2.01.00
LIMITATIONS
P 1
CONTENTS
AA
2.01.00
2.01.01
2.01.02
2.01.03
2.01.04
2.01.05
2.01.06
2.01.07
2.01.08
2.01.09
2.01.10
Mod 5948
C0NTENTS
GENERAL
WEIGHT AND LOADING
AIRSPEED AND OPERATIONAL PARAMETERS
POWER PLANT
SYSTEMS
TCAS
FMS
CABIN LIGHTING
TAWS
COCKPIT DOOR SECURITY SYSTEM (if installed)
001
APR 11
APR 11
cs
Mod 5948
2.01.01
LIMITATIONS
P2
001
GENERAL
APR 11
AA
MANEUVERING LIMIT LOAD FACTORS
FLAPS RETRACTED = - 1 G to 2.5 G
FLAPS EXTENDED = 0 G to + 2 G
GEAR DOWN
= 0 G to + 2 G
The corresponding positive accelerations limit the bank angle in turns and the severity
of pull up maneuvers.
CARGO DOOR OPERATION
Do not operate cargo door with a cross wind component of more than 45 kt.
DISPATCHABILITY
For dispatch in the event of equipment failure or missing equipment refer to MEL/CDL.
MAXIMUM NUMBER OF PASSENGER SEATS
74
Mod 5948
as limited by emergency exits configuration. Other limitations such as that
given by the emergency evacuation demonstration must be respected.
2.01.02
LIMITATIONS
P1
700
WEIGHT AND LOADING
APR 11
AA
DESIGN WEIGHT LIMITATIONS
MAXIMUM WEIGHT
KG
LB
TAXI
22 970
50 640
TAKE OFF
22 800
50 265
LANDING
22 350
49 273
ZERO FUEL
20 800
45 856
CENTER OF GRAVITY ENVELOPE
The limits of center of gravity are given in percentage of the mean aerodynamic chord
(MAC), landing gear extended.
The MAC is 2.303 meters long (90.67) inches.
Station O is located 2.362 meters (92.99 inches) forward of the fuselage nose.
The distance from station 0 to reference chord leading edge is 13.604 meters
(535.59 inches).
Mod : Mod 5948 + 5555
Model : 212A
2.01.02
LIMITATIONS
P2
WEIGHT AND LOADING
001
APR 11
AA
PASSENGERS BOARDING / DISEMBARKING
See WBM 1.10.04 p1
PASSENGERS BOARDING / DISEMBARKING
- The tail prop must installed before passengers boarding / disembarking;
- A possible toppling over should be taken into account from seven persons moving near
the rear part of an off loading aircraft.
Mod 5948
Model : 212A
2.01.02
LIMITATIONS
P1
800
WEIGHT AND LOADING
FEB 12
AA
DESIGN WEIGHT LIMITATIONS
MAXIMUM WEIGHT
KG
LB
TAXI
23170
51080
TAKE OFF
23000
50705
LANDING
22350
49273
ZERO FUEL
21000
46296
CENTER OF GRAVITY ENVELOPE
The limits of center of gravity are given in percentage of the mean aerodynamic chord
(MAC), landing gear extended.
The MAC is 2.303 meters long (90.67) inches.
Station O is located 2.362 meters (92.99 inches) forward of the fuselage nose.
The distance from station 0 to reference chord leading edge is 13.604 meters
(535.59 inches).
Mod : 5948 + 6219
Model : 212A
2.01.02
LIMITATIONS
P2
WEIGHT AND LOADING
001
APR 11
AA
PASSENGERS BOARDING / DISEMBARKING
See WBM 1.10.04 p1
PASSENGERS BOARDING / DISEMBARKING
- The tail prop must installed before passengers boarding / disembarking;
- A possible toppling over should be taken into account from seven persons moving near
the rear part of an off loading aircraft.
Mod 5948
Model : 212A
2.01.03
LIMITATIONS
P1
AIRSPEED AND OPERATIONAL PARAMETERS
001
APR 11
AA
AIRSPEEDS
* MAXIMUM OPERATING SPEED.
This limit must not be intentionnaly exceeded in any flight regime.
VMO = 250 kt
MMO = 0.55
* MAXIMUM DESIGN MANEUVERING SPEED VA
Full application of roll and yaw controls as well as maneuvers involving angles of
attack near the stall should be confined to speeds below VA.
VA = 175 kt
CAUTION : Rapidly alternating large rudder applications in combination
with large sideslip angles may result in structural failure at any
speed.
* MAXIMUM FLAPS EXTENDED OPERATING SPEEDS VFE
FLAPS 15 185 kt
FLAPS 30 150 kt
* MAXIMUM LANDING GEAR EXTENDED OPERATING SPEEDS
VLE = 185 kt
VLO RET= 160 kt
VLO LOW= 170 kt
* MAXIMUM ROUGH AIR SPEED
VRA= 180 kt
* MAXIMUM WIPER OPERATING SPEED
VWO = 160 kt
* MAXIMUM TIRE SPEED : 165 kt (Ground speed).
Mod 5948
2.01.03
LIMITATIONS
P2
AIRSPEED AND OPERATIONAL PARAMETERS
AA
ROFA-- 02-- 01-- 03-- 002-- A500AA
R STALL SPEEDS - VSR
Mod 5948
Eng. : PW127F / PW127M
001
APR 11
2.01.03
LIMITATIONS
P3
AIRSPEED AND OPERATIONAL PARAMETERS
001
APR 11
AA
V1 LIMITED BY VMCG
CAS (KT)
V1 LIMITED BY VMCG (FLAPS 15)
OUTSIDE AIR TEMPERATURE (DG.C)
Mod 5948
Eng. : PW127F / PW127M
2.01.03
LIMITATIONS
P4
AIRSPEED AND OPERATIONAL PARAMETERS
001
APR 11
AA
ROFA--02--01--03--004--A500AA
VMCA
CAS (KT)
VMCA (FLAPS 15)
VMCL
Mod 5948
Flaps
VMCL (CAS)
30
98 kt
15
98 kt
Eng. : PW127F / PW127M
APR 11
Altitude Zp (ft)
For operations on runways slope beyond 2% : refer to 3.11.18
MINIMUM RUNWAY WIDTH : 30m
For narrow runways operations : refer to 3.11.10
Mod : 5948 + 3037 + (3522 or 8044)
2.01.03
LIMITATIONS
P6
AIRSPEED AND OPERATIONAL PARAMETERS
001
APR 11
TAKE OFF AND LANDING (CONT’D)
The maximum crosswind demonstrated is:
- Take-- off: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 35kt
- Landing Flaps 30°: . . . . . . . . . . . . . . . . . . . . . . . . . . 35kt
Braking Action
TO
LDG
GOOD
1
1
35 kt
GOOD/MEDIUM
2
2
28 kt
MEDIUM
3/6
6
22 kt
MEDIUM/POOR
4
5
16 kt
POOR
7
7
10 kt
Maximum Crosswind
(TO and LDG)
Runway status: 1: dry runway, 2:wet up to 3mm depth, 3 (TO only): slush or water from 3 to
6mm depth, 4 (TO only):slush or water from 6 to 12.7mm depth,
5: slush or water from 3 to 12.7mm depth, 6: compact snow, 7: ice
Mod 5948
2.01.04
LIMITATIONS
P1
POWER PLANT
AA
001
APR 11
ENGINES
ENGINE PARAMETERS
Operating limits with no unscheduled maintenance action required.
Beyond these limits, refer to maintenance manual.
POWER
SETTING
TIME
LIMIT
TQ
(%)
ITT
(°C)
NH
(%)
NL
(%)
NP
(%)
OIL PRESS
(PSI)
OIL
TEMPERATURE
(°C)
RESERVE
TAKE OFF
10 mn
(***)
100
(**)
800
103.2
104.2
101
55 to 65
0 to 125
(3)
TAKE OFF
5 mn
90
(**)
(*)
101.9
101.4
101
55 to 65
0 to125
(3)
MAXIMUM
CONTINUOUS
NONE
(***)
90.9
(**)
800
103.2
104.2
101
55 to 65
0 to 125
(3)
40 mini
(****)
- 40 to 125
(3)
55 to 65
125
(3)
GROUND
IDLE
66 mini
HOTEL (4)
MODE
STARTING
715
5s
950
(2)
OTHER
TRANSIENT
- 54 min
800
106
(*****)
5s
20 s(1) (2)
20 mn
120
120
840
106.4
106.8
108
140
During RESERVE TAKE OFF, TQ indication may exceed 100 % but not 106.3 %.
(*)
ITT limite depends on outside air temperature; refer to 2.01.04 P 3 for detailed
information.
(**)
Value linked to 100 % NP.
(***)
- RTO: Time beyond 5 mn is linked to actual single engine operations only.
- MCT rating is the max power certified for continuous use. In-- flight emergencies
are the only conditions for which MCT use is authorized.
(****) Up to 75 % NH only.
(*****) Permissible for completion of flight provided TQ does not exceed 75.2 %
during climb and 73.13 % during cruise.
(1), (2), (3), (4) : see page 4.
Note : Flight with an engine running and the propeller feathered is not permitted.
Mod 5948
Model. : 212A
2.01.04
LIMITATIONS
P2
POWER PLANT
001
APR 11
AA
Note : Operation up to 106.3% torque is time unlimited when
NP is below 94%
Mod 5948
Model. : 212A
2.01.04
LIMITATIONS
P3
POWER PLANT
001
APR 11
AA
ITT LIMITS
Mod 5948
Model. : 212A
2.01.04
LIMITATIONS
P4
POWER PLANT
001
APR 11
AA
(1) - Determine and correct cause of overtorque.
- Record in engine log book for maintenance.
(2) - Determine and correct cause of overtemperature.
- Record in engine log book for maintenance.
(3) - Temperature up to 125°C is authorized without time limitation.
20 mn are authorized between 125°C and 140°C.
- Refer to ENG OIL Hl TEMP procedure.
Note : Oil temperature must be maintained above 45°C to ensure inlet strut
de-- icing.
Oil temperature must be maintained above 71°C to ensure fuel anti - icing
protection in absence of the low fuel temperature indication.
(4) - Do not use engine 2 in HOTEL MODE without a qualified person (flight crew or
maintenance) in the cockpit.
PROPELLERS
GROUND OPERATION
- Engine run up must be performed into the wind.
- Engine ground operations with crosswind between 5 and 20 kt should not exceed
58 % TQ.
IN FLIGHT OPERATION
USE OF NP SETTING BELOW 82 % IN ICING CONDITIONS IS PROHIBITED
ATR airplanes are protected against a positioning of power levers below the flight idle
stops in flight by an IDLE GATE device. It is reminded that any attempt to override
this protection is prohibited. Such positioning may lead to loss of airplane control or
may result in an engine overspeed condition and consequent loss of engine power.
GROUND OR FLIGHT
If a propeller is involved in an overspeed or in an engine overtorque, refer to the
propeller maintenance manual.
Mod 5948
Model. : 212A
2.01.04
LIMITATIONS
P5
001
POWER PLANT
DEC 13
AA
STARTER
3 STARTS WITH A 1 MINUTE 30 SECONDS MAXIMUM COMBINED STARTER
RUNNING TIME, FOLLOWED BY 4 MINUTES OFF
OIL SYSTEM
Approved lubricating oils
- Aero Shell Turbine oil 500
- Aero Shell Turbine oil 560
- Royco Turbine oil 500
- Royco Turbine oil 560
- Mobil Jet oil II
- Mobil Jet oil 254
- Castrol 4000
- Castrol 5000
- Exxon Turbo oil 2380
Mixing of different brands of oil or viscosities of oil is not recommended.
FUEL SYSTEM
- Use of JP 4 or JET B is prohibited.
- Acceptable fuels (refer to PWC Documentation to determine equivalent approved fuels).
MINIMUM FUEL TEMP (°C)
R
FUELS
FREEZING POINT
(°C)
Starting
Operation
MAXIMUM
FUEL TEMP
(°C)
JET A
JET A1
RT, TS1
JP 5
- 40
- 47
- 60
- 46
- 34
- 34
- 34
- 26
- 38
- 48
- 60
- 33
+ 57
+ 57
+ 57
+ 57
- Approved anti icing additives (maximum concentration allowed : 0.15 % per volume) :
- Philips PFA 55 MB
- MIL-- I-- 27 686 D
- Ethylene Glycol Monomethyl Ether as defined in MIL-- I-- 27 686 E.
Mod 5948
2.01.04
LIMITATIONS
P6
POWER PLANT
AA
REFUELING
MAXIMUM PRESSURE 3.5 BARS (50 PSI)
USABLE FUEL
THE TOTAL QUANTITY OF FUEL USABLE IN EACH TANK IS
2500 KG (5510 LBS)
NOTE : FUEL REMAINING IN THE TANKS WHEN
QUANTITY INDICATORS SHOW ZERO IS NOT USABLE
IN FLIGHT
UNBALANCE
MAXIMUM FUEL UNBALANCE : 730 kg (1609 lb)
FEEDING
- EACH ELECTRIC PUMP IS ABLE TO SUPPLY ONE ENGINE IN
THE WHOLE FLIGHT ENVELOPE
- ONE ELECTRICAL PUMP AND ASSOCIATED JET PUMP ARE
ABLE TO SUPPLY BOTH ENGINES IN THE WHOLE FLIGHT
ENVELOPE
Mod 5948
001
APR 11
2.01.05
LIMITATIONS
P1
030
SYSTEMS
AA
APR 11
AIR - PRESSURIZATION
MAXIMUM DIFFERENTIAL PRESSURE
MAXIMUM NEGATIVE DIFFERENTIAL PRESSURE
MAXIMUM DIFFERENTIAL PRESSURE FOR LANDING
MAXIMUM DIFFERENTIAL PRESSURE FOR OVBD VALVE FULL OPEN
SELECTION
MAXIMUM ALTITUDE FOR ONE BLEED OFF OPERATION
6.35 PSI
- 0.5 PSI
0.35 PSI
1 PSI
20 000 ft
ELECTRICAL SYSTEM
SOURCE
DC GEN
INV
ACW GEN
TRU
MAX LOAD
400 A
600 A
800 A
500 VA
575 VA
750 VA
20 KVA
30 KVA
40 KVA
60 A
90 A
TIME LIMIT
NONE
2 mn
8s
NONE
30 mn
5 mn
NONE
5 mn
5s
NONE
5 mn
SINGLE DC GEN OPERATION
In flight
: if OAT exceeds ISA + 25, flight level must be limited to FL 200
HYDRAULIC SYSTEM
SPECIFICATION : HYJET IV OR SKYDROL LD 4
LANDING GEAR
DO NOT PERFORM PIVOTING (SHARP TURNS) ON A LANDING GEAR WITH FULLY
BRAKED WHEELS EXCEPT IN CASE OF EMERGENCY
MFC
TAKE OFF WITH TWO OR MORE FAILED MFC MODULES IS PROHIBITED.
Mod : 5948 + 1603
2.01.05
LIMITATIONS
P2
SYSTEMS
100
APR 11
AA
OXYGEN
Reference temperature = Cabin Temperature or OAT whichever is higher, on ground
= Cabin Temperature in flight
Minimum bottle pressure required to cover a cabin depressurization at mid-- time of the
flight, an emergency descent from 25,000 ft to 13,000 ft within less than 4 minutes and a
flight continuation at an altitude below 13,000 ft.
A 25 % pax oxygen consumption is assumed.
In case of smoke emission, the system protects the flight crew members during 15 min.
Note : At dispatch the computed flight time after decompression should be at least
1/2 of estimated flight time to destination or flight time to the longest en route
alternate which ever is higher.
Provision is made to cover :
- unusuable quantity
- normal system leakage
- Ref. Temp errors.
Mod : 5948 + 4411
2.01.05
LIMITATIONS
P3
100
SYSTEMS
FEB 12
AA
AUTOMATIC FLIGHT CONTROL SYSTEM (AFCS)
-- Minimum height for autopilot engagement on take off : 100 ft.
-- Minimum height for autopilot use in single source configuration: do not use
AP/YD in single source configuration(one ADC and/or one AHRS lost :
-- below 1000 ft AGL, or
-- with stall warning inoperative.
-- NAV mode for VOR approach, using either autopilot or flight director is
authorized only if :
-- a co--located DME is available, and
-- DME HOLD is not selected
-- Minimum height for use of either autopilot or flight director :
-- Except during take off or approach : 1000 ft
-- VS or IAS mode during approach :160 ft
-- CAT 1 APP mode : 160 ft
Refer to 2.02.04 for CAT II operation
INSTRUMENTS MARKINGS
Red arc or radial line : minimum and maximum limits
Yellow arc : caution area
Green arc : normal area
FLAPS
Holding with any flaps extended is prohibited in icing conditions (except for single
engine operations);
ICING CONDITIONS
-- All icing detection lights must be operative prior to flight into icing conditions at
night.
-- The ice detector must be operative for flight into icing conditions.
Mod 5948 + 6521
2.01.05
LIMITATIONS
P4
SYSTEMS
AA
PAGE LEFT INTENTIONALLY BLANK
Mod 5948
001
FEB 12
2.01.06
LIMITATIONS
P1
001
TCAS
APR 11
AA
TCAS
LIMITATIONS
The limitations in Part 2.01 are applicable with the addition of the following:
1--
TCAS operation is approved for use in VFR meteorological conditions (VMC) and
IFR meteorological conditions (IMC).
2--
The pilot must not initiate evasive maneuvers using information from the traffic
display only or from a traffic advisory (TCAS TA) only.
These displays and advisories are intended only for assistance in visually locating
the traffic and lack the resolution necessary for use in evasive maneuvering.
3--
Compliance with TCAS resolution advisory is required unless the pilot considers it
unsafe to do so.
However, maneuvers which are in the opposite direction of the resolution advisory
(TCAS RA) are extremely hazardous and are prohibited unless it is visually
determined they are the only means to assure safe separation.
CAUTION : Once a non crossing RA has been issued the vertical speed should be
accurately adjusted to comply with the RA, in order to avoid negating
the effectiveness of a co-- ordinated maneuvre by the intruder.
WARNING : Non compliance with a crossing RA by one airplane may result in
reduced vertical separation. Therefore, safe horizontal separation
must also be assured by visual means.
4--
Evasive maneuvring should be made with the autopilot disengaged, and limited to
the minimum required to comply with the RA. The pilot must promptly return to the
previous ATC clearance when the TCAS “CLEAR OF CONFLICT” voice message is
announced.
5--
Prior to perform RA’s climb or increase climb, the crew should select the appropriate
engine power setting on the power MGT rotary selector.
6--
When a climb or increase climb RA occurs with the airplane in the landing
configuration or in the go-- around phase, a normal procedure of go-- around should
be followed including the appropriate power increase and configuration changes.
Mod 5948
2.01.06
LIMITATIONS
P2
TCAS
001
APR 11
AA
TCAS (CONT’D)
7--
Because of the limited number of inputs to TCAS for determination of aircraft
performance inhibits, there are instances where inhibiting RAs would be
appropriate, however it is not possible to do so. In these cases, TCAS may command
maneuvers which may significantly reduce stall margins or result in stall warning.
Conditions where this may occur include operations with a bank angle (wings level is
assumed), weight, altitude and temperature combinations outside those noted
below, leaving aircraft in landing configuration during climb RA on approach, engine
out operations, and abnormal configurations such as landing gear not retracted or
stick pusher/shaker failure.
The table below entitled “Flight Envelope in which climb resolution advisory can be
accomplished without stick pusher/shaker activation” outlines the parameters used
in the development of the performance inhibits. This table does not consider worst
turboprop flight conditions especially operations using minimum operating
airspeeds as are sometimes required (e.g. obstacle clearance, ATC constraints). In
all cases, stall warning must be given precedence over climb RA commands.
NOTE :
TCAS is viewed as a supplement to the pilot who, with the aid of the
ATC system, has the primary responsibility for avoiding mid-- air
collisions.
WARNING : Priority must be granted to increasing airspeed when reaching stall
warning even when this requires deviation from an RA command
issued by the TCAS.
Mod 5948
2.01.06
LIMITATIONS
P3
001
TCAS
APR 11
AA
TCAS (CONT’D)
FLIGHT ENVELOPE IN WHICH CLIMB RESOLUTION ADVISORY CAN
BE ACHIEVED WITHOUT STICK PUSHER / SHAKER ACTIVATION
FLIGHT
REGIME
G
WEIGHT
ALTITUDE
TEMP.
POWER
FLAPS
GEAR
Take off
FAR25/CS25
Take off
15
Spin up to go around
power during
maneuver from
power for level flight
AIRSPEED
INITIAL
MIN.
Up
V2 + 20
1.13 VS1g
15
UP
1.51
VS1g
1.13 VS1g
Spin up to go around
power during maneuver
from power required for
3° Glide Slope
Transition
from
30 to 15
DN
to
Up
VAPP+10
1.13 VS1g
Power for level flight
increase to Max
Continuous
Up
Up
Long
Range
Cruise
Higher of
1.13 VS1g
if defined
or buffet
onset
Climb limit
Approach
FAR25/CS25
Climb limit
Landing
Transitioning
to go around
at RA
FAR25/CS25
Enroute
Critical Wt/Alt
Climb limit
giving 1.3G to
buffet onset
Temperature range up to ISA + 27°
Altitude range
- Enroute
- Take off
- Approach and landing
Wings Level Assumed
Mod 5948
0
0
0
25000 ft
6000 ft
7000 ft
2.01.06
LIMITATIONS
P4
TCAS
001
APR 11
AA
TCAS (CONT’D)
8--
Inhibition schemes
8.1-- Non icing conditions
CONFIGURATION
RA CLIMB
RA INCREASE CLIMB
FLAPS 0
AUTHORIZED
AUTHORIZED
FLAPS 15 TO
AUTHORIZED
INHIBITED
FLAPS 15 APPROACH
AUTHORIZED
AUTHORIZED
FLAPS 30
AUTHORIZED
INHIBITED
CONFIGURATION
RA CLIMB
RA INCREASE CLIMB
FLAPS 0 Z < 20000 ft
AUTHORIZED
INHIBITED
FLAPS 0 Z > 20000 ft
INHIBITED
INHIBITED
FLAPS 15 TO
AUTHORIZED
INHIBITED
FLAPS 15 APPROACH
AUTHORIZED
INHIBITED
FLAPS 30
INHIBITED
INHIBITED
8.1-- Icing conditions
N O TE 1 :
NOTE 2 :
Mod 5948
Pilots are authorized to deviate from their current ATC clearance to
the extent necessary to comply with a TCAS resolution advisory.
Maneuvers based solely on information displayed on the traffic
display are not authorized.
2.01.06
LIMITATIONS
P5
TCAS
001
APR 11
AA
TCAS (CONT’D)
NORMAL PROCEDURES
The normal procedures in Part 2.03 are applicable.
EMERGENCY PROCEDURES
The emergency procedures in Part 2.04 are applicable.
PROCEDURES FOLLOWING FAILURES
The procedures following failures in Part 2.05 are applicable with the addition of the
following:
The TCAS must be turned TA ONLY in the following cases:
- Engine out operations
- Stick pusher/shaker failure
- Flight with landing gear down
The TCAS must be turned STBY in the following cases:
- ATC request
PERFORMANCES
The performances in Part 3 are applicable.
Mod 5948
2.01.07
LIMITATIONS
FLIGHT MANAGEMENT SYSTEM
FMS
P1
100
APR 11
AA
1 -- GENERAL
The FMS:
- complies with TSO C 129 and TSO C115B,
- is installed in compliance with, AC 20--130A for navigation use.
- has been demonstrated to meet primary means of navigation in oceanic/remote
areas in accordance with FAA Notice 8400.12B or equivalent in dual GPS
configuration.
- has been demonstrated to meet the En-- route continental B-- RNAV
requirements of AMC 20--4 or equivalent in single GPS configuration.
- has been demonstrated to meet the P--RNAV requirements of JAA TGL no10.
- has been demonstrated to meet the RNAV (GNSS) non--precision approach
requirement and RNP APCH AMC 20-- 27 specification in single GPS
configuration.
2 -- LIMITATIONS
Compliance with the above regulations does not constitute an operational
approval/authorization to conduct operations. Aircraft operators must apply to
their Authority for such an approval/authorization.
- The FMS pilot’s guide must be available on board.
- The approval of the system is based on the assumption that the navigation
database has been validated for intended use.
- In single GPS configuration, the system is approved for use for oceanic and
remote operations when only one long range navigation system is required.
- This system is approved for RNAV En--route continental (B--RNAV) and RNAV
terminal area operations like RNAV SID/STAR (P--RNAV).
NOTE : This system is approved in any of the following configurations: AP
coupling, FD only or raw data (HSI information).
- This system is also approved as a supplemental navigation means for
conventional En--route continental operations, conventional terminal operations
(SID/STAR) and conventional non--precision approach (e.g. NDB, VOR/DME,
LOC,...) provided :
S Approved navigation equipments, other than GNSS, required for the
route to be flown are installed and operational.
S When the system is used to fly non--precision approach not promulgated
as RNAV (GNSS) approach or when procedure coordinates
(SID/STAR, Approach) cannot be guaranteed as WGS84, raw data
(conventional navigation information) are displayed to verify the correct
RNAV (GNSS) guidance.
Mod : 5948 + 5965
2.01.07
LIMITATIONS
FLIGHT MANAGEMENT SYSTEM
FMS
P 1A
100
APR 11
AA
2 . 01 . 07 -- FMS (CONT’D)
- This system is also approved as a supplemental navigation means for
conventional En--route continental operations, conventional terminal
operations (SID/STAR) and conventional non--precision approach (e.g. NDB,
VOR/DME, LOC,...) provided :
S Approved navigation equipments, other than GNSS, required for the
route to be flown are installed and operational.
S When the system is used to fly non--precision approach not promulgated
as RNAV (GNSS) approach or when procedure coordinates
(SID/STAR, Approach) cannot be guaranteed as WGS84, raw data
(conventional navigation information) are displayed to verify the correct
RNAV (GNSS) guidance.
- Both single and Dual GPS configurations are approved for RNAV (GNSS)
non--precision approach provided:
SThe crew respects the published MDA (without VNAV (VDEV) credit)
SThe published approach procedure is referenced to WGS84 coordinates
or equivalent.
SBefore starting the approach, crew checks that for dual configuration at
least one GNSS is operating without GPS INTEG (on ND) or for single
configuration GNSS is operating without GPS INTEG (on ND).
SAPPR annunciation must be displayed in green on PFD for final approach.
NOTE : Pilots intending to conduct an RNP APCH procedure must fly the full
leg starting from IAF otherwise the system will not switch to APPR
mode (RNP and EHSI scale will remain at 1NM)
SRNAV (GNSS) non--precision approaches are performed only if a
non--GNSS approach procedure is available at destination or at alternate
destination.
SRNAV (GNSS) non--precision approaches must be aborted in case of GPS
INTEG on ND or UNABLE RNP on ND, and /or GPS or RNP annunciator on
MCDU.
annunciation on EHSI and/or UNABLE RNP message on MCDU
affecting the RNAV (GNSS) used for guidance.
SApproved navigation equipments, other than RNAV(GNSS), required for
the approach to be flown (at destination and at any required alternate
airport) are installed and operational.
NOTE : ILS, LOC, LOC BC, LDA, SDF and MLS approaches are not covered.
- The RNAV (GNSS) system can be used as advisory Baro--VNAV system.
NOTE : VDEV function must be permanently cross--checked by conventional
means (primary altimeters displays)
- If GNSS must be used in oceanic/remote area, B--RNAV (if DME are not
available), P--RNAV or for approach phases, the availability of the GPS integrity
(RAIM or FDE functions) must be checked by the operator using prediction tool
available in the GNSS during the pre--flight planning phase or any other
approved tool.
-
Mod : 5948 +5965
2.01.07
LIMITATIONS
FLIGHT MANAGEMENT SYSTEM
FMS
P 1B
100
FEB 12
AA
2 . 01 .07 -- FMS (CONT’D)
R 2 -- LIMITATIONS (CONT’D)
FMS predictions: Distance, time and fuel prediction deviations have been quantified
as follows:
S Climb: in the range ISA --20 to ISA +20, prediction deviations are lower than
10% and decrease to zero during climb . Outside this range, they could be
greater than 10% and decrease to zero during climb.
S Cruise: prediction deviations are lower than 5% in the whole environmental
envelope.
S Descent: prediction deviations are lower than 5% in the whole
environmental envelope.
3 -- PROCEDURES FOLLOWING FAILURE
- DUAL GPS
SFor RNAV (GNSS) non--precision approach : in the event of both GPS
INTEG alarm illuminations or if EPE increases a lot (different messages
can be triggered on MCDU), perform a go around unless suitable visual
reference is available.
SIn case of loss of navigation or navigation degradation leading to the loss
of the required navigation performance crew must inform ATC and revert to
alternate navigation means.
- SINGLE GPS
SFor RNAV (GNSS) non--precision approach, in the event of GPS INTEG
alarm illumination or if “UNABLE RNP” message occurs, perform a go
around unless suitable visual reference is available.
SIn case of loss of navigation or navigation degradation leading to the loss
of the required navigation performance crew must inform ATC and revert to
alternate navigation means.
Mod : 5948 +5965
2.01.08
LIMITATIONS
P1
CABIN LIGHTING
001
APR 11
AA
The general cabin illumination system must be used during not less than 15 minutes
before each flight.
Mod : 5948
2.01.09
LIMITATIONS
P 1
001
TAWS
APR 11
TAWS
1. Navigation is not to be predicated on the use of the terrain display.
Note :
The Terrain display is intended to serve as a situational awareness
tool only. It does not have the integrity, accuracy or fidelity on which to
solely base decisions for terrain or obstacle avoidance.
2.To avoid giving nuisance alerts, the predictive TAWS functions must be
inhibited when landing at an airport that is not included in the airport database.
3.The current local QNH must be entered in the Pilot’s altimeter for proper terrain
alerting.
4.QFE operation is not permitted in conjunction with TAWS.
Mod : 5948
2.01.10
LIMITATIONS
P 1
COCKPIT DOOR SECURITY SYSTEM
200
APR 11
AA
COCKPIT DOOR OPERATION : NORMAL PROCEDURES
This procedure should be applied, if local authorities require that the cockpit door remain
closed throughout the entire flight
Before Pushback or engine start
COCKPIT DOOR LOCKING SYSTEM SW . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON
COCKPIT DOOR CLOSED . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK
With the cockpit door toggle switch on CLOSE, the cockpit door is closed and locked.
After Engine Start
H If routine access is requested from the cabin :
The buzzer sounds in the cockpit for at least 2 seconds
Prior to unlocking the door, the flight crew should identify the person requesting entry.
H If entry is not authorized by the flight crew :
DOOR TOGGLE SW . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . DENY
Emergency access, the buzzer, and the Door Call Panel are inhibited for 3
minutes.
H If entry is authorized by the flight crew :
DOOR TOGGLE SW . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OPEN
The flight crew should pull the toggle switch and maintain it on the OPEN position,
until the cabin crew opens the door.
Note : If the flight crew does not take any action after the routine cabin request, the
cabin crew will be able to open the door by using the emergency access procedure.
H If the emergency access is initiated from the cabin :
The buzzer sounds continuously in the cockpit for 30 seconds, and the OPEN light
flashes on the central pedestal’s cockpit Door Control Panel.
Note : If the flight crew does not take any action, the door will unlock after 30 seconds.
H If entry is not authorized by the flight crew :
DOOR TOGGLE SW . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . DENY
Emergency access, the buzzer, and the Door Call Panel are inhibited for 3
minutes. When the situation in the cockpit permits, the flight crew should identify
the person requesting entry prior to unlocking the door.
H If entry is authorized by the flight crew :
DOOR TOGGLE SW . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OPEN
The flight crew should pull the toggle switch and maintain it on the OPEN position,
until the cabin crew opens the door.
Before leaving the aircraft
COCKPIT DOOR LOCKING SYSTEM SW . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF
FAULT LIGHT on Door Control Panel . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK
Mod :5948 + 5465
2.01.10
LIMITATIONS
P 2
COCKPIT DOOR SECURITY SYSTEM
200
APR 11
AA
COCKPIT DOOR OPERATION : NORMAL PROCEDURES (cont’d)
Daily Check
- COCKPIT DOOR LOCKING SYSTEM SW . . . . . . . . . . . . . . . . . . . . . . . ON
On the DOOR CALL PANEL
- EMER PB . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . PUSH
- Check OPEN LIGHT flashes
In the cockpit :
- Check buzzer
- Check OPEN LIGHT flashes
H If correct :
In the cockpit :
- TOGGLE SW on COCKPIT DOOR CONTROL PANEL . . . . . . . . . . DENY
- Check buzzer stops
- Check OPEN LIGHT extinguishes
On the DOOR CALL PANEL
- Check OPEN LIGHT extinguishes and DENIED LIGHT illuminates
H If correct :
- TOGGLE SW . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OPEN
- COCKPIT DOOR LOCKING SYSTEM SW . . . . . . . . . . . . . . . . . . OFF
- FUNCTIONAL CHECK OF THE MANUAL LOCK BOLT(S)
Mod : 5948 + 5465
2.01.10
LIMITATIONS
P 3
COCKPIT DOOR SECURITY SYSTEM
200
APR 11
AA
COCKPIT DOOR OPERATION : PROCEDURES FOLLOWING FAILURE
Electrical Power Lost
- Move the manual lock bolt to CLOSE position
- Note : when the door is locked with the manual bolt, the emergency access to
the cockpit is unavailable. It is recommended that at least two crew
members remain in the cockpit during that time.
Cockpit Door Jammed
S When cockpit exit required
- Cockpit door locking system . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF
- Remove the two locking pins (left hand edge, facing the door)
- Disconnect the electrical plug from the top of the door
- Push and remove corresponding door panel
Cockpit Door Control Panel FAULT LIGHT illuminates
- Move the manual lock bolt to CLOSE position
- Note : when the door is locked with the manual bolt, the emergency access to
the cockpit is unavailable. It is recommended that at least two crew
members remain in the cockpit during that time.
DC ESS BUS Lost
- Apply Cockpit Door Control Panel FAULT LIGHT illuminates procedure
- Note : Cockpit Door Control Panel FAULT LIGHT is inoperative.
Mod : 5948 + 5465
2.01.10
LIMITATIONS
P 4
COCKPIT DOOR SECURITY SYSTEM
200
APR 11
AA
COCKPIT DOOR OPERATION : OPENING THE COCKPIT DOOR FROM THE CABIN
CABIN CREW ROUTINE ACCESS . . . . . . . . . . . . . . . . . REQUEST on the Door Call Panel
CABIN CREW . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . PRESS CALL PB
CABIN CREW . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . STAND IN COCKPIT DOOR AXIS
The cabin crew should stand in the axis of the cockpit door.
A buzzer sounds in the cockpit.
H If entry is not authorized by the flight crew :
The flight crew denies the entry request via the DOOR TOGGLE SW.
The Door Call Panel red light comes ON steady, and indicates that the door is locked.
Emergency access, the buzzer, and the Door Call Panel are inhibited for 3 minutes.
H If entry is authorized by the flight crew :
The flight crew unlocks the door via the DOOR TOGGLE SW.
The Door Call Panel green light comes ON steady, and indicates that the door is
unlocked.
CABIN CREW . . . . . . . . . . . . . . . . . . . . . . . PULL the DOOR RIGHT PANEL to OPEN
CABIN CREW . . . . . . . . . . . . . . . . . . . UNLOCK the LEFT PANEL and PULL to OPEN
The door left panel is unlocked by moving the handle located in the cockpit side on the
door left panel
H If there is no reaction from the flight crew :
CABIN CREW SECOND ACCESS REQUEST . . . . . . REQUEST on the Door Call Panel
Repeat the above procedure.
H If there is no reaction from the flight crew after a second request :
CABIN CREW . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CALL THE COCKPIT
To establish contact with the flight crew and request access to the cockpit.
H If there is no reaction from the flight crew after a cabin crew interphone call :
CABIN CREW . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . PRESS THE EMERGENCY PB
Rotate the protecting plate and press the EMER PB. A buzzer sounds continuously in
the cockpit for 30 seconds, and the green light flashes on the Door Call Panel. After 30
seconds, the green light comes ON steady and the cabin crew can then pull the door
right panel to open and the buzzer stops.
This indicates that the door is unlocked for 10 seconds.
CABIN CREW . . . . . . . . . . . . . . . . . . . . . . . PULL the DOOR RIGHT PANEL to OPEN
CABIN CREW . . . . . . . . . . . . . . . . . . . UNLOCK the LEFT PANEL and PULL to OPEN
The door left panel is unlocked by moving the handle located in the cockpit side on the
door left panel
Mod : 5948 + 5465
2.02.00
PROCEDURES AND TECHNIQUES
P1
CONTENTS
001
DEC 13
AA
2.02.00
CONTENTS
2.02.01
OPERATING SPEEDS
2.02.02
DATA CARD
2.02.03
AIR
2.02.04
AFCS
2.02.05
ELECTRICAL SYSTEM
2.02.06
FLIGHT CONTROLS
2.02.07
FUEL SYSTEM
2.02.08
ADVERSE WEATHER
2.02.09
LANDING GEAR/BRAKES
2.02.10
FLIGHT PATTERNS
2.02.11
POWER PLANT
2.02.12
FLIGHT CHARACTERISTICS
2.02.13
Reserved
2.02.14
FLIGHT INSTRUMENTS
2.02.15
TCAS
2.02.16
TAWS
2.02.17
Reserved
2.02.18
FMS
2.02.19
HIGH LATITUDES OPERATIONS
2.02.20
Reserved
2.02.21
MPC Multi Purpose Computer
2.02.22
ACARS Aircraft Communication Addressing and Reporting System (*)
2.02.23
VIDEO CABIN SYSTEM (*)
2.02.24
DU, General Philosophy of use
R 2.02.25
Mod : 5948
ADS- B Out
(*) : if installed
2.02.01
PROCEDURES AND TECHNIQUES
P1
OPERATING SPEEDS
100
FEB 12
AA
GENERAL
- Older certification rules used as a reference the minimum speed which was recorded
during defined stall penetration.
This speed was established with a load factor lower than 1g. It was used as reference for all
operational speeds.
(example V2 = 1.2 Vsmin, VREF = 1.3 Vsmin).
- New certification now uses as a reference THE ONE G STALL SPEED VSR which is
typically 6 % greater than Vsmin.
- In order to provide the same practical maneuver margin, the factors applied to VSR
have been changed to reflect the increased value of VSR relative to Vsmin.
1.2 applied to Vsmin becomes 1.13 when applied to VSR
1.25 applied to Vsmin becomes 1.18 when applied to VSR
1.3 applied to Vsmin becomes 1.23 when applied to VSR
- The ATR 72-- 212A having been certificated to the new rules, the reference stalling
speed called VSR is determined as a one G stall speed and the new (reduced) factors
apply accordingly.
MAN / AUTO SPEED philosophy
The avionic suite (from L2B2 upgrade version) provides 2 selectable speeds:
- AUTO speed: (displayed in magenta on PFD speed scale) is the managed speed
computed by the FMS and depends on: flaps lever, power management, normal and
icing conditions, number of operational engines, (...)
This managed speed ensures safe speeds to operate the aircraft in all flight phases.
AUTO speed is upper limited by maximum speed (Vmax) and lower limited by
operational minimum speed (Vmin Ops).
Note: Refer to 1.10.22 for more details on PFD indications.
- MAN speed: (displayed in cyan on PFD speed scale) is the pilot manual selected
speed.
Mod : 5948 + 6521
2.02.01
PROCEDURES AND TECHNIQUES
P2
OPERATING SPEEDS
001
NOV 14
AA
DEFINITIONS
VSR
1 g stall speed for a specified configuration. It is a function of the
aircraft weight.
VMCG Minimum control speed on the ground from which a sudden failure of the
critical engine can be controlled by use of primary flight controls only, with the
other engine operating at RTO power.
V1
Speed at which the pilot can make a decision following failure of critical
engine:
. either to continue take-- off
. or to stop the aircraft
VR
Speed at which rotation is initiated to reach V2 at 35 ft height.
V2
Take off safety speed reached before 35 ft height with one engine failed and
providing second segment climb gradient not less than the minimum (2.4 %).
VMCA Minimum control speed in flight at which the aircraft can be controlled with
5° bank, in case of failure of the critical engine with the other engine at RTO
power (take off flaps setting and gear retracted.)
VMCL
Minimum flight speed at which aircraft can be controlled with 5° bank in case of
failure of the critical engine, the other being set at GA power (landing flaps
setting, gear extended) and which provides rolling capability specified by
regulations.
VFE
Maximum speed for each flaps configuration
Vmin OPS Minimal flight speed according to flying conditions and aircraft configuration.
R VGA :
Mod : 5948
Go Around Speed ( Refer to page p004)
2.02.01
PROCEDURES AND TECHNIQUES
P3
001
OPERATING SPEEDS
APR 11
AA
MINIMUM MANEUVER/OPERATING SPEEDS
Minimum maneuver/ operating speeds are defined in order to provide sufficient margin
against stall. They will vary with :
-
Normal or icing conditions,
weight,
configuration,
type of maneuver (HI or LO BANK).
They are defined by a minimum ratio to the appropriate stall speed given in FCOM
2.01.03 or by V2 when applicable.
NORMAL CONDITIONS
FLAPS
VmHB
0
15
VmLB
1.18 VSR
1.23 VSR and not less than
VMCL during approach
30
V2
Not used
Note : Refer to 2.02.08 for icing conditions.
UTILIZATION
- VMLB is the absolute minimum maneuver speed.
This speed
* is used for take off, and initial climb.
* must be used EN ROUTE FOR OBSTACLE LIMITED SITUATIONS (refer to chapter
3.09)
* should be used in flaps 0 configuration to obtain the best climb gradient.
In all these cases, bank angle must be restricted to 15° .
- VmHB is the minimum speed used for approach. It also provides the best two engines
rate of climb.
In this case, bank angle must be restricted to 30° .
The speeds and bank angles are automatically calculated by the FMS according to weight
and atmospheric conditions and displayed on the PFDs. These speeds are also available
in a pilot oriented manner as operating data booklet in the Quick Reference Handbook, in
which relevant maneuver/operating speeds are directly given for all weights.
Mod : 5948
2.02.01
PROCEDURES AND TECHNIQUES
P4
OPERATING SPEEDS
100
NOV 14
AA
CONSERVATIVE MANEUVERING SPEEDS
When performance consideration does not dictate use of minimum
maneuver / operating speeds, the following conservative maneuvering speeds are
recommended.
They cover all weight, for high bank operational maneuver, at all flight condition ( normal
and icing condition)
Flaps 0 : 180 kt.
Flaps 15 : 150 kt.
Flaps 30 : 135 kt.
FINAL APPROACH SPEED
VAPP = VmHB + WIND FACTOR
or VMCL, whichever is higher
WIND FACTOR = The highest of
- 1/3 of the head wind velocity,
- or the gust in full,
with a maximum wind factor of 15 kt.
Wind factor is added to give extra margin against turbulence, risk of wind shear etc...
ATR philosophy is to perform all approaches using speed auto mode.
GO AROUND SPEED VGA
R Normal conditions : 1.23 VSR flaps 15° or 1.1 VMCA whichever is higher.
R Icing conditions : 1.24 VSR flaps 15° or 1.1 VMCA whichever is higher.
MINIMUM SPEED FOR FLAPS RETRACTION
It is VmLB of the next flap setting.
Example :
- Minimum speed to retract flaps from 15 to 0 : VmLB0.
Mod 5948 + 6521
2.02.02
PROCEDURES AND TECHNIQUES
P1
DATA CARDS
AA
Mod : 5948
001
APR 11
APR 11
Mod 5948
2.02.03
PROCEDURES AND TECHNIQUES
P2
080
AIR
FEB 12
AA
AIR CONDITIONING
When operating from airfields with high OAT, it is essential to cooldown the cabin
before boarding passengers: this is best achieved by use of a ground conditioning
unit, but may also be done through the use of Hotel Mode, and in that case the following
R considerations will be applied :
- as soon as OAT exceeds 22° C and aircraft has remained exposed to direct sun,
PRE-- CONDITIONING becomes necessary for passengers comfort, prior to boarding;
- allow a reasonable period of time for pre-- conditioning, and use up to
MAXIMUM POWER AVAILABLE ON R/H ENGINE (GUST LOCK STOP) together with
HI FLOW selection.
Note 1: HI FLOW is very effective when R/H PL is advanced beyond Gl.
Note 2: Proper orientation of the aircraft on Parking area (wind blowing from 10
o’clock ideally) during Hotel Mode pre--conditioning is very favorable as it
gives better efficiency and allows to continue pre--conditioning during AFT
CARGO loading (hot air from RH engine exhaust blown away from service
door).
- If for any reasons, it has not been possible to bring cabin temperature down to
comfortable values prior to boarding, the following considerations will apply :
⋅ Packs operation during taxi should be performed with HI FLOW selected.
⋅ Switch FLOW selection to NORM prior to take-- off, but keep bleeds on, unless
performance limited.
⋅ As soon as CLB POWER is selected after take off, select HI FLOW and maintain HI
FLOW until comfortable cabin temp is obtained.
⋅ During cruise, monitor cabin temp when operating in NORM FLOW : if cabin temp
tends to increase again above comfortable values, use HI FLOW as necessary.
TEMP CONTROL
Temperature control is normally achieved in AUTO MODE, which incorporates all
necessary protections to avoid damage to packs turbines due to freezing.
In case of duct overheating, manual mode is recommended.
As manual mode does not incorporate the protections of AUTO MODE, the following
R considerations must be applied:
- Do not use temperature selector in manual mode unless auto mode is inoperative.
- When in manual mode, monitor duct temperature and adjust rotary selector to maintain
positive duct temp : this is essential to avoid pack freezing.
Mod : 5948 + 3037
APR 11
Mod 5948
APR 11
Mod 5948
2.02.04
PROCEDURES AND TECHNIQUES
P1
AFCS
001
FEB 12
AA
GENERAL
The ATR 72 with Mod 5948 is equipped with a Thales AutoPilot/Flight Director.
Systematic use of AP/FD is recommended in order to :
- Increase the accuracy of guidance and tracking in all weather conditions, from early
climb after take off down to landing minima.
- Provide increased passenger comfort through SMOOTH AND REPEATABLE altitude
and heading changes in all atmospheric conditions.
- Reduce crew workload and increase safety.
MAIN RULES OF USE
D AP and YD cannot be engaged on ground : any attempt to do it will result in the
message “YD INHIB” on FMA;
D FD is available on ground as soon as DC normal buses are powered, but FD bars are in
sight only if :
R - One upper mode is selected (Green indication on FMA).
- FD ON/OFF push button on FGCP is ON.
Note :
Mod : 5948
- FD ON/OFF push buttons, one on Left side and one on Right side act
only on FD DISPLAYS (FD Bars)
Left push button allows selection/deselection on Left side only. Right
push button allows selection/deselection on Right side only.
- STBY push button on FGCP deactivates all active and armed upper
modes.
- If Auto Pilot is ON, Basic Mode with associated bars are displayed.
2.02.04
PROCEDURES AND TECHNIQUES
P2
AFCS
100
FEB 12
AA
D The references to be flown may be coupled to left or right side by the CPL push button.
Changes of CPL side while coupled to VOR, LOC, or LNAV will revert to basic mode.
D Modes are engaged (green indication on FMA) or armed (Cyan indication on FMA) by
action on the relevant push button on FGCP.
FMA must be monitored for actual state of modes of AP/YD :
A second push on the push button associated to a mode already
engaged (or armed) disengages (or disarms) it and revert to basic
mode.
Lateral mode revert to ”Heading Hold”, Vertical mode revert to ”Pitch
Hold”
D ALT SEL mode is automatically armed as soon as the flight path is directed towards
the altitude set on PFD via FGCP. All altitudes clearance given by ATC should
systematically be set on PFD via FGCP to ensure automatic level off when AP is
engaged (or FD followed in case of manual fliying).
Note : After ALT mode has been engaged, the aircraft remains in level flight on the new
barometric setting.
D When HDG changes are performed, maximum bank angle is automatically selected
by the system. If the aicraft is below 1000ft or if IAS<VmHB, the AFCS system can
command at most 15°. Otherwise the system can command 27°.
This allows AFCS maneuvring in all conditions, including early climb after take-- off or go
around where speed may be down to Vmin OPS (Vm LB).
Mod : 5948 + 6521
2.02.04
PROCEDURES AND TECHNIQUES
P3
AFCS
100
FEB 12
Note : The Yaw AutoTrim function allows the AFCS to control the airplane in case of
engine failure inside all the airspeed domain.
D LATERAL TRIM with auto-- pilot engaged
- Trim on ROLL axis is inhibited when there is no RETRIM ROLL request set on FMA..
- As there is an auto-- trim on PITCH and YAW axis, no trim is required during the flight in
normal condition (without engine failure or aircraft dissymetry), in specific condition
the autopilot will indicate only roll out of trim.
- If roll trim is required : a message :
“RETRIM ROLL L(R) WING DOWN” is displayed on FMA, and on the roll trim indicator
a cyan arrow indicating in wich direction (left/right) trim is required.
- If excessive lateral trim increased and last, or AILERON MISTRIM message is
displayed on FMA :
⋅ DISCONNECT AP, HOLDING FIRMLY THE CONTROLS.
⋅ FLY MANUALLY PRIOR TO ADJUSTING LATERAL TRIMS.
⋅ The auto pilot may be reengaged following adjustment of the lateral trims.
- If If Yaw AutoTrim is failed, the system can request yaw trim with the following message
:”RETRIM AIRCRAFT NOSE LEFT/RIGHT” is displayed on FMA, and on the yaw trim
indicator a cyan arrow indicating in wich direction left/right trim is required.
D AUTO PILOT/YD DISCONNECT
Auto pilot may be disconnected by :
-
Quick disconnect push buttons on each control wheel
Action on normal or STBY Pitch Trims
AP push button on FGCP
YD push button on FGCP
GA push buttons on Power Levers
Pilot input on left or right rudder pedals over 30 daN (66 lb)
Pilot input on the control column (push or pull on pitch axis) over 10 daN (22 lb)
Yaw Damper and consequently AP, may be disconnected by :
- YD push button on FGCP,
- Pilot input on left or right rudder pedals over 30 daN (66 lb)
- At touch down when landing.
CAUTION : Overriding the Autopilot on roll axis will not lead to A/P disconnection.
The QUICK DISCONNECT push button is recommended for all normal AP disengagement
as it leaves the YD engaged.
A second push on the QUICK DISCONNECT pb will also cancel both audio and visual
AUTO PILOT OFF warnings.
Depressing the TCS push-- button allows to regain temporary manual control of the aircraft
without disconnecting the AP.
Mod : 5948 + 6521
2.02.04
PROCEDURES AND TECHNIQUES
P4
AFCS
100
FEB 12
AA
Note : Function of AP/YD are monitored on three axes.
When a monitored failure is detected, the AP/YD disengages and failure message is
displayed on FMA (AP/YD invalid or AP invalid). A new re-- engagement is possible only
if the failure message disappears.
TYPICAL AP/YD operation
D TASK sharing
- With AP engaged, PF will select references and modes.
- With FD only (AP not engaged) PF will call for references and modes to be set by PM.
D BEFORE TAKE OFF
-
Both FD ON
First cleared altitude set on PFD.
HDG bug checked on RWY HDG.
NAV Mode may be armed if SID is available in FMS.
IAS mode selected with AUTO mode (the FMS commands automatically V2+5).
D TAKE OFF
- As power is increased, lateral guidance FD bar remains centered as runway heading
is maintained, and if LNAV was preselected, LNAV Mode becomes active at 20 kt.
Vertical guidance FD bar stays at 8°
- Rotation is initiated to the recommended value (θ኏8°) as indicated by FD vertical
guidance bar.
- 5 seconds after lift-- off, AP may be engaged : it synchronizes on FD command and
maintains HDG or LNAV if selected and IAS.
- Turn may be initiated as required using HDG sel knob or according to LNAV Mode.
- When acceleration altitude is reached, setting CLB Power according to standard
climb procedure increases the speed Bug automatically to climb speed if in SPEED
BUG AUTO Mode.
If in SPEED BUG MAN Mode, the speed Bug must be set to required climb speed
through the speed target selector on ICP.
Mod : 5948 + 6521
2.02.04
PROCEDURES AND TECHNIQUES
P5
AFCS
001
DEC 13
AA
• CLIMB
Use IAS mode with climb speed set through the speed target selector on the ICP. IAS
should be preferred to VS mode, unless a vertical speed constraint is given by ATC.
R
CAUTION : The crew must always monitor IAS carefully , especially in VS and PITCH
modes as well as during ALT* phase.
Notes : 1. During climb in VS or PITCH mode with a rate exceeding the aircraft performance
the airspeed will continuously decrease.
2. When climbing in turbulences and/or vertical wind gradient conditions. ALT* mode
can be engaged with a VS exceeding the A/C performance capability , and then IAS
may significantly decrease before reaching the selected Altitude.
3. In both cases , AP will disengage automatically when stall alert is activated.
• LEVEL OFF
- Level off is automatic when reaching the selected altitude.
- Power must be adjusted to the new condition.
• RESUME CLIMB OR DESCENT
-
First, the new cleared altitude must be set on PFD.
For descent, engage IAS or VS mode.
For climb, engage preferably IAS mode.
In both cases, adjust power as necessary.
Mod : 5948
2.02.04
PROCEDURES AND TECHNIQUES
P6
AFCS
001
APR 11
AA
D NAVIGATION
HDG and NAV mode for VOR approach are used as required (Refer to FCOM 1.04)
Note : - Accuracy of VOR guidance is significantly improved when there is a DME
associated with the VOR.
Accuracy decreases if NAV VOR is engaged in DME HOLD mode.
D ILS approach mode
Before approach :
-
Select V/ILS source (on FGCP) on coupled (CPL) side.
Set approach course on HSI with CRS selector and tune ILS frequency.
Use HDG SEL mode to set appropriate intercept heading.
Arm both LOC and GS by depressing APP pb on FGCP.
Set SPEED BUG AUTO mode
(SPEED BUG AUTO Mode is recommended as much as possible, nevertheless
SPEED BUG MAN Mode may be used)
Note :
- LOC beam capture must be started (LOC* green on FMA before GS capture can take
place).
- LOC beam capture may lead to one initial overshoot when the capture conditions are
severe (Intercept Heading = RWY HDG ¦ 90°, high IAS, reduced distance to the ILS
transmitter), but, provided the distance is at least 5 Nm at the standard instrument
capture speed of 180 Kts, this initial overshoot will be followed by an asymptotic
capture without further oscillation, even with a 90° intercept angle.
- The bank angle limit is automatically set following speed versus VMHB (15° or 27°).
- When LOC capture is started:
Set RWY HDG with HDG bug
Set ILS frequency and set/check V/ILS source (on FGCP) on PM
side, check ILS course on PM side
- When GLIDE beam capture (G/S* green on FMA):
First Check glide validity (according approach chart)
Set Go around altitude
Mod : 5948
2.02.04
PROCEDURES AND TECHNIQUES
P7
001
AFCS
APR 11
AA
D NON PRECISION APPROACH
Use of auto-- pilot is recommended with :
- NAV mode for VOR or GNSS approach or LOC,
- HDG SEL mode for NDB approach,
- VS or IAS mode for descent.
D GO AROUND
When reaching decision height, or missed approach point after level off at MDA, if
required visual references are not established, a go-- around must be initiated.
The following procedure is recommended :
-
PF
(if no visual reference)
Announce”GO AROUND,
FLAPS ONE NOTCH, SET POWER”
Depress GA pbs on PLs
Advance PLs to the ramp
Rotate to GO AROUND
pitch attitude
Follow FD bars and cancel
AP Disconnect Alarm
Accelerate to or maintain
VGA (2-- 02-- 01 p4)
- Command “GEAR UP“
When climb is stabilized :
- Command “HDG/IAS“
Engage AUTO PILOT
PM
- Announce “Minimum”
- Retract FLAPS one notch
- Check NP= 100 %, adjust
if necessary
When positive rate of climb is
achieved :
- Announce “Positive rate”
- Set gear up
- Engage HDG and IAS MODE on FGCP
(if in IAS MODE+SPEED BUG AUTO
mode IAS Bug is automaticaly set to Go
Around speed
If in IAS mode+SPEED BUG MAN
mode, IAS Bug must be set manualy to
Go Around speed)
Note : GO AROUND mode gives (as a FD mode only):
- on pitch axis, a target attitude compatible with single engine performance.
- on roll axis, a steering command to maintain heading followed at GA
engagement or the FMS flight PLAN if LNAV was previously engaged.
As soon as climb is firmly established, and IAS>VminOPS use of HDG SEL / IAS
MODE+ Speed AUTO mode is recommended.
Mod : 5948
2.02.04
PROCEDURES AND TECHNIQUES
P8
AFCS
001
APR 11
AA
CAT 2 OPERATIONS
" GENERAL
CAT 2 approaches are flown with AP + FD ON.
" EQUIPEMENT REQUIRED
Approach with AP
Autopilot
1
COURSE rotary selector
2
AP quick disconnect
AP OFF warning (aural)
1 (PF side)
1
ILS receiver
2
AHRS
2
IESI
1
PFD
2
Radio altimeter
DH indicator
1 (with 2 displays)
2
GA pushbutton
1 (PF side)
Windshield wipers
1 (PF side)
Yaw damper
1
ADC
2
Hydraulic system
Blue + Green
Electrical system
DC: BUS1 / BUS2 / EMER / STBY / ESS ;
AC: BUS1 / BUS2 / STBY ; ACW: BUS1 / BUS2
MFC modules
Mod : 5948
3
2.02.04
PROCEDURES AND TECHNIQUES
P9
AFCS
AA
001
APR 11
Maximum demonstrated crosswind:
AutoPilot
Headwind
29 kt
Tailwind
10 kt
Crosswind
17 kt
" TASK SHARING
The philosophy of the task sharing is based on the following considerations:
- PF(!) task is aircraft flying during all the approach, he is in charge of speed
control. Approaching DH + 100ft, he looks outside to acquire visual references.
He makes decision for landing or go-- around.
- PM (@) task is approach monitoring with permanent reference to the instruments.
(!)PF, pilot flying,
- Monitors the A/C position, the flight path parameters and the AP.
- Controls the speed.
- Requests checklist, flaps setting and gear extension.
- Selects the modes and announces changes.
(@)PM, pilot monitoring,
- Is in charge of radio communications.
- Monitors the flight path, the speed, the mode changes, the systems and
the engines.
- Reads the checklist.
- Selects flaps setting and gear extension.
"
NORMAL APPROACH AND LANDING SEQUENCE
J
Prior to approach
D
BEFORE DESCENT, DESCENT, APPROACH AND BEFORE
LANDING PROCEDURES : SEE NORMAL PROCEDURE
... / ...
Mod 5948
2.02.04
PROCEDURES AND TECHNIQUES
P 10
001
AFCS
AA
J
APR 11
Before capture
D
PF has to perform the following tasks:
- NAVAIDS set to ILS frequency, ADF set as required.
- CRS set to final approach course.
- APP armed.
- SPEED BUG AUTO mode recommanded.
D
PM has to perform the following task:
- NAVAIDS and ADF set as required
From capture to decision height
Note: The call-- outs are written in bold with “ ...”.
Tasks and call- outs
CAT 2 events
PF
J
Localizer capture
Glide slope capture
“LOC STAR”
“GS STAR”
(!): Outer marker Check altitude on RA and altimeter,
or equivalent posi- and if aircraft is stabilized
tion (not lower
“WE CONTINUE”
than 1000ft)
Check dual coupling and no star on LOC
and G/S modes
“CHECK”
500 ft RA
DH + 100 ft RA
- Set runway HDG
- Set ILS freq
- Set/check V/ILS source (on
FGCP)
- Set/check ILS CRS
- Check CAT 2 on FMA
Set GA altitude
Check GA altitude
Request normal sequence for
LDG configuration
800 ft RA (#)
PNF
Set LDG configuration in sequence
“OUTER (!) ALTITUDE
CHECKED, STABILIZED(@)”
Check altitude on RA and altimeter and if aircraft stabilized
“800 FT, DUAL CPL, NO STAR“
Check dual coupling and no star
on LOC and G/S modes
“500”
Looks outside for visual references
DH / auto call-- out
“100 ABOVE”
Monitors the instruments
“DECISION”
(@): Stabilized means:
- On the final approach segment flight path.
- Landing flaps selected, VAPP reached.
- Final checklist completed.
(#): Any failure that is not completely treated before 800ft AGL, or that occurs
below 800ft AGL shall always lead to a missed approach.
Mod. : 5948
2.02.04
PROCEDURES AND TECHNIQUES
P 11
AFCS
001
APR 11
AA
J
If visual references sufficient
Tasks and call- outs
CAT 2 events
Visual at DH
80 ft RA
PF
PM
“LANDING”
Disconnect AP
50 ft RA
“80”
80
“50”
20 ft RA
“20”
Reduce PL and flare
J
Mod : 5948
If visual references insufficient, apply GO AROUND NORMAL procedure.
(2.03.20)
2.02.04
PROCEDURES AND TECHNIQUES
P 12
AFCS
001
APR 11
AA
D If APP P/B is engaged without an ILS frequency tuned on the coupled side, the APP
mode will not arm and the FMA will display a caution message : “CHCK NAV SRC”. In
this case, tune ILS and reengage APP mode.
D As soon as LOC“*” mode is displayed, the approach capability (as seen by
the AFCS computer), will be displayed on FMA (CAT I or CAT II).
D TRACK phase, for both LOC and GS (indicated by LOC and GS green without *)take
place automatically when the aircraft is on the beam. The transition to DUAL CPL
intervenes at 1200ft.
The standard deceleration procedure described above, normally allows to
reach 800 ft RA after LOC and GS TRACK phases have been achieved. If
it is not the case (excessive initial speed, etc.), new proper capture has to
be made. If late capture, the dual coupling engagement is impossible.
D Excess deviation is armed :
- below 300 ft for LOC
- between 300 ft and 100 ft for GS.
Any excess deviation appearance must be announced by PM (call “DEVIATION”).
This call must lead to :
- AP disconnection by PF
- Go around decision if visual references are not sufficient.
D AP/FD behaviour must be permanently monitored by PM. In case of anomaly
(sustained input not justified by LOC and GS deviations , excessive attitude*), the
PM must immediately call “ GUIDANCE ”.
This call must lead to :
-- AP disconnection by PF
- Go around decision if visual references are not sufficient.
* excessive attitude means
bank angle > 10°
pitch attitude < --4°
> +4°
- In case of “GUIDANCE” or “DEVIATION” callout by PM, (or AP
disconnection without visual references), a Go Around must be performed. If no
discrepancy is detected on PFD (CHECK ATT messages) PFD can be used with IESI
monitoring to set the initial missed approach attitude.
Mod : 5948
APR 11
Mod 5948
APR 11
Mod 5948
2.02.06
PROCEDURES AND TECHNIQUES
P1
FLIGHT CONTROLS
001
APR 11
ATR 72 is equipped with classical mechanical primary flight controls on all three axis.
The following peculiarities must be highlighted :
Mod 5948
2.02.06
PROCEDURES AND TECHNIQUES
P2
FLIGHT CONTROLS
001
APR 11
AA
PITCH : Both elevators are connected through a pitch uncoupling device, in order to
leave sufficient controllability in case of mechanical jamming of one control surface.
Activation of this device :
- requires heavy forces (52 daN/114 Ibs) to be applied to the control columns,
which minimizes the risk of untimely disconnection.
- indicated to the crew through the red warning « PITCH DISC » on the EWD.
- allows the flight to be safely achieved : refer to procedures following failures.
Note 1 : WHEN PITCH DISCONNECT takes place WITHOUT REAL JAMMING, speed
has to be limited to 180 kt and bank angle to 30° until flaps extension to avoid
overstressing the stabilizer.
Note 2 : The TWO yokes must be held once the aircraft is landed.
Once disconnected both elevators can be reconnected by applying the following
procedure:
BOTH ELEVATORS RECONNECTION ON GROUND
Conditions:
- Aircraft on ground and electrically powered.
- Both elevators disconnected.
- Red PITCH DISC alarm illuminated steady on EWD.
Procedure:
- Engage GUST LOCK and check both columns are locked.
- Depress and hold ELEV CLUTCH guarded pb (see 1.09.30) until PITCH DISC
flashes red on EWD.
- Release ELEV CLUTCH pb. After a few seconds, PITCH DISC extinguishes on EWD.
- Check both columns are effectively coupled.
Mod. :5948
2.02.06
PROCEDURES AND TECHNIQUES
P3
FLIGHT CONTROLS
001
APR 11
ROLL :
D Aileron spring tabs :
Flight controls are connected to the ailerons through the spring tabs, therefore,
maintaining the flight controls to neutral on the ground would not prevent the ailerons
from oscillating in case of strong tail wind (> 30 kt).
Therefore, in strong wind conditions it is recommended :
- to disengage the gust lock only when necessary before take off,
- after landing, to engage the gust lock before a turn that would expose the aircraft to
a tail wind component.
If aileron lock is not available, it is easier to maintain the ailerons fully deflected.
D Aileron trim :
Ailerons forces trimming is obtained by shifting the zero position of the left aileron
spring tab : this means that AILERON TRIM INDICATOR is only representative of the
differential loading of the spring tab and not of the aileron position.
Mod. : 5948
2.02.06
PROCEDURES AND TECHNIQUES
P4
FLIGHT CONTROLS
100
FEB 12
YAW: The rudder incorporates several particular features.
D The releasable centering unit (threshold cam) :
This threshold cam automatically synchronizes to actual rudder pedal position each
time the rudder trim switch is activated.
