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, 53553-53556 [E6-14940]

Download as PDF Federal Register / Vol. 71, No. 176 / Tuesday, September 12, 2006 / Rules and Regulations Note 3: This AD differs from the European ASBs and the EASA AD in that we do not permit flight with known cracks in the MSC tapered housing. (d) Adjusting the tightening torque on the upper ball-end attachment nut of a noncracked MSC or replacing a cracked MSC with an airworthy MSC with 177–199 in-lb (2–2.25 daN·m) tightening torque applied to the upper ball-end attachment nut is terminating action for the requirements of this AD. (e) To request a different method of compliance or a different compliance time for this AD, follow the procedures in 14 CFR 39.19. Contact the Manager, Safety Management Group, Rotorcraft Directorate, FAA, ATTN: Uday Garadi, Aviation Safety Engineer, Regulations and Guidance Group, Fort Worth, Texas 76193–0110, telephone (817) 222–5123, fax (817) 222–5961, for information about previously approved alternative methods of compliance. (f) Special flight permits will not be issued. (g) This amendment becomes effective on September 27, 2006. Note 4: The subject of this AD is addressed in European Aviation Safety Agency Emergency AD No. 2006–0055–E, dated March 1, 2006. Issued in Fort Worth, Texas, on September 1, 2006. David A. Downey, Manager, Rotorcraft Directorate, Aircraft Certification Service. [FR Doc. 06–7560 Filed 9–11–06; 8:45 am] BILLING CODE 4910–13–M DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2006–24639; Directorate Identifier 2005–NM–171–AD; Amendment 39–14761; AD 2006–19–04] 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: Final rule. AGENCY: 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 jlentini on PROD1PC65 with RULES SUMMARY: VerDate Aug<31>2005 15:49 Sep 11, 2006 Jkt 205001 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. DATES: This AD becomes effective October 17, 2006. The Director of the Federal Register approved the incorporation by reference of certain publications listed in the AD as of October 17, 2006. ADDRESSES: You may examine the AD docket on the Internet at https:// dms.dot.gov or in person at the Docket Management Facility, U.S. Department of Transportation, 400 Seventh Street, SW., Nassif Building, Room PL–401, Washington, DC. Go to https:// pubs.cas.honeywell.com/ or contact Honeywell International, Inc., Commercial Electronic Systems, 21111 North 19th Avenue, Phoenix, Arizona 85027–2708, for service information identified in this 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: Examining the Docket You may examine the airworthiness directive (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 street address stated in the ADDRESSES section. PO 00000 Frm 00009 Fmt 4700 Sfmt 4700 53553 Discussion The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to include an AD that would apply to certain 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. That NPRM was published in the Federal Register on May 3, 2006 (71 FR 25984). That NPRM proposed to require a revision to the Normal Procedures section of the airplane flight manual (AFM) to advise the flightcrew to check the status of the transponder after changing the air traffic control (ATC) code. That NPRM also proposed to 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, that NPRM proposed to require replacing the transponders of certain COM units with new or modified transponders. For certain other airplanes, that NPRM proposed to require installing a modification into certain transponders. Comments We provided the public the opportunity to participate in the development of this AD. We have considered the comments received. Support for NPRM The Air Line Pilots Association supports the NPRM. Request To Revise Applicability Dassault Falcon Jet (DFJ) requests that we delete Dassault Model MystereFalcon 900 airplanes and Model Falcon 2000 airplanes from the applicability of the NPRM. DFJ states that none of the discrepant communication units or transponders are installed on these model airplanes. According to DFJ, the discrepant parts are installed only on Model Falcon 900EX airplanes, serial number (S/N) 97 and S/Ns 120 and subsequent; and Model Falcon 2000EX airplanes, S/N 6 and S/Ns 28 and subsequent. We agree and have revised paragraph (c) of this AD accordingly. Request To Revise Compliance Time Empresa Brasileira de Aeronautica S.A. (EMBRAER) requests that we extend the compliance time for the AFM revision from 5 to 30 days. EMBRAER asserts that the loss of the transponder does not pose so great of a hazard to justify such an urgent compliance time. E:\FR\FM\12SER1.SGM 12SER1 53554 Federal Register / Vol. 71, No. 176 / Tuesday, September 12, 2006 / Rules and Regulations As justification for extending the compliance time, EMBRAER states that some of the affected airplanes might be on international trips, where it may not be possible to return an airplane to a convenient location and accomplish the AFM revision within 5 days after the effective date of this AD. We agree that the compliance times can be extended somewhat. We have determined that extending the compliance time to 14 days will not adversely affect safety. Therefore, we have revised paragraph (f) of this AD