AMC1 29.1305(a)(4) Powerplant instruments

• ED Decision 2023/001/R found in: CS-29 Amdt 11 - Large Rotercraft (Feb 2023)

AMC1 29.1305(a)(4) Powerplant instruments ED Decision 2023/001/R FUEL QUANTITY INDICATOR AND LOW-FUEL LEVEL WARNING This AMC provides guidance in the case where the fuel quantity indicator and the low-fuel warning device are not fully independent. AC 29.1305 provides guidance that supports the use of specific instruments that do not meet the principle of independence (integrated avionics, ECAS, etc.). However, it does not provide guidance regarding the independence between the fuel quantity sensor and the fuel low-level sensor. The fuel quantity sensor and the fuel low-level sensor should be independent. However, it is considered to be acceptable to place them on the same supporting structure providing that the following design precautions are ensured: (a) They are electrically independent. Each sensor should be connected to the aircraft systems via a dedicated connector and a dedicated harness; (b) A test capability is provided for each sensor to preclude an associated latent failure; and (c) It is demonstrated by tests such as equipment qualification tests, slosh and vibration tests as requested in [CS 29.965](#_DxCrossRefBm1178332021), analysis (such as safety analysis, particular risk analysis, zonal safety analysis, comparison with a fully independent design), or a combination thereof that no common modes can lead to the most severe hazard determined in [CS 29.1305](#_DxCrossRefBm1178332004)(a)(4)(ii). [Amdt No: 29/11] ##### AMC1 29.1305(a)(4) Powerplant instruments *ED Decision 2023/001/R* **FUEL QUANTITY INDICATOR AND LOW-FUEL LEVEL WARNING** This AMC provides guidance in the case where the fuel quantity indicator and the low-fuel warning device are not fully independent. AC 29.1305 provides guidance that supports the use of specific instruments that do not meet the principle of independence (integrated avionics, ECAS, etc.). However, it does not provide guidance regarding the independence between the fuel quantity sensor and the fuel low-level sensor. The fuel quantity sensor and the fuel low-level sensor should be independent. However, it is considered to be acceptable to place them on the same supporting structure providing that the following design precautions are ensured: (a) They are electrically independent. Each sensor should be connected to the aircraft systems via a dedicated connector and a dedicated harness; (b) A test capability is provided for each sensor to preclude an associated latent failure; and (c) It is demonstrated by tests such as equipment qualification tests, slosh and vibration tests as requested in [CS 29.965](#_DxCrossRefBm1685772486), analysis (such as safety analysis, particular risk analysis, zonal safety analysis, comparison with a fully independent design), or a combination thereof that no common modes can lead to the most severe hazard determined in [CS 29.1305](#_DxCrossRefBm1685772469)(a)(4)(ii). [Amdt No: 29/11]