Federal Register / Vol. 70, No. 217 / Thursday, November 10, 2005 / Proposed Rules 68381 

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–2005–22918; 

Directorate Identifier 2005–NM–172–AD. 

Comments Due Date 

(a) The FAA must receive comments on 

this AD action by December 12, 2005. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to Airbus Model A319–

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

–133, and Model A320–211, –212, –214, 

–231, –232, and –233 airplanes; certificated 

in any category; as identified in Airbus 

Service Bulletins A320–57–1117, dated July 

16, 2002, and A320–28–1102, Revision 01, 

dated February 11, 2005. 

Unsafe Condition 

(d) This AD results from several incidents 

of detached plastic identification labels 

found floating in the wing fuel tanks. We are 

issuing this AD to prevent plastic 

identification labels being ingested into the 

fuel pumps and consequently entering the 

engine fuel feed system, which could result 

in an engine shutdown. 

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/Corrective Actions of 

Four Wing-Tank Fuel Pumps and Canisters 

(f) Within 600 flight hours after the 

effective date of this AD: Perform a detailed 

inspection for detached identification labels 

in the four wing-tank fuel pumps and 

canisters, and do any applicable corrective 

actions, by doing all the actions in 

accordance with the Accomplishment 

Instructions of Airbus Service Bulletin A320–

28–1102, Revision 01, dated February 11, 

2005; except as provided by paragraph (j) of 

this AD. Do any applicable corrective action 

before further flight. Repeat the inspection 

thereafter at intervals not to exceed 600 flight 

hours. 

(g) For any wing-tank fuel pump failure 

that occurs after the effective date of this AD: 

Before further flight, perform a detailed 

inspection of the failed pump, the pump 

located in the same half wing, and the 

associated canister, in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A320–28–1102, Revision 01, 

dated February 11, 2005. Do any applicable 

corrective action, including replacing the 

failed pump, before further flight. 

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.’’

Inspections and Corrective Actions 

Accomplished According to Previous Issue 

of Service Bulletin 

(h) Inspections and corrective actions 

accomplished before the effective date of this 

AD according to Airbus Service Bulletin 

A320–28–1102, dated August 20, 2002; are 

considered acceptable for compliance with 

the corresponding actions specified in 

paragraph (f) of this AD. 

Repetitive Inspections/Corrective Actions of 

the Collector Cells, Wing Fuel Tank and 

Vent Box 

(i) Within 72 months after the effective 

date of this AD: Perform a detailed inspection 

for detached identification labels in the 

collector cells between ribs 1 and 2, the surge 

tank between ribs 22 and 26, and the wing 

fuel tank and vent box, and do any applicable 

corrective actions, by doing all the applicable 

actions in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A320–57–1117, dated July 

16, 2002. Do any applicable corrective action 

before further flight. Repeat the inspection 

thereafter at intervals not to exceed 72 

months. 

No Reporting Required 

(j) Although Airbus Service Bulletin A320–

28–1102, Revision 01, dated February 11, 

2005, specifies submitting an inspection 

report to the manufacturer, this AD does not 

include that requirement. 

Alternative Methods of Compliance 

(AMOCs) 

(k)(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 

(l) French airworthiness directive F–2005–

121, dated July 20, 2005, also addresses the 

subject of this AD. 

Issued in Renton, Washington, on October 

31, 2005. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 05–22444 Filed 11–9–05; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2005–22594; Directorate 

Identifier 2005–NE–28–AD] 

RIN 2120–AA64 

Airworthiness Directives; Rolls-Royce 

Corporation (formerly Allison Engine 

Company, Allison Gas Turbine 

Division, and Detroit Diesel Allison) 

250–B and 250–C Series Turboprop 

and Turboshaft Engines 

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 

Rolls-Royce Corporation 250–B and 

250–C series turboprop and turboshaft 

engines with certain part numbers 

(P/Ns) of gas producer rotor assembly tie 

bolts manufactured by EXTEX Ltd., 

Pacific Sky Supply Inc., Rolls-Royce 

Corporation (RRC), and Superior Air 

Parts Inc. This proposed AD would 

require operators to remove from service 

affected gas producer rotor assembly tie 

bolts. This proposed AD results from 

eleven reports of RRC tie bolt failure 

due to high cycle fatigue. We are 

proposing this AD to prevent tie bolt 

failure that could cause loss of engine 

power, resulting in a first stage turbine 

wheel overspeed and an uncontained 

engine failure. 

