Occurrences have been reported on Fokker 70 and Fokker 100 aeroplanes of uncontained auxiliary power unit (APU) turbine rotor rim failure during de-/anti-icing. The investigation results of these events have shown that these failures were caused by uncontrolled APU overspeed, due to ingestion of de-/anti-icing fluid through the APU air inlet, located in proximity to the dorsal fin.
becomes effective June 13, 2017
and supersedes EASA AD 2016-0125.
This AD requires revision of the Aircraft Maintenance Program, within 12
months from June 13, 2017, to incorporate the tasks and associated thresholds
and intervals described in Fokker Services Engineering Report SE-623 -
Issue 17 (ALS Part 2)
We have updated AD Status Reports
to include this AD.
4. 01/25/2017EASA AD 2017-00 becomes effective January 30, 2017 and pertains to
electrical arcing between the auxiliary power unit (APU) starter motor positive terminal and the APU fuel drain line. Investigation showed that these events were due to contact between the metal braiding on the APU fuel drain line and the positive terminal of the APU starter motor.
5. 01/25/2017EASA AD 2017-00 becomes effective January 30, 2017 and pertains to
revised stress analysis and life calculation, Rolls-Royce Deutschland (RRD) determined new provisional life limits for HPC stage 12 rotor disc Part Number (P/N) JR18449, reducing the maximum approved life limit defined in the Tay 620-15 and Tay 620-15/20 engine Time Limits Manual (TLM), Chapter 05-10-01, Task 05-10-01-800-000, currently at revision dated 15 September 2014.
Failure to replace a HPC stage 12 rotor disc P/N JR18449, before exceeding the thresholds defined by this AD, could lead to an uncontained HPC stage 12 rotor disc failure, possibly resulting in damage to, and/or reduced control of, the aeroplane.
Time Limits / Maintenance Checks - ALS Part 1 - Certification Maintenance Requirements - Implementation
This becomes effective 6 March 2015, and requires implementation of the maintenance actions as specified in ALS Part 1 of the instructions for Continued Airworthiness, Fokker Services Engineering Report SE-473 at issue 11
Time Limits / Maintenance Checks - ALS Part 3 - Fuel Airworthiness Limitations - Implementation
This AD becomes effective 10 March 2015 and requires implementation of the maintenance actions as specified in ALS Part 3 of the instructions for Continued Airworthiness, Fokker Services Engineering Report SE-672 at issue 5
This EASA AD becomes effective March 5, 2015 and requires a one-time inspection of the affected pressure bulkhead webplate and skin connection angle, and depending on findings, accomplishment of applicable corrective actions.
This AD is considered to be an interim action and further AD action may follow, possibly to lower the current ALS task threshold, if justified by the inspection results.