TM 55-1680-358-12&P
(5) Install three hex head bolts (30, Figure 3-2)
and flat washers (31) to secure each ramp center roller
mounting plate (12, Figure 3-11) to the helicopter ramp
floor.
(6) Attach each inboard ramp roller assembly
(13 and 14, Figure 3-2) to forward and aft ramp center
roller mounting bar assemblies (16 and 17). Use two
hex head bolts (36), flat washers (33) and self-locking
nuts (37). Make certain that the flat washers are used
under the component which turns, either the nut or bolt.
e. Ramp Skid Pad. Install ramp skid pad (20,
Figure 3-2) as follows:
(1) Refer to steps 2-9a. and 2-9a.(1) and
Figure 2-13 to gain access to screw locations.
(2) Install ramp skid pad (20, Figure 3-2) as
shown in Figure 2-19, using previously removed
hardware. Seal ramp skid pad periphery with (PR-1440-
Class B) BMS-5-44 Sealant.
2-10. System Installation - Ramp Extension Roller
Assembly. Install ramp extension roller assemblies
(15, Figure 3-2) as follows:
a. Ramp Extension Roller Assemblies. Install ramp
extension roller assemblies (15, Figure 3-2) as follows:
(1) Position a ramp extension roller assembly
(15) on the left ramp extension. Make sure that six
quick-release pins (1, Figure 3-12) engage the holes
drilled in paragraph 2-7 as shown in Figure 2-20.
(2) Install the remaining ramp extension roller
assembly (15, Figure 3-2) on right ramp extension as
described in paragraph 2-10b.(l).
b. Ramp and Ramp Extension Support Assemblies.
Install ramp support assembly (19, Figure 3-2) and ramp
extension support assembly (18) as follows:
(1) Refer to Figures 2-21 and 2-22 and position
ramp support assembly (19, Figure 3-2) so that index
support ramp support weldment (1, Figure 3-15)
engages both ramp support holes in ramp skid pad (20,
Figure 3-2). Adjust support assembly to the proper
height.
(2) Refer to Figures 2-21 and 2-22 and position
a ramp extension support assembly (18, Figure 3-2)
under each ramp extension roller assembly (15) so that
ramp extensions support index support (1, Figure 3-14)
is engaged. Ensure that FWD/AFT marking on support
assembly is oriented parallel with aircraft centerline.
2-30
