Airworthiness Directives; Airbus Airplanes, 42952-42954 [2012-17389]

Download as PDF 42952 Federal Register / Vol. 77, No. 141 / Monday, July 23, 2012 / Rules and Regulations (2) The controllability and maneuverability requirements of this part are met within a practical operational flight envelope (for example, speed, altitude, normal acceleration, and airplane configuration) that is described in the Airplane Flight Manual (AFM); and (3) The trim, stability, and stall characteristics are not impaired below a level needed to permit continued safe flight and landing. (B) In place of 14 CFR part 23, § 23.677 Trim systems requirement, comply with the following: SC 23.677 Load Alleviation Active Control Surface (a) Proper precautions must be taken to prevent inadvertent, improper, or abrupt Tamarack Active Control Surface (TACS) operation. (b) The load alleviation system must be designed so that, when any one connecting or transmitting element in the primary flight control system fails, adequate longitudinal control for safe flight and landing is available. (c) The load alleviation system must be irreversible unless the TACS is properly balanced and has no unsafe flutter characteristics. The system must have adequate rigidity and reliability in the portion of the system from the tab to the attachment of the irreversible unit to the airplane structure. (d) It must be demonstrated that the airplane is safely controllable and that the pilot can perform all maneuvers and operations necessary to effect a safe landing following any probable powered system runaway that reasonably might be expected in service, allowing for appropriate time delay after pilot recognition of the system runaway. The demonstration must be conducted at critical airplane weights and center of gravity positions. (C) In place of 14 CFR part 23, § 23.683 Operation tests requirement, comply with the following: mstockstill on DSK4VPTVN1PROD with RULES SC 23.683 Operation tests (a) It must be shown by operation tests that, when the load alleviation system is active and operational and loaded as prescribed in paragraph (b) of this section, the system is free from— (1) Jamming; (2) Excessive friction; and (3) Excessive deflection. (b) The prescribed test loads are, for the entire system, loads corresponding to the limit airloads on the appropriate surface. (D) In place of 14 CFR part 23, § 23.685 Control system details requirement, comply with the following: VerDate Mar<15>2010 16:44 Jul 20, 2012 Jkt 226001 SC 23.685 Control System Details (a) Each detail of the Tamarack Active Control Surface (TACS) must be designed and installed to prevent jamming, chafing, and interference from cargo, passengers, loose objects, or the freezing of moisture. (b) There must be means in the cockpit to prevent the entry of foreign objects into places where they would jam any one connecting or transmitting element of the system. (c) Each element of the load alleviation system must have design features, or must be distinctively and permanently marked, to minimize the possibility of incorrect assembly that could result in malfunctioning of the control system. (E) In place of 14 CFR part 23, § 23.697 Wing flap controls requirement, comply with the following: SC 23.697 Controls Load Alleviation System (a) The Tamarack Active Control Surface (TACS) must be designed so that, when the surface has been placed in any position, it will not move from that position unless the control is adjusted or is moved by the automatic operation of a load alleviation system. (b) The rate of movement of the TACS in response to the automatic device must give satisfactory flight and performance characteristics under steady or changing conditions of airspeed, engine power, and attitude. (F) In place of 14 CFR part 23, § 23.701 Flap interconnection requirement, comply with the following: SC 23.701 Load Alleviation System Interconnection (a) The load alleviation system and related movable surfaces as a system must— (1) Be synchronized by a mechanical interconnection between the movable surfaces; or by an approved equivalent means; or (2) Be designed so that the occurrence of any failure of the system that would result in an unsafe flight characteristic of the airplane is extremely improbable; or (b) The airplane must be shown to have safe flight characteristics with any combination of extreme positions of individual movable surfaces. Issued in Kansas City, Missouri, on July 13, 2013. Earl Lawrence, Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. 2012–17864 Filed 7–20–12; 8:45 am] BILLING CODE 4910–13–P PO 00000 Frm 00004 Fmt 4700 Sfmt 4700 DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2012–0329; Directorate Identifier 2011–NM–139–AD; Amendment 39–17127; AD 2012–14–13] RIN 2120–AA64 Airworthiness Directives; Airbus Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: We are adopting a new airworthiness directive (AD) for certain Airbus Model A318–112 and –121 airplanes; Model A319–111, –112, –115, –132, and –133 airplanes; Model A320– 214, –232, and –233 airplanes; and Model A321–211, –212, –213, and –231 airplanes. This AD was prompted by reports of some fuselage nuts found cracked. This AD requires an inspection to determine if certain fuselage nuts are installed, a detailed inspection for cracking of fuselage nuts having a certain part number, and related investigative and corrective actions if necessary. We are issuing this AD to detect and correct fuselage nuts found cracked, which could result in reduced structural integrity of the airplane. DATES: This AD becomes effective August 27, 2012. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of August 27, 2012. ADDRESSES: You may examine the AD docket on the Internet at http:// www.regulations.gov or in person at the U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC. 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: SUMMARY: Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to include an AD that would apply to the specified products. That NPRM was published in the Federal Register on April 2, 2012 (77 FR 19567). That NPRM proposed to correct an E:\FR\FM\23JYR1.SGM 23JYR1 Federal Register / Vol. 77, No. 141 / Monday, July 23, 2012 / Rules and Regulations Authority for This Rulemaking unsafe condition for the specified products. The MCAI states: During structural part assembly in Airbus production line, some nuts Part Number (P/ N) ASNA2531–4 were found cracked. Investigations were performed to determine the batches of the affected nuts and had revealed that these nuts have been installed in production on the fuselage of aeroplanes listed in the applicability section of this [EASA] AD. Static, fatigue and corrosion tests were performed, which demonstrated that no immediate maintenance action is necessary. However, a large number of these nuts are fitted on primary structural elements, which could have long-term consequences. This condition, if not corrected, could impair the structural integrity of the affected aeroplanes. For the reasons described above, this [EASA] AD requires [an inspection to determine if certain fuselage nuts are installed,] a detailed inspection [for cracking] of the affected nuts, associated corrective actions, [general visual inspection for scratching of the hole if necessary] depending on findings, and replacement of the affected P/N ASNA2531–4 nuts with new ones, having the same P/N. * * * * * Required actions include related investigative and corrective actions if necessary. Related investigative actions include a general visual inspection for scratching of the hole. Corrective actions include replacing the fastener and installing a new fuselage nut. You may obtain further information by examining the MCAI in the AD docket. Comments We gave the public the opportunity to participate in developing this AD. We received no comments on the NPRM (77 FR 19567, April 2, 2012) or on the determination of the cost to the public. mstockstill on DSK4VPTVN1PROD with RULES Conclusion We reviewed the available data and determined that air safety and the public interest require adopting the AD as proposed. Costs of Compliance We estimate that this AD will affect 152 products of U.S. registry. We also estimate that it will take about 15 workhours per product to comply with the basic requirements of this AD. The average labor rate is $85 per work-hour. Based on these figures, we estimate the cost of this AD to the U.S. operators to be $193,800, or $1,275 per product. In addition, we estimate that any necessary follow-on actions would take about 10 work-hours and require parts costing $362, for a cost of $1,212 per product. We have no way of determining the number of products that may need these actions. VerDate Mar<15>2010 16:44 Jul 20, 2012 Jkt 226001 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. We prepared a regulatory evaluation of the estimated costs to comply with this AD and placed it in the AD docket. 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 the NPRM (77 FR 19567, April 2, 2012), 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. PO 00000 Frm 00005 Fmt 4700 Sfmt 4700 42953 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 1. The authority citation for part 39 continues to read as follows: ■ Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The FAA amends § 39.13 by adding the following new AD: ■ 2012–14–13 Airbus: Amendment 39–17127. Docket No. FAA–2012–0329; Directorate Identifier 2011–NM–139–AD. (a) Effective Date This airworthiness directive (AD) becomes effective August 27, 2012. (b) Affected ADs None. (c) Applicability This AD applies to Airbus Model A318– 112 and –121 airplanes; Model A319–111, –112, –115, –132, and –133 airplanes; Model A320–214, –232, and –233 airplanes; and Model A321–211, –212, –213, and –231 airplanes; certificated in any category; manufacturer serial numbers 3339, 3340, 3350, 3355, 3360, 3367, 3369, 3372, 3380, 3382, 3385, 3387, 3388, 3390, 3393, 3395, 3397 through 3508 inclusive, 3510 through 3519 inclusive, 3522, 3523, 3525, 3527, 3529, 3530, 3537, 3539, 3542, 3544, 3546, 3548, 3552, and 3555. (d) Subject Air Transport Association (ATA) of America Code 53: Fuselage. (e) Reason This AD was prompted by reports of fuselage nuts found cracked. We are issuing this AD to detect and correct fuselage nuts found