General
Land Immediately, Land ASAP, Land as soon as Practicable, Continue Flight
Audio Warnings (Horn and Gong)
HORN - Button used to activate the audio warning
GONG - Red warning on warning panel
Audio Warnings (Continuous Tone)
Two continuous tones can be heard:
- A 310 Hz tone when NR is below 360 rpm.
- A 285 Hz tone when maximum take-off limitations are exceeded:
* After 1.5 sec. delay if power remains within transient range.
* Immediately when transient power limitations are exceeded. In addition, for VEMD after embodiement of (MOD. 07-3195)
* Immediately when max. transient rating is or will be exceeded during fast power
1. Collective - REDUCE to maintain NR in normal operating range or power within
limitations.
2. Engine parameters - CHECK.
Audio Warnings (Intermittent Tone)
An intermittent tone (310 Hz) is heard when the NR is above 410 rpm.
- Collective pitch - INCREASE
to maintain NR in normal operating range.
Engine Flame-Out
Over Land
- Collective pitch - REDUCE
to maintain NR in normal operating range. - IAS - Vy.
- 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.
Height of 70 ft (21 m)
5. Cyclic - FLARE.
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.
After touch-down
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.
Engine Flame-Out
Over Water
Apply same procedure as over land, 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.
After touch-down
10. Collective pitch - MAINTAIN
11. Door jettison handles - PULL-UP
12. Rotor brake - APPLY
Abandon aircraft once the rotor has stopped.
Engine Flame-Out
Hover IGE
- Collective - MAINTAIN.
- Pedals - CONTROL YAW.
- Collective - INCREASE as needed to cushion touch-down.
Engine Flame-Out
Hover OGE
- Collective pitch - FULL LOW PITCH.
- When NR stops decreasing
2. Cyclic - FORWARD
to gain airspeed according to available height.
3. Autorotation procedure - APPLY.
Engine Flame-Out
In-Flight Relighting
According to available height and cause of flame-out:
1. Starting selector - OFF position.
2. (FUEL P) or (FUEL PUMP) - ON.
3. Starting selector - ON position.
The relighting sequence will then run automatically as soon as Ng < 17 %. - After relighting
4. (FUEL P) or (FUEL PUMP) -OFF.
At least 1000 ft (300 m) are necessary to complete relighting procedure after flame-out.
Complete Loss of Tail Rotor Thrust
Hover IGE or (OGE within HV Diagram)
LAND IMMEDIATELY
1. Twist Grip - IDLE position.
2. Collective - INCREASE to cushion touch-down.
Complete Loss of Tail Rotor Thrust
Hover OGE (Clear Area, Outside H/V Diagram)
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.
LAND AS SOON AS POSSIBLE
If a go-around was performed, carry out an autorotative landing on an area suitable for the autorotation procedure.
Complete Loss Of Tail Rotor Thrust
In Cruise Flight
1.Airspeed - MAINTAIN Vy or higher.
2. Collective - ADJUST to obtain minimum sideslip angle.
LAND AS SOON AS POSSIBLE
APPROACH AND LANDING
On a suitable area for autorotative landing:
1. Twist grip - IDLE position.
2. Carry out an autorotative landing according to the autorotation procedure
Loss Of Tail Rotor Control (Stuck Pedal)
WARNING
LANDING IS MADE EASIER WITH A RH WIND COMPONENT.
WHEN AIRSPEED IS LESS THAN 20 KT (37 KM/H), GO-AROUND IS IMPOSSIBLE DUE TO LOSS OF VERTICAL FIN EFFICIENCY.
- Cyclic and collective - ADJUST to set IAS to 70 kt in level flight.
- (HYD TEST) or [ACCU TST] - ON, load compensator depressurizes.
After 5 sec: - (HYD TEST)or [ACCU TST] - 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 The Cabin
Not Identified
1) Heating, Demisting - OFF
SMOKE CLEARS
YES
1. CONTINUE FLIGHT
depending on atmospheric conditions
NO
1. (MASTER SW) or [EMER SW] - SHUT OFF.
2. (EXT PWR BATT) or (BAT/EPU) - OFF.
3. (DCT BAT) (if fitted) - OFF.
4. [GEN] or [GENE] - OFF.
5. [AVIONIC] (if fitted) - OFF.
6. Ventilate the cabin.
When smoke clears:
7. All consumers - OFF.
8. (MASTER SW) or [EMER SW] - ON.
9. (DCT BAT) (if fitted) - ON.
10. (EXT PWR BATT) or (BAT/EPU) - ON check DC Parameters.
11. [GEN] or [GENE] - ON, check DC Parameters.
SMOKE CLEARS
YES
If DC parameters correct:
12. [AVIONIC] (if fitted) - ON. 13. 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
NO
If DC parameters not correct:
12. [GEN] or [GENE] - OFF.
13. Apply case A of GENE DC
generator off line procedure.
LAND AS SOON AS PRACTICABLE
CAUTION
When (MASTER SW) or [EMER SW] is actuated or battery and generator are off line, the VEMD goes off. Apply the procedure for failure of both screens (Section 3.5 § 1 VEMD screen failures).
Smoke In The Cabin
Identified
- Corresponding system - OFF.
- Ventilate the cabin.
CONTINUE FLIGHT
depending on system failed.
NOTE
FLIGHT MANUAL
- 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 Single Screen Failure
- 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 pitch lever.
If top screen fails, the 3-parameter 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 Screen Failures
- 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).
IAS km/h = 185 km/h at 0 Hp - (4 km/h per 300 m).
1) LAND AS SOON AS PRACTICABLE
Landing procedure: Carry out a no hover landing.
NR Indication Failure
Collective - MAINTAIN Tq > 10 %. NR reading is given by Nf pointer.
LAND AS SOON AS PRACTICABLE
NF Indication Failure
NR gauge - CHECK in normal operating range with Tq > 0.
CONTINUE FLIGHT
Engine Oil Temp over 115 C
- Airspeed - SET to 80 Kt (148 km/h)
Temperature decreases
NO
2. LAND ASAP
YES
2. LAND AS SOON AS PRACTICABLE
3. Check oil cooler fan operation
Low Engine Oil Pressure
- CWP - Check (ENG P) Light
YES
2. LAND IMMEDIATELY
-Autorotation procedure - APPLY
-Shut down engine, time permitting.
NO
3. CWP Light Test - Completed
Light Illuminates - LAND AS SOON AS PRACTICABLE
Light Does Not Illuminate - LAND IMMEDIATELY
-Autorotation procedure - APPLY.
-Shut down engine, time permitting.
NG/Delta NG Indicator Failure
- Comply with the maximum torque value and t4 limit of 810°C.
- LAND AS SOON AS PRACTICABLE
Torque Meter Failure
- Comply with NG Table
- LAND AS SOON AS PRACTICABLE
Delta NG and Torque Meter Failure
(GOV) warning can also induce loss of Delta 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, and respect a t4 limit of 810°C.
- LAND AS SOON AS PRACTICABLE
