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
48428 Federal Register / Vol. 77, No. 157 / Tuesday, August 14, 2012 / Rules and Regulations 

overheating of the Cadensicon coil could be 

a possible ignition point within the fuel tank. 

This condition, if left uncorrected, could 

create an ignition source in the tank vapour 

space, possibly resulting in a wing fuel tank 

explosion and consequent loss of the 

aeroplane. 

For the reasons explained above, this 

[European Aviation Safety Agency] AD 

requires the replacement of all Type 1 FQICs 

with Type 2 FQICs. 

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 

have considered the comment received. 

Request for Extension of Compliance 

Time 

FedEx requested that we revise the 

compliance time for the actions required 

by paragraph (g) of the NPRM (77 FR 

6023, February 7, 2012), from 30 months 

to 36 months. FedEx explained that the 

lead time for the Airbus kit part number 

282039A01R01 is 60 days, as listed in 

Airbus Mandatory Service Bulletin 

A310–28–2039, Revision 01, dated 

January 19, 2011. FedEx explained 

further that a 30-day lead-time was 

quoted from Intertechnique for a Type 2 

FQIS unit. FedEx expressed that while 

the 30 months aligns with the heavy 

maintenance schedule for Model A310 

airplanes, it would take time to procure 

the new FQIS units and kits required to 

comply with the NPRM. Therefore, the 

additional 6 months it proposed for 

scheduling and material procurement 

will allow the work to be performed 

during a heavy maintenance check for 

all FedEx airplanes. 

We disagree to revise the compliance 

time in the final rule. In developing an 

appropriate compliance time, we 

considered the safety implications, parts 

availability, and normal maintenance 

schedules for timely accomplishment of 

the required actions in the final rule. 

However, under the provisions of 

paragraph (i) of this AD, we will 

consider requests for approval of an 

alternative method of compliance 

(AMOC) if sufficient data are submitted 

to substantiate that the change would 

provide an acceptable level of safety. 

We have not changed the AD in this 

regard. 

Conclusion 

We reviewed the available data, 

including the comment received, and 

determined that air safety and the 

public interest require adopting the AD 

as proposed—except for minor editorial 

changes. We have determined that these 

minor changes: 

• Are consistent with the intent that 

was proposed in the NPRM (77 FR 6023, 

February 7, 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 6023, 

February 7, 2012). 

Costs of Compliance 

We estimate that this AD will affect 

53 products of U.S. registry. We also 

estimate that it will take about 6 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 $200 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 $37,630, or 

$710 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 6023, 

February 7, 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: 

2012–16–06 Airbus: Amendment 39–17153. 

Docket No. FAA–2012–0038; Directorate 

Identifier 2011–NM–209–AD. 

(a) Effective Date 

This airworthiness directive (AD) becomes 

effective September 18, 2012. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Airbus Model A300 B4– 

601, B4–603, B4–620, and B4–622 airplanes, 

and Model A310–203, –204, –221, and –222 

airplanes, certificated in any category, all 

manufacturer serial numbers. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 28: Fuel. 


tkelley on DSK3SPTVN1PROD with RULES
Federal Register / Vol. 77, No. 157 / Tuesday, August 14, 2012 / Rules and Regulations 48429 

(e) Reason 

This AD was prompted by a report of a 

capacitive density condensator (cadensicon) 

coil overheating during testing. 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. 

(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 30 months after the effective date 

of this AD, inspect to determine whether any 

fuel quantity indication computer (FQIC) 

Type 1, having part number (P/N) SIC5054 or 

P/N SIC5051 (as applicable to the airplane 

model), is installed, in accordance with the 

Accomplishment Instructions of Airbus 

Mandatory Service Bulletin A300–28–6024, 

Revision 02, dated January 19, 2011; or 

Airbus Mandatory Service Bulletin A310–28– 

2039, Revision 01, dated January 19, 2011; as 

applicable. A review of airplane maintenance 

records is acceptable in lieu of this 

inspection if the part number of the FQIC can 

be conclusively determined from that review. 

