Airworthiness Directives; Sandel Avionics Incorporated Model ST3400 Terrain Awareness Warning System/Radio Magnetic Indicator (TAWS/RMI) Units Approved Under Technical Standard Order(s) C113, C151a, or C151b; Installed on Various Small and Transport Category Airplanes, 48461-48463 [E6-13447]

Download as PDF Federal Register / Vol. 71, No. 161 / Monday, August 21, 2006 / Rules and Regulations rmajette on PROD1PC67 with RULES (1) The applied side or drag load factor, or both factors, at the center of gravity must be the most critical value up to 50 percent and 40 percent, respectively, of the limit side or drag load factors, or both factors, corresponding to the most severe condition resulting from consideration of the prescribed taxiing and ground handling conditions; (2) For the braked roll conditions of Special Conditions B.3., paragraph (b)(2), the drag loads on each inflated tire may not be less than those at each tire for the symmetrical load distribution with no deflated tires; (3) The vertical load factor at the center of gravity must be 60 percent and 50 percent, respectively, of the factor with no deflated tires, except that it may not be less than 1g; and (4) The pivoting condition of Special Condition B.5. and the braked roll conditions of Special Condition B.3., paragraph (c), need not be considered with deflated tires. specified in paragraph (b)(1) of this paragraph; (4) The effects of wheel spin-up need not be included. (c) In lieu of the tests prescribed in this paragraph, changes in previously approved design weights and minor changes in design may be substantiated by analyses based on previous tests conducted on the same basic landing gear system that has similar energy absorption characteristics. 8. Shock Absorption Tests In lieu of § 25.723, the following special conditions apply: (a) The analytical representation of the landing gear dynamic characteristics that is used in determining the landing loads must be validated by energy absorption tests. A range of tests must be conducted to ensure that the analytical representation is valid for the design conditions specified in Special Conditions A.2. and A.3., if applicable. (1) The configurations subjected to energy absorption tests at limit design conditions must include both the condition with the maximum energy absorbed by the landing gear and the condition with the maximum descent velocity obtained from Special Condition A.2. and A.3. (2) The test attitude of the landing gear unit and the application of appropriate drag loads during the test must simulate the airplane landing conditions in a manner consistent with the development of rational or conservative limit loads. (b) Each landing gear unit may not fail in a test, demonstrating its reserve energy absorption capacity, assuming— (1) The weight and pitch attitude correspond to the condition from Special Condition A.2. that provides the maximum energy absorbed by the landing gear; (2) Airplane lift is not greater than the airplane weight acting during the landing impact, unless the presence of systems or procedures significantly affects the lift; (3) The test descent velocity is 120% of that corresponding to the condition [Docket No. FAA–2006–24101; Directorate Identifier 2005–NM–103–AD; Amendment 39–14718; AD 2006–16–18] VerDate Aug<31>2005 15:07 Aug 18, 2006 Jkt 208001 Issued in Renton, Washington, on July 20, 2006. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E6–13779 Filed 8–18–06; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 48461 This AD becomes effective September 25, 2006. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in the AD as of September 25, 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 Sandel Avionics Incorporated (Sandel), 2401 Dogwood Way, Vista, California 92081, for service information identified in this AD. FOR FURTHER INFORMATION CONTACT: Ha A. Nguyen, Aerospace Engineer, Systems and Equipment Branch, ANM– 130L, FAA, Los Angeles Aircraft Certification Office, 3960 Paramount Boulevard, Lakewood, California 90712–4137; telephone (562) 627–5335; fax (562) 627–5210. SUPPLEMENTARY INFORMATION: DATES: Examining the Docket Airworthiness Directives; Sandel Avionics Incorporated Model ST3400 Terrain Awareness Warning System/ Radio Magnetic Indicator (TAWS/RMI) Units Approved Under Technical Standard Order(s) C113, C151a, or C151b; Installed on Various Small and Transport Category Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. 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 RIN 2120–AA64 AGENCY: SUMMARY: The FAA is adopting a new airworthiness directive (AD). The new AD is for Sandel Avionics Incorporated Model ST3400 TAWS/RMI units as described above. This AD requires installing a warning placard on the TAWS/RMI and revising the Limitations section of the airplane flight manual (AFM). This AD also requires installing upgraded software in the TAWS/RMI. This AD results from a report that an inflight bearing error occurred in a Model ST3400 TAWS/RMI configured to receive bearing information from a very high frequency omnidirectional range (VOR) receiver interface via a composite video signal, due to a combination of input signal fault and software error. We are issuing this AD to prevent a bearing error, which could lead to an airplane departing from its scheduled flight path, which could result in a reduction in separation from, and a possible collision with, other