## 68181 Federal Register / Vol. 75, No. 214 / Friday, November 5, 2010 / Rules and Regulations

the FAA amends 14 CFR part 39 as follows:

**PART 39—AIRWORTHINESS DIRECTIVES** 

■ 

### 1. The authority citation for part 39 continues to read as follows:

Authority: 49 U.S.C. 106(g), 40113, 44701.

**§ 39.13 [Amended]**

■ 

### 2. The FAA amends § 39.13 by adding the following new AD:
2010–23–09 Austro Engine GmbH: Amendment 39–16498; Docket No. FAA–2010–1055; Directorate Identifier
2010–NE–35–AD.

Effective Date

(a) This airworthiness directive (AD) becomes effective November 22, 2010.

Affected ADs

(b) None.
Applicability

(c) This AD applies to Austro Engine GmbH model E4 diesel piston engines. These engines are installed on, but not limited to, Diamond Aircraft Industries DA 40 NG and DA 42 NG airplanes. Reason (d) Several power loss events have been reported, due to rail pressure control failures. Analyses have shown that high pressure (HP) fuel pumps failed as a result of pressure oscillations in the fuel supply line. We are issuing this AD to prevent engine power loss or in-flight shutdown, which could result in loss of control of the airplane.
Actions and Compliance

(e) Unless already done, do the following actions.

(1) Inspect the fuel pressure supply for excessive oscillations using the inspection schedule in Table 1 of this AD.



### T ABLE 

### 1—I NSPECTION 

### S CHEDULE

Accumulated time-since-new: Compliance time:

45 flight hours or more, on the effective date of this AD. ........................ Within 10 flight hours after the effective date of this AD. Fewer than 45 flight hours, on the effective date of this AD. .................. At the next scheduled 50 flight hour inspection. Repetitive inspections. .............................................................................. At each 50 flight-hour scheduled inspection.

(2) Replace the high-pressure fuel pumpbefore further flight with a serviceable highpressure fuel pump if the oscillations exceed 300mV (750hPa).

(3) Use Austro Engine GmbH Work Instruction No. WI–MSB–E4–009, dated October 7, 2010, to do the inspections.

FAA AD Differences

(f) None.
Alternative Methods of Compliance (AMOCs)

(g) The Manager, Engine Certification Office, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19.

Related Information

(h) Refer to MCAI European Aviation Safety Agency Airworthiness Directive 2010– 0206–E, dated October 8, 2010, and Austro Engine GmbH Mandatory Service Bulletin No. MSB–E4–009, dated October 7, 2010, for related information. Contact Austro Engine GmbH, Rudolf-Diesel-Strasse 11, A–2700 Weiner Neustadt, Austria, telephone: +43 2622 23000; fax: +43 2622 23000–2711, or go
to: http://www.austroengine.at, for a copy of this service bulletin.

(i) Contact James Lawrence, Aerospace Engineer, Engine Certification Office, FAA, Engine & Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803; e-mail: james.lawrence@faa.gov; telephone (781) 238–7176; fax (781) 238– 7199, for more information about this AD.
Material Incorporated by Reference

(j) You must use Austro Engine GmbH Work Instruction No. WI–MSB–E4–009, dated October 7, 2010, to do the inspections required by this AD.

(1) The Director of the Federal Register approved the incorporation by reference of this service information under 5 U.S.C. 552(a) and 1 CFR part 51.

(2) For service information identified in this AD, contact Austro Engine GmbH, Rudolf-Diesel-Strasse 11, A–2700 Weiner Neustadt, Austria, telephone: +43 2622 23000; fax: +43 2622 23000–2711, or go to: http://www.austroengine.at.

(3) You may review copies at the FAA, New England Region, 12 New England Executive Park, Burlington, MA; or at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call (202) 741–6030, or go to: http://www.archives.gov/federal-register/cfr/ibrlocations.html.

