SY1103-05 Electrical System Flashcards
(178 cards)
1
Q
How many Generators and characteristics
A
- two (left and right)
- three-phase AC Generators
2
Q
What RPM range are the generators fully operational
A
43-48% is the “cut-in range”
3
Q
When is the gearbox shift range to keep Generators in limits
A
65-75%
4
Q
With a generators switch in the off position, does the generator stop?
A
No, it’s disconnected from bus to protect system
5
Q
How many protection panels?
A
-two, one for each generator and the bus, which will disconnect gen from bus to protect system
6
Q
What powers static inverter
A
battery bus which converts DC to AC pwoer
7
Q
Function of static inverter
A
- changes DC to AC for engine starts
- supplies AC pwr to both cockpits right EED AC sensors (Fuel/O2) allows you to check right engine during engine start or AC failure
8
Q
How is static inverter activated
A
- push either start button
- move throttle into AB
- GAGE TEST/ QTY Check switch
9
Q
AC-powered instruments
A
- liquids
- Oil Px, Fuel Flow (also needs Lft essential bus to work 100%) Hydraulic Px, fuel quantity, O2 quantity
- RPM AC but have own power source
10
Q
Caution Panel Lights (WCA)
A
-DC powered to be bright
11
Q
GENERATOR illuminates
A
Connected to the bus contactor. Illuminates when the generator is disconnected from the AC bus circuit. Does not necessarily indicate generator failure.
12
Q
HYDRAULIC illuminates
A
Connected directly to the hydraulic pressure sensors and is independent of the gages. Illuminates when the pressure drops below 1,500 psi or during an overtemperature.
13
Q
FUEL PRESSURE illuminates
A
Connected to a sensor in the fuel lines downstream from the fuel boost pumps. Illuminates when line pressure drops below 6 psi (normal is 10 psi). Does not necessarily indicate boost pump failure.
14
Q
ENG ANTI-ICE ON illuminate
A
Connected to the anti-ice switch. Illuminates when the switch is turned ON or when the right AC fails with no crossover. The light does not illuminate when the system activates automatically with the engine RPM below 65%.
15
Q
OXYGEN illuminates
A
Connected to the oxygen quantity indicator gage. Illuminates when the indicator is at or below one liter. May blink due to sloshing in the reservoir when quantity is three liters or less.
16
Q
FUEL LOW illuminates
A
Connected to the EED fuel quantity indicators and a time delay circuit. Illuminates 7.5 seconds after either indicator reads below 250 pounds. Once the MASTER CAUTION light is reset, it will not relight after the second fuel quantity gage decreases. The indicators must be visually checked to determine which system is low.
17
Q
XFMR RECT OUT
A
This light illuminates when there is a possible failure of both transformer-rectifiers. The battery powers both essential DC busses and should last approximately 15 minutes if fully charged.
18
Q
If both TRUs fails what happens
A
the battery will power the two essential DC buses and the non-essential will be lost
19
Q
When a dual TRU fail occurs the voltage will drop from ____ to ____
A
28 VDC to 24 VDC, meaning battery is powering the 2/3 DC buses (essentials only)
20
Q
Times when XFMR TECT OUT can illuminate momentarily
A
heavy DC loads causing a dip in DC bus voltage, during flap transit, pressing fuel/O2 quantity check, AB engaged
21
Q
How long will the battery power the two essential DC buses for?
A
15 Min with 80% charge
22
Q
How many volts from the battery are required to connect to DC buses and when will it drop offline?
A
- Connection min of 18 V
- Drop offline at 10 V
23
Q
Total DC Failure
A
- ADC, UFCP, EEF, MFD, normal gear extension/retract, engine start, AB ignition, fire detection not available
- STBY attitude indicator will work for 9 min with accuracy of 6 degrees
24
Q
Total DC fail, wx dependent problem
A
VOR/ILS/TACAN, EGI (INS/GPS), and AIU (UHF/VHF radios) lost
25
TRU's convert _______ Volt, 3 phase AC power to _____ VDC
- 115-200 V AC
| - 28 VDC
26
static inverter is powered by the battery bus and converts
DC to AC, primarily to monitor rt engine start and fuel/O2 amounts
27
At shutdown, EGI storage and memory requires at least ____ secs of aircraft power after turning EGI off on AAP
10 Secs
28
Generator description
There are two, three-phase, 320 to 480-cycle, 115 to 200-volt
29
How many AC buses
2, Left and right
30
Protection panels testing points
- Right to left crossover is checked when the right engine is started.
