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CTSO-C79
火警探测器（辐射敏感型）
CTSO
C79
火警
探测器
辐射
敏感
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CTSO-C79 火警探测器（辐射敏感型）,CTSO-C79,火警探测器（辐射敏感型）,CTSO,C79,火警,探测器,辐射,敏感
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编 号：CTSO-C79 日 期：2019 年 6 月 4 日 局长授权 批 准： 中国民用航空技术标准规定 - 1 - 本技术标准规定根据中国民用航空规章民用航空材料、零部件和机载设备技术标准规定 （CCAR37）颁发。中国民用航空技术标准规定是对用于民用航空器上的某些航空材料、零部件和机载设备接受适航审查时，必须遵守的准则。 火警探测器（辐射敏感型） 1. 目的 本技术标准规定（CTSO）适用于为火警探测器（辐射敏感型）申请技术标准规定项目批准书（CTSOA）的制造人。本 CTSO 规定了火警探测器（辐射敏感型）为获得批准和使用适用的 CTSO 标记进行标识所必须满足的最低性能标准。 2. 适用范围 本 CTSO 适用于自其生效之日起提交的申请。 按本 CTSO 批准的设备，其设计大改应按 CCAR-21-R4 第 21.353 条要求重新申请CTSOA。 3. 要求 在本CTSO生效之日或生效之后制造并欲使用本CTSO标记进行标识的火警探测器（辐射敏感型）应满足附录 1 中的最低性能标准。 CAAC CTSO-C79 - 2 - 4. 标记 标记应包括 CCAR-21-R4 第 21.423 条（二）规定的所有信息，还应标出火警探测器的工作电压。符合活塞式、涡轮式发动机的要求或者两者兼之的探测器应在 CTSO 编号之后分别添加尾标-P、 -T 或者-PT，例如：CTSO-C79-P。 5. 资料要求 申请人必须向负责该项目审查的人员提交相关技术资料以支持设计和生产批准。提交资料包括 CCAR-21-R4 第 21.353 条（一）1规定的符合性声明和以下资料副本。 a. 技术资料包括： （1）运行说明和设备限制。 （2）安装程序，包括适用的安装原理图、布线图和规范，说明与安装有关的任何限制或其它条件。 （3）试验报告。 b. 第 a(1)和 a(2)所要求的资料应包括： （1）以度数表示的视锥（视锥的顶点在传感器的中心，视锥的轴线与传感器的面成直角)。 （2）视域边界的最大有效范围； （3）探测器位置处的最大允许正常环境温度； （4）正常运行时探测器位置处的最大温升和最小温升允许速率； （5）工作电压； CAAC CTSO-C79 - 3 - （6）安装或者支撑方法； （7）在不影响灵敏度或因温度而造成错误指示的情况下，可在一个回路或一个防火区内使用的最多或最少装置数目； （8）探测器位置处的最大允许振动； （9）由于磁效应造成的安装限制（最小距离） ； （10）射频峰值电压及对应频率； （11）设备是否适用于增压区、非增压区或两者兼容； （12）第 7.3.3、7.3.4、7.3.5 和 7.3.6 段中哪些情况对探测器有不利影响； （13）探测器是否符合 7.14 段的耐火要求。 CAAC CTSO-C79 - 4 - 附录 1 火警探测器（辐射敏感型）最低性能标准 1.0 目的目的 规定用于活塞发动机和涡轮发动机航空器动力装置的火警探测器的最低要求，航空器的运行使该仪器经受 3.3 规定的环境条件。 2.0 范围范围 本标准包括了辐射敏感“监视”型火警探测器的验收要求，探测器的用途是为了保护可能着火处的航空器动力装置安装、 辅助动力装置、燃烧加温器及其他的安装。在本文件中， “仪器”应理解为火警系统及其所有组件。 2.1 定义定义 辐射敏感型火警探测器是一种仪器，在遭受火焰放出的辐射能时，即开始发出警告信号。探测器及相关路线可设计成能针对以下一些因素进行选择：光谱敏感度，对探测器的辐射度，辐射度的上升率或辐射度起伏（闪烁）的频率特性，或其他的火焰特性。 3.0 一般要求一般要求 3.1 材料和工艺材料和工艺 3.1.1 材料材料 材料应具有经验和（或）试验证明能可靠地适用于航空仪器的质量。 3.1.2 工艺工艺 工艺应符合高级航空仪器的制造方法。 3.2 暂缺暂缺 3.3 环境条件环境条件 以下条件规定作为设计最低要求。试验应按 5、6 和 7条的规定进行。 CAAC CTSO-C79 - 5 - 3.3.1 温度温度 按制造人建议方法安装的仪器，应能在 A 栏所示周围温度范围内正常工作。 仪器安装位置 A 动力装置舱（活塞式） -30+130 动力装置舱（涡轮式） -30+150 增压区（两种类型的发动机） -30+50 非增压区或外部区（两种类型的发动机）-55+70 如果拟装用此仪器的舱最高周围温度高于 130（对于活塞发动机）和高于 150（对于涡轮发动机） ，或者如果预计周围温度低于 A栏的规定值，则制造人应选择并规定相应的特殊限制。 3.3.2 湿度湿度 仪器暴露在约70温度下相对湿度在095%范围的环境时，应正常工作，不造成不利影响，也不受到不利影响。 3.3.3 高度高度 按制造人说明书安装的仪器应正常工作，并不受相当于高度范围-1000+50000 英尺所经受的压力条件的不利影响，高度压力按 NACA1235 号报告的规定。 3.3.4 振动振动 按制造人说明书安装的仪器， 在经受下述特性的振动时，应正常工作，不造成不利作用，也不受到不利影响。 频率（周/秒） 最大全幅（英寸）最大加速度 活塞发动机 装在机体结构上 5500 0.050 10g 装在减震板上 550 0.020 1.5g 装在动力装置上 5500 0.100 20g 涡轮发动机 短舱和短舱支架、机翼、 尾翼和轮舱51000 0.036 10g 机身： 翼梁区之前 5500 0.036 2g CAAC CTSO-C79 - 6 - 翼梁区中间 51000 0.036 4g 翼梁区之后 5500 0.036 7g 5001000 5g 隔振区 550 0.020 1.5g 安装架 50500 0.5g 仪表板 5500 0.030 1.0g 3.3.5 液体和砂尘液体和砂尘 仪器暴露在雨水、燃油、盐雾、滑油或砂尘中时不得受到不利影响。 3.4 无线电干扰无线电干扰 应确定并规定因射频发射而造成的安装限制。 3.5 磁效应磁效应 应确定并规定因磁场而造成的安装限制。 4.0 详细要求详细要求 4.1 指示方式指示方式 仪器应能启动目视和（或）音响警告指示器。 4.2 可靠性可靠性 仪器应设计成能承受其在航空器上使用时易遭遇到的机械冲击、热冲击以及应力。航空器运行过程中遭遇到的电压变化，异常的高度，大气的污染，周围照明条件，飞行、着陆和起飞过程中遭遇到的加速度力，均不应造成假的警告信号。在航空器正常运行条件和大气条件的任何组合下，火警探测器不得发出假警告，探测器的灵敏度不得受到装有传感器的航空器舱内周围照明的明显影响。 旨在确定上述各种因素对探测器可靠性影响的试验详述于 7.3。 4.3 完整性试验方法完整性试验方法 仪器应设计成能提供在飞行中试验电气线路连接性和功能性的方法。 4.4 校准方法校准方法 仪器应设计成具有带耐敲打密封件的校准方法。 4.4.1 可调探测器系统可调探测器系统 具有调节手段的仪器应进行试验， 证明在整个CAAC CTSO-C79 - 7 - 调节范围内均符合本标准，特别是 7.1、7.1.1 和 7.3。 5.0 试验条件试验条件 5.1 大气条件大气条件 除另有规定者外，本标准要求的所有试验均应在约29.92 英寸汞柱大气压力、约 25周围温度和不大于 85%的相对湿度的条件下进行。 5.2 振动振动 除另有规定者外，所有性能试验可在仪器经受 0.0020.005英寸全幅， 15002000 周/分频率的振动条件下进行。 此处使用的术语“全幅”表示从正最大到负最大的总位移。 5.3 振动设备振动设备 振动设备应能沿仪器相互垂直的三根轴线的每一根施加振动，其频率和幅度按 3.3.4 的要求。 5.4 电源条件电源条件 除另有规定者外，所有试验应以制造人推荐的额定电源进行试验，试验时仪器应处于实际工作状态。 5.5 试验位置试验位置 除另有规定者外，仪器应按其正常工作位置进行安装和试验。 6.0 单项性能要求单项性能要求 所有仪器或其组件应经受制造人的试验，证明具体符合本标准的以下各项要求（视适用情况而定） 。 6.1 灵敏度和校准灵敏度和校准 传感器应按 7.1 的规定进行试验， 确定其响应灵敏度和校准。 6.2 介电性介电性 每一仪器应采用 6.2.1 和 6.2.2 的检查方法进行试验。 6.2.1 绝缘电阻绝缘电阻 所有相互连通的电气线路和金属外壳之间的绝缘电阻， 在 200 伏直流电接入 5 秒钟后， 不得低于 5 兆欧。 当线圈、 电阻、电容等一类元件两端出现电位时，不得测量线路的绝缘电阻，因为这CAAC CTSO-C79 - 8 - 种测量仅是为了确定绝缘是否足够。 6.2.2 过电位试验过电位试验 在电气线路之间和电气线路与金属外壳之间施加试验电位时，设备不得损坏。试验电位应是商用频率的正弦波电压，其均方根值是最高线路电压的 5 倍，或者按 6.2.2.1 或 6.2.2.2 的规定（以适用者为准） 。电位应从零开始，以均匀的速率增加到其试验值。在此值上应保持 5 秒钟，然后以均匀的速率降低到零。 由于这种试验是为了保证该线路组件具有合适的电气绝缘性， 因此当线圈、电阻、电容等一类元件两端出现电位时，对线路不得进行这种试验。 6.2.2.1 气密的仪器应从 200 伏（有效值）进行试验。 6.2.2.2 以低于 15 伏电位工作的线路不必经受过电位试验。 7.0 鉴定性能要求鉴定性能要求 应当按照制造人的建议，取必要数量的仪器进行试验，来证明所有仪器均符合本条的要求。每个仪器上的试验应按下述顺序依次进行，而且在试验开始后，不再对仪器进行调整。任一项试验中如果出现虚假警告信号，该仪器即不合格。除了 7.2、7.2.1、7.2.3 和 7.14 的试验外，每一项试验后均应进行 7.1 规定的响应时间试验。在进行 7.14 的试验时，被试验的仪器不必是经受整个系列鉴定试验的同一个仪表。 7.1 响应时间响应时间 仪器的传感器应朝向在直径 5 英寸的平盘中燃烧汽油所形成的火焰，相距 4 英尺，供入的空气最大流率为 10 英尺/秒。每次试验开始时汽油和盘的温度不得超过 85。