EC-130 Flight and Servo Controls Overview

1. EC 130 B4 Initial Pilot Ground School Chapter 8 Flight Controls and Servo Controls

2. Chapter 8 - Flight Controls and Servo Controls Main Rotor Controls …………...……………………….…………...….… 8.3 Cyclic Controls ……………………………………………….…………….. 8.5 Lever Support Brackets …………………………………………………… 8.8 Mixing Unit Accessories ……….………………...………………………. 8.10 Collective Twist Grips ……..…………..………………………………….. 8.11 Twist Grip Warning Light ………………....……………………………… 8.16 Collective Controls ………………………………………………………… 8.17 Tail Rotor Controls …………………..…………………………………….. 8.21 Tail Rotor Potentiometer …………………………………………………. 8.24 Servo Controls …………………………...………..……………………….. 8.26 Servo Control Operation …………………..……………………………… 8.28 Limit Caution Light ………..…………………….…………………………. 8.35 Distribution Valve Operation - Seizure Sensing ………………………. 8.36 Servo Caution Light ………………………………………………………… 8.38 Servo Caution Light Summary ……………………………………………. 8.43 Review Questions …………………………………………………………... 8.44 8.2

3. Main Rotor Controls Relay Lever Support Brackets Mixing Unit Collective Control Rod Longitudinal Control Rod Longitudinal Torque Tube Lateral Control Rods Collective Torque Tube Lateral Synchronizer Rod Longitudinal Control Rod Lateral Control Rod Longitudinal Bellcrank Lateral Bellcrank 8.3

4. Main Rotor Controls Fore & Aft Cyclic Lateral Cyclic Collective Pitch Forward 8.4

5. Standard Cyclic Grip 8.5

6. Optional Cyclic Grip 8.6

7. Cyclic Friction Pilot’s Side Only 8.7

8. Forward Forward Lever Support Brackets Forward Limit Light Switches Collective Lever L/H Lateral Relay Longitudinal Relay R/H Lateral Relay 8.8

9. Forward Forward Cyclic Compensator Spring 8.9

10. Forward Mixing Unit Accessories Anticipator (XPC) Collective Compensator Spring 8.10

11. Electrical unit Collective Twist Grips Copilot twist grip Flight detent lock Pilot twist grip Rack gear (pilot module) Copilot module rack and pinion gear Friction adjustment Ball-end rod Input pinion (pilot module) Torque tube between collective pitch levers Cam ‘Flight’ Position “TWIST GRIP” warning light microswitch Idle detection microswitch To FADEC 8.11

12. Collective Twist Grip Hoist Cable Cutter Fixed Landing Light Float Arming Switch Landing Light Switch and Swivel Button VEMD Scroll Switch 8.12

13. The “TWIST GRIP” Throttle - can be considered as a rolling switch....you are either in the Ground Idle position (NG approx. 67%), or the Flight position. There is no modulation of the fuel, therefore, the throttle can not be used to control yaw during an in-flight (cruise) emergency. The throttle is used for starting and shutdown (IDLE), to simulate engine failures, and for hovering tail rotor failures. 8.13

14. TWT GRIP Twist Grip Components The total ‘throw’ between the idle position and the flight position is approximately 800 of travel. There are no mechanical linkages between the throttle and the fuel control, only microswitches. Idle Detection Ramp Return Coil Spring (spring loaded to “Flight” position) Idle Switch Out of ‘Flight’ Position Switch 8.14

15. TWT GRIP WARNING PANEL CORRECTIVE ACTIONS Twist grip outside flight position 8.15 Flight Manual - Emergency Procedures - Page 3-13

16. TWT GRIP WARNING PANEL CORRECTIVE ACTIONS Twist grip ……………INCREASE to “FLIGHT” position CONTINUE FLIGHT Twist grip outside flight position 8.16 Flight Manual - Emergency Procedures - Page 3-13

17. Collective Friction Friction Wheel Friction Pads Friction Plate 8.17

18. Forward Collective Friction Components Friction Plate Friction Pads 8.18

19. Forward Collective Locking The collective incorporates a sliding sleeve. When moved FWD at flat pitch the collective is locked down. To release the collective, push down on the collective, and the slider will spring back unlocking the collective. 8.19

20. Forward Collective Stop Bolts Collective Stop Bolts are used to adjust the autorotative NR. 8.20

21. Tail Rotor Controls Flexible-Ball Cable attaches to Control Rod which connects to the Pitch Control Lever. Flexible-Ball Cable from T/R pedals to fenestron. 8.21

22. Tail Rotor Pedals Secondary Stops 8.22

23. Tail Rotor Pedal Components T/R Pedal Friction Device Potentiometer (DDN) 8.23

24. Why does the EC-130 have a T / R Pedal Potentiometer? Neutral Left Pedal Right Pedal 104 103 102 101 100 99 98 400 NR Hp > 15,000 ft NF % Hp = 10,000 ft Hp = 5000 ft 386 NR Hp < 1000 ft 0 10 20 30 40 50 60 70 80 90 100 Pedal Position (DDN) % It provides Noise Reduction by varying rotor RPM 8.24