- Both right to left and left to right crossovers are checked during the Before Taxiing check.
31
Static inverter activation (3 times)
- depressing either start button.
- advancing either throttle to MAX.
- placing the fuel/oxygen quantity check switch to CHECK or TEST position.
32
Static inverter supplies AC power to operate the following equipment
- Ignition – left and right ignitor plugs
- Right engine AC instruments.
- Both fuel quantity gages and the oxygen quantity gage.
33
With loss of AC, EED indicators do what
- AC lies
- Freezes hydraulic and O2
- Oil, Fuel flow, fuel quantity OFF
34
How to change aircraft lighting from DC to AC
- use the DIM switch
| - If DC fails you must manually change to AC, but if AC fails auto switch to DC
35
How long does it tkae for landing light to retract
10 sec
36
The drift rate of a RLG
less than 0.8 NM/hr (INS only)
37
Precise Positioning System (PPS)
- 7.0 meter horizontal accuracy - 12.8 meter vertical accuracy
- 40 nanosecond time (UTC) accuracy
38
Standard Positioning System (SPS)
- 7.8 meter horizontal accuracy - 13.6 meter vertical accuracy
- 40 nanoseconds time accurac
39
Generator Rated output
115 to 200 Volts, 3 Phase, 400 +/- 80 Cycles per Second
40
Generators are powered by
Airframe mounted Gearbox
41
Generator cut in range and shift range
- Cut-in @ 43-48%
| - Shift @ 65-75%
42
Left AC Bus powers (RALLFS)
```
Rudder trim
AoA vane heater
Landing/Taxi lights
Low Fuel Light/ Left Autosyn
Fuel Boost Pump
SAS
```
43
RIght AC bus powers (HAMBEFT)
```
Hud
A/C
Mdp
Boost Pump
Engine Anti-Ice
Flaps
Trim
```
44
TRUs AMPERAGE
50 Amps converts AC to 28 VDC
45
What do TRUs power, what connects them
- Power 2 essential and 1 non-essential DC buses
| - Diode Module connects
46
Diode Module
- give continuous power even if 1 TRU fails
- 1 TRU fail => PFL
- 2 TRUs => XMFR RECT OUT light
47
Left DC Bus powers (CFAST)
```
Crossfeed valve
Flaps
AAP
Speed Brake
Transponder
```
48
Right DC bus powers (FUMIN GEAA)
```
Fire dectection
UHF radio
MFD
Nose Wheel Steering
Gear
EED
ADC
AB
```
49
Non Essential DC bus powers (TUVV)
TCAS
UFCP
VTR
VHR Radio
50
Static Inverted activated what 3 times
- Engine start button
- OXY/Fuel check switch
- Throttle to AB
51
When Static inverter Activated, Provides an Alternate Source of AC Power for the Following:
- First Engine Start on the Ground or in Flight
- Operation of Right Engine Autosyn Instruments (FF, Oil, Hyd, L/R Fuel Quantity)
- Oxygen Indicators
52
What is the min Volt the battery must have to power DC essential buses
18 V and will remain on till 10 V
53
Fire Detection System Lights and the Master Caution Lights are_______ with DC Failure
inoperative
54
Landing/Taxi Light
- 10 Second Retraction Time
- AC and DC for Lights to Extend
- DC Only for Retraction
55
"When you lose a generator in the T-38C
A) the other generator normally picks up the load
B) you normally lose th AC components powered by the failed generator
C) you sould never try to reset the generator
D) you also lose the hydraulic system on the same engine"
A) The other generator picks up the total load without action by the pilot
56
"The ____ normally supplies power to the DC busses when an engine is operating
A) battery
B) transformer rectifer units
C) static inverter"
B) DC power is normally obtained through two Transformer-Rectifier Units (TRUs) which convert AC to DC power.
