z
Bombardier Inc.
123 Garratt Blvd.
Downsview, Ontario, Canada M3K 1Y5
Telephone (416) 633--7310
http://www.aerospace.bombardier.com
To:
Dash 8, Series 400 Operators
Date:
20 April, 2018
Subject:
PSM 1---84---1B, Dash 8, Series 400, Quick Reference Handbook, Revision 38
Insert the attached copy of Revision 38, dated 19 April, 2018, in the Quick Reference Handbook
using the revised List of Effective Pages as a guide.
Remove and destroy the superseded pages. Record the insertion of Revision 38 in the appropriate
columns of the Log of Revisions, page LOR 1.
Revision 38 incorporates the following Q400 AFM revisions:
--- 357, Update to Abnormal Fuel Temperature procedure,
--- 358, Introduction of Main Landing Gear Tire Failure procedure,
--- 365, Re-issue of Supplement 6, Auxiliary Power Unit (new FADEC).
Revision 38 also incorporates the following:
--- Elaboration of manual pressurization control in Cabin Pressurization Failure,
--- Clarification of Yaw Damper Not Centered, Audio System Failure and
TCAS failures procedures,
--- Update to Part 7, Fuselage Fire, Smoke or Fumes procedures,
--- Clarification of manual brake technique, Deice Boots failure and Pitot Heat failure procedures,
--- Miscellaneous changes.
Technical Publications Department
Bombardier Customer Services
NON-NORMAL/EMERGENCY CHECKLISTS
The Non-normal/Emergency checklists contain only those
items and procedures that differ from the normal operations
of the airplane.
The Non-normal/Emergency checklist assumes that if an
indicating light associated with a system is not illuminating,
the integrity of the bulb is checked prior to referring to the
checklist.
Each Non-normal/Emergency situation addressed in the
checklist will be arranged as required in the following format:
--- Items enclosed within a box shall be given due
consideration as immediate items to be accomplished
in order to respond to the emergency situation. These
boxed items may be completed by either following the
checklist or from memory, as required by individual
company approved procedures.
--- Checklist items specific to the malfunction.
--- Landing Considerations: This information is specific to
the malfunction and is used to supplement the normal
operations of the airplane. The Landing Considerations
must be reviewed as part of the approach briefing.
--- The statement “Land immediately at the nearest
suitable airport” is defined as:
Land at the nearest airport that offers sufficient
landing distance available and if required,
emergency services to support the emergency or
abnormality.
--- The statement “Land at the nearest suitable airport” is
defined as:
The airplane may continue to the destination
airport or the nearest airport where maintenance
services are available.
--- The statement “Maintenance action required prior to
next flight” is defined as:
“Maintenance action” is referring to procedures
which can be conducted by appropriately trained
and approved pilots as well as maintenance
personnel.
“Next Flight” is referring to the immediate or
imminent take-off after discovery.
A flow pattern concept is used throughout the QRH as
applicable, utilizing the decision (rhomb) symbol (
).
This decision symbol indicates a flow pattern which points
to two or more possible courses of action. The procedure is
completed once the (-- END --) symbol is reached.
MAY 19/18
APR
15/05
PSM 1---84---1B
PREFACE iii
Following
completion
of
the
appropriate
Non-normal/Emergency checklist, the Normal checklist will
be used as modified by the Non-normal/Emergency
checklist for the remainder of the flight.
Non-normal/Emergency checklists are referenced on the
Chapter 4 tab divider. Each section also contains a Table of
Contents with boxed titles denoting immediate action items.
Caution and Warning Light annunciations are shown
capitalized in bold type within quotation marks.
The last page of the QRH is an illustration of the Caution and
Warning Lights panel with a page reference for that
particular Caution or Warning Light.
MS 4---113581 or IS4Q2150011
MS 4---113581 introduces a software update to the ECS
Electronic Control Unit.
IS4Q2150011 introduces an upgraded ECS Electronic
Control Unit.
The respective pages are coded as follows:
MS 4-- 113581 or IS4Q2150011 ONLY
MS 4---126354 and (MS 4---901472 or MS 901473)
MS 4---126354 and (MS 4---901472 or MS 901473) introduce
Revised PTU Auto Start/Stop Logic which addresses a
possible PTU runaway with in-flight loss of #2 Hydraulic
system.
The respective pages are coded as follows:
MS 4-- 126354 and (MS 4-- 901472 or MS 4-- 901473) ONLY
The Abnormal and Emergency Checklist pages affected by
the above modifications, cabin interior configurations and
Local Authority requirements are identified in the List Of
Effective Pages (Page 15.1 and 15.2).
Pilots and operators must ensure that the appropriate QRH
pages are utilized, depending on both the configuration of
the airplane and Local Authority requirements.
PREFACE iv
PSM 1---84---1B
MAY
APR 15/05
19/18
TAXI CHECK
Taxi Light . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . as req’d
Altimeters . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . set
Flight Instruments . . . . . . . . . . . . . . . . . . . . . . . . . . . . . check
Tank Aux Pumps 1 and 2 . . . . . . . . . . . . . . . . . . . . . . . . . On
Autofeather . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Select
Flap . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . _____set / ind
Trims . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3 set
Condition levers . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Max
T/O Warn . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Test
Pitot Static Heat . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . on
Ice Protection . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . as req’d
Caution / Warning Lights . . . . . . . . . . . . . . . . . . . . . . . check
Flight Clearances . . . . . . . . . . . . . . . . . . . . . . . . . . reviewed
Cabin . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . secure
LINE UP
F/A Notification . . . . . . . . . . . . . . . . . . . . . . . . . . . . . as req’d
Bleed Air 1 and 2 . . . . . . . . . . . . . . . . . . . . . . . Min / as req’d
Anti-Collision . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . White
Transponder / TCAS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . on
Flight Controls . . . . . . . . . . . . . . . . . . . . . . . . . . . check / free
Flight / Taxi . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Flight
Landing / Taxi Lights . . . . . . . . . . . . . . . . . . . . . . . . . . on / Off
Note:
MAY 09/15
JUN
15/05
Before Entering icing Conditions, see page 2.7.
PSM 1---84---1B
Page 2.3
AFTER TAKE-OFF
Landing Gear . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Up
Flap . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 0
Autofeather . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . off
Climb Power . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . set
Bleed Air 1 and 2 . . . . . . . . . . . . . . . . . . . . . . . . on / as req’d
Stby Hyd Press and PTU Cntrl . . . . . . . . . . . . . . . . . . norm
Tank Aux Pumps 1 and 2 . . . . . . . . . . . . . . . . . . . . . . . . . . off
Engine Temps & Pressures . . . . . . . . . . . . . . . . . . . . . check
Ice Protection . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . as req’d
Cabin Press & Temp Controls . . . . . . . . . . . . . . . . . . . check
Passenger Signs . . . . . . . . . . . . . . . . . . . . . . . . . . . . as req’d
CRUISE
Altimeters . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . set
Power . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . set
Cabin Press . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . check
Lights . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . as req’d
Page 2.4
PSM 1---84---1B
MAY
APR 15/05
19/18
“CABIN PRESS”
(Warning Light)
OR
CABIN PRESSURIZATION FAILURE
(Loss of cabin pressure control and/or pressurization
controller “FAULT” Annunciation light illuminated)
D Bleed Air 1 and 2 . . . . . . . . . . . . . . . . . . . . . . on / Norm
D Cabin Pack and Flt Comp Pack . . . . . . . . . . . . . . Auto
D Auto / Man / Dump . . . . . . . . . . . . . . . . . . . . . . . . . . Auto
D Cabin Alt Fwd Outflow . . . . . . fully counter-clockwise
(Clsd)
D Fwd Outflow Valve . . . . . . . . . . . . . . . . . . . . . . . Normal
IF cabin altitude exceeds 8,000 ft:
D Bleed Selector . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Max
Control of pressurization is regained:
Yes
--- Monitor pressure differential, cabin altitude and
rate.
-- END -No
Auto / Man / Dump . . . . . . . . . . . . . . . . . . . . . . Man
Man Diff . . . . . . . . . . . . . . . . . . Incr / Decr as req’d
(5.46 psi diff max)
Note: INCR selection will increase cabin differential
pressure and cause the cabin altitude to descend.
DECR selection will decrease cabin differential
pressure and cause the cabin altitude to climb.
A one second selection of INCR / DECR will result in
approximately 300 ---500 fpm rate of change of cabin
altitude.
D
D
Control of pressurization is regained:
Yes
--- Use Cabin Altitude / Differential placard to
achieve appropriate cabin altitude in climb,
cruise and descent.
Prior to landing:
D Bleed Air 1 and 2 . . . . . . . . . . . . . . . . . Min / Off
-- END -No
--- Descend to below 14,000 ft as soon as
possible.
D UNPRESSURIZED FLIGHT (Page 4.4)
. . . . . . . . . . . . . . . . . . . . . . . . . . . . . accomplish
-- -- -- -- -- -- -- -- -- -- END -- -- -- -- -- -- -- -- -- --
MAY 19/18
APR
15/05
PSM 1---84---1B
Page 4.5
LOSS OF CABIN ALTITUDE, CABIN RATE
and CABIN DIFF INDICATORS
(All Indicators at Zero)
--D
D
D
Descend to below 14,000 ft as soon as possible.
Auto / Man / Dump . . . . . . . . . . . . . . . . . . . . . . . . . . Man
Man Diff . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Decr
UNPRESSURIZED FLIGHT (Page 4.4) . . accomplish
CABIN DIFF GREATER THAN 1.0 PSI
ON APPROACH
D
Cabin Alt Fwd Outflow . . . . . . . fully clockwise (Opn)
Note:
If Cabin differential does not decrease, assume
indication failure.
Prior to Landing:
D RAM VENTILATION (Page 4.4) . . . . . . . . . accomplish
CRACKED WINDSHIELD
D
D
D
-----
Airspeed . . . . . . . . . . . . . . . . . reduce (210 KIAS max)
Auto / Man / Dump . . . . . . . . . . . . . . . . . . . . . . . . . . Man
Man Diff . . . . . . . . . . . . . . Decr (2.5 --- 3.0 psi diff max)
Descend to below 14,000 ft if practical.
Use Man Diff control to maintain 2.5 --- 3.0 psi diff, or
less, in descent.
Prior to landing:
D Bleed Air 1 and 2 . . . . . . . . . . . . . . . . . . . . . . . . Min / Off
Page 4.6
PSM 1---84---1B
MAY
JUL 15/05
22/13
“FUSELAGE DOORS”
(Warning Light)
D
---
Passenger Signs . . . . . . . . . . . . . . . . . . . . . . . . . . . . . on
Confirm affected door on ’DOORS’ page of MFD.
Note:
A failed condition may also exist where NO
unsafe DOOR is indicated on the DOORS page
of the MFD.
IF pressurized:
--- Confirm normal pressure differential, cabin altitude and
rate.
Pressurization is normal:
Yes
D Passenger Signs . . . . . . . . . . . . . . . . . . . . . as req’d
--- Land at the nearest suitable airport.
-- END --
No
Loss of pressurization or Operating unpressurized
and
Security of affected door cannot be confirmed or
Operating handle of affected door is not in closed
position:
Warning: Do not attempt to secure affected door.
--- Land immediately at nearest suitable airport.
-- -- -- -- -- -- -- -- -- -- END -- -- -- -- -- -- -- -- -- --
“INTERNAL DOORS”
(Caution Light)
(Aircraft with Flight Compartment Door Remote Access
System)
“Internal Doors Fail” Advisory Light On:
D
D
Lower deadbolt latch . . . . . . . . rotate to secure door
Lock Isolate . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . press
-- END --
“BAGG DOOR” Advisory Light On:
---
Internal Baggage Door . . . . . . . . . . . . . check / secure
-- END --
“CKPT DOOR” Advisory Light On:
--- Flight Compartment Door . . . . . . . . . . check / secure
-- -- -- -- -- -- -- -- -- -- END -- -- -- -- -- -- -- -- -- -MAY 19/18
APR
15/05
PSM 1---84---1B
Page 4.9
“INTERNAL BAGG DOOR”
(Caution Light)
(Aircraft not equipped with Flight Compartment Door
Remote Access System)
---
Internal Baggage Door . . . . . . . . . . . . . check / secure
EMERGENCY OPENING OF
FLIGHT COMPARTMENT DOOR
(Door Jammed)
D
D
D
D
Unlock and push or step down on bottom hinge pin.
Unlock and pull down upper hinge pin.
Unlock and lift middle hinge pin.
Push flight compartment door at hinge side.
Note:
D
It may require a large force to open the flight
compartment door.
Rotate the flight compartment door counter-clockwise
and stow against the lavatory.
Note:
Upon forcing the flight compartment door open,
it may fall straight aft and lay flat on the cabin floor.
EMERGENCY OPENING OF
AIRSTAIR DOOR
(Door Fails To Open)
Electrical power applied to aircraft:
Yes
D
AIRSTAIR DOOR SOV cb
(Left Lower cb panel --- E1) . . . . . . . . . . . . . . . . pull
Note:
D
The airstair door failure to open may be
associated with a failure of IOM 1 or IOM 2.
Airstair Door . . . . . . . . . . . . . . . . . . . . . . . . . . . open
IF airstair door remains inoperative:
D Battery Master . . . . . . . . . . . . . . . . . . . . . . . . . . . Off
D Airstair Door . . . . . . . . . . . . . . . . . . . . . . . . . . . open
IF airstair door remains inoperative:
--- Exit via the left rear passenger access door.
-- END -No
--- Exit via the left rear passenger access door.
-- -- -- -- -- -- -- -- -- -- END -- -- -- -- -- -- -- -- -- -Page 4.10
PSM 1---84---1B
MAY
JUN 15/05
09/15
“FUSELAGE DOORS”
(Warning Light)
D
---
Passenger Signs . . . . . . . . . . . . . . . . . . . . . . . . . . . . . on
Confirm affected door on ’DOORS’ page of MFD.
Note:
A failed condition may also exist where NO
unsafe DOOR is indicated on the DOORS page
of the MFD.
IF pressurized:
--- Confirm normal pressure differential, cabin altitude and
rate.
Pressurization is normal:
Yes
D Passenger Signs . . . . . . . . . . . . . . . . . . . . . as req’d
--- Land at the nearest suitable airport.
-- END -No
Loss of pressurization or Operating unpressurized
and
Security of affected door cannot be confirmed or
Operating handle of affected door is not in closed
position:
Warning: Do not attempt to secure affected door.
--- Land immediately at nearest suitable airport.
-- -- -- -- -- -- -- -- -- -- END -- -- -- -- -- -- -- -- -- --
“COCKPIT DOOR”
(Caution Light)
(Aircraft with Flight Compartment Door Remote Access
System)
“Internal Doors Fail” Advisory Light On:
D
D
Lower deadbolt latch . . . . . . . . rotate to secure door
Lock Isolate . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . press
-- END --
“CKPT DOOR” Advisory Light On:
--- Flight Compartment Door . . . . . . . . . . check / secure
-- -- -- -- -- -- -- -- -- -- END -- -- -- -- -- -- -- -- -- --
FOR CARGO COMBI / 86 PAX AIRPLANES ONLY
MAY 19/18
APR
15/05
PSM 1---84---1B
Page 4.9
EMERGENCY OPENING OF
FLIGHT COMPARTMENT DOOR
(Door Jammed)
D
D
D
D
Unlock and push or step down on bottom hinge pin.
Unlock and pull down upper hinge pin.
Unlock and lift middle hinge pin.
Push flight compartment door at hinge side.
Note:
D
It may require a large force to open the flight
compartment door.
Rotate the flight compartment door counter-clockwise
and stow against the lavatory.
Note:
Upon forcing the flight compartment door open,
it may fall straight aft and lay flat on the cabin floor.
EMERGENCY OPENING OF
AIRSTAIR DOOR
(Door Fails To Open)
Electrical power applied to aircraft:
Yes
D
AIRSTAIR DOOR SOV cb
(Left Lower cb panel --- E1) . . . . . . . . . . . . . . . . pull
Note:
D
The airstair door failure to open may be
associated with a failure of IOM 1 or IOM 2.
Airstair Door . . . . . . . . . . . . . . . . . . . . . . . . . . . open
IF airstair door remains inoperative:
D Battery Master . . . . . . . . . . . . . . . . . . . . . . . . . . . Off
D Airstair Door . . . . . . . . . . . . . . . . . . . . . . . . . . . open
IF airstair door remains inoperative:
--- Exit via the left rear passenger access door.
-- END -No
--- Exit via the left rear passenger access door.
-- -- -- -- -- -- -- -- -- -- END -- -- -- -- -- -- -- -- -- --
FOR CARGO COMBI / 86 PAX AIRPLANES ONLY
Page 4.10
PSM 1---84---1B
MAY
FEB 23/16
15/05
NO STARTER CUT OUT
(START Light remains illuminated)
D
Start Select . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . off
Note:
D
Engine START and SELECT lights will take
approximately 15 seconds to go out.
DC Ext Power . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Off
Affected DC GEN caution light is illuminated:
Yes
D
DC Gen switch . . . . . . . . . . . . . . . . . . . Off then on
Affected DC GEN caution remains illuminated:
Yes
D
DC Gen switch . . . . . . . . . . . . . . . . . . . . . . . Off
Note:
Maintenance action required prior to
next flight.
-- END --
No
--- Check affected DC Gen load for normal
indications.
Note:
The flight may depart but maintenance
action required after landing.
-- -- -- -- -- -- -- -- -- -- END -- -- -- -- -- -- -- -- -- --
STARTER FAILURE ON GROUND
(SELECT Light remains illuminated)
D
D
D
D
D
---
Main, Aux and Stby Batteries . . . . . . . . . . . . . . . . . Off
DC Ext Power . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Off
AC Ext Power . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Off
Condition levers . . . . . . . . . . . . . . . . . . . . . . . . . Fuel Off
APU Pwr . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . off
Carry out remaining portions of Normal Shutdown
procedure.
MAY 09/15
JUN
15/05
PSM 1---84---1B
Page 5.5
APU FIRE
---
Confirm APU Automatic Shutdown (APU RUN
Advisory Light out and, APU FAIL, APU BTL LOW
and FUEL VALVE CLOSED Advisory Lights
illuminate).
IF APU BTL ARM or APU FIRE Advisory Lights remain
illuminated after 7 seconds:
D Extg switch . . . . . . . . . . . . . . . . . . . . . . . . . . . . press
POST APU AUTOMATIC SHUTDOWN (Page 5.6)
. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . accomplish
D
POST APU AUTOMATIC SHUTDOWN
APU Bleed . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . off
APU Gen . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . off
APU Pwr . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . off
D
D
D
Caution: Do not restart the APU following an automatic
shutdown if the FIRE Advisory Light is
illuminated.
APU START FAILURE
(APU FAIL Advisory Light illuminates during APU Start)
APU STARTER advisory light goes out:
D
APU Pwr . . . . . . . . . . . . . . . . . . . . . . . . . . . . off then on
Note:
---
After an APU start attempt, APU start will remain
disabled for approximately 7 seconds.
Attempt second APU start.
Note:
Observe APU Starter cranking limits.
-- END --
APU STARTER advisory light remains illuninated:
Note:
D
APU STARTER Light may remain illuminated for
approximately 10 seconds following illumination
of APU FAIL Light.
