Term
| Engine shutdown conditions... 13 of them |
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Definition
1. Engine fire
2. Turbine overheat
3. Nacelle overheat
4. Uncontrollable power
5. Propeller malfunctions
6. High TIT
7. Increasing oil temp
8. Decreasing oil pressure
9. Throttle control failure
10. Unusual vibration or roughness
11. Visible fluid leak
12. Start valve open light illumination (1790 and 1700 series)
13. Engine CHIP warning light w/ secondary indications |
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Term
Emergency signals: Ground evacuation
Abandon airplane: |
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Definition
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Term
Emergency signals: Ditching or crash landing
Prepare for ditching or crash landing: |
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Definition
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Term
Emergency signals: Ditching or crash landing
Brace for impact: |
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Definition
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Term
| Start valve open light illumination on the ground (1700s) |
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Definition
1. Move all throttles to ground idle
2. Move condition lever to Ground Stop for engine
3. Place the affected bleed air regulator to OFF |
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Term
| Start valve open light illumination in air (1700s) |
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Definition
1. Perform ESP
2. Place bleed air regulator to OFF |
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Term
Engine fire:
On the ground |
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Definition
1. Move all throttles to Ground Idle
2. Perform ESP |
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Term
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Definition
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Term
| Tailpipe fire during start |
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Definition
| 1. Follow Ground Evacuation Procedure |
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Term
Turbine Overheat Warning
On the ground |
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Definition
1. Move all the throttles to ground idle
2. Place condition lever to Ground Stop |
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Term
Turbine Overheat Warning
In flight |
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Definition
1. Retard the throttle for the affected engine toward Flight Idle
2. Land as soon as practical
3. If condition persists, perform ESP |
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Term
Nacelle overheat warning
On the ground |
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Definition
1. Move all the throttles to ground idle
2. Perform ESP |
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Term
Nacelle overheat warning
In flight |
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Definition
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Term
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Definition
1. Move all throttles to Ground Idle
2. Place the TD Control Switch for the affected engine in the NULL position
3. If this fails to eliminate the condition, place the condition lever to Ground Stop. |
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Term
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Definition
WARNING: If TIT is stabilized at 1083 degrees and throttle position is unrelated, see Engine Systems Failure
1. Retard throttle for the affected engine toward Flight Engine
2. Place TD Control Switch in Null
3. If condition persists, perform ESP |
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Term
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Definition
If blockage is suspected, such as due to a bird strike, and verified by lower torque, higher TIT, ect., perform ESP.
If blockage is suspected but not verified, ESP is recommended. |
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Term
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Definition
1. Tower/ Ground- Notified
2. Parking brake- Set (not on side of hot brakes)
3. DC Bus Tie Switch- Tied
4. Pressurization- Emergency Depressurization |
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Term
Brake systems failure
Normal Brake failure |
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Definition
| 1. Brake select switch- Emergency |
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Term
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Definition
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Term
| Unsatisfactory Anti-skid Test |
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Definition
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Term
| Takeoff Continued after Engine Failure |
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Definition
1. Maintain directional control with flight controls and engine power as necessary
NOTE: Complete ESP as soon as possible to reduce drag
2. Raise gear and accelerate to flap retraction speed
WARNING: It is important to reach VMCA2 prior to raising flaps above 15%. |
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Term
Takeoff Continued after Engine Failure
Obstacle clearance is a consideration... |
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Definition
WARNING:
-Gear retraction is initiated three seconds after takeoff
-Propeller feathering initiated 6 seconds after takeoff
-Flap retraction should be accomplished in 10% increments w/ speed increasing approx. 5 KTS in between |
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Term
|
Definition
-One pump each for booster and utility will be out (operation of equipment will take longer)
-No 1 and No 4 Generator out |
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Term
|
Definition
-One pump each for booster and utility will be out (operation of equipment will take longer)
-Auto. Ice Detection will be out (use manually)
-No 2 and No 3 Generator out
-Synchrophaser master will be INOP |
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Term
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Definition
-No utility system. Wing flaps and landing gear operated manually. Aux system is available for Nose Gear Extension. Aux system available for emergency brakes.