accordingly. Request To Revise Address of Part Manufacturer Honeywell states that its address, as provided in the NPRM, is no longer valid. Therefore, the commenter requests that we include the following address to acquire service information pertaining to this AD: 21111 North 19th Avenue, Phoenix, Arizona 85308. We agree and have verified with the United States Postal Service that the correct zip code for the address given above is 85027–2708. We have updated the commenter’s address in the ADDRESSES section and in paragraph (n) of this AD. Request To Revise Requirements Honeywell disagrees with the proposed corrective action to reinstall MOD V into the transponder of the COM unit if the COM unit fails the test described in paragraph (g) of the NPRM. (We proposed to accomplish this corrective action in accordance with Honeywell Alert Service Bulletin 7517400–23–A6015, Revision 001, dated July 29, 2005.) The commenter states that Honeywell Alert Service Bulletin 7510700–23–A0048, dated January 27, 2006, recommends only to verify that MOD AT has been installed and update the part number (P/N) of the COM unit for tracking purposes. Honeywell believes that it would be preferable to have operators inspect the COM unit to determine if MOD AT (transponder MOD V) has been installed. Honeywell adds that if MOD AT is installed, the airplane should be allowed to keep flying even if the COM unit P/N has not been updated. Honeywell’s justification is that the airplane has already received the fix and that updating the COM unit P/N adds no value. The commenter further proposes that the NPRM should advise operators that if a COM unit is returned to a shop for any reason, the replacement part must have the new P/N (with MOD AT) before it can be returned to the original equipment manufacturer (OEM) or operator. As justification, Honeywell states that a purge of all old P/Ns will take place once all OEMs have allowed the new P/Ns. We disagree. Honeywell proposes an alternative action only if a COM unit is inspected and determined to have MOD AT installed. However, the commenter offers no alternative if a COM unit is determined to not have MOD AT installed (i.e., fails the test described in paragraph (g) of this AD). MOD AT is accomplished by installing an XS–852E/ F mode S transponder having MOD V into the COM unit. Therefore, if a COM unit fails the test described in paragraph (g) of this AD, we have determined that the corrective action is to reinstall MOD V into the transponder of the COM unit, thereby ensuring that MOD AT has been installed properly. Further, we do not find it acceptable to allow some COM units to remain in service without updated P/Ns, even if MOD AT has been installed. This would create a high rate of confusion among OEMs, operators, and other end users in determining which COM units are in compliance with this AD. We have not revised this AD in this regard. Conclusion We have carefully reviewed the available data, including the comments received, and determined that air safety and the public interest require adopting the AD with the changes described previously. We have determined that these changes will neither increase the economic burden on any operator nor increase the scope of the AD. Costs of Compliance There are about 1,365 airplanes of the affected design in the worldwide fleet. This AD affects 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 work hour, for U.S. operators to comply with this AD. ESTIMATED COSTS Action Work hours Parts Cost per airplane 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. 1 ................................ 3 ................................ None ... $35 ...... $80 ............................ $275 .......................... 3 to 8, depending on test procedure. $175 .... $415 to $815, depending on testing procedure. Authority for This Rulemaking jlentini on PROD1PC65 with RULES Number of U.S.-registered airplanes 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, VerDate Aug<31>2005 15:49 Sep 11, 2006 Jkt 205001 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 PO 00000 Frm 00010 Fmt 4700 Sfmt 4700 1,023 603 420 Fleet cost $81,840. $165,825. $174,300 to $342,300, depending on testing procedure. products identified in this rulemaking action. Regulatory Findings We have determined that this AD will not have federalism implications under Executive Order 13132. This AD will 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 E:\FR\FM\12SER1.SGM 12SER1 Federal Register / Vol. 71, No. 176 / Tuesday, September 12, 2006 / Rules and Regulations responsibilities among the various levels of government. For the reasons discussed above, I certify that this AD: (1) Is not a ‘‘significant regulatory action’’ under Executive Order 12866; (2) Is not a ‘‘significant rule’’ under 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 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, Incorporation by reference, Safety. Adoption of the Amendment 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. Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: 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. PART 39—AIRWORTHINESS DIRECTIVES 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. I 1. The authority citation for part 39 continues to read as follows: I Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The Federal Aviation Administration (FAA) amends § 39.13 by adding the following new airworthiness directive (AD): I 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. jlentini on PROD1PC65 with RULES 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 VerDate Aug<31>2005 15:49 Sep 11, 2006 Jkt 205001 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/ PO 00000 Frm 00011 Fmt 4700 Sfmt 4700 53555 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 § 39.19 on any airplane to which the AMOC applies, notify the appropriate principal inspector in the FAA Flight Standards Certificate Holding District Office. E:\FR\FM\12SER1.SGM 12SER1 53556 Federal Register / Vol. 71, No. 176 / Tuesday, September 12, 2006 / Rules and Regulations 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 Honeywell Honeywell Honeywell Honeywell Honeywell Alert Alert Alert Alert Alert Service Service Service Service Service Bulletin Bulletin Bulletin Bulletin Bulletin 7510700–23–A0047 7510700–23–A0048 7517400–23–A6015 7517400–23–A6016 7517400–23–A0017 (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 https://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 https:// www.archives.gov/federal_register/ code_of_federal_regulations/ ibr_locations.html. Issued in Renton, Washington, on August 31, 2006. Kalene C. Yanamura, Acting Manager,Transport Airplane Directorate,Aircraft Certification Service. [FR Doc. E6–14940 Filed 9–11–06; 8:45 am] jlentini on PROD1PC65 with RULES BILLING CODE 4910–13–P VerDate Aug<31>2005 15:49 Sep 11, 2006 Jkt 205001 Revision level ........................................................................... ........................................................................... ........................................................................... ........................................................................... ........................................................................... DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2006–24787; Directorate Identifier 2006–NM–043–AD; Amendment 39–14760; AD 2006–19–03] RIN 2120–AA64 Airworthiness Directives; McDonnell Douglas Model DC–10–10 and DC–10– 10F Airplanes; Model DC–10–15 Airplanes; Model DC–10–30 and DC– 10–30F (KC–10A and KDC–10) Airplanes; Model DC–10–40 and DC– 10–40F Airplanes; Model MD–10–10F and MD–10–30F Airplanes; and Model MD–11 and MD–11F Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: SUMMARY: The FAA is adopting a new airworthiness directive (AD) for certain McDonnell Douglas transport category airplanes. This AD requires fabrication and installation of a wire harness guard in the right wheel well of the main landing gear (MLG), and related investigative and corrective actions as necessary. For certain airplanes, this AD also requires replacement of the electrical connectors of the auxiliary hydraulic pumps with improved electrical connectors and related investigative and corrective actions. This AD results from fuel system reviews conducted by the manufacturer. We are issuing this AD to prevent damage to the wire support bracket and wiring of the auxiliary hydraulic pump and, for certain airplanes, water intrusion through the electrical connectors of the auxiliary hydraulic pump. These conditions could lead to a potential ignition source in the right wheel well of the MLG around the fuel tank, which, in combination with flammable fuel vapors, could result in fuel tank explosions and consequent loss of the airplane. PO 00000 Frm 00012 Fmt 4700 Sfmt 4700 001 ...................... Original ............... 001 ...................... Original ............... Original ............... Date July 29, 2005. January 27, 2006. July 29, 2005. August 30, 2005. January 23, 2006. This AD becomes effective October 17, 2006. The Director of the Federal Register approved the incorporation by reference of certain publications listed in the AD as of October 17, 2006. ADDRESSES: You may examine the AD docket on the Internet at https:// dms.dot.gov or in person at the Docket Management Facility, U.S. Department of Transportation, 400 Seventh Street, SW., Nassif Building, Room PL–401, Washington, DC. Contact Boeing Commercial Airplanes, Long Beach Division, 3855 Lakewood Boulevard, Long Beach, California 90846, Attention: Data and Service Management, Dept. C1–L5A (D800–0024), for service information identified in this AD. FOR FURTHER INFORMATION CONTACT: Ken Sujishi, Aerospace Engineer, Cabin Safety/Mechanical and Environmental Systems Branch, ANM–150L, FAA, Los Angeles Aircraft Certification Office, 3960 Paramount Boulevard, Lakewood, California 90712–4137; telephone (562) 627–5353; fax (562) 627–5210. SUPPLEMENTARY INFORMATION: DATES: Examining the Docket You may examine the airworthiness directive (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 street address stated in the ADDRESSES section. Discussion The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to include an AD that would apply to certain McDonnell Douglas Model DC–10–10 and DC–10–10F airplanes; Model DC–10–15 airplanes; Model DC–10–30 and DC–10–30F (KC– 10A and KDC–10) airplanes; Model DC– 10–40 and DC–10–40F airplanes; Model MD–10–10F and MD–10–30F airplanes; E:\FR\FM\12SER1.SGM 12SER1

