1
Q
WHAT IS THE ADVANTAGE OF A COMPOSITE ROTOR BLADE OVER A METAL ONE
A
A. EXTENDED LIFE
2
Q
IN A FULLY ARTICULATED ROTOR HEAD WHAT WOULD BE THE EFFECT OF A FAULTY DAMPER
A
A. A LATERAL VIBRATION
3
Q
WHAT ITEMS ARE INVOLVED FOR AN ILS SYSTEM?
A
A. GLIDE SLOPE, LOCALIZER AND MARKER BEACON
4
Q
WHAT IS INVERTER USED FOR?
A
A. TO CHANGE DC TO AC
5
Q
WHAT ANTENNA IS USED IN AN ILS SYSTEM TO FIND THE CENTER OF THE RUNWAY?
A
A. LOCALIZER
6
Q
IF AN IMBALANCE IN THE ROTOR SYSTEM REMAINS CONSTANT WITH RPM CHANGE. WHAT IS THE POSSIBLE CAUSE?
A
A. CHORD WISE IMBALANCE
7
Q
WHAT COULD BE THE CAUSE OF A CHORD WISE IMBALANCE IN A SEMI-RIGID ROTOR HEAD?
A
A. THE DRAG BRACE LINK INCORRECTLY ADJUSTED (ref p.119)
8
Q
ON A CONGENITAL EUROPEAN MADE HELICOPTER (PUMA), WHEN APPLYING POWER WHICK PEDAL IS DEPRESSED?
A
A. RIGHT (Reference page 53 Helicopter Maintenance)
9
Q
TO CHANGE THE DIRECTION IN FORWARD FLIGHT A HELICOPTER DOES WHAT?
A
A. TILTS THE MAIN ROTOR DISK IN THE DESIRED DIRECTION OF FLIGHT
10
Q
WHERE IS THE ROTOR BRAKE USUALLY LOCATED ON A HELICOPTER?
A
A. TRANSMISSION INPUT
11
Q
A ROTOR SYSTEM OUT OF TRACK WOULD BE CAUSED BY?
A
A. VERTICAL VIBRATION USUALLY 1:1
12
Q
IF A HELICOPTER WITH A STABILIZER BAR IS OVER STABLE, WHAT IS THE CAUSE ?
A
A. A SOFT DAMPER (REF. HELICOPTER MANUAL TEXT P162.
13
Q
WHY IS A SEMI-RIGID ROTOR HEAD UNDER SLUNG?
A
A. TO IMPROVE STABILITY
14
Q
WHAT LOADS ARE IMPOSED ON A ROTOR?
A
A. TENSION AND TORSION
15
Q
IN AN AUTO ROTATION WHAT IS THE STATE OF THE TAIL ROTOR?
A
A. NEGATIVE THRUST (RIGHT PEDAL ON US HELICOPTERS)
16
Q
WHAT DOES HORIZONTAL STABILIZER DO?
A
A. IT PULLS THE TAIL DOWN TO REDUCE DRAG RATIO
17
Q
WHAT DOES A MOVABLE HORIZONTAL STABILIZER DO TO THE FLIGHT OG THE HELICOPTAR?
A
A. INCREASES THE CENTER OF GRAVITY RANGE
18
Q
WHAT TYPE OF AIRFOIL IS USED ON A HORIZONTAL STABILIZER?
A
A. AN INVERTED WING
19
Q
WHAT TYPE OF BEARING IS USED ON A PITCH CHANGE ROD END?
A
A. SPHERICAL
20
Q
ON MOST HELICOPTER THE FUEL SYSTEMS ARE WHAT TYPE?
A
A. FORCED FEED REF. HELICOPTER MAINTENANCE TEXT P318
21
Q
WHAT TYPE OF PUMP IS USED TO PRODUCE HIGH PRESSURE IN A HYDRAULIC SYSTEM?
A
A. PISTON PUMP
22
Q
HOW IS A PRIORITY VALVE ACTUATED?
A
A. HYDRAULICALLY
23
Q
IF A BATTERY IS DISCHARGED AT 7 AMPS FOR 5 HOURS WHAT IS ITS RATING?
A
A. 35 AMP-HOUR (NOT AMP/HOUR)
24
Q
ON HELICOPTER WITH A FREE TURBINE ENGINE A DUAL TACH INDICATED WHAT?
