3 ATTENT. FLIG. PER. EXAM. PREP.

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:

140 Determine the short field landing distance required from 50ft(screen height), for the a/c in (Fig.23). Given: PA………………………………SL OAT………………………… 30?C Wind ……………………….. 18 kt Head.

141 Determine the short field ground roll required, for the a/c in (Fig.23). Given: PA………………………………2000 ft OAT………………………… ISA Wind ……………………….. nil.

142 Determine the short field landing distance required from 50ft(screen height), for the a/c in (Fig.22), to full stop. Given: PA………………………………4000 ft OAT………………………… 10?C Wind ……………………….. 9 kt Tail

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.

144 The aircraft is fully loaded with skydivers, takes off from S.L. to 13.500 ft. The OAT is 15° C. Estimate the mean indicated ROC and the time to lift off (Fig 25)

145 The True Air Speed for the best rate of climb when climbing from sea level up to the service or operational ceiling:

146 An approach to land is made into wind because:

147 Having inadvertently flown into the vicinity of cloud which has extensive vertical and horizontal development, accretion of wing ice is observed. Your immediate action should be:

152 If an aeroplane with a lift/drag ratio of 9/1 was at 9000ft, the maximum distance it could glide in still air conditions would be:

153 Published take-off performance data, is complied from aircraft operating on:

154 Increasing or decreasing the power setting in a single engined aeroplane, changes the pitch attitude because:

155 When landing, if the TAS is significantly less than the ground speed, you will have:

156 If the stalling speed of an aeroplane in the landing configuration (Vso) is 55kt, what should be the minimum approach speed.

157 The airspeed should be kept relatively high during a prolonged climb so that:

162 The required fuel load for a flight is 500 pounds. Given that the specific gravity of the fuel is 0.73, how much fuel in litres should be uplifted, presuming the tanks are empty?

163 Before refuelling, an aircraft, had a weight of 2122 pounds and the total moments were 75900 lb in aft of the datum. 354 lb of fuel were loaded which had an effective arm of 48 inches aft of the datum. The new total aft of datum moments were:

164 In case of a full complement of passengers and maximum possible baggage load are to be carried:

165 An oil tank containing 3 US gallons of oil weighing 6 lb/gal . And is 17 inches from the aeroplane datum point. The oil tank moment, will be:

166 13 Imperial gallons of fuel with a specific gravity of 0.72 weighs:

167 Aeroplane planned take-off weight = 2122lb. Calculated C of G for departure = 35.78 inches aft of the datum. Planned fuel burn during the flight = 354lb, positioned 48 inches aft of the datum. What is the calculated C of G position in inches aft of the datum for landing?

168 For a given fuel load, if the aircraft all up weight is increased, the range will:

173 The probable consequence of any ambient temperature increase upon air density and aircraft performance would be: