81 FR 29505 - Airworthiness Directives; The Boeing Company Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 81, Issue 92 (May 12, 2016)
Federal Aviation Administration
Federal Register Volume 81, Issue 92 (May 12, 2016)
| Page Range | 29505-29508 | |
| FR Document | 2016-11167 |
[Federal Register Volume 81, Number 92 (Thursday, May 12, 2016)] [Proposed Rules] [Pages 29505-29508] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2016-11167] ======================================================================== 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. 92 / Thursday, May 12, 2016 / Proposed Rules [[Page 29505]] DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2016-6670; Directorate Identifier 2016-NM-006-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) 2013-19- 04, which applies to certain The Boeing Company Model 737-600, -700, - 700C, -800, and -900 series airplanes. AD 2013-19-04 currently requires repetitive detailed and high frequency eddy current (HFEC) inspections for cracking of the skin around the eight fasteners common to the ends of the station (STA) 540 bulkhead chords between stringers S-22 and S- 23, left and right sides; related investigative actions and corrective actions, if necessary; and provides an optional terminating modification. Since we issued AD 2013-19-04, we have received reports of additional cracks that are larger and initiated sooner than previously predicted. This proposed AD would reduce the inspection threshold and repetitive inspection intervals. We are proposing this AD to detect and correct fatigue cracking in the fuselage skin around the eight fasteners securing the STA 540 bulkhead chords. Such cracking can result in rapid decompression of the cabin. DATES: We must receive comments on this proposed AD by June 27, 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-2016-6670. 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- 6670; 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: Alan Pohl, Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue SW., Renton, WA 98057-3356; phone: 425-917-6450; 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-2016-6670; Directorate Identifier 2016-NM-006-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 September 9, 2013, we issued AD 2013-19-04, Amendment 39-17586 (78 FR 59801, September 30, 2013) (``AD 2013-19-04''), for certain The Boeing Company Model 737-600, -700, -700C, -800, and -900 series airplanes. AD 2013-19-04 requires repetitive detailed and HFEC inspections for cracking of the skin around the eight fasteners common to the ends of the STA 540 bulkhead chords between stringers S-22 and S-23, left and right sides; related investigative actions and corrective actions, if necessary; and provides an optional terminating modification. AD 2013-19-04 resulted from a report of cracks found in the skin at body STA 540 just below the left side of stringer S-22 on a Model 737-700 series airplane. We issued AD 2013-19-04 to detect and correct fatigue cracking in the fuselage skin around the eight fasteners securing the STA 540 bulkhead chords, which can result in rapid decompression of the cabin. Actions Since AD 2013-19-04 Was Issued Since we issued AD 2013-19-04, we have received reports of cracks that initiated sooner and are larger than previously predicted. Related Service Information Under 1 CFR Part 51 We reviewed Boeing Special Attention Service Bulletin 737-53-1294, Revision 2, dated December 9, 2015, which specifies procedures for doing inspections for cracking of the skin around the eight fasteners common to the ends of the STA 540 bulkhead chords between stringers S- 22 and S-23, left and right sides, repairing cracks, [[Page 29506]] and installing a chord splice as a preventive modification on crack- free skin. 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. 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 designs. Proposed AD Requirements Although this proposed AD does not explicitly restate the requirements of AD 2013-19-04, this proposed AD would retain all of the requirements of AD 2013-19-04. Those requirements are referenced in the service information identified previously, which, in turn, is referenced in paragraphs (g) through (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 this 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-2016-6670. 