Airworthiness Directives; The Boeing Company Airplanes, 3527-3530 [2015-00962]

Download as PDF Federal Register / Vol. 80, No. 15 / Friday, January 23, 2015 / Proposed Rules thermography inspection of the complete side shell panels to identify and mark the repair locations for disbonding or damage, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300– 55–6050; or A310–55–2051; both Revision 01, dated August 20, 2014; as applicable. (h) Related Investigative Actions/Repair or Replace If any disbonding or damage is found during any inspection required by paragraph (g)(1) or (g)(2) of this AD: Do the actions required by paragraphs (h)(1) and (h)(2) of this AD, as applicable. (1) At the time specified in paragraph 1.E., ‘‘Compliance,’’ of Airbus Service Bulletin A300–55–6050; or A310–55–2051; both Revision 01, dated August 20, 2014; as applicable, except as required by paragraph (j)(2) of this AD; do the applicable related investigative actions identified in Tables 3, 4A, 4B, 4C, 4D, and 5 of paragraph 1.E., ‘‘Compliance,’’ of Airbus Service Bulletin A300–55–6050; or A310–55–2051; both Revision 01, dated August 20, 2014; as applicable, to determine the type and extent of the disbonding or damage, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300–55–6050; or A310–55–2051; both Revision 01, dated August 20, 2014; as applicable. Repeat the applicable inspection at the time specified in paragraph 1.E., ‘‘Compliance’’ of Airbus Service Bulletin A300–55–6050; or A310–55– 2051; both Revision 01, dated August 20, 2014; as applicable. (2) Before further flight: Repair any disbonding or damage found during any inspection required by paragraph (h)(1) of this AD, or replace any affected rudder, as applicable, in accordance with the Accomplishment Instructions Airbus Service Bulletin A300–55–6050; or A310–55–2051; both Revision 01, dated August 20, 2014; as applicable, except as required by paragraph (j)(4) of this AD. emcdonald on DSK67QTVN1PROD with PROPOSALS (i) Repair Using SRM Procedure Not Allowed As of the effective date of this AD, do not accomplish a composite side shell panel repair on any rudder using an SRM procedure identified in Figure A–GBBAA (Sheet 01 and 02) or Figure A–GBCAA (Sheet 02) of Airbus Service Bulletin A310–55– 2051; or Figure A–GBBAA (Sheet 01, 02, or 03) or Figure A–GBCAA (Sheet 02 or 04) of Airbus Service Bulletin A300–55–6050; as applicable. (j) Exceptions to Service Information (1) Where Airbus Service Bulletins A300– 55–6050; and A310–55–2051; both dated September 11, 2012; specify a compliance time ‘‘from original service bulletin issue date,’’ this AD requires compliance within the specified compliance time after the effective date of this AD. (2) Where Airbus Service Bulletins A300– 55–6050; and A310–55–2051 both dated September 11, 2012; specify to contact Airbus for appropriate action: 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 VerDate Sep<11>2014 19:56 Jan 22, 2015 Jkt 235001 Airbus’s EASA Design Organization Approval (DOA). (3) Airplanes on which a rudder is installed having a serial number that is not in the range HF–1005 through HF–1323, inclusive; HF–1325, HF–1327, HF–1329, HF– 1331, HF–1332, HF–1340, TS–1324, TS– 1326, TS–1328, TS–1330, TS–1333 through TS–1339, inclusive; TS–1341 through TS– 1420, inclusive; or TS–2001 through TS– 2197, inclusive; are not affected by the requirements of paragraphs (g) and (h) of this AD, provided that no repairs have been done on the composite side shell panel of that rudder since installation in accordance with the applicable structural repair manual (SRM). (4) The compliance time for the initial detailed inspection of the restored area for loose or lost tape identified in Tables 3 and 4 of paragraph 1.E., ‘‘Compliance,’’ of Airbus Service Bulletins A300–55–6050 and A310– 55–2051, both Revision 01, dated August 20, 2014; specifies ‘‘within 500 FH or 4 months after closing holes.’’ This AD requires this action within 500 flight hours or 4 months, whichever occurs later after the holes are closed. (k) Credit for Previous Actions This paragraph provides credit for actions required by paragraphs (g) and (h) of this AD, if those actions were performed before the effective date of this AD using Airbus Service Bulletin A300–55–6050; or A310–55–2051; both dated September 11, 2012; as applicable; which are not incorporated by reference in this AD. 3527 116, Transport Airplane Directorate, FAA; or EASA; or Airbus’s EASA DOA. If approved by the DOA, the approval must include the DOA-authorized signature. (n) Related Information (1) Refer to Mandatory Continuing Airworthiness Information EASA Airworthiness Directive 2014–0026, dated January 28, 2014, for related information. This MCAI may be found in the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA–2014–1045. (2) For service information identified in this AD, contact Airbus SAS, Airworthiness Office—EAW, 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. You may view this service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425–227–1221. Issued in Renton, Washington, on January 13, 2015. John P. Piccola, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2015–00946 Filed 1–22–15; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION (l) Parts Installation Limitations As of the effective date of this AD, no person may install any affected rudder on any airplane, unless the actions required by paragraphs (g) and (h) of this AD have been accomplished. Federal Aviation Administration (m) 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: Dan Rodina, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA 1601 Lind Avenue SW., Renton, WA 98057–3356; telephone 425–227–2125; 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– RIN 2120–AA64 PO 00000 Frm 00030 Fmt 4702 Sfmt 4702 14 CFR Part 39 [Docket No. FAA–2015–0075; Directorate Identifier 2014–NM–202–AD] Airworthiness Directives; The Boeing Company Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: We propose to supersede Airworthiness Directive (AD) 2013–26– 08, which applies to certain The Boeing Company Model 737–600, –700, –700C, –800, –900, and –900ER series airplanes. AD 2013–26–08 currently requires inspecting the orientation of both sides of the coil cord connector keyways of the number 2 windows on the flight deck; re-clocking the connector keyways, if necessary; and replacing the coil cord assemblies on both number 2 windows on the flight deck. Since we issued AD 2013–26–08, we have determined that additional airplanes are subject to the identified unsafe condition. This proposed AD would add airplanes to the applicability. We are proposing this AD SUMMARY: E:\FR\FM\23JAP1.SGM 23JAP1 3528 Federal Register / Vol. 80, No. 15 / Friday, January 23, 2015 / Proposed Rules to prevent arcing, smoke, and fire in the flight deck, which could lead to injuries to or incapacitation of the flightcrew. DATES: We must receive comments on this proposed AD by March 9, 2015. 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 proposed AD, contact Boeing Commercial Airplanes, Attention: Data & Services Management, P.O. Box 3707, MC 2H–65, Seattle, WA 98124–2207; telephone 206–544–5000, extension 1; fax 206–766–5680; Internet https:// www.myboeingfleet.com. You may view this service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425–227–1221. 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–2015–0075; Directorate Identifier 2014–NM–202–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. Examining the AD Docket You may examine the AD docket on the Internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2015– 0075; 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 Discussion On December 20, 2013, we issued AD 2013–26–08, Amendment 39–17717 (79 FR 545, January 6, 2014), for certain The Boeing Company Model 737–600, –700, –700C, –800, –900, and –900ER series airplanes. AD 2013–26–08 requires inspecting the orientation of both sides of the coil cord connector keyways of the number 2 windows on the flight deck; re-clocking the connector keyways, if necessary; and replacing the coil cord assemblies on both number 2 windows on the flight deck. AD 2013– 26–08 resulted from reports of arcing available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: Frank Carreras, Aerospace Engineer, Systems and Equipment Branch, ANM– 130S, FAA, Seattle Aircraft Certification Office (ACO), 1601 Lind Avenue SW., Renton, WA 98057–3356; phone: 425– 917–6442; fax: 425–917–6590; email: frank.carreras@faa.gov. SUPPLEMENTARY INFORMATION: and smoke at the left number 2 window in the flight deck. We issued AD 2013– 26–08 to prevent arcing, smoke, and fire in the flight deck, which could lead to injuries to or incapacitation of the flightcrew. Actions Since AD 2013–26–08, Amendment 39–17717 (79 FR 545, January 6, 2014) Was Issued In AD 2013–26–08, Amendment 39– 17717 (79 FR 545, January 6, 2014), a commenter to the SNPRM (77 FR 41931, July 17, 2012) requested that we add additional airplanes to the applicability. We determined that