cracked, which could result in reduced structural integrity 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 and Replacement Within 72 months since first flight of the airplane or within 90 days after the effective date of this AD, whichever occurs later, do an inspection for nuts having part number (P/ N) ASNA2531–4 located in the fuselage. If a nut having P/N ASNA2531–4 is found, before further flight, do a detailed inspection for cracking of the nut, and all applicable related investigative and corrective actions, in E:\FR\FM\23JYR1.SGM 23JYR1 42954 Federal Register / Vol. 77, No. 141 / Monday, July 23, 2012 / Rules and Regulations accordance with the Accomplishment Instructions of Airbus Service Bulletin A320– 53–1218, Revision 01, including Appendices 01 and 02, dated June 17, 2010. If any cracking is found, before further flight, repair in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320– 53–1218, Revision 01, including Appendices 01 and 02, dated June 17, 2010. (h) Reporting Submit a report of the findings of the inspection required by paragraph (g) of this AD to Airbus in accordance with Appendix 01 of Airbus Service Bulletin A320–53–1218, Revision 01, including Appendices 01 and 02, dated June 17, 2010, at the applicable time specified in paragraph (h)(1) or (h)(2) of this AD. (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. mstockstill on DSK4VPTVN1PROD with RULES (i) Credit for Previous Actions This paragraph provides credit for inspections and replacements required by paragraph (g) of this AD, if those actions were performed before the effective date of this AD using Airbus Service Bulletin A320–53–1218, including Appendices 01 and 02, dated February 8, 2010. (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; phone: 425–227–1405; fax: 425–227– 1149. Information may be emailed to: 9ANM-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. (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 VerDate Mar<15>2010 16:44 Jul 20, 2012 Jkt 226001 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. DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2012–0730; Directorate Identifier 2012–SW–048–AD; Amendment 39–17124; AD 2012–14–10] RIN 2120–AA64 Airworthiness Directives; Boeing Vertol (Type Certificate Currently Held by Columbia Helicopters, Inc. (CHI)) and Kawasaki Heavy Industries, Limited Helicopters (Kawasaki) (k) Related Information Refer to MCAI European Aviation Safety Agency Airworthiness Directive 2011– 0120R1, dated July 13, 2011; and Airbus Service Bulletin A320–53–1218, Revision 01, including Appendices 01 and 02, dated June 17, 2010; for related information. Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule; request for comments. SUMMARY: (l) Material Incorporated by Reference (1) The Director of the Federal Register approved the incorporation by reference (IBR) of the following service information under 5 U.S.C. 552(a) and 1 CFR part 51. (2) You must use the following service information to do the actions required by this AD, unless the AD specifies otherwise. (i) Airbus Service Bulletin A320–53–1218, Revision 01, including Appendices 01 and 02, dated June 17, 2010. (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 review copies of the service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, Washington. For information on the availability of this material at the FAA, call 425–227–1221. (5) You may also review copies of the service information that is incorporated by reference at the National Archives and Records Administration (NARA). For information on the availability of this material at an NARA facility, call 202–741– 6030, or go to http://www.archives.gov/ federal_register/code_of_federal_regulations/ ibr_locations.html. Issued in Renton, Washington, on July 5, 2012. Kalene C. Yanamura, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2012–17389 Filed 7–20–12; 8:45 am] BILLING CODE 4910–13–P PO 00000 Frm 00006 Fmt 4700 Sfmt 4700 AGENCY: We are adopting a new airworthiness directive (AD) for CHI Model 107–II and Kawasaki Model KV107–II and KV107–IIA helicopters. This AD requires, before further flight, replacing certain upper collective pitch control yoke bolts. This AD is prompted by three failures of the affected bolts. These actions are intended to prevent failure of an upper collective pitch control yoke bolt (bolt), excessive vibration, migration of the shafts, and subsequent loss of control of the helicopter. This AD becomes effective August 7, 2012. We must receive comments on this AD by September 21, 2012. ADDRESSES: You may send comments by any of the following methods: • Federal eRulemaking Docket: Go to http://www.regulations.gov. Follow the online instructions for sending your comments electronically. • Fax: 202–493–2251. • Mail: Send comments to the U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC 20590–0001. • Hand Delivery: Deliver to the ‘‘Mail’’ address between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. DATES: 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 AD, the economic evaluation, any comments received, and other information. The street address for E:\FR\FM\23JYR1.SGM 23JYR1

