70204 Federal Register / Vol. 69, No. 232 / Friday, December 3, 2004 / Proposed Rules 

Subtitle VII, Part A, Subpart III, Section 

44701, ‘‘General requirements.’’ Under 

that section, the FAA is charged 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 AD. 

Regulatory Findings 

We have determined that this 

proposed AD would not have federalism 

implications under Executive Order 

13132. This proposed AD 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. 

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–2004–19795; 

Directorate Identifier 2004–NM–196–AD. 

Comments Due Date 

(a) The Federal Aviation Administration 

(FAA) must receive comments on this AD 

action by January 18, 2005. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to Boeing Model 777–

200 and –300 series airplanes, certificated in 

any category; as listed in Boeing Special 

Attention Service Bulletin 777–33–0025, 

dated September 1, 2004. 

Unsafe Condition 

(d) This AD was prompted by a report of 

an aft cargo fire during flight. We are issuing 

this AD to prevent a fire in the cargo 

compartment. 

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. 

Lamp Replacement 

(f) Within 18 months after the effective 

date of this AD, replace all halogen lamps in 

the cargo compartment ceiling light 

assemblies with new incandescent lamps, 

and install warning and identification 

placards; in accordance with Boeing Special 

Attention Service Bulletin 777–33–0025, 

dated September 1, 2004. 

Parts Installation 

(g) As of the effective date of this AD, no 

person may install a halogen bulb, part 

number 9203, in any airplane cargo ceiling 

light assembly. 

Alternative Methods of Compliance 

(AMOCs) 

(h) 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 

November 26, 2004. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service.

[FR Doc. 04–26665 Filed 12–2–04; 8:45 am] 

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration 

14 CFR Part 39

[Docket No. FAA–2004–19796; Directorate 

Identifier 2004–NM–61–AD] 

RIN 2120–AA64

Airworthiness Directives; Boeing 

Model 747–100, –100B, –100B SUD, 

–200B, –200C, –300, –400, and –400D 

Series Airplanes; and Model 747SR 

Series Airplanes

AGENCY: Federal Aviation 

Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: The FAA proposes to 

supersede an existing airworthiness 

directive (AD) for certain Boeing Model 

747 series airplanes. That AD currently 

requires a one-time inspection to 

determine the material type of the stop 

support fittings of the main entry doors 

(MEDs). That AD also currently requires 

repetitive detailed inspections to detect 

cracks of certain stop support fittings of 

the MEDs, and replacement of any 

cracked stop support fitting with a 

certain new stop support fitting. This 

proposed AD would add new 

inspections and replacement if 

necessary of the stop support fittings of 

MED 3, and add airplanes to the 

applicability. This proposed AD is 

prompted by reports of MED 3 having 

certain stop support fittings which are 

susceptible to stress corrosion cracking. 

We are proposing this AD to detect and 

correct stress corrosion cracking of the 

stop support fittings of the MEDs, which 

could result in damage to the adjacent 

forward edge frame of the door and 

consequent loss of a MED and rapid 

decompression of the airplane.

DATES: We must receive comments on 

this proposed AD by January 18, 2005.

ADDRESSES: Use one of the following 

addresses to submit comments on this 

proposed AD. 

• DOT Docket Web site: Go to http:/

/dms.dot.gov and follow the instructions 

for sending your comments 

electronically. 

• Government-wide rulemaking web 

site: Go to http://www.regulations.gov

and follow the instructions for sending 

your comments electronically. 

• Mail: Docket Management Facility; 

U.S. Department of Transportation, 400 

Seventh Street SW., Nassif Building, 

room PL–401, Washington, DC 20590. 

• Fax: (202) 493–2251. 

• Hand Delivery: room PL–401 on the 

plaza level of the Nassif Building, 400 

Seventh Street SW., Washington, DC, 

between 9 a.m. and 5 p.m., Monday 

through Friday, except Federal holidays. 

For service information identified in 

this proposed AD, contact Boeing 

Commercial Airplanes, P.O. Box 3707, 

Seattle, Washington 98124–2207. 

You can examine the contents of this 

AD docket on the Internet at http://

dms.dot.gov, or at the Docket 

Management Facility, U.S. Department 

of Transportation, 400 Seventh Street 

SW., room PL–401, on the plaza level of 

the Nassif Building, Washington, DC.

