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Q300 > Q300 QRH > Flashcards

Q300 QRH Flashcards

1
Q

UNPRESSURISED FLIGHT (Bleeds On)

A

• Auto/Man/Dump …………………Dump
• Bleed Air 1 and 2 …………On/Max
• Oxygen Masks ……………………………as req’d

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2
Q

RAPID DEPRESSURISATION/ EMERGENCY DESCENT

A

RAPID DEPRESSURISATION/ EMERGENCY DESCENT
• Oxygen Masks …………………………………On
• Mic Switch …………………….Mask
• Passenger Signs……………………………..On
EMERGENCY DESCENT, accomplish as req’d:
• Power levers…………….Flight Idle
• Condition Levers……………………Max
• Airspeed ……………………………..VMO
Note: If structural integrity is in doubt, limit airspeed as much as possible and avoid high manoeuvring loads.

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3
Q

CABIN PRESSURISATION FAILURE

A

If the aircraft fails to pressurise after take-off, follow the procedure for:
“CABIN PRESS”
Warning Light …………..Page 4.4
If the aircraft is over pressurising follow the procedure for: OVER PRESSURISATION ……….Page 4.4

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4
Q

OVER PRESSURISATION

A

Bleed 1……..Off
• Bleed 2………….On/Min
Loss of power to the pressurisation controller (Left Main DC Bus) or a ‘FAULT’ light will cause the aircraft to over pressurise.
• Auto/Man/Dump ………………….Auto
• CB - C4 (left main bus) ……….Check/reset
Aircraft pressurisation system works normally:
YES
• Bleed 1 ……………..On/Norm
— — — END — — —
NO
• Auto/Man/Dump……………Man
• Man Knob ……..as required(5.5 psi diff max)
• Use Cabin Altitude Differential placard to achieve
appropriate cabin altitude in climb cruise and descent.
Prior to Landing:
• Bleed Air 1 and 2 ……………Min/off

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5
Q

Cabin Press warning

A

(Loss of cabin pressure and/or pressurisation controller ‘FAULT’ light illuminated)
• Rapid Depressurisation/Emergency decent…….Accomplish
• Cab Alt indicator……………..Check
• Bleed Air 1 and 2 ……………..On/Max
• Cabin Pack and Flt Comp Pack……..Auto
• Auto/Man/Dump …………….Auto
• CB - C4 on the left main bus ………Check/reset
• Man Knob ……..Fully counter-clockwise
• Fwd Outflow Valve ……………….Norm
Control of the pressurisation is regained: YES
• No further action is required
. — — — END — — —
NO • Auto/Man/Dump ……………..Man • Man Knob……….as required(5.5 psi diff max)
Control of the pressurisation is regained:
YES
Use Cabin Altitude Differential placard to achieve appropriate cabin altitude in climb, cruise or descent.
Prior to Landing:
“CABIN PRESS”
CABIN PRESS
•
NO • •
Bleed Air 1 and 2……………………………………Min/off
— — — END — — —
Descend to below 14,000 ft as soon as possible UNPRESSURISED FLIGHT (pg 4.3)….Accomplish
— — — END — — —

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6
Q

“CABIN PACK HOT” or “FLT COMPT PACK HOT”

A

• Cabin Pack or Flt Comp Pack………..Off
Caution Light continues to cycle:
YES
• Bleed Air 1 and 2…………..Min/Off −
Descendtobelow14,000ftassoonaspossible.
WHEN cabin differential pressure has decreased to 0.5 psi or less:
• RAM VENTILATION (PAGE 4.3) ….. accomplish
— — — END — — —

No-
• No further action required.
— — — END — — —

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7
Q

“CABIN DUCT HOT” or “FLT COMPT DUCT HOT”

A

Duct Temp Selector ………..CAB or FC Duct
Duct Temperature continues to rise:
YES
• Cabin or Flt Comp Pack switch…………..Man
• Temp Control ………….Cool (10 secs)
Duct Temperature continues to rise:
YES
• Cabin Pack or Flt Comp Pack……….Off
— — — END — — —
NO
• No further action required.
— — — END — — —

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8
Q

“#1 BLEED HOT” or “#2 BLEED HOT”

A

Caution Light continues to cycle:
YES
Bleed Air (affected side) ………….Off
— — — END — — —

