81 FR 14711 - Airworthiness Directives; The Boeing Company Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 81, Issue 53 (March 18, 2016)
Federal Aviation Administration
Federal Register Volume 81, Issue 53 (March 18, 2016)
| Page Range | 14711-14716 | |
| FR Document | 2016-05842 |
[Federal Register Volume 81, Number 53 (Friday, March 18, 2016)] [Rules and Regulations] [Pages 14711-14716] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2016-05842] ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2015-0495; Directorate Identifier 2014-NM-172-AD; Amendment 39-18435; AD 2016-06-04] RIN 2120-AA64 Airworthiness Directives; The Boeing Company Airplanes AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Final rule. ----------------------------------------------------------------------- SUMMARY: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 737-300, -400, and -500 series airplanes. This AD was prompted by reports of cracking at certain fastener locations in the window corners of the window belt area. This AD requires repetitive high frequency eddy current (HFEC) inspections for fatigue cracking in certain fastener locations in the window corners of the window belt area, and related investigative and corrective actions if necessary. This AD also provides an optional preventive modification that terminates the inspections at the modified location. We are issuing this AD to detect and correct fatigue cracking around fastener locations that could cause multiple window corner skin cracks, which could result in rapid decompression and loss of structural integrity of the airplane. DATES: This AD is effective April 22, 2016. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of April 22, 2016. ADDRESSES: For service information identified in this final rule, contact Boeing Commercial Airplanes, Attention: Data & Services Management, P.O. Box 3707, MC 2H-65, Seattle, WA 98124-2207; telephone 206-544-5000, extension 1; fax 206-766-5680; Internet https://www.myboeingfleet.com. You may view this referenced service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425-227-1221. It is also available on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2015- 0495. 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- 0495; 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. FOR FURTHER INFORMATION CONTACT: Jennifer Tsakoumakis, Aerospace Engineer, Airframe Branch, ANM-120L, FAA, Los Angeles Aircraft Certification Office (ACO), 3960 Paramount Boulevard, Lakewood, CA 90712-4137; phone: 562-627-5264; fax: 562-627-5210; email: [email protected]. SUPPLEMENTARY INFORMATION: Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 by adding an AD that would apply to certain The Boeing Company Model 737-300, -400, and -500 series airplanes. The NPRM published in the Federal Register on March 24, 2015 (80 FR 15523) (``the NPRM''). The NPRM was prompted by reports of cracking at certain fastener locations in the window corners of the window belt area. The NPRM proposed to require repetitive HFEC inspections for fatigue cracking in certain fastener locations in the window corners of the window belt area, and related investigative and corrective actions if necessary. We are issuing this AD to detect and correct fatigue cracking around fastener locations that could cause multiple window corner skin cracks, which could result in rapid decompression and loss of structural integrity of the airplane. 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 for Clarification of Location of the Twelve Fastener Inspections Southwest Airlines (SWA) requested that a correction be made to paragraph (g) of the proposed AD to clarify the areas for the inspection of the twelve fastener locations. SWA noted that paragraph (g) of the proposed AD stated to inspect locations ``at the upper forward and lower aft corners of each window between station (STA) 360 and STA 540 and between STA 727 and STA 908.'' SWA stated that between STA 727 and STA 908, Boeing Alert Service Bulletin 737-53A1328, dated July 22, 2014, specifies the location as the lower forward and upper aft corners. We agree with the commenter for the reason provided. We have revised paragraph (g) of this AD to require an inspection of the twelve fastener locations at the upper forward and lower aft corners of each window between STA 360 and STA 540 and at the upper aft and lower forward corners of each window between STA 727 and STA 908. Request for Clarification of the Intent of the Inspection Requirements in Paragraph (g) of the Proposed AD SWA requested that we clarify the intent of paragraph (g) of the proposed AD. SWA stated that paragraph (g) of the proposed AD states to accomplish the inspections at the times specified in tables 1 and 2 of paragraph 1.E., [[Page 14712]] ``Compliance,'' of Boeing Alert Service Bulletin 737-53A1328, dated July 22, 2014, and then repeat the inspections at the applicable times specified in tables 1 and 2 until ``the terminating action in paragraph (h) of this AD is accomplished,'' which is the optional preventive modification in Part 3 of the Accomplishment Instructions of Boeing Alert Service Bulletin 737-53A1328, dated July 22, 2014. SWA stated that, per note (b) in tables 1 and 2, accomplishment of the preventive modification in accordance with Boeing Alert Service Bulletin 737- 53A1328, dated July 22, 2014, is terminating action for both the initial and repeat inspections at the modified locations. SWA stated that paragraph (g) of the proposed AD does not mention the option to accomplish the actions specified in paragraph (h) of the proposed AD in lieu of the initial inspection specified in paragraph (g) of this AD; it only states to ``repeat the inspections . . . until the terminating action specified in paragraph (h) of this AD is done.'' SWA noted it is unclear if the intent of paragraph (g) of this AD is to require accomplishment of the Part 1 external surface HFEC inspections of the skin prior to accomplishing the Part 3 preventive modification instructions, or if the intent of paragraph (g) of the proposed AD is to provide the operator the option to accomplish paragraph (h) of the proposed AD (preventive modification) in lieu of accomplishing paragraph (g) of the proposed AD (inspections), since the Part 3 modification instructions include open hole HFEC inspections of the skin. We agree to provide clarification. Paragraph (g) of this AD is not required