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UH-60 SYSTEMS REVIEW. 25 FEB 97. ALTERNATOR PROVIDES. NG SIGNAL TO COCKPIT POWER IGNITION POWER TO THE ECU. ELECTRONIC CONTROL UNIT (ECU). TGT LIMITING AT 850 (837-849) NP GOVERNOR AT 100 % (TO INC/DEC SW 96.4 - 100.5) NP OVERSP 106 +- 1(BRAIN)

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Alternator provides
ALTERNATOR PROVIDES

  • NG SIGNAL TO COCKPIT

  • POWER IGNITION

  • POWER TO THE ECU


Electronic control unit ecu
ELECTRONIC CONTROL UNIT (ECU)

  • TGT LIMITING AT 850 (837-849)

  • NP GOVERNOR AT 100 % (TO INC/DEC SW 96.4 - 100.5)

  • NP OVERSP 106 +- 1(BRAIN)

  • LOAD SHARING (TORQUE MATCH) 5 % (SIGNAL TO OTHER ENG)

  • NOTE: NP OVERSPEED PROTECTION FROM POU, WITH AN ECU FAILURE


Hydro mechanical unit hmu
HYDRO MECHANICAL UNIT (HMU)

  • FUEL PUMPING

  • FUEL FLOW METERING

  • ACCEL/DECEL LIMITING

  • NG LIMITING / NG SHUTDOWN @110%.

  • VG AND ANTI-ICE START BLEED VALVE POSITIONING

  • TORQUE MOTOR (ECU INPUT) TO TRIM IAW NG OUTPUT (YELLOW WIRE) TGT LIMITING,LOAD SHARING, NG GOVERNOR

  • LDS (COLL INPUT) TO MATCH NG OUTPUT TO MAIN ROTOR LOAD DEMANDS.

  • PAS (PWR CONTROL. LEVER INPUT) TO SET MAX POWER AVAILABLE AND OVERRIDE TO ECU (LOCKOUT IN A MALFUNCTION)

  • VAPOR VENT FOR PRIMING


Pressurinzing overspeed unit pou
PRESSURINZING OVERSPEED UNIT (POU)

  • SEQUENCE PRIMER FUEL

  • SEQUENCE MAIN FUEL

  • PURGE START/MAIN FUEL

  • PROVIDES NP OVERSPEED PROTECTION (MUSCLE), NEEDS THE ECU.


Afcs is made up of
AFCS IS MADE UP OF

  • SAS (1 AND 2)

  • FPS

  • TRIM

  • STABILATOR


FPS

  • BELOW 60 KIAS ABOVE

  • ATT HOLD PITCH ATT HOLD/A/S

  • ATT HOLD ROLL ATT HOLD

  • HDG HOLD YAW HDG HOLD/TURN

  • NOTE: FPS MUST HAVE SAS 1 OR 2, YAW BOOST AND TRIM SYSTEM


Fuel sys flow
FUEL SYS FLOW

  • PUMP (SUBMERGED)

  • PRIME BOOST PUMP (#1 ENG/APU)

  • PUMP (ENG. DRIVEN)

  • FILTER BYPASS 18-22 PSID

  • HMU

  • LIQUID TO LIQUID COOLER

  • POU, .18% NG START FUEL ENDS

  • ENGINE


Four items on the rear of the eng l to r
FOUR ITEMS ON THE REAR OF THE ENG (L TO R)

  • PARTICLE SEP BLOWER

  • POU VALVE (BLUE WIRE-NP SOLENOID)

  • HMU

  • STARTER DRIVE

  • NOTE: ACTUATOR UNDER THE HMU IS FOR VG LINK


Front of accy section l to r
FRONT OF ACCY SECTION(L TO R)

  • OIL TEMP SENSOR (150)

  • OIL PRESS SENSOR(<20 DEG)

  • ALTERNATOR

  • OIL FILTER

  • FUEL BOOST PUMP

  • OIL COOLER

  • FUEL FILTER


Stabilator
STABILATOR

  • THE ANGLE OF INCIDENCE IS CHANGED BY TWO ELECTRIC ACTUATORS


5 functions of the stabilator scalp
5 FUNCTIONS OF THE STABILATOR: SCALP

  • STREAMLINES STABILATOR <30 KTS

  • COLLECTIVE COUPLING:COMPENSATES FOR AIRCRAFT MOVEMENT

  • ANGLE OF INCIDENCE: LEVEL FUSELAGE AS AIRCRAFT INCREASES SPEED

  • LATERAL EXCURSIONS: INPUT FROM ACCELEROMETERS: RIGHT, STAB DOWN, LEFT STAB EDGE UP

  • PITCH RATE FEEDBACK: PITCH GYRO


Wow switch itabush
WOW SWITCH (ITABUSH)

