Airbus 29 A300 A310 Hydraulics

ATA 29 Hydraulic Power

MTT M540000 / R3.3 01AUG01 For Training Purposes Only

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ATA 29 A300/A310

THIS PAGE INTENTIONALLY LEFT BLANK


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ATA 29 A300/A310

A300/A310 HYDRAULIC SYSTEMS GENERAL


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ATA 29 A300/A310

A300/A310 HYDRAULIC SYSTEM - ABBREVIATIONS AND SYMBOLOGY

GLOSSARY OF ABBREVIATIONS ABBREVIATION A SA AP APU CRT ECAM HP LP PCU PTU RAT SC THS WLDP W TB


DEFINITION All Speed Aileron Auto Pilot Auxiliary Power Uun it Cathode Ray Tube Electronic Centralized Aircraft Monitoring High Pressure Low Pressure Power Control Unit Power Transfer Unit Ram Air Turbine Sing le Chime Trimmable Horizontal Stabilizer Warning Light Display Panel W i n g T i p Br a k e

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ATA 29 A300/A310

A300/A310 System Line Identification and FIN - General

FIN

FIN 291063 - The Functional Identification Number (FIN) identifies system components at each component location and adjacent to component installation area. A FIN label is affixed to the component and installation areas. The FIN is broken down in the Hydraulic system: 29 = HYD System 1063 = Component specific identification number


29-5 295

ATA 29 A300/A310

A300/A310 Hydraulic System - Fluid/Pipes and Component/Accessories Hydraulic Fluids General

The hydraulic fluid used on the A300-600 is HYJET IV-A. This fluid is more temperature tolerant than HYJET IV. When servicing the hydraulic system of the A300-600 aircraft, HYJET IV-A should be used whenever possible.

Components and Accessories

Hydraulic components components and accessories are identified in conformance conformance with NSA0140 by a 4-figure item number called out on the hydraulic Functional Diagram. The numbers are on placards; one affixed on the component or accessory itself, and one on the support on which the component or accessory is mounted.

Rigid Pipes

Rigid pipes are identified in conformance with NSA0140 and 0141 by: - The Part Number (e.g. A2913161502300) - An NSA0143 label identifying the pipe as an hydraulic pipe (black dots), its function (e.g. CASE DRAIN) and the direction of fluid flow (arrow) - An NSA0144 NSA0144 label identifying identifying the the system, system, comprising a colored band (Green, Blue, Yellow) plus the figure 1, 2 or 3 indicating the Green, Blue or Yellow system, respectively. -

Long pipes are identified at both ends.

In the case of manifold-mounted components, the identification placards are affixed on each component and on that part of the manifold receiving the component. (When the component is too small, the indication is marked directly on the component). All fittings on components or accessories are identified by an engraved letter indicated on the hydraulic Functional Diagram. Components are also identified by two NSA9000 placards: - a purple placard identifying the hydraulic fluid - a placard bearing the component designation.

Flexible Hoses

Flexible hoses are identified in conformance with NSA0140 NSA0140 and 0142 by: - A purple purple metal metal or heat heat shrinkable shrinkable sleeve indicating the fluid used used is a phosphate ester to NSA307.110 - The Part Number which which appears either on the purple sleeve or on a separate metal sleeve.


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ATA 29 A300/A310

A300/A310 Hydraulics Systems - Hydraulic Lines Routing (Typical)

Keel Beam


NOTE The stainless steel high pressure lines are electrically bonded by means of bonding braid and clips. Painted light alloy low pressure lines are excellent conductors and are not bonded.

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ATA 29 A300/A310



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ATA 29 A300/A310

A300/A310 Hydraulic System Connections - General


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ATA 29 A300/A310

A300/A310 Hydraulic System Connections/Mounting Connections/Mounting - Sealing Bobbins BOBBIN TYPE CONNECTOR Use on the pressure and return systems of manifolds on which a maximum number of components are installed by means of sealing bobbins and mounts (filters, pressure relief valves, priority valves, pressure switches, electrovalves...) ensures longer life of the pipes and fittings (which are not handled when components are removed), limits the risk of leakage and facilitates maintenance.


Refer to illustration for component-to-mounting connection principle by means of a bobbin. The bobbins are equipped with one square seal on component side and one 0-ring on mounting side. An identification groove is provided for fool proofing. Whenever a component is removed, the bobbin is held in the component by the square seal. If the component is not immediately reinstalled, the open port can be easily blanked off by means of a plug/cap.

29-10 2910

ATA 29 A300/A310

A300/A310 Hydraulic System Connections/Mounting Connections/Mounting - Sealing Bobbins


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ATA 29 A300/A310

A300/A310 Main Hydraulic Systems - System Fluid Capacities Hydraulic System Fluid Capacities - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - Ñ

QUANTITY Ñ Ñ________________________Ñ SPECIFICATION Ñ LITERS Ñ US GAL Ñ -------------------------- -Ñ-----------Ñ------------ Ñ-----------------------

S Y S T E M / C O M P O N E NT NT

GREEN SYSTEM Reservoir Total capacity Max. contents gauging Normal fill level Low level (warning

Ñ Ñ Ñ Ñ Ñ Ñ Ñ

Ñ Ñ Ñ

Ñ Ñ Ñ

40 Ñ 10.57 Ñ 30 Ñ 7.93 Ñ 25 Ñ 6.60 Ñ 5 ±0.5Ñ 1.32 ±0.13 Ñ

Material No.02-003 (Ref. 20-31-00)

level) Ñ Ñ Ñ Green system Ñ180 approx.Ñ 47.50 Ñ Total capacity Ñ Ñ Ñ -------------------------- -Ñ-----------Ñ------------ Ñ BLUE SYSTEM Reservoir Total capacity Max. contents gauging Normal fill level Low level (warning level) Blue system Total capacity

Ñ Ñ Ñ Ñ Ñ Ñ Ñ

Ñ Ñ Ñ

Ñ Ñ Ñ

Ñ Ñ Ñ Ñ

22 17 12

5.81 4.49 3.17

Ñ 5 ±0.5 Ñ1.32 ±0.13 Ñ Ñ Ñ 90 approx.Ñ 23.80 Ñ Ñ

Ñ Ñ Ñ Ñ Ñ Ñ Ñ Ñ

-------------------------- -Ñ-----------Ñ------------ Ñ Ñ Ñ Ñ YELLOW SYSTEM Ñ Ñ Ñ Reservoir Total capacity

Ñ Ñ Ñ Ñ

28 +3 reserve

Ñ Ñ Ñ Ñ

Ñ Ñ 7.40 +0.79Ñ Ñ

Max. contents gauging Ñ 24 Ñ 6.34 Ñ Normal fill level Ñ 18.5 Ñ 4.89 Ñ -------------------------- -Ñ-----------Ñ------------ Ñ Low level (warning level) Yellow system Total capacity

Ñ 5 ±0.5Ñ1.32 ±0.13 Ñ Ñ Ñ130 approx.Ñ 34.34 Ñ Ñ

Ñ Ñ Ñ Ñ

-------------------------- -Ñ-----------Ñ------------ Ñ-----------------------


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ATA 29 A300/A310

A300/A310 Main Hydraulic Systems Reservoir - Schematic (Typical) Hydraulic fluid bleed hole to prevent rupture of reservoir bleeds fluid overboard through depressurization relief valve - over-serviced over-serviced system

Air Space for reservoir air pressurization from ground source, Engine 1 and/or APU bleed air sources

NOTE: Various Contents shown not to scale - for reference purposes only


29-13 2913

ATA 29 A300/A310

A300/A310 Green - Blue - Yellow Hydraulic Systems - General The aircraft has three completely independent hydraulic systems, which operate simultaneously. They are designated BLUE, GREEN, YELLOW.

-

Each system is supplied from its own hydraulic reservoir. There are no provisions for routing of hydraulic fluid from one system to the other.

-

Four identical engine driven hydraulic pumps, 2 on each engine, pressurize the systems with a delivery pressure of 3000 PSI: -

GREE GREEN N BLUE YELL YELLOW OW

Hydraulic power is fed directly to the servo controls manifolds and then to the high pressure manifolds, which are permanently linked. The servo control manifolds supply the primary flight controls and spoilers through a servo controls selector valve.

2 pump pumps, s, one one on each each engi engine ne.. 1 pump on engi ne 1. 1 pump pump on engi engine ne 2.

Two non-reversible power transfer units are installed to provide for power transfer without fluid exchange, from the GREEN system to the BLUE or to the YELLOW system. They are required in case of power generation failure (for example, in case of engine failure or engine pump failure) and also for ground testing. If the engine driven pumps are not available, hydraulic power may also be generated by: -

Two electric pumps in the GREEN system (primarily intended for ground testing').


One electric pump in the YELLOW system to pressurize the brake accumulators (Parking /ALTN-OFF brakes), if required, or to operate the main cargo compartment doors. A ram air turbine (RAT) (RAT) driven pump in the YELLOW system to supply emergency hydraulic power. A hand pump in the YELLOW system to operate the main cargo compartment doors when the YELLOW electric pump is not available.

The high pressure manifolds are equipped with a priority valve which isolates slat, flap and gear operating systems, when the pressure has dropped below 1885 PSI which gives priority to Flight Controls. (See chapter FLIGHT CONTROLS for detailed information). In the event of engine fire the engine driven pumps are isolated from their hydraulic reservoirs by the FIRE VALVES. When an ENG FIRE handle is pulled, the respective valves close. In the yellow system, the FIRE valve closes also in case of LO LVL. The position of the FIRE VALVES is indicated on the lateral panel.

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ATA 29 A300/A310

A300 Hydraulic Power Users - Green - Blue - Yellow (G-B-Y) Systems

= A300/A310 Differences

System Numbers Main System 1 - Green 2 - Blue 3 - Yellow


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ATA 29 A300/A310

A300/A310 G-B-Y Hydraulic Systems - General The aircraft has three completely independent hydraulic systems, which operate simultaneously. They are designated BLUE, GREEN, YELLOW.

-

Each system is supplied from its own hydraulic reservoir. There are no provisions for routing of hydraulic fluid from one system to the other. Four identical engine driven hydraulic pumps, 2 on each engine, pressurize the systems with a delivery pressure of 3000 PSI: -

GREE GREEN N BLUE YELL YELLOW OW

Hydraulic power is fed directly to the servo controls manifolds and then to the high pressure manifolds, which are permanently linked. The servo control manifolds supply the primary flight controls and spoilers through a servo controls selector valve.

2 pump pumps, s, one one on each each engi engine ne.. 1 pump on engi ne 1. 1 pump pump on engi engine ne 2.

Two non-reversible power transfer units are installed to provide for power transfer without fluid exchange, from the GREEN system to the BLUE or to the YELLOW system. They are required in case of power generation failure (for example, in case of engine failure or engine pump failure) and also for ground testing. If the engine driven pumps are not available, hydraulic power may also be generated by: -

Two electric pumps in the GREEN system (primarily intended for ground testing').


-

One electric pump in the YELLOW system to pressurize the brake accumulators (Parking /ALTN-OFF brakes), if required, or to operate the main cargo compartment doors. A ram air turbine (RAT) driven pump in the YELLOW system to supply emergency hydraulic power. A hand pump in the YELLOW system to operate the main cargo compartment doors when the YELLOW electric pump is not available.

The high pressure manifolds are equipped with a priority valve which isolates slat, flap and gear operating systems, when the pressure has dropped below 1885 PSI which gives priority to Flight Controls. (See chapter FLIGHT CONTROLS for detailed information). In the event of engine fire the engine driven pumps are isolated from their hydraulic reservoirs by the FIRE VALVES. When an ENG FIRE handle is pulled, the respective valves close. In the yellow system, the FIRE valve closes also in case of LO LVL. The position of the FIRE VALVES is indicated on the lateral panel.

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ATA 29 A300/A310

Some A310 Hydraulic Power Users - Green - Blue - Yellow (G-B-Y) Systems

= A300/A310 Differences


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ATA 29 A300/A310

A300/A310 Hydraulic Power System - Description and Operation Each main system includes: - A reservoir from which fluid is drawn by... - The four four pumps pumps mounted mounted on the engine accessory gearboxes. The upper pump is always the Green pump. On the left engine, the lower pump is the Blue pump; on the right engine it is the Yellow pump.


29-18 2918

The engine pumps then pressurize: - A servo controls manifold, then... - An HP manifold, which directs pressure to the other user systems. - Valves (check valves, shutoff valves, selector valves, etc ...) govern the direction or priority of fluid flow. - Filters, with with a maximum filtering capability of 3 to 15-micron, maintain cleanliness of the fluid between... - The return manifold and the reservoir.

ATA 29 A300/A310

A300/A310 Main Hydraulic Power System


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ATA 29 A300/A310

A300/A310 Auxiliary Hydraulic System - General Auxiliary power is provi ded by: -

Two electric pumps, mounted in parallel, supplying the Green system directly, A Green/Blue power transfer unit, A Green/Yell ow power transfer unit, An electric pump in the Yellow system, A hand pump in the Yellow system, A ram air turbine in the Yellow system.


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ATA 29 A300/A310

A300/A310 Auxiliary Hydraulic Power Systems


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ATA 29 A300/A310

A300 Hydraulic Systems - Flight Controls and Other Operating Systems Flight Control Operating Systems Krueger – Green Slats – Green/Blue Flaps – Green/Yellow THS – Green/Yellow Notch Flap – Green Spoilers Green Blue 6 1-4-7

Y el l ow 2-3-5

ASA Droop – Green Roll AP – Green/Yellow

Other Operating Systems Landing Gear – Green Nose Wheel Steering – Green Standby Generator – Green Normal Brakes – Green Alternate Brakes – Yellow Parking Brake – Yellow Cargo Door – Yellow – Forward – Aft – Main Deck Ram Air Turbine – Yellow

Elevator (Pitch) Pitch AP – Green/Yellow

Electric Pump 1/2 – Green

Yaw Yaw AP – Green/Yellow Yaw Damper – Blue/Yellow

Electric Pump – Yellow Hand Pump Yellow LH PTU – Green/Blue RH PTU – Green/Yellow


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ATA 29 A300/A310

A300 Hydraulic Systems - Flight Control Areas and Servo Controls


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ATA 29 A300/A310

A310 Hydraulic Systems - Flight Controls and Other Operating Systems Flight Control Operating Systems

Other Operating Systems Landing Gear – Green

Krueger – Green Slats – Green/Blue Flaps – Green/Yellow THS – Green/Yellow Spoilers Green Blue Yellow 5 2-3-7 1-4-6 ASA Droop – Green Roll AP – Green/Yellow Elevator (Pitch) Pitch AP – Green/Yellow

Nose Wheel Steering – Green Standby Generator – Green (Some A310s) Normal Brakes – Green Alternate Brakes – Yellow Parking Brake – Yellow Cargo Door – Yellow – Forward – Aft – Main Deck Deck Ram Air Turbine – Yellow

Yaw Yaw AP – Green/Yellow Yaw Damper – Blue/Yellow

Electric Pump 1/2 – Green Electric Pump – Yellow Hand Pump Yellow LH PTU – Green/Blue RH PTU – Green/Yellow


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ATA 29 A300/A310

A310 Hydraulic Systems - Flight Control Areas and Servo Controls


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ATA 29 A300/A310

A300/Some A310 Hydraulic Systems - Component Location and Line Routing


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ATA 29 A300/A310

A300/Some A310 Main Hydraulic Systems - Components Location and Line Routing

Aft Fuselage and Tail Section MTT M540000 / R3.3 01AUG01 For Training Purposes Only

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ATA 29 A300/A310

Some A310 Main Hydraulic Systems - Components Location and Line Routing

* *No Standby Generator AC/DC Power MTT M540000 / R3.3 01AUG01 For Training Purposes Only

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ATA 29 A300/A310

A310 Main Hydraulic Systems - Components Location and Line Routing

Aft Fuselage and Tail Section MTT M540000 / R3.3 01AUG01 For Training Purposes Only

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ATA 29 A300/A310

A300/Some A310 HYD PWR Panel 427VU - Overhead Panel Indications 3

1 2

Reservoir Hydraulic Quantity Indicators Indicate the fluid level in the respective hydraulic reservoir. If on indicator is not electrically supplied, the pointer may move to any position without any warning. - Green arc: normal usable range of hydraulic fluid. - Upper small green arc On ground with reservoir pneumatically pressurized and hydraulic system depressurized: depressurized: Pointer within upper small green arc indicates indicates normal fluid level in reservoir. Pointer at max. max. limit limit of upper small green green arc arc indicates indicates max. max. normal fluid level in reservoir. Pointer at min. limit of upper small green arc indicates min. normal fluid level in reservoir. - Yellow arc with red dot Pointer within yellow arc indicates abnormal fluid level in reservoir. When pointer drops to AR below the red dot, ECAM system master caution lights on CAPT and F/O main instrument panels 3VU and 5VU and associated SC are activated.* 





3



A300/Some A310s

1 AIR Lights

In normal configuration, the air light is off, and the legend is not visible. The legend comes on amber when reservoir air pressure is below 22 PSI. It is accompanied by Master Caution lights on CAPT and F/O main instrument panels 3VU and 5VU with associated SC and ECAM activation.*

*Other A310s

On A310s which have the Warning Light Display Panel (WLDP) in place of the Master Caution lights, out of limits conditions are accompanied by the HYD light on the WLDP with associated SC and ECAM activation.

2 OVHT Lights

Some A310s

In normal configuration, the OVHT light is off, and the legend is not visible. The legend comes on amber when reservoir fluid (temperature reaches 95°C ± 5°) it is accompanied by Master Caution lights on CAPT and F/O main instrument panels 3VU and 5VU with associated SC and ECAM activation.*

Small Arc


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ATA 29 A300/A310

A300/Some A310 HYD PWR Panel 427VU - Overhead Panel Indications 4

5

PUMPS/ PUMPS/ENG ENG 1, 1, B and G, G, ENG 2, G and Y Pushbutt Pushbutton on Switch Switches es In normal configuration, in flight, the switch is pressed (in), and the legends are off. If pump delivery pressure drops below 1870 PSI, the LO PR legend in the upper half of the switch comes on amber. It is accompanied by Master Caution lights on CAPT and F/O main instrument panels 3VU and 5VU with associated SC and ECAM activation. If the switch is released (out), the pump is de-energized and the OFF legend in the lower half of the switch comes on white. It is accompanied by master caution lights on CAPT and F/O main instrument panels 3VU and 5VU with associated SC and ECAM activation.*

6

PTU PTU Pus Pushb hbut utto ton n Swi Switc tche hess Each power transfer unit (PTU), green/yellow and green/blue, is controlled by a pushbutton switch. When the switch is pressed (in), the PTU is activated, and the ON legend in the lower half of the switch comes on green. When the switch is released (out), the PTU is deactivated and the ON legend goes off.

6

5

*Other A310s A300/Some A310s

4

On A310s which have the Warning Light Display Panel (WLDP) in place of the Master Caution lights, out of limits conditions are accompanied by the HYD light on the WLDP with associated SC and ECAM activation.

ELEC PUMPS Pushbutto n Switch In normal configuration, the pushbutton switch legends are off and the electric pumps are de-energized. When the switch is pressed: - In normal configuration, the electric pumps are activated, the on legend in the lower half of the switch comes on white. - If both electric pumps are failed, the LO PR legend in the upper half of the switch comes on amber. It is accompanied by Master Caution lights on CAPT and F/O main instrument panels 3VU and 5VU with associated SC and ECAM activation.* - In the event of 28VDC power supply loss, ELEC PUMPS pushbutton switch returns to the released position.


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ATA 29 A300/A310

A300/A310 Hydraulic System - Controls and Indications


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ATA 29 A300/A310



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ATA 29 A300/A310

A300/A310 Maintenance Panel - HYD PWR Panel 472VU HYD PWR PANEL

3. RSVR OVHT TEST BLUE, GREEN, YELLOW PUSHBUTTON SWITCHES

1. ELEC PUMPS TEST SWITCH Pressed An overheat signal is simulated in the corresponding overheat detection circuit. If test is successful, the respective OVHT light on the HYD PWR section of the overhead panel will come on accompanied by Master Caution Lights on Capt and F/0 Main Instrument Panels 3VU and 5VU with associated SC and ECAM activation.

•

The switch controls the individual test of the electric pumps in the GREEN system. The switch is springloaded to neutral. For test, the elec pumps pushbutton switch on the HYD PWR section of the overhead panel must be selected ON, the ON legend ON; LO PR legend OFF. -

PUMP 1 (upper) position PUMP 2 is deactivated PUMP 1 only is operating PUMP 2 (lower) position PUMP 1 is deactivated PUMP 2 only is operating NEUTRAL (center) position Both pumps operate.

Released The overheat signal and the warnings are cancelled.

•

NOTE: These pushbutton switches are also used for THS actuator jamming test.

The test of each pump is successful if the LO PR legend in the elec pumps pushbutton switch does not come on.

4. The Hydraulic Hydraulic Circuit Breakers (CBs) are located on:

2. FIRE VALVES ENG 1, BLUE AND GREEN/ENG 2, GREEN GREEN AND YELLOW ANNUNCIATORS When the ANN LT switch on the rear panel is placed in read, the fire valves legends indicate the position of the respective fire valve which is controlled by the corresponding ENG FIRE handle. -

A300 - 133 VU Distribution Panel located on the rear wall of the flight deck – Main CB Panel. CBs located on LH side of 133VU – Hydraulic Section of Panel A310 - 128 VU Distri bution Panel located on rear wall of flight deck – Main CB Panel. CBs locate d on LH side of 128 VU Hydraulic Section of panel.

Open legend comes on White, indicating the valve is fully open Shut legend comes on White, indicating the valve is fully closed.


