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Eurocopter AS 350 83, Flight Manual

The Eurocopter AS 350 83 is a reliable and versatile helicopter used for various missions, from passenger transport to aerial filming. Ensure safe and efficient operation by downloading the free Flight Manual from manualshive.com, providing all the necessary information and guidelines for a smooth flight experience.

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Summary of Contents for AS 350 83

Page 1: ...GAC approved on certain pages means that these pages are an integral translation of the French issue approved by DGAC This RFM is approved for CANADIAN registered aircraft and consists of all pages ma...

Page 2: ...FLIGHT MANUAL PAGEINTENTIONALLY LEFT BLANK DGAC Approved 350 B3 O O P1 I A I B I C I F I 97 40 Page 2...

Page 3: ...SECTION PAGE DATECODE SECTION PAGE DATECODE 0 O P1 3 Op 98 38 2 2 2 Op 98 38 3 2 5 Op 98 38 3 3 4 op 98 38 t 4 LIST OF THE LATESTNORMAL NORMAL REVISION 0 APPROVED REVISIONS DGAC APPROVED DATE 23 SEP 1...

Page 4: ...ADDITIONAI APPROVED PAGES S crION PACE DATECODE __ CTION PAGE DATECODEr THIS AIRCRAFT DOES NOTOFFERANYPARTICULAR FEATURES REQUIRI NG THECUSTOMIZAnON OF THE FLIGHTMANUAL ON 8 GREEN PAGES 8 c 8 DGAC Ap...

Page 5: ...FLIGHT MANUAL PART 1 GENERAL LIMITATIONS EMERGENCY PROCEDURES NORMALPROCEDURES PERFORMANCE SUPPLEMENTS DGAC Approved 35083 O O P2 I A I B I C I F I 97 40 Page 1...

Page 6: ...TTHE INFORMATION REMAINS IN ACCORDANCE WITHTHE PARAGRAPH CONCERNED e No SECTION PAGE DATE Applicable before condition is met RC A 2 1 1 97 40 MODIFICATION 350A08 3929 Night VFR flight RC B 4 1 4 98 28...

Page 7: ...AL REVISION RN MODIFIESTHE PAGE NUMBER FORANYINFORMATION CONCERNED BELOW THEREADER WIll HAVE TO CHANGE THENUMBER OF THEPINK PAGE 8YHAND SOTHATTHEINFORMATION REMAINS IN ACCORDANCE WITHTHE PARAGRAPH CON...

Page 8: ...PAGE DATE CODE CODE 2A 2 1 1 RR 99 02 2 2 3 RR 99 02 3 2 5 RR 99 02 3 3 4 RR 99 02 28 2 1 1 RR 99 40 Supersedes RR2A 2 1 page 1 2C 4 1 3 RR 00 40 4 1 4 RR 00 40 2D RESERVED 2E 3 1 4 RR 00 45 2F 0 0 P...

Page 9: ...NUAL COMPOSITION OF RUSHREVISIONS RR The Ma nual onta ins the following additional yellow page s No S CTION PAGE CODE No SECTION PACE CODE DATE PATE 1 8 I ii c I c r c 8 c i DCAC Approved 350 B3 W J l...

Page 10: ...98 36 R 1 2 97 40 3 2 3 98 36 R 2 1 97 40 3 2 98 36 R 1 2 2 97 40 3 2 5 97 40 1 3 1 97 40 3 2 6 97 40 3 2 97 40 3 3 J 98 36 R 2 0 P6 1 98 36 R 3 3 2 97 40 2 1 1 98 36 R 3 3 3 98 36 R 2 1 2 98 36 R 3 3...

Page 11: ...40 4 2 4 97 40 S 0 P6 1 97 40 5 1 1 97 40 5 1 2 97 40 S 1 3 97 C 5 1 4 97 40 8 5 1 S 97 40 5 1 6 97 40 5 1 7 97 40 5 1 8 97 40 5 1 9 98 36 R 5 10 98 36 R 8 LISTOFTHE LATEST NO MAL APPROVED REVISIONS N...

Page 12: ...FI IG1 ITMANUAL Sf CII GENERAl CONTENTS Page 1 PRELIMINARY NOTES 1 1 2 UPDATING 1 1 3 SYMBOLS ANDCONVERSION TABLES 1 8 I 8 1 t i f i j c f _i DGAC Approved 35083 1 0 P6 I A IB IC I FJ 97 40 Page 1...

Page 13: ...FLIGHTMANUAL SECTION 1 Page 1 1 PRELIMINARY NOTES 1 1 2 UPDATING 1 1 3 SYMBOLS ANDCONVERSION TABLES 1 DGAC Approved 350 B3 1 0 P6 I A I B I C I F I 97 40 Page 1...

Page 14: ...ed in PART2 COMPLEMENTARY FLIGHTMANUAL as a complement to PART 1 This information is covered by SECTIONS 6 7 8 9 and 10 Each PARTof Manual makes up a whole and for this reason incorporates its own lis...

Page 15: ...d corner of each page of the approved PART 1 2 4 Customization modifications printed on green paper Special features of a particular helicopter may justify prioritary addenda to the information on cer...

Page 16: ...fully or partially update the manual The pages may be new pages or may supersede the existing pages They are printed on white paper The manual effectivity is specified on the new introductory 0 O P1...

Page 17: ...user s responsibility The pink pages are specified on a separate list 0 0 P3 or SUP 0 P3 page 1 r m These pages are unaffected by normal and rush revisions or by customization 2 4 The ERRATUM Drocedur...

Page 18: ...lb bars bar 14 5040 pounds per square inch psi kilometers per hour km h 0 5400 knot kt 2 2 Enqlish to metric Multiply By To obtain inches in 2 5400 centimeters cm feet ft 0 3048 meters m feetperminut...

Page 19: ...climbing speed Vy VY Rate of cl imb Rate of descent Vz R C Wind velocity Vw Vw Take off safety speed VSD VTOSS Rotor speed NR NR MQrg Unless otherwise specified the air speed values used refer to ind...

Page 20: ...10 FIRST LIMITATION INSTRUMENT 11 TORQUE LIMITATIONS 12 ENGINE LIMITATIONS 13 LUBRICATION SYSTEM LIMITATIONS 14 ELECTRICAL AND HYDRAULIC POWER SYSTEM LIMITATIONS 15 LANDING AND STOPPING LIMITATIONS ON...

Page 21: ...pter is approved out of icing conditions for Day VFR flight Night VFR flight when modification 350AO8 3929 or modification 350AO7 2839 or modification 072810 has been applied and the required equipmen...

Page 22: ...en the required equipment items are installed and serviceable provided such operation is permitted by the flight regulations of the country concerned 3 BASIS OF CERTIFICATION The helicopter is approve...

Page 23: ...cted from VNE 10 kt 19 km h 12 MPH when OATis below 30 C In the cross hatched zone in the C of G graph VNEis limited to 133 kt or to the value determined above whichever is the lowest value 6 1 2 VNE...

Page 24: ...ding VNEare summarized in the tables below ANYCONFIGURATIONS NOTMENTIONED AREPROHIBITED SLIDING DOOR ON THE LH SIDE AND STANDARD DOORS ON THE RH SIDE LH SLIDING DOOR OPEN OR REMOVED 135 kt 250 km h 15...

Page 25: ...ximum temperature ISA 35 limited to 50 7 3 Manoeuvrina limitations Do not exceed the load factor corresponding to the servo control reversibility limit 7 4 Fliaht in fallina snow Flight when visibilit...

Page 26: ...text 7 2 Temperature as follows 7 2 Temperature Minimum temperature 400C The instructions for operation in cold weather are given in supplement 4 Maximum temperature ISA 350 C limited to 500 C 8 DGAC...

Page 27: ...pm Minimum time between two consecutive brakings 5 min 10 FIRST LIMITATION INSTRUMENT i Maximum continuous limitation 9 6 Take off zone 5 min 9 6 to 10 Maximum take off limitation 10 Activation of the...

Page 28: ...CONTINUOUS POWER 12 1 Gas Generator Speed Maximum transient rating less than 5 sec Maximum take off rating 5 min With P2 air bleed off Refer to CAUTION R Maximum continuous 12 2 t4 Temperatures Maximu...

Page 29: ...0 87 with petrol 3 h between generals overhauls AVIATION GASOLINE F 18 AIR 3401 MIL G 5572 D Eng RD AVGAS 100 130 GRADE 100 130 2485 Add 2 mineral oil if possible AIR 3401 MIL G 5572 D Eng RD F 22 115...

Page 30: ...ROSENE 50 AVTUR FSII JP8 I KEROSENE 50 I AVTUR JP1 I AIR 3405 F34 AIR 3405 F35 MIL T 83133 JP 8 D Eng RD 2453 D Eng RD 2494 F 34 WITH ASTM D 1655 JET A1 F 35 WITHOUT ASTM D 1655 JET A KEROSENE HIGH FL...

Page 31: ...ompulsory if OATis below 20 C Authorized additives AIR 3652 MIL I 27686 D Eng RD 2451 S 748 MIL I 85470A R Concentration shall be from 0 10 to 0 15 by volume R R 12 5 2 Antistatic Additive SHELL ASA 3...

Page 32: ...an anti icing additive is compulsory if O A T is below 20 C Autorized additives AIR 3652 MIL I 27686 D Eng RD 2451 S 748 MIL 1 85470A Concentration shall be from 0 10 to 0 15 by volume 12 5 2 Antistat...

Page 33: ...mber USE FRANCEI U S J I U K Fiuid synthetico 0156 I MILL 23699 I DE D 2499 20 C 5 cSt SO C 2 13 3 Aooroved Enoine Lubricants NORMAL USE USE PROHIBITEDUNDE 30 C NATO SP C FiCATlONS OIL TYP SYMBOL FnAN...

Page 34: ...56 MIL L 23699 OTHER OILS USE PROHIBITED ABOVE 30 C SPECIFICATIONS I U S A I NATO SYMBOL OIL TYPE U K FRANCE 0 148 MIL L 7808 Fluid synthetic oil 3 to 3 5 cSt at 98 9 C 0 0 OJ 0 ci AIR 3514 0 150 Flui...

Page 35: ...tem Fluid Used Synthetic MIL H 83282 recommended Mineral base MIL H 5606 AIR 3520 DTD 585 NATO H 515 If the fluid specification is changed refer to the procedure specified in the Maintenance Manual 14...

Page 36: ...CREW One pilot in RHseat 18 TRANSPDRT OF PERSONNEL Numer of persons carried 6 maximum pilot included 19 MANDATORY INSPECTIONS AIRWORTHINESS LIMITATIONS Lifed components and the corresponding S L L are...

Page 37: ...MARKINGS 1 PLACARDS 1 1 Plates Displayed in the Cockpit Operating limitations VNE I POWER ON H pO 1tJ j P 11 IAS kts 1 0 155 POWER OFF 30 kts ADlalu I VNE POWER ON 133kts WC G ln hatched zon8 0 0 0 R...

Page 38: ...CHARGE REPARTIE MAXI 80 kg SUR PLANCHER CABINE ARRIERE 310 kg g g ON REAR CABIN FLOOR 682 Ib 0 DISTRIBUTED LOAD MAXI 1761b g SUR PLANCHER AVANT GAUCHE 150 kg ON L H FORWARD CABIN FLOOR 330 Ib In port...

Page 39: ......

Page 40: ......

Page 41: ...reen Normal operating range White Equipment operating limit Red triangle Transient limit The numerical values of the parameters on the VEMD are underlined in yellow in the cautionary zone flashing red...

Page 42: ...PRESSURE INDICATOR Red line Yellow arc Yellow arc Red line 1 1 bar 15 9 psi 1 1 2 bar 15 9 29 psi 6 9 8 bar 87 142 1 psi 9 8 bar 142 1 psi R Red line Yellow arc ENGINE OIL TEMPERATURE INDICATOR 115 10...

Page 43: ...THE CABIN 4 6 TAIL ROTORFAILURE 4 3 2 SYSTEMFAILURES 1 FUEL SYSTEMFAILURES 1 2 ENGINE SYSTEMFAILURES 1 3 VEMDFAILURES 2 4 ABNORMAL NR NF READINGS 5 5 HYDRAULIC SYSTEMFAILURES S 6 BLEED VALVE FLAG 6 3...

Page 44: ...120 km h airspeed Select the OFF IDLE FLIGHT selector to OFF According to the cause of loss of the engine Re light the engine see paragraph 3 2 of this Section Otherwise close the fuel shut off valve...

