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T38C Systems > SY1103-05 Electrical System > Flashcards

SY1103-05 Electrical System Flashcards

1
Q

How many Generators and characteristics

A
  • two (left and right)

- three-phase AC Generators

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2
Q

What RPM range are the generators fully operational

A

43-48% is the “cut-in range”

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3
Q

When is the gearbox shift range to keep Generators in limits

A

65-75%

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4
Q

With a generators switch in the off position, does the generator stop?

A

No, it’s disconnected from bus to protect system

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5
Q

How many protection panels?

A

-two, one for each generator and the bus, which will disconnect gen from bus to protect system

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6
Q

What powers static inverter

A

battery bus which converts DC to AC pwoer

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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
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8
Q

How is static inverter activated

A
  • push either start button
  • move throttle into AB
  • GAGE TEST/ QTY Check switch
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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
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10
Q

Caution Panel Lights (WCA)

A

-DC powered to be bright

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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.

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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.

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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.

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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%.

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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.

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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.

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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.

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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

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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)

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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

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21
Q

How long will the battery power the two essential DC buses for?

A

15 Min with 80% charge

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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

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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
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24
Q

Total DC fail, wx dependent problem

A

VOR/ILS/TACAN, EGI (INS/GPS), and AIU (UHF/VHF radios) lost

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25
Q

TRU’s convert _______ Volt, 3 phase AC power to _____ VDC

A
  • 115-200 V AC

- 28 VDC

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26
Q

static inverter is powered by the battery bus and converts

A

DC to AC, primarily to monitor rt engine start and fuel/O2 amounts

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27
Q

At shutdown, EGI storage and memory requires at least ____ secs of aircraft power after turning EGI off on AAP

A

10 Secs

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28
Q

Generator description

A

There are two, three-phase, 320 to 480-cycle, 115 to 200-volt

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29
Q

How many AC buses

A

2, Left and right

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30
Q

Protection panels testing points

A
  • 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.
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31
Q

Static inverter activation (3 times)

A
  • depressing either start button.
  • advancing either throttle to MAX.
  • placing the fuel/oxygen quantity check switch to CHECK or TEST position.
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32
Q

Static inverter supplies AC power to operate the following equipment

A
  • Ignition – left and right ignitor plugs
  • Right engine AC instruments.
  • Both fuel quantity gages and the oxygen quantity gage.
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33
Q

With loss of AC, EED indicators do what

A
  • AC lies
  • Freezes hydraulic and O2
  • Oil, Fuel flow, fuel quantity OFF
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34
Q

How to change aircraft lighting from DC to AC

A
  • use the DIM switch

- If DC fails you must manually change to AC, but if AC fails auto switch to DC

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35
Q

How long does it tkae for landing light to retract

A

10 sec

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36
Q

The drift rate of a RLG

A

less than 0.8 NM/hr (INS only)

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37
Q

Precise Positioning System (PPS)

A
  • 7.0 meter horizontal accuracy - 12.8 meter vertical accuracy
  • 40 nanosecond time (UTC) accuracy
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38
Q

Standard Positioning System (SPS)

A
  • 7.8 meter horizontal accuracy - 13.6 meter vertical accuracy
  • 40 nanoseconds time accurac
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39
Q

Generator Rated output

A

115 to 200 Volts, 3 Phase, 400 +/- 80 Cycles per Second

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40
Q

Generators are powered by

A

Airframe mounted Gearbox

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41
Q

Generator cut in range and shift range

A
  • Cut-in @ 43-48%

- Shift @ 65-75%

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42
Q

Left AC Bus powers (RALLFS)

A 
Rudder trim
AoA vane heater
Landing/Taxi lights
Low Fuel Light/ Left Autosyn
Fuel Boost Pump
SAS
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43
Q

RIght AC bus powers (HAMBEFT)

A 
Hud
A/C
Mdp
Boost Pump
Engine Anti-Ice
Flaps
Trim
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44
Q

TRUs AMPERAGE

A

50 Amps converts AC to 28 VDC

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45
Q

What do TRUs power, what connects them

A
  • Power 2 essential and 1 non-essential DC buses

- Diode Module connects

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46
Q

Diode Module

A
  • give continuous power even if 1 TRU fails
  • 1 TRU fail => PFL
  • 2 TRUs => XMFR RECT OUT light
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47
Q

Left DC Bus powers (CFAST)

A 
Crossfeed valve
Flaps
AAP
Speed Brake
Transponder
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48
Q

