CPT MURPHY, NYARNG Copyright 1995

CPT MURPHY, NYARNG Copyright 1995
COMMAND INSTRUMENT SYSTEM CPT MURPHY, NYARNG Copyright 1995 DOPPLER MODE N W S E 3 6 12 15 21 24 30 33 HDG CRS 4 COURSE KM 2 1 ROLL COMMAND BAR is also providing a straight line, wind drift corrected course, to the station / waypoint selected. 30 CLI MB G S 30 30 DI VE NAV MODE SEL DPLR VOR ILS BACK CRS FM HOME TURN RATE CRS HDG VERT GYRO BRG 2 NORM ALTER PLT CPLT ADF VOR CIS MODE SEL HDG ON NAV ALT Provides a COURSE DEVIATION BAR and COURSE DEVIATION POINTER which will provide a visual display of where the course lies in relationship to the helicopter. 1

COMMAND INSTRUMENT SYSTEM CPT MURPHY, NYARNG Copyright 1995 BACK COURSE APPROACH 4 33 KM COURSE 33 N 3 2 1 30 CLI MB 6 30 W E 24 12 1 2 21 S 15 HDG CRS 30 30 DI VE MODE SEL VOR ILS BACK CRS FM HOME DPLR VOR ILS DPLR BACK CRS FM HOME During localizer back course approaches and back course selected the course deviation bar, course deviation pointer and cyclic roll command bar will remain directional at all times. CIS MODE SEL HDG ON NAV ALT NORM ALTER PLT CPLT NORM ALTER ADF VOR TURN RATE CRS HDG VERT GYRO BRG 2 The ALT HOLD must be manually deselected due to the lack of glideslope information. 2

COMMAND INSTRUMENT SYSTEM CPT MURPHY, NYARNG Copyright 1995 GO-AROUND FUNCTION GA Follow for a level attitude. 30 CLI MB Go-Around enable switch 30 30 The go-around mode is disengaged by changing to any other mode on the pilot's CIS mode selector or VSI/HSI mode selector. DI VE MODE SEL VOR ILS BACK CRS FM HOME DPLR Automatically adjusts for a feet rate of climb when properly followed. VOR ILS DPLR BACK CRS FM HOME 5 seconds after the GA switch is pressed, the CISP will provide an adjusted cyclic pitch command bar, which, when followed, will result in an 80 KIAS for climbout. HDG NAV ALT NORM ALTER PLT CPLT NORM ALTER ADF VOR HDG NAV ALT ON ON ON CIS MODE SEL TURN RATE CRS HDG VERT GYRO BRG 2 3

COMMAND INSTRUMENT SYSTEM CPT MURPHY, NYARNG Copyright 1995 MULTIPLE FUNCTION ILS APPROACH DH MB 4 33 KM N COURSE 33 3 2 1 30 CLI MB 30 6 Raw data course deviation bar W E 24 12 Raw data glide slope indicator 1 2 21 15 S HDG CRS 30 30 DI VE Raw data course deviation pointer Remember the CPI and roll & pitch command bars are processed data instruments and you should cross check your raw data instruments to ensure accuracy. MODE SEL VOR ILS BACK CRS FM HOME DPLR HDG NAV ALT VOR ILS DPLR BACK CRS FM HOME HDG NAV ALT ON ON ON NORM ALTER PLT CPLT NORM ALTER ADF The HDG mode will remain on until aircraft enters the capture zone of the ILS. When aircraft enters the capture zone the HDG mode will drop off. The roll command bar will then receive its signals from the ILS receiver. CIS MODE SEL TURN RATE CRS HDG VERT GYRO BRG 2 When ALT mode is on, the collective position indicator will be used to hold present altitude. When glide slope interception occurs the ALT mode will drop off, and the collective position indicator will automatically change to ILS mode to maintain glide slope position. 4

COMMAND INSTRUMENT SYSTEM CPT MURPHY, NYARNG Copyright 1995 Illuminates when over flying any marker beacon. ILS NAVIGATION N W S E 3 6 12 15 21 24 30 33 HDG CRS 4 COURSE KM 2 1 DH MB Processed ILS data indicators 30 CLI MB APPROACH MODE (submode of ILS Mode) provides cyclic ROLL COMMAND of not more than +/-15 degrees to track localizer. COLLECTIVE POSITION INDICATOR provides glide slope free of oscillation with no more than 1 overshoot. 30 30 DI VE NOTE MODE SEL DPLR VOR ILS BACK CRS FM HOME TURN RATE CRS HDG VERT GYRO BRG 2 NORM ALTER PLT CPLT ADF VOR Prior to conducting an ILS approach ensure that both the pilot and copilot's radar altimeters LOW bug markers are set below the DH for that approach or the CIS will go into a LEVEL OFF mode directing the collective position indicator to maintain altitude based on the higher radar altimeter LOW bug marker, causing the raw data glideslope indicator to show aircraft above glide slope but the collective position indicator (CPI) showing on glide slope. CIS MODE SEL HDG ON NAV ALT Provides a pitch command bar that when followed will maintain airspeed within 5 KNOTS, provides a ROLL COMMAND BAR that when followed will intercept localizer course with no more than 1 OVERSHOOT at 10 MILES and 100 KNOTS to not more than 2 OVERSHOOTS at 5 to 20 MILES at AIRSPEEDS of 70 to 130 KNOTS. 5

COMMAND INSTRUMENT SYSTEM CPT MURPHY, NYARNG Copyright 1995 VOR NAVIGATION 4 33 KM N COURSE 33 3 2 1 30 CLI MB 30 6 W E 24 12 1 2 21 15 S HDG CRS 30 30 DI VE MODE SEL LEVEL-OFF MODE (VOR/ILS MODES) is selected and aircraft descends below P/CP LO BUG on radar altimeter the aircraft will maintain +/-10 FEET below 250 FEET AGL and +/-20 FEET above 250 FEET AGL when properly followed. VOR ILS BACK CRS FM HOME DPLR CIS MODE SEL HDG ON NAV ALT VOR ILS DPLR BACK CRS FM HOME NORM ALTER PLT CPLT NORM ALTER VOR TURN RATE CRS HDG VERT GYRO BRG 2 When intercepting the capture zone (+\- 10 degrees) of the selected course it provides a 45 degree intercept of selected radial with not more than 1 OVERSHOOT at 10 MILES and 100 KNOTS, and not more than 2 OVERSHOOTS at 5 to 40 MILES and 70 to 140 KNOTS. VOR NAV Mode also provides WIND DRIFT CORRECTION. 6

COMMAND INSTRUMENT SYSTEM CPT MURPHY, NYARNG Copyright 1995 ALTITUDE HOLD OPERATION 4 33 KM COURSE 33 N 3 2 1 30 CLI MB 30 6 NAV W E 24 12 1 2 21 S 15 G S HDG CRS 30 30 DI VE NAV MODE SEL DPLR VOR ILS BACK CRS FM HOME TURN RATE CRS HDG VERT GYRO BRG 2 NORM ALTER PLT CPLT ADF VOR CIS MODE SEL HDG ON NAV ALT Adjust collective as required to keep the collective position indicator between the two arrows. Maintain altitude within 50 FEET, when properly followed - must be selected with a rate of climb or descent of not more than 200 FEET PER MINUTE to indicate correctly. Designed to operate from feet to +10,000 feet at an airspeed of 70 to 150 KNOTS. 7

COMMAND INSTRUMENT SYSTEM CPT MURPHY, NYARNG Copyright 1995 MANUAL HEADING OPERATION HEADING SELECT MARKER 4 33 KM COURSE 33 N 3 2 1 30 CLI MB 30 6 NAV W E 24 12 1 2 21 15 G S S HDG CRS 30 30 DI VE NAV MODE SEL VOR ILS BACK CRS FM HOME DPLR DPLR VOR ILS BACK CRS FM HOME HDG NAV ALT NORM ALTER PLT CPLT NORM ALTER ADF VOR HDG NAV ALT ON ON ON CIS MODE SEL TURN RATE CRS HDG VERT GYRO BRG 2 8

MODE SELECT PANEL OPERATIONAL RULE OF 5
COMMAND INSTRUMENT SYSTEM CPT MURPHY, NYARNG Copyright 1995 MODE SELECT PANEL OPERATIONAL RULE OF 5 N W S E 3 6 12 15 21 24 30 33 HDG CRS NAV 4 COURSE KM H D G 2 1 (a) No. 1 Bearing pointer: Doppler/GPS (b) No. 2 Bearing pointer: ADF VOR (c) Course deviation bar (HSI): Doppler VOR Localizer GA DH MB (d) Course deviation pointer (VSI): Doppler VOR Localizer FM Home (has priority) CMD ATT 30 CLI MB G S (e) Roll command bar (VSI): Doppler VOR Localizer FM Home Heading 30 30 DI VE NAV 9

COMMAND INSTRUMENT SYSTEM CPT MURPHY, NYARNG Copyright 1995 N W S E 3 6 12 15 21 24 30 33 HDG CRS NAV 4 COURSE KM H D G 2 1 GA DH MB CMD ATT 30 CLI MB G S 30 30 DI VE NAV MODE SEL DPLR VOR ILS BACK CRS FM HOME TURN RATE CRS HDG VERT GYRO BRG 2 NORM ALTER PLT CPLT ADF VOR CIS MODE SEL HDG ON NAV ALT 10

UH-60 NOSE COMPARTMENT COMPONENTS
CPT MURPHY, NYARNG Copyright 1995 #1 AND #2 SIGNAL DATA CONVERTERS KY 58 FM #1 KY 58 UHF KY 58 FM #2 STABILATOR COMPARATOR TEST PANEL ROTOR OVERSPEED RESET AUDIBLE WARNING SIGNAL UNIT DIMMING CONTROL NVG LIGHTS AN/ARN 123V VOR/ILS/MARKER BEACON ARN 89 DIRECTION FINDER SET (ADF) ASN 43 GYRO MAGNETIC COMPASS DIMMING CONTROL NVG LIGHTS SAS 2/FPS COMPUTER SAS 1 AMP APR 39 C I S COPILOT'S TURN RATE GYRO ROLL PILOT'S TURN RATE GYRO Y A W DOPPLER ASN 128 P R O C E S S O R KIT1 AorC SAS 2 RATE GYROS IF EME MODIFIED GYROS WILL BE INCLOSED IN ONE BOX. #2 VERTICAL GYRO #1 VERTICAL GYRO Instruments Communications SAS/FPS Navigation NVG Lighting Aircraft Survivability Equipment Pilot Warning and Limitation Equipment 11

