80 FR 72569 - Airworthiness Directives; Airbus Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 80, Issue 224 (November 20, 2015)
Federal Aviation Administration
Federal Register Volume 80, Issue 224 (November 20, 2015)
| Page Range | 72569-72573 | |
| FR Document | 2015-28895 |
[Federal Register Volume 80, Number 224 (Friday, November 20, 2015)] [Rules and Regulations] [Pages 72569-72573] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2015-28895] ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2014-1043; Directorate Identifier 2013-NM-079-AD; Amendment 39-18321; AD 2015-23-05] 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 A330-200, A330-200 Freighter, and A330-300 series airplanes; and Model A340-200 and A340-300 series airplanes. This AD was prompted by reports of cracked support strut body ends at a certain frame location of the trimmable horizontal stabilizer (THS). This AD requires repetitive inspections for cracking of the strut ends of the THS support located at a certain frame in the tail cone, and replacement if necessary; and reinstallation or installation of reinforcing clamps on certain strut ends. We are issuing this AD to detect and correct cracked support strut body ends of the THS, which could lead to the loss of all four THS support struts, making the remaining structure unable to carry limit loads, resulting in the loss of the horizontal tail plane. DATES: This AD becomes effective December 28, 2015. The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of December 28, 2015. ADDRESSES: You may examine the AD docket on the Internet at http://www.regulations.gov/#!docketDetail;D=FAA-2014-1043 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 SAS, Airworthiness Office--EAL, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 45 80; email [email protected]; 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. It is also available on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2014- 1043. FOR FURTHER INFORMATION CONTACT: Vladimir Ulyanov, Aerospace Engineer, International Branch, ANM-116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057-3356; telephone 425-227-1138; 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 A330-200, A330-200 Freighter, and A330-300 series airplanes; and Model A340-200 and A340-300 series airplanes. The NPRM published in the Federal Register on January 23, 2015 (80 FR 3510). The NPRM was prompted by reports of cracked support strut body ends at a certain frame location of the THS. The NPRM proposed to require repetitive inspections for cracking of the strut ends of the THS support located at a certain frame in the tail cone, and replacement if necessary; and reinstallation or installation of reinforcing clamps on certain strut ends. We are issuing this AD to detect and correct cracked support strut body ends of the THS, which could lead to the loss of all four THS support struts, making the remaining structure unable to carry limit loads, resulting in the loss of the horizontal tail plane. The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, has issued EASA Airworthiness Directive 2014-0068, dated March 18, 2014 (referred to after this as the Mandatory Continuing Airworthiness Information, or ``the MCAI''), to correct an unsafe condition for all Airbus Model A330-200, A330-200 Freighter, and A330-300 series airplanes; and Model A340-200 and A340-300 series airplanes. The MCAI states: During scheduled maintenance on A330 aeroplanes, several Trimmable Horizontal Stabilizer (THS) support struts at frame (FR) 91 were found cracked at strut body ends. The THS is supported and articulated at FR 91 by four struts to fix the hinges (Y-bolts) and keep the structural integrity in lateral direction. Analysis revealed that cracks can reduce ability of the support struts to carry specified tension loads. This condition, if not detected and corrected, could lead to the loss of all four [[Page 72570]] THS support struts at FR91, which would make the remaining structure unable to carry limit loads, resulting in the loss of Horizontal Tail Plane. A340-500/600 aeroplanes are not affected by this [EASA] AD as different material is used on THS support struts. To address this potentially unsafe condition, EASA issued AD 2013-0076 [http://ad.easa.europa.eu/blob/easa_ad_2013_0076_superseded.pdf/AD_2013-0076_1] to require repetitive special detailed inspections [high frequency eddy current (HFEC) inspections for cracking] of all 8 strut ends of the THS support located at FR91 in the tail cone and, depending on findings, replacement of THS support struts. That [EASA] AD also required, for aeroplanes on which Airbus Modification 203493 had not been embodied in production, or Airbus Service Bulletin (SB) A330-53-3204 or SB A340-53-4199, as applicable, has not been embodied in service, the installation of a clamping device on each support strut end to stop growth of possible cracks (crack stopper function) in order to secure integrity of the struts. Since issuance of EASA AD 2013-0076 [http://ad.easa.europa.eu/blob/easa_ad_2013_0076_superseded.pdf/AD_2013-0076_1], it has been discovered that several aeroplanes are fitted with another strut configuration (SARMA Strut) [Societ[eacute] Anonyme de Recherche M[eacute]canique Appliqu[eacute]e] than the TAC (Technical Airborne Components Industries) strut, which caused the other strut not to be considered. Consequently, Airbus revised Airbus SB A330-53-3206 and SB A340-53-4208, accordingly in order to add a one-time [HFEC] inspection [for cracking] for SARMA struts and in case of finding to replace it with a TAC strut and thereafter to accomplish repetitive inspections and EASA issued AD 2013-0219 [http://ad.easa.europa.eu/blob/easa_ad_2013_0219_superseded.pdf/AD_2013-0219_1], which is superseded, and required accomplishment of the instructions as specified in the latest revision of each SB, as applicable. Since issuance of EASA AD 2013-0219 [http://ad.easa.europa.eu/blob/easa_ad_2013_0219_superseded.pdf/AD_2013-0219_1], based on the reporting received from operators, it has been determined that repetitive inspections are also to be accomplished for aeroplanes equipped with SARMA strut. Airbus introduced that inspection in the applicable SB at revision 3. For the reasons described above, this [EASA] AD retains the requirements of EASA AD 2013-0219, which is superseded, and requires accomplishment of repetitive [HFEC] inspective inspection [for cracking] for aeroplanes equipped with SARMA strut. This [EASA] AD is considered as an interim