the da 40 in a 'capsule' - poh of da 40 (section 7)

the it’s voltage is shown or else batt volt is indicated. 46. The ammeter gives the current with which the alternator is loaded. 47. The landing/taxy lights are on the left wing. 48. Combined position and strobe lights are on the wing tips. 49. Floodlights brightness can be adjusted and it illuminates the inst panel and all levers. 50. The internal inst lighting is controlled by a rotary button. 51. The pitot heating system is protected by thermal fuse. 52. The ALT warning is red in colour and only battery power is now available. 53 Low voltage caption comes on at 24 volts and goes off at 25 volts and is amber in colour. 54. Fuel press wx comes on at 14psi and is red in colour. 55. Fuel low level light comes on at 3 US gal +/- 1 US gal. The indication is calibrated for level flight only and is amber in colour. 56. Oil press light comes on at 25 psi and is red in colour. THE DA 40 IN A ‘CAPSULE’ NOTE: THIS INFORMATION IS TO ASSIST YOU IN PREPARING FOR THE DGCA PAPER ONLY. THE POH REMAINS THE MASTER FOR FLYING AND SUPERSEDES THIS IN CASE OF ANY DISCREPANCY. MIKE A JOHNSINGH Page 6 57. Door warning light comes on when front canopy or/and rear canopy is not closed and locked and is red in colour. 58. The battery is connected to the aircraft electrical system with a 70 amp circuit breaker. 59. The electronic ignition status light is white in colour. 60. The starter warning light is red in colour and comes on when the starter is being operated or when the connection between the starter motor and engine has not broken. 61. The pitot heating caution comes on when a) Pitot heater is off b) Malfunction of pitot heating system and when c) Thermal switch operates. The light is amber in colour. 62. A warning is indicated by the continuous aural alert, flashing of the red wx light and flashing of the red wx light associated with the system. 63. A caution is indicated by the momentary aural alert, flashing of the amber CAUTION light and flashing of the Amber Caution light associated with the system. 64. Low fuel light comes on when the fuel in any one tank is below 3 US gallon +- 1US gallon. This is a caution alarm. When the second tank fuel also drops to less than 3 US gallon +- 1US gallon then the alarm is continuous, caution light is flashed and the LOW FUEL light is flashed. On acknowledged also the LOW FUEL light continues to flash. THE DA 40 IN A ‘CAPSULE’ NOTE: THIS INFORMATION IS TO ASSIST YOU IN PREPARING FOR THE DGCA PAPER ONLY. THE POH REMAINS THE MASTER FOR FLYING AND SUPERSEDES THIS IN CASE OF ANY DISCREPANCY. MIKE A JOHNSINGH Page 7 65. The pitot heater thermal switch operates to keep the probe from overheating. It resets automatically. 66. There are two static measuring orifices at the lower and rear edge of the probe. 67. If airspeed drops below 1.1 times the stalling speed then the stall warning horn sounds. CHAPTER 8 AIRPLANE HDLG, CARE AND MAINTENANCE 68. For short term parking the airplane should be parked into the wind. 69. The control surface gust locks are used for locking the primary controls. 70. The airplane must be kept clean the bright structure, this prevents it from overheating. 71 Max difference permitted in the fuel quantity between left and right tank is 10 US gallons for standard tanks. CHAPTER 1 72. Max take off RPM- 2700. 73. Max take off mass 1200 kg. 74. The place to keep the airplane manual is in the side bag of the forward left seat. THE DA 40 IN A ‘CAPSULE’ NOTE: THIS INFORMATION IS TO ASSIST YOU IN PREPARING FOR THE DGCA PAPER ONLY. THE POH REMAINS THE MASTER FOR FLYING AND SUPERSEDES THIS IN CASE OF ANY DISCREPANCY. MIKE A JOHNSINGH Page 8 75. Span: 11.94 m Length: 8.01m Height: 1.97m 76. Wing Area: 13.54 m sq. MAC: 1.121m AR: 10.53 Dihedral: 5 Deg Sweep: 1 Deg 77. Aileron area: .654m sq (both ailerons) 78. Wing Flap area: 1.56m sq (Both flaps) 79. Horizontal tail: Area: 2.34m sq Elevator area: .665m sq Angle of incidence: - 3 Deg relative to long axis of ac. 80. Vertical Tail: Area: 1.60 sq m Rudder area: .047 sq m. THE DA 40 IN A ‘CAPSULE’ NOTE: THIS INFORMATION IS TO ASSIST YOU IN PREPARING FOR THE DGCA PAPER ONLY. THE POH REMAINS THE MASTER FOR FLYING AND SUPERSEDES THIS IN CASE OF ANY DISCREPANCY. MIKE A JOHNSINGH Page 9 OPERATING LIMITATIONS (CHAPTER 2) 81. Maneuvering speed limits (Va): 980 kg to 1150 Kg- 108 kts 780kg to 980 kg- 94 kts With MAM 40-227 carried out: 1036 kg to 1200 kg- 111kts 780kg to 1036 kg- 94kts 82. V fe: Max flap extension speed- LDG flaps- 91 KIAS. Take off- 108 KIAS. 83. Max structural cruising speed (Vno): 129KIAS 84. Vne: 178KIAS 85. Prop dia: 74 Inch (Max) 72 Inch (Min) 86. Prop pitch angle: 35 Deg +- 1 deg, to 13.5+-.2Deg, at 30 Inch station. 87. Green Arcs: LOWER RED ARC UPPER RED ARC MAP: 13 – 30 in Hg -- -- RPM: 500-2700 -- ABOVE 2700 Oil Temp- 149-230 F -- ABOVE 245 F CHT- 150-475 F -- ABOVE 500 F THE DA 40 IN A ‘CAPSULE’ NOTE: THIS INFORMATION IS TO ASSIST YOU IN PREPARING FOR THE DGCA PAPER ONLY. THE POH REMAINS THE MASTER FOR FLYING AND SUPERSEDES THIS IN CASE OF ANY DISCREPANCY. MIKE A JOHNSINGH Page 10 OIL PRESS: 56- 95PSI 25 PSI ABOVE 97 PSI FUEL PRESS: 14 – 35 PSI 14 PSI ABOVE 35 PSI VOLT- 25.1 to 30 V 24.1V ABOVE 32 V AMMETER- 2-75 A -- -- FUEL QUANTITY (STD TANK) 0-15/0-17 FUEL QUANTITY (LG RANGE) 0-16 + 0-9 US GAL Oil quantity min- 4 quarts, max 8 quarts. 