81 FR 29198 - Airworthiness Directives; Airbus Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 81, Issue 91 (May 11, 2016)
Federal Aviation Administration
Federal Register Volume 81, Issue 91 (May 11, 2016)
| Page Range | 29198-29202 | |
| FR Document | 2016-10914 |
[Federal Register Volume 81, Number 91 (Wednesday, May 11, 2016)] [Proposed Rules] [Pages 29198-29202] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2016-10914] ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2016-6429; Directorate Identifier 2015-NM-117-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) 2015-05- 02, for certain Airbus Model A318, A319, A320, and A321 series airplanes. AD 2015-05-02 requires revising the maintenance or inspection program to incorporate new, more restrictive airworthiness limitations. Since we issued AD 2015-05-02, an evaluation by the design approval holder (DAH) indicates that principal structural elements and certain life limited parts are subject to widespread fatigue damage (WFD). This proposed AD would require revising the maintenance or inspection program, as applicable, to incorporate new or revised structural inspection requirements. We are proposing this AD to prevent fatigue cracking, accidental damage, or corrosion in principal structural elements, and WFD, which could result in reduced structural integrity of the airplane. DATES: We must receive comments on this proposed AD by June 27, 2016. 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 NPRM, 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-2016- 6429; 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: [[Page 29199]] 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-2016-6429; Directorate Identifier 2015-NM-117-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. 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. On February 25, 2015, we issued AD 2015-05-02, Amendment 39-18112 (80 FR 15152, March 23, 2015) (``AD 2015-05-02'') to supersede AD 2014- 23-15, Amendment 39-18031 (80 FR 3871, January 26, 2015). AD 2015-05-02 requires revising the maintenance or inspection program, as applicable, to incorporate new, more restrictive airworthiness limitations on all Airbus Model A318, A319, A320, and A321 series airplanes. Since we issued AD 2015-05-02, an evaluation by the DAH indicates that principal structural elements and certain life limited parts are subject to widespread fatigue damage WFD. This proposed AD would require revising the maintenance or inspection program, as applicable, to incorporate new or revised structural inspection requirements. The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, has issued EASA Airworthiness Directive 2015-0083, dated May 12, 2015 (referred to after this as the Mandatory Continuing Airworthiness Information, or ``the MCAI''), to correct an unsafe condition. The MCAI states: The airworthiness limitations for Airbus A320 family aeroplanes are currently included in Airbus A318/A319/A320/A321 Airworthiness Limitations Section (hereafter referred to as `ALS') documents. The Damage Tolerant airworthiness limitation items are published in ALS Part 2, approved by EASA. The instructions contained in the ALS Part 2 have been identified as mandatory actions for continued airworthiness. Failure to comply with these instructions could result in an unsafe condition. Previously, EASA issued AD 2013-0147 (http://ad.easa.europa.eu/blob/easa_ad_2013_0147_superseded.pdf/AD_2013-0147_1) [which corresponds to FAA AD 2014-23-15, Amendment 39-18031 (80 FR 3871, January 26, 2015) to require accomplishment of all maintenance tasks as described in ALS Part 2 at Revision 02. The new ALS Part 2 Revision 03 [Issue October 27, 2014] includes new and/or more restrictive items and was approved on 27 October 2014. For the reason described above, this [EASA] AD retains the requirements of EASA AD 2013-0147, which is superseded, and requires accomplishment of all maintenance tasks as described in ALS Part 2 at Revision 03. The required action is revising the maintenance or inspection program to incorporate new or revised structural inspection requirements. The unsafe condition is fatigue cracking, accidental damage, or corrosion in principal structural elements, and WFD, which could result in reduced structural integrity of the airplane. 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-2016- 6429. Other Relevant Rulemaking We have issued NPRM Docket FAA-2015-6539, Directorate Identifier 2015-NM-036-AD (80 FR 74723, November 30, 2015), for all Airbus Model A318-111 and -112 airplanes; Model A319-111, -112, -113, -114, and -115 airplanes; Model A320-211, -212, and -214 airplanes; and Model A321- 111, -112, -211, -212, and -213 airplanes. That NPRM proposes to require repetitive inspections that reduce the compliance time for Task 712111-01, Detailed Inspection of Forward Engine Mount Installation. Therefore, Task 712111-01 is not included in this proposed AD. Related Service Information Under 1 CFR Part 51 Airbus has issued Part 2, Damage Tolerant Airworthiness Limitation Items (DT-ALI), Revision 04, dated December 18, 2015, of the A318/A319/ A320/A321 Airworthiness Limitation Section (ALS). The service information describes DT ALIs associated with WFD. Airbus has also issued Part 2, Damage Tolerant Airworthiness Limitation Items [[Page 29200]] (DT-ALI), Variation 4.2, dated January 15, 2016, of the A318/A319/A320/ A321 Airworthiness Limitation Section (ALS). The service information describes DT ALIs associated with WFD. This service information is reasonably available because the interested parties have access to it through their normal course of business or by the means identified in the ADDRESSES section. FAA's Determination 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. This proposed AD requires revisions to certain operator maintenance documents to include new actions (e.g., inspections). Compliance with these actions is required by 14 CFR 91.403(c). For airplanes that have been previously modified, altered, or repaired in the areas addressed by this proposed AD, the operator might not be able to accomplish the actions described in the revisions. In this situation, to comply with 14 CFR 91.403(c), the operator must request approval for an alternative method of compliance (AMOC) in accordance with the provisions of paragraph (k)(1) of this proposed AD. The request should include a description of changes to the required actions that will ensure the continued damage tolerance of the affected structure. Differences Between This Proposed AD and the MCAI or Service