80 FR 58226 - Airworthiness Directives; Airbus Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 80, Issue 187 (September 28, 2015)
Federal Aviation Administration
Federal Register Volume 80, Issue 187 (September 28, 2015)
| Page Range | 58226-58229 | |
| FR Document | 2015-24423 |
[Federal Register Volume 80, Number 187 (Monday, September 28, 2015)] [Proposed Rules] [Pages 58226-58229] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2015-24423] ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2015-3635; Directorate Identifier 2015-NM-037-AD] RIN 2120-AA64 Airworthiness Directives; Airbus Airplanes AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). ----------------------------------------------------------------------- SUMMARY: We propose to adopt a new airworthiness directive (AD) for all Airbus Model A318, A319, A320, and A321 series airplanes. This proposed AD was prompted by an evaluation by the design approval holder (DAH) indicating that the fuselage skin repairs are subject to widespread fatigue damage (WFD). This proposed AD would require an inspection to determine whether any fuselage external skin (doubler) repairs have been accomplished, an inspection for cracking of certain repaired external fuselage skin areas in the fuselage, and repair if necessary. We are proposing this AD to detect and correct fatigue cracking of the fuselage skin, which could result in reduced structural integrity of the airplane. DATES: We must receive comments on this proposed AD by November 12, 2015. 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: 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- 3635; 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-2015-3635; Directorate Identifier 2015-NM-037-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 Structural fatigue damage is progressive. It begins as minute cracks, and those cracks grow under the action of repeated stresses. This can happen because of normal operational conditions and design attributes, or because of isolated situations or incidents such as material defects, poor fabrication quality, or corrosion pits, dings, or scratches. Fatigue damage can occur locally, in small areas or structural design details, or globally. [[Page 58227]] Global fatigue damage is general degradation of large areas of structure with similar structural details and stress levels. Multiple- site damage is global damage that occurs in a large structural element such as a single rivet line of a lap splice joining two large skin panels. Global damage can also occur in multiple elements such as adjacent frames or stringers. Multiple-site-damage and multiple- element-damage cracks are typically too small initially to be reliably detected with normal inspection methods. Without intervention, these cracks will grow, and eventually compromise the structural integrity of the airplane, in a condition known as widespread fatigue damage (WFD). As an airplane ages, WFD will likely occur, and will certainly occur if the airplane is operated long enough without any intervention. The FAA's WFD final rule (75 FR 69746, November 15, 2010) became effective on January 14, 2011. The WFD rule requires certain actions to prevent structural failure due to WFD throughout the operational life of certain existing transport category airplanes and all of these airplanes that will be certificated in the future. For existing and future airplanes subject to the WFD rule, the rule requires that DAHs establish a limit of validity (LOV) of the engineering data that support the structural maintenance program. Operators affected by the WFD rule may not fly an airplane beyond its LOV, unless an extended LOV is approved. The WFD rule (75 FR 69746, November 15, 2010) does not require identifying and developing maintenance actions if the DAHs can show that such actions are not necessary to prevent WFD before the airplane reaches the LOV. Many LOVs, however, do depend on accomplishment of future maintenance actions. As stated in the WFD rule, any maintenance actions necessary to reach the LOV will be mandated by airworthiness directives through separate rulemaking actions. In the context of WFD, this action is necessary to enable DAHs to propose LOVs that allow operators the longest operational lives for their airplanes, and still ensure that WFD will not occur. This approach allows for an implementation strategy that provides flexibility to DAHs in determining the timing of service information development (with FAA approval), while providing operators with certainty regarding the LOV applicable to their airplanes. The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, has issued EASA Airworthiness Directive 2015-0036R1, dated March 31, 2015 (referred to after this as the Mandatory Continuing Airworthiness Information, or ``the MCAI''), to correct an unsafe condition on all Model A318, A319, A320, and A321 series airplanes. The MCAI states: During A320 family Extended Service Goal full scale fatigue tests, it was demonstrated that the inspection thresholds defined in the current Structural Repair Manual (SRM) for the A320 family skin repairs are insufficient to detect possible cracks becoming after repairs. The findings are limited to 1.2 [millimeter] (mm) fuselage skin and cover for all cut-out external repairs. The internal repairs are not affected. This condition, if not detected and corrected, could affect the structural integrity of the fuselage at the repaired skin area(s). To address this potential unsafe condition, Airbus issued Alert Operators Transmission (AOT) A53N007-14 to provide inspection instructions. For the reasons described above, EASA issued AD 2015-0036 [http://www.casa.gov.au/scripts/nc.dll?WCMS:OLDASSET::svPath=/ADFiles/over/a320/,svFileName=2015-0036.pdf] to require a one-time inspection of the affected areas and, depending on findings, accomplishment of applicable