1. Two Pumps: A. Primary pump– a variable volume, variable pressure self compensating type with remote controls. B. Charge pump– a fixed displacement type supercharging the return inlet of the primary pump. The benefits of such a system can be seen in the following High Test section.
2. Two Filters: A. Main system– 3 microns, absolute. B. Charge system– to meet charge pump specifications.
3. Heat Exchanger: Constant duty, forced air type. A component of the High Test system.
4. Reservoir: All-welded cylindrical-aluminum unit with bypass valve and relief valves. Sight gauges on large volume units.
5. Temperature Gauge: Panel mounted.
6. Volume and Pressure Control: Panel mounted.
7. Flow Meter: A visual in-line type.
8. Pressure Gauges: Main system– glycerin filled, panel mounted.
9. Manifold Block: One common block for both pressure and return in single system units. One block for pressure and two for return in dual systems.
10. Reverse Phase Relay: Protects against reverse operation of electric motor.
11. Hourmeter: Panel mounted.
12. Electric Motor: Sized to provide full rated flow at 3,000 PSI on a CONSTANT DUTY BASIS.
13. Two System Relief Valves: One of each in the main pressure and charge system.
14. Two Check Valves: One of each in the main pressure and charge system.
15. Bypass Valve: Main system– panel mounted. For volume adjustment prior to aircraft connection. Also for internal re-circulation of oil for cleaning. Note: The charge system also cleans the oil using the charge filter as the unit is running.
16. Pump Stand-By Valve: Panel mounted. Allows user to de-stroke main pump.
17. Magnetic Starter with overload thermal relays.
18. Circuit Breaker: Sized to motor.
19. Transformer: 115V for motor controls. Allows the economical replacement of motor control components.
20. Hydraulic Hoses: Pressure and return– 15 feet long (SA-1 through SA-6), 25 feet long (SA-7 through SA-20). Custom lengths available.
21. Stop/Start Switch: Panel mounted.
22. AC-Input Cord: 50 feet long (w/o wall plug). Custom lengths available.
23. Cabinet Chassis: All-welded steel chassis with two-fixed and two-swivel casters and floor brake. All-welded unitized cabinet with two large access panel and isolated electrical controls compartment.
24. Powder Coat: White.
25. Data: Hydraulic and electrical schematics. Operator’s manual.
26. Warranty: 1 year.
Configuration Guide Steps
Refer to chart above.
-1 100 Series: All welded steel unitized cabinet and base assembly– 2 rigid and 2 swivel casters, floor lock, 2 large access panels, isolated electrical control box.
Dimensions: (61” L) X (47” H) X (34” W)
-2 200 Series: All welded steel unitized cabinet on a welded base assembly, 2 rigid, 2 swivel casters, floor lock, 2 large access panels, isolated electrical control box.
Dimensions: (80” L) X (50” H) X (48” W)
-3 300 Series: For special units where the standard series cabinets will not be suitable.
-1 Single System: This option provides a single manifold block which controls both the pressure and return system flow. One hose is required for each system.
-2 Dual Systems with Selective Single-System Flow: This option provides a series of interlocking manifold blocks with control valves which allow the operator to operate dual systems, a single system at a time. Two Pressure and two return outlets are coupled to the aircraft. Each system is completely isolated from the other.
Benefits: By use of panel valves, the operator can direct the unit output to either system. With each system isolated the unit will not transfer fluid from one system to the other within the aircraft. With all four hoses connected to the aircraft at one time, the possibility of air or dirt ingestion into the aircraft is minimal.
-3 Dual Systems with Selective Single-System Flow or Dual Simultaneous Metered Flow in Both Systems: In addition to the performance of option 2, this option adds the ability to direct flow simultaneously in to both systems. Each system has its own flow meter and metering control valve.
Benefits: All the benefits of option 2 plus the ability to meter different flow to two systems in the aircraft where both systems have the same operating pressure. This has shown to be especially useful with helicopters.
-4 Dual Systems with 100% Separate Systems and Control aka “True Dual”: Basically this offers two single-system units in parallel with each system totally independent.
Benefit: The operator can test both aircraft systems at the same time with different flow and pressure in each system. This configuration offers further capability in that the parallel systems can be designed to give different volumes and flow. They can also accommodate similar or dissimilar fluids.
-5 Triple Systems with Selective Single System Flow or Simultaneous Metered Flow in All Systems.
-1 Static Test System provides a method of testing hydraulic components on the bench. It consists of a pressure-relieved hand pump, filter, pressure gauge, needle-pressure trap valve. It draws fluid from the unit reservoir.
Benefit: The special trap valve allows the operator to apply pressure to a unit and then close the trap valve. This indefinitely holds the pressure constant.
-2 Static Test Plus Crossover includes all the components and features of the static test system plus a series of valves which allow hand-pump pressure to be applied into the main pressure system of the unit.
Benefit: This option permits the manual operation of any hydraulic component on the aircraft system at extremely slow speeds to allow accurate adjustment of the landing gear, flaps or other components.
-1 Sustained High Pressure Test System: This provides a solution to excessive fluid-heat build up during extensive periods of test. When extensive testing occurs, the self-compensating pump goes into a compensated position when it has met the pressure and flow requirements. In this compensated mode, the effective horsepower being used is greatly reduced, yet a percentage of horsepower is still required to maintain the pump in compensation. This compensated horsepower then passes its energy into fluid-heat build up. The JETMAC system takes the fluid from the case drain of the pump and passes it repeatedly through a special, carefully sized cooling loop to remove the heat from the fluid and deliver conditioned oil to the intake port of the primary pump.
-1 Reservoir Pressurization provides pneumatic pump, filter, relief valve, panel-pressure gauge, panel-control switch, service hose.
