HP d212 Manual do Utilizador descarregar pdf (Página 96)

FMS-D212-725-1

Page 3-20

This document is private and confidential and is supplied on the express condition that it is not to be used for any

purpose or copied or communicated to any other person without written permission from Dart Aerospace Ltd.

Revision:

TC Approved Date: 08.12.17

3.5.6 Loss of Pitch Change Control Linkage

Indications:

In this type of failure, pitch change mechanism is broken at some point and

the tail rotor will assume a blade angle determined by aerodynamic and

counterbalance forces.

Procedures:

Corrective action procedures are described in FIXED PITCH FAILURES

above. The specific procedure to be used depends on yaw change

experienced.

3.6 Hydraulic System

The helicopter has two hydraulic powered flight control systems (1 and 2).

Both systems supply power to collective and cyclic, but tail rotor is powered

only by system 1.

If system pressure or temperature exceeds limits, affected system should be

turned off. Continued flight and normal maneuvers can be accomplished on

remaining system. Land as soon as practical. If system no. 1 fails and is

turned off, tail rotor control forces will increase but no change in limitations

result.

Indications:

1. #1 or #2 HYDR SYST caution light is illuminated.

If SYS 1 has failed:

2. Pedal forces will increase

Procedure:

1. HYD SYS 1 and 2 switches – Verify ON

2. Affected Hydraulic CONT circuit breaker – OUT, if hydraulics not

restored, push IN.

3. Affected HYD SYS switch – OFF

4. Airspeed – As desired

5. Land as soon as practical.

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HP d212 Manual do Utilizador Página 96