[Federal Register Volume 69, Number 147 (Monday, August 2, 2004)]
[Rules and Regulations]
[Pages 46095-46096]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 04-17370]



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  Federal Register / Vol. 69, No. 147 / Monday, August 2, 2004 / Rules 
and Regulations  

[[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 [email protected]. 
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 [email protected]. 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]
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