
[Federal Register Volume 81, Number 44 (Monday, March 7, 2016)]
[Proposed Rules]
[Pages 11690-11692]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2016-04562]



[[Page 11690]]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2016-3993; Directorate Identifier 2015-NM-065-AD]
RIN 2120-AA64


Airworthiness Directives; Airbus Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: We propose to adopt a new airworthiness directive (AD) for all 
Airbus Model A300 series airplanes; Model A300 B4-600, B4-600R, F4-600R 
series airplanes, and Model A300 C4-605R Variant F airplanes 
(collectively called Model A300-600 series airplanes); and Model A310 
series airplanes. This proposed AD was prompted by reports of partial 
loss of no-back brake (NBB) efficiency on the trimmable horizontal 
stabilizer actuator (THSA). This proposed AD would require an 
inspection to determine THSA part number, serial numbers, and flight 
cycles on certain THSAs; and repetitive replacement for certain THSAs. 
We are proposing this AD to prevent loss of THSA NBB efficiency, which 
in conjunction with the power gear not able to keep the ball screw in 
its last commanded position, could lead to an uncommanded movement of 
the horizontal stabilizer, possibly resulting in loss of control of the 
airplane.

DATES: We must receive comments on this proposed AD by April 21, 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 NPRM, contact Airbus 
SAS, Airworthiness Office--EAW, 1 Rond Point Maurice Bellonte, 31707 
Blagnac Cedex, France; telephone: +33 5 61 93 36 96; fax: +33 5 61 93 
44 51; email: account.airworth-eas@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-2016-
3993; 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 
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: Dan Rodina, Aerospace Engineer, 
International Branch, ANM-116, Transport Airplane Directorate, FAA, 
1601 Lind Avenue SW., Renton, WA 98057-3356; telephone: 425-227-2125; 
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-2016-3993; 
Directorate Identifier 2015-NM-065-AD'' at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of this proposed AD. We 
will consider all comments received by the closing date and may amend 
this proposed AD based on those comments.
    We will post all comments we receive, without change, to http://www.regulations.gov, including any personal information you provide. We 
will also post a report summarizing each substantive verbal contact we 
receive about this proposed AD.

Discussion

    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Union, has issued EASA AD 
2015-0081, dated May 7, 2015 (referred to after this as the Mandatory 
Continuing Airworthiness Information, or ``the MCAI''), to correct an 
unsafe condition. The MCAI states:

    During endurance qualification tests on a Trimmable Horizontal 
Stabilizer Actuator (THSA) concerning another aeroplane type, a 
partial loss of the noback brake (NBB) efficiency was experienced. 
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.
    Due to design similarity on the A300-600, A300-600ST and A310 
fleet, the same tests were initiated by the THSA manufacturer on 
certain type THSA, sampled from the field. Subject tests confirmed 
that THSA Part Number (P/N) 47142 series, as installed on the A300-
600, A300-600ST and A310 fleet, are also affected by this partial 
loss of NBB efficiency.
    This condition, if not detected and corrected, and in 
conjunction with the power gear not able to keep the ball screw in 
its last commanded position, could potentially lead to an 
uncommanded movement of the Horizontal Stabilizer, possibly 
resulting in loss of control of the aeroplane.
    For the reasons described above, this [EASA] AD requires the 
removal from service of each affected THSA, with the intent of in-
shop NBB carbon disk replacement.

    You may examine the MCAI in the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2016-
3993.

Related Service Information Under 1 CFR Part 51

    Airbus has issued Airbus Service Bulletin A300-27-6070, dated 
February 17, 2015; and Airbus Service Bulletin A310-27-2106, dated 
February 17, 2015. This service information describes procedures for 
inspection and replacement of the THSA.
    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 Proposed AD

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

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Explanation of Compliance Times

    In most ADs, we adopt a compliance time allowing a specified amount 
of time after the AD's effective date. In this case, however, EASA has 
already issued regulations that require operators to replace certain 
THSAs to address an identified unsafe condition by certain dates, but 
before exceeding certain flight cycle limits corresponding to each 
date. To provide for coordinated implementation of EASA's regulations 
and this proposed AD, we are using the same compliance dates in this 
proposed AD.
    This AD proposes the replacement of the NBB disks at an interval of 
14,600 flight cycles to take full benefit of the THSA published life 
limits. The replacement of the THSA NBB disks having already 
accumulated more than 14,600 flight cycles will start with the oldest 
THSA. A different grace period for NBB disks replacement has been 
defined depending on the flight cycles accumulated on the THSA NBB 
disks.

