SFC Diamond Twin Star DA42 User manual

© SFC OCT 2022
Diamond Twin Star DA42
Quick Reference Handbook
Abnormal Procedures

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DIAMOND TWINSTAR DA42
QUICK REFERENCE HANDBOOK (QRH)
DISCLAMER: This publication is to be used as a quick reference handbook and is to be read and used in
conjunction with the aeroplane flight manual and standard operating procedures. It does not replace or
supersede the aeroplane flight manual. It is the responsibility of the pilot in command to comply with all
relevant performance and documentation criteria relative to their flight operations. This QRH does not
include all abnormal or emergency procedures listed in the aeroplane flight manual.
QRH COLOUR INDEX Meaning
BLUE: - Memory Items/Flow Checks –Normal Procedures –
Actions to be completed without reference. (Have a grey
background)
YELLOW: - Do List –Normal Checklists –To be read line by line.
GREEN:- Aircraft Type Information.
RED:- Emergency Procedure –Actions to be completed from
memory and without reference. (Items with grey background
are memory items)
ORANGE: Abnormal procedure –Actions to be completed by
checklist as per the CAS message.
DEFINITIONS:
Land Immediately –The urgency of the landing is paramount. Emergency descent normally required with a
landing in an open field.
Land As Soon As Possible –Land without delay at the nearest suitable airfield at which a safe approach
and landing is assured.
Land As Soon As Practical –Landing at the discretion of the pilot. Extended flight beyond the nearest
approved landing area is not recommended.
Required Performance –In compliance with CASR Part 91.
OEI –One engine inoperative.
Decision Point –The point during the take-off phase, that the PIC makes the decision to either, abort the
take off and land straight ahead utilising any run off area, or continue the take-off, climb and emergency
procedure.

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QRH CONTENTS
Precautionary Landing
5
Autopilot Overspeed Recovery
21
Canopy in cooling gap position
6
Loss of Navigation Information
21
High RPM
6
Autopilot Out Of Trim
22
High Coolant Temperature
6
Flashing Yellow Mode Annunciation
24
Low Coolant Temperature
7
L/R Aux Fuel Transfer Fail
25
High Oil Temperature
7
Effect of G1000 Losses Upon A/P Op.
25
Low Oil Temperature
8
L/R ECU A Fail
26
High Oil Pressure
8
L/R ECU B Fail
28
Low Oil Pressure
8
High Gear Box Temperature
9
High Fuel Temperature
9
Low Fuel Temperature
10
Low Voltage Indication On The Ground
10
Low Voltage During Flight
10
L/R Fuel Low
11
L/R Volts Low
11
L/R Altn Fail
12
L/R Aux Fuel E
12
Pitot Fail/ht Off
13
Stall Ht Fail/Off
13
L/R Cool Lvl
13
Stick Limit
14
Check Gear
14
LOI
15
AHRS Aligning
15
Failure In Flap Operating System
16
MINSPD
16
Windshear Encounter
17
ESP Disengagement
17
Hydraulic Pump Failure
18
Cont. Hydraulic Pump Operation
18
Failures In Electrical Rudder Pedal
18
Starting Engine with External Power
19
Lightning Strike
20
Autopilot Disconnect
20

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PRECAUTIONARY LANDING
NOTE
A landing of this type is only necessary when there is a reasonable suspicion that due to
operational factors such as fuel shortage, weather conditions, etc. the possibility of
endangering the airplane and its occupants by continuing the flight cannot be excluded. The
pilot is required to decide whether or not a controlled landing in a field represents a lower
risk than the attempt to reach the nearest airfield under all circumstances.
NOTE
If no level landing area is available, a landing on an upward slope should be sought.
1. Select appropriate landing area.
2. Consider wind
3. Approach:
If possible, the landing area should be overflown at a suitable height in order to recognize
obstacles. The degree of offset at each part of the circuit will allow the wind speed and
direction to be assessed.
4. ATC …………………………………………………….…………………………………………………………………… ADVISE
5. Touchdown …………………………………………………………… WITH THE LOWEST POSSIBLE AIRSPEED
CAUTION
If sufficient time is remaining, the risk of fire in the event of a collision with obstacles can be
reduced as follows after a safe touch-down:
- ENGINE MASTER ……………………………………. BOTH OFF
- FUEL SELECTOR …...………………………………… BOTH OFF
- ELECT. MASTER ….………………………………………..….. OFF

