Garmin GI 275 Installation Manual page 174

The fuel flow transducer can be mounted by clamping the hoses connected to the transducer or by using a
bracket. If mounting with clamps, the unit placement must be no further than 6 inches from the clamp to
the nearest face of the transducer.
• The transducer can be installed in the following orientations:
◦ The wires pointing up
◦ The cap with five bolts pointing up
◦ The output port pointing up
◦ Any combination thereof
• The flow must follow the direction marked on the ports
• The hose connected to the IN port should be straight for a minimum of 4 inches
• The length of hose connected to the OUT port should be level or slope up. It must not slope down
more than 4 inches per foot
If mounting the transducer with a bracket, the bracket must be fabricated. The bracket can be fastened at
the top of the engine using the existing engine crankcase fasteners. The amount of available space between
the top of the engine and the engine cowling needs to be considered in the design of the bracket. The
location of the bracket and position of the fuel flow transducer must result in as few bends in the fuel lines
as possible.
The bracket must be fabricated from 300 series austenitic stainless steel (annealed per AMS 5901 or
½ hard per AMS 5517), sheet thickness 19 gauge minimum (0.044 inches), and installed as provisioned by
the aircraft structural repair manual or standard practices manual. Methods, techniques, and practices
defined in Chapter 4, Metal Structure, Welding and Brazing, of AC 43.13-1B Aircraft Inspection and
Repair are acceptable.
Hoses and fittings connected to fuel flow transducer must meet the following:
• The fuel flow transducer must be connected with new hoses and the hoses must not be subject to
movement that could loosen the fittings
• The hoses must have the same internal diameter as the hose being replaced and meet TSO-C53a
Type C or D (fire-resistant) specifications
• Fuel-compatible thread sealant or tape must be used for the NPT threads. To reduce the risk of fuel
system contamination, a minimal amount of sealant should be applied, leaving at least two threads
at the end of the fitting clear of sealant/tape. Before connecting any hoses, thoroughly clean and
flush the transducer and hoses to ensure they are free of any loose material
Fitting torque must not exceed 15 ft-lbf or two full turns past finger-tight, whichever occurs first
•
• The transducer and fuel hoses must be routed as far away from the aircraft exhaust system as
practical. The transducer must be protected with Aeroquip AE102-( ) fire-sleeve if within
6 inches of any exhaust component
• Line fittings, routing, alignment, bonding, and support spacing must be installed as defined in the
aircraft maintenance manual or Section 8-31 of AC 43.13-1B Aircraft Inspection and Repair
WARNING
Ensure the fuel flow transducer installation does not introduce thread sealant or debris into
the fuel system.
CAUTION
Do not blow pressurized air through the flow transducer.
190-02246-10
Rev. 11
GI 275 Part 23 AML STC Installation Manual
Page 4-73