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05-21 Time, Fuel and Distance to Climb 1600 kg

Description

Time, Fuel and Distance to Climb - 1600 kg / 3527 lb

Flaps:

Power:

90%, max. 2300 RPM

Airspeed:

94 KIAS

Gear:

retracted

Press. Alt.

[ft] / [m]

OAT

TAS

RoC

Time

Fuel

Distance

[°C]

[°F]

[kt]

[ft/min]

[m/s]

[min]

[US gal]

[NM]

1075

5.5

2000

610

1070

5.4

0.5

4000

1219

1070

5.4

6000

1829

1065

5.4

1.5

8000

2438

-1

1065

5.4

10000

3048

-5

1060

5.3

2.5

12000

3658

-9

100

1045

5.3

14000

4267

-13

102

1025

5.2

3.5

16000

4877

-17

104

1000

18000

5486

-21

-5

105

960

4.8

4.6

20000

6096

-25

-12

107

910

4.6

5.3

AFM DA 50 C

Doc No.: 9.01.01-E

Issue : 011

DA50-A-15-62-01-00A-040A-D

Page 05-35

14-Dec-2022

Содержание DA 50 C

Страница 1: ...26 Aug 2020 This Airplane Flight Manual has been approved by EASA under type certificate No EASA A 639 This Airplane Flight Manual is approved in accordance with 14 CFR Section 21 29 for U S register...

Страница 2: ...Engine Instrument Markings Description 02 7 02 06 Mass Weight Description 02 8 02 07 Center of Gravity Description 02 9 02 08 Approved Maneuvres Attitudes and Flight Conditions Description 02 10 02 0...

Страница 3: ...e Failures 03 16 Engine Failure during Take Off Emergency operation procedure 03 23 03 17 Engine Failures on Ground Emergency operation procedure 03 24 03 18 Engine Failure in Flight Emergency operati...

Страница 4: ...ction Failure Emergency operation procedure 03 56 03A Abnormal Operating Procedures 03A 1 Airplane Related CAS Cautions 03A 01 Airplane related G1000 Caution Messages Emergency operation procedure 03A...

Страница 5: ...pection Cabin Check Pre operation procedure 04 9 04 06 Pre Flight Inspection Walk Around Check Pre operation procedure 04 13 04 07 Before Starting Engine Pre operation procedure 04 18 04 08 Starting E...

Страница 6: ...g Description 05 16 05 10 Take Off Distance 1600 kg Description 05 19 Climb Performance Take Off Climb 05 11 Climb Performance Take Off Climb Description 05 23 05 12 Climb Performance Take Off Climb 1...

Страница 7: ...rformance 1600 kg Description 05 60 Glide 05 35 Glide Description 05 62 Approved Noise Data 05 36 Approved Noise Data Description 05 64 06 Mass and Balance Equipment 06 1 Mass and Balance 06 01 Genera...

Страница 8: ...n 07 31 07 18 Egress Hammer Description 07 34 07 19 Heating and Ventilation Description 07 35 Powerplant 07 20 Engine General Description 07 38 07 21 Propeller Description 07 39 07 22 Propeller Contro...

Страница 9: ...ion 07 89 Baggage Compartment 07 46 Baggage Compartment Description 07 91 07 47 Trim Weight Description 07 96 08 Airplane Handling Care and Maintenance 08 1 General 08 01 General Description 08 3 08 0...

Страница 10: ...Subject Page 09 01 Supplements Description 09 2 AFM DA 50 C Doc No 9 01 01 E Issue 011 Page ix 14 Dec 2022...

Страница 11: ...nter of Gravity Description DA50 A 15 10 00 07A 040A D 13 12 2022 Approved Maneuvres Attitudes and Flight Conditions Description DA50 A 15 10 00 08A 040A D 28 05 2021 Maneuvring Load Factors Descripti...

Страница 12: ...D 09 09 2021 Engine Failures on Ground Emergency operation procedure DA50 A 15 45 00 00A 141A D 28 05 2021 Engine Failure in Flight Emergency operation procedure DA50 A 15 45 01 02A 141A D 28 05 2021...

Страница 13: ...tion Messages Emergency operation procedure DA50 A 15 49 01 00A 141A D 18 05 2022 ALTN 1 FAIL Special operation DA50 A 15 52 04 01A 161A D 26 08 2020 ALTN 2 FAIL Special operation DA50 A 15 52 04 02A...

Страница 14: ...21A D 09 09 2021 Starting Engine Pre operation procedure DA50 A 15 33 00 04A 121A D 28 05 2021 Before Taxiing Pre operation procedure DA50 A 15 33 00 06A 121A D 15 07 2021 Taxiing Pre operation proced...

Страница 15: ...g Description DA50 A 15 62 02 01A 040A D 06 05 2022 Climb Performance Take Off Climb 1800 kg Description DA50 A 15 62 02 02A 040A D 06 05 2022 Climb Performance Take Off Climb 1600 kg Description DA50...

Страница 16: ...040A D 28 05 2021 Equipment Description DA50 A 15 82 00 00A 040A D 29 08 2022 Airframe Description DA50 A 51 00 00 99A 040A D 26 08 2020 Flight Controls Description DA50 A 27 00 00 99A 040A D 26 08 2...

Страница 17: ...2020 Multi Function Display MFD Description DA50 A 31 40 99 02A 040A D 28 05 2021 Audio Panel Description DA50 A 31 40 99 03A 040A D 26 08 2020 Attitude and Heading Reference System AHRS Description...

Страница 18: ...DA50 A 15 37 02 03A 040A D 26 08 2020 Cleaning and Care Description DA50 A 15 37 03 00A 040A D 28 05 2021 Cleaning the Aircraft from Ice and Snow Description DA50 A 15 37 04 00A 040A D 08 06 2022 Sup...

Страница 19: ...nal Standard Atmosphere 05 7 2 Wind Components 05 9 Climb Performance Take Off Climb 1 Gradient Formula 05 23 Climb Performance Cruise Climb 1 Gradient Formula 05 28 Go Around Climb Performance 1 Grad...

Страница 20: ...System 1 Fuel System 07 53 2 Schematic Normal Fuel Supply 07 56 3 Schematic Emergency Fuel Supply 07 57 4 Fuel Level Check Tool 07 62 5 Fuel Level Check Tool on Wing 07 63 Electrical Systems 1 Electr...

Страница 21: ...00 FRONT MATTER AFM DA 50 C Front Matter Doc No 9 01 01 E Issue 011 00 Page 00 1 14 Dec 2022...

Страница 22: ...SON FLIGHTS DURING THE NIGHT ON TOP UNDER INSTRUMENT METEOROLOGICAL CONDITIONS IMC OR ABOVE TERRAIN WHICH IS UNSUITABLE FOR A LANDING CONSTITUTE A RISK IT IS THEREFORE HIGHLY RECOMMENDED TO SELECT FLI...

Страница 23: ...pe expansion 50 065 9 01 01 E AFM Rev 1 50 072 Emergency Exit at PAX 50 099 AFM Ground Idle Flight Idle O M 50 014 Sun Visor 50 018 Installation of Armrest with Integrated Key Pad 50 020 Tablet Mount...

Страница 24: ...he technical content of Issue 3 has been approved under the authority of the DOA ref EASA 21J 052 Issue date 15 Jul 2021 4 Issue 4 Following changes are incorporated in Issue 4 Change Title M M 50 135...

Страница 25: ...DOA ref EASA 21J 052 Issue date 09 Sep 2021 6 Issue 6 Following changes are incorporated in Issue 6 Change Title M M 50 133 Trim Mass in Ventral Fin 50 157 AFM Doc No 9 01 01 E Issue 6 O M 50 001 Oxyg...

Страница 26: ...27 Jan 2022 8 Issue 8 Following changes are incorporated in Issue 8 Change Title M M 50 140 Garmin GMU 44B 50 188 Recording of Oxygen System Components 50 191 Climb Performance 50 200 AFM Doc No 9 01...

Страница 27: ...052 Issue date 14 Jun 2022 10 Issue 10 Following changes are incorporated in Issue 10 Change Title M M 50 138 Gust Lock Provisions 50 201 Emergency Exit Unauthorized Entry Protection Information 50 2...

Страница 28: ...dation of Limitation Placard 50 282 AFM Doc No 9 01 01 E Issue 11 O M 50 002 g RACC III Installation 50 011 n Ice Protection System TKS 50 048 GDC72 New Part Number Table 10 Issue 11 Changes The techn...

Страница 29: ...01 GENERAL AFM DA 50 C General Doc No 9 01 01 E Issue 011 01 Page 01 1 14 Dec 2022...

Страница 30: ...spective equipment and modification level The exact equipment of your serial number is recorded in section 06 10 Equipment Description The modification level is recorded in the following table as far...

Страница 31: ...ESPONDING PROCEDURE LEADS TO A MINOR OR TO A MORE OR LESS LONG TERM DEGRADATION IN FLIGHT SAFETY NOTE Draws the attention to any special item not directly related to safety but which is important or u...

Страница 32: ...ft Dihedral 5 5 Aspect ratio 11 0 Leading edge sweep back 1 MAC 1 274 m 4 18 ft Geometrical twist 2 2 Flaps Span 2 x 4 210 m 13 81 ft Area 2 x 1 385 m 14 91 ft Aileron Span 2 x 1 669 m 5 48 ft Area 2...

Страница 33: ...a incl rudder trim tab 0 049 m 0 53 ft Landing Gear Wheel track 2 87 m 9 41 ft Wheel base unloaded 2 77 m 9 08 ft Main Wheel Tire 6 00 6 for details refer to AMM Tire inflation pressure unloaded 3 8 b...

Страница 34: ...Maximum Landing Gear Operating Speed for Retraction This speed may not be exceeded during the retraction of the landing gear vNE Never Exceed Speed in smooth air This speed must not be exceeded in an...

Страница 35: ...maneuverability for take off and landing has been demonstrated during type certification MET Weather weather advice NAV Navigation route planning RoC Rate of Climb Mass and Balance CG Center of Gravit...

Страница 36: ...and NAV Receiver No 1 ADC Air Data Computer ENG INST Engine Instruments XPDR Transponder FLAPS Flap System PITOT Pitot Heating System LANDING Landing Light FLOOD Flood Light GEAR WARN Landing Gear An...

Страница 37: ...2 AUDIO Audio Panel AFCS ESP Auto Pilot System DME Distance Measuring Equipment TWX Lightning Detection System DATA LINK Data Link System For the engine ECU A Engine Control Unit A ECU B Engine Contro...

Страница 38: ...ath Loss LNAV V Lateral Navigation with Advisory Vertical Guidance LNAV VNAV Lateral Navigation Vertical Navigation LPV Localizer Performance with Vertical Guidance MAC Mean Aerodynamical Chord MSAS M...

Страница 39: ...9 mph m s x 196 85 fpm fpm 196 85 m s Speed of rotation RPM revolutions per minute Mass kg kilograms lb pounds kg x 2 2046 lb Force weight N newtons lbf pounds force N x 0 2248 lbf Pressure hPa hectop...

Страница 40: ...68 1 60 15 9 20 75 7 70 18 5 22 83 3 80 21 1 24 90 9 90 23 8 26 98 4 100 26 4 28 106 0 110 29 1 30 113 6 120 31 7 32 121 1 130 34 3 34 128 7 140 37 0 36 136 3 150 39 6 38 143 8 160 42 3 40 151 4 170...

Страница 41: ...01 06 Three View Drawing Description 1 Three View Drawing Figure 1 Three View Drawing AFM DA 50 C General Doc No 9 01 01 E Issue 011 DA50 A 06 00 00 01A 040A D 01 Page 01 13 14 Dec 2022...

Страница 42: ...of a Satellite Based Augmentation System complying with ICAO Annex 10 for IFR en route terminal area non precision approach and approach procedures with vertical guidance operation The G1000 NXi Integ...

Страница 43: ...y of its aviation databases Pilots and operators can view the LOA status and RTCA DO 200A List of Applicable Avionics 190 01999 00 at www FlyGarmin com Aviation Databases Type 2 LOA Status Navigation...

Страница 44: ...02 OPERATING LIMITATIONS AFM DA 50 C Operating Limitations Doc No 9 01 01 E Issue 011 02 Page 02 1 14 Dec 2022...

Страница 45: ...PERMISSIBLE Chapter 2 of this Airplane Flight Manual includes operating limitations instrument markings and placards necessary for the safe operation of the airplane its power plant standard systems...

Страница 46: ...s speed except in smooth air and then only with caution vNE Never exceed speed in smooth air 191 KIAS Do not exceed this speed in any operation vLO Max landing gear operating speed normal operation 16...

