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.
O 35 knots.
O 18 knots.
O 25 knots.
O 29 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.
O 20 knots.
O 28 knots.
O 30 knots.
O 32 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?
O 23 knots.
O 16 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?
O 15 knots.
O 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?
O Runway 32.
O Runway 6.
O Runway 29.
O Out of limits.
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?
O Runway 14,
O Runway 10.
O Runway 24.
O Runway 10/28.
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?
O 19 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:
O 680 NM
O 645 NM
O 710 NM
O 450 NM
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:
O 608 NM with TAS 167 kt.
O 600 NM with TAS 156 kt.
O 670 NM with TAS 142 kt.
O 710 NM. with TAS 114 kt.
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:
O 6 h
O 6.2 h
O 4.1 h
O 5 h
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:
O 905 NM with TAS 114 kt.
O 910 NM with TAS 112 kt.
O 732 NM with TAS 144 kt.
O 905 NM. with TAS 109 kt.
138 Refer to Endurance Profile diagram, (Fig.19) The endurance, at 2400RPM/ max. power settings and fully loaded at ISA conditions, should be approximatelly:
O 3.7 h at PA 8000 ft.
O 4.2 h at PA 12000 ft.
O 6.0 h at PA 8000 ft.
O unpredictable.
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:
O 580 NM at 93 KTAS.
O 580 NM at 122 KTAS.
O 485 NM at 122 KTAS
O 580 NM at VNE
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.
O 992 ft
O 1240ft
O 550ft
O 1488ft.
141 Determine the short field ground roll required, for the a/c in (Fig.23). Given: PA………………………………2000 ft OAT………………………… ISA Wind ……………………….. nil.
O 510 ft
O 500ft
O 520ft
O 1240ft.
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
O 2150 ft
O 1485ft
O 1336ft
O 670ft.
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.
O Time to climb 17 mins. Fuel & distance to climb 5.5 gallons and 35mins.
O Time to climb 19 mins. Fuel & distance to climb 6.5 gallons and 39mins.
O Time to climb 15 mins. Fuel & distance to climb 4.5 gallons and 36mins.
O Time to climb 20 mins. Fuel & distance to climb 7.0 gallons and 41mins.
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)
O 760 fpm and 15mins.
O 1030 fpm and 18 mins.
O 710 fpm and 18 mins.
O 815 fpm and 13 mins.
145 The True Air Speed for the best rate of climb when climbing from sea level up to the service or operational ceiling:
O tends to increase.
O tends to decrease.
O remains about constant.
O tends decreasing to converge with TAS for the best angle of climb.
146 An approach to land is made into wind because:
O this reduces both the ground speed and ultimately the landing distance required (LDR).
O it increases ground speed and decreases landing distance.
O this provides a better accelerated stop distance (ASDA)
O reduces ground speed and the landing distance available (LDA).
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:
O make a 180° turn or descend into warmer air layers.
O climb "ON TOP",of the cloud if capable.
O fly into the warmer air inside the cloud.
O continue on present course as clouds of extensive vertical development do not have extensive horizontal development, relying on de-icing systems.
148 Increasing an aeroplane's all up weight by will:
O increase both the take-off run and the stalling speed.
O increase both the rate and angle of climb.
O increase the manoeuvrability.
O decrease its inherent stability.
149 Select the statement that will result in a degraded performance and handling capability and which could result in the structural limitations being exceeded under certain flight conditions.
O An aeroplane that is over weight.
O An aeroplane operated at Vne.
O An aeroplane operated at above its maximum landing weight.
O An aeroplane operated at Vno.
150 When is carburetor icing most likely to occur:
O In summer with descent power setting.
O In summer during climb.
O In winter during climb.
O In winter during cruise power setting.
151 Limitations relating to aeroplane certification in the Normal Category are:
O an aeroplane maximum weight of below 5700kg restricted to no spinning or aerobatics and bank angles limited to 60°.
O the same those exist for Class A, aeroplane classification categories.
O an aeroplane maximum weight of below 5700kg, fully certified to aerobatics.
O an aeroplane maximum weight of below 5700 lb, restricted to no aerobatics and bank angles limited to 45°.
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