aircraft or terrain. PO 00000 Frm 00015 Fmt 4700 Sfmt 4700 The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to include an AD that would apply to Sandel Avionics Incorporated Model ST3400 terrain awareness warning system/radio magnetic indicator (TAWS/RMI) units approved under Technical Standard Order(s) C113, C151a, or C151b; installed on various small and transport category airplanes. That NPRM was published in the Federal Register on March 8, 2006 (71 FR 11549). That NPRM proposed to require installing a warning placard on the TAWS/RMI, installing upgraded software in the TAWS/RMI, revising the Limitations section of the airplane flight manual (AFM), and removing the placard and AFM revision after installing the software. Comments We provided the public the opportunity to participate in the development of this AD. We have considered the comments received. E:\FR\FM\21AUR1.SGM 21AUR1 48462 Federal Register / Vol. 71, No. 161 / Monday, August 21, 2006 / Rules and Regulations Support for the NPRM One commenter, Boeing, expresses support for the NPRM. Request for Clarification of Effect on Very High Frequency Omnidirectional Range (VOR) Receiver One commenter, Cessna, requests that we clarify the unsafe condition. Cessna states that we are not specific regarding the effect of system decoding on the automatic direction finder (ADF) signal. Cessna asserts that greater focus is needed on VOR bearing error. Cessna has provided a suggested revision for the summary of the NPRM and requests that we include an explanation of the effect of the ADF on the unsafe condition. We partially agree. The unsafe condition described in the AD affects only TAWS/RMI installations incorporating the RMI feature that are configured to receive bearing information from a VOR receiver interface via a composite video signal; there is no effect when the VOR receiver and the TAWS/RMI interface via ARINC 429. Further, this condition does not affect the TAWS/RMI bearing display when bearing information is being supplied from any ADF receiver. No technical change to the AD is needed in this regard; however, we have determined that the summary of the AD could more clearly specify the relationship of the required AFM revision to the required software upgrade. Therefore, we have clarified the summary of this AD to specify that the unsafe condition only occurs on TAWS/RMI units configured to interface with a VOR receiver via a composite video signal. rmajette on PROD1PC67 with RULES Request for Correction of Airplane Listings One commenter, Aviation Data Research, requests corrections to Table 1 of the NPRM. The commenter asserts that several of the airplane manufacturers and models are incorrectly specified and expresses concern that, although this information is clearly designated as advisory rather than regulatory, the inaccuracies might allow a legal defense against compliance with the AD. We partially agree. The described TAWS/RMI is subject to the requirements of this AD. Table 1 of the AD refers to airplanes equipped with the TAWS/RMI and, rather than being advisory, is part of the applicability of the AD. As indicated by the phrase, ‘‘but not limited to,’’ the TAWS/RMI is subject to this AD whether installed on any airplane by any manufacturer VerDate Aug<31>2005 15:07 Aug 18, 2006 Jkt 208001 during production or by any entity subsequent to production. However, we agree that an AD should provide accurate information. Therefore, we have revised Table 1 of the AD to identify model designations as published in the most recent type certificate data sheet for the affected models. Clarification of Summary The summary of the NPRM states, in part, that one proposed requirement of the AD is ‘‘removing the placard and AFM revision after installing the software.’’ However, the AD does not require these actions. To prevent confusion, we have revised the summary of the AD by deleting the clause quoted above. 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. 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 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. Costs of Compliance Adoption of the Amendment This AD will affect about 300 airplanes of U.S. registry. The required actions will take about 1 work hour per airplane, at an average labor rate of $65 per work hour. Based on these figures, the estimated cost of the AD for U.S. operators is $19,500, or $65 per airplane. I 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. PO 00000 Frm 00016 Fmt 4700 Sfmt 4700 Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: PART 39—AIRWORTHINESS DIRECTIVES 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 2006–16–18 Sandel Avionics Incorporated: Amendment 39–14718. Docket No. FAA–2006–24101; Directorate Identifier 2005–NM–103–AD. Effective Date (a) This AD becomes effective September 25, 2006. Affected ADs (b) None. Applicability (c) This AD applies to Sandel Avionics Incorporated (Sandel) Model ST3400 terrain awareness warning system/radio magnetic indicator (TAWS/RMI) units approved under Technical Standard Order(s) C113, C151a, or C151b; as identified in Sandel ST3400 E:\FR\FM\21AUR1.SGM 21AUR1 Federal Register / Vol. 71, No. 161 / Monday, August 21, 2006 / Rules and Regulations Service Bulletin SB3400–01, Revision B, dated September 15, 2004; as installed on various small and transport category airplanes, certificated in any category, 48463 including, but not limited, to the airplane models listed in Table 1 of this AD. TABLE 1.