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ATA 29 A300/A310

A300/A310 Hydraulic Power - Flight Compartment Controls and Indications

4

CB Panels - A300/133VU Shown - A310/128VU (Typical)


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ATA 29 A300/A310

A300 Hydraulic Systems Schematic - General


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ATA 29 A300/A310

A310 Hydraulic Systems Schematic - General


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ATA 29 A300/A310

A300 Hydraulic System Electrical Power Supply - General


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ATA 29 A300/A310

A310 Hydraulic System Electrical Power Supply - General


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ATA 29 A300/A310

GREEN MAIN HYDRAULIC SYSTEM NUMBER 1


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ATA 29 A300/A310

A300/Some A310 - Green Main Hydraulic Power System - Description -

GENERAL This system is the most important of the three. -

-

It includes one pump on each of the two engines. It actuates directly the majority of the user services except: - Twelve of the fourteen spoilers. - The yaw damper. - The cargo compartment doors. It can can operate independently on the ground by by means of the APU and the electric pumps. It is used to pressurize the other other systems systems by means of of the power transfer units. In addition, the Green system ground service panel features controls and indicators for the reservoir filling system. USERS

A. Supplied through th e servo controls mani fold, with indep endent supply capability on the ground - of the L wing - of the R wing - of the aft fuselage - Two all speed aileron servo controls L and R - Two elevator servo controls L and R - One rudder servo control - Two actuators on spoilers 6, L and R (A300) - Two actuators on Spoilers 5, L and R


One trimmable horizontal stabilizer actuator motor One autopilot roll actuator servo motor One autopilot pitch actuator servo motor One autopilot yaw actuator servo motor One pitch artificial feel actuator.

B. Supplied through the HP manifold - Two hydraulic motors of the the Green/Blue Green/Blue and Green/Yellow Green/Yellow power transfer units. - The normal braking system for the eight main landing gear wheels. And through a priority valve: - Two hydraulic hydraulic motors in the flap and and slat power control units. - Two Krueger flap actuators. - Two notch flap actuators (A300 only). - Two all speed aileron droop signal actuators. actuators. - Landing gear extension/ retraction and nose wheel steering systems: - three landing gear actuating cylinders - three downlock systems - four landing gear door actuating cylinders - seven landing gear and landing gear door uplocks uplocks with with uplock release actuators - two nose wheel steering actuating cylinders powered in parallel with the landing gear extension system. - Standby generator (A300, some A310s). NOTE: A300 Notch (Slot) Flaps operate at same time with LH/RH

Krueger operation during extension and retraction of the Krueger or Krueger Flaps.

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ATA 29 A300/A310

A300 Green Hydraulic Power System - Schematic


29-42 2942

ATA 29 A300/A310

A300/Some A310 - Green Main Hydraulic Power System - Description -

GENERAL This system is the most important of the three. -

-

It includes one pump on each of the two engines. It actuates directly the majority of the user services except: - Twelve of the fourteen spoilers. - The yaw damper. - The cargo compartment doors. It can can operate independently on the ground by by means of the APU and the electric pumps. It is used to pressurize the other other systems systems by means of of the power transfer units. In addition, the Green system ground service panel features controls and indicators for the reservoir filling system. USERS

A. Supplied through th e servo controls mani fold, with indep endent supply capability on the ground - of the L wing - of the R wing - of the aft fuselage - Two all speed aileron servo controls L and R - Two elevator servo controls L and R - One rudder servo control - Two actuators on spoilers 6, L and R (A300) - Two actuators on Spoilers 5, L and R


One trimmable horizontal stabilizer actuator motor One autopilot roll actuator servo motor One autopilot pitch actuator servo motor One autopilot yaw actuator servo motor One pitch artificial feel actuator.

B. Supplied through the HP manifold - Two hydraulic motors of the the Green/Blue Green/Blue and Green/Yellow Green/Yellow power transfer units. - The normal braking system for the eight main landing gear wheels. And through a priority valve: - Two hydraulic hydraulic motors in the flap and and slat power control units. - Two Krueger flap actuators. - Two notch flap actuators (A300 only). - Two all speed aileron droop signal actuators. actuators. - Landing gear extension/ retraction and nose wheel steering systems: - three landing gear actuating cylinders - three downlock systems - four landing gear door actuating cylinders - seven landing gear and landing gear door uplocks uplocks with with uplock release actuators - two nose wheel steering actuating cylinders powered in parallel with the landing gear extension system. - Standby generator (A300, some A310s). NOTE: A300 Notch (Slot) Flaps operate at same time with LH/RH

Krueger operation during extension and retraction of the Krueger or Krueger Flaps.

29-43 2943

ATA 29 A300/A310

A310 Green Hydraulic Power System - Schematic

*

*Some A310s MTT M540000 / R3.3 01AUG01 For Training Purposes Only

29-44 2944

ATA 29 A300/A310

A300 Green Main Hydraulic Power - Component Locations and FIN F IN

FUNCTIONAL DESIGNATION

291000 291002 291004 291005 291006 291007 291008 291010 291030 291031 111GK 110GK 291040 291042 291048 291049 291060 291063 291070 291072 3 0 WW

R E S E R V O I R - H Y D R A U L I C , GR GR E E N FILTER RSVR RETURN, GREEN MA NI F O L D - L P , G R E E N VALVE-DEPRESS/RELIEF, G RSVR GROUND CONNECTOR-SUCTION, G GROUND CONNECTOR-FILLING, G GROUND CONNECT OR-DELIVERY, G MA NI F O L D - S E R V O C O N T R O L S , G P UMP-EN G1 P UMP-EN G2 VAL VE-GREE N PUMP F IRE, ENG1 VAL VE-GREE N PUMP F IRE, ENG2 VALVE-NON RETURN VALVE-NON RETURN FILTER-G PUMP DELIVERY, ENG1 FILTER-G PUMP DELIVERY, ENG2 MA NI F O L D - H P , G R E E N RELIEF VALVE-GREEN PUMPS DELIVERY A CC U-G RE E N PWR P R E SS G AG E -G R EE N AC C U P R E SS S WI T C H - H P M A N I F O L D , G FILTER MODULE ASSY ENG PUMP CASE DRAIN FILTERS-ENG PUMP CASE D R AI N P R E SS S WI T C H - G P U M P , E N G 2 P R E SS S WI T C H - G P U M P , E N G 1 MA NI F O L D - E N G I N E P Y L O N MA NI F O L D - E N G I N E P Y L O N R ES ES TR TR IC IC TO TO RR- GR GR EE EE N P UM UM P R E CI CI R C U L A T I O N , E N G 1 RESTRICTOR-GREEN P UMP R ECIRCULATION CHECK VALVE-L/G RETURN, G CHECK VALVE-PTU RETURN, G CHECK VALVE-CASE DRAIN RETURN, G CHECK VALVE-FLAPS AND SLATS RETURN, CH ECK VA LVE -R ETUR N, G HP MAN IFOL D CHECK VALVE-L/G RETURN, G CHECK VALVE-BRK RETURN, G CHECK VALVE-RETURN, G/B PTU CHECK VALVE-G PUMP DELIVERY, ENG 1 CHECK VALVE-G PUMP DELIVERY, ENG 2 CHECK VALVE-G ELEC PUMP DELIVERY CHECK VALVE-G RSVR FILLING

112GK 113GK 291700 291701 291702 291703 291015 291019 291020 291021 291022 291023 291024 291026 291050 291051 291080 291131


PANEL

29-45 2945

Z O NE 147 148 147 147 147 147 147 147 435 445 575 675 410 410 147 147 147 147 147 147 147 452 462 452 462 483 473 473 483 473

,ENG2

G

4 83 147 147 147 147 147 147 147 147 147 147 147 147

A C C E S S AT A RE F. DOOR 734 29-11-11 734 29-11-15 734 147BL 147BL 147BL 734 435AL 445AL 575FB 675FB

734 734 734 734 734 734 734 452AR 462AR 452AR 452AR 483AL 473AL 473AL 483AL 473AL

29-11-34 29-11-32 29-11-32 29-11-33 29-11-33

29-11-42 29-11-42 29-11-12 29-11-55 29-11-56

29-11-36 29-11-36 29-11-36 2 9-11-36 29-11-62 29-11-62

483AL 734 734 734 734 734 734 734 734 734 734 734 734

ATA 29 A300/A310

A300 Green Main Hydraulic Power - Component Locations and FIN

D

E

F

D

E

D

F


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ATA 29 A300/A310

A300 Green Main Hydraulic Power - Component Locations and FIN F IN


291000 291002 291004 291005 291006 291007 291008 291010 291030 291031 111GK 110GK 291040 291042 291048 291049 291060 291063 291070 291072 3 0 WW

R E S E R V O I R - H Y D R A U L I C , GR GR E E N FILTER RSVR RETURN, GREEN MA NI F O L D - L P , G R E E N VALVE-DEPRESS/RELIEF, G RSVR GROUND CONNECTOR-SUCTION, G GROUND CONNECTOR-FILLING, G GROUND CONNECT OR-DELIVERY, G MA NI F O L D - S E R V O C O N T R O L S , G P UMP-EN G1 P UMP-EN G2 VAL VE-GREE N PUMP F IRE, ENG1 VAL VE-GREE N PUMP F IRE, ENG2 VALVE-NON RETURN VALVE-NON RETURN FILTER-G PUMP DELIVERY, ENG1 FILTER-G PUMP DELIVERY, ENG2 MA NI F O L D - H P , G R E E N RELIEF VALVE-GREEN PUMPS DELIVERY A CC U-G RE E N PWR P R E SS G AG E -G R EE N AC C U P R E SS S WI T C H - H P M A N I F O L D , G FILTER MODULE ASSY ENG PUMP CASE DRAIN FILTERS-ENG PUMP CASE D R AI N P R E SS S WI T C H - G P U M P , E N G 2 P R E SS S WI T C H - G P U M P , E N G 1 MA NI F O L D - E N G I N E P Y L O N MA NI F O L D - E N G I N E P Y L O N R ES ES TR TR IC IC TO TO RR- GR GR EE EE N P UM UM P R E CI CI R C U L A T I O N , E N G 1 RESTRICTOR-GREEN P UMP R ECIRCULATION CHECK VALVE-L/G RETURN, G CHECK VALVE-PTU RETURN, G CHECK VALVE-CASE DRAIN RETURN, G CHECK VALVE-FLAPS AND SLATS RETURN, CH ECK VA LVE -R ETUR N, G HP MAN IFOL D CHECK VALVE-L/G RETURN, G CHECK VALVE-BRK RETURN, G CHECK VALVE-RETURN, G/B PTU CHECK VALVE-G PUMP DELIVERY, ENG 1 CHECK VALVE-G PUMP DELIVERY, ENG 2 CHECK VALVE-G ELEC PUMP DELIVERY CHECK VALVE-G RSVR FILLING

112GK 113GK 291700 291701 291702 291703 291015 291019 291020 291021 291022 291023 291024 291026 291050 291051 291080 291131


PANEL

29-47 2947

Z O NE 147 148 147 147 147 147 147 147 435 445 575 675 410 410 147 147 147 147 147 147 147 452 462 452 462 483 473 473 483 473

,ENG2

G

4 83 147 147 147 147 147 147 147 147 147 147 147 147

A C C E S S AT A RE F. DOOR 734 29-11-11 734 29-11-15 734 147BL 147BL 147BL 734 435AL 445AL 575FB 675FB

734 734 734 734 734 734 734 452AR 462AR 452AR 452AR 483AL 473AL 473AL 483AL 473AL

29-11-34 29-11-32 29-11-32 29-11-33 29-11-33

29-11-42 29-11-42 29-11-12 29-11-55 29-11-56

29-11-36 29-11-36 29-11-36 2 9-11-36 29-11-62 29-11-62

483AL 734 734 734 734 734 734 734 734 734 734 734 734

ATA 29 A300/A310

A300 Green Main Hydraulic Power - Component Locations and FIN O

P O

P


29-48 2948

ATA 29 A300/A310

A310 Green Main Hydraulic Power - Component Locations and FIN FIN


PANEL

Z ON E

ACCESS DOOR

A T A R E F .

291000

RESERVOIR- HYDRAULIC, GREEN

147

734

29-11-11

291002 291004 291005 291006 291007

FILTER-RSVR RETURN, GREEN MANI F O L D - L P , G R E E N VALVE- DEPRESS RELI EF , G RSVR G R O U N D C O N N E C T O R - S U C T I ON , G GR OU N D C ON N E C T O R - F I L L I N G , G

147 147 147 147 147

734 734 147AL 147AL 147AL

29-11-15

291008 291010 291030

GR O U N D C ON N E C T O R - D E L I V E R Y , G MANI F O L D - S E R V O C O N T R O L S , G PUMP-GREEN, E N G 1

147 147 452

147AL 734 452AR

29-11-34 29-11-32

291031 111GK 110GK 291040

PUMP-GREEN, E N G 2 VALVE-ENGINE PUMP FIRE, ENG1 VALVE-ENGINE PUMP FIRE, ENG2 VALVE-NON RETURN

462 575 675 410

462AR 575AL 675AL

29-11-32 29-11-33 29-11-33

291042 291048 291049 112GK

VALVE-NON RETURN FILTER-G PUMP DELIVERY, ENG1 FILTER-G PUMP DELIVERY, ENG2 PR E SS SW I T C H - G P U M P , E N G 2

410 147 147 483

734 734 483AL

29-11-42 29-11-42 29-11-62

113GK 291700 291701 291702

PR E SS SW I T C H - G P U M P , E N G 1 MANI F O L D - E N G I N E P Y L O N MANI F O L D - E N G I N E P Y L O N RESTR ICTOR-GREEN PUMP RECIRCULATION, ENG1

473 473 483 473

473AL 473AL 483AL 473AL

29-11-62

291703 291060 291063 291070

RESTR ICTOR-GREEN PUMP RECIRCULATION, ENG2 MANI F O L D - H P , G R E E N RELIEF VALVE-GREEN PUMPS DELIVERY ACCU- GREEN PWR

483 147 147 147

483AL 734 734 734

29-11-12 29-11-55 29-11-56

291072 3 0W W

PRESS GAGE-GREEN ACCU PR E SS SW I T C H - H P M A N I F O L D , G FILTERS-ENGINE PUMP CASE D RA I N

148 147 452 462

734 734 452AR 4 62AR

29-11-36 29-11-36


29-49 2949

ATA 29 A300/A310



29-50 2950

ATA 29 A300/A310

A310 Green Main Hydraulic Power - Component Locations FIN FIN


PANEL

Z ON E

ACCESS DOOR

A T A R E F .

291000

RESERVOIR- HYDRAULIC, GREEN

147

734

29-11-11

291002 291004 291005 291006 291007

FILTER-RSVR RETURN, GREEN MANI F O L D - L P , G R E E N VALVE- DEPRESS RELI EF , G RSVR G R O U N D C O N N E C T O R - S U C T I ON , G GR OU N D C ON N E C T O R - F I L L I N G , G

147 147 147 147 147

734 734 147AL 147AL 147AL

29-11-15

291008 291010 291030

GR O U N D C ON N E C T O R - D E L I V E R Y , G MANI F O L D - S E R V O C O N T R O L S , G PUMP-GREEN, E N G 1

147 147 452

147AL 734 452AR

29-11-34 29-11-32

291031 111GK 110GK 291040

PUMP-GREEN, E N G 2 VALVE-ENGINE PUMP FIRE, ENG1 VALVE-ENGINE PUMP FIRE, ENG2 VALVE-NON RETURN

462 575 675 410

462AR 575AL 675AL

29-11-32 29-11-33 29-11-33

291042 291048 291049 112GK

VALVE-NON RETURN FILTER-G PUMP DELIVERY, ENG1 FILTER-G PUMP DELIVERY, ENG2 PR E SS SW I T C H - G P U M P , E N G 2

410 147 147 483

734 734 483AL

29-11-42 29-11-42 29-11-62

113GK 291700 291701 291702

PR E SS SW I T C H - G P U M P , E N G 1 MANI F O L D - E N G I N E P Y L O N MANI F O L D - E N G I N E P Y L O N RESTR ICTOR-GREEN PUMP RECIRCULATION, ENG1

473 473 483 473

473AL 473AL 483AL 473AL

29-11-62

291703 291060 291063 291070

RESTR ICTOR-GREEN PUMP RECIRCULATION, ENG2 MANI F O L D - H P , G R E E N RELIEF VALVE-GREEN PUMPS DELIVERY ACCU- GREEN PWR

483 147 147 147

483AL 734 734 734

29-11-12 29-11-55 29-11-56

291072 3 0W W

PRESS GAGE-GREEN ACCU PR E SS SW I T C H - H P M A N I F O L D , G FILTERS-ENGINE PUMP CASE D RA I N

148 147 452 462

734 734 452AR 4 62AR

29-11-36 29-11-36


29-51 2951

ATA 29 A300/A310



29-52 2952

ATA 29 A300/A310

A300 G-B-Y Hydraulic Systems - Reservoirs and Capacities - General Features Purpose . E a c h h y d r a u l i c s y s t e m i n c l u d e s a r e s e r vo vo i r w h i c h c o m p e n s a t e s f o r v a r i a t i o n s i n f l u i d vo v o l u m e d u e t o u s e r s e r v i c e o p e r a t i on on , a n d p r o v i d e s a r e s e r v e s u p p l y o f f lu lu i d . The volume of fluid in each system, including the fluid in the reservoir, is approximately 180 l (47.5 US Gal) for the Green system, 90 l (23.7 US Gal) for the Blue system and 130 l (34.3 US Gal) for the Yellow system. . The three reservoirs are air-pressurized to 3.5 bars (50.8 psi) relative. . E a c h r e s e r v o i r i s d e s i g n e d t o r e m a i n p r e s s u ri ri z e d f o r a t l e a s t 1 2 h o u r s . Description . The reservoirs are attached to the aircraft structure by two clampsecured straps. They each consist of a sheet steel cylinder with a mol d e d l i g h t a l l o y b a s e . C y l i n d e r d i a m e t e r i s t h e s a m e f o r e a c h r e s e r voir. Their relative capacities are therefore determined by their height. Green Blue Yellow Total 40 l (10.6 USgal) 22 l (5.81 USgal) 28 l (7.40 USgal) +3 l (0.79 USgal) (reserve) Max gageable 30 l (7.93 USgal) 17 l (4.49 USgal) 24 l (6.34 USgal) Fi l l l e v e l 25 l (6.60 USgal) 12 l (3.17 USgal) 18.5 l (4.89 USgal) Low level 5 l ± 0.5 5 l ± 0.5 5 l ± 0.5 (1.32 USgal ±0.13) (1.32 USgal ±0.13) (1.32 USgal ±0.13) warning T h e l e v e l o f t h e t h r e e re r e s e r v o i r s m a y b e a d j u st st e d s e p a r a t e l y a t t h e G r e e n system ground service panel. T h e Y e l l o w r e s e r v o i r i n c l u d e s a r e s e r v e fo fo r R A T s u p p l y ( R e f . 2 9 - 1 3 )

Mi d w a y d o w n t h e r e s e r v o i r i s m o u n t e d a q u a n t i t y t r a n s m i t t e r c o m p r i s i n g : . A float, with actuating linkage and snubber. . A direct reading quantity gage (Accuracy ± 2° angular) . An electrical connector for transmitting quantity signals and low level w a r n i n g s t o t h e f l i g h t co c o m p a r t m e n t a n d t o t h e G r e e n s y st st e m g r o u n d s e r v i c e panel. The bottom of the reservoir includes : . A suction port for supply of fluid to the pumps (+ one for the ram air turbine on the Yellow system reservoir). . A return port with an overheat sensor. . A port connected to a self-sealing depressurization/relief valve i n th t h e g r o u nd n d s e rv rv i c e p a n e l . ( R e f . F i g . 0 0 9 ) . A drain valve. Component Operating Settings - Air pressure switch : 1.5 ± 0.1 bars (21.75 ± 1.45 psi) - pressure decreasing 1 . 7 b a r s (2 ( 2 4 . 6 5 p s i ) m a xi x i m u m - p re re s s u r e i n c r e a s i n g . - Depressurization/relie f valve (4.2 + 0.3 - 0.2 bars) (60.9 + 4.35 - 2.90 psi) - pressure i n c r e a s in in g ( o p e n i n g ) 3 . 7 ± 0 . 1 b a r s ( 5 3 . 6 6 ± 1 . 4 5 p s i) i ) - p r e s s u r e d e c re re a s i n g ( c l o s i n g ) . - In the event of pressurization loss, pressure in the reservoir will not b e l o w e r t h a n 3 b a r s ( r e l a t i v e p r e s s u re re ) a f t e r 3 h o u r o p e r a t i o n .

- Air-fluid contact is direct. - A compartment feature ensures positive fluid supply to the pumps during negative "g" conditions of up to 20 seconds. - An internal device limits emulsion in the event of substantial return flow. A c c e ss o r y C o m p o n e n t s . The top of each reservoir is equipped with a pressurization manifold, including : . A check valve on the air supply line. . A d i r e ct c t r e a d i n g a i r p r e s su su r e g a g e . An air pressure switch which signals low pressure conditions to the flight compartment.


29-53 2953

ATA 29 A300/A310

A300/A310 G-B-Y Hydraulic System Reservoirs - General and Location

Yellow Reservoir Shown


Blue Reservoir Shown

29-54 2954

ATA 29 A300/A310

A310 Hydraulic System - Reservoir and Capacities - General Features Purpose . Each hydraulic system includes a reservoir which compensates for variat i o n s i n f l u i d v o lu lu m e d u e t o u s e r s e rv i c e o p e r a t i o n , a n d p r o v i d e s a r e s e r v e s u p p l y o f fl fl u i d . Reservoir volume included ; the volume of fluid in each system is approximately 170 l (44.8 US Gal) for Green system, 85 l (21.14 US Gal) for Blue system and 120 l (31.6 Us Gal) for Yellow system. . The three reservoirs are air-pressurized to 3.5 bars (50.8 psi). . Each reservoir is designed to remains pressurized for at least 12 hours. Description . The reservoirs are attached to the aircraft structure by two clamps e c u r e d s t r a p s . T h e y e a ch c h c o n s i s t o f a s h e e t s t e e l c yl yl i n d e r w i t h a mol d e d l i g h t a l l o y b a s e . C y l i n d e r d i a m e t e r i s t h e s a m e f o r e a c h r e s e r v o i r . T h e i r r e l a ti v e c a p a c i t i e s a r e t h e r e f o r e d e t e r m in e d b y t h e i r h e i g h t . Green Blue Yellow Total 40 l (10.57 USgal) 2 2 l (5.81 USgal) 28 l (7.4 USgal) ±3 l (0.79 USgal) (reserve) Max gageable 30 l (7.93 USgal) 17 l (4.49 USgal) 24 l (6.34 USgal) Fi l l l e v e l 17 l (4.49 USgal) 12 l (3.17 USgal) 18.5 l (4.89 (USgal) Low level 5 l ±0.5 (1.32 USgal ±.13) 5 l ±0.5 (1.32 USgal ±.13) warning The level of the three reservoirs may be adjusted separately at the Green s y s t e m g r o u n d s e rv rv i c e p a n e l . The yellow reservoir includes a reserve for RAT supply - Air-fluid contact is direct. - A compartment feature ensures positive fluid supply to the pumps during negative "g" conditions of up to 20 seconds. - An internal device limits emulsion in the event of substantial return flow.

