AIRBUS H125 / AS350B3e (2D Engine) Emergency Procedures Flashcards
AIRBUS H125 / AS350B3 Checkride Study Info
DISCLAIMER
This flash card study aide is provided to ease and assist in studying much more comprehensive material provided by Eurocopter / Airbus. The creator of this study aide accepts no responsibility for inaccuracies or abbreviation of procedures. This is intended to introduce the associated material and all persons using these cards should study and reference the officially distributed material from the manufacturer. It is recommended that after referencing each card, the student should independently verify the information on that card by looking it up and learning the comprehensive information from the direct source. If any inaccuracies, misleading or typo errors are found, please notify the administrator of the study deck.
FLAME OUT IN FLIGHT
SYMPTOMS
- Jerk in Yaw Axis (only in high power flight)
- Drop in Rotor RPM (Horn below 360 RPM)
- Torque at Zero
- NG Falling to Zero
- Generator Warning Light ON
- Engine Oil Pressure Warning Light ON
- ENTER AUTOROTATION!!
AUTOROTATION
FORWARD FLIGHT
(Following Engine Failure)
AUTOROTATION PROCEDURE OVER LAND
1. Collective pitch: REDUCE to maintain NR in normal operating range.
2. IAS : Vy (65 kias).
- If relighting impossible or after loss of tail rotor thrust
3. Twist grip: IDLE position.
4. Maneuver the aircraft into the wind on final approach.
- At height about 70 ft (21 m)
5. Cyclic : FLARE.- At 20/25 ft (6/8 m) and at constant attitude
6. Collective pitch : GRADUALLY INCREASE to reduce the rate of descent and forward speed.
7. Cyclic : FORWARD to adopt a slightly nose-up landing attitude (< 10°).
8. Pedals : ADJUST to cancel any sideslip tendency.
9. Collective pitch : INCREASE to cushion touch-down.- At 20/25 ft (6/8 m) and at constant attitude
10. Cyclic, collective, pedals : ADJUST to control ground run.
- Once the aircraft has stopped
11. Collective pitch : FULL LOW PITCH.
12. Rotor brake : APPLY below 170 rotor rpm.
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 (56 km/h)) and rate of descent.
Then apply following check list for items 10, 11, 12.
- After touch-down
10. Collective pitch : MAINTAIN.
11 Doors jettison handles : PULL-UP.
12. Rotor brake : APPLY
IGE HOVER AUTOROTATION
- Do Not Reduce Collective Pitch
- Control Yaw
- Cushion Touchdown by Increasing Collective
- Reduce Collective As Soon As Aircraft Is On The Ground
OGE HOVER AUTO
- FULL LOW Collective Pitch
- When NR stops decreasing, forward Cyclic to Gain Airspeed (dependent on height above ground)
- Attempt Remaining Autorotation Steps
RELIGHTING ENGINE IN FLIGHT
According to available height and cause of flame-out:
1. FUEL P / FUEL PUMP : ON
- GENE : OFF
- Starting selector : OFF, then ON position.
The relighting sequence will then run automatically as soon as N1 < 10 %.
- After relighting
4. GENE : ON
FUEL P / FUEL PUMP : OFF.
At least 1000 ft (300 m) are necessary to complete relighting procedure after flame-out.
TAIL ROTOR DRIVE FAILURE
Symptom
Will result in left yaw, extent will depend on power and speed at time of failure.
TAIL ROTOR FAILURE
Hover IGE
LAND IMMEDIATELY
- Twist Grip : IDLE position.
- Collective : INCREASE to cushion touch-down.
TAIL ROTOR FAILURE
Hover OGE
LAND AS SOON AS POSSIBLE
Simultaneously,
1. Collective : REDUCE depending on available
height.
2. Cyclic : FORWARD to gain speed.
3. Airspeed : MAINTAIN Vy or higher.
4. Collective : ADJUST to obtain minimum sideslip
angle.
If a go-around was performed, carry out an autorotative landing on an area suitable for the autorotation procedure.
TAIL ROTOR FAILURE
In Cruise Flight
LAND AS SOON AS POSSIBLE
- Airspeed : MAINTAIN Vy or higher.
- Collective : ADJUST to obtain minimum sideslip angle.
On a suitable area for autorotative landing:
- Twist grip : IDLE position.
- Carry out an autorotative landing according to the autorotation procedure
(Refer to Section 3.2 § 1)
LOSS OF TAIL ROTOR CONTROL
Symptom: jamming of pedals or loss of pedal effectiveness. These conditions make it impossible to change tail rotor thrust with the pedals.
WARNING: LANDING IS MADE EASIER WITH A RH WIND COMPONENT. WHEN AIRSPEED IS LESS 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.
