Patent Publication Number: US-11027948-B2

Title: Load assembly and method for lifting a load into an aircraft

Description:
CROSS-REFERENCE TO RELATED APPLICATION(S) 
     This application is a Divisional of U.S. application Ser. No. 15/188,655 which was filed on Jun. 21, 2016, entitled “LOAD ASSEMBLY AND METHOD FOR LIFTING A LOAD INTO AN AIRCRAFT,” which claims the benefit of U.S. Provisional Application No. 62/222,011 filed on Sep. 22, 2015 and entitled “BATTERY INSTALLATION SYSTEM,” each of which is incorporated herein by reference in its entirety. 
    
    
     TECHNICAL FIELD 
     The present invention generally relates to aircraft and more particularly relates to aircraft manufacturing, testing, and maintenance. 
     BACKGROUND 
     Aircraft commonly include one or more batteries that must be regularly removed and replaced for maintenance and service purposes. These batteries are typically heavy (e.g. 90 lbs.) and are located in areas of the aircraft that are difficult to access. For example, in the Gulfstream G650 aircraft, one battery is located in a forward section of its interior and two additional batteries are located in an aft section of its interior. In the past, a worker would manually carry the battery up or down a ladder to load the battery into the aircraft or to remove the battery from the aircraft. Because of the battery&#39;s weight, this was undesirable. To address this issue, some workers now use a lift located outside the aircraft to raise the battery into the aircraft or to lower the battery out of the aircraft. 
     While this solution is adequate, there is room for improvement. This is because the lift is located outside the aircraft and therefore does not help the worker move the battery through the aircraft&#39;s interior. To move the battery through the interior of the aircraft, a technician must lift and carry the battery by hand. While carrying the battery, the technician must move through small pathways in the interior by utilizing non-ergonomic positions while avoiding bodily injury and damage to sensitive equipment already on-board the aircraft. For these reasons, it is undesirable for a technician to carry a battery by hand. 
     Accordingly, it is desirable to provide a load assembly and a method for lifting a load into an aircraft. Furthermore, other desirable features and characteristics will become apparent from the subsequent summary and detailed description and the appended claims, taken in conjunction with the accompanying drawings and the foregoing technical field and background. 
     BRIEF SUMMARY 
     Various non-limiting embodiments of a load assembly for use with an aircraft, and various non-limiting embodiments of a method for lifting a load into the aircraft, are disclosed herein. 
     In a first non-limiting embodiment, the load assembly includes, but is not limited to, a support sub-assembly configured for removable coupling to a structural member of the aircraft. The structural member has a first interior position and a second interior position. The support sub-assembly extends between the first interior position and the second interior position. The load assembly further includes a lifting sub-assembly movably coupled to the support sub-assembly. The load assembly further includes, but is not limited to, a lifting sub-assembly. The lifting sub-assembly is movable along the support sub-assembly between the first interior position and the second interior position and is configured to lift and lower the load and to support the load as the lifting sub-assembly moves along the support sub-assembly between the first interior position and the second interior position. 
     In a second non-limiting embodiment, the method includes, but is not limited to, the step of coupling the support sub-assembly to a structural member of the aircraft. The method further includes, but is not limited to, the step of coupling the lifting sub-assembly to the support sub-assembly. The method further includes, but is not limited to, the step of coupling the load to the lifting sub-assembly. The method further includes, but is not limited to, the step of activating the lifting sub-assembly to lift the load. The method further includes, but is not limited to the step of moving the lifting sub-assembly from a first interior position to a second interior position. 
