This section of the FEDERAL REGISTER

contains regulatory documents having general

applicability and legal effect, most of which

are keyed to and codified in the Code of

Federal Regulations, which is published under

50 titles pursuant to 44 U.S.C. 1510.

The Code of Federal Regulations is sold by

the Superintendent of Documents. Prices of

new books are listed in the first FEDERAL

REGISTER issue of each week.

Rules and Regulations Federal Register

61975 

Vol. 75, No. 194 

Thursday, October 7, 2010 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–0644; Directorate 

Identifier 2009–NM–204–AD; Amendment 

39–16466; AD 2010–21–06] 

RIN 2120–AA64 

Airworthiness Directives; Airbus Model 

A300 B4–600 Series Airplanes, Model 

A300 B4–600R Series Airplanes, Model 

A300 C4–605R Variant F Airplanes, and 

Model A300 F4–600R Series Airplanes 

(Collectively Called A300–600 Series 

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) 

originated 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: 

Within the framework of the A300–600 

aircraft Service Life Extension programme 

(42,500 FC [flight cycles]), it has been 

concluded that a reinforcement of the 

junction of frame bases at FR48, FR49 and 

FR51 to FR53 is necessary to enable the 

aircraft to reach the Extended Service Goal 

(ESG). 

* * * [Failure of the frame base], if not 

corrected, could affect the structural integrity 

of the fuselage. 

* * * * * 

We are issuing this AD to require 

actions to correct the unsafe condition 

on these products. 

DATES: This AD becomes effective 

November 12, 2010. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of November 12, 2010. 

ADDRESSES: You may examine the AD 

docket on the Internet at http:// 

www.regulations.gov or in person at the 

U.S. Department of Transportation, 

Docket Operations, M–30, West 

Building Ground Floor, Room W12–140, 

1200 New Jersey Avenue, SE., 

Washington, DC. 

FOR FURTHER INFORMATION CONTACT: Dan 

Rodina, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue, SW., Renton, 

Washington 98057–3356; telephone 

(425) 227–2125; fax (425) 227–1149. 

SUPPLEMENTARY INFORMATION: 

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 July 1, 2010 (75 FR 38061). 

That NPRM proposed to correct an 

unsafe condition for the specified 

products. The MCAI states: 

Within the framework of the A300–600 

aircraft Service Life Extension programme 

(42,500 FC [flight cycles]), it has been 

concluded that a reinforcement of the 

junction of frame bases at FR48, FR49 and 

FR51 to FR53 is necessary to enable the 

aircraft to reach the Extended Service Goal 

(ESG). 

* * * [Failure of the frame base], if not 

corrected, could affect the structural integrity 

of the fuselage. 

For the reasons described above, this AD 

requires the reinforcement of the affected 

junction of frame bases. 

Required actions include doing a 

dimensional measurement of the holes, 

and doing corrective actions if 

necessary; doing an eddy current 

inspection of the holes for cracking, and 

doing corrective actions if necessary; 

and doing cold expansion of the holes 

and installing fasteners. Corrective 

actions include contacting Airbus for 

repair instructions and doing the repair. 

You may obtain further information by 

examining the MCAI in the AD docket. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

considered the comment received. The 

commenter supports the NPRM. 

Change to Compliance Time Specified 

in Paragraph (h) of This AD 

We have revised paragraph (h) of this 

AD by adding the compliance time 

‘‘within 100 flight cycles after the 

effective date of this AD’’ to the sentence 

ending with ‘‘accomplish those 

instructions.’’ We have evaluated the 

data and determined that adding this 

compliance time will not adversely 

affect safety. 

Conclusion 

We reviewed the available data, 

including the comments received, and 

determined that air safety and the 

public interest require adopting the AD 

with the change described previously. 

We determined that this change will not 

increase the economic burden on any 

operator or increase the scope of the AD. 

Differences Between This 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 our FAA 

policies. Any such differences are 

highlighted in a Note within the AD. 

Costs of Compliance 

We estimate that this AD will affect 

122 products of U.S. registry. We also 

estimate that it will take about 81 workhours per product to comply with the 

basic requirements of this AD. The 

average labor rate is $85 per work-hour. 

