Federal Register / Vol. 63, No. 102 /Thursday, May 28, 1998 / Proposed Rules 29151

propeller de-ice system, this proposal

would require the repair of the EICAS

to be accomplished in accordance with

a method approved by the FAA.

Cost Impact

The FAA estimates that 50 airplanes

of U.S. registry would be affected by this

proposed AD, that it would take

approximately 1 work hour per airplane

to accomplish the proposed inspection,

at an average labor rate of $60 per work

hour. Based on these figures, the cost

impact of the inspection proposed by

this AD on U.S. operators is estimated

to be $3,000, or $60 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:

Dornier Luftfahrt GmbH: Docket 98–NM–

112–AD.

Applicability: All Model 328–100 series

airplanes, 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 prevent failure of the engine indication

and crew alert system (EICAS) to provide a

warning to the flightcrew in the event of

failure of the propeller de-ice system, which

could result in damage to the airplane and

consequent loss of controllability of the

airplane, accomplish the following:

(a) Within 30 days after the effective date

of this AD, perform a one-time inspection of

the propeller de-ice system to verify the

proper functioning of the EICAS for the deice system, in accordance with Dornier Alert

Service Bulletin ASB–328–30–013, Revision

1, dated February 21, 1997.

(b) If the inspection required by paragraph

(a) of this AD indicates that the EICAS is

malfunctioning, prior to further flight, repair

the EICAS in accordance with a method

approved by the Manager, International

Branch, ANM–116, FAA, Transport Airplane

Directorate.

(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. 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 German airworthiness directive 97–066,

dated March 13, 1997.

Issued in Renton, Washington, on May 20,

1998.

Darrell M. Pederson,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 98–14027 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–NM–100–AD]

RIN 2120–AA64

Airworthiness Directives; Boeing

Model 747–100, 747–200, and 747–SP

Series Airplanes and Military Type E–

4B 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 Boeing Model 747–100, –200,

and 747–SP series airplanes and

military type E–4B airplanes. This

proposal would require repetitive

inspections to detect cracking of the

wing front spar web, and repair of

cracked structure. This proposal also

provides for optional terminating action

for the repetitive inspection

requirements. This proposal is

prompted by reports indicating that

fatigue cracks were found on the aft

surface of the wing front spar web. The

actions specified by the proposed AD

are intended to detect and correct such

fatigue cracking, which could result in

a fuel leak, and consequent increased

risk of a fire.

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. 97–NM–

100–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
29152 Federal Register / Vol. 63, No. 102 /Thursday, May 28, 1998 / Proposed Rules

Boeing Commercial Airplane Group,

P.O. Box 3707, Seattle, Washington

98124–2207. This information may be

examined at the FAA, Transport

Airplane Directorate, 1601 Lind

Avenue, SW., Renton, Washington.

FOR FURTHER INFORMATION CONTACT:

Tamara L. Anderson, Aerospace

Engineer, Airframe Branch, ANM–120S,

FAA, Transport Airplane Directorate,

Seattle Aircraft Certification Office,

1601 Lind Avenue, SW., Renton,

Washington 98055–4056; telephone

(425) 227–2771; fax (425) 227–1181.

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 97–NM–100–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.

97–NM–100–AD, 1601 Lind Avenue,

SW., Renton, Washington 98055–4056.

Discussion

The FAA has received reports

indicating that operators have found

numerous fatigue cracks on the aft

surface of the front spar web on Boeing

Model 747 series airplanes. The cracks

were found inside the wing fuel tank at

Front Spar Station Inboard (FSSI) 688

where the inboard nacelle rib post and

the 670 rib post attach to the web of the

front spar. All of the cracks were found

between these two rib posts inside the

wing fuel tank. Metallurgical analyses

indicate that the cracks were initiated

by fatigue on the aft surface of the front

spar web. The analyses also indicate

that the various fatigue cracks initiated

on the web itself, and not at the edges

of the adjacent fastener holes. Such

fatigue cracking, if not detected and

corrected, could result in a fuel leak and

consequent increased risk of a fire.

Explanation of Relevant Service

Information

The FAA has reviewed and approved

Boeing Service Bulletin 747–57A2303,

Revision 1, dated September 25, 1997,

which describes procedures for

repetitive ultrasonic inspections to

detect cracking of the wing front spar

web at the fastener rows behind and

between the upper link fittings for the

number 2 and 3 engine struts; and

repair, if necessary. The service bulletin

also describes procedures for an

optional terminating modification,

which, if accomplished, would

eliminate the need for the repetitive

inspections. The optional terminating

modification involves replacing the

cracked spar web with a shot-peened

spar web. Accomplishment of the

actions specified in the 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 accomplishment of the actions

specified in the service bulletin

described previously, except as

discussed below.