    
    
     
       BRIEF DESCRIPTION OF THE DRAWINGS 
       The present invention will hereinafter be described in conjunction with the following drawing figures, wherein like numerals denote like elements, and 
         FIG. 1  a fragmentary perspective view illustrating an aircraft and a first non-limiting embodiment of a load assembly; 
         FIG. 2  is a perspective view illustrating a support sub-assembly of the load assembly of  FIG. 1  in an operation state; 
         FIG. 3  is a perspective view illustrating the support sub-assembly of  FIG. 2  in a storage state; 
         FIGS. 4A, 4B, and 4C  are magnified perspective views illustrating a fixed spacer portion of the support sub-assembly in the storage state of  FIG. 3  transitioning to the operational state of  FIG. 2 ; 
         FIG. 5  is a fragmentary perspective view illustrating the aircraft and a second non-limiting embodiment of the load assembly; 
         FIG. 6  is a perspective view illustrating the support sub-assembly of  FIG. 5  in an operation state; 
         FIGS. 7A and 7B  are fragmentary perspective views illustrating a forward extender of the support sub-assembly of  FIG. 6 ; 
         FIGS. 8A and 8B  are fragmentary perspective views illustrating an aft extender of the support sub-assembly of  FIG. 6 ; 
         FIG. 9  is a perspective view illustrating a lifting sub-assembly of the load assembly of  FIGS. 1 and 5 ; 
         FIG. 10  is a fragmentary perspective view illustrating a portion of the lifting sub-assembly of  FIG. 9  supporting a load; 
         FIG. 11  is a fragmentary perspective view illustrating the load assembly including a shelf disposed in the aircraft; 
         FIG. 12  is a perspective view illustrating the shelf of  FIG. 11 ; 
         FIG. 13  is a fragmentary perspective view illustrating an opening to an exterior of the aircraft; 
         FIGS. 14A, 14B, 14C, and 14D  are fragmentary perspective views illustrating the method of positioning the lifting sub-assembly onto the support sub-assembly of the load assembly of  FIGS. 1 and 5 ; 
         FIGS. 15A, 15B, and 15C  are perspective views illustrating a step of coupling a load to the lifting sub-assembly; 
         FIGS. 16A and 16B  are fragmentary perspective views illustrating steps of activating the lifting sub-assembly in the aft section of the aircraft; 
         FIGS. 17A, 17B, and 17C  are fragmentary perspective views illustrating a steps of moving the load in an aft section of the aircraft from the shelf to an interior surface of the aircraft; and 
         FIGS. 18A and 18B  are fragmentary perspective views of the second non-limiting embodiment of  FIG. 5  illustrating the steps of activating the lifting sub-assembly in a forward section of the aircraft. 
     
    
    
     DETAILED DESCRIPTION 
     The following detailed description is merely exemplary in nature and is not intended to limit the invention or the application and uses of the invention. Furthermore, there is no intention to be bound by any theory presented in the preceding background or the following detailed description. 
     A load assembly for lifting or lowering a load in an aircraft is taught herein. In an exemplary embodiment, the load assembly is configured to be modular such that the load assembly can be utilized in the aircraft during maintenance or service of the aircraft, and removed from the aircraft prior to flight. The load assembly includes a support sub-assembly and a lifting sub-assembly. The support sub-assembly is configured for being removably coupled to a structural member of the aircraft with the structural member having a first interior position and a second interior position. The support sub-assembly includes a beam portion and a fixed spacer portion extending transversely from the beam portion. When the support sub-assembly is to be utilized in an aft section of the aircraft, each of the beam portion and the fixed spacer portion are configured for removable coupling to the structural member of the aircraft. When the support sub-assembly is to be utilized in a forward section of the aircraft, the support sub-assembly further includes a forward extender removably coupled to the fixed spacer portion and an aft extender removably coupled to the beam portion. The forward extender and the aft extender are configured for removable coupling to the structural member of the aircraft. 
     The lifting sub-assembly is movably coupled to the support sub-assembly. The lifting sub-assembly is movable along the support sub-assembly between the first interior position and the second interior position and configured to lift or lower the load in the aircraft. The lifting sub-assembly is also movable along the support sub-assembly between the first interior position and the second interior position to support the load as the lifting sub-assembly moves along the support sub-assembly between the first interior position and the second interior position. 
     In an embodiment, the lifting sub-assembly includes a winch and a cable bar with a cable coupling the cable bar to the winch. The lifting sub-assembly further includes a joining device removably coupled to the cable bar. The joining device is configured for removable coupling to the load. The winch is configured to extend and retract the cable for raising and lowering the load. 
     When the load assembly is to be utilized in the aft section of the aircraft, the load assembly includes a shelf disposed in the aft section of the aircraft. The shelf is utilized as a temporary support for supporting the load when the load is installed or removed from the aircraft. The shelf is disposed in line with the second interior position of the structural member for lifting the load from the shelf to the lifting sub-assembly, or lowering the load from the lifting sub-assembly to the shelf, when the lifting sub-assembly is in the second interior position. 
