2006-19-04: Honeywell COM unit and Mode S transponder

2006-19-04 Honeywell International, Inc.: Amendment 39-14761. Docket No. FAA-2006-24639; Directorate Identifier 2005-NM-171-AD. Effective Date (a) This AD becomes effective October 17, 2006. Affected ADs (b) None. Applicability (c) This AD applies to the Honeywell parts identified in paragraphs (c)(1) and (c)(2) of this AD, approved under Technical Standard Order TSO-C112, installed on but not limited to Bombardier Model BD-700-1A10 and BD-700-1A11 airplanes; Cessna Model 550 and 560 airplanes; Cessna Model 650 airplanes; Dassault Model Falcon 900EX airplanes, serial number (S/N) 97 and S/Ns 120 and subsequent; Dassault Model Falcon 2000EX airplanes, S/N 6 and S/Ns 28 and subsequent; EMBRAER Model EMB-135BJ, -135ER, -135KE, -135KL, and - 135LR airplanes; EMBRAER Model EMB-145, -145ER, -145MR, -145LR, - 145XR, -145MP, and -145EP airplanes; Learjet Model 45 airplanes; Lockheed Model 282-44A-05 (C-130B) airplanes; Lockheed Model 382G series airplanes; Raytheon Model Hawker 800 (including variant U- 125A), 800XP, and 1000 airplanes; certificated in any category. (1) Communication (COM) unit RCZ-833J part numbers (P/Ns) 7510700-763 and -863; RCZ-833K P/Ns 7510700-765 and -875; RCZ-851J P/N 7510700-813; RCZ-851K P/N 7510700-815; and RCZ-854J P/Ns 7510700-725 and -825. (2) Mode S transponder XS-856A P/Ns 7517400-865 and -885; XS- 856B P/Ns 7517400-866 and -886; and XS-857A P/Ns 7517400-876 and - 896. Unsafe Condition (d) This AD results from the transponder erroneously going into standby mode if the flightcrew takes longer than five seconds when using the rotary knob of the radio management unit to change the air traffic control code. We are issuing this AD to prevent the transponder of the COM unit from going into standby mode, which could increase the workload on the flightcrew and result in improper functioning of the traffic alert and collision avoidance system. Compliance (e) You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done. Airplane Flight Manual (AFM) Revision (f) For all airplanes: Within 14 days after the effective date of this AD, revise the Normal Procedures section of the applicable AFM to include the following statement: "After completion of any 4096 ATC Code change (also referred to as Mode A Code), check the status of the transponder. If the transponder indicates that it is in standby mode, re-select the desired mode (i.e., the transponder should be in the active mode)." This may be done by inserting a copy of this AD in the AFM. Accomplishing the actions specified in paragraph (h) or (j), as applicable, of this AD terminates the requirement of this paragraph. Replacement of Identification Plates for Certain COM Units (g) For airplanes equipped with any COM unit identified in paragraph (c)(1) of this AD: Within 18 months after the effective date of this AD, replace the product signature plate, identification plate, and MOD plate of the COM unit with new plates and test the COM unit, in accordance with the Accomplishment Instructions of Honeywell Alert Service Bulletin 7510700-23-A0048, dated January 27, 2006. If the COM unit fails the test, before further flight, reinstall MOD V into the transponder of the COM unit in accordance with Honeywell Alert Service Bulletin 7517400-23-A6015, Revision 001, dated July 29, 2005. Replacement of Certain Transponders (h) For airplanes equipped with any COM unit identified in paragraph (c)(1) of this AD: Before or concurrently with the actions required by paragraph (g) of this AD, replace the XS-852E/F mode S transponder of the COM unit with a new or modified XS-852E/F mode S transponder that has MOD V installed, in accordance with Honeywell Alert Service Bulletin 7510700-23-A0047, Revision 001, dated July 29, 2005. After accomplishing the replacement required by this paragraph, the AFM revision required by paragraph (f) of this AD may be removed from the AFM. Note 1: Honeywell Alert Service Bulletin 7510700-23-A0047, Revision 001, dated July 29, 2005, refers to Honeywell Alert Service Bulletin 7517400-23-A6015, Revision 001, dated July 29, 2005, as an additional source of service information for installing MOD V into an XS-852E/F mode S transponder. Replacement of Identification Plate for Certain Transponders (i) For airplanes equipped with any transponder identified in paragraph (c)(2) of this AD: Within 18 months after the effective date of this AD, replace the modification plate of the transponder with a new plate and test the transponder, in accordance with the Accomplishment Instructions of Honeywell Alert Service Bulletin 7517400-23-A0017, dated January 23, 2006. If the transponder fails the test, before further flight, reinstall MOD Y into the transponder as specified in paragraph (j) of this AD. Installation of MOD Y Into Certain Transponders (j) For airplanes equipped with any transponder identified in paragraph (c)(2) of this AD: Before or concurrently with the actions required by paragraph (i) of this AD, install MOD Y into the applicable mode S transponder, in accordance with the Accomplishment Instructions of Honeywell Alert Service Bulletin 7517400-23-A6016, dated August 30, 2005. After accomplishing the replacement required by this paragraph, the AFM revision required by paragraph (f) of this AD may be removed from the AFM. Parts Installation (k) For all airplanes: As of the effective date of this AD, no person may install any part identified in paragraph (c)(1) or (c)(2) on any airplane, unless the applicable software modification has been installed in the transponder in accordance with paragraph (h) or (j) of this AD, as applicable. No Reporting Requirement (l) Although the service bulletins referenced in this AD specify to submit certain information to the manufacturer, this AD does not include that requirement. Alternative Methods of Compliance (AMOCs) (m)(1) The Manager, Los Angeles Aircraft Certification Office (ACO), FAA, has the authority to approve AMOCs for this AD, if requested in accordance with the procedures found in 14 CFR 39.19. (2) Before using any AMOC approved in accordance with Sec. 39.19 on any airplane to which the AMOC applies, notify the appropriate principal inspector in the FAA Flight Standards Certificate Holding District Office. Material Incorporated by Reference (n) You must use the service information identified in Table 1 of this AD to perform the actions that are required by this AD, unless the AD specifies otherwise. Table 1 Material Incorporated by Reference Service Bulletin Revision Level Date Honeywell Alert Service Bulletin 7510700-23-A0047 001 July 29, 2005 Honeywell Alert Service Bulletin 7510700-23-A0048 Original January 27, 2006 Honeywell Alert Service Bulletin 7517400-23-A6015 001 July 29, 2005 Honeywell Alert Service Bulletin 7517400-23-A6016 Original August 30, 2005 Honeywell Alert Service Bulletin 7517400-23-A0017 Original January 23, 2006 (Only the first and second pages of Honeywell Alert Service Bulletin 7510700-23-A0047 and Honeywell Alert Service Bulletin 7517400-23-A6015 contains the revision level of the document.) The Director of the Federal Register approved the incorporation by reference of these documents in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Go to https://pubs.cas.honeywell.com/ or contact Honeywell International, Inc., Commercial Electronic Systems, 21111 North 19th Avenue, Phoenix, Arizona 85027-2708, for a copy of this service information. You may review copies at the Docket Management Facility, U.S. Department of Transportation, 400 Seventh Street, SW., Room PL-401, Nassif Building, Washington, DC; on the Internet at http://dms.dot.gov; or at the National Archives and Records Administration (NARA). For information on the availability of this material at the NARA, call (202) 741-6030, or go to http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html .