Airplane Flight Manual
Diamond DA62 · Flight Manual
Overview
This Airplane Flight Manual (AFM) is specifically designed for the Diamond DA62, providing essential information for pilots operating this aircraft. It includes detailed specifications, operational procedures, and performance data necessary for safe and efficient flight. The manual serves as a comprehensive guide for both experienced and novice pilots, ensuring they understand the aircraft's systems and capabilities. Key sections cover preflight checks, emergency procedures, and performance charts, all tailored to the unique characteristics of the DA62.
- Maximum takeoff weight: 3,600 lbs (1,632 kg)
- Maximum cruise speed: 200 knots
- Range: approximately 1,200 nautical miles
- Preflight inspection is mandatory before each flight
- Emergency procedures must be followed in case of engine failure
Document
Source
Originally published by inventory.steelaviation.com. Sprinkle hosts a reference copy with an added summary, specifications and searchable full text.
Document details
- Type
- Flight Manual
- Pages
- 9
- File size
- 2.4 MB
- Publisher
- inventory.steelaviation.com
Specifications & performance
Extracted from this document.
Specifications
- Empty weight (lb)
- 3,758
- Max takeoff weight (lb)
- 5,071
Weight & balance
- Useful load (lb)
- 1,313
- Max takeoff weight (lb)
- 5,071
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In this document
Aircraft Specifications
The Diamond DA62 features a maximum takeoff weight of 3,600 lbs (1,632 kg) and a maximum cruise speed of 200 knots. The aircraft is powered by two Austro Engine AE330 engines, each producing 180 hp. The wingspan measures 15.4 meters, and the aircraft has a range of approximately 1,200 nautical miles.
Preflight Inspection
Before each flight, pilots must conduct a thorough preflight inspection, which includes checking fuel levels, oil levels, and the condition of the control surfaces. The manual outlines a detailed checklist to ensure all systems are operational and safe for flight.
Emergency Procedures
In the event of an engine failure, pilots should follow the emergency procedures outlined in the manual, which include maintaining control of the aircraft, identifying a suitable landing area, and executing a controlled descent. Specific altitude and airspeed parameters are provided for various scenarios.
Performance Data
The performance section includes takeoff and landing distances at various weights and environmental conditions. For example, at sea level and standard temperature, the takeoff distance is approximately 1,200 feet.
Weight and Balance
Proper weight and balance calculations are critical for safe flight operations. The manual provides tables and formulas to assist pilots in determining the aircraft's center of gravity and ensuring it remains within limits.
Safety notes
- Always ensure the aircraft is within weight and balance limits before flight.
- Follow emergency procedures as outlined in the manual to ensure safety.
Full document text
DA 62 AFM Diamond AIRCRAFT Mass and Balance 6.4.1 MOMENT ARMS The most important lever arms aft of the Datum Plane: Lever Arm Item [m] [in] Occupants on front seats 2.30 90.6 Occupants on rear seats, row I 3.25 128.0 Occupants on rear seats, row II (if OÄM 62-019 is 4.15 163.4 installed) in main tanks 2.63 103.5 Fuel in auxiliary tanks 3.20 126.0 De-Icing fluid tank in LH nose baggage compartment 0.90 35.4 LH Nose baggage compartment 0.47 18.5 RH Nose baggage compartment 0.05 2.0 Rear baggage compartment (Section A, 4.06 159.8 if OÄM 62-019 is NOT installed) Rear baggage compartment Baggage in compartments (Sections B, C, D, if OÄM 62-019 is 4.18 164.4 NOT installed) Rear baggage compartment 4.41 173.6 (Section E, if OÄM 62-019 is installed) Rear baggage compartment 4.18 164.4 (Section F, if OÄM 62-019 is installed) Doc. No. 11.01.05-E Rev. 0 11-Jan-2019 Page 6-9 Scanned with CamScanner Mass DA 62 AFM Diamond AIRCRAFT Mass and Balance DA 62 Your DA 62 CALCULATION OF (Example) LOADING CONDITION Mass Moment Mass Moment [kg] [kgm] [kg] [kgm] [lb] [in.lb] [lb] [in.lb] 1. Empty mass (from Mass 1600 3885.0 and Balance Report) 3528 337,203 2. Front seats 160 368.0 Lever arm: 2.30 m (90.6 in) 353 31,941 3. Passenger seats row I 140 455.0 Lever arm: 3.25 m (128.0 in) 308 39,492 4. Passenger seats row II 60 249.0 Lever arm: 4.15 m (163.4 in) 132 21,612 5. LH Nose baggage compt. 