UH-60 PNEUMATIC SYSTEM DIAGRAM
CPT MURPHY, NYARNG Copyright 1995 COCKPIT VENT BLOWER OPERATION AMBIENT AIR BLOWER MOTOR (TEMPERATURE SWITCH SHUTS BLOWER OFF AT 120 DEGREES (C) ENGINE INLET ANTI-ICE MODULATING VALVE TO ICE DETECTOR PROBE HEATER TO CABIN TO EXTENDED RANGE AUX FUEL SYSTEM (14-18 PSI) Overtemp Sensor (90 to 96 C) AIR SOURCE HEAT / START ENGINE APU O F F HEATER CROSS BLEED VALVE VENT BLOWER START CONTROL VALVE O F F O F F OFF HI ON ON With heater ON maximum torque available is reduced by 4%, and fuel flow is increased 20 LBS per hour. 12

CPT MURPHY, NYARNG Copyright 1995 ENGINE ANTI-ICE SYSTEM ENGINE INLET ANTI-ICE MODULATING VALVE Bleed air is continually supplied to the aft probe through holes in the side to create a venturi effect for proper ice detection even at a hover. TO ICE DETECTOR PROBE #2 ENG INLET ANTI-ICE ON (1) Above 13 degrees C (55F) - Illumination of the ENG INLET ANTI-ICE advisory light indicates a system malfunction. (2) Above 4 degrees C (39F) to 13 degrees C (55F) - the ENG INLET ANTI-ICE advisory light may or may not illuminate. (3) At 4 degrees C (39F) and below - Failure of ENG INLET ANTI-ICE advisory light to illuminate indicates a system malfunction. Do not fly the aircraft in known icing conditions. #2 ENG ANTI-ICE ON when ENG ANTI-ICE is ON there will be a 16% reduction in maximum torque available for the effected engine. The fuel flow will increase 60 LBS per hour. THERMAL SWITCH ENGINE ANTI-ICE VALVE ENG ANTI-ICE NO. 1 NO. 2 #1 ENG INLET ANTI-ICE ON #1 ENG ANTI-ICE ON O F F O F F ON ON When ENG ANTI-ICE switche(s) are ON and ambient temperature (sensed at the Ambient Sense Port) is below +4 C degrees the ENGINE INLET ANTI_ICE MODULATING VALVE opens and allows bleed air to enter the ENG INLET fairing. When the fairing temperature reaches +93 C, ENG INLET ANTI-ICE ON advisory light illuminates. Electrically closed; will open when switch is turned on (Advisory light - on) or low power setting until 88%-92% NG (Advisory light - off). Also during AC power failure. 13

CPT MURPHY, NYARNG Copyright 1995 STARTING #2 ENGINE WITH APU CLOSES HEATER VALVE IF OPEN WHEN STARTER IS PRESSED,UNTIL STARTER DROP OUT. #2 ENG INLET ANTI-ICE ON ENGINE INLET ANTI-ICE MODULATING VALVE ICE DETECTOR PROBE #2 ENG ANTI-ICE ON ENGINE ANTI-ICE VALVE TO EXTENDED RANGE FUEL SYSTEM (14-18 PSI) #2 ENGINE STARTER #1 ENGINE STARTER CROSS BLEED VALVES AIR SOURCE HEAT / START START CONTROL VALVE ENGINE O F F APU ENGINE INLET ANTI-ICE MODULATING VALVE CLOSED on pre-flight , if open, bleed air can exit causing Hot Start or failed APU. ENGINE ANTI-ICE VALVE PNEUMATIC SOURCE INLET PORT Min: 40psig and 30ppm at 149 C Max: 50psig at 249 C #1 ENG INLET ANTI-ICE ON #1 ENG ANTI-ICE ON ENABLES CIRCUIT TO START BYPASS VALVE TO CLOSE WHEN STARTER IS PRESSED, UNTIL STARTER DROP OUT. 14

CPT MURPHY, NYARNG Copyright 1995 CROSSBLEED START #1 ENGINE WITH #2 ENGINE CLOSES HEATER VALVE IF OPEN WHEN STARTER IS PRESSED,UNTIL STARTER DROP OUT. #2 ENG INLET ANTI-ICE ON ENGINE INLET ANTI-ICE MODULATING VALVE ICE DETECTOR PROBE #2 ENG ANTI-ICE ON ENGINE ANTI-ICE VALVE TO EXTENDED RANGE FUEL SYSTEM (14-18 PSI) #2 ENGINE STARTER #1 ENGINE STARTER AIR SOURCE HEAT / START CROSS BLEED VALVES START CONTROL VALVE ENGINE O F F APU ENGINE INLET ANTI-ICE MODULATING VALVE CLOSED on pre-flight , if open, bleed air can exit causing Hot Start or failed APU. ENGINE ANTI-ICE VALVE PNEUMATIC SOURCE INLET PORT Prior to crossbleed starts the engine ANTI-ICE light must be off, and the operating engine must be at least 90% NG speed and rotor speed at 100% RPMR. Above 14,000 feet, press starter switch with ENG POWER CONT lever OFF, until the maximum motoring speed (about 24%) is reached, before going to IDLE. Min: 40psig and 30ppm at 149 C Max: 50psig at 249 C #1 ENG INLET ANTI-ICE ON #1 ENG ANTI-ICE ON 15

CPT MURPHY, NYARNG Copyright 1995 CABIN HEATER OPERATION AMBIENT AIR ENGINE ANTI-ICE ON advisory lights will be ON any time the respective engine is operating between 88-92% NG or below regardless of ANTI-ICE switch position. Do not use vent blower for heater operation. VENT BLOWER MOTOR ENGINE INLET ANTI-ICE MODULATING VALVE TO ICE DETECTOR PROBE HEATER #2 ENG INLET ANTI-ICE ON #2 ENG ANTI-ICE ON TO CABIN TO EXTENDED RANGE AUX FUEL SYSTEM (14-18 PSI) Overtemp Sensor (90 to 96 C) AIR SOURCE HEAT / START HEATER CROSS BLEED VALVES VENT BLOWER ENGINE START CONTROL VALVE O F F O F F O F F OFF HI APU ON ON ENGINE ANTI-ICE VALVE #1 ENG INLET ANTI-ICE ON With heater ON maximum torque is reduced by 4%, and fuel flow is increased 20 LBS per hour. #1 ENG ANTI-ICE ON 16

CPT MURPHY, NYARNG Copyright 1995 UH-60 PNEUMATIC SYSTEM DIAGRAM DUAL ENGINE START WITH APU MAXIMUM CONDITIONS: 6000 PA AND/OR 25 DEGREES C CLOSES HEATER VALVE IF OPEN WHEN STARTER IS PRESSED,UNTIL STARTER DROP OUT. #2 ENG INLET ANTI-ICE ON ENGINE INLET ANTI-ICE MODULATING VALVE ICE DETECTOR PROBE #2 ENG ANTI-ICE ON ENGINE ANTI-ICE VALVE TO EXTENDED RANGE FUEL SYSTEM (14-18 PSI) #2 ENGINE STARTER #1 ENGINE STARTER CROSS BLEED VALVES AIR SOURCE HEAT / START START CONTROL VALVE ENGINE O F F APU ENGINE INLET ANTI-ICE MODULATING VALVE CLOSED on pre-flight , if open, bleed air can exit causing Hot Start or failed APU. ENGINE ANTI-ICE VALVE PNEUMATIC SOURCE INLET PORT Min: 40psig and 30ppm at 149 C Max: 50psig at 249 C #1 ENG INLET ANTI-ICE ON #1 ENG ANTI-ICE ON ENABLES CIRCUIT TO START BYPASS VALVE TO CLOSE WHEN STARTER IS PRESSED, UNTIL STARTER DROP OUT. 17

UH-60 PNEUMATIC SYSTEM DIAGRAM STARTING #2 ENGINE WITH APU
CPT MURPHY, NYARNG STARTING #2 ENGINE WITH APU CLOSES HEATER VALVE IF OPEN closes start bypass valve on APU #2 ENGINE STARTER #1 ENGINE STARTER CROSS BLEED VALVE AIR SOURCE HEAT / START START CONTROL VALVE ENGINE O F F CLOSED on pre-flight , if open, bleed air can exit causing Hot Start or failed APU. APU PNEUMATIC SOURCE INLET PORT Min: 40psig and 30ppm at 149 C Max: 50psig at 249 C ENABLES CIRCUIT TO START BYPASS VALVE TO CLOSE WHEN STARTER IS PRESSED. 18

CPT MURPHY, NYARNG Copyright 1995 UH-60 PNEUMATIC SYSTEM DIAGRAM BLOWER MOTOR (DO NOT USE DURING HEATER OPERATION) TO ICE DETECTOR PROBE AMBIENT AIR ENGINE INLET ANTI-ICE MODULATING VALVE Bleed air is continually supplied to the probe through holes in the left side to create a venturi effect for proper ice detection even at a hover. HEATER #2 ENG INLET ANTI-ICE ON #2 ENG ANTI-ICE ON TO CABIN TO EXTENDED RANGE AUX FUEL SYSTEM (14-18 PSI) Overtemp Sensor (90 to 96 C) #2 ENGINE STARTER With heater ON maximum torque available is reduced by 4%, and fuel flow is increased 20 LBS per hour. #1 ENGINE STARTER AIR SOURCE HEAT / START ENGINE APU O F F when ENG ANTI-ICE is ON there will be a 16% reduction in maximum torque available for the effected engine. The fuel flow will increase 60 LBS per hour. CROSS BLEED VALVE START CONTROL VALVE #1 ENG INLET ANTI-ICE ON ENGINE ANTI-ICE VALVE PNEUMATIC SOURCE INLET PORT CLOSED on pre-flight , if open, bleed air can exit causing Hot Start or failed APU. ON O F F NO. 1 NO. 2 ENG ANTI-ICE #1 ENG ANTI-ICE ON Min: 40psig and 30ppm at 149 C Max: 50psig at 249 C When ENG ANTI-ICE switches are ON and ambient temperature (sensed at Ambient Sense Port) is below +4 C, degrees bleed air enters engine inlet fairing. When fairing temperature reaches +93 C, ENG INLET ANTI-ICE ON advisory light illuminates. Electrically closed, will open when switch is turned on (Advisory light - on) or low power setting until 88%-92% (Advisory light - off). Also below 30% in torque or due to AC power failure. HEATER HI OFF ON O F F VENT BLOWER 19

