Document ID: FAA-2009-0790-0005
Agency: faa
Document Type: Rule
Title: Airworthiness Directives: Airbus Model A330-200 and -300 Airplanes and Model A340-200, -300, -500, and -600 Airplanes
Posted Date: 2010-07-13T04:00Z

[Federal Register: July 13, 2010 (Volume 75, Number 133)]
[Rules and Regulations]               
[Page 39790-39795]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr13jy10-2]                         

[[Page 39790]]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2009-0790; Directorate Identifier 2008-NM-177-AD; 
Amendment 39-16285; AD 2010-10-06]
RIN 2120-AA64

 
Airworthiness Directives; Airbus Model A330-200 and -300 
Airplanes and Model A340-200, -300, -500, and -600 Airplanes

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

ACTION: Final rule.

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

SUMMARY: We are superseding an existing 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:

    Uncontained APU [auxiliary power unit] generator failures on 
ground have occurred on Airbus A330 aircraft in service. APU 
generator design is common to all A330 and A340 aircraft.
    Preliminary investigations confirmed that these failures have 
resulted in structural damage to the APU compartment and, in one 
case, to the stabiliser compartment. Loose APU generator parts can 
lead to damage to the APU firewall, reducing its fire extinguishing 
capability and potentially leading to a temporary uncontrolled fire.
    Although the root cause has not yet been determined, the 
investigation showed a sequence of events where a collapse of the 
Drive End Bearing (DEB) leads to an uncontained failure. Evidence 
has also shown that the DEB failures are not instantaneous, and 
therefore, the detection of small debris could indicate early stage 
of a DEB failure.
* * * * *

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

DATES: This AD becomes effective August 17, 2010.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in this AD as of August 17, 
2010.
    On June 26, 2007 (72 FR 31973, June 11, 2007), the Director of the 
Federal Register approved the incorporation by reference of certain 
other publications listed in this AD.

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, Washington 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 September 25, 2009 
(74 FR 48872), and proposed to supersede AD 2007-18-04, Amendment 39-
15184 (72 FR 50042, August 30, 2007). That NPRM proposed to correct an 
unsafe condition for the specified products. The MCAI states:

    Uncontained APU [auxiliary power unit] generator failures on 
ground have occurred on Airbus A330 aircraft in service. APU 
generator design is common to all A330 and A340 aircraft.
    Preliminary investigations confirmed that these failures have 
resulted in structural damage to the APU compartment and, in one 
case, to the stabiliser compartment. Loose APU generator parts can 
lead to damage to the APU firewall, reducing its fire extinguishing 
capability and potentially leading to a temporary uncontrolled fire.
    Although the root cause has not yet been determined, the 
investigation showed a sequence of events where a collapse of the 
Drive End Bearing (DEB) leads to an uncontained failure. Evidence 
has also shown that the DEB failures are not instantaneous, and 
therefore, the detection of small debris could indicate early stage 
of a DEB failure.
    To address this subject, EASA issued Emergency AD 2007-0188-E, 
requiring repetitive inspections of the APU generator Scavenge 
filter element and filter housing and of the APU generator Drain 
plug for signs of small debris coming from the APU generator, 
allowing detection of the early stage of APU generator failure. That 
AD was later revised to extend the compliance time and to provide 
another option for the repetitive inspection.
    Subsequently, another uncontained APU generator failure occurred 
on ground on an A330 aircraft, operated within the provisions of 
MMEL [master minimum equipment list] item 36-11-01, with similar 
structural damages as the previous APU generator burst events. The 
investigation of this event revealed that the inspection required by 
paragraph 4 of AD 2007-0188R1 before the first flight under the MMEL 
rectification interval had not been performed and that the APU 
generator had not been properly installed (two seal plates instead 
of one).
    Consequently, EASA issued AD 2008-0017, superseding AD 2007-
0188R1 and requiring the following additional actions:
    --a visual inspection of the APU generator seal plate fitting,
    --an inspection following MMEL item 36-11-01 or 24-22-01 
rectification and
    --an inspection each time a new or serviceable APU generator or 
APU is installed on an aircraft.
    EASA issued AD 2008-0017R1 to cancel the inspection of paragraph 
4 for A330 aircraft, when operated within the provisions of MMEL 
item 36-11-01 further to ETOPS [Extended-Range Twin-Engine 
Operations Performance Standards] certification of A330 APU.
    Finally, Airbus has developed a secondary housing for the APU 
generator that is designed to contain APU generator parts in the 
event of an APU generator burst.
    For the above described reasons, this AD retains the 
requirements of EASA AD 2008-0017R1, which is superseded, and adds 
the requirement to install a secondary housing on the APU generator. 
After installation of the secondary APU generator housing on an 
aircraft, the repetitive inspections of this AD are no longer 
required for that aircraft.

