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

TABLE 

### 1—A FFECTED 

### HMU S 

### — 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:


## 73497 Federal Register / Vol. 76, No. 229 / Tuesday, November 29, 2011 / Rules and Regulations

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


## 73498 Federal Register / Vol. 76, No. 229 / Tuesday, November 29, 2011 / Rules and Regulations

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—A CCEPTABLE 

### S ERVICE 

### I NFORMATION FOR 

### C ERTAIN 

### R EQUIREMENTS OF 

### P ARAGRAPH 

### ( H 

### ) OF 

### T HIS 

### 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


## 73499 Federal Register / Vol. 76, No. 229 / Tuesday, November 29, 2011 / Rules and Regulations

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, datedJanuary 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


## 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—C REDIT 

### S ERVICE 

### I NFORMATION FOR 

### C ERTAIN 

### A CTIONS

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—R ELATED 

### S ERVICE 

### I NFORMATION

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.


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

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: