Airworthiness Directives; 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, 25984-25987 [E6-6651]

Download as PDF 25984 Proposed Rules Federal Register Vol. 71, No. 85 Wednesday, May 3, 2006 This section of the FEDERAL REGISTER contains notices to the public of the proposed issuance of rules and regulations. The purpose of these notices is to give interested persons an opportunity to participate in the rule making prior to the adoption of the final rules. DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2006–24639; Directorate Identifier 2005–NM–171–AD] RIN 2120–AA64 Airworthiness Directives; 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 Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Notice of proposed rulemaking (NPRM). rmajette on PROD1PC67 with PROPOSALS AGENCY: SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD) for certain Honeywell COM units and transponders, installed on but not limited to certain transport category airplanes. This proposed AD would require 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 proposed AD would also require 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 proposed AD would require replacing the transponders of certain COM units with new or modified transponders. For certain other airplanes, this proposed AD would require installing a modification into certain transponders. This proposed 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 VerDate Aug<31>2005 15:34 May 02, 2006 Jkt 208001 unit to change the ATC code. We are proposing 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. DATES: We must receive comments on this proposed AD by June 19, 2006. ADDRESSES: Use one of the following addresses to submit comments on this proposed AD. • DOT Docket Web site: Go to https://dms.dot.gov and follow the instructions for sending your comments electronically. • Government-wide rulemaking Web site: Go to https://www.regulations.gov and follow the instructions for sending your comments electronically. • Mail: Docket Management Facility, U.S. Department of Transportation, 400 Seventh Street SW., Nassif Building, room PL–401, Washington, DC 20590. • Fax: (202) 493–2251. • Hand Delivery: Room PL–401 on the plaza level of the Nassif Building, 400 Seventh Street SW., Washington, DC, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. Go to https:// pubs.cas.honeywell.com/ or contact Honeywell International Inc., Commercial Electronic Systems, 5353 West Bell Road, Glendale, Arizona 85308–3912, for the service information identified in this proposed AD. FOR FURTHER INFORMATION CONTACT: Abby Malmir, Aerospace Engineer, Systems and Equipment Branch, ANM– 130L, FAA, Los Angeles Aircraft Certification Office, 3960 Paramount Boulevard, Lakewood, California 90712–4137; telephone (562) 627–5351; fax (562) 627–5210. SUPPLEMENTARY INFORMATION: Comments Invited We invite you to submit any relevant written data, views, or arguments regarding this proposed AD. Send your comments to an address listed in the ADDRESSES section. Include the docket number ‘‘FAA–2006–24639; Directorate Identifier 2005–NM–171–AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of the proposed AD. We will consider all comments received by the closing date PO 00000 Frm 00001 Fmt 4702 Sfmt 4702 and may amend the proposed AD in light of those comments. We will post all comments we receive, without change, to https:// dms.dot.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact with FAA personnel concerning this proposed AD. Using the search function of that Web site, anyone can find and read the comments in any of our dockets, including the name of the individual who sent the comment (or signed the comment on behalf of an association, business, labor union, etc.). You may review DOT’s complete Privacy Act Statement in the Federal Register published on April 11, 2000 (65 FR 19477–78), or you may visit https:// dms.dot.gov. Examining the Docket You may examine the AD docket on the Internet at https://dms.dot.gov, or in person at the Docket Management Facility office between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The Docket Management Facility office (telephone (800) 647–5227) is located on the plaza level of the Nassif Building at the DOT street address stated in the ADDRESSES section. Comments will be available in the AD docket shortly after the Docket Management System receives them. Discussion We have received a report indicating that the transponder erroneously goes 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 (ATC) code. (This error will not occur if the keyboard is used to change the ATC code.) This error occurs on certain Honeywell RCZ communication (COM) units that contain elementary surveillance transponders. When the transponder goes into standby mode, the secondary surveillance radar (SSR) symbol and the airplane’s position disappear from the ATC ground radar display. Also, the traffic alert and collision avoidance systems (TCAS) onboard the airplane and other nearby airplanes are compromised. Current operational procedures typically do not instruct the flightcrew to re-check the transponder status after changing the ATC code. The transponder erroneously going into E:\FR\FM\03MYP1.SGM 03MYP1 25985 Federal Register / Vol. 71, No. 85 / Wednesday, May 3, 2006 / Proposed Rules standby mode, if not corrected, could increase the workload on the flightcrew and result in improper functioning of the TCAS. Relevant Service Information We have reviewed Honeywell Alert Service Bulletin 7510700–23–A0048, dated January 27, 2006; and Honeywell Alert Service Bulletin 7517400–23– A0017, dated January 23, 2006. For COM units 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, Honeywell Alert Service Bulletin 7510700–23– A0048 describes doing the following procedures: • Replacing the product signature plate, identification plate, and modification plate with new plates. • Marking all the modifications installed in the COM unit on the new modification plate. • Testing the COM unit. • Reporting certain information to the manufacturer. Honeywell Alert Service Bulletin 7510700–23–A0048 also specifies prior or concurrent accomplishment of Honeywell Alert Service Bulletin 7510700–23–A0047, Revision 001, dated July 29, 2005. Honeywell Alert Service Bulletin 7510700–23–A0047 describes procedures for installing MOD AT into the COM unit and testing the COM unit. MOD AT involves replacing the XS– 852E/F mode S transponder, P/N 7517400–911 or –912, of the applicable COM unit with a new or modified XS– 852E/F mode S transponder that has MOD V installed. Honeywell Alert Service Bulletin 7510700–23–A0047 also refers to Honeywell Alert Service Bulletin 7517400–23–A6015, Revision 001, dated July 29, 2005, as an additional source of service information for modifying the XS–852E/F mode S transponder by installing MOD V into the transponder. For mode S transponders 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, Honeywell Alert Service Bulletin 7517400–23–A0017 describes doing the following procedures: • Replacing the modification plate of the transponder with a new plate. • Marking all the modifications installed in the transponder on the new modification plate of the transponder. • Testing the transponder. • Reporting certain information to the manufacturer. Honeywell Alert Service Bulletin 7517400–23–A0017 also specifies prior or concurrent accomplishment of Honeywell Alert Service Bulletin 7517400–23–A6016, dated August 30, 2005. Honeywell Alert Service Bulletin 7517400–23–A6016 describes procedures for installing MOD Y into the transponder and testing the transponder. Accomplishing the actions specified in the service information is intended to adequately address the unsafe condition. FAA’s Determination and Requirements of the Proposed AD We have evaluated all pertinent information and identified an unsafe condition that is likely to exist or develop on other products of this same type design. For this reason, we are proposing this AD, which would require revising the Normal Procedures section of the applicable Airplane Flight Manual to advise the flightcrew to check the status of the transponder after changing the ATC code. This AD would also require accomplishing the actions specified in the service information described previously, except as discussed under ‘‘Differences Between Proposed AD and Service Bulletins.’’ Differences Between Proposed AD and Service Bulletins Service Bulletin 7510700–23–A0048 recommends testing certain COM units; however, the service bulletin does not specify what corrective action to take if the COM unit fails the test. This proposed AD would require, before further flight after the test, reinstalling MOD V into the transponder of the COM unit, in accordance with Service Bulletin 7517400–23–A6015. Service Bulletin 7517400–23–A0017 recommends testing certain transponders; however, the service bulletin does not specify what corrective action to take if the transponder fails the test. This proposed AD would require, before further flight after the test, reinstalling MOD Y into the transponder, in accordance with Service Bulletin 7517400–23–A6016. Operators should note that, although the Accomplishment Instructions of the referenced service bulletins describe procedures for submitting a comment sheet related to service bulletin quality and a sheet recording compliance with the service bulletin, this proposed AD would not require those actions. Costs of Compliance There are about 1,365 airplanes of the affected design in the worldwide fleet. This proposed AD would affect about 1,023 airplanes of U.S. registry. Of those airplanes, about 603 airplanes are equipped with RCZ–833J/K, –851J/K, or 854J COM units and about 420 airplanes are equipped with XS–856A/B or –857A mode S transponders. The following table provides the estimated costs, at an average labor rate of $80 per hour, for U.S. operators to comply with this proposed AD. ESTIMATED COSTS Number of U.S.-registered airplanes AFM revision ....................................................... Part identification, testing, and replacement for RCZ–833J/K, –851J/K, and –854J COM units. Part identification, testing, and installation of software for XS–856A/B and –857A mode S transponders. rmajette on PROD1PC67 with PROPOSALS Work hours 1 ............................ 3 ............................ None $35 $80 ............... $275 ............. 3 to 8 1 .................. $175 $415 to $815 1. 1 Depending 1,023 603 420 Fleet cost $81,840. $165,825. $174,300 to $342,300.1 on test procedure. Authority for This Rulemaking Title 49 of the United States Code specifies the FAA’s authority to issue rules on aviation safety. Subtitle I, VerDate Aug<31>2005 Parts Cost per airplane Action 17:13 May 02, 2006 Jkt 208001 section 106, describes the authority of the FAA Administrator. Subtitle VII, Aviation Programs, describes in more PO 00000 Frm 00002 Fmt 4702 Sfmt 4702 detail the scope of the Agency’s authority. We are issuing this rulemaking under the authority described in subtitle VII, E:\FR\FM\03MYP1.SGM 03MYP1 25986 Federal Register / Vol. 71, No. 85 / Wednesday, May 3, 2006 / Proposed Rules part A, subpart III, section 44701, ‘‘General requirements.’’ Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action. Regulatory Findings We have determined that this proposed AD would not have federalism implications under Executive Order 13132. This proposed AD would not have a substantial direct effect on the States, on the relationship between the national Government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify that the proposed regulation: 1. Is not a ‘‘significant regulatory action’’ under Executive Order 12866; 2. Is not a ‘‘significant rule’’ under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); and 3. Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. We prepared a regulatory evaluation of the estimated costs to comply with this proposed AD and placed it in the AD docket. See the ADDRESSES section for a location to examine the regulatory evaluation. Comments Due Date (a) The FAA must receive comments on this AD action by June 19, 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 Mystere-Falcon 900 and Falcon 900EX airplanes; Dassault Model Falcon 2000 and Falcon 2000EX airplanes; 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 Air transportation, Aircraft, Aviation safety, Safety. (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. The Proposed Amendment Compliance Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 14 CFR part 39 as follows: (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. List of Subjects in 14 CFR Part 39 Airplane Flight Manual (AFM) Revision PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: Authority: 49 U.S.C. 106(g), 40113, 44701. rmajette on PROD1PC67 with PROPOSALS § 39.13 [Amended] 2. The Federal Aviation Administration (FAA) amends § 39.13 by adding the following new airworthiness directive (AD): Honeywell International, Inc.: Docket No. FAA–2006–24639; Directorate Identifier 2005–NM–171–AD. VerDate Aug<31>2005 15:34 May 02, 2006 Jkt 208001 (f) For all airplanes: Within 5 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. PO 00000 Frm 00003 Fmt 4702 Sfmt 4702 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 E:\FR\FM\03MYP1.SGM 03MYP1 Federal Register / Vol. 71, No. 85 / Wednesday, May 3, 2006 / Proposed Rules 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 § 39.19 on any airplane to which the AMOC applies, notify the appropriate principal inspector in the FAA Flight Standards Certificate Holding District Office. Issued in Renton, Washington, on April 25, 2006. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E6–6651 Filed 5–2–06; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2006–24667; Directorate Identifier 2006–NM–009–AD] RIN 2120–AA64 Airworthiness Directives; Goodyear Aviation Tires, Part Number 217K22–1, Installed on Various Transport Category Airplanes, Including But Not Limited to Bombardier Model BD–700– 1A10 and BD–700–1A11 Airplanes; and Gulfstream Model G–1159, G–1159A, G–1159B, G–IV, GIV–X, GV, and GV–SP Series Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Notice of proposed rulemaking (NPRM). rmajette on PROD1PC67 with PROPOSALS AGENCY: SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD) for certain aviation tires installed on various transport category airplanes. This proposed AD would require a onetime inspection of the nosewheel tires to determine if they are within a designated serial number range, and replacement if necessary. This proposed AD results from reports of tread separations and tread-area bulges on the nosewheel tires. We are proposing this AD to prevent tread separation from a nosewheel tire during takeoff or VerDate Aug<31>2005 15:34 May 02, 2006 Jkt 208001 landing, which could result in compromised nosewheel steering or ingestion of separated tread by an engine, and consequent reduced controllability of the airplane on the runway or in the air. DATES: We must receive comments on this proposed AD by June 19, 2006. ADDRESSES: Use one of the following addresses to submit comments on this proposed AD. • DOT Docket Web site: Go to https://dms.dot.gov and follow the instructions for sending your comments electronically. • Government-wide rulemaking Web site: Go to https://www.regulations.gov and follow the instructions for sending your comments electronically. • Mail: Docket Management Facility, U.S. Department of Transportation, 400 Seventh Street, SW., Nassif Building, room PL–401, Washington, DC 20590. • Fax: (202) 493–2251. • Hand Delivery: Room PL–401 on the plaza level of the Nassif Building, 400 Seventh Street SW., Washington, DC, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. Contact Bombardier, Inc., Bombardier Regional Aircraft Division, 123 Garratt Boulevard, Downsview, Ontario M3K 1Y5, Canada; Gulfstream Aerospace Corporation, Technical Publications Dept., P.O. Box 2206, Savannah, Georgia 31402–2206; or Goodyear Tire and Rubber Company, 1144 E. Market Street, Akron, OH 44316–0001; as applicable, for service information identified in this proposed AD. FOR FURTHER INFORMATION CONTACT: Nick Miller, Aerospace Engineer, Systems and Flight Test Branch, ACE–117C, Chicago Aircraft Certification Office, FAA, 2300 East Devon Avenue, Room 107, Des Plaines, IL 60018; telephone (847) 294–7518; fax (847) 294–7834. SUPPLEMENTARY INFORMATION: Comments Invited We invite you to submit any relevant written data, views, or arguments regarding this proposed AD. Send your comments to an address listed in the ADDRESSES section. Include the docket number ‘‘FAA–2006–24667; Directorate Identifier 2006–NM–009–AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of the proposed AD. We will consider all comments received by the closing date and may amend the proposed AD in light of those comments. We will post all comments we receive, without change, to https:// dms.dot.gov, including any personal PO 00000 Frm 00004 Fmt 4702 Sfmt 4702 25987 information you provide. We will also post a report summarizing each substantive verbal contact with FAA personnel concerning this proposed AD. Using the search function of that Web site, anyone can find and read the comments in any of our dockets, including the name of the individual who sent the comment (or signed the comment on behalf of an association, business, labor union, etc.). You may review DOT’s complete Privacy Act Statement in the Federal Register published on April 11, 2000 (65 FR 19477–78), or you may visit https:// dms.dot.gov. Examining the Docket You may examine the AD docket on the Internet at https://dms.dot.gov, or in person at the Docket Management Facility office between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The Docket Management Facility office (telephone (800) 647–5227) is located on the plaza level of the Nassif Building at the DOT street address stated in the ADDRESSES section. Comments will be available in the AD docket shortly after the Docket Management System receives them. Discussion We have received reports of tread separations and tread-area bulges on certain Goodyear Aviation nosewheel tires that are within a designated serial number range. Investigation revealed that the nosewheel tires have poor adhesion properties, which could cause tread loss during takeoff or landing. This condition, if not corrected, could result in compromised nosewheel steering or ingestion of separated tread by an engine, and consequent reduced controllability of the airplane on the runway or in the air. Relevant Service Information We have reviewed Goodyear Aviation Service Bulletin SB–2005–32–004, Revision 5, dated December 22, 2005. The service bulletin describes procedures for inspecting the nosewheel tires for the affected serial numbers, and for replacing affected tires. Accomplishing the actions specified in the service information is intended to adequately address the unsafe condition. We have also reviewed the following Gulfstream Alert Customer Bulletins. These Alert Customer Bulletins, all dated October 12, 2005, are additional sources of service information for identifying the affected serial numbers and replacing the tires if necessary. E:\FR\FM\03MYP1.SGM 03MYP1

Agencies

[Federal Register Volume 71, Number 85 (Wednesday, May 3, 2006)]
[Proposed Rules]
[Pages 25984-25987]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E6-6651]


========================================================================
Proposed Rules
                                                Federal Register
________________________________________________________________________

This section of the FEDERAL REGISTER contains notices to the public of 
the proposed issuance of rules and regulations. The purpose of these 
notices is to give interested persons an opportunity to participate in 
the rule making prior to the adoption of the final rules.

========================================================================


Federal Register / Vol. 71, No. 85 / Wednesday, May 3, 2006 / 
Proposed Rules

[[Page 25984]]



DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2006-24639; Directorate Identifier 2005-NM-171-AD]
RIN 2120-AA64


Airworthiness Directives; 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

AGENCY: Federal Aviation Administration (FAA), Department of 
Transportation (DOT).

ACTION: Notice of proposed rulemaking (NPRM).

-----------------------------------------------------------------------

SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD) 
for certain Honeywell COM units and transponders, installed on but not 
limited to certain transport category airplanes. This proposed AD would 
require 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 
proposed AD would also require 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 proposed AD would require replacing the transponders of 
certain COM units with new or modified transponders. For certain other 
airplanes, this proposed AD would require installing a modification 
into certain transponders. This proposed 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 proposing 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.

DATES: We must receive comments on this proposed AD by June 19, 2006.

ADDRESSES: Use one of the following addresses to submit comments on 
this proposed AD.
     DOT Docket Web site: Go to https://dms.dot.gov and follow 
the instructions for sending your comments electronically.
     Government-wide rulemaking Web site: Go to https://
www.regulations.gov and follow the instructions for sending your 
comments electronically.
     Mail: Docket Management Facility, U.S. Department of 
Transportation, 400 Seventh Street SW., Nassif Building, room PL-401, 
Washington, DC 20590.
     Fax: (202) 493-2251.
     Hand Delivery: Room PL-401 on the plaza level of the 
Nassif Building, 400 Seventh Street SW., Washington, DC, between 9 a.m. 
and 5 p.m., Monday through Friday, except Federal holidays.
    Go to https://pubs.cas.honeywell.com/ or contact Honeywell 
International Inc., Commercial Electronic Systems, 5353 West Bell Road, 
Glendale, Arizona 85308-3912, for the service information identified in 
this proposed AD.

FOR FURTHER INFORMATION CONTACT: Abby Malmir, Aerospace Engineer, 
Systems and Equipment Branch, ANM-130L, FAA, Los Angeles Aircraft 
Certification Office, 3960 Paramount Boulevard, Lakewood, California 
90712-4137; telephone (562) 627-5351; fax (562) 627-5210.

SUPPLEMENTARY INFORMATION:

Comments Invited

    We invite you to submit any relevant written data, views, or 
arguments regarding this proposed AD. Send your comments to an address 
listed in the ADDRESSES section. Include the docket number ``FAA-2006-
24639; Directorate Identifier 2005-NM-171-AD'' at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of the proposed AD. We will 
consider all comments received by the closing date and may amend the 
proposed AD in light of those comments.
    We will post all comments we receive, without change, to https://
dms.dot.gov, including any personal information you provide. We will 
also post a report summarizing each substantive verbal contact with FAA 
personnel concerning this proposed AD. Using the search function of 
that Web site, anyone can find and read the comments in any of our 
dockets, including the name of the individual who sent the comment (or 
signed the comment on behalf of an association, business, labor union, 
etc.). You may review DOT's complete Privacy Act Statement in the 
Federal Register published on April 11, 2000 (65 FR 19477-78), or you 
may visit https://dms.dot.gov.

Examining the Docket

    You may examine the AD docket on the Internet at https://
dms.dot.gov, or in person at the Docket Management Facility office 
between 9 a.m. and 5 p.m., Monday through Friday, except Federal 
holidays. The Docket Management Facility office (telephone (800) 647-
5227) is located on the plaza level of the Nassif Building at the DOT 
street address stated in the ADDRESSES section. Comments will be 
available in the AD docket shortly after the Docket Management System 
receives them.

