Federal Register / Vol. 77, No. 35 / Wednesday, February 22, 2012 / Proposed Rules 10409 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–0144; Directorate 

Identifier 2011–NM–152–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 A300 series airplanes; 

Model A310 series airplanes; Model 

A300 B4–600, B4–600R, and F4–600R 

series airplanes, and Model C4–605R 

Variant F airplanes (collectively called 

Model A300–600 series airplanes). This 

proposed AD was prompted by reports 

of cracked fuel pump canister hoods 

located in fuel tanks. This proposed AD 

would require replacing any hood 

halves of fuel pump canisters that are 

cracked. We are proposing this AD to 

prevent any detached canister hood 

fragments/debris from being ingested 

into the fuel feed system, and the 

metallic debris inside the fuel tank 

resulting in a potential source of 

ignition and consequent fire or 

explosion. 

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– 

EAW (Airworthiness Office), 1 Rond 

Point Maurice Bellonte, 31707 Blagnac 

Cedex, France; telephone +33 5 61 93 36 

96; fax +33 5 61 93 44 51; email: 

account.airworth-eas@airbus.com; 

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

may review copies of the referenced 

service information at the FAA, 

Transport Airplane Directorate, 1601 

Lind Avenue SW., Renton, 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: Dan 

Rodina, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue SW., Renton, 

Washington 98057–3356; telephone 

(425) 227–2125; 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–2012–0144; Directorate Identifier 

2011–NM–152–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 2011–0124, 

dated June 30, 2011 (referred to after 

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

condition for the specified products. 

The MCAI states: 

This [EASA] AD results from findings of 

cracked fuel pump canister hoods located in 

fuel tanks. 

From the analyses, laboratory testing and 

examinations made so far, it is presently 

thought that vibration-induced fatigue can be 

identified as the root cause for the cracks 

found on in-service aeroplanes. However, 

current data does not yet permit to exclude 

some other potential contributing factors. 

This condition, if not detected and 

corrected, could lead to detached canister 

hood fragments/debris to be ingested into the 

fuel feed system. Also, the metallic debris 

inside the fuel tank could result in a 

potential source of ignition and consequent 

fire or explosion. 

For the reasons described above, this 

[EASA] AD requires repetitive [detailed] 

inspections of all fuel pump canister hood 

halves and their replacement if any 

[cracking] damage is found. This [EASA] AD 

also requires the inspection results to be 

reported. 

This [EASA] AD is considered to be an 

interim action. The reports that are required 

by this [EASA] AD will enable the 

manufacturer to obtain better insight into the 

nature, cause, and extent of the fuel pump 

canister hood cracking, and eventually to 

develop final action to address the unsafe 

condition. Once final action has been 

identified, further AD actions could be 

considered. 

You may obtain further information by 

examining the MCAI in the AD docket. 

Relevant Service Information 

Airbus has issued Mandatory Service 

Bulletins A300–28–0089, A300–28– 

6106, and A310–28–2173, all including 

Inspection Findings—Reporting Sheet, 

all Revision 01, all dated April 15, 2011. 

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 221 products of U.S. 

registry. We also estimate that it would 

take up to 12 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 

$225,420, or $1,020 per product. 


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10410 Federal Register / Vol. 77, No. 35 / Wednesday, February 22, 2012 / Proposed Rules 

In addition, we estimate that any 

necessary follow-on actions would take 

about 1 work-hour. We have no way of 

determining the number of products 

that may need these actions. 

We have received no definitive data 

that would enable us to provide cost 

estimates for certain parts required for 

the on-condition actions (replacing fuel 

pump canister hood halves) 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); and 

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–2012–0144; 

Directorate Identifier 2011–NM–152–AD. 

(a) Comments Due Date 

We must receive comments by April 9, 

2012. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to the airplanes identified 

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

AD; certificated in any category; all 

certificated models; all serial numbers. 

(1) Airbus Model A300 B2–1C, B2K–3C, 

B2–203, B4–2C, B4–103, and B4–203 

airplanes. 

(2) Airbus Model A310–203, –204, –221, 

–222, –304, –322, –324, and –325 airplanes. 

