Document
Federal Aviation Administration, DOT § 31.12 (4) From 100 MHz to 8 GHz, use radiated APPENDIX A TO P ART 31—I NSTRUCTIONS FOR susceptibility tests at a minimum of 5 V/m. C ONTINUED A IRWORTHINESS [Doc. No. FAA–2006–23657, 72 FR 44028, Aug. 6, AUTHORITY : 49 U.S.C. 106(g), 40113, 44701– 2007] 44702, 44704.
S OURCE : Docket No. 1437, 29 FR 8258, July 1, PART 31—AIRWORTHINESS STAND- 1964, as amended by Amdt. 31–1, 29 FR 14563, Oct. 24, 1964, unless otherwise noted.
ARDS: MANNED FREE BAL- LOONS Subpart A—General Subpart A—General § 31.1 Applicability.
Sec.
(a) This part prescribes airworthiness 31.1 Applicability.
standards for the issue of type certifi- cates and changes to those certificates, Subpart B—Flight Requirements for manned free balloons.
31.12 Proof of compliance.
(b) Each person who applies under 31.14 Weight limits.
Part 21 for such a certificate or change 31.16 Empty weight.
must show compliance with the appli- 31.17 Performance: Climb.
cable requirements of this part.
31.19 Performance: Uncontrolled descent.
(c) For purposes of this part— 31.20 Controllability.
(1) A captive gas balloon is a balloon Subpart C—Strength Requirements that derives its lift from a captive lighter-than-air gas; 31.21 Loads.
(2) A hot air balloon is a balloon that 31.23 Flight load factor.
derives its lift from heated air; 31.25 Factor of safety.
31.27 Strength. (3) The envelope is the enclosure in which the lifting means is contained; Subpart D—Design Construction (4) The basket is the container, sus- pended beneath the envelope, for the 31.31 General.
balloon occupants; 31.33 Materials.
(5) The trapeze is a harness or is a 31.35 Fabrication methods.
31.37 Fastenings. seat consisting of a horizontal bar or 31.39 Protection. platform suspended beneath the enve- 31.41 Inspection provisions.
lope for the balloon occupants; and 31.43 Fitting factor.
(6) The design maximum weight is 31.45 Fuel cells.
the maximum total weight of the bal- 31.46 Pressurized fuel systems.
loon, less the lifting gas or air.
31.47 Burners.
31.49 Control systems.
[Doc. No. 1437, 29 FR 8258, July 1, 1964, as 31.51 Ballast.
amended by Amdt. 31–3, 41 FR 55474, Dec. 20, 31.53 Drag rope.
1976] 31.55 Deflation means.
31.57 Rip cords.
Subpart B—Flight Requirements 31.59 Trapeze, basket, or other means pro- vided for occupants.
§ 31.12 Proof of compliance.
31.61 Static discharge.
31.63 Safety belts.
(a) Each requirement of this subpart 31.65 Position lights.
must be met at each weight within the range of loading conditions for which Subpart E—Equipment certification is requested. This must be shown by— 31.71 Function and installation.
(1) Tests upon a balloon of the type Subpart F—Operating Limitations and for which certification is requested or Information by calculations based on, and equal in accuracy to, the results of testing; and 31.81 General.
(2) Systematic investigation of each 31.82 Instructions for Continued Airworthi- weight if compliance cannot be reason- ness.
ably inferred from the weights inves- 31.83 Conspicuity.
31.85 Required basic equipment. tigated.
14 CFR Ch. I (1–1–25 Edition) § 31.14 (b) Except as provided in § 31.17(b), al- scent that can result from any single lowable weight tolerances during flight failure of the heater assembly, fuel cell testing are + 5 percent and ¥ 10 per- system, gas value system, or maneu- cent. vering vent system, or from any single tear in the balloon envelope between [Amdt. 31–4, 45 FR 60179, Sept. 11, 1980] tear stoppers: (1) The maximum vertical velocity § 31.14 Weight limits.
attained.
