81 FR 25357 - Airworthiness Directives; The Boeing Company Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 81, Issue 82 (April 28, 2016)
Federal Aviation Administration
Federal Register Volume 81, Issue 82 (April 28, 2016)
| Page Range | 25357-25360 | |
| FR Document | 2016-09647 |
[Federal Register Volume 81, Number 82 (Thursday, April 28, 2016)] [Proposed Rules] [Pages 25357-25360] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2016-09647] ======================================================================== Proposed Rules Federal Register ________________________________________________________________________ This section of the FEDERAL REGISTER contains notices to the public of the proposed issuance of rules and regulations. The purpose of these notices is to give interested persons an opportunity to participate in the rule making prior to the adoption of the final rules. ======================================================================== Federal Register / Vol. 81, No. 82 / Thursday, April 28, 2016 / Proposed Rules [[Page 25357]] DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2016-5598; Directorate Identifier 2016-NM-001-AD] RIN 2120-AA64 Airworthiness Directives; The Boeing Company Airplanes AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). ----------------------------------------------------------------------- SUMMARY: We propose to supersede Airworthiness Directive (AD) 2012-22- 02, which applies to certain The Boeing Company Model 747-400, -400D, and -400F series airplanes. AD 2012-22-02 currently requires measuring the web at station (STA) 320 and, depending on findings, various inspections for cracks and missing fasteners, web and fastener replacement, and related investigative and corrective actions if necessary. Since we issued AD 2012-22-02, it was determined that there were no inspection or repair procedures included for airplanes with a STA 320 crown frame web thickness less than 0.078 inch, or greater than or equal to 0.084 inch and less than or equal to 0.135 inch. This proposed AD would require, for certain airplanes, replacement of the web, including related investigative and corrective actions if necessary. We are issuing this AD to prevent complete fracture of the crown frame assembly, and consequent damage to the skin. Such damage could result in in-flight decompression of the airplane. DATES: We must receive comments on this proposed AD by June 13, 2016. ADDRESSES: You may send comments, using the procedures found in 14 CFR 11.43 and 11.45, by any of the following methods:Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments. Fax: 202-493-2251. Mail: U.S. Department of Transportation, Docket Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue SE., Washington, DC 20590. Hand Delivery: Deliver to Mail address above between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For service information identified in this NPRM, 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-2016-5598. 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-2016- 5598; or in person at the Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this proposed AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Office (phone: 800-647-5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: Bill Ashforth, Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office (ACO), 1601 Lind Avenue SW., Renton, WA 98057-3356; phone: 425-917- 6432; fax: 425-917-6590; email: [email protected]. SUPPLEMENTARY INFORMATION: Comments Invited We invite you to send any written relevant data, views, or arguments about this proposed AD. Send your comments to an address listed under the ADDRESSES section. Include ``Docket No. FAA-2016-5598; Directorate Identifier 2016-NM-001-AD'' at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this proposed AD. We will consider all comments received by the closing date and may amend this proposed AD because of those comments. We will post all comments we receive, without change, to http://www.regulations.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact we receive about this proposed AD. Discussion On October 19, 2012, we issued AD 2012-22-02, Amendment 39-17238 (77 FR 69739, November 21, 2012) (``AD 2012-22-02''), for certain The Boeing Company Model 747-400, -400D, and -400F series airplanes. AD 2012-22-02 requires measuring the web at STA 320 and, depending on findings, various inspections for cracks and missing fasteners, web and fastener replacement, and related investigative and corrective actions if necessary. AD 2012-22-02 resulted from reports of crown frame web cracking at left buttock line (LBL) 15.0, STA 320. We issued AD 2012- 22-02 to prevent complete fracture of the crown frame assembly, and consequent damage to the skin and in-flight decompression of the airplane. Actions Since AD 2012-22-02 Was Issued Since we issued AD 2012-22-02, it was determined that there was no work included for airplanes with a STA 320 crown frame web thickness less than 0.078 inch, or greater than or equal to 0.084 inch and less than or equal to 0.135 inch. Related Service Information Under 1 CFR Part 51 We reviewed Boeing Alert Service Bulletin 747-53A2784, Revision 2, dated August 20, 2015. The service information describes procedures for various inspections for cracks and missing fasteners, web and fastener replacement, and related investigative and corrective actions, if necessary. 