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[Federal Register Volume 77, Number 157 (Tuesday, August 14, 2012)]
[Rules and Regulations]
[Pages 48427-48429]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2012-19254]

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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.

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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[deg]C. This potential

[[Page 48428]]

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 work-hours 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

0
1. The authority citation for part 39 continues to read as follows:

    Authority:  49 U.S.C. 106(g), 40113, 44701.

Sec.  39.13  [Amended]

0
2. The FAA amends Sec.  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.

[[Page 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.airworth-eas@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
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