3 EMERGENCY PROCEDURES

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an eurocopter EADS Company FLIGHT MANUAL AS355 NP SECTION 3 EMERGENCY PROCEDURES Page 3.1 GENERAL 3-1 3.1.1 AUDIO WARNINGS 3-1 3.1.2 VISUAL WARNINGS AND ADVISORIES 3-2 3.2 AUTOROTATION LANDING 3-3 3.2.1 CRUISE FLIGHT OVER LAND 3-3 3.2.2 DITCHING (WITHOUT EMERGENCY FLOATATION GEAR) 3-4 3.3 ENGINE FAILURE 3-5 3.3.1 ENGINE FAILURE ON TAKEOFF 3-5 3.3.2 ENGINE FAILURE IN HOVER 3-6 3.3.3 ENGINE FAILURE IN CRUISE FLIGHT 3-8 3.3.4 OEI APPROACH AND LANDING 3-8 3.4 IN FLIGHT INTENTIONAL ENGINE SHUTDOWN 3-9 3.5 IN FLIGHT ENGINE RELIGHTING 3-9 3.6 FUEL FLOW GOVERNOR FAILURES 3-10 3.7 SMOKE IN THE CABIN 3-12 3.7.1 SOURCE IDENTIFIED 3-12 3.7.2 SOURCE NOT IDENTIFIED 3-13 3.8 TAIL ROTOR MALFUNCTIONS 3-14 3.8.1 TAIL ROTOR DRIVE SHAFT FAILURE 3-14 3.8.2 TAIL ROTOR CONTROL FAILURE 3-15 3.9 ICING 3-16 3.10 AIR DATA INSTRUMENTS FAILURES 3-16 3.11 VEMD FAILURES AND CAUTION MESSAGES 3-18 3.11.1 VEMD SCREEN FAILURES 3-18 3.11.2 MESSAGES ON VEMD 3-18 3.11.3 CAUTION MESSAGES ON FLI 3-20 EASA APPROVED ORIGINAL ISSUEFLIGHT MANUAL AS355 NP an eurocopter EADS Company 3.12 ENGINES EMERGENCIES 3-24 3.12.1 FIRE 3-24 3.12.2 DIFF. POWER 3-25 3.12.3 ENGINE OIL SYSTEM 3-26 3.12.4 FADEC FAILURES 3-28 3.13 TRANSMISSION EMERGENCIES 3-30 3.14 HYDRAULIC EMERGENCIES 3-32 3.14.1 CAUTION LIGHTS 3-32 3.14.2 YAW CONTROL SERVO-UNIT SLIDE VALVE JAMMED 3-33 3.15 ELECTRICAL EMERGENCIES 3-34 3.15.1 BATTERY FAILURES 3-34 3.15.2 GENERATORS FAILURES 3-35 3.15.3 DIRECT BATTERY CIRCUIT FAILURE 3-37 3.15.4 AC SYSTEM* FAILURES 3-38 3.16 FUEL SYSTEM EMERGENCIES 3-41 3.17 MISCELLANEOUS CAUTION/ADVISORY LIGHTS 3-42 3.17.1 PITOTS 3-42 3.17.2 DOORS 3-42 3.17.3 HORN 3-42 3.17.4 TRAINING MODE 3-43 3.17.5 LIMIT 3-44 3.18 NR/N2 INDICATION FAILURES 3-45 3.18.1 NR INDICATION FAILURE 3-45 3.18.2 N2 INDICATION FAILURE 3-45 3.19 VARIOUS WARNINGS, FAILURES AND INCIDENTS 3-46 3.19.1 ROTOR BRAKE INOPERATIVE 3-46 3.19.2 ICS INOPERATIVE (GMA 340 H) 3-46 3.19.3 COCKPIT LIGHTING FAILURE 3-47 (*) if installed ii EASA APPROVED REVISION 3FLIGHT MANUAL an eurocopter EADS Company AS355 NP 3.1 GENERAL Emergency procedures describe the actions the pilot must perform according to the various cases of failure. However, according to the high diversity of the outside factors and type of terrain overflown, the pilot may have to adapt to the conditions from his experience. To help the pilot in his decision process, four expressions are used : LAND Self explanatory. LAND AS SOON AS POSSIBLE Emergency conditions that require to land at the nearest landing site where a safe landing can be made. LAND AS SOON AS PRACTICABLE Land at the nearest site where appropriate technical assistance may be expected. Extended flight is not recommended. CONTINUE FLIGHT Continue flight as planned. Have repairs performed at destination in compliance with the maintenance manual. NOTE Immediate actions that the pilot shall take and be able to perform from memory are written in bold characters. 3.1.1 AUDIO WARNINGS On the front overhead panel, a [HORN] pushbutton is used to activate the audio warning. When pressed in : HORN NOTE The pilot at the controls shall wear an adequate radio / ICS audio headset to monitor the audio warning through the ICS system. GONG A gong is generated each time a red warning light appears on the Caution and Warning Panel. EASA APPROVED 3 1 ORIGINAL ISSUEFLIGHT MANUAL AS355 NP an eurocopter EADS Company CONTINUOUS TONE Two continuous tones can be heard : - a 310 Hz tone when NR is ≤ 360 rpm. - a 285 Hz tone : . after 1.5 sec. delay when OEI limitations are exceeded, after 2.5 sec. delay when AEO limitations are exceeded, immediately when AEO transient limitations are or will be exceeded during fast power increase. 1. Collective pitch REDUCE to maintain NR in green range or power within limitations. 2. Engine parameters CHECK. INTERMITTENT TONE An intermittent tone (310 Hz) can be heard when the NR is above 410 rpm. 1. Collective pitch INCREASE to maintain NR in green range. 2. Apply applicable procedure according to the situation. 3.1.2 VISUAL WARNINGS AND ADVISORIES Symbol used for CWP warning, caution, advisory lights : ENG P.1 ENG P.1 ON OUT Symbol used for VEMD advisories: ON OUT OEI MAX OEI MAX ON OUT Symbol used for VEMD messages : CHECK N1 CHECK N1 ON OUT 2 EASA APPROVED REVISION 2an eurocopter EADS Company FLIGHT MANUAL AS355 NP 3.2 AUTOROTATION LANDING 3.2.1 CRUISE FLIGHT OVER LAND 1. Collective pitch REDUCE to maintain NR within green range. 