QRH REV 29.0 - TOTAL JUN 21 Kg

Kg
QRH Quick Reference Handbook
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PK1_QRH_45_L_SI_full_Rev29.0
Identification Title
OEB 25 Issue 1 Propeller Blade Pitch Change Mechanism Damage
OEB 27 Issue 1 Uncommanded Autofeather
OEB 28 Issue 1 MFC 1B and/or MFC 2B Fault
OEB 30 Issue 1 Spurious Glide Slope Capture
OEB 32 Issue 1 ENGINE FIRE WARNING
OEB 36 Issue 1 Bank angle limitation in Severe Icing Conditions
OEB 42 Issue 1 Static Inverter Double Loss
OEB 43 Issue 1 Cockpit Voice Recorder
OEB 49 Issue 1 Temporary ENG 1(2) OIL LO PR procedure
LIST OF EFFECTIVE OEBs
PAGE
INTENTIONALLY
GENERAL DESCRIPTION _ad23bea2-0586-49a0-b385-63974656a280 0.5
ALL An Operations Engineering Bulletin (OEB) is issued to rapidly inform operators of any deviations from initial design objectives that have a significant operational impact. An OEB provides the operators with technical information and temporary operational procedures that address these deviations. ATR strongly recommends that all Operators rapidly apply the OEB corrective actions as soon as they become available. OEB CONTENT AND MANAGEMENT An OEB:
- Is temporary and usually focuses on one operational subject. - Is included in the OEB section of both the FCOM and QRH. The procedural
part of OEB (OEB PROC) is provided in the OEB section of the QRH to ensure easy access by flight crew.
- Remains applicable until the appropriate corrective actions are completed. - Contains information that is recommended by ATR. It is not approved by
Airworthiness Authorities. If the procedures contained in the OEB differ from the procedures in the AFM, the AFM remains the reference. Note Following the installation of the OEB corrective modification/Service Bulletins (SB): if an Operator re-installs any spare equipment for which there was an associated OEB, it is the Operator’s responsibility to ensure that the OEB be applied again for the applicable aircraft.
OEB IN THE QRH Each FCOM OEB has an associated “OEB PROC” in the OEB section of the QRH, that includes:
- The title of the OEB PROC, - The OEB operational procedure(s) that the flight crew must apply.
DISTRIBUTION OEB’s are distributed to all FCOM holders and to others who need advice of changes to operational information. The Operator shall provide flight crews with the content of the OEB’s without delay. QRH LIST OF EFFECTIVE OEB’s The List of Effective Operations Engineering Bulletins (LOEB) enables flight crews to review all the Operations Engineering Bulletins (OEB’s) that are applicable to the fleet. Each time an OEB’s is issued or revised, the LOEB is updated.
Identification Title
OEB’s 12 Issue 01 Cockpit Voice Recorder
The QRH LOEB consists of: - The "Identification" field which identifies the OEB with its Identification and
issue Number. - The "Title" field provides the OEB title.
REVIEW OF THE OEB’s In accordance with the Standard Operating Procedures, and before each flight, the flight crew must review all OEB’s that are applicable to their aircraft. If the OEB’s conditions are applicable, the flight crew must apply the operational procedure(s) in the OEB’s section of the QRH.
OPERATIONS ENGINEERING BULLETINS OEB /
Propeller Blade Pitch Change Mechanism Damage _e6f4d1ef-063c-441c-9bfc-b0c9dd6a2e60 REV 7.0
ALL Procedure
Even if all the reported cases occurred on engine 2, the recommended procedure aims at confirming/identifying the affected engine first and then to shut it down. The identification of the affected engine can be performed thanks to engine parameters fluctuations monitoring or alerts displayed on one side. However, the identification may be less obvious depending on the damages and the level of vibrations. In this case, the following procedure will request to perform Power Lever and Propeller speed variations on one engine at a time and to assess which engine makes vibrations change (increase or decrease). In any case, every vibration occurrence is to be reported to maintenance. If the power levers has to be reduced to flight idle position during descent at high speed (close to VMO), it is recommended to perform a smooth and progressive power levers reduction. IN CASE OF SUDDEN AND HIGH VIBRATIONS
ICING CONDITIONS................................... ...................................CHECK Unbalanced blade icing may also generate propeller vibrations. In this case Refer to AFM - Procedure for Icing Conditions, or Refer to AFM - QRH SEVERE ICING procedure.
ENG PARAMETERS................................... ................................... CHECK Check for any fluctuations of power plant parameters that may indicate the affected engine, mainly TQ and NP. Check also for transient or steady alerts (PEC, ACW faults or any other alerts) that may be associated with power plant vibrations and indicate the affected engine.
If affected engine cannot be identified via engine parameters, flight crew should move one PL at a time: it may help to determine the affected side, as the vibrations level and frequency may change with PL position. IF AFFECTED ENGINE IS IDENTIFIED PL (affected eng).............................................................................. FI CL (affected eng)........................ ........................ FTR THEN FUEL S.O. LAND ASAP SINGLE ENG OPERATION procedure..........................................APPLY
IF AFFECTED ENGINE CANNOT BE IDENTIFIED PL 2................................................................................................ FI CL 2.............................................. .............................................. FTR IF VIBRATIONS SIGNIFICANTLY CHANGE
Engine 2 failure is suspected and should be shut down. CL 2....................................... ....................................... FUEL S.O. LAND ASAP SINGLE ENG OPERATION procedure.................. .................. APPLY
IF VIBRATIONS PERSIST Restore engine 2 and same check repeated on engine 1. CL 2......................................................................................AUTO PL 2................................................................................AS RQRD PL 1............................................. ............................................. FI CL 1........................................... ........................................... FTR IF VIBRATIONS SIGNIFICANTLY CHANGE
Engine 1 failure is suspected and should be shut down. CL 1..........................................................................FUEL S.O. LAND ASAP SINGLE ENG OPERATION procedure................................APPLY
END OF OEB 25
PK / 45 OEB 25 Page n°04
Uncommanded Autofeather _21f12523-3ff7-4ee4-8f05-fecbd32f16c7 4.1
ALL Procedure
TAKEOFF NORMAL PROCEDURE As a normal practice, at takeoff the ATPCS must be checked armed and announced Refer to FCOM - Takeoff. If it is not armed while both power levers are in the notch, or in the case of intermittent arming / disarming of the ATPCS, the takeoff has to be interrupted, as for any other anomaly intervening during the takeoff run.
ANY LOSS OF NP AND TQ MUST BE DEALT AS AN ENGINE FAILURE
AT TAKEOFF ENG 1(2) FLAME OUT AT TAKE OFF procedure............. ............. APPLY
AT ANY OTHER PHASE OF FLIGHT PL (affected eng).............................................................................. FI CL (affected eng)........................ ........................ FTR THEN FUEL S.O. LAND ASAP SINGLE ENG OPERATION procedure..........................................APPLY
END OF OEB 27
MFC 1B and-or MFC 2B Fault _cb0a75d6-9030-4a27-b36e-a994e40b6873 7.1
ALL Procedure
In flight If MFC 1B+2B FAULT MFC 1B.......................................... ..........................................RESET
Note RESET of each MFC must be performed one by one.
MFC 2B.......................................... ..........................................RESET If one MFC module recovered MFC (affected module) procedure............................................APPLY
If MFC 1B + 2B FAULT persist MFC 1B + 2B FAULT procedure....................... ....................... APPLY
For landing Nosewheel Steering is inoperative. Use rudder, differential braking and reverse which are still operative.
If MFC 1B (2B) FAULT MFC (affected module)............................... ............................... RESET If erroneous alert (Without Master Caution or Warning) persists MFC (operative module)............................ ............................ RESET
If MFC 1B (2B) FAULT persists MFC (affected module) procedure............................................APPLY
END OF OEB 28
Spurious Glide Slope Capture _160c3390-d49d-45a1-a82d-2b87d8b11f59 2.0
ALL Procedure
It is reminded to the flight crew that the GS interception must always be cross-checked by comparing altitude/distance between aircraft actual position and flight path published on the approach charts. After APP mode arming and when LOC* G/S deviations.............................. .............................. CLOSELY MONITOR FAP ALT/DIST................. ................. X CHECK WITH APPROACH CHARTS Note The flight crew should be prepared to take-over control in the case of a spurious G/S*, pitch movement or any flight path deviation.
In the case of a spurious G/S* AP .................................................. ..................................................OFF FD ................................................ ................................................ STBY FLIGHT PATH....................................... ....................................... ADJUST When back on the appropriate flight path AFCS ............................................. ............................................. SET AP ........................................... ........................................... AS RQRD
END OF OEB 30
ENGINE FIRE Warning _991cad58-ad82-43cb-97a9-097088b275a6 4.1
ALL Procedure
Procedure in case of ENG FIRE warning, in landing configuration, with PL at FI Following procedure has to be applied only in the following conditions:
- During steep slope descent at low speed (around 130 kt to final approach speed), and
- In landing configuration (Gear Down, Flaps 30 or 35) set at high altitude, and - Power Levers durably maintained at Flight Idle.
If ENG 1(2) FIRE warning during steep slope descent in landing configuration with PL at FI PL 1+2 ................................................................ADJUST ABOVE 10% TQ TQ increase improves the nacelle ventilation
If ENG 1(2) FIRE warning stops before 10 s PL 1+2 ........................................................MAINTAIN ABOVE 10% TQ LAND ASAP
If ENG 1(2) FIRE warning persists after 10 s ENG 1(2) FIRE OR SEVERE MECHANICAL DAMAGE IN FLIGHT
procedure........................................ ........................................ .APPLY MAINTENANCE REPORT............................. .............................PERFORM
Note Nacelles must be inspected in accordance with the appropriate maintenance procedures.
END OF OEB 32
Bank angle limitation in Severe Icing Conditions _fbbd16d8-a229-430d-9f1d-3447d5a07a3e 3.2
ALL Procedure
Recommendations: ATR reminds its strong recommendation to climb in IAS mode, with a target IAS set above the recommended speed (VmLB0 Icing in icing conditions, VmLB0 Icing + 10 kt in severe icing conditions). ATR informs that the additional 10 kt to VmLB0 Icing requested by the procedure protects the aircraft from stall only at low bank (<15 °) in severe icing conditions. ATR then reminds that the SEVERE ICING procedure asks for manual flying (AP OFF) and recommends to limit the bank angle to 15 ° when the IAS is below VmLB0 Icing + 30 kt. Procedure Add the following items to the DEGRADED PERF and SEVERE ICING procedures: If IAS < ICING BUG + 30 kt MAX BANK ANGLE : 15 °
Minimum icing speed and bank angle limitations:
CONFIGURATION LO BANK HI BANK
Icing conditions ICING BUG ICING BUG + 10 kt
DEGRADED PERF or SEVERE ICING
ICING BUG + 10 kt ICING BUG + 30 kt
Descend if necessary to maintain speed.
