81 FR 23586 - Airworthiness Directives; The Boeing Company Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 81, Issue 78 (April 22, 2016)
Federal Aviation Administration
Federal Register Volume 81, Issue 78 (April 22, 2016)
| Page Range | 23586-23591 | |
| FR Document | 2016-08539 |
[Federal Register Volume 81, Number 78 (Friday, April 22, 2016)] [Rules and Regulations] [Pages 23586-23591] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2016-08539] ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2015-2965; Directorate Identifier 2014-NM-227-AD; Amendment 39-18487; AD 2016-08-11] RIN 2120-AA64 Airworthiness Directives; The Boeing Company Airplanes AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Final rule. ----------------------------------------------------------------------- SUMMARY: We are superseding Airworthiness Directive (AD) 2012-17-13, which applied 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. This new AD adds a requirement to replace all chord segments made of 7079 aluminum with new, improved chord segments made of 7075 aluminum. 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. DATES: This AD is effective May 27, 2016. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of May 27, 2016. The Director of the Federal Register approved the incorporation by reference of certain other publications listed in this AD as of October 16, 2012 (77 FR 55681, September 11, 2012). ADDRESSES: For service information identified in this final rule, 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. It is also available on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2015-2965. 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 AD, the regulatory evaluation, any comments received, and other information. The address for the Docket Office (phone: 800-647- 5527) is Docket Management Facility, 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 23587]] 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: Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to supersede AD 2012-17-13, Amendment 39-17176 (77 FR 55681, September 11, 2012) (``AD 2012-17-13''). AD 2012-17-13 applied to certain The Boeing Company Model 707 airplanes, and Model 720 and 720B series airplanes. The NPRM published in the Federal Register on July 30, 2015 (80 FR 45453) (``the NPRM''). The NPRM 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. The NPRM proposed to continue to require, for certain airplanes, 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. The NPRM also proposed to continue to require, for all airplanes, inspecting certain structurally significant items, and repairing discrepancies if necessary. The NPRM proposed to add a requirement to replace all chord segments made of 7079 aluminum 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 compromise the structural integrity of the stabilizer. Comments We gave the public the opportunity to participate in developing this AD. The following presents the comments received on the NPRM and the FAA's response to each comment. Request To Clarify Certain Language in Paragraph (i) of the Proposed AD Boeing asked that we clarify the description of the affected components specified in paragraph (i) of the proposed AD, which is a restatement of paragraph (i) of AD 2012-17-13. Boeing stated that the intent of paragraph (i) of AD 2012-17-13 was to specify the inspection requirements for rear spar upper inboard chord segments made from 7075 aluminum. Boeing added that the restatement in paragraph (i) of the proposed AD specifies, ``For all airplanes with horizontal stabilizer components made from 7075 . . .'' and noted that this description could apply to any chord segment, not just the inboard upper. Boeing asked that the description be clarified to specify ``any horizontal stabilizer with a rear spar upper inboard chord segment made from 7075 aluminum, as determined during the inspection required by paragraph (h) of this AD.'' We agree to clarify paragraph (i) of this AD. The inspection required by paragraph (i) of this AD must be done on upper chords made from 7075 aluminum that are on the inboard end of the rear spar, as specified in Boeing 707 Alert Service Bulletin A3515, dated December 19, 2007; and Boeing 707 Alert Service Bulletin A3515, Revision 1, dated October 10, 2014; which are the appropriate sources of service information for accomplishing the required actions. We have revised paragraph (i) of this AD to clarify the inspection requirements. No additional action is necessary for operators that have already complied with paragraph (i) of this AD. Request To Clarify Certain Language in Paragraph (j) of the Proposed AD Boeing also asked that we clarify the language in the restatement of actions specified in paragraph (j) of the proposed AD in order to specify that the inspections in paragraph (i) of the proposed AD can only be deferred for 4,000 