-Flight controls supplied by booster system at half normal force.
-Nosewheel steering and anti-skid are not operative.
-No 1 and No 2 generator out |
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Term
|
Definition
-One pump each for Utility and Booster out (operation of equipment may take longer)
-No 1 and No 3 generator out |
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Term
|
Definition
-One pump each for Utility and Booster out (operation of equipment may take longer)
-No 2 and No 4 generator out |
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Term
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Definition
-No booster system.Flight controls supplied by utility system at half normal force.
- No. 3 and No. 4 generator out |
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Term
Propeller malfunctions
During takeoff: |
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Definition
1. Don't adjust affected throttle
2. Continue takeoff while maintaining directional control
NOTE: If ESP immediately, and prop fails to feather, higher than normal VMCA may result. Unless on fire, recommend VMCA2 is reached first. |
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Term
Propeller malfunctions
Prop Low oil warning light-
RPM w/in Limits |
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Definition
1. DON'T TOUCH THROTTLE!
2. Immediate landing feasible-attain 150 KTAS (if possible) and ESP
-Immediate landing not feasible-perform Pitchlock Check Procedure |
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Term
Propeller malfunctions
Prop Low oil warning light-
RPM outside allowable limits |
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Definition
1. DON'T TOUCH THROTTLE!
2. Immediate landing feasible-attain 150 KTAS (if possible) and ESP
-Immediate landing not feasible- Prop Governing Switch-MECH GOV |
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Term
Propeller malfunctions
RPM outside allowable limits (w/out prop low oil light) |
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Definition
1. DON'T TOUCH THROTTLE!
2. Prop Governor Switch-MECH GOV |
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Term
Propeller malfunctions
Prop fails to feather |
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Definition
CAUTION: Pull ignition control circuit breaker prior to resetting fire handle to prevent inadvertent ignition
1. Fire handle-Reset (if pulled and no indication of fire exists)
2. Feather override button-Hold in for 30 sec. then pull out |
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Term
| Indications of an engine and propeller decouple: |
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Definition
1. RPM may temp. increase then settle to normal.
2. Hydraulic pressure, generator output, and G/B oil pressure will remain normal.
3. Near zero torque, low TIT, low fuel flow, low Engine oil pressure
*ESP and don't restart |
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Term
| Prop brake failure (feathered propeller) |
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Definition
1. Reduce airspeed (not slower than VMCA1 out)
-if prop brake doesn't engage, eng. and G/B aren't receiving oil, land as soon as practicable)
-if prop stops rotating, determine if acceleration is appropriate |
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Term
| Indications of a Throttle Control Failure |
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Definition
1. Throttle moves independently of pilot input
WARNING: Do not attempt to restrain a throttle which moves on its own. To do so may cause the prop to go immediately into reverse or to full power.
2.Throttle frozen or binding
3. Power indication unrelated to throttle position |
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Term
| If a throttle moves independently of pilot input or a throttle is frozen or binding you should... |
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Definition
ESP!!! (talk about using the Fire Handle)
WARNING: Do not attempt to restrain a throttle which moves on its own. To do so may cause the prop to go immediately into reverse or to full power. |
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Term
| If power increase/decrease, not pilot-initiated, occurs or is suspected, a throttle control cable or TD System malfunction should be suspected. Proceed as follows: |
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Definition
1. TD Valve (affected engine)-NULL
-if power returns to normal, see TD Control Valve System Malfunction.
-If power remains unrelated, perform ESP. |
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Term
| A TD Control Valve System Malfunction may cause... |
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Definition
| A sudden increase/decrease in TIT with an accompanying change in torque and fuel flow. |
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Term
| If a sudden increase/decrease in TIT with an accompanying change in torque and fuel flow occurs during stabilized operation, you should... |
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Definition
Place the TD Control Valve Switch for the affected engine in the NULL position.
-If TIT stabilizes and returns to normal, leave switch in NULL and continue operation.
