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AD/BR700/4 Amdt 1 - Engine Electronic Controller
Rolls Royce Germany Turbine Engines - BRRolls Royce Germany Turbine Engines - BR700 Series
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Rolls Royce Germany Turbine Engines - BR700 Series
| AD/BR700/4 Amdt 1 | Engine Electronic Controller | 8/2005 DM |
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| Applicability: | BR700-715A1-30, BR700-715B1-30 and BR700-715C1-30 engines. |
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| Requirement: | 1. Carry out condition monitoring of the engine electronic controller/full authority digital engine control (EEC/FADEC) system by reading the EEC/FADEC system maintenance messages on the cockpit multifunction control display unit (MCDU) in accordance with Roll-Royce Germany Service Bulletin (SB)SB-BR700-73-900334 Revision 1, dated 26 September 2003, and take the appropriate action specified in the SB within the time limit specified in the SB. |
| 2. Remove EECs with serial numbers below 0351 from the engine and return them to BAe Systems Controls for modification in accordance with Rolls-Royce Germany SB-BR700-73-900316 Revision 2, dated 10 September 2003. | |
| Note: German LBA AD 2003-235 refers. | |
| Compliance: | For Requirement 1: |
| a. Engines which have Rolls Royce Germany SB-BR700-73-101318 incorporated, but do not have SB-BR700-73-101422 incorporated | |
| i. If not accomplished in accordance with the original issue of this initially inspect by 10 July 2005 and thereafter at intervals not exceeding 50 hours time in service (TIS). | |
| ii. If accomplished in accordance with the original issue of this Directive continue the inspection at intervals not exceeding 50 hours TIS. | |
| b. Engines which have Rolls Royce Germany SB-BR700-73-101422 incorporated - Within 20 flights after the “Eng Sys Fault” message is annunciated. | |
| For Requirement 2 - Remains unchanged as “Before 31 December 2004”. | |
| This Amendment becomes effective on 30 June 2005. |
| Background: | There have been several in-flight shut down events reported in 2002 on BR715 engines, which were caused by faults in the EEC/FADEC systems. The original issue of this Directive initially required condition monitoring of the EEC/FADEC system to detect early indication of faults, followed by modification of the EEC units to increase engine reliability and aircraft dispatchability. |
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