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CTSO-C145e 使用星基增强系统（SBAS）增强全球定位系统的机载导航传感器
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CTSO-C145e
使用星基增强系统（SBAS）增强全球定位系统的机载导航传感器
CTSO
C145e
使用
增强
系统
SBAS
全球定位系统
机载
导航
传感器
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CTSO-C145e 使用星基增强系统（SBAS）增强全球定位系统的机载导航传感器,CTSO-C145e,使用星基增强系统（SBAS）增强全球定位系统的机载导航传感器,CTSO,C145e,使用,增强,系统,SBAS,全球定位系统,机载,导航,传感器
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编 号：CTSO-C145e 日 期：2019 年 4 月 29 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。 用于星基增强系统（SBAS）增强全球定位系统的机载导航传感器 1. 目的 本技术标准规定（CTSO）适用于为使用星基增强系统（SBAS）增强全球定位系统（GPS）的机载导航传感器申请技术标准规定项目批准书（CTSOA）的制造人。本 CTSO 规定了使用星基增强系统增强全球定位系统的机载导航传感器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标记进行标识的使用星基增强系统增强全球定位系统的机载导航传感器应满CAAC CTSO-C145e - 2 - 足 RTCA/DO-229E全球定位系统/星基增强系统的最低性能标准（2016.12.15）第 2.1 节的 Beta 类最低性能标准和文件要求。Beta 类设备定义在 RTCA/DO-229E 第 1.4 节和本 CTSO 附录 2 新增的 1.8.3节。 注：制造商可选择使用附录注：制造商可选择使用附录 3 的的 RTCA/DO-229E 变更。这种变更是基于过去批准的偏离。变更。这种变更是基于过去批准的偏离。 aCTSO-145e 的申请人可选择使用其现有批准的设计数据和附加的证明数据，证明符合 RTCA/DO-229E 中的更改。要求更改的三个方面是：1）扩展 SBAS 伪随机噪声（PRN）代码（即，PRN 范围为 120 到 158） ；2）确保平稳降级至仅 GPS 运行；3）禁止使用广播导航信息修正表。 注注 1：申请人无需重新提交以前批准的偏离。先前批准的偏离和任何限制将适用于：申请人无需重新提交以前批准的偏离。先前批准的偏离和任何限制将适用于 CTSO-C145e CTSOA。 注注 2：1 级和级和 2 级、修订版“级、修订版“b”设备的申请人不得申请”设备的申请人不得申请 3dB 宽频带系统内噪声认证。宽频带系统内噪声认证。 bCTSO-C145e 的申请人可选择使用 CTSO-C204a SBAS CCA功能传感器。选择使用 CTSO-C204a SBA CCA 的申请人可以凭借CTSO-C204a 的 CTSOA 得到局方信任： ? 满足 MPS 第 2.1 节的要求； ? 硬件/软件鉴定； ? 失效状态分类； ? MPS 第 2.5 节性能试验（功能鉴定） ，本 CTSO 附录 1 中规定CAAC CTSO-C145e - 3 - 的除外。 c使用 CTSO-C204a SBAS CCA 功能传感器的 CTSO-C145e 申请人应进行附录 1 中所述的试验， 并满足本 CTSO 中未包含在上述项目符号中的其余段落以取得 CTSO-C145e 的 CTSOA。 注：根据注：根据 CCAR-21-R4 第十章技术标准规定项目批准书和设计批准认可证，使用第十章技术标准规定项目批准书和设计批准认可证，使用 CTSO-C204a SBAS CCA 功能传感器作为功能传感器作为CTSO-C145e 申请一部分的终端制造商对其申请一部分的终端制造商对其 CTSO-C145e 授权下的设计和功能负全责。授权下的设计和功能负全责。 d功能 本 CTSO 的标准适用于预期为输出所需飞行路径偏移命令的导航管理单元应用或如广播式自动相关监视（ADS-B）或地形提示警告系统（TAWS）等非导航应用提供位置、速度和时间信息的设备。在导航应用中， 飞行员或自动驾驶仪将使用导航管理单元输出的偏差来引导飞机。在非导航应用中，位置、速度、时间输出将为终端设备提供必要的输入。 这些 CTSO 标准不涉及与其他航空电子设备的集成问题。 e. 失效状态类别 （1）本 CTSO 第 3.d 节定义的功能失效会导致航路、终端、进近横向导航（LNAV）和进近 LNAV/垂直导航（VNAV）位置数据出现误导信息，属重大的失效状态。 （2） 本CTSO第3.d节定义的功能失效会导致没有垂直制导 （LP）和带有垂直制导（LPV）的进近航向性能的位置数据出现误导信息误CAAC CTSO-C145e - 4 - 导，属危险的失效状态。 （3） 本 CTSO 第 3.d 节定义的凭借进近 LP/LPV 位置数据的航路的功能丧失，属重大的失效状态。 （4）设备的设计保证等级应至少与这种失效状态类别相对应。 f. 功能鉴定 （1）应按 RTCA/DO-229E 第 2.5 节中试验条件，证明设备性能满足要求，或 （2） 当使用 CTSO-C204a SBAS CCA 功能传感器时， 按本 CTSO附录 1 的试验条件证明所需的性能。 g. 环境鉴定 应按 RTCA/DO-229E 第 2.4 节中的试验条件， 使用标准的环境条件和机载设备试验程序证明设备性能满足要求。 RTCA/DO-229E 要求采用 RTCA/DO-160E机载设备环境条件和试验程序 （2004.12.9）第 4.0 至 8.0 节和第 10.0 至 25.0 节。可以采用除 RTCA/DO-160E 以外其它适用于 SBAS CCA 功能传感器的标准环境条件和试验程序。 注注 1：通常情况下，：通常情况下，RTCA/DO-160D（包括（包括 Change 1 和和 Change 2）或早期版本不再适用，如果使用该版本则需按照本）或早期版本不再适用，如果使用该版本则需按照本 CTSO 第第 3.k节中的偏离要求进行证明。节中的偏离要求进行证明。 注注 2：使用：使用 CTSO-C204a SBAS CCA 传感器的申请人必须提供应用了传感器的申请人必须提供应用了 SBAS CCA 终端设备的环境鉴定。终端设备的环境鉴定。 h. 软件鉴定 （1）如果设备包含软件，则软件应按照 RTCA/DO-178B机载CAAC CTSO-C145e - 5 - 系统和设备合格审定中的软件考虑 （1992.12.1）或 RTCA/DO-178C机载系统和设备合格审定中的软件考虑 （2011.12.13）的要求进行研制。软件的设计保证等级应与本 CTSO 第 3.e 节规定的失效状态类别一致。 （2）使用 CTSO-C204a SBAS CCA 传感器的申请人可以使用CTSO-C204a 作为软件鉴定证明。 i. 电子硬件鉴定 （1） 如果设备中包含复杂电子硬件， 则应按照 RTCA/DO-254 机载电子硬件设计保证指南 （2000.4.19）的要求进行研制。硬件的设计保证等级应与本 CTSO 第 3.e 节规定的失效状态类别一致。对于确定为简单的机载电子硬件，可按 RTCA/DO-254 中第 1.6 节的要求处理。 （2）使用 CTSO-C204a SBAS CCA 传感器的申请人可以使用CTSO-C204a 作为硬件鉴定证明。 j. 气压辅助故障检测与排除（FDE） 。 如果设备使用气压辅助以提高 FDE 的可用性，则设备必须满足RTCA/DO-229E 附录 G 中的要求。 k. 偏离 如果采用替代或等效的符合性方法来满足本 CTSO 规定的最低性能标准要求，则申请人必须表明设备保持了等效的安全水平。申请人应按照 CCAR-21-R4 第 21.368 条（一）要求申请偏离。 CAAC CTSO-C145e - 6 - 4. 标记 a. 至少应为一个主要部件设置永久清晰的标记，标记应包括CCAR-21-R4 第 21.423 条（二）规定的所有信息。 b. 应为以下部件设置永久清晰的标记，标记至少包括制造人名称、组件件号和 CTSO 标准号： （1）所有容易拆卸（无需手持工具）的部件； （2）制造人确定的设备中可互换的所有组件。 c. 如果设备中包含软件和/或机载电子硬件，则件号必须能够表明软件和硬件的构型。件号编排时，在件号中可为硬件、软件和机载电子硬件各划分一个单独区域。 d. 可以使用电子标记标识软件和机载电子硬件，此标记可通过软件写入硬件部件内部，而不用将其标识在设备铭牌中。如果使用电子标记，则其必须容易读取，无需使用特殊工具或设备。 e. 必须按照 RTCA/DO-229E 第 1.4.2 节的规定， 将至少一个主要部件永久清晰地标记设备运行等级（例如，2 级） 。 5. 申请资料要求 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. 手册。包含以下内容： （1）运行说明和设备限制，该内容应对设备运行能力进行充分描述。 CAAC CTSO-C145e - 7 - （2）对所有偏离的详细描述。 （3）安装程序和限制。必须确保按照此安装程序安装设备后，设备仍符合本 CTSO 的要求。限制必须确定任何特殊的安装要求，还必须以注释的方式包含以下声明： “本设备满足技术标准规定中要求的最低性能标准和质量控制标准。如欲安装此设备，必须获得单独的安装批准。 ” “本设备满足技术标准规定中要求的最低性能标准和质量控制标准。如欲安装此设备，必须获得单独的安装批准。 ” （4）对于所有软件和机载电子硬件构型，包括如下内容： （i）软件件号，包括版本和设计保证等级； （ii）机载电子硬件件号，包括版本和设计保证等级； （iii）功能描述。 （5）设备中每个部件进行环境鉴定的试验条件总结。例如，可采用 RTCA/DO-160E机载设备环境条件和试验程序附录 A 的表格方式描述。 （6）原理图、布线图，以及设备安装所必需的其它文件。 （7）设备的可更换部件清单（注明件号） 。如适用，包括对供应商件号的交叉索引。 （i）如果设备仅在与特定天线一起使用时才能满足RTCA/DO-229E 的要求，则应将该天线（注明件号）作为一项安装要求。在安装手册（IM）将此要求作为一项限制。 （ii）如果设备使用标准天线就能满足 RTCA/DO-229E 的要求， 包括输入天线端口的最大允许电流和电压。 参见 CTSO-C144a 无源机载全球导航卫星系统（GNSS）天线 ，仅适用于 1 类设备；或CAAC CTSO-C145e - 8 - CTSO-C190有源机载全球导航卫星系统（GNSS）天线 ，适用于全部设备运行类别。 b. 持续适航文件，包含设备周期性维护、校准及修理要求，以保证设备的持续适航性。 如适用， 应包括建议的检查间隔和使用寿命。 c. 如果未使用 CTSO-C204a SBAS 功能传感器的设备包含软件，则还应提供：软件合格审定计划（PSAC） 、软件构型索引和软件完结综述。 d. 如果未使用 CTSO-C204a SBAS 功能传感器的设备包含简单的或复杂电子硬件，还应提供：硬件合格审定计划（PHAC） 、硬件验证计划、顶层图纸和硬件完结综述（或相似文件，如适用） 。 e. 铭牌图纸，规定设备如何标识本 CTSO 中第 4 节所要求的标记信息。 f. 对 SBAS 传感器与其他系统之间的接口进行充分的详细说明，以确保集成系统的正常运行。如果设备依靠任何外部输入（如气压辅助故障检测与排除）来满足 RTCA/DO-229E 的要求，则将这些输入作为安装要求。将此要求作为一项限制纳入 IM 中。 g. 如果软件鉴定将设备的合格性限制为特定的某些飞机类型，则确定鉴定等级，以及该设备不对所有机型运用。例如，RTCA/DO-178B（或 RTCA/DO-178C）C 级软件可能与某些飞机类型的危险失效状态有关。确定失效状态分类的其他限制，例如需要两个安装的装置。 h. 如果设备未被证明与卫星通信系统相兼容，在限制中说明设CAAC CTSO-C145e - 9 - 备不得安装在配备有卫星通信系统的飞机上。 i. 确定设备中所包含而未按照本CTSO第3节进行评估的功能或性能（即：非 CTSO 功能） 。在获得 CTSOA 的同时非 CTSO 功能也一同被接受。接受这些非 CTSO 功能，申请人必须声明这些功能，并在 CTSO 申请时提供以下信息： （1）非 CTSO 功能的描述，如性能规范、失效状态类别、软件、硬件以及环境鉴定类别。还应包括一份确认非 CTSO 功能不会影响设备对本 CTSO 第 3 节要求符合性的声明。 （2）安装程序和限制，能够确保非 CTSO 功能满足第 5.i.(1)节所声明的功能和性能规范。 （3）第 5.i.(1)节所描述非 CTSO 功能的持续适航要求。 （4）接口要求和相关安装试验程序，以确保对第 5.i.(1)节性能资料要求的符合性。 （5） （如适用） 试验大纲、 试验分析和试验结果， 以验证 CTSO设备的性能不会受到非 CTSO 功能的影响。 （6） （如适用）试验大纲、试验分析和试验结果，以验证第5.i.(1)节描述的非 CTSO 功能的功能和性能。 （7）也可以确认本 CTSO 第 3 节未评估的非 CTSO 功能和性能， 在提交CTSO申请的同时提交非CTSO功能的前期数据用以验收。 j. 按 CCAR-21-R4 第 21.358 条要求提供质量系统方面的说明资料，包括功能试验规范。质量系统应确保检测到可能会对 CTSO 最低性能标准符合性有不利影响的任何更改，并相应地拒收该产品。 CAAC CTSO-C145e - 10 - k. 材料和工艺规范清单。 l. 定义设备设计的图纸和工艺清单（包括修订版次） 。 m. 制造人的 CTSO 鉴定报告， 表明按本 CTSO 第 3.f 节完成的试验结果。 6. 制造人资料要求 除直接提交给局方的资料外，还应准备如下技术资料供局方评审： a. 用来鉴定每件设备是否符合本 CTSO 要求的功能鉴定规范； b. 