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

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. 

TABLE 1—INSPECTION SCHEDULE

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 pump 

before 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 on 

the 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, 

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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 on 

the 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 also 

estimate 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 

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

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—RUDDER PART NUMBER AND

AFFECTED RUDDER SERIAL NUMBER

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 

TABLE 1—RUDDER PART NUMBER AND

AFFECTED RUDDER SERIAL NUMBER—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 

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

TABLE 1—RUDDER PART NUMBER AND

AFFECTED RUDDER SERIAL NUMBER—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 

(m3). 

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 on 

the 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/m3 (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/m3 (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 

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

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—AIRBUS SERVICE INFORMATION

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. 

TABLE 3—MATERIAL INCORPORATED BY REFERENCE

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 information.) 

(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. 

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