10974 Federal Register / Vol. 66, No. 35 / Wednesday, February 21, 2001 / Proposed Rules

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–320–AD.

Applicability: Model 747–400 series

airplanes, as listed in Boeing Alert Service

Bulletin 747–30A2078, Revision 1, dated

November 16, 2000; 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 (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 reduced power to the heating

system of the pitot static probes, leading to

ice accumulation on the pitot static probes,

which could result in erroneous airspeed or

altitude indications to the flight crew, and

consequent reduced operational safety in all

phases of flight, accomplish the following:

Inspection

(a) Within 15 months after the effective

date of this AD, perform a special detailed

inspection to detect miswiring of diodes in

the heating system of the pitot static probes

by using a multimeter to verify continuity

between certain relay sockets, absence of a

diode between certain relay sockets, and

diode orientation between certain relay

sockets, per Boeing Alert Service Bulletin

747–30A2078, Revision 1, dated November

16, 2000. If any miswiring is found, rewire

per Boeing 747–400 Wiring Diagrams 30–31–

11 and 30–31–21, as referenced in the service

bulletin.

Note 2: Inspections accomplished prior to

the effective date of this AD per Boeing Alert

Service Bulletin 747–30A2078, dated August

24, 2000, are considered acceptable for

compliance with the applicable action

specified in this amendment.

Note 3: For the purposes of this AD, a

special detailed inspection is defined as: ‘‘An

intensive examination of a specific item(s),

installation, or assembly to detect damage,

failure, or irregularity. The examination is

likely to make extensive use of specialized

inspection techniques and/or equipment.

Intricate cleaning and substantial access or

disassembly procedures may be required.’’

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, 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 4: 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

(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.

Issued in Renton, Washington, on February

13, 2001.

Vi L. Lipski,

Manager, Transport Airplane Directorate,

Aircraft Certification Service.

[FR Doc. 01–4220 Filed 2–20–01; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000–NM–251–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

adoption of a new airworthiness

directive (AD) that is applicable to all

Boeing Model 747 series airplanes. This

proposal would require repetitive high

frequency eddy current inspections to

find cracking of the bulkhead frame

support at body station 2598 under the

hinge support fittings of the horizontal

stabilizer, and repair if cracking is

found. This action is necessary to find

and fix fatigue cracking in the frame

support, which could result in inability

of the structure to carry horizontal

stabilizer flight loads and reduced

controllability of the horizontal

stabilizer. This action is intended to

address the identified unsafe condition.

DATES: Comments must be received by

April 9, 2001.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, ANM–114,

Attention: Rules Docket No. 2000–NM–

251–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–

251–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: Rick

Kawaguchi, Aerospace Engineer,

Airframe Branch, ANM–120S, FAA,

Seattle Aircraft Certification Office,

1601 Lind Avenue, SW., Renton,

Washington 98055–4056; telephone

(425) 227–1153; 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

Federal Register / Vol. 66, No. 35 / Wednesday, February 21, 2001 / Proposed Rules 10975

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–251–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–251–AD, 1601 Lind Avenue,

SW., Renton, Washington 98055–4056.

Discussion

The FAA has received a report

indicating that a fatigue crack (1.25

inches in length) was found on the

bulkhead frame support under the hinge

support fittings of the horizontal

stabilizer at body station (BS) 2598 on

a Model 747–200F series airplane. The

airplane had accumulated

approximately 13,488 total flight cycles

and 58,697 total flight hours at the time

the crack was found. Such cracking in

the frame support, if not found and

fixed, could result in inability of the

structure to carry horizontal stabilizer

flight loads and reduced controllability

of the horizontal stabilizer.

Explanation of Relevant Service

Information

The FAA has reviewed and approved

Boeing Alert Service Bulletin 747–

53A2449, dated June 8, 2000. The

service bulletin describes procedures for

repetitive open-hole high frequency

eddy current inspections to find

cracking of the bulkhead frame support

located on the left and right sides at BS

2598 under the hinge support fittings of

the horizontal stabilizer. If cracking is

found, the service bulletin specifies to

contact Boeing for repair instructions.

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.

