Thank you all
The damaged area cover 5 frame bay and 8 stringer , all deformed parts identified , the conductivity test already done and revealed that 4 frame end 2 stringer must be replaced , for the skin the conductivity test ok but Airbus request a hardness test , whil performing the skin...
hi friends , i m facing to a fire damage on A330 cargo compartement there is some deformation on profiled assy and sheets , with discoloration on two frams , no damage on external skin .
i need help if somme one have experience with this kind of damage , my quation is how can we determin the...
Airbus procedure in SRM when the depth of corrosion exceed 0.25 mm the removal of the fasteners mandatory to rework corrosion , but it s very difficult to remove fasteners adjacent to corroded area on the gear rib wing top skin .
During a A320 C chek we found corrosion around gear rib and rear spar fasteners heads between rib 4 and rib 5 , in SRM airbus request to remove fastener befor reworking corrosion but there is no acces to remove the gear rib corroded fasteners adjacent to rear spar , it's my first experience with...
Tank you friends for your response , I'm familiarized with A320 SRM , first for the identification I refered to SRM 53-43-14 I found that the modification 26655k2205 applied to our aircraft, so the aft cargo compartment with CLS , but for materiel wish floor pnl made of the SRM give only the...
thank you debodine (CLS : cargo loading systeme) please you have any more explanation about ZONE B and ZONE C ,i have to localize my damage in which zone.
please can somone help me i have a quation about reparation of AIRBUS A321 cargo compartment floor panels ,first i didnt understand the diference btween zone B and zone C Bouth of them have a GFRP Panel and alsso the meaning of abreviation CLS ,and the deference btween (bulk cargo & occasional...