UH-60 FIRE EXTINGUISHING SYSTEM
CPT MURPHY, NYARNG Copyright 1995 13 8 FIRE EXTGH MAIN #2 DC PRI BUS 9 4 5 AMP OFF 12 LOGIC MODULE 7 PILOT'S CIRCUIT BREAKER PANEL WARNING 10 5 OFF Incase of fire when ac electrical power is not applied, the reserve fire extinguisher must be discharged. Fire extinguisher agent cannot be discharged into the #2 engine compartment if ac electrical power is not applied to the helicopter. 11 6 3 2 1 RESERVE FIRE EXT RESERVE O F F MAIN K24 FIRE EXTGH APU BATT UTIL BUS 5 AMP 10G IMPACT SWITCH (OMNI DIRECTIONAL) LOWER CONSOLE PANEL #2 ENGINE COMPARTMENT BATT UTIL BUS #2 DC PRIM BUS 2 2 CF3Br CF3Br MAIN RES 1 1 #2 DC PRIM BUS BATT UTIL BUS DIRECTIONAL CONTROL VALVE THERMAL RELIEF VALVE (CVERBOARD) Degrees F Bottle Temperature LOGIC MODULE NOTES 1. LAST SELECTOR ACTUATED WILL BE THE ONE ARMED 2. #1 ENGINE ARMED: MAIN-PIN 9 TO 4 3. #2 ENGINE ARMED: MAIN-PIN 10 TO RESERVE-PIN 12 TO 7 4. APU ARMED: PIN 3 TO MAIN-PIN 9 TO RESERVE-PIN 11 TO 6 #1 ENGINE FIRE EXTINGUISHER ARMING LEVER #2 ENGINE FIRE EXTINGUISHER ARMING LEVER #1 ENGINE COMPARTMENT APU 20

APU SIMPLIFIED BLOCK DIAGRAM
CPT MURPHY, NYARNG Copyright 1995 APU SIMPLIFIED BLOCK DIAGRAM APU TYPES OLDER VERSION(Turbomac) SHP NEWER VERSION(Garrett) SHP APU FAIL CAUTION LIGHT ILLUMINATES 1. APU fails to accelerate to 90% within 40 seconds, or accelerates to 90% or more then drops below 90% 2. At 110%, ESU will abort APU for an overspeed. 3. TGT exceeds limits, ESU will abort APU for overtemperature. APU CONTR INST 28 VDC BATT BUS 5 AMP APU POWER TRANSFER RELAY (0.5 SEC DELAY ON DROPOUT) APU CONTR INST 28 VDC BATT UTIL BUS NOTE The ESU will not shut down the APU for a high oil temperature. However; If pilot shuts down the APU while oil temperature is too high, it will not restart until oil temperature is below 120 degrees C. 5 AMP LOWER CONSOLE FUEL PUMP APU BOOST FUEL PRIME O F F PRIME BOOST PUMP ON APU CONTR FIRE EXTGH 90% or above for 1.5 seconds and below: 100% (LOADED) 103% (UNLOADED APU GEN SWITCH - ON)) OFF APU ON APU PRIME BOOST SHUTOFF VALVE APU ON ELECTRONIC SEQUENCE UNIT SHUT OFF ANY FUEL VALVES, AND TURN OFF IGNITION APU FAIL APU START VALVE APU OIL TEMP HI #1 FUEL TANK (LEFT SIDE) Oil temp exceeds 149 degrees C (wait 30 minutes to check oil level) APU ACCUMULATOR Minimum 2800 PSI 21

ELECTRICAL CONNECTION DIAGRAM
CPT MURPHY, NYARNG Copyright 1995 TGT (T4.5) HARNESS NP OVERSPEED AND TORQUE SENSOR TORQUE MOTOR NP SENSOR HMU LDVT POU SENSOR SWITCH HISTORY RECORDER ANTI-ICING AND START BLEED VALVE OCA ITEMS 2 SPARKS PER SECOND 5,000 TO 7,500 VOLTS IGNITER FUEL PRESSURE SWITCH FUEL FILTER SWITCH IGNITER ELECTRICAL CONTROL UNIT OIL PRESSURE TRANSMITTER OIL FILTER SWITCH IGNITION EXCITER NG 11 10 9 OIL TEMPERATURE TRANSMITTER CHIP DETECTOR NO TGT LIMITING DURING: 1. COMPRESSOR STALLS 2. ECU LOCKOUT 3. STARTING 4. ALTERNATOR FAILURE (partial or total failure) 8 7 6 ALTERNATOR E3 CANNON PLUG Additional power lead to overspeed circuit of ECU providing overspeed protection during ECU failure. (#1 AC primary bus for #1 engine) (#2 AC primary bus for #2 engine) 22

UH-60A ELECTRICAL SYSTEM
CPT MURPHY, NYARNG Copyright 1995 #2 GENERATOR FAILURE MAIN GENERATORS 115/200 VAC 30/45 KVA 400 Hz 3 PHASE OIL 12,000 RPM POWERS M/R DEICE, IF FAILED AND YOU PLACE APU INTO OPERATION YOU WILL NOT GET AN APU-ON ADVISORY LIGHT, BECAUSE THE #1 AC PRIMARY BUS IS STILL POWERED. #1 GEN BRG #1 GEN #2 GEN #2 GEN BRG APU SOLE SOURCE OF AC POWER ALL EQUIPMENT WILL OPERATE EXCEPT WHEN THE BACKUP PUMP IS ON, THE WINDSHIELD ANTI-ICE IS PREVENTED FROM BEING USED. POWERS THE T/R DEICE SYSTEM. APU GENERATOR 115/200 VAC 20/30 KVA 400 Hz 3 PHASE AIR 12,000 RPM 10 HRS USAGE WHEN LIGHT ILLUMINATES TEST MODE ONLY TESTS OUTPUT OF GENERATOR, DURING TEST IF CAUTION LIGHT GOES OUT GENERATOR IS OK. NO.1 TEST NO.2 TEST O F F R E S E T GCU GCU O F F R E S E T A PHASE CURRENT B PHASE CURRENT C PHASE CURRENT ON ON AUXILIARY JUNCTION BOX APU GEN ON GENERATOR CONTROL UNIT 1. VOLTAGE REGULATION 2. UNDERFREQUENCY PROTECTION (^95% RPMR GEN-ON, DISABLED BY WOW SWITCH) 3. OVERVOLTAGE PROTECTION ( VAC) 4. UNDERVOLTAGE PROTECTION ( VAC/BELOW 85% RPMR POWER OFF GEN-OFF)) 5. FEEDER FAULT (SHORT PROTECTION) 60 AMP CURRENT LIMITERS APU GEN #1 AC PRIMARY BUS #2 AC PRIMARY BUS GCU APU TEST AC ESSENTIAL BUS O F F R E S E T ON AC ESS BUS OFF EXT POWER MONITOR PANEL #1 CONVERTER #2 CONVERTER TIME BOOST CHARGE (LOW BATTERY) 115V AC TO 28V DC 115V AC TO 28V DC #1 CONV EXT PWR CONNECTED #2 CONV #1 GEN #1 DC PRIMARY BUS #2 DC PRIMARY BUS POWER TO OPERATE CHARGER/ ANALYZER SLOW CHARGE 100 AMP CURRENT LIMITER #2 GEN BATT LOW CHARGE DC ESSENTIAL BUS FAULT MONITOR CIRCUIT BATTERY FAULT DC ESS BUS OFF BATTERY 24V DC 5.5 AMP HOUR 20 CELLS BATT O F F ON BATTERY BUS BATTERY UTILITY 23

CPT MURPHY, NYARNG Copyright 1995 EXTERNAL POWER PRIOR TO ENGINE START #1 GEN BRG #1 GEN #2 GEN #2 GEN BRG MAX 10 HRS USAGE WHEN LIGHT ILLUMINATES A PHASE CURRENT B PHASE CURRENT C PHASE CURRENT GCU NO.2 TEST R E S E T ON O F F NO.1 TEST AUXILIARY JUNCTION BOX APU GEN ON 60 AMP CURRENT LIMITERS APU GEN #1 AC PRIMARY BUS #2 AC PRIMARY BUS GCU APU TEST R E S E T ON O F F AC ESSENTIAL BUS AC ESS BUS OFF EXT POWER MONITOR PANEL #1 CONVERTER #2 CONVERTER TIME BOOST CHARGE (LOW BATTERY) 115V AC TO 28V DC 115V AC TO 28V DC #1 CONV EXT PWR RESET O F F EXT PWR CONNECTED #2 CONV ON POWER TO OPERATE CHARGER/ ANALYZER #1 GEN #1 DC PRIMARY BUS #2 DC PRIMARY BUS @ 40% CHARGE LEFT SLOW CHARGE 100 AMP CURRENT LIMITER #2 GEN BATT LOW CHARGE DC ESSENTIAL BUS BATTERY LIFE AT 80% CHARGE: DAY - 22 MINUTES NIGHT - 14 MINUTES FAULT MONITOR CIRCUIT BATTERY FAULT DC ESS BUS OFF ABOVE 70 DEG OR DISSIMILARITY BETWEEN CELLS BATTERY 24V DC 5.5 AMP HOUR 20 CELLS BATT O F F ON BATTERY CAPACITY 35% AND BOTH CONVERTERS ARE OFF BATTERY BUS BATTERY UTILITY Does not work with a SEALED LEAD ACID BATTERY (SLAB) 24

