Emergency Procedures Flashcards
Land Immediately
Self explanatory.
Land as soon as possible
Land at the nearest site at which a safe landing can be made.
Land as soon as practicable
Extended flight is not recommended; the landing site and duration of the flight are at the discretion of the pilot.
Autorotation over land
- Reduce collective, maintain Nr
- Airspeed at Vy (65 kts)
- Twist grip to IDLE position (if relighting impossible or loss of tail rotor thrust)
- Maneuver into wind on final approach
- Flare at 75’
- Gradually increase collective to reduce descent and forward speed
- Cyclic forward for a <10° slightly nose up landing attitude
- Pedals for heading
- Collective up to cushion landing
- After touchdown adjust cyclic, collective and pedals for ground run
- Collective full low pitch once aircraft is stopped
- Apply rotor brake
Autorotation over water
Apply same procedure as over land, except items 10, 11 and 12, but maneuver to head the aircraft equally between the wind and wave direction on final approach. Ditch with minimum forward speed (IAS < 30 kt) and rate of descent. Then apply following check list for items 10, 11, 12.
• After touch-down
- Collective pitch …………… MAINTAIN
- Door jettison handles…. PULL-UP
- Rotor brake……………….. APPLY
Abandon aircraft once the rotor has stopped.
- Reduce collective, maintain Nr
- Airspeed at Vy (65 kts)
- Twist grip to IDLE position (if relighting impossible or loss of tail rotor thrust)
- Maneuver into wind on final approach
- Flare at 75’
- Gradually increase collective to reduce descent and forward speed
- Cyclic forward for a <10° slightly nose up landing attitude
- Pedals for heading
- Collective up to cushion landing
10.
11.
12.
Hover IGE engine failure
Hover auto
Hover OGE engine failure
WARNING
SAFE AUTOROTATIVE LANDING CAN NOT BE ENSURED IN CASE OF A FAILURE IN HOGE BELOW THE TOP POINT OF THE HV DIAGRAM (REFER TO SECTION 5.1) OR IN CONFINED AREA.
- Collective pitch ……………… FULL LOW PITCH
• When NR stops decreasing
- Cyclic ………………………… FORWARD to gain airspeed according to available height.
- Autorotation procedure ………. APPLY
In flight relighting
According to available height and cause of flame-out :
- Starting selector…………. OFF position
- [FUEL PUMP]…………… ON
- Starting selector…………. ON position
The relighting sequence will therefore be automatically carried out as soon as Ng < 17%.
• After relighting
4. [FUEL PUMP]……………. OFF
At least 1000 ft are necessary to complete relighting procedure after flame-out.
Complete loss of tail rotor thrust IGE hover
Land Immediately.
Hover auto
Complete loss of tail rotor thrust OGE hover
Simultaneously,
- Collective ………………… REDUCE depending on available height
- Cyclic …………………….. FORWARD to gain speed
- Cyclic …………………….. ADJUST to get Vy or higher
- Collective ……………….. Adjust to obtain minimum sideslip angle
LAND AS SOON AS POSSIBLE
If a go-around has been performed, carry out an autorotative landing on a suitable area for landing procedure.
Complete loss of tail rotor thrust in cruise flight
- Airspeed ……………………. Maintain Vy or higher
- Collective…………………. Adjust to obtain minimum sideslip angle
LAND AS SOON AS POSSIBLE
APPROACH AND LANDING
On a suitable area for autorotative landing :
- Twist grip ……………….. IDLE detent
- Carry out an autorotative landing
Loss of tail rotor control
Symptom : jamming of pedals or pedals effectiveness loss. These conditions induce an inability to change tail rotor thrust with the pedals.
WARNING
LANDING IS MADE EASIER BY LANDING WITH A RH WIND COMPONENT.
WHEN AIRSPEED IS LOWER THAN 20 KT, GO-AROUND IS IMPOSSIBLE DUE TO LOSS OF VERTICAL FIN EFFICIENCY.
- Cyclic and collective…………. ADJUST to set IAS to 70 kt (130 km/h) in level flight.
- [HYD TEST] pushbutton ……. DEPRESS, load compensator depressurizes.
After 5 seconds :
3. [HYD TEST] ………………… Reset to OFF position
On a suitable area for a running landing procedure:
Make a shallow approach with a slight left sideslip. Perform a running landing, the sideslip will be reduced progressively as airspeed is reduced and collective is applied to cushion the landing.