Mi d w a y d o w n t h e r e s e r v o i r i s m o u n t e d a q u a n t i t y t r a n s m i t t e r c o m p r i s i n g : . A float, with actuating linkage and snubber. . A d i r e c t r e a d i n g q u a n t i ty g a g e . . An electrical connector for transmitting quantity signals and low level w a r n i n g s t o t h e f l i g h t co c o m p a r t m e n t a n d t o t h e G r e e n s y st st e m g r o u n d s e r v i c e panel. The bottom of the reservoir includes : . A suction port for supply of fluid to the pumps (± one for the ram air turbine on the Yellow system reservoir). . A return port with an overheat sensor. . A port connected to a self-sealing depressurization/relief valve i n th t h e g r o u nd n d s e rv rv i c e p a n e l . ( R e f . F i g . 0 1 1 ) . A drain valve. Component Operating Settings - Air pressure switch : 1.5 ± 0.1 bars (21.75 ± 1.45 psi) - pressure decreasing 1 . 7 b a r s (2 ( 2 4 . 6 5 p s i ) m a xi x i m u m - p re re s s u r e i n c r e a s i n g . - Depressurization/relie f valve (4.2 ± 0.3 - 0.2 bars) (60.9 ± 4.35 - 2.90 psi) - pressure i n c r e a s in in g ( o p e n i n g ) 3 . 7 ± 0 . 1 b a r s ( 5 3 . 6 6 ± 1 . 4 5 p s i) i ) - p r e s s u r e d e c re re a s i n g ( c l o s i n g ) . - In the event of pressurization loss, pressure in reservoir will not be l o w e r t h a n 3 b a r s ( re l a t i v e p r e s s u r e ) a f t e r 3 h o u r s o p e r a t i o n .

A c c e ss o r y C o m p o n e n t s . The top of each reservoir is equipped with a pressurization manifold, including : . A c h e c k v a l v e o n t h e a i r su su p p l y l i n e . . A direct reading air pressure gage (Accuracy ± 2° of angle) . An air pressure switch which signals low pressure conditions to the flight compartment. . A blanking cap.


29-55 2955

ATA 29 A300/A310

A300/A310 G-B-Y Hydraulic System Reservoirs - General and Locations

Yellow Reservoir Shown


Blue Reservoir Shown

29-56 2956

ATA 29 A300/A310

A300/Some A310 Hydraulic Reservoir Pressurization System - PW JT9D-7R4 Engine Purpose - To ensure in each hydraulic reservoir an air pressure of 3 to 3.5 bars ( 4 3 . 5 t o 5 0 . 7 p s i ) re l a t i v e s o a s t o p r e v e n t c a v i t a t i o n o f p u m p s o n t h e ground and throughout the whole flight envelope. - To maintain the reservoir sufficiently air-tight in the event of failure of the pressurization system or after engine shut-down. Description - The same system pressurizes the three hydraulic reservoirs by means of air bled from the 14 th stage (GE engines) of the L engine HP compressor o r f r o m t h e a i r b l e e d sy s y s t e m , o r , w h e n th th e e n g i n e s a r e s h u t d o w n , f r o m t h e d o w n , f r o m t h e c o n n e c t o r o n t h e B l u e s y s t e m g ro ro u n d s e r v i c e p a n e l . Bl e e d i n g a i r f r o m t h e a i r b l ee e e d s y s t e m o f f e r s th th e a d v a n t a g e o f o b t a i n i n g air from the APU either on the ground or during flight. - A depressurization/relief valve associated with each reservoir and located o n t h e g r o u n d s e rv r v i c e p a n e l o f e a c h s y s te te m e n a b l e s : . o v e r p r e s su s u r e t o b e a v o i d e d i n t h e r e s e r v o i r by by e v a c u a t i o n o f a i r o r fluid. Valve setting: 4.2 + 0.3 - 0.2 bars, (60.9 + 4.3 - 2.9 psi) pressure increasing 3.7 ± 0.1 bars, (53.6 ± 1.4 psi) pressure decreasing . e a c h r e se se r v o i r t o b e i n d i v i d u a l l y d e p r e ss u r i z e d . - A pressure reducing valve on the line from the L engine HP stage regul a t e s p r e s s u r e i n t h e re s e r v o i r t o 3 . 5 b a r s r e l a t i v e . P r e s s u r e r e d u c i n g v a l v e i s s e t t o 3 . 5 ± 0 1 b a r s (5 0 ± 1 . 4 p s i ) - Maximum pressure delivered by the air blee d system is 3 bars. (43.5 psi). - On each reservoir, a pressure switch warns the crew of low air pressure. Pressure switch setting : . 1.5 bars (21.7 psi) - pressure decreasing (warning activation) . 1 . 7 b a r s m a x ( 2 4 . 6 p s i ) - p r e ss s s u r e i n c r e a s i n g ( w a r n i n g d e - a c t i va va t i o n ) . - A restrictor, mounted in the pylon on the line from the L engine is int e n d e d t o l i m i t t h e a i r f l o w s o a s o b t a i n a n a c c e p t a b l e t e m p e r a tu tu r e i n t h e e v e n t o f r u p t u r e o f t h e p r e s s u r i z a ti ti o n s y s t e m i n t h e w i n g o r f u s e l a g e . The restrictor is protected by a filter incorporating a stainless steel metallic screen. - A filter, equipped with a by-pass and by-pass opening indicator, is mounted in the wing, on the pressurization line from the L engine, upstream of t h e p r e s s u r e r e d u c i n g va l v e . T h i s f i l t e r i s i n t e n d e d t o p r o t e c t t h e p r e s s u r e r e d u c i n g v a l v e a n d ch c h e c k v a l v e s f ro r o m a n y c o n t a m i n a t i o n f r o m th th e engine. - The check valves mounted in the system and on the reservoir are of the flapper type.


- - - - - - - - - - - -- - - - - - - - - - - - - -- - - - - - - - - - - - - -- - - - - - - - - - - - - -- - - - - - - - - - - - - -FIN FUNCTIONAL DESIGNATION PANEL ZONE ACCESS DOOR - - - - - - - - - - - -- - - - - - - - - - - - - -- - - - - - - - - - - - - -- - - - - - - - - - - - - -- - - - - - - - - - - - - -291376 FILTER - RSVR PRESSURIZATION 571 571DB 291378 CHECK VALVE - ENG1 PRESS LINE ISOL 571 571DB 291380 VALVE - PRESS REDUCING 571 571AB 291382 CHECK VALVE - ENG1 PRESS LINE GND ISOL 571 571DB 291383 PRESS GAGE - RSVR AIR, G 147 734 291391 GROUND CONNECTOR - RSVR PRESSURIZATION PRESSURIZATION 571 571BB 291392 RESTRICTOR/FILTER - PRESS LINE, ENG1 411 291394 CHECK VALVE - APU PRESS LINE ISOL 148 744 291398 FILTER - RSVR PRESSURIZATION 143 147BZ 292383 PRESS GAGE - RSVR AIR, B 571 571DB 293383 PRESS GAGE - RSVR AIR, Y 671 671DB

29-57 2957

-------ATA REF. -------29-14-13 29-14-14 29-14-12 29-14-14

29-14-15 29-14-17 29-14-13

ATA 29 A300/A310

A300/Some A310 - Hydraulic Reservoir Pressurization System - PW JT9D-7R4 Engine

RESERVOIR AIR

A300

ENG 1 PRESSURIZATION LINE

RESERVOIRPRESSURIZATION

RESERVOIR PRESSURIZATION

ENG 1 PRESSURIZATION LINE ISOLATING APU PRESSURIZATION LINE ISOLATING



29-58 2958

ATA 29 A300/A310

Some A310 - Hydraulic Reservoir Pressurization System - PW JT9D-7R4 Engine Purpose - To ensure in each hydraulic reservoir an air pressure of 3 to 3.5 bars ( 4 3 . 5 t o 5 0 . 7 p s i ) r e l a ti v e s o a s t o p r e v e n t c a v i t a t i o n o f p u m p s o n t h e ground and throughout the whole flight envelope. - To maintain the reservoir sufficiently air-tight in the event of failure t h e p r e s s u r i z a t i o n s y s t e m o r a f t e r e n g i n e sh sh u t - d o w n . Description - The same system pressurizes the three hydraulic reservoirs by means of a i r b l e d f r o m t h e 1 5 t h s t a g e ( P & W e n g i n e s ) o f t h e L e n g i n e HP HP c o mmc o m p r e s s o r o r fr f r o m t h e a i r b l e e d s ys y s t e m , o r , w h e n t h e e n g in in e s a r e s h u t d o w n , f r o m t h e c o n n e ct c t o r o n t h e B l u e s ys y s t e m g r o u n d s e r vi vi c e p a n e l . Bl e e d i n g a i r f r o m t h e a i r b l e e d s y s t e m o f f e r s t h e a d v a n t a g e o f o b t a i n i n g air from the APU either on the ground or during flight. - The same system pressurizes the three hydraulic reservoirs by means of air bled from the 14 th stage (GE engines) of the L engine HP compressor or from the air bleed system, or, when the engines are shut down, from the d o w n , f r o m t h e c o n n e ct c t o r o n t h e B l u e s ys y s t e m g r o u n d s e r vi vi c e p a n e l . Bl e e d i n g a i r f r o m t h e a i r b l e e d s y s t e m o f f e r s t h e a d v a n t a g e o f o b t a i n i n g air from the APU either on the ground or during flight. - A depressurization/relief valve associated with each reservoir and located o n t h e g r o u n d s e rv rv i c e p a n e l o f e a c h s y s t e m e n a b l e s : . o v e r p r e s s u re re t o b e a v o i d e d i n t h e r e s e r v o i r b y e v a c u a t i o n o f a i r o r fluid. Valve setting : 4 . 2 + 0 .3 . 3 - 0 . 2 b a rs rs , ( 6 0 . 9 + 4 .3 .3 - 2 . 9 p s i ) p r e s s u r e i n c r e a s i n g 3.7 ± 0.1 bars, (53.6 ± 1.4 psi) pressure decreasing . each reservoir to be individually depressurized. - A pressure reducing valve on the line from the L engine HP stage regulates pressure in the reservoir to 3.5 bars relative. Pressure reducing valve is set to 3.5 ± 01 bars (50 ± 1.4 psi) - Maximum pressure delivered by the air bleed system is 3 bars. (43.5 psi). - On each reservoir, a pressure switch warns the crew of low air pressure. Pressure switch setting : . 1 . 5 b a r s ( 2 1 . 7 p s i ) - p r e s s u r e d e c r e a si s i n g ( w a r n i n g a c t i va va t i o n ) . 1 . 7 b a r s m a x ( 2 4 . 6 p s i ) - p r e s s u r e i n c re re a s i n g ( w a r n i n g d e - a c t i v a t i o n ) . - A restrictor, mounted in the pylon on the line from the L engine is int e n d e d t o l i m i t th th e a i r f l o w s o a s o b t a i n a n a c c e p t a b l e te m p e r a t u r e i n t h e e v e n t o f r u p t u r e o f t h e p r e s su s u r i z a t i o n s y st st e m i n t h e w i n g o r f u s e l a g e . T h e r e s t r i c t o r is p r o t e c t e d b y a f i l te r i n c o r p o r a t i n g a s ta i n l e s s s t e e l metallic screen. - A filter, equipped with a by-pass and by-pass opening indicator, is mounted in the wing, on the pressurization line from the L engine, upstream of the pressure reducing valve. This filter is intended to protect the press u r e r e d u c i n g va v a l v e a n d c h e c k v a lv l v e s f r o m a n y c o n ta ta m i n a t i o n f r o m t h e engine. - The check valves mounted in the system and on the reservoir are of the flapper type.


-----------------------------------------------------------------------------FIN FUNCTIONAL DESIGNATION PANEL ZONE ACCESS ATA DOOR REF. -----------------------------------------------------------------------------291376 FILTER-RSVR PRESSURIZATION 571 571DB 29-14-13 291378 CHECK VALVE-ENG1 PRESS LINE ISOL 571 571BB 29-14-14 291380 VALVE-PRESS REDUCING, ENG1 PRES571 571DB 29-14-12 291382 CHECK VALVE-ENG1 PRESS LINE ISOL 571 571DB 29-14-14 291383 PRESS GAGE-RSVR AIR, G 147 734 29-14-33 291391 GROUND CONNECTOR-RSVR PRESSURIZATION 571 571DB 29-14-21 291392 R E S T R I C T O R / F I L T E R - P RE RE S S L I N E , E N G 1 411 29-14-15 291394 CHECK VALVE-APU PRESS LINE ISOL 143 147BZ 29-14-17 291398 F I L T E R - R S V R P R E S S U R I Z A T IO IO N 143 147BZ 29-14-13

29-59 2959

ATA 29 A300/A310

A300/Some A310 - Hydraulic Reservoir Pressurization System - PW JT9D-7R4 Engine

RESERVOIR AIR

A300

ENG 1 PRESSURIZATION LINE


RESERVOIR PRESSURIZATION

ENG 1 PRESSURIZATION LINE ISOLATING APU PRESSURIZATION LINE ISOLATING



29-60 2960

ATA 29 A300/A310

A300/A310 RH ECAM Hydraulic Fluid Reservoir - Quantity Indication SERVICING

ACTION

The top of the upper Green arcs on the overhead indicators are NOT the "full marks" for the systems. The upper Green arcs are intended to show the normal service range with the aircraft on the ground. This service range allows for the normal thermal expansion of the hydraulic fluid.

The ECAM hydraulics page should always be consulted before changing the level in the hydraulic fluid reservoirs. The ECAM quantity indication should be considered correct for all A300-600R and A310-200 series aircraft.

The hydraulic fluid has an average coefficient of thermal expansion of 0.00085 per degree C. An aircraft might indicate a fluid level near the bottom of the normal service range after an overnight stay at EWR (Newark) (20°F/-7°C). The same aircraft, with no reservoir servicing, could indicate an hydraulic fluid level near the top of the normal service range after an overnight at IAH (Houston) (86°F/30°C).

If the triangular pointer is in the normal service range on the ECAM hydraulics page, the fluid level in the hydraulic reservoirs should be considered normal. The ECAM normal service range corresponds to the upper Green arcs on the later overhead indicators.

FedEx A310-200 series aircraft were acquired with two types of flight deck Overhead Panel Hydraulic Fluid Quantity Indicators. The upper Green arcs on the indicators on older aircraft are smaller than those used on later A310 aircraft.


If an hydraulic reservoir requires service, it should be filled only to the full mark corresponding to that system on the ground servicing panel. Never fill the reservoirs above the full level indicated on the Green ground service panel. If a reservoir is over-filled while being serviced, it should be drained to the proper level. Over-filling a system will cause additional maintenance and could damage the reservoir.

29-61 2961

ATA 29 A300/A310

A300/A310 Hydraulic Reservoirs and Pressurization System - Schematic


29-62 2962

ATA 29 A300/A310

A300/A310 RH ECAM HYD Page A300

Overhead Panel HYD PWR 427 VU Panel

NORMAL SERVICE RANGE WITH A/C ON THE GROUND

Some A310s


29-63 2963

ATA 29 A300/A310



29-64 2964

ATA 29 A300/A310

A300/A310 Hydraulic System Reservoir Air Lights - MEL Requirements

AIR Light In Normal configuration, the AIR light is extinguished and the legend is not visible. The legend comes on amber when reservoir air pressure is below 22 PSI. Illumination of the AIR light is associated associated with SC and ECAM activation On A300-600 and some A310-200 aircraft AIR light illumination is also accompanied by illumination of the Master CAUTION lights on the CAPT and F/O Main Instrument Panels 3VU and 5VU. On remaining A310-200 aircraft, it is accompanied by illumination of the HYD light on the Warning Light Display Panel.


29-65 2965

ATA 29 A300/A310

A300/A310 Hydraulic System Reservoir Air Lights - MEL Requirements


29-66 2966

ATA 29 A300/A310

GREEN AUXILIARY HYDRAULIC SYSTEM NUMBER 1


29-67 2967

ATA 29 A300/A310

A300/A310 Green Auxiliary Hydraulic Power - Description DESCRIPTION Two parallel-mounted electric pumps supply power: -

To the Green system, directly, To the Blue and Yellow systems, through Green/Blue and Green/Yellow power transfer units.

Both electric pumps draw fluid from the Green system reservoir, and are of the soft compensation type. They are used mainly on the ground, for testing or pre-flight check list procedures, but can also be used in flight, at the crew's discretion, to boost fluid flow. However, such cases of utilization are never of a mandatory nature. LOCATION Installed in the fuselage center section (hydraulics compartment) on the ceiling, between FR52 and FR53.


29-68 2968

ATA 29 A300/A310

A300/A310 Green Auxiliary Hydraulic Power


29-69 2969

ATA 29 A300/A310

A300 Green Hydraulic System - Electric Pumps - General Hydraulic Pump

-1 on the HP manifold of each system to indicate a l ow pressure condition in the system.

A p r e s s u r e c o m p e n s a t i n g m e c h a n i s m i s i n c o r p o r a t e d , w h i c h o p e r a t e s t o k e e p the delivery smooth and constant by altering the angle of the inclined hanger face in response to system pressure fluctua tions. Pressure is maintained within a preselected range in response to variations in system demand. The discharge flow decreases gradually in the three steps as shown in the curve of nominal pump-motor performance: - Output pressure at zero delivery: 206 +4 -0 bars (3028 PSI (+70/-0 PSI)) - O u t p u t p r e s s u r e f o r d e l i v e r y o f 2 3 l / m n : 1 9 5 b a r s ( 6 . 1 G P M / M I N @ 2 8 67 6 7 PS PS I ) - Output pressure for delivery of 36 l/mn: 115 bars. (9.51 GPM/MIN @1690 PSI) N O T E : B e t w e e n 2 3 a n d 3 6 l / m n , o u t l e t p r e s s u r e va va r i e s l i n e a r l y f r o m 195 bars to 115 bars. - Suction pressure . 1 bar absolute for delivery of 36 l/mn (9.51 GPM) . 0.6 bar absolute for delivery of 35 l/mn (9.25 GPM) . 0 . 2 b a r a b s o lu lu t e f o r d e l i v e r y o f 0 t o 3 0 l / m n . ( 0 T O 7 . 9 2 G P M ) - T o l e r a n c e o n d e l i v e r y , p r e s s u r e a n d e l e c t r i c a l v a l u e s i s ± 2 %. %.

W AR AR NI NI N G :

M A K E C E R TA TA I N TH TH A T TH TH E G RE RE E N R ES ES E R VO VO I R I S P R E S S U R I Z E D T O AV OI D EL EC TR IC PU M PS C AV IT AT IO N DU RI NG TH EI R OP ER AT IO N.

NOTE: 1 U.S. gallon = 3.785 liters.

Both pumps are controlled simultaneously by a pushbutton switch on the HYD PWR section of the overhead panel. When operated, the complete GREEN system is pressurized. Electrical power supply for the AC motors is from AC BUS 1 and AC BUS 2 respectively. PRESSURE SWITCHES AND PRESSURE TRANSMITTERS The pressure switches are installed: 1 on the delivery line of each engine pump to activate a warning in the event of pump low pressure condition. 1 on the common delivery line of the Green system electric pumps to indicate a pressure drop when these electric pumps are supplied with power.


-1 on the servo controls manifold of each system to indicate a low pressure condition. -1 on the ram air turbine pump delivery system, mounted on the ground checkout module. -1 on each reservoir to detect a low air pressure condition. A pressure transmitter is moun ted on the manifold of e ach of the three systems. Electric Motor - Contin uous duty operation on alternating current - Current: 45 A max. in continuous operation at full load - The motor is connected to the b usbar by a triple conductor cable ; the i m p e d a n c e o f e a c h c o n d u c t o r i s su su c h t h a t t h e i n - l i n e v o l t a g e d r o p i s a p p r o x i m a t e ly ly 5 . 5 V f o r t h e r a t e d l o a d - Mean nominal voltage of 3 phases at the busbar: 115/200 V - Mean limit voltage of 3-phases at the busbar: 111 and 119 V - In normal operation at nominal power, the mean voltage of the three phases at the motor terminals may therefore drop to 105.5 V, taking into a c c o u n t v o lt l t a g e v a r i a t i o n s d u e t o r e g u l a t i o n. n. - Rotational speed: approximately 7700 rpm - Air cooled.

The operating principle is based on a variable reluctance. Electric Pump Circuit Breakers (CB) CB Panel 101 VU (GEN 1/GEN 2) Avionics Bay -Green Electric Pump Number 1: -Rated: 50 Amps -Location: LH Side CB Panel 101 VU -CB FIN: 1GE Green Electric Pump Number 2: -Rated: 50 Amps -Location: RH Side CB Panel 101 VU CB FIN: 2GE

29-70 2970

ATA 29 A300/A310

A300 Green Hydraulic System Electric Pumps - General Installation

Removal CAUTION: CAUTION: CHECK THE HYDRAULIC HYDRAULIC SYSTEM SYSTEM FILTERS FILTERS IF THE PUMP HAS BEEN REMOVEDBECAUSE OF OPERATION WITHOUT FLUID, OR BECAUSE OF MALFUNCTIONING AND HENCE POSSIBLE INTERNAL DAMAGE. IF FOREIGN MATTER IS FOUND ON THE FILTERS, THE LINES CONNECTING THE PUMP TO THE FILTERS MUST BE FLUSHED. SUPPORT THE PUMP DURING REMOVAL AND INSTALLATION OPERATIONS. APPROXIMATE WEIGHT : 12.7 kg (28 lb.) AFTER REMOVAL CHECK THAT THE SHOCKMOUTS AND THE SHOCKMOUTS AND THE PUMP ATTACHMENT FITTINGS ARE NOT DAMAGED. IF ONE PART IS DAMAGED. SUBSTITUTE A NEW COMPLETE SET FOR USED ONE.


29-71 2971

ATA 29 A300/A310

A310 Green Hydraulic System - Electric Pumps - General Hydraulic Pump

Electric Motor

A p r e s s u r e c o m p e n s a t i n g m e c h a n i s m i s i n c o r p o r a t e d , w h i c h o p e r a t e s t o k e e p the delivery smooth and constant by altering the angle of the inclined hanger face in response to system pressure fluctua tions. Pressure is maintained within a preselected range in response to variations in system demand.

