
[Federal Register Volume 80, Number 32 (Wednesday, February 18, 2015)]
[Proposed Rules]
[Pages 8571-8575]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2015-02922]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2015-0243; Directorate Identifier 2014-NM-114-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

[[Page 8572]]

Airbus Model A300 series airplanes; Model A300 B4-600, B4-600R, and F4-
600R series airplanes, and 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 cracked 
aluminum support struts of the trimmable horizontal stabilizer (THS) 
caused by stress corrosion. This proposed AD would require inspections 
to identify the part number of each support strut, repetitive 
inspections for cracking of the THS support strut ends, installation of 
reinforcing clamps on strut ends, and replacement of support struts, if 
necessary. We are proposing this AD to detect and correct cracked THS 
support struts, which could lead to the rupture of all four support 
struts making the remaining structure unable to carry limit loads, 
which could result in loss of the THS and reduced control of the 
airplane.

DATES: We must receive comments on this proposed AD by April 6, 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--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-2015-
0243; 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-2015-0243; 
Directorate Identifier 2014-NM-114-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 2014-0164, dated July 11, 2014 (referred to 
after this as the Mandatory Continuing Airworthiness Information, or 
``the MCAI''), to correct an unsafe condition for all Airbus Model A300 
series airplanes; Model A300 B4-600, B4-600R, and F4-600R series 
airplanes, and A300 C4-605R Variant F airplanes (collectively called 
Model A300-600 series airplanes); and Model A310 series airplanes. The 
MCAI states:

    During scheduled maintenance, several Trimmable Horizontal 
Stabilizer (THS) support struts were found cracked at the strut 
ends. The THS is supported and articulated at frame (FR) 91 in the 
tail cone. Lateral movement is prevented by four diagonal support 
struts.
    Investigations revealed that the cracks were caused by stress 
corrosion and propagated from the inside to the outside of the 
strut.
    This condition, if not detected and corrected, could lead to the 
rupture of all four THS support struts at FR91, which would make the 
remaining structure unable to carry limit loads, potentially 
resulting in loss of the Horizontal Tail Plane.
    To address this unsafe condition, EASA issued [EASA] AD 2014-
0121 [http://ad.easa.europa.eu/ad/2014-0121] to require repetitive 
High Frequency Eddy Current (HFEC) inspections of the THS support 
strut ends, installation of reinforcing clamps on strut ends and, 
depending on findings, replacement of damaged support struts. 
Installation of reinforcing clamps on strut ends is considered a 
temporary solution pending introduction of a re-designed support 
strut.
    Since that [EASA] AD was issued, it was discovered that the 
[EASA] AD appeared to also require HFEC inspections of steel struts, 
which are not prone to cracking. The unsafe condition exists only on 
support struts made of aluminum, which were introduced through 
Airbus modification (mod) 06101, but may also have been installed in 
service as replacement parts on aeroplanes in pre-mod 06101 
configuration.
    For the reason described above, this [EASA] AD retains the 
requirements of EASA AD 2014-0121, which is superseded, and 
clarifies the need for an initial identification of the support 
struts installed on aeroplanes in pre-mod 06101 configuration. The 
related Airbus Service Bulletins (SB) remain unchanged.

    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-2015-
0243.

Relevant Service Information Under 1 CFR Part 51

    Airbus has issued the following service information. The actions 
described in this service information are intended to correct the 
unsafe condition identified in the MCAI.
     Airbus Service Bulletin A300-53-0394, dated February 14, 
2014. This service information describes procedures for reinforcing the 
support struts of the THS at frame 91 in the fuselage tail section of 
Airbus Model A300 series airplanes.
     Airbus Service Bulletin A300-53-0395, dated February 14, 
2014. This service information describes procedures for inspecting for 
cracking of the support struts of the THS at frame 91 in the fuselage 
tail section of Airbus Model A300 series airplanes.
     Airbus Service Bulletin A300-53-6172, dated February 14, 
2014. This service information describes procedures for reinforcing the 
support struts of the THS at frame 91 in the fuselage tail section of 
Airbus Model A300-600 series airplanes.