—MANUFACTURERS/AIRPLANE MODELS Manufacturer Airplane model(s) Airbus .................................................................. Avions Marcel Dassault—Breguet Aviation (AMD/BA). Boeing ................................................................. Bombardier (LearJet) .......................................... British Aerospace (Operations) Limited .............. Cessna ................................................................ Embraer .............................................................. Dassault-Aviation ................................................ Gulfstream .......................................................... Israel Aircraft Industries (IAI) .............................. McDonnell Douglas ............................................. Piper .................................................................... Raytheon ............................................................. Sabreliner ............................................................ Twin Commander ............................................... Viking Air Limited ................................................ Unsafe Condition (d) This AD results from a report that an in-flight bearing error occurred in a Model ST3400 TAWS/RMI unit configured to receive bearing information from a very high frequency omnidirectional range (VOR) receiver interface via a composite video signal, due to a combination of input signal fault and software error. We are issuing this AD to prevent a bearing error, which could lead to an airplane departing from its scheduled flight path, which could result in a reduction in separation from, and a possible collision with, other aircraft or terrain. 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. Installing Placard (f) Within 14 days after the effective date of this AD: Install a placard on the TAWS/ RMI which states, ‘‘NOT FOR PRIMARY VOR NAVIGATION,’’ in accordance with Sandel ST3400 Service Bulletin SB3400–01, Revision B, dated September 15, 2004. rmajette on PROD1PC67 with RULES Revising Airplane Flight Manual (AFM) (g) Within 14 days after the effective date of this AD: Revise the Limitations section of the applicable AFM to include the following statement: ‘‘Use of ST3400 TAWS/RMI for primary VOR navigation is prohibited unless the indicator has 3.07 or A3.06 software or later.’’ This may be done by inserting a copy of this AD into the AFM. Updating Software (h) Within 90 days after the effective date of this AD, in accordance with Sandel ST3400 Service Bulletin SB3400–01, Revision B, dated September 15, 2004: Fieldload the TAWS/RMI with updated software having revision 3.07 (for units having serial numbers (S/Ns) under 2000) or revision A3.06 (for units having S/Ns 2000 and VerDate Aug<31>2005 15:07 Aug 18, 2006 Jkt 208001 A300. Falcon 10. 727, 737, 747. 24, 35, 36, 55. Jetstream Series 3101. 208, 208B, 421C; 501, 525, 550, 560, 650, S550. EMB–120. Mystere-Falcon 50, Mystere-Falcon 200. G–I, G–1159A (G–III). 1124, 1125 Westwind Astra. DC–10. PA–31T2. 58; 1900D, 400; A36; BAe.125 Series 800A; HS.125 Series 600A/700A; Hawker 800–XP; 200, 300, 350, A200, B100, B200, B300, C90, C90A, C90B, E90, F90, MU–300–10. 60 (NA–265–60). 500–A, 695A. DHC–6. subsequent). The placard and AFM limitations revision installed as required by paragraphs (f) and (g) of this AD may be removed after the software upgrade required by paragraph (h) of this AD has been accomplished. Parts Installation (i) As of 90 days after the effective date of this AD, no person may install, on any airplane, an ST3400 TAWS/RMI unit, unless it has been modified in accordance with Sandel ST3400 Service Bulletin SB3400–01, Revision B, dated September 15, 2004. Alternative Methods of Compliance (AMOCs) (j)(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 14 CFR 39.19 on any airplane to which the AMOC applies, notify the appropriate principal inspector in the FAA Flight Standards Certificate Holding District Office. Material Incorporated by Reference (k) You must use Sandel ST3400 Service Bulletin SB3400–01, Revision B, dated September 15, 2004 (only the first page of the document shows the date of the document), to perform the actions that are required by this AD, unless the AD specifies otherwise. The Director of the Federal Register approved the incorporation by reference of this document in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Contact Sandel Avionics Incorporated (Sandel), 2401 Dogwood Way, Vista, California, 92081, 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 PO 00000 Frm 00017 Fmt 4700 Sfmt 4700 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 3, 2006. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E6–13447 Filed 8–18–06; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2004–19676; Directorate Identifier 2004–NM–138–AD; Amendment 39–14717; AD 2006–16–17] RIN 2120–AA64 Airworthiness Directives; Empresa Brasileira de Aeronautica S.A. (EMBRAER) Model EMB–135BJ, –135ER, –135KE, –135KL, and –135LR Airplanes; and Model EMB–145, –145ER, –145MR, –145LR, –145XR, –145MP, and –145EP 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 EMBRAER Model EMB–135 and –145 series airplanes. This AD requires determining the torque values of the screws that attach the seat tracks to the airplane, and corrective action if E:\FR\FM\21AUR1.SGM 21AUR1