- C o n t i n u o u s d u t y o p e r a t i on o n o n a l t e r n a t in in g c u r r e n t - Current: 45 A max. in continuous operation at full load - The motor is connected to the b usbar by a triple conductor cable ; the impedance of each conductor is such that the in-line voltage drop is a p p r o x i m a t e ly l y 5 . 5 V f o r t h e ra ra t e d l o a d - Mean nominal voltage of 3 phases at the busbar: 115/200 V - Mean limit voltage of 3-phases at the busbar: 111 and 119 V - In normal operation at nominal power, the mean voltage of the three phases at the motor terminals may therefore drop to 105.5 V, taking into a c c o u n t vo v o l t a g e v a r i at at i o n s d u e t o r e g u l a t i o n . - Rotational speed: approximately 7700 rpm - Air cooled.

The discharge flow decreases gradually in the three steps as shown in the curve of nominal pump-motor performance: - Output pressure at zero delivery: 206 +4 -0 bars (3028 PSI (+70/-0 PSI)) - O u t p u t p r e s s u r e f o r d e l i v e r y o f 2 3 l / m n : 1 9 5 b a r s ( 6 . 1 G P M / M I N @ 2 8 67 6 7 PS PS I ) - Output pressure for delivery of 36 l/mn: 115 bars. (9.51 GPM/MIN @1690 PSI) N O T E : B e t w e e n 2 3 a n d 3 6 l / m n , o u t l e t p r e s s u r e va va r i e s l i n e a r l y f r o m 195 bars to 115 bars. - Suction pressure . 1 bar absolute for delivery of 36 l/mn (9.51 GPM) . 0.6 bar absolute for delivery of 35 l/mn (9.25 GPM) . 0 . 2 b a r a b s o lu lu t e f o r d e l i v e r y o f 0 t o 3 0 l / m n . ( 0 T O 7 . 9 2 G P M ) - T o l e r a n c e o n d e l i v e r y , p r e s s u r e a n d e l e c t r i c a l v a l u e s i s ± 2 %. %.

W AR AR NI NI N G :

M A K E C E R TA TA I N TH TH A T TH TH E G RE RE E N R ES ES E R VO VO I R I S P R E S S U R I Z E D T O AV OI D EL EC TR IC PU M PS C AV IT AT IO N DU RI NG TH EI R OP ER AT IO N.


29-72 2972

ATA 29 A300/A310

A310 Green Hydraulic System Electric Pumps - Component Location


29-73 2973

ATA 29 A300/A310

A300/A310 Blue Main Hydraulic Power - Description GENERAL -

This system is the least complex of the three. It supplies only the flight controls. It is pressurized by: - the pump driven by the L engine - the Green/Blue power transfer unit - a ground power cart.

The self-sealing connectors for connection of ground power carts are located in a service panel under the L wing. These connectors include one for connection of pneumatic ground equipment, used to pressurize the three reservoirs simultaneously.

USERS A. Supplied throu gh the servo controls mani fold (or through wing an d aft fuselage isolation valves). -

B. Supplied through the the HP manifold, via a priority priority valve: valve: -


Two all speed aileron servo controls (L and R ASA) Two elevator servo controls (L and R) One rudder servo control Six actuators on L and R spoilers 1, 4 and 7 (A300) Six actuators on L and R spoilers 2, 3 and 7 (A310) One yaw damper actuator servo motor.

29-74 2974

One slat power control unit hydraulic motor.

ATA 29 A300/A310

A300 Blue Hydraulic Power System - Schematic


29-75 2975

ATA 29 A300/A310

BLUE MAIN HYDRAULIC SYSTEM NUMBER 2


29-76 2976

ATA 29 A300/A310

A300/A310 Blue Main Hydraulic Power - Description GENERAL -

This system is the least complex of the three. It supplies only the flight controls. It is pressurized by: - the pump driven by the L engine - the Green/Blue power transfer unit - a ground power cart.

The self-sealing connectors for connection of ground power carts are located in a service panel under the L wing. These connectors include one for connection of pneumatic ground equipment, used to pressurize the three reservoirs simultaneously.

USERS A. Supplied throu gh the servo controls mani fold (or through wing an d aft fuselage isolation valves). -

B. Supplied through the the HP manifold, via a priority priority valve: valve: -


Two all speed aileron servo controls (L and R ASA) Two elevator servo controls (L and R) One rudder servo control Six actuators on L and R spoilers 1, 4 and 7 (A300) Six actuators on L and R spoilers 2, 3 and 7 (A310) One yaw damper actuator servo motor.

29-77 2977

One slat power control unit hydraulic motor.

ATA 29 A300/A310

A310 Blue Hydraulic Power System - Schematic


29-78 2978

ATA 29 A300/A310

A300 Blue Main Hydraulic Power - Component Locations and FIN - - - - - - - - - - - - -- - - - - - - - - - - - - -- - - - - - - - - - - - - - -- - - - - - - - - - - - - - -- - - - - - - - - - - - - -- - FIN FUNCTIONAL DESIGNATION PANEL ZONE ACCESS ATA DOOR REF. - - - - - - - - - - - - -- - - - - - - - - - - - - -- - - - - - - - - - - - - - -- - - - - - - - - - - - - - -- - - - - - - - - - - - - -- - 292000 RESERVOIR - HYDRAULIC, BLUE 571 571AB 29-11-11 292002 FILTER - RSVR RETURN, BLUE 571 571AB 29-11-15

292005 292006 292008 292010

VALVE - DEPRESS/RELIEF, B RSVR GROUND CONNECTOR - SUCTION, B GROUND CONNECTOR - DELIVERY, B MANIFOLD - SERVO CONTROLS, B

571 571BB 571 571BB 571 571BB 147 734

292030 292040 292048 292060

PUMP-BLUE, ENG1 VALVE-NON RETURN FILTER - B PUMP DELIVERY, ENG1 MANIFOLD - HP, BLUE

435 420 147 147

2 92063 292070 292072

RELIEF VALVE - BLUE PUMP DELIVERY ACCU - BLUE PWR PRESS GAGE - BLUE ACCU

29-12-34

435AL

29-11-32

734 734

29-11-42 29-12-12

147 147 147

734 734 734

29-11-55 29-11-56

VALVE - BLUE PUMP FIRE, ENG1 P RE RE SS SS S WI WI T C H - H P M A N I F O L D , B FILTER MODULE ASSY - ENG PUMP CASE D RA RA I N

575 147 452

575FB 734 452AR

29-11-33

292004 292095 292050

FILTER - ENG PUMP CASE DRAIN MANIFOLD-LP, BLUE CHECK VALVE-G/B PTU DELIVERY CHECK VALVE-B PUMP DELIVERY, ENG 1

452 147 147 147

452AR 734 734 734

292014 292022 3 3 GJ GJ

CHECK VALVE-CASE DRAIN, B CHECK VALVE-RETURN, B HP MANIFOLD P R ES ES S S W I T C H - B P U M P , E N G 1

147 147 473

734 734 473AL

9GJ 2 9W 9W W


29-79 2979

ATA 29 A300/A310

A300 Blue Main Hydraulic Power - Component Location and FIN


29-80 2980

ATA 29 A300/A310

A300 Blue Main Hydraulic Power - Component Locations and FIN - - - - - - - - - - - - -- - - - - - - - - - - - - -- - - - - - - - - - - - - - -- - - - - - - - - - - - - - -- - - - - - - - - - - - - -- - FIN FUNCTIONAL DESIGNATION PANEL ZONE ACCESS ATA DOOR REF. - - - - - - - - - - - - -- - - - - - - - - - - - - -- - - - - - - - - - - - - - -- - - - - - - - - - - - - - -- - - - - - - - - - - - - -- - 292000 RESERVOIR - HYDRAULIC, BLUE 571 571AB 29-11-11 292002 FILTER - RSVR RETURN, BLUE 571 571AB 29-11-15

292005 292006 292008 292010

VALVE - DEPRESS/RELIEF, B RSVR GROUND CONNECTOR - SUCTION, B GROUND CONNECTOR - DELIVERY, B MANIFOLD - SERVO CONTROLS, B

571 571BB 571 571BB 571 571BB 147 734

292030 292040 292048 292060

PUMP-BLUE, ENG1 VALVE-NON RETURN FILTER - B PUMP DELIVERY, ENG1 MANIFOLD - HP, BLUE

435 420 147 147

2 92063 292070 292072

RELIEF VALVE - BLUE PUMP DELIVERY ACCU - BLUE PWR PRESS GAGE - BLUE ACCU

29-12-34

435AL

29-11-32

734 734

29-11-42 29-12-12

147 147 147

734 734 734

29-11-55 29-11-56

VALVE - BLUE PUMP FIRE, ENG1 P RE RE SS SS S WI WI T C H - H P M A N I F O L D , B FILTER MODULE ASSY - ENG PUMP CASE D RA RA I N

575 147 452

575FB 734 452AR

29-11-33

292004 292095 292050

FILTER - ENG PUMP CASE DRAIN MANIFOLD-LP, BLUE CHECK VALVE-G/B PTU DELIVERY CHECK VALVE-B PUMP DELIVERY, ENG 1

452 147 147 147

452AR 734 734 734

292014 292022 3 3 GJ GJ

CHECK VALVE-CASE DRAIN, B CHECK VALVE-RETURN, B HP MANIFOLD P R ES ES S S W I T C H - B P U M P , E N G 1

147 147 473

734 734 473AL

9GJ 2 9W 9W W


29-81 2981

ATA 29 A300/A310

A300 Blue Main Hydraulic Power - Component Locations and FIN


29-82 2982

ATA 29 A300/A310

A310 Blue Main Hydraulic Power - Component Locations and FIN

- - - - - - - - - - - - - -- - - - - - - - - - - - - - - -- - - - - - - - - - - - - - -- - - - - - - - - - - - - - -- - - - - - - - - - - - - - -FIN FUNCTIONAL DESIGNATION PANEL ZONE ACCESS ATA DOOR REF. - - - - - - - - - - - - - -- - - - - - - - - - - - - - - -- - - - - - - - - - - - - - -- - - - - - - - - - - - - - -- - - - - - - - - - - - - - -292000 R E S E R V O I R - H Y DR DR A U L I C , B L U E 571 571BB 29-11-11 292002 FILTER-RSVR RETURN, BLUE 571 29-11-15 292005 292006 292008 292010

VALVE-DEPRESS/RELIEF, B RSVR GROUND CONNECTOR-SU CTION, B G R O U N D C O N N E C T O R - D E L I V E R Y, Y, B MANIFOLD-SERVO CONTROLS, B

571 571DB 571 571DB 571 571DB 571 734

292030 9GJ 292040

PUMP-BLUE, ENG1 VALVE-BLUE PUMP FIRE, ENG1 VALVE-NON RETURN

452 575 420

292048 292060 292063 292070

FILTER-B PUMP DELIVERY, ENG1 MANIFOLD-HP, BLUE RELIEF VALVE-BLUE PUMP DELIVERY ACCU-BLUE PWR

292072 2 9W 9W W 292004

PRESS GAGE-BLUE ACCU P RE RE SS SS S WI WI T C H - H P M A N I F O L D , MANIFOLD-LP, BLUE

292095 292050 292014 292022

CHECK CHECK CHECK CHECK

33GJ

For Training Purposes Only

734

29-11-32 29-11-33 20-11-42 29-12-12 29-11-55 29-11-56

571 571 571

B

VALVE-G/B PTU DELIVERY VALVE-B PUMP DELIVERY, ENG 1 VALVE-CASE DRAIN, B VALVE-RETURN, B HP MANIFOLD

PRESS SWITCH-B PUMP, ENG1 FILTERS-ENGINE - PUMP CASE D RA RA I N

MTT M540000 / R3.3 01AUG01

571 571 571 571

452AR 575AL

29-12-34

147 147 147 147 473 435

29-83 2983

734 734 734 734 473AL 435AL

29-12-62 29-11-36

ATA 29 A300/A310

A310 Blue Main Hydraulic Power - Component Locations”


29-84 2984

ATA 29 A300/A310

BLUE AUXILIARY HYDRAULIC SYSTEM NUMBER 2


29-85 2985

ATA 29 A300/A310

Blue Auxiliary Hydraulic Power System DESCRIPTION The Green/Blue power transfer unit is composed of an hydraulic motor driving an hydraulic pump by means of a mechanical liaison (shaft). The motor operates off fluid supplied from the Green system; the pump pressurizes the Blue system and draws its fluid from the Blue system reservoir. This system allows transfer of power, while maintaining independence of the fluid sources. A solenoid or motor-controlled flow shut off valve integral with the motor enables activation or deactivation of the transfer unit. The transfer unit is used mainly on the ground to pressurize the Blue system by means of the Green system, which is itself pressurized by the Green system electric pumps or by a ground power cart. It may also be used in flight to compensate for failure of the Blue system engine pump. Transfer unit operation is initiated by commanding opening of the motor section solenoid-controlled flow shut off valve. To prevent transfer unit overspeed occurring in the event of a Blue system pressure line rupture, the motor section includes a flow limiter.

CONTROL The transfer unit is started by means of a PTU pushbutton switch located on overhead panel 427VU (the transfer unit is activated when the pushbutton switch is pressed in). Location – Installation – LH Wing Inboard – Wing Root Area The power transfer unit is located in the L wing triangular bay (Blue hydraulics compartment). It is attached through flexible fittings to a rigid mount, integral with the aircraft structure. All lines connected to the motor (pressure, return, return, case drain) and to the pump (suction, pressure, case drain) are teflon hoses covered with stainless steel braid. The transfer unit is installed with respect to the Blue system reservoir in such a way that there is a constant head of fluid. The transfer unit is started up by means of a PTU pushbutton switch located on overhead panel 427VU, (the transfer unit is activated when the pushbutton switch is pressed in).

LOCATION - INSTALLATION The power transfer unit is located in the wing center box, at FR53, on the left side of the fuselage. It is attached through flexible fittings to a rigid mount, integral with the aircraft structure. All lines con nected to the motor (press ure, return, case drai n) and to the pump (suction, pressure, case drain) are Teflon hoses covered with stainless steel braid.


29-86 2986

ATA 29 A300/A310

A300/A310 Blue Auxiliary Hydraulic Power System


29-87 2987

ATA 29 A300/A310

Green/Blue or Green/Yellow Green/Yellow Power Transfer Units (PTUs) (P TUs) - General Each PTU consists of a hydraulic motor driven by GREEN hydraulic pressure, and a hydraulic pump in the receiving system. Motor and pump are connected by a drive shaft.

HIGH PRESSURE MANIFOLD EQUIPMENT

Each motor has an electrovalve which controls pressurized GREEN hydraulic supply to the motor, the GREEN pressure being generated by the engine pump or the Green electric pumps.

-

The nominal output of the pump in the BLUE or in the YELLOW system is 23.7 gal/min (90 ltr/min) at a pressure of 2500 PSI. With no flow demand the pressure is 3000 PSI. Each motor in the GREEN system requires 29.3 gal/min (111 ltr/min) at 3000 PSI to produce the nominal pump output. Only one PTU may be operated at a time.

-

Each PTU is controlled by a pushbutton switch on the HYD PWR section of the overhead panel, which operates the motor electrovalve. A PTU may be used in flight in case of hydraulic power generation failure in the BLUE or the YELLOW system. On the ground, with the GREEN system pressurized by both electric pumps, they are used to pressurize the BLUE or the YELLOW system for maintenance purpose. Electrical power for both PTU solenoid valves is from the 28 DC normal bus.

Each high pressure manifold is equipped with: one pressure switch one pressure transmitter an over-pressure over-pressure relief/manual relief/manual relief valve (manual relief on ground only) a priority valve.

HP FILTERS 1 2 1 1 1 1 1 1

-

on th the ma main Bl Blue sy system on the main Green system on th the ma mai n Ye Yellow sy system on the the Gre Green en/B /Blu lue e powe powerr tra trans nsfe ferr uni unitt del deliv iver eryy line line on the the Gre Green en/Y /Yel ello low w pow power er tra trans nsfe ferr unit unit del deliv iver eryy line line on the Green Green system system brakin braking g line line 1 -in the reserv reservoir oir filling filling system system on the the del deliv iver eryy line line of of the the Gre Green en sys syste tem m elec electr tric ic pum pumps ps.. on the the Yel Yello low w sys syste tem m ele elect ctri ricc pum pump p del deliv iver eryy lin line. e.

These filters are of the non bypassing type, with a clogging indicator set to operate at 6 bars (87 PSI) ± 10%. Filtering capability is 3 to 15 microns (0.0001 in. to 0.0006 in.) absolute. An automatic shutoff mec hanism in the fi lters prevents any leakage and any fluid flow between the filter inlet and outlet when the bowl and filter element are removed and prevents ingress of air into the system when the filter is installed. Filter elements may be either cleanable or disposable.


29-88 2988

ATA 29 A300/A310

A310 Hydraulic Auxiliary Power System - Power Transfer Unit (PTU) - Component Locations


29-89 2989

ATA 29 A300/A310

A300/A310 Hydraulic Systems Systems - G/B or G/Y Power Transfer Unit (PTU) - Schematic Performance N o m i n a l d e l i ve r y Nomi nal pressure at nominal delivery

Max Max pre presssure sure,, tra trans nsfe ferr uni unitt wit with h low low deli delive very ry

Suction pressure or nominal pressure Max flow in case drain Max flow across motor (flow limiter setting)

Green Pressure and Return

G/B PTU - FIN 5GL G/Y PTU - FIN 6GL

Pump 9 1 L /M N 2500 PSI

Motor 1 21 L/ MN 2500 PSI min differential between inlet and outlet

3000 3000 PSI PSI (3400 PSI, ) exceptionally provided that associated SERVO CTL pushbutton switch is in the OFF position) 35 PSIG 8 L /M N

3000 PSI differential between inlet and outlet

100 PSIG 8 L/MN 1 25 L/ MN

Blue or Yellow Pressure

1 U.S. gallon = 3.785 liters


29-90 2990

ATA 29 A300/A310

A300/A310 Auxiliary Hydraulic Hydraulic Power System - G/B PTU Control

NOTE: Green/Yellow PTU Control System identical to G/B PTU Control System


29-91 2991

ATA 29 A300/A310

YELLOW YELLOW MAIN HYDRAULIC SYSTEM SYSTEM NUMBER 3


29-92 2992

ATA 29 A300/A310

A300/A310 Yellow Main Hydraulic Power System - Description compartment doors are operated separately through the associated electromechanical electromechanical selector valves on the manifold or by means of the hand pump connected at the outlet of the selector valves. The hand pump cannot be used for repre ssurizing the brake accumulators.

GENERAL The Yellow hydraulic system allows: -

Operation of the control surfaces even with with in-flight engine failure, by means of the ram air turbine Alternate braking and parking On ground operation of the cargo compartment doors.

USERS A. Supplie d through the servo co ntrols mani fold (or throu gh wing and aft fuselage isolation valves).

The three functions above correspond to three sections of the HP manifold.

-

A. The flight co ntrols section receives press ure through the s ervo controls manifold, from engine 2 pump, the RAT and the ground connector. It can be pressurized directly through a filter by the Green/Yellow power transfer transfer unit. It supplies the flap power control unit Yellow hydraulic motor through a priority valve and includes the same components as the other HP manifolds. B. The monitoring monitoring section section is supplied supplied by the the other two sections sections through through two check valves and includes two brake Yellow power accumulators, similar to but of a larger capacity than the hydraulic system power accumulators, a pressure transmitter and a brake Yellow pressure relief valve with manual depressurization feature.

B. Supplie Supplied d through through the HP HP manifol manifold: d: -

C. The cargo compartment compartment door section is supplied by the Yellow Yellow electric pump through a filter and a check valve. The forward and aft


Two all speed aileron servo controls, L and R Two elevator servo controls, L and R One rudder servo control Six actuators on spoilers 2, 3 and 5, L and R (A300) Six actuators on spoilers 1, 4 and 6, L and R (A310) One trimmable horizontal stabilizer actuator motor One autopilot pitch actuator servo motor One autopilot yaw actuator servomotor One autopilot roll actuator servomotor One pitch artificial feel unit actuator. One yaw damper actuator servo motor.

29-93 2993

One flap power control unit motor, via a priority valve Yellow braking system alternate and parking Two forward and aft aft cargo compartment compartment door door actuators. One main deck cargo compartment (MDCC) door actuator

ATA 29 A300/A310

A300 Yellow Hydraulic Power System - Schematic NOTE: MDCC Door on Main Deck is powered on the FWD/AFT Cargo Door pressure/return line system

*MDCC Door


29-94 2994

ATA 29 A300/A310

A300 Yellow Main Hydraulic Power - Component Locations and FIN

FIN


PANEL

ZONE

AC C E S S

ATA

DO O R

REF.

293000

RESERVOIR - HYDRAULIC, YELLOW

671

671AB

29-11-11

293002 293005

FILTER - RSVR RETURN, YELLOW VALVE - DEPRESS/RELIEF, Y RSVR

671 671

671AB 671BB

29-11-15

293006

GROUND CONNECTOR - SUCTION, Y

671

671BB

293008

GROUND CONNECTOR - DELIVERY, Y

671

671BB

293010

MANIFOLD - SERVO CONTROLS, Y

148

734

29-13-34

293031 293042

P U M P - Y E L L O W , EN G 2 VALVE- NON RETURN

445 420

445AL

29-11-32

293049

FILTER-Y PUMP DELIVERY, ENG 2

148

734

29-11-42

293060

MANIFOLD-HP, YELLOW

148

734

29-12-12

293063

RELIEF VALVE-YELLOW PUM P DELIVERY

148

734

29-13-55

293070 293072

A C C U - Y E LL O W P W R PRESS GAGE-YELLOW ACCU

148 148

734 734

29-11-56 29-11-33

2G D

VALVE-YELLOW, PUM P FI R E , E N G 2

675

675FB

31 W W

PRESS SWITCH-HP MANIFOLD,

148

734

6G D

PRESS SWITCH-Y PUMP, ENG 2

483

483AL

29-13-62

FILTERS-ENG PUMP CASE

462

462AR

29-11-36

Y

293014

DRAIN CHECK VALVE-BRAKE RETURN,

293022

CHECK VALVE-RETURN, Y HP M ANIFOLD

293024

CHECK VALVE-CASE DRAI N ,

148

734

293051

CHECK VALVE-Y PUMP DELIVERY, ENG 2

148

734

293054 293055

CHECK VALVE-AFT CARGO DO OR SUPPLY CHECK VALVE-FWD CARGO DOOR SUPPLY

148 148

734 734

293058

CHECK VALVE-BRK ACCU PRESS Y

148

734

293059

CHECK VALVE-BRK ACCU PRESS Y

148

734

293083

CHECK VALVE-Y ELEC PUMP DELIVERY

148

734

293093

CHECK VALVE-G/Y PTU DELIVERY

148

734

Y


Y

148

734

148

734

29-95 2995

ATA 29 A300/A310



29-96 2996

ATA 29 A300/A310

A300/A310 Yellow Main Hydraulic Power System - Description compartment doors are operated separately through the associated electromechanical electromechanical selector valves on the manifold or by means of the hand pump connected at the outlet of the selector valves. The hand pump cannot be used for repre ssurizing the brake accumulators.