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. [[Page 25358]] FAA's Determination We are proposing this AD because we evaluated all the relevant information and determined the unsafe condition described previously is likely to exist or develop in other products of the same type design. Proposed AD Requirements Although this proposed AD does not explicitly restate the requirements of AD 2012-22-02, this proposed AD would retain certain requirements of AD 2012-22-02. Those requirements are referenced in the service information identified previously, which, in turn, is referenced in paragraphs (h), (i), and (k) of this proposed AD. This proposed AD would require accomplishing the actions specified in the service information described previously, except as discussed under ``Differences Between the Proposed AD and the Service Information.'' For information on the procedures and compliance times, see this service information at http://www.regulations.gov by searching for and locating Docket No. FAA-2016-5598. The phrase ``related investigative actions'' is used in this proposed AD. Related investigative actions are follow-on actions that (1) are related to the primary action, and (2) further investigate the nature of any condition found. Related investigative actions in an AD could include, for example, inspections. The phrase ``corrective actions'' is used in this proposed AD. Corrective actions correct or address any condition found. Corrective actions in an AD could include, for example, repairs. Differences Between This Proposed AD and the Service Information For Boeing Alert Service Bulletin 747-53A2784, Revision 2, dated August 20, 2015, Table 4: STA 320 Post Web Replacement Inspection of paragraph 1.E., ``Compliance,'' the conditional action statement does not include airplanes that were inspected or repaired in accordance with Part 8 of the Work Instructions. The statement should read: ``All airplanes that have done the STA 320 crown frame web replacement in accordance with paragraph 3.B. WORK INSTRUCTIONS, PARTS 5 OR PART 8.'' Paragraph (k) of this proposed AD applies to all airplanes on which a web replacement is done as required by paragraphs (h), (i), and (j) of the proposed AD, e.g., the replacement is done as specified in Part 5 or Part 8 of paragraph 3.B., ``Work Instructions,'' of the service information. Costs of Compliance We estimate that this proposed AD affects 29 airplanes. We estimate the following costs to comply with this proposed AD: Estimated Costs -------------------------------------------------------------------------------------------------------------------------------------------------------- Action Labor cost Parts cost Cost per product Cost on U.S. operators -------------------------------------------------------------------------------------------------------------------------------------------------------- Measurement, inspection, and web 219 work-hours x $85 Up to $21,887........ Up to $40,502 per $Up to 1,174,558. replacement. [retained actions per hour = $18,615. inspection and from AD 2012[dash]22[dash]02]. replacement. Post-replacement inspection 135 work-hours x $85 $0................... $11,475 per $332,775 per inspection cycle. [retained actions from AD per hour = $11,475 inspection cycle. 2012[dash]22[dash]02]. per inspection cycle. -------------------------------------------------------------------------------------------------------------------------------------------------------- Authority for This Rulemaking Title 49 of the United States Code specifies the FAA's authority to issue rules on aviation safety. Subtitle I, Section 106, describes the authority of the FAA Administrator. Subtitle VII, Aviation Programs, describes in more detail the scope of the Agency's authority. We are issuing this rulemaking under the authority described in Subtitle VII, Part A, Subpart III, Section 44701, ``General requirements.'' Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action. Regulatory Findings We have determined that this proposed AD would not have federalism implications under Executive Order 13132. This proposed AD would not have a substantial direct effect on the States, on the relationship between the national Government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify that the proposed regulation: (1) Is not a ``significant regulatory action'' under Executive Order 12866, (2) Is not a ``significant rule'' under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979), (3) Will not affect intrastate aviation in Alaska and, (4) Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. The Proposed Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 14 CFR part 39 as follows: PART 39--AIRWORTHINESS DIRECTIVES 0 1. The authority citation for part 39 continues to read as follows: Authority: 49 U.S.C. 106(g), 40113, 44701. Sec. 39.13 [Amended] 0 2. The FAA amends Sec. 39.13 by removing Airworthiness Directive (AD) 2012-22-02, Amendment 39-17238 (77 FR 69739 November 21, 2012), and adding the following new AD: The Boeing Company: Docket No. FAA-2016-5598; Directorate