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

10691 

Vol. 77, No. 36 

Thursday, February 23, 2012 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–0152; Directorate 

Identifier 2011–NM–059–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 A330–200 series 

airplanes; Airbus Model A330–200 

Freighter series airplanes; Airbus Model 

A330–300 series airplanes; Airbus 

Model A340–200 series airplanes; and 

Airbus Model A340–300 series 

airplanes. This proposed AD was 

prompted by reports of sheared 

fasteners located on the outside skin of 

the forward cargo door and cracks on 

the frame fork ends, as well as cracks of 

the aft cargo door frame 64A. This 

proposed AD would require performing 

a detailed inspection of the outer skin 

rivets at the frame fork ends of the 

forward and aft cargo door for sheared, 

loose, and missing rivets, repairing the 

outer skin rivets, if necessary, and 

performing repetitive inspections. We 

are proposing this AD to detect and 

correct sheared, loose or missing 

fasteners on the forward and aft cargo 

door frame, which could result in the 

loss of structural integrity of the forward 

and aft cargo door. 

DATES: We must receive comments on 

this proposed AD by April 9, 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; telephone 

(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–2012–0152; Directorate Identifier 

2011–NM–059–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 2011–0007R1, 

dated February 14, 2011 (referred to 

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

unsafe condition for the specified 

products. The MCAI states: 

Two operators have reported cases of some 

sheared fasteners on the outside skin of the 

forward cargo door, detected during walk 

around checks. Further inspections revealed 

crack findings on the frame (FR) fork ends. 

In addition, during a scheduled 

maintenance check, the aft cargo door frame 

64A of an aeroplane has been found cracked 

for a length of more than 3 inches. Outer skin 

rivets were also found sheared. At time of 

findings the aeroplane had accumulated 

10564 flight cycles (FC), i.e. below the 12000 

FC threshold defined in DGAC [Direction 

Ge ́ne ́rale de l’Aviation Civile] France AD F– 

2001–124(B) and DGAC France AD F–2001– 

126(B) [which corresponds with FAA AD 

2001–16–01, Amendment 39–12369 (66 FR 

40874, August 6, 2001], which require a 

special detailed inspection of the aft cargo 

compartment door. 

In case of cracked or ruptured (forward or 

aft) cargo door frame, the loads will be 

transferred to the remaining structural 

elements. Such second load path is able to 

sustain the loads for a limited number of 

flight cycles only. Rupture of two vertical 

frames could result in the loss of the 

structural integrity of the forward or aft cargo 

door. 

For the above described reasons, this AD 

requires repetitive detailed visual inspections 

of the aft and forward cargo doors outer skin 

for sheared, loose or missing rivets at all 

frame fork ends and the accomplishment of 

the applicable corrective actions [repair if 

necessary]. 

This [EASA] AD is considered to be an 

interim action, further actions might be 

required to revise/supersede the above 

mentioned DGAC France ADs. 

This [EASA] AD is revised in order to 

recognize that aeroplanes on which Airbus 

modification 44852 has been embodied in 

production are not affected by the repetitive 

inspection requirements of this AD on the Aft 

Cargo Compartment Door. 


pmangrum on DSK3VPTVN1PROD with PROPOSALS-1
10692 Federal Register / Vol. 77, No. 36 / Thursday, February 23, 2012 / Proposed Rules 

You may obtain further information by 

examining the MCAI in the AD docket. 

Relevant Service Information 

Airbus has issued the following 

service information: 

• All Operators Telex A330– 

52A3084, dated December 20, 2010 (for 

Model A330–200 and A330–300 series 

airplanes); 

• All Operators Telex A330– 

52A3085, dated December 20, 2010 (for 

Model A330–200 and A330–300 series 

airplanes); 

• All Operators Telex A340– 

52A4091, dated December 20, 2010 (for 

Model A340–200 and A340–300 series 

airplanes); and 

• All Operators Telex A340– 

52A4092, dated December 20, 2010 (for 

Model A340–200 and A340–300 series 

airplanes). 

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 1 work-hours per product to 

comply with the 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 

$4,675, or $85 per product. 

We have received no definitive data 

that would enable us to provide cost 

estimates for the on-condition actions 

specified in this proposed AD. 

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–2012–0152; 

Directorate Identifier 2011–NM–059–AD. 

(a) Comments Due Date 

We must receive comments by April 9, 

2012. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Airbus Model A330– 

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

–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. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 52: Doors. 

(e) Reason 

This AD was prompted by reports of 

sheared fasteners located on the outside skin 

of the forward cargo door and cracks on the 

frame fork ends, as well as cracks of the aft 

cargo door frame 64A. We are issuing this AD 

to detect and correct sheared, loose or 

missing fasteners on the forward and aft 

cargo door frame, which could result in the 

loss of structural integrity of the forward and 

aft cargo door. 

