80 FR 22943 - Airworthiness Directives; Airbus Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 80, Issue 79 (April 24, 2015)
Federal Aviation Administration
Federal Register Volume 80, Issue 79 (April 24, 2015)
| Page Range | 22943-22946 | |
| FR Document | 2015-09549 |
[Federal Register Volume 80, Number 79 (Friday, April 24, 2015)] [Proposed Rules] [Pages 22943-22946] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2015-09549] ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2015-0926; Directorate Identifier 2014-NM-121-AD] RIN 2120-AA64 Airworthiness Directives; Airbus Airplanes AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). ----------------------------------------------------------------------- SUMMARY: We propose to supersede Airworthiness Directive (AD) 97-07-14, for certain Airbus Model A320-111, -211, and -231 airplanes. AD 97-07- 14 currently requires modification of an area on the front spar of the wing center section by installing shims and new fasteners to reinforce pressure floor fittings. Since we issued AD 97-07-14, we have determined the need for repetitive inspections on airplanes on which the modification of the rib flange on the front spar of the wing center section has been done. This proposed AD would continue to require modifying the rib flange on the front spar of the wing center section by installing shims and new fasteners to reinforce pressure floor fittings; and would require repetitive high frequency eddy current inspections for cracking of the radius of the rib flanges and vertical stiffener at frame 36, a rototest inspection for cracking of the fastener holes of the rib flanges, repair if needed, and adding additional airplanes to the applicability. We are proposing this AD to prevent fatigue cracking on the rib flange area of the front spar of the wing center section, which can reduce the structural integrity of fuselage frame 36 and the wing center section. DATES: We must receive comments on this proposed AD by June 8, 2015. ADDRESSES: You may send comments 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: U.S. Department of Transportation, Docket Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue SE., Washington, DC, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For service information identified in this proposed AD, contact Airbus, Airworthiness Office--EIAS, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +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 Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425-227-1221. 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-2015- 0926; 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 proposed 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. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: Sanjay Ralhan, Aerospace Engineer, International Branch, ANM-116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057-3356; telephone 425-227-1405; fax 425-227-1149. SUPPLEMENTARY INFORMATION: Comments Invited We invite you to send any written relevant data, views, or arguments about this proposed AD. Send your comments to an address listed under the ADDRESSES section. Include ``Docket No. FAA-2015-0926; Directorate Identifier 2014-NM-121-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 On March 27, 1997, we issued AD 97-07-14, Amendment 39-9988 (62 FR 16473, April 7, 1997). AD 97-07-14 requires modification of an area on the front spar of the wing center section by installing shims and new fasteners to reinforce pressure floor fittings on certain Airbus Model A320-111, -211 and -231 airplanes. Since we issued AD 97-07-14, Amendment 39-9988 (62 FR 16473, April 7, 1997), we have determined the need for repetitive inspections on airplanes on which Airbus Modification 20976 (modification of the rib flange on the front spar of the wing center section) was done in production, or was done using Airbus Service Bulletin A320-57-1013, dated April 12, 1989; or Airbus Service Bulletin A320-57-1013, Revision 1, dated September 29, 1992. The European Aviation Safety Agency (EASA), which is the Technical Agent [[Page 22944]] for the Member States of the European Union, has issued EASA Airworthiness Directive 2014-0053, dated March 7, 2014 (referred to after this as the Mandatory Continuing Airworthiness Information, or ``the MCAI''), to correct an unsafe condition on certain Airbus Model A320-211 and -231 airplanes. The MCAI states: During full scale fatigue tests on the Airbus A320 test specimen, cracks were found in the rib flange on the front spar side perpendicular to vertical posts at frame (FR) 36. It was determined that similar cracks could develop on certain in-service aeroplanes. This condition, if not detected and corrected, could affect the wing structural integrity. To reduce the risk of crack initiation, two modifications for aeroplanes in production and one modification for in-service aeroplanes were developed by Airbus: Prior to [manufacturer serial number] MSN 0085, the adaptation modification (Mod) 20976 was applied in production, consisting in installing shims under the fasteners linking the rib flange, the lower corner, the front spar and its vertical stiffener; from MSN 0085 onwards, the serial Mod 20908 was applied in production, consisting in installing reinforced lower surface rib flanges at front spar level. Airbus issued Service Bulletin (SB) A320-57-1013 for affected in-service aeroplanes, and [Directorate General for Civil Aviation] DGAC France issued AD 95-098-066 [which corresponds to FAA AD 97-07- 14, Amendment 39-9988, (62 FR 16473, April 7, 1997)] to require installation of shims under the fasteners linking the rib flange, the lower corner, the front spar and its vertical stiffener. Following a recent analysis, Airbus identified the need for repetitive [HFEC and rototest] inspections for aeroplanes on which Airbus SB A320-57-1013 or production Mod 20976 has been embodied. For the reason described above, this [EASA] AD retains the requirements of DGAC France AD 95-098-066, which is superseded, and requires repetitive [HFEC and rototest] inspections of the center wing lower ribs at FR 36 and, depending on findings, accomplishment of a repair. After EASA issued PAD 14-013, it was discovered that additional work [removal of shims and fasteners on the rib flange on the front spar side and doing an HFEC inspection for cracking of the radius of the rib flanges and a rototest inspection for cracking of the fastener holes during each inspection] to be included in Revision 01 of Airbus SB A320-57-1175, is required to accomplish the inspections. This Final [EASA] AD has been amended accordingly. Airplanes having MSNs 001, 009, and 015 were not included in the applicability of AD 97-07-14, Amendment 39-9988 (62 FR 16473, April 7, 1997). EASA AD 2014-0053, dated March 7, 2014, expanded the applicability to all airplanes having up to MSN 0084. We included paragraph (h) of this proposed AD to require the modification for the airplanes having MSNs 001, 009, and 015.