80 FR 61133 - Airworthiness Directives; The Boeing Company Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 80, Issue 196 (October 9, 2015)
Federal Aviation Administration
Federal Register Volume 80, Issue 196 (October 9, 2015)
| Page Range | 61133-61137 | |
| FR Document | 2015-25709 |
[Federal Register Volume 80, Number 196 (Friday, October 9, 2015)] [Proposed Rules] [Pages 61133-61137] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2015-25709] ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2015-3984; Directorate Identifier 2015-NM-033-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) 2008-13- 12 R1, which applies to certain The Boeing Company Model 737-100, -200, -200C, -300, -400, and -500 series airplanes. AD 2008-13-12 R1 currently requires various repetitive inspections for cracking of the upper frame to side frame splice of the fuselage, and other specified and corrective actions if necessary; and also provides for an optional preventive modification, which terminates the repetitive inspections. Since we issued AD 2008-13-12 R1, we have received reports of additional fatigue cracking of the upper frame to side frame splice of the fuselage, and two reports of severed frames. This proposed AD would add, for certain airplanes, an inspection to determine if the existing frame repair meets all specified requirements; for certain other airplanes, a new modification of the upper frame to side frame splice, which would terminate the repetitive inspections; and reduce certain inspection thresholds and repetitive intervals. We are proposing this AD to detect and correct fatigue cracking of the upper frame to side frame splice of the fuselage, which could result in reduced structural integrity of the frame and adjacent lap joint, causing increased loading in the fuselage skin, which will accelerate skin crack growth and result in decompression of the airplane. DATES: We must receive comments on this proposed AD by November 23, 2015. ADDRESSES: You may send comments, using the procedures found in 14 CFR 11.43 and 11.45, by any of the following methods:Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments. Fax: 202-493-2251. Mail: U.S. Department of Transportation, Docket Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue SE., Washington, DC 20590. Hand Delivery: 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, WA. 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- 3984. 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- 3984; 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, Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue SW., Renton, WA 98057-3356; phone: 425-917-6447; fax: 425-917-6590; email: [email protected]. 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-2015-3984; Directorate Identifier [[Page 61134]] 2015-NM-033-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 On June 12, 2008, we issued AD 2008-13-12, Amendment 39-15575 (73 FR 38905, July 8, 2008), which was revised by AD 2008-13-12 R1, Amendment 39-15719 (73 FR 67383, November 14, 2008), for certain The Boeing Company Model 737-100, -200, -200C, -300, -400, and -500 series airplanes. AD 2008-13-12 R1 requires various repetitive inspections for cracking of the upper frame to side frame splice of the fuselage, and other specified and corrective actions if necessary. AD 2008-13-12 R1 also provides for an optional preventive modification, which terminates the repetitive inspections. AD 2008-13-12 R1 resulted from a report that the upper frame of the fuselage was severed between stringers S- 13L and S-14L at station 747, and the adjacent frame at station 767 had a 1.3-inch-long crack at the same stringer location. We issued AD 2008- 13-12 R1 to detect and correct fatigue cracking of the upper frame to side frame splice of the fuselage, which could result in reduced structural integrity of the frame and adjacent lap joint. This reduced structural integrity can increase loading in the fuselage skin, which will accelerate skin crack growth and result in decompression of the airplane. Widespread Fatigue Damage (WFD) 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 design approval holder (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. Actions Since AD 2008-13-12 R1, Amendment 39-15719 (73 FR 67383, November 14, 2008) Was Issued Since AD 2008-13-12 R1, Amendment 39-15719 (73 FR 67383, November 14, 2008) was issued, we have received reports of additional fatigue cracking of the upper frame to side frame splice of the fuselage, and two reports of severed frames. Related Service Information Under 1 CFR Part 51 We reviewed Boeing Alert Service Bulletin 737-53A1261, Revision 1, dated January 30, 2015. The service information describes procedures for various repetitive inspections for cracking of the upper frame to side frame splice of the fuselage, an inspection to determine if the existing frame repair meets all specified requirements, and corrective actions if necessary. The service information also describes procedures for a new preventive modification, which would eliminate the need for the repetitive inspections. 