GENERAL The Yellow hydraulic system allows: -

Operation of the control surfaces even with with in-flight engine failure, by means of the ram air turbine Alternate braking and parking On ground operation of the cargo compartment doors.

USERS A. Supplie d through the servo co ntrols mani fold (or throu gh wing and aft fuselage isolation valves).

The three functions above correspond to three sections of the HP manifold.

-

A. The flight co ntrols section receives press ure through the s ervo controls manifold, from engine 2 pump, the RAT and the ground connector. It can be pressurized directly through a filter by the Green/Yellow power transfer transfer unit. It supplies the flap power control unit Yellow hydraulic motor through a priority valve and includes the same components as the other HP manifolds. B. The monitoring monitoring section section is supplied supplied by the the other two sections sections through through two check valves and includes two brake Yellow power accumulators, similar to but of a larger capacity than the hydraulic system power accumulators, a pressure transmitter and a brake Yellow pressure relief valve with manual depressurization feature.

B. Supplie Supplied d through through the HP HP manifol manifold: d: -

C. The cargo compartment compartment door section is supplied by the Yellow Yellow electric pump through a filter and a check valve. The forward and aft


Two all speed aileron servo controls, L and R Two elevator servo controls, L and R One rudder servo control Six actuators on spoilers 2, 3 and 5, L and R (A300) Six actuators on spoilers 1, 4 and 6, L and R (A310) One trimmable horizontal stabilizer actuator motor One autopilot pitch actuator servo motor One autopilot yaw actuator servomotor One autopilot roll actuator servomotor One pitch artificial feel unit actuator. One yaw damper actuator servo motor.

29-97 2997

One flap power control unit motor, via a priority valve Yellow braking system alternate and parking Two forward and aft aft cargo compartment compartment door door actuators. One main deck cargo compartment (MDCC) door actuator

ATA 29 A300/A310

A310 Yellow Hydraulic Power System - Schematic NOTE: MDCC Door on Main Deck is powered on the FWD/AFT Cargo Door pressure/return line system

*MDCC Door


29-98 2998

ATA 29 A300/A310


FIN

F UN C TI ON AL DES IGN AT I ON

PAN EL

ZONE

ACCESS

ATA

DOOR

REF.

293000

RESERVOIR- HYDRAULIC, YELLOW

671

671AB

29-11-11

293002 293005

671 671

671AB 671DB

29-11-15 29-13-19

293006

FILTER-RSVR RETURN, YELLOW VALVE-DEPRESS/RELIEF, Y RSVR G R OU N D C O N N E C T OR - D E L I V E R Y , Y

671

671DB

29-13-21

293008 293010 293031

G R O U N D C O N N E C T O R - S U C T I ON, Y MANI F O L D - S E R V O C O N T R O L S , Y PUMP-YELLOW, E N G 2

671 148 445

671DB 734 445AL

29-13-23 29-13-34 29-11-32

293031 293042 293049

PUMP-YELLOW, E N G 2 VALVE- N ON RET U RN FILT ER-Y PUMP DELIVERY, ENG 2

462 420 148

462AR

29-11-32

734

29-11-42

293060 293063 293070 293072

MANI F O L D - H P , Y E L L O W RELIEF VALVE-YELLOW PUMP DELIVERY AC CU - YEL LOW PWR PRESS GAGE-YELLOW ACCU

148 148 148 148

734 734 734 734

29-12-12 29-13-55 29-11-56

2GD 3 1 WW 6GD

VALVE-YELLOW, PUMP FIRE, ENG 2 PR E SS S WI T C H - H P M A N I F O L D , Y PR E SS S WI T C H - Y P U M P , E N G 2

675 148 445

675FB 734 445AL

29-11-33

6GD

PR E SS S WI T C H - Y P U M P , E N G 2 F ILT ERS- EN G PUMP CASE D RA RA I N VAL VE- MANUAL DEPRESS, Y RSVR

483 462

483AL 462AR

29-13-62 29-11-36

671

671DB

293087


29-99 2999

29-13-62

ATA 29 A300/A310



29-100 29100

ATA 29 A300/A310

YELLOW YELLOW AUXILIARY HYDRAULIC SYSTEM NUMBER 3


29-101 29101

ATA 29 A300/A310

Yellow Yell ow Auxilia Auxiliary ry Hydrau Hydraulic lic Power Power Syst System em (Power (Power Trans Transfer fer Unit) Unit) DESCRIPTION The Green/Yellow power transfer unit is identical to the Green/Blue power transfer unit. The description of its purpose and operation is identical to that of the Green/Blue power transfer unit (read Yellow instead of Blue).

PERFORMANCE Identical to that of the Green/Blue power transfer unit. LOCATION - INSTALLATION The Green/Yellow power transfer unit is installed in the hydraulic bay at FR53 on the right side of the fuselage.


29-102 29102

ATA 29 A300/A310

Yellow Yell ow Auxilia Auxiliary ry Power Power Syste System m - Power Power Trans Transfer fer Unit Unit (PTU) (PTU)


29-103 29103

ATA 29 A300/A310

A300/A310 Yellow Auxiliary Hydraulic Power - Electric Pump DESCRIPTION The Yellow system electric pump provides pressure for operation of the forward, aft and main deck cargo compartment doors and for the two brake Yellow power accumulators (on the ground and in flight). Fluid is supplied to it from the Yellow system reservoir. A 3 to 15-micron absolute filter is installed on the delivery line. LOCATION - INSTALLATION Rigidly attached to a mount integral with the structure of FR54 in the hydraulics compartment. The delivery, suction and case drain lines connected to the pump are rigid pipes.

CONTROL The electric pump may be started by: A. Placing the con trol valve man ual selecto r lever locate d near each cargo compartment door, in OPEN or CLOSE position. B. Pressing the the PARKING PARKING BRAKE BRAKE ACCU ACCU PRESS PRESS pushbutton pushbutton switch switch located next to the PARKING BRAKE control handle on the center pedestal in the flight compartment. This pressurizes the brake Yellow power accumulators. HAND PUMP In the event of an electric pump failure, a hand pump is used to operate the cargo compartment doors. This is a double-acting pump located in the MLG wheel well at FR54, RH side. Electric Pump Circuit Breaker (CB) -

-


29-104 29104

CB Panel 10VU (GEN1/GEN 2) Avionics Bay/Row Bay/Row B5 Yellow Electric Pump (A310) FedEx - Ratings depend upon FedEx A310 registration number/ effectivity codes: - 20 Amp - 30 Amp - 35 Amp - FIN: 23 GX Yellow Electric Pump (A300) FedEx - Rating: 20 Amp - FIN: 23 GX

ATA 29 A300/A310

A300/A310 Yellow System Electric Hydraulic Pump Control


29-105 29105

ATA 29 A300/A310

Yellow Yell ow Syste System m - ABEX ABEX Elec Electric tric Hydr Hydraulic aulic Pump The YELLOW system is provided with a self-regulating hydraulic pump, which is driven by an AC motor. The nominal output flow of 1.6 gal/min (6 ltr/min) is delivered at 2850 PSI. The pump is controlled by the PARKING BRAKE ACCU PRESS pushbutton on the center pedestal, near the PARKING BRAKE control handle, and by the OPEN/CLOSE selectors located adjacent to the main cargo compartment doors. Pressurization of the complete YELLOW system by the electric pump is prevented by manifold check valves. When the PARKING BRAKE ACCU PRESS pushbutton is operated or when an OPEN/CLOSE cargo door selection is made, the parking /ALTN--OFF /ALTN--OFF brakes accumulators and the main cargo compartment door operation circuit only are pressurized.

These are large power consumers and pressure is delivered to them through a priority valve which isolates them in the event of low pressure conditions. 

These are isolated by the associated selector valves when not operating (Green Systems only). In addition to the priority valve, they include:  

HP MANIFOLDS 

The HP manifolds receive pressure:  

Directly from the servo controls manifold From the electric pumps or power transfer units, through a filter and a check valve.

  

 

Directly to the servo controls manifold To the motors and selector valves of the landing gear, fl aps and slats To the standby generator manifold installed upstream of the flap motor.

A pressure transmitter Two pressure switches set to operate at 100 ± 5 bars (1450 ± 72.5 PSI) when pressure is decreasing A pump delive ry relief val ve with manual depressuriza tion feature. SYSTEMS SUPPLIED THROUGH THE YELLOW HP MANIFOLD

They distribute pressure: 

To the power transfer unit motors and to the normal braking system.

One flap power control unit motor, via a priority valve Yellow braking system ALT and Parking Two forward, aft and main deck cargo compartment door actuators.

Basic Configuration Pump  

FIN 25 GX (293082) Pump-Instl-HYD Yellow – Z148

Abex Pump – Model MPN 40109 CPN 2910438 PUMP-ELECTRICAL (ABEX) (VD0079) ADDED BY EA 6-2924- 47928 NOTE: PUMP MUST BE USED WITH ADAPTOR KIT P/N 60839 REF AMM 29-24-11


29-106 29106

A310 A CFT 416430 442443 445454

ATA 29 A300/A310

A300/Some A310 Yellow Hydraulic System - ABEX Electric Pump

POP OUT ∆ ∆P INDICATOR

RH MLG WHEEL WELL FR 54 AREA BASIC CONFIGURATION ABEX PUMP


29-107 29107

ATA 29 A300/A310

Yellow Yell ow Syste System m - VICKE VICKERS RS Electr Electric ic Hydra Hydraulic ulic Pump The YELLOW system is provided with a self-regulating self-regulating hydraulic pump, which is driven by an AC motor. The nominal output flow of 1.6 gal/min (6 ltr/min) is delivered at 2850 PSI. The pump is controlled by the PARKING BRAKE ACCU PRESS pushbutton on the center pedestal, near the PARKING BRAKE control handle, and by the OPEN/CLOSE selectors located adjacent to the main cargo compartment doors. Pressurization of the complete YELLOW system by the electric pump is prevented by manifold check valves. When the PARKING BRAKE ACCU PRESS pushbutton is operated or when an OPEN/CLOSE cargo door selection is made, the parking /ALTN--OFF /ALTN--OFF brakes accumulators accumulators and the main cargo compartment door operation circuit only are pressurized. HP MANIFOLDS

These are large power consumers and pressure is delivered to them through a priority valve which isolates them in the event of low pressure conditions. 

These are isolated by the associated selector valves when not operating (Green Systems only). In addition to the priority valve, they include:  



The HP manifolds receive pressure:  

Directly from the servo controls manifold From the electric pumps or power transfer units, through a filter and a check valve.

  

 

Directly to the servo controls manifold To the motors and selector valves of the landing gear, fl aps and slats To the standby generator manifold installed upstream of the flap motor.

A pressure transmi tter Two pressure switches set to operate at 100 ± 5 bars (1450 ± 72.5 PSI) when pressure is decreasing A pump deliv ery relief va lve with manual depressurizati on feature. SYSTEMS SUPPLIED THROUGH THE YELLOW HP MANIFOLD

They distribute pressure: 

To the power transfer unit motors and to the normal braking system.

One flap power control unit motor, via a priority valve Yellow braking system ALT and Parking Two forward, aft and main deck cargo compartment door actuators.

Basic Configuration Pump  

FIN 25 GX (293082) Pump-Instl-HYD Pump-Instl-HYD Yellow – Z148

Vickers Pump – Model MPN 848847 CPN 2911231 PUMP-ELECTRICAL (VICKERS) (V62983) SEE CMM 29-10-45 25GX 293082


29-108 29108

A310 ACFT 416430 442443 445454

ATA 29 A300/A310

Some A310 Yellow Hydraulic System - VICKERS Electric Pump

POP OUT ∆ ∆P INDICATOR SECONDARY CONFIGURATION VICKERS PUMP

RH MLG WHEEL WELL FR 54 AREA


29-109 29109

ATA 29 A300/A310

A300/A310 Yellow Auxiliary Hydraulic Hydraulic Power System - Electric Pump Control Description The Yellow system electric pump provides pressure for operation of the forward and aft cargo compartment doors and for the two brake Yellow power accumulators (on the ground and in flight). Fluid is supplied to it from the Yellow system reservoir. A 3 to 15-micron absolute filter is installed on the delivery line. Component Location - - - - - - - - - - - - -- - - - - - - - - - - - - -- - - - - - - - - - - - - -- - - - - - - - - - - - - -- - - - - - - - - - - - - FIN FUNCTIONAL DESIGNATION PANEL ZONE ACCESS ATA DOOR REF. - - - - - - - - - - - - -- - - - - - - - - - - - - -- - - - - - - - - - - - - -- - - - - - - - - - - - - -- - - - - - - - - - - - - 293084 FILTER-Y ELEC PUMP DELIVERY 148 734 29-24-12 25GX ELEC PUMP-YELLOW 148 734 29-24-11 Performance •

Hydraulic Pump - Constant pressure, variable displacement type - Nominal pressure: 206 bars/3028 PSI at zero delivery 196 bars/2881 PSI at nominal delivery - N o m i n a l d e l i v e r y : 6 l / m n /2 / 2 2. 2 . 7 G PM PM

•

Electric Motor - Continuous duty operation - Voltage: 3-phase, 400 Hz, 115/200VAC - Air cooled.

Location - Installation Rigidly attached to a mount integral with the structure of FR54 in the hydraulics compartment. The delivery, suction and case drain lines connected to the pump are rigid pipes. Control The electric pump may be started up by: •

Placing the control valve manual selector lever locate d near each cargo c o m p a r t m e n t d o o r , i n OP OP E N or or C L OS OS E p o si si t i o n .

•

Pressing the PARKING BRAKE ACCU PRESS pushbutton switch located next to the P A R K I N G BR B R A K E c o n t ro r o l h a n d l e o n t h e c e n t e r p e d e st st a l i n t h e f l i g h t c o m p a r t ment. This pressurizes the brake Yellow power accumulators.


29-110 29110

ATA 29 A300/A310

A300/A310 Yellow Auxiliary Hydraulic Hydraulic Power System - Electric Pump Control


29-111 29111

ATA 29 A300/A310

A300/A310 Yellow Auxiliary Hydraulic System - Hand Pump FIN 3085

Hand Pump In the event of an electric pump failure, a hand pump is used to operate the cargo compartment doors. This i s a double-acting pump located in thehydraulics compartment, at FR54, RH side. Delivery for one complete piston


29-112 29112

ATA 29 A300/A310

A300/A310 Hydraulic System - Fire Shutoff Valves (SOV) •

FIRE VALVES: TWO GREEN - ONE BLUE - ONE YELLOW

• •

• • •

The fire fire valves isolate engine pump pump suction suction in the event event of engine fire They are located in the wing, near the firewall They each consist of a plug valve actuated by a 115 V, 400 Hz quarter-turn electric actuator. Electric actuator removal is possible

•

without disturbing the hydraulic system; however, the correspondi ng reservoir should be depressurized beforehand The valve opens or closes in 1.8 1.8 sec. maximum They are are controlled controlled from the flight compartment by two ENG FIRE handles on the overhead panel. Four annunciators annunciators on the lateral panel indicate the position of the valves The Yellow system fire valve is also controlled in the closing direction when low level, 1.32 gal (5 ltr) is sensed in the Yellow system reservoir.

CAUTION: Fire Valve Motors must not operate continuously for more

than 30 seconds. Allow fire valve motors to cool after six successive sequences.


29-113 29113

ATA 29 A300/A310

A300/A310 Hydraulic System - Fire Shutoff Valve


29-114 29114

ATA 29 A300/A310

A300/A310 Green Hydraulic Pump Fire Valves - Control Schematic


29-115 29115

ATA 29 A300/A310

A300/A310 Yellow Hydraulic Pump Fire Valve - Control Schematic and Component Location


29-116 29116

ATA 29 A300/A310

ENGINE DRIVEN PUMPS (EDPs) GREEN - BLUE - YELLOW (G-B-Y) SYSTEMS


29-117 29117

ATA 29 A300/A310

A300 Hydraulic System - Engine Drive Pump (EDP) - Description - CF6-80C2A5F Engine When the engines are running, these pumps alone

to

pressurize

the

hydraulic

are normally used

systems.

Ÿ

Case drain leakage rate is approximately 2.5 GPM

for

a pump rotation speed of 3750 rpm. •

Location and Drive The pumps are mounted on and driven by the engine

•

accessory gearbox es, which in turn are driven by the HP compressor:

P u mp m p D e ac ac t i v a t i o n E ac a c h p um um p i s

deac tiva ted

by

re leasi ng

the

as soci ated

One Green system pump and the Blue system pump are

pushbutton switch on the overhead panel. This activates the pump depressurizing valve solenoid. A blocking valve

mounted under engine 1.

then isolates delivery while the yoke

Ÿ

is repositioned

perpendicular to the drive shaft to reduce delivery to almost zero. The pump is lubricated by internal leakage.

One Green system pump and the Yellow system pump are mounted under engine 2.

Ÿ

Rot a t i o n a l m o v e m e n t i s t r a n s m i t t e d t o t h e p u m p b y splined shear-type drive shaft. A drain manifold recovers

any

oil

leakage

from

the

accessory

a

•

gearbox

seal

or

Connections

The pumps are connected to the engine pylon by high temperature resistant flexible hoses and stainless steel

gearbox

end and any hydraulic fluid leakage from the pum p end, allowing the origin of the leakage to be determined and the accessory seal to be changed.

Hydraulic

pipes, allowing quick removal of the pumps. Ÿ

pump

Suction Suction hoses ar e equipped at each end with a selfsealing coupling. N O TE :

•

Description The

four

and

pumps

Leading are

of

Particulars

the

variable

displacement

are identical. They include nine pistons to rotational motion is imparted by a cylinder

type

which block,

and

fluid in the suction lines. Pump operating t i m e b e f o r e d e g r a da t i o n i s t h e n l i m i t ed t o 5 mi n u t e s .

and

reciprocating motion by a variable-angle yoke. Varying the angle of the yoke allows nominal pressure to be m ai n t a i n e d

within

a

wide

range

of

delivery

Ÿ

volumes,

spring

loaded

in

one

direction

and

switch

between

is set to operate at 125 pressure is decreasing. Ÿ

1.3 US

the bars

two.

The

(1810

pressure

ps i)

switc h

when

Case drain

g al / m n - 0 ) a t r a t ed d e l i v e r y s p e e d o f 3 5 4 0 r p m .

The case drain hose recovers pump internal leakage. It includes a 15 ì (0.0006 in.) absolute filter in

That is, 102.92% N2 for

the

Ÿ

Ÿ

pressure

outlet

pressure actuated in the other. Nomi n a l f l u i d : 1 3 6 + 5 l / m n - 0 ( 3 5 . 9 3 +

D el i v e r y A s p h e r i c a l p u l s a t i o n d a m p e n e r i s m o u n t e d a t t h e p u m p end, a check valve on the pylon structure, and a

proportional to engine speed. Servo pressure for changing the yoke angle is delivered by a compensator valve,

I n t he e v e nt o f a n e ng i ne f i r e , f i r e v a lv e s located in the wing shut off the supply of

Nomi n a l p r e s s u r e :

engine (GE)

206 + 3

- 0 bar s (3000 ps i) at

zero

(2842.7

psi)

and

a

check

valve

on

the

pylon

structure.

Hydraulic Engine Driven Pump - approximate weight: 28 pounds (13 KGS).

delivery. 196 bars

middle

at nominal

delivery.


29-118 29118

ATA 29 A300/A310

A300 Hydraulic Tubes and Hoses (From Pumps and Filters)

CF6-80C2A5F ENGINE

CASE DRAIN FILTERS

GREEN ENG 1/ENG 2 BLUE/ENG 1 YELLOW/ENG YELLOW/ENG 2

ENG 1/ENG 2

BLUE/YELLOW ENG 1/ENG 2


29-119 29119

ATA 29 A300/A310

A310 Hydraulic System - Engine Driven Pump - Description - CF6-80A3 Engine When the engines are running, these pumps alone

to

pres-

surize

the

hydraulic

are normally used

Ÿ

systems.

NOTE: minimum engine idling speed: -

•

Location and Drive

f o r e n g i n e ( G E ): N 2 = 5 5 26 r pm b e n c e a p u{ p rotation speed of 1934 rpm and fluid d el el i v e r y

The pumps are mounted on and driven by the engine accessory gearbox es, which in turn are driven by the HP compressor:

Ÿ

of

7 6 . 5 l / m n ( 2 0. 5 8 U S G a l )

Case drain leakage rate is approximately 2.5 GPM a pump rotation speed of 3750 rpm.

for

One Green system pump and the Blue system pump are mounted under engine 1.

•

E ac a c h p um um p i s d e a c t i v a t e d b y r e l e a s i n g t h e a s s o c i a t e d pushbutton switch on the overhead panel. This activates

One Green system pump and the Yellow system pump are mounted under engine 2. R ot a t i o n a l m o v e m e n t i s t r a n s m i t t e d splined shear-type drive shaft.

P u mp m p D e ac ac t i v a t i o n

the pump depressurizing valve solenoid. A blocking valve to

the

pump

by

a

then isolates delivery while the yoke is repositioned perpendicular to the drive shaft to reduce delivery to

A drain manifold

recovers any oil leakage from the accessory gearbox end and any hydraulic fluid leakage from the pump end, allowing the origin of the leakage to be determined and the accessory gearbox seal or pump seal to be changed.

almost zero. The pump is •

lubricated by internal leakage.

