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lift-off at low airspeeds and high angles of attack, 21-1
lost procedures, 11-16
low G conditions, 11-10
low rotor r.p.m. and blade stall, 11-10
mast bumping, 11-10
pilot-induced oscillation, 21-2
power pushover, 21-3
retreating blade stall, 11-6
settling with power, 11-5
systems malfunction, 11-11
vortex ring state, 11-5
EMERGENCYEQUIPMENTAND SURVIVALGEAR 11-16, 21-4
ENGINE
reciprocating, 5-1, 18-1
turbine, 5-1
ENGINE INSTRUMENTS 18-3
ENGINE STARTING PROCEDURE 9-2, 20-1
ENVIRONMENTAL SYSTEMS 5-10
EYE 13-1
cones, 13-1
rods, 13-2
FALSE HORIZON 13-3
FENESTRON TAIL ROTOR 1-2
FLIGHT AT SLOW AIRSPEEDS 20-12
FLIGHT CONTROLS 1-3, 4-1
antitorque pedals, 4-3
collective pitch, 4-1, 17-2
cyclic pitch, 4-2, 17-1
rudder, 17-2
swash plate assembly, 5-5
throttle, 4-1, 17-1
FLIGHT DIVERSION 11-15
FLIGHT INSTRUMENTS 12-1
airspeed indicator, 12-1, 18-4
altimeter, 12-2, 18-4
attitude indicator, 12-3
heading indicator, 12-3
magnetic compass, 12-4
turn-indicators, 12-4
vertical speed indicator, 12-2
FLIGHT MANUAL (See rotorcraft flight manual)
FORCES IN A TURN 3-8
FOUR FORCES
drag, 2-5, 16-4
lift, 2-3, 16-4
thrust, 2-5, 16-4
weight, 2-4
FREEWHEELING UNIT 5-4
FUEL INJECTION 5-8
FUEL SYSTEMS 5-6
FULLY ARTICULATED ROTOR 1-1, 5-4, 18-1
GO-AROUND 9-20, 20-15
GOVERNOR 4-2
failure, 11-14
GROSS WEIGHT 7-1
GROUND EFFECT 3-3
GROUND HANDLING 18-4
GROUND REFERENCE MANEUVERS 9-14, 20-8
rectangular course, 9-14, 20-8
s-turns, 9-16, 20-10
turns around a point, 9-17, 20-11
GROUND RESONANCE 11-7, 21-3
GYROPLANE
components, 15-2
instruments, 18-3
stability, 16-5
types, 15-1
GYROSCOPIC INSTRUMENTS 12-3
attitude indicator, 12-3
heading indicator, 12-3
D
E
F
G
turn indicators, 12-4
GYROSCOPIC PRECESSION 3-4
HANG TEST 19-4
HAZARDOUS ATTITUDES 14-5
anti-authority, 14-6, 22-3
impulsivity, 14-6, 22-1
invulnerability, 14-6, 22-1
macho, 14-6, 22-2
resignation, 14-6, 22-2
HEADING INDICATOR 12-3
HEIGHT/VELOCITY DIAGRAM 11-4, 19-3
HELICOPTER SYSTEMS 5-1
anti-icing, 5-11
autopilot, 5-10
carburetor, 5-7
clutch, 5-4
electrical, 5-8
engine, 5-1
environmental, 5-10
flight control, 4-1
fuel, 5-6
hydraulics, 5-9
main rotor, 5-4
pitot-static, 12-1
stability augmentation system, 5-10
swash plate assembly, 5-5
tail rotor drive, 5-3
transmission, 5-3
HIGH RATE OF DESCENT 20-12
HINGES 5-5
HOVERING
aerodynamics, 3-1
flight, 9-5
HOVERING OPERATIONS
autorotation, 11-4
forward flight, 9-7
rearward flight, 9-8
sideward flight, 9-7
turn, 9-6
vertical takeoff, 9-5
HOVER TAXI 9-9
HUMAN FACTORS 14-1
HYDRAULIC FAILURE 11-14
INDUCED DRAG 2-5
INDUCED FLOW 3-6
INSTRUMENT CROSS-CHECK 12-5
INSTRUMENT FLIGHT 12-5
aircraft control, 12-7
bank control, 12-9
emergencies, 12-18
straight-and-level flight, 12-7
straight climbs, 12-11
straight descents, 12-14
takeoff, 12-19
turns, 12-15
unusual attitudes, 12-18
INSTRUMENT INTERPRETATION 12-6
INSTRUMENT TURNS 12-15
30° bank turn, 12-17
climbing and descending turns, 12-17
compass turns, 12-17
timed turns, 12-16
turns to a predetermined heading, 12-16
ISOGONIC LINES 12-5
LANDING
crosswind, 9-11, 20-14
high-altitude, 20-14
illusions, 13-4
night, 13-5
normal, 20-13
running/roll-on, 10-5
short-field, 20-13
slope, 10-6
soft-field, 20-14
LANDING GEAR 1-2, 15-3, 18-4
LAWOF CONSERVATION OF ANGULAR MOMENTUM 3-2
L/DMAX 2-6
LIFT 2-3, 16-4
Bernoulli’s Principle, 2-3
magnus effect, 2-3
Newton’s Third Law of Motion, 2-4
LIFT-OFF AT LOW AIRSPEED AND HIGH ANGLE OF
ATTACK 21-1
LIFT-TO-DRAG RATIO 2-6
LOAD FACTOR 2-4
LOSS OF TAIL ROTOR EFFECTIVENESS 11-12
LOST PROCEDURES 11-16
LOW G CONDITIONS 11-10
LOW ROTOR RPM 11-10
LTE (See loss of tail rotor effectiveness)
MAGNETIC COMPASS 12-4
acceleration/deceleration error, 12-5
compass correction card, 12-5
magnetic deviation, 12-5
magnetic dip, 12-5
turning error, 12-5
variation, 12-4
MAGNUS EFFECT 2-3
MAIN ROTOR SYSTEM 1-1, 5-4
combination, 5-5
fully articulated, 1-1, 5-4
rigid, 1-2, 5-5
semirigid, 1-2, 5-5
　
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