应使用无色无铅汽油，响应时间不得超过 5 秒钟。 CAAC CTSO-C79 - 9 - 7.1.1 饱和试验饱和试验 传感器应面朝下安装在直径 2 英尺的平盘上方， 距平盘中心约 3 英寸，盘内盛有高出盘底的 1/8 英寸的汽油。汽油应使用传感器探测不出的火源点燃。响应时间不得超过 5 秒钟，当经受此试验 1 分钟时间过程中系统不得清除掉警告信号。 7.1.2 反复响应时间反复响应时间 火警探测器的传感器应按 7.1 规定朝向火焰 1 分钟。然后应防止其感受到火焰的影响。在清除掉警告信号后的 5 秒钟内，应将传感器再次朝向火焰。应在 5 秒内发出警告信号。 7.2 温升率造成的假警告温升率造成的假警告 7.2.1 和 7.2.2 所述的试验应在温度受控制的空气气流条件下进行，气流速度为 25025 英尺/分。此项试验的仪器应具有单个控制装置可配备的最大数目传感器的完整控制装置。 不应发出警告信号。 7.2.1 局部升温局部升温 一个传感器应经受图 3(a)阴影区所述温升率与持续时间的不同组合。其他的传感器应维持在周围室温下。试验的进行应模拟局部过热条件。不应发出警告信号。 7.2.2 普遍升温普遍升温 应利用图 3(b)重复进行 7.2.1 的试验，不同处是所有传感器均应同时经受温度的变化。 试验的进行应模拟在装有传感器的舱内普遍升温的条件。不应发出警告信号。 7.2.3 部分灭火造成的假清除警告部分灭火造成的假清除警告 仪器按 7.1 置于响应时间试验状态，试验火焰应施加 30 秒钟。然后将试验火焰遮挡成使其作用区减少约 50%。警告信号不得清除。再过 30 秒钟后，应将火焰完全去除，警告信号应在 10 秒钟内清除。 7.3 确立特殊环境条件下探测器可靠性的试验程序确立特殊环境条件下探测器可靠性的试验程序 以下试验程序应CAAC CTSO-C79 - 10 - 适用于确立各种不利条件下探测器系统可靠性的试验。进行试验时，系统应含有具体试验条件下所要求的临界数目的传感器。 7.3.1 暂缺暂缺 7.3.2 镁焰镁焰 利用 7.1 所述的试验设备和安装方式，将一根长 6 英寸、宽约 1/8 英寸、厚 0.005 英寸的镁带放在传感器元件和火焰之间的中央点处，与传感器成一条直线。点燃汽油，当警告灯发亮时，点燃镁带。当镁或汽油或两者均在燃烧时，警告信号不应清除。 7.3.3 日光日光 试验时日光应直接照射 （不通过关闭的窗户） 到探测器上，且太阳的天顶角应在 45以内，使穿过大气的斜线照径不致过长。照度应为 5000 英尺坎德拉或以上，测光计探头应朝向太阳。探测器应暴露在日光下 30 秒钟而不会启动警告装置。 7.3.4 断续阳光断续阳光 在此项试验中，应使用光阑叶系统来调制阳光（见7.3.3） ，使其频率范围为 100 周/秒到 0 周/秒。这一频率范围应来回扫掠足够长的时间， 使得在范围内的任何一频带上都有几秒钟的停顿时间。 令人满意的断续措施可以是在小型通用绕线电动机的轴上安装一个有 4 片叶片的光阑， 电动机的工作电源为一连续可调自耦变压器或其他的可调电压源。光阑的叶片要足够大，从而在位于探测器前方时能完全遮住太阳，使其照射不到探测器上，而且叶片距离探测器不得超过 1 英寸，使来自天空的日光本身也将得到调制。上述试验时不应发生警告信号。 7.3.5 日落和信号灯日落和信号灯 应使用一排彩色白炽灯泡来模拟若干日落阶段的色度特性。 （这一试验也可适用于标志灯和信标灯、指向标灯光的CAAC CTSO-C79 - 11 - 红色一侧以及动力装置近旁的防撞闪光灯。 ）灯泡应使用 40 瓦黄色、橙色和红色的， 例如通用电气 （GE） 公司的 40A/Y （航空黄色） 、 40A/O（航空橙色）和 40A/R（航空红色）或等效产品。试验应在柔和的室内照明下进行，作用在探测器上的照度不大于 1 英尺坎德拉。试验时应将探测器置于三个灯泡的每一个前面，相距 3 英尺，照射 30 秒（每个灯泡） ，不应引发警告。 7.3.6 限制光限制光 应当通过改变尺寸的孔口进行观察， 确定日光和白炽光对仪器的影响。孔口尺寸可随意选择，但必须代表航空器安装件中可能遇到的开口 （例如： 通风口、 集气斗、 发动机整流罩的排水口等等） 。 注：如果在 7.3.3、7.3.4 和 7.3.5 要求的周围光试验中仪器发出了假警告信号，但在其他方面是合格的，则应确定和施加安装限制。这种限制应作为所需资料的一部分，直接清晰地声明。 7.4 振动振动 共振：工作状态下的仪器应经受 3.3.4 规定的相应频率范围的共振频率检查，以确定是否存在零件的任何共振频率。使用的振幅可以是任何方便的值，只要不超过 3.3.4 规定的最大全幅或最大加速度。 然后应使仪器在共振频率下经受 3.3.4 规定的相应最大全幅或者最大加速度的振动，沿每一轴线各为时 1 小时。 如果沿任何一轴线施加振动时遇到一种以上的共振频率， 可以按最严重的共振完成试验期，或将试验期按各共振频率划分，两种办法中应考虑最可能产生失效的一种。 主要共振模态下的试验期不得少于半小时。 CAAC CTSO-C79 - 12 - 如果在规定的频率范围的共振频率不明显，应根据振动要求表（3.3.4）在造成最大加速度的最大全幅和频率下将仪器振动 2 小时。 循环：工作状态下的仪器应以在 3.3.4 规定范围内变化的频率试验 15 分钟的循环，沿每一轴线各为时 1 小时，试验时施加 3.3.4 规定的全幅或 3.3.4 规定的加速度中任一个作为限制值。 7.5 喷水喷水 位于航空器增压区之外的仪器组件应经受以下试验： 7.5.1 模拟雨水模拟雨水 组件应经受喷水 3 小时，模拟雨水。组件在试验之前不得按 7.1 进行干燥。 7.5.2 盐雾盐雾 安装在航空器外露部分的仪器组件应经受 20%浓度细雾化的氯化钠溶液喷射 50 小时，在此试验期结束后，应让组件干燥并按 7.1 进行试验。 7.6 湿度湿度 仪器应装在一腔室内为时 6 小时。腔室内温度保持在 702，相对湿度保持在 955%。在此之后，应断开加温，并让仪器在温度降到不得超过 38、湿度增加到 100%的环境中冷却 18 小时。这一整个循环应进行 5 次。 紧接着上述试验循环后，不得有影响性能的损伤或腐蚀的迹象。 7.7 燃油或滑油浸泡燃油或滑油浸泡 拟安装在发动机舱或可能受燃油或滑油污染的航空器其他部位的仪器组件，应经受下述试验： 7.7.1 燃油浸泡燃油浸泡 组件应在室温下浸入正常含铅量的100/130号汽油或涡轮发动机燃油中（视适合情况而定） ，然后在按 7.1 试验前，让其排油 1 分钟。在进行以后的试验之前不得对组件做清洁。 7.7.2 滑油浸泡滑油浸泡 应执行 7.7.1 规定的试验程序，使用 MIL-O-7808 滑CAAC CTSO-C79 - 13 - 油（涡轮发动机滑油）或 SAE 50 号滑油（活塞发动机滑油） ，视适合情况而定。 7.8 砂尘砂尘 拟安装在航空器外露部分（例如发动机短舱、轮舱等）的仪器组件，应经受充满砂粒的气流吹洗 4 小时，气流以 2.5 磅砂粒/小时的恒定流率吹洗。气流所含的砂粒经过 150 目筛网的筛选，砂粒应接触被试验件的所有外部部分。试验腔应相当于图 1 所示的情况。 7.9 高温工作高温工作 仪器应经受 3.3.1 表内 A 栏（温度）的适用的较高周围温度，为时 48 小时（电气设备接通） 。如果最高的荐用工作温度超过A栏的温度， 应采用此较高的温度。 仪器在此温度下应满足7.1和7.1.1的性能试验要求。 7.10 低温工作低温工作 与 7.9 的要求相同， 只是将 “较高的” 换成 “较低的” 。仪器随后应满足 7.1 和 7.1.1 的性能要求。 7.11 高度效应高度效应 7.11.1 高高度与爬升率高高度与爬升率 仪器应经受从正常大气压力变化到相当于50000 英尺高度的压力，变化率不低于 3000 英尺/分。仪器应当在相当于 50000 英尺高度的压力下保持 48 小时。然后在本款第一句规定的条件下，按 7.1 和 7.1.1 进行试验。在经受了此处规定的压力变化后，密封的组件不得有渗漏。其验证方法是应将密封的组件浸入水或等效物质中，并进行渗漏试验。 7.11.2 低高度低高度 仪器应经受 7.11.1 所述的相同试验，但压力应保持在相当于-1000 英尺的压力下，而且压力的变化率不必按该款的规定。 7.11.3 减压试验减压试验 拟安装在增压区的组件应经受 22 英寸汞柱的绝对CAAC CTSO-C79 - 14 - 压力 15 分钟。然后将压力降至 3 英寸汞柱。这一压力降的实现时间不得超过 10 秒钟。仪器在经受此项试验时不得发出假警告信号。 7.12 电压变化电压变化 当电压在 75%到 110%额定电压之间变化时，仪器应能工作。然后在此条件下按 7.1 对仪器进行试验。应验证对 4.2 的要求的符合性。 7.13 清除时间清除时间 仪器应按 7.1 要求朝向火焰，并对清除信号所需的时间进行三次测定。 测定的办法是先获得响应时间， 然后立即转动仪器，使其停止感受（观察）火焰，并记录信号消失所需的时间。此持续时间即为“清除时间” 。它不得超过 10 秒钟。在此试验过程中，传感器应经受最临界的振动（频率和幅度的条件按 7.4 的测定） 。 7.14 耐火性耐火性 对于要安装在火区内的仪器敏感组件（包括探测器和连接导线） ，应进行试验来验证对至少 1100的完全包容火焰的耐受能力，试验两次，每次 1 分钟。火焰应符合图 2 规定。在每次火焰暴露后，应将传感器冷却到室温。然后再将仪器第三次暴露于同一火焰。在每次暴露之后的 5 秒钟以内，应发出警告信号。在头两次暴露中，火焰移去后的 45 秒钟内，仪器应将其警告消除。在警告消除之前，对于仪器不得使用人为的冷却措施。 如果仪器不符合耐火试验要求，但在其他方面是合格的，则仪器可以安装在不会遭遇火焰的部位。 但仪器要限定安装在这种部位并遵守任何其他的有关限制。 7.15 无线电干扰无线电干扰 使用标准的 M-20B、NM-5A、NM-10A、NM-50A型或等效的噪声与场强计， 将噪声计在 90 千周到 1500 兆周的频率范CAAC CTSO-C79 - 15 - 围内转动，测量不同电路内产生的射频电压。应记下读数峰值（以微伏为单位） 。当读数峰值超过 200 微伏时，应将超过 200 微伏的所有读数列成表格并规定相应的安装限制。 7.16 磁效应磁效应 使用 Kueffel 与 Esser 公司的 5600 型或等同的磁罗盘，测定罗盘偏转不大于 5 度时仪器与罗盘之间的最小距离。 在验证最小距离时，应采集通过组件轴线的平面四个象限每一象限内的密集读数。 