A
A. ENGINE RPM AND ROTOR RPM
25
WHAT IS THE AIRFLOW IN AN AUTO ROTATION ?
A. UPWARDS
26
WHAT IS THE DRIVE LINK FOR THE MOVABLE PART OF A WASH PLATE USUALLY CONNECTED TO ?
A. MAST
27
WHY ARE CYCLIC INPUTS NOT INLINE WITH THE MOVEMENT DESIRED?
A. GYROSCOPID PRECESSION. THE PITCH LINKS LEAD BY 90 DEGREES
28
CARIOLES EFFECT IS RELATED TO ?
A.THE ADVANCING AND RETREATING BLADES ( PURPOSE OF THE DEAD-LAG HINGE) PAGE 46 CHANGE THE BLADE SPEED
29
THE COLLECTIVE TWISTE GRIP ON A FREE TURBINE HELICOPTER IS USED TO CONTROL?
A. COMPRESSOR RPM PAGE 170
30
WHY ARE SOME ROTORS PERMITTED TO FLAP?
A. TO COMPENSATE FOR DISSYMMETRY OF LIFT
31
A CONDITION WHERE THERE IS A DIFFERENCE IN THE AIRSPEED OF THE ADVANCING AND RETREATING ROTOR BLADE IS ?
A. DISSYMMETRY OF LIFT
32
A SINGLE ROTOR HELICOPTER IS IN HORIZONTAL FLIGHT. THE ANGLE OF ATTACK OF THE ADVANCING BLADE IS?
A. LESS THAN THE RETREATING BLADE
33
ALUMINUM ON METAL BLADES ARE?
A. ATTACHED TO THE SPAR BY BONDING
34
WHAT IS GROUND RESONANCE?
A. A SELF EXCITED VIBRATION THAT OCCURS ON THE GROUND
35
GROUND RESONANCE IS ASSOCIATED WITH WHAT TYPE OF ROTOR SYSTEM?
A. FULLY ARTICULATED
36
WHAT TYPE OF ROTOR SYSTEM NEEDS BLADE ALIGMENT ?
A. SEMI RIGID ROTOR PAGE 119
37
BLADE ALIGNMENT IS DONE TO ASSOCIATE THE BLADE?
A. CENTER OF GRAVITY WITH THE CENTER OF PRESSURE
38
INCREASED AIRFLOW THROUGH THE REAR OF THE ROTOR DISK IS CALLED?
A. TRANSVERSE FLOW
39
WHAT IS TRANSLATION?
A. THE ADDITIONAL LIFT THAT IS OBTAINED IN FORWARD FLIGHT
40
AT WHAT SPEED OES TRANSLATION OCCURS?
A. 15 TP 20 MPH
41
WHAT IS THE PURPOSE OF TRACKING THE MAIN ROTOR BLADES?
A. TO ENSURE ALL THE BLADES ARE IN THE SAME TIP PATH PLANE
42
A ROTOR HEAD WITH A HINGE TO ALLOW FOR FLAPPING IS CALLED WHAT?
A. ARTICULATED
43
WHEN AUTOPILOT IS ENGAGED WHAT IS USED TO GIVE THE PILOTS FEEL OF THE CONTROLS?
A. GRADIENTS PAGE 174
44
WHAT DOES A HYDRAULIC PUMP DO IN A HYDRAULIC SYSTEM?
A. CIRCULATED FLUID
45
IN STEADY RATE VERTICAL FLIGHT WHAT CONDITION OCCURS?
A. LIFT AND THRUST IN GREEN WHAT THE WEIGTH AND DRAG OF THE HELICOPTER
46
WHAT WILL HAPPEN IF THE OVER RUNNING CLUTCH SEIZES?
A. THE ROTOR WILL DRIVE THE ENGINE (AUTO ROTATION) PAGE 267
47
CONICAL ELASTOMERIC BEARING DO WHAT?
A. CARRY HIGH AXIAL AND RADIAL LOADS WITH SOME MOVEMENTS IN BOTH DIRECTION
48
WHEN THE TORQUE FROM THE ROTOR TURNS THE FUSELAGE WHAT IS OCCURING ?
A. NEWTON'S THIRD LAW (EVERY ACTION =OPPOSITE REACTION)
49
WHAT EFFECT THE ROTOR CONING ANGLE?
A. THE LIFT AND THE WEIGHT OF THE HELICOTER???
50
THE CHANGE IN THE ANGLE OF INCIDENCE FROM THE ROOT TO THE TIP IS CALLED?
