Document ID: chunk:federal_register_of_legislation:F2006L03801:body:0:p2
Version: federal_register_of_legislation:F2006L03801
Segment Type: other
Provision Reference: 
Character Range: 2960–5732

1 of this AD.

                 Table 1

             Affected aeroplanes                                                                                                                                                                     Model SR20 or SR22 aeroplane POH P/N  Date FAA-approved
              (1) Model SR20, S/N 1148 through 1267                                                                                                                                                  11934-002                             18 January 2006.
              (2) Model SR20, S/N 1005 through 1147 that have the 3,000-pound gross weight modification following Cirrus Design Corporation Service Bulletin SB 20–01–00, Issued: 25 February 2003.  11934-002                             18 January 2006.
              (3) SR20, S/N 1268 through 1739                                                                                                                                                        11934-003                             18 January 2006.
              (4) SR22, S/N 002 through 1739                                                                                                                                                         13772-001                             18 January 2006.

             Note:  FAA AD 2006-21-03 Amdt 39-14787 refers.
Compliance:     1. Within 50 hours time-in-service (TIS) after the effective date of this AD, unless already done.

                2. Before further flight after the check required by requirement 1 of this AD.

                  3. a. Within 50 hours TIS after the effective date of this AD, unless already done.

                  b. Within 50 hours TIS after the effective sate of this AD, unless already done, and thereafter before further flight anytime the O-ring seals are replaced due to overheating of the brake assembly (temperature indicator sticker turned black).

                  c. From the effective date of this AD.

                  d. From the effective date of this AD.

                4. Within 50 hours TIS after the effective date of this AD, unless already done.

             This Airworthiness Directive becomes effective on 21 December 2006.
Background:  This AD results from several reports of aeroplanes that experienced brake fires and two aeroplanes that lost directional control.  The actions specified in this AD are intended to detect, correct, and prevent overheating damage to the brake caliper piston O-ring seals, which could result in leakage of brake hydraulic fluid.  Consequently, this could lead to the loss of braking with loss of aeroplane directional control or brake fire.

James Coyne
Delegate of the Civil Aviation Safety Authority

25 October 2006