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 the same type design. Proposed AD Requirements Although this proposed AD does not explicitly restate the requirements of AD 2008-13-12, Amendment 39-15575 (73 FR 38905, July 8, 2008), revised by AD 2008-13-12 R1, Amendment 39-15719 (73 FR 67383, November 14, 2008), this proposed AD would retain all of the requirements of those ADs. Those requirements are referenced in the service information identified previously, which, in turn, is referenced in paragraph (g) of this proposed AD. This proposed AD would require accomplishing the actions specified in the service information described previously. Refer to this service information for information on the procedures and compliance times. Explanation of Proposed 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 [[Page 61135]] WFD without extensive new data that would substantiate and clearly warrant such an extension. Costs of Compliance We estimate that this proposed AD affects 391 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 ---------------------------------------------------------------------------------------------------------------- Retained inspections from AD Between 18 and 38 work- $0 Between $1,530 and Between $598,230 2008-13-12, Amendment 39-15575 hours x $85 per hour, $3,230 per and $1,262,930 (73 FR 38905, July 8, 2008). depending on airplane inspection cycle. per inspection configuration = cycle. between $1,530 and $3,230 per inspection cycle. New inspections................ 213 work-hours x $85 0 $18,105 per $7,079,055 per per hour, $18,105 per inspection cycle. inspection cycle. inspection cycle. New modification............... 256 work-hours x $85 .............. $21,760........... $8,508,160. per hour = $21,760. ---------------------------------------------------------------------------------------------------------------- We currently have no specific cost estimates associated with the parts necessary for the proposed modification. We have received no definitive data that would enable us to provide a cost estimate for the on-condition actions specified in this proposed AD. Authority for This Rulemaking Title 49 of the United States Code specifies the FAA's authority to issue rules on aviation safety. Subtitle I, Section 106, describes the authority of the FAA Administrator. Subtitle VII, Aviation Programs, describes in more detail the scope of the Agency's authority. We are issuing this rulemaking under the authority described in Subtitle VII, Part A, Subpart III, Section 44701, ``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) 2008-13-12 R1, Amendment 39-15719 (73 FR 67383, November 14, 2008), and adding the following new AD: The Boeing Company: Docket No. FAA-2015-3984; Directorate Identifier 2015-NM-033-AD. (a) Comments Due Date The FAA must receive comments on this AD action by November 23, 2015. (b) Affected ADs This AD replaces AD 2008-13-12 R1, Amendment 39-15719 (73 FR 67383, November 14, 2008). (c) Applicability This AD applies to The Boeing Company Model 737-100, -200, - 200C, -300, -400, and -500 series airplanes, certificated in any category, as identified in Boeing Alert Service Bulletin 737- 53A1261, Revision 1, dated January 30, 2015. (d) Subject Air Transport Association (ATA) of America Code 53, Fuselage. (e) Unsafe Condition This AD was prompted by reports of fatigue cracking of the upper frame to side frame splice of the fuselage, and two reports of severed frames. We are issuing this AD to detect and correct fatigue cracking of the upper frame to side frame splice of the fuselage, which could result in reduced structural integrity of the frame and adjacent lap joint, causing increased loading in the fuselage skin, which will accelerate skin crack growth and result in decompression of the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Repetitive Inspections and Corrective Actions for Certain Airplanes (1) For Groups 1 through 3, Configurations 1, 3, 4, and 5 airplanes; Group 7, Configurations 1, 3, 4, and 5 airplanes; Groups 4 through 6, Configurations 1, 3, 4, and 6 airplanes; and Groups 8 through 11, Configurations 1, 3, 4, and 6 airplanes; as identified in Boeing Alert Service Bulletin 737-53A1261, Revision 1, dated January 30, 2015: Do the actions specified in paragraphs (g)(1)(i) and (g)(1)(ii) of this AD, and all applicable corrective actions, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 737-53A1261, Revision 1, dated January 30, 2015, except as required by paragraph (i)(3) of this AD. Do all applicable corrective actions before further flight. (i) At the applicable time specified in Tables 1, 2, 3, 5, 6, and 8 of paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 737-53A1261, Revision 1, dated January 30, 2015, except as required by paragraphs (i)(1) and (i)(2) of this AD: Do medium frequency eddy current inspections for cracking of the