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Undeleted > Ch 6 unknown > Flashcards

Ch 6 unknown Flashcards

1
Q

nose wheel to main gear dist

A

22.76m

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2
Q

which pax signs illuminate when cabin alt >10000’

A

or oxy deployed
regardless of selector position
no smoking and fasten seatbelts illuminate
return to seats extinguish

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3
Q

dome lgts control overridden

A

when light override sw ON

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4
Q

nose gear ldg lgt when does it illuminate

A

when nose gear down and locked

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5
Q

taxi lgt

A

only when nose gear down and locked

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6
Q

EMER lgts

A

OFF prevents emerg lgts operation if airplane electrical power fails or is turned off
ARMED - all emerg lgts illuminate if airplane elec power fails or is turned off

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7
Q

at flt attendant panel PAX EMERG LGT

A

bypasses flt deck emerg lgts sw and illuminares all pax cabin and exterior emerg lgts

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8
Q

ACCESS DOORS lgt

A

fw equip bay or elec equip compartment door is not closed and latched and locked

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9
Q

flt deck window to verify it’s closed and locked

A

to verify it’s closed and locked
button now depressed
lever fully forward
WINDOW NOT CLOSED decal not visible

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10
Q

oxy panel pushing the RESET/TEST lever

A

with left panel door closed and OXY ON flag not displayed, turn oxy on momentarily to test the regulator.
with left oxy panel door closed and OXY ON flag displayed, turns oxy off

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11
Q

oxy mask

A

N - not 100% therefore air/oxy mixture depends on cabin alt
sel EMERG posn - supplies 100% oxy under positive pressure at all cabin altitudes (protects against smoke and harmful vapours). Comms may be difficult

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12
Q

landing lgts posn

A

in left and right wing root optimised for flare and ground roll

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13
Q

what lights in cockpit will you have with loss of ele power

A

standby magnetic compass
instrument panel flood lights
integral lgts for essential instruments on the L instrument, center instrument and overhd panels are auto switched to standby AC bus.

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14
Q

indicator lgts auto bright when:

A

ambient flt deck light level increases to a prescribed light value
loss of quip cooling air flow, detected in flt deck or fwd E/E compartment
equip cooling air overheat, as detected in flt deck or in the forward E/E compt or at the cooling air supply source

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15
Q

FASTEN SEATBELTS illuminates

A 
ON
AUTO and cabin alt exceeds 10000
land gear not up and locked
flap lever not UP
pax oxy ON
OFF selected and cabin alt exceeds 10000, pax oxy ON
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16
Q

RETURN TO SEAT

A

illuminates with FASTEN SEATBELTS
except for cabin alt exceeds 10000
and pax oxy ON

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17
Q

Emerg lights consists of

A

pax cabin interior emerg lgts
pax exterior emerg lgts
aft flt deck dome lgt

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18
Q

flt deck emerg lgts armed and door handle SLIDE ARMED and opened

A

the exterior lights open on the same side of the airplane also for overwing exit

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19
Q

emerg lgts powered by?

A

remote batteries which provide 15 mins when fully charged

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20
Q

interior emerg lgts

A 
door
aisle
escape path
exits lights
escape path - 15 mins equal 6.5 hrs
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21
Q

pax oxy sys

A

individual chemical oxy generators

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22
Q

halon fire ext

A

effective all types of fires
use from 4m
lasts 10 secs

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23
Q

smoke hood

A

max 15 mins use

red and green lights flash when out of O2

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24
Q

ELT freq

A

transmits on 121.5 MHZ, 243 MHZ and 406 MHZ

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25
Q

COMPT temp indicators

A

displays actual temp sensed in compt

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26
Q

COMPT temp INOP

A

fault in ZTC or duct temp overheat
compt temp control is OFF
trim air sw is OFF

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27
Q

Pack control sel

A

N - normal regulates pack outlet temp to a constant, moderate temp
C cool - pack to full cold
W warm - pack to full warm

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28
Q

RECIRC INOP

A

recirc fan is failed or not operating

recirc fan sw OFF

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29
Q

PACK INOP lgt

A

pack is overheated

fault in the auto control system

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30
Q

PACK RESET

A

resets an overheated pack if the pack has cooled to a temp below the overheat level

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31
Q

foot and shoulder heaters

A

an electric heater adds heat at HIGH or LOW setting to the conditioned air flowing to the area

