Federal Register / Vol. 66, No. 94 / Tuesday, May 15, 2001 / Proposed Rules 26817

it is determined that this proposal

would not have federalism implications

under Executive Order 13132.

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:

Airbus Industrie: Docket 2000–NM–383–AD.

Applicability: Model A319, A320, and

A321 series airplanes, certificated in any

category, except those on which Airbus

Industrie Modification 28289 has been

installed.

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 (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 injection of 115 volt alternating

current (VAC) into 28 volt direct current

(VDC) wire bundles, which could result in

high voltage conditions within the fuel tank

and the potential for damage to equipment,

electrical arcing, and fuel vapor ignition on

the ground, accomplish the following:

Modification

(a) Within 4 years after the effective date

of this AD, install additional protective

conduits and new supports to ensure

physical route segregation between the low

voltage wire bundles of the fuel quantity

indicating system (FQIS) and the high voltage

wire bundles of the ground power control

unit (GPCU), in accordance with Airbus

Service Bulletin A320–92–1007, Revision 02,

dated August 4, 2000.

Note 2: Modifications accomplished prior

to the effective date of this AD in accordance

with Airbus Service Bulletin A320–92–1007,

dated January 12, 2000, or Airbus Service

Bulletin A320–92–1007, Revision 01, dated

June 29, 2000, are considered acceptable for

compliance with the applicable actions

specified in this amendment.

Alternative Methods of Compliance

(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,

International Branch, ANM–116, Transport

Airplane Directorate, FAA. Operators shall

submit their requests through an appropriate

FAA Principal Maintenance Inspector, who

may add comments and then send them to

the Manager, International Branch, ANM–

116.

Note 3: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the International Branch,

ANM–116.

Special Flight Permits

(c) 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 4: The subject of this AD is addressed

in French airworthiness directive 2000–407–

150(B), dated September 20, 2000.

Issued in Renton, Washington, on May 9,

2001.

Donald L. Riggin,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 01–12177 Filed 5–14–01; 8:45 am]

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2001–NM–47–AD]

RIN 2120–AA64

Airworthiness Directives; McDonnell

Douglas Model 717 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 717

series airplanes. This proposal would

require repetitive inspections of the rod

ends of the spoiler hold-down actuators

for breakage along the intersection of the

thread runout and the outer spherical

surface of the lug; and replacement of

any broken rod end of the spoiler holddown actuators with a new rod end.

This proposal also would require

replacement of the rod ends of the

spoiler hold-down actuators with new

rod ends, and reidentification of the

spoiler hold-down actuators, which

would constitute terminating action for

the repetitive inspections. This action is

necessary to prevent failure of the rod

ends of the spoiler hold-down actuators

due to fatigue, which could result in

loss of the back-up protection of the

spoiler float hold-down and

unavailability of monitoring for an

uncommanded spoiler movement. This

action is intended to address the

identified unsafe condition.

DATES: Comments must be received by

June 29, 2001.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, ANM–114,

Attention: Rules Docket No. 2001–NM–

47–AD, 1601 Lind Avenue, SW.,

Renton, Washington 98055–4056.

Comments may be inspected at this

location between 9 a.m. and 3 p.m.,

Monday through Friday, except Federal

holidays. Comments may be submitted

via fax to (425) 227–1232. Comments

may also be sent via the Internet using

the following address: 9-anmnprmcomment@faa.gov. Comments sent

via fax or the Internet must contain

‘‘Docket No. 2001–NM–47–AD’’ in the

subject line and need not be submitted

in triplicate. Comments sent via the

Internet as attached electronic files must

be formatted in Microsoft Word 97 for

Windows or ASCII text.

26818 Federal Register / Vol. 66, No. 94 / Tuesday, May 15, 2001 / Proposed Rules

The service information referenced in

the proposed rule may be obtained from

Boeing Commercial Aircraft Group,

Long Beach Division, 3855 Lakewood

Boulevard, Long Beach, California

90846, Attention: Data and Service

Management, Dept. C1–L5A (D800–

0024). This information may be

examined at the FAA, Transport

Airplane Directorate, 1601 Lind

Avenue, SW., Renton, Washington; or at

the FAA, Los Angeles Aircraft

Certification Office, 3960 Paramount

Boulevard, Lakewood, California.

