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Eads eurocopter AS 365 N3 Flight Manual

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Summary of Contents for Eads eurocopter AS 365 N3

  • Page 3 REVISION TO AIRCRAFT PUBLICATION : AS 365 N3 PUBLICATION CONCERNED : COMPLEMENTARY FLIGHT MANUAL –Vol 2 APPENDIX.9.1 DATE CERTIFICATION REVISION No.: 11-42 PC2DLE CODE: CODE: - The outline of the revision is given below : . Sections or supplements affected (added or modified), .
  • Page 11 COMPLEMENTARY FLIGHT MANUAL COMPOSITION OF RUSH REVISIONS (RR) The Manual contains the following additional yellow page(s): DATE DATE SECTION PAGE SECTION PAGE CODE CODE 0.0.P4 1/01*RR* 12-05 R 9.0.P6 1 *RR* 11-20 9.30 1 *RR* 11-20 2 *RR* 12-05 R 32 *RR* 12-05 R 33 *RR*...
  • Page 15 COMPLEMENTARY FLIGHT MANUAL LIST OF EFFECTIVE PAGES (1) Page Revision Code − R : Revised, to be replaced − N : New, to be inserted SECTION PAGE DATE (1) SECTION PAGE DATE (1) 0. 0 02-48 7. 1 02-48 0. 0 02-48 7.
  • Page 16 COMPLEMENTARY FLIGHT MANUAL SECTION PAGE DATE (1) SECTION PAGE DATE (1) 7. 8 06-18 7. 13 10-40 7. 8 02-48 7. 13 10-40 7. 8 02-48 7. 13 10-40 7. 8 02-48 7. 13 10-40 7. 8 02-48 7. 13 10-40 7.
  • Page 17 COMPLEMENTARY FLIGHT MANUAL SECTION PAGE DATE (1) SECTION PAGE DATE (1) 8. 3 06-18 9. 22 02-48 8. 3 06-18 9. 23 06-18 8. 3 06-18 9. 23 02-48 8. 3 06-18 9. 25 02-48 8. 3 06-18 9. 25 04-10 8.
  • Page 18 COMPLEMENTARY FLIGHT MANUAL SECTION PAGE DATE (1) SECTION PAGE DATE (1) 9. 73 02-48 10. 2 02-48 9. 80 07-50 10. 2 02-48 9. 80 07-50 10. 2 02-48 10. 0 10-40 10. 2 02-48 10. 1 04-10 10. 2 02-48 10.
  • Page 19 COMPLEMENTARY FLIGHT MANUAL LIST OF MODIFICATIONS MENTIONED IN THE FLIGHT MANUAL This list includes all modifications that are or have been referenced to in the Flight Manual, except TUBOMECA modifications. Modification SUBJECT 07-79B32 Engine chip burning system 07-34C41 MFD 255 STEP 1' 07-71C38 "DIFF NG"...

  • Page 21: Table Of Contents

    COMPLEMENTARY FLIGHT MANUAL SECTION 6 WEIGHT AND BALANCE CONTENTS GENERAL - DEFINITIONS Pages 1. WEIGHTS - CONVENTIONAL TERMS ............1 2. CENTER OF GRAVITY - CONVENTIONAL TERMS ........2 3. WEIGHING .....................3 4. CALCULATING LONGITUDINAL CG LOCATION..........6 LONGITUDINAL LOCATION OF VARIABLE LOADS 1.

  • Page 25: Weighing

    COMPLEMENTARY FLIGHT MANUAL 3 WEIGHING Weighing is the only reliable way of obtaining: • Equipped empty weight (EEW). • Aircraft center of gravity (C.G.) location. The aircraft must be weighed: • On leaving the works. • Following any major modification. 3.1 PRELIMINARY STEPS •...
  • Page 26 COMPLEMENTARY FLIGHT MANUAL AS 365 N3 10-40 Page 4...
  • Page 27 COMPLEMENTARY FLIGHT MANUAL INVENTORY AT TIME OF AIRCRAFT WEIGHING MISCELLANEOUS RADIO COMMUNICATION RADIO NAVIGATION Aircraft tool kit ........AVIONICS First aid kit ......... Flight Manual ........VHF/AM ..........Fire extinguisher ........ UHF/AM ..........Engine access ladder ......V/UHF ..........Storage net ........VHF/UHF/AM ........

  • Page 28: Calculating Longitudinal Cg Location

    COMPLEMENTARY FLIGHT MANUAL 4 CALCULATING LONGITUDINAL C.G. LOCATION 4.1 METHOD The distance from the center of gravity of the aircraft to the datum plane is found by means of the following formula: Sum of moments = C.G. location Sum of weights •...

  • Page 29: Longitudinal Location Of Variable Loads

    COMPLEMENTARY FLIGHT MANUAL SECTION 6.2 LONGITUDINAL LOCATION OF VARIABLE LOADS 1 CREW METRIC SYSTEM ANGLO-SAXON SYSTEM CREW WEIGHT MOMENT CREW WEIGHT MOMENT (kg) (m.kg) (lb) (in.lb) 17848 19400 20952 22504 24056 25608 27160 28712 30264 AS 365 N3 02-48 Page 1...

  • Page 30: Passengers

    COMPLEMENTARY FLIGHT MANUAL 2 PASSENGERS 2.1 8-SEAT COMFORT LAYOUT NOTE The 4 front seats may be fitted rearward or forward facing METRIC SYSTEM ANGLO-SAXON SYSTEM MOMENT (m.kg) PASSENGERS PASSENGERS MOMENT (in.lb) WEIGHT (kg) WEIGHT (lb) 16890 22440 20268 26928 22520 29920 24772 32912...
  • Page 31 COMPLEMENTARY FLIGHT MANUAL 2.2 11-SEAT LAYOUT METRIC SYSTEM ANGLO-SAXON SYSTEM WEIGHT MOMENT (m.kg) WEIGHT MOMENT (in.lb) (kg) (lb) 16890 21495 25695 25980 20268 25794 30834 31176 22520 28660 34260 34640 24772 31526 37686 38104 29276 37258 44538 45032 33780 42990 51390 51960 39410...
  • Page 32 COMPLEMENTARY FLIGHT MANUAL 2.3 12-SEAT LAYOUT METRIC SYSTEM ANGLO-SAXON SYSTEM WEIGHT MOMENT (m.kg) WEIGHT MOMENT (in.lb) (kg) (lb) 16890 21495 25695 25980 20268 25794 30834 31176 22520 28660 34260 34640 24772 31526 37686 38104 29276 37258 44538 45032 33780 42990 51390 51960 39410...