repair instructions. Since that AD was issued, operators have questioned the inspection threshold for A318 aeroplanes (not yet in the Airbus AOT), which is actually identical to that for A319 aeroplanes. In addition, an error has been detected in paragraph (1), since external doublers may have been installed in the affected area by a modification that may not be recorded as repair. Such doubler installations are also subject to the inspection requirements of this AD, which is therefore revised to provide clarifications, correcting paragraph (1) and introducing a Note. Required actions include an inspection to determine whether any fuselage external skin (doubler) repairs have been accomplished, an external ultrasonic inspection or an internal low/high frequency eddy current inspection for cracking of certain repaired external fuselage skin areas in the fuselage, and repair if necessary. The compliance times vary depending on airplane configuration. The earliest compliance time is within 25,200 flight cycles since last repair, or within 350 flight cycles after the effective date of the AD, whichever occurs later. The latest compliance time is within 45,000 flight cycles since last repair; within 1,500 flight cycles from the effective date of the AD, without exceeding 49,100 flight cycles since last repair; or within 350 flight cycles since the effective date of the AD; whichever occurs last. 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-2015-3635. Related Service Information Under 1 CFR Part 51 Airbus has issued Alert Operators Transmission A53N007-14, dated July 22, 2014. The service information describes procedures for an inspection to detect cracking on repaired 1.2 millimeter fuselage skin areas on fuselage sections 11, 12, 13, 14, 16, and 17 at external doubler repairs. The actions described in this service information are intended to correct the unsafe condition identified in the MCAI. This service information is reasonably available because the interested parties have access to it through their normal course of business or by the means identified in the ADDRESSES section of this NPRM. 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 these same type designs. Costs of Compliance We estimate that this proposed AD affects 940 airplanes of U.S. registry. We also estimate that it would take about 2 work-hours per product to comply with the basic requirements of this proposed AD. The average labor rate is $85 per work-hour. Based on these figures, we estimate the cost of this proposed AD on U.S. operators to be $159,800, or $170 per product. We have received no definitive data that would enable us to provide cost estimates for the on-condition actions specified in this proposed AD. 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: [[Page 58228]] 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 adding the following new airworthiness directive (AD): Airbus: Docket No. FAA-2015-3635; Directorate Identifier 2015-NM- 037-AD. (a) Comments Due Date We must receive comments by November 12, 2015. (b) Affected ADs None. (c) Applicability This AD applies to the Airbus airplanes specified in paragraphs (c)(1) through (c)(4) of this AD, certificated in any category, all manufacturer serial numbers. (1) Airbus Model A318-111, -112, -121, and -122 airplanes. (2) Airbus Model A319-111, -112, -113, -114, -115, -131, -132, and -133 airplanes. (3) Airbus Model A320-211, -212, -214, -231, -232, and -233 airplanes. (4) Airbus 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 an evaluation by the design approval holder indicating that the fuselage skin repairs are subject to widespread fatigue damage. We are issuing this AD to detect and correct fatigue cracking of the fuselage skin, which could result in reduced structural integrity of the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Inspection To Determine Repair Areas At the applicable time specified in paragraph (g)(1) or (g)(2) of this AD: Do an inspection to determine whether any fuselage external skin (doubler) repairs have been accomplished on fuselage sections 11, 12, 13, 14, 16, and 17 with a skin thickness of 1.2 millimeters. A review of airplane maintenance records is acceptable in lieu of this inspection if the identification of applicable repairs can be conclusively determined from that review. (1) For Model A319, A320, and A321 series airplanes: Except as specified in paragraph (h)(1) and (h)(2) of this AD, at the applicable time specified in paragraphs 4.1.1.b., and 4.1.1.c., of ``Accomplishment Timescale,'' of Airbus Alert Operators Transmission (AOT) A53N007-14, dated July 22, 2014, or within 350 flight cycles after the effective date of this AD, whichever occurs later. (2) For Model A318 series airplanes: Except as specified in paragraph (h)(1) and (h)(2) of this AD, at the Model A319 airplane time specified in paragraphs 4.1.1.b., and 4.1.1.c., of ``Accomplishment Timescale,'' of Airbus AOT A53N007-14, dated July 22, 2014, or within 350 flight cycles after the effective date of this AD, whichever occurs later. (h) Exceptions to Service Information (1) Where paragraphs 4.1.1.b., and 4.1.1.c., of ``Accomplishment Timescale,'' of Airbus AOT A53N007-14, dated July 22, 2014, specifies ``FC'', this AD specifies ``flight cycles.'' (2) Where paragraphs 4.1.1.b., and 4.1.1.c., of ``Accomplishment Timescale,'' of Airbus AOT A53N007-14, dated July 22, 2014, specifies ``from AOT issuance'', this AD specifies ``as of the effective date of this AD.'' (i) Inspection for Cracking If, during the inspection required by paragraph (g) of this AD, it is determined that any fuselage external skin (doubler) repair has been accomplished on fuselage section 11, 12, 13, 14, 16, or 17: At the applicable time specified paragraph (g)(1) or (g)(2) of this AD, do an external ultrasonic inspection (US) or an internal low frequency eddy current (LFEC) inspection