NO
No further action required

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9
Q

“PASS DOOR”, “BAG DOOR”, “FWD EXIT DOOR” or “SERV DOOR”
PASS DOOR
BAG DOOR

A

Warning: Remain clear of affected door.
Do not attempt to secure affected door.
• Passenger signs …………….On
• Cabin………………. Depressurise
− Landimmediatelyatnearestsuitableairport.
• UNPRESSURISED FLIGHT (PAGE 4.3) …….accomplish
FWD EXIT DOOR
SERV DOOR

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10
Q

CRACKED WINDSHIELD

A

•Airspeed …………..reduce (190 KIAS max)
• Auto/Man/Dump…………….Man
• Man Knob …….. INCR (2.5-3.0 psi Diff max)
− Descendtobelow14,000ftifpractical.
− UseManKnobtomaintain2.5-3.0psiDiff,orless,in descent.
Prior to landing:
• Bleed Air 1 Min/Off

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11
Q

ENGINE FAIL/FIRE/SHUTDOWN (In Flight)

A

Affected Engine:
• Power Lever ………………Flight Idle
• Condition Lever ………………….Fuel Off
• Alternate Feather …………Feather
• Pull Fuel Off Handle …………………Pull
• Tank Aux Pump……………Off
IF Fire:
• Extg switch (affected engine) ……………….. Fwd Btl IF fire persists, wait up to 30 seconds:
• Extg Switch (affected engine)…………Aft Btl

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12
Q

ON GROUND EMERGENCIES

A

• Emerg Brake ………………On
• Power Levers ………………Flight Idle
• Condition Levers ……………. Fuel Off
• Tank Aux Pumps 1 and 2 …………Off
IF Fire:
• Extg switch (affected engine) ……….Fwd Btl Wait up to 30 secs, IF fire persists:
• Extg switch (affected engine) ……………..Aft Btl
IF Evacuation:
• Emergency Lights ……………On
• Fasten Belts …………………………….Off
• Evacuate ……………………… as req’d
• AC/ DC Ext Pwr/ APU …………………..Off
• Battery Master…………………….Off

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13
Q

OIL PRESSURE BELOW 40 PSI or “#1 ENG OIL PRESS” or
“#2 ENG OIL PRESS”
#1 ENG OIL PRESS

A

Affected Engine:
• ENGINE FAIL/ FIRE/ SHUTDOWN
(page 5.3) ………………accomplish

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14
Q

LOW OIL PRESSURE (40 - 55 psi)

A

Affected Engine:
• Power Lever ……………..Flight Idle
To reduce inflight drag:
• Condition Lever…………..Start/Feather
Note: Apply single engine operational considerations, however the propeller may be un-feathered and power applied as required in an emergency.

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15
Q

ABORTED ENGINE START
IMMINENT OVERTEMPERATURE,

HUNG START or FAILURE TO LIGHT UP

A

• Condition Lever ………..Fuel Off If ITT does not decrease immediately
• Pull Fuel Off Handle……………Pull
• Ignition (affected engine)………….Off Motor engine for a minimum of 15 seconds:
• Start Select ………………….Off
CLEARING AN ENGINE - consider

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16
Q

NO STARTER CUT-OUT FOLLOWING AN ENGINE START

A

(START light remains illuminated or a negative load on the generator load meter)
• Start Select Switch……………….Off
Note: ENGINE START and SELECT lights will take
approximately 5—15 seconds to go out.
Lights remain illuminated or a negative load still on the Generator load meter after 15 seconds?
YES• DCExternalPowerswitch…………Off
• APUGenerator…………………….Off
• EngineShutdown…………..carryout
• MainandAuxBatteries………….Off
• Battery Master ……………………………Off
Maintenance action is required prior to flight.
NO • Maintenance action is required prior to next flight
— — — END — — —

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17
Q

“CHECK FIRE DET” and
“FAULT A” or “FAULT B” (Advisory Light)
CHECK FIRE DET

A

(Fire Detector Loop Failure)
• Loop Select Knob ……… Set to non-illuminated fault position
• No further action required.
— — — END — — —

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18
Q

“#1 ENG MANUAL” or “#2 ENG MANUAL”

Caution lights

A

Affected Engine:
• ECU Mode ……………………………………………..Manual
• Power Lever ………………………………………….as req’d
Note: Avoid rapid power lever movement.
Landing Considerations:
− DONOTretardaffectedPowerLeverbelowDISCon landing.
− Propellermaybeoperatedintherestrictedrange 500— 780prpm during taxi
— — — END — — —

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19
Q

PROPELLER RPM CYCLING AT 1000 RPM

A

(POWER Lever Micro Switch Failure) Above 400ft AGL:
Autofeather………………..Off
POWER Levers……………Reduce to climb setting Condition Levers ………………MIN/900Np
Check RPM of affected propeller stops cycling.