CAAC CTSO-C79 - 16 - CAAC CTSO-C79 - 17 - CAAC CTSO-C79 - 18 - 标准的燃烧器装配件完整的材料燃烧器装配件示于图 2-1。此装配件的组件详图示于图 2-2、2-3 和 2-4。图 2-2 示出了燃烧器和燃烧器格栅的详图。 格栅由两块板组成，两块板之间用 1/8 英寸的铜管相连。燃气和空气在燃烧器底座内混合后，通过管子向上输送。燃烧在燃烧器顶板之上发生。冷却空气通CAAC CTSO-C79 - 19 - 过燃烧器格栅上下板之间四个 1/8 英寸管接嘴的孔输入燃烧器。冷却空气通过顶部的 38 号钻孔向上输送，作为控制火焰总体温度的手段。四个 1/8 英寸管接嘴孔的位置极为重要。它们的位置必须与四个象限中每一象限中心一排 1/8 英寸铜管直接对齐。这些连接位置如不正确，会造成冷却空气径向分配不匀，从而同样地影响火焰温度的分配。 图 2-3 示出了燃烧器底座的详图。在燃烧器堵头上钻制两个 11/32 英寸的直径孔时，应加以注意，连接这些孔的中心线与连接底座上两个 19/64 英寸直径的孔的中心线应成直角。如果这些 11/32 英寸直径的孔位置正确的话，则当由上而下垂直观察燃烧器底座时，应当看不见 19/64 英寸直径的孔。孔的这种偏置有助于燃气和空气在升至燃烧器格栅之前的混合。 图 2-4 示出了孔口与孔口腔的详图。共要求有三个孔口腔。其中的两个有端板，并在两端装有 3/8 英寸的螺塞，孔口腔直接固定在燃烧器底座内。第三个孔口腔一端有带螺塞的端板，另一端带有 4 个 1/4 英寸直径孔的板。孔口腔的此端通过 4 根钢管连接燃烧器，每根管子外径 1/4 英寸，长 13.5 英寸。连接底座的孔口腔之一用来计量供给燃烧器的燃气，其上有一个直径 5/32（0.01625）英寸的孔口。另一连接底座的孔口腔用来计量供给燃烧器的混合空气，其上有一直径1/4（0.25）英寸的孔口。靠 4 根 1/4 英寸外径铜管连接燃烧器的第三个孔口腔用来计量供给燃烧器的冷却空气，其上有一个直径 5/16（0.3125）英寸的孔口。燃气的发热量应为约 2500 英国热量单位（BTU)/英尺。燃烧器为了形成 2000F（1100）的火焰，每小时应消耗 26 立方英尺的燃气。所形成的火焰应均匀稳定，没有黄色的焰尖。 用压差压力表测量通过孔口后的压力降读数应为： 1. 燃气孔口（5/32 英寸直径） ：0.99 英寸水柱。 2. 混合空气孔口（1/4 英寸直径） ：9.25 英寸水柱。 3. 冷却空气孔口（5/16 英寸直径） ：11.0 英寸水柱。 为了使燃烧器能发出恰好的热量，应精确控制燃气和混合空气的压差。为了获得正确的温度，可能需要略为调整冷却空气。 CAAC CTSO-C79 - 20 - 图 3(a) 局部升温（见 7.2.1） 图 3(b) 普遍升温（见 7.2.2） English Translation Version for Reference Only Number：CTSO-C79 Date of approval：Jun 4, 2019 Approved by：Xu Chaoqun China Civil Aviation Technical Standard Order - 1 - This China Civil Aviation Technical Standard Order (CTSO) is issued according to Part 37 of the China Civil Aviation Regulations (CCAR-37). Each CTSO is a criterion which the concerned aeronautical materials, parts or appliances used on civil aircraft must comply with when it is presented for airworthiness certification. Fire Detectors (Radiation Sensing Type) 1. Purpose. This China Civil Aviation Technical Standard Order (CTSO) is for manufacturers applying for Fire Detectors (Radiation Sensing Type) CTSO authorization (CTSOA). This CTSO prescribes the minimum performance standards (MPS) that Fire Detectors (Radiation Sensing Type) must first meet for approval and identification with the applicable CTSO marking. 2. Applicability. This CTSO affects new application submitted after its effective date. Major design changes to article approved under this CTSO will require a new authorization in accordance with section 21.353 of CCAR-21R4. 3. Requirements New models of Fire Detectors (Radiation Sensing Type) identified English Translation Version for Reference Only CAAC CTSO-C79 - 2 - and manufactured on or after the effective date of this CTSO must meet the MPS qualification and documentation requirements in Appendix 1 of this CTSO. 4. Marking. Marking should include all the requirement in 21.353(2) of CCAR-21R4 and the operating voltage for the detector shall be shown. Compliance of the detector with the piston or turbine engine requirements, or both, shall be designated by -P, -T, or -PT, respectively, as a suffix following the China civil aviation technical standard order designation as CTSO-C79-P. 5. Application Data Requirements. The applicant must furnish the responsible certification personnel with the related data to support design and production approval. The application data include a statement of conformance as specified in section 21.353(a)(1) in CCAR-21R4 and one copy each of the following technical data: a. A Manual(s) containing the following: (i) The manufacturers operating instructions and equipment limitations; (ii) The installation procedures with applicable schematic drawings, wiring diagrams, and specifications, indicating any limitations, English Translation Version for Reference Only CAAC CTSO-C79 - 3 - restrictions, or other conditions pertinent to installation; and (iii) The manufacturers test report. b. The data required under paragraph (a)(i) and (ii) shall include the following: (i) Cone of vision expressed in degrees (apex of the cone is to be at the center of the sensor and the axis of the cone is to be at right angles to the face of the sensor). (ii) Maximum effective range at field extremities; (iii) Maximum allowable normal ambient temperature at the point of detector location; (iv) Maximum and minimum allowable rate of temperature rise at point of detector location as a result of normal operation; (v) Operating voltage; (vi) Mounting or support method; (vii) Maximum or minimum number of units which can be used in one circuit or one fire zone without adversely affecting sensitivity or causing false indications due to temperature; (viii) Maximum