
[Federal Register Volume 80, Number 246 (Wednesday, December 23, 2015)]
[Proposed Rules]
[Pages 79738-79742]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2015-30822]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2014-0006; Directorate Identifier 2013-NM-147-AD]
RIN 2120-AA64


Airworthiness Directives; Airbus Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Supplemental notice of proposed rulemaking (NPRM); reopening of 
comment period.

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SUMMARY: We are revising an earlier proposed airworthiness directive 
(AD) for all Airbus Model A330-200, A330-200 Freighter, A330-300, A340-
200, and A340-300 series airplanes. The NPRM proposed to require 
inspecting certain trimmable horizontal stabilizer actuators (THSAs) to 
determine the number of total flight cycles the THSA has accumulated, 
and replacing the THSA if necessary. The NPRM was prompted by the 
results of endurance qualification tests on the THSA, which revealed a 
partial loss of the no-back brake (NBB) efficiency in specific load 
conditions. This action revises the NPRM by adding airplanes to the 
proposed applicability, reducing the proposed compliance times for 
replacing affected THSAs, and revising the definition of a serviceable 
THSA. We are proposing this supplemental NPRM (SNPRM) to detect and 
correct premature wear of the carbon friction disks on the NBB of the 
THSA, which could lead to reduced braking efficiency in certain load 
conditions, and, in conjunction with the inability of the power gear 
train to keep the ball screw in its last commanded position, could 
result in uncommanded movements of the trimmable horizontal stabilizer 
and loss of control of the airplane. Since these actions impose an 
additional burden over those proposed in the NPRM, we are reopening the 
comment period to allow the public the chance to comment on these 
proposed changes.

DATES: We must receive comments on this SNPRM by February 8, 2016.

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 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 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.

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-2014-
0006; or in person at the Docket Management Facility 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 
Office (telephone: 800-647-5527) is in the ADDRESSES section. Comments 
will be available in the AD docket shortly after receipt.

[[Page 79739]]


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-2014-0006; 
Directorate Identifier 2013-NM-147-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

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 by adding an AD that would apply to all Airbus Model A330-200, 
A330-200 Freighter, A330-300, A340-200, and A340-300 series airplanes. 
The NPRM published in the Federal Register on February 3, 2014 (79 FR 
6104). The NPRM was prompted by the results of endurance qualification 
tests on the THSA, which revealed a partial loss of the NBB efficiency 
in specific load conditions. The NPRM proposed to require inspecting 
certain THSAs to determine the number of total flight cycles the THSA 
had accumulated, and replacing the THSA if necessary.

Actions Since Previous NPRM (79 FR 6104, February 3, 2014) was Issued

    Since we issued the NPRM (79 FR 6104, February 3, 2014), we have 
determined that additional airplanes are affected by the unsafe 
condition, the proposed compliance times for replacing affected THSAs 
should be reduced, and the definition of a serviceable THSA should be 
revised. The European Aviation Safety Agency (EASA), which is the 
Technical Agent for the Member States of the European Union, has issued 
EASA Airworthiness Directive 2014-0257R1, dated May 29, 2015 (referred 
to after this as the Mandatory Continuing Airworthiness Information, or 
``the MCAI''), to correct an unsafe condition on all Airbus Model A330-
200, A330-200 Freighter, A330-300, A340-200, and A340-300 series 
airplanes; and Model A340-500 and A340-600 series airplanes. The MCAI 
states:

    During endurance qualification tests on Trimmable Horizontal 
Stabilizer Actuator (THSA) of another Airbus aeroplane type, a 
partial loss of the no-back brake (NBB) efficiency was experienced. 
Due to THSA design similarity on the A330/A340 fleet, a similar 
partial loss of the NBB efficiency was identified on THSA Part 
Number (P/N) 47147 as installed on A330-300 and A340-200/-300 
aeroplanes, on THSA P/N 47172 as installed on A330-200/-300 and 
A340-200/-300 aeroplanes, and on THSA P/N 47175 as installed on 
A340-500/600 aeroplanes.
    Investigation results concluded that this partial loss of 
braking efficiency in some specific aerodynamic load conditions was 
due to polishing and auto-contamination of the NBB carbon friction 
disks.
    This condition, if not detected and corrected and in conjunction 
with the power gear train not able to keep the ball screw in its 
last commanded position, could lead to uncommanded movements of the 
THS, possibly resulting in loss of control of the aeroplane.
    To address this potential unsafe condition, EASA issued AD 2013-
0144 [http://ad.easa.europa.eu/blob/easa_ad_2013_0144.zip/AD_2013-0144R1_2] to require replacement of each THSA that has exceeded 
16,000 flight cycles (FC) in service, to be sent in shop for NBB 
carbon disk replacement.
    Since that AD was issued, a need for clarification has been 
demonstrated, regarding the identification of the THSA `affected' by 
this requirement.
    For this reason, EASA AD 2013-0144 [http://ad.easa.europa.eu/blob/easa_ad_2013_0144.zip/AD_2013-0144R1_2] was revised, confirming 
that this AD only affected those THSA identified by Part Number (P/
N) in Airbus Alert Operator Transmission (AOT) A27L005-13. In 
addition, a note was added to make clear that the life limits as 
specified in the current revision of ALS Part 4 are still relevant 
for the affected THSA, as applicable to aeroplane model and THSA P/
N.
    Since EASA AD 2013-0144R1 [http://ad.easa.europa.eu/ad/2013-0144R1] was issued, further assessment of the ageing/endurance issue 
has resulted in the conclusion that there is a need to replace the 
NBB installed on the THSA.
    Consequently, EASA issued AD 2014-0257 [http://ad.easa.europa.eu/blob/EASA_AD_2014_0257_R1.pdf/AD_2014-0257R1_1] 
which retained the requirements of EASA AD 2013-0144R1, which was 
superseded, and required removal from service of affected THSA. THSA 
should be sent in shop for NBB carbon disk replacement. This [EASA] 
AD affected additional THSA P/Ns when compared to EASA AD 2013-
0144R1 and Airbus AOT A27L005-13.
    Since that [EASA] AD was issued, it was determined that it is 
necessary to consider that the THSA removal for NBB disks 
replacement could also be calculated since last NBB disk replacement 
which was done in-shop.

    This proposed AD also adds Model A340-541 and A340-642 airplanes to 
the applicability. You may examine the MCAI in the AD docket on the 
Internet at http://www.regulations.gov/#!documentDetail;D=FAA-2014-
0006-0002.

Related Service Information Under 1 CFR part 51

    Airbus has issued the following service information, dated July 15, 
2014.
     Service Bulletin A330-27-3199 (for Model A330 series 
airplanes);
     Service Bulletin A340-27-4190 (for Model A340-200 and -300 
series airplanes); and
     Service Bulletin A340-27-5062 (for Model A340-500 and -600 
series airplanes).
    The service information describes procedures for inspecting the 
THSA to determine the part number and replacing THSAs having certain 
part numbers with a new or serviceable part. 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 of this NPRM.

Comments

    We gave the public the opportunity to participate in developing 
this AD. We have considered the comments received. The following 
presents the comments received on the NPRM (79 FR 6104, February 3, 
2014) and the FAA's response to each comment.
    One commenter, Chris Vargas, supported the intent of the NPRM (79 
FR 6104, February 3, 2014). Another commenter, Cameron Lane, restated 
the proposed costs and unsafe condition. We infer that this commenter 
supported the intent of the NPRM.

