title-14-part-31

691

Federal Aviation Administration, DOT

§ 31.12

(4) From 100 MHz to 8 GHz, use radiated

susceptibility tests at a minimum of 5 V/m.

[Doc. No. FAA–2006–23657, 72 FR 44028, Aug. 6,
2007]

PART 31—AIRWORTHINESS STAND-

ARDS: MANNED FREE BAL-
LOONS

Subpart A—General

Sec.
31.1

Applicability.

Subpart B—Flight Requirements

31.12

Proof of compliance.

31.14

Weight limits.

31.16

Empty weight.

31.17

Performance: Climb.

31.19

Performance: Uncontrolled descent.

31.20

Controllability.

Subpart C—Strength Requirements

31.21

Loads.

31.23

Flight load factor.

31.25

Factor of safety.

31.27

Strength.

Subpart D—Design Construction

31.31

General.

31.33

Materials.

31.35

Fabrication methods.

31.37

Fastenings.

31.39

Protection.

31.41

Inspection provisions.

31.43

Fitting factor.

31.45

Fuel cells.

31.46

Pressurized fuel systems.

31.47

Burners.

31.49

Control systems.

31.51

Ballast.

31.53

Drag rope.

31.55

Deflation means.

31.57

Rip cords.

31.59

Trapeze, basket, or other means pro-

vided for occupants.

31.61

Static discharge.

31.63

Safety belts.

31.65

Position lights.

Subpart E—Equipment

31.71

Function and installation.

Subpart F—Operating Limitations and

Information

31.81

General.

31.82

Instructions for Continued Airworthi-

ness.

31.83

Conspicuity.

31.85

Required basic equipment.

PPENDIX

ART

31—I

NSTRUCTIONS FOR

ONTINUED

IRWORTHINESS

UTHORITY

: 49 U.S.C. 106(g), 40113, 44701–

44702, 44704.

OURCE

: Docket No. 1437, 29 FR 8258, July 1,

1964, as amended by Amdt. 31–1, 29 FR 14563,
Oct. 24, 1964, unless otherwise noted.

Subpart A—General

§ 31.1

Applicability.

(a) This part prescribes airworthiness

standards for the issue of type certifi-
cates and changes to those certificates,
for manned free balloons.

(b) Each person who applies under

Part 21 for such a certificate or change
must show compliance with the appli-
cable requirements of this part.

that derives its lift from a captive
lighter-than-air gas;

(2) A hot air balloon is a balloon that

derives its lift from heated air;

(3) The envelope is the enclosure in

which the lifting means is contained;

(4) The basket is the container, sus-

pended beneath the envelope, for the
balloon occupants;

(5) The trapeze is a harness or is a

seat consisting of a horizontal bar or
platform suspended beneath the enve-
lope for the balloon occupants; and

(6) The design maximum weight is

the maximum total weight of the bal-
loon, less the lifting gas or air.

[Doc. No. 1437, 29 FR 8258, July 1, 1964, as
amended by Amdt. 31–3, 41 FR 55474, Dec. 20,
1976]

Subpart B—Flight Requirements

§ 31.12

Proof of compliance.

(a) Each requirement of this subpart

must be met at each weight within the
range of loading conditions for which
certification is requested. This must be
shown by—

(1) Tests upon a balloon of the type

for which certification is requested or
by calculations based on, and equal in
accuracy to, the results of testing; and

(2) Systematic investigation of each

weight if compliance cannot be reason-
ably inferred from the weights inves-
tigated.

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14 CFR Ch. I (1–1–24 Edition)

§ 31.14

(b) Except as provided in § 31.17(b), al-

lowable weight tolerances during flight
testing are + 5 percent and

10 per-

cent.

[Amdt. 31–4, 45 FR 60179, Sept. 11, 1980]

§ 31.14

Weight limits.

(a) The range of weights over which

the balloon may be safely operated
must be established.