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CANOPY IN COOLING GAP POSITION
Caution
If take-off was inadvertently done with the canopy in the cooling gap position, do not
attempt to close the canopy in flight. Land the airplane and close the canopy on ground.
HIGH RPM
1. Reduce power of affected engine.
2. Keep RPM within the green range using the POWER lever.
If the above mentioned measures do not solve the problem, refer to DEFECTIVE PROPELLER
RPM REGULATING SYSTEM checklist.
3. Land at the nearest suitable airfield.
HIGH COOLANT TEMPERATURE
Caution:
Coolant temperatures above the limit value of 105°C can lead to a total loss of power due
to engine failure.
- Check G1000 for L/R COOL LVL caution message (low coolant level).
L/R COOL LVL caution message not displayed:
During climb:
- Reduce power on affected engine by 10% or more as required.
- Increase airspeed by 10 KIAS or more as required.
- If the coolant temperature does not reach the green range within 60 seconds, reduce power
on affected engine as far as possible and increase airspeed.
During cruise:
- Reduce power on affected engine.
- Increase airspeed.
- Check coolant temperature in green range.

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LOW COOLANT TEMPERATURE
L/R COOL LVL caution message displayed:
- Reduce power on affected engine.
- Expect loss of coolant.
Warning
A further decrease in coolant temperature must be expected. Prepare for an engine failure.
HIGH OIL TEMPERATURE
Caution:
Oil temperatures above the limit value of 140°C can lead to a total loss of power due to
engine failure.
- Check Oil pressure
If the oil pressure is outside of the green range (lower limit):
- Reduce power on affected engine.
- Expect loss of engine oil.
Warning
A further increase in oil temperature must be expected. Prepare for an engine failure.
If the oil pressure is within the green range:
- Reduce power on affected engine.
- Increase airspeed.

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LOW OIL TEMPERATURE
Note
During an extended descent from high altitude with a low power setting oil temperature
may decrease. In this case an increase in power can help.
- Increase power.
- Reduce airspeed.
HIGH OIL PRESSURE
- Check oil temperature.
- Check coolant temperature.
If the temperatures are within the green range:
- expect false oil pressure indication. Keep monitoring temperatures.
If the temperatures are outside of the green range:
- Reduce power on affected engine
Warning
Land at the nearest suitable airfield. Prepare for an engine failure.
NOTE
At low oil temperatures high oil pressure may occur which could lead to an oil pressure
warning. In this case reduce the power setting until the warning disappears and conduct
the warm up with this reduced setting.
LOW OIL PRESSURE
Oil pressures below the lmit value of 0.9 bar can lead to a total loss of power due to engine
failure.
- Reduce power on affected engine.
- Expect loss of oil.
Warning
Land at the nearest suitable airfield. Prepare for an engine failure.

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HIGH GEAR BOX TEMPERATURE
Gearbox temperature aboves the limit value of 120°C can lead to a total loss of power due to
engine failure.
- Reduce power on affected engine.
- Increase airspeed
Caution
At high ambient temperature conditions and/or at low airspeeds with high power settings,
it can be assumed that there is no technical defect in the gearbox and that the above
mentioned procedure will decrease the temperature(s). This might not be the case if the
gearbox temperature does not return to the green range. In this case perform a
precautionary landing on the nearest suitable airfield. Prepare for an engine failure.
HIGH FUEL TEMPERATURE
Fuel temperatures above the limit value of 60°C can lead to a noticeable reduction of the
high pressure pump efficiency
-Reduce Power on affected engine.
-Increase airspeed
Caution
At high ambient temperature conditions and/or at low airspeeds with high power settings
and low fuel quantities, it can be assumed that the above mentioned procedure will
decrease the temperatures(s). If the fuel temperature does not return to the green range,
perform a precautionary landing on the nearest suitable airfield.
NOTE
Increased fuel temperature can occur when the fuel quantity in the main tank is low. If the
auxiliary tank is installed the fuel temperature can be decreased by transferring fuel from the
auxiliary to the main tank.

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LOW FUEL TEMPERATURE
- Increase power on affected engine.
- Reduce airspeed
Caution
At low ambient temperature conditions and/or at high airspeeds with low power settings,
it can be assumed that the above mentioned procedure will increase the temperature(s). If
the fuel temperature does not return to the green range perform a precautionary landing
on the nearest suitable airfield. Prepare for an engine failure.
LOW VOLTAGE INDICATION ON THE GROUND
1. Alternators ………………………………………………..……………………………………………………….CHECK ON
2. Circuit Breakers ………………………………………………….…………………………………………………… CHECK
If LOW VOLTAGE CAUTION is still indicated on the G1000:
- Terminate flight preparation.
LOW VOLTAGE DURING FLIGHT
1. Alternators ……………………………………………………………………………………………………….. CHECK ON
2. Circuit Breakers ……………………………………………….……………………………………………………….CHECK
2. Electrical Equipment ………………….……………………………………………………….. OFF IF NOT NEEDED
If LOW VOLTAGE CAUTION is still indicated on the G1000:
- Follow procedure in L/R ALTN FAIL.

