Document ID: chunk:federal_register_of_legislation:F2006B11142:reg:29
Version: federal_register_of_legislation:F2006B11142
Segment Type: reg
Provision Reference: reg 29
Character Range: 1551–3179

29      001 and up                      Pilot's circuit breaker panel

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

2.        Install a locally fabricated placard on or near the autopilot control head in clear view of the crew using letters at least 3/32 inch high, which reads:

                AUTOPILOT PITCH AXIS INOPERATIVE

                OBSERVE APPROPRIATE AFM AIRSPEED LIMITATIONS FOR INOPERATIVE AUTOPILOT

              and operate the airplane in accordance with this placard.

3.        Visually inspect the elevator control system to assure that Pitch Axis Servo (DC Torquer), P/N 6600163-( ) is installed.

                 (a)     If installed, modify the airplane by incorporating autopilot pitch trim monitor test switch in accordance with Gates Learjet Airplane Modification Kit AMK 80-16B, Change 2.

                 (b)     If not installed, modify the airplane by replacing the pitch servo actuator and capstan and incorporating autopilot pitch trim monitor test switch in accordance with Gates Learjet Airplane Modification Kits AMK 80-3, Change 4, and AMK 80-16B, Change 2, respectively.

4.        When paragraph 3 of this AD has been accomplished, the requirements of paragraphs 1 and 2 of this AD are no longer applicable.

 Compliance: For paras. 1 and 2 - Before further flight. For Para. 3 - Before 1 May 1981.

           Background:  This action is necessary to reduce the hazard created by a possible pitch axis malfunction which if not detected, could result in a hazardous flight attitude.