DATES: We must receive any comments 

on this proposed AD by January 9, 2006. 

ADDRESSES: Use one of the following 

addresses to comment on this proposed 

AD. 

68382 Federal Register / Vol. 70, No. 217 / Thursday, November 10, 2005 / Proposed Rules 

• 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–

0001. 

• 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 may examine the comments on 

this proposed AD in the AD docket on 

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

FOR FURTHER INFORMATION CONTACT: 

• Robert Baitoo, Aerospace Engineer, 

Los Angeles Aircraft Certification 

Office, FAA, Transport Airplane 

Directorate, 3960 Paramount Blvd., 

Lakewood, CA 90712–4137; telephone: 

(562) 627–5245, fax: (562) 627–5210, for 

questions about, EXTEX Ltd., or Pacific 

Sky Supply Inc. gas producer rotor 

assembly tie bolts. 

• John Tallarovic, Aerospace 

Engineer, Chicago Aircraft Certification 

Office, FAA, 2300 East Devon Avenue, 

Des Plaines, IL 60018–4696; telephone 

(847) 294–8180; fax (847) 294–7834, for 

questions about RRC gas producer rotor 

assembly tie bolts. 

• Jurgen Priester, Aerospace Engineer, 

Rotorcraft Directorate, FAA, 2601 

Meacham Blvd., Fort Worth, Texas, 

76137–4298, telephone (817) 222–5159, 

fax (817) 222–5785, for questions about 

Superior Air Part Inc. gas producer rotor 

assembly tie bolts. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to send us any written 

relevant data, views, or arguments 

regarding this proposal. Send your 

comments to an address listed under 

ADDRESSES. Include ‘‘Docket No. FAA–

2005–22594; Directorate Identifier 

2005–NE–28–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 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 the DOT 

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 AD Docket 

You may examine the docket that 

contains the proposal, any comments 

received and, any final disposition in 

person at the DOT Docket Offices 

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

through Friday, except Federal holidays. 

The Docket Office (telephone (800) 647–

5227) is located on the plaza level of the 

Department of Transportation Nassif 

Building at the street address stated in 

ADDRESSES. Comments will be available 

in the AD docket shortly after the 

Docket Management Facility receives 

them. 

Discussion 

The FAA has received eleven reports 

of failures of RRC manufactured tie bolts 

due to high cycle fatigue. The FAA 

believes that all of these failures are due 

to the inherent design of the part, which 

is also common to all of the PMA parts. 

Therefore, this AD requires removal of 

all RR and PMA tie-bolts. RRC has 

redesigned the tie bolt to minimize the 

risk of failure by high cycle fatigue. RRC 

manufactured these tie bolts under type 

and production certificate authority. 

EXTEX Ltd., Pacific Sky Supply Inc., 

and Superior Air Parts Inc. each 

independently manufactured 

replacement gas producer rotor 

assembly tie bolts under Parts 

Manufacturer Approval (PMA) 

authority. There have been no reported 

failures of PMA parts. The engines are 

installed in single-engine helicopters, 

along with several turboprop airplanes. 

This condition, if not corrected, could 

cause loss of engine power, resulting in 

a first stage turbine wheel overspeed 

and an uncontained engine failure. 

FAA’s Determination and Requirements 

of the Proposed AD 

We have evaluated all pertinent 

information from the four 

manufacturers’ safety assessments and 

have identified an unsafe condition that 

is likely to exist or develop in other RRC 

250–B17, –B17B, –B17C, –B17D, –B17E, 

–B17F, –B17F/1, –B17F/2, 250–C18, 

–C20, –C20B, –C20F, –C20J, –C20R, 

–C20R/1, –C20R/2, –C20R/4, –C20S, 

and –C20W series turboprop and 

turboshaft engines that have any of the 

following gas producer rotor assembly 

tie bolts installed: 

• EXTEX Ltd.: P/N A23008020, and 

E23008020 

• Pacific Sky Supply Inc.: P/N 

23008020P 

• Rolls-Royce Corporation: P/Ns 

23008020, 6843388 and 6876991 

• Superior Air Parts Inc.: P/N 

A23008020 

We are proposing this AD, which 

would remove these P/N gas producer 

rotor assembly tie bolts as specified in 

the compliance section of this proposed 

AD. 