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32
Q

Equip cooling sel

A

STBY - positions equip cooling sys for inboard air flow

OVRD - positions equip cooling sys for reverse air flow, shuts down NGS if installed

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33
Q

NO COOLING lgt

A

active in OVRD only

no reverse air flow through E/E compt avionics

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34
Q

equip cool VALVE lgt

A

valve not in commanded position

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35
Q

equip cool OVHT lgt

A

high temp or low airflow in equip cool sys

equip cooling test

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36
Q

equip cool SMOKE lgt

A

smoke in equip cool sys

equip cool test

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37
Q

equip cool test sw

A

on accessory panel
IFE will shut down when this test is done
SMOKE and OVHT lgts illuminate for successful test

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38
Q

cargo ht OVHT lgt

A

cargo compt temp above std control range

shutoff valve signaled closed

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39
Q

bulk cargo ht sel VENT

A

sel higher temp than NORM

turns on ventilating fan for bulk cargo compt

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40
Q

cabin alt MAn control

A

controls cabin outflow valve position with the cabin alt mode sel in MAN mode

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41
Q

LDG ALT sel range

A

-1000 to 14000

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42
Q

Cabin alt rate control index mark

A

500 fpm for climb 300 fpm descent

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43
Q

AUTO INOP lgt

A

AUTO 1 and 2 cabin alt control functions inop MAN mode sel

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44
Q

AUTO 1 or 2 sel

A

activates Auto 1 or 2 cabin alt control for auto ops

outflow valve positioned auto

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45
Q

MAN sel

A

outflow valve position controlled by cabin alt MAN control

AUTO INOP lgt illuminates

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46
Q

DUCT LEAK lgt

A

high temp bleed air leak is detected in the C pneumatic duct

system test

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47
Q

Engine bleed air OFF lgt

A

engine bleed air valve is closed:
auto due to sys fault
the sw is OFF
the engine is not running

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48
Q

DUCT LEAK lgt

A

a high temp bleed air leak is detected in left, right or engine strut pneumatic duct

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49
Q

BLEED lgt

A

engine high pressure bleed air valve and/or pressure regulating valves are open when they should be closed

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50
Q

OVHT lgt

A

engine bleed air overtemp

engine bleed valves auto closed

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51
Q

PACK non-normal ops

A

pack control, fault detection, and overheat protection are all auto
pack INOP lgt and L or R PACK TEMP for all pack control sys faults and overheats
The pack valve closes and the pack is shut down auto when an internal pack overheat is detected. PACK OFF lgt and L or R pack OFF in addition to PACK TEMP.
PACK RESET once cooled down.

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52
Q

FLT DECK TEMP, FWD CABIN TEMP, MID CABIN TEMP OR AFT CABIN TEMP

A

zone supply duct overheat
ZTC failure
trim system is OFF
compartment temp control is off

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53
Q

equip cooling components

A

a supply fan and an exhaust fan either recirculate the cooling air back through the system, or port it overboard.
in flight, only the exhaust fan operates, and the air recirculated through the system

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54
Q

cargo heat non-normal ops

A

cargo ht OVHT lgt and EICAS FWD, AFT or BULK CARGO OVHT when temp above std control range.
Shutoff valve closes when 32 deg exceeeded, reopens once temp reduced.

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55
Q

press. schedule in cruise

A

after level-off the landing alt and scheduled cabin alt are compared and the higher is selected for cruise cabin alt.
Cabin climbs to cruise alt at half-rate of the auto rate or descends at the auto rate.

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56
Q

bleed air OVHT valve position

A

If a bleed air overheat occurs, the engine bleed air valve is auto closed. With the engine bleed air valve closed, the HPSOV and PRV are closed. Activation of engine anti0ice will cause the PRV to open to provide cowl anti-ice unless a strut duct leak exists.

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57
Q

ICING lgt

A

ice detect sys indicates ice buildup on the airplane

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58
Q

Window ht INOP lgt

A

the window is not being heated

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59
Q

Wiper INT

A

every 7 secs

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60
Q

WAI how many slats

A

three outboard slats

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61
Q

pressing engine anti ice

A

engine anti-ice valves open, allow engine bleed air to anti-ice the engine cowl inlets.

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62
Q

pressing WAI

A

in flight, commands wing anti-ice valve in each wing to open, allowing bleed air to flow from the bleed air manifold to the affected slats.

