Proposed modification to G-TRYK – BMAA HB191 – Kiss 400 582(1)
Description
To add a Brauniger Alpha MFD EFIS and associated fuel flow meter to the above aircraft as part of the build process, instead of traditional analogue instrumentation.
The purpose of this document is to show compliance with TIL027 Issue 1 – Instrumentation and Avionics. Please note that the Alpha MFD is fitted as standard to the Pegasus CT.
Also note that a separate compass will be mounted on the front strut, as is usual in flex-wing Microlight aircraft.
Brauniger Alpha MFD
This is an electronic instrument with a very large Liquid Crystal Display, with dedicated areas that shows an analogue ASI (Calibrated from 24 to 110 m.p.h.) and a VSI calibrated in ft/min x 100. It also shows digital read outs for EGT 1 and 2, Engine Revs, Water Temperature and Altitude.
It has an intercom interface which gives audible warning of any preset limits being exceed. These limits can be set for altitude, airspeed (Vne and stall), EGTs and temperature sender cable breaks, low fuel, low voltage and water temp, and will be interfaced with the aircraft intercom system. In all cases, when a limit is exceed the associated display is activated and flashed in addition to the audible warning.
Note: A self-adhesive red-line will be affixed to the face of the ASI showing Vne and stall speed for the aircraft.
This picture is to show the instrument only. It will be fitted into the existing instrument panel, NOT in a pod as shown below.
Dimensions:
Front of instrument: 220 x 145 mm
Cockpit cut-out: 194 x 137 mm
Drillings for mount screws: 208 x 87 mm
Depth: 125 mm
Total Weight: 700 grams
Compliance
Section 3.2 – Instrument Panel essential requirements
3.2.1 Mechanical Strength
The front panel of the instrument entirely fills the available space, but the required cut-out will leave sufficient strength in the panel to avoid flexing. If any flexing is evident once the panel is fitted, I will bond wooden strakes to the back on the panel around the borders of the cut-out using an epoxy resin, and fit the panel mounting bolts through the wood. The installation will be tested for flexing using a load of 6.3 Kg – i.e. 9 times the instrument weight.
3.2.2 Instrument positioning
All instruments will be directly in front of the pilot. In addition, as the instrument utilises an LCD display, there can be no parallax error.
3.2.3 Multi-engine switches
Not applicable
3.2.4 Switches must be within reach of a small adult
strapped in the pilot seat
Checked and OK
3.2.5 Weight and CoG check
Given that the whole instrument weighs so little, there is unlikely to be an effect. However, the usual aircraft weighing will occur as part of the final inspection.
3.2.6 Security
The instrument will be fitted using M8 cylinder head bolts, with Nylock nuts on the rear.
3.2.7 Multi-cored cables
The cable loom will be the one supplied with the kit. An additional loom has been run comprising a flexible plastic corrugated cable conduit, containing the wiring for two EGT probes, a water temperature probe and the fuel-flow meter. Brauniger supplies all these, and all use multi-cored cable.
3.2.8 Cable security
The looms are fastened to the keel using cable-ties, under sufficient tension to very slightly deform the conduit. Any excess lengths will be trimmed to leave just sufficient to withdraw the instrument from the console. In the case of the thermocouple wiring, spare length will cable-tied into coils, and secured to the back of the instrument. In fact, all cables will be secured to the instrument using an integrated strain-relief point.
3.2.9 Primary Load Path
I can confirm the instrument will NOT be mounted as part of the primary load path of the aircraft.
Section 3.3 – Instrument Panel advisable requirements
3.3.1 Fastening
As previously stated, M8 Bolts backed with Nylock nuts will be used to secure the instrument
3.3.2 Cable lengths
As previously stated, sufficient cable length to allow the panel to be withdrawn will be allowed.
Section 4.2 Pitot- static system essential requirements
The Pitot will be as defined in the Kiss build instructions – i.e. it is unchanged.