Page 45: ...be quickly repositioned against the flight stop APply the procedure described in paragraph 2 1 except for the engine After landing with the collective down re position the twist grip in the flight not...

Page 46: ...k Warning Caution Advisory Panel GENlight off Booster pumpselected OFF PUMP and FUELP captions Extinguished If the starting cycle has to be aborted return the start switch to the closed position and s...

Page 47: ...is faulty carry out the appropriate procedure as detailed in SEmON 3 3 6 TAIL ROTOR FAILURE 6 1 Tail Rotor Drive Failure Loss of the tail rotor in power on flight results in a yaw movement to the left...

Page 48: ...ht illuminates when tested Land as soon as possible 2 2 Encine Oil Temperature hicher than Maximum specified values 2 2 1 At Low Speed or in Hover Land if possible Stop the engine Check that the coole...

Page 49: ...will be available R refer to the procedure provided in paragraph 3 3 for compliance with limitations Double display failure Real failure is highly improbable in practice this case occurs only when th...

Page 50: ...r the parameter which is over the r limit is not displayed at the time of failure In this case Press the SCROLL push button to show the out of limit parameter Check the parameters CROSS TALK FAILED PR...

Page 51: ...g 8 x 92 93 95 6 90 92 93 95 96 J 4 89 90 91 93 94 96 2 87 89 90 92 93 95 96 I 0 40 30 20 10 0 10 20 30 OAT COC llNQ and torQuemeter indications failure Governing failure red GOVwarning can also caus...

Page 52: ...Cont d The paragraph GOYindicator light is to be completed by LIGHT FAILURE PILOTACTION GOY e 8i In all cases the NR must be controlled so I that the max NRalarm isI never activated OGAC Approved 350...

Page 53: ...the upper section of the green range Slowly reduce the speed if necessary adjust the fuel flow rate slightly on the twist grip to maintain NR within the green range On final approach when the collect...

Page 54: ...TAil ROTOR FAilURE CAUTION LANDING IS MADE EASIER BY A WIND COMING FROM THE RiGHT IF THE AIRSPEED is lOWER THAN 20 kt 36 km h GO AROUND IS IMPOSSIBLE DUE TO THE lOSS OF EFFICIENCY OF THE FIN DGAC Appr...

Page 55: ...loss of NR indication Maintain engine torque above 10 land as soon as possible MQlE The NF value can be read on the VEMD screen Press SCROll then as many times as required to display the parameter in...

Page 56: ...aw servocontrol and depressurizes the load c ensating servo accumulator After 5 seconds reset the test button to the normal position Make a shallow approach to a clear landing area with a slight side...

Page 57: ......

Page 58: ...w axis land normally if rotation about the yaw axis cut off hydraulic pressure by actuating the switch situated on the collective pitch control lever In cruising flight Reduce speed entering into a si...

Page 59: ...w power set ings If the flag does not disappear at high power settings the maximum available engine power is reduced especially in cold weather If the flag does not reappear at lower power settings th...

Page 60: ...rpm 310 Hz tone R when maximumtake off limitations are exceeded for more than 1 5 R seconds 285 Hztone R 1 2 1 Reducecollective pitch to maintain NR in green arc or power within R limitations R 1 2 2...

Page 61: ...which remains pressurized increase indefinitely after a on forward and LH cyclic hydraulic pumpfailure or If necessary increase after hydraulic power lAS but the control load cut off via the collecti...

Page 62: ...ero oil pressure atthe powercorresponding to minimumpowerin level flight at 55 kt T BATT Batterymaximumtemperature Isolate thebattery push button OFF BATTTEMP andland assoon aspossible P MOT Engineoil...

Page 63: ...pon ding to minimum power in level flight at SS kt R T BATT Battery maximumtemperature Isolate the battery push BATT button OFF and land as TEMP soon as possible P MOT Engine oil pressure alarm Reduce...

Page 64: ...educe the speed if necessary adjust the fuel flow rate slightly on the twist grip to maintain NR within the green range On final approach when the collective pitch is increased on reaching the hover l...

Page 65: ......

Page 66: ...er charging Keep a watch on voltage BATT see NOTE 2 Continue flight according to circumstances KLAX Horn not set Set the horn by actuating the push button situated on HORN the control pedestal panel s...

Page 67: ...place the throttle in the FLIGHT GRIP notch OOV Permanently lit governing Avoid abrupt power variations Function degraded Flashing at idle or during shut down governing is operating but redundancy is...

Page 68: ...ature Test the waming caution advisory panel to check the MGB P light If the light does not illuminate MGB TEMP proceed as for MGB oil pressure at zero If the light illuminates land and check the MGB...

Page 69: ...GB Monitor MGB P and MGB T MGB CHIP lights Should either or both lights illuminate refer to illumination of relevantI light s in LIGHT column Metal particles in engine LAND AS SOON AS POSSIBLE LIM MOT...

Page 70: ...check 5 i 2 Figure 1 Station 1 Transparent panels Cleanliness Condition R Total pressure head PITOT Cover removed Check clean Landing gear cross members skids wear resistant plates Security Visual che...

Page 71: ...ition attachments Tail rotor blades Condition of skin no impact dents etc laminated stops separation TGB and Tail boomfairings Security Dzus fasteners locked Tail rotor guard if fitted Security condit...

Page 72: ...ed 8 is replaced by Fuel shut off control Forward position plastic guard or snap wire fitted The paragraph 3 CHECKS BEFORE STARTING THE ENGINE The check Fuel shut off lever lockwired Forward is replac...

Page 73: ...e aircraft weight sheet and SECTION 6 R Carry out the following checks Seats and control pedals Adjusted Seat belts Fastened MQI Check particularly that the copilot seat belt is fastened when this sea...

Page 74: ...Check that Ng increases Check that t4 remains below its limit Check that the rotor is turning Check that the engine oil pressure increases Check that the following Warning Caution Advisory Panel light...

Page 75: ......

Page 76: ...L Paragraph 4 STARTING Comple the starting procedure as follows On the ground to obtain zero thrust at the tail rotor it is necessary to push the LH pedal over 2 cm approx DGACApproved 35083 4 1 98 03...

Page 77: ...is replaced by Fuel shut off control Forward position plastic guard or snap wire fitted The paragraph 3 CHECKS BEFORE STARTING THE ENGINE The check Fuel shut off lever lockwired Forward is replaced by...

Page 78: ...vel check for hydraulic assistance by absence of control load Press the test push button to restore hy raulic pressure On console Check that HYDRlight goes out Carry out a hydraulic pressure isolation...

Page 79: ...aintain hover head into wind at a height of about 5 ft 1 5m Check that the engine and transmission monitoring instruments are within their normal operating ranges For transition from hover increase sp...

Page 80: ...seconds for one full rotation 8 3 Fl iaht with doors open It is advisable to check that objects cushions documents in the cabin are correctly secured before opening one or both of the sliding doors in...

Page 81: ...the partial cycles figure is not zero and that it is displayed in white 11 TURNAROUND CHECK TA R The turnaround check consists in R Checking MGB TGBand engine fluid levels R Check that there is no flo...

Page 82: ...lation parameters required are displayed on the VEMD lower display record the results The values provided by the VEMD can be checked against the graphs Figures 1 and 2 Refer to paragraph 1 2 R 1 2 Use...

Page 83: ...igh power single engine helicopter of this type Before forward flight in a 5 ft hover increase the collective pitch enough to ensure a momentary Ng increase of at least 1 After having reached a safe a...

Page 84: ...09 INCORRECT S 30 9 CORRECT 09 20 u 10 09 90 0 p 0 10 20 30 40 15 0 10 0 5 e40 g 0 II Z 390 0 s 0 38 TORQUE EXAMPLE OAT 10 C Hp 1000 ft NR 392 rpm Ng 92 TORQUE 83 P is in the correct zone Figure 1 DC...

Page 85: ...E 3 4 STARTING 4 5 CHECKS BEFORE TAKEOFF 6 6 TAKEOFF 6 7 CLIMBING 6 8 CRUISING FLIGHT AND MANOEUVRES 7 9 APPROACHAND LANDING 7 10 AFTER LANDING 8 11 TURNAROUND CHECK TA 8 12 USE OF THE HEATING DEMISTI...

Page 86: ...MARGIN CHECK 850 8 14 C 7 6 800 5 i 4 3 2 750 1 0 700 0 0 0 2 m 650 0 30 40 50 1 Hp 11 x 1000 OAT C EXAMPLE Hp SOOOft OAT 1S C T is in the correct zone T4 760 C Ng 93 Figure 2 OGAC Approved 35083 4 2...

Page 87: ...TRODUCTION 1 2 SUBSTANnATED WIND ENVELOPE 1 3 AIRSPEED CALIBRATION 1 4 AIRSPEED HEIGHT ENVELOPE 2 5 IGE HOVERINGFLIGHT PERFDRMANCE 4 6 OGE HOVERINGFLIGHT PERFORMANCE 6 7 RATESOF CLIMB 9 8 NOISE LEVELS...

Page 88: ...ted for winds of 40 kts from any direction and for 50 kt headwinds 2 2 Wind envelope in hover Hovering with wind from any direction has been substantiated over the entire flight envelope up to winds o...

Page 89: ...9 m for an airspeed of 4D knots 74 km h Detennin na variable Points C and D Point C Point C is defined by a constant height of 100 ft 30 m a variable airspeed depending on the altitude and on the air...

Page 90: ...HEIGHT I VELOCITY ENVELOPE 7DOO 6000 0 I 2000 1 0 WEIGHT 0 0 0 40 50 lbx100 6 45 40 35 OAT rC 1ft i i i i i i i i i ili i i i ii i 100 C 0 0 10 20 30 0 0 g g 2 Figure 1 OGAC Approved 35083 5 1 I A I...

Page 91: ...e performance must be reduced by 50 kg 0 s Zp s 23 000 ft NOTE 1 This performance is provided on the VEMD performance page Values corresponding to Zp 8 torques beyond the certified flight envelope mus...

Page 92: ...ONS IGE HOVERING FLIGHT PERFORMANCE 7 22 20 1 16 g 14 g E 12 0 0 10 8 6 4 g 2 w c S 0 1200 1400 1600 1800 2000 kg 2200 0 ao oo as OO 40 OO 4S OO ib 1 WEIGHT Figure 2 OGAC Approved 35083 5 1 I A I 8 I...

Page 93: ...duced by SO kg 0 Zp 23000 ft This performance is provided on the VEMDperformance page Values corresponding to Zp 8 torques beyond the certified flight envelope must not be taken into account refer to...

Page 94: ...OGE HOVERING FLIGHT PERFORMANCE 7 22 20 6 18 18 5 0 14 0 0 2 0 4 x x E 12 Q Q Z Z 10 3 8 6 4 0 0 j 2 s m 0 1200 200 w 3000 3500 4000 400 5000 5500 6000 Ib WEIGHT Figure 3 OGAC Approved 35083 5 1 I A I...

Page 95: ...ALUES using the graph opposite 32 34 lbx100 36 38 40 42 44 46 48 49 6 52 54 56 57 3 60 61 7 I I I 0 0 I 2 40 30 20 10 0 10 20 30 40 1500 2000 2500 3000 3500 OAT rC CORRECTED WEIGHT kg EXAM PLE OAT 15...

Page 96: ...T REDUCE PERFORMANCE DATA BY 250 ft min a a a II a CO g g a CO a II a II a I II a a II II I g z a f3 II jjj I a 0 a III I 0 III q q 0 0 I z 0 to 40 30 20 10 0 10 20 30 40 500 500 1000 1500 2000 ft mln...

Page 97: ...els detennined under the conditions specified in Chapter 11 R of APpendix 16 of the ICAO are as follows R Measurement as per ICAO Limit R lCAO APpendix 16 dB A R dB A R 84 6 86 5 R 8 DGACAPproved 350...

Page 98: ...supplements or supersedes the information given in the basic flight manual and or applicable flight ma ual supplements The effectivity of the supplement at the latest revision is specified on the LIs...

Page 99: ...Pages SUP O PI page 3 SUP 0 P3 page 1 and SUP 0 P4 page 1 concern the whole of the Supplements assigned to the helicopter mentioned on the title pages DGAC Approved 350 83 SUP O P1 I A 18 I C I D I FI...

Page 100: ...ded or modified Check that pages in each supplement are those specified in the list of effective pages Withdraw old and insert new supplements affected by this revision Retum the acknowledgement card...