-If malfunction persists, other engine systems are at fault. |
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Term
| Secondary Fuel Pump Pressure Light Illumination |
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Definition
| NOTE: If secondary fuel pump pressure light comes on or flickers while on cross-feed from the aux or external tanks, discontinue cross-feed. If light is extinguished, this could be an indication of a malfunctioning pressure switch or other mechanical issues. See -1. |
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Term
| Secondary Fuel Pump Pressure Light Illumination |
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Definition
1. Discontinue cross-feed from the aux/externals (see if light goes out)
2. Pull ignition control CB for corresponding engine
-if light goes out, failure of the 65% switch in the speed sensitive control is indicated
3. If light remains illuminated, reset circuit breaker and land as soon as practicable. Failure of primary pump has occurred.
-ESP at secondary indications (fluctuation in fuel flow, TIT, ect.) |
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Term
Speed-Sensitive Control Failure (Sheared Shaft)
Throttle above 65 degrees:
Indications are... |
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Definition
-Momentary illumination of secondary fuel pump pressure light
-fuel correction light on
-TIT will not exceed start limiting temp of 830. |
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Term
Speed-Sensitive Control Failure (Sheared Shaft)
Throttles below 65 degrees:
Indications are... |
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Definition
-Momentary illumination of secondary fuel pump pressure light
-TIT will not exceed start limiting temp of 830. |
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Term
Speed-Sensitive Control Failure (Sheared Shaft)
Proceed as follows: |
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Definition
1. Throttle for the affected engine-RETARD
2. TD Valve Switch for the affected engine-NULL
3. Ignition Control CB-PULLED |
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Term
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Definition
| -If oil pressure is decreasing out of limits, perform ESP. |
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Term
| Increasing Oil Temperature |
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Definition
1. Hold Oil Cooler Flap switch in the open position until oil cooler flap is in the open position (ask Load to verify)
2. Thereafter, manually open/close oil cooler flap as required
3. If engine oil temp can not be maintained w/in limits, ESP |
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Term
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Definition
1. If visible fluid leak (ESP)
2. No visible fluid leak, no corrective action is required as long as engine instruments are within limits.
-Secondaries (ESP) |
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Term
| If during the flight the aircrew notices a loss of oil quantity with heavy smoke coming from the tailpipe area, you should... |
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Definition
| Monitor the engine and ESP prior to landing. This should prevent oil combustion in the tailpipe after landing. |
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Term
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Definition
| Mission may be continued at the pilot's discretion. The engine should be monitored for SECONDARIES. If secondaries are present perform ESP. |
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Term
CHIP Warning light
On the ground |
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Definition
1. Place all throttles to Ground Idle
2. Place applicable Engine Condition Lever to Ground Stop |
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Term
CHIP Warning light
In flight |
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Definition
| Engine should be monitored for SECONDARIES. Land as soon as PRACTICABLE. If any secondaries are present, perform ESP. |
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Term
| Tach Generator failure may be indicated by... |
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Definition
1. Decrease or fluctuation of RPM
2. Decrease or fluctuation of Torque |
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Term
| If a Tach Generator failure occurs, proceed as follows... |
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Definition
1. Synchrophase Master Switch (if the affected engine is selected)-OFF/other Master
2. Propeller Governing Control Switch-MECH GOV |
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Term
Overtorque
19,600-21,500 in-lb |
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Definition
| Record in ALMIS/EAL. Continues operation is permitted. |
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Term
Overtorque
exceeds 21,500 in-lb |
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Definition
| Land as soon as practicable. Maintenance action is required prior to further flight. |
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Term
| A fuel boost pump failure, in a tank containing fuel, will be indicated by... |
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Definition
A low-pressure warning light (main tanks) or a tank empty light (AUX/EXT).