57
"If the left airframe mounted gearbox fails
A) the left generator light will illuminate
B) The utility hydraulic light will illuminate
C) you will have windmilling hydraulic for normal gear extension
D) both A and B are correct"
D) Indications are simultaneous illumination of the MASTER CAUTION, LEFT GENERATOR, UTILITY HYDRAULIC and CAUTION alert messages on the HUD and MFD.
58
```
"Which of the following are powered by the static inverter?
A) Left AC-powered engine instruments
B) flap position indicator
C) both fuel quantity indicators on EED
D) gear position lights"
```
C) When activated the static inverter supplies AC power for starting either engine on the ground or in flight as well as AC power to both cockpits for operating the right engine AC sensors, both fuel quantity sensors and oxygen quantity indicator.
59
```
"What must you do to extend and illuminate the landing taxi light
A) Turn on the position light
B) Extend the gear
C) Turn on the landing light switch
D) A, B, and C are necessary"
```
D) Extension/Retraction is controlled by a combination of the position light switch and gear movement. Illumination is controlled by the landing/taxi light switch
60
"If the MASTER CAUTION light and RIGHT GENERATOR light illuminate, how can you determine if the left generator is NOT powering the right AC bus?
A) Check for Blank HUD
B) Check for OFF flag in the standby attitude indicator
C) Check for blank MFD
D) Check for FAIL indications on the right oil pressue and fuel flow indicators, and on all fuel quantity displays"
A & D) Right Gen Fail No Cross indications are MASTER CAUTION, RIGHT GENERATOR, right fuel pressure and ANTI-ICE lights illuminate. HUD and UFCP go blank and MFD reverts to backup display. Right oil pressure and fuel flow and all three fuel quantities indicate OFF. Flight control hydraulic gauge freezes in last indication and OFF appears in oxygen quantity gauge.
61
"In the event of complete AC power failure
A) there will be no interior lighting available
B) the flood lights will automatically illuminate
C) The flood lights will illuminate provided the BRIGHT/DIM switch is placed to DIM
D) the flood lights will illuminate provided the flood light control knob is out of the OFF position"
D) The top two floodlights in each cockpit automatically revert to left essential DC power during AC power failures, if the floodlight switch is out of the off position
62
"The Caution Light Panel lights operate in DIM providing
A) the instrument light rheostat is out of the ___ position
B) the Caution light BRIGHT/DIM switch is moved momentarily to the ___ position
C) there is ___ power available"
OFF, DIM, AC ) The Caution Light panel is normally DC-powered in BRIGHT mode and AC-powered in DIM mode.
63
T/F The position lights may be operated in the BRIGHT or DIM position depending only on the setting of the position BRIGHT/DIM switch and proper electrical power
T
64
"How is the aircraft electrical system (AC and DC) energized on the ground without the engines operating
A) Battery Power
B) External Power Unit
C) Both A and B"
B) The APU connects directly to the AC busses, which power the TRUs to generate DC power
65
```
"Identify the AC-powered instruments
A) Oil pressure indicators
B) Nozzle position indicators
C) Fuel Flow indicators
D) Oxygen quantity indicators
E) flap position indicators
F) fuel quantity indicators
G) EGT indicators
H) hydraulic pressure indicators"
```
A, C, D, F, H
66
"Which statements describe the purpose and operating characteristics of the static inverter?
A) It can be used as an alternate source of DC power
B) It operates right AC-Powered instruments during starting of the right engine
C) DC power is converted to AC power
D) It can be activated through the use of fuel/oxygen check switch
E) It can operate all AC-powered instruments"
BCD) When activated the static inverter converts DC to AC power and supplies AC power for starting either engine on the ground or in flight as well as AC power to both cockpits for operating the right engine AC sensors, both fuel quantity sensors and oxygen quantity indicator.
67
```
"At what engine RPM range should the generators come on line?