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L/R FUEL LOW
*Left/Right engine main tank fuel quantity is low
1. Fuel Quantity …………………………………………………………………………………………………………CHECK
Caution
As soon as the amount of usable fuel in the main tank is low, a caution message is displayed.
The indication is calibrated for straight and level flight. The caution message may be triggered
during turns which are flown with slip, or while taxiing in curved.
If L/R FUEL FLOW caution is caused by un-coordinated flight:
Caution
Prolonged un-coordinated flight can lead to a L/R Fuel low caution and subsequent LOW PX
warning and L/R ECU FAIL caution and can cause fuel starvation to the engine resulting in a
loss of power.
2. Return to coordinated flight (not more than approx. half a ball sideslip, 3°-5° bank)
If LH & RH main tanks show remarkable different fuel quantities in flight:
- Expect loss of fuel on side with lower indication.
- Use CROSSFEED function to ensure fuel supply.
2. Fuel Selector …………………………………………….CROSSFEED (engine with LOW FUEL indication)
L/R VOLTS LOW
*Left/Right bus voltage is too low (less than 25 Volts).
Possible reasons are:
- A fault in the power supply.
- ALTERNATORS off.
Continue with LOW VOLTAGE INDICATION ON THE GROUND or LOW VOLTAGE INDICATION
IN FLIGHT checklist.
CAUTION
If both low voltage indications are ON, expect failure of both alternators and follow one
alternator failed or both alternators failed checklist.

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L/R ALTN FAIL
*Left/Right engine alternator has failed
NOTE
A L/R ALTN FAIL annunciation may be temporarily triggered during ground operation with
low engine power settings. This indicates no system malfunction.
(a) One alternator failed
1. Alternator ........................................................…………………………….........OFF/ AFFECTED SIDE
2. Bus Voltage .....................................................……………………………......................... MONITOR
3. Electrical Consumers ………......……….……………………………………….…… REDUCE AS PRACTICABLE
(b) Both alternators failed
1. Avionics Master ……………………………………………………………………………………….……………………OFF
2. LH/RH Alternator …………………………………………………………………………………………………………. OFF
3. XPDR ………………………………………………………………………………………………………………………….. STBY
4. Landing Gear ……………………………………..……………………… DOWN , WHEN DOWN AND LOCKED
PULL EMERGENCY RELEASE
5. Stall/Pitot Heat ……………………………………………………………………………………………………………. OFF
6. All Lights ………………………………………………………………………………………………..…………………….. OFF
L/R AUX FUEL E
* Left/Right auxiliary fuel tank empty (displayed only when AUX pump switch is ON).
The auxiliary tank empty caution message indicates an empty auxiliary fuel tank while the
fuel pump is switched ON.
1. L/R Auxiliary Fuel Pump …………………………………………………………………………..…………………….OFF

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L/R COOL LVL
*Left/Right engine coolant level is low.
A low coolant caution alert may indicate a loss of coolant. This will subsequently lead to
decreased engine cooling capability/loss of engine power due to engine failure.
1. Annunciations/Engine instruments …………………………………... MONITOR
Refer to High Coolant Temperature or Low Coolant Temperature
NOTE
The indication is calibrated for straight and level flight. The caution message may be triggered
during turns which are flown with slip, or while taxiing in curves.
PITOT FAIL/HT OFF
*Pitot heating system has failed, or
*Pitot heating system is OFF
1. Pitot Heat ……………………………………………………………… CHECK ON/AS REQ
If in icing conditions:
2. Expect loss of static instruments.
3. Leave icing zone/refer to unintentional flight into icing.
STALL HT FAIL/OFF
* Stall warning heat has failed, or
* Stall warning heat is OFF
1. Pitot Heat ……………………………………………………………… CHECK ON/AS REQ
If in icing conditions:
2. Expect loss of acoustic stall warning
3. Leave icing zone/refer to unintentional flight into icing

