AD 94-04-14 (SB 208A) for dissimilar metal corrosion does not apply to any 680S,E, F, Fl, or FLP (nor 500A,B, or U). These planes do not use the stainless spar cap for increased strength. The higher gross weight aircraft (and the 500 U(tility) use one or the other style of beefed up aluminum strap.
AD 94-04-13 (SB 90C) for the lower spar flange radius is every 500 hours. It requires removing some of the aft cabin interior to gain access, so it depends on the plane how much work is needed. The SB says 18 hours
680Fl and FLP need to comply with part II and part III which takes a lot more disassembly. The SB says 75 hours.
Obviously, if cracks are found it is a lot more.
AD 98-08-19 (SB 223) for cracked leading edge attachment bracket. Starting at 6000 hours, and every 1000 hours thereafter. It's pretty easy (like 1 hour) for nonbooted, non-pressurized planes after the initial 6000 hour inspection (which requires cutting access panels in the leading edge). Booted and or pressurized airplanes take a little more work to gain access.
The SB mentions 100 hours of work if repairs are needed.
