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 . as used herein , the word “ exemplary ” means “ serving as an example , instance , or illustration .” thus , any embodiment described herein as “ exemplary ” is not necessarily to be construed as preferred or advantageous over other embodiments . all of the embodiments described herein are exemplary embodiments provided to enable persons skilled in the art to make or use the invention and not to limit the scope of the invention which is defined by the claims . furthermore , there is no intention to be bound by any expressed or implied theory presented in the preceding technical field , background , brief summary , or the following detailed description . fig1 is a simplified cross sectional side view of a gas turbine engine 100 and a conventional agb 40 mounted thereon at the periphery of the air collector 45 . a typical gas turbine engine includes an air intake bellmouth 25 , a compressor 5 , a combustion section 10 , an exhaust turbine 15 , an exhaust plenum 20 and a conventional agb 40 . the compressor 5 , the exhaust turbine 15 and the agb 40 are all coaxially driven by the drive shaft 30 , which is shown only in part in the interest of brevity and clarity . with the exception of the agb 40 , the entire engine is enclosed in an engine casing 50 . the engine casing 50 and the agb 40 must all fit with the confines of an aerodynamic nacelle or within an engine bay . a nacelle is a cover housing that is separate from the aircraft fuselage that holds engines , fuel , or equipment . conventionally , accessories 42 that are driven by the accessory gearbox are arranged in a direction that is coaxial with the drive shaft 30 and are dispersed arcuately along an angular segment of the air collector 45 section of the engine casing 50 ( see , fig1 a ). this arrangement permits the accessories 42 to fit between a wall of an engine bay and the engine casing 50 . thus , in conventional architectures the agb 40 must also be arcuate . fig1 b is a simplified typical gearing architecture of a conventional agb 40 . the agb 40 may include , inter alia , gearing for a starter 110 , an inlet particle accelerator fan 115 , a compound idler gear 120 , lubrication oil pump 125 , an air oil separator 130 , a generator shaft 135 and a fuel pump 140 . the agb 40 is driven by the drive shaft 30 via a relatively long tower shaft 35 ( see fig1 ) and its associated bevel gears . referring again to fig1 , the accessories 42 driven by the agb 40 must be positioned around the circumference of the engine casing 50 to locations on the air collector 45 that are radially the closest to the drive shaft of the gas turbine engine 100 in order to maximize the space available between the nacelle and the engine casing 50 . as can be seen in fig1 , it is shown that the agb 40 must be simultaneously positioned distantly from the drive shaft 30 to allow the accessories 42 that are mounted on the forward or aft side of the agb 40 to clear the air collector 45 portion of the engine casing 50 . thus , the tower shaft 35 must be long enough to extend from the drive shaft 30 to the gearing ( see , fig1 a ) of the agb 40 . because the accessories 42 are arrayed around the circumference of the engine casing 50 , the agb 40 is necessarily laid out in the narrow arcuate configuration that wraps around the engine casing at a distance required to clear the radial profile of the engine casing 50 . the resulting arcuate arrangement of the agb 40 makes oil management more difficult because the oil is susceptible to gear churn as it travels along inside the agb 40 to the various scavenger ports ( not shown ) towards either distal end of the agb 40 . thus , the arcuate arrangement requires more oil scavenging points to collect the lubricating oil and return it to the lubricating oil pump . fig2 is a simplified cross sectional side view of the gas turbine engine 100 and an exemplary transverse agb 40 ′ mounted thereon according to embodiments . the gas turbine engine 100 includes the air intake bellmouth 25 , the compressor 5 , the combustion section 10 , the exhaust turbine 15 , the exhaust plenum 20 and a transverse agb 40 ′. the compressor 5 , the combustion section 10 , the exhaust turbine 15 and the transverse agb 40 ′ are all driven by the drive shaft 30 , which is shown in part in the interest of brevity and clarity . a salient feature of the embodiments of fig2 is the rotational axes 41 ′ of the transverse agb 40 ′ are perpendicular to the drive shaft 30 . thus , the rotational axes 41 ′ of all of the accessories ( not shown ) driven by the transverse agb 40 ′ are also perpendicular to