Weight & Balance for the Diamond DA40 TDI

Diamond DA40 TDI · Weight And Balance

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Overview

This document provides essential weight and balance information for the Diamond DA40 TDI aircraft. It is intended for pilots and aviation enthusiasts who need to understand the loading limits and weight distribution for safe flight operations. The document outlines the maximum weight limits, center of gravity (CG) calculations, and loading procedures to ensure compliance with safety regulations. Proper weight and balance management is crucial for optimal aircraft performance and safety during flight.

Maximum takeoff weight: 1,150 kg (2,535 lbs)
CG limits: 35% to 43% of MAC
Use the provided weight and balance form for calculations

Document

Source

Originally published by www.wingsoverholland.nl. Sprinkle hosts a reference copy with an added summary, specifications and searchable full text.

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Document details

Type: Weight And Balance
Pages: 12
File size: 3.2 MB
Publisher: www.wingsoverholland.nl

Specifications & performance

Extracted from this document.

Specifications

Empty weight (lb): 1,820
Fuel capacity (gal): 40
Max takeoff weight (lb): 2,535

Weight & balance

Useful load (lb): 715
Basic empty weight (lb): 1,820
Max takeoff weight (lb): 2,535

Documentation completeness

4/7

Most owners only have the POH. Here's the essential set for the Diamond DA40 TDI.

Pilot's Operating Handbook / AFM
Checklist
Maintenance Manual
Parts Catalog (IPC)
Systems & Wiring
Service Bulletins
Type Certificate (TCDS)

More Diamond DA40 TDImanuals & documents

See all 20 →

In this document

Maximum Weight Limits

The maximum takeoff weight for the Diamond DA40 TDI is 1,150 kg (2,535 lbs). This limit includes the weight of the aircraft, passengers, cargo, and fuel. Adhering to this limit is essential for safe flight operations.

Center of Gravity (CG) Limits

The CG limits for the Diamond DA40 TDI are between 35% and 43% of the mean aerodynamic chord (MAC). Pilots must calculate the CG based on the weight and distribution of passengers and cargo to ensure it remains within these limits.

Loading Procedures

Proper loading procedures involve calculating the total weight and determining the CG location before flight. The document provides a sample weight and balance form to assist pilots in recording the weights of passengers, baggage, and fuel.

Safety notes

Ensure the aircraft is within weight limits before flight.
Verify CG is within specified limits to maintain aircraft stability.

