Wide Body Aircraft Fueling Calculator (A330/A350/B787/B777)
Simulate widebody fuel distribution instantly based on aircraft variant and total fuel load.
WIDEBODY FUEL DISTRIBUTION SIMULATOR
| COMPARTMENT DISTRIBUTION | ARRIVAL (KG) | DEPARTURE (KG) |
|---|---|---|
| Left Outer Wing Cell | ||
| Left Main / Inner Tank | ||
| Center Fuselage Cavity | ||
| Right Main / Inner Tank | ||
| Right Outer Wing Cell | ||
| Stabilizer Trim (Tail) Tank | ||
| TOTAL VERIFIED WEIGHT |
Need to fuel a narrowbody aircraft? Switch over to our Aircraft Fueling Calculator (A320/B737).
Aircraft Fuel Tank Architecture Quick Reference
Official volumetric capacities (Liters) and structural ground-fueling distribution sequence metrics used by this simulator:
1. Airbus A330neo
- Max Volumetric Limit: 139,090 L
- Left / Right Outer Wings: 3,650 L each
- Left / Right Inner Wings: 41,800 L each
- Fuselage Center Tank: 41,700 L
- Stabilizer Trim (Tail) Tank: 6,490 L
- Scheduling Rule: Outer tanks fill first. The Trim (Tail) tank receives up to 6,490 L only if total block fuel weight exceeds 35,000 KG. Remaining fuel quantities then fill the Inner wing tanks symmetrically before overflowing into the Center fuselage cavity.
2. Airbus A350-900
- Max Volumetric Limit: 141,000 L
- Left / Right Main Wing Boxes: 53,000 L each
- Fuselage Center Compartment: 35,000 L
- Scheduling Rule: Unified wing box cavities are filled with strict balance symmetry up to a 106,000 L combined wing total before any remaining fuel shifts down into the Center structural cell.
3. Airbus A350-1000
- Max Volumetric Limit: 156,000 L
- Left / Right Main Wing Boxes: 56,000 L each
- Fuselage Center Compartment: 44,000 L
- Scheduling Rule: Wing box structures scale out evenly to max capacities first (112,000 L combined wing total). Remaining required block fuel overflows into the expanded long-range Center cell.
4. Boeing 787-8 Dreamliner
- Max Volumetric Limit: 126,206 L
- Left / Right Main Wing Tanks: 36,170 L each
- Center Wing Box Section: 53,866 L
- Scheduling Rule: Main wing structural tanks are forced to 100% full capacity symmetrically first. Ground fueling cross-feed valves unlock the center box section only after wing tanks are completely satisfied.
5. Boeing 787-9 / -10 Dreamliner
- Max Volumetric Limit: 138,700 L
- Left / Right Main Wing Tanks: 37,215 L each
- Enlarged Center Box Section: 64,270 L
- Scheduling Rule: Stretched wing boundaries fill symmetrically up to 37,215 L per side first, followed by downstream routing straight into the high-capacity central structural tank framework.
6. Boeing 777-300ER
- Max Volumetric Limit: 181,283 L
- Left / Right Main Wing Tanks: 28,390 L each
- Massive Center Core Section: 124,503 L
- Scheduling Rule: Symmetrical wing tank safety caps are reached first to ensure baseline wing-bending moment structural relief. All subsequent volume additions cascade entirely into the heavy fuselage core cell container.
7. Boeing 777-9 (777X Next-Gen)
- Max Volumetric Limit: 197,977 L
- Left / Right Main Wing Tanks: 32,175 L each
- Extended Center Core Section: 133,627 L
- Scheduling Rule: Main wing structures (excluding the mechanical folding wing tips, which remain completely dry during ground fueling maneuvers) fill evenly up to their threshold, with subsequent overflow channeled into the widebody’s primary center cavity.
Formulas & Calculations Used
- CALCULATED UPLIFT mass (KG): The total mass of fuel expected to be added to the aircraft based on the difference between your target gate departure weight and your arrival block weight.
- Formula: Departure Total Fuel (KG) – Arrival Total Fuel (KG)
- ACTUAL DENSITY UPLIFT (KG): The true physical weight of the fuel delivered by the ground fueling truck, calculated by converting the raw volume of pumped fuel against its specific density.
- Formula: Uplift (Liters) x Specific Gravity (SG)
- TOTAL DISCREPANCY (KG): The absolute weight difference between what the cockpit fuel gauges state should have been added versus what the fuel truck physically pumped into the aircraft.
- Formula: Calculated Uplift (KG) – Actual Density Uplift (KG)
- DISCREPANCY VARIANCE: The percentage deviation of the fueling error. In live operations, a variance exceeding +/- 5% triggers a fuel volume cross-check to inspect for fuel leaks or indicator system failures before flight dispatch clearance.
- Formula: (Total Discrepancy (KG) / Calculated Uplift Mass (KG)) x 100
Scope and Limitations
- Supported Fleets: Restricted to seven specific widebody configurations (A330neo, A350-900/-1000, B787-8/-9/-10, B777-300ER, B777-9). It cannot process unlisted variants, freighter configurations, or auxiliary fuel cell setups. [For narrowbody aircraft, use Aircraft Fueling Calculator (A320/B737)].
- Automated Logic: Applies automated manufacturer ground-fueling profiles (wing-root relief and main-tank dominance), including the A330neo 35,000 kg tail-trim threshold.
- Strict Symmetry: Assumes perfect lateral fuel distribution. It cannot simulate asymmetric ground fueling, structural fuel weight imbalances, or manual cross-feeding overrides.
- Static Density: Converts volume to mass using a fixed, user-defined Specific Gravity (0.700 to 0.890). It does not account for real-time fuel temperature variations or volumetric thermal expansion.
- Ground Only: Models pre-departure ground fueling distribution and delivery discrepancy tracking (5% variance tolerance threshold). It does not simulate in-flight fuel consumption or real-time Center of Gravity (CG) migration.