Federal Register / Vol. 63, No. 102 /Thursday, May 28, 1998 / Proposed Rules 29157

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 §§ 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.

Issued in Renton, Washington, on May 20,

1998.

Darrell M. Pederson,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 98–14039 Filed 5–27–98; 8:45 am]

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 98–NM–101–AD]

RIN 2120–AA64

Airworthiness Directives; Fokker

Model F.28 Mark 0100 Series Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Notice of proposed rulemaking

(NPRM).

SUMMARY: This document proposes the

adoption of a new airworthiness

directive (AD) that is applicable to

certain Fokker Model F.28 Mark 0100

series airplanes. This proposal would

require a one-time visual inspection and

a one-time eddy current and/or dye

penetrant inspection of the nose landing

gear (NLG) main fitting to detect

cracking; and rework of the NLG main

fitting, if necessary. This proposal is

prompted by issuance of mandatory

continuing airworthiness information by

a foreign civil airworthiness authority.

The actions specified by the proposed

AD are intended to prevent cracking of

the NLG main fitting, which could lead

to collapse of the NLG during takeoff

and landing and possible injury to the

flightcrew and passengers.

DATES: Comments must be received by

June 29, 1998.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, ANM–114,

Attention: Rules Docket No. 98–NM–

101–AD, 1601 Lind Avenue, SW.,

Renton, Washington 98055–4056.

Comments may be inspected at this

location between 9:00 a.m. and 3:00

p.m., Monday through Friday, except

Federal holidays.

The service information referenced in

the proposed rule may be obtained from

Fokker Services B.V., Technical Support

Department, P. O. Box 75047, 1117 ZN

Schiphol Airport, the Netherlands. This

information may be examined at the

FAA, Transport Airplane Directorate,

1601 Lind Avenue, SW., Renton,

Washington.

FOR FURTHER INFORMATION CONTACT:

Norman B. Martenson, Manager,

International Branch, ANM–116, FAA,

Transport Airplane Directorate, 1601

Lind Avenue, SW., Renton, Washington

98055–4056; telephone (425) 227–2110;

fax (425) 227–1149.

SUPPLEMENTARY INFORMATION:

Comments Invited

Interested persons are invited to

participate in the making of the

proposed rule by submitting such

written data, views, or arguments as

they may desire. Communications shall

identify the Rules Docket number and

be submitted in triplicate to the address

specified above. All communications

received on or before the closing date

for comments, specified above, will be

considered before taking action on the

proposed rule. The proposals contained

in this notice may be changed in light

of the comments received.

Comments are specifically invited on

the overall regulatory, economic,

environmental, and energy aspects of

the proposed rule. All comments

submitted will be available, both before

and after the closing date for comments,

in the Rules Docket for examination by

interested persons. A report

summarizing each FAA-public contact

concerned with the substance of this

proposal will be filed in the Rules

Docket.

Commenters wishing the FAA to

acknowledge receipt of their comments

submitted in response to this notice

must submit a self-addressed, stamped

postcard on which the following

statement is made: ‘‘Comments to

Docket Number 98–NM–101–AD.’’ The

postcard will be date stamped and

returned to the commenter.

Availability of NPRMs

Any person may obtain a copy of this

NPRM by submitting a request to the

FAA, Transport Airplane Directorate,

ANM–114, Attention: Rules Docket No.

98–NM–101–AD, 1601 Lind Avenue,

SW., Renton, Washington 98055–4056.

Discussion

The Rijksluchtvaartdienst (RLD),

which is the airworthiness authority for

the Netherlands, notified the FAA that

an unsafe condition may exist on certain

Fokker Model F.28 Mark 0100 series

airplanes, equipped with certain

Messier-Dowty (formerly Dowty Rotol)

nose landing gears (NLG). The RLD

advises that it received a report

indicating that the NLG of an airplane

broke off just below the NLG pintle pins

immediately after touchdown of the

nose wheel. The nose section of the

aircraft came to rest on the fuselage and

remaining portion of the NLG.