(a) The range of weights over which (2) The altitude loss from the point of the balloon may be safely operated failure to the point at which maximum must be established.
vertical velocity is attained.
(b) Maximum weight. The maximum (3) The altitude required to achieve weight is the highest weight at which level flight after corrective action is compliance with each applicable re- inititated, with the balloon descending quirement of this part is shown. The at the maximum vertical velocity de- maximum weight must be established termined in paragraph (a)(1) of this sec- so that it is not more than— tion.
(1) The highest weight selected by (b) Procedures must be established the applicant; for landing at the maximum vertical (2) The design maximum weight velocity determined in paragraph (a)(1) which is the highest weight at which of this section and for arresting that compliance with each applicable struc- descent rate in accordance with para- tural loading condition of this part is graph (a)(3) of this section.
shown; or [Amdt. 31–4, 45 FR 60179, Sept. 11, 1980] (3) The highest weight at which com- pliance with each applicable flight re- § 31.20 Controllability.
quirement of this part is shown.
The applicant must show that the (c) The information established under balloon is safely controllable and ma- paragraphs (a) and (b) of this section neuverable during takeoff, ascent, de- must be made available to the pilot in scent, and landing without requiring accordance with § 31.81.
exceptional piloting skill.
[Amdt. 31–3, 41 FR 55474, Dec. 20, 1976] [Amdt. 31–3, 41 FR 55474, Dec. 20, 1976] § 31.16 Empty weight.
Subpart C—Strength Requirements The empty weight must be deter- mined by weighing the balloon with in- § 31.21 Loads.
stalled equipment but without lifting Strength requirements are specified gas or heater fuel.
in terms of limit loads, that are the [Amdt. 31–4, 45 FR 60179, Sept. 11, 1980] maximum load to be expected in serv- ice, and ultimate loads, that are limit § 31.17 Performance: Climb.
loads multiplied by prescribed factors (a) Each balloon must be capable of of safety. Unless otherwise specified, climbing at least 300 feet in the first all prescribed loads are limit loads.
minute after takeoff with a steady rate of climb. Compliance with the require- § 31.23 Flight load factor.
ments of this section must be shown at In determining limit load, the limit each altitude and ambient temperature flight load factor must be at least 1.4.
for which approval is sought.
(b) Compliance with the require- § 31.25 Factor of safety.
ments of paragraph (a) of this section (a) Except as specified in paragraphs must be shown at the maximum weight (b) and (c) of this section, the factor of with a weight tolerance of + 5 percent.
safety is 1.5.
[Amdt. 31–4, 45 FR 60179, Sept. 11, 1980] (b) A factor of safety of at least five must be used in envelope design. A re- § 31.19 Performance: Uncontrolled de- duced factor of safety of at least two scent.
may be used if it is shown that the se- (a) The following must be determined lected factor will preclude failure due for the most critical uncontrolled de- to creep or instantaneous rupture from Federal Aviation Administration, DOT § 31.41 lack of rip stoppers. The selected fac- mined in accordance with § 31.19, tor must be applied to the more crit- whichever is higher, must be used.
ical of the maximum operating pres- [Doc. No. 1437, 29 FR 8258, July 1, 1964, as sure or envelope stress.
amended by Amdt. 31–4, 45 FR 60179, Sept. 11, (c) A factor of safety of at least five 1980] must be used in the design of all fi- brous or non-metallic parts of the rig- Subpart D—Design Construction ging and related attachments of the en- velope to basket, trapeze, or other § 31.31 General.
means provided for carrying occupants.
The suitability of each design detail The primary attachments of the enve- or part that bears on safety must be es- lope to the basket, trapeze, or other tablished by tests or analysis.
means provided for carrying occupants must be designed so that failure is ex- § 31.33 Materials.
tremely remote or so that any single (a) The suitability and durability of failure will not jeopardize safety of all materials must be established on flight.
the basis of experience or tests. Mate- (d) In applying factors of safety, the rials must conform to approved speci- effect of temperature, and other oper- fications that will ensure that they ating characteristics, or both, that have the strength and other properties may affect strength of the balloon assumed in the design data.
must be accounted for.
