
[Federal Register Volume 78, Number 186 (Wednesday, September 25, 2013)]
[Proposed Rules]
[Pages 58975-58978]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2013-23269]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2013-0791; Directorate Identifier 2012-NM-026-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 A318, A319, A320, and A321 series airplanes. This proposed 
AD was prompted by a report that an investigation showed that when a 
certain combination of a target/proximity sensor serial number is 
installed on a flap interconnecting strut, a ``target FAR'' signal 
cannot be detected when it reaches the mechanical end stop of the 
interconnecting strut. This proposed AD would require an inspection to 
determine the part number (P/N) of the interconnecting struts installed 
on the wings, identifying the P/N and the serial number (S/N) of the 
associated target and proximity sensor if applicable, and replacing or 
re-identifying the flap interconnecting strut if applicable. We are 
proposing

[[Page 58976]]

this AD to detect and correct a latent failure of the flap down drive 
disconnection due to an already-failed interconnecting strut sensor, 
which could result in asymmetric flap panel movement and consequent 
loss of control of the airplane.

DATES: We must receive comments on this proposed AD by November 12, 
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 service information identified in this proposed AD, contact 
Airbus, Airworthiness Office--EAS, 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 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: Sanjay Ralhan, Aerospace Engineer, 
International Branch, ANM-116, Transport Airplane Directorate, FAA, 
1601 Lind Avenue SW., Renton, Washington 98057-3356; telephone (425) 
227-1405; 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-2013-0791; 
Directorate Identifier 2012-NM-026-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 2012-0012, dated January 23, 2012 (referred to 
after this as ``the MCAI''), to correct an unsafe condition for the 
specified products. The MCAI states:

    The flap interconnecting strut is a safety device of the High 
Lift System which acts as an alternative load path from one flap 
surface to another in case of a flap drive system disconnection. In 
such a failure case, the installed proximity provide information to 
the slat flap control computer (SFCC) and the operation of the flap 
drive system is inhibited.
    A recent engineering investigation has shown that, when a 
certain combination of target/sensor serial number (s/n) is 
installed on a flap interconnecting strut, a ``target FAR'' signal 
cannot be detected when reaching the mechanical end stop of the 
interconnecting strut.
    This condition, if not corrected, could cause a flap down drive 
disconnection to remain undetected, due to an already-failed 
interconnecting strut sensor, potentially resulting in asymmetric 
flap panel movement and consequent loss of control of the aeroplane.
    For the reason described above, this [EASA] AD requires the 
identification and replacement [or re-identifying] of struts that 
have a certain target/sensor s/n combination installed.

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

Relevant Service Information

    Airbus has issued Service Bulletin A320-27-1206, Revision 01, dated 
October 10, 2011. 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.

Differences Between This AD and the MCAI or Service Information

    Although note 1 of the EASA Airworthiness Directive 2012-0012, 
dated January 23, 2012, allows flight for 50 flight cycles after the 
inspection of the flap down drive if an interconnecting strut cannot be 
replaced, this proposed AD does not include this exception.

Costs of Compliance

    We estimate that this proposed AD affects 755 airplanes of U.S. 
registry.
    We estimate the following costs to comply with this proposed AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                  Cost on U.S.
             Action                    Labor cost            Parts cost     Cost per  product      operators
----------------------------------------------------------------------------------------------------------------
Inspection and Re-               8 work-hours x $85 per  $0...............  $680 per           $513,400 per
 identification.                  hour = $680 per                            inspection cycle.  inspection
                                  inspection cycle.                                             cycle.
----------------------------------------------------------------------------------------------------------------


[[Page 58977]]

    We estimate the following costs to do any necessary replacements 
that would be required based on the results of the proposed inspection. 
We have no way of determining the number of aircraft that might need 
these replacements:

                                               On-condition Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                     Cost per
                    Action                                   Labor cost                Parts cost    product
---------------------------------------------------------------------------------------------------------------
Replacement..................................  10 work-hours x $85 per hour = $850..           $0         $850
----------------------------------------------------------------------------------------------------------------

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-2013-0791; Directorate Identifier 2012-NM-
026-AD.