[[Page 8573]]

     Airbus Service Bulletin A300-53-6174, dated February 14, 
2014. This service information describes procedures for inspecting for 
cracking of the support struts of the THS at frame 91 in the fuselage 
tail section of Airbus Model A300-600 series airplanes.
     Airbus Service Bulletin A310-53-2136, dated February 14, 
2014. This service information describes procedures for reinforcing the 
support struts of the THS at frame 91 in the fuselage tail section of 
Airbus Model A310 series airplanes.
     Airbus Service Bulletin A310-53-2137, dated February 14, 
2014. This service information describes procedures for inspecting for 
cracking of the support struts of the THS at frame 91 in the fuselage 
tail section of Airbus Model A310 series airplanes. This service 
information is reasonably available; see ADDRESSES for ways to access 
this service information.

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

    Unlike the procedures described in Airbus Service Bulletin A300-53-
0395; Airbus Service Bulletin A300-53-6174; and Airbus Service Bulletin 
A310-53-2137; each dated February 14, 2014; this proposed AD would not 
permit further flight if cracks are detected in the aluminum support 
strut ends of the trimmable horizontal stabilizer at frame 91. We have 
determined that, because of the safety implications and consequences 
associated with that cracking, any cracked aluminum support strut ends 
of the trimmable horizontal stabilizer must be repaired or modified 
before further flight. This difference has been coordinated with EASA 
and Airbus.

Costs of Compliance

    We estimate that this proposed AD affects 174 airplanes of U.S. 
registry.
    We also estimate that it would take about 5 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 $2,100 
per product. Based on these figures, we estimate the cost of this 
proposed AD on U.S. operators to be $439,350, or $2,525 per product.
    In addition, we estimate that any necessary follow-on actions would 
take about 15 work-hours and require parts costing $10,000, for a cost 
of $11,275 per product. We have no way of determining the number of 
aircraft that might need these actions.

Paperwork Reduction Act

    A federal agency may not conduct or sponsor, and a person is not 
required to respond to, nor shall a person be subject to 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 control 
number for the collection of information required by this proposed AD 
is 2120-0056. The paperwork cost associated with this proposed AD has 
been detailed in the Costs of Compliance section of this document and 
includes time for reviewing instructions, as well as completing and 
reviewing the collection of information. Therefore, all reporting 
associated with this proposed AD is 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.

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-2015-0243; Directorate Identifier 2014-NM-
114-AD.

(a) Comments Due Date

    We must receive comments by April 6, 2015.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to the Airbus airplanes specified 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.

[[Page 8574]]

    (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 53, Fuselage.

(e) Reason

    This AD was prompted by reports of cracked aluminum support 
struts of the trimmable horizontal stabilizer (THS) caused by stress 
corrosion. We are issuing this AD to detect and correct cracked THS 
support struts, which could lead to the rupture of all four support 
struts making the remaining structure unable to carry limit loads, 
which could result in loss of the THS and reduced control of the 
airplane.

(f) Compliance

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

(g) Inspection for Part Number

    For airplanes in pre-modification 06101 configuration: Within 12 
months after the effective date of this AD, do an inspection to 
identify the part number (P/N) of each support strut installed on 
the trimmable horizontal stabilizer (THS) at frame (FR) 91, in 
accordance with the Accomplishment Instructions of the applicable 
service bulletin identified in paragraphs (g)(1) through (g)(3) of 
this AD. A review of airplane maintenance records is acceptable in 
lieu of this inspection, provided those records can be relied upon 
for that purpose and the part number can be positively identified 
from that review. If no aluminum strut(s) having P/N R21449, 
R21449D, R21449G, or R21449H is found during any inspection required 
by this paragraph no further action is required by this AD for that 
horizontal stabilizer, except for paragraph (l) of this AD.
    (1) For Airbus Model A300 series airplanes: Airbus Service 
Bulletin A300-53-0395, dated February 14, 2014.
    (2) For Airbus Model A300 B4-600, B4-600R, and F4-600R series 
airplanes, and A300 C4-605R Variant F airplanes (collectively called 
Model A300-600 series airplanes): Airbus Service Bulletin A300-53-
6174, dated February 14, 2014.
    (3) For Airbus Model A310 series airplanes: Airbus Service 
Bulletin A310-53-2137, dated February 14, 2014.

