This section of the FEDERAL REGISTER

contains notices to the public of the proposed

issuance of rules and regulations. The

purpose of these notices is to give interested

persons an opportunity to participate in the

rule making prior to the adoption of the final

rules.

Proposed Rules Federal Register

49386 

Vol. 77, No. 159 

Thursday, August 16, 2012 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–0807; Directorate 

Identifier 2011–NM–191–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 all 

Airbus Model A318–111 and –112 

airplanes, and Model A319, A320, and 

A321 series airplanes. This proposed 

AD was prompted by reports of silicon 

particles inside the oxygen generator 

manifolds, which had chafed from the 

mask hoses during installation onto the 

generator outlets. This proposed AD 

would require identifying the part 

number and serial number of each 

passenger oxygen container, replacing 

the oxygen generator manifold of the 

affected oxygen container with a 

serviceable manifold, and performing an 

operational check of the manual mask 

release and corrective actions if 

necessary. We are proposing this AD to 

detect and correct non-serviceable 

oxygen generator manifolds, which 

could reduce or block the oxygen 

supply, which could result in injury to 

passengers when oxygen supply is 

needed. 

DATES: We must receive comments on 

this proposed AD by October 1, 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 Airbus 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. For B/E 

service information identified in this 

proposed AD, contact B/E Aerospace 

Systems GmbH, Revalstrasse 1, 23560 

Lubeck, Germany; telephone (49) 451 

4093–2976; fax (49) 451 4093–4488. 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: 

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: 

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–2012–0807; Directorate Identifier 

2011–NM–191–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 2011–0167, 

dated September 6, 2011 (referred to 

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

unsafe condition for the specified 

products. The MCAI states: 

During production of passenger oxygen 

containers, the manufacturer B/E Aerospace 

detected some silicon particles inside the 

oxygen generator manifolds. Investigation 

revealed that those particles (chips) had 

chafed from the mask hoses during 

installation onto the generator outlets. It was 

discovered that a defective mask hose 

installation device had caused the chafing. 

This condition, if not detected and corrected, 

could reduce or block the oxygen supply, 

possibly resulting in injury to passengers 

when oxygen supply is needed. 

For the reasons described above, this [EASA] 

AD requires the identification and 

modification of the affected oxygen container 

assemblies. This AD also prohibits the 

installation of the affected containers on any 

aeroplane as replacement parts. 

Required actions also include replacing 

the oxygen generator manifold of the 

affected oxygen container with a 

serviceable manifold, and doing an 

operational check of the manual mask 

release and corrective actions if 

necessary. You may obtain further 

information by examining the MCAI in 

the AD docket. 

Relevant Service Information 

Airbus has issued Service Bulletin 

A320–35A1047, dated March 29, 2011. 

B/E AEROSPACE has issued Service 

Bulletin 1XCXX–0100–35–005, Revision 

1, dated December 15, 2012; and 

22CXX–0100–35–003, Revision 1, dated 

December 20, 2011. The actions 

described in this service information are 


wreier-aviles on DSK7SPTVN1PROD with PROPOSALS
Federal Register / Vol. 77, No. 159 / Thursday, August 16, 2012 / Proposed Rules 49387 

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 220 airplanes of U.S. 

registry. We also estimate that it would 

take about 3 work-hours per oxygen 

container to comply with the basic 

requirements of this proposed AD. The 

average number of oxygen containers 

per airplane is 50. The average labor rate 

is $85 per work-hour. Required parts 

would 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, we estimate the cost of 

the proposed AD on U.S. operators to be 

$2,805,000, or $12,750 per airplane. 

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: 

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–2012–0807; Directorate Identifier 2011–NM–191–AD. 

(a) Comments Due Date 

We must receive comments by October 1, 

2012. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Airbus Model A318– 

111 and –112 airplanes; A319–111, –112, 

–113, –114, –115, –131, –132, and –133 

airplanes; A320–111, –211, –212, –214, –231, 

–232, and –233 airplanes; A321–111, –112, 

–131, –211, –212, –213, –231, and –232 

airplanes; certificated in any category; all 

manufacturer serial numbers (MSN). 