  • Page 39: Weight And Moment Of Equipment Items

    COMPLEMENTARY FLIGHT MANUAL 8 WEIGHT AND MOMENT OF EQUIPMENT ITEMS The following list covers the optional equipment items. It gives the approximate weight and moment of the removable components. WEIGHT MOMENT EQUIPMENT (kg) (lb) (m.kg) (in.lb) HOIST COMPLETE WITH ARM 65.45 144.29 239.54...
  • Page 40 COMPLEMENTARY FLIGHT MANUAL WEIGHT MOMENT EQUIPMENT (kg) (lb) (m.kg) (in.lb) MEDEVAC INSTALLATION WITHOUT 9.78 21.56 50.890 4416.9 STRETCHERS (Stowing position) - Straps, upper right stretcher hook 1.88 4.14 10.509 912.1 - Straps, upper left stretcher hook 1.88 4.14 10.509 912.1 - Straps for lower right stretcher 1.12 2.47...
  • Page 41 COMPLEMENTARY FLIGHT MANUAL WEIGHT MOMENT EQUIPMENT (kg) (lb) (m.kg) (in.lb) LOCATOR 11.06 24.38 40.34 3500 - Light and attachments 9.58 21.12 36.02 3126 - Support and attachments 0.46 1.01 1.73 - Cable loom 0.37 0.82 1.43 - Control grip 0.65 1.43 1.16 BLIND FLYING SCREENS...
  • Page 42 COMPLEMENTARY FLIGHT MANUAL WEIGHT MOMENT EQUIPMENT (kg) (lb) (m.kg) (in.lb) 8 STANDARD SEAT 32.00 70.55 109.788 9529.2 - Two-place seat: Front. LH 8.30 18.30 24.402 2118.0 • Front. RH 8.30 18.30 24.402 2118.0 • Aft. LH 7.70 16.98 30.492 2646.6 •...
  • Page 43 COMPLEMENTARY FLIGHT MANUAL PAGE INTENTIONNALY LEFT BLANK AS 365 N3 10-40 Page 15...

  • Page 44: Loading Charts

    COMPLEMENTARY FLIGHT MANUAL LOADING CHARTS The following charts (metric and anglo-saxon units) are used to easily determine the aircraft center of gravity. When the point obtained is close to the limits, it should be confirmed by calculations. Example: Item on chart - The weighting operation locates the CG at 4.07 m (160.23 in) for an EEW of 2500 kg (5511.55 lb) - 2 front seats used...
  • Page 45 COMPLEMENTARY FLIGHT MANUAL AS 365 N3 10-40 Page 17...
  • Page 46 COMPLEMENTARY FLIGHT MANUAL AS 365 N3 10-40 Page 18...

  • Page 49: Passengers

    COMPLEMENTARY FLIGHT MANUAL 2.2 12-SEAT LAYOUT METRIC SYSTEM ANGLO-SAXON SYSTEM MOMENT (m.kg) PASSENGERS PASSENGERS MOMENT (in.lb) WEIGHT (kg) WEIGHT (lb) 1378 3224 1590 3720 1802 4216 2014 4712 2120 4960 AS 365 N3 09-23 Page 3...

