Federal Register / Vol. 60, No. 6 / Tuesday, January 10, 1995 / Rules and Regulations 2495

increased sectional dimension, P/N

1379111E 1 (Modification No. 5162), in

accordance with the Instructions to

Modification No. 5162, Part 1 and Part 2,

Issue 1, dated June 1981.

(c) Incorporating Modification 5162 as

specified in paragraphs (a)(1) and (b) of this

AD eliminates the repetitive inspection

requirement of this AD.

(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) An alternative method of compliance or

adjustment of the initial and repetitive

compliance times that provides an equivalent

level of safety may be approved by the

Manager, Brussels Aircraft Certification

Office (ACO), Europe, Africa, Middle East

office, FAA, c/o American Embassy, B–1000

Brussels, Belgium. The request should be

forwarded through an appropriate FAA

Maintenance Inspector, who may add

comments and then send it to the Manager,

Brussels ACO.

Note: Information concerning the existence

of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Brussels ACO.

(f) The inspection required by this AD shall

be done in accordance with Jetstream Service

Bulletin No. 9/10, dated April 28, 1981. The

replacement required by this AD shall be

done in accordance with Instructions to

Modification No. 5162, Part 1 and Part 2,

Issue 1, dated June 1981. 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 Jetstream Aircraft Limited,

Manager Product Support, Prestwick Airport,

Ayrshire, KA9 2RW Scotland; or Jetstream

Aircraft Inc., Librarian, P.O. Box 16029,

Dulles International Airport, Washington, DC

20041–6029. Copies may be inspected at the

FAA, Central Region, Office of the Assistant

Chief Counsel, room 1558, 601 E. 12th Street,

Kansas City, Missouri, or at the Office of the

Federal Register, 800 North Capitol Street,

NW., suite 700, Washington, DC.

(g) This amendment (39–9119) becomes

effective on February 20, 1995.

Issued in Kansas City, Missouri, on January

4, 1995.

Henry A. Armstrong,

Acting Manager, Small Airplane Directorate,

Aircraft Certification Service.

[FR Doc. 95–518 Filed 1–9–95; 8:45 am]

BILLING CODE 4910–13–U

14 CFR Part 39

[Docket No. 91–CE–12–AD; Amendment 39–

9118; AD 95–01– 07]

Airworthiness Directives; Fairchild

Aircraft Models SA227–AC and SA227–

AT Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment supersedes

Airworthiness Directive (AD) 83–12–01,

which currently requires repetitively

inspecting the lower wing skin panel for

cracks on certain Fairchild Aircraft

Models SA227–AC and SA227–AT

airplanes, and installing wing skin

reinforcement doublers if any wing skin

crack is found. The Federal Aviation

Administration’s policy on aging

commuter-class aircraft is to eliminate,

or, in certain instances, reduce the

number of certain repetitive shortinterval inspections when improved

parts or modifications are available.

This action requires installing wing skin

reinforcement doublers or wing skin

stringer ties as terminating action for the

repetitive inspections that are currently

required by AD 83–12–01. The actions

specified by this AD are intended to

prevent fatigue failure of the lower wing

skin panels, which could result in loss

of control of the airplane.

DATES: Effective February 17, 1995.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of February

17, 1995.

ADDRESSES: Service information that

applies to this AD may be obtained from

Fairchild Aircraft, P.O. Box 790490, San

Antonio, Texas 78279–0490; telephone

(210) 824–9421. This information may

also be examined at the Federal

Aviation Administration (FAA), Central

Region, Office of the Assistant Chief

Counsel, room 1558, 601 E. 12th Street,

Kansas City, Missouri 64106; or at the

Office of the Federal Register, 800 North

Capitol Street, NW., suite 700,

Washington, DC.

FOR FURTHER INFORMATION CONTACT: Mr.

Hung Viet Nguyen, Aerospace Engineer,

FAA, Airplane Certification Office, 2601

Meacham Boulevard, Fort Worth, Texas

76193–0150; telephone (817) 222–5155;

facsimile (817) 222–5959.

