RFguy

If you need space and payload..... and speed... 700kg J230D. hard to beat in RAaus. 80kg in the back no issue.... 620kg with full fuel (140 ltrs + 2 pax) ... Centre of Lift of wing is over the "BAGS 1" so CG is generally always in range and hard to screw up . and you have the huge back door (that leaks ha ha) and flies better with weight behind you, also. Take a look at other airplanes CG envelopes in various configurations.

Goolagong is not "God's county". Kingaroy is "God's country".

I'd stay with those AN fittings on the ends of the M22 from memory Setrab interface. efisolutions in QLD have a good range, and you can find other misc items from Sparesbox and other car performance shops. Quite common. SOunds like skippy has all push on. Pressure is low (and negative on the oil cooler side ! ) in the rotax system, suits push on.... Marty what connectors are on your oil can ? I found that interface to the AN oil cooler a bit of a pain but findable (M18 from memory IMBW) -glen.

Wednesday, Thursday : Thruster88 and I flew my new Archer down from Charters Towers to Cowra, made it a two day event. Could be done in one but the LONG day would remove the fun. We have never seen any of central queensland, so this was a good chance to look around. Locals at airports very friendly. Overnighted at Cunnamulla. Nice full river running through it. Plenty of greenery around. 'soaring' techniques I learned during training with Rob Glenn in a hot summer years ago now - to see a thermal present by increased VSI , then pull the nose up slow and try and stay it in as long as possible. Required technique when trying to climb from 7500 to 9500 to take a look in the Archer. Turns a rather anemic 400 fpm into 800 fpm. I'll take that- it is the only thing is life truly free. and almost as good the big Jab LOL. I love NDBs. Such a great facility. Much more engaging than GNSS. and Thruster88 gets to practice his morse code.

test the ASI ? sounds like he was trying to bill extra hours. unless your aircraft was (over) due for testing as normally required is it every 2 years for a RAaus ? and no need to test the GPS, is is guaranteed to be accurate by its certification. (again might be a test). There is a CASA instrument that stipulates what needs to be tested after what changes are made, I will have a look at it, others might know.

What was recovery ? move all the drinks trolleys to the front of the aircraft ?

Putting aside CG location, recovery is usually about two things. Elevator authority that situation, throttle position. Certain combinations will be unrecoverable. But I think you know that , and that's not quite the question you are after. Recovery may not be possible if the CG is aft of the COL and the elevator gets locked into an aerodynamic situation where it (continues) to have no authority (IE no ability to pitch the aircraft so to reduce the AoA of the main wing below stall angle) . Take a look at some of the aircraft with specified NORMAL, UTILITY and AEROBATIC category weights and CG limits. Aero cat takes into account the higher likelihood of getting the aircraft into a more difficult to recover situation/configuration. So, its possible but unlikely to get NORMAL aircraft into difficult (recovery) situations, but highly likely with AEROBATIC. That and limits of airframe G force limits (weight). Nev (since you flew them) I was reading about 727s years ago in one of 'Jobs books where the recovery of the T tail in some attitudes was problematic, and this was new to many....

The less the tail has to do the better for efficiency. Bruce do you recall, for those gliders when set at the "design aft-limit" , in response to a impulse pitch input (up or down step), in terms of dynamic pitch stability, were they over damped (return very slowly to original attitude) or underdamped (borderline unstable probably aft CG for that airspeed/loading) IE entered an oscillatory condition like a car spring without a damper ) or somewhere in between ?

It's interesting to examine NORMAL or UTILITY category aft (and fore) CG limits if provided. Nev you are right an inch on a sailplane is (generally) alot less (% MAC) than an inch on a short empanage powered fixedwing. Bruce, is the fastest way down in a Libelle to induce a nose down spin ?

I dont think it stalled at all, looks like a perfect flare and land on the ocean, with enough energy / airspeed to get a GOOD flare (lots of tail authority)

Maybe, except there are many variations on crimp connectors- many crimp lugs require to get pinned from underneath- one side is a hemisphere (sortof) and the other side a square pin push Depends if you are trying to get a swaged joint, etc - many variations. Before substituting a makeshift die, try and get a look at the real tool.

do that. The twin filter Mr Funnel I have will keep up with a 20 litre jerry being poured in at max rate... Ideally, you need to fashion a collar for it to sit on- stops it falling over slightly, I use a I think 50mm long , 6" diameter bit of poly pipe with a antyi-scratch bead of edging on the bottom. . the collar becomes necessary as the things starts to slosh around when the pour rate is high

Low speeds is bad and hard on the gearbox and everything, Rotax specifically recommend minimum time at low RPM. Probably depends of you have fuel that is likely to varnish up, or evap (ethanol etc) in the bowls, or not, to whether you want to starve the bowls dry on shutdown me thinks. Mr Funnel comment- buy the one with dual filters- otherwise it will not keep up with a 20 litre jerry pour.

