[Federal Register Volume 78, Number 148 (Thursday, August 1, 2013)]
[Proposed Rules]
[Pages 46543-46546]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2013-18566]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2013-0665; Directorate Identifier 2012-NM-082-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 A330-300 series airplanes and Model A340-200 and -300 
series airplanes. This proposed AD was prompted by reports of corrosion 
found on certain trimmable horizontal stabilizer actuators (THSA), 
affecting the ballscrew lower splines between the tie bar and the 
screw-jack. This proposed AD would require repetitive detailed 
inspections for corrosion of certain THSAs, ballscrew integrity tests 
if necessary; and replacing any affected THSA with a serviceable or new 
and improved THSA, if necessary. We are proposing this AD to detect and 
correct corrosion of the THSAs, which could lead, in the case of 
ballscrew rupture, to the loss of transmission of THSA torque loads 
from the ballscrew to the tie-bar, prompting THSA blowback, and 
possibly resulting in loss of control of the airplane.

DATES: We must receive comments on this proposed AD by September 16, 
2013.

ADDRESSES: You may send comments 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 Airbus 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 [email protected]; Internet 
http://www.airbus.com. For Goodrich service information identified in 
this proposed AD, contact Goodrich Corporation, Actuation Systems, 
Product Support Department 13, Avenue de L'Eguillette--Saint-Ouen 
L'Aumone Boite Postale 7186 95056, Cergy Pontoise Cedex, France; fax: 
33-1-34326310. You may review copies of the 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; 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 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: 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-2013-0665; 
Directorate Identifier 2012-NM-082-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 Community, has issued EASA 
Airworthiness Directive 2012-0061R1, dated November 30, 2012 (referred 
to after this as ``the MCAI''), to correct an unsafe condition for the 
specified products. The MCAI states:

    Some Trimmable Horizontal Stabilizer Actuators (THSA), Part 
Number (P/N) 47147-500, have been found with corrosion, affecting 
the ballscrew lower splines between the tie bar and the screw-jack.
    The results of the technical investigations have identified that 
the corrosion was caused by a combination of:

--Contact/friction between the tie bar and the inner surface of the 
ballscrew leading to the removal of Molykote (corrosion protection) 
at the level of the tie bar splines,
--Humidity ingress initiating surface oxidation starting from areas 
where Molykote is removed, and
--Water retention in THSA lower part leading to corrosion spread out 
and to the creation of a brown deposit (iron oxide).

    The results of the technical investigations have also concluded 
that THSA P/N 47147-500 and P/N 47147-700 ballscrews might be 
affected by this corrosion issue.
    THSA P/N 47147-400 ballscrews might be affected as well, but 
should no longer be in service, and modified into P/N 47147-500, as 
required by EASA AD 2010-0192 and EASA AD 2010-0193 [and as required 
by FAA AD 2005-07-04, Amendment 39-14028 (70 FR 16104, March 30, 
2005)].
    This condition, if not detected and corrected, may lead, in case 
of ballscrew rupture, to loss of transmission of THSA torque loads 
from the ballscrew to the tie-bar, prompting THSA blowback, possibly 
resulting in loss of control of the aeroplane.
    To correct this potential unsafe condition, EASA issued AD 2012-
0061 to require repetitive [detailed] visual inspections of the 
ballscrew lower splines of THSA having P/N 47147-500 or P/N 47147-
700 to detect corrosion and, depending on findings [ballscrew 
integrity tests], the accomplishment of applicable corrective 
actions [replacing the affected THSA with a serviceable or improved 
THSA].
    Since that [EASA] AD [2012-0061] was issued, Airbus published 
new Service Bulletin (SB) A330-27-3194 or Airbus SB A340-27-4187 
(Airbus modification 202802), which allow installation in service of 
an improved THSA P/N 47172-530.
    For the reasons described above, this [EASA] AD [2012-0061R1] is 
revised to specify that installation of THSA P/N 47172-

[[Page 46544]]

530 is an alternative (optional) terminating action to the 
repetitive inspections required by this AD.

You may obtain further information by examining the MCAI in the AD 
docket.