Smoke in cabin - source not identified
Heating, Demisting…………….. OFF
Smoke clears?
Yes: CONTINUE FLIGHT, depending on atmospheric conditions
No:
- [MASTER SW] ……… SHUT OFF
- [EXT PWR BATT.] …. OFF
- [GEN] ………………… OFF
- Ventilate the cabin.
When smoke clears :
5. All consumers………… OFF
- [MASTER SW] ……… ON
- [EXT PWR BATT.] .. ON check DC parameters
- [GEN] ………………… ON check DC parameters
Smoke clears?
No: LASAPo
Yes:
DC parameters correct (and no smoke detected) :
- Avionics ON
- Minimum required consumers………… ON, one by one to identify the failed system; then keep it off.
CONTINUE FLIGHT: depending on atmospheric conditions
DC parameters not correct :
- [GEN] ………………… OFF
- Unnecessary equipment OFF
LAND AS SOON AS PRACTICABLE
CAUTION
When battery and generator are off line, the VEMD goes out and only the NR gauge remains. Apply both screen failure procedure (VEMD SCREEN FAILURE SECTION 3.5)
Smoke in cabin - source identified
- Corresponding system ………. OFF
- Ventilate the cabin
CONTINUE FLIGHT: depending on system failed.
NOTE
After DC had been switched-off and on in flight, GOV light will remain on until the next normal full engine and battery switch-off on the ground.
VEMD one screen failure
Failed Screen…………………. OFF.
Read all available informations on the other screen.
Informations are available using the SCROLL pushbutton either on the VEMD or on the collective pitch lever.
If top screen fails, the 3-parameters engine page will be automatically displayed on lower screen but with torque and Ng off line. Only T4 and digital Ng will be available, refer to paragraph 4 for compliance with limitations.
VEMD both screens failed
To avoid any power overlimit, the maximum authorized power will be the power needed to establish level flight with the following law :
IAS kt = 100 kt at sea level (-2kt/1000’ PA)
LAND AS SOON AS PRACTICABLE
Landing procedure: carry out a no hover landing.
Nr Indicator failure
Collective ……………………. MAINTAIN Tq > 10 %
NR reading is given by Nf pointer.
LAND AS SOON AS PRACTICABLE
Nf indicator failure
NR gauge ……………………. CHECK in green range with Tq > 0.
CONTINUE FLIGHT
NOTE 1
The Nf value can be read on the VEMD screen. Press “SELECT”, then “+” as many times as required to display the parameter in the rectangular window at the bottom of the FLI or 3-data screen.
NOTE 2
In case of Nf indication failure, the EBCAU (Engine Back-Up Control Ancillary Unit) may not be available.
Engine oil temp over 115°C
Fly at least 80 kts
If temp drops Land ASAPr. (oil cooler fan inop)
If temp does not drop Land ASAPo
Low engine oil pressure
- CWP …………………………….. Check ENG P light
No Light:
CWP light test:
ENG P light works: LASAPr
ENG P light does not work: Land Immediately
- Autorotation procedure ..APPLY.
- Shutdown engine time permitting.
Light On:
Land Immediately
- Autorotation procedure ..APPLY.
- Shutdown engine time permitting.
Ng/△Ng Indicator Failure
Comply with max TQ value and T4 limit of 810°C.
In this case the T4 limits displayed are the starting limitations.
LASAPr
Torque meter failure
Comply with Ng limit table.
Approximately 96% Ng, and △Ng -4 for Kauai temps and altitudes
LASAPr
△Ng and Torque meter failure
GOV warning can also induce loss of ∆Ng and torque indications.
The VEMD switches to 3-data symbology with only T4 and numeric Ng as valid parameter. Comply with Ng limitations in the above table (“Approximately 96% Ng, and △Ng -4 for Kauai temps and altitudes”), substituting the ∆Ng = - 4 limit by a T4 limit of 810°C.
LASAPr
Generator overvoltage > 31.5 Volts
(RED Underline)
- GEN ……………Off
- CWP ……………Monitor for BATT TEMP
- GENE Procedure Case A………Apply
LASAPr
Case A: GENE (CWP) light stays on after reset
Unnecessary equipment….OFF
U bus on VEMD……… monitor
LAND AS SOON AS PRACTICABLE
Generator overvoltage ≤ 31.5 Volts
(Yellow Underline)
29.0 V < UBUS ≤ 31.5 V
Monitor UBUS voltage.