(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) Forward Cargo Compartment Door 

Before the accumulation of 6,000 total 

flight cycles since first flight of the airplane 

or within 400 flight cycles after the effective 

date of this AD, whichever occurs later: 

Perform a detailed inspection of the outer 

skin rivets at the frame fork ends between 

FR20B and FR25 of the forward cargo door 

for sheared, loose, and missing rivets, in 

accordance with the instructions of Airbus 

All Operators Telex (AOT) A330–52A3085, 

dated December 20, 2010 (for Model A330– 

200 and A330–300 series airplanes); or 

Airbus AOT A340–52A4092, dated December 

20, 2010 (for Model A340–200 and A340–300 

series airplanes). Thereafter repeat the 

inspection at intervals not to exceed 800 total 

flight cycles. 

(h) Aft Cargo Compartment Door 

For all airplanes, except those on which 

Airbus Modification 44854 or Modification 

44852 has been embodied in production, or 

Airbus Service Bulletin A330–52–3044 or 

Airbus Service Bulletin A340–52–4054 has 

been embodied in service: Before the 

accumulation of 4,000 total flight cycles 

since first flight of the airplane, or within 400 

flight cycles after the effective date of this 

AD, whichever occurs later, perform a 

detailed inspection of outer skin rivets at the 

frame fork ends between FR60 and FR64A of 

the aft cargo door for sheared, loose or 

missing rivets, in accordance with the 

instructions of Airbus AOT A330–52A3084, 

dated December 20, 2010 (for Model A330– 


pmangrum on DSK3VPTVN1PROD with PROPOSALS-1
Federal Register / Vol. 77, No. 36 / Thursday, February 23, 2012 / Proposed Rules 10693 

200 and A330–300 series airplanes); or 

Airbus AOT A340–52A4091, dated December 

20, 2010 (for Model A340–200 and A340–300 

series airplanes). Thereafter repeat the 

inspection at intervals not to exceed 400 

flight cycles. 

(i) Corrective Action 

If any sheared, loose, or missing rivets are 

found during any inspection required by 

paragraph (g) or (h) of this AD: Before further 

flight, repair using a method approved by the 

Manager, International Branch, ANM–116, 

FAA; or European Aviation Safety Agency 

(EASA) (or its delegated agent). 

(j) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Branch, ANM–116, 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; telephone (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. 

(k) Related Information 

Refer to MCAI European Aviation Safety 

Agency Airworthiness Directive 2011– 

0007R1, dated February 14, 2011, and the 

service information specified in paragraphs 

(k)(1) through (k)(4) of this AD, for related 

information. 

(1) Airbus All Operators Telex (AOT) 

A330–52A3085, dated December 20, 2010. 

(2) Airbus AOT A340–52A4092, dated 

December 20, 2010. 

(3) Airbus AOT A330–52A3084, dated 

December 20, 2010. 

(4) Airbus AOT A340–52A4091, dated 

December 20, 2010. 

Issued in Renton, Washington, on February 

14, 2012. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2012–4208 Filed 2–22–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–0150; Directorate 

Identifier 2011–NM–234–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 series airplanes, 

Airbus Model A319 series airplanes, 

Airbus Model A320 series airplanes, 

and Airbus Model A321 series 

airplanes. This proposed AD was 

prompted by reports of oil residue 

between the stator and the rotor parts of 

the position resolvers of the angle of 

attack (AOA) vane, which was a result 

of incorrect removal of the machining 

oil during the manufacturing process of 

the AOA resolvers. This proposed AD 

would require inspecting to determine if 

certain AOA probes are installed, and 

replacing the affected AOA probe if 

necessary. We are proposing this AD to 

prevent erroneous AOA information and 

consequent delayed or non-activation of 

the AOA protection systems which, 

during flight at a high angle of attack, 

could result in reduced control of the 

airplane. 

DATES: We must receive comments on 

this proposed AD by April 9, 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 

Thales Avionics service information 

identified in this proposed AD, contact 

Thales Avionics, Retrofit Manager, 105, 

Avenue du Ge ́ne ́ral Eisenhower, BP 

63647, 31036 Toulouse Cedex 1, France; 

telephone +33 5 61 19 76 95; fax +33 5 

61 19 68 20; email 

retrofit.ata@fr.thalesgroup.com; Internet 

http://www.thalesgroup.com/aerospace. 

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–2012–0150; Directorate Identifier 

2011–NM–234–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 


pmangrum on DSK3VPTVN1PROD with PROPOSALS-1