2. IAS SET to 65 kt (120 km/h), heading into wind. Time permitting : 3. Emergency fuel shutoff levers AFT. 4. Booster pumps OFF. 5. Engines selectors OFF. 6. [EMERGENCY CUT OFF] OFF on final approach. At height around 70 ft (21 m), depending on gross weight and external conditions (wind and terrain) : 7. Cyclic FLARE to a nose-up attitude of 15/20°. At 20/25 ft (6/8 m) and at constant attitude : 8. Collective pitch INCREASE gradually to reduce the rate of descent and forward speed. 9. Cyclic FORWARD to adopt a slightly nose-up landing attitude 10. Pedals ADJUST to cancel any sideslip tendency. 11. Collective pitch INCREASE to cushion touch- down. EASA APPROVED 3 3 ORIGINAL ISSUEFLIGHT MANUAL AS355 NP eurocopter an EADS Company After touch-down : 12. Cyclic, collective, pedals CONTROL ground run. Once the aircraft has stopped : 13. Collective pitch FULL DOWN. 14. Rotor brake APPLY below 170 rpm. 15. [EMERGENCY CUT OFF] OFF (if not performed before). 3.2.2 DITCHING (WITHOUT EMERGENCY FLOATATION GEAR) Apply same procedure as over land, except items 12, 13 and 14. Maneuver to head the aircraft equally between the wind and waves direction on final approach. Ditch with minimum forward speed (IAS 30kt) (56 km/h) and rate of descent. Then apply the following : After touch-down : 12. Collective pitch MAINTAIN UP. 13. Rotor brake APPLY. 14. Door emergency handles PULL-UP, JETTISON forward doors. 15. Unfasten seat belts. Abandon aircraft once the rotor has stopped. 4 EASA APPROVED ORIGINAL ISSUEFLIGHT MANUAL an eurocopter EADS Company AS355 NP 3.3 ENGINE FAILURE NOTE 1 LIMIT may appear when exceeding AEO MTOP or when selected OEI rating is exceeded in case of an engine failure. NOTE 2 OEI ratings stops are selected by a pushbutton on the collective grip. Although N1 are limited to corresponding selected rating; torque limits are to be controlled by the pilot. 3.3.1 ENGINE FAILURE ON TAKEOFF By applying the takeoff procedure defined in SECTION 4 and depending on the terrain surface configuration, pilot should abort takeoff when failure occurs at IAS 360 rpm. 2. Cyclic stick NOSE UP to +15° attitude. When aircraft begin to sink 3. Cyclic stick REDUCE NOSE UP attitude 8°). 4. Collective pitch INCREASE to cushion touchdown. 5. Collective pitch FULL DOWN after complete stop. EASA APPROVED 5 ORIGINAL ISSUEFLIGHT MANUAL AS355 NP an eurocopter EADS Company 3.3.1.2 Continued takeoff 1. Collective pitch LOWER, maintain NR > 360 rpm, CONTROL OEI MAX power. 2. IAS Vy as soon as possible. 3 OEI rating SELECT OEI CONT after 2.5 min. max. Continue climbing : 4. Engine failed IDENTIFY. 5. Affected engine OFF. LAND AS SOON AS PRACTICABLE 3.3.2 ENGINE FAILURE IN HOVER 3.3.2.1 Hover IGE (or below H/V diagram low point) 1. Collective MAINTAIN 2. Pedals CONTROL YAW 3. Collective INCREASE as needed to cushion touchdown. 6 EASA APPROVED ORIGINAL ISSUEFLIGHT MANUAL eurocopter AS355 NP an EADS Company 3.3.2.2 Hover OGE WARNING SAFE LANDING CAN NOT BE GUARANTED IN CASE OF A FAILURE IN HOGE BELOW THE TOP POINT OF THE HV DIAGRAM (REFER TO SECTION 5) OR IN CONFINED AREA. 1. Collective pitch LOWER, maintain NR > 360 rpm. 2. Cyclic stick NOSE DOWN to -20° attitude to gain airspeed according to available height. Then if single engine climbing performance permits (refer to SECTION 5) : IAS = 40 kt (74 km/h) at height > 50 ft AGL (15 m)could be established YES NO Flight may be continued. LAND IMMEDIATELY Apply continued takeoff Cyclic stick FLARE. or OEI landing procedure As aircraft nears the ground : if terrain surface permits. Cyclic stick REDUCE NOSE UP attitude (FLIGHT MANUAL AS355 NP an eurocopter EADS Company 3.3.3 ENGINE FAILURE IN CRUISE FLIGHT Symptoms: - slight jerk in the yaw axis (the jerk may not be noticed at low power or during approach), - change in the noise level, - FLI needles split, - DIFF PWR + Gong, - ENG P. # GEN.# may light up on failed engine, - OEI MAX appears on FLI, - Low NR audio warning if NR ≤ 360 rpm. Flight may be continued on one engine. 1. Collective pitch LOWER, maintain NR > 375 rpm. 2. OEI rating SELECT OEI CONT 3. Failed engine IDENTIFY. 4. Failed engine OFF. 5. Corresponding [FUEL P] OFF. LAND AS SOON AS PRACTICABLE To obtain maximum fuel range capacity with OEI, fuel tanks crossfeed valve may be opened (refer to SECTION 4). 