设备校准程序； c. 原理图； d. 布线图； e. 材料和工艺规范； f. 按本 CTSO 第 3.g 节要求进行的环境鉴定试验结果； g. 如果不使用 CTSO-C204a SBAS 功能传感器的设备包含软件，提供 RTCA/DO-178B 或 RTCA/DO-178C 中规定的相关文档，包括所有支持 RTCA/DO-178B 或 RTCA/DO-178C 附件 A“软件等级的过程目标和输出”中适用目标的资料； h. 如果未使用 CTSO-C204a SBAS 功能传感器的设备包含复杂电子硬件， 应提供 RTCA/DO-254 附录 A 表 A-1 中定义的与设计保证等级和硬件生命周期相关的资料。对于简单电子硬件，应提供以下资料：测试用例或程序，测试结果，测试覆盖率分析，工具评估和鉴定资料，构型管理记录并包含问题报告。 CAAC CTSO-C145e - 11 - i. 如果未使用 CTSO-C204a，必须提供 RTCA/DO-229E 第.5 节规定的所有数据以评估地球静止（GEO）卫星偏差。 j. 如果设备包含非 CTSO 功能，必须提供第 6.a 节至第 6.h 节与非 CTSO 功能相关的资料。 7. 随设备提交给用户的资料要求 a. 如欲向一个机构（例如运营人或修理站）提交一件或多件按本 CTSO 制造的设备，则应随设备提供本 CTSO 第 5.a 节、第 5.b 节、第 5.f 节至第 5.h 节的资料副本，以及设备正确安装、审定、使用和持续适航所必需的资料。 b. 如果设备包含已声明的非 CTSO 功能，则还应包括第 5.i.(1)节至第 5.i.(4)节所规定资料的副本。 8. 引用文件 aRTCA 文件可从以下地址订购： Radio Technical Commission for Aeronautics, Inc. 1150 18th Street NW, Suite 910, Washington D.C. 20036 也可通过网站 订购副本。 CAAC CTSO-C145e - 12 - 附录 1 用于导航和非导航应用的 SBAS CCA 功能位置、 速度、 时间 （PVT）传感器的终端设备制造商试验 1. 范围 本附录描述了使用 CTSO-C204a SBAS CCA 功能传感器的终端设备制造商，除 RTCA/DO-229E 第 2.4 节的环境试验外，还需补充的设备级试验以获得 CTSO-C145e Beta 类批准。 这些试验程序旨在优化化简终端设备制造商的 CTSO-C145e 批准流程，允许 SBAS CCA 功能传感器级的设计和选择试验认证。但是，根据 CTSO-C145e TSOA最终设备制造商仍应对设备的设计和控制负全部责任。 2. 基本原则 （a）RTCA/DO-229E 已将 GPS/SBAS 设备的试验方法标准化，作为 CTSO-C145e 的基础。 RTCA/DO-229E 是以在飞机上安装设备的角度编写，第 2.4 节特别提到了设备运行环境问题，并提供可获批的试验方法，以验证在这种环境中设备的性能。第 2.4 节表述了 RTCA的共识，确定哪些 RTCA/DO-229E 要求对环境效应敏感。这些要求列在第 2.4.1 节的环境表格中。 （b）MOPS 要求易受环境影响的判定并不取决于某些主机设备内是否使用了 CCA。与设计用于恶劣环境的设备外壳相比，这与设计用于抵御良性环境的设备外壳的概念相同； 敏感要求的识别也是相同的。 （c）因此，本附录使用 RTCA/DO-229E 第 2.4.1 节的表格来确定终端设备中SBAS CCA功能传感器对环境效应敏感的MOPS要求。CAAC CTSO-C145e - 13 - 重点是 SBAS CCA 功能传感器在终端设备中安装后的环境变化。例如，终端设备内的其他组件可能会辐射对 GPS 功能产生干扰的射频能量。因此，在 CCA 级进行的环境试验与在终端设备中进行的试验不相等。这是定义 RTCA/DO-229E 第 2.5 节性能试验的基础，终端设备制造商需要重复这些试验。 （d）RTCA/DO-229E 第 2.4.1 节 Beta 类环境表格是确定 MOPS性能要求（易受环境条件影响）的主要来源。根据表格，敏感需求可分为两类：对大多数环境条件敏感的需求（见第 3 节）和对少数环境条件敏感的需求（见第 4 节） 。 注：Beta-1、-2 和-3 类设备的表格确定了对安装环境敏感的类似要求。 唯一的区别是与操作等级 （即 1、 2 或 3 级） 一致的适用 MOPS要求。 3. 大多数环境条件敏感的性能要求 RTCA/DO-229E 对精度（、 和 ）以及灵敏度和动态范围（0）的要求对大多数环境条件都很敏感。但是，这些要求与 .2 中的消息丢失率要求相关联。第 3.1 和 3.2 节确定终端设备制造商需要重复试验，以证明 SBAS CCA 功能传感器在终端设备安装后仍满足精度、动态范围和信息丢失率的性能要求。所有试验将在终端设备功能全部启用以构建最差的环境条件下进行。 3.1 RTCA/DO-229E 第 2.5.8 节精度试验 （a）第 2.5.8 节所述的精度试验实际上是一项涵盖精度、灵敏度和动态范围的联合试验。 本联合试验也适用于第 .5 节所述的环CAAC CTSO-C145e - 14 - 境下，以及第 .1 节所述的环境适应。 （b）仅针对具有宽带外部干扰噪声的试验用例，根据第 节进行精度验证。试验必须将 CCA 安装在终端设备中，且使用宽带干扰重复进行。 （1）环境试验仅限于宽带干扰，代表了对环境影响最敏感的最差情况信噪比条件。这等效于终端设备内 CCA 所处的环境。 （2）第 2.5.8 节包含 节的测量精度试验，详细试验程序见 。第 节试验必须在下文“内部干扰源的其他注意事项”一节中规定的最差情况下进行。测量精度试验可与 节的信息丢失率试验相结合。 （3）第 节为 24 小时实际卫星精度试验。第 节试验将设备暴露在各种信号条件和数据处理条件下，卫星几何结构的变化将使终端设备内组件与 SBAS CCA 功能传感器之间的相互作用可测。第 节的 24 小时试验可与第 节的 24 小时信息丢失率试验相结合 （参见 “内部干扰源的其他注意事项” 一节） 。 （4）第 节（SBAS 跟踪偏差）是对 GPS 硬件的分析，因此，只要射频路径中没有插入影响射频滤波响应的额外射频组件，就无需在终端设备级重复。否则，终端设备制造商必须重复SBAS 跟踪偏差试验。 （c）按照第 .1 节试验程序中表 2-25 的规定，将试验阈值从 110%放宽至 125%，以缩短试验时间。但是，第 2.5.8 节：终端设备中 CCA 的试验（不包括第 节的 SBAS 跟踪偏差试验）应在CAAC CTSO-C145e - 15 - 第 2.5 节规定的环境条件下进行，最大试验敏感度为 110%试验合格阈值。 （d）第 2.5.8 节试验（不包括第 节的 SBAS 跟踪偏差试验）将根据与预期操作等级（即 、 和 精度要求，视情况而定）一致的精度要求重复进行。 （e）多数情况下，为了缩短试验时间，只执行使用最小卫星功率的宽带外部干扰噪声试验。第 节试验仅在最差情况下的最小和最大卫星功率重复进行。 3.2 RTCA/DO-229E 第 2.5.2 节信息丢失率试验 （a） 第 2.5.2 节规定了第 .2 节消息丢失率要求的消息丢失率试验。本试验与第 2.5.8 节精度试验一起进行。第 节定义了SBAS 消息丢失率的试验程序，在 SBAS 卫星最小功率运行时收集数据以验证 SBAS 消息丢失率。第 节定义了合格/不合格标准。 （b）第 节的试验在第 3.1 节中描述的测量精度宽带干扰试验情况下进行。 （c）第 .1 节的试验与第 节 24 小时精度试验一同运行。第 .2 节确定了第 3.1（b） （3）所述试验的通过/失败标准。 4. 部分环境条件敏感的性能要求 （a）RTCA/DO-229E 第 2.4.1 节的 Beta 类表格（表 2-14、2-16和 2-18）指示初始采集时间（第 节）和卫星重新采集时间（第 节）对四种环境条件敏感：结冰、雷电感应瞬态敏感性、雷电CAAC CTSO-C145e - 16 - 直接效应和正常/异常运行条件。导航丧失（第 3.2、2.2和 2.2 节）和完整性丧失（第 3.1、2.1 和 2.1节）的要求对低和高工作温度敏感。 （b）雷电感应瞬态敏感性、雷电直接效应或结冰环境条件与有SBAS CCA 功能传感器的终端设备产生的环境无关。但是，终端设备制造商仍负责终端设备级满足整体环境认证。 （c）导航丧失和完整性指示丧失仅限于温度试验，且适用于RTCA/DO-229E 第 .2 和 .3 节的信息。 目的是确保在终端设备中安装 SBAS CCA 功能传感器后，用于指示导航丧失的接口在环境条件下正常工作。第 .2 节和第 .3 节指出，任何产生指示的源都可以使用，因其仅是界面，不是验证的检测机制。在终端设备级进行的温度试验是在最坏情况。 无需在室温下重复终端设备内的 CCA 级试验，因为环境鉴定充分说明了这些要求的试验。 （d） RTCA/DO-160E 第 16 节涉及飞机电源 （有关环境鉴定要求，请参阅 CTSO 第 3.f 节） 。第 和 节适用于电源电压调制（AC）/纹波（DC） 。鉴于 SBAS CCA 功能传感器对电源噪声的潜在敏感性，基于此在终端设备级反复试验需谨慎。 （e）第 4.1 节和第 4.2 节明确终端设备制造商需要反复试验，以证明 SBAS CCA 功能传感器在终端设备上安装后仍满足正常/异常操作条件下采集时间和重新采集时间的性能要求。 所有试验将在终端设备功能完全启用以构建最坏情况环境的条件下进行。 CAAC CTSO-C145e - 17 - 4.1 2.5.4 初始采集试验程序 RTCA/DO-229E 第 .4 节的信息采用第 2.5.4 节的初始采集试验。终端设备制造商应重复 RTCA/DO-229E 第 2.5.4 节中所述的初始采集试验。 4.2 2.5.6 卫星重新采集时间试验 终端设备制造商需要重复 RTCA/DO-229E 第 2.5.6 节中的卫星重新采集时间试验。 5. 内部干扰源的其他注意事项 （a）将 SBAS CCA 功能传感器安装到终端设备，由于终端设备还含有其他功能，需要仔细评估潜在的内部辐射和传导干扰。终端设备制造商必须评估每个操作模式，以确定模式是否改变 SBAS CCA功能传感器的安装环境。如果只有一个环境或一个最坏环境，那么第3 节精度和消息丢失率试验可以仅在运行模式下进行。例如，假如终端设备包含了一个在一个频率辐射的射频收发机， 则可以将收发机按最大数据满功率设置以产生一个最坏情况环境进行所有试验。 （b）在多个环境的情况下，精度和消息丢失率试验可以在各个环境下进行，也可以使用 RTCA/DO-229E 第 .3 节的方法在每个模式大致相等的时间下组合进行。 第 .3 节的方法必须用于确定除总试验外精度和消息丢失率组合试验的最大敏感度模式。例如，.3 方法适用于包含了一台大功率发射机的终端设备，该发射机可以在大量频率下运行，每一频率进行一次试验时不现实的。这类似于在 RTCA/DO-160E 射频和感应信号敏感性试验期间需要试验大量CAAC CTSO-C145e - 18 - 频率，也是第 .3 节方法制定的原因。 （c） 在进行采集和 24 小时精度试验时， 确定一个最坏情况环境。 6. 总结 （a）在将 SBAS CCA 功能传感器安装到终端设备中后，带有SBAS CCA 功能传感器的终端设备制造商需要在环境条件（见第 5节）下重复以下 RTCA/DO-229E 第 2.5 节试验： ? 第 2.5.8 节精度 （不包括第 节中的 SBAS 跟踪偏差试验）根据第 .1 节进行了调整， 但使用了 110%的试验通过阈值。 注：不包含 SBAS 跟踪偏差试验是可以接受的，前提是终端设备不插入射频信号路径和组件影响滤波响应。否则，终端设备制造商也必须重复 SBAS 跟踪偏差试验。 ? 第 2.5.2 节消息丢失率试验。 ? 第 2.5.4 节初始采集试验。 ? 第 2.5.6 节卫星重新采集时间试验。 （b）终端设备制造商仍负责在终端设备级完成完整的环境鉴定评估 （见CTSO第3.f段） 。 根据RTCA/DO-229E第.2和.3节，包含 SBAS CCA 功能传感器的终端设备制造商需分别将失去导航指示和完整性指示作为环境鉴定的一部分，进行重复试验。 CAAC CTSO-C145e - 19 - 附录 2 RTCA/DO-229E 的补充 本附录为 RTCA/DO-229E 新增的 1.8.3 小节，网络安全和 GPS欺骗抑制。新的内容提供了网络安全和欺骗抑制的信息，使RTCA/DO-229E 与新版 RTCA MOPS 和 RTCA/DO-253D 保持一致。 1.8.3 网络安全和欺骗抑制 本节包含了对 GPS 有意干扰的信息。欺骗是由射频波形引起的，这些波形在某些方面模仿真实信号，但在处理时会拒绝、降低、干扰或欺骗接收机的操作。欺骗可能是无意的，例如来自 GPS 中继器的信号的影响，或者可能是有意的，甚至是恶意的。有两类欺骗。测量欺骗引入了 RF 波形，这些波形导致目标接收机产生对到达时间、到达频率或其变化率的测量不正确。 数据欺骗将错误的数字数据引入目标接收机，用于信号处理和 PNT 计算。任何类型的欺骗都会造成从PNT 的错误输出到接收器故障的影响。 这些影响一开始可以是瞬时的或延迟的，甚至在欺骗结束之后影响仍可以继续。使用不当或安装的GNSS 重辐射器会造成欺骗。重辐射器回放，GNSS 仿真设备能够向GNSS 设备呈现误导性信息，可能造成持久影响。 设备制造商应采取措施减轻错误数据的处理。 使用 GNSS 信号度量或数据检查的 GNSS 传感器数据与独立位置源和/或其他检测监视器的交叉检查，可以通过天线、接收机实现，或通过与其他系统的集成至飞机级实现。在接收机中应该实现数据有效性检查，来识别并拒绝测量欺骗和数据欺骗。与 GPS 设备有关的其他指导和最佳做法见美国国土安全部文件“改善关键基础设施使用的全球定位系统(GPS)CAAC CTSO-C145e - 20 - 设备的运行和发展”1以及 IS-GPS-200 修订版 H， IRN003 （2016.7.28） 。也可参考 RTCA/DO-326A、ED-202A、RTCA/DO-355 以及 ED204，来评估脆弱性并识别抑制方法。 