Federal Register / Vol. 63, No. 102 /Thursday, May 28, 1998 / Proposed Rules 29155

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:

Airbus Industrie: Docket 98–NM–116–AD.

Applicability: Model A300 series airplanes,

as listed in Airbus Service Bulletin A300–57–

0232, Revision 01, dated January 12, 1998;

Model A310 series airplanes, as listed in

Airbus Service Bulletin A310–57–2075,

Revision 01, dated January 12, 1998; and

Model A300–600 series airplanes, as listed in

Airbus Service Bulletin A300–57–6079,

Revision 02, dated January 12, 1998;

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 (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 detect and correct cracks in the pylon

thrust and sideload fitting of the wing, which

could result in reduced structural integrity of

the airplane, accomplish the following:

(a) Prior to the accumulation of 2,800 total

flight cycles, or within 18 months after the

effective date of this AD, whichever occurs

later, perform a detailed visual inspection to

detect cracks in the pylon thrust and sideload

fitting of the wing, in accordance with Airbus

Service Bulletin A300–57–0232, Revision 01

(for Model A300 series airplanes); A310–57–

2075, Revision 01 (for Model A310 series

airplanes); or A300–57–6079, Revision 02

(for Model A300–600 series airplanes); all

dated January 12, 1998; as applicable. Repeat

the detailed visual inspection thereafter at

intervals not to exceed 2,800 flight cycles.

(b) If any crack is detected during any

inspection required by paragraph (a), prior to

further flight, replace the pylon thrust and

sideload fitting with a new fitting in

accordance with Airbus Service Bulletin

A300–57–0232, Revision 01 (for Model A300

series airplanes); A310–57–2075, Revision 01

(for Model A310 series airplanes); or A300–

57–6079, Revision 02 (for Model A300–600

series airplanes); all dated January 12, 1998;

as applicable. Thereafter, continue the

inspections in accordance with the

requirements of paragraph (a) of this AD.

(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,

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.

(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.

Note 3: The subject of this AD is addressed

in French airworthiness directive 97–358–

232(B), dated November 19, 1997.

Issued in Renton, Washington, on May 20,

1998.

Darrell M. Pederson,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 98–14040 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–136–AD]

RIN 2120–AA64

Airworthiness Directives; McDonnell

Douglas Model MD–90–30 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 McDonnell Douglas Model MD–

90–30 series airplanes. This proposal

would require modification of the

wiring of the strake ice protection

system (SIPS). This proposal is

prompted by a report of a fire in the

electrical and electronic compartment of

a Model MD–90–30 series airplane. The

actions specified by the proposed AD

are intended to prevent an electrical

short circuit of the wiring of the SIPS,

which could result in a fire in the

electrical and electronic compartment of

the airplane.

DATES: Comments must be received by

July 13, 1998.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, ANM–114,

Attention: Rules Docket No. 98–NM–

136–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

The Boeing Company, Douglas Products

Division, 3855 Lakewood Boulevard,

Long Beach, California 90846,

Attention: Technical Publications

Business Administration, Dept. C1–L51

(2–60). This information may be

examined at the FAA, Transport

Airplane Directorate, 1601 Lind

Avenue, SW., Renton, Washington; or at

the FAA, Transport Airplane

Directorate, Los Angeles Aircraft

Certification Office, 3960 Paramount

Boulevard, Lakewood, California.

FOR FURTHER INFORMATION CONTACT:

George Y. Mabuni, Aerospace Engineer,

Systems and Equipment Branch, ANM–

130L, FAA, Transport Airplane

Directorate, Los Angeles Aircraft

Certification Office, 3960 Paramount

Boulevard, Lakewood, California

90712–4137; telephone (562) 627–5341;

fax (562) 627–5210.

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
29156 Federal Register / Vol. 63, No. 102 /Thursday, May 28, 1998 / Proposed Rules

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–136–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–136–AD, 1601 Lind Avenue,

SW., Renton, Washington 98055–4056.

Discussion

The FAA received a report of a fire in

the electrical and electronic

compartment of a Model MD–90–30

series airplane which resulted in injury

to a mechanic. Investigation revealed

that the fire was caused by an electrical

short circuit at the termination of a wire

shield near the connector of the strake

controller. The short circuit has been

attributed to damaged insulation of

certain wiring of the strake ice

protection system (SIPS). This wiring

insulation was damaged during

manufacture because a shield

termination was not being performed

correctly. For this reason, this same

condition may exist on other airplanes

of the same type. Damaged insulation of

the wiring of the SIPS could fail, which

could cause an electrical short circuit

between the exposed wire conductors

and the shielded ground. Such an

electrical short circuit of the wiring of

the SIPS, if not corrected, could result

in a fire in the electrical and electronic

compartment of the airplane.

Explanation of Relevant Service

Information

The FAA has reviewed and approved

McDonnell Douglas Alert Service

Bulletin MD90–30A021, dated March

31, 1998, which describes procedures

for modification of the wiring of the

SIPS at the connectors of the strakes and

the strake controller. The modification

involves removing the pigtail ground

wires at the connectors of the strakes

and the strake controller, installing

shrink tubing over each power wire, and

performing a resistance test of the

electrical insulation. (The alert service

bulletin refers to this resistance test as

a ‘‘resistance check.’’) If any strake

heating wiring fails the resistance test,

the discrepant wiring is to be replaced

with new wiring and retested.

Accomplishment of the actions

specified in the alert service bulletin is

intended to adequately address the

identified unsafe condition.

Explanation of Requirements of

Proposed Rule

Since an unsafe condition has been

identified that is likely to exist or

develop on other products of this same

type design, the proposed AD would

require modification of the wiring of the

strake ice protection system. The actions

would be required to be accomplished

in accordance with the alert service

bulletin described previously.

Cost Impact

There are approximately 66 Model

MD–90–30 series airplanes of the

affected design in the worldwide fleet.

The FAA estimates that 23 airplanes of

U.S. registry would be affected by this

proposed AD, that it would take

approximately 15 work hours per

airplane to accomplish the proposed

actions, and that the average labor rate

is $60 per work hour. The cost of the

required parts would be minimal. Based

on these figures, the cost impact of the

proposed AD on U.S. operators is

estimated to be $20,700, or $900 per

airplane.

The cost impact figure discussed

above is 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:

McDonnell Douglas: Docket 98–NM–136–

AD.

Applicability: Model MD–90–30 series

airplanes, as listed in McDonnell Douglas

Alert Service Bulletin MD90–30A021, dated

March 31, 1998; 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 (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 an electrical short circuit of the

wiring of the strake ice protection system

(SIPS), which could result in a fire in the

electrical and electronic compartment of the

airplane, accomplish the following:

(a) Within 180 days after the effective date

of this AD, modify the wiring of the SIPS and

perform a resistance test of the electrical

insulation in accordance with McDonnell

Douglas Alert Service Bulletin MD90–

30A021, dated March 31, 1998. If any strake

heating wiring fails the resistance test, prior

to further flight, replace the discrepant

wiring with new wiring, and repeat the

resistance test, in accordance with the alert

service bulletin.

(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),
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,