flight cycles if the upper inboard chord is replaced with a new chord. Boeing stated that changing paragraph (i) of the proposed AD ensures that it is clear that the inspection can only be deferred for 4,000 flight cycles if the upper inboard chord is replaced. We agree with the commenter for the reason provided. We have changed paragraph (j) of this AD to specify ``For airplanes on which the rear spar upper inner chord is replaced with a new chord . . . :'' Request To Clarify Certain Language in Paragraph (q) of the Proposed AD Boeing also asked that we clarify the language in the new actions specified in paragraph (q) of the proposed AD. Boeing stated that paragraph (j) of the proposed AD states when to resume the inspections after the chord is replaced. Boeing added that paragraph (i) of the proposed AD states the type of inspection and the repetitive inspection interval. Therefore, Boeing stated that paragraph (q) of the proposed AD should point to paragraph (i) of the proposed AD. We agree to clarify paragraph (q) of this AD. As noted above, paragraph (j) of the this AD specifies inspecting the new chord within 4,000 flight cycles after the chord replacement, as required by paragraph (i) of this AD, and repeating the inspections thereafter at the times specified in paragraph (i) of this AD. Therefore, we have included similar language in paragraph (q) of this AD. Request To Clarify Service Information References In addition, Boeing asked that we include 707 in the title for ``Boeing Service Bulletin 3381,'' as identified in paragraphs (k) and (l) of the proposed AD, to be consistent with all the other service information references in the NPRM. We agree with the commenter for the reasons provided. We have changed the service information references in paragraphs (k)(3)(i) and (l) of this AD to specify ``Boeing 707 Service Bulletin 3381.'' Boeing also asked that we change the semi-colon (located between the service information references) in paragraph (k)(3)(ii) of the proposed AD to a comma, because it breaks up the sentence in an unintended way. We do not agree to change the semi-colon in paragraph (k)(3)(ii) of this AD. In ADs, we use a semi-colon to separate service information references, except in cases where the semi-colon between service information might cause confusion, e.g., a sentence that already uses semi-colons between text other than the service information. The semi- colon in paragraph (k)(3)(ii) of this AD does not change the intent of that paragraph. We have not changed this AD in this regard. Conclusion We reviewed the available data and determined that air safety and the public interest require adopting this AD with the changes described previously, and minor editorial changes. We have determined that these minor changes:Are consistent with the intent that was proposed in the NPRM for correcting the unsafe condition; and Do not add any additional burden upon the public than was already proposed in the NPRM. Related Service Information Under 1 CFR Part 51 We reviewed Boeing 707 Alert Service Bulletin A3515, Revision 1, dated October 10, 2014. The service [[Page 23588]] 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. Costs of Compliance We estimate that this AD affects 10 airplanes of U.S. registry. We estimate the following costs to comply with this AD: Table--Estimated Costs ---------------------------------------------------------------------------------------------------------------- Action Work hours Parts Cost per product Fleet cost ---------------------------------------------------------------------------------------------------------------- Retained inspections from AD Up to 32 work-hours x $0............... Up to $2,720 per Up to $27,200 per 2012-17-13. $85 per hour = up to inspection cycle. inspection $2,720 per inspection cycle. cycle. Replacement [new action]....... 500 work-hours x $85 Up to $228,000 Up to $2,705,000 Up to per work-hour = per chord. (up to 10 chords $27,050,000.2 $42,500 per chord. 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 AD will not have federalism implications under Executive Order 13132. This AD will 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 this AD: (1) Is not a ``significant regulatory action'' under Executive Order 12866, (2) Is not a ``significant rule'' under 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. Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA amends 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: 2016-08-11 The Boeing Company: Amendment 39-18487; Docket No. FAA- 2015-2965; Directorate Identifier 2014-NM-227-AD. (a) Effective Date This AD is effective May 27, 2016. (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 707 airplanes). (2) Boeing 707 Alert Service Bulletin A3515, Revision 1, dated October 10, 2014 (for Model 707 airplanes). (3) Boeing 707 Alert Service Bulletin A3516, dated April 4, 2008 (for Model 707 airplanes, and Model 720 and 720B series airplanes). [[Page 23589]] (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 and Affected Component Description 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 information and affected component description. For airplanes with any horizontal stabilizer with a rear spar upper inboard chord segment 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 and Revised Language for Affected Airplanes 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 and revised langue for affected airplanes. For airplanes on which the rear spar upper inner 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, inspect the new chord, as 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 707 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 707 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 [[Page 23590]] 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 707 Service Bulletin 3381, dated July 25, 1980; or Boeing 707 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 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 using a method approved 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 With Revised Service Information This paragraph restates the parts installation prohibition required by paragraph (p) of AD 2012-17-13, Amendment 39-17176 (77 FR 55681, September 11, 2012), with revised service information. 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, inspect the new chord, as required by paragraph (i) of this AD, and repeat the inspections thereafter at the times specified in paragraph (i) of this AD. (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) 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, modification, or alteration required by this AD if it is approved by the Boeing Commercial Airplanes Organization Designation Authorization (ODA) that has been authorized by the Manager, Los Angeles ACO, to make those findings. To be approved, the repair method, modification deviation, or alteration deviation must meet the certification basis of the airplane, and the approval must specifically refer to this AD. (4) AMOCs approved for AD 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 For more information about this AD, contact Chandra Ramdoss, Aerospace Engineer, Airframe Branch, ANM-120L, FAA, Los Angeles ACO, 3960 Paramount Boulevard, Lakewood, CA 90712-4137; phone: 562-627- 5239; fax: 562-627-5210; email: [email protected]. (t) Material Incorporated by Reference (1) The Director of the Federal Register approved the incorporation by reference (IBR) of the service information listed in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51. (2) You must use this service information as applicable to do the actions required by this AD, unless the AD specifies otherwise. (i) Boeing 707 Alert Service Bulletin A3515, Revision 1, dated October 10, 2014. [[Page 23591]] (ii) Reserved. (3) The following service information was approved for IBR on October 16, 2012 (77 FR 55681, September 11, 2012). (i) Boeing 707 Alert Service Bulletin A3515, dated December 19, 2007. (ii) Boeing 707 Alert Service Bulletin A3516, dated April 4, 2008. (iii) Subject 51-00-00, ``Structures-General,'' Figure 20, ``Electrical Conductivity Measurement for Aluminum,'' of Part 6-- Eddy Current, of the Boeing 707/720 Nondestructive Test Manual, Document D6-48023, Revision 118, dated July 15, 2011. The revision level of this document is identified on only the manual revision Transmittal Sheet. (iv) 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. The revision level of this document is identified on only the manual revision Transmittal Sheet. (v) 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. The revision level of this document is identified on only the manual revision Transmittal Sheet. (4) 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. (5) You may view this service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425-227-1221. (6) You may view this service information that is incorporated by reference at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202-741-6030, or go to: http://www.archives.gov/federal-register/cfr/ibr-locations.html. Issued in Renton, Washington, on April 5, 2016. Suzanne Masterson, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2016-08539 Filed 4-21-16; 8:45 am] BILLING CODE 4910-13-P
![23586 Federal Register / Vol. 81, No. 78 / Friday, April 22, 2016 / Rules and Regulations
assembly part number 2447M10G01 or (4) The following service information was airplanes, AD 2012–17–13 required
2447M10G02: Before October 1, 2016, do the approved for IBR on March 18, 2016 (81 FR inspecting certain structurally
actions specified by paragraph (j)(1) or (j)(2) 14704, March 18, 2016). significant items, and repairing
of this AD. (i) GE GEnx–1B Service Bulletin 72–0309
(1) Rework at least one engine in R00, dated March 11, 2016.