upper frame to side frame splice of the fuselage. (ii) Repeat the inspections specified in paragraph (g)(1)(i) of this AD at the applicable time specified in Tables 1, 2, 3, 5, 6, and 8 of paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 737-53A1261, Revision 1, dated January 30, 2015. [[Page 61136]] (2) For Groups 4 through 6, Configurations 2 and 5 airplanes; and Groups 8 through 11, Configurations 2 and 5 airplanes; as identified in Boeing Alert Service Bulletin 737-53A1261, Revision 1, dated January 30, 2015: Do the actions specified in paragraphs (g)(2)(i) and (g)(2)(ii) of this AD, and all applicable corrective actions, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 737-53A1261, Revision 1, dated January 30, 2015, except as required by paragraph (i)(3) of this AD. Do all applicable corrective actions before further flight. (i) At the applicable time specified in Tables 4 and 7 of paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 737-53A1261, Revision 1, dated January 30, 2015, except as required by paragraphs (i)(1) and (i)(2) of this AD: Do a detailed inspection to determine if the existing frame repair meets all requirements specified in Boeing Alert Service Bulletin 737-53A1261, Revision 1, dated January 30, 2015, and for any frame that does meet all requirements, do detailed and high frequency eddy current (HFEC) inspections for cracking of certain tied frames. (ii) Repeat the inspections for cracking specified in paragraph (g)(2)(i) of this AD at the applicable time specified in Tables 4 and 7 of paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 737-53A1261, Revision 1, dated January 30, 2015. (h) Post-Repair and Post-Modification Actions for Certain Airplanes For Group 1, Configurations 2 and 6 airplanes; Group 2, Configurations 2 and 6 airplanes; Group 3, Configurations 2 and 6 airplanes; and Group 7, Configurations 2 and 6 airplanes; as identified in Boeing Alert Service Bulletin 737-53A1261, Revision 1, dated January 30, 2015: Within 120 days after the effective date of this AD, do post-repair and post-modification actions using a method approved in accordance with the procedures specified in paragraph (n) of this AD. (i) Exceptions to Service Bulletin Specifications (1) Where Boeing Alert Service Bulletin 737-53A1261, Revision 1, dated January 30, 2015, specifies a compliance time ``after the Revision 1 date of this service bulletin,'' this AD requires compliance within the specified compliance time after the effective date of this AD. (2) Where the Condition column of paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 737-53A1261, Revision 1, dated January 30, 2015, specifies a condition based on whether an airplane has or has not been inspected, this AD bases the condition on whether an airplane has or has not been inspected as of the effective date of this AD. (3) Where Boeing Alert Service Bulletin 737-53A1261, Revision 1, dated January 30, 2015, specifies to contact Boeing for repair instructions: Before further flight, repair using a method approved in accordance with the procedures specified in paragraph (n) of this AD. (j) Post-Repair/Post-Modification Inspections Not Required The post-repair/post-modification inspections specified in Tables 12 through 17 of paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 737-53A1261, Revision 1, dated January 30, 2015, are not required by this AD, but may be used in support of compliance with section 121.1109(c)(2) or 129.109(c)(2) of the Federal Aviation Regulations (14 CFR 121.1109(c)(2) or 14 CFR 129.109(c)(2)). (k) Preventative Modification for Certain Airplanes For Groups 4 through 6, Configurations 1, 3, 4, and 6 airplanes; and Groups 8 through 11, Configurations 1, 3, 4, and 6 airplanes; as identified in Boeing Alert Service Bulletin 737-53A1261, Revision 1, dated January 30, 2015: Except as provided by paragraphs (i)(1) and (i)(2) of this AD, at the applicable time specified in Tables 3, 5, 6, and 8 in paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 737-53A1261, Revision 1, dated January 30, 2015, do the preventive modification, including doing detailed and HFEC inspections for cracking and applicable corrective actions in accordance with Part 4 of the Accomplishment Instructions of Boeing Alert Service Bulletin 737-53A1261, Revision 1, dated January 30, 2015, except as required by paragraph (i)(3) of this AD. Do all applicable corrective actions before further flight. Accomplishing the modification required by this paragraph terminates the inspections required by paragraph (g)(1) of this AD for the modified area only. (l) Terminating Action (1) For Groups 4 through 6, Configurations 1, 3, 4, and 6 airplanes; and Groups 8 through 11, Configurations 1, 3, 4, and 6 airplanes; as identified in Boeing Alert Service Bulletin 737- 53A1261, Revision 1, dated January 30, 2015: Accomplishing the preventive modification, including detailed and HFEC inspections for cracking and applicable corrective actions, in accordance with