     In a first exemplary embodiment, the load assembly may be utilized to service an aft battery of the aircraft, as follows. Although the context of the discussion below pertains to lifting and positioning a battery in an aircraft, it should be understood that the load assembly disclosed herein is not limited to use only with batteries nor for use only on aircraft. Rather, the load assembly disclosed and described herein may be employed to lift and position any other suitable load within any type of vehicle or structure. The beam portion and the fixed spacer portion of the support sub-assembly are coupled to the structural member of the aircraft. The lifting sub-assembly is coupled to the support sub-assembly. The joining devices are coupled to the aft battery and the cable bar is coupled to the joining devices. The lifting sub-assembly is activated to lift the aft battery from the exterior of the aircraft into the aircraft. The lifting sub-assembly is moved from the first interior position to the second interior position. The lifting sub-assembly is activated to lower the aft battery to the shelf. The lifting sub-assembly is released from the aft battery. The aft battery is moved along the shelf to an interior surface of the aircraft. The load assembly is removed from the aircraft. 
     In a second exemplary embodiment, the load assembly may be utilized to service a forward battery of the aircraft, as follows. The forward extender and the aft extender of the support sub-assembly are coupled to the structural member of the aircraft. The beam portion is coupled to the forward extender and the fixed spacer portion is coupled to the aft extender. The lifting sub-assembly is coupled to the support sub-assembly. The joining devices are coupled to the forward battery and the cable bar is coupled to the joining devices. The lifting sub-assembly is activated to lift the forward battery from the exterior of the aircraft into the aircraft. The lifting sub-assembly is moved from the first interior position to the second interior position. The lifting sub-assembly is activated to lower the forward battery to an interior surface of the aircraft the shelf. The lifting sub-assembly is released from the forward battery. The load assembly is removed from the aircraft. 
     A greater understanding of the load assembly described above and of the method for lifting a load into the aircraft may be obtained through a review of the illustrations accompanying this application together with a review of the detailed description that follows. 
       FIG. 1  is a non-limiting embodiment of a fragmentary perspective view illustrating an aircraft  10  having a plurality of structural members  12 . In certain embodiments, the plurality of structural member  12  as illustrated in  FIG. 1  is located in an aft section of the aircraft  10 . The plurality of structural members  12  are commonly referred to as bulkheads. The plurality of structural members  12  typically extends throughout the aircraft  10  for providing structural integrity to the aircraft  10 . The plurality of structural members  12  as illustrated in  FIG. 1  extend between a first interior position  14  and a second interior position  16 . Skin and structure of the aircraft  10  has been removed in  FIG. 1  for clarity purposes. Also illustrated in  FIG. 1  is a non-limiting embodiment of a load assembly  18 . The load assembly  18  is illustrated while coupled to the plurality of structural members  12 . The load assembly  18  includes a support sub-assembly  20  and a lifting sub-assembly  22 . The support sub-assembly  20  is configured for removable coupling to the structural member  12  of the aircraft  10 . The support sub-assembly  20  extends between the first interior position  14  and the second interior position  16  of the structural member  12 . The lifting sub-assembly  22  is movable along the support sub-assembly  20  between the first interior position  14  and the second interior position  16  and configured to lift or lower a load  92  (not shown in  FIG. 1 ) in the aircraft  10 . The lifting sub-assembly  22  is also movable along the support sub-assembly  20  between the first interior position  14  and the second interior position  16  to support the load  92  as the lifting sub-assembly  22  moves along the support sub-assembly  20  between the first interior position  14  and the second interior position  16 . As will be described in greater detail below, the load assembly  18  illustrated in  FIG. 1  is configured for aft battery installation or removal. 
       FIG. 2  is a perspective view illustrating the support sub-assembly  20  of  FIG. 1  in an operation state. The support sub-assembly  20  includes a beam portion  24  and a fixed spacer portion  26  extending transversely from the beam portion  24 . The beam portion  24  is generally linear extending between a first beam end  30  and a second beam end  32 . The beam portion  24  includes a top flange  34  and a bottom flange  36  with a web  38  disposed therebetween. The web  38  defines a plurality of web openings  40  between the first beam end  30  and the second beam end  32  for reducing weight of the beam portion  24 . The bottom flange  36  of the beam portion  24  includes locking pins  42  adjacent the first beam end  30  and adjacent the second beam end  32 . The fixed spacer portion  26  is adjacent the first beam end  30  and extends transversely from the top flange  34  to a fixed spacer surface  44 . 