Costs of Compliance

    We estimate that this proposed AD affects 152 airplanes of U.S. 
registry.
    We also estimate that it would take about 27 work-hours per product 
to comply with the basic requirements of this proposed AD. The average 
labor rate is $85 per work-hour. Required parts would cost about 
$590,000 per product. Based on these figures, we estimate the cost of 
this proposed AD on U.S. operators to be $90,028,840, or $592,295 per 
product.

Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to 
issue rules on aviation safety. Subtitle I, section 106, describes the 
authority of the FAA Administrator. ``Subtitle VII: Aviation 
Programs,'' describes in more detail the scope of the Agency's 
authority.
    We are issuing this rulemaking under the authority described in 
``Subtitle VII, Part A, Subpart III, Section 44701: General 
requirements.'' Under that section, Congress charges the FAA with 
promoting safe flight of civil aircraft in air commerce by prescribing 
regulations for practices, methods, and procedures the Administrator 
finds necessary for safety in air commerce. This regulation is within 
the scope of that authority because it addresses an unsafe condition 
that is likely to exist or develop on products identified in this 
rulemaking action.

Regulatory Findings

    We determined that this proposed AD would not have federalism 
implications under Executive Order 13132. This proposed AD would not 
have a substantial direct effect on the States, on the relationship 
between the national Government and the States, or on the distribution 
of power and responsibilities among the various levels of government.
    For the reasons discussed above, I certify this proposed 
regulation:
    1. Is not a ``significant regulatory action'' under Executive Order 
12866;
    2. Is not a ``significant rule'' under the DOT Regulatory Policies 
and Procedures (44 FR 11034, February 26, 1979);
    3. Will not affect intrastate aviation in Alaska; and
    4. Will not have a significant economic impact, positive or 
negative, on a substantial number of small entities under the criteria 
of the Regulatory Flexibility Act.

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-2016-3993; Directorate Identifier 2015-NM-
065-AD.

(a) Comments Due Date

    We must receive comments by April 21, 2016.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to the Airbus airplanes identified in paragraphs 
(c)(1) through (c)(6) of this AD, certificated in any category, all 
manufacturer serial numbers.
    (1) Airbus Model A300 B2-1A, B2-1C, B2K-3C, B2-203, B4-2C, B4-
103, and B4-203 airplanes.
    (2) Airbus Model A300 B4-601, B4-603, B4-620, and B4-622 
airplanes.
    (3) Airbus Model A300 B4-605R and B4-622R airplanes.
    (4) Airbus Model A300 F4-605R and F4-622R airplanes.
    (5) Airbus Model A300 C4-605R Variant F airplanes.
    (6) Airbus Model A310-203, -204, -221, -222, -304, -322, -324, 
and -325 airplanes.

(d) Subject

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

(e) Reason

    This AD was prompted by reports of partial loss of no-back brake 
(NBB) efficiency on the trimmable horizontal stabilizer actuator 
(THSA). We are issuing this AD to prevent loss of THSA NBB 
efficiency, which in conjunction with the power gear not able to 
keep the ball screw in its last commanded position, could lead to an 
uncommanded movement of the horizontal stabilizer, possibly 
resulting in loss of control of the airplane.

(f) Compliance

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

(g) Affected THSAs

    THSAs affected by the requirements of this AD have part numbers 
(P/Ns) 47142-403, 47142-413, 47142-414, and 47142-423.

    Note 1 to paragraph (g) of this AD:  FAA AD 2011-15-08, 
Amendment 39-16755 (76 FR 42029, July 18, 2011) requires 
installation of three secondary retention plates for the gimbal 
bearings on the THSA upper primary attachment, which involved a THSA 
part number change from the -300 series to the -400 series.


    Note 2 to paragraph (g) of this AD:  The life limits specified 
in Part 4 of the airworthiness limitations section are still 
relevant for the affected THSA. This AD addresses a replacement 
limit for the NBB disks installed on the THSA, not the life limit 
for the THSA itself.

