Sennheiser SI 234 - ANNEXE 802 Operations Instructions download pdf (Page 362)

Airplane Description DA 42 NG AFM

Page 7 - 14 Rev. 3 01-Apr-2014 Doc. No. 7.01.16-E

To test the gear warning system (refer to 4A.6.1 - PRE-FLIGHT INSPECTION) push the

test button close by the gear selector switch. The aural gear alert should appear.

CAUTION

If the aural alert does not appear, an unscheduled

maintenance is necessary.

To prevent inadvertent gear retraction on ground, an electric squat switch prevents the

hydraulic valve from switching if the master switch is on and the gear extension switch

is placed in the UP position.

After take-off, the gear should be retracted before an airspeed of 152 KIAS is exceeded.

The landing gear may be extended at any speed up to 188 KIAS.

The landing gear is designed to be manually operated in the event of failure. Since the

gear is held in the retracted position by hydraulic pressure, gravity will allow the gear to

extend if the system fails for any reason. To extend and lock the gears in the event of

failure, it is only necessary to relieve the hydraulic pressure by means of the emergency

gear extension lever, which is located under the instrument panel to the left of the center

console. Pulling this lever releases the hydraulic pressure and allows the gear to fall free.

Before pulling the emergency gear extension lever, place the gear selector switch in the

DOWN position.

NOTE

If the emergency gear extension has been pulled due to an

emergency, the system has to be checked before pushing

the lever in again.

The nose gear is steerable by the use of full rudder pedal travel. A gear damping element,

incorporated in the nose gear steering system, prevents shimmy tendencies. When the

gear is retracted, the nose wheel centers as it enters the wheel well, and the steering

linkage disengages to reduce pedal loads in flight.

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Sennheiser SI 234 - ANNEXE 802 Operations Instructions Page 362