Therefore before take-- off, rudder trim setting to zero must be made with rudder pedals
in neutral position.
D The rudder surface damper :
Structural protection of the rudder assembly against effect of wind gusts on ground is
ensured by a rudder surface damper, which is designed to prevent excessive speed of
deviations of the rudder surface.
When taxiing with strong winds, very large rudder forces would be required to control
the rudder surface: this is not necessary and rudder should be left « floating » in the
wind as the damper will effectively prevent any structural damage.
D The rudder trim :
Rudder forces trimming is obtained by shifting the zero position of the spring tab: this
means that « RUDDER TRIM INDICATIONS » are only representative of the
differential loading of the spring tab, AND NOT OF THE RUDDER POSITION.
Note : As speed increases, rudder trim deviation as large as 3 dots on the right may be
noted while rudder surface remains substantially at neutral.
D The yaw damper :
Yaw damper function is provided through the YAW CHANNEL of the AP and should
always be engaged in flight to improve passenger comfort.
The yaw damper provides in addition a sideslip cancellation function: its goal is to
keep the side slip indication centered. To automatically reducedl the sustained rudder
effort induced, the AFCS provides a Yaw Auto Trim function, engaged as soon as the
Yaw Damper is engaged.
In order to let the rudder axis free for pilot inputs (engine failure) without the need to
disconnect the YAW DAMPER on the FGCP, a force sensor has been implemented
and any pilot force exceeding 30 daN/66 Ibs applied on rudder will cause the YD
disengagement.
Mod 5948 + 6521
2.02.06
PROCEDURES AND TECHNIQUES
P5
FLIGHT CONTROLS
001
APR 11
AA
In order to avoid exceeding structural loads on the rudder and vertical stabilizer, the
following recommendations must be observed.
1) THE RUDDER IS DESIGNED TO CONTROL THE AIRCRAFT, IN THE FOLLOWING
CIRCUMSTANCIES:
a) In normal operations, for directional control
- During the takeoff roll, especially in crosswind condition.
- During landing flare with crosswind, for decrab maneuver.
- During the landing roll.
- The rudder may be used as deemed necessary, for turn coordination to prevent
excessive sideslip.
b) To counteract thrust asymmetry
Full rudder authority can be used to compensate for the yawing moment of asymmetric
thrust.
Note : at high speed (i.e. flaps up), thrust asymmetry (i.e. due to an engine failure) has
relatively small effect on lateral control of the aircraft. The amount of rudder
required to counter an engine failure and center the sideslip is small.
c) In some other abnormal situations
The rudder may also be used in some abnormal situations such as:
- Runaway rudder trim. The rudder pedals may be used to return the rudder to neutral.
- Aileron jam. The rudder may be used to smoothly control the roll.
- Landing gear unsafe indication (gear not downlocked). When a main landing gear is not
downlocked, the rudder may be used to establish sideslip in an attempt to downlock the
landing gear by aerodynamic side forces.
- Landing with landing gear not downlocked. The rudder can be used for directional control
on ground.
In all these normal or abnormal circumstances, proper rudder maneuvers will not affect
the aircraft’s structural integrity.
2) RUDDER SHOULD NOT BE USED:
- To induce roll, except in the previous case( Aileron jam) or
- To counter roll, induced by any type of turbulence.
Whatever the airborne flight condition may be, aggressive, full or nearly full, opposite
rudder inputs must not be applied. Such inputs can lead to loads higher than the limit, or
possibly the ultimate loads and can result in structural damage or failure.
Note : Rudder reversals must never be incorporated into airline policy, including
so-- called “aircraft defensive maneuvers” to disable or incapacitate hijackers.
As far as dutch roll is concerned, yaw damper action (if selected) or RCU (Releasable
Centering Unit) are sufficient to adequately dampen dutch roll oscillations. The rudder
should not be used to complement the yaw damper action.
Mod 5948
2.02.07
PROCEDURES AND TECHNIQUES
P1
FUEL SYSTEM
001
APR 11
AA
FUEL CROSSFEED
Allows feeding of 1 or 2 engines from either side tank, especially for fuel balancing.
PROCEDURE :
Intended tank to be used :
PUMP RUN and OFF LT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . extinguished
X FEED . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . IN LINE
Opposite tank :
PUMP . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF
When asymmetrical feeding is completed:
PUMPS both . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON
X FEED . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . X LINE
R Note: Each electrical pump is able to supply one engine in the whole flight
R
envelope.
R
One electrical pump and associated jet pump are able to supply both engines in
R
the whole flight envelope.
R
When X FEED is selected « in line », both electrical pumps are forced to run
R
(both RUN lights illuminate green) as long as associated PUMP pb is selected
ON.
R
CAUTION : When X FEED procedure is applied, some fuel transfer from the wing tank
where the pump is running to the other wing tank (where the pump is OFF)
may occur. This transfer is particularly noticeable at low power settings (X
FEED in Hotel mode is the worst case).
FUEL QUANTITY INDICATIONS
IN FLIGHT
Accurate readings require aircraft levelled without side slip and pitch attitude close to zero
degree.
ON GROUND
Accurate readings should be made with aircraft static (not taxiing) and fuel pumps running
for more than 4 minutes.
This procedure should be applied each time a comparative reading before and after flight
is intended with correlation to fuel used.
COMMENTS
- Fuel quantity indications are affected by excessive longitudinal and lateral attitudes
and accelerations.
- Fuel quantity indications are affected by the level of fuel in the feed tank. With pumps
running, the feed tanks are filled within a few minutes. This is the normal flight case.
Mod 5948
2.02.08
PROCEDURES AND TECHNIQUES
P1
ADVERSE WEATHER
001
APR 11
This chapter is divided in 4 parts :
- Icing
- Cold weather operations,
- Operations in wind conditions.
- Volcanic Ash encounter
ICING
I - GENERAL
Icing conditions are defined as follows :
" Atmospheric icing conditions
Atmospheric icing conditions exist when OAT on ground and for take-- off is at or
below 5°C or when TAT in flight is at or below 7°C and visible moisture in the air
in any form is present (such as clouds, fog with visibility of one mile or less, rain,
snow sleet and ice crystals).
" Ground icing conditions
Ground icing conditions exist when the OAT is at or below 5°C when operating on
ramps, taxiways and runways where surface snow, standing water or slush is
present.
" Regulatory requirements
Certification requirements defined in JAR/FAR 25 appendix C consider droplet sizes
up to 50 microns in diameter. No aircraft is certified for flight in conditions with
droplets larger than this diameter.
However, dedicated flight tests have linked unique ice accretion patterns to
conditions of droplet sizes up to 400 microns. Procedures have been defined in
case of inadvertent encounter of severe icing.
" Organization of this subchapter
It will address the following areas :
D Operations within the certified envelope.
D Information about severe icing beyond the certified envelope.
D Good operating practices.
Mod 5948
APR 11
(duplicated on the FMA).
Accordingly, the minimum maneuver / operating speeds defined for normal (no icing)
conditions (refer to FCOM 2.02.21) will automatically be increased and must be
respected as long as “ICING AOA” is illuminated.
These new minimum speeds are called “MINIMUM ICING SPEEDS”. They are defined
further in paragraph B.
Mod: 5948
APR 11
Mod 5948
2.02.08
PROCEDURES AND TECHNIQUES
P4
001
ADVERSE WEATHER
APR 11
AA
B) MINIMUM ICING SPEEDS
- The minimum maneuver/operating speeds defined for normal conditions
(2.02.01) MUST BE INCREASED and the new value enforced whenever
ICE ACCRETION
is possible (FIight in atmospheric icing conditions),
or exists (ice accretion developing or residual ice).
They are defined by the following table where VSR is the non affected 1G stall speed
as given in 2.01.03.
FLAPS
VmHB
VmLB
0
1.46 VSR
1.40 VSR
1.22 VSR
T/O - 2d segment
15
1.35 VSR
1.27 VSR
Final Take-- Off
1.30 VSR
EN ROUTE
1.24 VSR
GO AROUND
30
1.32 VSR
CAUTION : For obstacle clearance, the en-- route configuration with engine failure is
FLAPS 15° at a minimum speed of 1.30 VSR if ice accretion is observed.
- Relevant MINIMUM ICING SPEEDS are displayed on the PFD as soon as the
”ICING AOA” is illuminated (refer to 1.10.22). The icing speeds can be found for
reference in the Quick Reference Handbook for all weights.
Mod 5948
APR 11
(ICING on FMA + MC + SC + ICING amber on EWD)
Mod 5948
2.02.08
PROCEDURES AND TECHNIQUES
P6
ADVERSE WEATHER
001
APR 11
AA
E) PROCEDURES IN ATMOSPHERIC ICING CONDITIONS
During operations with AP ON during climb and descent, vertical speed mode should not
be used unless the airspeed is carefully monitored.
The recommended procedure is to use IAS mode with a speed selected which is equal to
or greater than the appropriate minimum speed (VmLB or VmHB). If the selected speed is
below VmHB, the autopilot will automatically limit the bank angle to 15°.
CAUTION : Close attention should be paid to the appearance of an AILERON MISTRIM
message flashing on the FMA and EWD: if the message appears, apply the
AILERON MISTRIM procedure.
Note : Permanent heating (Probes/windshield) is Always selected ON.
ENTERING ICING CONDITIONS
S
ANTI ICING (PROP - HORNS - SIDE WINDOWS) . . . . . . . . . . . . . . . . . . ON
Note : horns anti icing selection triggers the illumination of the “ICING AOA” green
light and green display on FMA, and lowers the AOA stall warning threshold.
S
MODE SEL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Confirm AUTO
S
MINIMUM Maneuver/Operating ICING SPEED . . . . . . . . . . . . . OBSERVED
S
ICE ACCRETION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MONITOR
Note : 1.These procedures are applicable TO ALL FLIGHT PHASES including take off.
Mod : 5948
2.02.08
PROCEDURES AND TECHNIQUES
P7
ADVERSE WEATHER
001
APR 11
AA
AT FIRST VISUAL INDICATION OF ICE ACCRETION, AND
AS LONG AS ATMOSPHERIC ICING CONDITIONS EXIST
F
ANTI ICING (PROP - HORNS - SIDE WINDOWS) . . . . . . . . . . . . Confirm ON
F
MODE SEL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Confirm AUTO
F
ENG DE ICING . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON
F
AIRFRAME DE ICING . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON
F
MINIMUM Maneuver/Operating ICING SPEED . . . . . . . . . . . . . OBSERVED
BE ALERT TO SEVERE ICING DETECTION.
In case of severe icing, refer to 2.04.05.
F
Notes:1. When ice accretion is visually observed, DE ICERS MUST BE SELECTED and
maintained ON as long as icing conditions exist.
2. The ice detector may not detect certain ice accretion form (see FCOM
1.13.20).
3. If a noticeable performance decrease and (or) significant vibrations occur
due to propeller residual icing then, in order to improve the deicing of the
blades, it is recommended :
D To check that the MODE SEL is AUTO, or that the MAN mode is selected
in accordance with SAT.
D To set CLs on 100 OVRD for continuous periods of not less than 5 minutes
in order to benefit from an increased centrifugal effect.
4. If ice accretion is seen by the detector with HORNS ANTI ICING and/or
AIRFRAME DE ICING still OFF, the ICING label will flash until corrective
actions are taken.
5. Engines de-- icing must be selected ON prior to airframe de-- icing to take
benefit of an immediate engines de-- icing.
If not, engines de-- icing will be effective 60 or 240 seconds later depending
on MODE SEL selection.
Mod : 5948
2.02.08
PROCEDURES AND TECHNIQUES
P8
ADVERSE WEATHER
001
APR 11
AA
WHEN LEAVING ICING CONDITIONS
DE ICING and ANTI ICING may be switched OFF.
Note : Leaving DE ICING in operation UNNECESSARILY is detrimental to boots life.
AIRFRAME cyan message is displayed flashing when the airframe deicing
system is still selected on five minutes after last ice accretion detection.
WHEN THE AIRCRAFT IS VISUALLY VERIFIED CLEAR OF ICE
ICING AOA caption may be cancelled and normal speeds used.
Note : Experience has shown that the last part to clear is the ice evidence probe. As
long as this condition is not reached, the icing speeds must be observed and the
ICING AOA caption must not be cancelled.
Mod : 5948
001
APR 11
Mod 5948
2.02.08
PROCEDURES AND TECHNIQUES
P 10
ADVERSE WEATHER
AA
001
APR 11
G) SUMMARY
DEFINITIONS : . ICING CONDITIONS : See Definition page 1. There is a risk of
ice accretion.
. ICE ACCRETION : Ice is building up on the airframe. ICING amber
light illuminates and flashing yellow ICING message is displayed
on the FMA.
. RESIDUAL ICE : Some ice is remaining on the airframe. May be in
or out of icing conditions.
Mod : 5948
A
APR 11
Mod : 5948
2.02.08
PROCEDURES AND TECHNIQUES
P 12
ADVERSE WEATHER
001
APR 11
AA
3) Mixed icing condition
Mixed icing condition may be encountered in the range of temperatures
- 10°C/0°C. It is basically an unstable condition, it is extremely temperature
dependent and it may change quite rapidly. This condition may surpass the ice
protection capabilities because the aggregate of impinging ice crystal/snow
and water droplet can adhere rapidly to the airframe surpassing the system
capabilities to shed ice, causing significant reduction in airplane performance
as in case of system failure.
C) CONSEQUENCES OF SEVERE ICE ACCRETION
The consequences of severe ice accretions are ice location dependent.
If the pollution extension occurs on the lower surface of the wing, it increases the
drag and the airplane speed decreases. It may lead to stall if no action is taken to
recover a correct speed.
If the pollution occurs first on the upper part of the wing, the drag is not affected
noticeably but controllability anomalies may be encountered.
Severe roll anomalies may be encountered with ”flaps 15” accretions flown with
flaps 0 setting. It should be emphasized that it is not the flaps 15 configuration itself
that is detrimental, but the low angle of attack that may result from such a setting,
especially close to VFE. This low or negative AOA increases the wing upper side
exposure to large droplet impingement. This is why holding with any flaps extended
is prohibited in icing conditions (except for single engine operations).
... / ...
Mod 5948
2.02.08
PROCEDURES AND TECHNIQUES
P 13
ADVERSE WEATHER
001
APR 11
AA
D) DETECTION
- During flight, severe icing conditions that exceed those for which the airplane is
certificated shall be determined by the following :
Severe icing is characterized by ice covering all or a substantial part of the unheated
portion of either side window,
Note : This cue is visible after a very short exposure (about 30 seconds).
and / or
Unexpected decrease in speed or rate of climb,
and / or
The following secondary indications :
. Water splashing and streaming on the windshield.
. Unusually extensive ice accreted on the airframe in areas not normally observed
to collect ice.
. Accumulation of ice on the lower surface of the wing aft of the protected areas.
. Accumulation of ice on the propeller spinner farther aft than normally observed.
- The following weather conditions may be conducive to severe in-- flight icing :
. Visible rain at temperatures close to 0°C ambient air temperature (SAT).
. Droplets that splash or splatter on impact at temperatures close to 0°C ambient
air temperature (SAT).
- The occurence of rain when SAT is below freezing temperature should always trigger
the alertness of the crew.
EXIT THE SEVERE ICING ENVIRONMENT
There are no regulatory requirements to certify an aircraft beyond CS/FAR 25
Appendix C. However, in case of inadvertent encounter with such conditions “severe
icing“ procedure must be applied (refer to 2.04.05).
Mod 5948
APR 11
Mod 5948
2.02.08
PROCEDURES AND TECHNIQUES
P 15
ADVERSE WEATHER
001
APR 11
AA
IV - GOOD OPERATING PRACTICES
Aircraft certification requirements describe the icing conditions likely to be encountered
in commercial aviation. However, as demonstrated by experience, icing remains one of
the major causes of incidents and accidents, and good airmanship prohibit any
complacency in this area.
The following basic rules should therefore be applied :
" Know as much about your operating environment as you can.
Carefully review weather packages for Pilot reports of icing conditions, tops reports,
temperatures aloft forecasts and forecasts of icing, freezing drizzle and freezing rain.
Monitor both Total Air Temperature and Static Air Temperature during climb and
while en route. Use the weather radar. Areas of precipitation which will paint on the
radar will be of sufficient droplet size to produce freezing rain when encountered in
freezing temperatures or on a cold soaked aircraft.
" Marginal freezing temperatures and icing conditions should create a heightened state
of awareness. Remember, severe ice can still be incurred at temperatures down to
approximately - 18° C, at high altitude.
" Be alert to severe icing cues defined pages 12/13.
" When severe icing is encountered, take appropriate steps to leave the conditions.
Since these unique conditions are usually small in area and associated with very
specific temperatures conditions, a change in altitude of just a couple thousand
feet may place you in a totally different environment.
" Make reports to ATC and Company.
There is no better operational tool available today than first hand reports of these
conditions. Remember that because these are localized areas and extremely temperature
dependent, another aircraft passing through the same area at a different airspeed
may experience different conditions. For example, a laboratory test showed for a
specific, yet normal condition, rime ice up to about 150 kt, mixed ice as speed was
increased to about 200 kt, glaze ice between 200 and 360 kt, and no accretion above
360 kt.
Note : Reporting of icing conditions as defined in the FAA’s Airman’s information
Manual (AIM) :
Trace : Ice becomes perceptible. Rate of accumulation is slightly greater
than the rate of sublimation. It is not hazardous even though
de-- icing/anti - icing equipment is not utilized unless encountered for an
extended period of time (over 1 hour).
Light : The rate of accumulation may create a problem if flight is prolonged
in this environment (over 1 hour). Occasional use of de-- icing/anti - icing
equipment removes/prevents accumulation. It does not present a problem if
the de-- icing/anti - icing equipement is used.
Moderate : The rate of accumulation is such that even short encounters
become potentially hazardous and use of de-- icing/anti - icing equipment or
flight diversion is necessary.
Severe : The rate of accumulation is such that de-- icing/anti - icing equipment
fails to reduce or control the hazard. Immediate flight diversion is necessary.
Mod 5948
FEB 12
Mod 5948
2.02.08
PROCEDURES AND TECHNIQUES
P 17
ADVERSE WEATHER
001
FEB 12
AA
CAUTION : Wing, tailplane, vertical and horizontal stabilizers, all control surfaces and
flaps should be clear of snow, frost and ice before take off.
PARTICULAR CASE : limited frost accretion on lower wing surfaces due to cold fuel
remaining and high ambient humidity.
As stated in the operational requirements, no person may take off an aircraft when
frost snow or ice is adhering to the wing, control surfaces or propeller of the aircraft.
FROST : frost is a light, powdery, crystalline ice which forms on the exposed
surfaces of a parked aircraft when the temperature of the exposed
surfaces is below freezing (while the free air temperature may beabove
freezing).
Frost degrades the airfoil aerodynamic characteristics. However, should the take
off be conducted with frost adhering to the lower surface of the wing, check the
following :
- The frost is located on the lower surface of the wing only.
- Frost thickness is limited to 2 mm.
- A visual check of the leading edge, upper surface of the wing, control surfaces
and propellers is performed to make certain that those surfaces are totally
cleared of ice.
- Performance decrement and procedures defined for take off in atmospheric
icing conditions are applied.
" DE ICING / ANTI ICING PROCEDURE
- External de-- /anti-- icing will be performed as close as possible from take-- off time in
order not to exceed the hold over time.
Type 1 (low viscosity) or type 2/4 (high viscosity) fluids are used for these operations.
The type 2/4 fluids are used for their anti icing qualities. As airflow increases the fluid is
spread through the elevator gap and over the lower surface of the elevator.
Depending on the brand of the fluid and the OAT, this phenomenon may temporarily
change the trim characteristics of the elevator by partially obstructing the elevator gap.
This may lead to a considerable increase in control forces necessary to rotate. This
effect is most pronounced when center of gravity is forward.
- To ensure the best possible tailplane de-- /anti-- icing, all along the fluid spraying, the
control columns must be firmly maintained on the forward stop together with the aileron
gust lock engaged.
- De-- /anti-- icing may be performed in Hotel mode provided BLEEDS are selected OFF.
If a de icing gantry is used, both engines must be shut down. For manual propeller de
icing, the engines must be shut down and air intake blanked or precaution taken not to
have de icing fluid in the air intake. No propeller blade should be located at 6 o’clock
position during this procedure.
Mod 5948
FEB 12
ENG1(2) OIL PRESS
Mod 5948
Mod: 5948
2.02.08
PROCEDURES AND TECHNIQUES
P 19
ADVERSE WEATHER
001
FEB 12
AA
" TAXIING
- The standard single engine TAXI procedure may still be used provided the friction
coefficient remains at or above 0.3 (braking action medium, snowtam code 3) and
nose wheel steering is not used with too large deflections.
Note : If the OAT is very low, it may be necessary any way to start up engine 1 early
enough to get the necessary oil warm up time (refer to Note (3) above).
- For taxiing with the very low friction coefficients (icy taxiways, slush), it is
recommended to use both engines, limit nose wheel travel and use with differential
power as necessary.
SPECIAL CASE
If contaminant layer is significant enough to possibly accumulate in the brake area
during ground operation, brakes disks may join due to icing during the flight, leading to
possible tyres damages at subsequent landing. The following special procedure
should be applied during taxi before and as close as possible to take off.
Set 18% Torque on each engine and keep taxi speed down to a ”man pace” during
30 seconds using normal brakes with minimum use of nose wheel steering to ensure a
symmetrical warming up of the brakes.
Mod 5948
2.02.08
PROCEDURES AND TECHNIQUES
P 20
ADVERSE WEATHER
001
FEB 12
AA
" TAKE OFF
Standard take off procedures will be used with the following additions :
. If runway is contaminated (ice, snow, slush), use the relevant performance penalties
defined in the performance section 3.03.
. Use of reverse on contaminated runways has to be limited at very low speeds to avoid
contaminant projections at the level of cockpit windshield which may reduce visibility
to zero (snow, slush). In atmospheric icing conditions, refer to appropriate speeds
and performance penalties and add the following :
- with very cold OAT, delay start of take off roll until oil temperature is at least 45°C
(this is necessary to guarantee inlet splitter de-- icing capability).
After the ground de icing/anti icing procedure, using type II/IV fluids, higher than
normal stick forces may be encountered. These control input forces may be more than
twice the normal take off force. This should not be interpreted as a ‘pitch jam‘ leading to
an unnecessary abort decision above V1. Although not systematic, this phenomenon
should be anticipated and discussed during pre-- take off briefing each time de
icing/anti icing procedures are performed. These increased pitch forces are strictly
limited to the rotation phase and disappear after take off.
In very exceptional circumstances, because of increased rotation forces, the pilot
canconsider that take off is impossible and consequently initiate an aborted take off .
The consequences of this decision are catered for by a specific performance penalty
(Refer to AFM SUPPLEMEMTS chapter).
AFTER V1, BE TAKE OFF MINDED
" BEFORE LANDING
If take-- off has been performed on a slush contaminated runway, this slush may seize
the brakes during cruise.
To prevent tire damage at touch down : in final approach, after the selection of GEAR
DOWN, select the ANTISKID to OFF, then pump the brakes at least 5 times and
thenreselect the ANTISKID to ON.
" LANDING
Same restrictions on reverse than for accelerate stop.
Apply relevant performance restrictions.
" PARKING
When OAT is below - 5_C / 23_F, particularly in wet conditions, avoid leaving the
aircraft with parking brake engaged and use chocks instead whenever possible.
Mod 5948
2.02.08
PROCEDURES AND TECHNIQUES
P 21
ADVERSE WEATHER
001
APR 11
AA
OPERATIONS IN WINDY CONDITIONS
Landing
The recommended landing flap configuration is the same as the standard landing flap
setting, even with strong crosswind. Large flaps extension does not impair the
controllability in any manner. Moreover it minimizes the flare duration and allows a quicker
speed decrease down to the taxi speed.
General
Precautions or special instructions may be necessary depending on the force and
direction of the wind. The following FCOM pages deal with this subject :
Tail wind limit and demonstrated cross wind
2 01 03
Final approach speed and wind factor
2 02 01
Cat II maximum demonstrated wind
2 02 04
Parking aircraft orientation
2 02 03 and 2 03 20
Aileron spring tabs (when equipped)
2 02 06
Taxiing with strong wind
2 02 06
Take off run
2 02 12
Rejected take off
2 02 12
Hotel mode limitation
2 03 06 and 2 05 02
Taxiing with tail wind component
2 03 09
Ditching
2 04 05
NAC OVHT
2 05 02
ELEVATOR JAM
2 05 06
PITCH DISCONNECT
2 05 06
AILERON JAM
2 05 06
SPOILER JAM
2 05 06
Mod : 5948
2.02.08
PROCEDURES AND TECHNIQUES
P 22
ADVERSE WEATHER
001
APR 11
AA
Windshear
This phenomenon may be defined as a notable change in wind direction and/or speed over
a short distance.
Windshear can be encountered in the vicinity of thunderstorms, into rain showers (even
without thunderstorms), during a frontal passage or on coastal airports (sea breeze
fronts).
Severe windshear encountered above 1000 feet, whilst unpleasant, can generally be
negociated safely. However if it is encountered below 500 feet on take off or
approach/landing it is potentially dangerous.
As far as possible this phenomenon must be avoided.
Procedure at take off :
• Delay the take off. If a low level windshear is reported calculate VR, V2 at the maximum
take off weight available for the day.
• When clear of obstacles accelerate as much as possible and clean up the aircraft.
• Climb at the normal climb speed.
Procedure during an approach : If a windshear is encountered,
• Initiate a normal go around procedure with 10° pitch .
• When positively climbing at a safe altitude, retract the gear and complete the normal
go around procedure.
CAUTION :
The positive rate of climb must be verified on at least two instruments.
COMMENTS :
1. Leaving the gear down until the climb is established will allow to
absorb some energy on impact, should the microburst exceed the
aircraft capability to climb.
2. Ten degrees pitch attitude is the best compromise to ensure a
climbing path together with an acceptable maximum AOA.
Mod : 5948
2.02.08
PROCEDURES AND TECHNIQUES
P 23
ADVERSE WEATHER
001
APR 11
VOLCANIC ASH ENCOUNTER
1- VOLCANIC ASH DESCRIPTION
Volcanic ash is, essentially, extremely fine particles of glass shards and pulverized rock,
the composition of which reflects the composition of the magma inside the volcano.
It is composed predominantly of siliceous materials (> 50%) that are both very hard and
very abrasive. The melting point of glassy silicates is around 1100_C that is close to the
operating temperature of the engine at cruise thrust.
The ash is accompanied by gaseous solutions of sulphur dioxide (sulphuric acid) and
chlorine (hydrochloric acid).
2- AVOIDANCE
Flight operations in volcanic ash are extremely hazardous and must be avoided. Flights in
areas of known volcanic activity must be avoided.
When a flight is planned into an area with known potential for volcanic activity:
- All NOTAMS and air traffic advisories have to be checked for current status of volcanic
activity.
- The planned route has to well avoid the area of volcanic activity.
- If possible, stay upwind of volcanic ash.
The first two or three days following an explosive eruption are especially critical because
high concentration of gas with hazardous concentration could be encountered at cruise
levels some considerable distance from the volcano. Beyond three days, it is assume that
if the ash is still visible by eye or from a satellite data, it still presents a hazard to aircraft.
3- DETECTION
Volcanic ash cloud does not produce ”return” or ”echoes” on the airborne weather radar.
Volcanic ash may be difficult to detect visually, especially at night or on instrumental
meteorological conditions. However, the following have been reported by flight crew:
- Acrid odor, similar to electrical smell, burned dust or sulfur.
- Smoke or dust appearing in the cabin and cockpit, leaving a coating on cabin and
cockpit surfaces.
- Multiple engine malfunctions, such as stall, increase ITT, flameout.
- Airspeed fluctuating erratically.
- At night, static electric discharges (St. Elmo’s fire) visible around the cockpit
windshields.
- At night, landing lights cast sharp, distinct shadows on the volcanic ash clouds as
opposed to the normally fuzzy, indistinct shadows cast on water / ice clouds.
4- EFFECTS ON POWERPLANT
The melting point of volcanic ash is close to the operating temperature of the engine at
cruise power. This can cause serious damage in hot section of the engine that could result
in engine thrust loss and possible flame out.
(.../...)
Mod : 5948
2.02.08
PROCEDURES AND TECHNIQUES
P 24
ADVERSE WEATHER
001
APR 11
4- EFFECTS ON POWERPLANT (CONT’D)
Pilots are therefore asked to reduce engine power settings to flight idle when possible to
lower the engine operating temperature below the melting point of volcanic ash.
The volcanic ash, being abrasive, also damage engine components causing loss of
engine thrust. The erosion also results in a decrease in the engine stall margin. Although
this abrasion effect takes longer than the melting fusion of volcanic ash to shut down the
engine, the abrasion damage is permanent and irreversible. Reduction of engine thrust to
idle slows the rate of erosion by the compressor blades but can not eliminate it entirely
while the engine is still ingesting air contaminated by volcanic ash.
Propeller blades may also be degraded by erosion inducing loss of traction efficiency.
Oil cooler efficiency may also be decreased either due to excessive erosion of the cooler
or due to blockage of the air intake by ashes.
5 - EFFECTS ON THE AIRFRAME AND EQUIPMENT
Volcanic ash abrades cockpit windows, airframe and flight surfaces. Any parts protruding
from airframe such as antennas, probes, ice detectors can be damaged and may be
rendered inoperable.
- The abrasion of the cockpit window reduces the pilot’s forward visibility. This can lead
to serious problems during landing phase.
- The abrasion damage of the wing or horizontal stabilizer leading edges can either
prevent the correct operation of the de-- icing boots or even detached parts of the boots
with subsequent drag increase.
- The abrasion damage of the landing lights can significantly reduce landing light
effectiveness.
- Damage to the antennas can lead to a complete loss of HF communications and a
degradation of VHF communications.
- Damage to the various sensors can seriously degrade the information available to the
pilot through the instrument.
Volcanic ash can obstruct probes and penetrate into air conditioning and equipment
cooling system. It can contaminates electrical and avionic units, fuel and hydraulic
system and smoke detection system.
- Pitot probe can be blocked by volcanic ash resulting in unreliable airspeed indications
or complete loss of airspeed indication in the cockpit.
Volcanic ash columns are highly charged electrically. The static charge on the aircraft
creates a ”cocoon” effect which may cause a temporary defection, or even complete loss
of VHF or HF communication with ground stations.
(.../...)
Mod : 5948
2.02.08
PROCEDURES AND TECHNIQUES
P 25
ADVERSE WEATHER
001
DEC 13
6 - PROCEDURE
R Refer to Procedures Following Failure : Volcanish Ash Encounter ; 2.05.13 p005_001
Mod : 5948
2.02.09
PROCEDURES AND TECHNIQUES
P1
001
LANDING GEAR/BRAKES
APR 11
AA
This chapter deals with the following points :
-
RUNWAY STATUS
NORMAL TAXI
TAXI WITH FAILURES
EMERGENCY BRAKING
RUNWAY STATUS
The following table gives for take-- off and landing the equivalent runway status
corresponding to the braking action or the friction coefficient.
This runway status may be used for the computation of the performances.
EQUIVALENT RUNWAY
STATUS
TAKE- OFF
LANDING
BRAKING
ACTION
GOOD
FRICTION
COEFFICIENT
0,40 and above
1
1
GOOD/MEDIUM
MEDIUM
0,39 to 0,36
0,35 to 0,30
2
3/6
2
5/6
MEDIUM/POOR
POOR
UNRELIABLE
0,29 to 0,26
0,25 and below
UNRELIABLE
4
7
8
5
7
8
EQUIVALENT RUNWAY STATUS :
1 : Dry runway
2 : Wet up to 3 mm depth
3 : Slush or water for depths between 3 and 6 mm
4 : Slush or water for depths between 6 and 13 mm
5 : Slush or water for depths between 3 and 13 mm
6 : Compact snow
7 : Ice
8 : Runway with high risk of hydroplaning
Mod 5948
2.02.09
PROCEDURES AND TECHNIQUES
P2
LANDING GEAR/BRAKES
001
APR 11
AA
NORMAL TAXI
CAUTION : If blue hydraulic circuit is pressurized, nose wheel steering has to be
switched off for towing by a ground vehicle.
- The ATR 72 is particularly easy to taxi, and even on one engine, there are no
limitations to go either forward or rearward : this flexibility should be systematically
used and is reflected in the standard operating procedure which assumes HOTEL
MODE operation of engine 2 prior to and during passenger boarding followed by initial
taxi on engine 2 only (including back track if taxi backwards required).
This procedure is highly recommended as GI power is quite sufficient on one engine only
to perform all taxiing (OUT and IN) and very obviously reduces block fuel by an amount
which may become VERY SIGNIFICANT on large airports.
CAUTION : Start up of engine 1 should be performed in a portion of taxi where captain
workload is low enough to allow an efficient monitoring of the start up.
- Use of brakes during taxiing may be very much reduced by systematic use of a small
amount of reverse when deceleration is needed.
- Radius of turn with nose wheel steering is very good and does not require any braking
ON THE INNER WHEELS.
CAUTION : PIVOTING (Sharp turns) UPON A LANDING GEAR WITH FULLY BRAKED
WHEELS IS NOT ALLOWED, except in emergency.
TAXI WITH FAILURES
TAXI WITH NOSE WHEEL STEERING OFF (or without blue HYD pressure)
D Obviously SINGLE ENGINE TAXI is no more possible
D Taxiing remains very easy with both engines operating EEC ON :
directional control is achieved primarily with differential power on engines, possibly
augmented by use of differential braking.
D Avoid sharp turns : turn radius without nose wheel steering should be limited to
about half turn radius with nose wheel steering.
TAXI WITH EEC OFF
On ground EEC off, engine response is somewhat degraded. Nevertheless, as long as at
least one engine is maintained at or below GI, the corresponding NP should remain high
enough to keep associated ACW GEN available and thus maintain both HYD pumps.
CAUTION : When taxiing with both EEC OFF, AVOID pushing both PL above GI to avoid
transient loss of ACW and MAIN HYD PUMPS.
Note : NOSE WHEEL steering remains available in all cases together with STBY
braking, through DC AUX pump.
Mod 5948
2.02.09
PROCEDURES AND TECHNIQUES
P3
LANDING GEAR/BRAKES
001
APR 11
AA
EMERGENCY BRAKING
- Emergency braking has been made operationally easier by design of the parking brake
lever which incorporates an “EMER BRAKE” notch : when the parking brake lever
is set in this notch, the regulator delivers a limited pressure which :
D allows the use of EMER BRAKING for abort take-- off at max V1 or at touch down
for landings after GREEN pressure has been completely lost.
D provides repeatable, smooth deceleration whilst minimizing the risk of blown up
tires.
CAUTION : Use of EMER BRAKE beyond the EMER BRAKE NOTCH ABOVE 60 Kts
MUST BE AVOIDED TOPREVENT WHEELSLOCK UPAND DAMAGESTO
WHEELS AND TIRES.
BELOW 60 Kts, a SMALL further travel (∼ 1 cm) IS AVAILABLE WITHOUT
RISKS OF DAMAGE WHEN MAXIMUM STOPPING PERFORMANCE IS
REQUIRED.
- A deflated tire is not easily noticeable from the cockpit : NO TAKE OFF should be
started after EMER BRAKE has been used at speeds in excess of a maximum taxiing
speed of 20 Kt without prior visual inspection of the main landing gear tires.
Mod : 5948
2.02.10
PROCEDURES AND TECHNIQUES
P1
FLIGHT PATTERNS
APR 11
CLB procedure:
AA
Mod : 5948
001
2.02.10
PROCEDURES AND TECHNIQUES
P2
FLIGHT PATTERNS
AA
Mod : 5948
001
APR 11
2.02.10
PROCEDURES AND TECHNIQUES
P3
FLIGHT PATTERNS
AA
Mod : 5948
001
APR 11
2.02.10
PROCEDURES AND TECHNIQUES
P4
FLIGHT PATTERNS
AA
Mod : 5948
001
APR 11
2.02.10
PROCEDURES AND TECHNIQUES
P5
FLIGHT PATTERNS
AA
Mod : 5948
001
APR 11
2.02.10
PROCEDURES AND TECHNIQUES
P6
FLIGHT PATTERNS
AA
Mod : 5948
001
APR 11
2.02.10
PROCEDURES AND TECHNIQUES
P7
FLIGHT PATTERNS
AA
Mod : 5948
001
APR 11
2.02.10
PROCEDURES AND TECHNIQUES
P8
FLIGHT PATTERNS
AA
Mod : 5948
001
APR 11
2.02.10
PROCEDURES AND TECHNIQUES
P9
FLIGHT PATTERNS
AA
Mod : 5948
001
APR 11
2.02.11
PROCEDURES AND TECHNIQUES
P1
001
POWER PLANT
APR 11
AA
START UP PROCEDURE
Prior to initiating start sequence EEC FAULT light must be extinguished, if EEC
FAULT is lit try to reset ; if unsuccessful, deselect EEC.
During engine start or relighting, the following items must be monitored.
- Correct NH increase when starting the sequence.
- Starter disconnection at 45 % NH.
- Maximum ITT : during a battery start one or two ITT peaks not exceeding 800°C may
usually be observed. ITT peaks are of lower value if a suitable GPU is used.
This example shows the start sequence of engine N° 1 on ground (engine 2 running)
NH %
Parameters
START 1
10
0
ON illuminated
STARTER/GENERATOR
CLA
25
45
62
(ON extinguished)
Starter
FUEL SO
generator
* FTR
IGNITION
EEC
ELECTRICAL SUPPLY OF
STARTER/GENERATOR
PLA
EEC ON
MAIN BAT.
(MAIN BAT.
+ GEN 2)
GI
* Passing from FUEL SO to FTR is possible between 10 and 19 % NH if ITT > 200° C.
ENG OIL LO PR FWS alarm is 30 seconds time delayed to avoid untimely ENG OIL LO PR
during engine start. Refer to 2.02.08 p18 for specific cold weather behaviour.
Note : This alert is inhibited when affected CL is in FUEL SO position.
Mod 5948
2.02.11
PROCEDURES AND TECHNIQUES
P2
POWER PLANT
AA
001
APR 11
TAKE OFF: USE OF BLEED VALVES
The aircraft is fitted with an automatic bleed valve closing in case of engine failure at
take off.
The closing signal is given by MFC’s when uptrim is triggered. BLEED FAULT light also
illuminates on the operative engine. Engine bleed valves may be routinely selected ON
(NORM FLOW) for take off. However, performance decrement has to be considered for
the ground phase. This decrement is given in chapter 3.03 and may be computed by the
FOS.
POWER SETTING AT TAKE OFF
Engine control normally uses temperature, altitude and speed data from the selected
ADC but reverts to its own sensors in case of detected failure or significant offset.
TAT/SAT information are valid only when the engine (propeller unfeathered)
corresponding to the selected ADC is running.
RTO torques must be computed using altitude and temperature information independant
from aircraft sources and compared to values displayed by torque bugs.
Take off power is routinely obtained by setting the power levers and the condition levers
into the notches. If needed, in order to match target torque bugs set according to
dependable data, it may be necessary to adjust the throttles out of the notches.
UNFEATHERING AFTER AN ENGINE RESTART IN FLIGHT
Unfeathering the propeller induces a limited lateral disturbance.
ENGINE PARAMETERS FLUCTUATION
The variation tolerances of engine parameters are shown in Figure. These tolerances
must be taken into account only in stabilized flight phases.
PARAMETERS
TQ
NH
ITT
NP
FLUCTUATION
AMPLITUDE
+/- 2 %
+/- 0.25 %
+/- 10_C
+/- 2.5 %
In case of engine parameters fluctuation it can be helpful to select the corresponding EEC
OFF then On according to EEC FAULT C/L before shutting the engine down.
If this action cures the problem, the flight can be continued accordingly.
MAN IGNITION
When one or both EEC (s) has (have) been deselected, the use of MAN ignition is
required when the aircraft penetrates heavy precipitation or severe turbulence areas,
when ice accretion develops or when using contaminated runway for take off or landing.
GO AROUND - POWER SET UP PROCEDURE
The throttle movement (PF) is to be applied accross the notch up to the ramp (beginning
of amber sector).
WARNING : Overriding the ramp threshold up to the absolute full travel will allow to
reach 1.15 x RTO TQ (EEC ON).
This should be used only is case of emergency.
CLs should routinely stay into the notches. Np is automatically set at 100 % provided PWR
MGT is on TO position and PLA is sufficient (see 1.16.40).
Mod 5948
2.02.11
PROCEDURES AND TECHNIQUES
P 2A
POWER PLANT
001
APR 11
PUSH BACK AND POWER BACK OPERATIONS
Push- back (with towbar)
- Push-- back is done after ATC clearance.
- Specific phraseology is used.
- Ground staff remains connected with the aircraft by using conventional signs and/or
headphones with several persons according to airline policy
- Parking brake released and steering OFF.
- Each crew member keeps his feet on the floor. NEVER USE BRAKES during push back
(to avoid tail strike and/or strain on towing system). Wait for disconnection of the tow bar
by the ground staff before switching the steering ON.
- Set nose wheel steering to ON. Caution: never set the hydraulic of the steering before the
disconnection of the tow bar.
Note:NAC OVHT and ENG FIRE can be triggered during push-- back in hotel mode, with a
tail wind greater than 10kts, including aircraft direction changes throughout the
procedure.
If the tail wind is above this limit, the push-- back has to be done, with the propeller(s)
running and unfeathered, and respecting ground safety rules and airport local rules.
Power back
- Before power back, both propellers are running and are unfeathered.
- Power back is done after ATC clearance.
- Ground staff area checked cleared before and during power back, by using conventional
signs and/or headphones with several people, as per prevailing airlines policy.
- Nose wheel steering remains ON.
- To avoid moving forward, apply slight power back just before releasing brake.
- Each crew member keeps his feet on the floor. NEVER USE BRAKES during power back
(to avoid tail strike).
- Power back is performed at low speed.
- Use Ground Idle or positive power to decrease speed or stop.
Note: NAC OVHT and ENG FIRE can be triggered, if a prolonged power-- back is
maintained with a tail wind greater than 10kts, including aircraft direction changes
throughout the procedure
Note: In Ground Idle, after parking brake release, the aircraft moves forward. The power
lever has to be retarded slightly to power back just before releasing the brake.
Note: Safety glasses have to be used by the ground staff, because of the possibility of
projection during power back operation.
Mod 5948
2.02.11
PROCEDURES AND TECHNIQUES
P3
POWER PLANT
001
APR 11
AA
ADAPTED FLIGHT IDLE
A low flight idle rating is associated with a significant increase of aerodynamic drag
profitable to the descent performance (approach and landing).
On the other hand, this increased drag penalises the lift at a high angle of attack.
The fulfillment of these two requirements has led to an adapted flight idle providing two
power settings.
The FI position being selected by the pilot, the power level (high or low) is set by the
EEC’s, as a function of an information provided by the MFC’s.
This information is associated with a limit angle of attack equal to α stall warning - 4°.
In case of high flight idle loss the aircraft behaviour during stall unchanged and the
decrease of lift is negligible and covered by the regulatory margins.
PROPELLER BRAKE USE
Propeller brake must be used only when READY light on propeller brake control panel is
illuminated.
1 - BRAKING SEQUENCE (ENG 2 Running)
Notes : The DC AUX pump runs automatically as soon as
- blue hydraulic pressure is below 1500 PSI and,
- gear is down and,
- one engine is running
and stops 15 seconds after the end of prop braking sequence (PROP BRK lights
illuminated).
Mod 5948
2.02.11
PROCEDURES AND TECHNIQUES
P4
POWER PLANT
001
DEC 13
2 - RELEASING SEQUENCE (ENG2 in hotel mode)
R Note : A pulse on AUX HYD PUMP pb starts the auxiliary hydraulic pump for
30 seconds.Selecting propeller brake sw to OFF position within this 30 s
temporization allows to keep the DC AUX PUMP running overriding the
30 seconds temporization.
Mod 5948
2.02.11
PROCEDURES AND TECHNIQUES
P5
001
POWER PLANT
APR 11
DIFFERENCE BETWEEN AN EEC FAULT CONDITION AND AN
ENGINE FLAME OUT IN FLIGHT
ENGINE FLAME OUT(*)
EEC FAULT
POWER EVOLUTION
Immediate power
loss
Moderate variation
(either way)
EEC FAULT
LIGHT
Not lit
Immediate illumination
NH
Rapidly below 74 %
Always above 74 %
ITT
rapidly below 350° C
Always above 350° C
POWER LEVER
Totally inefficient
Generally inefficient
refer to FCOM 1.16.30
ASSOCIATED DC
GEN LT
DC GEN Fault illuminates
rapidly
Normal
BLEED/PACK
FAULT illuminates rapidly
Normal
(*) If automatic relight has not operated
ENGINE OPERATION WITH EEC OFF
- EEC deactivation may lead to an important power variation at constant throttle
position. Power recovery will necessitate throttle readjustment.
- Maintaining target torque may necessitate positions out of the notch since constant
throttle position feature is lost. Some throttle readjustements will be necessary
during climb.
Engine response may be more sluggish when increasing power and a
temporary throttle overtravel may be necessary to obtain a fast power response.
- If EEC is selected from OFF to ON, an important power variation may result. That is
why the throttle has to be reduced below 52° prior to such an action.
- Landing with both EEC OFF will lead to a big propeller speed decay as the speed
decreases, so that ACW power may be lost at the end of the landing run. Be ready to
use nose wheel steering and emergency braking as required.
Engine response during taxi will be slower.
- Reverse power is reduced. Moreover, in case of acceleration stop, a one second stop
must be observed at Fl before setting PLs below.
Mod 5948
2.02.11
PROCEDURES AND TECHNIQUES
P6
POWER PLANT
001
APR 11
AA
ENGINE FAILURE SIMULATION FOR TRAINING PURPOSES
Flight training requires to simulate engine failure in a representative manner for both
controllability and performance aspects but without feathering engine (safety and
cooling of nacelle).
For a given PL position, the propeller THRUST (+) / DRAG (-- ) VARIES VERY
SIGNIFICANTLY WITH IAS, particularly at low speeds, as shown by the following table.
(Zp = 0 (ISA/NP max = 100%)
PL Position
0 kt
50 kt
100 kt
125 kt
150 kt
40
1300 daN
710 daN
200 daN
0 daN
~0 daN
36
1270 daN
670 daN
- 240 daN
- 600 daN
- 530 daN
Fl
1240 daN
640 daN
- 460 daN
- 850 daN
- 750 daN
Gl
140 daN
- 610 daN
- 2070 daN
Max Rev
- 610 daN
- 1370 daN
- 2900 daN
- The drag of a feathered engine is negligible between 0 and 150 kt.
- The maximum drag of a failed, unfeathered, engine varies with IAS and PL position
as follow :
PL Position
0 kt
50 kt
100 kt
125 kt
150 kt
TO
0 daN
80 daN
310 daN
470 daN
700 daN
Fl (B = 14°)
0 daN
80 daN
400 daN
620 daN
750 daN
The procedure for simulating engine failure is based on retarding PL to fixed positions,
optimised to cover correctly the T/O and approach phases i.e. for IAS around 110/
125 kts.
IN FLIGHT - To simulate an UNFEATHERED failed engine retard PL at Fl.
- To simulate a FEATHERED engine set PL to 39 for IAS 110/125 kt.
Note : ISA and altitude effects are negligible.
- For continued take-- off with simulated engine failure, retard PL to 39 for
IAS 110/125 kt in order to simulate auto feather action.
ON GROUND - Aborted T/O: Retard INITIALLY to Fl.
CAUTION : - On ground, in all cases, (single engine landing or aborted T/O), the
trainee must retard BOTH PL at Gl, then use reverse on «LIVE»
engine only, as necessary.
- Leaving the simulated « engine failed » PL at 39 or more (for single
engine landings) or Fl (for aborted T/O) would lead to non
representative controllability problems as the «failed » engine thrust
would change its initial drag into a big increase of forward thrust as IAS
decreases.
- To be exact, these values request a perfect rigging of engine controls.
A slight mismatch may induce a significant drag change. Pilot should
monitor performances and increase PLA as necessary.
Mod 5948
2.02.11
PROCEDURES AND TECHNIQUES
P7
POWER PLANT
001
APR 11
REVERSE PHASES
NP is the parameter to be monitored during reverse phases. (NP is the only regulated
parameter in these phases)
OPERATIONS OUT OF THE NOTCH
When PL are retarded, during descent and approach, trim efficiency is reduced (reference
point being notch), and cannot correct built-- in discrepencies between engines and their
associated controls. Tolerances due to PL rigging cannot be compensated in that area.
TQ split up to 8% (8 counts) can be evidenced between engines in stabilised conditions.
This is built-- in and results from requirement of TQ accuracy in notch, which is the power
setting used for about 90% of flight time.
TQ differences are allowable and can be eventually compensated manually by crew with
PL adjustment.
Mod 5948
2.02.12
PROCEDURES AND TECHNIQUES
P1
FLIGHT CHARACTERISTICS
001
APR 11
AA
TAKE OFF AND LANDING RUNS
- Proper crew coordination is required in order to hold the control column at all times
and prevent excessive elevator or aileron deflections due to wind and/or reversed air
flow from propellers.
The control column is initially held.
D in pitch : fully nose down, then slowly relaxed as speed increases.
D in roll : neutral or deflected TOWARD the wind in case of crosswind component, as
appropriate to maintain wings essentially level.
Note : Excessive aileron deflections should be avoided as they affect directional
control.
- For take-- off, use of nose wheel steering guidance is only recommended for the very
first portion of the take off run as rudder becomes very rapidly efficient when airspeed
increases (~ 40 kts) and ATR 72 exhibits a natural tendency to go straight.
- Action on nose wheel tiller should be smooth and progressive, particularly as ground
speed increases.
- Rudder must not be cycled during take-- off, particularly the first portion where nose
wheel is used: combination of unnecessary rudder cycling (with an increasingly
efficient rudder) and nose wheel control would then lead to
uncomfortable oscillations.
- Rolling take-- off technique
In order not to increase the take-- off distances, power must be set quickly during the
last phase of the line up turn.
- for landing or aborted take off, control column holding must be transferred to the
co-- pilot when the captain takes the nose wheel steering.
If reverse is used, at low speeds and with high power, the reversed air flow may
shake violently the flight controls, particularly with no crosswind: the control column
must be held very firmly and/or, below 30 kts, the GUST LOCK may be engaged.
Narrow Runways :
When the aircraft is operated on a narrow runway (width < 30 m (98 ft)), whoever
is the PF (CM1 or CM2), the CM1 should be ready to use Nose Wheel Steering as soon
as the nose wheel is on the ground.
If reverse is used, at low speeds and with high power, the reversed air flow may
shake violently the flight controls, particularly with no crosswind : the control column
must be held very firmly and/or, below 30 kts, the GUST LOCK may be engaged.
Refer to 3.11.10
Mod 5948
2.02.12
PROCEDURES AND TECHNIQUES
P2
FLIGHT CHARACTERISTICS
001
APR 11
AA
ENGINE FAILURE
AT TAKE OFF BELOW V1
Abort is mandatory: both PLs are retarded to Gl and full braking applied if needed.
Reverse is available even on single engine down to full stop: again, control column is
transferred to the co-- pilot when captain takes nose wheel steering and, in case of single
reverse operation roll control must be applied (possibly to full travel) in order to
minimize the tendency to bank on the side of the operating engine.
AT TAKE OFF ABOVE V1
Take off must be continued. Directional control must be maintained with rudder and, as
soon as aircraft becomes airborne, aileron input to stabilize heading with about 2° of
bank toward the operating engine is highly recommended in order to decrease rudder
deflection thence improve climb performance.
Both rudder and aileron forces may be completely trimmed out, even at minimum
scheduled V2. Once both yaw and roll axis are trimmed out, autopilot may be engaged.
IN APPROACH
Directional control must be maintained with rudder, (which disengages
automatically YD and AP if previously engaged) and aileron, in a manner similar to what
was described for the continued take off case.
The ATPCS functioning is different between approach and take-- off.
Even if TO position is selected:
- Uptrim function is never available
- Auto feather function may be available depending on PL position at the time of the
failure.
If autofeather has not operated (windmilling), the drag depends on the engine failed PL
position. For this reason :
- In approach, do not reduce the affected PL below 45° PLA before manually feathering
the engine.
- If a go around is performed, advance both PLs to the ramp. When appropriate,
manually feather the failed engine.
LANDING (PROPELLER FEATHERED)
- Flare technique remains unchanged and rudder input required to
compensate the asymmetric reduction at 20 ft is more smoothly achieved if YAW
DAMPER has been disconnected in short final.
- After main gear touch down, it is recommended to first lower nose wheel to ground
contact before reducing PL from Fl to Gl: this allows to better control the large
asymmetric associated drag increase on the live engine side. PL may be then
retarded to full reverse as required but roll attitude must be controlled which requires
large control wheel deflection by PNF.
Mod 5948
2.02.12
PROCEDURES AND TECHNIQUES
P3
FLIGHT CHARACTERISTICS
001
DEC 13
AA
STALLS
STALL WITHOUT ICE ACCRETION
In all configurations, when approaching the stall, the aircraft does not exhibit any
noticeable change in flight characteristics: control effectiveness and stability remains
good and there is no significant buffet down to CL max ; this is the reason why both the
stall alert (audio “cricket” and shaker) and stall identification (stick pusher) are
“artificial” devices based on angle of attack measurement.
Recovery of stall approaches should normally be started as soon as stall alert is
perceived : a gentle pilot push (together with power increase if applicable) will then allow
instantaneous recovery. If the stall penetration attempt is maintained after stall alert has
been activated, the STICK PUSHER may be activated : this is clearly unmistakable as the
control column is suddenly and abruptly pushed forward, which in itself initiates
recovery.
Note : The “pushing action” is equivalent to 40daN/88 lbs applied in 0.1 second and
it lasts as long as angle of attack exceeds the critical value.
R
WARNING : Stall training excercises without stick pusher are prohibited.
STALL WITH ICE ACCRETION
Even with airframe de-- icers used according to procedure (i.e. as soon as and as long as
ice accretion develops on airframe), the leading edges cannot be completely cleared of
ice accretion because of existence of “unprotected” elements on the leading edges and
continued accretion between two consecutive boots cycles.
This residual ice on leading edges changes noticeably the characteristics of flight
BELOW the minimum operating speeds defined for ice accretion, as follows :
- Control effectiveness remains good, but forces to manoeuver in roll and to a lesser
degree in pitch, may increase somewhat.
- Above the reduced angle of attack :
. An aerodynamic buffeting may be felt which will increase with the amount of ice
accumulated and angle of attack increase.
. Stability may be slightly affected in roll, but stick pusher should prevent angle of
attack increase before wing rocking tend to develop (Refer to FCOM 1.02.30 for
stall alarm threshold definition).
Recovery of stall in such conditions must be started as soon as stall warning is
activated or buffeting and/or beginning of lateral instability and/or sudden roll off is
perceived.
Recovery will be best accomplished by :
- A pilot push on the wheel as necessary to regain control.
- Selection of flaps 15.
- Increase in power, up to MCT if needed.
Mod 5948
2.02.12
PROCEDURES AND TECHNIQUES
P4
FLIGHT CHARACTERISTICS
001
APR 11
AA
APPROACH
- The deceleration capabilities of the ATR 72 provide a good operational
advantage which should be used extensively: decelerated approaches reduce noise,
minimize time and fuel burn and allow better integration in big airports. This is why
they have been described as the « standard approaches » in section 2.02.10 (flight
patterns).
- Initial approach speed will vary with ATC constrainsts and turbulence, but may be up
to 240 Kts.
- Initial approach speed may be maintained on a typical 3° glide slope down to the
following height above runway:
NP
DECELARATION HEIGHT
82 %
(IAS x 10) ft
Configuration changes should be made at VLE VFE when decelerating. This procedure
allows to reach VAPP speed at 500 ft above runway.
Note : If deceleration rate on approach appears unsufficient, it is always possible to
increase it by setting NPs on 100 OVRD, but at the expense of an increased
interior noise.
R STEEP SLOPE APPROACH
R Refer to 3.11.17
Mod 5948
2.02.12
PROCEDURES AND TECHNIQUES
P5
FLIGHT CHARACTERISTICS
001
APR 11
AA
LANDING
In order to minimize landing distance variations the following procedure is
recommended :
D Maintain standard final approach slope (3°) and final VAPP until 20 ft is called on
radioaltimeter.
D At« 20ft » call by PM, reduce to FI and flare visually as required.
Note : 20 ft leaves ample time for flare control from a standard 3° final slope.
- During this flare the airspeed will necessary decrease, leading to a touch down
speed of 5 to 10 kt lower than the stabilized approach speed.
D As soon as main landing gear is on ground.
- Control nose wheel impact
- Both PL : GI
- Both LO PITCH labels: check illuminated green.
CAUTION : If a thrust dissymetry occurs or if one NO REV red reverse video label
on EWD is illuminated, the use of any reverser is not allowed.
In this case the propeller pitch change mechanism is probably locked
at a positive blade angle, leading to a positive thrust for any PL
position.
- use feet brakes as required
- as speed reduces, and not later than about 40 kt (estimated) Capt takes NWS
control, co-- pilot hold control column fully forward.
Notes : 1. Max reverse is usable down to full stop if required, but to minimize flight
control shaking due to reverse operation at high powers, it is helpful to
release slowly PL back to GI when reaching low ground speeds (below
40 kt estimated).
2. Max braking is usable without restriction down to full stop, whatever the
runway conditions may be, provided ANTISKID is operative.
3. The tail bumper (with damping capabilities) effectively protect the tail in case
of excessive attitude (resulting from prolonged/floating flares) provided the
rate of sink at touchdown does not exceed 5 ft/sec.
4. In case of a significant bounce, a go around must be initiated.
Mod 5948
2.02.14
PROCEDURES AND TECHNIQUES
FLIGHT INSTRUMENTS
AHRS
P1
001
APR 11
AA
AHRS
AHRS alignment sequence takes place as soon as the battery is switched ON, and it takes
nominally 1 MINUTES DURING WHICH AIRCRAFT MUST NOT BE MOVED (on
ground).
AHRS are normally not affected by electrical transients asociated with engine start.
Note : during AHRS alignment, the alert “AHRS NOT ALIGN” is dispalyed on FWS, and
“AHRS DEGRADED” is diplayed on the corresponding PFD.
ON GROUND ONLY, if needed, AHRS reset may be performed by cycling all relevant C/B
OFF-- ON.
CAUTION : resetting AHRS C/B in flight is not recommended as in flight realignment
requires 1 minutes and 30 seconds of very stable flight (which may be
impossible to get in turbulences) and possibility of pulling the wrong C/B
could lead to complete AHRS failure unrecoverable for the rest of the flight.
CAUTION : Pilots must be aware of possible induced attitudes and heading errors in case
of continuous turns, specially in high latitudes countries; therefore racetrack
holding patterns are to be flown rather than circles.
Mod : 5948
2.02.14
PROCEDURES AND TECHNIQUES
FLIGHT INSTRUMENTS
WEATHER RADAR
P2
001
APR 11
AA
WEATHER RADAR
THe weather radar radiates power when operating in any mode other than STBY. Use of
weather radar on ground in a mode other than STBY requires special care :
- make certain that no personnel is working in front of aircraft within a sector of 3 meters
radius and 130_ left or right of the aircraft axis.
- direct aircraft nose so that no large size metal object (hangar, aircraft ...) is located
within a 30 meters radius.
- avoid operating radar during refueling operation of radiating aircraft or any other
aircraft within a 30 meters radius.
Mod : 5948
2.02.15
PROCEDURES AND TECHNIQUES
P1
TCAS
001
APR 11
AA
TCAS
GENERAL
TCAS is an airborne Traffic alert and Collision Avoidance System that interrogates ATC
transponders in nearby aircraft and generates appropriate aural and visual advisories to
the flight crew to provide adequate separation.
Air to Air communications for coordinating maneuvers between TCAS equipped aircraft is
provided by mode S ATC transponder.
Note 1 : TCAS system can only generate resolution advisories for intruders equipped
with operative mode S or mode C transponders (providing valid intruders
altitude information).
Note 2 : Traffic advisories can only be generated for intruders equipped with operative
mode S, C or A transponders (TCAS system provides no indication of aircraft
without operative transponders).
CAUTION
The TCAS equipment
q p
is viewed as a supplement
pp
to the pilot
p who,, with the aid of
the Air Traffic Control, has the primary responsability for avoiding mid-- air collisions.
START UP AND TEST
TRAFFIC display on ND:
- On MCP press ”ND”.
- On VCP select ”ND OVLY” tab, then select TRAFFIC ”NORM”
TCAS/ XPDR mode selection:
- On MCP press ”SURV”, select ”TCAS” tab and select ”STBY” mode
- Select ”XPDR” tab and select ”STBY” mode
To launch TCAS/XPDR Test :
- Through MCDU, launch TCAS/XPDR self test and check proper aural message and
visual display.
GROUND OPERATION
TCAS test should be carried out during cockpit preparation.
Unless otherwise instructed by ATC:
- on MCP press ”SURV”, select ”XPDR” tab on VCP, set ”ALT” mode and check
XPDR1 selected; then on MCP press ”SURV”, select ”TCAS” tab and select ”AUTO”
mode. On PFD / TCAS status indication, green message ”TCAS ABOVE” is displayed .
On PFD / TTransponder status indication, green message ”XPDR1(2) ALT” is
displayed
Mod : 5948
2.02.15
PROCEDURES AND TECHNIQUES
P2
TCAS
001
APR 11
AA
TCAS (CONT’D)
FLIGHT PROCEDURES
Procedure is initiated by a TCAS Traffic Advisory : TA.
“TRAFFIC - TRAFFIC”
CPT
- Decide task sharing and announce : “TCAS, I (you) have the controls.”.
PF
- Be minded for maneuver. Follow traffic evolution on the TCAS indicator.
PM
- Recall minimum safety altitude. Try to visually acquire the intruding aircraft.
Then may occur a Resolution Advisory : RA. Some RA will only advise to monitor vertical
speed (preventive RA). Others will advise to maneuver the aircraft.
The following procedures should then apply :
Sense of Resolution Advisory asking to maneuver
DESCEND
CLIMB
CPT
- Confirm “We descend.”.
PF
- Disconnect Auto Pilot
PM - Select proper rating on PWR MGT
- Descent at a rate in the green
rotary selector (MCT en route or TO in
(fly to) band on PFD vertical.
other phases e.g. take off, approach
speed scale
and landing)
- Ask for eventual configuration
changes.
PF - Disconnect Auto Pilot
Advise ATC
- Apply roughly the bugged power
- Monitor IAS compared to VLE,
- Climb at a rate in the green (fly to)
VFE, VMO pointer
band on PFD vertical speed scale.
- Monitor Aircraft altitude
- Ask for eventual configuration
compared to minimum
changes.
safety altitude.
PM - Adjust power to TQ objectives
- Advise ATC
- Monitor IAS compared VS.
PM -
CPT - Confirm “We climb.”.
Note : When a climb or increase climb RA occurs with the airplane in the landing
configuration or in the go - around phase, a normal go - around procedure
should be followed including the appropriate power increase and
configuration changes.
After separation has become adequate (range increasing), TCAS will issue following RA.
“CLEAR OF CONFLICT”
Return promptly to last assigned ATC clearance.
Mod : 5948
2.02.16
PROCEDURES AND TECHNIQUES
P1
TAWS
001
APR 11
AA
GPWS WARNING
Note : When flying under daylight VMC conditions, should a warning threshold be
deliberately exceeded or encountered due to known specific terrain at certain
locations, the warning may be regarded as cautionary and the approach may be
continued
A go around shall be initiated in case warning cause cannot be identified
immediately.
J
”TERRAIN” - ” PULL UP”
- POWER . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . GO AROUND
- A/P . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF
F When flight path is safe and caution/ warning cease :
Decrease pitch attitude and accelerate.
F When speed above minimum required and V/S positive :
Clean up aircraft as necessary.
J ”SINK RATE”
Adjust pitch attitude and power to silence the warning.
J “DON’T SINK”
Adjust pitch attitude and power to maintain level or climbing flight.
J ”TOO LOW GEAR” - ”TOO LOW FLAPS” :
Perform a go around.
J ”GLIDE SLOPE”
- Establish the airplane on the glide slope.
J ”BANK ANGLE”
- Ajust roll attitude to silence the warning,
Mod 5948
2.02.16
PROCEDURES AND TECHNIQUES
P2
TAWS
001
APR 11
AA
PREDICTIVE WARNINGS
”OBSTACLE AHEAD”
J
Verify the aeroplane flight path, correct it if required, if in doubt,
perform a climb until the caution alert ceases.
J ”TERRAIN AHEAD, PULL UP”
Verify the aeroplane flight path and correct it if required, if in doubt,
perform a climb until the caution alert ceases.
J “AVOID TERRAIN”
Immediately initiate a climb and then, based on any available information but
preferably external visual reference. continue to maneuver until warning ceases.
Mod 5948
2.02.18
PROCEDURES AND TECHNIQUES
P1
FMS
AA
R Refer to FCOM part 4 (FMS user guide).
Mod : 5948
001
FEB 12
2.02.19
PROCEDURES AND TECHNIQUES
P1
HIGH LATITUDES OPERATIONS
001
APR 11
AA
CONDITIONS
Anomalous heading errors may occur on aircraft equipped with the SAGEM APIRS
AHRS during high latitude operations, where the earth’s magnetic lines of force have
inclinations of greater than 75 degrees.
PROCEDURES
- Take special care to keep the slip indicator centered in order to minimize heading
errors.