Identifier 2016-NM-001-AD. (a) Comments Due Date The FAA must receive comments on this AD action by June 13, 2016. (b) Affected ADs This AD replaces AD 2012-22-02, Amendment 39-17238 (77 FR 69739, November 21, 2012) (``AD 2012-22-02''). [[Page 25359]] (c) Applicability This AD applies to The Boeing Company Model 747-400, -400D, and -400F series airplanes, certificated in any category, as specified in Boeing Alert Service Bulletin 747-53A2784, Revision 2, dated August 20, 2015. (d) Subject Air Transport Association (ATA) of America Code 53, Fuselage. (e) Unsafe Condition This AD was prompted by reports of crown frame web cracking at left buttock line (LBL) 15.0, station (STA) 320 and a determination that there were no inspection or repair procedures included in AD 2012-22-02 for airplanes with a STA 320 crown frame web thickness less than 0.078 inch, or greater than or equal to 0.084 inch and less than or equal to 0.135 inch. We are issuing this AD to prevent complete fracture of the crown frame assembly, and consequent damage to the skin. Such damage could result in in-flight decompression of the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Crown Frame Web Measurement for Certain Airplanes For Group 1, Configuration 3 airplanes identified in Boeing Alert Service Bulletin 747-53A2784, Revision 2, dated August 20, 2015: At the compliance time specified in Table 1 of paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 747-53A2784, Revision 2, dated August 20, 2015, measure the thickness of the crown frame web at STA 320, and do all applicable related investigative and corrective actions, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 747- 53A2784, Revision 2, dated August 20, 2015, except as required by paragraph (l)(2) of this AD. Do all related investigative and corrective actions at the applicable times specified in Table 2 and Table 3 of paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 747-53A2784, Revision 2, dated August 20, 2015. (h) Inspections (Web With No Repair Doubler) and Related Investigative and Corrective Actions (Including Web Replacement) For Group 1, Configuration 1 airplanes identified in Boeing Alert Service Bulletin 747-53A2784, Revision 2, dated August 20, 2015: For airplanes with a web thickness less than 0.136 inch and no repair doubler installed on the web, at the time specified in Table 2 of paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 747-53A2784, Revision 2, dated August 20, 2015, do a detailed inspection for cracks and a general visual inspection for missing fasteners of the crown frame web at STA 320; and do all applicable related investigative and corrective actions; in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 747-53A2784, Revision 2, dated August 20, 2015, except as specified in paragraph (l)(2) of this AD. Do the applicable related investigative and corrective actions at the applicable times specified in paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 747-53A2784, Revision 2, dated August 20, 2015. (i) Inspection (Web With Repair Doubler) and Related Investigative and Corrective Actions (Including Web Replacement) For Group 1, Configuration 1 airplanes identified in Boeing Alert Service Bulletin 747-53A2784, Revision 2, dated August 20, 2015: For airplanes with a web thickness less than 0.136 inch and a repair doubler installed on the web, at the time specified in Table 3 of paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 747-53A2784, Revision 2, dated August 20, 2015, do a detailed inspection for any crack in the upper chord and lower chord of the STA 320 crown frame; and do all applicable related investigative and corrective actions; in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 747- 53A2784, Revision 2, dated August 20, 2015, except as specified in paragraph (l)(2) of this AD. Do the applicable related investigative and corrective actions at the applicable times specified in paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 747-53A2784, Revision 2, dated August 20, 2015. At the applicable compliance time specified in paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 747-53A2784, Revision 2, dated August 20, 2015, except as provided by paragraph (l)(1) of this AD, do the actions specified in paragraphs (i)(1) and (i)(2) of this AD, and do all applicable corrective actions, in accordance with the Accomplishment Instructions of Boeing Service Bulletin 747-53A2784, Revision 2, dated August 20, 2015, except as required by paragraph (l)(2) of this AD. Do all applicable corrective actions before further flight. (1) Replace the web with a new web and do all applicable related investigative actions. (2) Do a detailed inspection for cracks in the upper or lower chord of the crown frame web at STA 320. (j) Web Replacement for Certain Airplanes For Group 1, Configuration 2 airplanes identified in Boeing Alert Service Bulletin 747-53A2784, Revision 2, dated August 20, 2015: At the applicable time specified in Table 5 of paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 747-53A2784, Revision 2, dated August 20, 2015, except as provided by paragraph (l)(1) of this AD, replace the web, including doing related investigative and corrective