APU STARTER FAILURE
(Page 5.7) . . . . . . . . . . . . . . . . . . . . . . . . . accomplish
-- -- -- -- -- -- -- -- -- -- END -- -- -- -- -- -- -- -- -- --
Page 5.6
PSM 1---84---1B
MAY
APR 15/05
19/18
APU STARTER FAILURE
(APU STARTER Advisory Light remains illuminated)
Note:
D
D
D
D
D
APU STARTER Light may remain illuminated for
approximately 10 seconds following illumination
of APU FAIL Light.
Main, Aux and Stby Batteries . . . . . . . . . . . . . . . . . Off
DC Ext Power . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Off
AC Ext Power . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Off
Condition levers . . . . . . . . . . . . . . . . . . . . . . . . . Fuel Off
APU Pwr . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . off
“APU” (Caution Light)
APU Failure (APU FAIL Advisory Light):
--- Confirm APU Automatic Shutdown.
D POST APU AUTOMATIC SHUTDOWN
(Page 5.6) . . . . . . . . . . . . . . . . . . . . . . . . . . . accomplish
-- END -APU GEN Overheat (GEN OHT Advisory Light):
--- Confirm APU Automatic Shutdown.
D POST APU AUTOMATIC SHUTDOWN
(Page 5.6) . . . . . . . . . . . . . . . . . . . . . . . . . . . accomplish
-- END -APU GEN Failure (GEN WARN Advisory Light):
(APU Caution Light will not illuminate)
D
---
APU Gen . . . . . . . . . . . . . . . . . . . . . . . . . . . . off then On
Monitor DC Bus volts and APU Generator load for
normal indications.
IF GEN WARN Advisory Light remains illuminated:
D APU Gen . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . off
-- -- -- -- -- -- -- -- -- -- END -- -- -- -- -- -- -- -- -- --
APU BLEED AIR OVERHEAT
(FLT COMPT DUCT HOT or CABIN DUCT HOT or CABIN
PACK HOT or FLT COMPT PACK HOT Caution Light)
D
APU Bleed . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . off
MAY 19/18
APR
15/05
PSM 1---84---1B
Page 5.7
THIS PAGE INTENTIONALLY LEFT BLANK
Page 5.8
PSM 1---84---1B
MAY
JUN 15/05
09/15
“#1 ENG FADEC FAIL” or
“#2 ENG FADEC FAIL”
(Warning Light)
Affected Engine:
D ENGINE FAILURE / FIRE / SHUTDOWN
(Page 5.16) . . . . . . . . . . . . . . . . . . . . . . . accomplish
Note:
FADEC Failure may cause the affected engine to
shut down automatically.
“#1 ENG FADEC” or
“#2 ENG FADEC”
(Caution Light)
Affected Engine:
D Power lever . . . . . . . . . . . . adjust slowly and smoothly
Note:
Symmetric torque may require asymmetric
Power lever positions.
Landing Considerations:
--- DO NOT retard affected Power lever below Disc on
landing.
“POWERPLANT”
(ED Advisory)
-----
Monitor engine performance.
Maintenance action required prior to next flight.
“CHECK FIRE DET” Warning Light and
“FAULT A” or
“FAULT B” Advisory Light
(Fire Detector Loop Failure)
---
Maintenance action required prior to next flight.
“CHECK FIRE DET” Warning Light and
“BTL LOW” Advisory Light
(Fire Bottle Pressure Low)
---
Maintenance action required prior to next flight.
MAY 19/18
APR
15/05
PSM 1---84---1B
Page 5.15
ENGINE FAILURE/FIRE/SHUTDOWN
(In Flight)
Affected Engine:
D Power lever . . . . . . . . . . . . . . . . . . . . . . . . Flight Idle
D Condition lever . . . . . . . . . . . . . . . . . . . . . . . Fuel Off
D Alternate Feather (if req’d) . . . . . . . . . . . . . . . . Fthr
D Pull Fuel/Hyd Off Handle . . . . . . . . . . . . . . . . . . . pull
D Tank Aux Pump . . . . . . . . . . . . . . . . . . . . . . . . . . . . off
If Fire:
D Extg switch (affected engine) . . . . . . . . . . . Fwd Btl
If Fire Persists,Wait Up To 30 Seconds:
D Extg switch (affected engine) . . . . . . . . . . . . . Aft Btl
Caution: Propeller may unfeather if Autofeather is selected
off before Condition lever is selected to Fuel Off.
D
D
D
D
D
D
---
Autofeather . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . off
Power levers . . . . . . . . . . . . . . . . . . . . operate together
Ignition (Affected Engine) . . . . . . . . . . . . . . . . . . . . . Off
Bleed Air:
Operating Engine . . . . . . . . . . . . . . . . . . . . . . . as req’d
Affected Engine . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Off
Stby Hyd Press . . . . . . . . . . . . . . . . . . . . . . . . . . . . . On
Tank Aux Pump (Operating Engine) . . . . . . . . . . . . On
Transfer fuel as required to maintain fuel balance.
IF No. 1 engine inoperative:
D PTU Cntrl . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . norm
IF No. 2 engine inoperative:
D PTU Cntrl . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . On
Landing Considerations:
--- Disengage autopilot at 1,000 ft AGL.
Landing Distance Factor:
REF SPEED
INCR ON
Flap 10 . . . . . . . . . . . . . . . . . .
Flap 15 . . . . . . . . . . . . . . . . . .
Flap 35 . . . . . . . . . . . . . . . . . .
Page 5.16
1.40
1.40
1.50
PSM 1---84---1B
1.75
1.75
1.80
MAY
APR 15/05
19/18
AUTOFLIGHT, FLIGHT INSTRUMENTS AND
NAVIGATION
LOSS OF PILOT, CO-PILOT and STANDBY
AIRSPEED and ALTITUDE INDICATIONS . . . . . . 6.16
LOSS OF BOTH AIRSPEED and BOTH
ALTITUDE INDICATIONS ON PILOT’s and
CO-PILOT’s PFDs . . . . . . . . . . . . . . . . . . . . . . . . . . 6.17
AUDIO SYSTEM FAILURE . . . . . . . . . . . . . . . . . . . 6.33
“AFCS CONTROLLER INOP” (Message on PFD) 6.7
“AFCS FAIL” (Message on PFD) . . . . . . . . . . . . . . . 6.7
“ALIGNING” (Message on PFD) . . . . . . . . . . . . . . 6.21
“ALT FAIL” (Message on PFD) . . . . . . . . . . . . . . . . 6.17
“ALT MISMATCH” (Message on PFD) . . . . . . . . . 6.19
“ALT OFF” (Message on PFD) . . . . . . . . . . . . . . . . 6.9
“AP DISENGAGED” (Flashing PFD Message
and Red “AP DISENG” Light) . . . . . . . . . . . . . . . . . 6.5
“AP FAIL” (Message on PFD) . . . . . . . . . . . . . . . . . . 6.5
“AP INHIBIT” (Message on PFD) . . . . . . . . . . . . . 6.12
“AP PITCH TRIM FAIL” (Message on PFD) . . . . . . 6.8
“AP/YD DISENGAGED” (Flashing PFD Message
and Red “AP DISENG” Light) . . . . . . . . . . . . . . . . . 6.5
“AP/YD FAIL” (Message on PFD) . . . . . . . . . . . . . . 6.5
ARCDU 1 and ARCDU 2 FAILURE . . . . . . . . . . . . 6.34
ARCDU FAILURE . . . . . . . . . . . . . . . . . . . . . . . . . . 6.35
“ARCDU FAILED”
(Message on ARCDU display) . . . . . . . . . . . . . . . 6.35
ATC TRANSPONDER FAILURES . . . . . . . . . . . . . 6.36
“ATT FAIL” (Message on PFD) . . . . . . . . . . . . . . . . 6.14
“AUTO TRIM FAIL” (Message on PFD) . . . . . . . . . . 6.8
“AVIONICS”
(Caution Light) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6.37
CONTINUED ON NEXT PAGE
MAY 19/18
APR
15/05
PSM 1---84---1B
Page 6.1
AUTOFLIGHT, FLIGHT INSTRUMENTS AND
NAVIGATION
“CAT II FAIL” (Message on PFD) . . . . . . . . . . . . . . 6.11
“CHECK ED” (Message on ED) . . . . . . . . . . . . . . 6.23
“CHECK NAV SOURCE” (Message on PFD) . . . . 6.9
“CHECK PFD1” or “CHECK PFD2”
(Message on PFD) . . . . . . . . . . . . . . . . . . . . . . . . . 6.13
“CUE” (Message on PFD) . . . . . . . . . . . . . . . . . . . 6.18
“DUAL OFF” (Message on PFD) . . . . . . . . . . . . . 6.12
“DU BAD CONF” (ED) . . . . . . . . . . . . . . . . . . . . . . 6.23
ENGINE DISPLAY FAILURE . . . . . . . . . . . . . . . . . 6.23
“ED MON FAIL” (ED) . . . . . . . . . . . . . . . . . . . . . . . . 6.24
“FADEC1/DU” or “FADEC2/DU” or
“FADECS/DU” (ED) . . . . . . . . . . . . . . . . . . . . . . . . 6.24
“FANS FAIL” (ED) . . . . . . . . . . . . . . . . . . . . . . . . . . . 6.24
“FD ADC DATA INVLD” (Message on PFD) . . . . 6.10
“FD ATT DATA INVLD” (Message on PFD) . . . . . 6.10
“FD HDG DATA INVLD” (Message on PFD) . . . . 6.11
“FD NAV DATA INVLD” (Message on PFD) . . . . 6.11
“FLT DATA RECORDER”
(Caution Light) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6.37
“GPS INTEG” (Message on PFD) . . . . . . . . . . . . 6.21
“GPWS” (Caution Light) . . . . . . . . . . . . . . . . . . . . 6.37
“GPWS I/F FAIL” (ED) . . . . . . . . . . . . . . . . . . . . . . . 6.24
“GS MISMATCH” (Message on PFD) . . . . . . . . . 6.20
“HDG FAIL” (Message on PFD) . . . . . . . . . . . . . . . 6.14
“HDG MISMATCH” (Message on PFD) . . . . . . . . 6.15
CONTINUED ON NEXT PAGE
Page 6.2
PSM 1---84---1B
MAY
APR 15/05
19/18
AUTOFLIGHT, FLIGHT INSTRUMENTS AND
NAVIGATION
“HOT DISPLAYS” (ED) . . . . . . . . . . . . . . . . . . . . . . 6.25
“HOT ED” (ED) . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6.25
“HOT MFD1” or “HOT MFD2” (ED) . . . . . . . . . . . 6.25
“HOT PFD1” or “HOT PFD2” (ED) . . . . . . . . . . . . 6.25
“IAS FAIL” and / or “ALT FAIL”
(Messages on PFD) . . . . . . . . . . . . . . . . . . . . . . . . 6.17
“IAS FAIL” (Message on PFD) . . . . . . . . . . . . . . . . 6.17
“IAS MISMATCH” (Message on PFD) . . . . . . . . . 6.18
“IOM1 FAIL” (ED) . . . . . . . . . . . . . . . . . . . . . . . . . . . 6.26
“IOM2 FAIL” (ED) . . . . . . . . . . . . . . . . . . . . . . . . . . . 6.27
“IOMS FAIL” (ED) . . . . . . . . . . . . . . . . . . . . . . . . . . . 6.26
“IOP BAD CONF” (ED) . . . . . . . . . . . . . . . . . . . . . . 6.27
“IOP1 FAIL” (ED) . . . . . . . . . . . . . . . . . . . . . . . . . . . 6.29
“IOP2 FAIL” (ED) . . . . . . . . . . . . . . . . . . . . . . . . . . . 6.30
“IOPS FAIL” (ED) . . . . . . . . . . . . . . . . . . . . . . . . . . . 6.28
“IVSI FAIL” (Message on PFD) . . . . . . . . . . . . . . . 6.14
“L FD FAIL” (Message on PFD) . . . . . . . . . . . . . . . . 6.8
“LOC MISMATCH” (Message on PFD) . . . . . . . . 6.20
“MFD1 LINK FAIL” or “MFD2 LINK FAIL” (ED) . . 6.31
“MISTRIM [TRIM L WING DN]” or “MISTRIM
[TRIM R WING DN]” (Message on PFD) . . . . . . . . 6.6
“MISTRIM [TRIM NOSE DOWN]” or “MISTRIM
[TRIM NOSE UP]” (Message on PFD) . . . . . . . . . 6.6
MULTIFUNCTION DISPLAY FAILURE . . . . . . . . . 6.22
“NAV DR” (Message on PFD) . . . . . . . . . . . . . . . . 6.21
“NAV INTEG” (Message on PFD) . . . . . . . . . . . . . 6.21
“PFD1 LINK FAIL” or “PFD2 LINK FAIL” (ED) . . . 6.31
CONTINUED ON NEXT PAGE
MAY 19/18
APR
15/05
PSM 1---84---1B
Page 6.3
AUTOFLIGHT, FLIGHT INSTRUMENTS AND
NAVIGATION
“PFD1 MON FAIL” or “PFD2 MON FAIL” or
“PFDS MON FAIL” (ED) . . . . . . . . . . . . . . . . . . . . . 6.31
“PITCH MISMATCH” (Message on PFD) . . . . . . 6.15
PRIMARY FLIGHT DISPLAY FAILURE . . . . . . . . . 6.13
“R FD FAIL” (Message on PFD) . . . . . . . . . . . . . . . 6.8
“RA1 FAIL” or “RA2 FAIL” (ED) . . . . . . . . . . . . . . . . 6.32
“RA” (Message on PFD) . . . . . . . . . . . . . . . . . . . . . 6.20
“RAD ALT MISMATCH” (Message on PFD) . . . . 6.20
“RAS FAIL” (ED) . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6.31
“ROLL MISMATCH” (Message on PFD) . . . . . . . 6.15
“TCAS FAIL” (Message on PFD and MFD) . . . . . 6.22
“WOW/IOP1 FAIL” or “WOW/IOP2 FAIL” (ED) . . 6.32
“WOW/IOPS FAIL” (ED) . . . . . . . . . . . . . . . . . . . . . 6.32
“WTG1 FAIL” or “WTG2 FAIL” (ED) . . . . . . . . . . . . 6.33
“WTGS FAIL” (ED) . . . . . . . . . . . . . . . . . . . . . . . . . . 6.33
“WX FAIL” (Message on MFD) . . . . . . . . . . . . . . . 6.22
“YD DISENGAGED” (Flashing PFD Message) . . . 6.5
“YD INHIBIT” (Message on PFD) . . . . . . . . . . . . . 6.12
“YD NOT CENTERED” (Message on PFD) . . . . . . 6.9
Page 6.4
PSM 1---84---1B
MAY
APR 15/05
19/18
“YD NOT CENTERED”
(Message on PFD)
(Yaw Damper has disengaged in a non-centered position)
Wait 15 seconds:
D Yaw Damper . . . . . . . . . . . . . . . . . . . . . . . . . . . . engage
IF “YD NOT CENTERED” message remains displayed:
D Rudder Trim . . . . . . . . . . . . . . . . adjust (as necessary)
D Yaw Damper . . . . . . . . . . . . . . . . . . . . . . . . . . . . engage
IF the Yaw Damper does not engage after adjusting the
rudder trim:
D Autopilot and Yaw Damper . . . . . . . do not make any
further attempts to engage
“ALT OFF”
(Message on PFD)
(Pitch Thumbwheel motion has cancelled ALT* or ALT
mode)
-----
Confirm PRESELECT Altitude is set to an appropriate
value.
Re-select Flight Director modes as required.
“CHECK NAV SOURCE”
(Message on PFD)
(NAV Source or frequency change has cancelled NAV
mode)
-----
Confirm appropriate navigation data source is
selected.
Re-select Flight Director modes as required.
MAY 19/18
APR
15/05
PSM 1---84---1B
Page 6.9
“FD ADC DATA INVLD”
(Message on PFD)
(Selected air data source to FD is invalid or mismatched)
---
D
D
---
Determine valid air data source by comparing IAS and
altitude displayed on PFD 1 and 2 against the standby
instrument.
EFIS ADC source . . . . select 1 or 2 (as appropriate)
Airspeed . . . . . . . . . . . . . . . . . . . . . . . . 200 KIAS (max)
Re-select Flight Director modes as required.
Lost Services:
Autopilot and Yaw Damper
Note:
“ELEVATOR FEEL”, “PITCH TRIM”, “SPLR
OUTBD” and “RUD CTRL” Caution lights will be
illuminated. Elevator forces, roll rate and rudder
sensitivity may be higher or lower than normal.
“FD ATT DATA INVLD”
(Message on PFD)
(Selected attitude data input to FD is invalid or
mismatched)
---
D
D
---
Determine valid attitude source by comparing pitch
and roll displayed on PFD 1 and 2 against the standby
instrument.
EFIS ATT/HDG source . . . select 1 or 2 (appropriate)
Airspeed . . . . . . . . . . . . . . . . . . . . . . . . 200 KIAS (max)
Re-select Flight Director modes as required.
Lost Services:
Autopilot and Yaw Damper
Note:
Page 6.10
“ELEVATOR FEEL” Caution light will be
illuminated. Elevator forces may be higher or
lower than normal.
PSM 1---84---1B
MAY
JUN 15/05
09/15
“ALT MISMATCH”
(Message on PFD)
(Air data 1 and 2 altitude indications do not match)
---
Determine valid air data source by comparing altitude
displayed on PFD 1 and 2 against the standby
instrument.
Note:
If a mechanical Standby Altimeter is installed in
the aircraft, correct the reading on the standby
instrument as follows:
FLAP
0_
ALT
(ft)
IAS (kt)
SL
Subtract (ft)
0
15,000
Subtract (ft)
20,000 Subtract (ft)
& above
D
--D
5_, 10_, 15_ & 35_
150 or
lower VMO
VAPP or
VREF
VFE
0
0
100
0
300
0
100
0
400
EFIS ADC SOURCE . . . . . . . . select 1 or 2 (as req’d)
Fly the aircraft by reference to the selected air data
source.
Airspeed . . . . . . . . . . . . . . . . . . . . . . . . 200 KIAS (max)
Lost Services:
Autopilot and Yaw Damper
Note:
MAY 07/13
15/05
“ELEVATOR FEEL”, “PITCH TRIM”, “SPLR
OUTBD” and “RUD CTRL” Caution lights will
illuminate. Elevator forces, roll rate and rudder
sensitivity may be higher or lower than usual.
PSM 1---84---1B
Page 6.19
“LOC MISMATCH” or “GS MISMATCH”
(Message on PFD)
(ILS 1 and 2 deviation indications do not match)
--D
Determine valid localizer or glideslope source.
HSI SEL . . . . . . . . . . . . . select L or R (as appropriate)
Note:
If a mismatch appears between the two ILS
sources in DUAL APPR mode, the flight director
will automatically switch back to the HSI (which
may not be valid) that was in use at the
commencement of the approach.
“RA” (Message on PFD)
(Both Radar Altimeters have failed)
Lost Services:
Stick Pusher (Page 13.8)
EGPWS (Page 6.37)
TCAS (Page 6.22)
CAT II Approach
---
Ensure required clearance from terrain, obstructions
and other aircraft is maintained using alternate sources
of available information.
Landing Considerations:
--- Select approach where minimums and operating
procedures are not dependant upon radar altitude.
--- Land with Condition levers MAX/1020 only.
--- Flap 35 Landing Distance on a contaminated runway is
increased by 400 feet.
“RAD ALT MISMATCH”
(Message on PFD)
(Radar Altimeter 1 and 2 indications do not match)
Landing Considerations:
--- Select approach where minimums and operating
procedures are not dependant upon radar altitude.
Note:
Page 6.20
EGPWS ”Minimums” callouts will be based on
Rad Alt 1 altitudes.