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20
Q

UNSCHEDULED PROPELLER FEATHERING

A

(May be indicated by high torque)

Above 400 ft AGL:
Affected Engine: ENGINEFAIL/FIRE/SHUTDOWN
(PAGE 5.3)………..accomplish

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21
Q

PROPELLER OVERSPEED

A

Above 400 ft AGL:
Synchrophase…………..Off
• Airspeed ………..reduce toward minimum speed appropriate to flap configuration and flight conditions
Affected Engine:
• Power lever ……………Flight Idle
• Condition Lever ………..Start/Feather
• Alternate Feather ……………..Fthr
IF propeller does NOT feather:
- DO NOT SHUT DOWN ENGINE.
• Alternate Feather Switch (affected engine) …….Norm (check Alternate advisory light out).
• Condition Levers………………Max
• Power Lever (affected engine) ……Advance.
Do not Exceed 1212rpm
• Power lever (non affected engine) …..as required to
maintain desired flight profile.
- Land immediately at nearest suitable airport.
IF propeller feathers:
• ENGINE FAIL/Fire shutdown………accomplish
Note: Power and Power levers will be asymmetric.
— — — END — — —

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22
Q

PROPELLER GROUND RANGE ADVISORY LIGHT CYCLING

A

• Power Levers ……..advance above Flight Idle

Caution: Avoid Power Lever positions that result in illumination of the Ground Range Advisory Light
Landing Considerations:
− DO NOT select affected Power Lever below Flight Idle on landing.
Landing Distance Factor:
Flap 15 ……………..1.21 Flap 35 ……………………1.32
— — — END — — —

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23
Q

APU FIRE

A

Confirm APU automatic shutdown (APU RUN advisory light out and APU BTL discharges)
IF APU BTL or APU FIRE advisory light remains illuminated:
• Extg switch……………Extg
• POST APU AUTOMATIC SHUTDOWN
(below) ………..accomplish

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24
Q

POST APU AUTOMATIC SHUTDOWN

A

• APU Bleed ………………………Off
• APU Gen ……………………….Off
• APU Power ………………………..Off
Caution: Do not restart the APU following an automatic shutdown if the FIRE advisory light is illuminated
— — — END — — —

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25
Q

RAM VENTILATION (Bleeds Off)

A

• Recirc Fans……………Off
• Bleed Air 1 and 2 …………..Min/Off
• Auto/Man/Dump ……………….Man
• Man knob ……..Fully clockwise (INCR)
• Fwd Outflow Valve ……………….Open
Note: Ram ventilation is most effective above 150 KIAS.

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26
Q

APU START FAILURE

A

(APU FLR Advisory Light illuminates during APU Start)
APU START and APU STARTER advisory lights go out:
YES
• APU Pwr………………………..Off/On
Note: After an APU start attempt, APU start will remain disabled for approximately 2 minutes.
− Wait2minutes,thenattemptsecondAPUstart. Note: Observe APU Starter cranking limits.
— — — END — — —
NO • APU STARTER FAILURE (below) … accomplish

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27
Q

APU STARTER FAILURE

A

(APU RUN with APU STARTER Advisory Light illuminated)
• APU ………………………….on
• Main Battery ………………….Off
• DC Ext Pwr ……………………Off
• DC Gen 1 and 2………………Off
• AC Ext Pwr ……………………Off
• AC Gen 1 & 2 …………………Off
• APU Pwr ………………………..Off
— — — END — — —

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28
Q

APU BLEED AIR OVERHEAT

FLT COMPT DUCT HOT or CABIN DUCT HOT or CABIN PACK HOT or FLT COMPT PACK HOT Caution Light

A

• APU Bleed…………………….Off

— — — END — — —

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29
Q

APU

Caution light

A

APU Failure
− ConfirmAPUAutomaticShutdown.
• POST APU AUTOMATIC SHUTDOWN
(Page 5.10) ………………..accomplish
— — — END — — —
APU GEN Overheat
− ConfirmAPU AutomaticShutdown. • POST APU AUTOMATIC SHUTDOWN
(Page 5.10) ………………………accomplish
— — — END — — —
APU Rear Bay Overheat
− ConfirmAPUAutomatic Shutdown. • POST APU AUTOMATIC SHUTDOWN
(Page 5.10) ………………accomplish
— — — END — — —
APU GEN Failure
• APU Gen ……………. Off then On
GEN WARN Advisory Light remains illuminated:
YES
• APU Gen ……………………..Off
— — — END — — —
NO
• No further action required.
— — — END — — —

