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.

Rules and Regulations Federal Register

8283

Vol. 60, No. 30

Tuesday, February 14, 1995

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
8284 Federal Register / Vol. 60, No. 30 / Tuesday, February 14, 1995 / Rules and Regulations

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.

§ 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

14 CFR Part 39

[Docket No. 94–SW–21–AD; Amendment

39–9147; AD 95–03–11]

Airworthiness Directives; McDonnell

Douglas Helicopter Systems and

Hughes Helicopters, Inc. Model 369,

OH–6A, and YOH–6A Series

Helicopters

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule; request for

comments.

SUMMARY: This amendment adopts a

new airworthiness directive (AD) that is

applicable to McDonnell Douglas

Helicopter Systems and Hughes

Helicopters, Inc. Model 369, OH–6A,

and YOH–6A series helicopters. This

action requires initial and repetitive

inspections of the tail rotor blade

abrasion strip (abrasion strip),

installation of stainless steel abrasion

tape over the inboard end of the

abrasion strip, and as a terminating

action, installation of a tail rotor blade

with a new-design abrasion strip. This

amendment is prompted by several

incidents of riveted abrasion strips

debonding and separating during flight,

resulting in severe out-of-balance

conditions and subsequent separation of