(d) Subject 

Air Transport Association (ATA) of 

America Code 35: Oxygen. 

(e) Reason 

This AD was prompted by reports of 

silicon particles inside the oxygen generator 

manifolds, which had chafed from the mask 

hoses during installation onto the generator 

outlets. We are issuing this AD to detect and 

correct non-serviceable oxygen generator 

manifolds, which could reduce or block the 

oxygen supply, which could result in injury 

to passengers when oxygen supply is needed. 

(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) Part Number and Serial Number 

Identification 

Within 4,500 flight cycles, or 6,000 flight 

hours, or 20 months, whichever occurs first, 

after the effective date of this AD, identify the 

part number and serial number of each 

passenger oxygen container. A review of 

airplane maintenance records is acceptable in 

lieu of this identification if the part number 

and serial number of the oxygen container 

can be conclusively determined from that 

review. 

(h) Replacement 

If the part number and serial number of the 

container are listed in table 2 and table 1 of 

this AD: Within the compliance time 

specified in paragraph (g) of this AD, replace 

the oxygen generator manifold of the affected 

oxygen container with a serviceable manifold 

and do an operational check of the manual 

mask release, in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A320–35A1047, dated 

March 29, 2011, except as provided by 

paragraphs (i)(1) through (i)(4) of this AD. If 

the operational check fails, before further 

flight, repair, using a method approved by 

either the Manager, International Branch, 

ANM 116, Transport Airplane Directorate, 

FAA; or the European Aviation Safety 

Agency (or its delegated agent). 

TABLE 1—AFFECTED SERIAL NUMBERS

ARBA–0000 to ARBA–9999 inclusive. 

ARBB–0000 to ARBB–9999 inclusive. 

ARBC–0000 to ARBC–9999 inclusive. 

ARBD–0000 to ARBD–9999 inclusive. 

ARBE–0000 to ARBE–9999 inclusive. 

BEBF–0000 to BEBF–9999 inclusive. 

BEBH–0000 to BEBH–9999 inclusive. 

BEBK–0000 to BEBK–9999 inclusive. 

BEBL–0000 to BEBL–9999 inclusive. 

BEBM–0000 to BEBM–9999 inclusive. 


wreier-aviles on DSK7SPTVN1PROD with PROPOSALS
49388 Federal Register / Vol. 77, No. 159 / Thursday, August 16, 2012 / Proposed Rules 

TABLE 2—PART NUMBER OF THE AFFECTED PASSENGER EMERGENCY OXYGEN CONTAINER ASSEMBLIES * 

Type I—15 Min. 

12C15L215XX0100 ....................... 12C15R335XX0100 ...................... 13C15R215XX0100 ...................... 14C15L335XX0100 

12C15L216XX0100 ....................... 12C15R336XX0100 ...................... 13C15R216XX0100 ...................... 14C15L336XX0100 

12C15L235XX0100 ....................... 12C15R475XX0100 ...................... 13C15R235XX0100 ...................... 14C15L475XX0100 

12C15L236XX0100 ....................... 12C15R476XX0100 ...................... 13C15R236XX0100 ...................... 14C15L476XX0100 

12C15L2F5XX0100 ....................... 12C15R4G5XX0100 ..................... 13C15R2F5XX0100 ...................... 14C15L4G5XX0100 

12C15L2F6XX0100 ....................... 12C15R4G6XX0100 ..................... 13C15R2F6XX0100 ...................... 14C15L4G6XX0100 

12C15L335XX0100 ....................... 13C15L216XX0100 ....................... 13C15R335XX0100 ...................... 14C15R215XX0100 

12C15L336XX0100 ....................... 13C15L235XX0100 ....................... 13C15R336XX0100 ...................... 14C15R216XX0100 

12C15L475XX0100 ....................... 13C15L236XX0100 ....................... 13C15R475XX0100 ...................... 14C15R235XX0100 

12C15L476XX0100 ....................... 13C15L2F5XX0100 ...................... 13C15R476XX0100 ...................... 14C15R236XX0100 

12C15L4G5XX0100 ....................... 13C15L2F6XX0100 ...................... 13C15R4G5XX0100 ..................... 14C15R2F5XX0100 