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63
Q

window heat for fuel jettison

A

for fuel jettisoning the aft-most cockpit windows are load shed

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64
Q

Probe heat

A

auto when engine running to pitot and AoA
airborne for TAT
two or more probe ht lgts EICAS PROBE HEAT

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65
Q

N1 sw

A

changes thrust ref from TO to CLB > 400’RA

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66
Q

BANK LIMIT SEL

A

bank angle varies between 15-25 degs depending on speed

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67
Q

LLZ capture

A

within 120 degs of LLZ course

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68
Q

GS capture

A

within 80 degs of LLZ course

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69
Q

ASA press 1

A

LAND 3

NO LAND 3

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70
Q

ASA PRESS 2

A

LAND 2

NO AUTOLAND

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71
Q

AUTO PILOT lgt

A

degraded operating condition in engaged autopilot
autopilot changed from FLCH to VS without pilot selection
ext when condition corrected or alt AP engaged which does not have fault

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72
Q

AFDS consists of

A

3 FCCs and the MCP

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73
Q

AFDS failure

A

during AP ops, failures affecting the active mode annunciate on the ADI. If the failure affects only the active mode:
the AP remains engaged in an attitude stabilising mode
amber line through mode annunciation
AUTOPILOT lgt
EICAS AUTOPILOT
failures affecting all autopilot modes results in AP disengagement

74
Q

AT modes

A 
SPD
IDLE
THR HOLD
N1
FLCH
GA
75
Q

LAND 3 FAIL OPERATIONAL

A

level of redundancy is such that a single fault cannot prevent the AP system from making an autoland

76
Q

LAND 2 FAIL PASSIVE

A

level of redundancy is such that a single fault cannot cause a significant deviation from the flt path

77
Q

GA pressed

A

2000fpm

or if FD and AP OFF - AT controls to go-around ref thrust subject to flap and Vmo limits speeds

78
Q

FD pitch for TO

A

V2 + 15 or liftoff speed + 15
if current airspeed remains above the target speed for 5 secs, target airpseed resets to current airspeed, to a max of v2 + 25kts

79
Q

pitch for EF

A

v2 if airspeed is below
existing speed if between v2 and v2 + 15
v2 +15 if airspeed above this value
roll command maintains ground track

80
Q

autoland when thr levers idle

A

15 feet

81
Q

AT limit modes

A

FLAP LIM
ALPHA
SPD LIM

82
Q

pitch limits modes

A

FLAP LIM

SPD LIM

83
Q

VOR audio panel RANGE

A

identifier only

84
Q

GND CALL

A

calls ground as long as sw pushed

85
Q

be careful decreasing HF sensitivity

A

may prevent SELCAL monitoring

86
Q

55 call

A

single HI/LO chime and flashing pink lgt

87
Q

Pilot alert

A

single hi chime on flt deck

88
Q

CVR ERASE

A

push 2 secs

on ground, AC power ON, and the park brake set

89
Q

RADIO TRANSMIT on EICAS

A

30 secs of transmission

90
Q

HF radios use common antenna

A

When either HF radio is transmitting, the antenna is disconnected from the other HF radio, and it cannot be used to transmit or received.
Both radios can receive simultaneously if neither is being used for transmitting
Tuning is a max 15 secs

91
Q

CVR records for

A

30 mins continuous loop tape or 120 min solid state any time AC power is applied to airplane

92
Q

BTB AUTO

A

arms auto AC bus tie circuits
arms auto DC bus tie circuits
arms auto flt instru transfer bus circuits

93
Q

AC bus ISOL lgt

A

a fault has occurred, auto opening the AC BTB

the AC bus tie sw is OFF

94
Q

GEN DRIVE lgt

A

high oil temp

low oil press

95
Q

stby power sel

A

OFF - stby busses unpowered
AUTO - stby busses transfer to battery power if normal ACP power lost
BAT - stby busses are powered from main batt
STBY PWR OFF lgt - stby AC or DC bus not powered

96
Q

describe elect sys

A

generates and distributes AC and DC power ro airplane systems
consists of:
main AC power
main DC power
battery/stby power and (HDG as installed)
System ops are auto
Elec faults are auto detected and isolated

97
Q

AC power sources

A

left and right IDG
APU GEN
entire AC load can be supplied by ext power
the power sources operate isolated from one another

98
Q

IDG

A

IDG has auto control and sys protection functions
when an engine starts, with the gen control sw ON, the IDG auto powers the respective main bus. The previous power source is disconnected from that bus.
IDG can be electrically disconnected by pushing gen control sw to OFF or sel ext power.

