Annunciator Panel Quizer

1
Annunciator Panel Quizer
2
Indicates primary inverter is inop. Operational
secondary and auxiliary inverters will Maintain
power to all fixed frequency busses.
3
Indicates secondary inverter is inoperative.
Operational primary and auxiliary Inverters will
maintain power to all fixed frequency buses.
4
Indicates auxiliary inverter is inoperative.
Operational primary and secondary Inverters will
maintain power to all fixed frequency buses.
5
Indicates no power to applicable bus. This is due
either to a failure of the 26 volt AC Transformer
(26 volt AC services lost), or loss of power at
the 115 volt AC fixed Frequency bus ( both 115
volt AC and 26 volt AC services lost.)
6
Illuminates to indicate horn heater elements are
unpowered or failed while system is Activated by
a HEAT selection. During test selection light
illuminates for 2 Sec. then Goes out to verify
system function.
7
GCU has isolated faulty bus due to generator
malfunction or bus fault. Will also get A TRU
fail light, PISSWATER gone.
8
Indicates applicable TRU is off-line or failed.
Secondary bus on the failed side will be Cross
tied to the remaining TRU output by logic relays.
A single TRU is sufficient to Operate all
secondary DC services. A double TRU failure will
cause the logic relays to Tie the secondary
buses to the main feeder busses. This allows the
28 volt DC Generators to provide power for
secondary DC services.
9
Illuminated Flight compartment EMER LIGHTS
switch selected off while electrical Power is
applied to the airplane. Light extinguishes when
EMER LIGHTS switch Is selected to ARM or ON.
10
Illuminate to indicate related pitot head heater
is deenergized, either by OFF selection Or power
failure.
11
Illuminate to indicate an overheat condition of
the associated windsheild, or side Window, or
temperature controller or temp. sensor
malfunction. For a windshield Overheat
condition, power is automatically cut off from
the heater elements (light Comes on) until the
HEAT switch is selected to WARM UP (light goes
out). After Appropriate cooling the switch may
be selected to NORM.
For a side window overheat condition, the FLT
WDO/HT switch is selected to OFF. The caution
light should go out as window cools off if the
caution light remains Illuminated the FLT WDO/HT
circuit breaker should be pulled.
12
Indicates overheat of applicable TRU. Select TRU
off by pulling L TRU or R TRU Circuit breaker
located on variable frequency AC breaker panel.
13
Indicates applicable hydraulic system fluid has
exceeded a temperature of 109 C As sensed at the
reservoir. The caution light will extinguish if
fluid cools to 95 c.
14
Illuminates to indicate overheat (over 88c) in
flight compartment supply duct. Temperature trim
valves are driven to maximum flight compartment
cooling Position. When temperature drops below
82c, normal operation resumes and caution Light
goes out.
Illuminates to indicate overheat (over 88c) in
cabin supply duct. Pack temperature Control
valves are driven to maximum cooling position.
When temperature drops below 82c, normal
operation resumes and caution light goes out.
15
Indicates that the electric motor windings
driving the applicable standby pump has a
Temperature exceeding 170c. The caution light
will extinguish if motor cools to 160c.
16
Indicates that applicable battery not connected
to its main feeder bus. Normal Indication when
battery is selected off.
17
Illuminates when system pressure falls below 5.5
psi as sensed at passenger door Supply line.
18

Illuminates when the air temperature downstream
of the pressure regulator and Shutoff valve
(PSRV) in the bleed air supply duct exceeds 290
c. The affected PSRV And high pressure bleed
valve close to cut off hot air supply to the
duct. Bleed air Supply for the de-icing system
will be unaffected. When duct temperature drops
below 290c the light will extinguish and bleed
air operation in the affected nacelle will be
Restored.
19

Indicates overheat of applicable DC generator.
Select generator off until light Extinguishes.
20

Indicates overheat of applicable AC generator.
Select generator off until light Extinguishes.
21