-For a main or aux tank, verify pressure. |
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Term
| If a fuel boost pump failure is confirmed of either A, B, or C phase circuit breakers (tripped), preoceed as follows... |
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Definition
1. Boost pump switch-OFF
2. Boost pump circuit breakers-PULL
3. Set up another fuel supply-as required |
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Term
| If an ext. tank empty light illuminates when its quantity gauge indicates fuel aboard, it could be a failure of the pump or one of several other components. Proceed as follows... |
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Definition
1. EXT tanks alt. pump-ON
2. Pump being used when light illuminated-OFF
-break of the BOOK! |
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Term
| If a main tank boost pump failure occurs during climb-out... |
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Definition
| Cross-feed the engine from another tank and continue climb to mission altitude. |
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Term
| If the fuel quantity indicator goes off-scale high or low, fails to press-to-test, or is inop,... |
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Definition
| Pull the associated fuel quantity gauge circuit breakers. |
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Term
| If an EXT or AUX tank dump valve fails to open when fuel dumping from that tank is desired... |
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Definition
| The fuel may be dumped through the bypass valve and the operative dump system for the EXT or AUX tank on that side. |
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Term
| If an EXT or AUX tank cross-feed valve fails to open when cross-feed operation from that tank is desired... |
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Definition
| Open the bypass valve for that tank and the operative EXT or AUX cross-feed valve on that side. |
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Term
| If the source of a fuel leak is unknown, it is recommended to... |
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Definition
| To establish tank to engine fuel flow and establish a fuel log. |
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Term
| If an external fuel leak is encountered near an engine,... |
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Definition
| Shutdown of the engine should be considered. Land as soon as POSSIBLE without using reverse thrust. |
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Term
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Definition
1. Advise ATC facility of the intensions to dump fuel
2. HF-ALE to STBY
3. Set fuel system for tank-to-engine flow... |
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Term
| Illumination of an AC Bus OFF Light |
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Definition
1. If the affected Generator Out light is also illuminated, place the generator switch to OFF. (break out the book)
2. If affected Generator Out light is not illuminated and systems assoc. with the bus are operating normally, verify volts, freqs, and load for affected generator... (break out book) |
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Term
| Indications of Partial Loss of the Essential AC Bus |
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Definition
1. Failure of Normal Brakes (on ground)
2. Erratic autopilot operation
3. Loss or malfunction of heading indication
4. Aux. hydraulic pump failure.
5. Illumination or flickering of No.2 fuel boost pump low pressure light.... |
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Term
| Partial Loss of the Essential AC Bus |
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Definition
1. All four propeller governing control switches-MECH GOV
2. Turn generator powering Ess. AC bus at the time to OFF
-If power is restored, follow Generator disconnect procedures
3. If power is not restored, BREAK OUT THE BOOK! |
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Term
| The circuit breakers that may be used to reduce the load on the Ess. AC Bus are color coded.... |
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Definition
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Term
| If a generator failure is confirmed during ground operations,... |
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Definition
| The affected engine may be shut down (Ground Stop) in lieu of the generator disconnect procedure. |
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Term
| Illumination of Generator Out Light |
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Definition
Generator Out? CHECK IT OUT!
Check volts, freqs, and load and break out the book!! |
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Term
Illumination of Generator Out Light
Voltage, Frequency, and Load are normal |
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Definition
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Term
Illumination of Generator Out Light
Frequency and voltage are normal, but no load is indicated... |
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Definition
| Leave generator switch on and monitor frequency and voltage. If voltage and frequency are lost, proceed with Generator Disconnect Procedure. |