allowable vibration at point of detector location; (ix) Installation limitations (minimum distance) because of magnetic effect; (x) Peak RF voltage and corresponding frequency; (xi) Whether instrument is for pressurized area, nonpressurized English Translation Version for Reference Only CAAC CTSO-C79 - 4 - area or both; (xii) Which of the conditions in paragraphs 7.3.3, 7.3.4, 7.3.5 and 7.3.6 adversely affect the detector; and (xiii) Whether detector meets the fire resistance requirements of paragraph 7.14. English Translation Version for Reference Only CAAC CTSO-C79 - 5 - Appendix 1 MPS for Fire Detectors (Radiation Sensing Type) 1.0 Purpose. To specify minimum requirements for powerplant fire detection instruments for use in piston and turbine engine-powered aircraft, the operation of which subjects the instrument to environmental conditions specified in paragraph 3.3. 2.0 Scope. This standard covers the requirements for acceptance of radiation sensing “surveillance” type fire detectors, intended for use in protecting aircraft powerplant installations, auxiliary powerplants, combustion heaters, and other installations where fires may occur. For purposes of this document, the “instrument” shall be considered as the fire warning system and all components thereof. 2.1 Definition. Radiation sensing type fire detector is an instrument which will initiate an alarm signal when exposed to radiant energy emitted by a flame. The detector and associated circuitry may be designed to be selective with respect to such factors as spectral sensitivity, irradiance level at the detector, rate of rise of irradiance, or frequency characteristics of the fluctuations of irradiance (flicker) or other flame characteristics. 3.0 General Requirements. 3.1 Materials and Workmanship. English Translation Version for Reference Only CAAC CTSO-C79 - 6 - 3.1.1 Materials. Materials shall be of a quality which experience and/or tests have demonstrated to be suitable and dependable for use in aircraft instruments. 3.1.2 Workmanship. Workmanship shall be consistent with high-grade aircraft instrument manufacturing practice. 3.2 Blank. 3.3 Environmental Conditions. The following conditions have been established as design minimum requirements. Tests shall be conducted as specified in paragraphs 5, 6 and 7. 3.3.1 Temperature. When installed in accordance with the manufacturers recommendations, the instrument shall function over the range of ambient temperatures shown in column A. Instrument Location A Powerplant Compartment (Piston) -30+130Power Plant Compartment (Turbine) -30+150Pressurized Areas (Both types of engines) -30+50Nonpressurized or External Areas (Both types of engines) -55+70If the instrument is intended for use in compartments where the maximum ambient temperature is higher than 130 C. for piston engines and 150 C. for turbine engines or if ambient temperatures lower than those specified in column A are anticipated, appropriate special limits shall be selected and specified by the manufacturer. 3.3.2 Humidity. The instrument shall function without adverse effect and English Translation Version for Reference Only CAAC CTSO-C79 - 7 - shall not be adversely affected when exposed to an atmosphere having any relative humidity in the range from 0 to 95 percent at a temperature of approximately 70 C. 3.3.3 Altitude. When installed in accordance with the instrument manufacturers instructions, the instrument shall function and shall not be adversely affected by pressure conditions equivalent to those experienced over an altitude range of -1,000 feet to 50,000 feet. Altitude pressures are to be per NACA Report 1235. 3.3.4 Vibration. When installed in accordance with the instrument manufacturers instructions, the instrument shall function without adverse effect and shall not be adversely affected when subjected to vibrations having the following characteristics: Frequency Cycles Per Sec Max. Double Amplitude in InchesMaximum Acceleration Piston Engines Airframe Structure Mounted 5500 0.050 10g Shock-Mounted Panel 550 0.020 1.5g Powerplant Mounted 5500 0.100 20g Turbine Engines Nacelle and Nacelle Mounts, Wings, Empenage and Wheel Wells 51000 0.036 10g Fuselage- Forward of Spar Area 5500 0.036 2g Center of Spar Area 51000 0.036 4g English Translation Version for Reference Only CAAC CTSO-C79 - 8 - Aft of Spar Area 5500 0.036 7g 5001000 5g Vibration Isolated550 0.020 1.5g Racks 50500 0.5g Instrument Panel 5500 0.030 1.0g 3.3.5 Fluids and Sand. The instrument shall not be adversely affected by exposure to rain, fuel, salt spray, oil, or sand. 3.4 Radio Interference. The installation limitations imposed as a result of radio frequency emissions shall be determined and specified. 