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 Boeing Special Attention Service Bulletin 737-53-1294, Revision 2, dated December 9, 2015, specifies to contact the manufacturer for instructions on how to repair certain conditions, but this proposed AD would require accomplishment of repair methods, modification deviations, and alteration deviations in one of the following ways: In accordance with a method that we approve; or Using data that meet the certification basis of the airplane, and that have been approved by the Boeing Commercial Airplanes Organization Designation Authorization (ODA) whom we have authorized to make those findings. Costs of Compliance We estimate that this proposed AD affects 903 airplanes of U.S. registry. We estimate the following costs to comply with this proposed AD: Estimated Costs ---------------------------------------------------------------------------------------------------------------- Cost on U.S. Action Labor cost Parts cost Cost per product operators ---------------------------------------------------------------------------------------------------------------- Inspection (left and right side 12 work-hours x $85 $0 $1,020 per $921,060 per skins). per hour = $1,020 inspection cycle. inspection cycle. per inspection cycle. ---------------------------------------------------------------------------------------------------------------- We estimate the following costs to do any necessary repairs and inspections that would be required based on the results of the proposed inspection. We have no way of determining the number of aircraft that might need these repairs: On-Condition Costs ---------------------------------------------------------------------------------------------------------------- Action Labor cost Parts cost Cost per product ---------------------------------------------------------------------------------------------------------------- Preventive modification (each 7 work-hours x $85 $894...................... $1,489. side). per hour = $595. Skin repair (each side)........... 39 work-hours x $85 Up to $5,635.............. Up to $8,950. per hour = $3,315. ---------------------------------------------------------------------------------------------------------------- According to the manufacturer, some of the costs of this proposed AD may be covered under warranty, thereby reducing the cost impact on affected individuals. We do not control warranty coverage for affected individuals. As a result, we have included all costs in our cost estimate. 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. [[Page 29507]] 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) 2013-19-04, Amendment 39-17586 (78 FR 59801, September 30, 2013), and adding the following new AD: The Boeing Company: Docket No. FAA-2016-6670; Directorate Identifier 2016-NM-006-AD. (a) Comments Due Date The FAA must receive comments on this AD action by June 27, 2016. (b) Affected ADs This AD replaces AD 2013-19-04, Amendment 39-17586 (78 FR 59801, September 30, 2013) (``AD 2013-19-04''). (c) Applicability This AD applies to The Boeing Company Model 737-600, -700, - 700C, -800, and -900 series airplanes; certificated in any category; as identified in Boeing Special Attention Service Bulletin 737-53- 1294, Revision 2, dated December 9, 2015. (d) Subject Air Transport Association (ATA) of America Code 53, Fuselage. (e) Unsafe Condition This AD was prompted by a report of cracks found in the skin at body station (STA) 540 just below the left side of stringer S-22. We are issuing this AD to detect and correct fatigue cracking in the fuselage skin around the eight fasteners securing the STA 540 bulkhead chords, which can result in rapid decompression of the cabin. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Inspection and Corrective Action Except as required by paragraphs (i)(1) and (i)(2) of this AD, at the applicable time specified in table 1 of paragraph 1.E. ``Compliance,'' of Boeing Special Attention Service Bulletin 737-53- 1294, Revision 2, dated December 9, 2015: Do detailed and high frequency eddy current (HFEC) inspections for cracking of the skin in the area around the eight fasteners securing the STA 540 bulkhead chords between stringers S-22 and S-23; and do all applicable related investigative and corrective actions; in accordance with Parts 1, 2, 3, 4, and 5 of the Accomplishment Instructions of Boeing Special Attention Service Bulletin 737-53-1294, Revision 2, dated December 9, 2015, except as required by paragraphs (i)(3) and (i)(4) of this AD. Do all applicable related investigative and corrective actions before further flight. Repeat the detailed and HFEC inspections thereafter at the intervals specified in table 1 of paragraph 1.E., ``Compliance,'' of Boeing Special Attention Service Bulletin 737-53-1294, Revision 2, dated December 9, 2015, until the optional preventive modification specified in paragraph (h) of this AD is done. (h) Optional Preventive Modification Accomplishing the preventive modification or repair, including an HFEC inspection for cracking of the skin and STA 540 bulkhead chords, and all applicable repairs, in accordance with paragraph 3.B, Part 2 or Part 4 (left side), and Part 3 or Part 5 (right side), of the Accomplishment Instructions of Boeing Special Attention Service Bulletin 737-53-1294, Revision 2, dated December 9, 2015, except as required by paragraph (i)(2) of this AD, terminates the inspection requirements of paragraph (g) of this AD for the side on which the modification is done. (i) Exceptions to Service Bulletin Specifications (1) Where paragraph 1.E., ``Compliance,'' of Boeing Special Attention Service Bulletin 737-53-1294, Revision 2, dated December 9, 2015, specifies a compliance time ``after the Revision 2 date of this