Source: http://travelsdocbox.com/Air_Travel/97799263-Amendment-docket-no-faa-directorate-identifier-2011-nm-139-ad.html
Timestamp: 2019-10-18 22:16:56
Document Index: 702356461

Matched Legal Cases: ['art 51', 'art 39', 'art 39', 'art 39', 'art 39', 'ART 39', 'art 39']

Amendment Docket No. FAA ; Directorate Identifier 2011-NM-139-AD - PDF
Download "Amendment Docket No. FAA ; Directorate Identifier 2011-NM-139-AD"
Ilene Barber
1 Page AIRBUS Amendment Docket No. FAA ; Directorate Identifier 2011-NM-139-AD PREAMBLE (a) Effective Date This airworthiness directive (AD) becomes effective August 27, (b) Affected ADs None. (c) Applicability This AD applies to Airbus Model A and -121 airplanes; Model A , -112, -115, 132, and -133 airplanes; Model A , -232, and -233 airplanes; and Model A , -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 (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) ASNA located in the fuselage. If a nut having P/N ASNA is found, before further flight, do a detailed inspection for cracking of the nut, and all applicable related investigative and corrective actions, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A , Revision 01, AIRBUS
2 Page 2 including Appendices 01 and 02, dated June 17, If any cracking is found, before further flight, repair in accordance with the Accomplishment Instructions of Airbus Service Bulletin A , Revision 01, including Appendices 01 and 02, dated June 17, (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 A , 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 A , including Appendices 01 and 02, dated February 8, (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 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 ; phone: ; fax: Information may be ed to: 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 AIRBUS
3 Page 3 for this information collection is 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 R1, dated July 13, 2011; and Airbus Service Bulletin A , 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 A , Revision 01, including Appendices 01 and 02, dated June 17, (3) For service information identified in this AD, contact Airbus, Airworthiness Office-EAS, 1 Rond Point Maurice Bellonte, Blagnac Cedex, France; telephone ; fax ; Internet (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 (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 , or go to FOR FURTHER INFORMATION CONTACT: Sanjay Ralhan, Aerospace Engineer, International Branch, ANM-116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, Washington ; telephone (425) ; fax (425) Issued in Renton, Washington, on July 5, Kalene C. Yanamura, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service AIRBUS
4 [Federal Register Volume 77, Number 141 (Monday, July 23, 2012)] [Rules and Regulations] [Pages ] From the Federal Register Online via the Government Printing Office [ [FR Doc No: ] DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA ; Directorate Identifier 2011-NM-139-AD; Amendment ; AD ] 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 A and -121 airplanes; Model A , -112, -115, -132, and -133 airplanes; Model A , - 232, and -233 airplanes; and Model A , -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, The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of August 27, ADDRESSES: You may examine the AD docket on the Internet at 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 ; telephone (425) ; fax (425)
5 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 unsafe condition for the specified products. The MCAI states: During structural part assembly in Airbus production line, some nuts Part Number (P/N) ASNA 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 ASNA 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. 2
6 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 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 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) ) 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: 3
7 PART 39 AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: Authority: 49 U.S.C. 106(g), 40113, [Amended] 2. The FAA amends by adding the following new AD: 4