Document ID: chunk:federal_register_of_legislation:F2006B06529:body:0:p2
Version: federal_register_of_legislation:F2006B06529
Segment Type: other
Provision Reference: 
Character Range: 3417–6337

PA-11,
                                PA-11S, PA-12, PA-12S, PA-14, PA-15, PA-16, PA-16S, PA-17, PA-18, PA-18A, PA-18A
                                (Restricted), PA-18S, PA-18-"105'' (Special),
                                PA-18S-"105'' (Special), PA-18-"125'' (Army L-
                                21A), PA-18AS-"125'', PA-18S-"125'', PA-18-
                                "135'' (Army L-21B), PA-18A-"135'', PA-18A-
                                "135'' (Restricted), PA-18AS-"135'', PA-18S-
                                "135'', PA-18-"150'', PA-18A-"150'', PA-18A-
                                "150'' (Restricted), PA-18AS-"150'', PA-18S-
                                "150'', PA-19 (Army L-18C), PA-19S, PA- 20,
                                P-20S, PA-20-"115'', PA-20S-"115'', PA-20-
                                "135'', PA-20S-"135'', PA-22, PA-22-108, PA- 22-135, PA-22S-135, PA-22-150, PA-22S-150, PA-22-160, PA-22S-160, PA-24, PA-24-250, PA-24-260, PA-24-400, PA-25, PA-25-235, PA- 25-260, PA-28-140, PA-28-150, PA-28-151,
                                PA-28-160, PA-28-161, PA-28-180, PA-28-235, PA-28S-160, PA-28R-180, PA-28S-180, PA-28- 181, PA-28R-200, PA-28R-201, PA-28R-201T, PA-28RT-201, PA-28RT-201T, PA-28-201T, PA28-236, PA-32R-301 (SP), PA-32R-301 (HP), PA-32R-301T, PA-32-301, PA-32-301T, PA-36-285, PA-36-300, PA-36-375, PA-38-112, PA-46-310P and PA-46-350P.

             Requirement: 1. Modify the deviation and flag output circuitry in accordance with the Modification Instructions section of Garmin Service Bulletin No 9905, Revision A, dated 17 September 1999.

             2. GNS 430 units, with the serial numbers listed in the Applicability Statement, may not be installed on any aeroplane unless modified in accordance with Requirement 1.

           Note 2: FAA AD 2001-23-17 Amdt 39-12516 refers.

 Compliance: For Requirement 1 - Within six months after the effective date of this Directive.

           For Requirement 2 - As of the effective date of this Directive.

           This Airworthiness Directive becomes effective on 21 February 2002.

           Background: The United States Federal Aviation Administration has received reports of inaccurate course deviations caused by external electrical noise to the GNS 430 unit's course deviation indicator (CDI). Such displays could result in the pilot making decisions that put the aircraft in unsafe flight conditions. This Directive requires the modification of the unit to incorporate circuitry changes to the GNS 430 unit's deviation and flag outputs to prevent external noise from causing inaccurate course deviation displays in the GNS 430 unit's CDI or horizontal situation indicator (HSI).

 Eugene Paul Holzapfel
 Delegate of the Civil Aviation Safety Authority 14 January 2002

 The above AD is notified in the Commonwealth of Australia Gazette on 30 January 2002.