Section 3 Flashcards
Maximum Decceleration Can Be Obtained by Maximum Braking Below ___kts
130kts
Optimum Braking Should Not be Attempted Above ___kts
100kts
Any time the aircraft departs a hard surface (taxiway or runway), immediately
Shutdown both engines
During heavy gross weight aborts, the nose will lower at approximately
120 Knots
Aerodynamic braking is more effective than cautious wheel braking above
100 Knots
If the abort was made as a result of an engine fire, place the throttle of the affected engine to OFF once
A/C is under control followed by emergency ground egress
Aerodynamic Braking Pitch Attitude
12 NH
SETOS Ensures ___fpm Climb Gradient
100fpm
SETOS and SETOS +10 KCAS, single-climb performance increases at the rate _____ of for each knot of airspeed above SETOS
8 to 50 fpm
SETOS climb should be restricted to only that required to avoid obstacles until the airspeed reaches
200 Knots
Fuel consumption with gear, gear/flaps 60 and gear/flaps full in lbs/min and lbs/NM
- Gear: 40lbs/min, 10 lbs/NM
- Gear/Flaps 60: 50lbs/min, 12lbs/NM
- Gear/Flaps Full: 60lbs/min, 15lbs/NM
Gear retraction, when initiated between SETOS +10 KCAS and 200 KCAS, may require up to _____ minutes with a left engine failure
1 minute
level flight/climb capability is obtained at ____ KCAS with 60% flaps or at ____ KCAS with the flaps up during SETOS
- 200 Knots
- 220 Knots (if high gross weight flap retraction after 220K)
Tire Failure Effects Most Pronounced Below ___kts
100kts
If Engine is Shutdown in Flight, Wait ___ Seconds Before Attempting a Restart
10 Seconds
During SE Operations, Turn Both Boost Pumps On and Crossfeed On When Below ___lbs in Either Fuel System
250lbs
Zoom Maneuver Should Be ___ Degrees Nose High
20 Degrees
Minimum RPM For Restart During Flight (To Provide Fuel Flow Through PVC Valves)
12-14%
Leave Throttle at Idle for ___ Seconds Before Aborting an air restart
30 Seconds
If Loss of Canopy May Occur or Has Occur, Slow Below ___kts
300kts
Minimum Drag Airspeed
225kts
The UTILITY HYDRAULIC or FLIGHT HYDRAULIC caution light will illuminate for either a
fluid overtemperature or a low pressure condition but not a high pressure condition
If the right engine is to be shut down, check _____?
Why?
- check right crossover
- If crossover is bad, consider lowering 60% flaps to reduce landing distance and trim the aircraft to final approach airspeed (fuel permitting). If crossover is good, leave generator OFF
Hydraulic pressure provided solely by a windmilling engine is _______ to control the aircraft for landing.
insufficient
If one system reads zero, hydraulic system transfer may occur. In this case, flight time could be limited to only ____ minutes.
35 minutes
The EED fuel flow indicator(s) on the inoperative engine may read as high as ____ PPH.
60 PPH
Left Generator No Cross INDICATIONS
-All AOA indexer lights on.
-Utility hydraulic gauge freezes. Left oil pressure and
left fuel flow EED indications display OFF.
-Master Caution with Left Gen light and Left Fuel Px lights
-At night, all interior and exterior lights except caution, warning, and indicator lights, flood lights, and utility lights lost.
Right Generator No Cross INDICATIONS
- Flight hydraulic gauge freezes, right fuel flow, and both fuel quantity EED indications display OFF. Oil pressure indications freeze.
- MASTER CAUTION, RIGHT GENERATOR, RIGHT FUEL PRESS, and ENG ANTI-ICE ON lights illuminate.
- At night, when Caution and Warning lights are set to DIM, Caution, Warning, and Indicator lights go to bright.
GENERATOR FAILURE - PARTIAL
• Boost pump (LEFT/RIGHT FUEL PRESS light may be on)
• Transformer-rectifier (XMFR RECT OUT light on)
• Flaps (slow flap actuation)
• HUD (two or more phase failures required to affect
HUD operations)
RIGHT ESSENTIAL 28-VDC BUS FAILURE ELECTRONICS LOST
Loss of TACAN and UHF radio indicates right essential 28-VDC bus failure.
LEFT ESSENTIAL 28-VDC BUS FAILURE ELECTRONICS LOST
- loss of VHF radio communications
- VOR/ILS is lost and DME limited to the last channel that was tuned.
- TACAN range and bearing is operational and steering information is accurate but limited to the last selected EGI destination.
- Flap control and speed brake are not operative.
- Landing gear operates normally, but position/warning lights function only in dim mode, if dim mode is selected.
- Attitude information is limited to a minimum of 9 minutes based on standby attitude indicator inertia.
Turning crossfeed on should cause the LEFT/RIGHT FUEL PRESSURE light(s) to go out. If not,
possibly fuel leak
If the FIRE light goes out, check the light by positioning the WARNING TEST switch to TEST. If one or both bulbs of the affected FIRE light does not illuminate, it indicates a possible burn-through of one or both fire sensors. Do what?
shutdown engine
When a FIRE light is preceded or accompanied by a pop, bang or thump
shutdown engine
Simultaneous failure of the engine RPM indications and oil pump (oil pressure indi- cates zero) may be an indication of
sheared oil pump shaft
T/F Under single-engine low fuel conditions (approximately 250 pounds in either system) with two operating boost pumps, placing the CROSSFEED ON and both BOOST PUMPS ON will provide the maximum usable fuel.
True
Heart of engine restart RPM range`
18-20%
T/F If dual engine flameout occurs, the right engine should be attempted first as right engine instruments will operate normally as soon as engine start button is pushed.
True
For a compressor stall do what
Rapidly retarding the throttle to IDLE and immediately pushing the engine start button may permit the engine to recover and prevent complete flameout.
If interconnect cable failure occurs after flaps are down 60% or more, a sudden pitch-up will occur and the aircraft will stall instantaneously. Full forward stick will be necessary to arrest the rate of pitch-up and the pilot must take corrective action within _____ seconds to ensure recovery without a loss of altitude.
3 seconds
The stability augmentor yaw system can fail with a result- ing rudder deflection of _____. This deflection will cause a yaw and resulting moderate rudder roll.
2 degrees
If a touchdown speed greater than ____ KCAS is computed,
another controllability check at a lower fuel weight should be considered. Touchdowns greater than ___ KCAS should not be attempted
200 KCAS
200 KCAS
After controllability check Maintain at least ___ KCAS above minimum controllable airspeed during descent and landing approach.
20 KCAS
After controllability check fly a power-on straight-in approach requiring minimum flare. Plan to touch down at ____knots above either normal touchdown speed or minimum control speed, whichever is higher.
10 Knots
First 5 steps of Alternate gear extension
- Airspeed - 240 KCAS OR LESS
- FLAPS - AS REQUIRED
- Gear door switch - OPEN
- Landing gear lever - LG DN
- Landing gear alternate release handle - PULL APPROXIMATELY 10 INCHES AND HOLD UNTIL GEAR UNLOCKS; THEN STOW HANDLE
Non-landable configurations
- one main down only
- only nose down
- nose and one main down
As a guide, the no flap landing distance is approximately
2X (2500 + fuel weight) + 1000’ (touchdown point)