Right DC bus powers (FUMIN GEAA)

A 
Fire dectection
UHF radio
MFD
Nose Wheel Steering 
Gear
EED
ADC
AB
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49
Q

Non Essential DC bus powers (TUVV)

A

TCAS
UFCP
VTR
VHR Radio

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50
Q

Static Inverted activated what 3 times

A
  • Engine start button
  • OXY/Fuel check switch
  • Throttle to AB
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51
Q

When Static inverter Activated, Provides an Alternate Source of AC Power for the Following:

A
  • First Engine Start on the Ground or in Flight
  • Operation of Right Engine Autosyn Instruments (FF, Oil, Hyd, L/R Fuel Quantity)
  • Oxygen Indicators
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52
Q

What is the min Volt the battery must have to power DC essential buses

A

18 V and will remain on till 10 V

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53
Q

Fire Detection System Lights and the Master Caution Lights are_______ with DC Failure

A

inoperative

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54
Q

Landing/Taxi Light

A
  • 10 Second Retraction Time
  • AC and DC for Lights to Extend
  • DC Only for Retraction
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55
Q

“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

A) The other generator picks up the total load without action by the pilot

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56
Q

“The ____ normally supplies power to the DC busses when an engine is operating
A) battery
B) transformer rectifer units
C) static inverter”

A

B) DC power is normally obtained through two Transformer-Rectifier Units (TRUs) which convert AC to DC power.

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57
Q

“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”

A

D) Indications are simultaneous illumination of the MASTER CAUTION, LEFT GENERATOR, UTILITY HYDRAULIC and CAUTION alert messages on the HUD and MFD.

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58
Q 
"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"
A

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.

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59
Q 
"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"
A

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

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60
Q

“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

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.

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61
Q

“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”

A

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

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62
Q

“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”

A

OFF, DIM, AC ) The Caution Light panel is normally DC-powered in BRIGHT mode and AC-powered in DIM mode.

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63
Q

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

A

T

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64
Q

“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”

A

B) The APU connects directly to the AC busses, which power the TRUs to generate DC power

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65
Q 
"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

A, C, D, F, H

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66
Q

“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”

A

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.

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67
Q 
"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"
A

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

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68
Q 
"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

A, C, D, F, G

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69
Q 
"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"
A

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

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70
Q

T/F With no malfunctions, all DC and AC electrical componenets can be powered with only the right engine running

A

T) The other generator picks up the total load without action by the pilot

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71
Q

“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%”

A

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.

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72
Q

“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”

A

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
Q

“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

A) The Caution Light panel is normally DC-powered in BRIGHT mode and AC-powered in DIM mode.

74
Q

What is the generator cut-in range

A

43-48%RPM

75
Q

Generator output?

A

115-220V, 3-phase, 320-480 cycles per second

76
Q

What range does the airframe mounted gearbox shift

A

65-75% RPM

77
Q

Does the OFF position stop the generator?

A

No, it disconnects it from its bus

78
Q

What three situations will the generator caution light illuminate

A

generator malfunction, bus fault, switched to OFF

79
Q

When a generator drops off line due to a bus fault, can you get a good crossover?

A

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
Q

What does the static inverter power

A

either engine start (ground or air), right engine AC sensors, both fuel quantity sensors and oxygen quantity

81
Q

How is the static inverter activated?

A

pusing either engine start button, advancing either throttle to AB, and holding the fuel/oxygen check switch

82
Q

How are the engine Tachometers powered

A

they have their own independent generator in the engine acessory gearbox

83
Q

Name the AC powered engine sensors

A

oil pressure, fuel flow (also needs left essential DC), hydraulic pressue, fuel quantity, oxygen quantity, and Tachometer

84
Q

How and which buses does the APU power

A

The APU connects to the AC busses which power the TRUs which power the DC busses

85
Q

Indications of generator fail with good crossover

A

illumination of MASTER CAUTION and generator lights and caution alert messages

86
Q

How many times can a generator be reset

A

once, in quick session

87
Q

Right gen fail no cross

A

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
Q

Left gen fail no cross indications

A

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
Q

Airframe mounted gearbox failure indications

A

MASTER CAUTION, generator and hydraulic lights for the effected engine and alert messages on the HUD and MFD.

