Federal Register / Vol. 65, No. 229 / Tuesday, November 28, 2000 / Proposed Rules 70819

Special Flight Permits

(l) 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 1996–

294(B) R4, dated March 10, 1999.

Issued in Renton, Washington, on

November 20, 2000.

Donald L. Riggin,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 00–30122 Filed 11–27–00; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000–NM–279–AD]

RIN 2120–AA64

Airworthiness Directives; Boeing

Model 707 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 707 series

airplanes. This proposal would require

modification of certain areas of the

upper skin of the wing. This action is

necessary to prevent cracking of the

upper skin of the wing, which could

result in reduced structural integrity of

the wing. This action is intended to

address the identified unsafe condition.

DATES: Comments must be received by

January 12, 2001.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, ANM–114,

Attention: Rules Docket No. 2000–NM–

279–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. Comments may be

submitted via fax to (425) 227–1232.

Comments may also be sent via the

Internet using the following address: 9-

anm-nprmcomment@faa.gov. Comments

sent via fax or the Internet must contain

‘‘Docket No. 2000–NM–279–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.

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:

James Rehrl, Aerospace Engineer,

Airframe Branch, ANM–120S, FAA,

Seattle Aircraft Certification Office,

1601 Lind Avenue, SW., Renton,

Washington 98055–4056; telephone

(425) 227–2783; 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 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 2000–NM–279–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.

2000–NM–279–AD, 1601 Lind Avenue,

SW., Renton, Washington 98055–4056.

Discussion

The FAA has received reports

indicating that cracking has been

detected in the upper skin of the wing

at wing stringers 10A and 11A on both

the left- and right-hand wings of certain

Boeing Model 707 series airplanes. The

cracking has been attributed to skin

fatigue. This condition, if not corrected,

could result in reduced structural

integrity of the wing.

Explanation of Relevant Service

Information

The FAA has reviewed and approved

Boeing Service Bulletin 2378, Revision

1, dated June 30, 1967, which, among

other actions, describes procedures for

modification of the upper skin of the

wing at wing stringers 10A and 11A.

The modification involves removing

fasteners at the inboard and outboard

ends of the stringer, inspecting these

fastener holes using an eddy current

method to detect cracking,

counterboring the inner surface of the

stringer at each fastener hole, installing

an anti-fretting strip between the wing

and stringer, enlarging fastener holes to

remove fatigued metal, and installing

new, improved fasteners.

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

modification specified in the service

bulletin described previously, except as

discussed below.

Differences Between the Proposed Rule

and Service Bulletin

Operators should note that the service

bulletin recommends, and describes

procedures for, an initial ultrasonic

inspection of the wing upper skin prior

to the accumulation of 18,000 flight

hours or within 800 flight hours after

receipt of the service bulletin,

whichever occurs later. The service

bulletin also recommends repetitive

inspections at intervals not to exceed

1,600 flight hours, until

accomplishment of a repair or

70820 Federal Register / Vol. 65, No. 229 / Tuesday, November 28, 2000 / Proposed Rules

modification. The service bulletin

suggests accomplishment of the

modification described previously ‘‘at

the major overhaul closest to 20,000

flight hours.’’

This proposed AD would not require

the repetitive inspections specified in

the service bulletin but would require

the modification of the upper skin of the

wing at wing stringers 10A and 11A

prior to the accumulation of 20,000

flight hours or within 24 months after

the effective date of this AD, whichever

occurs later. Mandating the terminating

action is based on the FAA’s

determination that long-term continued

operational safety will be better assured

by modifications or design changes to

remove the source of the problem, rather

than by repetitive inspections. Longterm inspections may not provide the

degree of safety assurance necessary for

the transport airplane fleet. This,

coupled with a better understanding of

the human factors associated with

numerous continual inspections, has led

the FAA to consider placing less

emphasis on inspections and more

emphasis on design improvements. The

proposed modification requirement is

consistent with these conditions. Also,

because many of the airplanes that are

affected by this AD will have already

passed the compliance threshold of

20,000 flight hours, as suggested in the

service bulletin, the FAA finds that it is

appropriate to include a grace period of

24 months after the effective date of this

AD, to allow time for the modification

to be accomplished on all affected

airplanes in a timely manner.

Operators also should note that, as

explained previously, the procedures for

the modification include an HFEC

inspection of fastener holes ‘‘to ensure

that there are no cracks.’’ However, the

service bulletin does not include

instructions for corrective actions if a

crack is found during this inspection.