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Term
Illumination of Generator Out Light
No voltage, frequency, or load... |
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Definition
1. Place generator switch OFF the ON-If frequency, voltage and load return to normal, continue operation.
2. If Freqs, volts and load don't come back, disconnect and land as soon as practicable. |
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Term
| The generator can be mechanically disconnected from the engine by holding the GEN DISC switch in DISC for approx. ___ seconds. |
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Definition
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Term
| Multiple Engine Power Loss/ RPM Rollback |
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Definition
1. Tank-to-engine fuel flow
2. All four TD Valve switches-NULL
3. Synchrophase Master Switch-OFF
4. Propeller Governor Switches-MECH GOV
***BREAK OUT BOOK!!*** |
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Term
| Loss of Secondary AC Systems |
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Definition
1. Select other power source
2. If failure continues, turn affected AC system off. |
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Term
| Illumination of the Isolated DC Bus on Battery Light |
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Definition
| In-flight failure of the reverse current relay. Battery power conservation measures must be initiated. Determine what ISOL DC and Battery power items may be turned off. Land as soon as POSSIBLE!! |
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Term
| Illumination of the Isolated DC Bus on Battery Light, for a maximum of ____ sec., is normal when items with high electrical starting loads are placed on the _____ Bus |
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Definition
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Term
Electrical Fire
If fire, smoke, or overheat of electrical equipment occurs, every attempt should be made to locate the malfunctioning unit and isolate by.... |
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Definition
| Turning off, pulling circuit breakers, or removing electrical plugs. |
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Term
Electrical Fire
With Operable ATM/APU |
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Definition
1. Tank-to-engine fuel flow
2. Prop Gov Control switches-MECH GOV
3. ATM/APU switch-START, RUN |
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Term
BUS ISOLATION PROCEDURE
LH AC |
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Definition
| Remove 3 LH AC Bus power current limiters at FS 245 |
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Term
BUS ISOLATION PROCEDURE
RH AC |
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Definition
| Remove 6 current limiters at FS 245 (3 RH AC Bus and 3 Deicing Power) |
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Term
BUS ISOLATION PROCEDURE
MAIN AC |
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Definition
| Remove 3 MAIN AC bus current limiters at FS 245 |
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Term
BUS ISOLATION PROCEDURE
MAIN DC |
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Definition
| Pull 6 MAIN TR circuit breakers on the copilot upper circuit breaker panel and the Main Ground Control circuit breaker on the copilot lower circuit breaker panel. |
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Term
BUS ISOLATION PROCEDURE
ESS AC |
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Definition
| Pull the 9 ESS AC circuit breakers at FS 245 and 9 ESS AC circuit breakers on pilot side circuit breaker panel. |
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Term
BUS ISOLATION PROCEDURE
ESS DC |
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Definition
**OIL COOLER FLAPS OPEN/FIXED!!**
Pull 6 MAIN TR circuit breakers on copilot upper circuit breaker panel and 6 ESS TR circuit breakers on pilot side circuit breaker panel. Do not tie the BUS TIE switch after landing. |
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Term
| Will the aircraft(1700 series) pressurize without the ESS DC bus?? Why? |
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Definition
No.
Any time power is removed from the ESS DC bus the engine bleed air regulators will close, shutting off airflow to both A/C packs. |
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Term
| Do you have fire detection after isolating the ESS DC bus? |
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Definition
| No. Land as soon as POSSIBLE!! |
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Term
BUS ISOLATION PROCEDURE
ISOL DC |
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Definition
| Pull the 6 Main TR circuit breakers on the copilot upper circuit breaker panel and the 6 ESS TR circuit breakers on the pilot side circuit breaker panel, and turn the DC power switch to the off position. **No ICS** |
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Term
BUS ISOLATION PROCEDURE
BAT BUS |
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Definition
| You can't isolate the BAT BUS DUMMY!!! |
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Term
|
Definition
1. Seat belts-FASTENED
2. Oxygen-AS REQUIRED
3. Pressurization- BEGIN DEPRESSURIZATION |
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Term
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Definition
1. Close engine bleed air regulators (affected wing) and bleed air divider valve.
2. Tank-to-engine fuel flow
3. Turn generators/all electrical equip. off (affected wing) |
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Term
Indications are:
1. Illumination of APU Fire light
2. Erratic operation of engine instruments
3. Lower than charted torque value
4. Erratic operation of electrical equipment
5. Reduced bleed air manifold pressure |
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Definition
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Term
MAJOR BLEED AIR LEAK
FE will proceed as follows... |
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Definition
1. Engine bleed air switches (for the affected wing)-CLOSED/OFF
2. Bleed air divider valve-CLOSED |
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Term
MAJOR BLEED AIR LEAK
After isolation of bleed air leak following a bleed air duct failure, proceed as follows: |