- Crosscheck AHRS heading information with GPS/GNSS.
- Continous turn of more than 360_ must be avoided; for holding, it is recommended to
fly racetrack patterns with straight flight legs of at least one minute between the U
turns.
Mod 5948
2.02.21
PROCEDURES AND TECHNIQUES
MPC
MULTI PURPOSE COMPUTER
P1
001
APR 11
AA
CONTENT
1-- APM FUNCTION LIMITATIONS/PROCEDURES . . . . . . . . . . . . . . . . . . . . . . . 2
1.1 - LIMITATIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
1.1.1 - OPERATIONS AND TECHNIQUES . . . . . . . . . . . . . . . . . . . . . .
1.1.1.1 - APM PRINCIPLE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
1.1.1.2 - APM INTERFACES . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
1.1.1.3 - APM TEST . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
1.1.2 - NORMAL PROCEDURES . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
1.1.2.1 - WEIGHT SELECTION AND COMPUTATION . . . . . . . . . . . . .
1.1.2.2 - CRUISE SPEED LOW PROCEDURE . . . . . . . . . . . . . . . . . .
1.1.3 - EMERGENCY PROCEDURES . . . . . . . . . . . . . . . . . . . . . . . . . .
1.1.4 - ABNORMAL AND FOLLOWING FAILURES PROCEDURES . . . .
1.1.4.1 - APM FAULT PROCEDURE . . . . . . . . . . . . . . . . . . . . . . . . . .
1.1.4.2 - DEGRADED PERF PROCEDURE . . . . . . . . . . . . . . . . . . . . .
1.1.4.3 - INCREASE SPEED PROCEDURE . . . . . . . . . . . . . . . . . . . .
2
2
2
3
4
5
5
6
6
6
6
7
7
1.2 - FLIGHT TIME MANAGEMENT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 8
2 - DMU PART . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9
Mod 5948
2.02.21
PROCEDURES AND TECHNIQUES
MPC
MULTI PURPOSE COMPUTER
P2
001
APR 11
AA
1 - APM FUNCTION LIMITATIONS/PROCEDURES
1.1 - LIMITATIONS
APM does not induce any specific limitation.
1.1.1 - OPERATIONS AND TECHNIQUES
1.1.1.1 - APM principle
The APM analysis is performed when the aircraft is in icing conditions: the ICING
AOA is illuminated and/or if the airframe de-- icing is selected ON and/or if ice
accretion has been detected at least once during the flight.
The APM analysis principle is to compare the aircraft theoretical drag with an
”in-- flight drag” computed with measured parameters available.
Measured parameters used by the APM are acquired each second and are
smoothed over a rolling average of 30 seconds to limit noise and error
measurements. Then, the drag is calculated over a rolling average of 60 seconds.
This means that the drag analysis alert would start after at least 90 seconds of
parameter acquisition.
The drag analysis starts as soon as the aircraft enters in icing conditions with
landing gears and flaps retracted. The APM analysis will only be done with both
engines operating.
A cruise speed monitoring will also be conducted by comparing the measured IAS to
the theoretical maximum cruise IASth.
Different alarm messages will be delivered to the crew depending on the drag
difference between computed drag and theoretical drag, and the speed difference
between measured IAS and theoretical IASth.
The alarm messages will not be delivered if the static air temperature is above 10
degrees Celsius.
Mod 5948
2.02.21
PROCEDURES AND TECHNIQUES
MPC
MULTI PURPOSE COMPUTER
AA
1 - APM FUNCTION LIMITATIONS/PROCEDURES (cont’d)
1.1.1.2. - APM Interfaces
R
Mod 5948
- PPH (POUND PER HOUR)
- KPH (KILOGRAM PR HOUR)
P3
001
DEC 13
2.02.21
PROCEDURES AND TECHNIQUES
MPC
P4
MULTI PURPOSE COMPUTER
001
APR 11
AA
1 - APM FUNCTION LIMITATIONS/PROCEDURES (cont’d)
1.1.1.3 - APM test
The APM test is activated by the crew daily, to check if all the APM components
works properly.
When the crew activated APM test and if the discrete ”APM ON/OFF” is ON
The following test sequence shall be broadcasted to CAC1/CAC2:
APM Aircrat Test
Cruise Speed Low (CSL)
Degraded Perf (DP)
Increase Speed (IS)
APM Fault
FDR Fail
FDAU Fail
”Cruise Speed Low” alarm is activated 1 second after activation of the APM Test
Then ”Degraded Perf” alarm is activated 1 second after activation of ”Cruise Speed
Low” alarm.
The other alarms are activated following the diagram here above.
All discrete outputs shall come back to inactive state when ”APM Aircraft Test” is
deactivated.
Mod 5948
2.02.21
PROCEDURES AND TECHNIQUES
MPC
MULTI PURPOSE COMPUTER
P5
001
APR 11
AA
1 - APM FUNCTION LIMITATIONS/PROCEDURES (cont’d)
1.1.2 - NORMAL PROCEDURES
1.1.2.1 - Weight Selection and Computation
Selection
To determine the aircraft theoretical and ”in-- flight” performances the aircraft weight
must be known.
On ground just before flight and as soon as the crew has computed the gross weight
on the load sheet, the crew must enter the corresponding weight in FMS
corresponding data sheet through the MCDU.
This parameter is available as ”Gross weight” parameter from two different sources
DU2/FMS1 and DU4/FMS2. Until take off, the ”Gross weight” is continuously
acquired.
- if TOW1 (from FMS1) is valid, it shall be selected.
- If TOW1 is invalid, then TOW2 (from FMS2) shall be selected if valid.
Computation
If the crew doesn’t select the take off weight before take off, then the APM shall
perform a take off weight computation at the beginning of the flight. This
computation is performed during the first minutes of the flight and before the APM
starts the drag analysis.
The actual weight is then updated in flight by internal computation.
Mod 5948
2.02.21
PROCEDURES AND TECHNIQUES
MPC
P6
MULTI PURPOSE COMPUTER
001
APR 11
AA
1 - APM FUNCTION LIMITATIONS/PROCEDURES (cont’d)
1.1.2.2 - CRUISE SPEED LOW PROCEDURE
CRUISE SPEED LOW on FMA
- Appears in cruise only, to inform the crew that an abnormal drag increase induces
a speed decrease of more than 10kt compared with the expected speed.
ICING CONDITIONS and SPEED . . . . . . . . . . . . . . . . . . . . . MONITOR
1.1.3 - EMERGENCY PROCEDURES
No specific Emergency Procedures linked to APM detection.
1.1.4 - ABNORMAL AND FOLLOWING FAILURE PROCEDURES
1.1.4.1 - APM FAULT PROCEDURE
The APM Fault light function is to inform the crew that there is a problem in the APM
computation, either in the MPC or in the aircraft wiring:
The Fault can be triggered by MPC in the following conditions:
- Invalid aircraft configuration,
- Unable to retrieve input APM parameter,
- MPC internal failure,
- TOW estimation failed.
In case of APM Fault light illumination, the crew has to select the APM OFF by
pushing on the Fault light button.
Note: As APM computation is not operative on Ground, the APM Fault is inhibited by
the computer on Ground.
Mod 5948
2.02.21
PROCEDURES AND TECHNIQUES
MPC
MULTI PURPOSE COMPUTER
P7
001
FEB 12
AA
1 - APM FUNCTION LIMITATIONS/PROCEDURES (cont’d)
1.1.4.2 - DEGRADED PERF PROCEDURE
DEGRADED PERF amber message on EWD with CAUTION light and Single Chime
and on FMA.
- Mainly appears in level flight after CRUISE SPEED LOW or in climb to inform the
crew that an abnormal drag increase induces a speed decrease or a loss of rate of
climb.
- The most probable reason is an abnormal ice accretion
R
AIRFRAME DE-- ICING . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK ON
IAS ABOVE ICING BUG + 10 KT . . . . . . . . . . . . . . . . . . MONITOR
AP (if engaged) . . . . . HOLD FIRMLY CONTROL WHEEL and DISENGAGE
R
H If SEVERE ICING conditions confirmed
Or
H If impossibility to maintain IAS above ICING BUG + 10 KT in level flight
Or
H If abnormal aircraft handling feeling
SEVERE ICING procedure (2.04.05) . . . . . . . . . . . . . . . . . . . . APPLY
H If normal conditions
SCHEDULED FLIGHT. . . . . . . . . . . . . . . . . . . . . . . . . . . . . CONTINUE
ICING CONDITIONS and SPEED. . . . . . . . . . . . . . . . . . . . MONITOR
Note: In case of APM messages “DEGRADED-- PERF” or “INCREASE-- SPEED”
Vmin OPS automatically increased by 10 kt.
R
R
1.1.4.3 - INCREASE SPEED PROCEDURE
INCREASE SPEED light illuminated flashing with CAUTION on EWD and on FMA
and Single Chime.
- Appears after DEGRADED PERF to inform the crew that the drag is abnormally
high and IAS is lower than ICING BUG + 10 KT
H If abnormal conditions confirmed
IMMEDIATELY PUSH THE STICK TO INCREASE SPEED
TO RECOVER MINIMUM IAS = ICING BUG + 10 KT
SEVERE ICING procedure (2.04.05) . . . . . . . . . . . . . . . . . . . . APPLY
R
Mod 5948
H If normal conditions
SCHEDULED FLIGHT. . . . . . . . . . . . . . . . . . . . . . . . . . . . . CONTINUE
ICING CONDITIONS and SPEED. . . . . . . . . . . . . . . . . . . . MONITOR
Note: In case of APM messages “DEGRADED-- PERF” or “INCREASE-- SPEED”
Vmin OPS automatically increased by 10 kt.
2.02.21
PROCEDURES AND TECHNIQUES
MPC
MULTI PURPOSE COMPUTER
P8
001
APR 11
AA
1.2 - FLIGHT TIME MANAGEMENT
The FDAU computes the flight time, computation starts with detection of ground/air
condition (confirmation > 1sec) and stops with detection of air/ground condition
(confirmation > 10sec).
The current Flight Number is initialized automatically from AVIONICS system (FMS1 and
FMS2) if available, otherwise manually from MCDU menu (through ACMS /MPC /INIT
TIME and FLIGHT NUMBER).
The following priority order is as follows:
(1) Initialization from FMS1,
(2) Initialization from FMS2,
(3) Initialization from DMU using parameters initialized with MCDU,
(4) Initialization with last Flight Number or null if never defined.
Mod 5948
2.02.21
PROCEDURES AND TECHNIQUES
MPC
MULTI PURPOSE COMPUTER
P9
001
APR 11
AA
2 - DMU (DATA MANAGEMENT UNIT) PART
The DMU system is dedicated to the aircraft maintenance.
The DMU has been designed to allow the user to customize the system according to his
specific application, requirements, operating environment and logistics. Programming
capabilities are provided, to allow modification of monitoring functions or implementation
of additional monitoring functions.
Mod 5948
2.02.24
PROCEDURES AND TECHNIQUES
DU
General Philosophy of use
P1
001
APR 11
AA
CONTENT
1 - NORMAL OPERATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2
2 - DEGRADED OPERATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3
3 - DISPATCH WITH ONE DU INOPERATIVE . . . . . . . . . . . . . . . . . . . . . . . . . . . 5
3-- 1 - DISPATCH WITH DU 1 INOPERATIVE . . . . . . . . . . . . . . . . . . . . . . . . . . 5
3-- 1 - DISPATCH WITH DU 3 INOPERATIVE . . . . . . . . . . . . . . . . . . . . . . . . . . 6
3-- 1 - DISPATCH WITH DU 5 INOPERATIVE . . . . . . . . . . . . . . . . . . . . . . . . . . 7
4 - DUAL DC GEN LOSS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 8
Mod 5948
2.02.24
PROCEDURES AND TECHNIQUES
DU
General Philosophy of use
P2
001
APR 11
AA
1- GENERAL
ATR 600 instrument panel is fitted with five Display Units (DU), named DU 1 to 5 from
left to right.
Different formats may be displayed on these DU: PFD (Primary Flight Display), MFD
(Multi Function Display) or EWD (Engine and Warning Display); in MFD format, the
choice exists between different pages depending on the flight phase, such as ND
(Navigation Display), SD (System Display), PERF, or other options. In normal
operation, the configuration is the following:
DU 1 (5) is dedicated to CM1 (2) PFD;
DU 3 on central panel is dedicated to EWD;
DU 2 (4) is normally dedicated to CM 1 (2) MFD.
A DISPLAY push button is located on the CAPT (F/O) SWITCHING lateral console in
order to cycle the three formats on DU 2 (4). In case of DU 2 (4) failure, this button is
switching the DU 1 (5) format.
In most of the formats, the lower part of the MFD is dedicated to VCP.
On the VCP, VHF page should be selected by default, as it is the most frequently used
page.
Mod 5948
2.02.24
PROCEDURES AND TECHNIQUES
DU
General Philosophy of use
P3
001
APR 11
AA
2- DEGRADED OPERATION
In case of DU failure, the consequence will depend on the DU position and an automatic
reversion logic is implemented so as to immediately guarantee the safety of the flight;
the highest priority is given to PFD, and then to EWD.
Then the crew remains free to choose the configuration via the DISPLAY pushbuttons,
and the Captain will decide who is PF and PM according to failure assessment and
company policy.
DU2 or 4 failure is inducing the loss of the hosted FMS and RMS functions; there is no
operational impact as the remaining FMS and RMS are taking over.
Hereunder are presented the different failure cases, and the ATR recommended policy.
DU1 failure:
PFD is automatically displayed on DU2.
ATR recommends PF is CM1, and CM2 keeps a normal configuration with two DU (PFD
and MFD).
DU2 failure:
The automatic reversion has no effect; FMS1 and RMS1 are lost.
ATR recommends PF is CM1, and CM2 keeps a normal configuration with two DU (PFD
and MFD).
DU3 failure:
The automatic reversion depends on the coupling side selected on the FGCP (the
system takes the information of PF/PNF side via the FGCP coupling selection): there is
no change on the PF side, but the EWD is displayed in place of PNF MFD.
PF can be CM1 as well as CM2; both pilots may display EWD on DU 2 or 4, thanks to the
DISPLAY pushbuttons; in case EWD is not displayed on any DU and should a Warning
or Caution occure, there will be an automatic reversion of EWD on the PM side.
ATR recommends to keep EWD displayed on PF side most of the time, and PM keeps a
normal configuration with two DU (PFD and MFD). Thanks to the high quality of the DU,
EWD remains easily readable by PM in cross view.
Mod 5948
2.02.24
PROCEDURES AND TECHNIQUES
DU
General Philosophy of use
P4
001
APR 11
AA
DU4 failure:
(Symmetrical to DU2 failure)
The automatic reversion has no effect; FMS2 and RMS2 are lost.
ATR recommends PF is CM2, and CM1 keeps a normal configuration with two DU (PFD
and MFD).
DU5 failure:
(Symmetrical to DU1 failure)
PFD is automatically displayed on DU4.
ATR recommends PF is CM2, and CM1 keeps a normal configuration with two DU (PFD
and MFD).
Mod 5948
2.02.24
PROCEDURES AND TECHNIQUES
DU
General Philosophy of use
P5
001
APR 11
AA
3- DISPATCH WITH ONE DU INOPERATIVE
According to MMEL, one DU among DU1, DU3 and DU5 may be inoperative for
dispatch, but DU2 and 4 must be operative as they are hosting FMS and RMS functions.
However all DU have the same P/N and are interchangeable; if DU2 (4) is inoperative, a
maintenance action is required to swap with DU1 (5), and dispatch is then possible
(refer to MEL).
In case of a second DU failure, several cases have to be considered, and for each case,
several solutions are possible; hereafter are presented ATR recommendations with the
objectives of providing PF with the optimal displays to fly and navigate, and PM with the
displays to communicate and monitor systems.
3.1. Dispatch with DU 1 INOP.
PF is CM1 with PFD on DU2, and CM2 keeps a normal configuration with two DU (PFD
and MFD).
In case DU2 fails, the automatic reversion has no effect; FMS1 and RMS1 are lost.
CM2 becomes PF, and CM1 tunes COM and NAV via MCDU; he/she can still monitor
navigation and systems by cross-- view on DU4 with the recommended following
configuration: DU3: EWD / DU4: MFD / DU5: PFD.
In case DU3 fails, PFD remains on DU2, and EWD is automatically displayed on DU4
(PM side). PF remains CM1.
ATR recommends the following: DU2: PFD / DU4: MFD (cruise)-- EWD (approach)/
DU5: PFD.
In case DU4 fails, the automatic reversion has no effect; FMS2 and RMS2 are lost.
The recommended configuration is the following: DU2: PFD / DU3: EWD / DU5: PFD.
PNF tunes COM and NAV via MCDU, and in VMC cruise PNF may occasionally switch
to MFD format.
In case DU5 fails, PFD is automatically displayed on DU4.
The recommended configuration is the following: DU2: PFD / DU3: EWD / DU4: PFD.
PM tunes COM and NAV via MCDU, and in VMC cruise PM may occasionally switch to
MFD format.
CAUTION : a full flexibility is offered for display selection on DU2 and DU4 via
both DISPLAY pushbuttons, and in case of DU1 and DU5 failure, the crew must
avoid any configuration without any PFD.
Mod 5948
2.02.24
PROCEDURES AND TECHNIQUES
DU
General Philosophy of use
P6
001
APR 11
AA
3.2. Dispatch with DU 3 INOP.
PF can be CM1 as well as CM2; both pilots may display EWD on DU 2 or 4, thanks to the
DISPLAY pushbuttons; in case EWD is not displayed on any DU and should a Warning
or Caution occure, there will be an automatic reversion of EWD on the PM side (the
system takes the information of PF/PM side via the FGCP coupling selection).
ATR recommends to keep EWD displayed on PF side most of the time, and PM keeps a
normal configuration with two DU (PFD and MFD). Thanks to the high quality of the DU,
EWD remains easily readable by PM in cross view.
In case DU1 fails, PFD is automatically displayed on DU2 and EWD on DU4.
ATR recommends PF is CM1 and the following configuration: DU2: PFD / DU4: MFD
(cruise)-- EWD (approach)/ DU5: PFD.
In case DU2 fails, EWD is automatically displayed on DU4; FMS1 and RMS1 are lost.
ATR recommends PF is CM1 and the following configuration: DU1: PFD / DU4: MFD
(cruise)-- EWD (approach)/ DU5: PFD.
In case DU4 fails, EWD is automatically displayed on DU2; FMS2 and RMS2 are lost.
ATR recommends PF is CM2 and the following configuration: DU1: PFD / DU2: MFD
(cruise)-- EWD (approach)/ DU5: PFD.
In case DU5 fails, PFD is automatically displayed on DU4, and EWD on DU2.
ATR recommends PF is CM2 and the following configuration: DU1: PFD / DU2: MFD
(cruise)-- EWD (approach)/ DU4: PFD.
Mod 5948
2.02.24
PROCEDURES AND TECHNIQUES
DU
General Philosophy of use
P7
001
APR 11
AA
3.3. Dispatch with DU 5 INOP.
PF is CM2 with PFD on DU4, and CM1 keeps a normal configuration with two DU (PFD
and MFD).
In case DU1 fails, PFD is automatically displayed on DU2.
The recommended configuration is the following: DU2: PFD / DU3: EWD / DU4: PFD.
PM tunes COM and NAV via MCDU, and in VMC cruise PM may occasionally switch to
MFD format.
CAUTION : a full flexibility is offered for display selection on DU2 and DU4 via
both DISPLAY pushbuttons, and in case of DU1 and DU5 failure, the crew must
avoid any configuration without any PFD.
In case DU2 fails, the automatic reversion has no effect; FMS1 and RMS1 are lost.
The recommended configuration is the following: DU1: PFD / DU3: EWD / DU4: PFD.
PM tunes COM and NAV via MCDU, and in VMC cruise PM may occasionally switch to
MFD format.
In case DU3 fails, PFD remains on DU4, and EWD is automatically displayed on DU2
(PM side). PF remains CM2.
ATR recommends the following configuration: DU1: PFD / DU2: MFD (cruise)-- EWD
(approach)/ DU4: PFD.
In case DU4 fails, the automatic reversion has no effect; FMS2 and RMS2 are lost.
PF must switch to CM1, and CM2 tunes COM and NAV via MCDU; he/she can still
monitor navigation and systems by cross-- view on DU2 with the recommended
following configuration: DU1: PFD / DU2: MFD / DU3: EWD.
Mod 5948
2.02.24
PROCEDURES AND TECHNIQUES
DU
P8
General Philosophy of use
100
FEB 12
AA
4- DUAL DC GEN LOSS
In case of dual DC GEN loss, only DU2 and DU4 remain operative.
PFD is automatically displayed DU2, and EWD on DU4, as AHRS2 and ADC2 are lost;
CM2 must switch AHRS and ADC to SYS 1 to be able to recover a normal PFD format on
DU4.
ATR recommends the following configuration:
both-- CM1 is PF and always keeps PFD on DU2; he/she monitors navigation on mini
bothboND;
both-- CM2 mainly uses DU4 in PFD format, and may temporarily switch to EWD and
bothboMFD ; he/she tunes VHF1 via VCP on MFD or MCDU1;
both - IESI is used for attitudes, IAS and altitude monitoring, and may be used to tune
bothbo VHF1 and V/ILS1; VOR, LOC and GLIDE deviations may also be displayed.
In case EWD is not displayed on any DU and should a Warning or Caution occure, there
will be an automatic reversion of EWD on PM side.
CAUTION : a full flexibility is offered for display selection on DU2 and DU4 via
both DISPLAY pushbuttons, and the crew must avoid configuration without any
PFD.
Mod 5948 + 6521
2.03.00
NORMAL PROCEDURES
P1
CONTENT
100
FEB 12
AA
2.03.00
CONTENT
2.03.01
FOREWORD
2.03.02
PRELIMINARY ( including human factor recommendations for Electronic Check List use)
2.03.03
PANEL SCAN SEQUENCE
2.03.04
FLIGHT PREPARATION
2.03.05
EXTERIOR INSPECTION
2.03.06
PRELIMINARY COCKPIT PREPARATION WITH THE USE OF GPU
2.03.07
PRELIMINARY COCKPIT PREPARATION WITH HOTEL MODE
2.03.08
FINAL COCKPIT PREPARATION
2.03.09
HOTEL MODE START UP
2.03.10
BEFORE PROPELLER ROTATION
2.03.11
BEFORE TAXI
2.03.12
TAXI
2.03.13
BEFORE TAKE OFF
2.03.14
TAKE OFF
2.03.15
CLIMB - CRUISE
2.03.16
BEFORE DESCENT - DESCENT
2.03.17
APPROACH
2.03.18
BEFORE LANDING
2.03.19
LANDING
2.03.20
GO AROUND
2.03.21
AFTER LANDING
2.03.22
PARKING
2.03.23
LEAVING THE AIRCRAFT
Mod 5948 + 6521
2.03.01
NORMAL PROCEDURES
P1
FOREWORD
AA
001
APR 11
FOREWORD
Procedures contained in this chapter are recommended by the manufacturer. They are
consistent with the other chapters of this manual, in particular 2.02 PROCEDURES AND
TECHNIQUE.
Normal procedures are not certified by the Authorities, and in the judgment of the
Manufacturer, are presented here in, as the best way to proceed from a technical and
operational stand point.
They are continuously updated, taking into account inputs from all operators and
lessons of the Manufacturer’s own experience.
In the same manner, they may be amended as needed by the Operator.
However if the FCOM is used as the on board Operational Manual, the Manufacturer
recommends channeling any suggested amendment through him for early publication
so as to maintain the consistency of the Manual.
The Operator should be aware that a complete rewriting of this chapter may be done
under his own responsability but could lead to difficulties in updating and maintaining
the necessary homogeneity with the other chapters of this manual.
Mod 5948
2.03.02
NORMAL PROCEDURES
P1
PRELIMINARY
AA
100
FEB 12
PRELIMINARY
The following sections provide expanded information related to normal procedures.
Normal procedures consist of inspections, preparations and normal check lists. All items are
listed in a sequence following a standardized scan of the cockpit panels (see section 2.03.03)
except when required by the logic of actions priority, to ensure that all actions are performed
the most efficient way.
Normal procedures are divided into phases of flight and accomplish by recall.
In the following assignation :
- CM1 refers to the Crew Member in the left hand seat
- CM2 refers to the Crew Member in the right hand seat
- PF
refers to the Pilot Flying
- PM
refers to the Pilot Monitoring
After completion of a given procedure, the related normal check list is used. The
normal check list developed by the manufacturers includes only the items that may
have a direct impact on safety and efficiency if not correctly accomplished. All normal
check lists are initiated at the Pilot’s flying command. Some normal procedures which
are non routine will be found in chapter 2.02 PROCEDURES AND TECHNIQUE and in
chapter 3.11 SPECIAL OPERATIONS.
All steps have to be performed before the first flight of the day or following a crew
change or maintenance action. Transit steps are the only ones to be completed after a
transit stop. They are grouped in the FINAL COCKPIT PREPARATION.
If there is any doubt as to whether the application of transit procedures covers
all safety aspects, the complete preparation must be accomplished.
ELECTRONIC CHECK- LISTS USE : HUMAN FACTOR RECOMMENDATIONS
Upon completing procedure, PNF need tick each item, i.e. meaning the item was
acknowledged and taken care of.
- Importance of procedure pending message:
Pending procedure notice need be carefully considered when displayed, therefore
meaning this one needs yet be performed and completed.
- Importance “PROCEDURE COMPLETED“ item:
Completed procedure item, is displayed at the end of each started procedure,
provided all items have been properly ticked. It is the only way to complete and
correctly terminate a started procedure.
- Importance “IF” statements:
Following each procedure’s ”IF” alternative proposition, PNF must carefully read and
understand these different alternatives to meet current depiction and get PF’s
approval and confirmation to comply with relevant ”IF” procedure.
Once an ”IF” case has been selected, PNF must carefully read and understand
relevant procedure’s proposition and it’s associated subtitle, obtain PF’s confirmation
before resuming corresponding associated task.
- DU failure:
Neither DU fault procedure exists and no relevant reference is made in FWS, FCOM
nor QRH.
Mod 5948 + 6521
2.03.03
NORMAL PROCEDURES
P1
PANEL SCAN SEQUENCE
AA
Mod 5948
001
APR 11
2.03.04
NORMAL PROCEDURES
P1
FLIGHT PREPARATION
AA
001
APR 11
FLIGHT PREPARATION
TECHNICAL CONDITION OF THE AIRCRAFT
The crew will verify the technical status of the aircraft in respect to airworthiness acceptability of
malfunction and influence on the flight plan, using all necessary operator’s documents, in
particular MEL (Minimum Equipment List).
WEATHER BRIEFING
The crew will receive a weather briefing which should include :
- actual and expected weather conditions for take off and climb out including
runway conditions,
- en route significant weather : winds and temperatures,
- terminal forecasts for destination and alternate airports,
- actual weather for destination and alternates for short range flights and recent
past weather if available,
- survey of the meteorological conditions at airports along the planned route.
NAV / COM FACILITIES EN ROUTE
The crew will study the latest relevant NOTAMs (NOtice To AirMen) and will check that all
required facilities at departure, destination and alternate airports are operational and that they
fulfill the appropriate requirements.
FLIGHT PLANS / OPERATIONAL REQUIREMENTS
The crew will check the company flight plan, in respect to routing, altitudes and flight time.
The crew will check the estimated load figures and will calculate maximum allowed take off
and landing weights.
The captain will decide the amount of fuel necessary for a safe conduct of the flight, taking into
consideration possible economic fuel transportation.
The captain will check ATC flight plan and ensure it is filed according to the prescribed
procedures.
Mod 5948
2.03.05
NORMAL PROCEDURES
P1
EXTERIOR INSPECTION
001
FEB 12
AA
INTRODUCTION
The exterior inspection is primarily a visual check to ensure that the overall condition
of the aircraft, the visible components and equipments are safe for the flight.
R It is performed the CM1 before each flight.
During exterior walk around, observe that the FLIGHT CONTROL SURFACES and
FLAPS are clear and memorize surfaces position.
Section content :
EXTERIOR WALK AROUND DRAWING . . . . . . . . . . . . . . . . . . . . . . . .
MAIN LEFT LANDING GEAR AND FAIRING . . . . . . . . . . . . . . . . . . . . .
LEFT WING TRAILING EDGE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
LEFT WING LEADING EDGE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
LEFT ENGINE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
LEFT FORWARD FUSELAGE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
NOSE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
RIGHT FORWARD FUSELAGE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
RIGHT ENGINE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
RIGHT WING LEADING EDGE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
RIGHT WING TRAILING EDGE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
MAIN RIGHT LANDING GEAR AND FAIRING . . . . . . . . . . . . . . . . . . . .
RIGHT AFT FUSELAGE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
TAIL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
LEFT AFT FUSELAGE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
PAGE 2
PAGE 3
PAGE 4
PAGE 4
PAGE 4
PAGE 4
PAGE 5
PAGE 5
PAGE 5
PAGE 6
PAGE 6
PAGE 6
PAGE 7
PAGE 7
PAGE 7
... / ...
Mod 5948
2.03.05
NORMAL PROCEDURES
P2
EXTERIOR INSPECTION
001
APR 11
EXTERIOR INSPECTION DRAWING
... / ...
Mod 5948
2.03.05
NORMAL PROCEDURES
P3
EXTERIOR INSPECTION
001
FEB 12
AA
EXTERIOR INSPECTION ACTIONS
MAIN LEFT LANDING GEAR AND FAIRING
R
PARKING BRAKE ACCU PRESSURE . . . . . . . . . . . . CHECK 1600 PSI MINIMUM
MAINTENANCE DOORS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CLOSED
GEAR DOORS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK
WHEELS AND TIRES . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CONDITION
BRAKE TEMPERATURE SENSORS . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK
BRAKE WEAR DETECTORS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK
LANDING GEAR STRUCTURE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK
HYDRAULIC LINES . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK
WHEEL WELL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK
UPLOCK . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OPEN
Note : On ground, the landing gear uplock box in closed position leads to red local
UNLK alarm in the cockpit.
The uplock box can be open by pulling the landing gear emergency
extension handle. Then, replace it in its initial position.
FREE FALL ASSISTER . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK
SAFETY PIN . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . REMOVED
BEACON LIGHT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK
AIR CONDITIONING PANEL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . LOCKED
PACK RAM AIR INLET . . . . . . . . . . . . . . . . . . . . . . . . . . . . . UNOBSTRUCTED
LANDING LIGHT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CONDITION
TAT PROBE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK
MAGNETIC FUEL LEVEL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . IN
... / ...
Mod 5948
2.03.05
NORMAL PROCEDURES
P4
EXTERIOR INSPECTION
001
FEB 12
AA
EXTERIOR INSPECTION ACTIONS (CONT’D)
LEFT WING TRAILING EDGE
R
FLAPS RAIL SEAL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK
FLAPS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CONDITION
EXHAUST NOZZLE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CLEAR
FLAPS POSITION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK
AILERON AND TAB . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK
STATIC DISCHARGERS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK
HORN . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CONDITION
LEFT WING LEADING EDGE
NAV AND STROBE LIGHTS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CONDITION
WING DE--ICING BOOTS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CONDITION
FUEL VENT NACA INLET . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CLEAR
MAGNETIC FUEL LEVEL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . IN
ICE DETECTOR . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK
LEFT ENGINE
R
R
LEFT COWLINGS . . . . . . . . . . . . . . . . . . . . . . . . . . ALL 4 LATCHES: CLOSED
OIL COOLING FLAPS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK
ENGINE AIR INTAKE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CLEAR
ENGINE DE--ICING BOOTS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CONDITION
SPINNER . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK
PROPELLER . . . . . . . . . . . . . . . . FEATHERED / CONDITION / FREE ROTATION
RIGHT COWLINGS . . . . . . . . . . . . . . . . . . . . . . . . . ALL 4 LATCHES: CLOSED
INNER WING LEADING EDGE AND FAIRING . . . . . . . . . . . . . . . . . CONDITION
LEFT FORWARD FUSELAGE
R
WING AND EMERGENCY LIGHTS . . . . . . . . . . . . . . . . . . . . . . . . . CONDITION
EMERGENCY EXIT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CLOSED
AVIONICS VENT OVBD VALVE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OPEN
CARGO DOOR OPERATING PANEL DOOR . . . . . . . . . . . . . . . . . . . . CLOSED
CARGO DOOR . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CLOSED AND LATCHED
O2 BOTTLE OVERBOARD DISCHARGE INDICATION . . . . . . . . . . . . . . . GREEN
ANGLE OF ATTACK PROBE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CONDITION
COCKPIT COMMUNICATION HATCH . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK
ICE EVIDENCE PROBE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CONDITION
STATIC PORTS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CLEAR
PITOT PROBES AND COVERS . . . . . . . . . . . . . . . . . . . . . CHECK / REMOVED
... / ...
Mod 5948
2.03.05
NORMAL PROCEDURES
P5
EXTERIOR INSPECTION
001
FEB 12
AA
EXTERIOR INSPECTION ACTIONS (CONT’D)
NOSE
R
R
WIPERS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CONDITION
RADOME AND LATCHES . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK
NOSE GEAR WHEELS AND TIRES . . . . . . . . . . . . . . . . . . . . . . . . CONDITION
NOSE GEAR STRUCTURE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CONDITION
TAXI & TAKE OFF LIGHTS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CONDITION
WHEEL WELL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK
FREE FALL ASSISTER . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK
SAFETY PIN . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . REMOVED
NOSE WHEEL STEERING . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CONDITION
HYDRAULIC LINES . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CONDITION
NOSE GEAR DOORS . . . . . . . . . . . . . . . . . . . . . . . . . CONDITION, 2 CLOSED
RIGHT FORWARD FUSELAGE
R
R
PITOT PROBE AND COVER . . . . . . . . . . . . . . . . . . . . . . . CHECK / REMOVED
STATIC PORTS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CLEAR
ANGLE OF ATTACK PROBE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CONDITION
EXTERNAL DC AND AC ELECTRICAL POWER ACCESS DOORS . . . . . . CHECK
EMERGENCY EXIT DOOR . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CLOSED
EMERGENCY EXIT LIGHT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CONDITION
ANTENNAS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK
WING LIGHT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CONDITION
RIGHT ENGINE
R
R
INNER WING LEADING EDGE AND FAIRING . . . . . . . . . . . . . . . . . CONDITION
LEFT COWLINGS . . . . . . . . . . . . . . . . . . . . . . . . . . ALL 4 LATCHES: CLOSED
ENGINE AIR INTAKE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CLEAR
ENGINE DE--ICING BOOTS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CONDITION
SPINNER . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK
PROPELLER . . . . . . . . . . . . . . . . FEATHERED / CONDITION / FREE ROTATION
Note : If propeller brake not set or not installed.
RIGHT COWLINGS . . . . . . . . . . . . . . . . . . . . . . . . . ALL 4 LATCHES: CLOSED
OIL COOLING FLAPS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK
... / ...
Mod 5948
2.03.05
NORMAL PROCEDURES
P6
EXTERIOR INSPECTION
001
FEB 12
AA
EXTERIOR INSPECTION ACTIONS (CONT’D)
RIGHT WING LEADING EDGE
WING DE--ICING BOOTS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CONDITION
FUEL VENT NACA INLET . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CLEAR
MAGNETIC FUEL LEVEL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . IN
NAV AND STROBE LIGHTS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CONDITION
RIGHT WING TRAILING EDGE
R
HORN . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CONDITION
STATIC DISCHARGERS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK
AILERON AND TAB . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK
FLAPS POSITION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK
EXHAUST NOZZLE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CLEAR
FLAPS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CONDITION
FLAPS RAIL SEAL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK
MAIN RIGHT LANDING GEAR AND FAIRING
R
R
R
MAGNETIC FUEL LEVEL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . IN
TAT PROBE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK
LANDING LIGHT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CONDITION
AIR CONDITIONING GROUND CONNECTION . . . . . . . . . . . . . . . . . . . . CHECK
PACK RAM AIR INLET . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CLEAR
AIR CONDITIONING PANEL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK
REFUELING CONTROL PANEL ACCESS DOOR . . . . . . CLOSED AND LATCHED
GEAR DOORS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK
LANDING GEAR STRUCTURE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK
HYDRAULIC LINES . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK
WHEEL WELL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK
UPLOCK . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OPEN
FREE FALL ASSISTER . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK
SAFETY PIN . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . REMOVED
WHEELS AND TIRES . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CONDITION
BRAKE WEAR DETECTORS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK
BRAKE TEMPERATURE SENSORS . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK
REFUELING POINT ACCESS DOOR . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK
... / ...
Mod 5948
2.03.05
NORMAL PROCEDURES
P7
EXTERIOR INSPECTION
001
FEB 12
AA
EXTERIOR INSPECTION ACTIONS (CONT’D)
RIGHT AFT FUSELAGE
R
VHF ANTENNAS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
SERVICE DOOR . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
TAIL PROP AND TAIL SKID . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
OUTFLOW VALVES . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
CHECK
CHECK
CHECK
CHECK
TAIL
FLIGHT CONTROLS ACCESS DOOR . . . . . . . . . . . . . . . . . . . . . . . . . LOCKED
VOR ANTENNAS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK
STABILIZER DE--ICING BOOTS . . . . . . . . . . . . . . . . . . . . . . . . . . . CONDITION
LOGO LIGHTS (if installed) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK
HORNS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CONDITION
STABILIZER, ELEVATORS AND TABS . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK
STATIC DISCHARGERS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK
FIN, RUDDER AND TAB . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK
TAIL CONE, NAV AND STROBE LIGHTS . . . . . . . . . . . . . . . . . . . . . . . CHECK
VORTEX GENERATORS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK
LEFT AFT FUSELAGE
WATER SERVICE PANEL ACCESS DOOR . . . . . . . . . . . . . . . . . . . . . CLOSED
TOILET SERVICE PANEL ACCESS DOOR . . . . . . . . . . . . . . . . . . . . . CLOSED
CABIN DOOR . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK
ENTRY EMER LIGHT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CONDITION
Mod 5948
2.03.06
NORMAL PROCEDURES
PRELIMINARY COCKPIT PREPARATION
P1
WITH THE USE OF GPU
001
APR 11
AA
CM2
- EMERGENCY EQUIPMENT.......................................................................CHECK
Check :
- Exit hatch closed, handle locked and safe tied, escape rope stowed
- Life jackets (if applicable) stowed
- Axe, flash lights, smoke goggles and oxygen masks stowed
- Portable fire extinguisher safe tied and pressure within green area
- Landing gear emergency extension handle stowed, cover closed
- Protective gloves
- GEAR PINS and COVERS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON BOARD
- All Circuits Breakers . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK
- PL1+2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . GI
- GUST LOCK . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ENGAGE / ON
Check GUST LOCK is properly engaged to fullfill the required conditions for PROP
BRAKE activation.
- CL 1+2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FUEL S/O
- FLAPS LEVER . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . SET
Set in accordance with Actual Flap position.
CAUTION
Do not pressurize hydraulic systems and activate flaps without clearance
from ground crew.
- LDG GEAR LEVER . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . DOWN
- EEC 1+2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . DEPRESSED IN
- BOTH WIPERS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF
- BATTERY (Toggle switch) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON
Check battery voltage on captain lateral console)
- MFC AUTO TEST . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK
Check :
- MFC 1A, 2A flashing (only if cargo door panel is closed), then MFC 1B, 2B flashing.
- EMER & ESS BUS SUPPLY INDICATOR . . CHECK ARROWS ILLUMINATED
Check battery voltage on captain lateral console.
- UNDV Light . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK EXTINGUISHED
Check battery voltage on Captain lateral console.
- IESI, DU 2&4, MCDU 1 ELECTRICALLY SUPPLIED . . . . . . . . . . . . . . CHECK
Mod 5948
2.03.06
NORMAL PROCEDURES
PRELIMINARY COCKPIT PREPARATION
P2
001
WITH THE USE OF GPU
APR 11
AA
- AVIONIC INITIALIZATION TEST . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK
Check Oral Warning, Caution, CRC sounds,
- Check DU 2, 4 display a green ”T”
- Check DU Brightness
- Check MCDU 1 ON
- GPU - DC EXT PWR P/B . . . . . . . . . . . . . . . . . . . . . . . . . . DEPRESSED / ON
Check AVAIL green light is illuminated, then depress the EXT PWR P/B :
- Check on OVERHEAD Panel
- BTC on line,
- EMER and MAIN BAT charging,
- EMER and ESS BUS supply indicator amber arrow extinguished,
- UNDV light extinguished
- DU BRIGHTNESS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK
- IESI ALIGNMENT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK
- ALERTING WINDOWS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK / CLR
- OVERHEAD PANEL SCAN . . . . . . . . . . . . . ANY WHITE LIGHT EXTINGUISH
. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . EXCEPT PROBES HTG & FUEL PUMPS
- ANNUNCIATOR LIGHT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . TEST
Check all Lights are illuminated (led test only)
- DOME LIGHT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . AS RQRD
- STBY COMPASS LIGHT . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK and OFF
- STORM LIGHT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK and OFF
- CALL & SELCAL (If installed) . . . . . . . . . . . . CHECK LIGHT EXTINGUISHED
- MIN CAB LIGHT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF
- FUEL PUMP & X FEED TESTS . . . . . . . . . . . . . . . . . . . . . . . . . . . PERFORM
FUEL PUMP & X FEED TESTS
Select ENG SD page on MFD prior to test start up.
- Initial set up : ENG PUMP 1 & 2 OFF
Check the following on OVERHEAD Panel + associated ENG SD page :
- FEED LO PR LIGHT ENG 1 + 2 . . . . . . . . . . . . . . . . . CHECK ILLUMINATED
- ENG 2 PUMP . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON
- RUN LIGHT ENG 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . ILLUMINATED
- FEED LO PR LIGHT ENG 2 . . . . . . . . . . . . . . . . . . . . EXTINGUISHED
Mod 5948
2.03.06
NORMAL PROCEDURES
PRELIMINARY COCKPIT PREPARATION
WITH THE USE OF GPU
AA
R
R
R
R
-
-
P3
001
FEB 12
- FUEL X FEED . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . DEPRESSED
- FUEL X FEED VALVE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . IN LINE
- MEMO PANEL DISPLAY FUEL X FEED LABEL . . . . . . . . DISPLAYED CYAN
Note: - X FEED LABEL may be flashing CYAN, in case of fuel unbalance & wrong
pump on selection.
- Check “X FEED” cyan label on MEMO PANEL DISPLAY
- FEED LO PR LIGHT ENG 1+2 . . . . . . . . . . . . . . . . . . . . . . . EXTINGUISHED
- FUEL X FEED . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . RELEASED
- FEED LO PRESS LIGHT ENG 1 . . . . . . . . . . . . . . . . . . . . . . . ILLUMINATED
Note : Feed Lo Press Light may take few minutes to illuminate again
- ENG 1 PUMP . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON
- RUN LIGHT ENG 1 . . . . . . . . . . . . . . . . . . . . . . . . . . . . ILLUMINATED
- FEED LO PR LIGHT ENG 1+2 . . . . . . . . . . . . . . . . . . EXTINGUISHED
ENG 1+2 FUEL PUMPS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK ON
DOORS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . TEST
DOOR TEST :
Depress TEST switch and check on OVERHEAD Panel. Check associated AIR
CABIN SD page :
- CAB OK & SVCE OK green lights . . . . . . . . . . . . . . . . . . . . . . . ILLUMINATE
(Provided associated doors are opened)
SPOILER LIGHTS . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK EXTINGUISHED
LDG GEAR INDICATOR . . . . . . . . . . . . . . CHECK 3 GREEN / NO RED LIGHT
TLU . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . AUTO
FLT CTL Fault Light . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . EXTINGUISHED
SELCAL (If installed) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK CODE
ENG 1 FIRE TEST . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . PERFORM
ENGINE FIRE PROTECTION TEST :
Check the following items :
- ENG 1 FIRE HANDLE . . . . . . . . . . . . . . . . . . . IN / LATCHED / LOCK WIRED
- Any lights . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . EXTINGUISHED
- Depress SQUIB TEST P/B and check :
- Both agents SQUIB lights . . . . . . . . . . . . . . . . . . . . . . . . ILLUMINATE
- Select TEST SW on FAULT position and check :
- Associated LOOP A and LOOP B lights . . . . . . . . . . . . . . ILLUMINATE
- SC . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . SOUNDS
- MC Amber light . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ILLUMINATES
- LOOP (FWS ALERTING WINDOW) . . . . . . . . . . . DISPLAYED AMBER
- Select TEST SW on FIRE position and check :
- Associated FIRE HANDLE red light . . . . . . . . . . . . . . . . ILLUMINATES
- CRC . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . SOUNDS
- MW light . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ILLUMINATES
- ENG 1 FIRE (EWD + FWS WINDOW) . . . . . . . . . . . DISPLAYED RED
- Press MW to silence CRC and extinguish the MW :
- Temporarily select CL out of FUEL S O Position and check :
- Associated CL FUEL S O red light . . . . . . . . . . . . .ILLUMINATES
Mod 5948
2.03.06
NORMAL PROCEDURES
PRELIMINARY COCKPIT PREPARATION
P4
WITH THE USE OF GPU
001
FEB 12
AA
R - EXTERNAL LIGHTS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . AS RQD
- PROP BRK . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON / LOCKED
Check PROP BRK Local Cyan light + EWD Cyan label
- ENG START Rotary selector . . . . . . . . . . . . . . . . . . . . . . OFF/START ABORT
- MAIN ELEC PWR Panel + associated ELEC SD page on MFD . . . . . . CHECK
- CVR and SSFDR TEST . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . PERFORM
CVR TEST :
CVR and DFDR test, on GPU:
Press on the RCDR PB (on the RCDR panel) and check ON light is illuminated.
CVR: when pushing on the CVR TEST PB, the CVR pointer has to be in the green
arc.
Press on the RESET PB (on the RCDR panel) and check ON light is extinguished.
- SIGNS PANEL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK
Also check the MEMO PANEL
- EMER EXIT LT TOGGLE SW . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ARM
- EMER EXIT LT DISARM light . . . . . . . . . . . . . . . . . . . . . . . . EXTINGUISHED
- DE ICING / ANTI ICING lights . . . . . . . . . . . . . . . . . . . . . . . . EXTINGUISHED
Except AFR AIR BLEED Amber light illuminated.
- PROBES HEATING . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .OFF
Switch off PROBES HEATING to avoid any burn injury to ground crew.
(STBY PITOT TUBE is supplied by DC STBY BUS.)
R - WINDSHIELD HEATING . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .ON
- AC WILD ELEC PWR . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK
Check on OVERHEAD Panel and associated ACW - HYD SD page
- HYD PWR . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK
Check on OVERHEAD panel :
- BLUE and GREEN PUMPS LO PR AMBER lights . . . . . ILLUMINATED
- Other LIGHTS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . EXTINGUISHED
Check on ACW-- HYD SD Page on MFD :
- BLUE and GREEN PUMPS LO PR . . . . . . . . . . . . . . . . . . . . . . . . . .
- FLAPS, SPOILERS, PROP BRK, N/W STRG . . . . . . . . . . . . . . . . . .
- EMER BRK ACCU . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
- NORM BRK, LDG GEAR . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
AMBER
AMBER
CHECK
AMBER
- EMER LOC XMTR . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . AUTO / NO LIGHT
Check toggle SW is in AUTO position, guarded and lock wired
R - ANN LT SW Position. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . AS RQD
Mod 5948
2.03.06
NORMAL PROCEDURES
PRELIMINARY COCKPIT PREPARATION
WITH THE USE OF GPU
P5
001
FEB 12
AA
- AIR BLEED / COMPT TEMP Panel . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK
Check on OVERHEAD Panel & associated AIR CABIN SD page
- AVIONICS VENT / OVBD VALVE . . . . . . . . . . . . . . . . . . . . AUTO / GUARDED
- OXYGEN PANEL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK
Check on OVERHEAD Panel & associated AIR CABIN SD page
- OXYGEN PRESS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK
- OXYGEN MAIN SUPPLY ON OVERHEAD Panel . . . . . . . . . . . . . . . . . ON
Check OXY SUPPLY CREW on AIR CABIN SD page . . . . . GREEN ARROW
- PAX SUPPLY . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . NO LIGHT
- COMPT SMK . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . TEST
Depress SMK TEST P/B and check :
- On Alerting Window : AFT SMK, FWD SMK, ELEC SMK . . . . . . . . . . . . RED
- On AIR CABIN SD page : LAV SMK, AFT COMPT SMK, FWD SMK, ELEC SMK
RED
- MW + MC + CRC . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ACTIVATE
- Press MW to silence the alarm
- AVIONICS VENT EXHAUST MODE P/B . . . . . . . . . . . . . . . . . . . . . . . . RESET
When test is over, press the exhaust P/B to restart the extract fan. (MECH call with
sound during reset)
- ENG 2 FIRE TEST . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . PERFORM
PEDESTAL
- ATPCS TEST . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . PERFORM
R ATPCS: STATIC TEST
Check the following results on EWD.
- Turn the ATPCS knob to the left to the arm position and check :
- ARM light . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ILLUMINATES
- TQ needles . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . > 60 %
- Turn the ATPCS knob to ENG 1 position and check :
- ENG 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . UPTRIM
- TQ 1 needle indicates . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ZERO
- After 2.15 s :
- ARM light . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . EXTINGUISHES
- ENG 1 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . AUTO FTR
- Turn the ATPCS knob to the right to the arm position and check :
- ARM light . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ILLUMINATES
- TQ needles . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . > 60 %
.../...
Mod 5948
2.03.06
NORMAL PROCEDURES
PRELIMINARY COCKPIT PREPARATION
WITH THE USE OF GPU
P6
001
FEB 12
AA
- Turn the ATPCS knob to ENG 2 position and check :
- ENG 1 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . UPTRIM
- TQ 2 needle indicates . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ZERO
- After 2.15s :
- ARM light . . . . . . . . . . . . . . . . . . . . . . . . . . . . EXTINGUISHES
- ENG 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . AUTO FTR
- TRIMS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK
TRIMS TEST
R TRIMS TEST
TRIMS CHECK BEFORE EACH FLIGHT
PITCH, ROLL AND YAW TRIM OPERATION . . . . . . . . . . . . . . . . . . . . CHECK
STBY PITCH TRIM OPERATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK
STBY PITCH TRIM SW . . . . . . . . . . . . . CHECK GUARDED / OFF POSITION
TRIMS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . RESET FOR TAKE OFF
TRIMS CHECK FOR THE FIRST FLIGHT OF THE DAY : (DAILY) refer to 2.03.24
- IDLE GATE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK
Check the IDLE GATE FAIL amber light is extinguished.
Check the IDLE GATE lever amber band is visible.
- EMER AUDIO CANCEL . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK GUARDED
- PARKING BRK . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .ON
Check ACCU BRAKE pressure on the dedicated indicator (Captain lateral console)
or on SD ACW-- HYD Page.
Use HYD AUX PUMP P/B if required.
WARNING
Do not pressurize hydraulic systems without cleareance from ground
crew.
- GUST LOCK . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .ON
- VCP : COM, NAV, SURV . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . SET / CHECK
- NAV ND OVLY / TRAFFIC set to ABOVE position
- SURV / XPDR 1 or 2 set to STBY
- TCAS set to AUTO
Mod 5948
2.03.06
NORMAL PROCEDURES
PRELIMINARY COCKPIT PREPARATION
WITH THE USE OF GPU
P7
001
NOV 14
AA
- MCDU BRIGHTNESS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK
- RADAR . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . STBY
Check “WAIT or STBY” green message on ND/PFD.
- COCKPIT DOOR LOCKING SYSTEM . . . . . . . . . . . . . . . . . . . . . . . . . CHECK
COCKPIT DOOR DAILY CHECK: . . . . . . . . . . . . . . . . . . . . . . refer to 2.03.24
CENTRAL PANEL
- ICE DETECT PANEL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . TEST/ CHECK
- STICK PUSHER . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK NO LIGHT
- APM P/B . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK NO LIGHT
- APM TEST . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . PERFORM
APM TEST: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . refer to 2.03.24
- PEC 1+2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . DEPRESSED IN/NO LIGHT
- ENG BOOST FUNCTION (If installed) . . . . . . . . . . . . . . . . . . . . . . . . . CHECK
ENG BOOST FUNCTION TEST (If installed) . . . . . . . . . . . . . . refer to 2.03.24
- PWR MGT rotary selector . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . TO
- IESI . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .CHECK NO FLAG
- EWD :
- EWD FLIGHT CONTROL window . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK
Check TRIMS and FLAPS, indications
- ENG 1 & 2 INSTRUMENTS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .CHECK
Check TQ, RTO TQ, TO TQ, NP, ITT
- TAT / SAT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .CHECK
ENG PANEL :
- EEC 1&2 P/B . . . . . . . . . . . . . . . . . . . CHECK DEPRESSED IN / NO LIGHT
- ATPCS P/B . . . . . . . . . . . . . . . . . . . . . CHECK DEPRESSED IN / NO LIGHT
- CAB PRESS PANEL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK
Check no light
Check the rotary selector is facing the green mark
Mod 5948
2.03.06
NORMAL PROCEDURES
PRELIMINARY COCKPIT PREPARATION
P8
WITH THE USE OF GPU
001
FEB 12
AA
R - AUTO PRESS PANEL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . TEST / CHECK
Depress the TEST P/B and check :
- On local panel :
- Cycling display between - 8800 and 18800 . . . . . . . . . . . . . . . CHECK
- MC + SC + AIR AUTO PRESS on Alerting Window (1 flash) . . . CHECK
- MODE SEL P/B FAULT amber light (1 flash) . . . . . . . . .ILLUMINATED
- CABIN SD page :
CAB ALT / VS / ∆P . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK
- LANDING GEAR INDICATIONS . . . . . . . . . . . . . . . . . . 3 GREEN / NO RED LT
ANTISKID PANEL P/B depressed in, no LIGHT . . . . . . . . . . . . . . . . . . . CHECK
GLARESHIELD :
- GPWS P/B TEST . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .PERFORM
CAPTAIN LATERAL CONSOLE
- COCKPIT COM HATCH . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OPEN
Cockpit com hatch must be opened until engine 1 start, in order to avoid that the
extract fan suction creates a depressurisation when passenger doors is closed.
(Ref. procedure and techniques 2.02.03).
- MAINTENANCE PANEL
- STICK PUSHER / SHAKER TEST (once a day) . PERMORM (refer to 2.03.24)
- ROTARY SELECTOR . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK NORM FLT
- N/W STEERING . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .AS RQD
- OXYGEN MASK (once a day) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK
OXYGEN MASK TEST (Hose and mask must be pressurized with oxygen)
- DO NOT REMOVE OXYGEN MASK
Mod 5948
2.03.06
NORMAL PROCEDURES
PRELIMINARY COCKPIT PREPARATION
P9
001
WITH THE USE OF GPU
FEB 12
AA
R - AUDIO CONTROL PANEL INT / RAD selector . . . . . . . . . . . . . . . . . . . . . . INT
1 - PRESS TO TEST & RESET P/B . . . . . . . . . . . . . . . . . . . . . . PRESS & HOLD
Check :
- Blinker momentarily turns yellow and then goes black (if no leak).
- Oxygen flow sounds through loudspeakers
2 - PRESS TO TEST AND RESET PB . . . . . . . . . . . . . . . . . . . . . . . . . . . . HOLD
RED GRIPS ON EACH SIDE OF THE HOSE . . . . . . . . . . . . . SQUEEZE
Check :
- Oxygen pressure inflates the harness.
- Blinker momentarily turns yellow and must turn dark if there is no leak.
- Oxygen flow sounds through loudspeakers
3 - PRESS TO TEST AND RESET PB . . . . . . . . . . . . . . . . . . . . . . . . . . . . HOLD
EMERGENCY KNOB . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . SELECT
Check :
- Blinker momentarily turns yellow and must turn dark if there is no leak
- Oxygen flow sounds through loudspeakers.
CAUTION:
WHEN TEST COMPLETED : Insure the oxygen mask control panel
remain in the following position :
- OXY LO PR LIGHT . . . . . . . . . . . . . . . . . . . CHECK
EXTINGUISHED
- N/100% ROCKER LEVER . . . . . . . . . . . . . SET TO 100 %
- CAPTAIN SWITCHING PANEL :
- AUDIO 1 SEL Light . . . . . . . . . . . . . . . . . . . . . . . CHECK EXTINGUISHED
- ATT/HDG, ADC . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK EXTINGUISHED
- TAWS PANEL :
- TERR . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . GUARDED NO LIGHT
- GPWS TOGGLE SWITCH . . . . . . . . . . . . . GUARDED / NORMAL POSITION
- GPWS Associated light . . . . . . . . . . . . . . . . . . . . . . . . . . . EXTINGUISHED
CAPTAIN INSTRUMENT PANEL
- CLOCK TIME . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK
- PFD :
- FMA . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK
- AIRSPEED, ALTIMETER, VSI. . . . . . . . . . . . . . . . . . . . . . CHECK NO FLAG
- EADI . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK ATTITUDE
- EHSI . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK
Mod 5948
2.03.06
NORMAL PROCEDURES
PRELIMINARY COCKPIT PREPARATION
WITH THE USE OF GPU
P 10
001
FEB 12
AA
R
- ND / EHSI : (Select ND on MFD)
- HDG . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CROSS CHECK & NO FLAG
- MEMO PANEL DISPLAY . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK
F/O LATERAL CONSOLE
- EXTRACT AIRFLOW . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OPEN / GUARDED
- OXYGEN MASK (once a day) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .CHECK
F/O SWITCHING PANEL :
- AUDIO SEL 2 Light . . . . . . . . . . . . . . . . . . . . . . . . . .CHECK EXTINGUISHED
- ATT/HDG, ADC . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK EXTINGUISHED
- ELAPSE TIME . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF / RESET
F/O INSTRUMENT PANEL
- CLOCK TIME . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK
- PFD :
- FMA . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK
- AIRSPEED, ALTIMETER, VSI . . . . . . . . . . . . . . . . . . . . . CHECK NO FLAG
- EADI . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK ATTITUDE
- ND / EHSI : (Select NAV Display on MFD)
- HDG . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CROSS CHECK & NO FLAG
- MEMO PANEL DISPLAY.......CHECK
- SYS PAGE
- AC/DC ELEC Page . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK
- CABIN Page . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK
- ACW HYD Page . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK
- ENGINE Page . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK
Mod 5948
2.03.07
NORMAL PROCEDURES
PRELIMINARY COCKPIT PREPARATION
P1
WITH HOTEL MODE
AA
001
APR 11
CM2
- EMERGENCY EQUIPMENT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK
Check :
- Exit hatch closed, handle locked and safe tied, escape rope stowed
- Life jackets (if applicable) stowed
- Axe, flash lights, smoke goggles and oxygen masks stowed
- Portable fire extinguisher safe tied and pressure within the green area
- Landing gear emergency extension handle stowed, cover closed
- Protective gloves
- GEAR PINS and COVERS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON BOARD
- All Circuit Breakers . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK
- PL 1 + 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . GI
- GUST LOCK . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ENGAGE / ON
Check GUST LOCK is properly engaged to fullfill the required conditions for PROP
BRAKE activation.
- CL 1 + 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FUEL S/O
- FLAPS LEVER . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . SET
Set in accordance with Actual Flap Position.
CAUTION
Do not pressurize hydraulic systems and activate flaps without
clearance from ground crew.
- LDG GEAR LEVER . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . DOWN
- EEC 1+2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . DEPRESSED IN
- BOTH WIPERS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF
- BATTERY (Toggle switch) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON
Check battery voltage on captain lateral console
- MFC AUTO TEST . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . PERFORMED
Check :
MFC 1A, 2A flashing (only if cargo door panel is closed), then MFC 1B, 2B
flashing)
- EMER & ESS BUS SUPPLY INDICATOR . . CHECK ARROWS ILLUMINATED
- UNDV light . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK EXTINGUISHED
Check battery voltage on Captain lateral console.
- IESI, DU 2&4, MCDU 1 ELECTRICALLY SUPPLIED . . . . . . . . . . . . . . CHECK
Mod 5948
2.03.07
NORMAL PROCEDURES
PRELIMINARY COCKPIT PREPARATION
WITH HOTEL MODE
P2
001
APR11
AA
- AVIONIC INITIALIZATION TEST . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK
Check Oral Warning, Caution, CRC sounds,
- Check DU 2, 4 display a green “T”
- Check DU Brightness
- Check MCDU 1 ON
- IESI ALIGNMENT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK
- ALERTING WINDOWS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK / CLR
- ENG 2 FIRE TEST . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . PERFORM
ENGINE FIRE PROTECTION TEST :
Check the following items :
- ENG 2 FIRE HANDLE . . . . . . . . . . . . . . IN / LATCHED / LOCK WIRED
- Any lights . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . EXTINGUISHED
- Depress SQUIB TEST P/B and check :
- Both agents SQUIB lights . . . . . . . . . . . . . . . . . . . . . . ILLUMINATE
- Select TEST SW on FAULT position and check :
- Associated LOOP A and LOOP B lights . . . . . . . . . . . . ILLUMINATE
- SC . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . SOUNDS
- MC Amber light . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ILLUMINATES
- LOOP (EWD + ALERTING WINDOW) . . . . . . . DISPLAYED AMBER
- Select TEST SW on FIRE position and check :
- Associated FIRE HANDLE red light . . . . . . . . . . . . . . ILLUMINATES
- CRC . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . SOUNDS
- MW light flashing red . . . . . . . . . . . . . . . . . . . . . . . . . ILLUMINATES
- ENG 2 FIRE (EWD + ALERTING WINDOW) . . . . DISPLAYED RED
- Press MW to silence CRC and extinguish the MW
- Temporarily select CL out of FUEL S O Position and check :
- Associated CL FUEL S O red light . . . . . . . . . . . . . ILLUMINATES
Mod 5948
2.03.07
NORMAL PROCEDURES
PRELIMINARY COCKPIT PREPARATION
WITH HOTEL MODE
AA
P3
001
APR 11
- ATPCS TEST . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . PERFORM
ATPCS TEST :
Check the following results on EWD :
- Turn the ATPCS knob to the left to the arm position and check :
- ARM light . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ILLUMINATES
- TQ needle . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . > 60 %
- Turn the ATPCS knob to ENG 1 position and check :
- ENG 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . UPTRIM
- TQ 1 needle indicates . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ZERO
- After 2.15s :
- ARM light . . . . . . . . . . . . . . . . . . . . . . . . . . . . . EXTINGUISHES
- ENG 1 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . AUTO FTR
- Turn the ATPCS knob to the right to the arm position and check :
- ARM light . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ILLUMINATES
- TQ needles . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . > 60 %
- Turn the ATPCS knob to ENG 2 position and check :
- ENG 1 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . UPTRIM
- TQ 2 needles indicates . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ZERO
- After 2.15s :
- ARM light . . . . . . . . . . . . . . . . . . . . . . . . . . . . . EXTINGUISHES
- ENG 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . AUTO FTR
- SERVICE DOOR . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CLOSED
- FUEL PUMP 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON
Check RUN LIGHT ON + FEED LO PRESS extinguished
- WING LIGHTS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON
- PROP BRK . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON / LOCKED
Check PROP BRK Local Cyan light + EWD Cyan label
- ENG 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . START IN HOTEL MODE
CAUTION
Prior to any engine start, select ENG SD page
Mod 5948
2.03.07
NORMAL PROCEDURES
PRELIMINARY COCKPIT PREPARATION
WITH HOTEL MODE
AA
P4
001
FEB 12
START SEQUENCE:
- ENGINE PROP AREA . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK CLEAR
- ENGINE START rotary selector . . . . . . . . . . . . . . . . . . . . . . . . . START A + B
A+B for the 1st flight of the day, then A or B for the next start
- START 2 P/B . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . DEPRESSED / ON
Start timing for maximum starter run time
Check : - START P/B ON light illuminates
- START green label on ENG SD page.
- ENGINE ROTATION (NH) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MONITOR
S When passing 10 % NH (maximum 19% NH if ITT > 200°c) :
- CL 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FTR
- TIMING . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK
- ITT rises within 10s . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK
R ENGINE START IN HOT ENVIRONMENT
In hot environments to prevent an engine starting from a “hot start“: High OAT or High
residual ITT, it is recommended to delay the fuel opening up to 20% NH.For residual ITT
below 100°C, open fuel up to 10% NH.
From 100°C to 200°C delay fuel opening by 1% NH per 10°C of residual ITT, up to 200°C
(20% NH)
Do not exceed 20% NH for fuel opening.
CAUTION
- If ITT >950°c
- If 840 < ITT < 950°C for more than 5s
- If 800 C°° < ITT < 840°C for more than 20s
R
R
R
R
} CL..................FUEL SO
} CL..................FUEL SO
} CL..................FUEL SO
S When passing 45 % NH :
- Check:
- START green label EXTINGUISHES on FUEL-- ENG SD page
- START P/B ON light extinguished
- Check maximum start time and max ITT (Refer to Limitation chap 2.01.04)
S When engines parameters are stabilized :
- ENGINE START ROTARY SELECTOR . . . . . . . . OFF/START ABORT
- GPU . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF
- DC GEN 2 FAULT LIGHT . . . . . . . . . . . . . . . . . . . . . . EXTINGUISHED
- DC BTC . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CLOSED
- BLEED / PACK / X VALVE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OPEN
- PL 1 + 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ADJUST AS RQD
GIf Z > 5000ft and SAT > ISA + 25C°, advance PL 2 up to the GUST LOCK stop.