  • IFF MODE 4

  • THERMAL SWITCH

  • AUDIO WARNING: LOW RPM

  • BACKUP PUMP-AUTO IS REMOVED

  • UNDERFREQENCY PROTECTION-GEN 95%RPM R

  • SAS/FPS DISABLED

  • HYD LEAK SYS ACTIVATED (HYD LEAK TEST SWITCH)


Load sharing
LOAD SHARING

  • LOW ENGINE INCREASES POWER BECAUSE OF LOAD SHARING AND THE HIGH ENG WILL DECREASE POWER BECAUSE NP GOVERNING


Pcl lockout
PCL LOCKOUT

  • ENGINE RESPONSE IS MUCH FASTER AND TGT LIMITING IS INOPERATIVE. CARE MUST BE TAKEN NOT TO EXCEED TGT LIMITS AND KEEP %RPMR AND %RPM 1 AND 2 OPERATING RANGE


4 mechanical mixes
4 MECHANICAL MIXES

  • COLLECTIVE TO PITCH: DOWNWASH

  • COLLECTIVE TO YAW: TORQUE

  • COLLECTIVE TO ROLL: TRANLATING TENDENCY

  • YAW TO PITCH: VERTICAL THRUST

  • NOTE: MINIMIZES INHERENT CONTROL COUPLING.


Backup pump op s
BACKUP PUMP OP’S

  • BACKUP PUMP WITH RESEVOIR (MICRO SW 60% REMAIN, AC MOTOR, DEPRESSURIZATION VALVE OPERATES AT 700 PSI

  • UTIL MODULE, BACKUP PUMP ADV LIGHT ,SLAM VALVE (VEL FUSE) 1.5 GPM.

  • 2ND STAGE T/R SERVO AND #2 T/R LIGHT

  • APU ACCUMULATOR: HYD FLUID WITH A RETURN LINE AND NITROGEN TO THE GAUGE WITH ACCUM LOW LIGHT FOR 2800 PSI AND BELOW.


B u pump activation
B/U PUMP ACTIVATION

  • #1 RES LOW

  • #1 HYD PUMP

  • #1 T/R SERVO

  • #2 HYD PUMP

  • APU ACCUM LOW


Leak isolation
LEAK ISOLATION

  • LDI- IS USED IN #1 T/R SERVO AND PILOT ASSIST AREA

  • TRANS MOD-IN THE HYD PUMPS

  • PILOT-PRIMARY SERVO

  • NOTE: THE HYD LEAK TEST SW CONTROLS THE LDI’S THROUGH THE LOGIC MODULE FOR 1 AND 2 HYD SYS


1 hyd sys op s
#1 HYD SYS OP’S

  • 1 HYD PUMP WITH RETURN AND PRESS FILTER RES LOW SW (60%)

  • TRANS MODULE WITH PRESS SW (2000 PSI) TRANS VALVE FOR B/U SYS AND LDI FOR 1T/R SERVO

  • 1ST STAGE SERVO L-R IS FOR,AFT,LAT WITH PRIM SERVOPRESS SW LIGHT

  • 1 STAGE T/R SERVO(INSIDE GEAR BOX) WITH 1 T/R LIGHT


Pilot assist area
PILOT ASSIST AREA

  • COLL BOOST SERVO(PWR STEERING) (GRUNT FACTOR)

  • PITCH BOOST SERVO (DAMPENS SAS FEEDBACK)

  • PITCH SAS ACTUATOR(STABILITY)

  • PITCH TRIM ACTUATOR (LONG AXIS AND ATTITUDE, CONTROLLED BY FPS AND TRIM BUTTON) 1000 PSI

  • ROLL SAS ACTUATOR (STABILITY)

  • YAW SAS ACTUATOR (STABILITY)

  • YAW BOOST ASSEMBLY(PWR STEER) (GRUNT FACTOR)

  • ROLL/YAW TRIM ACTUATOR (ELECT)

  • NOTE: COLL/YAW BOOST HAVE PRESS SW FOR SEG LIGHT


2 hyd sys op s
#2 HYD SYS OP’S

  • 2 HYD PUMP WITH RETURN AND PRESS FILTER RES LOW SW (60%)

  • TRANS MODULE WITH PRESS SW (2000 PSI) TRANS VALVE FOR B/U SYS AND LDI FOR PILOT ASSIST MODULE/AREA,PRIMARY SERVOS

  • 2ND STAGE SERVO L-R IS FOR,AFT,LAT WITH PRIM SERV PRESS SW LIGHT

  • PILOT ASSIST MODULE HAS SHUT OFF VALVES TO BOOST SERVO, SAS AND PITCH/TRIM ACTUATOR AND SAS OFF,BOOST SERVO,FPS,TRIM FAIL PRESS SW


Glide slope dev pointer
GLIDE SLOPE DEV POINTER

  • .25 DEG PER DOT


Processed information
PROCESSED INFORMATION

  • ROLL COMMAND BAR

  • PITCH COMMAND BAR (AIRSPEED)

  • COLLECTIVE POSITION INDICATOR

  • NOTE: ALL PROCESSED INFORMATION HAS YELLOW INDICATORS

  • NOTE: CIS MODE SEL WITH HDG, NAV AND ALT GIVES THIS!!