Страница 47: ...ting range with flaps fully extended Green arc 72 152 Normal operating range Yellow arc 152 191 Caution range only in smooth air Red line 191 Never exceed speed in smooth air Table 1 Airspeed Indicato...

Страница 48: ...r mt Propeller Type MTV 12 D 210 56 Diameter 2 10 m 4 Propeller RPM Maximum take off 2340 RPM Maximum continuous 2300 RPM Maximum overspeed up to 20 s 2500 RPM 5 Oil pressure Minimum 2 0 bar Minimum a...

Страница 49: ...p 60 C 12 Oil specification AeroShell Oil Diesel Ultra 13 Gearbox oil specification CENTURION Gearbox Oil N1 14 Engine starting temperature Minimum 25 C 15 Maximum restart altitude Maximum restart alt...

Страница 50: ...ure below 25 C 25 to 50 C 50 to 115 C 115 to 125 C above 125 C Coolant tempera ture below 25 C 25 to 60 C 60 to 101 C 101 to 105 C above 105 C Gearbox tempera ture below 25 C 25 to 50 C 50 to 105 C 10...

Страница 51: ...Area B of baggage compartment 35 kg 77 lb Max load in Compartment C of baggage compartment 10 kg 22 lb Max load in Compartment D of baggage compartment 5 kg 11 lb Table 1 Mass Weight NOTE In some cou...

Страница 52: ...tum plane at 1480 kg increasing linearly to see next row 2 458 m aft of datum plane at 1645 kg increasing linearly to see next row 2 47 m aft of datum plane at 1999 kg Flight Mass kg 1350 1 00 4 1 50...

Страница 53: ...NEUVERS ARE NOT PERMITTED The airplane is certified in the Normal Category in accordance with CS 23 Approved Maneuvers All normal flight maneuvers Stalling with the exception of dynamic stalling and L...

Страница 54: ...D FACTORS WILL LEAD TO AN OVERSTRESSING OF THE AIRPLANE CAUTION INTENTIONAL NEGATIVE G MANEUVERS ARE NOT PERMITTED at vO at vNE with flaps in T O or LDG position Positive 3 8 3 8 2 0 Negative 1 52 0 0...

Страница 55: ...ating altitude is 20 000 ft 6 096 m pressure altitude NOTE Additional altitude restrictions based on operational requirements for supplemental oxygen may apply AFM DA 50 C Operating Limitations Doc No...

Страница 56: ...Crew Description 1 Flight Crew Minimum crew 1 one person Maximum number of occupants 5 five persons AFM DA 50 C Operating Limitations Doc No 9 01 01 E Issue 011 DA50 A 15 10 00 11A 040A D 02 Page 02 1...

Страница 57: ...national operating rules and also depends on the route to be flown NOTE Many of the items of minimum equipment listed in the following table are integrated in the G1000 NXi For daytime VFR flights In...

Страница 58: ...hts Strobe lights anti collision lights Landing light Instrument lighting Flood light Flashlight Other oper ational min imum equipment Stall warning system Safety belts for each oc cupied seat Airplan...

Страница 59: ...vant for the DA 50 C airplane are shown below A list of all placards is included in the Airplane Maintenance Manual latest revision Chapter 11 Figure 2 Limitation Placards 1 AFM DA 50 C Operating Limi...

Страница 60: ...he Emergency Landing Gear Extension Lever max usable fuel LH Main Tank 25 0 US gal RH Aux Tank 24 0 US gal max difference LH RH tank 9 US gal vLE vLO 162 KIAS Figure 3 Limitation Placards 2 AFM DA 50...

Страница 61: ...Cowling WARNING JET A 1 APPROVED FUEL or see Airplane Flight Manual Engine Oil AeroShell Oil Diesel Ultra Figure 4 Limitation Placards 3 AFM DA 50 C Operating Limitations Doc No 9 01 01 E Issue 011 DA...

Страница 62: ...Figure 5 Limitation Placards 4 AFM DA 50 C Operating Limitations Doc No 9 01 01 E Issue 011 DA50 A 11 30 00 99A 040A D 02 Page 02 19 14 Dec 2022...

Страница 63: ...Figure 6 Limitation Placards 5 AFM DA 50 C Operating Limitations Doc No 9 01 01 E Issue 011 DA50 A 11 30 00 99A 040A D 02 Page 02 20 14 Dec 2022...

Страница 64: ...Figure 7 Limitation Placards 6 Figure 8 Limitation Placards 5 AFM DA 50 C Operating Limitations Doc No 9 01 01 E Issue 011 DA50 A 11 30 00 99A 040A D 02 Page 02 21 14 Dec 2022...

Страница 65: ...Figure 9 Limitation Placards 8 if Tablet Mount is installed AFM DA 50 C Operating Limitations Doc No 9 01 01 E Issue 011 DA50 A 11 30 00 99A 040A D 02 Page 02 22 14 Dec 2022...

Страница 66: ...D UNTIL THE DOSAGE IS WITHIN THE PERMITTED LIMITS NOTE The specified additives are qualified for the operation with the certified fuel designations To clean the fuel system of the airplane a higher do...

Страница 67: ...Additives The application of the following additive is permitted PRIST Hi Flash MIL DTL 85470 B ASTM D 4171 max 1500 ppm NOTE The instructions of the fuel additive supplier must be followed AFM DA 50...

Страница 68: ...to operation is not less than 25 C 13 F With the airplane cold soaked and its temperature below 20 C 4 F the use of an external pre heater for the engine and pilot compartment prior to operation is m...

Страница 69: ...an external power supply for engine starting with an empty airplane main battery is not permitted if the subsequent flight is intended to be a Night VFR or an IFR flight In this case the airplane main...

Страница 70: ...Locking Device The LH and RH crew doors and the passenger door must not be blocked by the key lock during operation of the airplane AFM DA 50 C Operating Limitations Doc No 9 01 01 E Issue 011 DA50 A...

Страница 71: ...ibility approaches is prohibited NOTE Refer to EASA AMC 20 25 or FAA AC 120 76A for the use of PED associated to electronic flight bag EFB operation The use of any device as an EFB may require separat...

Страница 72: ...02 19 Smoking Description 1 Smoking Smoking in the airplane is not permitted AFM DA 50 C Operating Limitations Doc No 9 01 01 E Issue 011 DA50 A 15 10 00 19A 040A D 02 Page 02 29 14 Dec 2022...

Страница 73: ...t database The GPS equipment database must incorporate the current update cycle 2 Accomplishment of ILS LOC LOC BC LDA SDF MLS or any other type of approach not approved for GPS overlay with the G1000...

Страница 74: ...de between longitude 70 W and 128 W Northern Canada North of 70 N latitude between longitude 85 E and 114 E Northern Russia South of 55 S latitude between longitude 120 E and 165 E Region south of Aus...

Страница 75: ...06 B0203 GMA1 GIA1 GMA1 GAI2 006 B0223 GRS1 GIA1 GRS1 GIA2 006 B0224 GMU1 006 B0319 PFD1 MFD1 006 B0328 006 B0329 006 C0048 GMU1 FPGA 006 C0049 GRS1 FPGA 006 C0055 GDC1 FPGA 006 D0159 GRS1 MV DB 006 D...

Страница 76: ...hat requires RNP 10 or RNP 4 capability If the Garmin WFDE Prediction program indicates fault exclusion FDE unavailability will exceed 34 minutes in accordance with FAA Order 8400 12A for RNP 10 requi...

Страница 77: ...com Support Contact Garmin Support Aviation Pilots and operators can view navigation data base alerts at www Garmin com In the Air NavData Alerts Both Garmin GPS navigation receivers must be operatin...

Страница 78: ...iate governing authority The navigation equipment required to join and fly an instrument approach procedure is indicated by the title of the procedure and notes on the IAP chart Use of the Garmin GPS...

Страница 79: ...iately available to the flight crew E ILS approaches using the autopilot flight director are limited to Category I approaches only F Autopilot maximum airspeed 185 KIAS Autopilot minimum airspeed 85 K...

Страница 80: ...03 EMERGENCY PROCEDURES AFM DA 50 C Doc No 9 01 01 E Issue 011 03 Page 03 1 14 Dec 2022...

Страница 81: ...EMERGENCY PROCEDURES GENERAL AFM DA 50 C Doc No 9 01 01 E Issue 011 03 Page 03 2 14 Dec 2022...

Страница 82: ...E CALMLY AND WITH DETERMINATION This Chapter contains checklists as well as the description of recommended procedures to be followed in the event of an emergency Engine failure or other airplane relat...

Страница 83: ...glide angle Flaps UP 94 Airspeed for emergency landing with engine off Flaps UP 94 Flaps T O 85 Flaps LDG 77 Emergency gear extension 102 Airspeed for Engine Restart windmilling 122 Table 1 Certain A...

Страница 84: ...ight emergency depressing and holding the Com transfer button on the G1000 for 2 seconds will tune the emergency frequency of 121 500 MHz If the display is available it will also show it in the Active...

Страница 85: ...AIRPLANE RELATED CAS WARNINGS AFM DA 50 C Doc No 9 01 01 E Issue 011 03 Page 03 6 14 Dec 2022...

Страница 86: ...r intake temperature is above 80 C See 03 15 ENG INTAKE Emer gency operation procedure ENG OIL TEMP Engine oil temperature is above 125 C See 03 08 ENG OIL TEMP Emergency operation procedure FUEL PRES...

Страница 87: ...n right fuel tank is above 60 C See 03 12 L R FUEL TEMP Emergency operation procedure REAR DOOR OPEN Rear door is not closed and locked See 03 11 Unlocked Doors Emergency operation procedure STARTER E...

Страница 88: ...ption of electrical power is too high Possible reasons are a fault in wiring or equipment A ENGINE SYSTEM DISPLAY select by pressing ENGINE softkey on MFD B Electrical equipment switch OFF as necessar...

Страница 89: ...OPPAGE AFTER THIS PERIOD OF TIME BE PREPARED FOR AN ENGINE FAILURE AND AN EMERGENCY LANDING A Circuit breakers all in If there is still no electrical power available B Landing Gear DOWN when down and...

Страница 90: ...message is not displayed it can be assumed that there is no technical defect in the cooling system and that the below mentioned procedure can decrease the temperature s If COOLANT LVL is NOT displaye...

Страница 91: ...If the coolant temperature does not return to the green range perform a precautionary landing on the nearest suitable airfield Prepare for an engine failure in accordance with 03 18 Engine Failure in...

Страница 92: ...Emergency operation procedure NOTE If high oil temperature is announced and the oil pressure indication is within the green range it can be assumed that there is no technical defect in the engine oil...

Страница 93: ...EMERGENCY FUEL PUMP switch ON If FUEL PRESS warning remains D FUEL valve EMERGENCY E EMERGENCY FUEL PUMP switch OFF If FUEL PRESS warning still remains F Imminent engine failure must be expected Prepa...

Страница 94: ...it can be assumed that there is no technical defect in the gearbox and that the below mentioned procedure will decrease the temperature s A POWER reduce B COWL FLAP open C Airspeed increase D GB OIL T...

Страница 95: ...40 KIAS E Land at next suitable airfield Rear Door Unlocked WARNING DO NOT TRY TO LOCK THE REAR DOOR IN FLIGHT THE SAFETY LATCH MAY DISENGAGE AND THE DOOR OPENS USUALLY THIS RESULTS IN A SEPARATION OF...

Страница 96: ...ities it can be assumed that the following procedure will decrease the temperature s A POWER reduce B COWL FLAP open C Airspeed increase D L FUEL TEMP R FUEL TEMP check for green range E If the fuel t...

Страница 97: ...quired C ENGINE MASTER OFF During flight Oil Pressure Low NOTE If the RPM indication is less than 1500 RPM with the power lever atFlight Idle FI the oil pressure must drop into the red range to cause...

Страница 98: ...atures If temperatures are not within green range J POWER reduce K Expect engine failure and prepare for an emergency landing without engine power in accordance with 03 41 Emergency Landing with Engin...

Страница 99: ...gine after starting Starter engaged warning STARTER illuminates after the engine has started On Ground A POWER lever Ground Idle GI B ENGINE MASTER OFF C ELECT MASTER OFF D Terminate flight preparatio...

Страница 100: ...for more than 30 seconds High engine intake temperatures leads to reduces power output A POWER reduce B COWL FLAP check open C Airspeed increase D Check if ENG INTAKE Warning reverts to Caution statu...

Страница 101: ...ENGINE FAILURES AFM DA 50 C Doc No 9 01 01 E Issue 011 03 Page 03 22 14 Dec 2022...

Страница 102: ...ead Continued Take Off G POWER lever check MAX H EMERGENCY FUEL PUMP switch check ON I FADEC switch FORCE B NOTE If selecting FORCE B does not solve the problem switch back to AUTO J ALTERNATE AIR OPE...