(h) Repetitive High Frequency Eddy Current (HFEC) Inspections

    For airplanes in post-modification 06101 configuration; and for 
airplanes in pre-modification 06101 configuration on which one or 
more aluminum support strut(s) having P/N R21449, P/N R21449D, P/N 
R21449G, or P/N R21449H was found during the inspection by paragraph 
(g) of this AD: Within the applicable compliance times specified in 
paragraphs (h)(1), (h)(2), or (h)(3) of this AD, do an HFEC 
inspection for cracking of the aluminum THS support strut ends at FR 
91, in accordance with the Accomplishment Instructions of the 
applicable service bulletin identified in paragraphs (g)(1) through 
(g)(3) of this AD. Reinforcing clamps already installed on strut 
ends must be removed before accomplishing the HFEC inspection and 
re-installed after the inspection, in accordance with the 
Accomplishment Instructions of the applicable service bulletin 
specified in paragraphs (g)(1) through (g)(3) of this AD. Repeat the 
inspection thereafter at intervals not to exceed 24 months.
    (1) For airplanes having manufacturer serial number (MSN) 0499 
through MSN 0747 inclusive (post-mod 06101): Within 12 months after 
the effective date of this AD.
    (2) For airplanes having MSN 0748 through MSN 0878 inclusive 
(post-mod 06101): Within 18 months after the effective date of this 
AD.
    (3) For airplanes having MSN 0001 through MSN 0498 inclusive 
(pre-mod 06101) having one or more aluminum struts: Within 24 months 
after the effective date of this AD.

(i) Installation of Reinforcing Clamps

    Concurrently with the initial HFEC inspection required by 
paragraph (h) of this AD, identify struts having P/N R21449, P/N 
R21449D, P/N R21449G, or P/N R21449H with no reinforcing clamps 
previously installed, and before next flight, install reinforcing 
clamps on each strut end, in accordance with the Accomplishment 
Instructions of the applicable service bulletin specified in 
paragraphs (i)(1) through (i)(3) of this AD.
    (1) For Airbus Model A300 series airplanes: Airbus Service 
Bulletin A300-53-0394, dated February 14, 2014.
    (2) For Airbus Model A300 B4-600, B4-600R, and F4-600R series 
airplanes, and A300 C4-605R Variant F airplanes (collectively called 
Model A300-600 series airplanes): Airbus Service Bulletin A300-53-
6172, dated February 14, 2014.
    (3) For Airbus Model A310 series airplanes: Airbus Service 
Bulletin A310-53-2136, dated February 14, 2014.

(j) Corrective Actions

    If, during any inspection required by paragraph (h) of this AD, 
any cracking is found, before further flight, replace the affected 
THS support strut(s) with serviceable struts and install clamps on 
each strut end, in accordance with the Accomplishment Instructions 
of the applicable service bulletin identified in paragraphs (g)(1) 
through (g)(3) of this AD.

(k) Clarification

    Installation of reinforcing clamps as required by paragraph (i) 
of this AD, and the replacement of support struts and/or the 
installation of clamps as required by paragraph (j) of this AD, do 
not constitute terminating action for the repetitive inspections 
required by paragraph (h) of this AD.

(l) Reporting

    At the applicable time specified in paragraphs (l)(1) and (l)(2) 
of this AD: After accomplishment of any inspection required by 
paragraphs (g) and (h) of this AD, report all inspection results to 
Airbus, including no findings, in accordance with the Accomplishment 
Instructions of the applicable service bulletins specified in 
paragraphs (g)(1) through (g)(3) of this AD, and paragraphs (i)(1) 
through (i)(3) of this AD.
    (1) If the inspection was done on or after the effective date of 
this AD: Submit the report within 30 days after the inspection.
    (2) If the inspection was done before the effective date of this 
AD: Submit the report within 30 days after the effective date of 
this AD.

(m) 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: 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) 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.

(n) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) European

[[Page 8575]]

Aviation Safety Agency Airworthiness Directive 2014-0164, dated July 
11, 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-2015-0243.
    (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 2, 2015.
Dionne Palermo,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2015-02922 Filed 2-17-15; 8:45 am]
BILLING CODE 4910-13-P


