Airworthiness Directives; The Boeing Company Airplanes, 74599-74603 [2014-29190]

Download as PDF Federal Register / Vol. 79, No. 241 / Tuesday, December 16, 2014 / Rules and Regulations (d) Subject Air Transport Association (ATA) of America Code 53, Fuselage. (e) Reason This AD was prompted by a report of cracking at the splice plate of the frame (FR) 47 butt joint crossing area found during fullscale fatigue testing. We are issuing this AD to detect and correct fatigue cracking of the splice plate of the FR47 butt joint crossing area, which could result in reduced structural integrity of the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. tkelley on DSK3SPTVN1PROD with RULES (g) Repetitive Inspections At the applicable time specified in paragraph (g)(1), (g)(2), or (g)(3) of this AD: Do a special detailed inspection (rototest) for cracking of both sides of the splice plate of the FR47 butt joint crossing area, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320– 53–1260, dated December 19, 2012. Repeat the inspection thereafter at intervals not to exceed 14,800 flight cycles or 29,600 flight hours, whichever occurs first. (1) For airplanes that, as of the effective date of this AD, have accumulated 44,000 or more total flight cycles or 88,000 or more total flight hours since first flight of the airplane: Do the inspection within 1,500 flight cycles or 3,000 flight hours after the effective date of this AD, whichever occurs first. (2) For airplanes that, as of the effective date of this AD, have accumulated 27,700 or more total flight cycles or 55,400 or more total flight hours, but fewer than 44,000 total flight cycles or 88,000 total flight hours since first flight of the airplane: Do the inspection within 3,000 flight cycles or 6,000 flight hours after the effective date of this AD, without exceeding 45,500 total flight cycles or 91,000 total flight hours since first flight of the airplane, whichever occurs first. (3) For airplanes that, as of the effective date of this AD, have accumulated fewer than 27,700 total flight cycles and less than 55,400 total flight hours since first flight of the airplane: Do the inspection before the accumulation of 30,700 total flight cycles or 61,400 total flight hours since first flight of the airplane, whichever occurs first. (h) Corrective Action If any crack is found during any inspection required by this AD: Before further flight, repair using a method approved by the Manager, International Branch, ANM–116, Transport Airplane Directorate, FAA; or the European Aviation Safety Agency (EASA); or Airbus’s EASA Design Organization Approval (DOA). If approved by the DOA, the approval must include the DOAauthorized signature. (i) Optional Modification Accomplishing the modification of the splice plate of the FR47 butt joint in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320– VerDate Sep<11>2014 16:25 Dec 15, 2014 Jkt 235001 53–1271, dated December 18, 2012, constitutes terminating action for the repetitive inspections required by paragraph (g) of this AD. (j) Other FAA AD Provisions The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, International Branch, ANM–116, Transport Airplane Directorate, 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 International Branch, send it to ATTN: Sanjay Ralhan, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057–3356; phone: 425–227–1405; fax: 425–227–1149. Information may be emailed to: 9-ANM-116AMOC-REQUESTS@faa.gov. 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. (2) Contacting the Manufacturer: For any requirement in this AD to obtain corrective actions from a manufacturer, the action must be accomplished using a method approved by the Manager, International Branch, ANM– 116, Transport Airplane Directorate, FAA; or the European Aviation Safety Agency (EASA); or Airbus’s EASA Design Organization Approval (DOA). If approved by the DOA, the approval must include the DOA-authorized signature. (k) Related Information Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA Airworthiness Directive 2013–0203, dated September 6, 2013, for related information. This MCAI may be found in the AD docket on the Internet at http://www.regulations. gov/#!documentDetail;D=FAA-2014-04530002. (l) 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 this AD specifies otherwise. (i) Airbus Service Bulletin A320–53–1260, dated December 19, 2012. (ii) Airbus Service Bulletin A320–53–1271, dated December 18, 2012. (3) For service information identified in this AD, contact Airbus, Airworthiness Office—EIAS, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 44 51; email account.airworth-eas@ airbus.com; Internet http://www.airbus.com. (4) You may view this service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For PO 00000 Frm 00015 Fmt 4700 Sfmt 4700 74599 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 December 3, 2014. Michael Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2014–29174 Filed 12–15–14; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2014–0257; Directorate Identifier 2014–NM–012–AD; Amendment 39–18051; AD 2014–25–09] RIN 2120–AA64 Airworthiness Directives; The Boeing Company Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Final rule. AGENCY: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 737–100, –200, –200C, –300, –400, and –500 series airplanes. This AD was prompted by reports of fatigue cracking in the skin assembly and bear strap of the aft lower corner of the forward airstair stowage doorway. This AD requires repetitive inspections for cracking of the skin assembly and bear strap of the forward airstair stowage doorway; post-repair and post-modification inspections for certain airplanes; and related investigative and corrective actions, if necessary. This AD also provides optional terminating actions for certain inspections. We are issuing this AD to detect and correct fatigue cracking, which could result in rapid loss of cabin pressure. DATES: This AD is effective January 20, 2015. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of January 20, 2015. ADDRESSES: 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:// SUMMARY: E:\FR\FM\16DER1.SGM 16DER1 74600 Federal Register / Vol. 79, No. 241 / Tuesday, December 16, 2014 / Rules and Regulations www.myboeingfleet.com. You may view this referenced service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425–227–1221. Examining the AD Docket You may examine the AD docket on the Internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2014– 0257; 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: 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: alan.pohl@ faa.gov. 