Cirrus SR22 G5 Weight and Balance Calculator
Ensure your Cirrus SR22 G5 is within approved weight and balance limits for every flight. This calculator helps you determine critical flight parameters.
Weight and Balance Calculator
Typical for SR22 G5. Refer to POH.
From POH/Weight & Balance Manual.
Pilot/Co-pilot.
Typically 95.7 inches from datum.
Optional.
Typically 95.7 inches from datum.
Typical.
Typically 131.3 inches from datum.
Typical.
Typically 131.3 inches from datum.
Max 100 lbs for SR22 G5.
Typically 158.7 inches from datum.
Max 50 lbs for SR22 G5.
Typically 181.9 inches from datum.
Gallons x 6 lbs/gallon. Max usable fuel 92 gal.
Approximate. Varies by tank usage.
Total Weight: — lbs
Total Moment: — in-lbs
Center of Gravity (CG): — in
Calculation uses the standard weight and balance formula: Sum of (Weight x Arm) for all items, divided by Total Weight.
Visualizing Moment vs. Weight for different flight configurations.
| Description | Station (Datum) | Arm (in) | Min Weight (lbs) | Max Weight (lbs) | Min CG (in) | Max CG (in) |
|---|---|---|---|---|---|---|
| Empty Weight CG | Datum | — | — | — | — | — |
| Forward CG Limit (Normal Operation) | Datum | — | — | — | 79.0 | 95.7 |
| Aft CG Limit (Normal Operation) | Datum | — | — | — | 95.7 | 108.0 |
| Maximum Takeoff Weight | Datum | — | — | 3600 | — | — |
What is Cirrus SR22 G5 Weight and Balance?
Weight and balance is a fundamental concept in aviation safety and performance for the Cirrus SR22 G5, as it is for all aircraft. It refers to the process of calculating the total weight of the aircraft and determining where that weight is distributed relative to a specific reference point known as the datum. Proper weight and balance management is critical for maintaining aircraft stability, control, and performance. An improperly loaded aircraft can be unstable, difficult to control, and may exceed its structural limits, leading to a catastrophic loss of control or structural failure. Therefore, accurately calculating and adhering to the weight and balance limitations is not just a recommendation; it's a mandatory safety procedure for every flight.
Who should use it: Every pilot, owner, or operator of a Cirrus SR22 G5 is responsible for ensuring their aircraft is operated within its approved weight and balance envelope. This includes pre-flight planning for every trip, considering passengers, baggage, and fuel loads. Flight instructors and ground school instructors also use these calculations to educate pilots on the importance of load distribution.
Common misconceptions: A frequent misconception is that weight and balance only matters when the aircraft is heavily loaded or operating near its maximum limits. In reality, weight and balance is a continuous concern throughout the flight envelope, affecting performance during takeoff, climb, cruise, and landing. Another misconception is that all passengers and baggage weigh the same; actual weights must be used or estimated conservatively, and their placement (arm) is just as crucial as their weight. Simply staying under the maximum takeoff weight doesn't guarantee a safe center of gravity.
Cirrus SR22 G5 Weight and Balance Calculation Formula and Mathematical Explanation
The core of any weight and balance calculation for the Cirrus SR22 G5 involves determining the aircraft's Center of Gravity (CG). This is achieved by calculating the total moment of the aircraft and dividing it by the total weight. A moment is the product of an object's weight and its distance (arm) from the datum.
The process is as follows:
- Identify all items loaded onto the aircraft: This includes the basic empty weight of the aircraft, crew, passengers, baggage, and fuel.
- Determine the weight of each item: Use actual weights whenever possible. If actual weights are not known, use conservative estimates based on average weights or manufacturer recommendations.
- Determine the center of gravity (arm) for each item: This is the horizontal distance from the aircraft's datum (a reference point, usually the nose of the aircraft) to the center of gravity of the item. These values are found in the aircraft's Pilot's Operating Handbook (POH) or Weight & Balance manual.
- Calculate the moment for each item: Multiply the weight of each item by its corresponding arm (Moment = Weight × Arm).
- Sum all the weights: Add up the weights of all items, including the aircraft's empty weight, passengers, baggage, and fuel. This gives you the Total Weight.
- Sum all the moments: Add up all the calculated moments. This gives you the Total Moment.
- Calculate the aircraft's Center of Gravity (CG): Divide the Total Moment by the Total Weight (CG = Total Moment / Total Weight).
