73496 Federal Register / Vol. 76, No. 229 / Tuesday, November 29, 2011 / Rules and Regulations 

TABLE 1—AFFECTED HMUS— 

Continued 

P/Ns S/Ns 

0292860750 830B 

0292860750 861B 

0292860750 944B 

0292860750 967B 

0292861020 632B 

Reason 

(d) 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: 

Non-conformities on adjustment of some 

hydromechanical units (HMUs) have been 

reported by a Turbomeca repair centre. The 

technical investigations carried out by 

Turbomeca are showing that only a limited 

number of HMUs are potentially affected by 

this non-conformity to HMU adjustment. 

Twenty nine HMUs have been identified 

with potential non-conformities in the proper 

adjustment of the metering valve. The exact 

location of these 29 HMUs is unknown. We 

are issuing this AD to prevent an 

uncommanded inflight shutdown, which 

could result in an emergency autorotation 

landing. 

Actions and Compliance 

(e) Unless already done, do the following 

actions. 

(f) Before further flight, perform a one-time 

functional test of the engine to confirm 

proper engine operation. This one-time 

functional test is not a normal engine run-up 

test. Use the instructions in paragraph 

2.B.(1)(a) of Turbomeca Alert Mandatory 

Service Bulletin No. A292 73 2841, Version 

A, dated July 4, 2011, to perform the 

functional test. 

(1) If the engine fails the functional test, 

replace the HMU with an HMU eligible for 

installation. 

(2) If the engine passes the functional test, 

do the following: 

(i) Within four months after the effective 

date of this AD, install software modification 

TU143 on the Engine Electronic Control Unit 

of the engine. Use paragraph 2.B. of 

Turbomeca Service Bulletin No. 292 73 2143, 

dated July 24, 2007 to do the installation; and 

(ii) Within 12 months after the effective 

date of this AD, replace the HMU with an 

HMU eligible for installation. 

Definition 

(g) For the purpose of this AD, an HMU 

eligible for installation is defined as one with 

a serial number not listed in Table 1 of this 

AD, or, an HMU that passed when tested 

using Turbomeca Service Bulletin No. 292 73 

2840. 

FAA AD Differences 

(h) None. 

Alternative Methods of Compliance 

(AMOCs) 

(i) The Manager, Engine Certification 

Office, FAA, may approve AMOCs for this 

AD. Use the procedures found in 14 CFR 

39.19 to make your request. 

Related Information 

(j) Refer to MCAI Airworthiness Directive 

2011–0128–E, dated July 6, 2011, for related 

information. 

(k) Contact Mark Riley, Aerospace 

Engineer, Engine Certification Office, FAA, 

Engine & Propeller Directorate, 12 New 

England Executive Park, Burlington, MA 

01803; phone: (781) 238–7758; fax: (781) 

238–7199, email: mark.riley@faa.gov; for 

more information about this AD. 

Material Incorporated by Reference 

(l) You must use the following service 

information to do the actions required by this 

AD, unless the AD specifies otherwise. The 

Director of the Federal Register approved the 

incorporation by reference (IBR) under 5 

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

following service information on the date 

specified: 

(1) Turbomeca Alert Mandatory Service 

Bulletin No. A292 73 2841, Version A, dated 

July 4, 2011, approved for IBR December 14, 

2011. 

(2) Turbomeca Service Bulletin No. 292 73 

2143, dated July 24, 2007, approved for IBR 

December 14, 2011. 

(3) For service information identified in 

this AD, contact Turbomeca S.A., 40220 

Tarnos, France; phone: 33–05–59–74–40–00, 

fax: 33–05–59–74–45–15. 

(4) You may review copies of the service 

information at the FAA, New England 

Region, 12 New England Executive Park, 

Burlington, MA. For information on the 

availability of this material at the FAA, call 

(781) 238–7125. 

(5) 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 an NARA facility, call (202) 741– 

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

federal-register/cfr/ibr-locations.html. 

Issued in Burlington, Massachusetts on 

November 14, 2011. 

Peter A. White, 

Manager, Engine and Propeller Directorate, 

Aircraft Certification Service. 

[FR Doc. 2011–30574 Filed 11–28–11; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2011–0717; Directorate 

Identifier 2010–NM–108–AD; Amendment 

39–16869; AD 2011–24–05] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are superseding an 

existing airworthiness directive (AD) 

that applies to certain Airbus Model 

A330–201, –202, –203, –223, –243, 

–301, –302, –303, –321, –322, –323, 

–341, –342, and –343 airplanes; and 

Model A340–200 and –300 series 

airplanes. 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: 

During A330 and A340 aeroplanes fatigue 

tests, cracks appeared on the right (RH) and 

left (LH) sides between the crossing area of 

the keel beam fitting and the front spar of the 

Centre Wing Box (CWB). This condition, if 

not corrected, could lead to keel beam 

rupture which would affect the area 

structural integrity. 

* * * * * 

We are issuing this AD to require 

actions to correct the unsafe condition 

on these products. 

