Piper PA-28-180 Weight and Balance Calculator

Fast and precise aviation loading calculation tool. Instant center of gravity verification for pilots. Check weight and balance limits before every single takeoff.

Aircraft Loading Input Parameters

1. Basic Aircraft Setup

Refer to your aircraft official records.
Standard factory value is approx 88.15 in.
Max capacity is 8 Quarts (15 lbs at 27.5 in).

2. Cabin Occupants

Combined Pilot & Front Passenger (Arm: 80.5 in).
Combined Rear Passengers (Arm: 118.1 in).

3. Fuel & Storage

AvGas @ 6 lbs/gal (Arm: 95.0 in, Max 50 gal).
Maximum allowance is 200 lbs (Arm: 142.8 in).

Formulas Used in Weight & Balance Calculations

In flight physics and aircraft performance engineering, calculating the Center of Gravity ($\text{CG}$) requires applying static torque equilibrium equations around a defined reference datum line. For the Piper PA-28-180 Cherokee, the datum is located 78.4 inches forward of the wing leading edge.

The calculation relies on three main physical formulas:

  1. Individual Station Moment ($\text{in-lbs}$): $$\text{Moment} = \text{Weight (lbs)} \times \text{Arm (inches)}$$
  2. Total Gross Weight ($\text{lbs}$): $$W_{\text{total}} = W_{\text{empty}} + W_{\text{oil}} + W_{\text{front}} + W_{\text{rear}} + W_{\text{fuel}} + W_{\text{baggage}}$$
  3. Center of Gravity ($\text{CG}$) Position ($\text{inches}$): $$\text{CG} = \frac{\sum \text{Moments}}{\sum \text{Weights}} = \frac{M_{\text{empty}} + M_{\text{oil}} + M_{\text{front}} + M_{\text{rear}} + M_{\text{fuel}} + M_{\text{baggage}}}{W_{\text{total}}}$$

Additionally, fuel weight is calculated dynamically assuming standard aviation gasoline density:

$$\text{Fuel Weight (lbs)} = \text{Volume (gallons)} \times 6.0\text{ lbs/gal}$$

How to Use This Calculator

Follow these quick steps to calculate your aircraft envelope parameters before takeoff:

Comprehensive Flight Physics: Piper PA-28-180 Weight and Balance Dynamics

Understanding weight and balance is fundamental to operational safety in general aviation. The Piper PA-28-180 Cherokee is a popular four-seat light aircraft, renowned for its forgiving handling characteristics and reliable performance. However, operating within safe weight and center of gravity limits remains a critical responsibility for every pilot in command. Exceeding structural gross weight limits or flying with an out-of-limit CG severely compromises stability, elevator authority, and overall aircraft performance.

The Center of Gravity Envelope and Aerodynamic Stability

The center of gravity is the point at which the total weight of the aircraft is concentrated. During flight, aerodynamic forces act around this point. In the PA-28-180, the allowable forward and aft CG boundaries form an envelope that varies based on total weight. If the CG moves too far forward, the tailplane must generate excessive downforce to maintain level attitude. This increases induced drag and raises stall speeds, while making flare maneuvers during landing difficult due to limited elevator authority.

Conversely, an aft CG condition reduces the distance between the center of pressure and the CG, diminishing longitudinal static stability. In an extreme aft loading scenario, the aircraft becomes unstable, prone to premature rotation on takeoff, and extremely difficult to recover from inadvertent stalls or spins.

Operational Fuel Burn and Envelope Shift

Fuel consumption during flight dynamically alters the gross weight and CG position. In the Cherokee 180, fuel tanks are located at an arm of 95.0 inches aft of datum. Because this arm is typically aft of the empty CG position, burning fuel moves the overall CG forward as total weight decreases. Pilots must verify that both takeoff condition and zero-fuel condition remain safely inside the normal category loading envelope to ensure controlled flight throughout the entire journey.

Frequently Asked Questions

The maximum allowable gross weight for the Piper PA-28-180 Cherokee in the Normal Category is 2,450 lbs for takeoff and landing operations.

The maximum structural weight limit for the baggage compartment located behind the rear seats is 200 lbs, with a fixed station arm of 142.8 inches aft of datum.

Aviation fuel weighs 6 lbs per gallon. As fuel at station 95.0 inches is consumed in flight, total moment decreases, causing the CG to gradually shift forward toward the landing configuration limit.

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Important Note: All the Calculators listed in this site are for educational purpose only and we do not guarentee the accuracy of results. Please do consult with other sources as well.