Страница 103: ...E CLEARED TAKE OFF IS PROHIBITED CAUTION IF THE OIL PRESSURE IS IN THE RED RANGE THE ENGINE MUST BE SHUT DOWN IMMEDIATELY NOTE If considered necessary the engine must be shut down Otherwise the cause...

Страница 104: ...quantity MAIN tank check G FUEL valve check NORMAL H EMERGENCY FUEL PUMP switch ON If in icing conditions visible moisture I ALTERNATE AIR ON If failure persists J POWER lever MAX K FUEL valve EMERGE...

Страница 105: ...he engine refer to 03 19 Restart Engine in Flight Emergency operation procedure If the remaining altitude is NOT sufficient for a restart attempt T Perform a precautionary landing on the nearest airfi...

Страница 106: ...PUMP switch ON H FADEC switch check AUTO I POWER lever Flight Idle FI J Airspeed 122 KIAS K ENGINE MASTER OFF ON L POWER lever move forward and check whether engine is producing thrust NOTE If necessa...

Страница 107: ...N METAL BLADES Oscillating RPM A POWER setting change If the Problem Does Not Clear B FADEC switch FORCE B If the Problem Does Not Clear C FADEC switch AUTO D Land on the nearest suitable airfield Pro...

Страница 108: ...nearest suitable airfield If an Increased Climb Gradient is Required N FLAPS T O position O Airspeed 79 KIAS P POWER lever as required do not exceed 2300 RPM Propeller Underspeed Q POWER lever as requ...

Страница 109: ...cowl flap position A Coolant temperature check The flight can be continued but coolant temperature has to be monitored It the coolant temperature becomes high follow the procedure according to 03 07...

Страница 110: ...the main fuel tank you may feed it from the auxiliary fuel tank by setting the FUEL valve to EMERGENCY F FUEL valve check ON EMERGENCY if required NOTE If the loss of power was due to unintentional s...

Страница 111: ...ot be restored by this procedure prepare for 03 18 Engine Failure in Flight Emergency operation procedure and land as soon as possible AFM DA 50 C Doc No 9 01 01 E Issue 011 DA50 A 15 45 01 00A 141A D...

Страница 112: ...LANDING GEAR SYSTEM FAILURES AFM DA 50 C Doc No 9 01 01 E Issue 011 03 Page 03 33 14 Dec 2022...

Страница 113: ...NOTE The landing gear should now extend by gravity spring force and relief of hydraulic pressure from the system If one or more landing gear indicator lights do not indicate the gear down and locked a...

Страница 114: ...on the side of the intact tire so that changes in direction which must be expected during roll out due to the braking action of the defective tire can be corrected on the runway C Land with one wing...

Страница 115: ...due to the greater rolling resistance WARNING IF SUFFICIENT TIME IS REMAINING THE RISK OF FIRE IN THE EVENT OF A COLLISION CAN BE REDUCED AS FOLLOWS AFTER A SAFE TOUCH DOWN A FUEL valve OFF B ENGINE M...

Страница 116: ...and at aft CG locations with flaps up and full power applied the airplane will easily recover from sideslip if the trim is set to neutral normal procedure Otherwise it may require corrective action w...

Страница 117: ...ime situation allows the following steps can help to reduce the risk of fire E ENGINE MASTER OFF F EMERGENCY FUEL PUMP switch check OFF G FUEL TRANS switch check OFF H FUEL valve OFF Touchdown I Touch...

Страница 118: ...FAILURES IN THE ELECTRICAL SYSTEM AFM DA 50 C Doc No 9 01 01 E Issue 011 03 Page 03 39 14 Dec 2022...

Страница 119: ...AL BUS ON C Electrical equipment switch OFF all equipment which is not needed D Land on the nearest suitable airfield Be prepared for an engine failure and an emergency landing in accordance with 03 4...

Страница 120: ...SMOKE AND FIRE AFM DA 50 C Doc No 9 01 01 E Issue 011 03 Page 03 41 14 Dec 2022...

Страница 121: ...on procedure 1 Engine Fire on Ground A ENGINE MASTER OFF B FUEL valve OFF C ELECT MASTER OFF After Standstill D Door open E Airplane evacuate immediately AFM DA 50 C Doc No 9 01 01 E Issue 011 DA50 A...

Страница 122: ...e on Ground A ELECT MASTER OFF If the Engine Is Running B POWER lever Ground Idle GI C ENGINE MASTER OFF D FUEL valve OFF lift and turn When the Engine Has Stopped E Door open F Airplane evacuate imme...

Страница 123: ...borted A POWER lever Ground Idle GI B ECS shut off PULL C Brakes apply bring the airplane to a stop D ENGINE MASTER OFF E FUEL valve OFF lift and turn F ELECT MASTER OFF After Standstill G Door open H...

Страница 124: ...MERGENCY OPERATION PROCEDURE A ECS shut off PULL B If possible fly along a short cut traffic circuit and land on the airfield After Climbing to a Height From Which the Selected Landing Area Can Be Rea...

Страница 125: ...ULATING AIR OFF FRESH AIR B ECS shut off PULL C Select appropriate emergency landing area D ENGINE MASTER OFF E FUEL valve OFF F ELECT MASTER OFF G Airspeed as required if possible select a faster air...

Страница 126: ...EXTINGUISHED WHETHER THE SMOKE HAS CLEARED OR NOT LAND IMMEDIATELY A AVIONIC MASTER OFF WARNING SWITCHING OFF THE ELECT MASTER WILL LEAD TO TOTAL FAILURE OF ALL ELECTRONIC AND ELECTRIC EQUIPMENT B ELE...

Страница 127: ...OTHER EMERGENCIES AFM DA 50 C Doc No 9 01 01 E Issue 011 03 Page 03 48 14 Dec 2022...

Страница 128: ...HEAT ON C Cabin heat ON D Cabin air DEFROST E POWER lever increase power in order to prevent ice build up on the propeller blades apply power changes periodically F ALTERNATE AIR OPEN G Alternate stat...

Страница 129: ...however usually together with flue gases it can be detected Increased concentration of carbon monoxide in closed spaces can be fatal The occurrence of CO in the cabin is possible only due to a defect...

Страница 130: ...eutral C Rudder full deflection against direction of spin D Elevator control stick forward When rotation has stopped E Rudder neutral F FLAPS UP G Elevator control stick pull carefully H Return the ai...

Страница 131: ...ft 300 m of altitude loss the maximum horizontal distance traveled in still air is 1 6 NM 3 0 km During this the propeller will continue to windmill A FLAPS UP B Gear UP C COWL FLAP CLOSED D Airspeed...

Страница 132: ...e 1 Emergency Descent A FLAPS UP WARNING MAX LANDING GEAR EXTENDED SPEED VLE VLO 162 KIAS B Airspeed not above 162 KIAS C Gear DOWN D POWER lever Flight Idle FI AFM DA 50 C Doc No 9 01 01 E Issue 011...

Страница 133: ...RH side of the PAX row The red release belt is located at the upper rear corner of the emergency exit window For activation follow instructions as placarded In case the emergency exit is blocked the...

Страница 134: ...TER OFF C PFD MFD control unit keypad if installed stowed D FUEL valve OFF E Airspeed Landing Gear Flaps as required Before touchdown F Belts and Harnesses fasten G Sun visors if installed locked in f...

Страница 135: ...OUT OF TRIM procedure below and expect residual control forces upon disconnect The autopilot will not re engage after disconnect with failed pitch trim If AUTOPILOT OUT OF TRIM ELE indication is pres...

Страница 136: ...03A ABNORMAL OPERATING PROCEDURES AFM DA 50 C Doc No 9 01 01 E Issue 011 03A Page 03A 1 14 Dec 2022...

Страница 137: ...AIRPLANE RELATED CAS CAUTIONS AFM DA 50 C Doc No 9 01 01 E Issue 011 03A Page 03A 2 14 Dec 2022...

Страница 138: ...A 04 CHECK GEAR Special operation COOLANT LVL Coolant level low See 03A 05 COOLANT LVL Special operation ECU A FAIL Engine ECU A has failed See 03A 06 ECU A FAIL Special operation ECU B FAIL Engine EC...

Страница 139: ...all warning heat is off See 03A 10 STALL HT FAIL STALL HT OFF Special opera tion VOLTS LOW Essential bus voltage is below 25 V See 03A 11 VOLTS LOW Spe cial operation STALL WARN FAIL Stall warning sys...

Страница 140: ...essential bus ON alternator 2 supplies electrical power to the main and essential bus and charges the main battery Electrical equipment connected to Alternator 2 e g RACC system will loose power C ESS...

Страница 141: ...alternator 2 has failed A Circuit breakers check if all OK pressed in B Alternator 2 switch OFF C Bus voltage monitor D NVFR or IFR operation terminate land on the next suitable airfield AFM DA 50 C D...

Страница 142: ...K GEAR caution message is displayed when either the flaps are in LDG position or the POWER lever is set to less than approx 20 and the landing gear is not down and locked A Landing gear down as requir...

Страница 143: ...ility loss of engine power due to engine failure NOTE The indication is calibrated for straight and level flight The caution message may be triggered during turns which are flown with slip or while ta...

Страница 144: ...onic ECU Engine Control Unit A the system automatically switches to ECU B E FADEC TEST button press for more than 2 seconds to reset the caution message If the ECU A FAIL caution re appears or cannot...

Страница 145: ...set if necessary E FADEC TEST button press for more than 2 seconds to reset the caution message If the ECU B FAIL caution re appears or cannot be reset F Land on nearest suitable airfield G The engine...

Страница 146: ...US GAL 1 US GAL A CAUTION MESSAGE IS DISPLAYED THE INDICATION IS CALIBRATED FOR STRAIGHT AND LEVEL FLIGHT THE CAUTION MESSAGE MAY BE TRIGGERED DURING TURNS WHICH ARE FLOWN WITH SLIP OR WHILE TAXIING...

Страница 147: ...s switched OFF or PITOT FAIL when there is a failure of the Pitot heating system Prolonged operation of the Pitot heating on the ground can also cause the Pitot heating caution message to be displayed...

Страница 148: ...peration of the stall warning heating on the ground also causes the stall warning heating failed caution message to be displayed In this case it indicates the activation of the thermal protection rela...

Страница 149: ...ncrease RPM If the caution light does not extinguish C Terminate flight preparation In Flight D Circuit breakers check E Electrical equipment OFF if not needed If the caution light does not extinguish...

Страница 150: ...lure of the stall warning system A Loss of acoustic stall warning B Continue flight while exercising caution when flying at lower airspeeds due to missing stall warning Use careful airspeed control an...

Страница 151: ...rature is high above 70 C for more than 30 seconds High engine intake temperatures leads to reduces power output A POWER reduce B COWL FLAP check open C Airspeed increase D Check if ENG INTAKE Caution...

Страница 152: ...ABNORMAL PROCEDURES AFM DA 50 C Doc No 9 01 01 E Issue 011 03A Page 03A 17 14 Dec 2022...

Страница 153: ...e control use attitude indicator if necessary D Airspeed use convenient airspeed and power setting NOTE Depending on rudder trim tab stuck position it might be necessary to bank slip slightly to reduc...

Страница 154: ...800 kg Description 1999 kg 05 28 Landing Distances Abnormal Flap Position 1999 kg Description If only UP available E Airspeed 84 KIAS up to 1600 kg 3527 lb 90 KIAS above 1600 kg 3527 lb up to 1800 kg...

Страница 155: ...CLOSED N Emergency gear extension lever check pushed in O Alternate static valve check CLOSED P FADEC check AUTO Q EMERGENCY FUEL PUMP switch check OFF R ELECT MASTER check OFF S AVIONIC MASTER check...

Страница 156: ...MFD to acknowledge W COOLANT LVL caution check OFF X Fuel temperature check WARNING NEVER ROTATE THE PROPELLER BY HAND AFM DA 50 C Doc No 9 01 01 E Issue 011 DA50 A 15 50 01 01A 161A D 03A Page 03A 21...

Страница 157: ...ambient temperatures it is possible that the engine will not start at the first attempt In this case wait 60 seconds between the start attempts A Strobe lights ACL ON B ENGINE MASTER ON C Annunciation...

Страница 158: ...tures are within green range N POWER lever Ground Idle GI O ENGINE MASTER OFF P Restart Engine according to 04 08 Starting Engine Pre operation procedure WARNING IF STARTING THE ENGINE IS NOT POSSIBLE...

Страница 159: ...G LEE EFFECTS DO NOT FLY INTO AREAS OF KNOWN OR FORECAST ICING A Airspeed as low as practicable do not exceed vO refer to 02 02 Airspeed Limitations Description B Grasp airplane controls firmly C Auto...

