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, 13498-13500 [E8-5001]

Download as PDF 13498 Federal Register / Vol. 73, No. 50 / Thursday, March 13, 2008 / Proposed Rules service in accordance with Avions de Transport Regional Service Bulletin ATR42– 30–0072 or ATR72–30–1042, both Revision l, both dated June 1, 2005; as applicable. Subject (d) Air Transport Association (ATA) of America Code 30: Ice and Rain Protection. Reason (e) The mandatory continuing airworthiness information (MCAI) states: A recent incident evidenced that some failures of the Pitot probe heating resistance may not be seen by the low current detection system on aircraft not equipped with [ATR] modification 05469 (SB (Service Bulletin) ATR42–30–0072 or ATR72–30–1042). In some conditions, an out of tolerance resistance, failing to provide a proper Pitot probe de-icing could not be detected. To address this unsafe condition, this Airworthiness Directive (AD) requires repetitive verification of the Pitot probes’ resistance and replacement of any defective probes, and ultimate replacement of the three low current sensors for Captain, First Officer and Standby Pitot probes. The unsafe condition is that undetected icing of the pitot probe could produce incorrect airspeed readings, which could lead to loss of control of the airplane. Actions and Compliance (f) Unless already done, do the following actions. (1) Within 550 flight hours after the effective date of this AD, measure the heating resistance of the three pitot probes, in accordance with the Accomplishment Instructions of Avions de Transport Regional Service Bulletin ATR42–30–0074 or ATR72– 30–1044, both dated May 14, 2007, as applicable. If any resistance exceeds 50 ohms, before next flight, replace the pitot probe in accordance with the Accomplishment Instructions of the applicable service bulletin. Repeat the measurement thereafter at intervals not to exceed 550 flight hours, until the current sensors have been replaced as required by paragraph (f)(2) of this AD. (2) Within 5,000 flight hours after the effective date of this AD, replace the three pitot probe current sensors, in accordance with the Accomplishment Instructions of Avions de Transport Regional Service Bulletin ATR42–30–0072 or ATR72–30– 1042, both Revision 1, both dated June 1, 2005; as applicable. Doing this paragraph ends the repetitive inspections required by paragraph (f)(1) of this AD. FAA AD Differences Note: This AD differs from the MCAI and/ or service information as follows: No differences. Other FAA AD Provisions (g) The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, International Branch, ANM–116, Transport Airplane Directorate, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. Send information to ATTN: Tom Rodriguez, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue, SW., Renton, Washington 98057–3356; telephone (425) 227–1137; fax (425) 227–1149. Before using any approved AMOC on any airplane to which the AMOC applies, notify your appropriate principal inspector (PI) in the FAA Flight Standards District Office (FSDO), or lacking a PI, your local FSDO. (2) Airworthy Product: For any requirement in this AD to obtain corrective actions from a manufacturer or other source, use these actions if they are FAA-approved. Corrective actions are considered FAA-approved if they are approved by the State of Design Authority (or their delegated agent). You are required to assure the product is airworthy before it is returned to service. (3) Reporting Requirements: For any reporting requirement in this AD, under the provisions of the Paperwork Reduction Act, the Office of Management and Budget (OMB) has approved the information collection requirements and has assigned OMB Control Number 2120–0056. Related Information (h) Refer to MCAI European Aviation Safety Agency (EASA) Airworthiness Directive 2007–0179, dated July 31, 2007, and the service information described in Table 1 of this AD, for related information. TABLE 1.—SERVICE INFORMATION Avions de Transport Regional Service Bulletin ATR42–30–0072 ATR42–30–0074 ATR72–30–1042 ATR72–30–1044 Revision level .............................................................................................................................. .............................................................................................................................. .............................................................................................................................. .............................................................................................................................. Issued in Renton, Washington, on March 3, 2008. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E8–5003 Filed 3–12–08; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2007–0290; Directorate Identifier 2007–NM–250–AD] rwilkins on PROD1PC63 with PROPOSALS 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 Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Notice of proposed rulemaking (NPRM). AGENCY: VerDate Aug<31>2005 16:23 Mar 12, 2008 Jkt 214001 PO 00000 Frm 00034 Fmt 4702 Sfmt 4702 1 ................................ Original ...................... 1 ................................ Original ...................... Dated June 1, 2005. May 14, 2007. June 1, 2005. May 14, 2007. SUMMARY: The FAA proposes to revise an existing airworthiness directive (AD) that applies to Sandel Avionics Incorporated Model ST3400 TAWS/RMI units as described above. The existing AD currently requires installing a warning placard on the TAWS/RMI and revising the Limitations section of the airplane flight manual (AFM). The existing AD also requires installing upgraded software in the TAWS/RMI. This proposed AD would allow installing later revisions of the software described in the existing AD. This proposed 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 proposing this AD to prevent a bearing error, which E:\FR\FM\13MRP1.SGM 13MRP1 Federal Register / Vol. 73, No. 50 / Thursday, March 13, 2008 / Proposed Rules 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: We must receive comments on this proposed AD by April 28, 2008. ADDRESSES: You may send comments by any of the following methods: • Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments. • Fax: 202–493–2251. • Mail: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue, SE., Washington, DC 20590. • Hand Delivery: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue, SE., Washington, DC 20590, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For service information identified in this AD, contact Sandel Avionics Incorporated (Sandel), 2401 Dogwood Way, Vista, California 92081. Examining the AD Docket You may examine the AD docket on the Internet at https:// www.regulations.gov; or in person at the Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this proposed AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Office (telephone 800–647–5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. 