at the time of accomplishment of the preventive modification specified in paragraph (h) of this AD. Paragraph (h) of this AD states that the preventive modification (including all applicable related investigative and corrective actions) terminates the inspections in paragraph (g) of this AD. This means all inspections (initial and repetitive) in paragraph (g) of this AD are not required if paragraph (h) of this AD is done. We have not changed this AD in this regard. Request for Clarification of Existing Repairs SWA requested clarification about existing repairs that meet the requirements of note (a) in tables 1 and 2 of paragraph l.E., ``Compliance,'' of Boeing Alert Service Bulletin 737-53A1328, dated July 22, 2014. SWA also requested to extend the note to apply to existing repairs that address damage other than cracking, provided that the repairs are evaluated and approved by Boeing via an FAA Form 8100- 9. In addition, SWA requested we clarify whether note (a) applies only to reinforcing repairs that encompass all twelve fastener locations at a window corner, or if note (a) also applies to existing non- reinforcing oversize hole repairs. We partially agree with the commenter. We agree with adding a paragraph to this AD to provide credit for previously approved repairs to address cracking issues, because Boeing Organization Designation Authorization (ODA) approved repairs installed prior the effective date of this AD are acceptable for terminating the initial and repetitive inspections in the area under the repair. We disagree with allowing any other repair as an alternative method of compliance (AMOC) because other repairs may or may not address the cracking issue. However, operators may request approval of an AMOC for these repairs using the procedures specified in paragraph (l) of this AD. We have added new paragraph (g)(1) to this AD to specify that the inspections required by the introductory text of paragraph (g) of this AD may be terminated in areas with repairs installed prior to the effective date of this AD, provided the repairs are reinforcing and address the cracking issue addressed in this AD, and installation was approved by the Boeing Commercial Airplanes ODA via FAA Form 8100-9. Request for Clarification of the Termination of Inspection for Repaired Area for Group 1 Airplanes All Nippon Airways (ANA) requested we clarify if, for Group 1 airplanes as identified in paragraph 1.A.1 ``Effectivity,'' of Boeing Alert Service Bulletin 737-53A1328, dated July 22, 2014, areas repaired using Boeing Alert Service Bulletin 737-53A1328, dated July 22, 2014, is terminating action for the repaired area. ANA pointed out that table 1 of Boeing Alert Service Bulletin 737-53A1328, dated July 22, 2014, includes this wording. We agree to provide clarification. Accomplishing a repair in accordance with Part 6 of the Accomplishment Instructions of Boeing Alert Service Bulletin 737-53A1328, dated July 22, 2014, also terminates the inspection of the repaired area for Group 1 airplanes. We have added new paragraph (g)(2) to this AD to specify that repairs done in accordance with Part 6 of the Accomplishment Instructions of Boeing Alert Service Bulletin 737-53A1328, dated July 22, 2014, terminate the inspection required by paragraph (g) of this AD in only the repaired area for Group 1 airplanes only. Request To Include Provisions for Airplanes Previously Inspected, Modified, and/or Repaired SWA requested that we revise the NPRM to include provisions for airplanes that were previously inspected, modified, and/or repaired using step 3 of the Accomplishment Instructions of Boeing Service Bulletin 737-53-1306, dated September 22, 2010; Revision 1, dated March 17, 2010; Revision 2, dated October 25, 2011; or Revision 3, dated January 22, 2014; as terminating action for the inspections required by paragraph (g) of the proposed AD, as well as any documented deviations that were approved by the Boeing ODA via an FAA Form 8100-9. SWA stated that step 3 of Boeing Service Bulletin 737-53-1306 (all revisions) includes inspection, preventive modification, and repair instructions for the window corner locations addressed by the proposed AD. Figures 8 through 10 of Boeing Service Bulletin 737-53-1306 (all revisions) provide inspection and preventive modification instructions, which also include instructions for a fastener oversize repair, edge margin requirements, and window forging replacement. Figures 13 through 18 provide external reinforcing repair instructions. Figures 40 through 43 were added in Boeing Service Bulletin 737-53-1306, Revision 3, dated January 22, 2014, to incorporate the option to replace the window belt panels in lieu of accomplishing the window corner inspections, preventive modification, and approved repairs. SWA stated that it considers the instructions in Step 3 of Boeing Service Bulletin 737-53- 1306 (all revisions) to meet the intent of the proposed AD since the instructions address and eliminate the unsafe condition that prompted the proposed AD. We do not agree to revise this AD because Boeing Service Bulletin 737-53-1306 is specific for SWA. We do not consider it appropriate to include various provisions in an AD applicable only to a single operator's unique configuration of affected airplanes. However, SWA may submit a request for an approval of an AMOC using the procedures specified in paragraph (l) of this AD. We have not changed this AD in this regard. Requests To Clarify Required Actions SWA and ANA requested that we clarify which actions specified in Boeing Alert Service Bulletin 737- [[Page 14713]] 53A1328, dated July 22, 2014, are required. SWA stated that paragraph (j)(3) of the proposed AD (paragraph (l)(3) in this AD) indicates that steps identified as ``RC'' (Required for Compliance) in Boeing Alert Service Bulletin 737-53A1328, dated July 22, 2014, must be accomplished ``in order to comply with this AD.'' The commenters noted that there are ``RC'' steps in Boeing Alert Service Bulletin 737-53A1328, dated July 22, 2014, that are not clearly addressed in the proposed AD. SWA noted that Parts 7 and 8 of Boeing Alert Service Bulletin 737-53A1328, dated July 22, 2014, contain steps that are identified as ``RC;'' however, the proposed AD does not mention the compliance times for these actions. SWA stated that Part 7 of Boeing Alert Service Bulletin 737-53A1328, dated July 22, 2014, provides window frame replacement