Federal Register / Vol. 72, No. 26 / Thursday, February 8, 2007 / Rules and Regulations 5919 

issuance. The FAA is requesting 

comments to allow interested persons to 

submit views that may not have been 

submitted in response to the prior 

opportunities for comment described 

above. 

List of Subjects in 14 CFR Part 23 

Aircraft, Aviation safety, Signs and 

symbols. 

Citation 

The authority citation for these 

special conditions is as follows: 

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

44701; 14 CFR 21.16 and 21.17; and 14 CFR 

11.38 and 11.19. 

The Special Conditions 

Accordingly, pursuant to the 

authority delegated to me by the 

Administrator, the following special 

conditions are issued as part of the type 

certification basis for the ATG Javelin 

Model 100. 

1. Protection of Electrical and 

Electronic Systems from High Intensity 

Radiated Fields (HIRF). Each system 

that performs critical functions must be 

designed and installed to ensure that the 

operations, and operational capabilities 

of these systems to perform critical 

functions, are not adversely affected 

when the airplane is exposed to high 

intensity radiated electromagnetic fields 

external to the airplane. 

2. For the purpose of these special 

conditions, the following definition 

applies: 

Critical Functions: Functions whose 

failure would contribute to, or cause, a 

failure condition that would prevent the 

continued safe flight and landing of the 

airplane. 

Issued in Kansas City, Missouri, on January 

31, 2007. 

Kim Smith, 

Manager, Small Airplane Directorate, Aircraft 

Certification Service. 

[FR Doc. E7–2097 Filed 2–7–07; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2007–27150; Directorate 

Identifier 2006–NM–288–AD; Amendment 

39–14929; AD 2007–03–18] 

RIN 2120–AA64 

Airworthiness Directives; Airbus Model 

A300 and A300–600 Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule; request for 

comments. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for the 

products listed above. This AD results 

from mandatory continuing 

airworthiness information (MCAI) 

issued by an aviation authority of 

another country to identify and correct 

an unsafe condition on an aviation 

product. The MCAI describes the unsafe 

condition as cracking in the wing main 

landing gear (MLG) rib 5 aft bearing 

forward lug, which could affect the 

structural integrity of the MLG 

attachment. This AD requires actions 

that are intended to address the unsafe 

condition described in the MCAI. 

DATES: This AD becomes effective 

February 23, 2007. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain documents listed in this AD 

as of February 23, 2007. 

We must receive comments on this 

AD by March 12, 2007. 

ADDRESSES: You may send comments by 

any of the following methods: 

• DOT Docket Web Site: Go to 

http://dms.dot.gov and follow the 

instructions for sending your comments 

electronically. 

• Fax: (202) 493–2251. 

• Mail: Docket Management Facility, 

U.S. Department of Transportation, 400 

Seventh Street, SW., Nassif Building, 

Room PL–401, Washington, DC 20590–

0001. 

• 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. 

• Federal eRulemaking Portal: http:// 

www.regulations.gov. Follow the 

instructions for submitting comments. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http://dms.dot.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 street address for the 

Docket Office (telephone (800) 647–

5227) is in the ADDRESSES section. 

Comments will be available in the AD 

docket shortly after receipt. 

FOR FURTHER INFORMATION CONTACT: Tom 

Stafford, Aerospace Engineer, 

International Branch, ANM–116, FAA, 

Transport Airplane Directorate, 1601 

Lind Avenue, SW., Renton, Washington 

98057–3356; telephone (425) 227–1622; 

fax (425) 227–1149. 

SUPPLEMENTARY INFORMATION: 

Streamlined Issuance of AD 

The FAA is implementing a new 

process for streamlining the issuance of 

ADs related to MCAI. This streamlined 

process will allow us to adopt MCAI 

safety requirements in a more efficient 

manner and will reduce safety risks to 

the public. This process continues to 

follow all FAA AD issuance processes to 

meet legal, economic, Administrative 

Procedure Act, and Federal Register 

requirements. We also continue to meet 

our technical decision-making 

responsibilities to identify and correct 

unsafe conditions on U.S.-certificated 

products. 

This AD references the MCAI and 

related service information that we 

considered in forming the engineering 

basis to correct the unsafe condition. 

The AD contains text copied from the 

MCAI and for this reason might not 

follow our plain language principles. 

Discussion 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Community, has issued Emergency 