Continue flight.
Undervoltage on DC bus (≤ 26.0 V)
(Yellow Underline)
GENE procedure apply.
Check UBUS voltage > 26.0 V
If > 26.0 V, Continue flight.
If < 26.0 V, apply GENE procedure.
Land ASAPr.
Generator Current Over Limit
(RED Underline Flashing)
- Unnecessary equipment ………..OFF
CONTINUE FLIGHT
Engine fire at startup
Warning Panel: ENG FIRE
- Engine Starting Selector - OFF
- Emergency Fuel Shutoff Handle - AFT
- FUEL Pump - OFF
- CRANK 10 seconds
- MASTER SW - OFF
- Rotor Brake - Apply (≤ 170 Nr)
- Evacuate and fight fire from outside
Engine fire at Hover, Take-off, Final
Warning Panel: ENG FIRE
LAND IMMEDIATELY
Carry out a no hover powered landing. Once on ground, apply following procedure:
- Engine Starting Selector - OFF
- Emergency Fuel Shutoff Handle - AFT
- FUEL Pump - OFF
- CRANK 10 seconds
- MASTER SW - OFF
- Rotor Brake - Apply (≤ 170 Nr)
- Evacuate and fight fire from outside
Engine Fire In Flight
Warning Panel: ENG FIRE
LAND IMMEDIATELY
- Collective pitch……….. REDUCE
- IAS …………………….. Vy
- Autorotation procedure … APPLY
- Emergency fuel shut-off handle ……….. AFT
- FUEL PUMP ………Check OFF
- Starting selector………. OFF position
After landing :
- [MASTER SW]……….. OFF
- Rotor brake ……………. APPLY (≤ 170 rpm)
- Evacuate aircraft and fight fire from outside.
Major Governor Failure In Flight
Emergency Mode Engaged
Warning Panel: GOV
Red Light
- Flight parameters ……..CHECK
Emergency mode automatically self-engages.
GOV illuminates.
- Collective pitch ………..AVOID abrupt changes
Maintain Ng > 80% Hp < 20000 ft
Maintain Ng > 85% Hp ≥ 20000 ft
LAND AS SOON AS PRACTICABLE
Approach and Landing :
Make a powered approach.
Avoid steep angle.
After touch down, shut-down :
Collective pitch…………….SLOWLY down to low pitch.
Starting selector ……………OFF.
NOTE
On VEHICLE page: FF and END .
This failure can also results in loss of ∆Ng and torque parameters on the VEMD.
GOV
Governing Function Degraded
Minor FADEC Failure
Warning Panel: GOV
Yellow Light
- Collective ……………….AVOID abrupt power changes
- IAS………………………MAINTAIN below VNE power off
LAND AS SOON AS PRACTICABLE
On ground : do not start engine.
GOV
Minor FADEC Failure
Flashing at idle or during starting or shut down
Warning Panel: GOV
Yellow Light
Governor redundancy failure, no impact on governing function.
Start-up procedure: abort, report to Maintenance Manual
Autorotation training: cancel training, return to base.
ENG P
Warning Panel: Red Light
Engine oil pressure
Oil pressure ……………… CHECK gauge
LOW OR NIL
LAND IMMEDIATELY
Autorotation procedure ..APPLY
Shutdown engine time permitting
NORMAL
LAND AS SOON AS PRACTICABLE
TWT GRP
Warning Panel: Red Light
Twist grip out of FLIGHT position
Twist grip ………………… TURN up to FLIGHT detent.
CONTINUE FLIGHT
ENG CHIP
Warning Panel: Yellow Light
Metal particles in engine oil circuit.
Collective pitch ………….. REDUCE power
LAND AS SOON AS POSSIBLE
Low power approach and landing
Be prepared in case of an engine loss of power.
NOTE
Takeoff is prohibited until specified checks in TURBOMECA Maintenance Manual have been completed.
MGB P
Warning Panel: Red Light
Main Gear Box low oil pressure (< 1 bar)
Collective …….REDUCE power
LAND AS SOON AS POSSIBLE
If a safe landing is not possible, continue flight to the nearest appropriate landing site, reduce power to fly at minimum power speed (Vy).