(a) Comments Due Date

    We must receive comments by November 12, 2013.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to all Airbus Model A318-111, -112, -121, and -
122 airplanes; Model A319-111, -112, -113, -114, -115, -131, -132, 
and -133 airplanes; Model A320-111, -211, -212, -214, -231, -232, 
and -233 airplanes; and Model A321-111, -112, -131, -211, -212, -
213, -231, and -232 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 a report that an investigation showed 
that when a certain combination of a target/proximity sensor serial 
number is installed on a flap interconnecting strut, a ``target 
FAR'' signal cannot be detected when reaching the mechanical end 
stop of the interconnecting strut. We are issuing this AD to detect 
and correct a latent failure of the flap down drive disconnection 
due to an already-failed interconnecting strut sensor, which could 
result in asymmetric flap panel movement and consequent 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) Inspection To Determine the Part Number of the Interconnecting 
Struts

    Within 8,000 flight hours after the effective date of this AD, 
inspect to determine the part number of the interconnecting struts 
installed on both the left-hand (LH) and right-hand (RH) wings of 
the airplane, in accordance with the Accomplishment Instructions of 
Airbus Service Bulletin A320-27-1206, Revision 01, dated October 10, 
2011. A review of the airplane maintenance records is acceptable for 
determining the part number of the installed interconnecting struts, 
in lieu of the inspection, if the part number of the installed 
interconnecting struts, and the part number and the serial number of 
the associated target and proximity sensor, can be conclusively 
determined from that review.
    (1) Airplanes on which Airbus modification 27956 has been 
embodied in production, on which no interconnecting strut having a 
part number specified in figure 1 to paragraph (g) of this AD, and 
has been replaced since the airplane's first flight: No further work 
is required by paragraph (g) of this AD.
    (2) If, during the inspection required by paragraph (g) of this 
AD, any interconnecting strut is installed with a part number 
specified in figure 1 to paragraph (g) of this AD: Within 8,000 
flight hours after the effective date of this AD, determine the part 
number and the serial number of the associated target and proximity 
sensor.

Figure 1 to Paragraph (g) of This AD--Interconnecting Strut Part Numbers
------------------------------------------------------------------------
                   Interconnecting strut part numbers
-------------------------------------------------------------------------
D5757030500000
D5757030500100
D5757030500200
D5757030500600
D5757030500800
D5757030501000
D5757030501200
D5757032200000
------------------------------------------------------------------------

    (i) For airplanes having conditions specified in paragraphs 
(g)(2)(i)(A), (g)(2)(i)(B), (g)(2)(i)(C), and (g)(2)(i)(D) of this 
AD: Before further flight, replace the interconnecting strut with a 
serviceable unit, in accordance with the Accomplishment Instructions 
of Airbus Service Bulletin A320-

[[Page 58978]]

27-1206, Revision 01, dated October 10, 2011. For the purpose of 
this AD, a serviceable interconnecting strut is a unit which has 
been determined to be in compliance with the requirements of this 
AD.
    (A) A target part number (P/N) ABS0121-13 or P/N 8-536-01, and
    (B) A target serial number lower than 1600, or a target serial 
number that is unreadable, and
    (C) A proximity sensor having P/N ABS0121-31 or P/N 8-372-04, 
and
    (D) A proximity sensor having a serial number between C59198 and 
C59435, or a serial number (S/N) C500000 or higher.
    (ii) For a target having S/N 1600 or higher and target P/N 
ABS0121-13 or P/N 8-536-01: Within 8,000 flight hours after the 
effective date of this AD, re-identify the interconnecting strut, in 
accordance with the Accomplishment Instructions of Airbus Service 
Bulletin A320-27-1206, Revision 01, dated October 10, 2011.

(h) Parts Installation Prohibition

    As of the effective date of this AD, no person may install an 
interconnecting strut with a part number specified in figure 1 to 
paragraph (g) of this AD, on any airplane, except for parts 
identified in paragraph (g)(2)(ii) of this AD, provided that the 
actions in paragraph (g)(2)(ii) are done.

(i) Credit for Previous Actions

    This paragraph provides credit for the actions required by 
paragraph (g) of this AD, if those actions were performed before the 
effective date of this AD using Airbus Service Bulletin A320-27-
1206, dated January 28, 2011, and if additional work has been 
accomplished using Airbus Service Bulletin A320-27-1206, Revision 
01, dated October 10, 2011.

(j) Other FAA AD Provisions

    The following provisions also apply to this AD:
    (1) Alternative Methods of Compliance (AMOCs): The Manager, 
International Branch, ANM-116, 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: Sanjay Ralhan, Aerospace Engineer, 
International Branch, ANM-116, Transport Airplane Directorate, FAA, 
1601 Lind Avenue SW., Renton, Washington 98057-3356; telephone (425) 
227-1405; 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) 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.

 (k) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) EASA Airworthiness Directive 2012-0012, dated January 23, 
2012, for related information, which can be found in the AD docket 
on the Internet at http://www.regulations.gov.
    (2) For service information identified in this AD, contact 
Airbus, Airworthiness Office--EAS, 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 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 September 13, 2013.
Jeffrey E. Duven,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2013-23269 Filed 9-24-13; 8:45 am]
BILLING CODE 4910-13-P