Therefore, paragraph (b) of this AD

states that, if any crack is found during

the inspection that is included as part

of the modification, the cracks must be

repaired in accordance with the

applicable chapter of the Boeing 707

Structural Repair Manual.

Cost Impact

There are approximately 5 airplanes

of the affected design in the worldwide

fleet. The FAA estimates that 1 airplane

of U.S. registry would be affected by this

proposed AD, that it would take

approximately 8 work hours to

accomplish the proposed actions, and

that the average labor rate is $60 per

work hour. Based on these figures, the

cost impact of the proposed AD on the

single U.S. operator is estimated to be

$480.

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,

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:

Boeing: Docket 2000–NM–279–AD.

Applicability: Model 707 series airplanes;

as listed in Boeing Service Bulletin 2378,

Revision 1, dated June 30, 1967; 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 cracking of the upper skin of

the wing, which could result in reduced

structural integrity of the wing, accomplish

the following:

Modification

(a) Prior to the accumulation of 20,000 total

flight hours, or within 24 months after the

effective date of this AD, whichever occurs

later, modify the upper skin of the wing at

wing stringers 10A and 11A on both the leftand right-hand wings of the airplane, in

accordance with Boeing Service Bulletin

2378, Revision 1, dated June 30, 1967.

(b) During the high frequency eddy current

inspection included as part of the

modification required by paragraph (a) of this

AD, if any crack is found, prior to further

flight, repair in accordance with the

applicable section of the Boeing 707

Structural Repair Manual.

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, Seattle

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, 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.

Special Flight Permits

(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.

Federal Register / Vol. 65, No. 229 / Tuesday, November 28, 2000 / Proposed Rules 70821

Issued in Renton, Washington, on

November 21, 2000.

Donald L. Riggin,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 00–30320 Filed 11–27–00; 8:45 am]

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000–NM–124–AD]

RIN 2120–AA64

Airworthiness Directives; Airbus Model

A310 and Model 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 all

Airbus Model A310 and A300–600

series airplanes. This proposal would

require revising the Airplane Flight

Manual. This action is necessary to

provide the flight crew with procedures

to maintain airplane controllability in

the event of an in-flight thrust reverser

deployment. This action is intended to

address the identified unsafe condition.

DATES: Comments must be received by

December 28, 2000.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, ANM–114,

Attention: Rules Docket No. 2000–NM–

124–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. Comments may also

be sent via the Internet using the

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

via the Internet must contain ‘‘Docket

No. 2000–NM–124–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.

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,

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 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 2000–NM–124–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.

2000–NM–124–AD, 1601 Lind Avenue,

SW., Renton, Washington 98055–4056.

Discussion

The Direction Ge ́ne ́rale de l’Aviation

Civile (DGAC), which is the

airworthiness authority for France, has

advised the FAA that certain procedures

have been revised in the Airplane Flight

Manual (AFM) for Airbus Model A310

and A300–600 series airplanes. In the

event of an in-flight thrust reverser

deployment, the existing ‘‘ENG REV

UNLK’’ procedure could result in

reduced controllability of the airplane.

The revised procedures are intended to

address this problem.

The FAA has approved the following

revisions to Section 4.02.00 of the

Airbus AFM’s for Model A310 and

A300–600 series airplanes powered by

Pratt & Whitney and General Electric

engines:

Model/Series Reference Date

A310–203, –221, –222, and –304 ........................................................................ Ref. 02 ................................ November 23, 1999.

A310–324 and –325 ............................................................................................. Ref. 04 ................................ November 24, 1999.

A300–600 B4–605R ............................................................................................. Ref. 02 ................................ November 23, 1999.

A300–600 F4–605R .............................................................................................. Ref. 05 ................................ November 24, 1999.

A300–600 B4–622R ............................................................................................. Ref. 06 ................................ November 25, 1999.

Related AD

The FAA has issued a related AD, AD

99–18–19, amendment 39–11285 (64 FR

48277, September 3, 1999), which is

applicable to certain General Electric

engines installed on Airbus Model A310

and A300–600 series airplanes. Among

other things, that AD requires, at

paragraph (g), an AFM revision similar

to that proposed in this notice of

proposed rulemaking (NPRM). The FAA

may consider further rulemaking to

remove the AFM revision requirement

of paragraph (g) of AD 99–18–19. The

FAA can more adequately address the

identified unsafe condition by

incorporating that requirement into this

proposed AD, which is directed to