FOR FURTHER INFORMATION CONTACT:

Technical information: Ivan Li, 

Aerospace Engineer, Airframe Branch, 

ANM–120S, FAA, Seattle Aircraft 

Certification Office, 1601 Lind Avenue, 

SW., Renton, Washington 98055–4056; 

Federal Register / Vol. 69, No. 232 / Friday, December 3, 2004 / Proposed Rules 70205

telephone (425) 917–6437; fax (425) 

917–6590. 

Plain language information: Marcia 

Walters, marcia.walters@faa.gov.

SUPPLEMENTARY INFORMATION: 

Docket Management System (DMS) 

The FAA has implemented new 

procedures for maintaining AD dockets 

electronically. As of May 17, 2004, new 

AD actions are posted on DMS and 

assigned a docket number. We track 

each action and assign a corresponding 

directorate identifier. The DMS AD 

docket number is in the form ‘‘Docket 

No. FAA–2004–99999.’’ The Transport 

Airplane Directorate identifier is in the 

form ‘‘Directorate Identifier 2004–NM–

999–AD.’’ Each DMS AD docket also 

lists the directorate identifier (‘‘Old 

Docket Number’’) as a cross-reference 

for searching purposes. 

Comments Invited 

We invite you to submit any written 

relevant data, views, or arguments 

regarding this proposed AD. Send your 

comments to an address listed under 

ADDRESSES. Include ‘‘Docket No. FAA–

2004–19796; Directorate Identifier 

2004–NM–61–AD’’ at the beginning of 

your comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of the proposed AD. We will 

consider all comments received by the 

closing date and may amend the 

proposed AD in light of those 

comments. 

We will post all comments we 

receive, without change, to http://

dms.dot.gov, including any personal 

information you provide. We will also 

post a report summarizing each 

substantive verbal contact with FAA 

personnel concerning this proposed AD. 

Using the search function of our docket 

Web site, anyone can find and read the 

comments in any of our dockets, 

including the name of the individual 

who sent the comment (or signed the 

comment on behalf of an association, 

business, labor union, etc.). You may 

review the DOT’s complete Privacy Act 

Statement in the Federal Register

published on April 11, 2000 (65 FR 

19477–78), or you may visit http://

dms.dot.gov.

We are reviewing the writing style we 

currently use in regulatory documents. 

We are interested in your comments on 

whether the style of this document is 

clear, and your suggestions to improve 

the clarity of our communications that 

affect you. You can get more 

information about plain language at 

http://www.faa.gov/language and http://

www.plainlanguage.gov.

Examining the Docket 

You can examine the AD docket in 

person at the Docket Management 

Facility office between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. The Docket 

Management Facility office (telephone 

(800) 647–5227) is located on the plaza 

level of the Nassif Building at the DOT 

street address stated in the ADDRESSES

section. Comments will be available in 

the AD docket shortly after the DMS 

receives them. 

Discussion 

On December 14, 1998, we issued AD 

98–26–13, amendment 39–10954 (63 FR 

70316, December 21, 1998), for certain 

Boeing Model 747–100, –100B, –200, 

–200B, –200C, –300, –400, and 747SR 

series airplanes having line numbers 1 

through 830 inclusive. That AD requires 

a one-time inspection to determine the 

material type of the stop support fittings 

of the main entry doors (MEDs). That 

AD also currently requires repetitive 

detailed inspections to detect cracks of 

certain stop support fittings of the 

MEDs, and replacement of any cracked 

stop support fitting with a certain new 

stop support fitting. That AD was 

prompted by reports that stress 

corrosion cracking was found on certain 

stop support fittings of the MEDs. We 

issued that AD to detect and correct 

stress corrosion cracking of the stop 

support fittings of the MEDs, which 

could lead to failure of the stop support 

fittings, consequent loss of a MED, and 

rapid decompression of the airplane. 

Actions Since Existing AD Was Issued 

Since we issued AD 98–26–13, we 

received a report from the manufacturer 

that the new stop support fittings 

installed in production for MED 3 on 

airplanes after line number 830 may not 

have been made of the correct material 

type. In addition, the new stop support 

fittings supplied by Boeing as the 

replacement fitting for MED 3 may not 

have been made from the correct 

material type. 