discrepancies if necessary. This new AD
accordance with paragraph 3.B. or 3.C. of the (ii) Reserved. adds a requirement to replace all chord
Accomplishment Instructions of GE GEnx–1B (5) For service information identified in segments made of 7079 aluminum with
Service Bulletin 72–0309 R00, dated March this AD, contact General Electric Company, new, improved chord segments made of
11, 2016; or paragraph 3.B. or 3.C. of the GE Aviation, Room 285, 1 Neumann Way, 7075 aluminum. This AD was prompted
Accomplishment Instructions of GE GEnx–1B Cincinnati, OH 45215; phone: 513–552–3272; by a determination that all chord
Service Bulletin 72–0314 R00, dated April 1, email: aviation.fleetsupport@ge.com. segments made of 7079 aluminum must
2016. Although GE GEnx Service Bulletins (6) You may view this service information be replaced with new, improved chord
GEnx–1B 72–0314 R00, dated April 1, 2016; at the FAA, Transport Airplane Directorate,
and GEnx–1B 72–0309 R00, dated March 11, 1601 Lind Avenue SW., Renton, WA. For
segments made of 7075 aluminum. We
2016; specify submitting certain tip clearance information on the availability of this are issuing this AD to detect and correct
measurements to GE, no report is required by material at the FAA, call 425–227–1221. stress corrosion and potential early
this AD. (7) You may view this service information fatigue cracking in the horizontal
(2) Remove at least one engine and replace that is incorporated by reference at the stabilizer, which could result in reduced
with an engine that is eligible for installation National Archives and Records structural integrity of the horizontal
that is not identified in the introductory text Administration (NARA). For information on stabilizer.
to paragraph (j) of this AD. the availability of this material at NARA, call
202–741–6030, or go to http:// DATES: This AD is effective May 27,
(k) Alternative Methods of Compliance 2016.
www.archives.gov/federal-register/cfr/ibr-
(AMOCs) The Director of the Federal Register
locations.html.
(1) The Manager, Seattle Aircraft approved the incorporation by reference
Certification Office (ACO), FAA, has the Issued in Burlington, Massachusetts, on
April 7, 2016. of a certain publication listed in this AD
authority to approve AMOCs for this AD, if
Ann C. Mollica, as of May 27, 2016.
requested using the procedures found in 14
CFR 39.19. In accordance with 14 CFR 39.19,
The Director of the Federal Register
Acting Manager, Engine & Propeller
send your request to your principal inspector Directorate, Aircraft Certification Service. approved the incorporation by reference
or local Flight Standards District Office, as of certain other publications listed in
Issued in Renton, Washington, on April 12,
appropriate. If sending information directly 2016. this AD as of October 16, 2012 (77 FR
to the manager of the ACO, send it to the
Victor Wicklund,
55681, September 11, 2012).
attention of the person identified in ADDRESSES: For service information
paragraph (l) of this AD. Information may be Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service. identified in this final rule, contact
emailed to: 9-ANM-Seattle-ACO-AMOC-
Requests@faa.gov. [FR Doc. 2016–09000 Filed 4–21–16; 8:45 am]
Boeing Commercial Airplanes,
(2) Before using any approved AMOC, Attention: Data & Services Management,
BILLING CODE 4910–13–P
notify your appropriate principal inspector, 3855 Lakewood Boulevard, MC D800–
or lacking a principal inspector, the manager 0019, Long Beach, CA 90846–0001;
of the local flight standards district office/ DEPARTMENT OF TRANSPORTATION telephone 206–544–5000, extension 2;
certificate holding district office. fax 206–766–5683; Internet https://
(3) An AMOC that provides an acceptable Federal Aviation Administration www.myboeingfleet.com. You may view
level of safety may be used for any repair, this referenced service information at
modification, or alteration required by this
AD if it is approved by the Boeing 14 CFR Part 39 the FAA, Transport Airplane
Commercial Airplanes Organization Directorate, 1601 Lind Avenue SW.,
[Docket No. FAA–2015–2965; Directorate
Designation Authorization (ODA) that has Identifier 2014–NM–227–AD; Amendment
Renton, WA. For information on the
been authorized by the Manager, Seattle 39–18487; AD 2016–08–11] availability of this material at the FAA,
ACO, to make those findings. To be call 425–227–1221. It is also available
approved, the repair method, modification RIN 2120–AA64 on the Internet at http://
deviation, or alteration deviation must meet www.regulations.gov by searching for
the certification basis of the airplane, and the Airworthiness Directives; The Boeing and locating Docket No. FAA–2015–
approval must specifically refer to this AD. Company Airplanes 2965.