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30
Q

HDG (Flag) SLAVE (Advisory Light)

A

• HDG REV……………. Select
— — — END — — —

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31
Q

ATT (Flag)

A

• ATT REV………………..Select
— — — END — — —

32
Q

BASIC (Advisory Light)

A

IN FLIGHT:
• ATT REV……….Select

ON THE GROUND:-
• If APIRS 1 is affected
• CB K1 (Left Essential Bus) ………………………… Pull
• CB F1 (Right Essential Bus) ……………………… Pull
• CBs K1 and F1 …………………………… Push to re-set
• If APIRS 2 is affected
• CB C8 (Right Main DC Bus) ………………………. Pull
• CB F1 (Left Essential Bus) ………………………… Pull
• CBs C8 and F1 ………………………….. Push to re-set
If the “Basic” Light remains illuminated after initialisation is complete, MCC must be called for rectification.
— — — END — — —

33
Q

AIR DATA COMPUTER

FAILURE

A

Symptoms of a DADC failure are;
The failure of the Altimeter and IVSI on the affected side.
The BASIC Light on APIRS will illuminate on the affected side. The SAT and Altitude Alerter display dashes and the ID802 Vertical Mode goes to PITCH if the active DADC fails.
The ID 802 [advisory display] “FD DADC Invalid”
EGPWS fail light if # 1 DADC has failed.
• HSI SEL ……………….Non Failed Side
• AFCS…………..Select Desired Modes
— — END — — —

34
Q

SYMBOL GENERATOR FAILURE

A

Failure is indicated by a red “x” centered across both screens or by blank screens.
• REVN switch………………….. Press
• HSI SEL………….Select unaffected side

35
Q

CRT DISPLAY FAILURE

A

Failure is indicated by a blank screen on the affected EHSI or EADI screen. To present a composite display on the serviceable screen:
• EHSI or EADI dim control knob ………….Off
Note: ILS/MLS approaches are not permitted using
composite display.

36
Q

ABNORMAL INDICATIONS OF AIRSPEED, ALTITUDE AND VERTICAL SPEED

A

• Static Source selector (affected side)……Alternate
Abnormal indications persist:
YES
− Relyontheflightinstrumentsontheopposite side
− Landatnearestsuitableairport
— — — END — — —
NO
No further action required.
— — — END — — —

37
Q

SMOKE warning light

A

• Oxygen Masks ………….On/100%
• Smoke Goggles (If applicable) ………… On
• Mic Switch………………….Mask
• Recirc Fans……………………….Off
− Landimmediatelyatthenearestsuitableairportifit cannot be visibly verified that the fire has been extinguished following fire suppression.
• Baggage Compartment Light ……..On − Extinguishfirewithportablefireextinguishers.
Note: If a pilot is required to fight the fire, protective breathing equipment must be donned prior to exiting the flight compartment.
IF necessary to clear smoke:
• Auto/ Man/ Dump………………Dump
− Descendtobelow14,000ftassoonaspossible.

38
Q

LAVATORY SMOKE WARNING

A

Assign the Flight Attendant to check the toilet for signs of a fire, smoke or a discharge of the lavatory rubbish bin fire extinguisher.
Smoke or fire is confirmed?
YES
• FUSELAGE FIRE/SMOKE/TOXIC FUMES
(page 7.4) …………..accomplish
NO
Note: The Lavatory smoke detector is very sensitive. Consider whether the source of air contamination is from outside the lavatory, such as Bleed Air contamina- tion, hairspray use or moisture vapour.
• Lavatory Smoke Detector ………………….Inhibit

39
Q

FUSELAGE FIRE/SMOKE/TOXIC FUMES

A

• Oxygen Masks……………On/100%Emer
• Smoke Goggles……………….On
• Mic Switch …………………..Mask
• Recirc Fans…………………..Off
————————–
• Emergency Lights ………when req’d
− Landimmediatelyatthenearestsuitableairportifitcannot be visibly verified that the fire has been extinguished following fire suppression.
Note: To prepare for and manage an immediate landing, the procedures given in the Unknown Source of Fire, Smoke or Fumes section may be terminated prior to completion.

