NATOPS1

The wheels will spin after takeoff until they loose rotational energy and stop on their own. There is no "brake" action to stop them.

Nice APN-59 Barrel!! Replacing that freekin thing SUKED!!! Replacing the cannonplug SUKED MORE!!!!

A few questions to narrow the task: What model aircraft? Inop as in: (a) never turns ON stays cold (watch the pressurization system climb/descent gauge) (b) gets HOT then turns off (c) other manifestation?

What ICS system do you have? The following info is for the AIC-14 system... Change the P and CP AMP selected from Norm to Alt 1 or Alt 2 Also inside the ICS and Radio select boxes there is a jumper to "change the function of the box (same box two functions) make sure the jumper it tight (remove clean contacts and reinsert jumper) If there is a problem with the ICS the boxes will change to a sort of "Hot Mic" function connecting the P and CP ICS

From what I remember the difference in location changes the airflow around/through the boundary layer and it is more of a pickup /interpretation difference but if you are so inclined you can go through the performance charts and determine it there is a TAS difference.

Too many to list... obvious difference, 4 tubes in the Rosemount vs only 2 in the non. The systems the tubes attach to are all different. FYI, ONE VERY IMPORTANT aspect is the performance charts are different for the two systems; if you use the wrong chart for calculating your TOLD data you will have incorrect numbers.

Sounds like a bad GCP: internal (PIR) or internal TR... Make sure your GCP is the same manufacture as your generator; ALSO make sure the GCP is fully seated in the rack and might want to "adjust it" with a quick hit/rap/ wack to get all the connections to make good contact. SWAP with one of your Eng Gen CGPs to be sure.

NOT a lot of info tto work with but IF the ground returns are only on one side of the display your ANT gyro stabilization is probably bad

You may need to have FLASH available for these animations to work (I think) GenDisc.exe GenDisc TEST.exe

The "fusible" plug (link) is the part that holds the spring compressed and the hardened plunger retracted. The test circuit is a lower amperage (7.5A if I remember correctly) and the disconnect power is 20 or 25A. IF you hold the test "too long" you an heat up the fusible link and release the disconnect plunger gendiscon.bmp

Read the FARs or ICAO for your situation

You need to be more specific. Which part of the fuel system are you asking about?

Question #1: No idea on GPM @ 3000 rpm between 6 and 12 is all I got on that... Question #2: Just assume that aircraft hydraulic utility system ,when No 1 EDP pressure is 3000 psi and No.2 EDP pump pressure 3100 psi how the pressure act passes thru passage of single pipe after isolation check valves ? The 3000 PSI pump will be at zero flow because the pump compensator (set at 3000) is satisfied with the pressure. The isolation check valve for this pump will be closed due to the 3100PSI being applied to the check valve preventing it from opening. The 3100 PSI output pump (compensator is set incorrectly) will displace fluid to maintain 3100 PSI, it's isolation check valve will be open and the system pressure gauges will read 3100. As hydraulics are used the pressure will drop and the 3000 PSI pump will be allowed to help out but only until the 3100 PSI pump builds its pressure back to 3100, then the 3000 pump will again go to zero flow condition.

ALSO FYI; The flight station mounted bleed air gauge reads 6 PSI lower than actual pressure. Add 6 to the indicated pressure for actual pressure being supplied.

The orange boot is covering the connection to the main bleed air duct. Would need your model AC to get the actual part we are looking at.

I agree it should not actually be able to engage but the fact it will be "disengaged" does not mean it will not try to engage as it spins up nor that it will spin up to max rotation speed "unladen" and disintegrate causing damage to the engine.

Check the fire loop element for stand off clearances from all ducts and foil covers. Make sure all the "clamps" are fully insulated from the fire loop as the element can "slip" through the split in the insulation sleeve. Good luck... APU fire light illuminate with both cargo and flight station AC systems? Have you "motored" an engine with the condition lever in ground stop so it will not start?

The pumps are connected to multiple power sources (and wire routing) so one set of wires accomplishes a simple control input to the pump regardless of power source.

Change your flexible hydraulic line between the reservoir and the Utility Suction Boost Pump(USBP). IF the line collapses to a degree there will be less hyd fluid (gallons per min) available to pump through the USBP out to the EDP. High demand requires hi volume flow and the only place to restrict hyd fluid affecting both USBP and EDP is the flex line between the reservoir and USBP.

Might be a "quick access" panel someone made to get to the ext power/ freq sense relays. Think that is the right panel... SHOULD BE a BIG RED WARNING sticker there toooooo

There are multiple references to touch and go operations with fuel in the external tanks. Check your Normal procedures section for guidance. Some places it says to land "with little, if any, usable fuel in the external tanks" and other places it says "Crossfeed from... external tanks may be done during… touch and go landings" Not really a yes it is OK or a NO it is NOT OK, to do touch and goes with external tank fuel and crossfeed operations but your sink rate is limited to 300 FPM at touchdown any time there is more than 500LBS in the external tank. Less than 500 LBS is considered empty and the tank should not be used for crossfeed as pressure will probably not be maintained as the fuel level is too low to maintain pump pick up with the changing pitch angles. Do you have fuselage tanks installed? If so you cannot have usable fuel in the external tanks with the fuselage tank not full (20,000LBS+)

3 and 4 do not drive the Hyd system used to retract the gear and it looks like only those two engines were started (because they are now feathered) so this is a mystery... unless this is an A model that still has the hyd systems split between the wings.

"This handle can't be fully retracted causing the flaps electrical control inoperative." When you say inoperative, what are the flaps doing? Not moving by hydraulic system I understand but when you used the electrical/hydraulic system was there any indications the valves moved, fluid was ported, motor ran, just the drive input to the flaps was disconnected due to the manual system remaining engaged? Try to disconnect the linkage at the flap drive and shift it manually then you can determine if the drive is damaged or if the binding is in the linkage.

Everyone here who has been denied or is appealing needs this document in their claim.

FYI, post was from 2013...