END OF OEB 36
Static Inverter Double Loss _6a722135-cde2-48b8-af47-269f36045394 1.0
ALL Procedure
STATIC INVERTER DOUBLE LOSS BTC .................................................. .................................................. ISOL C/B 3XA INV 1 127VU position AB3........................................................RESET C/B 10XA INV 2 124VU position AB4......................................................RESET KEEP FLYING WITH BTC ................................... ................................... ISOL If no static inverter recovered C/B 3XD 26VAC STBY BUS 122VU position Q39....................................OFF C/B 4XD 115VAC STBY BUS 122VU position Q40 ..................................OFF C/B 3XA INV 1 127VU position AB3......................... ......................... RESET C/B 10XA INV 2 124VU position AB4........................ ........................ RESET BTC ................................................. ................................................. ON
END OF OEB 42
Cockpit Voice Recorder _56636456-575e-4d78-b76e-ba55c0299b1f 3.0
0665 Procedure
The flight crew must use boomsets on ground and in flight below FL 100.
END OF OEB 43
Temporary ENG 1(2) OIL LO PR procedure _68994573-af56-4122-bbb0-3f2c7028e57c 0.2
ALL Procedure
In case of ENG 1(2) OIL LO PR alert, the flight crew must: - disregard the ENG 1(2) OIL LO PR procedure contained in the
PRO/NNO/ABN/70-POWER PLANT - apply the following procedure:
PL (affected ENG)........................................... ........................................... FI If both OIL LO PR alert on CAP and local alert are activated CL (affected ENG)....................................... ....................................... FTR After 10 seconds
If engine oil pressure no longer in red range CL (affected ENG)................................. ................................. AUTO ENGINE NORMAL OPERATIONS : RESUME MAINTENANCE ACTION REQUIRED
If engine oil pressure still in red range CL (affected ENG)............................................................FUEL S.O. LAND ASAP SINGLE ENG OPERATION procedure ( A70.12 ) ......................APPLY
If only local alert is activated CL (affected ENG)....................................... ....................................... FTR After 10 seconds
If engine oil pressure no longer in red range CL (affected ENG)................................. ................................. AUTO ENGINE NORMAL OPERATIONS : RESUME MAINTENANCE ACTION REQUIRED
If engine oil pressure still in red range CL (affected ENG)............................................................FUEL S.O. After engine shut down CL (affected ENG)................................ ................................FTR If CCAS activated after 30 s (normal warning delay) CL (affected ENG)..................................................FUEL S.O. ENG RESTART IN FLIGHT procedure ( A70.09 ) ............APPLY
If CCAS not activated after 30 s CL (affected ENG)..................................................FUEL S.O. LAND ASAP SINGLE ENG OPERATION procedure ( A70.12 ) ..... ..... APPLY
If OIL LO PR alert only activated on CAP ALERT : DISREGARD MAINTENANCE ACTION REQUIRED OIL PRESS LOCAL ALERT : MONITOR
If single engine operation NP (feathered ENG) : MONITOR If NP (feathered ENG) above 10 % IAS : LIMIT NOT TO EXCEED NP 101 % VAPP ....................................................................INCREASE BY 10 kt
Note Flight with an engine running and the propeller feathered is not permitted (Refer to AFM - Engine Parameters).
END OF OEB 49
1 Introduction _81435ea4-8e58-44fb-bcf6-8a92da74b84d 2.1
- OEB: Operations Engineering Bulletins (information to be added in upcoming revisions)
- GEN: General Information - LIM: Limitations (information to be added in upcoming revisions) - EMR: Emergency procedures - ABN: Abnormal procedures - NOR: Normal procedures - PER: Performance (Operational Data) - NCL: Normal Checklist (In the back of the QRH)
The Abnormal and Emergency Procedures are organized by aircraft system following ATA numbering system, as much as practical, (21. Air Conditioning, 22. Auto Pilot, 23. Communication, etc…). To easily locate a procedure within ATA chapter the procedures are sequenced in alphabetical order.
2 Procedures Initiation _2f7864eb-b1c1-46b3-b99e-b8d16473820f 1.0
ALL No action shall be initiated (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 procedure initiation, flight crew must assess the situation as a whole, taking into consideration the failures (when fully identified) and the constraints imposed.
3 Failure Consequences Analysis _d132efdd-00df-40f8-a082-c13b9e41e3a0 3.1
ALL The flight crew must assess the failures when fully identified and the constraints it imposes and make decision based on the remaining aircraft capabilities with the awareness of the current operational situations (condition, environment, and/or constraint). a) System Reset At flight crew discretion, one RESET of a failed system associated to an amber caution may be performed by selecting the related pb (push-button) OFF (for 3 s) then ON except for systems listed below. If the failure alert disappears, continue normal operation and record the event in the aircraft maintenance logbook for information. If not, apply the associated abnormal procedure. For the following systems the flight crew should strictly follow the abnormal procedure and RESET only when it is called by the abnormal procedure:
- ECU / EEC. - PEC. - CAB PRESS MODE SEL. - BAT CHG (EMER & MAIN).
In case of BLEED LEAK, or BUS FAULT alerts, do not reset the associated systems BLEED VALVE pb or GEN pb. b) Circuit Breaker (C/B) Reset CAUTION Circuit Breaker (C/B) must not be RESET by the flight crew unless otherwise specified in the operational documentation by ATR.
GENERAL INFORMATION QRH GEN PK / 45 Page n°01
cont'd…
- Flight Crew may REENGAGE a tripped circuit breaker ONLY IF HE/SHE JUDGES IT IS NECESSARY FOR A SAFE CONTINUATION OF THE FLIGHT. In this case only ONE reengagement should be attempted. If the failure alert disappears, continue normal operation, if not apply the associated abnormal procedure.
- Regardless the outcome on system behavior, when reengaging a tripped C/B, the flight crew must make a « Maintenance Action Required » entry in the Aircraft maintenance logbook describing the event.
WARNING DO NOT REENGAGE THE C/B OF THE FUEL PUMP(S).
Note Due to many customization possibilities of the C/B panels, before taking any action on a C/B, the flight crew must crosscheck that the C/B label corresponds to the affected system.
GENERAL INFORMATION QRH GEN PK / 45 Page n°02
cont'd…
L00.00 Introduction _63cea41d-8e83-47da-8aa8-e3e36f695851 1.2
ALL This section contains only the limitations that flight crew refer to on a regular basis. The complete AFM/FCOM Limitations section (LIM) and the limitations associated to Special Operations (PRO/SPO) remain applicable and must be adhered to. As much as practical, the information contained in this section is organized in the same way as the AFM/FCOM Limitations section. All references to airspeed and altitude relate to indicated values, unless otherwise specified.
LIMITATIONS LIM 1
PAGE
INTENTIONALLY
2 Maneuvering Limit Load Factors _50f667d9-e2a5-4754-b6ff-2f59e971a16f 0.1
ALL AFM DATA Gear and flaps retracted....................................................................+2.5 g to -1 g Gear and/or flaps extended................................. ................................. +2 g to 0 g
3 Maximum Number of Seats Maximum Number of Passenger Seats _65c35a0e-6ca5-4e70-86e3-f483f3eeae5f 0.1
ALL AFM DATA 60
PAGE
INTENTIONALLY
ALL
ZERO FUEL 16 700
2.1 CERTIFIED CENTER OF GRAVITY 1 Certified Center of Gravity Envelope _cf6e2dbd-2709-40eb-8637-d1acb4bb7657 5.1
ALL The limits of the center of gravity are given in percentage of the Mean Aerodynamic Chord (MAC), landing gear extended. The MAC is 2.285 m long. Station 0 is 2.362 m forward of the fuselage nose. The distance from station 0 to reference chord leading edge is 11.425 m.
ICN-4X-Y-000000-T-FB429-00250-F-01-N
9
10
11
12
13
14
15
16
17
18
19
-50 -40 -30 -20 -10 0 10 20 30 40Index Index
11 13 15 17 19 21 23 25 27 29 31 33 35 %MAC
MTOW : 18 600 kg
MLW : 18 300 kg
MZFW : 16 700 kg
cont'd…
WARNING CERTIFIED CENTER OF GRAVITY ENVELOPE MUST NOT BE USED FOR OPERATIONAL PURPOSE. PROPER OPERATIONAL CENTER OF GRAVITY ENVELOPE MUST BE DEFINED. REFER TO WBM - WBM LIM.1.16: OPERATIONAL CENTER OF GRAVITY ENVELOPE FOR FURTHER DETAILS.
LIMITATIONS LIM 3
cont'd…
ALL
VA Max. Design Maneuvering Speed 160 kt
VFE Max. Flaps Extended Operating Speeds
FLAPS 15 180 kt
FLAPS 25 160 kt
FLAPS 35 150 kt
VLO RET Max. Landing Gear Operating Speed (retraction) 160 kt
VLO LOW Max. Landing Gear Operating Speed (extension) 170 kt
VRA Max. Rough Air Speed 180 kt
VWO Max. Wipers Operating Speed 160 kt
CAS
VMCL
VMCG Refer to AFM/LIMITATIONS/SPEEDS/ MINIMUM CONTROL SPEEDS/ TAKEOFF V1 LIMITED BY VMCG
GS
LIMITATIONS LIM 4
2 Stall Speeds _75a24d19-0792-4722-8597-6daaa678ff42 0.4
ALL
ICN-4X-Y-000000-T-FB429-00011-C-02-N
35 / DOWN
25 / UP
15 / UP
0 / UP
105
90
85
80
70
115
3 Recommended Conservative Maneuvering Speed _f64e59b5-9bc6-4215-b52c-19eb49252432 1.1
ALL When performance consideration does not decide use of minimum maneuver speeds, the following conservative maneuvering speeds are recommended.
LIMITATIONS LIM 4
cont'd…
They cover all weight, for high bank operational maneuver, at all flight conditions (normal or icing):
- FLAPS 0: 175 kt - FLAPS 15: 145 kt - FLAPS 25: 135 kt - FLAPS 35: 125 kt
LIMITATIONS LIM 4
cont'd…
PAGE
INTENTIONALLY
ALL AFM DATA
2.1 WIND LIMITATION 1 Tailwind _664c0c7b-2691-496e-8313-0d3e49c5a057 0.2
ALL AFM DATA Takeoff and Landing Tailwind limit................................................ ................................................15 kt Note The limitation for tailwinds greater than 10 kt reflects the capability of the aircraft as evaluated in terms of airworthiness but does not constitute approval for operations under tailwinds exceeding 10 kt in case such operational approval is required by the National Authorities to the Operators.