The calculated CG must then be compared against the aircraft's approved CG range for the specific flight phase (e.g., takeoff, landing) as specified in the POH.
Variables and Formulas:
Moments: Calculated for each item and for the aircraft as a whole. A moment is a measure of the turning effect of a weight about the datum.
Formula: Moment = Weight × Arm
Total Weight: The sum of all weights aboard the aircraft.
Formula: Total Weight = Σ(Weights)
Total Moment: The sum of all individual moments.
Formula: Total Moment = Σ(Moments) = Σ(Weight × Arm)
Center of Gravity (CG): The average location of the weight of the aircraft. This is the primary result of the calculation.
Formula: CG = Total Moment / Total Weight
Variables Table:
| Variable | Meaning | Unit | Typical Range for SR22 G5 |
|---|---|---|---|
| Empty Weight | Weight of the aircraft without usable fuel, crew, passengers, or baggage. | lbs | ~2300 – 2450 lbs |
| Empty Weight CG Arm | Distance of the empty weight's CG from the datum. | inches | ~98.0 – 99.5 in |
| Occupant Weight | Weight of pilot, co-pilot, and passengers. | lbs | ~150 – 200 lbs per person |
| Occupant CG Arm | Distance of occupant's CG from the datum. | inches | ~95.7 in (front), ~131.3 in (rear) |
| Baggage Weight | Weight of baggage loaded in compartments. | lbs | 0 – 150 lbs (divided between compartments) |
| Baggage CG Arm | Distance of baggage's CG from the datum. | inches | ~158.7 in (compartment 1), ~181.9 in (compartment 2) |
| Fuel Weight | Weight of usable fuel. | lbs | 0 – 552 lbs (92 gal x 6 lbs/gal) |
| Fuel CG Arm | Distance of fuel's CG from the datum. | inches | ~112.0 in (typical for full tanks) |
| Total Weight | Sum of all weights on board. | lbs | ~2300 – 3600 lbs (max takeoff) |
| Total Moment | Sum of all moments (Weight x Arm). | in-lbs | Varies widely based on loadout |
| Center of Gravity (CG) | Resulting CG of the aircraft based on total weight and moment. | inches | ~79.0 – 108.0 in (normal operation limits) |
Practical Examples (Real-World Use Cases)
Example 1: Short Cross-Country Trip with Two People and Light Baggage
A pilot is planning a short flight with one passenger. They have their empty weight and CG, plus typical weights for themselves, their passenger, and some light baggage. They are carrying full usable fuel.
- Aircraft Empty Weight: 2325 lbs
- Empty Weight CG Arm: 98.7 in
- Pilot Weight: 180 lbs
- Pilot CG Arm: 95.7 in
- Passenger Weight: 160 lbs
- Passenger CG Arm: 95.7 in
- Baggage 1 Weight: 40 lbs
- Baggage 1 CG Arm: 158.7 in
- Fuel Weight: 300 lbs (50 gallons)
- Fuel CG Arm: 112.0 in
Calculation:
- Empty Weight Moment: 2325 lbs * 98.7 in = 229462.5 in-lbs
- Pilot Moment: 180 lbs * 95.7 in = 17226.0 in-lbs
- Passenger Moment: 160 lbs * 95.7 in = 15312.0 in-lbs
- Baggage 1 Moment: 40 lbs * 158.7 in = 6348.0 in-lbs
- Fuel Moment: 300 lbs * 112.0 in = 33600.0 in-lbs
- Total Weight: 2325 + 180 + 160 + 40 + 300 = 3005 lbs
- Total Moment: 229462.5 + 17226 + 15312 + 6348 + 33600 = 301948.5 in-lbs
- Calculated CG: 301948.5 in-lbs / 3005 lbs = 100.48 in
Interpretation:
The calculated CG of 100.48 inches is within the normal operating range (79.0 to 108.0 inches for takeoff). The total weight of 3005 lbs is well below the maximum takeoff weight of 3600 lbs. This configuration is safe for takeoff.
Example 2: Four Adults and Maximum Baggage with Near-Full Fuel Load
A pilot is taking three other adults on a longer trip and wants to maximize baggage and fuel. This is a common scenario requiring careful planning.
