Federal Register / Vol. 70, No. 217 / Thursday, November 10, 2005 / Proposed Rules 68379 

Unsafe Condition 

(d) This AD results from production 

inspections that showed that the spring 

assembly that controls rudder balance may 

not have the correct pre-load on some 

airplanes. We are issuing this AD to prevent 

uncommanded yaw movements and 

consequent reduced controllability 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. 

Service Bulletin Reference 

(f) The term ‘‘service bulletin,’’ as used in 

this AD, means the Accomplishment 

Instructions of the applicable service bulletin 

in Table 2 of this AD. 

TABLE 2.—SERVICE BULLETINS

Bombardier airplane model Bombardier service bulletin 

CL–600–1A11 (CL–600) ........................................................................... 600–0714, including Appendix 1 and excluding Appendix 2, dated April 

4, 2003. 

CL–600–2A12 (CL–601), and CL–600–2B16 (CL–601–3A and CL–

601–3R).

601–0549, including Appendix 1 and excluding Appendix 2, dated April 

4, 2003. 

CL–600–2B16 (CL–604) ........................................................................... 604–27–013, including Appendix 1 and excluding Appendix 2, dated 

April 4, 2003. 

Modification and Rigging 

(g) Within 12 months after the effective 

date of this AD: Modify and rig the adjustable 

rudder balance spring assembly for the 

rudder control surface, in accordance with 

the Accomplishment Instructions of the 

applicable service bulletin in Table 2 of this 

AD. Where the service bulletin specifies 

contacting Bombardier for instructions on 

making certain adjustments: Before further 

flight, adjust according to a method approved 

by the Manager, New York Aircraft 

Certification Office (ACO), FAA; or Transport 

Canada Civil Aviation (TCCA) (or its 

delegated agent). 

No Reporting Required 

(h) Although the service bulletins 

referenced in this AD specify to submit 

certain information to the manufacturer, this 

AD does not include that requirement. 

Parts Installation 

(i) After the effective date of this AD, no 

person may install on any airplane a rudder 

balance spring assembly unless it has been 

modified and rigged in accordance with 

paragraph (g) of this AD. 

Alternative Methods of Compliance 

(AMOCs) 

(j)(1) The Manager, New York ACO, 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 

(k) Canadian airworthiness directive CF–

2005–21, dated June 23, 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. 05–22445 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–2005–22918; Directorate 

Identifier 2005–NM–172–AD] 

RIN 2120–AA64 

Airworthiness Directives; Airbus Model 

A319–100 and A320–200 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 and 

A320–200 series airplanes. This 

proposed AD would require repetitive 

inspections of the wing-tank fuel 

pumps, canisters, and wing fuel tanks 

for detached identification labels, and 

corrective action if necessary. This 

proposed AD results from several 

incidents of detached plastic 

identification labels found floating in 

the wing fuel tanks. We are proposing 

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. 

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. 

• 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: 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 in the 

ADDRESSES section. Include the docket 

number ‘‘FAA–2005–22918; Directorate 

Identifier 2005–NM–172–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 

68380 Federal Register / Vol. 70, No. 217 / Thursday, November 10, 2005 / Proposed Rules 

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 A319–100 

and A320–200 series airplanes. The 

DGAC advises that, in several incidents, 

plastic identification labels have been 

found floating in the fuel tanks. There 

are two types of labels and the 

information on the labels identifies each 

rib number in the vent box and the 

manhole door fasteners in the wing fuel 

tank, for inspection purposes. 

Inspection of the airplanes revealed that 

the varnish coating and adhesive on the 

labels had deteriorated and the labels 

detached from the wing structure. 

Detached labels floating in the fuel tank 

could be ingested into the fuel pumps 

and consequently enter into the engine 

fuel feed system. These conditions, if 

not corrected, could result in an engine 

shutdown. 

Relevant Service Information 

Airbus has issued Service Bulletin 

A320–28–1102, Revision 01, dated 

February 11, 2005. The service bulletin 

describes procedures for repetitive 

detailed visual inspections of the four 

wing-tank fuel pumps and canisters for 

detached identification labels, and 

corrective action if necessary. The 

corrective action involves removing any 

label debris that is found, performing a 

detailed visual inspection for debris of 

the fuel filters and replacing the filters 

if necessary, and replacing the fuel 

pump if the inlet and outlet ports are 

blocked. The service bulletin also 

recommends sending an inspection 

report to Airbus. 

Airbus has also issued Service 

Bulletin A320–57–1117, dated July 16, 

2002. The service bulletin describes 

procedures for repetitive detailed visual 

inspections 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 corrective action if necessary. 

The corrective action involves removing 

any label debris that is found, removing 

any partially detached labels, and reidentifying certain fasteners and ribs. 

The DGAC mandated the service 

information and issued French 

airworthiness directive F–2005–121, 

dated July 20, 2005, to ensure the 

continued airworthiness of these 

airplanes in France. 

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 

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. For 

any wing-tank fuel pump failure that 

occurs, this proposed AD would also 

require performing a detailed inspection 

of the failed pump, the pump located in 

the same half wing, and the associated 

canister, and accomplishing any 

applicable corrective action, including 

replacing the pump. 

Difference Between the Proposed AD 

and French Airworthiness Directive 

The French airworthiness directive 

mandates changes to the master 

minimum equipment list (MMEL). This 

proposed AD will not mandate those 

MMEL changes because the limits 

imposed by the FAA-approved MMEL 

meet or exceed those mandated by the 

French airworthiness directive. We have 

coordinated this issue with the DGAC. 

Clarification of Inspection Terminology 

In this proposed AD, the ‘‘detailed 

visual inspections’’ specified in the 

service bulletins are referred to as 

‘‘detailed inspections.’’ We have 

included the definition for a detailed 

inspection in a note in the proposed AD. 

Costs of Compliance 

This proposed AD would affect about 

74 airplanes of U.S. registry. 

The inspection specified in Service 

Bulletin A320–28–1102 would take 

about 3 work hours (including an 

operational test) per airplane, at an 

average labor rate of $65 per work hour. 

Based on these figures, the estimated 

cost of this proposed inspection for U.S. 

operators is $14,430, or $195 per 

airplane, per inspection cycle. 

The inspection specified in Service 

Bulletin A320–57–1117 would take 

about 6 work hours (including an 

operational test) per airplane, at an 

average labor rate of $65 per work hour. 

Based on these figures, the estimated 

cost of this proposed inspection for U.S. 

operators is $28,860, or $390 per 

airplane, per inspection cycle. 

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 

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.