CTSO-C179b 可充电锂电池和电池系统

日期：2024 年 1 月 15 日局长授权

批准：

中国民用航空技术标准规定

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。

可充电锂电池和电池系统

1. 目的

本技术标准规定（CTSO）适用于为可充电锂电池和电池系统申请技术标准规定项目批准书（CTSOA）的制造人。本 CTSO 规定了可充电锂电池和电池系统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。

a ． 自本 CTSO 生效之日起，欲获得可充电锂电池和电池系统CTSOA 的申请人应按照本 CTSO 提交申请。但如果自本 CTSO 生效之日起 6 个月内，申请人能够向局方表明在新版本生效前一直按照CTSO-C179a 的最低性能标准进行研制，可以按 CTSO-C179a 提交申请。

b ． 自本 CTSO 生效之日起，按 CTSO-C179a 获得 CTSOA 的设备可以按批准时的规定继续制造。

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CAAC CTSO-179b

c ．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 标记进行标识的可充电锂电池和电池系统应满足 RTCA/DO-311A《可充电锂电池和电池系统最低运行性能标准》（2017 年 12 月 19 日发布）中第 1节和第 2 节中的最低性能标准和资料要求。RTCA/DO-311A 附录 C的内容并未得到局方认可。RTCA/DO-311A 第 1.4.1 节和第 1.4.2 节列出了能量类别和通风类别，试验将基于这些类别，并且按照本 CTSO第 4 节中的要求进行标记。

a ．功能

本 CTSO 的标准适用于预期为航空器设备或应急系统提供电源的可充电锂电池、电池组和电池系统。本 CTSO 的标准不适用于预期为航空器电推进系统提供电源的可充电锂电池、电池组和电池系统。

b ．失效状态类别

本 CTSO 没有标准的最低失效状态类别。设备适用的失效状态类别取决于其在特定航空器的预期用途。在设备设计时应记录其功能丧失和故障的失效状态类别。

c ．功能鉴定

应按 RTCA/DO-311A 中第 2.4.4 节的试验程序，证明产品性能满足第 2.2.1 节的要求。

d ．环境鉴定

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应按 RTCA/DO-311A 中第 2.3 节中试验条件（注：试验条件直接引用 RTCA/DO- 160G《机载设备环境条件和试验程序》（2010 年 12月 8 日发布）的章节），采用该设备适用的标准环境条件和试验程序，证明设备性能满足要求。申请人也可采用 RTCA/DO- 160G 以外的，其它适用于可充电锂电池、电池组和电池系统的标准环境条件和试验程序。

注：通常情况下，RTCA/DO-160D（包括 Change 1 和 Change 2）或早期版本不再适用，如果使用该版本则需按照本 CTSO 第 3.g 节中的偏离要求进行证明。

e ．软件鉴定

如果设备包含软件，则软件应按照 RTCA/DO- 178C《机载系统和设备合格审定中的软件考虑》（2011年 12 月 13 日发布）或其最新版本进行软件研制，包含参考的补充文件（如适用）。软件等级应至少与本 CTSO 第 3.b 节定 义的 失效 状态 类别 一致。 如按 照RTCA/DO- 178B（1992 年 12 月 1 日发布）进行软件研制，需与局方沟通确认，局方有权要求申请人在满足 RTCA/DO- 178B 同时还需要满足其它额外要求。

f．电子硬件鉴定

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 年 4 月 19 日）的要求进行研制。硬件的设计保证等级应与本 CTSO 第 3.b 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

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要求处理。

g ．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。

4. 标记

a ．应为每个锂电池或电池系统设置永久清晰的标记。标记应包括 CCAR-21-R4 第 21.423 条（二）款和 RTCA/DO-311A 第 2.1.3 节规定的所有信息。标记必须包含设备序列号。

b ．根据下表标记锂电池和电池系统（设备）：将 CTSO 标记为CTSO-C179b CLASSA-XY 或 CTSO-C179b CLASS B-XY，如下所示（其中 X 代表能量类别，Y 代表通风类别）：

