANCE: 150 litres (39 US gallons)

OPERATIVE AND ADDITIONAL LIMITATIONS

Maximum Operating Altitude

For aircraft embodying G1000 Nxi maximum operating altitude is 19500 ft. Otherwise, maximum operating altitude is 13000 ft.

Ambient Temperature

From -25°C (-13°F) to +50°C (122°F).

Flight Crew

The minimum crew is one pilot seated in the left hand seat.

Smoking

Smoking is not allowed.

Types of Surface

The take-off and landing can be conducted on hard paved or grass surfaces.

Stall warning

The aircraft must be equipped with an artificial stall warning.

WEIGHTS AND CENTER OF GRAVITY LIMITS

Condition	Weight (kg)	Weight (lbs)
Maximum Ramp Weight	3618 kg	7976 lbs
Maximum Take-off Weight	3600 kg	7937 lbs
Maximum Landing Weight	3600 kg	7937 lbs
Maximum Zero Fuel Weight	3480 kg	7673 lbs

MANEUVERS AND LOAD FACTOR LIMITS

Approved Maneuvers

This is a normal category aircraft. No aerobatic maneuvers, including spins, are authorized.

Maneuvers Load Factor Limits

Maneuver load factors limits are as follows:

Flaps UP

Positive: +3.44 g

Negative: -1.37 g

Flaps LAND

Positive: +2.0 g

Negative: 0.0 g

Steep Approach Operations

The airplane has demonstrated to be capable to conduct steep approach with flap LAND and propellers full forward at 110 KIAS with a Max Approach Gradient of 12° (21%). A glide path reference system is required in case of IFR conditions. In case an external aid is not available, the glide path can be controlled through the vertical speed indicator.

No determination of landing distance reduction has been performed and so landing distance data of normal approach (3°) needs to be considered also for steep approach manoeuvre.

• Deliberate Single Engine Approach are prohibited.

• Steep approaches in icing conditions are NOT ALLOWED.

SEATS AND BAGGAGE

Maximum Passenger Seating Configuration

Maximum passenger seating configuration is 9.

Baggage Loading Limit

Baggage Zone	Max Loading	Max Loading Intensity
Nose	103 kg / 227 lb	168 kg/m² / 34.6 lb/ft²
Rear	239 kg / 527 lb	152 kg/m² / 31.2 lb/ft²