Page 101: ...ADDITIONAL APPROVEDPAGES SECTION PAGE DATE CODE SECTION PAGE DATE CODE THIS AIRCRAFT DOES NOTOFFER ANY PARTICULAR FEATURES REQUIRING THE CUSTOMIZATIONOF THE FLIGHT MANUALON GREEN PAGES DGAC Approved...

Page 102: ...AL AND OPTIONAL SUPPLEMENTS 1 RESERVED 2 RESERVED 3 RESERVED 4 INSTRUCTIONS FOR OPERATION IN COLDWEATHER 5 to RESERVED 10 11 EXTERNAL LOAD TRANSPORT CARGO SWING 1160 kg 2557 lb 12 EXTERNAL LOAD TRANSP...

Page 103: ...OIST 136 kg 300 lb 19 PENDING 20 HYDRAULIC PUMPDRIVE ON MGB 21 FORWARD TWO PLACESEAT 22LONG AND SHORT FOOTSTEPS R 23RESERVED it 24 LOUDSPEAKER INSTALLATION 25 PENDING SPECIAL SUPPLEMENTS 50 FERRYFLIGH...

Page 104: ...THE PAGENUMBERFOR ANY INFORMATION CONCERNED BELOW THE READERWILL HAVE TO CHANGE THE NUMBEROF THE PINK PAGE BY HAND SO THAT THE INFORMATION REMAINS IN ACCORDANCE WITH THE PARAGRAPH CONCERNED Sup Page D...

Page 105: ...ellowpage s SUPPLEMENT NoRR PAGE DATE SUPPLEMENT NoRR PAGE DATE CODE CODE SUP11 1A 4 RR 98 48 Notapplicablefor CAAand ENAC Certification SUP 14 2A 1 RR 00 07 2 RR 00 07 SUP 17 1A 2 RR 02 08 SUP 0 P4 1...

Page 106: ...contains the following additional yellow page s SUPPLEMENT NoRR PAGE DATE SUPPLEMENT NoRR PAGE DATE CODE CODE SUP 11 1A 4 98 48 SUP 0 P4 1 RR 00 07 a SUP 14 2A 1 RR 00 07 2 RR 00 07 18 iI t DGACAppro...

Page 107: ...L COMPOSITION OF RUSHREVISIONS RR The Supplements contains the following additional yellow page s No SUP PAGE CODE No SUP PAGE CODE DATE DATE i DGAC Approved 350 83 SUP O P4 I A I 8 IC I D I FIG I 97...

Page 108: ...TE 1 SUPPLEMENT PAGE DATE 1 SUP 0 P1 1 97 40 SUP 0 P1 3 97 40 SUP 0 P2 1 98 05 SUP 0 P2 2 99 45 R SUP 0 P3 1 97 40 SUP 0 P4 1 97 40 SUP 0 P5 1 01 99 45 R SUP 0 1 99 37 SUP 0 2 97 40 LIST OF THE LATEST...

Page 109: ...ipment items impossible ITEM 15 Emergency floatation gear SUP 17 32 66 R 2l Ferry fl ight fuel tank SUP 50 22 23 32 68 22 External load carrying 2l 25 32 44 46 installation CARGOSLING SUP12 66 R 23 Ex...

Page 110: ...of an optional equipment item modifies the take off weights specified in the basic Flight Manual the new take off weights are provided by new charts or a penalty relative to the basic flight performan...

Page 111: ...supersedes the information given in the basic flight manual and or applicable flight manual supplements The effectivity Of the supplement at the latest revision is specified on the List of Effective...

Page 112: ...e inserted SUPPLEMENT PAGE DATE 1 SUPPLEMENT PAGE DATE 1 SUP 4 PI 1 97 40 N SUP 4 P5 1 01 97 40 N SUP 4 1 97 40 N SUP 4 2 97 40 N SUP 4 3 97 40 N SUP 4 4 97 40 N LIST OF THE LATESTNORMAL NORMAL REVISI...

Page 113: ...smitting items main rotor rotor mast tail drive and tail rotor flight controls engine controls When the aircraft has been subjected to very low temperatures it is recOlmlended that either reaular arou...

Page 114: ...n ENGINESTART ON COLD CHARGED 2 BAn BATTERY 1 DEMARRAGE AVEC BATTERIE g CHAUOE 20 CHARGEE 1 BAn ENGINE START ON WARM j20 C CHARGED 2 BAn BAmRY 4 CHECKS BEFORE FLIGHT Independently of the inspections p...

Page 115: ...er once the inspection is over to prevent ice from fonning Make sure that the windshield wiper is not stuck on the canopy FliQht controls EnQine controls Before operating the controls it is recomnende...

Page 116: ...ther side of the mid position 7 IN CASE OFENGINE FAILURE Following an engine failure at light weight the stabilized rotor speed may be below the audio warning threshold the pilot can switch off the ho...

Page 117: ...t manual and or applicable flight manual supplements The effectivity of the supplement at the latest revision is specified on the List oj Effective Pages THIS SUPPLEMENT MUST BE INCLUDED IN THE FLIGHT...

Page 118: ...SUPPLEMENT PAGE DATE 1 SUPPLEMENT PAGE DATE 1 SUP 11 P1 1 97 40 N SUP l1 PS 1 01 97 40 N SUP l1 1 97 40 N SUP l1 2 97 40 N SUP 11 3 97 40 N SUP l1 4 97 40 N SUP l1 5 97 40 N LISTOFTHE LATEST NORMAL NO...

Page 119: ...andle mounted on the underside of the collective lever The load indicator electrical circuit is protected by a fuse and the nonnal release hook control circuit by two fuses 3 1 0 2 0 0 0 N 0 0 ci z 2...

Page 120: ...2 CG in PROHIBmON Carrying of external passengers Absolute maximumpermissible speed with a load on the hook is 80 kt 148 km h 92 MPH Particular care must be exercised when bulky loads are being carri...

Page 121: ...AYANT TRAIT A L UTILISATION DU GIRAVION AVEC CHARGE EXTERIEURE A plate visible to the ground operator and located near to the hook indicates the maximum sling load 3 EMERGENCY PROCEDURES The emergenc...

Page 122: ...tallation On the ground before carrying out a load transport operation Check that the hook opens correctly both in normal and jettison control modes Zero the load indicator In flight press the SLING p...

Page 123: ...he subparagraphCheckof the installation after Checkthat the hook control modes text addedas follows Check the free rotation of the retaining latch and correct operation of its return spring 350 83 SUP...

Page 124: ...the switch on the cyclic stick Check that the load is effectivelv released If the load is not off actuate the jettison handle to release it 5 PERFORMANCE The Performance Data given in the basic Flight...

Page 125: ...and or applicable flight manual supplements The effectivity of the supplem en at the latest revision is specified on the list of Effective Pages THIS SUPPLEMENT MUST BE INCLUDED IN THE FLIGHT MANUAL...

Page 126: ...ted SUPPLEMENT PAGE DATE 1 SUPPLEMENT PAGE DATE 1 SUP l2 P1 1 97 40 N SUP 12 P5 1 01 97 40 N SUP 12 1 97 40 N SUP 12 2 97 40 N SUP 12 3 97 40 N SUP 12 4 97 40 N I I LISTOF THELATEST NORMAL NORMAL REVI...

Page 127: ...he load indicator electrical circuit is protected by a fuse and the nonnal release hook control circuit by two fuses 1 0 2 i I 2 LIMITATIONS The limitations laid down in the basic Flight Manual remain...

Page 128: ...ion 8 external passengers Absolute maxim permissible speed with a load on the hook is 80 knots 92 MPH 148 kin h particular care must be exercised when bulky loads are being carried on the sling NOTE T...

Page 129: ...e failure with external load If an engine failure should occur in flight with an external load establish autorotational flight and immediately release the load If engine failure occurs whilst ground p...

Page 130: ...off in a forward clintJ Manoeuvres All control movementsshould be madevery gently with very gradual acceleration and deceleration and only slightly bankedturns Establish zero translational ground spee...

Page 131: ...ht manual and or applicabie flight manual supplements The effectivity of the supplement at the latest revision is specified on the List of Eflective Pages THIS SUPPLEMENT MUST BE INCLUDED IN THE FLIGH...

Page 132: ...ed SUPPLEMENT PAGE DATE 1 SUPPLEMENT PAGE DATE SUP 13 PI 1 98 05 N SUP 13 P5 1 01 98 05 N SUP 13 1 98 05 N SUP 13 2 98 05 N SUP 13 3 98 05 N SUP 13 4 98 05 N SUP 13 5 98 05 N LlSTEDESDERNIERES REVISIO...

Page 133: ...ch indicates that there is no load on the hook an aDDer LD ON light which indicates that a load greater than 7 kg 15 lb is present on the hook A control system is provided for the pilot an SLING ELING...

Page 134: ...is limited to 2800 kg 6173 lb The maximum authorized weight is that which allows hovering Flight out of ground effect CAUTION THE MAXIMUMWEIGHTWITHOUTEXTERNALLOAOREMAINS LIMITEO TO THAT SPECIFIED IN T...

Page 135: ...ES MEMBRES DE L EQUIPAGE SUIVRE UN COURSDE FORMATIONEN TANT QUE MEMBRE D EQUIPAGEOU REMPLIR UNE FONCTIONESSENTIELLE AYANT TRAIT A L UTILISATION DU GIRAVION AVEC CHARGEEXTERIEURE A plate visible to the...

Page 136: ...icopter Consequently pilots are advised to train with gradually increased sling loads before undertaking heavy load carrying operations CAUTION IN WET WEATHER THICK RUBBERGLOVESSHOULDBE WORNBY THE OPE...

Page 137: ...dturns 4 4 Establish zero translational ground speed sufficiently high to ensure that the load is not dragged along the ground then descend vertically until the load is deposited 4 5 To release the lo...

Page 138: ...plicable flight manual supplements The effectivity of the supplement at the latest revision is specified on the List of Effective Pages THIS SUPPLEMENT MUST BE INCLUDED IN THE FLIGHT MANUAL WHEN THE E...

Page 139: ...AGE DATE 1 SUP 14 Pi 1 98 05 SUP 14 P5 1 01 98 36 N SUP 14 1 98 05 SUP 14 2 98 05 SUP 14 3 98 05 SUP 14 4 98 05 SUP 14 5 98 05 SUP 14 6 98 05 SUP 14 7 98 05 SUP 14 8 98 05 SUP 14 9 98 36 R LIST OF THE...

Page 140: ...om the air intake grid Open the engine cowling Check for snow ice or water in the air intake and particularly under the filter CHECKS BEFORE STARTING THE ENGINE Check the P2 indication on the VEMD and...

Page 141: ...trol and monitoring system During engine operation the ambient air flows through separator tubes which constitute the filter The filtered air is forced towards the engine air intake The sana is evacua...

Page 142: ...ir is forced towards the engine air intake The sand is evacuated by scavenge tubes ventilated by P2 air The electrical circuit supplies an electric valve via the SANDFILTn push button Opening and clos...

Page 143: ...ake grid Open the engine cowling Check for snow ice or water in the air intake and particularly under the filter CHECKS BEFORE STARTING THE ENGINE Test the indicator light located on the instrument pa...

Page 144: ...m the air intake grid Open the engine cowling Check for snow ice or water in the air intake and particularly under the filter CHECKS BEFORE STARTING THE ENGINE Check the P2 indication on the VEMD and...

Page 145: ...NG 50 40 9 INCORRECT 96 30 9 CORRECT 9 20 9a 0 A 9 10 rq 0 90 0 P 10 20 30 40 15 0 10 0 x Q 5 40 E e o Z 390 0 38 TORQUE EXAMPLE OAT 10 C Hp 1000 ft NR 392 rpm Ng 92 TORQUE 83 P is in the correct zone...

Page 146: ...al to 50 A If the electrical consumption is greater than 50 A the performance must be reduced by 50 kg 0 Zp 23000 ft This perfonnance is provided on the VEMD perfonnance page The values corresponding...

Page 147: ...PERFORMANCE WITH SAND FILTER NOT OPERATING 7 22 20 18 18 g 14 g 4 E 12 0 0 X x 10 3 8 6 2 4 0 1 0 2 w Q 0 1200 1400 1600 1800 2000 kg 2200 0 I I I I 3000 3500 4000 4500 Ib WEIGHT Figure 2 OGAC Approve...