Airworthiness Directive 2006–0372–E, 

dated December 14, 2006 (referred to 

after this as ‘‘the MCAI’’), to correct an 

unsafe condition for the specified 

products. The MCAI states that during 

routine visual inspection, a crack has 

been found in the wing MLG (main 

landing gear) rib 5 aft bearing forward 

lug on two Model A310 in-service 

aircraft. Laboratory examination of one 

of the cracked ribs confirmed that the 

crack is due to the presence of pitting 

corrosion in the forward lug holes. Also, 

on both aircraft medium to heavy 

corrosion was found in the forward lugs 

on the opposite wing after removal of 

the bushings. Similar to Model A310 

aircraft, Model A300 and A300–600 

aircraft are also affected by this 

situation, which, if not detected, could 

affect the structural integrity of the MLG 

attachment. The aim of the MCAI is to 

mandate repetitive detailed visual 

inspections of wing MLG rib 5 aft 

bearing forward lugs for detection of 

through cracks and corrective action 

(contacting Airbus and replacing 

cracked lugs if necessary). The MCAI 

notes that for Airbus Model A310 

aircraft, refer to EASA Emergency 

Airworthiness Directive 2006–0335–E, 

issued November 3, 2006. In response to 

that MCAI, on December 7, 2006, we 

issued AD 2007–02–09, amendment 39–

14896 (72 FR 2612, January 22, 2007), 

to address this unsafe condition on 

Model A310 airplanes. You may obtain 


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5920 Federal Register / Vol. 72, No. 26 / Thursday, February 8, 2007 / Rules and Regulations 

further information by examining the 

MCAI in the AD docket. 

Relevant Service Information 

Airbus has issued Service Bulletins 

A300–57A0248, including Appendix 01, 

dated December 12, 2006; and A300–

57A6105, including Appendix 01, dated 

December 12, 2006. The actions 

described in this service information are 

intended to correct the unsafe condition 

identified in the MCAI. 

FAA’s Determination and Requirements 

of This AD 

This product has been approved by 

the aviation authority of another 

country, and is approved for operation 

in the United States. Pursuant to our 

bilateral agreement with this State of 

Design Authority, they have notified us 

of the unsafe condition described in the 

MCAI and service information 

referenced above. We are issuing this 

AD because we evaluated all the 

information provided by the State of 

Design Authority and determined the 

unsafe condition exists and is likely to 

exist or develop on other products of the 

same type design. 

Differences Between the AD and the 

MCAI or Service Information 

We have reviewed the MCAI and 

related service information and, in 

general, agree with their substance. But 

we might have found it necessary to use 

different words from those in the MCAI 

to ensure the AD is clear for U.S. 

operators and is enforceable. In making 

these changes, we do not intend to differ 

substantively from the information 

provided in the MCAI and related 

service information. 

We might also have required different 

actions in this AD from those in the 

MCAI in order to follow FAA policies. 

Any such differences are described in a 

separate paragraph of the AD. These 

requirements take precedence over the 

actions copied from the MCAI. 

FAA’s Determination of the Effective 

Date 

An unsafe condition exists that 

requires the immediate adoption of this 

AD. The FAA has found that the risk to 

the flying public justifies waiving notice 

and comment prior to adoption of this 

rule because following routine visual 

inspection, two through cracks have 

been found in the wing MLG rib 5 lug 

on a Model A310 airplane. The cracks 

were extended through the entire 

thickness of the forward lug. Failure of 

this attachment could result in gear 

collapse upon landing. Therefore, we 

determined that notice and opportunity 

for public comment before issuing this 

AD are impracticable and that good 

cause exists for making this amendment 

effective in fewer than 30 days. 

Comments Invited 

This AD is a final rule that involves 

requirements affecting flight safety, and 

we did not precede it by notice and 

opportunity for public comment. We 

invite you to send any written relevant 

data, views, or arguments about this AD. 

Send your comments to an address 

listed under the ADDRESSES section. 

Include ‘‘Docket No. FAA–2007–27150; 

Directorate Identifier 2006–NM–288–

AD’’ at the beginning of your comments. 

We specifically invite comments on the 

overall regulatory, economic, 

environmental, and energy aspects of 

this AD. We will consider all comments 

received by the closing date and may 

amend this AD because 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 we receive 

about this AD. 

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 determined that this AD would 

not have federalism implications under 

Executive Order 13132. This 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 this 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. 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. 

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 FAA amends § 39.13 by adding 

the following new AD: 

2007–03–18 Airbus: Amendment 39–14929. 

Docket No. FAA–2007–27150; 

Directorate Identifier 2006–NM–288–AD. 

Effective Date 

(a) This airworthiness directive (AD) 

becomes effective February 23, 2007. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to Airbus Model A300 

and A300–600 airplanes; certificated in any 

category, all certified models, all serial 

numbers except for those where LH (lefthand) and RH (right-hand) wing MLG (main 

landing gear) rib 5 forward lugs have been 

repaired by installation of oversized 

interference fit bushings as per drawing 

R57240221. 

Reason 

(d) The MCAI states that during routine 

visual inspection, a crack has been found in 

the wing MLG rib 5 aft bearing forward lug 

on two Model A310 in-service aircraft. 

Laboratory examination of one of the cracked 

ribs confirmed that the crack is due to the 

presence of pitting corrosion in the forward 

lug holes. Also, on both aircraft medium to 

heavy corrosion was found in the forward 

lugs on the opposite wing after removal of 

the bushings. On December 7, 2006, we 

issued AD 2007–02–09, amendment 39–

14896 (72 FR 2612, January 22, 2007), to 

address this unsafe condition on Model A310 

airplanes. Similar to Model A310 aircraft, the 


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Federal Register / Vol. 72, No. 26 / Thursday, February 8, 2007 / Rules and Regulations 5921 

Model A300 and A300–600 aircraft are also 

affected by this situation, which, if not 

detected, could affect the structural integrity 

of the MLG attachment. The aim of the MCAI 

is to mandate repetitive detailed visual 

inspections of wing MLG rib 5 aft bearing 

forward lugs for detection of through cracks 

and corrective action (contacting Airbus and 

replacing cracked lugs if necessary). The 

MCAI notes that for Airbus Model A310 

aircraft, refer to EASA Emergency 

Airworthiness Directive 2006–0335–E, issued 

November 3, 2006. 