Issued in Burlington, Massachusetts, on October 27, 2010. Karen M. Grant, Acting Assistant Manager, Engine and Propeller Directorate, Aircraft Certification Service.
[FR Doc. 2010–27609 Filed 11–4–10; 8:45 am]

**BILLING CODE 4910–13–P**



### DEPARTMENT OF TRANSPORTATION

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2010–0279; Directorate Identifier 2009–NM–148–AD; Amendment**  **39–16496; AD 2010–23–07]**

**RIN 2120–AA64**



### Airworthiness Directives; Airbus Model **A318, A319, A320, and A321 Series Airplanes** 

**AGENCY** 

### : Federal Aviation Administration (FAA), Department of Transportation (DOT).

**ACTION** 

### : Final rule.

**SUMMARY** 

### : We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) originated by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as:

Surface defects were visually detected onthe rudder of one A319 and one A321 inservice aeroplane.

Investigation has determined that the defects reported on both rudders corresponded to areas that had been reworked in production. The investigation confirmed that the defects were a result of de-bonding between the skin and honeycomb

core.

An extended de-bonding, if not detected and corrected, may degrade the structural integrity of the rudder. The loss of the rudder leads to degradation of the handling qualities and reduces the controllability of the aeroplane.



### * * * * * We are issuing this AD to require actions to correct the unsafe condition on these products.

**DATES** 

### : This AD becomes effective December 10, 2010.

The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of December 10, 2010.

**ADDRESSES** 

### : You may examine the AD docket on the Internet at http:// www.regulations.gov or in person at the U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue, SE., Washington, DC.

**FOR FURTHER INFORMATION CONTACT** 

### : Tim Dulin, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA,


## 68182 Federal Register / Vol. 75, No. 214 / Friday, November 5, 2010 / Rules and Regulations

1601 Lind Avenue, SW., Renton, Washington 98057–3356; telephone (425) 227–2141; 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 April 2, 2010 (75 FR 16689). That NPRM proposed to correct an unsafe condition for the specified products. The MCAI states:

Surface defects were visually detected onthe rudder of one A319 and one A321 inservice aeroplane.

Investigation has determined that the defects reported on both rudders corresponded to areas that had been reworked in production. The investigation confirmed that the defects were a result of de-bonding between the skin and honeycomb

core.

An extended de-bonding, if not detected and corrected, may degrade the structural integrity of the rudder. The loss of the rudder leads to degradation of the handling qualities and reduces the controllability of the aeroplane.

This AD requires inspections of specific areas and, when necessary, the application of corrective actions for those rudders where production reworks have been identified. 

### Inspections include vacuum loss inspections for de-bonding of the rudders in reinforced areas and other areas (splice/lower rib/upper edge/ leading edge/other specified locations),and elasticity laminate checks for debonding of the rudders in the trailing edge area and other areas (splice/lower rib/upper edge/leading edge/other specified locations). Corrective actions include contacting Airbus for further instruction and doing the repair.

You may obtain further information by examining the MCAI in the AD docket.

Comments

We gave the public the opportunity to participate in developing this AD. We considered the comment received. Request To Clarify Additional Work in Paragraph (k) of the Proposed AD

Airbus requested that we clarify in paragraph (k) of the proposed AD that there is additional work for operators to comply with, i.e., in Airbus All Operators Telex (AOT) A320–55A1038, Revision 02, dated September 28, 2009. Airbus explained that there is an additional ultrasonic inspection for rudders on which a temporary vacuum loss hole restoration with resin or a permanent vacuum loss hole restoration has been performed previously in the reinforced area.

