[Federal Register Volume 60, Number 30 (Tuesday, February 14, 1995)]
[Rules and Regulations]
[Pages 8283-8284]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 95-3513]
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Rules and Regulations
Federal Register
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Federal Register / Vol. 60, No. 30 / Tuesday, February 14, 1995 /
Rules and Regulations
[[Page 8283]]
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 94-SW-15-AD; Amendment 39-9148; AD 95-03-12]
Airworthiness Directives; Schweizer Aircraft Corporation and
Hughes Helicopters, Inc. Model 269A, 269A-1, 269B, 269C, and TH-55A
Series Helicopters
AGENCY: Federal Aviation Administration, DOT.
ACTION: Final rule; request for comments.
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SUMMARY: This amendment supersedes an existing airworthiness directive
(AD), applicable to Schweizer Aircraft Corporation and Hughes
Helicopters, Inc. Model 269A, 269A-1, 269B, 269C, and TH-55A series
helicopters, that currently requires an initial and repetitive visual
inspection of the clutch control spring assembly for component wear and
replacement of affected unairworthy parts. This amendment requires the
same initial and repetitive visual inspection and replacements required
by the existing Priority Letter AD, but references a revised service
bulletin and provides replacement procedures for the aluminum spring
retainer thermofit tube (plastic sleeve). This amendment is prompted by
a recent accident involving a Model 269C helicopter that reportedly
lost engine drive power at 100 feet above ground level (AGL) with a
resulting unsuccessful autorotative landing, and the manufacturer's
issuance of revised service information that provides more detailed
instructions for replacement of two components of the belt drive clutch
control assembly. The actions specified by this AD are intended to
prevent failure of the aluminum spring retainer, loss of power to the
rotor drive system, and a subsequent forced landing.
DATES: Effective March 1, 1995.
The incorporation by reference of certain publications listed in
the regulations was approved previously by the Director of the Federal
Register as of September 1, 1994 (59 FR 38354, July 28, 1994).
Comments for inclusion in the Rules Docket must be received on or
before April 17, 1995.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Office of the Assistant Chief Counsel, Attention:
Rules Docket No. 94-SW-15-AD, 2601 Meacham Blvd., Room 663, Fort Worth,
Texas 76137.
The service information referenced in this AD may be obtained from
Schweizer Aircraft Corporation, P.O. Box 147, Elmira, New York 14902.
This information may be examined at the FAA, Office of the Assistant
Chief Counsel, 2601 Meacham Blvd., Room 663, Fort Worth, Texas; or at
the Office of the Federal Register, 800 North Capitol Street NW., suite
700, Washington, DC.
FOR FURTHER INFORMATION CONTACT: Mr. Raymond Reinhardt, Aerospace
Engineer, New York Aircraft Certification Office, FAA, New England
Region, 10 Fifth Street, Valley Stream, New York 11581, telephone (516)
256-7532; fax (516) 568-2716.
SUPPLEMENTARY INFORMATION: On March 4, 1993, the FAA issued Priority
Letter AD 93-03-01, to require an initial and repetitive visual
inspection of the clutch control spring assembly (assembly) for
component wear and security, and replacement of affected unairworthy
parts. That action was prompted by an accident involving a Schweizer
Aircraft Corporation Model 269C helicopter. Reportedly, the helicopter
lost engine drive power and was unsuccessful in performing a forced
landing from 100 feet above ground level (AGL). A subsequent
investigation revealed that the assembly had failed, and that the
aluminum spring retainer, part number (P/N) 269A5483-7, of the failed
assembly had excessive wear. That condition, if not corrected, could
result in failure of the aluminum spring retainer, loss of power to the
rotor drive system, and a subsequent forced landing.
Since the issuance of that AD, the manufacturer has issued a
revised service bulletin, Schweizer Service Bulletin (SB) B-256.2,
dated June 11, 1993, that describes procedures for an initial and
repetitive inspection for component wear of the assembly in greater
detail than the previously-issued service bulletin, and describes
procedures for further inspections if disassembly is necessary. It also
describes procedures for replacement of the aluminum spring retainer,
P/N 269A5452, P/N 269A5452-3, P/N 269A5452-5, or P/N 269A5483-7, and
the plastic sleeve, P/N 269A5590-101, which was not described in SB B-
256.1, dated January 20, 1993, the SB cited in AD 93-03-01.
Since an unsafe condition has been identified that is likely to
exist or develop on other Schweizer Aircraft Corporation and Hughes
Helicopters, Inc. Model 269A, 269A-1, 269B, 269C, and TH-55A
helicopters of the same type design, this AD supersedes AD 93-03-01 to
require an initial and repetitive visual inspection of the assembly for
component wear; and, if any worn or unairworthy parts are found,
disassembly, further inspections, and replacement of any unairworthy
parts. The actions are required to be accomplished in accordance with
SB B-256.2, dated June 11, 1993, described previously. The assembly
puts tension on the belt drive between the transmission and the main
rotor. If the assembly fails and there is no tension on the belt, the
transmission will not turn the main rotor. Due to the criticalness of
the clutch control assembly, and a short compliance time, this rule
must be issued immediately to correct an unsafe condition in aircraft.