Full document text

DA 40 D AFM Diamond Mass & Balance AIRCRAFT NOTE Refer to Section 1.6 UNITS OF MEASUREMENT for conversion of SI units to US units and vice versa. 6.2 DATUM PLANE The Datum Plane (DP) is a plane which is normal to the airplane's longitudinal axis and in front of the airplane as seen from the direction of flight. The airplane's longitudinal axis is parallel with the upper surface of a 600:31 wedge which is placed on top of the rear fuselage in front of the vertical stabilizer. When the upper surface of the wedge is aligned' horizontally, the Datum Plane is vertical. The Datum Plane is located 2.194 meters (86.38 in) forward of the most forward point of the root rib on the stub wing. 6.3 MASS AND BALANCE REPORT The empty mass and the corresponding CG position established before delivery are the first entries in the Mass and Balance Report. Every change in permanently installed equipment, and every repair to the airplane which affects the empty mass or the empty mass CG must be recorded in the Mass and Balance Report. For the calculation of flight mass and corresponding CG 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 empty mass: - Equipment as per Equipment Inventory (see Section 6.5) Including brake fluid, lubricant (6.0 liters = 6.3 qts), coolant (6.0 liters = 6.3 qts), gearbox oil (0.9 liters = 0.95 qts), plus unusable fuel (2 US gal = approx. 7.6 liters). Doc. # 6.01.05-E Revision 5 01-Jun-2008 Page 6-3 Mass & Balance Diamond DA 40 D AFM AIRCRAFT MASS AND BALANCE REPORT (Continuous report on structural or equipment changes) DA 40 D Serial No.: Du. 205 Registration: PHTIN Page No.: 1 Changes in Mass Addition (+) Subtraction (-) Current Empty Mass Description of Moment Moment Entry No. Mass Arm Moment Mass Date IN OUT Part or Modification Moment Arm Moment Mass Arm Moment [kg] [m] [kgm] [kg] [m] [kgm] [kg] [m] [kgm] 19.05-06/ 07-06-2011 OSB-A4-061/2 upon delivery 831 2.465 2048,3 838 2.47 2069.2 R Page 6 - 4 Revision 5 01-Jun-2008 Doc. # 6.01.05-E DA 40 D AFM Diamond eads Mass & Balance AIRCRAFT 6.4 FLIGHT MASS AND CENTER OF GRAVITY The following information enables you to operate your DA 40 D within the permissible mass and balance limits. For the calculation of the flight mass and the corresponding CG position the following tables and diagrams are required: 6.4.1 MOMENT ARMS 6.4.2 - LOADING DIAGRAM 6.4.3 CALCULATION OF LOADING CONDITION 6.4.4 PERMISSIBLE CENTER OF GRAVITY RANGE 6.4.5 PERMISSIBLE MOMENT RANGE The diagrams should be used as follows: 1. Take the empty mass and the empty mass moment of your airplane from the Mass and Balance Report, and enter the figures in the appropriate boxes under the column marked 'Your DA 40 D'in Table 6.4.3 - CALCULATION OF LOADING CONDITION. 2. Read the fuel quantity indicators to determine the fuel quantity. If an indicator shows 15 US gal, up to 19.5 US gal can be in the Long Range Tank. In this case, the exact quantity must be determined with the alternate mean for fuel quantity indication. 