Agencies

[Federal Register Volume 77, Number 141 (Monday, July 23, 2012)]
[Rules and Regulations]
[Pages 42952-42954]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2012-17389]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2012-0329; Directorate Identifier 2011-NM-139-AD; 
Amendment 39-17127; AD 2012-14-13]
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 certain 
Airbus Model A318-112 and -121 airplanes; Model A319-111, -112, -115, -
132, and -133 airplanes; Model A320-214, -232, and -233 airplanes; and 
Model A321-211, -212, -213, and -231 airplanes. This AD was prompted by 
reports of some fuselage nuts found cracked. This AD requires an 
inspection to determine if certain fuselage nuts are installed, a 
detailed inspection for cracking of fuselage nuts having a certain part 
number, and related investigative and corrective actions if necessary. 
We are issuing this AD to detect and correct fuselage nuts found 
cracked, which could result in reduced structural integrity of the 
airplane.

DATES: This AD becomes effective August 27, 2012.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of August 27, 
2012.

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

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:

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 to include an AD that would apply to the specified products. 
That NPRM was published in the Federal Register on April 2, 2012 (77 FR 
19567). That NPRM proposed to correct an

[[Page 42953]]

unsafe condition for the specified products. The MCAI states:

    During structural part assembly in Airbus production line, some 
nuts Part Number (P/N) ASNA2531-4 were found cracked. Investigations 
were performed to determine the batches of the affected nuts and had 
revealed that these nuts have been installed in production on the 
fuselage of aeroplanes listed in the applicability section of this 
[EASA] AD.
    Static, fatigue and corrosion tests were performed, which 
demonstrated that no immediate maintenance action is necessary. 
However, a large number of these nuts are fitted on primary 
structural elements, which could have long-term consequences.
    This condition, if not corrected, could impair the structural 
integrity of the affected aeroplanes.
    For the reasons described above, this [EASA] AD requires [an 
inspection to determine if certain fuselage nuts are installed,] a 
detailed inspection [for cracking] of the affected nuts, associated 
corrective actions, [general visual inspection for scratching of the 
hole if necessary] depending on findings, and replacement of the 
affected P/N ASNA2531-4 nuts with new ones, having the same P/N.
* * * * *
Required actions include related investigative and corrective actions 
if necessary. Related investigative actions include a general visual 
inspection for scratching of the hole. Corrective actions include 
replacing the fastener and installing a new fuselage nut. You may 
obtain further information by examining the MCAI in the AD docket.

Comments

    We gave the public the opportunity to participate in developing 
this AD. We received no comments on the NPRM (77 FR 19567, April 2, 
2012) or on the determination of the cost to the public.

Conclusion

    We reviewed the available data and determined that air safety and 
the public interest require adopting the AD as proposed.

Costs of Compliance

    We estimate that this AD will affect 152 products of U.S. registry. 
We also estimate that it will take about 15 work-hours per product to 
comply with the basic requirements of this AD. The average labor rate 
is $85 per work-hour. Based on these figures, we estimate the cost of 
this AD to the U.S. operators to be $193,800, or $1,275 per product.
    In addition, we estimate that any necessary follow-on actions would 
take about 10 work-hours and require parts costing $362, for a cost of 
$1,212 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 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.
    We prepared a regulatory evaluation of the estimated costs to 
comply with this AD and placed it in the AD docket.

