81884 Federal Register / Vol. 76, No. 250 / Thursday, December 29, 2011 / Proposed Rules 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2011–1327; Directorate 

Identifier 2011–NM–091–AD] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt 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 

proposed 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 

proposed AD would require modifying 

the NLG main fitting by adding primer 

paint to the cadmium around the dowel 

bush holes. We are proposing this AD to 

prevent NLG main fitting rupture, 

which could result in an NLG collapse. 

DATES: We must receive comments on 

this proposed AD by February 13, 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 W12–140, 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 SAS— 

Airworthiness Office—EAL, 1 Rond 

Point Maurice Bellonte, 31707 Blagnac 

Cedex, France; telephone +33 5 61 93 36 

96; fax +33 5 61 93 45 80; email 

airworthiness.A330-A340@airbus.com; 

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

may review copies of the referenced 

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. 

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: 

Vladimir Ulyanov, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue SW., Renton, 

Washington 98057–3356; phone: (425) 

227–1138; 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–2011–1327; Directorate Identifier 

2011–NM–091–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 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Community, has issued EASA 

Airworthiness Directive 2011–0032, 

dated March 1, 2011 (referred to after 

this as ‘‘the MCAI’’), 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. 

Relevant Service Information 

Airbus has issued Mandatory Service 

Bulletins A330–32–3241, dated 

November 26, 2010; and A340–32–4282, 

dated November 26, 2010. 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. 

Costs of Compliance 

Based on the service information, we 

estimate that this proposed AD would 

affect about 55 products of U.S. registry. 

We also estimate that it would take 

about 66 work-hours per product to 

comply with the basic requirements of 

this proposed AD. The average labor 

rate is $85 per work-hour. Required 

parts would cost about $10,000 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, we estimate the cost of the 

proposed AD on U.S. operators to be 

$858,550, or $15,610 per product. 

Authority for This Rulemaking 

Title 49 of the United States Code 

specifies the FAA’s authority to issue 

rules on aviation safety. Subtitle I, 

section 106, describes the authority of 

the FAA Administrator. ‘‘Subtitle VII: 

Aviation Programs,’’ describes in more 

detail the scope of the Agency’s 

authority. 

We are issuing this rulemaking under 

the authority described in ‘‘Subtitle VII, 

Part A, Subpart III, Section 44701: 

General requirements.’’ Under that 


wreier-aviles on DSK3TPTVN1PROD with PROPOSALS
Federal Register / Vol. 76, No. 250 / Thursday, December 29, 2011 / Proposed Rules 81885 

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); and 

3. Will not have a significant 

economic impact, positive or negative, 

on a substantial number of small entities 

under the criteria of the Regulatory 

Flexibility Act. 

We prepared a regulatory evaluation 

of the estimated costs to comply with 

this 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: 

PART 39—AIRWORTHINESS 

DIRECTIVES 

1. The authority citation for part 39 

continues to read as follows: 

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

§ 39.13 [Amended] 

2. The FAA amends § 39.13 by adding 

the following new AD: 

Airbus: Docket No. FAA–2011–1327; 

Directorate Identifier 2011–NM–091–AD. 

(a) Comments Due Date 

We must receive comments by February 

13, 2012. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Airbus Model A330– 

223F, –243F, –201, –202, –203, –223, –243, 

–301, –302, –303, –321, –322, –323, –341, 

–342, and –343 airplanes; and Model A340– 

211, –212, –213, –311, –312, and –313 

airplanes; certificated in any category; all 

manufacturer serial numbers, except 

airplanes on which Airbus modification 

200616 has been embodied in production. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 32: Landing gear. 

(e) Reason 

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. We are issuing this AD to 

prevent NLG main fitting rupture, which 

could result in an NLG collapse. 

(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) Actions 

At the later of the times specified in 

paragraph (g)(1), (g)(2), or (g)(3) of this AD, 

as applicable, modify the NLG main fitting by 

adding primer paint to the cadmium around 

the dowel bush holes, in accordance with the 

Accomplishment Instructions of Airbus 

Mandatory Service Bulletin A330–32–3241, 

dated November 26, 2010 (for Model A330– 

200 and –300 airplanes); or A340–32–4282, 

dated November 26, 2010 (for Model A340– 

200 and –300 airplanes). 

(1) Within 60 months since first flight of 

the NLG on any airplane. 

(2) Within 60 months since first flight of 

the NLG on any airplane after the most recent 

overhaul of the NLG. 

(3) Within 24 months after the effective 

date of this AD. 

(h) 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: 

Vladimir Ulyanov, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, Washington 98057– 

3356; phone: (425) 227–1138; fax: (425) 227– 

1149. Information may be emailed to: 

9-ANM-116-AMOC-REQUESTS@faa.gov. 

Before using any approved AMOC, notify 

your appropriate principal inspector, or 

lacking a principal inspector, the manager of 

the local flight standards district office/ 

certificate holding district office. The AMOC 

approval letter must specifically reference 

this AD. 

(2) Airworthy Product: For any requirement 

in this AD to obtain corrective actions from 

a manufacturer or other source, use these 

actions if they are FAA-approved. Corrective 

actions are considered FAA-approved if they 

are approved by the State of Design Authority 

(or their delegated agent). You are required 

to assure the product is airworthy before it 

is returned to service. 

(i) Related Information 

Refer to MCAI European Aviation Safety 

Agency (EASA) Airworthiness Directive 

2011–0032, dated March 1, 2011; Airbus 

Mandatory Service Bulletin A330–32–3241, 

dated November 26, 2010; and Airbus 

Mandatory Service Bulletin A340–32–4282, 

dated November 26, 2010; for related 

information. 

Issued in Renton, Washington, on 

December 16, 2011. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2011–33341 Filed 12–28–11; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2011–0223; Directorate 

Identifier 2010–NM–161–AD] 

RIN 2120–AA64 

Airworthiness Directives; Goodrich 

Evacuation Systems Approved Under 

Technical Standard Order (TSO) TSO– 

C69b and Installed on Airbus Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Supplemental notice of 

proposed rulemaking (NPRM); 

reopening of comment period. 

SUMMARY: We are revising an earlier 

proposed airworthiness directive (AD) 

for Goodrich Evacuation Systems 

approved under Technical Standard 

Order (TSO) TSO–C69b and installed on 

Airbus Model A330–200 and –300 series 

airplanes, Model A340–200 and –300 

series airplanes, and Model A340–500 

and –600 series airplanes. That NPRM 

proposed to supersede an existing AD. 

That NPRM proposed inspecting to 

determine the part number of the 

pressure relief valves on the affected 

Goodrich evacuation systems, replacing 

certain pressure relief valves, and 

adding airplanes to the applicability. 

That NPRM was prompted by reports 

that during workshop testing, certain 

pressure relief valves, which were 

required by the existing AD, did not seal 


wreier-aviles on DSK3TPTVN1PROD with PROPOSALS