Light
Dark
System
Log In
Loading...
Compare / EASA/
Incorporated Amendments
/
Compare & Highlight Differences
Appendix to AMC 20-2B
Available versions for ERULES-1963177438-6771
ED Decision 2020/010/R
found in: AMC-20 Amdt 22 - Airworthiness of Products, Parts and Appliances (May 2021)
From
AMC-20 Amdt 23 - A... (Jan 2022)
AMC-20 Amdt 22 - A... (May 2021)
AMC-20 Amdt 21 - A... (Apr 2021)
From section
To
AMC-20 Amdt 23 - A... (Jan 2022)
AMC-20 Amdt 22 - A... (May 2021)
AMC-20 Amdt 21 - A... (Apr 2021)
To section
No visible text changes
0 removals
0 additions
View
Rich
Plain
Sync scrolling
Share
From
Show details
Hide details
To
Show details
Hide details
Version
Show side by side
Appendix to AMC 20-2B ED Decision 2020/010/R The following is an example of the distribution of the tasks between the APU certification and the aircraft certification. <table border="1" cellpadding="0" cellspacing="0" width="607"><tr><td valign="top" width="157"><p><b>FUNCTIONS OR INSTALLATION CONDITIONS</b></p></td><td width="160"><p><b>SUBSTANTIATION UNDER CS-APU</b></p></td><td colspan="2" width="290"><p><b>SUBSTANTIATION UNDER CS-25</b></p></td></tr><tr><td width="157"><p><b>APU CONTROL AND PROTECTION</b></p></td><td valign="top" width="160"><p align="left">— Safety objective</p><p align="left">— Software/AEH criticality level</p></td><td valign="top" width="145"><p align="left">— Reliability</p><p align="left">— Software/AEH criticality level</p></td><td valign="top" width="145"></td></tr><tr><td width="157"><p><b>MONITORING</b></p></td><td valign="top" width="160"><p align="left">— Independence of control and monitoring parameters</p></td><td valign="top" width="145"><p align="left">— Monitoring parameter reliability</p></td><td valign="top" width="145"><p align="left">— Indication system reliability</p></td></tr><tr><td width="157"><p><b>AIRCRAFT DATA</b></p></td><td valign="top" width="160"><p align="left">— Protection of APU from aircraft data failures</p><p align="left">— Software/AEH criticality level</p></td><td valign="top" width="145"></td><td valign="top" width="145"><p align="left">— Aircraft data reliability</p></td></tr><tr><td width="157"><p><b>CONTROL SYSTEM ELECTRICAL SUPPLY</b></p></td><td valign="top" width="160"></td><td valign="top" width="145"></td><td valign="top" width="145"><p align="left">— Reliability and quality of aircraft supply if used</p></td></tr><tr><td width="157"><p><b>ENVIRONMENTAL CONDITIONS, LIGHTNING AND OTHER ELECTROMAGNETIC EFFECTS</b></p></td><td valign="top" width="160"><p align="left">— Equipment protection</p></td><td valign="top" width="145"><p align="left">— Declared capability</p></td><td valign="top" width="145"><p align="left">— Aircraft design</p><p align="left">— Aircraft wiring protection</p></td></tr></table> [Amdt 20/19]
Appendix to AMC 20-2B ED Decision 2020/010/R The following is an example of the distribution of the tasks between the APU certification and the aircraft certification. <table border="1" cellpadding="0" cellspacing="0" width="607"> <tr> <td valign="top" width="157"> <p><b>FUNCTIONS OR INSTALLATION CONDITIONS</b></p> </td> <td width="160"> <p><b>SUBSTANTIATION UNDER CS-APU</b></p> </td> <td colspan="2" width="290"> <p><b>SUBSTANTIATION UNDER CS-25</b></p> </td> </tr> <tr> <td width="157"> <p><b>APU CONTROL AND PROTECTION</b></p> </td> <td valign="top" width="160"> <p align="left">— Safety objective</p> <p align="left">— Software/AEH criticality level</p> </td> <td valign="top" width="145"> <p align="left">— Reliability</p> <p align="left">— Software/AEH criticality level</p> </td> <td valign="top" width="145"> </td> </tr> <tr> <td width="157"> <p><b>MONITORING</b></p> </td> <td valign="top" width="160"> <p align="left">— Independence of control and monitoring parameters</p> </td> <td valign="top" width="145"> <p align="left">— Monitoring parameter reliability</p> </td> <td valign="top" width="145"> <p align="left">— Indication system reliability</p> </td> </tr> <tr> <td width="157"> <p><b>AIRCRAFT DATA</b></p> </td> <td valign="top" width="160"> <p align="left">— Protection of APU from aircraft data failures</p> <p align="left">— Software/AEH criticality level</p> </td> <td valign="top" width="145"> </td> <td valign="top" width="145"> <p align="left">— Aircraft data reliability</p> </td> </tr> <tr> <td width="157"> <p><b>CONTROL SYSTEM ELECTRICAL SUPPLY</b></p> </td> <td valign="top" width="160"> </td> <td valign="top" width="145"> </td> <td valign="top" width="145"> <p align="left">— Reliability and quality of aircraft supply if used</p> </td> </tr> <tr> <td width="157"> <p><b>ENVIRONMENTAL CONDITIONS, LIGHTNING AND OTHER ELECTROMAGNETIC EFFECTS</b></p> </td> <td valign="top" width="160"> <p align="left">— Equipment protection</p> </td> <td valign="top" width="145"> <p align="left">— Declared capability</p> </td> <td valign="top" width="145"> <p align="left">— Aircraft design</p> <p align="left">— Aircraft wiring protection</p> </td> </tr> </table> [Amdt 20/19]
Appendix to AMC 20-2B ED Decision 2020/010/R The following is an example of the distribution of the tasks between the APU certification and the aircraft certification. <table border="1" cellpadding="0" cellspacing="0" width="607"> <tr> <td valign="top" width="157"> <p><b>FUNCTIONS OR INSTALLATION CONDITIONS</b></p> </td> <td width="160"> <p><b>SUBSTANTIATION UNDER CS-APU</b></p> </td> <td colspan="2" width="290"> <p><b>SUBSTANTIATION UNDER CS-25</b></p> </td> </tr> <tr> <td width="157"> <p><b>APU CONTROL AND PROTECTION</b></p> </td> <td valign="top" width="160"> <p align="left">— Safety objective</p> <p align="left">— Software/AEH criticality level</p> </td> <td valign="top" width="145"> <p align="left">— Reliability</p> <p align="left">— Software/AEH criticality level</p> </td> <td valign="top" width="145"> </td> </tr> <tr> <td width="157"> <p><b>MONITORING</b></p> </td> <td valign="top" width="160"> <p align="left">— Independence of control and monitoring parameters</p> </td> <td valign="top" width="145"> <p align="left">— Monitoring parameter reliability</p> </td> <td valign="top" width="145"> <p align="left">— Indication system reliability</p> </td> </tr> <tr> <td width="157"> <p><b>AIRCRAFT DATA</b></p> </td> <td valign="top" width="160"> <p align="left">— Protection of APU from aircraft data failures</p> <p align="left">— Software/AEH criticality level</p> </td> <td valign="top" width="145"> </td> <td valign="top" width="145"> <p align="left">— Aircraft data reliability</p> </td> </tr> <tr> <td width="157"> <p><b>CONTROL SYSTEM ELECTRICAL SUPPLY</b></p> </td> <td valign="top" width="160"> </td> <td valign="top" width="145"> </td> <td valign="top" width="145"> <p align="left">— Reliability and quality of aircraft supply if used</p> </td> </tr> <tr> <td width="157"> <p><b>ENVIRONMENTAL CONDITIONS, LIGHTNING AND OTHER ELECTROMAGNETIC EFFECTS</b></p> </td> <td valign="top" width="160"> <p align="left">— Equipment protection</p> </td> <td valign="top" width="145"> <p align="left">— Declared capability</p> </td> <td valign="top" width="145"> <p align="left">— Aircraft design</p> <p align="left">— Aircraft wiring protection</p> </td> </tr> </table> [Amdt 20/19]