for cracking of all of the repaired 1.2 millimeter (mm) fuselage skin areas, in accordance with the instructions specified in paragraph 4.2.2 ``Inspection Requirements,'' of Airbus AOT A53N007-14, dated July 22, 2014, except as provided by paragraph (j) of this AD. (j) Optional Inspection for Cracking As an optional method of compliance to the US or LFEC inspection required by paragraph (i) of this AD: Do a high frequency eddy current (HFEC) inspection for cracking in the cut-out surrounding the fastener area, at and in front (approximately 10-15 millimeters) of the fastener row, after doubler removal and before any new extended doubler installation, 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) Optional Repetitive Inspections In lieu of doing the inspection required by paragraph (i) of this AD: Within the applicable compliance time specified in paragraph 4.1.1 ``Accomplishment Timescale,'' of Airbus AOT A53N007- 14, dated July 22, 2014, after accomplishing the inspections required by paragraph (g) of this AD, do a detailed inspection or HFEC inspection and repeat the inspection thereafter within the applicable compliance times specified in paragraph 4.1.1 ``Accomplishment Timescale,'' of Airbus AOT A53N007-14, dated July 22, 2014. The inspections must be done in accordance with the instructions of paragraph 4.2.2 ``Inspection Requirements,'' of Airbus AOT A53N007-14, dated July 22, 2014. For Model A318 series airplanes, use the applicable compliance times and instructions specified in Airbus AOT A53N007-14, dated July 22, 2014, that are specified for Model A319 series airplanes. (l) Repair If any crack is found during any inspection required by paragraph (i), (j), or (k) of this AD: Before further flight, repair the cracking, in accordance with the instructions of paragraph 4.2.3 ``Findings,'' of Airbus AOT A53N007-14, dated July 22, 2014, except where Airbus AOT A53N007-14, dated July 22, 2014, specifies to contact Airbus for a repair design approval sheet or for further instructions, this AD requires repair using a method approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or the EASA; or Airbus's EASA DOA. (m) FAA-Approved Maintenance or Inspection Program Revision Concurrently with the accomplishment of any repair required by paragraph (l) of this [[Page 58229]] AD, revise the post-repair inspection threshold(s) in the applicable FAA-approved maintenance program or inspection program, as applicable, in accordance with the instructions specified in paragraph 4.1.1 ``Accomplishment Timescale,'' of Airbus AOT A53N007- 14, dated July 22, 2014; except for Model A318 series airplanes use the instructions specified for Model A319 series airplanes. (n) Other FAA AD Provisions The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the International Branch, send it to ATTN: 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. (2) Contacting the Manufacturer: For any requirement in this AD to obtain corrective actions from a manufacturer, the action must be accomplished using a method approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or the EASA; or Airbus's EASA DOA. If approved by the DOA, the approval must include the DOA-authorized signature. (o) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA Airworthiness Directive 2015-0036R1, dated March 31, 2015, 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-2015-3635. (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 September 16, 2015. Michael Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2015-24423 Filed 9-25-15; 8:45 am] BILLING CODE 4910-13-P
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(1) Alternative Methods of Compliance DEPARTMENT OF TRANSPORTATION may view this referenced service
(AMOCs): The Manager, International information at the FAA, Transport
Branch, ANM–116, Transport Airplane Federal Aviation Administration Airplane Directorate, 1601 Lind Avenue
Directorate, FAA, has the authority to SW., Renton, WA. For information on
approve AMOCs for this AD, if requested 14 CFR Part 39 the availability of this material at the
using the procedures found in 14 CFR 39.19. FAA, call 425–227–1221.
[Docket No. FAA–2015–3635; Directorate
In accordance with 14 CFR 39.19, send your
Identifier 2015–NM–037–AD] Examining the AD Docket
request to your principal inspector or local
Flight Standards District Office, as RIN 2120–AA64 You may examine the AD docket on
appropriate. If sending information directly the Internet at http://
to the International Branch, send it to ATTN: Airworthiness Directives; Airbus www.regulations.gov by searching for
Shahram Daneshmandi, Aerospace Engineer, Airplanes and locating Docket No. FAA–2015–
International Branch, ANM–116, Transport AGENCY: Federal Aviation 3635; or in person at the Docket
Airplane Directorate, FAA, 1601 Lind Administration (FAA), DOT. Management Facility between 9 a.m.
Avenue SW., Renton, WA 98057–3356; and 5 p.m., Monday through Friday,
ACTION: Notice of proposed rulemaking
telephone: 425–227–1112; fax: 425–227– except Federal holidays. The AD docket
1149. Information may be emailed to: 9- (NPRM).
contains this proposed AD, the
ANM-116-AMOC-REQUESTS@faa.gov. SUMMARY: We propose to adopt a new regulatory evaluation, any comments
Before using any approved AMOC, notify airworthiness directive (AD) for all received, and other information. The
your appropriate principal inspector, or Airbus Model A318, A319, A320, and street address for the Docket Operations
lacking a principal inspector, the manager of A321 series airplanes. This proposed office (telephone 800–647–5527) is in
the local flight standards district office/ AD was prompted by an evaluation by the ADDRESSES section. Comments will
certificate holding district office. The AMOC be available in the AD docket shortly
the design approval holder (DAH)
approval letter must specifically reference after receipt.
