2001-23-17: GNS 430 units

2001-23-17 GARMIN International: Amendment 39-12516; Docket No. 99-CE-87-AD. (a) What airplanes are affected by this AD? This AD applies to the GNS 430 units that are specified in paragraph (a)(1) of this AD and are installed on aircraft. These GNS 430 units are installed in, but not limited to, aircraft that are certificated in any category and presented in paragraph (a)(2) of this AD: (1) GNS 430 Units, part number 011-00280-00: serial numbers 9630001, 96300002, 96300017, 96300028, 96300034, 96300040, 96300068, 96300104, 96300108, 96300122, 96300125, 96300130, 96300142, 96300149, 96300161, 96300165, 96300218, 96300222, 96300232, 96300269, 96300272, 96300308, 96300333, 96300340, 96300348, 96300354, 96300369, 96300372, 96300382, 96300394, 96300411, 96300413, 96300429, 96300437, 96300451, 96300484, 96300485, 96300489, 96300504, 96300506, 96300513, 96300522, 96300549, 96300563, 96300585, 96300587, 96300618, 96300621, 96300624, 96300628, 96300641, 96300653, 96300664, 96300713, 96300734, 96300756, 96300766, 96300781, 96300785, 96300786, 96300808, 96300831, 96300837, 96300842, 96300846, 96300866, 96300870, 96300872, 96300899, 96300916, 96300923, 96300925, 96300929, 96300941, 96300961, 96300984, 96300987, 96301021, 96301108, 96301130, 96301280, and 96301296 through 96303200. (2) Aircraft with the GNS 430 Unit Installation (other aircraft could have field approval installations): TC holder Airplane models Cessna Aircraft Company 172, 182, 206, 208, 210, 401, 402, 404, 406, 411, 414, 414A, 421A, 421B, 421C, 425, 441, 500, 550, S550, 552, 560, 560XL, 501, 525, and 551. Mooney Aircraft M20, M20A, M20B, M20C, M20D, M20E, M20F, M20G, M20J, M20K, M20L, M20M, M20R, M20S, and M22. Raytheon Aircraft Company Beech Models E33, F33, G33, E33A, F33A, E33C, F33C, 35, 35R, A35, B35, B35TC, C35, D35, E35, F35, G35, H35, J35, K35, M35, N35, P35, S35, V35, V35TC, V35A, V35A-TC, V35B, V35B-TC, 36, A36, A36TC, 50, B50, C50, D50, D50A, D50B, D50C, D50E, E50, F50, G50, H50, J50, 60, A60, B60, 65-90, 65-A90, B90, C90, C90A, C90B, E90, F90, 100, A100, B100, 95-55, 95-A55, 95-B55, 95-C55, D-55, E55, 58, 58P, and 58TC. Socata TBM 700. The New Piper Aircraft, Inc. J3C-40, J3C-50, J3C-50S (Army L-4, L-4B, L-4H, and L-4J), J3C-65 (Navy NE-1 and NE-2), J3C-65S, J3F-50, J3F-50S, J3F-60, J3F-60S, J3F-65 (Army L-4D), J3F-65S, J3L, J3L-S, J3L-65 (Army L-4C), J3L-65S, J4, J4A, J4A-S, J4E (Army L-4E), J5A (Army L-4F), J5A-80, J5B (Army L-4G), J5C, AE-1, HE-1, 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. (b) Who must comply with this AD? Anyone who wishes to operate any aircraft with one of the affected GNS 430 units installed must comply with this AD. (c) What problem does this AD address? The actions specified by this AD are intended to prevent external noise from causing inaccurate course deviation displays in the GNS 430 unit's course deviation indicator (CDI) or horizontal situation indicator (HSI). Such displays could result in the pilot making flight decisions that put the aircraft in unsafe flight conditions. (d) What actions must I accomplish to address this problem? To address this problem, you must accomplish the following: Actions Compliance Procedures (1) Modify the affected GNS 430 unit to incorporate circuitry changes to the deviation and flag outputs. Within the next 6 months after December 28, 2001 (the effective date of this AD). In accordance with the MODIFICATION INSTRUCTIONS section of GARMIN Service Bulletin No.: 9905, Revision A, dated September 17, 1999. (2) Do not install an affected GNS 430 unit unless it has been modified as required by paragraph (d)(1) of this AD. As of December 28, 2001 (the effective date of this AD). In accordance with the MODIFICATION INSTRUCTIONS section of GARMIN Service Bulletin No.: 9905, Revision A, dated September 17, 1999. (e) Can I comply with this AD in any other way? You may use an alternative method of compliance or adjust the compliance time if: (1) Youralternative method of compliance provides an equivalent level of safety; and (2) The Manager, Wichita Aircraft Certification Office (ACO), approves your alternative. Submit your request through an FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, Wichita ACO. Note: This AD applies to any aircraft with the equipment installed as identified in paragraph (a) of this AD, regardless of whether the aircraft has been modified, altered, or repaired in the area subject to the requirements of this AD. For aircraft that have been modified, altered, or repaired so that the performance of the requirements of this AD is affected, the owner/operator must request approval for an alternative method of compliance in accordance with paragraph (e) of this AD. The request should include an assessment of the effect of the modification, alteration, or repair on the unsafe condition addressed by this AD; and, if you have not eliminated the unsafe condition,specific actions you propose to address it. (f) Where can I get information about any already-approved alternative methods of compliance? Contact Roger A. Souter, FAA, Wichita Aircraft Certification Office (ACO), 1801 Airport Road, Room 100, Wichita, Kansas 67209; telephone: (316) 946-4134; facsimile: (316) 946-4407, e-mail: roger.souter@faa.gov. (g) What if I need to fly the airplane to another location to comply with this AD? The FAA can issue a special flight permit under sections 21.197 and 21.199 of the Federal Aviation Regulations (14 CFR 21.197 and 21.199) to operate your airplane to a location where you can accomplish the requirements of this AD. (h) Are any service bulletins incorporated into this AD by reference? Actions required by this AD must be done in accordance with GARMIN Service Bulletin No.: 9905, Revision A, dated September 17, 1999. The Director of the Federal Register approved this incorporation by reference under 5 U.S.C. 552(a) and 1 CFR part 51.You may obtain copies from GARMIN International, 1200 East 151st Street, Olathe, Kansas 66062. You may view this information at FAA, Central Region, Office of the Regional Counsel, 901 Locust, Room 506, Kansas City, Missouri, or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. (i) When does this amendment become effective? This amendment becomes effective on December 28, 2001.