This AD retains the requirements of AD 2007-18-04. The new requirements 
include inspecting the APU generator scavenge oil filter element for 
contamination, the APU generator drain plug for contamination, and the 
APU generator scavenge filter housing for contamination, and a 
terminating action (installing a secondary housing line replaceable 
unit). Applicable corrective actions include, depending on the 
findings, replacing or reinstalling the APU generator scavenge oil 
filter and packing, replacing or reinstalling the APU generator drain 
plug, and replacing or reinstalling the APU generator scavenge filter 
housing. You may obtain further information by examining the MCAI in 
the AD docket.

Relevant Service Information

    The NPRM cited Airbus Service Bulletins A330-24-3045, dated June 
13, 2008; A340-24-4058, dated June 13, 2008; and A340-24-5022, dated 
June 23, 2008. Airbus has released the following new service bulletins:

[[Page 39791]]

                     Table--New Service Information
------------------------------------------------------------------------
           Airbus--              Revision--            Dated--
------------------------------------------------------------------------
Mandatory Service Bulletin               01  October 1, 2008.
 A330-24-3045.
Mandatory Service Bulletin               01  October 1, 2008.
 A340-24-4058.
Mandatory Service Bulletin               01  November 27, 2008.
 A340-24-5022.
------------------------------------------------------------------------

    The latest revisions of the service information make minor updates 
and specify that no additional work is necessary on airplanes modified 
in accordance with the original documents. We have revised this final 
rule to incorporate the latest revisions of the service information. We 
have also added paragraph (h)(6) and Table 5 to this AD to give credit 
for actions done in accordance with the original service information. 
We have reidentified subsequent tables accordingly.

Comments

    We gave the public the opportunity to participate in developing 
this AD. We considered the comment received.

Request To Include a Terminating Modification for Actions Required by 
Paragraphs (h)(3) and (h)(4) of the NPRM

    EVA Airways Corporation (EVA) requests that we revise the NPRM to 
include a terminating modification for actions required by paragraphs 
(h)(3) and (h)(4) of the NPRM. Accomplishing the actions specified in 
paragraph (h)(5) of the NPRM would terminate the actions required by 
paragraphs (g)(2), (g)(3), and (h)(2) of the NPRM. EVA refers to a 
message it received from Airbus and states that installing the APU 
generator secondary housing terminates the repetitive inspections 
specified in paragraphs (g)(2), (g)(3), (h)(2), (h)(3), and (h)(4) of 
the NPRM.
    We agree with the commenter's request. The EASA AD specifies that 
installing the secondary housing line replacement unit terminates 
repetitive inspections. We have also received information from Airbus 
indicating that installing the APU generator secondary housing 
terminates the repetitive inspections required by paragraphs (h)(3) and 
(h)(4) of the NPRM. We have revised paragraph (h)(5) of this final rule 
to specify that installing the APU generator secondary housing 
terminates the repetitive inspections specified in paragraphs (g)(2) 
and (g)(3) of this AD and the inspections specified in paragraphs 
(h)(2), (h)(3), and (h)(4) of this AD. We have also revised paragraphs 
(g)(2) and (g)(3) of this final rule to clarify that doing the 
installation required by paragraph (h)(5) of this AD terminates the 
repetitive inspections. We have also revised paragraphs (h)(2), (h)(3), 
and (h)(4) of this AD to clarify that doing the installation terminates 
the inspection requirements of those paragraphs.