Required parts will cost about $12,300 

per product. Where the service 

information lists required parts costs 

that are covered under warranty, we 

have assumed that there will be no 

charge for these parts. As we do not 

control warranty coverage for affected 

parties, some parties may incur costs 

higher than estimated here. Based on 

these figures, we estimate the cost of 

this AD to the U.S. operators to be 

$2,340,570, or $19,185 per product. 


srobinson on DSKHWCL6B1PROD with RULES
61976 Federal Register / Vol. 75, No. 194 / Thursday, October 7, 2010 / Rules and Regulations 

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 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 this AD: 

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. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http:// 

www.regulations.gov; or in person at the 

Docket Operations office between 9 a.m. 

and 5 p.m., Monday through Friday, 

except Federal holidays. The AD docket 

contains the NPRM, the regulatory 

evaluation, any comments received, and 

other information. The street address for 

the Docket Operations office (telephone 

(800) 647–5527) is in the ADDRESSES

section. Comments will be available in 

the AD docket shortly after receipt. 

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: 

2010–21–06 Airbus: Amendment 39–16466. 

Docket No. FAA–2010–0644; Directorate 

Identifier 2009–NM–204–AD. 

Effective Date 

(a) This airworthiness directive (AD) 

becomes effective November 12, 2010. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to Airbus Model A300 

B4–601, B4–603, B4–620, B4–622, B4–605R, 

and B4–622R airplanes; Model A300 C4– 

605R Variant F airplanes; and Model A300 

F4–605R and F4–622R airplanes; certificated 

in any category; on which modification 

12699 has not been completed. 

Subject 

(d) Air Transport Association (ATA) of 

America Code 53: Fuselage. 

Reason 

(e) The mandatory continuing 

airworthiness information (MCAI) states: 

Within the framework of the A300–600 

aircraft Service Life Extension programme 

(42,500 FC [flight cycles]), it has been 

concluded that a reinforcement of the 

junction of frame bases at FR48, FR49 and 

FR51 to FR53 is necessary to enable the 

aircraft to reach the Extended Service Goal 

(ESG). 

* * * [Failure of the frame base], if not 

corrected, could affect the structural integrity 

of the fuselage. 

* * * * * 

Compliance 

(f) You are responsible for having the 

actions required by this AD performed within 

the compliance times specified, unless the 

actions have already been done. 

Actions 

(g) Except for airplanes identified in 

paragraph (h) of this AD: At the time 

specified in paragraph (g)(1) or (g)(2) of this 

AD, as applicable, reinforce the junctions of 

frame bases FR48, FR49, FR51, FR52 and 

FR53, which includes doing a dimensional 

measurement of the holes, doing an eddy 

current inspection of the holes for cracking, 

doing a cold expansion of the holes, 

installing fasteners, and doing applicable 

corrective actions, in accordance with the 

Accomplishment Instructions of Airbus 

Mandatory Service Bulletin A300–53–6161, 

Revision 02, dated October 16, 2009. If 

cracking is found, before further flight, 

contact Airbus for repair instructions and do 

the repair. 

(1) For airplanes on which Airbus 

Modification No. 03986 has been 

accomplished as of the effective date of this 

AD: Before the accumulation of 37,600 total 

flight cycles. 

(2) For airplanes on which Airbus 

Modification No. 03986 has not been 

accomplished as of the effective date of this 

AD: Before the accumulation of 28,900 total 

flight cycles. 

(h) For airplanes modified prior to the 

effective date of this AD in accordance with 

the Accomplishment Instructions of Airbus 

Mandatory Service Bulletin A300–53–6161, 

dated February 13, 2009; or Revision 01, 

dated June 24, 2009: Within 10 days after the 

effective date of this AD, prior to doing any 

cold working process, determine if an eddy 

current inspection for cracking has been 

done, in accordance with the 

Accomplishment Instructions of Airbus 

Mandatory Service Bulletin A300–53–6161, 

Revision 02, dated October 16, 2009. If the 

eddy current inspection has not been done, 

or it cannot be proven that it has been done, 

contact Airbus for instructions and 

accomplish those instructions within 100 

flight cycles after the effective date of this 

AD. 

FAA AD Differences 

Note 1: This AD differs from the MCAI 

and/or service information as follows: No 

differences. 

Other FAA AD Provisions 

(i) The following provisions also apply to 

this AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Branch, ANM–116, Transport Airplane 

Directorate, 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: Dan Rodina, 

Aerospace Engineer, International Branch, 

ANM–116, Transport Airplane Directorate, 

FAA, 1601 Lind Avenue, SW., Renton, 

Washington 98057–3356; telephone (425) 

227–2125; fax (425) 227–1149. Before using 

any approved AMOC on any airplane to 

which the AMOC applies, notify your 

principal maintenance inspector (PMI) or 

principal avionics inspector (PAI), as 

appropriate, or lacking a principal inspector, 

your local Flight Standards District Office. 

The AMOC approval letter must specifically 

reference this AD. 

