Here is an informative aerobrake post by 'johnwill':
"There is a "maximum design landing weight" for AF airplanes, but it is a misleading criterion. AF fighters commonly are designed for 10 ft/sec landing at "maximum design landing weight", which is normally substantially less than max takeoff weight, whatever the AF decides is appropriate. For example, early F-16s had a max takeoff weight of 33,000 lb (quickly raised to 35,400 lb) and a max design landing weight of 27,500 lb. The misleading part of "maximum design landing weight" is that there is also a requirement for 6 ft/sec landing for all takeoff weights, including MDTOW. Those 10 and 6 ft/sec landing requirements were applied to the F-16, but I don't know the F-35A requirements.
Based on watching hundreds of test flight landings, almost all are around 1 or 2 ft/sec, so heavy landings are, as you say, no worries, well almost.
The biggest problem with heavy landings is not gear strength, but brake energy limits. So with a heavy landing, aero braking is often employed to reduce brake energy requirements."
http://www.f-16.net/index.php?name=PNph ... ing#231685
A4G Skyhawk: www.faaaa.asn.au/spazsinbad-a4g/ & www.youtube.com/channel/UCwqC_s6gcCVvG7NOge3qfAQ/videos?view_as=subscriber