(b)

Maximum weight. The maximum

weight is the highest weight at which
compliance with each applicable re-
quirement of this part is shown. The
maximum weight must be established
so that it is not more than—

(1) The highest weight selected by

the applicant;

(2) The design maximum weight

which is the highest weight at which
compliance with each applicable struc-
tural loading condition of this part is
shown; or

(3) The highest weight at which com-

pliance with each applicable flight re-
quirement of this part is shown.

paragraphs (a) and (b) of this section
must be made available to the pilot in
accordance with § 31.81.

[Amdt. 31–3, 41 FR 55474, Dec. 20, 1976]

§ 31.16

Empty weight.

The empty weight must be deter-

mined by weighing the balloon with in-
stalled equipment but without lifting
gas or heater fuel.

[Amdt. 31–4, 45 FR 60179, Sept. 11, 1980]

§ 31.17

Performance: Climb.

(a) Each balloon must be capable of

climbing at least 300 feet in the first
minute after takeoff with a steady rate
of climb. Compliance with the require-
ments of this section must be shown at
each altitude and ambient temperature
for which approval is sought.

(b) Compliance with the require-

ments of paragraph (a) of this section
must be shown at the maximum weight
with a weight tolerance of + 5 percent.

[Amdt. 31–4, 45 FR 60179, Sept. 11, 1980]

§ 31.19

Performance: Uncontrolled de-

scent.

(a) The following must be determined

for the most critical uncontrolled de-

scent that can result from any single
failure of the heater assembly, fuel cell
system, gas value system, or maneu-
vering vent system, or from any single
tear in the balloon envelope between
tear stoppers:

(1) The maximum vertical velocity

attained.

(2) The altitude loss from the point of

failure to the point at which maximum
vertical velocity is attained.

(3) The altitude required to achieve

level flight after corrective action is
inititated, with the balloon descending
at the maximum vertical velocity de-
termined in paragraph (a)(1) of this sec-
tion.

(b) Procedures must be established

for landing at the maximum vertical
velocity determined in paragraph (a)(1)
of this section and for arresting that
descent rate in accordance with para-
graph (a)(3) of this section.

[Amdt. 31–4, 45 FR 60179, Sept. 11, 1980]

§ 31.20

Controllability.

The applicant must show that the

balloon is safely controllable and ma-
neuverable during takeoff, ascent, de-
scent, and landing without requiring
exceptional piloting skill.

[Amdt. 31–3, 41 FR 55474, Dec. 20, 1976]

Subpart C—Strength Requirements

§ 31.21

Loads.

Strength requirements are specified

in terms of limit loads, that are the
maximum load to be expected in serv-
ice, and ultimate loads, that are limit
loads multiplied by prescribed factors
of safety. Unless otherwise specified,
all prescribed loads are limit loads.

§ 31.23

Flight load factor.

In determining limit load, the limit

flight load factor must be at least 1.4.

§ 31.25

Factor of safety.

(a) Except as specified in paragraphs

(b) and (c) of this section, the factor of
safety is 1.5.

(b) A factor of safety of at least five

must be used in envelope design. A re-
duced factor of safety of at least two
may be used if it is shown that the se-
lected factor will preclude failure due
to creep or instantaneous rupture from

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§ 31.41

lack of rip stoppers. The selected fac-
tor must be applied to the more crit-
ical of the maximum operating pres-
sure or envelope stress.

must be used in the design of all fi-
brous or non-metallic parts of the rig-
ging and related attachments of the en-
velope to basket, trapeze, or other
means provided for carrying occupants.
The primary attachments of the enve-
lope to the basket, trapeze, or other
means provided for carrying occupants
must be designed so that failure is ex-
tremely remote or so that any single
failure will not jeopardize safety of
flight.

(d) In applying factors of safety, the

effect of temperature, and other oper-
ating characteristics, or both, that
may affect strength of the balloon
must be accounted for.

(e) For design purposes, an occupant

weight of at least 170 pounds must be
assumed.