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 737–100, –200, –200C, –300, –400, and –500 series airplanes. The NPRM published in the Federal Register on May 1, 2014 (79 FR 24628). The NPRM was prompted by reports of fatigue cracking in certain areas. The NPRM proposed to require repetitive inspections for cracking of the skin assembly and bear strap of the forward airstair stowage doorway; post-repair and post-modification inspections for certain airplanes; and related investigative and corrective actions, if necessary. The NPRM also proposed to provide optional terminating actions for certain inspections. We are issuing this AD to detect and correct fatigue cracking, which could result in rapid loss of cabin pressure. Comments We gave the public the opportunity to participate in developing this AD. The following presents the comments received on the NPRM (79 FR 24628, May 1, 2014) and the FAA’s response to each comment. Effect of Winglets on AD Aviation Partners Boeing and UPS stated that the installation of winglets per Supplemental Type Certificate (STC) ST01219SE (http://rgl.faa.gov/ Regulatory_and_Guidance_Library/ rgstc.nsf/0/ebd1cec7b301293e86257 cb30045557a/$FILE/ST01219SE.pdf) does not affect the accomplishment of the manufacturer’s service instructions. We agree with the commenters’ statement. We have redesignated paragraph (c) of the NPRM (79 FR 24628, May 1, 2014) as (c)(1) in this AD and added new paragraph (c)(2) to this AD to state that the installation of winglets as specified in STC ST01219SE (http://rgl.faa.gov/Regulatory_and_ Guidance_Library/rgstc.nsf/0/ebd1c ec7b301293e86257cb30045557a/$FILE/ ST01219SE.pdf) does not affect accomplishment of the requirements of this AD, and 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 section 39.17 of the Federal Aviation Regulations (14 CFR 39.17). Request To Revise Paragraph (m) of the NPRM (79 FR 24628, May 1, 2014) Southwest Airlines (SWA) stated that the NPRM (79 FR 24628, May 1, 2014), does not address terminating the initial inspection if a repair was previously installed using Boeing Service Bulletin 737–53–1058, Revision 4, dated January 9, 2014. SWA requested that we revise the text of paragraph (m)(3) of the NPRM, to state that repairs or modifications using Boeing Service Bulletin 737–53–1058, Revision 4, dated January 9, 2014, terminates both the initial and repetitive inspections required by paragraph (j) of this AD. SWA also requested that repairs previously approved by a Boeing authorized representative via an FAA 8100–9 form are terminating action to both the initial and repetitive inspection requirements required by paragraph (j) of the NPRM. We agree with the request because it was not intended that a separate initial inspection would be performed on airplanes that have the repair previously installed. We have deleted the word ‘‘repetitive’’ from paragraphs (m)(1) through (m)(3) of this AD to clarify that accomplishing the actions in those paragraphs terminates certain initial and repetitive inspections. We have also added paragraph (m)(4) to this final rule, which specifies that the accomplishment of a repair of the aft lower corner of the forward airstair stowage doorway that was previously approved using FAA Form 8100–9, terminates the inspections required by paragraph (j) of this AD. 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 (79 FR 24628, May 1, 2014) for correcting the unsafe condition; and • Do not add any additional burden upon the public than was already proposed in the NPRM (79 FR 24628, May 1, 2014). We also determined that these changes will not increase the economic burden on any operator or increase the scope of this AD. Costs of Compliance We estimate that this AD affects 132 airplanes of U.S. registry. We estimate the following costs to comply with this AD: ESTIMATED COSTS Labor cost Parts cost Cost per product Inspection ...... tkelley on DSK3SPTVN1PROD with RULES Action 5 work-hours × $85 per hour = $425 per inspection cycle. None ............ $425 per inspection cycle We have received no definitive data that would enable us to provide cost VerDate Sep<11>2014 16:25 Dec 15, 2014 Jkt 235001 estimates for any on-condition actions specified in this AD. PO 00000 Frm 00016 Fmt 4700 Sfmt 4700 Cost on U.S. operators $56,100 per inspection cycle. Authority for This Rulemaking Title 49 of the United States Code specifies the FAA’s authority to issue E:\FR\FM\16DER1.SGM 16DER1 Federal Register / Vol. 79, No. 241 / Tuesday, December 16, 2014 / Rules and Regulations 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 1. The authority citation for part 39 continues to read as follows: tkelley on DSK3SPTVN1PROD with RULES ■ Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The FAA amends § 39.13 by adding the following new airworthiness directive (AD): ■ VerDate Sep<11>2014 16:25 Dec 15, 2014 Jkt 235001 2014–25–09 The Boeing Company: Amendment 39–18051; Docket No. FAA–2014–0257; Directorate Identifier 2014–NM–012–AD. (a) Effective Date This AD is effective January 20, 2015. (b) Affected ADs None. (c) Applicability (1) This AD applies to The Boeing Company Model 737–100, –200, –200C, –300, –400, and –500 series airplanes, certificated in any category, as identified in Boeing Service Bulletin 737–53–1058, Revision 4, dated January 9, 2014. (2) Installation of Supplemental Type Certificate (STC) ST01219SE (http://rgl.faa. gov/Regulatory_and_Guidance_Library/ rgstc.nsf/0/ebd1cec7b301293e86257cb300 45557a/$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. 74601 times specified in Table 1 of paragraph 1.E., ‘‘Compliance,’’ of Boeing Service Bulletin 737–53–1058, Revision 4, dated January 9, 2014, until the applicable terminating action specified in paragraph (m) of this AD is done. (1) Boeing Service Bulletin 737–53–1058, dated April 4, 1980. (2) Boeing Service Bulletin 737–53–1058, Revision 1, dated March 5, 1987. (3) Boeing Service Bulletin 737–53–1058, Revision 2, dated December 7, 1989. (4) Boeing Service Bulletin 737–53–1058, Revision 3, dated March 11, 1993. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (h) Inspections and Corrective Actions for Group 1 and Group 2 Airplanes That Have a Certain Repair Installed For Group 1 and Group 2 airplanes identified in Boeing Service Bulletin 737–53– 1058, Revision 4, dated January 9, 2014, on which a repair has been installed as specified in Boeing Service Bulletin 737–53–1058, dated April 4, 1980: Within the applicable times specified in Table 1 of paragraph 1.E., ‘‘Compliance,’’ of Boeing Service Bulletin 737–53–1058, Revision 4, dated January 9, 2014, except as required by paragraph (o)(1) of this AD, do a high frequency eddy current inspection for cracking of the bear strap of the forward airstair stowage doorway, and do low frequency eddy current and detailed inspections for cracking of the skin assembly and bear strap of the forward airstair stowage doorway; and do all applicable related investigative and corrective actions; in accordance with the Accomplishment Instructions of Boeing Service Bulletin 737– 53–1058, Revision 4, dated January 9, 2014, except as required by paragraph (o)(2) of this AD. Do all applicable related investigative and corrective actions before further flight. Repeat the inspections at the applicable times specified in Table 1 of paragraph 1.E., ‘‘Compliance,’’ of Boeing Service Bulletin 737–53–1058, Revision 4, dated January 9, 2014, until the applicable terminating action specified in paragraph (m) of this AD is done. (g) Inspections and Corrective Actions for Group 1 and Group 2 Airplanes That Do Not Have a Certain Repair or Preventative Modification Installed For Group 1 and Group 2 airplanes identified in Boeing Service Bulletin 737–53– 1058, Revision 4, dated January 9, 2014, on which no repair or preventative modification has been done as specified in any of the service information identified in paragraphs (g)(1) through (g)(4) of this AD: At the applicable times specified in Table 1 of paragraph 1.E., ‘‘Compliance,’’ of Boeing Service Bulletin 737–53–1058, Revision 4, dated January 9, 2014, except as required by paragraph (o)(1) of this AD, do high frequency eddy current and detailed inspections for cracking of the skin assembly and bear strap of the forward airstair stowage doorway, and do all applicable related investigative and corrective actions, in accordance with the Accomplishment Instructions of Boeing Service Bulletin 737– 53–1058, Revision 4, dated January 9, 2014, except as required by paragraph (o)(2) of this AD. Do all applicable related investigative and corrective actions before further flight. Repeat the inspections at the applicable (i) Inspections and Corrective Actions for Group 1 and Group 2 Airplanes That Have a Certain Preventative Modification Installed For Group 1 and Group 2 airplanes identified in Boeing Service