Federal Register / Vol. 77, No. 157 / Tuesday, August 14, 2012 / Rules and Regulations 48425 

(i) Exceptions to Service Bulletin 

Specifications 

The exceptions specified in paragraphs 

(i)(1) and (i)(2) of this AD apply to this AD. 

(1) Where Boeing Special Attention Service 

Bulletin 737–53–1315, dated July 29, 2011, 

specifies a compliance time after ‘‘the date of 

this service bulletin,’’ this AD requires 

compliance within the specified compliance 

time after the effective date of this AD. 

(2) Where Boeing Special Attention Service 

Bulletin 737–53–1315, dated July 29, 2011, 

specifies to contact Boeing for repair 

instructions: Before further flight, repair 

using a method approved in accordance with 

the procedures specified in paragraph (j) of 

this AD. 

(j) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Seattle Aircraft 

Certification Office (ACO), 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 manager of the ACO, it may be emailed 

to 9-ANM-Seattle-ACO-AMOCRequests@faa.gov. 

(2) 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. 

(3) An AMOC that provides an acceptable 

level of safety may be used for any repair 

required by this AD if it is approved by the 

Boeing Commercial Airplanes Organization 

Designation Authorization (ODA) that has 

been authorized by the Manager, Seattle 

ACO, to make those findings. For a repair 

method to be approved, the repair must meet 

the certification basis of the airplane, and the 

approval must specifically refer to this AD. 

(k) Related Information 

For more information about this AD, 

contact Wayne Lockett, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, Seattle 

Aircraft Certification Office (ACO), 1601 Lind 

Avenue SW., Renton, Washington 98057– 

3356; phone: 425–917–6447; fax: 425–917– 

6590; email: wayne.lockett@faa.gov. 

(l) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 

(IBR) under 5 U.S.C. 552(a) and 1 CFR part 

51. 

(2) You must use the following service 

information to do the actions required by this 

AD, unless the AD specifies otherwise. 

(i) Boeing Special Attention Service 

Bulletin 737–53–1315, dated July 29, 2011. 

(ii) Reserved. 

(3) For service information identified in 

this AD, contact Boeing Commercial 

Airplanes, Attention: Data & Services 

Management, P.O. Box 3707, MC 2H–65, 

Seattle, WA 98124–2207; telephone 206– 

544–5000, extension 1; fax 206–766–5680; 

Internet https://www.myboeingfleet.com. 

(4) You may review copies of the service 

information at the FAA, Transport Airplane 

Directorate, 1601 Lind Avenue SW., Renton, 

Washington 98057–3356. For information on 

the availability of this material at the FAA 

call 425–227–1221. 

(5) 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 NARA, call 202–741–6030, or go 

to: http://www.archives.gov/federal-register/ 

cfr/ibr-locations.html. 

Issued in Renton, Washington, on July 31, 

2012. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2012–19423 Filed 8–13–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–0192; Directorate 

Identifier 2011–NM–225–AD; Amendment 

39–17152; AD 2012–16–05] 

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 and –200 

freighter series airplanes; and Model 

A340–200, –300, –500, and –600 series 

airplanes. This AD was prompted by 

fuel system reviews conducted by the 

manufacturer. This AD requires 

modification of the control circuit for 

the fuel pumps for the center fuel tanks 

for certain airplanes, and center and rear 

fuel tanks for certain other airplanes. 

We are issuing this AD to prevent the 

potential of ignition sources inside fuel 

tanks, which, in combination with 

flammable fuel vapors, could result in 

fuel tank explosions and consequent 

loss of the airplane. 

DATES: This AD becomes effective 

September 18, 2012. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of September 18, 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, WA 

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 March 16, 2012 (77 FR 

15644). That NPRM proposed to correct 

an unsafe condition for the specified 

products. The MCAI states: 

* * * [T]he FAA issued a set of new rules 

related to Fuel Tank Safety including Special 

Federal Aviation Regulation (SFAR) 88. In 

line with SFAR88, the JAA [Joint Aviation 

Authorities] issued policy JAA INT/POL 25/ 

12 and recommended to the National 

Aviation Authorities (NAA) the application 

of a similar regulation. 

To ensure compliance with the 

requirements set by SFAR88 and JAA INT/ 

POL 25/12, this [EASA] AD requires that 

Ground Fault Interrupters (GFI) are installed 

into the electrical power supply circuits of 

fuel pumps for which the canisters become 

uncovered during normal operation, taking 

into account normal fuel reserve or the fuel 

level, triggering the low fuel level warning. 