We agree that additional work is included in Airbus AOT A320– 55A1038, Revision 02, dated September 28, 2009, which is referenced in the NPRM as the appropriate source of service information. However, the additional work specified in Airbus AOT A320–55A1038, Revision 02, dated September 28, 2009, is not required by this final rule. Therefore, we have revised paragraphs (g) and (h) of the final rule to allow operators to perform the required actions of this AD in accordance with Airbus AOT A320– 55A1038, Revision 01, dated June 10, 2009; or Revision 02, dated September 28, 2009. Also, we have revised paragraph (k) of this AD by removing reference to Airbus AOT A320– 55A1038, Revision 02, dated September 28, 2009, to clarify that only the additional areas specified in Airbus AOT A320–55A1038, Revision 01, dated June 10, 2009, must be inspected. We might consider further rulemaking to address the additional work specified in Airbus AOT A320–55A1038, Revision 02, dated September 28, 2009. Request To Include Alternative Contact Address for Positive Findings

Airbus requested that we include the Airbus Technical Aircraft on Ground (AOG) Center (AIRTAC) as a contact to report positive findings from the inspections in paragraphs (g) and (h) of the NPRM.

We agree to include the AIRTAC as a contact and have revised paragraph (j) of the final rule accordingly. Clarification of Paragraph (l) of This AD

We have clarified the statement

‘‘ unless the rudder is in compliance with this AD ’’ in paragraph (l) of this AD by specifying that applicable inspections in paragraphs (g) or (h) of this AD must be done and applicable actions in paragraph (i) of this AD must be done.

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

We estimate that this AD will affect 155 products of U.S. registry. We alsoestimate that it will take about 11 workhours per product to comply with the basic requirements of this AD. The average labor rate is $85 per work-hour. Based on these figures, we estimate the cost of this AD to the U.S. operators to be $144,925, or $935 per product. 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


## 68183 Federal Register / Vol. 75, No. 214 / Friday, November 5, 2010 / Rules and Regulations

3. Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act.

We prepared a regulatory evaluation of the estimated costs to comply with this AD and placed it in the AD docket. Examining the AD Docket

You may examine the AD docket on the Internet at http:// www.regulations.gov; or in person at the Docket Operations office between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains the NPRM, the regulatory evaluation, any comments received, and other information. The street address for the Docket Operations office (telephone (800) 647–5527) is in the **ADDRESSES** 

### section. Comments will be available in the AD docket shortly after receipt. List of Subjects in 14 CFR Part 39

Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. Adoption of the Amendment

■ 

### Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows:

**PART 39—AIRWORTHINESS DIRECTIVES** 

■ 

### 1. The authority citation for part 39 continues to read as follows:

Authority: 49 U.S.C. 106(g), 40113, 44701.

**§ 39.13 [Amended]**

■ 

### 2. The FAA amends § 39.13 by adding the following new AD:

2010–23–07 Airbus: Amendment 39–16496. Docket No. FAA–2010–0279; Directorate Identifier 2009–NM–148–AD.

Effective Date

(a) This airworthiness directive (AD) becomes effective December 10, 2010.

Affected ADs

(b) None.
Applicability

(c) This AD applies to Airbus Model A318– 111, –112, –121, and –122 airplanes; Model A319–111, –112, –113, –114, –115, –131, –132, and –133 airplanes; Model A320–111, –211, –212, –214, –231, –232, and –233 airplanes; and Model A321–111, –112, –131, –211, –212, –213, –231, and –232 airplanes; certificated in any category, all manufacturer serial numbers (S/Ns), if equipped with carbon fiber reinforced plastic rudders having part numbers (P/Ns) and S/Ns as listed in Table 1 of this AD. 

