Exam Review Flashcards
R32/4500ft
Runway 32 active, RVR is 4500ft
LTG
Lighting
$
In need of maintencance
DSNT
VC
OS
DSNT: distant = greater than 10 miles away
VC: 5-10 miles from airfield
OS: 0-5 miles from center of airfield
Vertical visibility
Put into the main body of the METAR when there is TOTAL OBSCURITY (no ceiling layer is present)
Varying winds *V
> 60* and greater than 6 knots
Wind is in degrees from TRUE NORTH
Ceiling
The lowest layer aloft which is broken or overcast, OR the vertical visibility is used when the sky is totally obscured.
Write down H and L chart
IALT. TALT
H. ——— L
L. ——— H
Pressure instruments
Altimeter, VSI, ASI
VSI is not mandatory for IFR flight
ASI
Diaphragm vented to pitot, case vented to static
Kollsman window
Corrects for barometric/atmospheric pressure changes
VSI
Diaphragm vented to static, case vented to calibrated leak (lag delay of several seconds)
MSL
- 92Hg with a standard lapse of -1in per 1000ft
- 2mb/HP**
15C with a standard lapse of 2C per 1000ft
Absolute altitude
Measured above terrain
PA
Measured from above **standard datum plane
True altitude
Altitude above MSL
Indicated altitude
Read from the altimeter
What do we do to determine the maximum altimeter error
FAA: +/-75ft
For aircraft specific altimeter error: reference or maintenance manuals
Once you set your field elevation, record Kollsman window setting. Once current altimeter setting is given, put in and check that error does not exceed 75ft/.07
IAS
Indicated airspeed read from the airspeed indicator, uncorrected
True airspeed
Calibrated airspeed corrected for density
Calibrated airspeed
Indicated airspeed corrected for installation and instrument error
Newtons law
1) inertia - all forces equal “balanced”
2) acceleration - forces “unbalanced”
3) action/reaction - rotor rotates, body rotates opposite
Airfoil
Any SURFACE or BODY that produces LIFT and THRUST
Airfoil types
Symmetrical
Non-symmetrical/un-symmetrical
Induced flow
Downward flow of air through the center of rotation/rotor blades
TAF: total aerodynamic force
Resultant force: lift plus drag on the airfoil
Drag
Induced - most critical in hover, caused by induced flow and vortices
Profile - relatively unchanged inflight, due to rotor blade skin
Parasitic - fuselage skin drag (increases with airspeed)
Total - total drag
Blowback
Rotor pitches backward (tilts up)
- flapping
- FORWARD cyclic feathering
Total Force
Total Aerodynamic Force
Total force = lift and thrust
TAF = lift and drag
Centrifugal force
Outward force of body in curved path
Provides rigidity to the rotor blades
CONING - a compromise between lift and centrifugal force (lift is perpendicular to the tip path plane)
IGE
One rotor disk diameter measured from the disk to the surface
Diminish effects if induced flow
Forward airspeed
ETL
16-24 knots - forward flight and hovering in a headwind (rotor outruns the vortices, operates in clean air)
Transverse Flow Effect (TFE)
10-20 knots. Forward half of rotor system sees more horizontal airflow and larger angle of attack, rear half sees more vertical airflow and lower angke of attack.
**Excessive coning
Causes: Low rpm Excessive weight Turbulent air High G maneuvers
*Retreating blade stall - causes relate: excessive coning has same causes, except retreating blade stall has a factor of density altitude.
**Three conditions for settling with power by the numbers
300fpm descent
20-100% engine power applied
Below ETL speed
To fix this:
- adjust airspeed with forward cyclic
- reduce collective
Autorotation
No power applied, rotor driven by relative wind
**Aerodynamic equilibrium: Rotor rpm within acceptable limits
Turn - increases RPM as airspeed increases
Dynamic rollover
Factors: HUMAN and PHYSICAL
SMOOTH, MODERATE collective reduction
P
R
E
**Primary cause of retreating blade stall
Excessive airspeed
- violent pitch up of the nose
- roll to the stall (left) side
**Down collective, gain control of aircraft
