[Federal Register Volume 68, Number 226 (Monday, November 24, 2003)]
[Proposed Rules]
[Pages 65857-65859]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 03-29219]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2003-SW-35-AD]
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: 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 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 proposal 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 the 
proposed AD are intended to detect an impending engine bearing 
(bearing) failure and prevent a bearing failure, oil leakage, severing 
of the shaft housing, an uncontained in-flight fire, and a subsequent 
immediate emergency landing.

DATES: Comments must be received on or before January 23, 2004.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Office of the Regional Counsel, Southwest Region, 
Attention: Rules Docket No. 2003-SW-35-AD, 2601 Meacham Blvd., Room 
663, Fort Worth, Texas 76137. You may also send comments electronically 
to the Rules Docket at the following address: [email protected]. 
Comments may be inspected at the Office of the Regional Counsel between 
9 a.m. and 3 p.m., Monday through Friday, except Federal holidays.

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:

[[Page 65858]]

Comments Invited

    Interested persons are invited to participate in the making of the 
proposed rule by submitting such written data, views, or arguments as 
they may desire. Communications should identify the Rules Docket number 
and be submitted in triplicate to the address specified above. All 
communications received on or before the closing date for comments will 
be considered before taking action on the proposed rule. The proposals 
contained in this document may be changed in light of the comments 
received.
    Comments are specifically invited on the overall regulatory, 
economic, environmental, and energy aspects of the proposed rule. All 
comments submitted will be available, both before and after the closing 
date for comments, in the Rules Docket for examination by interested 
persons. A report summarizing each FAA-public contact concerned with 
the substance of this proposal will be filed in the Rules Docket.
    Commenters wishing the FAA to acknowledge receipt of their mailed 
comments submitted in response to this proposal must submit a self-
addressed, stamped postcard on which the following statement is made: 
``Comments to Docket No. 2003-SW-35-AD.'' The postcard will be date 
stamped and returned to the commenter.

Discussion

    This document proposes adopting a new AD for Sikorsky Model S-61L, 
S-61N, S-61-NM, and S-61R helicopters. The AD would require, within 60 
days, installing a chip detector for the Number 5 engine bearing, 
installing an on-board chip detector annunciation system, and providing 
in the Emergency Procedures section of the RFM the emergency procedures 
for the flight crew to follow in the event that the engine chip 
detector warning light comes on during flight operations. This proposal 
is prompted by at least five similar events that varied in severity, in 
which the Number 5 bearing on the high-speed shaft connecting the 
engine to the transmission failed. Failure of this engine bearing 
resulted in uneven rotation of the shaft, leakage of engine oil that 
may be ignited by friction-induced heat, failure of the shaft housing, 
which is part of the fire containment system, and an uncontained fire. 
In the most severe incident, the fire consumed the aircraft after a 
successful emergency landing. The actions specified by the proposed AD 
are intended to detect an impending bearing failure and to prevent a 
bearing failure, oil leakage, severing of the shaft housing, an 
uncontained in-flight fire, and a subsequent immediate emergency 
landing.
    The FAA has reviewed General Electric Aircraft Engine 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. The FAA has also reviewed Sikorsky Aircraft Corporation 
Alert Service Bulletin No. 61B30-15, dated June 9, 2003, which 
describes procedures for installing an on-board cockpit annunciation 
system that interfaces with these engine chip detectors, as a means to 
detect metallic chips in the event of deterioration of the Number 5 
bearing in either engine.
    This unsafe condition is likely to exist or develop on other 
helicopters of the same type design. Therefore, the proposed AD would 
require, within 60 days, installing a chip detector for the No. 5 
bearing, installing an on-board chip detector annunication system, and 
revising the RFM to add procedures for crew response to an on-board 
chip detector annunciation. The actions would be required to be 
accomplished in accordance with the two service bulletins described 
previously.
    On July 10, 2002, the FAA issued a new version of 14 CFR part 39 
(67 FR 47997, July 22, 2002), which governs the FAA's AD system. The 
regulation now includes material that relates to altered products, 
special flight permits, and alternative methods of compliance. Because 
we have now included this material in part 39, we no longer need to 
include it in each individual AD.
    The FAA estimates that this proposed AD would affect 21 helicopters 
of U.S. registry, and the proposed actions would take approximately 
81.5 work hours per helicopter to accomplish at an average labor rate 
of $65 per work hour. Required parts would cost approximately $1,940 
per helicopter. Based on these figures, the total cost impact of the 
proposed AD on U.S. operators would be $7,238 per helicopter, or 
$151,998 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 
regulatory 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. 2003-SW-35-AD.

    Applicability: Model S-61L, S-61N, S-61-NM, and S-61R 
helicopters.
    Compliance: Required within 60 days, unless accomplished 
previously.
    To detect impending engine bearing (bearing) failure and prevent 
a bearing failure, oil leakage, severing of the shaft housing, an 
uncontained in-flight fire, and a subsequent immediate emergency 
landing, accomplish the following:
    (a) Install an engine chip detector, part number 3049T42P01 or 
3018T72P01, in the engine power turbine accessory drive assembly in 
accordance with 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 
in accordance with Sikorsky Aircraft Corporation Alert Service 
Bulletin No. 61B30-15, dated June 9, 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 an MWCP

[[Page 65859]]

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 in accordance with 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 in accordance 
with 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.

    Issued in Fort Worth, Texas, on November 17, 2003.
David A. Downey,
Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 03-29219 Filed 11-21-03; 8:45 am]
BILLING CODE 4910-13-P