Since a situation exists that requires the immediate adoption of
this regulation, it is found that notice and opportunity for prior
public comment hereon are impracticable, and that good cause exists for
making this amendment effective in less than 30 days.
Comments Invited
Although this action is in the form of a final rule that involves
requirements affecting flight safety and, thus, was not preceded by
notice and an opportunity for public comment, comments are invited on
this rule. Interested persons are invited to comment on this rule by
submitting such written data, views, or [[Page 8284]] arguments as they
may desire. Communications should identify the Rules Docket number and
be submitted in triplicate to the address specified under the caption
ADDRESSES. All communications received on or before the closing date
for comments will be considered, and this rule may be amended in light
of the comments received. Factual information that supports the
commenter's ideas and suggestions is extremely helpful in evaluating
the effectiveness of the AD action and determining whether additional
rulemaking action would be needed.
Comments are specifically invited on the overall regulatory,
economic, environmental, and energy aspects of the rule that might
suggest a need to modify the 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 that
summarizes each FAA-public contact concerned with the substance of this
AD will be filed in the Rules Docket.
Commenters wishing the FAA to acknowledge receipt of their comments
submitted in response to this rule must submit a self-addressed,
stamped postcard on which the following statement is made: ``Comments
to Docket No. 94-SW-15-AD.'' The postcard will be date stamped and
returned to the commenter.
The regulations adopted herein will not have substantial direct
effects 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, in
accordance with Executive Order 12612, it is determined that this final
rule does not have sufficient federalism implications to warrant the
preparation of a Federalism Assessment.
The FAA has determined that this regulation is an emergency
regulation that must be issued immediately to correct an unsafe
condition in aircraft, and that it is not a ``significant regulatory
action'' under Executive Order 12866. It has been determined further
that this action involves an emergency regulation under DOT Regulatory
Policies and Procedures (44 FR 11034, February 26, 1979). If it is
determined that this emergency regulation otherwise would be
significant under DOT Regulatory Policies and Procedures, a final
regulatory evaluation will be prepared and placed in the Rules Docket.
A copy of it, if filed, 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
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
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. App. 1354(a), 1421 and 1423; 49 U.S.C.
106(g); and 14 CFR 11.89.
Sec. 39.13 [Amended]
2. Section 39.13 is amended by adding a new airworthiness directive
(AD), Amendment 39-9148, to read as follows:
95-03-12 Schweizer Aircraft Corporation and Hughes Helicopters,
Inc.: Amendment 39-9148. Docket No. 94-SW-15-AD. Supersedes Priority
Letter AD 93-03-01, issued on March 4, 1993.
Applicability: Model 269A, 269A-1, 269B, 269C, and TH-55A series
helicopters, with aluminum spring retainer, part number (P/N)
269A5452, P/N 269A5452-3, P/N 269A5452-5, or P/N 269A5483-7,
installed, certificated in any category.
Compliance: Required as indicated, unless accomplished
previously.
To prevent failure of the aluminum spring retainer, loss of
power to the rotor drive system, and a subsequent forced landing,
accomplish the following:
(a) Within the next 5 hours time-in-service after the effective
date of this AD, and thereafter at intervals not to exceed 100 hours
time-in-service from the last inspection, visually inspect the
clutch control spring assembly for component wear in accordance with
the provisions of Part I, paragraph a(2) of Schweizer Service
Bulletin (SB) B-256.2, dated June 11, 1993.
(b) If worn parts are found during the inspections accomplished
in accordance with paragraph (a) of this AD, before the next flight,
disassemble and inspect the clutch control spring assembly and
replace parts found to be unairworthy with airworthy parts in
accordance with Part I, paragraph b. of SB B-256.2, dated June 11,
1993.
(c) An alternative method of compliance or adjustment of the
compliance time that provides an acceptable level of safety may be
used when approved by the Manager, New York Aircraft Certification
Office, FAA. Operators shall submit their requests through an FAA
Principal Maintenance Inspector, who may concur or comment and then
send it to the Manager, New York Aircraft Certification Office.
Note: Information concerning the existence of approved
alternative methods of compliance with this AD, if any, may be
obtained from the New York Aircraft Certification Office.
(d) Special flight permits may be issued in accordance with
sections 21.197 and 21.199 of the Federal Aviation Regulations (14
CFR 21.197 and 21.199) to operate the helicopter to a location where
the inspection requirements of this AD can be accomplished.
(e) The inspections and replacement, if necessary, shall be done
in accordance with SB B-256.2, dated June 11, 1993. This
incorporation by reference was approved previously by the Director
of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR
part 51 as of September 1, 1994 (59 FR 38354, July 28, 1994). Copies
may be obtained from Schweizer Aircraft Corporation, P.O. Box 147,
Elmira, New York 14902. Copies may be inspected at the FAA, Office
of the Assistant Chief Counsel, 2601 Meacham Blvd., Room 663, Fort
Worth, Texas; or at the Office of the Federal Register, 800 North
Capitol Street, NW., suite 700, Washington, DC.
(f) This amendment becomes effective on March 1, 1995.
Issued in Fort Worth, Texas, on February 6, 1995.
Eric Bries,
Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 95-3513 Filed 2-13-95; 8:45 am]
BILLING CODE 4910-13-P