LIMITATIONS LIM 5
2 Crosswind _f82e32cd-0c94-4fdc-91e6-de2b60fe4260 REV 4.1
ALL AFM DATA The maximum demonstrated crosswind on dry runway is: Takeoff................................................... ................................................... 45 kt Landing FLAPS 25........................................... ........................................... 45 kt Landing FLAPS 35........................................... ........................................... 44 kt The maximum recommended crosswind on wet runway is: Takeoff................................................... ................................................... 37 kt Landing FLAPS 25........................................... ........................................... 37 kt Landing FLAPS 35........................................... ........................................... 37 kt For contaminated runway, Refer to PRO.SPO.13.1.2 Maximum Recommended Crosswind. For crosswind operations, Refer to FCOM OPERATIONS IN WIND CONDITIONS.
3.1 RUNWAY 1 Runway Slope _12c30841-cefa-466f-b78b-45bbe6fd7787 1.3
ALL AFM DATA Maximum mean runway slope................................... ................................... ±2 % For operations on runways slope beyond 2 %, Refer to RUNWAYS SLOPE BEYOND 2 %.
LIMITATIONS LIM 5
4.1 DETERMINATION OF WIND COMPONENT
1 CROSSWIND DIAGRAM IN TAKEOFF AND LANDING _6416d51c-0ce5-41cf-b19c-b60b5ed7f4ec NEW 0.4
ALL 1) CROSSWIND DIAGRAM IN TAKE OFF AND LANDING FLAPS 25
1-POOR
3-MEDIUM
5-GOOD
ICN-XX-Y-000000-T-FB429-00060-A-01-N
110°
100°
90°
80°
70°
60°
50°
40°
30°
20°
10°
0
5
10
15
20
25
30
10
10
10
35
40
45
50
55
-15
-10
-5
-20
100 20 30 40 50 60
EXAMPLE: QFU 25 WIND 280°/25 kt WIND ANGLE = 30° HEAD - WIND = 21.5 kt CROSS - WIND = 12.5 kt
Tailwind limit
WIND ANGLE
CAT II OPERATION : Headwind : kt30 Tailwind : 1 kt3 Crosswind : kt25
C ro
ss w
in d
in cl
. g us
te s
- w et
r un
w ay
C ro
ss w
in d
in cl
. g us
te s
- d ry
r un
w ay
LIMITATIONS LIM 5
cont'd…
1-POOR
3-MEDIUM
5-GOOD
ICN-XX-Y-000000-T-FB429-00059-A-01-N
110°
100°
90°
80°
70°
60°
50°
40°
30°
20°
10°
0
5
10
15
20
25
30
10
10
10
35
40
45
50
55
-15
-10
-5
-20
100 20 30 40 50 60
EXAMPLE: QFU 25 WIND 280°/25 kt WIND ANGLE = 30° HEAD - WIND = 21.5 kt CROSS - WIND = 12.5 kt
Tailwind limit
WIND ANGLE
CAT II OPERATION : Headwind : kt30 Tailwind : 1 kt3 Crosswind : kt25
C ro
ss w
in d
in cl
. g us
te s
- w et
r un
w ay
C ro
ss w
in d
in cl
. g us
te s
- d ry
r un
w ay
ALL CAT 2 approaches are flown with AP + FD ON.
2 AP-FD Heights Limitations _7e7031df-35d7-4dd8-93af-136f052c616b 0.1
ALL
LIMITATIONS
Minimum height for use of AutoPilot in approach mode ............ ............ 80 ft Minimum decision height................................. .................................100 ft
LIMITATIONS LIM 5
cont'd…
cont'd…
ALL
Autopilot
cont'd…
ALL
AP quick disconnect 1 (PF side)
AP OFF warning (light and aural)
1
SGU 2
DH indicator 2
Yaw damper 1
Airspeed indicators 2: - F/O side must be operative a - If CAPT is PF, CAPT side must be
operative
AC: BUS1 / BUS2 / STBY ACW: BUS1 / BUS2
MFC modules 3
Probe Heating 3 Pitots, 6 statics, 2 AOAs and 2 TATs
a The standby airspeed instrument can be easily monitored only from the CAPT position (Captain position).
LIMITATIONS LIM 5
ALL AFM DATA Maximum differential pressure................................. ................................. 6.35 psi Maximum negative differential pressure........................... ........................... -0.5 psi Maximum differential pressure for landing......................... ......................... 0.35 psi Maximum differential pressure for OVBD VALVE full open selection....................1 psi Maximum altitude for one bleed off operation ...................... ...................... 20 000 ft
2.1 AUTO FLIGHT 1 Automatic Flight Control System _c3a644e5-340a-4955-91a4-0bf93333e57a 2.1
ALL Note For CAT II operation, Refer to CAT 2 APPROACH.
AFM DATA Minimum height for AP engagement after takeoff............................................ 100 ft NAV mode for VOR approach with either AP or FD is authorized only if:
- A collocated DME is available - DME HOLD is not selected.
Minimum height for use of either AP or FD: - Except during takeoff or approach......................... ......................... 1 000 ft - VS or IAS mode during approach .......................... .......................... 160 ft - CAT I APP mode...................................... ...................................... 160 ft
For CAT II operation, Refer to CAT 2 APPROACH.
3.1 ELECTRICAL POWER 1 Electrical System _a9298c1b-49a7-42db-81e2-0eddea1a6b1b 1.0
ALL Single DC GEN operation : In flight, if OAT exceeds ISA + 25 Flight level must be limited to FL200.
4.1 FLIGHT CONTROLS 1 Flaps _45c194a4-4b36-4162-ac33-256aff611625 1.2
ALL AFM DATA Holding with any flaps extended is prohibited in icing conditions (except for single engine operations).
LIMITATIONS LIM 6
5.1 ICE AND RAIN PROTECTION 1 Ice and Rain Protection _1f431dc4-7cb1-44d2-a881-0c3321d4803d 0.2
ALL
1) Icing Conditions AFM DATA All icing detection lights must be operative before a night flight. The ice detector must be operative.
7.1 PBN CAPABILITIES 1 PBN Capabilities _cffcd749-6a32-4ac0-a27e-4d2c8b48b584 2.2
ALL PBN capability of Honeywell/Trimble GNSS 1000 operating with HT 1000-60 (or later) software is RNAV5, RNAV2, RNAV1 and RNP1. Minimum Equipment Required: Minimum required equipment to enter RNAV5 airspace is:
- 1 RNAV system, implying: o 1 Current and valid navigation database o 1 MCDU o Navigation Source selection (on ECP) o 1 VOR and 1 DME capable of VOR/DME and /or DME/DME position
computation or 1 GNSS receiver - 1 EHSI - 1 EADI.
Minimum required equipment to enter RNAV1/RNAV2 airspace is: - 1 RNAV system, implying:
o 1 Current and valid navigation database o 1 MCDU o NAV SOURCE selection o 1 DME capable of DME/DME position computation or 1 GNSS receiver
(GPS may be required for RNAV1 terminal procedures) - 1 CDI (NAV lateral deviation) - EHSI - EADI.
Minimum required equipment to enter RNP1 airspace is: - 1 RNAV system, implying:
o 1 Current and valid navigation database o 1 MCDU o Navigation Source selection (on ECP) o 1 DME capable of DME/DME position computation AND 1 GNSS
receiver - 1 CDI (NAV lateral deviation) - EHSI - EADI.
LIMITATIONS LIM 6
8.1 OXYGEN 1 Minimum Bottle Pressure _53d5d86d-1ecd-4f0d-96cb-228f99570e21 REV 1.1
ALL
ICN-4X-Y-350000-T-FB429-00030-A-01-N
(minutes)
1900
Reference Temperature
: 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 min and a flight continuation at an altitude below 13 000 ft. A 25 % pax oxygen consumption is considered. In the case of smoke emission, the system protects the flight crew members during 15 min. Note Refer to national operational regulations to define minimum oxygen quantity requirement. Minimum oxygen pressure charts :
- Unusable oxygen quantity - Normal system leakage - Reference temperature errors.
9.1 DOORS 1 Cargo Door Operation _5c5010fd-2cbe-42d8-8139-ef06ea0c245c 0.1
ALL AFM DATA Do not operate cargo door with a lateral wind component of more than 45 kt.
LIMITATIONS LIM 6
10.1 POWER PLANT 1 Overtemperature Limit for Starting _034fe4b3-04ba-4c55-93c1-413da6afebc0 0.1
ALL
ICN-4X-Y-000000-T-FB429-00027-B-01-N
ALL
ICN-4X-Y-000000-T-FB429-00028-E-01-N
3 Overtorque Limit _03788e69-0a60-407c-ad4f-1c6bd2a88505 3.2
ALL
ICN-4X-Y-000000-T-FB429-00026-E-03-N
RECORD IN ENG LOG BOOK (except when note below applies)
REFER TO MAINTENANCE MANUAL
Note Operation up to 117 % torque is time unlimited when NP is below 90 %.
LIMITATIONS LIM 6
4 ITT Limitation at Normal Takeoff Rating _8f8a63b1-9deb-49e2-b858-0984bba8221d 0.1
ALL AFM DATA
760
780
765
50
5 Engine Parameters _6454c00d-bdc0-42b2-b799-569647289965 4.1
ALL AFM DATA Operating limits with no unscheduled maintenance action required. Beyond these limits Refer to maintenance manual.
POWER SETTING
TIME LIMIT
10 min f
100 a 800 103.2 104.2 101 55 to 65 0 to 125
NORMAL TAKEOFF 5 min 90 a e 101.9 101.4 101 55 to 65 0 to 125
MAXIMUM CONTINUOU
NONE g
100 a 800 103.2 104.2 101 55 to 65 0 to 125
GROUND IDLE
66 minimu
TRANSIENT h
20 s 137 840 104.3 106.5 106 40 to 100
5 s 120
OTHER 106 c
20 min 140
STARTING 5 s 950 -54 minimum
a Value linked to 100 % NP. b The flight crew must maintain the oil temperature above 45 °C in order to ensure
protection for the engine air inlet against ice accumulation. c Authorized to achieve a flight provided that TQ does not exceed 85 % in CLB and
84 % in CRZ. d Up to 75 % NH only. e ITT limits depend on outside air temperature. Refer to LIM.6.10.1.3 ITT Limitation
at Normal Takeoff Rating. f Time beyond 5 min is for single engine operations only. g MCT rating is the MAX power certified for continuous use. Only for in-flight
emergencies use the MCT. h Transient is defined as change in temperature caused by movement of the PLA
or CLA or an altitude change.
Note Flight with an engine running and the propeller feathered is not permitted.
6 Starter _a67b7d33-cb4f-458c-abea-8de9db88f2d8 0.1
ALL AFM DATA 3 starts within 1 min 30 s maximum combined starter running time followed by 4 min OFF.
