Part 31 — CCAR-31 载人自由气球适航标准

载人自由气球（热气球、飞艇）的适航审定标准。

FAR Part 31 原文

Part 31

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§ 31.1

Applicability.

(a) This part prescribes airworthiness standards for the issue of type certificates 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 applicable requirements of this part.

(c) For purposes of this part—

(1) A captive gas balloon is a balloon 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, suspended 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 envelope for the balloon occupants; and

(6) The design maximum weight is the maximum total weight of the balloon, less the lifting gas or air.

§ 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 reasonably inferred from the weights investigated.

(b) Except as provided in § 31.17(b), allowable weight tolerances during flight testing are + 5 percent and −10 percent.

§ 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 requirement 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 structural loading condition of this part is shown; or

(3) The highest weight at which compliance with each applicable flight requirement of this part is shown.

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

§ 31.16

Empty weight.

The empty weight must be determined by weighing the balloon with installed equipment but without lifting gas or heater fuel.

§ 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 requirements of this section must be shown at each altitude and ambient temperature for which approval is sought.

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

§ 31.19

Performance: Uncontrolled descent.

(a) The following must be determined for the most critical uncontrolled descent that can result from any single failure of the heater assembly, fuel cell system, gas value system, or maneuvering 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 determined in paragraph (a)(1) of this section.

(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 paragraph (a)(3) of this section.

§ 31.20

Controllability.

The applicant must show that the balloon is safely controllable and maneuverable during takeoff, ascent, descent, and landing without requiring exceptional piloting skill.

§ 31.21

Loads.

Strength requirements are specified in terms of limit loads, that are the maximum load to be expected in service, 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 reduced factor of safety of at least two may be used if it is shown that the selected factor will preclude failure due to creep or instantaneous rupture from lack of rip stoppers. The selected factor must be applied to the more critical of the maximum operating pressure or envelope stress.

(c) A factor of safety of at least five must be used in the design of all fibrous or non-metallic parts of the rigging and related attachments of the envelope to basket, trapeze, or other means provided for carrying occupants. The primary attachments of the envelope to the basket, trapeze, or other means provided for carrying occupants must be designed so that failure is extremely 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 operating 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.

§ 31.27

Strength.

(a) The structure must be able to support limit loads without detrimental effect.

(b) The structure must be substantiated by test to be able to withstand the ultimate loads for at least three seconds without failure. For the envelope, 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.

(c) An ultimate free-fall drop test 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, striking 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 occupants. A drop test height of 36 inches, or a drop test height that produces, upon impact, a velocity equal to the maximum vertical velocity determined in accordance with § 31.19, whichever is higher, must be used.

§ 31.31

General.

The suitability of each design detail or part that bears on safety must be established 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. Materials must conform to approved specifications 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 requires close control to reach this objective, 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 structure. Approved locking devices or methods must be used for all these bolts, pins, and screws, unless the installation is shown to be free from vibration. Self-locking nuts may not be used on bolts that are subject to rotation in service.

§ 31.39

Protection.

Each part of the balloon must be suitably protected against deterioration 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.

§ 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 surrounding 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 become typical of the member.

(c) The fitting factor need not be used if the joint design is made in accordance 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 supporting structure must be shown by tests to be capable of withstanding, without detrimental distortion or failure, any inertia loads to which the installation 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.

§ 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.

§ 31.47

Burners.

(a) If a burner is used to provide the lifting means, the system must be designed and installed so as not to create a fire hazard.

(b) There must be shielding to protect parts adjacent to the burner flame, and the occupants, from heat effects.

(c) There must be controls, instruments, 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 operation.

(d) The burner system (including the burner unit, controls, fuel lines, fuel cells, regulators, control valves, and other related elements) must be substantiated by an endurance test of at least 40 hours. Each element of the system 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 referenced 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 operation.

(2) The test program for the secondary or backup operation of the burner must include six hours of operation with a burn time for each five minute cycle of one minute at an intermediate fuel pressure.