Relevant Service Information

    Airbus has issued the following service information.
     Airbus Mandatory Service Bulletin A330-27-3179, including 
Appendix 01, dated February 14, 2012.
     Airbus Service Bulletin A330-27-3182, dated February 14, 
2012.
     Airbus Service Bulletin A330-27-3194, dated October 8, 
2012.
     Airbus Mandatory Service Bulletin A340-27-4175, including 
Appendix 01, dated February 14, 2012.
     Airbus Service Bulletin A340-27-4178, dated February 14, 
2012.
     Airbus Service Bulletin A340-27-4187, dated October 8, 
2012.
    Goodrich Actuation Systems has issued Service Bulletin 47147-27-18, 
dated February 17, 2012.
    The actions described in this service information are intended to 
correct the unsafe condition identified in the MCAI.

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 the same 
type design.

Costs of Compliance

    Based on the service information, we estimate that this proposed AD 
would affect about 30 products of U.S. registry. We also estimate that 
it would take about 6 work-hours per product to comply with the basic 
requirements of this proposed AD. The average labor rate is $85 per 
work-hour. Based on these figures, we estimate the cost of the proposed 
AD on U.S. operators to be $15,300, or $510 per product.
    In addition, we estimate that any necessary follow-on actions would 
take about 13 work-hours and require parts costing up to $722,556 for a 
cost of up to $723,661 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 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.
    We prepared a regulatory evaluation of the estimated costs to 
comply with this proposed AD and placed it in the AD docket.

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 AD:

Airbus: Docket No. FAA-2013-0665; Directorate Identifier 2012-NM-
082-AD.

(a) Comments Due Date

    We must receive comments by September 16, 2013.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to Airbus Model A330-301, -302, -303, -321, -
322, -323, -341, -342, and -343 airplanes; and Model A340-211, -212, 
-213, -311, -312, and -313 airplanes; certificated in any category; 
all manufacturer serial numbers.

(d) Subject

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

(e) Reason

    This AD was prompted by reports of corrosion found on certain 
trimmable horizontal stabilizer actuators (THSA), affecting the 
ballscrew lower splines between the tie bar and the screw-jack. We 
are issuing this AD to detect and correct corrosion of the THSAs, 
which could lead, in the case of ballscrew rupture, to loss of 
transmission of THSA torque loads from the ballscrew to the tie-bar, 
prompting THSA blowback, and possibly resulting in loss of control 
of the airplane.

(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) Repetitive Inspections

    At the applicable time specified in paragraph (g)(1) or (g)(2) 
of this AD, except as required by paragraphs (h)(1) and (h)(2) of 
this AD: Do a detailed inspection of the gaps between the screw 
shaft and tie rod teeth of any THSA having part numbers (P/N) 47147-
500 and 47147-700, to determine if the corrosion condition is Type 
I, Type II, or Type III, in accordance with the Accomplishment 
Instructions of Airbus Mandatory Service Bulletin A330-27-3179 (for 
Model A330-301, -302, -303, -321, -322, -323, -341, -342, and -343 
airplanes); or A340-27-4175 (for Model A340-211, -212, -213, -311, -
312, and -313 airplanes); both dated February 14, 2012; and the 
Accomplishment Instructions and flowchart following the 
Accomplishment Instructions of Goodrich Actuation Systems Service 
Bulletin 47147-27-18, dated February 17, 2012. Repeat the inspection 
thereafter at intervals not to exceed 24 months until the

[[Page 46545]]

modification specified in paragraph (k) is done.
    (1) For any THSA, which, as of the effective date of this AD, 
has accumulated less than 156 months since first flight on an 
airplane as THSA P/N 47147-400 or since its first flight after 
modification has been done as specified in the Accomplishment 
Instructions of Airbus Mandatory Service Bulletin A330-27-3052 or 
A340-27-4059: Do the inspection before the accumulation of 156 
months but not before the accumulation of 132 months since first 
flight on an airplane as THSA P/N 47147-400 or since the THSA first 
flight after its modification was done as specified in the 
Accomplishment Instructions of Airbus Mandatory Service Bulletin 
A330-27-3052 or A340-27-4059; or within 3 months after the effective 
date of this AD; whichever occurs later.
    (2) For any THSA, which, as of the effective date of this AD, 
has accumulated 156 months or more since first flight on an airplane 
as THSA P/N 47147-400 or since the THSA first flight after 
modification has been done as specified in the Accomplishment 
Instructions of Airbus Mandatory Service Bulletin A330-27-3052 or 
A340-27-4059: Do the inspection within 3 months after the effective 
date of this AD.

