Documentations sa 365 c2
 

We are four aeronautical engineering students at the Lycée du Val de Lys in ESTAIRES 59940.
As part of our BTS programme, we are required to complete a 70-hour project in the field of airworthiness
on the retractable landing light and its structural assembly. In order to complete this project,
we need more information or potentially to consult documentation on
the DAUPHIN SA 365 C2 type in the structural documentation.

Yours sincerely
https://cimg1.ibsrv.net/gimg/pprune....3f7f303cd.jpeg
https://cimg3.ibsrv.net/gimg/pprune....d5fca825b3.jpg

You guys are having all the fun in the Lycée du Val de Lys, would have loved a project like that when I was in the Lycée!

https://cimg0.ibsrv.net/gimg/pprune....7804678d0e.png

is it the part hanging out that you are consulting about? I would think it is just an accessory probably made by a third party, and attached with 6 screws....
I am not sure what structural factors are involved, hopefully somebody has a legacy document to put you on the right track.

Yes, indeed, we have enough material to work with at our establishment.
However, we already have at least some of the documentation concerning the retractable beacon.
We are particularly interested in the lower panel used to secure the retractable beacon.
Do you happen to have any information that could help us?
You can look at our IPC concerning the parts we are interested in.https://cimg6.ibsrv.net/gimg/pprune....614c5d3914.jpg

I think there is little likelyhood of the information you are looking for being available in the wider aviation community. Airbus product support would be the only likely source and only if they are still supporting the type. They have been trying to get the type certificate cancelled for some time. I would say that the panel as drawn is as manufactured. If a landing light was not installed a blanking plate would have been fitted. In the drawing you can see the reinforced area around the light. This would be to carry the weight of the unit and the flight loads imposed when the light was extended. Pilots often used the lights as forward facing identification lights so the structure should have been stressed to cope with all speeds in the flight envelope. The panel also took some of the load of the side panels which were hinged to it by the pip pins illustrated. Probably classified as secondary structure.

Looking at the photos was a trip back in time. Last time I worked on one was 1999 in Holland. Very serviceable aircraft but short in range. We flew with long range tanks as standard in the UK and Holland. The customers liked them and were very reluctant to upgrade to the 365N, Those auxiliary servos visible always seemed to leak.

What specifically are you interested in with that panel? Material type? manufacture process? Other?

We are interested in the manufacturing process and the job cards for removing and reinstalling it on the helicopter,
as well as its AMM and SRM on the ATA 53 and 33.

The books concerned are the SA365C MET and MRR. Again I would contact Airbus product support. Alternatively try to find someone who operates or has operated the type recently. For manufacturing you need to speak to the factory. I think there will not be much in the MET as installation is straight forward 5 screws at each end and the two support brackets in the middle with reference to disconnecting the landing light and radio aerial(?). Removal will add taking down the side panels first. The MRR may well just refer to standard practices for repair as the panel is a simple sheet metal structure..