60064 Federal Register / Vol. 77, No. 191 / Tuesday, October 2, 2012 / Proposed Rules 

thereafter at intervals not to exceed 3,000 

hours TIS on the P/N 83278 engine oil 

pressure switch, replace it with a new, zero 

time, P/N 83278 engine oil pressure switch. 

Record the engine oil pressure switch part 

number, date, and airplane hours in the 

airplane log book. The recorded engine oil 

pressure switch TIS will be used as the 

benchmark for calculation of the 3,000 hour 

TIS limit on the engine oil pressure switch. 

(h) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Wichita Aircraft 

Certification Office (ACO), 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 manager of the ACO, send it to the 

attention of the person identified in the 

Related Information section of this AD. 

(2) 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. 

(i) Related Information 

(1) For more information about this AD, 

contact Jeff Janusz, Sr. Propulsion Engineer, 

Wichita ACO, FAA, 1801 Airport Road, 

Wichita, KS 67209 phone: (316) 946–4148; 

fax: (316) 946–4107; email: jeff.janusz@faa.

gov. 

(2) For service information identified in 

this AD, contact Cessna Aircraft Company, 

Product Support, P.O. Box 7706, Wichita, 

Kansas 67277; telephone: (316) 517–5800; fax 

(316) 942–9006; Internet: www.cessna.com/

customer-service/technical-publications.

html. You may review copies of the 

referenced service information at the FAA, 

Small Airplane Directorate, 901 Locust, 

Kansas City, Missouri 64106. For information 

on the availability of this material at the 

FAA, call (816) 329–4148. 

Issued in Kansas City, Missouri, on 

September 26, 2012. 

Earl Lawrence, 

Manager, Small Airplane Directorate, Aircraft 

Certification Service. 

[FR Doc. 2012–24207 Filed 10–1–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–1034; Directorate 

Identifier 2011–NM–051–AD] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to supersede an 

existing airworthiness directive (AD) 

that applies to certain Airbus Model 

A318, A319, A320, and A321 series 

airplanes. The existing AD currently 

requires one-time and repetitive 

inspections of specific areas and, when 

necessary, corrective actions for those 

rudders where production rework has 

been identified. Since we issued that 

AD, we have determined that additional 

inspections and corrective actions are 

necessary to address the identified 

unsafe condition, and that additional 

airplanes with certain rudders are 

subject to the identified unsafe 

condition. This proposed AD would add 

airplanes with certain rudders to the AD 

applicability; change an inspection type 

for certain reinforced rudder areas; 

require pre-inspections and repairs if 

needed; and require permanent 

restoration of vacuum loss holes. This 

proposed AD would also require 

additional inspections for certain 

rudders and repair if needed; and 

require replacement of certain rudders 

with new rudders. We are proposing 

this AD to detect and correct extended 

de-bonding, which might 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 airplane. 

DATES: We must receive comments on 

this proposed AD by November 16, 

2012. 

ADDRESSES: You may send comments by 

any of the following methods: 

• Federal eRulemaking Portal: Go to 

http://www.regulations.gov. Follow the 

instructions for submitting comments. 

• Fax: (202) 493–2251. 

• Mail: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE., 

Washington, DC 20590. 

• Hand Delivery: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–40, 1200 New Jersey Avenue SE., 

Washington, DC, between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

For service information identified in 

this proposed 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; email 

account.airworth-eas@airbus.com; 

Internet http://www.airbus.com. You 

may review copies of the referenced 

service information at the FAA, 

Transport Airplane Directorate, 1601 

Lind Avenue SW., Renton, WA. For 

information on the availability of this 

material at the FAA, call 425–227–1221. 

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 this proposed AD, 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. 

FOR FURTHER INFORMATION CONTACT: 

Sanjay Ralhan, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue SW., Renton, WA 

98057–3356; telephone (425) 227–1405; 

fax (425) 227–1149. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 

this proposed AD. Send your comments 

to an address listed under the 

ADDRESSES section. Include ‘‘Docket No. 

FAA–2012–1034; Directorate Identifier 

2011–NM–051–AD’’ at the beginning of 

your comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of this proposed AD. We will 

consider all comments received by the 

closing date and may amend this 

proposed AD based on those comments. 

We will post all comments we 

receive, without change, to http:// 

www.regulations.gov, including any 

personal information you provide. We 

will also post a report summarizing each 

substantive verbal contact we receive 

about this proposed AD. 

Discussion 

On October 26, 2010, we issued AD 

2010–23–07, Amendment 39–16496 (75 

FR 68181, November 5, 2010; corrected 

December 17, 2010 (75 FR 78883)). That 

AD required actions intended to address 

an unsafe condition on the products 

listed above. 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Community, has issued EASA 

Airworthiness Directive 2010–0164, 

dated August 5, 2010 (referred to after 

this as ‘‘the MCAI’’), to correct an unsafe 

condition for the specified products. 

The MCAI states: 


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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. 

EASA AD 2009–0141 required inspections 

of specific areas and, when necessary, the 

application of corrective actions for those 

rudders where production reworks have been 

identified. 

This [EASA] AD retains the requirements 

of EASA AD 2009–0141 (addressing the 

populations of rudders affected by AOT 

A320–55–1038), which is superseded, and 

requires: 

— a local ultrasonic inspection for reinforced 

area instead of the local thermography 

inspection, which is maintained for nonreinforced areas, and 

— additional work performance for rudders 

on which this thermography inspection has 

been performed in the reinforced area, and 

— additional work performance for some 

rudders on which an additional area 

requiring inspections is defined. 

This [EASA] AD also addresses the 

populations of rudders affected by AOT 

A320–55–1039 and Airbus SB A320–55– 

1035, A320–55–1036 and A320–55–1037 

which were not included in EASA AD 2009– 

0141. 

Part number (P/N) D554 71000 020 00 

serial number (S/N) TS–1494, and P/N 

D554 71002 000 00 0002 S/N TS–2212 

are listed in Appendix A of EASA AD 

2010–0164, dated August 5, 2010. These 

two items are listed in table 6 of this 

proposed AD, because they were not 

listed in previous AD 2010–23–07, 

Amendment 39–16496 (75 FR 68181, 

November 5, 2010; corrected December 

17, 2010 (75 FR 78883)). This proposed 

AD requires the permanent restoration 

of vacuum loss holes and does not allow 

the temporary restoration with selfadhesive patches, or temporary 

restoration with resin that is specified in 

the MCAI. You may obtain further 

information by examining the MCAI in 

the AD docket. 

Relevant Service Information 

Airbus has issued the following 

service information. 

