36628 Federal Register / Vol. 63, No. 129 /Tuesday, July 7, 1998 / Proposed Rules

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:

Aerospatiale: Docket 98–NM–158–AD.

Applicability: All Model SN–601 (Corvette)

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 corrosion, cracking, or rupture

of the support arms of the aileron balance

weights, which may cause reduced flutter

damping or jamming of the aileron, and

consequent reduced controllability of the

airplane, accomplish the following:

(a) Within 10 landings or 10 days after the

effective date of this AD, whichever occurs

later: Perform a detailed visual inspection to

detect corrosion, cracking, or rupture of the

support arms of the aileron balance weights,

in accordance with Aerospatiale All

Operators Telex (AOT) A/BTE/AM 499.368/

95, dated March 7, 1995.

(1) If no corrosion, cracking, or rupture is

detected on the support arms, repeat the

inspection thereafter at intervals not to

exceed 200 flight hours or 6 months,

whichever occurs earlier.

(2) If any corrosion, cracking, or rupture is

detected on the support arms: Except as

provided by paragraph (b) of this AD, prior

to further flight, repair in accordance with

the AOT. Accomplishment of this repair

constitutes terminating action for the

repetitive inspection requirements of this

AD.

(b) If any corrosion, cracking, or rupture is

detected on the support arms, and

Aerospatiale All Operators Telex (AOT) A/

BTE/AM 499.368/95, dated March 7, 1995,

specifies to contact Aerospatiale for an

appropriate repair: Prior to further flight,

repair in accordance with a method approved

by either the Manager, International Branch,

ANM–116, FAA, Transport Airplane

Directorate; or the Direction Ge ́ne ́rale de

l’Aviation Civile (or its delegated agent).

(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 French airworthiness directive 95–054–

019 (B), dated March 29, 1995.

Issued in Renton, Washington, on June 30,

1998.

Vi L. Lipski,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 98–17956 Filed 7–6–98; 8:45 am]

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 97–NM–185–AD]

RIN 2120–AA64

Airworthiness Directives; Boeing

Model 747 Series Airplanes Equipped

with Pratt & Whitney Model JT9D–70

Engines

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Notice of proposed rulemaking

(NPRM).

SUMMARY: This document proposes the

supersedure of an existing airworthiness

directive (AD), applicable to certain

Boeing Model 747 series airplanes, that

currently requires repetitive inspections

to detect fatigue cracking of the spring

beams on the outboard struts;

replacement of cracked spring beams

with new or serviceable spring beams;

and follow-on actions. That action also

provides an optional terminating action

for the repetitive inspections. This

action would remove that optional

terminating action, and would require a

new terminating action. This proposal is

prompted by the development of an

improved process for manufacturing

titanium spring beams that will

eliminate the embedded porosity flaws

in the existing spring beams from which

fatigue cracking can originate. The

actions specified by this proposal are

intended to prevent fatigue cracking of

the spring beam, which could result in

loss of an outboard strut.

DATES: Comments must be received by

August 21, 1998.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, ANM–114,

Attention: Rules Docket No. 97–NM–

185–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

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
Federal Register / Vol. 63, No. 129 /Tuesday, July 7, 1998 / Proposed Rules 36629

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–185–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–185–AD, 1601 Lind Avenue,

SW., Renton, Washington 98055–4056.

Discussion

On November 30, 1994, the FAA

issued AD 94–25–01, amendment 39–

9085 (59 FR 63003, December 7, 1994),

applicable to certain Boeing Model 747

series airplanes, to require repetitive

detailed visual inspections to detect

fatigue cracking of the spring beams on

the outboard struts; replacement of

cracked spring beams with new or

serviceable spring beams; and follow-on

actions. That action also provides an

optional terminating action for the

repetitive inspections.

AD 94–25–01 was prompted by a

report of failure of a spring beam due to

cracking that was propagated by fatigue.

