Airworthiness Directives; Airbus Model A300 B4-600, B4-600R, and F4-600R Series Airplanes, and Model C4-605R Variant F Airplanes (Collectively Called A300-600 Series Airplanes)

[Federal Register Volume 76, Number 91 (Wednesday, May 11, 2011)]
[Rules and Regulations]
[Pages 27242-27244]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2011-10817]


-----------------------------------------------------------------------

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2011-0037; Directorate Identifier 2010-NM-273-AD; 
Amendment 39-16691; AD 2011-10-10]
RIN 2120-AA64


Airworthiness Directives; Airbus Model A300 B4-600, B4-600R, and 
F4-600R Series Airplanes, and Model C4-605R Variant F Airplanes 
(Collectively Called A300-600 Series Airplanes)

AGENCY: Federal Aviation Administration (FAA), Department of 
Transportation (DOT).

ACTION: Final rule.

-----------------------------------------------------------------------

SUMMARY: We are adopting a new airworthiness directive (AD) for the 
products listed above. This AD results from mandatory continuing 
airworthiness information (MCAI) originated by an aviation authority of 
another country to identify and correct an unsafe condition on an 
aviation product. The MCAI describes the unsafe condition as:

    [T]he FAA has published SFAR 88 (Special Federal Aviation 
Regulation 88).
    In their letters referenced 04/00/02/07/01-L296, dated March 
4th, 2002, and 04/00/02/07/03-L024, dated February 3rd, 2003, the 
JAA [Joint Aviation Authorities] recommended the application of a 
similar regulation to the National Aviation Authorities (NAA).
    Under this regulation, all holders of type certificates for 
passenger transport aircraft * * * are required to conduct a design 
review against explosion risks.
    During improvement of the protection of fuel pump wiring against 
short-circuit by accomplishment of Airbus Service Bulletin (SB) 
A300-24-6094, a study led by the manufacturer concluded that the 
harness, installed through the wing panel needed to be protected to 
prevent possible damage in case of chafing which could potentially 
lead to short-circuit [and intermittent function or loss of the 
inner tank fuel pump. Loss of both inner tank fuel pumps could 
result in inability to use the remaining fuel supply in the inner 
tank. A short-circuit could also result in an ignition source in a 
flammable leakage zone].
* * * * *

    We are issuing this AD to require actions to correct the unsafe 
condition on these products.

DATES: This AD becomes effective June 15, 2011.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of June 15, 
2011.

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, 2011 (76 
FR 6581). That NPRM proposed to correct an unsafe condition for the 
specified products. The MCAI states:

    [T]he FAA has published SFAR 88 (Special Federal Aviation 
Regulation 88).
    In their letters referenced 04/00/02/07/01-L296, dated March 
4th, 2002, and 04/00/02/07/03-L024, dated February 3rd, 2003, the 
JAA [Joint Aviation Authorities] recommended the application of a 
similar regulation to the National Aviation Authorities (NAA).
    Under this regulation, all holders of type certificates for 
passenger transport aircraft with either a passenger capacity of 30 
or more, or a payload capacity of 3,402 kg (7,500 lb) or more, which 
have received their certification since January 1st, 1958, are 
required to conduct a design review against explosion risks.
    During improvement of the protection of fuel pump wiring against 
short-circuit by

[[Page 27243]]

accomplishment of Airbus Service Bulletin (SB) A300-24-6094, a study 
led by the manufacturer concluded that the harness, installed 
through the wing panel needed to be protected to prevent possible 
damage in case of chafing which could potentially lead to short-
circuit [and intermittent function or loss of the inner tank fuel 
pump. Loss of both inner tank fuel pumps could result in inability 
to use the remaining fuel supply in the inner tank. A short-circuit 
could also result in an ignition source in a flammable leakage 
zone].
    For the reasons stated above, this [EASA] AD requires the 
replacement of bushes in the hydraulic reservoir panel.

    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 or on the determination of 
the cost to the public.

Conclusion

    We reviewed the available data and determined that air safety and 
the public interest require adopting the AD as proposed.

Differences Between This AD and the MCAI or Service Information

    We have reviewed the MCAI and related service information and, in 
general, agree with their substance. But we might have found it 
necessary to use different words from those in the MCAI to ensure the 
AD is clear for U.S. operators and is enforceable. In making these 
changes, we do not intend to differ substantively from the information 
provided in the MCAI and related service information.
    We might also have required different actions in this AD from those 
in the MCAI in order to follow our FAA policies. Any such differences 
are highlighted in a NOTE within the AD.