### TABLE 

### 1—R UDDER 

### P ART 

### N UMBER AND 

### A FFECTED 

### R UDDER 

### S ERIAL 

### N UMBER

Rudder P/N Affected rudder S/N

D554 71000 010 00 .................... TS–1069 D554 71000 010 00 .................... TS–1090 D554 71000 012 00 .................... TS–1227 D554 71000 014 00 .................... TS–1350 D554 71000 014 00 .................... TS–1366 D554 71000 014 00 .................... TS–1371 D554 71000 014 00 .................... TS–1383 D554 71000 014 00 .................... TS–1387 D554 71000 016 00 .................... TS–1412 D554 71000 018 00 .................... TS–1443 D554 71000 018 00 .................... TS–1444 D554 71000 018 00 .................... TS–1468 D554 71000 020 00 .................... TS–1480 D554 71000 020 00 .................... TS–1491 D554 71000 020 00 .................... TS–1495 D554 71000 020 00 .................... TS–1498 D554 71000 020 00 .................... TS–1499 D554 71000 020 00 .................... TS–1500 D554 71000 020 00 .................... TS–1505 D554 71000 020 00 .................... TS–1506 D554 71000 020 00 .................... TS–1507 D554 71000 020 00 .................... TS–1509 D554 71000 020 00 .................... TS–1515 D554 71000 020 00 .................... TS–1528 D554 71000 020 00 .................... TS–1530 D554 71000 020 00 .................... TS–1532 D554 71000 020 00 .................... TS–1535 D554 71000 020 00 .................... TS–1536 D554 71000 020 00 .................... TS–1538 D554 71000 000 00 .................... TS–1537 D554 71001 00 000 .................... TS–1540 D554 71001 000 00 .................... TS–1541 D554 71001 000 00 .................... TS–1543 D554 71001 000 00 .................... TS–1548 D554 71001 000 00 .................... TS–1549 D554 71001 000 00 .................... TS–1551 D554 71001 000 00 .................... TS–1554 D554 71001 000 00 .................... TS–1555 D554 71001 000 00 .................... TS–1556 D554 71001 000 00 .................... TS–1557 D554 71001 000 00 .................... TS–1559 D554 71001 000 00 .................... TS–1562 D554 71001 000 00 .................... TS–1563 D554 71001 000 00 .................... TS–1564 D554 71001 000 00 .................... TS–1565 D554 71001 000 00 .................... TS–1566 D554 71001 000 00 .................... TS–1567 D554 71001 000 00 .................... TS–1568 D554 71001 000 00 .................... TS–1569 D554 71001 000 00 .................... TS–1570 D554 71001 000 00 .................... TS–1573 D554 71001 000 00 .................... TS–1575 D554 71001 000 00 .................... TS–1578 D554 71001 000 00 .................... TS–1579 D554 71001 000 00 .................... TS–1580 D554 71001 000 00 .................... TS–1581 D554 71001 000 00 .................... TS–1582 D554 71001 000 00 .................... TS-1584 D554 71001 000 00 .................... TS–1593 D554 71001 000 00 .................... TS–1594 D554 71001 000 00 .................... TS–1596 D554 71001 000 00 .................... TS–1599 D554 71001 000 00 .................... TS–1603 D554 71001 000 00 .................... TS–1609 D554 71001 000 00 .................... TS–1621 D554 71001 000 00 .................... TS–1626 D554 71001 000 00 .................... TS–1627 D554 71001 000 00 .................... TS–1635 D554 71001 000 00 .................... TS–1637 D554 71002 000 00 .................... TS–2306 

