Airworthiness Directives; Schweizer Aircraft Corporation and Hughes Helicopters, Inc. Model 269A, 269A-1, 269B, 269C, and TH-55A Series Helicopters

[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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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.

-----------------------------------------------------------------------

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

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