88. There are two types of annunciator panels: DAI and white wire. 89. Warning light for oil press- Oil press below 25 PSI 90. Warning light for fuel press- Press below 14 PSI 91. CAUTION LIGHT FOR FUEL INDICATES US GAL 3 +- 1GAL IN TANK. 92. Maximum take off mass Normal -1150 kg MAM 40-227 MODIFIED- 1200 KG 93. Maximum landing mass: (Original Strut) - 1092 kg 94. Maximum landing mass: (Modified strut) - 1150 Kg 95. Max load in baggage compartment: 30 Kg 96. Max load in baggage tube: 5 Kg 97. The most forward position of CG is a) 2.40m aft of datum point upto 980 kg. THE DA 40 IN A ‘CAPSULE’ NOTE: THIS INFORMATION IS TO ASSIST YOU IN PREPARING FOR THE DGCA PAPER ONLY. THE POH REMAINS THE MASTER FOR FLYING AND SUPERSEDES THIS IN CASE OF ANY DISCREPANCY. MIKE A JOHNSINGH Page 11 b) 2.46m aft of datum point upto 1150kg. c) 2.48m aft of datum point upto 1200 kg. 98. The most rearward position of CG is a) 2.59m aft of datum point with standard tank b) 2.55 m aft of DP with long range tanks. 99. The normal category ac can carry out maneuvers up to AOB of 60 deg. 100. Utility category can maneuver up to AOB of 90 deg, but AH and DG are affected by AOB over 60 deg. 101. Load factors. Normal/(Utility)Category aircraft. AT Va AT Vne With Flap Down Positive 3.8g (4.4) 3.8(4.4) 2.0 Negative -1.52 (-1.76) Nil (-1) Nil 102. The maximum demonstrated operating altitude is 16,400 feet/5000mtrs. 102. Flights into known icing conditions are prohibited and also into known thunderstorms. 103. Maximum number of occupants are 4. 104. Fuel type is AV Gas 100LL. 105. Total fuel quantity: 20.6 X 2 US gal or appx 78 X 2 litres. THE DA 40 IN A ‘CAPSULE’ NOTE: THIS INFORMATION IS TO ASSIST YOU IN PREPARING FOR THE DGCA PAPER ONLY. THE POH REMAINS THE MASTER FOR FLYING AND SUPERSEDES THIS IN CASE OF ANY DISCREPANCY. MIKE A JOHNSINGH Page 12 106. Total unusable fuel is 2 X .5 US gal or appx 2 X 2 litres. 107. Fuel indication is by capacitance. 108. Upto serial no 40.054 the gauge shows 15 US gallons. 109. Serial no 40.055 and above the fuel gauge shows 17 US gal. 110. Arcs of the ASI. MARKING IAS IMP WHITE ARC 49-91 KIAS FULL FLAP OP LIMIT GREEN ARC 52-129 KIAS NORMAL OP LIMIT OF AC YELLOW ARC 129-178 KIAS CAUTION RANGE – SMOOTH AIR ONLY RED LINE(Vne) 178 KIAS MAXIMUM SPD IN ALL CONDITIONS. 111. Max difference in fuel between Lt and Rt tank is 10 US Gallons for standard tanks. 112. Max difference in fuel between Lt and Rt tank is 08 US Gallons for long range tanks. 113. The oil used in the DA 40 is SAE 15W50. 114. The min/max oil required in VFR is 4-8 Quarts. 115. The min/max oil required in IFR is 6-8 Quarts. 116. Max spd with full flap deflection is 91 KIAS. 117. Max spd with partial flap deflection is 108 KIAS. THE DA 40 IN A ‘CAPSULE’ NOTE: THIS INFORMATION IS TO ASSIST YOU IN PREPARING FOR THE DGCA PAPER ONLY. THE POH REMAINS THE MASTER FOR FLYING AND SUPERSEDES THIS IN CASE OF ANY DISCREPANCY. MIKE A JOHNSINGH Page 13 118. If alternative static is open emergency window and cockpit Vent must be closed. 119. The airplane must not be operated below -40 deg centigrade. CHAPTER 3 (EMERGENCY PROCEDURES) 120. Air speeds in emergencies. Engine failure after takeoff flaps T/O: 72 KIAS( 1150kg) : 74 KIAS (1200kg) 121. Air speed for best glide flaps up: 73 KIAS( 1150kg) : 76 KIAS (1200kg) 122. Air speed for Ldg engine off flaps up: 73 KIAS( 1150kg) : 76 KIAS (1200kg) Flaps toff: 72 KIAS( 1150kg) : 74 KIAS (1200kg) Flaps Ldg : 71 KIAS( 1150kg) : 73 KIAS (1200kg) 123. Engine rough running in air: 73 KIAS( 1150kg) : 76 KIAS (1200kg) 124. Restarting engine in the air windmilling prop: Min Speed 70 KIAS THE DA 40 IN A ‘CAPSULE’ NOTE: THIS INFORMATION IS TO ASSIST YOU IN PREPARING FOR THE DGCA PAPER ONLY. THE POH REMAINS THE MASTER FOR FLYING AND SUPERSEDES THIS IN CASE OF ANY DISCREPANCY. MIKE A JOHNSINGH Page 14 : Min spd for wind milling 65 KIAS : Recommended spd to fly is 80 KIAS. 125. Restarting in air with stationary prop: Min Spd 80 KIAS 126. Ht loss to start engine with prop stationary: 1000 ft/300m 127. Emergency elect system powers AH and floodlight in IFR version of DA 40. 128. Gliding spd of ac with flaps up is 76 KIAS for 1200kg and 73 KIAS for 1150 Kg. 129. The glide ratio is 1: 8.8 in wind milling configuration and for every 1000 ft ht loss the ac travels 1.45 Nm. 130. When the propeller is stationary then the glide ratio is 1: 10.3 and the ac travels 1.7 Nm for every 1000 feet loss of height. 131. Emergency landing speed engine off: 73 KIAS( 1150kg) : 76 KIAS (1200kg) 132. Spin recovery actions: Throttle IDLE, Opposite rudder, Control stick forward, ailerons neutral, Flaps up. When rotation stops, rudder neutral, stick back and ease out keeping below Vne. 133. Incase of suspected CO presence in cockpit front canopy can be unlatched in during flight. Flight characteristics will not vary greatly. CHAPTER 4A (NORMAL OPERATING PROCEDURES) THE DA 40 IN A ‘CAPSULE’ NOTE: THIS INFORMATION IS TO ASSIST YOU IN PREPARING FOR THE DGCA PAPER ONLY. THE POH REMAINS THE MASTER FOR FLYING AND SUPERSEDES THIS IN CASE OF ANY DISCREPANCY. MIKE A JOHNSINGH Page 15 134. Airspeed for climb after T/O. Vy or Best ROC with flaps to toff. 1150 KG: 66 KIAS 1200 KG: 67 KIAS 135. Airspeed for cruise climb. 