83 FR 46905 - Airworthiness Directives; Airbus SAS Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 83, Issue 180 (September 17, 2018)
Federal Aviation Administration
Federal Register Volume 83, Issue 180 (September 17, 2018)
| Page Range | 46905-46909 | |
| FR Document | 2018-19932 |
[Federal Register Volume 83, Number 180 (Monday, September 17, 2018)] [Proposed Rules] [Pages 46905-46909] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2018-19932] ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2018-0795; Product Identifier 2018-NM-076-AD] RIN 2120-AA64 Airworthiness Directives; Airbus SAS Airplanes AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). ----------------------------------------------------------------------- SUMMARY: We propose to supersede Airworthiness Directive (AD) 2014-20- 04, which applies to all Airbus SAS Model A318 series airplanes; Airbus SAS Model A319 series airplanes; Airbus SAS Model A320-111, -211, -212, -214, -231, -232, and -233 airplanes; and Airbus SAS Model A321-111, - 112, -131, -211, -212, -213, -231, and -232 airplanes. AD 2014-20-04 requires repetitive inspections for cracking of the four titanium angles between the belly fairing and the keel beam side panel, an inspection for cracking of the open holes if any cracking is found in the titanium angles, and repair or replacement if necessary. Since we issued AD 2014-20-04, we have determined that additional work is necessary for certain airplanes. This proposed AD would continue to require repetitive inspections for cracking of the four titanium angles between the belly fairing and the keel beam side panel, an inspection for cracking of the open holes if any cracking is found in the titanium angles, and repair or replacement if necessary. This proposed AD would also revise the applicability by adding Model A320-216 airplanes. This proposed AD would also require a detailed inspection for and replacement of certain rivets (including a rotating probe test for cracks in the open holes), and corrective actions if necessary. We are proposing this AD to address the unsafe condition on these products. DATES: We must receive comments on this proposed AD by November 1, 2018. ADDRESSES: You may send comments, using the procedures found in 14 CFR 11.43 and 11.45, by any of the following methods:Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments. Fax: 202-493-2251. Mail: U.S. Department of Transportation, Docket Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue SE, Washington, DC 20590. Hand Delivery: Deliver to Mail address above between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For service information identified in this NPRM, contact Airbus SAS, Airworthiness Office--EIAS, Rond-Point Emile Dewoitine No: 2, 31700 Blagnac Cedex, France; phone: +33 5 61 93 36 96; fax: +33 5 61 93 44 51; email: [email protected]; internet: http://www.airbus.com. You may view this referenced service information at the FAA, Transport Standards Branch, 2200 South 216th St., Des Moines, WA. For information on the availability of this material at the FAA, call 206-231-3195. Examining the AD Docket You may examine the AD docket on the internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2018- 0795; or in person at Docket Operations between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this NPRM, the regulatory evaluation, any comments received, and other information. The street address for Docket Operations (phone: 800-647- 5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: Sanjay Ralhan, Aerospace Engineer, International Section, Transport Standards Branch, FAA, 2200 South 216th St., Des Moines, WA 98198; phone and fax 206-231-3223. SUPPLEMENTARY INFORMATION: Comments Invited We invite you to send any written relevant data, views, or arguments about this proposal. Send your comments to an address listed under the ADDRESSES section. Include ``Docket No. FAA-2018-0795; Product Identifier 2018-NM-076-AD'' at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this proposed AD. We will consider all comments received by the closing date and may amend this proposed AD based on those comments. We will post all comments we receive, without change, to http://www.regulations.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact we receive about this proposed AD. Discussion We issued AD 2014-20-04, Amendment 39-17977 (79 FR 59636, [[Page 46906]] October 3, 2014) (``AD 2014-20-04''), for all Airbus SAS Model A318 series airplanes; Airbus SAS Model A319 series airplanes; Airbus SAS Model A320-211, -212, -214, -231, -232, and -233 airplanes; and Airbus SAS Model A321-111, -112, -131, -211, -212, -213, -231, and -232 airplanes. AD 2014-20-04 requires repetitive inspections for cracking of the four titanium angles between the belly fairing and the keel beam side panel, an inspection for cracking of the open holes if any cracking is found in the titanium angles, and repair or replacement if necessary. AD 2014-20-04 resulted from reports of cracks at the lower riveting of the four titanium angles that connect the belly fairing to the keel beam side panels on both sides of the fuselage. We issued AD 2014-20-04 to address cracking of the titanium angles that connect the belly fairing to the keel beam side panels on both sides of the fuselage, which could affect the structural integrity of the airplane. Actions Since AD 2014-20-04 Was Issued The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, has issued EASA AD 2018-0091, dated April 20, 2018 (referred to after this as the Mandatory Continuing Airworthiness Information, or ``the MCAI''), to correct an unsafe condition for all Airbus SAS Model A318 series airplanes; Airbus SAS Model A319 series airplanes; Airbus SAS Model A320-211, -212, -214, -216, -231, -232, and -233 airplanes; and Airbus SAS Model A321-111, -112, -131, -211, -212, -213, -231, and -232 airplanes. The MCAI states: During the fatigue test campaign of the A320 family type design, cracks were found at the lower riveting of the four titanium angles which connect the belly fairing to the keel beam side panels between frames FR40 and FR42, on both sides of the fuselage. This condition, if not detected and corrected, could affect the structural integrity of the aeroplane. To address this potential unsafe condition, Airbus issued Service Bulletin (SB) A320-53-1014, and DGAC [Direction G[eacute]n[eacute]rale de l'Aviation Civile] France issued AD 92- 201-030 [which corresponds to FAA AD 94-12-03, Amendment 39-8930 (59 FR 28763, June 3, 1994)(``AD 94-12-03'')] to require reinforcement of the belly fairing structure. Following new investigation which showed that these measures addressed only part of the unsafe condition, Airbus published SB A320-53-1259 and EASA