maneuvering load factor FAR 27

[slowrotor]

For the certification of rotorcraft in the USA, FAR 27.337 states: The rotorcraft must be designed for-
(a) A limit maneuvering load factor ranging from a positive limit of 3.5 to a negative limit of -1.0; or
(b) Any positive limit maneuvering load factor not less than 2.0 and any negative limit maneuvering load factor of not less than -0.5 for which-
(1) The probability of being exceeded is shown by analysis and flight tests to be extremely remote; and
(2) The selected values are appropriate to each weight condition between the design maximum and design maximum weights. END

A positive limit of load factor of just 2.0 is very low in my opinion. Are small helicopters such as Hughes 269,Brantly B2b and R22 designed to just a limit load of 2.0 ?

Airplanes are usually 3.7 normal, 4.4 utility and 6.0 acrobatic


I would think a limit load of 2.0 could be exceeded in a steep turn.

Also, the gust load standard for rotorcraft is 30 feet per second, airplane standard is 50 feet per second.
Why lower for rotorcraft?

P.S. I bought Shawn Coyles, The Art and Science of Flying Helicopters (great Book!) and Ray Proutys, Helicopter Performance, Stability and Control.These books should help limit my strange questions to this forum hopefully.