FOR FURTHER INFORMATION CONTACT:

Maureen Moreland, Aerospace

Engineer, Airframe Branch, ANM–120L,

FAA, Los Angeles Aircraft Certification

Office, 3960 Paramount Boulevard,

Lakewood, California 90712–4137;

telephone (562) 627–5238; 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 action may be changed in light

of the comments received.

Submit comments using the following

format:

• Organize comments issue-by-issue.

For example, discuss a request to

change the compliance time and a

request to change the service bulletin

reference as two separate issues.

• For each issue, state what specific

change to the proposed AD is being

requested.

• Include justification (e.g., reasons or

data) for each request.

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 action

must submit a self-addressed, stamped

postcard on which the following

statement is made: ‘‘Comments to

Docket Number 2001–NM–47–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.

2001–NM–47–AD, 1601 Lind Avenue,

SW., Renton, Washington 98055–4056.

Discussion

The FAA has received reports of

failures of the attach lug rod end on the

spoiler hold-down actuators on

McDonnell Douglas Model 717 series

airplanes. These failures initiated along

a region at the intersection of the thread

runout and the outer spherical surface

of the lug. Investigation revealed that

such failures were caused by fatigue

rupture with multiple failure origins.

Failure of the rod ends of the spoiler

hold-down actuators due to fatigue, if

not corrected, could result in loss of the

back-up protection of the spoiler float

hold-down and unavailability of

monitoring for an uncommanded spoiler

movement.

Explanation of Relevant Service

Information

The FAA has reviewed and approved

Boeing Alert Service Bulletin 717–

27A0010, dated August 15, 2000. This

service bulletin describes procedures for

repetitive general visual inspections of

the rod ends of the hold-down actuators

of the inboard and outboard spoilers for

breakage along the intersection of the

thread runout and the outer spherical

surface of the lug; and replacement of

any broken rod end of the spoiler holddown actuators with a new rod end.

The FAA also has reviewed and

approved Boeing Service Bulletin 717–

27–0013, dated January 30, 2001, and

Revision 01, dated February 28, 2001.

The service bulletin describes

procedures for replacement of the rod

ends of the spoiler hold-down actuators

with new rod ends, and reidentification

of the spoiler hold-down actuators,

which would eliminate the need for the

repetitive inspections described above.

The effectivity listing of Revision 01 of

the service bulletin was revised from the

original version of the service bulletin to

include additional airplanes that are

subject to 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 bulletins

described previously. Accomplishment

of the actions specified in the service

bulletins is intended to adequately

address the identified unsafe condition.

Explanation of Differences Between

Service Bulletin and the Proposed AD

Operators should note that, although

the effectivity listing of Boeing Service

Bulletin 717–27A0010 affects airplanes

having manufacturer’s fuselage numbers

5002 through 5082 inclusive, this

proposed AD does not affect McDonnell

Douglas Model 717 series airplanes,

manufacturer’s fuselage numbers 5002,

5003, 5037 and subsequent. Those

airplanes had improved rod ends

installed during production that address

the identified unsafe condition of this

proposed AD. Therefore, those airplanes

are not subject to the requirements of

this proposed AD.

Cost Impact

There are approximately 33 Model

717 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.

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 $1,380, or

$60 per airplane, per inspection cycle.

It would take approximately 14 work

hours per airplane to accomplish the

proposed replacement and

reidentification, at an average labor rate

of $60 per work hour. The manufacturer

has committed previously to its

customers that it will bear the cost of

replacement parts. As a result, the cost

of those parts is not attributable to this

proposed AD. Based on these figures,

the cost impact of the replacement and

reidentification proposed by this AD on

U.S. operators is estimated to be

$19,320, or $840 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 proposed AD were not adopted. The

cost impact figures discussed in AD

rulemaking actions represent only the

time necessary to perform the specific

actions actually required by the AD.

