[Federal Register Volume 78, Number 220 (Thursday, November 14, 2013)]
[Rules and Regulations]
[Pages 68352-68355]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2013-26564]


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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; 
Amendment 39-17509; AD 2013-14-04]
RIN 2120-AA64


Airworthiness Directives; Airbus 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 all 
Airbus Model A330-223F, -223, -321, -322, and -323 airplanes. This AD 
was prompted by fatigue load analysis that determined that the 
inspection interval for certain pylon bolts must be reduced. This AD 
requires a torque check of forward engine mount bolts, and replacement 
if necessary. 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.

DATES: This AD becomes effective December 19, 2013.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of December 19, 
2013.

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 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 [email protected]; Internet http://www.airbus.com.

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:

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 by adding an AD that would apply to the specified products. The 
NPRM was published in the Federal Register on March 28, 2013 (78 FR 
18925). The NPRM proposed to correct an unsafe condition for the 
specified products.
    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 Mandatory Continuing Airworthiness Information, or 
``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)

[[Page 68353]]

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 examine 
the MCAI in the AD docket on the Internet at http://www.regulations.gov/#!documentDetail;D=FAA-2013-0212-0002.

Comments

    We gave the public the opportunity to participate in developing 
this AD. We received no comments on the NPRM (78 FR 18925, March 28, 
2013) or on the determination of the cost to the public.

Additional Changes Made to This AD

    We have combined tables 1, 2, and 3 to paragraph (g) of the NPRM 
(78 FR 18925, March 28, 2013) into one table, designated as table 1 to 
paragraph (g) in this final rule, and updated table references in this 
AD accordingly. These changes do not affect the requirements or intent 
of paragraph (g) of this AD.

Conclusion

    We reviewed the relevant data and determined that air safety and 
the public interest require adopting this AD with the changes described 
previously--except for minor editorial changes. We have determined that 
these minor changes:
     Are consistent with the intent that was proposed in the 
NPRM (78 FR 18925, March 28, 2013) for correcting the unsafe condition; 
and
     Do not add any additional burden upon the public than was 
already proposed in the NPRM (78 FR 18925, March 28, 2013).

Costs of Compliance

    We estimate that this AD will affect 41 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. Based on these figures, we estimate the cost of 
this AD to the 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 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 that 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);
    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 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/#!docketDetail;D=FAA-2013-0212; 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 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.

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:

2013-14-04 Airbus: Amendment 39-17509. Docket No. FAA-2013-0212; 
Directorate Identifier 2012-NM-116-AD.

(a) Effective Date

    This airworthiness directive (AD) becomes effective December 19, 
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.

[[Page 68354]]

(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 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 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 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
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                                          Flight cycles
                                        accumulated on the
                                      effective date of this
                                       AD since last torque
                                        check performed as
          Airplane models              specified in Pratt &         Compliance time        Torque check interval
                                      Whitney Alert Service                                   (not to exceed)
                                      Bulletin PW4G-100-A71-
                                      32, or since airplane
                                         first flight, as
                                            applicable
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For Model A330-223,-321, -322, and - 0-1,850................  Within 2,350 flight cycles   2,350 flight cycles
 323 airplanes with AFT more than                              since the last torque        or 24,320 flight
 132 minutes.                                                  check as specified in        hours, whichever
                                                               Pratt & Whitney Alert        occurs first.
                                                               Service Bulletin PW4G-100-
                                                               A71-32, or since airplane
                                                               first flight, as
                                                               applicable.
For Model A330-223, -321, -322, and  1,851-2,700............  Within 500 flight cycles     2,350 flight cycles
 -323 airplanes with AFT more than                             after the effective date     or 24,320 flight
 132 minutes.                                                  of this AD without           hours, whichever
                                                               exceeding 2,700 flight       occurs first.
                                                               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.
For Model A330-321,-322, and -323    0-1,450................  Within 1,950 flight cycles   1,950 flight cycles
 airplanes with AFT equal or less                              since the last torque        or 20,210 flight
 than 132 minutes; and for Model                               check performed as           hours, whichever
 A330-321, -322, and -323 airplanes                            specified in Pratt &         occurs first.
 on which the AFT is not calculated                            Whitney Alert Service
 on a regular basis.                                           Bulletin PW4G-100-A71-32,
                                                               or since airplane first
                                                               flight, as applicable.
For Model A330-321, -322, and -323   1,451-2,700............  Within 500 flight cycles     1,950 flight cycles
 airplanes with AFT equal or less                              after the effective date     or 20,210 flight
 than 132 minutes; and for Model                               of this AD without           hours, whichever
 A330-321,-322, and -323 airplanes                             exceeding 2,700 flight       occurs first.
 on which the AFT is not calculated                            cycles since last torque
 on a regular basis.                                           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.
For Model A330-223F airplanes......  Not applicable.........  Within 2,140 flight cycles   2,140 flight cycles
                                                               or 6,600 flight hours,       or 6,600 flight
                                                               whichever occurs first       hours, whichever
                                                               since the last torque        occurs first.
                                                               check performed 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 
part number 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-

[[Page 68355]]

[email protected]. Before using any approved AMOC, notify your 
appropriate principal inspector, or lacking a principal inspector, 
the manager of the local flight standards district office/
certificate holding district office. The AMOC approval letter must 
specifically reference this AD.
    (2) Airworthy Product: For any requirement in this AD to obtain 
corrective actions from a manufacturer or other source, use these 
actions if they are FAA-approved. Corrective actions are considered 
FAA-approved if they are approved by the State of Design Authority 
(or their delegated agent). You are required to assure the product 
is airworthy before it is returned to service.

(l) Related Information

    (1) Refer to MCAI European Aviation Safety Agency Airworthiness 
Directive 2012-0094, dated May 31, 2012, for related information. 
You may examine the MCAI in the AD docket on the Internet at http://www.regulations.gov/#!documentDetail;D=FAA-2013-0212-0002.
    (2) Service information identified in this AD that is not 
incorporated by reference may be viewed at the addresses specified 
in paragraphs (m)(3) and (m)(4) of this AD.

(m) Material Incorporated by Reference

    (1) The Director of the Federal Register approved the 
incorporation by reference (IBR) of the service information listed 
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
    (2) You must use this service information as applicable to do 
the actions required by this AD, unless this AD specifies otherwise.
    (i) Airbus Mandatory Service Bulletin A330-71-3028, Revision 01, 
dated February 20, 2012.
    (ii) Reserved.
    (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; email [email protected]; 
Internet http://www.airbus.com.
    (4) You may view copies of the 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.
    (5) You may view this 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/cfr/ibr-locations.html.

    Issued in Renton, Washington, on June 21, 2013.
Jeffrey E. Duven,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2013-26564 Filed 11-13-13; 8:45 am]
BILLING CODE 4910-13-P