Federal Register / Vol. 69, No. 236 / Thursday, December 9, 2004 / Rules and Regulations 71349

perform the actions that are required by this 

AD, unless the AD specifies otherwise. The 

Director of the Federal Register approves the 

incorporation by reference of this document 

in accordance with 5 U.S.C. 552(a) and 1 CFR 

part 51. For copies of the service information, 

contact Boeing Commercial Airplanes, P.O. 

Box 3707, Seattle, Washington 98124–2207. 

For information on the availability of this 

material at the National Archives and 

Records Administration (NARA), call (202) 

741–6030, or go to http://www.archives.gov/

federal_register/code_of_federal_regulations/

ibr_locations.html. You may view the AD 

docket at the Docket Management Facility, 

U.S. Department of Transportation, 400 

Seventh Street SW., room PL–401, Nassif 

Building, Washington, DC.

Issued in Renton, Washington, on 

November 30, 2004. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service.

[FR Doc. 04–26794 Filed 12–8–04; 8:45 am] 

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration 

14 CFR Part 39

[Docket No. FAA–2004–19811; Directorate 

Identifier 2004–NM–201–AD; Amendment 

39–13893; AD 2004–25–05] 

RIN 2120–AA64

Airworthiness Directives; Boeing 

Model 747–100, 747–100B, 747–100B 

SUD, 747–200B, 747–200C, 747–200F, 

747–300, 747SP, and 747SR Series 

Airplanes

AGENCY: Federal Aviation 

Administration (FAA), DOT.

ACTION: Final rule; request for 

comments. 

SUMMARY: The FAA is adopting a new 

airworthiness directive (AD) for certain 

Boeing Model 747–100, 747–100B, 747–

100B SUD, 747–200B, 747–200C, 747–

200F, 747–300, 747SP, and 747SR series 

airplanes. This AD requires repetitive 

inspections to detect cracks and 

fractures of the strut front spar chord 

assembly at each strut location, and 

repair if necessary. This AD is prompted 

by a report of a fractured front spar 

chord assembly for strut No. 3, which 

resulted in the loss of the strut upper 

link load path. We are issuing this AD 

to prevent loss of the strut upper link 

load path and consequent fracture of the 

diagonal brace, which could result in inflight separation of the strut and engine 

from the airplane.

DATES: Effective December 27, 2004. 

The incorporation by reference of 

certain publications listed in the AD is 

approved by the Director of the Federal 

Register as of December 27, 2004. 

We must receive comments on this 

AD by February 7, 2005.

ADDRESSES: Use one of the following 

addresses to submit comments on this 

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 9:00 a.m. and 5:00 p.m., 

Monday through Friday, except Federal 

holidays. 

For service information identified in 

this AD, contact Boeing Commercial 

Airplanes, PO Box 3707, Seattle, 

Washington 98124–2207. You can 

examine this information at the National 

Archives and Records Administration 

(NARA). For information on the 

availability of this material at NARA, 

call (202) 741–6030, or go to: http://

www.archives.gov/federal_register/

code_of_federal_regulations/

ibr_locations.html.

You can examine the contents of this 

AD docket on the Internet at http://

dms.dot.gov, or in person 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. 

This docket number is FAA–2004–

19811; the directorate identifier for this 

docket is 2004–NM–201–AD. 

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. 

Examining the Dockets 

You can examine the AD docket on 

the Internet at http://dms.dot.gov, or 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.

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; 

telephone (425) 917–6437; fax (425) 

917–6590. Plain language information:

Marcia Walters, marcia.walters@faa.gov.

SUPPLEMENTARY INFORMATION: We have 

received a report indicating that the 

front spar chord assembly for strut No. 

3 fractured on a Boeing Model 747–

200B series airplane that had 

accumulated a total of 16,604 flight 

cycles and 79,013 flight hours. The front 

spar chord assembly fractured 4.37 

inches forward of the upper link attach 

lug. The manufacturer’s analysis 

showed that the fitting fractured as the 

result of fatigue at a critical stress area. 

Fracture of the front spar chord 

assembly will result in the loss of the 

strut upper link load path. Loss of the 

upper link load path would result in the 

transfer of additional loads to the 

diagonal brace load path, which could 

result in fracture of the diagonal brace. 

This condition, if not corrected, could 

result in in-flight separation of the strut 

and engine from the airplane.

Relevant Service Information 

We have reviewed Boeing Alert 

Service Bulletin (ASB) 747–54A2224, 

dated September 30, 2004. The ASB 

describes procedures for accomplishing 

detailed and high frequency eddy 

current (HFEC) inspections of the strut 

front spar chord assembly for cracks and 

fractures at each strut location. The ASB 

also specifies, if any crack or fracture is 

found, to contact the manufacturer for 

additional instructions and repair. 

Accomplishing the actions specified in 

the service information is intended to 

adequately address the unsafe 

condition. 