### T ABLE 

### 1—R UDDER 

### P ART 

### N UMBER AND 

### A FFECTED 

### R UDDER 

### S ERIAL 

### N UM



### BER

### —Continued

Rudder P/N Affected rudder S/N

D554 71002 000 00 0001 .......... TS–2003 D554 71002 000 00 0001 .......... TS–2005 D554 71002 000 00 0001 .......... TS–2013 D554 71002 000 00 0001 .......... TS–2016 D554 71002 000 00 0001 .......... TS–2019 D554 71002 000 00 0001 .......... TS–2020 D554 71002 000 00 0001 .......... TS–2022 D554 71002 000 00 0001 .......... TS–2024 D554 71002 000 00 0001 .......... TS–2026 D554 71002 000 00 0001 .......... TS–2031 D554 71002 000 00 0001 .......... TS–2033 D554 71002 000 00 0001 .......... TS–2043 D554 71002 000 00 0001 .......... TS–2047 D554 71002 000 00 0001 .......... TS–2048 D554 71002 000 00 0001 .......... TS–2054 D554 71002 000 00 0001 .......... TS–2058 D554 71002 000 00 0001 .......... TS–2059 D554 71002 000 00 0001 .......... TS–2064 D554 71002 000 00 0001 .......... TS–Z072 D554 71002 000 00 0001 .......... TS–2075 D554 71002 000 00 0001 .......... TS–2076 D554 71002 000 00 0001 .......... TS–2079 D554 71002 000 00 0001 .......... TS–2083 D554 71002 000 00 0001 .......... TS–2089 D554 71002 000 00 0002 .......... TS–2090 D554 71002 000 00 0002 .......... TS–2095 D554 71002 000 00 0002 .......... TS–2103 D554 71002 000 00 0002 .......... TS–2116 D55471002 000 00 0002 ............ TS–2122 D554 71002 000 00 0002 .......... TS–2133 D554 71002 000 00 0002 .......... TS–2142 D554 71002 000 00 0002 .......... TS–2147 D554 71002 000 00 0002 .......... TS–2157 D554 71002 000 00 0002 .......... TS–2158 D554 71002 000 00 0002 .......... TS–2162 D554 71002 000 00 0002 .......... TS–2167 D554 71002 000 00 0002 .......... TS–2174 D554 71002 000 00 0002 .......... TS–2176 D554 71002 000 00 0002 .......... TS–2181 D554 71002 000 00 0002 .......... TS–2189 D554 71002 000 00 0002 .......... TS–2191 D554 71002 000 00 0002 .......... TS–2203 D554 71002 000 00 0002 .......... TS–2205 D554 71002 000 00 0002 .......... TS–2207 D554 71002 000 00 0002 .......... TS–2224 D554 71002 000 00 0002 .......... TS–2229 D554 71002 000 00 0002 .......... TS–2233 D554 71002 000 00 0002 .......... TS–2241 D554 71002 000 00 0002 .......... TS–2246 D554 71002 000 00 0002 .......... TS–2249 D554 71002 000 00 0002 .......... TS–2270 D554 71002 000 00 0002 .......... TS–2275 D554 71002 000 00 0002 .......... TS–2289 D554 71002 000 00 0002 .......... TS–2290 D554 71002 000 00 0002 .......... TS–2294 D554 71002 000 00 0002 .......... TS–2309 D554 71002 000 00 0002 .......... TS–2347 D554 71002 000 00 0002 .......... TS–2348 D554 71002 000 00 0002 .......... TS–2349 D554 71002 000 00 0002 .......... TS–2357 D554 71002 000 00 0002 .......... TS–2361 D554 71002 000 00 0002 .......... TS–2380 D554 71002 000 00 0002 .......... TS–2383 D554 71002 000 00 0002 .......... TS–2390 D554 71002 000 00 0002 .......... TS–2394 D554 71002 000 00 0002 .......... TS–2396 D554 71002 000 00 0002 .......... TS–2401 D554 71002 000 00 0002 .......... TS–2406 D554 71002 000 00 0002 .......... TS–2461


## 68184 Federal Register / Vol. 75, No. 214 / Friday, November 5, 2010 / Rules and Regulations

T ABLE 

### 1—R UDDER 

### P ART 

### N UMBER AND



### A FFECTED 

### R UDDER 

### S ERIAL 

### N UM



### BER

### —Continued

Rudder P/N Affected rudder S/N

D554 71002 000 00 0002 .......... TS–2468 D554 71002 000 00 0002 .......... TS–2516 D554 71002 000 00 0002 .......... TS–2537 D554 71002 000 00 0002 .......... TS–2543 D554 71002 000 00 0002 .......... TS–2546 D554 71002 000 00 0002 .......... TS–2619 D554 71002 000 00 0002 .......... TS–2684 D554 71002 000 00 0003 .......... TS–2752 D554 71002 000 00 0003 .......... TS–2869 D554 71002 000 00 0003 .......... TS–2876 D554 71002 000 00 0003 .......... TS–2970 D554 11002 000 00 0003 .......... TS–2971 D554 71002 000 00 0003 .......... TS–2987 D554 11004 000 00 0000 .......... TS–3083 D554 71004 000 00 0000 .......... TS–3197

Note 1: Only rudder P/N D554 71000 010 00 having affected rudder S/N TS–1069 and TS–1090 and rudder P/N D554 71000 012 00 having affected rudder S/N TS–1227, have a core density of 24 kilogram (kg)/meters cubed (m 3 ).

