Patent Publication Number: US-6698544-B2

Title: Fall protection lanyard apparatus

Description:
CROSS REFERENCE TO RELATED APPLICATIONS 
     This application is a continuation-in-part of U.S. patent application Ser. No. 09/865,016, filed May 24, 2001. 
    
    
     STATEMENT REGARDING FEDERALLY SPONSORED RESEARCH OR DEVELOPMENT 
     N/A 
     COPYRIGHT NOTICE 
     A portion of the disclosure of this patent document contains material that is subject to copyright protection. The copyright owner has no objection to the facsimile reproduction by anyone of the patent document or patent disclosure as it appears in the Patent and Trademark Office patent file or records, but otherwise reserves all copyrights. 
     BACKGROUND OF THE INVENTION 
     1. Field of the Invention 
     The present invention relates generally to safety devices used in fall protection, and, more particularly, to lanyard apparatus for use in providing fall protection for a load in an elevated environment. 
     2. Description of the Background Art 
     There are a number of basic devices, such as safety harnesses, for use in providing fall protection for loads in elevated environments, such as loads in connection with human external load operations (“HEL”). Safety harnesses, for example, commonly consist of shoulder straps attached to a waist or chest belt. Some harnesses incorporate suspender-style straps with a tether point-of-attachment on the front center of the chest/waist strap. Others comprise a Y-shaped design, where the shoulder straps are connected to a strap extending vertically from the waist belt to form a three-point intersection. These harnesses are typically constructed of nylon webbing, and commonly include padding. The harness is designed to support the load (i.e., body weight) by the torso and shoulders of the user for suspension from a helicopter. Sit harnesses comprise another category of HEL devices. Also known as pelvic harnesses, bosun&#39;s seat, rescue harnesses, or rigger&#39;s harnesses, these devices suspend the user in a seated posture. The basic design of a sit harness includes a waist belt connected to leg loops routed around the top of the thighs. The point of the tether attachment typically extends directly in front of the upper pelvic region. Full-body harnesses (“FBH”) comprise a combination of sit harnesses and chest harnesses. While there are a number of variations of the basic design of the harness, all full-body harnesses include leg loops, shoulder straps, and either a waist belt, a chest belt, or both. 
     One application wherein such safety devices are used involves the use of rotary winged aircraft, such as helicopters, in external load transfer operations. For example, human external load operations typically involve the transportation of a passenger suspended by a cable assembly under a helicopter. For example, helicopters equipped with load suspension points, or hooks, are commonly used to transport loads in a sling configuration wherein the load is suspended beneath the helicopter by a suspension apparatus. In other applications, helicopters carry cargo as well as human loads in various configurations external to the fuselage, such as on the skids or on skid-mounted platforms. For example, load-bearing platforms may be affixed to the helicopter to permit persons to operate external to the crew compartment. In other situations, a person may stand on one of the helicopter landing skids and operate in the external environment. HEL operations are commonly performed in transmission line maintenance and repair procedures in the electrical power industry, in the logging industry to access remote work sites, and for emergency rescue operations. 
     The present inventor has contributed significantly to safety advances in helicopter external load operations, particularly external human load operations. My U.S. Pat. No. 4,673,059 discloses a method and system for placing a load, which may consist of a combination of personnel and equipment, on or in proximity to components of an energized power transmission line. My U.S. Pat. No. 5,417,304 discloses a method for suspending a load from a rotary winged aircraft, such as a helicopter, using an apparatus that incorporates an emergency release capable of being activated by the suspended person. 
     In certain situations, however, it is necessary or desirable to transfer external loads from a hovering helicopter to a structure, such as a power transmission tower or an energized or de-energized power transmission line, ground wire, or other elevated point or structure. Neither the methods disclosed in my &#39;059 and &#39;034 patents, nor the background art, discloses a suitable safety apparatus for accomplishing the transfer of an external load from a hovering helicopter to an elevated structure while maintaining adequate safeguards for both the helicopter as well as the load. 
     While my &#39;304 patent discloses an emergency release for use with a suspended load, the system disclosed therein is a release-on-command type system that requires the suspended person to: (1) realize the existence of an emergency effecting the helicopter; and (2) manually activate the quick release to permit the helicopter to pull away. If the suspended person fails to either realize an emergency situation requiring emergency release, or fails to activate the quick release that system will not adequately protect both the person and the helicopter. Thus, the primary concerns in such external load transfer applications involve maintaining adequate fall protection for the person or load during the transfer procedure without limiting helicopter operations, particularly the ability of the helicopter to execute emergency maneuvers and operations. It is critical to maintain full fall protection for the person or load through the entire transfer process, while at the same not limiting the operation of the helicopter in emergency situations. 