indicating that the fuselage skin repairs
this AD. FOR FURTHER INFORMATION CONTACT:
are subject to widespread fatigue
(2) Contacting the Manufacturer: For any Sanjay Ralhan, Aerospace Engineer,
damage (WFD). This proposed AD
requirement in this AD to obtain corrective International Branch, ANM–116,
would require an inspection to
actions from a manufacturer, the action must Transport Airplane Directorate, FAA,
determine whether any fuselage external
be accomplished using a method approved 1601 Lind Avenue SW., Renton, WA
by the Manager, International Branch, ANM–
skin (doubler) repairs have been
accomplished, an inspection for 98057–3356; telephone 425–227–1405;
116, Transport Airplane Directorate, FAA; or fax 425–227–1149.
the EASA; or Airbus Defense and Space
cracking of certain repaired external
fuselage skin areas in the fuselage, and SUPPLEMENTARY INFORMATION:
S.A.’s (formerly known as Construcciones
Aeronauticas, S.A.) EASA DOA. If approved repair if necessary. We are proposing Comments Invited
by the DOA, the approval must include the this AD to detect and correct fatigue
cracking of the fuselage skin, which We invite you to send any written
DOA-authorized signature. relevant data, views, or arguments about
could result in reduced structural
(i) Related Information integrity of the airplane. this proposed AD. Send your comments
(1) Refer to Mandatory Continuing
to an address listed under the
DATES: We must receive comments on
ADDRESSES section. Include ‘‘Docket No.
Airworthiness Information (MCAI) EASA this proposed AD by November 12,
Airworthiness Directive 2015–0040, dated FAA–2015–3635; Directorate Identifier
2015.
March 6, 2015, for related information. This 2015–NM–037–AD’’ at the beginning of
ADDRESSES: You may send comments, your comments. We specifically invite
MCAI may be found in the AD docket on the
using the procedures found in 14 CFR comments on the overall regulatory,
Internet at http://www.regulations.gov by
searching for and locating Docket No. FAA–
11.43 and 11.45, by any of the following economic, environmental, and energy
2015–3636.
methods: aspects of this proposed AD. We will
(2) For service information identified in
• Federal eRulemaking Portal: Go to consider all comments received by the
this AD, contact EADS–CASA, Military
http://www.regulations.gov. Follow the closing date and may amend this
Transport Aircraft Division (MTAD),
instructions for submitting comments. proposed AD based on those comments.
Integrated Customer Services (ICS),
• Fax: 202–493–2251. We will post all comments we
Technical Services, Avenida de Aragón 404,
• Mail: U.S. Department of receive, without change, to http://
28022 Madrid, Spain; telephone +34 91 585
Transportation, Docket Operations, M– www.regulations.gov, including any
55 84; fax +34 91 585 55 05; email 30, West Building Ground Floor, Room personal information you provide. We
MTA.TechnicalService@casa.eads.net; W12–140, 1200 New Jersey Avenue SE., will also post a report summarizing each
Internet http://www.eads.net. You may view Washington, DC 20590. substantive verbal contact we receive
this service information at the FAA, • Hand Delivery: U.S. Department of about this proposed AD.
Transport Airplane Directorate, 1601 Lind Transportation, Docket Operations, M–
30, West Building Ground Floor, Room Discussion
Avenue SW., Renton, WA. For information
on the availability of this material at the W12–140, 1200 New Jersey Avenue SE., Structural fatigue damage is
FAA, call 425–227–1221. Washington, DC, between 9 a.m. and 5 progressive. It begins as minute cracks,
p.m., Monday through Friday, except and those cracks grow under the action
Issued in Renton, Washington, on Federal holidays. of repeated stresses. This can happen
rmajette on DSK7SPTVN1PROD with PROPOSALS
September 16, 2015. For service information identified in because of normal operational
Michael Kaszycki, this proposed AD, contact Airbus, conditions and design attributes, or
Acting Manager, Transport Airplane Airworthiness Office—EIAS, 1 Rond because of isolated situations or
Directorate, Aircraft Certification Service. Point Maurice Bellonte, 31707 Blagnac incidents such as material defects, poor
[FR Doc. 2015–24424 Filed 9–25–15; 8:45 am] Cedex, France; telephone +33 5 61 93 36 fabrication quality, or corrosion pits,
BILLING CODE 4910–13–P 96; fax +33 5 61 93 44 51; email dings, or scratches. Fatigue damage can
account.airworth-eas@airbus.com; occur locally, in small areas or
Internet http://www.airbus.com. You structural design details, or globally.
