Federal Register / Vol. 70, No. 3 / Wednesday, January 5, 2005 / Proposed Rules 737

on the distribution of power and 

responsibilities among the various 

levels of government. 

For the reasons discussed above, I 

certify that the 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. 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. 

We prepared a regulatory evaluation 

of the estimated costs to comply with 

this proposed AD. See the ADDRESSES

section for a location to examine the 

regulatory evaluation.

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Safety.

The Proposed Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA proposes to amend 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. The FAA amends § 39.13 by adding 

the following new airworthiness 

directive (AD):

Boeing: Docket No. FAA–2004–19998; 

Directorate Identifier 2004–NM–224–AD. 

Comments Due Date 

(a) The Federal Aviation Administration 

(FAA) must receive comments on this AD 

action by February 22, 2005. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to Boeing Model 777–

200 series airplanes, certificated in any 

category; as listed in Boeing Special 

Attention Service Bulletin 777–28–0036, 

dated September 2, 2004. 

Unsafe Condition 

(d) This AD was prompted by reports that 

the ‘‘FUEL LOW CENTER’’ message does not 

activate when the fuel level in the center tank 

is low. We are issuing this AD to prevent the 

fuel pumps in the center fuel tank from 

running dry and becoming a potential 

ignition source, which could result in a fuel 

tank explosion. 

Compliance 

(e) You are responsible for having the 

actions required by this AD performed within 

the compliance times specified, unless the 

actions have already been done. 

Replacement 

(f) Within 24 months after the effective 

date of this AD, replace the pressure switches 

on the override/jettison fuel pumps with new 

pressure switches, and replace the ship side 

electrical connectors for the pressure 

switches on the override/jettison fuel pumps 

with new connectors, in accordance with the 

Accomplishment Instructions of Boeing 

Special Attention Service Bulletin 777–28–

0036, dated September 2, 2004. 

Alternative Methods of Compliance 

(AMOCs) 

(g) The Manager, Seattle Aircraft 

Certification Office, FAA, has the authority to 

approve AMOCs for this AD, if requested in 

accordance with the procedures found in 14 

CFR 39.19.

Issued in Renton, Washington, on 

December 27, 2004. 

Kevin M. Mullin, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service.

[FR Doc. 05–170 Filed 1–4–05; 8:45 am] 

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. 2001–NM–89–AD] 

RIN 2120–AA64 

Airworthiness Directives; Boeing 

Model 777–200 and –300 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 certain Boeing 

Model 777–200 and –300 series 

airplanes. That proposed AD would 

have required a one-time inspection of 

the clevis end of the vertical tie rods 

that support the center stowage bins to 

measure the exposed thread, installation 

of placards that advise of weight limits 

for certain electrical racks, a one-time 

inspection and records check to 

determine the amount of weight 

currently installed in those electrical 

racks, corrective actions, and 

replacement of the vertical tie rods for 

the center stowage bins or electrical 

racks with new improved tie rods, as 

applicable. This new action revises the 

proposed rule by revising the 

applicability to include additional 

airplanes. The actions specified by this 

new proposed AD are intended to 

prevent failure of the vertical tie rods 

supporting certain electrical racks and 

the center stowage bins, which could 

cause the center stowage bins or 

electrical racks to fall onto passenger 

seats below during an emergency 

landing, impeding an emergency 

evacuation or injuring passengers. This 

action is intended to address the 

identified unsafe condition.

DATES: Comments must be received by 

January 31, 2005.

ADDRESSES: Submit comments in 

triplicate to the Federal Aviation 

Administration (FAA), Transport 

Airplane Directorate, ANM–114, 

Attention: Rules Docket No. 2001–NM–

89–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–89–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 or 

2000 or ASCII text. 

The service information referenced in 

the proposed rule may be obtained from 

Boeing Commercial Airplanes, 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:

Robert Kaufman, Aerospace Engineer, 

Cabin Safety and Environmental 

Systems Branch, ANM–150S, FAA, 

Seattle Aircraft Certification Office, 

1601 Lind Avenue, SW., Renton, 

Washington 98055–4056; telephone 

(425) 917–6433; fax (425) 917–6590.

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

738 Federal Register / Vol. 70, No. 3 / Wednesday, January 5, 2005 / Proposed Rules 

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–89–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–89–AD, 1601 Lind Avenue, 

SW., Renton, Washington 98055–4056. 