Costs of Compliance

    We estimate that this AD will affect 120 products of U.S. registry. 
We also estimate that it will take about 13 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 $266 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 $164,520, or $1,371 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 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); and
    3. 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, 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:

2011-10-10 Airbus: Amendment 39-16691. Docket No. FAA-2011-0037; 
Directorate Identifier 2010-NM-273-AD.

Effective Date

    (a) This airworthiness directive (AD) becomes effective June 15, 
2011.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to all Airbus Model A300 B4-601, B4-603, B4-
620, B4-622, B4-605R, B4-622R, F4-605R, F4-622R, and C4-605R Variant 
F airplanes, certificated in any category, all certified models, all 
serial numbers, except airplanes on which Airbus Mandatory Service 
Bulletin A300-24-6102 (Airbus Modification 13381) has been embodied.

Subject

    (d) Air Transport Association (ATA) of America Code 24: 
Electrical Power.

Reason

    (e) The mandatory continuing airworthiness information (MCAI) 
states:

    [T]he FAA has published SFAR 88 (Special Federal Aviation 
Regulation 88).
    In their letters referenced 04/00/02/07/01-L296, dated March 
4th, 2002, and 04/00/02/07/03-L024, dated February 3rd, 2003, the 
JAA [Joint Aviation Authorities] recommended the application of a 
similar regulation to the National Aviation Authorities (NAA).
    Under this regulation, all holders of type certificates for 
passenger transport aircraft * * * are required to conduct a design 
review against explosion risks.
    During improvement of the protection of fuel pump wiring against 
short-circuit by accomplishment of Airbus Service Bulletin (SB) 
A300-24-6094, a study led by the manufacturer concluded that the 
harness, installed through the wing panel needed to be protected to 
prevent possible damage in case of chafing which could potentially 
lead to short-circuit [and intermittent function or loss of the 
inner tank fuel pump. Loss of both inner tank fuel pumps could 
result in

[[Page 27244]]

inability to use the remaining fuel supply in the inner tank. A 
short-circuit could also result in an ignition source in a flammable 
leakage zone].
* * * * *

Compliance

    (f) You are responsible for having the actions required by this 
AD performed within the compliance times specified, unless the 
actions have already been done.

Actions

    (g) Within 30 months after the effective date of this AD, 
install Teflon bushes in the hydraulic reservoir panel at the lower 
left-hand side in accordance with the Accomplishment Instructions of 
Airbus Mandatory Service Bulletin A300-24-6102, Revision 01, dated 
September 24, 2010.

Credit for Actions Accomplished in Accordance With Previous Service 
Information

    (h) Actions done before the effective date of this AD in 
accordance with Airbus Mandatory Service Bulletin A300-24-6102, 
dated August 13, 2009, are acceptable for compliance with the 
corresponding requirements of this AD.

FAA AD Differences

    Note 1: This AD differs from the MCAI and/or service information 
as follows: No differences.

Other FAA AD Provisions

    (i) 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 e-mailed to: [email protected]. 
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.

Related Information

    (j) Refer to MCAI European Aviation Safety Agency Airworthiness 
Directive 2010-0225, dated November 5, 2010; and Airbus Mandatory 
Service Bulletin A300-24-6102, Revision 01, dated September 24, 
2010; for related information.

Material Incorporated by Reference

    (k) You must use Airbus Mandatory Service Bulletin A300-24-6102, 
Revision 01, dated September 24, 2010, to do the actions required by 
this AD, unless the AD specifies otherwise.
    (1) The Director of the Federal Register approved the 
incorporation by reference of this service information under 5 
U.S.C. 552(a) and 1 CFR part 51.
    (2) For 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; e-mail [email protected]; 
Internet http://www.airbus.com.
    (3) 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.
    (4) 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/code_of_federal_regulations/ibr_locations.html.

    Issued in Renton, Washington, on April 26, 2011.
Kalene C. Yanamura,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2011-10817 Filed 5-10-11; 8:45 am]
BILLING CODE 4910-13-P

The complete text was extracted from the official GovInfo HTML edition for this publication. Acquired 2026-10-09T03:09:09.098420+00:00. Text extraction preserves the recorded source wording; it does not determine current requirements.

Open the captured official edition

Source SHA-256

a8617cddcdae820f299c9bb2dfbe21278e1bf22b127161746ee87c19d9a9b146

Text SHA-256

cd0fe29799b97e404346e237465d0e2be8800b2cf94ef82f338df9662ea1c75f