(h) Compliance Time Exceptions

    (1) Some THSAs having P/N 47147-500 (and further derivative with 
P/N 47147-700) were originally THSA P/N 47147-400 and were 
subsequently modified in service. In this case, the time accumulated 
by any THSA must be calculated from the first installation on 
airplanes as THSA P/N 47147-400.
    (2) Some THSAs having P/N 47147-500 (and further derivative with 
P/N 47147-700) were originally THSA P/N 47147-200, -210, -213, -300, 
-303, or -350 and were subsequently modified in service as specified 
in the Accomplishment Instructions of Airbus Mandatory Service 
Bulletin A330-27-3052 or A340-27-4059. In this case, the time 
accumulated by any THSA must be calculated from the first flight on 
an airplane after the THSA has been modified as specified in the 
Accomplishment Instructions of Airbus Mandatory Service Bulletin 
A330-27-3052 or A340-27-4059.

(i) Ballscrew Integrity Test and Corrective Actions

    If, during any inspection required by paragraph (g) of this AD, 
it is determined that a THSA has Type II or Type III corrosion, 
before further flight: Do a ballscrew integrity test, in accordance 
with the Accomplishment Instructions of Airbus Mandatory Service 
Bulletin A330-27-3179 (for Model A330-301, -302, -303, -321, -322, -
323, -341, -342, and -343 airplanes); or A340-27-4175 (for Model 
A340-211, -212, -213, -311, -312, and -313 airplanes); both dated 
February 14, 2012.
    (1) For THSAs having Type II or Type III corrosion, and the 
results of the ballscrew integrity test were not correct, as 
specified in the Accomplishment Instructions of Airbus Mandatory 
Service Bulletin A330-27-3179 (for Model A330-301, -302, -303, -321, 
-322, -323, -341, -342, and -343 airplanes); or A340-27-4175 (for 
Model A340-211, -212, -213, -311, -312, and -313 airplanes); both 
dated February 14, 2012: Before further flight, replace the affected 
THSA with a new or serviceable THSA, in accordance with the 
Accomplishment Instructions of Airbus Mandatory Service Bulletin 
A330-27-3179 (for Model A330-301, -302, -303, -321, -322, -323, -
341, -342, and -343 airplanes); or A340-27-4175 (for Model A340-211, 
-212, -213, -311, -312, and -313 airplanes); both dated February 14, 
2012.
    (2) For THSAs having Type III corrosion, and the results of the 
ballscrew integrity test are correct, as specified in the 
Accomplishment Instructions of Airbus Mandatory Service Bulletin 
A330-27-3179 (for Model A330-301, -302, -303, -321, -322, -323, -
341, -342, and -343 airplanes); or A340-27-4175 (for Model A340-211, 
-212, -213, -311, -312, and -313 airplanes); both dated February 14, 
2012: Within 10 days after the most recent inspection, replace the 
THSA with a new or serviceable THSA, in accordance with the 
Accomplishment Instructions of Airbus Mandatory Service Bulletin 
A330-27-3179 (for Model A330-301, -302, -303, -321, -322, -323, -
341, -342, and -343 airplanes); or A340-27-4175 (for Model A340-211, 
-212, -213, -311, -312, and -313 airplanes); both dated February 14, 
2012.
    (3) For THSAs having Type II corrosion and the results of the 
ballscrew integrity test are correct: Within 24 months or 4,400 
flight cycles after the most recent inspection, whichever occurs 
first, replace the THSA with a new or serviceable THSA, in 
accordance with the Accomplishment Instructions of Airbus Mandatory 
Service Bulletin A330-27-3179 (for Model A330-301, -302, -303, -321, 
-322, -323, -341, -342, and -343 airplanes); or A340-27-4175 (for 
Model A340-211, -212, -213, -311, -312, and -313 airplanes); both 
dated February 14, 2012.

(j) Replacement of a THSA Is Not Terminating Action

    Replacement of a THSA with a THSA having P/N 47147-500 or 47147-
700 does not constitute a terminating action for the repetitive 
inspections required by paragraph (g) of this AD.

