Airworthiness Directives; Sikorsky Aircraft Corporation Model S-61A, S-61D, S-61E, and S-61V Helicopters, 68766-68768 [E7-23604]

Download as PDF 68766 Federal Register / Vol. 72, No. 234 / Thursday, December 6, 2007 / Proposed Rules under the criteria of the Regulatory Flexibility Act. We prepared a regulatory evaluation of the estimated costs to comply with this proposed AD and placed it in the AD docket. See the ADDRESSES section for a location to examine the regulatory evaluation. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Safety. The Proposed Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 14 CFR part 39 as follows: PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 Alternative Methods of Compliance (AMOCs) (g)(1) The Manager, Seattle Aircraft Certification Office, 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 November 23, 2007. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E7–23639 Filed 12–5–07; 8:45 am] BILLING CODE 4910–13–P [Amended] DEPARTMENT OF TRANSPORTATION 2. The Federal Aviation Administration (FAA) amends § 39.13 by adding the following new airworthiness directive (AD): Federal Aviation Administration Boeing: Docket No. FAA–2007–0289; Directorate Identifier 2007–NM–208–AD. Comments Due Date (a) The FAA must receive comments on this AD action by January 22, 2008. Unsafe Condition (d) This AD results from a fuel system review conducted by the manufacturer. We are issuing this AD to prevent improperly sealed fasteners in the main and center fuel tanks from becoming an ignition source, in the event of a fault current, which could result in a fuel tank explosion and consequent loss of the airplane. 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. Fastener Sealing and Inspections (f) Within 60 months after the effective date of this AD, seal the applicable fasteners and do the general visual inspections of the wire bundle support installations, and do all the applicable corrective actions before further flight, by accomplishing all of the applicable actions specified in the Accomplishment Instructions of Boeing Alert 18:18 Dec 05, 2007 Jkt 214001 [Docket No. FAA–2007–0284; Directorate Identifier 2004–SW–06–AD] Airworthiness Directives; Sikorsky Aircraft Corporation Model S–61A, S– 61D, S–61E, and S–61V Helicopters Applicability (c) This AD applies to Boeing Model 757– 200, –200CB, –200PF, and –300 series airplanes, certificated in any category; as identified in Boeing Alert Service Bulletin 757–57A0064, dated July 16, 2007. VerDate Aug<31>2005 14 CFR Part 39 RIN 2120–AA64 Affected ADs (b) None. sroberts on PROD1PC70 with PROPOSALS Service Bulletin 757–57A0064, dated July 16, 2007. Federal Aviation Administration, DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: SUMMARY: This document proposes adopting a new airworthiness directive (AD) for the specified Sikorsky Aircraft Corporation (Sikorsky) model helicopters. The AD would require installing an electric chip detector on each engine and an on-board chip detector annunciation system. The AD would also require revising the Rotorcraft Flight Manual (RFM) to add procedures for crew response to the illumination of an on-board chip detector warning light. This AD would also require testing the engine chip detector system at specified intervals. This proposal is prompted by reports of Number 5 engine bearing failures. Failure of the bearing resulted in erratic movement of the high-speed, engine-totransmission shaft (shaft), an oil leak, an in-flight fire, and an emergency landing. The actions specified by the proposed AD are intended to detect an impending bearing failure, which if undetected and PO 00000 Frm 00004 Fmt 4702 Sfmt 4702 not addressed by appropriate crew action may result in an oil leak, a severed shaft housing, an uncontained in-flight fire, and a subsequent emergency landing. DATES: Comments must be received on or before February 4, 2008. ADDRESSES: Use one of the following addresses to submit comments on this proposed AD: • Federal eRulemaking Portal: Go to http://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. You may get the service information identified in this proposed AD from Sikorsky Aircraft Corporation, Attn: Manager, Commercial Technical Support, mailstop s581a, 6900 Main Street, Stratford, Connecticut, phone (203) 383–4866, e-mail address tsslibrary@sikorsky.com. You may examine the comments to this proposed AD in the AD docket on the Internet at http:// www.regulations.gov. FOR FURTHER INFORMATION CONTACT: Kirk Gustafson, Aviation Safety Engineer, Boston Aircraft Certification Office, Engine and Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803, telephone (781) 238–7190, fax (781) 238–7170. SUPPLEMENTARY INFORMATION: Comments Invited We invite you to submit any written data, views, or arguments regarding this proposed AD. Send your comments to the address listed under the caption ADDRESSES. Include the docket number ‘‘FAA–2007–0284, Directorate Identifier 2004–SW–06–AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of the proposed AD. We will consider all comments received by the closing date and may amend the proposed AD in light of those comments. We will post all comments we receive, without change, to http:// www.regulations.gov, including any personal information you provide. We will also post a report summarizing each E:\FR\FM\06DEP1.SGM 06DEP1 Federal Register / Vol. 72, No. 234 / Thursday, December 6, 2007 / Proposed Rules substantive verbal contact with FAA personnel concerning this proposed rulemaking. Using the search function of our docket Web site, you can find and read the comments to any of our dockets, including the name of the individual who sent or signed the comment. You may review the DOT’s complete Privacy Act Statement in the Federal Register published on April 11, 2000 (65 FR 19477–78). sroberts on PROD1PC70 with PROPOSALS Examining the Docket You may examine the docket that contains the proposed AD, any comments, and other information in person at the Docket Operations office between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The Docket Operations office (telephone (800) 647–5527) is located in Room W12–140 on the ground floor of the West Building at the street address stated in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. Discussion This document proposes adopting a new AD for Sikorsky Model S–61A, S– 61D, S–61E, and S–61V helicopters with GE CT58 series engines. The AD would require, within 60 days, installing an electric chip detector for the Number 5 bearing in both engines. The AD would also require installing an on-board chip detector annunciation system and revising the Emergency Procedures section of the RFM to add procedures for crew response to the illumination of an on-board chip detector warning light. In addition, the AD would require functional testing of the chip detector system at specified intervals. This proposal is prompted by five reports of bearing failure, which results in an oil leak, uneven rotation of the shaft, failure of the shaft housing, which is part of the fire containment system, and friction. The heat produced by this friction may ignite the leaking oil and result in an uncontained fire. The actions specified by the proposed AD are intended to detect an impending bearing failure, which if undetected and not addressed by appropriate crew action may result in an oil leak, severed shaft housing, an uncontained in-flight fire, and a subsequent emergency landing. The FAA has reviewed Sikorsky Alert Service Bulletin No. 61B30–15A, Revision A, dated October 20, 2003 (ASB). The Sikorsky ASB describes procedures for installing an engine chip detector system that will provide an ‘‘incockpit monitoring system’’ as a means to detect metallic chips if bearing deterioration occurs in either engine. Also, the FAA has reviewed General VerDate Aug<31>2005 18:18 Dec 05, 2007 Jkt 214001 Electric (GE) Aircraft Engines CT58 Service Bulletin Number 72–0195, dated May 1, 2003 (SB). The GE SB describes procedures for installing an alternate electrical chip detector (either part number 3018T72P01, cannon-type connector, or 3049T42P01, stud-type connector) to the power turbine accessory drive assembly. This unsafe condition is likely to exist or develop on other helicopters of the same type design. Therefore, the proposed AD would require the following within 60 days: • Installing an electric chip detector on each engine. • Installing an on-board chip detector annunciation system. • Thereafter, before further flight and at specified intervals, performing a functional test of the chip detector system. • Revising the RFM to add emergency procedures for crew response to the illumination of an on-board chip detector warning light. The actions would be required to be done following specified portions of the the service bulletins described previously. The FAA estimates that this proposed AD would affect 7 helicopters of U.S. registry. The proposed actions would take about 81.5 work hours per helicopter to install the engine chip detector and the on-board cockpit annunciation system. The proposed repetitive tests would affect about 7 helicopters and require 6 tests per year and require 1 work hour per test for 10 years of operating service. The average labor rate is $80 per work hour. Required parts would cost about $1,940 per helicopter. Based on these figures, the total cost impact of the proposed AD on U.S. operators would be $92,820 for the entire fleet The regulations proposed herein 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. Therefore, it is determined that this proposal would not have federalism implications under Executive Order 13132. For the reasons discussed above, I certify that this 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) if promulgated, 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. A copy of the draft PO 00000 Frm 00005 Fmt 4702 Sfmt 4702 68767 economic evaluation prepared for this action is contained in the Rules Docket. A copy of it may be obtained by contacting the Rules Docket at the location provided under the caption ADDRESSES. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Safety. The Proposed Amendment Accordingly, pursuant to the authority delegated to me by the Administrator, the Federal Aviation Administration proposes to amend part 39 of the Federal Aviation Regulations (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. § 39.13 [Amended] 2. Section 39.13 is amended by adding a new airworthiness directive to read as follows: Sikorsky Aircraft Corporation: Docket No. FAA–2007–0284; Directorate Identifier No. 2004–SW–06–AD. Applicability Model S–61A, S–61D, S–61E, and S–61V helicopters with GE CT 58 series engines installed, certificated in any category. Compliance Required within 60 days, unless accomplished previously. To detect an impending Number 5 engine bearing (bearing) failure, which if undetected and not addressed by appropriate crew action may result in an oil leak, severed shaft housing, an uncontained in-flight fire, and a subsequent emergency landing, do the following: (a) Remove engine chip detector, part number (P/N) 205T33P01, and install engine chip detector, part number (P/N) 3049T42P01 or 3018T72P01, in the engine power turbine accessory drive assembly of each engine. Install the chip detector by following the Accomplishment Instructions, paragraph 3.B., of General Electric Aircraft Engines CT58 Service Bulletin Number 72–0195, dated May 1, 2003. Note: This AD neither requires installing GE CT58 engines nor replacing an engine power turbine accessory drive assembly that has a 5⁄16 inch magnetic plug port and applies only to Sikorsky Model S–61A, S–61D, S– 61E, and S–61V helicopters with GE CT58 series engines installed. (b) Install an on-board engine chip detector annunciation system by following the Accomplishment Instructions, paragraphs 3.B. or 3.C., as appropriate for the different manufacturers of the master warning caution panel, of the Sikorsky Aircraft Corporation Alert Service Bulletin No. 61B30–15A, E:\FR\FM\06DEP1.SGM 06DEP1 68768 Federal Register / Vol. 72, No. 234 / Thursday, December 6, 2007 / Proposed Rules Revision A, dated October 20, 2003 (Sikorsky ASB). (c) After