  • Page 50: Transport Of Hoisted Loads

    COMPLEMENTARY FLIGHT MANUAL 3 TRANSPORT OF HOISTED LOADS METRIC SYSTEM ANGLO-SAXON SYSTEM WEIGHT (kg) MOMENT (m.kg) WEIGHT (lb) MOMENT (in.lb) 7163 8265 9367 10469 11571 12673 13775 14877 15979 17081 18183 19285 20387 21489 22591 23693 24795 25897 26999 28101 29203 30305 31407...
  • Page 53 COMPLEMENTARY FLIGHT MANUAL SECTION 7 DESCRIPTION AND SYSTEMS CONTENTS 7.1 MAIN DIMENSIONS - OVERALL DIMENSIONS 7.2 COCKPIT 7.3 POWER PLANT 7.4 FUEL SYSTEM 7.5 ROTORS AND TRANSMISSION ASSEMBLIES 7.6 FLIGHT CONTROLS 7.7 HYDRAULIC POWER SYSTEMS 7.8 ELECTRIC POWER SYSTEMS 7.9 AIR DATA SYSTEM 7.10 VENTILATION, HEATING AND DEMISTING 7.11 LIGHTING 7.12 AUTOPILOT SYSTEMS (AFCS)
  • Page 55 COMPLEMENTARY FLIGHT MANUAL SECTION 7.1 MAIN DIMENSIONS - OVERALL DIMENSIONS 1 MAIN AIRCRAFT DIMENSIONS AS 365 N3 09-23 Page 1...
  • Page 56 COMPLEMENTARY FLIGHT MANUAL 2 DOOR AND COMPARTMENT DIMENSIONS AS 365 N3 02-48 Page 2...
  • Page 61 COMPLEMENTARY FLIGHT MANUAL SECTION 7.3 POWER PLANT 1 DESCRIPTION 1.1 INSTALLATION The 365 N3 is powered by 2 ARRIEL 2C turbo shaft engines installed side by side behind the MGB. The engines are located in two insulated fire-proof bays. The two air intakes located forward of the MGB take advantage of the ram air pressure in forward flight.
  • Page 62 COMPLEMENTARY FLIGHT MANUAL 3 TORQUEMETER The sensors are torsion bar type. The signals are sent to the engine control units which convert them into digital signals. 4 GOVERNING The digital electronic governing essentially provides the following functions: • suction and filtering of fuel, •...
  • Page 65 COMPLEMENTARY FLIGHT MANUAL A diff. Ng ( Ng) indicator per engine, incorporating: - a scale graduated from - 8% to + 6%, which shows the Ng limit, - a LED indicating when the bleed valve is open, - a digital Ng display, - a "TEST"...
  • Page 66 COMPLEMENTARY FLIGHT MANUAL Amber caution lights : : Detection of metallic particles on the CHIP.1 CHIP.2 corresponding engine. : Minor governing failure. : "Training" mode engaged. NOTE Whenever a red warning lights up on the Caution Advisory Panel, lights are activated on the instrument panel. ALARM ALARM 6.5 "GONG"...
  • Page 67 COMPLEMENTARY FLIGHT MANUAL SECTION 7.4 FUEL SYSTEM 1 FUEL TANKS 1.1 DESCRIPTION Figure 1 - Fuel tank layout 1.1.1 Standard tanks The fuel is distributed into two independent groups of tanks with a total capacity of 1158 liters (915 kg). AS 365 N3 02-48 Page 1...
  • Page 68 COMPLEMENTARY FLIGHT MANUAL 1.2 TANK CAPACITY 1.2.1 Standard tanks TOTAL CAPACITY UNUSABLE CAPACITY Liters Kg * US.Gal Liters Kg * US.Gal LH GROUP ▪ LH center ▪ LH front ▪ RH front RH GROUP ▪ RH center ..
  • Page 69 COMPLEMENTARY FLIGHT MANUAL Figure 2 - Fuel system 1. Fuel shut-off control lever 7. Fuel transfer pump 2. Pressure transmitter 8. Jet pumps 3. Fuel low pressure switch 9. Booster pumps 4. Pre-clogging indicator light 10. Feeder-tank valve 5. Fuel transfer indicator light 11.
  • Page 70 COMPLEMENTARY FLIGHT MANUAL 3 CONTROLS AND INDICATORS 3.1 CONTROL QUADRANT One fuel shut-off control lever per engine closes the valve fitted on the engine fuel supply line. 3.2 CAUTION ADVISORY PANEL light repeats the light on fuel FUEL.Q FUEL.Q management panel. FUEL FILT FUEL P...
  • Page 71 COMPLEMENTARY FLIGHT MANUAL Figure 4 - Fuel contents indicator 3.4 FUEL MANAGEMENT PANEL ON CONSOLE • For each tank group : FUEL.Q : drop in the feeder tank level FILT : incipient filter clogging. FUEL P : drop in system fuel pressure. Two ”PUMP“...
  • Page 72 COMPLEMENTARY FLIGHT MANUAL Figure 5 - Fuel management panel AS 365 N3 10-40 Page 6...
  • Page 77 COMPLEMENTARY FLIGHT MANUAL SECTION 7.6 FLIGHT CONTROLS 1 GENERAL The flight controls comprise: • two cyclic pitch control sticks controlling the inclination of the swashplates, • two collective pitch levers controlling the vertical displacement of the swashplates, • two pairs of pedals controlling the angle of attack of the fenestron blades. The pedals also feature assisted differential brakes acting on the main landing gear wheels, •...
  • Page 78 COMPLEMENTARY FLIGHT MANUAL 3 CONTROLS ON COLLECTIVE PITCH LEVER GRIP The ramp of the collective pitch lever is fitted with a friction locking device. AS 365 N3 07-50 Page 2...
  • Page 89 COMPLEMENTARY FLIGHT MANUAL 6.3 EMERGENCY HYDRAULIC SYSTEM 6.3.1 Warning Light (red) : Allows the operation of the emergency system to be L/G.PUMP checked. REMINDER lights illuminate whenever a Caution Advisory ALARM ALARM Panel red light comes on. 6.3.2 Indicators The pressure of the accumulator can be checked by means of a pressure indicator on the RH side of the cabin floor.
  • Page 90 COMPLEMENTARY FLIGHT MANUAL 6.3.4 On-ground check of emergency system In the recess of the electrical ground power receptacles, a pushbutton and a warning light make it possible to check the emergency system and the repressurization of the accumulators. This check also illuminates the L/G.PUMP light on the Caution Advisory Panel.
  • Page 91 COMPLEMENTARY FLIGHT MANUAL 7 POWER BRAKES 7.1 GENERAL To reduce the loads required for applying the wheel brakes and parking brake, the system (fig.6) incorporates a hydraulic assistance ensured by: • four transmitters connected to the yaw pedals, • one braking relay installed under the cabin floor, on pilot side, •...
  • Page 92 COMPLEMENTARY FLIGHT MANUAL 7.2 OPERATION Any action on the transmitter of one of the control pedals displaces one of the braking relay pistons, thus pressurizing the corresponding braking circuit. The accumulator can be charged either automatically through the auxiliary hydraulic system, or through the electric pump of the emergency system controlled by the pilot.
  • Page 127 COMPLEMENTARY FLIGHT MANUAL 6.1.2 Annunciator panel Engagement of a mode is indicated by the illumination of the corresponding caption light on the Control unit and of the relevant annunciator. Figure 7 - Indication of the modes engaged For “V/L” and “G/S” modes, the annunciators are combined with amber warning lights which indicate excessive deviations.
  • Page 128 COMPLEMENTARY FLIGHT MANUAL 7 OPERATION OF THE FLIGHT DIRECTOR COUPLER To use the flight director ..........press “F/D” To use the coupler ............press “CPL” Engagement or disengagement of a function is obtained by depressing the corresponding pushbutton on the control panel (fig.6), except “G/A” mode on the collective lever grip (fig.8).
  • Page 135 COMPLEMENTARY FLIGHT MANUAL SECTION 7.13 DIGITAL AUTOPILOT APM 2010 1 GENERAL The autopilot provides automatic flight control in four axes of helicopter control and is operated in basic and upper modes. 1.1 DESCRIPTION OF THE INSTALLATION The AP includes the following components: −...
  • Page 136 COMPLEMENTARY FLIGHT MANUAL 1.2 OVERALL SYSTEM ARCHITECTURE Figure 1: Auto Pilot general block diagram. AS 365 N3 7.13 10-40 Page 2...
  • Page 137 COMPLEMENTARY FLIGHT MANUAL 1.3 COMMANDS 1.3.1 APMS Figure 2: APMS “AP” Push-button Engages and disengages the automatic pilot. AP disengaged AP engaged “A-TRIM” push-buttons Engage and disengage the yaw and cyclic auto-trim functions. Auto-trim disengaged Auto-trim engaged “TEST” push-button Engages the AP Pre-flight test. Flashing during the test “ALTA”...
  • Page 138 COMPLEMENTARY FLIGHT MANUAL “VNAV” push-button Engages and disengages the Vertical Navigation Not operational mode. mode armed mode captured. “CR.HT” knob Offers the possibility of adjusting a flying height. Press this knob and the CRUISE HEIGHT mode engages. The green engagement indicator light for this function comes on.
  • Page 139 COMPLEMENTARY FLIGHT MANUAL 1.3.2 Flight control sticks COLLECTIVE BEEP TRIM GSTC/SAS Engage/Disengage AFCS or SAS OFF CYCLIC BEEP TRIM TRIM RELEASE GO AROUND CPL REL COLLECTIVE RELEASE CYCLIC STICK COLLECTIVE PITCH Figure 3: Cyclic and collective GSTC/SAS push-button. One press allows the engagement/disengagement of GSPD mode when AP is on.
  • Page 140 COMPLEMENTARY FLIGHT MANUAL 1.3.3 Overhead panel controls Figure 4: Overhead panel controls 1.3.4 SAR modes control Figure 5: Hover drift control box hover sensor and radio altimeters reconfiguration box - A pilot hover drift control box, for adjustment of lateral and longitudinal ground speed references.