actions, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 747- 53A2784, Revision 2, dated August 20, 2015, except as required by paragraph (l)(2) of this AD. Do all applicable related investigative and corrective actions before further flight. (k) Post-Replacement Repetitive Inspections of Replaced Web Following any web replacement required by this AD, at the time specified in paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 747-53A2784, Revision 2, dated August 20, 2015: Do a detailed inspection for cracks of the web, upper chord, lower chord, and lower chord splice, and do all applicable corrective actions, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 747-53A2784, Revision 2, dated August 20, 2015, except as required by paragraph (l)(2) of this AD. Do all applicable corrective actions before further flight. If no crack is found, repeat the inspection thereafter at the intervals specified in paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 747-53A2784, Revision 2, dated August 20, 2015. Accomplishment of the inspections required by AD 2009-19-05, Amendment 39-16022 (74 FR 48138, September 22, 2009), terminates the requirements of this paragraph. (l) Exceptions to the Service Information With Updated Service Information (1) Where Boeing Alert Service Bulletin 747-53A2784, Revision 2, dated August 20, 2015, specifies a compliance time ``after the Revision 2 date of the service bulletin,'' this AD requires compliance within the specified compliance time after the effective date of this AD. (2) Where Boeing Alert Service Bulletin 747-53A2784, Revision 2, dated August 20, 2015, specifies to contact Boeing for appropriate action, accomplish applicable actions before further flight using a method approved in accordance with the procedures specified in paragraph (n) of this AD. (m) Credit for Previous Actions (1) This paragraph provides credit for the actions required by paragraphs (h), (i), and (k) of this AD, if those actions were performed before December 26, 2012 (the effective date of AD 2012- 22-02), using Boeing Service Bulletin 747-53A2784, dated August 27, 2009, which is not incorporated by reference in this AD. (2) This paragraph provides credit for the actions required by paragraphs (h), (i), and (k) of this AD, if those actions were performed before the effective date of this AD using Boeing Service Bulletin 747-53A2784, Revision 1, dated September 14, 2011. (n) Alternative Methods of Compliance (AMOCs) (1) The Manager, Seattle 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 (o) of this AD. (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 [[Page 25360]] Designation Authorization (ODA) that has been authorized by the Manager, Seattle ACO, to make those findings. To be approved, the repair method, modification deviation, or alteration deviation must meet the certification basis of the airplane, and the approval must specifically refer to this AD. (o) Related Information (1) For more information about this AD, contact Bill Ashforth, Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office (ACO), 1601 Lind Avenue SW., Renton, WA 98057- 3356; phone: 425-917-6432; fax: 425-91-6590; email: [email protected]. (2) For service information identified in this AD, contact Boeing Commercial Airplanes, Attention: Data & Services Management, P.O. Box 3707, MC 2H-65, Seattle, WA 98124-2207; telephone 206-544- 5000, extension 1; fax 206-766-5680; Internet https://www.myboeingfleet.com. You may view this service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425-227-1221. Issued in Renton, Washington, on April 15, 2016. Victor Wicklund, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2016-09647 Filed 4-27-16; 8:45 am] BILLING CODE 4910-13-P
![25357
Proposed Rules Federal Register
Vol. 81, No. 82
Thursday, April 28, 2016
This section of the FEDERAL REGISTER • Fax: 202–493–2251. 2016–NM–001–AD’’ at the beginning of
contains notices to the public of the proposed • Mail: U.S. Department of your comments. We specifically invite
issuance of rules and regulations. The Transportation, Docket Operations, M– comments on the overall regulatory,
purpose of these notices is to give interested 30, West Building Ground Floor, Room economic, environmental, and energy
persons an opportunity to participate in the W12–140, 1200 New Jersey Avenue SE., aspects of this proposed AD. We will
rule making prior to the adoption of the final
Washington, DC 20590. consider all comments received by the
rules.
• Hand Delivery: Deliver to Mail closing date and may amend this
address above between 9 a.m. and 5 proposed AD because of those
DEPARTMENT OF TRANSPORTATION p.m., Monday through Friday, except comments.
Federal holidays. We will post all comments we
Federal Aviation Administration For service information identified in receive, without change, to http://
this NPRM, contact Boeing Commercial www.regulations.gov, including any
14 CFR Part 39 Airplanes, Attention: Data & Services personal information you provide. We
Management, P.O. Box 3707, MC 2H–65, will also post a report summarizing each
[Docket No. FAA–2016–5598; Directorate substantive verbal contact we receive
Identifier 2016–NM–001–AD]
Seattle, WA 98124–2207; telephone
206–544–5000, extension 1; fax 206– about this proposed AD.
