Untitled Quiz

Hydraulic Power - Objectives

• Training objectives for this section are outlined on the graphic.

Hydraulic Power - Objectives (Page 2)

• Upon completion of training, you will be able to recall safety precautions for working on hydraulic power systems.
• Describe access to the hydraulic power systems and components.
• Describe the location of principal hydraulic power system components.
• Describe the function and normal operation of hydraulic power systems.
• Identify sources of information relevant to hydraulic power system fault isolation.
• Analyze information from sources to troubleshoot and correct hydraulic power system faults.
• Describe the procedure for removal and replacement of hydraulic power system components.
• Identify special tooling and equipment unique to the hydraulic power system.
• Give a full summary of the hydraulic power systems.

Hydraulic Power - Introduction (Page 3)

• Three independent hydraulic systems supply power for user systems.
• Main and auxiliary hydraulic systems supply pressurized fluid to airplane systems.
• Two thrust reversers, power transfer unit (PTU) motor, landing gear extension and retraction, nose wheel steering, and main gear brakes are supplied with pressurized fluid by systems A and B.
• Primary and secondary flight controls are also supplied.
• These systems comprise the hydraulic power system; main hydraulic systems, ground servicing system, and auxiliary hydraulic systems, hydraulic indicating systems.
• Main Hydraulic Systems are A and B. System A has most of its components on the left side of the airplane and system B on the right side.
• Ground servicing system fills all hydraulic reservoirs from a central location.
• Auxiliary Hydraulic Systems comprise the standby hydraulic system and the power transfer unit (PTU).
• Standby hydraulic power supplies reserve power for rudder, leading edge flaps and slats, and two thrust reversers.
• The PTU system provides alternative hydraulic power for the leading edge flaps, slats, and autoslat system.
• Hydraulic indicating systems show system A and B reservoir quantity, standby reservoir low quantity, and system A and B pressure in the flight compartment.

Hydraulic Power - Introduction (Page 4)

• System A and B engine-driven pump (EDP) low pressure
• System A and B electric motor-driven pump (EMDP) low pressure
• Standby electric motor-driven pump (EMDP) low pressure
• System A and B electric motor-driven pump (EMDP) overheat.
• The 737 short field performance (SFP) option allows operators to fly with increased payload in and out of airports with runways less than 5000 feet.
• Two position tail skid protects the fuselage during lower takeoff and landing speeds.
• Leading edge slats increase lift during takeoff.
• Spoiler actuators increase extension to help slow the airplane during landing.
• Hydraulic fluid BMS 3-11, TYPE IV erosion arresting, fire resistant fluid is used.

Hydraulic Power - Abbreviations (Page 4)

• List of abbreviations and acronyms for terms used, like alt (alternate), APU (auxiliary power unit), auto (automatically), and so on.

Hydraulic Power - Introduction (Page 5)

• Complete list of abbreviations used.

Hydraulic Power - Component Location (Page 6)

• List of hydraulic power user systems (thrust reversers, power transfer unit (PTU) motor, landing gear, nose wheel steering, main gear brakes, primary flight controls and secondary flight controls)
• List components and locations for hydraulic systems A, B, and auxiliary systems.
• Data on hydraulic indicating systems. (quantity, pressure, pump low pressure warning, hydraulic fluid overheat warning.)
• Diagram indicating the layout of the systems within the aircraft (on page 6)

Hydraulic Power - General Description (Page 7)

• Air pressure from the reservoir pressurization system keeps pressure on reservoir systems A, B, and standby.
• Pressurized reservoirs supply constant flow to hydraulic pumps.
• Hydraulic system A supplies power to thrust reversers, rudder (and some components on page 7 - ailerons, elevators,autopilot A, tail skid, ground spoilers, flight spoilers, landing gear, nose wheel steering, and alternate brakes).
• Hydraulic system B supplies power to thrust reversers, rudder, ailerons, elevators, autopilot B, flight spoilers, alternate landing gear retraction, alternate nose wheel steering, and normal brakes.
• Standby hydraulic system supplies alternative hydraulic pressure to thrust reversers, standby rudder, leading edge flaps, and slats.
• Hydraulic power transfer unit (PTU) system supplies alternative pressure to leading edge flaps and autoslat system if system B EDP pressure decreases.
• PTU controls the motor.
• System A pressurizes motor when PTU control valve is open.
• System B supplies the fluid to the pump.

Hydraulic Power - General Description Page 8

• Diagram showing system connectivity for systems A, B and standby within the airplane.