Страница 160: ...n be activated If fuel transfer from the auxiliary fuel tank to the main tank cannot be observed within a few minutes after switching on the transfer pump assume a defective fuel transfer system A FUE...

Страница 161: ...AUTOPILOT FAILURES AFM DA 50 C Doc No 9 01 01 E Issue 011 03A Page 03A 26 14 Dec 2022...

Страница 162: ...t tone B Pitch trim retrim if necessary using the trim wheel NOTE The autopilot disconnect may be accompanied by a red boxed PTCH pitch or ROL on the PFD indicating the axis which has failed The autop...

Страница 163: ...d B1 Autopilot reselect vertical mode if necessary NOTE Overspeed recovery mode provides a pitch up command to decelerate the airplane at or below the maximum autopilot operating speed 185 KIAS Oversp...

Страница 164: ...it the autopilot will roll the airplane wings level and default to roll mode ROL A Autopilot select HDG on mode controller B CDI select a valid nav source C Autopilot select NAV on mode controller If...

Страница 165: ...MPLE AN ARROW POINTING DOWN INDICATES NOSE DOWN CONTROL STICK FORCE WILL BE REQUIRED UPON AUTOPILOT DISCONNECT NOTE Momentary illumination 5 sec or less of the ELE or ELE indication during configurati...

Страница 166: ...CAUTION BE PREPARED FOR SUSTAINED CONTROL FORCES IN THE DIRECTION OF THE ANNUNCIATION ARROW FOR EXAMPLE AN AIL INDICATES THAT SUSTAINED RIGHT WING DOWN CONTROL STICK FORCE OR FOR RUD SUSTAINED RIGHT R...

Страница 167: ...ROL or PIT After 10 seconds the new mode PIT or ROL will be annunciated in green Loss of Selected Vertical Mode FLC VS ALT GS A Autopilot mode controls select another vertical mode If on an instrumen...

Страница 168: ...he autopilot will remain engaged with no func tional limitations GIA No 1 The autopilot disconnects and autopilot flight di rector and manual electric trim are inoperative GIA No 2 The autopilot disco...

Страница 169: ...04 NORMAL OPERATING PROCEDURES AFM DA 50 C Doc No 9 01 01 E Issue 011 04 Page 04 1 14 Dec 2022...

Страница 170: ...NORMAL OPERATING PROCEDURES GENERAL AFM DA 50 C Doc No 9 01 01 E Issue 011 04 Page 04 2 14 Dec 2022...

Страница 171: ...of the G1000 NXi PFD and MFD display may be degraded when wearing polarized sunglasses NOTE Normal operating procedures for GFC 700 are described in the Garmin G1000 NXi Cockpit Reference Guide P N 1...

Страница 172: ...dedicated use of the rudder and ailerons together With the landing gear extended and at aft CG locations with flaps up and full power applied the airplane will easily recover from sideslip if the trim...

Страница 173: ...IAS Airspeed for initial climb v50 ft Flaps T O 69 KIAS 73 KIAS 79 KIAS Airspeed for take off climb best rate of climb speed vY Flaps T O 79 KIAS Airspeed for cruise climb Flaps UP 94 KIAS Approach sp...

Страница 174: ...DAILY CHECK AFM DA 50 C Doc No 9 01 01 E Issue 011 04 Page 04 6 14 Dec 2022...

Страница 175: ...ks and major scratches On condition check of the hinges for the LH and RH pilot door and the passenger door Visual inspection of the locking bolts for proper movement with no backlash Tire inflation p...

Страница 176: ...CHECKLISTS FOR NORMAL OPERATING PROCEDURES AFM DA 50 C Doc No 9 01 01 E Issue 011 04 Page 04 8 14 Dec 2022...

Страница 177: ...cts check H Emergency Exit window remove pin and store in Pilot s or Co Pilot s backrest pocket I Sun visors if installed locked in fully upward position Emergency equipment A Egress hammer stowed and...

Страница 178: ...eck closed On the instrument panel A FADEC check AUTO B Alternators 1 and 2 check both ON C FUEL TRANS switch check OFF D EMERGENCY FUEL PUMP switch check OFF E ENGINE MASTER check OFF F ESS Bus check...

Страница 179: ...e minimize heater operation during ground operation NOTE Because the stall warning switch gets slightly warmer on ground STALL HT FAIL may be indicated on the PFD E PITOT STALL HEAT Stall Warning chec...

Страница 180: ...ll spring stick should move to aileron neutral elevator at back stop position N Elevator trim check free and correct movement up to full deflection AFM DA 50 C Doc No 9 01 01 E Issue 011 DA50 A 15 33...

Страница 181: ...CHAPTER 8 08 13 CLEANING THE AIRCRAFT FROM ICE AND SNOW DESCRIPTION CAUTION AFTER PARKING IN TEMPERATURES BELOW 0 C NO FLOWING LIQUID UPON ACTIVATING THE DRAIN VALVES IS A SIGN OF FROZEN WATER IN THE...

Страница 182: ...s full fuel may spill over through the tank vent E Tank air outlet on lower surface Visual inspection F Tank filler Visual inspection check closed G Vortex generators Undamaged 10 pieces clean H Pitot...

Страница 183: ...trim tab Visual inspection check safetying E Tie down Check clear F Tail skid and lower fin Visual inspection G Static dischargers 3 Visual inspection H Antennas Visual inspection I Vortex generators...

Страница 184: ...afety pin Visual inspection F Static discharger Visual inspection G Tie down Check clear H Position light strobe light ACL Visual inspection I Wing tip Visual inspection J Vortex generators Undamaged...

Страница 185: ...PROPELLER BY HAND WHILE THE ENGINE MASTER SWITCH IS ON ALSO DO NOT MOVE THE PROPELLER BY HAND WHILE THE ENGINE MASTER IS OFF IMMEDIATELY AFTER OPERATION REMAINING PRESSURE IN THE INJECTION SYSTEM RAIL...

Страница 186: ...LOCKING HANDLE DO NOT APPLY UNDUE FORCE A SLIGHT DOWNWARD INWARD PRESSURE ON THE DOORS MAY BE REQUIRED TO EASE THE HANDLE OPERATION CAUTION FOR TAKE OFF THE ADJUSTABLE BACKRESTS MUST BE FIXED IN THE U...

Страница 187: ...SWITCHING THE ELECT MASTER ON THE ELECTRICALLY DRIVEN HYDRAULIC GEAR PUMP MAY ACTIVATE ITSELF FOR 5 TO 20 SECONDS IN ORDER TO RESTORE THE SYSTEM PRESSURE SHOULD THE PUMP CONTINUE TO OPERATE CONTINUOUS...

Страница 188: ...will not start and damage to starter and electrical power circuit may occur A Strobe lights ACL ON B ENGINE MASTER ON NOTE The glow plugs are supplied with power by a preheat relay before and during s...

Страница 189: ...HAS BEEN RELEASED SET THE ENGINE MASTER TO OFF AND INVESTIGATE THE PROBLEM F ENGINE START button PRESS as required release when engine has started G Annunciations check OK normal range H Annunciation...

Страница 190: ...ALWAYS BE SWITCHED ON DURING NIGHT FLIGHT I Position lights landing and taxi lights as required J Primary flight display PFD no autopilot annunciations K Autopilot disconnect tone note NOTE The AFCS s...

Страница 191: ...e by pressing AP button N AP DISC switch press verify that the autopilot disconnects O TRIM set to take off position manually AFM DA 50 C Doc No 9 01 01 E Issue 011 DA50 A 15 33 00 06A 121A D 04 Page...

Страница 192: ...PROLONGED PERMANENT BRAKING WHILE TAXIING WILL OVERHEAT THE BRAKES AND MAY CAUSE LOSS OF BRAKE CAPACITY AND SUBSEQUENT DAMAGE TO THE AIRPLANE A Parking brake release B Brakes test on moving off C Flig...

Страница 193: ...IONS BETWEEN THE DOORS AND THE MATING FRAME FOR EXAMPLE SEAT BELTS CLOTHING ETC WHEN OPERATING THE LOCKING HANDLE DO NOT APPLY UNDUE FORCE A SLIGHT DOWNWARD INWARD PRESSURE ON THE DOORS MAY BE REQUIRE...

Страница 194: ...ING THE FADEC TEST BUTTON THIS APPLIES EVEN IF THE ENGINE SEEMS TO RUN NORMALLY AGAIN AFTER COMPLETION OF THE TEST PROCEDURE NOTE If the test button is released before the self test is completed the F...

Страница 195: ...ns check OK C Instruments check within normal range D RPM stabilizes at 2290 to 2340 RPM CAUTION THE LOAD INDICATIONS IN THE TABLE BELOW ARE MINIMUM VALUES TO BE INDICATED WITH THE AIRPLANE STATIONARY...

Страница 196: ...ation G Engine instruments check in green range H ALTERNATE STATIC SOURCE PULL ON check altimeter PUSH OFF I EMERGENCY FUEL PUMP switch ON note fuel pump sound J PITOT STALL HEAT as required K Ammeter...

Страница 197: ...b v 50ft Flight Mass up to 1600 kg 3527 lb above 1600 kg 3527 lb up to 1800 kg 3968 lb above 1800 kg 3968 lb Airspeed for rotation Take off run vR Flaps T O 59 KIAS 64 KIAS 68 KIAS Airspeed for initia...

Страница 198: ...LOAD latest after 5 min reduce to 90 MCP L COWL FLAP as required M ALTERNATE AIR OPEN in rain snow or visible moisture AFM DA 50 C Doc No 9 01 01 E Issue 011 DA50 A 15 34 00 01A 131A D 04 Page 04 30...

Страница 199: ...COOLING NOTE Operating in the gearbox cautionary range is permitted However prolonged operation is not recommended A Landing gear check UP B FLAPS check UP C Landing light check OFF as required D EME...

Страница 200: ...ite ALT altitude preselect armed note on PFD E Green ALT verify upon altitude capture NOTE If the altitude preselect is not changed before selecting VS the autopilot may re capture the current altitud...

Страница 201: ...Altitude A Altimeter setting adjust to appropriate value B Altitude preselect ALT set to desired altitude C Vertical mode and reference select on mode controller D White ALT altitude preselect armed...

Страница 202: ...e PFD The pilot must ensure that the current heading will result in a capture of the selected course If the CDI is one dot or less from center the autopilot will enter the capture mode when the NAV bu...

Страница 203: ...IONS GIVEN IN 02 14 FUEL DESCRIPTION NOTE The recommended cruise power setting is 75 A POWER lever up to 90 or maximum 2300 RPM B Trim as required C Annunciations Engine System Page monitor D COWL FLA...

Страница 204: ...E Green ALT verify upon altitude capture NOTE If the altitude preselect is not changed before selecting VS the autopilot may re capture the current altitude immediately after entering VS mode Always...

Страница 205: ...Altitude A Altimeter setting adjust to appropriate value B Altitude preselect ALT set to desired altitude C Vertical mode and reference select on mode controller D White ALT altitude preselect armed...

Страница 206: ...Deviation Indicator CDI is greater than one dot from center the autopilot will arm the NAV mode and indicate VOR or GPS in white on the PFD The pilot must ensure that the current heading will result i...

Страница 207: ...H A FUEL TRANS switch ON The transfer pump turns off automatically to avoid overfilling the main tank The switch remains in its position If the pump is not turned off it will continue pumping each ti...

Страница 208: ...urce when switched off The switching function may leave some remaining functionality e g data storage timer clock etc These devices can be considered switched off when in the deactivated status The sa...

Страница 209: ...D E Green ALT verify upon altitude capture NOTE If the altitude preselect is not changed before selecting VS the autopilot may re capture the current altitude immediately after entering VS mode Always...

Страница 210: ...priate value B Altitude preselect ALT set to desired altitude C Vertical mode and reference select on mode controller D White ALT altitude preselect armed note on PFD E Green ALT verify upon altitude...

Страница 211: ...the PFD The pilot must ensure that the current heading will result in a capture of the selected course If the CDI is one dot or less from center the autopilot will enter the capture mode when the NAV...

Страница 212: ...MFD control unit keypad if installed stowed E Controls no interference by foreign objects F Landing Taxi Position Strobe Lights ACL as required G EMERGENCY FUEL PUMP switch ON H FUEL valve NORMAL I G...

Страница 213: ...800 kg 3968 lb above 1800 kg 3968 lb vREF Flaps UP 84 KIAS 90 KIAS 94 KIAS vREF Flaps T O 77 KIAS 79 KIAS 85 KIAS vREF Flaps LDG 73 KIAS 75 KIAS 77 KIAS Table 1 Airspeeds AFM DA 50 C Doc No 9 01 01 E...