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![Federal Register / Vol. 80, No. 187 / Monday, September 28, 2015 / Proposed Rules 58227
Global fatigue damage is general Union, has issued EASA Airworthiness www.regulations.gov by searching for
degradation of large areas of structure Directive 2015–0036R1, dated March 31, and locating Docket No. FAA–2015–
with similar structural details and stress 2015 (referred to after this as the 3635.
levels. Multiple-site damage is global Mandatory Continuing Airworthiness
Related Service Information Under 1
damage that occurs in a large structural Information, or ‘‘the MCAI’’), to correct
CFR Part 51
element such as a single rivet line of a an unsafe condition on all Model A318,
lap splice joining two large skin panels. A319, A320, and A321 series airplanes. Airbus has issued Alert Operators
Global damage can also occur in The MCAI states: Transmission A53N007–14, dated July
multiple elements such as adjacent During A320 family Extended Service Goal
22, 2014. The service information
frames or stringers. Multiple-site- full scale fatigue tests, it was demonstrated describes procedures for an inspection
damage and multiple-element-damage that the inspection thresholds defined in the to detect cracking on repaired 1.2
cracks are typically too small initially to current Structural Repair Manual (SRM) for millimeter fuselage skin areas on
be reliably detected with normal the A320 family skin repairs are insufficient fuselage sections 11, 12, 13, 14, 16, and
inspection methods. Without to detect possible cracks becoming after 17 at external doubler repairs. The
intervention, these cracks will grow, repairs. The findings are limited to 1.2 actions described in this service
[millimeter] (mm) fuselage skin and cover for information are intended to correct the
and eventually compromise the
all cut-out external repairs. The internal
structural integrity of the airplane, in a repairs are not affected. unsafe condition identified in the
condition known as widespread fatigue This condition, if not detected and MCAI. This service information is
damage (WFD). As an airplane ages, corrected, could affect the structural integrity reasonably available because the
WFD will likely occur, and will of the fuselage at the repaired skin area(s). interested parties have access to it
certainly occur if the airplane is To address this potential unsafe condition, through their normal course of business
operated long enough without any Airbus issued Alert Operators Transmission or by the means identified in the
intervention. (AOT) A53N007–14 to provide inspection ADDRESSES section of this NPRM.
The FAA’s WFD final rule (75 FR instructions.
69746, November 15, 2010) became For the reasons described above, EASA FAA’s Determination and Requirements
issued AD 2015–0036 [http:// of This Proposed AD
effective on January 14, 2011. The WFD www.casa.gov.au/scripts/
rule requires certain actions to prevent nc.dll?WCMS:OLDASSET::svPath=/ADFiles/ This product has been approved by
structural failure due to WFD over/a320/,svFileName=2015-0036.pdf] to the aviation authority of another
throughout the operational life of require a one-time inspection of the affected country, and is approved for operation
certain existing transport category areas and, depending on findings, in the United States. Pursuant to our
airplanes and all of these airplanes that accomplishment of applicable repair bilateral agreement with the State of
will be certificated in the future. For instructions. Design Authority, we have been notified
existing and future airplanes subject to Since that AD was issued, operators have of the unsafe condition described in the
questioned the inspection threshold for A318
the WFD rule, the rule requires that MCAI and service information
aeroplanes (not yet in the Airbus AOT),
DAHs establish a limit of validity (LOV) which is actually identical to that for A319 referenced above. We are proposing this
of the engineering data that support the aeroplanes. In addition, an error has been AD because we evaluated all pertinent
structural maintenance program. detected in paragraph (1), since external information and determined an unsafe
Operators affected by the WFD rule may doublers may have been installed in the condition exists and is likely to exist or
not fly an airplane beyond its LOV, affected area by a modification that may not develop on other products of these same
unless an extended LOV is approved. be recorded as repair. type designs.
The WFD rule (75 FR 69746, Such doubler installations are also subject
November 15, 2010) does not require to the inspection requirements of this AD, Costs of Compliance
identifying and developing maintenance which is therefore revised to provide
We estimate that this proposed AD
clarifications, correcting paragraph (1) and
actions if the DAHs can show that such introducing a Note. affects 940 airplanes of U.S. registry.
actions are not necessary to prevent We also estimate that it would take
WFD before the airplane reaches the Required actions include an about 2 work-hours per product to
LOV. Many LOVs, however, do depend inspection to determine whether any comply with the basic requirements of
on accomplishment of future fuselage external skin (doubler) repairs this proposed AD. The average labor
maintenance actions. As stated in the have been accomplished, an external rate is $85 per work-hour. Based on
WFD rule, any maintenance actions ultrasonic inspection or an internal low/ these figures, we estimate the cost of
necessary to reach the LOV will be high frequency eddy current inspection this proposed AD on U.S. operators to
mandated by airworthiness directives for cracking of certain repaired external be $159,800, or $170 per product.
through separate rulemaking actions. fuselage skin areas in the fuselage, and We have received no definitive data
In the context of WFD, this action is repair if necessary. The compliance that would enable us to provide cost
necessary to enable DAHs to propose times vary depending on airplane estimates for the on-condition actions
LOVs that allow operators the longest configuration. The earliest compliance specified in this proposed AD.
operational lives for their airplanes, and time is within 25,200 flight cycles since
still ensure that WFD will not occur. last repair, or within 350 flight cycles Authority for This Rulemaking
This approach allows for an after the effective date of the AD, Title 49 of the United States Code
implementation strategy that provides whichever occurs later. The latest specifies the FAA’s authority to issue
flexibility to DAHs in determining the compliance time is within 45,000 flight rules on aviation safety. Subtitle I,
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timing of service information cycles since last repair; within 1,500 section 106, describes the authority of
development (with FAA approval), flight cycles from the effective date of the FAA Administrator. ‘‘Subtitle VII:
while providing operators with certainty the AD, without exceeding 49,100 flight Aviation Programs,’’ describes in more
regarding the LOV applicable to their cycles since last repair; or within 350 detail the scope of the Agency’s
airplanes. flight cycles since the effective date of authority.
