[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.
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(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