     The support sub-assembly  20  includes one or more retainer clamps  46  configured to engage an individual structural member of the plurality of structural members  12  for removably coupling the support sub-assembly  20  to the plurality of structural members  12 . The one or more retainer clamps  46  includes a forward retainer clamp  48  and an aft retainer clamp  50 . The fixed spacer portion  26  includes the forward retainer clamp  48  with the forward retainer clamp  48  disposed on the fixed spacer surface  44  of the fixed spacer portion  26  adjacent the first beam end  30 . The beam portion  24  includes the aft retainer clamp  50  with the aft retainer clamp  50  disposed on the beam portion  24  adjacent the second beam end  32 . 
     Each of the one or more retainer clamps  46  includes an adjustable clamp portion  52  and a fixed clamp portion  54 . The adjustable clamp portion  52  is removably coupled to the support sub-assembly  20  with fasteners  56  that are threaded to engage the support sub-assembly  20 . The fasteners  56  may be further defined as hand knobs. The fixed clamp portion  54  is generally fixedly coupled to the support sub-assembly  20 . The adjustable clamp portion  52  and the fixed clamp portion  54  are configured to engage opposing sides of the structural member  12  of the aircraft  10  for securing the support sub-assembly  20  to the structural member  12 . 
       FIG. 3  is a perspective view illustrating the support sub-assembly  20  of  FIG. 2  in a storage state. When the support sub-assembly  20  is in the storage state, the adjustable clamp portion  52  of the forward retainer clamp  48  is removed from the fixed spacer surface  44  of the fixed spacer portion  26  and coupled to a side surface  58  of the fixed spacer portion  26  with retaining pins  60 . The retaining pins  60  may be further defined as ball lock pins. 
       FIGS. 4A, 4B, and 4C  are magnified perspective views illustrating the fixed spacer portion  26  of the support sub-assembly  20  in the storage state of  FIG. 3  transitioning to the operational state of  FIG. 2 . Referring specifically to  FIG. 4A , the adjustable clamp portion  52  of the forward retainer clamp  48  is coupled to the side surface  58  of the fixed spacer portion  26  with retaining pins  60 . Referring specifically to  FIG. 4B , the adjustable clamp portion  52  of the forward retainer clamp  48  is transitioning from the side surface  58  of the fixed spacer portion  26  to the fixed spacer surface  44  of the fixed spacer portion  26 . Referring specifically to  FIG. 4C , the adjustable clamp portion  52  of the forward retainer clamp  48  is coupled to the fixed spacer surface  44  of the fixed spacer portion  26  with the fasteners  56 . 
       FIG. 5  is a fragmentary perspective view illustrating the aircraft  10  having the plurality of structural members  12 . In certain embodiments, the plurality of structural members  12  as illustrated in  FIG. 5  are located in a forward section of the aircraft  10 . One structural member of the plurality of structural members  12  is disposed at a first interior position  14  and another structural member of the plurality of structural members  12  is disposed at a second interior position  16 . Once again, skin and structure of the aircraft  10  has been removed in  FIG. 5  for clarity purposes. Also illustrated in  FIG. 5  is the second non-limiting embodiment of the load assembly  18  including the support sub-assembly  20  and the lifting sub-assembly  22 . In this embodiment, the support sub-assembly  20  of the load assembly  18  includes a forward extender  62  and an aft extender  64  for removable coupling the support sub-assembly  20  to the plurality of structural members  12  of the aircraft  10 . As will be described in greater detail below, the load assembly  18  illustrated in  FIG. 5  is configured for forward battery installation or removal. 
       FIG. 6  is a perspective view illustrating the support sub-assembly  20  of  FIG. 5  in an operation state. The forward extender  62  is configured to engage the forward retainer clamp  48  for removable coupling the forward extender  62  to the fixed spacer portion  26  adjacent the first beam end  30 . Specifically, when the forward extender  62  is utilized, the adjustable clamp portion  52  of the forward retainer clamp  48  is removed from the fixed spacer surface  44  of the fixed spacer portion  26  and coupled to the side surface  58  of the fixed spacer portion  26  with retaining pins  60 . The forward extender  62  engages the fixed clamp portion  54  of the forward retainer clamp  48  and is coupled to the fixed spacer surface  44  with the fasteners  56 . The aft extender  64  is configured to engage the aft retainer clamp  50  for removably coupling the aft extender  64  to the beam portion  24  adjacent the second beam end  32 . Specifically, when the aft extender  64  is utilized, the aft extender  64  engages the fixed clamp portion  54  of the aft retainer clamp  50  and is coupled to the beam portion  24  with adjustable clamp portion  52  of the aft retainer clamp  50 . 