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 the NPRM (77 FR 19567, April 2, 2012), 
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.

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:

2012-14-13 Airbus: Amendment 39-17127. Docket No. FAA-2012-0329; 
Directorate Identifier 2011-NM-139-AD.

(a) Effective Date

    This airworthiness directive (AD) becomes effective August 27, 
2012.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to Airbus Model A318-112 and -121 airplanes; 
Model A319-111, -112, -115, -132, and -133 airplanes; Model A320-
214, -232, and -233 airplanes; and Model A321-211, -212, -213, and -
231 airplanes; certificated in any category; manufacturer serial 
numbers 3339, 3340, 3350, 3355, 3360, 3367, 3369, 3372, 3380, 3382, 
3385, 3387, 3388, 3390, 3393, 3395, 3397 through 3508 inclusive, 
3510 through 3519 inclusive, 3522, 3523, 3525, 3527, 3529, 3530, 
3537, 3539, 3542, 3544, 3546, 3548, 3552, and 3555.

(d) Subject

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

(e) Reason

    This AD was prompted by reports of fuselage nuts found cracked. 
We are issuing this AD to detect and correct fuselage nuts found 
cracked, which could result in reduced structural integrity 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 and Replacement

    Within 72 months since first flight of the airplane or within 90 
days after the effective date of this AD, whichever occurs later, do 
an inspection for nuts having part number (P/N) ASNA2531-4 located 
in the fuselage. If a nut having P/N ASNA2531-4 is found, before 
further flight, do a detailed inspection for cracking of the nut, 
and all applicable related investigative and corrective actions, in

[[Page 42954]]

accordance with the Accomplishment Instructions of Airbus Service 
Bulletin A320-53-1218, Revision 01, including Appendices 01 and 02, 
dated June 17, 2010. If any cracking is found, before further 
flight, repair in accordance with the Accomplishment Instructions of 
Airbus Service Bulletin A320-53-1218, Revision 01, including 
Appendices 01 and 02, dated June 17, 2010.

(h) Reporting

    Submit a report of the findings of the inspection required by 
paragraph (g) of this AD to Airbus in accordance with Appendix 01 of 
Airbus Service Bulletin A320-53-1218, Revision 01, including 
Appendices 01 and 02, dated June 17, 2010, at the applicable time 
specified in paragraph (h)(1) or (h)(2) of this AD.
    (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.

(i) Credit for Previous Actions

    This paragraph provides credit for inspections and replacements 
required by paragraph (g) of this AD, if those actions were 
performed before the effective date of this AD using Airbus Service 
Bulletin A320-53-1218, including Appendices 01 and 02, dated 
February 8, 2010.

(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; phone: 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.
    (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.

(k) Related Information

    Refer to MCAI European Aviation Safety Agency Airworthiness 
Directive 2011-0120R1, dated July 13, 2011; and Airbus Service 
Bulletin A320-53-1218, Revision 01, including Appendices 01 and 02, 
dated June 17, 2010; for related information.

(l) Material Incorporated by Reference

    (1) The Director of the Federal Register approved the 
incorporation by reference (IBR) of the following service 
information under 5 U.S.C. 552(a) and 1 CFR part 51.
    (2) You must use the following service information to do the 
actions required by this AD, unless the AD specifies otherwise.
    (i) Airbus Service Bulletin A320-53-1218, Revision 01, including 
Appendices 01 and 02, dated June 17, 2010.
    (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 review copies of the service information at the FAA, 
Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, 
Washington. For information on the availability of this material at 
the FAA, call 425-227-1221.
    (5) You may also review copies of the service information that 
is incorporated by reference at the National Archives and Records 
Administration (NARA). For information on the availability of this 
material at an NARA facility, call 202-741-6030, or go to http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html.

    Issued in Renton, Washington, on July 5, 2012.
Kalene C. Yanamura,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2012-17389 Filed 7-20-12; 8:45 am]
BILLING CODE 4910-13-P