issued AD 2013-0122 [which corresponds to FAA AD 2014-20-04], retaining the requirements of DGAC France AD 92-201- 030, which was superseded, and requiring repetitive detailed inspections (DET) of the affected titanium angles and, depending on findings, repair or replacement of parts. After that [EASA] AD was issued, Airbus published Revision (Rev.) 01 and Rev. 02 of SB A320-53-1259. [Airbus SB A320-53-1259] Rev. 02 provided incorrect instructions to use Part Number (P/N) EN6081D4 rivets for the titanium angles installation, instead of P/N EN6081D5 rivets. Consequently, Airbus SB A320-53-1259 was updated (now at Rev. 03) including reference to the proper rivets. For the reason described above, this [EASA] AD retains the requirements of EASA AD 2013-0122, which is superseded, and requires additional work [a detailed inspection for and replacement of certain rivets, and applicable corrective actions] for aeroplanes on which Airbus SB A320-53-1259 at Rev. 02 was embodied. You may examine the MCAI in the AD docket on the internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2018- 0795. Model A320-216 Airplanes The Airbus SAS Model A320-216 was type certificated on December 19, 2016. Before that date, any EASA ADs that affected Model A320-216 airplanes were included on the Required Airworthiness Actions List (RAAL). One or more Model A320-216 airplanes have subsequently been placed on the U.S. Register, and will now be included in FAA AD actions. For Model A320-216 airplanes, the requirements that correspond to AD 2014-20-04 were mandated by the MCAI via the RAAL. Although that RAAL requirement is still in effect, for continuity and clarity we have identified Model A320-216 airplanes in paragraph (c) of this AD; the restated requirements of paragraphs (h) through (n) in this proposed AD would therefore apply to those airplanes. Related Service Information Under 1 CFR Part 51 Airbus SAS has issued Service Bulletin A320-53-1259, Revision 03, dated November 30, 2017. This service information describes procedures for repetitive inspections for cracking of the four titanium angles between the belly fairing and the keel beam side panel, an inspection for cracking of the open holes if any cracking is found in the titanium angles, repair or replacement if necessary, and a detailed inspection for and replacement of certain rivets (including a rotating probe test for cracks in the open holes). Airbus also issued Service Bulletin A320-53-1014, Revision 2, dated September 1, 1994. This service information describes procedures for reinforcement (modification) of the belly fairing structure. 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. FAA's Determination This product has been approved by the aviation authority of another country, and is approved for operation in the United States. Pursuant to our bilateral agreement with the State of Design Authority, we have been notified of the unsafe condition described in the MCAI and service information referenced above. We are proposing this AD because we evaluated all the relevant information and determined the unsafe condition described previously is likely to exist or develop on other products of the same type design. Proposed Requirements of This NPRM This proposed AD would retain all requirements of AD 2014-20-04. This proposed AD would also require accomplishing the actions specified in the service information described previously. Costs of Compliance We estimate that this proposed AD affects 1,250 airplanes of U.S. registry. We estimate the following costs to comply with this proposed AD: Estimated Costs ---------------------------------------------------------------------------------------------------------------- Labor cost Parts cost Cost per product Cost on U.S. operators ---------------------------------------------------------------------------------------------------------------- 295 work-hours x $85 per hour = $1,045 $26,120......................... $32,650,000. $25,075 (Old actions of AD 2014-20-04). Up to 168 work-hours x $85 per 0 Up to $14,280................... Up to $17,850,000. hour = Up to $14,280 (New actions of this AD). ---------------------------------------------------------------------------------------------------------------- [[Page 46907]] We estimate the following costs to do any necessary replacement that would be required based on the results of the proposed inspection. We have no way of determining the number of aircraft that might need this replacement: Estimated Costs of On-Condition Actions ------------------------------------------------------------------------ Cost per Labor cost Parts cost * product ------------------------------------------------------------------------ 168 work-hours x $85 per hour = $0 $14,280 $14,280.............................. ------------------------------------------------------------------------ * We have received no definitive data that would enable us to provide cost estimates for the on-condition parts costs. 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. This proposed AD is issued in accordance with authority delegated by the Executive Director, Aircraft Certification Service, as authorized by FAA Order 8000.51C. In accordance with that order, issuance of ADs is normally a function of the Compliance and Airworthiness Division, but during this transition period, the Executive Director has delegated the authority to issue ADs applicable to transport category airplanes to the Director of the System Oversight Division. Regulatory Findings We determined that this proposed AD would not have federalism implications under Executive Order 13132. This proposed AD would not have a substantial direct effect on the States, on the relationship between the national Government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify this proposed regulation: 1. Is not a ``significant regulatory action'' under Executive Order 12866, 2. Is not a ``significant rule'' under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979), 3. Will not affect intrastate aviation in Alaska, and 4. Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. The Proposed Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 14 CFR part 39 as follows: PART 39--AIRWORTHINESS DIRECTIVES 0 1. The authority citation for part 39 continues to read as follows: Authority: 49 U.S.C. 106(g), 40113, 44701. Sec. 39.13 [Amended] 0 2. The FAA amends Sec. 39.13 by removing Airworthiness Directive (AD) 2014-20-04, Amendment 39-17977 (79 FR 59636, October 3, 2014), and adding the following new AD: Airbus SAS: Docket No. FAA-2018-0795; Product Identifier 2018-NM- 076-AD. (a) Comments Due Date We must receive comments by November 1, 2018. (b) Affected ADs This AD replaces AD 2014-20-04, Amendment 39-17977 (79 FR 59636, October 3, 2014) (``AD 2014-20-04''). (c) Applicability This AD applies to the Airbus SAS airplanes specified in paragraphs (c)(1), (c)(2), (c)(3), and (c)(4) of this AD, certificated in any category, all manufacturer serial numbers. (1) Model A318-111, -112, -121, and -122 airplanes. (2) Model A319-111, -112, -113, -114, -115, -131, -132, and -133 airplanes. (3) Model A320-211, -212, -214, -216, -231, -232, and -233 airplanes. (4) Model A321-111, -112, -131, -211, -212, -213, -231, and -232 airplanes. (d) Subject Air Transport Association (ATA) of America Code 53, Fuselage. (e) Reason This AD was prompted by reports of cracks at the lower riveting of the four titanium angles that connect the belly fairing to the keel beam side panels on both sides of the fuselage. We are issuing this AD to detect and correct cracking of the titanium angles that connect the belly fairing to the keel beam side panels on both sides of the fuselage, which could affect the structural integrity of the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Retained Modification, With No Changes This paragraph restates the requirements of paragraph (g) of AD 2014-20-04, with no changes. For Model A320-111, -211, and -231 series airplanes, manufacturer serial numbers 003 through 092 inclusive: Prior to the accumulation of 12,000 total landings on the airplane, or within 300 days after January 10, 1994 (the effective date of AD 93-24-11, Amendment 39-8760 (58 FR 64875, December 10, 1993)), whichever occurs later, modify the belly fairing structure, in accordance with the Accomplishment Instructions of an Airbus service bulletin specified in paragraph (g)(1), (g)(2), or (g)(3) of this AD. As of the effective date of this AD, use only the Airbus service bulletin specified in paragraph (g)(3) of this AD. (1) Airbus Industrie Service Bulletin A320-53-1014, dated June 25, 1992. (2) Airbus Industrie Service Bulletin A320-53-1014, Revision 1, dated May 26, 1993. (3) Airbus Service Bulletin A320-53-1014, Revision 2, dated September 1, 1994. (h) Retained Repetitive Inspection, With Updated Service Information This paragraph restates the requirements of paragraph (h) of AD 2014-20-04, with updated service information. At the latest of the compliance times specified in paragraphs (h)(1), (h)(2), and (h)(3) of this AD: Do a detailed inspection for cracking of the four titanium angles between the belly fairing and the keel beam side panel, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-53-1259, dated November 6, 2012; or Airbus Service Bulletin A320-53-1259, Revision 03, dated November 30, 2017. After the effective date of this AD only Airbus Service Bulletin A320-53-1259, Revision 03, dated November 30, 2017, may be used. [[Page 46908]] (1) Before the accumulation of 30,000 total flight cycles or 60,000 total flight hours, whichever occurs first after first flight of the airplane. (2) Within 30,000 flight cycles or 60,000 flight hours, whichever occurs first after modification of the airplane as required by paragraph (g) of this AD, or after installation of new titanium angles, provided that, prior to installation, a rototest for cracking on the open holes has been accomplished with no crack findings, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-53-1259, dated November 6, 2012; or Airbus Service Bulletin A320-53-1259, Revision 03, dated November 30, 2017. After the effective date of this AD, only Airbus Service Bulletin A320-53-1259, Revision 03, dated November 30, 2017, may be used. (3) Within 3,000 flight cycles or 6,000 flight hours, whichever occurs first after the effective date of this AD. (i) Retained Post-Inspection Actions for No Crack Findings, With Updated Service Information This paragraph restates the requirements of paragraph (i) of AD 2014-20-04, with updated service information. If, during any inspection required by paragraph (h) of this AD, there is no crack finding: Accomplish the actions specified in either paragraph (i)(1) or (i)(2) of this AD. (1) Repeat the inspection required by paragraph (h) of this AD at intervals not to exceed 5,000 flight cycles or 10,000 flight hours, whichever occurs first. (2) Before further flight after the inspection required by paragraph (h) of this AD, remove all inspected titanium angles, accomplish a rototest for cracking on the open holes and, provided no cracks are found, install new titanium angles, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-53- 1259, dated November 6, 2012; or Airbus Service Bulletin A320-53- 1259, Revision 03, dated November 30, 2017. After the effective date of this AD, only Airbus Service Bulletin A320-53-1259, Revision 03, dated November 30, 2017, may be used. (j) Retained Post-Inspection Actions for Any Crack Findings, With Updated Service Information This paragraph restates the requirements of paragraph (j) of AD 2014-20-04, with updated service information. If, during any inspection required by paragraph (h) of this AD, there is any crack finding: Before further flight, remove the affected titanium angle(s), accomplish a rototest for cracking on the open holes, and, provided no cracks are found, install new titanium angles, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-53-1259, dated November 6, 2012; or Airbus Service Bulletin A320-53-1259, Revision 03, dated November 30, 2017. After the effective date of this AD, only Airbus Service Bulletin A320-53- 1259, Revision 03, dated November 30, 2017, may be used. (k) Retained Post-Installation Repetitive Inspections, With Updated Service Information This paragraph restates the requirements of paragraph (k) of AD 2014-20-04, with updated service information. For airplanes on which new titanium angles were installed as specified in paragraph (i)(2) or (j) of this AD: Within 30,000 flight cycles or 60,000 flight hours, whichever occurs first after the installation, accomplish a detailed inspection for cracking of the four titanium angles between the belly fairing and the keel beam side panel, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-53- 1259, dated November 6, 2012; or Airbus Service Bulletin A320-53- 1259, Revision 03, dated November 30, 2017. After the effective date of this AD, only Airbus Service Bulletin A320-53-1259, Revision 03, dated November 30, 2017, may be used. Repeat the inspection thereafter at intervals not to exceed 5,000 flight cycles or 10,000 flight hours, whichever occurs first. (l) Retained Post-Inspection Actions for Any Crack Findings During Post-Installation Inspections, With Updated Service Information This paragraph restates the requirements of paragraph (l) of AD 2014-20-04, with updated service information. If, during any inspection as required by paragraph (k) of this AD, there is any crack finding: Before further flight, remove the affected titanium angles, accomplish a rototest for cracking on the open holes, and, provided no cracks are found, install new titanium angles, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-53-1259, dated November 6, 2012; or Airbus Service Bulletin A320-53-1259, Revision 03, dated November 30, 2017. After the effective date of this AD, only Airbus Service Bulletin A320-53- 1259, Revision 03, dated November 30, 2017, may be used. (m) Retained Corrective Action for Rototest Crack Finding, With Updated Contact Information This paragraph restates the requirements of paragraph (m) of AD 2014-20-04, with updated contact information. If, during any rototest as required by paragraph (i), (j), or (l) of this AD, any crack is found: Before further flight, repair using a method approved by the Manager, International Section, Transport Standards Branch, FAA; or the European Aviation Safety Agency (EASA); or Airbus SAS's EASA Design Organization Approval (DOA). If approved by the DOA, the approval must include the DOA-authorized signature. (n) Retained No Termination Action for Repetitive Inspections, With No Changes This paragraph restates the requirements of paragraph (n) of AD 2014-20-04, with no changes. Repair or replacement of parts as specified in this AD does not terminate the repetitive inspections required by this AD. (o) New Requirement of This AD: Detailed Inspection for Certain Rivets For airplanes previously inspected using the Accomplishment Instructions of Airbus Service Bulletin A320-53-1259, dated November 6, 2012: At the earlier of the times specified in paragraphs (o)(1) and (o)(2) of this AD, do a detailed inspection of the rivet installation in the belly fairing shear walls and the titanium angles for part number EN6081D4 series rivets in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-53-1259, Revision 03, dated November 30, 2017. A review of the airplane maintenance records is acceptable to comply with the requirements this paragraph for that airplane, provided it can be determined that no titanium angles have been installed on that airplane in accordance with the Accomplishment Instructions of Revision 02 of Airbus Service Bulletin A320-53-1259, or if only rivets part number EN6081D5 have been used to install the titanium angles on that airplane. (1) Within 2,000 flight cycles or 4,000 flight hours, whichever occurs first after the effective date of this AD. (2) Before exceeding 5,000 flight cycles or 10,000 flight hours, whichever occurs first after accomplishment of the last inspection specified in paragraph (h) of this AD. (p) New Requirements of This AD: Replacement of Certain Rivets If any part number EN6081D4 series rivet is found during any inspection required by paragraph (o) of this AD, before further flight, do the actions specified in paragraphs (p)(1) and (p)(2) of this AD. (1) Remove the part number EN6081D4 series rivets and do a rotating probe test of the open holes for cracks, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-53- 1259, Revision 03, dated November 30, 2017. If any crack is found during any inspection required by this paragraph, before further flight, obtain corrective actions approved by the Manager, International Section, Transport Standards Branch, FAA; or EASA; or Airbus SAS's EASA DOA; and accomplish the corrective actions within the compliance time specified therein. If approved by the DOA, the approval must include the DOA-authorized signature. (2) Replace part number EN6081D4 series rivets with part number EN6081D5 series rivets in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-53-1259, Revision 03, dated November 30, 2017. (q) Other FAA AD Provisions (1) Alternative Methods of Compliance (AMOCs): The Manager, International Section, Transport Standards Branch, 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 Section, send it to the attention of the person identified in paragraph (r)(2) of this AD. Information may be emailed to: [email protected]. (i) 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. [[Page 46909]] (ii) AMOCs approved previously for AD 2014-20-04, Amendment 39- 17977 (79 FR 59636, October 3, 2014), are approved as AMOCs for the corresponding provisions of paragraphs (o) and (p) of this AD. (2) Contacting the Manufacturer: As of the effective date of this AD, 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 Section, Transport Standards Branch, FAA; or EASA; or Airbus SAS's EASA DOA. If approved by the DOA, the approval must include the DOA-authorized signature. (3) Required for Compliance (RC): If any service information contains procedures or tests that are identified as RC, those procedures and tests must be done to comply with this AD; any procedures or tests that are not identified as RC are recommended. Those procedures and tests that are not identified as RC may be deviated from using accepted methods in accordance with the operator's maintenance or inspection program without obtaining approval of an AMOC, provided the procedures and tests identified as RC can be done and the airplane can be put back in an airworthy condition. Any substitutions or changes to procedures or tests identified as RC require approval of an AMOC. (r) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA AD 2018-0091, dated April 20, 2018, for related information. This MCAI may be found in the AD docket on the internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2018-0795. (2) For more information about this AD, contact Sanjay Ralhan, Aerospace Engineer, International Section, Transport Standards Branch, FAA, 2200 South 216th St., Des Moines, WA 98198; phone and fax 206-231-3223. (3) For service information identified in this AD, contact Airbus SAS, Airworthiness Office--EIAS, Rond-Point Emile Dewoitine No: 2, 31700 Blagnac Cedex, France; phone: +33 5 61 93 36 96; fax: +33 5 61 93 44 51; email: [email protected]; internet: http://www.airbus.com. You may view this service information at the FAA, Transport Standards Branch, 2200 South 216th St., Des Moines, WA. For information on the availability of this material at the FAA, call 206-231-3195. Issued in Des Moines, Washington, on August 29, 2018. Jeffrey E. Duven, Director, System Oversight Division, Aircraft Certification Service. [FR Doc. 2018-19932 Filed 9-14-18; 8:45 am] BILLING CODE 4910-13-P
![Federal Register / Vol. 83, No. 180 / Monday, September 17, 2018 / Proposed Rules 46905
(j) Alternative Methods of Compliance DEPARTMENT OF TRANSPORTATION • Hand Delivery: Deliver to Mail
(AMOCs) address above between 9 a.m. and 5
(1) The Manager, Los Angeles ACO Branch, Federal Aviation Administration p.m., Monday through Friday, except
FAA, has the authority to approve AMOCs Federal holidays.
