[Federal Register Volume 76, Number 151 (Friday, August 5, 2011)]
[Rules and Regulations]
[Pages 47430-47435]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2011-19433]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2011-0388; Directorate Identifier 2010-NM-004-AD; 
Amendment 39-16761; AD 2011-16-03]
RIN 2120-AA64


Airworthiness Directives; Airbus Model A300 B4-600, A300 B4-600R, 
and A300 F4-600R Series Airplanes, and Model A300 C4-605R Variant F 
Airplanes (Collectively Called Model A300-600 Series Airplanes); Model 
A310 Series Airplanes; Model A318 Series Airplanes; Model A319 Series 
Airplanes; Model A320-211, -212, -214, -231, -232, and -233 Airplanes; 
Model A321 Series Airplanes; Model A330-200 and A330-300 Series 
Airplanes; and Model A340-200, A340-300, A340-500, and A340-600 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. For Model A310 and A300-600 series airplanes, the 
MCAI describes the unsafe condition as:

    Hamilton Sundstrand (HS), the manufacturer of the RAT [ram air 
turbine], reported the failure during a wind tunnel test of a 
balance weight fastening screw on the RAT turbine cover. After 
investigation, it has been discovered that a batch of screws, which 
are used to attach the balance washers of the HS RAT Turbine 
Assembly, has not been subject to the correct heat treatment and are 
consequently exposed to potential fracture.
    This condition, if not corrected, might lead to the ejection of 
screw heads and consequently to the detachment of the associated 
balance washers. The loss of balance washers could increase RAT 
vibrations, which might lead to a possible detachment of RAT parts 
and consequent loss of RAT functionality. The loss of the RAT, in 
combination with a total engine flame out, could result in loss of 
control of the aeroplane.
* * * * *
    For Model A318, A319, A320, and A321 series airplanes, the MCAI 
describes the unsafe condition as:

    Hamilton Sundstrand (HS) reported the failure of a balance 
weight fastening screw on the RAT turbine cover during a wind tunnel 
test. After investigation, it has been discovered that a batch of 
screws, used to attach the balance washers of the RAT Turbine 
assembly, has not received the correct heat treatment, making them 
more subject to a potential failure.
    This condition, if left uncorrected, could lead to the ejection 
of screw heads and detachment of the associated balance washers. The 
loss of balance washers would increase RAT vibrations, which could 
lead to a possible detachment of RAT parts and loss of RAT 
functionality. The loss of the RAT, in combination with a double 
engine failure, or a total loss of normal electrical power 
generation, could result in loss of control of the aeroplane.
* * * * *
    For Model A330 and A340 series airplanes, the MCAI describes the 
unsafe condition as:

    Hamilton Sundstrand (HS), the manufacturer of the RAT, reported 
the failure of a balance weight fastening screw on the RAT cover 
during a wind tunnel test. After investigation, it has been 
discovered that a batch of screws, which are used to attach the 
balance washers of the HS RAT turbine lower gear box assembly, has 
not been subject to the correct heat treatment and the screws are 
consequently exposed to potential fracture.
    This condition, if not corrected, might lead to the ejection of 
screw heads and consequently to the detachment of the associated 
balance washers. The loss of balance washers could increase RAT 
vibrations, which might lead to a possible detachment of RAT parts, 
and thus to damage to the aeroplane and risk of injury to persons on 
the ground.
* * * * *
    We are issuing this AD to require actions to correct the unsafe 
condition on these products.

DATES: This AD becomes effective September 9, 2011.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in this AD as of September 9, 
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,

[[Page 47431]]

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 May 4, 2011 (76 FR 
25259). That NPRM proposed to correct an unsafe condition for the 
specified products.
    The MCAI for Model A300-600 and A310 series airplanes states:

    Hamilton Sundstrand (HS), the manufacturer of the RAT [ram air 
turbine], reported the failure during a wind tunnel test of a 
balance weight fastening screw on the RAT turbine cover. After 
investigation, it has been discovered that a batch of screws, which 
are used to attach the balance washers of the HS RAT Turbine 
Assembly, has not been subject to the correct heat treatment and are 
consequently exposed to potential fracture.
    This condition, if not corrected, might lead to the ejection of 
screw heads and consequently to the detachment of the associated 
balance washers. The loss of balance washers could increase RAT 
vibrations, which might lead to a possible detachment of RAT parts 
and consequent loss of RAT functionality. The loss of the RAT, in 
combination with a total engine flame out, could result in loss of 
control of the aeroplane.
    For the reasons described above, this AD requires the 
identification of the affected RAT turbine assemblies and 
replacement of all balance weight screws or, in case balance washer 
detachment is found, replacement of the RAT turbine assembly.