Information This proposed AD differs from the MCAI in that it specifies revising the maintenance or inspection program, as applicable, to incorporate the ALIs specified in Airbus A318/A319/A320/A321 ALS Part 2, Damage Tolerant Airworthiness Limitation Items (DT-ALI), Revision 04, dated December 18, 2015; and Airbus A318/A319/A320/A321 ALS Part 2, Damage Tolerant Airworthiness Limitation Items (DT-ALI), Variation 4.2, dated January 15, 2016. The MCAI specifies incorporating the ALIs specified in Airbus A318/A319/A320/A321 ALS Safe Life Airworthiness Limitation Section (ALS), Part 2, Damage Tolerant Airworthiness Limitation Items (DT-ALI), Revision 03, Issue October 27, 2014. We have coordinated this change with EASA. EASA has issued EASA Proposed Airworthiness Directive (PAD) 16-029, dated February 24, 2016, which specifies incorporating the ALI's in Airbus A318/A319/A320/A321 ALS Part 2, Damage Tolerant Airworthiness Limitation Items (DT-ALI), Revision 04, dated December 18, 2015; and Airbus A318/A319/A320/A321 ALS Part 2, Damage Tolerant Airworthiness Limitation Items (DT-ALI), Variation 4.2, dated January 15, 2016. The MCAI specifies that if there are findings from the ALS inspection tasks, corrective actions must be accomplished in accordance with Airbus maintenance documentation. However, this proposed AD does not include that requirement. Operators of U.S.-registered airplanes are required by general airworthiness and operational regulations to perform maintenance using methods that are acceptable to the FAA. We consider those methods to be adequate to address any corrective actions necessitated by the findings of ALS inspections required by this proposed AD. Airworthiness Limitations Based on Type Design The FAA recently became aware of an issue related to the applicability of ADs that require incorporation of an ALS revision into an operator's maintenance or inspection program. Typically, when these types of ADs are issued by civil aviation authorities of other countries, they apply to all airplanes covered under an identified type certificate (TC). The corresponding FAA AD typically retains applicability to all of those airplanes. In addition, U.S. operators must operate their airplanes in an airworthy condition, in accordance with 14 CFR 91.7(a). Included in this obligation is the requirement to perform any maintenance or inspections specified in the ALS, and in accordance with the ALS as specified in 14 CFR 43.16 and 91.403(c), unless an alternative has been approved by the FAA. When a type certificate is issued for a type design, the specific ALS, including revisions, is a part of that type design, as specified in 14 CFR 21.31(c). The sum effect of these operational and maintenance requirements is an obligation to comply with the ALS defined in the type design referenced in the manufacturer's conformity statement. This obligation may introduce a conflict with an AD that requires a specific ALS revision if new airplanes are delivered with a later revision as part of their type design. To address this conflict, the FAA has approved AMOCs that allow operators to incorporate the most recent ALS revision into their maintenance/inspection programs, in lieu of the ALS revision required by the AD. This eliminates the conflict and enables the operator to comply with both the AD and the type design. However, compliance with AMOCs is normally optional, and we recently became aware that some operators choose to retain the AD- mandated ALS revision in their fleet-wide maintenance/inspection programs, including those for new airplanes delivered with later ALS revisions, to help standardize the maintenance of the fleet. To ensure that operators comply with the applicable ALS revision for newly delivered airplanes containing a later revision than that specified in an AD, we plan to limit the applicability of ADs that mandate ALS revisions to those airplanes that are subject to an earlier revision of the ALS, either as part of the type design or as mandated by an earlier AD. This proposed AD therefore applies to the airplanes identified in paragraph (c) of this proposed AD with an original certificate of airworthiness or original export certificate of airworthiness that was issued on or before the date of approval of the ALS revision identified in this proposed AD. Operators of airplanes with an original certificate of airworthiness or original export certificate of airworthiness issued after that date must comply with the airworthiness limitations specified as part of the approved type design and referenced on the type certificate data sheet. Record of Ex Parte Communication In preparation of AD actions, it is the practice of the FAA to obtain technical information and information on the operational and economic impact from design approval holders and aircraft operators. We discussed certain issues related to this NPRM in a recent meeting with Airlines for America (A4A). Shortly after this NPRM is published, we will post a summary of this meeting in the rulemaking docket. For information on locating the docket, see ``Examining the AD Docket.'' Costs of Compliance We estimate that this proposed AD affects 959 airplanes of U.S. registry. The actions required by AD 2015-05-02, and retained in this proposed AD take about 2 work-hours per product, at an average labor rate of $85 per work-hour. Based on these figures, the estimated cost of the actions that are [[Page 29201]] required by AD 2015-05-02 is $170 per product. 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 $163,030, or $170 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: 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) 2015-05-02, Amendment 39-18112 (80 FR 15152, March 23, 2015), and adding the following new AD: Airbus: Docket No. FAA-2016-6429; Directorate Identifier 2015-NM- 117-AD. (a) Comments Due Date We must receive comments by June 27, 2016. (b) Affected ADs This AD replaces AD 2015-05-02, Amendment 39-18112 (80 FR 15152, March 23, 2015) (``AD 2015-05-02''). (c) Applicability This AD applies to the Airbus airplanes identified in paragraphs (c)(1) through (c)(4) of this AD, certificated in any category, with an original certificate of airworthiness or original export certificate of airworthiness issued on or before January 15, 2016. (1) Model A318-111, -112, -121, and -122 airplanes. (2) Model A319-111, -112, -113, -114, -115, -131, -132, and -133 airplanes. (3) Model A320-211, -212, -214, -231, -232, and -233 airplanes. (4) Model A321-111, -112, -131, -211, -212, -213, -231, and -232 airplanes. (d) Subject Air