The function of this additional system 

protection is to electrically isolate the pump 

if a ground fault condition occurs 

downstream of the GFI. The GFI gives 

additional earth leakage protection to the 

downstream circuit. 

The unsafe condition is the potential of 

ignition sources inside fuel tanks, 

which, in combination with flammable 

fuel vapors, could result in fuel tank 

explosions and consequent loss of the 

airplane. The corrective action is 

modifying the control circuits of the fuel 

pump for the rear and center fuel tanks. 

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 (77 

FR 15644, March 16, 2012) or on the 

determination of the cost to the public. 

Changes to the AD 

European Aviation Safety Agency 

(EASA) has issued AD 2011–0196, dated 

October 7, 2011, corrected March 23, 

2012, to correct a typographical error in 

the applicability paragraph of the MCAI 

which changed the intent of the 

applicability. The exception to the 


tkelley on DSK3SPTVN1PROD with RULES
48426 Federal Register / Vol. 77, No. 157 / Tuesday, August 14, 2012 / Rules and Regulations 

applicability should have specified ‘‘or’’ 

instead of ‘‘and.’’ We have changed 

paragraph (c)(2) of this AD to add 

paragraphs (c)(2)(i) and (c)(2)(ii) to this 

AD to clarify the exception to the 

applicability of this AD. 

Airbus has issued Mandatory Service 

Bulletins A330–28–3113, Revision 01, 

dated March 27, 2012 (for Model A330– 

200 and –200 freighter series airplanes); 

and A340–28–4129, Revision 01, dated 

March 27, 2012 (for Model A340–200 

and –300 series airplanes); to include a 

test procedure for a certain ground fault 

interrupter. We have revised paragraphs 

(g) and (j) of this AD to reference Airbus 

Mandatory Service Bulletins A330–28– 

3113, Revision 01, dated March 27, 

2012; and A340–28–4129, Revision 01, 

dated March 27, 2012. We have added 

paragraph (h) to this AD to allow credit 

for actions done in accordance with 

Airbus Mandatory Service Bulletins 

A330–28–3113, dated July 19, 2011; and 

A330–28–4129, dated July 19, 2011; we 

have revised subsequent paragraph 

identifiers accordingly. 

Conclusion 

We reviewed the available data and 

determined that air safety and the 

public interest require adopting the AD 

with the changes described previously 

and minor editorial changes. We have 

determined that these changes: 

• Are consistent with the intent that 

was proposed in the NPRM (77 FR 

15644, March 16, 2012) for correcting 

the unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the NPRM (77 FR 15644, 

March 16, 2012). 

Costs of Compliance 

We estimate that this AD will affect 

29 products of U.S. registry. We also 

estimate that it will take about 10 workhours per product to comply with the 

basic requirements of this AD. The 

average labor rate is $85 per work-hour. 

Required parts will cost about $3,480 

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 

this AD to the U.S. operators to be 

$125,570 or $4,330 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 

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 AD: 

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 (77 FR 15644, 

March 16, 2012), 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: 

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: 

2012–16–05 Airbus: Amendment 39–17152. 

Docket No. FAA–2012–0192; Directorate 

Identifier 2011–NM–225–AD. 

(a) Effective Date 

This airworthiness directive (AD) becomes 

effective September 18, 2012. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to the airplanes specified 

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

AD, certificated in any category. 

(1) Airbus Model A330–201, –202, –203, 

–223, and –243 airplanes; all serial numbers; 

except those on which Airbus modification 

200242 has been accomplished in 

production. 

(2) Airbus Model A330–223F and –243F 

airplanes; all serial numbers; except 

airplanes identified in paragraph (c)(2)(i) or 

(c)(2)(ii) of this AD. 

(i) Airplanes on which Airbus modification 

58623 has been accomplished in production 

and on which Airbus modification 200281 

has not been accomplished in production; or 

(ii) Airplanes on which modification 

200242 has been accomplished in 

production. 

(3) Airbus Model A340–211, –212, –213, 

–311, –312, –313, –541, and –642 airplanes; 

all serial numbers; except airplanes on which 

Airbus modification 200242 has been 

accomplished in production. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 28, Fuel. 

(e) Reason 

This AD was prompted by fuel system 

reviews conducted by the manufacturer. We 

are issuing this AD to prevent the potential 

of ignition sources inside fuel tanks, which, 

in combination with flammable fuel vapors, 

could result in fuel tank explosions and 

consequent loss of the airplane. 