3.3.4 OEI APPROACH AND LANDING 1. IAS ≥ Vy. 2. OEI rating SELECT OEI MAX 3. Collective pitch CONTROL NR ≥ 375 rpm and ROD ≤ 500 ft/min. At 100 ft AGL (30 m) : 4. IAS REDUCE so as to get 40 kt (74 km/h) at 50 ft (15 m). As aircraft nears the ground : 5. Cyclic stick NOSE UP attitudeFLIGHT MANUAL an eurocopter EADS Company AS355 NP 3.4 IN FLIGHT INTENTIONAL ENGINE SHUTDOWN Depending on engine systems malfunctions or emergency conditions intentional single engine flight may be required. Apply the following procedure for intentional in-flight engine shutdown : 1. Collective pitch SET TRQ ≤ 40 % on each engine. 2. OEI stops selector SELECT OEI CONT 3. Engine # selector TRNG then OFF. 4. [FUEL P. #] OFF. 5. [GEN. #] OFF. If necessary : 6. Electrical consumption REDUCE (refer to SECTION 2). 7. [FUEL XFEED] ON (refer to SECTION 4). 3.5 IN FLIGHT ENGINE RELIGHTING Engine relighting is possible throughout the operating envelope as soon as engine oil temperature is ≥ -30°C. Depending on the type of failure, cause of the flame out or engine shutdown reason, engine restart may be attempted in the whole flight envelope : 1. Engine # selector OFF. 2. [FUEL P. #] CHECK ON. 3. Engine # selector FLT. The relighting sequence will automatically be carried out as soon as N1 ≤ 17%. NOTE When setting the engine selector through TRNG position, a transient hunting of the FLI of the other engine may be observed. EASA APPROVED 9 ORIGINAL ISSUEFLIGHT MANUAL AS355 NP an eurocopter EADS Company 3.6 FUEL FLOW GOVERNOR FAILURES These procedures are related to fuel governor failures not indicated by a warning light. For GOV and/or FADEC #, , refer to Engine Emergencies paragraph 3.12 of this section. Symptoms : - one engine with low FLI setting, - the other engine at medium or high FLI setting. Pilot actions : NR CHECK A NR 395 rpm : failure of the engine at high FLI setting 1. Collective pitch DO NOT REDUCE, try to keep NR 420 rpm if possible. 2. Affected engine IDENTIFY. 3 Affected engine selector OFF. 4 Collective LOWER, control 375 ≤ NR 395 rpm. 5 IAS Set to Vy. 6. In cruise flight OEI procedure APPLY. 10 EASA APPROVED REVISION 3an eurocopter EADS Company FLIGHT MANUAL AS355 NP C 375FLIGHT MANUAL AS355 NP an eurocopter EADS Company 3.7 SMOKE IN THE CABIN 3.7.1 SOURCE IDENTIFIED 1. Affected system OFF. 2. Cabin ventilation OPEN. 3. Front doors windows OPEN. 4. Sliding doors windows OPEN (if fitted). 5. Ventilation nozzles OPEN. 12 EASA APPROVED ORIGINAL ISSUEFLIGHT MANUAL an eurocopter EADS Company AS355 NP 3.7.2 SOURCE NOT IDENTIFIED 1. Heating, Demisting system OFF. 2. Overhead lights ON (night flight). 3. [EMERGENCY CUT OFF] DOWN POSITION. 4. [SHED BUS 1] + [SHED BUS 2] SHED position. 5 [OIL FANS] OFF 6. All switches and pushbuttons OFF except overhead lights, [DCT BAT] and [S/BY HORIZ] (if fitted). 7. [EMERGENCY CUT OFF] UP POSITION. Perform following actions in the prescribed order. Check DC parameters and correct operation of each new function before the next action. 8. [GENE 1] ON. 9. [GENE RST] DEPRESS (if required). 10. [BAT/EPU 1] ON. 11. Essential DC consumers ON one by one (depending on flight conditions). 12. I. GEN CHECK (refer to SECTION 2). 13. [GENE 2] ON. 14. [GENE RST] DEPRESS (if required). 15. [BAT/EPU 2] ON. 16. [OIL FANS] ON. 17. [SHED BUS 1] + [SHED BUS 2] ON. 18. All other DC consumers ON, one by one. When faulty system is identified : Faulty system OFF. NOTE In case electrical consumption is required to be reduced, [OIL FANS] may be kept OFF when IAS ≥ 60 kt (111 km/h). EASA APPROVED REVISION 1FLIGHT MANUAL AS355 NP an eurocopter EADS Company 3.8 TAIL ROTOR MALFUNCTION 3.8.1 TAIL ROTOR DRIVE SHAFT FAILURE Symptoms : The helicopter will yaw to the left. The rate of turn will depend on power applied and airspeed set at the time of the failure. Pilot's actions : In hover or at low speed near the ground : LAND IMMEDIATELY to prevent excessive turn rate. In cruise flight or in OGE hover (outside H/V diagram envelope): 1. Power REDUCE as much as possible. 2. Forward speed MAINTAIN or INCREASE (weathercock effect). 3. Cyclic stick MAINTAIN HEADING (roll control). Select a suitable landing area for a steep approach at a power enabling a reasonably coordinated flight. On final approach : 4. Engines SHUTDOWN. 5. Autorotation procedure APPLY, touchdown at the lowest possible ground speed. 