99
Q

EXT PWR AVAIL

A

voltage and freq within limits

pressing ON disconnects all other power sources

100
Q

UTIL BUS OFF

A

galley and utility bus unpowered

101
Q

ground service bus

A 
normally right main bus
or APU GEN
ext power
GSB powers:
main batt charger
APU batt charger
misc cabin and system loads
102
Q

ground handling bus

A

powered on ground only
from APU or ext power.
provided for loads such as cargo handling and equip energised for ground ops

103
Q

flight instru transfer busses

A

normally left main bus powers Capt flt instru transfer bus and R for FO. With BTB in AUTO, the flt instru transfer bus transfers to the opposite main bus in the event power is lost to a main AC bus.

104
Q

AC transfer busses

A

L and R AC transfer busses power items considered necessary for ETOPS, which are not powered by the batt/stby sys. Transfer busses are normally powered by their assoc main AC bus, but also powered by HDG when both AC busses unpowered.

105
Q

load shedding

A

occurs auto to ensure power avail to critical and essential equip
galleys first, then utility busses
then individ equip items powered by the main AC busses.
restores in reverse order

106
Q

example load shed

A

elec hyd pump prior start
center tank pumps prior start
util busses during engine start

107
Q

load shed during non-normal ops

A

util busses after gen fail
center tank pumps after eng fail
cabin ceiling lgts after eng fail

108
Q

DC elec sys

A 
uses TRUs to produce DC power.
TRUs powered by main AC busses
TRUs operate isolated from one another.
if 1 TRU fails, the DC BTB closes to keep both DC busses powered. 
No flt deck control for DC elec sys
109
Q

batt/stby power sys

A

supplies AC and DC power to selected flt instu, comms and nav sys, and other critical sys, if there are main AC and DC elec power sys failures

110
Q

batt/stby power sys busses

A

hot batt bus
batt bus
standby DC bus
standby AC bus

111
Q

hot batt bus

A

items which must be continuously powered such as clock
prior elec power powered by main batt
>elec power, main batt charger powers

112
Q

batt bus

A

prior elec power and batt sw ON, powered by main batt
>elec power, L DC sys powers batt bus, and the main batt is backup source
batt DISCH when main batt disch

113
Q

standby DC bus

A

powered by several sources
prior elec pwr, batt sw ON and stby sel AUTO, the main batt powers.
>elec power, L DC sys powers the standby DC bus and the main batt as backup

114
Q

standby AC bus

A

powered by several sources
prior elec pwr, batt sw ON and stby sel AUTO, the main batt powers stby inverter which provides AC power to stby AC bus
>elec pwr, L AC sys powers and main batt and stby inverter backup

115
Q

HDG busses

A 
AC:
L AC transfer bus
R AC transfer bus
Stby AC bus (through L AC transfer bus)
Capt flt instr transfer bus.
DC:
hot batt bus
batt bus
stby DC bus
When HDG begin to operate batt DISCH lgt as less power (5kVA) than batt until battery power decreases to the power level produced by the HDG.
116
Q

Capt and FO flight instu transfer bus

A

all items necess to fly
L and C SG
EFIS control panel

117
Q

hot batt bus powers

A

fire ext bottles
IRS emerg power R continuous, L & C 5 mins
with HDG L & C continuous, R 5mins
RAT manual deploy

118
Q

batt bus powers

A 
ldg gr alt extension
PA
interphone
engines, APU and cargo fire detect
RAT auto sys
119
Q

in flt start envelope displays

A

engine fire sw IN
FCW CUTOFF
n2 below idle
primary and secondary EICAS displayed

120
Q

APU sel OFF

A

closes APU bleed air valve
intiates APU cooling cycle
shuts down APU when cooling cycle continues
resets auto fault logic

121
Q

APU sel ON

A

opens APU fuel valve and inlet door
activates DC or AC fuel pump
powers APU controller
permits APU bleed air valve to open when bleed air sw ON and APU reaches operating speed

122
Q

describe engine

A

two-rotors

axial flow turbofan of high compression and bypass ratio

123
Q

EEC

A

in normal and alternates modes uses N1 RPM as the parameter for setting thrust.
in normal modes, EEC continuously computes max N1.
in alt mode, the EEC schedules N1 as a function of thrust lever position

124
Q

EEC alternate mode

A

thrust overboost can occur

N1 and N2 red line protection is still available in the alternate control mode

125
Q

engine start start sel to GND

A

opens start valve
engages air driven starter to N2 rotor
closes engine bleed air valve

126
Q

engine start FCW RUN

A

opens engine and spar fuel valves

activates elected igniter

127
Q

APU start requires which batt?

