1
Q
Modules of the Engine
A
- Cold Section
- Hot Section
- Power Turbine
- Accessory Gear Box
2
Q
Types of LRU’s (Five)
A
- Accessory Section
- Fuel System
- Electrical
- Oil System
- Air System
3
Q
Cold Section Module
A
- Inlet Particle Separator (IPS)
- Compressor
- Output Shaft Assembly
4
Q
Input Particle Separator (IPS) Components
A
- Output Shaft Assembly
- Swirl Frame
- Power Take Off (PTO)
- Front Frame
- Main Frame
- Scroll Case
5
Q
Compressor Function
A
Six stage air pump that continuously pressurizes combustion chamber, provides bleed air and cools hot section.
- 5 stage axial compressor and 1 stage centrifugal
6
Q
Hot Section Module
A
- Combustion Liner
- Stage 1 Nozzle
- Stage 1/2 Gas Generator (GG) Rotor
- GG Stator
7
Q
Power Turbine Module
A
- Turbine Case
- Power Turbine Rotor Assembly
- Power Turbine Drive Shaft Assembly
- Exhaust Frame
- C-Sump Assembly
8
Q
Electrical Connection Harness (Six)
A
Red Cables - Integrated Vehicle Health Monitoring System (IVHMS)
Yellow Cables - Engine electrical supply
Green Cables - Cockpit Indications
Blue Cables - Overspeed Sensors
Black Cables - Igniters, Exciters (Protective Heat Wrap)
White Cables - Airframe to engine electrical interface
9
Q
What drives the accessory gear box?
A
Gas Generator (Variable speeds)
10
Q
How many stages are there in the compressor section?
A
6 - 5 axial and 1 centrifugal
11
Q
What are the two operational sections of the engine?
A
Gas Generator (NG) and Power Turbine Speed (NP)
12
Q
How does the cockpit receive the NG signal?
A
NG winding of the alternator
13
Q
If NG signal is lost, what happens?
A
ENG OUT warning light and audio appears with 0% NG indicated
14
Q
Engine Fuel Flow
A
- Fuel Selector Valve
- Engine Drive Boost Pump
- Pressure Sensor and Filter
- HMU
- L2L Cooler
- ODV
- Fuel Injectors
15
Q
What happens when the fuel filter clogs?
A
Bypass indicator pops out and bypass valve opens
16
Q
Direct Current
A
Flow of electrons in one direction
17
Q
Alternating Current
A
Flow of electrons that reverses its direction at regularly recurring intervals
18
Q
Generators
A
- Converts mechanical energy into electrical
- Primary source of AC
19
Q
Converter
A
- Converts AC to DC
- Primary source of DC
20
Q
Battery Power
A
- Secondary source of DC
- Day: 15 Minutes
- Night: 12 Minutes
21
Q
What is a bus?
A
Heavy duty conductor that distributes electricity throughout a circuit
22
Q
Current Limiter vs Circuit Breaker
A
- Current limiters are one time use; must be replaced
- Circuit Breaker can be reset and used again, once fault is corrected
23
Q
AC Power Priority
A
- Main Generators
- APU Generator
- External Power
24
Q
GEN 1/2 BRG FAIL
A
- Write up to replace within 10 flight hours
25
What has priority over Windshield Anti-Ice when APU Gen is the sole source of power?
Backup hydraulic pump
26
How many generators are required during Blade De-Ice operations?
2
27
What components converts 115 VAC to 26 VAC?
Auto-Transformers
28
AC REF BUS DEGRAD Advisory
One or both Auto-Transformers has failed or AC power was lost
29
Dual Generator vs Dual Converter Fail
Dual generator has AC REF BUS DEGRAD Advisory and no fuel indications on EICAS
30
If both converters would fail which buses would be lost?
Both DC Primary buses
31
Only functioning MFD on battery power
MFD 3
32
Refueling Types
Primary: JP-8
Standard: JP-5
Alternative: JP-4
33
Three refueling methods
- Gravity
- Pressure
- Closed Circuit
34
Where does the APU draw its fuel?