(b) Material strength properties must (e) For design purposes, an occupant be based on enough tests of material weight of at least 170 pounds must be conforming to specifications so as to assumed.
establish design values on a statistical basis.
[Doc. No. 1437, 29 FR 8258, July 1, 1964, as amended by Amdt. 31–2, 30 FR 3377, Mar. 13, § 31.35 Fabrication methods.
1965] The methods of fabrication used § 31.27 Strength.
must produce a consistently sound structure. If a fabrication process re- (a) The structure must be able to quires close control to reach this objec- support limit loads without detri- tive, the process must be performed in mental effect.
accordance with an approved process (b) The structure must be substan- specification.
tiated by test to be able to withstand the ultimate loads for at least three § 31.37 Fastenings.
seconds without failure. For the enve- Only approved bolts, pins, screws, lope, a test of a representative part is and rivets may be used in the struc- acceptable, if the part tested is large ture. Approved locking devices or enough to include critical seams, methods must be used for all these joints, and load attachment points and bolts, pins, and screws, unless the in- members.
stallation is shown to be free from vi- (c) An ultimate free-fall drop test bration. Self-locking nuts may not be must be made of the basket, trapeze, or used on bolts that are subject to rota- other place provided for occupants. The tion in service.
test must be made at design maximum weight on a horizontal surface, with § 31.39 Protection.
the basket, trapeze, or other means Each part of the balloon must be provided for carrying occupants, strik- suitably protected against deteriora- ing the surface at angles of 0, 15, and 30 tion or loss of strength in service due degrees. The weight may be distributed to weathering, corrosion, or other to simulate actual conditions. There causes.
must be no distortion or failure that is likely to cause serious injury to the oc- § 31.41 Inspection provisions.
cupants. A drop test height of 36 inches, or a drop test height that pro- There must be a means to allow close duces, upon impact, a velocity equal to examination of each part that require the maximum vertical velocity deter- repeated inspection and adjustment.
14 CFR Ch. I (1–1–25 Edition) § 31.43 (c) There must be controls, instru- § 31.43 Fitting factor.
ments, or other equipment essential to (a) A fitting factor of at least 1.15 the safe control and operation of the must be used in the analysis of each heater. They must be shown to be able fitting the strength of which is not to perform their intended functions proven by limit and ultimate load tests during normal and emergency oper- in which the actual stress conditions ation.
are simulated in the fitting and sur- (d) The burner system (including the rounding structure. This factor applies to all parts of the fitting, the means of burner unit, controls, fuel lines, fuel attachment, and the bearing on the cells, regulators, control valves, and members joined. other related elements) must be sub- (b) Each part with an integral fitting stantiated by an endurance test of at must be treated as a fitting up to the least 40 hours. Each element of the sys- point where the section properties be- tem must be installed and tested to come typical of the member.
simulate actual balloon installation (c) The fitting factor need not be and use.
used if the joint design is made in ac- (1) The test program for the main cordance with approved practices and blast valve operation of the burner is based on comprehensive test data.
must include: (i) Five hours at the maximum fuel § 31.45 Fuel cells.
pressure for which approval is sought, If fuel cells are used, the fuel cells, with a burn time for each one minute their attachments, and related sup- cycle of three to ten seconds. The burn porting structure must be shown by time must be established so that each tests to be capable of withstanding, burner is subjected to the maximum without detrimental distortion or fail- thermal shock for temperature affected ure, any inertia loads to which the in- elements; stallation may be subjected, including (ii) Seven and one-half hours at an the drop tests prescribed in § 31.27(c). In intermediate fuel pressure, with a burn the tests, the fuel cells must be loaded time for each one minute cycle of three to the weight and pressure equivalent to ten seconds. An intermediate fuel to the full fuel quantity condition.