Costs of Compliance 

About 4,000 RRC 250–B and 250–C 

Series turboprop and turboshaft engines 

with affected P/Ns of gas producer rotor 

assembly tie bolts manufactured by 

EXTEX Ltd., Pacific Sky Supply Inc., 

Rolls-Royce Corporation (RRC), and 

Superior Air Parts Inc. are in the 

worldwide fleet. We estimate that 700 

engines installed on aircraft of U.S. 

registry would be affected by this 

proposed AD. We also estimate that it 

would take about 20 work hours per 

engine to perform the proposed actions, 

and that the average labor rate is $65 per 

work hour. Required parts would cost 

about $421 per engine. Based on these 

figures, we estimate the total cost of the 

proposed AD to U.S. operators to be 

$1,204,700. 

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 

Federal Register / Vol. 70, No. 217 / Thursday, November 10, 2005 / Proposed Rules 68383 

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. Would 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 

Under the authority delegated to me 

by the Administrator, the Federal 

Aviation Administration 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: 

Rolls-Royce Corporation (formerly Allison 

Engine Company, Allison Gas Turbine 

Division, and Detroit Diesel Allison): 

Docket No. FAA–2005–22594; 

Directorate Identifier 2005–NE–28–AD. 

Comments Due Date 

(a) The Federal Aviation Administration 

(FAA) must receive comments on this 

airworthiness directive (AD) action by 

January 9, 2006. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to Rolls-Royce 

Corporation (formerly Allison Engine 

Company, Allison Gas Turbine Division, and 

Detroit Diesel Allison) 250–B17, –B17B, 

–B17C, –B17D, –B17E, –B17F, –B17F/1, 

–B17F/2, 250–C18, –C20, –C20B, –C20F, 

–C20J, –C20R, –C20R/1, –C20R/2, –C20R/4, 

–C20S, and –C20W series turboprop and 

turboshaft engines with the gas producer 

rotor assembly tie bolt part numbers (P/Ns) 

listed in the following Table 1, installed: 

TABLE 1.—AFFECTED GAS PRODUCER ROTOR ASSEMBLY TIE BOLTS

Manufacturer Affected part Nos. 

EXTEX Ltd. (EXTEX) ............................................................................... A23008020 and E23008020. 

Rolls-Royce Corporation (RRC) ............................................................... 23008020, 6843388 and 6876991. 

Superior Air Parts Inc. (SAP) ................................................................... A23008020. 

Pacific Sky Supply Inc .............................................................................. 23008020P. 

These engines are installed on, but not 

limited to, aircraft in the following Table 2: 

TABLE 2.—APPLICABLE AIRCRAFT

Helicopter Models 

Agusta ....................................................................................................... A109, A109A, A109A II, A109C. 

Arrow Falcon Exporters ............................................................................ OH–58A+ and OH–58C. 

Bell Textron .............................................................................................. 206A, 206B, 206L. 

Enstrom .................................................................................................... TH–28, 480, 480B. 

Eurocopter France .................................................................................... AS355E, AS355F, AS355F1, AS355F2. 

Eurocopter Deutschland ........................................................................... BO–105A, BO–105C, BO–105S. 

FH–1100 Manufacturing Corp .................................................................. FH–1100. 

Garlick ....................................................................................................... OH–58A+ and OH–58C. 

McDonnell Douglas Company .................................................................. 369D, 369E, 369F, 369H, 369HM, 369HS, 369HE, 500N. 

San Joaquin .............................................................................................. OH–58A+ and OH–58C. 

Schweizer ................................................................................................. 269D. 

Aircraft Models 

B–N Group Ltd ......................................................................................... BN–2T and BN–2T–4R. 

SIAI Marchetti s.r.l .................................................................................... SF600, SF600A. 

Unsafe Condition 

(d) This AD results from eleven reports of 

RRC tie bolt failure due to high cycle fatigue. 

We are issuing this AD to prevent tie bolt 

failure that could cause loss of engine power, 

resulting in a first stage turbine wheel 

overspeed and an uncontained engine failure. 

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. 

Remove Gas Producer Rotor Assembly Tie 

Bolts 

(f) Remove the P/N gas producer rotor 

assembly tie bolts listed in Table 1 of this AD 

from service the next time they are 

disassembled for any reason, or by October 

31, 2011, whichever occurs first. 

