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TR > 13 Hydraulics > Flashcards

13 Hydraulics Flashcards

1
Q

🟧 OVERHEAT
- in ELEC 2/1

A

HYD fluid (to cool and lubricate the electric motor driven pump) has overheated or pump itself has overheated
- power automatically removed from AC electrical driven pump

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2
Q

ENGINE HYDRAULIC PUMP SWITCH
- ON

A

O - de-energizes blocking valve in pump to allow pump pressure to enter system
- should always remain on at shutdown to prolong solenoid life

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3
Q

Hydraulic system quantity
Hydraulic system pressure
- when both pumps off:

A

Q - indicates 0%-106% digitally
P - normal pressure 3000 PSI, max pressure 3500 PSI
W - indication may read hydraulic system reservoir pressure, normally < 100 PSI

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4
Q

HYD refill indications
- when valid:
- when illuminated:

A

V - ONLY when aircraft on ground with both ENG shutdown or after landing with flags up during taxi-in
I - hydraulic quantity below 76%

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5
Q

FLIGHT CONTROL SWITCH

A

STBY RUD = activates standby pump and opens standby rudder shutoff valve to pressurize STBY rudder PCU

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6
Q

Which HYD system to pressurize ALL flight controls

A

EITHER A or B, with NO decrease in controlability

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7
Q

HYD ENG DRIVEN PUMP
-failed
- switched to OFF
HYD ELECTRIC DRIVEN PUMP

A

ENG - provides 6 times HYD fluid compared to electric
- FAIL: ELEC pump on and HIGH demand on system: can result in low pressure
- operates as long as ENG is still operating
ELEC - AC electric motor-driven pump

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8
Q

Pulling ENG fire switch

A

shuts off HYD fluid to ENG driven pump

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9
Q

Heat exchanger
- why
- located

A

used for cooling and lubrication of pumps through heat exchanger before turning to reservoir.
- System A: main tank 1
- System B: main tank 2

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10
Q

MIN fuel quantity for ground operation of electric motor-driven pump

A

760 KG in related main tank

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11
Q

Check valve
system pressure transmitter

A

C - isolates related pump from Hydraulic system
S - sends combined pressure (ENG+ ELEC) to HYD system pressure indicator

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12
Q

SYSTEM A LEAK
- in ENG pump
- in ELEC pump

A

ENG: due to standpipe the quantity will NOT drop more than 20%, system A pressure (below 20%) will be maintained by ELEC pump
ELEC: quantity slowly decreases to 0 and the pressure will be lost

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13
Q

SYSTEM B LEAK
- in ENG pump or ELEC pump
- standpipe

A

Quantity INDICATIONS will decrease to 0% and the B pressure will be lost
Standpipe: will make sure if EITHER pump B Leakes and indications read 0, the fluid remaining (below standpipe) will be sufficient for PTU operation

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14
Q

Does a leak in HYD B effect STBY HYD SYSTEM

A

NO

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15
Q

POWER TRANSFER UNIT
- purpose
- uses what to power what
- operates when:

A

P - Supply additional HYD fluid when ENG pump B is inoperative

  • User SYS A pressure to power hydraulic motor driven pump which than pressurizes HYD B fluid
  • operates when all of these occur:
  • SYS B ENG driven pump hydraulic pressure drops below limits
  • airborne
  • flaps NOT up
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16
Q

Landing Gear Transfer Unit
- purpose
- supply
- when operating

A

P - SYS A ENG pump lost, it supplies the volume of HYD fluid needed to raise the landing gear

S - SYS B ENG pump supplies the volume of HYD fluid needed to operate the LGTU when ALL of these occur:
- airborne
- No 1 ENG RPM drops below a limit value
- landing gear lever in UP position
- either main landing gear NOT up + locked

17
Q

STBY HYD SYSTEM
- activated manual: positioning either FLT CTRL switch to STBY RUD:

A
  • activates STBY ELEC
  • closes FLT CTRL Shutoff valve, this deactivates LOW PRESSURE light
  • opens STBY RUD valve
  • allows STBY system to power rudder + thrust reversers
  • illuminates STBY RUD ON, MASTER CAUTION + FLT CTRL lights
18
Q

STBY HYD SYSTEM
- activates automatic: initiated when:
- automatic operation:

A
  • loss of system A OR B, and
  • flaps extended, and
  • airborne or wheel speed > 60 KTS, and
  • FLT CONTROL switch A or B HYD system ON
    —– OR ——
  • Main PCU FFM (Force Flight Monitor) trips
  • activates the STBY ELEC motor-driven pump
  • opens STBY rudder shutoff valve
  • allows STBY system to power rudder + thrust reversers
  • illuminates STBY RUD ON, MASTER CATUION, FLT CTRL LIGHTS
19
Q

LEAK in STBY HYD system
- decrease quant
- system B

A

STBY reservoir quantity decreases to 0, when STBY reservoir reaches half empty > 🟧 LOW QUANTITY

SYS B continues to operate normally, but reservoir B decreases until 70%

20
Q

Variations in HYD Quantity
- during normal operation
- not pressurized properly at higher altitudes

A

During normal operation:
- system becomes pressurized after ENG start
- raising/lowering landing gear of LE devices
-cold soaking occurs during long periods of cruise

Foaming can occur:
- HYD pressure fluctuations
- LOW PRESSURE light blinking
- MASTER CAUTION + HYD

TR (18 decks)

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