Explanation of Changes Made to This AD

    In paragraphs (g)(1), (g)(2), and (g)(3) of this AD, we have 
clarified that the service information specified in Table 2 or Table 3 
of this AD is acceptable for compliance with the applicable actions.

Conclusion

    We reviewed the relevant data, considered the comment received, and 
determined that air safety and the public interest require adopting the 
AD with the changes described previously. We also determined that these 
changes 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.

Explanation of Change to Costs of Compliance

    Since issuance of the NPRM, we have increased the labor rate used 
in the Costs of Compliance from $80 per work-hour to $85 per work-hour. 
The Costs of Compliance information, below, reflects this increase in 
the specified hourly labor rate.

Costs of Compliance

    We estimate that this AD will affect about 41 products of U.S. 
registry.
    The actions that are required by AD 2007-18-04 and retained in this 
AD take about 11 work-hours per product, at an average labor rate of 
$85 per work hour. Required parts cost $0 per product. Based on these 
figures, the estimated cost of the currently required actions is $935 
per product.
    We estimate that it will take about 10 work-hours per product to 
comply with the new basic requirements of this AD. The average labor 
rate is $85 per work-hour. Required parts will cost about $0 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 costs. 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 $34,850, or $850 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:

[[Page 39792]]

    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

0
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 removing Amendment 39-15184 (72 FR 
50042, August 30, 2007) and adding the following new AD:

2010-10-06 Airbus: Amendment 39-16285. Docket No. FAA-2009-0790; 
Directorate Identifier 2008-NM-177-AD.

Effective Date

    (a) This airworthiness directive (AD) becomes effective August 
17, 2010.

Affected ADs

    (b) This AD supersedes AD 2007-18-04, Amendment 39-15184.

Applicability

    (c) This AD applies to the airplanes certificated in any 
category, identified in paragraphs (c)(1) and (c)(2) of this AD.
    (1) Airbus Model A330-201, -202, -203, -223, -243, -301, -302, -
303, -321, -322, -323, -341, -342, and -343 series airplanes, all 
serial numbers, except those on which Airbus modification 56985 has 
been embodied in production.
    (2) Airbus Model A340-211, -212, -213, -311, -312, and -313 
series airplanes; and Model A340-541 and A340-642 airplanes; all 
serial numbers, except those on which Airbus modification 56985 has 
been embodied in production.

Subject

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

Reason

    (e) The mandatory continuing airworthiness information (MCAI) 
states:
    Uncontained APU [auxiliary power unit] generator failures on 
ground have occurred on Airbus A330 aircraft in service. APU 
generator design is common to all A330 and A340 aircraft.
    Preliminary investigations confirmed that these failures have 
resulted in structural damage to the APU compartment and, in one 
case, to the stabiliser compartment. Loose APU generator parts can 
lead to damage to the APU firewall, reducing its fire extinguishing 
capability and potentially leading to a temporary uncontrolled fire.
    Although the root cause has not yet been determined, the 
investigation showed a sequence of events where a collapse of the 
Drive End Bearing (DEB) leads to an uncontained failure. Evidence 
has also shown that the DEB failures are not instantaneous, and 
therefore, the detection of small debris could indicate early stage 
of a DEB failure.
    To address this subject, EASA issued Emergency AD 2007-0188-E, 
requiring repetitive inspections of the APU generator Scavenge 
filter element and filter housing and of the APU generator Drain 
plug for signs of small debris coming from the APU generator, 
allowing detection of the early stage of APU generator failure. That 
AD was later revised to extend the compliance time and to provide 
another option for the repetitive inspection.
    Subsequently, another uncontained APU generator failure occurred 
on ground on an A330 aircraft, operated within the provisions of 
MMEL [master minimum equipment list] item 36-11-01, with similar 
structural damages as the previous APU generator burst events. The 
investigation of this event revealed that the inspection required by 
paragraph 4 of AD 2007-0188R1 before the first flight under the MMEL 
rectification interval had not been performed and that the APU 
generator had not been properly installed (two seal plates instead 
of one).
    Consequently, EASA issued AD 2008-0017, superseding AD 2007-
0188R1 and requiring the following additional actions:

--a visual inspection of the APU generator seal plate fitting,
--an inspection following MMEL item 36-11-01 or 24-22-01 
rectification and
--an inspection each time a new or serviceable APU generator or APU 
is installed on an aircraft.