doing paragraph (b) of this AD, before further flight, perform a functional test of the engine chip detector system. Repeat the test at intervals not to exceed 150 hours time-in-service. Conduct the tests following the Accomplishment Instructions, paragraph 3.D., of the Sikorsky ASB. (d) Insert the emergency procedures contained in the Accomplishment Instructions, paragraph 3.E., of the Sikorsky ASB for an on-board engine chip detector warning indicator light into the Emergency Procedures section of the applicable Rotorcraft Flight Manual. (e) To request a different method of compliance or a different compliance time for this AD, follow the procedures in 14 CFR 39.19. Contact the Boston Aircraft Certification Office, Engine and Propeller Directorate, FAA, for information about previously approved alternative methods of compliance. (f) This amendment becomes effective on February 4, 2008. Issued in Fort Worth, Texas, on November 27, 2007. Mark R. Schilling, Acting Manager, Rotorcraft Directorate, Aircraft Certification Service. [FR Doc. E7–23604 Filed 12–5–07; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF HOMELAND SECURITY Federal Emergency Management Agency 44 CFR Part 67 [Docket No. FEMA–B–7747] Proposed Flood Elevation Determinations Federal Emergency Management Agency, DHS. ACTION: Proposed rule. sroberts on PROD1PC70 with PROPOSALS AGENCY: SUMMARY: Comments are requested on the proposed Base (1 percent annualchance) Flood Elevations (BFEs) and proposed BFE modifications for the communities listed in the table below. The purpose of this notice is to seek general information and comment regarding the proposed regulatory flood elevations for the reach described by the downstream and upstream locations in the table below. The BFEs and modified BFEs are a part of the floodplain management measures that the community is required either to adopt or show evidence of having in effect in VerDate Aug<31>2005 18:18 Dec 05, 2007 Jkt 214001 order to qualify or remain qualified for participation in the National Flood Insurance Program (NFIP). In addition, these elevations, once finalized, will be used by insurance agents, and others to calculate appropriate flood insurance premium rates for new buildings and the contents in those buildings. DATES: Comments are to be submitted on or before March 5, 2008. ADDRESSES: The corresponding preliminary Flood Insurance Rate Map (FIRM) for the proposed BFEs for each community are available for inspection at the community’s map repository. The respective addresses are listed in the table below. You may submit comments, identified by Docket No. FEMA–B–7747, to William R. Blanton, Jr., Chief, Engineering Management Branch, Mitigation Directorate, Federal Emergency Management Agency, 500 C Street, SW., Washington, DC 20472, (202) 646–3151, or (e-mail) bill.blanton@dhs.gov. FOR FURTHER INFORMATION CONTACT: William R. Blanton, Jr., Chief, Engineering Management Branch, Mitigation Directorate, Federal Emergency Management Agency, 500 C Street, SW., Washington, DC 20472, (202) 646–3151 or.(e-mail) bill.blanton@dhs.gov. SUPPLEMENTARY INFORMATION: The Federal Emergency Management Agency (FEMA) proposes to make determinations of BFEs and modified BFEs for each community listed below, in accordance with section 110 of the Flood Disaster Protection Act of 1973, 42 U.S.C. 4104, and 44 CFR 67.4(a). These proposed BFEs and modified BFEs, together with the floodplain management criteria required by 44 CFR 60.3, are the minimum that are required. They should not be construed to mean that the community must change any existing ordinances that are more stringent in their floodplain management requirements. The community may at any time enact stricter requirements of its own, or pursuant to policies established by other Federal, State, or regional entities. These proposed elevations are used to meet the floodplain management requirements of the NFIP and are also used to calculate the appropriate flood insurance premium rates for new buildings built after these elevations are made final, and for the contents in these buildings. PO 00000 Frm 00006 Fmt 4702 Sfmt 4702 Comments on any aspect of the Flood Insurance Study and FIRM, other than the proposed BFEs, will be considered. A letter acknowledging receipt of any comments will not be sent. Administrative Procedure Act Statement. This matter is not a rulemaking governed by the Administrative Procedure Act (APA), 5 U.S.C. 553. FEMA publishes flood elevation determinations for notice and comment; however, they are governed by the Flood Disaster Protection Act of 1973, 42 U.S.C. 4105, and the National Flood Insurance Act of 1968, 42 U.S.C. 4001 et seq., and do not fall under the APA. National Environmental Policy Act. This proposed rule is categorically excluded from the requirements of 44 CFR part 10, Environmental Consideration. An environmental impact assessment has not been prepared. Regulatory Flexibility Act. As flood elevation determinations are not within the scope of the Regulatory Flexibility Act, 5 U.S.C. 601–612, a regulatory flexibility analysis is not required. Executive Order 12866, Regulatory Planning and Review. This proposed rule is not a significant regulatory action under the criteria of section 3(f) of Executive Order 12866, as amended. Executive Order 13132, Federalism. This proposed rule involves no policies that have federalism implications under Executive Order 13132. Executive Order 12988, Civil Justice Reform. This proposed rule meets the applicable standards of Executive Order 12988. List of Subjects in 44 CFR Part 67 Administrative practice and procedure, Flood insurance, Reporting and recordkeeping requirements. Accordingly, 44 CFR part 67 is proposed to be amended as follows: PART 67—[AMENDED] 1. The authority citation for part 67 continues to read as follows: Authority: 42 U.S.C. 4001 et seq.; Reorganization Plan No. 3 of 1978, 3 CFR, 1978 Comp., p. 329; E.O. 12127, 44 FR 19367, 3 CFR, 1979 Comp., p. 376. § 67.4 [Amended] 2. The tables published under the authority of § 67.4 are proposed to be amended as follows: E:\FR\FM\06DEP1.SGM 06DEP1