1150 KG: 73 KIAS 1200 KG: 76 KIAS 136. Approach speed. Flaps to landing position. 1150 KG : 71 KIAS 1200 KG : 73 KIAS 137. Minimum spd during touch and go. Flaps to takeoff. 1150 KG: 66 KIAS 1200 KG: 67 KIAS 138. The main tire inflation press is 36 PSI and nose tire inflation pressure is 29 PSI. 139. Do not operate starter motor for more than 10 sec and let it cool for 20 sec. After 06 attempts to start let motor cool for 30 mins. 140. If ambient temp is below 0 Deg cel then pre heat and ext power source is recommended. 141. Warm up engine at 1500 RPM for 2-5 minutes. 142. Oil press should be in green sector within 15 sec of starting. If not then, switch off. 143. Fuel press should be 14 to 35 PSI. 144. Idle rpm should be 600-800 RPM. 145. Nose wheel lift off spd is 59 KIAS. (Page 4a- 25) THE DA 40 IN A ‘CAPSULE’ NOTE: THIS INFORMATION IS TO ASSIST YOU IN PREPARING FOR THE DGCA PAPER ONLY. THE POH REMAINS THE MASTER FOR FLYING AND SUPERSEDES THIS IN CASE OF ANY DISCREPANCY. MIKE A JOHNSINGH Page 16 145. To prevent vapor lock at high ambient temperatures run engine at speeds of 1800 RPM or more. 146. To check both tanks are feeding run at 1500 RPM for 01 minute. 147. In magneto check Max RPM drop permitted is 175 RPM and max difference is 50 RPM. 148. Take off spd at 1150 KG is 66 KIAS and at 1200 KG is 67 KIAS. (Page 4A -25a.) 149. CHT should be between 150 – 400 deg Fahrenheit and and should not exceed 435 deg F in fast cruise. MAX CHT is 500 deg F. 150. Best economy mixture is at 75% power, to achieve it lean mixture till engine runs rough and then enrich till the smooth running and EGT is maximum. 151. The max CHT is 500 deg F. 152. The best power mixture is at 75 % Power and the enrich till EGT is 100 Deg F lower. 153. When reducing power the CHT should not drop more than 50 deg F per minute. 154. Approach speed for 1200 KG mass is 73 KIAS and for 1150 Kg mass it is 71 KIAS. 155. Go around speed is 67 KIAS for 1200 Kg and 66 KIAS for 1150 kg. ABNORMAL OPERATIONS (CHAPTER 4B) 156. Precautionary approach speed is 76 KIAS for 1200 kg ac and 73 KIAS for 1150 Kg ac. THE DA 40 IN A ‘CAPSULE’ NOTE: THIS INFORMATION IS TO ASSIST YOU IN PREPARING FOR THE DGCA PAPER ONLY. THE POH REMAINS THE MASTER FOR FLYING AND SUPERSEDES THIS IN CASE OF ANY DISCREPANCY. MIKE A JOHNSINGH Page 17 157. If the oil temp reads constant 26 deg F or 317 deg F then the sensor is at fault. 158. Take off speed from short grass strip. 67 KIAS for 1200 kg ac and 66 KIAS for 1150 kg ac. 159. Landing with flap up or flaps to take off: for 1200 kg ac use 76 KIAS and for 1150 kg ac use 73 KIAS. CHAPTER V (PERFORMANCE) 160. At ISA + 15 deg C the ac engine power deteriorates by 3% and at ISA – 15 Deg C it improves by 3%. 161. Stalling speeds: ST AND LEVEL 1200 KG FLAPS UP : 53 KIAS 1150 KG FLAPS UP: 52 KIAS T/O : 52 KIAS T/O : 51 KIAS LDG : 52 KIAS LDG : 49 KIAS 162. Max cross wind component is 20 KIAS. 163. Lift off speed is 59 KIAS and climb out speed is 67 KIAS for 1200 kg and 66 KIAS for 1150 kg ac. 164. The climb gradient of the DA 40 is 7 % on go around with flaps to LDG the speed is to be maintained 73 KIAS. 165. The correct fuel indication of quantity takes 2 minutes to register after switch actuation. 166. The Datum Plane is 2.194 m ahead of the most forward point of the root wing on the stub wing. 167. The mass of fuel is taken to be .72 kg/ liter and engine oil is .89 kg/liter. Supercedes THE DA 40 IN A ‘CAPSULE’ NOTE: THIS INFORMATION IS TO ASSIST YOU IN PREPARING FOR THE DGCA PAPER ONLY. THE POH REMAINS THE MASTER FOR FLYING AND SUPERSEDES THIS IN CASE OF ANY DISCREPANCY. MIKE A JOHNSINGH Page 18 168. Forward limit of CG is 2.40m for up to 980 kg, 2.46m for up to 1150 kg and 2.48 for up to 1200 kg ac. SUPPLEMENTS(CHAPTER 9) 169. The ELT ACK Model E -01 transmits a distress tone 121.5 MHz and 243 MHz . When it transmits then the red LED flashes. 170. The acceleration indicator activates the ELT when it senses a change in velocity in the Longitudinal Axis. 171. The ELT has a three position switch. ON-OFF-ARMED. 172. The ELT may be activated in turbulence and hard landings. 173. For flight the ELT should be in ARMED mode. In this mode it has no power consumption. 174. The ELT is located on the right side of the fuselage. 175. The ELT battery should be replaced after the transmitter has been operative for more than one cumulative hour. 176. The ELT is independent of the AC electrical system. Power is given to the ELT by 8 batteries. 177. The ARTEX ME 406 ELT if fitted operates on 121.5 Mhz and 406.025 Mhz. 178 The 406.025 Tx transmits for 520 millisecond every 50 sec and sends a message to the satellite. 