Discussion 

A proposal to amend part 39 of the 

Federal Aviation Regulations (14 CFR 

part 39) to add an airworthiness 

directive (AD), applicable to certain 

Boeing Model 777–200 and –300 series 

airplanes, was published as a first 

supplemental notice of proposed 

rulemaking (NPRM) in the Federal 

Register on June 23, 2004 (69 FR 34966). 

That action proposed to require a onetime inspection of the clevis end of the 

vertical tie rods that support the center 

stowage bins to measure the exposed 

thread, installation of placards that 

advise of weight limits for certain 

electrical racks, a one-time inspection 

and records check to determine the 

amount of weight currently installed in 

those electrical racks, corrective actions, 

and replacement of the vertical tie rods 

for the center stowage bins or electrical 

racks with new improved tie rods, as 

applicable. The original NPRM and first 

supplemental NPRM were prompted by 

a report indicating that, under certain 

conditions on Boeing Model 777–200 

and –300 series airplanes, the vertical 

tie rods that attach the center stowage 

bins and electrical racks to the airplane 

structure can break. That condition, if 

not corrected, could result in the racks 

or stowage bins falling onto passenger 

seats below during an emergency 

landing, impeding an emergency 

evacuation or injuring passengers. 

Comments 

We have duly considered the 

comments received in response to the 

first supplemental NPRM. 

Request To Add Additional Airplanes 

One commenter notes that an airplane 

in its fleet that should be subject to the 

proposed AD is missing from the 

applicability of the first supplemental 

NPRM. The commenter states that it 

intends to accomplish the requirements 

on all of its airplanes. 

We agree that several line numbers 

were inadvertently omitted from the 

applicability of the first supplemental 

NPRM. Therefore, we are issuing this 

second supplemental NPRM and have 

revised the applicability statement to 

state that this supplemental NPRM 

applies to airplanes having line 

numbers 002 through 283 inclusive. We 

find that the estimated number of 

affected airplanes in the Cost Impact 

section of the first supplemental NPRM 

is correct; thus, we have not changed 

this section of this second supplemental 

NPRM. 

Request To Revise Compliance Time for 

Determining Installed Weight 

One commenter requests that we 

revise paragraph (a)(2) of the first 

supplemental NPRM to delete the words 

‘‘before further flight.’’ The commenter 

states that any airplane on which 

placards have been installed according 

to paragraph (a)(1) of the proposed AD 

before the effective date of the AD will 

be grounded upon the effective date of 

the AD until the inspection and records 

check to determine the weight installed 

in placarded electrical racks is done. 

We agree and have revised paragraph 

(a)(2) of this second supplemental 

NPRM to specify a separate compliance 

time of 12 months after the effective 

date of the AD for airplanes on which 

the actions in paragraph (a)(1) were 

done before the effective date of the AD. 

For airplanes on which the actions in 

paragraph (a)(1) are done after the 

effective date of this AD, the actions in 

paragraph (a)(2) would continue to be 

required before further flight after the 

installation of the placards required by 

paragraph (a)(1). 

Request To Give Credit for Actions 

Accomplished Previously 

One commenter requests that we 

revise paragraph (a)(1) of the first 

supplemental NPRM to include the 

words ‘‘except as provided by paragraph 

(e) of this AD.’’ The commenter states 

that adding this phrase will allow credit 

to operators who have already 

accomplished some of the AD 

requirements by doing Revision 1 of the 

service bulletin. 

We do not agree that any change is 

necessary in this regard. Paragraph (e) of 

the first supplemental NPRM, as well as 

this second supplemental NPRM, states 

that actions done before the effective 

date of the AD according to Boeing 

Special Attention Service Bulletin 777–

25–0144, dated January 25, 2001; or 

Revision 1, dated January 10, 2002; are 

acceptable for compliance with the 

corresponding actions required by this 

AD, which includes the actions in 

paragraph (a)(1).

Comment on Cost Impact Estimate 

One commenter estimates that 

approximately 205 work hours, 

including the time needed for rework, 

will be necessary to accomplish the 

requirements of the first supplemental 

NPRM on its fleet of 19 airplanes. The 

commenter estimates that it will incur a 

total cost of $59,500, including parts 

and labor. 

Because the commenter states that it 

has no objection to the proposed 

requirements, we infer that the 

commenter is providing these data for 

our information. We find that the costs 

estimated by the commenter are 

consistent with the cost stated in the 

Cost Impact section of this second 

supplemental NPRM. No change is 

necessary in this regard. 