No.1 Main Fuel Cell
35
What does XFD position do?
Draws fuel from opposite tank
36
FUEL 1/2 LOW Caution appears when?
Approx 172lbs of fuel
37
Closed Circuit Refueling Pressure
15psi at 110GPM
38
Pressure Refueling Pressure
55psi at 300GPM
39
Both main fuel tanks are in the ______ section of the aircraft.
Transition
40
The engine driven fuel boost pumps are driven by?
NG Section of the engine
41
What component purges fuel from main fuel manifold to prevent coking?
Overspeed and Drain Valve (ODV)
42
What alerts the pilot if fuel filter is being bypassed?
FUEL 1/2 BYPASS Caution
43
What component allows heat to be transferred from engine oil to the fuel?
Liquid to Liquid Cooler
44
The APU uses approximately how many pounds per hour?
120lbs per hour
45
The APU fuel is supplied from which main fuel cell?
No.1 Fuel Cell
46
What component controls the operation of the APU?
Digital Electronic Sequence Unit (DESU)
47
The PRIME BST PUMP ON advisory indicates what?
APU Boost Pump Switch is in the Prime or Boost position
48
FUEL 1 PRESS LOW Caution indicates what?
Fuel pressure on ENG 1 is below 9psi
49
What can happen if both the FUEL 1 PRESS LOW and FUEL 2 PRESS LOW cautions appear?
Flameout; Do not make rapid collective movements.
50
Underlined step for FUEL 1/2 BYPASS Indications
Land As Soon As Possible
51
Electronic Standby Instrument System (ESIS)
Provides the pilots with a visual display as a backup to the helicopter's PFD
-Pitch and Roll
- Airspeed
- Altitude
- Vertical Speed
- Heading
- Validity Indications
52
ESIS Components
- Display Unit
- Magnetometer
- Air Data Computer (ADC)
- Battery
53
Two external components that provide display information to the ESIS
- ADC
- Magnetometer
54
How long should the ESIS battery supply power?
30 Minutes
55
Where in the cockpit is the BATTERY STBY INST switch located?
Upper Console
56
In which position should the BATTERY STBY INST switch be for a beeping tone to be audible when aircraft is on ground with AC power removed?
ARM
57
ESIS Modes of Operations
- Power-on Self Test
- Identification
- Sensor Alignment
- Extended Maneuver
- Directional Gyro / Free Mode
58
What does a superimposed red X in the display area indicate?
Loss of info from a source unit (ADC / Magnetic Sensor) or internal sensors (Heading tape)
59
What might appear as a result of long duration attitude events lasting more than 6 minutes?
EXT MANUV
60
IVHMS Overview
- Improves maintenance capability, system readiness and extends capability of aircraft
- Automated recorded data
61
Beacon Batter Specs
- Activated when water switch is submerged
- 30 Day operating life
- 6 Year useful life
62
Length of IVHMU on-board memory data
Approximately 25 hours
63
Where is the Acoustic Locating Device mounted?
Ceiling cabin on the IVHMS Unit
64
What console in the cockpit is the Data Transfer Unit installed in?
Lower Console
65
What components make up the IVHMU?
- Health and Usage Monitoring System (HUMS)
- Flight Data Recorder (FDR) / Cockpit Voice Recorder (CVR)
- Acoustic Beacon
66
Intermittent Event Switch
- 30 Seconds aircraft flight data
- 30 Seconds cockpit noise data
- 5 Seconds of rotor track and balance data
67
How is IVHMS data transferred from the aircraft to the ground station?
PCMCIA Card
68
What starts / stops the recording of the CVR/FDR?
DCUs
69
What are the components of the AVCS?
- Active VIbration Control Computer (AVCC)
- Electronic Unit (EU)
- Force Generators x3
- Accelerometers x10
- VIB CONT Switch
- NR Speed Sensor
70
Where is the AVCC and EU installed?
