Honeywell International Inc. 9PGTPA-100A Manual De Usuario
Page 2032
1 Dec 2003
34-45-4
7
MAINTENANCE MANUAL
CAS-100 COLLISION AVOIDANCE SYSTEM
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• De-burr all holes on aircraft and clean mounting surface in accordance with
application of BMS 5-95 sealant. Clean and brush alodine on all exposed
surfaces on aircraft skin.
surfaces on aircraft skin.
• Apply a faying surface seal of BMS 5-95 to the faying surfaces of skin and
adapter. Apply BMS 5-95 to fasteners and install wet. Complete the riveting
operation and install nut plates per installation drawing. Remove excess sealant
from edges, exposed surfaces, and connector holes to expose sheet metal
adjacent to the connector clearance holes to allow inspection for cracks and
corrosion.
operation and install nut plates per installation drawing. Remove excess sealant
from edges, exposed surfaces, and connector holes to expose sheet metal
adjacent to the connector clearance holes to allow inspection for cracks and
corrosion.
(c)
Installation Procedure B
This installation procedure provides for shims to be added between adapter plate
and aircraft skin. The shims are used to fill edge gaps created by a mismatch in
curvature between the adapter plate and the aircraft skin.
and aircraft skin. The shims are used to fill edge gaps created by a mismatch in
curvature between the adapter plate and the aircraft skin.
• Fabricate the edge gap shims of 2024-T3 Alclad per drawing within T ± .010 inch
thickness and identify as L, R.
• Fabricate 0.125 inch stiffener plate per drawing dimensions. Attach stiffener
plate to adapter with eight 3/32 flush rivets per stiffener drawing dimensions.
Transfer stiffener holes to adapter plate. Drill and countersink back side of
adapter plate so rivets will mount flush with adapter plate.
Transfer stiffener holes to adapter plate. Drill and countersink back side of
adapter plate so rivets will mount flush with adapter plate.
• Attach adapter, stiffener plate and shims to skin, drill and cleco at centerline and
edge. If corrosion or damage is detected on the mounting surface, mask off area
adjacent to adapter and strip paint from sheetmetal. Treat corrosion and/or
damage in accordance with approved practices regarding pressurized
structures.
adjacent to adapter and strip paint from sheetmetal. Treat corrosion and/or
damage in accordance with approved practices regarding pressurized
structures.
• Prepare the mounting surface and adjacent area of aircraft skin to the adapter
plate with aluminum duct tape (see Figure 2005 for the adapter and moldable
shim assembled on the airframe), re-drill holes identified in Figure 2010 and
apply MS122 release material to duct tape surface. Prepare adapter plate
surface and shims by cleaning with acetone followed by application of BR127.
shim assembled on the airframe), re-drill holes identified in Figure 2010 and
apply MS122 release material to duct tape surface. Prepare adapter plate
surface and shims by cleaning with acetone followed by application of BR127.
NOTE: Caution should be taken not to get BR127 on antenna mounting surface
of adapter plate. Apply sufficient quantity of DMS4-828, moldable shim
material to the adapter plate and shims to fill the measured gap. If a
compound gap exists, apply additional DMS4-828 to close the gap. An
approximate material application is illustrated in the installation drawing.
material to the adapter plate and shims to fill the measured gap. If a
compound gap exists, apply additional DMS4-828 to close the gap. An
approximate material application is illustrated in the installation drawing.