Transport Association (ATA) of America Code 05, Periodic Inspections. (e) Reason This AD was prompted by an evaluation by the design approval holder (DAH) which indicates that principal structural elements and certain life limited parts are subject to widespread fatigue damage (WFD). We are issuing this AD to prevent fatigue cracking, accidental damage, or corrosion in principal structural elements, and WFD, 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) Retained Maintenance or Inspection Program Revision, With No Changes This paragraph restates the requirements of paragraph (n) of AD 2015-05-02, with no changes. Within 30 days after March 2, 2015 (the effective date of AD 2014-23-15, Amendment 39-18031 (80 FR 3871, January 26, 2015) (``AD 2014-23-15'')), revise the maintenance or inspection program, as applicable, to incorporate the Airworthiness Limitation Items (ALIs) specified in paragraphs (g)(1) and (g)(2) of this AD. The initial compliance time for accomplishing the actions is at the applicable time identified in the ALIs specified in paragraphs (g)(1) and (g)(2) of this AD; or within 4 months after March 2, 2015 (the effective date of AD 2014-23-15); whichever occurs later. (1) Airbus A318/A319/A320/A321 ALS Part 1--Safe Life Airworthiness Limitation Items, Revision 02, dated May 13, 2011. (2) Airbus A318/A319/A320/A321 ALS Part 2--Damage-Tolerant Airworthiness Limitation Items (DT ALI), Revision 02, dated May 28, 2013. (h) Retained Limitation: No Alternative Actions, Intervals, and/or Critical Design Configuration Control Limitations (CDCCLs), With Exception This paragraph restates the requirements of paragraph (o) of AD 2015-05-02, with an exception. Except as required by paragraph (i) of this AD, after accomplishing the revision required by paragraph (g) of this AD, no alternative actions (e.g., inspections), intervals, and/or CDCCLs may be used unless the actions, intervals, and/or CDCCLs are approved as an alternative method of compliance (AMOC) in accordance with the procedures specified in paragraph (k)(1) of this AD. (i) New Requirement of This AD: Maintenance or Inspection Program Revision Within 60 days after the effective date of this AD, revise the maintenance or inspection program, as applicable, to incorporate the ALIs specified in Airbus A318/A319/A320/A321 ALS Part 2, Damage Tolerant Airworthiness Limitation Items (DT-ALI), Revision 04, dated December 18, 2015; and Airbus A318/A319/A320/A321 ALS Part 2, Damage Tolerant Airworthiness Limitation Items (DT-ALI), Variation 4.2, dated January 15, 2016. The initial compliance time for accomplishing the actions is at the applicable time identified in the ALIs specified in Airbus A318/A319/A320/A321 ALS Part 2, Damage Tolerant Airworthiness Limitation Items (DT-ALI), Revision 04, dated December 18, 2015; and Airbus A318/A319/A320/A321 ALS Part 2, Damage Tolerant Airworthiness Limitation Items (DT-ALI), Variation 4.2, dated January 15, 2016; without exceeding the inspection intervals in the ALIs specified in the service information identified in paragraph (g)(2) of this AD, except for the ALI tasks identified in paragraphs (i)(1) though (i)(4) of this AD. Accomplishing these actions terminates the requirements of paragraph (g)(2) of this AD. (1) Task 712111-01-1, ``Detailed Inspection of Forward Engine Mount Installation.'' (2) Task 712111-01-2, ``Detailed Inspection of Forward Engine Mount Installation.'' (3) Task 712111-01-3, ``Detailed Inspection of Forward Engine Mount Installation.'' (4) Task 712111-01-4, ``Detailed Inspection of Forward Engine Mount Installation.'' [[Page 29202]] (j) New No Alternative Actions and/or Intervals After accomplishing the revision required by paragraph (i) of this AD, no alternative actions (e.g., inspections) and/or intervals may be used unless the actions and/or intervals are approved as an AMOC in accordance with the procedures specified in paragraph (k)(1) of this AD. (k) 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]. (i) Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/certificate holding district office. The AMOC approval letter must specifically reference this AD. (ii) AMOCs approved previously for AD 2015-05-02, are approved as AMOCs for the corresponding provisions of paragraphs (g) and (h) of this AD. (2) Contacting the Manufacturer: As of the effective date of this AD, for any requirement in this AD to obtain corrective actions from a manufacturer, the action must be accomplished using a method approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or the European Aviation Safety Agency (EASA); or Airbus's EASA Design Organization Approval (DOA). If approved by the DOA, the approval must include the DOA-authorized signature. (l) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA Airworthiness Directive 2015-0083, dated May 12, 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-2016-6429. (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 May 3, 2016. Michael Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2016-10914 Filed 5-10-16; 8:45 am] BILLING CODE 4910-13-P
![29198 Federal Register / Vol. 81, No. 91 / Wednesday, May 11, 2016 / Proposed Rules
(h) Retained Provision Regarding (4) AMOCs approved previously for AD cracking, accidental damage, or
Alternative Actions, Intervals With Updated 2007–11–13 are not approved as AMOCs corrosion in principal structural
Information with this AD. elements, and WFD, which could result
This paragraph restates the requirements of (l) Related Information in reduced structural integrity of the
paragraph (i) of AD 2007–11–13, with airplane.
updated information. Except as required by (1) For more information about this AD,
contact Eric Schrieber, Aerospace Engineer,
paragraph (i) of this AD: After the ALS has DATES: We must receive comments on
been revised as required by paragraph (g) of Airframe Branch, ANM–120L, FAA, Los
Angeles ACO, 3960 Paramount Boulevard, this proposed AD by June 27, 2016.
this AD, no alternative actions (e.g.,
inspections), intervals, may be used unless Lakewood, CA 90712–4137; phone: 562–627– ADDRESSES: You may send comments by
the actions, intervals, are approved as an 5348; fax: 562–627–5210; email: any of the following methods:
eric.schrieber@faa.gov.
alternative method of compliance (AMOC) in
(2) For service information identified in • Federal eRulemaking Portal: Go to
accordance with the procedures specified in http://www.regulations.gov. Follow the
paragraph (k) of this AD. this AD, contact Boeing Commercial
Airplanes, Attention: Data & Services instructions for submitting comments.
