19876 Federal Register / Vol. 74, No. 82 / Thursday, April 30, 2009 / Rules and Regulations 

Issued in Kansas City, Missouri, on April 

23, 2009. 

Scott A. Horn, 

Acting Manager, Small Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. E9–9793 Filed 4–29–09; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2007–0391; Directorate 

Identifier 2007–NM–271–AD; Amendment 

39–15891; AD 2009–09–05] 

RIN 2120–AA64 

Airworthiness Directives; Airbus Model 

A318–100 and A319–100 Series 

Airplanes; A320–111 Airplanes; A320– 

200 Series Airplanes; and A321–100 

and A321–200 Series Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: The FAA is superseding an 

existing airworthiness directive (AD), 

which applies to certain Airbus Model 

A318–100 and A319–100 series 

airplanes; A320–111 airplanes; A320– 

200 series airplanes; and A321–100 and 

A321–200 series airplanes. That AD 

currently requires a one-time inspection 

of the horizontal hinge pin of the 103VU 

electrical panel in the avionics 

compartment to determine if the hinge 

pin can move out of the hinge, and 

related investigative and corrective 

actions if necessary. This new AD 

instead requires installing a hinge pin 

stopper on the internal door of the 

103VU electrical panel. This AD results 

from a report indicating that electrical 

wire damage was found in the 103VU 

electrical panel due to contact between 

the hinge pin and the adjacent electrical 

wire harness. We are issuing this AD to 

prevent contact between the horizontal 

hinge pin and the adjacent electrical 

wire harness, which could result in 

damage to electrical wires, and 

consequent arcing and/or failure of 

associated systems. 

DATES: This AD becomes effective June 

4, 2009. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in the AD 

as of June 4, 2009. 

ADDRESSES: For service information 

identified in this AD, contact Airbus, 

Airworthiness Office—EAS, 1 Rond 

Point Maurice Bellonte, 31707 Blagnac 

Cedex, France; telephone +33 5 61 93 36 

96; fax +33 5 61 93 44 51; e-mail: 

account.airworth-eas@airbus.com; 

Internet http://www.airbus.com. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http:// 

www.regulations.gov; or in person at the 

Docket Management Facility between 9 

a.m. and 5 p.m., Monday through 

Friday, except Federal holidays. The AD 

docket contains this AD, the regulatory 

evaluation, any comments received, and 

other information. The address for the 

Docket Office (telephone 800–647–5527) 

is the Document Management Facility, 

U.S. Department of Transportation, 

Docket Operations, M–30, West 

Building Ground Floor, Room W12–140, 

1200 New Jersey Avenue, SE., 

Washington, DC 20590. 

FOR FURTHER INFORMATION CONTACT: Tim 

Dulin, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue, SW., Renton, 

Washington 98057–3356; telephone 

(425) 227–2141; fax (425) 227–1149. 

SUPPLEMENTARY INFORMATION: 

Discussion 

The FAA issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to include an AD that 

supersedes AD 2006–03–10, amendment 

39–14474 (71 FR 6665, February 9, 

2006). The existing AD applies to 

certain Airbus Model A318–100 and 

A319–100 series airplanes; A320–111 

airplanes; A320–200 series airplanes; 

and A321–100 and A321–200 series 

airplanes. That NPRM was published in 

the Federal Register on January 9, 2008 

(73 FR 1558). That NPRM proposed to 

discontinue the existing requirements 

and instead require installing a hinge 

pin stopper on the internal door of the 

103VU electrical panel. This AD results 

from a report indicating that electrical 

wire damage was found in the 103VU 

electrical panel due to contact between 

the hinge pin and the adjacent electrical 

wire harness. 

Comments 

We provided the public the 

opportunity to participate in the 

development of this AD. We have 

considered the comments that have 

been received on the NPRM. 

Request for Additional Action 

The Air Transport Association (ATA), 

on behalf of one of its members, 

Northwest Airlines (NWA), notes that 

the proposed modification prevents 

only outboard migration of the pins, and 

requests that the AD be changed to 

require a hinge pin stopper to be added 

to both ends of the hinge to completely 

contain the hinge pin and prevent 

inboard migration. 

We do not agree with ATA’s request. 

We are issuing this AD to address 

potential wire damage due to outboard 

migration of the hinge pin. There is no 

potential of wire damage due to inboard 

migration of the pin. However, if 

additional data show that inboard 

migration of the hinge pin causes an 

unsafe condition, we might consider 

further rulemaking. We have not 

changed the AD in this regard. 

Request for Alternate Modification 

The ATA, on behalf of NWA, requests 

that the AD be changed to allow the 

hinge stoppers to be installed using the 

existing hole in the lower angle fitting 

(part number D92510153000) adjacent 

to the end hinge mounting hole, instead 

of drilling a new hole through the hinge 

assembly. NWA states that this change 

would eliminate the need for any 

drilling during modification, and would 

more easily facilitate accomplishment 

within the line maintenance 

environment, providing greater 

scheduling flexibility. 

We do not agree with ATA’s request. 

Airbus Mandatory Service Bulletin 

A320–25–1535, dated April 27, 2007, 

specifies drilling a hole on the hinge. 

