Performance and Loading - cyber exam q's

Question 1

Corrected Effective Operational Length is a length of runway - including over-run - expressed in feet, and corrected for -

Answer 1

Runway Slope, Surface and approaches

which are declared by CASA as usable for T/O and LNDG by aircraft.

Question 2

CEOL is determined by reference to…

Answer 2

the AIP, subject to variations contained in NOTAMS

Question 3

the ‘Main Runway’ is the runway with the

Answer 3

greatest CEOL!

Question 4

Jet aircraft maximum rate of climb is determined by

Answer 4

excess power over weight

Question 5

Vs when related to transport category aircraft is

Answer 5

the minimum steady flight speed

Question 6

you want your aircraft to stay airborne as long as possible. You would achieve this by flying

Answer 6

at the altitude where use of engine design RPM would result in a speed of Vimd

Question 7

to achieve max angle of climb, you would climb at

Answer 7

Vimd using max thrust

Question 8

large jet aircraft have a large speed band where the rate of climb is fairly constant. This is because

Answer 8

for this band, the power available and power required curves are nearly parallel

Question 9

The CP of a transport aircraft wing should ideally have minimal movement with variations in speed because

Answer 9

large trim changes would caused by large CP movement

Question 10

Considering the flap extension increases lift, the reason they are not used for the climb is

Answer 10

Minimum drag speed is higher with flap and the extra drag cancels the lift benefit

Question 11

an emergency climb on encountering severe low level wind shear would be achieved by

Answer 11

climbing at a target speed of just above the stall and using takeoff power

Question 12

Jet aircraft specific air range (SAR) as a comparison of air distance per tonne of fuel consumed would be expressed in the form

Answer 12

100anm/1000kg

Question 13

to achieve max range in nil wind at a given FL, you would fly at

Answer 13

1.32Vimd

Question 14

Operating a jet engine at design RPM will give the

Answer 14

Minimum SFC

Question 15

Jet engine design RPM is

Answer 15

slightly less than max RPM

Question 16

Max air range is achieved by flying at

Answer 16

a cruise climb 1.32 and Vimd and design RPM

Question 17

For a given altitude and weight, the way the IAS varies for max AOC if flap is extended is

Answer 17

it (the AOC) decreases due to the lower Vimd

Question 18

The theoretical requirement (as far as the airframe is concerned) for max range is

Answer 18

an IAS of 1.32 Vimd

Question 19

If required to cruise at a level with significant H/W, when max range is needed you would fly

Answer 19

fly faster than the nil wind max range speed because you need to achieve the best GS/DRAG ratio

Question 20

The effect of changes in OAT on SGR of a TURBOJET at a particular weight, speed and altitudes is

Answer 20

Changers in OAT have NO significan effect on SGR

Question 21

The effect of changes in OAT on the specific fuel consumption (SFC) of a turbojet at a particular weight, speed and altitudes is

Answer 21

an increase in OAT results in a increased SFC

Question 22

The maximum range TAS of a turbojet aircraft is

Answer 22

determined by the AOA and best GS/Drag

Question 23

The AOA for max endurance in a turbo aircraft is

Answer 23

indepentant of wind and weight

Question 24

Westerly IFR hemispherical cruse levels for non RVSM ops are

Answer 24

FLY 280. 310, 350

Question 25

When using forecast conditions for the purpose of calculating Landing Weight Limitations, it is to be assumed that there will be

Answer 25

NO HWC available!

Question 26

In weight and balance calculations, a moment is defined as

Answer 26

a weight multiplied by an arm

Question 27

The definition of Basic Weight includes...

Answer 27

Operational Items!

Question 28

When discussing take off performance for a transport category aircraft with a MTOW in excess of 5700kg, the forth take off climb extends from