The requirements of that AD are

intended to prevent failure of the spring

beam, which could result in loss of an

outboard strut.

Actions Since Issuance of Previous Rule

Since the issuance of that AD, the

FAA has determined that the specified

optional terminating action, if

accomplished, would not adequately

address the unsafe condition. Neither

the fluorescent dye penetrant inspection

nor the zero-time overhaul, which are

part of the optional terminating action,

would detect the porosity flaws that are

embedded within the titanium material

of the existing spring beams. In

addition, an improved process for

manufacturing titanium spring beams

has been developed that will eliminate

the embedded porosity flaws in the

existing spring beams from which

fatigue cracking can originate. Such

fatigue cracking, if not corrected, could

result in loss of an outboard strut.

Explanation of Relevant Service

Information

The FAA has reviewed and approved

Boeing Service Bulletin 747–54–2177,

dated June 27, 1996, which describes

procedures for replacement of the spring

beams on the outboard struts with new,

improved spring beams, which would

eliminate the need for the repetitive

inspections of the spring beams.

In addition, the FAA has reviewed

and approved Boeing Service Bulletin

747–54A2171, Revision 1, dated June

27, 1996, which changes the original

issue of the alert service bulletin (which

was referenced in AD 94–25–01 as the

appropriate source of service

information). This revision changes the

repetitive inspection intervals and the

terminating action. Accomplishment of

the actions specified in the service

bulletins 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

supersede AD 94–25–01 to continue to

require the repetitive inspections to

detect fatigue cracking of the spring

beams on the outboard struts, and to

remove the follow-on actions. For

certain airplanes, this proposed AD

would reinstate the repetitive

inspections of AD 94–25–01 to detect

fatigue cracking of the spring beams on

the outboard struts. In addition, the

proposed AD would remove the current

optional terminating action, and would

require a new terminating action for the

repetitive inspections. The actions

would be required to be accomplished

in accordance with Boeing Service

Bulletin 747–54–2177 and Boeing Alert

Service Bulletin 747–54A2171.

Cost Impact

There are approximately 7 airplanes

of the affected design in the worldwide

fleet. The FAA estimates that 5

airplanes of U.S. registry would be

affected by this proposed AD.

The inspections that are currently

required by AD 94–25–01, and retained

in this proposed AD, take approximately

40 work hours per airplane, per

inspection cycle, to accomplish, at an

average labor rate of $60 per work hour.

Based on these figures, the cost impact

of the currently required inspections on

U.S. operators is estimated to be$12,000,

or $2,400 per airplane, per inspection

cycle.

The new replacement proposed by

this AD would take approximately 376

work hours per airplane to accomplish,

at an average labor rate of $60 per work

hour. Required parts would cost

approximately $105,000 per airplane.

Based on these figures, the cost impact

of the replacement proposed by this AD

on U.S. operators is estimated to

be$637,800, or $127,560 per airplane.

The cost impact figures discussed

above are based on assumptions that no

operator has yet accomplished any of

the current or 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

removing amendment 39–9085 (59 FR

63003, December 7, 1994), and by
36630 Federal Register / Vol. 63, No. 129 /Tuesday, July 7, 1998 / Proposed Rules

adding a new airworthiness directive

(AD), to read as follows:

Boeing: Docket 97–NM–185–AD. Supersedes

AD 94–25–01, Amendment 39–9085.

Applicability: Model 747 series airplanes,

line numbers 202 through 396 inclusive,

equipped with Pratt & Whitney Model JT9D–

70 engines; 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 (f) 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 fatigue cracking of the spring

beam, which could result in loss of an

outboard strut, accomplish the following:

(a) Prior to the accumulation of 10,000 total

flight cycles, or within 30 days after

December 22, 1994 (the effective date of AD

94–25–01), whichever occurs later, perform a

detailed visual inspection to detect fatigue

cracking of the spring beams on the outboard

struts, in accordance with Boeing Alert

Service Bulletin 747–54A2171, dated October

31, 1994, or Revision 1, dated June 27, 1996.