40
Q

EMERGENCY LANDING Both Engines Operating

A

Cabin …………………..Secure − IFpossibleensurenopassengersareseatedinthe
plane of the propellers, Row 4.
• GPWS CB—B9 (EGPWS—B3)
(Left Rear CB Panel) ………………….Pull
• Emergency Lights …………………On
• Auto/Man/Dump……………..Dump
• ELT…………………………………On
• shoulder harnesses…………Lock
• At 500ft AGL ………………….PA
“Attention Attention, this is the Captain, Brace for impact”
Review appropriate Landing Considerations:
Landing Gear Extended………..Page 8.3 Landing Gear Retracted ……….Page 8.3 Ditching ……………………………..Page 8.4

41
Q

FORCED LANDING (Both Engines Inoperative)

A

Flap (if possible)……………..0
Airspeed…………………1.3 Vs
Note:
When flap 0, landing gear retracted, propellers feathered and zero wind, 2.5 nautical miles can be travelled for every 1000 feet of altitude loss.
All hydraulic, pneumatic and non-essential electrical services will be inoperative.

Attempt engine airstart:
Engine Airstart (page 5.8) ………accomplish
When all attempts to achieve a successful airstart have failed:
Cabin……………………………..Secure
Main & Aux Batteries …………..Off
Passenger Signs …………………On
Emergency Lights ………………..On
ELT ……………………………………..On
Shoulder Harness ……………….Lock
At500ftAGL…………………………..PA
“Attention Attention, this is the Captain, Brace for impact”
Make the approach and landing into wind.
Extending landing gear will steepen the glide angle
and decrease the glide distance.
Review Appropriate Landing Considerations:
Landing Gear Extended……….Page 8.6 Landing Gear Retracted ………Page 8.6 Ditching……………………………..Page 8.7

42
Q

“MAIN BATTERY” or “AUX BATTERY”

A

• Battery (affected) ……….Off then On
Caution Light remains on
YES
Battery (affected)……………………………….. Off
— — — END — — —
NO
No further action required
— — — END — — —

43
Q

“MAIN BAT HOT” or “AUX BAT HOT”

A

• Battery Temperature Monitor ……… confirm overheat

Overheat confirmed
YES
• Battery (affected) ………………..Off Battery temperature continues to rise
YES
• Land immediately at nearest suitable airport.
— — — END — — —
NO
• Continue to monitor affected battery temperature.
— — END — — —
NO
• No further action required
— — END — — —

44
Q

“DC BUS”

A

Are other associated Caution Lights illuminated?
• MAIN DC BUS FAULT (below) ……….accomplish
— — — END — — —

• Bus Fault Reset ………………….Reset
— — — END — — —

45
Q

Main DC Bus Fault

A

Left Main DC Bus Fault
• Aux Battery………………..Off
• DC Gen 1 ……………………Off
• Bus Fault Reset ………………….Reset
− LeaveselectedswitchesintheOFFposition
The DC BUS Light remains illuminated?
YES
• Land at nearest suitable airport — — — END — — —
NO
• No further action required.
— — — END — — —
Right Main DC Bus Fault
• Main Battery …………………………Off
• DC Gen 2 ……………………………..Off
• Bus Fault Reset ………………….Reset
− LeaveselectedswitchesintheOFFposition
The DC BUS Light remains illuminated?
YES
• Land at nearest suitable airport.
• INBD ANTI-SKID and/or OUTBOARD ANTI-SKID
(Page 14.10)………….accomplish
— — — END — — —
NO
• No further action required
— — — END — — —

46
Q

LOSS OF GENERATED POWER

A

LOSS OF BOTH DC GENERATORS and either
BOTH AC GENERATORS or ONE or BOTH TRUs
• DC, AC Gens (affected) ……. Off then on (individually)
If Caution Lights remain on:
• DC/AC Gens (affected) ………………Off
• Storm/ Dome Lights …………Storm (if req’d)
• Main & Aux Batteries …………….Off
• Emergency Lights ……………. On then Off (until req’d)
Land immediately at nearest suitable airport.
Caution: Battery duration for operation of essential services is 30 minutes.
Note: Automatic control of cabin altitude is lost. Cabin differential pressure will increase until the safety outflow valve opens.
When below 14,000 ft de-pressurise cabin:
• Auto/Man/Dump ………………Man
• Man knob ………. Fully clockwise (INCR)

47
Q

Loss of ONE DC Generator and BOTH TRUs

A

• Emergency Lights …………… On then Off (until req’d)
Note: All secondary bus services are inoperative.