3 14 EASA APPROVED ORIGINAL ISSUEFLIGHT MANUAL eurocopter AS355 NP an EADS Company 3.8.2 TAIL ROTOR CONTROL FAILURE Symptoms : Pedals jamming of or pedals effectiveness loss, inability to change tail rotor thrust with the pedals. CAUTION Landing is made easier by landing with a rh wind component. WARNING BELOW 20 KT AIRSPEED, GO-AROUND IS IMPOSSIBLE DUE TO VERTICAL TAIL FIN EFFICIENCY LOSS. 1. Cyclic and collective ADJUST to set IAS to 70 kt (130 km/h) in level flight. 2. Tail rotor hydraulic OFF (collective grip switch). 3. [ACCU TST] DEPRESS for 5 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. EASA APPROVED 3 15 ORIGINAL ISSUEFLIGHT MANUAL AS355 NP an eurocopter EADS Company 3.9 ICING The first visible indication of icing is the formation of ice deposits on the windscreen wiper. [PITOT] CHECK ON, # PITOT CAUTION Leave icing conditions area as soon as possible. 3.10 AIR DATA INSTRUMENTS FAILURES PITOT / STATIC SYSTEM FAILURE Symptoms : Obviously incorrect or erratic altitude, airspeed or vertical speed indications. Pilot's actions : Should the pilot's air data instruments fail, refer to the indications of stand-by or copilot's instruments if fitted. 1. NORMAL/STD-BY static tap STD-BY. 2. [PITOT] CHECK ON, # PITOT 2. Cabin ventilation OFF. 3. Ventilation nozzles OFF. 4. All windows CLOSED. If failure persists : Power MAINTAIN recommended cruise power or below. LAND AS SOON AS PRACTICABLE 3 - 16 (3 - 17 blank) EASA APPROVED ORIGINAL ISSUEFLIGHT MANUAL an eurocopter EADS Company AS355 NP EASA APPROVED 3-17 ORIGINAL ISSUEFLIGHT MANUAL AS355 NP an eurocopter EADS Company 3.11 VEMD FAILURES AND CAUTION MESSAGES 3.11.1 VEMD SCREEN FAILURES Failure of one screen Failed screen OFF. Read all available parameters on the other screen. Engines and vehicle parameters are available using the [SCROLL] pushbutton either on the VEMD or on the collective pitch lever. Lower screen failure: ENG 00 VEH SCROLL X Upper screen failure: ENG SCROLL VEH Failure of both screens Can be a single failure when [EMERGENCY CUT OFF] or battery pushbuttons + DC generators are in OFF position. In this case, to avoid any power overlimit, the maximum authorized power will be the power needed to establish level flight with the following law : IAS = 100 kt 2 kt / 1000 ft Hp (185 km/h - 4 km/h / 300 m Hp) LAND AS SOON AS Landing procedure : carry out a no hover precautionary landing. 3.11.2 FAILURES/CAUTION MESSAGES 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. 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. 18 EASA APPROVED ORIGINAL ISSUEFLIGHT MANUAL an eurocopter EADS Company AS355 NP LANE 1 (or 2) FAILED Self explanatory. : PRESS OFF 1 (or 2) CROSSTALK FAILED : PRESS OFF 1 (or 2) Self explanatory BRIGHTNESS CONTROL FAILED Screens brightness control failed : (present brightness level frozen). (INTERNAL) CONFIG DIFFERS (Internal) configurations : MAINTENANCE inconsistency lane 1/lane 2. Displayed on both screens: press [OFF1] and [OFF2]. Operate the VEMD in single lane mode: Press [OFF1] or [OFF2] then check parameters consistency. VEH PARAM OUT RANGE : Abnormal vehicle parameter. ENG OUT RNG : Abnormal engine parameter. These messages may appear when a parameter usually displayed on one of the affected page reaches a limitation, as the relevant (vehicle or engine) page is not displayed. - [SCROLL] DEPRESS to reach the relevant page and check parameters. CHECK ENG : Caution message on engine page. Appears when a caution message is displayed on the engine page as the engine page is not displayed. - [SCROLL] DEPRESS to reach engine page and check the caution message. GPS NOT AVAILABLE GPS system not available : (no absolute time reference). - GPS navigation system (if fitted) CHECK ON. If no GPS on board, check VEMD configuration. OVERLIMIT DETECTED : Engine/vehicle overlimit recorded. Appears as soon as one power parameter overlimit has been recorded in the VEMD. It will be displayed on the FLI or engine page until 40% N1 during the starting procedure of the next flight. After the flight, check the recorded overlimit data and perform the associated maintenance actions. For all these messages: CONTINUE FLIGHT EASA APPROVED 3 19 REVISION 2FLIGHT MANUAL AS355 NP an eurocopter EADS Company 3.11.3 CAUTION MESSAGES ON FLI OEI CONT When in AEO mode, the OEI CONT power level is inappropriately pre-selected. Press the OEI stop selector on the collective grip to clear the message and to pre-select OEI MAX in case of an engine failure. CONTINUE FLIGHT ENG FAIL ENG FAIL TRQ 10 TRQ 8 12 124.5 0.0 6 14 Corresponding engine is TOT TOT failed. 