TM 1-1510-225-10 6-12 gravity, and contact areas of the individual cargo items for use in positioning the load. 6-16.  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    the    Center    of    Gravity Loading Diagram.  Refer to Figure 6-3.  Cargo moment may be determined by using the Cargo Moment chart, Figure 6-4. 6-17.  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.     The  cabin  section  flooring  will  withstand  a loading   of   200   pounds   per   square   foot   for   items supported on the seat tracks.  Floor areas where seat tracks are not present (walkways and aft baggage/utility  area)  will  only  support  100  pound  per square   foot   floor   loads.      Shoring   shall   be   used   to distribute  highly  condensed  weights  evenly  over  the cargo  areas.    Use  of  the  floor  seat   tracks  to  support loads is encouraged where possible. c. All   cargo   shall   be   adequately   secured   to prevent damage to the aircraft, other cargo, or the item itself. 6-18.  LOADING PROCEDURE. NOTE The cabin airstair door is weight limited to a    maximum    of    300    pounds    to    prevent possible structural damage. Loading  of  cargo  is  accomplished  through  the cabin   door   (21.5   in.   X   46.0   in.)   or   the   cargo   door (52 in. X 52 in.). 6-19.  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,  6.6 down, and 9.0 forward. 6-20.  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.  Refer to Figure 6-5.  When cargo is properly secured  by  tiedown  devices,  it  will  be  restrained  from moving in any direction within the aircraft. 6-21.  CARGO RESTRAINING METHOD. CAUTION To avoid structural damage, all cargo shall be restrained in accordance with Beech Kit Drawing  No.  101-5040,  which  provides  the correct methods for restraint and approved hardware. Cargo  is  restrained  by  passing  tiedown  devices over and around the cargo and attaching the ends of the   tiedown   device   to   the   seat   tracks   as   shown   in Figure  6-5.    The  number  of  tiedown  devices required to restrain a given weight of cargo may vary. 6-22.  CARGO UNLOADING. Unloading    of    cargo    shall    be    accomplished through the cabin door, or cargo door. Section VII.  CENTER OF GRAVITY 6-23.  CENTER OF GRAVITY LIMITATIONS. a. The  forward  Center  of  Gravity  (CG)  limit  is 188.3   arm   inches   from   14,000   pounds   to   13,500 pounds.  From 13,500 pounds down to 11,279 pounds, the    intermediate    arm    inch    values    vary    linearly    to 181 inches.      Below   11,279   pounds,   the   maximum forward CG remains 181 arm inches. b.     The aft CG limit is 196.4 inches aft of datum at all weights.  The Center of Gravity Loading Diagram is designed to establish forward and aft CG limitations.