LIMITATIONS LIM 6
11.1 FUEL SYSTEM 1 Fuel System _b7eba2e2-f0fd-4230-be2a-5e7ab8bd3d18 0.1
ALL
(°C)Starting Operation
RT -55 -34 -60 +57
TS–1 -60 -34 -60 +57
JP 5 -46 -26 -33 +57
JP 8 -47 -34 -48 +57
Note Use of JP4 and Jet B is prohibited.
USABLE FUEL
Total quantity of fuel usable in each tank 2 250 kg (4 960 lb)
Note Fuel remaining in the tanks when quantity indicators show zero is not usable in flight.
FUEL UNBALANCE
REFUELING
LIMITATIONS LIM 6
1.1 STEEP SLOPE APPROACH 1 Limitations _98a9ae39-0813-4c9e-889c-bce2c51a5dae 0.1
ALL (APPROACH SLOPE > 4.5 °) NOT APPLICABLE.
2.1 OPERATIONS ON NARROW RUNWAYS
1 Limitations _9c75239d-24ed-412a-ad19-f56f90e68733 REV 4.4
ALL The limitations of this Flight Manual (Refer to LIMITATIONS) must be completed by the following: Minimum runway width .................................... .................................... 14 m (46 ft) Maximum recommended crosswind for takeoff and landing on dry runway...... ...... 25 kt Maximum recommended crosswind for takeoff and landing on wet runway...... ......20 kt Refer to PROCEDURE/SPO/OPERATION ON NARROW RUNWAYS /ADVISORY MATERIAL – NON DRY RUNWAYS (Refer to AFM - Maximum Recommended Crosswind) for contaminated runway. The following equipment is required:
- Both ACW generators - Both main and DC auxiliary hydraulic pumps - MFC modules 1B and 2B - Nose wheel steering.
Note Refer to MMEL (ATA 61) in case of PEC inoperative.
LIMITATIONS LIM 7
PAGE
INTENTIONALLY
Alert Procedure Code
SMOKE or FUMES E26.01
E27.01
ENG 1(2) FIRE OR SEVERE MECHANICAL DAMAGE IN FLIGHT
E70.02
E70.03
ENG 1+2 FLAME OUT E70.05
BOMB ON BOARD E99.01
DITCHING E99.03
FORCED LANDING E99.06
SEVERE ICING E99.08
PACK 1+2 VALVES FAULT A21.03
RECIRC FAN 1(2) FAULT A21.06
AVIONICS VENT EXHAUST MODE FAULT A21.08
OVBD VALVE FAULT A21.09
AUTO PRESS FAULT A21.10
EXCESS CAB ALT A21.13
A22.01
AP PITCH TRIM FAIL (ADU MESSAGE) A22.04
DADC DATA INVALID (ADU MESSAGE) A22.05
CAS MESSAGES LIST QRH PRO PK / 45 Page n°01
XPDR FAULT A23.05
26 AC STBY BUS FAULT DETECTION A24.03
26 V AC STBY BUS FAULT A24.04
ACW BUS 1 OFF A24.06
ACW GEN 1(2) FAULT A24.08
ACW GEN 1+2 LOSS A24.09
BAT DISCHARGE IN FLIGHT A24.10
DC BUS 1 OFF A24.11
DC BUS 2 OFF A24.12
DC EMER BUS OFF A24.13
DC ESS BUS OFF A24.14
DC GEN 1(2) FAULT A24.15
DC SVCE-UTLY BUS SHED A24.18
EMER(MAIN) BAT CHG FAULT A24.19
EMER+MAIN BAT CHG LOSS A24.20
INV 1(2) FAULT A24.21
PITCH DISCONNECT A27.07
PITCH TRIM ASYM (LOCAL LIGHT) A27.10
PITCH TRIM INOPERATIVE A27.12
STICK PUSHER-SHAKER FAULT A27.13
AIL LOCK LIT A27.14
A27.17
RUDDER JAM A27.18
TLU FAULT A27.19
FUEL CLOG A28.02
FUEL LEAK DETECTION A28.04
HYD BLUE (GREEN) OVHT A29.03
HYD BLUE AND GREEN PUMPS LOSS A29.04
HYD BLUE AND GREEN SYS LOSS A29.05
HYD AUX LO PR A29.06
HYD AUX OVHT A29.07
AFR AIR BLEED FAULT A30.05
DE-ANTI ICING MODE SEL AUTO FAULT A30.06
DE ICING AIRFRAME FAULT A30.07
DE ICING MODE SEL FAULT A30.08
DE ICING ENG 1(2) FAULT A30.09
ICE DETECT FAULT A30.10
PROBES HTG FAILURE A30.11
WINDSHIELD HTG FAULT A30.13
ANTISKID FAULT A32.01
LDG GEAR RETRACTION NOT POSSIBLE A32.04
LDG GEAR UNSAFE INDICATION A32.05
LANDING WITH ABNORMAL LDG GEAR A32.06
ADC 1(2) FAILURE A34.01
ADC SW FAULT A34.03
AHRS 1(2) FAILURE A34.05
CRT FAIL A34.52
EFIS FAILURE A34.53
SGU FAIL A34.54
BLEED LEAK 1(2) A36.02
BLEED 1(2) OVHT A36.03
ENG BLEED 1(2) FAULT
PEC 1(2) FAULT A70.05
ENG 1(2) FLAME OUT IN FLIGHT A70.07
ENG 1(2) FLAME OUT ON GROUND A70.08
ENG RESTART IN FLIGHT A70.09
ENG STALL A70.10
SINGLE ENG OPERATION A70.12
ENG 1(2) OIL TEMP BELOW 45 °C A70.15
ENG 1(2) OIL TEMP HIGH A70.16
ENG NAC OVHT A70.18
UNEXPECTED 100 % NP ON ONE OR TWO ENGINES
A70.20
START 1(2) FAULT A70.26
X START FAIL A70.27
IDLE GATE FAIL A70.31
DOORS UNLK IN FLIGHT A99.02
OXYGEN LO PR A99.03
COCKPIT WINDOW CRACKED A99.05
VOLCANIC ASH ENCOUNTER A99.06
PAGE
INTENTIONALLY
1 General _bc2abd95-11dc-4339-9e3d-18450d46b5c9 1.4
ALL 1) Memory Item
- Memory item are BOXED. - Boxed actions are considered time-critical and should be memorized and
executed from memory. 2) Actions
- Actions are identified by the symbol . - Actions can be immediate in the form of CHALLENGE………RESPONSE, or
lasting in the form of SYSTEM STATE or ACTION or VALUE : DESCRIPTION.
- A lasting action can be for the remaining of flight, phase, or as long as a condition exist.
3) Conditions - When an action(s) is dependent of a condition the condition is identified by the
symbol . 4) Phases
- When actions have to be applied at phase of procedure/flight is identified by the symbol .
5) Information - Applicable information associated with an action of failure situation is presented
in all capital letters without any symbol e.g. MAINTENANCE ACTION REQUIRED, AP CAN BE REENGAGED.
6) Procedures – Checklists Priorities Procedures in QRH are classified in 3 parts:
- EMERGENCY - NORMAL - ABNORMAL
The CCAS generates alerts (Warnings & Cautions) as soon as a system malfunction is detected. The flight crew has to comply with the same hierarchy (Emergency, normal and abnormal procedures) when using QRH. 7) Flight phases sections versus Normal Checklists Some emergency or abnormal procedures contains flight phase sections that are not a substitude for the normal checklist. For example, "Before landing" section in the ACW GEN 1+2 LOSS procedure or in other emergency or abnormal procedures must be applied when required, and "Before Landing" normal checklist remains mandatory and applicable as per checklist methodology.
PROCEDURE PRO PLE PK / 45 Page n°01
PAGE
INTENTIONALLY
SMOKE or FUMES E26.01
E27.01
ENG 1(2) FIRE OR SEVERE MECHANICAL DAMAGE IN FLIGHT
E70.02
E70.03
ENG 1+2 FLAME OUT E70.05
BOMB ON BOARD E99.01
DITCHING E99.03
FORCED LANDING E99.06
SEVERE ICING E99.08
PAGE
INTENTIONALLY
_a5a61789-3c99-4ea4-acf8-e5a7d07de54e 7.1 ALL
If no generator recovered HYD GREEN PUMP ................................... ................................... OFF TRU ................................................................................................ON
If no TRU arrow light MAX IMC FLIGHT TIME : 30 min TRU ........................................... ........................................... OFF LAND ASAP
BAT sw ........................................... ........................................... OVRD CAB PRESS RATE knob ................ ................ 9 O'CLOCK (MAN position) CAB PRESS MODE SEL ................................................................ MAN AVIONICS VENT EXHAUST MODE ....................... ....................... OVBD ATC (VHF 1) ...................................... ...................................... NOTIFY MIN CAB LT ......................................... ......................................... OFF ADC sw .................................... .................................... SELECT ADC 1 ATC ....................................... ....................................... SELECT ATC 1 TLU sw .................................................................................... LO SPD
When RUD TLU LO SPD comes on TLU sw ................................................................................ AUTO
If IAS above 180 kt LARGE RUDDER INPUT........................................................AVOID
STICK PUSHER-SHAKER FAULT procedure ( A27.13 ) ......... ......... APPLY SIDE WINDOWS pb ........................................................................OFF WINDSHIELD HTG pb .................................. .................................. OFF AUTO PRESS FAULT procedure ( A21.10 ) ....................................APPLY BUS EQUIPMENT LIST ............................... ...............................CHECK Refer to STBY BUSSES AND BAT ONLY LOST EQUIPMENT LISTS (FCOM-PROCEDURES-NNO-ABN-24-ELECTRICAL-POWER-4-LOST EQUIPMENT LIST-1-STBY BUSSES AND BAT ONLY LOST EQUIPMENT LISTS)
For approach PAX INSTRUCTIONS ..........................................................USE PA HYD X FEED ...................................... ......................................ON
At touchdown IDLE GATE lever ....................................................................PULL
EMERGENCY PRO NNO PK / 45 Page n°01
PAGE
INTENTIONALLY
EMR.26 SMOKE
RECIRC FANS 1+2................... ................... OFF AP ............................... ............................... ON CABIN CREW COMMUNICATIONS.. .. ESTABLISH
CAUTION ELEC SMK warning may be triggered by an air conditioning smoke source.
SMOKE / FUMES SOURCE ................IDENTIFY If electrical smoke/fumes identified ELECTRICAL SMOKE procedure ( E26.02 ) ........
............................................................. APPLY If air conditioning smoke/fumes identified AIR COND SMOKE procedure ( E26.03 ) ............
............................................................. APPLY If FWD SMK comes on or smoke/fumes in FWD zone of aircraft FWD SMOKE procedure ( E26.04 ) ..... .....APPLY
If AFT SMK comes on or smoke/fumes in aft zone of aircraft AFT SMOKE procedure ( E26.06 ) ............APPLY
If smoke/fumes source not identified Note Refer to FCOM - QRH PRO/NNO/EMR/26/SMOKE SOURCE DETECTION provides additional guidance to identify smoke/ fumes source.