3. Multiply the individual masses by the moment arms quoted to obtain the moment for every item of loading and enter these moments in the appropriate boxes in Table 6.4.3 - CALCULATION OF LOADING CONDITION. 4. Add up the masses and moments in the respective columns. The total moments may be rounded to whole numbers. The CG position is calculated by dividing the total moment by the total mass (using row 5 for the condition with empty fuel tanks, and row 7 for the pre take-off condition). The resulting CG position must be inside the limits. As an illustration the total mass and the CG position are entered on Diagram 6.4.4 - PERMISSIBLE CENTER OF GRAVITY RANGE. This checks graphically that the current configuration of the airplane is within the permissible range. Doc. #6.01.05-E Revision 5 01-Jun-2008 Page 6 - 5 Mass & Balance Diamond DA 40 D AFM AIRCRAFT 5. Graphical method: Diagram 6.4.2-LOADING DIAGRAM is used to determine the moments. The masses and moments for the individual items of loading are added. Then Diagram 6.4.5-PERMISSIBLE MOMENT RANGE is used to check whether the total moment associated with the total mass is in the admissible range. The result found with the graphical method is however inaccurate. In doubtful cases the result must be verified using the exact method given above. Page 6-6 Revision 5 01-Jun-2008 Doc. # 6.01.05-E datum plane br DA 40 D AFM Diamond Mass & Balance AIRCRAFT 6.4.1 MOMENT ARMS PLASDNG OMIDAOJ RUL The most important lever arms aft of the Datum Plane: Front seats : 2.30 m 90.6 in - Rear seats : 3.25 m 128.0 in - Wing tank : 2.63 m 103.5 in - Baggage 3.65 m 143.7 in 3.65 m (143.7 in) 3.25 m (128.0 in) 2.63 m (103.5 in) 2.30 m (90.6 in) 2.194 m (86.4 in) root rib 600 mm (23.62 in) Doc. # 6.01.05-E Revision 5 01-Jun-2008 ep Page 6 - 7 31 mm (1.22 in) Load Mass [lb] [kg] 500 225 200 Fuel Quantity [US gal] [liters] 400 175 Page 6-8 Revision 5 01-Jun-2008 40 40 150 300 150 125 30 80 100 200 100 75 75 20 20 50 100 50 10 Doc. # 6.01.05-E 50 50 25 25 Front Seats Fuel Baggage Mass & Balance 6.4.2 LOADING DIAGRAM Rear Seats VINCEVEL Diamond AIRCRAFT 19 muted tone tavel insho [kgm] 100 200 300 400 500 [in.lb] 10,000 20,000 30,000 40,000 50,000 Load Moment MA DA 40 D AFM DA 40 D AFM Diamond AIRCRAFT 6.4.3 CALCULATION OF LOADING CONDITION a) Standard tank Mass & Balance DA 40 D (Example) Your DA 40 D CALCULATION OF Mass Moment Mass Moment LOADING CONDITION [kg] [kgm] [kg] [kgm] [lb] [in.lb] [lb] [in.lb] 1. Empty mass (from Mass and 735 1820 Balance Report) 1620 158,000 838 2069.1 2. Front seats 150 345 Lever arm: 2.30 m (90.6 in) 331 29,989 3. Rear seats 150 487.5 Lever arm: 3.25 m (128.0 in) 331 42,368 4. Baggage 0 0 Lever arm: 3.65 m (143.7 in) 0 0 5. Total mass and total moment with empty fuel tanks (Total of 1.-4.) 1035 2652.5 2282 230,357 6. On-board usable fuel 100.8 265.10