(i) New Maintenance or Inspection Program Management, 3855 Lakewood Boulevard, MC • Fax: 202–493–2251.
Revision D800–0019, Long Beach, CA 90846–0001;
telephone 206–544–5000, extension 2; fax • Mail: U.S. Department of
Within 180 days after the effective date of
this AD: Revise the maintenance or 206–766–5683; Internet https:// Transportation, Docket Operations, M–
inspection program, as applicable, to www.myboeingfleet.com. You may view this 30, West Building Ground Floor, Room
incorporate the information specified in service information at the FAA, Transport W12–140, 1200 New Jersey Avenue SE.,
Boeing 717–200 ALI, Report MDC–96K9063, Airplane Directorate, 1601 Lind Avenue SW., Washington, DC 20590.
Revision 14, dated July 2015. The initial Renton, WA. For information on the • Hand Delivery: U.S. Department of
compliance times for doing the actions availability of this material at the FAA, call
425–227–1221.
Transportation, Docket Operations, M–
specified in Boeing 717–200 ALI, Report
MDC–96K9063, Revision 14, dated July 2015,
30, West Building Ground Floor, Room
are at the later of the times specified in Issued in Renton, Washington, on April 28, W12–140, 1200 New Jersey Avenue SE.,
paragraphs (i)(1) and (i)(2) of this AD. 2016. Washington, DC, between 9 a.m. and 5
Compliance with this paragraph terminates Dionne Palermo, p.m., Monday through Friday, except
the requirements of paragraph (g) of this AD. Acting Manager, Transport Airplane Federal holidays.
(1) Within the applicable compliance times Directorate, Aircraft Certification Service. For service information identified in
specified in Boeing 717–200 ALI, Report
[FR Doc. 2016–10740 Filed 5–10–16; 8:45 am] this NPRM, contact Airbus,
MDC–96K9063, Revision 14, dated July 2015.
(2) Within 180 days from the effective date BILLING CODE 4910–13–P Airworthiness Office—EIAS, 1 Rond
of this AD. Point Maurice Bellonte, 31707 Blagnac
Cedex, France; telephone +33 5 61 93 36
(j) No Alternative Actions or Intervals DEPARTMENT OF TRANSPORTATION 96; fax +33 5 61 93 44 51; email
After the maintenance or inspection account.airworth-eas@airbus.com;
program has been revised as required by Federal Aviation Administration Internet http://www.airbus.com. You
paragraph (i) of this AD, no alternative may view this referenced service
actions (e.g., inspections) or intervals may be 14 CFR Part 39 information at the FAA, Transport
used unless the actions or intervals are
approved as an AMOC in accordance with [Docket No. FAA–2016–6429; Directorate Airplane Directorate, 1601 Lind Avenue
the procedures specified in paragraph (k) of Identifier 2015–NM–117–AD] SW., Renton, WA. For information on
this AD. the availability of this material at the
RIN 2120–AA64 FAA, call 425–227–1221.
(k) Alternative Methods of Compliance
(AMOCs) Airworthiness Directives; Airbus Examining the AD Docket
(1) The Manager, Los Angeles Aircraft Airplanes
You may examine the AD docket on
Certification Office (ACO), FAA, has the
authority to approve AMOCs for this AD, if
AGENCY: Federal Aviation the Internet at http://
requested using the procedures found in 14 Administration (FAA), DOT. www.regulations.gov by searching for
CFR 39.19. In accordance with 14 CFR 39.19, ACTION: Notice of proposed rulemaking and locating Docket No. FAA–2016–
send your request to your principal inspector (NPRM). 6429; or in person at the Docket
or local Flight Standards District Office, as Management Facility between 9 a.m.
appropriate. If sending information directly SUMMARY: We propose to supersede and 5 p.m., Monday through Friday,
to the manager of the ACO, send it to the Airworthiness Directive (AD) 2015–05– except Federal holidays. The AD docket
attention of the person identified in 02, for certain Airbus Model A318, contains this proposed AD, the
paragraph (l)(1) of this AD. A319, A320, and A321 series airplanes. regulatory evaluation, any comments
(2) Before using any approved AMOC,
AD 2015–05–02 requires revising the received, and other information. The
notify your appropriate principal inspector,
or lacking a principal inspector, the manager maintenance or inspection program to street address for the Docket Operations
of the local flight standards district office/ incorporate new, more restrictive office (telephone 800–647–5527) is in
certificate holding district office. airworthiness limitations. Since we the ADDRESSES section. Comments will
(3) An AMOC that provides an acceptable issued AD 2015–05–02, an evaluation be available in the AD docket shortly
level of safety may be used for any repair, by the design approval holder (DAH) after receipt.
