Hawker 850XP Pro Line 21 Airplane Flight Manual
Page 2
FAA Approved
Original Issue: Feb 28, 2006
Sub-section - 5.45
LANDING WAT DATA
INTRODUCTION
This Sub-section contains curves of weights at which for varying altitude and temperature the
Go-around and Approach Climb requirements of 14 CFR PART 25.119 and 25.121(d)
respectively are complied with and at which the energy input to the wheel brakes during a
normal landing is within the wheel brake normal capacity.
On Figure 5.45.1 the less steep lines on the left of the chart are determined by the Approach
Climb requirement with flaps 15
°
, landing gear up, and one engine failed. The steep lines on
the right of the chart are determined by the wheel brake energy requirement.
MAXIMUM LANDING WEIGHT FOR ALTITUDE AND TEMPERATURE
Instructions For Use Of Chart
The use of the graph is illustrated by broken arrowed lines.
To Determine the Landing WAT Limit Weight
• Enter from the left with the field pressure altitude. Move across to the air temperature.
• From the intersection of the air temperature and field pressure altitude, read the weight
on the bottom scale.
NOTES:
1. To obtain the effect of engine antice, add 10° C to the actual air temperature before
entering the graph.
2. Refer to Sub-section 5.50 to obtain the maximum weight for landing field length
available.
For Training Purposes Only