CTSO-C179b CLASS A：在 RTCA/DO-311A 第 2.4.5.5 节电池热包容性试验期间，电池内的所有电芯均发生热失控。

CTSO-C179b CLASS B：在 RTCA/DO-311A 第 2.4.5.5 节电池热包容性测试期间，电池内并非所有电芯发生热失控。

能量类别（X）

通风类别（Y）

1

A

B

C

2

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3

4

（例如：CTSO-C179b CLASS B- 1A 是一种可充电锂电池和电池系统，能量类别为 1，通风类别为 A，在 RTCA/DO-311A 第 2.4.5.5节试验时，并非所有电芯都进入热失控状态。）

c ．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）每个易于拆卸的部件（无需手持工具）；

（2）制造人确定的设备中可互换的所有组件。

d ．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。

e ．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。

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

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设计和生产批准。提交资料包括 CCAR-21-R4 第21.353 条（一）款 1项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（使用）说明和设备限制，该内容应对设备运行能力（使用特性）进行充分描述。

（2）对所有偏离的详细描述。

（3）试验结果汇总，包括合格/不合格标准和本 CTSO 第 3 节规定的可报告信息。

（4）安装程序和限制。必须确保按照此安装程序安装设备后，设备符合本 CTSO 的要求。限制中必须识别出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。”

（5）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。

（6）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- 160G《机载设备环境条件和试验程序》附录 A 的表格方式描述。

（7）原理图、布线图，以及设备安装所必需的其它文件。

（8）设备的可更换部件清单（注明件号）。如适用，包括对供

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应商件号的交叉索引。

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．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.f.(1)节所声明的功能和性能规范。

（3）第 5.f.(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.f.(1)节性能资料要求的符合性。

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（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.f.(1)节描述的非 CTSO 功能的功能和性能。

g．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。当前持有 CTSOAs 的申请人必须在必要时对现有的质量手册提交修订。

h ．按 CCAR-21-R4 第21.355 条的要求提供组织机构说明。

i ．材料和工艺规范清单。

j ．定义设备设计的图纸和工艺清单（包括修订版次）。

k ．制造人的 CTSO 鉴定报告，表明按本 CTSO 第 3.c 节完成的试验结果。

l ．试验结果副本，包括根据本 CTSO 第 3 节进行试验的方法、数据和试验报告。

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。

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e ．材料和工艺规范。

f．按本 CTSO 第 3.d 节要求进行的环境鉴定试验结果。

g ． 如设 备包 含软 件， 提供 本 CTSO 第 3.e 节所 要求 的RTCA/DO- 178C 或 RTCA/DO- 178B 中规定的相关文档，包括所有支持RTCA/DO- 178C 或RTCA/DO- 178B 附录A“软件等级的过程目标和输出” 中适用目标的资料。

h ．如果设备包含复杂电子硬件，应提供 RTCA/DO-254 附录 A表 A-1 中定义的与研制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：试验用例或程序，试验结果，试验覆盖率分析，工具评估和鉴定资料，构型管理记录并包含问题报告。

i ．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，应随设备提供本 CTSO 第 5.a 节和第 5.b 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.f.(1)节至第 5.f.(6)节所规定资料的副本。

8. 引用文件

RTCA 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

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也可通过网站 www.rtca.org 订购副本。

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附录 1 可充电锂电池和电池系统最低性能标准

本附录规定了可充电锂电池和电池系统的最低性能标准（MPS），适用的标准是 RTCA/DO-311A《可充电锂电池和电池系统最低性能标准》（2017 年 12 月 19 日发布），并对其做如下修订：

