page-116

518

14 CFR Ch. I (1–1–19 Edition)

Pt. 135, App. A

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

instead of

and

NE.

(b)

Takeoff weight limitations.

The max-

imum takeoff weight for each airport ele-
vation ambient temperature and available
takeoff runway length within the range se-
lected by the applicant may not exceed the
weight at which—

(1) The all-engine-operating takeoff dis-

tance 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-en-

gine-inoperative takeoff requirements speci-
fied in section 5(e); and

(3) The airplane complies with the one-en-

gine-inoperative takeoff and en route climb
requirements specified in sections 6 (b) and
(c).

(c)

Landing weight limitations.

The max-

imum landing weight for each airport ele-
vation (standard temperature) and available
landing runway length, within the range se-
lected 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 con-
sumption of fuel and oil en route.

20.

Performance information.

The Airplane

Flight Manual must contain the performance
information determined under the perform-
ance requirements of this appendix. The in-
formation must include the following:

(a) Sufficient information so that the take-

off 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 per-

formance information was obtained, includ-
ing the airspeed at the 50-foot height used to
determine landing distances.

mined 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 guid-
ance material including any relevant limita-
tions or information.

(e) An explanation of significant or un-

usual flight or ground handling characteris-
tics of the airplane.

(f) Airspeeds, as indicated airspeeds, cor-

responding to those determined for takeoff
under section 5(b).

21.

Maximum operating altitudes.

The max-

imum operating altitude to which operation
is allowed, as limited by flight, structural,
powerplant, functional, or equipment char-
acteristics, must be specified in the Airplane
Flight Manual.

22.

Stowage provision for airplane flight man-

ual.

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 re-

starting 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 multi-
plied by a factor accounting for propeller
control system malfunction, including quick
feathering action, simultaneously with 1

level flight loads. In the absence of a ration-
al analysis, a factor of 1.6 must be used.

(b) The limit torque is obtained by multi-

plying the mean torque by a factor of 1.25.

25.

Turbine engine gyroscopic loads.

Each

turbopropeller engine mount and its sup-
porting structure must be designed for the
gyroscopic loads that result, with the en-
gines 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 fol-

lowing:

(1) A yaw velocity of 2.5 radians per second.
(2) A pitch velocity of 1.0 radians per sec-

ond.

(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 re-
sulting from the failure of the critical engine
including the following conditions in com-
bination with a single malfunction of the
propeller drag limiting system, considering
the probable pilot corrective action on the
flight controls:

(1) At speeds between

and

the loads

resulting from power failure because of fuel
flow interruption are considered to be limit
loads.

VerDate Sep<11>2014

08:20 May 17, 2019

Jkt 247048

PO 00000

Frm 00528

Fmt 8010

Sfmt 8002

Y:\SGML\247048.XXX

247048