    EASA issued AD 2008-0017R1 to cancel the inspection of paragraph 
4 for A330 aircraft, when operated within the provisions of MMEL 
item 36-11-01 further to ETOPS [Extended-Range Twin-Engine 
Operations Performance Standards] certification of A330 APU.
    Finally, Airbus has developed a secondary housing for the APU 
generator that is designed to contain APU generator parts in the 
event of an APU generator burst.
    For the above described reasons, this AD retains the 
requirements of EASA AD 2008-0017R1, which is superseded, and adds 
the requirement to install a secondary housing on the APU generator. 
After installation of the secondary APU generator housing on an 
aircraft, the repetitive inspections of this AD are no longer 
required for that aircraft.

This AD retains the requirements of AD 2007-18-04, which superseded 
AD 2007-12-10, Amendment 39-15088. The new requirements include 
inspecting the APU generator scavenge oil filter element for 
contamination, the APU generator drain plug for contamination, and 
the APU generator scavenge filter housing for contamination, and a 
terminating action (installing a secondary housing line replaceable 
unit). Applicable corrective actions include, depending on the 
findings, replacing or reinstalling the APU generator scavenge oil 
filter and packing, replacing or reinstalling the APU generator 
drain plug, and replacing or reinstalling the APU generator scavenge 
filter housing.

RESTATEMENT OF REQUIREMENTS OF AD 2007-12-10, WITH NO CHANGES

Actions and Compliance

    (f) Unless already done, do the following actions.
    (1) For airplanes on which the date of issuance of the original 
French airworthiness certificate or the date of issuance of the 
original French or EASA export certificate of airworthiness is 
before March 1, 2007: Within 63 days after June 26, 2007 (the 
effective date of AD 2007-12-10), in accordance with the 
instructions of Airbus All Operators Telex (AOT) A330-24A3042, A340-
24A4056, or A340-24A5020, all Revision 02, all dated April 12, 2007; 
as applicable, inspect the inlet screen (last chance filter) for the 
generator scavenge-oil pump for signs of debris and, as applicable, 
apply all associated corrective actions before further flight.
    (2) For Model A330 aircraft operating under MMEL (master minimum 
equipment list) Item 24-22-01 `AC Main Generation' or MMEL Item 36-
11-01 `Bleed Air Supply System Failure' and on which the date of 
issuance of the original French airworthiness certificate or the 
date of issuance of the original French or EASA export certificate 
of airworthiness is before March 1, 2007: As of June 26, 2007, 
before each flight, perform a check of the differential pressure 
indicator button on the lube filter and the generator scavenge 
filter in accordance with the instructions of Airbus AOT A330-
24A3042, Revision 02, dated April 12, 2007, until accomplishment of 
paragraph (g)(5) of this AD.

    Note 1:  The repetitive checks before each flight specified in 
paragraph (f)(2) of this AD are not required for airplanes operated 
under

[[Page 39793]]

MMEL Item 36-11-01, provided the APU generator has been removed or 
deactivated in accordance with the instructions of Airbus AOT A330-
24A3042, Revision 02, dated April 12, 2007.

    (3) Actions done before June 26, 2007, in accordance with the 
applicable Airbus service information in Table 1 of this AD are 
acceptable for compliance with the corresponding provisions of 
paragraph (f) of this AD.