  • Page 141 COMPLEMENTARY FLIGHT MANUAL 1.4 ANNUNCIATION 1.4.1 AFCS strip of the MFD Color Code - No display is the nominal for attitude hold - Green display is the nominal for upper modes engaged or captured. - White under lining indicates a change in an active reference. - Blue display is dedicated to armed upper modes.
  • Page 142 COMPLEMENTARY FLIGHT MANUAL 1.4.4 Armed modes Collective Axis (A2) Roll/Yaw Axes (B2) Pitch Axis (C2) ALT.A ALT.A (*) SAR option 1.5 SYMBOLOGY MFD Display Mode Box is displayed for 10 s and then disappears New mode engaged – – – –...
  • Page 143 COMPLEMENTARY FLIGHT MANUAL 1.5 WARNINGS AND CAUTIONS MFD Display Definition AP/display data transmission fault. Reduce usual confidence displayed information (upper mode can only be disengaged) Coupling degraded or failed ▲ Collective axis trim fault. Move the control position down or up for manual recentering ▼...
  • Page 144 COMPLEMENTARY FLIGHT MANUAL 2 OPERATING MODES 2.1 BASIC STABILIZATION By default, the AP performs an attitude retention on pitch and roll axes and either heading hold or turn coordination on yaw axis. The natural cross coupling existing between the helicopter axes are automatically corrected.
  • Page 145 COMPLEMENTARY FLIGHT MANUAL 2.2 LATERAL UPPER MODES 2.2.1 General - For all lateral modes (NAV, VOR, LOC) engagement is inhibited below 35 kt. - For HDG, engagement is inhibited below 26 kt. - For all lateral modes, engagement is inhibited when aircraft is on ground. 2.2.2 Heading select (HDG) The HDG mode maintains the current heading upon engagement or acquires and holds a pre-selected heading.
  • Page 146 COMPLEMENTARY FLIGHT MANUAL a) Armament/disarmament On ND display once the navigation source is set to the VOR/ILS whatever VOR1/ILS1 or VOR2/ILS2 receptor is selected and tuned to the frequency of the relevant beacon, the mode is armed/disarmed by pressing the “NAV” pushbutton on APMS if the capture conditions are not satisfied: - iVORi, iVOR...
  • Page 147 COMPLEMENTARY FLIGHT MANUAL 2.2.4 Navigation mode (NAV) The NAV mode enables the helicopter to follow a selected path issued from a navigation computer. On ND display, once the navigation source is set to the "FMS" position, the mode is engaged/disengaged by pressing the “NAV” pushbutton on APMS: - iNAVi label is displayed on AFCS strip.
  • Page 148 COMPLEMENTARY FLIGHT MANUAL NOTE 1 For low angles of interception (lower than 25 degrees), capture condition is 1 dot. However a maximum time of 30 s is introduced when the mode is armed and the deviation below 2.1 dots to capture the localizer even if the deviation still exceeds 1 dot.
  • Page 149 COMPLEMENTARY FLIGHT MANUAL b) Engagement/disengagement On ND display once the navigation source is set to the VOR/ILS whatever VOR1/ILS1 or VOR2/ILS2 receptor is selected and tuned to the frequency of the relevant beacon, the mode is engaged/disengaged by pressing the “NAV”...
  • Page 150 COMPLEMENTARY FLIGHT MANUAL 2.3 VERTICAL AND LONGITUDINAL UPPER MODES 2.3.1 General - In three axes coupled mode (ALT or VS): . In case of insufficient collective pitch to meet the vertical mode reference, helicopter speed decreases and should 60 kt being crossed IAS mode will self-engage shifting the vertical mode to the collective axis.
  • Page 151 COMPLEMENTARY FLIGHT MANUAL 2.3.2 Altitude hold (ALT) The ALT mode maintains the current barometric altitude upon engagement. - below 60 kt the altitude is controlled through collective axis, however the mode shifts to the pitch axis if the airspeed exceeds 65 kt for at least 5 s. - above 60 kt, the altitude is controlled through cyclic axis (3 axes operation), or through collective axis when IAS is engaged (4 axes operation),...
  • Page 152 COMPLEMENTARY FLIGHT MANUAL Conditions that inhibit the ALT mode engagement: - aircraft on ground, - airspeed below 55 kt if the collective trim is unavailable, - anomaly detected by the monitoring of the data sent to the FDS for display to the pilot but ground proximity level-off activation. It is signaled by three amber lines across the AFCS strip.
  • Page 153 COMPLEMENTARY FLIGHT MANUAL 2.3.4 Altitude acquisition mode (ALT.A) The ALT.A mode acquires and holds a pre-selected altitude. Turning ALT.A rotary knob on APMS presets a reference altitude (step = 100 ft above 5000 ft and 50 ft below). Pressing ALT.A rotary knob on APMS results first in selection of VS mode (climb or descent) with a default vertical speed according to table below or current VS if higher until the difference between actual altitude and reference altitude becomes lower than 300 ft.
  • Page 154 COMPLEMENTARY FLIGHT MANUAL 2.3.5 Glide slope mode (G/S) The GS mode acquires and holds the selected glide slope in order to make an ILS approach to an airport. When approaching the ground the AP automatically reverts to ALT mode in order to hold an altitude corresponding to a radio height of 80 ft.
  • Page 155 COMPLEMENTARY FLIGHT MANUAL b) Engagement/disengagement On ND display once the navigation source is set to the VOR/ILS whatever VOR/ILS 1 or VOR/ILS 2 receptor is selected and tuned to the frequency of the relevant beacon the mode is engaged by pressing the “NAV” pushbutton on APMS if the capture conditions are satisfied.
  • Page 156 COMPLEMENTARY FLIGHT MANUAL 2.3.6 Indicated airspeed (IAS) The IAS mode maintains the current indicated airspeed upon engagement or acquires and holds a pre-selected indicated airspeed. Adjustment of IAS reference is obtained through the cyclic beep trim. - When approaching the ground ALT mode is automatically engaged in order to hold an altitude corresponding to a radio height of 150 ft.
  • Page 157 COMPLEMENTARY FLIGHT MANUAL 2.3.7 Go around (GA) The GA mode used in case of a missed approach or an automatic departure from the hover acquires and holds a pre-defined vertical speed of 1 000 ft/min or the current vertical speed (whichever is the highest) and Vy or the current airspeed (whichever is the highest).
  • Page 158 COMPLEMENTARY FLIGHT MANUAL 2.3.8 Capture and retention of radar height mode (CR.HT) The CR.HT mode acquires and holds a pre-selected radio height. Turning CR.HT rotary knob on APMS presets a reference height (step = 10 ft). - The reference height can be adjusted either by the rotary knob on APMS or by the trim located on collective stick.
  • Page 159 COMPLEMENTARY FLIGHT MANUAL 2.4.1 Hover height hold mode (HT/HOV) The HT/HOV mode acquires and holds a pre-selected hover height (i.e. HHT) and pre-selected ground speed reference (i.e. HOV) set by pilot/hoist's operator thumb-wheels. This mode also coordinates the descent and deceleration along a 4.5 degrees slope in case of engagement away from 3D hover references also named autonomous transition down.
  • Page 160 COMPLEMENTARY FLIGHT MANUAL Reference management: HHT: The HHT reference is permanently selectable/modifiable via "HT/HOV" APMS rotary knob unless a problem has been identified in the visualization feedback to the pilot. Once the mode is engaged to give more comfort of use provided no inhibition condition has been detected and the hover is established the collective beep can be used in order to modify this reference at beep rate of 150 ft/min.
  • Page 161 COMPLEMENTARY FLIGHT MANUAL 2.4.2 Ground speed mode (GSPD) The GSPD mode acquires zero ground speed upon engagement but allows synchronization on current ground speed (cyclic trim release) and acceleration (beep). When combined with HHT and engaged away from 3D hover this mode also coordinates the descent and deceleration along a 4.5 deg slope.
  • Page 162 COMPLEMENTARY FLIGHT MANUAL 2.4.3 Guided transition down (TDN) This transition down mode is guided via the FMS with several hover point designation possibilities: - Using “F/TDN” (Fix and TransDown) pushbutton on APMS when flying over the target. This action automatically configures both the AP and FMS to run the complete procedure: .
  • Page 163 COMPLEMENTARY FLIGHT MANUAL - complete loss of ground speed for at least 30 s, - reset of engagement signal from FMS for at least 10 s, - navigation source selection different from FMS selection for at least 30 s. Condition that inhibits the TDN mode engagement: - Aircraft on ground.
  • Page 165 COMPLEMENTARY FLIGHT MANUAL SECTION 8 SERVICING CONTENTS HANDLING Pages 1. TOWING......................1 MAINTENANCE DATA 1. COMMERCIAL DESIGNATION OF FUELS, LUBRICANTS AND HYDRAULIC FLUIDS .............1 2. FUEL ADDITIVES...................3 3. REFUELING ....................5 4. REFUELING WITH ROTOR TURNING, AIRCRAFT ON THE GROUND..5 TEST SCHEDULE 1.

  • Page 167: Handling

    COMPLEMENTARY FLIGHT MANUAL SECTION 8.1 HANDLING 1 TOWING 1.1 GENERAL Towing with the towing bar allows the aircraft to be moved on grounds of the same nature and condition as those on which it can normally move by its own means. The towing bar is fitted with a shear pin (ultimate load 1000 ±...
  • Page 168 COMPLEMENTARY FLIGHT MANUAL 1.3 HANDLING THE AIRCRAFT NOTE Have an assistant in the cockpit: - to apply the parking brake - to actuate the nose wheel alignment lock control (if necessary). • Install the towing bar on the bobbins fitted on the nose landing gear shaft. •...

  • Page 173: Refueling

    COMPLEMENTARY FLIGHT MANUAL 3 REFUELING • Place the helicopter on a level surface. • Connect the bower earthing cable to the electro-static balance connector on the helicopter. • Check, on the fuel gauges, the quantity of fuel remaining in the tanks. •...

  • Page 177: Test Sheets

    RR8B COMPLEMENTARY FLIGHT MANUAL 2 TEST SHEETS AS 365 N3 12-05 Page 2 *RR*...
  • Page 181 COMPLEMENTARY FLIGHT MANUAL AS 365 N3 02-48 Page 5...
  • Page 182 COMPLEMENTARY FLIGHT MANUAL AS 365 N3 10-04 Page 6...
  • Page 183 COMPLEMENTARY FLIGHT MANUAL AS 365 N3 06-18 Page 7...
  • Page 184 COMPLEMENTARY FLIGHT MANUAL AS 365 N3 07-50 Page 8...
  • Page 185 COMPLEMENTARY FLIGHT MANUAL AS 365 N3 07-50 Page 9...
  • Page 186 COMPLEMENTARY FLIGHT MANUAL AS 365 N3 06-18 Page 10...
  • Page 209 RR8B COMPLEMENTARY FLIGHT MANUAL AS 365 N3 12-05 Page 32 *RR*...
  • Page 212 RR8B COMPLEMENTARY FLIGHT MANUAL AS 365 N3 12-05 Page 33 *RR*...

  • Page 239: Maintenance Aid System

    COMPLEMENTARY FLIGHT MANUAL SECTION 8.5 MAINTENANCE AID SYSTEM 1 GENERAL Alphanumeric indicators provide information on the engines (failures, control unit condition, values recorded by sensors). The system essentially consists of the following items: • failure annunciator unit, located in the hold, •...

