Federal Register / Vol. 69, No. 236 / Thursday, December 9, 2004 / Rules and Regulations 71347

(1) Place a suitable container under the fuel 

strainer drain outlet prior to operating the 

strainer drain control for at least 4 seconds. 

Check strainer to ensure drain is closed.(2) 

Inspect the fluid drained from the fuel 

strainer and each wing tank quick drain for 

evidence of fuel contamination in the form of 

water, rust, sludge, ice, or any other 

substance not compatible with fuel. Also 

check for proper fuel grade before the first 

flight of each day and after each refueling. If 

any contamination is detected, comply with 

paragraph (f)(4) of this AD. 

(3) Repeat steps in paragraph (f)(1) and 

(f)(2) of this AD on each wing tank quick 

drain. 

(4) If the airplane has been exposed to rain, 

sleet, or snow, or if the wing fuel tanks or 

fuel strainer drains produce water or other 

contamination, you must purge the airplane 

fuel system to the extent necessary to ensure 

that there is no water, ice, or other fuel 

contamination. 

May I Request Another AMOC for This AD? 

(g) You may request a different method of 

compliance or a different compliance time 

for this AD by following the procedures in 14 

CFR 39.19. Unless FAA authorizes otherwise, 

send your request to your principal 

inspector. The principal inspector may add 

comments and will send your request to the 

Manager, Wichita Aircraft Certification Office 

(ACO), FAA. For information on any already 

approved alternative methods of compliance, 

contact Paul O. Pendleton, Aerospace 

Engineer, FAA, Wichita ACO, 1801 Airport 

Road, Room 100, Mid-Continent Airport, 

Wichita, Kansas 67209; telephone: (316) 946–

4143; facsimile: (316) 946–4107. 

Does This AD Incorporate Any Material by 

Reference? 

(h) You must do the actions required by 

this AD following the instructions in O & N 

Aircraft Modifications Inc. Mandatory 

Service Bulletin No. ON–100, dated February 

1, 1998. The Director of the Federal Register 

approved the incorporation by reference of 

this service bulletin in accordance with 5 

U.S.C. 552(a) and 1 CFR part 51. You may get 

a copy from O & N Aircraft Modifications 

Inc., 210 Windsock Lane, Seamans Airport, 

Factoryville, PA 18419. You may review 

copies at FAA, Central Region, Office of the 

Regional Counsel, 901 Locust, Room 506, 

Kansas City, Missouri 64106; 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 Kansas City, Missouri, on 

December 1, 2004. 

David A. Downey, 

Acting Manager, Small Airplane Directorate, 

Aircraft Certification Service.

[FR Doc. 04–26915 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–2004–19228; Directorate 

Identifier 2004–NM–77–AD; Amendment 39–

13897; AD 2004–25–09] 

RIN 2120–AA64 

Airworthiness Directives; Boeing 

Model 707 Airplanes and Model 720 

and 720B Series Airplanes

AGENCY: Federal Aviation 

Administration (FAA), DOT.

ACTION: Final rule.

SUMMARY: The FAA is adopting a new 

airworthiness directive (AD) for all 

Boeing Model 707 airplanes and Model 

720 and 720B series airplanes. This AD 

requires repetitive inspections of the left 

and right support ribs for the main 

landing gear (MLG) trunnion, related 

investigative/corrective actions if 

necessary, and other specified actions. 

This AD is prompted by reports of inservice cracking of the support ribs for 

the MLG trunnion. We are issuing this 

AD to detect and correct corrosion and 

cracking of the support ribs for the MLG 

trunnion, which could result in collapse 

of the MLG.

DATES: This AD becomes effective 

January 13, 2005. 

The incorporation by reference of a 

certain publication listed in the AD is 

approved by the Director of the Federal 

Register as of January 13, 2005.

ADDRESSES: For service information 

identified in this AD, contact Boeing 

Commercial Airplanes, P.O. 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 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: Candice 

Gerretsen, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, 

Seattle Aircraft Certification Office, 

1601 Lind Avenue, SW., Renton, 

Washington 98055–4056; telephone 

(425) 917–6428; fax (425) 917–6590. 

Plain language information: Marcia 

Walters, marcia.walters@faa.gov.

Examining the Docket 

The AD docket contains the proposed 

AD, comments, and any final 

disposition. 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.

