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EC 130 B4 Initial Pilot Ground School Chapter 9 Hydraulic System

EC 130 B4 Initial Pilot Ground School Chapter 9 Hydraulic System. Chapter 9 - Hydraulic System Hydraulic System - General …...……………………….…………...….… 9.3 Technical Characteristics ….……………………………….…………….. 9.5 Hydraulic System Schematic ……..……………………………………… 9.6

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EC 130 B4 Initial Pilot Ground School Chapter 9 Hydraulic System

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  1. EC 130 B4 Initial Pilot Ground School Chapter 9 Hydraulic System

  2. Chapter 9 - Hydraulic System Hydraulic System - General …...……………………….…………...….… 9.3 Technical Characteristics ….……………………………….…………….. 9.5 Hydraulic System Schematic ……..……………………………………… 9.6 Hydraulic Reservoirs …………....………………...………………………. 9.7 Hydraulic Manifolds ………..…………..………………………………….. 9.10 Hydraulic Filter Assembly ………………....……………………………… 9.13 Servo Actuators …………..………………………………………………… 9.14 Normal Operation ……...……………..…………………………………….. 9.15 Lower System Failure ……...………………………………………………. 9.16 Upper System Failure …………………...………..……………………….. 9.17 Hydraulic and Servo Caution Lights ……..……………………………… 9.22 Hydraulic Caution Light Summary …………...…………………………. 9.26 Review Questions …………………………………………………………... 9.27 9.2

  3. Tandem Reservoirs Tandem Reservoirs Hydraulic System - General Dual Hydraulic Systems are totally isolated from each other Three dual-body tandem mounted servo controls Aft pump is belt driven from the engine to MGB driveshaft Aft pump is belt driven from the engine to MGB driveshaft Forward pump directly driven from MGB 9.3

  4. General Overview of the Hydraulic System: • Dual hydraulic systems are totally isolated from each other • RH - pressure to lower servo bodies • RH - belt driven pump (as in AS350) • RH - reservoir is the forward of the two tanks • LH - pressure to upper servo bodies • LH - direct drive pump from MGB bevel gear • LH - reservoir is the rear of the two tanks • NO accumulators in the EC130 B4 hydraulic system • Tail rotor system is not boosted - there is no servo • Should either system fail, the flight controls remain boosted • from the other system for continued normal flight • Dual body, tandem mounted main servos • Common control input from flight controls • Rotary distribution valves 9.4

  5. Technical Characteristics MIL H5606 fluid NOT certified Hydraulic fluid is routed through the conical portion of the transmission housing for pre-heating purposes. 9.5

  6. Hydraulic System Schematic AFT FWD LH RH 9.6

  7. Hydraulic Reservoirs Front Reservoir Rear Pump R/H Manifold Lower Bodies Rear Reservoir Front Pump L/H Manifold Upper Bodies 9.7

  8. Forward Left Hand / Upper System Pump 9.8

  9. Right Hand / Lower System Pump 9.9

  10. Hydraulic Manifolds Regulation Valve 35 Bars Pressure Switch < 20 Bars Clogging Indicator > 2.7 Differential Pressure Filter 3 Micron Note: Both units are identical 9.10

  11. L/H Hydraulic - Upper System Manifold “Pop-Out” Clogging Indicator is here. 9.11

  12. R/H Hydraulic - Lower System Manifold “Pop-Out” Clogging Indicator is here. 9.12

  13. Hydraulic Filter Assembly with Clogging Indicator 3 Micron with No Bypass “Popped” Indicator Button 9.13

  14. Servo Actuators Upper body (LH hydraulics) Servo Input Lever Attaching Point Lower body (RH hydraulics 9.14

  15. Normal Operation 9.15

  16. Lower System Failure RH Belt Driven 9.16

  17. Upper System Failure LH MGB Driven 9.17

  18. SERVO HYDR WARNING PANEL CORRECTIVE ACTIONS + Loss of hydraulic pressure in one circuit. 9.18 Flight Manual - Emergency Procedures - Page 3-15

  19. SERVO HYDR WARNING PANEL CORRECTIVE ACTIONS Keep aircraft to a more or less level attitude Avoid abrupt maneuvers Maintain angle of bank lower than 300 Maintain IAS below 110 kt (or VNE if lower) Normal approach and landing + Loss of hydraulic pressure in one circuit. 9.19 Flight Manual - Emergency Procedures - Page 3-15

