This section of the FEDERAL REGISTER

contains regulatory documents having general

applicability and legal effect, most of which

are keyed to and codified in the Code of

Federal Regulations, which is published under

50 titles pursuant to 44 U.S.C. 1510.

The Code of Federal Regulations is sold by

the Superintendent of Documents. Prices of

new books are listed in the first FEDERAL

REGISTER issue of each week.

Rules and Regulations Federal Register

29207 

Vol. 77, No. 96 

Thursday, May 17, 2012 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2011–1321; Directorate 

Identifier 2011–NM–045–AD; Amendment 

39–17047; AD 2012–09–12] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are superseding an 

existing airworthiness directive (AD) for 

certain Airbus 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, and –131 

airplanes; equipped with an additional 

center tank (ACT). That AD currently 

requires identifying the part number of 

the ACT and, for certain ACTs, 

replacing the outer ACT manhole cover 

and seal. This new AD requires 

modifying certain ACTs by replacing the 

manhole seal with a new seal; adding 

certain ACT equipped airplanes to the 

applicability; and removing Model 

A320–111 airplanes from the 

applicability. This AD was prompted by 

reports that the modification required 

by the current AD was not fully 

effective. We are issuing this AD to 

prevent fuel and/or vapor leakage, 

which could result in a combustible fuel 

vapor/air mixture in the cargo 

compartment, and consequent fire risk. 

DATES: This AD becomes effective June 

21, 2012. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of June 21, 2012. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain other publication listed in 

this AD as of December 19, 2005 (70 FR 

69067, November 14, 2005). 

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: 

Sanjay Ralhan, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue SW., Renton, 

Washington 98057–3356; telephone 

(425) 227–1405; 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 December 15, 2011 (76 FR 

77934), and proposed to supersede AD 

2005–23–02, Amendment 39–14360 (70 

FR 69067, November 14, 2005). That 

NPRM proposed to correct an unsafe 

condition for the specified products. 

The MCAI states: 

Following an automatic ACT fuel transfer 

failure on an A319, it was noted that the ACT 

manhole cover seals were extruded, allowing 

leakage. 

This condition, if not corrected, can lead 

to fuel and/or vapour leakage, possibly 

resulting in a combustible fuel vapour/air 

mixture in the cargo compartment, which 

would constitute a fire risk. 

DGAC France AD F–2004–038 [which 

corresponds to FAA AD 2005–23–02] was 

issued to require the replacement of the ACT 

manhole cover and its seal in accordance 

with SB A320–28–1105, but this 

modification has proved not to be fully 

effective. Therefore, it is necessary to replace 

the seal material and to change the 

installation process in order to prevent such 

seal deformation and possibility of leakage. 

For the reasons described above, this 

[EASA] AD supersedes DGAC France AD F– 

2004–038 (EASA approval 2004–2110) and 

requires the replacement of the existing 

manhole seal with a new seal. 

This AD also adds certain ACT 

equipped airplanes, produced after AD 

2005–23–02, Amendment 39–14360 (70 

FR 69067, November 14, 2005) was 

issued, to the applicability. This AD 

also removes Model A320–111 airplanes 

from the applicability because there are 

no operational Model A320–111 

airplanes in the United States and 

Airbus intends to remove this model 

from the EASA Type Certificate Data 

Sheet (TCDS). 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 

have considered the comments received. 

Support for NPRM (76 FR 77934, 

December 15, 2011) 

Thomas Hayden Barnes stated he 

supports efforts to ensure airline safety 

and the NPRM (76 FR 77934, December 

15, 2011) appears reasonable. 

US Airways stated it supports the 

intent of the NPRM (76 FR 77934, 

December 15, 2011). 

Request to Revise Cost Estimate 

US Airways stated that 

accomplishment of the modification 

specified in Airbus Mandatory Service 

Bulletin A320–28–1162, Revision 02, 

dated December 18, 2009, will take 14.5 

man-hours per fuel tank. We infer that 

the commenter wants the preamble 

section of the final rule changed to 

reflect 14.5 work-hours per fuel tank. 

