80 FR 74047 - Airworthiness Directives; The Boeing Company Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 80, Issue 228 (November 27, 2015)
Federal Aviation Administration
Federal Register Volume 80, Issue 228 (November 27, 2015)
| Page Range | 74047-74052 | |
| FR Document | 2015-30008 |
[Federal Register Volume 80, Number 228 (Friday, November 27, 2015)] [Proposed Rules] [Pages 74047-74052] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2015-30008] ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2015-5812; Directorate Identifier 2015-NM-077-AD] RIN 2120-AA64 Airworthiness Directives; The Boeing Company Airplanes AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). ----------------------------------------------------------------------- SUMMARY: We propose to supersede Airworthiness Directive (AD) 2011-23- 05, which applies to certain The Boeing Company Model 737-300, -400, and -500 series airplanes. AD 2011-23-05 currently requires repetitive inspections for cracking of the 1.04-inch nominal diameter wire penetration hole, and applicable related investigative and corrective actions. Since we issued AD 2011-23-05, an evaluation by the design approval holder (DAH) indicates that the fuselage frames and frame reinforcements are subject to widespread fatigue damage (WFD). This proposed AD would add new inspection areas, a modification that terminates certain inspections, post-modification inspections, and repair if necessary. We are proposing this AD to detect and correct fatigue cracking of the fuselage frames and frame reinforcements, which could result in reduced structural integrity of the airplane. DATES: We must receive comments on this proposed AD by January 11, 2016. ADDRESSES: You may send comments, using the procedures found in 14 CFR 11.43 and 11.45, by any of the following methods:Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments. Fax: 202-493-2251. Mail: U.S. Department of Transportation, Docket Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue SE., Washington, DC 20590. Hand Delivery: Deliver to Mail address above between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For service information identified in this proposed AD, contact Boeing Commercial Airplanes, Attention: Data & Services Management, P. O. Box 3707, MC 2H-65, Seattle, WA 98124-2207; telephone 206-544-5000, extension 1; fax 206-766-5680; Internet https://www.myboeingfleet.com. You may view this referenced service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, Washington. For information on the availability of this material at the FAA, call 425- 227-1221. It is also available on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2015- 5812. 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- 5812; 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 Office (phone: 800-647-5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: Wayne Lockett, Aerospace Engineer, [[Page 74048]] Airframe Branch, ANM-120S, Seattle Aircraft Certification Office (ACO), FAA, 1601 Lind Avenue SW., Renton, Washington 98057-3356; phone: 425- 917-6447; fax: 425-917-6590; email: wayne.lockett@faa.gov. 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-2015-5812; Directorate Identifier 2015-NM-077-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 because of 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 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 October 20, 2011, we issued AD 2011-23-05, Amendment 39-16856 (76 FR 67343, November 1, 2011), for certain Model 737-300, -400, and - 500 series airplanes. AD 2011-23-05 superseded AD 2009-02-06 R1, Amendment 39-16015 (74 FR 45979, September 8, 2009). AD 2011-23-05 requires repetitive inspections for cracking of the 1.04-inch nominal diameter wire penetration hole, and applicable related investigative and corrective actions. AD 2011-23-05 resulted from reports of cracking in the frame, or in the frame and frame reinforcement, common to the 1.04-inch nominal diameter wire penetration hole intended for wire routing; and recent reports of multiple adjacent frame cracking found before the compliance time required by AD 2009-02-06 R1. We issued AD 2011-23-05 to detect and correct cracking in the fuselage frames and frame reinforcements, which could reduce the structural capability of the frames to sustain limit loads, and result in cracking in the fuselage skin and subsequent rapid depressurization of the airplane. Actions Since AD 2011-23-05, Amendment 39-16856 (76 FR 67343, November 1, 2011), Was Issued Since we issued AD 2011-23-05, Amendment 39-16856 (76 FR 67343, November 1, 2011), an evaluation by the DAH indicates that the fuselage frames and frame reinforcements are subject to WFD. Related Service Information Under 1 CFR Part 51 We reviewed Boeing Alert Service Bulletin 737-53A1279, Revision 2, dated April 21, 2015. The service information describes procedures for the following actions. Inspections of wire penetration holes, standoff/tooling holes, and the production fastener holes for cracking in the forward cargo compartment frames and frame reinforcements, between stringer (S) S-19 and S-22, on both left and right sides of the airplane. A preventive modification of frames between S-19 and S-22. Post-modification inspections. Repairs. 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 We are proposing this AD because we evaluated all the relevant information and determined the unsafe condition described previously is likely to exist or develop in other products of these same type designs. Proposed AD Requirements This proposed AD would retain all requirements of AD 2011-23-05, Amendment 39-16856 (76 FR 67343, November 1, 2011). This proposed AD would require accomplishing the actions specified in the service information described previously, except as discussed under ``Differences Between this Proposed AD and the Service Information.'' For information on the procedures and compliance times, see this service information at http://www.regulations.gov by searching for and locating Docket No. FAA-2015-5812. Differences Between This Proposed AD and the Service Information Boeing Alert Service Bulletin 737-53A1279, Revision 2, dated April 21, 2015, specifies to contact the manufacturer for instructions on how to [[Page 74049]] repair certain conditions, but this proposed AD would require repairing those conditions in one of the following ways: In accordance with a method that we approve; or Using data that meet the