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: rwilkins on PROD1PC63 with PROPOSALS Comments Invited We invite you to send any written relevant data, views, or arguments about this proposed AD. Send your comments to the address listed under the ADDRESSES section. Include ‘‘Docket No. FAA–2007–0290; Directorate Identifier 2007–NM–250–AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this proposed AD. We will consider all comments received by the VerDate Aug<31>2005 16:23 Mar 12, 2008 Jkt 214001 closing date and may amend this proposed AD because of those comments. We will post all comments we receive, without change, to https:// www.regulations.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact we receive about this proposed AD. Discussion On August 3, 2006, we issued AD 2006–16–18, amendment 39–14718 (71 FR 48461, August 21, 2006), for 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 AD requires installing a warning placard on the TAWS/RMI and revising the Limitations section of the airplane flight manual (AFM). That AD also requires installing upgraded software in the TAWS/RMI. That AD resulted 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 issued that 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. Actions Since Existing AD Was Issued Since we issued AD 2006–16–18, we have determined that later revisions of the software described in Sandel ST3400 Service Bulletin SB3400–01, Revision B, dated September 15, 2004, which is specified as the appropriate source of service information for accomplishing the requirements of the existing AD, are acceptable for installation in the TAWS/RMI without needing our further approval. FAA’s Determination and Requirements of the Proposed AD We have evaluated all pertinent information and identified an unsafe condition that is likely to exist or develop on other products of this same type design. For this reason, we are proposing this AD, which would revise AD 2006–16–18 to permit installing later revisions of the software described in the existing service information, and would retain the requirements of the existing AD. PO 00000 Frm 00035 Fmt 4702 Sfmt 4702 13499 Costs of Compliance This proposed AD describes the installation of later revisions of software than those specified in AD 2006–16–18; however, this change imposes no new costs on operators. Costs are repeated here for operator convenience only. This proposed AD would affect about 300 airplanes of U.S. registry. The proposed actions would take about 1 work hour per airplane, at an average labor rate of $80 per work hour. Based on these figures, the estimated cost of the proposed AD for U.S. operators is $24,000, or $80 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 proposed AD would not have federalism implications under Executive Order 13132. This proposed AD would not have a substantial direct effect on the States, on the relationship between the national Government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify that the proposed regulation: 1. Is not a ‘‘significant regulatory action’’ under Executive Order 12866; 2. Is not a ‘‘significant rule’’ under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); and 3. Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. We prepared a regulatory evaluation of the estimated costs to comply with this proposed AD and place it in the AD docket. See the ADDRESSES section for a E:\FR\FM\13MRP1.SGM 13MRP1 13500 Federal Register / Vol. 73, No. 50 / Thursday, March 13, 2008 / Proposed Rules Authority: 49 U.S.C. 106(g), 40113, 44701. location to examine the regulatory evaluation. § 39.13 List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Safety. The Proposed Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 14 CFR part 39 as follows: PART 39—AIRWORTHINESS DIRECTIVES (b) This AD revises AD 2006–16–18. [Amended] 2. The Federal Aviation Administration (FAA) amends § 39.13 by removing amendment 39–14718 (71 FR 48461, August 21, 2006) and adding the following new airworthiness directive (AD): 2006–16–18 R1 Sandel Avionics Incorporated: Docket No. FAA–2007– 0290; Directorate Identifier 2007–NM– 250–AD. Comments Due Date 1. The authority citation for part 39 continues to read as follows: Affected ADs (a) The FAA must receive comments on this AD action by April 28, 2008. 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 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 ........................................................................................................ 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 .................................................................................................. 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. 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. rwilkins on PROD1PC63 with PROPOSALS Installing Placard (f) Within 14 days after September 25, 2006 (the effective date of AD 2006–16–18): 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. VerDate Aug<31>2005 16:23 Mar 12, 2008 Jkt 214001 Revising Airplane Flight Manual (AFM) (g) Within 14 days after September 25, 2006: 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 September 25, 2006, 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). Revisions of software later than revision 3.07 or A3.06, as applicable, are considered acceptable for compliance with the requirements of this paragraph. 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 September 25, 2006, no person may install, on any airplane, a PO 00000 Frm 00036 Fmt 4702 Sfmt 4702 Model 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) To request a different method of compliance or a different compliance time for this AD, follow the procedures in 14 CFR 39.19. Before using any approved AMOC on any airplane to which the AMOC applies, notify your appropriate principal inspector (PI) in the FAA Flight Standards District Office (FSDO), or lacking a PI, your local FSDO. Issued in Renton, Washington, on March 3, 2008. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E8–5001 Filed 3–12–08; 8:45 am] BILLING CODE 4910–13–P E:\FR\FM\13MRP1.SGM 13MRP1