      Table 1--Acceptable Earlier Revisions of Service Information
------------------------------------------------------------------------
 Airbus all operators telex--       Revision--            Dated--
------------------------------------------------------------------------
A330-24A3042..................  Original.........  March 22, 2007.
A330-24A3042..................  01...............  March 29, 2007.
A340-24A4056..................  Original.........  March 22, 2007.
A340-24A4056..................  01...............  March 29, 2007.
A340-24A5020..................  Original.........  March 22, 2007.
A340-24A5020..................  01...............  March 29, 2007.
------------------------------------------------------------------------

RESTATEMENT OF REQUIREMENTS OF AD 2007-18-04, WITH REVISED SERVICE 
INFORMATION

Actions and Compliance

    (g) Unless already done, do the following actions.
    (1) For airplanes on which the date of issuance of the original 
French airworthiness certificate or the date of issuance of the 
original French or EASA export certificate of airworthiness is on or 
before July 1, 2007: Within 30 days after September 14, 2007 (the 
effective date of AD 2007-18-04), in accordance with the 
instructions of paragraph 4.2.1 of the applicable Airbus service 
information specified in Table 2 or 3 of this AD, clean and inspect 
the APU generator scavenge oil filter element and housing and 
inspect the APU generator drain plug to detect metallic debris, and 
apply all applicable associated corrective actions before further 
flight. After the effective date of this AD, use only the service 
information specified in Table 3 of this AD.

                      Table 2--Service Information
------------------------------------------------------------------------
  Airbus all operators telex--    Revision--            Dated--
------------------------------------------------------------------------
A330-24A3044...................           01  July 20, 2007.
A330-24A3044...................           02  December 20, 2007.
A340[dash]24A4057..............           02  August 14, 2007.
A340-24A5021...................           01  July 20, 2007.
------------------------------------------------------------------------

                    Table 3--New Service Information
------------------------------------------------------------------------
  Airbus all operators telex--    Revision--            Dated--
------------------------------------------------------------------------
A330-24A3044...................           03  May 26, 2008.
A340-24A4057...................           03  December 20, 2007.
A340-24A5021...................           02  December 20, 2007.
------------------------------------------------------------------------

    (2) Within 450 aircraft flight hours or 200 APU operating hours, 
whichever occurs later, after accomplishing the inspection required 
by paragraph (g)(1) of this AD, in accordance with the instructions 
of paragraph 4.2.2 of the applicable Airbus information specified in 
Table 2 or Table 3 of this AD: Inspect the APU generator scavenge 
oil filter element and housing and the APU generator drain plug to 
detect metallic debris; and apply all applicable associated 
corrective actions before further flight. Repeat the inspections 
thereafter at intervals not to exceed 450 aircraft flight hours or 
200 APU operating hours, whichever occurs later until the 
installation required by paragraph (h)(5) of this AD is done. After 
the effective date of this AD, use only the service information 
specified in Table 3 of this AD.
    (3) For airplanes on which the date of issuance of the original 
French airworthiness certificate or the date of issuance of the 
original French or EASA export certificate of airworthiness is after 
July 1, 2007: Within 450 aircraft flight hours or 200 APU operating 
hours after September 14, 2007, whichever occurs later, in 
accordance with the instructions of paragraph 4.2.2 of the 
applicable Airbus service information specified in Table 2 or Table 
3 of this AD: Inspect the APU generator scavenge oil filter element 
and housing and the APU generator drain plug to detect metallic 
debris; and apply all applicable associated corrective actions 
before further flight. Repeat the inspections thereafter at 
intervals not to exceed 450 aircraft flight hours or 200 APU 
operating hours, whichever occurs later until the installation 
required by paragraph (h)(5) of this AD is done. After the effective 
date of this AD, use only the service information specified in Table 
3 of this AD.
    (4) Actions done before September 14, 2007, in accordance with 
the applicable Airbus service information in Table 4 of this AD are 
acceptable for compliance with the corresponding provisions of 
paragraph (g) of this AD.