     The forward extender  62  includes one or more of the retainer clamps  46 , such as a forward extender retainer clamp  66 . More specifically, the forward extender  62  includes two forward extender retainer clamps  66 . The forward extender retainer clamps  66  of the forward extender  62  are each spaced from the forward retainer clamp  48  of the fixed spacer portion  26 . Each of the forward extender retainer clamps  66  includes the adjustable clamp portion  52  and the fixed clamp portion  54 . Each of the adjustable clamp portions  52  of the forward extender retainer clamps  66  are removably coupled to the forward extender  62  with the fasteners  56  which are threaded to engage the forward extender  62 . The fixed clamp portion  54  is generally fixedly coupled to the forward extender  62 . The adjustable clamp portion  52  and the fixed clamp portion  54  of the forward extender retainer clamps  66  are configured to engage opposing sides of an individual structural member of the plurality of structural members  12  for securing the forward extender  62  to the individual structural member. 
     The aft extender  64  includes one or more of the retainer clamps  46 . More specifically, the aft extender  64  includes an aft extender retainer clamp  68 . The aft extender retainer clamp  68  of the aft extender  64  is spaced from the aft retainer clamp  50  of the beam portion  24 . The aft extender retainer clamp  68  includes the adjustable clamp portion  52  and the fixed clamp portion  54 . The adjustable clamp portion  52  of the aft extender retainer clamp  68  is removably coupled to the aft extender  64  with the fasteners  56  which are threaded to engage the aft extender  64 . The fixed clamp portion  54  is generally fixedly coupled to the aft extender  64 . The adjustable clamp portion  52  and the fixed clamp portion  54  of the aft extender retainer clamp  68  is configured to engage opposing sides of the structural member  12  of the aircraft  10  for securing the aft extender  64  to the structural member  12 . 
       FIGS. 7A and 7B  are fragmentary perspective views illustrating the forward extender  62  of  FIG. 6 . The forward extender  62 , as illustrated in  FIG. 7A  with a view toward the aft section of the aircraft  10  and as illustrated in  FIG. 7B  with a view toward the forward section of the aircraft  10 , is coupled to a structural member of the plurality of structural members  12 . The forward extender  62  includes a forward locking member  70  configured to engage the fixed clamp portion  54  of the forward retainer clamp  48  and be coupled to the fixed spacer surface  44  with the fasteners  56 . 
       FIGS. 8A and 8B  are fragmentary perspective views illustrating the aft extender  64  of  FIG. 6 . The aft extender  64 , as illustrated in  FIG. 8A  with a view toward the aft section of the aircraft  10  and as illustrated in  FIG. 8B  with a view toward the forward section of the aircraft  10 , is coupled to a structural member of the plurality of structural members  12 . The aft extender  64  includes an aft locking member  72  configured to engage the fixed clamp portion  54  of the aft retainer clamp  50  and to be coupled to the beam portion  24  of the support sub-assembly  24  with adjustable clamp portion  52  of the aft retainer clamp  50 . 
       FIG. 9  is a perspective view illustrating the lifting sub-assembly  22  of  FIGS. 1 and 5 . As introduced above, the lifting sub-assembly  22  is movable along the support sub-assembly  20  between the first interior position  14  and the second interior position  16  (see  FIGS. 1 and 5 ) and configured to lift or lower the load  92  (not shown in  FIG. 9 ). The lifting sub-assembly  22  is also movable along the support sub-assembly  20  between the first interior position  14  and the second interior position  16  to support the load  92  as the lifting sub-assembly  22  moves along the support sub-assembly  20  between the first interior position  14  and the second interior position  16 . In certain embodiments, it is desirable to limit the weight of the lifting sub-assembly  22  in an effort to ease coupling of the lifting sub-assembly  22  to the support sub-assembly  20 . In various embodiments, the lifting sub-assembly  22  has a weight of no greater than 40 lbs., no greater than 30 lbs., or no greater than 25 lbs. 
     The lifting sub-assembly  22  includes a cart  74  having a first cart end  114  and a second cart end  116 . The cart  74  includes a plurality of gliders  76  configured to engage the support sub-assembly  20  such that the cart  74  is movable along the support sub-assembly  20  between the first interior position  14  and the second interior position  16  (see  FIGS. 1 and 5 ). Specifically, the gliders  76  of the cart  74  are configured to engage the bottom flange  36  of the beam portion  24  of the support sub-assembly  20 . In certain embodiments, the cart  74  includes two gliders  76  adjacent the first cart end  114  and two gliders  76  adjacent the second cart end  116  configured to engage the support sub-assembly  20 . 