ELECTRICAL SMOKE procedure ( E26.02 ) ........ ............................................................. APPLY
SMOKE SOURCE DETECTION SMOKE or FUMES SOURCE DETECTION _abfacd78-3e24-4101-a4cd-2fbe750f4c31 0.2
ALL - If smoke/fumes initially comes out of the ventilation outlets, the crew may
suspect air conditioning smoke. - Upon an engine failure or in case of engine abnormal parameters, smoke/
fumes may come from the bleed air system of the engine. In this case, air conditioning smoke can be considered.
- If the smoke/fumes is detected while an equipment is declared faulty or with a C/B tripped off, the crew may suspect that smoke/fumes is coming from this equipment.
- Burning equipment may be smelt or may enter the cockpit before ELEC SMK warning activation.
- Recirculation fans can propagate smoke/fumes in all the pressurized areas. Therefore, several smoke warnings may be triggered.
_50eded2b-d359-4f7f-b1eb-1f4e07b3d10e 3.3 ALL
- E26.02 ELECTRICAL SMOKE SMOKE or FUMES procedure ( E26.01 ) .. .. APPLY CAUTION ELEC SMK warning may be triggered by an air conditioning smoke source
AVIONICS VENT EXHAUST MODE...... ...... OVBD AIR FLOW......................... .........................HIGH DC SVCE & UTLY BUS..................................OFF DC BTC .......................... .......................... ISOL ICING CONDITIONS : LEAVE AND AVOID ACW GEN 1 + 2............................................OFF SUSPECTED EQUIPMENT............................OFF If smoke source not identified LAND ASAP ACW GEN 1+2 LOSS procedure ( A24.09 ) .........
............................................................. APPLY If smoke source identified OPERATING EQUIPMENT........ ........ RESTORE Note Restore ACW GEN, DC BTC and/or DC SVCE & UTLY BUS if appropriate
AFFECTED EQUIPMENT FAULT PROCEDURES .............................. .............................. APPLY
When P below 1 psi OVBD VALVE ................ ................ FULL OPEN AVIONICS VENT EXHAUST MODE.......... NORM
_e10128ed-55e0-4062-ba90-de025e1cd54c 5.1 ALL
- E26.03AIR COND SMOKE SMOKE or FUMES procedure ( E26.01 ) .. .. APPLY PACK VALVE 1...................... ...................... OFF MAX FL : 200/MEA CAUTION Air conditioning smoke may trigger an ELEC SMK warning. Do not apply ELECTRICAL SMOKE procedure in this case.
If smoke persists PACK VALVE 1...................... ...................... ON PACK VALVE 2..................... ..................... OFF ENG PARAMETERS : CAREFULLY MONITOR
If ENG amber on CAP associated to local ITT alert - OR -
Total loss of NL indication - OR -
Engine abnormality clearly identified (NH, NL, ITT indications, noise, surge...)
CAUTION Identify the engine that shows signs of abnormal operation in order to avoid shutting down the safe engine.
PL (affected ENG).................... .................... FI CL (affected ENG)............ FTR THEN FUEL S.O. LAND ASAP SINGLE ENG OPERATION procedure ( A70.12 )
.............................. .............................. APPLY
_057ea1a6-e8c4-4158-a983-ef79edf9da04 6.7 ALL
- E26.04 FWD SMOKE SMOKE or FUMES procedure ( E26.01 ) .. .. APPLY If passenger configuration CABIN CREW (PA)..... ..... ADVISE FOR ACTION AVIONICS VENT EXHAUST MODE .......... OVBD AIR FLOW................................................HIGH EXTRACT AIR FLOW lever ......... .........CLOSED LAND ASAP When P below 1 psi OVBD VALVE ..............................FULL OPEN AVIONICS VENT EXHAUST MODE ...... NORM
If cargo configuration CAUTION FWD SMK warning may be triggered by an air conditioning smoke source.
CAB PRESS MODE SEL ............. ............. MAN CAB ALT ................ ................ MAX INCREASE CREW OXY MASKS............. ............. AS RQRD If dual bleed operation ENG BLEED 2.................... .................... OFF
If dual pack operation PACK VALVE 2........................................OFF
CAB VENT AIR FLOW................ ................ OFF FLT COMPT TEMP SEL .............. .............. HOT LAND ASAP If immediate landing is not possible FL : 160/HIGHER (FL 200 is recommended) When EXCESS CAB ALT warning is triggered CAB ALT .......... MAINTAIN MAX INCREASE
Note Other smoke detection alarms maybe triggered during smoke evacuation process. Disregard them.
_0af7a442-901d-41b5-bbfa-0c5b1f3bb452 5.3 ALL
- E26.06AFT SMOKE SMOKE or FUMES procedure ( E26.01 ) .. .. APPLY If passenger configuration CABIN CREW (PA)..... ..... ADVISE FOR ACTION AIR FLOW................................................HIGH LAND ASAP
If cargo configuration CAUTION AFT SMK warning may be triggered by an air conditioning smoke source.
CAB PRESS MODE SEL ............. ............. MAN CAB ALT ................ ................ MAX INCREASE CREW OXY MASKS............. ............. AS RQRD If dual bleed operation ENG BLEED 2.................... .................... OFF
If dual pack operation PACK VALVE 2........................................OFF
CAB VENT AIR FLOW................ ................ OFF FLT COMPT TEMP SEL .............. .............. HOT LAND ASAP If immediate landing is not possible FL : 160/HIGHER (FL 200 is recommended) When EXCESS CAB ALT warning is triggered CAB ALT .......... MAINTAIN MAX INCREASE
Note Other smoke detection alarms maybe triggered during smoke evacuation process. Disregard them.
PAGE
INTENTIONALLY
EMR.27 FLIGHT CONTROLS
_e2d6a6fe-cd3a-4bd2-a65d-c2f93ffd7cfc 2.1 ALL
MAX IAS : 180 kt CONTROL COLUMNS................................................................UNCOUPLE FREE CONTROL COLUMN............................................................IDENTIFY PF..............................................................FREE CONTROL COLUMN SIDE PITCH DISCONNECT procedure ( A27.07 ) ..........................................APPLY
PAGE
INTENTIONALLY
_a59ac6be-ceda-4256-adc0-efba27c1cca1 4.5 ALL
- E70.01ENG 1(2) FIRE AT TAKEOFF Note Captain may decide to shut down affected engine before reaching acceleration altitude, but not before 400 ft AGL
WHEN AIRBORNE LDG GEAR..........................................................................................UP
AT VFTO If normal conditions FLAPS..............................................................................................0
If icing conditions FLAPS : MAINTAIN 15°
PL (affected ENG)........................................ ........................................ FI CL (affected ENG)......................... ......................... FTR THEN FUEL S.O. FIRE HANDLE (affected ENG)............................. ............................. PULL If fire persists after 10 s AGENT 1 (affected ENG)............................................................DISCH If fire persists 30 s after AGENT 1 DISCH AGENT 2 (affected ENG)........................... ........................... DISCH
LAND ASAP BLEED (operating ENG)......................................................OFF (if necessary) ATC................................................ ................................................ NOTIFY ENG (affected) : DO NOT RESTART SINGLE ENG OPERATION procedure ( A70.12 ) ................. ................. APPLY
_a82963e0-df9b-43e1-a3fe-b607b9a30dc1 2.4 ALL
PL (affected ENG).......................................... .......................................... FI CL (affected ENG)........................... ........................... FTR THEN FUEL S.O. FIRE HANDLE (affected ENG)............................... ............................... PULL If fire persists after 10 s AGENT 1 (affected ENG)................................ ................................ DISCH If fire persists 30 s after AGENT 1 DISCH AGENT 2 (affected ENG)............................................................DISCH
LAND ASAP ATC................................................ ................................................ NOTIFY ENG (affected) : DO NOT RESTART SINGLE ENG OPERATION procedure ( A70.12 ) ................. ................. APPLY
_57751aa9-ee1c-400c-9bf1-83f854c2e5e2 3.4 ALL
- E70.03 ENG 1(2) FIRE OR SEVERE MECHANICAL DAMAGE ON GROUND
AIRCRAFT..........................................................................................STOP BRAKE HANDLE............................................................................PARKING CL 1+2................................... ................................... FTR THEN FUEL S.O. FIRE HANDLE (affected ENG)............................... ............................... PULL If fire persists AGENT 1 (affected ENG)................................ ................................ DISCH If fire persists 30 s after AGENT 1 DISCH AGENT 2 (affected ENG)............................................................DISCH
ATC (VHF 1).......................................... .......................................... NOTIFY If evacuation required EMERGENCY EVACUATION (ON GROUND) procedure ( E99.05 ) ... ..APPLY
_68595bbb-7052-4b4b-bbb4-d217d85b9328 2.1 ALL
WHEN AIRBORNE LDG GEAR..........................................................................................UP If NO BLEEDS 1 + 2 FAULT BLEEDS 1 + 2....................................... ....................................... OFF
AT VFTO PL 1 + 2............................................................................IN THE NOTCH PWR MGT ........................................... ........................................... MCT IAS ................................................. .................................................SET If normal conditions FLAPS.............................................. .............................................. 0°
BLEED (operating eng)........................... ........................... OFF (if necessary) ATC ................................................................................................NOTIFY If damage FIRE HANDLE (affected eng).............................. .............................. PULL SINGLE ENG OPERATION procedure ( A70.12 ) ............... ............... APPLY
If no damage Note Engine relight may be performed at flight crew discretion.
ENG RESTART IN FLIGHT procedure ( A70.09 ) ..........................APPLY
If no restart SINGLE ENG OPERATION procedure ( A70.12 ) ..........................APPLY
_ff73daa7-8686-4574-82b6-79e3bef1e42a 8.3 ALL
Note In order to determine VmHB:
- In landing configuration, Refer to OPSDATA, or - In other configurations, Refer to PER.6.3.1 Reduced Flaps Landing
Configuration VAPP.
If only one engine recovered SYSTEMS (affected)................................. .................................RESTORE APM ................................................ ................................................ OFF SINGLE ENG OPERATION procedure ( A70.12 ) ............... ............... APPLY
If NO engine recovered ENG START selector ................................................OFF & START ABORT FUEL PUMPS 1+2..............................................................................OFF CAUTION Do not select avionics vent exhaust mode to OVBD.