The European Aviation Safety Agency the AD; whichever occurs last. You may We are issuing this rulemaking under
(EASA), which is the Technical Agent examine the MCAI in the AD docket on the authority described in ‘‘Subtitle VII,
for the Member States of the European the Internet at http:// Part A, Subpart III, Section 44701:
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![58228 Federal Register / Vol. 80, No. 187 / Monday, September 28, 2015 / Proposed Rules
General requirements.’’ Under that (c) Applicability (i) Inspection for Cracking
section, Congress charges the FAA with This AD applies to the Airbus airplanes If, during the inspection required by
promoting safe flight of civil aircraft in specified in paragraphs (c)(1) through (c)(4) paragraph (g) of this AD, it is determined that
air commerce by prescribing regulations of this AD, certificated in any category, all any fuselage external skin (doubler) repair
for practices, methods, and procedures manufacturer serial numbers. has been accomplished on fuselage section
the Administrator finds necessary for (1) Airbus Model A318–111, –112, –121, 11, 12, 13, 14, 16, or 17: At the applicable
and –122 airplanes. time specified paragraph (g)(1) or (g)(2) of
safety in air commerce. This regulation this AD, do an external ultrasonic inspection
is within the scope of that authority (2) Airbus Model A319–111, –112, –113,
–114, –115, –131, –132, and –133 airplanes. (US) or an internal low frequency eddy
because it addresses an unsafe condition current (LFEC) inspection for cracking of all
(3) Airbus Model A320–211, –212, –214,
that is likely to exist or develop on of the repaired 1.2 millimeter (mm) fuselage
–231, –232, and –233 airplanes. skin areas, in accordance with the
products identified in this rulemaking (4) Airbus Model A321–111, –112, –131,
action. instructions specified in paragraph 4.2.2
–211, –212, –213, –231, and –232 airplanes. ‘‘Inspection Requirements,’’ of Airbus AOT
Regulatory Findings (d) Subject A53N007–14, dated July 22, 2014, except as
provided by paragraph (j) of this AD.
We determined that this proposed AD Air Transport Association (ATA) of
would not have federalism implications America Code 53, Fuselage. (j) Optional Inspection for Cracking
under Executive Order 13132. This As an optional method of compliance to
(e) Reason
proposed AD would not have a the US or LFEC inspection required by
substantial direct effect on the States, on This AD was prompted by an evaluation by paragraph (i) of this AD: Do a high frequency
the relationship between the national the design approval holder indicating that eddy current (HFEC) inspection for cracking
Government and the States, or on the the fuselage skin repairs are subject to in the cut-out surrounding the fastener area,
widespread fatigue damage. We are issuing at and in front (approximately 10–15
distribution of power and millimeters) of the fastener row, after doubler
this AD to detect and correct fatigue cracking
responsibilities among the various of the fuselage skin, which could result in removal and before any new extended
levels of government. reduced structural integrity of the airplane. doubler installation, using a method
For the reasons discussed above, I approved by the Manager, International
certify this proposed regulation: (f) Compliance Branch, ANM–116, Transport Airplane
1. Is not a ‘‘significant regulatory Comply with this AD within the Directorate, FAA; or the European Aviation
action’’ under Executive Order 12866; compliance times specified, unless already Safety Agency (EASA); or Airbus’s EASA
2. Is not a ‘‘significant rule’’ under the done. Design Organization Approval (DOA).
DOT Regulatory Policies and Procedures (k) Optional Repetitive Inspections
(g) Inspection To Determine Repair Areas
(44 FR 11034, February 26, 1979); In lieu of doing the inspection required by
3. Will not affect intrastate aviation in At the applicable time specified in
paragraph (i) of this AD: Within the
Alaska; and paragraph (g)(1) or (g)(2) of this AD: Do an
applicable compliance time specified in
4. Will not have a significant inspection to determine whether any fuselage
paragraph 4.1.1 ‘‘Accomplishment
external skin (doubler) repairs have been
economic impact, positive or negative, Timescale,’’ of Airbus AOT A53N007–14,
accomplished on fuselage sections 11, 12, 13, dated July 22, 2014, after accomplishing the
on a substantial number of small entities 14, 16, and 17 with a skin thickness of 1.2
under the criteria of the Regulatory inspections required by paragraph (g) of this
millimeters. A review of airplane AD, do a detailed inspection or HFEC
Flexibility Act. maintenance records is acceptable in lieu of inspection and repeat the inspection
List of Subjects in 14 CFR Part 39 this inspection if the identification of thereafter within the applicable compliance
applicable repairs can be conclusively times specified in paragraph 4.1.1
Air transportation, Aircraft, Aviation determined from that review. ‘‘Accomplishment Timescale,’’ of Airbus
safety, Incorporation by reference, (1) For Model A319, A320, and A321 series AOT A53N007–14, dated July 22, 2014. The
Safety. airplanes: Except as specified in paragraph inspections must be done in accordance with
(h)(1) and (h)(2) of this AD, at the applicable the instructions of paragraph 4.2.2
The Proposed Amendment ‘‘Inspection Requirements,’’ of Airbus AOT
time specified in paragraphs 4.1.1.b., and
Accordingly, under the authority 4.1.1.c., of ‘‘Accomplishment Timescale,’’ of A53N007–14, dated July 22, 2014. For Model
delegated to me by the Administrator, Airbus Alert Operators Transmission (AOT) A318 series airplanes, use the applicable
the FAA proposes to amend 14 CFR part A53N007–14, dated July 22, 2014, or within compliance times and instructions specified
39 as follows: 350 flight cycles after the effective date of in Airbus AOT A53N007–14, dated July 22,
this AD, whichever occurs later. 2014, that are specified for Model A319
(2) For Model A318 series airplanes: series airplanes.