A) 22-25 % RPM
B) 25-30 % RPM
C) 38-42 % RPM
D) 43-48 % RPM"
```
D) 43-48%RPM Called generator cut-in range or speed. Each generator has a rated output of 115 to 200V, 3 phase, and 320-480 cycles per second
68
```
"Which of the following components would fail in the event of complete AC power failure
A) Fuel boost pumps
B) crossfeed switch and valve
C) trim
D) HUD
E) Fire Warning
F) Wing Flaps
G) Mission Data Processor"
```
A, C, D, F, G
69
```
"What AC-powered equipment can be operated when both generators fail
A) Left AC-powered engine instruments
B) Right AC-powered engine instruments
C) Fuel quantity indicators
D) Left and Right engine ignition"
```
BCD) The battery powers the battery bus which powers engine ignition and the static invertor. The static invertor powers the Right AC-powered engine instruments including the fuel quantity indicator
70
T/F With no malfunctions, all DC and AC electrical componenets can be powered with only the right engine running
T) The other generator picks up the total load without action by the pilot
71
"What is the primary cockpit indication if the left airframe mounted gearbox fails to shift
A) MASTER CAUTION light flashes momentarily as RPM passes 65 to 75%
B) LEFT GENERATOR, UTILITY HYDRAULIC and MASTER CAUTION light illuminate
C) LEFT GENERATOR, and transormer rectifer unit lights illuminate as RPM passes 65 to 75%
D) LEFT GENERATOR and MASTER CAUTION lights illuminate as RPM passes 65 to 75%"
D) gerbox failure to shift can occur when a throttle is moved forward or aft through 65-75%. The indications are the same as for generator failure: MASTER CAUTION, LEFT GENERATOR and left fuel pressure caution lights illuminate.
72
"Which instruments will be operational with both gererators inoperative
A) Tachometer and fuel flow indicators
B) Tachometer and nozzle position indicators
C) EGT indicators and tachometers
D) Nozzle position indicators and oil pressure indicators"
B & C) Tach is powerered seperately by own generator in the engine accessory gearbox. Nozzle position and EGT indicators are powered through the Righ essential DC bus.
73
"How are the Warning/caution Advisory System lights powered
A) By the AC bus in DIM position and by the left essential DC bus in BRIGHT operation
B) By the non-essential DC bus in DIM position and by the AC bus in BRIGHT operation
C) By a AC bus in all conditions
D) By a DC bus in all conditions"
A) The Caution Light panel is normally DC-powered in BRIGHT mode and AC-powered in DIM mode.
74
What is the generator cut-in range
43-48%RPM
75
Generator output?
115-220V, 3-phase, 320-480 cycles per second
76
What range does the airframe mounted gearbox shift
65-75% RPM
77
Does the OFF position stop the generator?
No, it disconnects it from its bus
78
What three situations will the generator caution light illuminate
generator malfunction, bus fault, switched to OFF
79
When a generator drops off line due to a bus fault, can you get a good crossover?
No, If the malfunction is a bus fault, the protection panel will not allow a generator reset or bus transfer to the opposite generator
80
What does the static inverter power
either engine start (ground or air), right engine AC sensors, both fuel quantity sensors and oxygen quantity
81
How is the static inverter activated?
pusing either engine start button, advancing either throttle to AB, and holding the fuel/oxygen check switch
82
How are the engine Tachometers powered
they have their own independent generator in the engine acessory gearbox
83
Name the AC powered engine sensors
oil pressure, fuel flow (also needs left essential DC), hydraulic pressue, fuel quantity, oxygen quantity, and Tachometer
84
How and which buses does the APU power
The APU connects to the AC busses which power the TRUs which power the DC busses
85
Indications of generator fail with good crossover
illumination of MASTER CAUTION and generator lights and caution alert messages
86
How many times can a generator be reset
once, in quick session
87
Right gen fail no cross
MASTER CAUTION, RIGHT GENERATOR, RIGHT FUEL PRESS, ANTI-ICE illuminate. HUD and UFCP go blank and MFD reverts to backup display. Also, right oil pressure and fuel flow, oxygen quantity and all three fuel quantity show OFF. Flight control hydraulic indicator freezes at last position.
88
Left gen fail no cross indications
MASTER CAUTION, LEFT GENERATOR, LEFT FUEL PRESS illuminate. Illumination of the AOA indicator lights and CAUTION alert meddage on the HUD and MFD. The left oil pressure and fuel flow indicators show FF and the utility hydraulic pressue gauge freezes
89
Airframe mounted gearbox failure indications
MASTER CAUTION, generator and hydraulic lights for the effected engine and alert messages on the HUD and MFD.