FORCED LANDING procedure ( E99.06 ) .................... .................... APPLY -OR- DITCHING procedure ( E99.03 ) ........................... ........................... APPLY
PAGE
INTENTIONALLY
EMR.99 MISCELLANEOUS
_b7b305b6-04c8-47d7-8b38-6c2fd94f541c 2.1 ALL
- E99.02COCKPIT DOOR LOCKING SYSTEM If Electrical Power Lost
MANUAL LOCK BOLT....................... ....................... CLOSE POSITION Note When the door is locked with the manual bolt, the emergency access to the cockpit is not available It is recommended that at least two crew members must remain in the cockpit during that time
If cockpit door is jammed in closed position and need to exit the cockpit THIRD OCCUPANT SEAT (if any)........................ ........................ FOLD UP TWO HORIZONTAL LATCHES ON THE LEFT PANEL DOOR...CHECK OPEN COCKPIT DOOR LOCKING SYSTEM sw..............................................OFF DOORS............................................. ............................................. PUSH If cockpit door still jammed in closed position ELECTRICAL PLUG ON TOP LEFT OF THE LEFT DOOR.......................
.....................................................................................DISCONNECT FOUR RED SAFETY PINS FROM THE DOORS........................REMOVE VERTICAL DOOR HANDLE............................ ............................ OPEN DOORS....................................................................PUSH & REMOVE
_5165e023-d889-424d-ac7c-4332aae133c9 6.1 ALL
PACKS 1+2........................................................................................OFF OVBD VALVE........................................................................FULL CLOSE ENG START selector ................................................OFF & START ABORT CABIN REPORT............................................................................OBTAIN
At 500 ft AGL DITCH pb ............................................. ............................................. ON
Just before ditching Note In case of night ditching, both engines shut down is performed at captain’s discretion as no landing lights available with propellers feathered.
BRACE FOR IMPACT.................................. ..................................ORDER FLARE ........................................... ........................................... INITIATE OPTIMAL PITCH ATTITUDE................................. ................................. 9° CL 1+2.................................................................... FTR THEN FUEL S.O. FIRE HANDLES 1+2..........................................................................PULL FUEL PUMPS 1+2..............................................................................OFF
For evacuation If one of the aft door is under the water line DOOR : DO NOT OPEN
EVACUATION (PA)................................... ................................... INITIATE ATC (VHF1)..................................................................................NOTIFY Before leaving aircraft EMER LOC XMTR....................................................CHECK EMITTING BAT .............................................. .............................................. OFF
_9d94a5cb-a461-49e5-9ebb-d233509dc7d4 3.1 ALL
ENG START selector ................................................OFF & START ABORT CABIN REPORT............................................................................OBTAIN
Just before landing BRACE FOR IMPACT.................................. ..................................ORDER
Note In case of night forced landing, both engines shut down is performed at captain’s discretion as no landing lights available with propellers feathered.
CL 1+2.................................................................... FTR THEN FUEL S.O. FIRE HANDLES 1+2..........................................................................PULL FUEL PUMPS 1+2..............................................................................OFF
_60d93efb-5e98-4a78-80e2-05501a99087e 6.1 ALL
- E99.08 SEVERE ICING IAS : ICING BUG + 30 kt (or ICING BUG IF FLAPS 15 EXTENDED) PWR MGT ............................................. ............................................. MCT PL 1+2............................................................................................ADJUST CL 1+2.................................................................................... 100 % OVRD DESCENT........................................... ........................................... INITIATE MEA / RECOMMENDED MAXIMUM ICING FLIGHT LEVEL......... ......... CHECK
CAUTION Firmly hold control column and wheel to avoid non-expected aircraft movements at AP disengagement
AP ........................................... ........................................... DISENGAGE
If not able to accelerate and maintain IAS above ICING BUG + 30 kt with flaps 0
- OR - If not able to accelerate and maintain IAS above ICING BUG with flaps 15 LOW BANK........................................................................................SET
SEVERE ICING CONDITION.............................. ..............................ESCAPE ATC ................................................................................................NOTIFY If abnormal aircraft roll behavior STALL procedure ( E99.09 ) .............................. ..............................APPLY
As long as aircraft is not clear of ice FLAPS : DO NOT RETRACT For landing APPROACH CONFIGURATION ...................... ...................... FLAPS 15 HIGH BANK CAN BE SET REDUCED FLAPS LANDING procedure ( A27.05 ) ........... ........... APPLY
Note Refer to PRO.NNO.ABN.30.5.3.A30.16 SEVERE ICING DETECTION for information on severe icing indications.
_58995808-e615-41b3-8bb9-b0f2175ed226 2.1 ALL
- E99.09 STALL CONTROL COLUMN..................................... ..................................... PUSH ENG PWR ..................................................................................INCREASE If FLAPS 0 FLAPS..............................................................................EXTEND TO 15
ATC ................................................................................................NOTIFY When out of stall FLIGHT PATH............................ ............................RECOVER SMOOTHLY
_17126473-ecbb-4038-b964-be6d1df70cb1 5.2 ALL
- E99.10UNRELIABLE AIRSPEED INDICATION CAUTION Unreliable airspeed indication procedure has to be applied only when the three airspeed sources (both ADC and IESI) indications differ.
AP/YD ................................................ ................................................ OFF FD .................................................................................................... STBY PITCH : MAINTAIN TQ : MAINTAIN If at takeoff or GA below 1 500 ft PITCH.......................................................................... 8 ° IMMEDIATELY
ICING CONDITIONS........................................................................ESCAPE VOLCANIC ASHES CONDITIONS.......................... ..........................ESCAPE
Climb TLU sw ........................................... ........................................... LO SPD PWR MGT ........................................................................................ CLB PL 1+2..........................................................................................NOTCH PITCH............................. .............................ADJUST FOLLOWING TABLE
Altitude (ft) 5 000 10 000 15 000 20 000
Normal conditions pitch 8 ° 6 ° 5 ° 4 °
Icing conditions pitch 7 ° 5 ° 4 ° 3 °
Cruise ALTITUDE : MAINTAIN TLU sw ........................................................................................ HI SPD
Note Average pitch around 0 ° at cruise speed.
PWR MGT ........................................... ........................................... CRZ PL 1+2..........................................................................................NOTCH
Descent TLU sw ........................................................................................ HI SPD PITCH : MAINTAIN AT -2.5 ° PL 1+2......................................................................ADJUST TO 30 % TQ
Initial Approach CAUTION Perform transition from clean to LDG configuration in level flight. Refer to ALTIMETER. If possible, maintain level flight during 30 s between each configuration update.
TLU sw ........................................... ........................................... LO SPD TQ ............................... ............................... ADJUST FOLLOWING TABLE
cont'd…
14 T 16 T 18T
FLAPS 0 - 180 kt 35 % 40 % 45 %
FLAPS 15 - 150 kt 30 % 35 % 40 %
FLAPS 35 - 130 kt 45 % 45 % 50 %
FLAPS..................................................................................................15 LDG GEAR.......................................... .......................................... DOWN PWR MGT ............................................. ............................................. TO FLAPS..................................................................................................35
Final Approach PL 1+2..................................... ..................................... ADJUST 35 % TQ Before Landing procedure ( 21 ) ........................... ........................... APPLY
Note Set an average pitch of -5 ° for a 3 ° slope approach.
cont'd…
DUCT 1(2) OVHT A21.01
PACK 1+2 VALVES FAULT A21.03
RECIRC FAN 1(2) FAULT A21.06
AVIONICS VENT EXHAUST MODE FAULT A21.08
OVBD VALVE FAULT A21.09
AUTO PRESS FAULT A21.10
EXCESS CAB ALT A21.13
AUTOPILOT Alert Procedure Code
A22.01
AP PITCH TRIM FAIL (ADU MESSAGE) A22.04
DADC DATA INVALID (ADU MESSAGE) A22.05
EXCESSIVE LATERAL TRIM REQUIRED A22.10
PITCH MISTRIM (ADU MESSAGE) A22.13
COMMUNICATIONS Alert Procedure Code
XPDR FAULT A23.05
ELECTRICAL Alert Procedure Code
26 AC STBY BUS FAULT DETECTION A24.03
ACW GEN 1(2) FAULT A24.08
ACW GEN 1+2 LOSS A24.09
BAT DISCHARGE IN FLIGHT A24.10
DC BUS 1 OFF A24.11
DC BUS 2 OFF A24.12
DC EMER BUS OFF A24.13
DC ESS BUS OFF A24.14
DC GEN 1(2) FAULT A24.15
DC SVCE-UTLY BUS SHED A24.18
EMER(MAIN) BAT CHG FAULT A24.19
EMER+MAIN BAT CHG LOSS A24.20
INV 1(2) FAULT A24.21
FLIGHT CONTROLS Alert Procedure Code
FLAPS ASYM A27.01
FLAPS JAM A27.02
FLAPS UNLK A27.04
PITCH DISCONNECT A27.07
PITCH TRIM ASYM (LOCAL LIGHT) A27.10
PITCH TRIM INOPERATIVE A27.12
STICK PUSHER-SHAKER FAULT A27.13
AIL LOCK LIT A27.14
A27.17
FUEL CLOG A28.02
FUEL LEAK DETECTION A28.04
HYDRAULIC SYSTEM Alert Procedure Code
HYD BLUE (GREEN) LO LVL A29.01
HYD BLUE (GREEN) LO PR A29.02
HYD BLUE (GREEN) OVHT A29.03
HYD BLUE AND GREEN PUMPS LOSS A29.04
HYD BLUE AND GREEN SYS LOSS A29.05
HYD AUX LO PR A29.06
HYD AUX OVHT A29.07
AFR AIR BLEED FAULT A30.05
DE-ANTI ICING MODE SEL AUTO FAULT A30.06
DE ICING AIRFRAME FAULT A30.07
DE ICING MODE SEL FAULT A30.08
DE ICING ENG 1(2) FAULT A30.09
ICE DETECT FAULT A30.10
PROBES HTG FAILURE A30.11
WINDSHIELD HTG FAULT A30.13
MFC Alert Procedure Code
MFC 1A FAULT A31.01
MFC 1B FAULT A31.02
MFC 2A Fault A31.03
MFC 2B FAULT A31.04
ANTISKID FAULT A32.01
LDG GEAR RETRACTION NOT POSSIBLE A32.04
LDG GEAR UNSAFE INDICATION A32.05