[Doc. No. 1437, 29 FR 8258, July 1, 1964, as
amended by Amdt. 31–2, 30 FR 3377, Mar. 13,
1965]

§ 31.27

Strength.

(a) The structure must be able to

support limit loads without detri-
mental effect.

(b) The structure must be substan-

tiated by test to be able to withstand
the ultimate loads for at least three
seconds without failure. For the enve-
lope, a test of a representative part is
acceptable, if the part tested is large
enough to include critical seams,
joints, and load attachment points and
members.

must be made of the basket, trapeze, or
other place provided for occupants. The
test must be made at design maximum
weight on a horizontal surface, with
the basket, trapeze, or other means
provided for carrying occupants, strik-
ing the surface at angles of 0, 15, and 30
degrees. The weight may be distributed
to simulate actual conditions. There
must be no distortion or failure that is
likely to cause serious injury to the oc-
cupants. A drop test height of 36
inches, or a drop test height that pro-
duces, upon impact, a velocity equal to
the maximum vertical velocity deter-

mined in accordance with § 31.19,
whichever is higher, must be used.

[Doc. No. 1437, 29 FR 8258, July 1, 1964, as
amended by Amdt. 31–4, 45 FR 60179, Sept. 11,
1980]

Subpart D—Design Construction

§ 31.31

General.

The suitability of each design detail

or part that bears on safety must be es-
tablished by tests or analysis.

§ 31.33

Materials.

(a) The suitability and durability of

all materials must be established on
the basis of experience or tests. Mate-
rials must conform to approved speci-
fications that will ensure that they
have the strength and other properties
assumed in the design data.

(b) Material strength properties must

be based on enough tests of material
conforming to specifications so as to
establish design values on a statistical
basis.

§ 31.35

Fabrication methods.

The methods of fabrication used

must produce a consistently sound
structure. If a fabrication process re-
quires close control to reach this objec-
tive, the process must be performed in
accordance with an approved process
specification.

§ 31.37

Fastenings.

Only approved bolts, pins, screws,

and rivets may be used in the struc-
ture. Approved locking devices or
methods must be used for all these
bolts, pins, and screws, unless the in-
stallation is shown to be free from vi-
bration. Self-locking nuts may not be
used on bolts that are subject to rota-
tion in service.

§ 31.39

Protection.

Each part of the balloon must be

suitably protected against deteriora-
tion or loss of strength in service due
to weathering, corrosion, or other
causes.

§ 31.41

Inspection provisions.

There must be a means to allow close

examination of each part that require
repeated inspection and adjustment.

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§ 31.43

Fitting factor.

(a) A fitting factor of at least 1.15

must be used in the analysis of each
fitting the strength of which is not
proven by limit and ultimate load tests
in which the actual stress conditions
are simulated in the fitting and sur-
rounding structure. This factor applies
to all parts of the fitting, the means of
attachment, and the bearing on the
members joined.

(b) Each part with an integral fitting

must be treated as a fitting up to the
point where the section properties be-
come typical of the member.

used if the joint design is made in ac-
cordance with approved practices and
is based on comprehensive test data.

§ 31.45

Fuel cells.

If fuel cells are used, the fuel cells,

their attachments, and related sup-
porting structure must be shown by
tests to be capable of withstanding,
without detrimental distortion or fail-
ure, any inertia loads to which the in-
stallation may be subjected, including
the drop tests prescribed in § 31.27(c). In
the tests, the fuel cells must be loaded
to the weight and pressure equivalent
to the full fuel quantity condition.

[Amdt. 31–3, 41 FR 55474, Dec. 20, 1976]

§ 31.46

Pressurized fuel systems.

For pressurized fuel systems, each

element and its connecting fittings and
lines must be tested to an ultimate
pressure of at least twice the maximum
pressure to which the system will be
subjected in normal operation. No part
of the system may fail or malfunction
during the test. The test configuration
must be representative of the normal
fuel system installation and balloon
configuration.