instructions, and steps 5 and 6 in Part 8 of Boeing Alert Service Bulletin 737-53A1328, dated July 22, 2014, provide post-repair/post-modification inspection instructions for window frames with short edge margin conditions at the compliance times specified in tables 3, 4, and 8 of Boeing Alert Service Bulletin 737- 53A1328, dated July 22, 2014. SWA assumed that actions identified in Table 3 and Table 8 are not required for compliance and that the actions identified in Table 4 are required for compliance. SWA also pointed out that step 10 of Part 2 of Boeing Alert Service Bulletin 737-53A1328, dated July 22, 2014, is not ``RC,'' but could result in accomplishment of Part 7 of Boeing Alert Service Bulletin 737-53A1328, dated July 22, 2014, which has ``RC'' steps. We agree to clarify the actions required by this AD. The post- modification and post-repair inspections identified in Table 4 and Table 5 in paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 737-53A1328, dated July 22, 2014, are required by this AD. The accomplishment instructions of Boeing Alert Service Bulletin 737- 53A1328, dated July 22, 2014, are unclear. Therefore, we have added new paragraph (i) to this AD to specify the actions identified in Table 4 and Table 5 in paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 737-53A1328, dated July 22, 2014. We have redesignated subsequent paragraphs accordingly. Regarding Part 7 of Boeing Alert Service Bulletin 737-53A1328, dated July 22, 2014, if operators chose to do the modification, certain actions specified in Part 3, Part 4, and Part 5 of Boeing Alert Service Bulletin 737-53A1328, dated July 22, 2014, are identified as ``RC'' steps. Within those steps, there is an on-condition action, which specifies to do Part 7; thus, step 1 of Part 7 of Boeing Alert Service Bulletin 737-53A1328, dated July 22, 2014 is required for compliance. Steps 2, 3, and 4 of Part 8 of Boeing Alert Service Bulletin 737- 53A1328, dated July 22, 2014, are referenced in Table 3 and Table 8 in paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 737- 53A1328, dated July 22, 2014, and are not required by this AD. We have added new paragraph (k) of this AD to clarify that the post- modification inspections specified in Table 3 and Table 8 in paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 737-53A1328, dated July 22, 2014, are airworthiness limitations that are required by maintenance and operational rules; therefore, these inspections are not required by this AD. We have redesignated subsequent paragraphs accordingly. Request To Clarify Office Responsible for AMOCs ANA requested that we clarify the office responsible for AMOCs. ANA stated that paragraph (j) of the proposed AD specifies that the Seattle ACO has the authority to approve AMOCs. However, ANA noted it has seen other ADs for out of production airplanes that refer to the Los Angeles ACO. We agree to clarify. The Los Angeles ACO is currently responsible for AMOCs for the airplanes identified in this AD. We have revised paragraphs (l)(1) and (l)(4) of this AD (paragraphs (j)(1) and (j)(4) of the proposed AD) to refer to the Los Angeles ACO. Requests for Clarification of Incorrect References Boeing and SWA requested that we clarify incorrect references in Boeing Alert Service Bulletin 737-53A1328, dated July 22, 2014. The commenters stated that note (e) in Figure 5 of Boeing Alert Service Bulletin 737-53A1328, dated July 22, 2014, incorrectly references table 2 of paragraph 3.B., Work Instructions, for post repair/modification inspections of short edge margins on window frames. The commenters stated that these references should be to table 3 of paragraph 3.B., Work Instructions. Boeing also identified the notes in figures 9, 10, 11, and 12 as additional locations where the reference to table 2 should be to table 3. The commenters requested that we clarify in this AD that repeat post repair and modification inspections for window frames with short edge margins are defined in table 3 rather than table 2 of paragraph 3.B, Work Instructions, in Boeing Alert Service Bulletin 737-53A1328, dated July 22, 2014. We agree with the commenters that the identified table references in Boeing Alert Service Bulletin 737-53A1328, dated July 22, 2014, are incorrect. We have added new paragraphs (j)(3) and (j)(4) to this AD to specify the correct table references. We have also added new paragraph (j)(5) to this AD to clarify that operators must comply with the edge margin requirements in Table 3 of the Accomplishment Instructions of Boeing Alert Service Bulletin 737-53A1328, dated July 22, 2014. We have also revised paragraphs (g) and (h) of this AD to include references to paragraphs (j)(3), (j)(4), and (j)(5) of this AD. Effect of Winglets on Accomplishment of the Proposed Actions Aviation Partners Boeing stated that accomplishing Supplemental Type Certificate (STC) ST01219SE (http://rgl.faa.gov/ Regulatory_and_Guidance_Library/rgstc.nsf/0/ be866b732f6cf31086257b9700692796/$FILE/ST01219SE.pdf) does not affect the actions specified in the NPRM. We concur with the commenter. We have redesignated paragraph (c) of the proposed AD as paragraph (c)(1) of this AD and added new paragraph (c)(2) to this AD to state that installation of STC ST01219SE does not affect the ability to accomplish the actions required by this AD. Therefore, for airplanes on which STC ST01219SE is installed, a ``change in product'' AMOC approval request is not necessary to comply with the requirements of 14 CFR 39.17. Conclusion We reviewed the relevant data, considered the comments received, 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. We also determined that these changes will not increase the economic burden on any operator or increase the scope of this AD. Related Service Information Under 1 CFR Part 51 We reviewed Boeing Alert Service Bulletin 737-53A1328, dated July 22, 2014. The service information describes procedures for HFEC inspections for [[Page 14714]] fatigue cracking in certain fastener locations in the window corners of the window belt area, and related investigative and corrective actions. 