Conclusion 

Since a certain change explained 

above expands the scope of the first 

supplemental NPRM, we have 

determined that it is necessary to reopen 

the comment period to provide 

additional opportunity for public 

comment. 

Cost Impact 

There are approximately 282 

airplanes of the affected design in the 

worldwide fleet. The FAA estimates that 

84 airplanes of U.S. registry would be 

affected by this proposed AD. 

For all airplanes: The records check 

and inspection to determine the weight 

currently installed in electrical rack E7 

would take approximately 1 work hour 

per airplane to accomplish, at an 

average labor rate of $65 per work hour. 

Based on these figures, the cost impact

Federal Register / Vol. 70, No. 3 / Wednesday, January 5, 2005 / Proposed Rules 739

of this proposed records check and 

inspection on U.S. operators is 

estimated to be $5,460, or $65 per 

airplane. 

For all airplanes: It would take 

approximately 1 work hour to 

accomplish the proposed installation of 

a placard specifying weight limits for 

electrical rack E7, at an average labor 

rate of $65 per work hour. Required 

parts would cost approximately $29. 

Based on these figures, the cost impact 

of this proposed placard installation on 

U.S. operators is estimated to be $7,896, 

or $94 per electrical rack. 

For airplanes subject to the records 

check and inspection to determine the 

weight currently installed in electrical 

rack E9, E11, E13, or E15: It would take 

approximately 1 work hour per 

electrical rack (up to 4 racks per 

airplane) to accomplish, at an average 

labor rate of $65 per work hour. Based 

on these figures, the cost impact of this 

proposed records check and inspection 

is estimated to be as much as $260 per 

airplane. 

For airplanes subject to the 

installation of a placard specifying 

weight limits for electrical rack E9, E11, 

E13, or E15: It would take 

approximately 1 work hour per 

electrical rack to accomplish, at an 

average labor rate of $65 per work hour. 

Required parts would cost 

approximately $29 per electrical rack. 

Based on these figures, the cost impact 

of this proposed installation is 

estimated to be as much as $376 per 

airplane. 

For airplanes subject to the inspection 

of the clevis end of the vertical support 

tie rod for the center stowage bin to 

measure the exposed thread: It would 

take as much as 3 work hours per 

airplane (0.25 work hour per tie rod, 

with up to 12 subject tie rods per 

airplane) at an average labor rate of $65 

per work hour. Based on these figures, 

the cost impact of this proposed 

inspection is estimated to be as much as 

$195 per airplane. 

For airplanes subject to the 

replacement of the vertical tie rods that 

support the center stowage bins: It 

would take as much as 6 work hours per 

airplane (0.5 work hour per tie rod, with 

up to 12 subject tie rods per airplane) 

at an average labor rate of $65 per work 

hour. Required parts would cost as 

much as $3,020 per airplane. Based on 

these figures, this proposed replacement 

is estimated to be as much as $3,410 per 

airplane. 

For airplanes subject to the 

replacement of the vertical tie rods that 

support the electrical racks: It would 

take as much as 2 work hours per 

airplane (0.5 work hour per tie rod with 

up to 4 subject tie rods per airplane) at 

an average labor rate of $65 per work 

hour. Required parts would cost as 

much as $3,012 per airplane. Based on 

these figures, this proposed replacement 

is estimated to be as much as $3,142 per 

airplane. 

The cost impact figures discussed 

above are 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 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. 

Authority for This Rulemaking 

Title 49 of the United States Code 

specifies the FAA’s authority to issue 

rules on aviation safety. Subtitle I, 

Section 106, describes the authority of 

the FAA Administrator. Subtitle VII, 

Aviation Programs, describes in more 

detail the scope of the Agency’s 

authority. 

We are issuing this rulemaking under 

the authority described in Subtitle VII, 

Part A, Subpart III, Section 44701, 

‘‘General requirements.’’ Under that 

section, Congress charges the FAA with 

promoting safe flight of civil aircraft in 

air commerce by prescribing regulations 

for practices, methods, and procedures 

the Administrator finds necessary for 

safety in air commerce. This regulation 

is within the scope of that authority 

because it addresses an unsafe condition 

that is likely to exist or develop on 

products identified in this rulemaking 

action. 

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 2001–NM–89–AD.

Applicability: Model 777–200 and –300 

series airplanes; certificated in any category; 

line numbers 002 through 283 inclusive.

Compliance: Required as indicated, unless 

accomplished previously. 