Quad Bay Antenna Wall
71
The AVCS VIB CONT switch is located where?
Upper Console
72
AVCS INOP Advisory
During run-up, ensure the advisory disappears above 90% NR
73
The normal NR operating range for the Active Vibration Control System is?
90 - 105% NR
74
The FMS can be accessed to check the ________ or initiate a _________ of the Active Vibration Control System.
- Status
- Built In Test (BIT)
75
The AVCS INOP Advisory illuminating in flight indicates?
Total failure of the AVCS
76
Main XMSN Modules
- Main Module
- Two Input Modules
- Two Accessory Modules
77
Main Module Components
- Main Bevel Gear
- Planetary Gears
78
Which accessory module has a low oil pressure switch and chip detector?
Left
79
How many modules make up the XMSN?
Five
80
Each accessory module drives what?
Main Generator and Hydraulic Pump
81
Oil pressure should remain in what psi range?
45 - 60psi
82
The fuzz burn-off feature is deactivated at what temperature?
140°C
83
How long can the intermediate and tail gear box run at cruise with loss of all oil?
30 Mins
84
What is the maximum NR for normal shutdown operations of the rotor brake?
NR below 40% and 150-180psi applied in no less than 12 seconds
85
With rotor brake applied, what is the contigency which allows you to move the PCLs from idle to fly?
Idle Inter-lock Lever
86
What prevents movement of the engine power levers from idle to fly?
Rotor Brake Solenoid
87
Advantage of wide chord blades
Increased maneuverability
88
Three control inputs connecting the primary servos to the main rotor swashplate
- Forward
- Aft
- Lateral
89
How many degrees is the tail rotor canted on the tail pylon?
20°
90
Severity of vibrations can usually be minimized by?
Reducing airspeed
91
Criteria for EDECU to swap to TGT Limiting contingency power?
- 3% Below reference NP
- 96% NR
- Rate of 5% per second
92
AFCS Overview
Enhances stability and handling qualities of the helicopter
93
Static Stability
Tendency the aircraft possess based on its design that allows it to maintain its original flight path (Long Term)
94
Dynamic Stability
Oscillation dampening about the pitch, roll, and yaw axis in the least amount of time
95
Inner and Outer Loop
Inner Loop: SAS, Dynamic Stability
Outer Loop: Trim/FPS, Autopilot
Pilot has overriding capabilities over SAS and Trim
96
Five basic subsystems of AFCS
- SAS
- Trim
-Stabilator
- FPS
-Flight Director
97
AFCS is comprimised of three parts
Sensors, Processors and Actuators
98
What is the central component of the AFCS system?
Two redundant FCCs
99
Which FCC is the only one that can send signals to the trim actuators?
No. 2 FCC
100
Which caution indicates majority of AFCS has shut down?
AFCS FAIL
101
Stabilator System
Variable angle of incidence airfoil that enhances handling and qualities in the pitch axis
102
Stabilator Manual Mode
Any ADC airspeed becomes invalid
103
Stabilator Functions (SCALP)
- Streamline at low airspeeds
- Collective Coupling
- Angle of Incidence
- Lateral Sideslip
- Pitch Coupling
104
Four signals used by FCC to position Stabilator? (CLAP)
- Collective
- Lateral Accelerometer
- Airspeed
- Pitch Rate
105
What provides the FCCs with pitch rate information?
EGIs
106
Purpose of SAS
Enhance dynamic stability of aircraft in pitch, roll and yaw axis. Limited in control authority (5% per)
107
What does SAS DEGRADED advisory mean?
Pitch, roll or yaw SAS channels from SAS 1/2 has disengaged due to a fault
108
Which caution indicates a failure that affects both SAS 1/2 or that hydraulic pressure is below minimum?
SAS OFF
109
How to release yaw trim above 50 Knots?