(Remove the gap covers and fairing access

panels to perform this inspection.)

(1) If no cracking is detected, repeat the

visual inspection thereafter at intervals not to

exceed 300 flight cycles until the

requirements of paragraph (d) of this AD

have been accomplished.

(2) If any cracking is detected, prior to

further flight, accomplish the replacement

actions specified in paragraph (d) of this AD.

Note: 2: Accomplishment of the optional

terminating action specified in paragraph (b)

of AD 94–25–01 does not constitute

terminating action for the requirements of

this AD.

(b) For airplanes that have accomplished

terminating action in accordance with

paragraph (b) of AD 94–25–01: Within 1,000

flight cycles after accomplishment of the

terminating action specified by AD 94–25–

01, or within 90 days after the effective date

of this AD, whichever occurs later, perform

a detailed visual inspection to detect fatigue

cracking of the spring beams on the outboard

struts, in accordance with Boeing Alert

Service Bulletin 747–54A2171, dated October

31, 1994, or Revision 1, dated June 27, 1996.

(1) If no cracking is detected, repeat the

detailed visual inspection thereafter at

intervals not to exceed 300 flight cycles until

the requirements of paragraph (d) of thisAD

have been accomplished.

(2) If any cracking is detected, prior to

further flight, accomplish the replacement

actions specified in paragraph (d) of this AD.

(c) For airplanes that have accomplished

installation of the Boeing-inspected spare

titanium spring beams in accordance with

Boeing Service Bulletin 747–

54A2171,Revision 1, dated June 27, 1996:

Within 3,000 flight cycles after

accomplishment of the installation of the

spare spring beams, or within 90 days after

the effective date of thisAD, whichever

occurs later, perform a detailed visual

inspection to detect fatigue cracking of the

spring beams on the outboard struts, in

accordance with Boeing AlertService Bulletin

747–54A2171, dated October 31, 1994, or

Revision 1, dated June 27, 1996.

(1) If no cracking is detected, repeat the

detailed visual inspection thereafter at

intervals not to exceed 300 flight cycles until

the requirements of paragraph (d) of thisAD

have been accomplished.

(2) If any cracking is detected, prior to

further flight, accomplish the replacement

actions specified in paragraph (d) of this AD.

(d) For all airplanes: Prior to the

accumulation of 10,000 total flight cycles, or

within 18 months after the effective date of

this AD, whichever occurs later, replace the

spring beams on the outboard struts with

new, improved spring beams, in accordance

with Boeing Service Bulletin 747–54–2177,

dated June 27, 1996. Accomplishment of this

replacement constitutes terminating action

for the repetitive inspection requirements of

this AD.

(e) As of the effective date of this AD, no

person shall install a spring beam assembly,

part numbers 65B89175–5, –6, –9, –10, –13,

–14, –19, and –20, on any airplane.

(f) 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

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, Seattle ACO.

Note 3: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Seattle ACO.

(g) 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 June 30,

1998.

Vi L. Lipski,

Acting Manager, Transport Airplane

Directorate,Aircraft Certification Service.

[FR Doc. 98–17947 Filed 7–6–98; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 98–NM–167–AD]

RIN 2120–AA64

Airworthiness Directives; British

Aerospace (Jetstream) Model 4101

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 British Aerospace (Jetstream)

Model 4101 airplanes. This proposal

would require modification of the attach

points of the uplock system of the nose

landing gear (NLG). 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 wear of the

attach points of the uplock system of the

NLG; such wear could result in damage

to the adjacent emergency hydraulic

system, or jamming of the uplock

system and consequent inability to

extend and retract the NLG.

DATES: Comments must be received by

August 6, 1998.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, ANM–114,

Attention: Rules Docket No. 98-NM–

167-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

AI(R) American Support , Inc., 13850

Mclearen Road, Herndon, Virginia

20171. 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.