WARNING
AT LOW POWER (VY) A MAXIMUM OF 55 MIN. OF SIMULATED FLIGHT TIME HAS BEEN DEMONSTRATED DURING BENCH TEST
MGB TEMP
Warning Panel: Yellow Light
Main Gear Box oil overheating (> 115°C)
- IAS………SET TO Vy
- CWP …..MONITOR
If MGB TEMP light goes out: LAND AS SOON AS PRACTICABLE
If MGB TEMP light stays on: LAND AS SOON AS POSSIBLE
MGB CHIP
Warning Panel: Yellow Light
Metal particles in MGB oil circuit.
Collective ………………….REDUCE power
MONITOR ………. MGB TEMP & MGB P lights
LAND AS SOON AS POSSIBLE
TGB CHIP
Warning Panel: Yellow Light
Avoid prolonged hovering
CONTINUE FLIGHT
HYDR
Warning Panel: Red Light
Loss of hydraulic pressure or pressure < 30 b
Keep aircraft to a more or less level attitude
Avoid abrupt maneuvers
CAUTION
Do not use [HYD TEST] pushbutton as this will depressurize the yaw load compensator resulting in heavy pedals control loads. Do not attempt to carry out hover flight or any low speed maneuver. The intensity and direction of the control feedback force will change rapidly. This will result in poor aircraft control and possible loss of control. As controls loads increase, be careful not to inadvertently move twist grip out of FLIGHT detent (TWT GRIP light out).
NOTE
Pressure in accumulators allows enough time to secure the flight and to establish the hydraulic failure safety speed.
HIGE, T/O, Final
- Land normally
- Twist grip ……..Set to IDLE detent
- Collective……LOCK
- Engine Starting selector ….OFF
In Flight
- Collective/Cyclic …………SET IAS within 40 to 60 kt (hydraulic failure safety speed)
- Collective HYD switch …..OFF.
Pilot has to exert forces:
- on collective increase or decrease around no force feedback point,
- on forward and left cyclic.
LAND AS SOON AS POSSIBLE
NOTE
Speed may be increased as necessary but controls loads will increase with speed.
Approach and landing: over a clear and flat area,
- perform a flat approach into wind,
- make a no-hover slow running landing around 10 kt,
- Do not hover or taxi without hydraulic pressure.
After landing:
- Collective …………………..LOCK
- Shutdown procedure ……….Apply
BATT TEMP
Warning Panel: Red Light
Battery Temp above maximum
- [EXT PWR BATT.] …..OFF
- U bus voltage …………..CHECK
NORMAL
LAND AS SOON AS PRACTICABLE
ABOVE U max
- [EXT PWR BATT.]…ON
- [GEN]………………..OFF
- Unnecessary equipments….. OFF
LAND AS SOON AS PRACTICABLE
BATT
Warning Panel: Yellow Light
Battery Off line
[EXT PWR BATT.]…………CHECK ON
YES
CHECK voltage on VEMD
LAND AS SOON AS PRACTICABLE
NO
[EXT PWR BATT.] …. ON
BATT light should go off
CONTINUE FLIGHT
GENE
Warning Panel: Yellow Light
DC Generator off line
- U bus on VEMD …….. CHECK
- [GEN] …………………CHECK ON
NO
[GEN] ………….ON
GENE Light goes out
CONTINUE FLIGHT
YES
“GENE RESET” circuit breaker …..Check not popped out (30α panel)
[GENE RESET]…………. Press
Case A: Light stays on
Unnecessary equipment….OFF
U bus on VEMD……… monitor
LAND AS SOON AS PRACTICABLE
Case B: Light goes out
CONTINUE FLIGHT
CAUTION
If the battery fails, the VEMD will go out and only the analog NR gauge will remain.
Apply the procedure for failure of both screens. (Section 3.5)
NOTE
GENE light comes on if the DC system is supplied with external power.
INV
Warning Panel: Yellow Light
AC power supply failure.
Inverter AC system:
[INV]……… CHECK ON
YES:
Loss of AC consumers
NOTE: AFCS* (Automatic Flight Control System) disengages automatically
Controls ……… HANDS ON
CONTINUE FLIGHT
NO:
[INV] ………………..ON
INV light should go out
CONTINUE FLIGHT
FUEL
Warning Panel: Yellow Light
Fuel quantity < 106 lbs
LAND AS SOON AS POSSIBLE
NOTE
15 min of flight time remain at MCP
WARNING
AVOID LARGE ATTITUDE CHANGES AS THIS COULD LEAD TO AN ENGINE FLAMEOUT
FUEL P
Warning Panel: Yellow Light
Low fuel pressure
(“Dont mess around with FADEC and the FUEL P and FUEL FILTER lights”… (LASAPo)
IN FLIGHT:
1. Collective pitch ………..REDUCE POWER
- Booster pump ………….ON
LAND AS SOON AS POSSIBLE
Low power approach and landing.