LANDING WITH ABNORMAL LDG GEAR A32.06
NAVIGATION Alert Procedure Code
ADC 1(2) FAILURE A34.01
ADC SW FAULT A34.03
AHRS 1(2) FAILURE A34.05
CRT FAIL A34.52
EFIS FAILURE A34.53
SGU FAIL A34.54
PNEUMATIC Alert Procedure Code
BLEED LEAK 1(2) A36.02
BLEED 1(2) OVHT A36.03
ENG BLEED 1(2) FAULT
EEC 1(2) FAULT A70.03
PEC 1(2) FAULT A70.05
ENG 1(2) FLAME OUT IN FLIGHT A70.07
ENG 1(2) FLAME OUT ON GROUND A70.08
ENG RESTART IN FLIGHT A70.09
ENG STALL A70.10
SINGLE ENG OPERATION A70.12
ENG 1(2) OIL TEMP BELOW 45 °C A70.15
ENG 1(2) OIL TEMP HIGH A70.16
ENG 1(2) OVER LIMIT A70.17
ENG NAC OVHT A70.18
UNEXPECTED 100 % NP ON ONE OR TWO ENGINES
A70.20
START 1(2) FAULT A70.26
X START FAIL A70.27
IDLE GATE FAIL A70.31
MISCELLANEOUS Alert Procedure Code
DOORS UNLK IN FLIGHT A99.02
OXYGEN LO PR A99.03
COCKPIT WINDOW CRACKED A99.05
VOLCANIC ASH ENCOUNTER A99.06
PAGE
INTENTIONALLY
_b47cb9f6-a287-4938-a109-f9af2e65710c 4.2 ALL
If alert persists PACK VALVE (affected side)................................ ................................ OFF MAX FL : 200/MEA At high altitude LARGE RAPID POWER CHANGES : AVOID
_2920dd9e-f5d2-4839-a270-df0cfca9ec64 2.5 ALL
_87f45607-b5f9-41b1-815e-dc8f8432eac6 2.0 ALL
_b7c1277a-7829-4387-8474-ef7002aaf06d 1.1 ALL
_dc18174f-d87b-4047-9c62-5976026493cc 0.1 ALL
_e892b4a1-a2c2-4728-b969-e780ec8c2317 0.2 ALL
A21.09 OVBD VALVE FAULT If ΔP > 1 psi OVBD VALVE : DO NOT SELECT FULL OPEN POSITION
If engine 1 running, in flight or on ground OVBD VALVE........................................................................FULL CLOSE
If engine 1 not running, on ground OVBD VALVE..........................................................................FULL OPEN
_840538b9-f542-468b-9d3f-202570c694de 4.1 ALL
FL 140 170 200 220 240 250
TARGET CAB ALT
(ft) 2 500 3 300 4 200 5 200 6 200 6 700
Before descent If CAB ALT above landing elevation CAB PRESS RATE knob .......................... ..........................DECREASE CAB ALT RATE.................................................. ADJUST 400 ft/min DN
If CAB ALT below landing elevation CAB PRESS RATE knob ......................................................INCREASE CAB ALT RATE........................................ ADJUST 1 000 ft/min UP MAX
When CAB ALT = landing elevation CAB PRESS RATE knob ........ ........ 9 O'CLOCK (MAN position) & MONITOR
After landing CAB PRESS RATE knob .................................................. MAX INCREASE
_51062107-8c24-4ed8-bf29-b3510963112e 7.1 ALL
If cabin altitude > 10 000 ft confirmed CAB PRESS RATE knob ................................9 O'CLOCK (MAN POSITION) CAB PRESS MODE SEL................................. ................................. MAN CAB PRESS RATE knob ............................ ............................ DECREASE
If EXCESS CAB ALT persists CREW OXY MASKS..................................... ..................................... DON CREW COMMUNICATIONS......................................................ESTABLISH OXYGEN PAX SUPPLY............................... ............................... AS RQRD OXYGEN PRESSURE....................................................................CHECK DESCENT....................................................................INITIATE AS RQRD MAX FL : 100/MEA
_40fe8e77-b971-42fb-8877-9a6fa6f918a7 4.3 ALL
A21.14EXCESS CAB DELTA P CAB PRESS RATE knob.................... .................... 9 O'CLOCK (MAN position) CAB PRESS MODE SEL ................................... ................................... MAN CAB PRESS RATE knob........................... ........................... MAX INCREASE If EXCESS CAB DELTA P persists DESCENT ..................................................................................INITIATE MAX FL : 100/MEA
Note Closing of the pack valves may trigger EXCESS CAB ALT alert
PACK VALVE 1+2....................................... ....................................... OFF MAX FLIGHT TIME : 80 min When ΔP < 1 psi OVBD VALVE.................................. .................................. FULL OPEN
FOLLOWING FAILURES PRO NNO
PAGE
INTENTIONALLY
ABN.22 AUTOPILOT
If composite mode CONTROL COLUMN & WHEEL...................... ......................HOLD FIRMLY AP ........................................... ........................................... DISENGAGE
AILERON MISTRIM (ADU MESSAGE) _b3ddeb48-0e5a-45d0-bfcb-3e90d3a94191 0.1
ALL A22.03AILERON MISTRIM (ADU MESSAGE)
CONTROL COLUMN & WHEEL................................................HOLD FIRMLY AP ............................................. ............................................. DISENGAGE LATERAL TRIMS..............................................................................ADJUST When lateral trims adjusted
ALL A22.04AP PITCH TRIM FAIL (ADU MESSAGE)
CONTROL COLUMN & WHEEL................................................HOLD FIRMLY AP ............................................. ............................................. DISENGAGE
A22.05DADC DATA INVALID (ADU MESSAGE) INSTRUMENTS....................................... .......................................XCHECK ADC FAILED..................................................................................IDENTIFY ADC sw .................................... ....................................SELECT VALID ADC If ADC 1 is failed C/B ADS / ADC 1 EMER SPLY ............................. .............................PULL C/B MFC / 1A AUX / ADC 1 HOT SPLY....................... ....................... PULL ADC 1(2) FAILURE procedure ( A34.01 ) ..................... .....................APPLY
If ADC 2 is failed C/B ADS / ADC 2 ...................................... ...................................... PULL ADC 1(2) FAILURE procedure ( A34.01 ) ..................... .....................APPLY
_01d6225f-bd86-482f-b380-aa21838f4101 2.1 ALL
ALL A22.13 PITCH MISTRIM (ADU MESSAGE) CONTROL COLUMN & WHEEL................................................HOLD FIRMLY AP ............................................. ............................................. DISENGAGE PITCH TRIM.......................................... ..........................................ADJUST When pitch trim adjusted
AP CAN BE REENGAGED
_0761eb38-2e41-46ba-a8c1-8082b30a5257 0.3 ALL
_31a415ef-b298-4788-b758-e5b945db3886 2.0 ALL
PAGE
INTENTIONALLY
_78b3063d-3f93-4059-96a5-945aae8b549c 1.1 ALL
A24.01AC BUS 1 OFF If AC BUS 1 OFF persists after 10 s DC BTC............................................ ............................................ RESET If AC BUS 1 OFF persists AC BUS 1 LOST EQUIPMENT LIST............................................CHECK
_5d33d6fa-2b3a-4f5c-8ac6-9e109af6e82b 0.3 ALL
Flight Controls - TRIMS indicator
_8991e462-d471-4092-99ee-25209b5d74a7 2.4 ALL
Lost Equipment List Navigation - F/O ASI - F/O VSI - F/O ALTM
- HDG RMI #1 - Bearing VOR #2 and ADF #2, 1/2 Course #2 and HDG #2 select
_b8fe0cc9-7f0e-4698-85fe-4f873a0e3e65 0.1 ALL
A24.0326 V AC STBY BUS FAULT DETECTION In case of 26 V AC STBY BUS fault, no ELEC alert is triggered on CAP. When 26 V AC STBY BUS is fault, following equipment are flagged :
- IAS #1 indicator - Altimeter #1 - V/S #1 indication - RMI #2 heading - Flaps position indicator
And - TAT/SAT indicator is lost - FLT CTL and GPWS alert are triggered on CAP
If 26 V AC STBY BUS fault suspected: 26 V AC STBY BUS FAULT procedure ( A24.04 ) ............... ............... APPLY
_2b871c05-2d1b-442e-aa1d-52d7f931242d 2.2 ALL
A24.04 26 V AC STBY BUS FAULT PF ................................................... ................................................... CM2 APM .................................................................................................... OFF TLU sw ............................... ............................... HI or LO SPD based on IAS CAUTION Flaps extension is not possible Flaps retraction : 0 ° ONLY possible
For Approach REDUCED FLAPS LANDING procedure Refer to AFM - (A27.05) ........APPLY
CAUTION If flaps already in landing position : In case of GO Around, climb performance is degraded due to flaps in landing position, until flaps retraction to 0 °
_beb55391-8ea2-495a-b6f1-a590dbaac9fc 1.2 ALL
26 V AC STBY BUS FAULT- Lost equipment list Flight Instruments - IAS #1 indicator - Altimeter #1 - V/S #1 indication - TAT/SAT indicator - RMI #2 heading
Flight Controls - Flaps extension - Flaps retraction except to 0 ° position - Flaps position indicator - TLU Auto-Mode Ice and rain protection - APM
_ad239e39-5b74-4581-9243-3c39567a0dea 0.3 ALL
A24.05 115 V AC STBY BUS FAULT NO CREW ACTION REQUIRED
115 V AC STBY BUS FAULT- Lost equipment list _94e257b2-41eb-4492-8f1b-e568ef4338b4 1.3
ALL 115 V AC STBY BUS FAULT- Lost equipment list
Flight Instruments - V/S indicator #2 Fire protection - AFT COMPT/LAV DET FANS
Indicating and recording - DATA RECORDER
_f205b6d2-737a-41dc-800a-5cc72f96b956 4.2 ALL
After touchdown TAXI : ON ENG 1+2
_0246a910-94bd-4cf8-a785-95ba2c2c1a01 2.2 ALL
Lost Equipment List Cabin - LH PAX Reading Lights Hydraulic - HYD BLUE PUMP Ice and Rain Protection - CAPT PITOT HTG - CAPT TAT HTG - CAPT ALPHA HTG - ANTI ICING PROP 1 - ANTI ICING RUD & L ELEV HORNS - CAPT WINDSHIELD HTG
Lights - Integrated Normal INST & PANELS Lights - L LAND Light - Left and rear STROBES
_9ee3b1f8-89f5-4b13-baf5-ac522b89fd03 4.2 ALL
_7bc421de-6050-46e1-882e-ef3628c40399 0.6 ALL
Lost Equipment List Cabin - Right PAX Reading Lights Electrical power - TRU not available Hydraulic - HYD GREEN PUMP Ice and Rain Protection - F/O PITOT HTG - F/O TAT HTG - F/O ALPHA HTG - F/O WINDSHIELD HTG - ANTI ICING HORNS AIL & R ELEV - ANTI ICING PROP 2 - ICE DETECTOR
Lights - TAXI & TO Lights - R LAND Light - R STROBE Light
_a2785ca0-e701-4a66-89f4-d46fbfae4ecf 0.1 ALL
_0bcc6df2-9cbf-4176-a5a4-37799ce6a161 2.1 ALL
LDG GEAR NORMAL OPERATION LOST LDG GEAR lever ............................................................................DOWN BLUE PRESSURE.................................... .................................... CHECK FLAPS 15..................................................................................AS RQRD LDG GEAR GRAVITY EXTENSION procedure ( A32.03 ) ......... ......... APPLY FLAPS 25/35..............................................................................AS RQRD
_dd66512e-d4f5-4ae4-85bc-5d05e0a49ba9 2.1 ALL
Lost Equipment List Cabin - TOILETS SYS (If supplied by ACW) Hydraulic - HYD GREEN AND BLUE PUMP Ice and Rain Protection - CAPT PITOT HTG - CAPT TAT ALPHA HTG - F/O PITOT HTG - F/O TAT ALPHA HTG - WINDSHIELD HTG - ANTI ICING HORNS - ANTI ICING PROP 1+2 - ICE DETECTOR
Lights - Integrated Normal INST & PANELS Lights - TAXI & TO Lights - LAND Lights
_5e1ea62d-2a36-4784-ab19-e5f954e2c929 5.0 ALL
A24.10BAT DISCHARGE IN FLIGHT ENG START selector ....................................................OFF & START ABORT If one ACW GEN lost HYD BLUE PUMP....................................... ....................................... OFF HYD X FEED........................................... ........................................... ON
TRU ................................................... ................................................... ON If battery discharge stops NORMAL OPERATIONS : RESUME MAINTENANCE ACTION REQUIRED.