     Currently, there is little standardization and a general lack of safety procedures practiced by those performing HEL operations. While regulations exist regarding the physical and structural characteristics of external load operations, little consideration has been given to the issue of humans as external loads. Federal Aviation Regulations applicable to rotorcraft operations, particularly those referring to human external loads, are found in Title 14 of the Code of Federal Regulations (CFR). The collection of FAA regulations found in 14 CFR is often referred to as the Federal Aviation Regulations (FARs). Within 14 CFR, part 133 pertains directly to rotorcraft external load operations and contains subparts that address applicability, certification rules, operating rules, and related requirements. In addition, part 27 requires that any external load attaching means must include a quick-release system to enable the pilot to release the external load quickly during flight. While the regulations address a number of areas, they provide no specific detail regarding the attachment method, human load transfer methods, or the structure or function of quick-release devices. 
     As a result of the lack of adequate safety methods there have been a number of rotorcraft accidents in connection with HEL operations. During the period from 1973 through 1995, it has been reported that there were 473 external load operations in which the helicopters were involved in either an accident or an incident. Of the 473 accidents listed, a substantial number involved operations using a sling line or sling load. Accordingly, it is recognized that the predominant cause of external load accidents involves problems with the sling line/load. 
     One common, yet inherently risky prior art method of transferring an external human load from a hovering helicopter to a structure, in a non-sling configuration, consists of bringing the helicopter to a hover immediately adjacent to a structure, wherein the helicopter may be stabilized by the placement of one or both skids (or wheels) on the structure for a period of time thereby allowing the person to step from the helicopter to the structure. This method, however, is significantly flawed in that, to avoid tethering the helicopter to the structure and thereby limiting the availability of emergency flight procedures (e.g. emergency pull-away), there exist periods of time during the transfer that the person is without fall protection, and consequently at substantial risk. For example, a person transferring from a helicopter to a tower typically detaches a safety lanyard from a secure point on the helicopter and attaches the safety lanyard to the tower during the transfer process. Thus, there exists a period of time, between detachment and re-attachment, that the person is without fall protection. If, during this time period, the helicopter executes an emergency pull-away maneuver, the person is at substantial risk of falling. 
     Thus, although HEL operations have been practiced, there remains a need a safety lanyard apparatus for use in providing fall protection for loads in an external environment. More particularly there exists a need for an improved safety lanyard for use in external load operations that is adapted to provide total fall protection for the load while preserving emergency operating procedures for the helicopter by incorporating an automatically activating emergency quick release. 
     BRIEF SUMMARY OF THE INVENTION 
     The present invention addresses the shortcomings of the background art by providing a fall protection lanyard apparatus for use in transferring loads in an elevated environment. The fall protection lanyard may be connected to a load and used to transfer the load from an airborne rotorcraft to a structure while providing fall protection and automatic emergency release capabilities to enable the rotorcraft to freely execute emergency maneuvers. A significant aspect of the invention relates to a lanyard apparatus that provides total fall protection for the load throughout the transfer process without restricting or otherwise limiting available emergency flight options/maneuvers by incorporating an emergency release that automatically activates on demand. 
     In a preferred embodiment, the fall protection lanyard apparatus includes first and second load-bearing lanyards, each terminating in a free end incorporating a hook or carabiner. The competing concerns of fall protection (for the load) and on-demand emergency release (for the aircraft) are each enabled by providing a quick release mechanism activated by a predetermined tension force, such as the force that would be experience if the first and second lanyards were simultaneously connected to the helicopter and a rigid structure and the helicopter executed an emergency pull-away thereby placing tension on the lanyard apparatus. 
     Each lanyard is preferably attached to a common point, such as a load bearing steel O-ring, which in turn is attached to a safety harness which secures the load. In one embodiment: the first lanyard incorporates a quick-release mechanism, which, upon activation, results in the separation of the hook end portion thereof; and the second lanyard incorporates a limited slip mechanism, which, upon application of a predetermined force thereon, activates the first lanyard&#39;s quick-release mechanism. In an alternate embodiment, a mechanical fitting, such as a rivet, or breakaway link or member is configured to bear the tension force and is selected to fail upon experiencing a predetermined force (e.g. 100 lbs.) thereby activating the quick release mechanism. The lanyard apparatus disclosed provides total fall protection during the transfer of a load to a structure in any elevated environment while providing an on-demand quick-release in emergency situations. 