90
Gearbox failure to shift indications
occurs when moving throttle(s) through 65-75% RPM. Indications are the same for a generator failure
91
Partial electric failure indications
same as gen fail with crossover
92
Partial electric failure indications with no cross
Flaps and boost pump operates slower or not at all. Slow or inop boost pump may lead to Fuel low pressure light. HUD operation/display may be affected. TRUs may drop offline
93
How is the Caution Light Panel and MASTER CAUTION light powered
both are DC in bright and right AC in DIM. FIRE light is bright and DC only
94
How can you light the WCA lights without DC power
Set the DIM
95
How can you light the WCA lights without AC power
Set to BRIGHT
96
Does a GENERATOR light always mean a generator failure?
No
97
HYDRAULIC light illuminate when hydraulic pressure drops below ___ or what
1500, overtemp
98
When does the FUEL PRESSURE light illuminate
fuel pressure drops below 6psi (normally 10)
99
When does the ENG ANTI-ICE ON light illuminate
switched on, right fail gen no cross
100
When is the ANTI-ICE system on w/o the light
below 65% RPM
101
When does the OXYGEN light illuminate
below 1 liter, may blink due to sloshing
102
When does the FUEL LOW light illuminate
7.5 seconds at 250lbs
103
Will the MASTER CAUTION light reilluminate after being reset when the second tank goes below 250
No
104
When does the XFMR RECT OUT light illuminate
possible failure of both TRUs. Battery will kick on and power both essential DC buses for approx 15 min.
105
What powers the rotating beacons and where are they
left AC, under the fuselage and on the tail
106
What powers the position lights and where are they
left AC, under the fuselage and on the tail and on each wingtip
107
extension and retraction of the landing/taxi light is controlled by what
combination of the position light switch and gear movement (gear down AND pos lights on = landing/taxi light extended)
108
What are the two landing/taxi light positions
With no weight on wheels, light is slightly retracted in the landing position with both filaments on. With weight on wheels, light is near vertical with only one filament one.
109
```
"What is the approximate life of the battery after TRU failure
A) 15min
B) 18min
C) 20min
D) 24min"
```
A) The battery will power the two essential DC busses for approx 15 min
110
"Which of the following statements best describe battery operation
A) The bettery relay will close, and the battery will charge anytime external AC power is supplied to the aircraft
B) If only one TRU fails, the battey picks up its load
C) If external power is connected, the battery should be turned ON
D) If the battery relay does no close, it is impossible for the battery to be charged"
CD) When the battery switch is turned on, a minimum voltage output is required before it will connect to the essential DC busses. Even though the battery will accept charge when it is as low as 10V, it takes 18V to close the battery relay.
111
"Which of the following statements describe a TRU malfunction
A) Failure of one TRU will cause a partial DC electrical malfunction
B) Steady Illumination of the XMFR RECT OUT caution light indicates that both TRU have failed
C) A faulty TRU is indicated when the XMFR RECT OUT caution light illuminates momentarily as the wing flaps are being lowered
D) The battery will supply DC power to the essential busses when both TRU hav failed"
BD) If the XMFR RECT OUT light illuminates on the caution light panel, both TRU are inop. In this case, the non-essential bus deenergizes and the battery will be supplying the two DC essential busses
112
"During normal operation, what is the primary DC power source
A) TRUs
B) Battery
C) Static Inverter"
A
113
```
"Which of the following aircraft components are inoperative when there is complete DC electrical failure
A) HUD
B) Flight Controls
C) MFD
D) AB operation
E) Crossfeed operation
F) Fuel boost pumps
G) Landing Gear Indicators (Bright mode)
H) TRIM
I) Fire warning lights
J) EED"
```
C,D,E,G,I,J
114
"How will you be warned when one TRU fails
A) The TRU light will illuminate
B) The DC-powered equipment will be inop
C) The battery will take over the DC power load
D) AVIONICS alert message on the HUD/MFD and a PFL display"
D) If one TRU fails, an AVIONICS alert is activated and the other TRU picks up the entire DC load
115
T/F When the external power unit is connected to the aircraft, all electrical busses are energized