Relevant Service Information 

We have reviewed Boeing Special 

Attention Service Bulletin 747–53–

2485, dated January 8, 2004. The service 

bulletin describes procedures for 

performing a high frequency eddy 

current (HFEC) inspection to determine 

the material type of the stop support 

fittings of MED 3. The service bulletin 

also describes procedures for repetitive 

visual inspections to detect cracks of the 

stop support fittings (not made from 

7075–T73 or 7050–T7451 material) of 

MED 3, and replacement of any cracked 

fitting with a new fitting made from 

7075–T73 or 7050–T7451 material. In 

addition, the service bulletin describes 

procedures for optional replacement of 

the stop support fittings of the MEDs 

with stop support fittings made from 

7075–T73 or 7050–T7451 material, 

which would eliminate the need for 

repetitive inspections. The new stop 

support fitting is less susceptible to 

stress corrosion cracking. 

The FAA has reviewed Boeing Service 

Bulletin 747–53–2358, Revision 1, dated 

April 19, 2001 (the original issue, dated 

August 26, 1993, is referenced as the 

appropriate source of service 

information for accomplishing AD 98–

26–13). Revision 1 of the service 

bulletin describes procedures for 

performing an HFEC inspection to 

determine the material type of the stop 

support fittings of the MEDs. The 

service bulletin also describes 

procedures for repetitive visual 

inspections to detect cracks of the stop 

support fitting (not made from 7075–

T73 or 7050–T7451 material) of the 

MEDs, and replacement of any cracked 

fitting with a new fitting made from 

7075–T73 or 7050–T7451 material. In 

addition, the service bulletin describes 

procedures for optional replacement of 

the stop support fittings of the MEDs 

with stop support fittings made from 

7075–T73 or 7050–T7451 material, 

which would eliminate the need for 

repetitive inspections. The new stop 

support fitting is less susceptible to 

stress corrosion cracking. 

We have determined that 

accomplishment of the actions specified 

in the service information will 

adequately address the unsafe 

condition. 

FAA’s Determination and Requirements 

of the Proposed AD 

We have evaluated all pertinent 

information and identified an unsafe 

condition that is likely to exist or 

develop on other products of this same 

type design. Therefore, we are 

proposing this AD, which would 

supersede AD 98–26–13. This proposed 

AD would continue to require a onetime inspection to determine the 

material type of the stop support fittings 

of the MEDs. This proposed AD would 

also continue to require repetitive 

detailed inspections to detect cracks of 

certain stop support fittings of the 

MEDs, and replacement of any cracked 

stop support fitting with a certain new 

stop support fitting. This proposed AD 

would also require new inspections and 

replacement if necessary of the stop 

support fittings of MED 3 and add 

airplanes to the applicability. This 

proposed AD would require you to use 

the service information described 

70206 Federal Register / Vol. 69, No. 232 / Friday, December 3, 2004 / Proposed Rules 

previously to perform these actions, 

except as discussed under ‘‘Differences 

Between the Proposed AD and Service 

Bulletins.’’

Differences Between the Proposed AD 

and Service Bulletins 

For certain airplanes, Boeing Special 

Attention Service Bulletin 747–53–

2485, dated January 8, 2004, specifies an 

inspection threshold of 6 years after the 

airplane was delivered or 18 months 

since the release of the service bulletin, 

whichever occurs later. However, for 

these same airplanes, paragraph (i) of 

the proposed AD specifies an inspection 

threshold of 72 months after the date of 

issuance of the original Airworthiness 

Certificate or the date of issuance of the 

original Export Certificate of 

Airworthiness, or 18 months after the 

effective date of the AD, whichever 

occurs later. This decision is based on 

our determination that the date the 

airplane was delivered may be 

interpreted differently by different 

operators. We find that our proposed 

terminology is generally understood 

within the industry and records will 

always exist that establish these dates 

with certainty.

Whereas Boeing Service Bulletin 747–

53–2358, dated August 26, 1993; and 

Boeing Service Bulletin 747–53–2358, 

Revision 1, dated April 19, 2001; specify 

a ‘‘visual inspection,’’ the intent of the 

proposed AD is to require a ‘‘detailed 

inspection.’’ Additionally, a note has 

been added to the proposed AD to 

define that inspection. 

Explanation of Change to Applicability 

We have revised the applicability of 

the existing AD to identify model 

designations as published in the most 

recent type certificate data sheet for the 

affected models. In paragraphs (f) and 

(g) of the proposed AD, the model 

designation ‘‘747–100B SUD’’ has been 

added. There is no increase in the 

number of applicable airplanes for these 

paragraphs. 