     The lanyard apparatus may be used to transfer a load from the hovering aircraft to an adjacent structure by: (1) attaching the free end of the first lanyard to the helicopter; (2) attaching the free end of the second lanyard to the structure; (3) detaching the first lanyard from the helicopter; and (4) depositing the load onto the structure. When transferring from the structure to the helicopter the method is essentially reversed. When transferring loads as described, fall protection is provided since the load is safely tethered to a load bearing structure at all times, e.g. helicopter or structure. In addition, the quick release mechanism may be used to simultaneously provide an emergency release that allows the helicopter to instantly pull away without placing the external load at risk. 
     Accordingly, it is a primary object of the instant invention to provide an improved fall protection apparatus. 
     Another object of the present invention is to provide a fall protection apparatus adapted to provide comprehensive fall protection for a person or thing in an elevated environment. 
     Still another object of the present invention is to provide a safety apparatus that provides fall protection for a human external load engaged in an airborne transfer, before, during, and after transfer to a structure. 
     Yet another object of the present invention is to provide a fall protection system for HEL operations that provides an emergency release for a helicopter tethered to a structure while transferring human and non-human loads to or from the structure. 
     Still another object of the present invention is to provide a fall protection system for HEL operations that automatically releases a tethered helicopter in an emergency pull-away situation while transferring a load to or from the structure, while leaving the load securely tethered to the structure. 
     Another object of the present invention is to provide an apparatus for use in transferring loads from a hovering rotorcraft to a structure while providing total fall protection and incorporating an emergency release that does not require activation by the person being transferred. 
    
    
     In accordance with these and other objects, which will become apparent hereinafter, the instant invention will now be described with particular reference to the accompanying drawings. 
     BRIEF DESCRIPTION OF THE SEVERAL VIEWS OF THE DRAWINGS 
     FIG. 1 depicts a top view of an emergency release lanyard apparatus according to the present invention; 
     FIG. 2 depicts a bottom view thereof; 
     FIG. 3 depicts a side view thereof; 
     FIG. 4 depicts a top view thereof wherein the lanyard end portion is disconnected from the remaining portion of the apparatus illustrating separation in an emergency release situation; 
     FIG. 5A is side detail view of a preferred embodiment emergency release mechanism for the lanyard apparatus in a connected configuration; 
     FIG. 5B is another side detail view thereof in a partially released configuration; 
     FIG. 5C is another side detail view thereof in a fully released configuration; 
     FIG. 5D is a detail view of the connecting mechanism shown in FIG. 5A; 
     FIG. 6A is a partial side view of the lanyard apparatus illustrating activation of the emergency release mechanism by deployment of the limited slip mechanism; 
     FIG. 6B is a partial side view thereof further illustrating activation of the emergency release mechanism; 
     FIG. 7A is an alternate embodiment lanyard apparatus in a connected configuration with a breakaway link; 
     FIG. 7B is view thereof in a disconnected configuration. 
     FIG. 8A is a partial bottom view of an alternate embodiment configuration incorporating a frangible link; 
     FIG. 8B is a view thereof were the frangible link has failed; 
     FIG. 9A is a partial bottom view of an alternate embodiment configuration wherein the frangible link is embodied in a hinge; 
     FIG. 9B is a view thereof where the frangible link has failed; and 
     FIG. 9C is a side detail view of the frangible link. 
    
    
     DETAILED DESCRIPTION OF THE INVENTION 
     With reference now to the drawings, there is illustrated a preferred embodiment of an emergency release lanyard apparatus according to the present invention for use in transferring a load in an elevated environment, for example, such as from a hovering helicopter to an elevated location on a structure. FIGS. 1 through 7B illustrate a fall protection lanyard, generally referenced as  10 . Lanyard apparatus  10  includes connected first and second lanyards, referenced as  12  and  14  respectively. In a preferred embodiment, lanyards  12  and  14  are connected to a common load-bearing ring  16 . Ring  16  further provides a connection point for attachment of lanyard apparatus  10  to a safety harness (not shown) secured to a load via a safety hook  17  or other equivalent mechanical connecting device. By way of example, the safety harness may be a personal safety harness worn by a human load, or a cargo harness attached to a non-human load. 
