Pt. 135, App. A

14 CFR Ch. I (1-1-19 Edition)

speed is authorized for flight test or pilot
training;
(2) If an airspeed limitation is based upon
compressibility effects, a statement to this
effect and information as to any symptoms,
the probable behavior of the airplane, and
the recommended recovery procedures; and
(3) The airspeed limits, shown in terms of
VMO/MMO instead of VNO and VNE.
(b) Takeoff weight limitations. The maximum takeoff weight for each airport elevation ambient temperature and available
takeoff runway length within the range selected by the applicant may not exceed the
weight at which - 
(1) The all-engine-operating takeoff distance determined under section 5(b) or the
accelerate-stop distance determined under
section 5(c), whichever is greater, is equal to
the available runway length;
(2) The airplane complies with the one-engine-inoperative takeoff requirements specified in section 5(e); and
(3) The airplane complies with the one-engine-inoperative takeoff and en route climb
requirements specified in sections 6 (b) and
(c).
(c) Landing weight limitations. The maximum landing weight for each airport elevation (standard temperature) and available
landing runway length, within the range selected by the applicant. This weight may not
exceed the weight at which the landing field
length determined under section 7(b) is equal
to the available runway length. In showing
compliance with this operating limitation, it
is acceptable to assume that the landing
weight at the destination will be equal to the
takeoff weight reduced by the normal consumption of fuel and oil en route.
20. Performance information. The Airplane
Flight Manual must contain the performance
information determined under the performance requirements of this appendix. The information must include the following:
(a) Sufficient information so that the takeoff weight limits specified in section 19(b)
can be determined for all temperatures and
altitudes within the operation limitations
selected by the applicant.
(b) The conditions under which the performance information was obtained, including the airspeed at the 50-foot height used to
determine landing distances.
(c) The performance information (determined by extrapolation and computed for the
range of weights between the maximum
landing and takeoff weights) for - 
(1) Climb in the landing configuration; and
(2) Landing distance.
(d) Procedure established under section 4
related to the limitations and information
required by this section in the form of guidance material including any relevant limitations or information.

(e) An explanation of significant or unusual flight or ground handling characteristics of the airplane.
(f) Airspeeds, as indicated airspeeds, corresponding to those determined for takeoff
under section 5(b).
21. Maximum operating altitudes. The maximum operating altitude to which operation
is allowed, as limited by flight, structural,
powerplant, functional, or equipment characteristics, must be specified in the Airplane
Flight Manual.
22. Stowage provision for airplane flight manual. Provision must be made for stowing the
Airplane Flight Manual in a suitable fixed
container which is readily accessible to the
pilot.
23. Operating procedures. Procedures for restarting turbine engines in flight (including
the effects of altitude) must be set forth in
the Airplane Flight Manual.
Airframe Requirements
Flight Loads
24. Engine torque. (a) Each turbopropeller
engine mount and its supporting structure
must be designed for the torque effects of:
(1) The conditions in FAR 23.361(a).
(2) The limit engine torque corresponding
to takeoff power and propeller speed multiplied by a factor accounting for propeller
control system malfunction, including quick
feathering action, simultaneously with 1g
level flight loads. In the absence of a rational analysis, a factor of 1.6 must be used.
(b) The limit torque is obtained by multiplying the mean torque by a factor of 1.25.
25. Turbine engine gyroscopic loads. Each
turbopropeller engine mount and its supporting structure must be designed for the
gyroscopic loads that result, with the engines at maximum continuous r.p.m., under
either - 
(a) The conditions in FARs 23.351 and
23.423; or
(b) All possible combinations of the following:
(1) A yaw velocity of 2.5 radians per second.
(2) A pitch velocity of 1.0 radians per second.
(3) A normal load factor of 2.5.
(4) Maximum continuous thrust.
26. Unsymmetrical loads due to engine failure.
(a) Turbopropeller powered airplanes must
be designed for the unsymmet- rical loads resulting from the failure of the critical engine
including the following conditions in combination with a single malfunction of the
propeller drag limiting system, considering
the probable pilot corrective action on the
flight controls:
(1) At speeds between Vmo and VD, the loads
resulting from power failure because of fuel
flow interruption are considered to be limit
loads.

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