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Definition
1. Reduce airspeed to 180 KIAS MAX
2. Operate airplane at minimum bank angles.
3. Reduce cabin pressure to a max. of 10 in. Hg.
LAND AS SOON AS POSSIBLE!!! |
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Term
| If an overheat warning light or gauge indicates an overheat condition, proceed as follows... |
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Definition
1. See overheat chart
2. If overheat condition is eliminated, land as soon as practicable.
3. If overheat persists, land as soon as POSSIBLE! |
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Term
| If an engine bleed air regulator cannot be closed (valve failure verified by observing torque) and bleed air system is leaking,.... |
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Definition
| It may be necessary to shut down the engine. |
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Term
EMERGENCY OPERATION OF AIR CONDITIONING SYSTEMS
With fumes/ smoke emitting from the air conditioning system, it may be necessary to... |
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Definition
| Place the FLT STA AIRFLOW SWITCH to MAX to determine which system has the malfunction. |
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Term
EMERGENCY OPERATION OF AIR CONDITIONING SYSTEMS
If the system cannot be shut off because of a regulator malfunctioning and its leaking bleed air,... |
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Definition
| Close bleed air regulators on that wing,(#1 and #2 for FLT STA; #3 and #4 for CARGO COMP) and close bleed air divider valve. |
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Term
| FLT DECK/CARGO COMPARTMENT AIR CONDITIONING SYSTEMS FAILURE |
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Definition
1. FLT STA airflow switch-MIN
2. Cargo compartment fan-ON |
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Term
FLT DECK/CARGO COMPARTMENT AIR CONDITIONING SYSTEMS FAILURE
In the event that either A/C pack shuts off automatically due to an over pressurization condition in the water separator (froze up), proceed as follows... |
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Definition
| Select a warmer temperature with the temp control switch/knob, for the affected system. After at least 3 minutes, place air conditioning master switch to OFF and then to original position. |
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Term
EMERGENCY OPERATION OF CABIN PRESSURIZATION SYSTEM
Closing #1 and #2 bleed air regulators and bleed air divider valve will cause what? |
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Definition
| Loss of operation of automatic pressurization (isolates bleed air from jet pump in outflow valve) and slowing of emergency depressurization (isolates bleed air from safety valve). |
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Term
EMERGENCY OPERATION OF CABIN PRESSURIZATION SYSTEM
Increasing Pressure |
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Definition
1. Immediately shut off bleed air, one engine at a time, until the rate of pressure increase is at a safe (comfortable value)
2. Control pressure by using bleed air as necessary to vary amount of conditioned air
3. If necessary for further control while descending, one of the A/C systems can be shut down to expedite depressurization. |
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Term
EMERGENCY OPERATION OF CABIN PRESSURIZATION SYSTEM
Decreasing Pressure |
|
Definition
1. Crew should don oxygen masks immediately
2. Descend to or maintain an airplane altitude where oxygen is not required.
3. Check for excessive cabin leakage by checking doors, windows, hatches, and the safety valve. |
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Term
IN-FLIGHT RELEASE OF LIFE RAFT
INDICATIONS |
|
Definition
| Vibrations which can range from slight to severe. These vibrations could be accompanied with bumps and bangs from the wing root area, and pitch and yaw control problems. |