Mod 5948
2.03.07
NORMAL PROCEDURES
PRELIMINARY COCKPIT PREPARATION
WITH HOTEL MODE
P5
001
FEB 12
AA
R - OVERHEAD PANEL SCAN . . . . . . . . . . . . . ANY WHITE LIGHT EXTINGUISH
R
EXCEPT PROBES HTG & FUEL PUMP
R - ANNUNCIATOR LIGHT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . TEST
R Check all Lights are illuminated (led test only)
R - DOME LIGHT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . AS RQD
R - STBY COMPASS LIGHT . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK AND OFF
R - STORM LIGHT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK AND OFF
- CALL & SELCAL (If installed) . . . . . . . . . . . . CHECK LIGHT EXTINGUISHED
- MIN CAB LIGHT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF
- FUEL PUMP & X FEED TESTS . . . . . . . . . . . . . . . . . . . . . . . . . . . PERFORM
FUEL PUMP & X FEED TESTS
Select FUEL-- ENG SD page on MFD prior to test start up.
Initial set up : ENG PUMP 1 OFF
Check the following on OVERHEAD panel + associated FUEL-- ENG SD page :
- FEED LO PR LIGHT ENG 1 . . . . . . . . . . . . . . . . . . . . CHECK ILLUMINATED
- ENG 2 PUMP . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON
- RUN LIGHT ENG 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ILLUMINATED
- FEED LO PR LIGHT ENG 2 . . . . . . . . . . . . . . . . . . . . . . . . . EXTINGUISHED
- FUEL X FEED . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . DEPRESSED
- FUEL X FEED VALVE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . IN LINE
- MEMO PANEL DISPLAY FUEL X FEED LABEL . . . . . . . . ILLUMINATE CYAN
Note: X FEED LABEL may be flashing CYAN, in case of fuel unbalance &
wrong pump on selection. Check “X FEED” blue cyan on MEMO PANEL.
- FEED LO PR LIGHT ENG 1+2 . . . . . . . . . . . . . . . . . . . . . . . EXTINGUISHED
- FUEL X FEED . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . REALEASED
- FEED LO PR LIGHT ENG 1 . . . . . . . . . . . . . . . . . . . . . . . . . . .ILLUMINATED
Note : Feed Lo Press Light may take few minutes to illuminate again.
- ENG 1 PUMP . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON
- FEED LO PR LIGHT ENG 1+2 . . . . . . . . . . . . . . . . . . . . . . . EXTINGUISHED
- ENG 1+2 FUEL PUMPS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK ON
- DOORS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . TEST
DOOR TEST :
Depress TEST switch and check on OVERHEAD Panel and associated AIR SD
page :
- CAB OK & SVCE OK green lights . . . . . . . . . . . . . . . . . . . . . . . ILLUMINATE
(provided associated doors are opened)
- SPOILER LIGHTS . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK / EXTINGUISED
- LDG GEAR INDICATOR . . . . . . . . . . . . . . CHECK 3 GREEN / NO RED LIGHT
Mod 5948
2.03.07
NORMAL PROCEDURES
PRELIMINARY COCKPIT PREPARATION
WITH HOTEL MODE
P6
001
FEB 12
AA
- TLU . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .AUTO
- FLT CTL Fault light . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . EXTINGUISHED
- SELCAL (if installed) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK CODE
- ENG 1 FIRE TEST . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . PERFORM
ENGINE FIRE PROTECTION TEST :
Check the following items :
- ENG 1 FIRE HANDLE . . . . . . . . . . . . . . . . . . . . IN / LATCHED / LOCK WIRE
- Any lights . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . EXTINGUISHED
- Depress SQUIB TEST P/B and check :
- Both agents SQUIB lights. . . . . . . . . . . . . . . . . . . . . . . . . ILLUMINATE
- Select TEST SW on FAULT position and check :
- Associated LOOP A and LOOP B lights . . . . . . . . . . . . . . ILLUMINATE
- SC . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . SOUNDS
- MC Amber light . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ILLUMINATES
- LOOP (ALERTING WINDOW) . . . . . . . . . . . . . . . DISPLAYED AMBER
- Select TEST SW on FIRE position and check :
- Associated FIRE HANDLE red light . . . . . . . . . . . . . . . . ILLUMINATES
- CRC . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . SOUNDS
- MW light flashing . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ILLUMINATES
- ENG 1 FIRE (EWD + ALERTING WINDOW) . . . . . . DISPLAYED RED
- Press MW to silence CRC and extinguish the MW
- Temporarily select CL out of FUEL S O Position and check :
- Associated CL FUEL S O red light . . . . . . . . . . . . . . . ILLUMINATES
- EXTERNAL LIGHTS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . AS RQRD
- ENG START Rotary selector . . . . . . . . . . . . . . . . . . . . . OFF / START ABORT
- MAIN ELEC PWR Panel + associated ELEC SD page on MFD . . . . . . CHECK
DC GEN 2 extinguished. BTC on line, EMER and MAIN BAT charging, EMER and ESS
BUS supply indicator amber arrow extinguished, UNDV light extinguished.
- CVR and SSFDR TEST . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . PERFORM
R CVR TEST :CVR and DFDR test (On BATTERY MODE or HOTEL MODE):
R CVR: when pushing on the CVR TEST PB, the CVR pointer has to be in the green
arc.
R DFDR: the status SYST light (on the FDEP or RCDR panel) has to be extinguished.
R Note: it can take over 1 minute to be extinguished after aircraft power up.
Mod 5948
2.03.07
NORMAL PROCEDURES
PRELIMINARY COCKPIT PREPARATION
P7
WITH HOTEL MODE
001
FEB 12
AA
- SIGNS PANEL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK
Also check the MEMO PANEL
- EMER EXIT LT TOGGLE SW . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ARM
- EMER EXIT LT DISARM light . . . . . . . . . . . . . . . . . . . . . . . . EXTINGUISHED
- DE ICING / ANTI ICING Lights . . . . . . . . . . . . . . . . . . . . . . . EXTINGUISHED
Except AFR AIR BLEED Amber light illuminated.
- PROBES HEATING . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF
Switch off PROBES HEATING to avoid any burn injury to ground crew.
R (STBY PITOT TUBE is supplied by DC STBY BUS).
R - WINDSHIELD HEATING . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON
- AC WILD ELEC PWR . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK
Check on OVERHEAD Panel and associated ACW-- HYD SD page
- HYD PWR . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK
Check on OVERHEAD panel :
- BLUE and GREEN PUMPS LO PR AMBER lights . . . . . . . . . . ILLUMINATED
- Other LIGHTS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . EXTINGUISHED
Check on ACW-- HYD SD Page on MFD
Check on HYD SD Page on MFD :
- BLUE and GREEN PUMPS LO PR . . . . . . . . . . . . . . . . . . . . . . . . . .
- FLAPS, SPOILER, PROP BRK, N/W STRG . . . . . . . . . . . . . . . . . . . .
- EMER BRK ACCU . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
- NORM BRK, LDG GEAR . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
AMBER
AMBER
CHECK
AMBER
- EMER LOC XMTR . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . AUTO / NO LIGHT
Check toggle SW is in AUTO position, guarded and lock wired
- ANN LT SW Position . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . AS RQD
- AIR BLEED / COMPT TEMP Panel . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK
Check on OVERHEAD Panel & associated CABIN SD page
- AVIONICS VENT / OVBD VALVE . . . . . . . . . . . . . . . . . . . . AUTO / GUARDED
- OXYGEN PANEL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK
Check on OVERHEAD Panel & associated CABIN SD page
- OXYGEN PRESS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK
- OXYGEN MAIN SUPPLY ON OVERHEAD Panel . . . . . . . . . . . . . ON
Check OXY SUPPLY CREW on CABIN SD page . . . . . GREEN ARROW
- PAX SUPPLY . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . NO LIGHT
Mod 5948
2.03.07
NORMAL PROCEDURES
PRELIMINARY COCKPIT PREPARATION
WITH HOTEL MODE
P8
001
FEB 12
AA
- COMPT SMK . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . TEST
Depress SMK TEST P/B and check :
- On Alerting Window : AFT SMK, FWD SMK, ELEC SMK . . . . . . . . . . . . RED
- On CABIN SD page: LAV SMK, AFT COMPT SMK, FWD SMK, ELEC SMK....RED
- MW + MC + CRC . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ACTIVATE
- Press MW to silence the alarm
- AVONICS VENT EXHAUST MODE P/B . . . . . . . . . . . . . . . . . . . . . . . . RESET
When test is over, press the exhaust P/B to restart the extract fan. (MECH call will
sound during reset).
PEDESTAL
- TRIMS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK
R TRIMS TEST
TRIMS CHECK BEFORE EACH FLIGHT
PITCH, ROLL AND YAW TRIM OPERATION . . . . . . . . . . . . . . . . . . . . CHECK
STBY PITCH TRIM OPERATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK
STBY PITCH TRIM SW . . . . . . . . . . . . . CHECK GUARDED / OFF POSITION
TRIMS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . RESET FOR TAKE OFF
TRIMS CHECK FOR THE FIRST FLIGHT OF THE DAY : (DAILY) refer to 2.03.24
- IDLE GATE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK
Check the IDLE GATE FAIL amber light is extinguished
Check the IDLE GATE lever amber band is visible
- EMER AUDIO CANCEL . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK GUARDED
- PARKING BRK . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON
Check ACCU BRAKE pressure on the dedicated indicator (Captain lateral console) or
on SD ACW-- HYD Page.
Use HYD AUX PUMP P/B if required.
WARNING
Do not pressurize hydraulic systems without clearance from ground crew.
Mod 5948
2.03.07
NORMAL PROCEDURES
PRELIMINARY COCKPIT PREPARATION
WITH HOTEL MODE
P9
001
FEB 12
AA
- GUST LOCK . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON
- VCP : COM, NAV, SURV . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . SET / CHECK
- NAV ND OVLY / TRAFFIC set to ABOVE position
- SURV / XPDR 1 or 2 set to STBY
- TCAS set to AUTO
- MCDU BRIGHTNESS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK
- RADAR . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . STBY
Check “STBY” message on ND/PFD.
R - COCKPIT DOOR LOCKING SYSTEM . . . . . . . . . . . . . . . . . . . . . . . . . CHECK
COCKPIT DOOR DAILY CHECK . . . . . . . . . . . . . . . . . . . . . . . . . refer to 2.03.24
Mod 5948
2.03.07
NORMAL PROCEDURES
PRELIMINARY COCKPIT PREPARATION
WITH HOTEL MODE
P 10
001
NOV 14
AA
CENTRAL PANEL:
- ICE DETECT PANEL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . TEST / CHECK
- STICK PUSHER . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK NO LIGHT
- APM P/B . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK NO LIGHT
- APM TEST . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . PERFORM
APM Test (daily) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . refer to 2.03.24
- PEC 1+2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . DEPRESSED IN / NO LIGHT
- ENG BOOST FUNCTION (If installed) . . . . . . . . . . . . . . . . . . . . . . . . . CHECK
- ENG BOOST FUNCTION TEST (If installed) . . . . . . . . . . . . . . refer to 2.03.24
- PWR MGT rotary selector . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . TO
- IESI . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK NO FLAG
- EWD :
- EWD FLIGHT CONTROL window . . . . . . . . . . . . . . . . . . . . . CHECK
Check TRIMS and FLAPS, indications
- ENG 1 & 2 INSTRUMENTS . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK
Check TQ, RTO TQ, TO TQ, NP, ITT
- TAT / SAT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK
ENG PANEL :
- EEC 1 & 2 P/B . . . . . . . . . . . . . . . . . . CHECK DEPRESSED IN / NO LIGHT
- ATPCS P/B . . . . . . . . . . . . . . . . . . . . . CHECK DEPRESSED IN / NO LIGHT
- CAB PRESS PANEL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK
Check no light
Check the rotary selector is facing the green mark
Mod 5948
2.03.07
NORMAL PROCEDURES
PRELIMINARY COCKPIT PREPARATION
P 11
WITH HOTEL MODE
001
FEB 12
AA
- AUTO PRESS PANEL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . TEST / CHECK
Depress the TEST P/B and check
- On local panel :
- Cycling display between - 8800 and 18800 . . . . . . . . . . . . . . . CHECK
- MC + SC + AIR AUTO PRESS on Alerting Window (1 flash) . . . CHECK
- MODE SEL P/B FAULT amber light (1 flash) . . . . . . . . . ILLUMINATED
- CABIN SD page :
CAB ALT / VS / ∆P . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK
ANTISKID PANEL P/B depressed in, no LIGHT . . . . . . . . . . . . . . . . . . . CHECK
GLARESHIELD :
- GPWS P/B TEST . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . PERFORM
CAPTAIN LATERAL CONSOLE
- COCKPIT COM HATCH . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OPEN
Cockpit com hatch must be opened until engine 1 start, in order to avoid that the
extract fan suction creates a depressurization when passenger doors is closed, (ref
procedure and techniques 2.02.03).
- MAINTENANCE PANEL
R - STICK PUSHER / SHAKER (once a day) . . . . . . . PERFORM (refer to 2.03.24)
- ROTARY SELECTOR . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK NORM FLT
- N/W STEERING . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . AS RQRD
- OXYGEN MASK (once a day) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK
OXYGEN MASK TEST (Hose and mask must be charged with oxygen)
- DO NOT REMOVE OXYGEN MASK
Mod 5948
2.03.07
NORMAL PROCEDURES
PRELIMINARY COCKPIT PREPARATION
WITH HOTEL MODE
P 12
001
FEB 12
AA
- AUDIO CONTROL PANEL INT / RAD selector . . . . . . . . . . . . . . . . . . . . . INT
1 - PRESS TO TEST & RESET PB . . . . . . . . . . . . . . . . . . . . . PRESS & HOLD
- Check :
- Blinker momentarily turns yellow and then goes black (if no leak)
- Oxygen flow sounds through loudspeakers
2 - PRESS TO TEST AND RESET PB. . . . . . . . . . . . . . . . . . . . . . . . . . . HOLD
RED GRIPS ON EACH SIDE OF THE HOSE . . . . . . . . . . . SQUEEZE
Check :
- Oxygen pressure inflates the harness.
- Blinker momentarily turns yellow and must turn dark if there is no leak.
- Oxygen flow sounds through oudspeakers
3 - PRESS TO TEST AND RESET PB . . . . . . . . . . . . . . . . . . . . . . . . . . HOLD
EMERGENCY KNOB . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . SELECT
Check :
- Blinker momentarily turns yellow and must turn dark if there is no leak
- Oxygen flow sounds through loudspeakers.
CAUTION
WHEN TEST COMPLETED : Insure the oxygen mask control panel remain
in the following position :
- OXY LO PR LIGHT . . . . . . . . . . . . . . . . . . . CHECK EXTINGUISHED
- N/100% ROCKER LEVER . . . . . . . . . . . . . SET TO 100 %
R - CAPTAIN SWITCHING PANEL :
R - AUDIO 1 SEL Light . . . . . . . . . . . . . . . . . . . . . . . . . CHECK EXTINGUISHED
- ATT/HDG, ADC . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK EXTINGUISED
- TAWS PANEL :
- TERR . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . GUARDED NO LIGHT
- GPWS TOGGLE SWITCH . . . . . . . . . . . . . GUARDED / NORMAL POSITION
- GPWS Associated light . . . . . . . . . . . . . . . . . . . . . . . . . . . EXTINGUISHED
Mod 5948
2.03.07
NORMAL PROCEDURES
PRELIMINARY COCKPIT PREPARATION
WITH HOTEL MODE
P 13
001
FEB 12
AA
CAPTAIN INSTRUMENT PANEL
- CLOCK TIME . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK
- PFD
- FMA . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK
- AIRSPEED, ALTIMETER, VSI . . . . . . . . . . . . . . . . . . . . . CHECK NO FLAG
- EADI . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK ATTITUDE
R
- EHSI . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK
- ND / EHSI : (Select ND on MFD)
- HDG . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CROSS CHECK & NO FLAG
R
- MEMO PANEL DISPLAY . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK
F/O LATERAL CONSOLE
- EXTRACT AIRFLOW . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OPEN / GUARDED
- OXYGEN MASK (once a day) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK
- AUDIO SEL 2 Light . . . . . . . . . . . . . . . . . . . . . . . . . CHECK EXTINGUISHED
- F/O SWITCHING PANEL :
- ATT/HDG, ADC . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK EXTINGUISHED
- ELAPSE TIME . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF / RESET
F/O INSTRUMENT PANEL
- CLOCK TIME . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK
- PFD
- FMA . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK
- AIRSPEED, ALTIMETER, VSI . . . . . . . . . . . . . . . . . . . . . CHECK NO FLAG
- EADI . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK ATTITUDE
- ND / EHSI : (Select NAV display on MFD)
R
R
R
R
R
R
- HDG . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CROSS CHECK & NO FLAG
- MEMO PANEL DISPLAY.......CHECK
- SYS PAGE
- AC/DC ELEC Page . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK
- CABIN Page . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK
- ACW HYD Page . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK
- ENGINE Page . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK
Mod 5948
2.03.08
NORMAL PROCEDURES
P1
FINAL COCKPIT PREPARATION
001
APR 11
AA
CM2
- ATIS INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OBTAIN
- TAKE OFF DATA CARD . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1st PART FILL
1st part : Weather, W lim according to performance computation, ACC ALT, Single
Eng flight path
- LANDING ELEVATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . SET
PF
FMS INITIAL PREPARATION :
PF should run through the 3 following steps to prepare the FMS :
1 - FMS INITIALIZATION
2 - NAVIGATION
3 - PERFORMANCE
1 - FMS INITIALIZATION :
At power up, check FMS starts correctly,by checking the following TESTs results.
Note : If “Power up” page doesn’t come :
- Press MENU key on the MCDU
- Select FMS 1 on left side : FMS 2 on right side
Mod 5948
2.03.08
NORMAL PROCEDURES
P2
FINAL COCKPIT PREPARATION
AA
001
APR 11
- INITIALIZATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK
- CONF DATA . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OK
- NAV DATA . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OK
- STD DATA . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .CHECK
Check STD DATA base expiry date. It out of date, swap database on NAV DATA page
or ask for new database loading.
.0
- Press INIT Lsk to open the INIT page
FMS initialization should be prepared using the following flow, performed from INIT
page.
Note : INIT page can be displayed at any time by :
- Pressing DATA Key,
- Pressing INIT
.1
UNITS >
- Press UNITS Lsk (see illus point 1 )
- UNITS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK
In order to avoid any confusion due to previous crew insertions, check all items of
the UNIT page.
.2
< POS INIT
- Press POS INIT Lsk
- POSITION INIT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . SET / CHECK
On POS INIT page :
- Check that LOCALIZATION MODE is BCP (GPS GREEN) and
- Initialize position : INIT POS = GPS POS, then Press on SENSORS INIT to
activate it
Mod 5948
2.03.08
NORMAL PROCEDURES
P3
FINAL COCKPIT PREPARATION
001
APR 11
AA
2 - NAVIGATION :
.3
< FPLN INIT
- Press FPLN UNIT Lsk
- Enter the ROUTE :
- Press on F-- PLN INIT then on ROUTE
- Enter the ROUTE, using the route IDENT or
FROM/TO
- Enter the FLT ID
- Press EXEC to activate F-- PLN
- Enter the RWY, SID, TRANS wpt
- Enter route WPT and AIRWAYS
- Enter the ARRIVAL RWY, STAR, TRANS wpt.
(for short legs)
- Check / enter Constraints (ALT CNSTR or SPD
CNSTR.)
- Press TMPY to check entered data before
activation.
- Press EXEC to activate F-- PLN
- Select PLAN on ND
- F- PLN VERIFICATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . PERFORM
SECONDARY F.PLN
.4
FPLN
- Press FPLN Key twice
- SEC F- PLN . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . AS APPROPRIATE
SEC F-- PLN is routinely a copy of the active F-- PLN. However,consideration may be
given to the following :
a)immediate return : Make a copy of the active F-- PLN and modify it as a suitable WPT
for an immediate return to the departure airfield in the event of, for example, an
engine failure.
b)diversion : If weather is below landing minimums at the departure airfield, the SEC
F-- PLN should be that required for a diversion immediately after take off.
c) RWY Departure change : If there is a chance of a change in the RWY or SID during
taxi, prepare for it by copying the active F-- PLN and make the necessary
modifications.
Mod 5948
2.03.08
NORMAL PROCEDURES
P4
FINAL COCKPIT PREPARATION
001
APR 11
AA
3 - PERFORMANCES
- Press DATA key, then INIT Lsk to open INIT Page.
PERFORMANCE DATA part should be prepared
using the following flow.
.5
WEIGHT >
- Press WEIGHT Lsk
- ZFW . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . INSERT
If the ZFW is unavailable, it is acceptable to enter the expected values in order to
obtain prediction.
- FOB . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . INSERT
Similary, the flight crew may enter the expected Fuel On Board if refueling has not
been completed at that time.
- GW . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK
- RESERVE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . INSERT
CAUTION
The characteristic speeds displayed on MCDU / MFD PERF page are
computed from Weights entered by crew on the MCDU.
Therefore, these weight data must the be checked. (Captain’s
responsibility)
.6
PERF INIT >
- Press PERF INIT Lsk
- CRZ ALT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . INSERT
Enter the expected CRUISE ALTITUDE. Enter ZFW before entering a CRUISE ALT.
(Mind the FORMAT : i.e enter : 20000 or FL200)
- CRZ MODE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK MAX CRUISE
- DFLT FPA . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK / SET if RQRD
Check the DEFAULT Flight Path Angle (3°).
- ALTN/CRZ ALT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . SET
Enter the Alternate airport and the desired cruise altitude to alternate. (Default
value : FL100).
Mod 5948
2.03.08
NORMAL PROCEDURES
P5
001
FINAL COCKPIT PREPARATION
APR 11
AA
.7
PERF
- Press PERF key once on MCDU
TAKE OFF page :
- RWY LNG / AXIS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK / SET if RQRD
Check the RWY length and AXIS stored in the database.
Set the correct value for any change affecting TORA, TODA, ASDA (Displaced
threshold, take off from intersection, work in progress reducing RWY length...)
- TRANS ALT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK / SET if RQRD
Check the transition altitude. Set a new value if required.
- V1, VR, V2 . . . . . . . . . . . . . . . . . . . . . . . . CHECK / MANUALLY SET IF RQRD
CAUTION
V1, VR, V2 are automatically computed considering that the runway is
NON- LIMITING.
A MANUAL INSERTION is required for any limitation.
(RWY LIMITATION, OBSTACLE, RWY CONTAMINATION...)
- Press PERF key (once more)
CRUISE page :
WINDS INSERTION :
The pilot has to choose between, 2 models : A simplified wind model and an accurate wind
model.
- SIMPLIFIED WIND MODEL : (Used for short flight)
If required, mean winds will be entered in the PERF CRUISE page.
- DEST MEANWIND . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . SET if RQRD
Enter the expected mean wind between DEP and DEST at the cruise altitude.
- ALTN MEANWIND . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . SET if RQRD
Insert the MEANWIND between DEP & ALTN at FL 100 or at the FL defined in the
PERF INIT page.
Mod 5948
2.03.08
NORMAL PROCEDURES
P6
001
FINAL COCKPIT PREPARATION
APR 11
AA
- ACCURATE WIND MODEL (May be used for long flight)
If the accurate wind model is chosen, winds need to be entered at any wpt directly in the
F-- PLN.
For this, press FPLN key and :
- Perform a vertical revision at the desired WPT.
- Enter the ORIGIN / WIND / FL. (Up to 4 FL may be considered)
- Enter WIND at each WPT until destination.
Note : The last wind will be propagated downstream until destination.
CAUTION
Once a vertical wind profile has been entered at one way point, the
SIMPLIFIED MODEL does not apply any more to the rest of the flight
End of FMS Initial Preparation
--------------------------------------- NAVAIDs . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . SET
Set :
- NAVAIDS using MCP / VCP
- COURSEs using FGCP
- NAV SOURCE on FGCP and
- Check on PFD :
- Cross check NAV SOURCE on PFD (EHSI)
- VOR / ILS 1 & 2 set MANUAL TUNE
Note:
If NOTAMs warn of any unreliable DME or VOR/DME, crew must deselect it from
position computation. Press MCDU DATA key, select NAV FRQ page then
DESELECTED those related NAVAIDs.
- COM . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . SET
Mod 5948
2.03.08
NORMAL PROCEDURES
P7
001
FINAL COCKPIT PREPARATION
FEB 12
AA
CM1
- PARKING BRAKE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON PRESS CHECK
- SIGNS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON
- MEMO PANEL DISPLAY . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK
- FUEL QTY on FUEL ENG SD page (MFD) . . . . . . . . . . CHECK & BALANCED
Cross check FUEL Quantity displayed on EWD, with Actual FUEL quantity
displayed on ENG SD page (Measured) with paper F-- PLN Fuel.
CAUTION
FOB displayed on EWD permanent data is the FOB entered by the crew
in the FMS
- ENG FUEL USED . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . RESET
ALL
- ALTIMETERS (3) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . SET & CHECK
- TAKE OFF TQ BUGS . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK GREEN DOT
T/O Torque (Green dot) should be cross checked using ATIS or TWR temperature
with QRH OPS DATA
- RESERVE TAKE OFF TQ . . . . . . . . . . . . . . . . . . . . . . . CHECK AMBER BUGS
RTO Torque (Amber Bug) should be cross checked using ATIS or TWR temperature
with QRH OPS DATA.
- SEATS, SEATS BELTS, HARNESS, RUDDER PEDALS . . . . . . . . . . ADJUST
R PF: - DEPARTURE BRIEFING . . . . . . . . . . . . . . . . . . . . . . . . . . . . . PERFORM
- FINAL COCKPIT PREPARATION C/L . . . . . . . . . . . . . . . . . . . . . . PERFORM
Mod 5948
2.03.09
NORMAL PROCEDURES
P1
HOTEL MODE START UP
001
FEB 12
AA
R According to operational requirement and limitations captain can decide to start up
Hotel Mode any time before start up clearance.
- SERVICE DOOR . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CLOSED
- FUEL PUMP 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON
Check RUN LIGHT ON + FEED LO PRESS extinguished
- WING LIGHTS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON
- PROP BRK . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON / LOCKED
Check PROP BRK Local Cyan light illuminated + EWD Cyan label displayed
- ENG 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . START IN HOTEL MODE
CAUTION
Prior to any engine start, check FUEL- ENG SD page displayed
START SEQUENCE
- ENGINE & PROP AREA . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK CLEAR
- ENGINE START rotary selector . . . . . . . . . . . . . . . . . . . . . . . . . START A + B
A+B for the 1st flight on the day, then A or B for the next start
- START 2 P/B . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . DEPRESSED / ON
Start timing for maximum starter run time
Check :
- START P/B ON light illuminated
- START green label on ENG SD page
- ENGINE ROTATION (NH) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MONITOR
S When passing 10 % NH (maximum 19% NH if ITT > 200°c) :
- CL 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FTR
- TIMING . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . START
- ITT rises within 10s . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK
ENGINE START in HOT ENVIRONMENT
In hot environments to prevent an engine starting from a “hot start” : High OAT or High
residual ITT, it is recommended to delay the fuel opening up to 20% NH.For residual ITT
below 100_C, open fuel up to 10% NH.
From 100_C to 200_C delay fuel opening by 1% NH per 10_C of residual ITT, up to
200_C (20% NH)
Do not exceed 20% NH for fuel opening.
Mod 5948
2.03.09
NORMAL PROCEDURES
P2
001
HOTEL MODE START UP
FEB 12
AA
R
CAUTION
- If ITT < 950°°C
} CL...............FUEL S O
- If 840 C°° <ITT <950°°C for more than 5s } CL...............FUEL S O
- If 800 C°° <ITT <840°°C for more than 20s } CL...............FUEL S O
S When passing 45 % NH :
Check :
- START green label EXTINGUISHES on ENG SD page
- START P/B ON light extinguished
Check maximum start time and max ITT (Refer to Limitation chap 2.01.04)
S When engines parameters are stabilized :
- ENGINE START ROTARY SELECTOR . . . . . . . OFF / START ABORT
- GPU . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF
- DC GEN 2 FAULT LIGHT . . . . . . . . . . . . . . . . . . . . . . EXTINGUISHED
- DC BTC . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CLOSED
- BLEED / PACK / X VALVE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OPEN
- PL 1 + 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ADJUST AS RQRD
If Z > 5000 ft and SAT > ISA + 25C°, advance PL 2 up to the GUST LOCK stop.
Mod : 5948
2.03.10
NORMAL PROCEDURES
BEFORE PROPELLER ROTATION
P1
500
NOV 14
AA
Note: If hotel mode wasn’t started at this point, start it now
When LOAD & TRIM SHEET is received
CM1
- LOAD AND TRIM SHEET . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK
CM1
- TAKE OFF WEIGHT / CG / PITCH TRIM . . . . . . . . . . . . . ANNOUNCE
CM2
- TAKE OFF DATA CARD . . . . . . . . . . . . . . . . . . . . . . . 2nd PART FILL
2nd part : TOW, SPEED, TRIM settings
- FMS WEIGHT & SPEEDS UPDATE . . . . . . . . . . . . . . . . . PERFORM
PF
Enter in the MCDU TAKE OFF page the last TO WEIGHT & TO CG
CM1
- ENG BOOST FUNCTION (If installed) . . . . . . . . . . . . . SET AS RQD
The BOOST FUNCTION is effective only when the engine is thermally limited.
Select correct rating ON when a gain in payload is necessary.
If using SUPERBOOST FUNCTION set corrected OAT in VCP PERF PAGE
CAUTION
V1, VR, V2 are automatically computed considering that the runway is
NON- LIMITING.
A MANUAL INSERTION is required for any limitation.
(RWY LIMITATION, OBSTACLE, RWY CONTAMINATION...)
ALL
- TAKE OFF DATA............................................................CONFIRMED
Confirm the last TO WEIGHT & SPEED using MCP/VCP and check :
- TO TRIM magenta.................................DISPLAYED on EWD
- V1.......................................................DISPLAYED on PFD
- V2......................................DISPLAYED on MFD PERF page
WARNING
PERFORMANCE CONFIRMATION
must be done according to ICING or NON ICING CONDITIONS
ALL
CM2
CM1
CM1
CM1
-
CM2
CM1
CM1
CM1
ALL
-
ALL TRIMS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . SET & CHECK
START UP CLEARANCE . . . . . . . . . . . . . . . . . . . . . . . . . . . OBTAIN
GROUND CREW CLEARANCE . . . . . . . . . . . . . . . . . . . . . . OBTAIN
TAIL PROP . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON BOARD
ALL DOORS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CLOSED
Checked on SD AIR page
CDLS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON
SEAT BELTS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON
BEACON . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON
NOSE WHEEL STEERING (if push back) . . . . . . . . . . . . . . . . . OFF
BEFORE PROPELLER ROTATION C/L . . . . . . . . . . . . . . PERFORM
Mod 5948 + (5908 or 7079)
2.03.11
NORMAL PROCEDURES
BEFORE TAXI
P1
001
FEB 12
AA
BEFORE TAXI
ALL
- LEFT / RIGHT SIDE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CLEAR
CM1
-
- HYD AUX PUMP . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .DEPRESS
Check HYD PRESS on SD HYD Page.
- PROP BRK . . . . . . . . . . . . . . . . . . . . . . . . CHECK READY LIGHT ON
- PROP BRK SW . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF
- PROP BRK CYAN . . . . . . . . . . . . . . . . . . . . . . CHECK EXTINGUISED
on overhead panel : - UNLOCK local light flashes then extinguishes
- PROP BRK Local Cyan light extinguished on EWD :
Cyan label disappear
CM2
- NP . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . STABILIZED
CM2
- CL2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . AUTO
R CM2
- PEC SGL CH . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK
on EWD : Single Channel label displayed for few seconds then extinguishes
CM2
- LOW PITCH . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK
on EWD : Low Pitch label is displayed
CM2
When NP stabilized at around 71% :
Check on the overhead panel and on associated SD page
- ACW GEN 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK
- ACW BTC . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CLOSED
- HYD . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK
R CM2
- PROBES HEATING . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON
R CM2
- ANTI ICING . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . AS RQD
R CM2
- HYD TRIPLE INDICATOR . . . . . . . CHECK 3 x 3000 PSI (on SD page)
CM2
- ANTISKID TEST . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . PERFORM
ANTISKID Test :
Depressed ANTISKID TEST P/B and check :
On alerting window :
- WHEEL A-- SKID . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . AMBER
- FFFF appears for few seconds . . . . . . . . . . . . . . . . . . . . AMBER
- NNNN appears at the end of the test for few seconds . . . . GREEN
R
Mod 5948
2.03.11
NORMAL PROCEDURES
BEFORE TAXI
P2
001
NOV 14
AA
CM2
CM2
CM2
- FLAPS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15°°
- ENG BOOST FUNCTION (If installed) . . . . . . . . . . . . . . . . . . CHECK
- ENG 1 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . START
START SEQUENCE as per ENG 2
CAUTION
Prior to all engine start, select ENG SD page
Note : DC GEN 2 FAULT may occur during ENG1 cross-- start in cold weather.Start-- up
sequence continues , on battery only , with a temporary loss of DU 1/3/5.EWD and ENG
SECONDARY page remain available on DU2 and 4 respectively to ensure engine parameter
monitoring.Once engine 1 start-- up is completed , DU 1/3/5 recover automatically , and a DC
GEN2 reset has to be carried on.
CM2
- CL1 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . AUTO
CM2
- SGL CH . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK
on EWD : Single Channel label displayed for few seconds then extinguishes
CM2
- LOW PITCH . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK
on EWD : Low Pitch label is displayed
When NP stabilized at around 71% :
Check on the overhead panel and on associated SD page
CM2
- ACW GEN 1 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK
CM2
- ACW BTC . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OPEN
CM1
- COCKPIT COM HATCH . . . . . . . . . . . . . . . . . . . . . CHECK CLOSED
CM2
- XPDR . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . AS REQUIRED
CM1
- FWS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . RCL
CM1
- Nose Wheel Steering . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON
CM2
- OVHD PANEL . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK NO LIGHT
Except exhaust mode FAULT light for 2mn.
ALL
- BEFORE TAXI C/L . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . PERFORM
Mod 5948
2.03.12
NORMAL PROCEDURES
P1
TAXI
100
DEC 13
AA
TAXI
CM2
- TAXI CLEARANCE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OBTAINED
CM1
- TAXI & TO LIGHTS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON
CM2
- ELAPSED TIME . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . AS RQD
ALL
- BRAKES . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECKS
Brakes checks :
- CM1 Set Taxi PWR
- CM1 set PARKING RAKE handle from ON to EMER position
- CM2 checks BRAKES while CM1 releases PARKING BRAKE
- CM1 checks BRAKES after CM2 have released BRAKES
- CM1 start to TAXI
ALL
- INTRUMENTS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK
Cross check Headings, Bearings, ADI, Side slip indicators
CM2
- FGCP
CAUTION
All actions on FGCP needs to be confirmed on FMA
- HDG SEL MODE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . SELECT
- NAV MODE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ARMED
- NAV SOURCE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK
- IAS BUG . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . SET
According to company policy
- IAS MODE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . SELECT
(Note : ALT SEL needs to be different from zero)
- COUPLING . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . PF SIDE
ALL
- FMA . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK
Mod 5948+6521
2.03.12
NORMAL PROCEDURES
P2
TAXI
001
APR 11
AA
CM2
- TO CONFIG . . . . . . . . . . . . . . . . . . . TEST & CHECK OK BLUE ON EWD
CM2
- ATC CLEARANCE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OBTAIN
ALL
- CLEARED ALTITUDE . . . . . . . . . . . . . . . . . . . . . . . . . . . . SET / CHECK
Check clearead ALT is displayed on PFD
ALL
- FMS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . REVISE IF NECESSARY
Carefully confirm that the ATC clearance agrees with the FMS (RWY, SID,
Constraints) and Disarm NAV MODE if HDG is to be used at Take off.
PF
- TO BRIEFING . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . PERFORM
- Take off briefing should usually be a brief confirmation of the departure briefing
made at the parking bay, and should include any change (RWY, SID...)
- Standard calls
- For significant failure before V1, CAPTAIN will call “STOP” and will take
any necessary stop actions.
- Above V1 take off will be continued and no action will be taken except on
CAPTAIN command ;
- Single Engine procedure is.............
- Acceleration Altitude is...................
- Departure clearance is...................
CM1
- CABIN REPORT . . . . . . . . . . . . . . . . OBTAIN FROM CABIN ATTENDANT
ALL
- TAXI C/L . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . COMPLETED
Mod 5948
2.03.13
NORMAL PROCEDURES
P1
001
BEFORE TAKE OFF
FEB 12
AA
Philosoply of use :
All items “up to the line”, can be done at any time before entering the runway.
“Below the line” items must be done when cleared to line up.
CM2
- GUST LOCK . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . RELEASE
ALL
- FLIGHT CONTROLS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK
Check full travel and freedom movement in PITCH, ROLL, YAW
For ROLL, check spoiler lights illuminate
CM2
- TCAS AUTO . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK
R CM2
- XPDR . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ALT
R CM2
- WEATHER RADAR . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . AS RQD
CM2
- AIR FLOW . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . NORM
CM1
- OVERHEAD PANEL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . SCAN
Check all light extinguished except ANTI ICING if required.
ALL
- DU CONFIGURATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK
Check display : PF : - MFD = ND / VOR1+2 MAN,
- MCDU = PERF - TAKE OFF page,
PNF : - MFD = ND / COM,
- MCDU = F/PLN page
CM2
- LINE UP CLEARANCE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OBTAIN
R CM2
- BLEED VALVES . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . AS RQD
CM1
- LANDING LIGHT & STROBE . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON
R
When lined up
ALL
- LATERAL FD BAR . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CENTER
Check HDG = RWY HDG. If not, push to synchronize HDG
CM1
- RUDDER CAM . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CENTER
ALL
- BEFORE TAKE OFF C/L . . . . . . . . . . . . . . . . . . . . . . . . . PERFORM
Mod 5948
2.03.14
NORMAL PROCEDURES
P1
TAKE OFF
AA
100
DEC 13
TAKE OFF
For Take Off at 100% TQ, refer to page 1A, 2A. (if applicable)
R CAUTION:
If operations are simultaneously conducted with High Altitude Runways (up to 11.000 ft),
associated procedure(s) in 7.01.07(refer to AFM) have also to be taken into account.
CM1
- “TAKE OFF” . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ANNOUNCE
CM1
- BRAKES . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . RELEASED
CM1
- PL 1 + 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . SET IN THE NOTCH
CM1
- FMA . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ANNOUNCE
IAS
CM2
- FMA . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK
CM2
- “ATPCS ARM” . . . . . . . . . . . . . . . . . . . . . . . CHECK then ANNOUNCE
CM2
- ENGINE PARAMETERS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK
Note :Parameters should be obtained at around 60 Kt
ACTUAL TQ . . . . . . . . . . . . . . . . . . . . . . . . . MATCH T.O BUG
Note : If necessary, adjust PLs to obtain TO TQ (bugs )
RTO BUG . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK
NP . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ~ 100 %
Note : NP =100 % - 0.6%I+0.8%
ITT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK
CM2
- TO INHIB . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK
CM2
- “POWER SET” . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ANNOUNCE
When reaching 70 Kt
CM2
- “SEVENTY KNOTS” . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ANNOUNCE
R CM1
- SPEED . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CROSS CHECK on PFD
And cross check speeds with IESI
ALL
- “I HAVE CONTROL” / “YOU HAVE CONTROL” . . . . . . . . ANNOUNCE
- If CM1 becomes PF, CM1 announce only “I HAVE CONTROL”
- If CM2 becomes PF, CM1 announce “YOU HAVE CONTROL” & CM2 answer “I
HAVE CONTROL”
PNF
- “V1” . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ANNOUNCE
R Mod 5948 + 6521
2.03.14
NORMAL PROCEDURES
P 1A
TAKE OFF 100% TQ
AA
150
DEC 13
TAKE OFF 100% TQ
R CAUTION:
If operations are simultaneously conducted with High Altitude Runways (up to 11.000 ft),
associated procedure(s) in 7.01.07(refer to AFM) have also to be taken into account.
CM1
- “TAKE OFF” . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ANNOUNCE
CM1
- BRAKES . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . RELEASED
CM1
- PL 1 + 2 . . . . . . . . . . . . . . . . . . . . . . . . . . ADVANCE TO THE RAMP
CM1
- FMA . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ANNOUNCE
IAS
CM2
- FMA . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK
CM2
- “ATPCS ARM” . . . . . . . . . . . . . . . . . . . . . . . CHECK then ANNOUNCE
CM2
- ENGINE PARAMETERS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK
Note :Parameters should be obtained at around 60 Kt
ACTUAL TQ . . . . . . . . . . . . . . . . . . . . . MATCH RTO TQ BUG
Note : If necessary, adjust PLs to obtain RTO TQ (bugs )
RTO BUG . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK
NP . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ~ 100 %
Note : NP =100 % - 0.6%I+0.8%
ITT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK
CM2
- TO INHIB . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK
CM2
- “POWER SET” . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ANNOUNCE
When reaching 70 Kt
CM2
- “SEVENTY KNOTS” . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ANNOUNCE
R CM1
- SPEED . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CROSS CHECK on PFD
And cross check speeds with IESI
ALL
- “I HAVE CONTROL” / “YOU HAVE CONTROL” . . . . . . . . ANNOUNCE
- If CM1 becomes PF, CM1 announce only “I HAVE CONTROL”
- If CM2 becomes PF, CM1 announce “YOU HAVE CONTROL” & CM2 answer “I
HAVE CONTROL”
PNF
- “V1” . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ANNOUNCE
R Mod 5948 + 6521 + 5731
2.03.14
NORMAL PROCEDURES
P2
TAKE OFF
AA
500
DEC 13
TAKE OFF (CONT’D)
When reaching VR :
PNF
- “ROTATE” . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ANNOUNCE
PF
- ROTATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . PERFORM
Note : Pitch rotates smoothly and follow FD bar.
After LIFT OFF :
PNF
- “POSITIVE RATE” . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ANNOUNCE
PF
- “GEAR UP” . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ORDER
PNF
- LDG GEAR LEVER . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . SELECT UP
PNF
- YAW DAMPER . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ENGAGE
PNF
- TAXI & TAKE OFF LIGHT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF
PNF
- IAS MODE (FGCP) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . SELECT
PNF
- SPEED TARGET . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CLIMB SPEED
PNF
- LDG GEAR LIGHTS . . . . . . . . . . . . . . . . . . . . . CHECK EXTINGUISHED
At ACCELERATION ALTITUDE :
PF
- “CLIMB PROCEDURE” . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ORDER
PNF
- CLIMB PROCEDURE:
- PL1 + 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK IN THE NOTCH
- PWR MGT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CLIMB
- NP . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK
- BLEEDS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK ON
Note : Pack 2 valve FAULT will illuminate during 10 seconds. A 10 seconds delay
is used for pack 2 valve to avoid pressure shocks.
- SPEED TARGET . . . . . . . . . . . . . . . . . . . . . MAGENTA 170 kt CHECK
- BOOST . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF (if necessary)
- “CLIMB PROCEDURE COMPLETED” . . . . . . . . . . . . . . . . ANNOUNCE
PNF
- FMA MODE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ANNOUNCE
PF
- FMA . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK
Mod : 5908 + 5948
2.03.14
NORMAL PROCEDURES
P 2A
TAKE OFF 100% TQ
AA
150
DEC 13
TAKE OFF 100% TQ (CONT’D)
When reaching VR :
PNF
- “ROTATE” . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ANNOUNCE
PF
- ROTATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . PERFORM
Note : rotates smoothly and follow FD bar.
After LIFT OFF :
PNF
- “POSITIVE RATE” . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ANNOUNCE
PF
- “GEAR UP” . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ORDER
- PL 1 + 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . RETARD IN THE NOTCH
PNF
- LDG GEAR LEVER . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . SELECT UP
PNF
- YAW DAMPER . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ENGAGE
PNF
- TAXI & TAKE OFF LIGHT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF
PNF
- LDG GEAR LIGHTS . . . . . . . . . . . . . . . . . . . . . CHECK EXTINGUISHED
When passing ACCELERATION ALTITUDE :
PF
- “AFTER TAKE OFF PROCEDURE” . . . . . . . . . . . . . . . . . . . . . . . ORDER
PNF
- AFTER TAKE OFF PROCEDURE:
- PL 1 + 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK IN THE NOTCH
- PWR MGT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CLIMB
- NP . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK
- BLEEDS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK ON
Note : Pack 2 valve FAULT will illuminate during 10 seconds. A 10 seconds delay
is used for pack 2 valve to avoid pressure shocks.
- SPEED TARGET . . . . . . . . . . . . . . . . . . . . MAGENTA A 170 kt CHECK
- “AFTER TAKE OFF PROCEDURE COMPLETED” . . . . . . . . . . ANNOUNCE
PNF
- FMA MODE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ANNOUNCE
PF
- FMA . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK
R Mod 5948 + 6521 + 5731
2.03.14
NORMAL PROCEDURES
P3
TAKE OFF
100
FEB 12
AA
When passing WHITE bug (F SPEED: White in Normal conditions)
PF
- “FLAPS ZERO” . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ORDER
PNF
- FLAPS ZERO . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . SELECT
PNF
- “FLAPS ZERO” . . . . . . . . . . . . . . . . . . . ANNOUNCE WHEN INDICATED
When passing ICING bug (F SPEED: Amber in Icing conditions)
PF
- “FLAPS ZERO” . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ORDER
PNF
- FLAPS ZERO . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . SELECT
PNF
- “FLAPS ZERO” . . . . . . . . . . . . . . . . . . . ANNOUNCE WHEN INDICATED
When cleared to a FL :
ALL
- ALTIMETERS 1+2 . . . . . . . . . . . . . . . . . . . . . SET STD & CROSS CHECK
Note : Set Standard pressure by pushing BARO SET P/B
ALL
- AFTER TAKE OFF C/L . . . . . . . . . . . . . . . . . . . . . . . . . . . . . PERFORM
PNF
- AFTER TAKE OFF procedure . . . . . . . . . . . . . . . . . . . . . . . COMPLETED
CHARACTERISTIC SPEEDS :
TAKE OFF SPEEDS Normal condition
Mod 5948 + 6521
2.03.14
NORMAL PROCEDURES
P4
TAKE OFF
AA
R
FINAL TAKE OFF SPEEDS Normal condition
FINAL TAKE OFF SPEEDS Icing condition
Mod 5948 + 6521
100
FEB 12
2.03.15
NORMAL PROCEDURES
P1
CLIMB - CRUISE
001
FEB 12
AA
CLIMB
Note : During Climb, check all system SD pages
Cab Press to be checked periodically.
Crossing FL 100 climbing (FL 100 or any other FL according to local regulation)
R PNF
- LANDING LIGHTS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF
CM1
- SEAT BELTS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . AS RQD
R PNF
- PRESSURIZATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK
R CM1
- NO DEVICES . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF
CRUISE
At Cruise FL :
R PNF
- SAT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK
R PNF
- CRUISE PARAMETERS . . . . . . . . . . . . . . . . COMPUTE WITH QRH
Reaching Cruise Speed :
R PNF
PF
- PWR MGT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CRZ
- CRUISE TORQUES + SPEEDS . . . . . . . . . . . . . . . . . . . . . CHECK
SYSTEMS :
R PNF
- ALL SYSTEMS on SD Page . . . . . . . . . . . . PERIODICALLY CHECK
FUEL :
R PNF
- FUEL / FOB . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK
ON FMS :
R PNF
- CRZ ALT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK
R PNF
- WINDs . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . SET / CHECK
ALL
- PREDICTIONS : (TOD, EFOB, PRAIM) . . . . . . . . . . . . . . . CHECK
Mod 5948
2.03.15
NORMAL PROCEDURES
P2
CLIMB - CRUISE
001
FEB 12
CRUISE SPEED LOW
ALERT
CONDITION
Cruise speed
decrease
VISUAL
- CRUISE SPEED LOW on FMA
AURAL
NIL
PROCEDURE
CRUISE SPEED LOW
Appears in cruise only, to inform the crew that an abnormal drag increase induces a
speed decrease of more than 10 kt compared with the expected speed
ICING CONDITIONS AND SPEED . . . . . . . . . . . . . . . . . . . . . . . . . . . MONITOR
R REDUCED POWER SETTING IN CRUISE
The airline, according to its cost policy, can choose to cruise at reduced power, e.g. at
long--range power or given IAS. The associated cruise derated tables need to be available
on board for the flight crew. Those tables can be published with the FOS Module 2,
In--flight performance, as shown in example in figure 1 page 2.
The PLs are set according to the torque given in the tables. This requires a PL adjustment
out of the notch.
Limitations:
The reduced power cruise is not allowed in case of icing conditions, as the IAS may
already be decreased due to ice accretion on the airframe.
In case of an engine failure, the PLs need to be immediately moved back into the notch,
power management to MCT.
From a maintenance point of view, reduced power operations may achieve lower engine
overhaul costs as a result of the reduced power settings.
Mod 5948
2.03.15
NORMAL PROCEDURES
P3
CRUISE
001
FEB 12
REDUCED POWER SETTING IN CRUISE (CONT’D)
Example:
Figure 1: Long Range cruise performance table - ATR 72 (PW127M)
This is an example of a long-- range cruise performance table generated with the
FOS Module 2. In the case the cruise weight is 20t, the cruise FL 190, the torque is
set to 51.6% and the cruise IAS will be 177kts.
Mod: 5948
2.03.16
NORMAL PROCEDURES
P1
BEFORE DESCENT - DESCENT
001
FEB 12
PF
- FWS ALERTING WINDOW . . . . . . . . . . . . . . . . . . . . . . . . . . . . . RCL
R PNF
- WEATHER & LANDING INFORMATION . . . . . . . . . . . . . . . . OBTAIN
R PNF
- LANDING DATA CARD . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FILL
CM1
- IESI . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . SET QNH
R PNF
- LANDING ELEVATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK
PF
FMS PREPARATION :
PF should run through the following 2 steps to prepare the FMS :
1 - NAVIGATION
2 - PERFORMANCE
1 - NAVIGATION :
.
FPLN
- Press FPLN key
- Check the Route to destination
- Enter the RWY, STAR, TRANS wpt
- Check/enter Constrainst (ALT CNSTR or SPD CNSTR).
- Prtess TMPY to check entered data before activation. (All STAR, APPR
& MISSED APPR Wpt)
- Press EXEC to activate F-- PLN
- F- PLN VERIFICATION
Cross check F-- PLN and Route on MCDU and NP MAP MODE
.
SECONDARY F- PLN
FPLN
- Press FPLN key twice
- SEC F- PLN . . . . . . . . . . . . . . . . . . . . . . . . . . . . . AS APPROPRIATE
Press twice on F-- PLN key to open SEC F-- PLN
Copy of the active F-- PLN and prepare a diversion to ALTERNATE
Mod 5948
2.03.16
NORMAL PROCEDURES
P2
BEFORE DESCENT - DESCENT
001
DEC 13
2 - PERFORMANCE :
.
PERF
- Press PERF key on the MCDU to display APPROACH page
- TRANS ALT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK
If transition altitude has changed.
- QNH . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . INSERT
- GND WIND / GUST . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . INSERT
- - - - - - - - - - - - - - - - - - - - - - - End of FMS preparation- - - - - - - - - - - - - - - - - - - - - PF
- NAVAIDs . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . SET
Prepare NAVAIDs using MCP VCP
Set - NAVAIDs using MCP / VCP (MCDU / RMS should only be used as
back up)
- COURSEs using FGCP
- Check on PFD :
- Cross check NAV SOURCE on PFD (EHSI)
- VOR / ILS 1&2 set MANUAL TUNE
Remark :
If ATIS warns of any unreliable DME or VOR/DME, crew must deselected.
Press DATA key, select NAV FRQ page then DESELECTED those related
NAVAIDs.
PF
- GO AROUND TQ . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK
ALL
- DH / MDA . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . SET & CHECK
ALL
- ARRIVAL BRIEFING . . . . . . . . . . . . . . . . . . . . . . . . . . . COMPLETE
ARRIVAL BRIEFING:
Main points are :
R ALL
Mod 5948
- Minimum safe altitude
- Weather at destination
- Approach procedures
- Decision Altitude / Height
- Go around Procedures
- Alternate
- Extra fuel
- DESCENT C/L . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . COMPLETE
2.03.16
NORMAL PROCEDURES
P3
BEFORE DESCENT - DESCENT
001
DEC 13
DESCENT
PNF
- DESCENT CLEARANCE . . . . . . . . . . . . . . . . . . . . . . . . . . . OBTAIN
PF
- ASSIGNED ALTITUDE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . SELECT
R PF
- IAS or VS MODE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . AS RQD
Crossing FL 100 : (FL 100 or any other FL according to local regulation)
PNF
- LANDING LIGHTS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON
CM1
- SEAT BELTS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON
CM1
- NO DEVICES . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON
CM1
- SEAT BELTS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON
ALL
- FMA . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK
PNF
- PRESSURIZATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK
R PNF
- ALL SYSTEMS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK
Mod 5948
2.03.16
NORMAL PROCEDURES
P4
BEFORE DESCENT - DESCENT
CHARACTERISTIC SPEEDS
FINAL APPROACH SPEEDS Normal condition
FINAL APPROACH SPEEDS Icing condition
Mod 5948 + 6521
100
FEB 12
2.03.17
NORMAL PROCEDURES
P1
APPROACH
001
FEB 12
AA
- Passing TRANSITION LEVEL or when cleared to an ALTITUDE (According to local
regulation) :
ALL
- ALTIMETERS 1+2 + IESI . . . . . . . . . . . . . . . SET QNH & CROSS CHECK
ALL
- PRESSURIZATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK
Note : Check Cabin ALT, RATE, DIFF pressure on SD pages
R
CAUTION
Max ∆ P authorized at landing = 0.35 psi
CM1
- CABIN REPORT . . . . . . . . . . . . . . . . OBTAIN FROM CABIN ATTENDANT
ALL
- APPROACH C/L . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . PERFORM
Mod 5948
2.03.18
NORMAL PROCEDURES
P1
BEFORE LANDING
100
DEC 13
AA
- DU CONFIGURATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK
Check display :
PF :
- MFD= ND ARC / VOR1+2 MAN,
- MCDU
= PERF APP page
PM :-- MFD
- MCDU
= ND / COM
= FPLN page
- When cleared for approach :
ALL
NAV SOURCES . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK
ALL
FMA . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . X CHECK
- When passing DECELERATION POINT :
R PF
ALL
- PL 1+2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . RETARD AS RQD
- SPEED SEL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK AUTO
- At appropriate speed :
PF
- “FLAPS 15” . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ORDER
PNF
- FLAPS 15 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . SELECT
PNF
- “FLAPS 15” . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ANNOUNCE
When FLAPS 15 are extended
R PNF
- TLU . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK LO SPEED
- At appropriate speed :
PF
- “GEAR DOWN” . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ORDER
PNF
- LDG GEAR LEVER . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . DOWN
PNF
- PWR MGT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . TO
PNF
- TAXI & TAKE OFF LIGHTS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON
When 3 green lights are illuminated :
PNF
- “LDG GEAR DOWN” . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ANNOUNCE
Mod 5948 + 6521
2.03.18
NORMAL PROCEDURES
P2
BEFORE LANDING
001
DEC 13
AA
- At appropriate speed :
R PF
- “FLAPS 30” . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ORDER
R PNF
- FLAPS 30 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . SELECT
R PNF
- “FLAPS 30” . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ANNOUNCE
When FLAPS 30 are extended
R PNF
- TLU . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK LO SPEED
ALL
- SPEED versus ICING CONDITIONS (ICING AOA LT) . . . . . . . . . . . CHECK
R PF
ALL
Mod : 5948
- PL 1 + 2 . . . . . . . . . . . . . . . . . . . . . . . . . ADJUST TO MAINTAIN V APP
Note : Vapp must be updated with the actual wind, in perf page
- BEFORE LANDING C/L . . . . . . . . . . . . . . . . . . . . . . . . . . . . . PERFORM
2.03.19
NORMAL PROCEDURES
P1
LANDING
100
DEC 13
PNF
At DH +500 ft (Or MDA + 500ft)
“FIVE HUNDRED ABOVE“ . . . . . . . . . . . . . . . . . . . . . . . . . . . ANNOUNCE
PNF
At DH +100 ft (Or MDA + 100ft)
“ONE HUNDRED ABOVE” . . . . . . . . . . . . . . . . . . . . . . . . . . . ANNOUNCE
At DH (Or MDA) :
PNF
“MINIMUM” . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ANNOUNCE
PF
- “LAND” or “GO AROUND, SET POWER, FLAPS” . . . . . . . . . . . . . . . . . .
. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ANNOUNCE AS APPROPRIATE
PF
- AP DISCONNECT . . . . . . . . . . . . . . . . . . PERFORM & ANNOUNCE
AP Disconnect PB press twice
R PNF
- YD . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . DISENGAGE
R
- YAW TRIM . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CENTER
PNF
- FLIGHT PARAMETERS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK
At 20 ft (radio altimeter)
- PL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FI
PF
PF
- FLARE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . PERFORM
PNF
PF
PNF
PNF
R
After touch down :
- IDLE GATE AUTOMATIC RETRACTION . . . . . . . . . . . . . . . . CHECK
- PL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . GI
- BOTH LOW PITCH GREEN LABEL . . . . . . . . . . . . . . . . . . . . CHECK
- “2 LOW PITCH” . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ANNOUNCE
ENGINES
LO PITCH LIGHT
PM ANNOUNCE
PF ACTION on
REVERSE
2 ENG
2 LO PITCH green
“2 LOW PITCH”
Normal use
1 LO PITCH green & 1 NO REV
reverse video red
“NO REVERSE”
No reverse
2 NO REV red reverse video
“NO REVERSE”
No reverse
1 LO PITCH green & 1 LO PITCH
amber or NO REV reverse video
“ONE LOW PITCH”
Use with care
1 ENG
R PF
R PNF
CM1
R CM2
ALL
- REVERSE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . USE AS RQD
- “SEVENTY KNOTS” . . . . . . . . . . . . . . . . . . . . . . . . . . . . ANNOUNCE
- NOSE WHEEL STEERING . . . . . . . . . . . . . . . . . . . . . . . . CONTROL
- CONTROL WHEEL . . . . . . . . . . . . . . . . . . . . . . . . . . . HOLD AS RQD
- “I HAVE CONTROL” / “YOU HAVE CONTROL” . . . . . . . ANNOUNCE
If PF is CM1, CM1 announce only “I HAVE CONTROL”
If PF is CM2, CM2 announce “YOU HAVE CONTROL” & CM1 answer :
“I HAVE CONTROL”
Mod 5948 + 6521
2.03.20
NORMAL PROCEDURES
P1
GO AROUND
001
FEB 12
AA
Simultaneously:
PF
- “GO AROUND, SET POWER, FLAPS ONE NOTCH” . . . . . . . . ANNOUNCE
PF
- GO AROUND P/B on PL . . . . . . . . . . . . . . . . . . . . . . . . . . . . DEPRESS
PF
- PL 1+2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ADVANCE TO RAMP
PF
- PITCH ATTITUDE . . . . . . . . . . . . . . . . . . ROTATE to GO AROUND PITCH
R PNF
- FLAPS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . RETRACT ONE NOTCH
PNF
- POWER . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK & ADJUST
Check TQ & NP = 100%
R PNF
- “POSITIVE RATE” . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ANNOUNCE
PF
- “GEAR UP” . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ORDER
R PNF
- LDG GEAR LEVER . . . . . . . . . . . . . . . . . . . . . . . . . . . . . SELECT UP
PNF
- YAW DAMPER . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON
PNF
- TAXI & TAKE OFF LIGHT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF
PF
- “HDG, LO BANK, IAS VGA” . . . . . . . . . . . . . . . . . . . . . . . . . . . ORDER
PNF
- HDG, LO BANK, IAS VGA . . . . . . . . . . . . . . . . . . . . . . . . . . . . . SELECT
PNF
- SPEED TARGET VGA . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK
Check speed target to VGA / AUTO mode
PNF
- “GEAR UP . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ANNOUNCE
PNF
- “FLAPS 15°° “ . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ANNOUNCE
PNF
- FMA . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK
When passing ACCELERATION ALTITUDE
PF
- PL 1 + 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . RETARD IN THE NOTCH
Then, refer to Take Off procedure
Mod 5948
2.03.21
NORMAL PROCEDURES
P1
001
AFTER LANDING
FEB 12
AA
When runway vacated :
CM1
- “AFTER LANDING PROCEDURE” . . . . . . . . . . . . . . . . . . . . . . . ORDER
CM2
- AFTER LANDING PROCEDURE :
R
- TRIMS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . RESET
- FLAPS 0 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . SELECT
- GUST LOCK . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ENGAGE
- FLIGHT CONTROL . . . . . . . . . . . . . . . . . . . . . CHECK LOCKED
- TCAS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . STBY
- XPDR . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . AS RQD
- RADAR . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . STBY
- LANDING LIGHT AND STROBE . . . . . . . . . . . . . . . . . . . . . OFF
- PROBES HTG / ANTI ICING / DE ICING . . . . . . . . . . . . . . . OFF
CM2
- ATPCS TEST (Last flight of the day) . . . . . . . . . . . . . . . . PERFORM
CAUTION
Do not perform ENG TEST while taxiing as ACW is temporary lost and,
subsequently, both main HYD pumps are temporarily lost as well.
R ATPCS TEST (dynamic test: once a day) . . . . . . . . . . . . . . . . . Refer to 2.03.24
Mod 5948
2.03.21
NORMAL PROCEDURES
P2
AFTER LANDING
001
FEB 12
AA
R
After at least one minute :
CM1
- CL1 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FTR THEN FUEL SO
CAUTION
Prior to ENG FTR, select HYD SD page, to check HYD pressure for
Normal brake efficiency
Note : Keep running at least one minute at GI power before shutting down to assist
in reducing residual heat build up in the engine nacelle.
Note : After the last flight of the day, maintain feather position for 20 seconds before
selecting FUEL SO to allow oil level check by maintenance.
CM2
- ACW BTC . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK CLOSED
ALL
- AFTER LANDING C/L . . . . . . . . . . . . . . . . . . . . . . . . . . . COMPLETE
CM2
- ACW BUSSES . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK SUPPLIED
Mod 5948
2.03.22
NORMAL PROCEDURES
P1
001
PARKING
NOV 14
AA
Note : If possible, park the aircraft with wind relative to the nose at 10 o’clock, to
minimize noise and exhaust gas inconvenience when in hotel mode.
Marshaller in sight (last turn):
CM2
- HYD SYST PRESS . . . . . . . . . . . . . . . . . . . . . . . . CHECK 3x 3000 psi
CM1
- TAXI & TO LIGHT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF
At the stand:
CM1
- PARKING BRAKE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON
Check HYD PRESS 3x 3000 psi
CM1
- CL 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FTR
CM1
- READY LIGHT . . . . . . . . . . . . . . . . . . . . . . . . CHECK ILLUMINATED
CM1
- PROP BRK . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ENGAGE
CAUTION
Engage PROP BRK only when NP STABILISED
CM1
- UNLK LIGHT . . . . . . . . . CHECK ILLUMINATED THEN EXTINGUISHED
CM1
- PROP BRK LIGHT . . . . . . . . . . . . . . . . . . . . . CHECK ILLUMINATED
CAUTION
If PROP BRK is used, ensure that propeller area is clear and protected
CM1
- PROP 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK STOPPED
CM1
- BEACON . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF
If GPU is used for disembarking :
CM1
- DC EXT PWR PB . . . . . . . . . . . . . . . . . . . . . . . . . DEPRESSED IN
If GPU available
CM1
- CL 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FUEL SO
CM1
- TAIL PROP . . . . . . . INSTALLED (CHECK WITH CABIN ATTENDANT)
CM1
- SEAT BELT SW . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF
CM1
- XPDR . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . STBY
CM1
- ENG BOOST FUNCTION (If installed) . . . . . . . . . . . . . . . . . . . . . OFF
CM1
- PARKING CHECK LIST . . . . . . . . . . . . . . . . . . . . . . . . . . . . PERFORM
Mod 5948
2.03.23
NORMAL PROCEDURES
P1
LEAVING THE AIRCRAFT
AA
001
APR 11
LEAVING THE AIRCRAFT
- OXYGEN MAIN SUPPLY . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF
- ICE & RAIN PROTECTION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF
- EXT LIGHTS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF
- EMER EXIT LT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . DISARM
- RADAR . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF
- CL 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FUEL SO
- FUEL PUMPS 1+2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF
- CDLS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF
If GPU was used for disembarking :
- DC EXT PWR . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF
- BAT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF
Mod 5948
2.03.24
NORMAL PROCEDURES
P1
DAILY CHECKS
001
DEC 13
AA
STICK PUSHER / SHAKER TEST (once a day)
- Release gust lock
- Push control column in nose down position
- Select WARN rotary selector (LH maintenance panel) to STICK PUSHER YES
- Depress and maintain PTT
- Monitor stall cricket and stick shaker.
- After ten seconds, monitor:
CHAN 1 and CHAN2 illuminate green on LH maintenance panel.
STICK PUSHER lights illuminate green on both pilots FMA.
Stick pusher actuator operates.
- Select WARN rotary selector to NORM FLT
- Reengage the gust lock
ATPCS TEST (dynamic test: once a day) (autofeather and uptrim while engines
running)
Conditions: - PL 1 + 2 in GI - CL 1 + 2 in AUTO.