for this AD, if requested using the procedures 14 CFR Part 39 For service information identified in
found in 14 CFR 39.19. In accordance with [Docket No. FAA–2018–0795; Product
this NPRM, contact Airbus SAS,
14 CFR 39.19, send your request to your Identifier 2018–NM–076–AD] Airworthiness Office—EIAS, Rond-
principal inspector or local Flight Standards Point Emile Dewoitine No: 2, 31700
District Office, as appropriate. If sending RIN 2120–AA64 Blagnac Cedex, France; phone: +33 5 61
information directly to the manager of the 93 36 96; fax: +33 5 61 93 44 51; email:
Airworthiness Directives; Airbus SAS account.airworth-eas@airbus.com;
certification office, send it to the attention of
Airplanes internet: http://www.airbus.com. You
the person identified in paragraph (k)(1) of
this AD. Information may be emailed to: AGENCY: Federal Aviation may view this referenced service
9-ANM-LAACO-AMOC-Requests@faa.gov. Administration (FAA), DOT. information at the FAA, Transport
(2) Before using any approved AMOC, ACTION: Notice of proposed rulemaking Standards Branch, 2200 South 216th St.,
notify your appropriate principal inspector, (NPRM). Des Moines, WA. For information on the
or lacking a principal inspector, the manager availability of this material at the FAA,
of the local flight standards district office/ We propose to supersede
SUMMARY: call 206–231–3195.
certificate holding district office. Airworthiness Directive (AD) 2014–20–
04, which applies to all Airbus SAS Examining the AD Docket
(3) An AMOC that provides an acceptable
level of safety may be used for any repair, Model A318 series airplanes; Airbus You may examine the AD docket on
modification, or alteration required by this SAS Model A319 series airplanes; the internet at http://
AD if it is approved by the Boeing Airbus SAS Model A320–111, –211, www.regulations.gov by searching for
Commercial Airplanes Organization –212, –214, –231, –232, and –233 and locating Docket No. FAA–2018–
Designation Authorization (ODA) that has airplanes; and Airbus SAS Model A321– 0795; or in person at Docket Operations
been authorized by the Manager, Los Angeles 111, –112, –131, –211, –212, –213, –231, between 9 a.m. and 5 p.m., Monday
ACO Branch, FAA, to make those findings. and –232 airplanes. AD 2014–20–04 through Friday, except Federal holidays.
To be approved, the repair method, requires repetitive inspections for The AD docket contains this NPRM, the
modification deviation, or alteration cracking of the four titanium angles regulatory evaluation, any comments
deviation must meet the certification basis ofbetween the belly fairing and the keel received, and other information. The
the airplane, and the approval must beam side panel, an inspection for street address for Docket Operations
specifically refer to this AD. cracking of the open holes if any (phone: 800–647–5527) is in the
cracking is found in the titanium angles, ADDRESSES section. Comments will be
(k) Related Information
and repair or replacement if necessary. available in the AD docket shortly after
(1) For more information about this AD, Since we issued AD 2014–20–04, we receipt.
contact Galib Abumeri, Aerospace Engineer, have determined that additional work is FOR FURTHER INFORMATION CONTACT:
Airframe Section, FAA, Los Angeles ACO necessary for certain airplanes. This Sanjay Ralhan, Aerospace Engineer,
Branch, 3960 Paramount Boulevard, proposed AD would continue to require International Section, Transport
Lakewood, CA 90712–4137; phone: 562–627– repetitive inspections for cracking of the Standards Branch, FAA, 2200 South
5324; fax: 562–627–5210; email: four titanium angles between the belly 216th St., Des Moines, WA 98198;
galib.abumeri@faa.gov. fairing and the keel beam side panel, an phone and fax 206–231–3223.
(2) For service information identified in inspection for cracking of the open SUPPLEMENTARY INFORMATION:
this AD, contact Boeing Commercial holes if any cracking is found in the
Airplanes, Attention: Contractual & Data titanium angles, and repair or Comments Invited
Services (C&DS), 2600 Westminster Blvd., replacement if necessary. This proposed We invite you to send any written
MC 110–SK57, Seal Beach, CA 90740–5600; AD would also revise the applicability relevant data, views, or arguments about
phone: 562–797–1717; internet: https:// by adding Model A320–216 airplanes. this proposal. Send your comments to
www.myboeingfleet.com. You may view this This proposed AD would also require a an address listed under the ADDRESSES
referenced service information at the FAA, detailed inspection for and replacement section. Include ‘‘Docket No. FAA–
Transport Standards Branch, 2200 South of certain rivets (including a rotating 2018–0795; Product Identifier 2018–
216th St., Des Moines, WA. For information probe test for cracks in the open holes), NM–076–AD’’ at the beginning of your
on the availability of this material at the and corrective actions if necessary. We comments. We specifically invite
FAA, call 206–231–3195. are proposing this AD to address the comments on the overall regulatory,
Issued in Des Moines, Washington, on unsafe condition on these products. economic, environmental, and energy
August 30, 2018. DATES: We must receive comments on aspects of this proposed AD. We will
Jeffrey E. Duven, this proposed AD by November 1, 2018. consider all comments received by the
Director, System Oversight Division, Aircraft ADDRESSES: You may send comments, closing date and may amend this
Certification Service. using the procedures found in 14 CFR proposed AD based on those comments.