service bulletin,'' this AD requires compliance within the specified compliance time after the effective date of this AD. (2) For airplanes on which Boeing Business Jet Lower Cabin Altitude Supplemental Type Certificate (STC) ST01697SE (http:// rgl.faa.gov/Regulatory_and_Guidance_Library/rgstc.nsf/0/ 0812969a86af879b8625766400600105/$FILE/ST01697SE.pdf) (6,500 feet maximum cabin altitude in lieu of 8,000 feet) has been incorporated, the flight-cycle related compliance times for the inspection required by paragraph (g) of this AD are different from those specified in paragraph 1.E., ``Compliance,'' of Boeing Special Attention Service Bulletin 737-53-1294, Revision 2, dated December 9, 2015. All initial compliance times specified in total flight cycles or flight cycles must be reduced to half of those specified in Boeing Special Attention Service Bulletin 737-53-1294, Revision 2, dated December 9, 2015. All repetitive interval compliance times specified in flight cycles must be reduced to one-quarter of those specified in paragraph 1.E., ``Compliance,'' of Boeing Special Attention Service Bulletin 737-53-1294, Revision 2, dated December 9, 2015. (3) If any cracking is found during any inspection required by this AD, and Boeing Special Attention Service Bulletin 737-53-1294, Revision 2, dated December 9, 2015, specifies to contact Boeing for appropriate action: Before further flight, repair using a method approved in accordance with the procedures specified in paragraph (l) of this AD. (4) The access and restoration instructions identified in the Accomplishment Instructions of Boeing Special Attention Service Bulletin 737-53-1294, Revision 2, dated December 9, 2015, are not required by this AD. Operators may perform those actions in accordance with approved maintenance procedures. (j) Part 26 Supplemental Inspections Not Required by This AD Table 2 of paragraph 1.E., ``Compliance,'' of Boeing Special Attention Service Bulletin 737-53-1294, Revision 2, dated December 9, 2015, specifies post-modification airworthiness limitation inspections in compliance with 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. (k) Credit for Previous Actions This paragraph provides credit for the actions required by paragraphs (g) and (h) of this AD, if those actions were performed before the effective date of this AD using Boeing Special Attention Service Bulletin 737-53-1294, dated March 31, 2011, which is not incorporated by reference in this AD; or Boeing Special Attention Service Bulletin 737-53-1294, Revision 1, dated June 14, 2013, which is incorporated by reference in AD 2013-19-04. (l) 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 (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) An AMOC that provides an acceptable level of safety may be used for any repair, modification, or alteration required by this AD if it is approved by the Boeing Commercial Airplanes Organization Designation Authorization (ODA) that has been authorized by the Manager, 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. [[Page 29508]] (4) AMOCs approved previously for the optional preventive modification installed in accordance with paragraph (h) of AD 2013- 19-04, and AMOCs approved previously for repairs for AD 2013-19-04, are approved as AMOCs for the corresponding provisions of this AD, provided that such modification or repair included installation of the splice plate as specified in Boeing Special Attention Service Bulletin 737-53-1294, except as provided by paragraph (l)(5) of this AD. (5) The time-limited repair approved as specified in FAA Letter 120S-15-140, dated June 3, 2015, is approved as an AMOC to the corresponding requirements of this AD. (m) Related Information (1) For more information about this AD, contact Alan Pohl, Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue SW., Renton, WA 98057-3356; phone: 425-917-6450; fax: 425-917-6590; 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 referenced service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. You may view this referenced service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425-227-1221. Issued in Renton, Washington, on May 5, 2016. Michael Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2016-11167 Filed 5-11-16; 8:45 am] BILLING CODE 4910-13-P
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Proposed Rules Federal Register
Vol. 81, No. 92
Thursday, May 12, 2016
This section of the FEDERAL REGISTER • Fax: 202–493–2251. FAA–2016–6670; Directorate Identifier
contains notices to the public of the proposed • Mail: U.S. Department of 2016–NM–006–AD’’ at the beginning of
issuance of rules and regulations. The Transportation, Docket Operations, M– your comments. We specifically invite
purpose of these notices is to give interested 30, West Building Ground Floor, Room comments on the overall regulatory,
persons an opportunity to participate in the W12–140, 1200 New Jersey Avenue SE., economic, environmental, and energy
rule making prior to the adoption of the final
Washington, DC 20590. aspects of this proposed AD. We will
rules.