A. BLADE TWIST
51
WHAT CONTROLS VERTICAL FLIGHT IN A HELICOPTER?
A. THE COLLECTIVE PITCH
52
WHAT DIRECTION DOES THE TORQUE OF THE MAIN ROTOR TURN THE FUSELAGE?
A. OPPOSITE THE MAIN ROTOR
53
WHAT IS USED TO VARY THE PITCH OF THE BLADES AS THEY FLY THROUGH THE TIP PATH PLANE?
A. COLLECTIVE???? / CYCLIC
54
WHAT IS RELATED TO THE TORQUE OF A HELICOPTER?
A. ENGINE INCREASES TORQUE INCREASE
55
IF HELICOPTER IS UNABLE TO MAKE TURNS IN A HOVER WHAT IS THE PROBLABLE CAUSE?
A. TAIL ROTOR RIGGED WRONG
56
WHEN THE COLLECTIVE IS RAISED WHAT HAPPENS?
A. POWER OUTPUT MUS INCREASE TO PREVENT A REDUCTION IN MAIN ROTOR RPM (NR)
57
WEN REFERRING TO THE MAIN ROTOR WHAT IS HUNTING?
A. HORIZONTAL MOVEMENT OF THE ROTOR BLADE ABOUT ITS VERTICAL HINGE
58
WHAT WOULD CAUSE A CENTRIFUGAL TYPE CLUTCH ENGAGEMENT AT TOO LOW AN ENGINE SPEED?
A. WEEK OR BROKEN CLUTCH SPRINGS
59
IF THE COLLECTIVE CONTROL IS LOWERED WHAT HAPPENS TO THE ROTOR BLADES?
A. THEY MOVE TO A LOWER PITCH ANGLE
60
FLAPPING OF FULLY ARTICULATED ROTOR BLADES IS A RESULT OF?
A. PITCH CHANGES CAUSED BY AERODYNAMIC REACTION
61
WHEN CYCLING CONTROL IS APPLIED TO A ROTATING ROTOR, THE MAXIMUM DISPLACEMENTE OF THE ROTOR DISK OCCURS ?
A. 90 DEGREES AFTER THE POINT OF APPLICATION
62
WHICH OF THE FOLLOWING WOULD MOST LIKELY CAUSE THE PEDALS TO CREEP DURING A GROUND RUN?
A. THE COUNTER WEIGHTS TO HEAVY
63
WHAT WOULD BE THE FIRST INDICATION OF A MISALIGNMENT OF A TAIL ROTOR SHAFT BEARING?
A. THE OVER HEATING OF THE BEARING
64
VIBRATION ORIGINATING IN AN ENGINE COOLING FAN WOULD BE CLASSIFIED AS ?
A. MEDIUM FREQUENCY VIBRATION (500-2000 CPM) (P.132)
65
IMPROPER TAIL ROTOR BALANCE IS LIKELY TO CAUSE?
A. A HIGH FRECUENCY VIBRATION (200+CPM) (P.132)
66
WHAT HAPPEN IF A METAL ROTOR BLADE HAS A 1/8 INCH CRACK?
A. THE BLADE MUST BE REPLACED.
67
A LINE DRAWN FROM BLADE TIP TO BLADE TIP WOULD REPRESENT?
A. THE LONGITUDINAL AXIS
68
WHAT IS THE MOST COMMON METHOD OF OBTAINING DYNAMIC BALANCE OF A SEMI-RIGID ROTOR HEAD
A. THE USER OF A STABILIZER BAR (P.52)
69
ON A HELICOPTER UTILIZING A TWO BLADE SEMI-RIGID ROTOR AND A STABILIZER BAR, THE STABILIZER BAR IS USED TO ?
A. PROVIDE A REFERENCE FOR CONTROLLING BLADE ANGLE OF ATTACK
70
OVER SENSITIVITY OF CONTROL RESPONSE TO CYCLIC STICK MOVEMENT COMBINED WITH AN UNSTABLE HELICOPTER COULD BE THE RESULT OF?
A. HARD STABILIZER BAR DAMPERS
71
IN A ROTOR DRIVE TRAIN THE FREE WHEEL UNIT PERMITS
A. ROTOR ROTATION INDEPENDETN FOR ENGINE ROTATION
72
WHAT DETERMINES THE CONING ANGLE OF A MAIN ROTOR?