25. Aft Tail Rotor Controls 8.25

26. Servo Controls Three Double-Cylinder Servo Actuators 8.26

27. Servo Actuators Upper body (LH hydraulics) Servo Input Lever Attaching Point Lower body (RH hydraulics) 8.27

28. Servo Control Operation 8.28

29. Distributor Valve - Normal Operation The servos use a dual rotary distributor valve to channel hydraulic fluid to and from the servo. The primary distributor valve (#1) moves freely within the back-up valve (#2). Should there be a seizing between the primary and backup valves, they will move together as a single unit, continuing to supply pressurized fluid and return. When this occurs (not as a result of a hydraulic failure), a SERVO caution light will illuminate. #1 #2 8.29

30. Distributor Valve - Normal Operation Inputs are being made through the input lever (1). The primary valve (2) moves freely within the secondary valve (3), which is held in place by a three ball bearing cap (4), a lever and a spring assembly (5). 4 2 5 3 1 1 8.30

31. LIMIT If heavy flight loads are encountered, the amount of force the hydraulic system can boost may be exceeded, therefore the floating arm is forced down against the microswitch and the LIMIT caution light illuminates. Right Lateral Servo The other cause of the LIMIT light would be excessive movement of the cyclic beyond allowable limits, again causing a microswitch to depress with the LIMIT caution light illuminating. Longitudinal Load Switches 8.31

32. LIMIT WARNING PANEL CORRECTIVE ACTIONS Main servo unit max load reached or Max rotor head stress reached 8.32 Flight Manual - Emergency Procedures - Page 3-21

33. LIMIT WARNING PANEL CORRECTIVE ACTIONS In high speed cruise flight or steep maneuvers : 1. Collective ……………. Reduce power 2. Cyclic ………………… Reduce speed or load factor. Main servo unit max load reached or Max rotor head stress reached 8.33 Flight Manual - Emergency Procedures - Page 3-21

34. LIMIT WARNING PANEL CORRECTIVE ACTIONS In high speed cruise flight or steep maneuvers : 1. Collective ……………. Reduce power 2. Cyclic ………………… Reduce speed or load factor. At rearward speed or hovering in a high tail wind: 1. Cyclic ………………… Reduce rearward speed Reduce tailwind component. Main servo unit max load reached or Max rotor head stress reached 8.34 Flight Manual - Emergency Procedures - Page 3-21

35. LIMIT WARNING PANEL CORRECTIVE ACTIONS In high speed cruise flight or steep maneuvers : 1. Collective ……………. Reduce power 2. Cyclic ………………… Reduce speed or load factor. At rearward speed or hovering in a high tail wind: 1. Cyclic ………………… Reduce rearward speed Reduce tailwind component. Main servo unit max load reached or Max rotor head stress reached CONTINUE FLIGHT 8.35 Flight Manual - Emergency Procedures - Page 3-21

36. SERVO Distributor Valve Operation Seizure Sensing If a seizure within the servo occurs, then the primary rotary valve and the secondary rotary valve will move as one. The rotation of the secondary valve causes the ball bearings to rise up on a ridge, displacing a lever against a microswitch, which causes the SERVO caution light to illuminate. 8.36

37. SERVO WARNING PANEL CORRECTIVE ACTIONS Jamming of a distributor valve on a main servo unit 8.37 Flight Manual - Emergency Procedures - Page 3-15

38. SERVO WARNING PANEL CORRECTIVE ACTIONS CONTINUE FLIGHT Jamming of a distributor valve on a main servo unit 8.38 Flight Manual - Emergency Procedures - Page 3-15

39. Servo Test Switch 8.39

40. ON THE GROUND TEST (NO PRESSURE) - when depressing the servo pushbutton on the center pedestal, the SERVO light will extinguish. SERVO SERVO 8.40

41. SERVO TEST WITH HYDRAULIC SYSTEM PRESSURIZED - pressing the servo pushbutton will illuminate the SERVO light on the CWP. 8.41

42. SERVO SEIZING OF DISTRIBUTOR VALVE - the seizing of the rotary distributor valve (primary to secondary) will cause the microswitch to move, illuminating the SERVO light. 8.42

43. SERVO SERVO SERVO SERVO Servo Light Summary • The light will extinguish during the ground • test before start with no hydraulics applied. • The light will illuminate during ground test • after start-up with hydraulics applied. • [ Whether pressurized or un-pressurized, pressing the • “Servo Test” button changes the status of the • light when everything is working correctly.] • Seizure of any one of the six servo distributor valves • will cause only the light to illuminate. 8.43

44. ReviewQuestions 8.44

45. 68. What are the main components in the main rotor / tail rotor flight system controls? B. Push-pull tubes and bell cranks / flexball cable and a push-pull tube.

46. 69. What is the purpose of the mixing unit? D. Sum (add) the cyclic inputs with the collective inputs.

47. 70. Which main rotor servo moves to pitch the aircraft nose up or down? A. The left forward servo.

48. 71. What adjustments need to be made for an autorotation rpm change IAW Section 8 of the Flight Manual? D. Low pitch adjustment stop / lock strip (down-stop bolt).

49. 72. How many hydraulic servos are utilized in the EC130 B4? A. Three dual bodied servos.

50. 73. When the pilot inputs control forces through the flight controls to the servo stops, where does the distributor valve stop? D. Hydraulic zero.