art 9A General Equipment
Positioned on the instrument panel are all the engine-monitoring, Flight monitoring and navigation instruments.
The instrument panel is secured with hex-head screws to the instrument panel frame, which is bolted to the forward part of the windscreen assembly.
On the instrument panel frame are positioned the monitoring equipment for the armament installation and the pressure gauge for the MW installation (see Part7B).
On the bottom edge of the instrument panel a hinged auxiliary panel is attached, which can be fixed in the upward position, and that latches to the cover of the MK 108 in the lowered position. On this auxiliary panel the ZSK 244A is fitted (see Part 8A).
Especially sensitive instruments: AFN-2 indicator, vertical speed indicator, artificial horizon, airspeed indicator, altimeter, and the repeater compass are mounted separately on an instrument Flight panel, which is attached to the main panel by vibration dampening mounts.
B. Installation and Removal
Before removing the instrument panel. Remove the auxiliary panel; to do this first release the latch and then attachments to the instrument panel.
Release all cable connections on the rear of the auxiliary panel and remove the auxiliary panel with the ZSK 244A from the cockpit.
In a similar manner, remove the instrument Flight panel from the instrument panel.
After that remove all electrical leads, electrical plugs, piping and Flexible cables from the rear of the instruments and remove the instrument panel with the attached instruments from the instrument panel frame after removing the four mounting screws.
When disconnecting electrical leads note that all leads are provided with ID tags.
Seal pipe and tubing ends as well as connections on the instruments as protection against contamination.
Installation of the instrument panel follows likewise in reverse sequence. The instruments are installed before the installation of the instrument panel.
Attachment of the instruments to the instrument panel is almost exclusively by slotted head screws, that are screwed into captive nuts (fixed to the rear face of the instrument panel). When tightening the mounting screws watch that the screws are tightened uniformly so that the instrument glass is not cracked.
The limit markings are indicated on the instruments by adjustment marks or by red marks.
Fig.1: Equipment Layout in the Cockpit
II. Engine Monitoring Instruments
Fig 2.Engine monitoring instruments
The following instruments are installed as engine monitoring instruments (see Fig. 2):
1 Manifold Pressure Gauge (Fig. 2/1)
2 Tachometer (Fig. 2/2).
3 Propeller Pitch Indicator (Fig. 2/3)
4 Dual Pressure Gauge for Oil & Fuel (Fig. 2/4).
5 Thermocouple for Oil (Fig. 2/5)
6 Thermocouple for Coolant (Fig. 2/6)
7 Temperature Gauge for Oil (Fig. 2/7)
8 Temperature Gauge for Coolant (Fig. 2/8)
9 Fuel Level Transmitter for Fuel (Fig. 2/9)
10 Fuel Contents Gauge (Fig. 2/10)
11 Low Fuel Warning Light (Fig. 2/11)
12 Pressure Gauge for MW Installation (Fig. 2/12)
For the above listed instruments see also Part 6, in which the powerplant equipment is also covered.
For operation, removal and installation, inspection and servicing see the corresponding D, (Lujt) T.
1. Manifold Pressure Gauge
The manifold pressure gauge with a measuring range of 0.6 to 1.8 atms. is installed in the lower right of the instrument panel. The pressure line is attached to the supercharger exhaust tube and passes through the fuselage forward bulkhead.
To measure engine RPMs a mechanical tachometer with a measuring range of 500 to 3500 RPM is mounted on the right of the instrument panel. Operation is through a two piece flexible shaft, which along with the tachometer drive is attached to the rear of the engine.
3. Propeller Pitch Indicator
The propeller pitch indicator is positioned on the right of the instrument panel nest to the tachometer. The pitch indicator is connected by a flexible cable and angular drive to a dual-purpose adjusting unit mounted under the front of the engine.
4. Dual Pressure Gauge
For fuel and oil pressure measurement, a dual pressure gauge is installed, which is positioned on the right of the instrument panel and is provided with an indicator for fuel and oil pressure. Pressure is tapped from the fuel transfer pump and from the oil filter respectively. On the pressure line connector at the engine a safety check valve is built into the fuel pressure line.
5. Thermocouple for Oil and Coolant Temperature
The thermocouple for oil temperature is inserted in the elbow of the oil llow line and the thermocouple for coolant temperature is inserted in the vapor separator on the right side of the engine.
6. Temperature Gauge for Oil and Coolant
The electrical oil temperature gauge and the coolant temperature gauge are positioned on the upper right of the instrument panel.
The oil temperature gauge shows the inlet temperature and the coolant temperature gauge the outlet temperature.
7. Fuel Level Transmitter
The fuel level transmitter is fitted to the cover on the top of the main fuel tank. The fuel level transmitter is fitted with a contact for low fuel warning, it operates the electrical fuel contents gauge and switches on the low fuel warning light.
8. Fuel Contents Gauge
The fuel contents gauge is positioned on the lower right of the instrument panel. An accurate indication is given only in flight attitude.
9. Low Fuel Warning Light
The low fuel warning light is positioned on the lower right of the instrument panel. The light indicates when the fuel level in the fuel tank is sufficient for only about 10 minutes of flight.
10. Pressure Gauge for MW Installation
The pressure gauge for the MW (Methanol-Water) installation is positioned on the upper right of the instrument panel frame and is connected to the feed line for MW mixture by a pressure line (see also Part 7B).