    The MCAI for Model A318, A319, A320, and A321 series airplanes 
states:

    Hamilton Sundstrand (HS) reported the failure of a balance 
weight fastening screw on the RAT turbine cover during a wind tunnel 
test. After investigation, it has been discovered that a batch of 
screws, used to attach the balance washers of the RAT Turbine 
assembly, has not received the correct heat treatment, making them 
more subject to a potential failure.
    This condition, if left uncorrected, could lead to the ejection 
of screw heads and detachment of the associated balance washers. The 
loss of balance washers would increase RAT vibrations, which could 
lead to a possible detachment of RAT parts and loss of RAT 
functionality. The loss of the RAT, in combination with a double 
engine failure, or a total loss of normal electrical power 
generation, could result in loss of control of the aeroplane.
    For the reasons described above, EASA AD 2009-0259 was issued in 
December 2009 to require the replacement of all balance weight 
screws on the affected RAT turbine assemblies, or replacement of the 
RAT, if any balancing washer was found missing.
    This AD retains some of the requirements of AD 2009-0259, which 
is superseded, and corrects its applicability by adding Airbus model 
A320-215 and A320-216 aeroplanes which were inadvertently omitted. 
Also, this AD requires the replacement of the set of balancing 
weights screws before the next operational or functional check of 
the RAT assembly.

    The MCAI for Model A330 and A340 series airplanes states:

    Hamilton Sundstrand (HS), the manufacturer of the RAT, reported 
the failure of a balance weight fastening screw on the RAT cover 
during a wind tunnel test. After investigation, it has been 
discovered that a batch of screws, which are used to attach the 
balance washers of the HS RAT turbine lower gear box assembly, has 
not been subject to the correct heat treatment and the screws are 
consequently exposed to potential fracture.
    This condition, if not corrected, might lead to the ejection of 
screw heads and consequently to the detachment of the associated 
balance washers. The loss of balance washers could increase RAT 
vibrations, which might lead to a possible detachment of RAT parts, 
and thus to damage to the aeroplane and risk of injury to persons on 
the ground.
    For the reasons described above, this AD requires the 
identification of the affected RAT turbine lower gear box assemblies 
and replacement of all balance screws or, in case balance washer 
detachment is found, replacement of the RAT turbine lower gear box 
assembly. * * *

    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

    Based on the service information, we estimate that this AD will 
affect about 1,004 products of U.S. registry. We also estimate that it 
will take about 2 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 $100 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 the AD on U.S. operators to be $271,080, or $270 
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,

[[Page 47432]]

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:

2011-16-03 Airbus: Amendment 39-16761. Docket No. FAA-2011-0388; 
Directorate Identifier 2010-NM-004-AD.

