[Federal Register Volume 80, Number 15 (Friday, January 23, 2015)]
[Proposed Rules]
[Pages 3510-3513]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2015-00993]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2014-1043; Directorate Identifier 2013-NM-079-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 A330-200, A330-200 Freighter, and A330-300 series 
airplanes; and Model A340-200 and A340-300 series airplanes. This 
proposed AD was prompted by reports of cracked support strut body ends 
at a certain frame location of the trimmable horizontal stabilizer 
(THS). This proposed AD would require repetitive inspections for 
cracking of the strut ends of the THS support located at a certain 
frame in the tail cone, and replacement if necessary; and 
reinstallation or installation of reinforcing clamps on certain strut 
ends. We are proposing this AD to detect and correct cracked support 
strut body ends of the THS, which could lead to the loss of all four 
THS support struts and which would make the remaining structure unable 
to carry limit loads, resulting in the loss of the horizontal tail 
plane.

DATES: We must receive comments on this proposed AD by March 9, 2015.

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 [email protected]; 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-
1043; 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: 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-2014-1043; 
Directorate Identifier 2013-NM-079-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 
Airworthiness Directive 2014-0068, dated March 18, 2014 (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, and A330-300 series airplanes; and Model A340-
200 and A340-300 series airplanes. The MCAI states:

    During scheduled maintenance on A330 aeroplanes, several 
Trimmable Horizontal Stabilizer (THS) support struts at frame (FR) 
91 were found cracked at strut body ends.
    The THS is supported and articulated at FR 91 by four struts to 
fix the hinges (Y-bolts) and keep the structural integrity in 
lateral direction.
    Analysis revealed that cracks can reduce ability of the support 
struts to carry specified tension loads.
    This condition, if not detected and corrected, could lead to the 
loss of all four THS support struts at FR91, which would make the 
remaining structure unable to carry limit loads, resulting in the 
loss of Horizontal Tail Plane.
    A340-500/600 aeroplanes are not affected by this [EASA] AD as 
different material is used on THS support struts.
    To address this potentially unsafe condition, EASA issued AD 
2013-0076 [http://ad.easa.europa.eu/blob/easa_ad_2013_0076_superseded.pdf/AD-2013-0076_1] to require 
repetitive special detailed inspections [high frequency eddy current 
(HFEC) inspections for cracking] of all 8 strut ends of the THS 
support located at FR91 in the tail cone and, depending on findings, 
replacement of THS support struts. That

[[Page 3511]]

[EASA] AD also required, for aeroplanes on which Airbus Modification 
203493 had not been embodied in production, or Airbus Service 
Bulletin (SB) A330-53-3204 or SB A340-53-4199, as applicable, has 
not been embodied in service, the installation of a clamping device 
on each support strut end to stop growth of possible cracks (crack 
stopper function) in order to secure integrity of the struts.
    Since issuance of EASA AD 2013-0076, it has been discovered that 
several aeroplanes are fitted with another strut configuration 
(SARMA Strut) [Societ[eacute] Anonyme de Recherche M[eacute]canique 
Appliqu[eacute]e] than the TAC (Technical Airborne Components 
Industries) strut, which caused the other strut not to be 
considered. Consequently, Airbus revised Airbus SB A330-53-3206 and 
SB A340-53-4208, accordingly in order to add a one-time [HFEC] 
inspection [for cracking] for SARMA struts and in case of finding to 
replace it with a TAC strut and thereafter to accomplish repetitive 
inspections and EASA issued AD 2013-0219 [http://ad.easa.europa.eu/blob/easa_ad_2013_0219_superseded.pdf/AD-2013-0219_1], which is 
superseded, and required accomplishment of the instructions as 
specified in the latest revision of each SB, as applicable.
    Since issuance of EASA AD 2013-0219, based on the reporting 
received from operators, it has been determined that repetitive 
inspections are also to be accomplished for aeroplanes equipped with 
SARMA strut. Airbus introduced that inspection in the applicable SB 
at revision 3.
    For the reasons described above, this [EASA] AD retains the 
requirements of EASA AD 2013-0219, which is superseded, and requires 
accomplishment of repetitive [HFEC] inspective inspection [for 
cracking] for aeroplanes equipped with SARMA strut.
    This [EASA] AD is considered as an interim action, pending the 
development of a terminating action.

