Federal Register / Vol. 60, No. 92 / Friday, May 12, 1995 / Rules and Regulations 25611

For the reasons discussed above, I

certify that this action (1) is not a

‘‘significant regulatory action’’ under

Executive Order 12866; (2) is not a

‘‘significant rule’’ under DOT

Regulatory Policies and Procedures (44

FR 11034, February 26, 1979); and (3)

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 final evaluation has

been prepared for this action and it is

contained in the Rules Docket. A copy

of it 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 the following new airworthiness

directive:

95–10–02 McDonnell Douglas: Amendment

39–9219. Docket 94–NM–175–AD.

Applicability: Model MD–11 series

airplanes; as listed in McDonnell Douglas

MD–11 Service Bulletin 27–36, Revision 1,

dated December 9, 1994, certificated in any

category.

Note 1: This AD applies to each airplane

identified in the preceding applicability

provision, regardless of whether it has been

modified, altered, or repaired in the area

subject to the requirements of this AD. For

airplanes that have been modified, altered, or

repaired so that the performance of the

requirements of this AD is affected, the

owner/operator must use the authority

provided in paragraph (c) to request approval

from the FAA. This approval may address

either no action, if the current configuration

eliminates the unsafe condition; or different

actions necessary to address the unsafe

condition described in this AD. Such a

request should include an assessment of the

effect of the changed configuration on the

unsafe condition addressed by this AD. In no

case does the presence of any modification,

alteration, or repair remove any airplane from

the applicability of this AD.

Compliance: Required as indicated, unless

accomplished previously.

To prevent inadvertent deployment of the

slats during flight, accomplish the following:

(a) Within 24 months after the effective

date of this AD, modify the airplane and

install an electrically controlled slat control

system in accordance with McDonnell

Douglas MD–11 Service Bulletin 27–36,

Revision 1, dated December 9, 1994.

(b) Accomplishment of the actions required

by paragraph (a) of this AD constitutes

terminating action for the requirements of the

following AD’s:

AD No. Amendment No.

Federal Register

citation

92–13–03 . 39–8273 (57 FR 27155,

June 18, 1992).

92–14–51 . 39–8325 (57 FR 38264,

August 24, 1992).

92–26–03 . 39–8430 (57 FR 57906,

December 8, 1992).

93–15–03 . 39–8649 (58 FR 41421,

August 4, 1993).

(c) An alternative method of compliance or

adjustment of the compliance time that

provides an acceptable level of safety may be

used if approved by the Manager, Los

Angeles Aircraft Certification Office (ACO),

FAA, Transport Airplane Directorate.

Operators shall submit their requests through

an appropriate FAA Principal Maintenance

Inspector, who may add comments and then

send it to the Manager, Los Angeles ACO.

Note 2: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Los Angeles ACO.

(d) 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 airplane to a

location where the requirements of this AD

can be accomplished.

(e) The installation shall be done in

accordance with McDonnell Douglas MD–11

Service Bulletin 27–36, Revision 1, dated

December 9, 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

Corporation, P.O. Box 1771, Long Beach,

California 90801–1771, Attention: Business

Unit Manager, Technical Administrative

Support, Dept. L51, M.C. 2–98. Copies may

be inspected at the FAA, Transport Airplane

Directorate, 1601 Lind Avenue, SW., Renton,

Washington; or at the FAA, Los Angeles

Aircraft Certification Office, Transport

Airplane Directorate, 3960 Paramount

Boulevard, Lakewood, California; or at the

Office of the Federal Register, 800 North

Capitol Street, NW., suite 700, Washington,

DC.

(f) This amendment becomes effective on

June 12, 1995.

Issued in Renton, Washington, on April 28,

1995.

Darrell M. Pederson,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 95–10987 Filed 5–11–95; 8:45 am]

BILLING CODE 4910–13–U

14 CFR Part 39

[Docket No. 93–SW–18–AD; Amendment

39–9226; AD 95–10–09]

Airworthiness Directives; Sikorsky

Aircraft Model S–58 and S–58T Series

Helicopters

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD),

applicable to Sikorsky Aircraft Model

S–58 and S–58T series helicopters, that

requires the removal and replacement of

the transmission main gear box ring gear

(ring gear) within certain time intervals,

and establishes a retirement life for the

ring gear. This amendment is prompted

by reports of failures of the ring gear due

to slow-growth fatigue cracks. The

actions specified by this AD are

intended to prevent failure of the ring

gear, failure of the main transmission,

and subsequent loss of control of the

helicopter.

DATES: Effective June 16, 1995.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of June 16,

1995.

ADDRESSES: The service information

referenced in this AD may be obtained

from Sikorsky Aircraft, Commercial

Customer Support, 6900 Main Street,

Stratford, Connecticut 06601–1381. This

information may be examined at the

FAA, Office of the Assistant Chief

Counsel, 2601 Meacham Boulevard,

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.

Francis X. Walsh, Aerospace Engineer,

Boston Aircraft Certification Office,

FAA, New England Region, 12 New

England Executive Park, Burlington,

Massachusetts 01803–5299, telephone

(617) 238–7158, fax (617) 238–7199.