  • Page 240: Procedure

    COMPLEMENTARY FLIGHT MANUAL 2 PROCEDURE The rotary switch is used to display the various modes required on the indicators: 2.1 “PRMTR” MODE (PARAMETER) The pushbutton is used to select a parameter by its alphabetical code. The code is displayed in the LH digit. The value of the parameter is displayed in the remaining four digits to the right.
  • Page 247 FLIGHT MANUAL FLIGHT MANUAL APPENDIX AS 365 N3 PROCEDURE GUIDE FOR OFFSHORE OR ASSIMILATED ELEVATED HELIDECK - PC2 DLE IMPORTANTE NOTE The effectivity of the appendix at the latest revision is specified on the List of Effective Pages. E U R O C O P T E R D i r e c t i o n T e c h n i q u e S u p p o r t Aéroport international Marseille-Provence 13725 Marignane Cedex - France AS 365 N3...
  • Page 249 COMPLEMENTARY FLIGHT MANUAL LIST OF EFFECTIVE PAGES (1) AIRWORTHINESS EFFECTIVITY:  Without indication....Applicable to all aircraft.  Indicated ......Specific to indicated civilian Airworthiness Authority. (2) VARIANT OF STANDARD DEFINITION EFFECTIVITY:  Without indication....Applicable to all aircraft.  XXX........Specific to aircraft equipped with XXX. (3) GROUP OF AIRCRAFT EFFECTIVITY: ...
  • Page 250 COMPLEMENTARY FLIGHT MANUAL DATE APPENDIX PAGES CODE APP.9.1 11-42 APP.9.1 11-42 APP.9.1 11-42 APP.9.1 11-42 APP.9.1 11-42 APP.9.1 11-42 LOG OF NORMAL REVISIONS BASIC RFM REVISIONS - EFFECTIVITY (1) (2) NORMAL REVISION 0 DATE CODE 11-42 Title Creation of the Appendix dealing with PC2 DLE performance. Revised information Deleted...
  • Page 251 COMPLEMENTARY FLIGHT MANUAL APPENDIX 9.1 PROCEDURE GUIDE FOR OFFSHORE OR ASSIMILATED ELEVATED HELIDECK - PC2 DLE 1 GENERAL This section provides additional procedure and performance: PC2 DLE (PC2 Defined Limited Exposure) in order to operate over OFFSHORE or assimilated elevated helideck environment.
  • Page 252 COMPLEMENTARY FLIGHT MANUAL 1.1 DEFINITIONS ITEM DEFINITION CAT. A CAT.A performance: climb at VTOSS, OEI 2 min from 35 ft to 200 ft. segment CAT. A CAT.A performance: climb at Vy, OEI CONTINUOUS from 200 ft to segment 1000 ft. Committal Point.
  • Page 253 COMPLEMENTARY FLIGHT MANUAL 2 OPERATING FLIGHT ENVELOPE LIMITS The performance given in this appendix is only applicable within the following operative flight envelope: • - 1000 ft ≤ Hp ≤ + 1000 ft • ISA - 10 ≤ OAT ≤ ISA + 30 NOTE For ISA - 10 ≤...
  • Page 254 COMPLEMENTARY FLIGHT MANUAL 1. Heating system............. Off RPM 365 2. RPM 365 switch ........... ON 3. NR increases............Check 365 rpm 4. Altimeter and Radio altimeter DH ......adjusted 5. Parking brake ............Applied 6. Hover at 3 ft............Rotor at the edge of the elevated helideck 7.
  • Page 255 COMPLEMENTARY FLIGHT MANUAL 3.2 TAKEOFF WITH AN ENGINE FAILURE BEFORE OR AT THE RP (BEFORE FUSELAGE ROTATION) A safe force landing on the deck is enabled – Aircraft is operating outside the exposure time 15 ft Figure 2: Elevated helideck rejected takeoff AS SOON AS FAILURE IS DETECTED: ABORTED TAKEOFF 1.
  • Page 256 COMPLEMENTARY FLIGHT MANUAL 3.3 TAKEOFF WITH AN ENGINE FAILURE AT OR AFTER DPATO: The aircraft is capable of continuing the flight. Aircraft is operating outside the exposure time Figure 3: Elevated helideck OEI at or after DPATO AS SOON AS FAILURE IS DETECTED: CONTINUED TAKEOFF 1.
  • Page 257 COMPLEMENTARY FLIGHT MANUAL At 200 ft 7. In level flight, IAS........Vy . 8. At Vy, landing gear ........ Retract. When the OEI 2 min indication flashes: 9. OEI continuous ........Select. 10. Collective pitch ........Adjust to maintain. NR = 350 rpm. When the climb is established: 11.
  • Page 258 COMPLEMENTARY FLIGHT MANUAL 3.4 TAKEOFF WITH AN ENGINE FAILURE BETWEEN THE RP (FUSELAGE ROTATION STARTED) AND BEFORE DPATO A safe forced landing is not assured - Aircraft is operating within the exposure time. Figure 4 Elevated helideck OEI landing or ditching AS SOON AS FAILURE IS DETECTED: 1.
  • Page 259 COMPLEMENTARY FLIGHT MANUAL 4 INFORMATION ON PERFORMANCE WITH AN ENGINE FAILURE UPON ELEVATED HELIDECK TAKEOFF The takeoff weight of this section guaranties at least the CATEGORY A 1 and 2 segments climbing performance and the twin-engine hover performance OGE. For each OAT Range (Temperate conditions ISA - 10 ≤ OAT ≤ ISA + 10 (refer to figure 6) and Hot conditions ISA + 10 <...
  • Page 260 COMPLEMENTARY FLIGHT MANUAL 4.28 4.22 TOTAL THEORETICAL EXPOSURE TIME CORRECTION (Minimum TTET 0.5 s) (Factored) wind effect Pressure altitude effect ISA effect +10 ktdecrease TTET by 1.5s +1000 ftincrease TTET by +10°Cincrease TTET by 1.0s +20 ktdecrease TTET by 3.0s 1.0s -10°C...
  • Page 261 COMPLEMENTARY FLIGHT MANUAL Example 1 (refer to figure 5): TTET determination depending on Wished takeoff weight = 4100 kg for: - Hp= 500 ft - OAT= 24°C (ISA+10) (see graph) - Actual headwind = 20 kt  factored wind 10 kt - Available drop down = 10 ft A) Ensure that the operating flight envelope limits are observed (refer to §...
  • Page 262 COMPLEMENTARY FLIGHT MANUAL Example 2 (refer to figure 5): Takeoff weight determination depending on Wished total theoretical exposure time = 0.5 s for: - Hp= -500 ft - OAT= 16°C (ISA) (see graph) - Actual wind = 20 kt  Factored wind 10 kt - Available drop down = 10 ft A) Ensure that the operating flight envelope limits are observed (refer to §...
  • Page 263 COMPLEMENTARY FLIGHT MANUAL 5 TAKEOFF PERFORMANCE 5.1 SL/ISA TOTAL THEORETICAL EXPOSURE TIME CORRECTION (Minimum TTET 0.5 s) (Factored) wind effect Pressure altitude effect ISA effect +10 ktdecrease TTET by 1.5s +1000 ftincrease TTET by +10°Cincrease TTET by 1.0s +20 ktdecrease TTET by 3.0s 1.0s -10°C...
  • Page 264 COMPLEMENTARY FLIGHT MANUAL 5.2 SL/ISA + 20 TOTAL THEORETICAL EXPOSURE TIME CORRECTION (Minimum TTET 1 s) (Factored) wind effect Pressure altitude effect ISA + 20 effect +10 ktdecrease TTET by 1.5s +1000 ftincrease TTET by 1.0s +10°Cincrease TTET by 1.5s +20 ktdecrease TTET by 3.0s -1000 ftsame TTET -10°C...
  • Page 265 COMPLEMENTARY FLIGHT MANUAL 6 LANDING PROCEDURES 6.1 NORMAL TWIN ENGINE LANDING ON ELEVATED HELIDECK Figure 14 Flat offset approach Figure 8 Normal AEO landing NOTE is the minimum ground speed, 40 ft above the deck at which drop down is possible.
  • Page 266 COMPLEMENTARY FLIGHT MANUAL 1. Compute VLSS and TTET (refer to landing performance § 8). 2. RPM 365 switch............. ON RPM 365 3. NR increases ..............Check 365 rpm 4. Parking brake ..............Applied 5. Carry out a shallow approach aiming to achieve VLSS with a rate of descent lower than 200 ft/min 6.
  • Page 267 COMPLEMENTARY FLIGHT MANUAL 6.2 ENGINE FAILURE BEFORE OR AT DPBL - ABORTED LANDING AND OEI CLIMB Go around is mandatory – Aircraft is operating outside the exposure time - 5° Figure 9: Aborted landing and OEI climb AS 365 N3 APP.9.1 11-42 Page 17...
  • Page 268 COMPLEMENTARY FLIGHT MANUAL AS SOON AS THE FAILURE IS DETECTED: GO AROUND 1. Collective pitch........Raise as necessary while maintaining NR > 350 rpm. 2. Pitch Attitude..........Set - 5° within approx. 1,5 seconds to accelerate to VTOSS (50 or 55 kt depending OAT).
  • Page 269 COMPLEMENTARY FLIGHT MANUAL 6.3 LANDING WITH AN ENGINE FAILURE AT OR AFTER THE CP Landing is mandatory. Figure 10: Landing with an engine failure at or after the CP AS SOON AS THE FAILURE IS DETECTED: 1. Continue drift to the helideck without pausing for hover IGE. 2.
  • Page 270 COMPLEMENTARY FLIGHT MANUAL 6.4 LANDING WITH AN ENGINE FAILURE AFTER DPBL AND BEFORE CP A safe forced landing is not assured. Aircraft is operating within the exposure time. - 20° Figure 11: Landing with an engine failure after DPBL and before CP AS 365 N3 APP.9.1 11-42...
  • Page 271 COMPLEMENTARY FLIGHT MANUAL AS SOON AS FAILURE IS DETECTED: 1. Pitch Attitude set .......... Nose down – 20° 2. Collective pitch ..........Maintain until audio horn then released to maintain above 340 rpm Approaching the ground: 3. Nose down attitude ........reduce to decrease rate of descent If the rate of descent is stopped after the nose down attitude is reduced, the flight might be continued.
  • Page 272 COMPLEMENTARY FLIGHT MANUAL 7 INFORMATION ON PERFORMANCE WITH AN ENGINE FAILURE - LANDING ON ELEVATED HELIDECK The landing weight of this section guaranties at least the CATEGORY A 1 and 2 segments climbing performance in case of go-around and the twin-engine hover performance OGE.
  • Page 273 COMPLEMENTARY FLIGHT MANUAL Charts and table enable determining: - Either the TTET and VLSS depending on Hp, OAT, factored wind, available drop down and wished landing weight (see example 1 figure 13). - Or the landing weight depending on HP, OAT, factored wind, available drop down and wished TTET (see example 2 figure 13).
  • Page 274 COMPLEMENTARY FLIGHT MANUAL 4.28 4.24 5.75 15.5 TOTAL THEORETICAL EXPOSURE TIME CORRECTION (Factored) wind effect Pressure altitude effect ISA effect +10 ktdecrease TTET by 4.5s +1000 ftincrease TTET by 2.0s +10°Cincrease TTET by 2.5s +20 ktdecrease TTET by 9.0s -1000 ft decrease TTET by 0.5s -10°C...
  • Page 275 COMPLEMENTARY FLIGHT MANUAL Example 1 (refer to figure 13): TTET and VLSS determination depending on Wished takeoff weight = 4000 kg for: - Hp= 500 ft - OAT= 24°C (ISA+10) (see graph) - Actual headwind = 20 kt  factored wind 10 kt - Available drop down = 10 ft A) Ensure that the operating flight envelope limits are observed (refer to §...
  • Page 276 COMPLEMENTARY FLIGHT MANUAL Example 2 (refer to figure 13): Landing weight determination depending on Wished total theoretical exposure time = 1 s for: - Hp= -500 ft - OAT= 16°C (ISA) (see graph) - Actual wind = 20 kt  Factored wind 10 kt - Available drop down = 10 ft A) Ensure that the operating flight envelope limits are observed (refer to §...
  • Page 277 COMPLEMENTARY FLIGHT MANUAL 8 LANDING PERFORMANCE 8.1 SL/ISA TOTAL THEORETICAL EXPOSURE TIME CORRECTION (Factored) wind effect Pressure altitude effect ISA effect +10 ktdecrease TTET by 4.5s +1000 ftincrease TTET by 2.0s +10°Cincrease TTET by 2.5s +20 ktdecrease TTET by 9.0s -1000 ft...
  • Page 278 COMPLEMENTARY FLIGHT MANUAL 8.2 SL/ISA + 20 TOTAL THEORETICAL EXPOSURE TIME CORRECTION (Factored) wind effect Pressure altitude effect ISA + 20 effect +10 ktdecrease TTET by 4.5s +1000 ftincrease TTET by 2.0s +10°Cincrease TTET by 2.5s +20 ktdecrease TTET by 9.0s -1000 ft...
  • Page 280 RR8A COMPLEMENTARY FLIGHT MANUAL SECTION 9 OPERATIONAL DATA Some sub-sections covering installations or procedures not used on this helicopter may be withdrawn from this manual. However they still appear in the table of contents and in the list of effective pages. CONTENTS 9.29 RESERVED...
  • Page 281 COMPLEMENTARY FLIGHT MANUAL SECTION 9 OPERATIONAL DATA Some sub-sections covering installations or procedures not used on this helicopter may be withdrawn from this manual. However they still appear in the table of contents and in the list of effective pages. CONTENTS GUIDANCE FOR CARGO SLING OPERATIONS 9.2 to 9.17 RESERVED...

