20950 Federal Register / Vol. 66, No. 81 / Thursday, April 26, 2001 / Proposed Rules

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:

Airbus Industrie: Docket 2001–NM–04–AD.

Applicability: Model A310 series airplanes

and Model A300 B4–600, B4–600R, and F4–

600R (collectively called A300–600) series

airplanes; certificated in any category; with

installed Inertial Reference Units (IRU)

Honeywell 10 MCU part number (P/N)

HG1050BD02 or HG1050BD05.

Compliance: Required as indicated, unless

accomplished previously.

To prevent a loss of positioning data and

a display of incorrect attitude data to the

flight crew, accomplish the following:

Revision to Airplane Flight Manual (AFM)

(a) Within 10 days after the effective date

of this AD, revise the Normal Procedures

section of the FAA-approved AFM to include

the following information. This may be

accomplished by inserting either a copy of

this AD or Temporary Revision (TR) 4.03.00/

22 into the A310 AFM or the A300–600

AFM, as applicable, facing 4.03.00 page 1.

‘‘COCKPIT PREPARATION

Do not move the aircraft during IRS

alignment.

PRIOR TO TAKEOFF

Scan PFD/ND to check correct display of

all primary attitude and heading

information.’’

(b) When the information in TR 4.03.00/22

has been incorporated into FAA-approved

general revisions of the AFM, the general

revisions may be incorporated in the AFM,

and this TR or this AD may be removed from

the AFM.

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,

International Branch, ANM–116, Transport

Airplane Directorate, FAA. Operators shall

submit their requests through an appropriate

FAA Principal Operations Inspector, who

may add comments and then send it to the

Manager, International Branch, ANM–116.

Note 1: 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

(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 2: The subject of this AD is addressed

in French airworthiness directive 2000–480–

325(B), dated November 29, 2000.

Issued in Renton, Washington, on April 19,

2001.

Donald L. Riggin,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 01–10345 Filed 4–25–01; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2001–NM–02–AD]

RIN 2120–AA64

Airworthiness Directives; Boeing

Model 747 Series Airplanes

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 detailed

visual inspections to find discrepancies

of the installation of the midspar fuse

pins of the inboard and outboard struts,

and follow-on actions, if necessary. The

existing AD also provides an optional

terminating modification for the

repetitive inspections. This action

would mandate accomplishment of the

previously optional terminating

modification. The actions specified by

the proposed AD are intended to find

and fix discrepancies of the installation

of the midspar fuse pins, which could

result in loss of the secondary retention

capability of the fuse pins, migration of

the fuse pins, and consequent loss of the

strut and engine from the airplane.

DATES: Comments must be received by

June 11, 2001.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, ANM–114,

Attention: Rules Docket No. 2001–NM–

02–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. 2001–NM–02–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

Federal Register / Vol. 66, No. 81 / Thursday, April 26, 2001 / Proposed Rules 20951

Airplane Directorate, 1601 Lind

Avenue, SW., Renton, Washington.

FOR FURTHER INFORMATION CONTACT:

Tamara Anderson, Aerospace Engineer,

Airframe Branch, ANM–120S, FAA,

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 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–02–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–02–AD, 1601 Lind Avenue,

SW., Renton, Washington 98055–4056.

Discussion

On February 26, 2001, the FAA issued

AD 2001–05–05, amendment 39–12141

(66 FR 13424, March 6, 2001),

applicable to certain Boeing Model 747

series airplanes, to require repetitive

detailed visual inspections to find

discrepancies of the installation of the

midspar fuse pins of the inboard and

outboard struts, and follow-on actions,

if necessary. That action also provides

for an optional terminating modification

for the repetitive inspections. The

requirements of that AD are intended to

find and fix discrepancies of the

installation of the midspar fuse pins,

which could result in loss of the

secondary retention capability of the

fuse pins, migration of the fuse pins,

and consequent loss of the strut and

engine from the airplane.

Actions Since Issuance of Previous Rule

In the preamble to AD 2001–05–05,

the FAA specified that the actions

required by that AD were considered

‘‘interim action’’ and that we were

considering requiring the optional

terminating modification, which would

constitute terminating action for the

repetitive inspections required by that

AD. The FAA has now determined that

it is necessary to mandate the

terminating modification, and this

proposed AD follows from that

determination.

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 2001–05–05 to continue

to require repetitive detailed visual

inspections to find discrepancies of the

installation of the midspar fuse pins of

the inboard and outboard struts, and

follow-on actions, if necessary. This

proposed AD also would mandate the

previously optional terminating

modification, which would end the

repetitive inspections. The actions

would be required to be done per the

service bulletin referenced in the

existing AD.

Cost Impact

There are approximately 1,111

airplanes of the affected design in the

worldwide fleet. The FAA estimates that

256 airplanes of U.S. registry would be

affected by this proposed AD.

The inspections that are currently

required by AD 2001–05–05 take

approximately 4 work hours per

airplane 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 $61,440, or

$240 per airplane, per inspection cycle.

The terminating modification that is

proposed in this AD action would take

approximately 4 work hours per

airplane to accomplish, at an average

labor rate of $60 per work hour.

