Mark

I have used a Megger on engine loops, but I'm not a fan of using one.

A Systron loop is pressure filled, so a Megger shouldn't hurt it. The Kidde???? I would stay away from a Megger.

With this problem, after we used the decade box for substitution, the loop read 30MΩ (that was just from removing the one terminal lug).

We smacked the white doughnut pretty hard and the 4.5KΩ returned. It didn't fail after the beating.

I use a regular VOM on most engines loops. A LCR Meter can also be used.

A LCR Meter should "always" be used on body and wing overheat loops.
  
     
 

767 with a hard fail on the left engine EEC (Electronic Engine Control).

Engines with a EEC have a mechanical fuel control. FADEC (Full Authority Digital Control) engines have a HMU (Hydromechanical Unit) to control fuel.

Either way, the EEC or FADEC require external inputs to assure proper engine functions.
  
     

With this problem, the EEC's were swapped between engines. The problem didn't follow.

We put a meter to all external inputs and measured the torque coils and feedback wires to the fuel control.

We found the T1.2 temperature sensor reading open. We verified the wires to the sensor plug were good. Resistance readings directly at the probe still had the open.

After a replacement sensor was obtained, we checked resistance. It read 220Ω.
  
     
  
After the replacement and engine run..... all EEC functions checked normal.
  
     

Interesting problem today. The right engine loop 1 was showing as failed on EICAS. The system installed was a Systron-Donner.

We disconnected the pylon plug and checked the total loop resistance 1.5KΩ, this is a good reading.

Moving to the detection card in the E&E, we had the same reading. The problem did not follow a card swap.

We tried something new and dialed in 1.5KΩ into the decade box and hooked it up to the pylon plug..... aircraft side. The system tested normal.

So..... the problem is on the engine, but total resistance is reading good???

We then disconnected one lead from the lower aft loop and used the decade box to simulate the loop (4.5KΩ). The system was failed.
  
     
  
When we did the same with the upper aft, the system checked good.

I don't recall having a loop read good resistance, but cause the system to fail. We got somewhat physical on tapping the white disc connection point with a screw driver. Resistance jumped to 30MΩ and back to the 4.5KΩ. After that..... the system tested normal with the lead connected.

The loop was changed anyway as we must of had a 'bad internal connection point on one of the studs.

After a Auto-Throttle clutch pack replacement in the nose compartment, we had a "Left FCC A/P Disconnect Switch" fault during MCDP (return to service tests).

This doesn't mean the left switch is the bad one because either switch could be the issue. The right and center FCC's can throw the same message.
  
  
     

The FCC's want to see a ground on pin "F15" of the "B" plug during system tests. Unless either yoke disconnect switch is depressed, the ground should always be present.

The signal path goes through the F/O's yoke, then the Capt's yoke in series.
  
     
  
We were open to ground from the Left FCC rack. I put a tone on the wire with the "Fox and Hound".
  
     
  
I had good tone under the F/O's yoke, but it died when making my way over the the Capt's yoke terminal block.
  
     
  
Backtracking to the area above the clutch pack we found this shit.....
  
     
  
One broken wire (ours) and another jewel of a wiring repair right along with it.

Regular butt splices hooked up to bastardized environmental splices on two sets of wires with about 8 inches between each of the splices on each wire. The environmental splices didn't have the sleeve shrunk down and a crimp on one of the barrels done with flat faced Knipex pliers.

We repaired the wires properly but seriously..... WTF??

 

Please reference rotate.aero/forum/test-equipment/224-fuel-quantity-test for fuel quantity basics and test box usage.
Please reference rotate.aero/forum/767-28fuel/765-surge-tank-sensors for one example of using the test box.

There is a cable connection issue when it comes to using different manufacturer Fuel Quantity Test Units.

Some, have reverse polarity BNC connectors.
  
     
  
On this Viavi  box, the LoZ and Comp connectors are males. The HiZ is female.

Most co-ax test cables are male on both ends, which connect to the HiZ BNC connector.

You must have a set of special cables made up (male on one end and female on the other.....
  
     
  
.....or what I call "gender-bender" adapters to use for the LoZ and Comp BNC's.
  
     
  
These are somewhat hard to find. I ordered some from a place called Show Me Cables .
  
 

Please reference rotate.aero/forum/767-28fuel/401-ata-28-21-pressure-fueling for more info on pressure fueling overflow protection.

We had an aircraft that would not accept fuel (open the fueling valves) without pressing the "reset" button at the fueling panel. When this button is used protection provided by the Fuel Level Sensing Card (M586) is bypassed.

Usually, when this fault occurs you have one of the two surge tank probes not feeding a capacitance signal to the card.

There is a extender card for testing the probes.
  
     
  
Co-ax cables are connected to a fuel quantity test box on the Hiz and LoZ "Tank Unit" inputs. (The indicator plugs are used for simulation.)
  
     
  
For a 767, you want to see around 7pF to 8pF. We had one reading correct and one not.
     
  
Switching from capacitance to resistance, showed a HiZ to Shield short on the low reading probe.
  
     
This reading (all meg readings) should be open or the high MegOhm range.

To isolate further we disconnected the probe.
  
     
  
Resistance was still low. We then disconnected the plug at the wing root to isolate the wing harness. After disconnect, the resistance reading showed open.
  
     
  
Our problem was the wing harness. 

It's a tough replacement as it runs into the center tank, through the main tank, and then into the surge tank.
  


 

Please reference rotate.aero/forum/ata24-767/343-ata-24-2...ed-power-feeder-wire for some of our previously encountered problems.

Another power feeder wire short. This time the problem was inside the pressure vessel, as we normally find these on the engine or pylon.

The BPCU (Bus Power Control Unit) faults are always the same, DP Trip (Differential Protection) and GEN/FDR Fault (Generator/Feeder).

System isolation is the first step in troubleshooting. The feeder wires from the engine IDG (Integrated Drive Generator) go to the generator contactor. There are some extra wires connected to the three big feed wires. Three (one for each phase) go to the Generator Control Unit or GCU. Removing the box from the rack isolates those wires. Two extra wires, one for a red "Bus Hot" light and a EICAS voltmeter input also need to be separated from the feeds. Removing the bulb and pulling the breaker will accomplish that.
  
     
     
  
Using the megger from the generator end, we found the blue wire with the short.
  
     
  
No registered meter scale and less than 1 Meg-Ohm resistance. (The meggar picked this up as a hard short, but a regular VOM showed an open circuit.)
  
       
  
We went ahead and removed the blue feeder from the contactor just to make sure nothing else was in the system. The reading was the same.
  
     
  
We shook all over the engine and pylon with the megger on..... no joy. Same thing with some wing leading edge panels removed. (Two hours or more)

When we started shaking the wires in the right side forward lower cargo deck, the meter started jumping.

I wonder why....
  
     
     
     
     
  
Fun Stuff!!!

  
 

Not the same day, but still a couple pretty nice shots.....
  
     
     
 

Servo valve explanation.....