Document ID: FAA-2007-0284-0001
Agency: faa
Document Type: Rule
Title: Airworthiness Directives; Sikorsky Aircraft Corporation Model S- 61A, S-61D, S-61E, and S-61V Helicopters
Posted Date: 2007-12-06T05:00Z

[Federal Register: December 6, 2007 (Volume 72, Number 234)]
[Proposed Rules]               
[Page 68766-68768]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr06de07-12]                         

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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).

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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]

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