Request To Revise THSA Life Limits

    US Airways stated that there is a conflict between the THSA life 
limits included in the NPRM (79 FR 6104, February 3, 2014) and the life 
limits included in the A330 Airworthiness Limitations. The commenter 
conveyed that it is concerned that operators would be unsure which life 
limits to follow. We infer that the commenter is requesting that the 
THSA life limits specified in the NPRM match those specified in the 
A330 Airworthiness Limitations.
    The THSA life limits specified in this SNPRM are more restrictive 
than the life limits specified in the A330 Airworthiness Limitations 
for the parts identified in paragraphs (g)(1) and (g)(2) of this 
proposed AD. This SNPRM proposes to require a one-time

[[Page 79740]]

replacement of an affected THSA with a serviceable part. Serviceable 
parts identified in paragraphs (g)(1) and (g)(2) of this proposed AD 
must not exceed the limits proposed in this SNPRM. Any serviceable part 
not identified in paragraph (g)(1) or (g)(2) of this proposed AD is 
subject to the life limits and maintenance tasks in the A330 
Airworthiness Limitations. We have been notified by Airbus that the NBB 
life limits will be reduced in a revised Airworthiness Limitation. We 
might consider further rulemaking if new airworthiness limitations are 
issued. No change was made to this proposed AD regarding this issue.

Request To Assign Life Limit to Only the NBB Disks

    US Airways requested that a life limit be assigned only to the NBB 
disks (part number FE194-031) and not the entire THSA. The commenter 
stated that the NBB disks are replaceable in the shop and the AD should 
not limit the life of the entire THSA.
    We partially agree with the commenter's request. EASA has revised 
MCAI 2014-0257, dated November 27, 2014, to include life limit 
computations for an affected THSA from the most recent NBB inspection, 
in addition to the accumulated total flight cycles since the THSA's 
first installation on an airplane. The revised MCAI is 2014-0257R1, 
dated May 29, 2015. We have revised paragraphs (g), (h)(1), (h)(2), and 
(h)(3) of this proposed AD accordingly.

Request To Reduce the Compliance Time

    Jennifer Paramski stated that the proposed compliance time in the 
NPRM (79 FR 6104, February 3, 2014) should be reduced because failure 
of the THSA is a substantial safety concern. The commenter stated that 
once the THSA has accumulated 16,000 total flight cycles, the airline 
has 30 months or 4,000 flight cycles to replace the part, and a lot can 
happen during that time because the part is sensitive to load 
conditions. The commenter interpreted the compliance time to replace 
the THSA as tiered and suggested that some airlines might try to extend 
the timeframe for THSA replacement because after 4,000 flight cycles 
from the initial 16,000 flights reached, an airline could argue that it 
should get an additional 1,500 flight cycles or 12 months to replace 
the part because of the second tier. The commenter explained that 
airlines would try to maximize the current part on all airplanes to try 
to maximize profit. The commenter emphasized that maximizing profits 
could jeopardize the safety of others, which, if there was an accident, 
would cause more monetary losses in the long run from lawsuits.
    We do not agree that the compliance time should be reduced. The 
thresholds for THSA replacement are not tiered, as stated by the 
commenter. The replacement threshold is based on the accumulation of 
total flight cycles as of the effective date of the final rule. An 
airline cannot exceed the thresholds mandated in a final rule unless it 
requests an alternative method of compliance, issued by the FAA, using 
the procedures specified in paragraph (n)(1) of this proposed AD. 
However, we have clarified the compliance times in this SNPRM by 
revising paragraph (h) of this proposed AD and including a new 
paragraph (i). The subsequent paragraphs were redesignated accordingly.

FAA's Determination and Requirements of This SNPRM

    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 these 
same type designs.
    Certain changes described above expand the scope of the proposed AD 
(79 FR 6104, February 3, 2014). As a result, we have determined that it 
is necessary to reopen the comment period to provide additional 
opportunity for the public to comment on this SNPRM.

Explanation of Compliance Times

    The MCAI requires operators to replace certain THSAs by certain 
dates. The replacements are done for THSAs exceeding a certain flight 
cycle limit corresponding to each date. EASA determined that 
accomplishing the replacements by these dates is necessary in order to 
address the identified unsafe condition. Therefore, we are also 
specifying compliance dates in this proposed AD.