• Airbus All Operators Telex (AOT) 

A320–55A1038, dated April 22, 2009. 

• Airbus AOT A320–55A1039, dated 

November 4, 2009. 

• Airbus Service Bulletin A320–55– 

1035, Revision 01, dated July 2, 2010. 

• Airbus Service Bulletin A320–55– 

1036, Revision 01, dated July 2, 2010. 

• Airbus Service Bulletin A320–55– 

1037, Revision 01, dated July 2, 2010. 

• Airbus Technical Disposition TD/ 

K4/S2/27051/2009, Issue B, dated 

February 25, 2009. 

• Airbus Technical Disposition TD/ 

K4/S2/27086/2009, Issue E, dated 

September 17, 2009. 

The actions described in this service 

information are intended to correct the 

unsafe condition identified in the 

MCAI. 

FAA’s Determination and Requirements 

of This Proposed AD 

This product has been approved by 

the aviation authority of another 

country, and is approved for operation 

in the United States. Pursuant to our 

bilateral agreement with the State of 

Design Authority, we have been notified 

of the unsafe condition described in the 

MCAI and service information 

referenced above. We are proposing this 

AD because we evaluated all pertinent 

information and determined an unsafe 

condition exists and is likely to exist or 

develop on other products of the same 

type design. 

Differences Between This AD and the 

MCAI or Service Information 

This proposed AD requires the 

permanent restoration of vacuum loss 

holes and does not allow the temporary 

restoration with self-adhesive patches, 

or temporary restoration with resin that 

is specified in the MCAI. 

Costs of Compliance 

Based on the service information, we 

estimate that this proposed AD would 

affect about 721 products of U.S. 

registry. 

The actions that are required by AD 

2010–23–07, Amendment 39–16496 (75 

FR 68181, November 5, 2010; corrected 

December 17, 2010 (75 FR 78883)), and 

retained in this proposed AD take about 

11 work-hours per product, at an 

average labor rate of $85 per work hour. 

The average labor rate is $85 per workhour. Based on these figures, we 

estimate the cost of the currently 

required actions on U.S. operators to be 

$674,135, or $935 per product. 

We estimate that it would take about 

11 work-hours per product to comply 

with the new basic requirements of this 

proposed AD. The average labor rate is 

$85 per work-hour. Based on these 

figures, we estimate the cost of the 

proposed AD on U.S. operators to be 

$674,135, or $935 per product. 

In addition, we estimate that any 

necessary follow-on actions would take 

about 12 work-hours and require parts 

costing $10,000, for a cost of $11,020 

per product. 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 proposed AD 

would not have federalism implications 

under Executive Order 13132. This 

proposed AD would 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 proposed regulation: 

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); 

3. Will not affect intrastate aviation in 

Alaska; and 

4. 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 proposed AD and placed it in the 

AD docket. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

The Proposed Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA proposes to amend 14 CFR part 

39 as follows: 


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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 airworthiness directive (AD) 

2010–23–07, Amendment 39–16496 (75 

FR 68181, November 5, 2010; corrected 

December 17, 2010 (75 FR 78883)), and 

adding the following new AD: 

Airbus: Docket No. FAA–2012–1034; 

Directorate Identifier 2011–NM–051–AD. 

(a) Comments Due Date 

We must receive comments by November 

16, 2012. 

(b) Affected ADs 

This AD supersedes AD 2010–23–07, 

Amendment 39–16496 (75 FR 68181, 

November 5, 2010; corrected December 17, 

2010 (75 FR 78883)). 

(c) Applicability 

This AD applies to the Airbus airplanes 

identified in paragraphs (c)(1), (c)(2), (c)(3), 

and (c)(4) of this AD; certificated in any 

category; all serial numbers having a rudder 

with a part number (P/N) and serial number 

(S/N) listed in table 1, 2, 3, 4a and 4b, 5a and 

5b, or 6 to paragraph (c) of this AD. 

(1) Model A318–111, –112, –121, and –122 

airplanes. 

(2) Model A319–111, –112, –113, –114, 

–115, –131, –132, and –133 airplanes. 

(3) Model A320–111, –211, –212, –214, 

–231, –232, and –233 airplanes. 

(4) Model A321–111, –112, –131, –211, 

–212, –213, –231, and –232 airplanes. 

TABLE 1 TO PARAGRAPH (C) OF THIS

AD 

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 

TABLE 1 TO PARAGRAPH (C) OF THIS

AD—Continued 

Rudder P/N 

Affected 

rudder 

S/N 

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 71001 000 00 ...................... TS–1537 

D554 71001 000 00 ...................... 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 

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–2072 

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 

TABLE 1 TO PARAGRAPH (C) OF THIS

AD—Continued 

Rudder P/N 

Affected 

rudder 

S/N 

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 

D554 71002 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 

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 71002 000 00 0003 ............. TS–2971 

D554 71002 000 00 0003 ............. TS–2987 

D554 71004 000 00 0000 ............. TS–3083 

D554 71004 000 00 0000 ............. TS–3197 

Note 1 to paragraph (c) of this AD: For 

table 1 to paragraph (c) of this AD, only 

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, have a core 


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density of 24 kilogram (kg)/meters cubed 

(m3). 

TABLE 2 TO PARAGRAPH (C) OF THIS

AD 

Rudder P/N 

Affected 

rudder 

S/N 

D554–71000–014–00 .................... TS–1278 

D554–71002–000–00–0001 .......... TS–2081 

D554–71002–000–00–0002 .......... TS–2125 

D554–71002–000–00–0002 .......... TS–2129 

D554–71002–000–00–0002 .......... TS–2160 

D554–71002–000–00–0002 .......... TS–2201 

D554–71002–000–00–0002 .......... TS–2328 

D554–71002–000–00–0002 .......... TS–2425 

D554–71002–000–00–0002 .......... TS–2511 

D554–71002–000–00–0003 .......... TS–2768 

D554–71002–000–00–0003 .......... TS–2999 

D554–71002–000–00–0003 .......... TS–3004 

D554–71002–000–00–0003 .......... TS–3051 

D554–71004–000–00–0001 .......... TS–3288 

TABLE 3 TO PARAGRAPH (C) OF THIS

AD 

Rudder P/N 

Affected 

rudder 

S/N 

D554–71000–008–00 .................... TS–1032 

D554–71000–010–00 .................... TS–1092 

D554–71000–014–00 .................... TS–1314 

D554–71000–018–00 .................... TS–1445 

D554–71000–020–00 .................... TS–1520 

D554–71002–000–00–0001 .......... TS–2037 

D554–71002–000–00–0002 .......... TS–2109 

D554–71002–000–00–0002 .......... TS–2123 

D554–71002–000–00–0002 .......... TS–2124 

D554–71002–000–00–0002 .......... TS–2424 

D554–71002–000–00–0002 .......... TS–2559 

D554–71002–000–00–0003 .......... TS–3061 

D554–71004–000–00–0001 .......... TS–3694 

D554–71004–000–00–0001 .......... TS–3709 

D554–71004–000–00–0002 .......... TS–4148 

Note 2 to paragraph (c) of this AD: For 

table 3 to paragraph (c) of this AD, only 

rudder P/N D554–71000–008–00 having 

affected rudder S/N TS–1032, and rudder P/ 

N D554–71000–010–00 having affected 

rudder S/N TS–1092, have a core density of 

24 kg/m3. 