12C15L4G6XX0100 ....................... 13C15L335XX0100 ....................... 13C15R4G6XX0100 ..................... 14C15R2F6XX0100 

12C15R215XX0100 ....................... 13C15L336XX0100 ....................... 14C15L215XX0100 ....................... 14C15R335XX0100 

12C15R216XX0100 ....................... 13C15L475XX0100 ....................... 14C15L216XX0100 ....................... 14C15R336XX0100 

12C15R235XX0100 ....................... 13C15L476XX0100 ....................... 14C15L235XX0100 ....................... 14C15R475XX0100 

12C15R236XX0100 ....................... 13C15L4G5XX0100 ...................... 14C15L236XX0100 ....................... 14C15R476XX0100 

12C15R2F5XX0100 ....................... 13C15L4G6XX0100 ...................... 14C15L2F5XX0100 ...................... 14C15R4G5XX0100 

12C15R2F6XX0100 ....................... 13C15R215XX0100 ...................... 14C15L2F6XX0100 ...................... 14C15R4G6XX0100 

Type I—22 Min. 

12C22L215XX0100 ....................... 12C22R335XX0100 ...................... 13C22R215XX0100 ...................... 14C22L335XX0100 

12C22L216XX0100 ....................... 12C22R336XX0100 ...................... 13C22R216XX0100 ...................... 14C22L336XX0100 

12C22L235XX0100 ....................... 12C22R475XX0100 ...................... 13C22R235XX0100 ...................... 14C22L475XX0100 

12C22L236XX0100 ....................... 12C22R476XX0100 ...................... 13C22R236XX0100 ...................... 14C22L476XX0100 

12C22L2F5XX0100 ....................... 12C22R4G5XX0100 ..................... 13C22R2F5XX0100 ...................... 14C22L4G5XX0100 

12C22L2F6XX0100 ....................... 12C22R4G6XX0100 ..................... 13C22R2F6XX0100 ...................... 14C22L4G6XX0100 

12C22L335XX0100 ....................... 13C22L216XX0100 ....................... 13C22R335XX0100 ...................... 14C22R215XX0100 

12C22L336XX0100 ....................... 13C22L235XX0100 ....................... 13C22R336XX0100 ...................... 14C22R216XX0100 

12C22L475XX0100 ....................... 13C22L236XX0100 ....................... 13C22R475XX0100 ...................... 14C22R235XX0100 

12C22L476XX0100 ....................... 13C22L2F5XX0100 ...................... 13C22R476XX0100 ...................... 14C22R236XX0100 

12C22L4G5XX0100 ....................... 13C22L2F6XX0100 ...................... 13C22R4G5XX0100 ..................... 14C22R2F5XX0100 

12C22L4G6XX0100 ....................... 13C22L335XX0100 ....................... 13C22R4G6XX0100 ..................... 14C22R2F6XX0100 

12C22R215XX0100 ....................... 13C22L336XX0100 ....................... 14C22L215XX0100 ....................... 14C22R335XX0100 

12C22R216XX0100 ....................... 13C22L475XX0100 ....................... 14C22L216XX0100 ....................... 14C22R336XX0100 

12C22R235XX0100 ....................... 13C22L476XX0100 ....................... 14C22L235XX0100 ....................... 14C22R475XX0100 

12C22R236XX0100 ....................... 13C22L4G5XX0100 ...................... 14C22L236XX0100 ....................... 14C22R476XX0100 

12C22R2F5XX0100 ....................... 13C22L4G6XX0100 ...................... 14C22L2F5XX0100 ...................... 14C22R4G5XX0100 

12C22R2F6XX0100 ....................... 13C22R215XX0100 ...................... 14C22L2F6XX0100 ...................... 14C22R4G6XX0100 

Type II—15 Min. 