DATES: This AD becomes effective 

January 3, 2012. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of January 3, 2012. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain other publications listed in 

this AD as of September 13, 2007 (72 FR 

44731, August 9, 2007). 

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: 

Vladimir Ulyanov, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue SW., Renton, 

Washington 98057–3356; telephone 

(425) 227–1138; 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 19, 2011 (76 FR 42602), 

and proposed to supersede AD 2007– 

16–02, Amendment 39–15141 (72 FR 

44731, August 9, 2007). That NPRM 

proposed to correct an unsafe condition 

for the specified products. The MCAI 

states: 


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During A330 and A340 aeroplanes fatigue 

tests, cracks appeared on the right (RH) and 

left (LH) sides between the crossing area of 

the keel beam fitting and the front spar of the 

Centre Wing Box (CWB). This condition, if 

not corrected, could lead to keel beam 

rupture which would affect the area 

structural integrity. 

In order to maintain the structural integrity 

of the aeroplane, EASA AD 2006–0315R1 

required repetitive special detailed 

inspections on the horizontal flange of the 

keel beam in the area of first fastener hole aft 

of FR40. 

This [EASA] AD, which supersedes EASA 

AD 2006–0315R1: 

—Retains the inspection requirements of 

EASA AD 2006–0315R1, 

—Extends the AD applicability to aeroplanes 

which have embodied Airbus modification 

49202, and 

—Modifies the inspection thresholds and 

intervals. 

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 single comment 

received. 

Request To Update Service Information 

Airbus requested that we incorporate 

the latest revisions of the primary 

service bulletins, Airbus Mandatory 

Service Bulletins A330–57–3081 and 

A340–57–4089, both including 

Appendix 01, both Revision 04, both 

dated May 31, 2011, and give credit for 

actions performed according to the 

revisions of these service bulletins 

specified in the NPRM (76 FR 42602, 

July 19, 2011). 

We agree to specify Revision 04, dated 

May 31, 2011, of Airbus Mandatory 

Service Bulletins A330–57–3081 and 

A340–57–4089, and have changed 

paragraphs (h), (j)(1), (j)(3), (n), (n)(1)(i), 

(n)(1)(ii)(B), (n)(2)(ii), (p)(1), and (p)(2); 

tables 1 and 3; and Notes 3 and 4; of this 

AD accordingly. Revision 04 of those 

service bulletins states that no 

additional work is required for airplanes 

modified by any previous issue of those 

service bulletins. We have also added 

Revision 03, dated July 31, 2009, of 

those service bulletins to table 2 of this 

AD, ‘‘Credit Service Information for 

Certain Actions.’’ 

Conclusion 

We 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 determined that these changes 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 

Based on the service information, we 

estimate that this AD will affect about 

35 products of U.S. registry. 

For the 9 airplanes affected by the 

existing AD, the actions that are 

required by AD 2007–16–02, 

Amendment 39–15141 (72 FR 44731, 

August 9, 2007), and retained in this AD 

take about 41 work-hours per product, 

at an average labor rate of $85 per work 

hour. Required parts cost about $191 per 

product. Based on these figures, the 

estimated cost of the currently required 

actions is $3,676 per product. 

For the 26 additional airplanes added 

in this AD, we estimate the actions in 

this AD will take about 41 work-hours 

per product, at an average labor rate of 

$85 per work hour. Required parts will 

cost about $191 per product. Based on 

these figures, the estimated cost of the 

proposed AD is $3,676 per product. 

In addition, because this AD advises 

to contact the manufacturer for repair 

instructions, we cannot estimate the 

parts or labor costs for any necessary 

follow-on actions. We have no way of 

determining the number of products 

that may need these actions. 

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 (76 FR 42602, July 

19, 2011), 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 

removing Amendment 39–15141 (72 FR 


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44731, August 9, 2007) and adding the 

following new AD: 

2011–24–05 Airbus: Amendment 39– 

16869. Docket No. FAA–2011–0717; 

Directorate Identifier 2010–NM–108–AD. 

Effective Date 

(a) This airworthiness directive (AD) 

becomes effective January 3, 2012. 

Affected ADs 

(b) This AD supersedes AD 2007–16–02, 

Amendment 39–15141 (72 FR 44731, August 

9, 2007). 

Applicability 

(c) This AD applies to the airplanes 

identified in paragraphs (c)(1) and (c)(2) of 

this AD; certificated in any category; except 

as provided by paragraph (c)(3) of this AD. 

(1) Airbus Model A330–201, –202, –203, 

–223, –243, –301, –302, –303, –321, –322, 

–323, –341, –342, and –343 airplanes, all 

serial numbers, except those on which 

Airbus modification 55306 or 55792 has been 

embodied in production. 

(2) Airbus Model A340–211, –212, –213, 

–311, –312, and –313 airplanes, all serial 

numbers, except those on which Airbus 

modification 55306 or 55792 has been 

embodied in production. 