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-2015-0926. Related Service Information Under 1 CFR part 51 Airbus has issued Service Bulletin A320-57-1175, Revision 01, including Appendix 01 and Appendix 02, dated May 28, 2014. The service information describes procedures for repetitive high frequency eddy current inspections for cracking of the radius of the rib flanges and vertical stiffener at frame 36, a rototest inspection for cracking of the fastener holes of the rib flanges, and repair. The actions described in this service information are intended to correct the unsafe condition identified in the MCAI. This service information is reasonably available; see ADDRESSES for ways to access this service information. Explanation of ``RC'' Procedures and Tests in Service Information The FAA worked in conjunction with industry, under the Airworthiness Directives Implementation Aviation Rulemaking Committee (AD ARC), to enhance the AD system. One enhancement was a new process for annotating which procedures and tests in the service information are required for compliance with an AD. Differentiating these procedures and tests from other tasks in the service information is expected to improve an owner's/operator's understanding of crucial AD requirements and help provide consistent judgment in AD compliance. The actions specified in the service information identified previously include procedures and tests that are identified as RC (required for compliance) because these procedures have a direct effect on detecting, preventing, resolving, or eliminating an identified unsafe condition. As specified in a NOTE under the Accomplishment Instructions of the specified service information, procedures and tests identified as RC must be done to comply with the proposed AD. However, procedures and 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 alternative method of compliance (AMOC), provided the procedures and tests identified as RC can be done and the airplane can be put back in a serviceable condition. Any substitutions or changes to procedures or tests identified as RC will require approval of an AMOC. FAA's Determination and Requirements of This Proposed AD 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 pertinent information and determined an unsafe condition exists and is likely to exist or develop on other products of the same type design. Differences Between the AD and the MCAI or Service Information Although Airbus Service Bulletin A320-57-1175, Revision 01, including Appendix 01 and Appendix 02, dated May 28, 2014, specifies to contact the manufacturer for instructions on how to repair certain conditions, this proposed AD would require repairing those conditions using a method approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or EASA or its delegated agent, or Airbus' EASA Design Organization Approval (DOA). Costs of Compliance We estimate that this proposed AD affects 11 airplanes of U.S. registry. The actions required by AD 97-07-14, Amendment 39-9988 (62 FR 16473, April 7, 1997), and retained in this proposed AD take about 13 work-hours per product, at an average labor rate of $85 per work-hour. Required parts cost about $576 per product. Based on these figures, the estimated cost of the actions that are required by AD 97-07-14 is $1,681 per product. We also estimate that it would take about 45 work-hours per product to comply with the basic requirements of this proposed AD. The average labor rate is $85 per work-hour. Required parts would cost about $1,600 per product. Based on these figures, we estimate the cost of this proposed AD on U.S. operators to be $59,675, or $5,425 per product. 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: [[Page 22945]] 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 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) 97-07-14, Amendment 39-9988 (62 FR 16473, April 7, 1997), and adding the following new AD: Airbus: Docket No. FAA-2015-0926; Directorate Identifier 2014-NM- 121-AD. (a) Comments Due Date We must receive comments by June 8, 2015. (b) Affected ADs This AD replaces AD 97-07-14, Amendment 39-9988 (62 FR 16473, April 7, 1997). (c) Applicability This AD applies to Airbus Model A320-211 and -231 airplanes, certificated in any category, all manufacturer serial numbers (MSN) up to MSN 0084 inclusive. (d) Subject Air Transport Association (ATA) of America Code 57, Wings. (e) Reason This AD was prompted by the determination that repetitive inspections are needed on airplanes on which the modification of the rib flange on the front spar of the wing center section has been done. We are issuing this AD to prevent fatigue cracking on the rib flange area of the front spar of the wing center section, which can reduce the structural integrity of fuselage frame 36 and the wing center section. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Retained Modification This paragraph restates the requirements of paragraph (a) of AD 97-07-14, Amendment 39-9988 (62 FR 16473, April 7, 1997). For airplanes with manufacturer serial number (MSN) 005 through 008 inclusive, MSN 010 through 014 inclusive, and MSN 016 through 042 inclusive: Prior to the accumulation of 16,000 total landings, or within 3 months after May 12, 1997 (the effective date of AD 97-07- 14), whichever occurs later, modify the rib flange on the front spar of the wing center section by installing shims and new fasteners to reinforce pressure floor fittings, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-57-1013, Revision 1, dated September 29, 1992. (h) Modification for Airplanes With MSNs 001, 009, and 015 Prior to the accumulation of 16,000 total landings since first flight, or within 30 days after the effective date of this AD, whichever occurs later, modify the rib flange on the front spar of the wing center section by installing shims and new fasteners to reinforce pressure floor fittings, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-57-1013, Revision 1, dated September 29, 1992. (i) New Requirement of This AD: Repetitive Inspections Within the applicable compliance times specified in paragraphs (i)(1) and (i)(2) of this AD, do a high frequency eddy current (HFEC) inspection for cracking of the radius of the rib flanges and vertical stiffener at frame 36 and do a rototest inspection for cracking of the fastener holes of the rib flanges and vertical stiffener, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-57-1175, Revision 01, including Appendix 01, dated May 28, 2014. During each inspection, remove the shims and fasteners on the rib flange on the front spar side and do an HFEC inspection for cracking of the radius of the rib flanges and a rototest inspection for cracking of the fastener holes. If no cracking is found, oversize the holes of the rib flange and the holes of the shims, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-57-1175, Revision 01, including Appendix 01, dated May 28, 2014. Repeat the inspections thereafter at intervals not to exceed 32,500 flight cycles or 65,000 flight hours, whichever occurs first. (1) For airplanes having Airbus Modification 20976 embodied: At the later of the times specified in paragraphs (i)(1)(i) or (i)(1)(ii) of this AD. (i) Before exceeding 47,800 flight cycles or 95,600 flight hours, whichever occurs first, since the airplane's first flight. (ii) Within 850 flight cycles or 1,700 flight hours, whichever occurs first, after the effective date of this AD. (2) For airplanes on which the modification of the front spar of the wing center section was accomplished using Airbus Service Bulletin A320-57-1013, Revision 1, dated September 29, 1992: At the later of the times specified in paragraphs (i)(2)(i) or (i)(2)(ii) of this AD. (i) Before exceeding 10,700 flight cycles or 21,500 flight hours, whichever occurs first, after the modification of the rib flange on the front spar of the wing center section was done using Airbus Service Bulletin A320-57-1013, Revision 1, dated September 29, 1992. (ii) Within 850 flight cycles or 1,700 flight hours, whichever occurs first, after the effective date of this AD. (j) Repair If, during any inspection required by paragraph (i) of this AD, any cracking is found, before further flight, repair 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). (k) Credit for Previous Actions This paragraph restates the requirements of Note 2 of paragraph (g) of AD 97-07-14, Amendment 39-9988 (62 FR 16473, April 7, 1997): This paragraph provides credit for the modification of the rib flange required by paragraph (g) of this AD, if those actions were performed before May 12, 1997 (the effective date of AD 97-07-14) using Airbus Service Bulletin A320-57-1013, dated April 12, 1989. (l) Other FAA AD Provisions The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, International [[Page 22946]] Branch, ANM-116, Transport Airplane Directorate, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the International Branch, send it to ATTN: Sanjay Ralhan, Aerospace Engineer, International Branch, ANM-116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057- 3356; telephone 425-227-1405; 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: 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 Branch, ANM-116, Transport Airplane Directorate, FAA; or EASA; or Airbus's EASA DOA. If approved by the DOA, the approval must include the DOA-authorized signature. (3) Required for Compliance (RC): Except as required by paragraph (j) of this AD, if the 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 and 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 a serviceable condition. Any substitutions or changes to procedures or tests identified as RC require approval of an AMOC. (m) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA Airworthiness Directive 2014-0053, dated March 7, 2014, 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-2015-0926. (2) For service information identified in this AD, contact Airbus, Airworthiness Office--EIAS, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +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 Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425-227-1221. Issued in Renton, Washington, on April 6, 2015. John P. Piccola, Jr., Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2015-09549 Filed 4-23-15; 8:45 am] BILLING CODE 4910-13-P
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the DOA, the approval must include the currently requires modification of an 0926; or in person at the Docket
DOA-authorized signature. area on the front spar of the wing center Management Facility between 9 a.m.
(n) Special Flight Permits section by installing shims and new and 5 p.m., Monday through Friday,
Special flight permits may be issued in
fasteners to reinforce pressure floor except Federal holidays. The AD docket
accordance with sections 21.197 and 21.199 fittings. Since we issued AD 97–07–14, contains this proposed AD, the
of the Federal Aviation Regulations (14 CFR we have determined the need for regulatory evaluation, any comments
21.197 and 21.199) to operate the airplane to repetitive inspections on airplanes on received, and other information. The
a location where the airplane can be which the modification of the rib flange street address for the Docket Operations
modified (if the operator elects to do so), on the front spar of the wing center office (telephone 800–647–5527) is in
provided the MLG remains extended section has been done. This proposed the ADDRESSES section. Comments will
throughout the flight. AD would continue to require be available in the AD docket shortly
(o) Related Information modifying the rib flange on the front after receipt.
(1) Refer to Mandatory Continuing spar of the wing center section by FOR FURTHER INFORMATION CONTACT:
Airworthiness Information (MCAI) European installing shims and new fasteners to Sanjay Ralhan, Aerospace Engineer,
Aviation Safety Agency (EASA) reinforce pressure floor fittings; and International Branch, ANM–116,
Airworthiness Directive 2014–0058, dated would require repetitive high frequency Transport Airplane Directorate, FAA,
March 11, 2014, for related information. This eddy current inspections for cracking of 1601 Lind Avenue SW., Renton, WA
MCAI may be found in the AD docket on the the radius of the rib flanges and vertical 98057–3356; telephone 425–227–1405;
Internet at http://www.regulations.gov by stiffener at frame 36, a rototest
searching for and locating Docket No. FAA–
fax 425–227–1149.
inspection for cracking of the fastener SUPPLEMENTARY INFORMATION:
2015–0831.