SUPPLEMENTARY INFORMATION: A

proposal to amend part 39 of the Federal

Aviation Regulations (14 CFR part 39) to

include an AD that would apply to

certain Fairchild Aircraft Models

SA227–AC and SA227–AT airplanes

was published in the Federal Register

on March 30, 1994 (59 FR 14797). The

action proposed to supersede AD 83–12-

01 with a new AD that would (1) retain

the requirement of repetitively

inspecting the lower wing skin panel,

and installing wing skin reinforcement

doublers if any wing skin crack is

found; and (2) require either installing

wing skin reinforcement doublers or

wing skin stringer ties as terminating

action for the repetitive inspections. The

proposed actions would be

accomplished in accordance with

Fairchild SB No. 227–57– 002, Issued:

June 6, 1983, Revised: January 23, 1984.

Interested persons have been afforded

an opportunity to participate in the

making of this amendment. No

comments were received on the

proposed rule or the FAA’s

determination of the cost to the public.

After careful review of all available

information, the FAA has determined

that air safety and the public interest

require the adoption of the rule as

proposed except for minor editorial

corrections. The FAA has determined

that these minor corrections will not

change the meaning of the AD nor add

any additional burden upon the public

than was already proposed.

This action is based on the FAA’s

aging commuter-class airplane policy,

which briefly states that owners/

operators in commuter service should

incorporate modifications or install

improved parts when the modification

or installation would eliminate, or, in

certain instances, reduce a repetitive

inspection on a critical structure.

The FAA estimates that 125 airplanes

in the U.S. registry will be affected by

this AD, that it will take approximately

9 workhours per airplane to accomplish

the required action if reinforcement

doublers were installed (1 workhour/

inspection and 8 workhours/

modification) or 25 workhours per

airplane to accomplish the required

action if wing skin stringer ties were

installed (1 workhour/inspection and 24

workhours/modification), and that the

average labor rate is approximately $55

an hour. Parts cost approximately $56

per airplane for the wing skin

reinforcement doublers and $179 per

airplane for the wing skin stringer ties.

Based on these figures, the total cost

impact of this AD on U.S. operators is

estimated to be either $68,875 for those

airplane operators incorporating the

reinforcement doubler modification or

$194,250 for those airplane operators

utilizing the wing skin stringer ties

modification. This cost figure is based

on the assumption that no affected

airplane owner/operator has

accomplished one of the required

inspection-terminating modifications.

The figure does not include repetitive

inspection costs. The FAA has no way

of determining how many repetitive

inspections each owner/operator may

incur.

The intent of the FAA’s aging

commuter airplane program is to ensure

safe operation of commuter-class

airplanes that are in commercial service

without adversely impacting private

operators. Of the approximately 125
2496 Federal Register / Vol. 60, No. 6 / Tuesday, January 10, 1995 / Rules and Regulations

airplanes in the U.S. registry that will be

affected by this AD, approximately 76

are operated in scheduled passenger

service. A significant number of the

remaining 49 airplanes are operated in

other forms of air transportation such as

air cargo and air taxi.

This AD allows 500 hours time-inservice (TIS) before mandatory

accomplishment of the design

modification. The average utilization of

the fleet for those airplanes in

commercial commuter service is

approximately 25 to 50 hours TIS per

week. Based on these figures, operators

of commuter-class airplanes involved in

commercial operation will have to

accomplish the required modification

within 2 to 5 calendar months after this

AD becomes effective. For private

owners, who typically operate between

100 to 200 hours TIS per year, this

allows 2 to 5 calendar years before the

required modification will be

mandatory.

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 copy of the final

evaluation prepared for this action is

contained in the Rules Docket. A copy

of it may be obtained by contacting 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

removing AD 83–12–01, Amendment

39–4693, and by adding a new AD to

read as follows:

95–01–07 Fairchild Aircraft: Amendment

39–9118; Docket No. 91–CE–12–AD.

Supersedes AD 83–12–01, Amendment

39–4693.

Applicability: The following model and

serial number airplanes, certificated in any

category:

Model Serial Nos.

SA227–AC ....... 415, 416, and 420 through

554.

SA227–AT ....... 423 through 554.

Compliance: Required as indicated in the

body of this AD, unless already

accomplished.

