title-14-part-29-sec29-1587

678

14 CFR Ch. I (1–1–24 Edition)

§ 29.1587

the fuel system in a configuration used
to show compliance with that section.

(power-off) is established under
§ 29.1505(c), information must be fur-
nished to explain the V

(power-off)

and the procedures for reducing air-
speed to not more than the V

(power-

off) following failure of all engines.

(d) For each rotorcraft showing com-

pliance with § 29.1353 (c)(6)(ii) or
(c)(6)(iii), the operating procedures for
disconnecting the battery from its
charging source must be furnished.

(e) If the unusable fuel supply in any

tank exceeds 5 percent of the tank ca-
pacity, or 1 gallon, whichever is great-
er, information must be furnished
which indicates that when the fuel
quantity indicator reads ‘‘zero’’ in
level flight, any fuel remaining in the
fuel tank cannot be used safely in
flight.

(f) Information on the total quantity

of usable fuel for each fuel tank must
be furnished.

(g) For Category B rotorcraft, the

airspeeds and corresponding rotor
speeds for minimum rate of descent
and best glide angle as prescribed in
§ 29.71 must be provided.

(Secs. 313(a), 601, 603, 604, and 605 of the Fed-
eral Aviation Act of 1958 (49 U.S.C. 1354(a),
1421, 1423, 1424, and 1425); and sec. 6(c), Dept.
of Transportation Act (49 U.S.C. 1655(c)))

[Amdt. 29–2, 32 FR 6914, May 5, 1967, as
amended by Amdt. 29–15, 43 FR 2328, Jan. 16,
1978; Amdt. 29–17, 43 FR 50602, Oct. 30, 1978;
Amdt. 29–24, 49 FR 44440, Nov. 6, 1984]

§ 29.1587

Performance information.

Flight manual performance informa-

tion which exceeds any operating limi-
tation may be shown only to the extent
necessary for presentation clarity or to
determine the effects of approved op-
tional equipment or procedures. When
data beyond operating limits are
shown, the limits must be clearly indi-
cated. The following must be provided:

(a)

Category A. For each category A

rotorcraft, the Rotorcraft Flight Man-
ual must contain a summary of the
performance data, including data nec-
essary for the application of any oper-
ating rule of this chapter, together
with descriptions of the conditions,
such as airspeeds, under which this

data was determined, and must con-
tain—

(1) The indicated airspeeds cor-

responding with those determined for
takeoff, and the procedures to be fol-
lowed if the critical engine fails during
takeoff;

(2) The airspeed calibrations;
(3) The techniques, associated air-

speeds, and rates of descent for auto-
rotative landings;

(4) The rejected takeoff distance de-

termined under § 29.62 and the takeoff
distance determined under § 29.61;

(5) The landing data determined

under § 29.81 and § 29.85;

(6) The steady gradient of climb for

each weight, altitude, and temperature
for which takeoff data are to be sched-
uled, along the takeoff path deter-
mined in the flight conditions required
in § 29.67(a)(1) and (a)(2):

(i) In the flight conditions required in

§ 29.67(a)(1) between the end of the
takeoff distance and the point at which
the rotorcraft is 200 feet above the
takeoff surface (or 200 feet above the
lowest point of the takeoff profile for
elevated heliports);

(ii) In the flight conditions required

in § 29.67(a)(2) between the points at
which the rotorcraft is 200 and 1000 feet
above the takeoff surface (or 200 and
1000 feet above the lowest point of the
takeoff profile for elevated heliports);
and

(7) Out-of-ground effect hover per-

formance determined under § 29.49 and
the maximum weight for each altitude
and temperature condition at which
the rotorcraft can safely hover out-of-
ground effect in winds of not less than
17 knots from all azimuths. These data
must be clearly referenced to the ap-
propriate hover charts.