Subject

(d) Air Transport Association (ATA) of America Code 55: Stabilizers.

Reason

(e) The mandatory continuing airworthiness information (MCAI) states:

Surface defects were visually detected onthe rudder of one A319 and one A321 inservice aeroplane.

Investigation has determined that the defects reported on both rudders corresponded to areas that had been reworked in production. The investigation confirmed that the defects were a result of de-bonding between the skin and honeycomb

core.

An extended de-bonding, if not detected and corrected, may degrade the structural integrity of the rudder. The loss of the rudder leads to degradation of the handling qualities and reduces the controllability of the aeroplane.

This AD requires inspections of specific areas and, when necessary, the application of corrective actions for those rudders where production reworks have been identified. Inspections include vacuum loss inspections for de-bonding of the rudders in reinforced areas and other areas (splice/lower rib/upper edge/leading edge/other specified locations), and elasticity laminate checks for de-bonding of the rudders in the trailing edge area and other areas (splice/lower rib/upper edge/ leading edge/other specified locations). Corrective actions include contacting Airbus for further instruction and doing the repair.
Compliance

(f) You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done. Actions (g) For rudders with a honeycomb core density of 24 kg/m 3 (rudder P/N D554 71000 010 00 having affected rudder S/Ns TS–1069 and TS–1090 and rudder P/N D554 71000 012 00 having affected rudder S/N TS–1227), do the actions specified in paragraphs (g)(1), (g)(2), (g)(3), and (g)(4) of this AD, in accordance with Airbus All Operators Telex (AOT) A320–55A1038, Revision 01, dated June 10, 2009; or Airbus AOT A320– 55A1038, Revision 02, dated September 28, 2009; for the locations defined in the AOT.

(1) Within 200 days after the effective date of this AD, perform a vacuum loss inspection on the rudder reinforced area.

(2) Within 20 months after the effective date of this AD, perform an elasticity laminate checker inspection on the rudder trailing edge area. Repeat the inspection two times, at intervals not to exceed 4,500 flight cycles but not sooner than 4,000 flight cycles after the last inspection.

(3) Within 200 days after the effective date of this AD, perform an elasticity laminate checker inspection of the other areas (splice/ lower rib/upper edge/leading edge/other specified locations). Repeat the inspection at intervals not to exceed 1,500 flight cycles or 200 days, whichever comes first.

(4) Within 20 months after the effective date of this AD, perform a vacuum loss inspection of the other areas (splice/lower rib/upper edge/leading edge/other specified locations). Accomplishment of the action specified in paragraph (g)(4) of this AD terminates the requirements of paragraph (g)(3) of this AD.

(h) For rudders that do not have a honeycomb core density of 24 kg/m 3 (all rudders identified in Table 1 of this AD, except: Rudder P/N D554 71000 010 00 having affected rudder S/Ns TS–1069 and TS–1090 and rudder P/N D554 71000 012 00 having affected rudder S/N TS–1227), do the actions specified in paragraphs (h)(1), (h)(2), (h)(3), and (h)(4) of this AD, in accordance with Airbus AOT A320–55A1038, Revision 01, dated June 10, 2009; or Airbus AOT A320–55A1038, Revision 02, dated September 28, 2009; for the locations defined in the AOT. For this AD, ‘‘ reference date ’’ is defined as the effective date of this AD or the date when the rudder will accumulate 20,000 total flight cycles from its first installation on an airplane, whichever occurs later.

(1) Within 200 days after the reference date, perform a vacuum loss inspection on the rudder reinforced area.

(2) Within 20 months after the reference date, perform an elasticity laminate checker inspection on the rudder trailing edge area. Repeat the inspection two times at intervals not to exceed 4,500 flight cycles but not sooner than 4,000 flight cycles after the last inspection.

