61924 Federal Register / Vol. 70, No. 207 / Thursday, October 27, 2005 / Proposed Rules 

We are issuing this rulemaking under 

the authority described in Subtitle VII, 

Part A, Subpart III, Section 44701, 

‘‘General requirements.’’ Under that 

section, Congress charges the FAA with 

promoting safe flight of civil aircraft in 

air commerce by prescribing regulations 

for practices, methods, and procedures 

the Administrator finds necessary for 

safety in air commerce. This regulation 

is within the scope of that authority 

because it addresses an unsafe condition 

that is likely to exist or develop on 

products identified in this rulemaking 

action. 

Regulatory 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 and placed it in the 

AD docket. 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 Federal Aviation 

Administration (FAA) amends § 39.13 

by adding the following new 

airworthiness directive (AD): 

Airbus: Docket No. FAA–2005–22794; 

Directorate Identifier 2005–NM–097–AD. 

Comments Due Date 

(a) The FAA must receive comments on 

this AD action by November 28, 2005. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to all Airbus Model 

A318–111 and –112 airplanes, Model A319–

111, –112, –113, –114, –115, –131, –132, and 

–133 airplanes, Model A320–111 airplanes, 

Model A320–211, –212, –214, –231, –232, 

and –233 airplanes, Model A321–111, –112, 

and –131 airplanes, and Model A321–211 

and –231 airplanes, certificated in any 

category. 

Unsafe Condition 

(d) This AD results from a report that 

during lab testing to verify the performance 

of the trimmable horizontal stabilizer 

actuator’s (THSA’s) secondary load path with 

a simulated failure of the THSA’s primary 

load path, the secondary load path’s nut did 

not jam (as it was supposed to do.) We are 

issuing this AD to ensure the integrity of the 

THSA’s primary load path, which if failed, 

could result in latent (undetected) loading 

and eventual failure of the THSA’s secondary 

load path and consequent uncontrolled 

movement of the horizontal stabilizer and 

loss of control 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. 

Repetitive Inspections and Corrective Action 

(f) Within 20 months since first flight, or 

within 600 flight hours after the effective 

date of this AD, whichever occurs later, do 

detailed inspections of the THSA 

attachments for proper clearances and any 

crack, damage, or metallic particles, and do 

related corrective actions as applicable, in 

accordance with the Accomplishment 

Instructions of Airbus Service Bulletin A320–

27–1164, Revision 02, dated March 30, 2005, 

except as described in paragraph (g) of this 

AD. Do corrective actions before further 

flight. Thereafter, repeat the inspections at 

intervals not to exceed 20 months. 

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.’’

(g) If any metallic particles are detected 

during the inspection required by paragraph 

(f) of this AD: Before further flight, repair the 

damage according to a method approved by 

either the Manager, International Branch, 

ANM–116, FAA, Transport Airplane 

Directorate; or the Direction Ge ́ne ́rale de 

l’Aviation Civile (DGAC) (or its delegated 

agent). 

Inspection Reports 

(h) Submit a report of the findings (both 

positive and negative) of the inspection 

required by paragraph (f) of this AD to 

Airbus, 1 Rond Point Maurice Bellonte, 

31707 Blagnac Cedex, France, at the 

applicable time specified in paragraph (h)(1) 

or (h)(2) of this AD. The report must include 

the inspection results, a description of any 

discrepancies found, the airplane serial 

number, and the number of landings and 

flight hours on the airplane. Under the 

provisions of the Paperwork Reduction Act of 

1980 (44 U.S.C. 3501 et seq.), the Office of 

Management and Budget (OMB) has 

approved the information collection 

requirements contained in this AD and has 

assigned OMB Control Number 2120–0056. 

(1) If the inspection was done after the 

effective date of this AD: Submit the report 

within 30 days after the inspection. 

(2) If any inspection was accomplished 

prior to the effective date of this AD: Submit 

the report within 30 days after the effective 

date of this AD. 