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STICK LIMIT
*Control stick limiting system (variable elevator stop) has failed.
The variable elevator backstop is activated depending on the position of the POWER levers
and the position of the flap selector switch. The system has two failure modes which can be
identified as follows:
(a) Both POWER levers are in a position for a power setting of more than approximately 20%
LOAD:
CAUTION
The variable elevator backstop is inoperative. In case of stalling with “power-on” the handling
qualities and stall-characteristics are degraded significantly. Do not stall the airplane in any
configuration.
(b) At least one POWER lever is in a position for a power setting of less than approximately
20% LOAD:
CAUTION
The variable elevator backstop is active all the time, reducing the maximum elevator “pull”-
deflection. This results in reduced elevator capacity. In this case it is important not to reduce
airspeed below required minimum VREF=84 KIAS (up to 1900 kg (4189lb)) or 86 KIAS (above
1900 kg (4189lb)) during the approach for landing, especially at loading conditions with
forward locations of the center of gravity.
CHECK GEAR
*Landing gear is not down and locked.
1. Landing Gear ……………………………………….……………………… DOWN/AS REQ
NOTE
The CHECK GEAR caution message is displayed when either the flaps are in LDG position or
one power lever is less than approx. 20% and the landing gear is not down and locked.

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LOI
*GPS integrity is insufficient for the current phase of flight
(a) Enroute, Oceanic, Terminal, or Initial Approach Phase of Flight
If the LOI annunciation is displayed in the enroute, oceanic, terminal, or initial approach
phase of flight, continue to navigate using the GPS equipment or revert to an alternate
means of navigation other than the G1000 GPS receiver appropriate to the route and phase
of flight. When continuing to use GPS navigation, position must be verified every 15 minutes
using the G1000 VOR/ILS receiver or another IFR-approved navigation system.
(b) Final Approach
If the LOI annunciation is displayed while on the final approach segment, GPS based
navigation will be aborted.
AHRS ALIGNING –KEEP WINGS LEVEL
*The AHRS (Attitude and Heading Reference System) is aligning.
Keep wings level using standby attitude indicator.

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MINSPD
*AFCS entered Minimum Airspeed Mode
1. Power Levers …………………………………………………………………… INCREASE POWER AS REQUIRED
TO CORRECT UNDERSPEED
2. Airplane attitude, speed and altitude …………………………………………………………………..MONITOR
After Minimum Airspeed Mode condition is corrected:
3. AUTOPILOT …………………………….. RESELECT VERTICAL AND LATERAL MODES (IF NECESSARY)
4. Power Levers …………………………………………………………………………………………… ADJUST AS REQ.
NOTE
Autopilot underspeed protection mode provides a pitch down command to maintain 90 +/-
20 KIAS or VSW + 2 KIAS, depending on the vertical mode selected. Underspeed protection is
not available below 200 feet AGL, except in go-around mode
FAILURE IN FLAP OPERATING SYSTEM
Failure in position indication or function
1. FLAPS position ………………………….……………………….…………………….………………. CHECK VISUALLY
2. Airspeed ………………………………………….…………………….……………………… KEEP IN WHITE SECTOR
(max. 113 KIAS)
3. FLAPS switch ……………………………….………………,,,,,,,………………………..RE-CHECK ALL POSITIONS
Modified Approach Procedure Depending on the available flap settings
(a) Only UP available:
Airspeed ……………………….…………………………….………………,,,,,,,……………………………….. MIN 86 KIAS
Land at a flat approach angle, use POWER lever to control airplane speed and rate of descent.
(b) Only APP available:
Airspeed ……………………………………………………….………………,,,,,,,,…………………………….. MIN 42 KIAS
Land at a flat approach angle, use POWER lever to control airplane speed and rate of descent.
(c ) Only LDG available:
Perform normal landing.

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WINDSHEAR ENCOUNTER
1. AP DISC SWITCH ………………………………….……………………………….………………... PRESS AND HOLD
2. Performance established windshear escape procedures
After Exiting Windshear:
3. AP DISC SWITCH ……………………….………………………….………………………….…………………... RELEASE
4. Autopilot/Yaw Damper ……………………….………………………….………………………….…………… IF REQ.
ESP DISENGAGEMENT
If ESP is erroneously activated use one of the following methods to disconnect:
- AP DISC Switch ………………….………………………….………………….……….……………… PRESS AND HOLD
- CWS button ………………….………………………….………………………….…………………… PRESS AND HOLD
- AUX- SYSTEM SETUP 2 page on MFD ……….………………… DISABLE STABILITY AND PROTECTION
If all three methods are NOT successful:
- AUTOPILOT circuit breaker …………………………………………………………………………..………………..PULL