modification, or alteration required by this indicates that principal structural
mstockstill on DSK3G9T082PROD with PROPOSALS
AD if it is approved by the Boeing FOR FURTHER INFORMATION CONTACT:
elements and certain life limited parts
Commercial Airplanes Organization are subject to widespread fatigue Sanjay Ralhan, Aerospace Engineer,
Designation Authorization (ODA) that has
damage (WFD). This proposed AD International Branch, ANM–116,
been authorized by the Manager, Los Angeles Transport Airplane Directorate, FAA,
ACO, FAA, to make those findings. To be would require revising the maintenance
or inspection program, as applicable, to 1601 Lind Avenue SW., Renton, WA
approved, the repair method, modification 98057–3356; telephone 425–227–1405;
deviation, or alteration deviation must meet incorporate new or revised structural
inspection requirements. We are fax 425–227–1149.
the certification basis of the airplane, and the
approval must specifically refer to this AD. proposing this AD to prevent fatigue SUPPLEMENTARY INFORMATION:
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![Federal Register / Vol. 81, No. 91 / Wednesday, May 11, 2016 / Proposed Rules 29199
Comments Invited existing and future airplanes subject to included in Airbus A318/A319/A320/A321
the WFD rule, the rule requires that Airworthiness Limitations Section (hereafter
We invite you to send any written referred to as ‘ALS’) documents. The Damage
relevant data, views, or arguments about DAHs establish a limit of validity (LOV)
Tolerant airworthiness limitation items are
this proposed AD. Send your comments of the engineering data that support the published in ALS Part 2, approved by EASA.
to an address listed under the structural maintenance program. The instructions contained in the ALS Part
ADDRESSES section. Include ‘‘Docket No.
Operators affected by the WFD rule may 2 have been identified as mandatory actions
FAA–2016–6429; Directorate Identifier not fly an airplane beyond its LOV, for continued airworthiness. Failure to
2015–NM–117–AD’’ at the beginning of unless an extended LOV is approved. comply with these instructions could result
The WFD rule (75 FR 69746, in an unsafe condition.
your comments. We specifically invite Previously, EASA issued AD 2013–0147
comments on the overall regulatory, November 15, 2010) does not require
(http://ad.easa.europa.eu/blob/easa_ad_
economic, environmental, and energy identifying and developing maintenance
2013_0147_superseded.pdf/AD_2013-
aspects of this proposed AD. We will actions if the DAHs can show that such 0147_1) [which corresponds to FAA AD
consider all comments received by the actions are not necessary to prevent 2014–23–15, Amendment 39–18031 (80 FR
closing date and may amend this WFD before the airplane reaches the 3871, January 26, 2015) to require
proposed AD based on those comments. LOV. Many LOVs, however, do depend accomplishment of all maintenance tasks as
on accomplishment of future described in ALS Part 2 at Revision 02. The
We will post all comments we new ALS Part 2 Revision 03 [Issue October
receive, without change, to http:// maintenance actions. As stated in the
WFD rule, any maintenance actions 27, 2014] includes new and/or more
www.regulations.gov, including any restrictive items and was approved on 27
personal information you provide. We necessary to reach the LOV will be October 2014.
will also post a report summarizing each mandated by airworthiness directives For the reason described above, this
substantive verbal contact we receive through separate rulemaking actions. [EASA] AD retains the requirements of EASA
about this proposed AD. In the context of WFD, this action is AD 2013–0147, which is superseded, and
necessary to enable DAHs to propose requires accomplishment of all maintenance
Discussion LOVs that allow operators the longest tasks as described in ALS Part 2 at Revision
operational lives for their airplanes, and 03.
Structural fatigue damage is
progressive. It begins as minute cracks, still ensure that WFD will not occur. The required action is revising the
and those cracks grow under the action This approach allows for an maintenance or inspection program to
of repeated stresses. This can happen implementation strategy that provides incorporate new or revised structural
because of normal operational flexibility to DAHs in determining the inspection requirements. The unsafe
conditions and design attributes, or timing of service information condition is fatigue cracking, accidental
because of isolated situations or development (with FAA approval), damage, or corrosion in principal
incidents such as material defects, poor while providing operators with certainty structural elements, and WFD, which
fabrication quality, or corrosion pits, regarding the LOV applicable to their could result in reduced structural
dings, or scratches. Fatigue damage can airplanes. integrity of the airplane. You may
occur locally, in small areas or On February 25, 2015, we issued AD examine the MCAI in the AD docket on
structural design details, or globally. 2015–05–02, Amendment 39–18112 (80 the Internet at http://
Global fatigue damage is general FR 15152, March 23, 2015) (‘‘AD 2015– www.regulations.gov by searching for
degradation of large areas of structure 05–02’’) to supersede AD 2014–23–15, and locating Docket No. FAA–2016–
with similar structural details and stress Amendment 39–18031 (80 FR 3871, 6429.
levels. Multiple-site damage is global January 26, 2015). AD 2015–05–02 Other Relevant Rulemaking
damage that occurs in a large structural requires revising the maintenance or
inspection program, as applicable, to We have issued NPRM Docket FAA–
element such as a single rivet line of a 2015–6539, Directorate Identifier 2015–
lap splice joining two large skin panels. incorporate new, more restrictive
airworthiness limitations on all Airbus NM–036–AD (80 FR 74723, November
Global damage can also occur in 30, 2015), for all Airbus Model A318–
multiple elements such as adjacent Model A318, A319, A320, and A321
series airplanes. 111 and –112 airplanes; Model A319–
frames or stringers. Multiple-site- 111, –112, –113, –114, and –115
damage and multiple-element-damage Since we issued AD 2015–05–02, an
evaluation by the DAH indicates that airplanes; Model A320–211, –212, and
cracks are typically too small initially to –214 airplanes; and Model A321–111,
be reliably detected with normal principal structural elements and
certain life limited parts are subject to –112, –211, –212, and –213 airplanes.