Required parts would cost

approximately $1,000 per airplane.

Based on these figures, the cost impact

of the modification proposed by this AD

on U.S. operators is estimated to be

$317,440, or $1,240 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. 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

20952 Federal Register / Vol. 66, No. 81 / Thursday, April 26, 2001 / Proposed Rules

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 39–12141 (66 FR

13424, March 6, 2001), and by adding a

new airworthiness directive (AD), to

read as follows:

Boeing: Docket 2001–NM–02–AD.

Supersedes AD 2001–05–05, amendment

39–12141.

Applicability: Model 747 series airplanes,

as listed in Boeing Service Bulletin 747–

54A2206, Revision 1, dated February 22,

2001, 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 find and fix discrepancies of the

installation of the midspar fuse pins of the

inboard and outboard strut, which could

result in loss of the secondary retention

capability of the fuse pins, migration of the

fuse pins, and consequent loss of the strut

and engine from the airplane; accomplish the

following:

Restatement of the Requirements of AD

2001–05–05

Inspections/Follow-On Actions

(a) At the time specified in paragraph (a)(1)

or (a)(2) of this AD, as applicable: Do a

detailed visual inspection to find

discrepancies (e.g., incorrect thread

protrusion, which is less than two threads

protruding from the nut between the nut and

the secondary retention washer; incorrect gap

between the fuse pin primary nut and

secondary retention washer; cracked or

broken torque stripe) of the installation of the

midspar fuse pins of the inboard and

outboard struts, per Figure 2 of Boeing

Service Bulletin 747–54A2206, Revision 1,

dated February 22, 2001.

(1) For airplanes modified per the

production equivalent of one of the AD’s

listed in Table 1 of this AD: Do the

inspection at the later of the times specified

in paragraphs (a)(1)(i) and (a)(1)(ii) of this

AD.

(i) Before the accumulation of 8,000 total

flight hours, or within 24 months since

manufacture of the airplane, whichever

occurs first.

(ii) Within 90 days after March 21, 2001

(the effective date of AD 2001–05–05,

amendment 39–12141).

(2) For airplanes modified per one of the

AD’s listed in Table 1 of this AD: Do the

inspection at the later of the times specified

in paragraphs (a)(2)(i) and (a)(2)(ii) of this

AD. Table 1 follows:

TABLE 1

AD No. Amendment

No.

AD 95–10–16 .......................... 39–9233

AD 95–13–05 .......................... 39–9285

AD 95–13–06 .......................... 39–9286

AD 95–13–07 .......................... 39–9287

AD 99–10–10 .......................... 39–11163

(i) Within 8,000 flight hours, or within 24

months since doing the modification,

whichever occurs first.

(ii) Within 90 days after March 21, 2001.

Note 2: Where there are differences

between the AD and the service bulletin, the

AD prevails.

Note 3: For the purposes of this AD, a

detailed visual inspection is defined as: ‘‘An

intensive visual examination of a specific

structural area, system, installation, or

assembly to detect damage, failure, or

irregularity. Available lighting is normally

supplemented with a direct source of good

lighting at intensity deemed appropriate by

the inspector. Inspection aids such as mirror,

magnifying lenses, etc., may be used. Surface

cleaning and elaborate access procedures

may be required.’’

(A) If no discrepancy is found: Repeat the

inspection at intervals not to exceed 8,000

flight hours or 24 months, whichever is first,

until you do the terminating modification

specified in paragraph (b) of this AD.

(B) If any discrepancy is found, and the

primary nut has backed off and contacts the

secondary retention washer: Before further

flight, do the terminating modification

specified in paragraph (b) of this AD.

(C) If any discrepancy is found, and the

primary nut does not contact the secondary

retention washer: Repeat the inspection at

intervals not to exceed 90 days. Within 18

months after the initial finding, or March 21,

2001, whichever occurs later, do the

terminating modification specified in

paragraph (b) of this AD.

Note 4: Inspections done prior to the

effective date of this AD per Boeing Alert

Service Bulletin 747–54A2206, dated October

19, 2000, are acceptable for compliance with

the inspections required by paragraph (a) of

this AD.

New Requirements of This AD

Terminating Action

(b) Within 6 years after the effective date

of this AD: Do the terminating modification

(replacement of the primary nut of the

midspar fuse pin with a new nut, installation

of torque stripe, a detailed visual inspection

of the fuse pin threads for damage, and

replacement, if necessary) per Figure 3 of

Boeing Service Bulletin 747–54A2206,

Revision 1, dated February 22, 2001. Doing

this modification ends the repetitive

inspections required by this AD.

Note 5: Doing the terminating modification

prior to the effective date of this AD per

Boeing Alert Service Bulletin 747–54A2206,

dated October 19, 2000, is acceptable for

compliance with the terminating action

required by paragraph (b) 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, 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 6: 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.

Issued in Renton, Washington, on April 19,

2001.

Donald L. Riggin,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 01–10344 Filed 4–25–01 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000–NM–421–AD]

RIN 2120–AA64

Airworthiness Directives; Airbus Model

A319, A320, and A321 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 A319, A320, and