Page 148: ...1 This perfonnance is provided on the VEMD performance page Values corresponding to Zp 0 torques beyond the certified flight envelope must not be taken into account refer to SECTION 2 1 7 The OGEweigh...

Page 149: ...ND FILTER NOT OPERATING 7 22 20 18 5 18 0 14 0 0 0 0 4 x x 12 0 0 J J 10 8 64 0 1 C 2 w 0 1200 1400 1600 1800 2000 2200 2400 kg 28000 I I I I I I I 3000 3500 4000 4500 5000 5500 6000 Ib WEIGHT Figure...

Page 150: ...VALUES using the graph opposite 32 34 lbx100 36 38 40 42 44 6 8 49 6 52 54 56 57 3 60 61 7 I 0 0 on 0 g O 30 20 10 0 10 20 30 O 2000 2500 3000 3500 OAT rC CORRECTED WEIGHT kg EXAMPLE OAT 1SoC ACTUAL W...

Page 151: ...0 It min N OT OPERATING NOTE WITH THE SAND FILTER OPERATING THE PERFORMANCE IS REDUCED BY 80 It min 0 0 0 0 CO 0 0 0 I N 0 iii z 40 30 20 10 0 10 20 30 40 minI g 1 1 1 1 1 1 1 I OAT C 0 1 2 3 4 5 6 hm...

Page 152: ...al and or applicable flight manual supplements The effectivity of the supplement 8tthe latest revision is specified on the List of Effective Pages THIS SUPPLEMENT MUST BE INCLUDED IN THE FLIGHT MANUAL...

Page 153: ...1 97 40 N SUP 16 P5 l Dl 97 40 N SUP 16 1 97 40 N SUP 16 2 97 40 N SUP 16 3 97 40 N SUP 16 4 97 40 N SUP 16 5 97 40 N SUP 16 6 97 40 N SUP 16 7 97 40 N SUP 16 8 97 40 N SUP 16 9 97 40 N SUP 16 10 97 4...

Page 154: ...system A control for adjustment of the rudder pedals friction Three control actuators one per axis Two trim actuators on pitch and roll axes Three galvanometers pitch roll yaw I Three disengaged chann...

Page 155: ...hold pushbutton 5 Airspeed hold pushbutton 6 Selected heading holdpushbutton 7 Coordinatedturn mode pushbutton 8 Failure monitoring unit andAPdisengage pushbutton Only the functions of the pushbuttons...

Page 156: ...he autopilot 4 Amberindicator lights Whenon the associated channel s is are not enaaaed n Theyawgalvanometer pointer is recenteredby movingthe rudder pedals in the direction shownby the pointer 1 3 Cv...

Page 157: ...olecontrols the static inverter 115 Vand26 V 400Hz a c powergeneratingsystem 1 6 Autopilot Monitorina Panel Figure 4 2 1 3 0 4 0 5 o o 7 8 9 6 IT No Descri n 1 A P warninglight blinking red 2 TRIM cau...

Page 158: ...caused by the autopilot Consequently disengage the autopilot If the anomaly disappears after disengagement re engage each channel in turn until failure is identified Retain channels that operate prope...

Page 159: ...tnE 10 seconds Fig 4 defective axis pilot power reduction may be required to comply with the limitations Autanatic disengagement Continue flight of faulty channel 3 6 TRIMmalfunction INDICATION SYMPT...

Page 160: ...i of load co 1 ensator shaft by applying a 10 daN load approx on cyclic stick 3 8 A C oower suoolv failure INDICATION SYMPTOM PILOT S ACTION AP light blinks for AP disengages automati Check that ALTER...

Page 161: ...n control panel Detail 5 on Figure 4 Fig 1 illuminate Lights on AP monitoring panel Fig 4 illwninate 21 2 second time delay Test function light 4 Figure 4 illuminates Test selector switch set to O Tes...

Page 162: ...t illuminates Fig 1 Sameprocedure as the pitch channel I 4 1 3 Pitch trim test Pitch channel engaged Relevant pushbutton light Fig 1 illuminates ONappears Test selector switch set to TRIM TRIM caution...

Page 163: ...ed The actuators counteract within the limits of their authority Through the 4 way button Deviation in the direction of operation of the attitude references 4 3 1 2 Yaw Feet off the pedals Channel hol...

Page 164: ...is then nil The yaw channel provides coordination 4 3 2 2 Altitude ALT This mode may be operated when the airspeed is above 60 kt 111 km h 69 MPH When this mode is engaged the autopilot holds the eng...

Page 165: ...or applicable flight manual supplements The effectivity of the supplement at the latest revision is specified on the List of Effective Pages THIS SUPPLEMENT MUST BE INCLUDED IN THE FLIGHT MANUAL WHEN...

Page 166: ...to be inserted SUPPLEMENT PAGE DATE 1 SUPPLEMENT PAGE DATE 1 SUP 17 P1 1 97 40 N SUP 17 P5 1 01 97 40 N SUP 17 1 97 40 N I SUP 17 2 97 4D N SUP 17 3 97 40 N LIST OF THE LATEST NORMAL NORMAL REVISION 0...

Page 167: ...pecified in the basic Manual remain applicable independently of the following Floats stowed system not armed no special limitations Floats stowed system armed or floatation gear inflated maximum IAS i...

Page 168: ...FORWARD DOORS MUST BE OPENED BY ACTUATING THEJEmSON CONTROL 4 NORMAL PROCEDURES Normal procedures specified in the basic Manual remain applicable independently of the following External checks Float c...

Page 169: ...40 50 60 70 FAHRENHEIT DEGREE 49 40 22 4 14 32 50 68 86 104 122 140 158 c PRESSION MAX BARS 242 247 257 268 278 288 298 308 318 328 339 349 362 MAX PRESSURE PSI 35013582372838874032417743224467 46124...

Page 170: ...y floatation gear in stowage position the performance data specified in SECTION 5 1 remain applicable except for clintling performance which is reduced by 50 ft min 15 m min at 55 kt IAS OGAC APproved...

Page 171: ...ht manual and or applicable flight manual supplements The effectivity of the supplement at the latest revision is specified on the List of Effective Pages THIS SUPPLEMENT MUST BE INCLUDED IN THE FLIGH...

Page 172: ...be inserted SUPPLEMENT PAGE DAlE 1 SUPPLEMENT PAGE DAlE 1 SUP 18 P1 1 97 40 N SUP 18 P5 1 01 97 40 N SUP 18 1 97 40 N SUP 18 2 97 40 N SUP 18 3 97 40 N LISTOFTHE LATEST NORMAL NORMAL REVISION 0 APPROV...

Page 173: ...jettison guarded switch on the pilot s collective lever which is used to sever the cable in an emergency A rocker switch 7 on the hoist operator s control grip which is used to raise lower and stop t...

Page 174: ...ver or cyclic stick handgrip which permits the load to be released in an emergency In the event of a complete electrical failure have the cable severed by meansof the mechanical cutter available to th...

Page 175: ...e load is hoisted on board With Air Equipement hoist when rigid compact loads over 80 kg 176 lb post mod AMS 1587 are being hoisted inconsequential oscillations may appear Operate the hoist AIR EQUIPE...

Page 176: ...ual and or applicable flight manual supplements The effectivity of the supplement at the latest revision is specified on the list of Effective Pages I THIS SUPPLEMENT MUST BE INCLUDED IN THE FLIGHT MA...

Page 177: ...replaced N New to be inserted SUPPLEMENT PAGE DATE 1 SUPPLEMENT PAGE DATE 1 SUP 20 PI 1 97 40 N SUP 20 P5 1 01 97 40 N SUP 20 1 97 40 N LIST OF THE LATEST NORMAL NORMAL REVISION 0 APPROVED REVISIONS...

Page 178: ...draulic pump runs dry the power taken must be less than 3 kW so that the aircraft s performance data is not affected Operation of the hydraulic pump under load is prohibited in hover in climb in level...

Page 179: ...or applicable flight manual supplements The effectivity of the supplem en a the latest revision is specified on the List of Eflective Pages THIS SUPPLEMENT MUST BE INCLUDED IN THE FLIGHT MANUAL WHEN T...

Page 180: ...be replaced N New to be inserted SUPPLEMENT PAGE DATE SUPPLEMENT PAGE DATE 1 SUP 21 Pi 1 97 40 N SUP 21 P5 1 01 97 40 N SUP 21 1 97 40 N LISTOFTHE LATEST NORMAL NORMAL REVISION 0 APPROVED REVISIONS D...

Page 181: ...ll the emergencyprocedures specified in the Basic Flight Manual and relevant Supplements remain applicable 4 NORMAL PROCEDURES The nonnal procedures given in the Basic Flight Manual and relevant Suppl...

Page 182: ...d or supplements listed in supplement O The effectivity of the supplement at the latest revision is specified on the List of Effective Pages THIS SUPPLEMENT MUST BE INCLUDED IN THE FLIGHT MANUAL WHEN...

Page 183: ...aced N New to be inserted SUPPLEMENT PAGE DATE 1 SUPPLEMENT PAGE DATE 1 SUP 22 P1 1 99 21 N SUP 22 P5 1 01 99 21 N SUP 22 1 99 21 N LISTOF THE LATEST NORMAL NORMALREVISION 1 APPROVED REVISIONS DGACAPP...

Page 184: ...t Supplements remain applicable 3 EMERGENCY PROCEDURES The emergency procedures specified in the basic Flight Manual and relevant Supplements remain applicable 4 NORMALPROCEDURES The normal procedures...

Page 185: ...ght manual and or applicable flight manual supplements The effectivity of the supplement aflhe latest revision is specified on the List of Effective Pages THIS SUPPLEMENT MUST BE INCLUDED IN THE FLIGH...

Page 186: ...e replaced N New to be inserted SUPPLEMENT PAGE DATE 1 SUPPLEMENT PAGE DATE 1 SUP 24 P1 1 97 40 N SUP 24 P5 1 01 97 40 N SUP 24 1 97 40 N LIST OF THE LATEST NORMAL NORMAL REVISION 0 APPROVED REVISIONS...

Page 187: ...llation all the limitations specified in the basic Flight Manual remain applicable independently of the following specific limitations Maximum speed VNE Power on 135 kt or basic aircraft VNE if it les...

Page 188: ...and or applicable flight manual suppiements The effectivity of the supplement at the latest revision is specified on the List of Effective Pages THIS SUPPLEMENT MUST BE INCLUDED IN THE FLIGHT MANUAL...

Page 189: ...to be inserted SUPPLEMENT PAGE DATE 1 SUPPLEMENT PAGE DATE 1 SUP 50 PI 1 97 40 N SUP 50 P5 1 01 97 40 N SUP 50 1 97 40 N SUP 50 2 97 40 N SUP 50 3 97 40 N LIST OF THE LATEST NORMAL NORMAL REVISION 0 A...

Page 190: ...AL PERMISSIONOF THE C PETENT AUTHORITIES The limitations laid down in the basic Flight Manual remain applicable In addition Only personnel indispensable to the accomplishment of the mission are author...

Page 191: ...Take off and fly with the transfer valve closed When the fuel gauge reads 80 open the transfer valve The fuel level in the two tanks is then equal if the quantity in the ferry tank is approx 79 2 USga...

Page 192: ...FUELTRANSFER IS NOTOPERATIVE LANDBEFORE THEFUELGAUGE READINGFALLS TO 60 FAILURE TO LAND ABOVE60 MAY RESULT IN CENTRE OFGRAVITY MOVING OUTSIDE ALLOWABLE LIMITS 5 PERFORMANCE The approved performance d...

Page 193: ...nual and or applicable flight manual supplements The effectivity of the supplement at the latest revision Is specified on the List of Effective Pages THIS SUPPLEMENT MUST BE INCLUDED IN THE FLIGHT MAN...

Page 194: ...laced N New to be inserted SUPPLEMENT PAGE DATE 1 SUPPLEMENT PAGE DATE 1 SUP 56 P1 1 99 37 N SUP 56 P5 1 01 99 37 N SUP 56 1 99 37 N LIST OF THE LATEST NORMAL NORMAL REVISION 0 APPROVED REVISIONS DGAC...

Page 195: ...the ropes unwound The load on the abseiling installation is limited to 120 kg per ring A plate affixed close to each ring indicates the maximum load 3 EMERGENCY PROCEDURES The EmergencyProcedures spe...

Page 196: ...d to the approved night manual when the listed equipment is installed The information contained herein supplements the information in the basic Helicopter t Manual or limitations procedures and perfor...

