57884 Federal Register / Vol. 69, No. 187 / Tuesday, September 28, 2004 / Proposed Rules 

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2004–19175; Directorate 

Identifier 2003–NM–246–AD] 

RIN 2120–AA64 

Airworthiness Directives; Boeing 

Model 747–100B SUD, –200B, –300, 

–400, and –400D Series Airplanes

AGENCY: Federal Aviation 

Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: The FAA proposes to adopt a 

new airworthiness directive (AD) for 

certain Boeing Model 747–100B SUD, 

–200B, –300, –400, and –400D series 

airplanes. This proposed AD would 

require repetitive inspections for 

cracking in fuselage stringers 8L, 8R, 

10L, and 10R at body stations 460, 480, 

and 500 frame locations; and repair if 

necessary. This proposed AD is 

prompted by findings of cracking in 

fuselage stringers 8L, 8R, 10L, and 10R 

at body stations 460, 480, and 500 frame 

locations. We are proposing this AD to 

detect and correct fatigue cracking in 

certain fuselage stringers which, if left 

undetected, could result in fuselage skin 

cracking that reduces the structural 

integrity of the skin panel, and 

consequent rapid depressurization of 

the airplane.

DATES: We must receive comments on 

this proposed AD by November 12, 

2004.

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. 

• By 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. 

You can get the service information 

identified in this proposed AD from 

Boeing Commercial Airplanes, P.O. Box 

3707, Seattle, Washington 98124–2207. 

You may examine the AD docket, 

which contains the proposed AD, 

comments received, and any final 

disposition, on the Internet at http://

dms.dot.gov.

FOR FURTHER INFORMATION CONTACT: Nick 

Kusz, Aerospace Engineer, Airframe 

Branch, ANM–120S, FAA, Seattle 

Aircraft Certification Office, 1601 Lind 

Avenue, SW., Renton, Washington 

98055–4056; telephone (425) 917–6432; 

fax (425) 917–6590.

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–

2004–19175; Directorate Identifier 

2003–NM–246–AD’’ in the subject line 

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 

submitted 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 that 

website, 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 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 may 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 

We have received reports of cracking 

at fuselage stringers 8L, 8R, 10L, and 

10R at body station 460, 480, and 500 

frame locations. These stringers are 

above and below the upper deck 

windows. The cracking was found on 

certain Boeing Model 747–100B SUD, 

–200B, –300, –400, and –400D series 

airplanes having stretched upper decks. 

Investigation revealed that the cracking 

was caused by fatigue. The affected 

airplanes had between 29,873 and 

90,333 total flight hours and between 

9,691 and 25,513 total flight cycles. If 

the fatigue cracking at the specified 

locations is not detected and corrected, 

the cracking could grow to include the 

fuselage skin along the window belt of 

the upper deck. Such cracking of the 

fuselage skin could result in reduced 

structural integrity of the skin panel, 

and consequent rapid depressurization 

of the airplane. 

Relevant Service Information 

We have reviewed Boeing Alert 

Service Bulletin 747–53A2484, dated 

June 26, 2003. The service bulletin 

describes procedures for doing 

repetitive detailed visual inspections of 

fuselage stringers 8L, 8R, 10L, and 10R 

at body station 460, 480, and 500 frame 

locations and repairing areas with 

cracking. The repair procedures include 

installing new frame clips and new, 

additional stringer splices and doublers. 

For cracking that exceeds the specified 

limitations, the service bulletin specifies 

to install new sections of stringer in 

accordance with the 747 Structural 

Repair Manual along with incorporation 

of repair parts from the service bulletin. 

The service bulletin also describes an 

optional modification, which eliminates 

the need for the repetitive inspections. 

The optional modification includes 

procedures for installing new frame 

Federal Register / Vol. 69, No. 187 / Tuesday, September 28, 2004 / Proposed Rules 57885

clips and new doublers; and repairing, 

as applicable. Accomplishing the 

actions specified in the service bulletin 

is intended to 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 airplanes of this same 

type design. Therefore, we are 

proposing this AD, which would require 

repetitive inspections for fatigue 

cracking in fuselage stringers 8L, 8R, 

10L, and 10R at body station 460, 480, 

and 500 frame locations; and repair if 

necessary. The proposed AD also would 

provide an optional terminating action 

for the repetitive inspections. The 

proposed AD would require you to use 

the service information described 

previously to perform these actions, 

except as discussed under ‘‘Differences 

Between the Proposed AD and Service 

Information.’’

Differences Between the Proposed AD 

and Service Information 

The manufacturer reanalyzed the 

service problem and has advised the 

FAA that the reanalysis has resulted in 

threshold and repetitive inspection 

intervals different from the service 

bulletin. This resulted in simplified 

initial thresholds and an increased 

number of flight cycles between 

repetitive inspections. This difference 

has been coordinated with the 

manufacturer. 

Clarification of Inspection Terminology 

In this proposed AD, the ‘‘detailed 

visual inspection’’ specified in the 

Boeing service bulletin is referred to as 

a ‘‘detailed inspection.’’ We have 

included the definition for a ‘‘detailed 

inspection’’ in a note in this proposed 

AD. 

