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[Federal Register Volume 78, Number 60 (Thursday, March 28, 2013)]
[Proposed Rules]
[Pages 18925-18928]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2013-07203]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2013-0212; Directorate Identifier 2012-NM-116-AD]
RIN 2120-AA64

Airworthiness Directives; Airbus Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: We propose to adopt a new airworthiness directive (AD) for all 
Airbus Model A330-223F, -223, -321, -322, and -323 airplanes. This 
proposed AD was prompted by fatigue load analysis that determined that 
the inspection interval for certain pylon bolts must be reduced. This 
proposed AD would require a torque check of forward engine mount bolts, 
and replacement if necessary. We are proposing this AD to detect and 
correct loose or broken bolts, which could lead to engine detachment 
in-flight, and damage to the airplane.

DATES: We must receive comments on this proposed AD by May 13, 2013.

ADDRESSES: You may send comments by any of the following methods:
     Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.
     Fax: (202) 493-2251.
     Mail: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE., Washington, DC 20590.
     Hand Delivery: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE., Washington, DC, between 9 a.m. and 5 p.m., Monday 
through Friday, except Federal holidays.
    For Airbus service information identified in this proposed 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; email airworthiness.A330-A340@airbus.com; Internet 
http://www.airbus.com. You may review copies of the referenced service 
information at the FAA, Transport Airplane Directorate, 1601 Lind 
Avenue SW., Renton, WA. For information on the availability of this 
material at the FAA, call 425-227-1221.

[[Page 18926]]

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 this proposed AD, 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.

FOR FURTHER INFORMATION CONTACT: Vladimir Ulyanov, Aerospace Engineer, 
International Branch, ANM-116, Transport Airplane Directorate, FAA 1601 
Lind Avenue SW., Renton, WA 98057-3356; telephone (425) 227-1138; fax 
(425) 227-1149.

SUPPLEMENTARY INFORMATION: 

Comments Invited

    We invite you to send any written relevant data, views, or 
arguments about this proposed AD. Send your comments to an address 
listed under the ADDRESSES section. Include ``Docket No. FAA-2013-0212; 
Directorate Identifier 2012-NM-116-AD'' at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of this proposed AD. We 
will consider all comments received by the closing date and may amend 
this proposed AD based on those comments.
    We will post all comments we receive, without change, to http://www.regulations.gov, including any personal information you provide. We 
will also post a report summarizing each substantive verbal contact we 
receive about this proposed AD.

Discussion

    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Community, has issued EASA 
Airworthiness Directive 2012-0094, dated May 31, 2012 (referred to 
after this as ``the MCAI''), to correct an unsafe condition for the 
specified products. The MCAI states:

    The forward mount engine pylon bolts, Part Number (P/N) 51U615, 
fitted on Airbus A330 aeroplanes with Pratt & Whitney (PW) PW4000 
engines, are made from MP159 material.
    The U.S. Federal Aviation Administration (FAA), as Engine 
Certification Authority, issued AD 2006-16-05 [Amendment 39-14705 
(71 FR 44185, August 4, 2006)] to require (paragraph (g) of that AD) 
repetitive torque checks of MP159 material forward mount pylon bolts 
fitted on certain PW4000 series engines.
    However, the engine mount system is considered to be part of 
aeroplane certification rather than the engine certification. 
Following further fatigue load analysis by Airbus of the A330 engine 
mount system, completed in February 2011 for both the freighter and 
passenger models of A330 aeroplanes, it was determined that MP159 
material forward mount pylon bolts inspection interval must be 
reduced.
    This condition, if not detected and corrected, could ultimately 
lead to engine detachment from the aeroplane, possibly resulting in 
damage to the aeroplane and/or injury to person on the ground.
    For the reasons described above, this [EASA] AD requires 
accomplishment of repetitive torque checks of the forward mount 
pylon bolts installed on A330 aeroplanes powered by PW4000 engines 
and, depending on findings, the replacement of all four bolts and 
associated nuts.

Findings (discrepancies) include loose or broken bolts. You may obtain 
further information by examining the MCAI in the AD docket.

Relevant Service Information

    Airbus has issued Mandatory Service Bulletin A330-71-3028, Revision 
01, dated February 20, 2012. The actions described in this service 
information are intended to correct the unsafe condition identified in 
the MCAI.

Compliance With AD 2006-16-05, Amendment 39-14705 (71 FR 44185, August 
4, 2006)

    Doing the actions required by paragraph (g) of this AD constitutes 
compliance with the requirements specified in paragraph (g) of AD 2006-
16-05, Amendment 39-14705 (71 FR 44185, August 4, 2006).

FAA's Determination and Requirements of This Proposed AD

    This product has been approved by the aviation authority of another 
country, and is approved for operation in the United States. Pursuant 
to our bilateral agreement with the State of Design Authority, we have 
been notified of the unsafe condition described in the MCAI and service 
information referenced above. We are proposing this AD because we 
evaluated all pertinent information and determined an unsafe condition 
exists and is likely to exist or develop on other products of the same 
type design.