A

both APU and main batt

128
Q

APU protection sys

A

on ground, batt sw OFF, APU auto shuts down, whilst it cools down no fire detect sys, doesn’t shutdown in flt

129
Q

engine fire sw PULL (5)

A 
closes assoc engine and spar fuel valves
closes assoc engine bleed air valves
trips assoc engine gen off
shuts off hydraulic fluid to the assoc engine-driven hyd pump
arms both engine fire ext bottles
130
Q

CARGO FWD armed

A

arms all cargo fire ext bottles
turns off recirc fans
shuts down NGS

131
Q

AFT ARMED

A

arms all fire ext bottles
turns off recirc fans
inhibits high flow of packs
shuts down NGS

132
Q

APU fire sw PULL

A 
closes APU fuel valve
trips APU gen off
closes APU air supply valve
shuts down the APU
arms APU fire ext bottle
133
Q

WHL WELL FIRE lgt

A

a fire is detected in one or both of the main gear wheel wells

134
Q

engine fire protection

A

engine fire and overheat detection
engine fire warning
engine overheat caution
engine fire ext

135
Q

APU fire protection

A

APU fire detections
APU fire warning
APU fire extinguishing

136
Q

main deck depress for cargo fire

A

there is a depressurisation. discharge sw on 300F which results in a gradual depressurisation of the aircraft to the approximate flight attitude

137
Q

SPD BRAKE LEVER on gnd

A

retract if thrust lever advanced to takeoff thrust

extend when in UP and reverse idle detent

138
Q

TRAILING EDGE lgt

A

flap disagree exists
flap assymetry exists
the flap load relief sys is not operating when required

139
Q

LEADING EDGE lgt

A

slat disagree exists

a slat assymetry exists

140
Q

pushing LE or TE ALTN

A

arms selected LE slat or TE flap aleternate drive unit

shuts off hyd power to the selected LE slat or TE flap drive system

141
Q

elevator feel

A

provide artificial feel forces to the pilot’s control columns
mechanical springs provide feel following a loss of the L and C hyd systems

142
Q

3 modes of stab trim

A

electric
alternate
automatic

143
Q

UNSCHED STAB TRIM

A

uncommanded stab trim is detected

alternate trim is used with an AP engaged

144
Q

PES

A

pitch enhancement system
hyd motor in R hyd sys driving a pump which uses trapped left trim system fluid to operate stab at 1/4 rate. only elec trim avail.

145
Q

rudder ratio

A

receives ADC airspeed inputs and provides control commands to an actuator powered by L hyd sys. The actuator then dampens the pilots’ inputs to the rudder

146
Q

yaw damper

A

turn coordination and dutchroll damping

147
Q

SPD BRAKE lever ARMED on ground

A

landing gear not tilted
thrust levers idle
speed brakes are driven to UP and spoiler panels fully extend

148
Q

instu source sel IRS

A

Capt normal posn L IRS source for L & C SG, capt VSI, and FO RDMI
ALTN - C IRS source for L & C SG, capt VSI and FO RDMI

149
Q

rising runway

A

from 200ft

150
Q

ATT DISAGREE

A

difference of more than 3 degrees between the captain and first officer’s pitch or roll displays is detected.