(3) Within 200 days after the reference date, perform an elasticity laminate checker inspection of the other areas (splice/lower rib/upper edge/leading edge/other specified locations). Repeat the inspection at intervals not to exceed 1,500 flight cycles or 200 days, whichever comes first.

(4) Within 20 months after the reference date, perform a vacuum loss inspection of the other areas (splice/lower rib/upper edge/ leading edge/other specified locations). Accomplishment of the actions specified in this paragraph terminates the requirements of paragraph (h)(3) of this AD.

(i) In case of de-bonding found during any inspection required by paragraph (g) or (h) of this AD, before further flight, contact Airbus for further instructions and apply the associated instructions and corrective actions in accordance with the approved data provided.

(j) At the applicable time specified in paragraph (j)(1) or (j)(2) of this AD, submit a report of the findings (both positive and negative), of each inspection required by paragraphs (g) and (h) of this AD. The report must include the inspection results, as specified in Airbus Technical Disposition TD/K4/S2/27086/2009, Issue E, dated September 17, 2009. For positive findings, submit the report to either the Manager, Seer1/Seer2/Seer3 Customer Services; fax +33 (0)5 61 93 28 73; e-mail region1.structurerepairsupport@airbus.com, region2.structurerepairsupport@airbus.com,

or region3.structurerepairsupport@airbus.com, or AIRTAC (Airbus Technical AOG Center) Customer Services; telephone +33 (0)5 61 93 34 00; fax +33 (0)5 61 93 35 00; e-mail airtac@airbus.com. For negative findings, submit the report to Nicolas Seynaeve, Sees1, Customer Services; telephone +33 (0)5 61 93 34 38; fax +33 (0)5 61 93 36 14; e-mail nicolas.seynaeve@airbus.com.

(1) For any inspection done on or after the effective date of this AD: Submit the report within 30 days after the inspection.

(2) For any inspection done before the effective date of this AD: Submit the report within 30 days after the effective date of this AD.

(k) All rudders that have passed the inspection specified in paragraphs (g)(1), (g)(2), (g)(3), (g)(4), (h)(1), (h)(2), (h)(3), and (h)(4) of this AD before the effective date of this AD, in accordance with Airbus AOT A320–55A1038, dated April 22, 2009; or Airbus Technical Disposition TD/K4/S2/ 27051/2009, Issue B, dated February 25, 2009; are compliant with this AD only for the areas inspected. Additional areas defined in Section 0, ‘‘ Reason for Revision, ’’ of Airbus AOT A320–55A1038, Revision 01, dated June 10, 2009, must be inspected as specified in paragraph (g) or (h) of this AD. For all areas, the repetitive inspections required by paragraph (g) or (h) of this AD remain applicable.

(l) After the effective date of this AD, no rudder listed in Table 1 of this AD may be installed on any airplane, unless the rudder is inspected in accordance with paragraph (g) or (h) of this AD, as applicable, and all applicable actions specified in paragraph (i) of this AD are done.

FAA AD Differences

Note 2: This AD differs from the MCAI and/or service information as follows: No differences.

Other FAA AD Provisions

(m) The following provisions also apply to this AD:

(1) Alternative Methods of Compliance (AMOCs): The Manager, International


## 68185 Federal Register / Vol. 75, No. 214 / Friday, November 5, 2010 / Rules and Regulations

Branch, ANM–116, Transport Airplane Directorate, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. Send information to ATTN: Tim Dulin, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, Washington 98057–3356; telephone (425) 227–2141; fax (425) 227–1149. Before using any approved AMOC on any airplane to which the AMOC applies, notify your principal maintenance inspector (PMI) or principal avionics inspector (PAI), as appropriate, or lacking a principal inspector, your local Flight Standards District Office. The AMOC approval letter must specifically reference this AD.

(2) Airworthy Product: For any requirement in this AD to obtain corrective actions from a manufacturer or other source, use these actions if they are FAA-approved. Corrective actions are considered FAA-approved if they are approved by the State of Design Authority (or their delegated agent). You are required to assure the product is airworthy before it is returned to service.