Actions and Compliance 

(e) Unless already done, do the following 

actions specified in paragraphs (e)(1), (e)(2), 

and (e)(3) of this AD in accordance with 

instructions defined in Airbus Service 

Bulletin A300–57A6105, dated December 12, 

2006; or A300–57A0248, dated December 12, 

2006; as applicable. 

(1) Before the accumulation of 12,000 total 

flight cycles since new or since the most 

recent MLG rib 5 replacement if applicable, 

or within 10 days after the effective date of 

this AD, whichever occurs latest: Perform a 

detailed visual inspection of the LH and RH 

wing MLG rib 5 aft bearing forward lugs. 

(2) If a crack is detected at the LH and/or 

RH aft bearing forward lug, contact Airbus 

immediately and proceed with the 

replacement before further flight. 

(3) Repeat the inspection at intervals not to 

exceed 100 flight cycles. 

Other FAA AD Provisions 

(f) The following provisions also apply to 

this AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Branch, ANM–116, Transport Airplane 

Directorate, FAA, ATTN: Tom Stafford, 1601 

Lind Avenue, SW., Renton, Washington 

98057–3356, has the authority to approve 

AMOCs for this AD, if requested using the 

procedures found in 14 CFR 39.19. 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. 

(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. 

(4) Special Flight Permits: We are not 

allowing special flight permits, as described 

in Section 21.197 and Section 21.199 of the 

Federal Aviation Regulations (14 CFR 21.197 

and 21.199). 

Related Information 

(g) Refer to MCAI European Aviation 

Safety Agency (EASA) Emergency 

Airworthiness Directive 2006–0372–E, dated 

December 14, 2006; and Airbus Service 

Bulletins A300–57A0248 and A300–

57A6105, both including Appendix 01, both 

dated December 12, 2006, for related 

information. 

Material Incorporated by Reference 

(h) You must use Airbus Service Bulletin 

A300–57A0248, excluding Appendix 01, 

dated December 12, 2006; or Airbus Service 

Bulletin A300–57A6105, excluding 

Appendix 01, dated December 12, 2006; as 

applicable; 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. 

Issued in Renton, Washington, on January 

26, 2007. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. E7–1883 Filed 2–7–07; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2006–26191 Directorate 

Identifier 2006–CE–60–AD; Amendment 39–

14927; AD 2007–03–16] 

RIN 2120–AA64 

Airworthiness Directives; EADS 

SOCATA Model TBM 700 Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for the 

products listed above. This AD results 

from mandatory continuing 

airworthiness information (MCAI) 

issued by an aviation authority of 

another country to identify and correct 

an unsafe condition on an aviation 

product. The MCAI describes the unsafe 

condition as an excessive lateral play 

caused by a nonconforming washer that 

might lead to the deterioration of the 

elevator trim tab bearing fatigue 

resistance. We are issuing this AD to 

require actions to correct the unsafe 

condition on these products. 

DATES: This AD becomes effective 

March 15, 2007. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of March 15, 2007. 

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. 

FOR FURTHER INFORMATION CONTACT: 

Albert J. Mercado, Aerospace Engineer, 

FAA, Small Airplane Directorate, 901 

Locust, Room 301, Kansas City, 

Missouri 64106; telephone: (816) 329–

4119; fax: (816) 329–4090. 

SUPPLEMENTARY INFORMATION: 

Streamlined Issuance of AD 

The FAA is implementing a new 

process for streamlining the issuance of 

ADs related to MCAI. The streamlined 

process will allow us to adopt MCAI 

safety requirements in a more efficient 

manner and will reduce safety risks to 

the public. This process continues to 

follow all FAA AD issuance processes to 

meet legal, economic, Administrative 

Procedure Act, and Federal Register 

requirements. We also continue to meet 

our technical decision-making 

responsibilities to identify and correct 

unsafe conditions on U.S.-certificated 

products. 

This AD references the MCAI and 

related service information that we 

considered in forming the engineering 

basis to correct the unsafe condition. 

The AD contains text copied from the 

MCAI and for this reason might not 

follow our plain language principles. 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to include an AD that would 

apply to the specified products. That 

NPRM was published in the Federal 

Register on November 20, 2006 (71 FR 

67084). That NPRM proposed to require 

a check for lateral play of the elevator 

trim tabs and installation, if necessary, 

of a setting washer. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

have considered the comments received. 

Comment Issue: Summary 

EADS SOCATA comments that the 

proposed AD specifies an excessive 


cprice-sewell on PROD1PC72 with RULES