(e) The test must also include at least three flameouts and restarts.

(f) Each element of the system must be serviceable at the end of the test.

§ 31.49

Control systems.

(a) Each control must operate easily, smoothly, and positively enough to allow proper performance of its functions. Controls must be arranged and identified to provide for convenience of operation and to prevent the possibility of confusion and subsequent inadvertent operation.

(b) Each control system and operating device must be designed and installed in a manner that will prevent jamming, chafing, or interference from passengers, cargo, or loose objects. Precaution must be taken to prevent foreign objects from jamming the controls. The elements of the control system must have design features or must be distinctly and permanently marked to minimize the possibility of incorrect assembly that could result in malfunctioning of the control system.

(c) Each balloon using a captive gas 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 balloon is at its maximum operating pressure.

(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 envelope skin temperatures occurring during operation. The indicator must be readily visible to the pilot and marked to indicate the limiting safe temperature 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.

§ 31.51

Ballast.

Each captive gas balloon must have a means for the safe storage and controlled release of ballast. The ballast must consist of material that, if released 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 becoming 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.

§ 31.57

Rip cords.

(a) If a rip cord is used for emergency deflation, it must be designed and installed to preclude entanglement.

(b) The force required to operate the rip cord may not be less than 25, or more than 75, pounds.

(c) The end of the rip cord to be operated by the pilot must be colored red.

(d) The rip cord must be long enough to allow an increase of at least 10 percent 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 trapeze, 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 bonding means in the design of each balloon using flammable gas as a lifting means to ensure that the effects of static discharges will not create a hazard.

§ 31.63

Safety belts.

(a) There must be a safety belt, harness, or other restraining means for each occupant, unless the Administrator 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 balloons that incorporate a basket or gondola.

§ 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° horizontal coverage at the intensities prescribed in this paragraph. The following light intensities must be determined with the light source operating at a steady state and with all light covers and color filters in place and at the manufacturer's rated minimum voltage. For the flashing aviation red light, the measured values must be adjusted to correspond to a red filter temperature of at least 130 °F:

(1) The intensities in the horizontal plane passing through the light unit must equal or exceed the following values:

(2) The intensities in vertical planes must equal or exceed the following values. An intensity of one unit corresponds to the applicable horizontal plane intensity specified in paragraph (b)(1) of this section.

(c) The steady white light must be located not more than 20 feet below the basket, trapeze, or other means for carrying 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 Commission on Illumination chromaticity coordinates as follows:

(1) Aviation red —

(2) Aviation white —

§ 31.71

Function and installation.

(a) Each item of installed equipment must—

(1) Be of a kind and design appropriate 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 limitations specified for that equipment; and

(4) Function properly when installed.

(b) No item of installed equipment, when performing its function, may affect the function of any other equipment so as to create an unsafe condition.

(c) The equipment, systems, and installations must be designed to prevent hazards to the balloon in the event of a probable malfunction or failure.

§ 31.81

General.

(a) The following information must be established:

(1) Each operating limitation, including the maximum weight determined under § 31.14.

(2) The normal and emergency procedures.

(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 performance;

(iii) The maximum vertical velocity, the altitude drop required to attain that velocity, and altitude drop required 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 characteristics.

(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.

§ 31.82

Instructions for Continued Air­worthiness.

The applicant must prepare Instructions for Continued Airworthiness in accordance with appendix A to this part that are acceptable to the Administrator. The instructions may be incomplete at type certification if a program exists to ensure their completion prior to delivery of the first balloon or issuance of a standard certificate of airworthiness, whichever occurs later.

§ 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 banners 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 balloon conspicuous during flight.

§ 31.85

Required basic equipment.

In addition to any equipment required by this subchapter for a specific kind of operation, the following equipment 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 appropriate units or in percent of fuel cell capacity.

(2) An envelope temperature indicator.

(c) For captive gas balloons, a compass.