     Lanyards  12  and  14  may be fabricated from any suitable, flexible load bearing material, such as nylon straps, rope, cable, or equivalent, preferably flexible, load bearing member. Lanyards  12  and  14  each terminate in a free end fitted with a safety hook. As best depicted in FIGS. 1 and 2, safety hooks  18  and  20  are connected at or proximal to the lanyard ends, and are preferably locking type hooks, such as ladder hooks or snap hooks, having a pivoting gate, referenced as  18 A and  20 A, with a double-action locking feature. The double-action locking mechanism is a safety feature that requires two separate and distinct manual acts/movements to open the gate and undo the hook thereby preventing the undesired or unintentional attachment/detachment of the hook. Hooks  18  and  20  are used to selectively attach the lanyard and load to points on a helicopter or structure during the transfer process as more fully disclosed herein. It should be noted, however, that the present invention contemplates that any suitable alternate means for connecting, including carabiners, locking carabiners, or clamps may be substituted for hooks  18  and  20 . 
     With reference now to FIGS. 1 through 4, attention is drawn to a quick release assembly, generally referenced as  30 . More particularly, lanyard  12  incorporates a quick release mechanism  30  that is adapted for activation by a predetermined threshold force applied to the lanyard apparatus. Upon activation of the quick release mechanism the end portion of lanyard  12 , generally referenced as segment  12 A, is released from the remaining portion of the lanyard apparatus, and particularly released from lanyard segment  12 , which remaining portion is generally referenced as segment  12 B. Quick release mechanism  30  includes a releasable connection joining lanyard segments  12 A and  12 B. As best depicted in FIGS. 5A,  5 B, and  5 C, quick release mechanism  30  preferably includes an interlocked series of rings, referenced as  32 A,  32 B and  32 C, secured in an interlocked load-bearing configuration, joining lanyard segments  12 A and  12 B. The interlocked rings are secured in a load-bearing configuration by a loop formed by parachute cord  34  having one end thereof attached to one side of lanyard segment  12 A, a mid-portion disposed through ring  32 C and metal grommet  36 , best seen in FIG. 2, in lanyard segment  12 A. As best seen in FIG. 5A, loop  34  is secured by a pin  38  removably inserted therethrough such that loop  34  secures rings  32 A-C in a securely interlocked configuration capable of withstanding substantial loads. As best depicted in FIGS. 5A-5C and  6 A and  6 B, retracted removal of pin  38  from loop  34  enables disconnection of lanyard segment  12 A from segment  12 B. More particularly, pin  38  is connected to a first end of a cable  40 , which is preferably slidably received within a conduit  42  terminating in an eyelet  48 , secured to lanyard segment  12 B. Cable  40  includes a second end  44  that is connected to lanyard segment  14 , and particularly end segment  14 A. Movement of cable  40  causes the cable to retract relative to conduit  42  and loop  34  thereby displacing pin  38  from loop  34  and allowing separation of lanyard segment  12 A from segment  12 B by disengagement of rings  32 A-C. 
     In the embodiment depicted in FIGS. 1-4 and  6 A and  6 B, lanyard  14  includes an end portion  14 A that is connected to the remaining portion of lanyard  14 , referenced as  14 B, via a limited slip/shock absorbing mechanism, generally referenced as  50 . Limited slip mechanism  50  allows for limited extension of lanyard  14  upon application of a predetermined force (e.g. 500 lbs.). In a preferred embodiment, the limited slip mechanism comprises a shock-absorbing lanyard, such as is available from Descent Control, Inc. of Fort Smith Ariz. and/or Miller Fall Protection Products, Inc. of Franklin, Pa. The present invention, however, contemplates use of any suitable limited slip mechanism and/or mechanism that provides for the lanyard extension in response to a predetermined threshold force. Upon application of a sufficient force, such as the force that would be encountered if the rotorcraft attempts to pull away in an emergency situation when tethered to the structure (e.g. hook  18  attached to helicopter and hook  20  attached to structure), the limited slip mechanism would activate thereby allowing the length of lanyard  14  to extend. In a preferred embodiment, a force in excess of 500 lbs. is required to activate the limited slip mechanism whereby an additional length of lanyard is deployed, however, lesser threshold forces may be desirable in other applications. As illustrated in FIGS. 5A-5C, extension of lanyard  14  causes activation of the quick release mechanism on lanyard  12  as described hereinabove by retraction of pin  38  into cable  42  thereby releasing looped cord  34 . Once released, the tension on the lanyards causes looped cord  34  to pull through eyelet  48  and ring  32 C thereby activating the quick release by allowing separation of rings  32  from the interlinked configuration. 
