[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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Rules and Regulations
Federal Register
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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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