Document ID: FAA-2007-0284-0006
Agency: faa
Document Type: Rule
Title: Airworthiness Directives; Sikorsky Aircraft Corporation Model S- 61A, S-61D, S-61E, and S-61V Helicopters
Posted Date: 2008-05-08T04:00Z

[Federal Register: May 8, 2008 (Volume 73, Number 90)]
[Rules and Regulations]               
[Page 25961-25962]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr08my08-1]                         

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[[Page 25961]]

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2007-0284; Directorate Identifier 2004-SW-06-AD; 
Amendment 39-15510; AD 2008-10-04]
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: Final rule.

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SUMMARY: This amendment adopts a new airworthiness directive (AD) for 
the specified Sikorsky Aircraft Corporation (Sikorsky) model 
helicopters that requires installing an electric chip detector on each 
engine and an on-board chip detector annunciation system. The AD also 
requires 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 also requires testing the engine chip detector 
system at specified intervals. This amendment 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 this 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: Effective June 12, 2008.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of June 12, 2008.

ADDRESSES: You may get the service information identified in this 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.
    Examining the Docket: You may examine the docket that contains this 
AD, any comments, and other information on the Internet at http://
www.regulations.gov or at the Docket Operations office, West Building 
Ground Floor, Room W12-140, 1200 New Jersey Avenue, SE., Washington, 
DC.

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: A proposal to amend 14 CFR part 39 to 
include an AD for the specified model helicopters was published in the 
Federal Register on December 6, 2007 (72 FR 68766). That action 
proposed to require, within 60 days, installing an electric chip 
detector for the Number 5 bearing in both engines on the specified 
Sikorsky model helicopters with GE CT58 series engines. That action 
also proposed 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, functional testing of the chip 
detector system at specified intervals was proposed.
    We have 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. We 
have also 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 (P/N) 3018T72P01, cannon-type connector, or 3049T42P01, 
stud-type connector) to the power turbine accessory drive assembly.
    Interested persons have been afforded an opportunity to participate 
in the making of this amendment. Due consideration has been given to 
the two comments made by one commenter about two typographical errors 
in the Notice of proposed rulemaking (NPRM). In paragraph (a) of the 
NPRM, an engine chip detector is incorrectly shown as P/N 205T33P01 
rather than P/N 2005T33P01. In paragraph (d), we referenced paragraph 
3.F. of the Sikorsky ASB rather than 3.E.
    We concur with the commenter and have changed the engine chip 
detector P/N from 205T33P01 to 2005T33P01 and have changed the 
referenced Sikorsky ASB paragraph from 3.E. to 3.F. in this AD.
    After careful review of the available data, including the comments 
noted above, we determined that air safety and the public interest 
require the adoption of the rule with the changes described previously. 
These changes will neither increase the economic burden on any operator 
nor increase the scope of the AD.
    This AD will affect 7 helicopters of U.S. registry, and it will 
take about 81.5 work hours per helicopter to install the engine chip 
detector and the on-board cockpit annunciation system. The repetitive 
tests will affect about 7 helicopters and require 6 tests per year and 
1 work hour per test for 10 years of operating service. The average 
labor rate is $80 per work hour. Required parts will cost about $1,940 
per helicopter. Based on these figures, we estimate the total cost 
impact of the AD on U.S. operators to be $92,820 for the entire fleet.

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 the 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

[[Page 25962]]

    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 an economic evaluation of the estimated costs to comply 
with this AD. See the AD docket to examine the economic evaluation.

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.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

Adoption of the Amendment

0
Accordingly, pursuant to the authority delegated to me by the 
Administrator, the Federal Aviation Administration amends part 39 of 
the Federal Aviation Regulations (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. Section 39.13 is amended by adding a new airworthiness directive to 
read as follows:

2008-10-04 Sikorsky Aircraft Corporation: Amendment 39-15510. Docket 
No. FAA-2007-0284; Directorate Identifier 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) 2005T33P01, 
and install engine chip detector, 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, 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.F., 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 Manager, Boston Aircraft Certification Office, Engine 
and Propeller Directorate, FAA, ATTN: Kirk Gustafson, Aviation 
Safety Engineer, 12 New England Executive Park, Burlington, MA 
01803, telephone (781) 238-7190, fax (781) 238-7170, for information 
about previously approved alternative methods of compliance.
    (f) Installing an engine chip detector shall be done by 
following the specified portions of General Electric Aircraft 
Engines CT58 Service Bulletin Number 72-0195, dated May 1, 2003. 
Installing an on-board engine chip detector annunciation system and 
performing a functional test of the engine chip detector system 
shall be done by following the specified portions of Sikorsky 
Aircraft Corporation Alert Service Bulletin No. 61B30-15A, Revision 
A, dated October 20, 2003. The Director of the Federal Register 
approved this incorporation by reference in accordance with 5 U.S.C. 
552(a) and 1 CFR part 51. Copies may be obtained 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. Copies may 
be inspected at the FAA, Office of the Regional Counsel, Southwest 
Region, 2601 Meacham Blvd., Room 663, Fort Worth, Texas, or at the 
National Archives and Records Administration (NARA). For information 
on the availability of this material at NARA, call 202-741-6030, or 
go to: http://www.archives.gov/federal_register/code_of_federal_
regulations/ibr_locations.html.
    (g) This amendment becomes effective on June 12, 2008.

    Issued in Fort Worth, Texas, on April 23, 2008.
David A. Downey,
Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. E8-9787 Filed 5-7-08; 8:45 am]

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