Effective Date

    (a) This airworthiness directive (AD) becomes effective 
September 9, 2011.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to the Airbus airplanes listed in paragraphs 
(c)(1), (c)(2), (c)(3), (c)(4), and (c)(5) of this AD, certificated 
in any category.
    (1) 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; and 
Model A310-203, -204, -221, -222, -304, -322, -324, and -325 
airplanes; all certified models, all manufacturer serial numbers, if 
equipped with a Hamilton Sundstrand ram air turbine (RAT) turbine 
assembly, as identified by part number (P/N) in Hamilton Sundstrand 
Service Bulletin 730816-29-15, dated August 4, 2009 (for Model A310 
airplanes), and Hamilton Sundstrand Service Bulletin 732365-29-7, 
dated August 4, 2009 (for Model A300-600 series airplanes); or 
equipped with a Hamilton Sundstrand RAT turbine lower gear box 
assembly on which the part number cannot be determined.
    (2) Airbus Model A318-111, -112, -121, and -122 airplanes; Model 
A319-111, -112, -113, -114, -115, -131, -132, and -133 airplanes; 
Model A320-211, -212, -214, -231, -232, and -233 airplanes; and 
Model A321-111, -112, -131, -211, -212, -213, -231, and -232 
airplanes; all manufacturer serial numbers, if equipped with a 
Hamilton Sundstrand RAT turbine assembly Model ERPS08M, as 
identified by part number in Hamilton Sundstrand Service Bulletin 
ERPS08M-29-8, dated June 17, 2009; or equipped with a Hamilton 
Sundstrand RAT turbine lower gear box assembly on which the part 
number cannot be determined.
    (3) Airbus Model A330-201, -202, -203, -223, -243, -301, -302, -
303, -321, -322, -323, -341, -342, and -343 airplanes; all 
manufacturer serial numbers, if equipped with a Hamilton Sundstrand 
RAT turbine lower gearbox assembly, as identified by part number in 
Hamilton Sundstrand Service Bulletin ERPS06G-29-6, dated July 20, 
2009; or equipped with a Hamilton Sundstrand RAT turbine lower gear 
box assembly on which the part number cannot be determined.
    (4) Model A340-211, -212, -213, -311, -312, and -313 airplanes; 
all manufacturer serial numbers, if equipped with a Hamilton 
Sundstrand RAT turbine lower gearbox assembly, as identified by part 
number in Hamilton Sundstrand Service Bulletin ERPS06G-29-6, dated 
July 20, 2009; or equipped with a Hamilton Sundstrand RAT turbine 
lower gear box assembly on which the part number cannot be 
determined.
    (5) Model A340-541 and -642 airplanes, all manufacturer serial 
numbers, if equipped with a Hamilton Sundstrand RAT turbine lower 
gearbox assembly, as identified by part number in Hamilton 
Sundstrand Service Bulletin ERPS33G-29-1, dated July 20, 2009; or 
equipped with a Hamilton Sundstrand RAT turbine lower gear box 
assembly on which the part number cannot be determined.

Subject

    (d) Air Transport Association (ATA) of America Code 29: 
Hydraulic power.

Reason

    (e) For Model A310 and A300-600 series airplanes, the MCAI 
describes the unsafe condition as:

    Hamilton Sundstrand (HS), the manufacturer of the RAT, reported 
the failure during a wind tunnel test of a balance weight fastening 
screw on the RAT turbine cover. After investigation, it has been 
discovered that a batch of screws, which are used to attach the 
balance washers of the HS RAT Turbine Assembly, has not been subject 
to the correct heat treatment and are consequently exposed to 
potential fracture.
    This condition, if not corrected, might lead to the ejection of 
screw heads and consequently to the detachment of the associated 
balance washers. The loss of balance washers could increase RAT 
vibrations, which might lead to a possible detachment of RAT parts 
and consequent loss of RAT functionality. The loss of the RAT, in 
combination with a total engine flame out, could result in loss of 
control of the aeroplane.
* * * * *
    For Model A318, A319, A320, and A321 series airplanes, the MCAI 
describes the unsafe condition as:

    Hamilton Sundstrand (HS) reported the failure of a balance 
weight fastening screw on the RAT turbine cover during a wind tunnel 
test. After investigation, it has been discovered that a batch of 
screws, used to attach the balance washers of the RAT Turbine 
assembly, has not received the correct heat treatment, making them 
more subject to a potential failure.
    This condition, if left uncorrected, could lead to the ejection 
of screw heads and detachment of the associated balance washers. The 
loss of balance washers would increase RAT vibrations, which could 
lead to a possible detachment of RAT parts and loss of RAT 
functionality. The loss of the RAT, in combination with a double 
engine failure, or a total loss of normal electrical power 
generation, could result in loss of control of the aeroplane.
* * * * *
    For Model A330 and A340 series airplanes, the MCAI describes the 
unsafe condition as:

    Hamilton Sundstrand (HS), the manufacturer of the RAT, reported 
the failure of a balance weight fastening screw on the RAT cover 
during a wind tunnel test. After investigation, it has been 
discovered that a batch of screws, which are used to attach the 
balance washers of the HS RAT turbine lower gear box assembly, has 
not been subject to the correct heat treatment and the screws are 
consequently exposed to potential fracture.
    This condition, if not corrected, might lead to the ejection of 
screw heads and consequently to the detachment of the associated 
balance washers. The loss of balance washers could increase RAT 
vibrations, which might lead to a possible detachment of RAT parts, 
and thus to damage to the aeroplane and risk of injury to persons on 
the ground.
* * * * *

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) At the applicable time specified in paragraph (g)(1), 
(g)(2), or (g)(3) of this AD: Inspect to determine the part number 
and serial number of the RAT turbine lower gear box assembly, in 
accordance with the applicable Airbus all operator telex (AOT) 
identified in table 1 of this AD. If the RAT turbine lower gear box 
assembly has a part number and a serial number that are not listed 
in the applicable Hamilton Sundstrand service bulletin identified in 
table 2 of this AD, no further action is required by this AD, except 
as required by paragraph (k) of this AD. A review of airplane 
maintenance

[[Page 47433]]

records is acceptable in lieu of this inspection if the part and 
serial numbers of the RAT turbine lower gear box assembly can be 
conclusively determined from that review.

                                              Table 1--Airbus AOTs
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                  Model                              Document                              Date
----------------------------------------------------------------------------------------------------------------
Model A300-600 series airplanes..........  Airbus AOT A300-29A6062.....  September 1, 2009.
Model A310 series airplanes..............  Airbus AOT A310-29A2098.....  September 1, 2009.
Model A318 series airplanes; Model A319    Airbus AOT A320-29A1150.....  June 24, 2009.
 series airplanes; Model A320-211, -212, -
 214, -231, -232, and -233 airplanes;
 Model A321 series airplanes.
Model A330-200 and A330-300 series         Airbus AOT A330-29A3110.....  September 1, 2009.
 airplanes.
Model A340-200 and A340n-300 series        Airbus AOT A340-29A4085.....  September 1, 2009.
 airplanes.
Model A340-500 and A340-600 series         Airbus AOT A340-500/600-      September 1, 2009.
 airplanes.                                 29A5015.
----------------------------------------------------------------------------------------------------------------

    (1) For airplanes identified in paragraph (c)(1) of this AD: 
Before the next RAT spin test, or within 1,500 flight hours or 9 
months after the effective date of this AD, whichever occurs first.
    (2) For airplanes identified in paragraph (c)(2) of this AD: 
Before the next RAT spin test, or within 3,000 flight hours or 12 
months after the effective date of this AD, whichever occurs first.
    (3) For airplanes identified in paragraph (c)(3), (c)(4), and 
(c)(5) of this AD: Before the next RAT spin test, or within 3,000 
flight hours or 8 months after the effective date of this AD, 
whichever occurs first.
    (h) If, during the inspection required by paragraph (g) of this 
AD, the RAT turbine lower gear box assembly has a part number and a 
serial number identified in the applicable Hamilton Sundstrand 
service bulletin specified in table 2 of this AD; or if the part 
number or serial number of the RAT turbine lower gear box assembly 
cannot be determined: Before further flight, inspect the RAT turbine 
lower gear box assembly to determine if the nameplate is identified 
with the applicable symbol specified in table 3 of this AD, in 
accordance with the applicable Airbus AOT specified in table 1 of 
this AD. If the RAT turbine lower gear box assembly nameplate has 
the applicable symbol that is identified in table 3 of this AD, no 
further action is required by this AD except as required by 
paragraph (k) of this AD. A review of airplane maintenance records 
is acceptable in lieu of this inspection if the symbol identified on 
the nameplate can be conclusively determined from that review.