RTCA/DO-311A

章节号和标题

原文内容

修订内容

1.7 参考

新增：GB/T 38031-2020电动汽车用动力蓄电池安全要求。

新增：GB/T 31486-2015电动汽车用动力蓄电池电性能要求及试验方法。

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1.8. 定义热失控

热失控：由电芯内材料的放热化学反应驱动的电池电芯的快速自持加热。热失控通常表现为温度和压力的急剧增加和电池电压的下降。

热失控：由电芯内材料的放热化学反应驱动的电池电芯的快速自持加热。热失控通常表现为温度和压力的急剧增加和电池电压的下降。热失控判定条件为：

a) 触发 对象 产生 电压降，且下降值超过初始电压的 25%；

b) 监测点温度达到制造商规定的最高工作温度；

c) 监测 点的 温升 速率dT/dt>1℃/s，且持续 3s以上。

当a)和c)或者b)和c)发生时，判定发生热失控。

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1.8.1 缩略语

新增： CAAC Civil aviation administration of China；

新增： CTSO China Technical Standard

Order。

2.1.3.1 独立电池标记

c. 此外，如适用，还应包括以下信息。

1). 资格 标志（ TSO、 ETSO，UL，UN 等）

2).改装编号或字母

3).重量

1). 资格 标志 （ TSO、 ETSO、CTSO，UL，UN等）

2). 改装编号或字母

3). 重量

新增：d. 电池单体的标记参考 2.1.3.2 嵌入式电池标记要求。

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2.4.4.4.1 手柄强度试验方法

a. EUT 上的每个手柄应承受 2 倍于 EUT 重量的载荷。载荷方向垂直向上。

a. EUT 上的每个手柄应承受 2 倍于 EUT 重量的载荷。载荷方向应与手柄提起电池的承力方向一致。

2.4.4.13.1 独立电池的过放试验

c.被测设备处于室温下，在放电的被测设备的正极和负极端子之间连接一个 1 欧姆电阻（或防止过电流跳闸所需的最小电阻）。电阻应保持连接，直到 EUT 电压低于EPV 的 5%。

c.被测设备处于环境温度下，在放电的被测设备的正极和负极端子之间连接一个 1 欧姆电阻（或防止过电流跳闸所需的最小电阻）。电阻应保持连接，直到 EUT 电压低于EPV 的 5%。对于具备充放电管理系统设计的电池和电池系统，通过管理系统完成过放电，直到EUT 电压低于 EPV 的5%。

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2.4.4.13.2 嵌入电池的过放试验

2.4.5.4.1 过充触发单体电池热失控包容性试验

i. 切断电源后，继续监视 EUT 16 小时。

i. 切断电源后，继续监视EUT 8 小时。

2.4.5.4.2 过热触发单体电池热失控包容性试验

h. 移除加热源后，继续监视 EUT 16 小时。

h. 移除加热源后，继续监视 EUT 8 小时。

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2.4.5.5 电池 热失控包容性试验

在这种情况下，需要与FAA 或适用的监管机构进行协调以满足本标准。

在这种情况下， 需要与CAAC 或适用的监管机构进行协调以满足本标准。

2.4.5.5.1 过充触发电池组热失控包容性试验

f. 初始热失控事件发生后，继续监测 EUT 16 小时。

f. 初始热失控事件发生后，继续监测 EUT 8 小时。

2.4.5.5.2 过热触发电池组热失控包容性试验

g. 初始热失控事件发生后，继续监测 EUT 16 小时。

g. 初始热失控事件发生后，继续监测 EUT 8 小时。

附录 AA.6 航运

删除：“在美国，49CFR的 100-185 部分规定了这些要求。”

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Number：CTSO-C179b

Date of approval：January 17, 2024

Approved by：Xu Feng

China Civil Aviation Technical Standard Order

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.

Rechargeable Lithium Batteries and Battery Systems

1. Purpose.

This China Civil Aviation Technical Standard Order (CTSO) is for manufacturers applying for Rechargeable Lithium Batteries and Battery Systems CTSO authorization (CTSOA). This CTSO specifies the minimum performance standards that rechargeable lithium batteries and battery systems must meet for approval and identification with the applicable CTSO marking.