Agencies

[Federal Register Volume 71, Number 161 (Monday, August 21, 2006)]
[Rules and Regulations]
[Pages 48461-48463]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E6-13447]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2006-24101; Directorate Identifier 2005-NM-103-AD; 
Amendment 39-14718; AD 2006-16-18]
RIN 2120-AA64


Airworthiness Directives; Sandel Avionics Incorporated Model 
ST3400 Terrain Awareness Warning System/Radio Magnetic Indicator (TAWS/
RMI) Units Approved Under Technical Standard Order(s) C113, C151a, or 
C151b; Installed on Various Small and 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). The 
new AD is for Sandel Avionics Incorporated Model ST3400 TAWS/RMI units 
as described above. This AD requires installing a warning placard on 
the TAWS/RMI and revising the Limitations section of the airplane 
flight manual (AFM). This AD also requires installing upgraded software 
in the TAWS/RMI. This AD results from a report that an in-flight 
bearing error occurred in a Model ST3400 TAWS/RMI configured to receive 
bearing information from a very high frequency omnidirectional range 
(VOR) receiver interface via a composite video signal, due to a 
combination of input signal fault and software error. We are issuing 
this AD to prevent a bearing error, which could lead to an airplane 
departing from its scheduled flight path, which could result in a 
reduction in separation from, and a possible collision with, other 
aircraft or terrain.

DATES: This AD becomes effective September 25, 2006.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in the AD as of September 25, 
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 Sandel Avionics Incorporated (Sandel), 2401 Dogwood Way, 
Vista, California 92081, for service information identified in this AD.

FOR FURTHER INFORMATION CONTACT: Ha A. Nguyen, Aerospace Engineer, 
Systems and Equipment Branch, ANM-130L, FAA, Los Angeles Aircraft 
Certification Office, 3960 Paramount Boulevard, Lakewood, California 
90712-4137; telephone (562) 627-5335; 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 Sandel Avionics 
Incorporated Model ST3400 terrain awareness warning system/radio 
magnetic indicator (TAWS/RMI) units approved under Technical Standard 
Order(s) C113, C151a, or C151b; installed on various small and 
transport category airplanes. That NPRM was published in the Federal 
Register on March 8, 2006 (71 FR 11549). That NPRM proposed to require 
installing a warning placard on the TAWS/RMI, installing upgraded 
software in the TAWS/RMI, revising the Limitations section of the 
airplane flight manual (AFM), and removing the placard and AFM revision 
after installing the software.