TABLE 4A TO PARAGRAPH (C) OF THIS

AD 

Rudder P/N with any S/N listed in table 4b to 

paragraph (c) of this AD 

D5547100000000 

D5547100000200 

D5547100000400 

D5547100000600 

D5547100000800 

D5547100001000 

D5547100001200 

D5547100001400 

D5547100001600 

D5547100001800 

D5547100002000 

D5547100100000 

D5547100200000 

D5547100300000 

D5547100400000 

TABLE 4B TO PARAGRAPH (C) OF THIS AD 

Affected S/N for rudders listed in table 4a to paragraph (c) of this AD 

TS–1368 TS–1616 TS–2080 TS–2159 TS–2222 TS–2276 TS–2327 

TS–1389 TS–1619 TS–2082 TS–2163 TS–2223 TS–2279 TS–2330 

TS–1496 TS–1622 TS–2084 TS–2168 TS–2227 TS–2280 TS–2331 

TS–1501 TS–1632 TS–2085 TS–2169 TS–2228 TS–2281 TS–2332 

TS–1503 TS–1639 TS–2086 TS–2170 TS–2230 TS–2284 TS–2333 

TS–1508 TS–2004 TS–2094 TS–2172 TS–2231 TS–2285 TS–2334 

TS–1516 TS–2008 TS–2096 TS–2175 TS–2232 TS–2286 TS–2336 

TS–1527 TS–2010 TS–2097 TS–2177 TS–2234 TS–2293 TS–2337 

TS–1529 TS–2012 TS–2098 TS–2179 TS–2235 TS–2297 TS–2338 

TS–1534 TS–2014 TS–2100 TS–2182 TS–2236 TS–2298 TS–2339 

TS–1545 TS–2017 TS–2101 TS–2183 TS–2238 TS–2299 TS–2340 

TS–1547 TS–2018 TS–2106 TS–2185 TS–2240 TS–2302 TS–2341 

TS–1553 TS–2023 TS–2113 TS–2192 TS–2242 TS–2303 TS–2343 

TS–1560 TS–2025 TS–2115 TS–2193 TS–2244 TS–2304 TS–2346 

TS–1561 TS–2029 TS–2118 TS–2195 TS–2245 TS–2305 TS–2352 

TS–1571 TS–2032 TS–2126 TS–2199 TS–2248 TS–2307 TS–2353 

TS–1572 TS–2034 TS–2130 TS–2200 TS–2250 TS–2310 TS–2354 

TS–1574 TS–2039 TS–2131 TS–2204 TS–2251 TS–2311 TS–2355 

TS–1576 TS–2040 TS–2132 TS–2206 TS–2252 TS–2312 TS–2356 

TS–1577 TS–2041 TS–2134 TS–2208 TS–2254 TS–2313 TS–2358 

TS–1583 TS–2046 TS–2136 TS–2209 TS–2258 TS–2315 TS–2360 

TS–1585 TS–2050 TS–2140 TS–2210 TS–2259 TS–2316 TS–2362 

TS–1588 TS–2051 TS–2143 TS–2211 TS–2260 TS–2319 TS–2363 

TS–1591 TS–2052 TS–2144 TS–2213 TS–2261 TS–2320 TS–2364 

TS–1600 TS–2053 TS–2145 TS–2216 TS–2262 TS–2321 TS–2365 

TS–1602 TS–2056 TS–2149 TS–2217 TS–2265 TS–2322 TS–2366 

TS–1607 TS–2060 TS–2152 TS–2218 TS–2268 TS–2323 TS–2367 

TS–1608 TS–2069 TS–2154 TS–2220 TS–2271 TS–2325 TS–2370 

TS–1614 TS–2070 TS–2155 TS–2221 TS–2272 TS–2326 TS–2371 

TS–2372 TS–2483 TS–2583 TS–2665 TS–2743 TS–2813 TS–2878 

TS–2373 TS–2484 TS–2584 TS–2666 TS–2744 TS–2814 TS–2879 

TS–2374 TS–2486 TS–2585 TS–2667 TS–2745 TS–2815 TS–2880 

TS–2377 TS–2488 TS–2586 TS–2668 TS–2747 TS–2816 TS–2881 

TS–2381 TS–2491 TS–2587 TS–2671 TS–2749 TS–2818 TS–2882 

TS–2382 TS–2493 TS–2590 TS–2674 TS–2751 TS–2819 TS–2885 

TS–2387 TS–2494 TS–2591 TS–2675 TS–2753 TS–2821 TS–2886 

TS–2388 TS–2498 TS–2592 TS–2676 TS–2754 TS–2822 TS–2890 

TS–2392 TS–2499 TS–2593 TS–2677 TS–2755 TS–2823 TS–2891 

TS–2393 TS–2501 TS–2596 TS–2679 TS–2756 TS–2824 TS–2892 

TS–2395 TS–2505 TS–2597 TS–2680 TS–2757 TS–2826 TS–2893 

TS–2397 TS–2506 TS–2601 TS–2681 TS–2758 TS–2827 TS–2896 

TS–2398 TS–2508 TS–2602 TS–2682 TS–2759 TS–2828 TS–2897 

TS–2399 TS–2510 TS–2603 TS–2683 TS–2760 TS–2830 TS–2898 


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TABLE 4B TO PARAGRAPH (C) OF THIS AD—Continued 