(l) Related Information AGENCY: Federal Aviation Examining the AD Docket
For more information about this AD, Administration (FAA), DOT.
contact Sue Lucier, Aerospace Engineer, ACTION: Final rule. You may examine the AD docket on
Propulsion Branch, ANM–140S, FAA, Seattle the Internet at http://
ACO, 1601 Lind Avenue SW., Renton, WA SUMMARY: We are superseding www.regulations.gov by searching for
98057–3356; phone: 425–917–6438; fax: 425– Airworthiness Directive (AD) 2012–17– and locating Docket No. FAA–2015–
917–6590; email: Suzanne.Lucier@faa.gov. 13, which applied to certain The Boeing 2965; or in person at the Docket
(m) Material Incorporated by Reference Company Model 707 airplanes, and Management Facility between 9 a.m.
(1) The Director of the Federal Register Model 720 and 720B series airplanes. and 5 p.m., Monday through Friday,
approved the incorporation by reference For certain airplanes, AD 2012–17–13 except Federal holidays. The AD docket
(IBR) of the service information listed in this required using redefined flight cycle contains this AD, the regulatory
paragraph under 5 U.S.C. 552(a) and 1 CFR counts; determining the type of material evaluation, any comments received, and
asabaliauskas on DSK3SPTVN1PROD with RULES
part 51. of the horizontal stabilizer, rear spar, other information. The address for the
(2) You must use this service information and upper and lower chords on the Docket Office (phone: 800–647–5527) is
as applicable to do the actions required by inboard and outboard ends of the rear Docket Management Facility, U.S.
this AD, unless the AD specifies otherwise.
(3) The following service information was
spar; repetitively inspecting for cracking Department of Transportation, Docket
approved for IBR on May 9, 2016. of the horizontal stabilizer components; Operations, M–30, West Building
(i) GE GEnx–1B Service Bulletin 72–0314 and repairing or replacing the chord, or Ground Floor, Room W12–140, 1200
R00, dated April 1, 2016. modifying chord segments made of 7079 New Jersey Avenue SE., Washington,
(ii) Reserved. aluminum, if necessary. For all DC 20590.
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![23588 Federal Register / Vol. 81, No. 78 / Friday, April 22, 2016 / Rules and Regulations
information describes procedures for chord segments made of 7075 Costs of Compliance
incorporating a new cycle counting aluminum. This service information is
procedure, determining the material for reasonably available because the We estimate that this AD affects 10
the horizontal stabilizer rear spar chord interested parties have access to it airplanes of U.S. registry.
segment, inspecting for stress corrosion through their normal course of business We estimate the following costs to
cracking and fatigue cracking, repair, or by the means identified in the comply with this AD:
and replacing all chord segments made ADDRESSES section.
of 7079 aluminum with new, improved
TABLE—ESTIMATED COSTS
Action Work hours Parts Cost per product Fleet cost
Retained inspections Up to 32 work-hours × $85 per hour = up $0 .............................. Up to $2,720 per in- Up to $27,200 per inspec-
from AD 2012–17– to $2,720 per inspection cycle. spection cycle. tion cycle.
13.
