Please note, this sample exam is a very limited sample of EASIER QUESTIONS
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Congratulations and thanks for taking the practice exam. Any Aeroplane or general exam errors, please send to ppefactcheck@gmail.com Any Helicopter specific exam errors, please report to ppeheli@gmail.com Please never report errors via Messenger to Matt. Please ask all general questions in the Facebook group. Remember to watch the how to study videos and be sure to use the “Super Active Study Techniques” and “Exam Super Cycles”.
The red axis is called the:
You plan to fly from NARRABRI (YNBR) (3019S 14950E) direct to ST GEORGE (YSGE) (2803S 14836E). To avoid clouds after departing YNBR you divert left of planned TR along the YNBR – WALGETT railway line. At WEE WAA township (approximately 20nm WNW YNBR) you decide to track direct to YSGE. Which of the following features would provide the most accurate ground speed check between WEE WAA and YSGE?
What parts of the aircraft are represented by numbers 13, 14 and 15?
Given: W/V = 250M/30. Runways available are 03/21 and 09/27. Which runway has the greatest headwind component for landing?
Rotation around the green axis is caused by which control surface?
The shape of an airfoil has no effect on lift produced. Lift is totally dependent on airspeed and angle of attack.
In the above alpha loading chart:
What is the basic empty moment index?
We have deliberately left off some details, to check your understanding of balancing an aircraft. In the CASA exam the arrows would be on the Alpha Chart.
Rotation around the blue axis is called:
An aircraft with the call sign VTC-567 would be called by saying:
What would be the appropriate label for the letter e on the diagram shown here?
Rotation around the red axis is called:
You are planning a flight in a 4 seater dual control aeroplane with the following passengers: 2 adults and 2 children aged 5 and 8 weighing 20 kg and 40 kg respectively. Assuming aircraft weight limitations will not be exceeded, which of the following limitations apply and why?
When the combined weight does not exceed 77 kg, 2 children may occupy the seat if they are seated side by side, restrained by a lap strap only, and the seatbelt is adjusted to secure both children at all times when a seat belt is required to be worn.
When the combined weight does not exceed 77 kg, 2 children may occupy the seat if they are seated side by side, restrained by a lap strap only, and the seatbelt is adjusted to secure both children at all times when a seat belt is required to be worn.
Find the ISA deviation if the outside air temp is +30ºC at 9000 ft?
ISA temp at 9000 ft = 15 – 2 x 9 = -3
OAT is +30
ISA Dev is +33
ISA temp at 9000 ft = 15 – 2 x 9 = -3
OAT is +30
ISA Dev is +33
Rotation around the green axis is called:
What airspeed can the aircraft operate not only in smooth air, but with some minor turbulence? The aircraft can safely be flown here, making smooth turns, cruising and without excessive control inputs.
Use your E6b or similar flight computer to determine the following approximate TAS.
OAT: -25
Pressure Alt: 19,000
CAS: 300
Set CAS against pressure altitude. Then set temp against your temp line and read of TAS. Note as a very rough rule of thumb to check and narrow down options use the 2% rule. But do not rely on it to decide between to answers. The 2% rule means CAS increases by 2% per 1000 ft in PA. So 2% x 300 = 6 KT 19 x 6 = 114 As you can see in this case 300 + 114 would have given you the wrong answer, but it would have given you two answers to choose from. The reason 2% is wrong is because TAS is very dependent on temp and the 2% rule just assumes temps will decrease with altitude. Rather than taking into account the exact temps at that altitude on that day. 
Set CAS against pressure altitude. Then set temp against your temp line and read of TAS. Note as a very rough rule of thumb to check and narrow down options use the 2% rule. But do not rely on it to decide between to answers. The 2% rule means CAS increases by 2% per 1000 ft in PA. So 2% x 300 = 6 KT 19 x 6 = 114 As you can see in this case 300 + 114 would have given you the wrong answer, but it would have given you two answers to choose from. The reason 2% is wrong is because TAS is very dependent on temp and the 2% rule just assumes temps will decrease with altitude. Rather than taking into account the exact temps at that altitude on that day.