action, pending the development of a terminating action. You may examine the MCAI in the AD docket on the Internet at http://www.regulations.gov/#!documentDetail;D=FAA-2014-1043-0002. Comments We gave the public the opportunity to participate in developing this AD. The following presents the comments received on the NPRM (80 FR 3510, January 23, 2015) and the FAA's response to each comment. Request To Add Inspection for Identifying Struts Delta Air Lines, Inc. (DAL) requested that we add a physical inspection to paragraph (g) of the proposed AD (80 FR 3510, January 23, 2015) to distinguish a Societ[eacute] Anonyme de Recherche M[eacute]canique Appliqu[eacute]e (SARMA) strut from a Technical Airborne Components Industries (TAC) strut. DAL stated that paragraph (g) of the proposed AD only identifies the dimensional diameter of SARMA struts; however, DAL stated that both TAC and SARMA struts have the same manufacturer part numbers but have different rod end diameters. DAL suggested language for doing a physical inspection of the strut end of each support strut for identification purposes. We agree that a physical inspection is necessary to determine the rod end diameter in order to distinguish between SARMA and TAC struts. However, that inspection is optional. Paragraph (g) of this AD defines SARMA struts as having a diameter that is less than 43 millimeters, and states that all other struts are TAC struts. Paragraph (h) of this AD requires inspecting TAC struts. Thus, operators must inspect all struts unless the strut is inspected to determine the diameter is less than 43 millimeters, i.e., it is a SARMA strut. We have not changed this AD in this regard. Request To Include Airbus Modification 203834 for Installing Reinforced Clamps DAL requested that we revise paragraph (h) of the proposed AD (80 FR 3510, January 23, 2015) to include Airbus Modification 203834 as an optional modification for installation of the reinforced clamps. DAL stated that Airbus has confirmed that Airbus Modification 203834 installs the same reinforced clamps as Airbus Modification 203493 specified in paragraph (h) of the proposed AD. We agree with the commenter's request. The FAA has approved two Airbus modifications for installing the reinforced clamps into production airplanes: Modification 203493 for airplanes having manufacturer serial number (MSN) 1466 to 1509 inclusive, and Modification 203834 for airplanes having MSN 1510 and on. Modification 203834 supersedes Modification 203493, and the first airplane delivered with Modification 203834 installed was MSN 1511. Thus, operators may have the two populations of airplanes: Those with Modification 203834 and those with Modification 203493. This AD must address both groups of airplanes accordingly. We have revised paragraph (h) of this AD to specify that, for airplanes on which Airbus Modification 203493 or 203834 has been embodied in production; or on which Airbus Service Bulletin A330-53-3204 or Airbus Service Bulletin A340 53-4199, as applicable; has been embodied in service, remove the clamp from each strut end before accomplishing the inspections required by paragraph (h) of this AD. Request To Include Additional Service Information DAL requested that we revise paragraphs (j)(1), (j)(2), and (l) of the proposed AD (80 FR 3510, January 23, 2015) to include Airbus Service Bulletin A330-53-3204. DAL stated that, when clamps were not previously installed, Airbus Service Bulletin A330-53-3204 becomes the source document for installing the clamps. We agree that Airbus Service Bulletin A330-53-3204, Revision 03, dated February 28, 2014, is an appropriate source of service information for installing clamps. However, we do not agree to revise this AD because that service information is already referenced in Airbus Service Bulletin A330-53-3206, Revision 03, dated February 28, 2014, which is referred to as one of the appropriate sources of service information for the actions required by paragraphs (j)(1), (j)(2), and (l) of this AD. As specified in the Accomplishment Instructions of Airbus Service Bulletin A330-53-3206, Revision 03, dated February 28, 2014., ``if no clamps were previously installed, accomplish Service Bulletin A330-53-3204 before next flight, to install them.'' Therefore, no change to this AD is necessary in this regard. Request To Clarify Flight With Cracking DAL requested that we clarify/confirm that the NPRM (80 FR 3510, January 23, 2015) will apply more strict replacement criteria when cracks are found than what is currently published in Airbus Service Bulletin A330-53-3206, Revision 03, dated February 28, 2014. DAL stated that Subtask 533206-280-201-001 of Airbus Service Bulletin A330-53- 3206, Revision 03, dated February 28, 2014, contains instructions [[Page 72571]] to allow continued operation of the airplane with small crack findings without immediate strut replacement. We agree. In the ``Differences Between this Proposed AD and the MCAI or Service Information'' section of the NPRM (80 FR 3510, January 23, 2015), we stated that ``Although EASA Airworthiness Directive 2014- 0068, dated March 18, 2014, Airbus Service Bulletin A330-53-3206, Revision 03, dated February 28, 2014, and Airbus Service Bulletin A340- 53-4208, Revision 03, dated February 28, 2014, allow further flight after certain cracks are found during compliance with the proposed action, paragraph (j)(2) of this AD would require that any cracked THS support strut be replaced with a new or serviceable TAC strut before further flight.'' No change to this AD is necessary in this regard. Conclusion We reviewed the relevant data, considered the comments received, and determined that air safety and the public interest require adopting this AD with the changes described previously and minor editorial changes. We have determined that these minor changes:Are consistent with the intent that was proposed in the NPRM (80 FR 3510, January 23, 2015) for correcting the unsafe condition; and Do not add any additional burden upon the public than was already proposed in the NPRM (80 FR 3510, January 23, 2015). We also determined that these changes will not increase the economic burden on any operator or increase the scope of this AD. Interim Action We consider this AD interim action. If final action is later identified, we might consider further rulemaking then. Related Service Information Under 1 CFR Part 51 We reviewed the following service information. Airbus Service Bulletin A330-53-3206, Revision 03, dated February 28, 2014. This service information