80 FR 45453 - Airworthiness Directives; The Boeing Company Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 80, Issue 146 (July 30, 2015)
Federal Aviation Administration
Federal Register Volume 80, Issue 146 (July 30, 2015)
| Page Range | 45453-45457 | |
| FR Document | 2015-18559 |
[Federal Register Volume 80, Number 146 (Thursday, July 30, 2015)] [Proposed Rules] [Pages 45453-45457] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2015-18559] ======================================================================= ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2015-2965; Directorate Identifier 2014-NM-227-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) 2012-17- 13, which applies to certain The Boeing Company Model 707 airplanes, and Model 720 and 720B series airplanes. For certain airplanes, AD 2012-17-13 required using redefined flight cycle counts; determining the type of material of the horizontal stabilizer, rear spar, and upper and lower chords on the inboard and outboard ends of the rear spar; repetitively inspecting for cracking of the horizontal stabilizer components; and repairing or replacing the chord, or modifying chord segments made of 7079 aluminum, if necessary. For all airplanes, AD 2012-17-13 required inspecting certain structurally significant items, and repairing discrepancies if necessary. Since we issued AD 2012-17- 13, we have determined that all chord segments made of 7079 aluminum must be replaced with new, improved chord segments made of 7075 aluminum. This proposed AD would add a requirement to replace all chord segments made of 7079 aluminum with new, improved chord segments made of 7075 aluminum. We are proposing this AD to detect and correct stress corrosion and potential early fatigue cracking in the horizontal stabilizer, which could result in reduced structural integrity of the horizontal stabilizer. DATES: We must receive comments on this proposed AD by September 14, 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. [[Page 45454]] 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, 3855 Lakewood Boulevard, MC D800-0019, Long Beach, CA 90846-0001; telephone 206-544-5000, extension 2; fax 206-766-5683; 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. 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- 2965; 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: Chandra Ramdoss, Aerospace Engineer, Airframe Branch, ANM-120L, FAA, Los Angeles Aircraft Certification Office (ACO), 3960 Paramount Boulevard, Lakewood, CA 90712-4137; phone: 562-627-5239; fax: 562-627-5210; 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-2015-2965; Directorate Identifier 2014-NM-227-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 August 24, 2012, we issued AD 2012-17-13, Amendment 39-17176 (77 FR 55681, September 11, 2012), for certain The Boeing Company Model 707 airplanes, and Model 720 and 720B series airplanes. For certain airplanes, AD 2012-17-13 required using redefined flight cycle counts, determining the type of material of the horizontal stabilizer, rear spar, and upper and lower chords on the inboard and outboard ends of the rear spar; repetitively inspecting for cracking of the horizontal stabilizer components; and repairing or replacing the chord, or modifying chord segments made from 7079 aluminum, if necessary. For all airplanes, AD 2012-17-13 required inspecting certain structurally significant items, and repairing discrepancies if necessary. AD 2012- 17-13 resulted from reports of stress corrosion cracking in the chord segments made from 7079 aluminum in the horizontal stabilizer rear spar, and potential early fatigue cracking in the chord segments made from 7075 aluminum. We issued AD 2012-17-13 to detect and correct stress corrosion and potential early fatigue cracking in the horizontal stabilizer, which could compromise the structural integrity of the stabilizer. Actions Since AD 2012-17-13, Amendment 39-17176 (77 FR 55681, September 11, 2012), Was Issued The preamble to AD 2012-17-13, Amendment 39-17176 (77 FR 55681, September 11, 2012), explained that we considered the requirements ``interim action'' and were considering further rulemaking. We now have determined that it is necessary to initiate further rulemaking to continue to require the repetitive inspections required by AD 2012-17- 13, and to add a requirement for replacement of all chord segments made of 7079 aluminum with new chord segments made of 7075 aluminum. This proposed AD follows from that determination. Related Service Information Under 1 CFR Part 51 We reviewed Boeing 707 Alert Service Bulletin A3515, Revision 1, dated October 10, 2014. The service information describes procedures for incorporating a new cycle counting procedure, determining the material for the horizontal stabilizer rear spar chord segment, inspecting for stress corrosion cracking and fatigue cracking, repair, and replacing all chord segments made of 7079 aluminum with new, improved chord segments made of 7075 aluminum. 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 2012-17-13, Amendment 39-17176 (77 FR 55681, September 11, 2012). This proposed AD would also add a requirement to replace all chord segments made of 7079 aluminum with new chord segments made of 7075 aluminum. This replacement would not terminate the repetitive inspections required by AD 2012-17-13. Costs of Compliance We estimate that this proposed AD affects 10 airplanes of U.S. registry. We estimate the following costs to comply with this proposed AD: Table--Estimated costs ---------------------------------------------------------------------------------------------------------------- Cost per Action Work hours Parts product Fleet cost ---------------------------------------------------------------------------------------------------------------- Retained inspections from AD Up to 32 work-hours X $0.............. Up to $2,720 Up to $27,200 per 2012-17-13, Amendment 39- $85 per hour = up to per inspection inspection cycle 17176 (77 FR 55681, $2,720 per cycle. September 11, 2012). inspection cycle. [[Page 45455]] Replacement [new action]..... 