[Federal Register: August 2, 2004 (Volume 69, Number 147)]
[Rules and Regulations]
[Page 46095-46096]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr02au04-1]
========================================================================
Rules and Regulations
Federal Register
________________________________________________________________________
This section of the FEDERAL REGISTER contains regulatory documents
having general applicability and legal effect, most of which are keyed
to and codified in the Code of Federal Regulations, which is published
under 50 titles pursuant to 44 U.S.C. 1510.
The Code of Federal Regulations is sold by the Superintendent of Documents.
Prices of new books are listed in the first FEDERAL REGISTER issue of each
week.
========================================================================
[[Page 46095]]
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 2003-SW-35-AD; Amendment 39-13756; AD 2004-15-22]
RIN 2120-AA64
Airworthiness Directives; Sikorsky Aircraft Corporation Model S-
61L, S-61N, S-61-NM, and S-61R Helicopters
AGENCY: Federal Aviation Administration, DOT.
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: This amendment adopts a new airworthiness directive (AD) for
the specified Sikorsky Aircraft Corporation (Sikorsky) model
helicopters that requires installing a Number 5 bearing chip detector
in each engine, installing an on-board chip detector annunciation
system, and revising the Rotorcraft Flight Manual (RFM) to add
procedures for crew response to an on-board chip detector annunciation.
This amendment is prompted by reports of the failure of the engine's
Number 5 bearing that resulted in erratic movement of the high-speed
engine-to-transmission shaft (shaft), oil leakage, an in-flight fire
and an emergency landing. The actions specified by this AD are intended
to detect an impending engine bearing (bearing) failure, which, if
undetected and not addressed by appropriate crew action, may result in
oil leakage, severing of the shaft housing, an uncontained in-flight
fire, and a subsequent emergency landing.
DATES: Effective September 7, 2004.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of September 7, 2004.
ADDRESSES: The service information referenced in this AD may be
obtained from Sikorsky Aircraft Corporation, Attn: Manager, Commercial
Tech Support, 6900 Main Street, Stratford, Connecticut 06614, phone
(203) 386-3001, fax (203) 386-5983; and from GE Aircraft Engines
Customer Support Center, M/D 285, 1 Neumann Way, Evendale, OH 45215,
telephone (513) 552-3272; fax (513) 552-3329, email GEAE.csc@ae.ge.com.
This information may be examined 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
.
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 November 24, 2003 (68 FR 65857). That action
proposed to require, within 60 days, installing a chip detector for the
No. 5 bearing, installing an on-board chip detector annunciation
system, and revising the RFM to add procedures for crew response to an
on-board chip detector annunciation.
Prior to issuing the proposal, Sikorsky had issued Alert Service
Bulletin (ASB) No. 61B30-15, dated June 9, 2003, which describes
procedures for installing an on-board cockpit annunciation system that
interfaces with the engine chip detectors, as a means to detect
metallic chips if deterioration of the Number 5 bearing in either
engine occurs. The FAA proposed to incorporate portions of that service
information into the AD. Also, General Electric Aircraft Engines has
issued GE Aircraft Engines CT58 Service Bulletin Number 72-0195, dated
May 1, 2003, which describes procedures for installing an electrical
chip detector (either part number 3018T72P01 or 3049T42P01) in the CT58
engine power turbine accessory drive assembly. Since issuing the
proposal, Sikorsky has issued ASB No. 61B30-15, Revision A, dated
October 20, 2003, which specifies the same procedure, but revises a
part number, corrects the drawing, and clarifies the location for the
warning light.
Interested persons have been afforded an opportunity to participate
in the making of this amendment. Due consideration has been given to
the comments received.
The one commenter, the manufacturer, submitted several comments
regarding the NPRM. Because Sikorsky has issued a revised ASB to
correct minor errors including a part number, a drawing, and
installation instructions, they suggest the AD should reference the
revised ASB rather than the previously issued ASB. They also suggest
that we change the AD to allow use of later, FAA-approved revisions of
the ASB to accomplish the AD.
The FAA partially agrees. The FAA will not include language that
would allow compliance using ``later FAA-approved revisions'' of an
ASB; however, individual owners and operators may request an alternate
method of compliance (AMOC) that would allow use of future revisions of
the ASB to comply with the AD. Regarding the revision to the current
ASB, the FAA agrees the AD should reference the most recent, correct
ASB, and the AD reflects that change.
The same commenter proposes that we change the unsafe condition
language in the Summary and Discussion sections of the AD. The
commenter states, ``The installation of the chip detector and warning
light will not PREVENT a bearing failure as stated. Its purpose is
solely for the detection of a deteriorating bearing and to notify the
crew such that appropriate action can be taken.''