(g) After the effective date of this AD, do 

not install any gas producer rotor assembly 

tie bolt P/Ns listed in Table 1 of this AD in 

any RRC 250–B and 250–C Series turboprop 

and turboshaft engines. 

Alternative Methods of Compliance 

(h) The Manager, Los Angeles Aircraft 

Certification Office, has the authority to 

approve alternative methods of compliance 

for EXTEX, and Pacific Sky Supply Inc. gas 

producer rotor assembly tie bolts addressed 

in this AD, if requested, using the procedures 

found in 14 CFR 39.19. The Manager, 

68384 Federal Register / Vol. 70, No. 217 / Thursday, November 10, 2005 / Proposed Rules 

Chicago Aircraft Certification Office, has the 

authority to approve alternative methods of 

compliance for RRC gas producer rotor 

assembly tie bolts addressed in this AD, if 

requested, using the procedures found in 14 

CFR 39.19. The Manager, Southwest Special 

Certification Office, has the authority to 

approve alternative methods of compliance 

for SAP gas producer rotor assembly tie bolts 

addressed in this AD, if requested, using the 

procedures found in 14 CFR 39.19. 

Material Incorporated by Reference 

(i) None. 

Related Information 

(j) RRC Commercial Engine Bulletin (CEB) 

CEB A–304, CEB A–1371, CEB A–72–4076, 

TP CEB A–176, TP CEB A–1319, TP CEB A–

72–2027, Revision N/C dated May 23, 2005, 

and EXTEX Service Bulletin T–090, Revision 

N/C, dated May 23, 2005, pertain to the 

subject of this AD. 

Issued in Burlington, Massachusetts, on 

November 4, 2005. 

Peter A. White, 

Acting Manager, Engine and Propeller 

Directorate, Aircraft Certification Service. 

[FR Doc. 05–22437 Filed 11–9–05; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2005–22919; Directorate 

Identifier 2005–NM–087–AD] 

RIN 2120–AA64 

Airworthiness Directives; Airbus Model 

A319–100, A320–200, A321–100, and 

A321–200 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 A319–100, A320–

200, A321–100, and A321–200 series 

airplanes. This proposed AD would 

require repetitive inspections for 

corrosion in the inside and outside 

lower walls of each type A, D, E, and F 

lavatory wall that has at least one wallmounted cabin attendant seat, and 

related investigative and corrective 

actions if necessary. The repetitive 

inspections may be terminated by 

repairing the wall with composite 

material, or replacing the entire wall 

with a new wall made of composite 

material. This proposed AD results from 

reports of corrosion in the lower part of 

the lavatory walls due to water ingress. 

We are proposing this AD to detect and 

correct corrosion and damage on the 

lower part of the lavatory walls, which 

could compromise the structural 

integrity of the cabin attendant seat 

attachments, and cause injury to the 

cabin attendants during a crash landing. 

DATES: We must receive comments on 

this proposed AD by December 12, 

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. 

• 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 Airbus, 1 

Rond Point Maurice Bellonte, 31707 

Blagnac Cedex, France. 

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–2005–

22919; the directorate identifier for this 

docket is 2005–NM–087–AD. 

FOR FURTHER INFORMATION CONTACT: Tim 

Dulin, Aerospace Engineer, 

International Branch, ANM–116, FAA, 

Transport Airplane Directorate, 1601 

Lind Avenue, SW., Renton, Washington 

98055–4056; telephone (425) 227–2141; 

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 under 

ADDRESSES. Include ‘‘Docket No. FAA–

2005–22919; Directorate Identifier 

2005–NM–087–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. 

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 Docket 

Management System (DMS) 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 A319–

100, A320–200, A321–100, and A321–

200 series airplanes. The DGAC advises 

that an operator reported cracks in the 

lavatory floor pans of the affected 

airplanes in its fleet. Further 

investigation showed that the cracks 

resulted from corrosion in the lower 

part of the lavatory wall, possibly 

caused by liquid that entered during 

cleaning and operation, and by rain 

entering through the main entry door. 

Extensive corrosion of the lower part of 

the lavatory wall could compromise the 

structural integrity of the cabin 

attendant seat (CAS) attachments. This 

condition, if not corrected, could result 

in injury to the cabin attendants during 

a crash landing. 

Relevant Service Information 

Airbus has issued Service Bulletin 

A320–25–1365, dated February 18, 

2005. The service bulletin describes 

procedures for doing a repetitive 

detailed visual inspection for corrosion