Explanation of ``RC'' Procedures and Tests in Service Information

    The FAA worked in conjunction with industry, under the 
Airworthiness Directive Implementation Aviation Rulemaking Committee 
(ARC), to enhance the AD system. One enhancement was a new process for 
annotating which procedures and tests in the service information are 
required for compliance with an AD. Differentiating these procedures 
and tests from other tasks in the service information is expected to 
improve an owner's/operator's understanding of crucial AD requirements 
and help provide consistent judgment in AD compliance. The procedures 
and tests identified as RC (required for compliance) in any service 
information have a direct effect on detecting, preventing, resolving, 
or eliminating an identified unsafe condition.
    As specified in a NOTE under the Accomplishment Instructions of the 
specified service information, procedures and tests that are identified 
as RC in any service information must be done to comply with the 
proposed AD. However, procedures and tests that are not identified as 
RC are recommended. Those procedures and tests that are not identified 
as RC may be deviated from using accepted methods in accordance with 
the operator's maintenance or inspection program without obtaining 
approval of an alternative method of compliance (AMOC), provided the 
procedures and tests identified as RC can be done and the airplane can 
be put back in a serviceable condition. Any substitutions or changes to 
procedures or tests identified as RC will require approval of an AMOC.

Costs of Compliance

    We estimate that this proposed AD affects 94 airplanes of U.S. 
registry.
    We also estimate that it would take about 3 work-hours per product 
to comply with the new basic requirements of this proposed AD. The 
average labor rate is $85 per work-hour. Required parts would cost 
about $0 per product. Based on these figures, we estimate the cost of 
this proposed AD on U.S. operators to be $23,970, or $255 per product.
    In addition, we estimate that any necessary follow-on actions would 
take about 23 work-hours and would require parts costing up to 
$722,556, for a cost of up to $724,511 per product. We have no way of 
determining the number of aircraft that might need this action.

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,

[[Page 79741]]

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.

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 airworthiness 
directive (AD):

Airbus: Docket No. FAA-2014-0006; Directorate Identifier 2013-NM-
147-AD.

(a) Comments Due Date

    We must receive comments by February 8, 2016.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to the Airbus airplanes identified in paragraphs 
(c)(1) through (c)(7) of this AD, certificated in any category, all 
manufacturer serial numbers.
    (1) Model A330-201, -202, -203, -223, and -243 airplanes.
    (2) Model A330-223F and -243F airplanes.
    (3) Model A330-301, -302, -303, -321, -322, -323, -341, -342, 
and -343 airplanes.
    (4) Model A340-211, -212, and -213 airplanes.
    (5) Model A340-311, -312, and -313 airplanes.
    (6) Model A340-541 airplanes.
    (7) Model A340-642 airplanes.

(d) Subject

    Air Transport Association (ATA) of America Code 27, Flight 
Controls.

(e) Reason

    This AD was prompted by the results of endurance qualification 
tests on the trimmable horizontal stabilizer actuator (THSA), which 
revealed a partial loss of the no-back brake (NBB) efficiency in 
specific load conditions. We are issuing this AD to detect and 
correct premature wear of the carbon friction disks on the NBB of 
the THSA, which could lead to reduced braking efficiency in certain 
load conditions, and, in conjunction with the inability of the power 
gear train unable to keep the ball screw in its last commanded 
position, could result in uncommanded movements of the trimmable 
horizontal stabilizer and loss of control of the airplane.

(f) Compliance

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

(g) Inspection To Determine THSA Part Number and Accumulated Total 
Flight Cycles

    Within 90 days after the effective date of this AD: Inspect the 
THSA to determine if it has a part number that is specified in 
paragraph (g)(1) or (g)(2) of this AD, and to determine the total 
number of flight cycles accumulated since the THSA's first 
installation on an airplane, or since the most recent NBB 
replacement. A review of airplane delivery or maintenance records is 
acceptable in lieu of this inspection if the part number of the THSA 
can be conclusively determined from that review.
    (1) For Model A330-200 Freighter, A330-200, A330-300, A340-200 
and A340-300 series airplanes: Part number (P/N) 47147-500, 47147-
700, 47172-300, 47172-500, 47172-510, or 47172-520.
    (2) For Model A340-500 and -600 series airplanes: P/N 47175-200, 
47175-300, 47175-500, or 47175-520.