- Hydraulic cut-off switch (collective grip) - OFF.
- [ACCU TST] - PRESS for 2 sec. (load compensator depressurizes) 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
(If smoke doesn’t clear)
- [BATT] : EMER SHED
- [GENE] : OFF.
- [AVIONIC] (if fitted) : OFF.
- Ventilate the cabin.
When smoke clears:
- All consumers : OFF.
- [BATT] : ON.
- [GENE] : ON, check DC Parameters.
If smoke doesn’t clear
LAND AS SOON AS POSSIBLE
If smoke DOES clear, but;
If DC parameters not correct:
- [GENE] : OFF.
- Apply case A of GENE DC generator off line procedure.
LAND AS SOON AS PRACTICABLE
Smoke clears, and DC parameters correct
- [AVIONIC] : ON.
- Minimum required consumers : ON, one by one, if smoke returns, switch off that particular system for remainder of flight.
CONTINUE FLIGHT
depending on atmospheric conditions
CAUTION
When [EMER SHED] is actuated the VEMD goes off. Apply the procedure for failure of both screens (Section 3.5 § 1 VEMD screen failures).
SMOKE IN CABIN
Source Identified
SOURCE IDENTIFIED
- Corresponding system : OFF.
- Ventilate the cabin.
CONTINUE FLIGHT
depending on system failed.
NOTE
After DC has been switched-off and on in flight, GOV light will remain on until the next normal full engine shut down and battery switch off on the ground
VEMD SCREEN FAILURES
Failure of one screen
Failed Screen : OFF.
Read all available information on the other screen.
Informations are available using the [SCROLL] pushbutton either on the VEMD or on the collective grip.
If top screen fails, the 3-parameter engine page will be automatically displayed on lower screen but with torque and ΔNg off line. Only T4 and digital Ng will be available, refer to paragraph 4 for compliance with limitations.
Failure of both screens
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 0 Hp - (2 kt / 1000 ft).
LAND AS SOON AS PRACTICABLE
Landing procedure: Carry out a no hover landing.
CAUTION MESSAGES ON VEMD
When a parameter is off line, the parameter value is not displayed on the corresponding VEMD screen and the parameter scale symbology is displayed in yellow.
Caution messages are self explanatory and the pilot shall comply with the action requested. If no light is lit on the caution and warning panel, no other action is required from the pilot.
IE: You get a VEMD message on shutdown “failure detected”, you may investigate, you may alert maintenance personnel, but it does not ground the helicopter unless an accompanying light such as GOV is illuminated. Message OVERLIMIT DETECTED do not conduct another flight until corrective Mx is conducted.
For all of these messages, unless otherwise required by accompanying caution/warning lights or procedures:
CONTINUE FLIGHT
NR (ROTOR RPM) INDICATOR FAILURE
Maintain engine torque above 10%: NR reading is then given by the N2 pointer
LAND AS SOON AS PRACTICABLE
N2 INDICATOR FAILURE
Check NR:
if it is normal with torque above 0%
CONTINUE FLIGHT
NOTE 1: The N2 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 may not be available.
ABNORMAL N2 GOVERNING
Abnormal low NR and N2 (Parameters aligned)
FADEC governs N2 to a value that is significantly lower than usual.
This failure can be caused by an erroneous collective anticipator signal (XPC). NR/Nf values may decrease to 360 rpm before the failure is detected by the FADEC ( GOV comes on).
If NR/Nf drop below 375 rpm in flight:
- Engine parameters : CHECK
- NR/N2 : CHECK both parameters aligned
LAND AS SOON AS PRACTICABLE
Due to reduced tail rotor control margins avoid hover flights with left crosswind and carry out a no hover landing.
Oil Temp Over °117c
Reduce power and set speed at 80 knots.
Temperature should fall rapidly; If not,
LAND AS SOON AS POSSIBLE
If temperature does decrease
LAND AS SOON AS PRACTICABLE
Check oil cooler fan operation
OIL
IN FLIGHT
- Test Warning-Caution Panel and check that ENP P light illuminates
- If ENG P light is already on, or does not illuminate when tested (presume it is on):
LAND IMMEDIATELY: Autoration procedures apply; Shut down engine time permitting
- If ENG P light does illuminate when tested:
- LAND AS SOON AS PRACTICABLE.
- Monitor ENG P light
Loss of N1, Torque or TOT parameters on VEMD
When a parameter is off line, the parameter value is not displayed on the VEMD upper screen and the parameter scale symbology is displayed in yellow.
The First Limitation Indicator (FLI) is replaced by the 3 data symbology (Ng/delta Ng, t4 and torque) and a failure message is displayed.