We agree. The total work-hours for 

accessing, modifying a fuel tank, and 

closing are estimated at 14.5 work-hours 

per fuel tank. We have changed the cost 

section in the final rule to reflect an 

estimate of 15 work-hours per fuel tank 

to comply with the new basic 

requirements of this AD. We have also 

revised the estimated cost of the AD on 

U.S. operators to be $919,275 (based on 

one fuel tank per airplane), or $1,275 

per fuel tank. 

Request To Revise the Parts Cost 

Statement 

US Airways requested we revise the 

parts cost statement of the NPRM (76 FR 

77934, December 15, 2011) to include 

the parts cost for the actions required by 

AD 2005–23–02, Amendment 39–14360 

(70 FR 69067, November 14, 2005) and 

that are retained in the NPRM. The 

commenter stated that the parts costs 

are not covered under warranty. 

We partially agree. Airbus Service 

Bulletin A320–28–1105, Revision 02, 

dated March 11, 2005, states that Airbus 

will provide the material at no charge 


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29208 Federal Register / Vol. 77, No. 96 / Thursday, May 17, 2012 / Rules and Regulations 

for orders placed before December 31, 

2003. Therefore, we agree that some 

operators may have had to pay for parts. 

We do not agree to add parts costs to 

this final rule, but we have added a 

statement to the cost section for actions 

that are required by AD 2005–23–02, 

Amendment 39–14360 (70 FR 69067, 

November 14, 2005) and retained in this 

AD. Where the service information lists 

required parts costs that are covered 

under warranty, we have assumed that 

there will be no charge for these parts. 

As we do not control warranty coverage 

for affected parties, some parties may 

incur costs higher than estimated here. 

Request To Allow Seal Replacement 

Without ACT Removal 

US Airways requested the NPRM (76 

FR 77934, December 15, 2011) be 

changed to allow installation of the 

seals without removing the ACTs from 

the airplane as specified in AD 2005– 

23–02, Amendment 39–14360 (70 FR 

69067, November 14, 2005). The 

commenter stated that in order to 

replace the seal on ACT number 2, only 

the integrated impact wall needs to be 

removed; and for seal replacement on 

ACT number 1, the ACT number 2 has 

to be rolled rearward approximately two 

feet to provide access to ACT number 1, 

which can then have its seal replaced 

without ACT removal. The commenter 

provided references to its internal 

documentation to support its request. 

We disagree. US Airways request does 

not substantiate the detailed procedures 

needed for deviation from the Airbus 

recommended actions specified in 

Airbus Mandatory Service Bulletin 

A320–28–1162, Revision 02, dated 

December 18, 2009, for installation of 

seals on the ACT number 1 and ACT 

number 2. In addition, Airbus foresees 

a potential safety hazard for mechanics 

if seals are installed without removing 

the ACTs due to inadequate ventilation 

and high concentration of fuel vapor. 

Under the provisions of paragraph (l) 

of this AD, we will consider requests for 

approval of alternate method of 

compliance (AMOC) if sufficient data 

are submitted to substantiate that 

deviation from the specified procedures 

in Airbus Mandatory Service Bulletin 

A320–28–1162, Revision 02, dated 

December 18, 2009, would provide an 

acceptable level of safety. We have not 

changed the AD in this regard. 

Explanation of Additional Changes 

Made to the AD 

We have revised the heading for 

paragraph (k) of this AD and the 

wording in paragraphs (h) and (k) of this 

AD; these changes have not changed the 

intent of those paragraphs. 

Conclusion 

We reviewed the available data, 

including the comments received, and 

determined that air safety and the 

public interest require adopting the AD 

as proposed, except for minor editorial 

changes and/or changes to the cost 

section that add the accessing and 

closing costs. We have determined that 

these minor changes: 

• Are consistent with the intent that 

was proposed in the NPRM (76 FR 

77934, December 15, 2011) for 

correcting the unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the NPRM (76 FR 77934, 

December 15, 2011). 

Costs of Compliance 

Based on the service information, we 

estimate that this AD affects 721 

products of U.S. registry. 