Страница 214: ...ill arm the VAPP mode and indicate VAPP in white on the PFD The pilot must ensure that the current heading will result in a capture of the selected course If the CDI is one dot or less from center the...

Страница 215: ...reference select on mode controller Back Course BC A Navigation source select LOC using CDI button on PFD B Course bearing pointer CRS set to ILS front course using course knob C Intercept heading est...

Страница 216: ...e 1600 kg 3527 lb up to 1800 kg 3968 lb 85 KIAS above 1800 kg 3968 lb D COWL FLAP OPEN as required When a positive rate of climb is established E Landing gear UP F FLAPS retract position UP When a saf...

Страница 217: ...D Missed approach procedure execute as applicable E Altitude preselelect ALT set to appropriate altitude At an appropriate safe altitude F Autopilot mode controller select appropriate lateral and ver...

Страница 218: ...lever Ground Idle GI B Brakes as required C ALTERNATE AIR CLOSED D Lights as required E Avionics as required F EMERGENCY FUEL PUMP switch OFF G PITOT STALL HEAT OFF H FLAPS UP AFM DA 50 C Doc No 9 01...

Страница 219: ...king brake set B POWER lever Ground Idle GI at least 2 minutes C FLAPS check UP D Engine System Page check E COWL FLAP CLOSED F AVIONIC MASTER OFF G Electrical consumers OFF H ENGINE MASTER OFF I Land...

Страница 220: ...irplane Post operation procedure 1 Exit Airplane A Exit the airplane to the aft on designated areas on the wing LH or RH AFM DA 50 C Doc No 9 01 01 E Issue 011 DA50 A 15 35 00 03A 151A D 04 Page 04 52...

Страница 221: ...Post Flight Inspection A Record any problem found in flight and during the post flight check in the log book B Park the airplane C If necessary moor the airplane AFM DA 50 C Doc No 9 01 01 E Issue 01...

Страница 222: ...moor if unsupervised for extended period WARNING THE PITOT PROBE BECOMES VERY HOT DURING OPERATION BE CAREFULL TO AVOID BURNS THIS CAN CAUSE INJURIES TO PERSONS D Pitot static probe cover E Emergency...

Страница 223: ...ates in rain this applies particularly to the take off distance and to the maximum horizontal speed The effect on the flight characteristics is minimal Flight through very heavy rain should be avoided...

Страница 224: ...does not exceed the approved values Anti microbial life fuel additives may be manually batch blended into the fuel tanks In this case introduce the additive while filling the tank after approximately...

Страница 225: ...13 2 40 2 88 68 58 9 1 99 100 26 4 80 4 177 37 117 9 3 99 150 39 6 120 6 266 05 176 8 5 98 Densities used for calculation Fuel 0 804 kg l PRIST Hi Flash 1 05 kg l Do not batch blend Table 2 PRIST Hi F...

Страница 226: ...at High Altitude At high altitudes the provision of oxygen for the occupants is necessary Legal requirements for the provision of oxygen should be adhered to AFM DA 50 C Doc No 9 01 01 E Issue 011 DA...

Страница 227: ...05 PERFORMANCE AFM DA 50 C Doc No 9 01 01 E Issue 011 05 Page 05 1 14 Dec 2022...

Страница 228: ...PERFORMANCE GENERAL AFM DA 50 C Doc No 9 01 01 E Issue 011 05 Page 05 2 14 Dec 2022...

Страница 229: ...light trials using an airplane and power plant in normal condition and corrected to the conditions of the International Standard Atmosphere ISA 15 C 59 F and 1013 25 hPa 29 92 inHg at sea level The pe...

Страница 230: ...ce data for the planned flight For a conversion of units see 01 05 Conversion Factors Description For temperatures altitudes and weights between those provided use a linear interpolation between the n...

Страница 231: ...DG Indicated Airspeed KIAS Calibrated Airspeed KCAS 60 59 65 63 70 68 75 73 80 78 85 83 90 88 95 93 100 98 105 103 110 108 115 112 120 117 125 122 130 127 133 130 Table 1 Airspeed Calibration Flaps TO...

Страница 232: ...85 84 90 88 95 93 100 98 105 103 110 108 115 113 120 118 125 123 130 128 135 133 140 138 145 143 150 148 155 153 160 158 165 163 170 168 175 173 180 178 185 183 190 188 Table 2 Airspeed Calibration F...

Страница 233: ...national Standard Atmosphere Description 1 International Standard Atmosphere Figure 1 International Standard Atmosphere AFM DA 50 C Doc No 9 01 01 E Issue 011 DA50 A 15 61 02 00A 040A D 05 Page 05 7 1...

Страница 234: ...Bank Angle 0 30 45 60 Gear Flaps KIAS KCAS KIAS KCAS KIAS KCAS KIAS KCAS UP UP 66 66 71 71 80 78 95 93 DOWN TO 60 59 65 63 72 70 85 83 DOWN LDG 55 54 64 62 71 69 84 82 Table 2 Stalling Speeds 1800 kg...

Страница 235: ...t kts 10 20 10 20 30 40 Headwind Component kts Flight Direction 0 Maximum demonstrated Crosswind Component Figure 2 Wind Components Max demonstrated crosswind component 15 kts Example Flight direction...

Страница 236: ...TAKE OFF DISTANCE AFM DA 50 C Doc No 9 01 01 E Issue 011 05 Page 05 10 14 Dec 2022...

Страница 237: ...t be attempt Grass runway wet Increase the dry grass runway distance calculation by 10 Soft ground Increase the ground roll by 45 in addition to the grass runway distance calculation if applicable Uph...

Страница 238: ...LOPE SHOULD BE USED WITH CAUTION SINCE PUBLISHED RUNWAY SLOPE DATA IS USUALLY THE NET SLOPE FROM ONE END OF THE RUNWAY TO THE OTHER RUNWAYS MAY HAVE POSITIONS AT THEIR LENGTH AT GREATER OR LESSER SLOP...

Страница 239: ...05 08 Take Off Distance 1999 kg Description AFM DA 50 C Doc No 9 01 01 E Issue 011 DA50 A 15 62 00 01A 040A D 05 Page 05 13 14 Dec 2022...

Страница 240: ...0 560 640 730 475 15 m 50 ft 810 860 910 1000 1160 1330 851 4000 1219 Ground Roll 480 510 540 600 690 790 500 15 m 50 ft 860 920 970 1090 1260 1440 896 5000 1524 Ground Roll 520 550 580 660 760 527 15...

Страница 241: ...850 2100 2400 1559 15 m 50 ft 2650 2850 3000 3300 3800 4350 2792 4000 1219 Ground Roll 1600 1700 1800 2000 2300 2600 1638 15 m 50 ft 2850 3000 3200 3600 4150 4750 2938 5000 1524 Ground Roll 1700 1800...

Страница 242: ...05 09 Take Off Distance 1800 kg Description AFM DA 50 C Doc No 9 01 01 E Issue 011 DA50 A 15 62 00 02A 040A D 05 Page 05 16 14 Dec 2022...

Страница 243: ...360 380 400 440 510 570 374 15 m 50 ft 600 640 670 740 850 960 629 4000 1219 Ground Roll 380 400 430 480 550 620 393 15 m 50 ft 640 670 720 800 920 1040 660 5000 1524 Ground Roll 410 430 460 520 590...

Страница 244: ...450 1650 1900 1227 15 m 50 ft 2000 2100 2200 2400 2800 3150 2064 4000 1219 Ground Roll 1250 1350 1400 1600 1800 2050 1289 15 m 50 ft 2100 2200 2350 2600 3000 3450 2164 5000 1524 Ground Roll 1350 1450...

Страница 245: ...05 10 Take Off Distance 1600 kg Description AFM DA 50 C Doc No 9 01 01 E Issue 011 DA50 A 15 62 00 03A 040A D 05 Page 05 19 14 Dec 2022...

Страница 246: ...d Roll 280 290 310 340 390 440 290 15 m 50 ft 460 490 520 560 650 740 484 4000 1219 Ground Roll 300 310 330 370 420 480 304 15 m 50 ft 490 520 550 610 700 800 508 5000 1524 Ground Roll 320 340 360 400...

Страница 247: ...00 1450 950 15 m 50 ft 1550 1600 1700 1850 2150 2450 1586 4000 1219 Ground Roll 1000 1050 1100 1200 1400 1600 997 15 m 50 ft 1600 1700 1800 2000 2300 2600 1665 5000 1524 Ground Roll 1050 1100 1200 135...

Страница 248: ...CLIMB PERFORMANCE TAKE OFF CLIMB AFM DA 50 C Doc No 9 01 01 E Issue 011 05 Page 05 22 14 Dec 2022...

Страница 249: ...d Airspeed vY The climb performance tables show the rate of climb The gradient of climb can be calculated using the following formula Figure 1 Gradient Formula NOTE Rate of climb at 1999 kg 4407 lb wi...

Страница 250: ...700 690 660 610 704 2000 610 710 710 700 690 680 670 630 570 690 4000 1219 700 690 680 670 660 640 590 530 673 6000 1829 680 670 660 650 640 600 540 655 8000 2438 660 650 630 620 610 550 500 636 1000...

Страница 251: ...30 830 790 730 836 2000 610 840 840 830 820 810 810 750 690 822 4000 1219 830 820 810 800 790 770 710 650 805 6000 1829 810 800 790 780 770 720 660 787 8000 2438 790 780 770 750 740 680 610 768 10000...

Страница 252: ...90 980 940 870 992 2000 610 1000 990 990 980 970 960 900 830 978 4000 1219 980 980 970 960 950 920 850 780 961 6000 1829 960 960 950 940 930 870 800 943 8000 2438 940 930 920 910 890 820 750 924 10000...

Страница 253: ...CLIMB PERFORMANCE CRUISE CLIMB AFM DA 50 C Doc No 9 01 01 E Issue 011 05 Page 05 27 14 Dec 2022...

Страница 254: ...or maximum 2300 RPM Flaps UP Landing gear retracted Airspeed 94 KIAS The climb performance tables show the rate of climb The gradient of climb can be calculated using the following formula Figure 1 G...

Страница 255: ...0 680 786 2000 610 800 800 790 780 770 760 710 650 781 4000 1219 800 790 780 770 760 740 680 620 774 6000 1829 790 780 770 760 750 710 650 768 8000 2438 780 770 760 750 730 670 610 759 10000 3048 740...

Страница 256: ...0 800 917 2000 610 940 930 920 910 910 900 840 770 913 4000 1219 930 920 910 910 900 870 800 740 908 6000 1829 920 910 910 900 880 830 770 902 8000 2438 920 910 890 880 870 800 730 895 10000 3048 870...

Страница 257: ...00 610 1090 1090 1080 1070 1060 1050 980 910 1072 4000 1219 1090 1080 1070 1060 1060 1030 950 870 1068 6000 1829 1090 1080 1070 1060 1040 990 910 1063 8000 2438 1080 1070 1060 1040 1030 950 870 1057 1...

Страница 258: ...TIME FUEL DISTANCE TO CLIMB AFM DA 50 C Doc No 9 01 01 E Issue 011 05 Page 05 32 14 Dec 2022...

Страница 259: ...90 4 0 0 0 2000 610 11 52 93 780 3 9 3 0 7 3 4000 1219 7 45 94 780 3 9 6 1 4 8 6000 1829 3 38 96 775 3 9 8 2 12 8000 2438 1 30 97 770 3 9 11 2 7 16 10000 3048 5 23 99 765 3 8 14 3 4 21 12000 3658 9 16...

Страница 260: ...5 4 7 0 0 0 2000 610 11 52 93 915 4 6 3 0 6 3 4000 1219 7 45 94 910 4 6 5 1 2 6 6000 1829 3 38 96 910 4 6 7 1 7 10 8000 2438 1 30 97 905 4 6 9 2 3 14 10000 3048 5 23 99 900 4 5 12 2 9 18 12000 3658 9...

Страница 261: ...075 5 5 0 0 0 2000 610 11 52 93 1070 5 4 2 0 5 2 4000 1219 7 45 94 1070 5 4 4 1 5 6000 1829 3 38 96 1065 5 4 6 1 5 9 8000 2438 1 30 97 1065 5 4 8 2 12 10000 3048 5 23 99 1060 5 3 10 2 5 15 12000 3658...

Страница 262: ...CRUISE PERFORMANCE AFM DA 50 C Doc No 9 01 01 E Issue 011 05 Page 05 36 14 Dec 2022...

Страница 263: ...e Conditions Flaps UP Landing gear retracted For conversion of OAT to delta ISA temperatures refer to Chapter 5 05 04 International Standard Atmosphere Description AFM DA 50 C Doc No 9 01 01 E Issue 0...