Hydraulic Power - Controls and Indications (Page 9)

• Controls and indications for hydraulic power systems are on the hydraulic panel and flight control panel.
• Located on the P5 forward overhead panel.
• Engine driven pumps (EDPs) and electric motor driven pumps (EMDPs) have a switch on the hydraulic panel (ON/OFF).
• ENG 1 switch controls the EDP for system A. ENG 2 switch controls the EDP for system B.
• ELEC 2 switch on the hydraulic panel controls the EMDP for system A. ELEC 1 switch on the Hydraulic panel controls the EMDP for system B.

Hydraulic Power - Controls and Indications (Page 10)

• The control switches for the standby system have switches to operate components for standby hydraulic system

• List the Flight compartment indications for systems A and B (quantity, system pressure, pump low pressure warning, and overheat (EMDPs only))

• List standby hydraulic system indications (low quantity, low pressure, and standby rudder on).

• Hydraulic pressure shows on systems A and B.

Hydraulic Power - Controls and Indications (Page 11)

• Hydraulic fluid quantity in percent of full on systems A and B reservoirs.
• Amber LOW QUANTITY light on flight control panel when quantity is below normal in standby reservoir.
• Amber LOW PRESSURE light for each pump when output pressure is below normal.
• System indicators for A and B are above the HYD PUMP control switches.
• Standby system LOW PRESSURE light to the right of FLT CONTROL switches on flight control panel
• System A and B EMDP OVERHEAT Lights are above the HYD PUMP control switch. Standby system does not have overheat indicator.

Hydraulic Power - Component Location (Page 12-13)

• Components for main, auxiliary, and servicing hydraulic systems are in these locations: engine accessory gearbox, main landing gear wheel well, and fuel tanks.
• Ram air bays, and aft wing-to-body fairing.
• Hydraulic system A components are on the left side of the airplane, system B components are on the right side.
• Engine-driven pumps (EDPs) and case drain filter modules are on the left and right engines.
• Reservoirs (2), EDP supply shut-off valve (2), EMDP, pressure module (2), and EMDP case drain filter module (2) are located in the main landing gear.
• System A heat exchanger in main tank 1, system B heat exchanger in main tank 2.
• System A and B ground service disconnect modules in the left and right ram air bays.
• Standby hydraulic system reservoir, module, and case drain filter module
• Standby EMDP is in the right aft wing-to-body fairing.
• Power transfer unit (PTU), and PTU pressure filter module are located in the main landing gear wheel well

Hydraulic Power - Component Location (Page 15)

• List of PTU flow limiter, PTU control valve, and EDP pressure switch.
• Ground servicing system components in the right forward corner of the main landing gear wheel well.

Hydraulic Power - Component Location (Page 16)

• Diagram illustrating the location of components in the main landing gear wheel well for systems A, B, and standby.
• Diagram also showing the location for EDP and case drain filter modules, and heat exchangers.

Main Hydraulic Systems - Introduction (Page 17)

• Two main hydraulic systems (systems A and B) operate full time during flight.
• All hydraulically powered components are operated by these systems.
• Ground servicing system allows servicing of reservoirs A, B, and standby hydraulic system from a single location.

Main Hydraulic Systems - General Description (Page 19, 21, 22)

• Hydraulic systems A and B operate independently.
• Systems operate at 3000 psi.
• Reservoirs (2), Reservoir pressurization manifold, EDP supply shutoff valve (2), Engine and APU fire control panel, EDP (2), EMDP (2), Pressure module (2), Case drain filter module (4), heat exchanger (2), and return filter module (2) are components of main hydraulic systems.
• Pressurized air from the pneumatic system flows through the reservoir pressurization system manifold to the reservoirs.
• Engine and APU fire control panel controls the EDP supply shutoff valves.
• EDP supply shutoff valves control hydraulic fluid to the EDP for each system.
• Hydraulic panel controls the EDPs and EMDPs, along with providing low pressure readings for each pump (amber LOW PRESSURE Lights) and overheat readings for EMDPs (amber OVERHEAT Lights).
• EDP and EMDPs supply pressure continuously to a pressure module.
• Case drain fluid removes heat and goes to the case drain filter module of each pump.

Main Hydraulic Systems - General Description (Page 20, 21)

• List of components for systems A and B: EDP motor, thrust reversers, rudder, ailerons, elevators, autopilot A, tail skid, ground spoilers, flight spoilers, landing gear, nose wheel steering, and alternate brakes.
• List of components for system B: right thrust reverser, alternate landing gear retraction, alternate nose wheel steering, and other normal brakes, rudder, ailerons, elevators, autopilot B, flight spoilers, and others.
• Standby hydraulic system supplies alternative hydraulic pressure to thrust reversers, rudder, leading edge flaps and slats..
• PTU system supplies alternative pressure to the leading edge flaps and autoslat system

Main Hydraulic Systems - General Description (Page 22)

• Diagram showing system components and interconnection flow paths of system A.
• Same diagram for system B.
• Labels for all components.