SUPPLEMENTARY INFORMATION: A

proposal to amend part 39 of the Federal

Aviation Regulations (14 CFR part 39) to

include an airworthiness directive (AD)

that is applicable to Sikorsky Aircraft

Model S–58 and S–58T series
25612 Federal Register / Vol. 60, No. 92 / Friday, May 12, 1995 / Rules and Regulations

helicopters was published in the

Federal Register on June 22, 1994 (59

FR 32144). That action proposed to

require the removal and replacement of

the ring gear within certain time

intervals, and proposed to establish a

retirement life for the ring gear.

Interested persons have been afforded

an opportunity to participate in the

making of this amendment. No

comments were received on the

proposal or the FAA’s determination of

the cost to the public. The FAA has

determined that air safety and the

public interest require the adoption of

the rule as proposed. Since the issuance

of the proposed rule, the FAA has

revised the average labor rate from $55

per work hour to $60 per work hour,

which increases the estimated cost

impact on operators to $486,250.

The FAA estimates that 125

helicopters of U.S. registry will be

affected by this AD, that it will take

approximately 31.5 work hours per

helicopter to accomplish the required

actions, and that the average labor rate

is $60 per work hour. Required parts

will cost approximately $2,000 per

helicopter. Based on these figures, the

total cost impact of the AD on U.S.

operators is estimated to be $486,250.

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.

For the reasons discussed above, I

certify that this action (1) is not a

‘‘significant regulatory action’’ under

Executive Order 12866; (2) is not a

‘‘significant rule’’ under DOT

Regulatory Policies and Procedures (44

FR 11034, February 26, 1979); and (3)

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 final evaluation has

been prepared for this action and it is

contained in the Rules Docket. A copy

of it 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:

95–10–09 Sikorsky Aircraft: Amendment

39–9226. Docket No. 93–SW–18–AD.

Applicability: Model S–58 and S–58T

series helicopters, certificated in any

category.

Note 1: This AD applies to each helicopter

identified in the preceding applicability

provision, regardless of whether it has been

modified, altered, or repaired in the area

subject to the requirements of this AD. For

helicopters that have been modified, altered,

or repaired so that the performance of the

requirements of this AD is affected, the

owner/operator must use the authority

provided in paragraph (d) to request approval

from the FAA. This approval may address

either no action, if the current configuration

eliminates the unsafe condition, or different

actions necessary to address the unsafe

condition described in this AD. Such a

request should include an assessment of the

effect of the changed configuration on the

unsafe condition addressed by this AD. In no

case does the presence of any modification,

alteration, or repair remove any helicopter

from the applicability of this AD.

Compliance: Required as indicated, unless

accomplished previously.

To prevent failure of the transmission main

gear box ring gear (ring gear), failure of the

main transmission, and subsequent loss of

control of the helicopter, accomplish the

following:

(a) Within the next 25 hours time-inservice (TIS) after the effective date of this

AD, accomplish the following:

(1) From component records, determine the

TIS for the ring gear, part number (P/N)

S1635–20058–2.

(i) If the TIS on the ring gear is 2,400 or

more hours on the effective date of this AD,

replace it with an airworthy serialized ring

gear within the next 100 hours TIS.

(ii) If the TIS on the ring gear is less than

2,400 hours on the effective date of this AD,

replace it with an airworthy serialized ring

gear at or before reaching 2,500 hours TIS.

(2) If the TIS on the ring gear cannot be

determined, replace it in accordance with the

time-since-last-overhaul (TSO) as follows:

(i) If the TSO on the ring gear is 1,150 or

more hours on the effective date of this AD,

replace it with an airworthy serialized ring

gear within the next 100 hours TIS.

(ii) If the TSO on the ring gear is less than

1,150 hours on the effective date of this AD,

replace it with an airworthy serialized ring

gear at or before reaching 1,250 hours TSO.

(3) Create a component log and a serial

number and apply the serial number to the

ring gear between the ring gear flanges in

accordance with Paragraph B of the

Accomplishment Instructions of Sikorsky

Aircraft Alert Service Bulletin No. 58B35–32

(ASB 58B35–32), dated July 6, 1993.

(b) Create a component log and a serial

number for replacement ring gears and apply

the serial number to the ring gear between

the ring gear flanges in accordance with

Paragraph B of the Accomplishment

Instructions of the ASB 58B35–32, dated July

6, 1993, prior to installing a replacement ring

gear on the helicopter.

(c) This AD establishes a retirement life of

2,500 hours TIS for the ring gear. However,

for ring gears with 2,400 or more hours TIS,

or if the TIS cannot be determined, 1,150 or

more hours TSO on the effective date of this

AD, those ring gears need not be retired until

on or before the accumulation of an

additional 100 hours TIS.

(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, Boston

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, Boston Aircraft Certification Office.

Note 2: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Boston Aircraft

Certification Office.

(e) 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 requirements of this

AD can be accomplished.

(f) The removal and replacement shall be

done in accordance with Sikorsky Aircraft

Alert Service Bulletin No. 58B35–32, dated

July 6, 1993. 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 Sikorsky Aircraft, Commercial

Customer Support, 6900 Main Street,

Stratford, Connecticut 06601–1381. Copies

may be inspected at the FAA, Office of the

Assistant Chief Counsel, 2601 Meacham

Boulevard, 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

June 16, 1995.

Issued in Fort Worth, Texas, on May 4,

1995.

Mark R. Schilling,

Acting Manager, Rotorcraft Directorate,

Aircraft Certification Service.

[FR Doc. 95–11539 Filed 5–11–95; 8:45 am]

BILLING CODE 4910–13–P