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
Federal Register / Vol. 60, No. 30 / Tuesday, February 14, 1995 / Rules and Regulations 8285

the tail rotor gearbox from the

helicopter. The actions specified in this

AD are intended to prevent loss of the

abrasion strip, separation of a tail rotor

blade, separation of the tail rotor

gearbox, and subsequent loss of control

of the helicopter.

DATES: Effective March 1, 1995.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of March 1,

1995.

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–21–AD, 2601

Meacham Blvd., Room 663, Fort Worth,

Texas 76137.

The service information referenced in

this AD may be obtained from

McDonnell Douglas Helicopter Systems,

Technical Publications, Bldg. 530/B111,

5000 E. McDowell Road, Mesa, Arizona

85205–9797. 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.

Brent Bandley, Aerospace Engineer, Los

Angeles Aircraft Certification Office,

FAA, Transport Airplane Directorate,

3960 Paramount Blvd., Lakewood,

California 90712, telephone (310) 627–

5237, fax (310) 627–5210.

SUPPLEMENTARY INFORMATION: On August

30, 1994, the FAA issued AD 94–18–08,

Amendment 39–9021 (59 FR 46163,

September 7, 1994) to require

installation of abrasion strip rivets

(rivets) within 25 hours time-in-service

or 7 calendar days, whichever occurs

first, on certain tail rotor blades. Also

required are owner/operator checks of

the abrasion strips for evidence of

debonding along the abrasion strip bond

line before the first flight of each day;

a dye-penetrant and tap-test inspection

to ensure the abrasion strip is secure if

the owner/operator checks reveal

evidence of debonding; and, if

debonding is confirmed, replacement of

the tail rotor blade with an airworthy

blade that has been modified with the

installation of rivets. Since the issuance

of that AD, there have been several

incidents of riveted tail rotor blade

abrasion strips debonding and

separating during flight, resulting in

severe out-of-balance conditions, and

subsequent separation of the tail rotor

gearbox from the helicopter. Based on

these incidents, the FAA has

determined that riveting the abrasion

strips alone does not create a fail-safe

design. An analysis has shown that the

debonding starts at the inboard end of

the abrasion strip. This condition, if not

corrected, could result in loss of the

abrasion strip, separation of a tail rotor

blade, separation of the tail rotor

gearbox, and subsequent loss of control

of the helicopter. Therefore, installation

of stainless steel abrasion tape over the

inboard end of the abrasion strips

within 25 hours time-in-service (TIS) or

90 calendar days, whichever occurs

first, and thereafter, at intervals not to

exceed 100 hours TIS, is necessary to

prevent debonding of the abrasion strip

from the tail rotor and to ensure the

integrity of the helicopter. However,

owners and operators must install

abrasion strip rivets as required by AD

94–18–08 prior to installing the

stainless steel abrasion tape.

Additionally, within 1,000 hours TIS,

installation of a tail rotor blade with a

new-design abrasion strip is required.

The FAA has reviewed McDonnell

Douglas Helicopter Systems Service

Information Notice HN–238, DN–187,

EN–80, FN–66, dated October 26, 1994,

which describes procedures for

inspection of the abrasion strips for

separation or voids and replacement if

separation or voids are evident;

installation of 304 stainless steel

abrasion tape (.0027-inch thick) over the

inboard end of the abrasion strips; and

replacement of existing tail rotor blades

with tail rotor blades equipped with

new-design abrasion strips.

Since an unsafe condition has been

identified that is likely to exist or

develop on other McDonnell Douglas

Helicopter Systems and Hughes

Helicopters, Inc. Model 369, OH–6A,

and YOH–6A series helicopters of the

same type design, this AD is being

issued to prevent loss of the abrasion

strip, separation of a tail rotor blade,

separation of the tail rotor gearbox, and

subsequent loss of control of the

helicopter. This AD requires initial and

repetitive inspections of the 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. Due to

the criticality of the abrasion strip and

maintaining a balanced tail rotor

system, and the short compliance time

for installation of the stainless steel

abrasion tape, this rule must be issued

immediately to correct an unsafe

condition. The actions are required to be

accomplished in accordance with the

service bulletin described previously.

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

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–21–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
8286 Federal Register / Vol. 60, No. 30 / Tuesday, February 14, 1995 / Rules and Regulations

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 to

read as follows:

95–03–11 McDonnell Douglas Helicopter

Systems and Hughes Helicopters, Inc.:

Amendment 39–9147. Docket No. 94–

SW–21–AD.

Applicability: Model 369, OH–6A, and

YOH–6A series helicopters, with tail rotor

blade assemblies, part number (P/N)

369A1613–7, 369A1613–503, 369A1613–505,

369A1613–509, 369D21606, 369D21606–509,

369D21613–11, 369D21613–31, 369D21613–

41, 369D21613–51, 369D21613–71,

369D21615, 369D21615–21, 369D21615–41,

or 421–088, installed, certificated in any

category.

