TB 1-1670-260-12
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prevent excessive loading on the tailboom. Reference A recommends that the published
rigging should ensure an initial nose up attitude of approximately 5 degrees prior to
hoisting the helicopter.
3.2.2.4 Reference A further states that the tail rotor blades be removed prior to
recovery to ensure airworthiness of the Tail Rotor system; to prevent damage to the tail
rotor system during recovery.
3.2.2.5 If removal of tail rotor blades from disabled helicopter prior to recovery is not
possible then tie the lower blade from the tail rotor to the disabled OH-58 helicopter
using a fixed length tie-down (without snap hook). Wrap tie-down to preclude blade
flapping during flight- -if further clarification is required or procedures for tying the lower
tail rotor blade to the airframe of the disabled helicopter contact AMSAM-RD-AE-I-
D-O (Mr. Gerald Johnson Jr.) for a sketch
or picture.
3.2.2.6 Prior to disabled helicopter recovery, remove engine to transmission drive shaft
flex frame (K-Flex) coupling. Install a "trip" accelerometer on a rigid component of the
3.2.2.7 Ensure that the recovery parameters (limitations) listed in Figure 4 are not
exceeded. If Figure 1 parameters are exceeded or it cannot be determined that
parameters were met, then contact AMSAM-RD-AE-I-D-O (Mr. Gerald Johnson Jr.)
for corrective action or deposition.
Figure 4. Recovered Helicopter Recovery
Parameters (Limitations)
Parameter
Blades On
Blades Off
Maximum Vertical Load Factor (see Note 1)
2g
2g
Max victim vehicle weight
5100 Lbs
5100 Lbs
Maximum speed
30 KIAS
60 KIAS
Maximum bank angle
20 Degrees
30 Degrees
Maximum rate of climb
1000 FPM
3000 FPM
Maximum rate of descent
1000 FPM
3000 FPM
Initial Attitude for Hoisting (Rigging)
+5 Degrees
+5 Degrees
Terrain Lifting Limits Fore/Aft Slope
-10 Degrees
-10 Degrees
Terrain Lifting Limits Lateral Slope
-10 Degrees
-10 Degrees
Tail Rotor Blades (see Note 2)
Removed
Removed
Drive Shaft Flex Frame (K-Flex) (see Note 3)
Removed
Removed
No
No
Use of Drogue Chute