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glide distance because of the reduction in rpm available
for the touchdown. In some instances at low altitude or
low airspeed (and/or high gross weight), settling may
be so rapid that little can be done to avoid a hardimpact
landing. In that case, it is critical to maintain
aircraft control and assume a safe landing attitude prior
to touchdown. Cushion the landing with all remaining
collective as the helicopter settles to the ground.
9-11
TM 1-1520-248-10
RIGHT CREW DOOR
JETTISON HANDLE
IMID
FIRST AID KIT
PILOT SEAT
CENTER POST
COPILOT/GUNNER
SEAT
FIRE EXTINGUISHER
LEFT CREW DOOR
/ I JETTISON HANDLE
40607M3
Jl206
Figure 9-1. Emergency Exits and Equipment
9-12
TM 1-1520-248-10
9-13
TM 1-1520-248-10
9-14
TM 1-1520-248-10 II
EXAMPLE
W A N T E D
GROSS WEIGHT LIMIT FOR
SAFE HEIGHT VELOCITY
OPERATION
KNOWN
DENSITY ALTITUDE = 8000 FT
METHOD
ENTER DENSITY ALTITUDE
MOVE RIGHT TO MAXIMUM
SAFE HEIGHT VELOCITY
LINE
DROP DOWN, READ
GROSS WEIGHT = 4260 LB
HEIGHT VELOCITY DIAGRAM
100% RPM
10
9
3 6 3 8 4 0 4 2 4 4 4 6 4% 5 0 5 2 5 4
GROSS WEIGHT - 100 POUNDS
DATA BASIS: PRELIMINARY FLIGHT TEST, APRIL 1991
40696V1416121
J2862
Figure 9-2. Height Velocity Diagram (Sheet 3 of 3)
II
9-15
9-8. MINIMUM RATE OF DESCENT - POWER
OFF.
The Power-off minimum rate of descent is attained at
an indicated airspeed of 55 knots and 100% NR
(standard day/sea level). See figure 9-3 for maximum
glide distance.
9-9. MAXIMUM GLIDE DISTANCE - POWER
OFF.
The maximum glide distance is attained at an indicated
airspeed of 80 knots and 100% NR (standard day/sea
level). See figure 9-3 for maximum glide distance.
9-10. ENGINE FAILURE - HOVER.
AUTOROTATE.
9-11. ENGINE FAILURE - LOW ALTITUDE/
LOW AIRSPEED DURING TAKEOFF OR
CRUISE.
1. AUTOROTATE.
2. EMER SHUTDOWN.- Accomplish during
descent if time permits.
9-12. ENGINE RESTART - DURING FLIGHT.
After an engine flameout, in flight, an engine restart
may be attempted within ten seconds without closing
the throttle. The throttle can be left in the open position
because NG speed should still be above minimum
starting speed and fuel flow will be on the normal
acceleration schedule. Because the exact cause of
engine flameout cannot be determined, the decision to
attempt the start will depend upon the altitude and lime
available, rate of descent, potential landing area, and
crew assistance available.
Under ideal conditions, approximately
one minute is required to regain powered
flight from the time the attempted start is
begun.
If the decision is made to attempt an in-flight start:
1. Attempt start.
9-13. ENGINE RESTART - DURING
FLIGHT (FADEC AUTOMATIC MODE).
After an engine flameout in flight the FADEC system in
the AUTO mode (only) will Initiate a restart sequence
without pilot action.
1. Establish autorotational descent.
2. LAND AS SOON AS POSSIBLE
9-14. ENGINE COMPRESSOR STALL.
Engine compressor stall is characterized by a sharp
rumble or a series of loud sharp reports, severe engine
vibration, and a rapid rise in TGT, depending on the
severity of the surge. After engine compressor stall,
maneuvers requiring rapid or maximum power
application should be avoided. Should engine
compressor stall occur:
(OH-58D) To prevent engine damage
caused by compressor stalls or engine
surges, do not rapidly increase collective
or throttle when in analog mode.
1. Collective - Reduce.
2. ENG ANTI ICE and HTR switches - ON.
3. LAND AS SOON AS POSSIBLE.
TM 1-1520-248-10
2. LAND AS SOON AS POSSIBLE. After the
engine is started and powered flight is reestablished,
perform a power-on approach
and landing without delay.
- After the
engine is started and powered flight is
reestablished, perform a power-on approach
and landing without delay.
The FADEC automatic mode will, without pilot
action, alleviate the stall condition. The FADEC will
adjust the fuel schedule to avoid further stall
occurrence. Occurrence of a compressor stall will
increment the ENG SURGE entry on the FADEC
monitor page.
9-15. (OH-58D) ENGINE OVERSPEED.
Engine overspeed will be indicated by a right yaw,
rapid increase in rotor (NR), gas producer (NG), and
engine rpm (NP), and an increase in engine and rotor
noise. If an engine overspeed is experienced:
1. Collective - Increase to load the rotor and
　
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本文鏈接地址：OPERATOR’S MANUAL FOR ARMY OH-58D HELICOPTER 2(88)