48
Q

“#1 DC GEN” and/or “#2 DC GEN”
#1 DC GEN
(LOSS OF ONE OR BOTH DC GENERATORS)

A

Attempt a reset on the failed Generators (one at a time)
• Failed Generator switches…………..Off then On
Are both “#1 DC GEN” and “#2 DC GEN” Caution
Lights illuminated?
NO
Is “#1 DC GEN” or “#2 DC GEN” Caution Light illuminated?
No further action required — — — END — — —
• Inoperative DC Generator ………………………… Off
Is a “DC BUS” Caution light illuminated?
NO
YES
#2 DC GEN
YES
NO
DC BUS
No further action required — — — END — — —
YES
Refer to “MAIN DC BUS FAULT” ……. Page 9.4 Both “#1 DC GEN” and “#2 DC GEN” Caution
Lights are illuminated
• Generator switches 1 and 2 ……………………………. Off
• Main and Aux Battery ……………………………………. Off
Note: With the Battery Master switch off, failure of one TRU will cause loss of all electrical power until the Battery Master switch is selected On.
• Battery Master …………………………………………….. Off — Land at nearest suitable airport.
IF All DC electrical power is subsequently lost:
• Battery Master …………………………………………….. On Note: The APIRS will require 90 seconds to initialise after
Battery Master is selected ON.
• LOSS OF GENERATED POWER
(Page9.6) ……………………………………..accomplish
— — — END — — —

49
Q

“#1 DC GEN HOT” or “#2 DC GEN HOT”

(Overheat of ONE DC Generator)

A

• Gen switch (affected) ………….Off
Note: Continued operation of the associated engine is permissible for the remainder of the flight. The affected
GEN HOT Caution Light may remain illuminated for the remainder of the flight.

50
Q

“#1 AC GEN” or “#2 AC GEN”

Loss of ONE AC Generator

A

• Gen switch (affected) ………….Off then On
Caution Light remains on:
YES
• Gen switch (affected)…………………………… Off — — — END — — —
NO
No further action required.
— — — END — — —

51
Q

“#1 AC GEN HOT” or “#2 AC GEN HOT”

Overheat of ONE AC Generator

A

• Gen switch (affected) ……….Off
Note: Continued operation of the associated engine is permissible for the remainder of the flight.
The affected GEN HOT caution light may remain illumi- nated for the remainder of the flight.

52
Q

“L TRU” or “R TRU”
or
“L TRU HOT” or “R TRU HOT”

Loss or overheat of one TRU

A

• Affected TRU CB (co-pilot vertical CB panel) ……. Pull

53
Q

“PRI INV”

A

• Primary Inverter …………….Off
• Auxiliary Inverter……………….Left
— — — END — — —

54
Q

“SEC INV”

A

• Secondary Inverter ………….Off
• Auxiliary Inverter ……………Right
— — — END — — —

55
Q

“AUX INV”

A

• Auxiliary Inverter ………..Off
Note: With the AUXILIARY INVERTER switch selected L or R and a failure of the primary, secondary or auxiliary inverter, both associated inverters may indicate failed (Illumination of PRI INV and AUX INV or SEC INV and AUX INV caution lights). Selection of PRI INV or SEC INV switch OFF may result in the AUX INV caution light extin- guishing.
If AUX INV Caution Light remains on:
• Auxiliary Inverter……….Off
— — — END — — —

56
Q

“PRI INV”, “SEC INV”, “AUX INV”,
“L 26 AC” and “R 26 AC”

Multiple Inverter Failure

A

• 115V Bus Tie CB (top row Avionics CB panel)……Pull —
Determine the inoperative inverters by reference to
the illuminated PRI INV and/or SEC INV and/or AUX
INV caution lights.
• Inverter switches (affected) …………Off
IF AUX Inverter operative:
• Auxiliary Inverter ………..Left or Right
Toward the illuminated L26 AC or R26 AC caution light
When one or more inverters are operating;
• 115V Bus Tie CB ……………Push in —
Monitor operating inverter volts and loads for normal operation
— — — END — — —

57
Q

ROLL CONTROL JAM

A

• Autopilot ………………….disengage
• Roll Disc Handle ……pull and turn 90°
Caution: With the ROLL DISC handle pulled, the autopilot must not be engaged.
Right Control Wheel free:
Note: Roll control will be degraded and forces will be normal.
IF continuous illumination of SPLR 1 and SPLR 2 PUSH OFF switchlights:
• Illuminated switchlights …………………… push both Off
Landing Considerations:
− Landatairportwithminimumcrosswindandturbu- lence using Flap 15.
— — — END — — —
Left Control Wheel free:
Note: Roll control forces will be low and tendency to overcontrol should be avoided.
Landing Considerations:
− Landatairportwithminimumcrosswindandturbulence using Flap 15 or 35.