Subsequently, the airline involved

performed a detailed visual inspection

of the NLG main fittings on all airplanes

in its fleet and identified three more

suspect NLG main fittings. Investigation

of these fittings revealed that the

cracking had originated on the inner

side of the right-hand downlock plunger

support web. The total number of flight

cycles on the airplanes with the cracked

NLG main fittings ranged from 9,300 to

17,600. The exact cause of the cracking

has not been determined at this time.

Such cracking of the NLG main fitting,

if not corrected, could lead to collapse

of the NLG during takeoff and landing,

and possible injury to the flightcrew and

passengers.

Explanation of Relevant Service

Information

The manufacturer has issued Fokker

Service Bulletin SBF100–32–112, dated

November 14, 1997, and Messier-Dowty

has issued Service Bulletin F100–32–92,

dated November 14, 1997. These service

bulletins describe procedures for a onetime visual inspection of the NLG main

fitting to detect cracking. The service

bulletins also describe procedures for a

one-time eddy current and/or dye

penetrant inspection if cracking is

suspected following accomplishment of

the visual inspection, and rework of the

NLG main fitting, if cracking is found.

The RLD classified these service

bulletins as mandatory and issued

Dutch airworthiness directive BLA

1997–116 (A), dated November 28,

1997, in order to assure the continued

airworthiness of these airplanes in the

Netherlands.

FAA’s Conclusions

This airplane model is manufactured

in the Netherlands and is type

certificated for operation in the United

States under the provisions of § 21.29 of

the Federal Aviation Regulations (14

CFR 21.29) and the applicable bilateral

airworthiness agreement. Pursuant to

this bilateral airworthiness agreement,
29158 Federal Register / Vol. 63, No. 102 /Thursday, May 28, 1998 / Proposed Rules

the RLD has kept the FAA informed of

the situation described above. The FAA

has examined the findings of the RLD,

reviewed all available information, and

determined that AD action is necessary

for products of this type design that are

certificated for operation in the United

States.

Explanation of Requirements of

Proposed Rule

Since an unsafe condition has been

identified that is likely to exist or

develop on other airplanes of the same

type design registered in the United

States, the proposed AD would require

accomplishment of the actions specified

in the service bulletins described

previously.

This proposed AD also requires that

operators report the results of the onetime inspection to Fokker Services B.V.

Because the cause of the addressed

cracking is not currently known, the

intent of these required inspection

reports is to enable Fokker to determine

how widespread such cracking

problems may be in the affected fleet.

Based on the results of these reports,

further corrective action may be

warranted.

Differences Between the Proposed AD

and the Dutch Airworthiness Directive

Operators should note that the

parallel Dutch airworthiness directive

specifies that the actions be

accomplished for airplanes on which

the nose landing gear (NLG) has

accumulated more than 8,000 total flight

cycles. However, because the exact

cause of the cracking remains unknown,

the FAA would require compliance with

the actions in this proposed AD for all

airplanes of this type design, including

those that have accumulated less than

8,000 total flight cycles as of the

effective date of this proposed AD, in

order to ensure the integrity of the entire

fleet.

Cost Impact

The FAA estimates that 127 airplanes

of U.S. registry would be affected by this

proposed AD.

It would take approximately 2 work

hours per airplane to accomplish the

proposed visual inspection, at an

average labor rate of $60 per work hour.

Based on these figures, the cost impact

of the proposed visual inspection on

U.S. operators is estimated to be

$15,240, or $120 per airplane.

It would take approximately 2 work

hours per airplane to accomplish the

proposed eddy current and/or dye

penetrant inspection, at an average labor

rate of $60 per work hour. Based on

these figures, the cost impact of the

proposed eddy current and/or dye

penetrant inspection on U.S. operators

is estimated to be $15,240, or $120 per

airplane.

The cost impact figures discussed

above are based on assumptions that no

operator has yet accomplished any of

the proposed 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 proposed herein

would 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

proposal would not have sufficient

federalism implications to warrant the

preparation of a Federalism Assessment.

For the reasons discussed above, I

certify that this proposed regulation (1)

is not a ‘‘significant regulatory action’’

under Executive Order 12866; (2) is not

a ‘‘significant rule’’ under the DOT

Regulatory Policies and Procedures (44

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

promulgated, 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 draft

regulatory 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, Safety.