Compliance: Required as indicated, unless

accomplished previously.

To prevent loss of the abrasion strip,

separation of a tail rotor blade, separation of

the tail rotor gearbox, and subsequent loss of

control of the helicopter, accomplish the

following:

(a) Within 25 hours time-in-service (TIS) or

90 calendar days, whichever occurs first, and

thereafter, at intervals not to exceed 100

hours TIS, inspect the tail rotor blade

abrasion strip for debonding from the tail

rotor blade. Prior to conducting the repetitive

inspections, remove any abrasion tape from

the tail rotor blade.

(1) If the inspection reveals debonding,

replace the tail rotor blade with an airworthy

blade that has been modified by an

installation of rivets, and install 304 stainless

steel abrasion tape (.0027-inch thick) over the

inboard end of the abrasion strip in

accordance with steps B through H of Part I

of the Accomplishment Instructions of

McDonnell Douglas Helicopter Systems

Service Information Notice (SIN) HN–238,

DN–187, EN–80, FN–66, dated October 26,

1994.

(2) If the inspection reveals no debonding,

install 304 stainless steel abrasion tape

(.0027-inch thick) over the inboard end of the

abrasion strip in accordance with steps B

through H of Part I of the Accomplishment

Instructions of McDonnell Douglas

Helicopter Systems SIN HN–238, DN–187,

EN–80, FN–66, dated October 26, 1994.

(b) Within 1,000 hours TIS after the

effective date of this AD, replace the affected

tail rotor blades in shipsets with tail rotor

blades that contain the new-design abrasion

strips in accordance with Part II of the

Accomplishment Instructions of SIN HN–

238, DN–187, EN–80, FN–66, dated October

26, 1994. Once the new-design abrasion

strips are installed on the tail rotor blades,

the tail rotor assembly P/N changes as

follows:

Old tail rotor assembly

No.

New tail rotor assembly No.

369A1613–7 ................... 369A1613–11.

369A1613–503 ............... 369A1613–507.

369A1613–505 ............... 369A1613–507.

369A1613–509 ............... 369A1613–507.

369D21606 ..................... 369D21606–511.

369D21606–509 ............. 369D21606–511.

369D21613–11 ............... 369D21613–11N.

369D21613–31 ............... 369D21613–31N.

369D21613–41 ............... 369D21613–61.

369D21613–51 ............... 369D21613–61.

369D21613–71 ............... 369D21613–61.

369D21615 ..................... 369D21615–N.

369D21615–21 ............... 369D21615–31.

369D21615–41 ............... 369D21615–31.

421–088 .......................... 421–088–11.

(c) Installation of tail rotor blades with

new-design abrasion strips installed in

accordance with Part II of the

Accomplishment Instructions of SIN HN–

238, DN–187, EN–80, FN–66, dated October

26, 1994, constitutes a terminating action for

the requirements of this AD.

(d) 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, Los

Angeles 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, Los Angeles Aircraft

Certification Office.

Note: Information concerning the existence

of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Los Angeles Aircraft

Certification Office.

(e) Special flight permits may be issued in

accordance with §§ 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 requirements of this AD

can be accomplished, provided there is no

evidence of debonding of the abrasion strip

at any point along the entire abrasion strip

bond line of the tail rotor blades.

(f) The modification and replacement shall

be done in accordance with McDonnell

Douglas Helicopter Systems Service

Information Notice HN–238, DN–187, EN–80,

FN–66, dated October 26, 1994. This

incorporation by reference was approved by

the Director of the Federal Register in

accordance with 5 U.S.C. 552(a) and 1 CFR

part 51. Copies may be obtained from

McDonnell Douglas Helicopter Systems,

Technical Publications, Bldg. 530/B111, 5000

E. McDowell Road, Mesa, Arizona 85205–

9797. 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.

(g) 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. 95–3512 Filed 2–13–95; 8:45 am]

BILLING CODE 4910–13–P

14 CFR Part 39

[Docket No. 94–CE–08–AD; Amendment 39–

9139; AD 95–03–02]

Airworthiness Directives; Brackett

Aircraft Company, Inc. Air Filter

Assemblies Installed on Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD) that

applies to airplanes with certain

Brackett Aircraft Company, Inc.

(Brackett) air filter assemblies that have

a neoprene gasket design installed

between the carburetor heat box and the

air filter frame. This action requires

repetitively inspecting (visually) the air

filter frame for a loose or deteriorating

gasket, and replacing any gasket found

loose or deteriorated. An accident report

concerning a Cessna Model 172 airplane

that experienced engine loss because a

six-inch piece of neoprene gasket

material was lodged in the carburetor

prompted this action. The actions

specified by this AD are intended to

prevent gasket particles from entering

the carburetor because of air filter gasket

failure, which could result in partial or

complete loss of engine power.

DATES: Effective March 17, 1995.