59236 Federal Register / Vol. 70, No. 196 / Wednesday, October 12, 2005 / Rules and Regulations 

further flight, repair per a method approved 

by either the Manager, International Branch, 

ANM–116, Transport Airplane Directorate, 

FAA; or the DGAC (or its delegated agent). 

Within 1,480 flight cycles or 7,400 flight 

hours, whichever is first, after repair of any 

cracking, perform an ultrasonic inspection as 

required by paragraph (g) of this AD. Repeat 

the ultrasonic inspection thereafter at 

intervals not to exceed 1,480 flight cycles or 

7,400 flight hours, whichever is first. 

No Reporting Required 

(i) Although Airbus Service Bulletin A340–

57–4087, dated November 21, 2003, specifies 

submitting an inspection report to the 

manufacturer, this AD does not include that 

requirement. 

Alternative Methods of Compliance 

(AMOCs) 

(j)(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 

(k) French airworthiness directive F–2005–

007, dated January 5, 2005, also addresses the 

subject of this AD. 

Material Incorporated by Reference 

(l) You must use Airbus Service Bulletin 

A340–57–4087, including Appendix 01, 

dated November 21, 2003, to perform the 

actions that are required by this AD, unless 

the AD specifies otherwise. The Director of 

the Federal Register approved the 

incorporation by reference of this document 

in accordance with 5 U.S.C. 552(a) and 1 CFR 

part 51. Contact Airbus, 1 Rond Point 

Maurice Bellonte, 31707 Blagnac Cedex, 

France, for a copy of this service information. 

You may review copies at the Docket 

Management Facility, U.S. Department of 

Transportation, 400 Seventh Street SW., 

room PL–401, Nassif Building, Washington, 

DC; on the Internet at http://dms.dot.gov; or 

at the National Archives and Records 

Administration (NARA). For information on 

the availability of this material at the NARA, 

call (202) 741–6030, or go to http:// 

www.archives.gov/federal-register/cfr/ibrlocations.html. 

Issued in Renton, Washington, on 

September 28, 2005. 

Kalene C. Yanamura, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 05–20073 Filed 10–11–05; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2005–21862; Directorate 

Identifier 2005–NM–091–AD; Amendment 

39–14333; AD 2005–20–36] 

RIN 2120–AA64 

Airworthiness Directives; Airbus Model 

A320–111 Airplanes; and Model A320–

200, A321–100, and A321–200 Series 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: The FAA is adopting a new 

airworthiness directive (AD) for certain 

Airbus Model A320–111 airplanes; and 

Model A320–200, A321–100, and A321–

200 series airplanes. This AD requires 

installing a bonding lead between the 

low pressure valve and the adjacent 

pipe assembly in each wing. This AD 

results from fuel system reviews 

conducted by the manufacturer. We are 

issuing this AD to prevent an ignition 

source for fuel vapor in the wing, which 

could result in fire or explosion in the 

adjacent wing fuel tank. 

DATES: This AD becomes effective 

November 16, 2005. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in the AD 

as of November 16, 2005. 

ADDRESSES: You may examine the 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., Nassif Building, room PL–401, 

Washington, DC. 

Contact Airbus, 1 Rond Point Maurice 

Bellonte, 31707 Blagnac Cedex, France, 

for service information identified in this 

AD. 

FOR FURTHER INFORMATION CONTACT: Dan 

Rodina, Aerospace Engineer, 

International Branch, ANM–116, FAA, 

Transport Airplane Directorate, 1601 

Lind Avenue, SW., Renton, Washington 

98055–4056; telephone (425) 227–2125; 

fax (425) 227–1149. 

SUPPLEMENTARY INFORMATION: 

Examining the Docket 

You may examine the airworthiness 

directive (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 street address stated in the 

ADDRESSES section. 

Discussion 

The FAA issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to include an AD that would 

apply to certain Airbus Model A320–

111 airplanes; and Model A320–200, 

A321–100, and A321–200 series 

airplanes. That NPRM was published in 

the Federal Register on July 19, 2005 

(70 FR 41352). That NPRM proposed to 

require installing a bonding lead 

between the low pressure valve and the 

adjacent pipe assembly in each wing. 

Comments 

We provided the public the 

opportunity to participate in the 

development of this AD. We have 

considered the comment received. 

Request to Allow Credit for Use of 

Original Issue of Service Bulletin 

One commenter requests that we give 

credit for actions accomplished prior to 

the effective date of the AD using Airbus 

Service Bulletin A320–28–1055, dated 

July 12, 1993. The commenter contends 

that such credit is permitted by French 

airworthiness directive F–2005–058, 

dated April 13, 2005. 

We agree with this request. We have 

reviewed the original issue of the 

service bulletin and determined that no 

significant technical changes were made 

in the issuance of Airbus Service 

Bulletin A320–28–1055, Revision 1, 

dated March 8, 1994. Therefore, we 

have added new paragraph (g) to give 

credit as specified and re-identified 

existing paragraphs (g) and (h) to (h)(1) 

and (i) in this AD. 

Clarification of Alternative Method of 

Compliance (AMOC) Paragraph 

We have revised this action to clarify 

the appropriate procedure for notifying 

the principal inspector before using any 

approved AMOC on any airplane to 

which the AMOC applies. 