500 work-hours X $85 Up to $228,000 Up to Up to $23,225,000 \2\ per work-hour = per chord. $2,322,500 (up $42,500. to 10 chords per airplane) \1\. ---------------------------------------------------------------------------------------------------------------- \1\ The parts for the modification could cost up to $2.28 million per airplane, depending on whether only one operator is ordering the parts or multiple operators. The parts cost will go down if multiple operators order parts at the same time. \2\ The number of chords which must be replaced on each specific airplane varies. 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) 2012-17-13, Amendment 39-17176 (77 FR 55681, September 11, 2012), and adding the following new AD: The Boeing Company: Docket No. FAA-2015-2965; Directorate Identifier 2014-NM-227-AD. (a) Comments Due Date The FAA must receive comments on this AD action by September 14, 2015. (b) Affected ADs This AD replaces AD 2012-17-13, Amendment 39-17176 (77 FR 55681, September 11, 2012). (c) Applicability This AD applies to The Boeing Company airplanes, certificated in any category; identified in paragraphs (c)(1) and (c)(2) of this AD. (1) Model 707 airplanes identified in Boeing 707 Alert Service Bulletin A3515, Revision 1, dated October 10, 2014. (2) Model 720 and 720B series airplanes identified in Boeing 707 Alert Service Bulletin A3516, dated April 4, 2008. (d) Subject Air Transport Association (ATA) of America Code 55, Stabilizers. (e) Unsafe Condition This AD was prompted by a determination that all chord segments made of 7079 aluminum must be replaced with new, improved chord segments made of 7075 aluminum. We are issuing this AD to detect and correct stress corrosion and potential early fatigue cracking in the horizontal stabilizer, which could result in reduced structural integrity of the horizontal stabilizer. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Retained Flight Cycle Counting Procedure, With Revised Service Information This paragraph restates the requirements of paragraph (g) of AD 2012-17-13, Amendment 39-17176 (77 FR 55681, September 11, 2012), with revised service information. Flight cycles, as used in this AD, must be counted as defined in the service information identified in paragraph (g)(1), (g)(2), or (g)(3) of this AD. (1) Boeing 707 Alert Service Bulletin A3515, dated December 19, 2007 (for Model airplanes). (2) Boeing 707 Alert Service Bulletin A3515, Revision 1, dated October 10, 2014 (for Model airplanes). (3) Boeing 707 Alert Service Bulletin A3516, dated April 4, 2008 (for Model airplanes, and Model 720 and 720B series airplanes). (h) Retained Determination of Material of the Components of the Horizontal Stabilizer, With Revised Service Information This paragraph restates the actions required by paragraph (h) of AD 2012-17-13, Amendment 39-17176 (77 FR 55681, September 11, 2012), with revised service information. For airplanes identified in Boeing 707 Alert Service Bulletin A3515, dated December 19, 2007, or Boeing 707 Alert Service Bulletin A3515, Revision 1, dated October 10, 2014: At the earlier of the times specified in paragraphs (h)(1) and (h)(2) of this AD, determine the type of material of the horizontal stabilizer, rear spar, upper chords, and lower chords on the inboard and outboard ends of the rear spar, in accordance with Part 2 of the Accomplishment Instructions of Boeing 707 Alert Service Bulletin A3515, dated December 19, 2007, or Boeing 707 Alert Service Bulletin A3515, Revision 1, dated October 10, 2014. (1) Within 180 days after October 16, 2012 (the effective date of AD 2012-17-13, Amendment 39-17176 (77 FR 55681, September 11, 2012)). (2) Before further flight after any horizontal stabilizer is replaced after October 16, 2012. (i) Retained Repetitive Inspections of 7075 Aluminum Components, With Revised Service Information This paragraph restates the actions required by paragraph (i) of AD 2012-17-13, Amendment 39-17176 (77 FR 55681, September 11, 2012), with revised service [[Page 45456]] information. For airplanes with horizontal stabilizer components made from 7075 aluminum, as determined during the inspection required by paragraph (h) of this AD: Within 180 days after October 16, 2012 (the effective date of AD 2012-17-13), and before further flight after any replacement of the horizontal stabilizer, do a special detailed inspection for cracking of the upper chord on the inboard end of the rear spar on both the left and right side horizontal stabilizers, from stabilizer station -13.179 to 92.55, in accordance with Part 3 of the Accomplishment Instructions of Boeing 707 Alert Service Bulletin A3515, dated December 19, 2007, or Boeing 707 Alert Service Bulletin A3515, Revision 1, dated October 10, 2014. Repeat the inspections thereafter at intervals not to exceed 500 flight cycles, and before further flight after any replacement of the horizontal stabilizer, except as provided by paragraph (j) of this AD. If any cracking is found, before further flight, either repair the cracking in accordance with Part 3 of the Accomplishment Instructions of Boeing 707 Alert Service Bulletin A3515, dated December 19, 2007, or Boeing 707 Alert Service Bulletin A3515, Revision 1, dated October 10, 2014, except as required by paragraph (n) of this AD; or replace the chord with a new chord, in accordance with Part 6 of the Accomplishment Instructions of Boeing 707 Alert Service Bulletin A3515, dated December 19, 2007, or Boeing 707 Alert Service Bulletin A3515, Revision 1, dated October 10, 2014. (j) Retained Repetitive Inspections on Airplanes With Replaced Chord, With Revised Service Information This paragraph restates the actions required by paragraph (j) of AD 2012-17-13, Amendment 39-17176 (77 FR 55681, September 11, 2012), with revised service information. For