Alternative Methods of Compliance 

(AMOCs) 

(i)(1) The Manager, International Branch, 

ANM–116, Transport Airplane Directorate, 

FAA, has the authority to approve AMOCs 

for this AD, if requested in accordance with 

the procedures found in 14 CFR 39.19. 

(2) Before using any AMOC approved in 

accordance with § 39.19 on any airplane to 

which the AMOC applies, notify the 

appropriate principal inspector in the FAA 

Flight Standards Certificate Holding District 

Office. 

Related Information 

(j) French airworthiness directive F–2005–

051, dated March 30, 2005, also addresses the 

subject of this AD. 

Issued in Renton, Washington, on October 

18, 2005. 

Kevin M. Mullin, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 05–21434 Filed 10–26–05; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2005–22810; Directorate 

Identifier 2005–NM–143–AD] 

RIN 2120–AA64 

Airworthiness Directives; Airbus Model 

A310–203, –204, and –222 Airplanes, 

and Model A310–300 Series Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Notice of proposed rulemaking 

(NPRM). 

Federal Register / Vol. 70, No. 207 / Thursday, October 27, 2005 / Proposed Rules 61925 

SUMMARY: The FAA proposes to adopt a 

new airworthiness directive (AD) for 

certain Airbus Model A310–203, –204, 

and –222 airplanes, and Model A310–

300 series airplanes. This proposed AD 

would require a one-time rototest 

inspection for cracking of the frame foot 

and adjacent frames and skin in the area 

surrounding the frame foot run-outs 

from fuselage frames (FR) 43 through FR 

46, and repair if necessary. The 

proposed AD also requires modification 

of certain fastener holes. This proposed 

AD results from a structural evaluation 

of Model A310 airplanes for widespread 

fatigue damage of the frame foot runouts from FR 43 through FR 46. The 

evaluation revealed that, on in-service 

airplanes, undetected cracking in this 

area can lead to the rupture of the frame 

foot and subsequent cracking of the 

adjacent frames and fuselage skin. We 

are proposing this AD to prevent fatigue 

cracking of the frame foot run-outs, 

which could lead to rupture of the frame 

foot and cracking in adjacent frames and 

skin, and result in reduced structural 

integrity of the fuselage. 

DATES: We must receive comments on 

this proposed AD by November 28, 

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. 

Contact Airbus, 1 Rond Point Maurice 

Bellonte, 31707 Blagnac Cedex, France, 

for service information identified in this 

proposed AD. 

FOR FURTHER INFORMATION CONTACT: Dan 

Rodina, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue, SW., Renton, 

Washington 98055–4056; telephone 

(425) 227–2125; fax (425) 227–1149. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to submit any relevant 

written data, views, or arguments 

regarding this proposed AD. Send your 

comments to an address listed in the 

ADDRESSES section. Include the docket 

number ‘‘FAA–2005–22810; Directorate 

Identifier 2005–NM–143–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 that 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. 

Examining the Docket 

You may 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 Docket 

Management System receives them. 

Discussion 

The Direction Ge ́ne ́rale de l’Aviation 

Civile (DGAC), which is the 

airworthiness authority for France, 

notified us that an unsafe condition may 

exist on certain Airbus Model A310–

203, –204, and –222 airplanes, and 

Model A310–300 series airplanes. The 

DGAC advises that a structural 

evaluation for widespread fatigue 

damage of the frame foot run-outs from 

fuselage frame (FR) 43 through FR 46 

was done on the subject airplanes. The 

evaluation revealed that, on in-service 

airplanes, undetected cracking in this 

area can lead to the rupture of the frame 

foot and subsequent cracking of the 

adjacent frames and fuselage skin. Such 

cracking would require an extensive 

repair and could have an impact on 

pressure loading strength capacity of the 

structure. These conditions, if not 

corrected, could result in reduced 

structural integrity of the fuselage. 