Clarification of Inspection Type 

Although Boeing Special Attention 

Service Bulletin 747–53–2485, dated 

January 8, 2004, specifies a ‘‘detailed 

visual inspection,’’ this proposed AD 

requires a ‘‘detailed inspection.’’

Clarification of Service Bulletin 

Operators should also note that 

Boeing Service Bulletin 747–53–2358, 

Revision 1, dated April 19, 2001, 

specifies in the ‘‘Action’’ and 

‘‘Description’’ paragraphs that you can 

end the repetitive inspections if you 

replace the stop support fittings with 

stop support fittings made from 7075–

T73 or 7050–T7451 material. However, 

the Note under ‘‘Stop Support Fitting 

Replacement’’ of the Work Instructions 

of the service bulletin only specifies 

ending repetitive inspections if you 

replace with stop support fittings made 

from 7075–T73. Replacing with stop 

support fittings made of 7075–T73 or 

7050–T7451 material does end the 

repetitive inspections as both are less 

susceptible to stress corrosion cracking. 

Change to the Number of Airplanes in 

the Costs of Compliance 

Operators should note that for AD 98–

26–13 we estimated that there are about 

575 airplanes of the affected design in 

the worldwide fleet and that about 164 

airplanes of U.S. registry would be 

affected by that AD. However, for this 

proposed AD, which includes actions 

required by AD 98–26–13, we estimate 

that there are 814 airplanes of the 

affected design in the worldwide fleet 

and that 119 airplanes of U.S. registry 

would be affected by the proposed AD. 

The increase in the number of airplanes 

worldwide is due to the expanded 

applicability. The decrease in number of 

airplanes of U.S. registry may be due to 

a number of reasons such as retirement 

of airplanes and transfer of airplanes to 

foreign operators. 

Change to Existing AD 

This proposed AD would retain all 

requirements of AD 98–26–13. Since AD 

98–26–13 was issued, the AD format has 

been revised, and certain paragraphs 

have been rearranged. As a result, the 

corresponding paragraph identifiers 

have changed in this proposed AD, as 

listed in the following table:

REVISED PARAGRAPH IDENTIFIERS

Requirement in AD 98–

26–13

Corresponding 

requirement in 

this proposed AD 

Paragraph (a) ................... Paragraph (f). 

Paragraph (b) ................... Paragraph (g). 

Paragraph (c) ................... Paragraph (l). 

Costs of Compliance 

There are about 814 airplanes of the 

affected design in the worldwide fleet. 

There are about 119 airplanes of U.S. 

registry that would be affected by this 

proposed AD. The following table 

provides the estimated costs for U.S. 

operators to comply with this proposed 

AD.

ESTIMATED COSTS

Action Work hours 

Average 

labor rate 

per hour 

Parts Cost per 

door 

HFEC Inspection (required by AD 98–26–13) ................................................................ 1 $65 None $65

Detailed Inspection as applicable (required by AD 98–26–13) ....................................... 2 65 None 130

Optional Terminating Action (specified in AD 98–26–13) ............................................... 124 65 $13,000 21,060

Detailed Inspection and HFEC Inspection as applicable (new proposed action) ........... 3 65 None 195

Replacement as applicable (new proposed action) ........................................................ 120 65 17,724 25,524

Authority for This Rulemaking 

The FAA’s authority to issue rules 

regarding aviation safety is found in 

Title 49 of the United States Code. 

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. 

This rulemaking is promulgated 

under the authority described in 

Subtitle VII, Part A, Subpart III, Section 

44701, ‘‘General requirements.’’ Under 

that section, the FAA is charged 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 proposed AD. 

Regulatory Findings 

We have determined that this 

proposed AD would not have federalism 

implications under Executive Order 

13132. This proposed AD 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

Federal Register / Vol. 69, No. 232 / Friday, December 3, 2004 / Proposed Rules 70207

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 

removing amendment 39–10954 (63 FR 

70316, December 21, 1998) and adding 

the following new airworthiness 

directive (AD):

Boeing: Docket No. FAA–2004–19796; 

Directorate Identifier 2004–NM–61–AD. 

Comments Due Date 

(a) The Federal Aviation Administration 

must receive comments on this airworthiness 

directive (AD) action by January 18, 2005. 

Affected ADs 

(b) This AD supersedes AD 98–26–13, 

amendment 39–10954. 

