Dash 1 Ch 1 Flashcards
One engine thrust, MIL and MAX:
2200/3300
Fuel flow for one engine, MAX at rest and Mach 1:
7300, 11,400 lb/hr
Pushing start arms ignition circuit for ___
30 sec
One engine normal oil capacity and air expansion space:
4 qt, 1 qt
Gravity flow guaranteed up to ___ alt:
6,000
Fuel cutoff switches operated by ___ and cut off fuel in ___:
DC, 1 sec
Fuel low level light comes on after ___ sec below ___ amount
7.5. 250 lbs
Gearbox shift occurs at ___ range:
65-75%
Voltage of battery is ___V and of DC rectifiers is ___V:
24, 28
AC system provides ___/___V power:
115/200
AC generators cut-in between ___:
43-48%
Min battery voltage of ___ is required to close batt relay:
18 V
Left engine provides ___ psi for ___ system:
3200, utility
Right engine provides ___ psi for ___ system:
3200, flt control
Hyd low press comes on at ___ psi, and goes back out at ___ psi:
1500, 1800
Rudder limited to ___ deg each side when nosegear out 3/4 or less:
6 deg
Landing gear extension/retraction takes approx ___:
6 sec
Gear horn and warning light come on when gear not down and locked and ____ kts or less, attitude ___ or below, and both throttles below ___:
210 kts, 10,000, 96%
When accelerating, gear light may not go out until ___:
240 kts
Landing gear alt release pulled out ___ inches, and requires ___ sec:
10 in, 15-35 sec
Rear canopy follows front by ___ after canopy jettison:
1 sec
Aneroid delays parachute opening until between ___:
15,000 to 11,500
Seat ejection occurs ___ after canopy jettison:
0.3 sec
Fuel for left engine is ___ gal serviced/usable and ___ lbs usable:
293/286 gal, 1916 lbs
Fuel for right engine is ___ gal serviced/usable and ___ lbs usable:
305/297 gal, 1990 lbs
Total fuel is ___ gal serviced/usable and ___ lbs usable:
598/583 gal, 3906 lbs
With single-engine and less than ___ in either system, leave both boost pumps on and crossfeed on:
250 lbs
A minimum of ___ RPM is required to achieve any engine fuel flow
12-14%
___% RPM is the heart of airstart envelope at any altitude:
18-20%
Ignition must occur before fuel flow reaches ___:
360 lb/hr
After aborted start, wait ___ min before attempting another start:
2 min
If EGT doesn’t rise w/in ___ sec of fuel flow indication, abort start:
12 sec
Flaps should be +/- ___ of 60% position:
5%
Normal rotation speed on initial takeoff is ___:
141 KIAS (this is rounded to 145)
Normal liftoff speed on initial takeoff is ___:
165 KIAS
Delay takeoff a min of ___ minutes behind large and ___ behind heavy aircraft
2, 4
With a xwind > __ knots, spacing behind large/heavy aircraft can be reduced
5
Abort takeoff if either afterburner doesn’t light within ___ sec:
5
Final turn speed is ___ plus I knot per 100 lb over 1000 lb fuel:
180 KIAS
Final appr speed is ___ plus I knot per 100 lb over 1000 lb fuel:
160 KIAS
Touchdown speed is ___ plus I knot per 100 lb over 1000 lb:
135 KIAS
Minimum Hydraulic pressure ___:
1500 psi
Each generator is ___ phase:
3
The O2 low light comes on at or below ___ liter, may blink at or below ___:
1, 3 liters
Below __, the engine anti-ice is always open, regardless of switch position:
65 % RPM
There are ___ rotating beacons, located where ___:
2, tail/lower fuselage
Battery energizes DC bus for ___:
15 minutes at 80% power
If oil pressure is high in cold weather, should be in limits Win ___:
6 min
The radio attenuation switch reduces UHF and VHF volume by ___:
66%
IDENT sends a pulse with transponder replies for ___ seconds:
15
Standby Al provides ___ deg climb, ___ deg dive, ___ deg roll capacity, and provides ___ minutes of useful info within +/- ___ deg after DC failure:
92, 78, 360 deg, 9 min, + 6 deg
Maintain a minimum of ___ RPM to ensure effective anti-ice operation:
80% RPM
Due to oil supply restriction, zero G flight restricted to ___ sec:
10 sec
Due to oil supply restriction, negative G flight restricted to ___ sec:
30 sec
Rudder system failure may push rudder to ___ deg
30 deg
Stab aug system failure may push rudder to ___ deg
2 deg
Touchdown greater than ___ KCAS should not be attempted
200 kts
With asymmetric flaps, maintain ___ kts above final appr/touchdown speed:
20 kts;
Do not touchdown at less than ___ kts with asymmetric flaps:
165 kts
On SE go-around, climb only as necessary until reaching ___ kts:
200 kts
When landing with all gear up, touch down ___ kts faster than normal:
10 kts
Maximum speed for nosewheel on runway:
174 kts
Estimation for landing roll is ___ ft + fuel (not including 1000 ft down):
2500 ft
Landing roll approximately ___ for no flap landing:
doubled
Anti-ice will cause a loss of ___ % thrust in MIL and ___ in MAX:
8.5%, 5.5%
If flab-slab interconnect fails and flaps needed for landing, ___ % flaps provides adequate control authority and controllable stick forces:
30-45%
Pressure reg. maintain cabin alt of ___ +/- ___ from ___ alt.to ___ alt:
8000 +/- 2000, 8 to 23
Avoid Max thrust dives when below ___ lb in either fuel tank:
650
Use ___ knots as go/no-go for simple tire failure:
100 kts
Increase final approach speed and touchdown speed by ___ gust factor:
½
Increase final turn, approach and touchdown by ___ kts for no flap:
15 kts
How many seconds until full parachute deployment:
3.42 sec
Landing light retraction takes ___ sec:
10 sec
AOA max range is ___. Max endurance/best angle of climb is ___:
0.18,0.3
Nozzles should stabilize within ___ sec after rapid throttle movements:
10 sec
Max allowable sink rates for landing: ___ fpm normal landing and ____ fpm crab landing (>1700 lbs fuel); and ____, _____ for
340, 200, 590, 395
First 4½ “ of stick travel provides ___ aileron deflection, Next 1½ “ of stick travel provides ___ aileron deflection:
50% , Full
Crossfeed recommended with fuel imbalance of ___ or greater:
200 lbs
Holding airspeed:
250-265 kts
Radar pattern typically burns ___ fuel:
325 lbs
Turbulent air/thunderstorm penetration speed is ___ kts:
280 kts
Climb possible at SETOS is ___ fpm:
100 fpm.
Climb increased by ___ fpm each kt between SETOS - SETOS + 10:
8-50 fpm
Gear retraction may take ___ when retracted between SETOS+ 10 and 200:
1 min
If unable to retract gear, best climb at ___ for 60% flaps, ___ for 0% flaps:
200 kts, 220 kts
Optimum pitch for ejection zoom:
20 deg
With loss of canopy, slow to ___ kts; min drag occurs at ___ kts:
300, 225 kts
If one hydr system reads zero, hydr system transfer may occur, and flight time could be limited to ___ min:
35 min
Controllability check should be accomplished at ___ AGL or higher:
6,000 ft
Maintain ___ kts above min controllable airspeed in descent/landing approach:
20 kts
Best glide speed is ___ kts + I knot/ 100 lbs fuel:
230
Multiply altitude in thousands of feet by ___ for glide distance in NM:
1.7
Max crosswind, dry runway (dash-1):
30 kts
Max crosswind, wet runway:
20 kts
Max crosswind, icy or standing water:
10 kts
Gross weight with fuel and two souls
12,800 lbs