certification basis of the airplane, and that have been approved by the Boeing Commercial Airplanes Organization Designation Authorization (ODA) whom we have authorized to make those findings. Explanation of Compliance Time The compliance time for the modification specified in this proposed AD for addressing WFD was established to ensure that discrepant structure is modified before WFD develops in airplanes. Standard inspection techniques cannot be relied on to detect WFD before it becomes a hazard to flight. We will not grant any extensions of the compliance time to complete any AD-mandated service bulletin related to WFD without extensive new data that would substantiate and clearly warrant such an extension. Costs of Compliance We estimate that this proposed AD affects 605 airplanes of U.S. registry. We estimate the following costs to comply with this proposed AD: Estimated Costs ---------------------------------------------------------------------------------------------------------------- Cost on U.S. Action Labor cost Parts cost Cost per product operators ---------------------------------------------------------------------------------------------------------------- Inspections [retained actions 16 work-hours x $85 $0 $1,360 per $822,800 per from AD 2011-23-05, Amendment 39- per hour = $1,360 inspection cycle. inspection cycle. 16856 (76 FR 67343, November 1, per inspection 2011). cycle. Inspections [new proposed action] 32 work-hours x $85 0 $2,720 per $1,645,600 per per hour = $2,720 inspection cycle. inspection cycle. per inspection cycle. Modification [new proposed 32 work-hours x $85 0 $2,720............. $1,645,600. action]. per hour = $2,720. ---------------------------------------------------------------------------------------------------------------- We estimate the following costs to do any necessary repairs that would be required based on the results of the proposed inspection. We have no way of determining the number of aircraft that might need these repairs: On-Condition Costs ---------------------------------------------------------------------------------------------------------------- Cost per Action Labor cost Parts cost product ---------------------------------------------------------------------------------------------------------------- Repair................................ 18 work-hours x $85 per hour = None.................... $1,530 $1,530. ---------------------------------------------------------------------------------------------------------------- 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 have 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 that the 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) 2011-23-05, Amendment 39-16856 (76 FR 67343, November 1, 2011), and adding the following new AD: The Boeing Company: Docket No. FAA-2015-5812; Directorate Identifier 2015-NM-077-AD. (a) Comments Due Date The FAA must receive comments on this AD action by January 11, 2016. (b) Affected ADs This AD replaces AD 2011-23-05, Amendment 39-16856 (76 FR 67343, November 1, 2011). (c) Applicability This AD applies to The Boeing Company Model 737-300, -400, and - 500 series airplanes; certificated in any category; as identified in Boeing Alert Service Bulletin 737-53A1279, Revision 2, dated April 21, 2015. [[Page 74050]] (d) Subject Air Transport Association (ATA) of America Code 53, Fuselage. (e) Unsafe Condition This AD was prompted by an evaluation by the design approval holder (DAH) indicates that the fuselage frames and frame reinforcements are subject to widespread fatigue damage (WFD). We are issuing this AD to detect and correct fatigue cracking of the fuselage frames and frame reinforcements, 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 Inspection, With References To Terminating Actions This paragraph restates the requirements of paragraph (g) of AD 2011-23-05, Amendment 39-16856 (76 FR 67343, November 1, 2011), with references to terminating actions. At the applicable time specified in paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 737-53A1279, Revision 1, dated September 2, 2011, except as required by paragraphs (k)(1), (k)(2), and (k)(4) of this AD: Do a high frequency eddy current (HFEC) surface or HFEC hole/edge inspection for any cracking of the 1.04-inch nominal diameter wire penetration hole in the frame and frame reinforcement between stringer (S) S-20 and S-21, in accordance with Part 2 of the Accomplishment Instructions of Boeing Alert Service Bulletin 737-53A1279, Revision 1, dated September 2, 2011. Accomplishment of the applicable inspections required by paragraphs (m) and (n) of this AD terminates the inspections required by this paragraph. Accomplishment of the modification required by paragraph (p) of this AD terminates the inspections required by this paragraph for the modified area only. (h) Retained Repetitive Inspections, With References To Terminating Actions This paragraph restates the requirements of paragraph (h) of AD 2011-23-05, Amendment 39-16856 (76 FR 67343, November 1, 2011), with references to terminating actions. Within 4,500 flight cycles after accomplishment of the most recent inspection specified in Part 2 or Part 4 of the Accomplishment Instructions of Boeing Alert Service Bulletin 737-53A1279, Revision 1, dated September 2, 2011, or within 90 days after November 16, 2011 (the effective date of AD 2011-23- 05), whichever occurs later: Do an HFEC hole/edge inspection for cracking of the 1.04-inch nominal diameter wire penetration hole in the frame and frame reinforcement between S-20 and S-21, in accordance with Part 4 of the Accomplishment Instructions of Boeing Alert Service Bulletin 737-53A1279, Revision 1, dated September 2, 2011. Repeat the inspection thereafter at intervals not to exceed 4,500 flight cycles. Accomplishment of the applicable inspections required by paragraphs (m) and (n) of this AD, terminates the inspections required by this paragraph. Accomplishment of the modification specified in paragraph (j) or (p) of this AD terminates the repetitive inspections required by this paragraph for the modified area only. Accomplishment of the repair specified in paragraph (i) of this AD terminates the repetitive inspections required by this paragraph for the repaired area only. (i) Retained Repair, With No Changes This paragraph restates the requirements of paragraph (i) of AD 2011-23-05, Amendment 39-16856 (76 FR 67343, November 1, 2011), with no changes. If any cracking is found during any inspection required by paragraph (g) or (h) of this AD: Before further flight, repair the crack including doing all applicable related investigative and corrective actions, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 737-53A1279, Revision 1, dated September 2, 2011, except as required by paragraph (k)(3) of this AD. All applicable related investigative and corrective actions must be done before further flight. Accomplishment of the requirements of this paragraph terminates the repetitive inspection requirements of paragraph (h) of this AD for the repaired location of that frame. (j) Retained Optional Terminating Action, With New Limitation This paragraph restates the optional action provided in paragraph (j) of AD 2011-23-05, Amendment 39-16856 (76 FR 67343, November 1, 2011), with new limitation. Accomplishment of the preventive modification before the effective date of this AD, including doing all related investigative and applicable corrective actions, specified in Part 5 of the Accomplishment Instructions of Boeing Alert Service Bulletin 737-53A1279, Revision 1, dated September 2, 2011, except as required by paragraph (k)(3) of this AD, terminates the repetitive inspection requirements of paragraph (h) of this AD for the modified location of that frame, provided the modification is done before further flight after an inspection required by paragraph (g) or (h) of this AD has been done, and no cracking was found on that frame location during that inspection. (k) Retained Exceptions to Service Information Specifications, With No Changes This paragraph restates the requirements of paragraph (k) of AD 2011-23-05, Amendment 39-16856 (76 FR 67343, November 1, 2011), with no changes. The following exceptions apply as specified in paragraphs (g), (i), and (j) of this AD. (1) Where paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 737-53A1279, Revision 1, dated September 2, 2011, refers to a compliance time ``from date on Revision 1 of this service bulletin,'' this AD requires compliance within the specified compliance time after November 16, 2011 (the effective date of AD 2011-23-05, Amendment 39-16856 (76 FR 67343, November 1, 2011)). (2) For airplanes meeting all of the criteria specified in paragraphs (k)(2)(i), (k)(2)(ii), and (k)(2)(iii) of this AD: The compliance time for the initial inspection specified in Part 2 of the Accomplishment Instructions of Boeing Alert Service Bulletin 737-53A1279, Revision 1, dated September 2, 2011, and required by paragraph (g) of this AD, may be extended to 90 days after November 16, 2011 (the effective date of AD 2011-23-05, Amendment 39-16856 (76 FR 67343, November 1, 2011)). (i) Model 737-300 series airplanes in Group 1, line numbers 1001 through 2565 inclusive; (ii) Airplanes that have accumulated 40,000 or more total flight cycles as of November 16, 2011 (the effective date of AD 2011-23-05, Amendment 39-16856 (76 FR 67343, November 1, 2011)); and (iii) Airplanes on which the modification specified in Boeing Service Bulletin 737-53-1273, dated September 20, 2006; Revision 1, dated December 21, 2006; Revision 2, dated June 4, 2007; Revision 3, dated December 7, 2009; or Revision 4, dated July 23, 2010; has been done, including any configuration or deviation that has been approved as an AMOC during accomplishment of these service bulletins, by the Boeing Commercial Airplanes Organization Designation Authorization (ODA) that has been authorized by the Manager, Seattle Aircraft Certification Office (ACO) to make those findings. (3) Where Boeing Alert Service Bulletin 737-53A1279, Revision 1, dated September 2, 2011, specifies to contact Boeing for appropriate repair instructions: Before further flight, repair the crack using a method approved in accordance with the procedures specified in paragraph (u) of this AD. (4) The ``Condition'' column of paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 737-53A1279, Revision 1, dated September 2, 2011, refers to total flight cycles ``at the date of/on this service bulletin.'' However, this AD applies to the airplanes with the specified total flight cycles as of November 16, 2011 (the effective date of AD 2011-23-05, Amendment 39-16856 (76 FR 67343, November 1, 2011)). (l) Retained Credit for Previous Actions, With No Changes This paragraph restates the requirements of paragraph (l) of AD 2011-23-05, Amendment 39-16856 (76 FR 67343, November 1, 2011), with no changes. Actions done in accordance with Boeing Alert Service Bulletin 737-53A1279, dated December 18, 2007, before November 16, 2011 (the effective date of AD 2011-23-05), are acceptable for compliance with the corresponding actions required by paragraphs (g), (h), (i), and (j) of this AD. (m) New Requirement of This AD: Inspections of Frames and Frame Reinforcements Between S-19 and S-22 for Certain Airplanes on Which Certain Inspections Have Not Been Accomplished For airplanes identified as Groups 1 through 6, Configuration 3, in Boeing Alert Service Bulletin 737-53A1279, Revision 2, dated April 21, 2015, with 30,000 total flight cycles or fewer as of the effective date of this AD, on which any inspections specified in Boeing Alert Service Bulletin 737-53A1279, Revision 1, dated September 2, 2011, have not been accomplished: Except as required by paragraphs (t)(1) and (t)(2) of this AD, at [[Page 74051]] the applicable time specified in table 1 of paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 737-53A1279, Revision 2, dated April 21, 2015, or within 4,500 flight cycles after the effective date of this AD, whichever occurs later, do inspections for cracking at certain locations in the frames and frame reinforcements in accordance with ``Part 2--Initial Detail and HFEC Inspection'' of the Accomplishment Instructions of Boeing Alert Service Bulletin 737-53A1279, Revision 2, dated April 21, 2015. Repeat the inspections for cracking at certain locations in the frames and frame reinforcements as specified in ``Part 4--Repeat Detail and HFEC Inspections'' of the Accomplishment Instructions of Boeing Alert Service Bulletin 737-53A1279, Revision 2, dated April 21, 2015, thereafter at the applicable interval specified in paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 737-53A1279, Revision 2, dated April 21, 2015; or, before further flight after accomplishing an inspection and no cracking was found, do ``Part 5--Preventative Modification'' as specified in the Accomplishment Instructions of Boeing Alert Service Bulletin 737- 53A1279, Revision 2, dated April 21, 2015. Accomplishment of the preventive modification specified in this paragraph terminates the repetitive inspections required by this paragraph for the modified area only. Do all actions specified in this paragraph in accordance with Accomplishment Instructions of Boeing Alert Service Bulletin 737-53A1279, Revision 2, dated April 21, 2015. (n) New Requirement of This AD: Inspections of Frames and Frame Reinforcements Between S-19 and S-22 for Groups 1-6, Configuration 3, Airplanes For airplanes identified as Groups 1 through 6, Configuration 3, in Boeing Alert Service Bulletin 737-53A1279, Revision 2, dated April 21, 2015, with more than 30,000 total flight cycles as of the effective date of this AD, or that have been inspected as specified in Boeing Alert Service Bulletin 737-53A1279, Revision 1, dated September 2, 2011: Except as required by paragraphs (t)(1) and (t)(2) of this AD, at the applicable time specified in table 1 of paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 737-53A1279, Revision 2, dated April 21, 2015, do inspections for cracking at certain locations of the frames and frame reinforcements in accordance with ``Part 4--Repeat Detail and HFEC Inspections'' of the Accomplishment Instructions of Boeing Alert Service Bulletin 737-53A1279, Revision 2, dated April 21, 2015. Repeat the inspections thereafter at the applicable interval specified in paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 737-53A1279, Revision 2, dated April 21, 2015; or, before further flight after accomplishing an inspection and no cracking was found, do ``Part 5--Preventative Modification'' as specified in the Accomplishment Instructions of Boeing Alert Service Bulletin 737- 53A1279, Revision 2, dated April 21, 2015. Accomplishment of the preventive modification specified in this paragraph terminates the repetitive inspections required by this paragraph for the modified area only. (o) New Requirement of This AD: Repairs If any crack is found during any inspection required by paragraph (m) or (n) of this AD: Before further flight, repair, in accordance with ``Part 3--Repair'' of the Accomplishment Instructions of Boeing Alert Service Bulletin 737-53A1279, Revision 2, dated April 21, 2015, except where Boeing Alert Service Bulletin 737-53A1279, Revision 2, dated April 21, 2015, specifies to contact Boeing for damage removal and repair instructions, repair before further flight using a method approved in accordance with the procedures specified in paragraph (u) of this AD. Accomplishing a repair terminates the inspections required by paragraphs (m) and (n) of this AD in the repaired area only. Accomplishment of a repair terminates the modification required by paragraph (p) of this AD at the repaired location only. (p) New Requirement of This AD: Preventative Modification of the Frames Between S-19 and S-22 For airplanes identified as Groups 1 through 6, Configuration 3, in Boeing Alert Service Bulletin 737-53A1279, Revision 2, dated April 21, 2015: Except as required by paragraphs (t)(1) and (t)(2) of this AD, at the applicable time specified in table 2 of paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 737-53A1279, Revision 2, dated April 21, 2015, do the preventive modification of the frames between S-19 and S-22, in accordance with ``Part 5-- Preventative Modification'' of the Accomplishment Instructions of Boeing Alert Service Bulletin 737-53A1279, Revision 2, dated April 21, 2015. Accomplish of the modification required by this paragraph terminates the requirements of paragraphs (g), (h), (m), and (n) of this AD for the modified location only. (q) New Requirement of This AD: Inspections of Preventive Modification for Groups 1-3, Configuration 1, Airplanes For airplanes identified as Groups 1 through 3, Configuration 1, in Boeing Alert Service Bulletin 737-53A1279, Revision 2, dated April 21, 2015: Except as required by paragraph (t)(1) of this AD, at the applicable time specified in table 3 of paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 737-53A1279, Revision 2, dated April 21, 2015, do HFEC, LFEC, and detailed inspections for cracking in accordance with ``Part 7--INSPECTION OF PREVENTATIVE MODIFICATION'' of the Accomplishment Instructions of Boeing Alert Service Bulletin 737-53A1279, Revision 2, dated April 21, 2015. Repeat the inspections thereafter at the applicable interval specified in paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 737-53A1279, Revision 2, dated April 21, 2015. If any cracking is found during any inspection required by this paragraph, before further flight, repair using a method approved in accordance with the procedures specified in paragraph (u) of this AD. (r) New Requirement of This AD: Inspections of Preventive Modification for Groups 1-6, Configuration 2 For airplanes identified as Groups 1 through 6, Configuration 2, in Boeing Alert Service Bulletin 737-53A1279, Revision 2, dated April 21, 2015: Except as required by paragraph (t)(1)of this AD, at the applicable time specified in table 4 or table 6 of paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 737-53A1279, Revision 2, dated April 21, 2015, do HFEC, LFEC, and detailed inspections for cracking in accordance with ``Part 8--INSPECTION OF PREVENTATIVE MODIFICATION'' of the Accomplishment Instructions of Boeing Alert Service Bulletin 737-53A1279, Revision 2, dated April 21, 2015. Repeat the inspections thereafter at the applicable interval specified in table 4 or table 6 of paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 737-53A1279, Revision 2, dated April 21, 2015. If any cracking is found during any inspection required by this paragraph, before further flight, repair using a method approved in accordance with the procedures specified in paragraph (u) of this AD. (s) New Requirement of This AD: Inspections of Preventive Modification for Group 4-6, Configuration 1, Airplanes For airplanes identified as Group 4 through 6, Configuration 1, in Boeing Alert Service Bulletin 737-53A1279, Revision 2, dated April 21, 2015: At the applicable time specified in table 5 of paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 737-53A1279, Revision 2, dated April 21, 2015, except as required by paragraph (t)(1) of this AD: Do HFEC, LFEC and detailed inspections for cracking in accordance with ``Part 7--INSPECTION OF PREVENTATIVE MODIFICATION'' of the Accomplishment Instructions of Boeing Alert Service Bulletin 737-53A1279, Revision 2, dated April 21, 2015. Repeat the inspections thereafter at the applicable time specified in paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 737-53A1279, Revision 2, dated April 21, 2015. If any cracking is found during any inspection required by this paragraph, before further flight, repair using a method approved in accordance with the procedures specified in paragraph (u) of this AD. (t) New Requirement of This AD: Exceptions to Service Bulletin Specifications (1) Where paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 737-53A1279, Revision 2, dated April 21, 2015, refers to a compliance time ``after the Revision 2 date of this service bulletin,'' this AD requires compliance within the specified compliance time after the effective date of this AD. (2) The ``Condition'' column in table 1 and table 2 of paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 737-53A1279, Revision 2, dated April 21, 2015, refers to total flight cycles ``at the Revision 2 date of this service bulletin.'' However, this AD applies to the airplanes with the specified total flight cycles as of the effective date of this AD. [[Page 74052]] (u) Alternative Methods of Compliance (AMOCs) (1) The Manager, Los Angeles Aircraft Certification Office (ACO), 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 manager of the ACO, send it to the attention of the person identified in paragraph (v)(1) of this AD. Information may be emailed to: 9-ANM-LAACO-AMOC-Requests@faa.gov. (2) 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. (3) An AMOC that provides an acceptable level of safety may be used for any repair, modification, or alteration required by this AD if it is approved by the Boeing Commercial Airplanes Organization Designation Authorization (ODA) that has been authorized by the Manager, Seattle ACO, to make those findings. To be approved, the repair method, modification deviation, or alteration deviation must meet the certification basis of the airplane and the approval must specifically refer to this AD. (4) AMOCs approved for AD 2009-02-06, Amendment 39-15796 (74 FR 10469, March 11, 2009); AD 2009-02-06 R1, Amendment 39-16015 (74 FR 45979, September 6, 2009); and AD 2011-23-05, Amendment 39-16856 (76 FR 67343, November 1, 2011); are approved as AMOCs for the corresponding provisions of this AD. (v) Related Information (1) For more information about this AD, contact Wayne Lockett, Aerospace Engineer, Airframe Branch, ANM-120S, Seattle Aircraft Certification Office (ACO), FAA, 1601 Lind Avenue SW., Renton, Washington 98057-3356; phone: 425-917-6447; fax: 425-917-6590; email: wayne.lockett@faa.gov. (2) For service information identified in this AD, contact Boeing Commercial Airplanes, Attention: Data & Services Management, P. O. Box 3707, MC 2H-65, Seattle, WA 98124-2207; telephone 206-544- 5000, extension 1; fax 206-766-5680; Internet https://www.myboeingfleet.com. You may view this referenced service information at the FAA, 1601 Lind Avenue SW., Renton, Washington. For information on the availability of this material at the FAA, call 425-227-1221. Issued in Renton, Washington, on November 17, 2015. Jeffrey E. Duven, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2015-30008 Filed 11-25-15; 8:45 am] BILLING CODE 4910-13-P
![Federal Register / Vol. 80, No. 228 / Friday, November 27, 2015 / Proposed Rules 74047
of Airbus Service Bulletin A320–53–1287, with this AD; any procedures or tests that are that the fuselage frames and frame
dated July 29, 2014, before further flight, not identified as RC are recommended. Those reinforcements are subject to
repair using a method approved by the procedures and tests that are not identified widespread fatigue damage (WFD). This
Manager, International Branch, ANM–116, as RC may be deviated from using accepted
proposed AD would add new inspection
Transport Airplane Directorate, FAA; or the methods in accordance with the operator’s
European Aviation Safety Agency (EASA); or maintenance or inspection program without areas, a modification that terminates
Airbus’s EASA Design Organization obtaining approval of an AMOC, provided certain inspections, post-modification
Approval (DOA). the procedures and tests identified as RC can inspections, and repair if necessary. We
be done and the airplane can be put back in are proposing this AD to detect and
(h) Non-Terminating Repair Action an airworthy condition. Any substitutions or correct fatigue cracking of the fuselage
Accomplishment of a repair on an airplane changes to procedures or tests identified as frames and frame reinforcements, which
as required by paragraphs (g)(2) and (g)(3) of RC require approval of an AMOC. could result in reduced structural
this AD, does not constitute terminating
(l) Related Information integrity of the airplane.
action for the repetitive detailed inspection
required by paragraph (g)(1) of this AD, (1) Refer to Mandatory Continuing DATES: We must receive comments on
unless the approved repair indicates Airworthiness Information (MCAI) EASA this proposed AD by January 11, 2016.
otherwise. Airworthiness Directive 2014–0259, dated ADDRESSES: You may send comments,
December 5, 2014, for related information. using the procedures found in 14 CFR
(i) Terminating Action for the Repetitive This MCAI may be found in the AD docket
Detailed Inspection 11.43 and 11.45, by any of the following
on the Internet at http://www.regulations.gov
Modification of the belly fairing on any
methods:
by searching for and locating Docket No.
airplane in accordance with the
• Federal eRulemaking Portal: Go to
FAA–2015–5814.
Accomplishment Instructions of Airbus (2) For service information identified in http://www.regulations.gov. Follow the
Service Bulletin A320–53–1281, Revision 01, this AD, contact Airbus, Airworthiness instructions for submitting comments.
dated December 1, 2014, constitutes Office—EIAS, 1 Rond Point Maurice • Fax: 202–493–2251.
terminating action for the repetitive detailed Bellonte, 31707 Blagnac Cedex, France; • Mail: U.S. Department of
inspection required by paragraph (g)(1) of telephone +33 5 61 93 36 96; fax +33 5 61 Transportation, Docket Operations, M–
this AD for that airplane. 93 44 51; email account.airworth-eas@ 30, West Building Ground Floor, Room
airbus.com; Internet http://www.airbus.com. W12–140, 1200 New Jersey Avenue SE.,
(j) Credit for Previous Actions
You may view this service information at the Washington, DC 20590.
This paragraph provides credit for actions FAA, Transport Airplane Directorate, 1601 • Hand Delivery: Deliver to Mail
required by paragraph (i) of this AD, if those Lind Avenue SW., Renton, WA. For
actions were performed before the effective
address above between 9 a.m. and 5
information on the availability of this
date of this AD using Airbus Service Bulletin p.m., Monday through Friday, except
material at the FAA, call 425–227–1221.
A320–53–1281, dated July 29, 2014, which is Federal holidays.
not incorporated by reference in this AD. Issued in Renton, Washington, on For service information identified in
November 17, 2015. this proposed AD, contact Boeing
(k) Other FAA AD Provisions Jeffrey E. Duven, Commercial Airplanes, Attention: Data
The following provisions also apply to this Manager, Transport Airplane Directorate, & Services Management, P. O. Box 3707,
AD: Aircraft Certification Service. MC 2H–65, Seattle, WA 98124–2207;
(1) Alternative Methods of Compliance
[FR Doc. 2015–30023 Filed 11–25–15; 8:45 am] telephone 206–544–5000, extension 1;
(AMOCs): The Manager, International
Branch, ANM–116, Transport Airplane BILLING CODE 4910–13–P fax 206–766–5680; Internet https://
Directorate, FAA, has the authority to www.myboeingfleet.com. You may view
approve AMOCs for this AD, if requested this referenced service information at
using the procedures found in 14 CFR 39.19. DEPARTMENT OF TRANSPORTATION the FAA, Transport Airplane
In accordance with 14 CFR 39.19, send your Directorate, 1601 Lind Avenue SW.,
request to your principal inspector or local Federal Aviation Administration Renton, Washington. For information on
Flight Standards District Office, as the availability of this material at the
appropriate. If sending information directly 14 CFR Part 39 FAA, call 425–227–1221. It is also
to the International Branch, send it to ATTN:
[Docket No. FAA–2015–5812; Directorate available on the Internet at http://
Sanjay Ralhan, Aerospace Engineer,
International Branch, ANM–116, Transport Identifier 2015–NM–077–AD] www.regulations.gov by searching for
Airplane Directorate, FAA, 1601 Lind and locating Docket No. FAA–2015–
RIN 2120–AA64 5812.
Avenue SW., Renton, WA 98057–3356;
telephone 425–227–1405; fax 425–227–1149.
Airworthiness Directives; The Boeing Examining the AD Docket
Information may be emailed to: 9-ANM-116-
AMOC-REQUESTS@faa.gov. Before using Company Airplanes You may examine the AD docket on
any approved AMOC, notify your appropriate AGENCY: Federal Aviation the Internet at http://
principal inspector, or lacking a principal Administration (FAA), DOT. www.regulations.gov by searching for
inspector, the manager of the local flight and locating Docket No. FAA–2015–
standards district office/certificate holding ACTION: Notice of proposed rulemaking
(NPRM). 5812; or in person at the Docket
district office. The AMOC approval letter
must specifically reference this AD.
Management Facility between 9 a.m.
(2) Contacting the Manufacturer: For any SUMMARY: We propose to supersede and 5 p.m., Monday through Friday,
requirement in this AD to obtain corrective Airworthiness Directive (AD) 2011–23– except Federal holidays. The AD docket
actions from a manufacturer, the action must 05, which applies to certain The Boeing contains this proposed AD, the
be accomplished using a method approved Company Model 737–300, –400, and regulatory evaluation, any comments
mstockstill on DSK4VPTVN1PROD with PROPOSALS
by the Manager, International Branch, ANM– –500 series airplanes. AD 2011–23–05 received, and other information. The
116, Transport Airplane Directorate, FAA; or currently requires repetitive inspections street address for the Docket Office
the EASA; or Airbus’s EASA DOA. If for cracking of the 1.04-inch nominal (phone: 800–647–5527) is in the
approved by the DOA, the approval must ADDRESSES section. Comments will be
include the DOA-authorized signature.
diameter wire penetration hole, and
(3) Required for Compliance (RC): If any applicable related investigative and available in the AD docket shortly after
service information contains procedures or corrective actions. Since we issued AD receipt.
tests that are identified as RC, those 2011–23–05, an evaluation by the FOR FURTHER INFORMATION CONTACT:
procedures and tests must be done to comply design approval holder (DAH) indicates Wayne Lockett, Aerospace Engineer,
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![Federal Register / Vol. 80, No. 228 / Friday, November 27, 2015 / Proposed Rules 74049
repair certain conditions, but this we have authorized to make those flight. We will not grant any extensions
proposed AD would require repairing findings. of the compliance time to complete any
those conditions in one of the following AD-mandated service bulletin related to
Explanation of Compliance Time
ways: WFD without extensive new data that
The compliance time for the would substantiate and clearly warrant
• In accordance with a method that
modification specified in this proposed such an extension.
we approve; or AD for addressing WFD was established
• Using data that meet the to ensure that discrepant structure is Costs of Compliance
certification basis of the airplane, and modified before WFD develops in We estimate that this proposed AD
that have been approved by the Boeing airplanes. Standard inspection affects 605 airplanes of U.S. registry.
Commercial Airplanes Organization techniques cannot be relied on to detect We estimate the following costs to
Designation Authorization (ODA) whom WFD before it becomes a hazard to comply with this proposed AD:
ESTIMATED COSTS
Action Labor cost Parts cost Cost per product Cost on U.S. operators
Inspections [retained actions from AD 2011–23– 16 work-hours × $85 $0 $1,360 per inspection $822,800 per inspection
05, Amendment 39–16856 (76 FR 67343, No- per hour = $1,360 cycle. cycle.
vember 1, 2011). per inspection cycle.
Inspections [new proposed action] ...................... 32 work-hours × $85 0 $2,720 per inspection $1,645,600 per inspec-
per hour = $2,720 cycle. tion cycle.
per inspection cycle.
Modification [new proposed action] ..................... 32 work-hours × $85 0 $2,720 .......................... $1,645,600.
per hour = $2,720.
We estimate the following costs to do required based on the results of the determining the number of aircraft that
any necessary repairs that would be proposed inspection. We have no way of might need these repairs:
ON-CONDITION COSTS
Cost per
Action Labor cost Parts cost product
Repair ...................................... 18 work-hours × $85 per hour = $1,530 .................................. None ....................................... $1,530
Authority for This Rulemaking States, on the relationship between the PART 39—AIRWORTHINESS
national Government and the States, or DIRECTIVES
Title 49 of the United States Code on the distribution of power and
specifies the FAA’s authority to issue responsibilities among the various
rules on aviation safety. Subtitle I, ■ 1. The authority citation for part 39
levels of government. continues to read as follows:
Section 106, describes the authority of
the FAA Administrator. Subtitle VII, For the reasons discussed above, I Authority: 49 U.S.C. 106(g), 40113, 44701.
Aviation Programs, describes in more certify that the proposed regulation:
(1) Is not a ‘‘significant regulatory § 39.13 [Amended]
detail the scope of the Agency’s
authority. action’’ under Executive Order 12866, ■ 2. The FAA amends § 39.13 by
We are issuing this rulemaking under (2) Is not a ‘‘significant rule’’ under removing Airworthiness Directive (AD)
the authority described in Subtitle VII, the DOT Regulatory Policies and 2011–23–05, Amendment 39–16856 (76
Part A, Subpart III, Section 44701, Procedures (44 FR 11034, February 26, FR 67343, November 1, 2011), and
‘‘General requirements.’’ Under that 1979), adding the following new AD:
section, Congress charges the FAA with (3) Will not affect intrastate aviation The Boeing Company: Docket No. FAA–
promoting safe flight of civil aircraft in in Alaska, and 2015–5812; Directorate Identifier 2015–
air commerce by prescribing regulations (4) Will not have a significant NM–077–AD.
for practices, methods, and procedures economic impact, positive or negative,
(a) Comments Due Date
the Administrator finds necessary for on a substantial number of small entities
safety in air commerce. This regulation under the criteria of the Regulatory The FAA must receive comments on this
AD action by January 11, 2016.
is within the scope of that authority Flexibility Act.
because it addresses an unsafe condition (b) Affected ADs
List of Subjects in 14 CFR Part 39
that is likely to exist or develop on This AD replaces AD 2011–23–05,
products identified in this rulemaking Air transportation, Aircraft, Aviation Amendment 39–16856 (76 FR 67343,
mstockstill on DSK4VPTVN1PROD with PROPOSALS
action. safety, Incorporation by reference, November 1, 2011).
Safety. (c) Applicability
Regulatory Findings
The Proposed Amendment This AD applies to The Boeing Company
We have determined that this Model 737–300, –400, and –500 series
proposed AD would not have federalism Accordingly, under the authority airplanes; certificated in any category; as
implications under Executive Order delegated to me by the Administrator, identified in Boeing Alert Service Bulletin
13132. This proposed AD would not the FAA proposes to amend 14 CFR part 737–53A1279, Revision 2, dated April 21,
have a substantial direct effect on the 39 as follows: 2015.
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![74052 Federal Register / Vol. 80, No. 228 / Friday, November 27, 2015 / Proposed Rules
(u) Alternative Methods of Compliance DEPARTMENT OF TRANSPORTATION DATES: We must receive comments on
(AMOCs) this proposed AD by January 11, 2016.
(1) The Manager, Los Angeles Aircraft Federal Aviation Administration ADDRESSES: You may send comments,
Certification Office (ACO), FAA, has the using the procedures found in 14 CFR
authority to approve AMOCs for this AD, if 14 CFR Part 39 11.43 and 11.45, by any of the following
requested using the procedures found in 14 [Docket No. FAA–2015–5816; Directorate methods:
CFR 39.19. In accordance with 14 CFR 39.19, Identifier 2015–NM–029–AD] • Federal eRulemaking Portal: Go to
send your request to your principal inspector http://www.regulations.gov. Follow the
or local Flight Standards District Office, as RIN 2120–AA64 instructions for submitting comments.
appropriate. If sending information directly • Fax: 202–493–2251.
to the manager of the ACO, send it to the Airworthiness Directives; The Boeing • Mail: U.S. Department of
attention of the person identified in Company Airplanes Transportation, Docket Operations, M–
paragraph (v)(1) of this AD. Information may AGENCY: Federal Aviation 30, West Building Ground Floor, Room
be emailed to: 9-ANM-LAACO-AMOC- Administration (FAA), DOT. W12–140, 1200 New Jersey Avenue SE.,
Requests@faa.gov. Washington, DC 20590.
ACTION: Notice of proposed rulemaking
(2) Before using any approved AMOC,
(NPRM). • Hand Delivery: Deliver to Mail
notify your appropriate principal inspector, address above between 9 a.m. and 5
or lacking a principal inspector, the manager SUMMARY: We propose to supersede p.m., Monday through Friday, except
of the local flight standards district office/ Airworthiness Directive (AD) 2006–10– Federal holidays.
certificate holding district office. For service information identified in
16, which applies to all The Boeing
(3) An AMOC that provides an acceptable this proposed AD, contact Boeing
Company Model 747–100, 747–100B,
level of safety may be used for any repair, Commercial Airplanes, Attention: Data
747–100B SUD, 747–200B, 747–200C,
modification, or alteration required by this & Services Management, P. O. Box 3707,
747–200F, 747–300, 747–400, 747–
AD if it is approved by the Boeing MC 2H–65, Seattle, WA 98124–2207;
400D, 747–400F, 747SR, and 747SP
Commercial Airplanes Organization telephone: 206–544–5000, extension 1;
series airplanes. AD 2006–10–16
Designation Authorization (ODA) that has
requires, for certain airplanes, repetitive fax: 206–766–5680; Internet https://
been authorized by the Manager, Seattle
inspections for cracking of the outboard www.myboeingfleet.com. You may view
ACO, to make those findings. To be
and center sections of the horizontal this referenced service information at
approved, the repair method, modification
stabilizer, and repair if necessary. For the FAA, Transport Airplane
deviation, or alteration deviation must meet
certain other airplanes, AD 2006–10–16 Directorate, 1601 Lind Avenue SW.,
the certification basis of the airplane and the
requires a detailed inspection to Renton, WA. For information on the
approval must specifically refer to this AD.
(4) AMOCs approved for AD 2009–02–06, determine the type of fasteners, and availability of this material at the FAA,
Amendment 39–15796 (74 FR 10469, March related investigative actions and repair call 425–227–1221. It is also available
11, 2009); AD 2009–02–06 R1, Amendment if necessary. Since we issued AD 2006– on the Internet at http://
39–16015 (74 FR 45979, September 6, 2009); 10–16, additional cracking was found in www.regulations.gov by searching for
and AD 2011–23–05, Amendment 39–16856 the splice plates, hinge fittings, terminal and locating Docket No. FAA–2015–
(76 FR 67343, November 1, 2011); are fittings, the upper skin of the outboard 5816.
approved as AMOCs for the corresponding and center sections, and the rear spar Examining the AD Docket
provisions of this AD. webs before reaching the inspection
interval specified in AD 2006–10–16. You may examine the AD docket on
(v) Related Information Cracked and fractured Maraging steel the Internet at http://
(1) For more information about this AD, fasteners were also found. This www.regulations.gov by searching for
contact Wayne Lockett, Aerospace Engineer, proposed AD would reduce the and locating Docket No. FAA–2015–
Airframe Branch, ANM–120S, Seattle compliance time for certain inspections 5816; or in person at the Docket
Aircraft Certification Office (ACO), FAA, and would add repetitive inspections Management Facility between 9 a.m.
1601 Lind Avenue SW., Renton, Washington for cracking of the splice plates, hinge and 5 p.m., Monday through Friday,
98057–3356; phone: 425–917–6447; fax: 425– fittings, terminal fittings, the upper skin except Federal holidays. The AD docket
917–6590; email: wayne.lockett@faa.gov. of the outboard and center sections, and contains this proposed AD, the
(2) For service information identified in the rear spar webs in Zone B. This regulatory evaluation, any comments
this AD, contact Boeing Commercial proposed AD would also add an received, and other information. The
Airplanes, Attention: Data & Services inspection to determine whether street address for the Docket Office
Management, P. O. Box 3707, MC 2H–65, fasteners are magnetic in Zone C, (phone: 800–647–5527) is in the
Seattle, WA 98124–2207; telephone 206– repetitive ultrasonic inspections for ADDRESSES section. Comments will be
544–5000, extension 1; fax 206–766–5680; cracking and fractures of affected available in the AD docket shortly after
Internet https://www.myboeingfleet.com. You fasteners, and related investigative and receipt.
may view this referenced service information corrective actions if necessary. This FOR FURTHER INFORMATION CONTACT:
at the FAA, 1601 Lind Avenue SW., Renton, proposed AD would also add an Nathan Weigand, Aerospace Engineer,
Washington. For information on the optional modification, which would Airframe Branch, ANM–120S, FAA,
availability of this material at the FAA, call terminate certain repetitive inspections, Seattle Aircraft Certification Office,
425–227–1221. 1601 Lind Avenue SW., Renton, WA
and would add post-modification
mstockstill on DSK4VPTVN1PROD with PROPOSALS
Issued in Renton, Washington, on inspections and corrective action if 98057–3356; phone: 425–917–6428; fax:
November 17, 2015. necessary. We are proposing this AD to 425–917–6590; email:
Jeffrey E. Duven, detect and correct this cracking, which nathan.p.weigand@faa.gov.
Manager, Transport Airplane Directorate, could lead to reduced structural SUPPLEMENTARY INFORMATION:
Aircraft Certification Service. capability of the outboard and center
sections of the horizontal stabilizer and Comments Invited
[FR Doc. 2015–30008 Filed 11–25–15; 8:45 am]
could result in loss of control of the We invite you to send any written
BILLING CODE 4910–13–P
airplane. relevant data, views, or arguments about
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Document Created: 2015-12-14 14:04:59
Document Modified: 2015-12-14 14:04:59
| 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 January 11, 2016. | |
| Contact | Wayne Lockett, Aerospace Engineer, Airframe Branch, ANM-120S, Seattle Aircraft Certification Office (ACO), FAA, 1601 Lind Avenue SW., Renton, Washington 98057-3356; phone: 425- 917-6447; fax: 425-917-6590; email: [email protected] | |
| FR Citation | 80 FR 74047 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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