     In the alternate embodiment depicted in FIGS. 7A and 7B, the limited slip mechanism may comprise a breakaway link  60  in combination with a third lanyard segment  14 C joining lanyard segments  14 A and  14 B. In this embodiment, the breakaway link  60  joins segments  14 A and  14 B in close proximity by linked connection with additional rings  62  and  64  attached to the respective end portions of lanyard segments  14 A and  14 B. In addition, lanyard segment  14 C has opposing ends connected to ring  62  and  64  respectively. Breakaway link  60  is selected such that application of a predetermined threshold force thereto results in separation of the link and extension of lanyard  14  by the length of segment  14 C. It should be noted, that any other suitable mechanism that allows for limited extension of lanyard  14  in response to the application of a force of a predetermined threshold value is considered within the scope of the present invention. 
     As previously noted, the second cable end  44  is connected to lanyard segment  14 A. Accordingly, when a predetermined opposing force is applied to hooks  18  and  20 , the limited slip mechanism  50  (or alternatively breakaway link  60 ) activates thereby allowing lanyard  14  to extend. Extension of lanyard  14  causes cable  40  to slide within conduit  42  thereby removing pin  38  from loop  34 . Once free, loop  34  no longer functions to maintain the connection between lanyard segments  12 A and  12 B thereby allowing the separation of lanyard section  12 A from the remaining portions of the device  10 . It should also be noted that the means for activating release  30 , e.g. limited slip mechanism  50  or breakaway link  60 , or an alternate means for activating release  30 , may in an alternate embodiment, be incorporated on lanyard segment  12 , and particularly on segment  12 B, rather than on lanyard segment  14 . 
     FIGS. 8A and 8B depict yet another embodiment wherein locking carabiners, referenced as  21 , are used in lieu of hooks. A locking carabiner includes an additional mechanism that makes it harder for the gate to open accidentally. Typically the additional mechanism is a sheath or sleeve, referenced as  21 A, that covers the gate and the outer C-shaped portion of the carabiner. The sheath either screws into place, or uses a spring to hold it in place. To open the gate, the sleeve must be moved from a first position to a second position wherein the gate may be opened. 
     In the embodiment depicted in FIGS. 8A and 8B, the quick release mechanism  30  again comprises the interlinked ring configuration wherein rings  32 A,  32 B, and  32 C maintained in a load-bearing interlocked configuration by loop  34  secured by pin  38  as disclosed hereinabove. As seen in FIG. 8A, a sleeve  39  is attached to lanyard segment  12 A to receive the end of pin  38  to prevent unintentional snagging. In this embodiment, however, lanyard segment  12 B includes a portion having hook and loop fastening material, comprising a hook patch  70  and a loop patch  72 , affixed thereto. The hook and loop fastening material allows for the folded connection of lanyard  12 B as depicted in FIG. 8A in a shortened/retracted configuration. Lanyard  12 B is maintained in the folded configuration by a cable  74  secured at one end thereof, referenced as  74 A, to a portion of lanyard  12 B by a load bearing rivet and plate assembly, referenced as  76 , and secured at the opposing end thereof, referenced as  74 B by a break-away rivet  78  secured by a rigid plate  79  forming a frangible link. In this embodiment, lanyard segment  12 B is maintained in the shortened configuration by cable  74 . The quick release is automatically triggered when a predetermined threshold force applied to lanyard  12  is reached and break-away rivet  78  fails thereby releasing cable end  74 B whereby the tension causes lanyard  12 B to lengthen pulling apart hook patch  70  from loop patch  72 , as best seen in FIG. 8B, resulting in a lengthening of lanyard segment  12 B. The lengthening of lanyard segment  12 B causes cable  40  to retract pin  38  from loop  34  thereby activating the quick release of rings  32 A- 32 C resulting in the detachable release of lanyard segment  12 A as described hereinabove. 