CPT MURPHY, NYARNG Copyright 1995 AC POWER PRIOR TO ENGINE START #1 GEN BRG #1 GEN #2 GEN APU SOLE SOURCE OF AC POWER ALL EQUIPMENT WILL OPERATE EXCEPT WHEN THE BACKUP PUMP IS ON, THE WINDSHIELD ANTI-ICE IS PREVENTED FROM BEING USED. #2 GEN BRG APU GENERATOR 115/200 VAC 20/30 KVA 400 Hz 3 PHASE AIR 12,000 RPM MAX 10 HRS USAGE WHEN LIGHT ILLUMINATES A PHASE CURRENT B PHASE CURRENT C PHASE CURRENT GCU NO.2 TEST R E S E T ON O F F NO.1 TEST AUXILIARY JUNCTION BOX APU GEN ON GENERATOR CONTROL UNIT 1. VOLTAGE REGULATION 2. UNDERFREQUENCY PROTECTION (^95% RPMR GEN-ON, DISABLED BY WOW SWITCH) 3. OVERVOLTAGE PROTECTION ( VAC) 4. UNDERVOLTAGE PROTECTION ( VAC/BELOW 85% RPMR POWER OFF GEN-OFF)) 5. FEEDER FAULT (SHORT PROTECTION) 60 AMP CURRENT LIMITERS APU GEN #1 AC PRIMARY BUS #2 AC PRIMARY BUS GCU APU TEST R E S E T ON O F F AC ESSENTIAL BUS AC ESS BUS OFF EXT POWER MONITOR PANEL #1 CONVERTER #2 CONVERTER TIME BOOST CHARGE (LOW BATTERY) 115V AC TO 28V DC 115V AC TO 28V DC #1 CONV EXT PWR CONNECTED #2 CONV CHARGER/ ANALYZER #1 GEN #1 DC PRIMARY BUS #2 DC PRIMARY BUS POWER TO OPERATE @ 40% CHARGE LEFT SLOW CHARGE 100 AMP CURRENT LIMITER #2 GEN BATT LOW CHARGE DC ESSENTIAL BUS BATTERY LIFE AT 80% CHARGE: DAY - 22 MINUTES NIGHT - 14 MINUTES FAULT MONITOR CIRCUIT BATTERY FAULT DC ESS BUS OFF ABOVE 70 DEG OR DISSIMILARITY BETWEEN CELLS BATTERY 24V DC 5.5 AMP HOUR 20 CELLS BATT O F F ON BATTERY CAPACITY 35% AND BOTH CONVERTERS ARE OFF BATTERY BUS BATTERY UTILITY Does not work with a SEALED LEAD ACID BATTERY (SLAB) 25

CPT MURPHY, NYARNG Copyright 1995 MAIN GENERATORS 115/200 VAC 30/45 KVA 400 Hz 3 PHASE OIL RPM POWERS M/R DEICE, IF FAILED AND YOU PLACE APU INTO OPERATION YOU WILL NOT GET AN APU-ON ADVISORY LIGHT, BECAUSE THE #1 AC PRIMARY BUS IS STILL POWERED. #1 GEN BRG #1 GEN #2 GEN #2 GEN BRG APU SOLE SOURCE OF AC POWER, ALL EQUIPMENT WILL OPERATE EXCEPT WHEN THE BACKUP PUMP IS ON, THEN THE WINDSHIELD ANTI-ICE IS PREVENTED FROM BEING USED. POWERS THE T/R DEICE SYSTEM. APU GENERATOR 115/200 VAC 20/30 KVA 400 Hz 3 PHASE AIR 12,000 RPM MAXIMUM OF10 HRS USAGE WHEN LIGHT ILLUMINATES TEST MODE ONLY TESTS OUTPUT OF GENERATOR, DURING TEST IF CAUTION LIGHT GOES OUT GENERATOR IS OK. NO.1 TEST NO.2 TEST R E S E T ON O F F O F F R E S E T GCU GCU A PHASE CURRENT B PHASE CURRENT C PHASE CURRENT ON AUXILIARY JUNCTION BOX APU GEN ON GENERATOR CONTROL UNIT 1. VOLTAGE REGULATION 2. UNDERFREQUENCY PROTECTION (^95% RPMR GEN-ON, DISABLED BY WOW SWITCH) 3. OVERVOLTAGE PROTECTION ( VAC) 4. UNDERVOLTAGE PROTECTION ( VAC/BELOW 85% RPMR POWER OFF GEN-OFF)) 5. FEEDER FAULT (SHORT PROTECTION) 60 AMP CURRENT LIMITERS APU GEN #1 AC PRIMARY BUS #2 AC PRIMARY BUS GCU APU TEST R E S E T ON O F F AC ESSENTIAL BUS CONNECTED IF #1 AC PRI BUS FAILURE EXTERNAL POWER MONITOR PANEL 1. UNDERVOLTAGE PROTECTION 2. OVERVOLTAGE PROTECTION 3. UNDERFREQUENCY PROTECTION 4. OVERFREQUENCY PROTECTION 5. CORRECT PHASE ROTATION AC ESS BUS OFF EXT POWER MONITOR PANEL #1 CONVERTER #2 CONVERTER TIME BOOST CHARGE (LOW BATTERY) 115V AC TO 28V DC 115V AC TO 28V DC EXT PWR RESET #1 CONV O F F EXT PWR CONNECTED #2 CONV ON POWER TO OPERATE CHARGER/ ANALYZER #1 GEN #1 DC PRIMARY BUS #2 DC PRIMARY BUS @ 40% CHARGE LEFT SLOW CHARGE 100 AMP CURRENT LIMITER #2 GEN BATT LOW CHARGE DC ESSENTIAL BUS BATTERY LIFE AT 80% CHARGE: DAY - 22 MINUTES NIGHT - 14 MINUTES FAULT MONITOR CIRCUIT BATTERY FAULT DC ESS BUS OFF CONNECTED IF #1 DC PRI BUS FAILURE ABOVE 70 DEG OR DISSIMILARITY BETWEEN CELLS BATTERY 24V DC 5.5 AMP HOUR 20 CELLS BATT O F F ON BATTERY CAPACITY 35% AND BOTH CONVERTERS ARE OFF BATTERY BUS BATTERY UTILITY Does not work with a SEALED LEAD ACID BATTERY (SLAB) 26

STABILATOR/FLIGHT CONTROL PANEL FAILURE ADVISORY LIGHTS (RIGHT)
#1 AND/OR #2 LATERAL ACCELEROMETER FAILED #1 AND/OR #2 COLLECTIVE STICK TRANSDUCER FAILED CPTR SAS 2 TRIM RGYR ACCL CLTV GYRO A/S FAILURE RESET R E S E T POWER ON RESET AIRSPEED AND/OR AIR DATA TRANSDUCER FAILED (THE ABOVE COULD BE AFFECTED BY STABILATOR SYSTEM MALFUNCTION) (1) #1 OR #2 VERTICAL GYRO FAILED (2) COMPASS SYSTEM FAILED 27

STABILATOR/FLIGHT CONTROL PANEL FAILURE ADVISORY LIGHTS (LEFT)
1. SAS/FPS COMPUTER FAILED 2. PITCH TRIM SERVO VALVE CIRCUIT OPEN 3. PITCH, ROLL, OR YAW SAS ACTUATOR VALVE CIRCUIT OPEN 1. PITCH, ROLL, OR YAW SAS ACTUATOR VALVE COIL FAILED 2. PITCH, ROLL, OR YAW RATE GYRO FAILED CPTR SAS 2 TRIM RGYR ACCL CLTV GYRO A/S FAILURE RESET R E S E T POWER ON RESET 1. PITCH TRIM SERVO COIL SHORT CIRCUIT 2. PITCH, ROLL, OR YAW TRIM ACTUATOR FAILED 3. ROLL STICK FORCE CHANGING TOO FAST (TRIM HARDOVER) 4. PEDAL FORCE CHANGING TOO FAST (TRIM HARDOVER) 1. PITCH GYRO FAILED 2. ROLL RATE GYRO FAILED 3. YAW RATE GYRO FAILED (THE ABOVE COULD BE AFFECTED BY STABILATOR SYSTEM MALFUNCTION) 28

STABILATOR / SAS-FPS SYSTEM
CP PITOT **The following systems must be operational for FPS to function at 100%. 1. SAS 1 and/or SAS 2 - ON 2. Boost - ON 3. Trim - ON 4. FPS - ON Stabilator in AUTO mode (enhances FPS operation but not required) P PITOT CPT MURPHY, NYARNG, Copyright 1995 AUTO CONTROL 10 DEG O F F UP TEST 4 DEGREES #1 STAB AMP #2 STAB ACT #2 STAB AMP ON 30 150 DN STABILATOR MISCOMPARE CHART #2 DC PRIM BUS A/S X-DUCER IF ONLY ONE ACTUATOR IS MOVING THE STABILATOR WILL ONLY TRAVEL DEGREES. FAULT MONITOR CIRCUIT PITCH RATE GYRO DISABLED ^60KTS BY A/S X-DUCER #1 STAB ACT PITCH RATE GYRO FAULT MONITOR CIRCUIT AIR DATA X-DUCER DC ESS BUS ATTITUDE HOLD PITCH AXIS ATTITUDE HOLD / AIRSPEED HOLD ROLL AXIS YAW AXIS HEADING HOLD HEADING HOLD OR TURN COORDINATION BELOW 60 KTS ABOVE FPS FUNCTIONS P STAB POS DEG 10 20 30 40 DN +9 DEGREES STABILATOR #2 LAT ACCL #1 #2 -39 DEGREES CP STAB POS DEG 10 20 30 40 DN POSITION TRANSDUCER COLLECTIVE POSITION TRANSDUCERS ON MIXING UNIT TRIM ACTUATORS NOTE Turn coordination requires 1/2 inch cyclic displacement AND 1 1/2 degrees of roll attitude change. SAS ACTUATORS ROLL PITCH YAW #1 LAT ACCL #1 SAS AMP ATTITUDE HOLD PITCH CYCLIC TRIM INTERRUPT SWITCH PEDAL TRIM INTERRUPT SWITCH (ANALOG) AIRSPEED HOLD ^60 KTS HEADING HOLD YAW RATE GYRO TURN COORDINATION ^60 KTS ELECTRONIC MIXING TRIM ASN 43 ROLL FPS COMPUTER #1 ACCL A/S X-DUCER YAW RATE GYRO **Has 100% control authority when coupled with TRIM and provides Static stability through long term rate dampening #2 VERTICAL GYRO (PILOT) #1 VERTICAL GYRO (CO-PILOT) YAW #2 SAS AMP (DIGITAL) SAS 1 & 2 has a total of 10% (5% each) control authority providing Dynamic stability through short term rate dampening #1&2 ACCL A/S DATA X-DUCER YAW RATE GYRO ROLL RATE GYRO YAW RATE GYRO 29