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 142 airplanes of U.S. registry. We estimate the following costs to comply with this AD: Estimated Costs: Required Actions ---------------------------------------------------------------------------------------------------------------- Cost on U.S. Action Labor cost Parts cost Cost per product operators ---------------------------------------------------------------------------------------------------------------- Inspection................. Up to 2,312 work- $0 Up to $196,520 per Up to $27,905,840 per hours x $85 per hour inspection cycle. inspection cycle. = $196,520 per inspection cycle. ---------------------------------------------------------------------------------------------------------------- Estimated Costs: Required Actions ---------------------------------------------------------------------------------------------------------------- Cost per Action Labor cost Parts cost product ---------------------------------------------------------------------------------------------------------------- Preventive modification....................... 108 work-hours x $85 per hour = $0 $9,180 $9,180. ---------------------------------------------------------------------------------------------------------------- We estimate the following costs to do any necessary repairs that would be required based on the results of the inspection. We have no way of determining the number of aircraft that might need repairs: On-Condition Costs ---------------------------------------------------------------------------------------------------------------- Action Labor cost Parts cost Cost per product ---------------------------------------------------------------------------------------------------------------- Repair...................... Up to 18 work-hours x $0 Up to $1,530 per repair. $85 per hour = $1,530 per repair. ---------------------------------------------------------------------------------------------------------------- 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 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 adding the following new airworthiness directive (AD): 2016-06-04 The Boeing Company: Amendment 39-18435 ; Docket No. FAA- 2015-0495; Directorate Identifier 2014-NM-172-AD. (a) Effective Date This AD is effective April 22, 2016. (b) Affected ADs None. (c) Applicability (1) This AD applies to The Boeing Company Model 737-300, -400, and -500 series airplanes, certificated in any category, as identified in Boeing Alert Service Bulletin 737-53A1328, dated July 22, 2014. (2) Installation of Supplemental Type Certificate (STC) ST01219SE (http://rgl.faa.gov/Regulatory_and_Guidance_Library/ rgstc.nsf/0/be866b732f6cf31086257b9700692796/$FILE/ST01219SE.pdf) does not affect the ability to accomplish the actions required by this AD. Therefore, for airplanes on which STC ST01219SE is installed, a ''change in product'' alternative method of compliance (AMOC) approval request is not necessary to comply with the requirements of 14 CFR 39.17. (d) Subject Air Transport Association (ATA) of America Code 53, Fuselage. (e) Unsafe Condition This AD was prompted by reports of fatigue cracking at certain fastener locations in the window corners of the window belt area. We are issuing this AD to detect and correct fatigue cracking around the fastener [[Page 14715]] locations that could cause multiple window corner skin cracks, which could result in rapid decompression and loss of structural integrity of the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Inspections At the applicable time specified in tables 1 and 2 of paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 737-53A1328, dated July 22, 2014, except as required by paragraph (j)(1) of this AD: Do external surface high frequency eddy current (HFEC) inspections for cracking of the skin at the 12 fastener locations at the upper forward and lower aft corners of each window between station (STA) 360 and STA 540 and at the upper aft and lower forward corners of each window between STA 727 and STA 908, left-side and right-side of the fuselage, at and between stringers S-11 and S-13; and all applicable related investigative and corrective actions; in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 737-53A1328, dated July 22, 2014, except as required by paragraphs (j)(2), (j)(3), (j)(4), and (j)(5) of this AD. Do all applicable related investigative and corrective actions before further flight. Repeat the inspections at the applicable times specified in tables 1 and 2 of paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 737-53A1328, dated July 22, 2014. Accomplishing the preventive modification specified in paragraph (h) of this AD terminates the repetitive inspections required by this paragraph at the modified location only. (1) The inspections required by the introductory text of paragraph (g) of this AD may be terminated in areas with repairs installed prior to the effective date of this AD, provided the repairs are reinforcing and address the cracking issue identified in this AD, and installation was approved by the Boeing Commercial Airplanes Organization Designation Authorization (ODA) via FAA Form 8100-9. (2) For Group 1 airplanes identified in Boeing Alert Service Bulletin 737-53A1328, dated July 22, 2014: Window corner crack repairs terminate the inspection required by the introductory text of paragraph (g) of this AD in the repaired area only. The repair, including all applicable related investigative and corrective actions, must be done in accordance with Part 6 of the Accomplishment Instructions of Boeing Alert Service Bulletin 737- 53A1328, dated July 22, 2014, except as required by paragraphs (j)(2), (j)(3), (j)(4), and (j)(5) of this AD. (h) Preventive Modification Accomplishment of a preventive modification in the fastener locations in the window corners of the window belt area between STA 360 and STA 540 and between STA 727 and STA 908, left-side and right-side of the fuselage, at and between stringers S-11 and S-13, terminates the inspections required by paragraph (g) of this AD at the modified location only. The modification, including all applicable related investigative and corrective actions, must be done in accordance with Part 3 of the Accomplishment Instructions of Boeing Alert Service Bulletin 737-53A1328, dated July 22, 2014, except as required by paragraphs (j)(2), (j)(3), (j)(4), and (j)(5) of this AD. (i) Repetitive Inspections, Replacements, and Corrective Actions For airplanes having any condition identified in Table 4 or Table 5 of paragraph l.E., ``Compliance,'' of Boeing Alert Service Bulletin 737-53A1328, dated July 22, 2014: At the applicable times specified in Table 4 and Table 5 of paragraph