describes procedures for inspections for cracking of the strut ends of the THS support located in the airplane tail cone. Airbus Service Bulletin A340-53-4208, Revision 03, dated February 28, 2014. This service information describes procedures for inspections for cracking of the strut ends of the THS support located in the airplane tail cone. This service information is reasonably available because the interested parties have access to it through their normal course of business or by the means identified in the ADDRESSES section of this AD. Costs of Compliance We estimate that this AD affects 84 airplanes of U.S. registry. We also estimate that it will take about 9 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 on U.S. operators to be $64,260, or $765 per product. We have received no definitive data that would enable us to provide cost estimates for the on-condition replacement specified in this AD. We estimate that any necessary follow-on strut reinforcements will take about 2 work-hours and require parts costing $5,680, for a cost of $5,850 per product. We have no way of determining the number of aircraft that might need this action. According to the manufacturer, some of the costs of this AD may be covered under warranty, thereby reducing the cost impact on affected individuals. We do not control warranty coverage for affected individuals. As a result, we have included all costs in our cost estimate. 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-2014-1043; 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 airworthiness directive (AD): 2015-23-05 Airbus: Amendment 39-18321. Docket No. FAA-2014-1043; Directorate Identifier 2013-NM-079-AD. (a) Effective Date This AD becomes effective December 28, 2015. (b) Affected ADs None. (c) Applicability This AD applies to the airplanes identified in paragraphs (c)(1), (c)(2), and (c)(3) of this AD, certificated in any category, all manufacturer serial numbers. (1) Airbus Model A330-201, -202, -203, -223, -223F, -243, and - 243F airplanes. [[Page 72572]] (2) Airbus Model A330-301, -302, -303, -321, -322, -323, -341, - 342, and -343 airplanes. (3) Airbus Model A340-211, -212, -213, -311, -312, and -313 airplanes. (d) Subject Air Transport Association (ATA) of America Code 53, Fuselage. (e) Reason This AD was prompted by reports of cracked support strut body ends at a certain frame location of the trimmable horizontal stabilizer (THS). We are issuing this AD to detect and correct cracked support strut body ends of the THS, which could lead to the loss of all four THS support struts and which would make the remaining structure unable to carry limit loads, resulting in the loss of the horizontal tail plane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Definition of Strut Types For the purpose of this AD, a Societ[eacute] Anonyme de Recherche M[eacute]canique Appliqu[eacute]e (SARMA) strut is a strut on which the diameter of the strut end is less than 43 millimeters. All other struts are Technical Airborne Components Industries (TAC) struts. (h) Repetitive Inspections of TAC Strut Ends At the applicable time specified in paragraph (i) of this AD, do a high frequency eddy current (HFEC) inspection for cracking of all TAC strut ends of the THS support located at frame (FR) 91 in the tail cone, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A330-53-3206, Revision 03, dated February 28, 2014; or Airbus Service Bulletin A340-53-4208, Revision 03, dated February 28, 2014; as applicable. Repeat the inspection thereafter at intervals not to exceed 42 months or 20,000 flight hours, whichever occurs first. For airplanes on which Airbus Modification 203493 or 203834 has been embodied in production, or Airbus Service Bulletin A330-53-3204 or Airbus Service Bulletin A340-53-4199, as applicable, has been embodied in service, remove the clamp from each strut end before accomplishing the inspections required by this paragraph. (i) Compliance Times for the Actions Required by Paragraphs (h) and (k) of This AD Do the inspections required by paragraphs (h) and (k) of this AD at the applicable times specified in paragraphs (i)(1), (i)(2), and (i)(3) of this AD. (1) For Model A330 series airplanes having manufacturer serial numbers 012 through 209 inclusive, and Model A340 series airplanes having manufacturer serial numbers 002 through 210 inclusive: Within 6 months after the effective date of this AD. (2) For Model A330 series airplanes having manufacturer serial numbers 211 through 422 inclusive, and Model A340 series airplanes having manufacturer serial numbers 212 through 447 inclusive: Within 24 months after the effective date of this AD. (3) For Model A330 series airplanes having manufacturer serial numbers 423 and subsequent, and Model A340 series airplanes having manufacturer serial numbers 450 through 955 inclusive: Within 36 months after the effective date of this AD or since the first flight of the airplane, whichever occurs later. (j) Corrective Action for TAC Strut Ends and Installation of Reinforcing Clamps (1) If, during any inspection required by paragraph (h) of this AD, no cracks are found: Before further flight, reinstall or install, as applicable, reinforcing clamps on the strut ends, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A330-53-3206, Revision 03, dated February 28, 2014; or Airbus Service Bulletin A340-53-4208, Revision 03, dated February 28, 2014; as applicable. (2) If, during any inspection required by paragraph (h) of this AD, any crack is found: Before further flight, replace any affected strut with a new or serviceable TAC strut and install reinforcing clamps on the strut end, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A330-53-3206, Revision 03, dated February 28, 2014; or Airbus Service Bulletin A340-53-4208, Revision 03, dated February 28, 2014; as applicable. (k) Repetitive Inspections of SARMA Strut Ends At the applicable time specified in paragraph (i) of this AD, do an HFEC inspection for cracking of all SARMA strut ends of the THS support located at FR 91 in the tail cone, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A330-53-3206, Revision 03, dated February 28, 2014; or Airbus Service Bulletin A340-53-4208, Revision 03, dated February 28, 2014; as applicable. Repeat the inspection thereafter at intervals not to exceed 12 months. (l) Corrective Action for SARMA Strut Ends If any crack is found on a strut end during the inspection required by paragraph (k) of this AD: Before further flight, replace any affected SARMA strut with a new or