N1 INDICATOR FAILURE
LAND AS SOON AS PRACTICABLE
Comply with the maximum TRQ value and TOT limit of 842°C.
NOTE
In this case, the TOT limitations displayed are the starting limitations.
An engine overlimit may be recorded and the OVERLIMIT DETECTED message displayed on VEMD if the TOT exceeds 750°C. The over limit can be ignored
TORQUEMETER FAILURE
LAND AS SOON AS PRACTICABLE
N1 AND Tq indications failure
LAND AS SOON AS PRACTICABLE
The VEMD switches to 3-data symbology with only TOT and numerical N1 as valid parameters. Comply with N1 limitations in the above table, and respect a TOT limit of 842°C.
TOT INDICATOR FAILURE
LAND AS SOON AS PRACTICABLE
• TOT Indicator Failure:
Comply with N1 and TRQ limitations.
Switch off heating and demisting system.
On ground: do not start the engine
IN FLIGHT
- [GEN] or [GENE] : OFF
- CWP : MONITOR for BATTERY TEMP
- [GENE RESET]
LAND AS SOON AS PRACTICABLE
CAUTION
If the battery fails, the VEMD will go out and only the analogue NR indication will remain. Apply the procedure for failure of both screens (Section 3.5 § 1 VEMD screen failures).
IN FLIGHT
- U/BUS voltage : MONITOR
CONTINUE FLIGHT
IN FLIGHT
- Reset GEN, if it then produces 26V or more;
CONTINUE FLIGHT
- If reset unsuccessful;
LAND AS SOON AS PRACTICABLE
NOTE
Probable cause of such a failure is a generator defect that does not make GENE come on
IN FLIGHT
- Unnecessary equipment : OFF
- *CONTINUE FLIGHT**
- *NOTE**
After engine starting on battery, a temporary high generator current is normal because the battery is being recharged. During this phase, avoid using high electrical load consumers
DURING START
- Engine starting selector : OFF position
- Emergency fuel shut-off handle : AFT
- [FUEL P] : OFF
- [CRANK] : PRESS (10 sec.)
- [EMER SW] : OFF
- Rotor brake : APPLY (below 170 rpm)
- Evacuate aircraft and fight fire from outside
Hover, Takeoff, Final
LAND IMMEDIATELY
Carry out a no hover powered landing. Once on ground, apply same procedure as above.
IN FLIGHT
LAND IMMEDIATELY
- Collective : LOWER
- IAS : Vy
- Autorotation procedure : APPLY
- Emergency fuel shut-off handle : AFT
- [FUEL P] : CHECK OFF
- Engine starting selector : OFF position
- After Landing: - [EMER SW] : OFF
- Rotor brake : APPLY (below 170 rpm)
- Evacuate aircraft and fight fire from outside
ON START UP
Engine starting selector : OFF position immediately
IN FLIGHT
- Flight parameters : CHECK
Emergency mode automatically self-engages GOV illuminates. - Collective : AVOID abrupt changes
Maintain Ng > 80% Hp < 20000 ft (6096 m)
Maintain Ng > 85% Hp ›20000 ft (6096 m)
LAND AS SOON AS PRACTICABLE
Approach and Landing:
. Make a powered approach
. Avoid steep angle
. Collective : SLOWLY down to low pitch. Engine starting selector : OFF
NOTE
On VEHICLE page:
FF and END .
This failure can also result in loss of delta Ng and torque
parameters on the VEMD.
Flashing at idle or during starting or shutdown
Governor redundancy failure, no impact on governing function.
. Start-up procedure: Abort, refer to Maintenance Manual
. Autorotation training: Cancel training, return to base
IN FLIGHT
Continuously on:
Governing function degraded
- Collective : AVOID abrupt power changes
- IAS : MAINTAIN below VNE power off
LAND AS SOON AS PRACTICABLE
On ground: Do not start engine
IN FLIGHT
Check engine oil pressure, if pressure is low, or zero,
LAND IMMEDIATELY
Autorotation procedures apply. Shut down engine time permitting
If engine oil pressure ok,
LAND AS SOON AS PRACTICABLE
IN FLIGHT
Twist grip : TURN to FLIGHT position
CONTINUE FLIGHT
IN FLIGHT
LAND AS SOON AS POSSIBLE
- *REDUCE power**
- *Low power approach and landing**
- *Be prepared in case of a loss of engine power.**
NOTE
Takeoff is prohibited until checks specified in TURBOMECA Maintenance Manual have been completed
IN FLIGHT
Reduce Power
LAND AS SOON AS POSSIBLE
Main Gear Box low oil pressure < 1 bar
If a safe landing is not possible, continue flight to the nearest appropriate landing site, reduce power to fly at minimum power speed (Vy).