58
Q

AILERON TRIM TAB RUNAWAY

A

•Airspeed ………………….reduce
• Aileron Trim …………..opposite to runaway
WHEN trim is at neutral position or IF trim actuator can- not be reversed:
• Ail Trim Act CB (J7—Left Essential)………pull

59
Q

ROLL CONTROL MALFUNCTION

A

(Aeroplane Rolls with No Control Wheel Input)
• Roll control …………….apply to hold wings level IF continuous illumination of SPLR 1 or SPLR 2
PUSHOFF switchlights:
• Illuminated switchlight………..Push off

Landing Considerations:
Landatanairportwithminimumcrosswindandtur- bulence using Flap 15 or 35.

IF SPLR 1 or SPLR 2 PUSHOFF switchlights do not illuminate:
• Power ……………………………apply
• Airspeed ……………………increase

Landing Considerations:
− Approachspeed1.4Vs
− Landatanairportwithminimumcrosswindandturbulence using Flap 15 or 35.
Landing Distance Factor:
Flap 15 ………………1.23
Flap 35 ……………..1.28

60
Q

“ROLL SPLR INBD HYD” or “ROLL SPLR OUTBD HYD”

A

• Roll Spoiler Pressure (affected system) ……..push off Landing Considerations:
− Approach and VREF speeds…………………..VREF+6 kts −

LandusingFlap15or35
Landing Distance Factor:
Flap 15 …………………1.21
Flap 35 …………………..1.21

61
Q

“ROLL SPLR INBD HYD” and “ROLL SPLR OUTBD HYD”

A

(Spoiler Cable Failure)
• SPLR 1 and SPLR 2 switchlights…………push off
Landing Considerations:
− Landatanairportwithminimumcrosswindandturbulence using Flap 15.

62
Q

PITCH CONTROL JAM

A

• Autopilot ………….disengage
• Flap and Airspeed …….maintain at time of jam
• Pitch Control ………….attempt to overcome jam
If unable to overcome jam:
• Relax control column force
• Pitch Disconnect Handle………..pull and turn 90°
Caution: With pitch disconnect handle pulled, the autopilot must not be engaged.
Note: Elevator forces will be lighter than normal and pitch control degraded.
• Airspeed ……………..150 KIAS (max) or speed at which jam occurred, whichever is higher.
If the elevator is free and floating:
• Airspeed …………..180 KIAS (max)
Landing Considerations:
− Land with the flap setting at the time of jam at an airport with minimum crosswind and turbulence
IF Flap 0, 5 or 10 landing:
• GPWS Flap Override ………………press
Approach and VREF Speeds:
− Flap 0, 5, 10 or 15……………….1.3 Vs
Landing Distance Factor:
Flap 0 (use Flap 35 chart) ………….1.54 Flap 5 (use Flap 35 chart……………….1.31 Flap 10 (use Flap 35 chart) ……………1.18 Flap 15 …………………1.10
Avoid pitch attitudes in excess of 6°at touch down.

63
Q

ELEVATOR CONTROL MALFUNCTION

Loss of elevator and manual trim control

A

• Stby Elevator Trim ……………Arm
• Nose Down/Nose Up ………….as req’d
Warning: The standby elevator trim rate is slow. Monitor the effect of a change in trim setting before initi-
ating another change.
Note: Elevator Trim pointer will not indicate trim position.

64
Q

ELEVATOR TRIM MALFUNCTION

A

Autopilot…………Disconnect
Elevator trim wheel rotates but will not trim the aircraft
YES
• Stby Elevator Trim ………………Arm
• Nose Down/Nose Up ……………as req’d
— — — END — — —
NO
Elevator trim is jammed.

65
Q

“FLAP DRIVE”

A

• No crew action req’d.
Note: Flap will continue to operate normally and
may be used to complete the flight

66
Q

ABNORMAL FLAP LANDING

A

Flap failed between 0 and 10:
YES
• GPWS Flap Override ……………..press At 500 ft AGL:
• Autopilot …………………..Disengage
Landing Considerations:
− Nosewheel should be promptly brought into contact with the ground following main wheel contact.
Approach and VREF Speeds:
Flap between 0 and 5:
− Use 1.3 Vs for Flap 0 ……………Chart Below
Flap between 5 and 10:
− Use1.3VsforFlap5……………..ChartBelow
Landing Distance Factor
Flap 0 to10, (use Flap 35 chart, page 3.5)………….. 1.54
Caution:
NO
Avoid pitch attitudes in excess of 6° at touch-down
If reverse power is required, care should be taken to ensure that engine torque limit in reverse is not exceeded.
— — — END — — —
Flap failed between 10, 15 or 35:
Landing Considerations:
− The smaller flap angle must be used when cal- culating landing performance.