      Table 4--Acceptable Earlier Revisions of Service Information
------------------------------------------------------------------------
  Airbus all operators telex--       Revision--            Dated--
------------------------------------------------------------------------
A330-24A3044...................  Original..........  July 5, 2007.
A340[dash]24A4057..............  Original..........  July 5, 2007.
A340[dash]24A4057..............  01................  July 20, 2007.
A340-24A5021...................  Original..........  July 5, 2007.
------------------------------------------------------------------------

[[Page 39794]]

     (5) For Model A330 aircraft operating under MMEL Item 24-22-01, 
``AC Main Generation,'' or MMEL Item 36-11-01, ``Bleed Air Supply 
System Failure'': Unless the APU generator has been deferred in 
accordance with the MMEL by deactivation (quill shaft removed) or 
removal, the inspection required by paragraph (g)(2) or (g)(3), as 
applicable, of this AD must be performed prior to the first flight 
of the specified MMEL repair time interval. Accomplishing the 
actions in this paragraph terminates the actions required by 
paragraph (f)(2) of this AD.

    Note 2:  For A330 aircraft, MMEL Item 24-22-01 (AC Main 
Generation) and/or MMEL Item 36-11-01 (Bleed Air Supply System 
Failure) require that the APU be used during the entire flight.

NEW REQUIREMENTS OF THIS AD

Actions and Compliance

    (h) Unless already done, do the following actions.
    (1) As of the effective date of this AD, before further flight 
after an APU generator or an APU is installed on the airplane: 
Inspect the APU generator scavenge oil filter element for 
contamination (including metallic particles), the APU generator 
drain plug for contamination (including metallic particles), and the 
APU generator scavenge filter housing for contamination (including 
metallic particles), in accordance with paragraph 4.2 of the 
applicable service information specified in Table 3 of this AD. Do 
all applicable corrective actions before further flight in 
accordance with paragraph 4.2 of the applicable service information 
specified in Table 3 of this AD.
    (2) Within 450 aircraft flight hours or 200 APU operating hours, 
whichever occurs later, after accomplishing the inspection required 
by paragraph (h)(1) of this AD, do the inspection as required by 
paragraph (g)(2) of this AD. Doing the installation required by 
paragraph (h)(5) of this AD terminates the requirements of this 
paragraph.
    (3) For Model A330 airplanes operated within the provisions of 
MMEL Item 24-22-01, ``AC Main Generation,'' that are dispatched with 
the APU operating during the entire flight in accordance with the 
provisions of MMEL Item 24-22-01: Perform the inspection required by 
paragraph (g)(2) of this AD at the applicable time in paragraph 
(h)(3)(i) or (h)(3)(ii) of this AD, unless the APU generator is 
removed or deactivated (quill shaft removed as described in the MMEL 
item). Doing the installation required by paragraph (h)(5) of this 
AD terminates the requirements of this paragraph.
    (i) Before the first flight of the MMEL rectification interval.
    (ii) Before the first flight following MMEL rectification.
    (4) Removing or deactivating the APU generator, or rendering the 
APU inoperative, in accordance with paragraph 4.3 of the applicable 
service information specified in Table 3 of this AD, defers the 
inspection required by paragraph (g)(2) of this AD. The deferred 
inspection must be performed before further flight after the system 
is reactivated. Doing the installation required by paragraph (h)(5) 
of this AD terminates the requirements of this paragraph.
    (5) Within 6 months after the effective date of this AD, install 
a secondary housing line replaceable unit (LRU) over the end of the 
APU generator, in accordance with the Accomplishment Instructions of 
the applicable service information specified in Table 6 of this AD. 
Performing this modification terminates the repetitive inspections 
required by paragraphs (g)(2) and (g)(3) of this AD, and the 
inspections required by paragraphs (h)(2), (h)(3), and (h)(4) of 
this AD.
    (6) Actions accomplished before the effective date of this AD in 
accordance with service information in Table 5 of this AD are 
acceptable for compliance with the corresponding actions specified 
in this AD.

     Table 5--Service Information Acceptable for Previous Compliance
------------------------------------------------------------------------
        Airbus service bulletin--                     Dated--
------------------------------------------------------------------------
A330-20-3045............................  June 13, 2008.
A340-24-4058............................  June 13, 2008.
A340-24-5022............................  June 23, 2008.
------------------------------------------------------------------------

FAA AD Differences

    Note 3: 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, FAA, has the authority to approve AMOCs for 
this AD, if requested using the procedures found in 14 CFR 39.19. 
Send information to ATTN: Vladimir Ulyanov, Aerospace Engineer, 
International Branch, ANM-116, Transport Airplane Directorate, FAA, 
1601 Lind Avenue SW., Renton, Washington 98057-3356; telephone (425) 
227-1138; 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.
    (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.
    (3) Reporting Requirements: For any reporting requirement in 
this AD, under the provisions of the Paperwork Reduction Act (44 
U.S.C. 3501 et seq.), the Office of Management and Budget (OMB) has 
approved the information collection requirements and has assigned 
OMB Control Number 2120-0056.