Bulletin 737–53– 1058, Revision 4, dated January 9, 2014, on which a preventative modification has been installed as specified in any of the service information identified in paragraphs (i)(1) through (i)(4) of this AD: Within the applicable times specified in Table 1 of paragraph 1.E., ‘‘Compliance,’’ of Boeing Service Bulletin 737–53–1058, Revision 4, dated January 9, 2014, except as required by paragraph (o)(1) of this AD, do a high frequency eddy current inspection for cracking of the bear strap of the forward airstair stowage doorway, a low frequency eddy current inspection for cracking of the skin assembly and bear strap of the forward airstair stowage doorway, and detailed inspections for cracking of the skin assembly and bear strap of the forward airstair stowage doorway; and do all related investigative and applicable corrective actions; in accordance with the Accomplishment Instructions of Boeing Service Bulletin 737–53–1058, (d) Subject Air Transport Association (ATA) of America Code 53, Fuselage. (e) Unsafe Condition This AD was prompted by reports of fatigue cracking in the skin assembly and bear strap of the aft lower corner of the forward airstair stowage doorway. We are issuing this AD to detect and correct fatigue cracking, which could result in rapid loss of cabin pressure. PO 00000 Frm 00017 Fmt 4700 Sfmt 4700 E:\FR\FM\16DER1.SGM 16DER1 74602 Federal Register / Vol. 79, No. 241 / Tuesday, December 16, 2014 / Rules and Regulations Revision 4, dated January 9, 2014, except as required by paragraph (o)(2) of this AD. Do all applicable related investigative and corrective actions before further flight. Repeat the inspections at the applicable times specified in Table 1 of paragraph 1.E., ‘‘Compliance,’’ of Boeing Service Bulletin 737–53–1058, Revision 4, dated January 9, 2014, until the applicable terminating action specified in paragraph (m) of this AD is done. (1) Boeing Service Bulletin 737–53–1058, dated April 4, 1980. (2) Boeing Service Bulletin 737–53–1058, Revision 1, dated March 5, 1987. (3) Boeing Service Bulletin 737–53–1058, Revision 2, dated December 7, 1989. (4) Boeing Service Bulletin 737–53–1058, Revision 3, dated March 11, 1993. (j) Inspections and Corrective Actions for Group 3 Through Group 5 Airplanes For Group 3 through Group 5 airplanes identified in Boeing Service Bulletin 737–53– 1058, Revision 4, dated January 9, 2014: At the applicable times specified in Table 2 of paragraph 1.E., ‘‘Compliance,’’ of Boeing Service Bulletin 737–53–1058, Revision 4, dated January 9, 2014, except as required by paragraph (o)(1) of this AD, do a high frequency eddy current inspection for cracking of the bear strap of the forward airstair stowage doorway, a low frequency eddy current inspection for cracking of the skin assembly and bear strap of the forward airstair stowage doorway, and detailed inspections for cracking of the skin assembly and bear strap of the forward airstair stowage doorway; and do all related investigative and applicable corrective actions; in accordance with the Accomplishment Instructions of Boeing Service Bulletin 737–53–1058, Revision 4, dated January 9, 2014, except as required by paragraph (o)(2) of this AD. Do all applicable related investigative and corrective actions before further flight. Repeat the inspections at the applicable times specified in Table 2 of paragraph 1.E., ‘‘Compliance,’’ of Boeing Service Bulletin 737–53–1058, Revision 4, dated January 9, 2014, until the applicable terminating action specified in paragraph (m) of this AD is done. tkelley on DSK3SPTVN1PROD with RULES (k) Inspections and Corrective Actions for Group 6 Airplanes For Group 6 airplanes identified in Boeing Service Bulletin 737–53–1058, Revision 4, dated January 9, 2014: Within 120 days after the effective date of this AD, inspect and repair any cracking using a method approved in accordance with the procedures specified in paragraph (q) of this AD. (l) Post-Repair and Post-Modification Inspections for Group 1 and Group 2 Airplanes For Group 1 and Group 2 airplanes on which any repair has been done as specified in any of the service information identified in paragraphs (l)(1) through (l)(3) of this AD, or on which any repair or modification has been done as specified in the service information identified in paragraph (l)(4) of this AD: At the applicable times specified in Table 3 of paragraph 1.E., ‘‘Compliance,’’ of Boeing Service Bulletin 737–53–1058, Revision 4, dated January 9, 2014, except as required by paragraph (o)(1) of this AD, do VerDate Sep<11>2014 16:25 Dec 15, 2014 Jkt 235001 a high frequency eddy current inspection for cracking in the bear strap and skin assembly and a general visual inspection for cracking in the frame of the forward airstair stowage doorway; or do low frequency eddy current inspections for cracking of the skin assembly and bear strap of the forward airstair stowage doorway; in accordance with the Accomplishment Instructions of Boeing Service Bulletin 737–53–1058, Revision 4, dated January 9, 2014. Options provided in Boeing Service Bulletin 737–53–1058, Revision 4, dated January 9, 2014, for accomplishing the inspections are acceptable for compliance with the corresponding requirements of this paragraph provided that the inspections are done at the applicable times specified in paragraph 1.E., ‘‘Compliance,’’ of the Boeing Service Bulletin 737–53–1058, Revision 4, dated January 9, 2014. If any cracking is found, before further flight, repair the cracking using a method approved in accordance with the procedures specified in paragraph (q) of this AD. Repeat the inspections at the applicable times specified in Table 3 of paragraph 1.E., ‘‘Compliance,’’ of Boeing Service Bulletin 737–53–1058, Revision 4, dated January 9, 2014. (1) Boeing Service Bulletin 737–53–1058, Revision 1, dated March 5, 1987. (2) Boeing Service Bulletin 737–53–1058, Revision 2, dated December 7, 1989. (3) Boeing Service Bulletin 737–53–1058, Revision 3, dated March 11, 1993. (4) Boeing Service Bulletin 737–53–1058, Revision 4, dated January 9, 2014. (m) Optional Terminating Actions (1) For Group 1 and Group 2 airplanes identified in Boeing Service Bulletin 737–53– 1058, Revision 4, dated January 9, 2014: Accomplishment of a repair for cracking of the skin assembly and bear strap of the forward airstair stowage doorway before the effective date of this AD, using any service information specified in paragraphs (m)(1)(i) through (m)(1)(iv) of this AD, terminates the inspections required by paragraphs (g), (h), and (i) of this AD. (i) Boeing Service Bulletin 737–53–1058, Revision 1, dated March 5, 1987. (ii) Boeing Service Bulletin 737–53–1058, Revision 2, dated December 7, 1989. (iii) Boeing Service Bulletin 737–53–1058, Revision 3, dated March 11, 1993. (iv) Boeing Service Bulletin 737–53–1058, Revision 4, dated January 9, 2014. (2) For Group 1 and Group 2 airplanes identified in Boeing Service Bulletin 737–53– 1058, Revision 4, dated January 9, 2014: Accomplishment of a preventative modification for cracking of the skin assembly and bear strap of the forward airstair stowage doorway before the effective date of this AD, in accordance with the Accomplishment Instructions of Boeing Service Bulletin 737–53–1058, Revision 4, dated January 9, 2014, terminates the inspections required by paragraphs (g), (h), and (i) of this AD. (3) For Group 3 through Group 5 airplanes identified in Boeing Service Bulletin 737–53– 1058, Revision 4, dated January 9, 2014: Repairing or modifying the forward airstair stowage doorway, in accordance with the PO 00000 Frm 00018 Fmt 4700 Sfmt 4700 Accomplishment Instructions of Boeing Service Bulletin 737–53–1058, Revision 4, dated January 9, 2014, terminates the inspections required by paragraph (j) of this AD. (4) Accomplishment, prior to the effective date of this AD, of a repair of the aft lower corner of the forward airstair stowage doorway that was approved by Boeing Commercial Airplanes Organization Designation Authorization (ODA) using FAA Form 8100–9, terminates the inspections required by paragraph (j) of this AD. (n) Credit for Previous Actions This paragraph provides credit for the actions required by paragraphs (g), (h), and (i) of this AD, if those actions were performed before the effective date of this AD using any service information specified in paragraphs (n)(i) through (n)(iii) of this AD. (i) Boeing Service Bulletin 737–53–1058, Revision 1, dated March 5, 1987. (ii) Boeing Service Bulletin 737–53–1058, Revision 2, dated December 7, 1989. (iii) Boeing Service Bulletin 737–53–1058, Revision 3, dated March 11, 1993. (o) Exceptions to the Service Information (1) Where Boeing Service Bulletin 737–53– 1058, Revision 4, dated January 9, 2014, specifies a compliance time ‘‘after the Revision 4 date of this service bulletin,’’ this AD requires compliance within the specified compliance time ‘‘after the effective date of this AD.’’ (2) Where Boeing Service Bulletin 737–53– 1058, Revision 4, dated January 9, 2014, specifies to contact Boeing for repair instructions: Before further flight, repair using a method approved in accordance with the procedures specified in paragraph (q) of this AD. (p) Post-Repair and Post-Modification Inspections for Group 3 Through Group 5 Airplanes Not Required The post-repair and post-modification inspections specified in Table 4 of paragraph 1.E., ‘‘Compliance,’’ of Boeing Service Bulletin 737–53–1058, Revision 4, dated January 9, 2014, are not required by this AD. Note 1 to paragraph (p) of this AD: The post-repair and post-modification inspections specified in Table 4 of paragraph 1.E., ‘‘Compliance,’’ of Boeing Service Bulletin 737–53–1058, Revision 4, dated January 9, 2014, may be used in support of compliance with section 121.1109(c)(2) or 129.109(b)(2) of the Federal Aviation Regulations (14 CFR 121.1109(c)(2) or 14 CFR 129.109(b)(2)). (q) 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 (r)(1) of this AD. Information may be emailed to: 9-ANM-Seattle-ACO-AMOCRequests@faa.gov. E:\FR\FM\16DER1.SGM 16DER1 Federal Register / Vol. 79, No. 241 / Tuesday, December 16, 2014 / Rules and Regulations (2) Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/ certificate holding district office. (3) An AMOC that provides an acceptable level of safety may be used for any repair required by this AD if it is approved by the Boeing Commercial Airplanes Organization Designation Authorization (ODA) that has been authorized by the Manager, Seattle ACO, to make those findings. For a repair method to be approved, the repair must meet the certification basis of the airplane, and the approval must specifically refer to this AD. (r) Related Information (1) For more information about this AD, contact Nenita Odesa, Aerospace Engineer, Airframe Branch, ANM–120L, FAA, Los Angeles Aircraft Certification Office, 3960 Paramount Boulevard, Lakewood, CA 90712– 4137; phone: (562) 627–5234; fax: (562) 627– 5210; email: nenita.odesa@faa.gov. (2) Service information identified in this AD that is not incorporated by reference is available at the addresses specified in paragraphs (s)(3) and (s)(4) of this AD. (s) Material Incorporated by Reference tkelley on DSK3SPTVN1PROD with RULES (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 Service Bulletin 737–53–1058, Revision 4, dated January 9, 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 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 December 5, 2014. Michael J. Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2014–29190 Filed 12–15–14; 8:45 am] BILLING CODE 4910–13–P VerDate Sep<11>2014 16:25 Dec 15, 2014 Jkt 235001 DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2014–0566; Directorate Identifier 2014–NM–041–AD; Amendment 39–18050; AD 2014–25–08] RIN 2120–AA64 Airworthiness Directives; Dassault Aviation Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: We are adopting a new airworthiness directive (AD) for certain Dassault Aviation Model FALCON 2000 and FALCON 2000EX airplanes. This AD was prompted by a design review, which revealed that the forward servicing compartment (FSC) is configured with tie-down points. This AD requires inspecting the FSC for installed tie-down points, and removing those tie-down points. We are issuing this AD to detect and correct installed tie-down points, which could lead to inadvertent use of the FSC as a cargo compartment, which could result in damage to the structure of the airplane or potential risk of fire. DATES: This AD becomes effective January 20, 2015. The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of January 20, 2015. ADDRESSES: You may examine the AD docket on the Internet at http://www. regulations.gov/#!docketDetail;D=FAA2014-0566; or in person at the 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. For service information identified in this AD, contact Dassault Falcon Jet, P.O. Box 2000, South Hackensack, NJ 07606; telephone 201–440–6700; Internet http://www.dassaultfalcon.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. FOR FURTHER INFORMATION CONTACT: Tom Rodriguez, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057–3356; telephone 425–227–1137; fax 425- 227–1149. SUMMARY: PO 00000 Frm 00019 Fmt 4700 Sfmt 4700 74603 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 Dassault Aviation Model FALCON 2000 and FALCON 2000EX airplanes. The NPRM published in the Federal Register on August 14, 2014 (79 FR 47592). The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Community, has issued EASA Airworthiness Directive 2014–0027R1, dated February 5, 2014 (referred to after this as the Mandatory Continuing Airworthiness Information, or ‘‘the MCAI’’), to correct an unsafe condition for certain Dassault Aviation Model FALCON 2000 and FALCON 2000EX airplanes. The MCAI states: The Forward Servicing Compartment (FSC) of the Falcon 2000 is an unpressurized service compartment located between fuselage frames 26 and 33. This compartment is accessible from a lockable external door located in the lower aft fuselage. A design review has brought to light that the compartment is configured with tie-down points, which were used by operators to fix loads (e.g. ski or golf bags) in that compartment. However, the FSC has not been designed and consequently demonstrated as being compliant with cargo compartment airworthiness requirements. This condition, if not corrected, could lead to inadvertent use of the FSC as [a] cargo compartment, which could result in damage to the structure of the aeroplane or potential risk of fire. To address this potential unsafe condition, Dassault Aviation issued Service Bulletin (SB) F2000–407 and SB F2000EX–289, as applicable, which provide instructions for removal of the tie-down points. For the reasons described above, this [EASA] AD requires removal of the tie-down points from the FSC. Note: Operators are also reminded about the intended function of the FSC. This [EASA] AD is revised to clarify the AD Applicability and to correct the [type certificate data sheet] TCDS Number. Required actions include inspecting for installed tie-down points. You may examine the MCAI in the AD docket on the Internet at http://www.regulations. gov/#!documentDetail;D=FAA-20140566-0002. Comments We gave the public the opportunity to participate in developing this AD. We received no comments on the NPRM (79 FR 47592, August 14, 2014) or on the determination of the cost to the public. Conclusion We reviewed the relevant data and determined that air safety and the E:\FR\FM\16DER1.SGM 16DER1