  • Page 283: Guidance For Cargo Sling Operations

    COMPLEMENTARY FLIGHT MANUAL SECTION 9.1 GUIDANCE FOR CARGO SLING OPERATIONS 1 PERSONNEL TRAINING Cargo sling operations may only be conducted by pilots who already have considerable experience with their aircraft. No pilot may perform solo cargo-carrying flights without first having accomplished such operation in the company of an instructor.
  • Page 284 COMPLEMENTARY FLIGHT MANUAL 3 AIRBORNE LOADS Heavy loads, such as bags of cement or drums of kerosene, which are carried in a net, present no particular problem. Special precautions must be taken in the case of bulky loads, which have a tendency to oscillate and even to "float"...
  • Page 285 COMPLEMENTARY FLIGHT MANUAL 5 CARGO RING SIZE RULE Extreme care must be exercised when rigging a load to the Cargo Hook. It is the responsibility of the operator to assure the cargo hook will function properly with each rigging. A placard located on both sided of the A/C illustrates the following: •...
  • Page 319 COMPLEMENTARY FLIGHT MANUAL 3 OPERATION 3.1 PRE-FLIGHT CHECKS • On the transmitter: check that “ARM-OFF-ON” switch is set to “ARM”. • In the cockpit: check that the remote control switch is set to “ARMED”. 3.2 OPERATION TESTING NOTE Test procedure is to be conducted once per month The self-test mode is a temporary mode.

  • Page 320: Adelt Cpt 609 Distress Beacon Installation

    COMPLEMENTARY FLIGHT MANUAL SECTION 9.25 4 - ADELT CPT-609 DISTRESS BEACON INSTALLATION 1 GENERAL Designed for guiding offshore search and rescue operations, the emergency locator transmitter transmits a signal on the international distress frequencies (121.5 MHZ, 243 MHZ and 406.025 MHz). The beacon switches on as soon as it is ejected from the aircraft, after using the control unit or automatically using different detectors (frangible or hydrostatic switches).

  • Page 323: Smith 503 Distress Beacon Installation

    COMPLEMENTARY FLIGHT MANUAL SECTION 9.25 5 - SMITH 503 DISTRESS BEACON INSTALLATION 1 GENERAL Designed for guiding offshore search and rescue operations, the emergency locator transmitter transmits a signal on the international distress frequencies (121.5 MHZ and 406.025 MHz). The beacon switches on as soon as it is ejected from the aircraft, after using the control unit or automatically using different detectors (frangible or hydrostatic switches).
  • Page 324 COMPLEMENTARY FLIGHT MANUAL 3 OPERATION The beacon may be deployed upon ditching automatically or manually when decided by the crew. 3.1 PRE-FLIGHT CHECK On system interface unit: • ARM/OFF Switch.......ARM (Guarded) Control panel: • DEPLOY and TRANSMIT switches ...Guarded. Operation testing: •...
  • Page 333 COMPLEMENTARY FLIGHT MANUAL 4.4 SPECIAL CHECKS (FIRST FLIGHT OF THE DAY) TEST:...... Press 10 s, then and/or : refer to maintenance manual. 4.5 ROTOR TUNING 4.5.1 General M’ARMS allows measurement of vibration level to establish main or tail rotor tuning diagnostic. •...