airplanes on which the chord is replaced with a new chord in accordance with Part 6 of the Accomplishment Instructions of Boeing 707 Alert Service Bulletin A3515, dated December 19, 2007, or Boeing 707 Alert Service Bulletin A3515, Revision 1, dated October 10, 2014: Within 4,000 flight cycles after the chord replacement, do the inspections required by paragraph (i) of this AD, and repeat the inspections thereafter at the times specified in paragraph (i) of this AD. (k) Retained Repetitive Inspections of 7079 Aluminum Components, With Revised Service Information This paragraph restates the actions required by paragraph (k) of AD 2012-17-13, Amendment 39-17176 (77 FR 55681, September 11, 2012), with revised service information. For airplanes with horizontal stabilizers that have components of the chords of the rear spar made from 7079 aluminum, as determined during the inspection required by paragraph (h) of this AD: Within 180 days after October 16, 2012 (the effective date of AD 2012-17-13), do the actions required by paragraphs (k)(1), (k)(2), and (k)(3) of this AD, and repeat those actions at the applicable intervals specified in paragraphs (k)(1), (k)(2), and (k)(3) of this AD. (1) Do a special detailed inspection for cracking of the upper chord of the inboard side of the rear spar of both the -left and right-side horizontal stabilizers from stabilizer station -13.179 to 92.55, in accordance with Part 3 of the Accomplishment Instructions of Boeing 707 Alert Service Bulletin A3515, dated December 19, 2007, or Boeing 707 Alert Service Bulletin A3515, Revision 1, dated October 10, 2014. Repeat the inspection thereafter at intervals not to exceed 250 flight cycles or 180 days, whichever occurs first. If any cracking is found during any inspection required by this paragraph, before further flight, either repair the cracking, in accordance with Part 3 of the Accomplishment Instructions of Boeing 707 Alert Service Bulletin A3515, dated December 19, 2007, or Boeing 707 Alert Service Bulletin A3515, Revision 1, dated October 10, 2014, except as required by paragraph (n) of this AD; or replace the chord with a new chord, in accordance with Part 6 of the Accomplishment Instructions of Boeing 707 Alert Service Bulletin A3515, dated December 19, 2007, or Boeing 707 Alert Service Bulletin A3515, Revision 1, dated October 10, 2014. (2) Do a high frequency eddy current inspection for cracking of the web flanges of the upper and lower chords of the rear spar in the left and right side horizontal stabilizers from stabilizer stations 92.55 to 272.55, in accordance with Part 4 of the Accomplishment Instructions of Boeing 707 Alert Service Bulletin A3515, dated December 19, 2007, or Boeing 707 Alert Service Bulletin A3515, Revision 1, dated October 10, 2014. Repeat the inspection thereafter at intervals not to exceed 1,000 flight cycles or 180 days, whichever occurs first. If any cracking is found during any inspection required by this paragraph, before further flight, do the actions specified in paragraph (k)(2)(i) or (k)(2)(ii) of this AD. (i) Determine whether the cracking meets the limits specified in Part 4 of the Accomplishment Instructions of Boeing 707 Alert Service Bulletin A3515, dated December 19, 2007, or Boeing 707 Alert Service Bulletin A3515, Revision 1, dated October 10, 2014, and whether a previous repair has been done; determine if all 7079 upper and lower chord segments installed on the horizontal stabilizer have had the Part II, Group 1, Preventative Modification specified in Boeing Service Bulletin 3356 done; and do all applicable repairs and modifications, in accordance with the Accomplishment Instructions of Boeing 707 Alert Service Bulletin A3515, dated December 19, 2007, or Boeing 707 Alert Service Bulletin A3515, Revision 1, dated October 10, 2014. Do the actions required by this paragraph in accordance with Part 4 of the Accomplishment Instructions of Boeing 707 Alert Service Bulletin A3515, dated December 19, 2007, or Boeing 707 Alert Service Bulletin A3515, Revision 1, dated October 10, 2014, except as required by paragraph (n) of this AD. Do all applicable repairs and modifications before further flight. (ii) Replace the chord with a new chord, in accordance with Part 6 of the Accomplishment Instructions of Boeing 707 Alert Service Bulletin A3515, dated December 19, 2007, or Boeing 707 Alert Service Bulletin A3515, Revision 1, dated October 10, 2014. (3) Do low frequency eddy current (LFEC) inspections for cracking of the forward skin flanges of the upper and lower chords of the rear spar in the left and right side horizontal stabilizers from stabilizer stations -13.179 to 272.55 (for lower chords) and 92.55 to 272.55 (for upper chords), in accordance with Part 5 of the Accomplishment Instructions of Boeing 707 Alert Service Bulletin A3515, dated December 19, 2007, or Boeing 707 Alert Service Bulletin A3515, Revision 1, dated October 10, 2014. Repeat the inspections thereafter at intervals not to exceed 1,000 flight cycles or 180 days, whichever occurs first. If any cracking is found during any inspection required by this paragraph, before further flight, do the actions specified in either paragraph (k)(3)(i) or paragraph (k)(3)(ii) of this AD. (i) Repair any cracking, determine whether all 7079 upper and lower chord segments installed on the horizontal stabilizer have had the Part II--Preventative Modification specified in Boeing Service Bulletin 3381 done, and do all applicable modifications, in accordance with the Accomplishment Instructions of Boeing 707 Alert Service Bulletin A3515, dated December 19, 2007, or Boeing 707 Alert Service Bulletin A3515, Revision 1, dated October 10, 2014. Do the actions required by this paragraph in accordance with Part 5 of the Accomplishment Instructions of Boeing 707 Alert Service Bulletin A3515, dated December 19, 2007, or Boeing 707 Alert Service Bulletin A3515, Revision 1, dated October 10, 2014, except as required by