Federal Register / Vol. 62, No. 6 / Thursday, January 9, 1997 / Rules and Regulations 1277

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 modification and replacement shall

be done in accordance with British

Aerospace Service Bulletin SB.55–014–

01510A, dated December 15, 1995; and

British Aerospace Service Bulletin SB.27–

150–01510B, dated December 15, 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 British

Aerospace Regional Aircraft Limited, Avro

International Aerospace Division, Customer

Support, Woodford Aerodrome, Woodford,

Cheshire SK7 1QR, England. 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

February 13, 1997.

Issued in Renton, Washington, on January

2, 1997.

S. R. Miller,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 97–365 Filed 1–8–97; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 96–NM–28–AD; Amendment

39–9879; AD 97–01–08]

RIN: 2120–AA64

Airworthiness Directives; Fokker

Model F27 Mark 100, 200, 300, 400, 500,

600, and 700 Series Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD),

applicable to certain Fokker Model F27

Mark 100, 200, 300, 400, 500, 600, and

700 series airplanes, that requires a onetime visual inspection to detect missing

rivet heads or loose rivets of the

applicable stringer-to-rib connections in

the upper and lower wing skin, and

repair, if necessary. In lieu of the onetime visual inspection or in addition to

that inspection, the AD also requires

replacement of certain rivets with

certain new rivets in all applicable ribto-stringer connections of the upper and

lower wings. This amendment is

prompted by reports of missing rivet

heads at the rib-to-stringer connections

of the upper and lower wing skin at

stringers 5 and 6. The actions specified

by this AD are intended to prevent

reduced structural integrity of the wings

that is caused by problems associated

with missing and/or loose rivets.

DATES: Effective February 13, 1997.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of February

13, 1997.

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 F27 Mark 100, 200, 300, 400,

500, 600, and 700 series airplanes was

published in the Federal Register on

July 24, 1996 (61 FR 38407). That action

proposed to require a one-time visual

inspection to detect missing rivet heads

or loose rivets of the applicable stringerto-rib connections in the upper and

lower skin, and repair, if necessary. In

lieu of the one-time visual inspection, or

in addition to that inspection, that

action also proposed to require

replacement of certain rivets with

certain new rivets in all applicable ribto-stringer connections of the upper and

lower wings.

Interested persons have been afforded

an opportunity to participate in the

making of this amendment. Due

consideration has been given to the

comments received.

Support for the Proposal

One commenter supports the

proposed rule.

Request to Cite the Latest Dutch AD

One commenter notes that the

preamble to the notice stated that ‘‘the

RLD classified [Fokker Service Bulletin

F27/57–74, dated November 15, 1994]

as mandatory and issued Dutch

airworthiness directive BLA 93–094 (A),

dated July 16, 1993 * * *.’’ The

commenter points out that the reference

to BLA 93–094 (A) is incorrect, since

that BLA 93–094 (A) was issued in

1993, a year earlier than the release of

Fokker Service Bulletin F27/57–74. The

commenter states that the Dutch BLA

that mandated that service bulletin is

BLA 94–148, dated November 24, 1994.

The FAA concurs. The FAA

inadvertently referenced the wrong BLA

number and issue date in the preamble

to the notice; it should have referenced

BLA 94–148 as the applicable Dutch

airworthiness directive. However, since

that information is not restated in this

final rule, no specific change is

necessary.

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 with the changes

previously described. The FAA has

determined that these changes will

neither increase the economic burden

on any operator nor increase the scope

of the AD.

Cost Impact

The FAA estimates that 6 Fokker

Model 100, 200, 300, 400, 500, 600, and

700 series airplanes of U.S. registry will

be affected by this AD.

The required inspection will take

approximately 4 work hours per

airplane to accomplish, at an average

labor rate of $60 per work hour. Based

on these figures, the cost impact of the

required inspection action on U.S.

operators is estimated to be $240 per

airplane.

The required replacement will take

approximately 19 work hours per

airplane to accomplish, at an average

labor rate of $60 per work hour. The

cost of required parts will be nominal.