The Static pipe is open to the inside of the pod, out of the airstream.
Section 5.2 Compass essential requirements
A traditional compass will be fitted to the front-strut using brass screws through a clamp.
Section 6.2 Electrical condition gauges essential requirements
The Alpha MFD includes a volt-meter. An in-line fuse for the instrument power supply will be fitted. Note that this aircraft includes the optional Rotax E gearbox with electric start, and thus has a regulator/rectifier and a battery. The power for the instrument will be taken from the factory supplied loom.
Note that in the event of primary power failing for any reason, the Alpha MFD has a backup battery
Section 7 – Switches essential requirements
All switches remain standard – i.e. as defined in the Kiss Build manual, taking into account changes mandated for Section S compliance as defined in the supplementary UK Mods Build manual, and utilising switch gear supplied as part of the kit.
Section 8 Fuel Flow Gauges – essential requirements
The fuel system supplied with the kit is to be modified to include a Brauniger supplied Fuel Flow meter between the fuel filter and the Mikuni fuel pump. The meter is a one piece nylon body, with 8mm inlet and outlet pipes, and is designed to allow fuel flow in the event of the sensor wheel becoming jammed. The inlet and outlet pipes are 3 cm long, and have a flange at the end for added security.
The existing fuel system between the tap, fuel filter and the pump, utilises 6mm i.d. fuel pipe. Given that the meter has 8mm inlet and outlets, two adapters have been manufactured from Aluminium as follows:
The Kiss kit included spare 6mm and 8mm fuel line, and it is this that will be used. Fuel lines will be fastened to the adapters and the fuel flow meter using fuel pipe clamps.
Diagram showing proposed fuel system between tap and fuel pump:
8.2.1 Security
As defined above. A leak test will be conducted once the installation is complete.
8.2.2 Fuel Flow Test
Fuel flow bleed off will be tested. However, as stated earlier, the fuel flow meter is of the type where fuel flow is not restricted should the internal sensor wheel become jammed. As this is being fitted as part of the build, and restrictions to the fuel flow should be readily apparent during the ground run-in procedure on the engine.
8.2.3 Fuel pressure measurement lines
Not applicable
8.2.4 Lines carrying fuel to sensors or gauges
Not applicable.
Section 9.2.2 Fuel Level Sight Gauge essential requirements
Please note that the Kiss has a ‘sight window’ in the pod, such that the fuel tank contents are visible to the pilot in flight. The tank is to be placarded with a calibrated fuel remaining scale, supplied with the kit.
Section 10.2 Engine RPM Gauge – essential requirements
10.2.1 Calibration
The Alpha MFD Tachometer is digital, and will run off the existing loom supplied as part of the kit. The Alpha MFD contains factory preset ‘multipliers’ for engine type, one of which exactly matches the Rotax 582 99 to be fitted to the Kiss. Nevertheless, an optical tachometer will be used to verify the accuracy of the gauge.
10.2.2 Circuit protection
The tacho circuit is an integral part of the Alpha MFD, and as such is protected by the fuse in the main Alpha MFD power line.
Please note that the Alpha MFD has been designed such that it cannot be switched off if there is Indicated Airspeed in excess of 32 m.p.h. (i.e. below stall speed) or a non-zero tachometer reading.
11.2 Engine Temperature Gauge essential requirement
As previously stated, the thermocouple cabling will not be shortened. Excess length will be coiled and secured at the back of the instrument.
12.2 Slip ball essential requirements
Not applicable
13 Venturi Airspeed Indicator
As stated previously, the AlphaMFD will use the Pitot supplied as part of the kit, which will be mounted in the position called for in the build manual.
14.2 GPS Essential requirements
A Garmin GPS III Pilot will be fitted to the top of the pod behind the windscreen. This will interfere with neither the view of the compass nor the instruments. A spring balance load test of the installation will be carried out, and the power supply will be separately fused. A backup lanyard will be fitted to the front strut.