90
Q

Gearbox failure to shift indications

A

occurs when moving throttle(s) through 65-75% RPM. Indications are the same for a generator failure

91
Q

Partial electric failure indications

A

same as gen fail with crossover

92
Q

Partial electric failure indications with no cross

A

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
Q

How is the Caution Light Panel and MASTER CAUTION light powered

A

both are DC in bright and right AC in DIM. FIRE light is bright and DC only

94
Q

How can you light the WCA lights without DC power

A

Set the DIM

95
Q

How can you light the WCA lights without AC power

A

Set to BRIGHT

96
Q

Does a GENERATOR light always mean a generator failure?

A

No

97
Q

HYDRAULIC light illuminate when hydraulic pressure drops below ___ or what

A

1500, overtemp

98
Q

When does the FUEL PRESSURE light illuminate

A

fuel pressure drops below 6psi (normally 10)

99
Q

When does the ENG ANTI-ICE ON light illuminate

A

switched on, right fail gen no cross

100
Q

When is the ANTI-ICE system on w/o the light

A

below 65% RPM

101
Q

When does the OXYGEN light illuminate

A

below 1 liter, may blink due to sloshing

102
Q

When does the FUEL LOW light illuminate

A

7.5 seconds at 250lbs

103
Q

Will the MASTER CAUTION light reilluminate after being reset when the second tank goes below 250

A

No

104
Q

When does the XFMR RECT OUT light illuminate

A

possible failure of both TRUs. Battery will kick on and power both essential DC buses for approx 15 min.

105
Q

What powers the rotating beacons and where are they

A

left AC, under the fuselage and on the tail

106
Q

What powers the position lights and where are they

A

left AC, under the fuselage and on the tail and on each wingtip

107
Q

extension and retraction of the landing/taxi light is controlled by what

A

combination of the position light switch and gear movement (gear down AND pos lights on = landing/taxi light extended)

108
Q

What are the two landing/taxi light positions

A

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
Q 
"What is the approximate life of the battery after TRU failure
A) 15min
B) 18min
C) 20min
D) 24min"
A

A) The battery will power the two essential DC busses for approx 15 min

110
Q

“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”

A

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
Q

“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”

A

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
Q

“During normal operation, what is the primary DC power source
A) TRUs
B) Battery
C) Static Inverter”

A

A

113
Q 
"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"
A

C,D,E,G,I,J

114
Q

“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”

A

D) If one TRU fails, an AVIONICS alert is activated and the other TRU picks up the entire DC load

115
Q

T/F When the external power unit is connected to the aircraft, all electrical busses are energized

A

T) The APU energizes the AC busses which powers the TRUs which power the DC busses

116
Q

The TRUs receive power from the ___ busses and supply power to the ___ busses

A

AC/DC

117
Q

The battery must have ___ volts minimum to connect to the DC busses when placing the battery switch ON

A

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
Q

T/F Anytime the MASTER CAUTION and XMFR RECT OUT caution lights blink, it is necessary to abort the mission

A

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
Q 
"Which of the following is a DC-powered instrument
A) Flap position indicator
B) Oxygen quantity indicator
C) HUD
D) Hydraulic pressure indicators"
A

A

120
Q

“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”

A

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
Q

“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”

A

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
Q

“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”

A

D) The battery powers the battery bus which contain, AB ignition, engine start and static invertor

123
Q

“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

A) To check the battery place the battey switch ON and ensure the caution warning indicator lights and gear postion indicator lights illuminate

124
Q

“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”

A

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
Q

The right TRU receives power from the ___ and the left receives power from the ___

A

right AC bus contactor, left AC bus contactor

126
Q

Can one TRU carry the entire DC load

A

yes

127
Q

What if both TRU fail

A

the battery picks up the DC load for only the two essential DC busses

128
Q

When is the non essential DC bus shed

A

when the bus drops from 28 VDC to 24 VDC

129
Q

What may cause a momentary illumination of XMFR RECT OUT

A

flaps moving, fuel/oxygen quantity check, AB ignition

130
Q

How long will the battery power the two essential DC busses

A

approx 15 min

131
Q

What is the lowest voltage the battery will accept a charge

A

10V

132
Q

What is the lowest voltage the battery will connect to the essential DC busses

A

18V

133
Q

Is the battery charging when the APU is connected?

A

yes

134
Q

What three times is battery power required

A

non-APU start, both TRU fail, both gen are inop

135
Q

Indications of a single TRU fail

A

AVIONICS alert on the HUD/MFD

136
Q

Indications of both TRU fail

A

MASTER CAUTION, XMFR RECT OUT illuminates and caution alert is displayed on MFD

137
Q

If ON, when does the battery drop off line?