A. BLADE FLAPPING LIMITS AND THE WEIGHT OF THE HELICOPTER?????
73
WHAT IS A DYNAMIC FLAP RESTAIN SYSTEM DESIGNED TO DO ?
A. TO LIMIT THE UPWARD TRAVEL OF THE ROTOR BLADES AT HIGH RPM
74
HYDRAULIC SERVO ACTUATORS ARE INCORPORATED INTO FLIGHT CONTROL SYSTEM TO?
A. REDUCE CONTROL FORCE FEEDBACK
75
WHAT IS NOT A DESIGN FEATURE OF A SEMI-RIGID MOTORY SYSTEM?
A. DRAG HINGES
76
WHEN HAND TRACKING A MAIN ROTOR THE AIR SHOUL BE CALM OR NEAR CALM
A. ??????
77
WHY IS ROTOR BLADE TRACKING CARRIED OUT?
A. TO ENSURE ALL BLADES FOLLOW THE SAME TIP PATH PLANE THROUGH OUT THE CYCLE OF ROTATION
78
FUSELAGE STATAION OF MOST NORTH AMERICAN HELICOPTERS IS?
A. LOCATED 13" AFT OF THE DATUM
79
IF A CENTER OF GRAVITY IS OUT OF LIMITS?
A. IT MAY CAUSE THE AIRCRAFT TO BE UNCONTROLLABLE IN FLIGHT
80
WHAT IS THE POINT OF REFERENCE FOA ALL WEIGHT AND BALANCE MEASUREMENTS?
A. THE DATUM
81
HOW IS THE MOMENT IN WEIGHT AND BALANCE COMPUTATIONS DETERMINED?
A. BY MULTIPLYING THE WEIGHT OF THE ITEM BY ITS ARM
82
HOW IS THE C OF G DETERMINED?
A. BY DIVIDING THE TOTAL MOMENT BY THE NET WEIGHT
83
FROM THE FOLLOWING INTO CALCULATED THE C OF G OG A LEVEL HELICOPTER?
A. Front jacking points total weight 1400 lbs
Rear jacking points total weight 1100 lbs
Distance between front jacking points and mast center line is 32”
Distance between front and rear jacking points is 68”
Relative to the rotor mast center line the C of G is 2.08” forward
Note: a - means forward of the datum
a + means aft of the datum
84
FROM THE FOLLOWING INFO CALCULATED THE REVISED C OF G Helicopter weight 35001bs
Present C of G is 1.5” forward of the rotor mast center line
Add a 20 lb. battery 25” aft of the rotor mast center line
A. Relative to the mast center line the new C of G is 1.35” forward
85
HOW DO YOU FIGURE OUT THE CORRECT TORQUE IF THERE IS AN EXTENSION USED ON THE TORQUE WRENCH?
TW= TxL/L+A
Where TW = Indicated torque value on wrench
T = Actual torque value applied to the bolt
L=Lever length
A = The attachment length
If T= 115.0 in Lbs L = 8.0”
TW= Unknown A = 1.5”
TW = 96.84 in lbs
86
WHEN REAMING A HOLE WITH A STRAIGHT REAMER (HAND)
A. THE REAMER SHOULD BE BACKED PERIODICALLY TO CLEAR THE FLUTES
87
A CONTROL TRAVEL IS NORMALLY LIMITED BY WHAT?
A. FIXED OR ADJUST STOPS
88
WHY IS THERE A SMALL HOLE DRILLED IN AN ADJUSTABLE ROD END?
A. TO PROVIDE A MEANS OF CHECKING FOR SAFETY
89
WHEN FIBER LOCK NUTS ARE INSTALLED ON FLAT END BOLTS, STUDS, OR SCREWS.
A. AT LEAST THREE THREADS MUST EXTEND THROUGH THE NUT
90
WHY IS THE USE OF VAPOR DEGREASING STEAM, CLEANING, MEK OR OTHERS SOLVENTS NOT RECOMMENDED FOR REMOVAL OF CORROSION PREVENTIVE COMPOUNDS FROM FLIGHT CONTROL CABLES?
A. BECAUSE THE CABLES INTENAL LUBRICATION WOULD ALSO BE REMOVED
91
FLIGHT CONTROL CABLES MUST BE REPLACED?