Page 197: ...FMS 0350 607 Page 2 of 4 LOG OF AMENDMENTS Rev Pages Revised By Approved By Inserted By Date No Revised and Date and Date Inserted A None J Bradley L B Samoil May 16 199 May 20th 1994 c I I 18 DOT AP...

Page 198: ...Reference Widow PLACARD located on lid i l 1 I IILI l i I I JI I i r J I rj Jii NOTE THE BASKETS ARE LOCATED CENTRALLY AT I LONGITUDINAL STATION 135 in I 3422 mm LH LATERAL BL 48 in 1222 mm 8 RH LATE...

Page 199: ...URES NO CHANGE 8CTION 4 PERFORMANCE DATA CRUISE Vh reduced by up to 15 KIAS j CLIMB Rate of climb may be reduced by up to 200 FPM AUTORATION Rate of descent may be increased by up to 100 FPM HOVER No...

Page 200: ...SE AS3SSF AS3SSF1 AS3SSF2 t l I y u I o r Ilation of Utility Basket in accordance with Dart Aero Accessories Inc Drawing No D3S0 607 Rev B dated February 2 1994 1 I Dart Aero Accessories Inc Maintenan...

Page 201: ...uiredwith this STC 4 approvalshouldnot be incorporatedin any aircraft of thesespecific modelson which other approvedmodificationsare in rated unlessit is determinedthatthe interrelationshipbetweenthis...

Page 202: ...Accessories Inc I c Limitations Drawing No D350 507 Revision B dated February 22 1994 R red E t 1 Dart Aero Accessories I Maintenance MamJal Supplement MMS D350 607 Revision A dated February 22 1994...

Page 203: ...ER AS350 355 MODELS This supplement must be attached to the approved flight manual when the listed equipment is installed The information contained herein supplements the information in the basic Heli...

Page 204: ...FMS D350 600 Page 2 of 4 LOG OFAMENDMENTS Rev Pages Revised By d By Inserted By Date No Revised and Date e Inserted A NEW B Williams ISSUE 95 09 25 I z CAA APPROVED...

Page 205: ...NS VFR FLIGHT ONLY Flight under IFR is prohibited with the pods installed INTERNAL GARGO LOADING Maximum Load in the LH Port Hold 364 Ib 165 kg DECAL locatedinsidedoor Maximum Load in the RH Stbd Hold...

Page 206: ...SECTION 4 NORMAL PROCEDURES DAILY INSPECTION Preflight Check physical integrity and security of the Spac9po body and door SECTION 5 REGULATORY PERFORMANCE DATA CLIMB Climb perfom1ance will be reduced...

Page 207: ...on the ft d h DOT STC N SH97 15 SHo7 60 alrcra Inaccor ancewlt 0 Section 2 3 4 and 5 of this document comprise the approved Flight Manual Supplement Compliance with Section 2 Certification Limitation...

Page 208: ...is almost doubled rightside 14 1 cubic feet left side 15 3 cubicfeet With the Cargo Pods SQUIRRELCHEEKS installed the RH cargo compartmentcan carry up to 175 kg 386Ib andthe LH compartment can carry u...

Page 209: ...change b For Climb use the standardperlormance chart inSection5 ot the Flight Manual but reduce the resulting rate of climb by the followingamount 0 tor AS 350 C D D1 B BA 200ft min 0 for AS 350 B1 62...

Page 210: ...T NOTE The practical value of this manual depends entirely upon its being correctly up dated The effectivity of the manual at the latest revision is specified on the List of Effective Pages Q Jd EU RO...

Page 211: ...C PLEMENTARYFLIGHT MANUAL PART 2 WEIGHT AND BALANCE SYSTEMS AND DESCRIPTION SERVICING OPERATIONAL INFORMATION ADDITIONAL PERFORMANCE 35083 O O P2 97 40 Page 1...

Page 212: ......

Page 213: ...d with IF A NORMALREVISION RN MODIFIES THE PAGENUMBERFORANY INFORMATION CONCERNEDBELOW THE READERWILL HAVE TO CHANGE THE NUMBEROF THE PINK PAGE BY HAND SO THAT THE INFORMATIONREMAINSIN ACCORDANCE WITH...

Page 214: ...RY FLIGHTMANUAL COMPOSITION OF RUSHREVISIONS RR The manual contains the following additional yellow page s DATE DATE No RR SECTION PAGE CODE No RR SECTION PAGE CODE 3A 0 0 P4 1 RR 01 20 8 2 4 RR 01 20...

Page 215: ...l containsthe followingadditionalyellow page s N RR SECTION PAGE DATE N RR SECTION PAGE DATE CODE CODE 4A 8 3 19 RR 02 13 10 2 1 RR 02 13 48 8 2 4 RA 02 18 10 2 1 RR 02 18 4C 9 2 7 RR 02 20 9 2 8 RR 0...

Page 216: ...COMPLEMENTARY FLIGHT MANUAL COMPOSITION OF RUSHREVISIONS RR The Manual contains the following additional yellow page s No SEmON PAGE CODE o SEmON PAGE COOE TE DATE I I 35083 O O P4 97 40 Page 1...

Page 217: ...7 5 3 98 46 6 1 3 00 23 7 6 1 97 40 6 1 4 00 23 7 6 2 97 40 6 2 1 97 40 7 6 3 97 40 6 2 2 00 23 7 6 4 00 23 6 2 3 00 23 7 7 1 97 40 6 2 4 00 23 7 8 1 97 40 6 2 5 97 40 7 8 2 97 40 6 2 6 97 40 7 8 3 9...

Page 218: ...97 40 8 4 9 00 23 8 2 1 00 23 8 4 10 97 40 8 2 2 00 23 8 4 11 97 40 8 2 3 97 40 8 4 12 97 40 8 2 4 02 03 R 9 0 P6 1 02 03 R 8 3 1 97 40 9 1 1 97 40 8 3 2 02 03 R 9 2 1 02 03 R 8 3 3 98 46 9 2 2 00 23...

Page 219: ...1 2 97 40 8 4 9 00 23 R 8 2 1 00 23 R 8 4 10 97 40 8 2 2 00 23 R 8 4 11 97 40 8 2 3 97 40 8 4 12 97 40 8 2 4 97 40 9 0 P6 1 97 40 8 3 1 97 40 9 1 1 97 40 8 3 2 00 23 R 9 2 1 00 23 R 8 3 3 98 46 9 2 2...

Page 220: ...46 10 1 4 98 46 10 1 5 98 46 8 10 1 6 98 46 10 1 7 00 23 10 1 8 98 46 10 1 9 98 46 10 2 1 00 23 10 3 1 00 23 10 3 2 00 23 10 3 3 00 23 10 3 4 00 23 10 3 5 00 23 10 3 6 00 23 10 3 7 00 23 10 3 8 00 23...

Page 221: ...E OF GRAVITY CONVENTIONAL TERMS 2 3 WEIGHING 3 4 CALCULATINGC G 3 6 2 LONGITUDINAL LOCATIONOF VARIABLE LOADS 1 CREWAND PASSENGERS 1 2 FREIGHT AND BAGGAGE TRANSPORT 2 3 FUEL 3 4 C G CHARTS 4 6 3 LATERA...

Page 222: ...ipped Emotv Weicht EEW This is the sumof Empty weight EW Specific operational or mission equipment EEW OEW varies according to the proposed mission 1 3 Operatina emotv weicht OEW This is the sum of Eq...

Page 223: ...are positive c A vertical plane perpendicular to the two mentioned above situated 3 40 m 133 8 in forward of the centre of the main rotor This is the X datum plane from which the longitudinal referenc...

Page 224: ...ty of the aircraft to the datum plane is calculated as follows Sumof moments CGlocation Sum of weights Determine the Equipped EmptyWeight Referring to the tables of Section 6 2 for the longitudinal C...

Page 225: ...xample kg m kg EEW 1200 4272 Crew 160 248 Passengers 140 356 Side cargo hold 50 160 Fuel 400 1390 TOTAL 1950 6426 CG 3 295 m 1950 i e longitudinal CGis within the permissible limits 4 2 2 In flight or...

Page 226: ...100 6102 9999 6693 BO 124 203 136 150 9153 12999 10039 100 155 254 170 200 12204 19998 13386 120 186 305 204 250 15255 24997 16732 140 219 356 238 300 18306 29997 20079 160 248 06 272 350 21537 34996...

Page 227: ...384 150 232 5 337 5 414 4 200 450 0 552 6 250 562 5 300 675 0 310 697 5 IMPERIAL UNITS WEIGHT MOMENT in lb lb B ill CD E 50 3051 4429 5439 6299 9055 100 6102 8858 10878 12598 18110 150 9153 13287 1631...

Page 228: ...50 396 54177 150 119 414 60 475 64985 200 158 549 70 554 75793 250 198 688 80 633 86601 300 237 824 90 712 97409 350 277 963 100 792 108353 400 316 1098 110 871 119161 540 427 1484 119 940 128601 I IM...

Page 229: ...cal line Example 1 Total weight 1800 kg for a centre of gravity of 3 30 m During the flight after consumption of 200 kg of fuel the centre of gravity will be 3 28 m Refer to chart Example 2 Total weig...

Page 230: ...SEAT FRETCABINE 5 CABINFREIGHT w U CARGOSLING 7 t SOUTESLAT 0 SlOEHOLOS c CARGOSWING 8 i I RESERV CONV 2 FERRYFUELTANK SOUTEAR 4 60 REARHOLD 1100 1200 1300 0 1400 I r 1500 Q I w 1600 So 1700 w 1800 i...

Page 231: ...NO BIPLACE TWO PLACE SEAT 9 FRET CABINE CABIN FREIGHT 5 s i CARGO SL 8 SaUTES L SIDE HO 9 I CARGO SW 0 0 RESERV CO FERRY FUEL r 3 SaUTE REAR H 1 250 300 g I I 52 3500 w CI CI 4000 450 500 550 6000 617...

Page 232: ...207 m 8 15 in F 0 620 m 24 45 in METRIC UNITS WEIGH MOMENT m kg A B D E EL 50 18 25 10 30 10 31 60 22 30 12 36 12 37 70 25 35 14 42 14 43 80 29 40 16 48 17 50 90 32 45 18 54 19 56 100 36 50 20 60 21...

Page 233: ...50 185 67 130 47 27 81 54 201 36 49 28 84 56 210 IMPERIAL UNffi WEIGHT MOMENT in lb 1b 1 B 0 E 1 1 1 Gl 100 1417 815 2445 1634 6079 2189 120 1700 978 2934 1961 7294 2627 140 1984 1141 3423 2287 8510 3...

Page 234: ...at 11 4 25 22 19 4 1688 I High back I 2 Two place seats rear 21 1 46 5 54 6 4739 1 Three place seat rear 26 2 57 8 67 6 5867 I complete with armrests Dual control 2 3 5 1 2 6 225 Battery 17 3 38 1 69...

Page 235: ...R 136 kg 300 lb R arm winch grip pulley block R belt shears R BREEZE electric hoist 44 0 97 1 115 8 10060 R 204 kg 450 lb R boom faired winch grip pulle R block belt shears R Drip pan 11 3 25 0 26 56...

Page 236: ...ON ADVISORY PANEL 7 4 POWER PLANT 7 5 FUELSYSTEM 7 6 ROTORAND TRANSMISSIONSYSTEMS 7 7 FLIGHT CONTROLS 7 8 HYDRAULIC SYSTEMS 7 9 ELECTRICAL POWER SYSTEMS 7 10 PITOT STATIC SYSTEM 7 11 HEATING AND DEMIS...

Page 237: ...TION 7 1 MAIN OIMENSIONS 1 AIRCRAFT DIMENSIONS 12 94 m 42 45 It I f1 86m 6 10ltdia g E _0 e 0 39 m 1 N 1 27It CO CO 10 93 m 35 86 It I CO E cD E 1 I S Plus 0 20 m 0 65 ft when aircraft equipped with h...

Page 238: ...96 Available cabin floor 2 60 m2 27 98 sq ft Cabin forward doors 1 1 29 m2 13 88 sq ft Cabin rear subdoors 0 69 m2 7 42 sq ft LH hold 0 43 m2 4 62 sq ft RH hold 0 35 m2 3 76 sq ft Rear hold 0 55 m2 5...

Page 239: ...COMPLEMENTARY FLIGHT MANUAL SECTION 7 2 mgsm This section is customized 35083 7 2 97 40 Page 1...