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Term
| If severe vibration occurs in flight, cause unknown, proceed as follows... |
|
Definition
1. Retard power and decrease airspeed.
2. Lower the flaps and have an aircrew member make a visual inspection of the life raft compartments and tail. |
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Term
| If the inner or outer pane of the of the windshield or cargo compartment windows crack during flight, ... |
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Definition
| Reduce cabin differential pressure to 10 in. Hg. or less. |
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|
Term
| If both panes of the windshield crack (FLT DECK)... |
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Definition
| Flight may be continued at 10 in. Hg. or less |
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|
Term
| If both panes of a cargo compartment window crack,... |
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Definition
| Reduce differential pressure to 0. |
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Term
NESA MALFUNCTION
If panels feel excessively hot, electrical arcing, or one of the panels containing thermistors... |
|
Definition
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|
Term
INOP WINDSHIELD ANTI-ICING
Operation with inoperative windshield anti-icing is permissible provided.... |
|
Definition
1. Airplane is not flown into known icing
2. The max. speed limit below 10,000 FT is 185 KIAS due to possible bird strikes. |
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Term
| ILLUMINATION OF PITOT HEAT OFF INDICATORS (CG 1717 AND UP) |
|
Definition
| Secure the affected system by placing the control switch to OFF and avoid flying into known icing conditions. Break out the book to see what systems will be lost in icing conditions. |
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|
Term
|
Definition
1. Oxygen-ON/100 PERCENT
2. Seat belts- FASTENED
3. Descend-AS REQUIRED |
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|
Term
HYDRAULIC SYSTEMS FAILURE
Loss of System Pressure or Leakage from an Undetermined Source |
|
Definition
1. Hydraulic pump switches-OFF (affected system only)
2. Suction boost pump switch-OFF (affected system only)
3. Hydraulic reservoir panel-Checked |
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Term
HYDRAULIC SYSTEMS FAILURE
Engine-Driven Pump Failure |
|
Definition
1. Hydraulic pump switch-OFF
2. Hydraulic reservoir level-CHECKED |
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|
Term
HYDRAULIC SYSTEMS FAILURE
in the event utility or booster hydraulic pressure in excess of 3,500 psi... |
|
Definition
| Indication of a failed pump compensator, do not shut off individual hydraulic pump switches. If shutoff valves are closed, excess pressure may build up until the pump or line ruptures. |
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Term
HYDRAULIC SYSTEMS FAILURE
In the unlikely event that pressure in either system exceeds 3,900 psi... |
|
Definition
1. Shut down an engine supplying pressure by using CRUISE ENGINE SHUTDOWN PROCEDURE.
2. If hydraulic pressure drops to normal, continue with 3 engine operation.
3. If pressure remains high, airstart shutdown engine and ESP other engine in affected hydraulic system. |
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|
Term
HYDRAULIC SYSTEMS FAILURE
Electric Suction Boost Pump Failure indication... |
|
Definition
| May be indicated by illumination of suction boost pressure warning light (<20 psi) and/or 100-200 psi drop in static system pressure. |
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|
Term
HYDRAULIC SYSTEMS FAILURE
Electric Suction Boost Pump Failure, proceed as follows... |
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Definition
1. Suction boost pump switch-OFF
2. Static pressure and hydraulic reservoir level-CHECKED |
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Term
FLIGHT CONTROL SYSTEMS FAILURE
Flight Control Hydraulic Booster Unit Failure
If a leak develops, proceed as follows... |
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Definition
1. Determine location of the leak.
2. Respective system control boost switch-OFF
3. If leak was isolated, and land as soon as practicable. |
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Term
FLIGHT CONTROL SYSTEMS FAILURE
Flight Control Hydraulic Booster Unit Failure
If a hydraulic booster unit fails in a hardover position... |
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Definition
1. Verify the cockpit control matches the maneuver being experienced.
2. Both respective control boost switches-OFF
3. Land as soon as POSSIBLE |
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Term
FLIGHT CONTROL SYSTEMS FAILURE
Tab System Failure
Trim tab circuit breakers are color coded... |
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Definition
| Red (ESS AC) on pilot side circuit breaker panel |
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Term
FLIGHT CONTROL SYSTEMS FAILURE
Runaway Aileron trim |
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Definition
1. Hold aileron trim tab switch in opposite direction
2. Pull AILERON TRIM TAB circuit breaker |
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Term
FLIGHT CONTROL SYSTEMS FAILURE
Runaway Rudder trim tab |
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Definition
1. Reduce airspeed until directional control is regained
2. Hold Rudder trim tab in opposite direction
3. Pull rudder trim tab circuit breaker |
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Term
FLIGHT CONTROL SYSTEMS FAILURE
Runaway Elevator Trim |
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Definition
1. Hold elevator trim tab switch on control wheel in opposite direction, and place the power selector switch OFF.
2. Place the elev tab power selector switch in the EMER position, and retrim the airplane. |
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