Part 4 of the Accomplishment Instructions of Boeing Alert Service Bulletin 737-53A1261, Revision 1, dated January 30, 2015, except as required by paragraph (i)(3) of this AD, terminates the inspections required by paragraph (g)(1) of this AD for the modified area only. (2) For Groups 4 through 6, Configurations 3 and 6 airplanes; and Groups 8 through 11, Configurations 3 and 6 airplanes; as identified in Boeing Alert Service Bulletin 737-53A1261, Revision 1, dated January 30, 2015: Accomplishing the repair, including HFEC inspections for cracking and applicable corrective actions, in accordance with Part 3 of the Accomplishment Instructions of Boeing Alert Service Bulletin 737-53A1261, Revision 1, dated January 30, 2015, except as required by paragraph (i)(3) of this AD, terminates the repetitive inspections required by paragraph (g)(1) of this AD for the repaired area only. (3) Accomplishment of the repair or the preventative modification specified in Boeing Message M-7200-02-1294, dated August 20, 2002, before the effective date of this AD terminates the repetitive inspections required by paragraph (g)(1) of this AD for the repaired or modified area only. (4) Accomplishment of the repair or the preventative modification in accordance with a method approved by the Manager, Los Angeles Aircraft Certification Office (ACO) terminates the repetitive inspections required by paragraph (g)(1) of this AD for the repaired or modified area only. (m) Credit for Previous Actions (1) This paragraph provides credit for the inspections required by paragraph (g) of this AD, if those inspections were performed before the effective date of this AD using Boeing Alert Service Bulletin 737-53A1261, dated January 19, 2006, which was incorporated by reference in AD 2008-13-12, Amendment 39-15575 (73 FR 38905, July 8, 2008). (2) This paragraph provides credit for the modification specified in paragraphs (k) and (l)(1) of this AD, if performed before the effective date of this AD using Boeing Alert Service Bulletin 737-53A1261, dated January 19, 2006, which was incorporated by reference in AD 2008-13-12, Amendment 39-15575 (73 FR 38905, July 8, 2008). (n) Alternative Methods of Compliance (AMOCs) (1) The Manager, Los Angeles 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 (o)(1) of this AD. Information may be emailed to: [email protected]. (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 required by this AD if it is approved by the Boeing Commercial Airplanes Organization Designation Authorization (ODA) that has been authorized by the Manager, Los Angeles ACO, to make those findings. For a repair method to be approved, the repair must meet the certification basis of the airplane, and the approval must specifically refer to this AD. (4) AMOCs approved for AD 2008-13-12, Amendment 39-15575 (73 FR 38905, July 8, 2008); and AD 2008-13-12 R1, Amendment 39-15719 (73 FR 67383, November 14, 2008); are approved as AMOCs for the corresponding provisions of paragraph (g) of this AD. (o) Related Information (1) For more information about this AD, contact Wayne Lockett, Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue SW., Renton, WA 98057-3356; phone: 425-917-6447; fax: 425-917-6590; email: [email protected]. (2) For service information identified in this AD, contact Boeing Commercial Airplanes, Attention: Data & Services [[Page 61137]] 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. Issued in Renton, Washington, on September 29, 2015. Jeffrey E. Duven, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2015-25709 Filed 10-8-15; 8:45 am] BILLING CODE 4910-13-P
![Federal Register / Vol. 80, No. 196 / Friday, October 9, 2015 / Proposed Rules 61133
72–A408, Circulation B, dated January 2015; Issued in Burlington, Massachusetts, on 11.43 and 11.45, by any of the following
ASB Mk. 522 Number 72–A413, Circulation October 2, 2015. methods:
A, dated January 2015; ASB Mk. 522 Number Colleen M. D’Alessandro, • Federal eRulemaking Portal: Go to
72–A412, Circulation B, dated January 2015; Directorate Manager, Engine & Propeller http://www.regulations.gov. Follow the
and ASB Mk. 601–22 Number 72–A207, Directorate, Aircraft Certification Service. instructions for submitting comments.
dated January 2015, to determine the new life [FR Doc. 2015–25607 Filed 10–8–15; 8:45 am] • Fax: 202–493–2251.
limits. BILLING CODE 4910–13–P • Mail: U.S. Department of
(2) For the RR Viper Mk. 601–22 turbojet Transportation, Docket Operations, M–
engine, remove compressor shaft, part 30, West Building Ground Floor, Room
number V900766, before the compressor DEPARTMENT OF TRANSPORTATION W12–140, 1200 New Jersey Avenue SE.,
shaft accumulates 20,720 flight cycles since Washington, DC 20590.
new. Federal Aviation Administration • Hand Delivery: Deliver to Mail
(f) Installation Prohibition address above between 9 a.m. and 5
14 CFR Part 39 p.m., Monday through Friday, except
After the effective date of this AD, do not
install any affected part identified in Federal holidays.