2. Applicability.

This CTSO affects new applications submitted after its effective date.

a. Since the effective date of this CTSO, applicants who wish to obtain the CTSOA of Rechargeable Lithium Batteries and Battery Systems should submit applications in accordance with this CTSO. CTSO-C179a will also remain effective until 6 months from this CTSO

CAAC CTSO-C179b

release. After this date, Civil Aviation Administration of China (CAAC) will no longer accept new applications for CTSO-C179a.

b. Since the effective date of this CTSO, equipment approved under CTSO-C179a may still be manufactured under the provisions of its original approval.

c. Major design changes to article approved under this CTSO will require a new authorization in accordance with Section 21.353 of CCAR-21-R4.

3. Requirements.

New models of rechargeable lithium cells and lithium batteries and battery systems identified and manufactured on or after the effective date of this CTSO must meet the minimum performance standards (MPS) and documentation requirements in section 1 and section 2 of RTCA document, DO-311A, Minimum Operational Performance Standards for Rechargeable Lithium Batteries and Battery Systems, dated December 19, 2017. The CAAC did not acknowledge Appendix C of RTCA/DO-311A. Section 1.4.1 and section 1.4.2 of RTCA/DO-311A lists the energy categories and venting categories. Testing will be based on these categories and must be identified as such in paragraph 4 of this CTSO.

a ．Functionality.

This CTSO’s Standards apply to equipment with rechargeable lithium cells, lithium batteries and battery systems intended to provide

power for aircraft equipment, including emergency systems. It should be noted that the standards specified in this CTSO do not extend to rechargeable lithium cells, lithium batteries, and battery systems intended to provide power for aircraft propulsion systems.

b. Failure Condition Classifications.

There is no standard minimum failure condition classification for this CTSO. The failure condition classification appropriate for the equipment will depend on the intended use of the equipment in a specific aircraft. Document the loss of function and malfunction failure condition classification for which the equipment is designed.

c. Functional Qualification

Demonstrate the required functional performance in section 2.2.1 of RTCA/DO-311A under the test conditions specified in section 2.4.4 of RTCA/DO-311A.

d. Environmental Qualification.

Demonstrate the required performance, under the test conditions specified in section 2.3 of RTCA/DO-311A, (Note: The test conditions directly quote the chapters of RTCA/DO-160G, Environmental Conditions and Test Procedures for Airborne Equipment, dated December 8, 2010), using standard environmental conditions and test procedures appropriate for airborne equipment. Applicants may use a different standard environmental condition and test procedure than

RTCA/DO- 160G provided the standard is appropriate for the rechargeable lithium cells, lithium batteries and battery systems.

Note: The use of RTCA/DO- 160D (with Changes 1 and 2 only) or earlier versions is generally not considered appropriate and will require substantiation via the deviation process as discussed in paragraph 3.g of this CTSO.

e. 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.b of this CTSO. If RTCA/DO-178B, dated December 1, 1992, is used as a method of software development compliance, CAAC reserves the right to require applicants to meet additional requirements in addition to RTCA/DO- 178B.

f. Electronic Hardware Qualification.

If the article includes complex custom airborne electronic hardware, develop the component according to RTCA/DO-254, Design Assurance Guidance for Airborne Electronic Hardware, dated April 19, 2000, to at least the design assurance level consistent with the failure condition classification defined in paragraph 3.b of this CTSO. For custom airborne

electronic hardware determined to be simple, RTCA/DO-254, paragraph

1.6 applies.

g. Deviations.

For using alternative or equivalent means of compliance to the criteria in the MPS of this CTSO, the applicant must show that the equipment maintains an equivalent level of safety. Apply for a deviation pursuant to Section 21.368(a) in CCAR-21-R4.