UH-60 AUTO FLIGHT CONTROL SYSTEM
CPT MURPHY, NYARNG Copyright 1995 PITCH TRIM TURN OFF VALVE BOOST TURN OFF VALVE SAS SHUTOFF VALVE SAS 1 AMPLIFIER SAS 2/FPS COMPUTER SAS OFF AFCS Subsystems 1. SAS 2. Trim 3. FPS 4. Stabilator SAS PRESSURE SWITCH PILOT ASSIST MODULE COLLECTIVE BOOST PRESSURE SWITCH STABILATOR CONTROL AUTO CONTROL UP COLLECTIVE BOOST SERVO PITCH TRIM ASSEMBLY ROLL SAS ACTUATOR TEST O F F BOOST SERVO OFF ON Maximum forces required to overcome slip clutches: YAW: 80 pounds Roll: 13 pounds DN AUTO FLIGHT CONTROL SAS 1 SAS 2 TRIM FPS ON ON ON ON BOOST FAILURE ADVISORY YAW BOOST PRESSURE SWITCH ON R E S E T CPTR SAS 2 ACCL CLTV R E S E T ROLL TRIM ACTUATOR YAW BOOST TRIM RGYR A/S GYRO YAW SAS ACTUATOR YAW BOOST SERVO POWER ON RESET YAW TRIM ACTUATOR PILOT ASSIST AREA 30

ELECTRICAL CONTROL UNIT SCHEMATIC
CPT MURPHY, NYARNG Copyright 1995 COLLECTIVE Np INCREASE/ DECREASE SWITCH (PILOT'S OVERRIDES CO-PILOT'S SWITCH) COCKPIT ENGINE INSTRUMENTS MIXING UNIT 115V 400HZ TGT Np TQ LDS PAS AIRFRAME ENGINE TORQUE MOTOR TGT LIMIT AMPLIFIER ( DEGREES) CELSIUS TORQUE MOTOR AMPLIFIER SELECT LEAST FUEL FLOW FEEDBACK LVDT TGT THERMO COUPLES STABILIZATION FEEDBACK HMU NP REFERENCE ALTERNATOR NP GOVERNING (ISOCHRONOUS CHIP) TGT ECU CONVERTS SIGNAL TO DISPLAY ON GAGE (+3) %NP Np SENSOR Ng 400HZ TRANSFORMER ALTERNATOR TRANSFORMER RECTIFIER HISTORY RECORDER DC TORQUE CIRCUIT Q1 LOAD SHARE COMPARATOR (MATCH WITHIN 5%) 400HZ Q2 OTHER ENGINE TORQUE (Q) POU TORQUE AND OVERSPEED SENSOR Np OVERSPEED SWITCH ( %) OVERSPEED SOLENOID TORQUE (Q) SIGNAL TO OTHER ENGINE 31

HYDROMECHANICAL UNIT . . . . HMU Functions
CPT. MURPHY, NYARNG Copyright 1995 HMU Functions POWER AVAILABLE SPINDEL (PAS) TELLS ECU THAT TORQUE SERVO HAS MOVED. COLLECTIVE PITCH INCREASE 1. High pressure fuel pumping 2. Fuel flow metering 3. Acceleration/Deceleration flow limiting 4. NG Limiting (NG SPEED & T2 INFORMATION) 5. Variable Geometry Positioning & Mechanical input to ANTI-ICE start bleed valve. 6. Torque Motor to Trim NG Output 7. Collective Pitch Compensation through the LDS 8. PAS Override and Control with ECU inoperative (ECU Lockout) 9. Vapor Vent on PAS Overtravel for Fuel System Priming (engine off, PCL - in LOCKOUT position, fuel prime switch - ON) LV DT TORQUE MOTOR SERVO LOAD DEMAND SPINDEL (LDS) INCREASE . . 0 DEGREES OVERRIDE DETENT NG CAM 67 DEGREES . 26 DEGREES . 120 DEGREES METERED FUEL OUTPUT VG SERVO WINDMILL BYPASS CAM VG ACTUATOR ACCEL T2 SENSOR T2 SERVO ACCEL/ DECEL COMP NG GOVERNOR NG FUEL OUT TO COOLER PS3 T2 FUEL PRESSURE SIGNAL DECEL NG SERVO PS3 SIGNAL INPUT SHUTOFF VALVE P3 T2 SENSOR (Turbine Inlet Temperature) VANE PUMP FROM FUEL FILTER 400 TO 832 PSI BYPASS VALVE 45 to 90 PSI FROM ENGINE DRIVEN FUEL PUMP AT 100% NG METERING VALVE VARIABLE GEOMETRY (VG) ACTUATOR AND ENGINE ANTI-ICE VALVE TO PUMP INLET 32

UH-60 FUEL SYSTEM DIRECT MODE APU #1 ENGINE #2 ENGINE
CPT Murphy, NYARNG Copyright 1995 UH-60 FUEL SYSTEM TO ENGINE 45 TO 90 PSI AT 100% NG 20 PSI MINIMUM AT 63% NG HMU FUEL PRESSURE 400 TO 832 PSI BASED ON NG SPEED. LDS (FROM COLLECTIVE) PAS (PCL) DIRECT MODE FROM TANK -3 TO -6 PSI (BOOST PUMPS OFF) P O U L L C HMU PSI F I L T E R F I L T E R ENGINE BOOST PUMP FUEL SEL FUEL SEL ENGINE BOOST PUMP HMU PSI L L C P O U ONE-WAY CHECK VALVE ONE-WAY CHECK VALVE #1 FUEL FLTR BYPASS #1 FUEL PRESS #2 FUEL PRESS #2 FUEL FLTR BYPASS BOOST FUEL TO PSI 25 MICRON 10 MICRON BELOW 8.5 PSI +/- .5 BUTTON POP: 8-10PSID BYPASS: 18-22PSID TO ILLUMINATE LIGHT. F I L T E R P U M P F I L T E R #1 ENGINE 7.62MM SELF SEALING LINE #2 ENGINE APU APU SHUTOFF FUEL QTY LBS X 100 1 2 #1 PRIME SHUTOFF GRAVITY GAL NATO (PRESSURE) (55 PSI/300GPM)-359 GAL CCR (CLOSED CURCUIT) (15 PSI/110GPM)-356 GAL #2 PRIME SHUTOFF FUEL PUMP APU BOOST PRIME BOOST PUMP ON O F F FUEL PRIME PRIME BOOST PUMP 5 PSI #2 FUEL LOW #1 FUEL LOW VENT LINE 7.62MM SELF SEALING TANKS HIGH LEVEL SHUTOFF VALVE PRESSURE REFUELING VALVE CCR & NATO ON OFF NO.2 PUMP NO.1 PUMP #2 FUEL TANK 180 GAL Cap. FUEL QTY PROBE LOWLEVEL SHUTOFF VALVE SUBMERGED BOOST PUMP 25PSI #1 FUEL TANK 180 GAL Cap. SUBMERGED BOOST PUMP 25PSI LOW FUEL SWITCH 172 lbs LIGHTS ON INDICATES ACCEPTABLE PRESSURE 33

UH-60 FUEL SYSTEM XFD #2 ENGINE APU #1 ENGINE #2 ENGINE
CPT Murphy, NYARNG Copyright 1995 UH-60 FUEL SYSTEM TO ENGINE 45 TO 90 PSI AT 100% NG 20 PSI MINIMUM AT 63% NG HMU FUEL PRESSURE 400 TO 832 PSI BASED ON NG SPEED. LDS (FROM COLLECTIVE) PAS (PCL) XFD #2 ENGINE FROM TANK -3 TO -6 PSI (BOOST PUMPS OFF) P O U L L C HMU PSI F I L T E R F I L T E R ENGINE BOOST PUMP FUEL SEL FUEL SEL ENGINE BOOST PUMP HMU PSI L L C P O U ONE-WAY CHECK VALVE ONE-WAY CHECK VALVE #1 FUEL FLTR BYPASS #1 FUEL PRESS #2 FUEL PRESS #2 FUEL FLTR BYPASS BOOST FUEL TO PSI 25 MICRON 10 MICRON BELOW 8.5 PSI +/- .5 BUTTON POP: 8-10PSID BYPASS: 18-22PSID TO ILLUMINATE LIGHT. F I L T E R P U M P F I L T E R #1 ENGINE 7.62MM SELF SEALING LINE #2 ENGINE APU APU SHUTOFF FUEL QTY LBS X 100 #1 PRIME SHUTOFF GRAVITY GAL NATO (PRESSURE) (55 PSI/300GPM)-359 GAL CCR (CLOSED CURCUIT) (15 PSI/110GPM)-356 GAL #2 PRIME SHUTOFF FUEL PUMP APU BOOST PRIME BOOST PUMP ON O F F FUEL PRIME PRIME BOOST PUMP 5 PSI 1 2 #2 FUEL LOW #1 FUEL LOW VENT LINE 7.62MM SELF SEALING TANKS HIGH LEVEL SHUTOFF VALVE PRESSURE REFUELING VALVE CCR & NATO ON OFF NO.2 PUMP NO.1 PUMP #2 FUEL TANK 180 GAL Cap. FUEL QTY PROBE LOWLEVEL SHUTOFF VALVE SUBMERGED BOOST PUMP 25PSI #1 FUEL TANK 180 GAL Cap. SUBMERGED BOOST PUMP 25PSI LOW FUEL SWITCH 172 lbs LIGHTS ON INDICATES ACCEPTABLE PRESSURE 34

UH-60 FUEL SYSTEM APU ON APU #1 ENGINE #2 ENGINE
CPT Murphy, NYARNG Copyright 1995 UH-60 FUEL SYSTEM APU ON (ENGINES OFF/BOOST PUMPS OFF)) F I L T E R P O U L L C HMU PSI F I L T E R ENGINE BOOST PUMP FUEL SEL FUEL SEL ENGINE BOOST PUMP HMU PSI L L C P O U ONE-WAY CHECK VALVE ONE-WAY CHECK VALVE #1 FUEL FLTR BYPASS #1 FUEL PRESS #2 FUEL PRESS #2 FUEL FLTR BYPASS BOOST FUEL TO PSI 25 MICRON 10 MICRON BELOW 8.5 PSI +/- .5 BUTTON POP: 8-10PSID BYPASS: 18-22PSID TO ILLUMINATE LIGHT. F I L T E R P U M P F I L T E R #1 ENGINE ESU #2 ENGINE APU APU SHUTOFF CONTR APU FIRE EXTGH OFF FUEL QTY LBS X 100 1 2 ON APU LIGHT ON INDICATES THAT DC POWER IS APPLIED TO PUMP ONLY. #1 PRIME SHUTOFF #2 PRIME SHUTOFF FUEL PUMP APU BOOST PRIME BOOST PUMP ON O F F FUEL PRIME PRIME BOOST PUMP 5 PSI #2 FUEL LOW #1 FUEL LOW VENT LINE 7.62MM SELF SEALING TANKS HIGH LEVEL SHUTOFF VALVE PRESSURE REFUELING VALVE CCR & NATO ON #2 FUEL TANK 180 GAL Cap. FUEL QTY PROBE ON NO.1 PUMP NO.2 PUMP LOWLEVEL SHUTOFF VALVE SUBMERGED BOOST PUMP 25PSI #1 FUEL TANK 180 GAL Cap. OFF OFF SUBMERGED BOOST PUMP 25PSI LOW FUEL SWITCH 172 lbs 35

