125 (Refer to Fig.9) Determine the maxi¬mum wind velocity for a 45° crosswind if the maxi¬mum crosswind component for the airplane is 25 knots.

126 (Refer to Fig.9) Determine the maxi¬mum wind velocity for a 50° crosswind if the maxi¬mum crosswind component for the airplane is 23 knots.

127 (Refer to Fig.9) What is the maximum wind velocity for a 30? crosswind if the maximum crosswind component for the airplane is 12 knots?

128 (Refer to Fig.9) What is the maximum wind velocity for a 35 ? crosswind if the maximum crosswind component for the airplane is 17 knots?

129 (Refer to Fig.9) With a reported wind of north at 20 knots, which runway (6, 29, or 32) is acceptable for use for an airplane with a 13-knot maxi¬mum crosswind component?

130 (Refer to Fig.9) With a reported wind of south at 20 knots, which runway (10, 14, ή 24) is appropriate for an airplane with a 13-knot maximum crosswind component?

131 (Refer to Fig.9) What is the crosswind component for a landing on Runway 18 if the tower reports the wind as 220° at 30 knots?

134 Refer to Range Profile diagram (Fig. 20). The still air range, cruising at 20.000 ft and fully loaded at Std. ISA, with 45mins. reserve fuel allowance, 55% cruise power settings, should be approximatelly:

135 Refer to Range Profile diagram (Fig. 20). The still air range, cruising at 24.000 ft and fully loaded at Std. ISA, with 45mins. reserve fuel allowance, 75% cruise power settings, should be approximatelly:

136 Refer to Endurance Profile diagram (Fig. 21). The endurance, with 45% cruise power settings at PA 16.000 ft, allowing 45 mins. reserve fuel and fully loaded at ISA conditions, should be approximatelly:

137 Refer to Range Profile diagram (Fig. 17). The still air range, cruising at 12.000 ft and fully loaded at Std. ISA, with 45mins. reserve fuel allowance, 45% cruise power settings, should be approximatelly:

138 Refer to Endurance Profile diagram, (Fig.19)
The endurance, at 2400RPM/ max. power settings and fully loaded at ISA conditions, should be approximatelly:

139 Refer to Range Profile diagram, (Fig.18)
The still air range, cruising at 6000 ft and fully loaded at Std ISA, based on 45mins. reserve fuel allowance, at 45% BHP and FF of 4.1 gallons, should be:

143 Estimate from graph in Fig.24, the Time, Fuel and Distance to climb.
Given: OAT at take off………………………………..10°C
OAT at cruise …………………………………. -10°C
Airport PA ……………………………………….2000ft
Cruise altitude ………………………………12000ft
Initial climb weight……………………….3650 lb
Power ……………………………………….full throttle.