In an aircraft with MTOW less than 5700 kg, which limitation applies to the carriage of cargo?
Calculate the approximate density altitude using the following.
Elevation 3000 FT
QNH 1013
Temp 20ºC
1. Find pressure height = Elevation + (1013-QNH) x 30 e.g. 3000 ft at QNH 1013, = 3000+ (1013-1013) x 30 = 3000+ 0 = 3000 ft
2. For the next part of the calculation ONLY, round pressure height to nearest 500 ft
3. Find ISA temp = temp – 2 x the thousands of feet (at the PH) e.g. 20ºC at 3000= 15 – 2 * 3 = 9
4. Take ISA temp away from OAT e.g. 20°C to get ISA deviation = 20° – 9° = 11° ISA dev
5. Multiply ISA deviation by 120 to get pressure correction height e.g. 120 x 11 = 1320 ft
6. Add elevation to pressure correction height to get density altitude e.g. 3000 ft + 1320 ft = 4320 ft
1. Find pressure height = Elevation + (1013-QNH) x 30 e.g. 3000 ft at QNH 1013, = 3000+ (1013-1013) x 30 = 3000+ 0 = 3000 ft
2. For the next part of the calculation ONLY, round pressure height to nearest 500 ft
3. Find ISA temp = temp – 2 x the thousands of feet (at the PH) e.g. 20ºC at 3000= 15 – 2 * 3 = 9
4. Take ISA temp away from OAT e.g. 20°C to get ISA deviation = 20° – 9° = 11° ISA dev
5. Multiply ISA deviation by 120 to get pressure correction height e.g. 120 x 11 = 1320 ft
6. Add elevation to pressure correction height to get density altitude e.g. 3000 ft + 1320 ft = 4320 ft
1. Find pressure height = Elevation + (1013-QNH) x 30
2. Round pressure height to nearest 500 ft
3. Find ISA temp = temp – 2 x the thousands of feet eg 26ºC at 2000 = 26 – 2 * 2 = 22
4. Take ISA temp away from OAT to get ISA deviation
5. Multiply ISA deviation by 120 to get pressure correction height
6. Add elevation to pressure correction height for to get density altitude
Calculate the approximate density height using the following.
Elevation 3000 FT
QNH 1020
Temp 4ºC
1. Find pressure height = Elevation + (1013 – QNH) x 30 e.g. 3000 FT at QNH 1013, = 3000+ (1013-1020) x 30 = 3000+ -210 = 2790 FT
2. For the next part of the calculation ONLY, round pressure height to nearest 500 FT = 3000 FT
3. Find ISA temp = temp – 2 x the thousands of feet (at the PH) e.g. 4ºC at 3000= 15 – 2 * 3 = 9
4. Take ISA temp away from OAT e.g. 4°C to get ISA deviation = 4° – 9° = -5° ISA dev
5. Multiply ISA deviation by 120 to get pressure correction height e.g. 120 x -5 = -600 FT
6. Add pressure height to pressure correction height to get density altitude e.g. 2790 FT + -600 FT = 2190 FT
1. Find pressure height = Elevation + (1013 – QNH) x 30 e.g. 3000 FT at QNH 1013, = 3000+ (1013-1020) x 30 = 3000+ -210 = 2790 FT
2. For the next part of the calculation ONLY, round pressure height to nearest 500 FT = 3000 FT
3. Find ISA temp = temp – 2 x the thousands of feet (at the PH) e.g. 4ºC at 3000= 15 – 2 * 3 = 9
4. Take ISA temp away from OAT e.g. 4°C to get ISA deviation = 4° – 9° = -5° ISA dev
5. Multiply ISA deviation by 120 to get pressure correction height e.g. 120 x -5 = -600 FT
6. Add pressure height to pressure correction height to get density altitude e.g. 2790 FT + -600 FT = 2190 FT
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