PSM 1---84---1B
MAY
APR 15/05
19/18
“GPS INTEG”
(Message on PFD)
(The integrity of the GPS position cannot be assured to
meet minimum requirements for the particular phase of
flight)
---
Monitor FMS position by cross-reference to other
navigation sensors.
Note:
“GPS INTEG” message can appear on the
ground, due to local obstructions to satellite
reception.
Landing Considerations:
--- GPS-based approaches are not available.
“NAV INTEG”
(Message on PFD)
(The integrity of the FMS position cannot be assured to
meet minimum requirements for the particular phase of
flight)
D
Revert to an alternate means of navigation using other
available navigation sensors.
Note:
“NAV INTEG” message can appear on the
ground, due to local signal reception
characteristics.
“NAV DR”
(Message on PFD)
(The FMS is navigating by dead reckoning on the last
known track, groundspeed, heading and TAS)
D
Revert to an alternate means of navigation using other
available navigation sensors.
“ALIGNING” (Message on PFD)
(AHRS is in the alignment mode)
---
Do not move aircraft until AHRS alignment is complete.
MAY 19/18
APR
15/05
PSM 1---84---1B
Page 6.21
MULTIFUNCTION DISPLAY FAILURE
(No data displayed on MFD screen)
D
---
MFD (affected) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Off
Use operating MFD to display systems or navigation
data as required.
“TCAS FAIL”
(Message on PFD and MFD)
(No TCAS traffic display or audible warnings)
D
TCAS / ATC page on ARCDU . . . . . . ATC 1 or ATC 2
(as appropriate)
IF TCAS FAIL message remains displayed on the PFD:
D
TCAS / ATC page on ARCDU . . . . . . . . . . . . ATC SBY
---
Ensure adequate separation is maintained from other
aircraft using alternate sources of available
information.
“WX FAIL”
(Message on MFD)
(No weather radar display)
D
WX Radar . . . . . . . . . . . . . . . . . . . . . . . . . . . Off then on
IF message persists:
--- Ensure required clearance from areas of convective
weather is maintained using alternate sources of
available information.
Page 6.22
PSM 1---84---1B
MAY
APR 15/05
19/18
“HOT DISPLAYS” (ED)
(Two or more EIS display units are overheating)
---
Land at nearest suitable airport.
IF a PFD or ED should subsequently fail:
D MFD (1 or 2 as appropriate) . . . . . . . . . . PFD or ENG
“HOT ED” (ED)
(The ED display is overheating)
---
Maintenance action required prior to next flight.
IF the ED should subsequently fail:
D MFD (1 or 2 as appropriate) . . . . . . . . . . . . . . . . . ENG
“HOT MFD1” or
“HOT MFD2” (ED)
(The indicated MFD display is overheating)
---
Maintenance action required prior to next flight.
IF the MFD should subsequently fail:
D Opposite MFD (as appropriate) . . . . . . . NAV or SYS
“HOT PFD1” or
“HOT PFD2” (ED)
(The indicated PFD display is overheating)
---
Maintenance action required prior to next flight.
IF the PFD should subsequently fail:
D MFD (1 or 2 as appropriate) . . . . . . . . . . . . . . . . . PFD
MAY 07/13
15/05
PSM 1---84---1B
Page 6.25
“IOMS FAIL” (ED)
(Both avionics data Input/Output Modules have failed)
Potential Lost Services:
Stick Pusher (Page 13.8)
All Warning Tones and Audible Alerts (except TCAS and
EGPWS)
Flap Automatic Pitch Trim (if AP disengaged)
Flap Position Indications
All HYD Press and all HYD Quantity Indications
Parking Brake Press Indication
#1 & #2 Oil Press Indications
#1 & #2 Fuel Flow Indications
#1 & #2 Fuel Temp Indications
Automatic updating of fuel quantity and aircraft weight
on FMS FUEL and PERF pages
Weather Radar Display (if P660 WXR) (Page 6.22)
Note:
Lost services will vary in response to the mode of
the specific IOM failure.
When selecting Flap 15 to Flap 35 or Flap 35 to
Flap15, there will be an increase in the pitch trim
adjustment.
Pusher Syst Fail Caution light will illuminate after
landing.
“IOM1 FAIL” (ED)
(#1 avionics data Input/Output Module has failed)
Potential Lost Services:
Stick Pusher (Page 13.8)
Flap Position Indication on MFD 1
#1 & #3 HYD Quantity Indications
Parking Brake Press Indication
#1 Oil Press Indication
#1 & #2 Fuel Flow Indications
#1 Fuel Temp Indication
Automatic updating of fuel quantity and aircraft weight
on FMS FUEL and PERF pages
Weather Radar Display (if P660 WXR) (Page 6.22)
D
MFD 2 WX/TERR . . . . . . . . . . . . . . . . . . . . WX (if req’d)
Note:
Page 6.26
Lost services will vary in response to the mode of
the specific IOM failure.
Pusher Syst Fail Caution light will illuminate after
landing.
PSM 1---84---1B
MAY
APR 15/05
19/18
“IOM2 FAIL” (ED)
(#2 avionics data Input/Output Module has failed)
Potential Lost Services:
Stick Pusher (Page 13.8)
Flap Position Indication on MFD 2
#2 Oil Press Indication
#2 HYD Quantity Indication
#2 Fuel Temp Indication
Weather Radar Display (if P660 WXR) (Page 6.22)
MFD 1 WX/TERR . . . . . . . . . . . . . . . . . . . . WX (if req’d)
D
When required to confirm flap position:
D ESID ALL button . . . . . . . . . . . . . press (momentarily)
Note:
Lost services will vary in response to the mode of
the specific IOM failure.
Pusher Syst Fail Caution light will illuminate after
landing.
“IOP BAD CONF” (ED)
(Configuration of an avionics Input/Output Processor is
incorrect on aircraft power-up)
---
Maintenance action required prior to next flight.
MAY 19/18
APR
15/05
PSM 1---84---1B
Page 6.27
“IOPS FAIL” (ED)
(Both avionics data Input/Output Processors have failed)
Potential Lost Services:
Stick Pusher (Page 13.8)
All Warning Tones and Audible Alerts
EGPWS
TCAS
Flap Automatic Pitch Trim (if AP disengaged)
FMS 1 and 2
VOR 1 and 2
DME 1 and 2
ADF 1 and 2
Heading Bug, Altitude Pre-Selector, HSI SEL transfer
Speed Bugs DH and MDA indications
Low Speed Cues
Inc Ref Speed Indication on ED
Radar Altitude Indication
ATC Mode S
CAT II Approach
Flap Position Indications
PFCS Indications
All HYD Press and all HYD Quantity Indications
#1 & #2 Oil Press Indications
#1 & #2 Fuel Flow Indications
#1 & #2 Fuel Temp Indications
#1 & #2 Fuel Quantity Indications
SAT Indications
Electrical Parameter Indications on Electrical Page
Doors Status Indications on Doors Page
Automatic updating of fuel quantity and aircraft weight
on FMS FUEL and PERF pages
Weather Radar Display (if P660 WXR) (Page 6.22)
D
D
Autopilot . . . . . . . . . . . . . . . . . . . . . . . . . . . . . disengage
Airspeed . . . . . . . . . . . . . . . . . . . . . . . . 200 KIAS (max)
---
Fly the aircraft by reference to raw data to accomplish
the remainder of the flight.
Establish and use alternate means to determine aircraft
position in order to navigate and to ensure required
clearance from terrain, obstructions, convective
weather and other aircraft is maintained.
---
CONTINUED ON NEXT PAGE
Page 6.28
PSM 1---84---1B
MAY
APR 15/05
19/18
Note:
Lost services will vary in response to the mode of
the specific IOP failure.
“ELEVATOR FEEL” Caution Light will illuminate.
Elevator forces may be higher or lower than
normal.
When selecting Flap 15 to Flap 35 or Flap 35 to
Flap15, there will be an increase in the pitch trim
adjustment.
Pusher Syst Fail Caution light will illuminate after
landing.
“IOP1 FAIL” (ED)
(#1 avionics data Input/Output Processor has failed)
Potential Lost Services:
Stick Pusher (Page 13.8)
EGPWS Audible Warnings
FMS 1
Speed Bugs DH and MDA indications on PFD 1
CAT II Approach
#1 & #3 HYD Quantity Indications
#1 Fuel Temp Indication
EGPWS Terrain Display on MFD 1
Weather Radar Display on MFD 1
D
D
D
Autopilot . . . . . . . . . . . . . . . . . . . . . . . . . . . . . disengage
Airspeed . . . . . . . . . . . . . . . . . . . . . . . . 200 KIAS (max)
MFD 2 WX/TERR . . . . . . . . . . . . WX or TERR (if req’d)
Note:
MAY 19/18
APR
15/05
Lost services will vary in response to the mode of
the specific IOP failure.
“ELEVATOR FEEL” Caution Light will illuminate.
Elevator forces may be higher or lower than
normal.
Spurious warning tones and audible alerts may
occur
Pusher Syst Fail Caution light will illuminate after
landing.
PSM 1---84---1B
Page 6.29
“IOP2 FAIL” (ED)
(#2 avionics data Input/Output Processor has failed)
Potential Lost Services:
Stick Pusher (Page 13.8)
TCAS (Page 6.22)
FMS 2
Speed Bugs, DH and MDA indications on PFD 2
CAT II Approach
#2 HYD Quantity Indications
#2 Fuel Temp Indication
EGPWS Terrain Display on MFD 2
Weather Radar Display on MFD 2
D
D
D
Autopilot . . . . . . . . . . . . . . . . . . . . . . . . . . . . . disengage
Airspeed . . . . . . . . . . . . . . . . . . . . . . . . 200 KIAS (max)
MFD 1 WX/TERR . . . . . . . . . . . . WX or TERR (if req’d)
Note:
Page 6.30
Lost services will vary in response to the mode of
the specific IOP failure.
“ELEVATOR FEEL” Caution Light will illuminate.
Elevator forces may be higher or lower than
normal.
Spurious warning tones and audible alerts may
occur
Pusher Syst Fail Caution light will illuminate after
landing.
PSM 1---84---1B
MAY
APR 15/05
19/18
“PFD1 LINK FAIL” or
“PFD2 LINK FAIL” (ED)
(The EIS is no longer able to monitor information
displayed on the indicated PFD for errors)
---
Maintenance action required prior to next flight.
“MFD1 LINK FAIL” or
“MFD2 LINK FAIL” (ED)
(The EIS is no longer able to monitor information
displayed on the indicated MFD for errors)
---
Maintenance action required prior to next flight.
“PFD1 MON FAIL” or “PFD2 MON FAIL” or
“PFDS MON FAIL” (ED)
(The EIS is no longer able to monitor information
displayed on the indicated PFD for errors)
---
Maintenance action required prior to next flight.
“RAS FAIL” (ED)
(Both Radar Altimeters have failed)
Lost Services:
Stick Pusher (Page 13.8)
EGPWS Aural Warnings
TCAS (Page 6.22)
CAT II Approach
--- Ensure required clearance from terrain, obstructions
and other aircraft is maintained using alternate sources
of available information.
Landing Considerations:
--- Select approach where minimums and operating
procedures are not dependant upon radar altitude.
--- Land with Condition levers MAX/1020 only.
--- Flap 35 Landing Distance on a contaminated runway is
increased by 400 feet.
MAY 19/18
APR
15/05
PSM 1---84---1B
Page 6.31
“RA1 FAIL” or
“RA2 FAIL” (ED)
(The indicated Radar Altimeter has failed)
---
Maintenance action required prior to next flight.
Note:
Radar altitude will continue to be displayed on
PFD 1 and 2 from the remaining operative radar
altimeter.
“WOW/IOPS FAIL” (ED)
(Neither Input/Output Processor is receiving Weight On
Wheels information)
Landing Considerations:
--- Airspeed Indications will go invalid on both PFDs below
80 Knots.
--- Stick Shaker may activate during landing rollout and
taxi.
“WOW/IOP1 FAIL” or
“WOW/IOP2 FAIL” (ED)
(The indicated Input/Output Processor is not receiving
Weight On Wheels information)
---
Maintenance action required prior to next flight.
Page 6.32
PSM 1---84---1B
MAY 07/13
15/05
“WTGS FAIL” (ED)
(Both Warning Tone Generators have failed)
Lost Warning Tones and Aural Alerts:
Engine Fire
Take-off Warning
Overspeed Warning
Autopilot Disengagement
Pitch Trim in Motion
Landing Gear Configuration
Beta Lockout
Caution / Warning Alert
Altitude Alert
SELCAL / Unilink Alerts
--- Establish and use alternate means to monitor aircraft
airspeed, altitude and operating condition.
Note:
EGPWS and TCAS audible warnings continue to
function normally.
“WTG1 FAIL” or
“WTG2 FAIL” (ED)
(The indicated Warning Tone Generator has failed)
---
Maintenance action required prior to next flight.
AUDIO SYSTEM FAILURE
(Loss of audio or no control of audio level or transmit
source selections)
IF FAIL is displayed in red on the ARCDU INT display area:
--- Assign communication duties with ATC and Cabin
Crew to pilot with functional audio system.
Note:
RCAU has automatically re-configured to select
VHF1, VHF 2 and interphone audio to the affected
pilot’s headset at a fixed volume. Affected pilot
handset, boom and mask microphones are
selected to transmit on INT ---only. VHF 1, VHF 2
and PACIS transmit functions are not available.
IF one pilot headset is no longer receiving any audio
signals:
--- Connect affected headset to the AUX output on the
Audio Jack Panel.
Note:
The AUX output is configured to receive the same
audio sources selected by the opposite pilot.
Own side VHF 1, VHF 2, INT and PACIS transmit
functions continue to operate normally.
MAY 19/18
APR
15/05
PSM 1---84---1B
Page 6.33
ARCDU 1 and ARCDU 2 FAILURE
(Loss of both ARCDU functions)
D
ARCDU 1 and 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Off
Wait 5 seconds:
D ARCDU 1 and 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . On
IF ARCDUs are still inoperative:
D
D
Stby VHF Control . . . . . . . . . . . . . . . . . . . . . . . . . . . . On
Norm / Emer . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Emer
---
Establish alternate means to communicate between
cockpit crew members as Hot MIC and INT transmit
functions are not available.
---
Establish air to ground communications on VHF 1 with
the left seat pilot using the standby VHF controller.
---
Establish alternate means to communicate with Cabin
Crew as PACIS transmit function is not available.
Note:
Page 6.34
In EMERGENCY mode, ARCDU selections revert
to default settings as follows:
Left ARCDU --- VHF 1 and interphone audio are
connected to the left seat pilot’s headset at a
fixed volume. Pilot’s handset, boom and mask
microphones are selected to transmit on VHF 1
only.
Right ARCDU --- VHF 2 and interphone audio are
connected to the right seat pilot’s headset at a
fixed volume. Right seat pilot’s handset, boom
and mask microphones are selected to transmit
on VHF 2 only.
PSM 1---84---1B
MAY
APR 15/05
19/18
ARCDU FAILURE
OR
“ARCDU FAILED”
(Message on ARCDU display)
(Loss of ARCDU functions)
D
ARCDU (affected) . . . . . . . . . . . . . . . . . . . . . . . . . . . Off
Wait 5 seconds:
D ARCDU (affected) . . . . . . . . . . . . . . . . . . . . . . . . . . . On
IF annunciation re-appears:
D Norm / Emer . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Emer
-----
Establish alternate means to communicate between
cockpit crew members as Hot MIC and INT transmit
functions are not available to pilot with failed ARCDU.
Assign communication duties with ATC and Cabin
Crew to pilot with functional ARCDU.
Note:
MAY 19/18
APR
15/05
In EMERGENCY mode, ARCDU selections revert
to default settings as follows:
Left ARCDU --- VHF 1 and interphone audio are
connected to the left seat pilot’s headset at a
fixed volume. Pilot’s handset, boom and mask
microphones are selected to transmit on VHF 1
only.
Right ARCDU --- VHF 2 and interphone audio are
connected to the right seat pilot’s headset at a
fixed volume. Right seat pilot’s handset, boom
and mask microphones are selected to transmit
on VHF 2 only.
PSM 1---84---1B
Page 6.35
ATC TRANSPONDER FAILURES
ATC 1 “FAIL” or ATC 2 “FAIL”
(Message on ARCDU TCAS/ATC exp page)
(ON ALT FAIL displayed in red on the ARCDU ATC
display area)
TCAS FAIL displayed on PFDs / MFDs:
D
---
TCAS / ATC page on ARCDU . . . . . . ATC 1 or ATC 2
(as appropriate)
Confirm ON ALT is displayed in green in ARCDU ATC
area for selected ATC and TCAS TA / RA or TA ONLY is
displayed on PFD / MFD.
-- END --
TCAS STBY displayed on PFDs / MFDs:
D
---
TCAS / ATC page on ARCDU . . . . . . ATC 1 or ATC 2
(as appropriate)
Confirm ON ALT is displayed in green in ARCDU ATC
area for selected ATC and TCAS TA / RA or TA ONLY is
displayed on PFD / MFD.
-- END --
TCAS TA / RA or TA ONLY displayed on PFDs / MFDs:
--- No ADS---B position data. Coordinate with Air Traffic
Control for inoperative ADS ---B Out operations. Other
ATC and TCAS functions are available except as noted.
Note:
When ADS ---B position data are not received,
Mode A codes must be entered with the selected
ATC in SBY.
-- -- -- -- -- -- -- -- -- -- END -- -- -- -- -- -- -- -- -- --
ALT 1 “FAIL” or ALT 2 “FAIL”
(Message on ARCDU TCAS/ATC exp page)
(ALT displayed in red on the ARCDU ATC display area)
D
---
TCAS / ATC page on ARCDU . . . . . . . ALT 1 or ALT 2
(as appropriate)
Confirm ALT is displayed in green in ARCDU ATC area
for selected ALT source.
Page 6.36
PSM 1---84---1B
MAY
APR 15/05
19/18
“AVIONICS”
(Caution Light)
-----
Check for associated advisory message on ED.
Maintenance action required prior to next flight.
“FLT DATA RECORDER”
(Caution Light)
D
Anti-Collision Light . . . . . . . . . . . . . . . . . Red or White
IF Caution Light remains on:
--- Maintenance action required prior to next flight.
“GPWS”
(Caution Light)
(Loss of EGPWS Terrain Display and Audible Warnings)
---
Establish and use alternate means to ensure required
clearance from terrain is maintained.
MAY 19/18
APR
15/05
PSM 1---84---1B
Page 6.37
THIS PAGE INTENTIONALLY LEFT BLANK
Page 6.38
PSM 1---84---1B
MAY 07/13
15/05
FUSELAGE FIRE, SMOKE or FUMES
“SMOKE” (Warning Light) . . . . . . . . . . . . . . . . 7.2
FUSELAGE FIRE, SMOKE or FUMES . . . . . . 7.2
SMOKE or FUMES REMOVAL
(UNKNOWN SOURCE) . . . . . . . . . . . . . . . . . . . 7.6
MAY 22/16
JUL
15/05
PSM 1---84---1B
Page 7.1
“SMOKE”
(Warning Light)
(SMOKE Warning Light and related Baggage / Cargo
SMOKE and EXTG Advisory Lights)
OR
FUSELAGE FIRE, SMOKE or FUMES
D
D
D
D
Oxygen Masks . . . . . . . . . . . . . . . . . . on / 100%
Smoke Goggles (if applicable) . . . . . . . . . . . on
Mic Switch . . . . . . . . . . . . . . . . . . . . . . . . . Mask
Recirc Fan . . . . . . . . . . . . . . . . . . . . . . . . . . . Off
IF SMOKE/EXTG switch is illuminated:
D Illuminated SMOKE / EXTG switch . . . . press
---
Prepare to land the aircraft without delay while
completing fire suppression and/or smoke or
fumes evacuation procedures.