(h) THSA Replacement for Airbus Model A330-200 Freighter, A330-200, 
A330-300, A340-200, and A340-300 Series Airplanes

    For Airbus Model A330-200 Freighter, A330-200, A330-300, A340-
200, and A340-300 series airplanes having a THSA with a part number 
specified in paragraph (g)(1) of this AD: At the applicable time 
specified in paragraph (h)(1), (h)(2), or (h)(3) of this AD, replace 
each affected THSA with a serviceable THSA, in accordance with the 
Accomplishment Instructions of Airbus Service Bulletin A330-27-3199, 
dated July 15, 2014; or Airbus Service Bulletin A340-27-4190, dated 
July 15, 2014; as applicable.

    Note 1 to paragraphs (h), (i), and (j) of this AD:  The THSA 
life limits specified in Part 4--Aging System Maintenance of the 
Airbus A330 and A340 Airworthiness Limitations Sections are still 
relevant, as applicable to airplane model and THSA part number.

    (1) For a THSA that has accumulated or exceeded 20,000 total 
flight cycles since the THSA's first installation on an airplane, or 
since the most recent NBB replacement, whichever is later, as of the 
effective date of this AD: Within 6 months after the effective date 
of this AD.
    (2) For a THSA that has accumulated or exceeded 16,000 total 
flight cycles, but less than 20,000 total flight cycles since the 
THSA's first installation on an airplane, or since the most recent 
NBB replacement, whichever is later, as of the effective date of 
this AD: At the applicable time specified in paragraphs (h)(2)(i) 
and (h)(2)(ii) of this AD.
    (i) For Model A330-200 Freighter, A330-200, and A330-300 series 
airplanes: Within 12 months after the effective date of this AD but 
without exceeding 20,000 total flight cycles.
    (ii) For Model A340-200, and A340-300 series airplanes: Within 
12 months after the effective date of this AD but without exceeding 
20,000 total flight cycles.
    (3) For a THSA that has accumulated less than 16,000 total 
flight cycles since first installation on an airplane, or since the 
most recent NBB replacement, whichever is later, as of the effective 
date of this AD: At the applicable time specified in paragraph (i) 
of this AD.

(i) Replacement Times for Airbus Model A330-200 Freighter, A330-200, 
A330-300, A340-200, and A340-300 Series Airplanes With THSAs Having 
Less Than 16,000 Total Flight Cycles as of the Effective Date of This 
AD

    The requirements of this paragraph apply to Airbus Model A330-
200 Freighter, A330-200, A330-300, A340-200, and A340-300 series 
airplanes having a THSA with a part number specified in paragraph 
(g)(1) of this AD that has accumulated less than 16,000 total flight 
cycles since first installation on an airplane, or since the most 
recent NBB replacement, whichever is later, as of the effective date 
of this AD. Not later than the date specified in paragraphs (i)(1), 
(i)(2), and (i)(3) of this AD, as applicable: For any THSA having 
reached or exceeded on that date the corresponding number of total 
flight cycles as specified in paragraphs (i)(1), (i)(2), and (i)(3) 
of this AD, as applicable, replace the THSA with a serviceable unit 
in accordance with the Accomplishment Instructions of Airbus Service 
Bulletin A330-27-3199, dated July 15, 2014; or Airbus Service 
Bulletin A340-27-4190, dated July 15, 2014; as applicable.
    (1) As of 12 months after the effective date of this AD: The 
THSA flight-cycle limit

[[Page 79742]]

(since first installation on an airplane, or since last NBB 
replacement, whichever occurs later) is 16,000 total flight cycles.
    (2) As of July 31, 2017: The THSA flight-cycle limit (since 
first installation on an airplane, or since last NBB replacement, 
whichever occurs later) is 14,000 total flight cycles.
    (3) As of July 31, 2018: The THSA flight-cycle limit (since 
first installation on an airplane, or since last NBB replacement, 
whichever occurs later) is 12,000 total flight cycles.