3.5 Magnetic Effect. The installation limitations imposed as the result of a magnetic field shall be determined and specified. 4.0 Detail Requirements. 4.1 Indication Means. The instrument shall be capable of actuating visual and/or aural alarm indicators. 4.2 Reliability. The instrument shall be designed to withstand the mechanical and thermal shocks, and stresses incident to its use in aircraft. False alarm signals shall not result from variations in voltage encountered during operation of the aircraft, abnormal attitudes, contaminants in the atmosphere, ambient light conditions, acceleration forces encountered during flight, landing and takeoff. The fire detector shall not false alarm and the detector sensitivity shall not be appreciably affected by the ambient light in the aircraft compartment in which the sensor is installed, under any combination of normal aircraft operating conditions and atmospheric conditions. Tests aimed at determining the effects of the English Translation Version for Reference Only CAAC CTSO-C79 - 9 - foregoing factors on detector reliability are described in paragraph 7.3. 4.3 Integrity Test Means. The instrument shall be designed to provide a means for testing the continuity and functioning of the electrical circuits inflight. 4.4 Calibration Means. The instrument shall be designed so that all calibration means are provided with tamper-proof seals. 4.4.1 Adjustable Detector Systems. Instruments which incorporate an adjustment means shall be tested to prove compliance with this standard, particularly paragraphs 7.1, 7.1.1 and 7.3 throughout the range of adjustability. 5.0 Test Conditions. 5.1 Atmospheric Conditions. Unless otherwise specified, all tests required by this standard, shall be conducted at an atmospheric pressure of approximately 29.92 inches of mercury and at an ambient temperature of approximately 25 C. and at a relative humidity of not greater than 85 percent. 5.2 Vibration. (To minimize friction): Unless otherwise specified, all tests for performance may be conducted with the instrument subjected to a vibration of 0.002 to 0.005 inch double amplitude at a frequency of 1,500 to 2,000 cycles per minute. The term double amplitude as used herein indicates the total displacement from positive maximum to negative maximum. English Translation Version for Reference Only CAAC CTSO-C79 - 10 - 5.3 Vibration Equipment. Vibration equipment shall be such as to allow vibration to be applied along each of three mutually perpendicular axis of the instrument at frequencies and amplitudes consistent with the requirements of paragraph 3.3.4. 5.4 Power Conditions. Unless otherwise specified, all tests shall be conducted at a power rating recommended by the manufacturer, and the instrument shall be in actual operation. 5.5 Test Position. Unless otherwise specified, the instrument shall be mounted and tested in its normal operating position. 6.0 Individual Performance Requirements. All instruments or components of such shall be subjected to tests by the manufacturer to demonstrate specific compliance with this standard including the following requirements where applicable. 6.1 Sensitivity and Calibration. The sensor shall be tested as specified in paragraph 7.1, to determine the response sensitivity and calibration. 6.2 Dielectric. Each instrument shall be tested by the methods of inspection listed in paragraphs 6.2.1 and 6.2.2. 6.2.1 Insulation Resistance. The insulation resistance between all electrical circuits connected together and the metallic case shall not be less than 5 megohms when 200 volts d.c. is applied for five seconds. Insulation resistance measurements shall not be made to circuits where the potential will appear across elements such as windings, resistors, English Translation Version for Reference Only CAAC CTSO-C79 - 11 - capacitors, etc., since this measurement is intended only to determine adequacy of insulation. 