NOTE
At low power (Vy) a maximum of 55 min. of simulated flight time has been demonstrated during bench tests
IN FLIGHT
Slow to Vy (65 KIAS), if light goes out
LAND AS SOON AS PRACTICABLE
if light stays on
LAND AS SOON AS POSSIBLE
IN FLIGHT
LAND AS SOON AS POSSIBLE
Reduce Power
Monitor MGB P and MGB TEMP
IN FLIGHT
CONTINUE FLIGHT
Avoid prolonged hovering
IN FLIGHT
LAND AS SOON AS PRACTICABLE
For all cases, normal approach and landing
LOSS OF HYDRAULIC PRESSURE (Less than 30 bar) on corresponding circuit
(Accompanied by GONG)
CAUTION
During high load factor maneuvers, servocontrol
reversibility may be encountered
Keep aircraft in a more or less level attitude.
Avoid abrupt maneuvers.
Maintain angle of bank less than 30°.
Maintain IAS below 110 kt (or VNE if less).
NOTE
One remaining circuit allows continued safe flight and
landing.
If HYD1, loss of LH circuit, may also get LIMIT light
If HYD2, loss of RH circuit: Tail rotor control hydraulic power lost.
CAUTION
Do not press the [ACCU TST] pushbutton as this would discharge the yaw load compensator and right pedal loads may be significant
IN FLIGHT
Disconnected for lead acid. If illuminated, possible wire short should be investigated.
Normal EP is:
If ABOVE U max
- [BAT/EPU] : ON
- [GENE] : OFF
- Unnecessary equipment : OFF
LAND AS SOON AS PRACTICABLE
Check that battery button is ON
If ON but bad V
LAND AS SOON AS PRACTICABLE
If V good
CONTINUE FLIGHT
IN FLIGHT
- U bus on VEMD : CHECK
- [GENE] : CHECK ON, if it IS:
- “GENE RST” : Circuit breaker check if popped
- If light goes out
CONTINUE FLIGHT
- If light remains on
- [GENE] : RST
- [GENE] : ON
If light goes out
CONTINUE FLIGHT
If light stays on:
- Unnecessary equipment : OFF
- U bus on VEMD : MONITOR
LAND AS SOON AS PRACTICABLE
CAUTION
If the battery fails, the VEMD will go out and only the analogue NR indication will remain. Apply the procedure for failure of both screens (Section 3.5 § 1 VEMD screen failures).
IN FLIGHT
- CHECK [INV] ON
- If On but Loss of all AC consumers
NOTE
AFCS* disengages automatically INV
Controls : HANDS ON
CONTINUE FLIGHT
LAND AS SOON AS POSSIBLE
Avoid large attitude changes
Remaining fuel approx. 15.8 Gal
Approx. 15 minutes flying time at MCP
WARNING
AVOID LARGE ATTITUDE CHANGES AS THIS COULD
LEAD TO AN ENGINE FLAME-OUT.
IN FLIGHT
LAND AS SOON AS POSSIBLE
- Collective : REDUCE POWER
- [FUEL P] or [FUEL PUMP] : ON
Low power approach and landing
- *WARNING**
- *BE PREPARED IN CASE OF AN ENGINE FLAME-OUT**
IN FLIGHT
Fuel filter pre-clogged
Fuel filter pre-clogging level 2 reached
WARNING
FUEL FILTER BY-PASS OPENING LEADS TO CONTAMINATION OF THE FUEL LINES AND THE GOVERNOR, WHICH MAY INDUCE N1 OSCILLATIONS, LIMITED POWER OR POSSIBLY FLAME-OUT.
LAND AS SOON AS PRACTICABLE
MONITOR N1 If N1 oscillations occur:
LAND IMMEDIATELY
Flashing at idle or during starting or shutdown
Fuel filter pre-clogging level 1 reached
• One flight of 3 hours maximum flight time can be
performed before maintenance action
Check pitot button ON
Monitor airspeed indicator
CONTINUE FLIGHT
Push horn button ON
CONTINUE FLIGHT
IN FLIGHT
Reduce airspeed (70 knots maximum)
LAND AS SOON AS PRACTICABLE
Descent and approach at low rate of descent
IN FLIGHT
CONTINUE FLIGHT
NOTE
The forward reading lights can be used as additional
instrument panel lighting.
IN FLIGHT
Main servo unit max. load reached
In high speed cruise flight or steep maneuvers:
- Collective : Reduce power.
- Cyclic : Reduce speed or load factor.
- *CONTINUE FLIGHT**
- *NOTE**
LIMIT may appear associated with HYD1 in case of
hydraulic failure
IN FLIGHT
LAND AS SOON AS PRACTICABLE
Jamming of a distributor valve on main servo unit
