1. Propeller blade angles are twisted along the length of the blade to compensate for centrifugal force and local velocity variations. 2. The blade angle is equal to the angle of attack minus the helix angle plus the blade incidence angle and angle of advance. 3. The most efficient propeller would have a geometric pitch of 80" and an effective pitch of 60" due to slip. 4. When windmilling, aerodynamic moments act against centrifugal moments to turn the blades to a feathered angle.

1. 1- Twisting of the blade angle :
a- Reduces the angle towards the root to allowblade cuff tobe fitted
b- Increases the angle towards the tipcompensetate for the cenerifugal force
c- Reduces the angle towards the tipto allowfor local velocity of the blade
2- The blade angle is equal to the angle of attack :
a- Minus helix angle
b- Plus blade incidence angle
c- Plus angle of advance
3- The most efficient propeller wouldbe one with:
a- Geometric pitch of 80” and an effective pitchof 60”
b- An effective pitchof 80”and geometric pitchof 100”
c- Geometric pitch of 80” and slipof 30”
4- When the propeller is windmilling ,aerodynamic turning moments:
a- Act against centrifugal turning moments andtendto turnthe blade to the
feathering angle
b- Oppose centrifugal turning moments andreduce the blade angle
c- Act withcentrifugal turning moments andtendto turnthe blade to the fine pitch
5- In flight, the torque bending force on a propeller causes the blades tobend:
a- Forwardin directionof flight
b- Rearwards fromthe directionof flight
c- Against the directionof rotation
6- As the forward speed of an aircraft fittedwitha fixedpitchpropeller increases:
a- Bothblade angle and angle of attack increase
b- Bothangle remains constant andangle of attack decreases
c- Blade angle and angle of attack decreases

2. 7- Aerodynamic inducedvibrations :
a- Are against at the blade tipand can be reducedby aerofoil shape and tipdesign
b- Can be avoidedby flying the aircraft outside critical ranges
c- Cause metal fatigue six inches fromblade tips require strengthenedspar
8- Composite propeller blade are protectedfromlightning strikedamage by :
a- Applying leadsolder at the blade tips of opposing blade
b- Constructionthe shell fromthe steel alloy , coatedwithcarbon fibre
c- Incorporating wire meshstrips under the outer layers of blade fibres
9- Counter weights fittedtovariable pitchpropeller are positioned:
A- Forwardof camberedface
B- On the plane of rotation
C- Rear of the pressure face
10- The configurationof contra – rotating propeller is suchthat :
a- Propeller rotate indifferentdirectiononseparate shaft
b- Propeller are causedtorotate inopposite directionby a gearbox
c- Propeller rotate inthe same direction
11- Fittedthe spacer behindthe rear cone will :
a- Rectify bottoming of rear cone and tightenthe hub
b- Allow the split hole inthe shaft alignwiththe retaining nut
c- Prevent the front cone bottoming by moving the hub forward
12- A blueing check carriedout during installationtoensure :
a- Concentricity of the propeller shaft is withinlimits
b- The propeller is seatedcorrectly onthe hub

3. c- The oil pressure suppliedtothe csuis sufficient
13- In the flyweight inthe csuare moving outwards thenthe propeller is:
a- Overspeeding andthe blade angle has to be increased
b- Underspeeding and the blade angle needs tobe increased
c- Underspeeding andthe blade angle must to be reduce
14- The feathering pumpis automatically stoppedwhen:
a- the pitchchange piston reaches the endof the coarse range and activates acut off
switch
b- the pilot select it off witha button on the propeller feathering control panel
c- oil pressure reaches apre-determinedlevelandisolatedthe electrical power tothe
oil pump
15- During normal flight condition, lowtorquemeter oil pressure will initiate:
a- turboprop engine re-light starting sequence
b- auto feathering of the blades
c- restart of the engine froma feathering position
16- the hub switch:
a- prevent the blades turning toa course angle during engine shutdown
b- allow the blade to be inthe ground fine positionfor engine starting
c- stopthe blade fining off the flight fine pitchstopfails
17- the directionof the differential motor ina tacho- generator synchronizing
systemis :
a- a result of the engine that generates the highest voltage
b- determinedby the frequency of the signal from the computer
c- selectedby rotationof the phasing control unit
18- A synchronizationsystemmay be usedwithgovernors with:

4. a- electrical headonly
b- mechanical head only
c- either mechanical or electrical heads
19- on a four –enginedaircraft withsynchronizationthe left hadengine is :
a- the master , only if selectedby the pilot
b- always the master engine
c- the slave, only when the engine next toits fail
20- on four bladed propeller the pulse generator inasynchrophasing systemare
fittedonthe :
a- root of the blades withidentical numbers
b- balde root coinciding withthe engine positionnumber
c- blade root of the master engine only
21- full de-ice mode :
a- allow electrical de-icing tobe selectedfor long periods during heavy ice toreduce
pilot workload
b- provide the max rate of fluid flowfrom the pump
c- has a spring loaded switchand de ices all propellers at once
22- some rubber de-icing systemboots containtwoheating elements :
a- to provide an alternative if the slipring contact fails during flight
b- to allowa greater concentration of heat on the blades
c- to allowtwo time cycles tobe usedfor light or heavy icing
23- fluidin a de-icing systemis fed to individual blades fromtank:
a- directly toa drilling ineachblade root using siphoning to induce flow
b- via a rheostat ,whichcontrol flow rate ,toslinger pipe
c- via a pump to slinger ring todistributeit tofeedshoes

5. 24- during a functional test of a fluid de-icing system:
a- dye added to the fluid will stainwhite washon the blades and show how effective
b- unevendistributionmay be causedby too much white wash in the fluid
c- dye should be allowedtodry on the blade before operating the systemfilledwith
dilutedwhite wash
25- an out of balance moment of wooden propeller :
a- Filling material fromthe tipof the blade
b- Adding solder tothe tip of blade
c- Indexing the angle at the of the blade
26- A check of relative positionof the blade tips as they travel one rotationis :
a- Carriedout during installationground runand can be referredtoas indexing
b- A final check after balancing and known as tracking
c- Accomplishedby rotating the propeller by mounting it inan arbour on balance
knives
27- Minor damage on a composite propellerblade :
a- Is consideredwithinthe scope of the operator and repair must be carriedout
immediately
b- May only be repairedif the paint is not cracked
c- May be repairedby a b1 qualifiedlicensedaircraft engineer
28- During a runout check of a propeller shaft DTI reading is 0.01 inchthis indicates
that the eccentricity of the shaft is :
a- 0.02 inch
b- 0.01 inch
c- 0.005 inch

6. 29- During ground run a propeller overspeedby 135 % of normal max speedthe:
a- Propeller shouldbe removedfor inspection if the time of the overspeed exceeded
limits
b- Tracking shouldbe checkedfollowing adetailedinspectionof the blade roots
c- Propeller shouldbe returnedtothe manufacturer
30- Before timing the range of movement fromcoarse to fine during a ground run :
a- The propeller must be exercisedtoensure that the oil is warmand the dome is free
of air
b- No movement of the pitchcontrol systemis allowedas it may influence the time
takento move throughthe range
c- The engine must be run at full power for tenminutes toensure max torque is
available
31- When exercising apropeller :
a- The blade are not tobe moved if the propeller is onwing and inhibited
b- The blade should be moved rapidly from coarse to fine to de-aerate the oil lines
c- Low rate of blade pitchchange is tobe usedto protect the internal seals from
damage
32- When preparing a propeller for off wing storage , it must be cleaned:
a- Witha pressure washtoremove contaminationfromthe root of blade
b- Withisopropyl alcohol ,ensuring that steel surfacesare leftdry for storage
c- Withlow alkaline soap ,by hand thenwrap the blade in polythene