4 16 825°C 350 C 2 OEI N1 OEI MAX or OEI CONT MAX N1 MV.55.1100.00 101.8% 2.0% is displayed upon OEI rating stop selected. - Engine failure procedure APPLY, refer to paragraph 3.3 in this section. FADEC FAIL FADEC FAIL TRQ 10 TRQ 12 71.7 Corresponding engine 14 FADEC is failed. TOT TOT 4 16 680 C 471 C If TRQ # 40% ± 2 N1 2 N1 TRQ value appears in a MV.55.1101.00 89.8 56.2 yellow box. - - CWP CHECK FADEC - FADEC # procedure APPLY, refer to paragraph 3.14 in this section. For these two emergencies : LAND AS SOON AS PRACTICABLE 20 EASA APPROVED ORIGINAL ISSUEFLIGHT MANUAL an eurocopter EADS Company AS355 NP FLI # FAIL on one engine : TRQ 10 TRQ 8 12 71.7% 6 14 Loss of three power 4 16 parameters. 2 Failed FLI pointer N1 N1 disappears. MV.55.1096.00 0 93.2% FLI 1 FAIL NOTE An automatic increase of 7 % of the remaining torque provides the possibility to observe the affected engine limitations. FLI # DISC on one engine : FLI # computation discrepancy between VEMD lane 1/lane 2. Failed FLI pointer disappears; digital values of power parameters are still displayed. FLI # DEGR on one engine : TRQ 10 TRQ Loss of one or two 12 71.7% 6 14 power parameters (TRQ, AN1/N1) 4 16 695°C The affected FLI is 2 N1 computed with the N1 MV.55.1095.00 89.7% 0 93.2% remaining FLI 1 DEGR parameter(s). For these failures : CONTINUE FLIGHT Perform a precautionary no-hover landing. EASA APPROVED 21 ORIGINAL ISSUEFLIGHT MANUAL AS355 NP an eurocopter EADS Company FLI # FAIL or FLI # DISC on both engines. TRQ TRQ 71.7% TOT TOT Both failed FLI AN1 pointers disappear. N1 N1 MV.55.1094.00 93.2% FLI 1 FAIL FLI 2 DISC - Two screens failure procedure APPLY, refer to paragraph 3.11 of this section. CHECK N1 / CHECK TRQ / CHECK Significant difference TRQ 10 TRQ 12 between the two engines % 39.2% 14 corresponding TOT TOT 4 parameters: 16 680 C 671 °C N1 2 - diff. N1 ≥ 5 % N1 MV.55.1093.00 89.8 0 87.2% - diff. TRQ ≥ CHECK TRQ - diff. ≥ 80°C. - N1/TRQ/TOT consistency CHECK, align parameters via engine trim if necessary. CORRECT NOT CORRECT - Possible loss of power. Invalid parameter computation. on one engine. CONTINUE FLIGHT CONTINUE FLIGHT - Perform a precautionary no hover landing. 3 - 22 (3 - 23 blank) EASA APPROVED ORIGINAL ISSUEFLIGHT MANUAL an eurocopter EADS Company AS355 NP EASA APPROVED 3 - 23 ORIGINAL ISSUEFLIGHT MANUAL AS355 NP an eurocopter EADS Company 3.12 ENGINE EMERGENCIES 3.12.1 FIRE WARNING CORRECTIVE ACTIONS PANEL IN FLIGHT : FIRE # 1. Power REDUCE. On affected engine : Fire in engine bay 2. Fuel shutoff control lever AFT. 3. Engine # selector OFF. 4. [FUEL P #] OFF. 5. [GEN #] OFF. 6 Heating and air conditioning OFF. 7. CWP MONITOR FIRE # After 1 min : NO YES LAND IMMEDIATELY LAND AS SOON AS PRACTICABLE When fire extinguishers are installed : 7. Eng # WAIT N1 ≤ 50 %. 8. extinguisher SHOOT. 9. CWP MONITOR FIRE # . After 1 min.: NO YES LAND AS SOON AS PRACTICABLE 10. 2ⁿᵈ extinguisher SHOOT. 11. CWP MONITOR FIRE # After 1 min.: NO YES LAND IMMEDIATELY LAND AS SOON AS PRACTICABLE 3 24 EASA APPROVED REVISION 1FLIGHT MANUAL an eurocopter EADS Company AS355 NP WARNING CORRECTIVE ACTIONS PANEL FIRE # ON GROUND, IN HOVER or ON LANDING : (Cont'd) LAND IMMEDIATELY Fire in engine bay. 1. Engines 1 and 2 selectors OFF. 2. [FUEL P 1] + [FUEL P 2] OFF. 3. Fuel shutoff control lever AFT. 4. + 2ⁿᵈ extinguishers (if fitted) SHOOT. When NR 7% 2. Engine parameters MONITOR. and/or 3. Engine Trim CHECK around medium position. TRQ > between both YES NO engines. + 4. Be prepared for possible Eng. Trim Balance engines. Triple "Gong" engine failure. audio warning. LAND AS SOON AS CONTINUE FLIGHT PRACTICABLE EASA APPROVED 3 25 ORIGINAL ISSUEFLIGHT MANUAL AS355 NP eurocopter an EADS Company 3.12.3 ENGINE OIL SYSTEM WARNING CORRECTIVE ACTIONS PANEL ENG P. # 1. Oil pressure CHECK EOP # on VEMD vehicle page. EOP #FLIGHT MANUAL eurocopter AS355 NP an EADS Company VEMD CORRECTIVE ACTIONS ENG OIL # 1. CWP CHECK ENG P.# BAR YES NO MV.55.1098.00 2. FLI CHECK TRQ # 0.6 TRQ reading correct. NO YES 2. ENG P.# 3. CWP MONITOR. procedure. Apply. 4. EOT MONITOR. LAND AS SOON AS CONTINUE FLIGHT PRACTICABLE ENG OIL # 1. Collective pitch REDUCE POWER. °C 2. [OIL FANS] CHECK ON. Upon flight conditions, engine # : 3. Selector OFF. MV.55.1097.00 4. OEI procedure APPLY. 