Costs of Compliance

    Based on the service information, we estimate that this proposed AD 
would affect about 41 products of U.S. registry. We also estimate that 
it would take about 2 work-hours per product to comply with the basic 
requirements of this proposed AD. The average labor rate is $85 per 
work-hour. Based on these figures, we estimate the cost of the proposed 
AD on U.S. operators to be $6,970, or $170 per product.
    In addition, we estimate that any necessary follow-on actions would 
take about 1 work-hour and require parts costing $6,747, for a cost of 
$6,832 per product. We have no way of determining the number of 
products that may need these actions.

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 proposed AD would not have federalism 
implications under Executive Order 13132. This proposed AD would 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 proposed 
regulation:
    1. Is not a ``significant regulatory action'' under Executive Order 
12866;
    2. Is not a ``significant rule'' under the DOT Regulatory Policies 
and Procedures (44 FR 11034, February 26, 1979);
    3. Will not affect intrastate aviation in Alaska; and
    4. Will not have a significant economic impact, positive or 
negative, on a substantial number of small entities under the criteria 
of the Regulatory Flexibility Act.
    We prepared a regulatory evaluation of the estimated costs to 
comply with this proposed AD and placed it in the AD docket.

[[Page 18927]]

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

The Proposed Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA proposes to amend 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:

Airbus: Docket No. FAA-2013-0212; Directorate Identifier 2012-NM-
116-AD.

(a) Comments Due Date

    We must receive comments by May 13, 2013.

(b) Affected ADs

    This AD affects AD 2006-16-05, Amendment 39-14705 (71 FR 44185, 
August 4, 2006).

(c) Applicability

    This AD applies to Airbus Model A330-223F, -223, -321, -322, and 
-323 airplanes, certificated in any category, all manufacturer 
serial numbers.

(d) Subject

    Air Transport Association (ATA) of America Code 71, Powerplant.

(e) Reason

    This AD was prompted by fatigue load analysis that determined 
that certain pylon bolts inspection interval must be reduced. We are 
issuing this AD to detect and correct loose or broken bolts, which 
could lead to engine detachment in-flight, and damage to the 
airplane.

(f) Compliance

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

(g) Torque Check and Replacement

    (1) Within the compliance times specified in table 1, table 2, 
or table 3 to paragraph (g) of this AD, as applicable to airplane 
model and utilization, do a torque check to determine if there are 
any loose or broken forward engine mount bolts (4 positions/engine) 
on both engines, and repeat that torque check at intervals not to 
exceed the values defined in table 1, table 2, or table 3 to 
paragraph (g) of this AD, in accordance with the Accomplishment 
Instructions of Airbus Mandatory Service Bulletin A330-71-3028, 
Revision 01, dated February 20, 2012. For the purposes of table 1 
and table 2 to paragraph (g) of this AD, the average flight time 
(AFT) is defined as a computation of the number of flight hours 
divided by the number of flight cycles accumulated since last torque 
check or since the airplane's first flight, as applicable.

Table 1 to Paragraph (g) of This AD: For Model A330-223, -321, -322 and
              323 Airplanes With AFT More Than 132 Minutes
------------------------------------------------------------------------
Flight cycles accumulated on the
 effective date of this AD since
 last torque check performed as
  specified in Pratt & Whitney                           Torque check
Alert Service Bulletin PW4G-100-    Compliance time    interval (not to
 A71-32; or since airplane first                            exceed)
      flight, as applicable
 
------------------------------------------------------------------------
0-1,850.........................  Within 2,350        2,350 flight
                                   flight cycles       cycles or 24,320
                                   since the last      flight hours,
                                   torque check as     whichever occurs
                                   specified in        first.
                                   Pratt & Whitney
                                   Alert Service
                                   Bulletin PW4G-100-
                                   A71-32, or since
                                   airplane first
                                   flight, as
                                   applicable.
1,851-2,700.....................  Within 500 flight   2,350 flight
                                   cycles after the    cycles or 24,320
                                   effective date of   flight hours,
                                   this AD without     whichever occurs
                                   exceeding 2,700     first.
                                   flight cycles
                                   since last torque
                                   check as
                                   specified in
                                   Pratt & Whitney
                                   Alert Service
                                   Bulletin PW4G-100-
                                   A71-32, or since
                                   airplane first
                                   flight, as
                                   applicable; or
                                   within 3 months
                                   after the
                                   effective date of
                                   this AD;
                                   whichever occurs
                                   later.
------------------------------------------------------------------------

 Table 2 to Paragraph (g) of This AD: For Model A330-321, -322, and -323
 Airplanes With AFT Equal or Less Than 132 Minutes; and for Model A330-
  321, -322, and -323 Airplanes on Which the AFT Is Not Calculated on a
                              Regular Basis
------------------------------------------------------------------------
Flight cycles accumulated on the
 effective date of this AD since
 last torque check as  performed
 as specified in Pratt & Whitney                         Torque check
Alert Service Bulletin PW4G-100-    Compliance time    interval (not to
A71-32;  or since airplane first                            exceed)
      flight, as applicable
 