pressure is 40 to 60 percent of the range [Amdt. 31–3, 41 FR 55474, Dec. 20, 1976] between the maximum fuel pressure referenced in paragraph (d)(1)(i) of this § 31.46 Pressurized fuel systems.
section and minimum fuel pressure ref- For pressurized fuel systems, each erenced in paragraph (d)(1)(iii); element and its connecting fittings and (iii) Six hours and fifteen minutes at lines must be tested to an ultimate the minimum fuel pressure for which pressure of at least twice the maximum approval is sought, with a burn time pressure to which the system will be for each one minute cycle of three to subjected in normal operation. No part ten seconds; of the system may fail or malfunction (iv) Fifteen minutes of operation on during the test. The test configuration vapor, with a burn time for each one must be representative of the normal minute cycle of at least 30 seconds; and fuel system installation and balloon (v) Fifteen hours of normal flight op- configuration.
eration.
[Amdt. 31–3, 41 FR 55474, Dec. 20, 1976] (2) The test program for the sec- ondary or backup operation of the § 31.47 Burners.
burner must include six hours of oper- (a) If a burner is used to provide the ation with a burn time for each five lifting means, the system must be de- minute cycle of one minute at an inter- signed and installed so as not to create mediate fuel pressure.
a fire hazard.
(e) The test must also include at (b) There must be shielding to pro- least three flameouts and restarts.
tect parts adjacent to the burner flame, and the occupants, from heat ef- fects.
Federal Aviation Administration, DOT § 31.61 (f) Each element of the system must trolled release of ballast. The ballast be serviceable at the end of the test. must consist of material that, if re- leased during flight, is not hazardous [Doc. No. 1437, 29 FR 8258, July 1, 1964, as to persons on the ground.
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] § 31.53 Drag rope.
If a drag rope is used, the end that is § 31.49 Control systems.
released overboard must be stiffened to (a) Each control must operate easily, preclude the probability of the rope be- smoothly, and positively enough to coming entangled with trees, wires, or allow proper performance of its func- other objects on the ground.
tions. Controls must be arranged and identified to provide for convenience of § 31.55 Deflation means.
operation and to prevent the possi- There must be a means to allow bility of confusion and subsequent in- emergency deflation of the envelope so advertent operation.
(b) Each control system and oper- as to allow a safe emergency landing. If ating device must be designed and in- a system other than a manual system stalled in a manner that will prevent is used, the reliability of the system jamming, chafing, or interference from used must be substantiated.
passengers, cargo, or loose objects. Pre- [Amdt. 31–2, 30 FR 3377, Mar. 13, 1965] caution must be taken to prevent for- eign objects from jamming the con- § 31.57 Rip cords.
trols. The elements of the control sys- tem must have design features or must (a) If a rip cord is used for emergency be distinctly and permanently marked deflation, it must be designed and in- to minimize the possibility of incorrect stalled to preclude entanglement.
assembly that could result in malfunc- (b) The force required to operate the tioning of the control system.
rip cord may not be less than 25, or (c) Each balloon using a captive gas more than 75, pounds.
as the lifting means must have an (c) The end of the rip cord to be oper- automatic valve or appendix that is ated by the pilot must be colored red.
able to release gas automatically at (d) The rip cord must be long enough the rate of at least three percent of the to allow an increase of at least 10 per- total volume per minute when the bal- cent in the vertical dimension of the loon is at its maximum operating pres- envelope.
sure.
(d) Each hot air balloon must have a § 31.59 Trapeze, basket, or other means to allow the controlled release means provided for occupants.
of hot air during flight.