T) The APU energizes the AC busses which powers the TRUs which power the DC busses
116
The TRUs receive power from the ___ busses and supply power to the ___ busses
AC/DC
117
The battery must have ___ volts minimum to connect to the DC busses when placing the battery switch ON
18V. When the battery switch is turned on, a minimum voltage output is required before it will connect to the essential DC busses. Even though the battery will accept charge when it is as low as 10V, it takes 18V to close the battery relay
118
T/F Anytime the MASTER CAUTION and XMFR RECT OUT caution lights blink, it is necessary to abort the mission
F) The XMFR RECT OUT caution light may illuminate momentarily with heavy DC loads on the electrical system that cause the DC voltage to drop below battery voltage. EX. flaps moving, fuel/oxygen check switch, AB ignition
119
```
"Which of the following is a DC-powered instrument
A) Flap position indicator
B) Oxygen quantity indicator
C) HUD
D) Hydraulic pressure indicators"
```
A
120
"With failure of both TRU and a dead battery
A) afterburner initiation is still possible
B) an airstart is not possible
C) gear must be lowered by the alternate system
D) Both B and C"
D) Lose of DC busses and battery include standy by attitude (9 min), normal gear, nosewheel steering, engine start and AB ignition, certain lights, crossfeed and fuel shutoff, fire detect system, flaps/flaps positino indicator, speed brake, landing light extention, EFCP, MFD, EED, UHF/VHF, VOR/ILS/TACAN, TCAN, VTR
121
"With failure of both TRU and a dead battery
A) afterburner initiation is still possible
B) an airstart is not possible
C) gear must be lowered by the alternate system
D) Both B and C"
D) Lose of DC busses and battery include standy by attitude (9 min), normal gear, nosewheel steering, engine start and AB ignition, certain lights, crossfeed and fuel shutoff, fire detect system, flaps/flaps positino indicator, speed brake, landing light extention, EFCP, MFD, EED, UHF/VHF, VOR/ILS/TACAN, TCAN, VTR
122
"If both TRU fail and battery is charged
A) DC power will be available indefinitely
B) the static inverter will not be available for airstarts
C) the XMFR RECT OUT caution light will not illuminate because the battery will power the DC busses
D) an airstart is possible with battery power only"
D) The battery powers the battery bus which contain, AB ignition, engine start and static invertor
123
"How can you check the battery to see if it is charged sufficiently?
A) Turn ON the battery switch prior to connecting the APU
B) Voltage can be checked anytime the battery switch is turned on
C) The battery must be checked by maintenance personal during the preflight inspection"
A) To check the battery place the battey switch ON and ensure the caution warning indicator lights and gear postion indicator lights illuminate
124
"Which of the following are true concerning a momentary blink of the XMFR RECT OUT caution light
A) The battery voltage is momentarily overriding the DC busses voltage
B) This momentary condition is normal when operating high DC load equipment
C) Both A and B
D) None of the above"
C) The XMFR RECT OUT caution light may illuminate momentarily with heavy DC loads on the electrical system that cause the DC voltage to drop below battery voltage. EX. flaps moving, fuel/oxygen check switch, AB ignition
125
The right TRU receives power from the ___ and the left receives power from the ___
right AC bus contactor, left AC bus contactor
126
Can one TRU carry the entire DC load
yes
127
What if both TRU fail
the battery picks up the DC load for only the two essential DC busses
128
When is the non essential DC bus shed
when the bus drops from 28 VDC to 24 VDC
129
What may cause a momentary illumination of XMFR RECT OUT
flaps moving, fuel/oxygen quantity check, AB ignition
130
How long will the battery power the two essential DC busses
approx 15 min
131
What is the lowest voltage the battery will accept a charge
10V
132
What is the lowest voltage the battery will connect to the essential DC busses
18V
133
Is the battery charging when the APU is connected?
yes
134
What three times is battery power required
non-APU start, both TRU fail, both gen are inop
135
Indications of a single TRU fail
AVIONICS alert on the HUD/MFD
136
Indications of both TRU fail
MASTER CAUTION, XMFR RECT OUT illuminates and caution alert is displayed on MFD
137
If ON, when does the battery drop off line?