RIN 2120–AA64 766–5680; Internet https:// Discussion
www.myboeingfleet.com. You may view
Airworthiness Directives; The Boeing this referenced service information at On October 19, 2012, we issued AD
Company Airplanes the FAA, Transport Airplane 2012–22–02, Amendment 39–17238 (77
Directorate, 1601 Lind Avenue SW., FR 69739, November 21, 2012) (‘‘AD
AGENCY: Federal Aviation
Renton, WA. For information on the 2012–22–02’’), for certain The Boeing
Administration (FAA), DOT.
availability of this material at the FAA, Company Model 747–400, –400D, and
ACTION: Notice of proposed rulemaking –400F series airplanes. AD 2012–22–02
(NPRM). call 425–227–1221. It is also available
on the internet at http:// requires measuring the web at STA 320
SUMMARY: We propose to supersede www.regulations.gov by searching for and, depending on findings, various
Airworthiness Directive (AD) 2012–22– and locating Docket No. FAA–2016– inspections for cracks and missing
02, which applies to certain The Boeing 5598. fasteners, web and fastener replacement,
Company Model 747–400, –400D, and and related investigative and corrective
–400F series airplanes. AD 2012–22–02 Examining the AD Docket actions if necessary. AD 2012–22–02
currently requires measuring the web at You may examine the AD docket on resulted from reports of crown frame
station (STA) 320 and, depending on the Internet at http:// web cracking at left buttock line (LBL)
findings, various inspections for cracks www.regulations.gov by searching for 15.0, STA 320. We issued AD 2012–22–
and missing fasteners, web and fastener and locating Docket No. FAA–2016– 02 to prevent complete fracture of the
replacement, and related investigative 5598; or in person at the Docket crown frame assembly, and consequent
and corrective actions if necessary. Management Facility between 9 a.m. damage to the skin and in-flight
Since we issued AD 2012–22–02, it was and 5 p.m., Monday through Friday, decompression of the airplane.
determined that there were no except Federal holidays. The AD docket Actions Since AD 2012–22–02 Was
inspection or repair procedures contains this proposed AD, the Issued
included for airplanes with a STA 320 regulatory evaluation, any comments Since we issued AD 2012–22–02, it
crown frame web thickness less than received, and other information. The was determined that there was no work
0.078 inch, or greater than or equal to street address for the Docket Office included for airplanes with a STA 320
0.084 inch and less than or equal to (phone: 800–647–5527) is in the crown frame web thickness less than
0.135 inch. This proposed AD would ADDRESSES section. Comments will be
0.078 inch, or greater than or equal to
require, for certain airplanes, available in the AD docket shortly after 0.084 inch and less than or equal to
replacement of the web, including receipt. 0.135 inch.
related investigative and corrective FOR FURTHER INFORMATION CONTACT: Bill
actions if necessary. We are issuing this Ashforth, Aerospace Engineer, Airframe Related Service Information Under 1
AD to prevent complete fracture of the Branch, ANM–120S, FAA, Seattle CFR Part 51
crown frame assembly, and consequent Aircraft Certification Office (ACO), 1601 We reviewed Boeing Alert Service
damage to the skin. Such damage could Lind Avenue SW., Renton, WA 98057– Bulletin 747–53A2784, Revision 2,
result in in-flight decompression of the 3356; phone: 425–917–6432; fax: 425– dated August 20, 2015. The service
airplane. 917–6590; email: Bill.Ashforth@faa.gov. information describes procedures for
DATES: We must receive comments on various inspections for cracks and
mstockstill on DSK5VPTVN1PROD with PROPOSALS
SUPPLEMENTARY INFORMATION:
this proposed AD by June 13, 2016. missing fasteners, web and fastener
Comments Invited replacement, and related investigative
ADDRESSES: You may send comments,
using the procedures found in 14 CFR We invite you to send any written and corrective actions, if necessary. This
11.43 and 11.45, by any of the following relevant data, views, or arguments about service information is reasonably
methods: this proposed AD. Send your comments available because the interested parties
• Federal eRulemaking Portal: Go to to an address listed under the have access to it through their normal
http://www.regulations.gov. Follow the ADDRESSES section. Include ‘‘Docket No. course of business or by the means
instructions for submitting comments. FAA–2016–5598; Directorate Identifier identified in the ADDRESSES section.