paragraph (n) of this AD. Do all applicable modifications before further flight. (ii) Replace the chord with a new chord, in accordance with Part 6 of the Accomplishment Instructions of Boeing 707 Alert Service Bulletin A3515, dated December 19, 2007; or Boeing 707 Alert Service Bulletin A3515, Revision 1, dated October 10, 2014. (l) Retained Modification/Chord Replacement, With Revised Service Information This paragraph restates the actions required by paragraph (l) of AD 2012-17-13, Amendment 39-17176 (77 FR 55681, September 11, 2012), with revised service information. For airplanes identified in Boeing 707 Alert Service Bulletin A3515, dated December 19, 2007, or Boeing 707 Alert Service Bulletin A3515, Revision 1, dated October 10, 2014, with horizontal stabilizers that have rear spar chord components made from 7079 aluminum and have not had embodied the modification of Part II of Boeing Service Bulletin 3381, dated July 25, 1980, or Boeing Service Bulletin 3381, Revision 1, dated July 31, 1981: Before further flight after determining the type of material in accordance with paragraph (h) of this AD, modify all 7079 chord segments installed on the horizontal stabilizer, in [[Page 45457]] accordance with Part 5 of the Accomplishment Instructions of Boeing 707 Alert Service Bulletin A3515, dated December 19, 2007, or Boeing 707 Alert Service Bulletin A3515, Revision 1, dated October 10, 2014; or replace the chord, in accordance with Part 6 of the Accomplishment Instructions of Boeing 707 Alert Service Bulletin A3515, dated December 19, 2007, or Boeing 707 Alert Service Bulletin A3515, Revision 1, dated October 10, 2014. (m) Retained Supplemental Structural Inspection Document Inspections This paragraph restates the actions required by paragraph (m) of AD 2012-17-13, Amendment 39-17176 (77 FR 55681, September 11, 2012). For all airplanes: Within 180 days or 1,000 flight cycles after October 16, 2012 (the effective date of AD 2012-17-13), whichever occurs first, do the inspections of the applicable structurally significant items specified in and in accordance with the Accomplishment Instructions of Boeing 707 Alert Service Bulletin A3516, dated April 4, 2008. If any cracking is found, before further flight, repair in accordance with the procedures specified in paragraph (r) of this AD. The inspections required by AD 85-12-01 R1, Amendment 39-5439 (51 FR 36002, October 8, 1986), are still required, except, as of October 16, 2012 (the effective date of AD 2012-17-13), the flight-cycle interval for the repetitive inspections specified in paragraph 1.E., ``Compliance,'' of Boeing 707 Alert Service Bulletin A3516, dated April 4, 2008, must be counted in accordance with the requirements of paragraph (g) of this AD. (n) Retained Exception to Certain Service Information: Contacting FAA for Crack Repair This paragraph restates the actions required by paragraph (n) of AD 2012-17-13, Amendment 39-17176 (77 FR 55681, September 11, 2012), with revised service information. If any cracking is found during any inspection required by this AD, and Boeing 707 Alert Service Bulletin A3515, dated December 19, 2007, or Boeing 707 Alert Service Bulletin A3515, Revision 1, dated October 10, 2014, specifies to contact Boeing for appropriate action: Before further flight, repair the cracking using a method approved in accordance with the procedures specified in paragraph (r) of this AD. (o) Retained Exception to Certain Service Information: Nondestructive Test Compliance Procedures This paragraph restates the requirements of paragraph (o) of AD 2012-17-13, Amendment 39-17176 (77 FR 55681, September 11, 2012), with revised service information. Where Boeing 707 Alert Service Bulletin A3515, dated December 19, 2007, or Boeing 707 Alert Service Bulletin A3515, Revision 1, dated October 10, 2014, specifies that operators ``refer to'' nondestructive test (NDT) procedures, the procedures must be done in accordance with the service information identified in paragraphs (o)(1), (o)(2), and (o)(3) of this AD, as applicable. (1) Figure 20, ``Electrical Conductivity Measurement for Aluminum,'' of Subject 51-00-00, ``Structures-General,'' of Part 6-- Eddy Current, of the Boeing 707/720 Nondestructive Test Manual, Document D6-48023, Revision 118, dated July 15, 2011. (2) Subject 55-10-07, ``Horizontal Stabilizer,'' of Part 6--Eddy Current, of the Boeing 707/720 Nondestructive Test Manual, Document D6-48023, Revision 118, dated July 15, 2011. (3) Subject 51-01-00, ``Orientation and Preparation for Testing'' of Part 1--General, of the Boeing 707/720 Nondestructive Test Manual, Document D6-48023, Revision 118, dated July 15, 2011. (p) Retained Parts Installation Prohibition As of October 16, 2012 (the effective date of AD 2012-17-13, Amendment 39-17176 (77 FR 55681, September 11, 2012)), no person may install any horizontal stabilizer assembly with any chord segment having a part number other than that identified in paragraph 2.C.2. of Boeing 707 Alert Service Bulletin A3515, dated December 19, 2007, or Boeing 707 Alert Service Bulletin A3515, Revision 1, dated October 10, 2014, on any airplane. (q) New Replacement of 7079 Aluminum Components Within 48 months after the effective date of this AD: Replace all 7079 aluminum chord segments of the upper and lower chords installed on the horizontal stabilizer with 7075 aluminum chord segments, in accordance with Part 6 of the Accomplishment Instructions of Boeing 707 Alert Service Bulletin A3515, Revision 1, dated October 10, 2014. Within 4,000 flight cycles after accomplishing the replacements required by this paragraph, repeat the inspection required by paragraph (j) of this AD; and repeat the inspection thereafter at intervals not to exceed 500 flight cycles, and before further flight after any replacement of the horizontal stabilizer. (r) 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 (s)(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 2012-17-13, Amendment 