(3) Airbus Model A300 B4–603, B4–620, 

and B4–622 airplanes, Model A300 B4–605R 

and B4–622R airplanes, Model A300 F4– 

605R and F4–622R airplanes, and Model 

A300 C4–605R Variant F airplanes. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 28: Fuel. 

(e) Reason 

This AD was prompted by reports of 

cracked fuel pump canister hoods located in 

fuel tanks. We are issuing this AD to prevent 

any detached canister hood fragments/debris 

from being ingested into the fuel feed system, 

and the metallic debris inside the fuel tank 

resulting in a potential source of ignition and 

consequent fire or explosion. 

(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) Initial Inspection and Replacement 

Within 30 months after the effective date 

of this AD, do a detailed inspection for 

cracking of the fuel pump canister hood 

halves installed on all fuel pump canisters 

having part numbers (P/N) 2052C11, 

2052C12, and C93R51–601, in accordance 

with the Accomplishment Instructions of the 

service bulletin specified in paragraphs 

(g)(1), (g)(2), and (g)(3) of this AD, as 

applicable. If any crack is found on any fuel 

pump canister hood half during any 

inspection, before further flight, replace the 

fuel pump canister hood half, in accordance 

with the Accomplishment Instructions of the 

service bulletin specified in paragraph (g)(1), 

(g)(2), or (g)(3) of this AD, as applicable. 

(1) For Model A300 airplanes: Airbus 

Mandatory Service Bulletin A300–28–0089, 

including Inspection Findings—Reporting 

Sheet, Revision 01, dated April 15, 2011. 

(2) For Model A300–600 airplanes: Airbus 

Mandatory Service Bulletin A300–28–6106, 

including Inspection Findings—Reporting 

Sheet, Revision 01, dated April 15, 2011. 

(3) For Model A310 airplanes: Airbus 

Mandatory Service Bulletin A310–28–2173, 

including Inspection Findings—Reporting 

Sheet, Revision 01, dated April 15, 2011. 

(h) Repetitive Inspections 

Within 30 months after accomplishing the 

actions specified in paragraph (g) of this AD, 

and thereafter at intervals not to exceed 30 

months, repeat the detailed inspection 

specified in paragraph (g) of this AD. 

(i) Credit for Actions Accomplished in 

Accordance With Previous Service 

Information 

Actions accomplished before the effective 

date of this AD in accordance with Airbus 

Mandatory Service Bulletins A300–28–0089, 

A300–28–6106, and A310–28–2173, all dated 

January 13, 2011, as applicable, are 

considered acceptable for compliance with 

the corresponding action specified in this 

AD. 

(j) Reporting to Airbus 

Submit reports of the findings (both 

positive and negative) of the inspections 

required by paragraphs (g) and (h) of this AD 

to Airbus at the applicable time specified in 

paragraph (j)(1) or (j)(2) of this AD, using the 

form ‘‘Inspection Findings—Reporting 

Sheet’’ provided in the service bulletin 

identified in paragraphs (g)(1), (g)(2), and 

(g)(3) of this AD, as applicable. 

(1) If the inspection was done on or after 

the effective date of this AD: Submit the 

report within 30 days after the inspection. 

(2) If the inspection was done before the 

effective date of this AD: Submit the report 

within 30 days after the effective date of this 

AD. 

(k) 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: 

Dan Rodina, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 


wreier-aviles on DSK5TPTVN1PROD with PROPOSALS
Federal Register / Vol. 77, No. 35 / Wednesday, February 22, 2012 / Proposed Rules 10411 

Avenue SW., Renton, Washington 98057– 

3356; telephone (425) 227–2125; fax (425) 

227–1149. Information may be emailed to: 

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

Before using any approved AMOC, notify 

your appropriate principal inspector, or 

lacking a principal inspector, the manager of 

the local flight standards district office/ 

certificate holding district office. The AMOC 

approval letter must specifically reference 

this AD. 

(2) Airworthy Product: For any requirement 

in this AD to obtain corrective actions from 

a manufacturer or other source, use these 

actions if they are FAA-approved. Corrective 

actions are considered FAA-approved if they 

are approved by the State of Design Authority 

(or their delegated agent). You are required 

to assure the product is airworthy before it 

is returned to service. 