(2) For Airbus service information
holes of the rib flanges, repair if needed,
identified in this AD, contact Airbus, and adding additional airplanes to the Comments Invited
Airworthiness Office—EIAS, 1 Rond Point applicability. We are proposing this AD We invite you to send any written
Maurice Bellonte, 31707 Blagnac Cedex, to prevent fatigue cracking on the rib relevant data, views, or arguments about
France; telephone +33 5 61 93 36 96; fax +33 flange area of the front spar of the wing this proposed AD. Send your comments
5 61 93 44 51; email account.airworth-eas@ center section, which can reduce the to an address listed under the
airbus.com; Internet http://www.airbus.com. structural integrity of fuselage frame 36 ADDRESSES section. Include ‘‘Docket No.
(3) For Messier-Bugatti-Dowty service and the wing center section.
information identified in this AD, contact FAA–2015–0926; Directorate Identifier
Messier Services Americas, Customer DATES: We must receive comments on 2014–NM–121–AD’’ at the beginning of
Support Center, 45360 Severn Way, Sterling, this proposed AD by June 8, 2015. your comments. We specifically invite
VA 20166 8910; phone: 703–450–8233; fax: ADDRESSES: You may send comments by comments on the overall regulatory,
703–404–1621; Internet: https:// any of the following methods: economic, environmental, and energy
techpubs.services/messier-dowty.com. • Federal eRulemaking Portal: Go to aspects of this proposed AD. We will
(4) You may view this service information http://www.regulations.gov. Follow the consider all comments received by the
at the FAA, Transport Airplane Directorate, closing date and may amend this
instructions for submitting comments.
1601 Lind Avenue SW., Renton, WA. For
information on the availability of this • Fax: 202–493–2251. proposed AD based on those comments.
material at the FAA, call 425–227–1221. • Mail: U.S. Department of We will post all comments we
Transportation, Docket Operations, M– receive, without change, to http://
Issued in Renton, Washington, on April 9, 30, West Building Ground Floor, Room www.regulations.gov, including any
2015. W12–140, 1200 New Jersey Avenue SE., personal information you provide. We
Jeffrey E. Duven, Washington, DC 20590. will also post a report summarizing each
Manager, Transport Airplane Directorate, • Hand Delivery: U.S. Department of substantive verbal contact we receive
Aircraft Certification Service. Transportation, Docket Operations, M– about this proposed AD.
[FR Doc. 2015–09288 Filed 4–23–15; 8:45 am] 30, West Building Ground Floor, Room
Discussion
BILLING CODE 4910–13–P W12–140, 1200 New Jersey Avenue SE.,
Washington, DC, between 9 a.m. and 5 On March 27, 1997, we issued AD 97–
p.m., Monday through Friday, except 07–14, Amendment 39–9988 (62 FR
DEPARTMENT OF TRANSPORTATION Federal holidays. 16473, April 7, 1997). AD 97–07–14
For service information identified in requires modification of an area on the
Federal Aviation Administration this proposed AD, contact Airbus, front spar of the wing center section by
Airworthiness Office—EIAS, 1 Rond installing shims and new fasteners to
14 CFR Part 39 Point Maurice Bellonte, 31707 Blagnac reinforce pressure floor fittings on
[Docket No. FAA–2015–0926; Directorate Cedex, France; telephone +33 5 61 93 36 certain Airbus Model A320–111, –211
Identifier 2014–NM–121–AD] 96; fax +33 5 61 93 44 51; email and –231 airplanes.
account.airworth-eas@airbus.com; Since we issued AD 97–07–14,
RIN 2120–AA64 Internet http://www.airbus.com. You Amendment 39–9988 (62 FR 16473,
may view this referenced service April 7, 1997), we have determined the
Airworthiness Directives; Airbus
information at the FAA, Transport need for repetitive inspections on
Airplanes
Airplane Directorate, 1601 Lind Avenue airplanes on which Airbus Modification
AGENCY: Federal Aviation SW., Renton, WA. For information on 20976 (modification of the rib flange on
tkelley on DSK3SPTVN1PROD with PROPOSALS
Administration (FAA), DOT. the availability of this material at the the front spar of the wing center section)
ACTION: Notice of proposed rulemaking FAA, call 425–227–1221. was done in production, or was done
(NPRM). using Airbus Service Bulletin A320–57–
Examining the AD Docket 1013, dated April 12, 1989; or Airbus
SUMMARY: We propose to supersede You may examine the AD docket on Service Bulletin A320–57–1013,
Airworthiness Directive (AD) 97–07–14, the Internet at http:// Revision 1, dated September 29, 1992.
for certain Airbus Model A320–111, www.regulations.gov by searching for The European Aviation Safety Agency
–211, and –231 airplanes. AD 97–07–14 and locating Docket No. FAA–2015– (EASA), which is the Technical Agent
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for the Member States of the European (h) of this proposed AD to require the the airplane can be put back in a
Union, has issued EASA Airworthiness modification for the airplanes having serviceable condition. Any substitutions
Directive 2014–0053, dated March 7, MSNs 001, 009, and 015.You may or changes to procedures or tests
2014 (referred to after this as the examine the MCAI in the AD docket on identified as RC will require approval of
Mandatory Continuing Airworthiness the Internet at http:// an AMOC.