179. It gives the serial number of the Tx or airplane ID, Country Code and ID code. 180. The 406.025Mhz Tx give a very accurate fix and it is 1-2 kms as compared to the 15-20kms of the 121.5Mhz Tx. THE DA 40 IN A ‘CAPSULE’ NOTE: THIS INFORMATION IS TO ASSIST YOU IN PREPARING FOR THE DGCA PAPER ONLY. THE POH REMAINS THE MASTER FOR FLYING AND SUPERSEDES THIS IN CASE OF ANY DISCREPANCY. MIKE A JOHNSINGH Page 19 INDIRA GANDHI RASHTRIYA URAN AKADEMI DA-40 : Multiple Choice Questions Name: Date: (Total Marks: 50) ------------------------------------------------------------------------------------------------------------------- Q.1. Engine specification of Diamond A/c is; (a) IO-320-D1A (b) IO-360-M1A (c) IO-540-M1B (d) AIO-360-M1A Q.2. The rated output power of engine in DA-40 at max continuous rpm is; (a) 180 hp at 2400 rpm (b) 180 hp at 2700 rpm (c) 160 hp at 2400 rpm (d) 160 hp at 270 rpm Q.3. The normal operating range of oil pressure is between; (a) 25 to 95 psi (b) 55 to 98 psi (c) 56 to 95 psi (d) 25 to 98 psi Q.4. The minimum & maximum oil capacity of the sump in diamond A/c engine is between; (a) 4 to 6 quarts (b) 3 to 8 quarts (c) 4 to 8 quarts (d) 4 to 6 quarts Q.5. maximum oil temperature of engine in DA-40 a/c is; (a) 145°F (b) 245°F (c) 180°F (d) 247°F Q.6. The maximum take-off mass of Diamond a/c is; (a) 1200 lbs (b) 1150 Kgs (c) 1150 lbs (d) 1200 Kgs Q.7. The maximum indicated fuel quantity (on display) in DA-40 a/c is; (a) 20 u.s gallon per tank (b) 8.5 u.s gallon per tank (c) 17 u.s gallon per tank (d) 10 u.s gallon per tank Q.8. The seats fitted on Diamond DA-40 a/c is/are; (a) Adjustable fore & aft (b) Adjustable back & forth (c) Non-adjustable (d) Adjustable very slightly Q.9. In case of main power failure, the emergency battery supplies power to which of following units; (a) PFD & MFD (b) Artificial horizon & flood lights (c) Artificial horizon A.S.I. (d) Only to flood lights Altimeter & Compass Q.10. The emergency battery supplies power to respective units for duration of; (a) Half an hour only (b) At least one & half hour (c) An hour only (d) None is correct Q.11. The rudder pedals in Diamond DA-40 a/c is/are; (a) Non-adjustable (b) Adjustable back & forth (c) Adjustable very small (d) None is correct Q.12. The rudder tab fitted on DA-40 a/c is; (a) Adjustable (b) Fixed (c) Trim able (d) Has no tab Q.13. The Aileron tab fitted on DA-40 a/c is; (a) Both ailerons have trim able tabs (b) Both ailerons have fixed tabs (c) Only one ailerons have trim able tabs (d) Only one aileron has fixed tab Q.14. The elevator fitted on DA-40 a/c has which type of tab; (a) Trim able (b) Fixed (c) Adjustable on ground only (d) Adjustable in flight only Q.15. The OAT probe is located at what particular location on DA-40 a/c; (a) On left side (b) On right side (c) On both sides (d) Has no fixed location Q.16. The Diamond DA-40 a/c is steerable while taxiing with the help of; (a) Rudder pedals (b) Differential brakes (c) Both rudder pedals & brakes (d) None is correct Q.17. The Nose wheel fitted on Diamond DA-40 a/c is; (a) Castor type (b) Fixed type (c) Retractable (d) Both ‘a & ‘b’ are correct Q.18. The alternate static valve is installed at what location; (a) On left fuselage side wall inside cockpit (b) On right fuselage side wall inside cockpit (c) On instrument panel (d) On center console Q.19. The main tires have tyre pressure of; (a) 29 psi (b) 30 psi (c) 36 psi (d) 32 psi Q.20. The nose wheel tyre has tyre pressure of; (a) 30 psi (b) 25psi (c) 29 psi (d) 32 psi Q.21. The flaps installed on Diamond DA-40 a/c are of; (a) Electrical type (b) Pneumatic type (c) Mechanical type (d) None is correct Q.22. The throttle lever installed on Diamond DA-40 a/c has what particular combination; (a) Large, black knob, lever, to forward is max power (b) Small, red knob, lever, to rear pos in max power (c) Large, black knob, lever, to rear pos in min power (d) Small, red knob, lever, to rear color handle is; Q.23. The central lever with blue color handle is; (a) Throttle lever (b) Propeller lever (c) Mixture lever (d) Parking brake lever Q.24. The right hand lever with red color handle is; (a) Throttle lever (b) Mixture lever (c) Propeller lever (d) Parking brake lever Q.25. The stall warning orifice located on left wing leading edge is operated by means of; (a) Suction activating a horn (b) Pressure activating a horn (c) Suction activating a horn and annunciator (d) Pressure activating a horn and annunciator INDIRA GANDHI RASHTRIYA URAN AKADEMI WRITTEN TEST Name: Date: PART-I: DA-40 1. The max landing weight is ________________ (1150 kg) 2. The max T/O weight is __________________ (1200 Kg) 3. The wing area is ___________________ (145.7 sq ft) 4. Mean Aerodynamic chord is ________________ (3'8.1 ft) 5. Max diameter of propeller is _______________ (5'10.9 ft) 6. Total usable fuel ____________ and unusable is _________ standard tanks (2x20.1 USG & 2x0.5 USG) 7. The permissible max positive load factor is ________ and -ve load factor is ____ at VA (+3.8 & -1.52) 8. Min oil capacity is_____ and max oil capacity is________ (4quarts & 8 quarts) 9. Length of A/c is _____________________ (26'3 ft) 10. Height of A/c _____________________ (6'6 ft) 11. Stalls speeds in T/o configuration _________________ (52 kts) 12. A/c model No. ____________________ (Diamond DA-40) 13. Propeller model No.