[Amdt. 31–3, 41 FR 55474, Dec. 20, 1976]

§ 31.47

Burners.

(a) If a burner is used to provide the

lifting means, the system must be de-
signed and installed so as not to create
a fire hazard.

(b) There must be shielding to pro-

tect parts adjacent to the burner
flame, and the occupants, from heat ef-
fects.

ments, or other equipment essential to
the safe control and operation of the
heater. They must be shown to be able
to perform their intended functions
during normal and emergency oper-
ation.

(d) The burner system (including the

burner unit, controls, fuel lines, fuel
cells, regulators, control valves, and
other related elements) must be sub-
stantiated by an endurance test of at
least 40 hours. Each element of the sys-
tem must be installed and tested to
simulate actual balloon installation
and use.

(1) The test program for the main

blast valve operation of the burner
must include:

(i) Five hours at the maximum fuel

pressure for which approval is sought,
with a burn time for each one minute
cycle of three to ten seconds. The burn
time must be established so that each
burner is subjected to the maximum
thermal shock for temperature affected
elements;

(ii) Seven and one-half hours at an

intermediate fuel pressure, with a burn
time for each one minute cycle of three
to ten seconds. An intermediate fuel
pressure is 40 to 60 percent of the range
between the maximum fuel pressure
referenced in paragraph (d)(1)(i) of this
section and minimum fuel pressure ref-
erenced in paragraph (d)(1)(iii);

(iii) Six hours and fifteen minutes at

the minimum fuel pressure for which
approval is sought, with a burn time
for each one minute cycle of three to
ten seconds;

(iv) Fifteen minutes of operation on

vapor, with a burn time for each one
minute cycle of at least 30 seconds; and

(v) Fifteen hours of normal flight op-

eration.

(2) The test program for the sec-

ondary or backup operation of the
burner must include six hours of oper-
ation with a burn time for each five
minute cycle of one minute at an inter-
mediate fuel pressure.

(e) The test must also include at

least three flameouts and restarts.

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§ 31.61

(f) Each element of the system must

be serviceable at the end of the test.

[Doc. No. 1437, 29 FR 8258, July 1, 1964, as
amended by Amdt. 31–2, 30 FR 3377, Mar. 13,
1965; Amdt. 31–7, 61 FR 18223, Apr. 24, 1996; 61
FR 20877, May 8, 1996]

§ 31.49

Control systems.

(a) Each control must operate easily,

smoothly, and positively enough to
allow proper performance of its func-
tions. Controls must be arranged and
identified to provide for convenience of
operation and to prevent the possi-
bility of confusion and subsequent in-
advertent operation.

(b) Each control system and oper-

ating device must be designed and in-
stalled in a manner that will prevent
jamming, chafing, or interference from
passengers, cargo, or loose objects. Pre-
caution must be taken to prevent for-
eign objects from jamming the con-
trols. The elements of the control sys-
tem must have design features or must
be distinctly and permanently marked
to minimize the possibility of incorrect
assembly that could result in malfunc-
tioning of the control system.

as the lifting means must have an
automatic valve or appendix that is
able to release gas automatically at
the rate of at least three percent of the
total volume per minute when the bal-
loon is at its maximum operating pres-
sure.

(d) Each hot air balloon must have a

means to allow the controlled release
of hot air during flight.

(e) Each hot air balloon must have a

means to indicate the maximum enve-
lope skin temperatures occurring dur-
ing operation. The indicator must be
readily visible to the pilot and marked
to indicate the limiting safe tempera-
ture of the envelope material. If the
markings are on the cover glass of the
instrument, there must be provisions
to maintain the correct alignment of
the glass cover with the face of the
dial.

[Doc. No. 1437, 29 FR 8258, July 1, 1964, as
amended by Amdt. 31–2, 30 FR 3377, Mar. 13,
1965]

§ 31.51

Ballast.