l.E., ``Compliance,'' of Boeing Alert Service Bulletin 737-53A1328, dated July 22, 2014, do a window frame replacement or an internal detailed inspection for cracks of the window forging around the fastener collars, as applicable, and do all applicable corrective actions, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 737-53A1328, dated July 22, 2014, except as required by paragraphs (j)(2), (j)(3), (j)(4), and (j)(5) of this AD. Repeat the inspections at the applicable times specified in table 4 and table 5 of paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 737-53A1328, dated July 22, 2014. (j) Exceptions to the Service Information Specifications (1) Where Boeing Alert Service Bulletin 737-53A1328, dated July 22, 2014, specifies a compliance time ``after the original issue date of this service bulletin,'' this AD requires compliance within the specified compliance time after the effective date of this AD. (2) Where Boeing Alert Service Bulletin 737-53A1328, dated July 22, 2014, specifies to contact Boeing for repair instructions: Before further flight, repair the cracking using a method approved in accordance with the procedures specified in paragraph (l) of this AD. Although Boeing Alert Service Bulletin 737-53A1328, dated July 22, 2014, specifies to contact Boeing for repair instructions, and specifies that action as Required for Compliance (RC), this AD requires repair as specified in this paragraph. (3) Where note (e) of Figure 5 of Boeing Alert Service Bulletin 737-53A1328, dated July 22, 2014, specifies to ``Refer to Paragraph 3.B., Work Instructions, Table 2 for edge margin requirements,'' operators must comply with Table 3 of paragraph 3.B., ``Work Instructions,'' of Boeing Alert Service Bulletin 737-53A1328, dated July 22, 2014, for edge margin requirements. (4) Where the notes for fastener codes A and B in figures 9, 10, 11, and 12 of Boeing Alert Service Bulletin 737-53A1328, dated July 22, 2014, refer to ``Paragraph 3.B., Work Instructions, Table 2'' for edge margin requirements, operators must comply with Table 3 of paragraph 3.B., ``Work Instructions,'' of Boeing Alert Service Bulletin 737-53A1328, dated July 22, 2014, for edge margin requirements. (5) Where note (e) of figures 6, 7, and 8 and step 1.a.(1) of Part 5 of the Accomplishment Instructions of Boeing Alert Service Bulletin 737-53A1328, dated July 22, 2014, specifies to ``Refer to Paragraph 3.B., Work Instructions, Table 3 for edge margin requirements,'' operators must comply with Table 3 of paragraph 3.B., ``Work Instructions,'' of Boeing Alert Service Bulletin 737- 53A1328, dated July 22, 2014, for edge margin requirements. (k) Post-Repair Inspections/Post-Modification Inspections Table 3 and Table 8 of paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 737-53A1328, dated July 22, 2014, specify post-modification airworthiness limitation inspections in compliance to 14 CFR 25.571(a)(3) at the modified locations, which support compliance with 14 CFR 121.1109(c)(2) or 129.109(b)(2). As airworthiness limitations, these inspections are required by maintenance and operational rules. It is therefore unnecessary to mandate them in this AD. Deviations from these inspections require FAA approval, but do not require an alternative method of compliance. (l) 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 (m) 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) Except as required by paragraph (j)(2) of this AD: For service information that contains steps that are labeled as RC, the provisions of paragraphs (l)(3)(i) and (l)(3)(ii) of this AD apply. (i) The steps labeled as RC, including substeps under an RC step and any figures identified in an RC step, must be done to comply with this AD. An AMOC is required for any deviations to RC steps, including substeps and identified figures. (ii) Steps not labeled as RC may be deviated from using accepted methods in accordance with the operator's maintenance or inspection program without obtaining approval of an AMOC, provided the RC steps, including substeps and identified figures, can still be done as specified, and the airplane can be put back in an airworthy condition. (4) 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 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. [[Page 14716]] (m) Related Information For more information about this AD, contact Jennifer Tsakoumakis, Aerospace Engineer, Airframe Branch, ANM-120L, FAA, Los Angeles Aircraft Certification Office (ACO), 3960 Paramount Blvd., Lakewood, CA 90712-4137; phone: 562-627-5264; fax: 562-627-5210; email: [email protected]. (n) 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 Alert Service Bulletin 737-53A1328, dated July 22, 2014. (ii) Reserved. (3) For service information identified in this AD, contact Boeing Commercial Airplanes, Attention: Data & Services Management, P.O. Box 3707, MC 2H-65, Seattle, WA 98124-2207; telephone 206-544- 5000, extension 1; fax 206-766-5680; Internet https://www.myboeingfleet.com. (4) 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. (5) 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 March 7, 2016. Michael Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2016-05842 Filed 3-17-16; 8:45 am] BILLING CODE 4910-13-P
![Federal Register / Vol. 81, No. 53 / Friday, March 18, 2016 / Rules and Regulations 14711
(IBR) of the service information listed in this actions if necessary. This AD also Discussion
paragraph under 5 U.S.C. 552(a) and 1 CFR provides an optional preventive
part 51. We issued a notice of proposed
modification that terminates the rulemaking (NPRM) to amend 14 CFR
(2) You must use this service information
as applicable to do the actions required by
inspections at the modified location. We part 39 by adding an AD that would
this AD, unless the AD specifies otherwise. are issuing this AD to detect and correct apply to certain The Boeing Company
(i) Boeing Alert Service Bulletin 747– fatigue cracking around fastener Model 737–300, –400, and –500 series
53A2808, dated November 30, 2012. locations that could cause multiple airplanes. The NPRM published in the
(ii) Boeing Service Bulletin 747–53A2465, window corner skin cracks, which Federal Register on March 24, 2015 (80
Revision 5, dated July 11, 2013. could result in rapid decompression and FR 15523) (‘‘the NPRM’’). The NPRM
(iii) Boeing Service Bulletin 747–53A2562, loss of structural integrity of the
Revision 3, dated July 11, 2013.