Costs of Compliance 

This proposed AD would affect about 

243 Boeing Model 747–100B SUD, 

–200B, –300, –400, and –400D series 

airplanes worldwide. 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

airplane 

Number

of U.S.-

registered

airplanes 

Fleet cost 

Inspection ................................................. 3 $65 None $195 69 $13,455 

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–2004–19175; 

Directorate Identifier 2003–NM–246–AD. 

Comments Due Date 

(a) The Federal Aviation Administration 

(FAA) must receive comments on this AD 

action by November 12, 2004. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to certain Boeing 

Model 747–100B SUD, –200B, –300, –400, 

and –400D series airplanes; certificated in 

any category; as listed in Boeing Alert 

Service Bulletin 747–53A2484, dated June 

26, 2003. 

Unsafe Condition 

(d) This AD was prompted by findings of 

cracking in fuselage stringers 8L, 8R, 10L, 

and 10R at body station 460, 480, and 500 

frame locations. We are proposing this AD to 

detect and correct fatigue cracking in the 

specified fuselage stringers which, if left 

undetected, could result in fuselage skin 

cracking that reduces the structural integrity 

of the skin panel, and consequent rapid 

depressurization 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. 

Inspection 

(f) Do a detailed inspection for cracking in 

fuselage stringers 8L, 8R, 10L, and 10R at 

body station 460, 480, and 500 frame 

locations, in accordance with Part 1 of the 

Accomplishment Instructions in Boeing Alert 

Service Bulletin 747–53A2484, dated June 

26, 2003. Do the inspections at the applicable 

time specified in paragraph (f)(1) or (f)(2) of 

this AD. Repeat the inspection thereafter at 

intervals not to exceed 3,000 flight cycles 

until the requirements of paragraph (h) of 

this AD are accomplished. 

(1) For airplanes with 19,000 total flight 

cycles or less as of the effective date of this 

AD: Prior to the accumulation of 8,000 total 

flight cycles or within 2,000 flight cycles 

after the effective date of this AD, whichever 

is later, not to exceed 20,000 total flight 

cycles. 

(2) For airplanes with more than 19,000 

total flight cycles as of the effective date of 

this AD: Within 1,000 flight cycles after the 

effective date of this AD.

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 mirror, magnifying 

lenses, etc., may be necessary. Surface 

cleaning and elaborate procedures may be 

required.’’

57886 Federal Register / Vol. 69, No. 187 / Tuesday, September 28, 2004 / Proposed Rules 

Repair 

(g) If any cracking is found during any 

inspection required by paragraph (f) of this 

AD: Before further flight, repair the affected 

stringer in accordance with Part 2 of the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 747–53A2484, dated June 

26, 2003. Repair terminates the repetitive 

inspections required by paragraph (f) of this 

AD for only the repaired stringer/frame 

location. 

Optional Terminating Action 

(h) Installing new frame clips and new 

doublers; and repairing as applicable; in 

accordance with Part 3 of the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 747–53A2484, dated June 

26, 2003, terminates the repetitive 

inspections required by this AD. 

Alternative Methods of Compliance 

(AMOCs) 

(i) 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.

Issued in Renton, Washington, on 

September 20, 2004. 

Kalene C. Yanamura, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service.

[FR Doc. 04–21648 Filed 9–27–04; 8:45 am] 

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2004–19177; Directorate 

Identifier 2002–NM–202–AD] 

RIN 2120–AA64 

Airworthiness Directives; Dassault 

Model Falcon 10 Series Airplanes

AGENCY: Federal Aviation 

Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: The FAA proposes to adopt a 

new airworthiness directive (AD) for all 

Dassault Model Falcon 10 series 

airplanes. This proposed AD would 

require a temporary change to the 

airplane flight manual to provide 

procedures to the flight crew for 

touchdown using the main landing gear 

to avoid a three-point landing. This 

proposed AD also would require 

repetitive inspections of the piston rod 

of the drag strut actuator of the nose 

landing gear (NLG) for cracks, which 

would terminate the AFM revision, and 

corrective actions if necessary. In 

addition, this proposed AD provides for 

a terminating modification, which 

would end the repetitive inspections. 

This proposed AD is prompted by 

reports of failure of the piston rod of the 

drag strut actuator of the NLG. The 

cause of such failure has been attributed 

to fatigue cracking caused by corrosion 

in the piston rod of the drag strut 

actuator. We are proposing this AD to 

prevent cracking and/or fracture of the 

piston rod of the drag strut actuator of 

the NLG, which could result in a gearup landing, structural damage, and 

possible injury to passengers and crew.

DATES: We must receive comments on 

this proposed AD by October 28, 2004.

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. 

• By 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 Dassault 

Falcon Jet, P.O. Box 2000, South 

Hackensack, New Jersey 07606. 

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: Tom 

Rodriguez, Aerospace Engineer, 

International Branch, ANM–116, FAA, 

Transport Airplane Directorate, 1601 

Lind Avenue, SW., Renton, Washington 

98055–4056; telephone (425) 227–1137; 

fax (425) 227–1149.

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–

2004–19177; Directorate Identifier 

2002–NM–202–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 submitted 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 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 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 

The Direction Ge ́ne ́rale de l’Aviation 

Civile (DGAC), which is the 

airworthiness authority for France,