Information, or ‘‘the MCAI’’), to correct www.regulations.gov by searching for
and locating Docket No. FAA–2015– FAA’s Determination and Requirements
an unsafe condition on certain Airbus
0926. of This Proposed AD
Model A320–211 and –231 airplanes.
The MCAI states: This product has been approved by
Related Service Information Under 1 the aviation authority of another
During full scale fatigue tests on the Airbus CFR part 51
A320 test specimen, cracks were found in the country, and is approved for operation
rib flange on the front spar side Airbus has issued Service Bulletin in the United States. Pursuant to our
perpendicular to vertical posts at frame (FR) A320–57–1175, Revision 01, including bilateral agreement with the State of
36. It was determined that similar cracks Appendix 01 and Appendix 02, dated Design Authority, we have been notified
could develop on certain in-service May 28, 2014. The service information of the unsafe condition described in the
aeroplanes. describes procedures for repetitive high MCAI and service information
This condition, if not detected and frequency eddy current inspections for referenced above. We are proposing this
corrected, could affect the wing structural cracking of the radius of the rib flanges
integrity. AD because we evaluated all pertinent
To reduce the risk of crack initiation, two
and vertical stiffener at frame 36, a information and determined an unsafe
modifications for aeroplanes in production rototest inspection for cracking of the condition exists and is likely to exist or
and one modification for in-service fastener holes of the rib flanges, and develop on other products of the same
aeroplanes were developed by Airbus: Prior repair. The actions described in this type design.
to [manufacturer serial number] MSN 0085, service information are intended to
the adaptation modification (Mod) 20976 was correct the unsafe condition identified Differences Between the AD and the
applied in production, consisting in in the MCAI. This service information is MCAI or Service Information
installing shims under the fasteners linking reasonably available; see ADDRESSES for Although Airbus Service Bulletin
the rib flange, the lower corner, the front spar
and its vertical stiffener; from MSN 0085
ways to access this service information. A320–57–1175, Revision 01, including
onwards, the serial Mod 20908 was applied Explanation of ‘‘RC’’ Procedures and Appendix 01 and Appendix 02, dated
in production, consisting in installing Tests in Service Information May 28, 2014, specifies to contact the
reinforced lower surface rib flanges at front manufacturer for instructions on how to
spar level. The FAA worked in conjunction with repair certain conditions, this proposed
Airbus issued Service Bulletin (SB) A320– industry, under the Airworthiness AD would require repairing those
57–1013 for affected in-service aeroplanes, Directives Implementation Aviation conditions using a method approved by
and [Directorate General for Civil Aviation] Rulemaking Committee (AD ARC), to
DGAC France issued AD 95–098–066 [which
the Manager, International Branch,
enhance the AD system. One ANM–116, Transport Airplane
corresponds to FAA AD 97–07–14, enhancement was a new process for
Amendment 39–9988, (62 FR 16473, April 7, Directorate, FAA; or EASA or its
1997)] to require installation of shims under
annotating which procedures and tests delegated agent, or Airbus’ EASA
the fasteners linking the rib flange, the lower in the service information are required Design Organization Approval (DOA).
corner, the front spar and its vertical for compliance with an AD.
stiffener. Differentiating these procedures and Costs of Compliance
Following a recent analysis, Airbus tests from other tasks in the service We estimate that this proposed AD
identified the need for repetitive [HFEC and information is expected to improve an affects 11 airplanes of U.S. registry.
rototest] inspections for aeroplanes on which owner’s/operator’s understanding of The actions required by AD 97–07–14,
Airbus SB A320–57–1013 or production Mod crucial AD requirements and help
20976 has been embodied.
Amendment 39–9988 (62 FR 16473,
provide consistent judgment in AD April 7, 1997), and retained in this
For the reason described above, this
[EASA] AD retains the requirements of DGAC compliance. The actions specified in the proposed AD take about 13 work-hours
France AD 95–098–066, which is superseded, service information identified per product, at an average labor rate of
and requires repetitive [HFEC and rototest] previously include procedures and tests $85 per work-hour. Required parts cost
inspections of the center wing lower ribs at that are identified as RC (required for about $576 per product. Based on these
FR 36 and, depending on findings, compliance) because these procedures figures, the estimated cost of the actions
accomplishment of a repair. have a direct effect on detecting, that are required by AD 97–07–14 is
After EASA issued PAD 14–013, it was preventing, resolving, or eliminating an
discovered that additional work [removal of
$1,681 per product.
identified unsafe condition. We also estimate that it would take
shims and fasteners on the rib flange on the
front spar side and doing an HFEC inspection
As specified in a NOTE under the about 45 work-hours per product to
for cracking of the radius of the rib flanges Accomplishment Instructions of the comply with the basic requirements of
and a rototest inspection for cracking of the specified service information, this proposed AD. The average labor
fastener holes during each inspection] to be procedures and tests identified as RC rate is $85 per work-hour. Required
included in Revision 01 of Airbus SB A320– must be done to comply with the parts would cost about $1,600 per
57–1175, is required to accomplish the proposed AD. However, procedures and product. Based on these figures, we
inspections. This Final [EASA] AD has been tests that are not identified as RC are estimate the cost of this proposed AD on
amended accordingly. recommended. Those procedures and U.S. operators to be $59,675, or $5,425
tkelley on DSK3SPTVN1PROD with PROPOSALS
Airplanes having MSNs 001, 009, and tests that are not identified as RC may per product.