Based on these figures, the cost impact

of the required replacement on U.S.

operators is estimated to be $1,140 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,
1278 Federal Register / Vol. 62, No. 6 / Thursday, January 9, 1997 / Rules and Regulations

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:

97–01–08 Fokker: Amendment 39–9879.

Docket 96–NM–28–AD.

Applicability: Model F27 Mark 100, 200,

300, 400, 500, 600, and 700 series airplanes,

serial numbers 10653 through 10692

inclusive; on which Part 1 of the

Accomplishment Instructions of Fokker

Service Bulletins F27/57–68 and F27/57–70

has not been accomplished; 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 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 loose or missing rivets at the

rib-to-stringer connections of the upper and

lower wing skin at stringers 5 and 6, which

could result in reduced structural integrity of

the wings; accomplish the following:

(a) Except as provided by paragraph (c) of

this AD: Prior to the accumulation of 10,000

total flight cycles, or within 2 months after

the effective date of this AD, whichever

occurs later, perform a one-time visual

inspection to detect missing rivet heads or

loose rivets of the applicable stringer-to-rib

connections in the upper and lower skin, in

accordance with Part 2 of the

Accomplishment Instructions of Fokker

Service Bulletin F27/57–74, dated November

15, 1994.

(1) If no missing rivet head and no loose

rivet is detected, no further action is required

by paragraph (a) of this AD.

(2) If any missing rivet head or loose rivet

is detected, prior to further flight, repair the

affected rib-to-stringer connection, in

accordance with Part 1 of the

Accomplishment Instructions of the service

bulletin.

(b) Prior to the accumulation of 10,000

total flight cycles, or within 1 year after the

effective date of this AD, whichever occurs

later, replace rivets having part number (P/

N) MS20600AD4W2 with new rivets having

P/N CR3553P4 in all applicable rib-tostringer connections of the upper and lower

wings, in accordance with Part 1 of the

Accomplishment Instructions of Fokker

Service Bulletin F27/57–74, dated November

15, 1994.

(c) Airplanes on which the replacement

required by paragraph (b) of this AD is

performed within the compliance time

specified in paragraph (a) of this AD are not

required to accomplish the inspection

required by paragraph (a) 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 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 2: Information concerning the

existence of approved alternative methods of

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 inspection, repair, and replacement

shall be done in accordance with Fokker

Service Bulletin F27/57–74, dated November

15, 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 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

February 13, 1997.

Issued in Renton, Washington, on January

2, 1997.

S. R. Miller,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 97–362 Filed 1–8–97; 8:45 am]

BILLING CODE 4910–13–U

14 CFR Part 39

[Docket No. 96–SW–03–AD; Amendment

39–9877; AD 97–01–06]

RIN 2120–AA64

Airworthiness Directives; Bell

Helicopter Textron, Inc.-Manufactured

Restricted Category Model HH–1K, TH–

1F, TH–1L, UH–1A, UH–1B, UH–1E,

UH–1F, UH–1H, UH–1L, and UH–1P

Helicopters

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD),

applicable to Bell Helicopter Textron,

Inc. (BHTI)-manufactured restricted

category Model HH–1K, TH–1F, TH–1L,

UH–1A, UH–1B, UH–1E, UH–1F, UH–

1H, UH–1L, and UH–1P helicopters,

that requires a one-time inspection of

the tail rotor slider (slider) to verify that

it was manufactured with the correct

outside diameter. This amendment is

prompted by a United States (U.S.)

Army Safety of Flight message that

reports that some sliders may have been

improperly manufactured with an

undersized wall thickness by U.S. Army

vendors. The actions specified by this

AD are intended to prevent fatigue

failure of the slider, which could cause

loss of tail rotor control and subsequent

loss of control of the helicopter.

EFFECTIVE DATE: February 13, 1997.

FOR FURTHER INFORMATION CONTACT: Mr.

Uday Garadi, Aerospace Engineer,

Rotorcraft Certification Office,

Rotorcraft Directorate, FAA, 2601

Meacham Blvd., Fort Worth, Texas

76137; telephone (817) 222–5157, fax

(817) 222–5961.

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 Bell Helicopter