Answer 28

``` OBSTACLE CLEARANCE HEIGHT at FINAL TAKE OFF CLIMB SPEED to 1500FT ```

Question 29

For a total fuel load of 29000 kg, the fuel would normally be loaded

Answer 29

full main tank with the remainder in the auxiliary tanks

Question 30

Expressing and aircraft CG position as a % of MAC permits comparison of the location of the CG relative to the position of the

Answer 30

center of pressure

Question 31

a reduction of Index Units (IU) refers to a centre of gravity shift which is

Answer 31

FORWARD

Question 32

In weight and balance calculations, the term I.U. refers to

Answer 32

a moment

Question 33

The CG must be checked at both

Answer 33

Taxi and Zero Fuel weights!

Question 34

for scale movements purposes, infants are

Answer 34

IGNORED! Adolescence and Children are HALF !

Question 35

When using standard weights to compile a load and trim sheet

Answer 35

using standard male and female weights instead of the standard adult weight will generally result in a LOWER total weight H O W E V E R . . . . . IF IF there are more MALES than female, use of standard weights(81kg) yields a lower total weight!!!!!!!!!!!!

Question 36

Loading of fuel in the aft auxiliary fuel tank is permitted when the total fuel requirement EXCEEDS ......

Answer 36

when the total fuel requirement EXCEEDS 20,600kgs (20.6 tonnes!!)

Question 37

With regard to decision speed (V1)

Answer 37

V1 is selected so that, if the take-off is continued after an engine failure which is recognised at or above the V1 speed, it will be possible to attain a height of 35 ft within the scheduled take-off distance, or if the take off is abandoned at or below the V2 speed it will be possible to bring the aircraft to a stop within the scheduled accelerated stop disantace.

Question 38

With regards to rotation speed (Vr)

Answer 38

rotation at the correct rate and Vr speed will result in V2 at or below 35 ft with one engine inoperative

Question 39

With regards to TOSS (V2)

Answer 39

V2 is achieved as a resulte of proper roation proceedures

Question 40

With regards to minimum control speed (Vmca)

Answer 40

Vmca is the minimum speed at which the aircraft can be kept within specific limits of heading and attitude with the critical engine in op and the remainder at take off power in the the second segment configurations

Question 41

With regard to the stall speed Vs

Answer 41

Vs is the minimum steady flight speed

Question 42

The scenario which is most likely to cause a tail strike in a large turbojet during takeoff would be

Answer 42

a normal rotation rate at a speed lower than Vr

Question 43

V2 must not be less than

Answer 43

1.2. Vs

Question 44

Following engine failure after takeoff in a multi engine aircraft above 5700kg , MTOW, the third takeoff segment ends

Answer 44

when the aircraft has reached normal climb speed and is in the clean configuration.

Question 45

IN a twin TURBO PROP above 5700kg MTOW, during a missed approach in the landing configuration with both engines operating, the required speed and gradient of climb respectively are

Answer 45

not in excess of 1.3 Vs and NOT less than 3.2%

Question 46

The use of a clearway for takeoff calcuations is permitted provides the TORA is ≥

Answer 46

TORA is ≥ TORR

Question 47

If used whith the approved takeoff ranges, the use of more flap on takeoff will

Answer 47

shorten then takeoff run, but lengthen the second and thirds segments

Question 48

A twin engines jet is approahcing to land at 1500ft AGL in the landing configuration with the critical engine inoperative. The net flight path gradient requirement, if any is

Answer 48

THERE IS NO REQUIREMENT

Question 49

As fuel is consumed from the wing tipts, the CG moves

Answer 49

Forward

Question 50

The airacraft is loaded with 15000kg of usable fuel in the main tanks for a flight. The correct statement regarding fuel feeding is

Answer 50

use tank to engine feed

Question 51

As the takeoff CG position becomes more rearward, the horizontal stabiliser trim units required for take off is

Answer 51

S M A L L E R ! ! !

Question 52

Before entering the landing charts when calculating landing weight for a CAT ONE ILS landing, a LDA of 2000 meters MUST BE reduced by

Answer 52

the greater of 13% or 300 metres - before entering the reference distance chart!

Question 53

When is the 'adjusted' LDA corrected for slope?

Answer 53

ONLY when the wind is AMBIENT!

Question 54

Wind does not alter LDA

Answer 54

Wind alters Landing Reference Distance ONLY

Question 55

When on approach to in gusty condition it is desirable to approach at a higher than normal speed to account for variation in airspeed. To calculate this sped margin, add half the wind speed and half the gust speed with a max increment of 20 kt above the approach speed. If the reported wind at the AD is 10 kt gusting 20kt, then the aircraft should approach at .

Answer 55

wind speed 10 ``` gust from 10 to 20 kt --> so the gust is 10kt 10kt*0.5 +10kt*0.5 =10kts Vref + 10 ```

Question 56

With a critical engine inoperative in a multi engine jet transport with a MTOW in excess of 5700kg, the 'gross' climb gradient in the second climb segment, as required for certification is

Answer 56

2.4% for a TWIN, 2.7% for a THREE engine aircraft and 3% for a FOUR engine aircraft.

Question 57

With a critical engine inoperative in a multi engine aircraft with a MTOW in excess of 5700kg, the 'net' climb gradient in the second climb segment, as required for certification, is

Answer 57

1.6% for a TWIN, 1.8% for a THREE engine aircraft and 2% for a FOUR engine aircraft

Question 58

Loading cargo into compartment ONE results in the CG moving .....

Answer 58

Forward! LEFT is Forward RIGHT is Rearward!

Question 59

The possibility of a large jet suffering a tail strike on the runway during takeoff is greatest with

Answer 59

an early (at any rate) slow rotation!

Question 60

The factors most affecting BRW are (6) SZRCEL

Answer 60

``` Structural maximums ZFW Runway limit Climb limit Enroute climb limit and LW limits ```

Question 61

The four climb segments following an enginre failure at V1 for a large turbine aircraft consists of

Answer 61

lift off to gear up, gear up to 400ft minimum, 400ft minimum to level to takeoff climb speed, 400 ft minimum to 1500 ft

Question 62

Following an engine failure recognised by V1 in a twin turbine, the gross climb gradient that must be achieved without landing gear retraction is

Answer 62

POSITIVE!