4. Marking.

a. Mark each battery and battery system permanently and legibly with all of the information in Section 21.423(b) of CCAR-21-R4 and Section 2.1.3 of RTCA/DO-311A. The marking must include the serial number.

b. Mark the article based on the following table: Label the CTSO as CTSO-C179b CLASS A-XY or CTSO-C179b CLASS B-XY, as shown below (where -X stands for energy category and Y stands for venting category):

CTSO-C179b CLASS A: During the RTCA/DO-311A section, 2.4.5.5 Battery Thermal Runaway Containment Test, all cells within the battery enter thermal runaway.

CTSO-C179b CLASS B: During the RTCA/DO-311A section, 2.4.5.5 Battery Thermal Runaway Containment Test, not all cells within the battery enter thermal runaway.

Energy Category (X)

Venting Category (Y)

(For example: CTSO-C179b CLASS B- 1A would be a rechargeable lithium battery and battery system that is of energy category 1 and a venting category A and not all the cells entered thermal runaway during RTCA/DO-311A section 2.4.5.5 testing.)

c. Mark following components permanently and legibly, including the manufacturer’s name, subassembly part number, and CTSO number:

(1) Each component that is easily removable (without hand tools);

(2) Each subassembly of the article that manufacturer determined may be interchangeable.

d. If the article includes software and/or airborne electronic hardware, then the article part numbering scheme must identify the software and airborne electronic hardware configuration. The part numbering scheme can use separate, unique part numbers for software, hardware, and airborne electronic hardware.

e. The applicant may use electronic part marking to identify software

and 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.

5. Application Data Requirements.

The applicant must give CAAC a statement of conformance, pursuant to Section 21.353(a)(1) in CCAR-21-R4 and one copy each of the following technical data to support the design and production approval.

a. Manuals containing the following:

(1) Operating instructions and article limitations sufficient to describe the equipment’s operational capability.

(2) Detailed description of all deviations.

(3) A summary of test results including pass/fail criteria and the required reportable information according to paragraph 3 of this CTSO.

(4) Installation procedures and limitations sufficient to ensure that the article when installed according to installation or operational procedures, still meets this CTSO’s requirements. Limitations must identify any unique aspects of the installation. The limitations must also include a note with the following statement:

“This article meets the minimum requirements of technical standard

order. Installation of this article requires separate approval.”

(5) For each unique configuration of software and airborne electronic hardware, reference the following:

(i) Software part number including revision and design assurance level;

(ii) Airborne electronic hardware part number including revision and design assurance level;

(iii) Functional description.

(6) A summary of the test conditions used for environmental qualifications for each component of the article. For example, drafting a form as described in RTCA/DO-160G, Environmental Conditions and Test Procedures for Airborne Equipment, Appendix A.

(7) Schematic drawings, wiring diagrams, and any other documentation necessary for installation.

(8) By-part-number list of replaceable components that makes up the article. Include vendor part number cross-references, when applicable.

b. Instruction of continued airworthiness, including the requirements for periodic maintenance, calibration, and repair of equipment, to ensure that the article continues to meet the CTSO approved design. If applicable, the recommended inspection interval and service life should be included.

c. If the article includes software: a plan for software aspects of certification (PSAC), software configuration index, and software

accomplishment summary.

d. If the article includes simple or complex custom airborne electronic hardware: a 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. Identify functionality contained in the article not evaluated under paragraph 3 of this CTSO (defined as non-CTSO functions). Non-CTSO functions are accepted in parallel with the CTSOA. For those non-CTSO functions to be accepted, applicant must declare these functions and include the following information with the 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 article’s 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.f.(1).

(3) Instructions for continued performance applicable to the non-CTSO function(s) described in paragraph 5.f.(1).

(4) Interface requirements and applicable installation test procedures to ensure compliance with the non-CTSO function(s) data defined in paragraph 5.f.(1).

(5) Test plans and analysis as appropriate, to verify that performance of the hosting CTSO article is not affected by the non-CTSO function(s).

