AD 2011-14-01

[Federal Register Volume 76, Number 129 (Wednesday, July 6, 2011)]
[Rules and Regulations]
[Pages 39248-39251]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 2011-15991]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2010-1197; Directorate Identifier 2010-NM-044-AD; 
Amendment 39-16736; AD 2011-14-01]
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); and Model A310 Series 
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 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:

    An operator of an A300-600 aeroplane reported finding a cracked 
pylon fuel drain pipe on engine <greek-i>1. * * *
    * * * The pipe drains the double wall of the wing-to-pylon 
junction in the event of fuel leakage.
    After investigation, it was concluded that the damage of the 
pylon fuel drain pipe had been caused by chafing of the pipe against 
over-length screws that had been installed in accordance with the 
Illustrated Parts Catalogue (IPC) during a maintenance phase of the 
Lower Aft Pylon Fairing (LAPF).
    This condition, if not detected and corrected, could, in 
combination with fuel leakage in the pylon, lead to an accumulation 
of fuel in the lowest point of the LAPF. As high temperatures are 
present within the

[[Page 39249]]

LAPF, and without ventilation, this could result in fuel (vapour) 
ignition and consequent fire.
* * * * *

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

DATES: This AD becomes effective August 10, 2011.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in this AD as of August 10, 
2011.

ADDRESSES: You may examine the AD docket on the Internet at <a href="http://www.regulations.gov">http://www.regulations.gov</a> 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 December 10, 2010 
(75 FR 76926). That NPRM proposed to correct an unsafe condition for 
the specified products. The MCAI states:

    An operator of an A300-600 aeroplane reported finding a cracked 
pylon fuel drain pipe on engine <greek-i>1.The pipe, Part Number (P/
N) A71715020, had separated and the end was found 5.5 inches from 
the pylon aft bulkhead. A similar case was also reported on an 
A300F4-608ST aeroplane.
    The affected pylon fuel drain pipe runs from the top of the 
pylon primary structure to the aft part of the pylon rear secondary 
structure and is partly attached under the pylon lower spar. The 
pipe drains the double wall of the wing-to-pylon junction in the 
event of fuel leakage.
    After investigation, it was concluded that the damage of the 
pylon fuel drain pipe had been caused by chafing of the pipe against 
over-length screws that had been installed in accordance with the 
Illustrated Parts Catalogue (IPC) during a maintenance phase of the 
Lower Aft Pylon Fairing (LAPF).
    This condition, if not detected and corrected, could, in 
combination with fuel leakage in the pylon, lead to an accumulation 
of fuel in the lowest point of the LAPF. As high temperatures are 
present within the LAPF, and without ventilation, this could result 
in fuel (vapour) ignition and consequent fire.
    To address and correct this unsafe condition, EASA * * * 
required an inspection [for missing pipes, or distortions or holes] 
of the pylon fuel drain pipe and the attachment screws and, 
depending on findings, the necessary corrective actions. In case 
over-length screws are found to be installed, depending on location 
and aeroplane configuration, these must be replaced.
* * * * *

    Required actions also include visually inspecting to determine the 
length and part number of the drain pipe attachment screws on the LAPF 
on the left- and right-hand pylons. Corrective actions include 
replacing or repairing the pipe, or replacing screws with incorrect 
part numbers with new screws. 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 considered the comments received.

Request To Extend the Compliance Time

    UPS requested that we extend the compliance time from 30 days to 30 
months after the effective date of the AD. Per the commenter, the NPRM 
stated that the over-length screws installed on the affected aircraft 
were installed in accordance with the illustrated parts catalog (IPC), 
and that the correct attachment screws are clearly identified in the 
UPS A300-600 IPC, so there is a minimal probability of installing an 
over-length screw. The commenter stated that the compliance time of 30 
days is too restrictive and believes that extending the threshold to 30 
months for those operators whose IPC does not list an over-length 
fastener would provide an equivalent level of safety and better fit 
within an operator's routine maintenance program and eliminate any 
undue burden associated with a restrictive timetable.
    We do not agree to extend the compliance time. The FAA received 
information confirming that over-length screws could have been 
introduced in production due to some erroneous drawings. Further, 
before 2007, not all IPCs were correct. Some of the IPCs for aircraft 
fitted with Pratt & Whitney engines were corrected in 2007. All IPCs 
were checked in 2010, and remaining erroneous IPCs were corrected. 
Although UPS may have the correct IPC, since some over-length screws 
could have been installed during production, a fleet inspection is 
needed to address the identified unsafe condition. However, under the 
provisions of paragraph (k) of this AD, we will consider requests for 
approval of an extension of the compliance time if sufficient data are 
submitted to substantiate that the new compliance time would provide an 
acceptable level of safety. We have not changed the AD in this regard.