Applicability 

(c) This AD applies to Boeing Model 747–

100, –100B, –100B SUD, –200B, –200C, –300, 

–400, and –400D series airplanes; and Model 

747SR series airplanes; having line numbers 

1 through 1301 inclusive; certificated in any 

category. 

Unsafe Condition 

(d) This AD was prompted by reports of 

main entry door (MED) 3 having certain stop 

support fittings which are susceptible to 

stress corrosion cracking. We are issuing this 

AD to detect and correct stress corrosion 

cracking of the stop support fittings of the 

MEDs which could result in damage to the 

adjacent forward edge frame of the door and 

consequent loss of a MED and rapid 

decompression of the airplane. 

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. 

Requirements of AD 98–26–13

Inspections and Corrective Action 

(f) For Model 747–100, –100B, –100B SUD, 

–200, –200B, –200C, –300, –400, and 747SR 

series airplanes having line numbers 1 

through 830 inclusive: Within 18 months 

after January 25, 1999 (the effective date of 

AD 98–26–13, amendment 39–10954), 

perform a high frequency eddy current 

(HFEC) inspection to determine the material 

type of the stop support fittings of the MEDs, 

in accordance with the Accomplishment 

Instructions of Boeing Service Bulletin 747–

53–2358, dated August 26, 1993; or Boeing 

Service Bulletin 747–53–2358, Revision 1, 

dated April 19, 2001. Perform the inspection 

only at those locations where the material 

type of the stop support fittings is unknown, 

as specified in Figure 3, Table 1, of either 

service bulletin. As of the effective date of 

this AD, do the actions in accordance with 

Boeing Service Bulletin 747–53–2358, 

Revision 1, dated April 19, 2001. 

(1) If the fitting is made from 7075–T73 or 

7050–T7451 material, no further action is 

required by this AD for that fitting; however, 

the requirements of paragraph (l) of this AD 

still applies. 

(2) If the fitting is not made from 7075–T73 

or 7050–T7451 material, before further flight, 

perform a detailed inspection to detect cracks 

of the stop support fitting of the MEDs, in 

accordance with the applicable service 

bulletin.

Note 1: For the purposes of this AD, a 

detailed inspection is ‘‘an intensive 

examination of a specific item, installation, 

or assembly to detect damage, failure, or 

irregularity. Available lighting is normally 

supplemented with a direct source of good 

lighting at an intensity deemed appropriate. 

Inspection aids such as mirrors magnifying 

lenses, etc. may be necessary. Surface 

cleaning and elaborate procedures may be 

required.’’

(i) If no crack is detected, repeat the 

detailed inspection thereafter at intervals not 

to exceed 36 months or 2,000 flight cycles, 

whichever occurs first. 

(ii) If any crack is detected, before further 

flight, replace the fitting with a stop support 

fitting made from 7075–T73 or 7050–T7451 

material, in accordance with the applicable 

service bulletin. 

(g) For Model 747–100, –100B, –100B SUD, 

–200, –200B, –200C, –300, –400, and 747SR 

series airplanes having line numbers 1 

through 830 inclusive: Replacement of the 

stop support fitting of the MEDs with a stop 

support fitting made from 7075–T73 material, 

in accordance with Boeing Service Bulletin 

747–53–2358, dated August 26, 1993; or 

replacement with a stop support fitting made 

from 7075–T73 or 7050–T7451 material, in 

accordance with Boeing Service Bulletin 

747–53–2358, Revision 1, dated April 19, 

2001; constitutes terminating action for the 

repetitive inspection requirements of 

paragraph (f) of this AD for the replaced 

fitting. As of the effective date of this AD, 

only Boeing Service Bulletin 747–53–2358, 

Revision 1, dated April 19, 2001, may be 

used. 

New Requirements of This AD 

Inspection for Material Type 

(h) For Model 747–100, –100B, –100B 

SUD, –200B, –200C, –300, –400, and –400D 

series airplanes, and Model 747SR series 

airplanes, having line numbers 1 through 830 

inclusive on which the actions specified in 

the Accomplishment Instructions of Boeing 

Service Bulletin 747–53–2358, dated August 

26, 1993; or Boeing Service Bulletin 747–53–

2358, Revision 1, dated April 19, 2001; have 

been done: Do the inspection specified in 

paragraph (h)(1) or (h)(2) of this AD, as 

applicable, at the time specified. 