Page 240: ...COMPLEMENTARY FLIGHT MANUAL SECTION 7 3 WARNING CAUTION ADVISORY PANEL This section is customized 35083 7 3 97 40 Page 1...

Page 241: ...ate interchangeable modules Axial C ressor Module with bleed valve Mounted at the forward end of the engine c rising a single stage axial c res50r followed by a guide vane Gas Generator Module Central...

Page 242: ...sory Panel includes lights that illuminate to indicate minimtnn oil pressure metal particles on the magnetic chip detectors KEY TOFIGURE OIL SYSTEM 8 DESCRIPTION DESCRIPTI Jj 1 Oil tank B Pressure rel...

Page 243: ...J I I I I I r J I I I I I I I I I 7 7 7 w 6op 600 600 8 I I I I L J Oz 4 5 J 1 I a O a I I I 1 I I I I I I 3 I I I L IlnJlJl J L J ASPIRATION OIL SUCTION LINE Vi 0 g PRESSION OIL PRESSURE LINE RETOUR...

Page 244: ...ree Ng exhaust gas temperature and torque parameters are converted on a common scale This indicator provides a synthetic engine power information Torquemeter Exhaust gas temperature t4 indicator Bleed...

Page 245: ...ng the engine in very cold weather 0 FLT VOL FLT VOL Automatic e g ne starting in R 4It normal condltlons Flight position 0 FWD Fuel control modeselector AUTO Automatic engine fuel control mode Guarde...

Page 246: ...oswitch controls the Ng regulated idle function thus preventing engine blowout in particular when practicing autorotation Returning the twist grip to the flight detent whenever necessary will switch t...

Page 247: ...agraph Fuel shutoff control by Fuel shutoff control This control is used to close the fuel shutoff valve Replace the subparagraph Rotor brake control by Rotor brake control When the brake is not relea...

Page 248: ...l I FUNffiON GOV FADECpower supply ENG ACC Power supply to starting relay and fuel cut off control electric valve CRANK Power supply to no fuel cranking control relay 32 ALPHA panel DESCRIPTI I FUNCTI...

Page 249: ...for flight AutCHnatic control of free turbine and gas generator rotational speeds to maintain a rotor rotational speed corresponding to the selected value whatever the changes in the aerodynamic load...

Page 250: ...1 UMIT I PO NlAND TORQUE MAJNT Tl UMITS TORQUE UMIT VEMD I Nt CALCULATION I I Dir UGHTS A COCKPIT I INDICATIONI I I STARTING I ACCESSORIES CONTROL I I Nl ING CH PO GHT DATUM I I Tl GHT CALCULATION 14...

Page 251: ...ty Fuel Liters USgal Imp Gal kg Remarks Quantity Total 540 143 119 Specific gravity 0 79 Usable after illumination 60 15 8 13 1 of low level light Unusable 1 25 0 33 0 28 079 CONVERSION TABLE GAUGE RE...

Page 252: ...warning which lights up when the low level is reached in the tank A p COMB FUEL P warning which lights up when the fuel pressure drops below 500 mb R A FILT COMB FUEL FILT warning which lights up when...

Page 253: ...COMPLEMENTARY FLIGHT MANUAL 18 I INJECTEURS I I I I I MOTEUR I ENGINE L 1 APPAR AIRCRA 6 7 5 4 12 3 t 10 11 2 POMP CARB FUELPUMP 1 R 350 83 7 5 98 46 Page 3 I I...

Page 254: ...direction 1 2 Tail rotor The two blade tail rotor is see saw mounted on the TGB The tail rotor blades rotate counterclockwise as viewed from the right side of the aircraft 2 TRANSMISSION SYSTEM The t...

Page 255: ...wer casing with MGB mounting provisions a lubrication module attached to the lower casing Lubrication of the MGBis monitored through a pressure switch causing the MGB p light to illuminate on the warn...

Page 256: ...ar 9 Oil level sight 2 Planet gear 10 Oil temperature switch 3 Sun gear 11 Magnetic plug 4 Low pressure switch 12 Oil pump 5 Oil filter and bypass 13 Pressure relief valve 6 Power input module 14 Oil...

Page 257: ...plash lubricated and is provided with an oil level sight glass 2 5 Rotor Brake rake is mechanically controlled by meanson the lever on the R control quadrant R Whenthe lever is FORWARD the rotor brake...

Page 258: ...of loads inside the cabin The hydraulic servo controls fitted to each control channel are described in SECTION 7 8 When the aircraft is fitted with the optional autopilot each channel is completed by...

Page 259: ...ervoir 21 supplying the pump Three single cylinder main servo controls 1 2 3 driving the fixed swashplate Each servo contro1 is equipped with a safety system comprising a hydraulic accumulator 4 a non...

Page 260: ...ch 11 on the collective pitch lever 12 can be used to cut off all hydraulic power by opening the three solenoid valves on the main rotor servo controls to depressurize the systen A push button 13 on t...

Page 261: ...o control 14 Low pressure warning light 4 Hydraulic acclJ11Ulator 1S Solenoid valve 5 Non return valve 16 Low pressure switch 6 Solenoid valve 17 Filter 7 Pressure relief valve 18 Pressure regulator 8...

Page 262: ...by means of its contactor whenthe following conditions are met electric power is available at the external power receptacle the MASTER SW pushbutton is released the EXT PWR BATT pushbutton is engaged...

Page 263: ...COMPLEMENTARY FLIGHT MANUAL 0 0 j 350 83 7 9 97 40 Page 2I...

Page 264: ...Paragraph 5 ELECTRICAL SYSTEM CONTROL AND MONITORING Replace the existing title 5 1 2 Selectors located on the instrument panel by 5 1 2 Selectors located on the instrument panel or overhead panel 8...

Page 265: ...disengaging the GEN push button by pressing the MASTER SW and CRANK push buttons automatically if a reverse current is detected from the battery to the generator a ground power unit is connected the...

Page 266: ...JO J u 6 6 lO l SJ J d 6U MOllOl 4 SA lds p OW3A 4 uo 6 d l 4 l 41 SJ WPJ a DU JO UOW S 3N3 l1VS S 46 l uo n J qwv dW3111VS 46 l 6U UJ M p l U d AJOS lpv uo n J 4 u p pnl u J S 46 l 6U MOlLOl 41 S 4D...

Page 267: ...Output voltages 115 and 26 VAC Frequency 400 Hz Power output 115 VAC 150 VA limited to 2S0 VA 26 VAC 150 VA 10 VA A C Dower svstem Input voltage 28 VDC Output voltage 26 VAC Frequency 400 Hz Power out...

Page 268: ...is mounted on the nose slightly to the left of the aircraft centerline III The total pressure circuit supplies the airspeed indicator It may include an optional heating resistor operated by the PITOT...

Page 269: ...ves 3 Airspeed indicator 9 Total pressure pick off 4 Rate of climb indicator with optional heating 5 Altimeter 10 VEMD R 6 PITOT light on Warning R Caution Advisory panel R AUTO PILOT AIR DATACIRCUIT...

Page 270: ...e instrument panel controls opening and adjustment of the ventilation circuit Overhead ventilation The air taken from the upper cabin area through a ram air scoop is 1 hen circula1 ed 1 0 1 he air out...

Page 271: ...air mixture is circulated through two separate circuits to the heating outlets provided under the front seats and to the demisting manifolds at the front Twomanually operated valves mounted on the P2...

Page 272: ...MS O SU i3W Aq Pi3ll0J UO pu J qsnq i3J p AJi3 q i34 WOJ pi3 lddns s 46 l i3WOP J i3J i34 Jodsu JL J V lqnd i34 4 M pi3dd nbi3 J J JO li3u d i3sn i3p S H i34 uo i3sn e Aq pi3 oJd i3Je S 46 l i3WOp Je...

Page 273: ...protected by a fuse on the RHside fuse panel For aircraft equipped with the Public Air Transport kit the rear dome R light is supplied from the battery direct busbar and controlled by means R of a swi...

Page 274: ...2 1 IntreQrated circuits of instrument Danel and console ITE DESCRIPTION ITE DESCRIPTION 1 INST LTS 1 fuse 10 Lighting of stand by ompass 2 INST LTS 2 fuse 11 Lighting of indicators having integrated...

Page 275: ...I JI JI JI JI JI JI J I JI JI JI JI JI JI J a a 0 0 II B 9J 0 Dr 9 S lH I JCZ1H IN I Av d I nor Z lSN ZlWIN JJf1N rJSN II O II 6 J I 9 J J I L 9 J H91 J H9IN a AVO a s IInor J SNI linN linN J SNI R o...

Page 276: ...by the A COLL LT fuse The anti collision light is controlled by the A COL LT push button on the control console 5 LANDING LIGHT The landing light is usually mounted at the front RHside of the aircraft...

Page 277: ...ode by default this constitutes the main operating mode of the equipment It contains the ENGINE VEHICLE FLI FLIGHT REPORT ENGINE POWER CHECKand PERFORMANCE pages CONFIG mode this mode contains the pag...

Page 278: ...decrease the numerical RKldule 1 2 andthe upper value of the selected data lower screen 2 SCROLL push button 6 ENTER push button CamlUte the page Validate the selected data 3 RESET push button Returnt...

Page 279: ...isplayed 8 LANE 1 FAILED LANE 2 FAILED PRESS OFFl PRESS OFF2 The line concerned can be cut by pressing the associated push button OFFl or OFF2 This validates the initialization tests and switches the...

Page 280: ...FLK HT I REPORT t t A GINE NGINE NGINE V ENGINE PERFOS g PEAFOS VEHICLE L A i B ENGINE L _ E ENGINE POWER CHECK F L I CCc i TEST ENGINE ENGINE N GPU TEST i VEHICLE j t A V NGINE NGINE A ENGINE g L I P...

Page 281: ......

Page 282: ...ae mJ II 0 Figure 4 FLI Page Values given as an example If one of the parameters on the FLI page becomes invalid the ENGINEpage is displayed automatically the parameters can then be read on independen...

Page 283: ...isplayed the first page provides the conditions to be satisfied where applicable in order to achieve a correct engine power check The check is broken down into three phases a value stabjlization phase...

Page 284: ...8 Second page of the EPC The PERFORMANCE paqe This page is used to calculate aircraft performance in the fonn of takeoff weights in and out ground effect The following parameters must be set the equi...

Page 285: ...ld LVO dB 1 1 5 9M SA9J1 I 10 9Sn r l Oap pSlJaAU r l 113 3 i 0IU sBuB4 J l J S eJnpeJoJd 5U MOLLO e41 ALdde SJel weJed a41 AJ poW JO les 01 senL A 1VO pue dZ LenlJe a41 lUnOJJe OlU sa el OW A e4t pel...

Page 286: ...JAJ au qJn aaJ I S LJA Le ol s LJAJ JoSsaJdwo w l46fL I Z ALLeJf eWO ne pa luaw J Uf s 4J 4M J qwnu l46fL I 1 i NOlldIH S30 311 a6ed 1 Od3 1H Il l OJ Jn6 1 S g In A a le S uMop n4s Uf6u 4 S J ap OW3A...

Page 287: ...1 8 2 ER G N T U S 1 I 2 FUELADDITIVES 1 1 3 LUBRICANTS 2 4 HYDRAULICFLUIDS 2 5 REFUELING l 3 8 3 TEST SCHEDULE 1 GENERAL t 1 2 TEST SHEETS t 2 8 4 DAILY OPERATINGCHECKS 1 INSPECTION ASSOCIATEDWITH TH...

Page 288: ...t balance Install ground handling wheels wheels outside skids see Oetail B Check that wheels are correctly locked see Detail A Lift the aircraft onto its wheels using a jacking lever Lock in this posi...

Page 289: ...COMPLEMENTARY FLIGHT MANUAL 0 m 0 g I g g A 350 83 8 1 97 40 Page 2...

Page 290: ...L I 27686 D ENG RD 2451 OTAN S 748 MIL I 85470A The additive is to be mixed with the fuel in the following proportions Minimum concentration by volume 0 10 R R Maximum concentration by volume 0 15 If...

Page 291: ...n Comconents 3 2 1 Lubricants CommercialDesignations Theauthorized lubricants are given in the LIMITATIONS SECTION 3 2 2 Capacity Main gearbox system included 6 5 litres 1 7 USgal or 1 4 Imp gal Tail...

Page 292: ...lighting not conforming to the rules of safety 8 Ensure during refueling or defueling that the bowser or the defueling unit is connected to the aircraft by the electro static balance connectors Strict...