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CONTINUOUS HYDRAULIC PUMP OPERATION
1. Landing Gear Indication Lights ………………………………………………….…………………………….. CHECK
2. Prepare for manual landing gear extension. Refer to Manual Extension of the landing gear
NOTE
The landing gear might extend as the hydraulic system pressure decreases. Consider for
higher aerodynamic drag, resulting in degraded flight performance, increased fuel
consumption and decreased range.
Unscheduled maintenance action is required after landing.
HYDRAULIC PUMP FAILURE
1. Landing Gear Indication Lights ……………………………………………….. CHECK
2. Prepare for manual landing gear extension. Refer to Manual Extension of the landing gear
NOTE
The landing gear might extend as the hydraulic system pressure decreases. Consider for
higher aerodynamic drag, resulting in degraded flight performance, increased fuel
consumption and decreased range.
Unscheduled maintenance action is required after landing
FAILURES IN ELECTRICAL RUDDER PEDAL ADJUSTMENT
Runaway away of Electrical Rudder Pedal Adjustment
NOTE
The circuit breaker for the rudder pedal adjustment is located below the related switch, on
the rear wall of the leg room.
1. Circuit Breaker ……………………………………………………,,,…….………………..…………………………. PULL

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STARTING ENGINE WITH EXTERNAL POWER
1. Before Start Checklist ………………………….……….………………………………………………... COMPLETED
2. Engine Fire Before Start Brief ……………………….…………………….………………………….. COMPLETED
3. External Power ……………………………………………….…………………….……………………………. CONNECT
4. Fuel Pumps LH/RH ……………………………………………….……………………...…………………… CHECK OFF
4. Position Lights ………………………………………………….…………………….……………..……………………… ON
5. Elect. Master …………………………………………………….…………………….……………………………………. ON
6. ENGINE Master ……………………………..……………….…………………….………………………… ON (LH side)
7. Annunciations …………………………….……………….……………………..………………… CHECK L GLOW ON
8. Annunciations/ Engine/ System Page ….…..……….…………………….… CHECK OK / Normal Range
After the L GLOW ON indication is extinguished:
9. Start Key…………….……………………..… START L AS REQ./ RELEASE WHEN ENGINE HAS STARTED
CAUTION
Do not overheat the starter motor. Do not operate the starter motor for more than 10
seconds.
If the “L STARTER” annunciation does not extinguish after the engine has started and the
START KEY has been released, set the ENGINE MASTER to OFF and investigate the problem.
10. Annunciations/ Engine/ System Page.….……….……………………... CHECK OK/ NORMAL RANGE
11. Annunciations/ Start ……………………..…………….…………………….…….…………………….. CHECK OFF
12. Annunciations/ Oil Pressure ……………...………….……………………………………..…………. CHECK OK
Warning
If the oil pressure has not moved from the red range within 3 seconds after starting, set the
ENGINE MASTER switch to OFF and investigate problem.
13. Circuit Breakers ..………….………………………….……………………..………….… CHECK ALL IN/ AS REQ.
14. Idle RPM ………….…………………….……….……….…………………….……………… CHECK, 710 +/30 RPM
15. External Power ………….……………………….………….…………………….……………………… DISCONNECT
16. RH Engine ………………………..……………….…………………….… START WITH NORMAL PROCEDURE

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LIGHTNING STRIKE
1. Airspeed…………………………………………………….…………………….…………. AS LOW AS PRACTICABLE
DO NOT EXCEED VO
2. Grasp airplane controls firmly
3. Autopilot ……………………………………………………………….……………………..……. DISENGAGE (CHECK)
4. PFD/ backup instruments …………………………….……….……………………..…… VERIFY PERIODICALLY
5. Continue flight under VMC
6. Land on next suitable airfield.
Caution
Due to possible damage to the airplane obey the following instructions:
- Avoid abrupt or full control surface movements.
- Avoid high g-loads on the airframe.
- Avoid high yaw angles
- Avoid turbulent air as far as possible (e.g. lee effects).
- Do not fly into areas of known or forecast icing
- Maintain VMC
AUTOPILOT DISCONNECT (yellow AP flashing on PFD)
1. AP DISC Switch ………………………………………….…………………….…………….. DEPRESS AND RELEASE
(to cancel disconnect tone)
2. Pitch Trim …………………………….…………………….….….. Retrim if necessary, using the trim wheel
NOTE
The autopilot disconnect may be accompanied by a red boxed PTCH (pitch) or ROL on the
PFD, indicating the axis which has failed. The autopilot cannot be re-engaged with either of
these annunciations present.