UH-60 FUEL SYSTEM APU #1 ENGINE #2 ENGINE LDS (FROM COLLECTIVE)
CPT Murphy, NYARNG Copyright 1995 UH-60 FUEL SYSTEM TO ENGINE 45 TO 90 PSI AT 100% NG 20 PSI MINIMUM AT 63% NG HMU FUEL PRESSURE 400 TO 832 PSI BASED ON NG SPEED. LDS (FROM COLLECTIVE) PAS (PCL) FROM TANK -3 TO -6 PSI (BOOST PUMPS OFF) P O U L L C HMU PSI F I L T E R F I L T E R ENGINE BOOST PUMP FUEL SEL FUEL SEL ENGINE BOOST PUMP HMU PSI L L C P O U ONE-WAY CHECK VALVE ONE-WAY CHECK VALVE #1 FUEL FLTR BYPASS #1 FUEL PRESS #2 FUEL PRESS #2 FUEL FLTR BYPASS BOOST FUEL TO PSI 25 MICRON 10 MICRON BELOW 8.5 PSI +/- .5 BUTTON POP: 8-10PSID BYPASS: 18-22PSID TO ILLUMINATE LIGHT. F I L T E R P U M P F I L T E R #1 ENGINE 7.62MM SELF SEALING LINE #2 ENGINE APU APU SHUTOFF FUEL QTY LBS X 100 1 2 #1 PRIME SHUTOFF GRAVITY GAL NATO (PRESSURE) (55 PSI/300GPM)-359 GAL CCR (CLOSED CURCUIT) (15 PSI/110GPM)-356 GAL #2 PRIME SHUTOFF FUEL PUMP APU BOOST PRIME BOOST PUMP ON O F F FUEL PRIME PRIME BOOST PUMP 5 PSI #2 FUEL LOW #1 FUEL LOW VENT LINE 7.62MM SELF SEALING TANKS HIGH LEVEL SHUTOFF VALVE PRESSURE REFUELING VALVE CCR & NATO ON OFF NO.2 PUMP NO.1 PUMP #2 FUEL TANK 180 GAL Cap. FUEL QTY PROBE LOWLEVEL SHUTOFF VALVE SUBMERGED BOOST PUMP 25PSI #1 FUEL TANK 180 GAL Cap. SUBMERGED BOOST PUMP 25PSI LOW FUEL SWITCH 172 lbs LIGHTS ON INDICATES ACCEPTABLE PRESSURE 36

All Hydraulic caution lights
CPT MURPHY, NYARNG Copyright 1995 UH-60 HYDRAULIC SYSTEM THERMAL SWITCH (160 DEGREE) DEPRESSURIZATION VALVE (700 PSI) .5 SEC-MAIN GEN 3-5 SEC-APU GEN LEAK IN #2 PRIMARY SERVO BACKUP HYD PUMP OFF ON A U T O (LDI TURNS PILOT ASSIST BACK ON) MOTOR 115 VAC HP BACKUP HYD PUMP All Hydraulic caution lights VELOCITY FUSE Light ON - Pressure decreases below 2000 PSI. Light OFF - Pressure increases above 2350 PSI. PS BACKUP HYD RESEVOIR #1 RSVR LOW UTILITY MODULE BACK-UP RSVR LOW #1 HYD PUMP/RESEVOIR #1 TAIL RTR SERVO #1 HYD PUMP BACK-UP PUMP ON YAW SAS ACTUATOR TAIL ROTOR SERVOS Transfer Valve SVO OFF 1ST STG PS PS YAW BOOST PS 1ST STAGE TRANSFER MODULE 2ND STG ROLL SAS ACTUATOR BOOST SERVO OFF 2ND STAGE APU ACCUM LOW APU ACCUMULATOR 1 2 4 PS OPTIONAL 2nd STAGE PS PS 2ND STAGE 1ST STAGE L PITCH SAS ACTUATOR PS PITCH/TRIM ACTUATOR 2ND STAGE 1ST STAGE #1 PRI SERVO PRESS PS A PITCH BOOST SERVO PS #2 TAIL RTR SERVO ON #2 PRI SERVO PRESS PS 2ND STAGE 1ST STAGE F PS COLLECTIVE BOOST SERVO PS TRIM FAIL #2 TAIL ROTOR SHUTOFF VALVE TRANSFER MODULE PRESSURE REDUCER CLOSES IF PRESSURE REACHES 1375 PSI 1000 PSI (NORMAL) PS TAIL SERVO NORMAL BACKUP LDI CONTROLS IN THE AIR #2 HYD PUMP PRESSURE REDUCER PS PILOT ASSIST MODULE FLT PATH STAB SHUTS OFF #1 TAIL ROTOR SERVO SHUTOFF VALVE ON TRANSFER MODULE OPENS #2 TAIL ROTOR SERVO SHUTOFF VALVE & ACTIVATES BACKUP PUMP. #2 RSVR LOW #2 HYD PUMP/RESEVOIR SAS OFF SAS2/FPS COMPUTER 37

UH-60 HYDRAULIC SYSTEM LEAK IN THE PILOT ASSIST AREA
CPT MURPHY, NYARNG Copyright 1995 UH-60 HYDRAULIC SYSTEM THERMAL SWITCH (160 DEGREE) DEPRESSURIZATION VALVE (700 PSI) .5 SEC-MAIN GEN 3-5 SEC-APU GEN LEAK IN THE PILOT ASSIST AREA BACKUP HYD PUMP OFF ON A U T O (LDI SHUT OFF PILOT ASSIST) MOTOR 115 VAC HP BACKUP HYD PUMP #2 RSVR LOW 60% of capacity remaining VELOCITY FUSE PS BACKUP HYD RESEVOIR #1 RSVR LOW UTILITY MODULE BACK-UP RSVR LOW #1 HYD PUMP/RESEVOIR #1 TAIL RTR SERVO #1 HYD PUMP BACK-UP PUMP ON YAW SAS ACTUATOR TAIL ROTOR SERVOS Transfer Valve SVO OFF 1ST STG PS PS YAW BOOST PS 1ST STAGE TRANSFER MODULE 2ND STG ROLL SAS ACTUATOR BOOST SERVO OFF 2ND STAGE APU ACCUM LOW APU ACCUMULATOR 1 2 4 PS OPTIONAL 2nd STAGE PS PS 2ND STAGE 1ST STAGE L PITCH SAS ACTUATOR PS PITCH/TRIM ACTUATOR 2ND STAGE 1ST STAGE #1 PRI SERVO PRESS PS A PITCH BOOST SERVO PS #2 TAIL RTR SERVO ON #2 PRI SERVO PRESS PS 2ND STAGE 1ST STAGE F PS COLLECTIVE BOOST SERVO PS TRIM FAIL #2 TAIL ROTOR SHUTOFF VALVE TRANSFER MODULE PRESSURE REDUCER CLOSES IF PRESSURE REACHES 1375 PSI 1000 PSI (NORMAL) PS TAIL SERVO NORMAL BACKUP LDI CONTROLS IN THE AIR #2 HYD PUMP PRESSURE REDUCER PS PILOT ASSIST MODULE FLT PATH STAB SHUTS OFF #1 TAIL ROTOR SERVO SHUTOFF VALVE ON TRANSFER MODULE OPENS #2 TAIL ROTOR SERVO SHUTOFF VALVE & ACTIVATES BACKUP PUMP. #2 RSVR LOW #2 HYD PUMP/RESEVOIR SAS OFF SAS2/FPS COMPUTER 38

UH-60 HYDRAULIC SYSTEM LEAK IN #2 PRIMARY SERVO
CPT MURPHY, NYARNG Copyright 1995 UH-60 HYDRAULIC SYSTEM THERMAL SWITCH (160 DEGREE) DEPRESSURIZATION VALVE (700 PSI) .5 SEC-MAIN GEN 3-5 SEC-APU GEN LEAK IN #2 PRIMARY SERVO BACKUP HYD PUMP OFF ON A U T O (#2 PRIMARY SERVO SWITCH ISOLATED) MOTOR 115 VAC HP BACKUP HYD PUMP VELOCITY FUSE PS BACKUP HYD RESEVOIR #1 RSVR LOW UTILITY MODULE BACK-UP RSVR LOW #1 HYD PUMP/RESEVOIR #1 TAIL RTR SERVO #1 HYD PUMP BACK-UP PUMP ON YAW SAS ACTUATOR TAIL ROTOR SERVOS Transfer Valve SVO OFF 1ST STG PS PS YAW BOOST PS 1ST STAGE TRANSFER MODULE 2ND STG ROLL SAS ACTUATOR BOOST SERVO OFF 2ND STAGE APU ACCUM LOW APU ACCUMULATOR 1 2 4 PS OPTIONAL 2nd STAGE PS PS 2ND STAGE 1ST STAGE L PITCH SAS ACTUATOR PS PITCH/TRIM ACTUATOR 2ND STAGE 1ST STAGE #1 PRI SERVO PRESS PS A PITCH BOOST SERVO PS #2 TAIL RTR SERVO ON #2 PRI SERVO PRESS PS 2ND STAGE 1ST STAGE F PS COLLECTIVE BOOST SERVO PS TRIM FAIL #2 TAIL ROTOR SHUTOFF VALVE TRANSFER MODULE PRESSURE REDUCER CLOSES IF PRESSURE REACHES 1375 PSI 1000 PSI (NORMAL) PS TAIL SERVO NORMAL BACKUP LDI CONTROLS IN THE AIR #2 HYD PUMP PRESSURE REDUCER PS PILOT ASSIST MODULE FLT PATH STAB SHUTS OFF #1 TAIL ROTOR SERVO SHUTOFF VALVE ON TRANSFER MODULE OPENS #2 TAIL ROTOR SERVO SHUTOFF VALVE & ACTIVATES BACKUP PUMP. #2 RSVR LOW #2 HYD PUMP/RESEVOIR SAS OFF SAS2/FPS COMPUTER 39