6.2.2 Overpotential Tests. Equipment shall not be damaged by the application of a test potential between electrical circuits, and the metallic case. The test potential shall be a sinusoidal voltage, of a commercial frequency, with an r.m.s. value of five times the maximum circuit voltage or per paragraphs 6.2.2.1 or 6.2.2.2, whichever applies. The potential shall start form Zero and be increased at a uniform rate to its test value. It shall be maintained at this value for five seconds, and then reduced at a uniform rate to zero. Since these tests are intended to insure proper electrical isolation of the circuit components in question, these tests shall not be applied to circuits where the potential will appear across elements such as windings, resistors, capacitors, etc. 6.2.2.1 Hermetically sealed instruments shall be tested at 200 volts r.m.s. 6.2.2.2 Circuits that operate at potentials below 15 volts are not to be subjected to overpotential tests. 7.0 Qualification Performance Requirements. As many instruments as deemed necessary to demonstrate that all instruments will comply with the requirements of this section shall be tested in accordance with the manufacturers recommendations. The tests on each instrument shall be conducted consecutively in the order listed, and after the tests have been English Translation Version for Reference Only CAAC CTSO-C79 - 12 - initiated, further adjustments to the instrument shall not be permitted. A false alarm signal occurring during any of the tests shall disqualify the instrument. A response time test per paragraph 7.1 shall be conducted after each test, except paragraphs 7.2, 7.2.1, 7.2.3, and 7.14. In conducting the test of paragraph 7.14, the instrument(s) tested need not be the same instrument(s) being subjected to the entire series of qualification tests. 7.1 Response Time. The sensor of the instrument shall be exposed, at a distance of four feet to a test flame produced by burning gasoline in a flat pan five inches in diameter and with a flow of air of ten feet per second maximum. The temperature of the gasoline and the pan at the start of each test shall not exceed 85 F. A nonleaded white gasoline shall be used. The response time shall not exceed five seconds. 7.1.1 Saturation Test. The sensor shall be mounted facing downward approximately three inches above the center of a flat pan, two feet in diameter, containing gasoline to a level of 1/8-inch from the bottom. The gasoline shall be ignited by a source that cannot be detected by the sensor. The response time shall not exceed five seconds, and the system shall not clear the alarm while exposed to this test for a period of one minute. 7.1.2 Repeat Response Time. The sensor of the fire detector shall be exposed to the flame as described in 7.1 for a period of one minute. It shall then be prevented from sensing the flame. Within five seconds after English Translation Version for Reference Only CAAC CTSO-C79 - 13 - the alarm has cleared, the sensor shall again be exposed to the flame. An alarm shall be signaled within five seconds. 7.2 False Alarm Due to Rate of temperature Rise. The tests described in 7.2.1 and 7.2.2 shall be conducted in a temperature controlled airflow moving at a velocity of 250 feet per minute plus or minus 25 feet per minute. The instrument for this test shall consist of a control unit complete with the maximum number of sensors to be used with a single control unit. No alarm signal shall occur. 7.2.1 Local Temperature Rise. One sensor shall be subjected to various combinations of rates of temperature rise and duration of those rates of rise shown in the shaded area of Figure 3(a). The other sensors in the system shall be maintained at ambient room temperature. This test shall be conducted simulating conditions due to local overheating. No alarm signal shall occur. 7.2.2 General Temperature Rise. The test described in 7.2.1 shall be repeated using Figure 3 (b) except that all the sensors shall be subjected to the temperature variations simultaneously. The test shall be conducted simulating conditions due to a general temperature rise throughout the compartment where the sensors are located. No alarm signal shall occur. 7.2.3 False Clearing of Alarm Due to Partial Extinguishment of Fire. With the instrument arranged to test the response time, in accordance with 7.1, the test flame shall be applied for 30 seconds. The test flame English Translation Version for Reference Only CAAC CTSO-C79 - 14 - shall the be masked so as to reduce its effective area by approximately 50 percent. The alarm signal shall not clear. After an additional 30 seconds, the flame shall be removed entirely, and the alarm signal shall clear within 10 seconds. 