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Tecnam P2012
Tecnam P2012
  • 🏁Introduction
    • Welcome
    • Difference Training
    • FAQ
  • 📓Aircraft Flight Manual
    • Section 1 - General
    • Section 2 - Limitations
    • Section 3 - Emergency Procedures
    • Section 4 - Normal Procedures
    • Section 5 - Performance
    • Section 6 - Weight & Balance
    • Section 7 - Airframe and Systems Description
    • Section 8 - Supplements
      • AUTOPILOT GFC700
      • TKS ICE PROTECTION
      • GCU 477 FMS KEYBOARD
      • AIR CONDITIONING
      • MEDEVAC / SMP CONFIG
  • ⭐SPECIAL FEATURES
    • Integrated Tablet / EFB
    • Key Bindings
    • Paintkit
    • Full Flight Video
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On this page
  • SPEED
  • Speed Limitations
  • Airspeed Indicator Markings
  • POWERPLANT
  • Engines
  • Propellers
  • Powerplant Limitations
  • Avionics System Instrument Markings
  • FUEL
  • OPERATIVE AND ADDITIONAL LIMITATIONS
  • Maximum Operating Altitude
  • Ambient Temperature
  • Flight Crew
  • Smoking
  • Types of Surface
  • Stall warning
  • WEIGHTS AND CENTER OF GRAVITY LIMITS
  • MANEUVERS AND LOAD FACTOR LIMITS
  • Approved Maneuvers
  • Maneuvers Load Factor Limits
  • Steep Approach Operations
  • SEATS AND BAGGAGE
  • Maximum Passenger Seating Configuration
  • Baggage Loading Limit
  1. Aircraft Flight Manual

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.

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Last updated 1 year ago

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:

Positive: +3.44 g

Negative: -1.37 g

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

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