Related Information

    (j) Refer to MCAI EASA Airworthiness Directive 2008-0173, dated 
September 15, 2008, and the service information identified in Table 
6 of this AD for related information.

            Table 6--Service Information Required by This AD
------------------------------------------------------------------------
            Airbus--              Revision--            Dated--
------------------------------------------------------------------------
AOT A330-24A3042...............           02  April 12, 2007.
AOT A330-24A3044...............           03  May 26, 2008.
AOT A340-24A4056...............           02  April 12, 2007.
AOT A340-24A4057...............           03  December 20, 2007.
AOT A340-24A5020...............           02  April 12, 2007.
AOT A340-24A5021...............           02  December 20, 2007.
Mandatory Service Bulletin A330-          01  October 1, 2008.
 24-3045.
Mandatory Service Bulletin A340-          01  October 1, 2008.
 24-4058.
Mandatory Service Bulletin A340-          01  November 27, 2008.
 24-5022.
------------------------------------------------------------------------

Material Incorporated by Reference

    (k) You must use the service information contained in Table 7 of 
this AD, as applicable, to do the actions required by this AD, 
unless the AD specifies otherwise.

[[Page 39795]]

             Table 7--All Material Incorporated by Reference
------------------------------------------------------------------------
            Airbus--              Revision--            Dated--
------------------------------------------------------------------------
AOT A330-24A3042...............           02  April 12, 2007.
AOT A330-24A3044...............           03  May 26, 2008.
AOT A340-24A4056...............           02  April 12, 2007.
AOT A340-24A4057...............           03  December 20, 2007.
AOT A340-24-A5020..............           02  April 12, 2007.
AOT A340-24A5021...............           02  December 20, 2007.
Mandatory Service Bulletin A330-          01  October 1, 2008.
 24-3045.
Mandatory Service Bulletin A340-          01  October 1, 2008.
 24-4058.
Mandatory Service Bulletin A340-          01  November 27, 2008.
 24-5022.
------------------------------------------------------------------------
(The AOT document number, revision level, and date are indicated on only
  page 1 of these documents.)

    (1) The Director of the Federal Register approved the 
incorporation by reference of the service information contained in 
Table 8 of this AD under 5 U.S.C. 552(a) and 1 CFR part 51.

             Table 8--New Material Incorporated by Reference
------------------------------------------------------------------------
            Airbus--              Revision--            Dated--
------------------------------------------------------------------------
AOT A330-24A3044...............           03  May 26, 2008.
AOT A340-24A4057...............           03  December 20, 2007.
AOT A340-24A5021...............           02  December 20, 2007.
Mandatory Service Bulletin A330-          01  October 1, 2008.
 24-3045.
Mandatory Service Bulletin A340-          01  October 1, 2008.
 24-4058.
Mandatory Service Bulletin A340-          01  November 27, 2008.
 24-5022.
------------------------------------------------------------------------

    (2) The Director of the Federal Register previously approved the 
incorporation by reference of the service information contained in 
Table 9 of this AD on June 26, 2007 (72 FR 31973, June 11, 2007).

         Table 9--Material Previously Incorporated by Reference
------------------------------------------------------------------------
                                     Revision
   Airbus all operators telex--      level--             Dated--
------------------------------------------------------------------------
A330-24A3042.....................           02  April 12, 2007.
A340-24A4056.....................           02  April 12, 2007.
A340-24A5020.....................           02  April 12, 2007.
------------------------------------------------------------------------

    (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, e-mail: 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 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, June 23, 2010.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2010-16181 Filed 7-12-10; 8:45 am]
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