Federal Register / Vol. 61, No. 113 / Tuesday, June 11, 1996 / Rules and Regulations 29467

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.

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. 106(g), 40113, 44701.

§ 39.13 [Amended]

2. Section 39.13 is amended by

adding the following new airworthiness

directive:

96–12–13 Dornier: Amendment 39–9656.

Docket 96–NM–112–AD.

Applicability: Model 328 series airplanes,

equipped with Honeywell GP–300 guidance

and display controller having part number

(P/N) 7015327–901 or –902; certificated in

any category.

Note 1: This AD applies to each airplane

identified in the preceding applicability

provision, regardless of whether it has been

otherwise 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 (b) 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 a defective light bulb from

causing a short circuit that emits smoke and

fumes into the cockpit, or causing damage to

the circuit cards and various components,

which may lock the autopilot into the

engaged mode, accomplish the following:

(a) Within 60 days after the effective date

of this AD, modify the Honeywell GP–300

guidance and display controller, having P/N

7015327–901 or –902, in accordance with

Honeywell Service Bulletin 7015327–22–2,

dated March 4, 1996.

(b) 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.

(c) 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.

(d) The modification shall be done in

accordance with Honeywell Service Bulletin

7015327–22–2, dated March 4, 1996. 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

Honeywell, Inc., Attn: Customer Support

Materiel, P.O. Box 21111, Phoenix, Arizona

85036. 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.

(e) This amendment becomes effective on

June 26, 1996.

Issued in Renton, Washington, on May 31,

1996.

Darrell M. Pederson,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 96–14224 Filed 6–10–96; 8:45 am]

BILLING CODE 4910–13–U

14 CFR Part 39

[Docket No. 92–NM–71–AD; Amendment

39–9657; AD 96–12–14]

RIN 2120–AA64

Airworthiness Directives; 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

Mark 0100 series airplanes, that requires

reinforcing the lower right-hand wing

skin at the fueling adapter. This

amendment is prompted by results of

tests, which revealed that fatigue cracks

can develop in the lower right-hand

wing skin at the attachment bolt holes

of the fueling adapter. The actions

specified by this AD are intended to

prevent reduced structural capability of

the wing and fuel leakage.

DATES: Effective July 16, 1996.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of July 16,

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:

Ruth E. Harder, Aerospace Engineer,

Standardization Branch, ANM–113,

FAA, Transport Airplane Directorate,

1601 Lind Avenue, SW., Renton,

Washington 98055–4056; telephone

(206) 227–1721; 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 Mark 0100 series airplanes

was published as a supplemental notice

of proposed rulemaking in the Federal

Register on April 2, 1996 (61 FR 14515).

That action proposed to require

reinforcing the lower right-hand wing

skin at the fueling adapter.

Discussion of Comments

Interested persons have been afforded

an opportunity to participate in the
29468 Federal Register / Vol. 61, No. 113 / Tuesday, June 11, 1996 / Rules and Regulations

making of this amendment. Due

consideration has been given to the

single comment received.

The commenter supports the

proposed rule.

Conclusion

After careful review of the available

data, including the comment 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 18 airplanes

of U.S. registry will be affected by this

AD, that it will take approximately 20

work hours per airplane to accomplish

the required actions, and that the

average labor rate is $60 per work hour.

Required parts will cost approximately

$950 per airplane. Based on these

figures, the cost impact of the AD on

U.S. operators is estimated to be

$38,700, or $2,150 per airplane.

The cost impact figure discussed

above is 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:

96–12–14 Fokker: Amendment 39–9657.

Docket 92–NM–71–AD.

Applicability: Model F28 Mark 0100 series

airplanes; serial numbers 11244 through

11286 inclusive, 11289, 11290 through 11293

inclusive, 11295, 11297, 11300, 11303,

11306, 11308, 11310, and 11312; certificated

in any category.

Note 1: This AD applies to each airplane

identified in the preceding applicability

provision, regardless of whether it has been

otherwise 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 (b) 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 reduced structural capability of

the wing and fuel leakage, accomplish the

following:

(a) Prior to the accumulation of 12,000 total

landings, or within 60 days after the effective

date of this AD, whichever occurs later,

reinforce the lower right-hand wing skin at

the fueling adapter by installing a new

stringer and new internal and external

doubler plates, in accordance with Fokker

Service Bulletin SBF100–57–008, Revision 2,

dated September 22, 1995.

Note 2: Accomplishment of the

reinforcement in accordance with Fokker

Service Bulletin SBF100–57–008, Revision 1,

dated March 29, 1992, prior to the effective

date of this AD is acceptable for compliance

with the requirement of paragraph (a) of this

AD.

(b) 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.

(c) 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.

(d) The reinforcement shall be done in

accordance with Fokker Service Bulletin

SBF100–57–008, Revision 2, dated

September 22, 1995. 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.

(e) This amendment becomes effective on

July 16, 1996.

Issued in Renton, Washington, on May 31,

1996.

Darrell M. Pederson,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 96–14225 Filed 6–10–96; 8:45 am]

BILLING CODE 4910–13–U

14 CFR Part 39

[Docket No. 95–CE–14–AD; Amendment 39–

9666; AD 96–12–23]

RIN 2120–AA64

Airworthiness Directives; Cessna

Aircraft Company 150 and A150 Series

and Models 152 and A152 Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD) that

applies to Cessna Aircraft Company

(Cessna) 150 and A150 series and

Models 152 and A152 airplanes that

have a Bush Conversions, Inc., Short

Takeoff and Landing (STOL) kit

incorporated in accordance with

Supplemental Type Certificate (STC)

SA1371SW. This action requires

measuring the wing stall fence for

maximum height, and installing a

smaller fence if the fence exceeds the

maximum height of 1.28 inches. An

accident of a Cessna Model 152 airplane

where the STOL kit adversely affected

the airplane’s stall characteristics

prompted this action. The actions