Yep. From recollection the F-22A's top speed and range requirements were lowered, as were it's availability and corrosion resistance requirements.Reading through this Flight Global article (Link) which has been discussed here... makes me wonder:
Is it common for the Pentagon or USAF to lower the "performance bar" of aircraft this late? If yes, were the performance bars of the F-22 and F-18E/F lowered, similarly?
The Super Hornet had acceleration, speed, altitude, range and payload requirements all lowered, due to drag and wing drop issues, as well as it's infamous "cantered" wing pylons... OTOH it did what the USN really wanted at a development cost of about $4.8B (IIRC). It's upgrade path has also turned it into a very fine combat aircraft.
Designing an aircraft is a compromise. Sometimes pushing for that X level of capability, simply isn't worth the cost or the tradeoff you may have to make in other areas to achieve it.
The F-22A is a classic example. It hit it's performance requirements in terms of acceleration, supercruise, maneuver performance and so on, but it's range suffered as a result. It hit it's low observability requirements, but it's maintainenance requirements are consequently huge.
It reached it's capability goals, but it cost a fortune to do so and many of the planned capabilities (advanced datalinks, IRST, "cheek" or "flank" AESA radar arrays etc) had to be canned.
If dropping 8 seconds on the acceleration time, means the F-35A can add back in the 30 odd pounds of self-protection equipment removed during SWAT, such as the PAO shut off valves, dry bay fire supression system and so on, well then I think it's a pretty simple choice to be made.
Does an 8 second reduction in the time it takes an F-35A (under "standard" paper conditions) to accelerate from Mach 0.8 to Mach 1.2 provide the 25% survivability boost, that the USAF - DOE&T says the self-protection equipment does?
I don't know, but I suspect not...