     The lifting sub-assembly  22  further includes a winch  78  coupled to the cart  74 . The winch  78  includes a battery, such as an 18-volt battery, for energizing the winch  78 . However, it is to be appreciated that the winch  78  may utilize any power source known in the art for energizing such winches. The winch  78  further includes a controller (not shown), which is operatively coupled to the winch  78  by a control cable (not shown), for operation of the winch  78 . The winch  78  also includes a strain gauge (not shown), which couples the control cable to the winch  78 , to prevent disengagement of the control cable from the winch  78 . The winch  78  also includes a safety wire (not shown) coupled to a tension release (not shown) to prevent unintentional release of engagement the winch  78 . In other embodiments, any other suitable winch may be employed. 
     The lifting sub-assembly  22  further includes a cable  82  having a first cable end  84  and a second cable end  86 . The first cable end  84  is coupled to the winch  78 . The winch  78  is configured to extend and retract the cable  82  for raising and lowering the load  92 . The lifting sub-assembly  22  further includes a pulley  80  coupled to the cart  74 . The second cable end  86  of the cable  82  extends through the pulley  80 . The pulley  80  is spaced from the winch  78 . 
     The lifting sub-assembly  22  further includes a cable bar  88  coupled to the second cable end  86 . The lifting sub-assembly  22  further includes at least one joining device  90  removably coupled to the cable bar  88 . In certain embodiments, two of the joining devices  90  are removably coupled to the cable bar  88 . The cable bar  88  includes retaining pins  94  spaced from each other for preventing disengagement of the joining device  90  from the cable bar  88 . The joining device  90  is configured for removable coupling to the load  92 . The joining device  90  includes a latch portion  96  configured for securing the joining device  90  to the cable bar  88 . The latch portion  96  is rotatable away from the cable bar  88  for disengaging the cable bar  88  from the joining device  90 . The joining device  90  includes a retaining pin  98  which is configured to engage the joining device  90  and the latch portion  96  to secure the latch portion  96  to the joining device  90  such that the joining device  90  is secured to the cable bar  88 . The joining device  90  is configured for removable coupling to the load  92 . The joining device  90  includes an extension  100  configured to engage the load  92  for coupling the joining device  90  to the load  92 . 
       FIG. 10  is a perspective view illustrating the cable bar  88 , the joining device  90 , and the load  92  of the lifting sub-assembly  22  of  FIG. 9 . The load  92  defines at least one slot  102  which is configured to be engaged by the extension  100  of the joining device  90 . In  FIG. 10 , the load  92  defines two of the slots  102  with each of the slots  102  spaced from each other. The extension  100  of each of the joining devices  90  engages one of the slots  102  such that two of the joining devices  90  are coupled to the load  92 . The cable bar  88 , which is coupled to the cable  82 , is also coupled to the joining devices  90  such that the load  92  is coupled to the cable bar  88  and thus coupled to the cable  82 . As such, extension or retraction of the cable  82  by the winch  78  will result in movement, such as lifting or lowering, of the load  92 . 
       FIG. 11  is a fragmentary perspective view illustrating the load assembly  18  including a shelf  104  disposed in the aircraft  10 . In certain embodiments, the shelf  104  is disposed in the aft section of the aircraft  10 . The shelf  104  is utilized as a temporary support for supporting the load  92  (e.g., the aft battery) when the aft battery is installed or removed from the aircraft  10 . However, it is to be appreciated that the shelf  104  may be utilized in any section of the aircraft for supporting any type of load. In various embodiments, the shelf  104  can support a load having a weight of no greater than 125 lbs., no greater than 110 lbs., or no greater than 100 lbs. The shelf  104  is disposed inline with the second interior position  16  for lifting the load  92  from the shelf  104  to the lifting sub-assembly  22 , or lowering the load  92  from the lifting sub-assembly  22  to the shelf  104 , when the lifting sub-assembly  22  is in the second interior position  16 . It is to be appreciated that the second interior position  16  may be inline with any interior surface of the aircraft. 