___________________ (Hartzell HC-C2YR- 1BFP/F-7497) 14. Flaps setting in T/o _________________ & landing _________________ (17° ± 1° & 42° ± 1°) 15. Type of electrical system is ________________ (28 Volts DC system) 16. Aspects of Radio__________________ (10.53) 17. Most forward CG __________ & most rearward CG _______________for AUW 1200 kg & standard tanks. (2.48 & 2.59) 18. Green arc of the following: a) Oil temp (149°- 230°F) b) Oil pressure (56 – 95 psi) c) CHT (150° - 475°F) d) Manifold pressure (13" – 30" Hg) e) Fuel pressure (14 – 35 psi) f) RPM (500 – 2400 RPM) g) Voltage (25.1 – 30 V) 19. State relevant speed a) Vso (52 kts) b) Vs1 (52 kts) c) VFE (ldg – 91 kts, T/o – 108 kts) d) VNO (129 kts) e) VNE 178 kts) f) VA (above 1150 kg) (111 kts) PART-II : EMERGENCIES: (35 Marks) Q.1. Procedure for forced landing with engine failed. - (5 Marks) Ans: i) Select suitable landing Area. If no level landing area available, select and upward slope ii) Consider winds iii) Approach : If possible fly along shortcut rectangular circuit on the d/w leg, landing area should be inspected for obstacles. iv) Airspeed – 76 kts v) Advise – ATC vi) Fuel selector – Off When certain landing field will be reached. vii) Flaps landing viii) Safety harness – Tighten ix) Ignition – Off x) Master switch – Off xi) Touchdown - lowest possible Airspeed. Q.2. Restarting engine in flight with propeller. - (5 marks) a)Stationary Ans: i) Airspeed – 80 kts ii) Electrical load – Reduce iii) Avionics Master Switch – Off iv) Master Switch (Battery) – On v) Mixture - Set vi) Fuel Selector – Fullest Tanks vii) Fuel Pump - On viii) Alternate Air - Open ix) Ignition – Start Note :- By increasing airspeed above 130 kts propeller will windmill . The ignition switch should be set to both. An altitude loss of at least 1000’ must be allowed. Q.3 Restarting engine in flight with propeller. b)Wind milling Ans: i) Airspeed – 80 kts ii) Fuel selector – Fullest Tanks iii) Ignition switch – Both iv) Mixture – Check Position v) Fuel Pump - On vi) Alternate Air – Open If engine does not start :- vii) Mixture – Push forward slowly until engine starts. Q.4. Engine fire :- - (10 Marks) a) On ground Ans: i) Fuel selector – Off ii) Cabin heat – Off iii) Brakes – Apply After stand still :- iv) Throttle – Max Power v) Master switch – Off When engine has stopped vi) Canopy - Open vii) Airplane – Evacuate immediately Q.5. Engine fire :- b) In flight :- Ans: i) Cabin Heat – Off ii) Select appropriate emergency landing field. When landing area is assured. iii) Fuel selector – Off iv) Throttle – Max Power v) Fuel Pump – Off vi) Emergency windows – Open if required carryout emergency landing with engine – off Q.6. In flight overvoltage light illuminates. - (5 Marks) Ans: i) Essential Bus – On ii) Master switch (Alt side only) – Off iii) unnecessary Equipment – Off (specially Pitot Heat) iv) Land – Nearest Airfield Q.7. Door warning light on. - (5 Marks) Ans: i) Airspeed – Reduce ii) Canopy – Check visually if closed iii) Rear Passenger Door – check visually if closed iv) Warning – Never unlock the rear passenger door during flight. If may break away. Land as soon as possible. Q-1 QNH IS:- (A) the airfield barometric pressure (B) the setting that will give zero indication on the airfield (C) the equivalent sea level pressure at the airfield (D) the setting that will indicate airfield height Q-2 what is density altitude: (a) Altitude in the standard atmosphere at which the prevailing density is equal to the density in the standard atmosphere (b) Pressure altitude corrected for prevailing temp (c) Temperature altitude (d) Pressure corrected Q-3 A radio altimeter is: (a) Ground based and measures true altitude (b) Ground based and measure true height (c) a/c based and measure true altitude (d) a/c based and measure true height DIAMOND DA-40 QUESTIONS BY JP SHARMA Note: Ref means the paragraph number of airplane flight manual 1. Weight of the DA-40 with unusable fuel and maximum oil is called---------- Ans: Empty mass. Ref: 1.5 (d) 2. VFE is ------------- Ans: Maximum flaps extended speed. Ref: 1.5 (a) 3. In Air Speed Indicator, the green arc is ---------- Ans: 52 KIAS – 129 KIAS. Ref: 2.3 Note : All the options given were wrong. Objection was filed. 4. Maximum take-off mass for normal category is---------- (a) 1150 Kg (b) 1200 Kg if MAM 40-227 is incorporated (c) Both (a) and (b) are correct Ans: (c) Both (a) and (b) are correct Ref: 2.7 Page 2.11a 5. Maximum continuous power is---------- Ans: 180 HP at 2700 RPM Ref: 7.9.1 read with Hartzell supplement page 8 of 10. 