Each aircraft has a specific pitch attitude and airspeed that  corresponds to the most efficient climb rate for a specified  weight. The POH/AFM contains the speeds that produce the  desired climb. These numbers are based on maximum gross  weight. Pilots must be familiar with how the speeds vary with  weight so they can compensate during flight.  To enter a constant airspeed climb from cruise airspeed,  slowly and smoothly apply aft elevator pressure in order  to raise the yellow chevron (aircraft symbol) until the tip  points to the desired degree of pitch.  [Figure 7-63]  Hold  the aft control pressure and smoothly increase the power  to the climb power setting. This increase in power may be  initiated either prior to initiating the pitch change or after  having established the desired pitch setting. Consult the POH/ AFM for specific climb power settings if anything other than  a full power climb is desired. Pitch attitudes vary depending  on the type of aircraft being flown. As airspeed decreases,  control forces need to be increased in order to compensate  for the additional elevator deflection required to maintain  attitude. Utilize trim to eliminate any control pressures. By  effectively using trim, the pilot is better able to maintain the  desired pitch without constant attention. The pilot is thus  able to devote more time to maintaining an effective scan of  all instrumentation. The VSI should be utilized to monitor the performance of the  aircraft. With a smooth pitch transition, the VSI tape should  begin to show an immediate trend upward and stabilize on a  Straight Climbs and Descents Entry Constant Airspeed Climb From Cruise Airspeed XPDR 5537 IDNT LCL10:12:34  INSET  PFD  CDI  XPDR  IDENT  TMR/REF  NRST  ALERTS  5 338  $_{1}$1652  200  46  13.7  2500  25.0  VOR 1 270 °  2  1  1  2  5 00  5300  5200  5100  5000  4900  4800  4300  3600  3500  3400  3300  3200  3100  20 80 5040 5000  150  140 130 100 110 90  1 120 9 TAS 126KT  OAT 6°C  NAV1 108.00 113.00 NAV2 108.00 110.60 134.000 118.000 COM1 123.800 118.000 COM2 $_{WPT }$_ _ _ _ _ _$_{ DIS }$_ _ ._ $_{NM}$ $_{DTK }$_ _ _$_{°}$ TRK 360° Current procedure  Before procedure  2300  23.0  Primary power Primary bank Primary pitch 500 Figure 7-63.  Constant airspeed climb from cruise airspeed. 7-46