62568 Federal Register / Vol. 72, No. 214 / Tuesday, November 6, 2007 / Rules and Regulations 

2007–23–02 Airbus: Amendment 39–15248. 

Docket No. FAA–2007–28925; 

Directorate Identifier 2007–NM–123–AD. 

Effective Date 

(a) This airworthiness directive (AD) 

becomes effective December 11, 2007. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to Airbus Model A330–

200 and –300 series airplanes and Model 

A340–200 and –300 series airplanes; 

certificated in any category; all 

manufacturer’s serial numbers (MSN) up to 

MSN 0402 included, except MSN 051. 

Subject 

(d) Air Transport Association (ATA) of 

America Code 53: Fuselage. 

Reason 

(e) The mandatory continuing 

airworthiness information (MCAI) states: 

During ground inspection of an A340–311 

aircraft, it has been discovered that 5 

fasteners were missing between Frame (FR) 

18 and FR19 on longitudinal joint at stringer 

28RH (right hand). 

Further investigations have revealed that 

the missing fasteners have not been installed 

in production due to incorrect production 

instructions. 

If not corrected, this situation could affect 

the structural integrity of the aircraft in the 

area of stringer 28 between FR18 and FR19 

at longitudinal joint. 

In order to re-establish the structural 

strength of the aircraft, this Airworthiness 

Directive (AD) renders mandatory the 

inspection of the longitudinal joint at stringer 

28 RH between FR18 and FR19 [for missing 

fasteners]. 

For airplanes on which any fastener is 

missing, the corrective actions include doing 

a detailed visual inspection for cracking of 

the adjacent fastener area from the outside, 

without removing the fasteners; and if no 

crack is found, doing a rotating probe 

inspection for cracks of the adjacent fastener 

holes after removing the fasteners, and 

replacing any missing fastener. The 

corrective actions also include contacting 

Airbus for repair instructions and repair if 

fasteners are not at nominal diameter or if 

any crack is found. 

Actions and Compliance 

(f) Before the accumulation of 14,000 flight 

cycles from the first flight of the aircraft, or 

within 1,500 flight cycles following the 

effective date of this AD, whichever occurs 

later, unless already done, do the following 

actions: Perform a detailed visual inspection 

of the longitudinal joint at stringer 28 RH 

between FR18 and FR19 for missing 

fasteners, and do all applicable corrective 

actions before further flight, in accordance 

with the instructions defined in Airbus 

Service Bulletin A330–53–3170 or A340–53–

4175, both dated March 27, 2007. 

FAA AD Differences 

Note: This AD differs from the MCAI and/ 

or service information as follows: No 

differences. 

Other FAA AD Provisions 

(g) The following provisions also apply to 

this AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Branch, ANM–116, FAA, has the authority to 

approve AMOCs for this AD, if requested 

using the procedures found in 14 CFR 39.19. 

Send information to ATTN: Tim Backman, 

Aerospace Engineer, International Branch, 

ANM–116, FAA, Transport Airplane 

Directorate, 1601 Lind Avenue, SW., Renton, 

Washington 98057–3356; telephone (425) 

227–2797; fax (425) 227–1149. 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. 

(2) Airworthy Product: For any requirement 

in this AD to obtain corrective actions from 

a manufacturer or other source, use these 

actions if they are FAA-approved. Corrective 

actions are considered FAA-approved if they 

are approved by the State of Design Authority 

(or their delegated agent). You are required 

to assure the product is airworthy before it 

is returned to service. 

(3) Reporting Requirements: For any 

reporting requirement in this AD, under the 

provisions of the Paperwork Reduction Act, 

the Office of Management and Budget (OMB) 

has approved the information collection 

requirements and has assigned OMB Control 

Number 2120–0056. 

Related Information 

(h) Refer to MCAI European Aviation 

Safety Agency Airworthiness Directive 2007–

0125, dated May 4, 2007, and Airbus Service 

Bulletins A330–53–3170 and A340–53–4175, 

both dated March 27, 2007, for related 

information. 

Material Incorporated by Reference 

(i) You must use the service information 

specified in Table 1 of this AD 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, 1 Rond Point 

Maurice Bellonte, 31707 Blagnac Cedex, 

France. 

(3) You may review copies at the FAA, 

Transport Airplane Directorate, 1601 Lind 

Avenue, SW., Renton, Washington; or 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/cfr/ibrlocations.html. 

TABLE 1.—MATERIAL INCORPORATED

BY REFERENCE

Airbus Service Bulletin Date 

A330–53–3170, excluding Appendix 01 ........ March 27, 2007. 

A340–53–4175, excluding Appendix 01 ........ March 27, 2007. 

Issued in Renton, Washington, on October 

27, 2007. 

Stephen P. Boyd, 

Assistant Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. E7–21686 Filed 11–5–07; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2007–28882; Directorate 

Identifier 2007–NM–035–AD; Amendment 

39–15247; AD 2007–23–01] 

RIN 2120–AA64 

Airworthiness Directives; Goodrich 

Evacuation Systems Approved Under 

Technical Standard Order (TSO) TSO–

C69b and Installed on Airbus Model 

A330–200 and –300 Series Airplanes, 

Model A340–200 and –300 Series 

Airplanes, and Model A340–541 and 

–642 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 Goodrich evacuation 

systems approved under TSO–C69b and 

installed on certain Airbus Model 

A330–200 and –300 series airplanes, 

Model A340–200 and –300 series 

airplanes, and Model A340–541 and 

–642 airplanes. That AD currently 

requires inspecting to determine the 

part number of the pressure relief valves 

on the affected Goodrich evacuation 

systems, and corrective action if 

necessary. For certain airplanes, this 

new AD requires an additional 

inspection to determine the part number 

of the pressure relief valves, and 

corrective action if necessary. This AD 

results from a report indicating that, 

during maintenance testing, the 

pressure relief valves on the affected 

Goodrich evacuation systems did not 

seal when activated, which caused the 

pressure in the escape slide/raft to drop 

below the minimum allowable raft 

mode pressure. We are issuing this AD 

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Federal Register / Vol. 72, No. 214 / Tuesday, November 6, 2007 / Rules and Regulations 62569 

to prevent loss of pressure in the escape 

slides/rafts after an emergency 

evacuation, which could result in 

inadequate buoyancy to support the 

raft’s passenger capacity during 

ditching, and increase the chance for 

injury to raft passengers. 

DATES: This AD becomes effective 

December 11, 2007. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in the AD 

as of December 11, 2007. 

On July 17, 2006 (71 FR 33606, June 

12, 2006), the Director of the Federal 

Register approved the incorporation by 

reference of Goodrich Service Bulletin 

25–355, dated July 25, 2005. 

ADDRESSES: For service information 

identified in this AD, contact Goodrich, 

Aircraft Interior Products, ATTN: 

Technical Publications, 3414 South 

Fifth Street, Phoenix, AZ 85040. 

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: 

Tracy Ton, Aerospace Engineer, Cabin 

Safety/Mechanical and Environmental 

Systems Branch, ANM–150L, FAA, Los 

Angeles Aircraft Certification Office, 

3960 Paramount Boulevard, Lakewood, 

California 90712–4137; telephone (562) 

627–5352; fax (562) 627–5210. 

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 2006–12–08, amendment 

39–14633 (71 FR 33606, June 12, 2006). 

The existing AD applies to Goodrich 

evacuation systems approved under 

Technical Standard Order (TSO) TSO–

C69b and installed on certain Airbus 

Model A330–200 and –300 series 

airplanes, Model A340–200 and –300 

series airplanes, and Model A340–541 

and –642 airplanes. That NPRM was 

published in the Federal Register on 

August 6, 2007 (72 FR 43576). That 

NPRM proposed to continue to require 

inspecting to determine the part number 

of the pressure relief valves on the 

affected Goodrich evacuation systems, 

and corrective action if necessary. For 

certain airplanes, that NPRM also 

proposed to require an additional 

inspection to determine the part number 

of the pressure relief valves, and 

corrective action if necessary. 

Comments 

We provided the public the 

opportunity to participate in the 

development of this AD. No comments 

have been received on the NPRM or on 

the determination of the cost to the 

public. 

Conclusion 

We have carefully reviewed the 

available data and determined that air 

safety and the public interest require 

adopting the AD as proposed. 