(1) Except as provided by paragraph (h)(2) 

of this AD, if any stop support fitting, 2L 

through 6L and 2R through 6R, of MED 3, 

was replaced before the effective date of this 

AD: Perform a one-time HFEC inspection to 

determine the material type of the stop 

support fittings of MED 3 that were replaced, 

in accordance with the Accomplishment 

Instructions of Boeing Special Attention 

Service Bulletin 747–53–2485, dated January 

8, 2004, at the later of the times specified in 

paragraphs (h)(1)(i) and (h)(1)(ii) of this AD. 

(i) Within 72 months after the stop support 

fitting of MED 3 was replaced. 

(ii) Within 18 months after the effective 

date of this AD. 

(2) If any stop support fitting, 2L through 

6L and 2R through 6R, of MED 3, cannot be 

determined conclusively by reviewing 

airplane maintenance records that the fitting 

was not replaced, within 18 months after the 

effective date of this AD, perform a one-time 

HFEC inspection to determine the material 

type of the stop support fitting, in accordance 

with the Accomplishment Instructions of 

Boeing Special Attention Service Bulletin 

747–53–2485, dated January 8, 2004. 

(i) For airplanes having line numbers 831 

through 1301 inclusive: At the later of the 

times specified in paragraphs (i)(1) and (i)(2) 

of this AD, perform a one-time HFEC 

inspection to determine the material type of 

the stop support fittings of MED 3 in 

accordance with the Accomplishment 

Instructions of Boeing Special Attention 

Service Bulletin 747–53–2485, dated January 

8, 2004. 

(1) Before 72 months since the date of 

issuance of the original Airworthiness 

Certificate or the date of issuance of the 

original Export Certificate of Airworthiness. 

(2) Within 18 months after the effective 

date of this AD. 

No Further Action 

(j) If, during any HFEC inspection required 

by paragraph (h) or (i) of this AD, any fitting 

is found to be made of 7075–T73 or 7050–

T7451 material, no further action is required 

by this AD for that fitting; however, 

paragraph (l) of this AD still applies. 

70208 Federal Register / Vol. 69, No. 232 / Friday, December 3, 2004 / Proposed Rules 

Initial and Repetitive Inspections for 

Cracking and Corrective Action 

(k) If, during any HFEC inspection required 

by paragraph (h) or (i) of this AD, any fitting 

is found not to be made of 7075–T73 or 

7050–T7451 material, before further flight, 

perform a detailed inspection for cracks of 

the fitting in accordance with the 

Accomplishment Instructions of Boeing 

Special Attention Service Bulletin 747–53–

2485, dated January 8, 2004. 

(1) If no crack is detected, repeat the 

detailed inspection specified in paragraph (k) 

of this AD thereafter at intervals not to 

exceed 36 months or 2,000 flight cycles, 

whichever comes first. Doing the 

replacement specified in paragraph (k)(2) of 

this AD ends the repetitive inspections for 

the replaced fitting.

(2) If any crack is detected, before further 

flight, replace the fitting with a fitting made 

of 7075–T73 or 7050–T7451 material in 

accordance with the Accomplishment 

Instructions of Boeing Special Attention 

Service Bulletin 747–53–2485, dated January 

8, 2004. No further action is required by this 

AD for that fitting; however, paragraph (l) of 

this AD still applies. 

Parts Installation 

(l) As of the date specified in paragraph 

(l)(1) or (l)(2) of this AD, as applicable, no 

person shall install on any airplane a stop 

support fitting of the MEDs made from either 

7079–T651 or 7075–T651 material. 

(1) For airplanes having line numbers 1 

through 830 inclusive: As of January 25, 

1999. 

(2) For airplanes having line numbers 831 

through 1301 inclusive: As of the effective 

date of this AD. 

Alternative Methods of Compliance (AMOCs) 

(m)(1) The Manager, Seattle Aircraft 

Certification Office (ACO), FAA, has the 

authority to approve AMOCs for this AD, if 

requested using the procedures found in 14 

CFR 39.19. 

(2) AMOCs, approved previously per AD 

98–26–13, amendment 39–10954, are 

approved as AMOCs with paragraph (f) or (g) 

of this AD, as applicable. However, any stop 

support fitting, 2L through 6L and 2R 

through 6R, of MED 3 that was replaced is 

still required to be inspected as required in 

paragraph (h) of this AD.

Issued in Renton, Washington, on 

November 26, 2004. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service.