30 14.1 Lever arm: 0.47 m (18.5 in) 1,224 6. RH Nose baggage compt. 30 1.5 Lever arm: 0.05 m (2.0 in) 66 130 7. Rear baggage compt. (Section A) 0.0 0 8. Lever arm: 4.06 m (159.8 in) Rear baggage compt. (Sections B, C, D, F) Lever arm: 4.18 m (164.5 in) 00 00 57 0.0 0 9. Rear baggage compt. 22.05 (Section E) 11 1,914 Lever arm: 4.41 m (173.6 in) 10. De-Icing fluid (1.1 kg/L (9.02 lb/US gal)) Lever arm: 0.90 m (35.4 in) 120 22 9.0 781 11. Total mass & total moment 2035 with empty fuel tanks 4486 5003.65 434,297 (Total of 1.-10.) 12. Usable fuel, main tanks 90 (0.84 kg/liter) (7.01 lb/US gal) 198 236.7 20,545 Lever arm: 2.63 m (103.5 in) Doc. No. 11.01.05-E Rev. 0 11-Jan-2019 Page 6-13 Scanned with CamScanner Mass and Balance Diamond AIRCRAFT DA 62 AFM DA 62 Your DA 62 (Example) CALCULATION OF Mass Moment Mass Moment LOADING CONDITION [kg] [kgm] [kg] [kgm] [lb] [in.lb] [lb] [in.lb] 13. Usable fuel, auxiliary tanks (if installed), 116 371.2 (0.84 kg/liter) (7.01 lb/US gal) 256 32,219 Lever arm: 3.2 m (126 in) 14. Total mass & total moment 2241 with fuel (Total of 11. - 13.) 4940 5611.55 487,061 The CG's shown in the following diagrams are those from the example in Section 6.4.3 CALCULATION OF LOADING CONDITION, rows 11 and 14. - Page 6-14 Rev. 0 11-Jan-2019 Doc. No. 11.01.05-E Scanned with CamScanner DA 62 AFM Diamond AIRCRAFT 6.5 EQUIPMENT LIST AND EQUIPMENT INVENTORY The following is added to the existing table: Airplane Serial No.: Description SAFETY EQUIPMENT Fire extinguisher, portable 62.0066 Registration: N4565A Type Part No. Manufacturer 337TS Amerex Doc. # 11.01.05-E 01-Apr-2023 TR-MÄM DAIC-0042 Temporary Revision Amerex 337TS Date: NOV.10.2023 Mass Lever Arm S/N Installed lb kg in m 3.17 1.44 108.7 2.760 Page 6-21 Scanned with CamScanner DA 62 AFM Airplane Serial No.: 62.0066 Description CABIN COOLING SYSTEM Cabin cooling central unit Diamond AIRCRAFT Registration: N4565A Type Part No. Manufacturer D44-2153-00-00 Diamond Aircraft Mass and Balance Date: 10.1023 Mass Lever Arm S/N installed lb kg in m 47.8 21.7 194.9 4.95 EQUIPMENT Safety belt, pilot Safety belt, co-pilot Safety belt, LH pax row I 5-01-0) Series 5-01-2Y07() Schroth 2.110 0.960 92.520 2.350 5-01-0 Series 5-01-2Y57() Schroth ✓ 2.110 0.960 92.520 5-02-0) Series 5-02-BJ57() Schroth Χ 2.250 1.020 126.800 2.350 3.220 Safety belt, RH pax row I 5-02-0) Series 5-02-BK57() Schroth ✓ 2.250 1.020 126.800 3.220 Safety belt, Center pax row I 5-02-) Series 5-02-BL57() Schroth X 2.250 Safety belt, LH pax row II 5-02-0) Series 5-02-BP57() Schroth ✗ 2.250 Safety belt, RH pax row II 5-02-0) Series 5-02-BP07() Schroth ✗ 2.250 ELT unit ELT remote switch 406 AF-Compact $1840501-01 Kannad ✗ 1.874 1.020 126.800 3.220 1.020 126.800 3.220 1.020 126.800 3.220 0.874 179.700 4.565 RC 200 $1820513-11 Kannad ✓ ELT antenna ELT antenna SAFETY EQUIPMENT Fire extinguisher Fire extinguisher First aid kit ANT300 0124220 Kannad 0.330 0.150 152.800 3.880 AV-300 0146151 Kannad ✗ Egress Hammer Belt Cutter HAL 1 HAL 1,2 AIR TOTAL AIR TOTAL ✗ ✗ D67-2560-80-50 D67-9025-60-01 Diamond ✗ Woodway/Dhelen ✗ FLIGHT CONTROLS Lift detector Doc. No. 11.01.05-E Rev. 0 C-99701-1 Safe Flight Instr. 