110 LAND AS SOON AS PRACTICABLE During approach : 5. Affected Engine FLT if necessary. EASA APPROVED 27 ORIGINAL ISSUEFLIGHT MANUAL AS355 NP an eurocopter EADS Company 3.12.4 FADEC FAILURES WARNING PANEL CORRECTIVE ACTIONS FADEC # IN CRUISE + 1. CHECK. Engines parameters. 2. Failed engine IDENTIFY corresponding FFCL. on FFCL #. Smooth collective pitch actions. + Maintain TRQ > 0 on not affected engine. FADEC FAIL Upon conditions and if necessary, slowly balance engines and power using the FFCL with . LAND AS SOON AS PRACTICABLE TRQ APPROACH AND LANDING PROCEDURE: Around 500 to 1000 ft (152 to 305 m) above landing site : (if TRQ # 40% ± 2) 1. IAS on VEMD. SET 70 kt (130 km/h) in level flight. 2. FFCL with SET TRQ to 40 % (failed engine). Full FADEC (Yellow box around TRQ value disappears on FLI) failure. 3. Approach SET IAS = 40 kt (74 km/h) with a slow rate of descent to an IGE hover. Corresponding Landing : from the IGE hover fuel flow frozen. 1. Collective pitch LOWER SLOWLY to low pitch. 2. NR MONITOR. On ground or as soon as high NR warning sounds : 3. FFCL with AFT. 4. Apply normal shutdown procedure. 28 EASA APPROVED ORIGINAL ISSUEFLIGHT MANUAL an eurocopter EADS Company AS355 NP WARNING CORRECTIVE ACTIONS PANEL GOV In cruise flight : 1. Both FFCL CHECK in neutral notch. Minor FADEC failure YES NO or FFCL out of 2. Collective pitch Avoid rapid 2. FFCL NEUTRAL. movements. neutral notch. 3. STATUS PAGE DISPLAY to identify affected engine and failure code. FLIGHT GOV Engine starting phase : (Cont'd) During starting phase, is low or nil after engine selector selected to ON. Faulty 1. Corresponding FFCL SLIGHTLY FORWARD. governing : 2. CHECK within limits. limited fuel flow When N1 > 68% : . during starting 3. FFCL BACK to neutral detent. phase. OVSP # Engine stopped or during starting phase : Normal procedure, overspeed protection is not armed for N2 ≤ 100 rpm. N2 overspeed Starting phase, NR > 100 rpm: detection. Overspeed protection system is defective. Abort start-up. In flight: Overspeed protection system is defective or Overspeed protection has been activated on engine #; engine # has been automatically shut down. Apply engine failure procedure, refer to § 3.3 of this section. LAND AS SOON AS PRACTICABLE EASA APPROVED 3 29 ORIGINAL ISSUEFLIGHT MANUAL AS355 NP an eurocopter EADS Company 3.13 TRANSMISSION EMERGENCIES WARNING PANEL CORRECTIVE ACTIONS MGB FIRE LAND IMMEDIATELY Fire in MGB 1. Engines oil temperatures CHECK. compartment. If temperature exceeds 107°C: 2. Engines selectors OFF. 3. Autorotation procedure APPLY. NOTE Fire in MGB may cause engine and MGB oil cooling systems failure. MGB TEMP 1. Collective pitch REDUCE POWER. 2. [OIL FANS] CHECK ON. MGB oil temperature 3. CWP TEST and MONITOR for MGB P ≥ 122°C. 4. IAS SET TO Vy. MGB TEMP MGB TEMP LAND AS SOON AS LAND AS SOON AS POSSIBLE PRACTICABLE 30 EASA APPROVED ORIGINAL ISSUEFLIGHT MANUAL eurocopter AS355 NP an EADS Company WARNING CORRECTIVE ACTIONS PANEL MGB P 1. Collective pitch REDUCE to set TRQ 2 30%. 2. IAS Vy. MGB oil pressureFLIGHT MANUAL AS355 NP an eurocopter EADS Company 3.14 HYDRAULIC EMERGENCIES 3.14.1 CAUTION LIGHTS WARNING PANEL CORRECTIVE ACTIONS HYD # CAUTION Under high load factor, servocontrol reversibility + could be encountered. SERVO Keep aircraft to a more or less level attitude. Avoid abrupt maneuvers. Loss of hydraulic Maintain angle of bank lower than 30°. pressure on Maintain IAS below 110 kt (204 km/h) (or VNE if lower). corresponding Normal approach and landing. circuit. NOTE One remaining circuit allows continued safe flight and landing. LAND AS SOON AS PRACTICABLE HYD 1 HYD 2 LIMIT may be on at Loss of tail rotor control high collective pitch. hydraulic boost. (refer to para. 3.17) CAUTION Do not depress as this would cause the load compensator accumulator to discharge and pedals control loads may become significant. SERVO Main servo unit LAND AS SOON AS PRACTICABLE distributor valve jamming. 