While on the ground and the aircraft is parked, how does one check if the standby or emergency gyro is operational?

16 minutes ago, Matt Sdeel said:

While on the ground and the aircraft is parked, how does one check if the standby or emergency gyro is operational?

Pull the knob to cage it.  If it’s upright and stays that way, it’s working. 

Short answer: In general, the standby attitude indicator is powered by a source independent of the aircraft's electrical system. From its own battery or the battery bus, which is considered independent and separate. Roughly, it should last about 30 minutes. 

During power-up, verify that no red warning/light is visible, cage to align, and verify stable with the aircraft position reference to the ground. Some are vacuum systems and may require higher engine RPM than idle to provide proper indications.

Edited March 28Mar 28 by LRBS

Will shaking the plane like suddenly braking the plane or if there's a sudden strong gush of wind make it vibrate or shudder if it's working properly?

To the extent that the aircraft's attitude changes (for example a slight nose-down movement when braking), you should see that reflected on the attitude indicator. "Vibrating" sounds more like a malfunction though.

Just to be aure: You're asking for simulation purposes, right? If this is about a real-world attitude indicator, don't take advice from me, ask a qualified flight instructor or mechanic.

11 hours ago, Matt Sdeel said:

Will shaking the plane like suddenly braking the plane or if there's a sudden strong gush of wind make it vibrate or shudder if it's working properly?

Well, bottom line.

Pneumatically driven gyros are vulnerable to any  accelerations (change in airspeeds or turning)

This acceleration will (after procession) indicate a false right roll, whereas the pendulum vanes will sense a false vertical and indicate an incorrect pitch-up movement.

And the opposite goes for deceleration.

For electric driven Attitude Indicators, the above do not really hold true. They have corrections applied to the platform and spins much faster. But gentle maneuvers and sustained turns can - in some designs (Mercury tilt switch)- cause gyro erection errors and indicate level flight in banked turns.

Sorry if I misunderstood the question 

6 hours ago, SAS443 said:

Well, bottom line.

Pneumatically driven gyros are vulnerable to any  accelerations (change in airspeeds or turning)

This acceleration will (after procession) indicate a false right roll, whereas the pendulum vanes will sense a false vertical and indicate an incorrect pitch-up movement.

And the opposite goes for deceleration.

For electric driven Attitude Indicators, the above do not really hold true. They have corrections applied to the platform and spins much faster. But gentle maneuvers and sustained turns can - in some designs (Mercury tilt switch)- cause gyro erection errors and indicate level flight in banked turns.

Sorry if I misunderstood the question 

So does that mean that there should be some movement on the standby gyros when the aircraft suddenly stops or suddenly accelerates or make a turn while on the ground?