0017 00 TM 1-1670-260-12&P __________________________________________________________________________________________   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 applicable recovery helicopter are specified in Table 1. Table 1. Recovery Helicopter Flight Parameters Parameter CH-47 Recovery Helicopter UH-60 Recovery Helicopter Maximum Airspeed: 30 Knots Indicated Air Speed (KIAS) 30 KIAS Maximum Bank Angle: 20 Degrees 20 Degrees Maximum Rate-of-Climb 1000 Feet Per Minute (FPM) 1000 FPM Maximum Rate-of-Descent 1000 Feet Per Minute (FPM) 1000 FPM Drogue Chute Optional (See Note Below) Optional (See Note Below) Maximum Allowable Vertical Load Factor 2g’s (See Note Below) 2g’s (See Note Below) Note: The maximum allowable load factor of 2g’s is not measurable by the crew; therefore it shall be assumed that the maximum vertical load factor has been exceeded during an OH-58 aerial recovery and that a post recovery inspection shall be performed.   WARNING Recovery helicopter should take care to ensure that the  damaged  helicopter  is  lifted  first  from  the  main rotor   hub   before   lifting   the   tail-boom   to   prevent excessive loading on the tail-boom. (Recommend an initial  attitude  of  approximately  5  degrees  nose  up prior to hoisting helicopter.) Pitch and roll variations that exceed the OH-58D’s –10 degree  slope  landing  and  take-off  will  result  in  the helicopter   exceeding   lifting   parameters,   requiring inspections    in    accordance    with    the    applicable technical manual. 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. 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. 0017 00-2