015 were not included in the be deviated from using accepted
applicability of AD 97–07–14, methods in accordance with the Authority for This Rulemaking
Amendment 39–9988 (62 FR 16473, operator’s maintenance or inspection Title 49 of the United States Code
April 7, 1997). EASA AD 2014–0053, program without obtaining approval of specifies the FAA’s authority to issue
dated March 7, 2014, expanded the an alternative method of compliance rules on aviation safety. Subtitle I,
applicability to all airplanes having up (AMOC), provided the procedures and section 106, describes the authority of
to MSN 0084. We included paragraph tests identified as RC can be done and the FAA Administrator. ‘‘Subtitle VII:
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![Federal Register / Vol. 80, No. 79 / Friday, April 24, 2015 / Proposed Rules 22945
Aviation Programs,’’ describes in more Airbus: Docket No. FAA–2015–0926; inspection for cracking of the radius of the
detail the scope of the Agency’s Directorate Identifier 2014–NM–121–AD. rib flanges and vertical stiffener at frame 36
authority. and do a rototest inspection for cracking of
(a) Comments Due Date the fastener holes of the rib flanges and
We are issuing this rulemaking under We must receive comments by June 8, vertical stiffener, in accordance with the
the authority described in ‘‘Subtitle VII, 2015. Accomplishment Instructions of Airbus
Part A, Subpart III, Section 44701: Service Bulletin A320–57–1175, Revision 01,
General requirements.’’ Under that (b) Affected ADs
including Appendix 01, dated May 28, 2014.
section, Congress charges the FAA with This AD replaces AD 97–07–14, During each inspection, remove the shims
promoting safe flight of civil aircraft in Amendment 39–9988 (62 FR 16473, April 7, and fasteners on the rib flange on the front
air commerce by prescribing regulations 1997). spar side and do an HFEC inspection for
for practices, methods, and procedures (c) Applicability cracking of the radius of the rib flanges and
a rototest inspection for cracking of the
the Administrator finds necessary for This AD applies to Airbus Model A320– fastener holes. If no cracking is found,
safety in air commerce. This regulation 211 and –231 airplanes, certificated in any oversize the holes of the rib flange and the
is within the scope of that authority category, all manufacturer serial numbers holes of the shims, in accordance with the
because it addresses an unsafe condition (MSN) up to MSN 0084 inclusive. Accomplishment Instructions of Airbus
that is likely to exist or develop on (d) Subject Service Bulletin A320–57–1175, Revision 01,
products identified in this rulemaking including Appendix 01, dated May 28, 2014.
Air Transport Association (ATA) of Repeat the inspections thereafter at intervals
action. America Code 57, Wings. not to exceed 32,500 flight cycles or 65,000
Regulatory Findings (e) Reason flight hours, whichever occurs first.
(1) For airplanes having Airbus
We determined that this proposed AD This AD was prompted by the Modification 20976 embodied: At the later of
would not have federalism implications determination that repetitive inspections are the times specified in paragraphs (i)(1)(i) or
under Executive Order 13132. This needed on airplanes on which the (i)(1)(ii) of this AD.
proposed AD would not have a modification of the rib flange on the front (i) Before exceeding 47,800 flight cycles or
substantial direct effect on the States, on spar of the wing center section has been 95,600 flight hours, whichever occurs first,
done. We are issuing this AD to prevent since the airplane’s first flight.
the relationship between the national fatigue cracking on the rib flange area of the
Government and the States, or on the (ii) Within 850 flight cycles or 1,700 flight
front spar of the wing center section, which hours, whichever occurs first, after the
distribution of power and can reduce the structural integrity of fuselage effective date of this AD.
responsibilities among the various frame 36 and the wing center section. (2) For airplanes on which the
levels of government. modification of the front spar of the wing
(f) Compliance
For the reasons discussed above, I center section was accomplished using
certify this proposed regulation: Comply with this AD within the Airbus Service Bulletin A320–57–1013,
1. Is not a ‘‘significant regulatory compliance times specified, unless already Revision 1, dated September 29, 1992: At the
done. later of the times specified in paragraphs
action’’ under Executive Order 12866;
2. Is not a ‘‘significant rule’’ under the (g) Retained Modification (i)(2)(i) or (i)(2)(ii) of this AD.
DOT Regulatory Policies and Procedures (i) Before exceeding 10,700 flight cycles or
This paragraph restates the requirements of
(44 FR 11034, February 26, 1979); 21,500 flight hours, whichever occurs first,
paragraph (a) of AD 97–07–14, Amendment
after the modification of the rib flange on the
3. Will not affect intrastate aviation in 39–9988 (62 FR 16473, April 7, 1997). For front spar of the wing center section was
Alaska; and airplanes with manufacturer serial number done using Airbus Service Bulletin A320–
4. Will not have a significant (MSN) 005 through 008 inclusive, MSN 010 57–1013, Revision 1, dated September 29,
economic impact, positive or negative, through 014 inclusive, and MSN 016 through 1992.
on a substantial number of small entities 042 inclusive: Prior to the accumulation of (ii) Within 850 flight cycles or 1,700 flight
16,000 total landings, or within 3 months hours, whichever occurs first, after the
under the criteria of the Regulatory after May 12, 1997 (the effective date of AD
Flexibility Act. effective date of this AD.