Replacement [new ac- 500 work-hours × $85 per work-hour = Up to $228,000 per Up to $2,705,000 (up Up to $27,050,000.2
tion]. $42,500 per chord. chord. 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 on a substantial number of small entities (1) Model 707 airplanes identified in
under the criteria of the Regulatory Boeing 707 Alert Service Bulletin A3515,
Title 49 of the United States Code
Flexibility Act. Revision 1, dated October 10, 2014.
specifies the FAA’s authority to issue (2) Model 720 and 720B series airplanes
rules on aviation safety. Subtitle I, List of Subjects in 14 CFR Part 39 identified in Boeing 707 Alert Service
Section 106, describes the authority of Bulletin A3516, dated April 4, 2008.
the FAA Administrator. Subtitle VII, Air transportation, Aircraft, Aviation
Aviation Programs, describes in more safety, Incorporation by reference, (d) Subject
detail the scope of the Agency’s Safety. Air Transport Association (ATA) of
authority. America Code 55, Stabilizers.
We are issuing this rulemaking under Adoption of the Amendment
(e) Unsafe Condition
the authority described in Subtitle VII, Accordingly, under the authority
Part A, Subpart III, Section 44701, This AD was prompted by a determination
delegated to me by the Administrator,
‘‘General requirements.’’ Under that that all chord segments made of 7079
the FAA amends 14 CFR part 39 as aluminum must be replaced with new,
section, Congress charges the FAA with follows:
promoting safe flight of civil aircraft in improved chord segments made of 7075
air commerce by prescribing regulations aluminum. We are issuing this AD to detect
PART 39—AIRWORTHINESS and correct stress corrosion and potential
for practices, methods, and procedures DIRECTIVES early fatigue cracking in the horizontal
the Administrator finds necessary for
stabilizer, which could result in reduced
safety in air commerce. This regulation ■ 1. The authority citation for part 39 structural integrity of the horizontal
is within the scope of that authority continues to read as follows: stabilizer.
because it addresses an unsafe condition
that is likely to exist or develop on Authority: 49 U.S.C. 106(g), 40113, 44701. (f) Compliance
products identified in this rulemaking § 39.13 [Amended] Comply with this AD within the
action. compliance times specified, unless already
■ 2. The FAA amends § 39.13 by done.
Regulatory Findings
removing Airworthiness Directive (AD) (g) Retained Flight Cycle Counting
We have determined that this AD will 2012–17–13, Amendment 39–17176 (77 Procedure, With Revised Service
not have federalism implications under FR 55681, September 11, 2012), and Information
Executive Order 13132. This AD will adding the following new AD:
not have a substantial direct effect on This paragraph restates the requirements of
2016–08–11 The Boeing Company: paragraph (g) of AD 2012–17–13,
the States, on the relationship between Amendment 39–18487; Docket No. Amendment 39–17176 (77 FR 55681,
the national government and the States, FAA–2015–2965; Directorate Identifier September 11, 2012), with revised service
or on the distribution of power and 2014–NM–227–AD. information. Flight cycles, as used in this
responsibilities among the various AD, must be counted as defined in the
levels of government. (a) Effective Date
service information identified in paragraph
For the reasons discussed above, I This AD is effective May 27, 2016. (g)(1), (g)(2), or (g)(3) of this AD.
certify that this AD: (b) Affected ADs (1) Boeing 707 Alert Service Bulletin
(1) Is not a ‘‘significant regulatory A3515, dated December 19, 2007 (for Model
asabaliauskas on DSK3SPTVN1PROD with RULES
This AD replaces AD 2012–17–13,
action’’ under Executive Order 12866, 707 airplanes).
Amendment 39–17176 (77 FR 55681,
(2) Is not a ‘‘significant rule’’ under (2) Boeing 707 Alert Service Bulletin
September 11, 2012).