- ATPCS P/B depressed in, OFF light extinguished
- PWR MGT on TO position
Check the following results on EWD:
- Turn the ATPCS knob to the left to the arm position and check
- ARM light . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ILLUMINATES
- TQ INDICATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . INCREASE
- NP & NH INDICATION . . . . . . . . . . . . . . . . . . . . . . . DECREASE
- Turn the ATPCS knob to ENG 1 position and check :
- ENG 2 UPTRIM LIGHT . . . . . . . . . . . . . . . . . . . . . . ILLUMINATES
- TQ 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . NO CHANGE
- NP, NH . . . . . . . . . . . . . . . . . . . . . . . . . . . INCREASE SLIGHTLY
- TQ 1 needles indication . . . . . . . . . . . DECREASE BELOW 18 %
- After 2.15 s : associated propeller is automatically feathered
- ARM light . . . . . . . . . . . . . . . . . . . . . . . . . . EXTINGUISHED
- PROP 1 AUTO FTR LABEL . . . . . . . . . . . . . . . . . DISPLAYS
- Turn the ATPCS knob to the right to the arm position and check :
- ARM light . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ILLUMINATES
- TQ INDICATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . INCREASE
- NP & NH INDICATION . . . . . . . . . . . . . . . . . . . . . . . DECREASE
- Turn the ATPCS knob to ENG 2 position and check :
- ENG 1 UPTRIM LIGHT . . . . . . . . . . . . . . . . . . . . . . ILLUMINATES
- TQ 1 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . NO CHANGE
- NP, NH . . . . . . . . . . . . . . . . . . . . . . . . . . . INCREASE SLIGHTLY
- TQ 2 needles indication . . . . . . . . . . . DECREASE BELOW 18 %
- After 2.15 s : associated propeller is automatically feathered
- ARM light . . . . . . . . . . . . . . . . . . . . . . . . . . EXTINGUISHED
- PROP 2 AUTO FTR LABEL . . . . . . . . . . . . . . . . . DISPLAYS
R CAUTION : Do not perform ENG TEST while taxiing as ACW is temporarily lost and
consequently, both HYD pumps are temporarlily lost as well.
Note : If ENG TEST must be repeated, wait 10 minutes before setting ATPCS selector
in ENG position in order not to damage feathering pumps. (Winding heating).
Mod: 5948
2.03.24
NORMAL PROCEDURES
P2
DAILY CHECKS
001
FEB 12
AA
TRIMS CHECK FOR THE FIRST FLIGHT OF THE DAY
- PITCH, ROLL AND YAW TRIM OPERATION . . . . . . . . . . . . . . . . . . . CHECK
- Check the normal trim activation in both directions by simultaneously depressing
both control rocker switches.
- For few seconds depress independently each single control rocker switch and
check the non-- activation of the corresponding TRIM in both possible directions.
- TRIMS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . RESET FOR TAKE OFF
COCKPIT DOOR DAILY CHECK (DAILY):
- COCKPIT DOOR LOCKING SYSTEM SW . . . . . . . . . . . . . . . . . . . . . . . . ON
In the cargo compartment, on the DOOR CALL panel :
- EMER P/B . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . DEPRESS
- CHECK OPEN LIGHT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FLASHES
In the cockpit, check
- BUZZER . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . SOUNDS
- OPEN LIGHT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FLASHES
- DENIED ACCESS TEST :
In the cockpit :
- TOGGLE SW on the COCKPIT DOOR CTL panel . . . . . . . . . DENY
- CHECK BUZZER . . . . . . . . . . . . . . . . . . . . . . . . . . . . . SILENCES
- CHECK OPEN LIGHT . . . . . . . . . . . . . . . . . . . . . . EXTINGUISHES
In the cargo compartment, on the DOOR CALL panel :
- OPEN LIGHT . . . . . . . . . . . . . . . . . . . . . . . . . . . . EXTINGUISHES
- DENIED LIGHT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ILLUMINATES
- AUTHORIZED ACCESS TEST :
In the cargo compartment, on the DOOR CALL panel :
- EMER P/B . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . DEPRESS
In the cockpit :
- TOGGLE SW . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OPEN
- DOOR LOCKING SYSTEM . . . . . . . . . . . . . . . . . . . . . . . . UNLOCK
- COCKPIT DOOR LOCKING SYSTEM SW . . . . . . . . . . . . . . . . . . . . . . . OFF
- COCKPIT DOOR CTL panel FAULT LIGHT . . . . . . . . . . . . . . . . . . . . CHECK
- FUNCTIONAL CHECK OF THE MANUAL LOCK BOLTs.
Mod: 5948
2.03.24
NORMAL PROCEDURES
P3
DAILY CHECKS
001
NOV 14
AA
APM TEST:
1 - Press and hold the APM PTT TEST P/B for all test duration and check:
2 - Check FMA :
- CRZ SPEED LOW
- DGD PERF
- INCREASE SPEED (flashing)
3 - Check : APM FAULT light (Local alarm)
4 - Check on FWS ALERTING Window (flashing)
- INCREASE SPEED
- DEGRADED PERF
- APM FAULT
Release APM PTT TEST P/B and check :
- ALL ALARMS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . EXTINGUISH
ENG BOOST FUNCTION TEST : (If installed)
Conditions :
- PL 1 + 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . GI
- EEC 1 + 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON
Test for each BOOST rating :
- Rating . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . SELECT
After 5s :
- ON light . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ILLUMINATED
- FAULT light . . . . . . . . . . . . . . . . . . . . . . . . . . . . EXTINGUISHED
End of test :
- ENG BOOST FUNCTION . . . . . . . . . . . . . . . . . . . . . . . . . . OFF
Note : Test can be performed disregarding engine running condition (both engines running,
and both engines shut-- off)
Mod: 5948
2.04.00
EMERGENCY PROCEDURES
P1
CONTENTS
AA
100
FEB 12
2.04.00
CONTENTS
2.04.01
INTRODUCTION
( including human factor recommendations for Electronic Check List use)
2.04.02
Alert
ENG 1(2) FIRE
ENG 1(2) FIRE
ENG 1(2) FIRE
ENG 1+2 OUT
ENG 1(2) OUT
2.04.03
Alert
ELEC SMK
FWD SMK
AFT SMK
AUX AFT SMK
2.04.04
POWER PLANT
Procedure
ENG 1(2) FIRE OR SEVERE MECHANICAL DAMAGE IN
FLIGHT
ENG 1(2) FIRE OR SEVERE MECHANICAL DAMAGE ON
GROUND
ENG 1(2) FIRE AT TAKE OFF
BOTH ENGINES FLAME OUT
ENG 1(2) FLAME OUT AT TAKE OFF
SMOKE
Procedure
SMOKE
ELECTRICAL SMOKE
AIR COND SMOKE
FWD SMOKE
AFT SMOKE
AUX AFT COMPT SMOKE
ELECTRICAL SYSTEM
Alert
Procedure
ELEC DC GEN 1+2
DUAL DC GEN LOSS
2.04.05
Alert
MISCELLANEOUS
Procedure
EMERGENCY DESCENT
DITCHING
FORCED LANDING
ON GROUND EMERGENCY EVACUATION
BOMB ON BOARD
SEVERE ICING
RECOVERY AFTER STALL OR ABNORMAL ROLL CONTROL
UNRELIABLE AIRSPEED INDICATION
Mod : 5948 + 6521
APR 11
PM -- Pilot monitoring
Mod : 5948
2.04.01
EMERGENCY PROCEDURES
P2
INTRODUCTION
100
DEC 13
AA
PROCEDURES INITIATION
- No action will be taken (apart from depressing MW pb):
. Until flight path is stabilized.
. Under 400 ft above runway (except for propeller feathering after engine failure
during approach at reduced power if go around is considered).
- Before performing a procedure, the crew must assess the situation as a whole, taking
into consideration the failures, when fully identified, and the constraints
imposed.
ANALYSIS OF CONSEQUENCES OF A FAILURE ON THE FLIGHT
Basic airmanship calls for a management review of the remaining aircraft capabilities
under the responsability of CM1.
FWS ALERTING
( see page 3 )
ELECTRONIC CHECK- LISTS USE : HUMAN FACTOR RECOMMENDATIONS
Upon completing procedure, PNF need tick each item, i.e. meaning the item was
acknowledged and taken care of.
- Importance of procedure pending message:
Pending procedure notice need be carefully considered when displayed, therefore
meaning this one needs yet be performed and completed.
- Importance “PROCEDURE COMPLETED“ item:
Completed procedure item, is displayed at the end of each started procedure,
provided all items have been properly ticked. It is the only way to complete and
correctly terminate a started procedure.
- Importance “IF” statements:
Following each procedure’s ”IF” alternative proposition, PNF must carefully read and
understand these different alternatives to meet current depiction and get PF’s
approval and confirmation to comply with relevant ”IF” procedure.
Once an ”IF” case has been selected, PNF must carefully read and understand
relevant procedure’s proposition and it’s associated subtitle, obtain PF’s confirmation
before resuming corresponding associated task.
R - Awareness of STATUS:
R The flight crew must open and review the statuses during recall.
- DU failure:
Neither DU fault procedure exists and no relevant reference is made in FWS, FCOM
nor QRH.
Mod : 5948 + 6521
2.04.01
EMERGENCY PROCEDURES
P3
INTRODUCTION
001
FEB 12
AA
R FWS ALERTING
When the TO inhibition signal computed by FMA is actived, all alerts are inhibed exept
(this inhibition is cancelled automatically at landing gear retraction or manually by action
on the RCL push-- button) :
WARNING
CAUTION
- ENG 1 (2) OUT
- LDG GEAR NOT DN
- CONFIG
- NAC OVHT
- PROP BREAK
- ENG 1 (2) OIL PRESS
- FLAPS UNLK
- PITCH DISC
- EXCESS CAB ∆P
- EXCESS CAB ALT
- TRIM RUNAWAY
- AP DISCONNECTION
- APCH CAPABILITY
- FD MODE REVERSION
- ALTITUDE ALERT
- PITCH TRIM ASYM
- FLT CTL TLU
- AP PITCH TRIM
- PICH MISTRIM
- AILERON MISTRIM
- RUDDER MISTRIM
- AP YAW TRIM
- ADC 1+2
- AHRS 1+2
- IRS 1+2
- ATT DISAGREE
- IAS DISAGREE
- ALT DISAGREE
- MFC 1B + 2B
- FLT CTL TLU
- ADC
- AHRS
- AHRS NOT ALIGN
- IRS
- IRS NOT ALIGN
- IRS IN ALIGN
- HDG DISAGREE
- IRS ATT ONLY
- DATA RECORDER
- CALLS
- VLE, VFE EXCEED
Mod : 5948
2.04.02
EMERGENCY PROCEDURES
P1
POWER PLANT
001
FEB 12
AA
ENG 1 (2) FIRE OR SEVERE MECHANICAL DAMAGE IN FLIGHT
ALERT
CONDITION
VISUAL
AURAL
Fire signal
-- MW light flashing red
-- Associated ENG 1(2) FIRE
red message on EWD + Red
reverse video FIRE 1 (2) on
EWD engine indications
-- red light in associated FIRE
handle
CRC
-- FUEL SO red light in
associated CL
PROCEDURE
ENG 1 (2) FIRE OR SEVERE
MECHANICAL DAMAGE IN FLIGHT
R
PL affected side . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FI
CL affected side . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FTR THEN FUEL SO
FIRE HANDLE affected side . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . PULL
J If condition persists after 10 seconds
AGENT 1 affected side . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . DISCH
J If condition persists after 30 seconds
AGENT 2 affected side . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . DISCH
LAND ASAP
SINGLE ENG OPERATION procedure (2.05.02) . . . . . . . . . . . . . . . . . . . APPLY
COMMENTS
- Fire handle remains illuminated as long as a fire is detected.
- The 10 seconds delay allows to reduce nacelle ventilation in order to increase the agent
effect.
- CRC stops when depressing MW. May also be cancelled by use of EMER AUDIO
CANCEL SW.
- Do not attempt to restart engine.
- Refer to SINGLE ENG OPERATION procedure.
Mod : 5948
2.04.02
EMERGENCY PROCEDURES
P2
POWER PLANT
001
FEB 12
AA
ENG 1 (2) FIRE OR SEVERE MECHANICAL DAMAGE ON GROUND
ALERT
CONDITION
VISUAL
AURAL
Fire signal
-- MW light flashing red
-- Associated ENG 1(2)
FIRE red message on EWD
+ Red reverse video FIRE 1
(2) on EWD engine
indications
-- red light in associated
FIRE handle
CRC
OR
ATPCS
sequence
or engine flame
out
-- Fuel SO red light in
associated CL
PROCEDURE
ENG 1 (2) FIRE OR SEVERE
MECHANICAL DAMAGE ON GROUND
R
PL 1 + 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . GI / REVERSE AS RQD
F When aircraft stopped
PARKING BRAKE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ENGAGE
CL 1 + 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FTR THEN FUEL SO
FIRE HANDLE affected side . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . PULL
J If condition persists
AGENT 1 affected side . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . DISCH
J If condition persists after 30 seconds
AGENT 2 affected side . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . DISCH
J If evacuation required
EMER EVACUATION ON GROUND procedure (2.04.05)) . . . . . . . APPLY
COMMENTS
- Same comments as in flight
- The aircraft may be stopped using full reverse
- Notify ATC the nature of the emergency and state intentions.
- Only VHF 1 is available on battery
- Battery is left ON until leaving the aircraft to ensure cabin communication. Only PA is
available on battery.
Mod : 5948
2.04.02
EMERGENCY PROCEDURES
P3
001
POWER PLANT
FEB 12
AA
R ENG 1 (2) FIRE AT TAKE OFF
ALERT
CONDITION
VISUAL
AURAL
Fire signal
-- MW light flashing red
-- Associated ENG 1(2) FIRE
red message on EWD + Red
reverse video FIRE 1 (2) on
EWD engine indications
-- red light in associated FIRE
handle
CRC
-- Fuel SO red light in
associated CL
R
PROCEDURE
ENG 1 (2) FIRE AT TAKE OFF
Note: Captain may decide to shut down affected engine before reaching
acceleration altitude, but not before 400ft AGL.
F When airborne
LDG GEAR . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . UP
F
At acceleration altitude
PWR MGT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MCT
F At VFTO
J If normal condition
FLAPS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 0°
J If icing condition
FLAPS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MAINTAIN 15°
PL affected side . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FI
CL affected side . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FTR THEN FUEL SO
FIRE HANDLE illuminated . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . PULL
J If fire persists after 10 seconds
AGENT 1 affected side . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . DISCH
J If fire persists after 30 seconds
AGENT 2 affected side . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . DISCH
BLEED engine alive . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF if necessary
LAND ASAP
SINGLE ENG OPERATION procedure (2.05.02) . . . . . . . . . . . . . . . . . . . . APPLY
COMMENTS
- Same comments as ENG FIRE IN FLIGHT procedure.
Mod : 5948
2.04.02
EMERGENCY PROCEDURES
P4
001
POWER PLANT
AA
FEB 12
BOTH ENGINES FLAME OUT
ALERT
CONDITION
VISUAL
AURAL
Both engines
flame--out
-- MW light flashing red
-- Associated ENG 1+2 OUT red message on EWD
CRC
PROCEDURE
BOTH ENGINES FLAME OUT
PL 1 + 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FI
J If NH drops below 30 % (no automatic relight)
CL 1 + 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FTR THEN FUEL SO
FUEL SUPPLY . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK
OPTIMUM SPEED . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Vm HB
COMMUNICATIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . VHF 1
ENG START ROTARY SELECTOR . . . . . . . . . . . . . . . . . . . . . START A & B
ENG 2 RELIGHT
ENG 2 START pb . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON
F When NH above 10%
CL 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FTR
ENG 2 RELIGHT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MONITOR
CL 2 then PL 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . AS RQD
ENG 1 RELIGHT
ENG 1 START pb . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON
F When NH above 10%
R
R
R
CL 1 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FTR
ENG 1 RELIGHT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MONITOR
CL 1 then PL 1 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . AS RQD
J If neither engine starts
CL 1 + 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FTR THEN FUEL SO
ENG START ROTARY SELECTOR . . . . . . . . . . . . . . . . OFF/START ABORT
FUEL PUMPS 1 + 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF
FORCED LANDING or DITCHING procedure(2.04.05) . . . . . . . . . . . . APPLY
CAUTION : Do not select AVIONICS VENT EXHAUST MODE to OVBD.
J If at least one engine recovered
CL / PL engine(s) recovered . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . AS RQD
J If one engine not recovered
CL engine NON recovered . . . . . . . . . . . . . . . . . . . FTR THEN FUEL SO
LAND ASAP
SINGLE ENG OPERATION procedure(2.05.02) . . . . . . . . . . . . . . APPLY
SYSTEMS affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . RESTORE
APM . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF
Mod : 5948
2.04.02
EMERGENCY PROCEDURES
P5
POWER PLANT
001
APR 11
AA
COMMENTS
- Fuel supply check consists in checking correct fuel quantity and correct pressure (use
Engine secondary SD page to have access to fuel data).
- The optimum airspeed to achieve best lift to drag ratio is Vm HB.
IF BOTH ENG ARE LOST
- If landing gear extension is scheduled, emergency extension has to be performed.
- In short final, reduce speed as required by landing field in order to touch down with
minimum vertical speed;
Mod : 5948
2.04.02
EMERGENCY PROCEDURES
P6
POWER PLANT
AA
001
FEB 12
ENG 1 (2) FLAME OUT AT TAKE OFF
ALERT
An engine flame out may be recognized by :
- Sudden dissymetry
- TQ decrease
- Rapid ITT decrease
CONDITION
VISUAL
AURAL
engine flame out
or ATPCS
sequence
-- MW light flashing red
-- Associated ENG 1 (2) OUT red
message on EWD + AUTO FTR and
UPTRIM labels on EWD
CRC
PROCEDURE
ENG 1(2) FLAME OUT AT TAKE OFF
R
UPTRIM . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK
AUTOFEATHER . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK
J If no uptrim
PL 1 + 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ADVANCE TO THE RAMP
F When airborne
LDG GEAR . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . UP
BLEED 1 + 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF, IF NOT FAULT
F At acceleration altitude
ALT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . SET
F At VFTO
PL 1 + 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . IN THE NOTCH
PWR MGT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MCT
IAS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . SET
J If normal conditions
SPD DGT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK VFTO
FLAPS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 0°
J If icing conditions
SPD DGT . . . . . . . . . . . . . . . . . . . . . . CHECK VFTO ICING FLAPS 15_
FLAPS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MAINTAIN 15°
PL affected side . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FI
CL affected side . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FTR THEN FUEL SO
BLEED engine alive . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF if necessary
J If damage suspected
FIRE HANDLE affected side . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . PULL
LAND ASAP
SINGLE ENG OPERATION procedure(2.05.02) . . . . . . . . . . . . . . . . . APPLY
J If no damage suspected
ENG RESTART IN FLIGHT procedure(2.05.02) . . . . . . . . . . . . . . . . . APPLY
J If unsuccessful :
LAND ASAP
SINGLE ENG OPERATION procedure(2.05.02) . . . . . . . . . . . . . . . . . APPLY
Mod : 5948
2.04.03
EMERGENCY PROCEDURES
P1
SMOKE
001
FEB 12
AA
SMOKE
PROCEDURE
SMOKE
CREW OXY MASKS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON / 100%
GOGGLES . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . SET
CREW COMMUNICATIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ESTABLISH
RECIRC FANS 1 + 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF
AP . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON
R
R
R
R
R
SMOKE SOURCE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . IDENTIFY
J If source not identified or electrical smoke suspected
Note : ELEC SMK may be activated by an air conditioning smoke source
ELECTRICAL SMOKE procedure(2.04.03) . . . . . . . . . . . . . . . . . . . . . APPLY
J If air conditioning smoke identified
AIR COND SMOKE procedure(2.04.03) . . . . . . . . . . . . . . . . . . . . . . . APPLY
J If FWD SMK illuminated or smoke in FWD zone of aircraft
FWD SMOKE procedure(2.04.03) . . . . . . . . . . . . . . . . . . . . . . . . . . . APPLY
J If AFT SMK illuminated or smoke in AFT zone of aircraft
AFT SMOKE procedure(2.04.03) . . . . . . . . . . . . . . . . . . . . . . . . . . . . APPLY
J If AUX AFT COMPT SMK illuminated (depending on models)
AUX AFT COMPT SMK procedure(2.04.03) . . . . . . . . . . . . . . . . . . . . APPLY
Mod : 5948
2.04.03
EMERGENCY PROCEDURES
P2
SMOKE
AA
001
FEB 12
ELECTRICAL SMOKE
ALERT
CONDITION
Smoke detected in the
avionics ventilation circuit
VISUAL
AURAL
-- MW light flashing red
-- ELEC SMK red message on
EWD
CRC
-- associated ELEC SMK red
indication on SD cabin page.
PROCEDURE
ELECTRICAL SMOKE
SMOKE procedure(2.04.03) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . APPLY
AVIONICS VENT EXHAUST MODE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OVBD
AIR FLOW . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . HIGH
DC SVCE AND UTLY BUS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF
DC BTC . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ISOL
ACW GEN 1 + 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF
SUSPECTED EQUIPMENTS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF
J If smoke origin not identified
LAND ASAP
ACW TOTAL LOSS procedure(2.05.04) . . . . . . . . . . . . . . . . . . . . . . . APPLY
J If smoke origin identified
NOT AFFECTED EQUIPMENTS . . . . . . . . . . . . . . . . . . . . . . . . . RESTORE
R
F During descent when nP below 1 PSI
OVBD VALVE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FULL OPEN
AVIONICS VENT EXHAUST MODE . . . . . . . . . . . . . . . . . . . . . . . . . NORM
COMMENTS
- Avionics compartment ventilation without cabin contamination is ensured by :
- selecting AVIONICS VENT EXHAUST mode OVBD
- shuting off the recirculation fans
- selecting the PACKS AIR FLOW HIGH.
- Auto isolation is prepared on the main electrical system by opening the BTC.
- Suspected equipment may be shut off contingently by pulling out associated circuit
breaker.
- When nP < 1 PSI, OVBD VALVE is selected FULL OPEN and AVIONICS VENT
EXHAUST mode NORM in order to recover air evacuation capability through the
EXTRACT FAN without any pressurization problem.
Mod : 5948
2.04.03
EMERGENCY PROCEDURES
P3
SMOKE
001
FEB 12
AA
AIR COND SMOKE
PROCEDURE
AIR COND SMOKE
R
R
SMOKE procedure(2.04.03) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . APPLY
PACK VALVE 1 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF
MAX FL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 200 / MEA
J If smoke persists
PACK VALVE 1 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON
PACK VALVE 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF
CAUTION : Evacuation of air conditioning smoke may trigger electrical smoke
warning. Disregard it.
ENGINES PARAMETERS . . . . . . . . . . . . . . . . . . . . . CAREFULLY MONITOR
J If any anomaly occurs such as :
- ENG OVER LIM amber message on EWD
- Total loss of NL indication
- Engine abnormality clearly identified (NH, NL, ITT indications, noise, surge...)
R
CAUTION : Confirm which engine is showing signs of abnormal operation in
order to avoid shutting down the safe engine.
PL affected side . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FI
CL affected side . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FTR THEN FUEL SO
LAND ASAP
SINGLE ENG OPERATION procedure . . . . . . . . . . . . . . . . . . . . . . . . APPLY
COMMENTS
- Ensure crew communication is established. Avoid the use of interphone position to
minimize interference from oxygen mask breathing noise. Check oxygen mask at
100%.
- Recirculation fans are switched off to limit cabin contamination.
Mod : 5948
2.04.03
EMERGENCY PROCEDURES
P4
SMOKE
001
FEB 12
AA
FWD SMOKE
ALERT
CONDITION
Smoke detected in the
forward cargo compartment
Smoke detected in the
forward cargo compartment
(CARGO VERSION ONLY)
VISUAL
AURAL
- MW lt flashing red
- FWD SMK red message on
EWD
- Associated FWD SMK red indication on SD Cabin page.
- MW lt flashing red
- FWD SMK red message on
EWD
- Associated FWD SMK red indication on SD Cabin page.
CRC
CRC
PROCEDURE
FWD SMK
SMOKE procedure(2.04.03) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . APPLY
R
R
1) PASSENGERS VERSION
CABIN CREW (PA) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ADVISE
AVIONICS VENT EXHAUST MODE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OVBD
AIR FLOW . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . HIGH
EXTRACT AIR FLOW LEVER (RH MAINT PANEL) . . . . . . . . . . . . . . . . . CLOSED
CABIN CREW WITH PORTABLE EXTINGUISHER LOCATE and KILL SOURCE OF
SMOKE
LAND ASAP
D During descent when P below 1 PSI
OVBD VALVE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FULL OPEN
AVIONICS VENT EXHAUST MODE . . . . . . . . . . . . . . . . . . . . . . . . . . . . NORM
2) CARGO VERSION
CAB PRESS MODE SEL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MAN
CAB ALT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MAX INCREASE
ENG 2 BLEED (Except when in single bleed operation) . . . . . . . . . . . . . . . . . . OFF
PACK VALVE 2 (Except when in single pack operation) . . . . . . . . . . . . . . . . . . . OFF
CAB VENT AIR FLOW . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF
FLIGHT COMPT TEMP SEL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . HOT
CAUTION : LAND ASAP. If a quick landing is not possible : climb and maintain minimum
FL160, FL 200 is recommended. When “Excess CAB ALT“ warning,
maintain FL 160, maintain CAB ALT Max increase.
Note : Smoke alert may be generated during smoke evacuation process.
Mod : 5948
2.04.03
EMERGENCY PROCEDURES
P5
SMOKE
001
APR 11
AA
COMMENTS
- Ensure crew communication is established. Avoid the use of interphone position to
minimize interference from oxygen mask breathing noise. Check oxygen mask at
100%.
- Cargo ventilation without cabin or cockpit contamination is ensured by:
- selecting AVIONICS VENT EXHAUST mode OVBD
- shuting off the recirculation fans
- selecting HIGH the PACKS AIR FLOW
- isolating the cockpit panels ventilation by selecting EXTRACT AIR FLOW to
CLOSED.
- Cabin crew is in charge to locate and kill source of smoke with the extinguisher.
- Cabin crew uses the portable oxygen bottle with the full face mask on 100 % position
with full pressure. A fire extinguisher (3 kg - 7 Lbs) is available at the left front
Locker).
- When nP < 1 PSI, OVBD VALVE is selected full open and avionics VENT NORM in
order to recover air evacuation capability through the extract fan without any
pressurization problem.
Mod 5948
2.04.03
EMERGENCY PROCEDURES
P6
SMOKE
AA
001
FEB 12
AFT SMOKE
ALERT
CONDITION
Smoke detected in the aft
cargo compartment or in the
lavatory
Smoke detected in the aft
cargo compartment (CARGO
VERSION ONLY)
VISUAL
- MW lt flashing red
- AFT SMK red message on EWD
- Associated LAV SMK or AFT
COMPT SMK or AFT SMK red
indication on SD cabin page.
- MW lt flashing red
- AFT SMK red message on EWD
- Associated AFT SMK red
indication on SD cabin page.
AURAL
CRC
CRC
PROCEDURE
AFT SMOKE
R
R
SMOKE procedure(2.04.03) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . APPLY
1) PASSENGERS VERSION
CABIN CREW (PA) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ADVISE FOR ACTION
AIR FLOW . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . HIGH
2) CARGO VERSION
CAB PRESS MODE SEL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MAN
CAB ALT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MAX INCREASE
ENG 2 BLEED (Except when in single bleed operation) . . . . . . . . . . . . . . . . . . OFF
PACK VALVE 2 (Except when in single pack operation) . . . . . . . . . . . . . . . . . . . OFF
CAB VENT AIR FLOW . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF
FLIGHT COMPT TEMP SEL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . HOT
CAUTION : LAND ASAP. If a quick landing is not possible : climb and maintain
minimum FL 160, FL 200 is recommended. When “Excess CAB ALT”
warning maintain FL 160, maintain CAB ALT Max increase.
Note : Smoke alert may be generated during smoke evacuation process.
COMMENTS (PASSENGERS VERSION ONLY)
- The cabin crew is in charge to locate and kill the source of smoke, if possible, using
the portable fire extinguisher located in the cabin. Before entering the aft cargo area,
the cabin attendant must wear an oxygen mask. To leave the aft cargo door open may
induce some cabin contamination therefore it must be avoided.
Mod 5948
2.04.03
EMERGENCY PROCEDURES
P7
001
SMOKE
FEB 12
AA
AUX AFT COMPT SMOKE
ALERT
CONDITION
Smoke detected in the
auxiliary aft cargo
compartment
VISUAL
- MW light flashing red
- AUX AFT SMK red message on EWD
- Associated AUX AFT
COMPT SMK red indication
on SD cabin page.
- SQUIB white light on
COMPT SMK panel
AURAL
CRC
PROCEDURE
AUX AFT COMPT SMOKE
(depending on models)
R
SMOKE procedure(2.04.03) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . APPLY
AUX AFT COMPT AGENT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . DISCH
COMMENTS
Aux aft cargo ventilation valve closes as soon as the aux aft cargo smoke signal is
generated and remains closed when the extinguishing agent has been discharged to
improve the agent efficiency.
Mod : 5948
2.04.04
EMERGENCY PROCEDURES
P1
001
ELECTRICAL SYSTEM
FEB 12
DUAL DC GEN LOSS
ALERT
CONDITION
VISUAL
AURAL
DC generation
channel is
inoperative
-- MW light flashing red
-- ELEC DC GEN 1+ 2 red message on EWD and 2
DC GEN amber message on EWD.
CRC
-- DC GEN 1(2) fault + DC BUS 1(2) OFF +
INV 2 FAULT + AC BUS 1(2) OFF + SHED
on overhead panel and in AC/DC SD page.
PROCEDURE
DUAL DC GEN LOSS
R
R
PF . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CAPT
DC GEN 1 + 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF then ON
J If no generator recovered
HYD GREEN PUMP . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF
TRU . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON
Make sure that TRU arrow illuminates, BAT arrows extinguish.
Note : If TRU FAULT LAND ASAP
MAN RATE KNOB . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9 O’CLOCK
CAB PRESS MODE SEL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MAN
AVIONICS VENT EXHAUST MODE . . . . . . . . . . . . . . . . . . . . . . . . . . OVBD
BAT SW . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OVRD
F/O ATT HDG . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . SWITCH TO SYS 1
F/O ADC . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . SWITCH TO SYS 1
AP . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . AS RQD
CAUTION: AP may be used in single source with limitations, especially the use of
AP is prohibited below 1000ft AGL.
COM / SURV / NAV . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . USE MCDU 1
XPDR . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . SET XPDR 1
ATC (VHF 1 or HF or HF 2) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . NOTIFY
MIN CAB LIGHT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF
Note : NAV lights switch set to ON is necessary to provide IEP illumination
TLU . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MAN MODE LO SPD
F When TLU LO SPD illuminates
TLU . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . AUTO
CAUTION: Avoid large rudder input if IAS above 180 kt.
STICK PUSHER / SHAKER . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF
STICK PUSHER / SHAKER FAULT procedure(2.05.06) . . . . . . . . . . . APPLY
SIDE WINDOWS / WINDSHIELD HTG . . . . . . . . . . . . . . . . . . . . . . . . . OFF
. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . to be continued next page .../...
Mod : 5948
2.04.04
EMERGENCY PROCEDURES
P2
ELECTRICAL SYSTEM
001
FEB 12
DUAL DC GEN LOSS
R
.../...
DE-- \ ANTI-- ICING MODE SEL AUTO FAULT procedure(2.05.09) . . . . APPLY
AUTO PRESS FAULT procedure(2.05.08) . . . . . . . . . . . . . . . . . . . . . APPLY
BUS EQUIPMENT LISTS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK
Note: Periodically compare PFD with IESI, crosscheck HDG / TK / STBY-- HDG
F Before descent
PAX INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . USE PA
HYD X FEED . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON
Note: Selecting HYD X FEED ON allows to recover green hydraulic system.
F At touch down
IDLE GATE LEVER . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . PULL
COMMENTS
- Safety analysis leads us to consider the case when the DUAL DC GEN LOSS is due
to :
. Single engine operation,
. DC GEN inoperative on the operating engine.
In such a case, HYD GREEN PUMP has to be set to OFF position in order not to
overload the ACW GEN of the remaining engine.
- Selecting TRU ON allows to recover EMER, ESS and STBY (AC and DC) buses supply
from ACW generators.
- HYD X FEED is opened in order to pressurize the whole hydraulic system from blue
pump.
- Minimum cabin light must be switched OFF to limit the electrical load of the TRU.
- As DC BUS 1 is lost, automatic pressurization is lost.
- Both stick pusher and stick shaker are lost without FAULT alarm.
- DC STBY BUS undervoltage may occur due to a failure of the STBY BUS system
circuit. In this event, the OVRD function may be used to transfer the STBY BUS supply
from the MAIN BAT BUS to the EMER BAT BUS.
- TLU AUTO mode is lost and MAN MODE must be used.
MAN MODE acts on TLU standby actuator which remains powered even if TLU is in LO SPD
established position.
When TLU SW is set to AUTO position, TLU standby actuator electrical power is off.
- PA must be used for pax instructions because cabin signs are not supplied in emergency.
Mod : 5948
2.04.05
EMERGENCY PROCEDURES
P1
MISCELLANEOUS
001
FEB 12
AA
EMERGENCY DESCENT
PROCEDURE
EMERGENCY DESCENT
R
R
OXYGEN MASKS / CREW COMMUNICATIONS . . . . . . . . . . . . . . . . . . AS RQD
GOGGLES . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . AS RQD
DESCENT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . INITIATE
PL 1 + 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FI
CL 1 + 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 100% OVRD
OXYGEN PAX SUPPLY . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . AS RQD
SPEED . . . . . . . . . . . . . . MMO / VMO (or less if structural damage is suspected)
SIGNS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON
ATC (VHF 1 / HF) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . NOTIFY
MEA . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK
COMMENTS
- Oxygen may be used with N/100 % rocker in N position if air in the cabin is not
contaminated.
- Maximum airspeed is MMO/VMO. But if structural damage is suspected, use the flight
controls with care and reduce speed as appropriate. Landing gear may be extended in
order to increase rate of descent.
- Notify ATC of the nature of the emergency encountered and state intentions. In the
event ATC cannot be contacted, select code A7700 or transmit the distress message
on one of the following frequencies (VHF) 121,5 MHz or (HF) 8364 KHz. Only VHF 1 is
available on battery.
- CL are selected 100% OVRD to increase drag and consequently to increase the rate of
descent.
Mod : 5948
2.04.05
EMERGENCY PROCEDURES
P2
MISCELLANEOUS
001
DEC 13
DITCHING
PROCEDURE
DITCHING
R
S Preparation (time permitting)
ATC (VHF1 or HF) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . NOTIFY
XPDR) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . EMERGENCY
CABIN CREW (PA) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . NOTIFY
SIGNS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON
GPWS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF
TERR . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF
CABIN AND COCKPIT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . PREPARE
. Loose equipment secured
. Survival equipment prepared
. Belts and shoulder harnesses locked.
AUTO PRESS - LDG ELEVATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . SET
S Approach
AUTO PRESS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . DUMP
PACKS 1 + 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF
OVBD VALVE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FULL CLOSE
HYD AUX PUMP pushbutton (pedestal) . . . . . . . . . . . . . . . . . . . . . . . DEPRESS
FLAPS (if available) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 30_
LDG GEAR LEVER . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . UP
S 30 secondes before impact or 1250 ft above sea level
DITCH pb . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON
ENG START ROTARY SELECTOR . . . . . . . . . . . . . . . . . OFF / START ABORT
CABIN REPORT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OBTAINED
S Before ditching (200 ft)
MINIMIZE IMPACT SLOPE
OPTIMUM PITCH ATTITUDE FOR IMPACT . . . . . . . . . . . . . . . . . . . . . . . . 9_
BRACE FOR IMPACT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ORDER
Note : In case of night ditching, shutting down both engines may be performed, at
captain discretion, immediately after the impact ( avoiding loss of landing
lights during flare out).
CL 1 + 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FTR THEN FUEL SO
FIRE HANDLES 1 + 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . PULL
FUEL PUMPS 1 + 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF
S After ditching
Note : After ditching, one aft door will be under the water line.
CABIN CREW (PA) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . NOTIFY
EVACUATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . INITIATE
S Before leaving aircraft
BAT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF
Mod : 5948
APR 11
A7700
Mod : 5948
2.04.05
EMERGENCY PROCEDURES
P4
MISCELLANEOUS
001
APR 11
AA
AIRCRAFT ATTITUDE IN CASE OF DITCHING
Note : This illustration is given as an example. It is not necessary the LH wing which
is down.
Mod : 5948
2.04.05
EMERGENCY PROCEDURES
P5
MISCELLANEOUS
001
DEC 13
FORCED LANDING
PROCEDURE
FORCED LANDING
R
S Preparation (time permitting)
ATC (VHF1 or HF) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . NOTIFY
XPDR . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . EMERGENCY
CABIN CREW (PA) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . NOTIFY
SIGNS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON
GPWS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF
TERR . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF
CABIN and COCKPIT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . PREPARE
. Loose equipment secured
. Survival equipment prepared
. Belts and shoulder harnesses locked.
AUTO PRESS - LDG ELEVATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . SET
S Approach
HYD AUX PUMP pushbutton(pedestal) . . . . . . . . . . . . . . . . . . . . . . . . . DEPRESS
FLAPS (if available) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 30_
LDG GEAR LEVER . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . AS RQD
AUTO PRESS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . DUMP
ENG START ROTARY SELECTOR . . . . . . . . . . . . . . . . . . OFF / START ABORT
CABIN REPORT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OBTAINED
S Before impact (200 ft)
BRACE FOR IMPACT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ORDER
Note : In case of night forced landing, shutting down both engines may be
performed, at captain discretion, immediately after the impact (avoiding loss of
landing lights during flare out).
CL 1 + 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FTR THEN FUEL SO
FIRE HANDLES 1 + 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . PULL
FUEL PUMPS 1 + 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF
S After impact, when aircraft stopped
CABIN CREW (PA) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . NOTIFY
AGENTS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . DISCH
EVACUATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . INITIATE
S Before leaving aircraft
BAT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF
Mod : 5948
APR 11
Mod : 5948
2.04.05
EMERGENCY PROCEDURES
P7
MISCELLANEOUS
001
FEB 12
R EMERGENCY EVACUATION ON GROUND
PROCEDURE
EMER EVACUATION ON GROUND
R
R
AIRCRAFT / PARKING BRAKE . . . . . . . . . . . . . . . . . . . . . . . . STOP / ENGAGE
AUTO PRESS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . DUMP
ATC (VHF1) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . NOTIFY
CL 1 + 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FTR THEN FUEL SO
MIN CAB LIGHT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON
CABIN CREW (PA) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . NOTIFY
FIRE HANDLES 1 + 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . PULL
AGENTS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . DISCH AS RQD
ENG START ROTARY SELECTOR . . . . . . . . . . . . . . . . . . OFF / START ABORT
FUEL PUMPS 1 + 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF
EVACUATION (PA) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . INITIATE
F Before leaving aircraft
BAT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF
COMMENTS
Careful analysis is required to decide passenger evacuation, however useful time
should not be wasted.
Notify ATC on the nature of the emergency and state intentions. Only VHF 1 is available on
battery.
On battery, only PA is available to communicate with cabin crew.
Mod : 5948
2.04.05
EMERGENCY PROCEDURES
P8
MISCELLANEOUS
001
FEB 12
BOMB ON BOARD
PROCEDURE
BOMB ON BOARD
R
R
AUTO PRESS-- LANDING ELEVATION . . . . . . . . . . . . . . . . . . . . CABIN ALTITUDE
ALT SEL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . DESCENT TO CABIN ALTITUDE
AVOID LOAD FACTORS
HANDLE BOMB CAREFULLY - AVOID SHOCKS
PLACE BOMB NEAR SERVICE DOOR PREFERABLY IN A BAG
ATTACHED TO THE DOOR HANDLE.
SURROUND IT WITH DAMPING MATERIAL
CABIN ATTENDANT OXYGEN AND FIRE EXTINGUISHER . . . . . . . . . . . . . . .
. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MOVE FORWARD
PAX . . . . . . . . . . . . . . . . . . . . . . . . . . . MOVE FORWARD/CRASH POSITION
D When Z aircraft = Z cabin
R
APPROACH CONFIG FLAPS 15 GEAR DOWN . . . . . . . . . . . . . . . SELECTED
AUTO PRESS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . DUMP
SERVICE DOOR . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . UNLOCK
LAND ASAP
Mod : 5948
2.04.05
EMERGENCY PROCEDURES
P9
MISCELLANEOUS
001
DEC 13
SEVERE ICING
MINIMUM ICING SPEED . . . . . . . . . . . . . . . . . . . . . . . . . . . INCREASE by 10 kt
PWR MGT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MCT
CL 1 + 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 100% OVRD
PL 1 + 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . NOTCH
AP (if engaged) . . . . . . . . . . FIRMLY HOLD CONTROL WHEEL and DISENGAGE
SEVERE ICING CONDITIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ESCAPE
ATC . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . NOTIFY
Note: In case of APM messages “DEGRADED-- PERF” or “INCREASE-- SPEED”
Vmin OPS automatically increased by 10kt.
H If an unusual roll response or uncommanded roll control movement is
observed :
Push firmly on the control wheel
FLAPS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . EXTEND 15_
H If the flaps are extended, do not retract them until the airframe is clear of
ice.
H For approach, if the aircraft is not clear of ice :
GPWS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FLAP/GPWS OVRD
STEEP SLOPE APPROACH (²4.5_) . . . . . . . . . . . . . . . . . PROHIBITED
APP/LDG CONF . . . . . . . . . . . . . . . . . . . . . . . . . . MAINTAIN FLAPS 15_
APP SPEED . . . . . . . . . . . “REDUCED FLAPS 15 LDG icing speeds “ 5 kt
Multiply landing distance FLAPS 30 by 2.12
R
DETECTION
Visual cue identifying severe icing is characterized by ice covering all or a substantial
part of the unheated portion of either side window
and / or
Unexpected decrease in speed or rate of climb
and / or
The following secondary indications :
. Water splashing and streaming on the windshield
. Unusually extensive ice accreted on the airframe in areas not normally observed to
collect ice
. Accumulation of ice on the lower surface of the wing aft of the protected areas
. Accumulation of ice on propeller spinner farther aft than normally observed
The following weather conditions may be conducive to severe in-- flight icing :
. Visible rain at temperatures close to 0_C ambient air temperature (SAT)
. Droplets that splash or splatter on impact at temperatures close to 0_C ambient air
temperature (SAT)
Mod : 5948
2.04.05
EMERGENCY PROCEDURES
P 10
MISCELLANEOUS
001
APR 11
AA
COMMENTS
- Since the autopilot may mask tactile cues that indicate adverse changes in handling
characteristics, use of the autopilot is prohibited when the severe icing defined above
exists, or when unusual lateral trim requirements or autopilot trim warnings are
encountered while the airplane is in icing conditions.
- Due to the limited volume of atmosphere where icing conditions usually exists, it is
possible to exit those conditions either :
. by climbing 2000 or 3000 ft, or
. if terrain clearance allows, by descending into a layer of air temperature above
freezing, or
. by changing course based on information provided by ATC.
Mod : 5948
2.04.05
EMERGENCY PROCEDURES
P 11
001
MISCELLANEOUS
FEB 12
RECOVERY AFTER STALL OR ABNORMAL ROLL CONTROL
PROCEDURE
RECOVERY AFTER STALL OR
ABNORMAL ROLL CONTROL
R
R
R
R
R
CONTROL WHEEL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . PUSH FIRMLY
H If flaps 0_ configuration
FLAPS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15_
PWR MGT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MCT
CL 1 + 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 100% OVRD
PL 1 + 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . NOTCH
ATC . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . NOTIFY
H If flaps are extended
PWR MGT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MCT
CL 1 + 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 100% OVRD
PL 1 + 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . NOTCH
ATC . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . NOTIFY
Note: This procedure is applicable regardless the LDG GEAR position is
(DOWN or UP).
Mod : 5948
2.04.05
EMERGENCY PROCEDURES
P 12
MISCELLANEOUS
001
DEC 13
UNRELIEABLE AIRSPEED INDICATION
ALERT
In case of disagreement between both ADC, AP (if engaged) disconnects being unable to
identify the valid ADC.
To make the difference with an isolated drifting, here the three airspeed indicators are
drifting, and indicate erroneous airspeed.
PROCEDURE
UNRELIABLE AIRSPEED INDICATION
R
AP/YD/FD . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF/OFF/STBY
PITCH AND TQ . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MAINTAIN
H If at take off or GA below 1500 ft
PITCH IMMEDIATELY . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 8_
ICING / VOLCANIC ASHES CONDITIONS . . . . . . . . . . . . . . . . . . . . . . . ESCAPE
PROBE HEATING, DE-- /ANTI-- ICING . . . . . . . . . . . . . . . . . . . . . . . . CHECK ON
APM . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF
WARNING: respect STALL alarm.
Note: Use any GPS Speed information if available.
F Take off phase, at or above acceleration altitude
ALTITUDE . . . . . . . . . . . . . . . . . . . . . . . . . MAINTAIN AT LEAST 30 SECONDS
FLAPS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 0_
PITCH . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 8_
Note: Use climb table here after to adjust pitch if required.
AFTER TAKE OFF normal procedure . . . . . . . . . . . . . . . . . . . . . . . . . . . APPLY
LAND AT THE NEAREST SUITABLE AIRPORT
F Climb
TLU . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . LO SPD
PWR MGT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CLB
PL 1 + 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . NOTCH
Altitude (ft)
5000
10000
15000
20000
Normal conditions pitch
Icing conditions
pitch
7°
5°
4°
3°
6°
4°
3°
2°
.to be continued next page../...
Mod : 5948
2.04.05
EMERGENCY PROCEDURES
P 13
MISCELLANEOUS
001
FEB 12
UNRELIEABLE AIRSPEED INDICATION (cont’d)
.../...
F Cruise
ALTITUDE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MAINTAIN
TLU . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . HI SPD
Note: Average pitch in cruise is around 0°
PWR MGT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CRZ
PL 1 + 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . NOTCH
F Descent
TLU . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . HI SPD
PITCH . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MAINTAIN AT --2.5°
PL 1 + 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ADJUST 30% TQ
DESCENT normal procedure(2.03.16) . . . . . . . . . . . . . . . . . . . . . . . . . . . APPLY
F Initial approach
TLU . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . LO SPD
APPROACH normal procedure(2.03.17) . . . . . . . . . . . . . . . . . . . . . . . . . APPLY
CAUTION : Transition from clean configuration to LDG configuration is to be
performed in level flight -- REFER TO ALTIMETER -- (if possible 30 seconds between each step).
NOTE: Refer to following tables to adjust TQ:
Aircraft configuration
-- Average speed
Flaps 0° -- 180 kt
TQ (Altitude of 3000ft)
14 T
35%
18 T
45%
22 T
50%
FLAPS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15°
Flaps 15° -- 150 kt
45%
45%
50%
LDG GEAR . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . DOWN
PWR MGT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . TO
FLAPS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 30°
Flaps 30° -- 130 kt
45%
45%
50%
F Final Approach
. PL 1 + 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ADJUST 35% TQ .
BEFORE LANDING normal procedure (2.03.18) . . . . . . . . . . . . . . . . . . APPLY
NOTE: Set an average pitch of --5° for a 3° slope approach.
COMMENTS
- Drift of all the airspeed indications occurs if pitots are partially or fully obstructed.
- This obstruction may be due to the severe icing or volcanic ashes.
- NEVER REENGAGE the autopilot and/or the yaw damper. The autopilot computer uses
the airspeed data to compute the deflection of the rudder. With an erroneous airspeed, the
autopilot orders inappropriate deflections of the rudder, which can lead to severe
structural damages and lost of control of the aircraft.
- The stall alert is triggered with the angle of attack, and has to be respected
Mod : 5948
2.05.00
PROCEDURES FOLLOWING FAILURE
P1
100
CONTENTS
R
R
R
R
R
R
FEB 12
2.05.00
CONTENTS
2.05.01
INTRODUCTION
( including human factor recommendations for Electronic Check List use)
2.05.02
POWER PLANT
Procedure
Alert
SINGLE ENG
SINGLE ENG OPERATION
ENG START
START FAULT
ENG X START
X START FAIL
ABNORMAL PARAMETERS DURING START
ENG START ITT
EXCESSIVE ITT DURING START
ENG START ITT
NO ITT DURING START
ENG START NO NH
NO NH DURING START
NAC OVHT
NAC OVHT
ABNORMAL ENG PARAMETERS IN FLIGHT
FIRE LOOP 1A
FIRE LOOP 1A (1B)(2A)(2B) FAULT
(1B)(2A)(2B)
PROP BRK
ABNORMAL PROP BRK (IF APPLICABLE)
ENG RESTART IN FLIGHT
ENG EEC
ENG EEC 1+2
ENG 1(2) OUT
R
R IDLE GATE
R ENG PROP NP
ENG 1(2) PEC SG CH
ENG 1(2) PEC
ENG LO PITCH
R ENG 1(2) OVER LIMIT
ENG 1(2) PROP LIM
ENG1(2) OIL TEMP L
ENG1(2) OIL TEMP H
ENG 1(2) OIL OVHT00
ENG 1(2) OIL PRESS
ENG BOOST
Mod : 5948 + 6521
ENG STALL
ONE EEC FAULT
BOTH EEC FAULT
ENG 1(2) FLAME OUT IN FLIGHT
ENG 1(2) FLAME OUT ON GROUND
IDLE GATE FAIL
UNEXPECTED 100% NP ON ONE OR BOTH ENGINES
PEC 1(2) SGL CH
PEC 1(2) FAULT
LO PITCH IN FLIGHT
ENG 1(2) OVER LIMIT
PROP 1(2) OVER LIMIT
ENG 1(2) OIL TEMP BELOW 45_C
ENG 1(2) OIL TEMP HIGH
ENG 1(2) OIL LO PR
ENG BOOST FAULT (IF APPLICABLE)
2.05.00
PROCEDURES FOLLOWING FAILURE
P2
100
CONTENTS
2.05.03
FUEL
Alert
FUEL 1(2) TEMP LO
FUEL 1(2) TEMP HI
ENG FUEL CLOG
FUEL FEED LO PR
Procedure
FUEL 1(2) ABNORMAL TEMP
FUEL LO LVL
FUEL LO LVL
ENG EXCESS ITT
FUEL LEAK
FUEL MISMATCH
FUEL MISMATCH
FUEL UNBALANCED
FUEL UNBALANCED
2.05.04
FUEL CLOG
FEED LO PR
ELECTRICAL SYSTEM
Alert
R ELEC DC BUS 1
Procedure
DC BUS 1 OFF
R ELEC AC BUS 1
AC BUS 1 OFF
R ELEC DC BUS 2
R ELEC AC BUS 2
DC BUS 2 OFF
AC BUS 2 OFF
ELEC ACW BUS 1(2)
ACW BUS 1(2) OFF
ELEC ACW 1+2
ACW TOTAL LOSS
ELEC DC ESS
DC ESS BUS OFF
ELEC DC EMER
DC EMER BUS OFF
ELEC DC GEN
DC GEN FAULT
ELEC INV 1(2)
INV 1(2) FAULT
ELEC ACW GEN 1(2)
ACW GEN FAULT
ELEC DC SHED
DC SVCE/UTLY BUS SHED
R ELEC BAT CHG
MAIN (or EMER) BAT CHG FAULT
R ELEC CHG LOSS
EMER + MAIN BAT CHG LOSS
ELEC BAT DISCH
BAT DISCHARGE IN FLIGHT
R ELEC AC STBY BUS
AC STBY BUS FAULT
R ELEC DC STBY BUS
DC STBY BUS FAULT
ELEC STBY BUS UND/V DC STBY BUS UND/V
STBY BUS / STBY BUSSES AND BAT ONLY LOST
EQUIPMENT LISTS
Mod : 5948 + 6521
FEB 12
2.05.00
PROCEDURES FOLLOWING FAILURE
P3
CONTENTS
2.05.05
001
FEB 12
HYDRAULIC
Alert
R HYD BLUE LO LVL (HYD
GREEN LO LVL)
HYD PUMPS LOSS
HYD SYS LOSS
Procedure
HYD BLUE (GREEN) LO LVL
BOTH MAIN HYD PUMPS LOSS
BOTH HYD SYS LOSS
R HYD BLUE(GREEN) (AUX) LO HYD BLUE (GREEN) LO PR
PR
HYD BLUE (GREEN) OVHT
HYD BLUE(GREEN) (AUX)
OVHT
HYD AUX LO PR
HYD AUX OVHT
2.05.06
HYD AUX LO PR
HYD AUX OVHT
FLIGHT CONTROLS
Alert
FLAPS UNLK
Procedure
FLAPS UNLK
FLAPS JAM
FLAPS ASYM
FLAPS JAM / UNCOUPLED / ASYM
REDUCED FLAPS LANDING
FLT CTL PUSHER
STICK PUSHER / SHAKER FAULT
PITCH TRIM ASYM
PITCH TRIM ASYM
PITCH TRIM INOPERATIVE
PITCH DISC
PITCH DISCONNECT
FLT CTL RUD RCU
DUTCH ROLL TENDENCY / RUDDER RELEASABLE
CENTERING UNIT FAIL
R PITCH DISC
PITCH DISCONNECT
PITCH RECONNECTION ON GROUND
R PITCH RECONNECT
PITCH RECONNECT
FLT CTL TLU
TLU FAULT
AIL LOCK LIT
AIL LOCK LIT
ELEVATOR JAM
AILERON JAM / SPOILER JAM
RUDDER JAM
Mod : 5948
2.05.00
PROCEDURES FOLLOWING FAILURE
P4
CONTENTS
2.05.07
LANDING GEAR
Alert
Procedure
LDG GEAR GRAVITY EXTENSION
LANDING WITH ABNORMAL LDG GEAR
LDG GEAR
LDG GEAR UNSAFE INDICATION
LDG GEAR RETRACTION IMPOSSIBLE
WHEELS A-- SKID
ANTI-- SKID FAULT
WHEELS BRK HOT
BRK TEMP HOT
2.05.08
AIR
Alert
R AIR BLEED 1(2)
Procedure
BLEED VALVE 1(2) FAULT
AIR BLEED1(2) OVHT
BLEED 1(2) OVHT
AIR BLEED 1(2)
BLEED 1(2) LEAK
R AIR X VALVE
X BLEED VALVE OPEN
AIR PACK
PACK VALVE FAULT
AIR PACK 1+2
BOTH PACK VALVES FAULT
AIR RECIR FAN 1(2)
RECIRC FAN 1(2) FAULT
R AIR DUCT 1(2) OVHT
DUCT OVHT
R CAB ALT
CABIN ALTITUDE
EXCESS CAB ALT
EXCESS CAB ALT
AIR AUTO PRESS
AUTO PRESS FAULT
R CAB nP
CABIN nP
R NEGATIVE CAB nP
NEGATIVE CAB nP
EXCESS CAB nP
EXCESS CAB nP
AIR VENT EXH
AVIONICS VENT EXHAUST MODE FAULT
AIR OVBD
OVBD VALVE FAULT
Mod : 5948 + 6521
100
FEB 12
2.05.00
PROCEDURES FOLLOWING FAILURE
P5
100
CONTENTS
2.05.09
DE/ANTI ICE
Alert
R A-- ICING BLEED
Procedure
AIRFRAME AIR BLEED FAULT
A-- ICING FRAME
A-- ICING SEL
DE-- ICING AIRFRAME FAULT
DE-- ICING MODE SEL FAULT
A-- ICING AUTO
MODE SEL AUTO FAULT
A-- ICING DETECT
ICE DETECT FAULT
A-- ICING ENG 1(2)
DE-- / ANTI-- ICING ENG 1(2) FAULT
A-- ICING PROP 1(2)
ANTI-- ICING PROP 1(2) FAULT
A-- ICING HORNS 1(2)
ANTI-- ICING HORNS 1(2) FAULT
A-- ICING L WSHLD
A-- ICING R WSHLD
A-- ICING WINDOWS
SIDE WINDOW / WINDSHIELD HTG FAULT
A-- ICING PROBE
A-- ICING PIT CPT(F/O)( SBY)
A-- ICING TAT CPT(F/O)
PROBES HTG FAULT
2.05.10
AUTOPILOT
Alert
AILERON MISTRIM
Procedure
AILERON MISTRIM
or EXCESSIVE LATERAL TRIM REQUIRED
or ABNORMAL FLIGHT CHARACTERISTICS
R PITCH MISTRIM
PITCH MISTRIM
R RUDDER MISTRIM
RUDDER MISTRIM
AP PITCH TRIM
R AP YAW TRIM
2.05.11
Mod : 5948 + 6521
AP PITCH TRIM FAIL
YAW AUTOTRIM FAIL
AIRCRAFT PERFORMANCE MONITORING
Refer to 2.02.21
FEB 12
2.05.00
PROCEDURES FOLLOWING FAILURE
P6
CONTENTS
2.05.12
AVIONICS
Alert
AUDIO SEL CAPT (F/O)
Procedure
AUDIO SEL FAULT
RMS 1 + 2
AHRS
RMS 1 + 2 FAULT
ONE AHRS FAIL
AHRS 1+2
AHRS 1 + 2 LOSS
AHRS NOT ALIGN
AHRS NOT ALIGN
R ADC
ONE ADC FAIL
R ADC1+2
ADC 1 + 2 LOSS
ATT DISAGREE
ATTITUDE DISAGREE
HDG DISAGREE
HEADING DISAGREE
ALT DISAGREE
ALTITUDE DISAGREE
IAS DISAGREE
IAS DISAGREE
VHF 1+2
VHF 1 + 2 LOSS
DU(n) DISCREPANCY
DUs DISCREPANCY
DU DISCREPANCY
DUs TEMP HI
ONE DU TEMP HI
MULTI DUs T HI
SEVERAL DUs TEMP HI
FWS SGL CH
AVNX FWS SGL CH
AVNX SWITCH SGL CH
AVNX SGL SWITCH
FWS 1 + 2 LOSS
AVNX SWITCH 1+2 LOS
AVNX CPM 1
AVNX CPM 1 LOSS
AVNX CPM 2
AVNX CPM 2 LOSS
CPM 1+2
AVNX CPM 1+2 LOSS
Mod : 5948 + 6521
100
NOV 14
2.05.00
PROCEDURES FOLLOWING FAILURE
P7
100
CONTENTS
2.05.12
AVIONICS
Alert
R AVNX IOM 12
Procedure
AVNX IOM 12 LOSS
R AVNX IOM 13
R AVNX IOM 22
AVNX IOM 13 LOSS
AVNX IOM 22 LOSS
R AVNX IOM 23
AVNX IOM 23 LOSS
R AVNX IOM 12 + 13
AVNX IOM 12 + IOM 13 LOSS
R AVNX IOM 12 + 22
AVNX IOM 12 + IOM 22 LOSS
R AVNX IOM 12 + 23
AVNX IOM 12 + IOM 23 LOSS
R AVNX IOM 13 + 22
AVNX IOM 13 + IOM 22 LOSS
R AVNX IOM 13 + 23
AVNX IOM 13 + IOM 23 LOSS
R AVNX IOM 22 + 23
AVNX IOM 22 + IOM 23 LOSS
R AVNX CPM 1 + IOM 22
AVNX CPM 1 + IOM 22 LOSS
R AVNX CPM 1 + IOM 23
AVNX CPM 1 + IOM 23 LOSS
R AVNX CPM 2 + IOM 12
AVNX CPM 2 + IOM 12 LOSS
R AVNX CPM 2 + IOM 13
AVNX CPM 2 + IOM 13 LOSS
2.05.13
MISCELLANEOUS
Alert
IOM 12
R RAD-- ALT LOSS
R AIR AFT (FWD) DET FAN
DOOR EMER
DOOR LH(RH) FWD
DOOR LH(RH) AFT
DOOR FWD COMPT
Procedure
COCKPIT DOOR CONTROL PANEL FAULT (If installed)
LOSS OF RADIO ALTIMETER INFORMATION
SMK DET FANS FAULT
DOORS UNLK IN FLIGHT
COCKPIT WINDOW CRACKED
OXY
R
OXYGEN LO PR
VOLCANISH ASH ENCOUNTER
Mod : 5948 + 6521
FEB 12
2.05.00
PROCEDURES FOLLOWING FAILURE
P8
CONTENTS
2.05.14
MFC
Alert
MFC 1A
Procedure
MFC 1A FAUL
MFC 1B
MFC 2A
MFC 1B FAULT
MFC 2A FAULT
MFC 2B
MFC 2B FAULT
MFC 1A + 1B
MFC 1A+1B FAULT
MFC 1A + 2A
MFC 1A+2A FAULT
MFC 1A + 2B
MFC 1A+2B FAULT
MFC 1B + 2A
MFC 1B+2A FAULT
MFC 2A + 2B
MFC 2A+2B FAULT
MFC 1B + 2B
MFC 1B+2B FAULT
Mod : 5948
001
FEB 12
2.05.01
PROCEDURES FOLLOWING FAILURE
P1
INTRODUCTION
001
APR 11
GENERAL
The procedures following failures represent the actions applicable after a failure to ensure
adequate dafety and to ease the further conduct of the flight. They are applied according
to the “Read and Do” principle except for the memory items.
PRESENTATION
The procedures are presented in the basic check list format with an adjacent expanded
section which provides:
- indication of the particular failure, alert condition
- explanation for actions where the reason is not self evident
- additional background information
The abbreviations used are identical with the nomenclature on the cockpit panels. All
actions are printed in CAPITAL letters.
Q : a preceding black square is used to identify a pre-- condition (in bold) for given
action(s).
O : a preceding black dot is used to indicate the moment (in bold) when given action(s)
have to be applied.
TASK SHARING
For all procedures, the general task sharing stated below is applicable.
The pilot flying remains pilot flying throughout the procedure.
PF, Pilot Flying, responsible for:
- PL
- flight path and airspeed control
- aircraft configuration
- navigation
PM, Pilot Monitoring, responsible for:
- check list reading
- execution of required actions
- actions on overhead panel
- CL
- communications
The AFCS is always coupled to the PF side (CPL selection).
Mod : 5948
2.05.01
PROCEDURES FOLLOWING FAILURE
P2
INTRODUCTION
100
DEC 13
AA
PROCEDURES INITIATION
- No action will be taken (apart from depressing MW pb):
. Until flight path is stabilized.
. Under 400 ft above runway (except for propeller feathering after engine failure
during approach at reduced power if go around is considered).
- Before performing a procedure, the crew must assess the situation as a whole, taking
into consideration the failures, when fully identified, and the constraints
imposed.
ANALYSIS OF CONSEQUENCES OF A FAILURE ON THE FLIGHT
Basic airmanship calls for a management review of the remaining aircraft capabilities
under the responsability of CM1.
FWS ALERTING
( see page 3 )
ELECTRONIC CHECK- LISTS USE : HUMAN FACTOR RECOMMENDATIONS
Upon completing procedure, PNF need tick each item, i.e. meaning the item was
acknowledged and taken care of.
- Importance of procedure pending message:
Pending procedure notice need be carefully considered when displayed, therefore
meaning this one needs yet be performed and completed.
- Importance “PROCEDURE COMPLETED“ item:
Completed procedure item, is displayed at the end of each started procedure,
provided all items have been properly ticked. It is the only way to complete and
correctly terminate a started procedure.
- Importance “IF” statements:
Following each procedure’s ”IF” alternative proposition, PNF must carefully read and
understand these different alternatives to meet current depiction and get PF’s
approval and confirmation to comply with relevant ”IF” procedure.
Once an ”IF” case has been selected, PNF must carefully read and understand
relevant procedure’s proposition and it’s associated subtitle, obtain PF’s confirmation
before resuming corresponding associated task.
R - Awareness of STATUS:
R The flight crew must open and review the statuses during recall.
- DU failure:
Neither DU fault procedure exists and no relevant reference is made in FWS, FCOM
nor QRH.
Mod : 5948 + 6521
2.05.01
PROCEDURES FOLLOWING FAILURE
P3
INTRODUCTION
001
FEB 12
AA
R FWS ALERTING
When the TO inhibition signal computed by FMA is actived, all alerts are inhibed exept
(this inhibition is cancelled automatically at landing gear retraction or manually by action
on the RCL push-- button) :
WARNING
CAUTION
- ENG 1 (2) OUT
- LDG GEAR NOT DN
- CONFIG
- NAC OVHT
- PROP BREAK
- ENG 1 (2) OIL PRESS
- FLAPS UNLK
- PITCH DISC
- EXCESS CAB ∆P
- EXCESS CAB ALT
- TRIM RUNAWAY
- AP DISCONNECTION
- APCH CAPABILITY
- FD MODE REVERSION
- ALTITUDE ALERT
- PITCH TRIM ASYM
- FLT CTL TLU
- AP PITCH TRIM
- PICH MISTRIM
- AILERON MISTRIM
- RUDDER MISTRIM
- AP YAW TRIM
- ADC 1+2
- AHRS 1+2
- IRS 1+2
- ATT DISAGREE
- IAS DISAGREE
- ALT DISAGREE
- MFC 1B + 2B
- FLT CTL TLU
- ADC
- AHRS
- AHRS NOT ALIGN
- IRS
- IRS NOT ALIGN
- IRS IN ALIGN
- HDG DISAGREE
- IRS ATT ONLY
- DATA RECORDER
- CALLS
- VLE, VFE EXCEED
Mod : 5948
2.05.02
PROCEDURES FOLLOWING FAILURE
P1
001
POWER PLANT
NOV 14
AA
SINGLE ENG OPERATION
ALERT
CONDITION
Engine flame out
VISUAL
AURAL
- MC light flashing amber
- SINGLE ENG amber message
on EWD
SC
PROCEDURE
SINGLE ENG OPERATION
PWR MGT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MCT
ENG BOOST FUNCTION (if installed) . . . . . . . . . . . . . . . . . . . . . . . . . . . AS RQD
LAND ASAP
FUEL PUMP affected side . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF
DC GEN affected side . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF
ACW GEN affected side . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF
PACK affected side . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF
BLEED affected side . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF
APM . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF
TCAS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . TA ONLY
OIL PRESSURE AND NP ON FAILED ENGINE . . . . . . . . . . . . . . . . . . . MONITOR
Note: In icing conditions, FLAPS 15 will be selected to improve drift down performances
and single engine ceiling.