If any FQIC Type 1 having P/N SIC5054 or 

P/N SIC5051 is installed, within 30 months 

after the effective date of this AD, replace the 

FQIC Type 1 with a FQIC Type 2 having P/ 

N SIC5055, P/N SIC5076, P/N SIC5082, or P/ 

N SIC5083 (as applicable to Model A310 

series airplanes) or with a FQIC Type 2 

having P/N SIC5077 (as applicable to Model 

A300 B4–600 series airplanes), and modify 

the associated wiring, in accordance with the 

Accomplishment Instructions of Airbus 

Mandatory Service Bulletin A300–28–6024, 

Revision 02, dated January 19, 2011; or 

Airbus Mandatory Service Bulletin A310–28– 

2039, Revision 01, dated January 19, 2011; as 

applicable. 

(h) Parts Installation Prohibition 

As of the effective date of this AD, no 

person may install any FQIC Type 1 having 

P/N SIC5054 or P/N SIC5051, on any 

airplane. 

(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: 

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. 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 Airworthiness Directive 2011–0186, 

dated September 23, 2011, and the service 

information specified in paragraphs (j)(1) and 

(j)(2) of this AD, for related information. 

(1) Airbus Mandatory Service Bulletin 

A300–28–6024, Revision 02, dated January 

19, 2011. 

(2) Airbus Mandatory Service Bulletin 

A310–28–2039, Revision 01, dated January 

19, 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 

A300–28–6024, Revision 02, dated January 

19, 2011. 

(ii) Airbus Mandatory Service Bulletin 

A310–28–2039, Revision 01, dated January 

19, 2011. 

(3) For Airbus service information 

identified in this 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.airwortheas@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. 2012–19254 Filed 8–13–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF COMMERCE 

Bureau of Industry and Security 

15 CFR Part 774 

The Commerce Control List 

CFR Correction 

In the Federal Register published on 

July 26, 2012, on page 43711, in the 

third column, in instruction 3.C., 

‘‘5A003’’ is corrected to read ‘‘5A002’’. 

[FR Doc. 2012–19955 Filed 8–13–12; 8:45 am] 

BILLING CODE 1505–01–D 

FEDERAL MINE SAFETY AND HEALTH 

REVIEW COMMISSION 

29 CFR Parts 2700, 2701, 2702, 2704, 

2705, 2706 

Commission Address Change 

AGENCY: Federal Mine Safety and Health 

Review Commission (FMSHRC). 

ACTION: Final rule. 

SUMMARY: The Federal Mine Safety and 

Health Review Commission is relocating 

its Headquarters office and is amending 

its regulations to inform the public of 

the address change. 

DATES: This final rule will take effect on 

August 27, 2012. 

ADDRESSES: This final rule is available 

on FMSHRC’s Web site, http:// 

www.fmshrc.gov. 

FOR FURTHER INFORMATION CONTACT: 

Sarah Stewart, Deputy General Counsel, 

Office of the General Counsel, Federal 

Mine Safety and Health Review 

Commission, at (202) 434–9935 or 

sstewart@fmshrc.gov. 

SUPPLEMENTARY INFORMATION: 

A. Background 

On August 24, 2012, FMSHRC will 

move its Headquarters office from 601 

New Jersey Avenue NW., Suite 9500, 

Washington, DC 20001 to 1331 

Pennsylvania Avenue NW., Suite 520N, 

Washington, DC 20004–1710. 

B. Notice and Public Procedure 

Because this amendment deals with 

agency management and procedures, the 

notice and comment provisions of the 

Administrative Procedure Act do not 

apply pursuant to 5 U.S.C. 553(a)(2) and 

(b)(3)(A). 

Good cause exists to dispense with 

the usual 30-day delay in the effective 

date because the amendments are of a 

minor and administrative nature dealing 

with only a change in address. 

The Commission is an independent 

regulatory agency and, as such, is not 


tkelley on DSK3SPTVN1PROD with RULES