自 70 年代末个人计算机发展以来，机载设备信息漏洞（例如网络安全风险）一直存在于数字系统中，甚至更长的时间出现在 RF 系统中，并且随着互联网的出现，这些风险大幅增加。通常，导航接收机的接入已经被控制，导航接收机仅在 RF 信号、OEM 或飞机操作员控制的维护和更新过程中才易受攻击。在某些情况下，飞机 GNSS接收机可以由批准的人员现场加载， 需要地面接收机的物理访问和物理接口。然而，未来并非所有机载设备的安全性都依赖于这种物理隔离。 互联网和 Wi-Fi 已经成为飞机/设备制造商用于更新已安装的机载电子软件、更新数据库或提供与飞行机组人员、客舱）例如，娱乐系统、天气等）通信的通行方法。 大多数国家均会监督飞机的飞行安全系统（有时称为“授权服务” ） ，并为飞机提供如 ILS、VOR、GNSS 和 DME 等的信息。但是，通常不提供“不可信”连接的监督，如互联网、Wi-Fi 或制造商提供的允许将外部数据输入到飞机系统中的设备接口。 设备的设计可能会暴露飞机信息漏洞，连接到公共接口也会出现漏洞。因此，制造商在设备设计中应考虑飞机信息安全风险缓解策略， 特别是当设备具备飞机与飞机-外部系统之间的接口时。 除了 MOPS 中包含的与航空器信息安全相关的具体性能要求之外，建议制造商考虑航空器信息安全风险减轻的分层方法，包括技术CAAC CTSO-C145e - 21 - （例如，软件、信号滤波）和物理策略。从技术角度，例如，包括信号欺骗检测能力或者更严格的多因素身份验证技术，如密码、PIN 和数字证书。从物理角度，尽管导航航电设备通常位于乘客无法进入的航空电子设备舱中，但是制造商仍应考虑连接器等特殊工具，以防止乘客篡改信息。最后，同样重要的是，制造商应该考虑供应链风险管理；例如，如果制造商外包软件代码开发，应考虑承包商及其员工是否经过适当审查。 当申请人采用不可信的连接， 可能潜在地引入飞机信息安全漏洞时，民航局应对其监管。这要求申请人不仅要解决新安装设备的信息安全漏洞和缓解技术，而且还要考虑漏洞如何传播到现有的下游系统。此外，飞机制造商应考虑为飞机操作人员建立适当的程序，以便在装机设备的整个生命周期内保持设备的安全防护。因此，建议制造商参考其设备装机的信息安全审查和缓解策略， 以便申请人满足设备安装的规章要求。 注 1： /sites/default/files/documents/Improving_the_Operation_and_Development_of_Global_Positioning_System_(GPS)_Equipment_Used_by_Critical_Infrastructure_S508C.pdf CAAC CTSO-C145e - 22 - 附录 3 选择性更改：RTCA/DO-229E 常用的偏离请求 本附录描述了 RTCA/DO-229E 基于过去常用偏离的变化。制造商可以选择执行 RTCA/DO-229E 中的指定部分的更改。执行RTCA/DO-229E 的更改应减少对偏离请求的需求。 2.3 LPV 和 LP 的进近操作要求 在段后添加以下注释： 注：如果设备有适当的限制，并且 LP 方法不能供飞行员选择，那么制造商提供的设备可以不具备 LP 进近能力。 English Translation Version for Reference Only Number：CTSO-C145e Date of approval：Apr 29, 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. Airborne Navigation Sensors Using The Global Positioning System Augmented By The Satellite Based Augmentation System (SBAS) 1. Purpose. This China Civil Aviation Technical Standard Order (CTSO) is for manufacturers applying for airborne navigation sensors using the global positioning system (GPS) augmented by the satellite based augmentation system (SBAS) CTSO authorization (CTSOA). This CTSO prescribes the minimum performance standards(MPS) that airborne navigation sensors using the GPS augmented by the SBAS 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. English Translation Version for Reference Only CAAC CTSO-C145e - 2 - 3. Requirements New models of airborne navigation sensors using the GPS augmented by the SBAS identified and manufactured on or after the effective date of this CTSO must meet the MPS qualification and documentation requirements for functional equipment Class Beta in RTCA, Inc. document RTCA/DO-229E, Minimum Operational Performance Standards for Global Positioning System/Satellite-Based Augmentation System Airborne Equipment dated December 15, 2016, Section 2.1. Class Beta equipment is defined in RTCA/DO-229E, Section 1.4 and Appendix 2 adds a new section 1.8.3. Note: Manufacturers have the option to use the RTCA/DO-229E change described in Appendix 3. The change is based on a past commonly granted deviation. a. An alternate method for applicants is to apply for CTSO-C145e using their existing approved design data plus additional substantiation data showing compliance with the changes in RTCA/DO-229E. The three areas where requirements changed are: 1) expanding the SBAS pseudorandom noise (PRN) codes (i.e., PRN range of 120 thru 158); 2) ensuring a graceful degradation to GPS-only operations; and, 3) prohibiting use of the broadcast Navigation Message Correction Table. Note 1: It is not necessary for applicants to re-submit previously approved deviations. Previously approved deviations, and any limitations, English Translation Version for Reference Only CAAC CTSO-C145e - 3 - will apply to the CTSO-C145e CTSOA. Note 2: Applicants with Class 1 and 2, revision b equipment must not have claimed the 3db broadband intrasystem noise credit. b. CTSO-C145e applicants have the option to use a CTSO-C204a SBAS CCA functional sensor. Applicants choosing to use a CTSO-C204a SBAS CCA can take certification compliance credit by virtue of the CTSO-C204a CTSOA for: ? Meeting the MPS section 2.1 requirements; ? The hardware/software qualification; ? The failure condition classification; and, ? MPS section 2.5 performance testing (functional qualification) except those specified in Appendix 1 of this CTSO. c. The CTSO-C145e applicant using a CTSO-C204a SBAS CCA functional sensor shall perform the testing described in Appendix 1 and satisfy the remaining paragraphs in this CTSO not covered by the bullets above to receive a CTSO-C145e CTSOA. Note: The end-use manufacturer using a CTSO-C204a SBAS CCA functional sensor as part of their CTSO-C145e application assumes full responsibility for the design and function under their CTSO-C145e authorization. d. Functionality. This CTSOs standards apply to equipment intended to provide English Translation Version for Reference Only CAAC CTSO-C145e - 4 - position, velocity, time information for a navigation management unit application that outputs deviation commands keyed to a desired flight path, or a non-navigation application such as automatic dependent surveillance-broadcast (ADS-B) or terrain awareness and warning system (TAWS). In navigation applications, pilots or autopilots will use the deviations output by the navigation management unit to guide the aircraft. In non-navigation applications, the position, velocity, time outputs will provide the necessary input for the end-use equipment. These TSO standards do not address integration issues with other avionics. e. Failure Condition Classifications. (1) Failure of the function defined in paragraph 3.d resulting in misleading information for en route, terminal, approach lateral navigation (LNAV), and approach LNAV/vertical navigation (VNAV) position data is a Major failure condition. (2) Failure of the function defined in paragraph 3.d resulting in misleading information for approach localizer performance without vertical guidance (LP), and approach localizer performance with vertical guidance (LPV) position data is a Hazardous failure condition. (3) Loss of the function defined in paragraph 3.d for enroute through approach LP/LPV position data is a Major failure condition. (4) Design the system to at least these failure condition