TS–2407 TS–2512 TS–2605 TS–2685 TS–2762 TS–2831 TS–2899 

TS–2408 TS–2514 TS–2606 TS–2688 TS–2765 TS–2832 TS–2900 

TS–2409 TS–2517 TS–2611 TS–2689 TS–2771 TS–2833 TS–2903 

TS–2410 TS–2518 TS–2612 TS–2691 TS–2772 TS–2834 TS–2904 

TS–2411 TS–2521 TS–2614 TS–2695 TS–2773 TS–2835 TS–2906 

TS–2412 TS–2522 TS–2615 TS–2697 TS–2775 TS–2836 TS–2907 

TS–2415 TS–2527 TS–2616 TS–2698 TS–2776 TS–2837 TS–2908 

TS–2417 TS–2529 TS–2617 TS–2699 TS–2778 TS–2838 TS–2909 

TS–2421 TS–2532 TS–2620 TS–2700 TS–2779 TS–2839 TS–2910 

TS–2422 TS–2536 TS–2625 TS–2701 TS–2780 TS–2840 TS–2911 

TS–2423 TS–2540 TS–2626 TS–2707 TS–2782 TS–2843 TS–2913 

TS–2427 TS–2544 TS–2628 TS–2710 TS–2783 TS–2844 TS–2914 

TS–2428 TS–2545 TS–2629 TS–2711 TS–2784 TS–2845 TS–2916 

TS–2435 TS–2547 TS–2630 TS–2712 TS–2785 TS–2846 TS–2917 

TS–2437 TS–2551 TS–2631 TS–2713 TS–2786 TS–2848 TS–2919 

TS–2440 TS–2552 TS–2632 TS–2714 TS–2788 TS–2849 TS–2920 

TS–2444 TS–2553 TS–2634 TS–2716 TS–2790 TS–2850 TS–2922 

TS–2446 TS–2554 TS–2635 TS–2717 TS–2791 TS–2851 TS–2923 

TS–2447 TS–2555 TS–2636 TS–2719 TS–2792 TS–2852 TS–2924 

TS–2453 TS–2558 TS–2637 TS–2722 TS–2793 TS–2853 TS–2925 

TS–2455 TS–2562 TS–2640 TS–2724 TS–2794 TS–2854 TS–2927 

TS–2458 TS–2563 TS–2641 TS–2725 TS–2795 TS–2855 TS–2928 

TS–2460 TS–2566 TS–2642 TS–2726 TS–2796 TS–2856 TS–2929 

TS–2463 TS–2568 TS–2644 TS–2727 TS–2797 TS–2857 TS–2930 

TS–2466 TS–2570 TS–2647 TS–2728 TS–2799 TS–2860 TS–2932 

TS–2467 TS–2571 TS–2648 TS–2732 TS–2801 TS–2861 TS–2933 

TS–2471 TS–2572 TS–2650 TS–2734 TS–2803 TS–2862 TS–2934 

TS–2472 TS–2573 TS–2651 TS–2735 TS–2804 TS–2863 TS–2935 

TS–2474 TS–2574 TS–2653 TS–2736 TS–2805 TS–2864 TS–2937 

TS–2476 TS–2575 TS–2656 TS–2738 TS–2807 TS–2865 TS–2938 

TS–2477 TS–2576 TS–2657 TS–2739 TS–2808 TS–2868 TS–2939 

TS–2478 TS–2579 TS–2658 TS–2740 TS–2810 TS–2872 TS–2943 

TS–2481 TS–2580 TS–2659 TS–2741 TS–2811 TS–2874 TS–2944 

TS–2482 TS–2581 TS–2662 TS–2742 TS–2812 TS–2877 TS–2946 

TS–2948 TS–3040 TS–3113 TS–3177 TS–3249 TS–3689 TS–3928 

TS–2949 TS–3043 TS–3114 TS–3178 TS–3250 TS–3690 TS–3936 

TS–2950 TS–3046 TS–3116 TS–3179 TS–3251 TS–3695 TS–3939 

TS–2951 TS–3049 TS–3119 TS–3180 TS–3252 TS–3699 TS–3942 

TS–2953 TS–3050 TS–3120 TS–3181 TS–3253 TS–3702 TS–3950 

TS–2954 TS–3052 TS–3121 TS–3182 TS–3255 TS–3703 TS–3958 

TS–2955 TS–3054 TS–3122 TS–3183 TS–3256 TS–3704 TS–3961 

TS–2957 TS–3055 TS–3123 TS–3184 TS–3257 TS–3706 TS–3968 

TS–2958 TS–3056 TS–3124 TS–3185 TS–3259 TS–3708 TS–3987 

TS–2959 TS–3058 TS–3125 TS–3186 TS–3262 TS–3710 TS–3993 

TS–2960 TS–3060 TS–3126 TS–3188 TS–3271 TS–3717 TS–3995 

TS–2962 TS–3065 TS–3127 TS–3189 TS–3276 TS–3718 TS–4003 

TS–2964 TS–3066 TS–3129 TS–3191 TS–3278 TS–3734 TS–4027 

TS–2965 TS–3071 TS–3131 TS–3193 TS–3282 TS–3743 TS–4031 

TS–2968 TS–3072 TS–3132 TS–3194 TS–3286 TS–3761 TS–4087 

TS–2969 TS–3074 TS–3133 TS–3195 TS–3289 TS–3772 TS–4099 

TS–2973 TS–3075 TS–3134 TS–3198 TS–3290 TS–3780 TS–4118 

TS–2976 TS–3076 TS–3135 TS–3200 TS–3291 TS–3789 TS–4145 

TS–2980 TS–3077 TS–3138 TS–3201 TS–3292 TS–3805 TS–4146 

TS–2984 TS–3078 TS–3139 TS–3202 TS–3295 TS–3820 TS–4147 

TS–2985 TS–3079 TS–3140 TS–3204 TS–3297 TS–3821 TS–4163 

TS–2986 TS–3080 TS–3141 TS–3205 TS–3306 TS–3822 TS–4167 

TS–2988 TS–3081 TS–3142 TS–3207 TS–3309 TS–3824 TS–4175 

TS–2991 TS–3082 TS–3143 TS–3210 TS–3310 TS–3825 TS–4178 

TS–2998 TS–3084 TS–3144 TS–3215 TS–3317 TS–3839 TS–4181 

TS–3001 TS–3087 TS–3145 TS–3216 TS–3320 TS–3841 TS–4186 

TS–3002 TS–3088 TS–3148 TS–3217 TS–3328 TS–3843 TS–4195 

TS–3003 TS–3089 TS–3149 TS–3218 TS–3388 TS–3844 TS–4212 

TS–3005 TS–3090 TS–3151 TS–3219 TS–3392 TS–3846 TS–4232 

TS–3006 TS–3091 TS–3154 TS–3221 TS–3395 TS–3849 TS–4271 

TS–3009 TS–3093 TS–3155 TS–3222 TS–3429 TS–3850 TS–4331 

TS–3011 TS–3094 TS–3156 TS–3223 TS–3441 TS–3851 TS–4345 

TS–3016 TS–3096 TS–3158 TS–3224 TS–3516 TS–3853 TS–4366 

TS–3018 TS–3097 TS–3159 TS–3226 TS–3561 TS–3855 TS–4396 

TS–3020 TS–3098 TS–3160 TS–3227 TS–3567 TS–3857 TS–4401 

TS–3021 TS–3100 TS–3161 TS–3232 TS–3574 TS–3860 TS–4420 

TS–3025 TS–3101 TS–3162 TS–3234 TS–3590 TS–3862 TS–4461 

TS–3026 TS–3102 TS–3164 TS–3235 TS–3591 TS–3863 TS–4480 

TS–3027 TS–3103 TS–3166 TS–3236 TS–3595 TS–3871 TS–4636 

TS–3028 TS–3104 TS–3167 TS–3237 TS–3598 TS–3878 TS–4651 


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TABLE 4B TO PARAGRAPH (C) OF THIS AD—Continued 

TS–3030 TS–3105 TS–3168 TS–3240 TS–3609 TS–3879 TS–4678 

TS–3031 TS–3106 TS–3169 TS–3241 TS–3625 TS–3882 TS–4696 

TS–3032 TS–3107 TS–3170 TS–3242 TS–3638 TS–3883 TS–4770 

TS–3033 TS–3108 TS–3171 TS–3243 TS–3650 TS–3885 N/A 

TS–3034 TS–3109 TS–3172 TS–3244 TS–3669 TS–3910 N/A 

TS–3035 TS–3110 TS–3174 TS–3245 TS–3684 TS–3914 N/A 

TS–3037 TS–3111 TS–3175 TS–3247 TS–3685 TS–3921 N/A 