drops below 10V
138
If ON, indications of weak battery
low volumes, raspy interphone and poor radio transmission capability, caution panel lights dim
139
If the battery is on, power can be conserved by turning off what
MFD, EED, UHF backup control, EGI, VOR/ILS/TACAN, emergency flood lights and TCAS
140
Total DC failure recovery considerations
chase ship or to a VFR field (Lost all comm/navigation capability)
141
Right essential DC bus failure recovery considerations
standyby instruments for control and performance, stay VMC or use chase ship to lead back. Squawk emer and use NAV B/U for the VOR. Alternate gear extension
142
Left essential DS bus failure recovery considerations
stay VMC, or use chase to lead back. No-flap required
143
Total electrical failure recovery considerations
standy by instruments only. Idle to Mil only, no AB. No airstart, alternate gear extension with no indication. No flaps trim or speedbrake
144
Right AC bus Failure considerations
MDP and HUD inop. Only backups on MFD. Must use UHF/NAV backup control panel. No flaps, trim right boost pump, A/C and eventually canopy seal
145
Left AC bus failure considerations
mostly a concern at night since normal aircraft lighting is affected. SAS, rudder trim and left boost pump are inop
146
What type of power does the APU provide?
AC (replicating generators and engines running)
147
What happens when a generator connects to a bus after an APU is connected?
External power relay disconnects the APU
148
What must you sometimes do to get the aircraft to accept APU power?
Cycle battery off, then on
149
What type and amount of power do the TRUs put out?
28V DC
150
What happens if one TRU fails?
The other will carry the entire DC electrical load
151
How many and what types of DC busses are there?
3 - 2 essential, 1 non-essential
152
What DC busses are powered if the battery is the only source of power?
2 essential busses
153
What are the 4 situations when the battery would be the only source of DC power?
Starts without an APU, both TRUs failed, Both GENs inop, and DC components causing a drain on DC bus below 24 volts
154
What three things are on the battery bus?
static inverter, L/R start control, L/R afterburner ignition control
155
What is the min volts for the battery to connect to the DC bus?
18 V
156
What is the min voltage for the battery to stay online?
10 V
157
How long (approximately) will battery power last?
15 mins
158
What are the DC-powered instruments and displays (FEMS)?
Flap position indicator, EED (EGT. Nozzle position), MFD, and standby attitude indicator
159
What position do map lights turn on?
Past 17* from stowed
160
Are map lights DC or AC?
DC
161
Is interior lighting DC or AC?
AC
162
During an AC power failure, what will happen to the interior lights?
They will revert to DC - bright during night, dim during day
163
Is bright mode for the WCA system AC or DC?
DC
164
What are the 4 instruments not affected by the caution/light panel dimmer switch?
Marker beacon, FIRE lights, AOA, and takeoff trim indicator lights
165
How do you dim the WCA lights?
Ensure rheostat is out of off, place switch in DIM to change from DC to AC
166
What happens of an AC power failure occurs for the WCA lights?
Revert to DC (bright) mode
167
What 2 lights cannot be dimmed?
FIRE lights and Takeoff trim indicator
168
What 3 lights are inop with a DC failure?
FIRE lights, Master Caution Lights, and RCP nosegear light
169
What 2 things have to happen for the tone test pattern to work?
MDP timed-in and gear warning silence button depressed
170
What 3 things does the test switch on the right front console test?
tone test pattern, fire detection system, and master cuation and caution panel lights
171
What are the 2 places the rotating beacon is located?
Bottom of fuselage and vertical stab
172
What 3 places are position lights located?
wintips, vertical stab, lower fuselage
173
Do formation lights work in AETC equipped aircraft?
No
174
What are the two main features of the landing/taxi light?
Retractable, and dual filament
175
What two things must be activated for the landing/taxi light to be extended?
Position lights ON, and landing gear handle DOWN
176
When are both filaments in the landing light on?
When the aircraft is airborne and the gear is down
177
When is only one filament in the lighting light on?
When the weight of the aircraft is on the main gear
178
How long does it take the landing light to retract?
10 seconds