classifications. English Translation Version for Reference Only CAAC CTSO-C145e - 5 - f. Functional Qualification. (1) Demonstrate the required functional performance under the test conditions specified in RTCA/DO-229E, Section 2.5, or (2) When using a CTSO-C204a SBAS CCA functional sensor, demonstrate the required performance under the test conditions in appendix 1 of this CTSO. g. Environmental Qualification. Demonstrate the required performance under the test conditions specified in RTCA/DO-229E, Section 2.4 using standard environmental conditions and test procedures appropriate for airborne equipment. RTCA/DO-229E requires the use of RTCA/DO-160E, Environmental Conditions and Test Procedures for Airborne Equipment, dated December 9, 2004, Sections 4.0 through 8.0 and 10.0 through 25.0. You may use a different standard environmental condition and test procedure than RTCA/DO-160E, provided the standard is appropriate for the SBAS sensor. Note1: The use of RTCA/DO-160D (with Changes 1 and 2 only, incorporated) or earlier versions is generally not considered appropriate and will require substantiation via the deviation process as discussed in paragraph 3.k of this CTSO. Note 2: Applicants using a CTSO-C204a SBAS CCA sensor must perform the environmental qualification with the SBAS CCA in the English Translation Version for Reference Only CAAC CTSO-C145e - 6 - end-use equipment. h. Software Qualification. If the article includes software, develop the software according to RTCA/DO-178C, Software Considerations in Airborne Systems and Equipment Certification, dated December 13, 2011, including referenced supplements as applicable, to at least the software level consistent with the failure condition classification defined in paragraph 3.e of this CTSO. The applicant may also develop the software according to RTCA/DO-178B, dated December 1, 1992. (2) Applicants using a CTSO-C204a SBAS CCA sensor may use CTSO-C204a as substantiation for the software qualification. i. Electronic Hardware Qualification. If the article includes complex custom airborne electronic hardware, develop the component according to RTCA/DO-254, dated April 19, 2000, Design Assurance Guidance for Airborne Electronic Hardware, to at least the design assurance level consistent with the failure condition classification defined in paragraph 3.e of this CTSO. For custom airborne electronic hardware determined to be simple, RTCA/DO-254, paragraph 1.6 applies. (2) Applicants using a CTSO-C204a SBAS CCA sensor may use CTSO-C204a as substantiation for the hardware qualification. j. Barometric-aided Fault Detection and Exclusion (FDE). English Translation Version for Reference Only CAAC CTSO-C145e - 7 - If the equipment uses barometric-aiding to enhance FDE availability, then the equipment must meet the requirements in RTCA/DO-229E, appendix G. k. Deviations. For using alternative or equivalent means of compliance to the criteria in this CTSO, the applicant must show that the equipment maintains an equivalent level of safety. Apply for a deviation under the provision of 21.368(a) in CCAR-21R4. 4. Marking. a. Mark at least one major component permanently and legibly with all the information in 21.423(b) of CCAR-21R4. The marking must include the serial number. b. Also, mark the following permanently and legibly, with at least the manufacturers name, subassembly part number, and the CTSO number: (1) Each component that is easily removable (without hand tools); and, (2) Each subassembly of the article that manufacturer determined may be interchangeable. c. If the article includes software and/or airborne electronic hardware, then the article part numbering scheme must identify the software and English Translation Version for Reference Only CAAC CTSO-C145e - 8 - airborne electronic hardware configuration. The part numbering scheme can use separate, unique part numbers for software, hardware, and airborne electronic hardware. d. The applicant may use electronic part marking to identify software or airborne electronic hardware components by embedding the identification within the hardware component itself (using software) rather than marking it on the equipment nameplate. If electronic marking is used, it must be readily accessible without the use of special tools or equipment. e. At least one major component must be permanently and legibly marked with the operational equipment class (for example, Class 2) as defined in RTCA/DO-229E, Section 1.4.2. 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: (1) Operating instructions and equipment limitations sufficient to describe the equipments operational capability. English Translation Version for Reference Only CAAC CTSO-C145e - 9 - (2) Describe in detail any deviations. (3) Installation procedures and limitations sufficient to ensure that the SBAS sensor, when installed according to the installation or operational procedures, still meets this CTSOs requirements. Limitations must identify any unique aspects of the installation. The limitations must include a note with the following statement: “This article meets the minimum performance and quality control standards required by a CTSO. Installation of this article requires separate approval.” (4) For each unique configuration of software and airborne electronic hardware, reference the following: (a) Software part number including revision and design assurance level; (b) Airborne electronic hardware part number including revision and design assurance level; (c) Functional description. (5) A summary of the test conditions used for environmental qualifications for each component of the article. For example, a form as described in RTCA/DO-160G, Environmental Conditions and Test Procedures for Airborne Equipment, Appendix A. (6) Schematic drawings, wiring diagrams, and any other documentation necessary for installation of the SBAS sensor. English Translation Version for Reference Only CAAC CTSO-C145e - 10 - (7) List of replaceable components, by part number, that makes up the SBAS sensor. Include vendor part number cross-references, when applicable. (a) If the equipment can