TS–3038 TS–3112 TS–3176 TS–3248 TS–3687 TS–3924 N/A 

TABLE 5A TO PARAGRAPH (C) OF THIS

AD 

Rudder P/N with any S/N listed in table 5b to 

paragraph (c) of this AD 

D5547100000000 

D5547100000200 

D5547100000400 

D5547100000600 

D5547100000800 

D5547100001000 

D5547100001200 

D5547100001400 

D5547100001600 

D5547100001800 

D5547100002000 

D5547100100000 

D5547100200000 

D5547100300000 

D5547100400000 

TABLE 5B TO PARAGRAPH (C) OF THIS

AD 

TS–2141 

TS–2269 

TS–2274 

TS–2295 

TS–2317 

TS–2664 

TS–2715 

TABLE 6 TO PARAGRAPH (C) OF THIS

AD 

Rudder P/N 

Affected 

rudder 

S/N 

D554 71000 020 00 ...................... TS–1494 

D554 71002 000 00 0002 ............. TS–2212 

(d) Subject 

Air Transport Association (ATA) of 

America Code 55, Stabilizers. 

(e) Reason 

This AD was prompted by reports of 

surface defects on rudders that were the 

result of debonding between the skin and 

honeycomb core. We are issuing this AD to 

detect and correct extended de-bonding, 

which might 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 airplane. 

(f) Compliance 

You are responsible for having the actions 

required by this AD performed within the 

compliance times specified, unless the 

actions have already been done. 

(g) Retained Repetitive Inspections of 

Rudders With a Core Density of 24 kg/m3

This paragraph restates the requirements of 

paragraph (g) of AD 2010–23–07 Amendment 

39–16496 (75 FR 68181, November 5, 2010; 

corrected December 17, 2010 (75 FR 78883)). 

For rudders identified in table 1 to paragraph 

(c) of this AD 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 applicable AOT 

specified in this paragraph. 

(1) Within 200 days after December 10, 

2010 (the effective date of AD 2010–23–07, 

Amendment 39–16496 (75 FR 68181, 

November 5, 2010; corrected December 17, 

2010 (75 FR 78883))): Perform a vacuum loss 

inspection on the rudder reinforced area. 

(2) Within 20 months after December 10, 

2010 (the effective date of AD 2010–23–07, 

Amendment 39–16496 (75 FR 68181, 

November 5, 2010; corrected December 17, 

2010 (75 FR 78883))): 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 December 10, 

2010 (the effective date of AD 2010–23–07, 

Amendment 39–16496 (75 FR 68181, 

November 5, 2010; corrected December 17, 

2010 (75 FR 78883))): 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 December 10, 

2010 (the effective date of AD 2010–23–07, 

Amendment 39–16496 (75 FR 68181, 

November 5, 2010; corrected December 17, 

2010 (75 FR 78883))): 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) Retained Repetitive Inspections of 

Rudders Without a Core Density of 24 kg/m3

This paragraph restates the requirements of 

paragraph (h) of AD 2010–23–07 Amendment 

39–16496 (75 FR 68181, November 5, 2010; 

corrected December 17, 2010 (75 FR 78883)). 

For rudders that do not have a honeycomb 

core density of 24 kg/m3 (all rudders 

identified in table 1 to paragraph (c) 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 applicable AOT specified in this 

paragraph. As of the effective date of this AD, 

use only Airbus AOT A320–55A1038, 

Revision 02, dated September 28, 2009. For 

this paragraph, ‘‘reference date’’ is defined as 

December 10, 2010 (the effective date of AD 

2010–23–07), 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) Retained Corrective Actions for DeBonding 

This paragraph restates the requirements of 

paragraph (i) of AD 2010–23–07 Amendment 

39–16496 (75 FR 68181, November 5, 2010; 

corrected December 17, 2010 (75 FR 78883)). 

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 


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60070 Federal Register / Vol. 77, No. 191 / Tuesday, October 2, 2012 / Proposed Rules 

in accordance with the approved data 

provided, or repair the debonding using a 

method approved by either the Manager, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA; or the European 

Aviation Safety Agency (EASA) (or its 

delegated agent). After the effective date of 

this AD, repair the debonding using only a 

method approved by either the Manager, 

International Branch, ANM–116; or the 

EASA (or its delegated agent). 

(j) Retained Reporting for Findings From 

Actions Required by Paragraphs (g) and (h) 

of this AD 

This paragraph restates the requirements of 

paragraph (j) of AD 2010–23–07 Amendment 

39–16496 (75 FR 68181, November 5, 2010; 

corrected December 17, 2010 (75 FR 78883)). 

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, email 

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, email 

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; email 

nicolas.seynaeve@airbus.com. 