[Docket No. FAA–2015–3984; Directorate For service information identified in
paragraph (e) of this AD into any engine, nor Identifier 2015–NM–033–AD]
return any engine to service with any affected this proposed AD, contact Boeing
part identified in paragraph (e) of this AD RIN 2120–AA64 Commercial Airplanes, Attention: Data
installed, if any affected part exceeds the life & Services Management, P.O. Box 3707,
limit specified in the appropriate ASB Airworthiness Directives; The Boeing MC 2H–65, Seattle, WA 98124–2207;
identified in paragraph (e)(1) and/or the life Company Airplanes telephone 206–544–5000, extension 1;
limit identified in paragraph (e)(2) of this AD. fax 206–766–5680; Internet https://
AGENCY: Federal Aviation www.myboeingfleet.com. You may view
(g) Alternative Methods of Compliance Administration (FAA), DOT. this referenced service information at
(AMOCs)
ACTION: Notice of proposed rulemaking the FAA, Transport Airplane
The Manager, Engine Certification Office, (NPRM). Directorate, 1601 Lind Avenue SW.,
may approve AMOCs for this AD. Use the Renton, WA. For information on the
procedures found in 14 CFR 39.19 to make SUMMARY: We propose to supersede availability of this material at the FAA,
your request. You may email your request to: Airworthiness Directive (AD) 2008–13– call 425–227–1221. It is also available
ANE-AD-AMOC@faa.gov. 12 R1, which applies to certain The on the Internet at http://
(h) Related Information
Boeing Company Model 737–100, –200, www.regulations.gov by searching for
–200C, –300, –400, and –500 series and locating Docket No. FAA–2015–
(1) For more information about this AD, airplanes. AD 2008–13–12 R1 currently
contact Philip Haberlen, Aerospace Engineer,
3984.
requires various repetitive inspections
Engine Certification Office, FAA, Engine & for cracking of the upper frame to side Examining the AD Docket
Propeller Directorate, 12 New England frame splice of the fuselage, and other
Executive Park, Burlington, MA 01803;
You may examine the AD docket on
specified and corrective actions if the Internet at http://
phone: 781–238–7770; fax: 781–238–7199;
necessary; and also provides for an www.regulations.gov by searching for
email: philip.haberlen@faa.gov.
optional preventive modification, which and locating Docket No. FAA–2015–
(2) Refer to MCAI European Aviation
terminates the repetitive inspections. 3984; or in person at the Docket
Safety Agency AD 2015–0127R1, dated
August 14, 2015, for more information. You
Since we issued AD 2008–13–12 R1, we Management Facility between 9 a.m.
may examine the MCAI in the AD docket on
have received reports of additional and 5 p.m., Monday through Friday,
the Internet at http://www.regulations.gov by fatigue cracking of the upper frame to except Federal holidays. The AD docket
searching for and locating Docket No. FAA– side frame splice of the fuselage, and contains this proposed AD, the
2012–1331. two reports of severed frames. This regulatory evaluation, any comments
(3) RR ASB Mk. 521 Number 72–A408, proposed AD would add, for certain received, and other information. The
Circulation A, dated January 2015; ASB Mk. airplanes, an inspection to determine if street address for the Docket Office
521 Number 72–A408, Circulation B, dated the existing frame repair meets all (phone: 800–647–5527) is in the
January 2015; ASB Mk. 522 Number 72– specified requirements; for certain other ADDRESSES section. Comments will be
A413, Circulation A, dated January 2015; airplanes, a new modification of the available in the AD docket shortly after
ASB Mk. 522 Number 72–A412, Circulation upper frame to side frame splice, which receipt.
B, dated January 2015; and ASB Mk. 601–22 would terminate the repetitive FOR FURTHER INFORMATION CONTACT:
Number 72–A207, dated January 2015, can be inspections; and reduce certain Wayne Lockett, Aerospace Engineer,
obtained from RR, using the contact inspection thresholds and repetitive Airframe Branch, ANM–120S, FAA,
information in paragraph (h)(4) of this intervals. We are proposing this AD to Seattle Aircraft Certification Office,
proposed AD. detect and correct fatigue cracking of the 1601 Lind Avenue SW., Renton, WA
(4) For service information identified in upper frame to side frame splice of the 98057–3356; phone: 425–917–6447; fax:
this AD, contact DA Services Operations fuselage, which could result in reduced 425–917–6590; email: wayne.lockett@
Room at Rolls-Royce plc, Defense Sector structural integrity of the frame and faa.gov.
Bristol, WH–70, P.O. Box 3, Filton, Bristol adjacent lap joint, causing increased
BS34 7QE, United Kingdom; phone: +44 (0) loading in the fuselage skin, which will SUPPLEMENTARY INFORMATION:
rmajette on DSK7SPTVN1PROD with PROPOSALS
117 97 90700; fax: +44 (0) 117 97 95498; accelerate skin crack growth and result Comments Invited
email: defence-operations-room@rolls- in decompression of the airplane.
royce.com. We invite you to send any written
DATES: We must receive comments on
(5) You may view this service information relevant data, views, or arguments about
this proposed AD by November 23, this proposed AD. Send your comments
at the FAA, Engine & Propeller Directorate,
2015. to an address listed under the
12 New England Executive Park, Burlington,
MA. For information on the availability of ADDRESSES: You may send comments, ADDRESSES section. Include ‘‘Docket No.
this material at the FAA, call 781–238–7125. using the procedures found in 14 CFR FAA–2015–3984; Directorate Identifier
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![Federal Register / Vol. 80, No. 196 / Friday, October 9, 2015 / Proposed Rules 61135
WFD without extensive new data that Costs of Compliance We estimate the following costs to
would substantiate and clearly warrant We estimate that this proposed AD comply with this proposed AD:
such an extension. affects 391 airplanes of U.S. registry.