(6) Test plans and analysis as appropriate, to verify the function and performance of the non-CTSO function(s) as described in paragraph 5.f.(1).

g. The quality system description required by Section 21.358 of CCAR-21-R4, including functional test specifications. The quality system must ensure that you will detect any change to the approved design that could adversely affect compliance with the CTSO MPS, and reject the article accordingly. Applicants who currently hold CTSOAs must submit revisions to the existing quality manual as necessary (not required for applicants that don’t hold CTSOAs).

h. Provide a description of the organization as required by Section 21.355 ofCCAR-21-R4.

i. Material and process specifications list.

j. A List of all drawings and processes (including revision level) that define the article’s design.

k. Manufacturer’s CTSO qualification report showing results of

testing accomplished according to paragraph 3.c of this CTSO.

l. One copy of the test results including methods, data and test reports from testing in accordance with paragraph 3 of this CTSO.

6. Manufacturer Data Requirements.

Besides the data given directly to CAAC, have the following technical data available for review by CAAC:

a. Functional qualification specifications for qualifying each production article to ensure compliance with this CTSO.

b. Article 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.d of this CTSO.

g. If the article includes software, the appropriate documentation defined in RTCA/DO- 178B or RTCA/DO- 178C specified in paragraph 3.e of this CTSO, including all data supporting the applicable objectives in Annex A, Process Objectives and Outputs by Software Level of RTCA/DO- 178B or RTCA/DO- 178C.

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 are required: test cases or procedures, test results, test coverage analysis, tool assessment and qualification data, and configuration management records, including problem reports.

i. If the article contains non-CTSO function(s), you must also make items 6.a through 6.h available as they pertain to the non-CTSO function(s).

7. Furnished Data Requirements.

a. When furnishing one or more articles manufactured under this CTSO to one entity (such as an operator or repair station), provide one copy access to the data in paragraphs 5.a and 5.b of this CTSO. Add any other data needed for the proper installation, certification, use, or continued compliance with this CTSO.

b. If the article contains declared non-CTSO function(s), include one copy of the data in paragraphs 5.f.(1) through 5.f.(6).

8. Availability of Referenced Documents.

Order RTCA documents from RTCA Inc.1150 18th Street NW, Suite 910, Washington, D.C. 20036. You can also order copies online at www.rtca.org .

Appendix 1 Minimum Operational Performance Standard for

This appendix prescribes the minimum performance standards (MPS) for airplane galley insert equipment. The applicable standard is RTCA/DO-311A, Minimum Operational Performance Standards for Rechargeable Lithium Batteries and Battery Systems, dated December 19, 2017. We modified it as follows:

Current Wording

Modified Wording

1.7 References

Addition: “GB/T 38031-2020 Safety requirements for traction batteries for electric vehicles.”

Addition: “GB/T 31486-2015 Electrical performance

requirements and test methods for traction batteries for electric vehicles.”

1.8 Definition of Terms

Thermal Runaway:

Rapid self-sustained heating of a battery cell driven by exothermic chemical

reactions of the materials within the cell. Thermal runaway is generally evidenced by a sharp increase in temperature and pressure and a drop in cell voltage.

Rapid self-sustained heating of a battery cell driven by exothermic chemical reactions of the materials within the cell. Thermal runaway is generally evidenced by a sharp increase in temperature and pressure and a drop in cell voltage. The criteria for thermal runaway determination are as follows:

a) The triggering entity experiences a voltage drop, with a decrease exceeding 25% of the initial voltage.

b) The temperature at the monitored location reaches the maximum working temperature specified by the manufacturer.

c) The rate of temperature rise at the monitored location, represented as dT/dt > 1℃/s and sustains for a minimum duration of 3 seconds.

The occurrence of thermal runaway is determined when either a) & c) or b) & c) are satisfied.”

1.8.1 Acronyms and Abbreviations

Addition： CAAC Civil aviation administration of China；

Addition： CTSO China Technical Standard Order.

2.1.3.1 Standalone Battery Marking

c. In addition, the following information should be included as applicable.