• Hand Delivery: Deliver to Mail consider all comments received by the
address above between 9 a.m. and 5 closing date and may amend this
DEPARTMENT OF TRANSPORTATION p.m., Monday through Friday, except proposed AD because of those
Federal holidays. comments.
Federal Aviation Administration For service information identified in We will post all comments we
this NPRM, contact Boeing Commercial receive, without change, to http://
14 CFR Part 39 Airplanes, Attention: Data & Services www.regulations.gov, including any
Management, P.O. Box 3707, MC 2H–65, personal information you provide. We
[Docket No. FAA–2016–6670; Directorate Seattle, WA 98124–2207; telephone will also post a report summarizing each
Identifier 2016–NM–006–AD]
206–544–5000, extension 1; fax 206– substantive verbal contact we receive
RIN 2120–AA64 766–5680; Internet https:// about this proposed AD.
www.myboeingfleet.com. You may view Discussion
Airworthiness Directives; The Boeing this referenced service information at
Company Airplanes the FAA, Transport Airplane On September 9, 2013, we issued AD
Directorate, 1601 Lind Avenue SW., 2013–19–04, Amendment 39–17586 (78
AGENCY: Federal Aviation
Renton, WA. For information on the FR 59801, September 30, 2013) (‘‘AD
Administration (FAA), DOT.
availability of this material at the FAA, 2013–19–04’’), for certain The Boeing
ACTION: Notice of proposed rulemaking Company Model 737–600, –700, –700C,
(NPRM). call 425–227–1221. It is also available
on the Internet at http:// –800, and –900 series airplanes. AD
SUMMARY: We propose to supersede www.regulations.gov by searching for 2013–19–04 requires repetitive detailed
Airworthiness Directive (AD) 2013–19– and locating Docket No. FAA–2016– and HFEC inspections for cracking of
04, which applies to certain The Boeing 6670. the skin around the eight fasteners
Company Model 737–600, –700, –700C, common to the ends of the STA 540
Examining the AD Docket bulkhead chords between stringers S–22
–800, and –900 series airplanes. AD
2013–19–04 currently requires You may examine the AD docket on and S–23, left and right sides; related
repetitive detailed and high frequency the Internet at http:// investigative actions and corrective
eddy current (HFEC) inspections for www.regulations.gov by searching for actions, if necessary; and provides an
cracking of the skin around the eight and locating Docket No. FAA–2016– optional terminating modification. AD
fasteners common to the ends of the 6670; or in person at the Docket 2013–19–04 resulted from a report of
station (STA) 540 bulkhead chords Management Facility between 9 a.m. cracks found in the skin at body STA
between stringers S–22 and S–23, left and 5 p.m., Monday through Friday, 540 just below the left side of stringer
and right sides; related investigative except Federal holidays. The AD docket S–22 on a Model 737–700 series
actions and corrective actions, if contains this proposed AD, the airplane. We issued AD 2013–19–04 to
necessary; and provides an optional regulatory evaluation, any comments detect and correct fatigue cracking in
terminating modification. Since we received, and other information. The the fuselage skin around the eight
issued AD 2013–19–04, we have street address for the Docket Office fasteners securing the STA 540
received reports of additional cracks (phone: 800–647–5527) is in the bulkhead chords, which can result in
that are larger and initiated sooner than ADDRESSES section. Comments will be rapid decompression of the cabin.
previously predicted. This proposed AD available in the AD docket shortly after Actions Since AD 2013–19–04 Was
would reduce the inspection threshold receipt. Issued
and repetitive inspection intervals. We FOR FURTHER INFORMATION CONTACT:
Since we issued AD 2013–19–04, we
are proposing this AD to detect and Alan Pohl, Aerospace Engineer, have received reports of cracks that
correct fatigue cracking in the fuselage Airframe Branch, ANM–120S, FAA, initiated sooner and are larger than
skin around the eight fasteners securing Seattle Aircraft Certification Office, previously predicted.