Costs of Compliance 

There are about 689 airplanes of the 

affected design in the worldwide fleet. 

This AD affects about 27 airplanes of 

U.S. registry. 

The actions that are required by AD 

2006–12–08 and retained in this AD 

take about 1 work hour per airplane, at 

an average labor rate of $80 per work 

hour. Based on these figures, the 

estimated cost of the currently required 

actions is $2,160, or $80 per airplane. 

All airplanes affected by the new 

required action are currently operated 

by non-U.S. operators under foreign 

registry. If an affected airplane is 

imported and placed on the U.S. 

Register in the future, the new actions 

will take about 1 work hour per 

airplane, at an average labor rate of $80 

per work hour. Based on these figures, 

the estimated cost of the new actions 

specified in this AD for U.S. operators 

is $80 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 removing amendment 39–14633 (71 

FR 33606, June 12, 2006) and by adding 

the following new airworthiness 

directive (AD): 

2007–23–01 Goodrich (Formerly BF 

Goodrich): Amendment 39–15247. 

Docket No. FAA–2007–28882; 

Directorate Identifier 2007–NM–035–AD. 

Effective Date 

(a) This AD becomes effective December 

11, 2007. 

Affected ADs 

(b) This AD supersedes AD 2006–12–08. 

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62570 Federal Register / Vol. 72, No. 214 / Tuesday, November 6, 2007 / Rules and Regulations 

Applicability 

(c) This AD applies to Goodrich evacuation 

systems approved under Technical Standard 

Order (TSO) TSO–C69b, as installed on 

Airbus Model A330–201, –202, –203, –223, 

–243, –301, –321, –322, –323, –341, –342, 

and –343 airplanes; Model A340–211, –212, 

–213, –311, –312, and –313 airplanes; and 

Model A340–541 and –642 airplanes; 

certificated in any category. 

Unsafe Condition 

(d) This AD results from a report indicating 

that, during maintenance testing, the 

pressure relief valves on the affected 

Goodrich evacuation systems did not seal 

when activated, which caused the pressure in 

the escape slide/raft to drop below the 

minimum allowable raft mode pressure. We 

are issuing this AD to prevent loss of 

pressure in the escape slides/rafts after an 

emergency evacuation, which could result in 

inadequate buoyancy to support the raft’s 

passenger capacity during ditching, and 

increase the chance for injury to raft 

passengers. 

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. 

Restatement of Requirements of AD 2006–

12–08 

Inspection for Certain Part Number (P/N) 

(f) For all airplanes: Within 36 months after 

July 17, 2006 (the effective date of AD 2006–

12–08): Perform an inspection to determine 

the part number of the pressure relief valve 

on the Goodrich evacuation systems in 

accordance with the Accomplishment 

Instructions of Goodrich Service Bulletin 25–

355, dated July 25, 2005; or Goodrich Service 

Bulletin 25–355, Revision 1, dated July 24, 

2006. After the effective date of this AD, only 

Goodrich Service Bulletin 25–355, Revision 

1, dated July 24, 2006, may be used. 

(1) If any pressure relief valve having P/N 

4A3791–3 is installed, before further flight, 

replace the valve with a new or serviceable 

valve having P/N 4A3641–1 and mark the girt 

adjacent to the placard, in accordance with 

the Accomplishment Instructions of the 

service bulletin. 

(2) If any pressure release valve having P/ 

N 4A3641–1 is installed, before further flight, 

mark the girt adjacent to the placard in 

accordance with the Accomplishment 

Instructions of the service bulletin. 

Part Installation for Airplanes Identified in 

Original Issue of the Service Bulletin 

(g) As of July 17, 2006, no person may 

install a pressure relief valve having P/N 

4A3791–3, on any airplane equipped with 

Goodrich evacuation systems identified in 

Goodrich Service Bulletin 25–355, dated July 

25, 2005. 

New Requirements of This AD 

Inspection for Certain Other P/N 

(h) For Model A340–541 airplanes: Within 

36 months after the effective date of this AD, 

perform an inspection to determine the part 

number of the pressure relief valve on the 

Goodrich evacuation systems in accordance 

with the Accomplishment Instructions of 

Goodrich Service Bulletin 25–355, Revision 

1, dated July 24, 2006. 