The commenter did not provide 

sufficient data to substantiate that using 

the existing hole would address the 

identified unsafe condition. To use a 

different method from the one specified 

in that service bulletin, operators may 

request approval of an alternative 

method of compliance (AMOC) 

according to paragraph (g) of the AD. 

We have not changed the AD in this 

regard. 

Conclusion 

We have carefully reviewed the 

available data, including the comments 

that have been submitted, and 

determined that air safety and the 

public interest require adopting the AD 

as proposed. 

Costs of Compliance 

This AD affects about 658 Airbus 

Model A318–100 and A319–100 series 

airplanes; A320–111 airplanes; A320– 

200 series airplanes; and A321–100 and 

A321–200 series airplanes of U.S. 

registry. The new actions take about 1 

work hour per airplane, at an average 

labor rate of $80 per work hour. 

Required parts cost about $20 per 

airplane. Based on these figures, the 

estimated cost of the new actions 

specified in this AD for U.S. operators 

is $65,800, or $100 per airplane. 

Federal Register / Vol. 74, No. 82 / Thursday, April 30, 2009 / Rules and Regulations 19877 

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 removing amendment 39–14474 (71 

FR 6665, February 9, 2006) and by 

adding the following new airworthiness 

directive (AD): 

2009–09–05 Airbus: Amendment 39–15891. 

Docket No. FAA–2007–0391; Directorate 

Identifier 2007–NM–271–AD. 

Effective Date 

(a) This AD becomes effective June 4, 2009. 

Affected ADs 

(b) This AD supersedes AD 2006–03–10. 

Applicability 

(c) This AD applies to Airbus Model A318– 

111 and 112; A319–111, –112, –113, –114, 

–115, –131, –132, and –133; A320–111, –211, 

–212, –214, –231, –232, and –233; and A321– 

111, –112, –131, –211, –212, –213, –231, and 

–232 airplanes; certificated in any category; 

all manufactured serial numbers; except for 

those airplanes on which Airbus 

Modification 36115 has been done in 

production or Airbus Mandatory Service 

Bulletin A320–25–1535, dated April 27, 

2007, has been done in service. 

Unsafe Condition 

(d) This AD results from a report indicating 

that electrical wire damage was found in the 

103VU electrical panel due to contact 

between the hinge pin and the adjacent 

electrical wire harness. We are issuing this 

AD to prevent contact between the horizontal 

hinge pin and the adjacent electrical wire 

harness, which could result in damage to 

electrical wires, and consequent arcing and/ 

or failure of associated systems. 

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 

(f) Within 18 months after the effective 

date of this AD, install a hinge pin stopper 

on the internal door of the 103VU electrical 

panel in accordance with the 

Accomplishment Instructions of Airbus 

Mandatory Service Bulletin A320–25–1535, 

dated April 27, 2007. 

Alternative Methods of Compliance 

(AMOCs) 

(g)(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) To request a different method of 

compliance or a different compliance time 

for this AD, follow the procedures in 14 CFR 

39.19. Before using any approved AMOC on 

any airplane to which the AMOC applies, 

notify your appropriate principal inspector 

(PI) in the FAA Flight Standards District 

Office (FSDO), or lacking a PI, your local 

FSDO. 

Related Information 

(h) European Aviation Safety Agency 

Airworthiness Directive 2007–0214, dated 

August 7, 2007, also addresses the subject of 

this AD. 

Material Incorporated by Reference 

(i) You must use Airbus Mandatory Service 

Bulletin A320–25–1535, dated April 27, 

2007, to do the actions required by this AD, 

unless the AD specifies otherwise. 

(1) The Director of the Federal Register 

approved the incorporation by reference of 

this service information under 5 U.S.C. 

552(a) and 1 CFR part 51. 

(2) For service information identified in 

this AD, contact Airbus, Airworthiness 

Office—EAS, 1 Rond Point Maurice Bellonte, 

31707 Blagnac Cedex, France; telephone +33 

5 61 93 36 96; fax +33 5 61 93 44 51; e-mail: 

account.airworth-eas@airbus.com; Internet 

http://www.airbus.com. 

(3) You may review copies of the service 

information at the FAA, Transport Airplane 

Directorate, 1601 Lind Avenue, SW., Renton, 

Washington. For information on the 

availability of this material at the FAA, call 

425–227–1221 or 425–227–1152. 

(4) You may also review copies of the 

service information that is incorporated by 

reference at the National Archives and 

Records Administration (NARA). For 

information on the availability of this 

material at 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 April 15, 

2009. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. E9–9714 Filed 4–29–09; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF HEALTH AND 

HUMAN SERVICES 

Food and Drug Administration 

21 CFR Part 524 

[Docket No. FDA–2009–N–0665] 

Ophthalmic and Topical Dosage Form 

New Animal Drugs; Selamectin 

AGENCY: Food and Drug Administration, 

HHS. 

ACTION: Final rule. 

SUMMARY: The Food and Drug 

Administration (FDA) is amending the 

animal drug regulations to reflect 

approval of a supplemental new animal 

drug application (NADA) filed by Pfizer, 

Inc. The supplemental NADA revises 

the minimum age of treatment from 6 

weeks to 8 weeks for kittens treated 

with a topical selamectin solution. 

DATES: This rule is effective April 30, 

2009.