was prompted by reports of cracking at
airplane. certain fastener locations in the window
(3) For Boeing service information
identified in this AD, contact Boeing corners of the window belt area. The
DATES: This AD is effective April 22, NPRM proposed to require repetitive
Commercial Airplanes, Attention: Data &
Services Management, P.O. Box 3707, MC
2016. HFEC inspections for fatigue cracking in
2H–65, Seattle, WA 98124–2207; telephone The Director of the Federal Register certain fastener locations in the window
206–544–5000, extension 1; fax 206–766– approved the incorporation by reference corners of the window belt area, and
5680; Internet https:// of a certain publication listed in this AD related investigative and corrective
www.myboeingfleet.com. as of April 22, 2016. actions if necessary. We are issuing this
(4) You may view this service information
at the FAA, Transport Airplane Directorate,
AD to detect and correct fatigue
ADDRESSES: For service information
1601 Lind Avenue SW., Renton, WA. For cracking around fastener locations that
identified in this final rule, contact
information on the availability of this could cause multiple window corner
Boeing Commercial Airplanes,
material at the FAA, call 425–227–1221. skin cracks, which could result in rapid
Attention: Data & Services Management,
(5) You may view this service information decompression and loss of structural
that is incorporated by reference at the P.O. Box 3707, MC 2H–65, Seattle, WA integrity of the airplane.
National Archives and Records 98124–2207; telephone 206–544–5000,
Administration (NARA). For information on extension 1; fax 206–766–5680; Internet Comments
the availability of this material at NARA, call https://www.myboeingfleet.com. You We gave the public the opportunity to
202–741–6030, or go to: http:// may view this referenced service participate in developing this AD. The
www.archives.gov/federal-register/cfr/ibr- information at the FAA, Transport following presents the comments
locations.html. Airplane Directorate, 1601 Lind Avenue received on the NPRM and the FAA’s
Issued in Renton, Washington, on March 9, SW., Renton, WA. For information on response to each comment.
2016. the availability of this material at the
Michael Kaszycki, FAA, call 425–227–1221. It is also Request for Clarification of Location of
Acting Manager, Transport Airplane available on the Internet at http:// the Twelve Fastener Inspections
Directorate, Aircraft Certification Service. www.regulations.gov by searching for Southwest Airlines (SWA) requested
[FR Doc. 2016–06001 Filed 3–17–16; 8:45 am] and locating Docket No. FAA–2015– that a correction be made to paragraph
BILLING CODE 4910–13–P 0495. (g) of the proposed AD to clarify the
areas for the inspection of the twelve
Examining the AD Docket fastener locations. SWA noted that
DEPARTMENT OF TRANSPORTATION You may examine the AD docket on paragraph (g) of the proposed AD stated
the Internet at http:// to inspect locations ‘‘at the upper
Federal Aviation Administration forward and lower aft corners of each
www.regulations.gov by searching for
and locating Docket No. FAA–2015– window between station (STA) 360 and
14 CFR Part 39 STA 540 and between STA 727 and
0495; or in person at the Docket
[Docket No. FAA–2015–0495; Directorate Management Facility between 9 a.m. STA 908.’’ SWA stated that between
Identifier 2014–NM–172–AD; Amendment and 5 p.m., Monday through Friday, STA 727 and STA 908, Boeing Alert
39–18435; AD 2016–06–04] except Federal holidays. The AD docket Service Bulletin 737–53A1328, dated
contains this AD, the regulatory July 22, 2014, specifies the location as
RIN 2120–AA64 the lower forward and upper aft corners.
evaluation, any comments received, and
We agree with the commenter for the
Airworthiness Directives; The Boeing other information. The address for the
reason provided. We have revised
Company Airplanes Docket Office (phone: 800–647–5527) is
paragraph (g) of this AD to require an
Docket Management Facility, U.S. inspection of the twelve fastener
AGENCY: Federal Aviation
Department of Transportation, Docket locations at the upper forward and
Administration (FAA), DOT.
Operations, M–30, West Building lower aft corners of each window
ACTION: Final rule.
Ground Floor, Room W12–140, 1200 between STA 360 and STA 540 and at
SUMMARY: We are adopting a new New Jersey Avenue SE., Washington, the upper aft and lower forward corners
airworthiness directive (AD) for certain DC 20590. of each window between STA 727 and
The Boeing Company Model 737–300, FOR FURTHER INFORMATION CONTACT: STA 908.
–400, and –500 series airplanes. This Jennifer Tsakoumakis, Aerospace
AD was prompted by reports of cracking Request for Clarification of the Intent of
Engineer, Airframe Branch, ANM–120L,
asabaliauskas on DSK3SPTVN1PROD with RULES
at certain fastener locations in the the Inspection Requirements in
FAA, Los Angeles Aircraft Certification Paragraph (g) of the Proposed AD
window corners of the window belt Office (ACO), 3960 Paramount
area. This AD requires repetitive high Boulevard, Lakewood, CA 90712–4137; SWA requested that we clarify the
frequency eddy current (HFEC) phone: 562–627–5264; fax: 562–627– intent of paragraph (g) of the proposed
inspections for fatigue cracking in 5210; email: jennifer.tsakoumakis@ AD. SWA stated that paragraph (g) of
certain fastener locations in the window faa.gov. the proposed AD states to accomplish
corners of the window belt area, and the inspections at the times specified in
related investigative and corrective SUPPLEMENTARY INFORMATION: tables 1 and 2 of paragraph 1.E.,
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![14714 Federal Register / Vol. 81, No. 53 / Friday, March 18, 2016 / Rules and Regulations
fatigue cracking in certain fastener available because the interested parties Costs of Compliance
locations in the window corners of the have access to it through their normal We estimate that this AD affects 142
window belt area, and related course of business or by the means airplanes of U.S. registry.
investigative and corrective actions. identified in the ADDRESSES section. We estimate the following costs to
This service information is reasonably comply with this AD:
ESTIMATED COSTS: REQUIRED ACTIONS
Action Labor cost Parts cost Cost per product Cost on U.S. operators
Inspection ......... Up to 2,312 work-hours × $85 per $0 Up to $196,520 per inspection Up to $27,905,840 per inspection
hour = $196,520 per inspection cycle. cycle.
cycle.
