
[Federal Register Volume 82, Number 61 (Friday, March 31, 2017)]
[Rules and Regulations]
[Pages 15985-15988]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2017-06098]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2017-0245; Directorate Identifier 2017-NM-023-AD; 
Amendment 39-18841; AD 2017-07-05]
RIN 2120-AA64


Airworthiness Directives; Airbus Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule; request for comments.

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SUMMARY: We are adopting a new airworthiness directive (AD) for all 
Airbus Model A330-243, -243F, -341, -342, and -343 airplanes. This AD 
requires an inspection to determine if affected hydraulic pressure tube 
assemblies are installed, and replacement with serviceable hydraulic 
pressure tube assemblies if necessary. This AD also requires repetitive 
replacements of serviceable hydraulic pressure tube assemblies. This AD 
was prompted by a determination that cracks can develop on the ripple 
damper of the hydraulic pressure tube assembly and reports of failure 
of the ripple damper of the hydraulic pressure tube assembly. We are 
issuing this AD to address the unsafe condition on these products.

DATES: This AD becomes effective April 17, 2017.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of April 17, 
2017.
    We must receive comments on this AD by May 15, 2017.

ADDRESSES: You may send comments, using the procedures found in 14 CFR 
11.43 and 11.45, 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 service information identified in this final rule, 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 view this 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. It is also available on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2017-
0245.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2017-
0245; 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. 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: 

Discussion

    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Union, has issued EASA 
Airworthiness Directive 2017-0041, dated February 24, 2017; corrected 
February 28, 2017 (referred to after this as the Mandatory Continuing 
Airworthiness Information, or ``the MCAI''), to correct an unsafe 
condition for all Airbus Model A330-243, -243F, -341, -342, and -343 
airplanes. The MCAI states:

    Following introduction in-service of Airbus modification (mod) 
205242, a new hydraulic pressure tube assembly Part Number (P/N) 
AE711121-18 was installed, one on each engine, with an integral 
ripple damper. It was determined that, at a relatively low number of 
cycles, cracks can develop on the ripple damper weld of this new 
hydraulic pressure tube, which could lead to hydraulic leakage and 
consequent loss of the green hydraulic system. Recently, there has 
been a high rate of failure of the affected dampers that, if 
continued, may exceed the overall safety objective of the certified 
design.
    This condition, if not corrected, could, in combination with 
other system failures, result in reduced control of the aeroplane.
    Prompted by these findings, Airbus issued Alert Operators 
Transmission (AOT) A71L012-16 Revision 01, to provide instructions 
to replace the hydraulic pressure tube assembly P/N AE711121-18 with 
an improved assembly, P/N AE711121-18 Rev A, equipped with a double-
welded ripple damper.
    For the reasons described above, this [EASA] AD requires 
[inspection for and] replacement of each affected hydraulic pressure 
tube assembly with a [serviceable] tube assembly having the double 
welded ripple damper installed. This [EASA] AD also requires 
implementation of a life limit

[[Page 15986]]

on the new part [i.e., repetitive replacements of serviceable 
hydraulic pressure tube assemblies]. This [EASA] AD is considered as 
interim measure and further AD action may follow.
    This [EASA] AD is republished to correct the TCDS number and add 
a previous manufacturer name.

    You may examine the MCAI on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2017-
0245.

Related Service Information Under 1 CFR Part 51

    Airbus has issued Alert Operators Transmission (AOT) A71L012-16, 
Revision 01, dated February 24, 2017. The service information describes 
procedures for replacing hydraulic pressure tube assembly, part number 
(P/N) AE711121-18, and hydraulic pressure tube assembly, P/N AE711121-
18 Rev A. This service information is reasonably available because the 
interested parties have access to it through their normal course of 
business or by the means identified in the ADDRESSES section.

FAA's Determination and Requirements of This 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 issuing this AD because we 
evaluated all pertinent information and determined the unsafe condition 
exists and is likely to exist or develop on other products of these 
same type design.