Each captive gas balloon must have a

means for the safe storage and con-

trolled release of ballast. The ballast
must consist of material that, if re-
leased during flight, is not hazardous
to persons on the ground.

§ 31.53

Drag rope.

If a drag rope is used, the end that is

released overboard must be stiffened to
preclude the probability of the rope be-
coming entangled with trees, wires, or
other objects on the ground.

§ 31.55

Deflation means.

There must be a means to allow

emergency deflation of the envelope so
as to allow a safe emergency landing. If
a system other than a manual system
is used, the reliability of the system
used must be substantiated.

[Amdt. 31–2, 30 FR 3377, Mar. 13, 1965]

§ 31.57

Rip cords.

(a) If a rip cord is used for emergency

deflation, it must be designed and in-
stalled to preclude entanglement.

(b) The force required to operate the

rip cord may not be less than 25, or
more than 75, pounds.

ated by the pilot must be colored red.

(d) The rip cord must be long enough

to allow an increase of at least 10 per-
cent in the vertical dimension of the
envelope.

§ 31.59

Trapeze, basket, or other

means provided for occupants.

(a) The trapeze, basket, or other

means provided for carrying occupants
may not rotate independently of the
envelope.

(b) Each projecting object on the tra-

peze, basket, or other means provided
for carrying occupants, that could
cause injury to the occupants, must be
padded.

§ 31.61

Static discharge.

Unless shown not to be necessary for

safety, there must be appropriate bond-
ing means in the design of each balloon
using flammable gas as a lifting means
to ensure that the effects of static dis-
charges will not create a hazard.

[Amdt. 31–2, 30 FR 3377, Mar. 13, 1965]

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§ 31.63

Safety belts.

(a) There must be a safety belt, har-

ness, or other restraining means for
each occupant, unless the Adminis-
trator finds it unnecessary. If installed,
the belt, harness, or other restraining
means and its supporting structure
must meet the strength requirements
of subpart C of this part.

(b) This section does not apply to bal-

loons that incorporate a basket or gon-
dola.

[Amdt. 31–2, 30 FR 3377, Mar. 13, 1965, as
amended by Amdt. 31–3, 41 FR 55474, Dec. 20,
1976]

§ 31.65

Position lights.

(a) If position lights are installed,

there must be one steady aviation
white position light and one flashing
aviation red (or flashing aviation
white) position light with an effective
flash frequency of at least 40, but not
more than 100, cycles per minute.

(b) Each light must provide 360

hori-

zontal coverage at the intensities pre-
scribed in this paragraph. The fol-
lowing light intensities must be deter-
mined with the light source operating
at a steady state and with all light cov-
ers and color filters in place and at the
manufacturer’s rated minimum volt-
age. For the flashing aviation red light,
the measured values must be adjusted
to correspond to a red filter tempera-
ture of at least 130

(1) The intensities in the horizontal

plane passing through the light unit
must equal or exceed the following val-
ues:

Position light

Minimum

intensity

(candles)

Steady white ........................................................

Flashing red or white ...........................................

(2) The intensities in vertical planes

must equal or exceed the following val-
ues. An intensity of one unit cor-
responds to the applicable horizontal
plane intensity specified in paragraph
(b)(1) of this section.

Angles above and below the horizontal in any

vertical plane (degrees)

Minimum

intensity

(units)

0 ...........................................................................

1.00

0 to 5 ...................................................................

0.90

5 to 10 .................................................................

0.80

10 to 15 ...............................................................

0.70

Angles above and below the horizontal in any

vertical plane (degrees)

Minimum

intensity

(units)

15 to 20 ...............................................................

0.50

20 to 30 ...............................................................

0.30

30 to 40 ...............................................................

0.10

40 to 60 ...............................................................

0.05

cated not more than 20 feet below the
basket, trapeze, or other means for car-
rying occupants. The flashing red or
white light must be located not less
than 7, nor more than 10, feet below the
steady white light.