Страница 264: ...141 142 144 145 45 7 9 122 123 124 125 126 8000 2438 90 15 3 167 169 171 173 175 75 12 4 156 157 159 161 162 60 10 1 142 143 145 146 148 45 7 9 124 125 126 127 128 10000 3048 90 15 9 170 172 174 176 1...

Страница 265: ...10 7 152 154 155 157 158 45 8 131 132 133 134 135 18000 5486 68 12 1 163 165 167 169 171 60 11 155 156 158 160 161 45 8 133 134 135 135 136 20000 6096 60 11 156 158 160 162 164 45 8 2 134 135 136 137...

Страница 266: ...LANDING DISTANCES AFM DA 50 C Doc No 9 01 01 E Issue 011 05 Page 05 40 14 Dec 2022...

Страница 267: ...the ground roll by 15 Grass runway dry longer than 10 cm 3 9 in Increase the ground roll at least by 25 Grass runway wet or soft runway Increase the ground roll by 10 Downhill slope Increase the grou...

Страница 268: ...LD BE USED WITH CAUTION SINCE PUBLISHED RUNWAY SLOPE DATA IS USUALLY THE NET SLOPE FROM ONE END OF THE RUNWAY TO THE OTHER RUNWAYS MAY HAVE POSITIONS AT THEIR LENGTH AT GREATER OR LESSER SLOPES THAN P...

Страница 269: ...Ground Roll 400 430 450 490 560 630 422 15 m 50 ft 750 780 810 860 960 1060 771 4000 1219 Ground Roll 440 460 490 540 620 690 454 15 m 50 ft 790 820 850 920 1030 1140 808 5000 1524 Ground Roll 480 51...

Страница 270: ...1850 2050 1382 15 m 50 ft 2450 2550 2650 2850 3150 3500 2529 4000 1219 Ground Roll 1450 1550 1650 1800 2050 2300 1487 15 m 50 ft 2600 2700 2800 3050 3400 3750 2650 5000 1524 Ground Roll 1600 1700 1800...

Страница 271: ...4 Ground Roll 370 390 420 450 510 570 386 15 m 50 ft 720 750 780 830 920 1010 742 4000 1219 Ground Roll 400 430 450 500 570 640 417 15 m 50 ft 760 790 820 890 980 1090 778 5000 1524 Ground Roll 440 47...

Страница 272: ...700 1900 1265 15 m 50 ft 2400 2450 2550 2700 3000 3350 2434 4000 1219 Ground Roll 1350 1400 1500 1650 1850 2100 1366 15 m 50 ft 2500 2600 2700 2900 3250 3600 2553 5000 1524 Ground Roll 1450 1550 1650...

Страница 273: ...914 Ground Roll 330 350 380 410 460 520 349 15 m 50 ft 690 720 740 790 870 960 713 4000 1219 Ground Roll 370 390 410 460 510 580 380 15 m 50 ft 730 760 790 850 940 1040 750 5000 1524 Ground Roll 410...

Страница 274: ...0 1700 1144 15 m 50 ft 2300 2350 2450 2600 2900 3150 2337 4000 1219 Ground Roll 1200 1300 1350 1500 1700 1900 1247 15 m 50 ft 2400 2500 2600 2800 3100 3400 2458 5000 1524 Ground Roll 1350 1400 1500 17...

Страница 275: ...LANDING DISTANCE ABNORMAL FLAP POSITION AFM DA 50 C Doc No 9 01 01 E Issue 011 05 Page 05 49 14 Dec 2022...

Страница 276: ...1190 1330 980 3000 914 Ground Roll 570 600 630 690 780 880 595 15 m 50 ft 990 1030 1070 1150 1280 1430 1026 4000 1219 Ground Roll 610 650 690 760 860 970 629 15 m 50 ft 1050 1090 1140 1240 1380 1530 1...

Страница 277: ...ll 1850 2000 2100 2250 2550 2900 1951 15 m 50 ft 3250 3400 3550 3800 4200 4700 3366 4000 1219 Ground Roll 2050 2150 2250 2500 2850 3200 2063 15 m 50 ft 3450 3600 3750 4050 4550 5050 3508 5000 1524 Gro...

Страница 278: ...0 1110 1240 909 3000 914 Ground Roll 510 550 580 630 720 800 538 15 m 50 ft 920 960 1000 1070 1200 1320 953 4000 1219 Ground Roll 560 590 630 700 780 880 580 15 m 50 ft 970 1020 1060 1160 1280 1420 10...

Страница 279: ...ll 1700 1800 1900 2100 2350 2600 1764 15 m 50 ft 3050 3150 3300 3550 3950 4350 3125 4000 1219 Ground Roll 1850 1950 2100 2300 2600 2900 1902 15 m 50 ft 3200 3350 3500 3800 4200 4700 3283 5000 1524 Gro...

Страница 280: ...0 920 1030 1130 838 3000 914 Ground Roll 470 500 530 570 640 730 491 15 m 50 ft 850 890 930 980 1100 1220 880 4000 1219 Ground Roll 510 550 570 630 720 810 531 15 m 50 ft 900 940 980 1060 1180 1310 92...

Страница 281: ...ll 1550 1650 1750 1850 2100 2400 1609 15 m 50 ft 2800 2900 3050 3250 3600 4000 2886 4000 1219 Ground Roll 1700 1800 1900 2100 2350 2650 1741 15 m 50 ft 2950 3100 3200 3500 3900 4300 3037 5000 1524 Gro...

Страница 282: ...GO AROUND CLIMB PERFORMANCE AFM DA 50 C Doc No 9 01 01 E Issue 011 05 Page 05 56 14 Dec 2022...

Страница 283: ...vREF The climb performance tables show the rate of climb The gradient an angle of climb can be calculated using the following formula Figure 1 Gradient Formula NOTE Rate of climb at MSL and ISA condi...

Страница 284: ...ure C F ISA 20 4 10 14 0 32 10 50 20 68 30 86 40 104 50 122 SL 495 485 475 460 445 430 390 335 452 2000 610 485 470 455 445 430 410 350 300 442 4000 1219 470 455 440 425 410 375 315 265 432 6000 1829...

Страница 285: ...ISA 20 4 10 14 0 32 10 50 20 68 30 86 40 104 50 122 SL 610 600 585 575 560 545 495 430 566 2000 610 600 585 570 555 545 525 455 395 556 4000 1219 585 570 555 540 525 490 420 355 545 6000 1829 570 555...

Страница 286: ...ure C F ISA 20 4 10 14 0 32 10 50 20 68 30 86 40 104 50 122 SL 745 735 720 710 695 685 625 550 703 2000 610 735 725 710 695 680 660 580 510 693 4000 1219 725 710 695 680 665 620 545 470 682 6000 1829...

Страница 287: ...GLIDE AFM DA 50 C Doc No 9 01 01 E Issue 011 05 Page 05 61 14 Dec 2022...

Страница 288: ...e in nautical miles per 1000 ft 300 m of altitude loss in a glide traveled in still air Glide ratio Maximum horizontal distance per 1000 ft 300 m altitude loss Windmilling propeller 10 0 1 6 NM 3 0 km...

Страница 289: ...APPROVED NOISE DATA AFM DA 50 C Doc No 9 01 01 E Issue 011 05 Page 05 63 14 Dec 2022...

Страница 290: ...0 dB A CS 36 Subpart C 85 0 dB A No determination has been made by the Federal Aviation Administration that the noise levels of this aircraft are or should be acceptable or unacceptable for operation...

Страница 291: ...06 MASS AND BALANCE EQUIPMENT AFM DA 50 C Doc No 9 01 01 E Issue 011 06 Page 06 1 14 Dec 2022...

Страница 292: ...MASS AND BALANCE AFM DA 50 C Doc No 9 01 01 E Issue 011 06 Page 06 2 14 Dec 2022...

Страница 293: ...t approved for this airplane exists Equipment List The set of items marked as installed constitutes the Equipment Inventory Before the airplane is delivered the empty mass and the corresponding CG pos...

Страница 294: ...of flight When the airplane is aligned horizontally by means of the weighing tool the Datum Plane is vertical The Datum Plane is located 2 196 meters 86 46 in in front of the leading edge of the wing...

Страница 295: ...position or moment the current empty mass and the corresponding CG position or moment in accordance with the Mass and Balance Report must always be used Condition of the airplane for establishing the...

Страница 296: ...or modification Changes in mass Current empty mass Addition Subtraction IN OUT Mass Moment Arm Moment Mass Moment Arm Moment Mass Moment Arm Moment Table 1 Mass and Balance Report AFM DA 50 C Doc No...

Страница 297: ...item of loading and enter these moments in the appropriate boxes in Table 06 07 Calculation of Loading Condition Description D Add up the masses and moments in the respective columns The CG position...

Страница 298: ...ts on front seats 2 24 88 2 Occupants on rear seats 3 13 123 2 Fuel 2 63 103 5 Baggage in Area A and Compartment C 3 98 156 7 Baggage in Area B and Compartment D 4 35 171 3 Trim Weight 1 0 to 20 0 kg...

Страница 299: ...200 300 400 500 25 50 100 125 150 175 200 225 75 kg lb Load Mass 10 000 20 000 30 000 40 000 50 000 100 200 300 400 500 kgm in lb Load Moment 10 20 30 40 Fuel Quantity US gal liters 50 100 150 200 50...

Страница 300: ...s 8 and 10 by the related total mass to obtain the CG positions Locate the values in the diagram in 06 08 Permissible Center of Gravity Range Description If the CG positions and related masses fall in...

Страница 301: ...e in Area B Lever arm 4 35 m 6 Baggage in Compartment C Lever arm 3 98 m 7 Baggage in Compartment D Lever arm 4 35 m 8 Total mass and total moment with empty fuel tanks Total of 1 7 9 Usable fuel main...

Страница 302: ...in Area B Lever arm 171 3 in 6 Baggage in Compartment C Lever arm 156 7 in 7 Baggage in Compartment D Lever arm 171 3 in 8 Total mass and total moment with empty fuel tanks Total of 1 7 9 Usable fuel...

Страница 303: ...rm 171 3 in 10 kg 22 lb 43 5 kgm 3 769 in lb 6 Baggage in Compartment C Lever arm 3 98 m Lever arm 156 7 in 5 kg 11 lb 19 9 kgm 1 724 in lb 7 Baggage in Compartment D Lever arm 4 35 m Lever arm 171 3...

Страница 304: ...f datum plane at 1480 kg increasing linearly to see next row 2 458 m aft of datum plane at 1645 kg increasing linearly to see next row 2 47 m aft of datum plane at 1999 kg Flight Mass kg 1350 1 00 4 1...

Страница 305: ...900 2000 2100 2 50 0 Flight Mass Moment kg m 3800 3900 4 00 0 3700 3600 3500 3 00 4 3 00 3 3 00 2 4800 4700 4600 4100 4 00 2 4 00 3 4 00 4 4500 5 00 3 5 00 2 5 00 1 4900 5000 4 0 000 0 320 000 340 000...

Страница 306: ...EQUIPMENT LIST AFM DA 50 C Doc No 9 01 01 E Issue 011 06 Page 06 16 14 Dec 2022...

Страница 307: ...bitrary combination The airplane manufacturer must be contacted before removing or installing equipment with the exception of replacing a unit by an identical unit The items of equipment installed in...

Страница 308: ...86 011 01904 03 Garmin Pitch clutch cartridge 011 02147 03 Garmin Roll servo GSA 81 011 00878 20 Garmin Roll servo mount GSM 86 011 01904 03 Garmin Roll clutch cartridge 011 02147 09 Garmin Pitch trim...

Страница 309: ...chroth Safety belt co pilot 5 01 Series 5 01 2Y57 Schroth Safety belt LH pax 5 02 Series 5 02 BJ57 Schroth Safety belt RH pax 5 02 Series 5 02 BK57 Schroth Safety belt center pax 5 02 Series 5 02 BL57...

Страница 310: ...rp INDICATING REC SYSTEM Primary flight display PFD GDU 1050 011 03470 00 Garmin Multi function display MFD GDU 1055 011 03470 80 Garmin Control unit GCU 476 011 01237 10 Garmin Control unit GCU 476 0...

Страница 311: ...ium Antenna Cl 490 1 Comant Iridium Antenna Cl 490 490 Comant COMM 1 GPS 2 antenna Cl 2580 200 Comant COMM 2 antenna CI 292 2 Comant Audio panel Marker ICS GMA 1360 011 03568 00 Garmin Pitot Static pr...