Agencies

[Federal Register Volume 73, Number 50 (Thursday, March 13, 2008)]
[Proposed Rules]
[Pages 13498-13500]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E8-5001]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2007-0290; Directorate Identifier 2007-NM-250-AD]
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: Notice of proposed rulemaking (NPRM).

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

SUMMARY: The FAA proposes to revise an existing airworthiness directive 
(AD) that applies to Sandel Avionics Incorporated Model ST3400 TAWS/RMI 
units as described above. The existing AD currently requires installing 
a warning placard on the TAWS/RMI and revising the Limitations section 
of the airplane flight manual (AFM). The existing AD also requires 
installing upgraded software in the TAWS/RMI. This proposed AD would 
allow installing later revisions of the software described in the 
existing AD. This proposed 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 proposing 
this AD to prevent a bearing error, which

[[Page 13499]]

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: We must receive comments on this proposed AD by April 28, 2008.

ADDRESSES: You may send comments by any of the following methods:
     Federal eRulemaking Portal: Go to https://
www.regulations.gov. Follow the instructions for submitting comments.
     Fax: 202-493-2251.
     Mail: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue, SE., Washington, DC 20590.
     Hand Delivery: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue, SE., Washington, DC 20590, between 9 a.m. and 5 p.m., 
Monday through Friday, except Federal holidays.
    For service information identified in this AD, contact Sandel 
Avionics Incorporated (Sandel), 2401 Dogwood Way, Vista, California 
92081.

Examining the AD Docket

    You may examine the AD docket on the Internet at https://
www.regulations.gov; or in person at the Docket Management Facility 
between 9 a.m. and 5 p.m., Monday through Friday, except Federal 
holidays. The AD docket contains this proposed AD, the regulatory 
evaluation, any comments received, and other information. The street 
address for the Docket Office (telephone 800-647-5527) is in the 
ADDRESSES section. Comments will be available in the AD docket shortly 
after receipt.

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: 

Comments Invited

    We invite you to send any written relevant data, views, or 
arguments about this proposed AD. Send your comments to the address 
listed under the ADDRESSES section. Include ``Docket No. FAA-2007-0290; 
Directorate Identifier 2007-NM-250-AD'' at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of this proposed AD. We 
will consider all comments received by the closing date and may amend 
this proposed AD because of those comments.
    We will post all comments we receive, without change, to https://
www.regulations.gov, including any personal information you provide. We 
will also post a report summarizing each substantive verbal contact we 
receive about this proposed AD.