CCAR-31 原文

CCAR-31

来源: 官方全文

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載人自由氣球適航規定 來源：中國民航局 列印本頁 中國民用航空總局令 第181號 《載人自由氣球適航規定》已經2007年3月13日中國民用航空總局局務會議通過，現予公佈，自2007年4月15日起施行。 局長 楊元元 二〇〇七年三月十五日 A章 總則 適用範圍 第31.1條 (a) 本部規定頒發載人自由氣球型號合格證及其更改的適航標準。 (b) 按照中國民用航空規章第21部的規定申請或更改該型號合格證的法人，必須表明符合本部中適用的要求。 (c) 本部中： (1) 輕氣球是靠輕於空氣的氣體産生升力的氣球； (2) 熱氣球是靠熱空氣産生升力的氣球； (3) 球囊是用於包容升力物質的包殼； (4) 吊籃是吊于球囊下用於載人的容器； (5) 吊架是懸挂于球囊下用於載人的索帶或者有水準扶桿或平板的座椅； (6) 最大設計重量是氣球的最大總重量減去升力氣體或者空氣的重量。 B章 飛行要求 符合性驗證 第31.12條 (a) 在申請合格審定的載重狀態範圍內，對每一重量，都必須滿足本章的每一要求。這必須有如下方法表明： (1) 申請合格審定的該型號的氣球的試驗，或根據試驗結果有同樣準確性的計算； (2) 如果從所審查的重量不能合理地推論符合性，則對各重量進行系統的審查。 (b) 除第31.17條(b)的規定外，在飛行試驗中允許的重量允差為+5%及－10%。 第31.14條 重量限制 (a) 必須明確規定氣球可以安全工作的重量範圍。 (b) 最大重量。最大重量是符合本部每一適用要求的最重的重量。最大重量必須確定並且不超過： (1) 申請人選擇的最重的重量； (2) 最大設計重量——符合本部每一適用結構載荷條件的最重的重量； (3) 符合本部每一適用飛行要求的最重的重量。 (c) 必須將(a)、(b)所規定的內容按照第31.81條的要求提供給駕駛員。 第31.16條 空重 空重必須是在裝有設備但無升力氣體或者燃料的情況下稱得的氣球重量。 第31.17條 性能：上升 (a) 每個氣球必須能在起飛(離地)後的第一分鐘內以穩定速率上升至少91.44米(300英尺)。必須在申請批准的每一高度及環境溫度下證明符合本條的要求。 (b) 必須在最大重量增加5%的情況下證明符合(a)的要求。 第31.19條 性能：無操縱下降 (a) 必須在燃燒器組件、燃料箱系統、燃氣控制系統或操縱放氣系統中任何單一失效或在止裂帶間球囊的任何單個撕裂可能導致的最危險的非操縱下降情況下確定以下數據： (1) 所達到的最大垂直速度； (2) 從失效發生點到獲得最大垂直速度點的高度損失； (3) 以本條(a)(1)所定的最大垂直速度下降的氣球從開始糾正操作到實現水準飛行所需的高度。 (b) 必須規定以本條(a)(1)所確定的最大垂直速度著陸的程式及按本條(a)(3)停止下降的程式。 第31.20條 操縱性 申請人必須表明，氣球在起飛、上升、下降及著陸期間可以安全地操縱和進行機動而不需特殊的駕駛技術。 C章 強度要求 載荷 第31.21條 強度要求根據限制載荷與極限載荷確定。限制載荷指使用中可能出現的最大載荷。極限載荷為限制載荷乘以規定的安全系數。除非另有規定，所有規定的載荷均為限制載荷。 第31.23條 飛行載荷系數 在確定限制載荷時，限制飛行載荷系數必須至少為1.4。 第31.25條 安全系數 (a) 除本條(b)、(c)規定外，安全系數為1.5。 (b) 球囊設計中，安全系數必須至少為5。如果能表明所選擇的系數將能防止由於缺少止裂帶而發生漸進或暫態撕裂造成的故障，則安全系數可以減小，但至少為2。所選用的系數必須應用於更臨界的最大工作壓力或球囊應力。 (c) 設計球囊與吊籃、吊架或其他載人器具的索具及相關連接件的所有纖維質或非金屬件時，安全系數必須至少為5。球囊與吊籃、吊架或其他載人器具間的主要連接件的設計，必須使得故障極不可能發生或任何單一故障將不影響飛行安全。 (d) 在應用安全系數時，必須考慮可能影響氣球強度的溫度和其他使用特性或者兩者同時作用的影響。 (e) 設計中，每一乘員的重量必須至少為77.112千克(170磅)。 第31.27條 強度 (a) 結構必須能承受限制載荷而無有害影響。 (b) 必須經試驗證明，結構能承受極限載荷至少3秒鐘而不失效。對於球囊，如果某個有代表性的部分足夠大，能夠包括關鍵接縫、接頭及承載連接點及構件，則可以用此部分進行試驗。 (c) 必須進行吊籃、吊架或其他載人器具的極限自由落震試驗。試驗必須用吊籃、吊架或其他載人器具，在水準面上以最大設計重量進行。應分別以0°、15°、30°撞擊地面。重量分佈可以模擬實際情況。不允許可能導致乘員嚴重受傷的變形或失效。必須用下列高度中的較大者進行落震實驗： (1) 0.9144米(36英寸)； (2) 使得撞擊時的速度等於第31.19條確定的最大垂直速度的高度。 D章 設計構造 總則 第31.31條 每個影響安全的設計細節或零件的適用性必須通過試驗或分析確定。 第31.33條 材料 (a) 所有材料的適用性和耐久性都必須建立在經驗或試驗的基礎上。材料必須符合批准的標準，以保證這些材料具有設計資料中採用的強度和其他性能。 (b) 材料的強度特性必須以符合標準的材料的足夠試驗為依據，以便在統計的基礎上確定設計值。 第31.35條 製造方法 採用的製造方法必須能生産出一個始終完好的結構。如果某種製造工藝需要嚴格控制才能達到此目的，則該工藝必須按照經批准的工藝規範執行。 第31.37條 緊固件 只有經過批准的螺栓、銷釘、螺釘和鉚釘才可用於結構中。必須對所有這些螺栓、銷釘和螺釘採用批准的鎖定裝置或方法，除非表明其安裝不承受振動。自鎖螺母不能用於工作中經受轉動的螺栓。 第31.39條 保護 氣球的每個部分都必須適當地保護，防止在工作中由於氣候、腐蝕或其他原因造成性能降低或強度喪失。 第31.41條 檢查措施 必須有措施，使能夠對每個要求反覆檢查和調整的零件進行接近檢查。 第31.43條 接頭系數 (a) 在分析每個未經限制載荷和極限載荷試驗(試驗時在接頭和周圍結構上模擬實際應力狀態)以證實其強度的接頭時，接頭系數至少取1.15。這一系數適用於接頭本體、連接手段和連接構件支承部位的所有零件。 (b) 對於整體接頭，一直到截面性質成為其構件典型截面為止的部分必須作為接頭處理。 (c) 如果接頭設計以批准的方法和全面的試驗數據為依據，則不必採用接頭系數。 第31.45條 燃料箱 如果採用燃料箱，則必須用試驗表明燃料箱、燃料箱連接件和有關的支撐結構能夠經受整套裝置所可能受到的任何慣性載荷，包括第31.27條(c)中規定的落震試驗，不會産生有害的變形或失效。試驗時，燃料箱必須載入到與滿燃料狀態相等的重量和壓力。 第31.46條 增壓燃料系統 對於增壓燃料系統，每個元件和它的連接接頭和導管必須試驗到極限壓力，該壓力至少為系統正常工作時所承受最大壓力的兩倍。試驗期間，無任何系統零件失效或故障。試驗構形必須能代表正常燃料系統的安裝和氣球構形。 