Agencies

[Federal Register Volume 71, Number 176 (Tuesday, September 12, 2006)]
[Rules and Regulations]
[Pages 53553-53556]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E6-14940]

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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2006-24639; Directorate Identifier 2005-NM-171-AD;
Amendment 39-14761; AD 2006-19-04]
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: Final rule.

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

SUMMARY: 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.

DATES: This AD becomes effective October 17, 2006.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in the AD as of October 17,
2006.

ADDRESSES: You may examine the AD docket on the Internet at https://
dms.dot.gov or in person at the Docket Management Facility, U.S.
Department of Transportation, 400 Seventh Street, SW., Nassif Building,
Room PL-401, Washington, DC.
Go to https://pubs.cas.honeywell.com/ or contact Honeywell
International, Inc., Commercial Electronic Systems, 21111 North 19th
Avenue, Phoenix, Arizona 85027-2708, for service information identified
in this 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:

Examining the Docket

You may examine the airworthiness directive (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 street address stated in the ADDRESSES section.

Discussion

The FAA issued a notice of proposed rulemaking (NPRM) to amend 14
CFR part 39 to include an AD that would apply to certain 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. That NPRM was published in the Federal Register on
May 3, 2006 (71 FR 25984). That NPRM proposed to require a revision to
the Normal Procedures section of the airplane flight manual (AFM) to
advise the flightcrew to check the status of the transponder after
changing the air traffic control (ATC) code. That NPRM also proposed to
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, that NPRM proposed to
require replacing the transponders of certain COM units with new or
modified transponders. For certain other airplanes, that NPRM proposed
to require installing a modification into certain transponders.

Comments

We provided the public the opportunity to participate in the
development of this AD. We have considered the comments received.

Support for NPRM

The Air Line Pilots Association supports the NPRM.

Request To Revise Applicability

Dassault Falcon Jet (DFJ) requests that we delete Dassault Model
Mystere-Falcon 900 airplanes and Model Falcon 2000 airplanes from the
applicability of the NPRM. DFJ states that none of the discrepant
communication units or transponders are installed on these model
airplanes. According to DFJ, the discrepant parts are installed only on
Model Falcon 900EX airplanes, serial number (S/N) 97 and S/Ns 120 and
subsequent; and Model Falcon 2000EX airplanes, S/N 6 and S/Ns 28 and
subsequent.
We agree and have revised paragraph (c) of this AD accordingly.

Request To Revise Compliance Time

Empresa Brasileira de Aeronautica S.A. (EMBRAER) requests that we
extend the compliance time for the AFM revision from 5 to 30 days.
EMBRAER asserts that the loss of the transponder does not pose so great
of a hazard to justify such an urgent compliance time.

[[Page 53554]]

As justification for extending the compliance time, EMBRAER states that
some of the affected airplanes might be on international trips, where
it may not be possible to return an airplane to a convenient location
and accomplish the AFM revision within 5 days after the effective date
of this AD.
We agree that the compliance times can be extended somewhat. We
have determined that extending the compliance time to 14 days will not
adversely affect safety. Therefore, we have revised paragraph (f) of
this AD accordingly.

Request To Revise Address of Part Manufacturer

Honeywell states that its address, as provided in the NPRM, is no
longer valid. Therefore, the commenter requests that we include the
following address to acquire service information pertaining to this AD:
21111 North 19th Avenue, Phoenix, Arizona 85308.
We agree and have verified with the United States Postal Service
that the correct zip code for the address given above is 85027-2708. We
have updated the commenter's address in the ADDRESSES section and in
paragraph (n) of this AD.