Agencies

[Federal Register Volume 79, Number 241 (Tuesday, December 16, 2014)]
[Rules and Regulations]
[Pages 74599-74603]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2014-29190]


-----------------------------------------------------------------------

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2014-0257; Directorate Identifier 2014-NM-012-AD; 
Amendment 39-18051; AD 2014-25-09]
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 737-100, -200, -200C, -300, -400, and -500 
series airplanes. This AD was prompted by reports of fatigue cracking 
in the skin assembly and bear strap of the aft lower corner of the 
forward airstair stowage doorway. This AD requires repetitive 
inspections for cracking of the skin assembly and bear strap of the 
forward airstair stowage doorway; post-repair and post-modification 
inspections for certain airplanes; and related investigative and 
corrective actions, if necessary. This AD also provides optional 
terminating actions for certain inspections. We are issuing this AD to 
detect and correct fatigue cracking, which could result in rapid loss 
of cabin pressure.

DATES: This AD is effective January 20, 2015.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of January 20, 
2015.

ADDRESSES: 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://

[[Page 74600]]

www.myboeingfleet.com. You may view this referenced service information 
at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., 
Renton, WA. For information on the availability of this material at the 
FAA, call 425-227-1221.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2014-
0257; 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: 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: alan.pohl@faa.gov.

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 737-100, -200, -200C, -300, -400, and -500 series airplanes. The 
NPRM published in the Federal Register on May 1, 2014 (79 FR 24628). 
The NPRM was prompted by reports of fatigue cracking in certain areas. 
The NPRM proposed to require repetitive inspections for cracking of the 
skin assembly and bear strap of the forward airstair stowage doorway; 
post-repair and post-modification inspections for certain airplanes; 
and related investigative and corrective actions, if necessary. The 
NPRM also proposed to provide optional terminating actions for certain 
inspections. We are issuing this AD to detect and correct fatigue 
cracking, which could result in rapid loss of cabin pressure.

Comments

    We gave the public the opportunity to participate in developing 
this AD. The following presents the comments received on the NPRM (79 
FR 24628, May 1, 2014) and the FAA's response to each comment.