serviceable TAC strut and install reinforcing clamps on the strut end, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A330-53-3206, Revision 03, dated February 28, 2014; or Airbus Service Bulletin A340-53-4208, Revision 03, dated February 28, 2014; as applicable. (m) No Terminating Action Replacement of THS struts on an airplane does not constitute terminating action for the repetitive inspections required by this AD. (n) No Reporting Although Airbus Service Bulletin A330-53-3206, Revision 03, dated February 28, 2014; and Airbus Service Bulletin A340-53-4208, Revision 03, dated February 28, 2014; specify to submit certain information to the manufacturer, this AD does not include that requirement. (o) Credit for Previous Actions This paragraph provides credit for actions required by paragraphs (g), (h), (j), and (k) of this AD, if those actions were performed before the effective date of this AD using any of the service information identified in paragraphs (n)(1) through (n)(6) of this AD. This service information is not incorporated by reference in this AD. (1) Airbus Service Bulletin A330-53-3206, dated February 7, 2013. (2) Airbus Service Bulletin A330-53-3206, Revision 01, dated June 10, 2013. (3) Airbus Service Bulletin A330-53-3206, Revision 02, dated August 8, 2013. (4) Airbus Service Bulletin A340-53-4208, dated February 7, 2013. (5) Airbus Service Bulletin A340-53-4208, Revision 01, dated June 10, 2013. (6) Airbus Service Bulletin A340-53-4208, Revision 02, dated August 8, 2013. (p) 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: Vladimir Ulyanov, Aerospace Engineer, International Branch, ANM-116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057-3356; telephone 425-227-1138; fax 425-227-1149. Information may be emailed to: [email protected]. 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. (q) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA Airworthiness Directive 2014-0068, dated March 18, 2014, for related information. This MCAI may be found in the AD docket on the Internet at http://www.regulations.gov/#!documentDetail;D=FAA- 2014-1043-0002. (2) Service information identified in this AD that is not incorporated by reference is available at the addresses specified in paragraphs (r)(3) and (r)(4) of this AD. (r) 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. [[Page 72573]] (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 A330-53-3206, Revision 03, dated February 28, 2014. (ii) Airbus Service Bulletin A340-53-4208, Revision 03, dated February 28, 2014. (3) For service information identified in this AD, contact Airbus SAS, Airworthiness Office--EAL, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 45 80; email [email protected]; 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 October 30, 2015. Michael Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2015-28895 Filed 11-19-15; 8:45 am] BILLING CODE 4910-13-P
![Federal Register / Vol. 80, No. 224 / Friday, November 20, 2015 / Rules and Regulations 72569
(2) Service information identified in this DEPARTMENT OF TRANSPORTATION SW., Renton, WA. For information on
AD that is not incorporated by reference is the availability of this material at the
available at the addresses specified in Federal Aviation Administration FAA, call 425–227–1221. It is also
paragraphs (o)(5) and (o)(6) of this AD. available on the Internet at http://
(o) Material Incorporated by Reference
14 CFR Part 39 www.regulations.gov by searching for
[Docket No. FAA–2014–1043; Directorate and locating Docket No. FAA–2014–
(1) The Director of the Federal Register 1043.
approved the incorporation by reference Identifier 2013–NM–079–AD; Amendment
39–18321; AD 2015–23–05] FOR FURTHER INFORMATION CONTACT:
(IBR) of the service information listed in this
paragraph under 5 U.S.C. 552(a) and 1 CFR RIN 2120–AA64 Vladimir Ulyanov, Aerospace Engineer,
part 51. International Branch, ANM–116,
(2) You must use this service information Airworthiness Directives; Airbus Transport Airplane Directorate, FAA,
as applicable to do the actions required by Airplanes 1601 Lind Avenue SW., Renton, WA
this AD, unless the AD specifies otherwise. 98057–3356; telephone 425–227–1138;
AGENCY: Federal Aviation fax 425–227–1149.
(3) The following service information was
Administration (FAA), Department of
approved for IBR on December 28, 2015. SUPPLEMENTARY INFORMATION:
(i) Lockheed Service Bulletin 382–57–85
Transportation (DOT).
(82–790), Revision 3, dated July 8, 2013, ACTION: Final rule. Discussion
including Appendix A, Revision 3, dated July We issued a notice of proposed
SUMMARY: We are adopting a new rulemaking (NPRM) to amend 14 CFR
8, 2013, and Appendixes B, C, D, E, F, and
airworthiness directive (AD) for all part 39 by adding an AD that would
G, all Revision 1, all dated March 8, 2007.
Airbus Model A330–200, A330–200 apply to all Airbus Model A330–200,
(ii) Reserved.
(4) The following service information was
Freighter, and A330–300 series A330–200 Freighter, and A330–300
approved for IBR on June 22, 2011 (76 FR
airplanes; and Model A340–200 and series airplanes; and Model A340–200
28626, May 18, 2011). A340–300 series airplanes. This AD was and A340–300 series airplanes. The
(i) Lockheed Service Bulletin 382–57–85 prompted by reports of cracked support NPRM published in the Federal
(82–790), Revision 2, dated August 23, 2007, strut body ends at a certain frame Register on January 23, 2015 (80 FR
including Appendixes A, B, C, D, E, F, and location of the trimmable horizontal 3510). The NPRM was prompted by
G, all Revision 1, all dated March 8, 2007. stabilizer (THS). This AD requires reports of cracked support strut body
(ii) Reserved. repetitive inspections for cracking of the ends at a certain frame location of the
(5) For Lockheed Martin Corporation/ strut ends of the THS support located at THS. The NPRM proposed to require
Lockheed Martin Aeronautics Company a certain frame in the tail cone, and repetitive inspections for cracking of the
service information identified in this AD, replacement if necessary; and strut ends of the THS support located at
contact Lockheed Martin Corporation/ reinstallation or installation of a certain frame in the tail cone, and
Lockheed Martin Aeronautics Company, reinforcing clamps on certain strut ends. replacement if necessary; and
Airworthiness Office, Dept. 6A0M, Zone We are issuing this AD to detect and reinstallation or installation of
0252, Column P–58, 86 S. Cobb Drive, correct cracked support strut body ends reinforcing clamps on certain strut ends.