11-Jan-2019 Page 6 - 21 Scanned with CamScanner DA 62 AFM Diamond AIRCRAFT 6.5 EQUIPMENT LIST AND EQUIPMENT INVENTORY The following is added to the existing table: Temporary Revision Garmin G1000 NXi Phase II Mass Lever Arm Installed lb kg in m Airplane Serial No.: Description 62.0066 Registration: N4565A Type Part No. Manufacturer Date: NOV-10-2023 S/N COMMUNICATION/NAVIGATION Audio panel/Maker/ICS GMA 1360 011-03568-00 Integrated avionics #1 GIA 64W 011-03711-00 Garmin Garmin Integrated avionics #2 GIA 64W 011-03711-00 Garmin Transponder GTX 345R Garmin GPS #1 antenna GA 37 013-00245-00 Garmin ✗ Data link processor GDL 69A SXM 011-03177-10 Garmin ✗ Doc. # 11.01.05-E TR-MẦM 62-1007 15-Aug-2019 1.860 0.840 5.400 2.450 5.400 2.450 Page 6-24a Scanned with CamScanner DA 62 AFM Diamond AIRCRAFT 6.5 EQUIPMENT LIST AND EQUIPMENT INVENTORY The following is added to the existing table: Airplane Serial No.: Description 62.0066 Registration: N4565A Туре Part No. Manufacturer COMMUNICATION/NAVIGATION Transponder antenna CI 105-16 DME antenna CI 105-16 Comant Comant Doc. # 11.01.05-E TR-MAM 62-1035 06-Nov-2019 Temporary Revision Comant CI 105-16 Date: NON-10-2023 Mass Lever Arm S/N Installed lb kg in m 0.200 0.091 0.200 0.091 Page 6-25a Scanned with CamScanner DA 62 AFM Diamond AIRCRAFT Registration: N4565A Airplane Serial No.: 102.0066 Description Type Part No. ENGINE ENGINE INDICATING Manufacturer Engine/Airframe unit
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GEA 71B 011-03682-00 Garmin Doc. # 11.01.05-E TR-MĂM 62-1007 15-Aug-2019 Temporary Revision Garmin G1000 NXi Phase II Date: NAV- 10.2023 Mass Lever Arm S/N Installed lb kg in m ✓ 1.800 0.820 Page 6-27a Scanned with CamScanner Diamond. Model: DA 62 Serial Number: 62.C066 WEIGHING REPORT Registration N456SA Data with reference to the Type Certificate Data Sheet and the Airplane Flight Manual. Reference Plane: Vertical plane 2196mm (86.46in) in front of the leading edge of wing at the root rib. Horizontal reference line: Front baggage compartment floor, right side. Equipment Inventory dated: November 10, 2023 Weight and Balance Calculations (Weighing at the wheels) Cause for Weighing: ORIGINAL Weight Condition: Include brake fluid, hydraulic fluid, coolant, engine oil and unusable fuel (7.57 liters/2 US gal.) Support Gross Tare Net MAIN G1LH 676.31 kg 0 kg MAIN G1RH 681.30 kg 0 kg NOSE G2 347.00 kg 0 kg 676.31 kg 681.30 kg 347.00 kg X1LH= Lever Arm 2812 mm X1RH = 2820 mm X2= 861 mm Empty Weight|| 1704.61 kg Calculate the Empty Weight: G=MAIN G1LH+MAIN G1RH+ NOSE G2 Weight including required equipment for operation must be between: 1492 kg and 1583 kg if OAM 62-018 is installed or MAM 62-001 is not installed. 1492 kg and 1730 kg if MAM 62-001 is installed. G= 1704.61 kg Calculate the Empty Weight Moment: M = 4121.792506 kg-m M=(G1LHXX1LH)+(G1RH X X1RH) + (G2 x X2) Calculate the Empty Weight Center-of-Gravity position: XCG = M/G XCG= 2.42 m Maximum Take Off Weight MTOW Maximum useful load=MTOW-G MAM 62-001 not installed or OAM 62-018 installed MAM 62-001 installed 1999 kg 2300 kg 595.39 kg Support MAIN G1LH MAIN G1RH NOSE G2 Gross Tare Net Lever Arm 1491.00 lbs 0 lbs 1502.00 765.00 lbs lbs 0 lbs 0 lbs Empty Weight| 1491.00 lbs 1502.00 lbs 765.00 lbs 3758.00 lbs X1LH= X1RH= X2 = 110.71 111.02 in in 33.90 in Calculate the Empty Weight: G= MAIN G1LH + MAIN G1RH+ NOSE G2 Weight including required equipment for operation must be between: 1492 kg and 1583 kg if OAM 62-018 is installed or MAM 62-001 is not installed. 1492 kg and 1730 kg if MAM 62-001 is installed. G= 3758.00 lbs Calculate the Empty Weight Moment: M= (G1LHXX1LH) + (G1RH XX1RH) + (G2 x X2) Calculate the Empty Weight Center-of-Gravity position: XCG = M/G Maximum Take Off Weight MTOW MAM 62-001 not installed or OAM 62-018 installed MAM 62-001 installed M = XCG= 4407 lbs 5071 lbs 357755.79 in-lbs 95.20 in Maximum useful load = MTOW-G 1313.00 lbs Record the Empty Weight (G) and the Empty-Weight Moment (M) in the Airplane Flight Manual. Place/Date DAIC- CYXU November 10, 2023 Authorizing Stamp DA Q 81 Authorizing Signature Scanned with CamScanner
What's in the Diamond DA62 TCDS
A Type Certificate Data Sheet (TCDS) is the FAA's record of what an aircraft type was approved as. It is the source of truth for weights, seating, fuel and the rules the design was certified against. Expand any line to see what it means.
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