ESTIMATED COSTS
Action Labor cost Parts cost Cost per product Cost on U.S. operators
Retained inspections Between 18 and 38 work-hours × $85 per hour, $0 Between $1,530 and Between $598,230 and
from AD 2008–13–12, depending on airplane configuration = be- $3,230 per inspection $1,262,930 per in-
Amendment 39– tween $1,530 and $3,230 per inspection cycle. spection cycle.
15575 (73 FR 38905, cycle.
July 8, 2008).
New inspections ............ 213 work-hours × $85 per hour, $18,105 per in- 0 $18,105 per inspection $7,079,055 per inspec-
spection cycle. cycle. tion cycle.
New modification ........... 256 work-hours × $85 per hour = $21,760 ........ ........................ $21,760 ........................ $8,508,160.
We currently have no specific cost Procedures (44 FR 11034, February 26, (d) Subject
estimates associated with the parts 1979), Air Transport Association (ATA) of
necessary for the proposed (3) Will not affect intrastate aviation America Code 53, Fuselage.
modification. in Alaska, and (e) Unsafe Condition
We have received no definitive data (4) Will not have a significant
economic impact, positive or negative, This AD was prompted by reports of
that would enable us to provide a cost
on a substantial number of small entities fatigue cracking of the upper frame to side
estimate for the on-condition actions frame splice of the fuselage, and two reports
specified in this proposed AD. under the criteria of the Regulatory of severed frames. We are issuing this AD to
Flexibility Act. detect and correct fatigue cracking of the
Authority for This Rulemaking
List of Subjects in 14 CFR Part 39 upper frame to side frame splice of the
Title 49 of the United States Code fuselage, which could result in reduced
specifies the FAA’s authority to issue Air transportation, Aircraft, Aviation structural integrity of the frame and adjacent
rules on aviation safety. Subtitle I, safety, Incorporation by reference, lap joint, causing increased loading in the
Section 106, describes the authority of Safety. fuselage skin, which will accelerate skin
crack growth and result in decompression of
the FAA Administrator. Subtitle VII, The Proposed Amendment the airplane.
Aviation Programs, describes in more
detail the scope of the Agency’s Accordingly, under the authority (f) Compliance
authority. delegated to me by the Administrator,
Comply with this AD within the
We are issuing this rulemaking under the FAA proposes to amend 14 CFR part compliance times specified, unless already
the authority described in Subtitle VII, 39 as follows: done.
Part A, Subpart III, Section 44701, PART 39—AIRWORTHINESS (g) Repetitive Inspections and Corrective
‘‘General requirements.’’ Under that DIRECTIVES Actions for Certain Airplanes
section, Congress charges the FAA with (1) For Groups 1 through 3, Configurations
promoting safe flight of civil aircraft in ■ 1. The authority citation for part 39 1, 3, 4, and 5 airplanes; Group 7,
air commerce by prescribing regulations continues to read as follows: Configurations 1, 3, 4, and 5 airplanes;
for practices, methods, and procedures Authority: 49 U.S.C. 106(g), 40113, 44701. Groups 4 through 6, Configurations 1, 3, 4,
the Administrator finds necessary for and 6 airplanes; and Groups 8 through 11,
safety in air commerce. This regulation § 39.13 [Amended] Configurations 1, 3, 4, and 6 airplanes; as
is within the scope of that authority identified in Boeing Alert Service Bulletin
■ 2. The FAA amends § 39.13 by
737–53A1261, Revision 1, dated January 30,
because it addresses an unsafe condition removing Airworthiness Directive (AD) 2015: Do the actions specified in paragraphs
that is likely to exist or develop on 2008–13–12 R1, Amendment 39–15719 (g)(1)(i) and (g)(1)(ii) of this AD, and all
products identified in this rulemaking (73 FR 67383, November 14, 2008), and applicable corrective actions, in accordance
action. adding the following new AD: with the Accomplishment Instructions of
The Boeing Company: Docket No. FAA– Boeing Alert Service Bulletin 737–53A1261,
Regulatory Findings Revision 1, dated January 30, 2015, except as
2015–3984; Directorate Identifier 2015–
We have determined that this NM–033–AD. required by paragraph (i)(3) of this AD. Do all
proposed AD would not have federalism applicable corrective actions before further
(a) Comments Due Date flight.
implications under Executive Order
The FAA must receive comments on this (i) At the applicable time specified in
13132. This proposed AD would not Tables 1, 2, 3, 5, 6, and 8 of paragraph 1.E.,
have a substantial direct effect on the AD action by November 23, 2015.
‘‘Compliance,’’ of Boeing Alert Service
States, on the relationship between the (b) Affected ADs Bulletin 737–53A1261, Revision 1, dated
national Government and the States, or This AD replaces AD 2008–13–12 R1, January 30, 2015, except as required by
on the distribution of power and Amendment 39–15719 (73 FR 67383, paragraphs (i)(1) and (i)(2) of this AD: Do
rmajette on DSK7SPTVN1PROD with PROPOSALS
responsibilities among the various November 14, 2008). medium frequency eddy current inspections
levels of government. for cracking of the upper frame to side frame
(c) Applicability splice of the fuselage.
For the reasons discussed above, I
This AD applies to The Boeing Company (ii) Repeat the inspections specified in
certify that the proposed regulation: Model 737–100, –200, –200C, –300, –400, paragraph (g)(1)(i) of this AD at the
(1) Is not a ‘‘significant regulatory and –500 series airplanes, certificated in any applicable time specified in Tables 1, 2, 3, 5,
action’’ under Executive Order 12866, category, as identified in Boeing Alert 6, and 8 of paragraph 1.E., ‘‘Compliance,’’ of
(2) Is not a ‘‘significant rule’’ under Service Bulletin 737–53A1261, Revision 1, Boeing Alert Service Bulletin 737–53A1261,
the DOT Regulatory Policies and dated January 30, 2015. Revision 1, dated January 30, 2015.
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![Federal Register / Vol. 80, No. 196 / Friday, October 9, 2015 / Proposed Rules 61137
Management, P.O. Box 3707, MC 2H–65, CCL are clear, do not inadvertently Background
Seattle, WA 98124–2207; telephone 206– control items in normal commercial use,
544–5000, extension 1; fax 206–766–5680; The Bureau of Industry and Security
account for technological developments, (BIS), Department of Commerce
Internet https://www.myboeingfleet.com. You
and properly implement the national maintains the Export Administration
may view this referenced service information
at the FAA, Transport Airplane Directorate, security and foreign policy objectives of Regulations, including the Commerce
1601 Lind Avenue SW., Renton, Washington. the reform effort. This notice also Control List (CCL). The Export Control
For information on the availability of this furthers the retrospective regulatory Reform Initiative, a fundamental reform
material at the FAA, call 425–227–1221. review directed by the President in of the U.S. export control system, has
Issued in Renton, Washington, on Executive Order 13563. resulted in transfer to the CCL of items
September 29, 2015. DATES: Comments must be received by that the President has determined do
Jeffrey E. Duven, BIS no later than December 8, 2015. not warrant control on the United States
Manager, Transport Airplane Directorate, Munitions List (USML), including
Aircraft Certification Service. ADDRESSES: Comments may be certain military vehicles, vessels of war,
[FR Doc. 2015–25709 Filed 10–8–15; 8:45 am]
submitted to the Federal rulemaking submersible vessels, oceanographic
portal (http://www.regulations.gov). You equipment, auxiliary and miscellaneous
BILLING CODE 4910–13–P
can find this notice by searching on its military equipment, and related items
regulations.gov docket number, which is therefor. The USML is part of the
BIS–2015–0039. Comments may also be International Traffic in Arms
DEPARTMENT OF COMMERCE
submitted via email to Regulations maintained by the
Bureau of Industry and Security publiccommments@bis.doc.gov or on Department of State. Through this
paper to Regulatory Policy Division, notice, BIS is seeking comments to
15 CFR Part 774 Bureau of Industry and Security, Room perform a complementary review of
2099B, U.S. Department of Commerce, military vehicles, vessels of war,
[Docket No. 150820757–5757–01] Washington, DC 20230. Please refer to submersible vessels, oceanographic
RIN 0694–XC025 in all comments and equipment, auxiliary and miscellaneous
Commerce Control List: Request for in the subject line of email comments.
Comments Regarding Controls on military equipment, and related items
All comments (including any personally on the CCL, concurrent with the
Military Vehicles, Vessels of War, identifying information) will be made
Submersible Vessels, Oceanographic Department of State’s review of the
available for public inspection and controls implemented in its recent
Equipment, and Auxiliary and copying. Commerce’s full plan for
Miscellaneous Military Equipment revisions to Categories VI, VII, XIII, and
retrospective regulatory review can be XX of the USML (which control surface
AGENCY: Bureau of Industry and accessed at: http://open.commerce.gov/ vessels of war and special naval
Security, Commerce. news/2011/08/23/commerce-plan- equipment, military ground vehicles,
ACTION: Notice of inquiry. retrospective-analysis-existing-rules. miscellaneous military articles and
FOR FURTHER INFORMATION CONTACT: For materials, submersible vessels, and
SUMMARY: The Bureau of Industry and related items therefor), to ensure that
questions regarding ground vehicles and
Security (BIS), Department of the descriptions of these items on the
related items (ECCNs 0A606, 0B606,
Commerce, maintains the Export CCL are clear, do not inadvertently
0C606, 0D606 and 0E606), contact Gene
Administration Regulations, including control items in normal commercial use,
Christiansen, Office of National Security
the Commerce Control List (CCL). The account for technological developments,
and Technology Transfer Controls, at
Export Control Reform Initiative, a and properly implement the national
202–482–2984 or gene.christiansen@
fundamental reform of the U.S. export security and foreign policy objectives of
bis.doc.gov. For questions regarding
control system, has resulted in transfer the reform effort.
surface vessels and related items
to the CCL of items that the President Specifically, BIS is soliciting
(ECCNs 8A609, 8B609, 8C609, 8D609
has determined do not warrant control comments on the clarity, usability and
and 8E609) or submersible vessels and
on the United States Munitions List any other matters related to
related items (ECCNs 8A620, 8B620,
(USML), including certain military implementation of the ‘‘600 series’’
8D620, and 8E620), contact Alexander
vehicles, vessels of war, submersible Export Control Classification Numbers
Lopes, Office of Nonproliferation and
vessels, oceanographic equipment, (ECCNs) that control the following
Treaty Compliance, at 202–482–4875 or
auxiliary and miscellaneous military items, as well as certain items related
alexander.lopes@bis.doc.gov. For
equipment, and related items therefor. thereto: military vehicles (ECCNs
questions regarding miscellaneous
The USML is part of the International 0A606, 0B606, 0C606, 0D606, and
equipment, materials, and related items
Traffic in Arms Regulations maintained 0E606); vessels of war (ECCNs 8A609,
(ECCNs 0A617, 0B617, 0C617, 0D617,
by the Department of State. Through 8B609, 8C609, 8D609, and 8E609);
and 0E617), contact Michael Rithmire,
this notice, BIS is seeking public submersible vessels and oceanographic
Office of National Security and
comments to perform a complementary equipment (ECCNs 8A620, 8B620,
Technology Transfer Controls, at 202–
review of the aforementioned items on 8D620, and 8E620); and auxiliary and
482–6105 or michael.rithmire@
the CCL, concurrent with the miscellaneous military equipment
bis.doc.gov. For questions regarding
Department of State’s review of the (ECCNs 0A617, 0B617, 0C617, 0D617,
license applications for any of the items
controls implemented in its recent and 0E617).
specified above, contact Elena Love,
rmajette on DSK7SPTVN1PROD with PROPOSALS
revisions to Categories VI, VII, XIII, and
Thomas DeFee or Jeffery Leitz of the The Export Control Reform Initiative:
XX of the USML (which control surface
Office of Strategic Industries and USML Review and the CCL
vessels of war and special naval
Economic Security, by phone, at 202–
equipment, military ground vehicles, A core element of the Export Control
482–4506, or by email, at Elena.Love@
miscellaneous military articles and Reform (ECR) Initiative has been the
bis.doc.gov, Thomas.DeFee@bis.doc.gov,
materials, submersible vessels, and streamlining of categories on the USML
or Jeffrey.Leitz@bis.doc.gov.
related items therefor), to ensure that and the control on the CCL of those
the descriptions of these items on the SUPPLEMENTARY INFORMATION: items that the President determines do
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Document Created: 2015-12-15 08:34:18
Document Modified: 2015-12-15 08:34:18
| Category | Regulatory Information | |
| Collection | Federal Register | |
| sudoc Class | AE 2.7: GS 4.107: AE 2.106: | |
| Publisher | Office of the Federal Register, National Archives and Records Administration | |
| Section | Proposed Rules | |
| Action | Notice of proposed rulemaking (NPRM). | |
| Dates | We must receive comments on this proposed AD by November 23, 2015. | |
| Contact | Wayne Lockett, Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue SW., Renton, WA 98057-3356; phone: 425-917-6447; fax: 425-917-6590; email: [email protected] | |
| FR Citation | 80 FR 61133 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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