(j) THSA Replacement for Airbus Model A340-500 and -600 Series 
Airplanes

    For Airbus Model A340-500 and A340-600 series airplanes having a 
THSA with a part number specified in paragraph (g)(2) of this AD: 
Not later than the date specified in paragraphs (j)(1), (j)(2), 
(j)(3), and (j)(4) of this AD, as applicable: For any THSA having 
reached or exceeded on that date the corresponding number of total 
flight cycles as specified in paragraphs (j)(1), (j)(2), (j)(3), and 
(j)(4) of this AD, as applicable, replace each affected THSA with a 
serviceable THSA, in accordance with the Accomplishment Instructions 
of Airbus Service Bulletin A340-27-5062, dated July 15, 2014.
    (1) As of the effective date of this AD: The THSA flight-cycle 
limit (since first installation on an airplane, or since last NBB 
replacement, whichever occurs later) is 6,000 total flight cycles.
    (2) As of April 30, 2017: The THSA flight-cycle limit (since 
first installation on an airplane, or since last NBB replacement, 
whichever occurs later) is 5,200 total flight cycles.
    (3) As of April 30, 2018: The THSA flight-cycle limit (since 
first installation on an airplane, or since last NBB replacement, 
whichever occurs later) is 4,400 total flight cycles.
    (4) As of April 30, 2019: The THSA flight-cycle limit (since 
first installation on an airplane, or since last NBB replacement, 
whichever occurs later) is 3,500 total flight cycles.

(k) THSA Replacement Intervals for All Airbus Airplanes Identified in 
Paragraph (c) of This AD

    For any part installed as required by this AD having a part 
number identified in paragraph (g)(1) or (g)(2) of this AD: From the 
dates specified in paragraphs (i) and (j) of this AD, as applicable, 
and prior to exceeding the accumulated number of total flight cycles 
corresponding to each time, replace each affected THSA with a 
serviceable part, in accordance with the Accomplishment Instructions 
of the applicable service information identified in paragraphs 
(k)(1), (k)(2), and (k)(3) of this AD.
    (1) Airbus Service Bulletin A330-27-3199, dated July 15, 2014.
    (2) Airbus Service Bulletin A340-27-4190, dated July 15, 2014.
    (3) Airbus Service Bulletin A340-27-5062, dated July 15, 2014.

(l) Definition of Serviceable THSA

    For the purposes of this AD a serviceable THSA is a THSA:
    (1) Having a part number identified in paragraph (g)(1) or 
(g)(2) of this AD that has not exceeded any of the total accumulated 
flight cycles identified in paragraphs (i)(1) through (i)(3) of this 
AD, or paragraphs (j)(1) through (j)(4) of this AD, as applicable; 
or
    (2) Having a part number that is not identified in paragraph 
(g)(1) or (g)(2) of this AD.

(m) Parts Installation Limitation

    From each date specified in paragraphs (i)(1), (i)(2), and 
(i)(3) of this AD, and paragraphs (j)(1) through (j)(4) of this AD, 
as applicable, a THSA having a part number identified in paragraph 
(g)(1) or (g)(2) of this AD may be installed on any airplane, 
provided the THSA has not exceeded the corresponding number of 
accumulated total flight cycles.

(n) 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) 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.
    (3) Required for Compliance (RC): If any service information 
contains procedures or tests that are identified as RC, those 
procedures and tests must be done to comply with this AD; any 
procedures or tests that are not identified as RC are recommended. 
Those procedures and tests that are not identified as RC may be 
deviated from using accepted methods in accordance with the 
operator's maintenance or inspection program without obtaining 
approval of an AMOC, provided the procedures and tests identified as 
RC can be done and the airplane can be put back in an airworthy 
condition. Any substitutions or changes to procedures or tests 
identified as RC require approval of an AMOC.

(o) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) EASA Airworthiness Directive 2014-0257R1, dated May 29, 2015, 
for related information. This MCAI may be found in the AD docket on 
the Internet at http://www.regulations.gov/#!documentDetail;D=FAA-
2014-0006-0002.
    (2) 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. 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.

    Issued in Renton, Washington, on October 30, 2015.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2015-30822 Filed 12-22-15; 8:45 am]
 BILLING CODE 4910-13-P