satisfy the requirements of RTCA/DO-229E only when used with a particular antenna, make the use of that antenna (by part number) a requirement on the installation. Include this requirement in the installation manual (IM) as a limitation. (b) If the equipment is installed with a standard antenna, include maximum tolerable currents and voltages into the antenna port. See CTSO-C144a, Passive Airborne Global Navigation Satellite System (GNSS) Antenna, applicable only to operational Class 1 equipment, or CTSO-C190, Active Airborne Global Navigation Satellite System (GNSS) Antenna, applicable to all equipment operational classes. b. Instructions covering periodic maintenance, calibration, and repair, for the continued airworthiness of the SBAS sensor. Include recommended inspection intervals and service life, as appropriate. c. If not using a CTSO-C204a SBAS functional sensor and the article includes software: a plan for software aspects of certification (PSAC), software configuration index, and software accomplishment summary. d. If not using a CTSO-C204a SBAS functional sensor and the article includes simple or complex custom airborne electronic hardware: a English Translation Version for Reference Only CAAC CTSO-C145e - 11 - plan for hardware aspects of certification (PHAC), hardware verification plan, top-level drawing, and hardware accomplishment summary (or similar document, as applicable). e. A drawing depicting how the article will be marked with the information required by paragraph 4 of this CTSO. f. Adequate specifics on the interface between the SBAS sensor and other systems to ensure proper functioning of the integrated system. If the equipment depends on any external inputs (like baro-aided FDE) to satisfy the requirements of RTCA/DO-229E, make those inputs a requirement in the installation. Include this requirement in the IM as a limitation. g. If the software qualification limits eligibility of the equipment to certain aircraft types, identify the qualification level, and that the equipment is not eligible for all aircraft types. For example, RTCA/DO-178B (or RTCA/DO-178C) Level C software may be associated with a hazardous failure condition for certain aircraft types. Identify other limitations applicable to the failure condition classification, for example, that two installed units are necessary. h. If the equipment has not been demonstrated as compatible with satellite communications (SatCom) record in the limitations section that the equipment should not be installed in SatCom equipped aircraft. i. Identify functionality or performance contained in the article not English Translation Version for Reference Only CAAC CTSO-C145e - 12 - evaluated under paragraph 3 of this CTSO (that is, non-CTSO functions). Non-CTSO functions are accepted in parallel with the CTSO authorization. For those non-CTSO functions to be accepted, you must declare these functions and include the following information with your CTSO application: (1) Description of the non-CTSO function(s), such as performance specifications, failure condition classifications, software, hardware, and environmental qualification levels. Include a statement confirming that the non-CTSO function(s) do not interfere with the articles compliance with the requirements of paragraph 3. (2) Installation procedures and limitations sufficient to ensure that the non-CTSO function(s) meets the declared functions and performance specification(s) described in paragraph 5.i.(1). (3) Instructions for continued performance applicable to the non-CTSO function(s) described in paragraph 5.i.(1). (4) Interface requirements and applicable installation test procedures to ensure compliance with the performance data defined in paragraph 5.i.(1). (5) Test plans, analysis and results, as appropriate, to verify that performance of the hosting CTSO article is not affected by the non-CTSO function(s). (6) Test plans, analysis and results, as appropriate, to verify the English Translation Version for Reference Only CAAC CTSO-C145e - 13 - function and performance of the non-CTSO function(s) as described in paragraph 5.i.(1). (7) Alternatively, identify non-CTSO functionality or performance contained in the article not evaluated under paragraph 3 and submit previously accepted data for the non-CTSO function for acceptance in parallel with this CTSO application. j. The quality system description required by section 21.358 of CCAR-21R4, including functional test specifications. The quality system should ensure that it will detect any change to the approved design that could adversely affect compliance with the CTSO MPS, and reject the article accordingly. k. Material and process specifications list. l. List of all drawings and processes (including revision level) that define the articles design. m. Manufacturers CTSO qualification report showing results of testing accomplished according to paragraph 3.f of this CTSO. 6. Manufacturer Data Requirements. Besides the data given directly to the authorities, have the following technical data available for review by the authorities: a. Functional qualification specifications for qualifying each production article to ensure compliance with this CTSO. English Translation Version for Reference Only CAAC CTSO-C145e - 14 - b. Equipment calibration procedures. c. Schematic drawings. d. Wiring diagrams. e. Material and process specifications. f. The results of the environmental qualification tests conducted according to paragraph 3.g of this CTSO. g. If the article includes software, the appropriate documentation defined in the version of RTCA/DO-178 or RTCA/DO-178C specified by paragraph 3.h of this CTSO, including all data supporting the applicable objectives in Annex A, Process Objectives and Outputs by Software Level. h. If the article includes complex custom airborne electronic hardware, the appropriate hardware life cycle data in combination with design assurance level, as defined in RTCA/DO-254, Appendix A, Table A-l. For simple custom airborne electronic hardware, the following data: test cases or procedures, test results, test coverage analysis, tool assessment and qualification data, and configuration management records, including problem reports. i. If not using CTSO-C204a, all the data necessary to evaluate the geo stationary (GEO) satellite bias as defined in RTCA/DO-229E, Section .5. j. If the article contains non-CTSO function(s), the applicant must English Translation Version for Reference Only CAAC CTSO-C145e - 15 - also make available items 6.a through 6.h as they pertain to the non-CTSO function(s). 