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


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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.

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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 http://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 http://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
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                                                                                                           Number of U.S.-
             Action                       Work hours               Parts           Cost per airplane          registered             Fleet cost
                                                                                                              airplanes
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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.
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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
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            Service bulletin                      Revision level                            Date
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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.
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    (Only the first and second pages of Honeywell Alert Service 
Bulletin 7510700-23-A0047 and Honeywell Alert Service Bulletin 
7517400-23-A6015 contains the revision level of the document.) The 
Director of the Federal Register approved the incorporation by 
reference of these documents in accordance with 5 U.S.C. 552(a) and 
1 CFR part 51. Go to https://pubs.cas.honeywell.com/ or contact 
Honeywell International, Inc., Commercial Electronic Systems, 21111 
North 19th Avenue, Phoenix, Arizona 85027-2708, for a copy of this 
service information. You may review copies at the Docket Management 
Facility, U.S. Department of Transportation, 400 Seventh Street, 
SW., Room PL-401, Nassif Building, Washington, DC; on the Internet 
at http://dms.dot.gov; or at the National Archives and Records 
Administration (NARA). For information on the availability of this 
material at the NARA, call (202) 741-6030, or go to http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html.

    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]
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