Specifications

SECTION VII
MODEL 560 FLIGHT PLANNING AND PERFORMANCE
CLIMB
Multiengine climb performance is presented in tabulated form on the following pages. The climb
presented is based on 247 KIAS/0.62 INDICATED MACH.
This performance is based on maximum continuous thrust setting on both engines (refer to the
Multiengine Normal Climb thrust setting chart, Figure 7-6), gear and flaps up, speedbrakes retracted and
anti-ice systems OFF. The performance is also presented for anti-ice systems ON.
The time, distance, fuel and rate-of-climb used to any given altitude is based on the climb starting at
sea level. If the climb is initiated at some other altitude, it is necessary to go into the data twice, once at
the initial altitude and once at the final altitude. The difference in time, distance and fuel between these two
altitudes provides the proper values for the climb. The data allows for fuel burnoff in the climb; therefore,
the weight presented is at the start of the climb.
The climb data for the conditions requiring a step climb are based on climbing direct to the highest
obtainable altitude as shown in the step climb weight table, cruising at the altitude until the desired weight is
achieved, and then climbing to the desired altitude or the next step altitude per the step climb weight table.
I 56OMB-01 Configuration AA 7-57