| No. |
Airworthiness Clause |
Advisory Circular |
Standard for Conformity Verification Tests Acceptable to Airworthiness Authorities |
| Equipment Level |
System Level |
| 1 |
25.1309 Equipment, system and installation |
AC21-16G |
RTCADO-160G Environmental Conditions and Test Procedures for Airborne Equipment |
SAEARP60493 Guide to Civil Aircraft Electromagnetic Compatibility |
| (a) For equipment, system and installation required for its functions in the aircraft airworthiness standard, the design must guarantee that the reserved functions can be completed under various predicable operation conditions. |
AC20-190 |
| 2 |
25.1316 System lightning protection |
AC20-136B |
SAEARP5412B Aircraft Lightning Environment and Related Test Waveforms
SAEARP5414B Aircraft Lightning Zone
SAEARP5415A Airworthiness Certification User Manual for Lightning Indirect Effects of Aircraft Electronic and Electrical Systems
SAEARP5416A Aircraft Lightning Test
SAEARP5577 Certification of Aircraft Lightning Direct Effect
|
| (a) The design and installations of each electrical and electronic systems that their function failure can influence or hinder the continuous safe flight and landing of the airplane must guarantee that works and working capacity of systems implementing these functions are not exerted on any negative influence when airplane encounters lightning environment. |
| (b) The design and installations of various electrical and electronic systems that their function failures can influence or reduce the aircraft capacity or lead to the unit's adverse operating conditions must guarantee that these functions can be recovered after airplane encounters lightning environment. |
| (c) The conformance of lightning protection standards in (a) and (b) of this article shall be based on severe lightning environment. The applicant shall design and verify the protection capacity of the airplane electrical / electronic system for lightning influences through the following methods: |
| (1) Confirm lightning area of the airplane; |
| (2) build external lightning environment within the lightning area; |
| (3) build external environment; |
| (4) judge all electronic and electrical systems meeting the requirements in this article and their positions on or within the airplane; |
| (5) confirm the sensitivity of the system to internal and external lightning environment; |
| (6) design protective measures; |
| (7) verify sufficiency of protective measures. |
| 3 |
25.1317 High intensity radiated field (HIRF) protection |
AC20-158A |
SAEARP 5583A Guide to Certification of Aircraft in a High Intensity Radiated Field (HIRF) Environment |
| (a) Otherwise stipulated in (d) of this article, the design and installation of each electronic and electrical systems that their function failure can influence or hinder continuous safety flight and landing of the airplane must comply with the following requirements: |
| (1) When the airplane is exposed to the HIRF environment I described in Appendix L and after its exposure, its function shall not be exerted on any negative influence; |
| (2) After the airplane is exposed to the HIRF environment I described in Appendix L, the system shall automatically restore its normal function in time, unless restoration of the system function is in conflict with other operational or functional requirements of the system; and |
| (3) When the airplane is exposed to the HIRF environment II described in Appendix L and after its exposure, its function shall not be exerted on any negative influence. |
| (b) The electronic and electrical system that its failure will reduce the airplane performance or unit's reaction capacity to adverse operating conditions shall be designed and installed. When the equipment providing these functions is exposed to the HIRF equipment test level 1 or 2 described in Appendix L, system shall not be influenced adversely. |
| (c) The electronic and electrical system that its failure will reduce the airplane performance or unit's reaction capacity to adverse operating conditions shall be designed and installed. When the equipment providing these functions is exposed to the HIRF equipment test level 3 described in Appendix L, system shall not be influenced adversely. |
| (d) Before December 1, 2012, if the design and installation of electronic or electrical systems that their function fault will hinder continuous safe flight and landing, the provisions of Article (a) may not be met if the following requirements are conformed to: |
| (1) The system has previously met the special conditions stipulated in CCAR21.16 issued before December 7, 2011; |
| (2) the HIRF anti-interference characteristic of the system have not changed since it conforms the special conditions; |
| (3) provide data previously indicating compliance with special conditions. |