Marietta, GA 30063; telephone 770–494– of the THS, which could lead to the loss We are issuing this AD to detect and
5444; fax 770–494–5445; email ams.portal@ of all four THS support struts, making correct cracked support strut body ends
lmco.com; Internet http:// the remaining structure unable to carry of the THS, which could lead to the loss
www.lockheedmartin.com/ams/tools/ limit loads, resulting in the loss of the of all four THS support struts, making
TechPubs.html. horizontal tail plane. the remaining structure unable to carry
(6) You may view this referenced service DATES: This AD becomes effective limit loads, resulting in the loss of the
information at the FAA, Transport Airplane December 28, 2015. horizontal tail plane.
Directorate, 1601 Lind Avenue SW., Renton, The Director of the Federal Register The European Aviation Safety Agency
WA. For information on the availability of approved the incorporation by reference (EASA), which is the Technical Agent
this material at the FAA, call 425–227–1221. of certain publications listed in this AD for the Member States of the European
(7) You may view this service information as of December 28, 2015. Union, has issued EASA Airworthiness
that is incorporated by reference at the
ADDRESSES: You may examine the AD Directive 2014–0068, dated March 18,
National Archives and Records
docket on the Internet at http:// 2014 (referred to after this as the
Administration (NARA). For information on
www.regulations.gov/ Mandatory Continuing Airworthiness
the availability of this material at NARA, call
#!docketDetail;D=FAA-2014-1043 or in Information, or ‘‘the MCAI’’), to correct
202–741–6030, or go to http://
person at the Docket Management an unsafe condition for all Airbus
www.archives.gov/federal-register/cfr/ibr-
Facility, U.S. Department of Model A330–200, A330–200 Freighter,
locations.html.
Transportation, Docket Operations, M– and A330–300 series airplanes; and
Issued in Renton, Washington, on October 30, West Building Ground Floor, Room Model A340–200 and A340–300 series
29, 2015. W12–140, 1200 New Jersey Avenue SE., airplanes. The MCAI states:
Jeffrey E. Duven, Washington, DC. During scheduled maintenance on A330
Manager, Transport Airplane Directorate, For service information identified in aeroplanes, several Trimmable Horizontal
Aircraft Certification Service. this AD, contact Airbus SAS, Stabilizer (THS) support struts at frame (FR)
[FR Doc. 2015–28464 Filed 11–19–15; 8:45 am] Airworthiness Office—EAL, 1 Rond 91 were found cracked at strut body ends.
Point Maurice Bellonte, 31707 Blagnac The THS is supported and articulated at FR
BILLING CODE 4910–13–P
Cedex, France; telephone +33 5 61 93 36 91 by four struts to fix the hinges (Y-bolts)
tkelley on DSK3SPTVN1PROD with RULES
and keep the structural integrity in lateral
96; fax +33 5 61 93 45 80; email
direction.
airworthiness.A330–A340@airbus.com; Analysis revealed that cracks can reduce
Internet http://www.airbus.com. You ability of the support struts to carry specified
may view this referenced service tension loads.
information at the FAA, Transport This condition, if not detected and
Airplane Directorate, 1601 Lind Avenue corrected, could lead to the loss of all four
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![72570 Federal Register / Vol. 80, No. 224 / Friday, November 20, 2015 / Rules and Regulations
THS support struts at FR91, which would Comments 203834 supersedes Modification
make the remaining structure unable to carry 203493, and the first airplane delivered
limit loads, resulting in the loss of Horizontal We gave the public the opportunity to
participate in developing this AD. The with Modification 203834 installed was
Tail Plane. MSN 1511.
A340–500/600 aeroplanes are not affected following presents the comments
Thus, operators may have the two
by this [EASA] AD as different material is received on the NPRM (80 FR 3510,
populations of airplanes: Those with
used on THS support struts. January 23, 2015) and the FAA’s
Modification 203834 and those with
To address this potentially unsafe response to each comment.
condition, EASA issued AD 2013–0076
Modification 203493. This AD must
[http://ad.easa.europa.eu/blob/easa_ad_ Request To Add Inspection for address both groups of airplanes
2013_0076_superseded.pdf/AD_2013-0076_ Identifying Struts accordingly. We have revised paragraph
1] to require repetitive special detailed (h) of this AD to specify that, for
Delta Air Lines, Inc. (DAL) requested
inspections [high frequency eddy current airplanes on which Airbus Modification
that we add a physical inspection to
(HFEC) inspections for cracking] of all 8 strut 203493 or 203834 has been embodied in
paragraph (g) of the proposed AD (80 FR
ends of the THS support located at FR91 in production; or on which Airbus Service
the tail cone and, depending on findings,
3510, January 23, 2015) to distinguish a
Bulletin A330–53–3204 or Airbus
replacement of THS support struts. That Societé Anonyme de Recherche
Service Bulletin A340 53–4199, as
[EASA] AD also required, for aeroplanes on Mécanique Appliquée (SARMA) strut
applicable; has been embodied in
which Airbus Modification 203493 had not from a Technical Airborne Components
service, remove the clamp from each
been embodied in production, or Airbus Industries (TAC) strut. DAL stated that strut end before accomplishing the
Service Bulletin (SB) A330–53–3204 or SB paragraph (g) of the proposed AD only inspections required by paragraph (h) of
A340–53–4199, as applicable, has not been identifies the dimensional diameter of
embodied in service, the installation of a
this AD.
SARMA struts; however, DAL stated
clamping device on each support strut end to that both TAC and SARMA struts have Request To Include Additional Service
stop growth of possible cracks (crack stopper the same manufacturer part numbers but Information
function) in order to secure integrity of the have different rod end diameters. DAL
struts. DAL requested that we revise
Since issuance of EASA AD 2013–0076
suggested language for doing a physical paragraphs (j)(1), (j)(2), and (l) of the
[http://ad.easa.europa.eu/blob/easa_ad_ inspection of the strut end of each proposed AD (80 FR 3510, January 23,
2013_0076_superseded.pdf/AD_2013-0076_ support strut for identification 2015) to include Airbus Service Bulletin
1], it has been discovered that several purposes. A330–53–3204. DAL stated that, when
aeroplanes are fitted with another strut We agree that a physical inspection is clamps were not previously installed,
configuration (SARMA Strut) [Societé necessary to determine the rod end Airbus Service Bulletin A330–53–3204
Anonyme de Recherche Mécanique diameter in order to distinguish becomes the source document for
Appliquée] than the TAC (Technical between SARMA and TAC struts. installing the clamps.