Difference Between Service Bulletin

and This Proposed AD

The service bulletin specifies that the

manufacturer must be contacted for

repair of certain conditions, but this

proposal would require the repair of

those conditions to be accomplished per

a method approved by the FAA, or per

data meeting the type certification basis

of the airplane approved by a Boeing

Company Designated Engineering

Representative who has been authorized

by the FAA to make such findings. For

a method to be approved, the approval

letter must specifically reference this

AD.

Cost Impact

There are approximately 1,314

airplanes of the affected design in the

worldwide fleet. The FAA estimates that

258 airplanes of U.S. registry would be

affected by this proposed AD, that it

would take approximately 8 work hours

(4 work hours per side) per airplane to

accomplish the proposed inspections,

and that the average labor rate is $60 per

work hour. Based on these figures, the

cost impact of the proposed AD on U.S.

operators is estimated to be $123,840, or

$480 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 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–251–AD.

Applicability: Model 747 series airplanes,

as listed in Boeing Alert Service Bulletin

747–53A2449, dated June 8, 2000,

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 fatigue cracking in the

bulkhead frame support at body station (BS)

2598 under the hinge support fittings of the

horizontal stabilizer, which could result in

inability of the structure to carry horizontal

stabilizer flight loads and reduced

controllability of the horizontal stabilizer,

accomplish the following:

Repetitive High Frequency Eddy Current

(HFEC) Inspections

(a) Before the accumulation of 10,000 total

flight cycles, or within 1,000 flight cycles

after the effective date of this AD, whichever

occurs later: Do an open-hole HFEC

10976 Federal Register / Vol. 66, No. 35 / Wednesday, February 21, 2001 / Proposed Rules

inspection to find cracking of the bulkhead

frame support under the hinge support

fittings of the horizontal stabilizer on the left

and right sides at BS 2598, per Figure 2 of

the Accomplishment Instructions of Boeing

Alert Service Bulletin 747–53A2449, dated

June 8, 2000. Repeat the inspection after that

at intervals not to exceed 3,000 flight cycles.

Repair

(b) If any cracking is found during any

inspection required by paragraph (a) of this

AD, before further flight, repair per a method

approved by the Manager, Seattle Aircraft

Certification Office (ACO), FAA; or per data

meeting the type certification basis of the

airplane approved by a Boeing Company

Designated Engineering Representative who

has been authorized by the Manager, Seattle

ACO, to make such findings. For a repair

method to be approved by the Manager,

Seattle ACO, as required by this paragraph,

the approval letter must specifically

reference 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

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.

Special Flight Permit

(d) Special flight permits may be issued in

accordance with §§ 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 February

13, 2001.

Vi L. Lipski,

Manager, Transport Airplane Directorate,

Aircraft Certification Service.

[FR Doc. 01–4219 Filed 2–20–01; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000–NM–179–AD]

RIN 2120–AA64

Airworthiness Directives; BAe

Systems (Operations) Limited Model

BAe 146 and Model Avro 146–RJ

Series Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Supplemental notice of

proposed rulemaking; reopening of

comment period.

SUMMARY: This document revises an

earlier proposed airworthiness directive

(AD), applicable to all BAe Systems

(Operations) Limited Model BAe 146

and Model Avro 146–RJ series airplanes,

that would have superseded an existing

AD that currently requires a one-time

inspection for ‘‘drill marks’’ and

corrosion on the underside of the wing

top skin, and corrective actions, if

necessary. The proposed AD would

have required a one-time inspection for

‘‘drill marks’’ and corrosion, and

corrective actions, if necessary, per new

procedures. For certain airplanes, the

proposed AD would have added a

requirement for one-time detailed visual

and borescopic inspections of the fuel

tank, pump, and stringers for paint

debris and inadequacy of the existing

protective treatment coating; and

corrective actions, if necessary. This

new action revises the proposed rule by

requiring repetitive inspections for

‘‘drill marks’’ and corrosion on the

underside of the wing top skin, and

corrective actions, if necessary, until all

corrective actions and protective

treatment actions are done. The actions

specified by this new proposed AD are

intended to prevent corrosion from

developing on the underside of the top

skin of the center wing, which could

result in reduced structural integrity of

the airplane.

DATES: Comments must be received by

March 19, 2001.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, ANM–114,

Attention: Rules Docket No. 2000–NM–

179–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–179–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

British Aerospace Regional Aircraft

American Support, 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.

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–179–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–179–AD, 1601 Lind Avenue,

SW., Renton, Washington 98055–4056.