(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 FAAapproved if they are approved by the State 

of Design Authority (or their delegated 


srobinson on DSKHWCL6B1PROD with RULES
Federal Register / Vol. 75, No. 194 / Thursday, October 7, 2010 / Rules and Regulations 61977 

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 

(44 U.S.C. 3501 et seq.), the Office of 

Management and Budget (OMB) has 

approved the information collection 

requirements and has assigned OMB Control 

Number 2120–0056. 

Related Information 

(j) Refer to MCAI European Aviation Safety 

Agency Airworthiness Directive 2009–0188, 

dated August 26, 2009; and Airbus 

Mandatory Service Bulletin A300–53–6161, 

Revision 02, dated October 16, 2009; for 

related information. 

Material Incorporated by Reference 

(k) You must use Airbus Mandatory 

Service Bulletin A300–53–6161, Revision 02, 

including Appendix 01, dated October 16, 

2009 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 SAS—EAW 

(Airworthiness Office), 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.airwortheas@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. 

(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 

September 23, 2010. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2010–25017 Filed 10–6–10; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–0552; Directorate 

Identifier 2009–NM–095–AD; Amendment 

39–16464; AD 2010–21–04] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Model 747–100, 747–200B, 

and 747–200F Series Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: The FAA is superseding two 

existing airworthiness directives (ADs), 

which apply to certain Model 747–100, 

747–200B, and 747–200F series 

airplanes. The existing ADs currently 

require inspections to detect fatiguerelated skin cracks and corrosion of the 

skin panel lap joints in the fuselage 

upper lobe, and repair if necessary. One 

of the existing ADs, AD 94–12–09, also 

requires modification of certain lap 

joints and inspection of modified lap 

joints. The other AD, AD 90–15–06, 

requires repetitive detailed external 

visual inspections of the fuselage skin at 

the upper lobe skin lap joints for cracks 

and evidence of corrosion, and related 

investigative and corrective actions. 

This AD reduces the maximum interval 

of the post-modification inspections, 

and adds post-repair inspection 

requirements for certain airplanes. This 

AD results from reports of cracking on 

modified airplanes. We are issuing this 

AD to detect and correct fatigue 

cracking and corrosion in the fuselage 

upper lobe skin lap joints, which could 

lead to rapid decompression of the 

airplane and inability of the structure to 

carry fail-safe loads. 

DATES: This AD becomes effective 

November 12, 2010. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in the AD 

as of November 12, 2010. 

ADDRESSES: For service information 

identified in this AD, contact Boeing 

Commercial Airplanes, Attention: Data 

& Services Management, P.O. Box 3707, 

MC 2H–65, Seattle, Washington 98124– 

2207; telephone 206–544–5000, 

extension 1; fax 206–766–5680; e-mail 

me.boecom@boeing.com; Internet 

https://www.myboeingfleet.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: Ivan 

Li, Aerospace Engineer, Airframe 

Branch, ANM–120S, FAA, Seattle 

Aircraft Certification Office, 1601 Lind 

Avenue, SW., Renton, Washington 

98057–3356; telephone (425) 917–6437; 

fax (425) 917–6590. 

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 90–15–06, Amendment 

39–6653 (55 FR 28600, July 12, 1990), 

and AD 94–12–09, Amendment 39–8937 

(59 FR 30285, June 13, 1994). The 

existing ADs apply to certain Model 

747–100, 747–200B, and 747–200F 

series airplanes. That NPRM was 

published in the Federal Register on 

June 22, 2010 (75 FR 35356). That 

NPRM proposed to continue to require 

inspections to detect fatigue-related skin 

cracks and corrosion of the skin panel 

lap joints in the fuselage upper lobe, 

and repair if necessary; modification of 

certain lap joints and inspection of 

modified lap joints; and repetitive 

detailed external visual inspections of 

the fuselage skin at the upper lobe skin 

lap joints for cracks and evidence of 

corrosion, and related investigative and 

corrective actions. That NPRM also 

proposed to reduce the maximum 

interval of the post-modification 

inspections, and adds post-repair 

inspection requirements for certain 

airplanes. 

Comments 

We provided the public the 

opportunity to participate in the 

development of this AD. We have 

considered the comment that has been 

received on the NPRM. 

Request to Correct Typographical Error 

in Paragraph (l) of the NPRM 

Boeing requests that we revise 

paragraph (l) of the NPRM to change the 

numeral ‘‘1’’ to the letter ‘‘l’’ to correctly 

identify the paragraph references. 

We agree and have corrected the 

typographical error accordingly. 


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