[FR Doc. 2018–19840 Filed 9–14–18; 8:45 am] 11.43 and 11.45, by any of the following We will post all comments we
methods: receive, without change, to http://
BILLING CODE 4910–13–P
• Federal eRulemaking Portal: Go to www.regulations.gov, including any
daltland on DSKBBV9HB2PROD with PROPOSALS
http://www.regulations.gov. Follow the personal information you provide. We
instructions for submitting comments. will also post a report summarizing each
• Fax: 202–493–2251. substantive verbal contact we receive
• Mail: U.S. Department of about this proposed AD.
Transportation, Docket Operations,
M–30, West Building Ground Floor, Discussion
Room W12–140, 1200 New Jersey We issued AD 2014–20–04,
Avenue SE, Washington, DC 20590. Amendment 39–17977 (79 FR 59636,
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![46906 Federal Register / Vol. 83, No. 180 / Monday, September 17, 2018 / Proposed Rules
October 3, 2014) (‘‘AD 2014–20–04’’), 3, 1994)(‘‘AD 94–12–03’’)] to require Related Service Information Under 1
for all Airbus SAS Model A318 series reinforcement of the belly fairing structure. CFR Part 51
airplanes; Airbus SAS Model A319 Following new investigation which
showed that these measures addressed only
Airbus SAS has issued Service
series airplanes; Airbus SAS Model Bulletin A320–53–1259, Revision 03,
A320–211, –212, –214, –231, –232, and part of the unsafe condition, Airbus
published SB A320–53–1259 and EASA dated November 30, 2017. This service
–233 airplanes; and Airbus SAS Model
issued AD 2013–0122 [which corresponds to information describes procedures for
A321–111, –112, –131, –211, –212,
FAA AD 2014–20–04], retaining the repetitive inspections for cracking of the
–213, –231, and –232 airplanes. AD
requirements of DGAC France AD 92–201– four titanium angles between the belly
2014–20–04 requires repetitive
030, which was superseded, and requiring fairing and the keel beam side panel, an
inspections for cracking of the four
repetitive detailed inspections (DET) of the inspection for cracking of the open
titanium angles between the belly
affected titanium angles and, depending on holes if any cracking is found in the
fairing and the keel beam side panel, an
findings, repair or replacement of parts. titanium angles, repair or replacement if
inspection for cracking of the open
After that [EASA] AD was issued, Airbus necessary, and a detailed inspection for
holes if any cracking is found in the
published Revision (Rev.) 01 and Rev. 02 of and replacement of certain rivets
titanium angles, and repair or
replacement if necessary. AD 2014–20– SB A320–53–1259. [Airbus SB A320–53– (including a rotating probe test for
04 resulted from reports of cracks at the 1259] Rev. 02 provided incorrect instructions cracks in the open holes).
lower riveting of the four titanium to use Part Number (P/N) EN6081D4 rivets Airbus also issued Service Bulletin
angles that connect the belly fairing to for the titanium angles installation, instead of A320–53–1014, Revision 2, dated
the keel beam side panels on both sides P/N EN6081D5 rivets. Consequently, Airbus September 1, 1994. This service
of the fuselage. We issued AD 2014–20– SB A320–53–1259 was updated (now at Rev. information describes procedures for
04 to address cracking of the titanium 03) including reference to the proper rivets. reinforcement (modification) of the
angles that connect the belly fairing to For the reason described above, this belly fairing structure.
[EASA] AD retains the requirements of EASA This service information is reasonably
the keel beam side panels on both sides
AD 2013–0122, which is superseded, and available because the interested parties
of the fuselage, which could affect the
requires additional work [a detailed have access to it through their normal
structural integrity of the airplane.
inspection for and replacement of certain course of business or by the means
Actions Since AD 2014–20–04 Was rivets, and applicable corrective actions] for identified in the ADDRESSES section.
Issued aeroplanes on which Airbus SB A320–53–
1259 at Rev. 02 was embodied. FAA’s Determination
The European Aviation Safety Agency
(EASA), which is the Technical Agent This product has been approved by
You may examine the MCAI in the
for the Member States of the European the aviation authority of another
AD docket on the internet at http://
Union, has issued EASA AD 2018–0091, country, and is approved for operation
www.regulations.gov by searching for
dated April 20, 2018 (referred to after in the United States. Pursuant to our
and locating Docket No. FAA–2018–
this as the Mandatory Continuing bilateral agreement with the State of
0795.
Airworthiness Information, or ‘‘the Design Authority, we have been notified
MCAI’’), to correct an unsafe condition Model A320–216 Airplanes of the unsafe condition described in the
for all Airbus SAS Model A318 series MCAI and service information
airplanes; Airbus SAS Model A319 The Airbus SAS Model A320–216 was referenced above. We are proposing this
series airplanes; Airbus SAS Model type certificated on December 19, 2016. AD because we evaluated all the
A320–211, –212, –214, –216, –231, Before that date, any EASA ADs that relevant information and determined
–232, and –233 airplanes; and Airbus affected Model A320–216 airplanes the unsafe condition described
SAS Model A321–111, –112, –131, were included on the Required previously is likely to exist or develop
–211, –212, –213, –231, and –232 Airworthiness Actions List (RAAL). One on other products of the same type
airplanes. The MCAI states: or more Model A320–216 airplanes have design.
subsequently been placed on the U.S.