Discussion

    We have received a report indicating that the transponder 
erroneously goes 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 (ATC) code. (This error will not occur 
if the keyboard is used to change the ATC code.) This error occurs on 
certain Honeywell RCZ communication (COM) units that contain elementary 
surveillance transponders. When the transponder goes into standby mode, 
the secondary surveillance radar (SSR) symbol and the airplane's 
position disappear from the ATC ground radar display. Also, the traffic 
alert and collision avoidance systems (TCAS) onboard the airplane and 
other nearby airplanes are compromised. Current operational procedures 
typically do not instruct the flightcrew to re-check the transponder 
status after changing the ATC code. The transponder erroneously going 
into

[[Page 25985]]

standby mode, if not corrected, could increase the workload on the 
flightcrew and result in improper functioning of the TCAS.

Relevant Service Information

    We have reviewed Honeywell Alert Service Bulletin 7510700-23-A0048, 
dated January 27, 2006; and Honeywell Alert Service Bulletin 7517400-
23-A0017, dated January 23, 2006.
    For COM units 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, Honeywell 
Alert Service Bulletin 7510700-23-A0048 describes doing the following 
procedures:
     Replacing the product signature plate, identification 
plate, and modification plate with new plates.
     Marking all the modifications installed in the COM unit on 
the new modification plate.
     Testing the COM unit.
     Reporting certain information to the manufacturer.
    Honeywell Alert Service Bulletin 7510700-23-A0048 also specifies 
prior or concurrent accomplishment of Honeywell Alert Service Bulletin 
7510700-23-A0047, Revision 001, dated July 29, 2005.
    Honeywell Alert Service Bulletin 7510700-23-A0047 describes 
procedures for installing MOD AT into the COM unit and testing the COM 
unit. MOD AT involves replacing the XS-852E/F mode S transponder, P/N 
7517400-911 or -912, of the applicable COM unit with a new or modified 
XS-852E/F mode S transponder that has MOD V installed. Honeywell Alert 
Service Bulletin 7510700-23-A0047 also refers to Honeywell Alert 
Service Bulletin 7517400-23-A6015, Revision 001, dated July 29, 2005, 
as an additional source of service information for modifying the XS-
852E/F mode S transponder by installing MOD V into the transponder.
    For mode S transponders 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, 
Honeywell Alert Service Bulletin 7517400-23-A0017 describes doing the 
following procedures:
     Replacing the modification plate of the transponder with a 
new plate.
     Marking all the modifications installed in the transponder 
on the new modification plate of the transponder.
     Testing the transponder.
     Reporting certain information to the manufacturer.
    Honeywell Alert Service Bulletin 7517400-23-A0017 also specifies 
prior or concurrent accomplishment of Honeywell Alert Service Bulletin 
7517400-23-A6016, dated August 30, 2005. Honeywell Alert Service 
Bulletin 7517400-23-A6016 describes procedures for installing MOD Y 
into the transponder and testing the transponder.
    Accomplishing the actions specified in the service information is 
intended to adequately address the unsafe condition.

FAA's Determination and Requirements of the Proposed AD

    We have evaluated all pertinent information and identified an 
unsafe condition that is likely to exist or develop on other products 
of this same type design. For this reason, we are proposing this AD, 
which would require revising the Normal Procedures section of the 
applicable Airplane Flight Manual to advise the flightcrew to check the 
status of the transponder after changing the ATC code. This AD would 
also require accomplishing the actions specified in the service 
information described previously, except as discussed under 
``Differences Between Proposed AD and Service Bulletins.''

Differences Between Proposed AD and Service Bulletins

    Service Bulletin 7510700-23-A0048 recommends testing certain COM 
units; however, the service bulletin does not specify what corrective 
action to take if the COM unit fails the test. This proposed AD would 
require, before further flight after the test, reinstalling MOD V into 
the transponder of the COM unit, in accordance with Service Bulletin 
7517400-23-A6015.
    Service Bulletin 7517400-23-A0017 recommends testing certain 
transponders; however, the service bulletin does not specify what 
corrective action to take if the transponder fails the test. This 
proposed AD would require, before further flight after the test, 
reinstalling MOD Y into the transponder, in accordance with Service 
Bulletin 7517400-23-A6016.
    Operators should note that, although the Accomplishment 
Instructions of the referenced service bulletins describe procedures 
for submitting a comment sheet related to service bulletin quality and 
a sheet recording compliance with the service bulletin, this proposed 
AD would not require those actions.

