TKS ICE PROTECTION

This section contains supplemental information to operate, in a safe and efficient manner, the aircraft in icing conditions when equipped with TKS Ice Protection System.

LIMITATIONS

The optional TKS Ice Protection System allows flight in icing conditions, within envelopes for Continuous Maximum and Intermittent Maximum intensity of atmospheric icing conditions defined by 14 CFR Part 25, Appendix C.

In icing conditions, the airplane must be operated as described in the “Normal Procedures” section of this supplement. Where specific operational speeds and performance information have been established for such conditions, this information must be used.

Single Engine

Intentional single engine operations in icing conditions are prohibited.

Steep approach

Steep approaches in icing conditions are NOT allowed.

Autopilot Operations

Autopilot operation is prohibited when operating in severe icing conditions as defined in this supplement.

Use of the autopilot is prohibited when any unusual ice (e.g. runback ice) is observed forming aft of the protected surfaces of the wing, or when unusual lateral trim requirements or autopilot trim warnings are encountered.

Climbs must be made using FLC mode.

Minimum Dispatch Fluid Level

Dispatch into known or forecast icing conditions with less than 33 liters (8.6 USG) of ice protection fluid is prohibited. The pilot must ensure adequate fluid quantity before each flight. Duration times for 33 liters (8.6 USG) minimum dispatch fluid level:

NORM ........................................................................ 90 Minutes

HIGH ......................................................................... 45 Minutes

MAX ........................................................................ 22.5 Minutes

Ice Protection Fluid Limits

Usable Capacity ..................................... 54.0 Liters (14.3 USG)

Tank Total Capacity ................................ 54.5 Liters (14.4 USG)

Maximum Available System Operating Time

With the ice protection system fluid tank full, the following maximum operating times are available: NORM Flow Duration .............................................. 150 Minutes

HIGH Flow Duration .................................................. 75 Minutes

MAX Flow Duration ................................................. 37.5 Minutes

Windshield Pump

The windshield pump is rated for intermittent use only. Continuous operation may damage the pump. Do not operate the windshield pump longer than 10 seconds. Allow 10 seconds between operations.

A single push button operation starts a windshield pump operation of 5 seconds.

EMERGENCY PROCEDURES

A failure of the Ice Protection System (IPS) is defined as any condition, observed or suspected, in which the system fails to remove ice from protected surfaces including the propeller, in addition to any Ice Protection System CAS failure annunciations.

FAILURE OF ICE PROTECTION SYSTEM

(Ice accumulation, observed or suspected, on airplane protected surface)

1. Pitot Heat switches (L and R) ......................................... VERIFY ON

2. TKS Selector switch ...................................................... HIGH or MAX

3. WINDSHIELD button ................................ PUSH (Momentary switch)

Repeat operation of windshield pump to verify system is primed properly, as evidenced by ice protection fluid exiting the windshield nozzles. Activate BACKUP PUMP if the system does not prime.

4. Defrost ........................................................................... SELECT ON

5. Propeller lever .................................................................... MAX RPM

6. ICE LIGHT switch ...................................................... AS REQUIRED

7. Icing Conditions ................................ EXIT AS SOON AS POSSIBLE

ICE PROTECTION SYSTEM LOW PRESSURE

1. BACKUP PUMP switch ................................................................. ON

2. TKS Selector switch ................................................................... HIGH

3. TKS Ice Protection System ............................................... MONITOR

If annunciation is permanently ON:

4. Icing Conditions .................. EXIT AS SOON AS POSSIBLE

ICE PROTECTION SYSTEM HIGH PRESSURE

1. Icing Conditions ................................ EXIT AS SOON AS POSSIBLE

ICE PROTECTION SYSTEM LOW FLOW RATE

1. DE ICING PUMP circuit breaker ....................... RESET, if necessary

2. WINDSHIELD button ..................................................................... ON

Repeat operation of windshield pump to verify system is primed properly, as evidenced by ice protection fluid exiting the windshield nozzles.

3. TKS Selector switch ................................................................... HIGH

If warning annunciation is no longer shown:

4. Ice Protection System ............................................ MONITOR

(END)

If annunciation remains or is intermittent:

5. BACKUP PUMP switch ...................................................... ON

6. Icing Conditions .................................................. AVOID/EXIT

(END)

LOW LEVEL

The LO LVL message will start to be displayed when 0-15 lt (0-4 USG) fluid is into the tank. This means about 30 minutes residual capacity in NORMAL mode (15 min in HIGH, 7,5 min in MAX).

1. Icing Conditions ............................................................. AVOID/EXIT

NORMAL PROCEDURES

OPERATION IN ICING CONDITIONS

The P2012 airplane is certified for flight in the icing conditions within Continuous and Intermittent Envelopes defined by the Appendix "C" to FAR 25. Nevertheless, icing conditions exceeding the capabilities of the anti-icing and de-icing systems may be encountered. For this reason, the pilot must avoid such severe ice conditions and must exit the icing conditions if an abnormal accretion rate or location on the airplane is recognized.