The Proposed Amendment

Accordingly, pursuant to the

authority delegated to me by the

Administrator, the Federal Aviation

Administration proposes to amend 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:

Fokker Services B.V.: Docket 98–NM–101–

AD

Applicability: Model F.28 Mark 0100 series

airplanes; equipped with Messier-Dowty

Nose Landing Gear (NLG) having part

number (P/N) 201071001 or P/N 201071002,

on which the NLG main fitting has not been

overhauled in accordance with Component

Maintenance Manual 32–20–51; 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 (e) 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 cracking of the NLG main

fitting, which could lead to collapse of the

NLG during takeoff and landing and possible

injury to the flightcrew and passengers,

accomplish the following:

(a) Perform a one-time visual inspection to

detect cracking of the NLG main fitting, in

accordance with Fokker Service Bulletin

SBF100–32–112, dated November 14, 1997,

at the applicable time specified in either

paragraph (a)(1) or (a)(2) of this AD. If any

cracking is found, prior to further flight,

accomplish the requirements of paragraph (b)

of this AD.

(1) For airplanes that have accumulated

less than 15,000 total flight cycles as of the

effective date of this AD: Inspect prior to the

accumulation of 8,000 total flight cycles, or

within 90 days after the effective date of this

AD, whichever occurs later.

(2) For airplanes that have accumulated

15,000 or more total flight cycles as of the

effective date of this AD: Inspect within 30

days after the effective date of this AD.

(b) Perform a one-time eddy current and/

or dye penetrant inspection to detect

cracking of the NLG main fitting, in

accordance with Messier-Dowty Service

Bulletin F100–32–92, dated November 14,

1997, at the applicable time specified in

either paragraph (b)(1) or (b)(2) of this AD.

Accomplishment of the inspection required

by paragraph (b) of this AD, if accomplished

prior to the inspection required by paragraph

(a) of this AD, terminates the inspection

required by paragraph (a) of this AD.

(1) For airplanes that have accumulated

less than 15,000 total flight cycles as of the

effective date of this AD: Inspect prior to the

accumulation of 8,000 total flight cycles, or

within 180 days after the effective date of this

AD, whichever occurs later.
Federal Register / Vol. 63, No. 102 /Thursday, May 28, 1998 / Proposed Rules 29159

(2) For airplanes that have accumulated

15,000 or more total flight cycles as of the

effective date of this AD: Inspect within 60

days after the effective date of this AD.

(c) If any crack is detected during the

inspection required by paragraph (b) of this

AD, prior to further flight, rework the NLG

main fitting in accordance with MessierDowty Service Bulletin F100–32–92, dated

November 14, 1997.

(d) Within 7 days after accomplishing the

inspection required by either paragraph (a) or

(b) of this AD, submit a report of the

inspection results (both positive and negative

findings) to Fokker Services B.V., Technical

Support Department, P.O. Box 75047, 1117

ZN Schiphol Airport, the Netherlands.

Information collection requirements

contained in this regulation have been

approved by the Office of Management and

Budget (OMB) under the provisions of the

Paperwork Reduction Act of 1980 (44 U.S.C.

3501 et seq.) and have been assigned OMB

Control Number 2120–0056.

(e) 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,

International Branch, ANM–116, 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, International Branch,

ANM–116.

Note 2: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the International Branch,

ANM–116.

(f) 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.

Note 3: The subject of this AD is addressed

in Dutch airworthiness directive BLA 1997–

116 (A), dated November 28, 1997.

Issued in Renton, Washington, on May 20,

1998.

Darrell M. Pederson,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 98–14038 Filed 5–27–98; 8:45 am]

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 97–CE–112–AD]

RIN 2120–AA64

Airworthiness Directives; Pilatus

Britten-Norman Ltd. BN–2, BN–2A, BN–

2B, and BN–2T Series Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Supplemental notice of

proposed rulemaking (NPRM);

Reopening of the comment period.