FAA’s Determination and Requirements 

of This AD 

The unsafe condition described 

previously is likely to exist or develop 

on other airplanes of the same type 

design. Therefore, we are issuing this 

AD to prevent loss of the strut upper 

link load path and consequent fracture 

71350 Federal Register / Vol. 69, No. 236 / Thursday, December 9, 2004 / Rules and Regulations 

of the diagonal brace, which could 

result in in-flight separation of the strut 

and engine from the airplane. This AD 

requires accomplishing the actions 

specified in the service information 

described previously, except as 

discussed under ‘‘Difference Between 

the AD and the ASB.’’

Difference Between the AD and the ASB 

The ASB specifies that you may 

contact the manufacturer for 

instructions on how to repair certain 

conditions, but this AD requires you to 

repair those conditions in one of the 

following ways: 

• Using a method that we approve; or 

• Using data that meet the type 

certification basis of the airplane, and 

that have been approved by a Boeing 

Company Designated Engineering 

Representative who has been authorized 

by the FAA to make those findings. 

FAA’s Determination of the Effective 

Date 

An unsafe condition exists that 

requires the immediate adoption of this 

AD; therefore, providing notice and 

opportunity for public comment before 

the AD is issued is impracticable, and 

good cause exists to make this AD 

effective in less than 30 days. 

Comments Invited 

This AD is a final rule that involves 

requirements that affect flight safety and 

was not preceded by notice and an 

opportunity for public comment; 

however, we invite you to submit any 

relevant written data, views, or 

arguments regarding this AD. Send your 

comments to an address listed under 

ADDRESSES. Include ‘‘Docket No. FAA–

2004–19811; Directorate Identifier 

2004–NM–201–AD’’ at the beginning of 

your comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of the AD. We will consider all 

comments received by the closing date 

and may amend the 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 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 can review the DOT’s 

complete Privacy Act Statement in the 

Federal Register published on April 11, 

2000 (65 FR 19477–78), or you can 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 with 

you. You can get more information 

about plain language at http://www/

faa.gov/language and http://

www.plainlanguage.gov.

Regulatory Findings 

We have determined that this AD will 

not have federalism implications under 

Executive Order 13132. This AD will 

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 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 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, Incorporation by reference, 

Safety.

Adoption of the Amendment

■ Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA amends 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):

2004–25–05 Boeing: Amendment 39–13893. 

Docket No. FAA–2004–19811; 

Directorate Identifier 2004–NM–201–AD. 

Effective Date 

(a) This AD becomes effective December 

27, 2004. 

Applicability 

(b) This AD applies to Boeing 747–100, 

747–100B, 747–100B SUD, 747–200B, 747–

200C, 747–200F, 747–300, 747SP, and 747SR 

series airplanes; as listed in Boeing Alert 

Service Bulletin (ASB) 747–54A2224, dated 

September 30, 2004; certificated in any 

category. 

Unsafe Condition 

(c) This AD was prompted by a report of 

a fractured front spar chord assembly for 

strut No. 3, which resulted in the loss of the 

strut upper link load path. The FAA is 

issuing this AD to prevent loss of the strut 

upper link load path and consequent fracture 

of the diagonal brace, which could result in 

in-flight separation of the strut and engine. 

Compliance 

(d) You are responsible for having the 

actions required by this AD performed within 

the compliance times specified, unless the 

actions have already been done. 

Detailed and High Frequency Eddy Current 

(HFEC) Inspections 

(e) Within 90 days after the effective date 

of this AD, perform detailed and HFEC 

inspections to detect any cracks or fractures 

of the front spar chord assembly for struts 

Number 1 through 4 inclusive, in accordance 

with Boeing ASB 747–54A2224, dated 

September 30, 2004. 

(f) Accomplishment of the detailed and 

HFEC inspections in accordance with Boeing 

747 Fleet Team Digest 747–FTD–54–04002, 

dated April 15, 2004, May 4, 2004, June 1, 

2004, July 12, 2004, or July 28, 2004; or 

Boeing Message 1–C6ELC (Service Request ID 

No.: 218724992), dated April 14, 2004; before 

the effective date of this AD, is considered 

acceptable for compliance with the 

requirements of paragraph (e) of this AD. 

Repetitive Inspections 

(g) For airplanes on which no crack or 

fracture is detected: At the times specified in 

Table 1—Repetitive Intervals of this AD, 

perform the detailed and HFEC inspections 

required by paragraph (e) of this AD at the 

intervals specified in Table 1.

TABLE 1.—REPETITIVE INTERVALS

For Airplanes 

identified in 

Boeing ASB 

747–54A2224, 

dated September 30, 

2004, as—

At intervals not to exceed—

Group 1 .......... 1,000 flight cycles or 18 

months, whichever occurs 

first. 

Group 2 and 

Group 3.

1,200 flight cycles or 18 

months, whichever occurs 

first. 

Group 4 and 

Group 6.