Request To Revise Requirements

Honeywell disagrees with the proposed corrective action to
reinstall MOD V into the transponder of the COM unit if the COM unit
fails the test described in paragraph (g) of the NPRM. (We proposed to
accomplish this corrective action in accordance with Honeywell Alert
Service Bulletin 7517400-23-A6015, Revision 001, dated July 29, 2005.)
The commenter states that Honeywell Alert Service Bulletin 7510700-23-
A0048, dated January 27, 2006, recommends only to verify that MOD AT
has been installed and update the part number (P/N) of the COM unit for
tracking purposes. Honeywell believes that it would be preferable to
have operators inspect the COM unit to determine if MOD AT (transponder
MOD V) has been installed. Honeywell adds that if MOD AT is installed,
the airplane should be allowed to keep flying even if the COM unit P/N
has not been updated. Honeywell's justification is that the airplane
has already received the fix and that updating the COM unit P/N adds no
value. The commenter further proposes that the NPRM should advise
operators that if a COM unit is returned to a shop for any reason, the
replacement part must have the new P/N (with MOD AT) before it can be
returned to the original equipment manufacturer (OEM) or operator. As
justification, Honeywell states that a purge of all old P/Ns will take
place once all OEMs have allowed the new P/Ns.
We disagree. Honeywell proposes an alternative action only if a COM
unit is inspected and determined to have MOD AT installed. However, the
commenter offers no alternative if a COM unit is determined to not have
MOD AT installed (i.e., fails the test described in paragraph (g) of
this AD). MOD AT is accomplished by installing an XS-852E/F mode S
transponder having MOD V into the COM unit. Therefore, if a COM unit
fails the test described in paragraph (g) of this AD, we have
determined that the corrective action is to reinstall MOD V into the
transponder of the COM unit, thereby ensuring that MOD AT has been
installed properly. Further, we do not find it acceptable to allow some
COM units to remain in service without updated P/Ns, even if MOD AT has
been installed. This would create a high rate of confusion among OEMs,
operators, and other end users in determining which COM units are in
compliance with this AD. We have not revised this AD in this regard.

Conclusion

We have carefully reviewed the available data, including the
comments received, and determined that air safety and the public
interest require adopting the AD with the changes described previously.
We have determined that these changes will neither increase the
economic burden on any operator nor increase the scope of the AD.

Costs of Compliance

There are about 1,365 airplanes of the affected design in the
worldwide fleet. This AD affects 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
work hour, for U.S. operators to comply with this 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, 3........................... $35......... $275........................ 603 $165,825.
and replacement for RCZ-833J/
K, -851J/K, and -854J COM
units.
Part identification, testing, 3 to 8, depending on test $175........ $415 to $815, depending on 420 $174,300 to $342,300,
and installation of software procedure. testing procedure. depending on testing
for XS-856A/B and -857A mode S procedure.
transponders.
--------------------------------------------------------------------------------------------------------------------------------------------------------

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, 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 AD will not have federalism
implications under Executive Order 13132. This AD will 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

[[Page 53555]]

responsibilities among the various levels of government.
For the reasons discussed above, I certify that this AD:
(1) Is not a ``significant regulatory action'' under Executive
Order 12866;
(2) Is not a ``significant rule'' under 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 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, Incorporation by
reference, Safety.

Adoption of the Amendment

0
Accordingly, under the authority delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

0
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]

0
2. The Federal Aviation Administration (FAA) amends Sec. 39.13 by
adding the following new airworthiness directive (AD):

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.

[[Page 53556]]

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 001............................. July 29, 2005.
7510700-23-A0047.
Honeywell Alert Service Bulletin Original........................ January 27, 2006.
7510700-23-A0048.
Honeywell Alert Service Bulletin 001............................. July 29, 2005.
7517400-23-A6015.
Honeywell Alert Service Bulletin Original........................ August 30, 2005.
7517400-23-A6016.
Honeywell Alert Service Bulletin Original........................ January 23, 2006.
7517400-23-A0017.
----------------------------------------------------------------------------------------------------------------

(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 https://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 https://
www.archives.gov/federal_register/code_of_federal_regulations/
ibr_locations.html.

Issued in Renton, Washington, on August 31, 2006.
Kalene C. Yanamura,
Acting Manager,Transport Airplane Directorate,Aircraft Certification
Service.
[FR Doc. E6-14940 Filed 9-11-06; 8:45 am]
BILLING CODE 4910-13-P

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