TM 1-1520-218-10 6-11 Section V.  MISSION EQUIPMENT Not Applicable. Section VI.  CARGO LOADING 6-14.  AIR CARGO FEATURES. The 245 cubic foot cabin area is easily converted for  mixed   or   all   cargo   use   by   removing   passenger seats and a partial partition, Figure 6-6.  A top-hinged cargo    door    with    an    opening    52    inches    wide    by 52 inches   high,   is   provided   on   the   left   side   of   the fuselage   to   admit   bulk   cargo      D1     T   The   floor   is designed to support 200 pounds per square foot when supported  by  the  seat  tracks.    The  areas  where  seat track  support  is  not  possible  will  support  100  pounds per  square  foot  floor  loading.    Seat  tracks  are  to  be used for securing cargo containers. 6-15.  AERIAL DELIVERY SYSTEM. Procedures for aerial delivery of personnel and cargo have not been developed. The  cargo  door  is  a  structural  panel  and shall be closed for flight. There are no provisions for static lines; however, free  fall  parachute  operations  may  be  accomplished. The cabin door may be removed for flight by installing Beech Aircraft Corporation  Kit 100-4006.  Flights  with the   door   removed   must   be   in   accordance   with   the Federal Aviation Administration approved flight manual supplement, which accompanies this kit. 6-16.  PREPARATION OF GENERAL CARGO. Before  loading  cargo,  loading  personnel  should determine such data as weight, dimensions, center of gravity, and contact areas of the individual cargo items for use in positioning the load. 6-17.  CARGO CENTER OF GRAVITY PLANNING. The  cargo  loading  shall  be  planned  so  that  the center of gravity of the loaded aircraft will fall within the operating limits shown on Center of Gravity Limitations graph,  Figures  6-7  and  6-8.    Cargo  moment  may  be determined  by  using  the  Cargo  Moment  chart,  Figure 6-5. 6-18.  LOAD PLANNING. The basic factors to be considered in any loading situation are as follows: a.    Cargo shall be arranged to permit access to all emergency equipment and exits during flight. b.    Floorboard  and  bulkhead  structural  capacity shall  be  considered  in  the  loading  of  heavy  or  sharp edged  containers  and  equipment.    Shorings  shall  be used   to   distribute   highly   condensed   weights   evenly over the cargo areas. c.    All   cargo   shall   be   adequately   secured   to prevent damage to the aircraft, other cargo, or the item itself. 6-19.  LOADING PROCEDURE. a.    Loading  of  cargo   is   accomplished   through the cabin door  C  or cargo door  D  T . 6-20.  SECURING LOADS. All  cargo  shall  be  secured  with  restraints  strong enough to withstand the maximum force exerted in any direction.    The  maximum force  can  be  determined  by multiplying    the    weight    of    the    cargo    item    by    the applicable load factor.  These established load factors (the ratio between the total force and the weight of the cargo  item)  are  1.5  to  the  side  and  rear,  3.0  up  3.0 down, and 9.0 forward. 6-21.  RESTRAINT DEVICES. The   aircraft   is   equipped   with   full-length   seat tracks,   which   are   used   to   support   the   cargo   and provide    attachment    points    for    the    cargo    tiedown devices, Figure  6-9.  When cargo is properly secured by tiedown devices, it will be restrained from moving in any direction within the aircraft. WARNING