第31.47條 燃燒器 (a) 如果使用燃燒器作為提供升力的裝置，則系統必須設計和安裝成不致有著火的危險。 (b) 必須有防護裝置，防止乘員和靠近燃燒器火焰的零件受熱影響。 (c) 必須有控制器件、儀錶或其他安全控制和使用燃燒器所必需的設備。必須表明它們在正常和應急工作時能夠完成預定的功能。 (d) 燃燒器系統(包括燃燒器單元、控制器件、燃料管、燃料箱、調節器、控制閥和其他相關元件)必須經受至少40小時的持久試驗驗證。試驗時，系統的每個元件都必須安裝並經受試驗，以模擬真實的氣球安裝和使用。 (1) 對燃燒器的主火焰控制活門使用的試驗大綱必須包括： (i) 在申請批准的最大燃料壓力下工作5小時，每分鐘迴圈內有3至10秒進行燃燒。燃燒時間的確定應使得每個燃燒器上受溫度影響的元件遭受最大的熱衝擊； (ii) 在中等燃料壓力下工作7.5小時，每分鐘迴圈內有3至10秒進行燃燒。中等燃料壓力為本條(d)(1)(i)中最大燃料壓力和本條(d)(1)(iii)中最小燃料壓力之間的40％到60％； (iii) 在申請批准的最小燃料壓力下工作6小時15分鐘，每分鐘迴圈內有3至10秒進行燃燒； (iv) 在使用燃料蒸汽燃燒的情況下工作15分鐘，每分鐘迴圈內至少30秒進行燃燒； (v) 15小時的正常飛行操作。 (2) 對燃燒器輔助或備用火焰控制活門使用的試驗大綱應當包括：在中等燃料壓力下工作6小時燃料，每5分鐘迴圈內有1分鐘進行燃燒。 (e) 試驗還必須包括至少3次熄火和再起動。 (f) 試驗結束時，系統的每個元件必須是可用的。 第31.49條 操縱系統 (a) 每一操縱器件的操作必須簡便、平穩和確切以正確地完成其功能。操縱器件的佈局和標識必須方便操作，防止混淆和隨之發生誤動的可能性。 (b) 每個操縱系統和操縱裝置必須設計和安裝成能夠防止因乘員、貨物和鬆散物引起的卡阻、摩擦、干擾。必須採取預防措施防止外來物卡阻操縱器件。操縱系統元件必須具有某種設計特徵或做出明顯的永久性標記，使可能導致操縱系統故障的不正確裝配的可能性減至最小。 (c) 每個以充輕氣提供升力的氣球必須有一個能自動釋放氣體的自動閥或通氣管，當氣球在最大工作壓力時，放氣速率每分鐘至少為總容積的3％。 (d) 每個熱氣球必須有一個裝置，使得在飛行期間可有控制地釋放熱空氣。 (e) 每個熱氣球必須有一個裝置來指示飛行期間球囊表面最高溫度。螢幕必須容易被駕駛員看到，並應有指示球囊材料安全限制溫度的標記。如果標記在儀錶玻璃罩上，必須採取措施使玻璃罩與刻度盤對準。 第31.51條 壓艙物 每個輕氣球必須有一個安全存放和可控制地釋放壓艙物的裝置。壓艙物必須由在飛行中釋放時不會對地面人員造成危害的材料組成。 第31.53條 阻力繩 如果使用阻力繩，氣球外的自由端必須硬化，防止其與樹木、電線或地面上的其他物體纏繞。 第31.55條 放氣裝置 必須有一個可使球囊應急放氣的裝置保證安全的應急著陸。如果使用人工放氣系統之外的放氣系統，則必須證明其可靠性。 第31.57條 球囊拉索 (a) 如果使用了球囊拉索來應急放氣，拉索的設計和安裝必須能夠防止纏繞。 (b) 操縱球囊拉索所需的力不小于11.34千克(25磅)，不大於34.02千克(75磅)。 (c) 由駕駛員使用的球囊拉索末端必須為紅色。 (d) 球囊拉索必須足夠長，以允許球囊在垂直方向上的尺寸至少增加10％。 第31.59條 吊架、吊籃或其他載人器具 (a) 吊架、吊籃或其他載人器具不能有相對於球囊的旋轉。 (b) 吊架、吊籃或其他載人器具上可能傷害乘員的凸出物必須包裹。 