AIRWORTHINESS DIRECTIVE For the reasons set out in the background section, the CASA delegate whose signature appears below issues the following Airworthiness Directive (AD) under subregulation 39.1 (1) of CAR 1998. The AD requires that the action set out in the requirement section (being action that the delegate considers necessary to correct the unsafe condition) be taken in relation to the aircraft or aeronautical product mentioned in the applicability section: (a) in the circumstances mentioned in the requirement section; and (b) in accordance with the instructions set out in the requirement section; and (c) at the time mentioned in the compliance section. Bombardier (Boeing Canada/De Havilland) DHC-8 Series Aeroplanes AD/DHC-8/86 Wing De-icing Boot Patch Limits 4/2002 Applicability: Model DHC-8 aeroplanes, series 100, 200 and 300. Requirement: 1. Carry out a visual inspection of the wing leading edge de-icer boots to assess compliance with repair patch limits for the critical zone published in Bombardier Aircraft Maintenance Manuals: Series 100: PSM 1-8-2, Revision 49, dated 3 October 2001; Chapter 30- 10-48 Series 200: PSM 1-82-2, Revision 11, dated 19 October 2001; Chapter 30-12-00 Series 300: PSM 1-83-2, TR 30-21, dated 30 October 2001; Chapter 30-10-48 2. For those aeroplanes with wing de-icer boots which exceed the patch size and/or number limits in the critical zone, identified during the inspection at Requirement 1, insert a copy of this Airworthiness Directive in the Aircraft Flight Manual (AFM) advising flight crews of the performance penalties detailed in the following table: AFM Sections AFM Limits With De-Ice Boot Patch Limits Exceeded Flap settings as applicable to aircraft model. Note: T/O Speed: Sub-Section 5-2 V1, Vr & V2 Add: 5 kt (flap 0°) 5 kt (flap 5°) 5 kt (flap 10°) 5 kt (flap 15°) Add: Final T/O Climb Speed 5 kt (flap 0°) T/O WAT Limit: Sub-section 5-3 Note: Weight reduction not required when Subtract: limited by maximum structural weight. 180 kg, 400 lb. (flap 0°) 90 kg, 200 lb. (flap 5°) No change (flap 10°) No change (flap 15°) T/O Climb: Sub-Section 5-4 1st Seg. Gradient Subtract: 0.008 (flap 0°) 0.004 (flap 5°) 0.004 (flap 10°) 0.004 (flap 15°) 2nd Seg. Gradient Subtract: 0.005 (flap 0°) 0.002 (flap 5°) 0.002 (flap 10°) 0.002 (flap 15°) Final Seg. Gradient Subtract: 0.009 (flap 0°) T/O Field Length: Sub-Section 5-5 TOR, TOD & ASD Add: 16% (flap 0°) 16% (flap 5°) 16% (flap 10°) 16% (flap 15°) Net T/O Flight Path: Sub-Section 5-6 Ref Gradient Subtract: 0.005 (flap 0°) 0.002 (flap 5°) 0.002 (flap 10°) 0.002 (flap 15°) 4th Seg. Net Gradient Subtract: 0.012 (flap 0°) Flap Retraction Initiation Speed Add: 5 kt (flap 5°) 5 kt (flap 10°) 5 kt (flap 15°) Enroute Climb Data: Sub-Section 5-7 Enroute Climb Speed: Add: Net Climb Gradient 5 kt Subtract: 0.004 Subtract: OEI-Climb Ceiling 1200 ft Landing Speed: Sub-Section 5-8 Approach, Go-around & Vref Add: 5 kt (flap 5°) . 5 kt (flap 10°) 5 kt (flap 15°) 5 kt (flap 35°) Landing WAT Limit: Sub-Section 5-9 Note: Weight reduction not required when limited by maximum structural weight. Subtract: 860 kg, 1900 lb. (flap 10°) 225 kg, 500 lb. (flap 15°) 180 kg, 400 lb. (flap 35°) Landing Climb Data: Sub-Section 5-10 Approach Gross Climb Gradient Subtract: 0.010 (flap 5°) 0.003 (flap 10°) 0.002 (flap 15°) Balked Landing Gross Climb Gradient Subtract: 0.035 (flap 10°) 0.017 (flap 15°) 0.016 (flap 35°) Landing Field Length: Sub-Section 5-11 Add: 23% (flap 10°) 16% (flap 15°) 10% (flap 35°) Brake Energy: Sub-Section 5-12 Accel/Stop B.E. Add: 7% (flap 0°) 7% (flap 5°) 7% (flap 10°) 7% (flap 15°) Landing B.E. Add: 30% (flap 10°) 20% (flap 15°) 8% (flap 35°) 3. Replace any wing de-icer boot(s) that exceed(s) the critical zone repair limit. 4. Remove the copy of this Airworthiness Directive that was inserted in the Aircraft Flight Manual in accordance with requirement 2 of this Airworthiness Directive. From the effective date of this Airworthiness Directive no person shall install de-Icer boot patches in the critical zone of the wing de-icer boots that exceeds the limits contained in the Bombardier Aircraft Maintenance Manuals referenced in Requirement 1 of this Airworthiness Directive. Note: Canadian AD CF-2001-43 and Bombardier All Operator Message (AOM)D- 7534-8-AOM-667 and D-7534-8-AOM-690 refer. Compliance: For requirement 1: Within 60 days from the effective date of this Airworthiness Directive. For requirement 2: Before further flight after the assessment required by Requirement 1 has been conducted. For requirement 3: Within 24 months of the effective date of this Airworthiness Directive. For requirement 4 : When the wing de-icer boots for both wings are within the repair limits for the critical zone. This Airworthiness Directive becomes effective on 18 April 2002. Background: Bombardier Aircraft Maintenance Manuals have been revised to include new limits for the size and number of patches that can be used for repair of the wing leading edge de-icer boots. Exceeding these limits, which are based on the aerodynamic smoothness of the boots, may adversely impact the stall margin of the aeroplane. To correct this condition, this Directive requires a one-off inspection of the wing de-icer boots, and introduces temporary aeroplane performance penalties for the attention of flight crew until de-icer boots that exceed in-service repair limits are replaced. Eugene Paul Holzapfel Delegate of the Civil Aviation Safety Authority 10 March 2002 The above AD is notified in the Commonwealth of Australia Gazette on 27 March 2002.