Code of Federal Regulations - Title 14

331

Federal Aviation Administration, DOT

§ 23.1587

(a) For all airplanes, the following in-

formation must be furnished—

(1) The stalling speeds V

and V

with the landing gear and wing flaps
retracted, determined at maximum
weight under § 23.49, and the effect on
these stalling speeds of angles of bank
up to 60 degrees;

(2) The steady rate and gradient of

climb with all engines operating, deter-
mined under § 23.69(a);

(3) The landing distance, determined

under § 23.75 for each airport altitude
and standard temperature, and the
type of surface for which it is valid;

(4) The effect on landing distances of

operation on other than smooth hard
surfaces, when dry, determined under
§ 23.45(g); and

(5) The effect on landing distances of

runway slope and 50 percent of the
headwind component and 150 percent of
the tailwind component.

(b) In addition to paragraph (a) of

this section, for all normal, utility, and
acrobatic category reciprocating en-
gine-powered airplanes of 6,000 pounds
or less maximum weight, the steady
angle of climb/descent, determined
under § 23.77(a), must be furnished.

(b) of this section, if appropriate, for
normal, utility, and acrobatic category
airplanes, the following information
must be furnished—

(1) The takeoff distance, determined

under § 23.53 and the type of surface for
which it is valid.

(2) The effect on takeoff distance of

operation on other than smooth hard
surfaces, when dry, determined under
§ 23.45(g);

(3) The effect on takeoff distance of

runway slope and 50 percent of the
headwind component and 150 percent of
the tailwind component;

(4) For multiengine reciprocating en-

gine-powered airplanes of more than
6,000 pounds maximum weight and mul-
tiengine turbine powered airplanes, the
one-engine-inoperative takeoff climb/
descent gradient, determined under
§ 23.66;

(5) For multiengine airplanes, the

enroute rate and gradient of climb/de-
scent with one engine inoperative, de-
termined under § 23.69(b); and

(6) For single-engine airplanes, the

glide performance determined under
§ 23.71.

(d) In addition to paragraph (a) of

this section, for normal, utility, and
acrobatic category multiengine jets
weighing over 6,000 pounds, and com-
muter category airplanes, the fol-
lowing information must be fur-
nished—

(1) The accelerate-stop distance de-

termined under § 23.55;

(2) The takeoff distance determined

under § 23.59(a);

(3) At the option of the applicant, the

takeoff run determined under § 23.59(b);

(4) The effect on accelerate-stop dis-

tance, takeoff distance and, if deter-
mined, takeoff run, of operation on
other than smooth hard surfaces, when
dry, determined under § 23.45(g);

(5) The effect on accelerate-stop dis-

tance, takeoff distance, and if deter-
mined, takeoff run, of runway slope
and 50 percent of the headwind compo-
nent and 150 percent of the tailwind
component;

(6) The net takeoff flight path deter-

mined under § 23.61(b);

(7) The enroute gradient of climb/de-

scent with one engine inoperative, de-
termined under § 23.69(b);

(8) The effect, on the net takeoff

flight path and on the enroute gradient
of climb/descent with one engine inop-
erative, of 50 percent of the headwind
component and 150 percent of the tail-
wind component;

(9) Overweight landing performance

information (determined by extrapo-
lation and computed for the range of
weights between the maximum landing
and maximum takeoff weights) as fol-
lows—

(i) The maximum weight for each air-

port altitude and ambient temperature
at which the airplane complies with
the climb requirements of § 23.63(d)(2);
and

(ii) The landing distance determined

under § 23.75 for each airport altitude
and standard temperature.

(10) The relationship between IAS

and CAS determined in accordance
with § 23.1323 (b) and (c).

VerDate Mar<15>2010

10:12 Mar 18, 2014

Jkt 232046

PO 00000

Frm 00341

Fmt 8010

Sfmt 8010

Y:\SGML\232046.XXX

232046

pmangrum on DSK3VPTVN1PROD with CFR