Document ID: chunk:federal_register_of_legislation:F2006B09245:body:0:p2
Version: federal_register_of_legislation:F2006B09245
Segment Type: other
Provision Reference: 
Character Range: 3880–9503

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