Note: Refer to QRH pages (4.61) and (4.62) to determine single engine gross ceiling.
Note: If during the flight, a positive oil pressure has been noted on the failed engine for
a noticeable period of time, maintenance must be informed.
Note: monitor fuel balance. Recommended operational maximum fuel unbalance is
200 kg (440 lb).
● When FUEL CROSS FEED is required
FUEL PUMP affected side . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON
FUEL X FEED . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON
FUEL PUMP on operating engine . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF
To be continued next page(...\...)
Mod : 5948
2.05.02
PROCEDURES FOLLOWING FAILURE
P2
POWER PLANT
001
DEC 13
AA
PROCEDURE
SINGLE ENG OPERATION (cont’d)
● For approach
MAX APPROACH SLOPE for Steep Slope Approach . . . . . . . . . . . . . . . . 5.5_
BLEED NOT AFFECTED . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF
CL live engine . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 100% OVRD
V APP . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . NOT LESS THAN VGA
H IF AFFECTED ENGINE NP ABOVE 10%
V APP . . . . . . . . . . . . . . . . . . . . . . . . . . . . NOT LESS THAN V REF + 10kt
D When V APP is increased
SPD TGT MAN . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . USE
LDG DISTANCE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MULTIPLY BY 1.15
Note: Refer to 4.64 to determine 1.1VMCA, and to 4.65 to determine landing
distance.
Note: ILS CAT 2 prohibited.
● At touch down
CAUTION: Do not reduce below FI before nose wheel is on the ground.
SINGLE ENG OPERATION
COMMENTS
- Refer to section Procedures and Techniques for fuel unbalance.
- For approach and landing, comply with Procedures and Techniques, Flight Patterns
sub-- section 2.02.10.
Mod : 5948
2.05.02
PROCEDURES FOLLOWING FAILURE
P3
100
POWER PLANT
FEB 12
AA
START FAULT
ALERT
CONDITION
Start sequence incident
VISUAL
AURAL
- MC light flashing amber
- ENG START amber message
on EWD + amber reverse video
START indication
- associed START FAULT amber
light on overhead panel
SC
START FAULT
ENG START ROTARY SELECTOR . . . . . . . . . . . . . . . . . . . . OFF / START ABORT
■ If above 45 % NH
START ON LIGHT . . . . . . . . . . . . . . . . . . . . . . . . . CHECK EXTINGUISHED
START . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . TO BE CONTINUED
X START FAIL
ALERT
VISUAL
CONDITION
On ground, during second
R engine start, operative DC
GEN does not come on line to
supply the START BUS
between 10 % and 45 % NH
- MC light flashing amber
- ENG X START amber
message on EWD
- X START FAIL amber light on
overhead panel
PROCEDURE
X START FAIL
R
CONTINUE NORMAL ENGINE START
MAINTENANCE ACTION IS REQUIRED
Mod : 5948 + 6521
AURAL
SC
2.05.02
PROCEDURES FOLLOWING FAILURE
P4
001
POWER PLANT
FEB 12
AA
ABNORMAL PARAMETERS DURING START
PROCEDURE
ABNORMAL PARAMETERS DURING START
■ If ITT tends to exceed 900_
_C, or no ITT, or no NH
CL affected side . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FUEL SO
ENG START ROTARY SELECTOR . . . . . . . . . . . . . . . . . OFF / START ABORT
Then refer to the relevant procedure:
■ EXCESSIVE ITT DURING START procedure (2.05.02 page 4)
■ NO ITT DURING START procedure (2.05.02 page 5)
■ NO NH DURING START procedure (2.05.02 page 5)
R
EXCESSIVE ITT DURING START
ALERT
CONDITION
VISUAL
ITT incident during start
- MC light flashing amber
- ENG START ITT amber
message on EWD
AURAL
SC
PROCEDURE
EXCESSIVE ITT DURING START
● When NH below 30 %
ENG START ROTARY SELECTOR . . . . . . . . . . . . . . . . . . . . . . . . . . . CRANK
START PB . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON
● After 15 seconds
R
ENG START ROTARY SELECTOR . . . . . . . . . . . . . . OFF / START ABORT
CAUTION: If ITT exceeds 950_C, maintenance action is required
Mod : 5948
2.05.02
PROCEDURES FOLLOWING FAILURE
P5
100
POWER PLANT
FEB 12
AA
NO ITT DURING START
ALERT
CONDITION
NO ITT during start
VISUAL
- MC light flashing amber
- ENG START ITT amber
message on EWD
AURAL
SC
PROCEDURE
NO ITT DURING START
● After 30 seconds, to allow fuel draining
ENG START ROTARY SELECTOR . . . . . . . . . . . . . . . . . . . . . . . . . . . CRANK
START PB . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON
● After 15 seconds
ENG START ROTARY SELECTOR . . . . . . . . . . . . . . OFF / START ABORT
NO NH DURING START
ALERT
CONDITION
NO NH during start
VISUAL
- MC light flashing amber
- ENG START NO NH amber
message on EWD
AURAL
SC
PROCEDURE
NO NH DURING START
Note : On BAT only, OIL PRESS IND is not available.
ENG START ROTARY SELECTOR . . . . . . . . . . . . . . . . . . . . START A or START B
START PB . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON
■ If after 10 seconds OIL pressure increases
CL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FTR
Continue START procedure, being informed NH indicator is inoperative.
■ If after 10 seconds no OIL pressure
ENG START ROTARY SELECTOR . . . . . . . . . . . . . . . . . OFF / START ABORT
Suspect starter motor failure. Maintenance action is required.
Mod : 5948 + 6521
2.05.02
PROCEDURES FOLLOWING FAILURE
P6
POWER PLANT
001
FEB 12
AA
NAC OVHT
ALERT
CONDITION
VISUAL
AURAL
Nacelle temperature exceeds
170°C (338°F) when aircraft is
on ground
- MW flashing red
- NAC OVHT red message on
EWD
CRC
PROCEDURE
NAC OVHT
■ If during hotel mode operation
PL 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . GI
CL 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FTR THEN FUEL SO
■ If during taxi
AIRCRAFT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . STOP
PL 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . SLIGHTLY INCREASE POWER
■ If NAC OVHT persist within 30 seconds
R
PARKING BREAK . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ENGAGE
PL 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . GI
CL 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FTR THEN FUEL SO
FUEL PUMP 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF
RETURN TO PARKING
R
COMMENTS
- In case of tailwind component greater than 10 kt and just after engine start, propeller
must be unfeathered rapidly to take advantage of the wind created by propeller
rotation and consequently to avoid exhaust gas return flow in the nacelle.
- When taxiing with tail wind component, use of reverse requires special care as air flow
created by propeller reversing combined with tail wind will induce an exhaust gas
return flow which may damage the nacelle. It is consequently recommended not leave
PL in reverse position for any period of time exceeding 10 seconds.
- NAC OVHT alert is inhibited when both wow systems detect aircraft airborne.
Mod : 5948
2.05.02
PROCEDURES FOLLOWING FAILURE
P7
POWER PLANT
001
FEB 12
AA
ABNORMAL ENG PARAMETERS IN FLIGHT
PROCEDURE
ABNORMAL ENG PARAMETERS IN FLIGHT
R
R
R
J If Intermittent fluctuations or unrealistic steady indication
ATPCS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF
F When adequate flight situation
PL affected side . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FI
EEC affected side . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF
J If normal engine operations recovered
ONE EEC FAULT procedure (2.05.02 page12) . . . . . . . . . . . . . . . APPLY
J If abnormal fluctuations or indications persist
- or - J If TQ = 0% and NP < 77%
PL affected side . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FI
CL affected side . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FUEL SO
LAND ASAP
SINGLE ENG OPERATIONS procedure (2.05.02 page1) . . . . . . . APPLY
J If “HBV” indication on display
AVOID SUDDEN PL MOVEMENTS
COMMENTS
- AFU provides TQ indication to the cockpit intruments. (needle).
- Untimely TQ indication drop lasting more than 2.15 seconds will induce an ATPCS
sequence if ATPCS was already armed.
- With engine at high power, a spurious ATPCS sequence would provoke an automatic
feathering and a very significant overtorque deselecting ATPCS will avoid such a
possibility.
- With no reliable TQ indication, engine power monitoring is assured on the affected
engine through NH / NP indications.
- Refer to 2.02.11 page 2.
Mod : 5948
2.05.02
PROCEDURES FOLLOWING FAILURE
P8
POWER PLANT
001
FEB 12
AA
FIRE LOOP 1A (1B) (2A) (2B) FAULT
ALERT
CONDITION
R
Fire loop fault detected
VISUAL
- MC flashing amber
- FIRE LOOP 1A (1B) (2A)
(2B) amber message on EWD
AURAL
CRC
PROCEDURE
FIRE LOOP 1A (1B) (2A) (2B) FAULT
LOOP AFFECTED . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF
Mod : 5948
2.05.02
PROCEDURES FOLLOWING FAILURE
P9
POWER PLANT
001
FEB 12
AA
ABNORMAL PROP BRK (If applicable)
ALERT
CONDITION
VISUAL
AURAL
Propeller brake not locked in
full locked or in full released
position - or-Propeller brake engaged and
GUST LOCK released - or-Propeller brake engaged and
propeller rotating
- UNLK red light on overhead panel
- MW+PROP BRK red message on EWD
- or-- with action on PROP BRK SW :
- UNLK red light on overhead panel then
after 30 seconds
- MW+PROP BRK red message on EWD
CRC
PROCEDURE
ABNORMAL PROP BRK (If applicable)
R
R
J If on ground
J If propeller rotation and FWS PROP BRK alert
- or J If UNLK light and FWS PROP BRK alert
CL 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FUEL SO
MAINTENANCE ACTION IS REQUIRED
J If FWS PROP BRK alert only
J If GUST LOCK ON
CL 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FUEL SO
J If DC and AC GPU are not available
ENG 1 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . START
CL 1 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . AUTO
F When READY light illuminates
PROP BRK . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF
UNLK LIGHT . . . . . . . . . . . . . . . . . . . . . CHECK EXTINGUISHED
PROP BRK PWR SPLY C/B . . . . . . . . . . . . . . . . . . . . . . . . . PULL
J If GUST LOCK OFF
GUST LOCK . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON
F According to operational situation
PROP BRK . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF
ALL PROP BRK LIGHTS . . . . . . . . . . . . . CHECK EXTINGUISHED
J If in flight
CONTINUE NORMAL OPERATION
ENG 2 PARAMETERS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MONITOR
F After landing
CL 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FUEL SO
MAINTENANCE ACTION IS REQUIRED
Mod : 5948
2.05.02
PROCEDURES FOLLOWING FAILURE
P 10
POWER PLANT
001
FEB 12
AA
ENG RESTART IN FLIGHT
PROCEDURE
ENG RESTART IN FLIGHT
R
R
R
R
FUEL SUPPLY . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK
CL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FUEL SO
PL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FI
CAUTION: After ATPCS sequence PWR MGT rotary selector must be set to MCTposition before engine restart in order to cancel propeller feathering.
ENG START ROTARY SELECTOR . . . . . . . . . . . . . . . . . . . . . . . . . START A & B
START PB . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON
Note : AP-- YD may disconnect during start
F When NH above 10 %
CL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FTR
RELIGHT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MONITOR
CL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . AUTO
PL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ADJUST TO OTHER ENGINE
ENG START ROTARY SELECTOR . . . . . . . . . . . . . . . . . . OFF/START ABORT
SYSTEMS AFFECTED . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . RESTORE
APM . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF
COMMENTS
- Engine relighting in flight is only guaranteed within the envelope and always
necessitate starter assistance.
- The power may be restored immediately after relighting provided OIL TEMP > 0°C.
- Should the engine fail to light up within 10 seconds, select fuel to shut off, the ignition
OFF and allow engine to be ventilated for 30 seconds minimum prior to making
another attempt.
Mod : 5948
2.05.02
PROCEDURES FOLLOWING FAILURE
P 11
POWER PLANT
001
FEB 12
AA
ENG STALL
ALERT
An engine stall may be recognized by :
- varying degrees of abnormal engine noise (rumbling bangs)
- fluctuating engine parameters
- abnormal PL response
- rapid ITT increase
PROCEDURE
ENG STALL
R
R
R
PL affected side . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FI
ENG PARAMETERS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK
J If abnormal engine parameters
CL affected side . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FTR THEN FUEL SO
LAND ASAP
SINGLE ENG OPERATION procedure (2.05.02 page 1) . . . . . . . . . . . . . APPLY
J If normal engine parameters
DE-- /ANTI-- ICING ENG . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON
PL affected side . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . SLOWLY ADVANCE
J If stall recurs
Reduce thrust and operate below the stall threshold
J If normal operations recovered
Continue normal operation
Mod : 5948
2.05.02
PROCEDURES FOLLOWING FAILURE
P 12
POWER PLANT
001
FEB 12
ONE EEC FAULT
ALERT
CONDITION
EEC failure
VISUAL
- MC light flashing amber
- ENG EEC amber MESSAGE on EWD
- associated EEC FAULT amber light on central
panel
AURAL
SC
PROCEDURE
ONE EEC FAULT
R
R
R
R
ATPCS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF
CAUTION: DO NOT DESELECT EEC FLASHING.
F When adequate flight situation
PL affected side . . . . . . . . . . . . . . . . . . . . . . . . RETARD IN GREEN SECTOR
EEC affected side . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . RESET
J If EEC recovered
ATPCS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON
PL affected side . . . . . . . . . . . . . . . . . . . . . . . . . . . . . RESTORE POWER
J If EEC fault persists
EEC affected side . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF
PL affected side . . . . . . . . . . . . . . . . . . . . . . . . . . . . . RESTORE POWER
. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . HANDLE THROTTLE WITH CARE
F In the following cases : icing conditions, engine(s) flame out,
emergency descent, severe turbulence, heavy rain
MAN IGN . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON
F In final approach
CL 1 + 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 100% OVRD
V APP . . . . . . . . . . . . . . . . . . . . . . . . NOT LESS THAN V REF + 10 kt
SPD TGT MAN . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . USE
LDG DIST . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MULTIPLY BY 1.15
Note: Refer to Part 4 to determine landing distance
Note: If engine failure during go around, do not reduce PL below
45°before feathering
F After landing
TAXI WITH THE AFFECTED ENGINE FEATHERED
Note: ACW BTC must be checked closed in order to avoid the loss of
ACW bus on ground
COMMENTS
Refer to 2.05.02 page 14.
mod : 5948
2.05.02
PROCEDURES FOLLOWING FAILURE
P 13
POWER PLANT
001
FEB 12
BOTH EEC FAULT
ALERT
CONDITION
Both EEC failure
VISUAL
- MC light flashing amber
- ENG EEC 1+2 amber message on EWD
- EEC FAULT amber light(s) on central panel
AURAL
SC
PROCEDURE
R
R
R
R
R
R
EEC 1 + 2 FAULT
ATPCS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF
CAUTION: DO NOT DESELECT EEC FLASHING.
F When adequate flight situation
PL 1 + 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . RETARD IN GREEN SECTOR
EEC 1 + 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . RESET
J If EEC 1 + 2 recovered
ATPCS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON
PL 1 + 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . RESTORE POWER
J If only one EEC recovered
ONE EEC FAULT procedure (2.05.02 page 12) . . . . . . . . . . . . . . . . . APPLY
J If EEC 1+2fault persists
EEC 1 + 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF
PL 1 + 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . RESTORE POWER,
. . . . . . . . . . . . . . . . . . . . . . . . . . . . . HANDLE THROTTLES WITH CARE
TQ IND ENG 1 + 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MONITOR
F In the following cases : icing conditions, engine(s) flame out,
emergency descent, severe turbulence, heavy rain
MAN IGN . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON
F In final approach
CL 1 + 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 100% OVRD
V APP . . . . . . . . . . . . . . . . . . . . . . . . . . . . . NOT LESS THAN V REF + 10 kt
SPD TGT MAN . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . USE
LDG DIST . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MULTIPLY BY 1.15
Note: Refer to Part 4 to determine landing distance
Note: If engine failure during go around, do not reduce PL below 45°before
feathering
F After landing
BRAKE HANDLE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . EMER AS RQD
CAUTION : Both main HYD pumps will be lost at low speed.
Note: Revers power is reduced
TAXI ON BOTH ENGINES, HANDLE THROTTLES WITH CARE
COMMENTS : Refer to 2.05.02 page 14.
Mod : 5948
2.05.02
PROCEDURES FOLLOWING FAILURE
P 14
POWER PLANT
001
APR 11
ONE EEC FAULT (CONT’D)
COMMENTS specific for ONE EEC FAULT
- When EEC fails, two cases must be considered :
High Power
Low Power
PL set forward 52_
PL set aft of 52_ in green sector
EEC FAULT light flashes, NH is
EEC FAULT comes on steady, EEC is
automatically frozen to its prior value (FAIL
automatically deselected (Automatic
FIX)
reversion)
- Feathering the engine with EEC failed for taxi and static operation will avoid prolonged
time in NP restricted band (propeller limitation).
BOTH EEC FAULT (CONT’D)
COMMENTS specific for BOTH EEC FAULT
- During reduction at touch down, both ACW GEN may be lost and therefore both main
HYD pumps.
- Both digital torque indications are lost when TQ are below 20%.
Mod 5948
2.05.02
PROCEDURES FOLLOWING FAILURE
P 15
POWER PLANT
001
FEB 12
AA
ENG 1(2) FLAME OUT IN FLIGHT
ALERT
CONDITION
Engine 1(2) flame
out
VISUAL
- MW light flashing amber
- ENG 1(2) OUT amber message on EWD
AURAL
SC
PROCEDURE
ENG 1(2) FLAME OUT IN FLIGHT
PL affected side . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FI
J If NH drops below 30% (no immediate relight)
CL affected side . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FTR THEN FUEL SO
J If damage suspected
FIRE HANDLE affected side . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . PULL
LAND ASAP
SINGLE ENG OPERATION procedure (2.05.02 page 1) . . . . . . . . . . APPLY
J If no damage suspected
ENG RESTART IN FLIGHT procedure (2.05.02 page 10) . . . . . . . . . . APPLY
J If engine out confirmed
LAND ASAP
SINGLE ENG OPERATION procedure (2.05.02 page 1) . . . . . . . APPLY
R
R
COMMENTS
- Shut down the engine if no immediate relight.
- The causes of engine flame out can generally be divided into two categories :
. External causes such as icing, very heavy turbulence, fuel mismanagement. These
causes, which may affect both engines can generally be easily determined and an
immediate relight can be attempted.
. Internal causes which as engine stalls or failures usually affect a single engine and are
not so easily determined. In these cases, the engine is shut down then the cause of the
flame out investigated. If it cannot be positively determined what caused the flame
out, the need for engine restart should be evaluated against the risk or further engine
damage or fire that may result from a restart attempt.
- If damage is suspected, as precautionary measure, the FIRE handle is pulled.
Mod 5948
2.05.02
PROCEDURES FOLLOWING FAILURE
P 16
POWER PLANT
001
FEB 12
AA
ENG 1(2) FLAME OUT ON GROUND
PROCEDURE
ENG 1(2) FLAME OUT ON GROUND
R
PL 1+ 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . GI
STOP THE AIRCRAFT
D When aircraft stopped
PARKING BRK . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ENGAGE
CL affected side . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FTR THEN FUEL SO
ENG FIRE HANDLE affected side . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . PULL
FUEL PUMP affected side . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF
RETURN TO PARKING
IDLE GATE FAIL
ALERT
Automatic idle gate system
failure
- MC light flashing amber
- IDLE GATE amber message
on EWD
- IDLE GATE FAIL amber light
on pedestal
SC
PROCEDURE
IDLE GATE FAIL
F In flight
IDLE GATE LEVER . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . PUSH
F At touch down
IDLE GATE LEVER . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . PULL
COMMENTS
- In flight, pushing idle gate lever sets the stop at FI.
- On ground, pulling the lever removes the stop and allows reduction below FI (GI and
reverse).
- One reason for IDLE GATE FAIL alert may be a problem in the WOW (Weight On Wheel)
system. Other systems may be affected. Report to maintenance.
Mod 5948
2.05.02
PROCEDURES FOLLOWING FAILURE
P 17
100
POWER PLANT
FEB 12
AA
R UNEXPECTED 100% NP ON ONE OR BOTH ENGINES
ALERT
CONDITION
VISUAL
AURAL
Unexpected 100% NP on one or - MC light flashing amber
R two engines
- ENG PROP NP amber
message on EWD
SC
PROCEDURE
UNEXPECTED 100% NP ON ONE OR BOTH ENGINES
R
CL 1 + 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 100% OVRD
PEC 1(2) SGL CH
ALERT
CONDITION
Anomaly detection on either
PEC channel
VISUAL
- MC light flashing amber
- ENG 1(2) PEC SGL CH
amber message on EWD
- SGL amber message on SD
page
PROCEDURE
PEC 1(2) SGL CH
R
DO NOT RESET PEC IN FLIGHT - NO CREW ACTION REQUIRED
ANTICIPATE A PEC FAULT AT LANDING
MAINTENANCE ACTION IS REQUIRED
COMMENTS
- In case of PEC FAULT at landing :
. do not set PLs below FI before nose wheel is on the ground
. do not use reverse on affected engine
Mod 5948 + 6521
AURAL
SC
2.05.02
PROCEDURES FOLLOWING FAILURE
P 18
POWER PLANT
001
FEB 12
AA
PEC 1(2) FAULT
ALERT
CONDITION
Anomaly detection on both PEC
channels
VISUAL
- MC light flashing amber
- ENG 1(2) PEC amber
message on EWD
- Associated FAULT light on
central panel
AURAL
SC
PROCEDURE
PEC 1(2) FAULT
R
J If below 400 ft
GO AROUND procedure (2.03.17) . . . . . . . . . . . . . . . . . . . . . . . . . . APPLY
R
F Above 400 ft or at acceleration altitude
CL affected side . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 100% OVRD
PEC affected side . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . RESET
J If PEC recovered
CL affected side . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . AUTO
J If PEC fault persists
PEC affected side . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF
AVOID sudden PL movements
F Before landing
CL 1+2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 100% OVRD
Reverse is not available on affected side.
F After landing
TAXI ON BOTH ENGINES
Note: ACW BTC must be checked closed in order to avoid the loss of ACW
bus on ground.
R
R
R
R
COMMENTS
- Expect NP blocked at 102.5% (overspeed stop)
- Do not set PLs below FI before nose wheel is on ground.
- Reverse is not available because the secondary low pitch stop retraction solenoïd is
disabled which forbids the blades to go below the low pitch protection.
- When the PEC is deenergized a NP cancel signal is sent to the EEC to cancel the EEC
NP governing mode (that controls the NP speed at 850 rpm) on ground.
- ACW may be lost if NP drops below 65.5% on the affected engine.
- CL is set to OVRD to minimize NP transient when PEC is switched OFF/RESET.
Mod 5948
2.05.02
PROCEDURES FOLLOWING FAILURE
P 19
POWER PLANT
001
FEB 12
AA
LO PITCH IN FLIGHT
ALERT
CONDITION
Low pitch detection in flight
VISUAL
- MC light flashing amber
- ENG LO PITCH amber
message on EWD
- associed amber LO PITCH
flag on EWD
AURAL
SC
PROCEDURE
LO PITCH IN FLIGHT
PL affected side . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FI
CL affected side . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FTR THEN FUEL SO
R
LAND ASAP
SINGLE ENG OPERATION procedure (2.05.02 page 1) . . . . . . . . . . . . APPLY
COMMENTS
- If a low pitch is detected, pitch increases and returns to values which do not generate
alert. If failure still persists, pitch will decrease again which causes a cycling situation.
Mod 5948
2.05.02
PROCEDURES FOLLOWING FAILURE
P 20
POWER PLANT
001
FEB 12
ENG 1(2) OVER LIMIT
ALERT
CONDITION
VISUAL
AURAL
ITT above limit in flight or on
ground except at start
or TQ in red range or NH in red
range or NL in red range
- MC light flashing amber
- ENG 1(2) OVER LIMIT
amber message on EWD
- associated ITT flag on EWD
OR any parameter in red range
(TQ, NH, NL)
SC
PROCEDURE
ENG 1(2) OVER LIMIT
PL affected side . . . . . . . . . . . . . . . . . . RETARD TO RESTORE NORMAL VALUES
R
R
J If TQ, NH, and/or ITT still over limit and if conditions permit
PL affected side . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FI
CL affected side . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FTR THEN FUEL SO
LAND ASAP
SINGLE ENG OPERATION procedure (2.05.02 page 1) . . . . . . . . . . . . . APPLY
J If All (TQ, NH, and/or ITT) below limit or if conditions do not permit
Note: BLEED VALVE may be selected OFF in order to reduce ITT on the affected
engine.
COMMENTS
- Red limits must not be deliberately exceeded.
- Check indication to determine limit exceedance and proceed accordingly.
- Over limit conditions and primary engine(s) parameters must be recorded for
maintenance purposes.
- If conditions do not permit engine shut down, land as soon as possible using the
minimum power required to sustain safe flight.
Mod 5948
2.05.02
PROCEDURES FOLLOWING FAILURE
P 21
POWER PLANT
001
FEB 12
AA
PROP 1(2) OVER LIMIT
ALERT
CONDITION
Propoller speed in red range
VISUAL
AURAL
- MC light flashing amber
- ENG 1(2) PROP LIM amber
message on EWD
SC
PROCEDURE
PROP 1(2) OVER LIMIT
R
R
PL affected side . . . . . . . . . . . . . . . . . . . . . . . RETARD TO SET NP BELOW 106%
PEC affected side . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . RESET
PL affected side . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . AS RQD
Note: 106% allowed to complete a flight without overshooting 73% TQ in CRZ and
75 % in CLB.
J If NP decreases below 106%
CONTINUE NORMAL FLIGHT
J If NP remains above 106% and conditions permit
PL affected side . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FI
CL affected side . . . . . . . . . . . . . . . . . . . . . . . . . . . . FTR THEN FUEL SO
LAND ASAP
SINGLE ENG OPERATION procedure (2.05.02 page 1) . . . . . . . . . . APPLY
COMMENTS
- Red limits must not be deliberately exceeded.
- Transients in amber sector are normal during engine acceleration.
- Check indication to determine limit exceedance and proceed accordingly.
- Over limit conditions and primary engine(s) parameters must be recorded for
maintenance purposes.
- If conditions do not permit engine shut down, land as soon as possible using the
minimum power required to sustain safe flight. Nevertheless NP 106% is allowed to
complete a flight
Mod 5948
2.05.02
PROCEDURES FOLLOWING FAILURE
P 22
POWER PLANT
001
FEB 12
AA
ENG 1(2) OIL TEMP BELOW 45_
_C
ALERT
VISUAL
CONDITION
Engine oil temp below 45_C
- MC light flashing amber
- ENG 1(2) OIL TEMP L
amber message on EWD
AURAL
SC
PROCEDURE
ENG 1(2) OIL TEMP BELOW 45_
_C
R
R
J If icing conditions are expected or present
ENG POWER . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . If possible, INCREASE
J If no icing conditions
NO CREW ACTION REQUIRED
Mod 5948
2.05.02
PROCEDURES FOLLOWING FAILURE
P 23
POWER PLANT
001
FEB 12
AA
ENG 1(2) OIL TEMP OVHT
ENG 1(2) OIL TEMP HIGH
ALERT
CONDITION
VISUAL
AURAL
Engine oil temp between
125_C and 140_C
- MC light flashing amber
- ENG 1(2) OIL TEMP H amber
message on EWD
SC
Engine oil temp above
140_C
- MW light flashing red
- ENG 1(2) OIL OVHT amber
message on EWD
SC
PROCEDURE
ENG 1(2) OIL TEMP HIGH
R
J If OIL TEMP between 125_
_C and 140_
_C
OIL TEMP AND PRESS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MONITOR
Note : If OIL temperature rise follows PL reduction, advancing PL may reduce OIL
temperature .
Note : If OIL temperature rise occurs in steady state conditions, a power reduction
should permit a reduction in OIL temperature.
J If OIL TEMP between 125_
_C and 140_
_C for more than 20 minutes
PL affected side . . . . . . . . . . RETARD TO SET MINIMUM POSSIBLE POWER
CAUTION : Flight time must be minimized to reduce engine operating time in these
abnormal conditions.
J If OIL TEMP above 140_
_C
PL affected side . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FI
CL affected side . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FTR THEN FUEL SO
LAND ASAP
SINGLE ENG OPERATION procedure (2.05.02 page 1) . . . . . . . . . . . . . APPLY
COMMENTS
- Normal steady oil temperature is in the range 71/99_C.
- Increased power setting may reduce the OIL TEMP due to the increase of fuel flow
across the fuel/oil heat exchanger.
- If an OIL TEMP rise occurs in steady state condition a failure of the oil cooler flap may be
suspected, if no other engine malfunction is noted. In this case reducing power may
limit temperature excursion.
Mod 5948
2.05.02
PROCEDURES FOLLOWING FAILURE
P 24
POWER PLANT
001
FEB 12
AA
ENG 1(2) OIL LO PR
ALERT
CONDITION
Oil pressure drops below 40
PSI
VISUAL
- MW light flashing red
- ENG 1(2) OIL PRESS red
message on EWD
- LO PR flag in MFD system page
AURAL
CRC
PROCEDURE
ENG 1(2) OIL LO PR
R
PL affected side . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FI
J If ENG OIL PRESS in red range and LO PR flag
CL affected side . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FTR THEN FUEL SO
LAND ASAP
SINGLE ENG OPERATION procedure (2.05.02 page 1) . . . . . . . . . . . . . APPLY
J If ENG OIL PRESS in red range and no LO PR flag
CL affected side . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FTR THEN FUEL SO
J If LO PR flag
ENG RESTART IN FLIGHT procedure (2.05.02 page 10) . . . . . . . . . . APPLY
J If LO PR flag still missing.
LAND ASAP
SINGLE ENG OPERATION procedure (2.05.02 page 1) . . . . . . . . . . APPLY
J If ENG OIL PRESS in normal range and LO PR flag
DISREGARD
MAINTENANCE ACTION IS REQUIRED
COMMENTS
Refer to 2.05.02 page 26.
Mod 5948
2.05.02
PROCEDURES FOLLOWING FAILURE
P 25
POWER PLANT
001
FEB 12
AA
ENG OIL LO PR (CONT’D)
COMMENTS
R
- Engine oil low pressure is identified thanks to two low pressure detectors:
- the first one driving LO PR red flag on engine secondary page MFD.
- the second one is the source of oil pressure indication on engine secondary page MFD.
Low pressure condition from any of these two detectors will trigger FWS alert
(MW+CRC+ENG 1(2) OIL on EWD)
- If LO PR flag only is activated, alert must be disregarded, oil press local alert indication
press indication (in red range) must be constantly monitored during flight.
- If Local alert only is activated (press indication in red range) provided LO PR flag on
MFD is checked operative, twin engine operation should be resumed.
- NP > 10% after a shut off procedure may indicate an incomplete feathering. In this case,
the approach speed is increased to compensate the extra drag of the incompletely
feathered propeller.
Mod 5948
2.05.02
PROCEDURES FOLLOWING FAILURE
P 26
POWER PLANT
100
NOV 14
AA
ENG BOOST FAULT
ALERT
CONDITION
Rating disagreement
between EEC’s and ENG
BOOST FUNCTION
VISUAL
AURAL
- MC light flashing amber
- ENG BOOST amber message on
EWD
- FAULT amber light on BOOST
SUPERBOOST or both
SC
PROCEDURE
ENG BOOST FUNCTION FAULT
J ON GROUND
PL 1 + 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . GI
J If ON light illuminated
BOOST Function . . . . . . . . . . . . . . . . . . . . . . . . . CONFIRM TO ON LIGHT
Consider Rating with ON light for performance computation
Inform maintenance
J If ON light extinguished
BOOST Function . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF
Consider basic Rating for performance computation
Inform maintenance
J IN FLIGHT
J If ON light illuminated
BOOST Function . . . . . . . . . . . . . . . . . . . . . . . . CONFIRM TO ON LIGHT
Consider Rating with ON light for performance computation
Inform maintenance
J If ON light extinguished
BOOST Function . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF
Consider basic Rating for performance computation
Inform maintenance
COMMENTS
- ENG BOOST FUNCTION FAULT illuminate whenever an engine rating is not in
accordance with ENG BOOST FUNCTION TOOGLE SWITCH position.
- ENG BOOST FUNCTION rating is only available when ON light is illuminated
- If one EEC Off, ENG BOOST FUNCTION ON operations remain available, and ENG
BOOST FONCTION FAULT lights will be illuminated.
Mod : 5948 + (5908 or 7079)
2.05.03
PROCEDURES FOLLOWING FAILURE
P1
FUEL
001
FEB 12
AA
FUEL 1(2) ABNORMAL TEMP
ALERT
VISUAL
CONDITION
Fuel temp is greater than
50_C with engine running
AURAL
- MC light flashing amber
- FUEL 1(2) TEMP HI amber
message on EWD
SC
Fuel temp is lower than 0_C - MC light flashing amber
with engine running
- FUEL 1(2) TEMP LO amber
message on EWD
SC
PROCEDURE
FUEL 1(2) ABNORMAL TEMP
R
J If too high (>50_
_C)
Note : AVOID rapid throttle movement.
OIL TEMP AND ENGINES PARAMETERS . . . . . . . . . . . . . . . . . . . MONITOR
J If too low (<0_
_C)
Note : If repair can’t be done, use anti-- icing additive for next refueling
COMMENTS
- Fuel is heated through a FUEL/OIL heat exchanger. Increasing fuel flow may reduce fuel
temperature.
- Rapide throttle movement with high temperature fuel may cause surge or flame out.
- In case of too low temperature, anti icing additive is needed to prevent ice formation in
the fuel supply system. Record it in the maintenance book.
Mod 5948
2.05.03
PROCEDURES FOLLOWING FAILURE
P2
FUEL
001
FEB 12
AA
FUEL CLOG
ALERT
CONDITION
Pressure of the switch fuel
pump outlet filter is greater
than 25 PSI.
VISUAL
AURAL
- MC light flashing amber
- ENG FUEL CLOG amber message
on EWD
- CLOG flag on MFD system page
SC
PROCEDURE
FUEL CLOG
R
R
J If FUEL CLOG engines 1 + 2
ENGINES PARAMETERS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MONITOR
J If abnormal engines parameters
LAND ASAP
MAINTENANCE ACTION IS REQUIRED
J If FUEL CLOG one engine only
ENGINE PARAMETERS affected side . . . . . . . . . . . . . . . . . . . . . . . MONITOR
Mod 5948
2.05.03
PROCEDURES FOLLOWING FAILURE
P3
FUEL
001
FEB 12
AA
R FUEL FEED LO PR
ALERT
CONDITION
Engine feed low pressure
VISUAL
- MC light flashing amber
- FUEL FEED LO PR amber
message on EWD
- FEED LO PR amber light on
overhead panel.
AURAL
SC
PROCEDURE
R
R
R
FUEL FEED LO PR
PUMP affected side . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CONFIRM ON
ENGINE affected side . . . . . . . . . . . . . . MONITOR FOR POSSIBLE RUN DOWN
J If engine runs down or if fuel quantity decreases significantly
PL affected side . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FI
CL affected side . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FTR THEN FUEL SO
FUEL PUMP affected side . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF
FIRE HANDLE affected side . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . PULL
LAND ASAP
SINGLE ENG OPERATION procedure (2.05.02 page 1) . . . . . . . . . . . . . APPLY
CAUTION : Do not open X FEED valve.
COMMENTS
- The illumination of FEED LO PR light associated with PUMP RUN light identifies a
LEAK in the fuel line which may lead to engine rundown.
- If engine runs down or if fuel quantity decreases significantly, affected line must be
isolated by selecting the pump OFF and by closing the fuel shut-- off valve.
- If PUMP RUN does not illuminate, pump system may be defective and a X FEED
attempt may be performed in order to restore engine supply. Max fuel unbalance has to
be considered.
Mod : 5948
2.05.03
PROCEDURES FOLLOWING FAILURE
P4
FUEL
001
FEB 12
AA
FUEL LO LVL
ALERT
CONDITION
Fuel quantity indication
below 160 kg / 352 lb
- or Feeder tank not full
VISUAL
AURAL
- MC light flashing amber
- FUEL LO LVL amber message on
EWD
- Feeder tank in amber with fuel
quantity in amber on MFD (level
between 160kg and 50kg) or in
red reverse video (level below
50kg)
SC
PROCEDURE
FUEL LO LVL
R
R
AVOID EXCESSIVE AIRCRAFT ATTITUDES
J If Fuel low level both tanks
LAND ASAP
J If Fuel low level one tank only
J If leak suspected
FUEL LEAK procedure (2.05.03 page 5) . . . . . . . . . . . . . . . . . . . . . . APPLY
J If no leak suspected
J If fuel tank quantity < 160 kg / 352 lb
FUEL X FEED . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON
J If fuel tank quantityI ≥ 160 kg / 352 lb,
FUEL COMSUMPTION . . . . . . . . . . . . . . . . . . . . . . . . . . . . MONITOR
FUEL X FEED is not necessary
Note: Feeder jet pump malfunction is suspected
COMMENTS
- After fuel pump is selected ON, feeder tank is full within 10 minutes.
- The LO LVL alert for each side will be triggered by :
. the fuel remaining indicated on FQI, when it is less than 160 kg / 352 lb.
. the secondary low level detection system, when feeder tank is not completely full.
- In case of feeder jet pump malfunction, fuel quantity unusable in each fuel tank is raised
from 20 kg / 44 lb to 130 kg / 287 lb.
Mod 5948
2.05.03
PROCEDURES FOLLOWING FAILURE
P5
001
FUEL
FEB 12
AA
FUEL LEAK
ALERT
CONDITION
A fuel leak may be detected by either :
- sum of fuel on board (FOB), read in steady flight at cruise level,
and fuel used (FU), FOB+FU significantly less than fuel at departure, or
- passenger observation (fuel spray from engine or wing tip), or
- total fuel quantity decreasing at an abnormal rate, or
- fuel imbalance, or
- a tank emptying too fast (leak from engine or a hole in a tank), or
- excessive fuel flow (leak from engine), or
- fuel smell in the cabin
VISUAL AURAL
NIL
NIL
PROCEDURE
FUEL LEAK
F When a leak is confirmed
LAND ASAP
R
R
Mod 5948
J If leak from engine (excessive fuel flow or feed spray from engine)
PL affected side . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FI
CL affected side . . . . . . . . . . . . . . . . . . . . . . . . . . . . FTR THEN FUEL SO
FUEL PUMP affected side . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF
FIRE HANDLE affected side . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . PULL
SINGLE ENG OPERATION procedure (2.05.02 page 1) . . . . . . . . . . APPLY
J If excessive fuel flow was identified before engine shutdown
FUEL X FEED valve can be opened
J In all other cases, FUEL X FEED valve must remain closed
J If leak not located
FUEL X FEED . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MAINTAIN CLOSED
Note : The FUEL X feed must remain closed to prevent the leak affecting both
sides.
F Before landing
ATC . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . NOTIFY
2.05.03
PROCEDURES FOLLOWING FAILURE
P6
FUEL
001
FEB 12
AA
FUEL MISMATCH
ALERT
CONDITION
the difference between fuel
quantity computed by FMS
and the fuel quantities
processed by the FCU is
greater than 200kg during
more than 10s (on ground)
or 60s (in flight).
VISUAL
- MC light flashing amber
- FUEL MISMATCH amber message
on EWD
AURAL
SC
PROCEDURE
FUEL MISMATCH
R
R
R
J If leak suspected
FUEL LEAK procedure (2.05.03 page 5) . . . . . . . . . . . . . . . . . . . . . . . . APPLY
J If normal fuel condition
FOB . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . UPDATE IN CRZ PITCH RANGE
Note : CRZ PITCH RANGE : 3_DN ; 5 _UP
Mod 5848
2.05.03
PROCEDURES FOLLOWING FAILURE
P7
FUEL
001
FEB 12
AA
FUEL UNBALANCED
ALERT
CONDITION
discrepancy greater than
100 Kg between the left
and right tanks fuel
quantities.
VISUAL
- MC light flashing amber
- FUEL UNBALANCED amber
message on EWD
AURAL
SC
PROCEDURE
FUEL UNBALANCED
R
R
R
R
J If FUEL LEAK suspected
FUEL LEAK procedure (2.05.03 page 5) . . . . . . . . . . . . . . . . . . . . . . . . APPLY
J If normal fuel condition
JIf LEFT TANK QTY > RIGHT TANK QTY
FUEL X FEED . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON
FUEL PUMP LEFT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON
FUEL PUMP RIGHT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF
JIf LEFT TANK QTY < RIGHT TANK QTY
FUEL X FEED . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON
FUEL PUMP RIGHT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON
FUEL PUMP LEFT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF
R
Mod : 5848
F When fuel balanced
RESUME NORMAL FUEL OPERATIONS
2.05.04
PROCEDURES FOLLOWING FAILURE
P1
ELECTRICAL SYSTEM
DC BUS 1 OFF
ALERT
CONDITION
DC BUS 1 not
R supplied (short
circuit
R protection)
VISUAL
- MC light flashing amber
- ELEC DC BUS 1 amber message and ELEC DC
GEN amber message on EWD
- DC GEN 1 FAULT, DC BUS 1 OFF, AC BUS 1 OFF, INV
1 FAULT and DC SVCE/UTLY BUS SHED amber
lights on overhead panel
- DC GEN 1 FAULT, DC BUS (1) OFF, DC BUS 1 OFF,
INV 1 FAULT and DC SVCE/UTLY BUS SHED amber
message on AC/DC SD page
100
FEB 12
AURAL
SC
PROCEDURE
DC BUS 1 OFF
R
DC GEN 1 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF
AUTO PRESS FAULT procedure . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . APPLY
DC SVCE AND UTLY BUS SHED . . . . . . . . . . . . . . . . . . . . . . . . . MAINTAIN ON
ADC CAPT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MONITOR IAS / BARO ALT
Affected equipment fault Procedure . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . APPLY
DC BUS 1 EQUIPMENT LIST . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK
F At touch down
IDLE GATE LEVER . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . PULL
DC BUS 1 LOST EQUIPMENT LIST
Flight controls
- CAPT STICK SHAKER & PUSHER
Indicating/recording
- DU1 & DU3
Engines
- IDLE GATE (AUTO mode)
- ENG 1 oil press / temp
Navigation and Communications
- Weather Radar
- TAWS advisory
- DME
Note : if two DME are installed, DME remains
operational
* - HF 1
*-- SELCAL
*-- OBSVR AUDIO SYS
Mod 5948 + 6521
Ice & rain protection
- CAPT STATIC PROBES
- STBY STATIC PROBES
- CAPT SIDE WINDOW
Air
- ENG1 & 2 - BLEED LEAK CAUTION
- DUCT/COMPT Cockpit and cabin
temperature indication
- Automatic Pressure CTL
- RECIRC FAN 1
Lights
- CABIN - LAT LT (LEFT)
- CAPT NORM LT (DOME, MIP, CHARTHOLDER,
STORM)
- ANN LT TEST
- LMU - PED & LT
Information systems
*-- EFB1 PWR
(*) if installed
2.05.04
PROCEDURES FOLLOWING FAILURE
P 1A
100
ELECTRICAL SYSTEM
FEB 12
DC BUS 1 OFF (CONT’D)
For more information on BUS EQUIPMENT LISTS see 1.06.60
COMMENTS
- DC SVCE/UTLY BUS pushbutton may be maintained ON with SHED illuminated in order to
keep DC UTLY BUS 2 on line.
- Stick pusher is lost.
AC BUS 1 OFF
ALERT
CONDITION
AC BUS not
R supplied (short
circuit protection)
VISUAL
AURAL
- MC light flashing amber
- ELEC AC BUS 1 amber message on EWD
- associated INV FAULT and BUS OFF
amber lights on overhead panel
- associated INV FAULT and BUS OFF
amber message on AC/DC SD page
SC
R PROCEDURE
AC BUS 1 OFF
Note : Wait for 10 seconds in order to confirm the failure.
DC BTC . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ISOL THEN ON
J IF AC BUS 1 OFF persists
AC BUS 1 EQUIPMENT LIST . . . . . . . . . . . . . . . . . . . . CHECK
AC BUS 1 LOST EQUIPMENT LIST
115 AC BUS 1
26 AC BUS 1
- RAD ALT / GPWS / TCAS
- ENG 1 & 2-- BLEED LEAK
DETECTION
For more information on BUS EQUIPMENT LISTS see 1.06.60
Mod 5948 + 6521
2.05.04
PROCEDURES FOLLOWING FAILURE
P2
100
ELECTRICAL SYSTEM
AA
FEB 12
DC BUS 2 OFF
ALERT
CONDITION
VISUAL
DC BUS 2 not
R supplied (short
circuit protection)
AURAL
- MC light flashing amber
- ELEC DC BUS 2 amber message and
ELEC DC GEN amber message on EWD
- DC GEN 2 FAULT, DC BUS 2 OFF, AC
BUS 2 OFF, INV 2 FAULT and DC
SVCE/UTLY BUS SHED amber lights on
overhead panel
- DC GEN 2 FAULT, DC BUS 2 OFF, AC
BUS 2 OFF, INV 2 FAULT and DC
SVCE/UTLY BUS SHED amber message
on AC/DC SD page
SC
PROCEDURE
DC BUS 2 OFF
R
DC GEN 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF
PF . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CAPT
F/O SWITCHING ADC . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . SWITCH TO SYS 1
ICP F/O LOST . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . USE ICP CAPT
VHF 1 / XPDR 1 / VOR-- ILS 1 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . SELECT
TLU . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . HI or LO SPD ACCORDING TO IAS
PAX INSTRUCTION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . USE PA
DC SVCE / UTLY BUS PB . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MAINTAIN ON
DC BUS 2 EQUIPMENT LIST . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK
Affected equipment fault Procedure . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . APPLY
Note: ILS CAT 2 IS PROHIBITED
FAfter touch down
TAXI ON BOTH ENGINES
FAt Parking
Connect GPU before CL1 set to FUEL SO
R
DC BUS 2 LOST EQUIPMENT LIST
Flight controls
- F/O STICK SHAKER
- TLU auto mode
Indicating/recording
- F/O MCDU
- DU5
Ice & rain protection
- F/O STATIC PROBES
- F/O WIPER
- F/O SIDE WINDOW
Hydraulic
- AUX HYD PUMP auto mode
To be continued next page ...\...
Mod 5948 + 6521
2.05.04
PROCEDURES FOLLOWING FAILURE
P 2A
001
ELECTRICAL SYSTEM
FEB 12
DC BUS 2 OFF (CONT’D)
R
DC BUS 2 LOST EQUIPMENT LIST(CONT’D)
Engines
- IDLE GATE CAUTION
Air
- RECIRC FAN 2
Landing gear
- Secondary indication
Navigation and Communications
- ICP F/O
- VOR-- ILS 2 ( CAT II capability lost)
*-- ACARS
- VHF 2
- ( TAWS & TCAS)
- XPDR 2
- ADC 2
* - GPS 2
*-- DOOR VIDEO
Lights
- TAXI and TO
- WING
- FLT COMPT - OVHD
- LMU
- F/O NORM LT (UTILITY SPOT &
FLOOD, CHARTHOLDER)
- (NO DVCE) & SEAT BELTS
Doors
- DOORS AFT LH & RH Monitoring
- CDLS SPLY
Information systems
*-- EFB2 PWR
(*) if installed
For more information on BUS EQUIPMENT LISTS see 1.06.60
COMMENTS
- CM1 is pilot flying due to complete loss of CM2 panel.
Mod 5948
2.05.04
PROCEDURES FOLLOWING FAILURE
P3
ELECTRICAL SYSTEM
100
FEB 12
AA
R AC BUS 2 OFF
ALERT
VISUAL
CONDITION
AC BUS not
R supplied (short
circuit protection)
AURAL
- MC light flashing amber
- ELEC AC BUS 2 amber message on EWD
- associated INV FAULT and BUS OFF
amber lights on overhead panel
- associated INV FAULT and BUS OFF
amber message on AC/DC SD page
SC
PROCEDURE
R
R
AC BUS 2 OFF
Note : Wait for 10 seconds in order to confirm the failure.
DC BTC . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ISOL THEN ON
J If AC BUS 2 OFF persists
CABIN TEMP SEL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MAN
AC BUS 2 EQUIPMENT LIST . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK
AC BUS 2 LOST EQUIPMENT LIST
R
R
115 AC BUS 2
26 AC BUS 2
- CABIN TEMPERATURE SENSOR FAN
- * RAD ALT 2
- PRINTER
(*) If installed
For more information on BUS EQUIPMENT LISTS see FCOM 1.06.60
COMMENTS
- The DC BTC pushbutton controls also the AC BTR. The reset of this pushbutton may
help to recover the affected AC BUS.
- In case of inverter failure, the AC BUS OFF light illuminates during 10 seconds through
the BTR temporizing, then extinguishes. The AC BUS is then available. An AC BUS
failure is effective as soon as the light stays on after 10 seconds.
Mod 5948 + 6521
2.05.04
PROCEDURES FOLLOWING FAILURE
P4
ELECTRICAL SYSTEM
ACW BUS 1 OFF / ACW BUS 2 OFF
ALERT
CONDITION
ACW BUS not
R supplied (short
circuit protection)
VISUAL
- MC light flashing amber
- ELEC ACW BUS 1(2) amber message on
EWD
- associated ACW GEN FAULT and ACW
BUS OFF amber lights on overhead panel
- associated ACW GEN FAULT and ACW
BUS OFF amber message on HYD/ACW
SD page.
100
FEB 12
AURAL
SC
PROCEDURE
R
ACW BUS 1 (2) OFF
LEAVE AND AVOID ICING CONDITIONS
AS LONG AS ICING CONDITIONS EXIST
ICE ACCRETION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MONITOR IEP
ACW GEN affected side . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF
J If ACW BUS 1 OFF
CAPT SWITCHING ADC . . . . . . . . . . . . . . . . . . . . . . . . SWITCH TO SYS 2
HYD X FEED . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON
J If Icing condition
ANTI ICING PROP 1(2) FAULT procedure(2.05.09) . . . . . . . . . . . APPLY
ANTI ICING HORNS 1(2) FAULT procedure(2.05.09) . . . . . . . . . . APPLY
ACW BUS 1 LOST EQUIPMENT LIST . . . . . . . . . . . . . . . . . . . . CHECK
PERIODICALLY COMPARE IAS & ALT TO IESI
Affected equipment fault Procedure . . . . . . . . . . . . . . . . . . . . . . . . . . APPLY
ACW BUS 1 LOST EQUIPMENT LIST . . . . . . . . . . . . . . . . . . . . . . . . CHECK
J If ACW BUS 2 OFF
F/O SWITCHING ADC . . . . . . . . . . . . . . . . . . . . . . . . . SWITCH TO SYS 1
HYD X FEED . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON
PERIODICALLY COMPARE IAS & ALT TO IESI
J If Icing condition
ANTI ICING PROP 1(2) FAULT procedure(2.05.09) . . . . . . . . . . . APPLY
ANTI ICING HORNS 1(2) FAULT procedure(2.05.09) . . . . . . . . . . APPLY
ACW BUS 1 LOST EQUIPMENT LIST . . . . . . . . . . . . . . . . . . CHECK
PERIODICALLY COMPARE IAS & ALT TO IESI
Affected equipment fault Procedure . . . . . . . . . . . . . . . . . . . . . . . . . . APPLY
ACW BUS 1 LOST EQUIPMENT LIST . . . . . . . . . . . . . . . . . . . . . . CHECK
J If IAS discrepancy occurs
UNRELIABLE AIRSPEED INDICATION procedure (2.05.12) . . . . . . . APPLY
F After touch down
TAXI ON BOTH ENGINES
Mod 5948 + 6521
2.05.04
PROCEDURES FOLLOWING FAILURE
P5
ELECTRICAL SYSTEM
001
FEB 12
+
ACW BUS 1 OFF / ACW BUS 2 OFF
ACW BUS 1 LOST EQUIPMENT LIST
Ice & rain protection
- PROBES HTG - CAPT PITOT
- PROBES HTG - CAPT ALPHA
R - PROBES HTG - CAPT TAT
R - ANTI-- ICING PROP 1
- L WINDSHIELD HTG
- ANTI-- ICING RUD & L ELEV HORNS
Hydraulic
R - MAIN BLUE PUMP
Lights
- L LANDING LIGHT
- L AND REAR STROBES
- FLT COMP - OVHD ( integrated inst &
panel)
ACW BUS 2 LOST EQUIPMENT LIST
Ice & rain protection
- ICE DETECTOR
R - PROBES HTG - F/O PITOT
- PROBES HTG - F/O ALPHA
- PROBES HTG - F/O TAT
- ANTI-- ICING PROP 2
- R WINDSHIELD HTG
- ANTI-- ICING AIL & R ELEV HORNS
Hydraulic
- GREEN PUMP
Electrical power
- TRU (not available)
Lights
- TAXI AND TO LIGHTS
- R LANDING LIGHT
- RIGHT STROBE
For more information on BUS EQUIPMENT LISTS see FCOM 1.06.60
COMMENTS
- Monitor airspeed on non affected side due to loss of affected side pitot heating.
Mod 5948
2.05.04
PROCEDURES FOLLOWING FAILURE
P6
ELECTRICAL SYSTEM
001
FEB 12
AA
ACW TOTAL LOSS
ALERT
CONDITION
ACW total loss
VISUAL
- MC light flashing amber
- ELEC ACW 1+2 amber message on EWD
- both ACW GEN FAULT and ACW BUS
OFF amber message on HYD/ACW SD
page
AURAL
SC
PROCEDURE
R
ACW TOTAL LOSS
LEAVE AND AVOID ICING CONDITIONS
AS LONG AS ICING CONDITIONS EXIST
ICE ACCRETION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MONITOR IEP
ACW GEN 1 + 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF
HYD X FEED . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK OFF
PERIODICALLY COMPARE IAS & ALT on PFDs WITH IESI
Note : IESI probes are de-- iced by AC STBY BUS. IESI becomes the
reference instrument.
ACW TOTAL LOSS EQUIPMENT LIST . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK
Affected equipment fault Procedure . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . APPLY
HYD MAIN PUMPS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF
LDG GEAR NORMAL OPERATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . LOST
NORMAL BRAKE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . LOST
LDG DIST . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MULTIPLY BY 1.5
Note : Refer to Part 4 to determine LDG DIST
F Before landing
LDG GEAR LEVER . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . DOWN
HYD BLUE PRESSURE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK
FLAPS 15_ . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . AS RQD
LDG GEAR GRAVITY EXTENSION procedure (2.05.07 page 1) . . . . . . . APPLY
FLAPS 30_ . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . AS RQD
F After touch down
REVERSE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . AS RQD
BRAKE HANDLE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . EMER AS RQD
TAXI ON BOTH ENGINES
Mod 5948
2.05.04
PROCEDURES FOLLOWING FAILURE
P7
ELECTRICAL SYSTEM
001
FEB 12
AA
ACW TOTAL LOSS
R
ACW TOTAL LOST EQUIPMENT LIST
Ice & rain protection
- ICE DETECTOR
- PROBES HTG - CAPT and F/O PITOT
- PROBES HTG - CAPT and F/O
R
ALPHA
- PROBES HTG - CAPT and F/O TAT
- L and R WINDSHIELD HTG
- ANTI-- ICING (all) HORNS
- ANTI-- ICING PROP 1 + 2
Hydraulic
R - MAIN BLUE & GREEN PUMP
Electrical power
- TRU (not available)
Lights
- TAXI AND TO LIGHTS
- LANDING (all)
- STROBES(all)
- FLT COMP - OVHD(integrated inst &
panel)
For more information on BUS EQUIPMENT LISTS see FCOM 1.06.60
COMMENTS
- IESI speed tape will be used as a reference as both sides pitot heating is lost.
- The HYD DC AUX PUMP allows flaps extension, maintains the nosewheel steering
and powers the emergency brake accumulator.
- If a go around has to be performed :
. landing gear will not retract
. flaps will retract with a lower speed than normal normal due to DC AUX PUMP size.
- Landing distance is multiplied by 1.5 due to loss of normal braking.
Mod 5948
2.05.04
PROCEDURES FOLLOWING FAILURE
P8
ELECTRICAL SYSTEM
001
FEB 12
AA
DC ESS BUS OFF
ALERT
CONDITION
DC ESS BUT not
supplied
VISUAL
- MC light flashing amber
- ELEC DC ESS amber message on EWD
- DC ESS OFF message on AC/DC SD
page
AURAL
SC
PROCEDURE
R
DC ESS BUS OFF
LEAVE AND AVOID ICING CONDITIONS
HYD GREEN PUMP . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF
HYD X FEED . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON
TRU . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON
J If DC ESS BUS recovered
CAUTION: DO NOT RESTORE HYD GREEN PUMP
TRU . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MAINTAIN ON
MAINTENANCE ACTION IS REQUIRED
J If DC ESS BUS FAULT persists
TRU . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF
PF . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . F/O
DESCENT TOWARD . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FL100 / MEA
ANTI/DE-- ICING MODE SEL AUTO FAULT procedure (2.05.09) . . . . . . . . APPLY
PERF PAGE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . SELECT TAT 2
ADC CAPT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MONITOR IAS / BARO-- ALT
LANDING ELEVATION . . . . . . . . . . . . . . . . . . . . . . SET PRESSURE ALTITUDE
DC ESS BUS EQUIPMENT LIST . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK
Affected equipment fault Procedure . . . . . . . . . . . . . . . . . . . . . . . . . . . . . APPLY
J If Cockpit Door Locking System installed
COCKPIT DOOR MANUAL LOCK BOLT(S) . . . . . . MOVE TO CLOSE POSITION
CAUTION: At least two crewmembers must remain in the cockpit during that time
Note: Cockpit Door Control Panel FAULT LIGHT is inoperative.
Note: When the door is locked with the manual bolt(s), the emergency access to
the cockpit is unavailable.
F Before landing
ANTI-- SKID . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF
ANTI-- SKID FAULT procedure (2.05.07) . . . . . . . . . . . . . . . . . . . . . . . . . . APPLY
F After touch down
TAXI ON BOTH ENGINES
COMMENTS
- For DC ESS BUS OFF LOST EQUIPMENT LIST refer to 1.06.60 pages 9 and 10.
Mod 5948
2.05.04
PROCEDURES FOLLOWING FAILURE
P9
ELECTRICAL SYSTEM
AA
001
FEB 12
DC EMER BUS OFF
ALERT
CONDITION
DC EMER BUS no
longer supplied
VISUAL
- MC light flashing amber
- ELEC DC EMER amber message on EWD
- EMER BUSS OFF message on AC/DC SD page
AURAL
SC
PROCEDURE
R
DC EMER BUS OFF
LEAVE AND AVOID ICING CONDITIONS
HYD MAIN BLUE PUMP . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF
HYD X FEED . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON
TRU . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON
J If DC EMER BUS recovered
CAUTION: DO NOT RESTORE HYD MAIN BLUE PUMP
TRU . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MAINTAIN ON
MAINTENANCE ACTION IS REQUIRED
J If DC EMER BUS FAULT persists
TRU . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF
VHF 2 / XPDR 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . USE
DESCENT TOWARD . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FL 100 / MEA
STBY PITCH TRIM . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . USE AS RQD
LANDING ELEVATION . . . . . . . . . . . . . . . . . . . . . SET PRESSURE ALTITUDE
CAUTION: Minimize flight time to reduce time without engine fire detection
TLU . . . . . . . . . . . . . . . . . . . . . . . . . . . . . HI or LO SPD ACCORDING TO IAS
ICE ACCRETION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MONITOR IEP
DC EMER BUS OFF EQUIPMENT LIST . . . . . . . . . . . . . . . . . . . . . . . CHECK
Affected equipment fault Procedure . . . . . . . . . . . . . . . . . . . . . . . . . . . . APPLY
J If ice accretion
DE-- ICING AIRFRAME FAULT procedure (2.05.09) . . . . . . . . . . . . . . . . APPLY
DE-- ICING MODE SEL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OVRD
DE-- ICING MODE SEL FAULT procedure(2.05.09) . . . . . . . . . . . . . . . . APPLY
ANTI-- ICING PROP FAULT procedure(2.05.09) . . . . . . . . . . . . . . . . . . . APPLY
ANTI-- ICING HORNS FAULT procedure(2.05.09) . . . . . . . . . . . . . . . . . . APPLY
F Before landing
ANTI-- SKID . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF
N/W STEERING . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF
ANTI-- SKID FAULT procedure (2.05.07) . . . . . . . . . . . . . . . . . . . . . APPLY
F After touch down
TAXI ON BOTH ENGINES
COMMENTS
- For DC EMER BUS OFF LOST EQUIPMENT LIST refer to 1.06.60 pages 7 and 8.
- ACW powered blue hydraulic pump is lost. HYD X FEED must be selected to open
position to pressurize blue hydraulic circuit.
Mod 5948
2.05.04
PROCEDURES FOLLOWING FAILURE
P 10
ELECTRICAL SYSTEM
AA
001
FEB 12
DC GEN FAULT
ALERT
CONDITION
VISUAL
One DC generation - MC light flashing amber
channel inoperative - ELEC DC GEN amber message on EWD
- associated DC GEN FAULT amber light
on overhead panel
- associated DC GEN FAULT message on
AC/DC SD page.
AURAL
SC
PROCEDURE
DC GEN FAULT
R
DC GEN affected side . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF
J If OAT exceeds ISA + 25
FL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 200 MAX
F After touch down
TAXI ON BOTH ENGINES
F At parking
J If DC GEN 2 FAULT
Connect GPU before CL1 set to FUEL SO
COMMENTS
- If OAT exceeds ISA+25, the maximum allowed flight level is FL 200 due to ventilation
problem of the remaining DC generator.
INV 1(2) FAULT
ALERT
CONDITION
Under/Over voltage
at INV output
VISUAL
- MC light flashing amber
- ELEC INV 1(2) amber message on EWD
- associated INV FAULT amber light on
overhead panel
- INV 1(2) FAULT message on AC/DC SD
page
AURAL
SC
PROCEDURE
INV 1(2) FAULT
R
MAINTENANCE ACTION IS REQUIRED
COMMENTS
- After 10 seconds following INV FAULT, the AC BTC is automatically closed causing
affected AC BUS and AC STBY BUS to be supplied from the remaining inverter.
Mod 5948
2.05.04
PROCEDURES FOLLOWING FAILURE
P 11
ELECTRICAL SYSTEM
AA
001
FEB 12
ACW GEN FAULT
ALERT
CONDITION
One ACW
generation channel
inoperative
VISUAL
- MC light flashing amber
- ELEC ACW GEN 1 (2) amber message
on EWD
- associated ACW GEN FAULT amber
light on overhead panel
- ACW GEN 1 (2) FAULT message on
HYD/ACW SD page
AURAL
SC
PROCEDURE
R
ACW GEN FAULT
R
ACW GEN affected side . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF
LEAVE AND AVOID ICING CONDITIONS
J If ACW GEN 2 FAULT
F After touch down
TAXI ON BOTH ENGINES
DC SVCE/UTLY BUS SHED
ALERT
CONDITION
VISUAL
AURAL
One DC UTLY BUS
automatically shed
after a source
overload
- MC light flashing amber
- ELEC DC SHED amber message on
EWD
- DC SVCE/UTLY BUS SHED amber light
on overhead panel
- SHED message on AC/DC SD page
SC
PROCEDURE
DC SVCE/UTLY BUS SHED
R
DC SVCE/UTLY BUS PB . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . AS RQD
COMMENTS
- For DC SVCE/UTLY BUS SHED LOST EQUIPMENT LIST refer to 1.06.60 pages 12
to 14.