the drive shaft 30 . although the rotational axes 41 ′ of the transverse agb 40 ′ are disclosed as being perpendicular , it will be appreciated that the rotational axes 41 ′ need not be precisely perpendicular . the rotational axes 41 ′ of the transverse agb 40 ′ may deviate from true perpendicularity as may be required by the overarching design of the gas turbine engine 100 . another salient feature of the embodiments of fig2 is that the mounting for the transverse agb 40 ′ may be moved aft from the air collector 45 towards the combustion section 10 to take advantage of the narrower radius of the engine casing in the vicinity of a narrowing ( commonly referred to as the waist ) 51 of the engine casing 50 that is located in the vicinity of the high pressure stages 7 of the compressor 5 . thus , the accessories ( not shown ) may be aggregated together more compactly in the transverse agb 40 ′ to fit into the space available at the waist 51 . in the case of the conventional agb 40 ( see , fig1 ), the length of the various accessories attached thereto prevented any space savings because the physical size of the accessories clashed either with the air collector 45 or the engine casing 50 in the vicinity of the combustion section 10 . an additional advantage that may be realized from the use of a transverse agb 40 ′ is that the tower shaft 35 ′ may be reduced in length thereby eliminating weight and reducing torsion strain that would otherwise occur in a longer tower shaft ( such as tower shaft 35 of fig1 ). the tower shaft 35 ′ has a first end 202 and a second end 203 . the first end 202 is connected to the gearing 42 ′ of the transverse agb 40 ′ via a translational gear 43 and the second end 203 is connected to the drive shaft 30 via a bevel gear via the opening 36 ′ in the housing 20 ′. further , oil scavenging is improved . by reducing the width and increasing the depth of the transverse agb 40 ′, most of the agb lubrication oil returns to the engine casing via the tower shaft opening 36 ′ in the transverse agb 40 ′. thus , fewer scavenging ports 44 are required in the agb housing 20 ′ to collect and return the agb lubrication oil . whatever number of scavenging ports 44 that may be required can be located at the lowest points in the transverse agb 40 ′. this may be desirable to scavenge oil when the gas turbine engine 100 is in a non - level flight attitude such that the tower shaft opening 36 ′ is not the lowest point in the transverse agb 40 ′. fig2 illustrates one scavenging port 44 at a potential low point in the transverse agb 40 ′. such illustration is merely exemplary and should not be construed as limiting the number of scavenging ports disclosed herein to the single scavenging port 44 . fig2 a is an rendition of an exemplary installation on an hpw3000 gas turbine engine produced by from advanced turbine engine company ( atec ) with a exemplary transverse mounted agb 40 ′ according to embodiments . the gas turbine engine 100 includes the housing 50 , the air intake bellmouth 25 , the compressor 5 , the combustion section 10 , the exhaust turbine 15 , the exhaust plenum 20 ( see , fig2 ) and the transverse agb 40 ′. the accessories 42 ′ driven by the transverse agb may include a starter 110 , an inlet particle accelerator fan 115 , one or more pumps ( 120 , 125 ), an air oil separator 130 , an air turbine starter 135 and a fuel control unit 140 . fig2 b is a disembodied view of an exemplary gearing arrangement for a transverse agb 40 ′. the transversal agb 40 ′ is driven by the tower shaft 35 ′ ( via a bevel gear ) and drives a number of gears ( 110 ′- 140 ′) for the accessories 42 ′. exemplary accessories may include the air oil separator 130 ′, fuel pump 120 ′, idler gear 25 ′, starter 110 ′, generator shaft 135 ′ and a lubrication oil pump 140 ′ ( see , also fig2 a ). fig3 is a side by side comparison of plan views of an exemplary gas turbine engine with a conventional agb 40 and with a transverse agb 40 ′. as may be seen , the width requirement of the transverse agb 40 ′ is 4 . 2 in . as compared to the conventional agb 40 that has a width requirement of 19 . 2 in ., which is a 79 % reduction . the length requirement in this particular embodiment increases slightly from 10 . 4 inches to 14 . 1 inches . because the agb 40 represents the widest component of the engine ; it is the controlling factor in regard to space constraints within the engine bay or nacelle . while at least one exemplary embodiment has been presented in the foregoing detailed description of the invention , 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 invention as set forth in the appended claims .