If at least one battery is still discharging TRU ................................................ ................................................ OFF HYD X FEED .................................. .................................. OFF AS RQRD HYD BLUE PUMP................................ ................................ ON AS RQRD LAND ASAP
_ffaedc9b-827f-4809-88b0-fa80aa1721e0 5.1 ALL
A24.11DC BUS 1 OFF DC GEN 1.............................................. .............................................. OFF PF ........................................................................................................ F/O AUTO PRESS FAULT procedure ( A21.10 ) ..................... ..................... APPLY DC SVCE/UTLY BUS pb : MAINTAIN ON DC BUS 1 LOST EQUIPMENT LIST.......................... ..........................CHECK AFFECTED EQUIPMENT FAULT procedure..................... .....................APPLY
Note - CAS digital part is no longer supplied. Only warnings (level 3, red) are
processed - Stick pusher is lost without FAULT alarm.
At touchdown IDLE GATE lever ..............................................................................PULL
_7ddb32cf-cff3-4142-bde2-0a7372f953c0 3.1 ALL
Lost Equipment List Air - AUTOPRESS - BLEED LEAK indicator 1+2 Flight controls - STICK PUSHER - CM1 STICK SHAKER Ice and Rain protection - CM1 STATIC PORTS ANTI ICING - STBY STATIC PORTS ANTI ICING - CM1 SIDE WINDOWS ANTI ICING - CM2WINDSHIELD HTG indicator Lights - CM1 DOME - CM1 CHARTHOLDER - CM1 READING LIGHTS - CM2 FLOOD PANELS - STORM LIGHTS - ANNUNCIATOR LT TEST - NAV Lights - BEACON Light
Miscellaneous - TOILET FLUSHING (if supplied by DC) Navigation - WEATHER RADAR - RADIO ALTIMETER - SELCAL (if installed) - (E)GPWS - CM1 DME #1 Power Plant - FF/FU #1 - FUEL TEMP #1 - FUEL CLOG #1 - OIL PRESS - OIL TEMP #1 - AUTO IDLE GATE
_f11fd1f8-4711-4c04-8b8c-7b8ae1884bad 4.1 ALL
_d43f1ee9-c34a-40ba-ac29-7d2aed1ea9a7 1.2 ALL
Lost Equipment List Air - LANDING ELEVATION indicator Doors - DOORS UNLK Lights - CDLS Fire Protection - NAC OVHT Flight controls - STBY PITCH TRIM CTL - F/O STICK SHAKER - TLU AUTO CONTROL Hydraulic Power - HYD PWR AUX PUMP IND - HYD PWR AUX PUMP AUTO MODE Ice and Rain protection - F/O STATIC PORTS ANTI ICING - F/O SIDE WINDOWS ANTI ICING - F/O WINDSHIELD HTG indicator - F/O PROBES indicator - F/O WIPER Indicating - Recording Systems - CAP AMBER ALERT (except MAINT PNL, PRKG BRK, MFC) Landing Gear - SECONDARY indicator Lights - F/O CHARTHOLDER - F/O READING Lights - INTEGRATED INSTRUMENTS Lights - INTEGRATED PANELS Lights - TAXI & T.O Lights - WING Lights - PAX SIGNS Lights
Navigation - F/O EADI/EHSI - SGU #2 - VOR #2 - ILS #2 - DME #2 - ADF #2 - CAPT RMI - VHF #2 - ATC #2 - ADC #2 - ALT ALERT #2 - F/O CLOCK - TCAS or T2CAS (if installed) - GPS KLN90 (if installed) Power Plant - FF/FU #2 - FUEL TEMP #2 - FUEL CLOG #2 - OIL PRESS #2 - OIL TEMP #2 - IDLE GATE CAUTION
_0058e085-94f7-4125-a4c4-6b004026db1a NEW 4.0 ALL
CAUTION Do not restore HYD BLUE PUMP
TRU : MAINTAIN ON MAINTENANCE ACTION REQUIRED
If DC EMER BUS not recovered (TQ indications loss persists) TRU ................................................ ................................................ OFF VHF 2 / XPDR 2........................................ ........................................ USE DESCENT......................................... ......................................... INITIATE MAX FL : 100/MEA STBY PITCH TRIM..............................................................USE AS RQRD LANDING ELEVATION......................................SET PRESSURE ALTITUDE FLIGHT TIME : MINIMIZE ENGINE FIRE DETECTION LOST TLU .............................. .............................. HI or LO SPD BASED ON IAS ICE ACCRETION : MONITOR IEP DC EMER BUS OFF EQUIPMENT LIST..................... ..................... CHECK AFFECTED EQUIPMENT FAULT PROCEDURES............... ...............APPLY If ice accretion DE ICING AIRFRAME FAULT procedure ( A30.07 ) ........... ........... APPLY DE ICING MODE SEL FAULT procedure ( A30.08 ) ........... ........... APPLY ANTI ICING PROP 1(2) FAULT procedure ( A30.02 ) .......... .......... APPLY ANTI ICING HORNS 1(2) FAULT procedure ( A30.01 ) ......... .........APPLY
Before landing N/W STEERING...................................... ......................................OFF ANTISKID FAULT procedure ( A32.01 ) ........................................APPLY
_8d436419-0766-4725-a135-265e4a73a305 2.2 ALL
Lost Equipment List Air - OVBD VALVE CTL - UNDERFLOOR VALVE CTL - OVBD VALVES indicator - UNDERFLOOR VALVES indicator - AIR COOLING HIGH FLOW indicator - PRESS indicator - EXCESS ALT indicator - PNEUMATIC OUTFLOW VALVES - FWD COMPT VENTILATION VALVE Auto Flight - AP/FD COMPUTER - GUIDANCE indicator Doors - DOORS UNLK Lights - CDLS Electrical Power - AC BUS OFF 1+2 indicator - ACW BUS OFF 1+2 indicator - INV 1 FAULT indicator - DC BUS OFF 1+2 indicator - DC STBY BUS indicator (UNDV/ OVRD) - EMER BAT CHG indicator Fire Protection - CL FIRE IND 1+2 - FIRE HANDLE ENG 1+2 indicator - FIRE DETECTION ENG 1+2 Flight controls - PITCH TRIM NORMAL COMMAND - RUDDER TRIM - AILERON TRIM
Hydraulic Power - BLUE PUMP CTL - BLUE PUMP indicator - GREEN PUMP indicator Ice and Rain protection - AAS CTL indicator - AAS CTL ALERTS - WING BOOTS A - EMPENNAGE BOOTS A - ENG 1 BOOTS A+B - PROP 1+2 ANTI ICING CTL - PROP 1+2 ANTI ICING indicator - HORNS ANTI ICING indicator - HORNS ANTI ICING CTL Indicating - Recording Systems - FDAU ON GROUND Landing Gear - ANTISKID OUTBOARD - NOSE WHEEL STEERING - WOW 1 CTL Lights - CAPT PANELS - PYLON - STBY COMPASS - LAVATORY (EMER) Navigation - ATC 1 - CAPT CLOCK Power Plant - A/F AUX PUMPS CTL - TQ 1+2 indicator
_2f5d1612-9a83-4c3d-91b2-ec41455c22a5 0.3 ALL
A24.14DC ESS BUS OFF DC ESS BUS OFF LOST EQUIPMENT LIST.................... ....................CHECK COCKPIT DOOR MANUAL BOLT(S)........ ........MOVE TO CLOSE POSITION Note
1) Cockpit Door Control panel FAULT light is inoperative. 2) When the door is locked with the manual bolt(s), the emergency access
to the cockpit is not available. It is recommended that at least two crew members remain in the cockpit during that time.
_22c4d4d5-031c-4156-b4b2-595114aa5099 2.2 ALL
Lost Equipment List - Part 1 Air - PACK VALVE 1+2 - RECIRC FAN 1+2 indicator - EXTRACT FAN CTL - LANDING ELEVATION indicator - COCKPIT AUTOMATIC TEMP CTL - COCKPIT MANUAL TEMP CTL - CABIN AUTOMATIC TEMP CTL - CABIN MANUAL TEMP CTL - COCKPIT TEMP indicator - CABIN TEMP indicator Auto Flight - AP OFF indicator - DISC by QUICK DISCONNECT Communication - FLIGHT INTERPHONES - AUDIO CONTROL PANELS - CAPT COCKPIT AMPLIFIER - CVR / PASSENGER ADDRESS - MECHANICAL CALL - COCKPIT CREW CALL - CABIN CREW CALL Electrical Power - DC SVCE BUS 1+2 CTL - DC UTLY BUS 1+2 CTL - MAIN BAT CHG indicator - INV 2 FAULT indicator
Fire Protection - AVIONICS SMK DET - TOILETS SMK DET - FWD COMPT SMK DET - AFT COMPT SMK DET - AFT COMPT CTL - AFT COMPT indicator - FWD COMPT CTL - FWD COMPT indicator - Toilets DET FANS CTL - Toilets DET FANS indicator - FWD COMPT Fire Extinguishing CTL indicator - FWD COMPT Fire Extinguishing CTL TEST - AUX AFT COMPT Flight controls - CLUTCH REENGAGEMENT SYSTEM - AILERON LOCKING CTL Fuel - FQI 1+2 - X FEED VALVE - STARTING PUMPS 1+2 - MOTIVE FLOW VALVES 1+2 Hydraulic Power - GREEN PUMP CTL
_9c5ae291-98bb-4b8a-ba18-e5c53a766690 1.1 ALL
Lost Equipment List - Part 2 Ice and Rain protection - DE ICING ISOL VALVES - SIDE WINDOWS ANTI ICING indicator - CAPT PROBES indicator - STBY PROBES indicator - TAT PROBES indicator - CAPT WIPER Indicating - Recording Systems - FDAU in FLIGHT Landing Gear - ANTISKID OUTBO

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