(d) There must be a means to retract

and store the lights.

(e) Each position light color must

have the applicable International Com-
mission on Illumination chromaticity
coordinates as follows:

(1)

Aviation red—

y is not greater than 0.335; and z is not great-

er than 0.002.

(2)

Aviation white—

x is not less than 0.300 and not greater than

0.540;

y is not less than x

0.040 or

0.010, which-

ever is the smaller; and

y is not greater than x + 0.020 nor

0.636

0.0400

Where

is the

y coordinate of the Planckian

radiator for the value of

x considered.

[Doc. No. 1437, 29 FR 8258, July 1, 1964, as
amended by Amdt. 31–1, 29 FR 14563, Oct. 24,
1964; Amdt. 31–4, 45 FR 60179, Sept. 11, 1980]

Subpart E—Equipment

§ 31.71

Function and installation.

(a) Each item of installed equipment

must—

(1) Be of a kind and design appro-

priate to its intended function;

(2) Be permanently and legibly

marked or, if the item is too small to
mark, tagged as to its identification,
function, or operating limitations, or
any applicable combination of those
factors;

(3) Be installed according to limita-

tions specified for that equipment; and

(4) Function properly when installed.
(b) No item of installed equipment,

when performing its function, may af-
fect the function of any other equip-
ment so as to create an unsafe condi-
tion.

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Pt. 31, App. A

stallations must be designed to prevent
hazards to the balloon in the event of a
probable malfunction or failure.

[Amdt. 31–4, 45 FR 60180, Sept. 11, 1980]

Subpart F—Operating Limitations

and Information

§ 31.81

General.

(a) The following information must

be established:

(1) Each operating limitation, includ-

ing the maximum weight determined
under § 31.14.

(2) The normal and emergency proce-

dures.

(3) Other information necessary for

safe operation, including—

(i) The empty weight determined

under § 31.16;

(ii) The rate of climb determined

under § 31.17, and the procedures and
conditions used to determine perform-
ance;

(iii) The maximum vertical velocity,

the altitude drop required to attain
that velocity, and altitude drop re-
quired to recover from a descent at
that velocity, determined under § 31.19,
and the procedures and conditions used
to determine performance; and

(iv) Pertinent information peculiar

to the balloon’s operating characteris-
tics.

(b) The information established in

compliance with paragraph (a) of this
section must be furnished by means
of—

(1) A Balloon Flight Manual; or
(2) A placard on the balloon that is

clearly visible to the pilot.

[Amdt. 31–4, 45 FR 60180, Sept. 11, 1980]

§ 31.82

Instructions for Continued Air-

worthiness.

The applicant must prepare Instruc-

tions for Continued Airworthiness in
accordance with appendix A to this
part that are acceptable to the Admin-
istrator. The instructions may be in-
complete at type certification if a pro-
gram exists to ensure their completion
prior to delivery of the first balloon or
issuance of a standard certificate of
airworthiness, whichever occurs later.

[Amdt. 31–4, 45 FR 60180, Sept. 11, 1980]

§ 31.83

Conspicuity.

The exterior surface of the envelope

must be of a contrasting color or colors
so that it will be conspicuous during
operation. However, multicolored ban-
ners or streamers are acceptable if it
can be shown that they are large
enough, and there are enough of them
of contrasting color, to make the bal-
loon conspicuous during flight.

§ 31.85

Required basic equipment.

In addition to any equipment re-

quired by this subchapter for a specific
kind of operation, the following equip-
ment is required:

(a) For all balloons:
(1) [Reserved]
(2) An altimeter.
(3) A rate of climb indicator.
(b) For hot air balloons:
(1) A fuel quantity gauge. If fuel cells

are used, means must be incorporated
to indicate to the crew the quantity of
fuel in each cell during flight. The
means must be calibrated in appro-
priate units or in percent of fuel cell
capacity.

(2) An envelope temperature indi-

cator.

pass.