The actions that are required by AD 

2005–23–02, Amendment 39–14360 (70 

FR 69067, November 14, 2005) and 

retained in this AD take about 1 workhour per product, at an average labor 

rate of $85 per work hour. Required 

parts cost about $0 per product. Where 

the service information lists required 

parts costs that are covered under 

warranty, we have assumed that there 

will be no charge for these parts. As we 

do not control warranty coverage for 

affected parties, some parties may incur 

costs higher than estimated here. Based 

on these figures, the estimated cost of 

the currently required actions is $85 per 

product. 

We estimate that it would take about 

15 work-hours per fuel tank to comply 

with the new basic requirements of this 

AD. The average labor rate is $85 per 

work-hour. Where the service 

information lists required parts costs 

that are covered under warranty, we 

have assumed that there will be no 

charge for these parts. As we do not 

control warranty coverage for affected 

parties, some parties may incur costs 

higher than estimated here. Based on 

these figures, we estimate the cost of the 

AD on U.S. operators to be $919,275, or 

$1,275 per fuel tank. 

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 that this 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 AD and placed it in the AD docket. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http:// 

www.regulations.gov; or in person at the 

Docket Operations office between 9 a.m. 

and 5 p.m., Monday through Friday, 

except Federal holidays. The AD docket 

contains the NPRM (76 FR 77934, 

December 15, 2011), the regulatory 

evaluation, any comments received, and 

other information. The street address for 

the Docket Operations office (telephone 

(800) 647–5527) is in the ADDRESSES

section. Comments will be available in 

the AD docket shortly after receipt. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

Adoption of the Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA amends 14 CFR part 39 as 

follows: 


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Federal Register / Vol. 77, No. 96 / Thursday, May 17, 2012 / Rules and Regulations 29209 

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) 

2005–23–02, Amendment 39–14360 (70 

FR 69067, November 14, 2005), and 

adding the following new AD: 

2012–09–12 Airbus: Amendment 39–17047. 

Docket No. FAA–2011–1321; Directorate 

Identifier 2011–NM–045–AD. 

(a) Effective Date 

This airworthiness directive (AD) becomes 

effective June 21, 2012. 

(b) Affected ADs 

This AD supersedes AD 2005–23–02, 

Amendment 39–14360 (70 FR 69067, 

November 14, 2005). 

(c) Applicability 

This AD applies to Airbus airplanes listed 

in paragraphs (c)(1), (c)(2), and (c)(3) of this 

AD; certificated in any category; all serial 

numbers; if equipped with one or more 

additional center tank(s) (ACT) with a part 

number (P/N) listed in table 1 of this AD. 

This AD does not apply to airplanes already 

having received Airbus modification 38036 

in production. 

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

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

(2) Model A320–211, –212, –214, –231, 

–232, and –233 airplanes. 

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

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

TABLE 1—AFFECTED ACT PART NUMBERS FOR APPLICABILITY

D2827091100000 D2827105100200 D2827105300600 D2827105500400 

D2827091100200 D2827105100400 D2827105300800 D2827105500600 

D2827091100400 D2827105100600 D2827105400000 D2827105500800 

D2827091100600 D2827105100800 D2827105400200 D2827105600000 

D2827091100800 D2827105200000 D2827105400400 D2827105600200 

D2827091101000 D2827105200200 D2827105400600 D2827105600400 

D2827091300000 D2827105200400 D2827105400800 D2827105600600 

D2827091300200 D2827105200600 D2827105401000 D2827105600800 

D2827091300400 D2827105200800 D2827105401200 D2827107500000 

D2827091300600 D2827105300000 D2827105401400 D2827107500200 

D2827091300800 D2827105300200 D2827105500000 D2827107500400 

D2827105100000 D2827105300400 D2827105500200 D2827107500600 

(d) Subject 

Air Transport Association (ATA) of 

America Code 28, Fuel. 

(e) Reason 

This AD was prompted by reports that the 

modification required by AD 2005–23–02, 

Amendment 39–14360 (70 FR 69067, 

November 14, 2005), was not fully effective. 

We are issuing this AD to prevent fuel and/ 

or vapor leakage, which could result in a 

combustible fuel vapor/air mixture in the 

cargo compartment, and consequent fire risk. 