Agencies

[Federal Register Volume 72, Number 234 (Thursday, December 6, 2007)]
[Proposed Rules]
[Pages 68766-68768]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E7-23604]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2007-0284; Directorate Identifier 2004-SW-06-AD]
RIN 2120-AA64


Airworthiness Directives; Sikorsky Aircraft Corporation Model S-
61A, S-61D, S-61E, and S-61V Helicopters

AGENCY: Federal Aviation Administration, DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: This document proposes adopting a new airworthiness directive 
(AD) for the specified Sikorsky Aircraft Corporation (Sikorsky) model 
helicopters. The AD would require installing an electric chip detector 
on each engine and an on-board chip detector annunciation system. The 
AD would also require revising the Rotorcraft Flight Manual (RFM) to 
add procedures for crew response to the illumination of an on-board 
chip detector warning light. This AD would also require testing the 
engine chip detector system at specified intervals. This proposal is 
prompted by reports of Number 5 engine bearing failures. Failure of the 
bearing resulted in erratic movement of the high-speed, engine-to-
transmission shaft (shaft), an oil leak, an in-flight fire, and an 
emergency landing. The actions specified by the proposed AD are 
intended to detect an impending bearing failure, which if undetected 
and not addressed by appropriate crew action may result in an oil leak, 
a severed shaft housing, an uncontained in-flight fire, and a 
subsequent emergency landing.