[FR Doc. 04–26664 Filed 12–2–04; 8:45 am] 

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration 

14 CFR Part 71

[Docket No. FAA–2004–19410; Airspace 

Docket No. 04–ANM–09] 

RIN 2120–AA66

Proposed Revision of Federal Airways 

V–2, V–257 and V–343; MT

AGENCY: Federal Aviation 

Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking.

SUMMARY: This action proposes to revise 

three Very High Frequency 

Omnidirectional Range (VOR) Federal 

airways southeast of Missoula, MT (V–

2, V–257, and V–343). These VOR 

Federal airways are being impacted due 

to the decommissioning of the 

Drummond VOR and would be revised 

or eliminated by this proposed action.

DATES: Comments must be received on 

or before January 18, 2005.

ADDRESSES: Send comments on this 

proposal to the Docket Management 

System, U.S. Department of 

Transportation, Room Plaza 401, 400 

Seventh Street, SW., Washington, DC 

20590–0001. You must identify FAA 

Docket No. FAA–2004–19410 and 

Airspace Docket No. 04–ANM–09, at the 

beginning of your comments. You may 

also submit comments on the Internet at 

http://dms.dot.gov.

FOR FURTHER INFORMATION CONTACT: Ken 

McElroy, Airspace and Rules Division, 

Office of System Operations and Safety, 

Federal Aviation Administration, 800 

Independence Avenue, SW., 

Washington, DC 20591; telephone: (202) 

267–8783.

SUPPLEMENTARY INFORMATION: 

Comments Invited 

Interested parties are invited to 

participate in this proposed rulemaking 

by submitting such written data, views, 

or arguments, as they may desire. 

Comments that provide the factual basis 

supporting the views and suggestions 

presented are particularly helpful in 

developing reasoned regulatory 

decisions on the proposal. Comments 

are specifically invited on the overall 

regulatory, aeronautical, economic, 

environmental, and energy-related 

aspects of the proposal. 

Communications should identify both 

docket numbers (FAA Docket No. FAA–

2004–19410 and Airspace Docket No. 

04–ANM–09) and be submitted in 

triplicate to the Docket Management 

System (see ADDRESSES section for 

address and phone number). You may 

also submit comments through the 

Internet at http://dms.dot.gov. 

Commentors wishing the FAA to 

acknowledge receipt of their comments 

on this notice must submit with those 

comments a self-addressed, stamped 

postcard on which the following 

statement is made: ‘‘Comments to FAA 

Docket No. FAA–2004–19410 and 

Airspace Docket No. 04–ANM–09.’’ The 

postcard will be date/time stamped and 

returned to the commenter. 

All communications received on or 

before the specified closing date for 

comments will be considered before 

taking action on the proposed rule. The 

proposal contained in this notice may 

be changed in light of comments 

received. All comments submitted will 

be available for examination in the 

public docket both before and after the 

closing date for comments. A report 

summarizing each substantive public 

contact with FAA personnel concerned 

with this rulemaking will be filed in the 

docket. 

Availability of NPRM’s 

An electronic copy of this document 

may be downloaded through the 

Internet at http://dms.dot.gov. Recently 

published rulemaking documents can 

also be accessed through the FAA’s Web 

page at http://www.faa.gov or the 

Federal Register’s Web page at http://

www.gpoaccess.gov/fr/index.html. 

You may review the public docket 

containing the proposal, any comments 

received, and any final disposition in 

person in the Dockets Office (see

ADDRESSES section for address and 

phone number) between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. An informal docket 

may also be examined during normal 

business hours at the office of the 

Regional Air Traffic Division, Federal 

Aviation Administration, 1601 Lind 

Avenue, SW., Renton, WA 98055–4056. 

Persons interested in being placed on 

a mailing list for future NPRM’s should 

call the FAA’s Office of Rulemaking, 

(202) 267–9677, for a copy of Advisory 

Circular No. 11–2A, Notice of Proposed 

Rulemaking Distribution System, which 

describes the application procedure. 

Background 

The Drummond VOR has been out of 

service since April 2003, for the reasons 

discussed below, and the site on which 

the VOR was located was leased land. 

In 2002, the FAA learned that the 

landowner had constructed a house 

within 1,000 feet of the VOR without 

providing proper notice to the FAA. The 

VOR was temporarily taken out of 

service until the impacts of the house 

could he identified. A subsequent flight