Difference Between This AD and the MCAI

    The MCAI mandates replacement of the hydraulic pressure tube 
assembly, using Airbus AOT A71L012-16, Revision 01, dated February 24, 
2017. However, Airbus AOT A71L012-16, Revision 01, dated February 24, 
2017, also specifies to first inspect or do a records review to 
determine the part number of the hydraulic pressure tube assembly. 
Therefore, paragraph (i) of this AD requires the inspection or records 
review.
    The MCAI includes a compliance time of ``within 5 months'' for the 
replacement of the affected part. We have determined that a compliance 
time of ``within 4 months'' is necessary to adequately address the 
identified unsafe condition. We have included the 4-month compliance 
time in paragraphs (j), (l), and (m) of this AD.
    We have coordinated these differences with EASA.

FAA's Determination of the Effective Date

    An unsafe condition exists that requires the immediate adoption of 
this AD. The FAA has found that the risk to the flying public justifies 
waiving notice and comment prior to adoption of this rule because 
cracks can develop on the ripple damper of the hydraulic pressure tube 
assembly, which could lead to hydraulic leakage and consequent loss of 
the green hydraulic system and because of reports of failure of the 
ripple damper of the hydraulic pressure tube assembly. This condition 
could, in combination with other system failures, result in reduced 
control of the airplane. Therefore, we determined that notice and 
opportunity for public comment before issuing this AD are impracticable 
and that good cause exists for making this amendment effective in fewer 
than 30 days.

Comments Invited

    This AD is a final rule that involves requirements affecting flight 
safety, and we did not precede it by notice and opportunity for public 
comment. We invite you to send any written relevant data, views, or 
arguments about this AD. Send your comments to an address listed under 
the ADDRESSES section. Include ``Docket No. FAA-2017-0245; Directorate 
Identifier 2017-NM-023-AD'' at the beginning of your comments. We 
specifically invite comments on the overall regulatory, economic, 
environmental, and energy aspects of this AD. We will consider all 
comments received by the closing date and may amend this 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 AD.

Costs of Compliance

    We estimate that this AD affects 53 airplanes of U.S. registry.
    We also estimate that it will take about 5 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 $20,000 per 
product. Based on these figures, we estimate the cost of this AD on 
U.S. operators to be $1,082,525, or $20,425 per product.
    According to the manufacturer, some of the costs of this AD may be 
covered under warranty, thereby reducing the cost impact on affected 
individuals. We do not control warranty coverage for affected 
individuals. As a result, we have included all costs in our cost 
estimate.

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.

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:

[[Page 15987]]

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 airworthiness 
directive (AD):

2017-07-05 Airbus: Amendment 39-18841; Docket No. FAA-2017-0245; 
Directorate Identifier 2017-NM-023-AD.

(a) Effective Date

    This AD becomes effective April 17, 2017.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to Airbus Model A330-243, -243F, -341, -342, and 
-343 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 a determination that cracks can develop 
on the ripple damper of the hydraulic pressure tube assembly, which 
could lead to hydraulic leakage and consequent loss of the green 
hydraulic system. This AD was also prompted by reports of failure of 
the ripple damper of the hydraulic pressure tube assembly. We are 
issuing this AD to prevent cracking and failure of the ripple damper 
of the hydraulic pressure tube assembly, which could, in combination 
with other system failures, result in reduced control of the 
airplane.

(f) Compliance

    Comply with this AD within the compliance times specified, 
unless already done.

(g) Definition of Affected Part

    For the purpose of this AD, a hydraulic pressure tube assembly, 
part number (P/N) AE711121-18, as introduced by Airbus mod 205242, 
is hereafter referred to as an ``affected part'' in this AD.

(h) Definition of Serviceable Part

    For the purpose of this AD, a ``serviceable part'' is a 
hydraulic pressure tube assembly (which has a double-welded ripple 
damper installed), P/N AE711121-18 Rev A, that has accumulated fewer 
than 800 total flight cycles since first installation on an 
airplane. The hydraulic pressure tube assembly, P/N AE711121-18 Rev 
A, is introduced by Airbus mod 206979 on the production line.