Question 63

The reason for specifying a max ZFW for an aircaft is

Answer 63

to prevent excessive stress on the wings and fuselage with low fuel quantities!

Question 64

The speed Vref is

Answer 64

the landing speed in a nominated configuration

Question 65

The accelerate stop distance required (ASDR) for a particular aircraft is shown in the manufacturers data assumes

Answer 65

there is a 2 to 3 second reaction time between V1 and pilot response

Question 66

An aircraft lading at a 3 degree approach angle, crosses the landing threshold at 50ft higher than normal landing approach height. compared to the normal touchdown position, the extra distance the touchdown position for approach is......

Answer 66

1000ft THE RULE: 1000ft runway distance per 50ft! BASED ON: a 3 degree GS Txr sitting ~1000ft from the landing threshold which puts you at 50ft over the landing threshold.

Question 67

If you get an ETOPS question

Answer 67

rip out CAO 82.0

Question 68

When a range of V1 speed is available for a given set of conditions, selection of a high V1 will

Answer 68

Decrease the 1-INOP TODR and Increase the ASDR!

Question 69

If a clearway is approved for inclusion in the TODA, the effect on BRW is

Answer 69

The BRW may be increase if RUNWAY LIMITED!

Question 70

With regard to the speed V2

Answer 70

V2 speed should be reached at or before 35'

Question 71

When considering the obstacle clearance requirements for large multi-engines turbine aircraft in the event of an engine failure after take off, the second segment climb refers to the period from

Answer 71

Gear up to a minimum, height of 400' (obstacle clearance height)

Question 72

Clearway is the difference between TODA and....

Answer 72

TODA vs TORA!

Question 73

The effect on the V1 speed if 'stopway is included' in the take off and ASD performance calculations is

Answer 73

V1 must be increased!

Question 74

The most critical segment for obstacle clearance in the event of an engine failure on the take-off is the

Answer 74

SECOND SEGMENT

Question 75

V1 must be greater than or equal to V..

Answer 75

Vmcg plus recognition time!

Question 76

As fuel is consumed from the wing tips the CoG moves

Answer 76

FORWARD

Question 77

The mixing of standard and Male/Female Adult weights on the same load sheet is.... Pr.. .. ..

Answer 77

PROHIBITED!

Question 78

Last minute passenger adjustment allow for a maximum of ....

Answer 78

TEN passengers OR 900kg of freight Without changing stab trim!

Question 79

The maximum number of Last minute passengers is determined by the line that encloses both the

Answer 79

TAXI and ZFW centre of gravity positions!!

Question 80

Compared to a balanced field take off calculation, the addition of a clearway to the TODA in a rwy limited T/O performance calculation will permit a higher g...

Answer 80

a higher gross weight at take off with a LOWER V1

Question 81

Compared to a balanced field take off calculation, the addition of a stopway to the ASDA in a rwy limited T/O performance calculation will permit a higher gr...

Answer 81

a higher gross weight at take off with a HIGHER V1

Question 82

The inclusion of a clearway in a TOD limited take off performance calculation will permit a h...

Answer 82

higher gross weight take off!!!

Question 83

At a given FL, maximum range given a BRW is achieved by flying

Answer 83

at a speed corresponding to the best TAS/DRAG ratio in nil wind and this is equivalent to 1.32 times the best L/D ratio speed which occurs at slower speed as weight reduces.

Question 84

Effect of CoG on Vmca

Answer 84

a forward CoG results in a lower Vmca!

Question 85

At a constant Mach, the effect of an increase in OAT on SAR and TAS are

Answer 85

TAS increases, SAR will not significantly change!>

Question 86

The purpose of the MZFW is

Answer 86

to limit the payload which may be loaded on the aircraft to protect the wings from excessive bending moments IN FLIGHT!

Question 87

When discussing T/O performance for aircraft with MTOW >5700kg, the first 'take-off climb segment' extends 'from'

Answer 87

a point where the aircraft first reaches 35'above the take-off surface to the point where landing gear retraction is completed.

Question 88

When discussing T/O performance for aircraft with MTOW >5700kg, the second segment extends from

Answer 88

gear up to 'obstacle clearance height'

Question 89

A wet runway will

Answer 89

reduce the accelerate stop limited TOW if V1 I not change!

Question 90

The use of additional flap settings on take-off has the effect of -

Answer 90

INCREASING runway limited take off weight but REDUCING climb limited take-off weight!

Question 91

In determining obstacle clearance requirements in the event of an engine failure in a multi-engine jet with MTOW .5700kg, in the ABSENCE of detailed obstacle clearance data it is ACEPTABLE to -

Answer 91

use Airservices Australia's declaired TODA's and gradients!

Question 92

The maximum range of a turbojet at a particular altitude will be achieved by flying at

Answer 92

a speed resulting in the best GS/Drag ratio!!!!!

Question 93

The purpose of passenger seat allocation is

Answer 93

to ensure safe loading when the aircraft is NOT AT full passenger capacity!!