Why are yaw rate and pitch rate obtained by these equations? I am reading "Introduction to Aircraft Aeroelasticity and Loads" by Jan R. Wright and Jonathan E. Cooper. 

The book said: In steady bank turn (as shown in picture below), The rate of turn is given by: 
$\omega_{turn} = V/r $  (I understand this)


And so the aircraft experiences steady yaw and pitch rates given
by':

$n_{yaw}= \omega_{turn}cos \phi$

$q = \omega_{turn}sin \phi$

I don't understand 2 equations above. I think the yaw rate would be equal to the turn rate and the pitch rate is zero.
Turn rate is referenced to earth axes, yaw rate to aircraft axes, hence the $cos\Phi$:


If you turn at $\Phi$ = 0, your rate of turn is the yaw rate and the pitch rate is zero. 
If you turn at $\Phi$ = 90°, your yaw rate is zero and your pitch rate = rate of turn.


In order to maintain a steady turn and not lose altitude the pilot does need to pull on the stick when turning..