Main Hydraulic Systems - Controls and Indications (Page 23-24)

• Hydraulic panel and Flight control panel contain the controls for hydraulic systems on the P5 forward overhead panel.
• The engine fire switches control the fluid supply to engine-driven pumps (EDPs)
• EDPs and EMDPs each have a switch on the hydraulic panel.
• ENG 1 and ENG 2 switches control EDP for systems A and B.

Main Hydraulic Systems - Controls and Indications (Page 23, 26)

• ELEC 2 and ELEC 1 switches control EMDPs for systems A and B, respectively.
• Engine fire switches isolate the engine if a fire occurs
• Switches also control supply shutoff valves for related EDPs.
• Indicators and lights (Quantity, system pressure, pump low pressure, Overheat).
• Indicators and lights for standby hydraulic system (Quantity, low pressure, standby rudder on)

Main Hydraulic Systems - Indication (Page 23, 26)

• Indicates quantity (in percentages of full) for reservoirs A and B; pressure for A and B, pump low pressure, and pump overheat.
• Indicates Quantity, system pressure, and low pressure for Standby hydraulic system, and pressure

Main Hydraulic Systems - Component Location (Page 27-28)

• Components for main, auxiliary, and ground servicing hydraulic systems in the flight compartment, engine, and wing.
• Engine-driven pumps (EDPs) and case drain filter modules are on the engine.
• Two heat exchangers are in the main fuel tanks.

Main Hydraulic Systems - Component Location (Page 29)

• Components of hydraulic systems, A, B, and ground servicing, located in the main landing gear wheel wells.

Main Hydraulic Systems - Component Location (Page 30)

• Diagram showing system A and B components in the main landing gear.
• Components include reservoirs and modules.

Main Hydraulic Systems - Reservoir Pressurization System (Page 31, 32)

• The reservoir pressurization system provides pressure to systems A, B, and the standby system reservoirs.
• The system receives pressure from a pneumatic sources (engine bleed systems, APU bleed air, and external ground air).

Main Hydraulic Systems - Reservoir Pressurization System (Page 33, 34)

• The reservoir pressurization manifold has components for connecting to hydraulic systems A and B.
• The air charging valve on the manifold removes pressurization from the reservoirs.
• Cross fittings send pneumatic pressure from the pneumatic system to the hydraulic system reservoirs.
• Pressure relief valves open at 60-65 psi.

Main Hydraulic Systems - Reservoir Pressurization System (Page 35-36)

• The pneumatic system pressurizes the reservoirs to approximately 18 to 42 psi.
• Air from the pneumatic system passes through filters, vents, and cross-fittings removing contamination and moisture.
• Filters have a hard seat check valve that prevents fluid back flow and reservoir fumes in the ECS ducts.
• Cross fittings control airflow through check valves, ports, and restrictors.
• The balance line connects system B to the standby reservoir.
• The air pressure indication shows pressure on the reservoirs.
• Pressure relief valves protect the reservoirs.

Main Hydraulic Systems - Reservoir Pressurization System (Page 37-38)

• Diagram indicating the layout of the reservoirs, their connections, and the pneumatic system components.

Main Hydraulic Systems - Reservoir Pressurization System (Page 39)

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Main Hydraulic Systems - Reservoir Pressurization System (Page 40, 41)

• The reservoir pressurization system.
• System A and B components are similar. Reservoirs supply fluid, system A components are on the left of the airplane, and system B on the right.
• EDP and EMDP components are on the engine.
• Reservoir components in main landing gear. (reservoir (2), EDP supply shut-off valve (2), EMDP (2), Pressure module (2), Case drain filter module (4), heat exchanger (2), and return filter module (2).

Main Hydraulic Systems - Reservoir Pressurization System (Page 42)

• Diagram of reservoir pressurization system.
• Air lines are routed through many components that are labeled with their function. (e.g., case drain, system A and B, standby).

Main Hydraulic Systems - Reservoir Pressurization System (Page 42-43)

• A more detailed diagram for both system A and B showing fluid flow from the reservoir to various components and the pneumatic components providing pressurization.

... (Continues with similar detailed study notes for all subsequent documents)