39-17176 (77 FR 55681, September 11, 2012), are approved as AMOCs for the corresponding provisions of this AD. (s) Related Information (1) For more information about this AD, contact Chandra Ramdoss, Aerospace Engineer, Airframe Branch, ANM-120L, FAA, Los Angeles Aircraft Certification Office (ACO), 3960 Paramount Boulevard, Lakewood, CA 90712-4137; phone: 562-627-5239; fax: 562-627-5210; email: [email protected]. (2) For service information identified in this AD, contact Boeing Commercial Airplanes, Attention: Data & Services Management, 3855 Lakewood Boulevard, MC D800-0019, Long Beach, CA 90846-0001; telephone 206-544-5000, extension 2; fax 206-766-5683; 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. Issued in Renton, Washington, on July 16, 2015. Suzanne Masterson, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2015-18559 Filed 7-29-15; 8:45 am] BILLING CODE 4910-13-P
![Federal Register / Vol. 80, No. 146 / Thursday, July 30, 2015 / Proposed Rules 45453
• Email: ConventionalCooking proposed rulemaking (NOPR) and DEPARTMENT OF TRANSPORTATION
Products2014STD0005@ee.doe.gov. public meeting in the Federal Register
Include the docket number EERE–2014– that proposed new and amended energy Federal Aviation Administration
BT–STD–0005 in the subject line of the conservation standards for residential
message. conventional ovens. 80 FR 33030. The 14 CFR Part 39
• Mail: Ms. Brenda Edwards, U.S. NOPR requested comment from the [Docket No. FAA–2015–2965; Directorate
Department of Energy, Building public on the proposed standards, Identifier 2014–NM–227–AD]
Technologies Program, Mailstop EE–5B, associated analyses, and results, and
Notice of Proposed Rulemaking for RIN 2120–AA64
provided for the written submission of
Energy Conservation Standards for comments by August 10, 2015. The Airworthiness Directives; The Boeing
Residential Conventional Ovens, Docket Association of Home Appliance Company Airplanes
No. EERE–2014–BT–STD–0014, 1000
Manufacturers (AHAM) requested that
Independence Avenue SW., AGENCY: Federal Aviation
DOE extend the comment period by 60
Washington, DC 20585–0121. If Administration (FAA), DOT.
possible, please submit all items on a days so that manufacturers can obtain
ACTION: Notice of proposed rulemaking
CD. It is not necessary to include sufficient data to fully analyze DOE’s
proposed rule according to the (NPRM).
printed copies.
• Hand Delivery/Courier: Ms. Brenda conventional oven test procedure final SUMMARY: We propose to supersede
Edwards, U.S. Department of Energy, rule that was published on July 2, 2015. Airworthiness Directive (AD) 2012–17–
Building Technologies Program, 950 80 FR 37954. Because there are 13, which applies to certain The Boeing
L’Enfant Plaza SW., Suite 600, currently no performance based energy Company Model 707 airplanes, and
Washington, DC 20024. Telephone (202) conservation standards, AHAM noted Model 720 and 720B series airplanes.
586–2945. If possible, please submit all that manufacturers do not conduct For certain airplanes, AD 2012–17–13
items on a CD, in which case it is not regular energy tests on conventional required using redefined flight cycle
necessary to include printed copies. ovens. AHAM further stated that by counts; determining the type of material
Instructions: All submissions received allowing additional time for of the horizontal stabilizer, rear spar,
must include the agency name and manufacturers (and other stakeholders and upper and lower chords on the
docket number for this rulemaking. No who wish to conduct testing) to test inboard and outboard ends of the rear
telefacsimiles (faxes) will be accepted. their products, manufacturers will be spar; repetitively inspecting for cracking
Docket: The docket is available for able to provide key data to support of the horizontal stabilizer components;
review at www.regulations.gov, DOE’s analysis. and repairing or replacing the chord, or
including Federal Register notices, modifying chord segments made of 7079
comments, and other supporting Based on AHAM’s request, DOE aluminum, if necessary. For all
documents/materials. All documents in determines that a 30 day extension of airplanes, AD 2012–17–13 required
the docket are listed in the the public comment period is inspecting certain structurally
www.regulations.gov index. However, appropriate to allow interested parties significant items, and repairing
not all documents listed in the index additional time to submit comments. discrepancies if necessary. Since we
may be publicly available, such as DOE notes that it issued and made issued AD 2012–17–13, we have
information that is exempt from public available a pre-publication version of determined that all chord segments
disclosure. the conventional oven test procedure made of 7079 aluminum must be
A link to the docket Web page can be final rule on June 9, 2015. Based on replaced with new, improved chord
found at: http://www.regulations.gov/ DOE’s testing experience, extending the segments made of 7075 aluminum. This
#!documentDetail;D=EERE-2014-BT- comment period by 30 days for a 90 day proposed AD would add a requirement
STD-0005-0014. This Web page contains total period should be sufficient time for to replace all chord segments made of
a link to the docket for this notice on the manufacturers to conduct testing using 7079 aluminum with new, improved
regulation.gov site. The the new oven test procedure and chord segments made of 7075
www.regulations.gov Web page contains aggregate results. DOE will consider any aluminum. We are proposing this AD to
instructions on how to access all comments received by midnight of detect and correct stress corrosion and
documents in the docket, including September 9, 2015 to be timely potential early fatigue cracking in the
public comments. submitted. horizontal stabilizer, which could result
FOR FURTHER INFORMATION CONTACT: in reduced structural integrity of the
Issued in Washington, DC, on July 23, horizontal stabilizer.
Mr. John Cymbalsky, U.S. Department of
2015.
Energy, Office of Energy Efficiency DATES: We must receive comments on
and Renewable Energy, Building Kathleen B. Hogan, this proposed AD by September 14,
Technologies Program, EE–2J, 1000 Deputy Assistant Secretary for Energy 2015.
Independence Avenue SW., Efficiency, Energy Efficiency and Renewable
Energy.
ADDRESSES: You may send comments,
Washington, DC 20585–0121. using the procedures found in 14 CFR
Telephone: (202) 287–1692. Email: [FR Doc. 2015–18687 Filed 7–29–15; 8:45 am]
11.43 and 11.45, by any of the following
kitchen_ranges_and_ovens@ BILLING CODE 6450–01–P
methods:
ee.doe.gov. • Federal eRulemaking Portal: Go to
Ms. Celia Sher, U.S. Department of
Lhorne on DSK7TPTVN1PROD with PROPOSALS
http://www.regulations.gov. Follow the
Energy, Office of the General Counsel, instructions for submitting comments.
GC–33, 1000 Independence Avenue • Fax: 202–493–2251.
SW., Washington, DC 20585–0121. • Mail: U.S. Department of
Telephone: (202) 287–6122. Email: Transportation, Docket Operations, M–
Celia.Sher@hq.doe.gov. 30, West Building Ground Floor, Room
SUPPLEMENTARY INFORMATION: On June W12–140, 1200 New Jersey Avenue SE.,
10, 2015, DOE published a notice of Washington, DC 20590.
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![Federal Register / Vol. 80, No. 146 / Thursday, July 30, 2015 / Proposed Rules 45455
TABLE—ESTIMATED COSTS—Continued
Action Work hours Parts Cost per product Fleet cost
Replacement [new action] .................... 500 work-hours X $85 per work-hour Up to $228,000 Up to $2,322,500 Up to
= $42,500. per chord. (up to 10 chords $23,225,000 2
per airplane) 1.
1 The parts for the modification could cost up to $2.28 million per airplane, depending on whether only one operator is ordering the parts or
multiple operators. The parts cost will go down if multiple operators order parts at the same time.
2 The number of chords which must be replaced on each specific airplane varies.
Authority for This Rulemaking The Proposed Amendment (f) Compliance
Title 49 of the United States Code Comply with this AD within the
Accordingly, under the authority compliance times specified, unless already
specifies the FAA’s authority to issue delegated to me by the Administrator, done.
rules on aviation safety. Subtitle I, the FAA proposes to amend 14 CFR part
Section 106, describes the authority of (g) Retained Flight Cycle Counting
39 as follows: Procedure, With Revised Service
the FAA Administrator. Subtitle VII,
Information
Aviation Programs, describes in more PART 39—AIRWORTHINESS
detail the scope of the Agency’s DIRECTIVES This paragraph restates the requirements of
authority. paragraph (g) of AD 2012–17–13,
Amendment 39–17176 (77 FR 55681,
We are issuing this rulemaking under ■ 1. The authority citation for part 39 September 11, 2012), with revised service
the authority described in Subtitle VII, continues to read as follows: information. Flight cycles, as used in this
Part A, Subpart III, Section 44701, Authority: 49 U.S.C. 106(g), 40113, 44701. AD, must be counted as defined in the
‘‘General requirements.’’ Under that service information identified in paragraph
section, Congress charges the FAA with § 39.13 [Amended] (g)(1), (g)(2), or (g)(3) of this AD.
promoting safe flight of civil aircraft in (1) Boeing 707 Alert Service Bulletin
air commerce by prescribing regulations ■ 2. The FAA amends § 39.13 by A3515, dated December 19, 2007 (for Model
removing Airworthiness Directive (AD) airplanes).
for practices, methods, and procedures (2) Boeing 707 Alert Service Bulletin
the Administrator finds necessary for 2012–17–13, Amendment 39–17176 (77
FR 55681, September 11, 2012), and A3515, Revision 1, dated October 10, 2014
safety in air commerce. This regulation (for Model airplanes).
is within the scope of that authority adding the following new AD: (3) Boeing 707 Alert Service Bulletin
because it addresses an unsafe condition The Boeing Company: Docket No. FAA– A3516, dated April 4, 2008 (for Model
that is likely to exist or develop on 2015–2965; Directorate Identifier 2014– airplanes, and Model 720 and 720B series
products identified in this rulemaking NM–227–AD. airplanes).
action. (a) Comments Due Date (h) Retained Determination of Material of
the Components of the Horizontal Stabilizer,
Regulatory Findings The FAA must receive comments on this With Revised Service Information
AD action by September 14, 2015.
We have determined that this This paragraph restates the actions
proposed AD would not have federalism (b) Affected ADs required by paragraph (h) of AD 2012–17–13,
implications under Executive Order This AD replaces AD 2012–17–13, Amendment 39–17176 (77 FR 55681,
13132. This proposed AD would not Amendment 39–17176 (77 FR 55681, September 11, 2012), with revised service
September 11, 2012). information. For airplanes identified in
have a substantial direct effect on the
Boeing 707 Alert Service Bulletin A3515,
States, on the relationship between the (c) Applicability dated December 19, 2007, or Boeing 707
national Government and the States, or Alert Service Bulletin A3515, Revision 1,
This AD applies to The Boeing Company
on the distribution of power and dated October 10, 2014: At the earlier of the
airplanes, certificated in any category;
responsibilities among the various identified in paragraphs (c)(1) and (c)(2) of times specified in paragraphs (h)(1) and
levels of government. (h)(2) of this AD, determine the type of
this AD.