WARNING
BE PREPARED IN CASE OF AN ENGINE FLAME-OUT.
FUEL FILT
Warning Panel: Yellow Light
Fuel filter clogged.
(“Dont mess around with FADEC and the FUEL P and FUEL FILTER lights”… (LASAPo)
WARNING
FUEL FILTER BY-PASS OPENING DRIVES POLLUTION INTO THE FUEL LINES, AND THE GOVERNOR, WHICH MAY INDUCE OSCILLATIONS, LIMITED POWER OR EVENTUALLY FLAME-OUT.
Collective pitch ………….. REDUCE POWER
FUEL FILT Light stays ON:
LAND AS SOON AS POSSIBLE
VEMD………….MONITOR Ng
If Ng oscillations occur:
LAND IMMEDIATELY
Autorotation procedure……. APPLY.
FUEL FILT Light goes off:
Establish flight at reduced power.
LAND AS SOON AS PRACTICABLE
VEMD………….MONITOR Ng
If Ng oscillations occur:
LAND IMMEDIATELY
Autorotation procedure……. APPLY.
PITOT
Warning Panel: Yellow Light
Pitot heating not operative
[PITOT] …………………… CHECK ON
YES:
Monitor airspeed indicator
CONTINUE FLIGHT
NO:
[PITOT] ………………. ON
CONTINUE FLIGHT
HORN
Warning Panel: Yellow Light
Aural warning not operative
[HORN] ……………………CHECK ON
YES:
Aural warning failure
CONTINUE FLIGHT
NO
[HORN] ………………. ON
CONTINUE FLIGHT
DOOR
Warning Panel: Yellow Light
One or both cargo hold doors unlocked
Airspeed …………………..REDUCE to 70 kts
LAND AS SOON AS PRACTICABLE
descent and approach at low rate of descent.
Rotor Brake Inoperative
WARNING
WAIT UNTIL ROTOR COMES TO A STNADSTILL LEAVING THE AIRCRAFT.
Rotor stopping with wind blowing:
- Aircraft…………………….. INTO WIND.
- Cyclic stick ………………… slightly INTO WIND.
Flight control hardover or servojam
A hardover results in uncommanded movements of one or two flight controls (including yaw).
A servojam results in a higher than normal force to move the flight controls.
HIGE, T/O, Final: (if immediate landing is possible)
LAND IMMEDIATELY
After landing:
- HYD switch (collective grip) … OFF.
- Engine and rotor shutdown procedure ………APPLY
In Flight:
- Airspeed ………………. between 40 to 60 kt in level flight, enter sideslip if necessary.
- HYD switch (collective grip)… OFF. Proceed as in case of HYDR
LAND AS SOON AS POSSIBLE
Bleed Valve Failure
When the bleed valve opens, a flag appeasrs on the FLI or 3-data page.
The Flag disappears when the bleed valves closes.
The bleed valve is normally open when then the engine is shut down, during starting and at low power settings.
If the flag does not disappear at high power setting (i.e. near MCP or above), the maximum available engine power is reduced, specifically by cold weather.
If the flag does not reappear at low power settings, the engine may surge. Avoid abrupt changes in power settings.
• Bleed valve failure results in GOV Warning Light
LAND AS SOON AS PRACTICABLE
Abnormal Nf Governing
Abnormal low Nr and Nf (Parameters aligned)
FADEC governs Nf to a value that is significantly lower than usual.
This failure can be cause by an erroneous collective anticipator signal (XPC). Nr/Nf values may decrease to 360 rpm before the failure is detected by the FADEC. (GOV Warning Light comes on.)
If Nr/Nf drops below 375 rpm in flight:
- Engine parameters ……….. CHECK
- Nr/Nf ……… CHECK both parameters aligned
LAND AS SOON AS PRACTICABLE
Due to reduced tail rotor margins avoid hover flights with left crosswind and carry out a no hover anding.