7.3 Test Procedures to Establish Detector Reliability Under Special Environmental Conditions. The following test procedures shall apply to establish detector system reliability under various adverse conditions. In conducting the tests, the system shall contain the critical number of sensors for specific test conditions. 7.3.1 B1ank. 7.3.2 Magnesium Flame. Using the test apparatus and setup given in paragraph 7.1 place a 6 inch length of magnesium ribbon, approximately 1 /8 inch wide and 0.005 inch thick, at a point midway between the sensor element and the fire and in line with the sensor. Ignite the gasoline and while the alarm light is on, ignite the magnesium. The alarm shall not clear while either the magnesium, the gasoline, or both are burning. 7.3.3 Sunlight. The test shall be made with sunlight shining directly on the detector (not through a closed window) and the sun shall be within 45 of the zenith so that the slant path through the atmosphere will not be too long. The illumination shall be 5,000 foot-candles or greater, with the light meter probe facing the sun. The detector shall be exposed to sunlight for 30 seconds without actuating the alarm. English Translation Version for Reference Only CAAC CTSO-C79 - 15 - 7.3.4 Chopped Sunlight. In this test, the sunlight (see 7.3.3) shall be modulated by a shutter blade system over a frequency range of 100 cycles per second to 0 cycles per second. This frequency range shall be swept out over a sufficient duration so that there will be a dwell time of a few seconds in any frequency band over the range. A satisfactory chopping arrangement would be a four-bladed shutter on the shaft of a small universal-wound motor operating from a Variac or other source of adjustable voltage. The shutter blades must be large enough to obscure the sun completely from the detector when they are in front of the detector, and blades should be not more than 1 inch away from the detector so that the light from the sky itself will also be modulated. No alarms shall result from the above testing. 7.3.5 Sunsets and Signal Lights. An array of colored, incandescent light bulbs shall be used to simulate the calorimetric properties of sunsets at several stages. (This test would also take care of identification and marker lights, and red side of a beacon light, and the aniticollision light that flicks past the powerplants). The bulbs shall be 40 watt yellow, orange, and red ones such as General Electric Nos. 40 A/Y, 40 A/O, and 40 A/R, or equivalent. The test is to be conducted in a subdued room illumination of not more than one-foot candle on the detector (too dim to read fine print). The test shall compose an exposure of the detector to each of the three lamps, at 3 feet, for 30 seconds each, without causing an alarm. English Translation Version for Reference Only CAAC CTSO-C79 - 16 - 7.3.6 Restricted Light. The effect of sunlight and incandescent light on the instrument when viewed through apertures of varying sizes shall be determined. The aperture sizes may be chosen arbitrarily but should be representative of openings that might be encountered in an aircraft installation (e.g. vents, scoops, and drains in engine cowling, etc.) NOTE: If the instrument false alarms during ambient light test requirements of paragraphs 7.3.3, 7.3.4, 7.3.5, and 7.3.6, but otherwise qualifies, installation limitations shall be determined and imposed. These limitations shall be clearly and explicitly stated as part of the required data. 7.4 Vibration. Resonance: The instrument, while operating, shall be subjected to a resonant frequency survey of the appropriate range specified in paragraph 3.3.4 in order to determine if there exists any resonant frequencies of the parts. The amplitude used may be any convenient value that does not exceed the maximum double amplitude and the maximum acceleration specified in paragraph 3.3.4. The instrument shall than be subjected to vibration at the appropriate maximum double amplitude or maximum acceleration specified in paragraph 3.3.4 at the resonant frequency for a period of one hour in each axis. When more than one resonant frequency is encountered with English Translation Version for Reference Only CAAC CTSO-C79 - 17 - vibration applied along any axis, a test period may be accomplished at the most severe resonance or the period may be divided among the resonant frequencies, whichever shall be considered most likely to produce failure. The test period shall not be less than one-half hour at any major resonant mode. When resonant frequencies are not apparent within the specified frequency range, the instrument shall be vibrated for two hours in accordance with the vibration requirements schedule (paragraph 3.3.4) at the maximum double amplitude and the frequency to provide the maximum acceleration. Cycling: The instrument, while operating, shall be tested with the frequency varied between limits specified in paragraph 3.3.4 in 15-minute cycles for a period of one hour in each axis at an applied double amplitude specified in paragraph 3.3.4 or an acceleration specified in 3.3.4 whichever is the limiting value. 