151
Q

stby ASI and stby altimeter

A

L AUX pitot sys and alt static source

alt static source

152
Q

Air data sys

A 
pitot-static sys
one TAT
two AoA probes
two ADCs
and electric flt instru
153
Q

CDU DSPY light

A

when modification in progress, and and RTE, RTE LEGS, RTE DATA, HOLD, CRZ, or DES page is shown

154
Q

IRS disp sel

A

TK/GS - true track and GS
PPOS
WIND true wind when inflt
HDG true hdg

155
Q

ATT

A

attitude and hdg only (only hdg set)

156
Q

LOW FUEL EICAS AND FUEL CONFIG LGT

A

less than 2200lbs in either left or right main tank

157
Q

C AIR DEMAND PUMP AUTO

A

operates when heavy load items (ldg gear, flap/slat, ground spoiler) are selected

158
Q

describe hydraulic sys

A

System (L and R) consists of a reservoir, engine-driven primary pump, and an electric motor-driven demand pump
Reservoir pressurised by bleed air
primary hyd pump is an engine-driven pump
elec motor-driven demand pump provides additional hyd power either on demand or continuously for periods of high system demand. Also backup power source.

159
Q

describe C hyd sys

A

reservoir, 2 elect motor-driven pumps, an air-driven demand pump, and a ram air turbine (RAT) pump
no 1 hyd pump on C hyd sys is auto isolated, if sys quantity is sensed low, to provide hyd pressure to the reserve brakes and steering sys
HDG - C air demand pump operates continuously when powered.

160
Q

BRAKE TEMP lgt

A

wheel brake temp value of 5 or more

161
Q

BRAKE SOURCE lgt

A

both normal and alternate brake sys press are low

162
Q

air ground sensing

A

tilt sensors located on each main ldg gear

nose air/ground sensing sys for stall warning and portions of caution/warning sys

163
Q

landing gear held up by?

A

nose gear by uplocks

main gear by door structure

164
Q

tailskid

A

does not extend when the alternate gear exteniosn sys is used

165
Q

reserves brakes and steering

A

uses alternate brakes and nose wheel steering sys

166
Q

autobrake application

A

starts after main gear touchdown but increases once main landing gear untilt occurs

167
Q

ALT ALERT lgt

A

between 300 and 900’ from selected altitude

168
Q

terrain display

A

dotted green - 2000’ below to 500’ (250’ gr dn) below
dotted amber - 500’ (250’ gr dn) to 2000 above
dotted red - >2000’ above

169
Q

terrain annunciation

A

red - warning occurring - 20-30 secs to impact

amber - caution occurring - 40-60 secs to impact

170
Q

PWS display

A 
display AUTO on HSI when:
aircraft below 1200'AGL
PWS alert occurs
WXR not displayed
HSI in VOR, APP, MAP or CTR MAP
If PWS alert when TERR selected will show PWS unless TERR pushed to cancel
171
Q

System alert definitions

A

warning - immediate crew awareness and corrective action
caution - immediate crew awareness. corrective action may be required
advisory - routine crew awareness. corrective action may be required.

172
Q

ENG SHUTDOWN (7)

A 
ENG ANTI-ICE
ENG BLEED OFF
GEN DRIVE
GEN OFF
ENG OIL PRESS
HYD PRIM PUMP
ENG CONTROL
173
Q

TO CONFIG

A 
LE slats not in TO posiiton
TE flaps not in TO position
slat/falp position disagree with flap lever posn
stab out of green band
speed brake lever not DN
park brake valve closed
174
Q

LDG CONFIG

A 
aircraft in flt
ldg gear not down and locked
either of following exists:
flaps in landing posn (25 or 30)
any thrust lever at idle < 800'RA
175
Q

GPWS inputs

A 
air data sys
IRS
ILS
RA
GPS
176
Q

GPWS modes

A

1 excessive descent rate SINK RATE
2 excessive terrain closure rate TERRAIN
3 altitude loss after takeoff DON’T SINK, TOO LOW TERRAIN
4 unsafe terrain clearance when not in landing configuration TOO LOW FLAPS (159KTS)/GEAR (190KTS)
5 Excessive deviation below ILS GS GLIDESLOPE (>1.3DOTS)
6 Callouts and bank angle
7 Windshear

177
Q

PWS explanation

A

detects disturbed air ahead of the aircraft which contains moisture or particulate matter and which fits a known pattern of windshear activity

178
Q

PWS inhibits

A 
WARNINGS - 100kts to 50'AGL
CAUTIONS - 80kts to 400'AGL
winshear immediate-alert warnings
GPWS immediate-alert warnings
GPWS look-ahead terrain alerts
179
Q

RA/TA times

A

RA 15-35 secs

TA 20-48 secs

180
Q

TCAS inhibits

A

INCREASE DESCENT RAs RA
PWS
GPWS
windshear

Undeleted (36 decks)

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