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AS350B3 > Emergency Procedures > Flashcards

Emergency Procedures Flashcards

(57 cards)

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1
Q

Land Immediately

A

Self explanatory.

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2
Q

Land as soon as possible

A

Land at the nearest site at which a safe landing can be made.

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3
Q

Land as soon as practicable

A

Extended flight is not recommended; the landing site and duration of the flight are at the discretion of the pilot.

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4
Q

Autorotation over land

A
  1. Reduce collective, maintain Nr
  2. Airspeed at Vy (65 kts)
  3. Twist grip to IDLE position (if relighting impossible or loss of tail rotor thrust)
  4. Maneuver into wind on final approach
  5. Flare at 75’
  6. Gradually increase collective to reduce descent and forward speed
  7. Cyclic forward for a <10° slightly nose up landing attitude
  8. Pedals for heading
  9. Collective up to cushion landing
  10. After touchdown adjust cyclic, collective and pedals for ground run
  11. Collective full low pitch once aircraft is stopped
  12. Apply rotor brake
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5
Q

Autorotation over water

A

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

  1. Collective pitch …………… MAINTAIN
  2. Door jettison handles…. PULL-UP
  3. Rotor brake……………….. APPLY

Abandon aircraft once the rotor has stopped.

  1. Reduce collective, maintain Nr
  2. Airspeed at Vy (65 kts)
  3. Twist grip to IDLE position (if relighting impossible or loss of tail rotor thrust)
  4. Maneuver into wind on final approach
  5. Flare at 75’
  6. Gradually increase collective to reduce descent and forward speed
  7. Cyclic forward for a <10° slightly nose up landing attitude
  8. Pedals for heading
  9. Collective up to cushion landing

10.

11.

12.

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6
Q

Hover IGE engine failure

A

Hover auto

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7
Q

Hover OGE engine failure

A

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.

  1. Collective pitch ……………… FULL LOW PITCH

• When NR stops decreasing

  1. Cyclic ………………………… FORWARD to gain airspeed according to available height.
  2. Autorotation procedure ………. APPLY
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8
Q

In flight relighting

A

According to available height and cause of flame-out :

  1. Starting selector…………. OFF position
  2. [FUEL PUMP]…………… ON
  3. 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.

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9
Q

Complete loss of tail rotor thrust IGE hover

A

Land Immediately.

Hover auto

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10
Q

Complete loss of tail rotor thrust OGE hover

A

Simultaneously,

  1. Collective ………………… REDUCE depending on available height
  2. Cyclic …………………….. FORWARD to gain speed
  3. Cyclic …………………….. ADJUST to get Vy or higher
  4. 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.

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11
Q

Complete loss of tail rotor thrust in cruise flight

A
  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 detent
  2. Carry out an autorotative landing
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12
Q

Loss of tail rotor control

A

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.

  1. Cyclic and collective…………. ADJUST to set IAS to 70 kt (130 km/h) in level flight.
  2. [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.

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13
Q

Smoke in cabin - source not identified

A

Heating, Demisting…………….. OFF

Smoke clears?

Yes: CONTINUE FLIGHT, depending on atmospheric conditions

No:

  1. [MASTER SW] ……… SHUT OFF
  2. [EXT PWR BATT.] …. OFF
  3. [GEN] ………………… OFF
  4. Ventilate the cabin.

When smoke clears :
5. All consumers………… OFF

  1. [MASTER SW] ……… ON
  2. [EXT PWR BATT.] .. ON check DC parameters
  3. [GEN] ………………… ON check DC parameters

Smoke clears?

No: LASAPo

Yes:

DC parameters correct (and no smoke detected) :

  1. Avionics ON
  2. 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 :

  1. [GEN] ………………… OFF
  2. 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)

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14
Q

Smoke in cabin - source identified

A
  1. Corresponding system ………. OFF
  2. 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.

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15
Q

VEMD one screen failure

A

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.

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16
Q

VEMD both screens failed

A

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.

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17
Q

Nr Indicator failure

A

Collective ……………………. MAINTAIN Tq > 10 %

NR reading is given by Nf pointer.

LAND AS SOON AS PRACTICABLE

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18
Q

Nf indicator failure

A

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.

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19
Q

Engine oil temp over 115°C

A

Fly at least 80 kts

If temp drops Land ASAPr. (oil cooler fan inop)

If temp does not drop Land ASAPo

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20
Q

Low engine oil pressure

A
  • 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.
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21
Q

Ng/△Ng Indicator Failure

A

Comply with max TQ value and T4 limit of 810°C.

In this case the T4 limits displayed are the starting limitations.

LASAPr

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22
Q

Torque meter failure

A

Comply with Ng limit table.

Approximately 96% Ng, and △Ng -4 for Kauai temps and altitudes

LASAPr

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23
Q

△Ng and Torque meter failure

Study These Flashcards
A

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

24
Q

T4 Indicator Failure

Study These Flashcards
A

Comply with Ng and torque limitations.

Switch off heating and demisting system.

On ground, do not try to start the engine.