-2 Reservoir Service System:
Direct to Aircraft: A motor-driven low-volume, low-pressure pump supplies fluid through a service hose direct to the aircraft reservoir service inlet. The system includes a panel-mounted pressure gauge, and control switch, fluid filter, service hose.
Through-the-Unit System: Fluid is directed into the main pressure system of the unit and enters the aircraft through the aircraft system. The system includes a panel mounted pressure gauge, control switch, motor and pump.
-3 Water Removal System (petroleum-based fluids only): This filter, installed in the charge pump loop, removes water from hydraulic fluid.
-4 Engines: For units designed to be operated in the field, two engine configurations are offered: Gasoline or Diesel.
-5 Trailer: Four-wheel, pneumatic tires, equipped with automotive type front-wheel steering, and handbrake. Suitable for ramp towing at 10 MPH.
-6 Safety Switches:
Pressure: Interlocked with the main motor controls. Shuts unit down when pressure to main pump inlet falls below designated valve.
Temperature: Interlocked with the main motor controls. Shuts unit down if fluid temperature in the cooling loop exceeds a designated limit.
-7 Soft-Start Motor Controls: Designed for motors of 40 HP and above where the in-rush amperage at start-up is high. This supplies limited current to part of the motor windings. When the motor begins rotation, in approximately 8 to 10 seconds, the remainder of the motor windings are activated bringing the motor to full RPM.
Benefit: Minimizes initial amperage draw on “across the line” starting.
-8 Aeroquip Quick Disconnects: Hose end.
-9 Aeroquip Industrial Quick Disconnects: These are installed in the hose end which connects to the power unit.
Benefit: Easier hose storage and retention of hose prime.
-10 Digital Flow Monitoring Kit: This kit is designed to detect internal leakage of components within the aircraft system. It consists of two major components– a transmitter and digital flow indicator. The transmitter is placed in series in the pressure lin between the power unit and the aircraft. With the power unit holding pressure against a static aircraft system, any small transfer of fluid into the aircraft will be detected by the transmitter and the related indicator. Flow detection is measured in increments of .0632 cu. in. flow.
Benefits: Besides its ability to detect possible major problems before they occur, this unit also permits accurate flow reading on component actuation where the cycle concerned is too rapid to be readable on the conventional in-line flow meter. These kits are usable with all power units manufactured by JETMAC.
-11 Flushing and Sampling Kit: An aluminum manifold allowing connection of pressure and return hoses to create a loop for fluid cycling and sampling. Once the hoses are connected, the fluid in the unit is cycled at low flow and minimum pressure through the unit’s internal filters, ensuring fluid cleanliness prior to aircraft connection. A port on the bottom of the manifold enables a sample of fluid to be taken for testing. Aeroquip quick disconnects can be installed and are quoted separately.
-12 Internal Drip Pan: An aluminum tray with a 1” lip is affixed to the base of the hydraulic power unit and sealed. It catches any hydraulic fluid that may drip from the unit’s internal hydraulic components, preventing fluid from reaching the hangar floor.
-13 External Hose Drip Pan: An aluminum tray with a 2” lip situated underneath the external hose storage rack on the side of the unit. This pan catches any fluid that may drip from external hoses during storage, preventing fluid from reaching the hangar floor.
-1 208V, 60HZ, 3 Phase
-2 220V-240V, 60HZ, 3 Phase
-3 440V-480V, 60HZ, 3 Phase
-4 200V, 50HZ, 3 Phase
-5 380V-400V, 50HZ, 3 Phase
-6 415V, 50HZ, 3 Phase
-3 Skydrol 500B
-4 Skydrol LD4
-5 HyJet IV
-6 HyJet V
HPU Configuration Guide
|STEP 1||STEP 2||STEP 3||STEP 4||STEP 5||STEP 6||STEP 7||STEP 8|
|STEP 1||STEP 4||STEP 7|
|FLUID CATEGORY AND FLOW||STATIC TEST SYSTEM||ELECTRICAL|
|Petroleum Based||GPM@3000 PSI||Motor HP||Phosphate Ester||-0||Without||-1||208V, 60HZ, 3 Phase|
|-1||5||10||-2||-1||Static Test||-2||220V-240V, 60HZ, 3 Phase|
|-3||10||20||-4||-2||Static Test Plus Crossover||-3||440V-480V, 60HZ, 3 Phase|
|-5||15||30||-6||-4||200V, 50HZ, 3 Phase|
|-7||20||40||-8||-5||380V-400V, 50HZ, 3 Phase|
|-9||25||50||-10||STEP 5||-6||415V, 50HZ, 3 Phase|
|-11||30||60||-12||HIGH TEST SYSTEM (STANDARD)|
|STEP 2||OTHER OPTIONS||-2||83282|
|CABINET SERIES||-3||Skyrol 500B|
|-1||Aircraft reservoir pressurization||-4||Skydrol LD4|
|-1||100 Series Cabinet - For unit from 5GPM to 15GPM||-2||Reservoir fill system||-5||HyJet IV|
|-2||200 Series Cabine - For units 20 GPM and greater||A. Direct to aircraft||-6||HyJet V|
|-3||Custom Cabinet||B. Through unit system|
|-3||Water removal system|
|STEP 3||A. Gasoline|
|SYSTEM SPECIFICATION||B. Diesel|
|-1||Single System||-6||Safety Cut Off|
|-2||Dual System, Single Flow Meter||A. Pressure|
|-3||Dual System, Dual Flow Meter||B. Temperature|
|-4||Dual Single Systems, "True Dual"||-7||Soft start|
|-5||Triple System||-8||Aeroquip quick disconnects|
|-9||Industrial quick disconnects - hose to unit|
|-10||Digital flow monitoring kit|
|-11||Internal drip pan|
|-12||External hose drip pan|
|-13||Flushing and sampling block|