Page 293: ...N REFUELING WITHROTORS TURNING IS PROHIBITED R Strictly comply with the instructions defined below R Shut the engine down R Apply the rotor brake R Switch the battery off before getting off the aircra...

Page 294: ...ION REFUELINGWITH ROTORS TURNINGIS PROHIBITED G Strictly comply wit h t he inst ruct ions defined below shut t he engine down Apply t he rotor brake Switch t he battery off before getting off the airc...

Page 295: ...s paragraph with the following text CAUTION REFUELING WITH ROTORS TURNING IS PROHIBITED Strictly comply with the instructions defined below Shut the engine down Apply the rotor brake Switch the batter...

Page 296: ...RATIONAL REGULATIONS Strictly comply with the instructions defined below Head aircraft into forward wind sector z 45 if wind above 10 kt Lock the collective pitch lever in full low pitch position chec...

Page 297: ...acement of major components or after an extensive operation or further to periodic inspections The test sheets are in the form of reproducible sheets which can directly be filled in by the crew e CAUT...

Page 298: ...00 tJ 0 Eo j i oo s 8 00 z Eo OO Q 0 j i E 0 b 00 0 o Q s s ZE t s 8 o Zc J 00 j i5 O Eo 0 8 Eo 0 i 0 00 I1 0 5 5 555555 z o 8 000000000000 0 z t e e S 0 0 0 000 s 0 8 c 0 0 0 000 00 tJ o q Q C I IQ...

Page 299: ...n 0 e e o Eo 0 0 o z OrnE z rn z e rn a 00 t t E i 0 0 i II o Eo Co o i j E t g e E o 0 9 d e Eo O J 0 Q E 0 r lQEo jc Q E t Z Z E r t Co 0 t5 C Z 6 9z j O OO g O g e 0 z e O e Eo C Z rn Z C g Eo 0 C...

Page 300: ...0 P 0 r 5 u z Z Q foj Il Q E 1 rn rn I s rz i E5 I j I B BB B o o tl Q 1 j j j Po 0 OJ 6 IIII IIII Ili G GB G Z A e j j E _ foo j 1 g 1 r 0 C I Z I E I 0 U I I 1 0 r 1 c A I 1 o r i i r 1 fOl I 1 A O...

Page 301: ...Ii 0 E o c m 0 r 0 cOo bO U Q zz 00 Qj 00 0 O o g 0 1 8 I g Zl rz1 e 1 tJ0 rx riI 00 B _0 6 E o 0 U x 8e 3 00 Qj JO O U o j OJ Qj E ofE g 00 5 2 riI fE E o E o riI rz1 O A _E o 00 01 t I Z riI S P b...

Page 302: ...Z 0 0 I J o g f i g E 5 C C r_ i 0 0 Q OJ Q Q 2 C 0 to to to 01 as OJ n n n 2 i Q i Q i Q i OJ C I J J J t J J 2 G G G G G G G G o i O tO to Q to OJ to OJ u 1 0 00 Go B Q B B obi B u 0 q 0 0 o CQ I Q...

Page 303: ...0 0 I f g td c o 0 o 0 Eoo 0 3 bOo J 3 os OJ J 0 0 6 j 00 tJ 0 0 0 iX a rzl rzJ g d O 60 dd 0 8 0 1 0 bo OS 01 D o o o o t S 6 E1 E10 g c c lU lU d os rz E d 00 z rzJ rz I rc rzl s o 0 c P4rzJ u 0 to...

Page 304: ...0 2 0 0 00 QI o g J s 11 b E I Eo Eo 8 g 1 3 E I s 00 QI 8 11 0 Z 5 E 0 0 Eo IO fa J fl Oy O_ w rn Z P o m r ouo as as I 8P r 0 O J 3flp i ZSea r 1 nu U zo u COOH to a Z t Z te Z Sa 1 Ir HEo UJJ l P u...

Page 305: ...e bO eo 1 f 9 I S S OE t Z Od Po Q to 1 N a U oS 5 fi i g 2 8 8 00 00 oS gj j E 2 E U m uE 5 U t Z Po _ XI U U r_ r tc Co t UPo E 0 s 5 I J 0 bO E g U P 0 5 S o Uci ZZ Q rIJ f tIt gZ 0 XIoS A s o E U...

Page 306: ...5 l j Ji g w rn b 0 30 3 0 3 0 3 Z 0 3 c E r g 0 3 r 3 I 0 v a 0 ri Z o 0 00 0 G a 0 s oo o 3 0 0 0 0 Z 0 III 0 00 0 o G I o rn 9 g g 0 11 OJ r 0 c CO 0 t I 0 Z a g g 5 6 3 S _ z 0 S 0 g n p 0 z t 3...

Page 307: ...0 o 0 z c z Z S 00 z DO c t OJ ro 0 zc E s 0 Eo o o 0 bI gco E 6B 5 00 00 j bo L 0 O c c 0 u E Eo o C t g 0 a g bO o g u J 0 0 5 v 0 e 00 i c S 21 gJ 0 c c 0 p c 0 v 5 II e og L 00 E C 0 z o 8 r a eO...

Page 308: ...g Z o f j 3 s 1i1 Il r 1 c O S _lIS C 0 t o I19 00 u r PoZ o gj J 0 O It o 8 g E NO 0 2J t 5 0 0 uC z t 0 ij t U lIS 1 0 E O t I O f t 1 OIlS bOO k rl 0 0 S 1 a 0 r4 0 1 0 0 6iJ U o IIS r I Po 0 0 I G...

Page 309: ...o 0 S CE E o t Q 82 6iI O 1 E U E o 3 11 e E o SZ 0 oJ 0 t 0 uS Q Q A CI g 0 0 bO c Z f Ii c O Q 0l E oE o ZO Z CI CQ 0 C to CI p okO E o U U S Z 3 bD c I C 1 1 rIJ 0 0 1 1 Z f4 U fi u a to Z C 0 5 E...

Page 310: ...e z C C C E ii ii ii g i i c 00 i Q1 tII c Q 03 w rn 0 3C 0 3C a 0 3 g 0 w w E E f 0 z o rn A C1 C1 rn I o o O DQ P C P rn t i rn 03 s 0 0 0 0 03 z o o rn fig j iO 0 3 c 0 3 c 0 3 w Z 0 0 ii n t E s...

Page 311: ...Z e 0 0 0 0 m E i fo z Eo 0 Q c Z e s o e mm m o s 0 9 9 9 0 e s II o 00 0 i m Vv v S Z 0 00 fj Q f z N Z Z 2 91 4 0 g g OJ tO 1I o8 00 Q j aQ Q 0 II r 0 0 S z 0 Eo Q m rl 0 s I s z d 0 8 g Z IC S Q s...

Page 312: ...t j 1 0 e S I 0 0 0 co rIJ S S Z g C Z Z nco g2 9 I a m g r 0 I I a 0 rll 8 S E 0 I s D Q I C ciQ z Q1 0 Q toj e rIJ j g t Z 0 00 1 0 0 2 O e oZ co S a a 8 rft Ss m v I rIJ tojS D n S o 0 g a s g a O...

Page 313: ...m 0 Q oS ro i 8 e e I1J Z S f I1J 8 e i I 11J 11J 1 5 g o or 1 m 0 1 O g E C I 0 0 c CX O Z Q pO V P I1J m C J CL oS s D Q Q 0 V I I1J E 0 0 5 0 0 7 100 o 0 Q i 5 Z o 1 M M 0 0 I1J i E t t 00 8 E E o...

Page 314: ...g 00 d E 03 0 0 s s r I t 190 g S s a s z Q1 5 C f Z t c ot e ot o t t ZZ 0 0 _ 0 0 0 0 0 3 3 0 O I o colJl o 2 g 33 g 00 oo b os 0 3 z 0 0 0 0 8 as rIJ co CO COco co O co 3o C 3 3 i 0 co S 8 i 0 0 00...

Page 315: ...OJ 0 Q 0 e g Q oJ t 0 0 Z e OJ 00 to OJ 0 A Z 2 E 0 w 0 0 OJ 0 0 a 0 oJ OJ oJ g oJ OJ r M 0 Co oJ I 0 0 w e Co t 0 bo g 0 0 0 Co l rn oJ e bo 0 t c 5 Q Co S e Z gE z8 J 2 s 0 kQ 0 0 l t Z 16 rl 0 8 1...

Page 316: ...N AL B SECTION 8 3 TEST SHEETS Replace the Figure of the page 19 with the following Figure 430 420 rpm 00 i 80 ji c 80 i Z Z t 340 OJ S g S 320 50 40 30 20 a 10 t u 8 0 rn 100 20 0 Z 30 E t 40 00 350...

Page 317: ...ENTARY FLIGHT MANUAL z 30 0 Q E E 1 a 20 E a 0 P m 2 Po 5 00 g z Po AI 80 t Q II 11 Z cn 4 I 0 CD 0 60 E 4 0 U 40 320 50 40 30 E 0 11 20 0 u u j 10 00 I 0 10 0 Z 20 E I 0 30 t 40 00 N 35083 8 3 98 46...

Page 318: ...2 S E bO E E E 8 0 1n 5 In In 0 Z z Z 0 i 0 a a U o _ E o b8 c H 0 Q g bO 0 0 o oot o w bO bO bO 00 So fi 0 n e g g E t U E t U E t U Q CIS InQ InQ In r 1 0 ICIS I I 00 8 E i1 E i1 E Qj m U 0 1 3 In r...

Page 319: ...I oo r tIJ o 0 tIJ r 1 Eo C I CQ Z 0 o 0 0 0 tIJ u r LO IQ IQ IQ e cZ e Q O 0 E t t t t O 0 0 0 OOQ 0 0000 gt t o 000000 p OO tIJ i9 Z O 000 U OQ tIJ S Q Z if U 01 P g 0 0 tJ 1 r_ tJ 0 A 0 z r l tj E...

Page 320: ...S FLIGHTS 1 1 General This inspection is to be performed once only either after the last flight of the day or before the first flight of the next day of flying The inspection associated with the day...

Page 321: ...cracks Cabin access door Security and correctly locked Pitot heads and static vents Fit blanking covers if necessary STATION2 LH baggage compartment door Condition security open all objects tied down...

Page 322: ...on Star No delamination splinters Star recesses No cracks Spherical thrust bearings and frequency adapters No elastomer faults unbonding scratches blisters extrusion cracks 2 layer frequency adapter C...

Page 323: ...partment door Security closing STATION3 Horizontal stabilizer fin tail bumper Security condition TGB Oil level no leaks Tail rotor guard if fitted Security condition STATION4 TGB Security by applying...

Page 324: ...R that no teflon material has R squeezed out R that the ball shows no signs R or burnishing or scoring R Figure 3 0 0 Q A BALANCEARM HINGE Flapping hinge bearing according to type Type 1 cups on eith...

Page 325: ...em Security no leaks lines Hydraulic reservoir Check fluid level security R tightness R Engine oil tank system Oil level security tightness Engine oil cooler Security no leaks Universal joint assembly...

Page 326: ...y a check after the last flight of the day These checks consist in performing a visual examination of each optional equipment item in order to check its aeneral condition and security on the aircraft...

Page 327: ...sing the hoist operator s grip During the UP order check that the GREEN light is EXTINGUISHED the REDlight is EXTINGUISHED Maintain the up order on the hoist operator s grip and press the test push bu...

Page 328: ...altitude over the sea wash the inflation cylinders and the cradle assemblies 2 3 CROP SPRAYING INSTALLATION R This optional equipment requires the presence of qualified staff to perform the daily ope...

Page 329: ...smission assemblies and cabin be effected before take off although the helicopter is capable of carrying Dut engine start up and rotor spinning at temperatures down to 40 C During the preheating opera...

Page 330: ...o controls and the rotor head spring antivibrator Power plant Remove the air intake cover and the exhaust nozzle blank after removing snow from the aircraft surface Remove snow and ice accretion in th...

Page 331: ...ON8 4 1 are to be c leted by the following actions Inspection of the engine magnetic plugs should be performed within 30 min after the rotor has stopped rotating in order to avoid seal damaging Care m...

Page 332: ...ERMANN HAILERS OP 2480 9 2 EMERGENCY LOCATORTRANSMITTERS R 9 3 SCHERMULYFLARES 8 9 4 AIR AMBULANCEINSTALLATION 9 5 SWIVELLING LANDING LIGHT 9 6 RETRACTABLESWIVELLING LANDING LIGHT 9 7 SEARCHLIGHT 9 8...