32 EASA APPROVED REVISION 1FLIGHT MANUAL eurocopter AS355 NP an EADS Company 3.14.2 YAW CONTROL SERVO-UNIT SLIDE VALVE JAMMED (yaw pedals jamming) In hover: Angular speed Zero. YES NO LAND NORMALLY Hydraulic switch OFF (collective grip switch). LAND AS SOON AS POSSIBLE In cruising flight : IAS Reduce, enter side slip if necessary. Hydraulic switch OFF (collective grip switch). LAND AS SOON AS PRACTICABLE EASA APPROVED 3 33 ORIGINAL ISSUEFLIGHT MANUAL AS355 NP an eurocopter EADS Company 3.15 ELECTRICAL EMERGENCIES 3.15.1 BATTERY FAILURES WARNING PANEL CORRECTIVE ACTIONS BAT TEMP 1. [BAT/EPU 1] + [BAT/EPU 2] OFF. Battery internal BAT TEMP BAT TEMP overheating. LAND AS SOON AS LAND AS SOON AS POSSIBLE PRACTICABLE NOTE Engine restarting impossible. BAT FUSE 1. CWP MONITOR for BAT TEMP Battery isolated 2.V.ESS MONITOR. from DC circuit. CONTINUE FLIGHT BAT.1 1. [BAT/EPU 1] + [BAT/EPU 2] CHECK ON. + BAT.2 CONTINUE FLIGHT Battery off line. BAT.# 1. [BAT/EPU #] CHECK ON. Affected battery contactor open. CONTINUE FLIGHT 3 34 EASA APPROVED ORIGINAL ISSUEFLIGHT MANUAL an eurocopter EADS Company AS355 NP 3.15.2 GENERATORS FAILURES GEN.1 1. [GENE 1] + [GENE 2] CHECK ON. + 2. [GENE RST] DEPRESS. GEN.2 GEN.1 + GEN.2 Both DC generators failure. YES NO CONTINUE FLIGHT 3. [GENE 1] + [GENE 2] OFF. SHED. 5. [OIL FANS] OFF 6. IAS MAINTAIN ≥ 60 kt (111 km/h) LAND AS SOON AS PRACTICABLE Exit IMC conditions as soon as possible if applicable. The battery supplies the main buses. The maximum endurance with a normally charged battery with the minimum required equipments is : - by day : 45 min. - by IFR/ night: 30min. EASA APPROVED 35 ORIGINAL ISSUEFLIGHT MANUAL AS355 NP an eurocopter EADS Company GEN.# 1. [GENE #] CHECK ON. 2. [GENE RST] DEPRESS. Failure of one DC generator. GEN.# YES NO 3. [GENE #] OFF. CONTINUE FLIGHT 4. I. GEN MONITOR. During hoisting mission (as applicable) : Finish present hoisting, abort mission. GEN > I max (refer to SECTION 2) : Unnecessary consumers SHED. CONTINUE FLIGHT NOTE - For Hp > 16000 ft (4880 m) avoid abrupt power increase as transients may occur. - If [OIL FANS] has to be set OFF, maintain IAS ≥ 60 kt (111 km/h). 36 EASA APPROVED ORIGINAL ISSUEFLIGHT MANUAL an eurocopter EADS Company AS355 NP VEMD CORRECTIVE ACTIONS Over voltage on one generator (> 29 V) : V.ESS 1. Affected generator OFF. V 2. CWP MONITOR for BAT TEMP 32.0 3. GEN.# procedure Apply. CONTINUE FLIGHT I.GEN Over intensity on one generator : A 1. Affected generator OFF. 155 2. GEN.# procedure Apply. CONTINUE FLIGHT Over intensity on both generators : I.GEN 1. [BAT/EPU 1] + [BAT/EPU 2] OFF. A 155 159 If over intensity persists on one generator : 2. Affected generator OFF. 3. GEN.# procedure Apply. LAND AS SOON AS PRACTICABLE 3.15.3 DIRECT BATTERY CIRCUIT FAILURE DCT With DC circuit not powered : BAT Direct Battery circuit is on line, switch off if necessary (shutdown procedure) or keep it on when required (Smoke in the cabin procedure). [DCT BAT] lights on With DC circuit normally powered : Direct Battery circuit off line : FADEC computers are only supplied by their own engine alternators. [DCT BAT] CHECK ON. LAND AS SOON AS PRACTICABLE EASA APPROVED 3 37 REVISION 1FLIGHT MANUAL AS355 NP an eurocopter EADS Company 3.15.4 AC SYSTEM* FAILURES WARNING PANEL CORRECTIVE ACTIONS INV. # Single inverter* AC system (VFR version) : [ INV # ] CHECK ON. Inverter failure Affected inverter RESET, if possible. CONTINUE FLIGHT NOTE AFCS* disengages automatically, fly hands on. Dual AC inverter system* (IFR version) : [INV#] CHECK ON. AC voltage CHECK. Affected inverter RESET if possible. CONTINUE FLIGHT NOTE The other inverter takes over and automatically supplies the overall AC circuit. INV. 1 Total AC* power failure. + Flight controls HANDS ON. INV. 2 NOTE AFCS* disengages automatically. LEAVE IMC CONDITIONS AS SOON AS POSSIBLE. * If installed 3 - 38 (3 - 39 blank) EASA APPROVED REVISION 1FLIGHT MANUAL eurocopter AS355 NP an EADS Company EASA APPROVED ORIGINAL ISSUEFLIGHT MANUAL AS355 NP an eurocopter EADS Company 3.16 FUEL SYSTEM EMERGENCIES WARNING PANEL CORRECTIVE ACTIONS FUEL 1. Fuel quantities CHECK. Avoid large pitch attitude changes. Fuel quantity 2. Fuel transfer PERFORM IF NECESSARY. ≤6% in one or two fuel tanks. NOTE Below 20%, the rear tank (RH gauge) tends to empty into the front tank. Level equalizing is obtained with a 4% difference (e.g. front - - 6 % rear). With both tanks at 6 % 18 min. flying time remains in level flight at MCP. When both fuel gauges near zero reading : LAND IMMEDIATELY 1. Collective pitch REDUCE POWER. F.FILT # 2. CWP F.FILT # Pre-clogging of fuel filter #. YES NO CONTINUE FLIGHT Shutdown affected engine. Landing ENG. # on FLT if necessary. F.FILT 1 Heavy fuel system contamination. + 1. Collective pitch REDUCE POWER. F.FILT 2 LAND AS SOON AS POSSIBLE 3 40 EASA APPROVED ORIGINAL ISSUEFLIGHT MANUAL an eurocopter EADS Company AS355 NP VEMD CORRECTIVE ACTIONS 1. [FUEL P #] CHECK ON. FP# YES NO Fuel quantity CHECK [FUEL P #] ON. CONTINUE FLIGHT Fuel quantity CHECK 0.8 BAR CONTINUE FLIGHT EASA APPROVED 3 41 REVISION 3FLIGHT MANUAL AS355 NP an eurocopter EADS Company 3.17 MISCELLANEOUS CAUTION/ADVISORY LIGHTS 3.17.1 PITOTS WARNING PANEL CORRECTIVE ACTIONS P. PITOT For corresponding system : or [PITOT] CHECK ON. A. PITOT * IAS Monitor readings. Pitot heating CONTINUE FLIGHT inoperative. 