(3) This AD is not applicable to Airbus 

Model A340–211, –212, –213, –311, –312, 

and –313 airplanes on which the repair 

specified in Airbus Repair Drawing 

R57115053, R57115051, or R57115047 

(installation of titanium doubler on both 

sides) has been accomplished. AD 2007–12– 

08, Amendment 39–15086 (72 FR 31171, 

June 6, 2007), applies to these airplanes. 

Subject 

(d) Air Transport Association (ATA) of 

America Code 57: Wings. 

Reason 

(e) The mandatory continuing 

airworthiness information (MCAI) states: 

During A330 and A340 aeroplanes fatigue 

tests, cracks appeared on the right (RH) and 

left (LH) sides between the crossing area of 

the keel beam fitting and the front spar of the 

Centre Wing Box (CWB). This condition, if 

not corrected, could lead to keel beam 

rupture which would affect the area 

structural integrity. 

* * * * * 

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. 

Restatement of Requirements of AD 2007– 

16–02, Amendment 39–15141 (72 FR 44731, 

August 9, 2007) With Revised Service 

Information 

(g) For Model A330–201, –202, –203, –223, 

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

and –343 airplanes, except those on which 

Airbus modification 49202 has been 

embodied in production, or Airbus Service 

Bulletin A330–57–3090 has been embodied 

in service, and Model A340–200 and –300 

series airplanes, except those on which 

Airbus modification 49202 has been 

embodied in production or Airbus Service 

Bulletin A340–57–4098 has been embodied 

in service, and except Model A340–211, 

–212, –213, –311, –312, and –313 airplanes 

on which the repair specified in Airbus 

Repair Drawing R57115053, R57115051, or 

R57115047 has been accomplished: Do the 

actions required by paragraphs (h), (l), and 

(m) of this AD. 

(h) For airplanes identified in paragraph (g) 

of this AD, within the mandatory threshold 

(flight cycles or flight hours) mentioned in 

the paragraph 1.E.(2) of Airbus Service 

Bulletin A340–57–4089, including Appendix 

01, Revision 02; or A330–57–3081, including 

Appendix 01, Revision 02; both dated 

January 24, 2006; depending on the 

configuration of the aircraft model; or within 

3 months after September 13, 2007 (the 

effective date of AD 2007–16–02 (72 FR 

44731, August 9, 2007)); whichever occurs 

later: Carry out the NDT (non-destructive 

test) inspection of the hole(s) of the 

horizontal flange of the keel beam located on 

FR 40 datum on RH (right-hand) and/or LH 

(left-hand) side of the fuselage, in accordance 

with the instructions of the applicable 

service bulletin listed in table 1 of this AD. 

After the effective date of this AD, use only 

Airbus Mandatory Service Bulletin A330–57– 

3081, including Appendix 01, Revision 04, 

dated May 31, 2011; or Airbus Mandatory 

Service Bulletin A340–57–4089, including 

Appendix 01, Revision 04, dated May 31, 

2011; as applicable. Inspection in accordance 

with Airbus A330/A340 200–300 Technical 

Disposition F57D03012810, Issue B, dated 

August 18, 2003; or Airbus A330/A340 

Technical Disposition 582.0651/2002, Issue 

A, dated October 17, 2002; satisfies the 

inspection requirements for the first rotating 

probe inspection which is specified at the 

inspection threshold of this AD. Doing the 

inspection required by paragraph (n) of this 

AD terminates the requirements of this 

paragraph of this AD. 

Note 1: In order to prevent large repairs or 

heavy maintenance, Airbus recommends to 

perform the above inspection according to 

recommended thresholds mentioned in 

paragraph 1.E.(2) of Airbus Service Bulletin 

A340–57–4089, including Appendix 01, 

Revision 02; or Airbus Service Bulletin 

A330–57–3081, including Appendix 01, 

Revision 02; both dated January 24, 2006. 

TABLE 1—ACCEPTABLE SERVICE INFORMATION FOR CERTAIN REQUIREMENTS OF PARAGRAPH (H) OF THIS AD 

Document Revision Date 

Airbus Service Bulletin A330–57–3081, including Appendix 01 ................................................................. 02 January 24, 2006. 

Airbus Mandatory Service Bulletin A330–57–3081, including Appendix 01 ............................................... 04 May 31, 2011. 

Airbus Service Bulletin A340–57–4089, including Appendix 01 ................................................................. 02 January 24, 2006. 

Airbus Mandatory Service Bulletin A340–57–4089, including Appendix 01 ............................................... 04 May 31, 2011. 

(i) In case of any crack finding during the 

inspection required by paragraph (h) of this 

AD, before further flight, contact Airbus in 

order to get repair instructions before next 

flight, and repair before further flight. 