                            Table 2--Applicable Hamilton Sundstrand Service Bulletins
----------------------------------------------------------------------------------------------------------------
                  Model                              Document                              Date
----------------------------------------------------------------------------------------------------------------
Model A300-600 series airplanes..........  Hamilton Sundstrand Service   August 4, 2009.
                                            Bulletin 732365-29-7.
Model A310 series airplanes..............  Hamilton Sundstrand Service   August 4, 2009.
                                            Bulletin 730816-29-15.
Model A318 series airplanes; Model A319    Hamilton Sundstrand Service   June 17, 2009.
 series airplanes; Model A320-211, -212, -  Bulletin ERPS08M-29-8.
 214, -231, -232, and -233 airplanes;
 Model A321 series airplanes.
Model A330-200 and A330-300 series         Hamilton Sundstrand Service   July 20, 2009.
 airplanes and Model A340-200 and A340-     Bulletin ERPS06G-29-6.
 300 series airplanes.
Model A340-500 and A340-600 series         Hamilton Sundstrand Service   July 20, 2009.
 airplanes.                                 Bulletin ERPS33G-29-1.
----------------------------------------------------------------------------------------------------------------


                    Table 3--Nameplate Identification
------------------------------------------------------------------------
                         Model                               Symbol
------------------------------------------------------------------------
Model A300-600 series airplanes.......................              29-7
Model A310 series airplanes...........................             29-15
Model A318 series airplanes; Model A319 series                      29-8
 airplanes; Model A320-211, -212, -214, -231, -232,
 and -233 airplanes; Model A321 series airplanes......
Model A330-200 and A330-300 series airplanes..........              29-6
Model A340-200 and A340-300 series airplanes..........              29-6
Model A340-500 and A340-600 series airplanes..........              29-1
------------------------------------------------------------------------

    (i) If, during the inspection required by paragraph (h) of this 
AD, the RAT turbine lower gear box assembly does not have the 
applicable symbol specified in table 3 of this AD: Before further 
flight, do a general visual inspection for the missing and fractured 
balance screws and for missing washers in accordance with the 
applicable Airbus AOT specified in table 1 of this AD.
    (1) If all balance screws are fitted on the turbine and are not 
fractured or missing, at the applicable time specified in paragraph 
(i)(1)(i), (i)(1)(ii), or (i)(1)(iii) of this AD: Replace the RAT 
turbine lower gear box assembly with a new or serviceable RAT 
turbine lower gear box assembly, or replace all balance screws on 
the RAT turbine lower gear box assembly with new or serviceable 
balance screws, in accordance with the applicable Airbus AOT 
specified in table 1 of this AD.
    (i) For airplanes identified in paragraph (c)(1) of this AD: 
Within 1,500 flight hours or 9 months after the effective date of 
this AD, whichever occurs first.
    (ii) For airplanes identified in paragraph (c)(2) of this AD: 
Within 3,000 flight hours or 12 months after the effective date of 
this AD, whichever occurs first.
    (iii) For airplanes identified in paragraphs (c)(3), (c)(4), and 
(c)(5) of this AD: Within 3,000 flight hours or 8 months after the 
effective date of this AD, whichever occurs first.
    (2) If one or more screws are fractured but the associated 
balance washers are still fitted on the RAT turbine lower gear box 
assembly, before further flight, do the actions specified in 
paragraph (i)(2)(i) or (i)(2)(ii) of this AD, in accordance with the 
applicable Airbus AOT specified in table 1 of this AD.
    (i) Replace the RAT turbine lower gear box assembly with a new 
or serviceable RAT turbine lower gear box assembly.
    (ii) Replace all balance screws on the RAT turbine lower gear 
box assembly with new or serviceable balance screws, including 
replacing any missing washers.

[[Page 47434]]

    (3) If one or more screws are fractured and any balance washer 
is missing, before further flight, replace the RAT turbine lower 
gear box assembly with new or serviceable RAT turbine lower gear box 
assembly, in accordance with the applicable Airbus AOT specified in 
table 1 of this AD.

Reporting Requirement

    (j) At the applicable time specified in paragraph (j)(1) or 
(j)(2) of this AD, submit a report of the findings (both positive 
and negative) of the inspection required by paragraph (i) of this AD 
to Airbus, as specified in Paragraph 7 of the applicable AOT 
specified in table 1 of this AD. The report must include the 
inspection results, a description of any discrepancies found, the 
airplane serial number, and the number of landings and flight hours 
on the airplane.
    (1) If the inspection was done on or after the effective date of 
this AD: Submit the report within 30 days after the inspection.
    (2) If the inspection was done before the effective date of this 
AD: Submit the report within 30 days after the effective date of 
this AD.