DOT Regulatory Policies and Procedures A3515, Revision 1, dated October 10, 2014
(44 FR 11034, February 26, 1979), (c) Applicability (for Model 707 airplanes).
(3) Will not affect intrastate aviation This AD applies to The Boeing Company (3) Boeing 707 Alert Service Bulletin
in Alaska, and airplanes, certificated in any category; A3516, dated April 4, 2008 (for Model 707
(4) Will not have a significant identified in paragraphs (c)(1) and (c)(2) of airplanes, and Model 720 and 720B series
economic impact, positive or negative, this AD. airplanes).
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![Federal Register / Vol. 81, No. 78 / Friday, April 22, 2016 / Rules and Regulations 23591
(ii) Reserved. ACTION: Final rule. of airspace necessary to ensure the
(3) The following service information was safety of aircraft and the efficient use of
approved for IBR on October 16, 2012 (77 FR SUMMARY: This action establishes Class airspace. This regulation is within the
55681, September 11, 2012). E airspace in Coldwater, KS. Controlled scope of that authority as it establishes
(i) Boeing 707 Alert Service Bulletin airspace is necessary to accommodate
A3515, dated December 19, 2007. controlled airspace at Comanche County
new Standard Instrument Approach Airport, Coldwater, KS.
(ii) Boeing 707 Alert Service Bulletin
Procedures (SIAPs) at Comanche County
A3516, dated April 4, 2008. History
(iii) Subject 51–00–00, ‘‘Structures- Airport. The FAA is taking this action
General,’’ Figure 20, ‘‘Electrical Conductivity to enhance the safety and management On February 11, 2016, the FAA
Measurement for Aluminum,’’ of Part 6— of Instrument Flight Rule (IFR) published in the Federal Register a
Eddy Current, of the Boeing 707/720 operations at the airport. Additionally, notice of proposed rulemaking (NPRM)
Nondestructive Test Manual, Document D6– to this action corrects the spelling of the to establish Class E Airspace in the
48023, Revision 118, dated July 15, 2011. The airport name to Comanche County Coldwater, KS area. (81 FR 7251) FAA
revision level of this document is identified Airport, inadvertently misspelled in the
on only the manual revision Transmittal
2015–5194. Interested parties were
proposal. invited to participate in this rulemaking
Sheet.
(iv) Subject 51–01–00, ‘‘Orientation and DATES: Effective 0901 UTC, July 21, effort by submitting written comments
Preparation for Testing’’ of Part 1—General, 2016. The Director of the Federal on the proposal to the FAA. No
of the Boeing 707/720 Nondestructive Test Register approves this incorporation by comments were received.
Manual, Document D6–48023, Revision 118, reference action under title 1, Code of Class E airspace designations are
dated July 15, 2011. The revision level of this Federal Regulations, part 51, subject to published in paragraph 6005 of FAA
document is identified on only the manual the annual revision of FAA Order Order 7400.9Z dated August 6, 2015,
revision Transmittal Sheet. and effective September 15, 2015, which
7400.9 and publication of conforming
(v) Subject 55–10–07, ‘‘Horizontal
Stabilizer,’’ of Part 6—Eddy Current, of the amendments. is incorporated by reference in 14 CFR
Boeing 707/720 Nondestructive Test Manual, ADDRESSES: FAA Order 7400.9Z,
part 71.1. The Class E airspace
Document D6–48023, Revision 118, dated Airspace Designations and Reporting designations listed in this document
July 15, 2011. The revision level of this Points, and subsequent amendments can will be published subsequently in the
document is identified on only the manual
be viewed on line at http:// Order.
revision Transmittal Sheet.