A. IF THE CABLES IS DISTORTED, WORTH OR CORRODED EVEN IF NO STRANDS ARE BROKEN
92
IF A BATTERY RELAY CHATTERS WHEN THE BATTERY MASTER IS SWITCHED ON WHAT MAY BE THE CAUSE?
A. A LOW BATTERY VOLTAGE
93
WHAT IS THE REQUIRED WHEN MORE THAN ONE ALTERNATOR (AC GEN) IS POWERING AN AC BUS?
A. THE SAME PHASE SEQUENCE, FREQUENCY AND VOLTAGE
94
WHAT SHOULD THE SECTION OF ELECTRIC CABLE SIZE BE BASED ON?
A. CURRENT CARRYING CAPACITY AND VOLTAGE DROP
95
HOW WOULD YOU CORRECT THE OVERCHARGING OF AN AIRCRAFT BATTERY?
A. ADJUST THE VOLTAGE REGULATOR
96
WHAT DOES THE MASTER SWITCH OF A D.C. ELCECTRICAL SYSTEM CONNECT TO?
A. THE BATTERY AND THE DC BUS
97
HOW IS A SPLIT BUS RELAY ENERGIZED?
A. BY EITHER BATERY OR EXTERNAL POWER
98
WHY MUST THE OUTPUT VOLTAGE & CURRENT OF TWO DC GENERATORS BE BALANCED?
A. TO PREVENT A REVERSE FLOW OF CURRENT AND REVERSE POLARITY TO THE LOWER OUTPUT GENERATOR
99
HOW IS THE BULB OG A FIRE WARNING SYSTEM NORMALLY TESTED?
A. BY PRESSING THE OUTER RIENG OF THE LIGHT
100
WHAT FLIGHT INSTRUMENT REQUIRES THE USE OF BOTH PITOT AND STATIC SYSTEM?
A. AIR SPEED INDICATOR
101
WHICH INSTRUMENT DOES NOT REQUIRE STATIC PRESSURE FOR OPERATION?
A. TURN AND BANK INDICATOR
102
DURING A COMPASS SWING THE SIGHTING COMPASS INDICATED 354 AND THE AIRCRAFT COMPASS INDICATED 356, WHAT SHOULD THE AIRCRAFT BE ADJUSTED TO INDICATE?
A. 354 NORTH AND EAST, ALL ERROR SHOUL BE TAKEN OUT; SOUTH AND WEST 1/2 ERROR SHOULD BE TAKEN OUT
103
LAMINAR AIRFLOW BECOMES WHAT WHEN IT GETS CLOSER TO THE TRAILING EDGE?
A. THE BOUNDARY LAYER BECMES THICKER AND LAMINAR FLOW DIMINISHES
104
WHAT TAB HELP THE PILOT STEER?
A. SPRING TAB HELPS BOOS MAIN CONTROL
105
MONOCOQUE FUSELAGE USES WHAT FOR ITS PRIMARY LOAD?
A. SKIN STIFFENERS WITH NO SUB-STRUCTURE
106
A DIHEDRAL ANGLE IS MEASURED FROM?
A.THE LATERL AXIS OF A/C AND THE CENTER LINE OF THE WING
107
ROTOR BRAKE ON TURBINE ENGINE CHOPPER ACIVATED BY:
A. BLEED AIR / ENGINE OIL / TRANMISSION OI / DEDICATED HYDRAULIC SYSTEM
108
DYNAMIC BALANCE OF THE ROTOR CAN BE DONE USING
A. VIBREX SYSTEM/ PHASOR ONLY/ PHASOR AND VIBREX/ PHASOR AND STROBEX
109
ONE FAILED DAMPER ON FULLY ARTICULATED HEAD WOULD CASE A 1-1 BEAT F ????
A. 2-1 LATERAL VIBRATION / 2-1 VERTICAL VIBRATION/ BOTH OUT OF TRACK AND INBALANCE
110
RATE OF CLIMB INDICATOR IS CONNECTED TO ?
A. VERTICAL GYRO / PITOT SYSTEM / STATIC SYSTEM / BOTH PILOT AND STATIC
111
AFT STABILIZER AIRFOILS IS:
A. SYMMETRICAL/ NON-SYMETRICAL / INVERTED SYMMETRICAL/ INVERTED NON-SYMMETRICAL
112
MUST BUMPING USUALLY RELATED TO WHAT TYPE OF ROTOR
A. RIGID / SEMI-RIGID / SEMI ARTICULATED/ ARTICULATED
GENERAL PRACTICE
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