To prevent fatigue failure of the lower wing

skin panels, which could result in loss of

control of the airplane, accomplish the

following:

(a) Within the next 50 hours time-inservice (TIS) after the effective date of this

AD, unless already accomplished

(compliance with AD 83–12–01), dye

penetrant inspect the lower wing skin panel

of both wings in the area of Wing Station

(WS) 187.0 in accordance with paragraph IIA

of the ACCOMPLISHMENT INSTRUCTIONS

section of Fairchild Service Bulletin (SB)

227–57–002, Issued: June 6, 1983, Revised:

January 23, 1984.

(1) If cracks are found, prior to further

flight, install reinforcement doublers, part

number 27K31013–001 LH and 27K31013–

002 RH, in accordance with paragraph IIB of

the ACCOMPLISHMENT INSTRUCTIONS

section of Fairchild SB 227–57–002, Issued:

June 6, 1983, Revised: January 23, 1984.

(2) If no cracks are found, reinspect

thereafter at intervals not to exceed 50 hours

TIS until the modification specified in

paragraph (b) of this AD is accomplished.

(b) Within the next 500 hours TIS after the

effective date of this AD, unless already

accomplished as specified in paragraph (a)(1)

of this AD, accomplish one of the following

on both wings:

(1) Install reinforcement doublers, part

number 27K31013–001 LH and 27K31013–

002 RH, in accordance with paragraph IIB of

the ACCOMPLISHMENT INSTRUCTIONS

section of Fairchild SB 227–57–002, Issued:

June 6, 1983, Revised: January 23, 1984; or

(2) Install stringer ties, P/N 27–13869, in

accordance with paragraph IIC of the

ACCOMPLISHMENT INSTRUCTIONS

section of Fairchild SB 227–57–002, Issued:

June 6, 1983, Revised: January 23, 1984.

(c) Incorporating (on both wings) the

modification specified in paragraph (a)(1),

(b)(1) or (b)(2) of this AD terminates the

repetitive inspection requirement of this AD.

(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) An alternative method of compliance or

adjustment of the initial or repetitive

compliance times that provides an equivalent

level of safety may be approved by the

Manager, Airplane Certification Office

(ACO), 2601 Meacham Boulevard, Fort

Worth, Texas 76193–0150. The request shall

be forwarded through an appropriate FAA

Maintenance Inspector, who may add

comments and then send it to the Manager,

Fort Worth ACO.

Note: Information concerning the existence

of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Fort Worth ACO.

(f) The inspections and installation

required by this AD shall be done in

accordance with Fairchild Service Bulletin

227–57–002, Issued: June 6, 1983, Revised:

January 23, 1984. 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 Fairchild Aircraft, P.O. Box

790490, San Antonio, Texas 78279–0490.

Copies may be inspected at the FAA, Central

Region, Office of the Assistant Chief Counsel,

Room 1558, 601 E. 12th Street, Kansas City,

Missouri, or at the Office of the Federal

Register, 800 North Capitol Street, NW., suite

700, Washington, DC.

(g) This amendment (39–9118) supersedes

AD 83–12–01, Amendment 39–4693.

(h) This amendment (39–9118) becomes

effective on February 17, 1995.

Issued in Kansas City, Missouri, on January

4, 1995.

Henry A. Armstrong,

Acting Manager, Small Airplane Directorate,

Aircraft Certification Service.

[FR Doc. 95–517 Filed 1–9–95; 8:45 am]

BILLING CODE 4910–13–M

14 CFR Part 71

[Airspace Docket No. 94–ASW–2]

Alteration of Jet Routes; Louisiana

AGENCY: Federal Aviation

Administration (FAA), DOT.

ACTION: Final rule; correction.

SUMMARY: This document contains a

correction to the final rule published on

December 9, 1994. In the airspace

designation of Jet Route J–37 the Hobby

084° radial was in error. This correction

changes the ‘‘Hobby 084°’’ radial to read

the ‘‘Hobby 090°’’ radial.

EFFECTIVE DATE: February 2, 1995.

FOR FURTHER INFORMATION CONTACT:

Norman W. Thomas, Airspace and

Obstruction Evaluation Branch (ATP–