Flight in freezing drizzle and freezing rain is prohibited. If the airplane encounters conditions that are determined to contain freezing rain or freezing drizzle, the pilot must immediately exit these conditions by changing altitude or course.

Some handling and performance changes can be experienced with ice build upon unprotected parts and run-back ice on the wings (bottom skins).

The most noticeable characteristics is a significant increase in power required to maintain a specific cruise speed and a reduction in climb performance.

AIRSPEEDS FOR NORMAL OPERATIONS

Anti-ice system operation (TKS envelope):

Min airspeed ..................................................................................... 94 KIAS

Max airspeed (flap UP) .......................173 KIAS or 200 KTAS, whichever is lower

En route Climb (Flaps Up):

Cruise Climb ..................................................................................... 99 KIAS

Holding:

Flaps 0° .......................................................................................... 130 KIAS

Approach to Landing / Balked Landing:

Flaps LAND .............................................. 95 KIAS

Flaps TO .............................................. 105 KIAS

Flaps UP ............................................. 116 KIAS

PRE-FLIGHT CHECKS

1. Circuit breakers ........................................................................... SET

2. MASTER switch ............................................................................. ON

3. CROSS LH/RH switches ............................................................... ON

4. TIE BUS switch ............................................................................. ON

5. Doors ...................................................................................... CLOSE

6. WINDSHIELD button .................................... ON (Momentary Switch)

Verify presence of Ice Protection Fluid from spray nozzles.

1. TKS Selector switch ................................................................ NORM

2. TKS NRM MODE annunciation ............................................. SHOWN

3. Check that fluid flows evenly from active zones and from propeller nozzles

4. TKS Selector switch ................................................................ OFF

5. BACKUP PUMP switch ............................................................. ON

6. BACKUP PUMP ............................................... CHECK RUNNING

7. BACKUP PUMP switch ........................................................... OFF

8. ICE LIGHT switch ........................................ ON, VERIFY (LH side)

Wing ice light as well as visual ice detection probe light may not be visible with daylight.

1. TKS Mode ................................................................... HI then MAX

2. TKS HIGH/MAX MODE annunciation ................................... SHOWN

3. Stall warning Ice Mode………………………………………………… ON, CHECK annunciation then OFF

4. Fluid Quantity ...................... VERIFY 33 Litres (8.6 USG) MINIMUM

5. TKS Selector switch ................................................................ OFF

6. CROSS LH/RH switches .......................................................... OFF

7. TIE BUS switch ........................................................................ OFF

8. MASTER .................................................................................. OFF

Above 20°C (68F) the decreasing fluid viscosity could cause one or more “LOW PRESS” messages.

BEFORE TAKE-OFF

Activate Pitot Heater and Stall Heater in any visible moisture at an ambient temperature below +5°C (41°F).

ANTICIPATED ICING CONDITIONS IMMEDIATELY AFTER TAKEOFF

1. Pitot Heater (L and R) and Stall Heater ……………..............................ON

2. TKS Selector switch ........................ NORM or HIGH AS REQUIRED

3. ICE LIGHT switch ...................................................... AS REQUIRED

Verify airframe is free of contamination immediately before takeoff.

After reaching 400 ft AGL:

4. Stall warning Ice Mode……………….………………………………… ON

IN FLIGHT

Activate Pitot Heater and Stall Heater in any visible moisture at an ambient temperature below +5°C (41°F).

IF ICING CONDITIONS EXIST

1. Pitot Heater (L and R) and Stall Heater ……………..............................ON

2. WINDSHIELD button ................................................. AS REQUIRED

3. Defrost ........................................................................ AS REQUIRED

4. ICE LIGHT switch ...................................................... AS REQUIRED

5. Monitor ice accumulation:

At first sign of ice accretion:

6. TKS Selector switch ........................ NORM or HIGH AS REQUIRED

7. Stall warning Ice Mode……………….………………………………… ON If ice continues to accrete on wing leading edge:

8. TKS Selector switch .......................................................... HIGH/MAX

9. Fluid level and IPS CAS messages ................... CHECK Periodically

If ice continues to accrete on wing leading edge or does not shed:

10. BACKUP PUMP switch ................................................................. ON

INADVERTENT ICING ENCOUNTER

1. Pitot Heater (L and R) and Stall Heater ……………..............................ON

2. TKS Selector switch .................................................. HIGH or NORM

3. Stall warning Ice Mode……………….………………………………… ON If ice accumulation occurs, then:

4. TKS Selector button .................................................................... MAX

5. WINDSHIELD button ................................................. AS REQUIRED

WHILE IN ICING CONDITIONS

1. ICE LIGHT switch ...................................................... AS REQUIRED

2. Defrost ........................................................................ AS REQUIRED

3. Ice Protection Fluid Quantity and CAS Messages ............. MONITOR

4. Airspeed .................... MAINTAIN 94-173 KIAS or less than 200 KTAS

AFTER EXITING ICING CONDITIONS

1. TKS Selector switch .................................................................... OFF

2. Stall warning Ice Mode……………….………………………………… OFF

3. Airspeed ........................................ AS FLIGHTCONDITIONS DICTATE

4. ICE LIGHT switch ...................................................... AS REQUIRED

5. Defrost ........................................................................ AS REQUIRED

6. WINDSHIELD button ..... ON as required, to remove windshield ice

During icing conditions in cruise, increase engine power (up to maximum continuous power) to maintain cruise speed as ice accumulates on the unprotected areas and causes the aircraft to slow down.