DATES: Comments must be received on or before February 4, 2008.

ADDRESSES: Use one of the following addresses to submit comments on 
this proposed AD:
     Federal eRulemaking Portal: Go to http://
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.
    You may get the service information identified in this proposed AD 
from Sikorsky Aircraft Corporation, Attn: Manager, Commercial Technical 
Support, mailstop s581a, 6900 Main Street, Stratford, Connecticut, 
phone (203) 383-4866, e-mail address tsslibrary@sikorsky.com.
    You may examine the comments to this proposed AD in the AD docket 
on the Internet at http://www.regulations.gov.

FOR FURTHER INFORMATION CONTACT: Kirk Gustafson, Aviation Safety 
Engineer, Boston Aircraft Certification Office, Engine and Propeller 
Directorate, 12 New England Executive Park, Burlington, MA 01803, 
telephone (781) 238-7190, fax (781) 238-7170.

SUPPLEMENTARY INFORMATION: 

Comments Invited

    We invite you to submit any written data, views, or arguments 
regarding this proposed AD. Send your comments to the address listed 
under the caption ADDRESSES. Include the docket number ``FAA-2007-0284, 
Directorate Identifier 2004-SW-06-AD'' at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of the proposed AD. We will 
consider all comments received by the closing date and may amend the 
proposed AD in light of those comments.
    We will post all comments we receive, without change, to http://
www.regulations.gov, including any personal information you provide. We 
will also post a report summarizing each

[[Page 68767]]

substantive verbal contact with FAA personnel concerning this proposed 
rulemaking. Using the search function of our docket Web site, you can 
find and read the comments to any of our dockets, including the name of 
the individual who sent or signed the comment. You may review the DOT's 
complete Privacy Act Statement in the Federal Register published on 
April 11, 2000 (65 FR 19477-78).

Examining the Docket

    You may examine the docket that contains the proposed AD, any 
comments, and other information in person at the Docket Operations 
office between 9 a.m. and 5 p.m., Monday through Friday, except Federal 
holidays. The Docket Operations office (telephone (800) 647-5527) is 
located in Room W12-140 on the ground floor of the West Building at the 
street address stated in the ADDRESSES section. Comments will be 
available in the AD docket shortly after receipt.

Discussion

    This document proposes adopting a new AD for Sikorsky Model S-61A, 
S-61D, S-61E, and S-61V helicopters with GE CT58 series engines. The AD 
would require, within 60 days, installing an electric chip detector for 
the Number 5 bearing in both engines. The AD would also require 
installing an on-board chip detector annunciation system and revising 
the Emergency Procedures section of the RFM to add procedures for crew 
response to the illumination of an on-board chip detector warning 
light. In addition, the AD would require functional testing of the chip 
detector system at specified intervals. This proposal is prompted by 
five reports of bearing failure, which results in an oil leak, uneven 
rotation of the shaft, failure of the shaft housing, which is part of 
the fire containment system, and friction. The heat produced by this 
friction may ignite the leaking oil and result in an uncontained fire. 
The actions specified by the proposed AD are intended to detect an 
impending bearing failure, which if undetected and not addressed by 
appropriate crew action may result in an oil leak, severed shaft 
housing, an uncontained in-flight fire, and a subsequent emergency 
landing.
    The FAA has reviewed Sikorsky Alert Service Bulletin No. 61B30-15A, 
Revision A, dated October 20, 2003 (ASB). The Sikorsky ASB describes 
procedures for installing an engine chip detector system that will 
provide an ``in-cockpit monitoring system'' as a means to detect 
metallic chips if bearing deterioration occurs in either engine. Also, 
the FAA has reviewed General Electric (GE) Aircraft Engines CT58 
Service Bulletin Number 72-0195, dated May 1, 2003 (SB). The GE SB 
describes procedures for installing an alternate electrical chip 
detector (either part number 3018T72P01, cannon-type connector, or 
3049T42P01, stud-type connector) to the power turbine accessory drive 
assembly.
    This unsafe condition is likely to exist or develop on other 
helicopters of the same type design. Therefore, the proposed AD would 
require the following within 60 days:
     Installing an electric chip detector on each engine.
     Installing an on-board chip detector annunciation system.
     Thereafter, before further flight and at specified 
intervals, performing a functional test of the chip detector system.
     Revising the RFM to add emergency procedures for crew 
response to the illumination of an on-board chip detector warning 
light.
    The actions would be required to be done following specified 
portions of the the service bulletins described previously.
    The FAA estimates that this proposed AD would affect 7 helicopters 
of U.S. registry. The proposed actions would take about 81.5 work hours 
per helicopter to install the engine chip detector and the on-board 
cockpit annunciation system. The proposed repetitive tests would affect 
about 7 helicopters and require 6 tests per year and require 1 work 
hour per test for 10 years of operating service. The average labor rate 
is $80 per work hour. Required parts would cost about $1,940 per 
helicopter. Based on these figures, the total cost impact of the 
proposed AD on U.S. operators would be $92,820 for the entire fleet
    The regulations proposed herein 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. Therefore, it 
is determined that this proposal would not have federalism implications 
under Executive Order 13132.
    For the reasons discussed above, I certify that this 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) if promulgated, 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. A copy of the draft 
economic evaluation prepared for this action is contained in the Rules 
Docket. A copy of it may be obtained by contacting the Rules Docket at 
the location provided under the caption ADDRESSES.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Safety.