inspection methods. Without That NPRM proposes to require
intervention, these cracks will grow, widespread fatigue damage WFD. This
proposed AD would require revising the repetitive inspections that reduce the
and eventually compromise the compliance time for Task 712111–01,
structural integrity of the airplane, in a maintenance or inspection program, as
Detailed Inspection of Forward Engine
condition known as widespread fatigue applicable, to incorporate new or
Mount Installation. Therefore, Task
damage (WFD). As an airplane ages, revised structural inspection
712111–01 is not included in this
WFD will likely occur, and will requirements.
proposed AD.
certainly occur if the airplane is The European Aviation Safety Agency
operated long enough without any (EASA), which is the Technical Agent Related Service Information Under 1
intervention. for the Member States of the European CFR Part 51
The FAA’s WFD final rule (75 FR Union, has issued EASA Airworthiness Airbus has issued Part 2, Damage
mstockstill on DSK3G9T082PROD with PROPOSALS
69746, November 15, 2010) became Directive 2015–0083, dated May 12, Tolerant Airworthiness Limitation Items
effective on January 14, 2011. The WFD 2015 (referred to after this as the (DT–ALI), Revision 04, dated December
rule requires certain actions to prevent Mandatory Continuing Airworthiness 18, 2015, of the A318/A319/A320/A321
structural failure due to WFD Information, or ‘‘the MCAI’’), to correct Airworthiness Limitation Section (ALS).
throughout the operational life of an unsafe condition. The service information describes DT
certain existing transport category The MCAI states: ALIs associated with WFD.
airplanes and all of these airplanes that The airworthiness limitations for Airbus Airbus has also issued Part 2, Damage
will be certificated in the future. For A320 family aeroplanes are currently Tolerant Airworthiness Limitation Items
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![Federal Register / Vol. 81, No. 91 / Wednesday, May 11, 2016 / Proposed Rules 29201
required by AD 2015–05–02 is $170 per the FAA proposes to amend 14 CFR part Limitation Items (ALIs) specified in
product. 39 as follows: paragraphs (g)(1) and (g)(2) of this AD. The
We also estimate that it would take initial compliance time for accomplishing the
about 2 work-hours per product to PART 39—AIRWORTHINESS actions is at the applicable time identified in
comply with the basic requirements of DIRECTIVES the ALIs specified in paragraphs (g)(1) and
this proposed AD. The average labor (g)(2) of this AD; or within 4 months after
■ 1. The authority citation for part 39 March 2, 2015 (the effective date of AD 2014–
rate is $85 per work-hour. Based on
continues to read as follows: 23–15); whichever occurs later.
these figures, we estimate the cost of (1) Airbus A318/A319/A320/A321 ALS
this proposed AD on U.S. operators to Authority: 49 U.S.C. 106(g), 40113, 44701. Part 1—Safe Life Airworthiness Limitation
be $163,030, or $170 per product. Items, Revision 02, dated May 13, 2011.
§ 39.13 [Amended]
Authority for This Rulemaking (2) Airbus A318/A319/A320/A321 ALS
■ 2. The FAA amends § 39.13 by Part 2—Damage-Tolerant Airworthiness
Title 49 of the United States Code removing Airworthiness Directive (AD) Limitation Items (DT ALI), Revision 02, dated
specifies the FAA’s authority to issue 2015–05–02, Amendment 39–18112 (80 May 28, 2013.
rules on aviation safety. Subtitle I, FR 15152, March 23, 2015), and adding
the following new AD: (h) Retained Limitation: No Alternative
section 106, describes the authority of
Actions, Intervals, and/or Critical Design
the FAA Administrator. ‘‘Subtitle VII: Airbus: Docket No. FAA–2016–6429; Configuration Control Limitations (CDCCLs),
Aviation Programs,’’ describes in more Directorate Identifier 2015–NM–117–AD. With Exception
detail the scope of the Agency’s
(a) Comments Due Date This paragraph restates the requirements of
authority.
We must receive comments by June 27, paragraph (o) of AD 2015–05–02, with an
We are issuing this rulemaking under
2016. exception. Except as required by paragraph
the authority described in ‘‘Subtitle VII, (i) of this AD, after accomplishing the
Part A, Subpart III, Section 44701: (b) Affected ADs revision required by paragraph (g) of this AD,
General requirements.’’ Under that This AD replaces AD 2015–05–02, no alternative actions (e.g., inspections),
section, Congress charges the FAA with Amendment 39–18112 (80 FR 15152, March intervals, and/or CDCCLs may be used unless
promoting safe flight of civil aircraft in 23, 2015) (‘‘AD 2015–05–02’’). the actions, intervals, and/or CDCCLs are
air commerce by prescribing regulations approved as an alternative method of
(c) Applicability
for practices, methods, and procedures compliance (AMOC) in accordance with the
the Administrator finds necessary for This AD applies to the Airbus airplanes procedures specified in paragraph (k)(1) of
identified in paragraphs (c)(1) through (c)(4) this AD.