------------------------------------------------------------------------
0-1,450.........................  Within 1,950        1,950 flight
                                   flight cycles       cycles or 20,210
                                   since the last      flight hours,
                                   torque check        whichever occurs
                                   performed as        first.
                                   specified in
                                   Pratt & Whitney
                                   Alert Service
                                   Bulletin PW4G-100-
                                   A71-32, or since
                                   airplane first
                                   flight, as
                                   applicable.
1,451-2,700.....................  Within 500 flight   1,950 flight
                                   cycles after the    cycles or 20,210
                                   effective date of   flight hours,
                                   this AD without     whichever occurs
                                   exceeding 2,700     first.
                                   flight cycles
                                   since last torque
                                   check performed
                                   as specified in
                                   Pratt & Whitney
                                   Alert Service
                                   Bulletin PW4G-100-
                                   A71-32, or since
                                   airplane first
                                   flight, as
                                   applicable; or
                                   within 3 months
                                   after the
                                   effective date of
                                   this AD;
                                   whichever occurs
                                   later.
------------------------------------------------------------------------

[[Page 18928]]

   Table 3 to Paragraph (g) of This AD: For Model A330-223F Airplanes
------------------------------------------------------------------------
                                          Torque check interval (not to
            Compliance time                          exceed)
------------------------------------------------------------------------
Within 2,140 flight cycles or 6,600      2,140 flight cycles or 6,600
 flight hours, whichever occurs first     flight hours, whichever occurs
 since the last torque check performed    first.
 as specified in Pratt & Whitney Alert
 Service Bulletin PW4G-100-A71-32, or
 since airplane first flight, as
 applicable.
------------------------------------------------------------------------

     (2) If any loose or broken bolt is detected during the check 
required by paragraph (g)(1) of this AD, before further flight, 
replace all four forward engine mount bolts and associated nuts, on 
the engine where the loose or broken bolt was detected, with new 
bolts and nuts, in accordance with the Accomplishment Instructions 
of Airbus Mandatory Service Bulletin A330-71-3028, Revision 01, 
dated February 20, 2012.
    (3) Replacement of bolts and nuts as required by paragraph 
(g)(2) of this AD is not terminating action for the repetitive 
torque checks required by paragraph (g)(1) of this AD.

(h) Compliance with AD 2006-16-05, Amendment 39-14705 (71 FR 44185, 
August 4, 2006)

    Doing the actions required by paragraph (g) of this AD 
constitutes compliance with the requirements specified in paragraph 
(g) of AD 2006-16-05, Amendment 39-14705 (71 FR 44185, August 4, 
2006).

(i) Parts Installation Prohibition

    As of the effective date of this AD, no person may install any 
INCO718 material, forward mount pylon bolt having Pratt & Whitney P/
N 54T670 on any airplane.

(j) Credit for Previous Actions

    This paragraph provides credit for the actions required by 
paragraphs (g)(1) and (g)(2) of this AD, if those actions were 
performed before the effective date of this AD using Airbus 
Mandatory Service Bulletin A330-71-3028, dated December 16, 2011, 
which is not incorporated by reference in this AD.

(k) Other FAA AD Provisions

    The following provisions also apply to this AD:
    (1) Alternative Methods of Compliance (AMOCs): The Manager, 
International Branch, ANM-116, Transport Airplane Directorate, FAA, 
has the authority to approve AMOCs for this AD, if requested using 
the procedures found in 14 CFR 39.19. In accordance with 14 CFR 
39.19, send your request to your principal inspector or local Flight 
Standards District Office, as appropriate. If sending information 
directly to the International Branch, send it to ATTN: Vladimir 
Ulyanov, Aerospace Engineer, International Branch, ANM-116, 
Transport Airplane Directorate, FAA 1601 Lind Avenue SW., Renton, WA 
98057-3356; telephone (425) 227-1138; fax (425) 227-1149. 
Information may be emailed to: 9-ANM-116-AMOC-REQUESTS@faa.gov. 
Before using any approved AMOC, notify your appropriate principal 
inspector, or lacking a principal inspector, the manager of the 
local flight standards district office/certificate holding district 
office. The AMOC approval letter must specifically reference this 
AD.
    (2) Airworthy Product: For any requirement in this AD to obtain 
corrective actions from a manufacturer or other source, use these 
actions if they are FAA-approved. Corrective actions are considered 
FAA-approved if they are approved by the State of Design Authority 
(or their delegated agent). You are required to assure the product 
is airworthy before it is returned to service.

(l) Related Information

    (1) Refer to MCAI European Aviation Safety Agency Airworthiness 
Directive 2012-0094, dated May 31, 2012; and Airbus Mandatory 
Service Bulletin A330-71-3028, Revision 01, dated February 20, 2012.
    (2) For Airbus 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; email airworthiness.A330-A340@airbus.com; 
Internet http://www.airbus.com. You may review copies of the 
referenced service information at the FAA, Transport Airplane 
Directorate, 1601 Lind Avenue SW., Renton, WA. For information on 
the availability of this material at the FAA, call 425-227-1221.

    Issued in Renton, Washington, on March 20, 2013.
Jeffrey E. Duven,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2013-07203 Filed 3-27-13; 8:45 am]
BILLING CODE 4910-13-P
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