Code of Federal Regulations - Title 14

828

14 CFR Ch. I (1–1–14 Edition)

Pt. 29, App. B

servicing, tow instructions and limitations,
mooring, jacking, and leveling information.

(b)

Maintenance Instructions. (1) Scheduling

information for each part of the rotorcraft
and its engines, auxiliary power units, ro-
tors, accessories, instruments, and equip-
ment that provides the recommended periods
at which they should be cleaned, inspected,
adjusted, tested, and lubricated, and the de-
gree of inspection, the applicable wear toler-
ances, and work recommended at these peri-
ods. However, the applicant may refer to an
accessory, instrument, or equipment manu-
facturer as the source of this information if
the applicant shows that the item has an ex-
ceptionally high degree of complexity requir-
ing specialized maintenance techniques, test
equipment, or expertise. The recommended
overhaul periods and necessary cross ref-
erences to the Airworthiness Limitations
section of the manual must also be included.
In addition, the applicant must include an
inspection program that includes the fre-
quency and extent of the inspections nec-
essary to provide for the continued air-
worthiness of the rotorcraft.

(2) Troubleshooting information describing

probable malfunctions, how to recognize
those malfunctions, and the remedial action
for those malfunctions.

(3) Information describing the order and

method of removing and replacing products
and parts with any necessary precautions to
be taken.

(4) Other general procedural instructions

including procedures for system testing dur-
ing ground running, symmetry checks,
weighing and determining the center of grav-
ity, lifting and shoring, and storage limita-
tions.

and information needed to gain access for in-
spections when access plates are not pro-
vided.

(d) Details for the application of special in-

spection techniques including radiographic
and ultrasonic testing where such processes
are specified.

(e) Information needed to apply protective

treatments to the structure after inspection.

(f) All data relative to structural fasteners

such as identification, discard recommenda-
tions, and torque values.

(g) A list of special tools needed.

a29.4

Airworthiness Limitations Section

The Instructions for Continued Airworthi-

ness must contain a section titled Airworthi-
ness Limitations that is segregated and
clearly distinguishable from the rest of the
document. This section must set forth each
mandatory replacement time, structural in-
spection interval, and related structural in-
spection procedure required for type certifi-
cation. If the Instructions for Continued Air-
worthiness consist of multiple documents,
the section required by this paragraph must

be included in the principal manual. This
section must contain a legible statement in
a prominent location that reads: ‘‘The Air-
worthiness Limitations section is FAA ap-
proved and specifies maintenance required
under §§ 43.16 and 91.403 of the Federal Avia-
tion Regulations unless an alternative pro-
gram has been FAA approved.’’

[Amdt. 29–20, 45 FR 60178, Sept. 11, 1980, as
amended by Amdt. 29–27, 54 FR 34330, Aug. 18,
1989; Amdt. 29–54, 76 FR 74664, Dec. 1, 2011]

PPENDIX

ART

29—A

IRWORTHI

NESS

RITERIA FOR

ELICOPTER

STRUMENT

LIGHT

General. A transport category helicopter

may not be type certificated for operation
under the instrument flight rules (IFR) of
this chapter unless it meets the design and
installation requirements contained in this
appendix.

II.

Definitions. (a) V

means instrument

climb speed, utilized instead of V

for com-

pliance with the climb requirements for in-
strument flight.

(b) V

NEI

means instrument flight never ex-

ceed speed, utilized instead of V

for com-

pliance with maximum limit speed require-
ments for instrument flight.

MINI

means instrument flight min-

imum speed, utilized in complying with min-
imum limit speed requirements for instru-
ment flight.

III.

Trim. It must be possible to trim the

cyclic, collective, and directional control
forces to zero at all approved IFR airspeeds,
power settings, and configurations appro-
priate to the type.

IV.

Static longitudinal stability. (a) General.

The helicopter must possess positive static
longitudinal control force stability at crit-
ical combinations of weight and center of
gravity at the conditions specified in para-
graphs IV (b) through (f) of this appendix.
The stick force must vary with speed so that
any substantial speed change results in a
stick force clearly perceptible to the pilot.
The airspeed must return to within 10 per-
cent of the trim speed when the control force
is slowly released for each trim condition
specified in paragraphs IV (b) through (f) of
this appendix.

(b)

Climb. Stability must be shown in climb

thoughout the speed range 20 knots either
side of trim with—

(1) The helicopter trimmed at V

;

(2) Landing gear retracted (if retractable);

and

(3) Power required for limit climb rate (at

least 1,000 fpm) at V

or maximum contin-

uous power, whichever is less.

(c)

Cruise.

Stability must be shown

throughout the speed range from 0.7 to 1.1 V

or V

NEI

, whichever is lower, not to exceed

knots from trim with—

VerDate Mar<15>2010

10:12 Mar 18, 2014

Jkt 232046

PO 00000

Frm 00838

Fmt 8010

Sfmt 8002

Y:\SGML\232046.XXX

232046

pmangrum on DSK3VPTVN1PROD with CFR