Illuminate to indicate affected engine ECU fuel
scheduling is cancelled and engine Is operating
on Manual HMU fuel schedule.
22

Engine fuel filter blocked.
23

Fuel boost pressure to engine inlet inadequete
(less than 5.5 psi) / Boos ejector Pump failed.
24

Affected system hydraulic pressure has dropped
below 2000 psi. Will illuminate with A pump
failure, hydraulic fluid loss, or engine
shutdown/failure.
25

Indicates applicable 28 volt DC generator is off
line or shut down by the GCU due to Generator
malfunction or bus fault. Main feeder bus on the
failed side will be cross Tied to the remaining
generator output if indicated generator is off
line due to Reasons other than bus fault. A
double generator failure will cause the logic
relays To tie the main feeder buses to the
secondary buses. This allows the TRUs to
Maintain power to the main and essential busses.
26

Indicates applicable AC variable generator is off
line or shut down by the GCU due to Generator
malfunction. Variable frequency buses on the
failed side will be cross tied To the remaining
generator output.
27

Indicates that the isolation valve on the
affected hydraulic system has closed. This Valve
isolates the affected hydraulic systems rudder
actuator from the remainder of The hydraulic
system. This valve will close when there is a
drop in system fluid level Due to fluid loss
(approx. 2/3 fluid left). The rudder actuator on
the affected system Will be able to continue to
operate using fluid which is circulated in a
closed system Loop.
28

Fuel tank quantity in collector tank falls below
130 pounds.
29

Indicates rudder actuator pressures have either
not dropped to 900 psi when Airspedd exceeds 140
kts. IAS or risen to 1500 psi when airspeed drops
below 140 Kts. IAS. There is a 200 kt. IAS
limitation associated with whis light.
Usually illuminates in conjunction with 1 RUD
HYD or 2 RUD HYD caution lights. Indicates that
a rudder actuator has depressurized and the
remaining actuator is Receiving full system
pressure (3000 P.S.I.) There is a 200 Kt. IAS
limitation associated With this light.
30

Indicates that one of the inboard or outboard
spoiler lift/dump valves is not Positioned
correctly. The affected spoiler system may not
extend upon aircraft Touchdown.
Indicates no metered extend pressure to affected
spoiler system actuators. Applicable ROLL SPOILER
PRESSURE push off light in front of F/O should
be pushed to Deactivate the malfunctioning
system.
31

Indicates that the applicable rudder actuator is
depressurized or that pressure has Fallen below
600 P.S.I. There is a 200 Kt. Limitation
associated with these lights.
32

When illuminated this light indicates that the
secondary shafting of the flap system
is Experiencing torque loading associated with
the extension or retraction of flaps. Indicates
possible failure of primary flap drive shafting.
Hydraulic pressure to the flap drive system has
fallen below 1500 P.S.I. Possibility of Flaps
being immobilized in their existing position.
33

Stall transducer or lift computer on affected
side has failed or the system is Deenergized.

Nose wheel steering ECU failure/ Nose wheel in
free castor mode.
34

Anti skid system is unserviceable or system is
selected off / Lights illuminate Briefly during
test.

After retraction indicates gear door sequence
valve failure. Landing gear must not be Extended
by normal DN selection. Use alternate handpump
when gear extension is Required.
35

Illuminates with beacon light selected off.
Parking brake set.

36

Indicates failure in a w.o.w sensor. PSEU will
continue to provide WOW signals due to circuit
and sensor redundancy.

Refuel / Defuel selection made on refuel / defuel
control panel Master caution light is not
activated when illuminated Fuel transfer not
possible.
37

Fire in baggage or cargo compartment / smoke
detector self test.
Illuminates concurrent with both alarm and Fault
conditions.
Cabin altitude exceeds 10,000 ft.

Oil pressure drops below 40 P.S.I. shutdown
engine.
38

Door opened

Temperature of applicable battery has exceeded 65
c battery should be disconnected From DC
electrical system and closely monitored.