178
14 CFR Ch. I (1–1–14 Edition)
Pt. 23, SFAR No. 23
of
V
1
, considering the approved ranges of al-
titude and weight. The ground run calibra-
tion will be determined assuming an engine
failure at the mimimum value of
V
1
.
(c) The airspeed error of the installation
excluding the instrument calibration error,
must not exceed 3 percent or 5 knots which-
ever is greater, throughout the speed range
from
V
MO
to 1.3
S
1
with flaps retracted and
from 1.3
VS
O
to
V
FE
with flaps in the landing
position.
(d) Information showing the relationship
between IAS and CAS must be shown in the
Airplane Flight Manual.
14.
Static air vent system. The static air vent
system must meet the requirements of FAR
23.1325. The altimeter system calibration
must be determined and shown in the Air-
plane Flight Manual.
O
PERATING
L
IMITATIONS AND
I
NFORMATION
15.
Maximum operating limit speed V
MO
/
M
MO.
Instead of establishing operating limitations
based on
V
ME
and
V
NO,
the applicant must
establish a maximum operating limit speed
V
MO
/
M
MO
in accordance with the following:
(a) The maximum operating limit speed
must not exceed the design cruising speed
Vc
and must be sufficiently below
V
D
/
M
D
or
V
DF
/
M
DF
to make it highly improbable that
the latter speeds will be inadvertently ex-
ceeded in flight.
(b) The speed
Vmo must not exceed 0.8 V
D
/
M
D
or 0.8
V
DF
/
M
DF
unless flight demonstra-
tions involving upsets as specified by the Ad-
ministrator indicates a lower speed margin
will not result in speeds exceeding
V
D
/
M
D
or
V
DF.
Atmospheric variations, horizontal
gusts, and equipment errors, and airframe
production variations will be taken into ac-
count.
16.
Minimum flight crew. In addition to
meeting the requirements of FAR 23.1523, the
applicant must establish the minimum num-
ber and type of qualified flight crew per-
sonnel sufficient for safe operation of the
airplane considering—
(a) Each kind of operation for which the
applicant desires approval;
(b) The workload on each crewmember con-
sidering the following:
(1) Flight path control.
(2) Collision avoidance.
(3) Navigation.
(4) Communications.
(5) Operation and monitoring of all essen-
tial aircraft systems.
(6) Command decisions; and
(c) The accessibility and ease of operation
of necessary controls by the appropriate
crewmember during all normal and emer-
gency operations when at his flight station.
17.
Airspeed indicator. The airspeed indi-
cator must meet the requirements of FAR
23.1545 except that, the airspeed notations
and markings in terms of
V
NO
and
V
NE
must be replaced by the
V
MO
/
M
MO
notations.
The airspeed indicator markings must be
easily read and understood by the pilot. A
placard adjacent to the airspeed indicator is
an acceptable means of showing compliance
with the requirements of FAR 23.1545(c).
A
IRPLANE
F
LIGHT
M
ANUAL
18.
General. The Airplane Flight Manual
must be prepared in accordance with the re-
quirements of FARs 23.1583 and 23.1587, and
in addition the operating limitations and
performance information set forth in sec-
tions 19 and 20 must be included.
19.
Operating limitations. The Airplane
Flight Manual must include the following
limitations—
(a)
Airspeed limitations. (1) The maximum
operating limit speed
V
MO
/
M
MO
and a state-
ment that this speed limit may not be delib-
erately exceeded in any regime of flight
(climb, cruise, or descent) unless a higher
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
V
MO
/
M
MO
instead of
V
NO
and
V
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. This weight may not
exceed the weight at which:
(1) The all-engine operating takeoff dis-
tance determined in accordance with section
5(d) or the accelerate-stop distance deter-
mined in accordance with section 5(c), which
ever is greater, is equal to the available run-
way 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 en route climb require-
ments specified in section 6(b), assuming
that a standard temperature lapse rate ex-
ists from the airport elevation to the alti-
tude of 5,000 feet, except that the weight may
not exceed that corresponding to a tempera-
ture of 41
°
F at 5,000 feet.
20.
Performance information. The Airplane
Flight Manual must contain the performance
information determined in accordance with
the provisions of the performance require-
ments of this regulation. The information
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.
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