Страница 312: ...Magnetometer GMU 44 011 00870 10 Garmin Magnetometer GMU 44B 011 04201 00 Garmin Dual VOR dual GS duplexer CI 1125 Comant LH VOR LOC GS antenna CI120G S Comant RH VOR LOC GS antenna CI120G S Comant V...

Страница 313: ...L 3 Stormscope antenna NY 163 805 10930 001 L 3 ADF receiver RA 3502 01 0505 757 912 Becker ADF RMI converter AC 3504 01 0856 010 912 Becker ADF antenna AN 3500 0832 601 912 Becker Flight Stream 510 0...

Страница 314: ...DZ Nagano 0 29 0 13 230 3 5 85 ENGINE Engine Centurion 3 0 06 7200 K0003 Continental Aerospace Exhaust tubes D54 7806 01 00 Diamond Aircraft Exhaust tubes D54 7806 02 00 Diamond Aircraft Exhaust tubes...

Страница 315: ...istration Date Mass Lever Arm Description Type Part No Manufacturer S N ins lb kg in m Place Date Signature Table 1 Equipment List AFM DA 50 C Doc No 9 01 01 E Issue 011 DA50 A 15 82 00 00A 040A D 06...

Страница 316: ...07 DESCRIPTION OF THE AIRPLANE AND ITS SYSTEMS AFM DA 50 C Doc No 9 01 01 E Issue 011 07 Page 07 1 14 Dec 2022...

Страница 317: ...a special fire resistant matting which is covered by stainless steel cladding 2 Wings The wings have a front and rear spar each wing has a top shell and a bottom shell The wings as well as the ailero...

Страница 318: ...FLIGHT CONTROLS AFM DA 50 C Doc No 9 01 01 E Issue 011 07 Page 07 3 14 Dec 2022...

Страница 319: ...olled by cables The flaps are electrically operated Elevator forces can be balanced by a trim tab on the elevator which is operated by a Bowden cable Rudder forces can be balanced by a trim tab on the...

Страница 320: ...l system A rod end bearing is screwed into a steel push rod and locked by means of a jam nut which has locking varnish applied to it Damage to this varnish can indicate a twisting and thus a change to...

Страница 321: ...UP totally retracted Take off T O and Landing LDG The flaps are operated by means of a 3 position flap selector switch on the instrument panel The positions of the switch correspond to the positions...

Страница 322: ...rews to the rear web of the vertical stabilizer The mating part on the rudder is a bracket which is attached to the rudder by 2 bolts The upper bolt and nut is accessible to visual inspection Operatio...

Страница 323: ...o the pushrod can be visually inspected at the upper end of the rudder Bolts secured by crown nuts and split pins are connecting the elevator to the horizontal tail at the other 4 hinges locations The...

Страница 324: ...r of the power lever To guard against overrotating the trim wheel incorporates a friction device A mark on the wheel shows the take off T O position Turn wheel to the front trim nose down Turn wheel t...

Страница 325: ...of the power lever An indication on the G1000 NXi MFD shows the center position the bold area and the direction of movement Push the right button right turn trim to the right Push the left button left...

Страница 326: ...Forward Adjustment To move the pedals forward depress upper side of switch When pedals are in correct position release switch 2 Rearward Adjustment To move the pedals in the rearward direction depres...

Страница 327: ...INSTRUMENT PANEL AFM DA 50 C Doc No 9 01 01 E Issue 011 07 Page 07 12 14 Dec 2022...

Страница 328: ...pedal switches 5 Pitot Static heat switch 20 USB charging ports 6 Alternator Switches 21 Emergency compass 7 FADEC Test button 22 ELT control unit 8 FADEC Force B switch 23 Primary flight display PFD...

Страница 329: ...Figure 1 Instrument Panel AFM DA 50 C Doc No 9 01 01 E Issue 011 DA50 A 31 10 00 99A 040A D 07 Page 07 14 14 Dec 2022...

Страница 330: ...LANDING GEAR AFM DA 50 C Doc No 9 01 01 E Issue 011 07 Page 07 15 14 Dec 2022...

Страница 331: ...etracts in a rearward movement and the left and right main landing gears retract simultaneously inboard Hydraulic pressure on the actuators keeps the landing gear in the retracted position A pressuriz...

Страница 332: ...sion the airspeed should be reduced to 102 KIAS Otherwise the aerodynamic drag on the nose gear delays or prevents a complete extension of the gear At low OAT and cold soaked aircraft the landing gear...

Страница 333: ...The operating mode for the retraction of the landing gear is shown in Figure 3 While energizing the right hydraulic valve the fluid flow in the hydraulic system is started due to different piston area...

Страница 334: ...re Switch Zero Current Extending LG Cylinders Zero Current Emergency Extension Valve Figure 1 Extension of the Landing Gear AFM DA 50 C Doc No 9 01 01 E Issue 011 DA50 A 32 30 00 99A 040A D 07 Page 07...

Страница 335: ...ressure Switch Zero Current Extended LG Cylinders Zero Current Emergency Extension Valve Figure 2 Landing Gear Extended AFM DA 50 C Doc No 9 01 01 E Issue 011 DA50 A 32 30 00 99A 040A D 07 Page 07 20...

Страница 336: ...ure Switch Zero Current Retracting LG Cylinders Energized Emergency Extension Valve Figure 3 Retraction of the Landing Gear AFM DA 50 C Doc No 9 01 01 E Issue 011 DA50 A 32 30 00 99A 040A D 07 Page 07...

Страница 337: ...Pressure Switch Energized Retracted LG Cylinders Emergency Extension Valve Energized Figure 4 Landing Gear Retracted AFM DA 50 C Doc No 9 01 01 E Issue 011 DA50 A 32 30 00 99A 040A D 07 Page 07 22 14...

Страница 338: ...p Pressure Switch Extending LG Cylinders Emergency Extension Valve Figure 5 Emergency Extension of the Landing Gear AFM DA 50 C Doc No 9 01 01 E Issue 011 DA50 A 32 30 00 99A 040A D 07 Page 07 23 14 D...

Страница 339: ...king Brake The lever is located on the small center console under the instrument panel on the left side of the power lever and is in the upper position when the brakes are set To operate the parking b...

Страница 340: ...SEATS AND SAFETY HARNESSES AFM DA 50 C Doc No 9 01 01 E Issue 011 07 Page 07 25 14 Dec 2022...

Страница 341: ...harnesses are fastened by inserting the end of the belts in the belt lock and are opened by pressing the red release on the belt lock The front seats have adjustable backrests installed The angle of...

Страница 342: ...bar Support Inboard Hinge Lumbar Support Lever Outboard Hinge Bowden Cable Release Button Figure 1 Pilots Seat AFM DA 50 C Doc No 9 01 01 E Issue 011 DA50 A 25 10 00 01A 040A D 07 Page 07 27 14 Dec 20...

Страница 343: ...DOORS AND INTERIOR AFM DA 50 C Doc No 9 01 01 E Issue 011 07 Page 07 28 14 Dec 2022...

Страница 344: ...essure damper prevents each pilot door from dropping in strong winds the assemblies must be securely held The pilot doors can be blocked by a locking device on the each side near the opening levers by...

Страница 345: ...ure damper prevents the door from dropping in strong winds the assembly must be securely held The passenger door is protected against unintentional opening by an additional lever The door can be block...

Страница 346: ...f the emergency exit window is done via the red handle at the rear upper corner of the window The handle is closed by covers inside and outside to avoid mishandling These covers remain installed until...

Страница 347: ...Figure 1 Emergency Exit Window AFM DA 50 C Doc No 9 01 01 E Issue 011 DA50 A 56 10 00 99A 040A D 07 Page 07 32 14 Dec 2022...

Страница 348: ...ivation Handle Cover 2 Fig 1 Activation Handle 3 Fig 1 Window Attachments 7x 4 Fig 1 Activation Rope 5 Fig 1 Activation Handle AFM DA 50 C Doc No 9 01 01 E Issue 011 DA50 A 56 10 00 99A 040A D 07 Page...

Страница 349: ...RE OF SHARP EDGES AND FRAGMENTS OF THE BROKEN WINDOW An egress hammer is installed on the floor panel behind the co pilot s seat If the doors can not be opened in case of an emergency use the egress h...

Страница 350: ...the cabin This procedure might be useful whenever rapid warm up of the pilot compartment is necessary or for short time application during flight to prevent entering of contaminated air That function...

Страница 351: ...by pulling the knob of the ECS shut off valve In this case the Recirculating valve must remain in the FRESH air position and FAN must be switched off This will seal the cabin from the exterior at the...

Страница 352: ...POWERPLANT AFM DA 50 C Doc No 9 01 01 E Issue 011 07 Page 07 37 14 Dec 2022...

Страница 353: ...y two turbochargers A reduction gear reduces the propeller speed All RPM figures are published in propeller revolutions The engine has a dual channel FADEC Full Authority Digital Engine Control which...

Страница 354: ...The blades are made from wood and are covered with GFRP with an acryl lacquer painted finish A stainless steel sheath protects the outboard leading edges of the blades from erosion The inboard section...

Страница 355: ...ase the blade pitch angle gearbox oil is pumped into the propeller hub Decreasing the oil pressure leads to a decrease of pitch and a higher RPM Depending on the power lever setting the propeller pitc...

Страница 356: ...PID RPM CHANGES THE LIGHT WOODEN PROPELLER BLADES PRODUCE MORE RAPID RPM CHANGES THAN METAL BLADES NOTE A Ground Idle GI function enables the pilot to reduce the power below Flight Idle FI at field el...

Страница 357: ...FADEC FORCE B Switch For normal operation this switch is set to AUTOMATIC The engine is controlled by ECU A In case of a failure of the active engine control unit ECU there should be an automatic swi...

Страница 358: ...t temperature C Gearbox Temp Gearbox oil temperature C Rudder Trim Rudder Trim RPM Propeller RPM 1 min Fuel Qty Fuel quantity US gal Fuel Temp Fuel temperature C Fuel Pres Fuel pressure bar FFlow GPH...

Страница 359: ...Figure 2 G1000 NXi Engine page AFM DA 50 C Doc No 9 01 01 E Issue 011 DA50 A 77 00 00 99A 040A D 07 Page 07 44 14 Dec 2022...

Страница 360: ...Figure 3 G1000 NXi Full Engine Page AFM DA 50 C Doc No 9 01 01 E Issue 011 DA50 A 77 00 00 99A 040A D 07 Page 07 45 14 Dec 2022...

Страница 361: ...nt temperature the external cooling circuit is activated by a thermostatic valve Additionally a coolant to air heat exchanger is provided for the cabin heat system The flow through the heat exchanger...

Страница 362: ...Figure 4 Liquid Cooling System Schematic Diagram AFM DA 50 C Doc No 9 01 01 E Issue 011 DA50 A 75 20 00 99A 040A D 07 Page 07 47 14 Dec 2022...

Страница 363: ...ass is controlled by the FADEC through the waste gate valve A manifold pressure sensor behind the compressor allows the FADEC to calculate the correct position of the waste gate valve This prevents ex...

Страница 364: ...ir Filter RH Engine LH Cylinders Intercooler LH Waste Gate LH Turbine LH Turbo Charger LH Alternate Air Valve LH Air Filter Box LH Air Filter LH Exhaust LH Solenoid Valve LH Solenoid Valve RH Figure 5...

Страница 365: ...raft electrical power In case of failure of one of the systems the engine control automatically switches to the healthier control unit The control unit ensures in normal mode among other functions tha...

Страница 366: ...FUEL SYSTEM AFM DA 50 C Doc No 9 01 01 E Issue 011 07 Page 07 51 14 Dec 2022...

Страница 367: ...ft cylinder bank camshaft and it is part of the engine The fuel fine filter is housed in a disposable cartridge The high pressure pump feeds high pressure fuel in to the common fuel rail which supplie...

Страница 368: ...l Probe Check Valve with Capillary Tank Vent Lines Pressure Relief Valve Fuel Filler Middle Chamber Aux Tank Inboard Chamber Aux Tank Outboard Chamber Aux Tank Fuel Temperature Sensor High Level Trans...

Страница 369: ...by the essential bus and the other one is the emergency pump which is supplied by the main bus The main bus is supplied by the generator 1 in case of its failure the generator 2 supplies the main bus...

Страница 370: ...tent operation After closing the shut off valve it can be easily reopened using the same handle This mechanically actuated handle can be placed in 3 positions see Figure 2 and Figure 3 NORMAL engine s...

Страница 371: ...Figure 2 Schematic Normal Fuel Supply AFM DA 50 C Doc No 9 01 01 E Issue 011 DA50 A 28 00 99 02A 040A D 07 Page 07 56 14 Dec 2022...

