85-22-10: Flight Director Indicators and Horizontal Situation Indicators

85-22-10 COLLINS AVIONICS DIVISION/ROCKWELL INTERNATIONAL: Amendment 39-5207. Applies to the following flight director indicators and horizontal situation indicators certificated to the applicable requirements of Technical Standard Orders C3a, C3b, C4c, C52a, and C66a (*): MODEL PART NO. SERIAL NO. 329B-7A 522-3206-005 5018 thru and including 5021 329B-7J 522-3867-003 1000 thru and including 1001 ADI-44V 622-5139-001 1024 thru and including 1036 622-5139-002 1024 thru and including 1036 622-5139-003 1024 thru and including 1036 622-5139-004 1024 thru and including 1036 ADI-84 787-6173-013 4079 thru and including 4109 787-6173-016 4079 thru and including 4109 ADI-84A 622-3594-013 5549 thru and including 5646 622-3594-015 5549 thru and including 5646 622-3594-016 5549 thru and including 5646 622-3594-017 5549 thru and including 5646 331A-8H 777-1026-004 3204 thru and including 3227 HSI-45 622-4298-001 1246 thru and including 1326 HSI-70 622-4913-001 1670 thru and including 1681 (*) This AD only applies to indicators manufactured between June 1, 1985, and October 25, 1985. It does not apply to indicators installed in an aircraft prior to June 1, 1985. Compliance: Required as indicated unless already accomplished. To prevent internal gear slippage that may result in erroneous display, with no warning annunciation, of pitch and/or roll command and roll pointer displays in flight director indicators or course and/or heading displays in horizontal situation indicators, accomplish the following: (a) For affected flight director indicators, prior to further use, or if installed in an aircraft, prior to further flight, remove the indicator, inspect the gear shaft assemblies to determine if the taper pin is properly installed, and if necessary, modify the assemblies in accordance with the instructions contained in the appropriate Collins' Alert Service Bulletin identified below: MODEL ALERT SERVICE BULLETIN NO. DATE 329B-7A A13 October 25, 1985 329B-7J A9 October 25, 1985 ADI-44V A4 October 25, 1985 ADI-84 A10 October 29, 1985 ADI-84A A10 October 29, 1985 (b) For affected horizontal situation indicators not installed in an aircraft, prior to further use, inspect the gear shaft assemblies to determine if the taper pin is properly installed, and if necessary, modify the assemblies in accordance with the instructions contained in the appropriate Collins' Alert Service Bulletin identified below: MODEL ALERT SERVICE BULLETIN NO. DATE 331A-8H A7 October 28, 1985 HSI-45 A4 October 28, 1985 HSI-70 A1 October 29, 1985 (c) For affected Models 331A-8H and HSI-45 horizontal situation indicators installed on an aircraft: (1) Prior to further flight, deactivate the autopilot and flight director by pulling the respective circuit breakers, and, (2) Fabricate and install on the instrument panel adjacent to the HSI/ADI and visible to the pilot the following placard using letters of a minimum 0.10 inch in height: "AP/FD INOPERATIVE. COURSE AND HEADING INDEX NOT TO BE USED FOR NAVIGATION," and operate the aircraft accordingly. (3) Within 25 hours time-in-service after the effective date of this AD, inspect the gear shaft assemblies to determine if the taper pin is properly installed, and if necessary, modify the assemblies in accordance with the instructions in the appropriate Collins' Alert Service Bulletin identified below: MODEL ALERT SERVICE BULLETIN NO. DATE 331A-8H A7 October 29, 1985 HSI-45 A4 October 28, 1985 (4) The requirements of paragraphs (c)(1) and (c)(2) of this AD are no longer required when paragraph (c)(3) of this AD has been accomplished. (d) For affected Model HSI-70 horizontal situation indicators installed on an aircraft, prior to further flight, remove the indicator. Prior to further use of the indicator, inspect the gear shaft assemblies todetermine if the taper pin is properly installed, and if necessary modify the assemblies in accordance with the instructions contained in Collins' Alert Service Bulletin No. A1, dated October 29, 1985. (e) The inspection and modification requirements of paragraphs (a) through (d) of this AD must be accomplished by a FAA certified instrument repair station. (f) Within five (5) days report, in writing, all defects found during accomplishment of this AD to the Manager, Wichita Aircraft Certification Office, 1801 Airport Road, Room 100, Mid-Continent Airport, Wichita, Kansas 67209. (Reporting approved by the Office of Management and Budget under OMB No. 2120-0056.) (g) Aircraft may be flown in accordance with Federal Aviation Regulation 21.197 to a location where this AD can be accomplished. (h) An equivalent method of compliance with this AD, if used, must be approved by the Manager, Wichita Aircraft Certification Office, 1801 Airport Road, Room 100, Mid-Continent Airport, Wichita, Kansas 67209. All persons affected by this directive may obtain copies of the documents referred to herein upon request to Collins Radio Division/Rockwell International, 400 Collins Road NE, Cedar Rapids, Iowa 52406 or the FAA, Rules Docket, Office of the Regional Counsel, Room 1558, 601 East 12th Street, Kansas City, Missouri 64106. This amendment becomes effective December 31, 1985, as to all persons except those persons to whom it was made immediately effective by priority letter AD 85-22-10, issued October 30, 1985, which contained this amendment.