67
Q

RUDDER JAM
(Restricted Rudder Pedal Movement)

A

Warning: Should the rudder pedal (rudder jam) suddenly break free, do not apply rudder
pedal input in the opposite direction.
• Affected rudder pedal . . . . . apply normal push force
Rudder pedal moves as required:
YES
• Affected rudder pedal . . . . . . reduce push force and allow rudder to centre
— — — END — — —
NO
Rudder pedal does not respond to normal push force (rudder remains jammed or rudder jam reoccurs):
- Use roll control as required for directional control.
• Airspeed……………………1.3VS(min)

68
Q

RUD 1 or RUD 2 PUSH OFF (Switchlight On)

A

• Illuminated switchlight………………push off
• Airspeed …………….200 KIAS (max)
Caution: Avoid abrupt or excessive rudder movements above 150 KIAS.

69
Q

“#1 RUD HYD” or “#2 RUD HYD”

A

• Affected RUD 1 or RUD 2 switchlight……..push off
• Airspeed ……………….200 KIAS (max)
Caution: Avoid abrupt or excessive rudder movements above 150 KIAS.

70
Q

“RUD PRESS” or “RUD FULL PRESS”

A

• Airspeed ……….200 KIAS (max)

Caution: Avoid abrupt or excessive rudder movements above 150 KIAS.

71
Q

RUDDER TRIM ACTUATOR RUNAWAY

A

• Rudder Trim……………opposite to runaway
WHEN trim is at the neutral position or IF the trim actuator cannot be reversed:
• Rud Trim Act CB (F7—Left Essential)………………pull

72
Q

“#1 TANK FUEL LOW” or “#2 TANK FUEL LOW”

A

• Fuel Quantity …………..check
Affected tank fuel content is low:
YES
— Check for external and internal fuel leaks.
Note: A check of the cabin will be necessary to identify a possible internal fuel leak.

Fuel leak confirmed:

YES:
• ENGINE FAIL/FIRE/SHUTDOWN
(Page 5.3) ……………….accomplish
——END——
NO:
Transfer fuel from unaffected tank Monitor fuel tank quantity.
— — — END — — —

Fuel tank Qty NOT Low:
— Maintain level attitude as much as possible
• Tank Aux Pump (affected engine)………..On
− Monitor fuel quantity
If “ENG FUEL PRESS” Caution Light illuminates: • ENGINE FAIL/FIRE/SHUTDOWN
(Page 5.3)…………..accomplish
— — — END — — —

73
Q

“#1 ENG FUEL PRESS” or “#2 ENG FUEL PRESS”

A

Tank Aux Pump (affected side)………..On

Caution Light remains on:
YES
• Tank Aux Pump (affected side)…………Off
− Check for external leaks and for fuel odour within aeroplane.
IF either is confirmed:
• ENGINE FAIL/ FIRE/ SHUTDOWN
(page 5.3)……………………………………..accomplish
— — — END — — —
NO • No further action required.
— — — END — — —

74
Q

ABNORMAL FUEL TEMPERATURE

A

• Tank Aux Pump (affected side) ……………On
• Continue flight but maintain level attitude as much as possible.
− Monitor fuel temperature and fuel pressure.
IF fuel temperature returns to normal:
• Tank Aux Pump (affected side)………..Off

75
Q

FUEL TRANSFER FAILURE

A

Tank Aux Pump Fails to Automatically Activate:

Tank Aux Pump Advisory Light Fails to illuminate:
• Tank Aux Pump (affected side)………………………. On
When transfer is complete:
• Tank Aux Pump (affected side)………………………. Off
• Fuel Transfer ………………….. Off
— — — END — — —

One or Both Fuel Transfer Valve Advisory Lights not at OPEN:
• Fuel Transfer ………………………. Off
− Consider the effects of maximum lateral fuel asymmetry or low fuel level.

76
Q

“#1 FUEL FLTR BYPASS” or “#2 FUEL FLTR BYPASS”

A

• No crew action req’d.
Note: Monitor fuel flow, ITT and NH. If erratic, indicates contamination has passed filter. Consider engine shutdown.

Q300 (10 decks)

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