Request To Use Thicker Washer as Advised in Service Information Letter

    UPS requested FAA concurrence that using an alternative washer, P/N 
NSA5149-3, as recommended by Airbus in Service Information Letter 54-
035, Revision 01, dated July 9, 2010, will not have an impact on the 
AD. This washer would be used in lieu of P/N NSA5149-4 under the head 
of the attachment screws, to prevent cracking of the LAPF.
    We partially agree with the commenter's request. The alternative 
washer is a recommended improvement, but not a modification addressing 
an unsafe condition/airworthiness issue. As the Service Information 
Letter mentions, both washers are fully interchangeable; the last IPC 
update (2010) also reflects this interchangeability. Therefore, we 
confirm that use of either washer is adequate. In this regard, and to 
avoid the need for an alternative method of compliance (AMOC) on this 
issue in the future, we have added the washer having P/N NSA5149-3 to 
paragraphs (g)(1) and (g)(2) of this AD.

Conclusion

    We reviewed the available data, including the comments received, 
and determined that air safety and the public interest require adopting 
the AD with the change described previously. We determined that this 
change will not increase the economic burden on any operator or 
increase the scope of the AD.

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 168 products of U.S. registry. 
We also estimate that it will take about 4 work-

[[Page 39250]]

hours per product to comply with the basic requirements of this AD. The 
average labor rate is $85 per work-hour. Based on these figures, we 
estimate the cost of this AD to the U.S. operators to be $57,120, or 
$340 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 <a href="http://www.regulations.gov">http://www.regulations.gov</a>; 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:

2011-14-01 Airbus: Amendment 39-16736. Docket No. FAA-2010-1197; 
Directorate Identifier 2010-NM-044-AD.

Effective Date

    (a) This airworthiness directive (AD) becomes effective August 
10, 2011.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to Airbus Model A300 B4-601, B4-603, B4-620, 
and B4-622 airplanes; Model A300 B4-605R and B4-622R airplanes; 
Model A300 F4-605R and F4-622R airplanes; Model A300 C4-605R Variant 
F airplanes; and Model A310-203, -204, -221, -222, -304, -322, -324, 
and -325 airplanes; certificated in any category; all serial 
numbers.

Subject

    (d) Air Transport Association (ATA) of America Code 54: 
Nacelles/pylons.

Reason

    (e) The mandatory continuing airworthiness information (MCAI) 
states:
    An operator of an A300-600 aeroplane reported finding a cracked 
pylon fuel drain pipe on engine <greek-i>1. * * *
    * * * The pipe drains the double wall of the wing-to-pylon 
junction in the event of fuel leakage.
    After investigation, it was concluded that the damage of the 
pylon fuel drain pipe had been caused by chafing of the pipe against 
over-length screws that had been installed in accordance with the 
Illustrated Parts Catalogue (IPC) during a maintenance phase of the 
Lower Aft Pylon Fairing (LAPF).
    This condition, if not detected and corrected, could, in 
combination with fuel leakage in the pylon, lead to an accumulation 
of fuel in the lowest point of the LAPF. As high temperatures are 
present within the LAPF, and without ventilation, this could result 
in fuel (vapour) ignition and consequent fire.
* * * * *

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.