(1) For any inspection done on or after 

December 10, 2010 (the effective date of AD 

2010–23–07, Amendment 39–16496 (75 FR 

68181, November 5, 2010; corrected 

December 17, 2010 (75 FR 78883))): Submit 

the report within 30 days after the 

inspection. 

(2) For any inspection done before 

December 10, 2010 (the effective date of AD 

2010–23–07, Amendment 39–16496 (75 FR 

68181, November 5, 2010; corrected 

December 17, 2010 (75 FR 78883))): Submit 

the report within 30 days after December 10, 

2010. 

(k) Retained Inspection in Additional Areas 

This paragraph restates the provisions of 

paragraph (k) of AD 2010–23–07, 

Amendment 39–16496, (75 FR 68181, 

November 5, 2010; corrected December 17, 

2010 (75 FR 78883)). 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 December 10, 

2010 (the effective date of AD 2010–23–07), 

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; or Airbus AOT A320–55A1038, 

Revision 02, dated September 28, 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) Retained Parts Installation Limitations 

This paragraph restates the requirements of 

paragraph (l) of AD 2010–23–07, Amendment 

39–16496 (75 FR 68181, November 5, 2010; 

corrected December 17, 2010 (75 FR 78883)). 

After December 10, 2010 (the effective date 

of AD 2010–23–07), no rudder listed in table 

1 to paragraph (c) 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. 

(m) New Restoration of Vacuum Loss Holes 

If no de-bonding is found during any 

inspection required by paragraph (g) or (h) of 

this AD: Before further flight, restore the 

vacuum loss holes by doing a permanent 

restoration with resin, in accordance with 

Note 3 of Airbus AOT A320–55A1038, 

Revision 02, dated September 28, 2009. 

Before doing the resin injection, do a local 

ultrasound inspection in reinforced areas, 

and a thermography inspection in other 

areas, for damage, in accordance with Note 

3 of Airbus AOT A320–55A1038, Revision 

02, dated September 28, 2009. If any damage 

is found during any inspection required by 

this paragraph: Before further flight, repair 

the damage using a method approved by 

either the Manager, International Branch, 

ANM–116; or the EASA (or its delegated 

agent). 

(n) New X-Ray, Elasticity Laminate Checker 

(ELCh), Vacuum Loss, or Thermography 

Inspection 

For rudders identified in table 2 to 

paragraph (c) of this AD, do the actions 

specified in paragraphs (n)(1) and (n)(2) of 

this AD, in accordance with Airbus AOT 

A320–55A1039, dated November 4, 2009, for 

the locations defined in that AOT. For this 

paragraph, ‘‘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 20 months after the effective 

date of this AD, or within 200 days after the 

reference date, whichever occurs first: 

Perform X-ray, and/or ELCh, and/or vacuum 

loss, and/or thermography inspections for 

damage, as applicable to rudder part number 

and serial number, in accordance with the 

instructions of paragraph 4.2.2.1.1. of Airbus 

AOT A320–55A1039, dated November 4, 

2009. 

(2) At the applicable time specified in 

paragraph (n)(2)(i) or (n)(2)(ii) of this AD, 

send the developed X-ray films and the film 

layout arrangement, if applicable, to Attn: 

SDC32 Technical Data and Documentation 

Services, Airbus Customer Services 

Directorate, 1 Rond Point Maurice Bellonte, 

31707 Blagnac Cedex, France; fax (+33) 5 61 

93 28 06; email sb.reporting@airbus.com. 

(i) If the inspection was done on or after 

the effective date of this AD: Submit the Xray films and the film layout arrangement 

within 10 days after the inspection. 

(ii) If the inspection was done before the 

effective date of this AD: Submit the X-ray 

films and the film layout arrangement within 

10 days after the effective date of this AD. 

(3) If any damage is found during any 

inspection required by paragraph (n) of this 

AD: Before further flight, repair the damage 

using a method approved by either the 

Manager, International Branch, ANM–116; or 

the EASA (or its delegated agent). 

(o) New ELCh Inspection, Vacuum Loss 

Inspection, and Repairs 

For rudders identified in table 2 to 

paragraph (c) of this AD: Within 1,500 flight 

cycles or 200 days after doing the 

requirements of paragraph (n)(1) of this AD, 

whichever occurs first, do the actions 

specified in paragraphs (o)(1) and (o)(2) of 

this AD. 

(1) Perform an ELCh inspection for damage 

on the rudder trailing edge area, in 

accordance with the instructions of 

paragraph 4.2.2.1.2. of Airbus AOT A320– 

55A1039, dated November 4, 2009. In case of 

no finding, 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. 

(2) Perform a vacuum loss inspection for 

damage of the other areas (splice/lower rib/ 

upper edge/leading edge/other specified 

locations), in accordance with the 

instructions of paragraph 4.2.2.1.2. of Airbus 

AOT A320–55A1039, dated November 4, 

2009. 

(3) If any damage is found during any 

inspection required by paragraph (o) of this 

AD: Before further flight, repair the damage 

using a method approved by either the 

Manager, International Branch, ANM–116; or 

the EASA (or its delegated agent). 

(p) New Restorations and Inspections of 

Certain Vacuum Loss Holes, and Repairs 

If no damage is found during any 

inspection required by paragraph (o) of this 

AD: Before further flight, restore the vacuum 

loss holes by doing a permanent restoration 

with resin, in accordance with Note 3 of 

Airbus AOT A320–55A1039, dated 

November 4, 2009. Before doing the resin 

injection, do a local ultrasound inspection in 

reinforced areas, and a thermography 

inspection in other areas, for damage, in 

accordance with Note 3 of Airbus AOT 

A320–55A1039, dated November 4, 2009. If 

any damage is found during any inspection 

required by this paragraph: Before further 

flight, repair the damage using a method 

approved by either the Manager, 

International Branch, ANM–116; or the 

EASA (or its delegated agent). 

(q) New Rudder Replacement for Rudders 

Identified in Table 3 to Paragraph (c) of This 

AD 

For rudders identified in table 3 to 

paragraph (c) of this AD, do the actions 

specified in paragraphs (q)(1) and (q)(2) of 

this AD, in accordance with the instruction 

of Airbus AOT A320–55A1039, dated 

November 4, 2009, for the locations defined 

in that AOT. For this paragraph, ‘‘reference 

date’’ is defined as the effective date of this 


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Federal Register / Vol. 77, No. 191 / Tuesday, October 2, 2012 / Proposed Rules 60071 

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) For rudders identified in table 3 to 

paragraph (c) of this AD with a honeycomb 

core density of 24 kg/m3 (rudder P/N D554– 

71000–008–00 having affected rudder S/N 

TS–1032 and rudder P/N D554–71000–010– 

00 having affected rudder S/N TS–1092): 

Within 200 days after the effective date of 

this AD, replace the rudder with a new 

rudder, in accordance with a method 

approved by the Manager, International 

Branch, ANM–116; or the EASA (or its 

delegated agent). 

