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.
Last updated
Section 2 includes operating limitations instrument markings and basic placards necessary for safe operation of P2012 aircraft, its engines, standard systems and equipment.
Last updated
The following table addresses the airspeed limitations and their operational significance:
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.
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
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
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)
For aircraft embodying G1000 Nxi maximum operating altitude is 19500 ft. Otherwise, maximum operating altitude is 13000 ft.
From -25°C (-13°F) to +50°C (122°F).
The minimum crew is one pilot seated in the left hand seat.
Smoking is not allowed.
The take-off and landing can be conducted on hard paved or grass surfaces.
The aircraft must be equipped with an artificial stall warning.
This is a normal category aircraft. No aerobatic maneuvers, including spins, are authorized.
Maneuver load factors limits are as follows:
Positive: +3.44 g
Negative: -1.37 g
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.
Maximum passenger seating configuration is 9.
| Condition | Weight (kg) | Weight (lbs) |
|---|---|---|
| Baggage Zone | Max Loading | Max Loading Intensity |
|---|---|---|
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
Nose
103 kg / 227 lb
168 kg/m² / 34.6 lb/ft²
Rear
239 kg / 527 lb
152 kg/m² / 31.2 lb/ft²