Airborne Components Industries) strut, However, that inspection is optional. We agree that Airbus Service Bulletin
which caused the other strut not to be Paragraph (g) of this AD defines SARMA A330–53–3204, Revision 03, dated
considered. Consequently, Airbus revised struts as having a diameter that is less February 28, 2014, is an appropriate
Airbus SB A330–53–3206 and SB A340–53–
than 43 millimeters, and states that all source of service information for
4208, accordingly in order to add a one-time
[HFEC] inspection [for cracking] for SARMA
other struts are TAC struts. Paragraph installing clamps. However, we do not
struts and in case of finding to replace it with (h) of this AD requires inspecting TAC agree to revise this AD because that
a TAC strut and thereafter to accomplish struts. Thus, operators must inspect all service information is already
repetitive inspections and EASA issued AD struts unless the strut is inspected to referenced in Airbus Service Bulletin
2013–0219 [http://ad.easa.europa.eu/blob/ determine the diameter is less than 43 A330–53–3206, Revision 03, dated
easa_ad_2013_0219_superseded.pdf/AD_ millimeters, i.e., it is a SARMA strut. February 28, 2014, which is referred to
2013-0219_1], which is superseded, and We have not changed this AD in this as one of the appropriate sources of
required accomplishment of the instructions regard. service information for the actions
as specified in the latest revision of each SB, required by paragraphs (j)(1), (j)(2), and
as applicable. Request To Include Airbus
Modification 203834 for Installing (l) of this AD. As specified in the
Since issuance of EASA AD 2013–0219
[http://ad.easa.europa.eu/blob/easa_ad_ Reinforced Clamps Accomplishment Instructions of Airbus
2013_0219_superseded.pdf/AD_2013-0219_ Service Bulletin A330–53–3206,
DAL requested that we revise Revision 03, dated February 28, 2014.,
1], based on the reporting received from
operators, it has been determined that paragraph (h) of the proposed AD (80 FR ‘‘if no clamps were previously installed,
repetitive inspections are also to be 3510, January 23, 2015) to include accomplish Service Bulletin A330–53–
accomplished for aeroplanes equipped with Airbus Modification 203834 as an 3204 before next flight, to install them.’’
SARMA strut. Airbus introduced that optional modification for installation of Therefore, no change to this AD is
inspection in the applicable SB at revision 3. the reinforced clamps. DAL stated that necessary in this regard.
For the reasons described above, this Airbus has confirmed that Airbus
[EASA] AD retains the requirements of EASA Modification 203834 installs the same Request To Clarify Flight With
AD 2013–0219, which is superseded, and reinforced clamps as Airbus Cracking
requires accomplishment of repetitive Modification 203493 specified in DAL requested that we clarify/
[HFEC] inspective inspection [for cracking] paragraph (h) of the proposed AD. confirm that the NPRM (80 FR 3510,
for aeroplanes equipped with SARMA strut.
We agree with the commenter’s January 23, 2015) will apply more strict
This [EASA] AD is considered as an
interim action, pending the development of request. The FAA has approved two replacement criteria when cracks are
a terminating action. Airbus modifications for installing the found than what is currently published
tkelley on DSK3SPTVN1PROD with RULES
reinforced clamps into production in Airbus Service Bulletin A330–53–
You may examine the MCAI in the airplanes: Modification 203493 for 3206, Revision 03, dated February 28,
AD docket on the Internet at http:// airplanes having manufacturer serial 2014. DAL stated that Subtask 533206–
www.regulations.gov/ number (MSN) 1466 to 1509 inclusive, 280–201–001 of Airbus Service Bulletin
#!documentDetail;D=FAA-2014-1043- and Modification 203834 for airplanes A330–53–3206, Revision 03, dated
0002. having MSN 1510 and on. Modification February 28, 2014, contains instructions
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![Federal Register / Vol. 80, No. 224 / Friday, November 20, 2015 / Rules and Regulations 72571
to allow continued operation of the identified in the ADDRESSES section of For the reasons discussed above, I
airplane with small crack findings this AD. certify that this AD:
without immediate strut replacement. 1. Is not a ‘‘significant regulatory
Costs of Compliance
We agree. In the ‘‘Differences Between action’’ under Executive Order 12866;
this Proposed AD and the MCAI or We estimate that this AD affects 84 2. Is not a ‘‘significant rule’’ under the
Service Information’’ section of the airplanes of U.S. registry. DOT Regulatory Policies and Procedures
NPRM (80 FR 3510, January 23, 2015), We also estimate that it will take (44 FR 11034, February 26, 1979);
we stated that ‘‘Although EASA about 9 work-hours per product to 3. Will not affect intrastate aviation in
Airworthiness Directive 2014–0068, comply with the basic requirements of Alaska; and
dated March 18, 2014, Airbus Service this AD. The average labor rate is $85
4. Will not have a significant
Bulletin A330–53–3206, Revision 03, per work-hour. Based on these figures,
economic impact, positive or negative,
dated February 28, 2014, and Airbus we estimate the cost of this AD on U.S.
on a substantial number of small entities
Service Bulletin A340–53–4208, operators to be $64,260, or $765 per
under the criteria of the Regulatory
Revision 03, dated February 28, 2014, product.