During the fatigue test campaign of the Register, and will now be included in Proposed Requirements of This NPRM
A320 family type design, cracks were found
at the lower riveting of the four titanium
FAA AD actions. For Model A320–216 This proposed AD would retain all
angles which connect the belly fairing to the airplanes, the requirements that requirements of AD 2014–20–04. This
keel beam side panels between frames FR40 correspond to AD 2014–20–04 were proposed AD would also require
and FR42, on both sides of the fuselage. mandated by the MCAI via the RAAL. accomplishing the actions specified in
This condition, if not detected and Although that RAAL requirement is still the service information described
corrected, could affect the structural integrity in effect, for continuity and clarity we previously.
of the aeroplane. have identified Model A320–216
To address this potential unsafe condition, airplanes in paragraph (c) of this AD; Costs of Compliance
Airbus issued Service Bulletin (SB) A320–
53–1014, and DGAC [Direction Générale de the restated requirements of paragraphs We estimate that this proposed AD
l’Aviation Civile] France issued AD 92–201– (h) through (n) in this proposed AD affects 1,250 airplanes of U.S. registry.
030 [which corresponds to FAA AD 94–12– would therefore apply to those We estimate the following costs to
03, Amendment 39–8930 (59 FR 28763, June airplanes. comply with this proposed AD:
ESTIMATED COSTS
daltland on DSKBBV9HB2PROD with PROPOSALS
Cost per Cost on U.S.
Labor cost Parts cost product operators
295 work-hours × $85 per hour = $25,075 (Old actions of AD 2014–20–04) $1,045 $26,120 .......................... $32,650,000.
Up to 168 work-hours × $85 per hour = Up to $14,280 (New actions of this 0 Up to $14,280 ................ Up to $17,850,000.
AD).
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![Federal Register / Vol. 83, No. 180 / Monday, September 17, 2018 / Proposed Rules 46907
We estimate the following costs to do be required based on the results of the determining the number of aircraft that
any necessary replacement that would proposed inspection. We have no way of might need this replacement:
ESTIMATED COSTS OF ON-CONDITION ACTIONS
Cost per
Labor cost Parts cost * product
168 work-hours × $85 per hour = $14,280 ............................................................................................................. $0 $14,280
* We have received no definitive data that would enable us to provide cost estimates for the on-condition parts costs.
Authority for This Rulemaking 3. Will not affect intrastate aviation in (d) Subject
Alaska, and Air Transport Association (ATA) of
Title 49 of the United States Code
4. Will not have a significant America Code 53, Fuselage.
specifies the FAA’s authority to issue
rules on aviation safety. Subtitle I, economic impact, positive or negative, (e) Reason
section 106, describes the authority of on a substantial number of small entities This AD was prompted by reports of cracks
the FAA Administrator. Subtitle VII: under the criteria of the Regulatory at the lower riveting of the four titanium
Aviation Programs, describes in more Flexibility Act. angles that connect the belly fairing to the
detail the scope of the Agency’s keel beam side panels on both sides of the
List of Subjects in 14 CFR Part 39 fuselage. We are issuing this AD to detect and
authority. correct cracking of the titanium angles that
We are issuing this rulemaking under Air transportation, Aircraft, Aviation connect the belly fairing to the keel beam
the authority described in Subtitle VII, safety, Incorporation by reference, side panels on both sides of the fuselage,
Part A, Subpart III, Section 44701: Safety. which could affect the structural integrity of
‘‘General requirements.’’ Under that the airplane.
The Proposed Amendment
section, Congress charges the FAA with (f) Compliance
promoting safe flight of civil aircraft in Accordingly, under the authority Comply with this AD within the
air commerce by prescribing regulations delegated to me by the Administrator, compliance times specified, unless already
for practices, methods, and procedures the FAA proposes to amend 14 CFR part done.
the Administrator finds necessary for 39 as follows:
safety in air commerce. This regulation (g) Retained Modification, With No Changes
is within the scope of that authority PART 39—AIRWORTHINESS This paragraph restates the requirements of
because it addresses an unsafe condition DIRECTIVES paragraph (g) of AD 2014–20–04, with no
changes. For Model A320–111, –211, and
that is likely to exist or develop on
–231 series airplanes, manufacturer serial
products identified in this rulemaking ■ 1. The authority citation for part 39 numbers 003 through 092 inclusive: Prior to
action. continues to read as follows: the accumulation of 12,000 total landings on
This proposed AD is issued in Authority: 49 U.S.C. 106(g), 40113, 44701. the airplane, or within 300 days after January
accordance with authority delegated by 10, 1994 (the effective date of AD 93–24–11,
the Executive Director, Aircraft § 39.13 [Amended] Amendment 39–8760 (58 FR 64875,
Certification Service, as authorized by December 10, 1993)), whichever occurs later,
■ 2. The FAA amends § 39.13 by modify the belly fairing structure, in
FAA Order 8000.51C. In accordance
removing Airworthiness Directive (AD) accordance with the Accomplishment
with that order, issuance of ADs is Instructions of an Airbus service bulletin
2014–20–04, Amendment 39–17977 (79
normally a function of the Compliance specified in paragraph (g)(1), (g)(2), or (g)(3)
FR 59636, October 3, 2014), and adding
and Airworthiness Division, but during of this AD. As of the effective date of this AD,
the following new AD:
this transition period, the Executive use only the Airbus service bulletin specified
Director has delegated the authority to Airbus SAS: Docket No. FAA–2018–0795; in paragraph (g)(3) of this AD.
issue ADs applicable to transport Product Identifier 2018–NM–076–AD. (1) Airbus Industrie Service Bulletin A320–
category airplanes to the Director of the 53–1014, dated June 25, 1992.