1,500 flight cycles or 18 

months, whichever occurs 

first. 

Group 5 .......... 2,000 flight cycles or 18 

months, whichever occurs 

first. 

Federal Register / Vol. 69, No. 236 / Thursday, December 9, 2004 / Rules and Regulations 71351

Corrective Action 

(h) If any crack or fracture is found during 

any inspection required by this AD, and the 

bulletin specifies contacting Boeing for 

appropriate action: Before further flight, 

repair the crack or fracture according to 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 (DER) who has been 

authorized by the Manager, Seattle ACO, to 

make those findings. For a repair method to 

be approved, the approval must specifically 

reference this AD. 

Alternative Methods of Compliance 

(AMOCs) 

(i)(1) The Manager, Seattle ACO, FAA, has 

the authority to approve AMOCs for this AD, 

if requested in accordance with the 

procedures found in 14 CFR 39.19. 

(2) An AMOC that provides an acceptable 

level of safety may be used for any repair 

required by this AD, if it is approved by a 

Boeing Company DER who has been 

authorized by the Manager, Seattle ACO, to 

make those findings. For a repair method to 

be approved, the approval must specifically 

refer to this AD. 

Material Incorporated by Reference 

(j) You must use Boeing Alert Service 

Bulletin 747–54A2224, dated September 30, 

2004, to perform the actions that are required 

by this AD, unless the AD specifies 

otherwise. The Director of the Federal 

Register approves the incorporation by 

reference of this document in accordance 

with 5 U.S.C. 552(a) and 1 CFR part 51. For 

copies of the service information, contact 

Boeing Commercial Airplanes, PO Box 3707, 

Seattle, Washington 98124–2207. You can 

review copies at the Docket Management 

Facility, U.S. Department of Transportation, 

400 Seventh Street SW., room PL–401, Nassif 

Building, Washington, DC; or at the National 

Archives and Records Administration 

(NARA). For information on the availability 

of this material at NARA, call (202) 741–

6030, or go to http://www.archives.gov/

federal_register/code_of_federal_regulations/

ibr_locations.html.

Issued in Renton, Washington, on 

November 30, 2004. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service.

[FR Doc. 04–26793 Filed 12–8–04; 8:45 am] 

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2004–19816; Directorate 

Identifier 2004–NM–231–AD; Amendment 

39–13895; AD 2004–25–07] 

RIN 2120–AA64 

Airworthiness Directives; Airbus Model 

A330 and A340 Series Airplanes

AGENCY: Federal Aviation 

Administration (FAA), DOT.

ACTION: Final rule; request for 

comments. 

SUMMARY: The FAA is adopting a new 

airworthiness directive (AD) for certain 

Airbus Model A330 and A340 series 

airplanes. This AD requires regularly 

performing a complete electrical 

shutdown of the airplane to reset the 

integrated standby instrument system 

(ISIS). This AD also provides an 

optional terminating action. This AD is 

prompted by reports indicating that an 

airplane lost the ISIS, then, during the 

same flight, lost all electronic 

instrument system (EIS) display units. 

We are issuing this AD to prevent loss 

of the ISIS, which, if combined with 

loss of all EIS display units, could 

reduce the flightcrew’s situational 

awareness and contribute to loss of 

control of the airplane or impact with 

obstacles or terrain.

DATES: Effective December 27, 2004. 

The incorporation by reference of 

certain publications listed in the AD is 

approved by the Director of the Federal 

Register as of December 27, 2004. 

We must receive comments on this 

AD by February 7, 2005.

ADDRESSES: Use one of the following 

addresses to submit comments on this 

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 AD, contact Airbus, 1 Rond Point 

Maurice Bellonte, 31707 Blagnac Cedex, 

France. You can examine this 

information at the National Archives 

and Records Administration (NARA). 

For information on the availability of 

this material at NARA, call (202) 741–

6030, or go to: http://www.archives.gov/

federal_register/

code_of_federal_regulations/

ibr_locations.html. 

You can examine the contents of this 

AD docket on the Internet at http://

dms.dot.gov, or in person 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. 

This docket number is FAA–2004–

19816; the directorate identifier for this 

docket is 2004–NM–231–AD. 

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. 

Examining the Docket 

You can examine the AD docket on 

the Internet at http://dms.dot.gov, or 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.

FOR FURTHER INFORMATION CONTACT:

Technical information: Tim Backman, 

Aerospace Engineer, International 

Branch, ANM–116, FAA, Transport 

Airplane Directorate, 1601 Lind 

Avenue, SW., Renton, Washington 

98055–4056; telephone (425) 227–2797; 

fax (425) 227–1149. 

Plain language information: Marcia 

Walters, marcia.walters@faa.gov.

SUPPLEMENTARY INFORMATION: The 

Direction Generale de l’Aviation Civile 

(DGAC), which is the airworthiness 

authority for France, notified the FAA 

that an unsafe condition may exist on 

certain Airbus Model A330 and A340