(a) The trapeze, basket, or other (e) Each hot air balloon must have a means to indicate the maximum enve- means provided for carrying occupants lope skin temperatures occurring dur- may not rotate independently of the ing operation. The indicator must be envelope.
readily visible to the pilot and marked (b) Each projecting object on the tra- to indicate the limiting safe tempera- peze, basket, or other means provided ture of the envelope material. If the for carrying occupants, that could markings are on the cover glass of the cause injury to the occupants, must be instrument, there must be provisions padded.
to maintain the correct alignment of the glass cover with the face of the § 31.61 Static discharge.
dial.
Unless shown not to be necessary for [Doc. No. 1437, 29 FR 8258, July 1, 1964, as safety, there must be appropriate bond- amended by Amdt. 31–2, 30 FR 3377, Mar. 13, ing means in the design of each balloon 1965] using flammable gas as a lifting means to ensure that the effects of static dis- § 31.51 Ballast.
charges will not create a hazard.
Each captive gas balloon must have a means for the safe storage and con- [Amdt. 31–2, 30 FR 3377, Mar. 13, 1965] 14 CFR Ch. I (1–1–25 Edition) § 31.63 Minimum § 31.63 Safety belts.
Angles above and below the horizontal in any intensity vertical plane (degrees) (units) (a) There must be a safety belt, har- ness, or other restraining means for 15 to 20 ............................................................... 0.50 each occupant, unless the Adminis- 20 to 30 ............................................................... 0.30 trator finds it unnecessary. If installed, 30 to 40 ............................................................... 0.10 the belt, harness, or other restraining 40 to 60 ............................................................... 0.05 means and its supporting structure (c) The steady white light must be lo- must meet the strength requirements cated not more than 20 feet below the of subpart C of this part.
basket, trapeze, or other means for car- (b) This section does not apply to bal- rying occupants. The flashing red or loons that incorporate a basket or gon- white light must be located not less dola.
than 7, nor more than 10, feet below the [Amdt. 31–2, 30 FR 3377, Mar. 13, 1965, as steady white light.
amended by Amdt. 31–3, 41 FR 55474, Dec. 20, (d) There must be a means to retract 1976] and store the lights.
§ 31.65 Position lights.
(e) Each position light color must have the applicable International Com- (a) If position lights are installed, mission on Illumination chromaticity there must be one steady aviation coordinates as follows: white position light and one flashing (1) Aviation red — aviation red (or flashing aviation white) position light with an effective y is not greater than 0.335; and z is not great- flash frequency of at least 40, but not er than 0.002.
more than 100, cycles per minute.
(2) Aviation white — (b) Each light must provide 360 ° hori- zontal coverage at the intensities pre- x is not less than 0.300 and not greater than scribed in this paragraph. The fol- 0.540; lowing light intensities must be deter- y is not less than x ¥ 0.040 or y ¥ 0.010, which- o mined with the light source operating ever is the smaller; and at a steady state and with all light cov- y is not greater than x + 0.020 nor ers and color filters in place and at the 0.636 ¥ 0.0400 x ; Where y is the y coordinate of the Planckian manufacturer’s rated minimum volt- o radiator for the value of x considered.
age. For the flashing aviation red light, the measured values must be adjusted [Doc. No. 1437, 29 FR 8258, July 1, 1964, as to correspond to a red filter tempera- amended by Amdt. 31–1, 29 FR 14563, Oct. 24, ture of at least 130 ° F: 1964; Amdt. 31–4, 45 FR 60179, Sept. 11, 1980] (1) The intensities in the horizontal plane passing through the light unit Subpart E—Equipment must equal or exceed the following val- ues: § 31.71 Function and installation.
(a) Each item of installed equipment Minimum Position light intensity must— (candles) (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 (2) The intensities in vertical planes mark, tagged as to its identification, must equal or exceed the following val- function, or operating limitations, or ues. An intensity of one unit cor- any applicable combination of those responds to the applicable horizontal factors; plane intensity specified in paragraph (3) Be installed according to limita- (b)(1) of this section.
tions specified for that equipment; and Minimum (4) Function properly when installed.