safety in air commerce. This regulation
of this AD, certificated in any category, with
is within the scope of that authority an original certificate of airworthiness or (i) New Requirement of This AD:
because it addresses an unsafe condition original export certificate of airworthiness Maintenance or Inspection Program
that is likely to exist or develop on issued on or before January 15, 2016. Revision
products identified in this rulemaking (1) Model A318–111, –112, –121, and –122 Within 60 days after the effective date of
action. airplanes. this AD, revise the maintenance or inspection
(2) Model A319–111, –112, –113, –114, program, as applicable, to incorporate the
Regulatory Findings –115, –131, –132, and –133 airplanes. ALIs specified in Airbus A318/A319/A320/
We determined that this proposed AD (3) Model A320–211, –212, –214, –231, A321 ALS Part 2, Damage Tolerant
would not have federalism implications –232, and –233 airplanes. Airworthiness Limitation Items (DT–ALI),
under Executive Order 13132. This (4) Model A321–111, –112, –131, –211, Revision 04, dated December 18, 2015; and
proposed AD would not have a –212, –213, –231, and –232 airplanes. Airbus A318/A319/A320/A321 ALS Part 2,
substantial direct effect on the States, on (d) Subject Damage Tolerant Airworthiness Limitation
the relationship between the national Items (DT–ALI), Variation 4.2, dated January
Air Transport Association (ATA) of 15, 2016. The initial compliance time for
Government and the States, or on the America Code 05, Periodic Inspections. accomplishing the actions is at the applicable
distribution of power and time identified in the ALIs specified in
responsibilities among the various (e) Reason
Airbus A318/A319/A320/A321 ALS Part 2,
levels of government. This AD was prompted by an evaluation by
Damage Tolerant Airworthiness Limitation
For the reasons discussed above, I the design approval holder (DAH) which
Items (DT–ALI), Revision 04, dated December
certify this proposed regulation: indicates that principal structural elements
18, 2015; and Airbus A318/A319/A320/A321
1. Is not a ‘‘significant regulatory and certain life limited parts are subject to
ALS Part 2, Damage Tolerant Airworthiness
action’’ under Executive Order 12866; widespread fatigue damage (WFD). We are
Limitation Items (DT–ALI), Variation 4.2,
issuing this AD to prevent fatigue cracking,
2. Is not a ‘‘significant rule’’ under the dated January 15, 2016; without exceeding
accidental damage, or corrosion in principal
DOT Regulatory Policies and Procedures structural elements, and WFD, which could the inspection intervals in the ALIs specified
(44 FR 11034, February 26, 1979); result in reduced structural integrity of the in the service information identified in
3. Will not affect intrastate aviation in airplane. paragraph (g)(2) of this AD, except for the
Alaska; and ALI tasks identified in paragraphs (i)(1)
4. Will not have a significant (f) Compliance though (i)(4) of this AD. Accomplishing these
economic impact, positive or negative, Comply with this AD within the actions terminates the requirements of
on a substantial number of small entities compliance times specified, unless already paragraph (g)(2) of this AD.
done. (1) Task 712111–01–1, ‘‘Detailed
under the criteria of the Regulatory
Inspection of Forward Engine Mount
Flexibility Act. (g) Retained Maintenance or Inspection Installation.’’
mstockstill on DSK3G9T082PROD with PROPOSALS
List of Subjects in 14 CFR Part 39 Program Revision, With No Changes (2) Task 712111–01–2, ‘‘Detailed
This paragraph restates the requirements of Inspection of Forward Engine Mount
Air transportation, Aircraft, Aviation paragraph (n) of AD 2015–05–02, with no Installation.’’
safety, Incorporation by reference, changes. Within 30 days after March 2, 2015 (3) Task 712111–01–3, ‘‘Detailed
Safety. (the effective date of AD 2014–23–15, Inspection of Forward Engine Mount
Amendment 39–18031 (80 FR 3871, January Installation.’’
The Proposed Amendment
26, 2015) (‘‘AD 2014–23–15’’)), revise the (4) Task 712111–01–4, ‘‘Detailed
Accordingly, under the authority maintenance or inspection program, as Inspection of Forward Engine Mount
delegated to me by the Administrator, applicable, to incorporate the Airworthiness Installation.’’
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![29202 Federal Register / Vol. 81, No. 91 / Wednesday, May 11, 2016 / Proposed Rules
(j) New No Alternative Actions and/or Issued in Renton, Washington, on May 3, • Hand Delivery: Deliver to Mail
Intervals 2016. address above between 9 a.m. and 5
After accomplishing the revision required Michael Kaszycki, p.m., Monday through Friday, except
by paragraph (i) of this AD, no alternative Acting Manager, Transport Airplane Federal holidays.
actions (e.g., inspections) and/or intervals Directorate, Aircraft Certification Service. For service information identified in
may be used unless the actions and/or [FR Doc. 2016–10914 Filed 5–10–16; 8:45 am] this NPRM, contact Boeing Commercial
intervals are approved as an AMOC in
accordance with the procedures specified in BILLING CODE 4910–13–P Airplanes, Attention: Data & Services
paragraph (k)(1) of this AD. Management, P.O. Box 3707, MC 2H–65,
Seattle, WA 98124–2207; telephone
(k) Other FAA AD Provisions DEPARTMENT OF TRANSPORTATION 206–544–5000, extension 1; fax 206–
The following provisions also apply to this 766–5680; Internet https://
AD: Federal Aviation Administration www.myboeingfleet.com. You may view
(1) Alternative Methods of Compliance this referenced service information at
(AMOCs): The Manager, International 14 CFR Part 39 the FAA, Transport Airplane
Branch, ANM–116, Transport Airplane
Directorate, FAA, has the authority to [Docket No. FAA–2016–6430; Directorate Directorate, 1601 Lind Avenue SW.,
approve AMOCs for this AD, if requested Identifier 2015–NM–176–AD;] Renton, WA. For information on the
using the procedures found in 14 CFR 39.19. availability of this material at the FAA,
RIN 2120–AA64
In accordance with 14 CFR 39.19, send your call 425–227–1221. It is also available
request to your principal inspector or local Airworthiness Directives; The Boeing on the Internet at http://
Flight Standards District Office, as www.regulations.gov by searching for
appropriate. If sending information directly Company Airplanes
and locating Docket No. FAA–2016–
to the International Branch, send it to ATTN: AGENCY: Federal Aviation 6430.