(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 

Within 48 months after the effective date 

of this AD, do the actions specified in 


tkelley on DSK3SPTVN1PROD with RULES
Federal Register / Vol. 77, No. 157 / Tuesday, August 14, 2012 / Rules and Regulations 48427 

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

applicable. 

(1) For Model A330–200 and –200F series 

airplanes, and Model A340–200 and –300 

series airplanes: Modify the control circuit 

for the fuel pump for the center fuel tank, in 

accordance with the Accomplishment 

Instructions of Airbus Mandatory Service 

Bulletin A330–28–3113, Revision 01, dated 

March 27, 2012 (for Model A330–200 and 

–200 freighter series airplanes); or A340–28– 

4129, Revision 01, dated March 27, 2012 (for 

Model A340–200 and –300 series airplanes). 

(2) For Model A340–500 and –600 series 

airplanes: Modify the control circuit for the 

fuel pump for the rear and/or center fuel 

tanks, in accordance with the 

Accomplishment Instructions of Airbus 

Mandatory Service Bulletin A340–28–5051, 

dated September 1, 2011. 

(h) Credit for Previous Actions 

This paragraph provides credit for the 

actions required by paragraph (g)(1) of this 

AD, if those actions were performed before 

the effective date of this AD, using Airbus 

Mandatory Service Bulletin A330–28–3113 

or A340–28–4129, both dated July 19, 2011, 

as applicable. 

(i) 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, WA 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. 

(j) Related Information 

Refer to MCAI European Aviation Safety 

Agency (EASA) Airworthiness Directive 

2011–0196, dated October 7, 2011, corrected 

March 23, 2012, and the service bulletins 

specified in paragraphs (j)(1), (j)(2), and (j)(3) 

of this AD, for related information. 

(1) Airbus Mandatory Service Bulletin 

A330–28–3113, Revision 01, dated March 27, 

2012. 

(2) Airbus Mandatory Service Bulletin 

A340–28–4129, Revision 01, dated March 27, 

2012. 

(3) Airbus Mandatory Service Bulletin 

A340–28–5051, dated September 1, 2011. 

(k) Material Incorporated by Reference 

(1) 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. 

(2) You must use the following service 

information to do the actions required by this 

AD, unless the AD specifies otherwise. 

(i) Airbus Mandatory Service Bulletin 

A330–28–3113, Revision 01, dated March 27, 

2012. 

(ii) Airbus Mandatory Service Bulletin 

A340–28–4129, Revision 01, dated March 27, 

2012. 

(iii) Airbus Mandatory Service Bulletin 

A340–28–5051, dated September 1, 2011. 

(3) For service information identified in 

this 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. 

(4) 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. 

(5) 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 July 31, 

2012. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2012–19262 Filed 8–13–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–0038; Directorate 

Identifier 2011–NM–209–AD; Amendment 

39–17153; AD 2012–16–06] 

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 all 

Airbus Model A300 B4–600 series 

airplanes and Model A310–203, –204, 

–221, and –222 airplanes. This AD was 

prompted by a report of a capacitive 

density condensator (cadensicon) coil 

overheating during testing. This AD 

requires an inspection to determine if a 

certain fuel quantity indication 

computer (FQIC) is installed, 

replacement of identified FQICs, and 

modification of the associated wiring. 

We are issuing this AD to detect and 

correct potential overheating of the 

cadensicon coil, which could create an 

ignition source inside a fuel tank, 

which, in combination with flammable 

fuel vapors, could result in a fuel tank 

explosion and consequent loss of the 

airplane. 

DATES: This AD becomes effective 

September 18, 2012. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of September 18, 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: 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: 

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 February 7, 2012 (77 FR 

6023). That NPRM proposed to correct 

an unsafe condition for the specified 

products. The MCAI states: 

In view to address the scope of Special 

Federal Aviation Regulation 88 (SFAR 88) 

(66 FR 23086, May 7, 2001) and the 

equivalent JAA Internal Policy INT/POL/25/ 

12, a safety analysis of Fuel Quantity 

Indication Computers (FQIC) fitted to Wide 

Body aeroplanes has been performed. 

Detailed analysis has shown that on early 

standard FQIC, Type 1, there is an 

insufficient gap on the printed circuit board 

between an 115V [volt] supply and a direct 

path to the Capacitive Density Condensator 

(Cadensicon). 

During tests that were carried out applying 

115V to the Cadensicon coil, measured 

temperature levels were in excess of the 

acceptable level of 200°C. This potential 


tkelley on DSK3SPTVN1PROD with RULES