7. Furnished Data Requirements. a. If furnishing one or more articles manufactured under this CTSO to one entity (such as an operator or repair station), provide one copy or technical data and information specified in paragraphs 5.a and 5.b of this CTSO. Add any data needed for the proper installation, certification, use, or for continued compliance with the CTSO, of the SBAS sensor. b. If the article contains declared non-CTSO function(s), include one copy of the data in paragraphs 5.i.(1) through 5.i.(4). 8. Availability of Referenced Documents. Order RTCA documents from: Radio Technical Commission for Aeronautics, Inc. 1150 18th Street NW, Suite 910, Washington D.C. 20036 You may also order them online from the RTCA Internet website at: . English Translation Version for Reference Only CAAC CTSO-C145e - 16 - APPENDIX 1. END-USE EQUIPMENT MANUFACTURER TESTS FOR SBAS CCA FUNCTIONAL POSITION, VELOCITY, TIME (PVT) SENSORS USED FOR NAVIGATION AND NON-NAVIGATION APPLICATIONS 1. Scope. This appendix describes the required supplementary equipment level testing, in addition to the environmental testing of RTCA/DO-229E, section 2.4, required by the end-use equipment manufacturer to receive a CTSO-C145e Class Beta authorization when using a CTSO-C204a SBAS CCA functional sensor. These test procedures are intended to streamline and simplify the CTSO-C145e authorization process for the end-use equipment manufacturer by allowing credit for the design and selected testing done at the SBAS CCA functional sensor level. However, the end-use equipment manufacturer retains full responsibility for the design and control of the article per their CTSO-C145e CTSOA. 2. General Principles. (a) Testing methods for GPS/SBAS equipment have been standardized by RTCA/DO-229E and serve as the basis for CTSO-C145e. RTCA/DO-229E was written with the perspective of equipment that can be installed on aircraft. Section 2.4 specifically addresses the issues of the environment in which the equipment operates and provides approved test methods to validate performance in this environment. Section 2.4 English Translation Version for Reference Only CAAC CTSO-C145e - 17 - represents RTCA consensus in identifying which RTCA/DO-229E requirements are sensitive to environmental effects. These requirements are listed in the environmental tables referenced in section 2.4.1. (b) The determination that a MOPS requirement is susceptible to the environment does not depend on whether or not the implementation is a CCA within some host equipment. This is the same concept as an equipment enclosure designed to protect against a benign environment compared to one designed for a severe environment; the identification of susceptible requirements is the same. (c) Therefore this appendix uses the tables of RTCA/DO-229E, section 2.4.1 to identify the MOPS requirements susceptible to environmental affects for an SBAS CCA functional sensor in the end-use equipment. The focus is on the change in environment seen by the SBAS CCA functional sensor as a result of its installation in the end-use equipment. For example, other components inside the end-use equipment may radiate RF energy that could interfere with the GPS functions; therefore the ambient testing done at CCA level is not equivalent to tests done in the end-use equipment. This is the basis for defining the RTCA/DO-229E, section 2.5 performance tests that need to be repeated by the end-use equipment manufacturer. (d) The Class Beta environmental table referenced in RTCA/DO-229E, section 2.4.1 are the prime source to determine the English Translation Version for Reference Only CAAC CTSO-C145e - 18 - MOPS performance requirements susceptible to environmental conditions. Based on the table, the susceptible requirements can be grouped in two categories: those susceptible to most types of environmental conditions (described in section 3) and those susceptible to just a few (described in section 4). Note: The Tables for Class Beta-1, -2, and -3 equipment identify similar requirements susceptible to the installed environment. The only difference is the applicable MOPS requirements consistent with the operational class (i.e., class -1, - 2, or -3). 3. Performance Requirements Susceptible to Most Environmental Conditions. The RTCA/DO-229E requirements for Accuracy (, , and ) and Sensitivity and Dynamic Range (0) are sensitive to most environmental conditions. However, these requirements are linked to the message loss rate requirement in .2. Section 3.1 and 3.2 below identifies the testing end-use equipment manufacturers are required to repeat to demonstrate the SBAS CCA functional sensor continues to meet the Accuracy, Dynamic Range, and Message Loss Rate performance requirements after installation in the end-use equipment. All tests will be run under conditions where the end-use equipment functions are fully enabled to create the worst-case environment. 3.1 RTCA/DO-229E, 2.5.8 Accuracy Test. English Translation Version for Reference Only CAAC CTSO-C145e - 19 - (a) The accuracy test described in section 2.5.8 is actually a joint test covering both accuracy, and sensitivity and dynamic range. This joint testing also applies under environment as stated in section .5 with environmental adaptation as described in section .1. (b) The demonstration of accuracy is done in accordance with section only for the test case with a broadband external interference noise. This test must be repeated when the CCA is installed in the end-use equipment and it is sufficient to perform it using broadband interference. (1) The environmental testing is limited to broadband interference as it represents the worst case signal to noise condition which is the most sensitive to environmental effects. This applies equally to the environment for the CCA created by the end-use equipment. (2) Section 2.5.8 contains a measurement accuracy test in with the detailed test procedure in . The test must be run under the worst case environment identified in the “Additional considerations for internal interference sources” section below. The measurement accuracy testing can be combined with the message loss rate testing in . (3) Section is a 24-Hour actual satellite accuracy test. The section test exposes the equipment to a variety of signal conditions and data processing conditions over varying satellite geometry English Translation Version for Reference Only CAAC CTSO-C145e - 20 - that will increase confidence that no unforeseen interactions between components within the end-use equipment and the SBAS CCA functional sensor goes undetected. The 24 hr testing in can be combined with the 24 hr message loss rate testing in (see Additional Considerations for Internal Interference Sources section). (4) Section (SBAS Tracking Bias) is an analysis of the GPS hardware and is therefore not necessary to repeat at the end-use equipment level as long as no extra RF components that affect the RF filtering response are inserted in the RF path. Otherwise the end-use equipment manufacturer must repeat the SBAS Tracking Bias test as well. (c) The test threshold is relaxed from 110% to 125% as specified in table 2-25 of the .1 test procedure to shorten test time. However, Section 2.5.8 testing (excluding the SBAS Tracking Bias test in ) for the CCA in the end-use equipment shall be under ambient conditions per section 2.5 with the 110% test pass threshold for maximum test sensitivity. (d) The Section 2.5.8 testing (excluding the SBAS Tracking Bias test in ) will be repeated against the accuracy requirement consistent with the desired operational class (i.e., , , and accuracy requirements as appropriate). (e) Only the broadband external interference noise test case using English Translation Version for Reference Only CAAC CTSO-C145e - 21 - minimum satellite power will be executed in most cases to shorten test time. Section testing will be repeated for both minimum and maximum satellite power for the worst case environment only. 3.2 RTCA/DO-229E, 2.5.2 Message Loss Rate Test. (a) Section 2.5.2 specifies the message loss rate test for the .2 message loss rate requirement. This test is conducted in conjunction with the 2.5.8 accuracy testing. Section defines the test procedure to collect data verifying the SBAS message loss rate in the presence of interference using the test cases where the SBAS satellite is at minimum power. Section defines the pass/fail criteria. (b) The test in section will be performed during the measurement accuracy broadband interference test case described in paragraph 3.1. (c) The test procedure in section .1 is run in conjunction with the 24-hour accuracy test. Section .2 defines the pass/fail criteria for the test case described in paragraph 3.1(b)(3). 4. Performance Requirements Partially Susceptible to Environmental Conditions. (a) The class Beta tables (tables 2-14, 2-16, and 2-18) in section 2.4.1 of RTCA/DO- 229E indicates the requirements for Initial Acquisition Time () and Satellite Reacquisition Time () are sensitive to four environmental conditions: Icing, Lightning Induced English Translation Version for Reference Only CAAC CTSO-C145e - 22 - Transient Susceptibility, Lightning Direct Effects, and Normal/Abnormal Operating Conditions. The requirements for Loss of Navigation (3.2, 2.2, and 2.2) and Loss of Integrity (3.1, 2.1, and 2.1) are sensitive to low and high operating temperature. (b) The Lightning Induced Transient Susceptibility, Lightning Direct Effects, or Icing environmental conditions are not pertinent to the environment created by the end-use equipment relative to the SBAS CCA functional sensor. However, the end-use equipment manufacturer remains responsible for meeting the overall environmental qualification at the end-use equipment level. (c) Loss of navigation and loss of integrity indications are limited to temperature testing and the information in RTCA/DO-229E, sections .2 and .3 is appropriate. The purpose is to ensure that the interface used to indicate the loss of navigation is functional under environmental conditions after the SBAS CCA functional sensor is installed in the end-use equipment. Sections .2 and .3 indicate that any source that generates the indication can be used since it is the interface and not the detection mechanism that is verified. The temperature testing done at the end-use equipment level is the worst-case scenario. It is not necessary to repeat the CCA level test at room temperature in the end-use equipment since the environmental English Translation Version for Reference Only CAAC CTSO-C145e - 23 - qualification adequately addresses testing for these requirements. (d) RTCA/DO-160E section 16 relates to aircraft power supply (refer to TSO paragraph 3.g for environmental qualification requirements). Sections and are for supply voltage modulation (ac) /ripple (dc). Given the potential susceptibility of the SBAS CCA functional sensor to power supply noise, it is prudent to repeat tests at the end-use equipment level on this basis. (e) Sections 4.1 and 4.2 identify the testing end-use equipment manufacturers are required to repeat to demonstrate the SBAS CCA functional sensor continues to meet the Acquisition Time and Reacquisition Time performance requirements relative to Normal/Abnormal Operating Conditions after installation in the end-use equipment. All tests will be run under conditions where the end-use equipment functions are fully enabled to create the worst-case environment. 4.1 2.5.4 Initial Acquisition Test Procedures. The information in RTCA/DO-229E, section .4 on the initial acquisition test in section 2.5.4 applies. The end-use equipment manufacturer shall repeat the initial acquisition testing described in RTCA/DO-229E, section 2.5.4. 