The FAA agrees that the chip detector and warning light do not
prevent a bearing failure, in that the system inherently depends on
early stages of bearing deterioration to trigger the warning system.
However, the unsafe condition results from advanced stages of bearing
deterioration (complete bearing failure), and this condition may be
prevented by providing the crew with emergency procedures that include,
if practical, shutting down the affected engine and transitioning to
single engine flight when the bearing
[[Page 46096]]
experiences these early stages of deterioration.
The same commenter states the cost impact estimate stated in the
NPRM is inaccurate. The commenter states the cost of parts is $2,600,
resulting in a cost-per-helicopter of $7,897, or a total fleet cost of
$165,847.
The FAA agrees with the revised costs and we have changed the
economic analysis accordingly.
After careful review of the available data, including the comments
noted above, the FAA has determined that air safety and the public
interest require the adoption of the rule with the changes described
previously. The FAA has determined that these changes will not increase
the scope of the AD. Also, we have determined that an increase in
estimated costs of $659 per helicopter does not constitute a
substantial increase of the economic burden on any operator.
The FAA estimates that this AD will affect 21 helicopters of U.S.
registry, and the required actions will take approximately 81.5 work
hours per helicopter to accomplish at an average labor rate of $65 per
work hour. Required parts will cost approximately $2,600 per
helicopter. Based on these figures, the total estimated cost impact of
the AD on U.S. operators is $7,897 per helicopter, or $165,847 for the
entire fleet.
The regulations adopted herein 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. Therefore, it
is determined that this final rule does not have federalism
implications under Executive Order 13132.
For the reasons discussed above, I certify that this action (1) is
not a ``significant regulatory action'' under Executive Order 12866;
(2) is not a ``significant rule'' under 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. A final evaluation has been prepared for this action
and it is contained in the Rules Docket. A copy of it may be obtained
from the Rules Docket at the location provided under the caption
ADDRESSES.
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:
2004-15-22 Sikorsky Aircraft Corporation: Amendment 39-13756. Docket
No. 2003-SW-35-AD.
Applicability: Model S-61L, S-61N, S-61-NM, and S-61R
helicopters, certificated in any category.
Compliance: Required within 60 days, unless accomplished
previously.
To detect an impending engine bearing (bearing) failure, which,
if undetected and not addressed by appropriate crew action, may
result in oil leakage, severing of the shaft housing, an uncontained
in-flight fire, and a subsequent emergency landing, accomplish the
following:
(a) Install an engine chip detector, part number 3049T42P01 or
3018T72P01, in the engine power turbine accessory drive assembly
using the Accomplishment Instructions, paragraphs 3.A. and 3.B., in
General Electric Aircraft Engines CT58 Service Bulletin Number 72-
0195, dated May 1, 2003.
(b) Install an on-board engine chip detector annunciation system
using Sikorsky Aircraft Corporation Alert Service Bulletin No.
61B30-15, Revision A. dated October 20, 2003 (ASB). For helicopters
with a master warning caution panel (MWCP) manufactured by United
Controls or Sundstrand Data, install in accordance with paragraph
3.B. of the ASB. For helicopters with a MWCP manufactured by Grimes
Mfg., install in accordance with paragraph 3.C. of the ASB.
(c) After accomplishing paragraph (b) of this AD, before further
flight, perform a functional test of the engine chip detector system
and repeat the functional test at intervals not to exceed 150 hours
TIS using the Accomplishment Instructions, paragraph 3.D., of the
ASB.
(d) Insert the emergency procedures for an on-board engine chip
detector warning light illumination into the Emergency Procedures
section of the applicable Rotorcraft Flight Manual using the
Accomplishment Instructions, paragraph 3.E., of the ASB.
(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) The actions, including installations, testing, and inserting
information into the Rotorcraft Flight Manual, shall be done in
accordance with General Electric Aircraft Engines CT58 Service
Bulletin Number 72-0195, dated May 1, 2003; and Sikorsky Aircraft
Corporation Alert Service Bulletin No. 61B30-15, 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 Tech Support, 6900 Main
Street, Stratford, Connecticut 06614, phone (203) 386-3001, fax
(203) 386-5983; and from GE Aircraft Engines Customer Support
Center, M/D 285, 1 Neumann Way, Evendale, OH 45215, telephone (513)
552-3272; fax (513) 552-3329, e-mail GEAE.csc@ae.ge.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 September 7, 2004.
Issued in Fort Worth, Texas, on July 22, 2004.
David A. Downey,
Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 04-17370 Filed 7-30-04; 8:45 am]
BILLING CODE 4910-13-P