(b)

Category B. For each category B

rotorcraft, the Rotorcraft Flight Man-
ual must contain—

(1) The takeoff distance and the

climbout speed together with the perti-
nent information defining the flight
path with respect to autorotative land-
ing if an engine fails, including the cal-
culated effects of altitude and tempera-
ture;

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Pt. 29, App. A

(2) The steady rates of climb and in-

ground-effect hovering ceiling, to-
gether with the corresponding air-
speeds and other pertinent informa-
tion, including the calculated effects of
altitude and temperature;

(3) The landing distance, appropriate

airspeed, and type of landing surface,
together with all pertinent information
that might affect this distance, includ-
ing the effects of weight, altitude, and
temperature;

(4) The maximum safe wind for oper-

ation near the ground;

(5) The airspeed calibrations;
(6) The height-velocity envelope ex-

cept for rotorcraft incorporating this
as an operating limitation;

(7) Glide distance as a function of al-

titude when autorotating at the speeds
and conditions for minimum rate of de-
scent and best glide angle, as deter-
mined in § 29.71;

(8) Out-of-ground effect hover per-

formance determined under § 29.49 and
the maximum safe wind demonstrated
under the ambient conditions for data
presented. In addition, the maximum
weight for each altitude and tempera-
ture condition at which the rotorcraft
can safely hover out-of-ground-effect in
winds of not less than 17 knots from all
azimuths. These data must be clearly
referenced to the appropriate hover
charts; and

(9) Any additional performance data

necessary for the application of any op-
erating rule in this chapter.

[Doc. No. 5084, 29 FR 16150, Dec. 3, 1964, as
amended by Amdt. 29–21, 48 FR 4392, Jan. 31,
1983; Amdt. 29–24, 49 FR 44440, Nov. 6, 1984;
Amdt. 29–39, 61 FR 21901, May 10, 1996; Amdt.
29–40, 61 FR 21908, May 10, 1996; Amdt. 29–44,
64 FR 45338, Aug. 19, 1999; Amdt. 29–51, 73 FR
11001, Feb. 29, 2008; Amdt. 29–59, 88 FR 8740,
Feb. 10, 2023]

§ 29.1589

Loading information.

There must be loading instructions

for each possible loading condition be-
tween the maximum and minimum
weights determined under § 29.25 that
can result in a center of gravity beyond
any extreme prescribed in § 29.27, as-
suming any probable occupant weights.

PPENDIX

ART

29—I

NSTRUCTIONS

FOR

ONTINUED

IRWORTHINESS

a29.1

General

(a) This appendix specifies requirements

for the preparation of Instructions for Con-
tinued Airworthiness as required by § 29.1529.

(b) The Instructions for Continued Air-

worthiness for each rotorcraft must include
the Instructions for Continued Airworthiness
for each engine and rotor (hereinafter des-
ignated ‘‘products’’), for each appliance re-
quired by this chapter, and any required in-
formation relating to the interface of those
appliances and products with the rotorcraft.
If Instructions for Continued Airworthiness
are not supplied by the manufacturer of an
appliance or product installed in the rotor-
craft, the Instructions for Continued Air-
worthiness for the rotorcraft must include
the information essential to the continued
airworthiness of the rotorcraft.

a program to show how changes to the In-
structions for Continued Airworthiness made
by the applicant or by the manufacturers of
products and appliances installed in the
rotorcraft will be distributed.

a29.2

Format

(a) The Instructions for Continued Air-

worthiness must be in the form of a manual
or manuals as appropriate for the quantity
of data to be provided.

(b) The format of the manual or manuals

must provide for a practical arrangement.

a29.3

Content

The contents of the manual or manuals

must be prepared in the English language.
The Instructions for Continued Airworthi-
ness must contain the following manuals or
sections, as appropriate, and information:

(a)

Rotorcraft maintenance manual or section.

(1) Introduction information that includes an
explanation of the rotorcraft’s features and
data to the extent necessary for mainte-
nance or preventive maintenance.

(2) A description of the rotorcraft and its

systems and installations including its en-
gines, rotors, and appliances.

(3) Basic control and operation information

describing how the rotorcraft components
and systems are controlled and how they op-
erate, including any special procedures and
limitations that apply.

(4) Servicing information that covers de-

tails regarding servicing points, capacities of
tanks, reservoirs, types of fluids to be used,
pressures applicable to the various systems,
location of access panels for inspection and
servicing, locations of lubrication points, the
lubricants to be used, equipment required for
servicing, tow instructions and limitations,
mooring, jacking, and leveling information.

(b)

Maintenance Instructions. (1) Scheduling

information for each part of the rotorcraft