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-2014-
1043.

Related Service Information

    Airbus has issued the following service information:
     Airbus Service Bulletin A330-53-3206, Revision 03, dated 
February 28, 2014. This service information describes procedures for 
inspections for cracking of the strut ends of the THS support located 
in the airplane tail cone for Model A330 airplanes.
     Airbus Service Bulletin A340-53-4208, Revision 03, dated 
February 28, 2014. This service information describes procedures for 
inspections for cracking of the strut ends of the THS support located 
in the airplane tail cone for Model A340 airplanes.
    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 these 
same type designs.

Differences Between This Proposed AD and the MCAI or Service 
Information

    Although EASA Airworthiness Directive 2014-0068, dated March 18, 
2014, Airbus Service Bulletin A330-53-3206, Revision 03, dated February 
28, 2014, and Airbus Service Bulletin A340-53-4208, Revision 03, dated 
February 28, 2014, allow further flight after certain cracks are found 
during compliance with the proposed action, paragraph (j)(2) of this 
proposed AD would require that any cracked THS support strut be 
replaced with a new or serviceable TAC strut before further flight.

Interim Action

    We consider this proposed AD interim action. If final action is 
later identified, we might consider further rulemaking then.

Costs of Compliance

    We estimate that this proposed AD affects 84 airplanes of U.S. 
registry.
    We also estimate that it would take about 9 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 this proposed AD on U.S. operators to be $64,260, or $765 
per product.
    We have received no definitive data that would enable us to provide 
cost estimates for the on-condition replacement specified in this 
proposed AD.
    We estimate that any necessary follow-on strut reinforcements would 
take about 2 work-hours and require parts costing $5,680, for a cost of 
$5,850 per product. We have no way of determining the number of 
aircraft that might need this action.
    According to the manufacturer, some of the costs of this proposed 
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 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:


[[Page 3512]]


    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-2014-1043; Directorate Identifier 2013-NM-
079-AD.

(a) Comments Due Date

    We must receive comments by March 9, 2015.

(b) Affected ADs

    None.

(c) Applicability

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

(d) Subject

    Air Transport Association (ATA) of America Code 53, Fuselage.

(e) Reason

    This AD was prompted by reports of cracked support strut body 
ends at a certain frame location of the trimmable horizontal 
stabilizer (THS). We are issuing this AD to detect and correct 
cracked support strut body ends of the THS, which could lead to the 
loss of all four THS support struts and which would make the 
remaining structure unable to carry limit loads, resulting in the 
loss of the horizontal tail plane.

(f) Compliance

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

(g) Definition of Strut Types

    For the purpose of this AD, a Societ[eacute] Anonyme de 
Recherche M[eacute]canique Appliqu[eacute]e (SARMA) strut is a strut 
on which the diameter of the strut end is lower than 43 millimeters. 
All other struts are Technical Airborne Components Industries (TAC) 
struts.

(h) Repetitive Inspections of TAC Strut Ends

    At the applicable time specified in paragraph (i) of this AD, do 
a high frequency eddy current (HFEC) inspection for cracking of all 
TAC strut ends of the THS support located at frame (FR) 91 in the 
tail cone, in accordance with the Accomplishment Instructions of 
Airbus Service Bulletin A330-53-3206, Revision 03, dated February 
28, 2014; or Airbus Service Bulletin A340-53-4208, Revision 03, 
dated February 28, 2014; as applicable. Repeat the inspection 
thereafter at intervals not to exceed 42 months or 20,000 flight 
hours, whichever occurs first. For airplanes on which Airbus 
Modification 203493 has been embodied in production, or Airbus 
Service Bulletin A330-53-3204 or Airbus Service Bulletin A340-53-
4199, as applicable, has been embodied in service, remove the clamp 
from each strut end before accomplishing the inspections required by 
this paragraph.