UH-60 HYDRAULIC SYSTEM LEAK IN #1 TRANSFER MODULE
CPT MURPHY, NYARNG Copyright 1995 UH-60 HYDRAULIC SYSTEM THERMAL SWITCH (160 DEGREE) DEPRESSURIZATION VALVE (700 PSI) .5 SEC-MAIN GEN 3-5 SEC-APU GEN LEAK IN #1 TRANSFER MODULE BACKUP HYD PUMP OFF ON A U T O (LDI CAN"T ISOLATE LEAK) MOTOR 115 VAC HP BACKUP HYD PUMP VELOCITY FUSE PS BACKUP HYD RESEVOIR #1 RSVR LOW UTILITY MODULE BACK-UP RSVR LOW #1 HYD PUMP/RESEVOIR #1 TAIL RTR SERVO #1 HYD PUMP BACK-UP PUMP ON YAW SAS ACTUATOR TAIL ROTOR SERVOS Transfer Valve SVO OFF 1ST STG PS PS YAW BOOST PS 1ST STAGE TRANSFER MODULE 2ND STG ROLL SAS ACTUATOR BOOST SERVO OFF 2ND STAGE APU ACCUM LOW APU ACCUMULATOR 1 2 4 PS OPTIONAL 2nd STAGE PS PS 2ND STAGE 1ST STAGE L PITCH SAS ACTUATOR PS PITCH/TRIM ACTUATOR 2ND STAGE 1ST STAGE #1 PRI SERVO PRESS PS A PITCH BOOST SERVO PS #2 TAIL RTR SERVO ON #2 PRI SERVO PRESS PS 2ND STAGE 1ST STAGE F PS COLLECTIVE BOOST SERVO PS TRIM FAIL #2 TAIL ROTOR SHUTOFF VALVE TRANSFER MODULE PRESSURE REDUCER CLOSES IF PRESSURE REACHES 1375 PSI 1000 PSI (NORMAL) PS TAIL SERVO NORMAL BACKUP LDI CONTROLS IN THE AIR #2 HYD PUMP PRESSURE REDUCER PS PILOT ASSIST MODULE FLT PATH STAB SHUTS OFF #1 TAIL ROTOR SERVO SHUTOFF VALVE ON TRANSFER MODULE OPENS #2 TAIL ROTOR SERVO SHUTOFF VALVE & ACTIVATES BACKUP PUMP. #2 RSVR LOW #2 HYD PUMP/RESEVOIR SAS OFF SAS2/FPS COMPUTER 40

UH-60 HYDRAULIC SYSTEM LEAK AT #2 TRANSFER MODULE
CPT MURPHY, NYARNG Copyright 1995 UH-60 HYDRAULIC SYSTEM THERMAL SWITCH (160 DEGREE) DEPRESSURIZATION VALVE (700 PSI) .5 SEC-MAIN GEN 3-5 SEC-APU GEN LEAK AT #2 TRANSFER MODULE BACKUP HYD PUMP OFF ON A U T O (LDI CAN'T ISOLATE LEAK) MOTOR 115 VAC HP BACKUP HYD PUMP if #1 PRI SERVO caution light goes on (#1 primary servo jam), establish a landing attitude, minimize control imputs, and begin a descent. VELOCITY FUSE PS BACKUP HYD RESEVOIR #1 RSVR LOW UTILITY MODULE BACK-UP RSVR LOW #1 HYD PUMP/RESEVOIR #1 TAIL RTR SERVO #1 HYD PUMP BACK-UP PUMP ON YAW SAS ACTUATOR TAIL ROTOR SERVOS Transfer Valve SVO OFF 1ST STG PS PS YAW BOOST PS 1ST STAGE TRANSFER MODULE 2ND STG ROLL SAS ACTUATOR BOOST SERVO OFF 2ND STAGE APU ACCUM LOW APU ACCUMULATOR 1 2 4 PS OPTIONAL 2nd STAGE PS PS 2ND STAGE 1ST STAGE L PITCH SAS ACTUATOR PS PITCH/TRIM ACTUATOR 2ND STAGE 1ST STAGE #1 PRI SERVO PRESS PS A PITCH BOOST SERVO PS #2 TAIL RTR SERVO ON #2 PRI SERVO PRESS PS 2ND STAGE 1ST STAGE F PS COLLECTIVE BOOST SERVO PS TRIM FAIL #2 TAIL ROTOR SHUTOFF VALVE TRANSFER MODULE PRESSURE REDUCER CLOSES IF PRESSURE REACHES 1375 PSI 1000 PSI (NORMAL) PS TAIL SERVO NORMAL BACKUP LDI CONTROLS IN THE AIR #2 HYD PUMP PRESSURE REDUCER PS PILOT ASSIST MODULE FLT PATH STAB SHUTS OFF #1 TAIL ROTOR SERVO SHUTOFF VALVE ON TRANSFER MODULE OPENS #2 TAIL ROTOR SERVO SHUTOFF VALVE & ACTIVATES BACKUP PUMP. #2 RSVR LOW #2 HYD PUMP/RESEVOIR SAS OFF SAS2/FPS COMPUTER 41

#1 HYD PUMP CAUTION LIGHT
CPT MURPHY, NYARNG Copyright 1995 UH-60 HYDRAULIC SYSTEM THERMAL SWITCH (160 DEGREE) DEPRESSURIZATION VALVE (700 PSI) .5 SEC-MAIN GEN 3-5 SEC-APU GEN LEAK IN #1 HYD PUMP BACKUP HYD PUMP OFF #1 HYD PUMP CAUTION LIGHT (UP STREAM FROM THE TRANSFER MODULE) A U T O MOTOR 115 VAC HP BACKUP HYD PUMP ON Light ON - Pressure decreasing to 2000 PSI. Light OFF - Pressure increases to 2350 PSI. VELOCITY FUSE PS BACKUP HYD RESEVOIR #1 RSVR LOW UTILITY MODULE BACK-UP RSVR LOW #1 HYD PUMP/RESEVOIR #1 TAIL RTR SERVO #1 HYD PUMP BACK-UP PUMP ON YAW SAS ACTUATOR TAIL ROTOR SERVOS Transfer Valve SVO OFF 1ST STG PS PS YAW BOOST PS 1ST STAGE TRANSFER MODULE 2ND STG ROLL SAS ACTUATOR BOOST SERVO OFF 2ND STAGE APU ACCUM LOW APU ACCUMULATOR 1 2 4 PS OPTIONAL 2nd STAGE PS PS 2ND STAGE 1ST STAGE L PITCH SAS ACTUATOR PS PITCH/TRIM ACTUATOR #1 PRI SERVO PRESS PS 2ND STAGE 1ST STAGE A PITCH BOOST SERVO PS #2 TAIL RTR SERVO ON #2 PRI SERVO PRESS PS 2ND STAGE 1ST STAGE F PS COLLECTIVE BOOST SERVO PS TRIM FAIL #2 TAIL ROTOR SHUTOFF VALVE TRANSFER MODULE PRESSURE REDUCER CLOSES IF PRESSURE REACHES 1375 PSI 1000 PSI (NORMAL) PS TAIL SERVO NORMAL BACKUP LDI CONTROLS IN THE AIR #2 HYD PUMP PRESSURE REDUCER PS PILOT ASSIST MODULE FLT PATH STAB SHUTS OFF #1 TAIL ROTOR SERVO SHUTOFF VALVE ON TRANSFER MODULE OPENS #2 TAIL ROTOR SERVO SHUTOFF VALVE & ACTIVATES BACKUP PUMP. #2 RSVR LOW #2 HYD PUMP/RESEVOIR SAS OFF SAS2/FPS COMPUTER 42

LEAK IN #1 TAIL ROTOR (LDI ISOLATES LEAK)
CPT MURPHY, NYARNG Copyright 1995 UH-60 HYDRAULIC SYSTEM THERMAL SWITCH (160 DEGREE) DEPRESSURIZATION VALVE (700 PSI) .5 SEC-MAIN GEN 3-5 SEC-APU GEN LEAK IN #1 TAIL ROTOR (LDI ISOLATES LEAK) BACKUP HYD PUMP OFF #1 RSVR LOW A U T O MOTOR 115 VAC HP BACKUP HYD PUMP Light ON - 60% Capacity remaining ON BACKUP PUMP ON VELOCITY FUSE Light ON - Presure increases to 2350 PSI on rise. Light OFF - Pressure decreases through 2000 PSI. PS BACKUP HYD RESEVOIR #1 RSVR LOW UTILITY MODULE BACK-UP RSVR LOW #1 HYD PUMP/RESEVOIR #1 TAIL RTR SERVO #1 HYD PUMP BACK-UP PUMP ON LDI Closes #1 tail rotor servo valve. YAW SAS ACTUATOR TAIL ROTOR SERVOS Transfer Valve SVO OFF 1ST STG PS PS YAW BOOST PS 1ST STAGE TRANSFER MODULE 2ND STG ROLL SAS ACTUATOR BOOST SERVO OFF 2ND STAGE APU ACCUM LOW APU ACCUMULATOR 1 2 4 PS OPTIONAL 2nd STAGE PS PS 2ND STAGE 1ST STAGE L PITCH SAS ACTUATOR PS PITCH/TRIM ACTUATOR PS 2ND STAGE 1ST STAGE #1 PRI SERVO PRESS A PITCH BOOST SERVO PS #2 TAIL RTR SERVO ON #2 PRI SERVO PRESS PS 2ND STAGE 1ST STAGE F PS COLLECTIVE BOOST SERVO PS LDI opens #2 tail rotor servo valve. TRIM FAIL #2 TAIL ROTOR SHUTOFF VALVE TRANSFER MODULE PRESSURE REDUCER CLOSES IF PRESSURE REACHES 1375 PSI 1000 PSI (NORMAL) PS TAIL SERVO NORMAL BACKUP LDI CONTROLS IN THE AIR #2 HYD PUMP PRESSURE REDUCER PS PILOT ASSIST MODULE FLT PATH STAB SHUTS OFF #1 TAIL ROTOR SERVO SHUTOFF VALVE ON TRANSFER MODULE OPENS #2 TAIL ROTOR SERVO SHUTOFF VALVE & ACTIVATES BACKUP PUMP. #2 RSVR LOW #2 HYD PUMP/RESEVOIR SAS OFF SAS2/FPS COMPUTER 43