Hydraulic Connections The pumps are connected to the engine pylon by high temperature resistant flexible hoses and stainless steel

•

Description

and

Leading

Particulars

The four pumps are of the variable displacement type are identical. They include nine pistons to which rotational

motion

is

imparted

by

a

cylinder

block,

pipes, allowing quick removal of the pumps. Suction

and

Ÿ

Suction hoses ar e equipped at each end with a self-

and

sealing coupling. N O TE : In the event

reciprocating motion by a variable-angle yoke. Varying the angle of the yoke allows nominal pressure to be m ai n t a i n e d

within

a

wide

range

of

delivery

located

volumes,

spring

loaded

in

one

direction

and

Ÿ

Ÿ

1.3 US

Ÿ

Ÿ

That is, 102.92% N2 for

engine fire, shut

off

the

fire

valves

supply

of

D el i v e r y A s p h e r i c a l p u l s a t i o n d a m p e n e r i s m o u n t e d a t t h e p u m p end,

g al / m n ) - 0 a t r a t ed d e l i v e r y s p e e d o f 3 5 4 0 r p m . Ÿ

an

wing

mi n u t e s .

outlet

pressure actuated in the other. Nomi n a l f l u i d : 1 3 6 + 5 l / m n - 0 ( 3 5 . 9 3 +

of

the

fluid in the suction lines. Pump operating t i m e b e f o r e d e g r ad a t i o n i s t h e n l i m i te d t o 5

proportional to engine speed. Servo pressure for changing the yoke angle is delivered by a compensator valve,

in

a

check

valve

at

the

pylon

end,

and

a

pressure

s wi wi t c h b e t w e e n t h e t w o . T h e p r e s s u r e s w i t c h i s s e t t o operate at 125 bars (1810 psi) when pressure is

engine (GE)

Nomi n a l p r e s s u r e : 2 0 6 + 3 - 0 b a r s ( 3 0 0 0 p s i ) a t z e r o d el el i v e r y . 1 9 6 b a r s ( 2 8 4 2 . 7 p s i ) a t n o m i n a l d e l i v e r y .

decreasing.

indicates pump rotation speeds according to the

Case drain The case drain hose recovers

flight phases, these corresponding to a typical 90 mn

It includes a 15 &mgr;

f l i g h t .

in the middle and a check valve at the py lon end.


Ÿ

29-120 29120

pump internal leakage.

(0.0006 in.) absolute filter

ATA 29 A300/A310

A310 Hydraulic System - Engine Driven Pumps - CF6-80A3 Engine

D F W


29-121 29121

ATA 29 A300/A310

A310 Hydraulic System - Engine Driven Pump - Description - PW JT9D-7R4 Engine When the engines are running, these pumps alone •

to

pres-

surize

the

hydraulic

are normally used

N O TE :

-

f o r e n g i n e ( P W) W) : N 2 = 4 0 1 4 r p m , h e n c e a pump rotation speed of 2003 rpm and fluid d el el i v e r y o f 7 9 . 2 l / m n ( 2 0 . 91 U S G a l )

Location and Drive The pumps are mounted on and driven by

the engine

Ÿ

accessory gearbox es, which in turn are driven by the HP compressor: One Green system pump and the Blue system pump are mounted under engine 1. One Green system pump

•

Case drain leakage rate is approximately 2.5 GPM a pump rotation speed of 3750 rpm.

for

Pump Deactivation

and the Yellow system pump are mounted under engine 2. Rot a t i o n a l m o v e m e n t i s t r a n s m i t t e d t o t h e p u m p b y a

Each pump is deactivated by releasing the assoc iated pushbutton switch on the overhead panel. This activates

splined shear-type drive shaft. A drain manifold recovers any oil leakage from the accessory gearbox

the pump depressurizing valve solenoid. A blocking valve end

then isolates delivery while the yoke is repositioned perpendicular to the drive shaft to reduce delivery to

and any hydraulic fluid leakage from the pump end, allowing the origin of the leakage to be determined and the accessory gearbox seal or pump seal to be changed.

almost zero. The pump is lubricated by internal leakage. •

•

mi n i m u m e n g i n e i d l i n g s p e e d :

systems.

Description and Leading Particulars The four pumps are of the variable displacement type and

temperature resistant flexibl e hoses and stainless pipes, allowing quick removal of the pumps.

rotational motion is imparted by a cylinder block, and reciprocating motion by a variable-angle yoke. Varying angle

of

the

yoke

allows

nominal

press ure

to

Ÿ

Suction

be

N O TE :

Ÿ

Ÿ Ÿ

in

the

Ÿ

3 - 0 bar s (3000 ps i) at ze ro

engine

fire, fire

valves

switch

between

the

two.

The

pressure

switc h

is set to operate at 125 bars (1810 psi) when pressure is decreasing.

at nominal

delivery. Ÿ

of an

mi n u t e s . D el i v e r y

pressure

delivery. 196 bars (2842.7 psi)

event

A s p h e r i c a l p u l s a t i o n d a m p e n e r i s m o u n t e d a t t h e p u m p end, a check valve at the pylon str ucture, and a

9 0 . 8 7 % N 2 f o r en en g i n e ( P W )

Nomi n a l p r e s s u r e : 2 0 6 +

the

t i m e b e f o r e d e g r ad a t i o n i s t h e n l i m i te d t o 5

other.

Nomi n a l f l u i d : 1 3 6 + 5 l / m n - 0 ( 3 5 . 9 3 + 1 . 3 U S g al / m n ) - 0 a t r a t e d d el i v e r y s p e e d o f 3 5 4 0 r p m . tha t i s,

In

located in the wing shut off the supply of fluid in the suction lines. Pump operating

changing the yoke angle is delivered by a compensator valve, spring loaded in one direction and outlet actuated

steel

Suction hoses ar e equipped at each end with a selfsealing coupling.

m ai n t a i n e d w i t h i n a w i d e r a n g e o f d e l i v e r y v o l u m e s , proportional to engine speed. Servo pressure for

pressure

Connections

The pumps are connected to the engine pyl on by high

are identical. They include nine pistons to which

the

Hydraulic

Ÿ

Case drain

Figure indicates pump rotation speeds according to the flight phases, these corresponding to a typical

The case drain hose recovers pump internal leakage. It includes a 15 &mgr; (0.0006 in.) absolute filter in the

90

mi d d l e a n d a

mn

flight.


29-122 29122

check valve

at the pylon

structure.

ATA 29 A300/A310

A310 Hydraulic System - Engine Driven Pumps - PW JT9D-7R4 Engine

D F W


29-123 29123

ATA 29 A300/A310

A300/Some A310s - Hydraulic Power System - Pump Connections (Typical)

NOTE: Some A310s - HYD EDPs are mounted on rear face/aft RH side of the Accessory Gearbox PW JT9D-7R4

NOTE: A300/Some A310s - HYD EDPs are mounted on front face of the Accessory Gear Box - GE CF6-80A3 and CF6-80C2AF


29-124 29124

ATA 29 A300/A310

A300/Some A310s - Engine Hydraulic Pumps Location - GE CF6-80A3/CF6-80C2A5F

A310

A300

AFT LOOKING FORWARD

FWD

FWD FWD


29-125 29125

ATA 29 A300/A310

Some A310 - Engine Hydraulic Pumps Location - PW JT9D-7R4 Engine

AFT LOOKING FORWARD

ENG 1/2 OUTBOARD HYD. PUMPS GREEN

ENG 1 - BLUE ENG 2 - YELLOW


29-126 29126

ATA 29 A300/A310

A300/Some A310 Engine Driven Pumps - Hydraulic Pressure Switches - Component Locations

GE CF6-80A3/A310

Two Versions of Installation

GE CF6-80C2A5F/A300 PW JT9D-7R4/A310


29-127 29127

ATA 29 A300/A310

A300/A310 Hydraulic Hydraulic Tubes and Hoses (To Pylons) - Typical Connections The pumps are connected to the engine pylon by high temperature resistant flexible hoses and stainless steel pipes, allowing quick removal of the pumps. SUCTION

DELIVERY A spherical pu lsation damp ener is mounted at the pump end, a c heck valve on the pylon structure and a pressure switch between the two. The pressure switch is set to operate at 125 bars (1810 PSI) when pressure is decreasing.

Suction hoses are equipped at each end with a self-sealing coupling. CASE DRAIN NOTE: In the event of an engine fire, fire valves located in the wing shut

off the supply of fluid in the suction lines. Pump operating time before degradation is then limited to 5 minutes.


The case drain hose recovers pump internal leakage. It includes a 15 micron (0.0006 in.) absolute filter in the middle and a check valve on the pylon structure.

29-128 29128

ATA 29 A300/A310

A300/A310 Hydraulic Tubes and Hoses (To Pylon) - Typical Installation

NOTE: GE CF6-80A3 and PW JT9D-7R4 Typically the same modules but located at different engine assembly areas. HYDRAULIC CASE DRAIN FILTER MODULES


29-129 29129

ATA 29 A300/A310



29-130 29130

ATA 29 A300/A310

G-B-Y HYDRAULIC SYSTEM ACCESSORIES


29-131 29131

ATA 29 A300/A310

A300/Some A310 Engine Driven Pumps - Delivery Relief Valve - Installation - (Typical)

FIN Label


29-132 29132

ATA 29 A300/A310



29-133 29133

ATA 29 A300/A310

A300 Hydraulic Systems - Location of Filters/FIN/Access Doors -------------------------- -------------------------- -------------------------ITEM NAME PANEL ZONE ACCESS DOOR -------------------------- -------------------------- -------------------------291002 Filter - Reservoir Return, 220 l/ 148 min (58 US gal/min.) 291048 Filter - HP, 140 l/min (37 US 147 291049

US gal/min.) Filter - HP, 140 gal/min.)

l/min (37

US

147

291079 291132

Filter - HP, 70 l/min (18.5 US gal/min.) Filter - HP, Reservoir Filling, 6 min (1.5 US gal/min.)

292002 292048

Filter - Reservoir Return, 220 min (58 US gal/min.) Filter - HP, 140 l/min (37 US

292091

gal/min.) Filter - HP, 90 l/min (23.8 US gal/min.)

293002

147 l/

l/

147 571

571AB

147 147

293049

Filter - Reservoir Return, 220 min (58 US gal/min) Filter - HP, 140 l/min (37 US

293084 293090

gal/mi Filter gal/mi Filter

HP, 90 l/min (23.8 US

148

321298

gal/min.) Filter - HP, 70 l/min (18.5 US gal/min.)

147

147SZ

- Case Drain, Eng. 1 Pump - Case Drain, Eng. 2 Pump

452

452AR

452

462AR

Filter - Case Drain, Eng. 1 Blue Pump Filter - Case Drain, Eng. 2

452

452AR

452

462AR

Filter Green Filter Green

n. n. -

l/

671

671AB

147

) HP, 6

l/min (1.5 US

148

)

Yellow Pump Filter - Ram

Air

Turbine

NOTE: HP and case drain filters must always be removed in the case of inadvertent or a c c i d e n t a l c l o s u re o f a f i r e s h u t o f f v a l v e i n f l i g h t ( m o r e t h a n 5 m i n . ) o r i n the event of an anomaly occurring in engine pump opera tion.


29-134 29134

ATA 29 A300/A310

A300 Hydraulic Systems - Location of Filters and FIN - Typical Installation


29-135 29135

ATA 29 A300/A310

A300/A310 Hydraulic System Filter Bowls - Maintenance Practices Information Subject: AIRBUS HYDRAULIC SYSTEM FILTER BOWLS

Title: Aircraft Maintenance Practices- Hydraulic System Filter Bowl Maintenance Practices The purpose of document is to inform all FedEx Aircraft Maintenance Personnel on the Removal and Installation of Hydraulic System Filter Bowls, 0Rings (Packings) and Torquing of Filter Bowls on the Airbus Fleet aircraft. Improper procedures affect Airbus aircraft reliability and costs FedEx money in Delays and Cancellations.

-

HISTORY: The Airbus Fleet previously experienced various problems with installed filter bowls and fi lter bowl 0-Rings (Packings). The main leakage areas are the Left and Right Main Gear Wheel Wells (Hydraulic Bay). One of the main problem(s) that we are experiencing during the last several months are the filter bowls and filter bowl housing assemblies leaking and damaged from improper installation techniques. The majority of the Green I Blue I Yellow Systems filter housings and bowls are located on the High Pressure Manifolds, Servo Control Manifolds and Return Manifolds which are located in t he Hydraulic Bay.

-

-

The filter bowls and filter bowl housings have been cracked due to improper torquing of the filter bowl after servicing with a new filter and O-Rings. Upon reinstallation of the filter bowl into the f ilter housing assembly, the bowl is over tightened tightened by hand or over torqued beyond prescribed Aircraft Maintenance Manual (AMM) limits in the applicable ATA Chapter. Due to the over torqued condition, 0-Ring damage, flight conditions, ground static conditions, fuselage wind vibrations during l anding gear retraction and extension cycles, climatic conditions and other factors involved results in a hydraulic leak. The hydraulic leak develops and is found during ground checks by the aircraft maintenance or flight crews. If both crew(s) do not notice t he hydraulic leak in the leak area before flight, the aircraft will suffer a ground delay or flight cancellation until the leak source is corrected and pressure checked per AMM procedures.. WHY HYDRAULIC LEAKS: The hydraulic leaks that are affecting Airbus Fleet reliability are due to some of t he following condition(s):

-

Improper filter bowl bowl installation after filter replacement replacement (Possibly cuts on new 0-Ring due to filter bowl reinstallation into filt er housing assembly) Lack of AMM prescribed lubricant for new 0-Ring I Packing during reassembly of filter Loose fittings and/or and/or damaged fittings (cracked (cracked and scored flare areas) areas) on filter housing assembly (Improper visual check of component attachments during disassembly) Loose filter housing housing mounting mounting bolts (Failure to check check bolts for for security) security) Worn mating surface on filter bowls and housing assemblies (Failure to check on disassembly procedure) Worn threads on the filter bowl and/or and/or housing assembly (Failure to check on disassembly procedure I Visual Check) Cracked filter bowls and filter housing assemblies (Due to over over forgoing forgoing of filter bowls) New 0Rings (Packings) damaged during build-up of the filter bowl (Improper procedures and lack of proper tooling for installing new 0-Rings) (See AMM Chapter 20-23-16) Filter bowl 0-Ring missing, reused 0-Ring, damaged 0-Ring (Cuts, tears, worn) (Due to improper procedures during previous filter element servicing) Insufficient torque on filter bowls and housing hardware during installation procedures (Failure to use torque wrench, wrong torque value or improper forgoing procedures) Improper leak check of hydraulic hydraulic filter bowl bowl and and housing housing assembly during system pressurized conditions (Good visual checks are worth the time) Lack of pressurized pressurized leak check upon completion of new new filter element servicing

PROACTIVE CORRECTIVE ACTIONS: Apply sound maintenance procedures per AMM during disassembly and reassembly reassembly of the filter element during filter servicing maintenance. If all of the above conditions) in "Why Hydraulic Leaks" paragraph were prevented during new filter element servicing or filter housing maintenance, there should be no hydraulic leaks, except for material I component defects. Finally, if you have followed the AMM procedures, our hydraulic leaks can be "cured by you". Most of all you have increased the FedEx Airbus Fleet Reliability level for our valued customers. You have also saved money for FedEx by preventing Delays and/or Cancellations of scheduled revenue flights by applying the P-S-P Philosophy.


29-136 29136

ATA 29 A300/A310

A300/A310 High Pressure (HP) and Servo Controls Hydraulic Manifold and Filters Installation/Location

Servo Control Manifolds


HP Manifolds

29-137 29137

ATA 29 A300/A310

A300/A310 Hydraulic System Filters - Return Line Filter The Return Line Filters are located near each reservoir on a Return Manifold. One on each line comprising a 3 ì (0.0001 in.) absolute filter element (disposable type only), a clogging indicator (set to operate at 3 ± 0.5 bars) (43.8 ± 7.3 psi), bypas s system (setting: 5 ± 0.5 bars ) (73 ± 7.3 psi), and a dash-pot on clogging indicator supply line. The filters also have an automatic shut off mechanism to facilitate removal. Clogging Indicator When the filter is clogged, the increase in differential pressure causes the protrusion of a red colored button, visible through a transparent frame. The filter element must be replaced as soon as possible. The clogging indicator is reset by simply removing the transparent frame and pressing the indicator button. In low temperature conditions, clogging indicator operation is inhibited (thermostatic (thermostatic locking at 0° ± 2°C (32.9 ± 3.6°F) with unlocking at 30°C (86°F). Return Manifolds The return manifolds receive return fluid separately from the user services and case drains through check valves (except in the case of the servo controls to allow interconnection of the servo control chambers in the event of loss of pressure in the associated system). Fluid is returned to the reservoir through the return filter, located near the reservoir. The return manifolds are located near the HP manifolds (only the Yellow system manifolds are located away from the reservoir).


29-138 29138

ATA 29 A300/A310

A300/A310 Hydraulic System Filters - Return Line Filter Locations

Blue System shown LH wing root area Yellow System - Identical RH wing root area

FIN 2002 - Filter/Blue 3002 - Filter/Yellow

Green System shown Hydraulic Bay

1

2

3

4

5


29-139 29139

ATA 29 A300/A310

A300/A310 Hydraulic Rudder Servo Control - Integral Protective Filters General Description The two filters serve two purposes: The Servo Control Units (Actuators) for the All Speed Ailerons (ASA), Elevators and Rudder Rudder have two integral protective filters installed in the actuator body unit adjacent to the pressure and return port areas. Also, other hydraulic servo valves may have this feature. The two filters are installed in the pressure inlet and return outlet ports of the actuator body units. These fine wire mesh filters filter out hydraulic fluid foreign matter prior to entering the servo control module. All hydraulic fluid leaving the control control module, piston ram area, and internal lines/passages is filtered by the second filter in the return (outlet) area. The tow internal filters are not line replaceable units. If one or both of the filters have internal blockage, the complete servo control unit must be replaced.


•

Filter all fluid entering the servo control module and actuator body areas. The controls module’s delicate and precision machined areas require the highest degree of internal filtration to prevent internal jamming and/or passage way blockage.

•

Filter all fluid leaving or exiting the servo servo control module and actuator body areas areas.. During tear down for fault analysis and/or component overhaul purposes, this will provide positive identification of internal failure or malfunctioning of the servo control unit internal functions.

Additional troubleshooting feature is extreme heating at either or both of the two internal filter locations can possibly identify blockage of the filter. This is identified by excessive heat or loud audible hissing sound.

29-140 29140

ATA 29 A300/A310

A300/A310 Hydraulic Rudder Servo Control - Integral Protective Filters Integral Protective Filters


29-141 29141

ATA 29 A300/A310

A300/A310 Hydraulic System - Filter Clogging Indicator •

•

Checks The removal/installation procedure for each filter element is described in the relevant ATA section (Ref. P. Block 301 - Servicing). Check of clogging indicators - indicator in = filter in good condition - indicator protruding = filter clogged.

The clogging indicator is reset by simply removing the transparent cap and pressing the indicator button. In low temperature conditions, clogging indicator operation is inhibited (thermostatic locking at 32.9 ± 3.6°F (0° ± 2°C) with unlocking at 86°F (30°C).

If an indicator is protruding (color red or blue according to the type of filter) it is necessary to check the filter element in order to determine the causes of contamination and also whether it is necessary to reclaim system fluid totally or partially. (Ref. 12-36-29, P. Block 1). When the filter is clogged, the increase in differential pressure causes the protrusion of a red colored button, visible through a transparent cap. The filter element must be replaced as soon as possible.


29-142 29142

ATA 29 A300/A310

A300/A310 Hydraulic System - Filter Clogging Indicator

A300 Blue System HP Manifold Shown


29-143 29143

ATA 29 A300/A310

A300/A310 Main Hydraulic System - Power Accumulators - Typical Installation Power

accumulators

T h e p o we w e r ac a c c u mu mu l a t o r s o n t h e H P m a n i f o l d i n e a c h s y s t e m d a m p en p u m p d el i v e r y p u l s a t i o n s a n d a n y p r e s s u r e s u r g e s , a n d compensate for pump response time in the event of high output demand. They are spherical,

bladder

type

accumulators,

c h a r g i n g p r e s s u r e o f 1 0 0 b a r s ( 1 45 0

psi) at

with

20° C

a

(68° F).

1 4 4 b a r s ( 1 6 65 p s i ) a t 6 0 ° C , 9 0 b a r s ( 1 3 0 5 p s i ) a t - 1 0 ° C ( 1 4 ° F ) a nd 8 6 b a r s ( 1 2 4 7 p s i ) a t - 2 0 ° C ( 4 ° F ) . C h a r g i n g o f each accumulator is achieved via an air charging valve, connected to a direct-reading pressure gage. The minimum volume of fluid which can be liberated between 2 0 6 b a rs ( 3 00 0 135 bars is 250

psi) (hydraulic system nominal pressure) and cm³ (15.2 cu.in.) throughou t the tem perature

range + 20° C to 110° C (+ 68° F

to + 230° F) .

T h e p ow o w e r a c c u mu mu l a t o r s a r e s e c u r e d t o structure The quick-release fastening

mounts att ached to t he system includes a

safety device protecting the accumulator against vibrations. The accumulators are installed in such a way that any accidental burst would not cause damage to more than two systems

at

a

time.


29-144 29144

ATA 29 A300/A310

A300/A310 Main Hydraulic System Accumulators - Component Location - Blue System (Typical)

BLUE SYSTEM

GREEN SYSTEM

Blue System FIN 2070 Accumulator LH MLG Wheelwell/HYD Bay


29-145 29145

ATA 29 A300/A310

A300/A310 Main Hydraulic System Green - Blue - Yellow - Accumulator Servicing HYDRAULIC SYSTEM ACCUMULATORS Serving – AMM 12-14-29/Pageblock 1 CAUTION : CHECK THAT THE LANDING GEAR GROUND SAFETIES INCLUDING WHEEL CHOCKS ARE IN POSITION. BEFORE APPLYING OR RELIEVING HYDRAULIC SYSTEM PRESSURE, MAKE CERTAIN THAT THE TRAVEL RANGES OF THE CONTROL SURFACES ARE CLEAR. BEFORE PRESSURIZING THE HYDRAULIC SYSTEMS, CHECK THAT ALL CONTROLS ARE SET TO CORRESPOND WITH THE ACTUAL POSITION OF THE SERVICES THEY OPERATE.

NOTE

1.

: T h e n i t r o g e n c h a r g i n g p r o c e d u r e s d e s c r i b e d i n t h i s t o p i c a p pl y t o t h e accumulator of each system (Green 1070, Blue 2070 and Yellow 3070, 3125, 3126).