(j) Should no crack be detected during the 

inspection required by paragraph (h) of this 

AD: 

(1) Before further flight: Follow up the 

actions indicated in the flow charts, Figure 

7, 8, or 9, of Airbus Service Bulletin A340– 

57–4089, including Appendix 01, Revision 

02, dated January 24, 2006, or Airbus 

Mandatory Service Bulletin A340–57–4089, 

including Appendix 01, Revision 04, dated 

May 31, 2011; or Figure 5, 6, or 7, of Airbus 

Service Bulletin A330–57–3081, including 

Appendix 01, Revision 02, dated January 24, 

2006, or Airbus Mandatory Service Bulletin 

A330–57–3081, including Appendix 01, 

Revision 04, dated May 31, 2011; in 

accordance with the instructions of Airbus 

Service Bulletin A340–57–4089, including 

Appendix 01, Revision 02, dated January 24, 

2006, or Airbus Mandatory Service Bulletin 

A340–57–4089, including Appendix 01, 

Revision 04, dated May 31, 2011; or Airbus 

Service Bulletin A330–57–3081, including 

Appendix 01, Revision 02, dated January 24, 

2006, or Airbus Mandatory Service Bulletin 

A330–57–3081, including Appendix 01, 

Revision 04, dated May 31, 2011; as 

applicable. 

(2) Within 30 days after September 13, 

2007, or within 30 days after doing the 

inspection required by paragraph (h) of this 

AD, whichever occurs later: Send the report 

of actions carried out in paragraph (j)(1) of 

this AD to Airbus. 

(3) Renew the inspection at mandatory 

intervals given in paragraph 1.E.(2) of Airbus 

Service Bulletin A340–57–4089, including 

Appendix 01, Revision 02, dated January 24, 

2006; or Airbus Service Bulletin A330–57– 

3081, including Appendix 01, Revision 02, 

dated January 24, 2006; as applicable; in 

accordance with the instructions of Airbus 

Service Bulletin A340–57–4089, including 

Appendix 01, Revision 02, dated January 24, 

2006, or Airbus Mandatory Service Bulletin 

A340–57–4089, including Appendix 01, 

Revision 04, dated May 31, 2011; or Airbus 

Service Bulletin A330–57–3081, including 

Appendix 01, Revision 02, dated January 24, 

2006, or Airbus Mandatory Service Bulletin 

A330–57–3081, including Appendix 01, 

Revision 04, dated May 31, 2011; as 

applicable; and send the inspection results to 

Airbus. Doing the inspection required by 


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paragraph (n) of this AD terminates the 

requirements of this paragraph of this AD. 

Note 2: In order to prevent large repairs or 

heavy maintenance, Airbus recommends to 

perform the above repetitive inspection 

according to recommended intervals 

mentioned in paragraph 1.E.(2) of Airbus 

Service Bulletin A340–57–4089, including 

Appendix 01, Revision 02, dated January 24, 

2006; or Airbus Service Bulletin A330–57– 

3081, including Appendix 01, Revision 02, 

dated January 24, 2006. 

(k) Upon detection of a crack during a 

repetitive inspection required by paragraph 

(j)(3) of this AD, before further flight, contact 

Airbus to get repair instructions, and repair 

before further flight. 

(l) For airplanes identified in paragraph (g) 

of this AD: No additional work is required for 

compliance with paragraph (h) of this AD for 

aircraft on which the inspection specified in 

Airbus Service Bulletin A330–57–3081, 

dated October 30, 2003, or Revision 01, dated 

May 18, 2004; or Airbus Service Bulletin 

A340–57–4089, dated October 30, 2003, or 

Revision 01, dated March 2, 2004, has been 

accomplished. Nevertheless, the operators 

must check that their inspection program is 

in accordance with paragraph 1.E.(2) of 

Airbus Service Bulletin A340–57–4089, 

including Appendix 01, Revision 02, dated 

January 24, 2006; or Airbus Service Bulletin 

A330–57–3081, including Appendix 01, 

Revision 02, dated January 24, 2006; as 

applicable; for the repetitive inspection. 

(m) For airplanes identified in paragraph 

(g) of this AD on which Airbus Modification 

41652 is not embodied: When the aircraft has 

been modified in accordance with Airbus 

Service Bulletin A330–57–3090, dated March 

27, 2006; or Airbus Service Bulletin A340– 

57–4098, dated March 27, 2006; as 

applicable; the repetitive inspections 

required by this AD are cancelled. In case of 

any crack finding during the modification: 

Where the applicable service bulletin 

specifies to contact Airbus, before further 

flight, contact Airbus to get repair 

instructions, and repair. 

New Requirements of This AD 

(n) At the applicable time in paragraph 

(n)(1) or (n)(2) of this AD: Do an NDT 

inspection of the hole(s) of the horizontal 

flange of the keel beam located on FR 40 

datum on RH and/or LH side of the fuselage, 

in accordance with the Accomplishment 

Instructions of Airbus Mandatory Service 

Bulletin A330–57–3081, including Appendix 

01, Revision 04, dated May 31, 2011; or 

Airbus Mandatory Service Bulletin A340–57– 

4089, including Appendix 01, Revision 04, 

dated May 31, 2011; as applicable. Inspection 

in accordance with Airbus A330/A340 200– 

300 Technical Disposition F57D03012810, 

Issue B, dated August 18, 2003; or Airbus 

A330/A340 Technical Disposition 582.0651/ 

2002, Issue A, dated October 17, 2002; is 

acceptable for compliance with the 

inspection requirements for the first rotating 

probe inspection required by this paragraph. 

Doing the inspection required by this 

paragraph terminates the requirements of 

paragraphs (h) and (j)(3) of this AD. 

(1) For airplanes on which an inspection 

required by paragraph (h) of this AD has not 

been done as of the effective date of this AD: 

At the applicable time specified in paragraph 

(n)(1)(i) or (n)(1)(ii) of this AD. 

(i) For all airplanes except those identified 

in paragraph (g) of this AD: Within the 

‘‘Mandatory Threshold’’ (flight cycles or 

flight hours) specified in table 1 of paragraph 

1.E.(2) of the Accomplishment Instructions of 

Airbus Mandatory Service Bulletin A330–57– 

3081, including Appendix 01, Revision 04, 

dated May 31, 2011; or Airbus Mandatory 

Service Bulletin A340–57–4089, including 

Appendix 01, Revision 04, dated May 31, 

2011; as applicable; or within 3 months after 

the effective date of this AD; whichever 

occurs later. The compliance times for 

configurations 02 through 06 specified in the 

‘‘Mandatory Threshold’’ column in table 1 of 

paragraph 1.E., ‘‘Compliance,’’ are total flight 

cycles and total flight hours. 

(ii) For airplanes identified in paragraph (g) 

of this AD: At the earlier of the times 

specified in paragraphs (n)(1)(ii)(A) and 

(n)(1)(ii)(B) of this AD. 

(A) Within the ‘‘Mandatory Threshold’’ 

(flight cycles or flight hours) specified in 

table 1 of paragraph 1.E.(2) of Airbus Service 

Bulletin A340–57–4089, including Appendix 

01, Revision 02, dated January 24, 2006; or 

Airbus Service Bulletin A330–57–3081, 

including Appendix 01, Revision 02, dated 

January 24, 2006; depending on the 

configuration of the aircraft model; or within 

3 months after September 13, 2007; 

whichever occurs later. The compliance 

times for Model A330 post-mod. No. 41652 

and pre-mod. No. 44360, post-mod. No. 

44360, and pre-mod. No. 49202 (specified in 

Airbus Service Bulletin A330–57–3081, 

including Appendix 01, Revision 02, dated 

January 24, 2006); and Model A340 postmod. No. 41652, post-mod. No. 43500 and 

pre-mod. No. 44360, post-mod. No. 44360 

and pre-mod. No. 49202, and Weight Variant 

027 (specified in Airbus Service Bulletin 

A340–57–4089, including Appendix 01, 

Revision 02, dated January 24, 2006); 

specified in the ‘‘Mandatory Threshold’’ 

column in table 1 of paragraph 1.E., 

‘‘Compliance,’’ are total flight cycles and 

total flight hours. 

(B) Within the ‘‘Mandatory Threshold’’ 

(flight cycles or flight hours) specified in 

table 1 of paragraph 1.E.(2) of the 

Accomplishment Instructions of Airbus 

Mandatory Service Bulletin A330–57–3081, 

including Appendix 01, Revision 04, dated 

May 31, 2011; or Airbus Mandatory Service 

Bulletin A340–57–4089, including Appendix 

01, Revision 04, dated May 31, 2011; as 

applicable; or within 3 months after the 

effective date of this AD; whichever occurs 

later. The compliance times for 

configurations 02 through 06 specified in the 

‘‘Mandatory Threshold’’ column in table 1 of 

paragraph 1.E., ‘‘Compliance,’’ are total flight 

cycles and total flight hours. 

(2) For airplanes on which an inspection 

required by paragraph (h) of this AD has been 

done as of the effective date of this AD: At 

the earlier of the times specified in 

paragraphs (n)(2)(i) and (n)(2)(ii) of this AD. 

(i) Within the ‘‘Mandatory Intervals’’ given 

in table 1 of paragraph 1.E.(2) of Airbus 

Service Bulletin A340–57–4089, including 

Appendix 01, Revision 02, dated January 24, 

2006; or Airbus Service Bulletin A330–57– 

3081, including Appendix 01, Revision 02, 

dated January 24, 2006; as applicable. 

(ii) Within the applicable ‘‘Mandatory 

Interval’’ specified in table 1 of Paragraph 

1.E.(2). of Airbus Mandatory Service Bulletin 

A330–57–3081, including Appendix 01, 

Revision 04, dated May 31, 2011; or Airbus 

Mandatory Service Bulletin A340–57–4089, 

including Appendix 01, Revision 04, dated 

May 31, 2011; as applicable; or within 3 

months after the effective date of this AD; 

whichever occurs later. 

Note 3: To prevent large repairs or heavy 

maintenance, Airbus recommends to perform 

the above inspection according to 

recommended thresholds specified in 

paragraph 1.E.(2) of Airbus Mandatory 

Service Bulletin A330–57–3081, including 

Appendix 01, Revision 04, dated May 31, 

2011; or Airbus Mandatory Service Bulletin 

A340–57–4089, including Appendix 01, 

Revision 04, dated May 31, 2011; as 

applicable. 