Inspection and Corrective Actions

    (g) Within 30 days after the effective date of this AD, do a 
general visual inspection for missing pipes, or distortions or 
holes, of the fuel drain pipes of the LAPF, and if no missing pipes, 
distortions, and holes are found, do a general visual inspection to 
determine the length and part number of the drain pipe attachment 
screws on the LAPF on the left-hand and right-hand pylons, in 
accordance with the Accomplishment Instructions of Airbus Mandatory 
Service Bulletin A300-54A6039, Revision 01, dated March 11, 2010 
(for Model A300-600 series airplanes); or A310-54A2040, Revision 02, 
dated June 10, 2010 (for Model A310 series airplanes).
    (1) If missing pipes, distortions, or holes of the fuel drain 
pipes are detected during any inspection required by paragraph (g) 
of this AD, before further flight, replace the drain pipe, in 
accordance with the Accomplishment Instructions of Airbus Mandatory 
Service Bulletin A300-54A6039, Revision 01, dated March 11, 2010 
(for Model A300-600 series airplanes); or A310-54A2040, Revision 02, 
dated June 10, 2010 (for Model A310 series airplanes); or contact 
Airbus for repair instructions and do the repair; except where the 
applicable service bulletin specifies using washers having part 
number (P/N) NSA5149-4, washers having P/N NSA5149-3 may 
alternatively be used.
    (2) If screw length is outside the measurement specified in the 
Accomplishment Instructions of Airbus Mandatory Service Bulletin 
A300-54A6039, Revision 01, dated March 11, 2010 (for Model A300-600 
series airplanes); or A310-54A2040, Revision 02, dated June 10, 2010 
(for Model A310 series airplanes); or screws having incorrect part 
numbers are found during any inspection required by paragraph (g) of 
this AD, before further flight, replace the screws with screws 
having P/N NAS1102E3-10, NAS1102E3-12, or NAS560HK3-2, as applicable 
to location and airplane (engine) configuration, in accordance with 
the Accomplishment Instructions of Airbus Mandatory Service Bulletin 
A300-54A6039, Revision 01, dated March 11, 2010 (for Model A300-600 
series airplanes); or A310-54A2040, Revision 02, dated June 10, 2010 
(for Model A310 series airplanes); except where the applicable 
service bulletin specifies using washers having P/N NSA5149-4, 
washers having P/N NSA5149-3 may alternatively be used.
    (h) As of the effective date of this AD, do not install screws 
on the LAPF, other than screws having P/N NAS1102E3-10, NAS1102E3-
12, or NAS560HK3-2, as applicable to location and airplane (engine) 
configuration, in accordance with the Accomplishment Instructions of 
Airbus Mandatory Service Bulletin A300-54A6039,

[[Page 39251]]

Revision 01, dated March 11, 2010 (for Model A300-600 series 
airplanes); or A310-54A2040, Revision 02, dated June 10, 2010 (for 
Model A310 series airplanes).

Credit for Actions Accomplished in Accordance With Previous Service 
Information

    (i) Actions accomplished before the effective date of this AD in 
accordance with the service bulletins identified in table 1 of this 
AD are considered acceptable for compliance with the corresponding 
actions specified in this AD.

                                        Table 1--Credit Service Bulletins
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                                    Airbus Mandatory
           For model--             Service Bulletin--           Revision--                     Dated--
----------------------------------------------------------------------------------------------------------------
A300-600 series airplanes.......  A300-54A6039.......  Original....................  January 19, 2010.
A310 series airplanes...........  A310-54A2040.......  Original....................  January 19, 2010.
A310 series airplanes...........  A310-54A2040.......  01..........................  March 11, 2010.
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No Reporting

    (j) Although Airbus Mandatory Service Bulletins A300-54A6039, 
Revision 01, dated March 11, 2010; and A310-54A2040, Revision 02, 
dated June 10, 2010; specify to submit certain information to the 
manufacturer, this AD does not include that requirement.

FAA AD Differences

    Note 1: This AD differs from the MCAI and/or service information 
as follows: Although the MCAI or service information tells you to 
submit information to the manufacturer, paragraph (j) of this AD 
does not require that information.

Other FAA AD Provisions

    (k) 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. Before 
using any approved AMOC on any airplane to which the AMOC applies, 
notify your principal maintenance inspector (PMI) or principal 
avionics inspector (PAI), as appropriate, or lacking a principal 
inspector, your local Flight Standards 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

    (l) Refer to MCAI European Aviation Safety Agency Airworthiness 
Directive 2010-0085, dated May 3, 2010; Airbus Mandatory Service 
Bulletin A300-54A6039, Revision 01, dated March 11, 2010; and Airbus 
Mandatory Service Bulletin A310-54A2040, Revision 02, dated June 10, 
2010; for related information.

Material Incorporated by Reference

    (m) You must use Airbus Mandatory Service Bulletin A300-54A6039, 
Revision 01, excluding Appendix 01 and including Appendices 02 and 
03, dated March 11, 2010; or Airbus Mandatory Service Bulletin A310-
54A2040, Revision 02, excluding Appendix 01 and including Appendices 
02 and 03, dated June 10, 2010; as applicable; 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: <a href="/cdn-cgi/l/email-protection#630200000c160d174d020a11140c11170b4e06021023020a110116104d000c0e"><span class="__cf_email__" data-cfemail="610002020e140f154f000813160e1315094c040012210008130314124f020e0c">[email&#160;protected]</span></a>; 
Internet <a href="http://www.airbus.com">http://www.airbus.com</a>.
    (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: <a href="http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html">http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html</a>.

    Issued in Renton, Washington, on June 16, 2011.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2011-15991 Filed 7-5-11; 8:45 am]
BILLING CODE 4910-13-P