Fuel Flow - Garmin GI 275 Maintenance Manual

5.11.4

Fuel Flow

The fuel flow transducer can be mounted using the bracket or clamping hoses connected to the transducer.
If mounting with clamps, the placement must be no further than 6 inches from the clamp to the nearest face
of the transducer.
• The transducer can be oriented with the wires pointing up, or the cap with five bolts pointing up, or
the output port pointing up, or any combination thereof
• The hose connected to the IN port must be straight for a minimum of 4 inches
• The hose connected to the OUT port should be level or slope up. It must not slope down more than
4 inches per foot
Hoses and fittings connected to fuel flow transducer must meet the following:
1. New hoses must have the same internal diameter as the hose being replaced and meet TSO-C53a
Type C or D (fire resistant) specifications.
2. 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.
3. Fitting torque must not exceed 12 ft-lbf or two full turns past finger tight, whichever occurs first.
4. 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.
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.
If the fuel flow transducer bracket must be replaced, the replacement 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.
190-02246-11
Rev. 1
GI 275 Part 23 AML STC Maintenance Manual
Page 5-32