Relevant Service Information 

Airbus has issued Service Bulletin 

A310–53–2124, dated April 4, 2005. The 

service bulletin describes procedures for 

performing a one-time rototest 

inspection to find cracking of the frame 

foot and adjacent frames and skin in the 

area surrounding the frame foot run-outs 

from FR 43 through FR 46, and repair 

of cracking within certain limits. If the 

cracking is outside the limits specified 

in the service bulletin, the service 

bulletin procedures recommend 

contacting the manufacturer for repair 

instructions. The service bulletin also 

describes procedures for modification of 

certain fastener holes. The modification 

includes cold expanding the fastener 

holes most susceptible to fatigue, which 

are located between FR 43 and FR 46 on 

the center box and on the upper fuselage 

bent sections, and installing new 

fasteners. Accomplishing the actions 

specified in the service information is 

intended to adequately address the 

unsafe condition. The DGAC mandated 

the service information and issued 

French airworthiness directive F–2005–

078, dated May 11, 2005, to ensure the 

continued airworthiness of these 

airplanes in France. 

Section 1.E., Compliance, of the 

service bulletin specifies compliance 

times for the actions in the service 

bulletin. The thresholds for the one-time 

inspection and modification range from 

between 22,200 flight cycles or 51,700 

flight hours, whichever is first, to 26,800 

flight cycles or 77,700 flight hours, 

whichever is first, depending on the 

configuration of the airplane. The 

service bulletin also includes a grace 

period of 3,000 flight cycles for 

airplanes that have exceeded certain 

flight-hour or flight-cycle thresholds, 

depending on the configuration of the 

airplane. 

FAA’s Determination and Requirements 

of the Proposed AD 

These airplane models are 

manufactured in France and are type 

certificated for operation in the United 

States under the provisions of section 

21.29 of the Federal Aviation 

Regulations (14 CFR 21.29) and the 

applicable bilateral airworthiness 

agreement. Pursuant to this bilateral 

airworthiness agreement, the DGAC has 

kept the FAA informed of the situation 

described above. We have examined the 

DGAC’s findings, evaluated all pertinent 

information, and determined that we 

need to issue an AD for airplanes of this 

61926 Federal Register / Vol. 70, No. 207 / Thursday, October 27, 2005 / Proposed Rules 

type design that are certificated for 

operation in the United States. 

Therefore, we are proposing this AD, 

which would require accomplishing the 

actions specified in the service 

information described previously, 

except as discussed under ‘‘Differences 

Among Proposed AD, French 

Airworthiness Directive, and Service 

Bulletin.’’

Differences Among Proposed AD, 

French Airworthiness Directive, and 

Service Bulletin 

The applicability of the French 

Airworthiness Directive excludes 

airplanes on which Airbus Service 

Bulletin A310–53–2124 has been 

accomplished in service. However, we 

have not excluded those airplanes in the 

applicability of this proposed AD; 

rather, this proposed AD would include 

a requirement to accomplish the actions 

specified in that service bulletin. This 

proposed AD would ensure that the 

actions specified in the service bulletin 

and required by this proposed AD are 

accomplished on all affected airplanes. 

Operators must continue to operate the 

airplane in the configuration required 

by this proposed AD unless an 

alternative method of compliance is 

approved. 

The service bulletin specifies to 

contact the manufacturer for 

instructions on how to repair certain 

conditions, but this proposed AD would 

require repairing those conditions using 

a method that we or the DGAC (or its 

delegated agent) approve. In light of the 

type of repair that would be required to 

address the unsafe condition, and 

consistent with existing bilateral 

airworthiness agreements, we have 

determined that, for this proposed AD, 

a repair we or the DGAC approve would 

be acceptable for compliance with this 

proposed AD. 

Costs of Compliance 

This proposed AD would affect about 

59 airplanes of U.S. registry. The 

proposed actions would take about 31 

work hours per airplane, at an average 

labor rate of $65 per work hour. 

