Federal Register / Vol. 61, No. 121 / Friday, June 21, 1996 / Rules and Regulations 31825

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. 106(g), 40113, 44701.

§ 39.13 [Amended]

2. Section 39.13 is amended by

adding the following new airworthiness

directive:

96–13–05 Fokker: Amendment 39–9673.

Docket 95–NM–170–AD.

Applicability: Model F28 series airplanes;

serial numbers 11003 through 11241

inclusive, 11991, and 11992; certificated in

any category.

Note 1: Fokker Model F28 Mark 0100 series

airplanes are not subject to the requirements

of this AD.

Note 2: 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 request approval for an

alternative method of compliance in

accordance with paragraph (c) of this AD.

The request should include an assessment of

the effect of the modification, alteration, or

repair on the unsafe condition addressed by

this AD; and, if the unsafe condition has not

been eliminated, the request should include

specific proposed actions to address it.

Compliance: Required as indicated, unless

accomplished previously.

To prevent fatigue cracking of the elevator

gust lock housing and the gust lock support

structure, which could result in loss of the

elevator and the support structure, and

subsequent possible loss of primary pitch

control, accomplish the following:

(a) Within 30 days after the effective date

of this AD, perform a one-time detailed

visual inspection to detect cracking of the

elevator gust lock housing and the gust lock

support structure, in accordance with Fokker

Service Bulletin F28/55–30, Revision 1,

dated January 4, 1993.

(b) If any cracking is found, prior to further

flight, repair or replace the cracked elevator

gust lock housing or gust lock support

structure with a new or serviceable part in

accordance with Fokker Service Bulletin

F28/55–30, Revision 1, dated January 4,

1993. Use of the elevator gust lock system is

prohibited until cracked parts are replaced

with new or serviceable parts.

(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,

Standardization Branch, ANM–113, 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, Standardization

Branch, ANM–113.

Note 3: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Standardization Branch,

ANM–113.

(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 airplane to

a location where the requirements of this AD

can be accomplished.

(e) The inspection, repair, and replacement

shall be done in accordance with Fokker

Service Bulletin F28/55–30, Revision 1,

dated January 4, 1993, which contains the

following list of effective pages:

Page No.

Revision

level

shown on

page

Date shown on

page

1–2 ............... 1 .............. Jan. 4, 1993.

3–5 ............... Original .... Aug. 24, 1992.

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 Fokker Aircraft USA, Inc., 1199 North

Fairfax Street, Alexandria, Virginia 22314.

Copies may be inspected at the FAA,

Transport Airplane Directorate, 1601 Lind

Avenue, SW., Renton, Washington; or at the

Office of the Federal Register, 800 North

Capitol Street, NW., suite 700, Washington,

DC.

(f) This amendment becomes effective on

July 26, 1996.

Issued in Renton, Washington, on June 13,

1996.

James V. Devany,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 96–15603 Filed 6–20–96; 8:45 am]

BILLING CODE 4910–13–U

14 CFR Part 39

[Docket No. 95–NM–151–AD; Amendment

39–9674; AD 96–13–06]

RIN 2120–AA64

Airworthiness Directives; Fokker

Model F28 Series Airplanes (Excluding

Fokker Model F28 Mark 0100 Series

Airplanes)

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD),

applicable to certain Fokker Model F28

series airplanes, that requires

replacement of junction fittings of the

horizontal stabilizer with improved

fittings. For certain airplanes, this

amendment also requires replacement of

the drive-fitting bushings and bolts of

the horizontal stabilizer with improved

bushings and bolts. This amendment is

prompted by reports of stress corrosion

cracking in a junction fitting lug of the

horizontal stabilizer. The actions

specified by this AD are intended to

prevent such cracking, which could

result in failure of a lug and

uncommanded movement of the

horizontal stabilizer. This condition, if

not corrected, could result in reduced

controllability of the airplane.

DATES: Effective July 26, 1996.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of July 26,

1996.

ADDRESSES: The service information

referenced in this AD may be obtained

from Fokker Aircraft USA, Inc., 1199

North Fairfax Street, Alexandria,

Virginia 22314. This information may be

examined at the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, Rules Docket,

1601 Lind Avenue, SW., Renton,

Washington; or at the Office of the

Federal Register, 800 North Capitol

Street, NW., suite 700, Washington, DC.

FOR FURTHER INFORMATION CONTACT: Tim

Dulin, Aerospace Engineer,

Standardization Branch, ANM–113,

FAA, Transport Airplane Directorate,

1601 Lind Avenue, SW., Renton,

Washington 98055–4056; telephone

(206) 227–2141; fax (206) 227–1149.

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 certain Fokker

Model F28 series airplanes was

published in the Federal Register on
31826 Federal Register / Vol. 61, No. 121 / Friday, June 21, 1996 / Rules and Regulations

April 1, 1996 (61 FR 14273). That action

proposed to require replacement of

aluminum 7079 junction fittings (left

and right) of the horizontal stabilizer

with improved fittings made from

aluminum 7075. For certain airplanes,

that action also proposed to require

replacement of the drive-fitting

bushings and bolts of the horizontal

stabilizer with new bushings and bolts

made from a different material having

improved resistance to corrosion.