(a) Comments Due Date
System Oversight Division. (2) Airbus Industrie Service Bulletin A320–
We must receive comments by November 53–1014, Revision 1, dated May 26, 1993.
Regulatory Findings 1, 2018. (3) Airbus Service Bulletin A320–53–1014,
(b) Affected ADs Revision 2, dated September 1, 1994.
We determined that this proposed AD
would not have federalism implications This AD replaces AD 2014–20–04, (h) Retained Repetitive Inspection, With
under Executive Order 13132. This Amendment 39–17977 (79 FR 59636, October Updated Service Information
proposed AD would not have a 3, 2014) (‘‘AD 2014–20–04’’). This paragraph restates the requirements of
substantial direct effect on the States, on paragraph (h) of AD 2014–20–04, with
(c) Applicability
updated service information. At the latest of
the relationship between the national This AD applies to the Airbus SAS the compliance times specified in paragraphs
Government and the States, or on the airplanes specified in paragraphs (c)(1), (h)(1), (h)(2), and (h)(3) of this AD: Do a
distribution of power and (c)(2), (c)(3), and (c)(4) of this AD, certificated detailed inspection for cracking of the four
responsibilities among the various in any category, all manufacturer serial titanium angles between the belly fairing and
daltland on DSKBBV9HB2PROD with PROPOSALS
levels of government. numbers. the keel beam side panel, in accordance with
For the reasons discussed above, I (1) Model A318–111, –112, –121, and –122 the Accomplishment Instructions of Airbus
certify this proposed regulation: airplanes. Service Bulletin A320–53–1259, dated
(2) Model A319–111, –112, –113, –114, November 6, 2012; or Airbus Service Bulletin
1. Is not a ‘‘significant regulatory
–115, –131, –132, and –133 airplanes. A320–53–1259, Revision 03, dated November
action’’ under Executive Order 12866, (3) Model A320–211, –212, –214, –216, 30, 2017. After the effective date of this AD
2. Is not a ‘‘significant rule’’ under the –231, –232, and –233 airplanes. only Airbus Service Bulletin A320–53–1259,
DOT Regulatory Policies and Procedures (4) Model A321–111, –112, –131, –211, Revision 03, dated November 30, 2017, may
(44 FR 11034, February 26, 1979), –212, –213, –231, and –232 airplanes. be used.
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![Federal Register / Vol. 83, No. 180 / Monday, September 17, 2018 / Proposed Rules 46909
(ii) AMOCs approved previously for AD as RC may be deviated from using accepted Moines, WA 98198; phone and fax 206–231–
2014–20–04, Amendment 39–17977 (79 FR methods in accordance with the operator’s 3223.
59636, October 3, 2014), are approved as maintenance or inspection program without (3) For service information identified in
AMOCs for the corresponding provisions of obtaining approval of an AMOC, provided this AD, contact Airbus SAS, Airworthiness
paragraphs (o) and (p) of this AD. the procedures and tests identified as RC can Office—EIAS, Rond-Point Emile Dewoitine
(2) Contacting the Manufacturer: As of the be done and the airplane can be put back in No: 2, 31700 Blagnac Cedex, France; phone:
effective date of this AD, for any requirement an airworthy condition. Any substitutions or +33 5 61 93 36 96; fax: +33 5 61 93 44 51;
in this AD to obtain corrective actions from changes to procedures or tests identified as email: account.airworth-eas@airbus.com;
a manufacturer, the action must be RC require approval of an AMOC. internet: http://www.airbus.com. You may
accomplished using a method approved by view this service information at the FAA,
the Manager, International Section, Transport (r) Related Information Transport Standards Branch, 2200 South
Standards Branch, FAA; or EASA; or Airbus (1) Refer to Mandatory Continuing 216th St., Des Moines, WA. For information
SAS’s EASA DOA. If approved by the DOA, Airworthiness Information (MCAI) EASA AD on the availability of this material at the
the approval must include the DOA- 2018–0091, dated April 20, 2018, for related FAA, call 206–231–3195.
authorized signature. information. This MCAI may be found in the Issued in Des Moines, Washington, on
(3) Required for Compliance (RC): If any AD docket on the internet at http:// August 29, 2018.
service information contains procedures or www.regulations.gov by searching for and Jeffrey E. Duven,
tests that are identified as RC, those locating Docket No. FAA–2018–0795.
procedures and tests must be done to comply (2) For more information about this AD, Director, System Oversight Division, Aircraft
with this AD; any procedures or tests that are contact Sanjay Ralhan, Aerospace Engineer, Certification Service.
not identified as RC are recommended. Those International Section, Transport Standards [FR Doc. 2018–19932 Filed 9–14–18; 8:45 am]
procedures and tests that are not identified Branch, FAA, 2200 South 216th St., Des BILLING CODE 4910–13–P
daltland on DSKBBV9HB2PROD with PROPOSALS
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Document Created: 2018-09-15 01:37:39
Document Modified: 2018-09-15 01:37:39
| 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 | Proposed Rules | |
| Action | Notice of proposed rulemaking (NPRM). | |
| Dates | We must receive comments on this proposed AD by November 1, 2018. | |
| Contact | Sanjay Ralhan, Aerospace Engineer, International Section, Transport Standards Branch, FAA, 2200 South 216th St., Des Moines, WA 98198; phone and fax 206-231-3223. | |
| FR Citation | 83 FR 46905 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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