Chinook CH-47/Systems
SECTION 2. SYSTEMS
Contents
1 Helicopter
1.1 General
The Shergood CH-47D is a twin-turbine engine tandem rotor helicopter designed for transportation of cargo, troops and weapons during day, night, visual and instrument conditions. The heicopter is powered by two T550GA-714A shaft-turbine engines on the aft fuselage. Each engine drives a separate engine transmission. Drive shafts from each engine transmission is connected to a shared combining transmission which in turn drives the forward and aft transmissions. The forward transmission is housed in the forward pylon above the cockpit, the combining transmission is housed on the forward side of the aft pylon, and the aft transmission is also housed in the aft pylon behind the combining transmission. When the rotors are not turning, and APU (Auxilary Power Unit) can be used to supply electrical power and hydraulic pressure. Fuel is carried in pods on the sides with main, forward auxilary and aft auxilary tanks on each side. An entrance door is located on the forward right side of the main cabin, while a hydraulically powered ramp is in the back.
1.2 Gross Weight
The maximum gross weight is 50,000 pounds.
1.3 Landing Gear Systems
The landing gear system consists for four non-retractable landing gears mounted on the fuselage pods. The forward gear a fixed with twin wheels. The aft landing gears are single wheels mounted on swivels. In addition, the aft right gear can be steered from the cockput to improve ground handling. Landing Gear Proximity Switches Proximity switches are mounted on each aft landing gear. GROUND CONTACT lights on the maintenance panel in the aft rear of the helicopter indicate when the switches have been activated. While ground contact switches are activated, the trim system will position the forward and aft rotors on GND position for better ground handling.
1.4 Steering and Swivel Lock System
The ground steering control panel (see Figure 1) is located on the center panel between the pilot and co-pilot seats. The ground steering mode is controlled by a three position switch with the following positions:
- STEER - Active steering of the right rear wheel.
- UNLOCK - Free castering of the rear wheels.
- LOCK - Rear wheels locked in straight forward position.
The steering system is powered by the utility hydraulic system. In addition the PWR STEER switch on the upper console must also be in the ON position to use ground steering, or change the active steering mode. When the STEER steering mode is selected, the "keyboard" control mode is active, and the helicopter is in ground contact, the left/right arrow keys that normally control lateral cyclic will switch to controling the wheel position displayed as pedal inputs.
1.5 Parking Brake
A parking brake is located below the lower left corner of the pilot-side instrument panel. Click the parking brake to pull or push the handle. A green "PARK BRAKE ON" capsule will illuminate to indicate the parking brake is engaged. The parking brake requires hydraulic pressure from the utility system, and for the PWR STEER switch to be in the ON position to activate or deactivate. If there is no hydraulic pressure, the parking brake handle can still be pulled or pushed, but the brakes will not engage.
1.6 Pilot-Side Instrument Panel
| 1. Cruise Guide Indicator (CGI) | 2. Airspeed Indicator | 3. Radio Call Sign Plate | 4. Master Caution Light |
| 5. Attitude Indicator | 6. Altimeter | 7. Vertical Speed Indicator (VSI) | 8. Radar Altimeter Dimmer Knob |
| 9. Cockpit Air Knob (display only) | 10. Turn and slip indicator | 11. VGI (Vertical Gyro Indicator) mode switch | 12. Horizontal Situation Indicator (HSI) |
| 13. Marker Beacon Lights | 14. Radar Altimeter | 15. Chronometer | 16. Rotor tachometer (RPM) |
| 17. Torquemeter | 18. CGI (Cruise Guide Indicator) test switch |
1.7 Co-Pilot-Side Instrument Panel
| 1. Torquemeter | 2. Airspeed Indicator | 3. Attitude Indicator | 4. Altimeter |
| 5. Master Caution Light | 6. Radio Call Sign Plate | 7. Radar Altimeter Dimmer Knob | 8. Vertical Speed Indicator (VSI) |
| 9. Turn and slip indicator | 10. VGI (Vertical Gyro Indicator) mode switch | 11. Horizontal Situation Indicator (HSI) | 12. Chronometer |
| 13. Radar Altimeter | 14. Cockpit Air Knob (display only) | 15. Rotor tachometer (RPM) |
1.8 Center Instrument Panel
| 1. IFF Failed Indicator Light | 2. Transponder Cypher Active Indicator Light | 3. FIRE PULL handles (Fuel Shut-Off) | 4. Fire Detection Test Switch |
| 5. Agent Discharge Switch | 6. Gas Producer (N1) Tachometer | 7. Power Turbine Inlet Temp. (PTIT) Indicator | 8. Transmission Oil Pressure Indicator |
| 9. Transmission Oil Pressure Selector | 10. Longitudinal Cyclic Trim Indicators | 11. Transmission oil temperature indicator | 12. Fuel flow indicator |
| 13. Transmission oil temperature selector | 14. Fuel quantity indicator | 15. Fuel quantity selector | 16. Caution light and antenna selector |
| 17. Engine Oil Pressure Indicators | 18. Engine Oil Temperator Indicators | 19. Caution/Advisory Panel | 20. GPS Alert Indicator |
| 21. GPS Zeroize Switch |
2 Emergency Equipment
2.1 Engine Fire Detection System
The engine fire detection/extinguisher system is designed to extinguish fires in the engine compartment only. The system (see Figure 5) is comprised of two FIRE PULL handles, indicator lights on each handle, an agent discharge switch, a FIRE DETR test switch, and two fire extinguisher agent containers. When a fire is detected in an engine, a light reading "FIRE PULL FUEL SHUT-OFF" will illuminate on the handle for the affected engine. To discharge agent into an engine, first pull the handle to select the engine, then move the AGENT DISCH rocker switch to select a bottle to be discharged. Power is supplied to the fire detection and #1 and #2 extinguisher systems through the #1 and #2 DC buses, respectively.