Watch for signs of air filter icing and pull the Alternate Air control if necessary. An unexplained loss in engine power could be caused by ice blocking the air intake filter. Opening the alternate air valve allows preheated air from the engine compartment to be aspirated.

AUTOPILOT

The autopilot may be used in icing conditions within the icing envelopes defined in 14 CFR 25 Appendix C. However, every 10-20 minutes the autopilot should be disconnected to detect any out-of-trim conditions caused by ice buildup. If significant out-of-trim or other anomalous conditions are detected, the autopilot shall remain off for the remainder of the flight.

BEFORE LANDING

Activate Pitot Heater and Stall Heater in any visible moisture at an ambient temperature below +5°C (41°F).

If icing conditions exist or are anticipated, or at first sign of ice accretion:

1. Pitot Heater (L and R) and Stall Heater ……………..............................ON

2. TKS Selector switch ....................................................... NORM/HIGH

3. Stall warning Ice Mode……………….………………………………… ON

4. Monitor ice accumulation If ice accretion rate is low:

5. TKS Selector switch ................................................................ NORM If ice is not shedding:

6. TKS Selector switch .................................................................... MAX

7. WINDSHIELD button ..................... AS REQUIRED (Momentary Switch)

8. ICE LIGHT switch ...................................................... AS REQUIRED

DESCRIPTION

PROTECTION SYSTEM

The P2012 Ice Protection System is a fluid based system whereby a fluid that acts as a freezing point depressant (FPD) is delivered via a set of branching pipelines to the leading edges of the wing, tails, propellers, and windshield.

The FPD fluid is stored in a tank located within the aircraft fuselage upper side. During operation, the fluid passes from the tank to the two metering pumps. A branching pipeline network allows flow through proportioning units to each of the ice protection devices. A secondary branch from the pump flows through a solenoid and a small electric gear pump. This branch provides the pilot with an on demand fluid to the windshield.

Control of the system is performed by a series of switches. The pilot will select the desired mode of operation with the switches available. The Timer Box provides three different types of operation for the main metering pump. These operations are Normal mode (both pumps simultaneously for a time cycle of 30 seconds on and 90 seconds off), High mode (one pump runs continuously) and Max mode (two pumps run continuously, for a time of 2 minutes). Normal mode is considered the appropriate mode of operation to provide ice protection during typical icing encounters. A final mode is available to the system which bypasses the Timer Box. This is called Backup mode. Backup runs one pump continuously and is identical to High mode. Backup is designed to be electrically isolated from the remainder of the system to provide an independent means of pumping fluid in the event of a main system failure.

TIMER BOX MANAGED MODES

• Normal: both pumps ON for 30 seconds, then 90 seconds OFF

• High: one pump permanently ON

• Max (push): one pump permanently ON, the other ON for 2 minutes

ESSENTIAL BUS CONNECTED MODE

• Backup: one pump permanently ON

SYSTEM OPERATION

TKS Ice protection control panel is installed on instrument panel and allows the pilot control of the main functions of DE-ICE system.

TKS Ice Protection Control Panel

It is composed by following switches:

• Mode Selector Switch, is a stable position switch and allows to set three operative modes:

  • OFF, the DE-ICE System is Inoperative;

  • NORM, the DE-ICE System is in Normal Mode;

  • HIGH, the DE-ICE System is in High Mode

• MAX Switch, is a temporary switch and allows to set the MAX operative mode when pushed;

• W/S DE-ICE Switch, is a temporary switch and allows to activate the Windshield Pump;

• Back-up Pump guarded Switch, is a stable position switch and allows to activate the Metering back-up Pump.

DETECTION SYSTEM

P2012 A/C is equipped with two means used for inspect the presence of ice conditions on the aircraft. The first means is an Anti ICE External Light and the second means is a lighted blade.

• The Anti ICE External Light is installed on left engine nacelle, the beam of led illuminate the outboard left wing leading edge, and is used to recognize the presence of ice conditions on a/c wing.

• The Lighted blade is installed externally on left side of windshield, in field of pilot’s view, easily viewable and inspectable and is used to allow quickly the ice formation visualization.

A specific switch easily accessible to pilot and labeled as to operation is provided, is installed on TKS Anti ICE Control Panel. The switch turns on simultaneously the Anti ICE External Light and the Lighted Blade.

The same switch, when held fully up, warms up the ice inspection blade, allowing removal of ice build up.

SYSTEM INDICATION

Indications related to TKS system are provided to the pilot, in the Engine Information System of the MFD:

• AMOUNT of remaining anti-icing fluid in Liters;

• OPERATING TIME (in Hours and minutes) of ICE protection system when the system is active (or else when the switch is in NORM, HIGH or MAX mode);

• OPERATIVE MODE (NORM, HIGH or MAX) displayed in GREEN/BLUE.

TKS EIS Page (indicative)