Angles above and below the horizontal in any intensity vertical plane (degrees) (b) No item of installed equipment, (units) when performing its function, may af- 0 ........................................................................... 1.00 fect the function of any other equip- 0 to 5 ................................................................... 0.90 ment so as to create an unsafe condi- 5 to 10 ................................................................. 0.80 10 to 15 ............................................................... 0.70 tion.
Federal Aviation Administration, DOT Pt. 31, App. A (c) The equipment, systems, and in- § 31.83 Conspicuity.
stallations must be designed to prevent The exterior surface of the envelope hazards to the balloon in the event of a must be of a contrasting color or colors probable malfunction or failure.
so that it will be conspicuous during [Amdt. 31–4, 45 FR 60180, Sept. 11, 1980] operation. However, multicolored ban- ners or streamers are acceptable if it can be shown that they are large Subpart F—Operating Limitations enough, and there are enough of them and Information of contrasting color, to make the bal- loon conspicuous during flight.
§ 31.81 General.
(a) The following information must § 31.85 Required basic equipment.
be established: In addition to any equipment re- (1) Each operating limitation, includ- quired by this subchapter for a specific ing the maximum weight determined kind of operation, the following equip- under § 31.14.
ment is required: (2) The normal and emergency proce- (a) For all balloons: dures.
(1) [Reserved] (3) Other information necessary for (2) An altimeter.
safe operation, including— (3) A rate of climb indicator.
(i) The empty weight determined (b) For hot air balloons: under § 31.16; (1) A fuel quantity gauge. If fuel cells (ii) The rate of climb determined are used, means must be incorporated under § 31.17, and the procedures and to indicate to the crew the quantity of conditions used to determine perform- fuel in each cell during flight. The ance; means must be calibrated in appro- (iii) The maximum vertical velocity, priate units or in percent of fuel cell the altitude drop required to attain capacity.
that velocity, and altitude drop re- (2) An envelope temperature indi- quired to recover from a descent at cator.
that velocity, determined under § 31.19, (c) For captive gas balloons, a com- and the procedures and conditions used pass.
to determine performance; and (iv) Pertinent information peculiar [Amdt. 31–2, 30 FR 3377, Mar. 13, 1965, as to the balloon’s operating characteris- amended by Amdt. 31–3, 41 FR 55474, Dec. 20, 1976; Amdt. 31–4, 45 FR 60180, Sept. 11, 1980] tics.
(b) The information established in compliance with paragraph (a) of this section must be furnished by means of— A PPENDIX A TO P ART 31—I NSTRUCTIONS FOR C ONTINUED A IRWORTHINESS (1) A Balloon Flight Manual; or (2) A placard on the balloon that is A 31.1 GENERAL clearly visible to the pilot.
(a) This appendix specifies requirements [Amdt. 31–4, 45 FR 60180, Sept. 11, 1980] for the preparation of Instructions for Con- tinued Airworthiness as required by § 31.82.
§ 31.82 Instructions for Continued Air- (b) The Instructions for Continued Air- worthiness.
worthiness for each balloon must include the Instructions for Continued Airworthiness for The applicant must prepare Instruc- all balloon parts required by this chapter tions for Continued Airworthiness in and any required information relating to the accordance with appendix A to this interface of those parts with the balloon. If part that are acceptable to the Admin- Instructions for Continued Airworthiness are istrator. The instructions may be in- not supplied by the part manufacturer for a complete at type certification if a pro- balloon part, the Instructions for Continued gram exists to ensure their completion Airworthiness for the balloon must include the information essential to the continued prior to delivery of the first balloon or airworthiness of the balloon.
issuance of a standard certificate of (c) The applicant must submit to the FAA airworthiness, whichever occurs later.