Known Source of Fire, Smoke or Fumes:
Flight Compartment:
Note:
If an electrical source of fire, smoke or fumes
is positively identified, remove power to
source if possible.
--- Extinguish fire with portable fire extinguishers.
--- If it cannot be visibly verified that the fire has been
extinguished following fire suppression, land
immediately at the nearest suitable airport.
To remove smoke or fumes:
D Cabin Alt Fwd Outflow . . . . . . . . . . turn clockwise
towards Opn
Note:
Flight compartment airflow will carry the
smoke or fumes forward.
IF additional assistance to remove smoke or fumes is
required:
Note:
This step will de-pressurize the aircraft
rapidly.
D Fwd Outflow Valve . . . . . . . . . . . . . . . . . . . . . Open
--- Descend to below 14,000 ft as soon as possible.
--- END --CONTINUED ON NEXT PAGE
Page 7.2
PSM 1---84---1B
MAY
APR 15/05
19/18
EMERGENCY LANDING
(Both Engines Operating)
-----
Flight compartment and cabin . . . . . . . . . . . . . secure
If possible, ensure no passengers are seated in the
plane of the propellers.
Note:
D
D
D
D
D
Configuring the forward right hand emergency
exit for ditching may require the aircraft to be
depressurized to reduce the force on the lower
exit door handle.
EGPWS cb (Left Upper cb panel --- A1) . . . . . . . . . pull
Emergency Lights . . . . . . . . . . . . . . . . . . . . . . . . . . . On
Auto / Man / Dump . . . . . . . . . . . . . . . . . . . . . . . . . Dump
ELT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . On
Shoulder Harness . . . . . . . . . . . . . . . . . . . . . . . . . . lock
Review appropriate Landing Considerations:
Landing Gear Extended . . . . . . . . . . . . . . . . . Page 8.3
Landing Gear Retracted . . . . . . . . . . . . . . . . . Page 8.3
Ditching . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Page 8.4
Landing Gear Extended:
When airplane comes to a stop:
D Emerg Brake . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . set
D Condition levers . . . . . . . . . . . . . . . . . . . . . . . . . Fuel Off
D Pull Fuel/Hyd Off Handles . . . . . . . . . . . . . . . . . . . . pull
D Battery Master . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Off
--- Evacuate airplane.
Landing Gear Retracted:
Landing Considerations:
--- Land using Flap 35.
--- Maintain VREF until immediately prior to flare.
--- DO NOT exceed 6_ nose up during flare.
--- Touch down with minimum speed and minimum rate of
descent without stalling.
After ground contact:
D Condition levers . . . . . . . . . . . . . . . . . . . . . . . . . Fuel Off
D Pull Fuel/Hyd Off Handles . . . . . . . . . . . . . . . . . . . . pull
D Battery Master . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Off
When airplane comes to a stop:
--- Evacuate airplane.
MAY 19/18
APR
15/05
PSM 1---84---1B
Page 8.3
Ditching:
D
D
D
Condition levers . . . . . . . . . . . . . . . . . . . . . . . . . . . . Max
Bleed Air 1 and 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . Off
Flap . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 35
Landing Considerations:
--- DO NOT select Landing Gear Down.
--- In rolling swell surface conditions attempt to ditch
along and parallel to the crests as much into wind as
swell line permits. In other water surface conditions
land into wind.
--- Maintain VREF until immediately prior to flare.
--- Commence flare to achieve zero vertical velocity
immediately prior to water contact.
--- Maintain pitch attitude of 10_ nose up.
--- Touch down with minimum speed and minimum rate of
descent without stalling.
--- A transient nose-up pitching motion may result
following touchdown. Overcorrection of this tendency
could result in porpoising or nosing in.
After water contact:
D Condition levers . . . . . . . . . . . . . . . . . . . . . . . . . Fuel Off
D Pull Fuel/Hyd Off Handles . . . . . . . . . . . . . . . . . . . . pull
D Battery Master . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Off
When airplane comes to a stop:
Warning: DO NOT open the Aft Doors or the lower portion
of the right forward emergency exit.
---
Evacuate airplane.
Note:
Page 8.4
After completion of the ditching run, the airplane
will float with one wing in the water. The upper
portion of the right forward emergency exit and
the airstair door should be used for evacuation.
The airstair door ditching dam must be in place
prior to opening the door.
PSM 1---84---1B
MAY
JUN 15/05
09/15
FORCED LANDING
(Both Engines Inoperative)
D
D
Hyd #3 Isol Vlv . . . . . . . . . . . . . . . . . . . . . . . . . . . Open
Airspeed . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1.23 VSR
Note:
With Flap 0_, landing gear retracted, propellers
feathered and zero wind, 2.5 nautical miles can
be travelled for every 1,000 feet of altitude loss.
All Hydraulic(except for elevator control),
pneumatic, and non-essential electrical services
will be inoperative.
D
ENGINE AIRSTART (Page 5.9) . . . . . . . . . accomplish
When all attempts to achieve a successful airstart have
failed:
--- Flight compartment and cabin . . . . . . . . . . . . . secure
Note:
Configuring the forward right hand emergency
exit for ditching may require the aircraft to be
depressurized to reduce the force on the lower
exit door handle.
D
D
D
D
D
Main, Aux & Stby Batteries . . . . . . . . . . . . . . . . . . . Off
Passenger signs . . . . . . . . . . . . . . . . . . . . . . . . . . . . . on
Emergency Lights . . . . . . . . . . . . . . . . . . . . . . . . . . . On
ELT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . On
Shoulder Harness . . . . . . . . . . . . . . . . . . . . . . . . . . lock
-----
Make the approach and landing into wind.
Extending landing gear will steepen glide angle and
decrease glide distance.
Review Appropriate Landing Considerations:
Landing Gear Extended . . . . . . . . . . . . . . . . . Page 8.6
Landing Gear Retracted . . . . . . . . . . . . . . . . . Page 8.6
Ditching . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Page 8.7
MAY 19/18
APR
15/05
PSM 1---84---1B
Page 8.5
Landing Gear Extended:
Landing Considerations:
IF the available surface is appropriate, extend landing gear
allowing sufficient time for alternate gear extension.
--- Maintain 1.23 VSR until immediately prior to flare.
--- Commence flare to achieve zero vertical velocity
immediately prior to ground contact.
--- DO NOT exceed 6_ nose up during flare.
--- Touch down with minimum speed and minimum rate of
descent without stalling.
Prior to landing:
D ALTERNATE LANDING GEAR EXTENSION
(Page 14.3) . . . . . . . . . . . . . . . . . . . . . . . . . . accomplish
After touchdown:
D Battery Master . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Off
D Emerg Brake . . . . . . . . . . . . . . . . . apply intermittently
When airplane comes to a stop:
--- Evacuate airplane.
Landing Gear Retracted:
Landing Considerations:
--- Maintain 1.23 VSR until immediately prior to flare.
--- Commence flare to achieve zero vertical velocity
immediately prior to ground contact.
--- DO NOT exceed 5_ nose up during flare
--- Touch down with minimum speed and minimum rate of
descent without stalling.
When airplane comes to a stop:
D Battery Master . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Off
--- Evacuate airplane.
Page 8.6
PSM 1---84---1B
MAY
APR 15/05
19/18
GALLEY
BUS
MAY 15/05
OCT
31/10
PSM 1---84---1B
GCU
#1 AC GEN
HOT
#1 AC
GEN
OFF
L VARIABLE
AC BUS
L TRU
#1 AC GEN
#1 AC
GEN
L AC BUS
28V DC
#2 AC
GEN
R AC BUS
EXT
PWR
#2 AC GEN
OFF
28V DC
#2 AC GEN
HOT
GCU
#2 AC
GEN
R VARIABLE
AC BUS
R TRU
OFF
GALLEY
BUS
NOTE
Condition levers above
START & FEATHER.
Min/850 to Max/1050 RPM range.
AC GEN1 and AC GEN2 switches on.
AC Power Schematic
Page 9.3
LOSS OF MAIN DC BUS POWER
Lost Services:
LEFT MAIN DC BUS
Autopilot and Yaw Damper
Auto Cabin Pressurization
Stick Pusher
ALT Downlock Ind
L ECS Auto
Rud Sys Isol
Ovrhd, Glareshied, Plt Lts
L Flare, L Appr, Taxi Lts
PFD1
ESID CP, Plt EFIS CP
FMS1, DME1 ADF1
EGPWS, TCAS, ATC1
Flt Attnd Handset
Weather Radar
RIGHT MAIN DC BUS
Autopilot and Yaw Damper
Stick Pusher
Anti-Skid
R ECS Auto
Pilot Window Heat
Deice Boot Lights
Cntr Console, Co-Plt Lts
R Flare, R Appr, Anti-Col Lts
Cabin Lights
PFD2, MFD2, ADU2
TCAS, ATC2
VHF2
FMS2, DME2, VOR2
Clock 2
MAIN DC BUS FAILURE
No “DC BUS” Caution Light
Left Main DC Bus Failure:
Note:
D
D
D
---
A failure of the Left Main DC Bus will result in the
loss of some or all of the services powered by the
Left Main DC Bus. Illumination of caution lights
and presentation of messages associated with
the lost systems will occur, refer to LOSS OF
MAIN DC BUS POWER (Page 9.4).
DC Gen 1 Load . . . . . . . . . . . . . . . . . . . . . . . . confirm 0
Aux Battery Load . . . . . . . . . . . . . confirm negative (---)
DC Gen 1 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Off
Confirm all lost services are restored (LOSS OF MAIN
DC BUS POWER, Page 9.4).
Right Main DC Bus Failure:
Note:
D
D
D
---
A failure of the Right Main DC Bus will result in the
loss of some or all of the services powered by the
Right Main DC Bus. Illumination of caution lights
and presentation of messages associated with
the lost systems will occur, refer to LOSS OF
MAIN DC BUS POWER (Page 9.4).
DC Gen 2 Load . . . . . . . . . . . . . . . . . . . . . . . . confirm 0
Main Battery Load . . . . . . . . . . . . confirm negative (---)
DC Gen 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Off
Confirm all lost services are restored (LOSS OF MAIN
DC BUS POWER, Page 9.4).
Page 9.4
PSM 1---84---1B
MAY
APR 15/05
19/18
“DC BUS”
(Caution Light)
Other associated caution lights are illuminated:
Yes
D
MAIN DC BUS FAULT (below) . . . . . . accomplish
-- END --
D
Bus Fault Reset . . . . . . . . . . . . . . . . . . . . . . . . Reset
No
-- -- -- -- -- -- -- -- -- -- END -- -- -- -- -- -- -- -- -- --
MAIN DC BUS FAULT
“DC BUS” Caution Light
Left Main DC Bus Fault:
(“DC BUS”, “#1 DC GEN”, “STBY BATTERY” and “AUX
BATTERY” Caution Lights):
D Aux & Stby Batteries . . . . . . . . . . . . . . . . . . . . . . . . . Off
D DC Gen 1 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Off
D Bus Fault Reset . . . . . . . . . . . . . . . . . . . . . . . . . . . Reset
--- Leave selected switches in the OFF position.
DC BUS Caution Light remains illuminated:
Yes
Note:
ECS pack airflow is lost and cabin will
depressurize.
--- Descend to below 14,000 ft as soon as possible.
D Auto / Man / Dump . . . . . . . . . . . . . . . . . . . . . . . Man
D Man Diff . . . . . . . . . . . . . . . . . . . . . . . . Incr (50 sec)
--- Land at nearest suitable airport.
When below 14,000 ft, ventilate cabin:
D Recirc Fan . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Off
D Bleed Air 1 and 2 . . . . . . . . . . . . . . . . . . . . . Min / Off
D Cabin Alt Fwd Outflow . . . . fully clockwise (Opn)
D Fwd Outflow Valve . . . . . . . . . . . . . . . . . . . . . Open
Note:
Ram ventilation is most effective above 150
KIAS.
--- Refer to LOSS OF MAIN DC BUS POWER (Page
9.4) for a list of lost services.
-- END -No
--- Monitor DC Bus volts and Generator loads for
normal indications.
-- END --
CONTINUED ON NEXT PAGE
MAY 19/18
APR
15/05
PSM 1---84---1B
Page 9.5
Right Main DC Bus Fault:
(“DC BUS”, “#2 DC GEN”, and “MAIN BATTERY”
Caution Lights)
D Main Battery . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Off
D DC Gen 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Off
D Bus Fault Reset . . . . . . . . . . . . . . . . . . . . . . . . . . . Reset
--- Leave selected switches in the OFF position.
DC BUS Caution Light remains illuminated:
Yes
Note:
ECS pack airflow is lost and cabin will
depressurize.
--- Descend to below 14,000 ft as soon as possible.
--- Land at nearest suitable airport.
When below 14,000 ft, ventilate cabin:
D Recirc Fan . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Off
D Bleed Air 1 and 2 . . . . . . . . . . . . . . . . . . . . . Min / Off
D Auto / Man / Dump . . . . . . . . . . . . . . . . . . . . . . . Man
D Man Diff . . . . . . . . . . . . . . . . . . . . . . . . Incr (50 sec)
D Cabin Alt Fwd Outflow . . . . fully clockwise (Opn)
D Fwd Outflow Valve . . . . . . . . . . . . . . . . . . . . . Open
Note:
Ram ventilation is most effective above 150
KIAS.
--- Refer to LOSS OF MAIN DC BUS POWER (Page
9.4) for a list of lost services.
Landing Considerations:
--- Anti-Skid will be inoperative. For maximum
deceleration, use intermittent 1 second pedal brake
applications with intervals of reduced braking as
brief as possible.
Caution: Excessive application of pedal brakes can
result in skidding and tire failure.
Landing Distance Factor:
REF SPEED
INCR ON
Flap 10 . . . . . . . . . . . . . . . . . .
Flap 15 . . . . . . . . . . . . . . . . . .
Flap 35 . . . . . . . . . . . . . . . . . .
1.70
1.70
1.70
2.1
2.1
2.0
-- END -No
--- Monitor DC Bus volts and Generator loads for
normal indications.
-- -- -- -- -- -- -- -- -- -- END -- -- -- -- -- -- -- -- -- --
Page 9.6
PSM 1---84---1B
MAY
APR 15/05
19/18
“DC BUS”
(Caution Light)
Other associated caution lights are illuminated:
Yes
No
D
MAIN DC BUS FAULT (below) . . . . . . accomplish
-- END --
D
Bus Fault Reset . . . . . . . . . . . . . . . . . . . . . . . . Reset
-- -- -- -- -- -- -- -- -- -- END -- -- -- -- -- -- -- -- -- --
MAIN DC BUS FAULT
“DC BUS” Caution Light
Left Main DC Bus Fault:
(“DC BUS”, “#1 DC GEN”, “STBY BATTERY” and “AUX
BATTERY” Caution Lights):
D Aux & Stby Batteries . . . . . . . . . . . . . . . . . . . . . . . . . Off
D DC Gen 1 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Off
D Bus Fault Reset . . . . . . . . . . . . . . . . . . . . . . . . . . . Reset
--- Leave selected switches in the OFF position.
DC BUS Caution Light remains illuminated:
Yes
Note:
Automatic cabin pressure control is lost.
The FAULT advisory light on the
pressurization control panel will be
illuminated.
D Auto / Man / Dump . . . . . . . . . . . . . . . . . . . . . . Man
D Man Diff . . . . . . . . . . . as req’d (5.46 psi diff max)
--- Use Cabin Altitude / Differential placard to achieve
appropriate cabin altitude in climb, cruise and
descent.
--- Land at nearest suitable airport.
--- Refer to LOSS OF MAIN DC BUS POWER (Page
9.4) for a list of lost services.
Prior to landing:
D Bleed Air 1 and 2 . . . . . . . . . . . . . . . . . . . . . Min / Off
-- END -No
--- Monitor DC Bus volts and Generator loads for
normal indications.
-- END --
CONTINUED ON NEXT PAGE
MS 4-- 113581 or IS4Q2150011 ONLY
MAY 19/18
APR
15/05
PSM 1---84---1B
Page 9.5
Right Main DC Bus Fault:
(“DC BUS”, “#2 DC GEN”, and “MAIN BATTERY”
Caution Lights)
D Main Battery . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Off
D DC Gen 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Off
D Bus Fault Reset . . . . . . . . . . . . . . . . . . . . . . . . . . . Reset
--- Leave selected switches in the OFF position.
DC BUS Caution Light remains illuminated:
Yes
--- Land at nearest suitable airport.
--- Refer to LOSS OF MAIN DC BUS POWER (Page
9.4) for a list of lost services.
Landing Considerations:
--- Anti-Skid will be inoperative. For maximum
deceleration, use intermittent 1 second pedal brake
applications with intervals of reduced braking as
brief as possible.
Caution: Excessive application of pedal brakes can
result in skidding and tire failure.
Landing Distance Factor:
REF SPEED
INCR ON
Flap 10 . . . . . . . . . . . . . . . . . .
Flap 15 . . . . . . . . . . . . . . . . . .
Flap 35 . . . . . . . . . . . . . . . . . .
1.70
1.70
1.70
2.1
2.1
2.0
-- END -No
--- Monitor DC Bus volts and Generator loads for
normal indications.
-- -- -- -- -- -- -- -- -- -- END -- -- -- -- -- -- -- -- -- --
MS 4-- 113581 or IS4Q2150011 ONLY
Page 9.6
PSM 1---84---1B
MAY
APR 15/05
19/18
LOSS OF AC BUS POWER
Lost Services:
L AC BUS
R AC BUS
Stick Pusher System
L Aux Fuel Pump
L Prop Deicing
L Alpha Vane Heater
L TRU
L Ice Detection Sensor
Pilot Windshield Heat
(Norm & Warmup)
L Engine Intake Heater
L Pitot Static Heater
Stick Pusher System
R Aux Fuel Pump
R Prop Deicing
R Alpha Vane Heater
R TRU
R Ice Detection Sensor
Standby Hydraulic Pump
Co-pilot Windshield Heat
(Norm)
Pilot Side Window Heat
R Engine Intake Heater
R Pitot Static Heater
“L AC BUS” or “R AC BUS”
(Caution Light)
D
D
-----------
Stick Pusher Shutoff . . . . . . . . . . . . . . . . . . . . press Off
Airspeed . . . . . . . . . . . . . . . . . . . . . . . . . . . . . VREF (min)
Maintain airspeed appropriate for icing conditions and
other failures if applicable.
Fuel transfer from the tank associated with the affected
fuel aux pump is unavailable.
Affected windshield will not be de-misted or anti-iced.
Avoid icing conditions.
Refer to LOSS OF AC BUS POWER (Page 9.7) for a list
of lost services.
IF there are abnormal indications of airspeed or altitude
on the pilot’s or co-pilot’s PFD:
D EFIS ADC Source . . . . . . . . . . . . . . . . 1 or 2 (as req’d)
IF icing conditions are encountered:
D Condition levers . . . . . . . . . . . . . . . . . . . . . . . . . . . . Max
--- Affected propeller and engine intake will not be
anti-iced.
--- Monitor affected engine performance.
--- Exit icing conditions as soon as possible.