- Aircraft Empty Weight: 2325 lbs
- Empty Weight CG Arm: 98.7 in
- Front Seat 1 (Pilot) Weight: 200 lbs
- Front Seat 1 CG Arm: 95.7 in
- Front Seat 2 (Co-pilot) Weight: 190 lbs
- Front Seat 2 CG Arm: 95.7 in
- Rear Seat 1 Weight: 180 lbs
- Rear Seat 1 CG Arm: 131.3 in
- Rear Seat 2 Weight: 170 lbs
- Rear Seat 2 CG Arm: 131.3 in
- Baggage 1 Weight: 100 lbs (Max)
- Baggage 1 CG Arm: 158.7 in
- Baggage 2 Weight: 50 lbs (Max)
- Baggage 2 CG Arm: 181.9 in
- Fuel Weight: 500 lbs (approx. 83 gallons)
- Fuel CG Arm: 112.0 in
Calculation:
- Empty Weight Moment: 2325 * 98.7 = 229462.5 in-lbs
- Pilot Moment: 200 * 95.7 = 19140.0 in-lbs
- Co-pilot Moment: 190 * 95.7 = 18183.0 in-lbs
- Rear Seat 1 Moment: 180 * 131.3 = 23634.0 in-lbs
- Rear Seat 2 Moment: 170 * 131.3 = 22321.0 in-lbs
- Baggage 1 Moment: 100 * 158.7 = 15870.0 in-lbs
- Baggage 2 Moment: 50 * 181.9 = 9095.0 in-lbs
- Fuel Moment: 500 * 112.0 = 56000.0 in-lbs
- Total Weight: 2325 + 200 + 190 + 180 + 170 + 100 + 50 + 500 = 3715 lbs
- Total Moment: 229462.5 + 19140 + 18183 + 23634 + 22321 + 15870 + 9095 + 56000 = 393705.5 in-lbs
- Calculated CG: 393705.5 in-lbs / 3715 lbs = 106.0 in
Interpretation:
In this scenario, the calculated total weight is 3715 lbs, which exceeds the maximum takeoff weight (MTOW) of 3600 lbs. Even if the weight were within limits, the CG of 106.0 inches is approaching the aft limit of 108.0 inches. This loadout is not permissible. The pilot would need to reduce weight, potentially by carrying less fuel or lighter baggage, or by not carrying all four adults. A re-calculation would be necessary with adjustments.
How to Use This Cirrus SR22 G5 Weight and Balance Calculator
Using this calculator is straightforward and essential for safe flight planning. Follow these steps:
- Gather Aircraft Data: Have your Cirrus SR22 G5's POH or Weight & Balance manual ready. You'll need the exact Empty Weight and Empty Weight CG arm.
- Input Aircraft Empty Weight: Enter the weight of your aircraft in the "Aircraft Empty Weight (lbs)" field and its corresponding CG arm in the "Empty Weight CG (in)" field.
- Input Occupant Weights and CG: For each seat (pilot, co-pilot, rear passengers), enter the actual or estimated weight of the person in pounds and their CG arm in inches. The CG arms for standard seats are usually provided but can be adjusted if occupants are positioned differently.
- Input Baggage Weights and CG: Enter the weight of baggage for each compartment and their respective CG arms. Be mindful of compartment weight limits (max 100 lbs in baggage compartment 1 and 50 lbs in baggage compartment 2 for SR22 G5).
- Input Fuel Weight and CG: Determine the weight of the usable fuel you plan to carry. Remember that fuel weighs approximately 6 lbs per US gallon. Enter this weight and the appropriate fuel CG arm. The fuel CG arm can vary slightly depending on which tanks are used first, but a typical value is provided.
- Click "Calculate": Once all fields are populated, click the "Calculate" button.
How to Read Results:
- Primary Result (Center of Gravity – CG): This is the most critical value. It shows the calculated CG of the aircraft in inches from the datum.
- Total Weight: The sum of all weights entered. Check this against the Maximum Takeoff Weight (MTOW) of 3600 lbs for the SR22 G5.
- Total Moment: An intermediate value used in the CG calculation.
- Intermediate Values: The calculated total weight and total moment are displayed for reference.
Decision-Making Guidance:
Compare the calculated CG to the limits specified in the table below the calculator and in your POH:
- Forward Limit: Ensure the calculated CG is not forward of the minimum forward CG limit (e.g., 79.0 inches for normal operation).
- Aft Limit: Ensure the calculated CG is not aft of the maximum aft CG limit (e.g., 108.0 inches for normal operation).
- Maximum Takeoff Weight: Ensure the Total Weight does not exceed 3600 lbs.
If your results fall outside these limits, you must adjust the load by removing weight, repositioning items, or reducing the number of occupants or fuel. The "Reset" button can be used to clear current entries and start over.