第31.61條 靜電放電 除非表明對安全是不必要的，否則在設計每個以可燃氣體為升力物質的氣球時，必須有適當的搭接手段，以確保靜電放電不會引起危險。 第31.63條 安全帶 (a) 每個乘員必須有安全帶、肩帶或其他約束手段，除非局方認為其不必要。如果被安裝，則這些安全帶、肩帶或其他約束手段及其支撐結構必須滿足本部C章的強度要求。 (b) 本條不適用於裝有吊籃或吊艙的氣球。 第31.65條 航行燈 (a) 如果安裝航行燈，必須有一個穩定的航空白色航行燈和一個閃光的航空紅色(或閃光的航空白色)航行燈，有效閃光頻率至少為40次/分，但不超過100次/分。 (b) 每個航行燈必須按本條規定的光強具有360°的水準作用範圍。下列的光強必須在使用穩態工作光源、安裝所有的燈罩和濾色鏡並且在製造人規定的最小電壓下確定。對於閃光航空紅色燈，測量值必須調整到對應至少130℉的紅色濾光鏡溫度。 (1) 通過光源的水準面上的光強必須等於或超過下列值： 航行燈 最小光強(燭光) 穩定白色 20 閃光紅色或白色 40 (2) 在垂直平面上的光強必須等於或超過下列值。一個單位的光強對應于本條(b)(1)條所規定的相應水準面的光強。 在垂直平面內與 水準面的夾角(度) 最小光強(單位) 0° 1.00 0°－5° 0.90 5°－10° 0.80 10°－15° 0.70 15°－20° 0.50 20°－30° 0.30 30°－40° 0.10 40°－60° 0.05 (c) 穩定的白色燈必須安裝在吊籃、吊架或其他載人器具以下不超過6.096米(20英尺)處。閃光紅色或白色燈必須安裝在穩定白色燈以下不小于2.1336米(7英尺)，且不大於3.048米(10英尺)處。 (d) 必須有收上和存放燈具的裝置。 (e) 每個航行燈的顏色必須具有國際照明委員會規定的相應色度坐標值： (1) 航空紅色 “y”不大於0.335； “z”不大於0.002。 (2) 航空白色 “x”不小于0.300且不大於0.540； “y”不小于“x－0.040”或“yo?0.010”,取小者； “y”不大於“x+0.020”，也不大於“0.636?0.0400x”； 其中，“yo”為普朗克輻射器相對於“x”值的“y”坐標值。 E章 設備 功能與安裝 第31.71條 (a) 安裝的每項設備必須符合下列要求： (1) 種類和設計與預定功能相適應； (2) 作永久和明顯的標記，如果零件太小而難以作標記，則用標簽標明其名稱、功能或使用限制或這些因素的任何組合； (3) 按對該設備規定的限制進行安裝； (4) 安裝後功能正常。 (b) 所安裝的每項設備，不允許影響任何其他設備的功能以致于産生不安全狀態。 (c) 設備、系統和安裝必須設計成能防止在發生可能的故障或失效情況下對氣球的危害。 F章 使用限制與資料 總則 第31.81條 (a) 必須制定下列資料： (1) 每一使用限制，包括第31.14條所確定的最大重量； (2) 正常和應急程式； (3) 其他安全操作所必需的資料，包括： (i) 按第31.16條確定的空重； (ii) 按第31.17條確定的上升速率以及用來確定該性能的程式和條件； (iii) 按第31.19條確定的最大垂直速度、達到該速度所需的下降高度、從該速度改出所需的下降高度，以及用於確定這些性能的程式和條件； (iv) 因氣球的使用特性而特有的有關資料。 (b) 按本條(a)制定的資料，必須以下列形式之一提供： (1) 氣球飛行手冊； (2) 氣球上能被駕駛員清晰看見的標牌。 