SUMMARY: This document proposes to

revise an earlier proposed airworthiness

directive (AD) that would have required

replacing the washers on the attachment

bolts of the lower fitting of the main

landing gear (MLG) on certain Pilatus

Britten-Norman Ltd. (Pilatus BrittenNorman) BN–2, BN–2A, BN–2B, and

BN–2T series airplanes. The proposed

AD was the result of mandatory

continuing airworthiness information

(MCAI) issued by the airworthiness

authority for the United Kingdom. The

actions specified by the proposed AD

are intended to prevent the bolts that

attach the lower fitting of the MLG to

the nacelle from becoming threadbound,

which could result in structural failure

of the MLG with consequent loss of

control of the airplane during takeoff,

taxi, or landing operations. Since

issuing the NPRM, the Federal Aviation

Administration (FAA) has realized that

the Model BN–2T–4R airplanes were

inadvertently omitted from the

proposed AD. In addition, Pilatus

Britten-Norman has revised the service

information to include replacing the

attachment bolts and nuts of the lower

fitting of the MLG instead of re-using

the existing bolts and nuts. This service

information also adjusts the torque

values of the nuts. The FAA has

determined that the procedures

included in the revised service

information should be incorporated into

the proposed AD, and that the comment

period for the proposal should be

reopened and the public should have

additional time to comment.

DATES: Comments must be received on

or before July 3, 1998.

ADDRESSES: Submit comments in

triplicate to the FAA, Central Region,

Office of the Regional Counsel,

Attention: Rules Docket No. 97–CE–

112–AD, Room 1558, 601 E. 12th Street,

Kansas City, Missouri 64106. Comments

may be inspected at this location

between 8 a.m. and 4 p.m., Monday

through Friday, holidays excepted.

Service information that applies to the

proposed AD may be obtained from

Pilatus Britten-Norman Limited,

Bembridge, Isle of Wight, United

Kingdom PO35 5PR; telephone: 44–1983

872511; facsimile: 44–1983 873246.

This information also may be examined

at the Rules Docket at the address above.

FOR FURTHER INFORMATION CONTACT: Mr.

Roger Chudy, Aerospace Engineer,

Small Airplane Directorate, Aircraft

Certification Service, 1201 Walnut, suite

900, Kansas City, Missouri 64106;

telephone: (816) 426–6932; facsimile:

(816) 426–2169

SUPPLEMENTARY INFORMATION:

Comments Invited

Interested persons are invited to

participate in the making of the

proposed rule by submitting such

written data, views, or arguments as

they may desire. Communications

should identify the Rules Docket

number and be submitted in triplicate to

the address specified above. All

communications received on or before

the closing date for comments, specified

above, will be considered before taking

action on the proposed rule. The

proposals contained in this

supplemental notice may be changed in

light of the comments received.

Comments are specifically invited on

the overall regulatory, economic,

environmental, and energy aspects of

the proposed rule. All comments

submitted will be available, both before

and after the closing date for comments,

in the Rules Docket for examination by

interested persons. A report that

summarizes each FAA-public contact

concerned with the substance of this

proposal will be filed in the Rules

Docket.

Commenters wishing the FAA to

acknowledge receipt of their comments

submitted in response to this

supplemental notice must submit a selfaddressed, stamped postcard on which

the following statement is made:

‘‘Comments to Docket No. 97–CE–112–

AD.’’ The postcard will be date stamped

and returned to the commenter.

Availability of Supplemental NPRM’s

Any person may obtain a copy of this

supplemental NPRM by submitting a

request to the FAA, Central Region,

Office of the Regional Counsel,

Attention: Rules Docket No. 97–CE–

112–AD, Room 1558, 601 E. 12th Street,

Kansas City, Missouri 64106.

Discussion

A proposal to amend part 39 of the

Federal Aviation Regulations (14 CFR

part 39) to include an AD that would

apply to certain Pilatus Britten-Norman

BN–2, BN–2A, BN–2B, and BN–2T

series airplanes was published in the

Federal Register as a notice of proposed

rulemaking (NPRM) on March 19, 1998

(63 FR 13379). The NPRM proposed to

require replacing the washers on the

attachment bolts of the lower fitting of

the MLG. Accomplishment of the

proposed action as specified in the

NPRM would be in accordance with

Pilatus Britten-Norman Service Bulletin

BN–2/SB.231, Initial Issue, dated

October 17, 1996.