Interested persons have been afforded

an opportunity to participate in the

making of this amendment. Due

consideration has been given to the two

comments received.

Support for the Proposal

Both commenters support the

proposed rule.

Conclusion

After careful review of the available

data, including the comments noted

above, the FAA has determined that air

safety and the public interest require the

adoption of the rule as proposed.

Cost Impact

The FAA estimates that 14 airplanes

of U.S. registry will be affected by this

AD.

For airplanes on which the

replacement of aluminum 7079 junction

fittings with improved fittings is

required, the FAA estimates that it will

take approximately 430 work hours per

airplane to accomplish the replacement,

at an average labor rate of $60 per work

hour. Required parts will cost

approximately $40,000 per airplane.

Based on these figures, the cost impact

of the AD on U.S. operators for

replacement of aluminum 7079 fittings

is estimated to be $65,800 per airplane.

For airplanes on which replacement

of the drive-fitting bushings and bolts

on the horizontal stabilizer with new

bushings and bolts is required, the FAA

estimates that it will take approximately

10 work hours per airplane to

accomplish the replacement, at an

average labor rate of $60 per work hour.

Required parts will cost approximately

$2,100 per airplane. Based on these

figures, the cost impact of the AD on

U.S. operators for replacement of the

drive-fitting bushings and bolts is

estimated to be $2,700 per airplane.

The cost impact figures discussed

above are based on assumptions that no

operator has yet accomplished any of

the requirements of this AD action, and

that no operator would accomplish

those actions in the future if this AD

were not adopted.

Regulatory Impact

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. 106(g), 40113, 44701.

§ 39.13 [Amended]

2. Section 39.13 is amended by

adding the following new airworthiness

directive:

96–13–06 Fokker: Amendment 39–9674.

Docket 95–NM–151–AD.

Applicability: Model F28 series airplanes;

serial numbers 11003 through 11151

inclusive, 11991, and 11992; certificated in

any category.

Note 1: Fokker Model F28 Mark 0100 series

airplanes are not subject to the requirements

of this AD.

Note 2: 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 request approval for an

alternative method of compliance in

accordance with paragraph (d) of this AD.

The request should include an assessment of

the effect of the modification, alteration, or

repair on the unsafe condition addressed by

this AD; and, if the unsafe condition has not

been eliminated, the request should include

specific proposed actions to address it.

Compliance: Required as indicated, unless

accomplished previously.

To prevent stress corrosion cracking of the

junction fitting lug of the horizontal

stabilizer, which could result in failure of the

lug and uncommanded movement of the

horizontal stabilizer, and subsequent reduced

controllability of the airplane, accomplish

the following:

(a) Within 18 months after the effective

date of this AD, replace the aluminum 7079

junction fittings (left and right) of the

horizontal stabilizer with improved fittings

made from aluminum 7075, in accordance

with Part 1 of the Accomplishment

Instructions of Fokker Service Bulletin F28/

55–029, Revision 1, dated January 23, 1993.

(b) For airplanes on which the drive-fitting

bushings and bolts of the horizontal stabilizer

have not been replaced in accordance with

Fokker Service Bulletin F28/55–24: Within

18 months after the effective date of this AD,

replace the drive-fitting bushings and bolts of

the horizontal stabilizer with new bushings

and bolts, in accordance with Part 2 of the

Accomplishment Instructions of Fokker

Service Bulletin F28/55–029, Revision 1,

dated January 23, 1993.

(c) Accomplishment of the replacements

required by paragraphs (a) and (b) of this AD

constitute terminating action for the

inspections identified as item 55–50–05 in

the Fokker Structural Integrity Program (SIP)

Document 28438, Part 1, revised up through

October 15, 1992, which are required by AD

93–13–04, amendment 39–8617 (58 FR

38513, July 19, 1993). Once these

replacements are accomplished, the life

limits of the fitting lugs (identified as items

55–50–01 and 55–50–02 in the SIP

Document) no longer apply.

(d) 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,

Standardization Branch, ANM–113, 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, Standardization

Branch, ANM–113.

Note 3: Information concerning the

existence of approved alternative methods of
Federal Register / Vol. 61, No. 121 / Friday, June 21, 1996 / Rules and Regulations 31827

compliance with this AD, if any, may be

obtained from the Standardization Branch,

ANM–113.

(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 airplane to

a location where the requirements of this AD

can be accomplished.

(f) The replacements shall be done in

accordance with Fokker Service Bulletin

F28/55–029, Revision 1, dated January 23,

1993, which contains the following list of

effective pages:

Page No.

Revision

level

shown on

page

Date shown on

page

1–3 ............... 1 .............. Jan. 23, 1993.

4–45 ............. Original .... Sep. 20, 1992.

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 Fokker Aircraft USA, Inc., 1199 North

Fairfax Street, Alexandria, Virginia 22314.