第31.82條 持續適航文件 申請人必鬚根據本部附錄A編制局方可接受的持續適航文件。如果有計劃保證在交付第一架氣球之前或者在頒發標準適航證之前完成這些文件，則這些文件在型號合格審定時可以是不完備的。 第31.83條 識別 球囊的外表面必須有一種或多種反差明顯的顏色，使其在使用期間清晰可見。也可用多色的彩旗或飄帶，只要能表明其足夠大且有足夠的色彩反差使得氣球在飛行中明顯可見。 第31.85條 要求的基本設備 除適航規章對特定使用類型要求的設備外，還要求如下設備： (a) 對所有氣球： (1) [備用] (2) 高度表； (3) 升降速度表。 (b) 對熱氣球： (1) 燃料量表，如果使用燃料箱則必須具有在飛行中向操作人員指示每個燃料箱燃料量的裝置，該裝置必須以適當單位的刻度指示或以燃料箱容積的百分比指示； (2) 球囊溫度指示器。 (c) 對輕氣球：羅盤。 G章 附則 施行日期 第31.91條 本規定自2007年4月15日起施行。 附錄A 持續適航文件 第A31.1條 總則 (a) 本附錄規定了第31.82條所要求的持續適航文件的編制要求。 (b) 氣球的持續適航文件必須包括中國民用航空規章要求的氣球各部件的持續適航文件，以及所需的有關這些部件與氣球相互連接關係的資料。如果部件製造人未提供部件的持續適航文件，則氣球的持續適航文件必須包括這些對此氣球的持續適航性必不可少的資料。 (c) 申請人必須向局方提交一份文件，説明如何分發由申請人或部件製造人制定的持續適航文件的更改資料。 第A31.2條 格式 (a) 必鬚根據所提供資料的數量將持續適航文件編成一本或多本手冊。 (b) 手冊的編排格式必須實用。 第A31.3條 內容 手冊的內容必須用中文編寫。持續適航文件必須含有下列資料： (a) 説明性資料，包括在維修或預防性維修所需範圍內對氣球特點和數據的説明。 (b) 氣球及其系統和安裝的説明。 (c) 氣球及其部件和系統的基本操作和使用資料。 (d) 維護資料，包括有關在使用中維護氣球各部件(包括燃燒器噴口、燃料箱及閥門)的詳細資料。 (e) 氣球及其球囊、操縱裝置、索具、吊籃結構、燃料系統、儀錶和燃燒器組件的每一部分的定期維修資料，提供對上述各項進行清洗、調整、試驗和潤滑的薦用週期、適用的磨損容差和在這些週期內推薦的工作內容。但是，如果申請人表明某項附件、儀錶或設備非常複雜，需要專業化的維修技術、測試設備或專業技術處理，則申請人可以註明向該件的製造人索取上述資料。薦用的翻修週期和本文件適航限制條款必要的相互參照也必須列入。此外，申請人必須提交一份包含氣球持續適航性所需的檢查頻度和範圍的檢查大綱。 (f) 説明可能發生的故障，如何判別這些故障以及對這些故障採取補救措施的檢查排故資料。 (g) 重著陸後檢查項目和如何檢查的詳細資料。 (h) 包括貯存限制的貯存資料。 (i) 球囊及吊籃或吊架的修理資料。 第A31.4條 適航限制條款 持續適航文件必須包含題為適航限制的條款，該條應單獨編排並與文件的其他部分明顯地區分開來。該條必須規定強制性的更換時間、結構檢查時間間隔、有關結構檢查程式以及型號合格審定要求的球囊結構的完整性。如果持續適航文件由多本文件組成，則本條要求的條款必須編在主要手冊中。必須在該條顯著位置清晰説明：“本適航限制條款已經中國民用航空總局批准，規定了中國民用航空規章有關維護和營運的條款所要求的維修。” 附件： 載人自由氣球適航規定

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