For the reasons discussed above, I material of the horizontal stabilizer, rear spar,
(1) Model 707 airplanes identified in
certify that the proposed regulation: upper chords, and lower chords on the
Boeing 707 Alert Service Bulletin A3515,
inboard and outboard ends of the rear spar,
(1) Is not a ‘‘significant regulatory Revision 1, dated October 10, 2014. in accordance with Part 2 of the
action’’ under Executive Order 12866, (2) Model 720 and 720B series airplanes Accomplishment Instructions of Boeing 707
(2) Is not a ‘‘significant rule’’ under identified in Boeing 707 Alert Service Alert Service Bulletin A3515, dated
the DOT Regulatory Policies and Bulletin A3516, dated April 4, 2008. December 19, 2007, or Boeing 707 Alert
Procedures (44 FR 11034, February 26, (d) Subject Service Bulletin A3515, Revision 1, dated
1979), October 10, 2014.
Air Transport Association (ATA) of (1) Within 180 days after October 16, 2012
(3) Will not affect intrastate aviation America Code 55, Stabilizers. (the effective date of AD 2012–17–13,
in Alaska, and Amendment 39–17176 (77 FR 55681,
(e) Unsafe Condition
(4) Will not have a significant September 11, 2012)).
economic impact, positive or negative, This AD was prompted by a determination (2) Before further flight after any horizontal
that all chord segments made of 7079
Lhorne on DSK7TPTVN1PROD with PROPOSALS
on a substantial number of small entities stabilizer is replaced after October 16, 2012.
aluminum must be replaced with new,
under the criteria of the Regulatory (i) Retained Repetitive Inspections of 7075
improved chord segments made of 7075
Flexibility Act. aluminum. We are issuing this AD to detect Aluminum Components, With Revised
List of Subjects in 14 CFR Part 39 and correct stress corrosion and potential Service Information
early fatigue cracking in the horizontal This paragraph restates the actions
Air transportation, Aircraft, Aviation stabilizer, which could result in reduced required by paragraph (i) of AD 2012–17–13,
safety, Incorporation by reference, structural integrity of the horizontal Amendment 39–17176 (77 FR 55681,
Safety. stabilizer. September 11, 2012), with revised service
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![Federal Register / Vol. 80, No. 146 / Thursday, July 30, 2015 / Proposed Rules 45457
accordance with Part 5 of the 00–00, ‘‘Structures-General,’’ of Part 6—Eddy (4) AMOCs approved for AD 2012–17–13,
Accomplishment Instructions of Boeing 707 Current, of the Boeing 707/720 Amendment 39–17176 (77 FR 55681,
Alert Service Bulletin A3515, dated Nondestructive Test Manual, Document D6– September 11, 2012), are approved as
December 19, 2007, or Boeing 707 Alert 48023, Revision 118, dated July 15, 2011. AMOCs for the corresponding provisions of
Service Bulletin A3515, Revision 1, dated (2) Subject 55–10–07, ‘‘Horizontal this AD.
October 10, 2014; or replace the chord, in Stabilizer,’’ of Part 6—Eddy Current, of the
accordance with Part 6 of the Boeing 707/720 Nondestructive Test Manual, (s) Related Information
Accomplishment Instructions of Boeing 707 Document D6–48023, Revision 118, dated (1) For more information about this AD,
Alert Service Bulletin A3515, dated July 15, 2011. contact Chandra Ramdoss, Aerospace
December 19, 2007, or Boeing 707 Alert (3) Subject 51–01–00, ‘‘Orientation and Engineer, Airframe Branch, ANM–120L,
Service Bulletin A3515, Revision 1, dated Preparation for Testing’’ of Part 1—General, FAA, Los Angeles Aircraft Certification
October 10, 2014. of the Boeing 707/720 Nondestructive Test Office (ACO), 3960 Paramount Boulevard,
Manual, Document D6–48023, Revision 118, Lakewood, CA 90712–4137; phone: 562–627–
(m) Retained Supplemental Structural dated July 15, 2011. 5239; fax: 562–627–5210; email:
Inspection Document Inspections
(p) Retained Parts Installation Prohibition chandraduth.ramdoss@faa.gov.
This paragraph restates the actions (2) For service information identified in
required by paragraph (m) of AD 2012–17– As of October 16, 2012 (the effective date this AD, contact Boeing Commercial
13, Amendment 39–17176 (77 FR 55681, of AD 2012–17–13, Amendment 39–17176 Airplanes, Attention: Data & Services
September 11, 2012). For all airplanes: (77 FR 55681, September 11, 2012)), no Management, 3855 Lakewood Boulevard, MC
Within 180 days or 1,000 flight cycles after person may install any horizontal stabilizer D800–0019, Long Beach, CA 90846–0001;
October 16, 2012 (the effective date of AD assembly with any chord segment having a telephone 206–544–5000, extension 2; fax
2012–17–13), whichever occurs first, do the part number other than that identified in 206–766–5683; Internet https://
inspections of the applicable structurally paragraph 2.C.2. of Boeing 707 Alert Service www.myboeingfleet.com. You may view this
significant items specified in and in Bulletin A3515, dated December 19, 2007, or referenced service information at the FAA,
accordance with the Accomplishment Boeing 707 Alert Service Bulletin A3515, Transport Airplane Directorate, 1601 Lind
Instructions of Boeing 707 Alert Service Revision 1, dated October 10, 2014, on any Avenue SW., Renton, WA. For information
Bulletin A3516, dated April 4, 2008. If any airplane. on the availability of this material at the
cracking is found, before further flight, repair FAA, call 425–227–1221.
in accordance with the procedures specified (q) New Replacement of 7079 Aluminum
in paragraph (r) of this AD. The inspections Components Issued in Renton, Washington, on July 16,
required by AD 85–12–01 R1, Amendment Within 48 months after the effective date 2015.