(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 Determination of Part Number 

With New Sealing Procedures 

This paragraph restates the requirements of 

paragraph (f) of AD 2005–23–02, Amendment 

39–14350 (70 FR 69067, November 14, 2005), 

with new sealing procedures. Within 30 days 

(for Model A319–111, –112, –113, –114, 

–115, –131, –132, and –133 airplanes) or 12 

months (for Model A320–211, –212, –214, 

–231, –232, and –233 airplanes; and Model 

A321–111, –112, and –131 airplanes) after 

December 19, 2005 (the effective date of AD 

2005–23–02, Amendment 39–14360 (70 FR 

69067, November 14, 2005): Determine 

whether the P/N of each ACT installed on the 

airplane is included in table 2 of this AD. If 

no ACT installed on the airplane has a P/N 

included in table 2 of this AD, no further 

work is required by this paragraph. 

TABLE 2—AFFECTED ACT P/NS FOR AD 2005–23–02, AMENDMENT 39–14360 

[70 FR 69067, November 14, 2005] 

D2827091100000 D2827105100200 D2827105300400 D2827105500200 

D2827091100200 D2827105100400 D2827105400000 D2827105500400 

D2827091100600 D2827105200000 D2827105400200 D2827105600000 

D2827091300000 D2827105200200 D2827105400400 D2827105600200 

D2827091300200 D2827105200400 D2827105400600 D2827105600400 

D2827091300400 D2827105300000 D2827105400800 D2827107500000 

D2827105100000 D2827105300200 D2827105500000 D2827107500200 

(h) Retained Manhole Cover/Seal 

Replacement 

This paragraph restates the requirements of 

paragraph (g) of AD 2005–23–02, 

Amendment 39–14350 (70 FR 69067, 

November 14, 2005). Within 30 days (for 

Model A319–111, –112, –113, –114, –115, 

–131, –132, and –133 airplanes) or 12 months 

(for Model A320–211, –212, –214, –231, 

–232, and –233 airplanes; and Model A321– 

111, –112, and –131 airplanes) after 

December 19, 2005 (the effective date of AD 

2005–23–02, Amendment 39–14360 (70 FR 

69067, November 14, 2005)): For each ACT 

P/N listed in table 2 of this AD: Before 

further flight, replace the outer ACT manhole 

cover with a reinforced manhole cover and 

replace the outer manhole cover seal with a 

new seal, in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A320–28–1105, Revision 02, 

dated March 11, 2005. This paragraph 

provides credit for the replacements required 

by this paragraph if the replacements were 

performed before December 19, 2005, using 

Airbus Service Bulletin A320–28–1105, 

Revision 01, dated March 18, 2003; and 

Airbus Service Bulletin A320–28–1105, 

dated October 22, 2002. As of the effective 

date of this AD, doing the manhole cover seal 

replacement required by paragraph (i) of this 

AD, terminates the manhole cover seal 

replacement required by this paragraph. 

(i) ACT Modification 

Within 3,000 flight cycles or 24 months, 

whichever occurs first after the effective date 

of this AD: Modify the affected ACT listed in 

table 1 of this AD by replacing the manhole 

seal, in accordance with the Accomplishment 

Instructions of Airbus Mandatory Service 

Bulletin A320–28–1162, Revision 02, dated 

December 18, 2009. Accomplishing the 

manhole cover sealing replacement specified 

in this paragraph terminates the manhole 


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29210 Federal Register / Vol. 77, No. 96 / Thursday, May 17, 2012 / Rules and Regulations 

cover sealing replacement required in 

paragraph (h) of this AD. 

(j) Parts Installation 

As of the effective date of this AD, no 

person may install an ACT, having a part 

number is listed in table 1 of this AD, on any 

airplane unless it has been modified prior to 

its installation, in accordance with Airbus 

Mandatory Service Bulletin A320–28–1162, 

Revision 02, dated December 18, 2009. 