(o) If any cracking is found during any 

inspection required by paragraph (n) of this 

AD, before further flight, repair in accordance 

with a method approved by the International 

Branch, ANM–116, Transport Airplane 

Directorate, FAA, or European Aviation 

Safety Agency (EASA) (or its delegated 

agent). 

(p) If no cracking is found during any 

inspection required by paragraph (n) of this 

AD, do the actions required by paragraphs 

(p)(1) and (p)(2) of this AD. 

(1) Before further flight: Install new or 

oversized fastener, as applicable; seal the 

fastener; and do all other applicable actions; 

in accordance with the Accomplishment 

Instructions of Airbus Mandatory Service 

Bulletin A330–57–3081, including Appendix 

01, Revision 04, dated May 31, 2011; or 

Airbus Mandatory Service Bulletin A340–57– 

4089, including Appendix 01, Revision 04, 

dated May 31, 2011; as applicable. 

(2) Repeat the inspection required by 

paragraph (n) of this AD thereafter at 

intervals not to exceed the mandatory 

intervals specified in Paragraph 1.E.(2). of 

Airbus Mandatory Service Bulletin A330–57– 

3081, including Appendix 01, Revision 04, 

dated May 31, 2011; or Airbus Mandatory 

Service Bulletin A340–57–4089, including 

Appendix 01, Revision 04, dated May 31, 

2011; as applicable. 

Note 4: To prevent large repairs or heavy 

maintenance, Airbus recommends to perform 

the above repetitive inspection according to 

recommended intervals mentioned in 

paragraph 1.E.(2) of Airbus Mandatory 

Service Bulletin A330–57–3081, including 

Appendix 01, Revision 04, dated May 31, 

2011; or Airbus Mandatory Service Bulletin 

A340–57–4089, including Appendix 01, 

Revision 04, dated May 31, 2011; as 

applicable. 

Credit for Actions Accomplished in 

Accordance With Previous Service 

Information 

(q) Inspections done before the effective 

date of this AD in accordance with the 

service information specified in table 2 of 

this AD are acceptable for compliance with 


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73500 Federal Register / Vol. 76, No. 229 / Tuesday, November 29, 2011 / Rules and Regulations 

the corresponding inspection required by 

paragraph (n) of this AD. 

TABLE 2—CREDIT SERVICE INFORMATION FOR CERTAIN ACTIONS

Document Revision Date 

Airbus Service Bulletin A330–57–3081, including Appendix 01 ................................................................. 02 January 24, 2006. 

Airbus Mandatory Service Bulletin A330–57–3081 ..................................................................................... 03 July 31, 2009. 

Airbus Service Bulletin A340–57–4089, including Appendix 01 ................................................................. 02 January 24, 2006. 

Airbus Mandatory Service Bulletin A340–57–4089 ..................................................................................... 03 July 31, 2009. 

Airbus Service Bulletin A330–57–3081 ....................................................................................................... ........................ October 30, 2003. 

Airbus Service Bulletin A330–57–3081 ....................................................................................................... 01 May 18, 2004. 

Airbus Service Bulletin A340–57–4089 ....................................................................................................... ........................ October 30, 2003. 

Airbus Service Bulletin A340–57–4089 ....................................................................................................... 01 March 2, 2004. 

(r) Modifying the fasteners installation in 

the junction keel beam fitting at FR 40, in 

accordance with Airbus Service Bulletin 

A330–57–3098, dated August 30, 2007; or 

Airbus Service Bulletin A340–57–4106, 

dated August 30, 2007; as applicable; before 

the effective date of this AD terminates the 

requirements of this AD; except for airplanes 

on which a crack was detected at hole 5 

before oversizing of the keel beam (in 

accordance with step 3.B.(1)(b)3 of the 

Accomplishment Instructions of Airbus 

Service Bulletin A330–57–3098, dated 

August 30, 2007; or Airbus Service Bulletin 

A340–57–4106, dated August 30, 2007), 

before further flight, repair in accordance 

with a method approved by the International 

Branch, ANM–116, Transport Airplane 

Directorate, FAA, or EASA (or its delegated 

agent). 

(s) Modifying the fasteners installation in 

the junction keel beam fitting at FR 40, in 

accordance with Airbus Service Bulletin 

A330–57–3098, excluding Appendix 1, 

Revision 01, dated July 31, 2009; or Airbus 

Service Bulletin A340–57–4106, excluding 

Appendix 1, Revision 01, dated July 31, 

2009; as applicable; terminates the 

requirements of this AD. 

(t) Modifying the fasteners installation in 

the junction keel beam fitting at FR 40, in 

accordance with Airbus Service Bulletin 

A330–57–3090, dated March 27, 2006; or 

Airbus Service Bulletin A340–57–4098, 

dated March 27, 2006; as applicable; 

terminates the requirements of this AD. 

(u) In case of any crack finding during any 

modification specified paragraphs (r), (s), and 

(t) of this AD: Where the applicable service 

bulletin specifies to contact Airbus, before 

further flight, repair in accordance with a 

method approved by the International 

Branch, FAA, or EASA (or its delegated 

agent). 