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![25358 Federal Register / Vol. 81, No. 82 / Thursday, April 28, 2016 / Proposed Rules
FAA’s Determination For information on the procedures Replacement Inspection of paragraph
and compliance times, see this service 1.E., ‘‘Compliance,’’ the conditional
We are proposing this AD because we information at http:// action statement does not include
evaluated all the relevant information www.regulations.gov by searching for airplanes that were inspected or
and determined the unsafe condition and locating Docket No. FAA–2016– repaired in accordance with Part 8 of
described previously is likely to exist or 5598. the Work Instructions. The statement
develop in other products of the same The phrase ‘‘related investigative should read: ‘‘All airplanes that have
type design. actions’’ is used in this proposed AD. done the STA 320 crown frame web
Related investigative actions are follow- replacement in accordance with
Proposed AD Requirements on actions that (1) are related to the paragraph 3.B. WORK INSTRUCTIONS,
Although this proposed AD does not primary action, and (2) further PARTS 5 OR PART 8.’’ Paragraph (k) of
explicitly restate the requirements of AD investigate the nature of any condition this proposed AD applies to all
2012–22–02, this proposed AD would found. Related investigative actions in airplanes on which a web replacement
an AD could include, for example, is done as required by paragraphs (h),
retain certain requirements of AD 2012–
inspections. (i), and (j) of the proposed AD, e.g., the
22–02. Those requirements are The phrase ‘‘corrective actions’’ is
referenced in the service information replacement is done as specified in Part
used in this proposed AD. Corrective 5 or Part 8 of paragraph 3.B., ‘‘Work
identified previously, which, in turn, is actions correct or address any condition
referenced in paragraphs (h), (i), and (k) Instructions,’’ of the service
found. Corrective actions in an AD information.
of this proposed AD. This proposed AD could include, for example, repairs.
would require accomplishing the Costs of Compliance
actions specified in the service Differences Between This Proposed AD
information described previously, and the Service Information We estimate that this proposed AD
except as discussed under ‘‘Differences For Boeing Alert Service Bulletin affects 29 airplanes.
Between the Proposed AD and the 747–53A2784, Revision 2, dated August We estimate the following costs to
Service Information.’’ 20, 2015, Table 4: STA 320 Post Web comply with this proposed AD:
ESTIMATED COSTS
Action Labor cost Parts cost Cost per product Cost on U.S. operators
Measurement, inspection, 219 work-hours × $85 per Up to $21,887 Up to $40,502 per inspec- $Up to 1,174,558.
and web replacement. [re- hour = $18,615. tion and replacement.
tained actions from AD
2012-22-02].
Post-replacement inspection 135 work-hours × $85 per $0 .................. $11,475 per inspection cycle $332,775 per inspection cycle.
[retained actions from AD hour = $11,475 per in-
2012-22-02]. spection cycle.
Authority for This Rulemaking 13132. This proposed AD would not The Proposed Amendment
have a substantial direct effect on the Accordingly, under the authority
Title 49 of the United States Code
specifies the FAA’s authority to issue States, on the relationship between the delegated to me by the Administrator,
rules on aviation safety. Subtitle I, national Government and the States, or the FAA proposes to amend 14 CFR part
Section 106, describes the authority of on the distribution of power and 39 as follows:
the FAA Administrator. Subtitle VII, responsibilities among the various
Aviation Programs, describes in more levels of government. PART 39—AIRWORTHINESS
detail the scope of the Agency’s DIRECTIVES
For the reasons discussed above, I
authority. certify that the proposed regulation: ■ 1. The authority citation for part 39
We are issuing this rulemaking under (1) Is not a ‘‘significant regulatory continues to read as follows:
the authority described in Subtitle VII, action’’ under Executive Order 12866, Authority: 49 U.S.C. 106(g), 40113, 44701.