Land ASAPr

25
Generator overvoltage \> 31.5 Volts | (RED Underline)
1. GEN ...............Off 2. CWP ...............Monitor for BATT TEMP 3. 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
26
Generator overvoltage ≤ 31.5 Volts | (Yellow Underline)
29.0 V \< UBUS ≤ 31.5 V Monitor UBUS voltage. Continue flight.
27
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.
28
Generator Current Over Limit | (RED Underline Flashing)
1. Unnecessary equipment ...........OFF CONTINUE FLIGHT
29
Engine fire at startup Warning Panel: ENG FIRE
1. Engine Starting Selector - OFF 2. Emergency Fuel Shutoff Handle - AFT 3. FUEL Pump - OFF 4. CRANK 10 seconds 5. MASTER SW - OFF 6. Rotor Brake - Apply (≤ 170 Nr) 7. Evacuate and fight fire from outside
30
Engine fire at Hover, Take-off, Final Warning Panel: ENG FIRE
LAND IMMEDIATELY ## Footnote Carry out a no hover powered landing. Once on ground, apply following procedure: 1. Engine Starting Selector - OFF 2. Emergency Fuel Shutoff Handle - AFT 3. FUEL Pump - OFF 4. CRANK 10 seconds 5. MASTER SW - OFF 6. Rotor Brake - Apply (≤ 170 Nr) 7. Evacuate and fight fire from outside
31
Engine Fire In Flight Warning Panel: ENG FIRE
LAND IMMEDIATELY ## Footnote 1. Collective pitch........... REDUCE 2. IAS .......................... Vy 3. Autorotation procedure ... APPLY 4. Emergency fuel shut-off handle ........... AFT 5. FUEL PUMP .........Check OFF 6. Starting selector.......... OFF position After landing : 7. [MASTER SW]........... OFF 8. Rotor brake ................ APPLY (≤ 170 rpm) 9. Evacuate aircraft and fight fire from outside.
32
Major Governor Failure In Flight Emergency Mode Engaged Warning Panel: GOV Red Light
1. Flight parameters ........CHECK Emergency mode automatically self-engages. GOV illuminates. 2. 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.
33
Major Governor Failure During Engine Start Emergency Mode Engaged Warning Panel: GOV Red Light
Engine Starting selector..............OFF position immediately
34
GOV Governing Function Degraded Minor FADEC Failure Warning Panel: GOV Yellow Light
1. Collective ...................AVOID abrupt power changes 2. IAS...........................MAINTAIN below VNE power off LAND AS SOON AS PRACTICABLE On ground : do not start engine.
35
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.
36
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
37
TWT GRP Warning Panel: Red Light
Twist grip out of FLIGHT position ## Footnote Twist grip ..................... TURN up to FLIGHT detent. CONTINUE FLIGHT
38
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.
39
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
40
MGB TEMP Warning Panel: Yellow Light
Main Gear Box oil overheating (\> 115°C) ## Footnote 1. IAS.........SET TO Vy 2. CWP .....MONITOR If MGB TEMP light goes out: LAND AS SOON AS PRACTICABLE If MGB TEMP light stays on: LAND AS SOON AS POSSIBLE
41
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
42
TGB CHIP Warning Panel: Yellow Light
Avoid prolonged hovering CONTINUE FLIGHT
43
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_ 1. Land normally 2. Twist grip ........Set to IDLE detent 3. Collective......LOCK 4. Engine Starting selector ....OFF _In Flight_ 1. Collective/Cyclic ............SET IAS within 40 to 60 kt (hydraulic failure safety speed) 2. 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
44
BATT TEMP Warning Panel: Red Light
Battery Temp above maximum 1. [EXT PWR BATT.] .....OFF 2. U bus voltage ..............CHECK _NORMAL_ LAND AS SOON AS PRACTICABLE _ABOVE U max_ 1. [EXT PWR BATT.]...ON 2. [GEN]....................OFF 3. Unnecessary equipments..... OFF LAND AS SOON AS PRACTICABLE
45
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
46
GENE Warning Panel: Yellow Light
DC Generator off line 1. U bus on VEMD ........ CHECK 2. [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.
47
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
48
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
49
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 2. Booster pump .............ON LAND AS SOON AS POSSIBLE Low power approach and landing. WARNING BE PREPARED IN CASE OF AN ENGINE FLAME-OUT.
50
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.
51
PITOT Warning Panel: Yellow Light
Pitot heating not operative [PITOT] ........................ CHECK ON _YES_: Monitor airspeed indicator CONTINUE FLIGHT _NO_: [PITOT] ................... ON CONTINUE FLIGHT
52
HORN Warning Panel: Yellow Light
Aural warning not operative [HORN] ........................CHECK ON _YES:_ Aural warning failure CONTINUE FLIGHT NO [HORN] ................... ON CONTINUE FLIGHT
53
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.
54
Rotor Brake Inoperative
WARNING WAIT UNTIL ROTOR COMES TO A STNADSTILL LEAVING THE AIRCRAFT. Rotor stopping with wind blowing: 1. Aircraft.......................... INTO WIND. 2. Cyclic stick ..................... slightly INTO WIND.
55
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: 1. HYD switch (collective grip) ... OFF. 2. Engine and rotor shutdown procedure .........APPLY _In Flight:_ 1. Airspeed ................... between 40 to 60 kt in level flight, enter sideslip if necessary. 2. HYD switch (collective grip)... OFF. Proceed as in case of HYDR LAND AS SOON AS POSSIBLE
56
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
57
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: 1. Engine parameters ........... CHECK 2. 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.

AS350B3 (4 decks)

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