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:
Maximum Continuous Power: 375hp @ 2575rpm
Maximum Cylinder Head Temperature: 500°F
Maximum Turbine Inlet Temperature: 1650°F
Maximum Oil Temperature: 245°F
Oil Pressure:
Minimum for idle: 25 psi
Minimum normal: 55 psi
Maximum normal: 95 psi
Maximum for starting and warm-up: 115 psi
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:
Positive: +3.44 g
Negative: -1.37 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 |
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