3.17.2 DOORS DOOR IAS REDUCE to 120 kt (222 km/h) maximum speed. One or two cargo LAND AS SOON AS PRACTICABLE compartment side door(s) not NOTE locked. Land to check doors if possible or continue flight at reduced speed. Keep a low rate of descent, perform a shallow approach. 3.17.3 HORN HORN [HORN] CHECK ON. Audio warning NO YES inoperative. [HORN] ON. Audio warning system defective. CONTINUE FLIGHT (*) If installed 3 42 EASA APPROVED REVISION 3FLIGHT MANUAL an eurocopter EADS Company AS355 NP 3.17.4 TRAINING MODE WARNING CORRECTIVE ACTIONS PANEL TRNG One engine selector on training mode position (TRNG), refer to SUPP 9 - 6 : One engine in - Corresponding engine N2 is governed at 355 rpm (at training mode. zero power). - The "working" engine power (N1, TRQ) is limited to the OEI MAX or OEI CONT training power level. - In case of "working" engine failure, or if NR drops below 355 rpm, training mode will be automatically cancelled, the engine in TRNG mode accelerates and delivers power up to its OEI limits. CONTINUE FLIGHT EASA APPROVED 3 43 REVISION 3FLIGHT MANUAL AS355 NP an eurocopter EADS Company 3.17.5 LIMIT LIMIT During cruise flight or steep maneuvers : Main servo unit 1. Collective pitch REDUCE POWER. max load reached 2. Cyclic REDUCE SPEED or LOAD FACTOR as applicable. or CONTINUE FLIGHT Power limit NOTE reached: LIMIT may appear associated with HYD 1 in case of hydraulic failure (refer to para. 3.14 in this section). AEO: - Ng >Ng MTOP In hover flight : - Torque > 89% 1. FLI - > 779°C. CHECK both FLI, balance engines if necessary. In OEI mode upon OEI 2. Helicopter loading data CHECK. stop selected : OEI MAX selected: During OEI procedures : / - Ng > Ng max OEI 1. FLI MAX CHECK POWER. - Torque > 130.5 % 2. OEI stop CHECK appropriate OEI stop is - TOT > 886°C selected. NOTE Torque limits are to be controlled by the pilot. 3 44 EASA APPROVED REVISION 3FLIGHT MANUAL eurocopter AS355 NP an EADS Company 3.18 NR/N2 INDICATIONS FAILURES 3.18.1 NR INDICATION FAILURE Collective pitch MAINTAIN TRQ 1+ TRQ 2 ≥ NR reading is given by N2 pointers. LAND AS SOON AS PRACTICABLE 3.18.2 N2 INDICATION FAILURE N2 # failure : NR indication CHECK in green range with TRQ CONTINUE FLIGHT EASA APPROVED 3 45 REVISION 3 IFLIGHT MANUAL AS355 NP an eurocopter EADS Company 3.19 VARIOUS WARNINGS, FAILURES AND INCIDENTS 3.19.1 ROTOR BRAKE INOPERATIVE WARNING WAIT FOR FULL ROTOR SHUTDOWN BEFORE LEAVING THE AIRCRAFT. Rotor stopping with wind blowing: 1. Aircraft INTO WIND. 2. Cyclic stick slightly INTO WIND. 3.19.2 ICS INOPERATIVE (GMA 340 H): 1. ICS OFF. 2. COM 1 Check ON, adjust volume. 3. [ICS FAIL]* EMER (on copilot side if dual pilot IFR configuration fitted). NOTE 1 VHF communications will remain available for the RH pilot only via COM 1 transceiver. For dual pilot IFR optional configuration an [ICS FAIL] selector allows pilots intercommunication via COM 1 when set to "EMER" in case of ICS failure. Audio warnings will be transmitted via the COM 1 audio system. NOTE 2 Abort or cancel hoisting operations in case of ICS failure. (*) if installed 46 EASA APPROVED REVISION 3an eurocopter EADS Company FLIGHT MANUAL AS355 NP 3.19.3 COCKPIT LIGHTING FAILURE Overhead panels and console lighting failure [SYST LT] OFF. Overhead panels and console will be supplied by the [INST LT] circuit. Overall brightness will then be adjusted by the pilot instrument panel lighting potentiometer. Pilot's instruments lighting failure [INST LT] OFF. Instrument panel will be supplied by the [SYST LT] circuit. Overall brightness will then be adjusted by the console lighting potentiometer. Full cockpit lighting failure Unlikely but could be a single failure in case of DC power shedding (Smoke in cabin procedure). Cockpit dome lights ON. EASA APPROVED REVISION 3