Key Factors That Affect Cirrus SR22 G5 Weight and Balance Results
Several factors significantly influence the weight and balance calculations for your Cirrus SR22 G5:
- Passenger and Crew Weight: The number of people on board and their individual weights directly impact both total weight and the location of the CG. Heavier occupants, especially in the rear seats, will shift the CG aft. Always use actual weights or conservative estimates.
- Baggage Loading: The weight and location of baggage are crucial. Heavier baggage or baggage placed in the rear compartments will shift the CG aft. The SR22 G5 has limits for each baggage compartment.
- Fuel Load: Fuel is a significant weight component. The CG of the fuel itself (typically forward of the main wing) has a forward effect on the overall CG. Flying with full tanks will result in a heavier aircraft and a CG closer to the forward limit compared to carrying minimal fuel.
- Aircraft Empty Weight and CG: Any changes to the aircraft, such as installed equipment (e.g., avionics upgrades, long-range tanks), can alter the empty weight and its CG. These changes must be documented and incorporated into the weight and balance calculations. Always use the current, updated empty weight and CG from the aircraft's records.
- Datum Reference Point: The chosen datum affects the arm values for all items. While the datum is fixed by the manufacturer, understanding its position relative to the aircraft's structure is key to interpreting the arm values correctly. A change in the datum itself would require re-calculating all arms.
- Flight Phase Limits: Weight and balance limits can change depending on the phase of flight. For example, the forward and aft CG limits for takeoff might differ from those for landing. Always use the appropriate limits specified in the POH for your intended flight operations.
- Optional Equipment and Modifications: Installing new equipment, such as a Garmin Perspective avionics suite or other modifications, can change the empty weight and center of gravity. It's vital to update the aircraft's Weight and Balance data with these changes.
- Dynamic Load Changes: While this calculator is for pre-flight planning, real-world flights can see dynamic load changes. For instance, fuel burn reduces weight but may not significantly shift the CG if fuel is drawn evenly from both wing tanks. However, the cumulative effect over long flights is substantial.
Frequently Asked Questions (FAQ)
What is the maximum takeoff weight for a Cirrus SR22 G5?
The maximum takeoff weight (MTOW) for a Cirrus SR22 G5 is 3600 lbs.
What are the normal CG limits for the Cirrus SR22 G5?
For normal operations, the CG must be between 79.0 inches and 108.0 inches aft of the datum. Specific limits for takeoff and landing might be more restrictive and are detailed in the POH.
How much does usable fuel weigh in an SR22 G5?
Usable fuel weighs approximately 6 pounds per US gallon. The SR22 G5 typically has 92 gallons of usable fuel, meaning a full tank weighs about 552 lbs.
What happens if my aircraft is outside the CG limits?
Operating an aircraft outside its approved CG limits is extremely dangerous and illegal. It can lead to instability, loss of control, and structural failure. Always ensure your aircraft is within limits before flight.
Can I carry more than 4 people in my SR22 G5?
The SR22 G5 is designed for a pilot plus three passengers. Exceeding this limit will likely put the aircraft outside its weight and balance envelope and potentially its structural limits.
How do I find the exact CG arm for passengers or baggage?
The Pilot's Operating Handbook (POH) or Weight & Balance Manual for your specific aircraft will provide the standard CG arms for each seat and baggage compartment. For non-standard loading, you may need to calculate the center of the item being loaded.
What is the datum in weight and balance calculations?
The datum is an imaginary vertical plane or line established by the manufacturer from which all horizontal distances (arms) are measured. For the Cirrus SR22, the datum is typically located at the aircraft's nose.
What is the difference between moment and CG?
Moment (Weight x Arm) is a measure of the turning effect of a weight about the datum. The Center of Gravity (CG) is the calculated point where the entire weight of the aircraft can be considered to act. CG is derived from the total moment divided by the total weight.
How often should I update my aircraft's weight and balance data?
You must update your aircraft's weight and balance data any time equipment is added, removed, or changed. Regular reviews are also recommended, especially if the aircraft is used for diverse missions.
Related Tools and Resources
- View Flight Load Visualization
- Explore More Aviation Calculators
- Cirrus SR22 Maintenance Guide
- Pilot Proficiency Checklist
- Essential Aviation Weather Resources
- Aircraft Fuel Planning Guide
- Understanding Flight Performance Metrics
For comprehensive flight planning, always refer to your aircraft's official Pilot's Operating Handbook (POH) and consult with qualified aviation professionals.