ESTIMATED COSTS: REQUIRED ACTIONS
Cost per
Action Labor cost Parts cost product
Preventive modification ................................................ 108 work-hours × $85 per hour = $9,180 .................... $0 $9,180
We estimate the following costs to do required based on the results of the determining the number of aircraft that
any necessary repairs that would be inspection. We have no way of might need repairs:
ON-CONDITION COSTS
Action Labor cost Parts cost Cost per product
Repair ............... Up to 18 work-hours × $85 per hour = $1,530 per repair .................................. $0 Up to $1,530 per repair.
Authority for This Rulemaking For the reasons discussed above, I 2016–06–04 The Boeing Company:
certify that this AD: Amendment 39–18435 ; Docket No.
Title 49 of the United States Code (1) Is not a ‘‘significant regulatory FAA–2015–0495; Directorate Identifier
specifies the FAA’s authority to issue action’’ under Executive Order 12866, 2014–NM–172–AD.
rules on aviation safety. Subtitle I, (2) Is not a ‘‘significant rule’’ under (a) Effective Date
section 106, describes the authority of DOT Regulatory Policies and Procedures This AD is effective April 22, 2016.
the FAA Administrator. Subtitle VII: (44 FR 11034, February 26, 1979),
Aviation Programs, describes in more (3) Will not affect intrastate aviation (b) Affected ADs
detail the scope of the Agency’s in Alaska, and None.
authority. (4) Will not have a significant (c) Applicability
We are issuing this rulemaking under economic impact, positive or negative,
(1) This AD applies to The Boeing
the authority described in Subtitle VII, on a substantial number of small entities Company Model 737–300, –400, and –500
Part A, Subpart III, Section 44701: under the criteria of the Regulatory series airplanes, certificated in any category,
‘‘General requirements.’’ Under that Flexibility Act. as identified in Boeing Alert Service Bulletin
section, Congress charges the FAA with List of Subjects in 14 CFR Part 39 737–53A1328, dated July 22, 2014.
promoting safe flight of civil aircraft in (2) Installation of Supplemental Type
air commerce by prescribing regulations Air transportation, Aircraft, Aviation Certificate (STC) ST01219SE (http://
for practices, methods, and procedures safety, Incorporation by reference, rgl.faa.gov/Regulatory_and_Guidance_
Safety. Library/rgstc.nsf/0/
the Administrator finds necessary for be866b732f6cf31086257b9700692796/$FILE/
safety in air commerce. This regulation Adoption of the Amendment ST01219SE.pdf) does not affect the ability to
is within the scope of that authority accomplish the actions required by this AD.
because it addresses an unsafe condition Accordingly, under the authority
Therefore, for airplanes on which STC
that is likely to exist or develop on delegated to me by the Administrator, ST01219SE is installed, a ’’change in
products identified in this rulemaking the FAA amends 14 CFR part 39 as product’’ alternative method of compliance
action. follows: (AMOC) approval request is not necessary to
comply with the requirements of 14 CFR
Regulatory Findings PART 39—AIRWORTHINESS 39.17.
DIRECTIVES
This AD will not have federalism (d) Subject
asabaliauskas on DSK3SPTVN1PROD with RULES
implications under Executive Order ■ 1. The authority citation for part 39 Air Transport Association (ATA) of
13132. This AD will not have a continues to read as follows: America Code 53, Fuselage.
substantial direct effect on the States, on Authority: 49 U.S.C. 106(g), 40113, 44701. (e) Unsafe Condition
the relationship between the national This AD was prompted by reports of
government and the States, or on the § 39.13 [Amended]
fatigue cracking at certain fastener locations
distribution of power and ■ 2. The FAA amends § 39.13 by adding in the window corners of the window belt
responsibilities among the various the following new airworthiness area. We are issuing this AD to detect and
levels of government. directive (AD): correct fatigue cracking around the fastener
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![14716 Federal Register / Vol. 81, No. 53 / Friday, March 18, 2016 / Rules and Regulations
(m) Related Information countries for the benefits of the African section 502 of the Trade Act of 1974. It
For more information about this AD, Growth and Opportunity Act (AGOA). requires that a petition adequately
contact Jennifer Tsakoumakis, Aerospace This authority has been delegated to the identify the country and the concern. A
Engineer, Airframe Branch, ANM–120L, Office of the United States Trade petition indicating the existence of
FAA, Los Angeles Aircraft Certification Representative (USTR). exceptional circumstances warranting
Office (ACO), 3960 Paramount Blvd., an out-of-cycle review must contain a
DATES: The interim final rule is effective
Lakewood, CA 90712–4137; phone: 562–627– statement of reasons explaining why an
5264; fax: 562–627–5210; email: on March 18, 2016. USTR will accept
jennifer.tsakoumakis@faa.gov. comments on the interim final rule in out-of-cycle review is warranted.
writing on or before April 18, 2016. Section 2017.2 explains how USTR
(n) Material Incorporated by Reference will process petitions. USTR will
ADDRESSES: All comments must be
(1) The Director of the Federal Register consider petitions filed in accordance
submitted electronically at
approved the incorporation by reference with the public comment period of the
(IBR) of the service information listed in this www.regulations.gov, docket number
annual (normal cycle) review of all
paragraph under 5 U.S.C. 552(a) and 1 CFR USTR–2016–0002.
beneficiary countries in conjunction
part 51. FOR FURTHER INFORMATION CONTACT: For with that review. USTR will consider
(2) You must use this service information procedural questions, please contact petitions filed outside of that time frame
as applicable to do the actions required by Yvonne Jamison, Trade Policy Staff
this AD, unless the AD specifies otherwise. in the next (normal cycle) annual
Committee, at 202–395–3475. Direct all review. If USTR receives a petition
(i) Boeing Alert Service Bulletin 737–
other questions to Constance Hamilton, outside of the annual (normal cycle)
53A1328, dated July 22, 2014.