22C15L110XX0100 ....................... 22C15L280XX0100 ....................... 22C15R110XX0100 ...................... 22C15R280XX0100 

22C15L120XX0100 ....................... 22C15L290XX0100 ....................... 22C15R120XX0100 ...................... 22C15R290XX0100 

22C15L130XX0100 ....................... 22C15L370XX0100 ....................... 22C15R140XX0100 ...................... 22C15R370XX0100 

22C15L140XX0100 ....................... 22C15L3J0XX0100 ....................... 22C15R150XX0100 ...................... 22C15R3J0XX0100 

22C15L150XX0100 ....................... 22C15L480XX0100 ....................... 22C15R160XX0100 ...................... 22C15R480XX0100 

22C15L160XX0100 ....................... 22C15L4H0XX0100 ...................... 22C15R170XX0100 ...................... 22C15R4H0XX0100 

22C15L170XX0100 ....................... 22C15L4S0XX0100 ...................... 22C15R210XX0100 ...................... 22C15R4S0XX0100 

22C15L210XX0100 ....................... 22C15L4T0XX0100 ...................... 22C15R220XX0100 ...................... 22C15R4T0XX0100 

22C15L220XX0100 ....................... 22C15L680XX0100 ....................... 22C15R240XX0100 ...................... 22C15R6U0XX0100 

22C15L240XX0100 ....................... 22C15L680XX0100 ....................... 22C15R270XX0100.

22C15L270XX0100 ....................... 22C15L6U0XX0100.

Type II—22 Min. 

22C22L110XX0100 ....................... 22C22L280XX0100 ....................... 22C22R110XX0100 ...................... 22C22R280XX0100 

22C22L120XX0100 ....................... 22C22L290XX0100 ....................... 22C22R120XX0100 ...................... 22C22R290XX0100 

22C22L130XX0100 ....................... 22C22L370XX0100 ....................... 22C22R140XX0100 ...................... 22C22R370XX0100 

22C22L140XX0100 ....................... 22C22L3J0XX0100 ....................... 22C22R150XX0100 ...................... 22C22R3J0XX0100 

22C22L150XX0100 ....................... 22C22L480XX0100 ....................... 22C22R160XX0100 ...................... 22C22R480XX0100 

22C22L160XX0100 ....................... 22C22L4H0XX0100 ...................... 22C22R170XX0100 ...................... 22C22R4H0XX0100 

22C22L170XX0100 ....................... 22C22L4S0XX0100 ...................... 22C22R210XX0100 ...................... 22C22R4S0XX0100 

22C22L210XX0100 ....................... 22C22L4T0XX0100 ...................... 22C22R220XX0100 ...................... 22C22R4T0XX0100 

22C22L220XX0100 ....................... 22C22L680XX0100 ....................... 22C22R240XX0100 ...................... 22C22R6U0XX0100 

22C22L240XX0100 ....................... 22C22L6U0XX0100 ...................... 22C22R270XX0100.

22C22L270XX0100.

* Variables XX show the color code of the oxygen container assembly. 


wreier-aviles on DSK7SPTVN1PROD with PROPOSALS
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(i) Exceptions 

(1) Oxygen containers Type I that have 

been modified in accordance with the 

Accomplishment Instructions of B/E 

Aerospace Service Bulletin 1XCXX–0100– 

35–005, Revision 1, dated December 15, 

2012; and oxygen containers Type II that 

have been modified in accordance with the 

Accomplishment Instructions of B/E 

Aerospace Service Bulletin 22CXX–0100–35– 

003, Revision 1, dated December 20, 2011; 

are compliant with the requirements of 

paragraph (h) of this AD. 

(2) Airplanes on which Airbus 

modification 150703 or Airbus modification 

150704 have not been embodied in 

production do not have to comply with the 

requirements of paragraph (h) of this AD, 

unless an oxygen container has been replaced 

since the airplane’s entry into service. 

(3) Airplanes on which Airbus 

modification 150703 or Airbus modification 

150704 have been embodied in production 

and which are not listed by model and MSN 

in Airbus Service Bulletin A320–35A1047, 

dated March 29, 2011, are not subject to the 

requirements of paragraphs (g) and (h) of this 

AD, unless an oxygen container has been 

replaced since the airplane’s entry into 

service. 

(4) Model A319 airplanes that are equipped 

with a gaseous oxygen system for passengers, 

installed in production with Airbus 

modification 33125, do not have the affected 

passenger oxygen containers installed. 