  20. SERVO HYDR LIMIT WARNING PANEL CORRECTIVE ACTIONS Keep aircraft to a more or less level attitude Avoid abrupt maneuvers Maintain angle of bank lower than 300 Maintain IAS below 110 kt (or VNE if lower) Normal approach and landing NOTE light may be on if RH circuit failed or during load factor maneuvers One remaining circuit allows continued safe flight and landing + Loss of hydraulic pressure in one circuit. [ Note: The Flight Manual is incorrect. “RH” should say “LH” ] 9.20 Flight Manual - Emergency Procedures - Page 3-15

  21. SERVO HYDR LIMIT WARNING PANEL CORRECTIVE ACTIONS Keep aircraft to a more or less level attitude Avoid abrupt maneuvers Maintain angle of bank lower than 300 Maintain IAS below 110 kt (or VNE if lower) Normal approach and landing NOTE light may be on if RH circuit failed or during load factor maneuvers One remaining circuit allows continued safe flight and landing + Loss of hydraulic pressure in one circuit. [ Note: The Flight Manual is incorrect. “RH” should say “LH” ] LAND AS SOON AS PRACTICABLE 9.21 Flight Manual - Emergency Procedures - Page 3-15

  22. SERVO HYDR LIMIT WARNING PANEL CORRECTIVE ACTIONS Keep aircraft to a more or less level attitude Avoid abrupt maneuvers Maintain angle of bank lower than 300 Maintain IAS below 110 kt (or VNE if lower) Normal approach and landing NOTE light may be on if RH circuit failed or during load factor maneuvers One remaining circuit allows continued safe flight and landing + Loss of hydraulic pressure in one circuit. [ Note: The Flight Manual is incorrect. “RH” should say “LH” ] LAND AS SOON AS PRACTICABLE CAUTION Under high load factor, servocontrol reversibility can be encountered. 9.22 Flight Manual - Emergency Procedures - Page 3-15

  23. LIMIT LIMIT LIMIT Left Hand Hydraulic Fluid is used to support the upper Right Hand roll servo rod end bearing. When the Left Hand Hydraulic system fails with the rotor turning, the rod end bearing drops against the limit light switch, thereby activating the light. Why does the light illuminate with a Left Hand hydraulic system failure? 9.23

  24. Each hydraulic system (LH for upper bodies, RH for lower bodies) provides pressure to keep a plunger and spring from displacing the secondary distributor valve, causing the SERVO caution light to illuminate. SERVO SERVO SERVO Why does the light illuminate with a hydraulic failure? 9.24

  25. SERVO SERVO Should a hydraulic failure occur, the loss of pressure in the system will allow for the plunger to move due to a spring force, displacing an arm attached to the secondary rotary valve, causing the SERVO light to illuminate on the CWP (in addition to the HYDR light). Hydraulic Failure Seizure of at least one of six distributor valves illuminates the SERVO light. 9.25

  26. SERVO HYDR LIMIT SERVO HYDR Hydraulic & Servo Light Summary • Loss of hydraulic pressure in the lower system will • cause the HYD P light and SERVO light to illuminate. • Loss of hydraulic pressure to the upper system will • cause the HYD P, SERVO & LIMIT lights to • illuminate. 9.26

  27. Review Questions 9.27

  28. 81. The hydraulic fluid tubing is routed through a certain component just prior to going to the servos. What component is this, and why is the fluid routed through it? C. Conical housing of the transmission; to pre-heat the hydraulic fluid.

  29. 82. Does the hydraulic filter have by-pass capability? B. No

  30. 83. What cockpit indicators notify the pilot of a loss of hydraulic pressure in one circuit? D. HYDR light and a SERVO light illuminating. If the LH circuit has failed you will also have the LIMIT light illuminated.

  31. 84. When experiencing a loss of hydraulic pressure in one circuit, which of the following landing recommendations is indicated in the emergency procedures? C. LAND AS SOON AS PRACTICABLE

  32. EC 130 B4 Initial Pilot Ground School End of Chapter 9 Hydraulic System

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