These figures typically do not include

incidental costs, such as the time

required to gain access and close up,

Federal Register / Vol. 66, No. 94 / Tuesday, May 15, 2001 / Proposed Rules 26819

planning time, or time necessitated by

other administrative actions.

Regulatory Impact

The regulations proposed herein

would not have a substantial direct

effect 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,

it is determined that this proposal

would not have federalism implications

under Executive Order 13132.

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 2001–NM–47–

AD.

Applicability: Model 717 series airplanes,

manufacturer’s fuselage numbers 5004

through 5036 inclusive; 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 rod ends of the

spoiler hold-down actuators due to fatigue,

which could result in loss of the back-up

protection of the spoiler float hold-down and

unavailability of monitoring for an

uncommanded spoiler movement,

accomplish the following:

General Visual Inspection

(a) Within 450 flight hours after the

effective date of this AD, do a general visual

inspection of the rod ends of the spoiler

hold-down actuators of the inboard and

outboard spoilers for breakage along the

intersection of the thread runout and the

outer spherical surface of the lug, per Boeing

Alert Service Bulletin 717–27A0010, dated

August 15, 2000.

Note 2: For the purposes of this AD, a

general visual inspection is defined as ‘‘A

visual examination of an interior or exterior

area, installation, or assembly to detect

obvious damage, failure, or irregularity. This

level of inspection is made under normally

available lighting conditions such as

daylight, hangar lighting, flashlight, or droplight, and may require removal or opening of

access panels or doors. Stands, ladders, or

platforms may be required to gain proximity

to the area being checked.’’

Condition 1 (No Breakage Present)

(1) If no breakage is present, repeat the

general visual inspection every 450 flight

hours.

Condition 2 (Breakage Present)

(2) If any breakage is present, before further

flight, replace the broken rod end of the

spoiler hold-down actuator with a new rod

end, per Boeing Alert Service Bulletin 717–

27A0010, dated August 15, 2000; or Boeing

Service Bulletin 717–27–0013, dated January

30, 2001, or Revision 01, dated February 28,

2001. As of the effective date of this AD, the

replacement shall be done per Boeing Service

Bulletin 717–27–0013, Revision 01, dated

February 28, 2001. For rod ends that have

been replaced per Boeing Alert Service

Bulletin 717–27A0010, dated August 15,

2000, repeat the general visual inspection

thereafter every 450 flight hours.

Accomplishment of this replacement per

Boeing Service Bulletin 717–27–0013

constitutes terminating action for the

requirements of this AD for that rod end.

Terminating Action

(b) Within 15 months or 3,600 flight hours

after the effective date of this AD, whichever

occurs first, replace the rod ends of the

spoiler hold-down actuators with new rod

ends, and reidentify the spoiler hold-down

actuators, per Boeing Service Bulletin 717–

27–0013, dated January 30, 2001, or Revision

01, dated February 28, 2001.

Accomplishment of this replacement and

reidentification constitutes terminating

action for the requirements of this AD.

Alternative Methods of Compliance

(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, Los

Angeles Aircraft Certification Office (ACO),

FAA. 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 3: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Los Angeles ACO.

Special Flight Permit

(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.

Issued in Renton, Washington, on May 9,

2001.

Donald L. Riggin,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 01–12176 Filed 5–14–01; 8:45 am]

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000–NM–405–AD]

RIN 2120–AA64

Airworthiness Directives; Boeing

Model 757 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 Boeing Model 757 series

airplanes. This proposal would require

an inspection to determine the serial

numbers of geared rotary actuators

(GRA) for the leading edge slats, and

replacement of certain actuators with

new or reworked actuators. This action

is necessary to prevent a fractured

spring washer in a GRA, which could

lead to a disconnect in the GRA, and

result in a slat skew condition and

consequent reduced controllability of

the airplane. This action is intended to

address the identified unsafe condition.