To prevent failure of the vertical tie rods 

supporting certain electrical racks and the 

center stowage bins, which could cause the 

center stowage bins or electrical racks to fall 

onto passenger seats below during an 

emergency landing, impeding an emergency 

evacuation or injuring passengers, 

accomplish the following: 

Inspection To Determine Weight and Placard 

Installation 

(a) For airplanes in the groups listed in the 

table under paragraph 3.B.1.b.(3) of the 

Accomplishment Instructions of Boeing 

Special Attention Service Bulletin 777–25–

0144, Revision 2, dated January 15, 2004: 

Within 5 years after the effective date of this 

AD, do the applicable actions in paragraphs 

(a)(1) and (a)(2) of this AD. 

(1) Install placards that show weight limits 

for electrical racks E7, E11, and E15; as 

applicable; per the Accomplishment 

Instructions of the service bulletin. 

(2) For each electrical rack on which a 

placard was installed per paragraph (a)(1) of 

this AD: At the applicable compliance time 

specified in paragraph (a)(2)(i) or (a)(2)(ii) of 

this AD, perform a one-time inspection and 

records check to determine the weight of 

equipment installed in that electrical rack. 

This records review and inspection must 

include determining what extra equipment, if 

any, has been installed in the subject rack of 

the airplane, performing a detailed

740 Federal Register / Vol. 70, No. 3 / Wednesday, January 5, 2005 / Proposed Rules 

inspection to determine whether this 

equipment is installed on the airplane, 

calculating the total weight of the installed 

equipment, and comparing that total to the 

weight limit specified on the placard 

installed per paragraph (a)(1) of this AD. If 

the weight is outside the limits specified in 

the placard to be installed per the service 

bulletin, before further flight, remove 

equipment from the rack to meet the weight 

limit specified in the placard. 

(i) For airplanes on which the actions 

required by paragraph (a)(1) of this AD were 

done before the effective date of this AD: 

Within 12 months after the effective date of 

this AD. 

(ii) For airplanes on which the actions 

required by paragraph (a)(1) of this AD are 

done after the effective date of this AD: 

Before further flight after installing the 

placards.

Note 1: For the purposes of this AD, a 

detailed 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.’’

Inspection To Measure Exposed Thread and 

Corrective Actions 

(b) For airplanes in the groups listed in the 

table under paragraph 3.B.1.b.(1) of the 

Accomplishment Instructions of Boeing 

Special Attention Service Bulletin 777–25–

0144, Revision 2, dated January 15, 2004: 

Within 5 years after the effective date of this 

AD, perform a detailed inspection of the 

clevis end of the vertical support tie rod for 

the center stowage bin to measure the 

exposed thread, per the Accomplishment 

Instructions of the service bulletin. If the 

measurement of the exposed thread is 

outside the limits specified in Figure 2 of the 

service bulletin, before further flight, perform 

all corrective actions specified in steps 2 

through 14 inclusive of Figure 2 of the 

service bulletin (including installing a 

threaded sleeve, torquing the jam nuts, 

inserting a pin in the witness hole to ensure 

that the witness hole is blocked by the clevis 

shank, and making any applicable 

adjustment of the clevis). Perform the 

corrective actions per the Accomplishment 

Instructions of the service bulletin, except as 

provided by paragraph (e) of this AD.

Replacement of Tie Rods for Center Stowage 

Bin 

(c) For airplanes in Group 21, as listed in 

the Airplane Group column of the table 

under 3.B.1.b.(2) of the Accomplishment 

Instructions of Boeing Special Attention 

Service Bulletin 777–25–0144, Revision 2, 

dated January 15, 2004: Within 5 years after 

the effective date of this AD, replace the 

vertical support tie rods for the center 

stowage bin with new improved tie rods 

(including replacing the existing tie rod with 

a new improved tie rod, torquing the jam 

nuts, inserting a pin in the witness hole to 

ensure that the witness hole is blocked by the 

clevis shank, and making any applicable 

adjustment of the clevis) by doing all actions 

specified in steps 1 through 8 of Figure 3 of 

the service bulletin. Do these actions per the 

Accomplishment Instructions of the service 

bulletin. Any required adjustment of the 

clevis must be done before further flight. 

Inspection To Determine Weight, Tie Rod 

Replacement, and Placard Installation 

(d) For airplanes in the groups listed in the 

table under paragraph 3.B.1.b.(4) of the 

Accomplishment Instructions of Boeing 

Special Attention Service Bulletin 777–25–

0144, Revision 2, dated January 15, 2004: Do 

the actions in paragraphs (d)(1), (d)(2), and 

(d)(3) of this AD. 