FAA AD Differences 

Note 5: This AD differs from the MCAI 

and/or service information as follows: No 

differences. 

Other FAA AD Provisions 

(v) The following provisions also apply to 

this AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Branch, FAA, has the authority to approve 

AMOCs for this AD, if requested using the 

procedures found in 14 CFR 39.19. In 

accordance with 14 CFR 39.19, send your 

request to your principal inspector or local 

Flight Standards District Office, as 

appropriate. If sending information directly 

to the International Branch, send it to ATTN: 

Vladimir Ulyanov, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, Washington 98057– 

3356; telephone (425) 227–1138; fax (425) 

227–1149. Information may be emailed to: 

9-ANM-116-AMOC-REQUESTS@faa.gov. 

Before using any approved AMOC, notify 

your appropriate principal inspector, or 

lacking a principal inspector, the manager of 

the local flight standards district office/ 

certificate holding 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 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: A federal 

agency may not conduct or sponsor, and a 

person is not required to respond to, nor 

shall a person be subject to a penalty for 

failure to comply with a collection of 

information subject to the requirements of 

the Paperwork Reduction Act unless that 

collection of information displays a current 

valid OMB Control Number. The OMB 

Control Number for this information 

collection is 2120–0056. Public reporting for 

this collection of information is estimated to 

be approximately 5 minutes per response, 

including the time for reviewing instructions, 

completing and reviewing the collection of 

information. All responses to this collection 

of information are mandatory. Comments 

concerning the accuracy of this burden and 

suggestions for reducing the burden should 

be directed to the FAA at: 800 Independence 

Ave. SW., Washington, DC 20591, Attn: 

Information Collection Clearance Officer, 

AES–200. 

Related Information 

(w) Refer to MCAI European Aviation 

Safety Agency Airworthiness Directive 2010– 

0024, dated February 12, 2010, and the 

applicable service information specified in 

table 3 of this AD, for related information. 

TABLE 3—RELATED SERVICE INFORMATION

Document Revision Date 

Airbus Service Bulletin A330–57–3081, including Appendix 01 ................................................................. 02 January 24, 2006. 

Airbus Mandatory Service Bulletin A330–57–3081, including Appendix 01 ............................................... 04 May 31, 2011. 

Airbus Service Bulletin A340–57–4089, including Appendix 01 ................................................................. 02 January 24, 2006. 

Airbus Mandatory Service Bulletin A340–57–4089, including Appendix 01 ............................................... 04 May 31, 2011. 

Airbus Service Bulletin A330–57–3090 ....................................................................................................... ........................ March 27, 2006. 

Airbus Service Bulletin A330–57–3098, excluding Appendix 1 .................................................................. 01 July 31, 2009. 

Airbus Service Bulletin A340–57–4106, excluding Appendix 1 .................................................................. 01 July 31, 2009. 

Airbus Service Bulletin A340–57–4098 ....................................................................................................... ........................ March 27, 2006. 

Airbus A330/A340 200–300 Technical Disposition F57D03012810 ........................................................... Issue B August 18, 2003. 

Airbus A330/A340 Technical Disposition 582.0651/2002 ........................................................................... Issue A October 17, 2002. 


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Federal Register / Vol. 76, No. 229 / Tuesday, November 29, 2011 / Rules and Regulations 73501 

Material Incorporated by Reference 

(x) You must use the following service 

information specified in paragraphs (x)(1), 

(x)(2), (x)(7), (x)(8), (x)(9), and (x)(10) of this 

AD, as applicable, to do the actions required 

by this AD, unless the AD specifies 

otherwise. If you accomplish the optional 

actions specified by this AD, you must use 

the service information specified in 

paragraphs (x)(3), (x)(4), (x)(5), (x)(6), (x)(9), 

and (x)(10) of this AD, as applicable, to 

perform those actions, unless the AD 

specifies otherwise. The Director of the 

Federal Register approved the incorporation 

by reference (IBR) under 5 U.S.C. 552(a) and 

1 CFR part 51 of the following service 

information on the date specified: 

(1) Airbus Mandatory Service Bulletin 

A330–57–3081, including Appendix 01, 

Revision 04, dated May 31, 2011, approved 

for IBR January 3, 2012. 

(2) Airbus Mandatory Service Bulletin 

A340–57–4089, including Appendix 01, 

Revision 04, dated May 31, 2011, approved 

for IBR January 3, 2012. 

(3) Airbus Service Bulletin A330–57–3098, 

excluding Appendix 1, Revision 01, dated 

July 31, 2009, approved for IBR January 3, 

2012. 

(4) Airbus Service Bulletin A340–57–4106, 

excluding Appendix 1, Revision 01, dated 

July 31, 2009, approved for IBR January 3, 

2012. 

(5) Airbus A330/A340 200–300 Technical 

Disposition F57D03012810, Issue B, dated 

August 18, 2003, approved for IBR January 3, 

2012. 

