Emergency

DA 42 NG AFM

Procedures

3.11.5 FUEL SUPPLY FAILURE
1. FUEL SELECTOR . . . . . . . . . . . . . . . . . . . .	CROSSFEED /
	affected engine

WARNING

In case of a fuel supply failure a fuel pump inspection is required prior to the next flight.

2. Fuel quantity . . . . . . . . . . . . . . . . . . . . . . . . . monitor

3. Fuel pump of affected engine . . . . . . . . . . . . ON

If fuel supply failure remains:

4. FUEL SELECTOR . . . . . . . . . . . . . . . . . . . . . ON 5. Fuel pump of affected engine . . . . . . . . . . . . ON

6. Fuel quantity . . . . . . . . . . . . . . . . . . . . . . . . . monitor

CAUTION

Switching on the fuel pump in combination with CROSSFEED may cause damage to the high-pressure pump.

END OF CHECKLIST

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3.11.6 RECOVERY FROM AN UNINTENTIONAL SPIN

CAUTION

Spin recovery has NOT been shown during certification as it is NOT required for this airplane category. The given recovery method is based on general experience!

CAUTION

Intentional spins are prohibited in this airplane. In the event a spin is encountered unintentionally, immediate recovery actions must be taken.

Single-engine stalling is not permitted.

CAUTION

Steps 1 to 4 must be carried out immediately and

	simultaneously.
1.	POWER lever . . . . . . . . . . . . . . . . . . . . . . . .	IDLE
2.	Rudder . . . . . . . . . . . . . . . . . . . . . . . . . . . . .	full deflection against
		direction of spin
3.	Elevator (control stick) . . . . . . . . . . . . . . . . .	fully forward
4.	Ailerons . . . . . . . . . . . . . . . . . . . . . . . . . . . . .	neutral
5.	FLAPS . . . . . . . . . . . . . . . . . . . . . . . . . . . . .	UP

CONTINUED

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Emergency			DA 42 NG AFM
Procedures
When rotation has stopped:
6.	Rudder . . . . . . . . . . . . . . . . . . . . . . . . . . . . .	neutral
7.	Elevator (control stick) . . . . . . . . . . . . . . . . . .	pull carefully

8.Return the airplane from a descending into a normal flight attitude. Do not exceed the 'never exceed speed', vNE = 188 KIAS.

END OF CHECKLIST

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Procedures

3.11.7 EMERGENCY DESCENT
1.	FLAPS . . . . . . . . . . . . . . . . . . . . . . . . . . . . .	UP
2.	Gear . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .	DOWN
3.	POWER lever . . . . . . . . . . . . . . . . . . . . . . . .	IDLE
4.	Airspeed . . . . . . . . . . . . . . . . . . . . . . . . . . . .	as required

WARNING

Max. structural cruising speed . . . . . . . vNO = 151 KIAS.

Never exceed speed in smooth air . . . . vNE = 188 KIAS.

END OF CHECKLIST

3.11.8 EMERGENCY EXIT

In case of a roll over of the airplane on ground, the rear side door can be used as exit. For this purpose unlock the front hinge of the rear side door. The function is displayed on a placard beside the hinge.

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Emergency

DA 42 NG AFM

Procedures

3.11.9 AUTOPILOT OR ELECTRIC TRIM MALFUNCTION / FAILURE

NOTE

An autopilot or electric trim malfunction may be recognized by an unexpected deviation from the desired flight path, abnormal flight control or trim wheel movement, or flight director commands which cause unexpected or contradictory information on the other cockpit displays. It may be accompanied by the aural autopilot disconnect tone, a red

AFCS, red PTCH, red ROL, red YAW, red AP or yellow AP indication on the PFD, or a yellow CHECK ATTITUDE on the PFD. The autopilot and AHRS monitors normally detect failures and automatically disconnect the autopilot.

Failure of the electric pitch trim, indicated by a red boxed PTRM flashing on the PFD, may not cause the autopilot to disconnect. Be alert to possible autopilot out of trim conditions

(see AUTOPILOT OUT OF TRIM procedure below), and expect residual control forces upon disconnect. The autopilot will not re-engage after disconnect with failed pitch trim. If AUTOPILOT OUT OF TRIM ELE indication is present, expect substantial elevator forces on autopilot disconnect.

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NOTE

Accomplish items 1 and 2 simultaneously!

1.	Airplane control stick . . . . . . . . . . . . . . . . . . .	grasp firmly and regain airplane
		control
2. AP DISC switch . . . . . . . . . . . . . . . . . . . . . . .		DEPRESS AND HOLD
3.	Trim . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .	retrim airplane manually as
		required
4.	AUTOPILOT circuit breaker . . . . . . . . . . . . . .	pull
5. AP DISC switch . . . . . . . . . . . . . . . . . . . . . . .		RELEASE

NOTE

When the AUTOPILOT circuit breaker is pulled, the manual electric trim and autopilot autotrim systems will be disabled.

WARNING

Do not attempt to re-engage the autopilot following an autopilot, autotrim, or manual electric trim malfunction until the cause for the malfunction has been corrected.

END OF CHECKLIST

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Procedures

Intentionally left blank.

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