PART 39—AIRWORTHINESS
DIRECTIVES Except as specified in paragraph (h)(1) and (l) Repair
(h)(2) of this AD, at the Model A319 airplane
If any crack is found during any inspection
■ 1. The authority citation for part 39 time specified in paragraphs 4.1.1.b., and
required by paragraph (i), (j), or (k) of this
continues to read as follows: 4.1.1.c., of ‘‘Accomplishment Timescale,’’ of
AD: Before further flight, repair the cracking,
Airbus AOT A53N007–14, dated July 22, in accordance with the instructions of
Authority: 49 U.S.C. 106(g), 40113, 44701. 2014, or within 350 flight cycles after the paragraph 4.2.3 ‘‘Findings,’’ of Airbus AOT
§ 39.13 [Amended] effective date of this AD, whichever occurs A53N007–14, dated July 22, 2014, except
later. where Airbus AOT A53N007–14, dated July
■ 2. The FAA amends § 39.13 by adding
(h) Exceptions to Service Information 22, 2014, specifies to contact Airbus for a
the following new airworthiness
repair design approval sheet or for further
directive (AD): (1) Where paragraphs 4.1.1.b., and 4.1.1.c., instructions, this AD requires repair using a
rmajette on DSK7SPTVN1PROD with PROPOSALS
Airbus: Docket No. FAA–2015–3635; of ‘‘Accomplishment Timescale,’’ of Airbus method approved by the Manager,
Directorate Identifier 2015–NM–037–AD. AOT A53N007–14, dated July 22, 2014, International Branch, ANM–116, Transport
specifies ‘‘FC’’, this AD specifies ‘‘flight Airplane Directorate, FAA; or the EASA; or
(a) Comments Due Date cycles.’’ Airbus’s EASA DOA.
We must receive comments by November (2) Where paragraphs 4.1.1.b., and 4.1.1.c.,
12, 2015. of ‘‘Accomplishment Timescale,’’ of Airbus (m) FAA-Approved Maintenance or
AOT A53N007–14, dated July 22, 2014, Inspection Program Revision
(b) Affected ADs specifies ‘‘from AOT issuance’’, this AD Concurrently with the accomplishment of
None. specifies ‘‘as of the effective date of this AD.’’ any repair required by paragraph (l) of this
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![Federal Register / Vol. 80, No. 187 / Monday, September 28, 2015 / Proposed Rules 58229
AD, revise the post-repair inspection DEPARTMENT OF THE TREASURY written comments by August 4, 2015
threshold(s) in the applicable FAA-approved must submit an outline of the topics to
maintenance program or inspection program, Internal Revenue Service be addressed and the amount of time to
as applicable, in accordance with the
be devoted to each topic by Wednesday,
instructions specified in paragraph 4.1.1
‘‘Accomplishment Timescale,’’ of Airbus
26 CFR Part 1 October 7, 2015.
AOT A53N007–14, dated July 22, 2014; A period of 10 minutes is allotted to
[REG–132634–14]
except for Model A318 series airplanes use each person for presenting oral
the instructions specified for Model A319 RIN 1545–BM43 comments. After the deadline for
series airplanes. receiving outlines has passed, the IRS
(n) Other FAA AD Provisions
Qualifying Income From Activities of will prepare an agenda containing the
Publicly Traded Partnerships With schedule of speakers. Copies of the
The following provisions also apply to this Respect to Minerals or Natural
AD: agenda will be made available, free of
(1) Alternative Methods of Compliance Resources; Hearing charge, at the hearing or in the Freedom
(AMOCs): The Manager, International of Information Reading Room (FOIA RR)
AGENCY: Internal Revenue Service (IRS),
Branch, ANM–116, Transport Airplane (Room 1621) which is located at the
Treasury.
Directorate, FAA, has the authority to 11th and Pennsylvania Avenue,
approve AMOCs for this AD, if requested ACTION: Notice of public hearing on entrance, of 1111 Constitution Avenue
using the procedures found in 14 CFR 39.19. proposed rulemaking. NW., Washington, DC.