Comments

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

[[Page 48462]]

Support for the NPRM

    One commenter, Boeing, expresses support for the NPRM.

Request for Clarification of Effect on Very High Frequency 
Omnidirectional Range (VOR) Receiver

    One commenter, Cessna, requests that we clarify the unsafe 
condition. Cessna states that we are not specific regarding the effect 
of system decoding on the automatic direction finder (ADF) signal. 
Cessna asserts that greater focus is needed on VOR bearing error. 
Cessna has provided a suggested revision for the summary of the NPRM 
and requests that we include an explanation of the effect of the ADF on 
the unsafe condition.
    We partially agree. The unsafe condition described in the AD 
affects only TAWS/RMI installations incorporating the RMI feature that 
are configured to receive bearing information from a VOR receiver 
interface via a composite video signal; there is no effect when the VOR 
receiver and the TAWS/RMI interface via ARINC 429. Further, this 
condition does not affect the TAWS/RMI bearing display when bearing 
information is being supplied from any ADF receiver. No technical 
change to the AD is needed in this regard; however, we have determined 
that the summary of the AD could more clearly specify the relationship 
of the required AFM revision to the required software upgrade. 
Therefore, we have clarified the summary of this AD to specify that the 
unsafe condition only occurs on TAWS/RMI units configured to interface 
with a VOR receiver via a composite video signal.

Request for Correction of Airplane Listings

    One commenter, Aviation Data Research, requests corrections to 
Table 1 of the NPRM. The commenter asserts that several of the airplane 
manufacturers and models are incorrectly specified and expresses 
concern that, although this information is clearly designated as 
advisory rather than regulatory, the inaccuracies might allow a legal 
defense against compliance with the AD.
    We partially agree. The described TAWS/RMI is subject to the 
requirements of this AD. Table 1 of the AD refers to airplanes equipped 
with the TAWS/RMI and, rather than being advisory, is part of the 
applicability of the AD. As indicated by the phrase, ``but not limited 
to,'' the TAWS/RMI is subject to this AD whether installed on any 
airplane by any manufacturer during production or by any entity 
subsequent to production. However, we agree that an AD should provide 
accurate information. Therefore, we have revised Table 1 of the AD to 
identify model designations as published in the most recent type 
certificate data sheet for the affected models.

Clarification of Summary

    The summary of the NPRM states, in part, that one proposed 
requirement of the AD is ``removing the placard and AFM revision after 
installing the software.'' However, the AD does not require these 
actions. To prevent confusion, we have revised the summary of the AD by 
deleting the clause quoted above.

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

    This AD will affect about 300 airplanes of U.S. registry. The 
required actions will take about 1 work hour per airplane, at an 
average labor rate of $65 per work hour. Based on these figures, the 
estimated cost of the AD for U.S. operators is $19,500, or $65 per 
airplane.

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 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):

2006-16-18 Sandel Avionics Incorporated: Amendment 39-14718. Docket 
No. FAA-2006-24101; Directorate Identifier 2005-NM-103-AD.

Effective Date

    (a) This AD becomes effective September 25, 2006.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to Sandel Avionics Incorporated (Sandel) 
Model ST3400 terrain awareness warning system/radio magnetic 
indicator (TAWS/RMI) units approved under Technical Standard 
Order(s) C113, C151a, or C151b; as identified in Sandel ST3400

[[Page 48463]]

Service Bulletin SB3400-01, Revision B, dated September 15, 2004; as 
installed on various small and transport category airplanes, 
certificated in any category, including, but not limited, to the 
airplane models listed in Table 1 of this AD.