MAY 09/15
JUN
15/05
PSM 1---84---1B
Page 9.7
LOSS OF GENERATED POWER
“#1 DC GEN” and “#2 DC GEN”
and either
“#1 AC GEN”
“L TRU”
or
and
and/or
“#2 AC GEN”
“R TRU”
(Caution Lights)
(Loss of BOTH DC Generators and BOTH AC Generators
or loss of BOTH DC Generators and ONE or BOTH TRUs)
D
DC, AC Gens (affected) . . . Off then on (individually)
IF Caution Lights remain on:
D DC, AC Gens (affected) . . . . . . . . . . . . . . . . . . . . . . Off
D Storm/Dome Lights . . . . . . . . . . . . . . . . Storm (if req’d)
D Main, Aux & Stby Batteries . . . . . . . . . . . . . . . . . . . Off
D Emergency Lights . . . . . . . . . On then Off (until req’d)
--- Land immediately at nearest suitable airport.
Caution: Battery duration for operation of essential
services is 60 minutes (45 minutes JAA).
Note:
---
ECS pack air flow is lost and cabin will
depressurize.
Descend to below 14,000 ft as soon as possible.
When below 14,000 ft, ventilate cabin:
D Auto / Man / Dump . . . . . . . . . . . . . . . . . . . . . . . . . . Man
D Man Diff . . . . . . . . . . . . . . . . . . . . . . . . . . . Incr (50 secs)
D Cabin Alt Fwd Outflow . . . . . . . fully clockwise (Opn)
D Fwd Outflow Valve . . . . . . . . . . . . . . . . . . . . . . . . . Open
Note:
Ram ventilation is most effective above 150 KIAS.
Landing Considerations:
--- Anti-Skid will be inoperative. For maximum
deceleration, use intermittent 1 second pedal brake
applications with intervals of reduced braking as brief
as possible.
Caution: Excessive application of pedal brakes can result
in skidding and tire failure.
Landing Distance Factor:
REF SPEED
INCR ON
Flap 10 . . . . . . . . . . . . . . . . . .
Flap 15 . . . . . . . . . . . . . . . . . .
Flap 35 . . . . . . . . . . . . . . . . . .
Page 9.8
1.70
1.70
1.70
PSM 1---84---1B
2.1
2.1
2.0
MAY
APR 15/05
19/18
“#1 DC GEN” and “#2 DC GEN”
and
“#1 AC GEN” or “#2 AC GEN”
(Caution Lights)
(Loss of BOTH DC Generators and ONE AC Generator)
D Gens (affected) . . . . . . . . . . Off then on (individually)
IF Caution Lights remain on:
D Gens (affected) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Off
--- AC Gen (operative) . . . . . . . . . . . . . . . . . . monitor load
--- Land immediately at nearest suitable airport.
“#1 DC GEN” and “#2 DC GEN”
(Caution Lights)
(Loss of BOTH DC Generators)
D
DC Gen 1 and 2 . . . . . . . . . . Off then on (individually)
IF both Caution Lights remain on:
D DC Gen 1 and 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Off
--- L TRU and R TRU . . . . . . . . . . . . . . . . . . . monitor load
“#1 DC GEN” or “#2 DC GEN”
and
“L TRU” and “R TRU”
(Caution Lights)
(Loss of ONE DC Generator and BOTH TRUs)
Note:
---
All secondary bus services are inoperative.
Land at nearest suitable airport.
“#1 DC GEN” or “#2 DC GEN”
(Caution Light)
(Loss of ONE DC Generator)
D
Gen switch (affected) . . . . . . . . . . . . . . . . . Off then on
Caution Light remains on:
Yes
D
Gen switch (affected) . . . . . . . . . . . . . . . . . . . . . Off
-- END --
No
--- Monitor affected DC Bus volts and Generator load
for normal indications.
-- -- -- -- -- -- -- -- -- -- END -- -- -- -- -- -- -- -- -- --
MAY 19/18
APR
15/05
PSM 1---84---1B
Page 9.9
“#1 DC GEN HOT” or
“#2 DC GEN HOT”
(Caution Light)
(Overheat of ONE DC Generator)
D
Gen switch (affected) . . . . . . . . . . . . . . . . . . . . . . . . Off
Note:
Continued operation of the associated engine is
permissible for the remainder of the flight.
The affected GEN HOT light may remain
illuminated for the remainder of the flight.
“#1 AC GEN” and “#2 AC GEN”
(Caution Light)
(Loss of both AC Generator with Propeller De-Ice
selected ON)
Note:
D
D
D
The PROP DEICE caution light may also be
illuminated.
Prop selector . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Off
Condition levers . . . . . . . . . . . . . . . . . . . . . . . . . . . . Max
AC Gen 1 and AC Gen 2
switches . . . . . . . . . . . . . . . . . . Off then on individually
IF Caution Light remains on:
D AC Gen switch (affected) . . . . . . . . . . . . . . . . . . . . . Off
--- Exit icing conditions as soon as possible.
“#1 AC GEN” or “#2 AC GEN”
(Caution Light)
(Loss of ONE AC Generator)
D
Gen switch (affected) . . . . . . . . . . . . . . . . . Off then on
Caution Light remains on:
Yes
D
Gen switch (affected) . . . . . . . . . . . . . . . . . . . . . Off
-- END --
No
--- Monitor affected AC Generator volts and load for
normal indications.
-- -- -- -- -- -- -- -- -- -- END -- -- -- -- -- -- -- -- -- -Page 9.10
PSM 1---84---1B
MAY
APR 15/05
19/18
“#1 AC GEN HOT” or
“#2 AC GEN HOT”
(Caution Light)
(Overheat of ONE AC Generator)
D
Gen switch (affected) . . . . . . . . . . . . . . . . . . . . . . . . Off
Note:
Continued operation of the associated engine is
permissible for the remainder of the flight.
The affected GEN HOT light may remain
illuminated for the remainder of the flight.
“L TRU” or
“R TRU” or
“L TRU HOT” or
“R TRU HOT”
(Caution Light)
(Loss or overheat of ONE TRU)
D
L TRU or R TRU cb (Right Upper cb panel) . . . . . pull
MAY 09/15
JUN
15/05
PSM 1---84---1B
Page 9.11
“MAIN BATTERY” or
“AUX BATTERY” or
“STBY BATTERY”
(Caution Light)
D
Battery (affected) . . . . . . . . . . . . . . . . . . . . . Off then on
Caution Light remains on:
Yes
Battery (affected) . . . . . . . . . . . . . . . . . . . . . . . . . Off
D
-- END -No
--- Monitor affected Battery load and DC Bus volts for
normal indications.
-- -- -- -- -- -- -- -- -- -- END -- -- -- -- -- -- -- -- -- --
“MAIN BAT HOT” or
“AUX BAT HOT” or
“STBY BAT HOT”
(Warning Light)
--D
Electrical Page . . . . . . . . . . . . . . . . . . confirm overheat
Battery (affected) . . . . . . . . . . . . . . . . . . . . . . . . . . . . Off
Battery temperature continues to rise:
Yes
--- Land immediately at the nearest suitable airport.
-- END -No
--- Continue to monitor affected Battery temperature.
-- -- -- -- -- -- -- -- -- -- END -- -- -- -- -- -- -- -- -- --
“EMER LTS DISARMED”
(Caution Light)
D
Emergency Lights . . . . . . . . . . . . . . . . . . . . . . . . . . Arm
Page 9.12
PSM 1---84---1B
MAY
APR 15/05
19/18
FLIGHT CONTROLS
ROLL CONTROL JAM . . . . . . . . . . . . . . . . . . . . . . . 10.3
ROLL CONTROL MALFUNCTION . . . . . . . . . . . . 10.4
AILERON TRIM RUNAWAY . . . . . . . . . . . . . . . . . . . 10.5
“ROLL SPLR INBD HYD” and
“ROLL SPLR OUTBD HYD”
(Caution Lights) . . . . . . . . . . . . . . . . . . . . . . . . . . . . 10.5
“ROLL SPLR INBD HYD” or
“ROLL SPLR OUTBD HYD”
(Caution Light) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 10.6
“ROLL SPLR INBD GND” or
“ROLL SPLR OUTBD GND”
(Caution Light) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 10.6
“SPLR OUTBD” (Caution Light) . . . . . . . . . . . . . . 10.6
PITCH CONTROL JAM . . . . . . . . . . . . . . . . . . . . . . 10.7
“ELEVATOR FEEL” and “PITCH TRIM” and
“SPLR OUTBD” and “RUD CTRL”
(Caution Lights) . . . . . . . . . . . . . . . . . . . . . . . . . . . . 10.8
“ELEVATOR ASYMMETRY” (Caution Light) . . . 10.8
“ELEVATOR PRESS” (Caution Light) . . . . . . . . . 10.8
“ELEVATOR FEEL” (Caution Light) . . . . . . . . . . . 10.8
“PITCH TRIM” (Caution Light) . . . . . . . . . . . . . . . 10.9
ELEVATOR TRIM SWITCH FAILURE . . . . . . . . . 10.10
ELEVATOR TRIM INDICATOR FAILURE . . . . . . 10.10
ABNORMAL FLAP LANDING . . . . . . . . . . . . . . . 10.11
“FLAP DRIVE” (Caution Light) . . . . . . . . . . . . . . 10.12
“FLAP POWER” (Caution Light) . . . . . . . . . . . . 10.12
RUDDER JAM . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 10.13
“RUD 1 PUSH OFF” or “RUD 2 PUSH OFF”
(Switchlight On) . . . . . . . . . . . . . . . . . . . . . . . . . . . 10.13
“#1 RUD HYD” or “#2 RUD HYD”
(Caution Light) . . . . . . . . . . . . . . . . . . . . . . . . . . . . 10.14
“RUD CTRL” (Caution Light) . . . . . . . . . . . . . . . . 10.14
RUDDER TRIM ACTUATOR RUNAWAY . . . . . . . 10.14
MAY 19/18
APR
15/05
PSM 1---84---1B
Page 10.1
THIS PAGE INTENTIONALLY LEFT BLANK
Page 10.2
PSM 1---84---1B
MAY 15/05
PITCH CONTROL JAM
Autopilot . . . . . . . . . . . . . . . . . . . . . . . . . . . disengage
Flap and Airspeed . . . . . . . maintain at time of jam
Control Columns . . . . . . . . . . . both pilots attempt
to overcome jam
D
D
D
IF unable to overcome jam:
D Relax control column force.
D Pitch Disc Handle . . . . . . . . . . . . . pull and turn 90_
D Control Columns . . . . . . . . . . . both pilots attempt
pitch control
--- Pilot with free control column will fly the aircraft.
Caution: With the PITCH disconnect handle pulled, the
autopilot must not be engaged.
Note:
Elevator forces will be lighter than normal and
pitch control degraded.
IF jam occurs below 170 KIAS:
D Airspeed . . . . . . . . . . . . . . . . . . . . . . . . 170 KIAS (max)
IF jam occurs above 170 KIAS:
D Airspeed . . . . . . . . . . . . airspeed at time of jam (max)
Landing Considerations:
--- Land using Flap 10 or 15 at an airport with minimum
crosswind and turbulence.
---
Approach & VREF speeds
REF SPEED
INCR ON
Flap 10 . . . . . . . . . . . . . . . . . .
Flap 15 . . . . . . . . . . . . . . . . . .
VREF
VREF
VREF + 20
VREF + 20
Landing Distance Factor:
REF SPEED
INCR ON
Flap 10 . . . . . . . . . . . . . . . . . .
Flap 15 . . . . . . . . . . . . . . . . . .
MAY 09/15
JUN
15/05
1.35
1.35
PSM 1---84---1B
1.69
1.69
Page 10.7
“ELEVATOR FEEL” and
“PITCH TRIM” and
“SPLR OUTBD” and
“RUD CTRL”
(Caution Lights)
D
D
Autopilot . . . . . . . . . . . . . . . . . . . . . . . . . . . . . disengage
Airspeed . . . . . . . . . . . . . . . . . . . . . . . . 200 KIAS (max)
“ELEVATOR ASYMMETRY”
(Caution Light)
D
D
Autopilot . . . . . . . . . . . . . . . . . . . . . . . . . . . . . disengage
Airspeed . . . . . . . . . . . . . . . . . . . . . . . . 200 KIAS (max)
“ELEVATOR PRESS”
(Caution Light)
---
Hyd Press #3 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . check
IF pressure is indicated:
D Hyd #3 Isol Vlv . . . . . . . . . . . . . . . . . . . . . . . . . . . norm
IF Caution Light remains illuminated:
--- Maintenance action required prior to next flight.
“ELEVATOR FEEL”
(Caution Light)
D
D
Autopilot . . . . . . . . . . . . . . . . . . . . . . . . . . . . . disengage
Airspeed . . . . . . . . . . . . . . . . . . . . . . . . 200 KIAS (max)
Page 10.8
PSM 1---84---1B
MAY
APR 15/05
19/18
ABNORMAL FLAP LANDING
D
GPWS Flap Override . . . . . . . . . . . . . . . . . . . . . . . press
Flap failed between 0 and 10:
Landing Considerations:
--- Disengage autopilot at 1,000 ft AGL if flap less than 5.
--- To decrease the landing descent rate and not exceed a
pitch attitude of 6_, when the landing descent rate is
higher than desired, power will be required in the
landing flare through to touchdown.
--- To decrease the landing descent rate at airport altitudes
greater than 5,000 ft, it may be necessary to maintain
power in the landing flare through to touchdown.
--- Nosewheel should be promptly brought into contact
with the ground following main wheel contact.
--- High landing speeds may result in Brake Kinetic Energy
limits being exceeded.
--- If flap failed between gated positions, the smaller flap
angle must be used when calculating the landing
performance that follows.
--- Approach & VREF speeds
REF SPEED
INCR ON
Flap 0 . . . . . . . . . . . . .
Flap 5 . . . . . . . . . . . . .
1.23 VSR
1.23 VSR
1.23 VSR + 25
1.23 VSR + 20
Landing Distance Factor:
REF SPEED
INCR ON
Flap 0 (use Flap 35 chart)
Flap 5 (use Flap 35 chart)
2.0
2.0
2.5
2.5
Caution: Avoid pitch attitudes in excess of 6_ at
touchdown.
DO NOT select Power levers below Flight Idle
until indicated airspeed is below 150 kts.
-- END -Flap failed between 10, 15 or 35:
Landing Considerations:
--- The smaller flap angle must be used when calculating
landing performance.
-- -- -- -- -- -- -- -- -- -- END -- -- -- -- -- -- -- -- -- --
MAY 19/18
APR
15/05
PSM 1---84---1B
Page 10.11
“FLAP DRIVE”
(Caution Light)
(Flap Degraded Operation)
Flap movement stops:
Yes
--- Further operation of flap is not available and flap will
remain in the failed position.
D ABNORMAL FLAP LANDING
(Page 10.11) . . . . . . . . . . . . . . . . . . . . . accomplish
-- END -No
D Flap . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . as req’d
--- Flap may be operated normally to complete the
flight.
-- -- -- -- -- -- -- -- -- -- END -- -- -- -- -- -- -- -- -- --
“FLAP POWER”
(Caution Light)
(Flap System Failure)
D
Flap . . . . . . . . . . . . . . . select to match flap indication
Note:
D
Ensure the Flaps lever release trigger is fully
engaged in the appropriate flap gate.
FLAPS CONT cb (Left Lower cb panel --- L7) . . . . pull
Wait 2 seconds minimum:
D FLAPS CONT cb (Left Lower cb panel --- L7) push in
Note:
Flaps Cont CB is limited to one reset.
Caution Light remains on:
Yes
--- Operation of flap is not available and flap will remain
in last selected position.
D ABNORMAL FLAP LANDING
(Page 10.11) . . . . . . . . . . . . . . . . . . . . . accomplish
-- END -No
Wait 20 seconds following reset of the Flaps Cont CB:
D Flap . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . as req’d
-- -- -- -- -- -- -- -- -- -- END -- -- -- -- -- -- -- -- -- --
Page 10.12
PSM 1---84---1B
MAY
APR 15/05
19/18
RUDDER JAM
(Restricted Rudder Pedal Movement)
Warning: Should the rudder pedal (rudder jam) suddenly
break free, do not apply rudder pedal input in
the opposite direction.
D
Affected rudder pedal . . apply normal push force
Rudder pedal moves as required:
D Affected rudder pedal . . . . reduce push force and
allow rudder to centre
-- END -Rudder pedal does not respond to normal push force
(rudder remains jammed or rudder jam reoccurs):
--- Use roll control as required for directional control.
IF rudder jam occurs on take-off and conditions permit:
--- Return for landing on the take-off runway.
D Nosewheel Steering . . . . . . . . . . . . . . . . . . . . . . . . . Off
Landing Considerations:
--- Land at an airport with no known or forecast icing
conditions and with minimum crosswind and
turbulence, using Flap 10, 15 or 35.
--- Small amounts of asymmetric power may be used to
maintain directional control on approach.
After touchdown:
--- Use asymmetric braking and power, as required, to
maintain directional control.
Landing Distance Factor:
REF SPEED
INCR ON
Flap 10 . . . . . . . . . . . . . . . . . .
Flap 15 . . . . . . . . . . . . . . . . . .
Flap 35 . . . . . . . . . . . . . . . . . .
1.40
1.40
1.50
N/A
N/A
N/A
After Landing:
D Nosewheel Steering . . . . . . . . . . . . . . . . . . . . . . . . . . on
-- -- -- -- -- -- -- -- -- -- END -- -- -- -- -- -- -- -- -- --
“RUD 1 PUSH OFF” or
“RUD 2 PUSH OFF”
(Switchlight On)
D
Illuminated switchlight . . . . . . . . . . . . . . . . press Off
MAY 19/18
APR
15/05
PSM 1---84---1B
Page 10.13
“#1 RUD HYD” or
“#2 RUD HYD”
(Caution Light)
---
Maintenance action required prior to next flight.
“RUD CTRL”
(Caution Light)
Airspeed . . . . . . . . . . . . . . . . . . . . . . . . 200 KIAS (max)
D
Landing Considerations:
--- Maximum crosswind for landing is 20 kt.
RUDDER TRIM ACTUATOR RUNAWAY
D
Rudder Trim . . . . . . . . . . . . . . . opposite to runaway
WHEN trim is at the neutral position or if the trim actuator
cannot be reversed:
D RUD TRIM ACT cb (Left Lower cb panel --- F7) . . pull
Page 10.14
PSM 1---84---1B
MAY
APR 15/05
19/18
Fuel Transfer
MAY 15/05
OCT
31/10
PSM 1---84---1B
Page 11.3
“#1 TANK FUEL LOW” or
“#2 TANK FUEL LOW”
(Caution Light)
--- Fuel Quantity . . . . . . . . . . . . . . . . . . . . . . . . . . . . . check
Fuel 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
D
No
No
ENGINE FAILURE / FIRE / SHUTDOWN
(Page 5.16) . . . . . . . . . . . . . . . . . . . accomplish
-- END --
D Transfer fuel from unaffected tank.
--- Monitor fuel quantity.
-- END --
--- Maintain level attitude as much as possible.
D Tank Aux Pump (affected engine) . . . . . . . . . . On
--- Monitor fuel quantity.
IF “ENG FUEL PRESS” Caution Light illuminates:
D ENGINE FAILURE / FIRE / SHUTDOWN
(Page 5.16) . . . . . . . . . . . . . . . . . . . . . . . accomplish
-- -- -- -- -- -- -- -- -- -- END -- -- -- -- -- -- -- -- -- --
“#1 ENG FUEL PRESS” or
“#2 ENG FUEL PRESS”
(Caution Light)
D Tank Aux Pump (affected side) . . . . . . . . . . . . . . . . On
Caution Light remains on:
Yes
D Tank Aux Pump (affected side) . . . . . . . . . . . . . . off
--- Check for external leaks and for fuel odour within
the airplane.