Страница 372: ...Figure 3 Schematic Emergency Fuel Supply AFM DA 50 C Doc No 9 01 01 E Issue 011 DA50 A 28 00 99 02A 040A D 07 Page 07 57 14 Dec 2022...

Страница 373: ...for refuelling of the tanks Each fuel tank filler connection is marked with the words Jet A 1 and the permissible fuel designation As an electrical bonding grounding point exhaust portion of the engi...

Страница 374: ...ncludes a protractor for an additional pitch angle measurement Read and record the pitch angle 2 Main LH and Auxiliary Tank RH Unfold the fuel indicator and center it at the nose of wing Read the fuel...

Страница 375: ...3 5 13 2 160 150 143 135 128 4 5 17 0 170 165 155 148 137 5 5 20 8 180 168 160 152 145 6 5 24 6 186 178 170 161 152 7 5 28 4 198 190 180 174 165 8 5 32 2 212 205 198 185 175 9 5 36 0 220 215 210 200...

Страница 376: ...cator Pitch Angle Reading Usable Fuel Quantity 2 3 4 5 6 US gal Liter 425 415 407 400 380 23 5 89 0 Table 2 Auxiliary Tank RH AFM DA 50 C Doc No 9 01 01 E Issue 011 DA50 A 28 40 00 99A 040A D 07 Page...

Страница 377: ...N OF FLIG HT DO NOT USE FOR WEIG HT AND LEVEL DIAMOND Pa rt No D60 281 7 90 00_ 01 Fixation Knob Axle Scale Figure 4 Fuel Level Check Tool AFM DA 50 C Doc No 9 01 01 E Issue 011 DA50 A 28 40 00 99A 0...

Страница 378: ...Main Tank 90mm Center Wing Fuel Quantity Indicator Figure 5 Fuel Level Check Tool on Wing AFM DA 50 C Doc No 9 01 01 E Issue 011 DA50 A 28 40 00 99A 040A D 07 Page 07 63 14 Dec 2022...

Страница 379: ...ELECTRICAL SYSTEMS AFM DA 50 C Doc No 9 01 01 E Issue 011 07 Page 07 64 14 Dec 2022...

Страница 380: ...h are installed under the passengers seats The field of alternator 2 is energized by two 12V 7 2Ah sealed lead acid batteries connected in series 1 1 Alternator Control Each alternator has an alternat...

Страница 381: ...N BUS The MAIN BUS is connected to the Tie Relay via a 50 Amp re circuit breaker Also it is connected to the power output of Alternator 1 and 2 each via a 60 Amp re circuit breaker The MAIN BUS provid...

Страница 382: ...Figure 1 Electrical System AFM DA 50 C Doc No 9 01 01 E Issue 011 DA50 A 24 00 99 00A 040A D 07 Page 07 67 14 Dec 2022...

Страница 383: ...play as airspeed indicator and altimeter The user interface of the Standby Attitude Module allows for simple intuitive operation using a single push and turn control knob Refer to the Mid Continent MD...

Страница 384: ...iliary flight display AFD page that contains information for all active alerts This structure allows the crew to scroll through all system alerts if the alerts window overflows This approach displays...

Страница 385: ...ne glow plugs are powered FUEL XFER The annunciation is active when the fuel transfer from auxiliary to main tank is in progress Table 2 Annunciation Advisory Alerts on the G1000 NXi 4 Message Advisor...

Страница 386: ...GARMIN G1000 NXI AFM DA 50 C Doc No 9 01 01 E Issue 011 07 Page 07 71 14 Dec 2022...

Страница 387: ...ionic box is located in the rear fuselage A push to talk PTT button for the COM portion of the G1000 NXi is mounted on the end of each control stick There are connection facilities for up to 5 headset...

Страница 388: ...n a warning or caution message is received a warning or caution annunciator will flash on the PFD accompanied by an aural tone A warning is accompanied by a repeating tone and a caution is accompanied...

Страница 389: ...Figure 1 Primary Flight Display AFM DA 50 C Doc No 9 01 01 E Issue 011 DA50 A 31 40 99 01A 040A D 07 Page 07 74 14 Dec 2022...

Страница 390: ...isted Additionally the MFD incorporates the controls for the autopilot system Engine instruments are displayed on the MFD Discrete engine sensor information is processed by the Garmin engine airframe...

Страница 391: ...r beacon lights appear on the PFD In addition a clearance recorder records the last 2 minutes of received audio Lights above the selections indicate what selections are active Pressing the red DISPLAY...

Страница 392: ...e pitch and roll attitude sideslip and heading Operation is possible in a degraded mode if the system loses any of these inputs Status messages alert the crew of the loss of any of these inputs The AH...

Страница 393: ...computer ADC provides airspeed altitude vertical speed and air temperature to the display system In addition to the primary displays this information is used by the FMS and TIS systems AFM DA 50 C Doc...

Страница 394: ...g The PFD MFD control unit is installed in the center armrest Access to the control unit is accomplished by a folding mechanism The control unit must be stowed during take off and landing all emergenc...

Страница 395: ...AUTOPILOT AFM DA 50 C Doc No 9 01 01 E Issue 011 07 Page 07 80 14 Dec 2022...

Страница 396: ...FC 700 autopilot and manual electric trim MET will not operate until the system has satisfactorily completed a preflight test The preflight test begins automatically with initial power application to...

Страница 397: ...anual electric trim will be inoperative Loss of GIA 2 will also prevent autopilot and manual electric trim operation but flight director will be available Loss of the standby airspeed indicator standb...

Страница 398: ...with a yellow flashing AP on the PFD accompanied by a two second autopilot disconnect tone Normal disconnects are those initiated by the pilot with the AP DISC switch the manual electric trim switch T...

Страница 399: ...r plane and disengage AP If AP disengaged move AP TRIM switches separately to release Table 2 Warning Alerts on the Automatic Flight Control System AFCS Caution Alerts on the Automatic Flight Control...

Страница 400: ...ow er up and preflight system tests as this may cause the preflight system test to fail or never to start if servos fail their power up tests Power must be cycled to the servos to remedy the sit uatio...

Страница 401: ...PITOT STATIC SYSTEM AFM DA 50 C Doc No 9 01 01 E Issue 011 07 Page 07 86 14 Dec 2022...

Страница 402: ...gh the static ports also on that probe To protect against dirt and condensation there are filters in the system The Pitot probe is electrically heated With the alternate static valve the static pressu...

Страница 403: ...STALL WARNING SYSTEM AFM DA 50 C Doc No 9 01 01 E Issue 011 07 Page 07 88 14 Dec 2022...

Страница 404: ...us sound in the cockpit The lift transducer vane the mounting plate and the complete housing are heated to prevent icing Heating is engaged together with the Pitot heating A toggle to test switch is p...

Страница 405: ...BAGGAGE COMPARTMENT AFM DA 50 C Doc No 9 01 01 E Issue 011 07 Page 07 90 14 Dec 2022...

Страница 406: ...the the baggage tray step in the middle of the compartment Area B is extending from the baggage tray step to the rear wall of the baggage tray Max mass of all items stored only above front barrier hei...

Страница 407: ...Figure 1 Baggage Compartment I AFM DA 50 C Doc No 9 01 01 E Issue 011 DA50 A 25 50 00 99A 040A D 07 Page 07 92 14 Dec 2022...

Страница 408: ...Figure 2 Baggage Compartment II AFM DA 50 C Doc No 9 01 01 E Issue 011 DA50 A 25 50 00 99A 040A D 07 Page 07 93 14 Dec 2022...

Страница 409: ...Figure 3 Baggage Compartment III AFM DA 50 C Doc No 9 01 01 E Issue 011 DA50 A 25 50 00 99A 040A D 07 Page 07 94 14 Dec 2022...

Страница 410: ...Figure 4 Front Barrier and Baggage Tray Step AFM DA 50 C Doc No 9 01 01 E Issue 011 DA50 A 25 50 00 99A 040A D 07 Page 07 95 14 Dec 2022...

Страница 411: ...h a lightning protection system which is connencted to the lightning protection system of the airplane WARNING THE MAXIMUM TRIM MASS IN THE TRIM WEIGHT CONTAINER MUST NOT EXCEED 20 0 KG 44 1 LB WARNIN...

Страница 412: ...08 AIRPLANE HANDLING CARE AND MAINTENANCE AFM DA 50 C Doc No 9 01 01 E Issue 011 08 Page 08 1 14 Dec 2022...

Страница 413: ...GENERAL AFM DA 50 C Doc No 9 01 01 E Issue 011 08 Page 08 2 14 Dec 2022...

Страница 414: ...ground handling and servicing of the airplane The Airplane Maintenance Manual lists certain inspection and maintenance requirements which must be followed if the airplane is to retain a new plane per...

Страница 415: ...currently effective Operator s Manuals Service Instructions Service Letters and Service Bulletins of Continental Aerospace Technologies and mt Propeller must be followed For airframe inspections the...

Страница 416: ...ne Alterations or Repairs Alterations or repairs to the airplane may be carried out only according to the Airplane Maintenance Manual and only by authorized personnel AFM DA 50 C Doc No 9 01 01 E Issu...

Страница 417: ...SERVICING AFM DA 50 C Doc No 9 01 01 E Issue 011 08 Page 08 6 14 Dec 2022...

Страница 418: ...FUEL BURNS AND CAN CAUSE INJURY TO PEOPLE AND DAMAGE TO EQUIPMENT WARNING CONNECT THE AIRPLANE AND THE FUEL SUPPLY VEHICLE TO ELECTRICAL GROUND BEFORE REFUELING IF YOU DO NOT GROUND THE AIRPLANE STAT...

Страница 419: ...move the fuel filler cap located on top of the outer wing Check cap retaining cable for damage 3 Refuel the airplane 4 Install the fuel filler cap 5 Repeat steps step A 2 to step A 4 for the other win...

Страница 420: ...onditions Not applicable 3 Main Procedure A Engine Oil Level Check 1 Open the inspection door on the bottom of the upper left cowling 2 Remove the filler cap 3 Clean the oil dip stick 4 Install the fi...

Страница 421: ...e D Consumable Materials Not applicable E Expendable Parts Not applicable F Safety Conditions Not applicable 3 Main Procedure A Gearbox Oil Level Check 1 Open the inspection door on the front of the r...

Страница 422: ...xpendable Parts Not applicable F Safety Conditions Not applicable 3 Main Procedure A Tire Inflation Pressure Check 1 Remove dust cap from valve stem by turning counterclockwise 2 Connect tire gauge to...

Страница 423: ...GROUND HANDLING AFM DA 50 C Doc No 9 01 01 E Issue 011 08 Page 08 12 14 Dec 2022...

Страница 424: ...he manufacturer to assist steering The steering bar is engaged in the appropriate hole in the nosewheel as shown in Figure 1 The steering bar must be removed before starting the engine In the event th...

Страница 425: ...Max 42 1 Max 42 Figure 1 Steering Bar Legend 1 Fig 1 Nose Wheel AFM DA 50 C Doc No 9 01 01 E Issue 011 DA50 A 15 37 02 00A 040A D 08 Page 08 14 14 Dec 2022...

Страница 426: ...ols It is recommended that the control surfaces gust lock is used when parking outdoors because otherwise the control surfaces can hit the stops in strong tail wind This can lead to excessive wear or...

Страница 427: ...Figure 2 Gust Lock Installation AFM DA 50 C Doc No 9 01 01 E Issue 011 DA50 A 15 37 02 01A 040A D 08 Page 08 16 14 Dec 2022...

Страница 428: ...ane there is a hole which can be used to tie down the airplane to the ground Also on each wing near the wing tip an eyelet with a metric M8 thread can be installed and used as tie down points AFM DA 5...

Страница 429: ...The airplane can be jacked at the two jackpoints located on the lower side of the center wing s LH and RH root ribs as well as at the tail fin AFM DA 50 C Doc No 9 01 01 E Issue 011 DA50 A 15 37 02 0...

Страница 430: ...ewarm water Final cleaning should be carried out with a clean piece of chamois leather or soft cloth Never rub or polish dry acrylic glass 3 Propeller Damage and malfunctions during operation must be...

Страница 431: ...KS 80 Aeroshell Compound 07 AL 5 DTD 406B Table 1 Fluids for cleaning the aircraft from ice and snow A Remove any snow from the airplane using a soft brush B Spray cleaning fluid onto ice covered surf...

Страница 432: ...09 SUPPLEMENTS AFM DA 50 C Supplements Doc No 9 01 01 E Issue 011 09 Page 09 1 14 Dec 2022...

Страница 433: ...quipment according to 06 10 Equipment Description 1 List of Supplements Airplane S N Registration Date No Title Issue Reference applicable YES NO A034 Electronic Stability and Pro tection System ESP 0...

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