All posts by Todd's Time

How in the world does the capacitance fuel qty system work on a Premier?

A. Fuel Probe
There are four capacitance-type fuel probes in each wing tank. The outboard fuel probe is installed aft of spar 4, outboard of WCANT 182.00. The midtank fuel probe is between rib 4 and 5, aft of spar 4. The forward inboard fuel probe is forward of spar 3 at WS 12.00. On Airplanes RB-4 thru RB-74 Not Modified by Kit 390-9200, the collector tank probe is located forward of spar 6 and inboard of WS 12.00. On airplanes RB-2, RB-3, RB-75 and After; and Prior Serials Modified by Kit 390-9200, the collector tank probe is installed aft of spar 3 and inboard of the fuel boost pump.
B. Fuel Quantity Indicator
The fuel quantity indicators (28M1, Left; 28M2, Right) are in the lower center cockpit subpanel. The indicators receive 28 VDC from the LEFT FUEL QTY (28CB7) and RIGHT FUEL QTY (28CB8) circuit breakers. Each indicator receives a capacitance signal from the four fuel probes in each wing tank. The indicator displays the remaining left and right wing tank fuel quantity as an analog and digital display in pounds. Each indicator represents the signal as an analog bar display and a three and a half (3 1/2) digit LED readout.
RH gage failed P/N 84-121-4 S/N 0805-172(failed, reads dashes)

Heffley home videos

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9. June 6 2004.   0 to 5.00 memorial day motor cycles. 5.30 Mom with water hose.  9.00 lucia scooter 10.00 Joe lands in j4.   June 12 13.26 Lucia rides bike.  21.00 luci shoot footage. 23.30 Florida. 2004. 27.00 grandma.  36.00 lucia skate. with Sam and Kinsey. 49.00 twister 107.00 end.

 

 

 

Byt squawks at Portsmouth.


1. Hyd. pressure gage 2 inop. – Number 2 hyd gage dead below the zero peg until it warms up. PN 5502-360-80-10 SN 764, then it started working half way through our troubleshooting. rang wires.

 Number 1 gage will not go to 2100 lbs with the AUX pump,  hangs at 1600 lbs until you tap it. video.  PN5502-360-80-10  SN 765

2. Number 1 engine ignition –  L3KK left ignition switch.  820UN01S1BAOA.  IPC 31-11-30-21 .  SO number 403787. 1 gage only. ref.

3. Printer cockpit jammed – fixed paper jam

4. Look in radome  – visual inspection good

5. Landing LED taxi – provide quote

6. ANTISKID Menelco. – Suspect moisture in nose axle.

7 . Overhead panels loose – resecured

8. Face on entry away light – Reinstalled face.

9. Light check , logo lights – LOGO lights not installed on this AC.

10. reevaluate possibility of repair for overhead panel. –  paper overlay, month long repair removal.

11. change router password 

 

 

 

Why would a Falcon 50 Passenger temp run away from HOT in AUTO mode

Complaint:  Cabin cold in flight in auto mode:

EDIT squawk turned out to be : cabin cold in AUTO and in MANUAL.

How could the heat ducts become clogged in a Falcon 50?

I failed to realise early on that the cabin valve backing away from hot was normal operation.  Also, when crew is max hot, the cabin backs down even lower.  This also seems to be normal operation.

 

Observation: Pass Valve position needle will drive full hot, then immediately back down to half scale or lower. In the air and on the ground with APU.

 

EDIT 20/20 hindsight, this is normal operation. Also, it is exaggerated when the crew valve is toward hot. Who knew?

 

At about :40 seconds the valve runs cold on its own.

Reference:

F50 Pass temp electrical:   f50passtempcontrol

Associated:

With the flood duct open, the problem is reduced.

EDIT: with the flood duct open, the cabin will quickly overheat.

With CABIN and CREW valves selected OFF, the problem goes away.

With a SEPARATE temp sensor plugged into 163H, hanging in free air, THE PROBLEM GOES AWAY.   THIS is the ONLY way we have affected the squawk.

 

Troubleshooting so far:

We  have shorted 162H AMP pin A and B together. This takes the temp select system out of the system and commands full hot.  Squawk remains the same.

Crew Bleed or Pass bleed or both yield the same result.  Squawk remains the same.

AMP to 163H wires rung out carefully. M, H, J.

AMPs swapped cabin and crew.  Squawk remains the same.

162H Temp select controllers swapped for a loaner unit,  Squawk remains the same.

Back-pinned v to assure it had a solid ground during operation.

With amp unplugged, Ohm meter on M, H, and J  Both halves of the sensor read ~89  ohms at max cold, ~124  ohms at max hot.

Unrelated?

pulled 5 temp switches for a unrelated bleed oheat light when wing heat switched off, turned out to be a sticking PRV

Unrelated?

Removed  failed seals at upper and lower turbo cooler Best-O-Bell inlet pipes. Installed 4 each  new seals.

PARTS OFF: P/N 460-150 S/N NA.

PARTS ON: P/N 460-150 REV P  LOT# 0110336483.

Performed leak check.

Quoted text from John Taylor:

  1. Leading Particulars.

Type of Control …………………………………………………………………………………………………….. Pulse modulated

Temperature Selector Range ……………………………………………………………. 60°F to 90°F (15.4°C to 31.9°C)

Input Voltage ……………………………………………………………………………………………………………… 18 to 32 VDC

Maximum Output …………………………………………………………………………………………………. 2 amps at 28 VDC

Ambient Temperature Range ………………………………………………………………-65°F to 165°F (-54°C to 72°C)

Deadband ………………………………………………………………………………………………………………….. 3.0°F (1.7°C)

Transient Voltage Protection …………………………………………………………………………………. + 80 volt, -600 volt

Reverse Voltage Protection ………………………………………………………………………………………………………. Yes

Output Protection …………………………………………………………………………………………………………………….. Yes

Hi-Limit Protection ………………………………………………………………………………………………………. 160°F (70°C)

Cabin Sensor …………………………………. Negative Temperature Coefficient Disc Thermistor ( See Figure 1 )

Temperature Readout Sensor ……………………………….. Wire wound positive temperature coefficient 0.2°/F

Construction …………………………………………………………………………………………………………. Repairable Assy.

Connector Type …………………………………………………………………………………… Mates with MS3120A-14-195

Size

Length (max) ……………………………………………………………………………………… 8.400 inches (213.36 mm)

Width (max) ………………………………………………………………………………………….. 3.900 inches (99.06 mm)

Height (max) …………………………………………………………………………………………. 3.225 inches (81.91 mm)

Weight (approx.) ……………………………………………………………………………………….. 18 ounces (510.3 gm)

Temp Amplifier simplified block diagram:

temp-control

Fairview Airport Runway Association Meeting Minutes

7TS0

 

Here is a zip with the originating documents for FARA.

 

They were part of the now deprecated www.7ts0.com

FARADocs FromFairviewAirportdotcom

 

I found this minutes on the old interwebs, not assured to be approved

040409_found Minutes

Here is a 2011, Source unknown

Here are the scans of the the minutes as filed in the Secretaries Box, “Meetings” folder.  Enjoy.

2013-09-28_fara

2014-09-26_fara

2014-09-27-fara

2015-5-11_FARA

2015-10-24-fara

2016-05-01-fara

2016-10-1_fara

2016 Fall minutes accepted

2017 06 08 FARA_Minutes