IF either is confirmed:
D ENGINE FAILURE / FIRE / SHUTDOWN
(Page 5.16) . . . . . . . . . . . . . . . . . . . . . . . accomplish
-- END -No
--- Monitor affected fuel flow and quantity for normal
indications.
-- -- -- -- -- -- -- -- -- -- END -- -- -- -- -- -- -- -- -- --
Page 11.4
PSM 1---84---1B
MAY
APR 15/05
19/18
ABNORMAL FUEL TEMPERATURE
(Below 0_ C or Above 71_ C)
(Fuel Inlet Temperature indication on ED above or below
normal operating range)
D
---
Tank Aux Pump (affected side) . . . . . . . . . . . . . . . . On
Monitor affected engine performance.
Note:
Intermittent operation above or below normal
operating range must be reported to
maintenance prior to next flight.
ABNORMAL FUEL TANK TEMPERATURE
(Fuel Tank Temperature indication on Fuel Page colder
than allowable minimum fuel temperature)
---
Fuel tank temperature . . . . . . . . . . . . . . . . . . . . monitor
Where conditions permit:
--- Maneuver to a warmer air mass.
D Power . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . increase
FUEL TRANSFER FAILURE
Tank Aux Pump Fails to Automatically Activate:
IF Tank Aux Pump Advisory Light Fails to illuminate:
D Tank Aux Pump (appropriate side) . . . . . . . . . . . . . On
When transfer is complete:
D Tank Aux Pump (appropriate side) . . . . . . . . . . . . . . off
D Fuel Transfer . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . off
-- END -One or Both Fuel Transfer Valves Fail(s) to Open:
D
---
Fuel Transfer . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . off
Consider the effects of maximum lateral fuel
asymmetry or fuel low level.
-- -- -- -- -- -- -- -- -- -- END -- -- -- -- -- -- -- -- -- --
MAY 19/18
APR
15/05
PSM 1---84---1B
Page 11.5
“#1 FUEL FLTR BYPASS” or
“#2 FUEL FLTR BYPASS”
(Caution Light)
-----
Monitor fuel flow, ITT, and NH. If erratic, may indicate
contamination has passed filter.
Maintenance action required prior to next flight.
“FUELING ON”
(Caution Light)
(Refuel / Defuel Door open)
---
This is a normal indication during fueling operations.
Page 11.6
PSM 1---84---1B
MAY
FEB 23/16
15/05
No. 1 and No. 2 HYDRAULIC SYSTEMS
FAILURE
(No Pressure indicated in the No. 1 and No. 2 Hydraulic
Systems)
D Autopilot . . . . . . . . . . . . . . . . . . . . . . . . . . . . . disengage
D Yaw Damper . . . . . . . . . . . . . . . . . . . . . . . . . . disengage
D Airspeed . . . . . . . . . . . . . . . . . . . . . . . . 200 KIAS (max)
--- Use aileron, elevator and, if required for directional
control, small inputs of asymmetric power, to control
the aircraft.
IF Flap at 0 or 5:
D GPWS Flap Override . . . . . . . . . . . . . . . . . . . . . . . press
Lost Services:
--- All hydraulically-powered services except elevator.
Landing Considerations:
--- Land immediately at the nearest suitable airport with
minimum crosswind and turbulence.
--- Align aircraft with runway using asymmetric power prior
to lowering the nosewheel to the runway.
--- Nosewheel steering will be inoperative. To maintain
directional control, significant asymmetric power will be
required.
--- Use Emergency Brake to stop aircraft, approximately 6
brake applications available. Use intermittent 1 second
Emergency Brake applications with intervals of
reduced braking as brief as possible.
--- Use of maximum reverse power for stopping may
cause directional deviation.
--- Approach & VREF speeds
REF SPEED
INCR ON
Flap 0 . . . . . . . . . .
Flap 5 . . . . . . . . . .
Flap 10/15 . . . . . .
Flap 35 . . . . . . . . .
1.23 VSR + 10
1.23 VSR + 10
VREF + 10
VREF + 10
1.23 VSR + 25
1.23 VSR + 20
VREF + 20
VREF + 25
Landing Distance Factor:
REF SPEED
INCR ON
Flap 0/5 (use Flap 35 chart) . . . 2.65
Flap 10/15 . . . . . . . . . . . . . . . . . . 1.85
Flap 35 . . . . . . . . . . . . . . . . . . . . . 1.85
2.90
2.10
2.20
Prior to landing:
D ALTERNATE LANDING GEAR EXTENSION
(Page 14.3) . . . . . . . . . . . . accomplish when required
Caution: Avoid pitch attitudes in excess of 6_ at
touchdown.
Unless required for immediate directional
control, DO NOT select Power levers below
Flight Idle until airspeed is below 150 KIAS.
Excessive application of emergency braking can
result in skidding and tire failure.
MAY 19/18
APR
15/05
PSM 1---84---1B
Page 12.5
No. 1 HYDRAULIC SYSTEM FAILURE
LOSS of ALL FLUID from
No. 1 HYDRAULIC SYSTEM
(“#1 ENG HYD PUMP” and “#1 HYD ISO VLV” Caution
Lights, and ENGINE 1 HYD valve CLOSED Advisory Light
and no Quantity indicated on No. 1 HYD QTY
Note:
“#1 HYD ISO VLV” Caution Light may go out with
very low hydraulic fluid quantity in the No. 1
Hydraulic system.)
D
D
D
HYD #3 Isol Vlv . . . . . . . . . . . . . . . . . . . . . . . . . . . Open
Stby Hyd Press . . . . . . . . . . . . . . . . . . . . . . . . . . . norm
PTU Cntrl . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . norm
IF Flap failed between 0 and 10:
D GPWS Flap Override . . . . . . . . . . . . . . . . . . . . . . . press
Lost Services:
Flap
Normal / Anti-Skid Brakes
Inbd Roll Spoiler / Elevator No. 1 / Rudder No. 1 System
Landing Considerations:
--- Disengage autopilot at 1,000 ft AGL if flap less than 5.
--- Use Emergency Brake to stop aircraft, unlimited brake
applications available. Use intermittent 1 second
Emergency Brake applications with intervals of
reduced braking as brief as possible.
--- Approach & VREF speeds:
REF SPEED
INCR ON
Flap 0 . . . . . . . . . . 1.23 VSR + 10
Flap 5 . . . . . . . . . . 1.23 VSR + 10
Flap 10 . . . . . . . . .
VREF + 10
Flap 15 . . . . . . . . .
VREF + 10
Flap 35 . . . . . . . . .
VREF + 10
Landing Distance Factor:
1.23 VSR + 25
1.23 VSR + 20
VREF + 20
VREF + 20
VREF + 25
REF SPEED
INCR ON
Flap 0 (use Flap 35 chart) . .
Flap 5 (use Flap 35 chart) . .
Flap 10 . . . . . . . . . . . . . . . . . .
Flap 15 . . . . . . . . . . . . . . . . . .
Flap 35 . . . . . . . . . . . . . . . . . .
2.65
2.65
1.85
1.85
1.85
2.90
2.90
2.10
2.10
2.20
Caution: Avoid pitch attitudes in excess of 6_ at
touchdown.
DO NOT select Power levers below Flight Idle
until airspeed is below 150 KIAS.
Excessive application of emergency braking can
result in skidding and tire failure.
Page 12.6
PSM 1---84---1B
MAY
APR 15/05
19/18
“#1 ENG HYD PUMP”
(Caution Light)
(No Pressure may be Indicated in the No. 1 Hydraulic
System)
D
D
---
Stby Hyd Press . . . . . . . . . . . . . . . . . . . . . . . . . . . . . On
PTU Cntrl . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . norm
Monitor pressure and quantity in No. 1 Hydraulic
system for normal indications.
Note:
Hydraulic pressure will be indicated in the No.3
system and the “#1 HYD ISO VLV” Caution Light
may be illuminated until normal pressure is
restored in the No. 1 Hydraulic system.
Landing Considerations:
--- Flap extension and retraction is slower than normal.
Caution: With #1 ENG HYD PUMP caution light
illuminated, DO NOT select PTU CNTRL switch
on.
“#1 HYD ISO VLV”
(Caution Light)
(Partial Loss of Fluid from the No. 1 Hydraulic System)
---
Monitor quantity in No. 1 Hydraulic system for further
loss of fluid.
Lost Services:
Normal / Anti-Skid Brakes
Inboard Roll Spoilers
Landing Considerations:
--- Use Emergency Brake to stop aircraft, unlimited brake
applications available. Use intermittent 1 second
Emergency Brake applications with intervals of
reduced braking as brief as possible.
--- Approach & VREF speeds:
REF SPEED
INCR ON
Flap 10 . . . . . . . . . . . . . . . VREF + 10
Flap 15 . . . . . . . . . . . . . . . VREF + 10
Flap 35 . . . . . . . . . . . . . . . VREF + 10
Landing Distance Factor:
Flap 10 . . . . . . . . . . . . . . . . . .
Flap 15 . . . . . . . . . . . . . . . . . .
Flap 35 . . . . . . . . . . . . . . . . . .
VREF + 20
VREF + 20
VREF + 25
REF SPEED
INCR ON
1.85
1.85
1.85
2.10
2.10
2.20
Caution: Excessive application of emergency braking can
result in skidding and tire failure.
MAY 19/18
APR
15/05
PSM 1---84---1B
Page 12.7
No. 2 HYDRAULIC SYSTEM FAILURE
LOSS of ALL FLUID from
No. 2 HYDRAULIC SYSTEM
(“#2 ENG HYD PUMP” and “#2 HYD ISO VLV” Caution
Lights, and ENGINE 2 HYD valve CLOSED Advisory Light
and no Quantity indicated on No. 2 HYD QTY
Note:
“#2 HYD ISO VLV” Caution Light may go out with
very low hydraulic fluid quantity in the No. 2
Hydraulic system.)
D
D
D
D
HYD #3 Isol Vlv . . . . . . . . . . . . . . . . . . . . . . . . . . . Open
PTU Cntrl . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . norm
HYD PWR XFER cb
(Right Lower cb panel --- L8) . . . . . . . . . . . . . . . . . . pull
Stby Hyd Press . . . . . . . . . . . . . . . . . . . . . . . . . . . . . On
Lost Services:
Normal Gear Extension and Retraction
Nosewheel Steering
Emerg Brakes (when Park Brake pressure depleted)
OutbdRollSpoiler/ ElevatorNo. 2/ RudderNo. 2System
Landing Considerations:
--- Use asymmetric braking and power, as required, to
maintain directional control after touchdown.
--- Approach & VREF speeds:
REF SPEED
INCR ON
Flap 10 . . . . . . . . . . . . . . . VREF + 10
Flap 15 . . . . . . . . . . . . . . . VREF + 10
Flap 35 . . . . . . . . . . . . . . . VREF + 10
Landing Distance Factor:
Flap 10 . . . . . . . . . . . . . . . . . .
Flap 15 . . . . . . . . . . . . . . . . . .
Flap 35 . . . . . . . . . . . . . . . . . .
VREF + 20
VREF + 20
VREF + 25
REF SPEED
INCR ON
1.85
1.85
1.85
2.10
2.10
2.20
Prior to landing:
D ALTERNATE LANDING GEAR EXTENSION
(Page 14.3) . . . . . . . . . . . . accomplish when required
Page 12.8
PSM 1---84---1B
MAY
APR 15/05
19/18
“#1 ENG HYD PUMP”
(Caution Light)
(No Pressure may be Indicated in the No. 1 Hydraulic
System)
D
D
---
Stby Hyd Press . . . . . . . . . . . . . . . . . . . . . . . . . . . . . On
PTU Cntrl . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . norm
Monitor pressure and quantity in No. 1 Hydraulic
system for normal indications.
Note:
Hydraulic pressure will be indicated in the No.3
system and the “#1 HYD ISO VLV” Caution Light
may be illuminated until normal pressure is
restored in the No. 1 Hydraulic system.
Landing Considerations:
--- Flap extension and retraction is slower than normal.
Caution: With #1 ENG HYD PUMP caution light
illuminated, DO NOT select PTU CNTRL switch
on.
“#1 HYD ISO VLV”
(Caution Light)
(Partial Loss of Fluid from the No. 1 Hydraulic System)
---
Monitor quantity in No. 1 Hydraulic system for further
loss of fluid.
Lost Services:
Normal / Anti-Skid Brakes
Inboard Roll Spoilers
Landing Considerations:
--- Use Emergency Brake to stop aircraft, unlimited brake
applications available. Use intermittent 1 second
Emergency Brake applications with intervals of
reduced braking as brief as possible.
--- Approach & VREF speeds:
REF SPEED
INCR ON
Flap 10 . . . . . . . . . . . . . . . VREF + 10
Flap 15 . . . . . . . . . . . . . . . VREF + 10
Flap 35 . . . . . . . . . . . . . . . VREF + 10
Landing Distance Factor:
Flap 10 . . . . . . . . . . . . . . . . . .
Flap 15 . . . . . . . . . . . . . . . . . .
Flap 35 . . . . . . . . . . . . . . . . . .
VREF + 20
VREF + 20
VREF + 25
REF SPEED
INCR ON
1.85
1.85
1.85
2.10
2.10
2.20
Caution: Excessive application of emergency braking can
result in skidding and tire failure.
MAY 19/18
APR
15/05
PSM 1---84---1B
Page 12.7
No. 2 HYDRAULIC SYSTEM FAILURE
LOSS of ALL FLUID from
No. 2 HYDRAULIC SYSTEM
(“#2 ENG HYD PUMP” and “#2 HYD ISO VLV” Caution
Lights, and ENGINE 2 HYD valve CLOSED Advisory Light
and no Quantity indicated on No. 2 HYD QTY
Note:
“#2 HYD ISO VLV” Caution Light may go out with
very low hydraulic fluid quantity in the No. 2
Hydraulic system.)
D
D
HYD #3 Isol Vlv . . . . . . . . . . . . . . . . . . . . . . . . . . . Open
PTU Cntrl . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . norm
Lost Services:
Normal Gear Extension and Retraction
Nosewheel Steering
Emerg Brakes (when Park Brake pressure depleted)
OutbdRollSpoiler/ ElevatorNo. 2/ RudderNo. 2System
Landing Considerations:
--- Use asymmetric braking and power, as required, to
maintain directional control after touchdown.
--- Approach & VREF speeds:
REF SPEED
INCR ON
Flap 10 . . . . . . . . . . . . . . . VREF + 10
Flap 15 . . . . . . . . . . . . . . . VREF + 10
Flap 35 . . . . . . . . . . . . . . . VREF + 10
Landing Distance Factor:
Flap 10 . . . . . . . . . . . . . . . . . .
Flap 15 . . . . . . . . . . . . . . . . . .
Flap 35 . . . . . . . . . . . . . . . . . .
VREF + 20
VREF + 20
VREF + 25
REF SPEED
INCR ON
1.85
1.85
1.85
2.10
2.10
2.20
Prior to landing:
D ALTERNATE LANDING GEAR EXTENSION
(Page 14.3) . . . . . . . . . . . . accomplish when required
MS 4-- 126354 and (MS 4-- 901472 or MS 4-- 901473) ONLY
Page 12.8
PSM 1---84---1B
MAY
APR 15/05
19/18
“#2 ENG HYD PUMP”
(Caution Light)
(No Pressure may be Indicated in the No. 2 Hydraulic
System)
D
---
PTU Cntrl . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . On
Monitor pressure and quantity in No. 2 Hydraulic
system for normal indications.
Note:
Hydraulic pressure will be indicated in the No.3
system and the “#2 HYD ISO VLV” Caution Light
may be illuminated until normal pressure is
restored in the No. 2 Hydraulic system.
“#2 HYD ISO VLV”
(Caution Light)
(Partial Loss of Fluid from the No. 2 Hydraulic System)
D
D
---
PTU Cntrl . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . norm
HYD PWR XFER cb
(Right Lower cb panel --- L8) . . . . . . . . . . . . . . . . . . pull
Monitor quantity in No. 2 Hydraulic system for further
loss of fluid.
Lost Services:
Normal Gear Extension and Retraction
Nosewheel Steering
Emerg Brakes (when Park Brake pressure depleted)
Outboard Roll Spoilers
Landing Considerations:
--- Use asymmetric braking and power, as required, to
maintain directional control after touchdown.
--- Approach & VREF speeds:
REF SPEED
INCR ON
Flap 10 . . . . . . . . . . . . . . . VREF + 10
Flap 15 . . . . . . . . . . . . . . . VREF + 10
Flap 35 . . . . . . . . . . . . . . . VREF + 10
Landing Distance Factor:
Flap 10 . . . . . . . . . . . . . . . . . .
Flap 15 . . . . . . . . . . . . . . . . . .
Flap 35 . . . . . . . . . . . . . . . . . .
VREF + 20
VREF + 20
VREF + 25
REF SPEED
INCR ON
1.85
1.85
1.85
2.10
2.10
2.20
Prior to landing:
D ALTERNATE LANDING GEAR EXTENSION
(Page 14.3) . . . . . . . . . . . . accomplish when required
MAY 19/18
APR
15/05
PSM 1---84---1B
Page 12.9
PTU FAILURE
(Amber PTU CNTRL “FAIL” Advisory Light is illuminated)
D
PTU Cntrl . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . norm
Caution: PTU Cntrl must not be selected ON following
illumination of PTU Cntrl Fail advisory light.
“#1 HYD FLUID HOT“ or
“#2 HYD FLUID HOT”
(Caution Light)
---
Monitor pressure and quantity in affected Hydraulic
system for normal indications.
“#1 STBY HYD PUMP HOT”
(Caution Light)
Flap selector lever set at 0:
D
Stby Hyd Press . . . . . . . . . . . . . . . . . . . . . . . . . . . norm
-- END --
Flap selector lever set to greater than 0:
--- Monitor pressure in Stby Hydraulic system for normal
indications.
-- END --
“#3 HYD PUMP”
(Caution Light)
---
Maintenance action required prior to next flight.
Page 12.10
PSM 1---84---1B
MAY
APR 15/05
19/18
“#2 ENG HYD PUMP”
(Caution Light)
(No Pressure may be Indicated in the No. 2 Hydraulic
System)
D
---
PTU Cntrl . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . On
Monitor pressure and quantity in No. 2 Hydraulic
system for normal indications.
Note:
Hydraulic pressure will be indicated in the No.3
system and the “#2 HYD ISO VLV” Caution Light
may be illuminated until normal pressure is
restored in the No. 2 Hydraulic system.
“#2 HYD ISO VLV”
(Caution Light)
(Partial Loss of Fluid from the No. 2 Hydraulic System)
---
Monitor quantity in No. 2 Hydraulic system for further
loss of fluid.
Lost Services:
Normal Gear Extension and Retraction
Nosewheel Steering
Emerg Brakes (when Park Brake pressure depleted)
Outboard Roll Spoilers
Landing Considerations:
--- Use asymmetric braking and power, as required, to
maintain directional control after touchdown.
--- Approach & VREF speeds:
REF SPEED
INCR ON
Flap 10 . . . . . . . . . . . . . . . VREF + 10
Flap 15 . . . . . . . . . . . . . . . VREF + 10
Flap 35 . . . . . . . . . . . . . . . VREF + 10
Landing Distance Factor:
Flap 10 . . . . . . . . . . . . . . . . . .