(1) If any pressure relief valve having P/N 

4A3791–6 is installed, before further flight, 

replace the valve with a new or serviceable 

valve having P/N 4A3641–26 and mark the 

girt adjacent to the placard, in accordance 

with the Accomplishment Instructions of the 

service bulletin. 

(2) If any pressure release valve having P/ 

N 4A3641–26 is installed, before further 

flight, mark the girt adjacent to the placard 

in accordance with the Accomplishment 

Instructions of the service bulletin. 

Parts Installation for All Airplanes 

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

person may install a pressure relief valve 

having P/N 4A3791–3, on any airplane 

equipped with Goodrich evacuation systems 

identified in Goodrich Service Bulletin 25–

355, Revision 1, dated July 24, 2006. 

(j) As of the effective date of this AD, no 

person may install a pressure relief valve 

having P/N 4A3791–6, on any airplane 

equipped with Goodrich evacuation systems 

identified in Goodrich Service Bulletin 25–

355, Revision 1, dated July 24, 2006. 

Alternative Methods of Compliance 

(AMOCs) 

(k)(1) The Manager, Los Angeles Aircraft 

Certification Office, 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. 

(3) AMOCs approved previously in 

accordance with AD 2006–12–08 are 

approved as AMOCs for the corresponding 

provisions of this AD. 

Material Incorporated by Reference 

(l) You must use Goodrich Service Bulletin 

25–355, dated July 25, 2005; or Goodrich 

Service Bulletin 25–355, Revision 1, dated 

July 24, 2006; as applicable, to perform the 

actions that are required by this AD, unless 

the AD specifies otherwise. 

(1) The Director of the Federal Register 

approved the incorporation by reference of 

Goodrich Service Bulletin 25–355, Revision 

1, dated July 24, 2006, in accordance with 5 

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

(2) On July 17, 2006 (71 FR 33606, June 12, 

2006), the Director of the Federal Register 

approved the incorporation by reference of 

Goodrich Service Bulletin 25–355, dated July 

25, 2005. 

(3) Contact Goodrich, Aircraft Interior 

Products, ATTN: Technical Publications, 

3414 South Fifth Street, Phoenix, AZ 85040, 

for a copy of this service information. You 

may review copies at the FAA, Transport 

Airplane Directorate, 1601 Lind Avenue, 

SW., Renton, Washington; or 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/federalregister/cfr/ibr-locations.html. 

Issued in Renton, Washington, on October 

27, 2007. 

Stephen P. Boyd, 

Assistant Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. E7–21685 Filed 11–5–07; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF HEALTH AND 

HUMAN SERVICES 

Food and Drug Administration 

21 CFR Part 558 

New Animal Drugs; Ractopamine 

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 

Elanco Animal Health. The 

supplemental NADA provides for an 

increased level of monensin in threeway combination Type C medicated 

feeds containing ractopamine, 

monensin, and tylosin for cattle fed in 

confinement for slaughter and a revision 

to bacterial pathogen nomenclature. 

DATES: This rule is effective November 

6, 2007. 

FOR FURTHER INFORMATION CONTACT: 

Daniel A. Benz, Center for Veterinary 

Medicine (HFV–126), Food and Drug 

Administration, 7500 Standish Pl., 

Rockville, MD 20855, 301–827–0223, 

e-mail: daniel.benz@fda.hhs.gov. 

SUPPLEMENTARY INFORMATION: Elanco 

Animal Health, A Division of Eli Lilly 

& Co., Lilly Corporate Center, 

Indianapolis, IN 46285, filed a 

supplement to NADA 141–224 that 

provides for use of OPTAFLEXX 

(ractopamine hydrochloride), 

RUMENSIN (monensin USP), and 

TYLAN (tylosin phosphate) Type A 

medicated articles to make dry and 

liquid three-way combination 

medicated feeds for cattle fed in 

confinement for slaughter. The 

supplemental NADA provides for an 

increased level of monensin in 

combination Type C medicated feeds 

and a revision to bacterial pathogen 

nomenclature. The supplemental NADA 

is approved as of October 12, 2007, and 

the regulations in 21 CFR 558.500 are 

amended to reflect the approval. 

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