But not too many of them (rotax) stop. The failures of the ignition modules though was a real FU by Rotax and shows where they are good, and where they are not. Stacking two ignition modules hard on top of eachother in an area of high temperature was just asking for trouble. A 10mm gap between them would have ensured cooling. In my opinion, electronics is an area NOT to trust Rotax due to their demonstrated incompetance. However, they have demonstrated competance (to me) with the hard to get right stuff like pistons, heads, cooling, gearbox. The inlet manifold is a bit of a compromise (mixture variance front and rear at low gas velocities ) but its bearable. The dual carb is fiddly but acceptable.

cant compare unless airspeed /efficiency is in the picture. I went four blade for rotax because of superior takeoff performance- more blades, less blade loading per blade and not as far into 'stall' if you like , IE AoA per blade lower , ---at low airspeeds much less than the screw speed. Exact performance will depend a bit at what drag you end up with and IE what RPM your end up with. Little / no penalty for 4 versus 2 blades with the Eprop at cruise speed. That's the advantage I like. AND Eprop will get you all this data...

CRIMP, for sure. soldering creates a brittle, heat treated joint. Suggest as high strand count as you can get. Now, as for wire : and, may I quote AC43 : There is no need to speculate. AC43.13-1B , https://www.faa.gov/documentlibrary/media/advisory_circular/ac_43.13-1b_w-chg1.pdf CHAPTER 11 - AIRCRAFT ELECTRICAL SYSTEMS Section 6 : Aircraft Electrical Wire Selection. Section 14 : Terminal Repairs. 11-174 General 11-178 Crimp on Terminal Lugs I strongly suggest users modify and maintain their LSA airplane electrics to AC43.13. There is about 20 good pages to read between Section 6 and Section 17. That been said, I'd suggest a high strand count cable with insulation good for fire temps, and appropriate crimp lugs for that cable, and a suitable crimp tool , or fashioned die in a vice to generate the impression.

Well the #6 telltale will likely be recession., that's the hottest spot.... Do check that the rockers slide left right at TDC. exactly how much spare clearance you have depends on WHICH lengthof push rod Jabiru gave you. they vary.... most of the original Gen3 were too long and then went down a couple of mm ! (and didnt tell anyone and the manual has errors) eventually, you'll need to remove the heads , milled down say 0.9mm from the non recessed area so you get a nice flat surface again, and then drop in a 0.9mm shim. like below :

I mean WHICH screws out of the 6 moved ? I cant beleive that is Jabiru's advice as it is bollocks in IMO if that is so. Problem is dynamic version static friction influencing torque. Hence the reason to back them off to they are moving when you are measuring torque. Otherwise resultant tension could be out by perhaps 2:1... as you are overcoming static friction, corrosion etc etc lots of errors.

if you are employed as a contractor, that's the big bucks

were the head screws adjust backed off half a turn CCW , then CW again ? or just from where it was at ? Which head screws exactly ? with hydra lifters. the only way you will really know the 'lash' is to have them bled down. However, another the way that is useful, at TDC, you should be able to wiggle the rockers back and forth left to right on the valve head. No vertical up down (opening) movement will usually be detectable IE NO play---, but you can feel whether there is heaps of pressure or little pressure ('rest pressure') by pulling the rockers each way on the valve heads. (Mark Dunstone is credited with that one) . I used a little thread gunk to stop the cover screws unwinding... I prefer screws than clips. Leakdowns sound good.

Now that's a cool idea Ian. No doubt the airlines have something like that. Years ago one would write a fancy algorithm. Now you might just compute all options (IE in 100' and 3 deg track steps) and present the user with the best three to evaluate. I assume the published GPWT charts could be obtained as a data matrix. -glen

Suction cup seems to work fine in the Jabiru and covers a day or few. As for range measurement : Yeah, my seemingly laborious proceedure to measure Skyecho range - well, you guys know what I do for a living, I have to put my c0ck on the block , and I need to be able to stand behind my numbers... hence the methodology. One man's overkill is another man's freedom from court challenge.

Garfly, writing time related code is easy. we all write for UTC with offsets, or number of nano seconds since 1st of January 1980, and a few other derivatives HOWEVER what is difficult is dealing with changes of time in and out of daylight saving, as skipping time might skip important scheduled events, or the other way, might run them twice.

@O-K - that is real world testing with reduced ambiguities.... What you first described was essentially random point testing. The result will essentially be meaningless. You need alot of testing to get data you could talk about. probably 100x the data , compared with my method which seeks to reduce the uncertainty . You cant get signal strength from the system so you'll need to move the system performance intoa region where you can measure signal strength by means of works OR does not work. That's the reason to get distance. Once you are at distance , say > 13nm, you can fly in a circle around a point on the ground without changing the range more than 10%. By flying circles you can map the directivity of your airplane / skyecho combination. Then by doing some rotation of the fixed device at the 'base' you can assess the degree of directivity by the device without the airplane around it... AFter rotating the fixed device, you might need to go further away or come closer to get on the threshold again.... Well there are other ways, but that's how I'd do it with a pair of Skyechos and nothing else. Now if I were doing it, I'd get the plane to go out into the apron, and set up my test gear , and just read the signal coming back from the airplane as it was rotated 360deg like a compass swing test..... You can do this with a $30 ebay RTL-SDR receiver and a laptop...

experimenting with another (airborne) aircraft will simply multiply the two uncertainties from the two aircraft. You'd be better to park the 2nd aircraft , or set up the SkyEcho on a tripod, with tablet sitting on a seat underneath, and fly the 1st plane (device under test) in some direction (get some altitude to maintain line of site ) and once on station 10 to 15nm, where the pickups are becoming marginal, execute a shallow 15 deg max turn 360 deg and note the pickup variation with test aircraft heading. repeat 3 times to generate trend. Rotate test receiver 90 or 180 deg and do it again.