Flap 15 . . . . . . . . . . . . . . . . . .
Flap 35 . . . . . . . . . . . . . . . . . .
VREF + 20
VREF + 20
VREF + 25
REF SPEED
INCR ON
1.85
1.85
1.85
2.10
2.10
2.20
Prior to landing:
D ALTERNATE LANDING GEAR EXTENSION
(Page 14.3) . . . . . . . . . . . . accomplish when required
MS 4-- 126354 and (MS 4-- 901472 or MS 4-- 901473) ONLY
MAY 19/18
APR
15/05
PSM 1---84---1B
Page 12.9
PTU FAILURE
(Amber PTU CNTRL “FAIL” Advisory Light is illuminated)
D
PTU Cntrl . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . norm
Caution: PTU Cntrl must not be selected ON following
illumination of PTU Cntrl Fail advisory light.
“#1 HYD FLUID HOT“ or
“#2 HYD FLUID HOT”
(Caution Light)
---
Monitor pressure and quantity in affected Hydraulic
system for normal indications.
“#1 STBY HYD PUMP HOT”
(Caution Light)
Flap selector lever set at 0:
D
Stby Hyd Press . . . . . . . . . . . . . . . . . . . . . . . . . . . norm
-- END --
Flap selector lever set to greater than 0:
--- Monitor pressure in Stby Hydraulic system for normal
indications.
-- END --
“#3 HYD PUMP”
(Caution Light)
---
Maintenance action required prior to next flight.
Page 12.10
PSM 1---84---1B
MAY
APR 15/05
19/18
ICE AND RAIN PROTECTION,
STALL PROTECTION
“DEICE PRESS” (Caution Light) . . . . . . . . . . . . . 13.3
ENGINE INTAKE BOOT FAILURE . . . . . . . . . . . . 13.4
“DEICE TIMER” (Caution Light) . . . . . . . . . . . . . 13.5
“PROP DEICE” (Caution Light) . . . . . . . . . . . . . . 13.5
“WSHLD HOT” (Caution Light) . . . . . . . . . . . . . . 13.6
“SIDE WDO HOT” (Caution Light) . . . . . . . . . . . 13.6
“WSHLD CTRL” (Caution Light) . . . . . . . . . . . . . . 13.6
WINDSHIELD WIPER SWITCH FAILURE . . . . . . 13.6
“ICE DETECT FAIL” (Caution Light) . . . . . . . . . . 13.6
ENGINE OIL TEMP BELOW 65 _C . . . . . . . . . . . . 13.6
“ENG ADPT HEAT 1” or
“ENG ADPT HEAT 2” (Caution Light) . . . . . . . . . 13.6
“PITOT HEAT 1” or “PITOT HEAT 2”
(Caution Light) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13.7
“PITOT HEAT STBY” (Caution Light) . . . . . . . . . 13.7
“#1 STALL SYST FAIL” or
“#2 STALL SYST FAIL” and
“PUSHER SYST FAIL” (Caution Lights) . . . . . . . 13.8
“PUSHER SYST FAIL” (Caution Light) . . . . . . . . 13.8
MAY 19/18
APR
15/05
PSM 1---84---1B
Page 13.1
Airframe De-Icing System
Page 13.2
PSM 1---84---1B
OCT
MAY 15/05
31/10
“DEICE PRESS”
(Caution Light)
D
Airframe Mode Selector . . . . . . . . . . . . . . . . . . Manual
After 10 seconds:
D Airframe Mode Selector . . . . . . Slow / Fast (as req’d)
IF DEICE PRESS Caution Light persists:
D Boot Air . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Iso
--- Deice Pressure Indicator . . . . . . . . . . . . . . . . check
Deice Pressure Indication is normal in both the No.
1 and No. 2 Systems (18 ±3 psi):
---
Deice Panel . . . . . . . . . . . check boot Advisory Lights
during Slow / Fast cycle
No. 1 or No. 2 Deice Boots -- one Advisory Light fails
to illuminate:
--- Exit icing conditions as soon as possible.
(See Landing Considerations, Page 13.4)
No. 3 or No. 4 Deice Boots -- both No. 3 or both No. 4
Advisory Light fail to illuminate:
--- Exit icing conditions as soon as possible.
(See Landing Considerations, Page 13.4)
No. 5 or No. 6 Deice Boots -- one Advisory Light fails
to illuminate:
FOR remainder of flight (affected engine):
D Engine Intake Door . . . . . . . . . . . . . . . . . . . . . open
--- Exit icing conditions as soon as possible.
IF aircraft is not aerodynamically clean after leaving
icing conditions:
D See Minimum Airspeed in Flight in Icing Conditions
(Page 2.7).
-- END --
CONTINUED ON NEXT PAGE
MAY 19/18
APR
15/05
PSM 1---84---1B
Page 13.3
“DEICE PRESS”
(Caution Light) (Cont’d)
Deice Pressure Indication is abnormal OR 2 or
more Wing Deice Boot Advisory Lights on the same
side fail to illuminate:
--D
D
Exit icing conditions as soon as possible.
Engine Intake Doors . . . . . . . . . . . . . . . . . . . . . . . open
Airframe Mode Selector . . . . . . . . . . . . . . . . . . Manual
Caution: Do not select the WING positions during manual
deicing of the tail and engine intake.
D
Airframe Manual Selector . . . . . . . . . . . tail and engine
Note:
Only engine intake boot on the side with normal
pressure will be deiced.
Dwell period at each Tail and Engine Intake
position should be approximately 6 secs.
Landing Considerations:
IF landing in icing conditions or the aircraft is not
aerodynamically clean after leaving icing conditions:
--- Land at Flap 10 or 15
--- Minimum Hold speed
Flap 0 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 190 kts
--- Approach, Go Around & VREF speeds
Flap 5 . . . . . . . . . . . . . . . . . . . . . . . . VAPP / VGA + 30 kts
Flap 10 . . . . . . . . . . . . . . . . VAPP / VGA / VREF + 30 kts
Flap 15 . . . . . . . . . . . . . . . . VAPP / VGA / VREF + 25 kts
Landing Distance Factor:
Flap 10 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1.80
Flap 15 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1.80
-- -- -- -- -- -- -- -- -- -- END -- -- -- -- -- -- -- -- -- --
ENGINE INTAKE BOOT FAILURE
FOR remainder of flight (affected engine):
D Engine Intake Door . . . . . . . . . . . . . . . . . . . . . . . . open
--- Exit icing conditions as soon as possible.
Page 13.4
PSM 1---84---1B
MAY
APR 15/05
19/18
“DEICE TIMER”
(Caution Light)
---
Deice Boots Advisory Lights . . . . . . . . . . . . . . monitor
IF Deice Boot sequencing is incorrect:
D Airframe Mode Selector . . . . . . . . . . . . . . . . . . Manual
D Airframe Manual Selector . . . . . . . . . . cycle (as req’d)
--- Exit icing conditions as soon as possible.
Note:
Dwell period at each position should be
approximately 6 seconds.
Allow for a dwell period of not less than 24
seconds before commencing subsequent
inflation of boots.
“PROP DEICE”
(Caution Light)
D
---
Prop selector . . . . . . . . . . . . . . . . . . . . . . . . Off then On
Monitor PROPS Advisory lights for normal operation.
IF Prop Deice Caution Light persists:
D Condition levers . . . . . . . . . . . . . . . . . . . . . . . . . . . . Max
--- Exit icing conditions as soon as possible.
--- Confirm operation of the propeller deice system of the
operating engine by observing PROPS advisory light
(operating engine) illuminates and goes out
repeatedly.
Note:
MAY 19/18
APR
15/05
Only one reset of the Prop selector switch is
allowed. Prop Selector must remain ON until
clear of icing conditions.
With an engine shutdown and propeller deice
selected, the PROP DEICE caution light will
illuminate.
PSM 1---84---1B
Page 13.5
“WSHLD HOT”
(Caution Light)
D
---
Windshield Heat . . . . . . . . . . . . . . . . . . . . . . . Warm Up
Exit icing conditions as soon as possible.
“SIDE WDO HOT”
(Caution Light)
D
Plt Side Wdo/Ht . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Off
“WSHLD CTRL”
(Caution Light)
---
Exit icing conditions as soon as possible.
WINDSHIELD WIPER SWITCH FAILURE
D
Alternate Pilot Wiper switch . . . . . . . . . . . . . . . . . . . . on
“ICE DETECT FAIL”
(Caution Light)
---
Monitor ice detection spigots on windshield wipers and
wing leading edges to determine icing conditions.
ENGINE OIL TEMP BELOW 65 _C
(Prop Deice On In Flight)
-----
Monitor affected engine performance.
Exit icing conditions as soon as possible.
“ENG ADPT HEAT 1” or
ENG ADPT HEAT 2”
(Caution Light)
-----
Monitor affected engine performance.
Exit icing conditions as soon as possible.
Page 13.6
PSM 1---84---1B
MAY
JUN 15/05
09/15
“PITOT HEAT 1” or
“PITOT HEAT 2”
(Caution Light)
D
---
Pitot Static (affected) . . . . . . . . . . . . . . . . . . . . . . . . . on
Exit icing conditions as soon as possible.
IF there are abnormal indications of airspeed or altitude on
the pilot’s or co-pilot’s PFD:
D EFIS ADC Source . . . . . . . . . . 1 or 2 (as appropriate)
--- Fly the aircraft by reference to the selected air data
source.
D Airspeed . . . . . . . . . . . . . . . . . . . . . . . . 200 KIAS (max)
Lost Services:
Autopilot and Yaw Damper
Note:
“ELEVATOR FEEL”, “PITCH TRIM”, “SPLR
OUTBD” and “RUD CTRL” Caution lights will
illuminate. Elevator forces, roll rate and rudder
sensitivity may be higher or lower than usual.
“PITOT HEAT STBY”
(Caution Light)
D
Stby Pitot Static . . . . . . . . . . . . . . . . . . . . . . . . . . . . . on
IF there are abnormal indications of airspeed or altitude on
the ISI:
--- Do not rely on standby airdata indications.
MAY 19/18
APR
15/05
PSM 1---84---1B
Page 13.7
“#1 STALL SYST FAIL” or
“#2 STALL SYST FAIL”
and
“PUSHER SYST FAIL”
(Caution Lights)
---
Maintain airspeed at or above the minimum appropriate
for the phase of flight, icing conditions and other
failures if applicable.
Landing Considerations:
--- Minimum Hold speed:
REF SPEED
INCR ON
Flap 0 . . . . . . . . . . . . . . 1.23 VSR
---
1.23 VSR + 25
Approach & VREF speeds:
REF SPEED
INCR ON
Flap 5 . . . . . . . . . . . . . . 1.23 VSR
Flap 10/15 . . . . . . . . . . VREF
Flap 35 . . . . . . . . . . . . . VREF
1.23 VSR + 20
VREF + 20
VREF + 15
“PUSHER SYST FAIL”
(Caution Light)
D
---
Stick Pusher Shutoff . . . . . . . . . . . . . . . . . . . . press Off
Maintain airspeed at or above the minimum appropriate
for the phase of flight, icing conditions and other
failures if applicable.
Landing Considerations:
--- Minimum Hold speed:
REF SPEED
INCR ON
Flap 0 . . . . . . . . . . . . . . 1.23 VSR
---
1.23 VSR + 25
Approach & VREF speeds:
REF SPEED
INCR ON
Flap 5 . . . . . . . . . . . . . . 1.23 VSR
Flap 10/15 . . . . . . . . . . VREF
Flap 35 . . . . . . . . . . . . . VREF
Page 13.8
PSM 1---84---1B
1.23 VSR + 20
VREF + 20
VREF + 15
MAY
FEB 23/16
15/05
LANDING GEAR
ALTERNATE LANDING GEAR EXTENSION
or “LDG GEAR INOP” (Caution Light) . . . . . . . . 14.3
MAIN LANDING GEAR DOOR MALFUNCTIONS 14.4
NOSE LANDING GEAR DOOR MALFUNCTIONS 14.5
ALL LANDING GEAR FAIL TO RETRACT . . . . . . 14.5
LANDING GEAR INDICATOR
MALFUNCTION . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14.6
“NOSE STEERING” (Caution Light) . . . . . . . . . . 14.6
“TOUCHED RUNWAY” (Warning Light) . . . . . . . 14.7
“INBD ANTI-SKID” and/or “OUTBD ANTI-SKID”
(Caution Lights) . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14.7
MAIN LANDING GEAR TIRE FAILURE . . . . . . . . 14.7
“WT ON WHEELS” (Caution Light) . . . . . . . . . . . 14.8
“PARKING BRAKE” (Caution Light) . . . . . . . . . . 14.8
MAY 19/18
APR
15/05
PSM 1---84---1B
Page 14.1
THIS PAGE INTENTIONALLY LEFT BLANK
Page 14.2
PSM 1---84---1B
MAY 15/05
ALTERNATE LANDING GEAR EXTENSION
or “LDG GEAR INOP” (Caution Light)
(One or more Landing Gear fail to extend)
Landing Considerations:
--- Landing Gear cannot be retracted.
--- Nosewheel steering will be inoperative.
Note:
D
D
D
D
D
D
The main and nose gear release handles pull
force will be significantly higher than
experienced during practice alternate landing
gear extensions. The required pull force, to
release the gear uplocks, can be as high as 41
kg (90 lb). It may require a repeated pull effort to
achieve a landing gear down and locked
indication.
Airspeed . . . . . . . . . . . . . . . . . . . . . . . . 185 KIAS (max)
L/G Inhibit switch . . . . . . . . . . . . . . . . . . . . . . . . . . Inhibit
Landing Gear lever . . . . . . . . . . . . . . . . . . . . . . . . Down
Landing Gear Alternate Release door . . . . . . . . open
Main Gear Release handle . . . . . . . . . . pull fully down
Check L & R DOOR amber open and LEFT & RIGHT
green locked down advisory lights illuminate.
Landing Gear Alternate Extension door . . . . . . open
Note:
IF LEFT and/or RIGHT green gear locked down
Advisory Lights do not illuminate, insert
Hydraulic Pump handle in socket and operate
until LEFT and RIGHT green gear locked down
Advisory Lights illuminate.
Nose Gear Release handle . . . . . . . . . . . . pull fully up
Check N DOOR amber open and NOSE green locked
down advisory lights illuminate.
Note:
Leave Landing Gear Alternate Release and
Alternate Extension Doors fully open and L/G
Inhibit switch at Inhibit.
D
D
D
Gear-Locked-Down indicator . . . . . . . . . on / check / off
Anti-Skid . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Test
After Landing:
As soon as possible after engine shutdown:
D Ground Locks . . . . . . . . . . . . . . . . . . . . . . . . . . . . install
MAY 09/15
JUN
15/05
PSM 1---84---1B
Page 14.3
MAIN LANDING GEAR DOOR
MALFUNCTIONS
(Continuous Illumination of Amber Main Gear Door Open
Advisory Light after Landing Gear selection)
Landing Gear Up selected:
D Airspeed . . . . . . . . . . . . . . . . . . . . . . . . 185 KIAS (Max)
D Flap . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 0
Amber Main Gear Door Open Advisory Light remains
illuminated:
Yes
D Airspeed . . . . . . . . . . . . . . . . . . . . . 185 KIAS (Max)
--- DO NOT extend landing gear via normal selection.
Prior to landing:
D ALTERNATE LANDING GEAR EXTENSION
(Page 14.3) . . . . . . . . . accomplish when required
Note:
Intermittent illumination of amber main gear
door open advisory light must be reported to
maintenance.
-- END --
No
--- Continue flight at normal airspeed.
-- END -Landing Gear Down selected:
D Airspeed . . . . . . . . . . . . . . . . . . . . . . . . 185 KIAS (Max)
--- Complete flight with landing gear down.
-- -- -- -- -- -- -- -- -- -- END -- -- -- -- -- -- -- -- -- --
Page 14.4
PSM 1---84---1B
MAY
APR 15/05
19/18
NOSE LANDING GEAR DOOR
MALFUNCTIONS
(Continuous Illumination of Amber Nose Gear Door Open
Advisory Light after Landing Gear selection)
Landing Gear Up selected:
D Airspeed . . . . . . . . . . . . . . . . . . . . . . . . 185 KIAS (Max)
--- DO NOT extend landing gear via normal selection.
Prior to landing:
D ALTERNATE LANDING GEAR EXTENSION
(Page 14.3) . . . . . . . . accomplish when required
Note:
Intermittent illumination of amber nose gear door
open advisory light must be reported to
maintenance.
-- END --
Landing Gear Down selected:
D Airspeed . . . . . . . . . . . . . . . . . . . . . . . . 185 KIAS (Max)
--- Complete flight with landing gear down.
-- -- -- -- -- -- -- -- -- -- END -- -- -- -- -- -- -- -- -- --
ALL LANDING GEAR FAIL
TO RETRACT
(3 Red Gear Unsafe Advisory Lights illuminated with
Landing Gear Lever selected Up)
Note:
Landing Gear Doors may be open or closed
(Amber Doors Open Advisory Lights illuminated
or out).
Note:
If the Landing Gear Alternate Release door is
open, the landing gear will not retract. Do not
close the Landing Gear Alternate Release door
with the Landing Gear lever in the up position.
D
-----
Landing Gear lever . . . . . . . . . . . . . . . . . . . . . . . . Down
Confirm 3 Green Gear Locked Down Advisory Lights
illuminate.
DO NOT re-select landing gear up.
Land at the nearest suitable airport.
MAY 19/18
APR
15/05
PSM 1---84---1B
Page 14.5
LANDING GEAR INDICATOR
MALFUNCTION
IF any of the Green gear-locked-down Advisory Lights fail to
illuminate:
D Landing Gear Alternate Extension door . . . . . . open
D Gear-Locked-Down indicator . . . . . . . . . on / check / off
D Landing Gear Alternate Extension door . . . . . . close
“NOSE STEERING”
(Caution Light)
In Flight:
D Steering Tiller . . . . . . . . . . . . . . . . . . . . . . . . . . centered
IF Caution Light remains on:
D Nosewheel Steering . . . . . . . . . . . . . . . . . . . . . . . . . Off
Landing Considerations:
--- Land at an airport with minimum crosswind and
turbulence.
After touchdown:
--- Use asymmetric braking and power, as required, to
maintain directional control.
On the Ground:
--- Taxi airplane forward to centre nosewheel.
With the airplane stopped:
D Steering Tiller and Rudder pedals . . . . . . . . centered
D Nosewheel Steering . . . . . . . . . . . . . . . . . . Off then on
--- Wait 7 secs for Nosewheel Steering to re-engage.
Caution Light remains on:
Yes
D Nosewheel Steering . . . . . . . . . . . . . . . . . . . . . . Off
--- Use asymmetric braking and power, as required, to
taxi airplane.
--- Maintenance action required prior to flight.
-- END -No
--- Check nosewheel for correct response to steering
inputs prior to flight.
-- -- -- -- -- -- -- -- -- -- END -- -- -- -- -- -- -- -- -- --
Page 14.6
PSM 1---84---1B
MAY
JUN 15/05
09/15
“TOUCHED RUNWAY”
(Warning Light)
Due to the possibility of runway debris:
D Advise ATC and airport operations of the fuselage /
runway contact.
--- Aircraft must not be flown prior to inspection and
maintenance approval.
“INBD ANTI-SKID” and/or
“OUTBD ANTI-SKID”
(Caution Lights)
D
Anti-Skid . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . On
IF Caution Light remains on:
Landing Considerations:
--- Anti-Skid will be inoperative. For maximum
deceleration, use intermittent 1 second pedal brake
applications with intervals of reduced braking as brief
as possible.
