Refer to figure or CAP 697 Figure 4.5.3.2 for Pressure Altitude 37000 ft.

Given the following information, how much Trip Fuel is required for a Commercial Air Transport flight?

Ramp mass: 52500 kg

Taxi Fuel: 150 kg

Take-off and Climb Fuel: 1650 kg

Cruise distance: 378 NAM

Average wind component in cruise: +20 kt

OAT: ISA

Descent Fuel: 275 kg

Approach and Landing Fuel: 80 kg

Contingency Fuel: 5% of Trip Fuel

Alternate Fuel: 250 kg

Holding fuel consumption: 2400 kg per hour

*Refer to figure.*

This question gives you a lot of unnecessary information, but it is quite simple if you follow the following steps:

*The only information missing to calculate trip fuel is the fuel consumed during the cruise section of the flight (kg). Therefore, we must find out the weight at the beginning and at the end of cruise.*

*First Step*: __Finding the weight at the beginning of cruise__

*Note: Ramp mass includes taxi fuel *

- Weight at the beginning of cruise = Ramp mass – Taxi fuel – (take off + climb) =
**52 500 – 150 – 1650 = 50 700 kg**

*Second Step*: Enter the table, first column on the left shows mass in thousands of kg and first line at top shows mass in hundreds of kg.

- Enter the table a mass of 50 700 kg => Select line on the left column that says 50 000 kg and at the top, in the first line, where it says 700 kg =>
**find Value of 3494 NAM**

*Third Step*: We know that cruise distance = 378 NAM; therefore, using the table, to find out aircraft weight at the end of cruise, we need to subtract cruise distance from 3494 NAM: **3116 NAM**

*Fourth Step:* Find 3116 NAM in the table => which corresponds to a weight of **48 800 kg.**

We know that **cruise fuel** (kg) is the __difference between the weight at the beginning of cruise and the weight at the end of cruise__ = **50 700 - 48 800 = 1900 kg**

**Trip fuel = (take off + climb) + cruise + descent + (approach + landing) = 1650 + 1900 + 275 + 80 = 3905 kg**

Your Notes (not visible to others)