(6) Airbus A330/A340 Technical 

Disposition 582.0651/2002, Issue A, dated 

October 17, 2002, approved for IBR January 

3, 2012. 

(7) Airbus Service Bulletin A330–57–3081, 

including Appendix 01, Revision 02, dated 

January 24, 2006, approved for IBR 

September 13, 2007 (72 FR 44731, August 9, 

2007). 

(8) Airbus Service Bulletin A340–57–4089, 

including Appendix 01, Revision 02, dated 

January 24, 2006, approved for IBR 

September 13, 2007 (72 FR 44731, August 9, 

2007). 

(9) Airbus Service Bulletin A330–57–3090, 

March 27, 2006, approved for IBR September 

13, 2007 (72 FR 44731, August 9, 2007). 

(10) Airbus Service Bulletin A340–57– 

4098, March 27, 2006, approved for IBR 

September 13, 2007 (72 FR 44731, August 9, 

2007). 

(11) For service information identified in 

this AD, contact Airbus SAS—Airworthiness 

Office—EAL, 1 Rond Point Maurice Bellonte, 

31707 Blagnac Cedex, France; telephone +33 

5 61 93 36 96; fax +33 5 61 93 45 80; email 

airworthiness.A330–A340@airbus.com; 

Internet http://www.airbus.com. 

(12) 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. 

(13) 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 an NARA facility, 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 

November 7, 2011. 

Kalene C. Yanamura, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2011–29803 Filed 11–28–11; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 71 

[Docket No. FAA–2011–0845; Airspace 

Docket No. 11–ACE–19] 

Amendment of Class E Airspace; 

Carroll, IA 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: This action amends Class E 

airspace for Carroll, IA. 

Decommissioning of the Carroll nondirectional beacon (NDB) at Arthur N. 

Neu Airport, Carroll, IA, has made this 

action necessary to enhance the safety 

and management of Instrument Flight 

Rule (IFR) operations at the airport. 

DATES: Effective date: 0901 UTC, 

February 9, 2012. The Director of the 

Federal Register approves this 

incorporation by reference action under 

1 CFR Part 51, subject to the annual 

revision of FAA Order 7400.9 and 

publication of conforming amendments. 

FOR FURTHER INFORMATION CONTACT: 

Scott Enander, Central Service Center, 

Operations Support Group, Federal 

Aviation Administration, Southwest 

Region, 2601 Meacham Blvd., Fort 

Worth, TX 76137; telephone (817) 321– 

7716. 

SUPPLEMENTARY INFORMATION: 

History 

On August 26, 2011, the FAA 

published in the Federal Register a 

notice of proposed rulemaking to amend 

Class E airspace for Carroll, IA, 

reconfiguring controlled airspace at 

Arthur N. Neu Airport (76 FR 53353) 

Docket No. FAA–2011–0845. Interested 

parties were invited to participate in 

this rulemaking effort by submitting 

written comments on the proposal to the 

FAA. No comments were received. Class 

E airspace designations are published in 

paragraph 6005 of FAA Order 7400.9V 

dated August 9, 2011, and effective 

September 15, 2011, which is 

incorporated by reference in 14 CFR 

71.1. The Class E airspace designations 

listed in this document will be 

published subsequently in the Order. 

The Rule 

This action amends Title 14 Code of 

Federal Regulations (14 CFR) part 71 by 

amending Class E airspace extending 

upward from 700 feet above the surface 

for the Carroll, IA area. 

Decommissioning of the Carroll NDB 

and cancellation of the NDB approach at 

Arthur N. Neu Airport has made 

reconfiguration of the airspace 

necessary for the safety and 

management of IFR operations at the 

airport. 

The FAA has determined that this 

regulation only involves an established 

body of technical regulations for which 

frequent and routine amendments are 

necessary to keep them operationally 

current. Therefore, this regulation: (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) 

does not warrant preparation of a 

regulatory evaluation as the anticipated 

impact is so minimal. Since this is a 

routine matter that will only affect air 

traffic procedures and air navigation, it 

is certified that this rule, when 

promulgated, will not have a significant 

economic impact on a substantial 

number of small entities under the 

criteria of the Regulatory Flexibility Act. 

The FAA’s authority to issue rules 

regarding aviation safety is found in 

Title 49 of the U.S. Code. Subtitle 1, 

section 106, describes the authority of 

the FAA Administrator. Subtitle VII, 

Aviation Programs, describes in more 

detail the scope of the agency’s 

authority. This rulemaking is 

promulgated under the authority 

described in subtitle VII, part A, subpart 

I, section 40103. Under that section, the 

FAA is charged with prescribing 

regulations to assign the use of airspace 

necessary to ensure the safety of aircraft 

and the efficient use of airspace. This 

regulation is within the scope of that 

authority as it amends controlled 

airspace at Arthur N. Neu Airport, 

Carroll, IA. 

List of Subjects in 14 CFR Part 71 

Airspace, Incorporation by reference, 

Navigation (air). 

Adoption of the Amendment 

In consideration of the foregoing, the 

Federal Aviation Administration 

amends 14 CFR part 71 as follows: 


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