Costs of Compliance

    There are about 1,365 airplanes of the affected design in the 
worldwide fleet. This proposed AD would affect about 1,023 airplanes of 
U.S. registry. Of those airplanes, about 603 airplanes are equipped 
with RCZ-833J/K, -851J/K, or 854J COM units and about 420 airplanes are 
equipped with XS-856A/B or -857A mode S transponders. The following 
table provides the estimated costs, at an average labor rate of $80 per 
hour, for U.S. operators to comply with this proposed AD.

                                                                     Estimated Costs
--------------------------------------------------------------------------------------------------------------------------------------------------------
                                                                                                    Number of U.S.-
              Action                         Work hours             Parts      Cost per  airplane     registered                 Fleet cost
                                                                                                       airplanes
--------------------------------------------------------------------------------------------------------------------------------------------------------
AFM revision......................  1...........................       None  $80..................           1,023  $81,840.
Part identification, testing, and   3...........................        $35  $275.................             603  $165,825.
 replacement for RCZ-833J/K, -851J/
 K, and -854J COM units.
Part identification, testing, and   3 to 8 \1\..................       $175  $415 to $815 \1\.....             420  $174,300 to $342,300.\1\
 installation of software for XS-
 856A/B and -857A mode S
 transponders.
--------------------------------------------------------------------------------------------------------------------------------------------------------
\1\ Depending on test procedure.

Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to 
issue rules on aviation safety. Subtitle I, section 106, describes the 
authority of the FAA Administrator. Subtitle VII, Aviation Programs, 
describes in more detail the scope of the Agency's authority.
    We are issuing this rulemaking under the authority described in 
subtitle VII,

[[Page 25986]]

part A, subpart III, section 44701, ``General requirements.'' Under 
that section, Congress charges the FAA with promoting safe flight of 
civil aircraft in air commerce by prescribing regulations for 
practices, methods, and procedures the Administrator finds necessary 
for safety in air commerce. This regulation is within the scope of that 
authority because it addresses an unsafe condition that is likely to 
exist or develop on products identified in this rulemaking action.

Regulatory Findings

    We have determined that this proposed AD would not have federalism 
implications under Executive Order 13132. This proposed AD would not 
have a substantial direct effect on the States, on the relationship 
between the national Government and the States, or on the distribution 
of power and responsibilities among the various levels of government.
    For the reasons discussed above, I certify that the proposed 
regulation:
    1. Is not a ``significant regulatory action'' under Executive Order 
12866;
    2. Is not a ``significant rule'' under the DOT Regulatory Policies 
and Procedures (44 FR 11034, February 26, 1979); and
    3. Will not have a significant economic impact, positive or 
negative, on a substantial number of small entities under the criteria 
of the Regulatory Flexibility Act.
    We prepared a regulatory evaluation of the estimated costs to 
comply with this proposed AD and placed it in the AD docket. See the 
ADDRESSES section for a location to examine the regulatory evaluation.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Safety.

The Proposed Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA proposes to amend 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

    1. The authority citation for part 39 continues to read as follows:

    Authority: 49 U.S.C. 106(g), 40113, 44701.


Sec.  39.13  [Amended]

    2. The Federal Aviation Administration (FAA) amends Sec.  39.13 by 
adding the following new airworthiness directive (AD):

Honeywell International, Inc.: Docket No. FAA-2006-24639; 
Directorate Identifier 2005-NM-171-AD.

Comments Due Date

    (a) The FAA must receive comments on this AD action by June 19, 
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 Mystere-
Falcon 900 and Falcon 900EX airplanes; Dassault Model Falcon 2000 
and Falcon 2000EX airplanes; 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 5 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

[[Page 25987]]

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.

    Issued in Renton, Washington, on April 25, 2006.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. E6-6651 Filed 5-2-06; 8:45 am]
BILLING CODE 4910-13-P

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