Parts Installation

    (k) As of the effective date of this AD, no person may install, 
on any airplane, a RAT turbine lower gear box assembly, as 
identified by part number in the applicable Hamilton Sundstrand 
service bulletin specified in table 2 of this AD, unless it has been 
inspected and all applicable corrective actions have been done, in 
accordance with the 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

    (l) 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, 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.
    (3) Reporting Requirements: A Federal agency may not conduct or 
sponsor, and a person is not required to respond to, nor shall a 
person be subject to a penalty for failure to comply with a 
collection of information subject to the requirements of the 
Paperwork Reduction Act unless that collection of information 
displays a current valid OMB Control Number. The OMB Control Number 
for this information collection is 2120-0056. Public reporting for 
this collection of information is estimated to be approximately 5 
minutes per response, including the time for reviewing instructions, 
completing and reviewing the collection of information. All 
responses to this collection of information are mandatory. Comments 
concerning the accuracy of this burden and suggestions for reducing 
the burden should be directed to the FAA at: 800 Independence Ave., 
SW., Washington, DC 20591, Attn: Information Collection Clearance 
Officer, AES-200.

Related Information

    (m) Refer to the applicable MCAI European Aviation Safety Agency 
(EASA) AD specified in table 4 of this AD, the Airbus AOTs specified 
in table 1 of this AD, and the Hamilton Sundstrand service bulletins 
specified in table 2 of this AD, for related information.

                            Table 4--EASA ADs
------------------------------------------------------------------------
          For model--               EASA AD--             Dated--
------------------------------------------------------------------------
A300-600 and A310 series               2009-0258  December 10, 2009.
 airplanes.
A318, A319, A320, and A321             2010-0120  June 21, 2010.
 series airplanes.
A330 and A340 series airplanes         2009-0260  December 10, 2009
                                                   (corrected December
                                                   14, 2009).
------------------------------------------------------------------------

Material Incorporated by Reference

    (n) You must use the service information contained in table 5 of 
this AD, as applicable, to do the actions required by this AD, 
unless the AD specifies otherwise.

               Table 5--Material Incorporated by Reference
------------------------------------------------------------------------
              Document                               Date
------------------------------------------------------------------------
Airbus All Operator Telex A300-       September 1, 2009.
 29A6062.
Airbus All Operator Telex A310-       September 1, 2009.
 29A2098.
Airbus All Operator Telex A320-       June 24, 2009.
 29A1150.
Airbus All Operator Telex A330-       September 1, 2009.
 29A3110.
Airbus All Operator Telex A340-       September 1, 2009.
 29A4085.
Airbus All Operator Telex A340-500/   September 1, 2009.
 600-29A5015.
Hamilton Sundstrand Service Bulletin  August 4, 2009.
 732365-29-7.
Hamilton Sundstrand Service Bulletin  August 4, 2009.
 730816-29-15.
Hamilton Sundstrand Service Bulletin  June 17, 2009.
 ERPS08M-29-8.
Hamilton Sundstrand Service Bulletin  July 20, 2009.
 ERPS06G-29-6.
Hamilton Sundstrand Service Bulletin  July 20, 2009.
 ERPS33G-29-1.
------------------------------------------------------------------------

    (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 Airbus service information identified in this AD, 
contact the appropriate office listed below.
    (i) For Model A300-600 and A310 series airplanes: 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.
    (ii) For Model A318, A319, A320, and A321 series airplanes: 
Airbus, Airworthiness

[[Page 47435]]

Office--EAS, 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.
    (iii) For Model A330 and A340 series airplanes: 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 [email protected]; Internet http://www.airbus.com.
    (3) For Hamilton Sundstrand service information identified in 
this AD, contact Hamilton Sundstrand, Technical Publications, Mail 
Stop 302-9, 4747 Harrison Avenue, P.O. Box 7002, Rockford, Illinois 
61125-7002; telephone 860-654-3575; fax 860-998-4564; e-mail 
[email protected]; Internet http://www.hamiltonsundstrand.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, on July 20, 2011.
Kalene C. Yanamura,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2011-19433 Filed 8-4-11; 8:45 am]
BILLING CODE 4910-13-P