the STA 540 bulkhead chords. Such 1601 Lind Avenue SW., Renton, WA
cracking can result in rapid 98057–3356; phone: 425–917–6450; fax: Related Service Information Under 1
decompression of the cabin. 425–917–6590; email: alan.pohl@ CFR Part 51
DATES: We must receive comments on faa.gov. We reviewed Boeing Special
jstallworth on DSK7TPTVN1PROD with PROPOSALS
this proposed AD by June 27, 2016. SUPPLEMENTARY INFORMATION: Attention Service Bulletin 737–53–
ADDRESSES: You may send comments, 1294, Revision 2, dated December 9,
using the procedures found in 14 CFR Comments Invited 2015, which specifies procedures for
11.43 and 11.45, by any of the following We invite you to send any written doing inspections for cracking of the
methods: relevant data, views, or arguments about skin around the eight fasteners common
• Federal eRulemaking Portal: Go to this proposed AD. Send your comments to the ends of the STA 540 bulkhead
http://www.regulations.gov. Follow the to an address listed under the chords between stringers S–22 and S–
instructions for submitting comments. ADDRESSES section. Include ‘‘Docket No. 23, left and right sides, repairing cracks,
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![Federal Register / Vol. 81, No. 92 / Thursday, May 12, 2016 / Proposed Rules 29507
List of Subjects in 14 CFR Part 39 STA 540 bulkhead chords between stringers action: Before further flight, repair using a
S–22 and S–23; and do all applicable related method approved in accordance with the
Air transportation, Aircraft, Aviation investigative and corrective actions; in procedures specified in paragraph (l) of this
safety, Incorporation by reference, accordance with Parts 1, 2, 3, 4, and 5 of the AD.
Safety. Accomplishment Instructions of Boeing (4) The access and restoration instructions
Special Attention Service Bulletin 737–53– identified in the Accomplishment
The Proposed Amendment
1294, Revision 2, dated December 9, 2015, Instructions of Boeing Special Attention
Accordingly, under the authority except as required by paragraphs (i)(3) and Service Bulletin 737–53–1294, Revision 2,
delegated to me by the Administrator, (i)(4) of this AD. Do all applicable related dated December 9, 2015, are not required by
the FAA proposes to amend 14 CFR part investigative and corrective actions before this AD. Operators may perform those actions
39 as follows: further flight. Repeat the detailed and HFEC in accordance with approved maintenance
inspections thereafter at the intervals procedures.
PART 39—AIRWORTHINESS specified in table 1 of paragraph 1.E.,
‘‘Compliance,’’ of Boeing Special Attention (j) Part 26 Supplemental Inspections Not
DIRECTIVES Required by This AD
Service Bulletin 737–53–1294, Revision 2,
■ 1. The authority citation for part 39 dated December 9, 2015, until the optional Table 2 of paragraph 1.E., ‘‘Compliance,’’
continues to read as follows: preventive modification specified in of Boeing Special Attention Service Bulletin
paragraph (h) of this AD is done. 737–53–1294, Revision 2, dated December 9,
Authority: 49 U.S.C. 106(g), 40113, 44701. 2015, specifies post-modification
(h) Optional Preventive Modification airworthiness limitation inspections in
§ 39.13 [Amended] Accomplishing the preventive compliance with 14 CFR 25.571(a)(3) at the
■ 2. The FAA amends § 39.13 by modification or repair, including an HFEC modified locations, which support
removing Airworthiness Directive (AD) inspection for cracking of the skin and STA compliance with 14 CFR 121.1109(c)(2) or
2013–19–04, Amendment 39–17586 (78 540 bulkhead chords, and all applicable 129.109(b)(2). As airworthiness limitations,
FR 59801, September 30, 2013), and repairs, in accordance with paragraph 3.B, these inspections are required by
adding the following new AD: Part 2 or Part 4 (left side), and Part 3 or Part maintenance and operational rules. It is
5 (right side), of the Accomplishment therefore unnecessary to mandate them in
The Boeing Company: Docket No. FAA– Instructions of Boeing Special Attention this AD. Deviations from these inspections
2016–6670; Directorate Identifier 2016– Service Bulletin 737–53–1294, Revision 2, require FAA approval, but do not require an
NM–006–AD. dated December 9, 2015, except as required alternative method of compliance.