       FIG. 12  is a perspective view illustrating the shelf  104  of  FIG. 11 . The shelf  104  includes two arms  106  opposite each other extending to distal ends. The arms  106  are configured to engage the aircraft  10  for placement of the shelf  104  in the aircraft  10 . Each of the arms  106  gradually increases in height in the direction of the distal ends. This gradual increase in height permits ease of movement of the load  92  from the shelf  104  to the aircraft  10 , or from the aircraft  10  to the shelf  104 . The shelf  104  has a surface  108  extending to the distal ends. The surface  108  of the shelf  104  has a low coefficient of friction for easing movement of the load  92  from the shelf  104  to the aircraft  10 , or from the aircraft  10  to the shelf  104 . In certain embodiments, the surface  108  of the shelf  104  includes a low-friction coating for reducing the coefficient of friction of the surface  108 . In other embodiments, the shelf  104  is formed from a low-friction material for reducing the coefficient of friction of the surface  108 . 
     With continuing reference to  FIGS. 1-12 ,  FIG. 13  is a fragmentary perspective view illustrating an opening  110  in a bottom surface of the aircraft  10  to an exterior of the aircraft  10 . In certain embodiments, the opening  110  is inline with the first interior position  14  of the structural member  12  for lifting the load  92  from the exterior of the aircraft to the lifting sub-assembly  22 , or lowering the load  92  to the exterior of the aircraft from the lifting sub-assembly  22 , when the lifting sub-assembly  22  is in the first interior position  14 . The load assembly  18  further includes a protective layer  112  configured to engage the aircraft  10  adjacent the opening  110  for minimizing damage to the aircraft  10  by the load assembly  18 . Specifically, the protective layer  112  is disposed between the aircraft  10  and the cable  82  when the load  92  is lifted into the aircraft  10  or lowered to the exterior of the aircraft  10  to prevent contact between the aircraft  10  and the cable  82 , or the aircraft  10  and the load  92 . However, it is to be appreciated the that the protective layer  112  may be utilized in any location throughout the aircraft  10  to prevent contact between the aircraft  10  and any component of the load assembly  18 . 
       FIGS. 14A, 14B, 14C, and 14D  are fragmentary perspective views illustrating the method of utilizing the load assembly  18  in the aft section of the aircraft  10 . As illustrated in  FIG. 14A , the method includes the step of coupling the support sub-assembly  20  to the structural member  12  of the aircraft  10 . This step may be further defined as the step of coupling the beam portion  24  and the fixed spacer portion  26  to the structural member  12  of the aircraft  10 . 
     The method also includes the step of coupling the lifting sub-assembly  22  to the support sub-assembly  20  in the aft section of the aircraft  10 . As illustrated in the transition from  FIGS. 14A to 14B , from  14 B to  14 C, and from  14 C to  14 D, this step may include the step of engaging the first beam end  30  of the beam portion  24  of the support sub-assembly  20  with the second cart end  116  of the cart  74 , and may then include the step of engaging the first beam end  30  with the first cart end  114  of the cart  74 . In certain embodiments, the step of coupling the lifting sub-assembly  22  to the support sub-assembly  20  in the aft section of the aircraft  10  may include the step of engaging the first beam end  30  of the beam portion  24  of the support sub-assembly  20  with the gliders  76  of the second cart end  116  of the cart  74 , and may then include the step of engaging the first beam end  30  with the gliders  76  of the first cart end  114  of the cart  74 . 
     Although not illustrated, in the second non-limiting embodiment of the load assembly  18  for utilizing the load assembly  18  in the forward section of the aircraft  10 , the step of coupling the support sub-assembly  20  to the structural member  12  of the aircraft  10  includes the step of coupling the forward extender  62  and the aft extender  64  to the structural member  12  and the step of coupling the support sub-assembly  20  to the forward extender  62  and the aft extender  64 . 
     The method also includes the step of coupling the lifting sub-assembly  22  to the support sub-assembly  20  in the forward section of the aircraft  10 . This step may include the step of engaging the second beam end  32  of the beam portion  24  of the support sub-assembly  20  with the first cart end  114  of the cart  74 , and may then include the step of engaging the second beam end  32  with the second cart end  116  of the cart  74 . In certain embodiments, the step of coupling the lifting sub-assembly  22  to the support sub-assembly  20  in the forward section of the aircraft  10  may include the step of engaging the second beam end  32  of the beam portion  24  of the support sub-assembly  20  with the gliders  76  of the second cart end  116  of the cart  74 , and may then include the step of engaging the second beam end  32  with the gliders  76  of the first cart end  114  of the cart  74 . 