Sanjay Ralhan, Aerospace Engineer,
Administration (FAA), DOT.
International Branch, ANM–116, Transport Examining the AD Docket
Airplane Directorate, FAA, 1601 Lind ACTION: Notice of proposed rulemaking
Avenue SW., Renton, WA 98057–3356; (NPRM). You may examine the AD docket on
telephone 425–227–1405; fax 425–227–1149. the Internet at http://
Information may be emailed to: 9-ANM-116- SUMMARY: We propose to supersede www.regulations.gov by searching for
AMOC-REQUESTS@faa.gov. Airworthiness Directive (AD) 2005–13– and locating Docket No. FAA–2016–
(i) Before using any approved AMOC, 30, which applies to all Boeing Model 6430; or in person at the Docket
notify your appropriate principal inspector, 737–100, –200, and –200C series Management Facility between 9 a.m.
or lacking a principal inspector, the manager airplanes. AD 2005–13–30 currently and 5 p.m., Monday through Friday,
of the local flight standards district office/
requires repetitive inspections to detect except Federal holidays. The AD docket
certificate holding district office. The AMOC
approval letter must specifically reference discrepancies of certain fuselage skin contains this proposed AD, the
this AD. panels located just aft of the wheel well, regulatory evaluation, any comments
(ii) AMOCs approved previously for AD and repair if necessary. Since we issued received, and other information. The
2015–05–02, are approved as AMOCs for the AD 2005–13–30, an evaluation by the street address for the Docket Office
corresponding provisions of paragraphs (g) design approval holder (DAH) indicates (phone: 800–647–5527) is in the
and (h) of this AD. that the fuselage skin is subject to ADDRESSES section. Comments will be
(2) Contacting the Manufacturer: As of the widespread fatigue damage (WFD), and available in the AD docket shortly after
effective date of this AD, for any requirement we have received reports of cracks at the receipt.
in this AD to obtain corrective actions from
chem-milled steps in the fuselage skin. FOR FURTHER INFORMATION CONTACT:
a manufacturer, the action must be
accomplished using a method approved by This proposed AD would add new Wade Sullivan, Aerospace Engineer,
the Manager, International Branch, ANM– fuselage skin inspections for cracking, Airframe Branch, ANM–120S, FAA,
116, Transport Airplane Directorate, FAA; or inspections to detect missing or loose Seattle Aircraft Certification Office
the European Aviation Safety Agency fasteners and any disbonding or (ACO), 1601 Lind Avenue SW., Renton,
(EASA); or Airbus’s EASA Design cracking of bonded doublers, permanent WA 98057–3356; phone: 425–917–6430;
Organization Approval (DOA). If approved by repairs of time-limited repairs, related fax: 425–917–6590; email:
the DOA, the approval must include the investigative and corrective actions if
DOA-authorized signature. wade.sullivan@faa.gov.
necessary, and skin panel replacement.
SUPPLEMENTARY INFORMATION:
(l) Related Information We are proposing this AD to detect and
(1) Refer to Mandatory Continuing correct fatigue cracking of the fuselage Comments Invited
Airworthiness Information (MCAI) EASA skin panels, which could cause rapid We invite you to send any written
Airworthiness Directive 2015–0083, dated decompression of the airplane. relevant data, views, or arguments about
May 12, 2015, for related information. This DATES: We must receive comments on this proposed AD. Send your comments
MCAI may be found in the AD docket on the this proposed AD by June 27, 2016.
Internet at http://www.regulations.gov by to an address listed under the
searching for and locating Docket No. FAA– ADDRESSES: You may send comments, ADDRESSES section. Include ‘‘Docket No.
2016–6429. using the procedures found in 14 CFR FAA–2016–6430; Directorate Identifier
(2) For service information identified in 11.43 and 11.45, by any of the following 2015–NM–176–AD’’ at the beginning of
this AD, contact Airbus, Airworthiness methods: your comments. We specifically invite
Office—EIAS, 1 Rond Point Maurice • Federal eRulemaking Portal: Go to comments on the overall regulatory,
mstockstill on DSK3G9T082PROD with PROPOSALS
Bellonte, 31707 Blagnac Cedex, France; http://www.regulations.gov. Follow the economic, environmental, and energy
telephone +33 5 61 93 36 96; fax +33 5 61 instructions for submitting comments. aspects of this proposed AD. We will
93 44 51; email account.airworth-eas@
• Fax: 202–493–2251. consider all comments received by the
airbus.com; Internet http://www.airbus.com.
You may view this service information at the • Mail: U.S. Department of closing date and may amend this
FAA, Transport Airplane Directorate, 1601 Transportation, Docket Operations, M– proposed AD because of those
Lind Avenue SW., Renton, WA. For 30, West Building Ground Floor, Room comments.
information on the availability of this W12–140, 1200 New Jersey Avenue SE., We will post all comments we
material at the FAA, call 425–227–1221. Washington, DC 20590. receive, without change, to http://
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Document Created: 2016-05-11 01:11:48
Document Modified: 2016-05-11 01:11:48
| 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 27, 2016. | |
| 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 | 81 FR 29198 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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