(a) Comments Due Date by paragraph (i)(2) of this AD, terminates the
inspection requirements of paragraph (g) of (k) Credit for Previous Actions
The FAA must receive comments on this this AD for the side on which the This paragraph provides credit for the
AD action by June 27, 2016. modification is done. actions required by paragraphs (g) and (h) of
(b) Affected ADs this AD, if those actions were performed
(i) Exceptions to Service Bulletin before the effective date of this AD using
This AD replaces AD 2013–19–04, Specifications Boeing Special Attention Service Bulletin
Amendment 39–17586 (78 FR 59801, (1) Where paragraph 1.E., ‘‘Compliance,’’ of 737–53–1294, dated March 31, 2011, which
September 30, 2013) (‘‘AD 2013–19–04’’). Boeing Special Attention Service Bulletin is not incorporated by reference in this AD;
(c) Applicability 737–53–1294, Revision 2, dated December 9, or Boeing Special Attention Service Bulletin
2015, specifies a compliance time ‘‘after the 737–53–1294, Revision 1, dated June 14,
This AD applies to The Boeing Company
Revision 2 date of this service bulletin,’’ this 2013, which is incorporated by reference in
Model 737–600, –700, –700C, –800, and –900
series airplanes; certificated in any category; AD requires compliance within the specified AD 2013–19–04.
as identified in Boeing Special Attention compliance time after the effective date of
this AD. (l) Alternative Methods of Compliance
Service Bulletin 737–53–1294, Revision 2, (AMOCs)
dated December 9, 2015. (2) For airplanes on which Boeing Business
Jet Lower Cabin Altitude Supplemental Type (1) The Manager, Seattle Aircraft
(d) Subject Certificate (STC) ST01697SE (http:// Certification Office (ACO), FAA, has the
Air Transport Association (ATA) of rgl.faa.gov/Regulatory_and_Guidance_ authority to approve AMOCs for this AD, if
America Code 53, Fuselage. Library/rgstc.nsf/0/ requested using the procedures found in 14
0812969a86af879b8625766400600105/$FILE/ CFR 39.19. In accordance with 14 CFR 39.19,
(e) Unsafe Condition ST01697SE.pdf) (6,500 feet maximum cabin send your request to your principal inspector
This AD was prompted by a report of altitude in lieu of 8,000 feet) has been or local Flight Standards District Office, as
cracks found in the skin at body station incorporated, the flight-cycle related appropriate. If sending information directly
(STA) 540 just below the left side of stringer compliance times for the inspection required to the manager of the ACO, send it to the
S–22. We are issuing this AD to detect and by paragraph (g) of this AD are different from attention of the person identified in
correct fatigue cracking in the fuselage skin those specified in paragraph 1.E., paragraph (m) of this AD. Information may be
around the eight fasteners securing the STA ‘‘Compliance,’’ of Boeing Special Attention emailed to: 9-ANM-Seattle-ACO-AMOC-
540 bulkhead chords, which can result in Service Bulletin 737–53–1294, Revision 2, Requests@faa.gov.
rapid decompression of the cabin. dated December 9, 2015. All initial (2) Before using any approved AMOC,
compliance times specified in total flight notify your appropriate principal inspector,
(f) Compliance cycles or flight cycles must be reduced to half or lacking a principal inspector, the manager
Comply with this AD within the of those specified in Boeing Special of the local flight standards district office/
compliance times specified, unless already Attention Service Bulletin 737–53–1294, certificate holding district office.