6. The engine is---------- Ans: Lycoming, IO-360-M1A, air cooled, four cylinder, four stroke. Ref: 7.9.1 7. Maneuvering speed for mass 1036 Kg to up to 1200 Kg is--------- Ans: 111 KIAS. Ref: 2.2 Page 2.3 (a) 8. Low voltage caution is illuminated---------- Ans: When on board voltage falls below 24 volt. Ref: 7.11.2 9. Oil pressure warning light is illuminated---------- Ans: When oil pressure falls below 25 Psi. Ref: 7.11.2 10. Fuel pressure warning light is illuminated---------- Ans: When fuel pressure falls below 14 Psi. Ref: 7.11.2 11. Maximum structural cruising speed is---------- Ans: 129 KIAS Ref: 2.2 12. The colour of the starter warning light is ---------- Ans: Red Ref: 2.6 and 7.11.2 13. The datum plane is located---------- Ans: 2.194 M forward of the most forward point of the root rib on the stub wing. Ref: 6.2 14. Approved maneuvers for the Normal and utility category are ---------- Ans: Maneuvers with 60° bank and 90° bank. Ref: 2.9 15. Maximum positive load factor for normal category is---------- Ans: 3.8 at VA and 3.8 at VNE Ref: 2.10 16. Emergency battery in IFR model supplies power to the attitude gyro and flood light for--- ------- Ans: 90 minutes Ref: 7.11.1 17. The speed after which take off can not be abandoned---------- Answer: 59 KIAS Ref: 4A.3.7 Note: The question has insufficient information. 59 KIAS being the VR, is the closest answer 18. A stable oil temperature of 26° F or 317° F suggests----------- Ans: Failure of oil temperature sensor. Ref: 3.2.3 (d) 19. Restarting the DA-40 engine is possible at all airspeeds ---------- Ans: Above 70 KIAS and upto VNE Ref: 3.2.4 20. Restarting the engine is possible at all airspeeds ---------- Ans: Above 80 KIAS and upto VNE Ref: 3.2.6 21. Presence of carbon mono-oxide is indicated by ---------- Ans: Visual alarm Ref: 3.7.6 22. The starter duty cycle is---------- Ans: 10 seconds ON, 6 attempts, half an hour cooling period. Ref: 4A.3.3 (a) 23. Before take off engine must run on each tank for---------- Ans: At least 1 minute at 1500 RPM. Ref: 4A.3.6 24. Oil pressure should be in green arc---------- Ans: Within 15 seconds after starting engine. Ref: 4A.3.3 25. To optimize engine life, the CHT should lie ---------- Ans: Between 150° F and 400° F in continuous operation. Ref: 4A.3.9 26. Oil temperature should not remain under 180° F for long periods so as to---------- Ans: Avoid accumulation of condensation water. Ref: 4A.3.9 27. The maximum difference permitted in fuel quantity is ---------- Ans: 10 US Gallons Ref: 4A.3.9 28. The mixture leaning procedure for best power is---------- Ans: The mixture should first be set for best economy. The mixture should then be enriched until the EGT is approximately 100° F lower. Ref: 4A.3.10 Note: None of the options was correct. Objection was filed. 29. The airspeed for going around for a mass of (not remembered) is---------- Ans: One of the following is the correct answer:- 67 KIAS (1200 Kg) 66 KIAS (1150 Kg) 60 KIAS (1000 Kg) 54 KIAS (850 Kg) Ref: 4A.3.13 30. Above a safe height, for a mass of (not remembered) the RPM and airspeed should be---- ------ Ans: One of the following is the correct answer:- RPM 2400, airspeed 76 KIAS RPM 2400, airspeed 76 KIAS RPM 2400, airspeed 76 KIAS RPM 2400, airspeed 76 KIAS Ref: 4A.3.13 31. An uphill slope of 2% (2 M per 100 M or 2 feet per 100 feet) will result in an increase in the take off distance of approximately---------- Ans: 10 % Ref: 5.3.6 32. Refer the given performance chart (the chart is same as in 5.3.7). Pressure altitude is 5000 feet, temperature is 12° F, take off mass is 1150 Kg, The rate of climb is---------- Ans: 3.0 M/S Ref: 5.3.7 33. A landing mass above 1150 Kg up to 1200 Kg will increase the landing over------- Ans: 50 feet Ref: 5.3.10 page 5-16a Note: Question was not complete. None of the options was correct. Correct answer ought to be - “Increase landing distance over 50 feet obstacle by 6 %”. “50 feet” was the closest option. 34. The circuit breaker for the rudder pedal adjustment is located---------- Ans: At the rear wall of the leg room. Ref: 35. When the lower white light is illuminated the flaps are in ---------- Ans: Landing position Ref: 7.3 36. In the given diagram (the diagram is same as in 7.4 (IFR Instrument panel) page 7.9) the instrument labeled 11 is---------- Ans: Altimeter Ref: 7.4, IFR instrument panel diagram on page 7.9 37. In the given diagram (the diagram is same as in 7.4 (IFR Instrument panel) page 7.9) the instrument labeled 19 is---------- Ans: Course Deviation Indicator Ref: 7.4, IFR instrument panel diagram on page 7.9 38 Which of the button in the given diagram (the diagram is same as in 7.9.4) has an addition function on switch on: Display mode? Ans: Button 3 Ref: 7.9.4 39. Stall warning horn sounds when---------- Ans: The speed is below 1.1 times the stall speed. Ref: 7.3 40. Autopilot engagement speeds are ---------- Ans: Minimum 70 KIAS and maximum 165 KIAS Ref: Supplement for Autopilot KAP 140 for DA 40 AFM 41. Autopilot should be disengaged below---------- Ans: 200 feet AGL in approach operations and below 800 feet in all other operations. Ref: Supplement for Autopilot KAP 140 for DA 40 AFM 42. Ans: Ref: 43. Ans: Ref: 44. Ans: Ref: 45. Ans: Ref: 46. Ans: Ref: 47. Ans: Ref: 48. Ans: Ref: 49. Ans: Ref: 50. Ans: Ref: 1 | P a g e NFTI DA 40 Name:…………………………………………………………. Date:…………………………………………………………… Marks:…………………………………………………………………. 