Press pedal switches and Cyclic TRIM REL Switch
110
Collective trim beeper can be used below 50KIAS for the yaw axis to adjust what?
Left or right heading
111
Flight Path Stabilization (FPS)
Maintains pitch and roll attitude, and heading during cruise flight. Provides coordinated turn feature above 50KIAS
112
Caution that one or more of the FPS functions have disengaged due to failure
FPS FAIL
113
What kind of functions does the Trim perform when FPS is engaged?
Basic Autopilot
114
What caution appears when one or more functions of the FD has disengaged?
FLT DIR FAIL
115
What caution appears when a coupled FD automatically decouples due to failure
FD COUPLE FAIL
116
Flight Controls Systems Overview
Movement of flight controls are transmitted mechanically through trim actuators, pilot assist servos, through the MMU to the primary servos to increase/decrease tail rotor pitch
117
Malfunction Types
Leak - RSVR LOW
Pump Fail - HYD PUMP FAIL
Component Fail - SERVO
118
Flight Control Sections
- Cockpit Controls
- Pilot Assist
- MMU
- Tail Rotor Cables
- Tail Rotor Quadrant
119
Pilot Assist Area
Contains trim actuators, collective and yaw boost servos, SAS actuators and pilot assist module
120
AFCS Control Panel
- Stabilator Control
- Auto Flight Control
121
Stability Augmentation System (SAS)
Pitch, Roll and Yaw actuators controlled by the FCCs
122
Mechanical Mixing Unit (MMU)
Designed to reduce inherent control coupling by combining, summing, and coupling collective, pitch, and yaw inputs
123
Collective to Pitch
Compensates effects of changes in rotor downwash on stabilator caused by collective pitch changes (Rotor Disk tilt FWD/AFT to collective)
124
Collective to Roll
Compensates rolling moments of translating tendency caused by changes in tail rotor thrust (Pull in collective adds left rotor disk tilt)
125
Collective/Airspeed to Yaw Mixing
Compensates for the Q effect caused by changes in collective position
126
Four Mechanical Mixes provided by MMU
- Collective to Pitch
- Collective to Roll
- Collective to Yaw
- Yaw to Pitch
127
TAIL ROTOR QUAD FAIL Caution
One or both tail rotor cables has failed
128
If only one cable breaks, what kind of aircraft control does the pilot have?
Full aircraft control
129
If both cables break, how does the pilot control yaw?
Airspeed dependent on the aircraft GWT
130
Hydraulic Modules
- Utility Module
- Pilot Assist Module
- Transfer Modules
131
No. 1 Transfer Module
- 1st Stage Primary Servos shutoff valve
- No. 1 HYD PUMP pressure switch
- 1st Stage Tail Rotor shutoff valve
132
No. 2 Transfer Module
- Pilot Assist Module shutoff valve
- No. 2 HYD PUMP pressure switch
- 2nd Stage Primary Servos shutoff valve
133
Velocity Fuse
Supplies hydraulic fluid charge to APU starter. Compresses nitrogen
134
LDI and Logic Modules
- Turn on advisories and/or cautions
- Open/Close appropiate valves addressing malfunction
- Command backup pump to operate
135
Leak Detection / Isolation (LDI)
Protects flight control hydraulic system by preventing further loss of hydraulic fluid in case of leak
136
What does moving the SERVO OFF switch from NORM to 1ST/2ND STG do?
Turns that stage (1st/2nd) of the three primary servos off
137
What prevents the two stages of primary servos from being turned off simultaneously?
Electrical Interlock
138
Which panel contains the TAIL SERVO and BACKUP HYD PUMP switches?
MISC SWITCH Panel
139
How much fluid must leak for the RSVR LOW Caution to activate?
Less than 60% fluid remaining
140
What are the No. 1/2 Hydraulic Pumps mounted to and driven by?
Accessory Modules
141
What is the backup pump driven by?
Electric Motor
UH-60M
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