Volume: 1Date: 2024-01-01Original Date: 2024-01-01Title: Section 25.337 - Limit maneuvering load factors.Context:
Title 14 - Aeronautics and Space. CHAPTER I - FEDERAL AVIATION ADMINISTRATION, DEPARTMENT OF TRANSPORTATION. SUBCHAPTER C - AIRCRAFT. PART 25 - AIRWORTHINESS STANDARDS: TRANSPORT CATEGORY AIRPLANES. Subpart C - Structure. - Flight Maneuver and Gust Conditions.
§ 25.337Limit maneuvering load factors.(a) Except where limited by maximum (static) lift coefficients, the airplane is assumed to be subjected to symmetrical maneuvers resulting in the limit maneuvering load factors prescribed in this section. Pitching velocities appropriate to the corresponding pull-up and steady turn maneuvers must be taken into account.
(b) The positive limit maneuvering load factor
n
for any speed up to
Vn
may not be less than 2.1 + 24,000/ (
W
+ 10,000) except that
n
may not be less than 2.5 and need not be greater than 3.8—where
W
is the design maximum takeoff weight.
(c) The negative limit maneuvering load factor—
Code of Federal Regulations /
Title 14 - Aeronautics and Space /
Vol. 1 / 2024-01-01238
(1) May not be less than −1.0 at speeds up to
VC
; and
(2) Must vary linearly with speed from the value at
VC
to zero at
VD
.
(d) Maneuvering load factors lower than those specified in this section may be used if the airplane has design features that make it impossible to exceed these values in flight.
[Doc. No. 5066, 29 FR 18291, Dec. 24, 1964, as amended by Amdt. 25-23, 35 FR 5672, Apr. 8, 1970]