# Section 2 - Limitations

## SPEED

### Speed Limitations

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

<figure><img src="https://2387545683-files.gitbook.io/~/files/v0/b/gitbook-x-prod.appspot.com/o/spaces%2F9qG9FQILvWDmv4pRrAjW%2Fuploads%2Fsq1CJVGrI6SYLUu878ws%2Fimage.png?alt=media&#x26;token=98795842-c33c-42b9-a936-f4bdf43a70a8" alt=""><figcaption></figcaption></figure>

### Airspeed Indicator Markings

<figure><img src="https://2387545683-files.gitbook.io/~/files/v0/b/gitbook-x-prod.appspot.com/o/spaces%2F9qG9FQILvWDmv4pRrAjW%2Fuploads%2FMY8mYsOjkYQslJ0eyteg%2Fimage.png?alt=media&#x26;token=4692544b-4f03-47ec-87d2-a6f27e606a97" alt=""><figcaption></figcaption></figure>

## 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&#x20;
3. Maximum Turbine Inlet Temperature: 1650°F&#x20;
4. Maximum Oil Temperature: 245°F&#x20;
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

<figure><img src="https://2387545683-files.gitbook.io/~/files/v0/b/gitbook-x-prod.appspot.com/o/spaces%2F9qG9FQILvWDmv4pRrAjW%2Fuploads%2F1pWwFYicsVAcuStOliEn%2Fimage.png?alt=media&#x26;token=62de1792-9ef1-4d6e-99e6-17e51067c985" alt=""><figcaption></figcaption></figure>

## 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&#x20;

From -25°C (-13°F) to +50°C (122°F).

### Flight Crew&#x20;

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

### Smoking&#x20;

Smoking is not allowed.

### Types of Surface&#x20;

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

<table><thead><tr><th width="290.3333333333333">Condition</th><th>Weight (kg)</th><th>Weight (lbs)</th></tr></thead><tbody><tr><td>Maximum Ramp Weight</td><td>3618 kg</td><td>7976 lbs</td></tr><tr><td>Maximum Take-off Weight</td><td>3600 kg</td><td>7937 lbs</td></tr><tr><td>Maximum Landing Weight</td><td>3600 kg</td><td>7937 lbs</td></tr><tr><td>Maximum Zero Fuel Weight</td><td>3480 kg</td><td>7673 lbs</td></tr></tbody></table>

<figure><img src="https://2387545683-files.gitbook.io/~/files/v0/b/gitbook-x-prod.appspot.com/o/spaces%2F9qG9FQILvWDmv4pRrAjW%2Fuploads%2FGdkVAquAeRsOXuqSuK87%2Fimage.png?alt=media&#x26;token=bb2bc15c-71a6-4f57-8a1a-3276dd1d92b9" alt=""><figcaption></figcaption></figure>

## 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:

{% tabs %}
{% tab title="Flaps UP" %}
Positive: +3.44 g

Negative: -1.37 g
{% endtab %}

{% tab title="Flaps LAND" %}
Positive: +2.0 g

Negative: 0.0 g
{% endtab %}
{% endtabs %}

### 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.&#x20;

* 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 |