Flexibility Act.
allow further flight after certain cracks We have received no definitive data
are found during compliance with the that would enable us to provide cost Examining the AD Docket
proposed action, paragraph (j)(2) of this estimates for the on-condition
You may examine the AD docket on
AD would require that any cracked THS replacement specified in this AD.
We estimate that any necessary the Internet at http://
support strut be replaced with a new or www.regulations.gov/#!docket
serviceable TAC strut before further follow-on strut reinforcements will take
about 2 work-hours and require parts Detail;D=FAA-2014-1043; or in person
flight.’’ No change to this AD is at the Docket Management Facility
necessary in this regard. costing $5,680, for a cost of $5,850 per
product. We have no way of between 9 a.m. and 5 p.m., Monday
Conclusion determining the number of aircraft that through Friday, except Federal holidays.
might need this action. The AD docket contains this AD, the
We reviewed the relevant data, regulatory evaluation, any comments
considered the comments received, and According to the manufacturer, some
of the costs of this AD may be covered received, and other information. The
determined that air safety and the street address for the Docket Operations
public interest require adopting this AD under warranty, thereby reducing the
cost impact on affected individuals. We office (telephone 800–647–5527) is in
with the changes described previously the ADDRESSES section.
and minor editorial changes. We have do not control warranty coverage for
determined that these minor changes: affected individuals. As a result, we List of Subjects in 14 CFR Part 39
• Are consistent with the intent that have included all costs in our cost
Air transportation, Aircraft, Aviation
was proposed in the NPRM (80 FR 3510, estimate.
safety, Incorporation by reference,
January 23, 2015) for correcting the Authority for This Rulemaking Safety.
unsafe condition; and
• Do not add any additional burden Title 49 of the United States Code Adoption of the Amendment
upon the public than was already specifies the FAA’s authority to issue
rules on aviation safety. Subtitle I, Accordingly, under the authority
proposed in the NPRM (80 FR 3510, delegated to me by the Administrator,
January 23, 2015). section 106, describes the authority of
the FAA Administrator. ‘‘Subtitle VII: the FAA amends 14 CFR part 39 as
We also determined that these
Aviation Programs,’’ describes in more follows:
changes will not increase the economic
burden on any operator or increase the detail the scope of the Agency’s
PART 39—AIRWORTHINESS
scope of this AD. authority.
DIRECTIVES
We are issuing this rulemaking under
Interim Action the authority described in ‘‘Subtitle VII, ■ 1. The authority citation for part 39
We consider this AD interim action. If Part A, Subpart III, Section 44701: continues to read as follows:
final action is later identified, we might General requirements.’’ Under that
section, Congress charges the FAA with Authority: 49 U.S.C. 106(g), 40113, 44701.
consider further rulemaking then.
promoting safe flight of civil aircraft in § 39.13 [Amended]
Related Service Information Under 1 air commerce by prescribing regulations
CFR Part 51 ■ 2. The FAA amends § 39.13 by adding
for practices, methods, and procedures
We reviewed the following service the following new airworthiness
the Administrator finds necessary for
information. directive (AD):
safety in air commerce. This regulation
• Airbus Service Bulletin A330–53– is within the scope of that authority 2015–23–05 Airbus: Amendment 39–18321.
3206, Revision 03, dated February 28, because it addresses an unsafe condition Docket No. FAA–2014–1043; Directorate
2014. This service information describes that is likely to exist or develop on Identifier 2013–NM–079–AD.
procedures for inspections for cracking products identified in this rulemaking (a) Effective Date
of the strut ends of the THS support action. This AD becomes effective December 28,
located in the airplane tail cone. 2015.
• Airbus Service Bulletin A340–53– Regulatory Findings
4208, Revision 03, dated February 28, We determined that this AD will not (b) Affected ADs
2014. This service information describes have federalism implications under None.
procedures for inspections for cracking Executive Order 13132. This AD will (c) Applicability
tkelley on DSK3SPTVN1PROD with RULES
of the strut ends of the THS support not have a substantial direct effect on
This AD applies to the airplanes identified
located in the airplane tail cone. the States, on the relationship between in paragraphs (c)(1), (c)(2), and (c)(3) of this
This service information is reasonably the national government and the States, AD, certificated in any category, all
available because the interested parties or on the distribution of power and manufacturer serial numbers.
have access to it through their normal responsibilities among the various (1) Airbus Model A330–201, –202, –203,
course of business or by the means levels of government. –223, –223F, –243, and –243F airplanes.
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![Federal Register / Vol. 80, No. 224 / Friday, November 20, 2015 / Rules and Regulations 72573
(2) You must use this service information could result in rapid depressurization of skin lap joints are subject to WFD. The
as applicable to do the actions required by the airplane. NPRM proposed to require repetitive
this AD, unless this AD specifies otherwise. post-modification inspections for
DATES: This AD is effective December
(i) Airbus Service Bulletin A330–53–3206, cracking of the skin or internal doubler
Revision 03, dated February 28, 2014. 28, 2015.
(ii) Airbus Service Bulletin A340–53–4208, The Director of the Federal Register along the edge fastener rows of the
Revision 03, dated February 28, 2014. approved the incorporation by reference modification, and repair if necessary.
(3) For service information identified in of a certain publication listed in this AD We are issuing this AD to detect and
this AD, contact Airbus SAS, Airworthiness as of December 28, 2015. correct fatigue cracking in certain
Office—EAL, 1 Rond Point Maurice Bellonte, ADDRESSES: For service information fuselage skin lap joints, which could
31707 Blagnac Cedex, France; telephone +33 identified in this AD, contact Boeing result in rapid depressurization of the
5 61 93 36 96; fax +33 5 61 93 45 80; email airplane.