(3) Reporting Requirements: A federal 

agency may not conduct or sponsor, and a 

person is not required to respond to, nor 

shall a person be subject to a penalty for 

failure to comply with a collection of 

information subject to the requirements of 

the Paperwork Reduction Act unless that 

collection of information displays a current 

valid OMB Control Number. The OMB 

Control Number for this information 

collection is 2120–0056. Public reporting for 

this collection of information is estimated to 

be approximately 5 minutes per response, 

including the time for reviewing instructions, 

completing and reviewing the collection of 

information. All responses to this collection 

of information are mandatory. Comments 

concerning the accuracy of this burden and 

suggestions for reducing the burden should 

be directed to the FAA at: 800 Independence 

Ave. SW., Washington, DC 20591, Attn: 

Information Collection Clearance Officer, 

AES–200. 

(l) Related Information 

Refer to MCAI European Aviation Safety 

Agency (EASA) Airworthiness Directive 

2011–0124, dated June 30, 2011; and the 

Airbus mandatory service bulletins identified 

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

AD; for related information. 

Issued in Renton, Washington, on February 

7, 2012. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2012–4163 Filed 2–21–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–0149; Directorate 

Identifier 2011–NM–255–AD] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company 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 

The Boeing Company Model 777–200 

and –300 series airplanes. This 

proposed AD was prompted by reports 

of fatigue cracks in the lap joints, which 

initiated at scribe lines that were made 

during production when maskant was 

removed from the affected skin panels. 

This proposed AD would require 

repetitive external phased-array 

ultrasonic inspections to detect cracks 

of the affected fuselage skin lap splices 

in Sections 41, 43, and 44, as applicable, 

and repair if necessary. We are 

proposing this AD to detect and correct 

such fatigue cracking, which, if not 

detected and corrected, could grow large 

and cause sudden decompression and 

the inability to sustain limit flight and 

pressure loads. 

DATES: We must receive comments on 

this proposed AD by April 9, 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 p.m., Monday through Friday, except 

Federal holidays. 

For service information identified in 

this proposed AD, contact Boeing 

Commercial Airplanes, Attention: Data 

& Services Management, P.O. Box 3707, 

MC 2H–65, Seattle, Washington 98124– 

2207; telephone 206–544–5000, 

extension 1; fax 206–766–5680; email 

me.boecom@boeing.com; Internet 

https://www.myboeingfleet.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 Management Facility 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 Office 

(phone: 800–647–5527) is in the 

ADDRESSES section. Comments will be 

available in the AD docket shortly after 

receipt. 

FOR FURTHER INFORMATION CONTACT: 

James Sutherland, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, 

Seattle Aircraft Certification Office, 

1601 Lind Avenue SW., Renton, 

Washington 98057–3356; phone: 425– 

917–6533; fax: 425–917–6590; email: 

James.Sutherland@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 

this proposal. Send your comments to 

an address listed under the ADDRESSES

section. Include ‘‘Docket No. FAA– 

2012–0149; Directorate Identifier 2011– 

NM–255–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 because of 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 

We received a report indicating that, 

on the affected airplanes, scribe lines 

may have been inadvertently made in 

the overlapped skin in lap joints if a 

sharp tool was used to remove the 

maskant from the aluminum skin panels 

during assembly of the affected lap 

joints. During fatigue testing of Model 

777 airplanes, lap joint cracks were 

found, and analysis indicated that those 

cracks initiated at scribe lines that were 

made during production when maskant 

was removed from the affected skin 

panels. Such fatigue cracking, if not 

detected and corrected, could grow large 

and cause sudden decompression and 

the inability to sustain limit flight and 

pressure loads. 

Relevant Service Information 

We reviewed Boeing Alert Service 

Bulletin 777–53A0043, dated November 

9, 2011. For information on the 

procedures and compliance times, see 

this service information at http:// 

www.regulations.gov by searching for 

Docket No. FAA–2012–0149. 


wreier-aviles on DSK5TPTVN1PROD with PROPOSALS