Reason for the Job To charge accumulator

with

nitrogen to

obtain

correct

B. Charging of Accumulator (1)Unscrew protective cap (1) from nitrogen (2)Unscrew nut (2) one and a half turns.

charging

valve

(3).

(3)Connect an HP hose (8) between nitrogen cylinder (7) and 3-way valve (6) (4)Install a pressure gage (10) calibrated from 0 to 2176 psi (0 - 150 bars) on 3-way valve (6). (5)Open valves (5) and (9) as well as nitrogen cylinder, in order to vent

system. (6)Close valves

(5)

and

(9).

EFF: ALL 12-14-29-0 Page : 2 Sep 01/93

Figure 001 (Sheet 1) Nitrogen Charging of Hydraulic Accumulators

pressure.

2. Equipment and Materials - - - - - - - - - - - - - - -- - - - - - - - - - - - - - - - - -- - - - - - - - - - - - - - - - -- - - - - - - - - - - - - - - - -- - - - - - - - - - - EFF: ALL 12-14-29-0 Page : 3 Sep 01/93 ITEM DESIGNATION - - - - - - - - - - - - - - -- - - - - - - - - - - - - - - - - -- - - - - - - - - - - - - - - - -- - - - - - - - - - - - - - - - -- - - - - - - - - - -

(7)Connect HP hose (4) to charging valve (3). (8)Slowly open valve (9) and stabilize final pressure at value corresponding to ambient temperature, as shown in correction chart. Close valve (9).

A. B.

Access Platform, 2.6 m Air/Hydraulic Tool Kit

C. Referenced Procedures - 29-10-00, P. Block 301

Nitrog en

- 29-14-00, P. Block 301 - 32-12-11, P. Block 301 3.

(8

ft.

6

in.)

Cylind er

Main Hydraulic Power Depressuriza tion

Pressurization/

Hydraulic Reservoir Pressurizing System Main Gear Main Door (Ground Door(s) Opening)

(12)Close nitrogen cylinder order to vent system. C.

Procedure (Ref. Fig.

(9)Disconnect HP hose (4) from charging valve (3). (10)Tighten nut (2) on charging valve (3) ; make certain that pressure gage (10) indicates correct pressure. (11)Open valve (5) in order to vent system (pressure gage (10) indicates zero).

001)

A. Job Set-Up (1)Open right main landing gear door (Ref. 32-12-11, P. Block 301). (2)Depressurize reservoir of associated system. Depressurization equipment must remain connected to connector 1005 (2005) (3005) (Ref. 29-14-00, P. Block 301). (3)Depressurize hydraulic system (Ref. 29-10-00, P. Block 301). (4)Display warning notices on ground connectors of relevant system,

and

o n p a n e l 4 2 7 V U , p r o h i b i t i n g s y s t e m p r e s s u r i z a ti o n .


29-146 29146

(7)

and

open

valve

(9)

of

3-way

valve

(6)

in

Cl o s e - U p (1)Check charging valve (3) for leakage. (2)Install protective cap (1). (3)Pressurize reservoir of corresponding system (Ref. 29-14-00, P. Block 301). (4)Remove warning notice. (5)Remove all ground handling and maintenance equipment, standard and special tools, together with ground power and replenishing equipment, all access equipment and miscellaneous items. (6)Remove access platform. (7)Close right main landing gear door (Ref. 32-12-11, P. Block 301).

ATA 29 A300/A310

Gaseous Gaseou s Nitrogen Charging of Hydraulic Accumulators


29-147 29147

ATA 29 A300/A310

A300/A310 Alternate Brake System - Brake Accumulator Servicing Brake

Power

Accumulator

(3125

-

3126)

Charging

(h)Depressurize Yellow hydraulic reservoir (Ref. 29-14-00, P. Block 301) and prohibit its pressurization by displaying a warning notice: (Ref. 29-13-00, P. Block 301) and prohibit pressurization by displaying a warning notice:

A. Reason for the Job (1)Brake power accumulator charging.

B. Equipment and Materials --------------------- -------------------------- -------------------------- -----ITEM DESIGNATION --------------------- -------------------------- -------------------------- -----(1) Air/Hydraulic Tool Kit (2) Nitrogen Cylinder (3) Circuit Breaker Safety Clips (4) Warning Notices (5) Safety Barriers (6) Access Platform 2.60 m (8 ft. 7 in.) Referenced Procedures - 24-41-00, P. Block 301 AC External Power Control - 29-14-00, P. Block 301 Hydraulic Reservoir Pressurizing System - 32-12-11, P. Block 301 Main Gear Main Door (Ground Doors(s) Opening) - 29-13-00, P. Block 301 Yellow System - Pressurization/ Depressurization

C. P r o c e d u r e (Ref. Fig. 005) (1)Job Set-Up (a)On panel 4VU - make certain that landing gear control lever is in DOWN po si tion and prohibit its operation by displaying a warning notice. (b)Between First Officer's and Third Occupant's seats - make certain that Landing gear Free Fall extension control is in normal position. (c)Open safety and tag the following circuit breakers: -------------------------- ----------------------- -------------------------- --PANEL SERVICE IDENT. LOCATION -------------------------- ----------------------- -------------------------- --133VU HYDRAULIC/ELEC/ PUMPS/WARN 4GE 331/V60 133VU HYDRAULIC/ACCU PRESS/CTL &/CARGO 7GX 333/T51 DOOR/PUMP

(d)Position access platform. (e)Position safety barriers prohibiting access to gear door travel ranges. WARNING: MAKE CERTAIN THAT THE DOOR TRAVEL RANGES ARE CLEAR. (f)Open right main gear door (Ref. 32-12-11, P. Block 301). WARNING: WHEN DOORS ARE OPEN MAKE CERTAIN THAT SAFETY COLLARS ARE POSITIONED ON DOOR ACTUATING CYLINDERS. (g)Depressurize Yellow hydraulic system and Yellow braking system by means of pressure relief valve 3067 using manual control located on pressure manifold 3060 and prohibit pressurization by displaying a warning notice: - on Yellow hydraulic system ground connectors. - on panel 427VU to prohibit energization of power transfer unit (right PTU pushbutton switch).


- on panel 429VU to prohibit APU starting. - on hydraulic reservoir pressurization connector. (2)Accumulator Charging (Ref. Fig. 006) NOTE : T h e f o l l o w i n g p r o c e d u r e i s d e s c r i b e d f o r o n e a c c u m u l a t o r . the same for the other accumulator. (a)Remove protective cap (1) from filling valve. (b)Unscrew nut (2) by one turn and a half.

It

is

(c)Connect line (4) between the nitrogen source and three-way valve. (d)Connect line (3) to three-way valve. (e)Install a pressure gage graduated from 0 to 150 bars (0 to 2175 psi) on the three-way valve. (f)Open valves A and B and apply nitrogen pressure to bleed the system. (g)Close valves A and B. (h)Connect line (3) to the filling valve. (j)Open valve A gradually and stabilize the pressure at 100 bars (1450 psi) according to ambient temperature. Cl o s e v a l v e A . (k)Tighten nut (2). Depressurize Yellow system by means of pressure relief valve 3067 using manual control and make certain that accumulator press u r e g a g e s t i l l i n d i c a t e s c o r r e c t p r e s s u r e . T o p u p n i t r o g e n a s n e ce ce s sary. Make certain that accumulator pressure gage indicates 100 bars (1450 ps i) . (l)Open valve B to bleed the system. (Pressure gage pointer returns to

29-148 29148

zero). (m)Disconnect line (3) from filling valve. (n)Install protective cap (1) on filling valve. (p)Close nitrogen source valve and open three-way valve A to bleed system. (q)Disconnect line (4) from nitrogen source and three-way valve. (r)Disconnect line (3) to three-way valve. ( 3 ) C l o s e - Up Up

the

( a ) M a k e c e r t a i n t h a t w o r k i n g a r e a i s c l e a n a n d c l e a r o f t o o l s a n d mi s c e l laneous items of equipment. (b)Pressurize hydraulic reservoir (Ref. 29-14-00, P. Block 301). (c)Remove safety clips and tags, and close circuit breakers 4GE and 7GX. WARNING: WARNING: MAKE CERTAIN THAT DOOR TRAVEL RANGES ARE CLEAR. (d)Close landing gear doors (Ref. 32-12-11, P. Block 301). (e)Remove warning notices. (f)Close access doors, remove access platform and safety barriers. ( g ) R e m o v e a l l g r o u n d h a n d l i n g a n d m a i n t e n a n c e e q u i p m e n t , s t a n d a r d a n d s p eecial tools, together with ground power and replenishing equipment, all access equipment and miscellaneous items.

ATA 29 A300/A310

A300/A310 Alternate Brake System - Accumulator FIN 3125/3126 Servicing

Accumulator Changing Chart


29-149 29149

ATA 29 A300/A310



29-150 29150

ATA 29 A300/A310

RAM AIR TURBINE RAT


29-151 29151

ATA 29 A300/A310

A300/A310 Yellow Hydraulic System - Ram Air Turbine (RAT) - General The ram air turbine (RAT) is used in the event of failure of both engines, to supply emergency hydraulic power to the Yellow Hydraulic System Primary Flight Controls. It is composed of: - A hinged support strut - A two-bladed turbine - A variable displacement hydraulic pump - A linkage connecting the assembly to the doors. - An uplock mechanism - An ejection jack - A ground checkout module The ram air turbine is normally retracted and held in this position by an uplock mechanism. Ejection is initiated by mechanical release of the uplock mechanism, and is continued by a mechanical ejection jack. Stowage of the RAT in its compartment is achieved manually on the ground. Yellow Hydraulic System Primary Flight Controls All Speed Ailerons – LH/RH Wings • Elevators – LH/RH Horizontal Stabilizers • Rudder – Vertical Stabilizer (also called Fin) • Spoilers – A300/Roll Control/Spoilers Control/Spoilers 3 and 5 • A310/Roll Control/Spoil ers 4 and 6 • Trimmable Horizontal Stabilizers Actuator – Yellow System •


29-152 29152

ATA 29 A300/A310

A300/A310 Yellow Hydraulic System - Ram Air Turbine - General


29-153 29153

ATA 29 A300/A310

A300/A310 Yellow Hydraulic System - Ram Air Turbine - Component FIN/Data

- - - - - - - - - - - - - -- - - - - - - - - - - - - -- - - - - - - - - - - - - -- - - - - - - - - - - - - - -- - - - - - - - - - - - - -- - - - - - - - FIN FUNCTIONAL DESIGNATION PANEL ZONE ACCESS ATA DOOR REF. - - - - - - - - - - - - - -- - - - - - - - - - - - - -- - - - - - - - - - - - - -- - - - - - - - - - - - - - -- - - - - - - - - - - - - -- - - - - - - - 293097 CONTROL HANDLE-RAT 211 29-25-13 221 293140 RAM AIR TURBINE 671 671EB 29-25-27 295854 UPLOCK MECHANISM 671 671EB 29-25-26 671FB 295855 JACK-RAT EJECTION 671 671EB 29-25-33 671FB 2GF MODULE-RAT GROUNDCHECK OUT 671 671AB 29-25-29 C ON ON T RO RO L C A BL BL E Q U AD AD R AN AN T - R A T 211 121 BL 29 -2 5-1 6 B E LL L L C R AN AN K A S S SY Y - F US U S L G -T - T O - WI N G 671 671AB 29-25 -22 RAT CTL FEEDTHROUGH FILTER 671 671EB 29-25-35 671FB D OO OO R SS- R A M A I R T U RB RB I N E 671 29- 25- 34


29-154 29154

ATA 29 A300/A310

A300/A310 Yellow Hydraulic System - Ram Air Turbine - Component Location/FIN


29-155 29155

ATA 29 A300/A310

A300/A310 A300/A31 0 Yellow Hydraulic System - Ram Air Turbine - Component Functions Function of the Various Components •

•

Ej e c t i o n

jack

Strut

The

The strut receives: ( a) T h e t u rb i ne

powered actuator that extends RAT into the airstream. Hel i c a l c o m p r e s s i o n s p r i ng s i n i t i a t e R A T d e p l o y m en t

( b ) T he he pu p u mp mp

ejection

jack

consists

of

an

oil

dampened,

a g a i n s t c o m p a r t m e n t d o o r s . O n c e c a u g h t by t h e

(c) The pivot post coupling.

with associated

hydraulic swivel

spring

airstream,

the RAT is forced to the fully deployed position. As RAT approaches the fully deployed position, oil is forced

( d ) T h e e j e c t io n j a c k p i s t o n r o d e y e - e n d

through

( e ) T h e p l u n g e r l o c k i ng t h e r o t a t i n g s e c t i o n w h en t h e R A T is not fully extended

dampening effect. The dampening effect prevents high shock loads from being transmitted into the RAT and into

( f ) T h e t u r bi n e / h y dr a u l i c p um p d r i v e s h af t

the aircraft structure.

( g ) T h e u pl o c k r ol l e r (h) The linkage connecting the

RAT

to

the door

various

sized

internal

orifices

causing

a

opening

mechanism. •

Turbine

assembly

The turbine: R e c ei v e s is •

27

th e

t wo

b l ad e s , t i p -t o - ti p

di a m et e r

of

w h ic h

in.

H o u s es es

th e

b la de

p it c h

Hydraulic pump T he h e pu pu mp mp i s u s e d i n n o r m a l o p e r a t i o n

to prov ide

hydraulic power. It is also us ed on the ground as a m ot o r t o d r i v e checkout. •

t he

turbine

for

gov erning

sy stem

Linkage connecting the strut to the door opening mechanism. The connecting linkag e is an integral part of the ram air turbine assembly, and accompanies the doors as they open at the start of RAT ejection, until they auto mati cal ly

•

d ow o w nl nl o c k

U pl pl o c k m e c h a n i s m The uplock holds RAT deployed.

RAT

when fully in

stowed

deployment

is

o pe n .

position

initiated

until

from

RAT

is

flight

compartment. Rotation of uplock input shaft moves an internal locking cam that unlocks the uplock hook. Rel e a s e

of

this

RAT out into the

uplock

hook

allows

ejection

jack

to

push

airstream.


29-156 29156

ATA 29 A300/A310

Yellow Yello w Hydraul Hydraulic ic System System - Ram Air Turbine Turbine


29-157 29157

ATA 29 A300/A310

A300/A310 Yellow Hydraulic System - Ram Air Turbine - Ejection Control System Ej e c t i o n C o n t r o l Ram air turbine ejection is controlled by a handle at the Captain's station or a second handle at the First Of f i c e r ' s s t a t i o n . Each handle drives a control system connected to the uplock mechanism release system. Mechanical control linkage cable diamet er is 0.125 in. (3.175 mm).


29-158 29158

ATA 29 A300/A310

A300/A310 Yellow Hydraulic System - Ram Air Turbine Control System A300 RAT System

A310 RAT System


29-159 29159

ATA 29 A300/A310

Yellow Yello w Hydraul Hydraulic ic System System - Ram Air Turbine Turbine The RAT may be ejected throughout the Whole Flight Envelope, Normal and Peripheral. The RAT is used to supply emergency hydraulic power to the Yellow Hydraulic System for aircraft control purposes. If two or all Hydraulic Systems (Green, Blue and/or Yellow (G-B-Y) Systems) have failed or in case of Engine 1 and 2 FlameOuts, the RAT System can be used for Yellow System Flight Control purposes. The RAT is a self-regulating Hydraulic Pump driven by a constant speed propeller. It is connected to the Yellow Hydraulic System and will pressurize the system when the RAT is extended into the airstream. The RAT consists of a Constant Pressure, Variable Displacement Hydraulic Pump that can supply the Yellow Hydraulic System throughout the above envelope, 3028 PSI +44 PSI (206 +3, -0 Bars at Zero Delivery and > 2837 PSI (>193 Bars) at Full Delivery: 16.9 US Gallons Per Minute (45 Liters Per Minute). Note: One Bar equals 14.7 PSI and One US Gallon equals 3.785 Liters for calculation purposes. The above Delivery / Pressure Performance is met for the following limit configurations of the aircraft: • •

Airspeed of 360 Knots with a +/- 2 Degrees Skid Skid Angle Airspeed of 130 Knots with a +/- 5 Degrees Skid Skid Angle

Response Time (Time between the Uplock Release Manual Command and the appearance of Nominal Pressure in the RAT Pump Delivery Pressure Line) is less than (<) 6.5 Seconds.

Two RAT Handles are installed in the Flight Compartment, One on each Side Console. The A300-600 RAT Handles are flush mounted on the SideWalls above the LH/RH Side Consoles aft end. The A310-200 Series are mounted on the LH/RH Side Consoles on the aft end with vertical handles. Operation of either RAT Handle mechanically UNLOCKS the RAT. The Ejection Jack (Actuator) extends the RAT by internal spring force and fluid dampens out the downward ejection force to the LOCK position. The RAT Compartment Fairing Doors are OPENED at the same time during the RAT Extension Cycle; the Fairing Doors (LH and RH Doors) are mechanically linked with the RAT Unit. The RAT is LOCKED in the DOWN Position once it is extended from the Flight Compartment and cannot be RETRACTED. The RAT can only be RESTOWED when the aircraft is on the ground. The Restow Procedure requires at least two people to restow it for safety purposes since the Ejection Jack is spring loaded to the downward position. NOTE: There is no Indication Light or RH ECAM – HYD Page Indication when the RAT is accidentally “EXTENDED” in flight, when the Yellow Hydraulic System Engine Driven Pump (EDP) and Green/Yellow Power Transfer Unit (PTU) are switched OFF. The Hydraulic Pressure in the Yellow Servo Controls Manifold will indicate approximately 2875 PSI from the RAT Hydraulic Pump Power Generation in the extended position during flight condition.

The RAT is fixed to an extendible strut stowed in the RAT Compartment located in the Lower Right Wing Root adjacent to the RH Main Gear and Hydraulic Compartment Compartment (RH Main Gear Wheel Well).


29-160 29160

ATA 29 A300/A310

Yellow Yell ow Hydraul Hydraulic ic System System - Ram Air Turbin Turbine e - Perfor Performanc mance e Informat Information ion


29-161 29161

ATA 29 A300/A310

A300/A310 Yellow Hydraulic System - Ram Air Turbine Extension Jack - Servicing A .

Reason for the Job

( 2) F i l l i n g

( 1) F i l l i n g o r t o p p i n g- u p a f t e r i n s p e c t i o n o r r e m o v a l . B.

Equipment

and

( a ) R e m o v e p r ot e c t i v e c a p f r om c h a r g i n g v a l ve . ( b ) C he he c k t h a t f l e x i b l e h o s e o f s y r i n g e 9 8 A 2 9 0 0 3 0 0 1 0 0 0

Materials

is

- - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - ITEM DESIGNATION

filled

with

hydraulic

fluid.

( c ) T a k e a r e f e r en c e o n s y r i n g e g r ad u a t i o n. (d) Connect flexible hose to charging valve.

- - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - -

( e ) L o o s e n b l e e de r

( 1 ) 9 8 A 2 90 9 0 0 3 0 01 01 0 0 0

Gr a d u a t e d S y r i n g e 0 . 5 (0.132 US gallon)

( f ) P e r f o r m m e as u r e m e n t by f i l l i n g j a c k u n t i l hydraulic fluid begins to run from bleeder scr ew.

(2)

A c c e s s P l a t fo r m 2 . 6 m (8 ft. 8 in.)

( 3 ) M at e r i a l

No.

02-003

Ref e r e n c e d P r o c e d u r e - 29-25-00, P. Block 301

Hydraulic

Fluids

(Ref.

l

s c re w .

( g ) I f a d d e d f l u i d v o lu m e i s g r e a t e r t h a n 1 7 c l ( 0 .0 4 5 U S Ga Gal l o n ) , r e m o v e j a c k a n d p e r f o r m l e a k a g e c h e c k 20-31-00)

(Ref.

CMM

29-21-23).

( h ) TO R Q U E bl e e d e r s c r e w t o b e t w e e n 0 . 2 5 a n d 0 . 3 5 m. d a N ( 2 0 a n d 3 0 l b f . i n . ) .

Yellow Auxiliary Power (Ram Air

Turbine)

( j ) Di s c o n n e c t

- CMM 29-21-23

( k ) I n s t a l l p r o t ec t i v e c a p o n c h a r g i n g v a l v e . ( l ) Cl e a n r e s i d u a l f l u i d f r o m e x t e r i o r o f j a c k .

( 1 ) J o b s e t -u p ( a ) P o s i t i o n s a f e ty b a r r i e r s a n d d i s p l a y w a rn i n g

( m) m) S a f e t y ( 3 ) Cl o s e - U p

notices around RAT extension area. ( b ) P o s i ti o n a c c e s s p l a tf o r m . ( c ) I n s t a l l pr o t e c t i v e e q ui p m e n t

on RAT.

(d) I n

RAT in

flight

c om p a r t m e n t s e l e c t

f l ex i b l e h o s e .

bleeder

screw

with

( a ) C l e a n R A T . Wi p e o f f a l l

lockwire.

traces

( b ) Ret r a c t R A T ( R e f . 2 9 - 2 5 - 0 0 , ( c ) R e m o v e t o p p i n g- u p un i t . e x t e n de d

P.

of hyd raulic Block

fluid.

30 1 ) .

( d ) R e m ov e a c c e s s p la t f or m .

position (Ref. 29-25-00, P. Block 301). ( e ) Di s p l a y w a r n i n g n o t i c e p r o h i b i t i n g c o n n e c t i o n o f RAT check-out unit to receptacle 142VC in zone 144.


29-162 29162

ATA 29 A300/A310

A300/A310 Yellow Hydraulic System - Ram Air Turbine Extension Jack - Servicing


29-163 29163

ATA 29 A300/A310



29-164 29164

ATA 29 A300/A310

HYDRAULIC SYSTEM SERVICING


29-165 29165

ATA 29 A300/A310

A300/A310 Hydraulic System - Replenishing - General The hydraulic system reservoirs on this aircraft can be serviced in one of two ways: 1. Using Using an hydra hydraulic ulic tank tank replen replenishin ishing g unit 2. Using the the built in hand pump and servicing servicing hose for extracting extracting clean, clean, serviceable hydraulic fluid from containers (one quart and gallon cans, etc.) The hand pump and servicing hose are located behind and forward of the green hydraulic system servicing panel, on the LH side of the fuselage, aft of the LH main gear wheel well.


