10972 Federal Register / Vol. 66, No. 35 / Wednesday, February 21, 2001 / Proposed Rules

been eliminated, the request should include

specific proposed actions to address it.

Compliance: Required as indicated, unless

accomplished previously.

To prevent in-flight loss of inboard and

outboard flap assemblies due to failure of H–

11 attaching bolts, which could result in

reduced controllability of the airplane,

accomplish the following:

Inspection or Torque Verification, and

Corrective Actions, if Necessary

(a) Within 2 months after September 25,

2000, (the effective date of AD 2000–16–10,

amendment 39–11866), do an ultrasonic

inspection of the attaching bolts on the

inboard and outboard support on the

outboard flap assembly and on the outboard

support on the inboard flap assembly to

detect failed bolts, or verify the torque of the

attaching bolts on the inboard support on the

outboard flap, per McDonnell Douglas Alert

Service Bulletin DC10–57A143, dated

December 20, 1999.

(1) If no failed bolt is found, repeat the

ultrasonic inspection or torque verification

every 6 months.

(2) If any failed bolt is found, before further

flight, replace the bolt and associated parts

with a new Inconel bolt and new associated

parts per the service bulletin, except as

provided by paragraphs (a)(2)(i) and (a)(2)(ii)

of this AD. Accomplishment of the

replacement constitutes terminating action

for the repetitive requirements of paragraph

(a)(1) of this AD for that bolt.

(i) If an Inconel bolt is not available for

accomplishment of the replacement,

replacement with a new H–11 steel bolt is

acceptable provided that operators repeat the

ultrasonic inspection or torque verification

every 6 months until the requirements of

paragraph (c) of this AD are accomplished.

(ii) If a PLI washer is not available for

accomplishment of the Inconel replacement,

a new Inconel bolt can be temporarily

installed without a new PLI washer provided

that the bolt is torqued to the applicable

value specified in the service bulletin.

Within 6,000 flight hours after an Inconel

bolt is torqued, replace the PLI washer with

a new washer per the service bulletin.

Torque Verification

(b) For airplanes on which the verification

of the torque of the attaching bolts on the

inboard support on the outboard flap was

done per paragraph (a) of this AD: Within 2

months after the effective date of this AD,

verify the torque of the attaching bolts on the

outboard support on the inboard and

outboard flaps, per McDonnell Douglas Alert

Service Bulletin DC10–57A143, dated

December 20, 1999; and do the applicable

action(s) specified in paragraph (a)(1) or

(a)(2) of this AD.

Bolt Replacement

(c) Within 2 years after accomplishing the

initial inspection required by paragraph (a) of

this AD or the torque verification required by

paragraphs (a) and (b) of this AD, do the

action specified in paragraph (a)(2) of this AD

for all H–11 bolts.

Accomplishment of the replacement of all

H–11 bolts with Inconcel bolts constitutes

terminating action for the requirements of

this AD.

Spares

(d) As of 2 years after the effective date of

this AD, no person shall install, on any

airplane, an H–11 steel bolt, part number

71658–8–44, 71658–7–44, 71658–7–54,

71658–7–56, 71658–7–29, 71658–9–31,

71658–9–34, 71658–9–38, 71658–9–41,

71658–10–41, 71658–7–26, 71658–7–27, or

71658–8–29, on the inboard or outboard flap

assembly.

Alternative Methods of Compliance

(e)(1) 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 2: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Los Angeles ACO.

(2) Alternative methods of compliance,

approved previously per AD 2000–16–10,

amendment 39–11866, are considered to be

approved as alternative methods of

compliance with this AD.

Special Flight Permits

(f) 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. 01–4221 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–320–AD]

RIN 2120–AA64

Airworthiness Directives; Boeing

Model 747–400 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 747–400 series

airplanes. This proposal would require

an inspection to detect miswiring of

diodes in the heating system of the pitot

static probes, and corrective action, if

necessary. This action is necessary 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.

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–

320–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–320–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: Don

Eiford, Aerospace Engineer, Systems

and Equipment Branch, ANM–130S,

FAA, Seattle Aircraft Certification

Office, 1601 Lind Avenue, SW., Renton,

Washington 98055–4056; telephone

(425) 227–2788; 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

Federal Register / Vol. 66, No. 35 / Wednesday, February 21, 2001 / Proposed Rules 10973

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–320–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–320–AD, 1601 Lind Avenue,

SW., Renton, Washington 98055–4056.

Discussion

The FAA has received reports

indicating that several operators have

found burnt diodes in the heating

system of the pitot static probes on

certain Boeing Model 747–400 series

airplanes. Investigation revealed that

diodes in the power reduction circuitry

were miswired. The miswiring results in

the probe-head heat element always

being at full-power, while the probe

strut heater is only at half-power. If the

probe strut heater is only at half-power,

ice may accumulate on the pitot static

probes. This condition, if not corrected,

could result in erroneous airspeed or

altitude indications to the flight crew,

and consequent reduced operational

safety in all phases of flight.

Explanation of Relevant Service

Information

The FAA has reviewed and approved

Boeing Alert Service Bulletin 747–

30A2078, Revision 1, dated November

16, 2000, which describes procedures

for an inspection to detect miswiring of

diodes in the heating system of the pitot

probes. The inspection involves 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. If any miswiring is found, the

service bulletin specifies to rewire per

Boeing 747–400 Wiring Diagrams 30–

31–11 and 30–31–21. Doing the actions

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 operators to do the actions

specified in the service bulletin

described previously, except as

discussed below.

Differences Between This Proposed AD

and the Service Bulletin

Operators should note that, although

the service bulletin recommends

accomplishing the inspection at the

earliest maintenance opportunity when

manpower and facilities are available,

the FAA has determined that this

compliance time may not ensure that

the identified unsafe condition is

addressed in a timely manner. In

developing an appropriate compliance

time for this proposed AD, the FAA

considered not only the manufacturer’s

recommendation, but the degree of

urgency associated with addressing the

subject unsafe condition, the average

utilization of the affected fleet, and the

time necessary to perform the proposed

AD. In light of all of these factors, the

FAA finds a 15-month compliance time

to be warranted, in that it represents an

appropriate interval of time allowable

for affected airplanes to continue to

operate without compromising safety.

Operators also should note that, while

the service bulletin describes only an

inspection/verification that necessitates

use of a multimeter, this proposed AD

refers to this inspection/verification as a

‘‘special detailed inspection.’’ The

definition of a ‘‘special detailed

inspection’’ is included as a note in the

proposed AD.

Cost Impact

There are approximately 497

airplanes of the affected design in the

worldwide fleet. The FAA estimates that

69 airplanes of U.S. registry would be

affected by this proposed AD, that it

would take approximately 2 work hours

per airplane 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 U.S. operators is estimated to be

$8,280, or $120 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,

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:

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