1. Qualification marking (TSO, ETSO, UL, UN, etc.)

2. Modification numbers or letters

3. Weight

c. In addition, the following information should be included as applicable.

1. Qualification marking (CTSO, TSO, ETSO, UL, UN, etc.)

2. Modification numbers or letters

Addition: d. The marking requirements for cells should be in accordance with the section 2.1.3.2. Embedded Battery Marking.

2.2.1.6 Capacity at Low and High Temperatures

The battery shall comply with the low and high temperature capacity values declared in the design documentation when discharged at the Operating Low and Operating High Temperatures (per Section 4 of RTCA/DO-160 for the category declared by the manufacturer).

The battery shall comply with the low and high temperature capacity values declared in the design documentation when discharged at the Operating Low and Operating High Temperatures (per Section 4 of RTCA/DO- 160G for the category declared by the manufacturer).

2.3.1 Environmental

Performance Requirements

The environmental test procedures are contained in RTCA/DO-160. The

following performance

requirements apply when

The environmental test procedures are contained in RTCA/DO- 160G. The

following performance

requirements apply when

performing environmental tests.

performing environmental tests.

2.4.4.4.1 Test Method

a. Each handle on the EUT shall be subjected to a load of 2 times the EUT weight. The load shall be applied in a vertical upward direction.

a. Each handle on the EUT shall be subjected to a load equal to 2 times the EUT weight. The load should be applied in consistent with the direction of the handle lifting the battery."

2.4.4.13.1 Test Method for Standalone Batteries

c. With the EUT at ambient temperature, connect a 1 ohm resistor (or the minimum resistance needed to prevent overcurrent tripping) between the positive and negative terminals of the discharged EUT. The resistor shall remain connected until the EUT voltage is below 5% of the EPV.

c. With the EUT at ambient temperature, connect a 1 ohm resistor (or the minimum resistance needed to prevent overcurrent tripping) between the positive and negative terminals of the discharged EUT. The resistor shall remain connected until the EUT voltage is below 5% of the EPV. For EUT with a charge/discharge management system, over-discharge can be achieved through the management system until the EUT voltage is below 5% of the EPV.

2.4.4.13.2 Test Method for Embedded Batteries

c. With the EUT at ambient temperature, connect a 1 ohm resistor (or the minimum resistance needed to prevent overcurrent tripping) between the positive and negative terminals of the discharged battery. The resistor shall remain connected until the battery voltage is below 5% of the EPV.

2.4.5.4.1 Test Method for

i. Continue to monitor the

i. Continue to monitor the

Single Cell Thermal

Runaway via Overcharging

EUT for 16 hours after the power supply has been removed.

EUT for 8 hours after the power supply has been removed.

2.4.5.4.2 Test Method for Single Cell Thermal

Runaway via Overheating

h. Continue to monitor the EUT for 16 hours after the power to the heating device has been removed.

h. Continue to monitor the EUT for 8 hours after the power to the heating device has been removed.

2.4.5.5 Battery Thermal

Runaway Containment Test

In this case, compliance to this standard would require coordination with the FAA or applicable regulatory agency.

In this case, compliance to this standard would require coordination with the CAAC or applicable regulatory agency.

2.4.5.5.1 Test Method

Battery Thermal Runaway via Overcharging

f. Continue to monitor the EUT for 16 hours after the initial thermal runaway event.

f. Continue to monitor the EUT for 8 hours after the initial thermal runaway event.

2.4.5.5.2 Test Method for Battery Thermal Runaway via Overheating

g. Continue to monitor the EUT for 16 hours after the initial thermal runaway event.

g. Continue to monitor the EUT for 8 hours after the initial thermal runaway event.

Appendix AA.6 Shipping

Deletion: Delete “In the U.S., these regulations are found in 49 CFR Parts 100-185.”

(The English version is for reference only. In case of any discrepancy or ambiguity of meaning between this English translation and the Chinese version, the latter shall prevail.)