ACCUMULATOR LOW (NORMAL STARTING)
CPT MURPHY, NYARNG Copyright 1995 UH-60 HYDRAULIC SYSTEM THERMAL SWITCH (160 DEGREE) DEPRESSURIZATION VALVE (700 PSI) .5 SEC-MAIN GEN 3-5 SEC-APU GEN ACCUMULATOR LOW (NORMAL STARTING) BACKUP HYD PUMP OFF A U T O MOTOR 115 VAC HP BACKUP HYD PUMP ROTOR NOT TURNING ON VELOCITY FUSE PS BACKUP HYD RESEVOIR #1 RSVR LOW UTILITY MODULE BACK-UP RSVR LOW #1 HYD PUMP/RESEVOIR #1 TAIL RTR SERVO #1 HYD PUMP BACK-UP PUMP ON YAW SAS ACTUATOR TAIL ROTOR SERVOS Transfer Valve SVO OFF 1ST STG PS PS YAW BOOST PS 1ST STAGE TRANSFER MODULE 2ND STG ROLL SAS ACTUATOR BOOST SERVO OFF 2ND STAGE APU ACCUM LOW APU ACCUMULATOR 1 2 4 PS OPTIONAL 2nd STAGE PS PS 2ND STAGE 1ST STAGE L PITCH SAS ACTUATOR PS PITCH/TRIM ACTUATOR 2ND STAGE 1ST STAGE #1 PRI SERVO PRESS PS A PITCH BOOST SERVO PS #2 TAIL RTR SERVO ON #2 PRI SERVO PRESS PS 2ND STAGE 1ST STAGE F PS COLLECTIVE BOOST SERVO PS TRIM FAIL #2 TAIL ROTOR SHUTOFF VALVE TRANSFER MODULE PRESSURE REDUCER CLOSES IF PRESSURE REACHES 1375 PSI 1000 PSI (NORMAL) PS TAIL SERVO NORMAL BACKUP LDI CONTROLS IN THE AIR #2 HYD PUMP PRESSURE REDUCER PS PILOT ASSIST MODULE FLT PATH STAB SHUTS OFF #1 TAIL ROTOR SERVO SHUTOFF VALVE ON TRANSFER MODULE OPENS #2 TAIL ROTOR SERVO SHUTOFF VALVE & ACTIVATES BACKUP PUMP. #2 RSVR LOW #2 HYD PUMP/RESEVOIR SAS OFF SAS2/FPS COMPUTER 44

ELECTRICAL INTERLOCK SYSTEM
CPT MURPHY, NYARNG Copyright 1995 UH-60 HYDRAULIC SYSTEM THERMAL SWITCH (160 DEGREE) DEPRESSURIZATION VALVE (700 PSI) .5 SEC-MAIN GEN 3-5 SEC-APU GEN LEAK IN #1 PRIMARY SERVO BACKUP HYD PUMP OFF ON A U T O If #2 PRI SERVO PRESS caution light goes on (primary servo jam), establish landing attitude, minimize control imputs and begin a descent. (#1 PRIMARY SERVO SWITCH ISOLATED) MOTOR 115 VAC HP BACKUP HYD PUMP VELOCITY FUSE ELECTRICAL INTERLOCK SYSTEM PS Is active when primary servo pressure is at least 2350 PSI, deactivates when pressure drops below 2000 PSI. BACKUP HYD RESEVOIR #1 RSVR LOW UTILITY MODULE BACK-UP RSVR LOW #1 HYD PUMP/RESEVOIR #1 TAIL RTR SERVO #1 HYD PUMP BACK-UP PUMP ON YAW SAS ACTUATOR TAIL ROTOR SERVOS Transfer Valve SVO OFF 1ST STG PS PS YAW BOOST PS 1ST STAGE TRANSFER MODULE 2ND STG ROLL SAS ACTUATOR BOOST SERVO OFF 2ND STAGE APU ACCUM LOW APU ACCUMULATOR 1 2 4 PS OPTIONAL 2nd STAGE PS PS 2ND STAGE 1ST STAGE L PITCH SAS ACTUATOR PS PITCH/TRIM ACTUATOR 2ND STAGE 1ST STAGE #1 PRI SERVO PRESS PS A PITCH BOOST SERVO PS #2 TAIL RTR SERVO ON #2 PRI SERVO PRESS PS 2ND STAGE 1ST STAGE F PS COLLECTIVE BOOST SERVO PS TRIM FAIL #2 TAIL ROTOR SHUTOFF VALVE TRANSFER MODULE PRESSURE REDUCER CLOSES IF PRESSURE REACHES 1375 PSI 1000 PSI (NORMAL) PS TAIL SERVO NORMAL BACKUP LDI CONTROLS IN THE AIR #2 HYD PUMP PRESSURE REDUCER PS PILOT ASSIST MODULE FLT PATH STAB SHUTS OFF #1 TAIL ROTOR SERVO SHUTOFF VALVE ON TRANSFER MODULE OPENS #2 TAIL ROTOR SERVO SHUTOFF VALVE & ACTIVATES BACKUP PUMP. #2 RSVR LOW #2 HYD PUMP/RESEVOIR SAS OFF SAS2/FPS COMPUTER 45

UH-60 HYDRAULIC SYSTEM NORMAL OPERATIONS L A F 46
CPT MURPHY, NYARNG Copyright 1995 UH-60 HYDRAULIC SYSTEM THERMAL SWITCH (160 DEGREE) DEPRESSURIZATION VALVE (700 PSI) .5 SEC-MAIN GEN 3-5 SEC-APU GEN NORMAL OPERATIONS BACKUP HYD PUMP OFF A U T O MOTOR 115 VAC HP BACKUP HYD PUMP VELOCITY FUSE 1 GPM (NORMAL) SHUTDOWN AT 1.5 GPM ON PS BACKUP HYD RESEVOIR #1 RSVR LOW UTILITY MODULE BACK-UP RSVR LOW #1 HYD PUMP/RESEVOIR #1 TAIL RTR SERVO #1 HYD PUMP BACK-UP PUMP ON YAW SAS ACTUATOR TAIL ROTOR SERVOS Transfer Valve SVO OFF 1ST STG PS PS YAW BOOST PS 1ST STAGE TRANSFER MODULE 2ND STG ROLL SAS ACTUATOR BOOST SERVO OFF 2ND STAGE APU ACCUM LOW APU ACCUMULATOR 1 2 4 PS OPTIONAL 2nd STAGE PS PS 2ND STAGE 1ST STAGE L PITCH SAS ACTUATOR PS PITCH/TRIM ACTUATOR 2ND STAGE 1ST STAGE #1 PRI SERVO PRESS PS A PITCH BOOST SERVO PS #2 TAIL RTR SERVO ON #2 PRI SERVO PRESS PS 2ND STAGE 1ST STAGE F PS COLLECTIVE BOOST SERVO PS TRIM FAIL #2 TAIL ROTOR SHUTOFF VALVE TRANSFER MODULE PRESSURE REDUCER CLOSES IF PRESSURE REACHES 1375 PSI 1000 PSI (NORMAL) PS TAIL SERVO NORMAL BACKUP LDI CONTROLS IN THE AIR #2 HYD PUMP PRESSURE REDUCER PS PILOT ASSIST MODULE FLT PATH STAB SHUTS OFF #1 TAIL ROTOR SERVO SHUTOFF VALVE ON TRANSFER MODULE OPENS #2 TAIL ROTOR SERVO SHUTOFF VALVE & ACTIVATES BACKUP PUMP. #2 RSVR LOW #2 HYD PUMP/RESEVOIR SAS OFF SAS2/FPS COMPUTER 46

UH-60 HYDRAULIC SYSTEM L A F 47 THERMAL SWITCH (160 DEGREE)
DEPRESSURIZATION VALVE (700 PSI) .5 SEC-MAIN GEN 3-5 SEC-APU GEN UH-60 HYDRAULIC SYSTEM CPT MURPHY, NYARNG Copyright 1995 BACKUP HYD PUMP OFF VELOCITY FUSE 1 GPM (NORMAL) SHUTDOWN AT 1.5 GPM A U T O MOTOR 115 VAC HP BACKUP HYD PUMP ON PS BACKUP HYD RESEVOIR #1 RSVR LOW UTILITY MODULE BACK-UP RSVR LOW #1 HYD PUMP/RESEVOIR #1 TAIL RTR SERVO #1 HYD PUMP BACK-UP PUMP ON YAW SAS ACTUATOR TAIL ROTOR SERVOS Transfer Valve SVO OFF 1ST STG PS PS YAW BOOST PS 1ST STAGE TRANSFER MODULE 2ND STG ROLL SAS ACTUATOR BOOST SERVO OFF 2ND STAGE APU ACCUM LOW PS PS 4 2ND STAGE 1ST STAGE L PITCH SAS ACTUATOR 2 PS 1 PS OPTIONAL 2nd STAGE APU ACCUMULATOR PITCH/TRIM ACTUATOR #1 PRI SERVO PRESS PS 2ND STAGE 1ST STAGE A PITCH BOOST SERVO PS #2 TAIL RTR SERVO ON #2 PRI SERVO PRESS PS 2ND STAGE 1ST STAGE F PS COLLECTIVE BOOST SERVO PS TRIM FAIL #2 TAIL ROTOR SHUTOFF VALVE TRANSFER MODULE PRESSURE REDUCER CLOSES IF PRESSURE REACHES 1375 PSI 1000 PSI (NORMAL) PS TAIL SERVO NORMAL BACKUP LDI CONTROLS IN THE AIR #2 HYD PUMP PRESSURE REDUCER PS PILOT ASSIST MODULE FLT PATH STAB SHUTS OFF #1 TAIL ROTOR SERVO SHUTOFF VALVE ON TRANSFER MODULE OPENS #2 TAIL ROTOR SERVO SHUTOFF VALVE & ACTIVATES BACKUP PUMP. #2 RSVR LOW #2 HYD PUMP/RESEVOIR SAS OFF SAS2/FPS COMPUTER 47

UH-60 SYSTEMS BREAKDOWN HANDOUT
NEW YORK ARMY NATIONAL GUARD ARMY AVIATION SUPPORT FACILITY 1 HANGER A, LONG ISLAND MACARTHUR AIRPORT RONKONKOMA, NEW YORK 11779 QUESTIONS OR IMPROVEMENTS CONTACT CPT. EDWARD J MURPHY (516) Copyright 1995 c 48

CPT MURPHY, NYARNG Copyright 1995

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