(i) Compliance Times for Paragraphs (h) and (k) of This AD

    Do the inspections required by paragraphs (h) and (k) of this AD 
at the applicable times specified in paragraphs (i)(1), (i)(2), and 
(i)(3) of this AD.
    (1) For Model A330 series airplanes having manufacturer serial 
numbers 012 through 209 inclusive, and Model A340 series airplanes 
having manufacturer serial numbers 002 through 210 inclusive: Within 
6 months after the effective date of this AD.
    (2) For Model A330 series airplanes having manufacturer serial 
numbers 211 through 422 inclusive, and Model A340 series airplanes 
having manufacturer serial numbers 212 through 447 inclusive: Within 
24 months after the effective date of this AD.
    (3) For Model A330 series airplanes having manufacturer serial 
numbers 423 and subsequent, and Model A340 series airplanes having 
manufacturer serial numbers 450 through 955 inclusive: Within 36 
months after the effective date of this AD or since the first flight 
of the airplane, whichever occurs later.

(j) Corrective Action for TAC Strut Ends and Installation of 
Reinforcing Clamps

    (1) If, during any inspection required by paragraph (h) of this 
AD, no cracks are found: Before further flight, reinstall or 
install, as applicable, reinforcing clamps on the strut ends, in 
accordance with the Accomplishment Instructions of Airbus Service 
Bulletin A330-53-3206, Revision 03, dated February 28, 2014; or 
Airbus Service Bulletin A340-53-4208, Revision 03, dated February 
28, 2014.
    (2) If, during any inspection required by paragraph (h) of this 
AD, any crack is found: Before further flight, replace any affected 
strut with a new or serviceable TAC strut and install reinforcing 
clamps on the strut end, in accordance with the Accomplishment 
Instructions of Airbus Service Bulletin A330-53-3206, Revision 03, 
dated February 28, 2014; or Airbus Service Bulletin A340-53-4208, 
Revision 03, dated February 28, 2014; as applicable.

(k) Repetitive Inspections of SARMA Strut Ends

    At the applicable time specified in paragraph (i) of this AD, do 
an HFEC inspection for cracking of all SARMA strut ends of the THS 
support located at FR 91 in the tail cone, in accordance with the 
Accomplishment Instructions of Airbus Service Bulletin A330-53-3206, 
Revision 03, dated February 28, 2014; or Airbus Service Bulletin 
A340-53-4208, Revision 03, dated February 28, 2014; as applicable. 
Repeat the inspection thereafter at intervals not to exceed 12 
months.

(l) Corrective Action for SARMA Strut Ends

    If any crack is found on a strut end during the inspection 
required by paragraph (k) of this AD: Before further flight, replace 
any affected SARMA strut with a new or serviceable TAC strut and 
install reinforcing clamps on the strut end, in accordance with the 
Accomplishment Instructions of Airbus Service Bulletin A330-53-3206, 
Revision 03, dated February 28, 2014; or Airbus Service Bulletin 
A340-53-4208, Revision 03, dated February 28, 2014; as applicable.

(m) No Terminating Action

    Replacement of THS struts on an airplane does not constitute 
terminating action for the repetitive inspections required by this 
AD.

(n) No Reporting

    Although Airbus Service Bulletin A330-53-3206, Revision 03, 
dated February 28, 2014, and Airbus Service Bulletin A340-53-4208, 
Revision 03, dated February 28, 2014, specify to submit certain 
information to the manufacturer, this AD does not include that 
requirement.

(o) Credit for Previous Actions

    This paragraph provides credit for actions required by 
paragraphs (g) through (k) of this AD, if those actions were 
performed before the effective date of this AD using any of the 
service information identified in paragraphs (n)(1) through (n)(6) 
of this AD. This service information is not incorporated by 
reference in this AD.
    (1) Airbus Service Bulletin A330-53-3206, dated February 7, 
2013.
    (2) Airbus Service Bulletin A330-53-3206, Revision 01, dated 
June 10, 2013.
    (3) Airbus Service Bulletin A330-53-3206, Revision 02, dated 
August 8, 2013.
    (4) Airbus Service Bulletin A340-53-4208, dated February 7, 
2013.
    (5) Airbus Service Bulletin A340-53-4208, Revision 01, dated 
June 10, 2013.
    (6) Airbus Service Bulletin A340-53-4208, Revision 02, dated 
August 8, 2013.

(p) 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: [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) 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

[[Page 3513]]

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.

(q) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) EASA Airworthiness Directive 2014-0068, dated March 18, 2014, 
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-2014-1043.
    (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 [email protected]; 
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 January 11, 2015.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2015-00993 Filed 1-22-15; 8:45 am]
BILLING CODE 4910-13-P