1. The operating limits are given in section: a) Section 1 b) Section 2 b c) Section 3 d) Section 4 2. The Emergency procedures are given in section: a) Section 1 b) Section 2 c c) Section 3 d) Section 4 3. Leading edge sweep is …………deg. a) 1 Deg a b) 2 Deg c) 3 Deg d) 5 Deg 4. The MAC length is ……………m a) 1.122m b) 1.123m c) 1.124m d d) 1.121m 5. The best angle of climb speed is called a) Vx b) Vy c) Vz a d) Vno 6. The max flap extension speed is called a) Vfo b) Vfa c) Vfe c d) Vno 7. Density altitude is the altitude at which: a) Altitude at ISA conditions when air density equals current air density a b) The altitude given by the altimeter with QNH 2 | P a g e NFTI DA 40 c) The altitude given by the altimeter when it has QFE set 8. Empty mass has the following a) Useable fuel + VFR Oil requirements + All operating consumables b) Unuseable fuel + VFR Oil requirements + All operating consumables c) Useable fuel + Maximum oil + All operating consumables d) Unusable fuel + Maximum Oil + All operating consumables d 9. Green arc of ASI is from: a) 49 KIAS to 91 KIAS b) 52 KIAS to 129 KIAS b c) 53 KIAS to 128 KIAS d) 51 KIAS to 129 KIAS 10. Minimum fuel press is a) 13 PSI b) 25 PSI c) 14 PSI c d) 23 PSI 11. Maximum CHT is …………….def F a) 245 Deg F b) 500 Deg F c) 545 Deg F b d) 230 Deg F 12. Minimum oil pressure at idle is ……………PSI a) 25 PSI b) 20 PSI c) 21 PSI a d) 22 PSI 13. The low Voltage comes on at …………..V a) 24. V b) 24.1V c) 25 V a d) 25.1V 14. Up to …………………serial number the fuel quantity is shown as 15 US Gallons. a) 40.055 b) 40.056 c c) 40.054 d) 40.057 15. The maximum take off mass is a) 1150 Kg 3 | P a g e NFTI DA 40 b) 1200 Kg c c) Both a and b 16. DAI variant light is ………………shape. a) Square b) Circle c) Rectangle a d) Triangle 17. The most rearward CG position is ……………..m with long range tanks. a) 2.59m b) 2.58m c) 2.56m d d) 2.55m 18. The datum plane is located …………m from root rib of stub wing. a) 2.194m b) 2.193m a c) 2.194cm d) 2.193cm 19. The maximum angle of bank of utility and normal category is …………deg a) 60 deg and 90 deg b) 90 deg and 60 deg b c) 60 deg and 80 deg d) 80 deg and 60 deg 20. The accuracy of the AH and DG gets affected above ……………deg bank. a) 90 Deg b) 75 Deg c) 60 Deg c d) 45 Deg 21. The max load factor with flaps to take off is ………………. a) 2 g b) 3.8 g c) 4.4 g a d) Zero g 22. The max load factor with flaps to landing is a) 1 g b) 2 g c) 3 g b d) Zero g 4 | P a g e NFTI DA 40 23. The minimum quantity of oil for IFR is ……………quarts. a) 6 Quarts b) 4 Quarts a c) 8 quarts 24. The max speed to fly with flaps to landing position is……………… a) 91 KIAS b) 91 KTAS c) 108 KIAS a d) 108 KTAS 25. The maximum time available from emergency power pack is: a) 30 minutes b) 45 minutes c) 60 minutes d d) 90 minutes 26. Engine rough running speed for 850 Kg a) 57 KIAS b) 58 KIAS c) 59 KIAS d d) 60 KIAS 27. Oil temperature sensor fail is given by oil temp of a) 26 deg F and 317 deg F b) 26 deg C and 317 deg C c) 245 Deg F a d) 245 Deg C 28. The minimum speed to restart the engine with wind milling prop is a) 65 KIAS b) 65 KTAS c c) 70 KIAS d) 80 KIAS 29. Restarting the engine with wind milling prop will cause a height loss of…………. a) 1000m b) 1000 feet b c) 300 feet d) 3000m 30. Speed to start engine in air with stationary propeller is ………… a) 65 KIAS b) 70 KIAS c) 75 KIAS d 5 | P a g e NFTI DA 40 d) 80 KIAS 31. The presence of CO is indicated by a ……………….alarm. a) Alarm sound b) Visual Alarm b c) Both a and b 32. Air speed for cruise climb for 1150 kg is………….KIAS a) 73 KIAS b) 76 KIAS a c) 68 KIAS d) 71 KIAS 33. Minimum speed during touch and go is …………KIAS for 1200 KG a) 71 KIAS b) 73 KIAS c) 67 KIAS c d) 76 KIAS 34. Best ROC with flaps to take off is ……………KIAS for 1000 KG is a) 60 KIAS b) 66 KIAS c) 67 KIAS a d) 54 KIAS 35. In the long range tanks the correct indication takes ………..minutes a) 4 Minutes b) 3 Minutes c) 2 Minutes c d) 1 Minutes 36. The stall warning horn comes on at …………….times the stall speed. a) 1.4 times b) 1.3 times d c) 1.2 times d) 1.1 times 37. The starter motor timings are ………….sec of operation …………….sec of cooling. a) 10 sec and 30 sec b) 10 sec and 20 sec c) 20 sec and 30 minutes d d) 10 sec and 30 minutes 38. The oil pressure should register within ………..sec a) 1 Sec b) 5 Sec d 6 | P a g e NFTI DA 40 c) 10 Sec d) 15 Sec 39. The warm up time for the engine is …………………RPM for ………..to …………….minutes. a) 1200 RPM for 2 to 5 minutes b) 1400 RPM for 2 to 5 minutes c) 1500 RPM for 2 to 5 minutes c d) 1800 RPM for 2 to 5 minutes 40. In strong cross wind take off the steering can be augmented with the use of …………………….. a) Ailerons b) Throttle c c) Toe brakes 41. To optimize engine life ensure that the CHT does not cross ……deg F in fast cruise. a) 435 Deg F b) 400 Deg F c c) 450 Deg F 42. If oil temperature stays below …………….deg F then condensation will accumulate. a) 150 Deg F b) 165 Deg F c) 180 Deg F c d) 220 Deg F 43. The best economy mixture is at a power setting of …….% power and the mixture should be made rich to get …………….Deg F lower for best power mixture. a) 80 % and 100 Deg F b) 90 % and 110 Deg F c) 75 % and 90 Deg F d d) 75 % and 100 Deg F 44. When reducing power the CHT should not vary …..deg F per minute a) 100 Def F b) 50 Deg F c) 25 Deg F b d) 10 Deg F 45. At a safe height the RPM should be …………….and speed for 1000 Kg should be………. a) 2400 and 68 KIAS b) 2700 and 68 KIAS c) 2500 and 67 KIAS a d) 2100 and 67 KIAS 46. A constant oil temperature of 26 deg F or 317 deg F indicates a ……………………… 7 | P a g e NFTI DA 40 a) An oil cooler failure. b) A faulty indication in the cockpit. c c) A faulty oil temperature sensor. 