(ii) Reserved. Deputy Assistant U.S. Trade review process that indicates the
(3) For service information identified in Representative for African Affairs, at existence of exceptional circumstances,
this AD, contact Boeing Commercial Constance_Hamilton@ustr.eop.gov or the AGOA Implementation
Airplanes, Attention: Data & Services 202–395–9514. Subcommittee will consider whether
Management, P.O. Box 3707, MC 2H–65, SUPPLEMENTARY INFORMATION: there is a basis for the initiation of an
Seattle, WA 98124–2207; telephone 206– out-of-cycle review and make
544–5000, extension 1; fax 206–766–5680; I. Background
recommendations to the Trade Policy
Internet https://www.myboeingfleet.com. The AGOA (Title I of the Trade and
(4) You may view this service information Staff Committee, which will, in turn,
Development Act of 2000, Pub. L. 106– advise the U.S. Trade Representative. If
at the FAA, Transport Airplane Directorate,
1601 Lind Avenue SW., Renton, WA. For 200) (19 U.S.C. 2466a et seq.), as the U.S. Trade Representative finds that
information on the availability of this amended, contains provisions for there are exceptional circumstances
material at the FAA, call 425–227–1221. enhanced trade benefits for eligible sub- warranting an out-of-cycle review,
(5) You may view this service information Saharan African countries. within 30 days of that determination
that is incorporated by reference at the Section 506(c) of the TPEA, which USTR will announce a schedule for the
National Archives and Records was signed into law on June 29, 2015 review in the Federal Register.
Administration (NARA). For information on (Pub. L. 114–27, sec. 105(d)(3), 129 Stat. Section 2017.3 requires USTR to
the availability of this material at NARA, call 366–367)), requires the President to publish a summary of the actions taken
202–741–6030, or go to: http:// establish a process to allow any
www.archives.gov/federal-register/cfr/ibr- in response to petitions in the Federal
locations.html.
interested person, at any time, to file a Register. The notice also will include a
petition with USTR concerning the list of pending petitions upon which no
Issued in Renton, Washington, on March 7, compliance of any sub-Saharan African decision has been made.
2016. country listed in section 107 of the Section 2017.4 provides that all
Michael Kaszycki, AGOA (19 U.S.C. 3706), with the submitted materials will be made
Acting Manager, Transport Airplane eligibility requirements set forth in available for public inspection at
Directorate, Aircraft Certification Service. section 104 of the AGOA (19 U.S.C. www.regulations.gov other than
[FR Doc. 2016–05842 Filed 3–17–16; 8:45 am] 3703) and the eligibility criteria set forth appropriately designated confidential
BILLING CODE 4910–13–P in section 502 of the Trade Act of 1974 business information.
(19 U.S.C. 2462). On February 26, 2016, The TPEA extended the AGOA until
the President delegated this authority to September 30, 2025. See Pub. L. 114–27,
OFFICE OF THE UNITED STATES USTR. See E.O. 13720 of Feb. 26, 2016, sec. 103, 129 Stat. 364, June 29, 2015.
TRADE REPRESENTATIVE 81 FR 11087, Mar. 2, 2016. Section 2017.5 provides that the AGOA
petition process will expire on that date
15 CFR Part 2017 II. Analysis of the Interim Final Rule
unless extended by statute.
[Docket Number USTR–2016–0002] The interim final rule adds 15 CFR
part 2017. The new Part 2017 III. Requirements for Submission
RIN 0350–AA07 establishes a petition process that All submissions must be in English
supplements the annual (normal cycle) and must be submitted electronically
Establishment of a Petition Process To request for public comments on whether via http://www.regulations.gov. USTR
Review the Eligibility of Countries a beneficiary sub-Saharan African will not accept hand-delivered
Under the African Growth and country is meeting the eligibility criteria submissions. To make a submission
Opportunity Act (AGOA) and requirements of the AGOA program using http://www.regulations.gov, enter
AGENCY: Office of the United States (see, e.g., 80 FR 48951, Aug. 14, 2015). the docket number USTR–2016–0002 in
asabaliauskas on DSK3SPTVN1PROD with RULES
Trade Representative. Section 2017.0 defines acronyms used the ‘‘Search for’’ field on the home page
ACTION: Interim final rule with request throughout Part 2017. and click ‘‘Search.’’ The site will
for comments. Section 2017.1 permits any interested provide a search-results page listing all
party to submit a petition, at any time, documents associated with this docket.
SUMMARY: The Trade Preferences regarding whether a beneficiary sub- Find a reference to this notice by
Extension Act of 2015 (TPEA) requires Saharan African country meets the selecting ‘‘Notice’’ under ‘‘Document
the President to establish a petition eligibility requirements in section 104 of Type’’ in the ‘‘Filter Results by’’ section
process to review the eligibility of the AGOA and the eligibility criteria in on the left side of the screen and click
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Document Created: 2018-02-02 15:13:42
Document Modified: 2018-02-02 15:13:42
| 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 April 22, 2016. | |
| Contact | Jennifer Tsakoumakis, Aerospace Engineer, Airframe Branch, ANM-120L, FAA, Los Angeles Aircraft Certification Office (ACO), 3960 Paramount Boulevard, Lakewood, CA 90712-4137; phone: 562-627-5264; fax: 562-627-5210; email: [email protected] | |
| FR Citation | 81 FR 14711 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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