0012 00
TM 1-1670-260-12&P
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2. PRE-RECOVERY PROCEDURES
WARNING
To prevent catastrophic failure do not use the UMARK if
its record log indicates 20 or more aerial recovery uses.
Ensure that a pre-usage inspection is performed on the UMARK contents as outlined in Work Package 0027 00.
Do not use the UMARK kit if the kits usage log indicates 20 or more uses of the kit. Refer to Work Package 0027
00 for disposition instructions if the kit has 20 or more uses. Do not use the kit if any required content items fail
pre-usage inspection.
3. RECOVERY FLIGHT PARAMETERS AND PRECAUTIONS
Flight parameters for the CH-47 recovery helicopter are specified in Table 1.
Table 1. Recovery Helicopter Flight Parameters
Maximum Airspeed:
40 Knots Indicated Air Speed (KIAS)
Maximum Bank Angle:
20 Degrees
Maximum Rate-of-Climb
1000 Feet Per Minute (FPM)
Maximum Rate-of-Descent
1000 Feet Per Minute (FPM)
Drogue Chute
No
Maximum Sink Rate
5.6 Feet Per Second (See Note Below)
Terrain Lifting Limits – Fore/Aft Slope
12 Degrees
Terrain Lifting Limits – Lateral Slope
12 Degrees
Note: If maximum sink rate cannot be determined then perform a hard landing inspection in accordance with the
applicable technical manual.
WARNING
Once the damaged helicopter is connected to the
recovery helicopter and lifted to a hover, the pitch
attitude of the damaged helicopter must be checked to
ensure a nose down attitude is achieved.
A damaged helicopter may rotate while in a hover.
This rotation may cause slings of some UMARK
rigging configurations to twist or to tighten at the main
rotor assembly. The rotation will generally stop as
airspeed is increased to approximately 5 to 10 knots.
The recovery helicopter flight crew should minimize
hover time.
If oscillations of damaged helicopter develop during
flight, tests have shown that lowering airspeed,
returning to wings level flight, and initiating a climb
has a stabilizing effect.
0012 00-2