(k) Credit for Previous Actions 

This paragraph provides credit for the 

modification required by paragraph (i) of this 

AD, if the modification was performed before 

the effective date of this AD using Airbus 

Mandatory Service Bulletin A320–28–1162, 

dated February 6, 2008; or Revision 01, dated 

July 16, 2008. 

(l) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

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. 

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, Washington 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. 

(m) Related Information 

Refer to MCAI European Aviation Safety 

Agency (EASA) Airworthiness Directive 

2010–0177, dated August 30, 2010; Airbus 

Mandatory Service Bulletin A320–28–1162, 

Revision 02, dated December 18, 2009; and 

Airbus Service Bulletin A320–28–1105, 

Revision 02, dated March 11, 2005; for 

related information. 

(n) Material Incorporated by Reference 

(1) You must use the following service 

information to do the actions required by this 

AD, unless the AD specifies otherwise. The 

Director of the Federal Register approved the 

incorporation by reference (IBR) of the 

following service information under 5 U.S.C. 

552(a) and 1 CFR part 51 on the date 

specified. 

(2) The following service information was 

approved for IBR as of the effective date of 

this AD: 

(i) Airbus Mandatory Service Bulletin 

A320–28–1162, Revision 02, dated December 

18, 2009. 

(3) The following service information was 

approved for IBR on December 19, 2005 (70 

FR 69067, November 14, 2005): 

(i) Airbus Service Bulletin A320–28–1105, 

Revision 02, dated March 11, 2005. 

(4) For Airbus 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.airwortheas@airbus.com; Internet http:// 

www.airbus.com. 

(5) 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. 

(6) You may also review copies of the 

service information that is incorporated by 

reference at the National Archives and 

Records Administration (NARA). For 

information on the availability of this 

material at an NARA facility, call 202–741– 

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

federal_register/code_of_federal_regulations/

ibr_locations.html. 

Issued in Renton, Washington, on May 1, 

2012. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2012–11490 Filed 5–16–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2011–1327; Directorate 

Identifier 2011–NM–091–AD; Amendment 

39–17048; AD 2012–09–13] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

Airbus Model A330–200 freighter series 

airplanes; Model A330–200 and –300 

series airplanes; and Model A340–200 

and –300 series airplanes. This AD was 

prompted by a report of corrosion found 

on the main fitting of the nose landing 

gear (NLG) leg in the vicinity of the 

dowel pin bushes retaining the lower 

steering flange. This AD requires 

modifying the NLG main fitting by 

adding primer paint to the cadmium 

around the dowel bush holes. We are 

issuing this AD to prevent NLG main 

fitting rupture, which could result in an 

NLG collapse. 

DATES: This AD becomes effective June 

21, 2012. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of June 21, 2012. 

ADDRESSES: You may examine the AD 

docket on the Internet at http:// 

www.regulations.gov or in person at the 

U.S. Department of Transportation, 

Docket Operations, M–30, West 

Building Ground Floor, Room W12–140, 

1200 New Jersey Avenue SE., 

Washington, DC. 

FOR FURTHER INFORMATION CONTACT: 

Vladimir Ulyanov, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue SW., Renton, 

Washington 98057–3356; telephone 

425–227–1138; fax 425–227–1149. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to include an AD that would 

apply to the specified products. That 

NPRM was published in the Federal 

Register on December 29, 2011 (76 FR 

81884). That NPRM proposed to correct 

an unsafe condition for the specified 

products. The MCAI states: 

Corrosion has been found on the main 

fitting of the NLG leg in the vicinity of the 

dowel pin bushes retaining the lower steering 

flange on A330/A340 aeroplanes. The 

majority of parts have been reworked and 

returned to service. 

This corrosion, if not avoided, could lead 

to the NLG main fitting rupture, possibly 

resulting in a NLG collapse, which would 

constitute an unsafe condition. 

In order to maintain the structural integrity 

of the NLG, this [EASA] AD requires the 

accomplishment of a modification which 

consists in adding primer paint to the 

cadmium around the dowel bush holes on 

the main fitting, in order to provide further 

protection against cadmium degradation. 

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 

received no comments on the NPRM (76 

FR 81884, December 29, 2011) or on the 

determination of the cost to the public. 


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