7.5 Water Spray. The instrument components which are to be located outside the pressurized area of the aircaft shall be subjected to the following tests: 7.5.1 Simulated Rain. The component shall be subjected to a spray of water to simulate rain for a period of three hours. The component shall not be dried prior to testing, per paragraph 7.1. 7.5.2 Salt Spray. The instrument components which are to be installed in English Translation Version for Reference Only CAAC CTSO-C79 - 18 - exposed portions of the aircraft shall be subjected to a finely atomized spray of 20 percent sodium chloride solution for 50 hours. At the end of this period, the component shall be allowed to dry and shall be tested per paragraph 7.1. 7.6 Humidity. The instrument shall be mounted in a chamber maintained at a temperature of 702 C. and a relative humidity of 955% for a period of six hours. After this period, the heat shall be shut off and the instrument shall be allowed to cool for a period of 18 hours in this atmosphere in which the humidity rises to 100% as the temperature decreases to not more than 38 C. This complete cycle shall be conducted five times. Immediately after this cycling, there shall be no evidence of damage or corrosion which affects performance. 7.7. Fuel and Oil Immersion. The instrument components which are to be installed in engine compartments or other locations in the aircraft where they may be contaminated by fuel or oil shall be subjected to the following tests: 7.7.1 Fuel Immersion. The component shall be immersed in normally leaded grade 100/130 gasoline or turbine engine fuel as appropriate, at room temperature and then allowed to drain for one (1) minute before being tested, per paragraph 7.1. No cleaning shall be accomplished prior to conducting subsequent tests. English Translation Version for Reference Only CAAC CTSO-C79 - 19 - 7.7.2 Oil Immersion. The test procedures out lined in paragraph 7.7.1 shall be conducted with MIL-O-7808 oil (turbine engine oil) or SAE #50 (piston engine oil) as appropriate. 7.8 Sand. The instrument components which are to be located in externally exposed portions of the aircraft (such as in nacelles, wheel wells, etc.) shall be subjected to a sand-laden airstream flowing at a constant rate of 2 pounds of sand per hour for four hours. The airstream shall contain sand that has been sifted through a 150-mesh screen and the particles shall come in contact with all external parts of the component being tested. The test chamber shall be equivalent to that shown in Figure 1. 7.9 High Temperature Operation. The instrument shall be subjected to the applicable higher ambient temperature listed in Column A of table in paragraph 3.3.1 Temperature, for a period of 48 hours (electrical equipment energized). Where the highest recommended operating temperature exceeds those of Column A, this higher temperature shall be used. The instrument shall meet, while at that temperature(s), the performance tests described in paragraphs 7.1 and 7.1.1. 7.10 Low Temperature Operation. Same as requirement 7.9, except substitute “lower” for “higher”. The instrument shall then meent, at that temperature, the performance tests described in paragraphs 7.1 and 7.1.1. 7.11 Altitude Effects. English Translation Version for Reference Only CAAC CTSO-C79 - 20 - 7.11.1 High Altitude ant Rate of Climb. The instrument shall be subjected to a pressure that is varied from normal atmospheric pressure to an altitude pressure equivalent to 50,000 feet at a rate of not less than 3,000 feet per minute. The instrument shall be maintained at the altitude pressure equivalent to 50,000 feet for a period of 48 hours. The instrument shall then be tested per paragraphs 7.1 and 7.1.1 under the conditions specified in the first sentence. Sealed components shall not leak as a result of exposure to the pressures stated herein. This shall be demonstrated by immersion of se
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