done. Revision 2, dated December 9, 2015. All (3) An AMOC that provides an acceptable
repetitive interval compliance times level of safety may be used for any repair,
(g) Inspection and Corrective Action specified in flight cycles must be reduced to modification, or alteration required by this
jstallworth on DSK7TPTVN1PROD with PROPOSALS
Except as required by paragraphs (i)(1) and one-quarter of those specified in paragraph AD if it is approved by the Boeing
(i)(2) of this AD, at the applicable time 1.E., ‘‘Compliance,’’ of Boeing Special Commercial Airplanes Organization
specified in table 1 of paragraph 1.E. Attention Service Bulletin 737–53–1294, Designation Authorization (ODA) that has
‘‘Compliance,’’ of Boeing Special Attention Revision 2, dated December 9, 2015. been authorized by the Manager, Seattle
Service Bulletin 737–53–1294, Revision 2, (3) If any cracking is found during any ACO, to make those findings. To be
dated December 9, 2015: Do detailed and inspection required by this AD, and Boeing approved, the repair method, modification
high frequency eddy current (HFEC) Special Attention Service Bulletin 737–53– deviation, or alteration deviation must meet
inspections for cracking of the skin in the 1294, Revision 2, dated December 9, 2015, the certification basis of the airplane, and the
area around the eight fasteners securing the specifies to contact Boeing for appropriate approval must specifically refer to this AD.
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![29508 Federal Register / Vol. 81, No. 92 / Thursday, May 12, 2016 / Proposed Rules
(4) AMOCs approved previously for the eddy current (HFEC) inspections for contains this proposed AD, the
optional preventive modification installed in cracks around the rivets at the upper regulatory evaluation, any comments
accordance with paragraph (h) of AD 2013– fastener row of the skin lap splice of the received, and other information. The
19–04, and AMOCs approved previously for fuselage, and repairing any crack found. street address for the Docket Office
repairs for AD 2013–19–04, are approved as
AMOCs for the corresponding provisions of
Since we issued AD 2006–20–11, an (phone: 800–647–5527) is in the
this AD, provided that such modification or evaluation done by the design approval ADDRESSES section. Comments will be
repair included installation of the splice holder (DAH) indicated that the fuselage available in the AD docket shortly after
plate as specified in Boeing Special Attention skin lap splice is subject to widespread receipt.
Service Bulletin 737–53–1294, except as fatigue damage (WFD). This proposed FOR FURTHER INFORMATION CONTACT: Eric
provided by paragraph (l)(5) of this AD. AD would no longer allow the detailed Schrieber, Aerospace Engineer,
(5) The time-limited repair approved as inspections and would instead require Airframe Branch, ANM–120L, FAA, Los
specified in FAA Letter 120S–15–140, dated repetitive external HFEC inspections for
June 3, 2015, is approved as an AMOC to the
Angeles Aircraft Certification Office
cracking of the skin lap splices of the (ACO), 3960 Paramount Boulevard,
corresponding requirements of this AD.
fuselage, and repair if necessary. We are Lakewood, CA 90712–4137; phone:
(m) Related Information proposing this AD to detect and correct 562–627–5348; fax: 562–627–5210;
(1) For more information about this AD, fatigue cracking at certain skin lap email: eric.schrieber@faa.gov.
contact Alan Pohl, Aerospace Engineer, splice locations of the fuselage, which SUPPLEMENTARY INFORMATION:
Airframe Branch, ANM–120S, FAA, Seattle could result in reduced structural
Aircraft Certification Office, 1601 Lind integrity and rapid decompression of Comments Invited
Avenue SW., Renton, WA 98057–3356; the airplane.
phone: 425–917–6450; fax: 425–917–6590; We invite you to send any written
email: alan.pohl@faa.gov. DATES: We must receive comments on relevant data, views, or arguments about
(2) For service information identified in this proposed AD by June 27, 2016. this proposed AD. Send your comments
this AD, contact Boeing Commercial ADDRESSES: You may send comments, to an address listed under the
Airplanes, Attention: Data & Services using the procedures found in 14 CFR ADDRESSES section. Include ‘‘Docket No.