     In yet another alternate embodiment depicted in FIGS. 9A-9C, lanyard segment  12 B is maintained in the shortened configuration by a hinged plate assembly, generally referenced as  80 , which forms the frangible link. Hinged plate assembly  80  includes a first hinge leaf  82  pivotally connected to a second hinge leaf  84  by a pivot pin  86 . First hinge leaf  82  is securely connected to lanyard  12  by a strong connection, such as by riveting with one or more rivets  89 . Second hinge leaf  84  is connected to a plate  88 , which in turn is connected to lanyard segment  12 A by a strong riveted connection  89  as best seen in FIG. 9C. A rivet  90  connects hinge leaf  84  to plate  88 . Rivet  90  is specifically selected to fail when a predetermined threshold force is applied to lanyard  12 , and particularly to hinge assembly  80 . Upon the failure of rivet  90 , hinge leaf  84  is released thereby allowing the lengthening of lanyard segment  12 B as depicted in FIG.  9 B. The lengthening of lanyard segment  12 B causes cable  40  to retract pin  38  from loop  34  thereby activating the quick release of rings  32 A- 32 C resulting in the detachable release of lanyard segment  12 A as described hereinabove. 
     The emergency release lanyard apparatus disclosed herein may be used to safely transfer a load in an elevated environment. For example, loads may be transferred from a first elevated platform, such as an airborne rotorcraft, to an adjacent elevated platform or structure while providing fall protection for the load and emergency release capabilities. Use of the fall protection lanyard  10  in an elevated environment requires secured attachment of the apparatus to the load and/or to a safety harness attached to the load, and safe transfer is accomplished by: (1) attaching the free end of lanyard  12  to the first elevated platform by attachment of hook  18 ; (2) releasing any auxiliary safety restraints; (3) attaching the free end of lanyard  14  to the second elevated platform by attachment of hook  20 ; (4) detaching lanyard  12  from the first elevated platform; and (5) depositing the load onto the second elevated platform. When transferring from the second elevated platform (e.g. tower) to the first elevated platform (e.g. helicopter) the method is essentially reversed. 
     The competing concerns of fall protection (for the load) and on-demand emergency release (for the aircraft) in HEL operations are each enabled by the emergency release lanyard  10 . The lanyard apparatus provides total fall protection for the load throughout the transfer process without restricting or otherwise limiting available emergency flight options/maneuvers by incorporating an emergency release that automatically activates on demand. A significant aspect of the present invention in the HEL application involves maintaining complete fall protection for the load before, during, and after the transfer process without impairing the availability of emergency flight maneuvers for the helicopter as is the case with prior art methods. It should be noted that, with use of the fall protection lanyard disclosed herein, the load is protected from an accidental fall during all phases of the transfer. Specifically, fall protection may be initially provided by an FAA safety restraint (e.g. seat belt or equivalent cargo restraint). During the next step in the process wherein the first lanyard  12  is attached to the aircraft, fall protection is provided by secured attachment of the lanyard segment  12  to a load bearing point on the helicopter; after which the FAA restraint may be removed. During the next step in the process, wherein the second lanyard segment  14  is connected to the adjacent structure, fall protection is provided by the second lanyard segment. It should be noted, that during this phase of the transfer, e.g. when the first lanyard segment is attached to the helicopter and the second lanyard segment is attached to the structure, the helicopter is effectively tethered to the structure, and the load is tethered to both the helicopter and the structure. If an actual or perceived emergency dictates that the helicopter pilot execute an emergency pull-away maneuver, the lanyard apparatus is placed in tension. When the predetermined force is reached, the limited slip mechanism  50  (or one of the alternate embodiments, e.g. break-away link  60 ) activates thereby deploying an additional length of lanyard, which change in length activates the quick-release mechanism of lanyard segment  12  thereby releasing hook  18  and allowing the helicopter to depart while lanyard  14  functions to secure the load to the structure. In the absence of an emergency, hook  18  is detached from the helicopter and the load is secured to the structure by lanyard  14 . It should be noted that the limited slip mechanism ( 50  or  60 ), or an alternate means for activating release  30 , may in an alternate embodiment, be incorporated on lanyard segment  12 , and particularly on segment  12 B, rather than on lanyard segment  14 . 
     Furthermore, the present invention may be used in a variety of applications that require the safe transfer of a load from one elevated point to another while providing fall protection. 
     The instant invention has been shown and described herein in what is considered to be the most practical and preferred embodiment. It is recognized, however, that departures may be made therefrom within the scope of the invention and that obvious structural and/or functional modifications will occur to a person skilled in the art.