Effect of Winglets on AD

    Aviation Partners Boeing and UPS stated that the installation of 
winglets per Supplemental Type Certificate (STC) ST01219SE (http://
rgl.faa.gov/Regulatory_and_Guidance_Library/rgstc.nsf/0/
ebd1cec7b301293e86257cb30045557a/$FILE/ST01219SE.pdf) does not affect 
the accomplishment of the manufacturer's service instructions.
    We agree with the commenters' statement. We have redesignated 
paragraph (c) of the NPRM (79 FR 24628, May 1, 2014) as (c)(1) in this 
AD and added new paragraph (c)(2) to this AD to state that the 
installation of winglets as specified in STC ST01219SE (http://
rgl.faa.gov/Regulatory_and_Guidance_Library/rgstc.nsf/0/
ebd1cec7b301293e86257cb30045557a/$FILE/ST01219SE.pdf) does not affect 
accomplishment of the requirements of this AD, and 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 section 39.17 of the Federal Aviation 
Regulations (14 CFR 39.17).

Request To Revise Paragraph (m) of the NPRM (79 FR 24628, May 1, 2014)

    Southwest Airlines (SWA) stated that the NPRM (79 FR 24628, May 1, 
2014), does not address terminating the initial inspection if a repair 
was previously installed using Boeing Service Bulletin 737-53-1058, 
Revision 4, dated January 9, 2014. SWA requested that we revise the 
text of paragraph (m)(3) of the NPRM, to state that repairs or 
modifications using Boeing Service Bulletin 737-53-1058, Revision 4, 
dated January 9, 2014, terminates both the initial and repetitive 
inspections required by paragraph (j) of this AD. SWA also requested 
that repairs previously approved by a Boeing authorized representative 
via an FAA 8100-9 form are terminating action to both the initial and 
repetitive inspection requirements required by paragraph (j) of the 
NPRM.
    We agree with the request because it was not intended that a 
separate initial inspection would be performed on airplanes that have 
the repair previously installed. We have deleted the word 
``repetitive'' from paragraphs (m)(1) through (m)(3) of this AD to 
clarify that accomplishing the actions in those paragraphs terminates 
certain initial and repetitive inspections. We have also added 
paragraph (m)(4) to this final rule, which specifies that the 
accomplishment of a repair of the aft lower corner of the forward 
airstair stowage doorway that was previously approved using FAA Form 
8100-9, terminates the inspections required by paragraph (j) of this 
AD.

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:
     [Agr]re consistent with the intent that was proposed in 
the NPRM (79 FR 24628, May 1, 2014) for correcting the unsafe 
condition; and
     Do not add any additional burden upon the public than was 
already proposed in the NPRM (79 FR 24628, May 1, 2014).
    We also determined that these changes will not increase the 
economic burden on any operator or increase the scope of this AD.

Costs of Compliance

    We estimate that this AD affects 132 airplanes of U.S. registry.
    We estimate the following costs to comply with this AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                 Cost on U.S.
        Action                 Labor cost              Parts cost         Cost per product        operators
----------------------------------------------------------------------------------------------------------------
Inspection...........  5 work-hours x $85 per     None................  $425 per inspection  $56,100 per
                        hour = $425 per                                  cycle.               inspection cycle.
                        inspection cycle.
----------------------------------------------------------------------------------------------------------------

    We have received no definitive data that would enable us to provide 
cost estimates for any on-condition actions specified in this AD.

Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to 
issue

[[Page 74601]]

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):

2014-25-09 The Boeing Company: Amendment 39-18051; Docket No. FAA-
2014-0257; Directorate Identifier 2014-NM-012-AD.

(a) Effective Date

    This AD is effective January 20, 2015.

(b) Affected ADs

    None.

(c) Applicability

    (1) This AD applies to The Boeing Company Model 737-100, -200, -
200C, -300, -400, and -500 series airplanes, certificated in any 
category, as identified in Boeing Service Bulletin 737-53-1058, 
Revision 4, dated January 9, 2014.
    (2) Installation of Supplemental Type Certificate (STC) 
ST01219SE (http://rgl.faa.gov/Regulatory_and_Guidance_Library/
rgstc.nsf/0/ebd1cec7b301293e86257cb30045557a/$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 in the skin 
assembly and bear strap of the aft lower corner of the forward 
airstair stowage doorway. We are issuing this AD to detect and 
correct fatigue cracking, which could result in rapid loss of cabin 
pressure.

(f) Compliance

    Comply with this AD within the compliance times specified, 
unless already done.

(g) Inspections and Corrective Actions for Group 1 and Group 2 
Airplanes That Do Not Have a Certain Repair or Preventative 
Modification Installed

    For Group 1 and Group 2 airplanes identified in Boeing Service 
Bulletin 737-53-1058, Revision 4, dated January 9, 2014, on which no 
repair or preventative modification has been done as specified in 
any of the service information identified in paragraphs (g)(1) 
through (g)(4) of this AD: At the applicable times specified in 
Table 1 of paragraph 1.E., ``Compliance,'' of Boeing Service 
Bulletin 737-53-1058, Revision 4, dated January 9, 2014, except as 
required by paragraph (o)(1) of this AD, do high frequency eddy 
current and detailed inspections for cracking of the skin assembly 
and bear strap of the forward airstair stowage doorway, and do all 
applicable related investigative and corrective actions, in 
accordance with the Accomplishment Instructions of Boeing Service 
Bulletin 737-53-1058, Revision 4, dated January 9, 2014, except as 
required by paragraph (o)(2) of this AD. Do all applicable related 
investigative and corrective actions before further flight. Repeat 
the inspections at the applicable times specified in Table 1 of 
paragraph 1.E., ``Compliance,'' of Boeing Service Bulletin 737-53-
1058, Revision 4, dated January 9, 2014, until the applicable 
terminating action specified in paragraph (m) of this AD is done.
    (1) Boeing Service Bulletin 737-53-1058, dated April 4, 1980.
    (2) Boeing Service Bulletin 737-53-1058, Revision 1, dated March 
5, 1987.
    (3) Boeing Service Bulletin 737-53-1058, Revision 2, dated 
December 7, 1989.
    (4) Boeing Service Bulletin 737-53-1058, Revision 3, dated March 
11, 1993.

