TY - GEN
T1 - A36 wing temporary repair substantiation
AU - Gruskeiwicz, D.
AU - Stepura, S.
AU - Berkowitz, O.
AU - Ioffe, O.
AU - Skorohod, A.
AU - Llie, F. A.
AU - Semmesh, N. N.Y.
AU - Dukhovny, I.
AU - Glam, B.
AU - Enchiu, K.
AU - Socher, A.
AU - Gabay, U.
AU - Peretz, D.
PY - 2011/1/1
Y1 - 2011/1/1
N2 - The IAF (Israeli Air Force) maintains light transport aircraft which are purchased as COTS (Commercial off the Shelf), which sometimes leads to lack of necessary engineering data. Last year severe corrosion was detected on the entire IAF BONANZA A36 fleet in the wing front spar hinges. According to Hawker-BeechCraf manuals, no repairs are allowed at this location. This paper outlines a procedure for designing and substantiating a temporary repair in a lack of engineering data. The process was based on a few known parameters and included principles from reverse engineering methodology. In the beginning of the process, minimal required geometrical database was obtained through on plane measurements. This information was used in order to derive the aerodynamic loads and find the critical cases for the wing. At the same time, a quick structural hybrid repair design was performed based on classical strength theory. In addition, a complete FE wing model was constructed and calibrated to ground test results. In the end, the temporary repair was certified and implemented on the aircraft. Towards the end of this process the manufacturer released available engineering data which confirmed some of IAF loads estimation and took an active role in improving the repair design.
AB - The IAF (Israeli Air Force) maintains light transport aircraft which are purchased as COTS (Commercial off the Shelf), which sometimes leads to lack of necessary engineering data. Last year severe corrosion was detected on the entire IAF BONANZA A36 fleet in the wing front spar hinges. According to Hawker-BeechCraf manuals, no repairs are allowed at this location. This paper outlines a procedure for designing and substantiating a temporary repair in a lack of engineering data. The process was based on a few known parameters and included principles from reverse engineering methodology. In the beginning of the process, minimal required geometrical database was obtained through on plane measurements. This information was used in order to derive the aerodynamic loads and find the critical cases for the wing. At the same time, a quick structural hybrid repair design was performed based on classical strength theory. In addition, a complete FE wing model was constructed and calibrated to ground test results. In the end, the temporary repair was certified and implemented on the aircraft. Towards the end of this process the manufacturer released available engineering data which confirmed some of IAF loads estimation and took an active role in improving the repair design.
UR - https://www.scopus.com/pages/publications/84904500278
M3 - Conference contribution
AN - SCOPUS:84904500278
SN - 9781617380839
T3 - 50th Israel Annual Conference on Aerospace Sciences 2010
SP - 339
EP - 354
BT - 50th Israel Annual Conference on Aerospace Sciences 2010
PB - Technion – Israel Institute of Technology
T2 - 50th Israel Annual Conference on Aerospace Sciences 2010
Y2 - 17 February 2010 through 18 February 2010
ER -