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(0.84 kg/liter) (7.01 lb/US gal) Lever arm: 2.63 m (103.5 in) 222 23,001 7. Total mass and total moment 1135.8 2917.60 with full fuel tanks (Total 5. plus 6.) 2504 253,357 8. The total moments from rows 5 and 7 (2652.5 and 2917.6 kgm (30,357 and 53,357 in.lb)) must be divided by the related total mass (1035 and 1135.8 kg (2282 and 2504 lb) respectively) and then located in Diagram 6.4.4 - PERMISSIBLE CENTER OF GRAVITY RANGE. As in our example CG positions (2.562 m and 2.569 m (100.95 and 101.18 in) respectively) and masses fall into the permitted area, this loading condition is allowable. Doc. # 6.01.05-E Revision 5 01-Jun-2008 Page 6 - 9 Mass & Balance Diamond DA 40 D AFM AIRCRAFT b) Long Range Tank DA 40 D Your DA 40 D (Example) CALCULATION OF Mass Moment Mass Moment LOADING CONDITION [kg] [kgm] [kg] [kgm] [lb] [in.lb] [lb] [in.lb] 1. Empty mass (from Mass and 735 1820 Balance Report) 1620 158,000 2. Front seats 150 345 Lever arm: 2.30 m (90.6 in) 331 29,989 3. Rear seats 80 260 Lever arm: 3.25 m (128.0 in) 176 22,528 4. Baggage 0 0 Lever arm: 3.65 m (143.7 in) 0 0 5. Total mass and total moment with empty fuel tanks (Total of 1.-4.) 965 2425 2127 210,517 6. On-board usable fuel 100.8 265.10 (0.84 kg/liter) (7.01 lb/US gal) Lever arm: 2.63 m (103.5 in) 222 22,977 7. Total mass and total moment 1065.8 2690.10 with full fuel tanks (Total 5. plus 6.) 2349 233,494 8. The total moments from rows 5 and 7 (2425 and 2690.1 kgm (210,517 and 233,494 in.lb)) must be divided by the related total mass (965 and 1065.8 kg (2127 and 2349 lb) respectively) and then located in Diagram 6.4.4 - PERMISSIBLE CENTER OF GRAVITY RANGE. As in our example CG positions (2.513 m and 2.524 m (98.97 and 99.40 in) respectively) and masses fall into the permitted area, this loading condition is allowable. Page 6 - 10 Revision 5 01-Jun-2008 Doc. #6.01.05-E DA 40 D AFM Diamond Mass & Balance AIRCRAFT 6.4.4 PERMISSIBLE CENTER OF GRAVITY RANGE a) Standard tank: Flight Mass [kg] Center of Gravity Position [in] 94 96 98 100 102 2600 1150 1100 1150 kg / 2535 lb ☑ 2400 Normal 1050 1000 2200 980 kg/2161 lb 950 Flight Mass [lb] 900 2000 Utility & Normal 850 800 750 2.40 780 kg/1720 lb 2.45 2.50 2.55 CG 1800 Envelope 2.60 Center of Gravity Position [m] The CG shown in the diagram is that from the example in Table 6.4.3 (a) CALCULA- TION OF LOADING CONDITION, row 7 (pre take-off condition). The flight CG position must be within the following limits: Most forward flight CG: 2.40 m (94.5 in) aft of Datum Plane at 780 to 980 kg (1720 to 2161 lb) 2.46 m (96.9 in) aft of Datum Plane at 1150 kg (2535 lb) linear variation between these values Most rearward flight CG: 2.59 m (102.0 in) aft of Datum Plane Doc. # 6.01.05-E Revision 5 01-Jun-2008 Page 6 - 11 Flight Mass [kg] Mass & Balance b) Long Range Tank Diamond MADA 40 D AFM AIRCRAFT Center of Gravity Position [in] 94 96 98 100 101 2600 1150 1150 kg / 2535 lb 1100 2400 Normal 1050 1000 2200 980 kg/2161 lb 950 900 2000 Flight Mass [lb] Utility & Normal 850 800 750 2.40 X CG 1800 Envelope 780 kg/1720 lb 2.45 2.50 2.55 Center of Gravity Position [m] The CG shown in the diagram is that from the example in Table 6.4.3 (b) CALCULA- TION OF LOADING CONDITION, row 7 (pre take-off condition). The flight CG position must be within the following limits: Most forward flight CG: 2.40 m (94.5 in) aft of Datum Plane at 780 to 980 kg (1720 to 2161 lb) 2.46 m (96.9 in) aft of Datum Plane at 1150 kg (2535 lb) linear variation between these values Most rearward flight CG: 2.55 m (102.0 in) aft of Datum Plane Page 6 - 12 Revision 5 01-Jun-2008 Doc. # 6.01.05-E Doc. # 6.01.05-E Revision 5 01-Jun-2008 Page 6 - 13 FLIGHT MASS MOMENT [in.lb] 160,000 180,000 1150 1100 FLIGHT MASS [kg] 1000 980 900 900 200,000 -DA40D (Example from 6.4.3) Center of Gravity Position 2.40 m/94.5" 2.46 m/ 96.9" 2.50 m/98.4" 2.55 m / 100.4" 2.59 m/102.0" 260,000 220,000 240,000 2550 2500 2400 2300 2200 2100 2000 1900 1800 6.4.5 PERMISSIBLE MOMENT RANGE a) Standard tank FLIGHT MASS [lb] 1700 2600 2800! 3000 2830 2978 800 780- 2000 2200 1872 2020 2400 2352 FLIGHT MASS MOMENT [kgm] DA 40 D AFM Diamond ate Mass & Balance AIRCRAFT Page 6 - 14 Revision 5 01-Jun-2008 FLIGHT MASS MOMENT [in.lb] 160,000 180,000 1150 200,000 1100 DA40D (Example from 6.4.3) 1000 980 FLIGHT MASS (WEIGHT) [kg] Doc. # 6.01.05-E 900 Center of Gravity Position 2.40 m / 94.5" 2.46 m/96.9" 2.50 m/98.4" 260 2.55 m / 100.4" 220,000 240,000 800 780 2000 2200 2400 1872 2020 2352 T 2550 2500 2400 2300 2200 b) Long Range Tank 2100 FLIGHT MASS (WEIGHT) [lb] 2000 1900 1800 1 1700 2600 2800! 3000 2830 2932,5 FLIGHT MASS MOMENT [kgm] Mass & Balance Diamond AIRCRAFT DA 40 D AFM

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