(h) Inspection for Affected THSAs, Flight Cycles, and THSA Replacement

    Before each date and before exceeding the corresponding THSA 
flight-cycle limits specified in paragraphs (j)(1), (j)(2), and 
(j)(3) of this AD, do the actions specified in paragraphs (h)(1) and 
(h)(2) of this AD, and before exceeding the flight cycle limit 
corresponding to each date as specified in paragraphs (j)(1), 
(j)(2), and (j)(3) of this AD, do the actions specified in paragraph 
(i) of this AD.
    (1) Do an inspection of the THSA to determine the part number 
and serial number.
    (2) Do an inspection of the airplane maintenance records to 
determine the flight cycles accumulated on each affected THSA since 
first installation on an airplane, or since last NBB replacement, 
whichever is later. If no maintenance records conclusively 
identifying the last NBB disk replacement are available, the flight 
cycles accumulated since first installation of the THSA on an 
airplane apply.

(i) THSA Replacement

    By each date specified in paragraphs (j)(1), (j)(2), and (j)(3) 
of this AD, for those affected THSAs having reached or exceeded the 
corresponding number of flight cycles

[[Page 11692]]

specified in paragraphs (j)(1), (j)(2), and (j)(3) of this AD, 
replace the THSA with a serviceable unit, in accordance with the 
Accomplishment Instructions of Airbus Service Bulletin A300-27-6070, 
dated February 17, 2015; or Airbus Service Bulletin A310-27-2106, 
dated February 17, 2015, as applicable.

(j) Compliance Dates and THSA Flight Cycle Limits

    Paragraphs (j)(1), (j)(2), and (j)(3) of this AD specify 
compliance dates and THSA flight cycle limits for accomplishing the 
actions required by paragraphs (h) and (i) of this AD.
    (1) As of 30 days after the effective date of this AD: The 
affected THSA flight-cycle limit is 30,000 flight cycles since first 
installation of the THSA on an airplane, or since last NBB 
replacement, whichever is later.
    (2) As of February 1, 2017: The affected THSA flight-cycle limit 
is 20,000 flight cycles since first installation of the THSA on an 
airplane, or since last NBB replacement, whichever is later.
    (3) As of February 1, 2018: The affected THSA flight-cycle limit 
is 14,600 flight cycles since first installation of the THSA on an 
airplane, or since last NBB replacement, whichever is later.

(k) Serviceable THSA Definition

    For the purpose of this AD, a serviceable THSA is a unit 
identified in paragraph (k)(1) or (k)(2) of this AD.
    (1) A THSA identified in paragraph (g) of this AD that, as of 
each date specified in paragraphs (j)(1), (j)(2), and (j)(3) of this 
AD, has not exceeded the flight cycle limits specified in paragraphs 
(j)(1), (j)(2), and (j)(3) of this AD since first installation of 
the THSA on an airplane, or since the last NBB disk replacement, 
whichever is later.
    (2) A THSA with a different part number (e.g., a THSA that is 
not identified in paragraph (g) of this AD) that is not affected by 
the requirements of this AD.

(l) THSA Replacements

    As of each date and before exceeding the flight cycle limit 
corresponding to each date specified in paragraphs (j)(1), (j)(2), 
and (j)(3) of this AD: Replace each affected THSA with a serviceable 
unit, in accordance with the Accomplishment Instructions of Airbus 
Service Bulletin A300-27-6070, dated February 17, 2015; or Airbus 
Service Bulletin A310-27-2106, dated February 17, 2015.

(m) Parts Installation Limitation

    Before each date specified in paragraphs (j)(1), (j)(2), and 
(j)(3) of this AD, an operator may install an affected THSA on an 
airplane, provided that the unit has not exceeded the corresponding 
number of flight cycles specified in paragraphs (j)(1), (j)(2), and 
(j)(3) of this AD, since first installation on an airplane, or since 
last NBB replacement, whichever occurred later.

(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 Dan Rodina, 
Aerospace Engineer, International Branch, ANM-116, Transport 
Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057-
3356; telephone: 425-227-2125; 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 AD 2015-0081, dated May 7, 2015, 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-2016-3993.
    (2) For service information identified in this AD, contact 
Airbus SAS, Airworthiness Office--EAW, 1 Rond Point Maurice 
Bellonte, 31707 Blagnac Cedex, France; telephone: +33 5 61 93 36 96; 
fax: +33 5 61 93 44 51; email: account.airworth-eas@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 February 24, 2016.
Dionne Palermo,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2016-04562 Filed 3-4-16; 8:45 am]
 BILLING CODE 4910-13-P


