If a hydraulic system fails completely or an uncontrollable leak occurs, the airplane should be _______________
Answer: landed as soon as practicable
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KC135
- Failure to close the engine bleed valves on the ___________ side of the manifold could cause damage to the airplane wing components due to escaping bleed air
- Application of hydraulic pressure to the main gear during manual extension may result in ___________
- If the source of the leakage in the system cannot be determined, the hydraulic fluid quantity gauge for the affected system should be monitored during and after actuation of the crossover valve lever. If a fluid loss of the unaffected system is observed, return the _______ to _________
- It is safe to use the crossover valve after loss of fluid from either hydraulic system, provided pressure can be ________ and ________ in the affected system with the appropriate hydraulic pressure and aux pump switches on. When the LH system is affected, set the inboard spoiler switch to cut-off. When the RH system is affected set the CIPS generator switch to EMER and turn the rudder power switch to OFF
- Given: the left hydraulic pressure gauge indicates 1,800 psi with no other indications. You have determined that the accumulator preload is low and have repressurized the system. To check the actual system pressure, read the ____________ gauge by cycling the pilot's brakes
- Given: the right hydraulic system pressure gauge indicates a sustained pressure of 3,550 psi with no indication of fluid loss or overhear. Immediately __________ the ______ system.
- Given: Loss of fluid in the right hydraulic system with no other indications, immediately depressurize the ________ system.
- Given: A loss of quantity in the left hydraulic system with no other indications. You have followed the procedure through closing the supply switch for the outboard pump, but there is still a fluid loss. You would now try to isolate the leak by placing __________ to cutoff.
- Given: Loss of quantity in the right system with no other indications. Depressurizing the right hydraulic system does not stop the fluid leak. The next step is to close the __________ for the ______ pump.
- Given: a loss of hydraulic quantity with no other indications. Immediately _______ the affected system.
- Given: the number three hydraulic pump inoperative light comes on with loss of fluid. Immediately move the number three _____________ to closed.
- Given: the number four hydraulic pump inoperative light comes on with no indications of fluid loss and remains on after the right hydraulic system is depressurized and repressurized. Set the _________ pump supply switch to closed.
- To prevent excessive fuel pressure surges at completion of fuel dumping, set the ______ pump switches to ______ prior to setting the fuel dump switches to OFF
- Since the possibility exists that a main tank leak is caused by a skin crack rather than fuel line failure, it is mandatory to ______________ to reduce the possibility of further structural failure.
- Discontinue emergency tank emptying procedure before the fuel quantity indication reaches the ____ marking on the fuel quantity gauge.
- Indications of possible fuel leakage include:
- A broken and/or jammed drive chain in the forward stabilizer trim mechanism can prevent __________ or ________________ trimming
- To ___________, any repositioning of the crossover valve should be done smoothly an rapidly.
- A creeping stabilizer is a stabilizer that does not remain in a ________ and may be caused by partial loss of the stabilizer jackscrew braking. Trim position should be monitored at all times and the _________ should be held as required to maintain trim position. Under this condition, the airplane should be ________ as soon as practicable
- If inadvertent or incorrect stabilizer trimming occurs during flight, the runaway is most apt to be caused by an electrical malfunction and can best be stopped by setting the tab trim cutout switch to CUTOUT. If the trim wheel continues to rotate after the stab trim switch is set to CUTOUT, the aircrew should _______________________
- When the rudder power switch is turned off, check rudder pressure ____________
- (Runaway Stabilizer Trim During Takeoff) If above S1, the _____ will set the stab trim switch to ________
- The boldface for Uncommanded Rudder, Yaw, Roll is:
- For nose up trim, set the _______ switch to CUT-OFF and raise the speed brakes
If the answers is incorrect or not given, you can answer the above question in the comment box. If the answers is incorrect or not given, you can answer the above question in the comment box.