Document ID: FAA-2013-0791-0003
Agency: faa
Document Type: Rule
Title: Airworthiness Directives: Airbus Airplanes
Posted Date: 2014-02-19T05:00Z

[Federal Register Volume 79, Number 33 (Wednesday, February 19, 2014)]
[Rules and Regulations]
[Pages 9398-9400]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2014-02996]

[[Page 9398]]

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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; 
Amendment 39-17745; AD 2014-03-08]
RIN 2120-AA64

Airworthiness Directives; Airbus Airplanes

AGENCY: Federal Aviation Administration (FAA), Department of 
Transportation (DOT).

ACTION: Final rule.

-----------------------------------------------------------------------

SUMMARY: We are adopting a new airworthiness directive (AD) for all 
Airbus Model A318, A319, A320, and A321 series airplanes. 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 it reaches the mechanical end stop of the interconnecting 
strut. This AD requires an inspection to determine the part number of 
the interconnecting struts installed on the wings, identifying the part 
number and the serial number of the associated target and proximity 
sensor if applicable, and replacing or re-identifying the flap 
interconnecting strut if applicable. 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.

DATES: This AD becomes effective March 26, 2014.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of March 26, 
2014.

ADDRESSES: You may examine the AD docket on the Internet at http://www.regulations.gov/#!docketDetail;D=FAA-2013-0791; or in person at the 
Docket Management Facility, U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE., Washington, DC.
    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 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.

FOR FURTHER INFORMATION CONTACT: Sanjay Ralhan, Aerospace Engineer, 
International Branch, ANM 116, Transport Airplane Directorate, FAA, 
1601 Lind Avenue SW., Renton, WA 98057-3356; telephone (425) 227-1405; 
fax (425) 227-1149.

SUPPLEMENTARY INFORMATION:

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 by adding an AD that would apply to all Airbus Model A318, 
A319, A320, and A321 series airplanes. The NPRM published in the 
Federal Register on September 25, 2013 (78 FR 58975). The NPRM 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. The NPRM proposed to require an inspection to determine the part 
number of the interconnecting struts installed on the wings, 
identifying the part number and the serial number of the associated 
target and proximity sensor if applicable, and replacing or re-
identifying the flap interconnecting strut if applicable. 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.
    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 Mandatory Continuing Airworthiness Information, or 
``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 examine the MCAI in the AD docket on the Internet at http://www.regulations.gov/#!documentDetail;D=FAA-2013-0791-0002.

Comments

    We gave the public the opportunity to participate in developing 
this AD. We received no comments on the NPRM (78 FR 58975, September 
25, 2013) or on the determination of the cost to the public.

Conclusion

    We reviewed the relevant data and determined that air safety and 
the public interest require adopting this AD as proposed. We have 
determined that these minor changes:
     Are consistent with the intent that was proposed in the 
NPRM (78 FR 58975, September 25, 2013) for correcting the unsafe 
condition; and
     Do not add any additional burden upon the public than was 
already proposed in the NPRM (78 FR 58975, September 25, 2013).

Costs of Compliance

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

[[Page 9399]]

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

    We estimate the following costs to do any necessary replacements 
that would be required based on the results of the 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 AD will not have federalism implications 
under Executive Order 13132. This AD will 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 that this AD:
    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.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://www.regulations.gov/#!docketDetail;D=FAA-2013-0791; 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 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.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

Adoption of the Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA amends 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:

2014-03-08 Airbus: Amendment 39-17745. Docket No. FAA-2013-0791; 
Directorate Identifier 2012-NM-026-AD.

(a) Effective Date

    This airworthiness directive (AD) becomes effective March 26, 
2014.

(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

[[Page 9400]]

production, and on which no interconnecting strut has been replaced 
with a strut having a part number specified in figure 1 to paragraph 
(g) of this AD 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
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                   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 A320-27-1206, Revision 01, dated October 
10, 2011. For the purposes of this AD, a serviceable interconnecting 
strut is a unit which has been determined to be in compliance with 
the following 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. Airbus Service Bulletin A320-27-1206, 
dated January 28, 2011, is not incorporated by reference in this AD.

(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, 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: 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. This MCAI may be found in the AD 
docket on the Internet at http://www.regulations.gov/#!documentDetail;D=FAA-2013-0791-0002.
    (2) Service information identified in this AD that is not 
incorporated by reference may be viewed at the addresses specified 
in paragraphs (l)(3) and (l)(4) of this AD.

(l) Material Incorporated by Reference

    (1) The Director of the Federal Register approved the 
incorporation by reference (IBR) of the service information listed 
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
    (2) You must use this service information as applicable to do 
the actions required by this AD, unless this AD specifies otherwise.
    (i) Airbus Service Bulletin A320-27-1206, Revision 01, dated 
October 10, 2011.
    (ii) Reserved.
    (3) 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.
    (4) 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.
    (5) You may view this service information that is incorporated 
by reference at the National Archives and Records Administration 
(NARA). For information on the availability of this material at 
NARA, call 202-741-6030, or go to: http://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued in Renton, Washington, on January 22, 2014.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2014-02996 Filed 2-18-14; 8:45 am]
BILLING CODE 4910-13-P