(k) Optional Terminating Modification

    (1) Replacing any THSA having P/N 47147-500 with a new improved 
THSA having P/N 47172-300 (Airbus modification 200238), in 
accordance with the Accomplishment Instructions of Airbus Service 
Bulletin A330-27-3182 (for Model A330-301, -302, -303, -321, -322, -
323, -341, -342, and -343 airplanes); or A340-27-4178 (for Model 
A340-211, -212, -213, -311, -312, and -313 airplanes); both dated 
February 14, 2012; terminates the repetitive inspections required by 
paragraph (g) of this AD.
    (2) Replacing any THSA having P/N 47147-700 with a new improved 
THSA having P/N 47172-530 (Airbus modification 202802), in 
accordance with the Accomplishment Instructions of Airbus Service 
Bulletin A330-27-3194 (for Model A330-301, -302, -303, -321, -322, -
323, -341, -342, and -343 airplanes); or A340-27-4187 (for Model 
A340-211, -212, -213, -311, -312, and -313 airplanes); both dated 
October 8, 2012; terminates the repetitive inspections required by 
paragraph (g) of this AD.

(l) Parts Installation Limitation

    As of the effective date of this AD, no person may install a 
THSA, P/N 47147-500 or P/N 47147-700, on any airplane, unless the 
THSA is classified as Type I (no corrosion), in accordance with the 
criteria defined in Goodrich Actuation Systems Service Bulletin 
47147-27-18, dated February 17, 2012; and thereafter inspected in 
accordance with the requirements of paragraph (g) of this AD and any 
applicable actions required by paragraph (i) of this AD are 
accomplished.

(m) Reporting

    Submit a report of the findings (both positive and negative) of 
the inspection required by paragraph (g) of this AD to Airbus, at 
the applicable time specified in paragraph (m)(1) or (m)(2) of this 
AD, using Appendix 01 of Airbus Mandatory Service Bulletins A330-27-
3179 (for Model A330-301, -302, -303, -321, -322, -323, -341, -342, 
and -343 airplanes); or A340-27-4175 (for Model A340-211, -212, -
213, -311, -312, and -313 airplanes); both dated February 14, 2012.
    (1) If the inspection was done on or after the effective date of 
this AD: Submit the report within 90 days after the inspection.
    (2) If the inspection was done before the effective date of this 
AD: Submit the report within 90 days after the effective date of 
this AD.

(n) Other FAA AD Provisions

    The following provisions also apply to this AD:
    (1) Alternative Methods of Compliance (AMOCs): The Manager, 
International Branch, 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: [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.

[[Page 46546]]

    (3) Reporting Requirements: A federal agency may not conduct or 
sponsor, and a person is not required to respond to, nor shall a 
person be subject to a penalty for failure to comply with a 
collection of information subject to the requirements of the 
Paperwork Reduction Act unless that collection of information 
displays a current valid OMB Control Number. The OMB Control Number 
for this information collection is 2120-0056. Public reporting for 
this collection of information is estimated to be approximately 5 
minutes per response, including the time for reviewing instructions, 
completing and reviewing the collection of information. All 
responses to this collection of information are mandatory. Comments 
concerning the accuracy of this burden and suggestions for reducing 
the burden should be directed to the FAA at: 800 Independence Ave. 
SW., Washington, DC 20591, Attn: Information Collection Clearance 
Officer, AES-200.

(o) Related Information

    (1) Refer to MCAI European Aviation Safety Agency Airworthiness 
Directive 2012-0061R1, dated November 30, 2012; and the service 
information identified in paragraphs (o)(1)(i) through (o)(1)(vii) 
of this AD; for related information.
    (i) Airbus Mandatory Service Bulletin A330-27-3179, dated 
February 14, 2012.
    (ii) Airbus Service Bulletin A330-27-3182, dated February 14, 
2012.
    (iii) Airbus Service Bulletin A330-27-3194, dated October 8, 
2012.
    (iv) Airbus Mandatory Service Bulletin A340-27-4175, dated 
February 14, 2012.
    (v) Airbus Service Bulletin A340-27-4178, dated February 14, 
2012.
    (vi) Airbus Service Bulletin A340-27-4187, dated October 8, 
2012.
    (vii) Goodrich Actuation Systems Service Bulletin 47147-27-18, 
dated February 17, 2012.
    (2) For Airbus 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 Goodrich Actuation Systems 
service information identified in this AD, contact Goodrich 
Corporation, Actuation Systems, Product Support Department 13, 
Avenue de L'Eguillette--Saint-Ouen L'Aumone Boite Postale 7186 
95056, Cergy Pontoise Cedex, France; fax: 33-1-34326310. You may 
review copies of the 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.

    Issued in Renton, Washington, on July 21, 2013.
Stephen P. Boyd,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2013-18566 Filed 7-31-13; 8:45 am]
BILLING CODE 4910-13-P