  • Page 335: Cockpit Voice And Flight Data Recorder : Cvfdr

    COMPLEMENTARY FLIGHT MANUAL SECTION 9.28 COCKPIT VOICE AND FLIGHT DATA RECORDER 1 GENERAL The CVFDR performs the following main functions : FDR function : the helicopter system configuration flight parameter acquisition and recording, CVR function : the cockpit audio signal acquisition and recording (voice, communications and background).
  • Page 336 COMPLEMENTARY FLIGHT MANUAL CVR caution light : indicates a voice recording fault. FDR caution light : indicates a flight data recording fault. MFDAU caution light (figure1) : indicates a Flight Data Acquisition unit fault. DFDAU caution light (figure2) ERASE pushbutton : used to erase the audio tracks.
  • Page 340 RR8A COMPLEMENTARY FLIGHT MANUAL SECTION 9.30 DUAL GNS 430W SYSTEM OPERATOR'S MANUAL PUBLISHED BY THE MANUFACTURER, MUST BE USED FOR COMPLETE OPERATING INSTRUCTIONS. 1 GENERAL This system allows radio communications and radio navigation. 2 DESCRIPTION The control units are located on the console. NOTE 1 VHF2 121.5 push-button is to be used in case radio control is lost on both GNS 430W:...

  • Page 341: Mfd 255 Ef Multifunction Display

    COMPLEMENTARY FLIGHT MANUAL SECTION 9.31 MFD 255 EF MULTIFUNCTION DISPLAY THIS SECTION ONLY DEALS WITH GENERAL INFORMATION AND THE OPERATING PRINCIPLE MFD, PILOT’S GUIDE PUBLISHED MANUFACTURER MUST USED COMPLETE OPERATING INSTRUCTIONS. 1 GENERAL 1.1 SYSTEM CONFIGURATION The MFD Multi Function Display System includes: −...
  • Page 342 COMPLEMENTARY FLIGHT MANUAL 1.3 BRIEF DESCRIPTION The navigation and radio-navigation equipment, the autopilot and flight coupler, interface with the MFD system via the switching unit. The structure of the system compensates for the loss of essential information: - Loss of an attitude or heading gyro or air data computer ( reconfiguration on the second sensor), - Loss of the upper PFD screen (display of PFD function on lower screen and possibility of complementary display of main navigation information in...
  • Page 343 COMPLEMENTARY FLIGHT MANUAL MFD TEST PAGE This page allows to check built-in test of MFD: • Access on ground by pressing TST pushbutton on advisory panel. • Revert to PFD and ND by pressing MODE pushbutton bezel key. AS 365 N3 9.31 07-50 Page 3...
  • Page 344 COMPLEMENTARY FLIGHT MANUAL ARCHITECTURE AS 365 N3 9.31 07-50 Page 4...
  • Page 346 RR8B COMPLEMENTARY FLIGHT MANUAL RECONFIGURATION CONTROL UNIT (RCU) The RCU is located on the console and is used to select the valid sensor in the event of a component failure. Without SAR modes With SAR modes AHRS, ADC and RA: Position "NORM": Normal operation: Pilot = 2, Copilot = 1.
  • Page 347 RR8B COMPLEMENTARY FLIGHT MANUAL AHRS CONTROL UNIT The AHRS control unit is located on the console. Function ON/OFF pushbutton: Energizes the AHRSs. IOFFI – Switches off the AHRSs. COMP pushbutton: Compensates the directional gyros. ICOMPI – Magnetic compensation position selected. This mode can only be initiated on the ground, before startup.

  • Page 355: Locator Searchlight

    COMPLEMENTARY FLIGHT MANUAL SECTION 9.33 1 - “LOCATOR” SEARCHLIGHT 1 GENERAL The LOCATOR searchlight mounted at the LH rear bottom structure fairing is designed for multiple purposes (surveillance, search and rescue,...). It is energized and oriented by means of control switches provided on a handgrip hooked onto a support secured to the console.

  • Page 356: Second Landing Light

    COMPLEMENTARY FLIGHT MANUAL SECTION 9.33 2 - SECOND LANDING LIGHT 1 GENERAL An additional landing light, controllable in elevation and azimuth, can be mounted in the nose area, on the LH side or RH side after MOD 07 33B62 of the lower fairing symmetrically to the basic landing light.

  • Page 371: Dynamics Monitoring System: Dms

    COMPLEMENTARY FLIGHT MANUAL SECTION 9.80 DYNAMICS MONITORING SYSTEM 1 GENERAL This system allows monitoring drive trains health by the vibratory analysis. The monitoring equipment must allow to make vibratory measurements in the purpose: - to inform of an excessive vibratory level, - to make measurements with an immediate help in adjustment of certain mechanical components of the aircraft (rotors, drive shaft, fan,...) - to store data on a ground station to follow-up the H/C vibration trend.
  • Page 372 COMPLEMENTARY FLIGHT MANUAL • Press ENTER to initiate the action or validate the displayed value. NOTE With no action on the Control Panel keys for 30 seconds, the system automatically reverts to the stand-alone health monitoring mode with the message "Monitoring In Progress".
  • Page 373 COMPLEMENTARY FLIGHT MANUAL SECTION 10 ADDITIONAL PERFORMANCE DATA CONTENTS 10.1 CORRESPONDENCE CHARTS Pages 1. PRESSURE ALTITUDE / DENSITY ALTITUDE ..........1 2. TAS / CAS ......................2 10.2 LEVEL FLIGHT PERFORMANCE 1. EFFECT OF EQUIPMENT ................1 2. SINGLE AND TWIN-ENGINE LEVEL FLIGHT SPEED AND HOURLY FUEL CONSUMPTION CHARTS ......2 3.
  • Page 383 COMPLEMENTARY FLIGHT MANUAL AS 365 N3 10.2 07-50 Page 7...
  • Page 384 COMPLEMENTARY FLIGHT MANUAL AS 365 N3 10.2 02-48 Page 8...
  • Page 417 COMPLEMENTARY FLIGHT MANUAL AS 365 N3 10.2 07-50 Page 41...
  • Page 418 COMPLEMENTARY FLIGHT MANUAL AS 365 N3 10.2 02-48 Page 42...
  • Page 433 COMPLEMENTARY FLIGHT MANUAL AS 365 N3 10.3 04-10 Page 5...
  • Page 434 COMPLEMENTARY FLIGHT MANUAL AS 365 N3 10.3 07-50 Page 6...
  • Page 445 COMPLEMENTARY FLIGHT MANUAL 10.7 RATE OF CLIMB WITH TRAINING MODE AT OEI 30s The determination of R/C requires the use of reduced weights (M/σ). In order to simplify the use of the figures and in order to avoid confusion between “density weight”...
  • Page 446 COMPLEMENTARY FLIGHT MANUAL Figure 1 AS 365 N3 10.7 10-40 Page 2...
  • Page 447 COMPLEMENTARY FLIGHT MANUAL Figure 2 AS 365 N3 10.7 10-40 Page 3...
  • Page 448 COMPLEMENTARY FLIGHT MANUAL Figure 3 AS 365 N3 10.7 10-40 Page 4...

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