Management, P.O. Box 3707, MC 2H–65, 11.43 and 11.45, by any of the following FAA–2016–6669; Directorate Identifier
Seattle, WA 98124–2207; telephone 206– methods: 2015–NM–191–AD’’ at the beginning of
544–5000, extension 1; fax 206–766–5680;
• Federal eRulemaking Portal: Go to your comments. We specifically invite
Internet https://www.myboeingfleet.com. You
may view this referenced service information http://www.regulations.gov. Follow the comments on the overall regulatory,
at the FAA, Transport Airplane Directorate, instructions for submitting comments. economic, environmental, and energy
1601 Lind Avenue SW., Renton, WA. You • Fax: 202–493–2251. aspects of this proposed AD. We will
may view this referenced service information • Mail: U.S. Department of consider all comments received by the
at the FAA, Transport Airplane Directorate, Transportation, Docket Operations, M– closing date and may amend this
1601 Lind Avenue SW., Renton, WA. For 30, West Building Ground Floor, Room proposed AD because of those
information on the availability of this W12–140, 1200 New Jersey Avenue SE., comments.
material at the FAA, call 425–227–1221. Washington, DC 20590. We will post all comments we
Issued in Renton, Washington, on May 5, • Hand Delivery: Deliver to Mail receive, without change, to http://
2016. address above between 9 a.m. and 5 www.regulations.gov, including any
Michael Kaszycki, p.m., Monday through Friday, except personal information you provide. We
Acting Manager, Transport Airplane Federal holidays. will also post a report summarizing each
Directorate, Aircraft Certification Service. For service information identified in substantive verbal contact we receive
[FR Doc. 2016–11167 Filed 5–11–16; 8:45 am] this NPRM, contact Boeing Commercial about this proposed AD.
BILLING CODE 4910–13–P Airplanes, Attention: Data & Services
Discussion
Management, 3855 Lakewood
Boulevard, MC D800–0019, Long Beach, On September 22, 2006, we issued AD
DEPARTMENT OF TRANSPORTATION CA 90846–0001; telephone: 206–544– 2006–20–11, Amendment 39–14781 (71
5000, extension 2; fax: 206–766–5683; FR 58485, October 4, 2006) (‘‘AD 2006–
Federal Aviation Administration Internet https:// 20–11’’), for certain The Boeing
www.myboeingfleet.com. You may view Company Model 757–200, –200CB, and
14 CFR Part 39 this referenced service information at –200PF series airplanes. AD 2006–20–
[Docket No. FAA–2016–6669; Directorate the FAA, Transport Airplane 11 requires initial and repetitive
Identifier 2015–NM–191–AD] Directorate, 1601 Lind Avenue SW., detailed or HFEC inspections for cracks
Renton, WA. For information on the around the rivets at the upper fastener
RIN 2120–AA64 availability of this material at the FAA, row of the skin lap splice of the
call 425–227–1221. It is also available fuselage, and repairing any crack found.
Airworthiness Directives; The Boeing
on the Internet at http:// AD 2006–20–11 resulted from reports of
Company Airplanes
www.regulations.gov by searching for cracking in the fuselage skin of the
AGENCY: Federal Aviation and locating Docket No. FAA–2016– crown skin panel. We issued AD 2006–
Administration (FAA), DOT. 6669. 20–11 to detect and correct premature
ACTION: Notice of proposed rulemaking fatigue cracking at certain skin lap
Examining the AD Docket splice locations of the fuselage, and
jstallworth on DSK7TPTVN1PROD with PROPOSALS
(NPRM).
You may examine the AD docket on consequent rapid decompression of the
SUMMARY: We propose to supersede the Internet at http:// airplane.
Airworthiness Directive (AD) 2006–20– www.regulations.gov by searching for Structural fatigue damage is
11, which applies to certain The Boeing and locating Docket No. FAA–2016– progressive. It begins as minute cracks,
Company Model 757–200, –200CB, and 6669; or in person at the Docket and those cracks grow under the action
–200PF series airplanes. AD 2006–20– Management Facility between 9 a.m. of repeated stresses. This can happen
11 currently requires initial and and 5 p.m., Monday through Friday, because of normal operational
repetitive detailed or high frequency except Federal holidays. The AD docket conditions and design attributes, or
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Document Created: 2016-05-12 01:07:33
Document Modified: 2016-05-12 01:07:33
| 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 27, 2016. | |
| Contact | Alan Pohl, Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue SW., Renton, WA 98057-3356; phone: 425-917-6450; fax: 425-917-6590; email: [email protected] | |
| FR Citation | 81 FR 29505 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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