The Proposed Amendment

    Accordingly, pursuant to the authority delegated to me by the 
Administrator, the Federal Aviation Administration proposes to amend 
part 39 of the Federal Aviation Regulations (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. Section 39.13 is amended by adding a new airworthiness directive 
to read as follows:

Sikorsky Aircraft Corporation: Docket No. FAA-2007-0284; Directorate 
Identifier No. 2004-SW-06-AD.

Applicability

    Model S-61A, S-61D, S-61E, and S-61V helicopters with GE CT 58 
series engines installed, certificated in any category.

Compliance

    Required within 60 days, unless accomplished previously.
    To detect an impending Number 5 engine bearing (bearing) 
failure, which if undetected and not addressed by appropriate crew 
action may result in an oil leak, severed shaft housing, an 
uncontained in-flight fire, and a subsequent emergency landing, do 
the following:
    (a) Remove engine chip detector, part number (P/N) 205T33P01, 
and install engine chip detector, part number (P/N) 3049T42P01 or 
3018T72P01, in the engine power turbine accessory drive assembly of 
each engine. Install the chip detector by following the 
Accomplishment Instructions, paragraph 3.B., of General Electric 
Aircraft Engines CT58 Service Bulletin Number 72-0195, dated May 1, 
2003.

    Note: This AD neither requires installing GE CT58 engines nor 
replacing an engine power turbine accessory drive assembly that has 
a \5/16\ inch magnetic plug port and applies only to Sikorsky Model 
S-61A, S-61D, S-61E, and S-61V helicopters with GE CT58 series 
engines installed.

    (b) Install an on-board engine chip detector annunciation system 
by following the Accomplishment Instructions, paragraphs 3.B. or 
3.C., as appropriate for the different manufacturers of the master 
warning caution panel, of the Sikorsky Aircraft Corporation Alert 
Service Bulletin No. 61B30-15A,

[[Page 68768]]

Revision A, dated October 20, 2003 (Sikorsky ASB).
    (c) After doing paragraph (b) of this AD, before further flight, 
perform a functional test of the engine chip detector system. Repeat 
the test at intervals not to exceed 150 hours time-in-service. 
Conduct the tests following the Accomplishment Instructions, 
paragraph 3.D., of the Sikorsky ASB.
    (d) Insert the emergency procedures contained in the 
Accomplishment Instructions, paragraph 3.E., of the Sikorsky ASB for 
an on-board engine chip detector warning indicator light into the 
Emergency Procedures section of the applicable Rotorcraft Flight 
Manual.
    (e) To request a different method of compliance or a different 
compliance time for this AD, follow the procedures in 14 CFR 39.19. 
Contact the Boston Aircraft Certification Office, Engine and 
Propeller Directorate, FAA, for information about previously 
approved alternative methods of compliance.
    (f) This amendment becomes effective on February 4, 2008.

    Issued in Fort Worth, Texas, on November 27, 2007.
Mark R. Schilling,
Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. E7-23604 Filed 12-5-07; 8:45 am]
BILLING CODE 4910-13-P