(h) Inspections and Corrective Actions for Group 1 and Group 2 
Airplanes That Have a Certain Repair Installed

    For Group 1 and Group 2 airplanes identified in Boeing Service 
Bulletin 737-53-1058, Revision 4, dated January 9, 2014, on which a 
repair has been installed as specified in Boeing Service Bulletin 
737-53-1058, dated April 4, 1980: Within the applicable times 
specified in Table 1 of paragraph 1.E., ``Compliance,'' of Boeing 
Service Bulletin 737-53-1058, Revision 4, dated January 9, 2014, 
except as required by paragraph (o)(1) of this AD, do a high 
frequency eddy current inspection for cracking of the bear strap of 
the forward airstair stowage doorway, and do low frequency eddy 
current and detailed inspections for cracking of the skin assembly 
and bear strap of the forward airstair stowage doorway; and do all 
applicable related investigative and corrective actions; in 
accordance with the Accomplishment Instructions of Boeing Service 
Bulletin 737-53-1058, Revision 4, dated January 9, 2014, except as 
required by paragraph (o)(2) of this AD. Do all applicable related 
investigative and corrective actions before further flight. Repeat 
the inspections at the applicable times specified in Table 1 of 
paragraph 1.E., ``Compliance,'' of Boeing Service Bulletin 737-53-
1058, Revision 4, dated January 9, 2014, until the applicable 
terminating action specified in paragraph (m) of this AD is done.

(i) Inspections and Corrective Actions for Group 1 and Group 2 
Airplanes That Have a Certain Preventative Modification Installed

    For Group 1 and Group 2 airplanes identified in Boeing Service 
Bulletin 737-53-1058, Revision 4, dated January 9, 2014, on which a 
preventative modification has been installed as specified in any of 
the service information identified in paragraphs (i)(1) through 
(i)(4) of this AD: Within the applicable times specified in Table 1 
of paragraph 1.E., ``Compliance,'' of Boeing Service Bulletin 737-
53-1058, Revision 4, dated January 9, 2014, except as required by 
paragraph (o)(1) of this AD, do a high frequency eddy current 
inspection for cracking of the bear strap of the forward airstair 
stowage doorway, a low frequency eddy current inspection for 
cracking of the skin assembly and bear strap of the forward airstair 
stowage doorway, and detailed inspections for cracking of the skin 
assembly and bear strap of the forward airstair stowage doorway; and 
do all related investigative and applicable corrective actions; in 
accordance with the Accomplishment Instructions of Boeing Service 
Bulletin 737-53-1058,

[[Page 74602]]

Revision 4, dated January 9, 2014, except as required by paragraph 
(o)(2) of this AD. Do all applicable related investigative and 
corrective actions before further flight. Repeat the inspections at 
the applicable times specified in Table 1 of paragraph 1.E., 
``Compliance,'' of Boeing Service Bulletin 737-53-1058, Revision 4, 
dated January 9, 2014, until the applicable terminating action 
specified in paragraph (m) of this AD is done.
    (1) Boeing Service Bulletin 737-53-1058, dated April 4, 1980.
    (2) Boeing Service Bulletin 737-53-1058, Revision 1, dated March 
5, 1987.
    (3) Boeing Service Bulletin 737-53-1058, Revision 2, dated 
December 7, 1989.
    (4) Boeing Service Bulletin 737-53-1058, Revision 3, dated March 
11, 1993.

(j) Inspections and Corrective Actions for Group 3 Through Group 5 
Airplanes

    For Group 3 through Group 5 airplanes identified in Boeing 
Service Bulletin 737-53-1058, Revision 4, dated January 9, 2014: At 
the applicable times specified in Table 2 of paragraph 1.E., 
``Compliance,'' of Boeing Service Bulletin 737-53-1058, Revision 4, 
dated January 9, 2014, except as required by paragraph (o)(1) of 
this AD, do a high frequency eddy current inspection for cracking of 
the bear strap of the forward airstair stowage doorway, a low 
frequency eddy current inspection for cracking of the skin assembly 
and bear strap of the forward airstair stowage doorway, and detailed 
inspections for cracking of the skin assembly and bear strap of the 
forward airstair stowage doorway; and do all related investigative 
and applicable corrective actions; in accordance with the 
Accomplishment Instructions of Boeing Service Bulletin 737-53-1058, 
Revision 4, dated January 9, 2014, except as required by paragraph 
(o)(2) of this AD. Do all applicable related investigative and 
corrective actions before further flight. Repeat the inspections at 
the applicable times specified in Table 2 of paragraph 1.E., 
``Compliance,'' of Boeing Service Bulletin 737-53-1058, Revision 4, 
dated January 9, 2014, until the applicable terminating action 
specified in paragraph (m) of this AD is done.

(k) Inspections and Corrective Actions for Group 6 Airplanes

    For Group 6 airplanes identified in Boeing Service Bulletin 737-
53-1058, Revision 4, dated January 9, 2014: Within 120 days after 
the effective date of this AD, inspect and repair any cracking using 
a method approved in accordance with the procedures specified in 
paragraph (q) of this AD.

(l) Post-Repair and Post-Modification Inspections for Group 1 and Group 
2 Airplanes

    For Group 1 and Group 2 airplanes on which any repair has been 
done as specified in any of the service information identified in 
paragraphs (l)(1) through (l)(3) of this AD, or on which any repair 
or modification has been done as specified in the service 
information identified in paragraph (l)(4) of this AD: At the 
applicable times specified in Table 3 of paragraph 1.E., 
``Compliance,'' of Boeing Service Bulletin 737-53-1058, Revision 4, 
dated January 9, 2014, except as required by paragraph (o)(1) of 
this AD, do a high frequency eddy current inspection for cracking in 
the bear strap and skin assembly and a general visual inspection for 
cracking in the frame of the forward airstair stowage doorway; or do 
low frequency eddy current inspections for cracking of the skin 
assembly and bear strap of the forward airstair stowage doorway; in 
accordance with the Accomplishment Instructions of Boeing Service 
Bulletin 737-53-1058, Revision 4, dated January 9, 2014. Options 
provided in Boeing Service Bulletin 737-53-1058, Revision 4, dated 
January 9, 2014, for accomplishing the inspections are acceptable 
for compliance with the corresponding requirements of this paragraph 
provided that the inspections are done at the applicable times 
specified in paragraph 1.E., ``Compliance,'' of the Boeing Service 
Bulletin 737-53-1058, Revision 4, dated January 9, 2014. If any 
cracking is found, before further flight, repair the cracking using 
a method approved in accordance with the procedures specified in 
paragraph (q) of this AD. Repeat the inspections at the applicable 
times specified in Table 3 of paragraph 1.E., ``Compliance,'' of 
Boeing Service Bulletin 737-53-1058, Revision 4, dated January 9, 
2014.
    (1) Boeing Service Bulletin 737-53-1058, Revision 1, dated March 
5, 1987.
    (2) Boeing Service Bulletin 737-53-1058, Revision 2, dated 
December 7, 1989.
    (3) Boeing Service Bulletin 737-53-1058, Revision 3, dated March 
11, 1993.
    (4) Boeing Service Bulletin 737-53-1058, Revision 4, dated 
January 9, 2014.