                 Table 1.--Manufacturers/Airplane Models
------------------------------------------------------------------------
         Manufacturer                      Airplane model(s)
------------------------------------------------------------------------
Airbus.......................  A300.
Avions Marcel Dassault--       Falcon 10.
 Breguet Aviation (AMD/BA).
Boeing.......................  727, 737, 747.
Bombardier (LearJet).........  24, 35, 36, 55.
British Aerospace              Jetstream Series 3101.
 (Operations) Limited.
Cessna.......................  208, 208B, 421C; 501, 525, 550, 560, 650,
                                S550.
Embraer......................  EMB-120.
Dassault-Aviation............  Mystere-Falcon 50, Mystere-Falcon 200.
Gulfstream...................  G-I, G-1159A (G-III).
Israel Aircraft Industries     1124, 1125 Westwind Astra.
 (IAI).
McDonnell Douglas............  DC-10.
Piper........................  PA-31T2.
Raytheon.....................  58; 1900D, 400; A36; BAe.125 Series 800A;
                                HS.125 Series 600A/700A; Hawker 800-XP;
                                200, 300, 350, A200, B100, B200, B300,
                                C90, C90A, C90B, E90, F90, MU-300-10.
Sabreliner...................  60 (NA-265-60).
Twin Commander...............  500-A, 695A.
Viking Air Limited...........  DHC-6.
------------------------------------------------------------------------

Unsafe Condition

    (d) This AD results from a report that an in-flight bearing 
error occurred in a Model ST3400 TAWS/RMI unit configured to receive 
bearing information from a very high frequency omnidirectional range 
(VOR) receiver interface via a composite video signal, due to a 
combination of input signal fault and software error. We are issuing 
this AD to prevent a bearing error, which could lead to an airplane 
departing from its scheduled flight path, which could result in a 
reduction in separation from, and a possible collision with, other 
aircraft or terrain.

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.

Installing Placard

    (f) Within 14 days after the effective date of this AD: Install 
a placard on the TAWS/RMI which states, ``NOT FOR PRIMARY VOR 
NAVIGATION,'' in accordance with Sandel ST3400 Service Bulletin 
SB3400-01, Revision B, dated September 15, 2004.

Revising Airplane Flight Manual (AFM)

    (g) Within 14 days after the effective date of this AD: Revise 
the Limitations section of the applicable AFM to include the 
following statement: ``Use of ST3400 TAWS/RMI for primary VOR 
navigation is prohibited unless the indicator has 3.07 or A3.06 
software or later.'' This may be done by inserting a copy of this AD 
into the AFM.

Updating Software

    (h) Within 90 days after the effective date of this AD, in 
accordance with Sandel ST3400 Service Bulletin SB3400-01, Revision 
B, dated September 15, 2004: Field-load the TAWS/RMI with updated 
software having revision 3.07 (for units having serial numbers (S/
Ns) under 2000) or revision A3.06 (for units having S/Ns 2000 and 
subsequent). The placard and AFM limitations revision installed as 
required by paragraphs (f) and (g) of this AD may be removed after 
the software upgrade required by paragraph (h) of this AD has been 
accomplished.

Parts Installation

    (i) As of 90 days after the effective date of this AD, no person 
may install, on any airplane, an ST3400 TAWS/RMI unit, unless it has 
been modified in accordance with Sandel ST3400 Service Bulletin 
SB3400-01, Revision B, dated September 15, 2004.

Alternative Methods of Compliance (AMOCs)

    (j)(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 14 CFR 
39.19 on any airplane to which the AMOC applies, notify the 
appropriate principal inspector in the FAA Flight Standards 
Certificate Holding District Office.

Material Incorporated by Reference

    (k) You must use Sandel ST3400 Service Bulletin SB3400-01, 
Revision B, dated September 15, 2004 (only the first page of the 
document shows the date of the document), to perform the actions 
that are required by this AD, unless the AD specifies otherwise. The 
Director of the Federal Register approved the incorporation by 
reference of this document in accordance with 5 U.S.C. 552(a) and 1 
CFR part 51. Contact Sandel Avionics Incorporated (Sandel), 2401 
Dogwood Way, Vista, California, 92081, 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 3, 2006.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
 [FR Doc. E6-13447 Filed 8-18-06; 8:45 am]
BILLING CODE 4910-13-P
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