Discussion

    On August 3, 2006, we issued AD 2006-16-18, amendment 39-14718 (71 
FR 48461, August 21, 2006), for 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 AD requires installing a warning placard on the TAWS/RMI and 
revising the Limitations section of the airplane flight manual (AFM). 
That AD also requires installing upgraded software in the TAWS/RMI. 
That AD resulted 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 issued that 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.

Actions Since Existing AD Was Issued

    Since we issued AD 2006-16-18, we have determined that later 
revisions of the software described in Sandel ST3400 Service Bulletin 
SB3400-01, Revision B, dated September 15, 2004, which is specified as 
the appropriate source of service information for accomplishing the 
requirements of the existing AD, are acceptable for installation in the 
TAWS/RMI without needing our further approval.

FAA's Determination and Requirements of the Proposed AD

    We have evaluated all pertinent information and identified an 
unsafe condition that is likely to exist or develop on other products 
of this same type design. For this reason, we are proposing this AD, 
which would revise AD 2006-16-18 to permit installing later revisions 
of the software described in the existing service information, and 
would retain the requirements of the existing AD.

Costs of Compliance

    This proposed AD describes the installation of later revisions of 
software than those specified in AD 2006-16-18; however, this change 
imposes no new costs on operators. Costs are repeated here for operator 
convenience only.
    This proposed AD would affect about 300 airplanes of U.S. registry. 
The proposed actions would take about 1 work hour per airplane, at an 
average labor rate of $80 per work hour. Based on these figures, the 
estimated cost of the proposed AD for U.S. operators is $24,000, or $80 
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 proposed AD would not have federalism 
implications under Executive Order 13132. This proposed AD would not 
have a substantial direct effect on the States, on the relationship 
between the national Government and the States, or on the distribution 
of power and responsibilities among the various levels of government.
    For the reasons discussed above, I certify that the proposed 
regulation:
    1. Is not a ``significant regulatory action'' under Executive Order 
12866;
    2. Is not a ``significant rule'' under the DOT Regulatory Policies 
and Procedures (44 FR 11034, February 26, 1979); and
    3. Will not have a significant economic impact, positive or 
negative, on a substantial number of small entities under the criteria 
of the Regulatory Flexibility Act.
    We prepared a regulatory evaluation of the estimated costs to 
comply with this proposed AD and place it in the AD docket. See the 
ADDRESSES section for a

[[Page 13500]]

location to examine the regulatory evaluation.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Safety.

The Proposed Amendment

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

PART 39--AIRWORTHINESS DIRECTIVES

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

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


Sec.  39.13  [Amended]

    2. The Federal Aviation Administration (FAA) amends Sec.  39.13 by 
removing amendment 39-14718 (71 FR 48461, August 21, 2006) and adding 
the following new airworthiness directive (AD):

2006-16-18 R1 Sandel Avionics Incorporated: Docket No. FAA-2007-
0290; Directorate Identifier 2007-NM-250-AD.

Comments Due Date

    (a) The FAA must receive comments on this AD action by April 28, 
2008.

Affected ADs

    (b) This AD revises AD 2006-16-18.

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 
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--Breguet          Falcon 10.
 Aviation (AMD/BA).
Boeing.................................  727, 737, 747.
Bombardier (LearJet)...................  24, 35, 36, 55.
British Aerospace (Operations) Limited.  Jetstream Series 3101.
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 (IAI).......  1124, 1125 Westwind Astra.
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 September 25, 2006 (the effective date 
of AD 2006-16-18): 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 September 25, 2006: 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 September 25, 2006, 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). 
Revisions of software later than revision 3.07 or A3.06, as 
applicable, are considered acceptable for compliance with the 
requirements of this paragraph. 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 September 25, 2006, no person may 
install, on any airplane, a Model 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) To request a different method of compliance or a different 
compliance time for this AD, follow the procedures in 14 CFR 39.19. 
Before using any approved AMOC on any airplane to which the AMOC 
applies, notify your appropriate principal inspector (PI) in the FAA 
Flight Standards District Office (FSDO), or lacking a PI, your local 
FSDO.

    Issued in Renton, Washington, on March 3, 2008.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
 [FR Doc. E8-5001 Filed 3-12-08; 8:45 am]
BILLING CODE 4910-13-P
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