97–07–14), whichever occurs later, modify
List of Subjects in 14 CFR Part 39 the rib flange on the front spar of the wing (j) Repair
center section by installing shims and new If, during any inspection required by
Air transportation, Aircraft, Aviation fasteners to reinforce pressure floor fittings, paragraph (i) of this AD, any cracking is
safety, Incorporation by reference, in accordance with the Accomplishment found, before further flight, repair using a
Safety. Instructions of Airbus Service Bulletin A320– method approved by the Manager,
57–1013, Revision 1, dated September 29, International Branch, ANM–116, Transport
The Proposed Amendment 1992. Airplane Directorate, FAA; or the European
Accordingly, under the authority (h) Modification for Airplanes With MSNs Aviation Safety Agency (EASA); or Airbus’s
delegated to me by the Administrator, 001, 009, and 015 EASA Design Organization Approval (DOA).
the FAA proposes to amend 14 CFR part Prior to the accumulation of 16,000 total (k) Credit for Previous Actions
39 as follows: landings since first flight, or within 30 days This paragraph restates the requirements of
after the effective date of this AD, whichever Note 2 of paragraph (g) of AD 97–07–14,
PART 39—AIRWORTHINESS occurs later, modify the rib flange on the Amendment 39–9988 (62 FR 16473, April 7,
DIRECTIVES front spar of the wing center section by 1997): This paragraph provides credit for the
installing shims and new fasteners to modification of the rib flange required by
■ 1. The authority citation for part 39 reinforce pressure floor fittings, in paragraph (g) of this AD, if those actions were
continues to read as follows: accordance with the Accomplishment performed before May 12, 1997 (the effective
Instructions of Airbus Service Bulletin A320–
tkelley on DSK3SPTVN1PROD with PROPOSALS
Authority: 49 U.S.C. 106(g), 40113, 44701. date of AD 97–07–14) using Airbus Service
57–1013, Revision 1, dated September 29, Bulletin A320–57–1013, dated April 12,
§ 39.13 [Amended] 1992. 1989.
■ 2. The FAA amends § 39.13 by (i) New Requirement of This AD: Repetitive (l) Other FAA AD Provisions
removing Airworthiness Directive (AD) Inspections The following provisions also apply to this
97–07–14, Amendment 39–9988 (62 FR Within the applicable compliance times AD:
16473, April 7, 1997), and adding the specified in paragraphs (i)(1) and (i)(2) of this (1) Alternative Methods of Compliance
following new AD: AD, do a high frequency eddy current (HFEC) (AMOCs): The Manager, International
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![22946 Federal Register / Vol. 80, No. 79 / Friday, April 24, 2015 / Proposed Rules
Branch, ANM–116, Transport Airplane Issued in Renton, Washington, on April 6, NARA, call 202–741–6030, or go to
Directorate, FAA, has the authority to 2015. http://www.archives.gov/federal_
approve AMOCs for this AD, if requested John P. Piccola, Jr., register/code_of_federal-regulations/ibr_
using the procedures found in 14 CFR 39.19. Acting Manager, Transport Airplane locations.html.
In accordance with 14 CFR 39.19, send your Directorate, Aircraft Certification Service. FAA Order 7400.9, Airspace
request to your principal inspector or local [FR Doc. 2015–09549 Filed 4–23–15; 8:45 am] Designations and Reporting Points, is
Flight Standards District Office, as published yearly and effective on
BILLING CODE 4910–13–P
appropriate. If sending information directly
September 15. For further information,
to the International Branch, send it to ATTN:
you can contact the Airspace Policy and
Sanjay Ralhan, Aerospace Engineer,
DEPARTMENT OF TRANSPORTATION Regulations Group, Federal Aviation
International Branch, ANM–116, Transport
Airplane Directorate, FAA, 1601 Lind Administration, 800 Independence
Federal Aviation Administration Avenue, SW., Washington, DC, 20591;
Avenue SW., Renton, WA 98057–3356;
telephone 425–227–1405; fax 425–227–1149. telephone: 202–267–8783.
14 CFR Part 71
Information may be emailed to: 9-ANM-116- FOR FURTHER INFORMATION CONTACT: John
AMOC-REQUESTS@faa.gov. Before using [Docket No. FAA–2015–0046; Airspace Fornito, Operations Support Group,
any approved AMOC, notify your appropriate Docket No. 14–ASO–23] Eastern Service Center, Federal Aviation
principal inspector, or lacking a principal Administration, P.O. Box 20636,
inspector, the manager of the local flight Proposed Establishment of Class E Atlanta, Georgia 30320; telephone (404)
standards district office/certificate holding Airspace; Headland, AL 305–6364.
district office. The AMOC approval letter
AGENCY: Federal Aviation SUPPLEMENTARY INFORMATION:
must specifically reference this AD.