In accordance with 14 CFR 39.19, send your Because of access restrictions, the IRS
request to your principal inspector or local SUMMARY: This document provides
Flight Standards District Office, as notice of public hearing on proposed will not admit visitors beyond the
appropriate. If sending information directly regulations relates to section immediate entrance area more than 30
to the International Branch, send it to ATTN: 7704(d)(1)(E) of the Internal Revenue minutes before the hearing starts. For
Sanjay Ralhan, Aerospace Engineer, Code relating to qualifying income from information about having your name
International Branch, ANM–116, Transport
exploration, development, mining or placed on the building access list to
Airplane Directorate, FAA, 1601 Lind attend the hearing, see the FOR FURTHER
Avenue SW., Renton, WA 98057–3356; production, processing, refining,
INFORMATION CONTACT section of this
telephone 425–227–1405; fax 425–227–1149. transportation, and marketing of
minerals or production, processing, document.
Information may be emailed to: 9-ANM-116-
AMOC-REQUESTS@faa.gov. Before using refining, transportation, and marketing Martin V. Franks,
any approved AMOC, notify your appropriate of minerals or natural resources. Chief, Publications and Regulations Branch,
principal inspector, or lacking a principal Associate Chief Counsel (Procedure and
DATES: The public hearing is being held
inspector, the manager of the local flight Administration).
standards district office/certificate holding on Tuesday, October 27, 2015, at 10 a.m.
district office. The IRS must receive outlines of the [FR Doc. 2015–24568 Filed 9–25–15; 8:45 am]
(2) Contacting the Manufacturer: For any topics to be discussed at the public BILLING CODE 4830–01–P
requirement in this AD to obtain corrective hearing by Wednesday, October 7, 2015.
actions from a manufacturer, the action must ADDRESSES: The public hearing is being
be accomplished using a method approved held in the IRS Auditorium, Internal
by the Manager, International Branch, ANM–
DEPARTMENT OF LABOR
Revenue Service Building, 1111
116, Transport Airplane Directorate, FAA; or
the EASA; or Airbus’s EASA DOA. If Constitution Avenue NW., Washington, Mine Safety and Health Administration
approved by the DOA, the approval must DC 20224. Send Submissions to
include the DOA-authorized signature. CC:PA:LPD:PR (REG–132634–14), Room 30 CFR Part 75
5205, Internal Revenue Service, P.O.
(o) Related Information RIN 1219–AB78
Box 7604, Ben Franklin Station,
(1) Refer to Mandatory Continuing Washington, DC 20044. Submissions
Airworthiness Information (MCAI) EASA Proximity Detection Systems for
may be hand-delivered Monday through
Airworthiness Directive 2015–0036R1, dated Mobile Machines in Underground Coal
Friday to CC:PA:LPD:PR (REG–132634–
March 31, 2015, for related information. This Mines
MCAI may be found in the AD docket on the 14), Couriers Desk, Internal Revenue
Internet at http://www.regulations.gov by Service, 1111 Constitution Avenue NW., AGENCY: Mine Safety and Health
searching for and locating Docket No. FAA– Washington, DC or sent electronically Administration, Labor.
2015–3635. via the Federal eRulemaking Portal at ACTION: Proposed rule; scheduling of
(2) For service information identified in www.regulations.gov (IRS–2015–0021). public hearing.
this AD, contact Airbus, Airworthiness FOR FURTHER INFORMATION CONTACT:
Office—EIAS, 1 Rond Point Maurice SUMMARY: The Mine Safety and Health
Concerning the regulations, Caroline E.
Bellonte, 31707 Blagnac Cedex, France; Administration (MSHA) is announcing
telephone +33 5 61 93 36 96; fax +33 5 61 Hay (202) 317–5279; concerning
submissions of comments, the hearing the date and location of public hearings
93 44 51; email account.airworth-eas@
airbus.com; Internet http://www.airbus.com. and/or to be placed on the building on the Agency’s proposed rule
You may view this service information at the access list to attend the hearing, Regina addressing Proximity Detection Systems
FAA, Transport Airplane Directorate, 1601 Johnson at (202) 317–6901 (not toll-free for Mobile Machines in Underground
Lind Avenue SW., Renton, WA. For numbers). Coal Mines, published on September 2,
information on the availability of this
SUPPLEMENTARY INFORMATION: The
2015.
material at the FAA, call 425–227–1221.
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subject of the public hearing is the DATES: The public hearing dates and
Issued in Renton, Washington, on notice of proposed rulemaking (REG– locations are listed in the
September 16, 2015. 132634–14) that was published in the SUPPLEMENTARY INFORMATION section of
Michael Kaszycki, Federal Register on Wednesday, May 6, this document. Comments must be
Acting Manager, Transport Airplane 2015 (73 FR 25970). The rules of 26 CFR received by midnight Eastern Standard
Directorate, Aircraft Certification Service. 601.601(a)(3) apply to the hearing. Time on December 1, 2015.
[FR Doc. 2015–24423 Filed 9–25–15; 8:45 am] Persons who wish to present oral ADDRESSES: Comments, requests to
BILLING CODE 4910–13–P comments at the hearing that submitted speak, and informational materials for
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Document Created: 2018-02-26 10:22:07
Document Modified: 2018-02-26 10:22:07
| 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 12, 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 58226 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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