(i) Identification of Affected Parts

    Within 15 days after the effective date of this AD, inspect to 
determine the part number of the hydraulic pressure tube assembly 
that is installed on each engine. A review of airplane maintenance 
records is acceptable in lieu of this inspection if the part number 
of the hydraulic pressure tube assembly can be conclusively 
determined from that review.

(j) Replacement of Affected Parts

    Within the compliance time specified in table 1 to paragraph (j) 
of this AD, as applicable, or within 4 months after the effective 
date of this AD, whichever occurs first, replace each affected part 
(see paragraph (g) of this AD) with a serviceable part (see 
paragraph (h) of this AD), in accordance with the instructions of 
Airbus Alert Operators Transmission (AOT) A71L012-16, Revision 01, 
dated February 24, 2017.

    Table 1 to Paragraph (j) of This AD--Replacement Compliance Times
------------------------------------------------------------------------
     Flight cycles accumulated *                Compliance time
------------------------------------------------------------------------
Fewer than 775 total flight cycles...  Before exceeding 800 total flight
                                        cycles on the affected hydraulic
                                        pressure tube assembly since
                                        first installation on an
                                        airplane.
775 total flight cycles or more......  Within 25 flight cycles after the
                                        effective date of this AD.
An unknown number of flight cycles     Within 25 flight cycles after the
 accumulated.                           effective date of this AD.
------------------------------------------------------------------------
* Unless specified otherwise, the flight cycles in the ``flight cycles
  accumulated'' column of table 1 to paragraph (j) of this AD are those
  accumulated by an affected hydraulic pressure tube assembly, on the
  effective date of this AD, since first installation on an airplane.

(k) Repetitive Replacement of Serviceable Parts--Life Limit

    Before a serviceable part (see paragraph (h) of this AD) exceeds 
800 total flight cycles since first installation on an airplane, 
replace it with a serviceable part, in accordance with the 
instructions of Airbus AOT A71L012-16, Revision 01, dated February 
24, 2017.

(l) Engine Installation Limitation

    As of the effective date of this AD, except as required by 
paragraph (m) of this AD, it is allowed to install on any airplane a 
replacement engine having an affected part (see paragraph (g) of 
this AD) installed, provided that, before that affected part exceeds 
800 total flight cycles since first installation on an airplane, or 
within 4 months after the effective date of this AD, whichever 
occurs first, the part is replaced with a serviceable part (see 
paragraph (h) of this AD), in accordance with the instructions of 
Airbus AOT A71L012-16, Revision 01, dated February 24, 2017.

(m) Parts and Engine Installation Prohibition

    As of 4 months after the effective date of this AD: Do not 
install on any airplane an affected part (see paragraph (g) of this 
AD), or an engine having an affected part installed.

(n) Credit for Previous Actions

    This paragraph provides credit for actions required by paragraph 
(j) of this AD, if those actions were performed before the effective 
date of this AD using Airbus AOT A71L012-16, dated December 22, 
2016.

(o) 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.
    (2) Contacting the Manufacturer: For any requirement in this AD 
to obtain corrective actions from a manufacturer, the action must be 
accomplished using a method approved by the Manager, International 
Branch, ANM-116, Transport Airplane Directorate, FAA; or the 
European Aviation Safety Agency (EASA); or Airbus's EASA Design 
Organization Approval (DOA). If approved by the DOA, the approval 
must include the DOA-authorized signature.

(p) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) EASA Airworthiness Directive 2017-0041, dated February 24, 
2017; corrected February 28, 2017, for related information. This 
MCAI may be found in the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-
2017-0245.
    (2) For more information about this AD, 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. Information 
may be emailed to: 9-ANM-116-AMOC-REQUESTS@faa.gov.

[[Page 15988]]

    (3) Service information identified in this AD that is not 
incorporated by reference is available at the addresses specified in 
paragraphs (q)(3) and (q)(4) of this AD.

(q) 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 Alert Operators Transmission (AOT) A71L012-16, 
Revision 01, dated February 24, 2017.
    (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 airworthiness.A330-A340@airbus.com; 
Internet http://www.airbus.com.
    (4) You may view this 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 March 17, 2017.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2017-06098 Filed 3-30-17; 8:45 am]
BILLING CODE 4910-13-P


