1. General

Question 1

List the 3 terms used to refer to the degree of urgency in which a landing must occur

Answer 1

Land immediately
Land as soon as possible
Land as soon as practical

Question 2

Basic design & construction brief

Answer 2

5 bladed fully articulated system
Anti torque via a 2 (or 4) bladed semi rigid type tail rotor
Turbine powered
Constructed primarily of aluminium alloy
Power transferred via main drive shaft to main rotor & another drive shaft to tail rotor
“Overrunning” clutch allows freewheeling during auto

Question 3

Airframe structure

Answer 3

Rigid, 3 dimensional truss type structure.
Increase in crew safety by means of roll bar and reduction in points of failure.
Designed to be energy absorbing.

Question 4

Fuselage design

Answer 4

Semi-monocoque structure divided into 3 sections.
- Forward section
- Lower fuselage
- Aft section

Question 5

Lower cockpit design & construction

Answer 5

Compartment space for aircraft battery, small cargo storage or installation of avionics equipment.
Access via 2 floor door plates.

Question 6

Lower section design

Answer 6

Center beam provides housing for 2 fuel cells.
Cargo hook located on bottom of fuselage inline with the center beam.

Question 7

Tailboom structure & design

Answer 7

Monocoque aluminum alloy frame & skin.
Houses tail rotor drive shaft, one piece dynamically balanced requires no intermediate couplings or bearings.

Question 8

Landing gear design & construction

Answer 8

Skid type attached to fuselage at 12 points.
Aerodynamic fairings cover struts.
Nitrogen charged landing gear dampers act as springs & shock absorbers to cushion landings & reduce ground resonance.

Question 9

Power plant brief

Answer 9

Allison Model 250-C20B gas turbine engine.
Take-off power of 420shp.
375shp at 103% N2 RPM used for take-off.
350shp max continuous for all other flight modes.

Question 10

Why is max rated and max take-off power different?

Answer 10

Provides a higher engine critical altitude

Question 11

Drive system
Clutch

Answer 11

Overrunning clutch transmits power from engine to main drive shaft.
Clutch has no external controls & automatically disengages during auto & shutdown.

Question 12

Drive System
Oil cooling system

Answer 12

Engine oil cooler blower is belt driven off the main drive shaft. The oil cooler blower draws cooling air from the air inlet fairing to supply ambient air to the engine & transmission oil coolers & to the engine compartment.

Question 13

Drive System
Main rotor transmission

Answer 13

Main rotor transmission is mounted on the basic airframe structure above the passenger/cargo compartment.
Transmission is lubricated by its own air cooled lubrication system.

Question 14

Drive System
Tail Rotor transmission

Answer 14

Tail rotor transmission is mounted on the aft end of the tailboom & has a self-contained lubricant system.
The tail rotor is mounted on the output shaft of the transmission & consists of 4 variable pitch blades.

Question 15

Main rotor system
MDHS Strap Pack

Answer 15

First, Strap configuration allows centrifugal load exerted by 1 blade to be countered by the opposing 2 blades, thus very light centrifugal loads on the hub.
Second, the V-legs of the strap pack rotate as driving members to turn blades.
Finally, the straps are configured to allow feathering & flapping.

Question 16

Purpose of the Auto Reignition System?

Answer 16

Provides automatic actuation of the ignition exciter in the event that power is lost as a result of engine flame out.

Question 17

How does the Auto Reignition System work?

Answer 17

Each time that an ENGINE OUT/ Low rotor horn warning is activated, the RE IGN ARMED indicator will illuminate, showing that the ignition exciter has been energized.
This light will remain on until manually reset after N¹ and Nr increase back above values 55% / 468rpm.
The ignitor will stop firing once N¹ and Nr increase above 55% / 468rpm.

Question 18

What happens with Auto Reignition System in the event of a N¹ or Nr tach failure?

Answer 18

The RE IGN ARMED indicator will illuminate & the ignition exciter will remain energized until the engine is shut down or the auto reignition system is disarmed.

Question 19

Fuel System Capacity
Usable & unusable

Liters & pounds

Answer 19

Usable
235 L
421.9 Ilbs

Unusable
7.2 L
13.1 Ilbs

Total
242 L
435 Ilbs

Question 20

Oil Capacities
Engine
Main Transmission
Tail Rotor Transmission

Answer 20

Engine - 3quart / 2.84L
Main Transmission - 12pints / 5.67L
Tail Rotor Transmission - 0.5pints / 0.23L

Question 21

Main rotor diameter

Answer 21

26.41 feet
8 meters

Question 22

Skid width

Answer 22

6.45 feet
2 meters

Question 23

Overall length

Answer 23

30.84 feet
9.4 metres

Question 24

Overall height

Answer 24

8.9 feet
2.7 metres

Question 25

Cargo hook structural load limit

Answer 25

2,000 lbs

Question 26

Max Load Combination Weight

Answer 26

3,550 lbs

Question 27

VNE with load attached

Answer 27

80 kts IAS

Question 28

Max operating altitude with hook load

Answer 28

14,000 ft density altitude

Question 29

Above what weight must weight be external and jettisonable?

Answer 29

Any weight above 3,000 lbs must be external and jettisonable

Question 30

4 bladed tail rotor IGE controllability max wind strength

Answer 30

17 kts

Question 31

4 bladed tail rotor least favourable wind direction for IGE controllability

Answer 31

45 degrees right of the nose

Question 32

Fuel burn at 70psi

Answer 32

125 litres p/h
270 lbs p/h

Question 33

Endurance of 500D. No reserve, still air

Answer 33

1.9 hours

Question 34

Heliservices Min Fuel Policy for 500

Answer 34

100 lbs

Question 35

Cargo deck weight capacity

Answer 35

1,300 lbs
585 kgs