- It is crew decision to select DC SVCE/UTLY BUS pushbutton OFF or not. In case this
pushbutton is selected OFF, it will :
. confirm automatic shedding of affected DC UTLY BUS
. shut off the non affected DC UTLY BUS and the DC SVCE BUS
Mod 5948
2.05.04
PROCEDURES FOLLOWING FAILURE
P 12
ELECTRICAL SYSTEM
001
FEB 12
AA
R MAIN ( OR EMER) BAT CHG FAULT
ALERT
CONDITION
Incipient battery
thermal runaway or
charge contactor
failure
VISUAL
- MC light flashing amber
- ELEC BAT CHG amber message on
EWD
- associated CHG FAULT amber light on
overhead panel
- associated CHG FAULT message on
AC/DC SD page
AURAL
SC
PROCEDURE
R
MAIN (or EMER) BAT CHG FAULT
CHG associated . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF
Mod 5948
2.05.04
PROCEDURES FOLLOWING FAILURE
P 13
ELECTRICAL SYSTEM
001
FEB 12
AA
R EMER + MAIN BAT CHG LOSS
ALERT
CONDITION
VISUAL
AURAL
MFC failure leading
to dual battery
charge contactors
loss
- MC light flashing amber
- ELEC CHG LOSS amber message on
EWD
- both amber arrows illuminated on
overhead panel
- CHG FAULT message on AC/DC SD page
NIL
PROCEDURE
R
EMER + MAIN BAT CHG LOSS
MFC MODULES, one at a time . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF / RESET
J If EMER + MAIN BAT recovered
MAINTENANCE ACTION IS REQUIRED
J If EMER + MAIN BAT CHG LOSS persists
J If no BAT arrow
MAINTENANCE ACTION IS REQUIRED
J If BOTH BAT arrows illuminated
CAUTION : if one ACW GEN is lost, HYD MAIN BLUE PUMP to be set to OFF
and HYD X FEED to be set to ON
TRU . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON
JIf TRU online
MINIMIZE FLIGHT TIME( without battery charge)
JIf TRU FAULT
LAND ASAP
COMMENTS
- This case should only occur following a MFC software failure.
Mod 5948
2.05.04
PROCEDURES FOLLOWING FAILURE
P 14
ELECTRICAL SYSTEM
001
FEB 12
AA
BAT DISCHARGE IN FLIGHT
ALERT
CONDITION
Battery(ies)
discharge in flight
(but DC main
sources available)
VISUAL
- MC light flashing amber
- ELEC BAT DISCH amber message on
EWD
- Left and/or Right amber arrow(s)
illuminated on overhead panel
- MAIN (EMER) BAT amber message on
AC/DC SD page
AURAL
SC
PROCEDURE
R
BAT DISCHARGE IN FLIGHT
ENG START ROTARY SELECTOR . . . . . . . . . . . . . . . . . . . OFF / START ABORT
CAUTION : if one ACW GEN is LOST, HYD MAIN BLUE PUMP to be set to OFF
and HYD X FEED to be set to ON
TRU . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON
J If BAT discharge disappears
CONTINUE NORMAL FLIGHT - MAINTENANCE ACTION IS REQUIRED
J If battery(ies) still discharging
TRU . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF
HYD X FEED . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF AS RQD
HYD MAIN BLUE PUMP . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON AS RQD
LAND ASAP
Mod : 5948
2.05.04
PROCEDURES FOLLOWING FAILURE
P 15
ELECTRICAL SYSTEM
AA
100
FEB 12
AC STBY BUS FAULT
ALERT
CONDITION
TBD
VISUAL
- MC light flashing amber
- ELEC AC STBY amber message on
EWD
AURAL
SC
PROCEDURE
AC STBY BUS FAULT
R
APM . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF
TLU . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . HI or LO SPD ACCORDING TO IAS
SPEED TGT MAN . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . USE
DC STBY BUS FAULT
ALERT
CONDITION
ELEC DC STBY
BUS ± 19.5 V
VISUAL
AURAL
- MC light flashing amber
- ELEC DC STBY BUS amber message on
EWD
SC
PROCEDURE
DC STBY BUS FAULT
R
R
EMER BAT CHG . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF then ON
J If DC STBY BUS FAULT persists
CAUTION : if one ACW GEN is LOST, HYD MAIN BLUE PUMP to be set to OFF
and HYD X FEED to be set to ON
TRU . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON
J If DC STBY BUS recovered
CAUTION : DO NOT RESTORE HYD MAIN BLUE PUMP
J If DC STBY BUS FAULT still persists
TRU . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF
HYD X FEED . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF AS RQD
HYD MAIN BLUE PUMP . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON AS RQD
AVNX IOM 12 + IOM 13 LOSS procedure(2.05.12) . . . . . . . . . . . . . . . . APPLY
LOST EQUIPMENT LIST(1.06.60) . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK
F Before landing
LDG GEAR GRAVITY EXTENSION procedure(2.05.07) . . . . . . . . . . . APPLY
REDUCED FLAPS LANDING procedure(2.05.06) . . . . . . . . . . . . . . . APPLY
Mod : 5948 + 6521
2.05.04
PROCEDURES FOLLOWING FAILURE
P 16
ELECTRICAL SYSTEM
AA
001
FEB 12
DC STBY BUS UND/V
ALERT
CONDITION
DC STBY BUS
UND/V <18 V
VISUAL
- MC light flashing amber
- ELEC STBY UND/V amber message on
EWD
AURAL
SC
PROCEDURE
DC STBY BUS UND/V
J If no DUAL DC GEN LOSS
CAUTION : If one ACW GEN is LOST, HYD MAIN BLUE PUMP to be set to OFF
and HYD X FEED to be set to ON
TRU . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON
J If STBY BUS UND/V disappears
TRU . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MAINTAIN ON
MAINTENANCE ACTION IS REQUIRED
J If STBY BUS UND/V persists
TRU . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF
HYD X FEED . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF AS RQD
HYD MAIN BLUE PUMP . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON AS RQD
DC STBY BUS FAULT procedure(2.05.04) . . . . . . . . . . . . . . . . . . . . . APPLY
J If DUAL DC GEN LOSS and TRU not available
FFor approach only
STBY BUS OVRD . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . SELECT
Mod : 5948
2.05.04
PROCEDURES FOLLOWING FAILURE
P 17
ELECTRICAL SYSTEM
AA
STBY BUS AND BAT ONLY LOST EQUIPMENT LISTS
Mod 5948
001
FEB 12
2.05.04
PROCEDURES FOLLOWING FAILURE
P 18
ELECTRICAL SYSTEM
AA
STBY BUSSES AND BAT ONLY LOST EQUIPMENT LISTS (CONT’D)
Mod 5948
001
FEB 12
2.05.05
PROCEDURES FOLLOWING FAILURE
P1
HYDRAULIC
001
FEB 12
AA
HYD BLUE (GREEN) LO LVL
ALERT
CONDITION
VISUAL
AURAL
Tank compartment
fluid quantity
below 2,5 l (0,67 US
gal)
- MC light flashing amber
- HYD BLUE LO LVL (HYD GREEN LOLV)
amber message on EWD + on ACW HYD
SD page amber LO LVL display
- associated LO LVL amber light and LO PR
amber Iight on MAIN PUMP pushbutton,
on overhead panel
SC
PROCEDURE
R
HYD BLUE (GREEN) LO LVL
J If blue system affected
HYD X FEED . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK OFF
HYD MAIN BLUE PUMP . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF
HYD AUX PUMP . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF
FFor approach
REDUCED PLAPS LANDING procedure(2.05.06) . . . . . . . . . . . . . . . . APPLY
FAfter touch down
USE NORMAL BRAKE FOR STEERING
TAXI ON BOTH ENGINES
J If green system affected
HYD X FEED . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK OFF
HYD GREEN PUMP . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF
LDG DIST . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MULTIPLY BY 1.5
Note : Refer to Part 4 to determine landing distance
F Before landing
LDG GRAVITY EXTENSION procedure(2.05.07) . . . . . . . . . . . . . . . APPLY
F After touch down
REVERSE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . AS RQD
BRK HANDLE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . EMER AS RQD
TAXI ON BOTH ENGINES
HYD SYS LOST EQUIPMENT LIST
BLUE
R
FLAPS / SPOILERS / N/W STEERING
PROP BRK (If installed)
EMER AND PARKING BRK(on
accumulator only)
Mod 5948
GREEN
LDG GEAR EXT / RET
NORMAL BRK
2.05.05
PROCEDURES FOLLOWING FAILURE
P 1A
HYDRAULIC
001
FEB 12
AA
HYD BLUE LO LVL/HYD GREEN LO LVL
COMMENTS
- In case of LO LVL, X FEED remains closed and X FEED valve operation is automatically
inhibited.
- For emergency/parking brake, the brake accumulator allows at least six applications of
braking force at full braking pressure.
- If green system affected, landing distance is increased due to loss of normal braking. If
a go around has to be performed, landing gear will not retract.
Mod 5948
2.05.05
PROCEDURES FOLLOWING FAILURE
P2
HYDRAULIC
001
FEB 12
AA
BOTH MAIN HYD PUMPS LOSS
ALERT
VISUAL
CONDITION
Loss of hydraulic
pump information
AURAL
- MC light flashing amber
- HYD PUMPS LOSS amber message on
EWD
SC
PROCEDURE
BOTH MAIN HYD PUMPS LOSS
R
R
R
MAIN BLUE AND GREEN PUMPS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF
HYD X FEED . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK OFF
LDG DIST . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MULTIPLY BY 1.5
Note : Refer to Part 4 to determine landing distance
F Before landing
LDG GEAR LEVER . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . DOWN
HYD BLUE PRESSURE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK
FLAPS 15_ . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . AS RQD
LDG GEAR GRAVITY EXTENSION procedure (2.05.07) . . . . . . . . . . . . . APPLY
FLAPS 30_ . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . AS RQD
F After touch down
REVERSE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . AS RQD
BRK HANDLE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . EMER AS RQD
TAXI ON BOTH ENGINES
BOTH MAIN HYD PUMPS LOST EQUIPMENT LIST
BLUE
GREEN
Recovered when LDG GEAR lever is DOWN
FLAPS / SPOILERS / N/W STEERING
PROP BRK (if applicable)
EMER AND PARKING BRK (on
R accumulator only)
LDG GEAR EXT / RET
NORM BRK
COMMENTS
- For emergency/parking brake, the brake accumulator allows at least six applications of
braking force at full braking pressure.
- Landing distance is increased due to loss of normal braking. If a go around has to be
performed, landing gear will not retract.
Mod 5948
2.05.05
PROCEDURES FOLLOWING FAILURE
P3
HYDRAULIC
001
FEB 12
AA
BOTH HYD SYS LOSS
ALERT
VISUAL
CONDITION
Loss of hydraulic
system information
AURAL
- MC light flashing amber
- HYD SYS LOSS amber message on EWD
SC
PROCEDURE
BOTH HYD SYS LOSS
R
R
R
MAIN AND AUX PUMPS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF
F For approach
GPWS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FLAP OVRD
LDG GEAR GRAVITY EXTENSION procedure (2.05.07) . . . . . . . . . . . . . APPLY
V APP . . . . . . . . . . . . . . . . . . . . . . . . . . . . . VmHB 0 + 5 KT + WIND EFFECT
LDG DIST . . . . . . . . . . . . . . . . . . . . . MULTIPLY LDG DIST FLAPS 30 BY 2.9
Note: Refer to Part 4 to determine VmHB and LDG DIST
Note : LDG Gear cannot be retracted
CAUTION : Tail strike may occur if pitch attitude exceeds 8° during the flare
depending upon vertical speed at touch down.
F After touch down
REVERSE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . AS RQD
BRK HANDLE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . EMER AS RQD
TAXI ON BOTH ENGINES
BOTH HYD SYS LOST EQUIPMENT LIST
BLUE
R
FLAPS / SPOILERS / N/W STEERING
PROP BRK (if applicable)
EMER AND PARKING BRK (on
accumulator only)
GREEN
LDG GEAR EXT / RET
NORM BRK
COMMENTS
- The landing distance is increased due to loss of flaps and normal braking.
- For emergency/parking brake, the brake accumulator allows at least six applications of
braking force at full braking pressure.
- If a go around has to be performed, landing gear will not retract.
Mod 5948
2.05.05
PROCEDURES FOLLOWING FAILURE
P4
001
HYDRAULIC
FEB 12
AA
HYD BLUE (GREEN) LO PR / HYD BLUE (GREEN) OVHT
ALERT
CONDITION
VISUAL
AURAL
Pump delivery
- MC light flashing amber
pressure below 1500 - HYD BLUE (GREEN) (AUX) LO PR amber
PSI (103.5 bar)
message on EWD
- associated pump LO PR amber light on
overhead panel and amber indication on
ACW/HYD SD page
SC
Pump case drain
line temperature
above 121_C
SC
- MC light flashing amber
- HYD BLUE (GREEN) (AUX) OVHT amber
message on EWD
- associated OVHT amber light on overhead
panel and amber indication on ACW/HYD
SD page
PROCEDURE
HYD BLUE (GREEN) LO PR / HYD BLUE (GREEN) OVHT
R
HYD PUMP affected side . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF
HYD X FEED . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON
HYD AUX LO PR / HYD AUX OVHT
R
HYD AUX PUMP . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF
COMMENTS
- Failed system users are supplied by the non affected pump when opening the cross
feed.
- In case of overheat, an attempt to restore the system may be performed after OVHT
alert has extinguished.
Mod 5948
2.05.06
PROCEDURES FOLLOWING FAILURE
P1
FLIGHT CONTROL
001
FEB 12
AA
FLAPS UNLK
ALERT
CONDITION
Flaps untimely
retraction of more
than 3_ when flaps
extended
VISUAL
- MW light flashing red
- FLAPS UNLK red message on EWD
AURAL
CRC
PROCEDURE
FLAPS UNLK
R
R
R
J If before V1
TAKE OFF . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ABORT
J If after V1
VR, V2 . . . . . . . . . . . . . . . . . . SPEED BUGS AUTOMATICALLY INCREASED
J If FLAPS UNLK during approach
GO AROUND procedure (2.03.20) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . APPLY
VGA . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . NOT LESS THAN Vmin OPS
F When possible
FLAPS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 0_
REDUCED FLAPS LANDING procedure (2.05.06) . . . . . . . . . . . . . . . . . APPLY
Mod 5948
2.05.06
PROCEDURES FOLLOWING FAILURE
P2
FLIGHT CONTROL
001
FEB 12
AA
FLAPS JAM / UNCOUPLED / ASYM
ALERT
FLAPS UNCOUPLED : No specific alert.
FLAPS ASYM / JAM :
CONDITION
Flaps asymmetry of
more than 6.7_
during flaps
actuation
VISUAL
- MC light flashing amber
- FLAPS ASYM amber message on EWD
Flaps have not
- MC light flashing amber
reached the selected - FLT CTL amber messsage on EWD
position after 30s.
- FLAPS JAM amber message on EWD
AURAL
SC
SC
PROCEDURE
FLAPS JAM / UNCOUPLED / ASYM
FLAPS CTL LEVER . . . . . . . . . . . . . . . . . . . NEAR FLAPS PRESENT POSITION
R
F For approach
REDUCED FLAPS LANDING procedure (2.05.06) . . . . . . . . . . . . . . . . . APPLY
Mod 5948
2.05.06
PROCEDURES FOLLOWING FAILURE
P3
001
FLIGHT CONTROL
FEB 12
AA
REDUCED FLAPS LANDING
PROCEDURE
REDUCED FLAPS LANDING
R
GPWS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FLAP OVRD
STEEP SLOPE APPROACH (≥4.5_) . . . . . . . . . . . . . . . . . . . . . . . PROHIBITED
R
R
Note : Refer to Part 4 to determine VmHB and LDG DIST
Note: ILS CAT 2 IS PROHIBITED
CAUTION : Tail strike may occur if pitch attitude exceeds 8° during the flare
depending upon vertical speed at touch down.
COMMENTS
- GPWS must be selected GPWS OVRD / FLAP OVRD to prevent nuisance alerts on
final approach.
Mod 5948
2.05.06
PROCEDURES FOLLOWING FAILURE
P4
FLIGHT CONTROL
001
FEB 12
AA
STICK PUSHER / SHAKER FAULT
ALERT
CONDITION
Stick pusher /
shaker fault
VISUAL
- MC light flashing amber
- FLT CTL PUSHER amber message on
EWD
- FAULT amber light in STICK PUSHER
pushbutton
AURAL
SC
PROCEDURE
STICK PUSHER / SHAKER FAULT
R
STICK PUSHER / SHAKER . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF
TCAS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . TA ONLY
IAS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . NOT LESS THAN Vmin OPS+10KT
SPD TGT MAN . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . USE
LDG DISTANCE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MULTIPLY BY 1.15
Note : Refer to Part 4 to determine VmHB/VmLB and LDG DIST
CAUTION : AP single source prohibited below 1000 ft AGL is prohibited.
COMMENTS
- The minimum maneuvering speeds are increased by 10 kt in order to increase stall
margin.
- If ALPHA probes are not heated, ice accretion may modify alpha probes indication. If
angle of attack information offsets 4_, STICK PUSHER / SHAKER FAULT light
illuminates. When living icing conditions, as soon as alpha probes are cleared of ice,
STICK PUSHER / SHAKER may be recovered by selecting it ON.
Mod 5948
2.05.06
PROCEDURES FOLLOWING FAILURE
P5
FLIGHT CONTROL
001
FEB 12
AA
PITCH TRIM ASYM
ALERT
CONDITION
Pitch tabs
desynchronisation
VISUAL
- MC light flashing amber
- PITCH TRIM ASYM amber message on
EWD
AURAL
SC
PROCEDURE
PITCH TRIM ASYM
R
AP DISCONNECTION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CONFIRM MANUALLY
PITCH TRIM INOPERATIVE procedure (2.05.06) . . . . . . . . . . . . . . . . . . . . . APPLY
Note: ILS CAT 2 IS PROHIBITED
COMMENTS
- When a PITCH TRIM ASYM alert is generated, AP automatically disconnects and
cannot be reengaged. However, it is recommended to manually confirm AP
disconnection.
- Don’t use the trims anymore and apply PITCH TRIM INOPERATIVE procedure.
PITCH TRIM INOPERATIVE
ALERT
Both normal and standby pitch trim controls are inoperative.
PROCEDURE
PITCH TRIM INOPERATIVE
R
EXISTING CONFIGURATION AND SPEED . . . . . . MAINTAIN AS LONG AS POSSIBLE
F For approach
STEEP SLOPE APPROACH (≥4.5_) . . . . . . . . . . . . . . . . . . . . . . PROHIBITED
FLAPS . . . . . . . . . . . . . . . . . . EXTEND AT VFE FOR EACH CONFIGURATION
IAS . . . . . . . . . . . . . . . . . . . . . . . . . . . . NOT LESS THAN Vmin OPS + 10 KT
SPD TGT MAN . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . USE
LDG DISTANCE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MULTIPLY BY 1.15
Note: ILS CAT 2 IS PROHIBITED
Note : Refer to Part 4 to determine VmHB / VmLB and LDG DIST
COMMENTS
- Maintain existing configuration and speed as long as possible to avoid high forces on
the columns.
- The landing distance is increased due to landing speed increase.
Mod 5948
2.05.06
PROCEDURES FOLLOWING FAILURE
P6
FLIGHT CONTROL
AA
001
APR 11
DUTCH ROLL TENDENCY / RUDDER RELEASABLE CENTERING UNIT FAIL
ALERT
DUTCH ROLL TENDANCY: no specific alert
RUDDER RELEASABLE CENTERING UNIT FAIL
CONDITION
releasable
centering unit
clutch energized
more than 60s with
Y/D off
VISUAL
- MW light flashing amber
- FLT CTL RUD RCU amber message on
EWD
AURAL
SC
PROCEDURE
DUTCH ROLL TENDENCY / RUDDER RELEASABLE CENTERING
UNIT FAIL
J If YD is available
YD . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ENGAGE
J If YD is not available
LOCK THE RUDDER PEDALS WITH THE FEET TO PREVENT UNEXPECTED
RUDDER PEDAL MOVEMENT
Mod 5948
2.05.06
PROCEDURES FOLLOWING FAILURE
P7
FLIGHT CONTROL
001
FEB 12
AA
PITCH DISCONNECT
ALERT
CONDITION
Pitch coupling
mechanism
disconnected
VISUAL
- MW light flashing red
- PITCH DISC red message on EWD
AURAL
CRC
PROCEDURE
PITCH DISCONNECT
R
R
R
R
FREE COLUMN(S) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . IDENTIFY
PF . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FREE CONTROL COLUMN SIDE
IAS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 180 KT MAX
BANK ANGLE . . . . . . . . . . . . . . . . . . . . . . . . 30_ MAX UNTL FLAPS EXTENSION
LEAVE AND AVOID ICING CONDITIONS
IAS MINI . . . . . . . . . . . . . . . . . . . . . . . . . . . . NOT LESS THAN Vmin OPS + 10 KT
JIf one elevator is stuck to full down position
IAS MAX . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 154 KT
EXTEND FLAPS IF NECESSARY
JIf elevator jamming occurs at take off
IAS MAX . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 161 KT
MAINTAIN FLAPS IF NECESSARY
JIf other cases
IAS MAX . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 180 KT
F For approach
STEEP SLOPE APPROACH (≥4.5_) . . . . . . . . . . . . . . . . . . . . . . PROHIBITED
LAND AT AIRPORT WITH MINIMUM CROSSWIND
IAS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . NOT LESS THAN Vmin OPS + 10 KT
SPD TGT MAN . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . USE
LDG DISTANCE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MULTIPLY BY 1.15
F For landing
PL 1 + 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . REDUCE SMOOTHLY TO FLARE
Note: ILS CAT 2 IS PROHIBITED
Note : Refer to Part 4 to determine LDG DATA
F When on ground
PITCH RECONNECTION ON GROUND procedure (2.05.06) . . . . . . . . . APPLY
COMMENTS
- As both elevator channels are disconnected, pitch control efficiency is reduced.
Mod 5948
2.05.06
PROCEDURES FOLLOWING FAILURE
P8
FLIGHT CONTROL
001
FEB 12
AA
PITCH RECONNECTION ON GROUND
This procedure may be applied on ground after a PITCH DISCONNECT.
PROCEDURE
PITCH RECONNECTION ON GROUND
GUST LOCK . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ENGAGE
BOTH COLUMNS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK LOCKED
ELEV CLUTCH GUARDED PB . . . . . . . . . . . . . . . . . . . . . . . DEPRESS AND HOLD
F When PITCH DISC extinguishes on EWD
ELEV CLUTCH GUARDED PB . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . RELEASE
PITCH RECONNECT ON EWD . . . . . . . . . . . . . . . . . . . . CHECK EXTINGUISHED
GUST LOCK . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF
BOTH COLUMNS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK COUPLED
PITCH RECONNECT
ALERT
CONDITION
Pitch recoupling
system actived
VISUAL
- MW light flashing red
- PITCH RECONNCT red message on EWD
PROCEDURE
PITCH RECONNECT
R
NO CREW ACTION
MAINTENANCE ACTION IS REQUIRED
Mod 5948
AURAL
CRC
2.05.06
PROCEDURES FOLLOWING FAILURE
P9
FLIGHT CONTROL
001
FEB 12
AA
TLU FAULT
ALERT
CONDITION
VISUAL
Both ADC are lost, or
- MC light flashing amber
disagree between actual and - FLT CTL TLU amber message on
theoretical TLU position, or
EWD
TLU synchro position failure - TLU FAULT amber light on
overhead panel
AURAL
SC
PROCEDURE
TLU FAULT
R
R
J If ADC 1 + 2 are lost
J If IAS above 185 kt
TLU . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . HI SPD
J If IAS below 185 kt
TLU . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . LO SPD
DISREGARD TLU FAULT ALERT
J If at least one ADC operates
J If IAS above 185 kt
TLU . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . HI SPD
J If TLU FAULT alarm persists
SPEED . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 180 KT MAX
TLU . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . LO SPD
J If IAS below 185 kt
SPEED . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 180 KT MAX
TLU . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . LO SPD
DISREGARD TLU FAULT ALERT
J If TLU LO SPEED message missing
IAS . . . . . . . . . . . . . . . . . . . . . . . . NOT LESS THAN Vmin OPS + 10 KT
SPD TGT MAN . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . USE
LDG DISTANCE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MULTIPLY BY 1.15
LAND AT AIRPORT WITH MINIMUM CROSSWIND
Note : Maximum demonstrated crosswind (dry runway) with TLU HI SPD mode : 15 kt.
COMMENTS
- If both ADC are lost, TLU automatic functioning is lost. TLU must be set manually
according to IAS read on the STBY ASI.
Mod 5948
2.05.06
PROCEDURES FOLLOWING FAILURE
P 10
FLIGHT CONTROL
001
FEB 12
AA
AIL LOCK LIT
ALERT
CONDITION
Disagree between aileron
locking actuators and gust
lock control (temporized
alert 8 seconds)
VISUAL
- MC light flashing amber
- AIL LOCK LIT amber message on
EWD
Aileron locking actuators not - MW light flashing red
fully retracted and PL on TO - CONFIG red message on EWD
position, or
- AIL LOCK LIT amber message on
Disagree between aileron
EWD
locking actuators and gust
lock control during the TO
CONFIG test
AURAL
SC
CRC
PROCEDURE
AIL LOCK LIT
R
R
J If before take off
RETURN TO PARKING
REFER TO MMEL ATA 27 ITEM 70--1 GUST LOCK SYSTEM
J If after landing
TAKE SPECIAL CARE FOR TAXI (WIND EFFECTS)
F At parking
USE STANDBY SYSTEM FOR AILERON LOCK AT PARKING
MAINTENANCE ACTION IS REQUIRED
COMMENTS
- A malfunction of an aileron locking actuators is pointed out according two levels of
protection:
. an amber alarm, before take off, with a 8 seconds temporization
. a red alarm if either TO CONFIG test is performed or both PL are on TO position
Mod 5948
2.05.06
PROCEDURES FOLLOWING FAILURE
P 11
FLIGHT CONTROL
001
FEB 12
AA
ELEV JAM
ALERT
There is no indication of an elevator jam other than an inability to operate the control
column.
PROCEDURE
ELEVATOR JAM
R
CONTROL COLUMNS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . UNCOUPLE
FREE COLUMN . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . IDENTIFY
IAS MAX . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 180 KT
LEAVE AND AVOID ICING CONDITIONS
IAS MINI . . . . . . . . . . . . . . . . . . . . . . . . . . . . NOT LESS THAN Vmini OPS + 10 KT
J If one elevator is stuck to full down position
IAS MAX . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 154 KT
EXTEND FLAPS IF NECESSARY
J If elevator jamming occurs at take off
IAS MAX . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 161 KT
MAINTAIN FLAPS IF NECESSARY
J If other cases
IAS MAX . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 180 KT
PITCH DISCONNECT procedure (2.05.06) . . . . . . . . . . . . . . . . . . . . . . . . APPLY
Note: ILS CAT 2 IS PROHIBITED
COMMENTS
- Both pilots accomplish a firm action on their own column IN THE WAY REQUIRED BY
THE JAMMING CONDITION.
One of the two channels must yield; force required 52 daN (115 lb).
- If uncoupling is unsuccessful, when trajectory under control and above safety altitude,
apply opposite efforts on both control columns.
- Stick pusher acts on left hand elevator. If left hand control column is jammed, stick
pusher must be considered inoperative.
- The maximum speed authorized if elevator jamming occurs at take off is linked to the
elevator take off position.
- If right hand control column is jammed, AutoPilot is no more available.
- After uncoupling, only one pilot has control and actuates one elevator only.
Mod 5948
2.05.06
PROCEDURES FOLLOWING FAILURE
P 12
FLIGHT CONTROL
001
FEB 12
AA
AILERON JAM / SPOILER JAM
ALERT
There is no indication of an aileron jam other than an inability to operate the control wheel
laterally.
Spoiler jam may be detected when a SPLR light is illuminated on the overhead panel with
control wheel at neutral position.
PROCEDURE
AILERON JAM / SPOILER JAM
R
R
R
R
BANK ANGLE LIMIT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 25_ MAX
HYD MAIN BLUE AND AUX HYD PUMPS . . . . . . . . . . . . . . . . . . . . . . . . . . OFF
LAND AT AIRPORT WITH MINIMUM CROSSWIND
F For approach
STEEP SLOPE APPROACH (≥4.5_) . . . . . . . . . . . . . . . . . . . . . . PROHIBITED
HYD MAIN BLUE AND AUX HYD PUMPS . . . . . . . . . . . . . . . . . . . . . . . . . . ON
V APP . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . NOT LESS THAN V REF + 10 KT
SPD TGT MAN . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . USE IF NECESSARY
LDG DIST . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MULTIPLY BY 1.15
Note : Refer to Part 4 to determine landing distance
Note: ILS CAT 2 IS PROHIBITED
CAUTION : Do not extend FLAPS in turn.
F When in landing configuration
HYD MAIN BLUE AND AUX HYD PUMPS . . . . . . . . . . . . . . . . . . . . . . . . . OFF
F Immediately after touch down
HYD MAIN BLUE AND AUX HYD PUMPS . . . . . . . . . . . . . . . . . . . . . . . . . ON
COMMENTS
- Bank angle is limited to 25_ due to reduced roll control efficiency.
- Blue pump and AUX pump are selected OFF in order to decrease drag from associated
extended spoiler. These pumps are selected ON again when necessary then selected
OFF. They must be reselected ON immediately after touch down in order to recover
nose wheel steering.
Mod 5948
2.05.06
PROCEDURES FOLLOWING FAILURE
P 13
FLIGHT CONTROL
001
FEB 12
AA
RUDDER JAM
ALERT
There is no indication of a rudder jam other than an inability to operate the rudder pedals.
PROCEDURE
RUDDER JAM
R
R
R
STEEP SLOPE APPROACH (≥4.5_) . . . . . . . . . . . . . . . . . . . . . . . PROHIBITED
LAND AT AIRPORT WITH MINIMUM CROSSWIND
LANDING . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FLAPS 30_
USE DIFFERENTIAL POWER TO MINIMIZE SIDESLIP
Note: ILS CAT 2 IS PROHIBITED
F At touch down
NOSE DOWN BEFORE REDUCTION BELOW FI
Mod 5948
2.05.07
PROCEDURES FOLLOWING FAILURE
P1
LANDING GEAR
001
FEB 12
AA
LDG GEAR GRAVITY EXTENSION
PROCEDURE
LDG GEAR GRAVITY EXTENSION
R
R
LDG GEAR LEVER . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . DOWN
EMER EXTENSION HANDLE . . . . . . . . . . . . . PULL ABOVE PEDESTAL LEVEL
. . . . . . . . . . . . . . . . . . . . AND MAINTAIN UP TO GREEN LIGHTS ILLUMINATED
CAUTION : Do not twist handle when operating.
TCAS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . TA ONLY
J If ABNORMAL LDG GEAR indication
LANDING WITH ABNORMAL LDG GEAR procedure (2.05.07) . . . . . . . . APPLY
Note : LDG Gear cannot be retracted
COMMENTS
- Although gravity extension is possible up to VLO, it is recommended to perform it at a
lower speed compatible with flight conditions.
- Pulling the handle mechanically releases the up locks. Pushing the handle back resets
the uplocking system.
TRAINING
- After gravity extension for training purposes, reset the emergency extension handle
before normal retraction. If handle is maintained pulled, hydraulic configuration will
inhibit gear retraction.
Mod 5948
2.05.07
PROCEDURES FOLLOWING FAILURE
P2
LANDING GEAR
001
FEB 12
AA
LANDING WITH ABNORMAL LDG GEAR
PROCEDURE
LANDING WITH ABNORMAL LDG GEAR
R
R
R
F Preparation
CABIN CREW (PA) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . NOTIFY
ATC / XPDR . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . NOTIFY / AS RQD
SEAT BELTS / NO DVCE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON
GPWS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF
CABIN AND COCKPIT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . PREPARE
LOOSE AND SURVIVAL EQUIPMENT SECURED AND PREPARED
BELTS AND SHOULDER HARNESS . . . . . . . . . . . . . . . . . . . . . . . . LOCKED
FUEL QTY . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . IF POSSIBLE, REDUCE
J If abnormal nose LDG GEAR
CG LOCATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . IF POSSIBLE, AFT
J If abnormal main LDG GEAR
FUEL UNBALANCE . . . . . . . . . . . . . . . . . . . . . IF POSSIBLE, ESTABLISH
Note: Reduced fuel on side with failed LDG GEAR, and do not exceed fuel
unbalance limit ( 730 kg ).
F Approach
LDG GEAR LEVER . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CONFIRM DOWN
LDG GEAR EMER EXT HANDLE . . . . . . . . . . . . . . . . . . . CONFIRM PULLED
MAN IGN . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF
CABIN REPORT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CONFIRM OBTAINED
F Before landing
BLEEDS 1 + 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF
BRACE FOR IMPACT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ORDER
F At touch down
PL 1 + 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . GI
CL 1 + 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FTR THEN FUEL SO
F After touch down
FIRE HANDLES 1 + 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . PULL
F When aircraft stopped
PARKING BRAKE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . SET
CABIN CREW (PA) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . NOTIFY
FUEL PUMPS 1 + 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF
AGENT 1 ENG 1 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . DISCH
AGENT 1 ENG 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . DISCH
EVACUATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . INITIATE
F Before leaving aircraft
BAT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF
To be continued next page...\...
Mod 5948
2.05.07
PROCEDURES FOLLOWING FAILURE
P3
LANDING GEAR
AA
001
APR 11
LANDING WITH ABNORMAL LDG GEAR (CONT’D)
COMMENTS
- The procedure is intended for use when one or more landing gear fail to extend and/or
lockdown following the application of either normal or gravity extension procedure.
It is considered preferable to use all available gear locked down rather than carry out a
belly landing. Under these circumstances, a hard surface runway landing is to be
recommended.
Full advantage should be taken from foam spread on the runway.
- Notify ATC of the nature of emergency encountered and state intentions.
- Notify the cabin crew of the nature of emergency encountered and state intentions.
Specify the available time.
- GPWS is selected OFF to avoid nuisance warnings.
- Burn fuel off down to the minimum possible impact weight. This reduces VAPP and as a
consequence the load factor for impact and the energy which must be dissipated.
Mod 5948
2.05.07
PROCEDURES FOLLOWING FAILURE
P4
LANDING GEAR
AA
001
APR 11
LDG GEAR UNSAFE INDICATION
ALERT
VISUAL
CONDITION
Any gear not seen
down locked, and
Flaps 30, and
ZRA < 500 ft
Any gear not seen
down locked, and
At least one PL at
FI, and
ZRA < 500 ft
- MW light flashing red
- LDG GEAR NOT DN red message on
EWD
- Red light in landing gear lever
- Any green ∇ light not illuminated on
either panel
AURAL
CRC
which may not be
silenced by
depressing MW PB
CRC
which may be
silenced by
depressing MW PB
Note : The second condition is inhibited during 150 seconds after the retraction of at least
one landing gear leg, to cover the case of the one engine go around.
Note : In both cases, ZRA condition is inhibited in case of radio altimeter failure.
PROCEDURE
LDG GEAR UNSAFE INDICATION
J If LDG GEAR selected DOWN
J If GREEN light OFF on one panel only
UNSAFE INDICATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . DISREGARD
J If GREEN light OFF on both panels
LDG GEAR GRAVITY EXTENSION procedure (2.05.07 page 1) . . . . APPLY
J If LDG GEAR selected UP
J If RED light ON on one panel only
UNSAFE INDICATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . DISREGARD
J If RED or GREEN light ON on both panels
LEAVE AND AVOID ICING CONDITIONS
IAS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 160 KT MAX
LDG GEAR . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . DOWN
TCAS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . TA ONLY
Mod 5948
2.05.07
PROCEDURES FOLLOWING FAILURE
P5
LANDING GEAR
AA
001
APR 11
LDG GEAR UNSAFE INDICATION (CONT’D)
COMMENTS
Landing gear selected DOWN
- If all green lights are illuminted on one panel, the unsafe indication is false.
- If overhead panel (detection system 2) gives false indication, use of emergency audio
cancel will be requested to cancel aural warning CRC as soon as flaps will be selected
30.
- If one gear remains unlocked, perform turns to increase load factor and perform
alternating side slips in an attempt to lock the gear.
Landing gear selected UP
- If light illuminated on one indicator but indications are normal on the other panel, the
unsafe indication is false.
- Flight with landing gear extended has a significant effect on fuel consumption and
climb gradient : see 3.11 - SPECIAL OPERATIONS.
- Landing gear down selection may be delayed if peformance requires.
Mod 5948
2.05.07
PROCEDURES FOLLOWING FAILURE
P6
LANDING GEAR
001
FEB 12
AA
LDG GEAR RETRACTION IMPOSSIBLE
PROCEDURE
LDG GEAR RETRACTION IMPOSSIBLE
R
LEAVE AND AVOID ICING CONDITIONS
LDG GEAR LEVER . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . DOWN
IAS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . VLE MAX
FWS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . RCL
TCAS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . TA ONLY
IDLE GATE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MONITOR
ANTI- SKID FAULT
PROCEDURE
ANTI- SKID FAULT
R
ANTI-- SKID . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF
LDG DISTANCE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MULTIPLY BY 1.4
Note : Refer to Part 4 to determine LDG DIST
F AT touch down
REVERSE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . AS RQD
NORMAL BRAKE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . USE WITH CARE
BRAKE HANDLE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . EMER AS RQD
BRK TEMP HOT
PROCEDURE
BRK TEMP HOT
J If BRK TEMP HOT occurs before take off
TAKE OFF . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . DELAY
J If BRK TEMP HOT occurs in flight
LEAVE LDG GEAR DOWN FOR 1 MINUTE AFTER TAKE OFF
FOR COOLING EXCEPT IN CASE OF EMERGENCY
Mod 5948
2.05.07
PROCEDURES FOLLOWING FAILURE
P7
001
LANDING GEAR
AA
APR 11
ANTI- SKID FAULT
ALERT
CONDITION
Anti-- skid channel
loss (power loss or
loss of transducer or
valve continuity)
VISUAL
- MC light flashing amber
- WHEELS A--SKID amber message on
EWD
AURAL
SC
PROCEDURE
ANTI- SKID FAULT
ANTI SKID . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF
LDG DIST . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MULTIPLY BY 1.4
F At touch down
REVERSE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . AS RQD
NORMAL BRAKE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . USE WITH CARE
BRAKE HANDLE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . EMER AS RQD
COMMENTS
- landing distance is increased due to reduced braking efficiency.
BRK TEMP HOT
ALERT
CONDITION
Brake temperature
over 150_C
VISUAL
- MC light flashing amber
- WHEELS BRK HOT amber message
on EWD
AURAL
SC
PROCEDURE
BRK TEMP HOT
J If BRK TEMP HOT occurs before take off
TAKE OFF . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . DELAY
J If BRK TEMP HOT occurs in flight
LEAVE LDG GEAR DOWN FOR 1 MINUTE AFTER TAKE OFF FOR COOLING
EXCEPT IN CASE OF EMERGENCY
Mod 5948
M
2.05.08
PROCEDURES FOLLOWING FAILURE
P1
001
AIR
AA
APR 11
BLEED VALVE 1 (2) FAULT
ALERT
CONDITION
Bleed valve position
in disagree with
command
VISUAL
- MC light flashing amber
- AIR BLEED 1(2) amber message on
EWD + air bleed amber indication on
Air Cabin SD page
- Associated BLEED and PACK FAULT
amber lights on overhead panel
AURAL
SC
PROCEDURE
BLEED VALVE 1(2) FAULT
PACK VALVE affected side . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF
BLEED VALVE affected side . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF
MAX FL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 200 / MEA
AVOID LARGE QUICK POWER CHANGES AT HIGH ALTITUDES
COMMENTS
- Following the detection of a FAULT, the affected BLEED VALVE will close automatically
and the associated PACK VALVE will close due to lack of air supply. The associated
actions confirm automatic operation and extinguish related alerts, allowing flight to be
continued with one pack supplied.
- Pack should be confirmed closed first due to PACK FAULT inhibition (as soon as
BLEED is selected OFF, PACK FAULT light extinguishes).
- A failure of Handling Bleed Valve combined with BLEED OFF operation may lead to
engine stall. Engine stall may be prevented through slow power levers movements,
especially when advancing the power levers.
- An engine stall is indicated by one or a series of mild surges. These will normally stop
without crew action, however a slight power reduction, if appropriate, will restore
normal operation.
Mod 5948
2.05.08
PROCEDURES FOLLOWING FAILURE
P2
001
AIR
AA
APR 11
BLEED 1(2) OVHT
ALERT
CONDITION
Overheat in bleed
duct :
T duct > 274_C /
525_F
VISUAL
- MC light flashing amber
- AIR BLEED1(2) OVHT amber
message on EWD + amber Bleed
indication on Air Cabin SD page
- Associated OVHT, BLEED and PACK
FAULT amber lights on overhead
panel
AURAL
SC
PROCEDURE
BLEED 1(2) OVHT
PACK VALVE affected side . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF
BLEED VALVE affected side . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF
MAX FL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 200 / MEA
AVOID LARGE QUICK POWER CHANGES AT HIGH ALTITUDES
COMMENTS
- Following the detection of an overheat, the affected BLEED VALVE will close
automatically and the associated PACK VALVE will close due to lack of air supply. The
associated actions confirm automatic operation and extinguish related alerts,
allowing flight to be continued with one pack supplied.
- Pack should be confirmed closed first due to PACK FAULT inhibition (as soon as
BLEED is selected OFF, PACK FAULT light extinguishes).
- System may be restored in flight after OVHT alert has extinguished.
Mod 5948
2.05.08
PROCEDURES FOLLOWING FAILURE
P3
AIR
100
FEB 12
AA
BLEED 1(2) LEAK
ALERT
CONDITION
Bleed leak detected as long as
R bleed air distribution duct work
1(2) side
VISUAL
- MC light flashing amber
- AIR BLEED 1(2) LEAK amber
message on EWD
- Associated LEAK, BLEED and
PACK FAULT amber lights on
overhead panel
- Amber bleed and pack valve
associated with the amber label
LEAK, on the Cabin SD page
AURAL
SC
PROCEDURE
BLEED 1(2) LEAK
R
PACK VALVE affected side . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF
BLEED VALVE affected side . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF
MAX FL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 200 / MEA
AVOID LARGE QUICK POWER CHANGES AT HIGH ALTITUDES
CAUTION : Bleed (Affected side) must not be restored in flight.
Note : If a bleed leak occurs on ground during taxi, go back to parking.
COMMENTS
- Following the detection of a leak, the affected BLEED VALVE will close automatically
and the associated PACK VALVE will close due to lack of air supply. The associated
actions confirm automatic operation and extinguish related alerts, allowing flight to be
continued with one pack supplied.
- Pack should be confirmed closed first due to PACK FAULT inhibition (as soon as
BLEED is selected OFF, PACK FAULT light extinguishes).
- System must not be restored in flight because it may create hazards.
Mod 5948 + 6521
2.05.08
PROCEDURES FOLLOWING FAILURE
P4
001
AIR
FEB 12
AA
X VALVE OPEN
ALERT
CONDITION
VISUAL
AURAL
X valve open while it - MC light flashing amber
should be closed
- AIR X VALVE amber message on
EWD
- X VALVE OPEN amber light on
overhead panel
- Amber X valve, on the Cabin SD page
SC
PROCEDURE
R
X BLEED VALVE OPEN
CAUTION : Do not supply both packs from one single bleed.
COMMENTS
- If both bleeds are available, no special procedure has to be applied. In case of bleed
failure, associated pack must be selected OFF.
PACK VALVE FAULT
ALERT
CONDITION
Pack valve position disagrees
with command or overheat
downstream of the compressor
(T > 204_C / 393_F)
VISUAL
AURAL
- MC light flashing amber
- AIR PACK amber message on
EWD
- Associated PACK FAULT amber
light on overhead panel
- Amber Pack valve, on the Cabin SD
page
SC
PROCEDURE
PACK VALVE FAULT
PACK VALVE affected side . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF
MAX FL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 200 / MEA
AVOID LARGE QUICK POWER CHANGES AT HIGH ALTITUDES
COMMENTS
- If both bleeds are available, no special procedure has to be applied. In case of bleed
failure, associated pack must be selected OFF.
Mod 5948
2.05.08
PROCEDURES FOLLOWING FAILURE
P5
AIR
001
FEB 12
AA
BOTH PACK VALVES FAULT
ALERT
VISUAL
CONDITION
Pack valve position disagrees
with command or overheat
downstream of the compressor
(T > 204_C / 393_F)
- MC light flashing amber
- AIR PACK 1+2 amber message on
EWD
- Associated PACK FAULT amber
light on overhead panel
- Both amber Pack valves, on the
Cabin SD page.
AURAL
SC
PROCEDURE
BOTH PACK VALVES FAULT
R
MAX FL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 100 / MEA
F When ∆P below 1PSI
OVBD VALVE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FULL OPEN
MAN RATE KNOB . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9 O’CLOCK
CAB PRESS MODE SEL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MAN
MAN RATE KNOB . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MAX INCREASE
COMMENTS
- No air is entering in the cabin. Leaks will increase cabin altitude.
RECIRC FAN FAULT
ALERT
CONDITION
VISUAL
Recirculation fan underspeed or
fan electrical motor overheat
- MC light flashing amber
- AIR RECIRC FAN 1(2) amber
message on EWD
- associated RECIRC FAN FAULT
amber light on overhead panel
- Amber recirculation fan, on the
Cabin SD page
AURAL
SC
PROCEDURE
RECIRC FAN 1(2) FAULT
RECIRC FAN affected side . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF
Mod 5948
2.05.08
PROCEDURES FOLLOWING FAILURE
P6
AIR
100
FEB 12
AA
DUCT OVHT
ALERT
VISUAL
CONDITION
Overheat in the duct (T duct
R > 92_C / 200_F)
- MC light flashing amber
- AIR DUCT 1(2) OVHT amber message
on EWD + amber DUCT OVHT on Air
Cabin SD page.
- associated TEMP SEL OVHT amber light
on overhead panel
AURAL
SC
PROCEDURE
DUCT 1(2) OVHT
R
R
TEMP SEL affected side . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MAN
COMPT TEMP SELECTOR affected side . . . . . . . . . . . . . . . . . . . . . . . . . . COLD
CAUTION : Monitor DUCT TEMP and make sure it remains positive.
J If DUCT OVHT alert persists
PACK VALVE affected side . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF
MAX FL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 200 / MEA
AVOID LARGE QUICK POWER CHANGES AT HIGH ALTITUDES
COMMENTS
- The OVHT alert light will remain as long as overtemperature is detected in the duct. It is
not inhibited when in MAN mode.
- When alert disappears, controlling COMPT TEMP manually is required.
- If alert does not disappear, the temperature control valve is jammed open. Pack valve
has to be closed.
R CABIN ALTITUDE
ALERT
CONDITION
Cabin altitude > 7175 ft
VISUAL
- MC light flashing amber
- CAB ALT amber message on EWD
AURAL
SC
PROCEDURE
CABIN ALTITUDE
CABIN ALTITUDE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MONITOR
Mod 5948 + 6521
2.05.08
PROCEDURES FOLLOWING FAILURE
P7
AIR
001
FEB 12
AA
EXCESS CAB ALT
ALERT
CONDITION
Cabin altitude above 10000 ft.
VISUAL
- MW light flashing red
- EXCESS CAB ALT red message
on EWD + red reverse video ALT
flashing on air cabin SD page.
AURAL
CRC
PROCEDURE
EXCESS CAB ALT
R
R
CABIN PRESS IND . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK
J If rapid decompression
EMERGENCY DESCENT procedure (2.04.05 ) . . . . . . . . . . . . . . . . . . . APPLY
J If cabin altitude above 10 000 ft
MAN RATE KNOB . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9 O’CLOCK
CAB PRESS MODE SEL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MAN
MAN RATE KNOB . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . DECREASE
J If EXCESS CAB ALT persists
CREW OXYGEN MASKS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON
CREW COMMUNICATIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ESTABLISH
OXYGEN PAX SUPPLY . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . AS RQD
OXYGEN PRESSURE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK
DESCENT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . AS RQD / MEA
COMMENTS
- Check first for pressurization system fault. If system fault, apply appropriate procedure
(manual regulation). If no abnormal indication, start descent.
Mod 5948
2.05.08
PROCEDURES FOLLOWING FAILURE
P8
AIR
001
FEB 12
AA
AUTO PRESS FAULT
ALERT
CONDITION
Air auto press amber light on
EWD
VISUAL
- MC light flashing amber
- FAULT amber light on MAN
pushbutton
- AUTO PRESS displayed amber on
the cabin SD page
AURAL
SC
PROCEDURE
AUTO PRESS FAULT
MAN RATE KNOB . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9 O’CLOCK
CAB PRESS MODE SEL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MAN
MAN RATE KNOB . . . . . . . . . . . . . . . . . . . . . . . . AS RQD TO SET CABIN RATE
R
R
R
R
F Before descent
J If CAB ALT above landing elevation
MAN RATE KNOB . . . . . . . . . . . . . . . . . . . . . . DECREASE 400 FT/MN DN
J If CAB ALT below landing elevation
MAN RATE KNOB . . . . . . . . . . . . . . . . . . INCREASE 1000 FT/MN UP MAX
F When CAB ALT = landing elevation
MAN RATE KNOB . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9 O’CLOCK
COMMENTS
No comment.
Mod 5948
2.05.08
PROCEDURES FOLLOWING FAILURE
P9
AIR
AA
100
FEB 12
CAB ∆P
ALERT
CONDITION
Cabin ∆P> 6.25 PSI
Cabin ∆P< - 0.3 PSI
VISUAL
- MC light flashing amber
- CAB ∆P amber message on EWD
AURAL
SC
PROCEDURE
CABIN ∆P
CABIN ∆P . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MONITOR
Mod 5948 + 6521
2.05.08
PROCEDURES FOLLOWING FAILURE
P 10
AIR
AA
100
FEB 12
NEGATIVE CAB ∆P
ALERT
CONDITION
CAB ∆P < - 0.5 PSI
VISUAL
- MW light flashing red
- NEGATIVE CABIN ∆P red message on
EWD
AURAL
CRC
PROCEDURE
NEGATIVE CAB ∆P
MAN RATE KNOB . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9 O’CLOCK
CAB PRESS MODE SEL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MAN
MAN RATE KNOB . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MAX DECREASE
A/C RATE OF DESCENT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ADJUST
Mod 5948 + 6521
2.05.08
PROCEDURES FOLLOWING FAILURE
P 11
AIR
001
FEB 12
AA
EXCESS CAB ∆P
ALERT
CONDITION
Differential pressure exceeds
6.35 PSI
VISUAL
AURAL
- MW light flashing red
- EXCESS CAB ∆P red message on
EWD
- The ∆P value is displayed white on
red bacckground on the Cabin SD
page.
- DIFF PRESS local IND exceeds
6.6 PSI
CRC
PROCEDURE
EXCESS CAB ∆P
R
R
MAN RATE KNOB . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9 O’CLOCK
CAB PRESS MODE SEL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MAN
MAN RATE KNOB . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MAX INCREASE
J If Excess cab ∆P persists
DESCENT TO A COMPATIBLE FL / MEA . . . . . . . . . . . . . . . . . . . . . INITIATE
Mod 5948
2.05.08
PROCEDURES FOLLOWING FAILURE
P 12
AIR
001
FEB 12
AA
AVIONICS VENT EXHAUST MODE FAULT
ALERT
CONDITION
Underspeed or overheat of
extract fan (T > 90_C / 194_F)
VISUAL
AURAL
- MC light flashing amber
- AIR VENT EXH amber message
on EWD
- Exhaust vent is displayed amber on
the Cabin SD page.
- EXHAUST MODE FAULT amber
light on overhead panel
SC
PROCEDURE
AVIONICS VENT EXHAUST MODE FAULT
EXHAUST MODE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OVBD
COMMENTS
- EXHAUST MODE to OVBD position controls the OVBD valve to partially open and
stops the extract fan; ventilation air is then discharged overboard instead of being
directed to the underfloor valve. Ventilation is ensured by ∆P between cabin and
outside air.
Mod 5948
2.05.08
PROCEDURES FOLLOWING FAILURE
P 13
AIR
001
FEB 12
AA
OVBD VALVE FAULT
ALERT
CONDITION
OVBD valve position not
corresponding with aircraft
condition
VISUAL
- MC light flashing amber.
- AIR OVBD amber message on
EWD.
- FAULT amber light on overhead
panel.
- Associated OVBD indications in
amber on ACW/HYD SD page.
AURAL
SC
PROCEDURE
OVBD VALVE FAULT
R
R
CAUTION : Do not select OVBD valve FULL OPEN if CAB ∆P above 1 PSI.
J If engine 1 running, in flight or on ground
OVBD VALVE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FULL CLOSE
J If engine 1 out , on ground
OVBD VALVE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FULL OPEN
COMMENTS
- The OVBD VALVE should automatically close 2 minutes after engine 1 start (OIL LO
PRESS signal). If it remains open after FULL CLOSE selection, maintenance action is
required.
- FULL CLOSE / FULL OPEN selection overrides OVBD selection.
Mod 5948
2.05.09
PROCEDURES FOLLOWING FAILURE
P1
DE/ANTI ICE
001
FEB 12
AA
R AIRFRAME AIR BLEED FAULT
ALERT
CONDITION
Low pressure in the
de-- icing common air
manifold (P < 14 PSI )
- or Overtemperature (T >
230_C) upstream the
pressure regulating
valve
VISUAL
- MC light flashing amber
- A--ICING BLEED amber message on
EWD
- AFR AIR BLEED FAULT amber light
on overhead panel
AURAL
SC
PROCEDURE
R
R
AIRFRAME AIR BLEED FAULT
LEAVE AND AVOID ICING CONDITIONS
AFR AIR BLEED . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF
J If DE- ICING ENG FAULT light illuminate after 6 s
DE-- ICING ENG affected side . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF
AFR AIR BLEED . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON
AFR AIR BLEED light . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK EXTINGUISH
J If DE- ICING ENG FAULT light does not illuminate on any side
DE-- ICING AIR FRAME FAULT procedure (2.05.09) . . . . . . . . . . . . . . . . APPLY
Mod 5948
2.05.09
PROCEDURES FOLLOWING FAILURE
P2
DE/ANTI ICE
001
FEB 12
AA
R DE- ICING AIRFRAME FAULT
ALERT
VISUAL
CONDITION
Distribution valve output
controlled open but no
downstream pressure detected
- or Distribution valve output
controlled closed but
downstream pressure detected
- MC light flashing amber
- A--ICING FRAME amber message
on EWD
- AIRFRAME is displayed amber on
Memo Panel
- Associated FAULT amber light on
overhead panel
AURAL
SC
PROCEDURE
R
R
DE- ICING AIRFRAME FAULT
LEAVE AND AVOID ICING CONDITIONS
IAS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . NOT LESS THAN Vmin OPS + 10 KT
V APP . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . NOT LESS THAN V REF + 10 KT
SPD TGT MAN . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . USE
DE-- ICING AIR FRAME . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF
J If in icing conditions
LDG DISTANCE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MULTIPLY BY 1.15
Note : Refer to Part 4 to determine SPEEDS and LDG DIST
STEEP SLOPE APPROACH (≥4.5_) . . . . . . . . . . . . . . . . . . . . . . PROHIBITED
Mod 5948
2.05.09
PROCEDURES FOLLOWING FAILURE
P3
DE/ANTI ICE
001
FEB 12
AA
DE- ICING MODE SEL FAULT
ALERT
CONDITION
Improper De-- Icing cycles
schedule
VISUAL
AURAL
- MC light flashing amber
- A--ICING SEL amber message on
EWD
- DE--ICING MODE SEL FAULT
amber light on overhead panel
- AIRFRAME and ENG 1 and 2 are
displayed amber on Memo Panel
SC
PROCEDURE
DE- ICING MODE SEL FAULT
R
R
DE-- ICING MODE SEL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OVRD
MONITOR DE-- ICING
J In case of engine flame out
OVRD . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . RELEASE
COMMENTS
- The OVRD mode allows to operate engines and airframe dual distribution valves in
case of engine boots primary control failure.
- DE-- ICING MODE SEL OVRD must be used if there is evidence of boots cycling
malfunctionning even if DE-- ICING MODE SEL FAULT is not illuminated.
- When DE-- ICING MODE SEL is selected to OVRD, ENG and AIR FRAME FAULT lights
are inhibited and boots cycling operated only according to FAST mode.
- In case of DE-- /ANTI-- ICING ENG FAULT and after a prolonged flight with considerable
accretion, it is possible that when setting the DE-- ICING MODE SEL to OVRD, the
engine may ingest the build up ice and a flame out could occur. As the functionning of
this device is sequential (i.e. the two engines are not concerned at the same time), it is
suggested to release the DE-- ICING MODE SEL pushbutton before the same
phenomenon occurs on the second engine.
Mod 5948
2.05.09
PROCEDURES FOLLOWING FAILURE
P4
DE/ANTI ICE
001
FEB 12
AA
R DE- \ ANTI- ICING MODE SEL AUTO FAULT
ALERT
CONDITION
MFC 1B or 2B and/or ADC
failure
- or Discrepancy between outputs
VISUAL
- MC light flashing amber
- A--ICING AUTO amber message
on EWD
- FAULT amber light on overhead
panel
AURAL
SC
PROCEDURE
R
DE- \ ANTI- ICING MODE SEL AUTO FAULT
R
DE-- \ ANTI-- ICING MODE SEL AUTO . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MAN
DE-- ICING and ANTI-- ICING MANUAL MODE PBs
ACCORDING TO CURRENT SAT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . SELECT
R
COMMENTS
- In case of FAULT or discrepancy between ADCs information and until pitlot’s action:
. High speed boots activation is selected (airframe + engines)
. High power cycle (20/60) is selected (propellers)
- OVRD gaurded pushbutton has to be used in case of cycle anomaly, indicated by its
own FAULT light.
ICE DETECT FAULT
ALERT
CONDITION
Ice detector failure
VISUAL
- MC light flashing amber
- A--ICING DETECT amber
message on EWD
AURAL
SC
PROCEDURE
ICE DETECT FAULT
ICE ACCRETION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MONITOR IEP
Mod 5948
2.05.09
PROCEDURES FOLLOWING FAILURE
P5
DE/ANTI ICE
001
FEB 12
AA
DE- /ANTI- ICING ENG 1(2) FAULT
ALERT
VISUAL
CONDITION
Distribution valve output
controlled open but no
downstream pressure detected
- or Distribution valve output
controlled closed but
downstream pressure detected
- MC light flashing amber
- ANTI ICING ENG 1(2) amber
message on EWD
- Associated FAULT amber light on
overhead panel
AURAL
SC
PROCEDURE
DE- /ANTI- ICING ENG 1(2) FAULT
R
LEAVE AND AVOID ICING CONDITIONS
ENG PARAMETERS affected side . . . . . . . . . . . . . . . . . . . . . . . . . . . MONITOR
DE-- /ANTI-- ICING ENG affected side . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF
COMMENTS
- Very large ice accretion on the engine air intake may generate an engine flame out
when the ice breaks free.
- Several cases of MFC failure may generate an engine DE-- ICING FAULT alert prior
DE-- ICING MODE SEL FAULT. Engine DE-- ICING may be recovered when selecting
DE-- ICING MODE SEL OVRD.
Mod 5948
2.05.09
PROCEDURES FOLLOWING FAILURE
P6
DE/ANTI ICE
001
FEB 12
AA
ANTI- ICING PROP 1(2) FAULT
ALERT
CONDITION
VISUAL
One or more blade heating units - MC light flashing amber
inoperative
- A--ICING PROP 1(2) amber
message on EWD + amber
indication PROP 1 (2) on Memo
display.
- Associated FAULT amber light on
overhead panel
AURAL
SC
PROCEDURE
ANTI- ICING PROP 1(2) FAULT
R
LEAVE AND AVOID ICING CONDITIONS
ANTI-- ICING PROP affected side . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF
J If propeller unbalance due to ice becomes excessive
CL 1 + 2 . . . . . . . . . . . . . MOVE TO 100% OVRD FOR AT LEAST 5 MINUTES
COMMENTS
- If propeller unbalance due to ice becomes significant periodically moving both CL to
100% OVRD will modify centrifugal forces allowing ice elimination.
Mod 5948
2.05.09
PROCEDURES FOLLOWING FAILURE
P7
DE/ANTI ICE
001
FEB 12
AA
ANTI- ICING HORNS 1(2) FAULT
ALERT
CONDITION
VISUAL
AURAL
Power loss on a horn anti-- icing
unit
- MC light flashing amber
- A--ICING HORNS 1(2) amber
message on EWD
- HORN 1(2) are displayed amber on
Memo Panel
- AssociatedFAULT amber light on
overhead panel
SC
PROCEDURE
ANTI- ICING HORNS 1(2) FAULT
R
LEAVE AND AVOID ICING CONDITIONS
ANTI ICING HORNS affected side . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF
J If in icing conditions, every 5 minutes
FLIGHT CONTROLS . . . . . . . . . . . . . . . CHECK FREEDOM OF MOVEMENT
COMMENTS
- One unit controls rudder and left elevator horns when the other controls ailerons and
right elevator horns.
- Checking of flight controls will prevent ice accretion between flight controls and related
fixed parts of aircraft structure which could generate flight control jamming.
Mod 5948
2.05.09
PROCEDURES FOLLOWING FAILURE
P8
DE/ANTI ICE
AA
001
APR 11
SIDE WINDOW / WINDSHIELD HTG FAULT
ALERT
CONDITION
VISUAL
AURAL
Loss of side window heating
- MC light flashing amber
- A--ICING WINDOWS amber
message on EWD
- SIDE WINDOWS is displayed
amber on Memo Panel
- Associated FAULT amber light on
overhead panel
SC
Loss of windshield heating
- MC light flashing amber
- A--ICING L(R) WSHLD amber
message on EWD
- Associated FAULT amber light on
overhead panel
SC
PROCEDURE
SIDE WINDOW / WINDSHIELD HTG FAULT
SIDE WINDOW / WINDSHIELD HTG affected side . . . . . . . . . . . . . . . . . . . . OFF
Mod 5948
2.05.09
PROCEDURES FOLLOWING FAILURE
P9
DE/ANTI ICE
100
FEB 12
AA
PROBES HTG FAULT
ALERT
CONDITION
Power loss on a probe
anti-- icing unit
R
VISUAL
- MC light flashing amber
- A--ICING (PIT CPT) (PIT F/O) (PIT
SBY) (TAT CPT) (TAT F/O)
amber message on EWD
- A-- ICING ALPHA, ALPHAs amber
messages on EWD.
- Associated FAULT amber light on
overhead panel
AURAL
SC
PROCEDURE
PROBES HTG FAULT
R
R
R
J If one ALPHA PROBE HTG fault
STICK PUSHER / SHAKER . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MONITOR
J If ALPHA PROBE HTG 1 + 2 loss
STICK PUSHER / SHAKER . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF
STICK PUSHER / SHAKER FAULT procedure (2.05.06) . . . . . . . . . . . . . APPLY
J If (Pitot / Static / TAT) affected side PROBE HTG fault
ADC affected side switching . . . . . . . . . . . . . . . . . . . . . ALTERNATE SYSTEM
FD MODES . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . RESTORE IF LOST
PERIODICALLY COMPARE IAS & BARO ALT WITH IESI
J If PROBE HTG STBY fault
IESI IAS and BARO ALT indications . . . . . . . . . . . . . . . . . . . . . . DISREGARD
COMMENTS
- Erroneous indications may be displayed on associated equipment (CM1, CM2 or IESI,
TAT/SAT) due to loss of probe heating.
Mod 5948 + 6521
2.05.10
PROCEDURES FOLLOWING FAILURE
P1
AUTOPILOT
001
FEB 12
AA
AILERON MISTRIM
or EXCESSIVE LATERAL TRIM REQUIRED
or ABNORMAL FLIGHT CHARACTERISTICS
ALERT
CONDITION
When the aileron servo motor
reaches a second torque value
threshold
VISUAL
- MC light flashing amber
- AILERON MISTRIM amber
message on EWD + AILERON
MISTRIM amber message on
FMA
AURAL
SC
PROCEDURE
AILERON MISTRIM
or EXCESSIVE LATERAL TRIM REQUIRED
or ABNORMAL FLIGHT CHARACTERISTICS
R
R
R
FLIGHT CONTROLS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . HOLDING FIRMLY
AP . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . DISCONNECT
Note : FLY MANUALLY UNTIL ADJUSTING THE AILERON TRIMS.
Note : The autopilot may be reengaged after adjustment of the aileron trims.
COMMENTS
- Ailerons forces may be affected by external conditions such as
. prolonged exposure to severe icing
. de-- /anti-- icing hold over time exceeded
Mod 5948
2.05.10
PROCEDURES FOLLOWING FAILURE
P2
AUTOPILOT
001
FEB 12
AA
PITCH MISTRIM
ALERT
CONDITION
When the pitch servo motor
reaches a second torque value
threshold
VISUAL
- MC light flashing amber
- PITCH MISTRIM amber message
on EWD + PITCH MISTRIM
amber message on FMA
AURAL
SC
PROCEDURE
PITCH MISTRIM
R
R
R
FLIGHT CONTROLS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . HOLDING FIRMLY
AP . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . DISCONNECT
Note : FLY MANUALLY UNTIL ADJUSTING THE PITCH TRIM.
Note : AP may be reengaged after adjustment of the pitch trims.
COMMENTS
- Elevator hinge moment may be affected by external conditions.
- From experience, the most likeky cause appears to be take off with ice remaining on the
tail plane (de-- /anti-- icing hold overtime exceeded).
Severe icing may also be a factor.
RUDDER MISTRIM
ALERT
CONDITION
When the rudder servo motor
reaches a second torque value
threshold
VISUAL
- MC light flashing amber
- RUDDER MISTRIM amber
message on EWD + RUDDER
MISTRIM amber message on
FMA
AURAL
SC
PROCEDURE
RUDDER MISTRIM
R
R
R
FLIGHT CONTROLS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . HOLDING FIRMLY
YD . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . DISCONNECT
Note : FLY MANUALLY UNTIL ADJUSTING THE RUDDER TRIM
Note : AP & YD may be reengaged after adjustment of the rudder trims.