Required parts would cost about $1,730 

per kit (two kits per airplane). Based on 

these figures, the estimated cost of the 

proposed AD for U.S. operators is 

$323,025, or $5,475 per airplane. 

Authority for This Rulemaking 

Title 49 of the United States Code 

specifies the FAA’s authority to issue 

rules on aviation safety. Subtitle I, 

Section 106, describes the authority of 

the FAA Administrator. Subtitle VII, 

Aviation Programs, describes in more 

detail the scope of the Agency’s 

authority. 

We are issuing this rulemaking under 

the authority described in Subtitle VII, 

Part A, Subpart III, Section 44701, 

‘‘General requirements.’’ Under that 

section, Congress charges the FAA with 

promoting safe flight of civil aircraft in 

air commerce by prescribing regulations 

for practices, methods, and procedures 

the Administrator finds necessary for 

safety in air commerce. This regulation 

is within the scope of that authority 

because it addresses an unsafe condition 

that is likely to exist or develop on 

products identified in this rulemaking 

action. 

Regulatory 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 and placed it in the 

AD docket. 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 Federal Aviation 

Administration (FAA) amends § 39.13 

by adding the following new 

airworthiness directive (AD): 

Airbus: Docket No. FAA–2005–22810; 

Directorate Identifier 2005–NM–143–AD. 

Comments Due Date 

(a) The FAA must receive comments on 

this AD action by November 28, 2005. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to Airbus Model A310–

203, –204, and –222 airplanes, and Model 

A310–304, –322, –324, and –325 airplanes; 

certificated in any category; except those 

airplanes on which Airbus Modification 

13023 has been accomplished in production. 

Unsafe Condition 

(d) This AD results from a structural 

evaluation of Model A310 airplanes for 

widespread fatigue damage of the frame foot 

run-outs from frame (FR) 43 through FR 46. 

We are issuing this AD to prevent fatigue 

cracking of the frame foot run-outs, which 

could lead to rupture of the frame foot and 

cracking in adjacent frames and skin, and 

result in reduced structural integrity of the 

fuselage. 

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/Repair/Modification 

(f) At the later of the times specified in 

paragraphs (f)(1) and (f)(2) of this AD, 

perform a one-time rototest inspection for 

cracking of the frame foot and adjacent 

frames and skin in the area surrounding the 

frame foot run-outs from fuselage frame FR 

43 through FR46 by doing all the applicable 

actions specified in the Accomplishment 

Instructions of the service bulletin. Except as 

required by paragraph (g) of this AD, repair 

any cracking before further flight in 

accordance with the Accomplishment 

Instructions of the service bulletin. Before 

further flight after performing the inspection, 

modify the fastener holes located between FR 

43 and FR 46 on the center box and on the 

upper fuselage bent sections in accordance 

with the Accomplishment Instructions of the 

service bulletin. 

(1) Before the accumulation of the total 

flight-cycle or flight-hour threshold, 

whichever is first, specified in the 

Accomplishment Timescale table in 

paragraph 1.E.(2), ‘‘Compliance’’ of the 

service bulletin. 

(2) At the earlier of the times specified in 

paragraphs (f)(2)(i) and (f)(2)(ii) of this AD. 

(i) Before the accumulation of the total 

flight-cycle or flight-hour threshold, 

whichever is first, specified in Notes 01, 02, 

and 03 in paragraph 1.E.(2), ‘‘Compliance’’ of 

the service bulletin, after the effective date of 

this AD. 

(ii) Within 3,000 flight cycles after the 

effective date of this AD. 

Repair Per FAA or Direction Ge ́ne ́rale de 

l’Aviation Civile (DGAC) 

(g) For any cracking found during any 

inspection required by this AD for which the 

Federal Register / Vol. 70, No. 207 / Thursday, October 27, 2005 / Proposed Rules 61927 

service bulletin specifies to contact the 

manufacturer for an appropriate repair: 

Before further flight, repair in accordance 

with a method approved by the Manager, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA; or the DGAC (or 

its delegated agent). 