(2) For rudders identified in table 3 to 

paragraph (c) of this AD that do not have a 

honeycomb core density of 24 kg/m3 (all 

except rudder P/N D554–71000–008–00 

having affected rudder S/N TS–1032 and 

rudder P/N D554–71000–010–00 having 

affected rudder S/N TS–1092): Within 20 

months after the effective date of this AD or 

within 200 days after the reference date, 

whichever occurs first, replace the rudder 

with a new rudder, in accordance with a 

method approved by the Manager, 

International Branch, ANM–116. 

(r) New Vacuum Loss Inspection for 

Reinforced Areas of Rudder Identified in 

Table 4 to Paragraph (c) of This AD 

For rudders identified in tables 4a and 4b 

to paragraph (c) of this AD: At the later of the 

times specified in paragraphs (r)(1) and (r)(2) 

of this AD, perform a vacuum loss inspection 

on the rudder reinforced area for damage, in 

accordance with the Accomplishment 

Instructions of Airbus Service Bulletin A320– 

55–1035, Revision 01, dated July 2, 2010 (for 

Model A320 airplanes); Airbus Service 

Bulletin A320–55–1036, Revision 01, dated 

July 2, 2010 (for Model A318 and A321 

airplanes); or Airbus Service Bulletin A320– 

55–1037, Revision 01, dated July 2, 2010 (for 

Model A319 airplanes). 

(1) Before the rudder accumulates 17,000 

total flight cycles from its first installation on 

an airplane without exceeding 20 months 

from the effective date of this AD. 

(2) Within 200 days after the effective date 

of this AD. 

(s) New ELCh Inspection for Rudder Trailing 

Edge Area 

For rudders identified in tables 4a and 4b 

to paragraph (c) of this AD: Within 20 

months after the effective date of this AD, 

perform an ELCh inspection for damage on 

the rudder trailing edge area, in accordance 

with the Accomplishment Instructions of 

Airbus Service Bulletin A320–55–1035, 

Revision 01, dated July 2, 2010 (for Model 

A320 airplanes); Airbus Service Bulletin 

A320–55–1036, Revision 01, dated July 2, 

2010 (for Model A318 and A321 airplanes); 

or Airbus Service Bulletin A320–55–1037, 

Revision 01, dated July 2, 2010 (for Model 

A319 airplanes). 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. 

(t) New ELCh Inspection for Additional 

Rudder Areas 

For rudders identified in tables 4a and 4b 

to paragraph (c) of this AD: At the later of the 

times specified in paragraphs (t)(1) and (t)(2) 

of this AD, perform an ELCh inspection for 

damage of the other areas (splice/lower rib/ 

upper edge/leading edge/other specified 

locations) for damage, in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A320–55–1035, Revision 01, 

dated July 2, 2010 (for Model A320 

airplanes); Airbus Service Bulletin A320–55– 

1036, Revision 01, dated July 2, 2010 (for 

Model A318 and A321 airplanes); or Airbus 

Service Bulletin A320–55–1037, Revision 01, 

dated July 2, 2010 (for Model A319 

airplanes). Repeat the inspection thereafter at 

intervals not to exceed 1,500 flight cycles or 

200 days, whichever comes first. 

(1) Before the rudder accumulates 17,000 

total flight cycles from its first installation on 

an airplane without exceeding 20 months 

from the effective date of this AD. 

(2) Within 200 days after the effective date 

of this AD. 

(u) New Vacuum Loss Inspection for Certain 

Areas of Rudders Identified in Tables 4a and 

4b to Paragraph (c) of This AD 

For rudders identified in tables 4a and 4b 

of this AD: Within 20 months after the 

effective date of this AD, perform a vacuum 

loss inspection for damage of the lower rib, 

upper edge, leading edge, and other specified 

locations, in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A320–55–1035, Revision 01, 

dated July 2, 2010 (for Model A320 

airplanes); Airbus Service Bulletin A320–55– 

1036, Revision 01, dated July 2, 2010 (for 

Model A318 and A321 airplanes); or Airbus 

Service Bulletin A320–55–1037, Revision 01, 

dated July 2, 2010 (for Model A319 

airplanes). Accomplishment of the actions 

specified in this paragraph terminates the 

requirements of paragraph (t) of this AD. 

(v) New Corrective Actions for Certain 

Inspections 

In case of damage found during any 

inspection required by paragraph (r), (s), (t), 

or (u) of this AD: Before further flight, repair 

the damage using a method approved by 

either the Manager, International Branch, 

ANM–116; or the EASA (or its delegated 

agent). 

(w) New Restorations and Inspections of 

Certain Vacuum Loss Holes, and Repairs 

If no damage is found during any 

inspection required by paragraph (r) or (u) of 

this AD: Before further flight, restore the 

vacuum loss holes by doing a permanent 

restoration with resin, in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A320–55–1035, Revision 01, 

dated July 2, 2010 (for Model A320 

airplanes); Airbus Service Bulletin A320–55– 

1036, Revision 01, dated July 2, 2010 (for 

Model A318 and A321 airplanes); or Airbus 

Service Bulletin A320–55–1037, Revision 01, 

dated July 2, 2010 (for Model A319 

airplanes). Before doing the resin injection, 

do a local ultrasound inspection in 

reinforced areas, and a thermography 

inspection in other areas, for damage, in 

accordance with the Accomplishment 

Instructions of Airbus Service Bulletin A320– 

55–1035, Revision 01, dated July 2, 2010 (for 

Model A320 airplanes); Airbus Service 

Bulletin A320–55–1036, Revision 01, dated 

July 2, 2010 (for Model A318 and A321 

airplanes); or Airbus Service Bulletin A320– 

55–1037, Revision 01, dated July 2, 2010 (for 

Model A319 airplanes). If any damage is 

found during any inspection required by this 

paragraph: Before further flight, repair the 

damage using a method approved by either 

the Manager, International Branch, ANM– 

116; or the EASA (or its delegated agent). 