Differences Between Proposed Rule and

Service Bulletin

Operators should note that, although

the service bulletin specifies that the

manufacturer may be contacted for

disposition of certain repair conditions,

this proposal would require the repair of

those conditions to be accomplished in

accordance with a method approved by

the FAA.

Optional Terminating Modification

This proposed AD also would provide

for an optional terminating modification

of the wing front spar web . The FAA

has determined that the repetitive

inspections proposed by this AD can be

allowed to continue in lieu of

accomplishment of a terminating action.

In making this determination, the FAA

considers that, in this case, long-term

continued operational safety will be

adequately assured by accomplishing

the repetitive inspections to detect

fatigue cracking before it represents a

hazard to the airplane.

Cost Impact

There are approximately 190

airplanes of the affected design in the

worldwide fleet. The FAA estimates that

95 airplanes of U.S. registry would be

affected by this proposed AD, that it

would take approximately 64 work

hours per airplane to accomplish the

proposed inspection, at an average labor

rate of $60 per work hour. Based on

these figures, the cost impact of the

inspection proposed by this AD on U.S.

operators is estimated to be $364,800, or

$3,840 per airplane, per inspection

cycle.

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.

Should an operator elect to

accomplish the optional terminating

modification, it would take

approximately 518 work hours per

airplane to accomplish the modification,

at an average labor rate of $60 per work

hour. Required parts would cost

approximately $17,000 per airplane.

Based on these figures, the cost impact

of the optional terminating modification

proposed by this AD is estimated to be

$48,080 per airplane.

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
Federal Register / Vol. 63, No. 102 /Thursday, May 28, 1998 / Proposed Rules 29153

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:

Boeing: Docket 97–NM–100–AD.

Applicability: Model 747–100, 747–200,

and 747–SP series airplanes and military

type E–4B airplanes; as listed in Boeing

Service Bulletin 747–57A2303, Revision 1,

dated September 25, 1997; 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 detect and correct fatigue cracking of

the wing front spar web, which could result

in a fuel leak, and consequent increased risk

of a fire, accomplish the following:

(a) Perform an ultrasonic inspection to

detect cracking of the wing front spar

web at the fastener rows behind and

between the upper link fittings for the

number 2 and 3 engine struts, in

accordance with the Accomplishment

Instructions of Boeing Service Bulletin

747–57A2303, Revision 1, dated

September 25, 1997, at the time

specified in paragraph (a)(1) or (a)(2) of

this AD, as applicable.

(1) For airplanes identified as Group

1, 2, 3, or 5 in the alert service bulletin:

Inspect prior to the accumulation of

12,500 total flight cycles, or within 15

months after the effective date of this

AD, whichever occurs later. Repeat the

inspection thereafter at intervals not to

exceed 2,200 flight cycles.

(2) For airplanes identified as Group

4, 6, 7, 8, 9, or 10 in the alert service

bulletin: Inspect prior to the

accumulation of 18,000 total flight

cycles, or within 15 months after the

effective date of this AD, whichever

occurs later. Repeat the inspection

thereafter at intervals not to exceed

3,000 flight cycles.

(b) If any crack is found during any

inspection required by paragraph (a) of

this AD, prior to further flight,

accomplish either paragraph (b)(1) or

(b)(2) of this AD.

(1) Accomplish the terminating action

in accordance with the Accomplishment

Instructions of Boeing Service Bulletin

747–57A2303, Revision 1, dated

September 25, 1997. Accomplishment of

this action constitutes terminating

action for the repetitive inspection

requirements of this AD; or

(2) Repair in accordance with a

method approved by the Manager,

Seattle Aircraft Certification Office

(ACO), FAA, Transport Airplane

Directorate.

(c) Replacement of the affected wing

front spar web with a new shot-peened

wing front spar web in accordance with

the Accomplishment Instructions of

Boeing Service Bulletin 747–57A2303,

Revision 1, dated September 25, 1997,

constitutes terminating action for the

repetitive inspection requirements 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, Seattle

ACO. Operators shall submit their

requests through an appropriate FAA

Principal Maintenance Inspector, who

may add comments and then send it to

the Manager, Seattle ACO.

Note 2: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Seattle ACO.

(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.

Issued in Renton, Washington, on May 20,

1998.

Darrell M. Pederson,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 98–14028 Filed 5–27–98; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 98–NM–116–AD]

RIN 2120–AA64

Airworthiness Directives; Airbus Model

A300, A310, and A300–600 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 Airbus Model A300, A310, and

A300–600 series airplanes. This

proposal would require repetitive

detailed visual inspections to detect

cracks in the pylon thrust and sideload

fitting of the wing, and replacement of

any cracked pylon thrust and sideload

fitting with a new fitting. 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 detect and correct

cracks in the pylon thrust and sideload

fitting of the wing, which could result

in reduced structural integrity of the

airplane.

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–

116–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

Airbus Industrie, 1 Rond Point Maurice

Bellonte, 31707 Blagnac Cedex, France.

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,