(m) Optional Terminating Actions

    (1) For Group 1 and Group 2 airplanes identified in Boeing 
Service Bulletin 737-53-1058, Revision 4, dated January 9, 2014: 
Accomplishment of a repair for cracking of the skin assembly and 
bear strap of the forward airstair stowage doorway before the 
effective date of this AD, using any service information specified 
in paragraphs (m)(1)(i) through (m)(1)(iv) of this AD, terminates 
the inspections required by paragraphs (g), (h), and (i) of this AD.
    (i) Boeing Service Bulletin 737-53-1058, Revision 1, dated March 
5, 1987.
    (ii) Boeing Service Bulletin 737-53-1058, Revision 2, dated 
December 7, 1989.
    (iii) Boeing Service Bulletin 737-53-1058, Revision 3, dated 
March 11, 1993.
    (iv) Boeing Service Bulletin 737-53-1058, Revision 4, dated 
January 9, 2014.
    (2) For Group 1 and Group 2 airplanes identified in Boeing 
Service Bulletin 737-53-1058, Revision 4, dated January 9, 2014: 
Accomplishment of a preventative modification for cracking of the 
skin assembly and bear strap of the forward airstair stowage doorway 
before the effective date of this AD, in accordance with the 
Accomplishment Instructions of Boeing Service Bulletin 737-53-1058, 
Revision 4, dated January 9, 2014, terminates the inspections 
required by paragraphs (g), (h), and (i) of this AD.
    (3) For Group 3 through Group 5 airplanes identified in Boeing 
Service Bulletin 737-53-1058, Revision 4, dated January 9, 2014: 
Repairing or modifying the forward airstair stowage doorway, in 
accordance with the Accomplishment Instructions of Boeing Service 
Bulletin 737-53-1058, Revision 4, dated January 9, 2014, terminates 
the inspections required by paragraph (j) of this AD.
    (4) Accomplishment, prior to the effective date of this AD, of a 
repair of the aft lower corner of the forward airstair stowage 
doorway that was approved by Boeing Commercial Airplanes 
Organization Designation Authorization (ODA) using FAA Form 8100-9, 
terminates the inspections required by paragraph (j) of this AD.

(n) Credit for Previous Actions

    This paragraph provides credit for the actions required by 
paragraphs (g), (h), and (i) of this AD, if those actions were 
performed before the effective date of this AD using any service 
information specified in paragraphs (n)(i) through (n)(iii) of this 
AD.
    (i) Boeing Service Bulletin 737-53-1058, Revision 1, dated March 
5, 1987.
    (ii) Boeing Service Bulletin 737-53-1058, Revision 2, dated 
December 7, 1989.
    (iii) Boeing Service Bulletin 737-53-1058, Revision 3, dated 
March 11, 1993.

(o) Exceptions to the Service Information

    (1) Where Boeing Service Bulletin 737-53-1058, Revision 4, dated 
January 9, 2014, specifies a compliance time ``after the Revision 4 
date of this service bulletin,'' this AD requires compliance within 
the specified compliance time ``after the effective date of this 
AD.''
    (2) Where Boeing Service Bulletin 737-53-1058, Revision 4, dated 
January 9, 2014, specifies to contact Boeing for repair 
instructions: Before further flight, repair using a method approved 
in accordance with the procedures specified in paragraph (q) of this 
AD.

(p) Post-Repair and Post-Modification Inspections for Group 3 Through 
Group 5 Airplanes Not Required

    The post-repair and post-modification inspections specified in 
Table 4 of paragraph 1.E., ``Compliance,'' of Boeing Service 
Bulletin 737-53-1058, Revision 4, dated January 9, 2014, are not 
required by this AD.

    Note 1 to paragraph (p) of this AD:  The post-repair and post-
modification inspections specified in Table 4 of paragraph 1.E., 
``Compliance,'' of Boeing Service Bulletin 737-53-1058, Revision 4, 
dated January 9, 2014, may be used in support of compliance with 
section 121.1109(c)(2) or 129.109(b)(2) of the Federal Aviation 
Regulations (14 CFR 121.1109(c)(2) or 14 CFR 129.109(b)(2)).

(q) 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 (r)(1) of this AD. 
Information may be emailed to: 9-ANM-Seattle-ACO-AMOC-Requests@faa.gov.

[[Page 74603]]

    (2) Before using any approved AMOC, notify your appropriate 
principal inspector, or lacking a principal inspector, the manager 
of the local flight standards district office/certificate holding 
district office.
    (3) An AMOC that provides an acceptable level of safety may be 
used for any repair required by this AD if it is approved by the 
Boeing Commercial Airplanes Organization Designation Authorization 
(ODA) that has been authorized by the Manager, Seattle ACO, to make 
those findings. For a repair method to be approved, the repair must 
meet the certification basis of the airplane, and the approval must 
specifically refer to this AD.

(r) Related Information

    (1) For more information about this AD, contact Nenita Odesa, 
Aerospace Engineer, Airframe Branch, ANM-120L, FAA, Los Angeles 
Aircraft Certification Office, 3960 Paramount Boulevard, Lakewood, 
CA 90712-4137; phone: (562) 627-5234; fax: (562) 627-5210; email: 
nenita.odesa@faa.gov.
    (2) Service information identified in this AD that is not 
incorporated by reference is available at the addresses specified in 
paragraphs (s)(3) and (s)(4) of this AD.

(s) 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 Service Bulletin 737-53-1058, Revision 4, dated 
January 9, 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 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 December 5, 2014.
Michael J. Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2014-29190 Filed 12-15-14; 8:45 am]
BILLING CODE 4910-13-P