(2) Contacting the Manufacturer: As of the
Administration (FAA), DOT.
Comments Invited
effective date of this AD, for any requirement ACTION: Notice of proposed rulemaking
in this AD to obtain corrective actions from (NPRM). Interested persons are invited to
a manufacturer, the action must be comment on this rule by submitting
SUMMARY: This action proposes to such written data, views, or arguments,
accomplished using a method approved by
the Manager, International Branch, ANM–
establish Class E Airspace at Headland, as they may desire. Comments that
116, Transport Airplane Directorate, FAA; or AL, to accommodate new Area provide the factual basis supporting the
EASA; or Airbus’s EASA DOA. If approved Navigation (RNAV) Global Positioning views and suggestions presented are
by the DOA, the approval must include the System (GPS) Standard Instrument particularly helpful in developing
DOA-authorized signature. Approach Procedures (SIAPs) serving reasoned regulatory decisions on the
(3) Required for Compliance (RC): Except Headland Municipal Airport. Controlled proposal. Comments are specifically
as required by paragraph (j) of this AD, if the airspace is necessary for the safety and invited on the overall regulatory,
service information contains procedures or management of instrument flight rules aeronautical, economic, environmental,
tests that are identified as RC, those (IFR) operations at the airport. and energy-related aspects of the
procedures and tests must be done to comply DATES: 0901 UTC. Comments must be proposal.
with this AD; any procedures and tests that received on or before June 8, 2015. Communications should identify both
are not identified as RC are recommended. ADDRESSES: Send comments on this rule docket numbers (FAA Docket No. FAA–
Those procedures and tests that are not 2015–0046; Airspace Docket No. 14–
to: U. S. Department of Transportation,
identified as RC may be deviated from using
Docket Operations, West Building ASO–23) and be submitted in triplicate
accepted methods in accordance with the
Ground Floor, Room W12–140, 1200 to the Docket Management System (see
operator’s maintenance or inspection
New Jersey, SE., Washington, DC ADDRESSES section for address and
program without obtaining approval of an
AMOC, provided the procedures and tests 20590–0001; Telephone: 1–800–647– phone number). You may also submit
identified as RC can be done and the airplane 5527; Fax: 202–493–2251. You must comments through the Internet at http://
can be put back in a serviceable condition. identify the Docket Number FAA–2015– www.regulations.gov.
Any substitutions or changes to procedures 0046; Airspace Docket No. 14–ASO–23, Persons wishing the FAA to
or tests identified as RC require approval of at the beginning of your comments. You acknowledge receipt of their comments
an AMOC. may also submit and review received on this action must submit with those
comments through the Internet at comments a self-addressed stamped
(m) Related Information
http://www.regulations.gov. postcard on which the following
(1) Refer to Mandatory Continuing You may review the public docket statement is made: ‘‘Comments to
Airworthiness Information (MCAI) EASA containing the proposal, any comments Docket No. FAA–2015–0046; Airspace
Airworthiness Directive 2014–0053, dated received, and any final disposition in Docket No. 14–ASO–23.’’ The postcard
March 7, 2014, for related information. This person in the Dockets Office between will be date/time stamped and returned
MCAI may be found in the AD docket on the 9:00 a.m. and 5:00 p.m., Monday to the commenter.
Internet at http://www.regulations.gov by
through Friday, except Federal holidays. All communications received before
searching for and locating Docket No. FAA–
The Docket Office (telephone 1–800– the specified closing date for comments
2015–0926.
(2) For service information identified in
647–5527), is on the ground floor of the will be considered before taking action
this AD, contact Airbus, Airworthiness building at the above address. on the proposed rule. The proposal
Office—EIAS, 1 Rond Point Maurice
FAA Order 7400.9Y, Airspace contained in this notice may be changed
Bellonte, 31707 Blagnac Cedex, France; Designations and Reporting Points, and in light of the comments received. A
tkelley on DSK3SPTVN1PROD with PROPOSALS
telephone +33 5 61 93 36 96; fax +33 5 61 subsequent amendments can be viewed report summarizing each substantive
93 44 51; email account.airworth-eas@ online at http://www.faa.gov/air_traffic/ public contact with FAA personnel
airbus.com; Internet http://www.airbus.com. publications/. The Order is also concerned with this rulemaking will be
You may view this service information at the available for inspection at the National filed in the docket.
FAA, Transport Airplane Directorate, 1601 Archives and Records Administration
(NARA). For information on the Availability of NPRMs
Lind Avenue SW., Renton, WA. For
information on the availability of this availability of this proposed An electronic copy of this document
material at the FAA, call 425–227–1221. incorporation by reference material at may be downloaded from and
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Document Created: 2015-12-16 08:43:02
Document Modified: 2015-12-16 08:43:02
| 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 June 8, 2015. | |
| Contact | Sanjay Ralhan, Aerospace Engineer, International Branch, ANM-116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057-3356; telephone 425-227-1405; fax 425-227-1149. | |
| FR Citation | 80 FR 22943 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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