CTHIn ForceLegislation
AD/ERJ-170/18 Amdt 1 - Electrical Wiring and ARINC 429 Data Bus
Embraer ERJ-170 Series AeroplanesEmbraer ERJ-170 Series Aeroplanes
Start here
Get a plain-English read of Embraer ERJ-170 Series Aeroplanes
Turn the raw legal text into a practical explanation grounded in AD/ERJ-170/18 Amdt 1 - Electrical Wiring and ARINC 429 Data Bus.
Embraer ERJ-170 Series Aeroplanes
| AD/ERJ-170/18 Amdt 1 | Electrical Wiring and ARINC 429 Data Bus | 1/2009 |
|---|
| Applicability: | ERJ 170-100 STD, ERJ 170-100 LR, ERJ 170-100 SU, ERJ 170-100 SE,ERJ 170-200 STD, ERJ 170-200 LR and ERJ 170-200 SU, with serial numbers (S/N) identified in Embraer Service Bulletins (SB) 170-24-0019 original issue, dated6 December 2006, 170-24-0020 original issue, dated 30 November 2006, and170-31-0020 original issue, dated 20 July 2007. |
|---|---|
| Requirement: | 1. Modify the electrical wiring on the overhead panel in the cockpit in accordance with SB 170-24-0019 original issue. |
| 2. Change the Air Data Smart Probe 3 channel B power supply bus from ESS2 to ESS3, in accordance with SB 170-24-0020 original issue. | |
| 3. Duplicate the ARINC 429 airspeed signal for an extension longer than the rotor burst impact area; change the primary power source for MAU 2 from DC BUS 2 to DC ESS BUS 2; and, change the wiring of Slat/Flap Actuators Control Electronics (SF-ACE) 1 and 2 to Primary Actuator Control Electronics (P-ACE) 1, 2 and 3, in accordance with SB 170-31-0020 original issue. | |
| Later revision of the above SBs, approved by the Brazilian Agência Nacional de Aviação Civil (ANAC), are acceptable for compliance with the relevant requirements of this Directive. | |
| Note: ANAC AD 2008-09-01 refers. | |
| Compliance: | For Requirements 1, 2 and 3 - Within the next 6000 hours time in service after the effective date of the original issue of this Directive. |
| This Amendment becomes effective on 15 January 2009. | |
| Background: | The ANAC has advised that a re-assessment of rotor burst analysis has shown the possibility of loss of electrical power supply to the following aircraft systems could result in loss of the aircraft pitch and yaw control:Air data, ailerons, multifunctional spoilers and rudder. |
| Since the loss of aircraft pitch and yaw control affects flight safety, the original issue of this Directive mandated corrective actions. | |
|---|---|