(1) Within 5 years after the effective date 

of this AD, replace the vertical support tie 

rods for electrical racks E9, E11, and E13 

(including replacing the existing tie rods 

with new improved tie rods, replacing an 

existing tie rod clamp with a new improved 

tie rod clamp, performing a free-play 

inspection of certain electrical racks, 

adjusting jam nuts as applicable, performing 

a general visual inspection through the 

witness hole to make sure tie rod threads are 

visible, and making any applicable 

adjustment to ensure tie rod threads are 

visible) by doing all actions specified in 

Figures 5, 6, 7, and 9 of the service bulletin; 

as applicable. Do these actions per the 

Accomplishment Instructions of the service 

bulletin. Any required adjustment must be 

done before further flight. 

(2) Before further flight after accomplishing 

paragraph (d)(1) of this AD, install placards 

that show weight limits for electrical racks 

E9, E11, and E13; as applicable; per the 

Accomplishment Instructions of the service 

bulletin. 

(3) For each electrical rack on which a 

placard was installed per paragraph (d)(2) of 

this AD: Before further flight after 

accomplishing paragraphs (d)(1) and (d)(2) of 

this AD, perform a one-time inspection and 

records check to determine the weight of 

equipment installed in that electrical rack. 

This records review and inspection must 

include determining what, if any, extra 

equipment has been installed in the subject 

racks of the airplane, performing a detailed 

inspection to determine that this equipment 

is installed on the airplane, calculating the 

total weight of the installed equipment, and 

comparing that total to the weight limit 

specified on the placard installed per 

paragraph (d)(2) of this AD. If the weight is 

outside the limits specified in the placard, 

before further flight, remove equipment from 

the rack to meet the weight limit specified in 

the placard. 

Actions Accomplished Previously 

(e) Actions accomplished before the 

effective date of this AD per the 

Accomplishment Instructions of Boeing 

Special Attention Service Bulletin 777–25–

0144, dated January 25, 2001; or Revision 1, 

dated January 10, 2002; are acceptable for 

compliance with the corresponding actions 

required by this AD, provided that the 

additional actions specified in Part 2 or 3 of 

the Accomplishment Instructions of Boeing 

Special Attention Service Bulletin 777–25–

0144, Revision 2, dated January 15, 2004, are 

accomplished within the compliance time 

specified in this AD. 

Alternative Methods of Compliance 

(f) In accordance with 14 CFR 39.19, the 

Manager, Seattle Aircraft Certification Office, 

FAA, is authorized to approve alternative 

methods of compliance (AMOCs) for this AD.

Issued in Renton, Washington, on 

December 27, 2004. 

Kevin M. Mullin, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service.

[FR Doc. 05–171 Filed 1–4–05; 8:45 am] 

BILLING CODE 4910–13–P

DEPARTMENT OF COMMERCE

National Oceanic and Atmospheric 

Administration

15 CFR Part 904

[Docket No. 040902252–4252–01; I.D. 

092804C]

RIN 0648–AS54

Civil Procedures

AGENCY: Office of General Counsel for 

Enforcement and Litigation, National 

Oceanic and Atmospheric 

Administration (NOAA), Commerce.

ACTION: Proposed rule; amendments and 

technical refinements to Civil 

Procedures; reopening of the comment 

period.

SUMMARY: In a proposed rule published 

in the Federal Register on October 12, 

2004, NOAA requested comments on 

proposed revisions to its Civil 

Procedures which govern the Agency’s 

administrative proceedings for the 

assessment of civil penalties; 

suspension, revocation, modification, or 

denial of permits; issuance and use of 

written warnings; and release or 

forfeiture of seized property. The 

comment period for the proposed rule 

closed on December 13, 2004. 

Comments addressed various issues and 

included requests to extend the 

comment period. The intent of this 

document is to announce the reopening 

of the public comment period.

DATES: Written comments must be 

received on or before January 31, 2005.

ADDRESSES: Send comments to Meggan 

Engelke-Ros, Enforcement Attorney, 

Office of General Counsel for 

Enforcement and Litigation, NOAA. 

Comments may be submitted by:

• Mail to 8484 Georgia Avenue, Suite 

400, Silver Spring, MD 20910;

• E-mail to 

Part904.comments@noaa.gov; or