Rule of 5 for cis
RULE OF 5 FOR CIS

  • #1 POINTER - DOPPLER

  • #2 POINTER- ADF AND VOR

  • COURSE DEV BAR (HSI)- DOPPLER,VOR AND LOCALIZER

  • COURSE DEV POINTER (VSI) DOPPLER , VOR, LOCALIZER, FM HOME.

  • ROLL COMMAND BAR(VSI)- VOR, HDG DOPPLER, LOCALIZER, FM HOME,


Hdg and nav sel
HDG AND NAV SEL

  • IF YOUR HEADING AND NAV ARE SELECTED YOU WILL BE IN HDG MODE.

  • NOTE: NAV SW OPS, COMMANDS 45 DEG INTERCEPTOF SELECTED COURSE (HSI COURSE WINDOW. WHEN HDG MODE IS NOT SELECTIED, WITHIN 10 DEG OF VOR COUSE, 2.5 DEG LOCALIZER CENTER, CAUSES HEADING MODE TO DROP OUT AUTOMATICALLY WEN WITHIN CAPT ZONE.


Engine starts
ENGINE STARTS

  • AIR ASSISTED (PNEUMATIC)

  • ENG AIR INLET IS OPEN AT 4 DEG AND CLOSED AT 13 DEGS

  • APU START - HYDRAULIC ASSISTED


Miscellanous info
MISCELLANOUS INFO

  • TORQUE Q1 AND Q2 WITHIN 5%

  • LOW ROTOR AUDIO 95%

  • NG ENGINE OUT 55%

  • MIN ENG OIL PSI 20 PSI, 35 PSI AT 90 % NG.

  • TGT LIMITING 850 DEG C

  • BEST COCKPIT INDICATIONS RPMR AND TGT

  • ENGINE CORRELATION: TGT - NG - TQ AND %RPMR WITH ENG 1 AND 2 100%

  • OIL TANK 1.7 GAL, BYPASS COOLER BELOW 71 DEG C 1 QUART PER 6.5 FLT HR


Engine sections
ENGINE SECTIONS

  • COLD SECTION MODULE

  • ACCESSORY SECTION

  • HOT SECTION INSERTED IN THE CENTER OF THE COLD SECT

  • POWER TURBINE SECTION


Pneumatic sys
PNEUMATIC SYS

  • 4% LESS MAX TORQ AVAIL DUAL ENG/ HEATER

  • 16% MAX TORQ AVAIL SINGLE ENG/ ANTICE

  • 18% MAX TORQ AVAIL SING ENG/ CROSS BLEED START


Interconnecting harnesses
INTERCONNECTING HARNESSES

  • YELLOW: SUPPLIES PWR FROM ENG ALTERNATOR (ENG FUNCTIONS)

  • BLUE: OVERSPD SIGNAL

  • GREEN: COCKPIT INSTR SIGNALS

  • BLACK: IGNITION, 2 IGNITORS


Miscellanous info1
MISCELLANOUS INFO

  • DESIGN WEIGHT 16,825, MAX 22,000 MODIFIED

  • DECK LOAD LIMIT 300 LBS PER SQ FT

  • TRANSITIONS SECTION 2 MAIN TANKS 180 GAL EACH 1 ON LEFT 2 ON RIGHT

  • TAIL PHLON MOUNTING FOR INTERMEDIATE GEARBOX 58 DEG AND TAIL GEARBOX 105 DEG

  • MAIN ROTOR FULLY ARTICULATED

  • T/R CANTER 20 DEG, 400 LBS LIFT at 16,250, 2.5 % BWEIGHT


Miscellanous info2
MISCELLANOUS INFO

  • STABILATOR 14.4 FT LONG ONE PIECE

  • ANG OF INCID CHG BY 2 ELECT ACCUATORS

  • LANDING GEAR strock 11.25 g

  • AIRFRAME SECT NOSE(crew), MID (pax), AFT (TRANITION)(FUEL), TAIL CONE, TAIL ROTOR PYLON, HORIZONTAL STAB, MAIN ROTOR PYLON


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