Commercial Airplanes, Attention: Data
airworthiness.A330-A340@airbus.com;
Internet http://www.airbus.com. & Services Management, P. O. Box 3707, Comments
(4) You may view this service information MC 2H–65, Seattle, WA 98124–2207;
telephone 206–544–5000, extension 1; We gave the public the opportunity to
at the FAA, Transport Airplane Directorate,
fax 206–766–5680; Internet https:// participate in developing this AD. The
1601 Lind Avenue SW., Renton, WA. For
information on the availability of this www.myboeingfleet.com. You may view following presents the comments
material at the FAA, call 425–227–1221. this referenced service information at received on the NPRM (80 FR 25630,
(5) You may view this service information the FAA, Transport Airplane May 5, 2015) and the FAA’s response to
that is incorporated by reference at the Directorate, 1601 Lind Avenue SW., each comment.
National Archives and Records
Renton, WA. For information on the Request To Remove Warranty
Administration (NARA). For information on
the availability of this material at NARA, call availability of this material at the FAA, Statement
202–741–6030, or go to: http:// call 425–227–1221. It is also available Boeing requested that we remove the
www.archives.gov/federal-register/cfr/ibr- on the Internet at http:// statement that ‘‘some of the costs of this
locations.html. www.regulations.gov by searching for proposed AD may be covered under
Issued in Renton, Washington, on October and locating Docket No. FAA–2015– warranty’’ in the Costs of Compliance
30, 2015. 1266. section of the NPRM (80 FR 25630, May
Michael Kaszycki, Examining the AD Docket 5, 2015). Boeing stated that the actions
Acting Manager, Transport Airplane You may examine the AD docket on in the NPRM are not covered by
Directorate, Aircraft Certification Service.
the Internet at http:// warranty.
[FR Doc. 2015–28895 Filed 11–19–15; 8:45 am] We agree with the commenter’s
www.regulations.gov by searching for
BILLING CODE 4910–13–P request. We have revised the Costs of
and locating Docket No. FAA–2015–
Compliance section of this final rule
1266; or in person at the Docket
accordingly.
Management Facility between 9 a.m.
DEPARTMENT OF TRANSPORTATION and 5 p.m., Monday through Friday, Request To Revise Paragraph Headings
Federal Aviation Administration except Federal holidays. The AD docket Boeing requested that we revise the
contains this AD, the regulatory headings of paragraphs (g), (h), (j), and
14 CFR Part 39 evaluation, any comments received, and (k) of the proposed AD (80 FR 25630,
other information. The address for the May 5, 2015) by removing reference to
[Docket No. FAA–2015–1266; Directorate Docket Office (phone: 800–647–5527) is the inspections as ‘‘repetitive’’ or
Identifier 2014–NM–151–AD; Amendment Docket Management Facility, U.S. ‘‘initial.’’ Boeing stated that these
39–18327; AD 2015–23–11] Department of Transportation, Docket revisions will provide consistency
Operations, M–30, West Building among paragraph headings because
RIN 2120–AA64 Ground Floor, Room W12–140, 1200 paragraphs (g), (j), and (k) of the
New Jersey Avenue SE., Washington, proposed AD do not have an initial
Airworthiness Directives; The Boeing DC 20590.
Company Airplanes inspection program, yet paragraph (h) of
FOR FURTHER INFORMATION CONTACT: the proposed AD has only an initial
AGENCY: Federal Aviation Nathan Weigand, Aerospace Engineer, inspection.
Administration (FAA), DOT. Airframe Branch, ANM–120S, FAA, We acknowledge the commenter’s
ACTION: Final rule. Seattle Aircraft Certification Office, concern and agree to clarify the
1601 Lind Avenue SW., Renton, WA headings. We do not presume that the
SUMMARY: We are adopting a new 98057–3356; phone: 425–917–6428; fax: term ‘‘repetitive’’ necessarily excludes
airworthiness directive (AD) for certain 425–917–6590; email: the initial action. An action cannot be
The Boeing Company Model 747–100, nathan.p.weigand@faa.gov. repeated without accomplishment of the
747–100B, 747–100B SUD, 747–200B, SUPPLEMENTARY INFORMATION: initial action. In addition, in many ADs
747–300, 747SR, and 747SP series we use the term ‘‘repetitive’’ actions for
airplanes. This AD was prompted by an Discussion
paragraphs that include the initial
evaluation by the design approval We issued a notice of proposed action and repetitive actions. Paragraphs
holder (DAH) indicating that certain rulemaking (NPRM) to amend 14 CFR (g), (j), and (k) of this AD include both
fuselage skin lap joints are subject to part 39 by adding an AD that would a sentence specifying the initial
widespread fatigue damage (WFD). This apply to certain The Boeing Company inspection and a sentence specifying the
AD requires repetitive post-modification Model 747–100, 747–100B, 747–100B repetitive inspections. We have not
tkelley on DSK3SPTVN1PROD with RULES
inspections for cracking of the skin or SUD, 747–200B, 747–300, 747SR, and changed this AD in this regard.
internal doubler along the edge fastener 747SP series airplanes. The NPRM
rows of the modification, and repair if published in the Federal Register on Request To Clarify Compliance Time
necessary. We are issuing this AD to May 5, 2015 (80 FR 25630). The NPRM Boeing requested that we clarify the
detect and correct fatigue cracking in was prompted by an evaluation by the compliance time in paragraphs (g), (h),
certain fuselage skin lap joints, which DAH indicating that certain fuselage (j), and (k) of the proposed AD (80 FR
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Document Created: 2015-12-14 13:58:23
Document Modified: 2015-12-14 13:58:23
| Category | Regulatory Information | |
| Collection | Federal Register | |
| sudoc Class | AE 2.7: GS 4.107: AE 2.106: | |
| Publisher | Office of the Federal Register, National Archives and Records Administration | |
| Section | Rules and Regulations | |
| Action | Final rule. | |
| Dates | This AD becomes effective December 28, 2015. | |
| Contact | Vladimir Ulyanov, Aerospace Engineer, International Branch, ANM-116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057-3356; telephone 425-227-1138; fax 425-227-1149. | |
| FR Citation | 80 FR 72569 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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