[Amdt. 31–2, 30 FR 3377, Mar. 13, 1965, as
amended by Amdt. 31–3, 41 FR 55474, Dec. 20,
1976; Amdt. 31–4, 45 FR 60180, Sept. 11, 1980]

PPENDIX

ART

31—I

NSTRUCTIONS

FOR

ONTINUED

IRWORTHINESS

31.1

GENERAL

(a) This appendix specifies requirements

for the preparation of Instructions for Con-
tinued Airworthiness as required by § 31.82.

(b) The Instructions for Continued Air-

worthiness for each balloon must include the
Instructions for Continued Airworthiness for
all balloon parts required by this chapter
and any required information relating to the
interface of those parts with the balloon. If
Instructions for Continued Airworthiness are
not supplied by the part manufacturer for a
balloon part, the Instructions for Continued
Airworthiness for the balloon must include
the information essential to the continued
airworthiness of the balloon.

a program to show how changes to the In-
structions for Continued Airworthiness made

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698

14 CFR Ch. I (1–1–24 Edition)

Pt. 33

by the applicant or by the manufacturers of
balloon parts will be distributed.

31.2

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.

31.3

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 information:

(a) Introduction information that includes

an explanation of the balloon’s features and
data to the extent necessary for mainte-
nance or preventive maintenance.

(b) A description of the balloon and its sys-

tems and installations.

tion for the balloon and its components and
systems.

(d) Servicing information that covers de-

tails regarding servicing of balloon compo-
nents, including burner nozzles, fuel tanks,
and valves during operations.

(e) Maintenance information for each part

of the balloon and its envelope, controls, rig-
ging, basket structure, fuel systems, instru-
ments, and heater assembly that provides
the recommended periods at which they
should be cleaned, adjusted, tested, and lu-
bricated, the applicable wear tolerances, and
the degree of work recommended at these pe-
riods. However, the applicant may refer to
an accessory, instrument, or equipment
manufacturer as the source of this informa-
tion if the applicant shows that the item has
an exceptionally high degree of complexity
requiring specialized maintenance tech-
niques, test equipment, or expertise. The rec-
ommended overhaul periods and necessary
cross references to the Airworthiness Limi-
tations section of the manual must also be
included. In addition, the applicant must in-
clude an inspection program that includes
the frequency and extent of the inspections
necessary to provide for the continued air-
worthiness of the balloon.

(f) Troubleshooting information describing

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

(g) Details of what, and how, to inspect

after a hard landing.

(h) Instructions for storage preparation in-

cluding any storage limits.

(i) Instructions for repair on the balloon

envelope and its basket or trapeze.

31.4

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, including envelope struc-
tural integrity, 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.’’

[Amdt. 31–4, 45 FR 60180, Sept. 11, 1980, as
amended by Amdt. 31–5, 54 FR 34330, Aug. 18,
1989]

PART 33—AIRWORTHINESS

STANDARDS: AIRCRAFT ENGINES

Subpart A—General

Sec.
33.1

Applicability.

33.3

General.

33.4

Instructions for Continued Airworthi-

ness.

33.5

Instruction manual for installing and

operating the engine.

33.7

Engine ratings and operating limita-

tions.

33.8

Selection of engine power and thrust

ratings.

Subpart B—Design and Construction;

General

33.11

Applicability.

33.13

[Reserved]

33.15

Materials.

33.17

Fire protection.

33.19

Durability.

33.21

Engine cooling.

33.23

Engine mounting attachments and

structure.

33.25

Accessory attachments.

33.27

Turbine, compressor, fan, and turbo-

supercharger rotor overspeed.

33.28

Engine control systems.

33.29

Instrument connection.

Subpart C—Design and Construction;

Reciprocating Aircraft Engines

33.31

Applicability.

33.33

Vibration.

33.34

Turbocharger rotors.

33.35

Fuel and induction system.

33.37

Ignition system.

33.39

Lubrication system.

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