Caution: Excessive application of pedal brakes can result
in skidding and tire failure.
Landing Distance Factor:
REF SPEED
INCR ON
Flap 10 . . . . . . . . . . . . . . . . . .
Flap 15 . . . . . . . . . . . . . . . . . .
Flap 35 . . . . . . . . . . . . . . . . . .
1.70
1.70
1.70
2.1
2.1
2.0
MAIN LANDING GEAR
TIRE FAILURE
(Known or Suspected Main Landing Gear Tire Failure)
Landing Considerations:
--- Promptly decelerate aircraft to below 80 KIAS using
anti-skid braking. Reverse thrust, commensurate with
directional control and runway conditions, may also be
used to expedite the deceleration.
MAY 19/18
APR
15/05
PSM 1---84---1B
Page 14.7
“WT ON WHEELS”
(Caution Light)
Caution: Landing Gear may not retract.
Note:
Caution Light may extinguish after landing,
however, maintenance action will be required
prior to next flight.
“PARKING BRAKE”
(Caution Light)
(Caution Light Remains On After Parking Brake Released)
---
Maintenance action required prior to next flight.
Page 14.8
PSM 1---84---1B
MAY
APR 15/05
19/18
LIST OF EFFECTIVE PAGES
Page
Date
LOR 1
LOR 2
MAY 15/05
MAY 15/05
PREFACE i
PREFACE ii
PREFACE iii
PREFACE iv
MAY 07/13
MAY 15/05
APR 19/18
APR 19/18
COCKPIT PREPARATION
1.1
JUN 09/15
1.2
JUL 22/16
1.3
FEB 23/16
1.4
JUN 09/15
1.5
JUN 09/15
1.6
MAY 15/05
NORMAL CHECKLIST
2.1
JUL 22/16
2.2
JUL 22/16
2.3
JUN 09/15
2.4
APR 19/18
2.5
JUN 09/15
2.6
JUN 09/15
2.7
MAY 15/05
2.8
DEC 05/11
PERFORMANCE
3.1
3.2
3.3
3.4
3.5
3.6
3.7
3.8
3.9
3.10
3.11
3.12
3.13
3.14
3.15
3.16
MAY 15/05
MAY 15/05
MAY 15/05
MAY 15/05
MAY 15/05
MAY 15/05
MAY 15/05
MAY 15/05
MAY 15/05
MAY 15/05
MAY 15/05
MAY 15/05
MAY 15/05
MAY 15/05
MAY 15/05
MAY 15/05
NON-NORMAL CHECKLIST
4.1
FEB 23/16
4.1D
FEB 23/16
4.2
OCT 31/10
4.3
OCT 31/10
4.4
JUN 09/15
4.5
APR 19/18
4.6
JUL 22/13
4.7
JUN 09/15
4.8
JUN 09/15
4.9
APR 19/18
4.9D
APR 19/18
4.10
JUN 09/15
4.10D
FEB 23/16
Page
FEB 23/16
JUN 09/15
JUN 09/15
JUN 09/15
JUN 09/15
APR 19/18
APR 19/18
JUN 09/15
JUN 09/15
FEB 23/16
FEB 23/16
FEB 23/16
JUN 09/15
JUN 09/15
JUN 09/15
APR 19/18
APR 19/18
6.1
6.2
6.3
6.4
6.5
6.6
6.7
6.8
6.9
6.10
6.11
6.12
6.13
6.14
6.15
6.16
6.17
6.18
6.19
6.20
6.21
6.22
6.23
6.24
6.25
6.26
6.27
6.28
6.29
6.30
6.31
6.32
6.33
6.34
6.35
6.36
6.37
6.38
APR 19/18
APR 19/18
APR 19/18
APR 19/18
JUN 09/15
JUN 09/15
JUN 09/15
JUN 09/15
APR 19/18
JUN 09/15
JUN 09/15
JUN 09/15
JUN 09/15
MAY 07/13
MAY 07/13
MAY 07/13
JUN 09/15
MAY 07/13
MAY 07/13
APR 19/18
APR 19/18
APR 19/18
JUN 09/15
MAY 07/13
MAY 07/13
APR 19/18
APR 19/18
APR 19/18
APR 19/18
APR 19/18
APR 19/18
MAY 07/13
APR 19/18
APR 19/18
APR 19/18
APR 19/18
APR 19/18
MAY 07/13
D
CARGO COMBI / 86 PAX AIRPLANES ONLY
[
DOT OR FAA ONLY
u
EASA ONLY
MAY 19/18
APR
15/05
Date
5.1
5.2
5.3
5.4
5.5
5.6
5.7
5.8
5.9
5.10
5.11[
5.11u
5.12
5.13
5.14
5.15
5.16
PSM 1---84---1B
Page 15.1
LIST OF EFFECTIVE PAGES
Page
Date
Page
7.1
7.2
7.3
7.4
7.5
7.6
JUL 22/16
APR 19/18
JUL 22/16
JUL 22/16
JUL 22/16
JUL 22/16
11.1
11.2
11.3
11.4
11.5
11.6
FEB 23/16
OCT 31/10
OCT 31/10
APR 19/18
APR 19/18
FEB 23/16
8.1
8.2
8.3
8.4
8.5
8.6
8.7
8.8
MAY 15/05
MAY 15/05
APR 19/18
JUN 09/15
APR 19/18
APR 19/18
JUN 09/15
MAY 15/05
9.1
9.2
9.3
9.4
9.5
9.5}
9.6
9.6}
9.7
9.8
9.9
9.10
9.11
9.12
JUN 09/15
OCT 31/10
OCT 31/10
APR 19/18
APR 19/18
APR 19/18
APR 19/18
APR 19/18
JUN 09/15
APR 19/18
APR 19/18
APR 19/18
JUN 09/15
APR 19/18
12.1
12.2
12.3
12.4
12.5
12.6
12.7
12.8
12.8*
12.9
12.9*
12.10
NOV 09/11
OCT 31/10
OCT 31/10
OCT 31/10
APR 19/18
APR 19/18
APR 19/18
APR 19/18
APR 19/18
APR 19/18
APR 19/18
APR 19/18
13.1
13.2
13.3
13.4
13.5
13.6
13.7
13.8
APR 19/18
OCT 31/10
APR 19/18
APR 19/18
APR 19/18
JUN 09/15
APR 19/18
FEB 23/16
10.1
10.2
10.3
10.4
10.5
10.6
10.7
10.8
10.9
10.10
10.11
10.12
10.13
10.14
APR 19/18
MAY 15/05
FEB 23/16
JUL 22/16
JUL 22/16
FEB 23/16
JUN 09/15
APR 19/18
FEB 29/08
JUN 09/15
APR 19/18
APR 19/18
APR 19/18
APR 19/18
14.1
14.2
14.3
14.4
14.5
14.6
14.7
14.8
APR 19/18
MAY 15/05
JUN 09/15
APR 19/18
APR 19/18
JUN 09/15
APR 19/18
APR 19/18
APPENDIX
15.1
15.2
15.3
15.4
15.5
15.6
15.6D
APR 19/18
APR 19/18
OCT 31/10
MAY 07/13
MAY 07/13
APR 19/18
APR 19/18
}
Date
MS 4---113581 or IS4Q2150011
* MS 4---126354 and (MS 4---901472 or MS 4---901473)
D
CARGO COMBI / 86 PAX AIRPLANES ONLY
Page 15.2
PSM 1---84---1B
MAY
APR 15/05
19/18
ED ANNUNCIATIONS
CHECK ED . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . see Page 6.23
DU BAD CONF . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . see Page 6.23
ED MON FAIL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . see Page 6.24
FADEC1/DU . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
FADEC2/DU . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
FADECS/DU . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
FANS FAIL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
see Page 6.24
see Page 6.24
see Page 6.24
see Page 6.24
GPWS I/F FAIL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . see Page 6.24
HOT DISPLAYS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
HOT ED . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
HOT MFD1 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
HOT MFD2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
HOT PFD1 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
HOT PFD2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
see Page 6.25
see Page 6.25
see Page 6.25
see Page 6.25
see Page 6.25
see Page 6.25
IOM1 FAIL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
IOM2 FAIL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
IOMS FAIL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
IOP BAD CONF . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
IOP1 FAIL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
IOP2 FAIL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
IOPS FAIL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
see Page 6.26
see Page 6.27
see Page 6.26
see Page 6.27
see Page 6.29
see Page 6.30
see Page 6.28
MFD1 LINK FAIL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . see Page 6.31
MFD2 LINK FAIL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . see Page 6.31
PFD1 LINK FAIL . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
PFD2 LINK FAIL . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
PFD1 MON FAIL . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
PFD2 MON FAIL . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
PFDS MON FAIL . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
see Page 6.31
see Page 6.31
see Page 6.31
see Page 6.31
see Page 6.31
RA1 FAIL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . see Page 6.32
RA2 FAIL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . see Page 6.32
RAS FAIL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . see Page 6.31
WOW/IOP1 FAIL . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
WOW/IOP2 FAIL . . . . . . . . . . . . . . . . . . . . . . . . . . . .
WOW/IOPS FAIL . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
WTG1 FAIL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
WTG2 FAIL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
WTGS FAIL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
MAY 07/13
15/05
PSM 1---84---1B
see Page 6.32
see Page 6.32
see Page 6.32
see Page 6.33
see Page 6.33
see Page 6.33
Page 15.5
Page 15.6
PSM 1---84---1B
APR 15/05
19/18
MAY
WSHLD
HOT
13.6
SMOKE
7.2
R TRU
9.9 *
INTERNAL
DOORS
4.9
CHECK
FIRE DET
5.15 *
#3 HYD
PUMP
12.10
EMER LTS
DISARMED
9.12
CABIN
PRESS
4.5
14.7
TOUCHED
RUNWAY
13.3
DEICE
PRESS
13.5
DEICE
TIMER
13.5
PROP
DEICE
13.6
ENG ADPT
HEAT 2
13.7
PITOT
HEAT 2
13.6
ICE DETECT
FAIL
9.11
R TRU
HOT
9.11
L TRU
HOT
4.8 *
FLT COMPT
PACK HOT
4.8 *
CABIN
PACK HOT
4.8
CABIN
DUCT HOT
4.8
FLT COMPT
DUCT HOT
6.37
AVIONICS
9.12 *
AUX
BATTERY
9.12 *
MAIN
BATTERY
9.12 *
STBY
BATTERY
12.8 *
#2 HYD
ISO VLV
12.6 *
#1 HYD
ISO VLV
5.10
#1 ENG
OIL PRESS
11.6
#1 FUEL
FLTR BYPASS
12.10
#1 HYD
FLUID HOT
9.11
#1 AC GEN
HOT
9.10
#1 DC GEN
HOT
4.7 *
#1 BLEED
HOT
5.14
#1 PEC
5.15
#1 ENG
FADEC FAIL
11.4
#1 TANK
FUEL LOW
5.15
#1 ENG
FADEC
9.8 *
#1 AC GEN
9.8 *
#1 DC GEN
12.6 *
#1 ENG
HYD PUMP
11.4
#1 ENG
FUEL PRESS
5.15
#2 ENG
FADEC FAIL
11.4
#2 TANK
FUEL LOW
5.15
#2 ENG
FADEC
9.8 *
#2 AC GEN
9.8 *
#2 DC GEN
12.8 *
#2 ENG
HYD PUMP
11.4
#2 ENG
FUEL PRESS
5.10
#2 ENG
OIL PRESS
11.6
#2 FUEL
FLTR BYPASS
12.10
#2 HYD
FLUID HOT
9.11
#2 AC GEN
HOT
9.10
#2 DC GEN
HOT
4.7 *
#2 BLEED
HOT
5.14
#2 PEC
9.12
STBY BAT
HOT
5.7
APU
10.14 *
RUD
CTRL
10.14
#1 RUD
HYD
10.5 *
ROLL SPLR
INBD HYD
12.10
#1 STBY HYD
PUMP HOT
10.6
ROLL SPLR
INBD GND
9.12
AUX BAT
HOT
10.12
FLAP
POWER
10.12
FLAP
DRIVE
10.14
#2 RUD
HYD
10.5 *
ROLL SPLR
OUTBD HYD
10.6 *
SPLR
OUTBD
10.6
ROLL SPLR
OUTBD GND
9.12
MAIN BAT
HOT
14.6
NOSE
STEERING
14.3
LDG GEAR
INOP
14.7
INBD
ANTI-SKID
13.8
PUSHER
SYST FAIL
13.8
#2 STALL
SYST FAIL
13.8
#1 STALL
SYST FAIL
4.9
FUSELAGE
DOORS
11.6
FUELING
ON
14.8
WT ON
WHEELS
14.7
OUTBD
ANTI-SKID
14.8
PARKING
BRAKE
6.37
GPWS
6.37
FLT DATA
RECORDER
* This caution/warning light is addressed in multiple procedures. Where applicable, only the most critical of the associated procedures is page-referenced.
Ensure the appropriate procedure is carried out.
13.6
SIDE WDO
HOT
13.6
9.9 *
10.8
13.6
ENG ADPT
HEAT 1
WSHLD
CTRL
DC BUS
ELEVATOR
ASYMMETRY
13.7
L TRU
9.7
10.8 *
PITOT
HEAT 1
ELEVATOR
PRESS
R AC BUS
ELEVATOR
FEEL
13.7
9.5 *
9.7
10.9 *
PITOT HEAT
STBY
10.8
L AC BUS
PITCH
TRIM
ED ANNUNCIATIONS
CHECK ED . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . see Page 6.23
DU BAD CONF . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . see Page 6.23
ED MON FAIL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . see Page 6.24
FADEC1/DU . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
FADEC2/DU . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
FADECS/DU . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
FANS FAIL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
see Page 6.24
see Page 6.24
see Page 6.24
see Page 6.24
GPWS I/F FAIL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . see Page 6.24
HOT DISPLAYS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
HOT ED . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
HOT MFD1 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
HOT MFD2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
HOT PFD1 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
HOT PFD2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
see Page 6.25
see Page 6.25
see Page 6.25
see Page 6.25
see Page 6.25
see Page 6.25
IOM1 FAIL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
IOM2 FAIL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
IOMS FAIL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
IOP BAD CONF . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
IOP1 FAIL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
IOP2 FAIL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
IOPS FAIL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
see Page 6.26
see Page 6.27
see Page 6.26
see Page 6.27
see Page 6.29
see Page 6.30
see Page 6.28
MFD1 LINK FAIL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . see Page 6.31
MFD2 LINK FAIL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . see Page 6.31
PFD1 LINK FAIL . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
PFD2 LINK FAIL . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
PFD1 MON FAIL . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
PFD2 MON FAIL . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
PFDS MON FAIL . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
see Page 6.31
see Page 6.31
see Page 6.31
see Page 6.31
see Page 6.31
RA1 FAIL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . see Page 6.32
RA2 FAIL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . see Page 6.32
RAS FAIL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . see Page 6.31
WOW/IOP1 FAIL . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
WOW/IOP2 FAIL . . . . . . . . . . . . . . . . . . . . . . . . . . . .
WOW/IOPS FAIL . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
WTG1 FAIL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
WTG2 FAIL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
WTGS FAIL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
MAY 07/13
15/05
PSM 1---84---1B
see Page 6.32
see Page 6.32
see Page 6.32
see Page 6.33
see Page 6.33
see Page 6.33
Page 15.5
FOR CARGO COMBI / 86 PAX AIRPLANES ONLY
Page 15.6
PSM 1---84---1B
APR 15/05
19/18
MAY
13.6
WSHLD
HOT
13.6
SMOKE
7.2
9.9 *
R TRU
9.9 *
COCKPIT
DOOR
4.9
CHECK
FIRE DET
5.15 *
10.8
#3 HYD
PUMP
12.10
EMER LTS
DISARMED
9.12
CABIN
PRESS
4.5
14.7
TOUCHED
RUNWAY
13.3
DEICE
PRESS
13.5
DEICE
TIMER
13.5
PROP
DEICE
13.6
ENG ADPT
HEAT 2
13.7
PITOT
HEAT 2
13.6
ICE DETECT
FAIL
9.11
R TRU
HOT
9.11
L TRU
HOT
4.8 *
FLT COMPT
PACK HOT
4.8 *
CABIN
PACK HOT
4.8
CABIN
DUCT HOT
4.8
FLT COMPT
DUCT HOT
6.37
AVIONICS
9.12 *
AUX
BATTERY
9.12 *
MAIN
BATTERY
9.12 *
STBY
BATTERY
12.8 *
#2 HYD
ISO VLV
12.6 *
#1 HYD
ISO VLV
5.10
#1 ENG
OIL PRESS
11.6
#1 FUEL
FLTR BYPASS
12.10
#1 HYD
FLUID HOT
9.11
#1 AC GEN
HOT
9.10
#1 DC GEN
HOT
4.7 *
#1 BLEED
HOT
5.14
#1 PEC
5.15
#1 ENG
FADEC FAIL
11.4
#1 TANK
FUEL LOW
5.15
#1 ENG
FADEC
9.8 *
#1 AC GEN
9.8 *
#1 DC GEN
12.6 *
#1 ENG
HYD PUMP
11.4
#1 ENG
FUEL PRESS
5.15
#2 ENG
FADEC FAIL
11.4
#2 TANK
FUEL LOW
5.15
#2 ENG
FADEC
9.8 *
#2 AC GEN
9.8 *
#2 DC GEN
12.8 *
#2 ENG
HYD PUMP
11.4
#2 ENG
FUEL PRESS
5.10
#2 ENG
OIL PRESS
11.6
#2 FUEL
FLTR BYPASS
12.10
#2 HYD
FLUID HOT
9.11
#2 AC GEN
HOT
9.10
#2 DC GEN
HOT
4.7 *
#2 BLEED
HOT
5.14
#2 PEC
9.12
STBY BAT
HOT
5.7
APU
10.14 *
RUD
CTRL
10.14
#1 RUD
HYD
10.5 *
ROLL SPLR
INBD HYD
12.10
#1 STBY HYD
PUMP HOT
10.6
ROLL SPLR
INBD GND
9.12
AUX BAT
HOT
10.12
FLAP
POWER
10.12
FLAP
DRIVE
10.14
#2 RUD
HYD
10.5 *
ROLL SPLR
OUTBD HYD
10.6 *
SPLR
OUTBD
10.6
ROLL SPLR
OUTBD GND
9.12
MAIN BAT
HOT
14.6
NOSE
STEERING
14.3
LDG GEAR
INOP
14.7
INBD
ANTI-SKID
13.8
PUSHER
SYST FAIL
13.8
#2 STALL
SYST FAIL
13.8
#1 STALL
SYST FAIL
4.9
FUSELAGE
DOORS
11.6
FUELING
ON
14.8
WT ON
WHEELS
14.7
OUTBD
ANTI-SKID
14.8
PARKING
BRAKE
6.37
GPWS
6.37
FLT DATA
RECORDER
* This caution/warning light is addressed in multiple procedures. Where applicable, only the most critical of the associated procedures is page-referenced.
Ensure the appropriate procedure is carried out.
13.6
SIDE WDO
HOT
WSHLD
CTRL
13.6
ENG ADPT
HEAT 1
L TRU
DC BUS
ELEVATOR
ASYMMETRY
13.7
ELEVATOR
PRESS
9.7
10.8 *
PITOT
HEAT 1
9.5 *
R AC BUS
ELEVATOR
FEEL
13.7
PITOT HEAT
STBY
10.8
9.7
L AC BUS
10.9 *
PITCH
TRIM