To perform a system test and check the warning lights, the FIRE DETR switch can be placed in the TEST position. If the system is functioning properly, the "FIRE PULL" indication on both handles will illuminate.
2.2 TROOP WARN Panel
Two troop alarm and jump light boxes are mounted in the rear of the aircraft. The forward box is mounted near the ceiling to the left of the cockpit entrance. The aft box is mounted to the right side of the ramp in the rear of the aircraft. Each box is comprised of an electrical bell and a red and green light fixture on either side. The troop alarm system is controlled through a panel on the overhead switch panel (see Figure 6). A three position switch controls which light is illuminated, and a switch turns the bell on or off. Indicator lights on the panel indicate when either light is illuminated.
The troop warning panel can service multiple purposes. It can be used to warn troops to keep clear of APU during engine start, to indicate emergency situations with predetermined signals, or to indicate when the aircraft is over a drop zone.
3 Engines and Related Systems
3.1 General
The Shergood CH-47D is equipped with two T55-GA-714A engines mounted in separate nacelles on either side of the aft pylon. Each engine is capable of producing up to 4,867 shaft horse power. The compressor is comprised of 7 axial stages and one centrifugal stage. Hot gasses leaving the combustor power a two stage turbine driving the compressor and a two stage power output turbine. The engine is kept lubricated by a 12 quart oil tank located at the inlet side of the engine. Floats in the oil reservoir activate the low oil caution lights when the oil is below minimum capacity.
3.2 Engine Condition Levers
The engine condition levers (ECL) are located in the overhead switch panel (see Figure 7). Each ECL has OFF, ground (GND) and flight(FLT) positions. ECLs should be in the GND position for engine start, and set to the OFF position to shut down the engine.
3.3 FADEC Description
The CH-47D engines are controlled by dual FADEC (Fully Authority Digital Engine Control) units, one for each engine. The FADEC oversees engine start and maintains proper operating RPM during flight. The control panel for the FADECs is located on the upper switch panel and is shown shown in Figure 8. The FADEC for each engine can be operated in primary (PRI) or revisionary (REV) mode. Two switches control the mode the respective FADEC. In normal operation, primary mode should be used. Reversionary mode can be used in the event of failure of the primary system. Engine RPM will not be as stable using revisionary mode.
An Nr selector can be used to select the target rotor RPM between 97% and 103%. In normal use, 100% should be selected. The 97% setting can be used during water operations to reduce spray.
The FADEC units are normally powered with dedicated alternators on each engine. The backup power switch (labeled B/U POWER) when ON enables the FADEC units to be powered from the aircraft battery bus as well. The B/U POWER switch should always be ON during engine operation.
The LOAD SHARE switch selects between PTIT (turbine inlet temperature) and torque matching for sharing load between engines. Torque matching is normally the preferred option. Load sharing may not be as accurate in PTIT mode.
The ENG START switch is used to begin the start sequence. It is a three position rocker switch allowing only one engine to be started at a time. Press and hold the ENG START on the 1 or 2 position to start the indicated engine. In order for start to be successful, the target engine must have fuel pressure, AC power must be energized, and there must be utility hydraulic pressure available. The FADEC ensures that these start conditions are met before engaging the starter motor.
3.4 DECU
Two DECU units (see Figure 9), one for each engine, are mounted in the aft portion of the airframe near their respective engines. The DECUs contain the electronics for the primary and revisionary modes. Each DECU contains a two-digit hexadecimal BIT display indicating the operating status of the DECU.
On power-up, the DECU will undergo a self-check and systems check. During start, the BIT display will display 88 to indicate a successful start, or a fault code to indicate an error in the FADEC.
3.5 Engine Instruments and Cautions
The engine instruments are the N1 tachometer, the dual torquemeter, power turbine inlet temperature (PTIT), fuel flow, oil pressure and oil temperature indicators.
The N1 tachometers, PTIT, oil pressure and oil temperature instruments are located in separate columns on the left side of the center instrument panels. The torquemeter is located in the pilot and copilot instrument clusters and has one needle for each engine. The fuel flow gauge is located on the right side of the center console.
For each engine, the following caution capsules illuminate in abnormal conditions:
- ENG 1(2) OIL LOW. This is illuminated when approximately 2 quarts of usable oil remains.
- ENG 1(2) CHIP DET. This is illuminated when metal particles in the oil system bridge a magnetic gap. If caution may indicate an impending engine failure.
- ENG 1(2) FAIL. This indicates an engine failure during start, or during flight.