A

drops below 10V

138
Q

If ON, indications of weak battery

A

low volumes, raspy interphone and poor radio transmission capability, caution panel lights dim

139
Q

If the battery is on, power can be conserved by turning off what

A

MFD, EED, UHF backup control, EGI, VOR/ILS/TACAN, emergency flood lights and TCAS

140
Q

Total DC failure recovery considerations

A

chase ship or to a VFR field (Lost all comm/navigation capability)

141
Q

Right essential DC bus failure recovery considerations

A

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
Q

Left essential DS bus failure recovery considerations

A

stay VMC, or use chase to lead back. No-flap required

143
Q

Total electrical failure recovery considerations

A

standy by instruments only. Idle to Mil only, no AB. No airstart, alternate gear extension with no indication. No flaps trim or speedbrake

144
Q

Right AC bus Failure considerations

A

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
Q

Left AC bus failure considerations

A

mostly a concern at night since normal aircraft lighting is affected. SAS, rudder trim and left boost pump are inop

146
Q

What type of power does the APU provide?

A

AC (replicating generators and engines running)

147
Q

What happens when a generator connects to a bus after an APU is connected?

A

External power relay disconnects the APU

148
Q

What must you sometimes do to get the aircraft to accept APU power?

A

Cycle battery off, then on

149
Q

What type and amount of power do the TRUs put out?

A

28V DC

150
Q

What happens if one TRU fails?

A

The other will carry the entire DC electrical load

151
Q

How many and what types of DC busses are there?

A

3 - 2 essential, 1 non-essential

152
Q

What DC busses are powered if the battery is the only source of power?

A

2 essential busses

153
Q

What are the 4 situations when the battery would be the only source of DC power?

A

Starts without an APU, both TRUs failed, Both GENs inop, and DC components causing a drain on DC bus below 24 volts

154
Q

What three things are on the battery bus?

A

static inverter, L/R start control, L/R afterburner ignition control

155
Q

What is the min volts for the battery to connect to the DC bus?

A

18 V

156
Q

What is the min voltage for the battery to stay online?

A

10 V

157
Q

How long (approximately) will battery power last?

A

15 mins

158
Q

What are the DC-powered instruments and displays (FEMS)?

A

Flap position indicator, EED (EGT. Nozzle position), MFD, and standby attitude indicator

159
Q

What position do map lights turn on?

A

Past 17* from stowed

160
Q

Are map lights DC or AC?

A

DC

161
Q

Is interior lighting DC or AC?

A

AC

162
Q

During an AC power failure, what will happen to the interior lights?

A

They will revert to DC - bright during night, dim during day

163
Q

Is bright mode for the WCA system AC or DC?

A

DC

164
Q

What are the 4 instruments not affected by the caution/light panel dimmer switch?

A

Marker beacon, FIRE lights, AOA, and takeoff trim indicator lights

165
Q

How do you dim the WCA lights?

A

Ensure rheostat is out of off, place switch in DIM to change from DC to AC

166
Q

What happens of an AC power failure occurs for the WCA lights?

A

Revert to DC (bright) mode

167
Q

What 2 lights cannot be dimmed?

A

FIRE lights and Takeoff trim indicator

168
Q

What 3 lights are inop with a DC failure?

A

FIRE lights, Master Caution Lights, and RCP nosegear light

169
Q

What 2 things have to happen for the tone test pattern to work?

A

MDP timed-in and gear warning silence button depressed

170
Q

What 3 things does the test switch on the right front console test?

A

tone test pattern, fire detection system, and master cuation and caution panel lights

171
Q

What are the 2 places the rotating beacon is located?

A

Bottom of fuselage and vertical stab

172
Q

What 3 places are position lights located?

A

wintips, vertical stab, lower fuselage

173
Q

Do formation lights work in AETC equipped aircraft?

A

No

174
Q

What are the two main features of the landing/taxi light?

A

Retractable, and dual filament

175
Q

What two things must be activated for the landing/taxi light to be extended?

A

Position lights ON, and landing gear handle DOWN

176
Q

When are both filaments in the landing light on?

A

When the aircraft is airborne and the gear is down

177
Q

When is only one filament in the lighting light on?

A

When the weight of the aircraft is on the main gear

178
Q

How long does it take the landing light to retract?

A

10 seconds

T38C Systems (15 decks)

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