Part A, Subpart III, Section 44701,
‘‘General requirements.’’ Under that (2) Is not a ‘‘significant rule’’ under § 39.13 [Amended]
section, Congress charges the FAA with the DOT Regulatory Policies and
■ 2. The FAA amends § 39.13 by
promoting safe flight of civil aircraft in Procedures (44 FR 11034, February 26, removing Airworthiness Directive (AD)
air commerce by prescribing regulations 1979), 2012–22–02, Amendment 39–17238 (77
for practices, methods, and procedures (3) Will not affect intrastate aviation FR 69739 November 21, 2012), and
the Administrator finds necessary for in Alaska and, adding the following new AD:
safety in air commerce. This regulation
(4) Will not have a significant The Boeing Company: Docket No. FAA–
is within the scope of that authority 2016–5598; Directorate Identifier 2016–
economic impact, positive or negative,
because it addresses an unsafe condition
mstockstill on DSK5VPTVN1PROD with PROPOSALS
on a substantial number of small entities NM–001–AD.
that is likely to exist or develop on
products identified in this rulemaking under the criteria of the Regulatory (a) Comments Due Date
action. Flexibility Act. The FAA must receive comments on this
AD action by June 13, 2016.
Regulatory Findings List of Subjects in 14 CFR Part 39
(b) Affected ADs
We have determined that this Air transportation, Aircraft, Aviation This AD replaces AD 2012–22–02,
proposed AD would not have federalism safety, Incorporation by reference, Amendment 39–17238 (77 FR 69739,
implications under Executive Order Safety. November 21, 2012) (‘‘AD 2012–22–02’’).
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![25360 Federal Register / Vol. 81, No. 82 / Thursday, April 28, 2016 / Proposed Rules
Designation Authorization (ODA) that has replacement inspections would be Airframe Branch, ANM–120S, FAA,
been authorized by the Manager, Seattle required if the replacement was done. Seattle Aircraft Certification Office
ACO, to make those findings. To be We are proposing this AD to detect and (ACO), 1601 Lind Avenue SW., Renton,
approved, the repair method, modification correct cracking in the upper chord of WA 98057–3356; phone: 425–917–6430;
deviation, or alteration deviation must meet
the certification basis of the airplane, and the
the overwing stub beam caused by high fax: 425–917–6590; email:
approval must specifically refer to this AD. flight cycle fatigue stresses from both wade.sullivan@faa.gov.
pressurization and maneuver loads. SUPPLEMENTARY INFORMATION:
(o) Related Information Cracking of the overwing stub beam
(1) For more information about this AD, could adversely affect the fuselage Comments Invited
contact Bill Ashforth, Aerospace Engineer, structural integrity and result in We invite you to send any written
Airframe Branch, ANM–120S, FAA, Seattle possible decompression of the airplane. relevant data, views, or arguments about
Aircraft Certification Office (ACO), 1601 Lind this proposal. Send your comments to
Avenue SW., Renton, WA 98057–3356; DATES: We must receive comments on
this proposed AD by June 13, 2016. an address listed under the ADDRESSES
phone: 425–917–6432; fax: 425–91–6590;
section. Include ‘‘Docket No. FAA–
email: Bill.Ashforth@faa.gov. ADDRESSES: You may send comments,
(2) For service information identified in 2016–5597; Directorate Identifier 2016–
using the procedures found in 14 CFR
this AD, contact Boeing Commercial NM–009–AD’’ at the beginning of your
11.43 and 11.45, by any of the following
Airplanes, Attention: Data & Services comments. We specifically invite
methods:
Management, P.O. Box 3707, MC 2H–65, comments on the overall regulatory,
• Federal eRulemaking Portal: Go to
Seattle, WA 98124–2207; telephone 206– economic, environmental, and energy
http://www.regulations.gov. Follow the
544–5000, extension 1; fax 206–766–5680; aspects of this proposed AD. We will
Internet https://www.myboeingfleet.com. You instructions for submitting comments.
consider all comments received by the
may view this service information at the • Fax: 202–493–2251.
closing date and may amend this
FAA, Transport Airplane Directorate, 1601 • Mail: U.S. Department of
proposed AD because of those
Lind Avenue SW., Renton, WA. For Transportation, Docket Operations, M–
comments.
information on the availability of this 30, West Building Ground Floor, Room We will post all comments we
material at the FAA, call 425–227–1221. W12–140, 1200 New Jersey Avenue SE., receive, without change, to http://
Issued in Renton, Washington, on April 15, Washington, DC 20590. www.regulations.gov, including any
2016. • Hand Delivery: Deliver to Mail personal information you provide. We
Victor Wicklund, address above between 9 a.m. and 5 will also post a report summarizing each
Acting Manager, Transport Airplane p.m., Monday through Friday, except substantive verbal contact we receive
Directorate, Aircraft Certification Service. Federal holidays. about this proposed AD.