29-166 29166

ATA 29 A300/A310

Green - Blue - Yellow Hydraulic System - Fluid Servicing


29-167 29167

ATA 29 A300/A310

A300/A310 Hydraulic Systems - Reservoir Fluid Level Check - Servicing Hydraulic

Reservoir

Fluid Level

Check

(f)Depressurize hydraulic system concerned (Ref. 29-10-00, P. Block 301). Do not depressurize hydraulic system reservoirs. NOTE : In Yellow hydraulic system do not depressurize Braking system accumulators as normal Yellow reservoir servicing procedure

A. Reason for the Job (1)Reservoir fluid level check.

B. Equipment and Materials --------------------- ------------------------- ------------------------ --------ITEM DESIGNATION --------------------- ------------------------- ------------------------ --------(1) Acccess Platform 2.6 m (8 ft. 8 in.) Referenced Procedures - 24-41-00, P. Block 301 AC External Power Control - 29-10-00, P. Block 301 Main Hydraulic Power - Pressurizat ion/ Depressurization - 29-14-00, P. Block 301 Hydraulic Reservoir Pressurizing System - 29-24-00, P. Block 301 Yellow Auxiliary Power Electrical Pump - 32-12-11, P. Block 301 Main Gear Main Door - (Ground Door(s) Opening) C. Procedure (Ref. Fig. 001) (1)Job set-up (a)Connect electrical ground power unit and energize the aircraft electrical network (Ref. 24-41-00, P. Block 301). (b)In flight compartment, select following aircraft configuration : 1 Speedbrakes and spoilers retracted . 2 Landing gear extended and doors closed. 3 Forward and aft cargo compartment doors 811 and 812 closed. NOTE : To take into account the difference of fluid contained in actuators extension chambers : - Wi t h a l l c a r g o d o o r s o p e n , t h e r e s e r v o i r f i l l l e v e l i s t o b e adjusted between 17.5 and 18 liters (4.6 and 4.75 US.G) instead of 18.5 liters (4.89 US.G). - Wi t h o n l y u p p e r d e c k c a r g o d o o r f u l l y o p e n ( F W D a n d A F T c a r g o doors closed), the reservoir fill level is to be adjusted at 18 liters (4.75 US.G) instead of 18.5 liters (4.89 US.G). - Wi t h o n l y F W D a n d A F T c a r g o d o o r s f u l l y o p e n a n d u p p e r d e c k cargo door closed, the reservoir fill level is to be adjusted at 18 liters (4.75 US.G) instead of 18.5 liters (4.89 US.G). - Wi t h a l l c a r g o d o o r s c l o s e d , t h e r e s e r v o i r f i l l l e v e l i s t o be adjusted between to 18 and 18.5 liters (4.75 and 4.89 US.G) 4 On HYD PWR panel 427VU, ELEC PUMPS pushbutton switch released (out). LO PR and ON legends off. 5 On panel 427VU, PTU pushbutton switches released (out). ON legends off. (c)Open left landing gear main door (Ref. 32-12-11, P. Block 301). (d)Position access platform. (e)Display warning notices prohibiting operation of the hydraulic systems, as this would result in a change in the basic aircraft configuration and consequently a change in the level of fluid in the reservoir to be replenished.


m u s t b e p e r f o r m e d w i t h B r a k e a c c u m u l a t o r s h y d r a u l i c a ll y p r e s surized. Make certain that pressure in Brake accumulators is approximately 3.000 psi (206 bars). NOTE : However, when Brake accumulators are hydraulically depressurized it is possible to perform servicing as follows. - either add 3.5 liters to normal level i.e 18.5 liters in order to take into account Brake accumulators capacity -

or hydraulically repressurize Brake accumulators (Ref. 29-24-00, P. Block 301) and perform normal servicing procedure. (g)Make certain that hydraulic system accumulator associated to the reservoir to be checked is empty of fluid i.e that nitrogen pressure is 1450 psi (100 bars). NOTE : If according to above note, Yellow hydraulic reservoir servicing is made with brake accumulators hydraulically depressurized, check that nitrogen pressure is 1450 psi (100 bars). (h)Make certain that pressure read on indicator associated to the reservoir to be checked is between 1.8 bars (26 psi) and 3.5 bars (50 psi). If required, pressurize relevant reservoir (Ref. 29-14-00, P. Block 301). (2)Fluid level check (a)Open access door 147AL, place reservoir filling manual selector 8GQ in position corresponding to reservoir being checked. (b)On reservoir fill level indicator plate 10GQ, check that light of color corresponding to reservoir selected comes on. (c)Check that pointer on hydraulic quantity repeater indicator 9GQ is opposite colored line corresponding to reservoir selected. NOTE : When Brake accumulators are hydraulically depressurized, reservoir fluid level should be checked on Yellow reservoir quantity transmitter and not on hydraulic quantity repeater indicator 9GQ.

29-168 29168

(d)Place reservoir filling manual selector 8GQ in neutral position. (3)Close-up ( a ) D e - e n e r gi z e t h e a i r c r a f t e l e c t r i c a l n e t w o r k a n d d i s c o n n e c t e l e c t r i c a l ground power unit (Ref. 24-41-00, P. Block 301). (b)Close access door 147AL. (c)Remove access platform. (d)Close left landing gear main door (Ref. 32-12-11, P. Block 301). (e)Remove all ground handling and maintenance equipment, standard and special tools, together with ground power and replenishing equipment, all access equipment and miscellaneous items.

ATA 29 A300/A310

A300/A310 Hydraulic Systems Systems - Reservoir Fluid Level Check - Location


29-169 29169

ATA 29 A300/A310

A300/A310 Hydraulic Systems - Hydraulic Reservoir Replenishing Hydraulic A.

Reservoir

Replenishing

Reason for the Job (1)Hydraulic reservoir

filling

or

topping

up.

B. Equipment and Materials - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - -- - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - -- - - ITEM DESIGNATION - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - -- - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - -- - - ( 1 ) 9 7 A 2 9 1 0 2 0 3 50 0 0 C o n n e c t o r - P r e s s u r iz i n g , H y d r a u l i c T a n k or equivalent (2)99A29001006000 or

equivalent

(3) (4) (5)Material No. 02-003 Referenced Procedures - 24-41-00, P. Block 301

Unit-Topping Up Hydraulic

Tank

(Hand Operated) Access Platform, 2.6 m (8 Fluid Recovery Containers

ft.

8

in.)

Hydraulic Fluids (Ref. 20-31-00) AC External Power Control

- 29-00-00, P. Block 401 - 29-10-00, P. Block 301

General Removal/Installation Main Hydraulic Power - Pressurization/

- 29-14-00, P. Block 301 - 29-24-00, P. Block 301

D e p r e s s u r i z at i o n Hydraulic Reservoir Pressurizing System Yellow Auxiliary Power Electric Pump

- 32-12-11,

P. Block

301

Main Gear Main Door - (Ground Door(s)

Opening)

C. P r o c e d u r e (1)Job set-up (a)Connect electrical

ground

power

unit

and

energize

the

aircraft

electrical network (Ref. 24-41-00, P. Block 301). (b)In flight compartment, select following aircraft configuration : 1 Speedbrakes and spoilers retracted. 2 Landing gear extended and doors closed. 3 Forward and aft cargo compartment doors 811 and 812 closed. 4 On HYD PWR panel 427VU, ELEC PUMPS pushbutton switch released (out). LO PR and ON legends off. 5 On panel 427VU, PTU pushbutton

o f f . (c)Open left landing gear main (d)Position access platform.

door

switches (Ref.

released

32-12-11,

P.

(out).

ON legends

Block

301).

( e ) D i s p l a y w a r n i n g n o t i c e s p r o h i b i t i ng o p e r a t i o n o f t h e h y d r a u l i c s y s t e m s as this would result in a change in the basic aircraft configuration and consequently a change in the level of fluid in the reservoir to be

replenished. (f)Depressurize hydraulic

system

concerned

(Ref.

29-10-00,

P.

Block

301).

Do not depressurize hydraulic system reservoirs. NOTE : In Yellow hydraulic system do not depressurize Braking system accumulators as normal Yellow reservoir servicing procedure must be performed with Brake accumulators hydraulically pressurized. Make certain that pressure in Brake accumulators is approximately 3.000 psi (206 bars).


29-170 29170

ATA 29 A300/A310

A300/A310 Hydraulic Systems - Hydraulic Reservoir Servicing


29-171 29171

ATA 29 A300/A310

A300/A310 Hydraulic Systems - Hydraulic Reservoir Replenishing NOTE:

However, when Brake accumulators are hydraulicall y depressurized it is possible to perform servicing as follows. - either add 3.5 liters to normal level i.e 18.5 liters in -

order to take into account Brake accumulators capacity or hydraulically repressurize Brake accumulators (Ref. 29-24-00, P. Block 301) and perform normal servicing procedure.

(g)Make certain that hydraulic system accumulator associated to the reservoir to be checked is empty of fluid i.e that nitrogen pressure is 1450 psi (100 bars). NOTE: If according to above note Yellow hydraulic reservoir servicing is made with brake accumulators hydraulically depressurized check that nitrogen pressure is 1450 psi (100 bars). (h)Make certain that pressure read on indicator associated to the reservoir to be checked is between 1.8 bars (26 psi) and 3.5 bars (50 psi). If required, pressurize relevant reservoir (Ref. 29-14-00, P. Block 301). (2)Filling/t Perform quantity NOTE: -

opping up related bleeding procedure to make certain that is correct (Ref. 29-00-00, P. Block 401): if a large number of components is replaced,

hydraulic

fluid

-

if there is a hydraulic fluid low level which causes loss of system, - if there is a large loss of hydraulic fluid. (a)Filling of reservoir using hydraulic tank (reservoir) replenishing unit.

the

NOTE: Make certain that filling pressure does not exceed 11 bars (160 psi). 1 In zone 147, on Green system ground connector, place reservoir filling manual selector 8GQ in position corresponding to reservoir to be filled. 2

On reservoir fill level indicator plate 10GQ, check that light of color corresponding to reservoir selected comes on. 3 Start up hydraulic tank replenishing unit. Observe rise in fluid level on reservoir hydraulic quantity repeater indicator 9GQ. Stop flow of hydraulic fluid when pointer of quantity repeater is opposite colored

l i n e c o r r e s p o n d i ng t o s e l e c t e d r e s e r v o i r . 4 Depending on ambient temperature, adjust fluid level according to the table below. If the ground temperature is between two values in the table, the operator must choose the nearest indicated value. NOTE: Hydraulic tank replenishing unit pressure must not exceed 11.03 bars (160 psi). For a pressure of 7.6 to 11.03 bars (110 to 160 psi), flow rate is 3.5 l/mn (0.92 US gal/mn). NOTE: When Brake accumulators are hydraulically depressurized, reservoir fluid level should be checked on Yellow reservoir

quantity transmitter and not on hydraulic quantity repeater indicator 9GQ. 4 Place reservoir filling manual selector 8GQ in neutral (NEUTRE) position. (b)Topping up of reservoir using reservoir filling hand-pump.

(Ref. Fig.


002)

29-172 29172

ATA 29 A300/A310

A300/A310 Hydraulic Systems - Hand Pump Service Equipment Location Backside of Green Hydraulic Service Panel 147BL

LH Main Gear Wheelwell

Clogged Filter Pop-out Indicator


29-173 29173

ATA 29 A300/A310

A300/A310 Hydraulic Systems - Hydraulic Reservoir Replenishing 2 Remove locking pin and withdraw filling tube from hand-pump handle. 3 Place filling tube in hydraulic fluid reserve. 4 Connect hand-pump handle to pump splined shaft. Access is gained through Green hydraulic ground connector (access door 147AL). 5 On Green hydraulic system ground connector, place filling selector 8GQ in position corresponding to reservoir to be topped-up. 6 On fill level indicator plate 10GQ, check that light of color corresponding to reservoir selected comes on. 7 Not Applicable. 8 Operate pump and observe rise in fluid level on quantity repeater 9GQ. Stop flow of hydraulic fluid when pointer of quantity repeater 9GQ is o p p o s i t e c o l o r e d l i n e c o r r e s p o n d i ng t o s e l e c t e d r e s e r v o i r . NOTE: If quantity repeater 9GQ does not indicate full and an overflow occurs, the tank is overfull and cannot be properly pressurized.

NOTE:

9 10 11 12

Place filling selector 8GQ in neutral (NEUTRE) position. Remove hand-pump handle from pump. Insert filling tube in hand-pump handle. Install locking pin. Place hand-pump handle in stowage position. NOTE:

When Brake accumulators are hydraulically depressurized, reservoir fluid level should be checked on Yellow reservoir quantity transmitter and not on hydraulic quantity repeater indicator 9GQ.

If the reservoir has been drained prior to replenishment, it must be pressurized, and a leakage check must be performed, both for the overall assembly and, more especially, for the drain valve plugs.

(3)Close-up (a)De-energize the aircraft electrical network and disconnect electrical ground power unit (Ref. 24-41-00, p. Block 301). (b)Disconnect and remove hydraulic fluid reserve. (c)Close access door 147AL. (d)Remove access platform.

tank

replenishing

(e)Close left main gear main door (Ref. 32-12-11, P. (f)Remove warning notices and access equipment.


29-174 29174

unit

and hydraulic

Block 301).

ATA 29 A300/A310

A300/A310 Hydraulic Systems - Hand Pump Service Equipment Location Backside of Green Hydraulic Service Panel 147BL

LH Main Gear Wheelwell

Clogged Filter Pop-out Indicator


29-175 29175

ATA 29 A300/A310

GREEN - BLUE - YELLOW HYDRAULIC RESERVOIRS RESERVOIRS - DRAINING PROCEDURE Draining of Hydraulic Reservoirs WARNING: CHECK THAT THELANDING GEAR GROUND SAFETIES SAFETIES INCLUDING INCLUDI NG WHEEL CHOCKSARE IN POSITION.

1

BEFOREAPPLYING OR RELIEVING HYDRAULIC SYSTEMPRESSURE, MAKECERTAIN THAT THE TRAVEL RANGES OF THE CONTROL SURFACES ARE CLEAR. BEFOREPRESSURIZING HYDRAULIC SYSTEMS, CHECK THAT ALL CONTROLS ARE SET TO CORRESPOND WITH THE ACTUAL POSITION OF THE SERVICES THEY OPERATE. NOTE: Draining described in this section is effective for Green, Blue and Yellow reservoirs, reservoi rs, 291000, 292000 and 293000 respectively. respecti vely.

For Training Purposes Only

291000:

ELEC/PUMPS/WARN PTU CTL/G/B

4GE 1GL

331/V60 332/U59

133VU

PTU CTL/G/Y

6GL

332/U60

2 For Blue reservoir 292000: - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - -

PANEL SERVICE IDENT. LOCATION - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - 133VU

MTT M540000 / R3.3 01AUG01

reservoir

133VU 133VU

A. Reason for the Job (1)Draining (1)Draini ng to change hydraulic fluid. flui d. B. Equipment and Materials ---------------------------------------------------------------------------------------------------------------------------------------------------------ITEM DESIGNATION ---------------------------------------------------------------------------------------------------------------------------------------------------------(1) AccessPlatform 2.6 m (8 ft. 8 in.) (2) Reservoir Draining Hose (3) Container Referenced Procedures - 12-36-29, P. Block 1 Hydraulics - 29-10-00, P. Block 301 Main Hydraulic Power - Pressurization/ Depressurization - 29-14-00, P. Block 301 Hydraulic Reservoir Pressurizing System - 32-12-11, P. Block 301 Main Gear Main Door - (Ground Door(s) Opening) C. Procedure (Ref. Fig. 302) (1)Job Set-Up (a)In (a)I n flight fli ght compartment display warning notices on HYD PWRpanel 427VU prohibiting prohibi ting operation operati on of controls control s and movement of components powered by system whose reservoir reservoi r is to be drained. (b)Openright main gear door (Ref. 32-12-11, P. Block 301). (c)Install access platform. (d)Depressurize Green, Blue or Yellow reservoir (Ref. 29-14-00, P. Block 301). (e)Depressurize relevant hydraulic system(Ref. 29-10-00, P. Block 301). (f)Open, safety and tag the following circuit breakers:

For Green

- - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - PANEL SERVICE IDENT. LOCATION - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - -

PTU CTL/G/B 3 For

Yellow

1GL reservoir

332/U59

293000:

- - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - PANEL SERVICE IDENT. LOCATION

- - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - 133VU PTU CTL/G/Y 6GL 332/U60 133VU

ACCU PRESS/CTL &/CARGO DOOR/PUMP

(2)Draining (a)Install

container

under

reservoir

7GX

to

be

333/T51

drained.

(b)Cut and remove lockwire and unscrew needle valve access port plug as well as drain port plug. (c)Connect one end of drain hose to drain port and insert other end into fluid container of sufficient capacity. (d)Using a plain screwdriver, unscrew needle valve. (e)Tighten needle valve when (f)Disconnect drain hose.

reservoir

(g)Install the two plugs coated new O-rings, and wirelock.

with

is

completely

hydraulic fluid

empty. and

fitted

with

(3)Close-Up (a)Remove depressurizing equipment. (b)Remove all ground handling equipment, standard and special tools, together with ground power and replenishing equipment, all access equipment and miscellaneous items.

29-176 29176

ATA 29 A300/A310

A300/A310 Hydraulic Systems - Reservoir Draining (Standard Procedure)


29-177 29177

ATA 29 A300/A310

A300/A310 Hydraulic System - System Draining - Alternate Method Through Sampling Valve

A300/A310 Main Gear Main Doors - Manual Release Handle Mechanism Location Opening the right gear door only on the A300 will allow access to all 3 Sampling Valves on each system (G-B-Y) Servo Controls Manifold located in the Hydraulic Bay Main Gear Wheel Wells.


29-178 29178

ATA 29 A300/A310


Green and Yellow Hydraulic System Servo Control Manifolds with hydraulic fluid sampling valves on each manifold. The sampling valves will be used for draining excess hydraulic fluid from the green and yellow hydraulic systems.

The Green Hydraulic System Sampling Valve dust cap has been removed for draining the system with special tool device. Yellow System Sampling Valve is installed and lockwired in position. Step 2


29-179 29179

ATA 29 A300/A310


The Yellow System Servo Controls Manifold Sampling Valve can be used for draining the Yellow Hydraulic System. Also, drains the system reservoir down to a lower level as indicated on the reservoir tank unit quantity indicators. Ensure that safe and adequate work platform or ladder is used when draining yellow system reservoir.

The Green System Servo Controls Manifold shown above is similar to the A300-600 for utilizing the fluid sampling valve to drain the Green System and reservoir to the proper fluid level. Step 2


29-180 29180

ATA 29 A300/A310

A300/A310 Hydraulic System - System Draining - Alternate Method Through Sampling Valve Blue and Green System Draining

A310 Blue System Servo Controls Manifold (SCM) is located in the left wing root area forward of the main gear strut (shock absorber) well. The A300-600 Blue SCM is located in the LH main gear well (hydraulic bay) at the 8 o’clock position looking forward adjacent to fuselage frame FR47 (rear wing spar).

A310 System Servo Controls Manifold Manifold with sampling valve dust cap lockwire removed. Cap is ready to be removed and to expose the sampling valve “Open and Close” device for draining fluid and shutting the sampling valve. Step 2


29-181 29181

ATA 29 A300/A310


Green System Draining

Step 3 - Requires two people. The first person pressurizes the over-serviced system in the flight compartment utilizing the green hydraulic system (if over-serviced). The green system may be pressurized for the blue or yellow system power transfer unit pressurizing the affected over-serviced system. Also, observes the fluid quantity on the overhead HYD PWR panel 429VU. The second person pulls down on the special draining tool to release hydraulic fluid from the Sampling valve. The fluid is drained into a suitable container which can hold 5 US gallons (20 liters). When the hydraulic quantity indicates the proper level, turn off the hydraulic pumps and release pressure from drain tool. Reinstall sampling valve cap and lockwire.


29-182 29182

ATA 29 A300/A310



29-183 29183

ATA 29 A300/A310

AIRBUS ATA 29 QUICK QUIZ The following quiz covers training areas to further increase your knowledge and skills of the Airbus A300/A310 aircraft and other areas of importance to you... 1. WHAT IS THE PURPOSE PURPOSE OF THE PRIORITY

5. WHICH HYDRAULIC HYDRAULIC SERVICE PANEL

VALVES LOCATED ON THE HIGH PRESSURE

PROVIDES SERVICING OF ALL THREE HYD

MANIFOLDS? THE VALVES “CLOSE” AT

RESERVOIRS? WHERE IS IT LOCATED?

APPROXIMATELY _______PSI. 6. WHERE IS THE HYD FLUID FLUID OVERHEAT OVERHEAT 2. WHAT IS THE PURPOSE OF THE SERVO

SENSOR LOCATED? WHAT TEMP WILL

CONTROLS MANIFOLD? WHERE ARE THEY

ACTIVATE THE RESERVOIR O/HEAT LIGHT?

LOCATED? NAME THE SPECIAL FEATURE

THE O/HEAT LIGHT IS LOCATED?

ON THE MANIFOLD... 7. WHICH MAIN ENGINE ENGINE PROVIDES PROVIDES AIR PRESS PRESS 3. HOW IS THE RAM AIR TURBINE DEPLOYED

TO PRESSURIZE THE HYD RESERVOIRS?

DURING EMERGENCY CONDITIONS FOR

NAME THE EXTRACTION STAGE ON THE GE

FLIGHT CONDITIONS? WILL IT RETRACT

AND PW ENGINES…HOW IS IT REDUCED IN

AUTOMATICALLY AUTOMATICALL Y AFTER USE IN FLIGHT?

PRESSURE FOR THE RESERVOIR(S)? RESERVOIR(S)?

4. WHERE ARE THE SAFETY VALVES (HYD

8. NAME THE VARIOUS VARIOUS WAYS TO OPERATE THE

FUSE) LOCATED IN THE GREEN HYD SYS?


YELLOW ELEC HYD PUMP? CB LOCATION?

29-184 29184

ATA 29 A300/A310

AIRBUS ATA 29 QUICK QUIZ - ANSWER SHEET/NOTES

1.

5.

2.

6.

3.

7.

4.

8.


29-185 29185

ATA 29 A300/A310

THIS PAGE INTENTIONALLY LEFT BLANK ATA 29 - END COURSE CODE - M540000


29-186 29186

ATA 29 A300/A310

Airbus 29 A300 A310 Hydraulics

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