(4) For service information identified in www.faa.gov/airtraffic/publications/. Availability and Summary of
this AD, contact Boeing Commercial For further information, you can contact Documents for Incorporation by
Airplanes, Attention: Data & Services the Airspace Policy Group, Federal Reference
Management, 3855 Lakewood Boulevard, MC Aviation Administration, 800 This document amends FAA Order
D800–0019, Long Beach, CA 90846–0001; Independence Avenue SW.,
telephone 206–544–5000, extension 2; fax 7400.9Z, airspace Designations and
Washington, DC 20591; telephone: 202– Reporting Points, dated August 6, 2015,
206–766–5683; Internet https:// 267–8783. The Order is also available
www.myboeingfleet.com. and effective September 15, 2015. FAA
for inspection at the National Archives Order 7400.9Z is publicly available as
(5) You may view this service information
at the FAA, Transport Airplane Directorate, and Records Administration (NARA). listed in the ADDRESSES section of this
1601 Lind Avenue SW., Renton, WA. For For information on the availability of
document. FAA Order 7400.9Z lists
information on the availability of this this material at NARA, call 202–741–
Class A, B, C, D, and E airspace areas,
material at the FAA, call 425–227–1221. 6030, or go to http://www.archives.gov/
air traffic service routes, and reporting
(6) You may view this service information federal_register/code_of_federal-
that is incorporated by reference at the
points.
regulations/ibr_locations.html.
National Archives and Records FAA Order 7400.9, Airspace The Rule
Administration (NARA). For information on Designations and Reporting Points, is
the availability of this material at NARA, call This amendment to Title 14, Code of
published yearly and effective on Federal Regulations (14 CFR) part 71
202–741–6030, or go to: http://
www.archives.gov/federal-register/cfr/ibr-
September 15. establishes Class E airspace extending
locations.html. FOR FURTHER INFORMATION CONTACT: upward from 700 feet above the surface
Rebecca Shelby, Central Service Center, within a 7.5-mile radius of Comanche
Issued in Renton, Washington, on April 5,
2016. Operations Support Group, Federal County Airport, Coldwater, KS, to
Aviation Administration, Southwest accommodate new standard instrument
Suzanne Masterson,
Region, 10101 Hillwood Parkway, Fort approach procedures. Controlled
Acting Manager, Transport Airplane
Worth, TX 76177; telephone: (817) 222– airspace is needed for the safety and
Directorate, Aircraft Certification Service.
5857. management of IFR operations at the
[FR Doc. 2016–08539 Filed 4–21–16; 8:45 am]
SUPPLEMENTARY INFORMATION: airport. Additionally, the airport name
BILLING CODE 4910–13–P
Authority for This Rulemaking is corrected from Commanche County
Airport to Comanche County Airport.
The FAA’s authority to issue rules Class E airspace designations are
DEPARTMENT OF TRANSPORTATION
regarding aviation safety is found in published in Paragraph 6005 of FAA
Federal Aviation Administration Title 49 of the United States Code. Order 7400.9Z, dated August 6, 2015,
Subtitle I, Section 106 describes the and effective September 15, 2015, which
14 CFR Part 71 authority of the FAA Administrator. is incorporated by reference in 14 CFR
asabaliauskas on DSK3SPTVN1PROD with RULES
Subtitle VII, Aviation Programs, 71.1. The Class E airspace designations
[Docket No. FAA–2015–5194; Airspace describes in more detail the scope of the listed in this document will be
Docket No. 15–ACE–6] agency’s authority. This rulemaking is published subsequently in the Order.
promulgated under the authority
Establishment of Class E Airspace; Regulatory Notices and Analyses
described in Subtitle VII, Part, A,
Coldwater, KS
Subpart I, Section 40103. Under that The FAA has determined that this
AGENCY:Federal Aviation section, the FAA is charged with regulation only involves an established
Administration (FAA), DOT. prescribing regulations to assign the use body of technical regulations for which
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Document Created: 2017-08-22 23:36:47
Document Modified: 2017-08-22 23:36:47
| 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 | Rules and Regulations | |
| Action | Final rule. | |
| Dates | This AD is effective May 27, 2016. | |
| 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 | 81 FR 23586 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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