       FIGS. 15A, 15B, and 15C  are perspective views illustrating the step of coupling the load  92  to the lifting sub-assembly  22  either in the aft section or the forward section of the aircraft  10 . As illustrated in the transition from  FIGS. 15A to 15B  and from  15 B to  15 C, this step may include the step of disposing the cable bar  88  on the load  92 , the step of coupling the joining device  90  to the load  92 , and the step of coupling the cable bar  88  to the joining device  90 . 
       FIG. 16A  is a fragmentary perspective view illustrating the step of activating the lifting sub-assembly  22  to lift the load  92  in the aft section of the aircraft  10 . This step may be further defined as the step of activating the lifting sub-assembly  22  to lift the load from the exterior of the aircraft  10 . Although not illustrated, the step of activating the lifting sub-assembly  22  to lift the load  92  may be further defined as the step of activating the lifting sub-assembly  22  to lift the load  92  from the interior surface of the aircraft  10 . 
     The method also includes the step of moving the lifting sub-assembly  22  from the first interior position  14  to the second interior position  16 . In one embodiment, the first interior position  14  is inline with the opening  110  defined by the aircraft  10  and the second interior position  16  is inline with the interior surface of the aircraft  10 . In another embodiment, the first interior position  14  is inline with the interior surface of the aircraft  10  and the second interior position  16  is inline with the opening  110  defined by the aircraft  10 . 
       FIG. 16B  is a fragmentary perspective view illustrating the step of activating the lifting sub-assembly  22  to lower the load  92  in the aft section of the aircraft  10 . This step may be further defined as the step of activating the lifting sub-assembly  22  to lower the load to the interior surface of the aircraft  10 . Although not illustrated, the step of activating the lifting sub-assembly  22  to lower the load  92  may be further defined as activating the lifting sub-assembly  22  to lower the load  92  to the exterior of the aircraft  10 . 
       FIGS. 17A, 17B, and 17C  are fragmentary perspective views illustrating the step of moving the load  92  from the shelf  104  to the interior surface of the aircraft  10 . As illustrated in  17 A, the load  92  is disposed on the shelf  104 . As illustrated in  17 B, the load  92  is moved to one of the arms  106  of the shelf  104 . As illustrated in  17 C, the load  92  is moved from one of the arms  106  of the shelf  104  to the interior surface of the aircraft  10 . 
       FIG. 18A  is a fragmentary perspective view looking toward the forward section of the aircraft  10  illustrating the step of activating the lifting sub-assembly  22  to lift the load  92  in the forward section of the aircraft  10 . This step may be further defined as the step of activating the lifting sub-assembly  22  to lift the load  92  from the exterior of the aircraft  10 . Although not illustrated, the step of activating the lifting sub-assembly  22  to lift the load  92  may be further defined as the step of activating the lifting sub-assembly  22  to lift the load  92  from the interior surface of the aircraft  10 . 
     The method also includes the step of moving the lifting sub-assembly  22  from the first interior position  14  to the second interior position  16 . In one embodiment, the first interior position  14  is inline with the opening  110  defined by the aircraft  10  and the second interior position  16  is inline with the interior surface of the aircraft  10 . In another embodiment, the first interior position  14  is inline with the interior surface of the aircraft  10  and the second interior position  16  is inline with the opening  110  defined by the aircraft  10 . 
       FIG. 18B  is a fragmentary perspective view looking toward the aft section of the aircraft  10  illustrating the step of activating the lifting sub-assembly  22  to lower the load  92  in the forward section of the aircraft  10 . This step may be further defined as the step of activating the lifting sub-assembly  22  to lower the load to the interior surface of the aircraft. Although not illustrated, the step of activating the lifting sub-assembly  22  to lower the load  92  may be further defined as activating the lifting sub-assembly  22  to lower the load  92  to the exterior of the aircraft  10 . 
     While at least one exemplary embodiment has been presented in the foregoing detailed description of the disclosure, it should be appreciated that a vast number of variations exist. It should also be appreciated that the exemplary embodiment or exemplary embodiments are only examples, and are not intended to limit the scope, applicability, or configuration of the invention in any way. Rather, the foregoing detailed description will provide those skilled in the art with a convenient road map for implementing an exemplary embodiment of the invention. It being understood that various changes may be made in the function and arrangement of elements described in an exemplary embodiment without departing from the scope of the disclosure as set forth in the appended claims.