Copies may be inspected at the FAA,

Transport Airplane Directorate, 1601 Lind

Avenue, SW., Renton, Washington; or at the

Office of the Federal Register, 800 North

Capitol Street, NW., suite 700, Washington,

DC.

(g) This amendment becomes effective on

July 26, 1996.

Issued in Renton, Washington, on June 13,

1996.

James V. Devany,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 96–15602 Filed 6–20–96; 8:45 am]

BILLING CODE 4910–13–U

14 CFR Part 97

[Docket No. 28601; Amdt. No. 1735]

RIN 2120–AA65

Standard Instrument Approach

Procedures; Miscellaneous

Amendments

AGENCY: Federal Aviation

Administration (FAA), DOT.

ACTION: Final rule.

SUMMARY: This amendment establishes,

amends, suspends, or revokes Standard

Instrument Approach Procedures

(SIAPs) for operations at certain

airports. These regulatory actions are

needed because of the adoption of new

or revised criteria, or because of changes

occurring in the National Airspace

System, such as the commissioning of

new navigational facilities, addition of

new obstacles, or changes in air traffic

requirements. These changes are

designed to provide safe and efficient

use of the navigable airspace and to

promote safe flight operations under

instrument flight rules at the affected

airports.

DATES: An effective date for each SIAP

is specified in the amendatory

provisions.

Incorporation by reference-approved

by the Director of the Federal Register

on December 31, 1980, and reapproved

as of January 1, 1982.

ADDRESSES: Availability of matters

incorporated by reference in the

amendment is as follows:

For Examination

1. FAA Rules Docket, FAA

Headquarters Building, 800

Independence Avenue, SW.,

Washington, DC 20591;

2. The FAA Regional Office of the

region in which the affected airport is

located; or

3. The Flight Inspection Area Office

which originated the SIAP.

For Purchase

Individual SIAP copies may be

obtained from:

1. FAA Public Inquiry Center (APA–

200), FAA Headquarters Building, 800

Independence Avenue, SW.,

Washington, DC 20591; or

2. The FAA Regional Office of the

region in which the affected airport is

located.

By Subscription

Copies of all SIAPs, mailed once

every 2 weeks, are for sale by the

Superintendent of Documents, U.S.

Government Printing Office,

Washington, DC 20402.

FOR FURTHER INFORMATION CONTACT: Paul

J. Best, Flight Procedures Standards

Branch (AFS–420), Technical Programs

Division, Flight Standards Service,

Federal Aviation Administration, 800

Independence Avenue, SW.,

Washington, DC 20591; telephone (202)

267–8277.

SUPPLEMENTARY INFORMATION: This

amendment to part 97 of the Federal

Aviation Regulations (14 CFR part 97)

establishes, amends, suspends, or

revokes Standard Instrument Approach

Procedures (SIAPs). The complete

regulatory description of each SIAP is

contained in official FAA form

documents which are incorporated by

reference in this amendment under 5

U.S.C. 552(a), 1 CFR part 51, and § 97.20

of the Federal Aviation Regulations

(FAR). The applicable FAA Forms are

identified as FAA Forms 8260–3, 8260–

4, and 8260–5. Materials incorporated

by reference are available for

examination or purchase as stated

above.

The large number of SIAPs, their

complex nature, and the need for a

special format make their verbatim

publication in the Federal Register

expensive and impractical. Further,

airmen do not use the regulatory text of

the SIAPs, but refer to their graphic

depiction on charts printed by

publishers of aeronautical materials.

Thus, the advantages of incorporation

by reference are realized and

publication of the complete description

of each SIAP contained in FAA form

documents is unnecessary. The

provisions of this amendment state the

affected CFR (and FAR) sections, with

the types and effective dates of the

SIAPs. This amendment also identifies

the airport, its location, the procedure

identification and the amendment

number.

The Rule

This amendment to part 97 is effective

upon publication of each separate SIAP

as contained in the transmittal. Some

SIAP amendments may have been

previously issued by the FAA in a

National Flight Data Center (FDC)

Notice to Airmen (NOTAM) as an

emergency action of immediate flight

safety relating directly to published

aeronautical charts. The circumstances

which created the need for some SIAP

amendments may require making them

effective in less than 30 days. For the

remaining SIAPs, an effective date at

least 30 days after publication is

provided.

Further, the SIAPs contained in this

amendment are based on the criteria

contained in the U.S. Standard for

Terminal Instrument Approach

Procedures (TERPS). In developing

these SIAPs, the TERPS criteria were

applied to the conditions existing or

anticipated at the affected airports.

Because of the close and immediate

relationship between these SIAPs and

safety in air commerce, I find that notice

and public procedure before adopting

these SIAPs are impracticable and

contrary to the public interest and,

where applicable, that good cause exists

for making some SIAPs effective in less

than 30 days.

The FAA has determined that this

regulation only involves an established

body of technical regulations for which

frequent and routine amendments are

necessary to keep them operationally

current. It, therefore—(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)

does not warrant preparation of a

regulatory evaluation as the anticipated