(x) Credit for Certain Previous Actions 

This paragraph provides credit for the 

inspections required by paragraphs (r), (s), (t), 

(u), and (w) of this AD only for the inspected 

area for rudders identified in tables 4a and 

4b to paragraph (c) of this AD, if the area 

passed the inspection before the effective 

date of this AD using Airbus Service Bulletin 

A320–55–1035, dated February 17, 2010 (for 

Model A320 airplanes); Airbus Service 

Bulletin A320–55–1036, dated February 17, 

2010 (for Model A318 and A321 airplanes); 

or Airbus Service Bulletin A320–55–1037, 

dated February 17, 2010 (for Model A319 

airplanes). For all other inspected areas, the 

repetitive inspections required by paragraph 

(s), (t), and (w) of this AD are still required. 

(y) New ELCh Inspection and Repairs for 

Certain Rudders 

For rudders identified in tables 5a and 5b 

to paragraph (c) of this AD: Within 4,500 

flight cycles but not sooner than 4,000 flight 

cycles after the sampling inspection, perform 

an ELCh inspection for damage on the rudder 

trailing edge area, in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A320–55–1035, Revision 01, 

dated July 2, 2010 (for Model A320 

airplanes); Airbus Service Bulletin A320–55– 

1036, Revision 01, dated July 2, 2010 (for 

Model A318 and A321 airplanes); or Airbus 

Service Bulletin A320–55–1037, Revision 01, 

dated July 2, 2010 (for Model A319 

airplanes). Repeat the inspection within 

4,500 flight cycles, but not sooner than 4,000 

flight cycles after the last inspection. If any 

damage is found during any inspection 

required by paragraph (y) of this AD: Before 

further flight, repair the damage using a 

method approved by either the Manager, 

International Branch, ANM–116; or the 

EASA (or its delegated agent). 

(z) Credit for Certain Other Previous Actions 

This paragraph provides credit for the 

inspection required by paragraph (y) of this 

AD only for the inspected area for rudders 

identified in tables 5a and 5b to paragraph (c) 

of this AD that have passed the inspection 

before the effective date of this AD using 

Airbus Service Bulletin A320–55–1035, 

dated February 17, 2010 (for Model A320 

airplanes); Airbus Service Bulletin A320–55– 

1036, dated February 17, 2010 (for Model 

A318 and A321 airplanes); or Airbus Service 

Bulletin A320–55–1037, dated February 17, 

2010 (for Model A319 airplanes). For all 

inspection areas, the repetitive inspections 

required by paragraph (y) of this AD are still 

required. 


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60072 Federal Register / Vol. 77, No. 191 / Tuesday, October 2, 2012 / Proposed Rules 

(aa) New Repetitive Inspections of Rudders 

Identified in Table 6 to Paragraph (c) of This 

AD 

For rudders identified in table 6 to 

paragraph (c) of this AD, do the actions 

specified in paragraphs (aa)(1), (aa)(2), 

(aa)(3), and (aa)(4) of this AD, in accordance 

with Airbus AOT A320–55A1038, Revision 

02, dated September 28, 2009. For this 

paragraph, ‘‘reference date’’ is defined as the 

date when the rudder will accumulate 20,000 

total flight cycles from its first installation on 

an airplane. 

(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. 

(bb) New De-Bonding Corrective Actions 

In case of de-bonding found during any 

inspection required by paragraph (aa) 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. 

(cc) New Restoration of Vacuum Loss Holes 

If no de-bonding is found during any 

inspection required by paragraph (aa) of this 

AD: Before further flight, restore the vacuum 

loss holes by a permanent restoration with 

resin, in accordance with Note 3 of Airbus 

AOT A320–55A1038, Revision 02, dated 

September 28, 2009. Before doing the resin 

injection, do a local ultrasound inspection in 

reinforced areas, and a thermography 

inspection in other areas, for damage, in 

accordance with Note 3 of Airbus AOT 

A320–55A1038, Revision 02, dated 

September 28, 2009. If any damage is found 

during any inspection required by this 

paragraph: Before further flight, repair the 

damage using a method approved by either 

the Manager, International Branch, ANM– 

116; or the EASA (or its delegated agent). 

(dd) New Reporting for Paragraphs (n), (o), 

(r), (s), (t), (u), (y), and (aa) of This AD 

At the applicable time specified in 

paragraph (dd)(1) or (dd)(2) of this AD, 

submit a report of the findings (both positive 

and negative) of each inspection required by 

paragraphs (n), (o), (r), (s), (t), (u), (y), and 

(aa) 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, email 

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, email 

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, email 

nicolas.seynaeve@airbus.com. 

(1) For any inspection done on or after the 

effective date of this AD: Submit the report 

within 10 days after the inspection. 

(2) For any inspection done before the 

effective date of this AD: Submit the report 

within 10 days after the effective date of this 

AD. 

(ee) New Parts Installation Limitation 

As of the effective date of this AD, no 

rudder listed in table 1, 2, 3, 4a, 4b, 5a, 5b, 

or 6 to paragraph (c) of this AD may be 

installed on any airplane, unless the rudder 

is in compliance with the requirements of 

this AD. 

(ff) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Branch, ANM–116, 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: 

Sanjay Ralhan, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

telephone (425) 227–1405; 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. 

(gg) Related Information 

(1) Refer to MCAI EASA Airworthiness 

Directive 2010–0164, dated August 5, 2010, 

and the following service information, for 

related information. 

(i) Airbus AOT A320–55A1038, dated 

April 22, 2009. 

(ii) Airbus AOT A320–55A1038, Revision 

01, dated June 10, 2009. 

(iii) Airbus AOT A320–55A1038, Revision 

02, dated September 28, 2009. 

(iv) Airbus AOT A320–55A1039, dated 

November 4, 2009. 

(v) Airbus Service Bulletin A320–55–1035, 

Revision 01, dated July 2, 2010. 

(vi) Airbus Service Bulletin A320–55– 

1036, Revision 01, dated July 2, 2010. 

(vii) Airbus Service Bulletin A320–55– 

1037, Revision 01, dated July 2, 2010. 

(viii) Airbus Technical Disposition TD/K4/ 

S2/27051/2009, Issue B, dated February 25, 

2009. 

(ix) Airbus Technical Disposition TD/K4/ 

S2/27086/2009, Issue E, dated September 17, 

2009. 

(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; email 

account.airworth-eas@airbus.com; Internet 

http://www.airbus.com. You may review 

copies of the referenced service information 

at the FAA, Transport Airplane Directorate, 

1601 Lind Avenue SW., Renton, WA. For 

information on the availability of this 

material at the FAA, call 425–227–1221. 

Issued in Renton, Washington, on 

September 21, 2012. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2012–24175 Filed 10–1–12; 8:45 am] 

BILLING CODE 4910–13–P 


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