a program to show how changes to the In- [Amdt. 31–4, 45 FR 60180, Sept. 11, 1980] structions for Continued Airworthiness made 14 CFR Ch. I (1–1–25 Edition) Pt. 33 by the applicant or by the manufacturers of ness Limitations that is segregated and balloon parts will be distributed. clearly distinguishable from the rest of the document. This section must set forth each A 31.2 FORMAT mandatory replacement time, structural in- spection interval, and related structural in- (a) The Instructions for Continued Air- spection procedure, including envelope struc- worthiness must be in the form of a manual tural integrity, required for type certifi- or manuals as appropriate for the quantity cation. If the Instructions for Continued Air- of data to be provided.
worthiness consist of multiple documents, (b) The format of the manual or manuals the section required by this paragraph must must provide for a practical arrangement.
be included in the principal manual. This A 31.3 CONTENT section must contain a legible statement in a prominent location that reads: ‘‘The Air- The contents of the manual or manuals worthiness Limitations section is FAA ap- must be prepared in the English language.
proved and specifies maintenance required The Instructions for Continued Airworthi- under §§ 43.16 and 91.403 of the Federal Avia- ness must contain the following information: tion Regulations.’’ (a) Introduction information that includes an explanation of the balloon’s features and [Amdt. 31–4, 45 FR 60180, Sept. 11, 1980, as data to the extent necessary for mainte- amended by Amdt. 31–5, 54 FR 34330, Aug. 18, nance or preventive maintenance.
1989] (b) A description of the balloon and its sys- tems and installations.
PART 33—AIRWORTHINESS (c) Basic control and operation informa- tion for the balloon and its components and STANDARDS: AIRCRAFT ENGINES systems.
(d) Servicing information that covers de- Subpart A—General tails regarding servicing of balloon compo- nents, including burner nozzles, fuel tanks, Sec.
and valves during operations.
33.1 Applicability.
(e) Maintenance information for each part 33.3 General.
of the balloon and its envelope, controls, rig- 33.4 Instructions for Continued Airworthi- ging, basket structure, fuel systems, instru- ness.
ments, and heater assembly that provides 33.5 Instruction manual for installing and the recommended periods at which they operating the engine.
should be cleaned, adjusted, tested, and lu- 33.7 Engine ratings and operating limita- bricated, the applicable wear tolerances, and tions.
the degree of work recommended at these pe- 33.8 Selection of engine power and thrust riods. However, the applicant may refer to ratings.
an accessory, instrument, or equipment manufacturer as the source of this informa- Subpart B—Design and Construction; tion if the applicant shows that the item has General an exceptionally high degree of complexity requiring specialized maintenance tech- 33.11 Applicability.
niques, test equipment, or expertise. The rec- 33.13 [Reserved] ommended overhaul periods and necessary 33.15 Materials.
cross references to the Airworthiness Limi- 33.17 Fire protection.
tations section of the manual must also be 33.19 Durability.
included. In addition, the applicant must in- 33.21 Engine cooling.
clude an inspection program that includes 33.23 Engine mounting attachments and the frequency and extent of the inspections structure.
necessary to provide for the continued air- 33.25 Accessory attachments.
worthiness of the balloon.
33.27 Turbine, compressor, fan, and turbo- (f) Troubleshooting information describing supercharger rotor overspeed.
probable malfunctions, how to recognize 33.28 Engine control systems.
those malfunctions, and the remedial action for those malfunctions. 33.29 Instrument connection.
(g) Details of what, and how, to inspect after a hard landing. Subpart C—Design and Construction; (h) Instructions for storage preparation in- Reciprocating Aircraft Engines cluding any storage limits.
(i) Instructions for repair on the balloon 33.31 Applicability.
envelope and its basket or trapeze.
33.33 Vibration.
33.34 Turbocharger rotors.
A 31.4 AIRWORTHINESS LIMITATIONS SECTION 33.35 Fuel and induction system.
The Instructions for Continued Airworthi- 33.37 Ignition system.
ness must contain a section titled Airworthi- 33.39 Lubrication system.