SUPPLEMENTARY INFORMATION: The FAA 

proposed to amend 14 CFR part 39 with 

an AD for all Boeing Model 707 

airplanes and Model 720 and 720B 

series airplanes. That action, published 

in the Federal Register on October 4, 

2004 (69 FR 59151), proposed to require 

repetitive inspections of the left and 

right support ribs for the main landing 

gear (MLG) trunnion, related 

investigative/corrective actions if 

necessary, and other specified actions. 

Comments 

We provided the public the 

opportunity to participate in the 

development of this AD. We have 

considered the comment that was 

submitted on the proposed AD. The 

commenter, the manufacturer, supports 

the proposed AD. 

Conclusion 

We have carefully reviewed the 

available data, including the comment 

that has been submitted, and 

determined that air safety and the 

public interest require adopting the AD 

as proposed. 

Costs of Compliance 

There are about 227 airplanes of the 

affected design worldwide. The 

following table provides the estimated 

costs for U.S. operators to comply with 

this AD.

71348 Federal Register / Vol. 69, No. 236 / Thursday, December 9, 2004 / Rules and Regulations 

ESTIMATED COSTS

Action Work hours 

Average 

labor rate 

per hour 

Parts Cost per airplane 

Number of 

U.S.-

registered

airplanes 

Fleet cost 

Inspection, per inspection cycle.6 $65 None ........................... $390, per inspection 

cycle.

32 $12,480, per inspection cycle. 

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 AD. 

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 this AD: 

(1) Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866; 

(2) Is not a ‘‘significant rule’’ under 

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):

2004–25–09 Boeing: Amendment 39–13897. 

Docket No. FAA–2004–19228; 

Directorate Identifier 2004–NM–77–AD. 

Effective Date 

(a) This AD becomes effective January 13, 

2005. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to all Boeing Model 

707–100 long body, –200, –100B long body, 

and –100B short body series airplanes; and 

Model 707–300, –300B, –300C, and –400 

airplanes; and Model 720 and 720B series 

airplanes; certificated in any category. 

Unsafe Condition 

(d) This AD was prompted by reports of inservice cracking of the support ribs for the 

main landing gear (MLG) trunnion. We are 

issuing this AD to detect and correct 

corrosion and cracking of the support ribs for 

the MLG trunnion, which could result in 

collapse of the MLG. 

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. 

Service Bulletin References 

(f) The term ‘‘alert service bulletin,’’ as 

used in this AD, means the Accomplishment 

Instructions of Boeing 707 Alert Service 

Bulletin A3510, dated January 15, 2004. 

Repetitive Detailed Inspection and 

Corrective Action 

(g) Within 6 months after the effective date 

of this AD: Do a detailed inspection for 

corrosion and cracking of the left and right 

support ribs of the MLG trunnion. Do the 

inspection in accordance with all of the 

actions in Part I of the alert service bulletin. 

Repeat the inspection thereafter at intervals 

not to exceed 6 months. 

(h) If any corrosion or cracking is found 

during any inspection required by paragraph 

(g) of this AD: Before further flight, do all 

applicable related investigative and 

corrective actions, and the other specified 

actions, in accordance with the alert service 

bulletin; except, where the alert service 

bulletin specifies to contact Boeing, before 

further flight, repair in accordance with a 

method approved by the Manager, Seattle 

Aircraft Certification Office (ACO), FAA; or 

in accordance with 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 refer to this AD. 

Repetitive High Frequency Eddy Current 

(HFEC) Inspection and Corrective Action 

(i) Within 12 months after the effective 

date of this AD: Do a HFEC inspection for 

cracking of the left and right support ribs of 

the MLG trunnion. Do the inspection in 

accordance with all of the actions in Part II 

of the alert service bulletin. Repeat the 

inspection thereafter at intervals not to 

exceed 12 months. 

(j) If cracking is found during any 

inspection required by paragraph (i) of this 

AD: Before further flight, repair the cracked 

area in accordance with a method approved 

by the Manager, Seattle ACO; or in 

accordance with data meeting the type 

certification basis of the airplane 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. 

Alternative Methods of Compliance 

(AMOCs) 

(k)(1) The Manager, Seattle ACO, 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 

(l) You must use Boeing 707 Alert Service 

Bulletin A3510, dated January 15, 2004, to 

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