BMS 9-8 Allowables 1

[whalesA3D]

I have an Airbus A-320 nose landing gear door. The outer skin is cracked in the monolithic area at the upper aft end of the door, aft of the aft hinge. I am looking to substitute BMS 9-8 dry carbon fabric and EA 9396 resin for the SRM callout of G-806 fabric and Ciba Redux 501 resin. I would be willing to sell our director of quality's soul to the devil for a copy of the BMS 9-8 allowables so I can compare baseline values. We don't want to buy a roll of the G-806 to do one repair. I have the Airbus allowables. Willing to do some horse trading.

 

[der8110]

Why not just design a repair based on required loads? You already have properties for the materials you have, and with either material, the strength is probably far in excess of what is needed. Aft of aft hinge indicates it's a free edge, probably impact or abuse damage rather than operational loads.

You need a more compelling offer. Hell is already overpopulated with quality people.

 

[MechanicalChef]

Your material is BMS 9-8 spec, but who is the manufacturer? Do you have any contacts with material vendors? Hexcel for example sells material created to Boeing 9-8 spec (

http://www.hexcel.com/Products/Fabrics/Carbon/),

so perhaps you could try asking them for more details of what they call out for allowables.

 

[SWComposites]

1) Boeing allowables are not published for bare fiber or fabric, they are always for fiber/resin combination. Also, the fiber suppliers will not have allowables for a resin system that they do not produce.
2) I don't know of a way to legally get a copy of the Boeing allowables for BMS 9-8/BMS 8-301.
3) There are some allowables published in Mil-Handbook-17, Volume 2, section 4.2.27 for T300/EA9396. T300 is qualified to BMS 9-8. EA9396 is qualified to BMS 8-301.

Hope this helps,

Steve

 

[whalesA3D]

Thanks for the information gentlemen, especially Steve. The T300/EA9396 is what I needed. Just what the Dr. ordered.