Unless these airplanes have been modified 

in-service (no approved Airbus modification 

exists), the requirements of paragraphs (g) 

and (h) of this AD do not apply to these 

airplanes. 

(j) Parts Installation Limitations 

As of the effective date of this AD, no 

person may install an oxygen container 

having a part number specified in table 2 of 

this AD and having a serial number specified 

in table 1 of this AD, on any airplane, unless 

the container has been modified in 

accordance with the Accomplishment 

Instructions of any of the following service 

bulletins; as applicable: 

(1) Airbus Service Bulletin A320–35A1047, 

dated March 29, 2011. 

(2) B/E AEROSPACE Service Bulletin 

1XCXX–0100–35–005, Revision 1, dated 

December 15, 2012. 

(3) B/E AEROSPACE Service Bulletin 

22CXX–0100–35–003, Revision 1, dated 

December 20, 2011. 

(k) Credit for Previous Actions 

This paragraph provides credit for the 

actions required by paragraph (h) of this AD, 

if those actions were performed before the 

effective date of this AD using the service 

information specified in paragraph (k)(1) or 

(k)(2) of this AD. 

(1) B/E AEROSPACE Service Bulletin 

1XCXX–0100–35–005, dated March 14, 2011. 

(2) B/E AEROSPACE Service Bulletin 

22CXX–0100–35–003, dated March 17, 2011. 

(l) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Branch, 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 

(1) Refer to MCAI European Aviation 

Safety Agency Airworthiness Directive 2011– 

0167, dated September 6, 2011, and the 

service information specified in paragraphs 

(m)(1)(i), (m)(1)(ii), and (m)(1)(iii) of this AD, 

for related information. 

(i) Airbus Service Bulletin A320–35A1047, 

dated March 29, 2011. 

(ii) B/E AEROSPACE Service Bulletin 

1XCXX–0100–35–005, Revision 1, dated 

December 15, 2012. 

(iii) B/E AEROSPACE Service Bulletin 

22CXX–0100–35–003, Revision 1, dated 

December 20, 2011. 

(2) For Airbus 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. For B/E service 

information identified in this proposed AD, 

contact B/E Aerospace Systems GmbH, 

Revalstrasse 1, 23560 Lubeck, Germany; 

telephone (49) 451 4093–2976; fax (49) 451 

4093–4488. 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 August 

3, 2012. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2012–20112 Filed 8–15–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–0845; Directorate 

Identifier 2012–CE–013–AD] 

RIN 2120–AA64 

Airworthiness Directives; Revo, 

Incorporated 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 Revo, 

Incorporated Models COLONIAL C–1, 

COLONIAL C–2, LAKE LA–4, LAKE 

LA–4A, LAKE LA–4P, and LAKE LA–4– 

200 airplanes. The existing AD currently 

requires a one-time dye-penetrant 

inspection of the horizontal stabilizer 

attachment fitting and repetitive visual 

inspections of the fitting for any 

evidence of fretting, cracking, or 

corrosion (with necessary replacement 

and modification); replacement of the 

fitting upon reaching the 850-hours 

time-in-service (TIS) safe life; and 

reporting to the FAA the results of the 

initial inspection and any cracks found 

on repetitive inspections. Since we 

issued AD 2005–12–02, Revo, 

Incorporated informed the FAA that 

while the drawing numbers are 

different, the attachment fittings on the 

Model COLONIAL C–1 airplanes are 

identical in every other respect to those 

installed on the airplanes referenced in 

AD 2005–12–02. This proposed AD 

would retain the actions required by AD 

2005–12–02, add the Model COLONIAL 

C–1 airplanes to the Applicability, and 

add an optional terminating action for 

the requirements. We are proposing this 

AD to correct the unsafe condition on 

these products. 

DATES: We must receive comments on 

this proposed AD by October 1, 2012. 

ADDRESSES: You may send comments, 

using the procedures found in 14 CFR 

11.43 and 11.45, 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: Deliver to Mail 

address above between 9 a.m. and 5 


wreier-aviles on DSK7SPTVN1PROD with PROPOSALS