Alternative Methods of Compliance 

(AMOCs) 

(h)(1) The Manager, International Branch, 

ANM–116, has the authority to approve 

AMOCs for this AD, if requested in 

accordance with the procedures found in 14 

CFR 39.19. 

(2) Before using any AMOC approved in 

accordance with 14 CFR 39.19 on any 

airplane to which the AMOC applies, notify 

the appropriate principal inspector in the 

FAA Flight Standards Certificate Holding 

District Office. 

Related Information 

(i) French airworthiness directive F–2005–

078, dated May 11, 2005, also addresses the 

subject of this AD. 

Issued in Renton, Washington, on October 

20, 2005. 

Kalene C. Yanamura, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 05–21428 Filed 10–26–05; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2005–22812; Directorate 

Identifier 2005–NM–134–AD] 

RIN 2120–AA64 

Airworthiness Directives; Airbus Model 

A330–200, A330–300, A340–200, and 

A340–300 Series Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: The FAA proposes to adopt a 

new airworthiness directive (AD) for 

certain Airbus Model A330–200, A330–

300, A340–200, and A340–300 series 

airplanes. This proposed AD would 

require repetitive detailed inspections 

for cracking in the aft web of support rib 

6 between certain bottom skin stringers 

on both wings; high frequency eddy 

current inspections for cracking of the 

attachment holes of the fuel pipes, and 

repair if necessary. This proposed AD 

would also provide for an optional 

modification, which would extend a 

certain inspection threshold. This 

proposed AD results from a report of 

significant cracking found in the aft web 

of support rib 6 on both wings. We are 

proposing this AD to prevent cracking 

in the aft web of support rib 6, which 

could result in overloading of adjacent 

ribs and the surrounding wing structure 

and consequent reduced structural 

integrity of the wing. 

DATES: We must receive comments on 

this proposed AD by November 28, 

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. 

Contact Airbus, 1 Rond Point Maurice 

Bellonte, 31707 Blagnac Cedex, France, 

for the service information identified in 

this proposed AD. 

FOR FURTHER INFORMATION CONTACT: 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. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to submit any relevant 

written data, views, or arguments 

regarding this proposed AD. Include the 

docket number ‘‘FAA–2005–22812; 

Directorate Identifier 2005–NM–134–

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 that 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 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. 

Examining the Docket 

You may 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 Docket 

Management System receives them. 

Discussion 

The Direction Ge ́ne ́rale de l’Aviation 

Civile (DGAC), which is the 

airworthiness authority for France, 

notified us that an unsafe condition may 

exist on certain Airbus Model A330–

200, A330–300, A340–200, and A340–

300 series airplanes. The DGAC advises 

that a report was received indicating 

significant cracking in the aft web of 

support rib 6 on the left and right wings 

on a Model A330 series airplane. When 

the cracking was found, during an 8Ccheck, the airplane had accumulated 

10,441 total flight cycles and 40,153 

total flight hours. The cracking was 

located in the lower part of the rib 6 aft 

hole between bottom skin stringers 18 

and 20. The cracking extended from the 

fuel pipe fastener holes to the lower 

edge of the rib 6 hole and into the refuel 

pipe hole where the cracking had gone 

through the full thickness of the rib. 

Subsequent inspections on several 

Model A330 and A340 series airplanes 

revealed similar cracking in the same 

area. These conditions, if not corrected, 

could result in overloading of adjacent 

ribs and the surrounding wing structure 

and consequent reduced structural 

integrity of the wing. 

Relevant Service Information 

Airbus has issued Service Bulletins 

A330–57–3085 (for Model A330 series 

airplanes) and A340–57–4093 (for 

Model A340 series airplanes), both 

Revision 01, both dated March 25, 2005. 

The service bulletins describe 

procedures for detailed inspections for 

cracking in the aft web of support rib 6 

between bottom skin stringers 18 and 20 

on both wings, and high frequency eddy 

current (HFEC) inspections for cracking