Airworthiness Directive · Amendment 39-14761 · Honeywell RCZ-833J/K, -851J/K, and -854J Communication (COM) Units, Equipped with XS-852E/F Mode S Transponders; and Honeywell XS-856A/B and -857A Mode S Transponders; Installed on But Not Limited to Certain Transport Category Airplanes
Honeywell RCZ-833J/K, -851J/K, and -854J Communication (COM) Units, Equipped with XS-852E/F Mode S Transponders; and Honeywell XS-856A/B and -857A Mode S Transponders; Installed on But Not Limited to Certain Transport Category Airplanes
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.
The FAA is adopting a new airworthiness directive (AD) for certain Honeywell COM units and transponders, installed on but not limited to certain transport category airplanes. This AD requires a revision to the Normal Procedures section of the airplane flight manual to advise the flightcrew to check the status of the transponder after changing the air traffic control (ATC) code. This AD also requires replacing certain identification plate(s) with new plate(s), testing certain COM units or transponders as applicable, and corrective action if necessary. For certain airplanes, this AD requires replacing the transponders of certain COM units with new or modified transponders. For certain other airplanes, this AD requires installing a modification into certain transponders. 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 ATC 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.
You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done.
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.
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.
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.
(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.
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.
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.
Although the service bulletins referenced in this AD specify to submit certain information to the manufacturer, this AD does not include that requirement.