(3) Reporting Requirements: For any reporting requirement in this AD, under the provisions of the Paperwork Reduction Act (44 U.S.C. 3501 et seq. ), the Office of Management and Budget (OMB) has approved the information collection requirements and has assigned OMB Control Number 2120–0056.

Related Information

(n) Refer to MCAI European Aviation Safety Agency Airworthiness Directive 2009– 0141, dated July 2, 2009, and the service information identified in Table 2 of this AD, for related information.



### TABLE 

### 2—A IRBUS 

### S ERVICE 

### I NFORMATION

Document Revision/issue Date

Airbus All Operators Telex A320–55A1038 ............................................................................... Revision 01 ................. June 10, 2009. Airbus All Operators Telex A320–55A1038 ............................................................................... Revision 02 ................. September 28, 2009. Airbus Technical Disposition TD/K4/S2/27086/2009 ................................................................. Issue E ....................... September 17, 2009.

Material Incorporated by Reference

(o) You must use the service information contained in Table 3 of this AD to do the actions required by this AD, unless the AD specifies otherwise.



### T ABLE 

### 3—M ATERIAL 

### I NCORPORATED BY 

### R EFERENCE

Document Revision/issue Date

Airbus All Operators Telex A320–55A1038* ............................................................................. Revision 01 ................. June 10, 2009. Airbus All Operators Telex A320–55A1038* ............................................................................. Revision 02 ................. September 28, 2009. Airbus Technical Disposition TD/K4/S2/27086/2009 ................................................................. Issue E ....................... September 17, 2009.

(* The first page of these documents contain the document number, revision level, and date; no other pages contain this informat ion.)

(1) The Director of the Federal Register approved the incorporation by reference of this service information under 5 U.S.C. 552(a) and 1 CFR part 51.

(2) For service information identified in this AD, contact Airbus, Airworthiness Office—EAS, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 44 51; e-mail: account.airworth-eas@airbus.com; Internet http://www.airbus.com.

(3) You may review copies of the service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, Washington. For information on the availability of this material at the FAA, call

425–227–1221.

(4) You may also review copies of the service information that is incorporated by reference at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202–741–6030, or go

to: http://www.archives.gov/federal

_register/ code

_ of

_ federal

_regulations/ibr

_ locations.html

.

Issued in Renton, Washington, on October 26, 2010. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service.
[FR Doc. 2010–27614 Filed 11–4–10; 8:45 am]

**BILLING CODE 4910–13–P** 

### DEPARTMENT OF TRANSPORTATION

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2010–0640; Directorate Identifier 2009–NM–142–AD; Amendment**  **39–16494; AD 2010–23–05]**

**RIN 2120–AA64**



### Airworthiness Directives; EADS CASA **(Type Certificate Previously Held by Construcciones Aeronauticas, S.A.)**  **Model CN–235, CN–235–100, CN–235– 200, and CN–235–300 Airplanes, and**  **Model C–295 Airplanes**

**AGENCY** 

### : Federal Aviation Administration (FAA), Department of Transportation (DOT).

**ACTION** 

### : Final rule.

**SUMMARY** 

### : We are superseding an existing airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) originated by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as: Prompted by [an] accident * * *the FAA published SFAR 88 (Special Federal Aviation Regulation 88) * * *.


### * * * * *

Fuel Airworthiness Limitations arising from the required systems safety analysis are items that have been shown to have failure mode(s) associated with an ‘unsafe condition’ * * *. These are identified in Failure Conditions for which an unacceptable probability of ignition risk could exist if specific tasks and/or practices are not performed in accordance with the corrective actions(s) developed by the TC [type certificate] holder. 

### We are issuing this AD to require actions to correct the unsafe condition on these products.

**DATES** 

### : This AD becomes effective December 10, 2010.

The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of December 10, 2010.

**ADDRESSES** 

### : You may examine the AD docket on the Internet at http:// www.regulations.gov or in person at the U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue, SE., Washington, DC.