39–5439 (51 FR 36002, October 8, 1986), are of this AD: Replace all 7079 aluminum chord Suzanne Masterson,
still required, except, as of October 16, 2012 segments of the upper and lower chords Acting Manager, Transport Airplane
(the effective date of AD 2012–17–13), the installed on the horizontal stabilizer with Directorate, Aircraft Certification Service.
flight-cycle interval for the repetitive 7075 aluminum chord segments, in
inspections specified in paragraph 1.E., accordance with Part 6 of the [FR Doc. 2015–18559 Filed 7–29–15; 8:45 am]
‘‘Compliance,’’ of Boeing 707 Alert Service Accomplishment Instructions of Boeing 707 BILLING CODE 4910–13–P
Bulletin A3516, dated April 4, 2008, must be Alert Service Bulletin A3515, Revision 1,
counted in accordance with the requirements dated October 10, 2014. Within 4,000 flight
of paragraph (g) of this AD. cycles after accomplishing the replacements DEPARTMENT OF TRANSPORTATION
required by this paragraph, repeat the
(n) Retained Exception to Certain Service inspection required by paragraph (j) of this Federal Aviation Administration
Information: Contacting FAA for Crack AD; and repeat the inspection thereafter at
Repair intervals not to exceed 500 flight cycles, and 14 CFR Part 39
This paragraph restates the actions before further flight after any replacement of
required by paragraph (n) of AD 2012–17–13, the horizontal stabilizer. [Docket No. FAA–2015–2964; Directorate
Amendment 39–17176 (77 FR 55681, Identifier 2014–NM–206–AD]
(r) Alternative Methods of Compliance
September 11, 2012), with revised service
information. If any cracking is found during (AMOCs) RIN 2120–AA64
any inspection required by this AD, and (1) The Manager, Los Angeles Aircraft
Boeing 707 Alert Service Bulletin A3515, Certification Office (ACO), FAA, has the Airworthiness Directives; Airbus
dated December 19, 2007, or Boeing 707 authority to approve AMOCs for this AD, if Airplanes
Alert Service Bulletin A3515, Revision 1, requested using the procedures found in 14
dated October 10, 2014, specifies to contact CFR 39.19. In accordance with 14 CFR 39.19, AGENCY: Federal Aviation
Boeing for appropriate action: Before further send your request to your principal inspector Administration (FAA), DOT.
flight, repair the cracking using a method or local Flight Standards District Office, as ACTION: Notice of proposed rulemaking
approved in accordance with the procedures appropriate. If sending information directly (NPRM).
specified in paragraph (r) of this AD. to the manager of the ACO, send it to the
attention of the person identified in SUMMARY: We propose to adopt a new
(o) Retained Exception to Certain Service paragraph (s)(1) of this AD. Information may
Information: Nondestructive Test
airworthiness directive (AD) for all
be emailed to: 9-ANM-LAACO-AMOC- Airbus Model A319, A320, and A321
Compliance Procedures Requests@faa.gov. series airplanes. This proposed AD is
This paragraph restates the requirements of (2) Before using any approved AMOC,
paragraph (o) of AD 2012–17–13, notify your appropriate principal inspector, intended to complete certain mandated
Amendment 39–17176 (77 FR 55681, or lacking a principal inspector, the manager programs intended to support the
September 11, 2012), with revised service of the local flight standards district office/ airplane reaching its limit of validity
information. Where Boeing 707 Alert Service certificate holding district office. (LOV) of the engineering data that
Bulletin A3515, dated December 19, 2007, or (3) An AMOC that provides an acceptable support the established structural
Lhorne on DSK7TPTVN1PROD with PROPOSALS
Boeing 707 Alert Service Bulletin A3515, level of safety may be used for any repair maintenance program. This proposed
Revision 1, dated October 10, 2014, specifies required by this AD if it is approved by the AD would require reinforcing the
that operators ‘‘refer to’’ nondestructive test Boeing Commercial Airplanes Organization forward pressure bulkhead at a certain
(NDT) procedures, the procedures must be Designation Authorization (ODA) that has
done in accordance with the service been authorized by the Manager, Los Angeles stringer on both the left-hand and right-
information identified in paragraphs (o)(1), ACO, to make those findings. For a repair hand sides, and related investigative
(o)(2), and (o)(3) of this AD, as applicable. method to be approved, the repair must meet and corrective actions if necessary. We
(1) Figure 20, ‘‘Electrical Conductivity the certification basis of the airplane, and the are proposing this AD to prevent fatigue
Measurement for Aluminum,’’ of Subject 51– approval must specifically refer to this AD. cracking of the forward pressure
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Document Created: 2018-02-23 09:30:18
Document Modified: 2018-02-23 09:30:18
| 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 September 14, 2015. | |
| Contact | Chandra Ramdoss, Aerospace Engineer, Airframe Branch, ANM-120L, FAA, Los Angeles Aircraft Certification Office (ACO), 3960 Paramount Boulevard, Lakewood, CA 90712-4137; phone: 562-627-5239; fax: 562-627-5210; email: [email protected] | |
| FR Citation | 80 FR 45453 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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