Conclusion 

We have carefully reviewed the 

available data, including the comment 

received, and determined that air safety 

and the public interest require adopting 

the AD with the changes described 

previously. We have determined that 

these changes will neither increase the 

economic burden on any operator nor 

increase the scope of the AD. 

Costs of Compliance 

This AD will affect about 403 

airplanes of U.S. registry. The required 

Federal Register / Vol. 70, No. 196 / Wednesday, October 12, 2005 / Rules and Regulations 59237 

actions will take about 2 work hours per 

airplane, at an average labor rate of $65 

per work hour. Required parts will be 

obtained from operator stores. Based on 

these figures, the estimated cost of the 

AD for U.S. operators is $52,390, or 

$130 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 AD will 

not have federalism implications under 

Executive Order 13132. This AD will 

not have a substantial direct effect on 

the States, on the relationship between 

the national government and the States, 

or on the distribution of power and 

responsibilities among the various 

levels of government. 

For the reasons discussed above, I 

certify that this AD: 

(1) Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866; 

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

DOT Regulatory Policies and Procedures 

(44 FR 11034, February 26, 1979); and 

(3) Will not have a significant 

economic impact, positive or negative, 

on a substantial number of small entities 

under the criteria of the Regulatory 

Flexibility Act. 

We prepared a regulatory evaluation 

of the estimated costs to comply with 

this AD 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, Incorporation by reference, 

Safety. 

Adoption of the Amendment 

■ Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA amends 14 CFR part 39 as 

follows: 

PART 39—AIRWORTHINESS 

DIRECTIVES 

■ 1. The authority citation for part 39 

continues to read as follows: 

Authority: 49 U.S.C. 106(g), 40113, 44701. 

§ 39.13 [Amended] 

■ 2. The Federal Aviation 

Administration (FAA) amends § 39.13 

by adding the following new 

airworthiness directive (AD): 

2005–20–36 Airbus: Amendment 39–14333. 

Docket No. FAA–2005–21862; 

Directorate Identifier 2005–NM–091–AD. 

Effective Date 

(a) This AD becomes effective November 

16, 2005. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to Airbus Model A320–

111, –211, –212, –214, –231, –232, and –233 

airplanes, and Model A321–111, –112, –131, 

–211, and –231 airplanes, certificated in any 

category; except those airplanes on which 

Airbus Modification 23645 has been 

incorporated in production. 

Unsafe Condition 

(d) This AD was prompted by the results 

of fuel system reviews conducted by the 

manufacturer. We are issuing this AD to 

prevent an ignition source for fuel vapor in 

the wing, which could result in fire or 

explosion in the adjacent wing fuel tank. 

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. 

Installation of Bonding Lead 

(f) Within 56 months after the effective 

date of this AD, install a bonding lead 

between the low pressure valve and the 

adjacent pipe assembly in each wing, in 

accordance with the Accomplishment 

Instructions of Airbus Service Bulletin A320–

28–1055, Revision 1, dated March 8, 1994. 

Actions Accomplished Using Original Issue 

of Service Bulletin 

(g) Actions accomplished prior to the 

effective date of this AD in accordance with 

Airbus Service Bulletin A320–28–1055, 

dated July 12, 1993, are considered 

acceptable for compliance with the 

corresponding actions required by paragraph 

(f) of this AD. 

Alternative Methods of Compliance 

(AMOCs) 

(h)(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 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–

058, dated April 13, 2005, also addresses the 

subject of this AD. 

Material Incorporated by Reference 

(j) You must use Airbus Service Bulletin 

A320–28–1055, Revision 1, dated March 8, 

1994, to perform the actions that are required 

by this AD, unless the AD specifies 

otherwise. The Director of the Federal 

Register approved the incorporation by 

reference of this document in accordance 

with 5 U.S.C. 552(a) and 1 CFR part 51. 

Contact Airbus, 1 Rond Point Maurice 

Bellonte, 31707 Blagnac Cedex, France, for a 

copy of this service information. You may 

review copies at the Docket Management 

Facility, U.S. Department of Transportation, 

400 Seventh Street SW., room PL–401, Nassif 

Building, Washington, DC; on the Internet at 

http://dms.dot.gov; or at the National 

Archives and Records Administration 

(NARA). For information on the availability 

of this material at the NARA, call (202) 741–

6030, or go to http://www.archives.gov/ 

federal_register/code_of_federal_regulations/ 

ibr_locations.html. 

Issued in Renton, Washington, on 

September 28, 2005. 

Kalene C. Yanamura, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 05–20067 Filed 10–11–05; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2005–21173; Directorate 

Identifier 2005–CE–22–AD; Amendment 39–

14321; AD 2005–20–25] 

RIN 2120–AA64 

Airworthiness Directives; The Cessna 

Aircraft Company Models 401, 401A, 

401B, 402, 402A, 402B, 402C, 404, 411, 

411A, 414, 414A, 421, 421A, 421B, 

421C, 425, and 441 Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: The FAA adopts a new 

airworthiness directive (AD) for certain 

The Cessna Aircraft Company (Cessna) 

Models 401, 401A, 401B, 402, 402A, 

402B, 402C, 404, 411, 411A, 414, 414A, 

421, 421A, 421B, 421C, 425, and 441 

airplanes equipped with certain 

avionics bus circuit breaker switches.