Mod 5948
2.05.10
PROCEDURES FOLLOWING FAILURE
P3
AUTOPILOT
100
FEB 12
AA
PITCH TRIM FAIL
ALERT
CONDITION
VISUAL
Displayed when the AFCS is not - MC light flashing amber
able to command the pitch trim - AP PITCH TRIM amber message
and the AP is engaged
on EWD + AP PITCH TRIM FAIL
amber message on FMA
AURAL
SC
PROCEDURE
AP YAW TRIM FAIL
R
AP PITCH TRIM FAIL
R
FLIGHT CONTROLS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . HOLDING FIRMLY
AP . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . DISCONNECT
PITCH TRIM . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ADJUST
FLY MANUALLY
R
R
ALERT
CONDITION
Yaw trim fail
VISUAL
- MC light flashing amber
- AP YAW TRIM amber message on
EWD
AURAL
SC
PROCEDURE
R
YAW AUTOTRIM FAIL
F When RETRIM message on FMA
FLIGHT CONTROLS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . HOLDING FIRMLY
YD . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . DISCONNECT
Note : FLY MANUALLY UNTIL ADJUSTING THE RUDDER TRIM
Note : YD & AP may be reengaged after adjustment of the rudder trim.
Mod 5948 + 6521
2.05.11
PROCEDURES FOLLOWING FAILURE
P1
AIRCRAFT PERFORMANCE MONITORING
AA
For APM PROCEDURES, refer to FCOM 2.02.21.
Mod 5948
001
APR 11
2.05.12
PROCEDURES FOLLOWING FAILURE
P1
001
AVIONICS
FEB 12
AA
AUDIO SEL FAULT
ALERT
CONDITION
RCAU processing
board failure or
power loss
VISUAL
AURAL
- MC light flashing amber
- AUDIO SEL CAPT (F/0) amber
message on EWD
- AUDIO SEL FAULT amber light on
associated side panel
SC
PROCEDURE
AUDIO SEL FAULT
AUDIO SEL affected side . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ALTN
COMMENTS
- In ALTN mode, affected crew station is connected directly and only to :
. VHF 1 if CM1 station is affected
. VHF 2 if CM2 station is affected
R RMS 1 + 2 FAULT
ALERT
CONDITION
Both RMS fail
VISUAL
- MC light flashing amber
- RMS 1+2 amber message on EWD
AURAL
SC
PROCEDURE
R
RMS 1 + 2 FAULT
R
R
R
VHF1-- VOR / ILS1 TUNING . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . USE IESI
Note : Loss of XPDR/TCAS TUNING.
Note : Last tuned freq saved : VHF 2, VOR 2, DME 1 + 2, ADF 1+ 2
Note: ILS CAT 2 IS PROHIBITED
COMMENTS
- Only VHF1 and V/ILS can be tuned via IESI (frequencies and CRS for VOR).
Mod 5948
2.05.12
PROCEDURES FOLLOWING FAILURE
P2
001
AVIONICS
NOV 14
AA
ONE AHRS FAIL
ALERT
CONDITION
Loss of one AHRS
VISUAL
AURAL
- MC light flashing amber
- AHRS amber message on EWD
SC
PROCEDURE
ONE AHRS FAIL
R
AFFECTED ATT/ HDG switching . . . . . . . . . . . . . . . . . . . . . . ALTERNATE SYS
FD MODES . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CONFIRM
AP . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . AS RQD
WHEN WINGS LEVELED :
Periodically compare PFD with IESI
CROSSCHECK HDG / TK / STBY-- COMPASS
CAUTION : Use of AP is prohibited below 1000 ft AGL..
COMMENTS
- AP (if engaged) disconects, can be reengaged once the valid AHRS selected.
AHRS 1 + 2 LOSS
ALERT
CONDITION
Loss of both AHRS
VISUAL
AURAL
- MC light flashing amber
- AHRS 1+ 2 amber message on EWD
SC
PROCEDURE
AHRS 1+ 2 LOSS
R
R
PF . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CAPT
IESI . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . USE
STBY COMPASS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . USE
AIRCRAFT . . . . . . . . . . . . . . . . . . . . . . . . . . . . STABILIZE SPEED AND LEVEL
VISUAL FLYING CONDITIONS . . . . . . . . . . . . . . . . . . . MAINTAIN IF POSSIBLE
ATC . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . NOTIFY
FMS PROG PAGE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . USE
Note : PFD ATT and HDG are lost. ILS deviations and ADF BRG are valid
Note : Terrain picture display is available.
Mod 5948
2.05.12
PROCEDURES FOLLOWING FAILURE
P3
001
AVIONICS
FEB 12
AA
AHRS NOT ALIGN
ALERT
CONDITION
AHRS not aligned
VISUAL
AURAL
- MC light flashing amber
- AHRS NOT ALIGN amber message on
EWD
SC
PROCEDURE
AHRS NOT ALIGN
R
R
R
R
J If AHRS not aligned on ground
AIRCRAFT . . . . . . . . . . . . . . . . . . . . . . . STOP UNTIL ALERT DISAPPEARS
J If AHRS not aligned in flight
AHRS FAULT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . IDENTIFIED
AIRCRAFT . . . . . . . . . . . . . . . . STABILIZE SPEED AND LEVEL DURING 90s
J If alert disappears
AP may be re-- engaged
J If AHRS NOT ALIGN persists after 3 minutes
ONE AHRS FAIL procedure(2.05.12) . . . . . . . . . . . . . . . . . . . . . . . . APPLY
Mod 5948
2.05.12
PROCEDURES FOLLOWING FAILURE
P4
001
AVIONICS
AA
NOV 14
ADC FAIL
ALERT
CONDITION
One ADC fail
VISUAL
- MC light flashing amber
- ADC amber message on EWD
AURAL
SC
PROCEDURE
ADC FAIL
R
AFFECTED ADC switching . . . . . . . . . . . . . . . . . . . . . . . . ALTERANATE SYS
PF MODES . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CONFIRM
AP . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . AS RQD
PERIODICALLY COMPARE IAS / ALT ON PFDs WITH IESI
CAUTION : Use of AP is prohibited below 1000 ft AGL
CAUTION : Baro setting is available only on non affected side
J If ADC 1 lost
LANDING ELEVATION . . . . . . . . . . . . . . . . . . SET PRESSURE ALTITUDE
COMMENTS
R - AP (if engaged) disconnects, can be reengaged once the valid ADC is selected.
ADC 1 + 2 LOSS
ALERT
CONDITION
Loss of both ADC
VISUAL
- MC light flashing amber
- ADC 1 + 2 amber message on EWD
AURAL
SC
PROCEDURE
ADC 1+2 LOSS
PF . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CAPT
IESI . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . USE
MAN RATE KNOB . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9 O’CLOCK
CAB PRESS MODE SEL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MAN
AUTO PRESS FAULT procedure(2.05.08) . . . . . . . . . . . . . . . . . . . . . . . APPY
ENGINE PARAMETERS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MONITOR
TCAS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . STBY
GPWS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF
TLU . . . . . . . . . . . . . . . . . . . . . . . . . . . . HI or LO SPD ACCORDING TO IAS
TLU FAULT procedure(2.05.06) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . APPLY
Note : DE-- /ANTI-- ICING auto mode selection is lost
Mod 5948
2.05.12
PROCEDURES FOLLOWING FAILURE
P5
AVIONICS
AA
LEFT INTENTIONALLY BLANK
Mod 5948
001
APR 11
2.05.12
PROCEDURES FOLLOWING FAILURE
P6
AVIONICS
001
NOV 14
AA
ATTITUDE DISAGREE
ALERT
CONDITION
Attitude disagree
VISUAL
AURAL
- MC light flashing amber
- ATT DISAGREE amber message on EWD
+ amber CHECK ATT on the PFDs
SC
PROCEDURE
ATTITUDE DISAGREE
R
BOTH PFD - IESI ATT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CROSSCHECK
AFFECTED AHRS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . IDENTIFY
AFFECTED ATT HDG switching . . . . . . . . . . . . . . . . . . . . . . . . ALTERNATE SYS
FD MODES . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CONFIRM
AP . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . AS RQD
CAUTION : Use of AP is prohibited below 1000 ft AGL
PERIODICALLY COMPARE ATT ON FPDs WITH IESI
PERIODICALLY COMPARE HDG / TK / STBY-- COMPASS
Mod 5948
2.05.12
PROCEDURES FOLLOWING FAILURE
P7
001
AVIONICS
AA
NOV 14
HEADING DISAGREE
ALERT
VISUAL
CONDITION
Heading disagree
- MC light flashing amber
- HDG DISAGREE amber message on EWD
+ amber CHECK HDG on PFDs
AURAL
SC
PROCEDURE
HEADING DISAGREE
R
WHEN WINGS LEVELED:
HDG / TK / STBY-- COMPASS . . . . . . . . . . . . . . . . . . . . . . . . . . CROSSCHECK
AFFECTED AHRS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . IDENTIFY
AFFECTED ATT HDG switching . . . . . . . . . . . . . . . . . . . . . . . . ALTERNATE SYS
FD MODES . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CONFIRM
AP . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . AS RQD
CAUTION : Use of AP is prohibited below 1000 ft AGL
PERIODICALLY COMPARE ATT ON PFDs WITH IESI
PERIODICALLY COMPARE HDG / TK / STBY-- COMPASS
ALTITUDE DISAGREE
ALERT
CONDITION
Altitude disagree
VISUAL
- MC light flashing amber
- ALT DISAGREE amber message on
EWD + amber CHECK ALT on PFDs
AURAL
SC
PROCEDURE
ALTITUDE DISAGREE
BOTH PFD IESI ALT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CROSSCHECK
AFFECTED ADC . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . IDENTIFY
AFFECTED ADC switching . . . . . . . . . . . . . . . . . . . . . . . . . . . ALTERNATE SYS
FD MODES . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CONFIRM
AP . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . AS RQD
CAUTION : Use of AP is prohibited below 1000 ft AGL
PERIODICALLY COMPARE IAS / ALT ON PFDs WITH IESI
Mod 5948
2.05.12
PROCEDURES FOLLOWING FAILURE
P8
001
AVIONICS
NOV 14
AA
IAS DISAGREE
ALERT
CONDITION
IAS disagree
VISUAL
- MC light flashing amber
- IAS DISAGREE amber message on EWD
+ amber CHECK IAS on PFDs
AURAL
SC
PROCEDURE
IAS DISAGREE
R
BOTH PFD IESI IAS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CROSSCHECK
AFFECTED ADC . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . IDENTIFY
AFFECTED ADC switching . . . . . . . . . . . . . . . . . . . . . . . . . . . ALTERNATE SYS
FD MODES . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CONFIRM
AP . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . AS RQD
CAUTION : use of AP is prohibited below 1000 ft AGL
PERIODICALLY COMPARE IAS / ALT ON PFDs WITH IESI
J If IAS discrepancy between PFD and IESI
Refer to UNRELIABLE AIRSPEED INDICATION procedure(2.04.05)
VHF 1+2 LOSS
ALERT
CONDITION
VHF 1 + 2 fail
VISUAL
- MC light flashing amber
- VHF 1+2 amber message on EWD
AURAL
SC
PROCEDURE
VHF 1 + 2 LOSS
XPDR . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . TRANSMIT CODE 7600
Mod 5948
2.05.12
PROCEDURES FOLLOWING FAILURE
P9
100
AVIONICS
FEB 12
AA
DU DISCREPANCY
ALERT
CONDITION
DU with corrupted
R parameters
VISUAL
- MC light flashing amber
- DUs DISCREPANCY amber message
on EWD
AURAL
SC
PROCEDURE
R
DU DISCREPANCY
DU FORMAT SHOWS CORRUPTED PARAMETERS
EACH DU . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . RESET
F After DU RESET
J If DU DISCREPANCY between PFD and IESI
AFFECTED DU . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF
J If DU DISCREPANCY disappears
RESUME NORMAL OPERATIONS
Mod 5948 + 6521
2.05.12
PROCEDURES FOLLOWING FAILURE
P 10
100
AVIONICS
FEB 12
AA
ONE DU TEMP HI
ALERT
CONDITION
R
One DU temp high
VISUAL
- MC light flashing amber
- DUs TEMP HI amber message on EWD
AURAL
SC
PROCEDURE
R
ONE DU TEMP HI
R
MFC 2A . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . RESET
SEVERAL DUs TEMP HI
ALERT
CONDITION
R
2 DUs temp high
VISUAL
- MC light flashing amber
- DUs T HI amber message on EWD
AURAL
SC
PROCEDURE
R
SEVERAL DUs TEMP HI
MFC 2 A . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . RESET
J If alert persists after 15 mn
OVBD VALVE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . AUTO
AVIONICS VENT EXHAUST MODE . . . . . . . . . . . . . . . . . . . . . . . . . . . OVBD
MAINTENANCE ACTION IS REQUIRED
J In case of one DU loss
LAND ASAP
Note : Several DU may be lost
Mod 5948 + 6521
2.05.12
PROCEDURES FOLLOWING FAILURE
P 11
100
AVIONICS
FEB 12
AA
AVNX FWS SGL CH
ALERT
CONDITION
One of FWA is
detected faulty
VISUAL
AURAL
- MC light flashing amber
- FWS SGL CH amber message on EWD
SC
PROCEDURE
AVNX FWS SGL CH
R
R
NO CREW ACTION REQUIRED
MAINTENANCE ACTION IS REQUIRED
AVNX SGL SWITCH
ALERT
CONDITION
only one switch is
R available
VISUAL
- MC light flashing amber
- AVNX SGL SWITCH amber message
on EWD
PROCEDURE
AVNX SGL SWITCH
R
R
NO CREW ACTION REQUIRED
MAINTENANCE ACTION IS REQUIRED
Mod 5948 + 6521
AURAL
SC
2.05.12
PROCEDURES FOLLOWING FAILURE
P 12
001
AVIONICS
FEB 12
AA
R FWS 1 + 2 LOSS
ALERT
CONDITION
Both CPM are
reported faulty
VISUAL
- The message is displayed on a blank
black page on the Procedure Window
AURAL
SC
PROCEDURE
R
R
FWS 1 + 2 LOSS
J If FPLN NOT AVAILABLE on ND
AVNX SWITCH 1+ 2 LOSS procedure(2.05.12) . . . . . . . . . . . . . . . . . . . APPLY
J If FPLN available on ND
J If TRIM indication not available on EWD
AVNX CPM 1+ 2 LOSS procedure(2.05.12) . . . . . . . . . . . . . . . . . . . APPLY
J If TRIM indication available on EWD
CABIN PRESS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MONITOR
ENGINE PARAMETERS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MONITOR
LOST EQUIPMENT LIST . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK
Note: In case of caution or warning monitor local alerts.
R
FWS 1 + 2 LOSS LOST EQUIPMENT LIST
FWS CAUTION alerts on EWD
FWS WARNING alerts on EWD
MASTER WARNINGS Lost
ENG 1(2) OUT
ENG 1+ 2 OUT
ELEC DC GEN 1+ 2
PROP BRK
ENG 1(2) OIL
EXCESS CAB ALT
EXCESS CAB delta P
NEGATIVE CAB delta P
Mod 5948
FWS Electronic Checklists on EWD
2.05.12
PROCEDURES FOLLOWING FAILURE
P 13
001
AVIONICS
FEB 12
AA
AVNX SWITCH 1+2 LOSS
ALERT
VISUAL
CONDITION
AURAL
AVNX switch are lost - The message is displayed on a blank
black page on the Procedure Window
SC
PROCEDURE
AVNX SWITCH 1 + 2 LOSS
R
LAND ASAP
ENGINE PARAMETERS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MONITOR
ICE DETECT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MONITOR IEP
SPEEDS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MONITOR
RMS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . AVAILABLE ON MCDU and IESI ONLY
VOR/ILS 1 TUNING . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . USE IESI
LOST EQUIPMENT LIST . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK
R
AVNX SWITCH 1 + 2 LOSS LOST EQUIPMENT LIST
AP/YD
FD
FWS
FMS
APM Messages
RA Display
TCAS Display
TAWS
WEATHER RADAR
DH/MDA
R
- SPD TGT : AUTO / MAN
- All speeds computed by the FMS lost (on
ground : V1, VR, V2 in flight: VmLB0,
VmHB, NORMAL, VMHB ICING SPEED
BUGS, Vmin OPS, VPROT, VMIN SPEED
BANDS)
ALL NAV MEANS EXCEPT VOR/ILS1
Prop1 Anti Icing
Prop2 Anti Icing
Mod 5948
WARNING alerts:
PITCH DISCONNECT
NAC OVHT
SMOKES
FLAPS UNLOCK
OIL LO PR
EXCESS CAB DP
EXCESS CAB ALT
FWS CAUTION alerts on EWD
FWS WARNING alerts on EWD
FWS Electronic Checklists on EWD
2.05.12
PROCEDURES FOLLOWING FAILURE
P 14
100
AVIONICS
FEB 12
AA
AVNX CPM 1 LOSS
ALERT
CONDITION
CPM 1 fail
VISUAL
- MC light flashing amber
- AVNX CPM 1 amber message on EWD
AURAL
SC
PROCEDURE
AVNX CPM 1 LOSS
R
R
LEAVE AND AVOID ICING CONDITIONS
ANTI/DE-- ICING MODE SEL AUTO FAULT procedure(2.05.09) . . . . . . . . . . APPLY
J If icing conditions
ANTI-- ICING PROP 1(2) FAULT procedure(2.05.09) . . . . . . . . . . . . . . . . . . APPLY
TLU . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . HI or LO SPD ACCORDING TO IAS
ENG PARAMETERS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MONITOR
LANDING ELEVATION . . . . . . . . . . . . . . . . . . . . . . . SET PRESSURE ALTITUDE
LOST EQUIPMENT LIST . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .CHECK
LOST FUNCTION/EQPT LIST see FCOM par 1.01.40
Mod 5948 + 6521
2.05.12
PROCEDURES FOLLOWING FAILURE
P 15
001
AVIONICS
FEB 12
AA
AVNX CPM 2 LOSS
ALERT
CONDITION
CPM 2 fail
VISUAL
- MC light flashing amber
- CPM 2 amber message on EWD
AURAL
SC
PROCEDURE
AVNX CPM 2 LOSS
R
LEAVE AND AVOID ICING CONDITIONS
ANTI/DE-- ICING MODE SEL AUTO FAULT procedure (2.05.09) . . . . . . . . . APPLY
J If icing conditions
ANTI-- ICING PROP 1(2) FAULT procedure (2.05.09) . . . . . . . . . . . . . . . . . APPLY
TLU . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . HI or LO SPD ACCORDING TO IAS
ENG PARAMETERS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MONITOR
LOST EQUIPMENT LIST . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .CHECK
LOST FUNCTION/EQPT LIST see FCOM par 1.01.40
Mod 5948
2.05.12
PROCEDURES FOLLOWING FAILURE
P 16
001
AVIONICS
FEB 12
AA
AVNX CPM 1+2 LOSS
ALERT
CONDITION
CPM 1+2 fail
VISUAL
- MC light flashing amber
- CPM 1+2 amber message on EWD
AURAL
SC
PROCEDURE
AVNX CPM 1 + 2 LOSS
R
R
R
LEAVE AND AVOID ICING CONDITIONS
OPERATIONAL SPEEDS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . USE QRH
Note : Refer to QRH part 4 to determine SPEEDS
ICE DETECT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MONITOR IEP
LAND ASAP
ANTI/DE-- ICING MODE SEL AUTO FAULT procedure (2.05.09) . . . . . . . . . APPLY
JIf icing conditions
ANTI-- ICING PROP 1(2) FAULT procedure (2.05.09) . . . . . . . . . . . . . . . . . APPLY
DE-- ICING . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MONITOR OVERHEAD PANEL
MAN RATE KNOB . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9 O’Clock
CAB PRESS MODE SEL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MAN
DESCENT TOWARD . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FL100 / MEA
MAN RATE KNOB . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 10 O’Clock
TLU . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . HI or LO SPD ACCORDING TO IAS
ENG PARAMETERS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MONITOR
LOST EQUIPMENT LIST . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .CHECK
VOR/ILS 1 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . USE IESI
LOST FUNCTION/EQPT LIST see FCOM par 1.01.40
COMMENTS
HI and LO SPEED protection indication is lost.
Ice detector is lost.
Mod 5948
2.05.12
PROCEDURES FOLLOWING FAILURE
P 17
100
AVIONICS
FEB 12
AA
AVNX IOM 12 LOSS
ALERT
CONDITION
R
IOM 12 fail
VISUAL
AURAL
- MC light flashing amber
- AVNX IOM 12 amber message on EWD
SC
PROCEDURE
AVNX IOM 12 LOSS
R
R
LEAVE AND AVOID ICING CONDITIONS
ANTI/DE-- ICING MODE SEL AUTO FAULT procedure (2.05.09) . . . . . . . . . APPLY
JIf icing conditions
ANTI-- ICING PROP 1(2) FAULT procedure (2.05.09) . . . . . . . . . . . . . . . . . APPLY
ENG PARAMETERS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MONITOR
LOST EQUIPMENT LIST . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .CHECK
LANDING ELEVATION . . . . . . . . . . . . . . . . . . . . . . . SET PRESSURE ALTITUDE
LOST FUNCTION/EQPT LIST see FCOM 1.01.40
AVNX IOM 22 LOSS
ALERT
CONDITION
IOM 22 fail
VISUAL
AURAL
- MC light flashing amber
- AVNX IOM 22 amber message on EWD
SC
PROCEDURE
AVNX IOM 22 LOSS
R
LEAVE AND AVOID ICING CONDITIONS
ANTI/DE-- ICING MODE SEL AUTO FAULT procedure (2.05.09) . . . . . . . . . APPLY
JIf icing conditions
ANTI-- ICING PROP 1(2) FAULT procedure (2.05.09) . . . . . . . . . . . . . . . . APPLY
ENG PARAMETERS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MONITOR
LOST EQUIPMENT LIST . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .CHECK
LOST FUNCTION/EQPT LIST see FCOM 1.01.40
Mod 5948 + 6521
2.05.12
PROCEDURES FOLLOWING FAILURE
P 18
100
AVIONICS
FEB 12
AA
AVNX IOM 13 LOSS
ALERT
CONDITION
R
IOM 13 fail
VISUAL
AURAL
- MC light flashing amber
- AVNX IOM 13 amber message on EWD
SC
PROCEDURE
AVNX IOM 13 LOSS
R
R
R
ANTI/DE-- ICING MODE SEL AUTO FAULT procedure (2.05.09) . . . . . . . . . APPLY
TLU . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . HI or LO SPD ACCORDING TO IAS
ENG PARAMETERS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MONITOR
LOST EQUIPMENT LIST . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .CHECK
LANDING ELEVATION . . . . . . . . . . . . . . . . . . . . . . . SET PRESSURE ALTITUDE
LOST FUNCTION/EQPT LIST see FCOM 1.01.40
AVNX IOM 23 LOSS
ALERT
CONDITION
R
IOM 23 fail
VISUAL
AURAL
- MC light flashing amber
- AVNX IOM 23 amber message on EWD
SC
PROCEDURE
AVNX IOM 23 LOSS
R
R
ANTI/DE-- ICING MODE SEL AUTO FAULT procedure (2.05.09) . . . . . . . . . APPLY
TLU . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . HI or LO SPD ACCORDING TO IAS
ENG PARAMETERS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MONITOR
LOST EQUIPMENT LIST . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .CHECK
LOST FUNCTION/EQPT LIST see FCOM 1.01.40
Mod 5948 + 6521
2.05.12
PROCEDURES FOLLOWING FAILURE
P 19
100
AVIONICS
FEB 12
AA
AVNX IOM 12 + IOM 13 LOSS
ALERT
CONDITION
IOM 12 + IOM 13
R fail
VISUAL
- MC light flashing amber
- AVNX IOM 12+13 amber message on
EWD
AURAL
SC
PROCEDURE
AVNX IOM 12 + IOM 13 LOSS
R
R
LEAVE AND AVOID ICING CONDITIONS
LAND ASAP
ANTI/DE-- ICING MODE SEL AUTO FAULT procedure (2.05.09) . . . . . . . . . APPLY
J If icing conditions
ANTI-- ICING PROP 1(2) FAULT procedure (2.05.09) . . . . . . . . . . . . . . . . APPLY
TLU . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . HI or LO SPD ACCORDING TO IAS
ENG PARAMETERS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MONITOR
LOST EQUIPMENT LIST . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .CHECK
LANDING ELEVATION . . . . . . . . . . . . . . . . . . . . . . . SET PRESSURE ALTITUDE
LOST FUNCTION/EQPT LIST see FCOM 1.01.40
Mod 5948 + 6521
2.05.12
PROCEDURES FOLLOWING FAILURE
P 20
100
AVIONICS
FEB 12
AA
AVNX IOM 12 + IOM 22 LOSS
ALERT
CONDITION
IOM 12 + IOM 22
R fail
VISUAL
- MC light flashing amber
- AVNX IOM 12+22 amber message on
EWD
AURAL
SC
PROCEDURE
AVNX IOM 12 + IOM 22 LOSS
R
R
R
LEAVE AND AVOID ICING CONDITIONS
LAND ASAP
ANTI/DE-- ICING MODE SEL AUTO FAULT procedure (2.05.09) . . . . . . . . . APPLY
J If icing conditions
ANTI-- ICING PROP 1(2) FAULT procedure (2.05.09) . . . . . . . . . . . . . . . . APPLY
Note : LO PITCH engine 1 INDICATION LOST
AUTO PRESS FAULT procedure (2.05.08) . . . . . . . . . . . . . . . . . . . . . . . . . APPLY
ENG PARAMETERS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MONITOR
LOST EQUIPMENT LIST . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .CHECK
J At touch down
CAUTION : DO NOT USE REVERSE ON ENGINE 1
LOST FUNCTION/EQPT LIST see FCOM 1.01.40
Mod 5948 + 6521
2.05.12
PROCEDURES FOLLOWING FAILURE
P 21
100
AVIONICS
FEB 12
AA
AVNX IOM 12 + IOM 23 LOSS
ALERT
CONDITION
IOM 12 + IOM 23
R fail
VISUAL
- MC light flashing amber
- AVNX IOM 12+23 amber message on
EWD
AURAL
SC
PROCEDURE
AVNX IOM 12 + IOM 23 LOSS
R
R
LEAVE AND AVOID ICING CONDITIONS
LAND ASAP
ANTI/DE-- ICING MODE SEL AUTO FAULT procedure (2.05.09) . . . . . . . . . APPLY
J If icing conditions
ANTI-- ICING PROP1(2) FAULT procedure (2.05.09) . . . . . . . . . . . . . . . . . APPLY
TLU . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . HI or LO SPD ACCORDING TO IAS
ENG PARAMETERS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MONITOR
LOST EQUIPMENT LIST . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .CHECK
LANDING ELEVATION . . . . . . . . . . . . . . . . . . . . . . . SET PRESSURE ALTITUDE
LOST FUNCTION/EQPT LIST see FCOM 1.01.40
COMMENTS
If AUTO PRESS MODE is lost, CAB ALT + CAB∆P + CAB VS indicating are lost, descend
to FL 100 / MEA. Select MAN MODE. MAN PRESS KNOB select 11 O’CLOCK
Mod 5948 + 6521
2.05.12
PROCEDURES FOLLOWING FAILURE
P 22
100
AVIONICS
FEB 12
AA
AVNX IOM 13 + IOM 22 LOSS
ALERT
VISUAL
CONDITION
IOM 13 + IOM 22
R fail
- MC light flashing amber
- AVNX IOM 13+22 amber message on
EWD
AURAL
SC
PROCEDURE
AVNX IOM 13 + IOM 22 LOSS
R
R
LEAVE AND AVOID ICING CONDITIONS
SPD TGT MAN . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . USE
Note : Refer to QRH part 4 to determine SPEEDS
ICE DETECT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MONITOR IEP
LAND ASAP
ANTI/DE-- ICING MODE SEL AUTO FAULT procedure (2.05.09) . . . . . . . . . APPLY
JIf icing conditions
ANTI-- ICING PROP 1(2) FAULT procedure (2.05.09) . . . . . . . . . . . . . . . . APPLY
DE-- ICING . . . . . . . . . . . . . . . . . . . . . . . . . . . . MONITOR OVERHEAD PANEL
TLU . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . HI or LO SPD ACCORDING TO IAS
ENG PARAMETERS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MONITOR
LOST EQUIPMENT LIST . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK
LANDING ELEVATION . . . . . . . . . . . . . . . . . . . . . . SET PRESSURE ALTITUDE
LOST FUNCTION/EQPT LIST see FCOM 1.01.40
COMMENTS
Ice detection is lost.
Mod 5948 + 6521
2.05.12
PROCEDURES FOLLOWING FAILURE
P 23
100
AVIONICS
FEB 12
AA
AVNX IOM 13 + IOM 23 LOSS
ALERT
CONDITION
IOM 13 + IOM 23
R fail
VISUAL
- MC light flashing amber
- IOM 13+23 amber message on EWD
AURAL
SC
PROCEDURE
AVNX IOM 13 + IOM 23 LOSS
R
R
LEAVE AND AVOID ICING CONDITIONS
LAND ASAP
ANTI/DE-- ICING MODE SEL AUTO FAULT procedure (2.05.09) . . . . . . . . . APPLY
J If icing conditions
ANTI-- ICING PROP 1(2) FAULT procedure (2.05.09) . . . . . . . . . . . . . . . . APPLY
TLU . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .HI or LO SPD ACCORDING TO IAS
Note : LO PITCH engine 2 INDICATION LOST
ENG PARAMETERS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MONITOR
LOST EQUIPMENT LIST . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK
LANDING ELEVATION . . . . . . . . . . . . . . . . . . . . . . . SET PRESSURE ALTITUDE
JAt touch down
CAUTION : DO NOT USE REVERSE ON ENGINE 2
LOST FUNCTION/EQPT LIST see FCOM 1.01.40
Mod 5948 + 6521
2.05.12
PROCEDURES FOLLOWING FAILURE
P 24
100
AVIONICS
FEB 12
AA
AVNX IOM 22 + IOM 23 LOSS
ALERT
CONDITION
IOM 22 + IOM 23
R fail
VISUAL
- MC light flashing amber
- IOM 22+23 amber message on EWD
AURAL
SC
PROCEDURE
AVNX IOM 22 + IOM 23 LOSS
R
LEAVE AND AVOID ICING CONDITIONS
LAND ASAP
ANTi/DE-- ICING MODE SEL AUTO FAULT procedure (2.05.09) . . . . . . . . . APPLY
JIf icing conditions
ANTI-- ICING PROP 1(2) FAULT procedure (2.05.09) . . . . . . . . . . . . . . . . APPLY
TLU . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . HI or LO SPD ACCORDING TO IAS
ENG PARAMETERS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MONITOR
LOST EQUIPMENT LIST . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK
LOST FUNCTION/EQPT LIST see FCOM 1.01.40
Mod 5948 + 6521
2.05.12
PROCEDURES FOLLOWING FAILURE
P 25
100
AVIONICS
FEB 12
AA
AVNX CPM 1 + IOM 22 LOSS
ALERT
CONDITION
R
VISUAL
CPM 1 + IOM 22 fail - MC light flashing amber
- AVNX CPM 1+ IOM 22 amber message
on EWD
AURAL
SC
PROCEDURE
AVNX CPM 1 + IOM 22 LOSS
R
R
LEAVE AND AVOID ICING CONDITIONS
LAND ASAP
SPD TGT MAN . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . USE
Note : Refer to QRH part 4 to determine SPEEDS.
ICE DETECT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MONITOR IEP
ANTI/DE-- ICING MODE SEL AUTO FAULT procedure (2.05.09) . . . . . . . . . APPLY
JIf icing conditions
ANTI-- ICING PROP 1(2) FAULT procedure (2.05.09) . . . . . . . . . . . . . . . . APPLY
DE-- ICING . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MONITOR OVERHEAD PANEL
DE-- ICING AIRFRAME FAULT LOST . . . . . . . . . . . . . . . . . . . MONITOR WINGS
TLU . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . HI or LO SPD ACCORDING TO IAS
Note : LO PITCH engine 1 INDICATION LOST
ENG PARAMETERS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MONITOR
LOST EQUIPMENT LIST . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK
AUTO PRESS FAULT procedure (2.05.08) . . . . . . . . . . . . . . . . . . . . . . . . .APPLY
JAt touch down
CAUTION : DO NOT USE REVERSE ON ENGINE 1
LOST FUNCTION/EQPT LIST see FCOM 1.01.40
Mod 5948 + 6521
2.05.12
PROCEDURES FOLLOWING FAILURE
P 26
100
AVIONICS
DEC 13
AA
AVNX CPM 1 + IOM 23 LOSS
ALERT
CONDITION
VISUAL
CPM 1 + IOM 23 fail - MC light flashing amber
- AVNX CPM 1+ IOM 23 amber message
on EWD
AURAL
SC
PROCEDURE
AVNX CPM 1 + IOM 23 LOSS
R
LEAVE AND AVOID ICING CONDITIONS
LAND ASAP
ANTI/DE-- ICING MODE SEL AUTO FAULT procedure (2.05.09) . . . . . . . . . APPLY
JIf icing conditions
ANTI-- ICING PROP 1(2) FAULT procedure (2.05.09) . . . . . . . . . . . . . . . . . APPLY
TLU . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . HI or LO SPD ACCORDING TO IAS
Note : MMO & VMO AURAL WARNINGS LOST
Note : LO PITCH engine 2 INDICATION LOST
ENG PARAMETERS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MONITOR
LOST EQUIPMENT LIST . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK
LANDING ELEVATION . . . . . . . . . . . . . . . . . . . . . . . SET PRESSURE ALTITUDE
JAt touch down
CAUTION : DO NOT USE REVERSE ON ENGINE 2
LOST FUNCTION/EQPT LIST see FCOM 1.01.40
Mod 5948 + 6521
2.05.12
PROCEDURES FOLLOWING FAILURE
P 27
100
AVIONICS
FEB 12
AA
AVNX CPM 2 + IOM 12 LOSS
ALERT
CONDITION
R
VISUAL
CPM 2 + IOM 12 fail - MC light flashing amber
- AVNX CPM 2+ IOM 12 amber message
on EWD
AURAL
SC
PROCEDURE
AVNX CPM 2 + IOM 12 LOSS
R
R
LEAVE AND AVOID ICING CONDITIONS
LAND ASAP
ANTI/DE-- ICING MODE SEL AUTO MODE FAULT procedure (2.05.09) . . . . APPLY
JIf icing conditions
ANTI-- ICING PROP 1(2) FAULT procedure (2.05.09) . . . . . . . . . . . . . . . . . APPLY
TLU . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . HI or LO SPD ACCORDING TO IAS
Note : LO PITCH engine 1 INDICATION LOST
ENG PARAMETERS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MONITOR
LOST EQUIPMENT LIST . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK
HYD GREEN PRESS . . . . . . . . . . . . . . . . . . . . . . . . . MONITOR OVHD PANEL
FLAPS SETTING . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MONITOR VISUALY
AUTO PRESS FAULT procedure(2.05.08) . . . . . . . . . . . . . . . . . . . . . . . . .APPLY
JAt touch down
CAUTION : DO NOT USE REVERSE ON ENGINE 1
LOST FUNCTION/EQPT LIST see FCOM 1.01.40
Mod 5948 + 6521
2.05.12
PROCEDURES FOLLOWING FAILURE
P 28
100
AVIONICS
FEB 12
AA
AVNX CPM 2 + IOM 13 LOSS
ALERT
CONDITION
R
VISUAL
CPM 2 + IOM 13 fail - MC light flashing amber
- AVNX CPM 2+ IOM 13 amber message
on EWD
AURAL
SC
PROCEDURE
AVNX CPM 2 + IOM 13 LOSS
R
R
LEAVE AND AVOID ICING CONDITIONS
SPD TGT MAN . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . USE
Note : Refer to QRH part 4 to determine SPEEDS.
ICE DETECT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MONITOR IEP
LAND ASAP
ANTI/DE-- ICING MODE SEL AUTO FAULT procedure (2.05.09) . . . . . . . . . APPLY
JIf icing conditions
ANTI-- ICING PROP 1(2) FAULT procedure (2.05.09) . . . . . . . . . . . . . . . . APPLY
TLU . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . HI or LO SPD ACCORDING TO IAS
Note : MMO & VMO AURAL WARNINGS LOST
Note : LO PITCH engine 2 INDICATION LOST
ENG PARAMETERS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MONITOR
LOST EQUIPMENT LIST . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK
LANDING ELEVATION . . . . . . . . . . . . . . . . . . . . . . . SET PRESSURE ALTITUDE
JAt touch down
CAUTION : DO NOT USE REVERSE ON ENGINE 2
LOST FUNCTION/EQPT LIST see FCOM 1.01.40
COMMENTS
If AUTO PRESS MODE is lost, CAB ALT + CAB∆P + CAB VS indicating are lost, descend
to FL 100 / MEA. Select MAN MODE. MAN PRESS KNOB select 11 O’CLOCK
Mod 5948 + 6521
2.05.13
PROCEDURES FOLLOWING FAILURE
P1
001
MISCELLANEOUS
FEB 12
AA
COCKPIT DOOR CONTROL PANEL FAULT
PROCEDURE
COCKPIT DOOR CONTROL PANEL FAULT (if installed)
R
COCKPIT DOOR MANUAL LOCK BOLT(S) . . . . . . . MOVE TO CLOSE POSITION
Note : When the door is locked with the manual bolt(s), the emergency access to the
cockpit is unavailable.
CAUTION : At least two crewmembers must remain in the cockpit during that time.
LOSS OF RADIO ALTIMETER INFORMATION
ALERT
CONDITION
Loss of
radioaltimeters
VISUAL
- MC light flashing amber
- RAD--ALT LOSS amber message on
EWD
AURAL
NIL
PROCEDURE
LOSS OF RADIO ALTIMETER INFORMATION
R
R
GPWS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF
TCAS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . STBY
CAUTION : LDG GEAR NOT DOWN undue warning may be generated when
reducing PL; this alarm may be cancelled by using EMER AUDIO.
CANCEL.
FFor approach
SPD TGT MAN . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . USE
Note : ILS CAT 2 is invalid
Mod 5948
2.05.13
PROCEDURES FOLLOWING FAILURE
P2
100
MISCELLANEOUS
FEB 12
AA
SMK DET FANS FAULT
ALERT
CONDITION
Smoke detectors
R fans failure
VISUAL
AURAL
- MC light flashing amber
- AIR AFT (FWD) DET FAN amber
message on EWD
- FANS FAULT amber light on overhead
panel
- Associated DET FANS amber indication
on SD Cabin page.
SC
PROCEDURE
SMK DET FANS FAULT
FAN . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ALTN
Mod 5948 + 6521
2.05.13
PROCEDURES FOLLOWING FAILURE
P3
001
MISCELLANEOUS
FEB 12
AA
DOORS UNLK IN FLIGHT
ALERT
VISUAL
CONDITION
Door UNLK in flight
- MC light flashing amber
- DOOR EMER (LH FWD) (RH FWD)
(LH AFT) (RH AFT) (FWD COMPT)
amber message on EWD
- associated door amber light on
overhead panel
- Associated door amber indication on
SD Cabin page.
AURAL
SC
PROCEDURE
DOORS UNLK IN FLIGHT
J If any door except FWD COMPT
SIGNS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON
Associated DOOR . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . VISUALLY CHECK
J If unlocked or check not feasible
LANDING ELEVATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9000 ft
MAX FL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 100 / MEA
R
J If FWD COMPT
NO CREW ACTION REQUIRED
COMMENTS
- As the doors (except FWD COMPT) open outwards, when one is not locked, the ∆P
must be reduced by aircraft descent and landing elevation selection.
COCKPIT WINDOW CRACKED
PROCEDURE
COCKPIT WINDOW CRACKED
WINDOW HEAT affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF
LANDING ELEVATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9000 ft
MAX FL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 100 / MEA
Mod 5948
2.05.13
PROCEDURES FOLLOWING FAILURE
P4
001
MISCELLANEOUS
AA
FEB 12
OXYGEN LO PR
ALERT
CONDITION
VISUAL
Low pressure (below - MC light flashing amber
50 PSI) in the LP
- OXY amber message on EWD
distribution circuit
- MAIN SUPPLY LO PR amber light on
overhead panel
- Associated LO PR amber indication on
SD cabin page.
AURAL
SC
PROCEDURE
OXYGEN LO PR
R
OXY MAIN SUPPLY . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF THEN ON
J If OXYGEN LO PR light remains illuminated
MAIN SUPPLY . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF
OXYGEN PORTABLE UNIT . . . . . . . . . . . . . . INSTALL IN COCKPIT AS RQD
COMMENTS
- The 120 l portable oxygen bottle permits a continuous diluted flow to one crew member
at 13 000 ft for a duration of 30 mn.
Oxygen low pressure supply valve position may disagree with actual oxygen MAIN
SUPPLY pushbutton position if this pushbutton is activated by very close consecutive
actions.
Interval between OFF and ON actions on oxygen MAIN SUPPLY must be greater than
one second to be sure that low pressure supply valve position is in accordance with
actual pushbutton position.
- This bottle can be placed in the cockpit.
Mod 5948
2.05.13
PROCEDURES FOLLOWING FAILURE
P5
MISCELLANEOUS
001
FEB 12
AA
VOLCANISH ASH ENCOUNTER
PROCEDURE
VOLCANISH ASH ENCOUNTER
R
R
R
FOLLOWING ITEMS HAVE TO BE APPLIED WHILE MAKING A 180° TURN AND
STARTING DESCENT (IF MSA PERMITS)
ATC . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . NOTIFY
PL 1 + 2 (If conditions permit) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . RETARD
CREW OXY MASKS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON / 100%
CABIN CREW . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . NOTIFY
PASSENGER OXYGEN . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . AS RQD
AIR FLOW . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . HIGH
ENG PARAMETERS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MONITOR
AIRSPEED INDICATIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MONITOR
Note: Reducing TQ reduces ash ingestion, maximizes engine surge margin and
lowers engine turbine temperature. Monitor particularly ITT; it may become necessary
to set PL to Flight Idle, if conditions permit.
Note: In extreme case, it may be necessary to consider precautionary engine shut
down and engine restart in flight. If both engines flame out, refer to BOTH ENGINE
FLAME OUT procedure (2.04.02)
Note: Volcanic ash may clog the pitot probes resulting in unreliable speed indications.
If airspeed is unreliable or lost, adjust airplane attitude and torque, and refer to
UNRELIABLE AIRSPEED INDICATION EMERGENCY procedure (2.04.05)
Mod 5948
2.05.14
PROCEDURES FOLLOWING FAILURE
P1
001
MFC
FEB 12
AA
MFC 1A FAULT
ALERT
CONDITION
MFC 1A FAULT
VISUAL
- MC light flashing amber
- MFC 1A amber message on EWD
- Associated MFC FAULT amber light on
overhead panel
AURAL
SC
PROCEDURE
MFC 1A FAULT
R
MODULE 1A . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF / RESET
JIf MFC 1A FAULT persists
MODULE 1A . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF
JIf before take off
RETURN TO PARKING
JIf in flight
MFC 1A MODULE LOST EQUIPMENT LIST . . . . . . . . . . . . . . . . . . . CHECK
COMMENTS
- As HP valve 1 is lost, air is bled only from the LP stage. Applicable pack performance is
affected at low engine power.
- Landing gear primary RED UNLK indications are lost.
Mod 5948
2.05.14
PROCEDURES FOLLOWING FAILURE
P2
001
MFC
FEB 12
AA
MFC 1B FAULT
ALERT
CONDITION
MFC 1B FAULT
VISUAL
- MC light flashing amber
- MFC 1B amber message on EWD
- Associated MFC FAULT amber light on
overhead panel
AURAL
SC
PROCEDURE
MFC 1B FAULT
R
MODULE 1B . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF / RESET
JIf MFC 1B Fault persists
MODULE 1B . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF
J If before take off
RETURN TO PARKING
PACK 1 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF
OVBD VALVE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FULL OPEN
JIf in flight
F Immediately after take off
LDG GEAR . . . . . . . . . . . . . . . . . DOWN FOR COOLING FOR 1 MINUTE
EXCEPT IN CASE OF EMERGENCY
F During flight
OVBD VALVE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FULL CLOSE
MFC 1B MODULE LOST EQUIPMENT LIST . . . . . . . . . . . . . . . . . CHECK
F After runway vacated
PACK 1 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF
OVBD VALVE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FULL OPEN
CAUTION : Before opening any door, PACKS 1 and 2 must be selected OFF and
cockpit communication hatch must be open.
COMMENTS
- As WOW signal is lost, OVBD valve must be selected FULL OPEN manually on ground
to improve racks cooling.
- Hot brakes indication is lost; LDG GEAR must remain down during 1 minute after take
off for cooling.
- Ground turbofan 1 being lost, PACK 1 must be switched OFF on ground to avoid any
overheat problem.
- ENG 1 OIL LO PRESS light remains ON when engine 1 is shut down.
- After landing, as outflow valves do not fully open, selecting OVBD valve FULL OPEN
relieves the ∆P between cabin and outside.
- On ground, pressurization digital controller test capability is lost.
Mod 5948
2.05.14
PROCEDURES FOLLOWING FAILURE
P3
001
MFC
FEB 12
AA
MFC 2A FAULT
ALERT
CONDITION
MFC 2A FAULT
VISUAL
- MC light flashing amber
- MFC 2A amber message on EWD
- Associated MFC FAULT amber light on
overhead panel
AURAL
SC
PROCEDURE
MFC 2A FAULT
R
R
MODULE 2A . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF / RESET
JIf MFC 2A Fault persists
MODULE 2A . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF
JIf before take off
RETURN TO PARKING
OVBD VALVE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FULL OPEN
JIf in flight
IDLE GATE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MONITOR
AVIONICS VENT EXHAUST MODE . . . . . . . . . . . . . . . . . . . . . . . . . . OVBD
MFC 2A MODULE LOST EQUIPMENT LIST . . . . . . . . . . . . . . . . . . . CHECK
F At touch down
IDLE GATE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MONITOR
F After runway vacated
OVBD VALVE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FULL OPEN
COMMENTS
- EXHAUST MODE to OVBD position controls the OVBD valve to partially open:
ventilation air is then discharged overboard instead of being directed to the underfloor
valve. Ventilation is ensured by ∆P between cabin and outside.
- As WOW signal is lost, OVBD valve must be selected FULL OPEN manually on ground
to improve racks cooling.
- IDLE GATE FAIL amber alert is lost.
- As HP valve 2 is lost, air is bled only from the LP stage. Pack 2 performance is affected
at low engine power.
- Right hand side window anti-- icing is lost.
- As extract fan is lost, avoid leaving avionics selected ON on ground for a long period of
time with high OAT.
- Landing gear secondary green arrows and RED UNLK indications are lost.
Mod 5948
2.05.14
PROCEDURES FOLLOWING FAILURE
P4
001
MFC
FEB 12
AA
MFC 2B FAULT
ALERT
CONDITION
MFC 2B FAULT
VISUAL
- MC light flashing amber
- MFC 2B amber message on EWD
- Associated MFC FAULT amber light on
overhead panel
AURAL
SC
PROCEDURE
MFC 2B FAULT
R
R
MODULE 2B . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF / RESET
J If MFC 2B Fault persists
MODULE 2B . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF
JIIf before take off
RETURN TO PARKING
PACK 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF
OVBD VALVE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FULL OPEN
JIIf in flight
MONITOR IEP
F Immediately after take off
LDG GEAR . . . . . . . . . . . . . . DOWN FOR COOLING FOR 1 MINUTE
EXCEPT IN CASE OF EMERGENCY
F During flight
OVBD VALVE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FULL CLOSE
MFC 2B MODULE LOST EQUIPMENT LIST . . . . . . . . . . . . . . CHECK
F After runway vacated
PACK 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF
OVBD VALVE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FULL OPEN
CAUTION : Before opening any door, PACKS 1 and 2 must be selected OFF and
cockpit communication hatch must be open.
COMMENTS
- As WOW signal is lost, OVBD valve must be selected FULL OPEN manually on ground
to improve racks cooling.
- Hot brakes indication is lost; LDG GEAR must remain down during 1 minute after take
off for cooling.
- Ground turbofan 2 being lost, PACK 2 must be switched OFF on ground to avoid any
overheat problem.
- ENG 2 OIL LO PRESS light remains ON when engine 2 is shut down.
- Landing gear secondary green arrows and RED UNLK indications are lost.
- After landing, selecting the OVBD valve fully open relieves the ∆P between cabin and
outside.
- Right hand side window anti-- icing is lost without FAULT indication.
Mod 5948
2.05.14
PROCEDURES FOLLOWING FAILURE
P5
MFC
AA
MFC 1A + 1B FAULT
ALERT
CONDITION
VISUAL
MFC 1A + 1B
- MC light flashing amber
FAULT
- MFC 1A + 1B amber message on EWD
- Associated MFC FAULT amber light on overhead panel
001
FEB 12
AURAL
SC
PROCEDURE
MFC 1A + 1B FAULT
R
R
R
R
R
MODULES 1A + 1B . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF / RESET
JIf MFC 1A+1B Fault persists
MODULES 1A + 1B . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF
JIf before take off
RETURN TO PARKING
PACK 1 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF
OVBD VALVE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FULL OPEN
JIf in flight
LEAVE AND AVOID ICING CONDITIONS
OVBD VALVE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FULL CLOSE
ANTI-- ICING PROP 1 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF
ANTI-- ICING PROP 1(2) FAULT procedure (2.05.09) . . . . . . . . . . . . . . . APPLY
DE-- ICING MODE SEL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OVRD AS RQD
PACK 1 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF
BLEED 1 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF
BLEED VALVE 1(2) FAULT procedure (2.05.08) . . . . . . . . . . . . . . . . . . APPLY
GPWS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF
MFC 1A + 1B MODULES LOST EQUIPMENT LIST . . . . . . . . . . . . . . CHECK
F Before landing
ATPCS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF
V APP . . . . . . . . . . . . . . . . . . . . . . . . . NOT LESS THAN V REF + 10 KT
SPD TGT MAN . . . . . . . . . . . . . . . . . . . . . . . . . . . . USE IF NECESSARY
LDG DIST . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MULTIPLY BY 1.15
F After runway vacated
OVBD VALVE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FULL OPEN
CAUTION : Before opening any door, PACKS 1 and 2 must be selected OFF and
cockpit communication hatch must be open.
COMMENTS
- Landing gear primary green arrows and RED UNLK indications are lost.
- PACK 1, BLEED 1, left hand side window anti-- icing and stick pusher are lost without
FAULT indications.
- AC BUS 1 is lost leading to loss of trim indication, GPWS and weather radar.
- ATPCS must be selected OFF before landing due to loss of autofeather on engine 1.
Check go around performances ATPCS OFF.
See also COMMENTS for MFC 1A FAULT (2.05.14 page 1) and for MFC 1B FAULT
(2.05.14 page 2).
Mod 5948
2.05.14
PROCEDURES FOLLOWING FAILURE
P6
001
MFC
FEB 12
AA
MFC 1A + 2A FAULT
ALERT
CONDITION
MFC 1A + 2A
FAULT
VISUAL
- MC light flashing amber
- MFC 1A + 2A amber message on
EWD
- Associated MFC FAULT amber light on
overhead panel
AURAL
SC
PROCEDURE
MFC 1A + 2A FAULT
R
R
R
MODULES 1A + 2A . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF / RESET
JIf MFC 1A+2A Fault persists
MODULE 1A + 2A . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF
JIf before take off
RETURN TO PARKING
OVBD VALVE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FULL OPEN
JIf in flight
AVIONICS VENT EXHAUST MODE . . . . . . . . . . . . . . . . . . . . . . . . . . OVBD
TLU . . . . . . . . . . . . . . . . . . . . . . . . . . . . HI or LO SPD ACCORDING TO IAS
GPWS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF
MFC 1A + 2A MODULES EQUIPMENT LIST . . . . . . . . . . . . . . . . . . CHECK
Note : Airframe FAULT amber alert is lost.
Note : When airframe de-- icing is used, monitor boots inflation.
Note : As AP OFF alert is lost, use of AP below 1000 ft AGL is prohibited.
F Before landing
LDG GEAR GRAVITY EXTENSION procedure(2.05.07) . . . . . . . . . . APPLY
F At touch down
IDLE GATE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MONITOR
F After runway vacated
OVBD VALVE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FULL OPEN
COMMENTS
- AC BUS 1 + 2 are lost leading to loss of trim indication, GPWS and weather radar.
- DC BUS 1 + 2 OFF warnings on overhead panel are lost.
- Mechanical, crew and hostess call are lost.
- Stick pusher FAULT indication is lost but stick pusher is still available.
See also COMMENTS for MFC 1A FAULT (2.05.14 page 1) and for MFC 2A FAULT
(2.05.14 page 3).
Mod 5948
2.05.14
PROCEDURES FOLLOWING FAILURE
P7
001
MFC
FEB 12
AA
MFC 1A + 2B FAULT
ALERT
CONDITION
MFC 1A + 2B
FAULT
VISUAL
- MC light flashing amber
- MFC 1A + 2B amber message on
EWD
- Associated MFC FAULT amber light on
overhead panel
AURAL
SC
PROCEDURE
MFC 1A + 2B FAULT
R
R
R
MODULES 1A + 2B . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF / RESET
JIf MFC 1A + 2B Fault persists
MODULES 1A + 2B . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF
JIf before take off
RETURN TO PARKING
PACK 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF
OVBD VALVE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FULL OPEN
JIf in flight
OVBD VALVE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FULL CLOSE
HYD MAIN BLUE PUMP . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF
HYD X FEED . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON
DE-- ICING MODE SEL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OVRD AS RQD
MFC 1A + 2B MODULE EQUIPMENT LIST . . . . . . . . . . . . . . . . . . . . CHECK
Note : AP does not disconnect after STBY PITCH TRIM activation.
F Before landing
Note : Flaps control is lost.
REDUCED FLAPS LANDING procedure (2.05.06) . . . . . . . . . . . . . . APPLY
LDG GEAR GRAVITY EXTENSION procedure(2.05.07) . . . . . . . . . . APPLY
F After runway vacated
PACK 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF
OVBD VALVE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FULL OPEN
Note: ILS CAT 2 IS PROHIBITED
CAUTION : Before opening any door, PACKS 1 and 2 must be selected OFF and
cockpit communication hatch must be open.
COMMENTS
- Selecting de-- icing mode to OVRD position allows to recover all pneumatic de-- icers
operations.
- Main blue HYD pump control is lost as well as flaps control. Selecting HYD X FEED
open allows to recover blue HYD pressure but flaps control remains lost
See also COMMENTS for MFC 1A FAULT (2.05.14 page 1) and for MFC 2B FAULT
(2.05.14 page 4).
Mod 5948
2.05.14
PROCEDURES FOLLOWING FAILURE
P8
MFC
001
FEB 12
AA
MFC 1B + 2A FAULT
ALERT
CONDITION
MFC 1B + 2A FAULT
VISUAL
- MC light flashing amber
- MFC 1B + 2A amber message on
EWD
- Associated MFC FAULT amber light on
overhead panel
AURAL
SC
PROCEDURE
MFC 1B + 2A FAULT
R
R
R
R
MODULES 1B + 2A . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF / RESET
JIf MFC 1B + 2A Fault persists
MODULES 1B + 2A . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF
JIf before take off
RETURN TO PARKING
PACK 1 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF
OVBD VALVE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FULL OPEN
JIf in flight
DE-- ICING MODE SEL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OVRD AS RQD
AVIONICS VENT EXHAUST MODE . . . . . . . . . . . . . . . . . . . . . . . . . . OVBD
MFC 1B + 2A MODULE EQUIPMENT LIST . . . . . . . . . . . . . . . . . . . . CHECK
F Before landing
Note : Flaps control is lost.
REDUCED FLAPS LANDING procedure (2.05.06) . . . . . . . . . . . . . . APPLY
LDG GEAR GRAVITY EXTENSION procedure (2.05.07) . . . . . . . . . DOWN
F At touch down
IDLE GATE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MONITOR
F After runway vacated
PACK 1 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF
OVBD VALVE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FULL OPEN
Note: ILS CAT 2 IS PROHIBITED
CAUTION : Before opening any door, PACKS 1 and 2 must be selected OFF and
cockpit communication hatch must be open.
COMMENTS
- Selecting de-- icing mode to OVRD position allows to recover all pneumatic de-- icers
operations.
- DC BUS 2 OFF warning on overhead panel is lost.
- Hostess and crew indications calls are lost.
- Hot brakes indicating system test is lost.
- Landing gear controls, secondary RED UNLK and green arrows indications are lost.
See also COMMENTS for MFC 1B FAULT (2.05.14 page 2) and for MFC 2A FAULT
(2.05.14 page 3).
Mod 5948
2.05.14
PROCEDURES FOLLOWING FAILURE
P9
001
MFC
FEB 12
AA
MFC 2A + 2B FAULT
ALERT
CONDITION
MFC 2A + 2B
FAULT
VISUAL
- MC light flashing amber
- MFC 2A + 2B amber message on
EWD
- Associated MFC FAULT amber light on
overhead panel
AURAL
SC
PROCEDURE
(refer to page 10)
.../...
Mod 5948
2.05.14
PROCEDURES FOLLOWING FAILURE
P 10
MFC
001
FEB 12
AA
MFC 2A + 2B FAULT
PROCEDURE
MFC 2A + 2B FAULT
R
R
R
R
R
MODULES 2A + 2B . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF / RESET
JIf MFC 2A + 2B fault persists
MODULES 2A + 2B . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF
JIf before take off
RETURN TO PARKING
BLEED 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF
PACK 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF
OVBD VALVE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FULL OPEN
JIf in flight
LEAVE AND AVOID ICING CONDITIONS
MONITOR IEP
AVIONICS VENT EXHAUST MODE . . . . . . . . . . . . . . . . . . . . . . . . . . OVBD
ANTI-- ICING PROP 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF
ANTI-- ICING PROP 1(2) FAULT procedure (2.05.09) . . . . . . . . . . . . . . . APPLY
DE-- ICING MODE SEL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OVRD AS RQD
PACK 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF
BLEED 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF
BLEED VALVE 1(2) FAULT procedure (2.05.08) . . . . . . . . . . . . . . . . . . APPLY
MFC 2A + 2B MODULES EQUIPMENT LIST . . . . . . . . . . . . . . . . . . CHECK
F Before landing
ATPCS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF
V APP . . . . . . . . . . . . . . . . . . . . . . . . . NOT LESS THAN V REF + 10 KT
SPD TGT MAN . . . . . . . . . . . . . . . . . . . . . . . . . . . . USE IF NECESSARY
LDG DIST . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MULTIPLY BY 1.15
Note : Refer to Part 4 to determine landing distance
F At touch down
IDLE GATE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MONITOR
F After runway vacated
OVBD VALVE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FULL OPEN
CAUTION : Before opening any door, PACKS 1 and 2 must be selected OFF and
cockpit communication hatch must be open.
COMMENTS
- STICK PUSHER, PACK 2, BLEED 2 are lost without FAULT indications.
- ATPCS must be selected OFF before landing due to loss of autofeather on engine 1.
Check go around performances ATPCS OFF.
- Hostess and crew indications calls are lost.
See also COMMENTS for MFC 2A FAULT (2.05.14 page 3) and for MFC 2B FAULT
(2.05.14 page 4).
Mod 5948
2.05.14
PROCEDURES FOLLOWING FAILURE
P 11
001
MFC
FEB 12
AA
MFC 1B + 2B FAULT
ALERT
CONDITION
MFC 1B + 2B
FAULT
VISUAL
AURAL
- MC light flashing amber
- MFC 1B+ 2B amber message on EWD
- Associated MFC FAULT amber light on
overhead panel
SC
PROCEDURE
(refer to page 12)
.../...
Mod : 5948
2.05.14
PROCEDURES FOLLOWING FAILURE
P 12
MFC
001
FEB 12
AA
MFC 1B + 2B FAULT
PROCEDURE
MFC 1B + 2B FAULT
R
R
R
MODULES 1B + 2B . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF / RESET
JIf MFC 1B + 2B Fault persists
MODULES 1B + 2B . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF
CAUTION : FWS DEGRADED, MONITOR OVERHEAD PANEL
JIf before take off
RETURN TO PARKING
PACK 1 + 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF
OVBD VALVE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FULL OPEN
JIf in flight
MONITOR IEP
OVBD VALVE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FULL CLOSE
MFC 1B + 2B MODULES EQUIPMENT LIST . . . . . . . . . . . . . . . . . . . CHECK
F Before landing
NOSE WHEEL STEERING . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF
LDG GEAR GRAVITY EXTENSION procedure (2.05.07) . . . . . . . . . APPLY
ANTI-- SKID . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF
ANTI-- SKID FAULT procedure (2.05.07) . . . . . . . . . . . . . . . . . . . . . APPLY
F At touch down
IDLE GATE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . PULL
DIFFERENTIAL BRAKING . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . USE
F After runway vacated
PACK 1 + 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF
OVBD VALVE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FULL OPEN
ANTI-- ICING HORNS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF
PROBES HTG . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF
Note : ATPCS ARM light is not available. Autofeather label is lost.
Note : External power cannot be used.
CAUTION : Before opening any door, PACKS 1 and 2 must be selected OFF and
cockpit communication hatch must be open.
COMMENTS
- MC, MW and most of centralized alerts are lost : monitor overhead panel.
- Braking is lost below 35 kt if anti-- skid is ON.
- IDLE GATE automatic function is not available.
- TAT heating FAULT light is lost.
- No whooler is heard during trim activation.
- Stall Warning and Stick Shaker are lost without FAULT indication. Stick Pusher is
available.
See also COMMENTS for MFC 1B FAULT (2.05.14 page 2) and for MFC 2B FAULT
(2.05.14 page 4).
Mod : 5948
m
APR 11
Mod 5948
APR 11
Mod 5948
2.06.02
LOADING - FUEL - BALANCE CHART
P1
CARGO LANDING
AA
FORWARD AND REAR CARGO COMPARTMENTS
Refer to “Weight and Balance Manual”
R WBM : 1.60.03.
Mod 5948
001
DEC 13
APR 11
Mod 5948
2.06.03
LOADING - FUEL - BALANCE CHART
P2
001
FUEL LOADING
DEC 13
AA
REFUELING PROCEDURE
- Observe the safety precautions and make certain that the tanker and the aircraft are
properly grounded.
. Note : Refueling when right engine is running in Hotel mode is prohibited.
- Press FQI TEST pb and check :
S High Level + Valve Open lights ON.
S Fuel QTY + selected QTY displays ON.
AUTOMATIC REFUELING
- Check REFUEL VALVES switches are at NORM position and guarded.
- Set the preselected total fuel quantity on the SELECTED QTY ind.
- Place Mode selector switch in REFUEL position.
- Start refueling.
MANUAL REFUELING
- Raise REFUEL VALVES switch gards and place all switches in SHUT position.
- Place Mode selector switch in REFUEL position.
- Place appropriate REFUEL VALVES switch in OPEN position.
- Start refueling.
- Monitor individual tank content on FUEL Qty indicator and select appropriate tank
REFUEL VALVE switch to SHUT as tank content reaches required fuel quantity.
R
Note : 1. Total time to fill out wing tanks is approximately 18 minutes.
2. As tanks become full, fuel flow will be stopped by high level sensors and
appropriate tank HIGH LEVEL light will illuminate.
Mod : 5948
2.06.03
LOADING - FUEL - BALANCE CHART
P3
FUEL LOADING
001
FEB 12
AA
GRAVITY FILLING
R
R
- Position access platform to access the overwing refueling caps and attach refueling
hose grounding cable to the grounding connection near overwing refueling cap.
Remove overwing refueling cap.
- Start filling, monitor quantity of fuel delivered on FQI and observe the HIGH LEVEL
indicator lights on refueling panel ; stop filling when required fuel level is reached or
when HIGH LEVEL indicator lights(s) comes on.
USE OF MANUAL (MAGNETIC) INDICATORS
Each tank is equipped with 2 indicators :
- one in the inner part of the wing (between the engine and the fuselage).
- one in the outer part of the wing.
S Read and note aircraft roll attitude on clinometer in the hydraulic bay (LH landing
gear fairing).
Aircraft bank angle is positive for wing up, negative for wing down.
Note : Pitch attitude must be between - 3° degrees and + 1° degree. In this range
pitch has no influence.
S Position access platform.
S Unlock indicator rod with screwdriver and slowly withdraw rod until magnetic attraction
between rod and float magnets is felt.
S
S
S
S
Check rod freedom by pushing up both rod and float magnet.
Slowly withdraw rod down to floating level.
Note the graduation on rod which aligns with wing bottom surface.
Replace indicator and lock with screwdriver.
- If both gauges indications don’t indicate extremum values (0 or 30 for inner gauge,
0 or 19 for outer gauge, disregard clinometer indication. Fuel quantity is determined
thanks to internal and external indicator reading.
Note : Clinometer indication is disregraded for accuracy purposes.
- If one gauge indicates an extremum value (0 or 30 for inner gauge, 0 or 19 for outer
gauge, disregard this extremum value, use clinometer indication and the other gauge
value.
Mod 5948
APR 11
Mod 5948
APR 11
Mod 5948
APR 11
Mod : 5948
APR 11
Mod : 5948
APR 11
Mod 5948
APR 11
Mod 5948
APR 11
Mod 5948
APR 11
Mod 5948
APR 11
Mod 5948
APR 11
Mod 5948
2.06.04
LOADING - FUEL - BALANCE CHART
P4
WEIGHT AND BALANCE
EXAMPLE BASED ON FICTITIOUS DATA
CAUTION : Fictitious data
Refer to WBM for operational use
MOD 5948
001
APR 11