[FR Doc. 2016–09647 Filed 4–27–16; 8:45 am] For service information identified in
this NPRM, contact Boeing Commercial Discussion
BILLING CODE 4910–13–P
Airplanes, Attention: Data & Services We have received ten reports from
Management, P.O. Box 3707, MC 2H–65, four operators of cracks in the upper
DEPARTMENT OF TRANSPORTATION Seattle, WA 98124–2207; telephone chord of the overwing stub beams at
206–544–5000, extension 1; fax 206– body STA 578 emanating from the rivet
Federal Aviation Administration 766–5680; Internet https:// location common to the crease beam
www.myboeingfleet.com. You may view inner chord and the overwing stub beam
14 CFR Part 39 this referenced service information at upper chord on The Boeing Company
the FAA, Transport Airplane Model 737–400 series airplanes. The
[Docket No. FAA–2016–5597; Directorate
Identifier 2016–NM–009–AD]
Directorate, 1601 Lind Avenue SW., earliest reported crack in an overwing
Renton, WA. For information on the stub beam upper chord occurred on an
RIN 2120–AA64 availability of this material at the FAA, airplane with 31,843 total flight cycles.
call 425–227–1221. It is also available Seven airplanes had a severed overwing
Airworthiness Directives; The Boeing on the internet at http://
Company Airplanes stub beam upper chord on either the left
www.regulations.gov by searching for or right side, and two airplanes had
AGENCY: Federal Aviation and locating Docket No. FAA–2016– severed overwing stub beam upper
Administration (FAA), DOT. 5597. chords on the left and right sides.
ACTION: Notice of proposed rulemaking Examining the AD Docket Cracks in the upper chord of the
(NPRM). overwing stub beams, if not corrected,
You may examine the AD docket on could result in high flight cycle fatigue
SUMMARY: We propose to adopt a new the Internet at http:// stresses from both pressurization and
airworthiness directive (AD) for all The www.regulations.gov by searching for maneuver loads, which can cause
Boeing Company Model 737–400 series and locating Docket No. FAA–2016– cracking in the upper chord of the
airplanes. This proposed AD was 5597; or in person at the Docket overwing stub beam at STA 559, STA
prompted by reports of cracks in the Management Facility between 9 a.m. 578, and STA 601. Cracking of the
upper chord of the overwing stub beams and 5 p.m., Monday through Friday, overwing stub beam could adversely
at body station (STA) 578 emanating except Federal holidays. The AD docket affect the fuselage structural integrity
from the rivet location common to the contains this proposed AD, the and result in possible decompression of
crease beam inner chord and the regulatory evaluation, any comments
mstockstill on DSK5VPTVN1PROD with PROPOSALS
the airplane.
overwing stub beam upper chord. This received, and other information. The
proposed AD would require repetitive street address for the Docket Office Related Service Information Under 1
inspections for cracking, and related (phone: 800–647–5527) is in the CFR Part 51
investigative and corrective actions if ADDRESSES section. Comments will be We reviewed Boeing Alert Service
necessary. Replacement of the overwing available in the AD docket shortly after Bulletin 737–53A1347, dated December
stub beam would terminate the receipt. 9, 2015. The service information
repetitive inspections for cracking at the FOR FURTHER INFORMATION CONTACT: describes procedures for doing a surface
replacement location only, and post- Wade Sullivan, Aerospace Engineer, high frequency eddy current inspection
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Document Created: 2016-04-28 01:05:57
Document Modified: 2016-04-28 01:05:57
| Category | Regulatory Information | |
| Collection | Federal Register | |
| sudoc Class | AE 2.7: GS 4.107: AE 2.106: | |
| Publisher | Office of the Federal Register, National Archives and Records Administration | |
| Section | Proposed Rules | |
| Action | Notice of proposed rulemaking (NPRM). | |
| Dates | We must receive comments on this proposed AD by June 13, 2016. | |
| Contact | Bill Ashforth, Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office (ACO), 1601 Lind Avenue SW., Renton, WA 98057-3356; phone: 425-917- 6432; fax: 425-917-6590; email: [email protected] | |
| FR Citation | 81 FR 25357 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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