4.2 2.5.6 Satellite Reacquisition Time Test. The end-use equipment manufacturer is required to repeat the English Translation Version for Reference Only CAAC CTSO-C145e - 24 - Satellite Reacquisition Time testing in RTCA/DO-229E, section 2.5.6. 5. Additional Considerations for Internal Interference Sources. (a) Installing a SBAS CCA functional sensor into end-use equipment that also includes other functions requires careful evaluation of potential internal radiated and conducted interference. The end-use equipment manufacturer must evaluate each operating mode to determine if the mode changes the environment for the installed SBAS CCA functional sensor. If there is only one environment or there is clearly one worst case environment, then the accuracy and message loss rate testing in section 3 can be run in that operating mode only. For example, if the end-use equipment includes an RF transmitter that radiates at one frequency; one could reasonably argue that setting the transmitter at full power with maximum data throughput will generate a clear worst-case environment in which to run all testing. (b) In the case of multiple environments, the accuracy and message loss rate tests can either be run under each environment or the methodology in RTCA/DO-229E, section .3 can be used to run an aggregate with approximately equal time in each mode. The methodology in section .3 must be used to identify modes of greatest susceptibility under which the combined accuracy and message loss rate are repeated in addition to the aggregate test. For example, the .3 methodology is appropriate for end-use equipment that contains a high English Translation Version for Reference Only CAAC CTSO-C145e - 25 - power transmitter operating on a large number of frequencies such that it is impractical to run a test at each frequency. This is analogous to the large number of frequencies that need to be tested during RTCA/DO-160E RF and Induced Signal Susceptibility testing and is the reason why the section .3 methodology was developed. (c) It is sufficient to identify one worst case environment when performing acquisition and 24 hour accuracy testing. 6. Summary. (a) The end-use equipment manufacturer that incorporates an SBAS CCA functional sensor is required to repeat the following RTCA/DO-229E, section 2.5 testing under ambient conditions (see section 5) after installing the SBAS CCA functional sensor in the end-use equipment: ? The section 2.5.8 Accuracy (excluding the SBAS Tracking Bias test in ) adapted per section .1 except that the 110% test pass threshold is used. Note: Excluding the SBAS Tracking Bias test is acceptable, provided the end-use equipment does not insert in the RF signal path, components that affect the filtering response. Otherwise the end-use equipment manufacturer must repeat the SBAS Tracking Bias test as well. ? The section 2.5.2 Message Loss Rate Test. English Translation Version for Reference Only CAAC CTSO-C145e - 26 - ? The section 2.5.4 Initial Acquisition Test. ? The section 2.5.6 Satellite Reacquisition Time Test. (b) The end-use equipment manufacturer remains responsible for completing a full environmental qualification evaluation (see CTSO paragraph 3.g) at the end-use equipment level. The end-use equipment manufacturer that incorporates an SBAS CCA functional sensor is required to repeat Loss of Navigation indication and Loss of Integrity indication as part of the environmental qualification according to RTCA/DO-229E, sections .2 and .3 respectively. English Translation Version for Reference Only CAAC CTSO-C145e - 27 - APPENDIX 2. ADDITIONs TO RTCA/DO-229E. This appendix describes required modifications and additions to RTCA/DO-229E for compliance with this CTSO. This appendix adds a new section 1.8.3 on cybersecurity and GPS spoofing mitigation and corrects a long-standing mistake in the section 2.4 environmental requirements tables. The new section 1.8.3 contains no new requirements but provides information for cybersecurity and spoofing mitigation to make RTCA/DO-229E consistent with the new RTCA MOPS template and RTCA/DO-253D. 1.8.3 Cybersecurity and Spoofing Mitigation. This section contains information to address intentional interference to the GPS. Spoofing is caused by RF waveforms that mimic true signals in some ways, but deny, degrade, disrupt, or deceive a receivers operation when they are processed. Spoofing may be unintentional, such as effects from the signals of a GPS repeater, or may be intentional and even malicious. There are two classes of spoofing. Measurement spoofing introduces RF waveforms that cause the target receiver to produce incorrect measurements of time of arrival or frequency of arrival or their rates of change. Data spoofing introduces incorrect digital data to the target receiver for its use in processing of signals and the calculation of PNT. Either class of spoofing can cause a range of effects, from incorrect English Translation Version for Reference Only CAAC CTSO-C145e - 28 - outputs of PNT to receiver malfunction. The onset of effects can be instantaneous or delayed, and the effects can continue even after the spoofing has ended. Improperly used or installed GNSS re-radiators act like spoofers. Re-radiators replay and GNSS emulator devices can present misleading information to GNSS equipment and/or could cause lasting effects. Equipment manufacturers should implement measures to mitigate processing of erroneous data. Cross-checks of GNSS sensor data against independent position sources and/or other detection monitors using GNSS signal metrics or data checks can be implemented in the antenna, receiver, and/or through integration with other systems at the aircraft level. Data validity checks to recognize and reject measurement and data spoofing should be implemented in the receiver. Additional guidance and best practices related to GPS equipment can be found in the U.S. Department of Homeland Security document “Improving the Operation and Development of Global Positioning System (GPS) Equipment Used by Critic
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