47. The circuit breaker for the rudder pedal adjustment is on the ……………… a) The rear wall of the leg room. b) The front wall of the leg room. a c) The centre wall of the leg room. 48. An uphill slope of 2% increases takeoff run by ……………..% a) 20 % b) 15 % c) 10 % c d) 5 % 49. ROC at an altitude of 5000 feet with mass of 1150 KG and temperature of 12 Deg C is …………….. a) 2 m/s b) 2.5 m/s c c) 2.8 m/s d) 3 m/s 50. Autopilot minimum engagement speed is ………………… a) 65 KIAS b) 66 KIAS c) 67 KIAS c d) 70 KIAS NATIONAL FLYING TRAINING INSTITUTE PRIVATE LIMITED Registered Address: C/o Airport Authority of India, Birsi Airport, P.O. Paraswada, Gondia – 441614, Maharashtra, India NAME:____________________________________ Dt: __/__/09 1. DA-40 engine Model No ____a__________ A) IO-360 M1A B) IO-370-M2A C) IO-330-M3A IO-360 M1B 2. Nose Wheel Shock Absorber in DA-40 is ………. b A) Sprung Steel B) Elastomer Pack C) Disk D) Sponge 3. Aspect Ratio of DA-40 is____b___ A) 12.53 B) 10.53 C) 9.53 D) 13.53 4. Glide Ratio of DA-40 is………………. a A) 1: 8.8 B) 1:5.8 C) 1:9.0 D) 1:7.6 5. DA-40 has ______d_______ Fuel System. A) Gravity feed B) Electrically driven C) Engine driven D) Both B & C 6 DA-40 dihedral angle is ………… a A) 5o B) 3o C) 1o D) 2o 7. DA-40 wing shape is…………… A) Tapered B) Elliptical C) Rectangular D) None of the above 8. Angle of Incidence for DA-40 Wings is…… -3 ………. 9. DA-40 main wheel landing gear Shock absorbers are___sprung steel struts___________ 10. DA-40 Fuel Capacity__40____ Gallons and Usable fuel is___39____ galons. 11. DA-40’s Emergency frequency or ELT frequency is __406,121.5_____ 12. DA-40 in NFTI has ________fuel tanks 13. DA-40’s construction is by ___grpf/crpf___________ 14. DA-40 take off speed and Landing Speeds are _____and _76___(without flaps) 15. DA-40 take off speed and Landing Speeds are _67____and __73__(with flaps) 16. Vne Speed in a DA-40 is __178___ 17. Engine max horse Power of DA-40 engine is__180___ 18. The number of fuel pumps DA-40 has_2___ 19. Ideal fuel for DA-40 engine is__Avgas 100ll_____ 20. Service Ceiling of DA-40 is__16400’____ 21. The landing/taxy lights are on the __left______wing. 22. Max structural cruising speed (Vno): _129__KIAS 23. Never Exceed Speed is _178___ 24. In magneto check Max RPM drop permitted is _175__and max difference is _50__ RPM. 25. The glide ratio is _1_:_8.8__in wind milling configuration and for every _1000___ ft ht loss the ac travels _1.45___ Nm. 26 32. The ELT has a three position switch.__off, on, arm______________ 33. Go around speed is _67_KIAS for 1200 Kg and _66_ KIAS for 1150 kg. 34. Restarting in air with stationary prop: Min Spd_80___KIAS 35. Ht loss to start engine with prop stationary: _1000___ ft/_300__m MARKING IAS IMP 36. WHITE ARC 49- 91 KIAS FULL FLAP OP LIMIT 37. GREEN ARC 52-129 KIAS NORMAL OP LIMIT OF AC 38. YELLOW ARC 129-178 KIAS CAUTION RANGE – SMOOTH AIR ONLY 39. RED LINE(Vne) 178 KIAS MAXIMUM SPD IN ALL CONDITIONS. 40. Max difference in fuel between Lt and Rt tank is _10__US Gallons for standard tanks. 41. The min/max oil required in IFR is 6 - 8 Quarts 42. The Total usable fuel quantity of the main fuel tanks is of DA42 in gallons is 43. Maximum number of occupants are _4__. 44. The airplane has a T tail and is GFRP construction. 45. The Max continuous RPM of the DA42’s engines is 46. The rudders and elevator are of __gfrp sandwich________ construction. 47. The main landing gear is of __sprung steel strut____and the free caterings nose wheel is sprung by an __elastomer package________________ 48. The wheel brakes are on the main wheel are _hydraulically operated disc brakes_________ and operated by toe pedals. 49. Displacement of the engine is _5916___ Cm cube/ _361____inch cube. 50. The max power of the engine is _180____ HP at 2700 RPM at sea level under ISA and _160___HP at 2400 RPM at SL at ISA. 1. An aircraft including maximum oil, all consumables and maximum fuel a. Empty mass b. Max t/o weight b c. Max landing weight d. Payload 2. Certificate if Airworthiness is issued in the form of a. C.23 b. C.23A c c. C.23A & AFM 3. Positive load factor for normal category at Va&Vne a. 3.8 & 3.8 b. 3.0 & 2.0 a c. 3.2 & 3.5 d. 2.7 & 3.5 4. Instrument No. 15 in the conventional instrument panel is a. Altimeter and slaving meter b. Airspeed indicator b c. Vertical speed indicator d. Compass 5. Which button will show display mode a. Button 1 [engine soft key in MFD] b. Button 3 c. Button 5 a d. Button 7 6. Minimum airspeed for restarting engine in air is a. 65 b. 79 c. 89 a d. 78 7. Da-40 aircraft is a. Lycoming IO-360-M1A aircooled 4 stroke b. Lycoming IO-360-M2A aircooled 4 stroke c. Lycoming IO-360-M1A oilcooled 4 stroke a d. Lycoming IO-260-M1A aircooled 4 stroke 8. Green in ASI is a. 52-129 b. 91-129 a c. 50-133 d. 49-91 9. Max continous RPM for DA-40 aircraft is a. 160 BHP a b. 180 BHP