AD/F100/32 - Thrust Reverser Electrical Control Modification

COMMONWEALTH OF AUSTRALIA (Civil Aviation Regulations 1998), PART 39 - 105 CIVIL AVIATION SAFETY AUTHORITY

SCHEDULE OF AIRWORTHINESS DIRECTIVES

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Fokker F100 (F28 Mk 100) Series Aeroplanes

AD/F100/32 Thrust Reverser Electrical Control Modification 5/99

Applicability: All F.28 Mk.0070 and Mk.0100 aeroplanes.

Requirement: 1. Modify the Flight Warning Computer (FWC) and the Thrust Reverser Stow Limit relay wiring in accordance with Fokker Service Bulletin (SB) F100-78-012 dated 22 November 1996.

2. Perform operational checks of each Thrust Reverser Secondary Lock Actuator and Primary Lock Switch, and perform an operational check of the Thrust Reverser Indicating and Alerting System, including feedback cable mechanism, in accordance with Fokker SB F100-78-013 dated 22 November 1996.

3. For aircraft that are post SB F100-78-004, at the effective date of this directive, perform a functional check for internal leakage of the Thrust Reverser Selector Valve in accordance with Maintenance Review Board (MRB) task 783200-00-02.

4. Flight Manual Changes

Revise the Abnormal Procedures Section of the Aircraft Flight Manual (AFM) to include the Flight Manual information specified in RLD AD BLA nr: 1996- 140/2.

This task may be accomplished by inserting a copy of RLD AD BLA nr: 1996- 140/2, Appendix 1 into the Abnormal Procedures Section of the AFM."

5. Modify the wiring of the Thrust Reverser Electrical Control System and Indication and Warning System in accordance with Fokker SB F100-78-014 dated 15 August 1998.

6. Modify all Aft Engine Cowling part number 1159P41440, in accordance with Fokker Component SB P41440-78-05 dated 15 August 1998.

7. Install a Voltage Spike Protection Diode over the coil of the Thrust Reverser Secondary Lock Solenoid on all Aft Engine Cowling part number 1159P41440, in accordance with Fokker Component SB P41440-78-05 dated 15 August 1998.

Note: Netherlands AD 1996-140/2 refers.

Compliance: 1. Prior to 22 June 1999.

2. Within 500 flight cycles after the accomplishment of Requirement 1 and thereafter at intervals not to exceed 500 flight cycles.

3. Either:

within 12 000 hours time in service (TIS) after modification in accordance with Fokker SB F100-78-004, or

b. within 6000 hours TIS after Fokker SB F100-78-012 has been accomplished.

COMMONWEALTH OF AUSTRALIA (Civil Aviation Regulations 1998), PART 39 - 105 CIVIL AVIATION SAFETY AUTHORITY

SCHEDULE OF AIRWORTHINESS DIRECTIVES

Whichever is the later, and thereafter at intervals not to exceed 12 000 hours TIS.

4. Prior to 22 July 1999.

5. Before fitting to an aircraft or prior to 22 September 2000.

6. Before fitting to an aircraft or prior to 22 September 2000.

7. Before fitting to an aircraft or prior to 22 September 2000. This Airworthiness Directive becomes effective on 20 May 1999.

Background: To prevent the possibility of the accidental deployment of the Thrust Reverser during take-off Fokker have issued operational measures and modifications to the FWC wiring.