Page 333: ...e data is negligible 2 DESCRIPTION The system ma nly cons sts of co two amplifiers located in the LH side baggage hold four hailers mounted in pairs on the landing gear rear cross beam one microphone...

Page 334: ...re and is located inside the rear luggage bay A beacon location label is attached to the outside of the aircraft A control switch is fitted underneath the instrument panel on the pilot s side An anten...

Page 335: ...oact detector reset New aeneration locator beacon NG Select the locator switch to OFFjRST hold it in this position for 2 to 3 seconds then select it back to AUTO Old aeneration locator beacon The impa...

Page 336: ...ar cargo hold An external label indicating transmitter location An AUTO MANU control switch located under the instrument panel on the pilot s side An AUTO TEST RESET pushbutton located next to the con...

Page 337: ...witch is set to the AUTO position The red XMIT ALERT light comes on during transmitter operation Resettina the inlJact detector Control switch set to AUTO I Press the AUTOTEST RESET pushbutton I The t...

Page 338: ...m A label fitted close to the switch reads EMERGENCY LOCATOR TRANSMITTER FOR AVIATION EMERGENCY USE ONLY 3 3 1 Pre fliaht Insoection On the instrument panel check that remote control switch is set to...

Page 339: ...control switch ON for two seconds or the transmitter selector to OFF Re select the switch to ARM 4 2 ManualODeration The unit may be actuated manually by setting the switch to ON 4 3 Portable ODeratio...

Page 340: ...itted with ARM ON OFF switch An antenna located inthe uppersection of the intermediatestructure A remote control switch locatedin instrumentpanel 1 2 3 a a N ON ARMED g TEST RESET REMOTE CONTROL PANEL...

Page 341: ...Hz to ensure that the emergency locator transmitter has not accidentally been switched on 4 OPERATING PROCEDURE 4 1 Automatic Ooeration The transmitter is actuated automatically in the event of an imp...

Page 342: ...ton situated on the control a firing push button on the pilot s cyclic control grip The firing circuit is protected by a fuse situated on the control console fuse panel 3 OPERATINGINSTRUCTIONS The max...

Page 343: ...CRIPTION Fitting out in the air ant ulance role involves removing the copilot S seat the dual controls and if necessary the rear left hand bench seat The lower stretcher 6 rests on the cabin floor it...

Page 344: ...ntJulance duty versiDn requires a numberof preliminary cabin alterations 3 1 1 Lower Stretcher Remove dual controls copilot s seat seat cushions from L H rear passenger seat Fold up L H rear passenger...

Page 345: ...tcher on the cabin floor Set the upper stretcher on the support post Engage the rear handles of the stretchers in the brackets on the rear bulkhead Secure the retaining straps and hooks at the front a...

Page 346: ...2 TROL The controls of the swivelling landing light are located on the pilot s collective pitch lever handgrip assenbly AnON OFFswitch is used to control the lighting which is confirmed by the illumi...

Page 347: ...lever handgrip assembly R An ON OFF switch is used to control the lighting which is confirmed by the illumination of an indicator light on the instrument panel or on the warning Caution Advisory pane...

Page 348: ...A 450 W power light Detail A secured to the bottom forward LH side of the lower structure forward LH side comprising a glass dome 3 a swivelling parabolic reflector 4 a fixed arc lamp 5 a housing 2 a...

Page 349: ...n Th s s connrmed by the ll inat on of the anmer indicat or light A four way button 7 s used to operate the reflector for orientating the l ght beamin the des red direction To prevent any premature da...

Page 350: ...o the pads via clamps SEFA skis have a glass fiber resin laminate structure and SURFAIR skis have a metal structure The rear spatula of the ski is reinforced with one or twO struts SURFAIR skis enable...

Page 351: ...UNCTION 1 Rocker switch OFF neutral Stops system operation FAN engaged Switches on ventilation AjC engaged Switches on ventilation and air conditioning 2 Rocker switch LOW neutral Slow ventilation HI...

Page 352: ...ended to close the external ventilation flap when R using the system in the air conditioning mode to get a better R efficiency R System shutdown Set rocker switch 1 to OFF neutral position Should the...

Page 353: ...DITION ANCE DATA CONTENTS 10 1 BASIC PERFORMANCE DATA 10 2 EFFECT OF EQUIPMENTITEMS ON PERFORMANCE DATA 10 3 PERFORMANCE DATA WITH SANS FILTER INSTALLED AND PROTECTIONOF THE R AIR INTAKE AGAINST INDUC...

Page 354: ...ECTED WEIGHT 1 TAS CAS IN FAST CRUISE 2 TAS CAS IN RECOMMENDED CRUISE 3 FUEL CONSUMPTION RANGE IN FAST CRUISE 4 FUEL CONSUMPTION ENDURANCE IN RECOMMENDED CRUISE 5 RANGE IN RECOMMENDED CRUISE 6 FUEL CO...

Page 355: ...ORRECTED WEIGHT TO DETERMINE SPEEDS on facing page lbx100 36 38 40 42 44 46 48 49 6 52 54 56 57 3 60 61 7 I I I 0 0 0 I 40 30 20 10 0 10 20 30 40 2000 2500 3000 OAT OC CORRECTED WEIGHT kg EXAMPLE OAT...

Page 356: ...COMSUMPTION 50 A TAS CAS IN FAST CRUISE 40 30 20 10 0 10 20 OAT rC glO 1 0 110 120 130 l klt 150 0 0 1 m 220 240 260 280 I I I I I I I I I w 70 80 gO 100 110 120 130 kt 150 CAS EXAMPLE OAT 15 C CORREC...

Page 357: ...b CORRECTED WEIGHT TO DETERMINE SPEEDS on facing page 32 34 lbx100 36 38 40 42 44 46 48 49 6 52 54 56 57 3 60 61 7 0 0 40 30 20 10 0 10 20 30 40 2000 2500 3000 OAT OC CORRECTED WEIGHT kg EXAMPLE OAT 1...

Page 358: ...THE UPPER LH PRESSURE AlTITUOE CURVES TA A RECOMMENDED CRUISE m I I I I I I I OAT C 90 100 110 120 130 kt TAS g ci w II 120 140 160 180 200 220 km h 260 OD I 1 I I I I I I I 60 70 80 90 100 110 120 1...

Page 359: ...GE IN FAST CRUISE kg h Ib h 18 8 16 6 350 14 4 300 12 2 250 10 100 200 8 80 0 4 0 5 0 6 0 7 0 8 g km 0 8 11 2 1 4 1 6 k9 NM I II I I 2 2 3 3 5 lb NM CONS SPEED 1000 NM km 500 80 400 w 60 300 40 200 0...

Page 360: ...O 1 2 0 6 240 1 1 2 5 II 2 0 260 1 0 5 2 0 9 0 8 0 4 0 7 1 5 0 3 0 6 50 Q 40 30 0 20 7 I 10 0 0 p 10 20 I 30 48 5 w 4 Z 3 c 0 C 2 0 Z 1 w 0 70 80 90 100 110 120 130 140 150 kg h I I I I I I I I I I I...

Page 361: ...t 0 0 1600 g 3500 u 0 r J 1400 I I 0 0 2 0 1 0 0 0 0 0 x 6 x 2 E Co 8 Co I I 10 3 12 ISA 20 WEIGHT UU Kg 2000 kg 1800 kg ISA 10 STD ISA 0 0 tttfJI ISA 10 Q w Q m ISA 20 0 100 200 300 400 500 600 700 8...

Page 362: ...AT MINIMUM HOURLY FUEL CONSUMPTION 35 70 40 80 4 90 5 U C UJ t 1 100 5 6 110 4 OAT C 12 60 tt 240 10 220 01 9 200 J I C ai ai Z 8 180 Z 0 0 t t 160 J7 J a a 140 06 0 0 J J 120 5 100 4 0 ENDURANCE h EX...

Page 363: ...COMPLEMENTARY FLIGHT MANUAL B RR 48 SUPERSEDES RR 4A SECTION10 2 EFFECTOF EOUIPEMNT ITEMS ON PERFORMANCE DATA Disregard the information given in RR 4A 35063 10 2 02 18 Page 1 RR...

Page 364: ...MENTITEMS ON PERFORMANCE DATA description table by the following i Fast cruise Recommended cruise Equlpment installed Airspeed fuel Range Airspeed fuel Range km h kt con sump km h kt consump tion tion...

Page 365: ...xceeding t4 limitations Heating and demisting 8 4 4 4 8 4 4 4 systems within t4 limitations Electrical 4 2 1 2 2 2 consuR1 tion 50 A High landing gear 4 2 1 5 4 2 1 5 Skis 2 1 1 2 1 1 Electric hoist 6...

Page 366: ...SUMPTION RANGE I FAST CRUISE 4 FUEL CONSUMPTION ENDURANCE IN RECOMMENDED CRUISE 5 RANGE IN RECOMMENDED CRUISE 6 2 SAND FILTER OPERATING The level flight performances are modified as follow 2 1 In TorQ...

Page 367: ...OADS 2250 kg 4961Ib FOR DETERMINING THE SPEEDS using the graph opposite I 32 34 lbx100 36 38 40 42 44 46 48 49 6 2 4 6 7 3 0 1 7 0 0 0 0 20 10 0 10 20 30 40 3500 OAT C CORRECTED WEIGHT kg EXAM PLE OAT...

Page 368: ...ING OR TAS CAS PROTECTION AGAINST INDUCTION OF SNOW IN FAST CRUISE 10 0 10 OAT rC 9 0 100 1 0 1 0 130 l O TAS 1 O Q Q a m 120 1m 200 240 km h 280 f I I I I I I I 80 100 120 140 kt W CAS EXAMPLE OAT 1S...

Page 369: ...2250 kg 4961Ib FOR DETERMINING THE SPEEDS using the graph opposite 32 34 lbx100 36 38 40 42 44 46 48 49 6 52 54 56 57 3 60 61 7 0 0 0 40 30 20 10 0 10 20 30 40 3500 OAT C CORRECTED WEIGHT kg EXAMPLE...

Page 370: ...ION OF SNOW TAS CAS IN RECOMMENDED CRUISE 10 0 10 20 30 40 50 16 I 8 I I 2 2 0 2F OAT rC 90 100 110 1120 130 kI 140 TA 0 O t 0 0 c w m 160 18 m 180 200 220 240 260 I I I I I I I I I 60 70 80 90 100 11...

Page 371: ...SE kg h 80 b h 6 350 u z 0 U 140 300 2 0 I 250 0 200 80 150 60 30 40 500 4 0 5 0 6 0 7 0 8 0 9 1 kg km OAT OC 0 8 I I 1 2 I 1 4 I 1 6 I 1 8 kg kt I I I I I 2 2 5 3 3 5 4 lb NM NM 1000 I CONS SPEED 500...

Page 372: ...kg km kg NM lb NM 0 9 3 5 0 8 3 c 0 7 w 0 6 2 5 0 5 S I l 2 0 U 0 4 1 5 50 40 30 20 10 U 0 I Q t 10 0 20 30 40 _6 5 w 4 0 3 0 a 2 c u w z 1 w u O 70 80 90 100 110 120 130 140 150 160 kg h I I I I I 15...

Page 373: ...0 l 4000 Jo IIJ 0 Ii IQ 1600 0 3500 0 0 1400 I 0 0 2000 m 1000 4000 6000 2000 8000 10000 3000 12000 20 t WEIGHT 10 2200 kg ff33s 2000 kg a 1800 kg 0 LU Z a C cn 10 0 OF Q w Q 200 100 200 300 400 500 6...

Page 374: ...R spider bearing plate assembly inspection 100 hrs AD 84 064 037 B R3 Insp of T R spar without disassembly IAW SB 05 11R5 100 hrs AD T2001 640 089 A Insp of T R Blade trailing edge IAW Alert Telex 05...

Page 375: ...ssembly IAW SB 05 11R5 500 hrs AD 85 135 042 B Check that FUEL is engraved on A F fuel filter every time the filter is replaced IAW SB 01 14 N A to AVO 500 hrs AD 86 097 047 B A F fuel filter bowl tig...

Page 376: ...reKI is thecoefficientfromtable1 colTesponding to themaximumNgreachedduringthe flight and K2 is the coefficientfromtable2 colTesponding to theMinimum Ngreachedatorbelow85 duringtheflight TABLE TABLE 2...

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