further delay of AD 2013–26–08 was not appropriate in light of the identified unsafe condition that existed on the airplanes specified in the applicability of AD 2013–26–08. We stated that we might consider additional rulemaking in the future. We now have determined that further rulemaking is indeed necessary, and this proposed AD follows from that determination. FAA’s Determination We are proposing this AD because we evaluated all the relevant information and determined the unsafe condition described previously is likely to exist or develop in other products of the same type design. Proposed AD Requirements This proposed AD would retain all requirements of AD 2013–26–08, Amendment 39–17717 (79 FR 545, January 6, 2014). This proposed AD would add Group 3 airplanes, as identified in Boeing Special Attention Service Bulletin 737–30–1058, Revision 5, dated April 24, 2013, to the applicability. Costs of Compliance We estimate that this proposed AD affects 718 airplanes of U.S. registry. We estimate the following costs to comply with this proposed AD: ESTIMATED COSTS emcdonald on DSK67QTVN1PROD with PROPOSALS Keyway inspection and installation (Group1, Configuration 1 airplanes) [actions retained from AD 2013-26-08, Amendment 39-17717 (79 FR 545, January 6, 2014)]. Adjustment of receptacles (Group 1, Configuration 2, Group 2, and Group 3 airplanes) [actions retained from AD 2013-26-08, Amendment 39-17717 (79 FR 545, January 6, 2014)]. 6 work-hours × $85 per hour = $510. $1,608 $2,118 ............... 712 $1,508,016. 4 work-hours × $85 per hour = $340. $0 $340 .................. 410 $139,400. 19:56 Jan 22, 2015 Jkt 235001 PO 00000 Frm 00031 Fmt 4702 Sfmt 4702 Cost per product Cost on U.S. operators Labor cost VerDate Sep<11>2014 Parts cost Number of airplanes Action E:\FR\FM\23JAP1.SGM 23JAP1 3529 Federal Register / Vol. 80, No. 15 / Friday, January 23, 2015 / Proposed Rules ESTIMATED COSTS—Continued Action Labor cost Coil cord inspection (Group 1, Configuration 3, and Group 2 airplanes) [actions retained from AD 2013-26-08, Amendment 39-17717 (79 FR 545, January 6, 2014)]. 1 work-hour × $85 per hour = $85 per coil cord. We estimate the following costs to do any necessary replacements that would Parts cost Cost per product $0 $85 per coil cord be required based on the results of the proposed inspection. We have no way of Number of airplanes 404 Cost on U.S. operators $34,340 per coil cord. determining the number of aircraft that might need these replacements: ON-CONDITION COSTS Action Labor cost Replacement ........................ 3 work-hours × $85 per hour = $255 per coil cord assembly. According to the manufacturer, some of the costs of this 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. Parts cost $1,735 per coil cord assembly. (b) Affected ADs This AD replaces AD 2013–26–08, Amendment 39–17717 (79 FR 545, January 6, 2014). List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. (e) Unsafe Condition This AD was prompted by reports of arcing and smoke at the left number 2 window in the flight deck. We are issuing this AD to prevent arcing, smoke, and fire in the flight deck, which could lead to injuries to or incapacitation of the flightcrew. 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 1. The authority citation for part 39 continues to read as follows: ■ Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] emcdonald on DSK67QTVN1PROD with PROPOSALS ■ 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. The Boeing Company: Docket No. FAA– 2015–0075; Directorate Identifier 2014– NM–202–AD. 19:56 Jan 22, 2015 Jkt 235001 $1,990 per coil cord assembly. 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. Regulatory Findings VerDate Sep<11>2014 Cost per product 2. The FAA amends § 39.13 by removing Airworthiness Directive (AD) 2013–26–08, Amendment 39–17717 (79 FR 545, January 6, 2014), and adding the following new AD: (a) Comments Due Date The FAA must receive comments on this AD action by March 9, 2015. PO 00000 Frm 00032 Fmt 4702 Sfmt 4702 (c) Applicability This AD applies to The Boeing Company Model 737–600, –700, –700C, –800, –900, and –900ER series airplanes, certificated in any category, as identified in Boeing Special Attention Service Bulletin 737–30–1058, Revision 5, dated April 24, 2013. (d) Subject Air Transport Association (ATA) of America Code 30, Ice and Rain Protection. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Retained Inspection and Replacement for Group 1, Configuration 1, Airplanes This paragraph restates the requirements of paragraph (g) of AD 2013–26–08, Amendment 39–17717 (79 FR 545, January 6, 2014), with no changes. For airplanes identified as Group 1, Configuration 1, in Boeing Special Attention Service Bulletin 737–30–1058, Revision 5, dated April 24, 2013: Within 48 months after February 10, 2014 (the effective date of AD 2013–26–08), do the actions specified in paragraphs (g)(1) and (g)(2) of this AD. (1) Do a general visual inspection of the orientation of the coil cord connector keyways on the captain’s and first officer’s sides of the flight compartment, in accordance with the Accomplishment Instructions of Boeing Special Attention Service Bulletin 737–30–1058, Revision 5, dated April 24, 2013, except as specified in E:\FR\FM\23JAP1.SGM 23JAP1 3530 Federal Register / Vol. 80, No. 15 / Friday, January 23, 2015 / Proposed Rules paragraph (k) of this AD. If the orientation is not at the specified position, before further flight, turn the receptacle connector to the correct position, in accordance with the Accomplishment Instructions of Boeing Special Attention Service Bulletin 737–30– 1058, Revision 5, dated April 24, 2013, except as specified in paragraph (k) of this AD. (2) Replace the coil cords with new coil cords on both sides of the flight deck, in accordance with the Accomplishment Instructions of Boeing Special Attention Service Bulletin 737–30–1058, Revision 5, dated April 24, 2013, except as specified in paragraph (k) of this AD. (h) Retained Receptacle Replacement for Group 1, Configuration 2, and Group 2, Configuration 1 Airplanes This paragraph restates the requirements of paragraph (h) of AD 2013–26–08, Amendment 39–17717 (79 FR 545, January 6, 2014), with no changes. For airplanes identified as Group 1, Configuration 2, and Group 2, Configuration 1, in Boeing Special Attention Service Bulletin 737–30–1058, Revision 5, dated April 24, 2013: Within 48 months after February 10, 2014 (the effective date of AD 2013–26–08), install the receptacle connector with changed keyway position on both sides of the flight deck, in accordance with the Accomplishment Instructions of Boeing Special Attention Service Bulletin 737–30–1058, Revision 5, dated April 24, 2013, except as specified in paragraph (k) of this AD. emcdonald on DSK67QTVN1PROD with PROPOSALS (i) Retained Coil Cord Inspection and Corrective Action This paragraph restates the requirements of paragraph (i) of AD 2013–26–08, Amendment 39–17717 (79 FR 545, January 6, 2014), with no changes. For airplanes identified as Group 1, Configuration 3, and Group 2, Configuration 2, in Boeing Special Attention Service Bulletin 737–30–1058, Revision 5, dated April 24, 2013: Within 48 months after February 10, 2014 (the effective date of AD 2013–26–08), do a general visual inspection for rubbing damage of the coil cord on the captain’s and first officer’s sides of the flight compartment, in accordance with the Accomplishment Instructions of Boeing Special Attention Service Bulletin 737–30– 1058, Revision 5, dated April 24, 2013, except as specified in paragraph (k) of this AD. If any rubbing damage is found: Before further flight, replace the coil cord with a new coil cord, in accordance with the Accomplishment Instructions of Boeing Special Attention Service Bulletin 737–30– 1058, Revision 5, dated April 24, 2013, except as specified in paragraph (k) of this AD. (j) New Requirements of This AD: Receptacle Replacement for Group 3 Airplanes For airplanes identified as Group 3 in Boeing Special Attention Service Bulletin 737–30–1058, Revision 5, dated April 24, 2013: Within 48 months after the effective date of this AD, install the receptacle connector with changed keyway position on both sides of the flight deck, in accordance with the Accomplishment Instructions of Boeing Special Attention Service Bulletin VerDate Sep<11>2014 19:56 Jan 22, 2015 Jkt 235001 737–30–1058, Revision 5, dated April 24, 2013, except as specified in paragraph (k) of this AD. (k) Exceptions to Boeing Special Attention Service Bulletin 737–30–1058, Revision 5, Dated April 24, 2013 (1) This paragraph restates the provisions of paragraph (j)(1) of AD 2013–26–08, Amendment 39–17717 (79 FR 545, January 6, 2014), with no changes. In the circuit breaker tables of the Work Instructions of Boeing Special Attention Service Bulletin 737–30– 1058, Revision 5, dated April 24, 2013, the panel number for circuit breaker C00393 is incorrectly identified as ‘‘P6–12.’’ The correct panel number reference for circuit breaker C00393, ‘‘WINDOW HEAT POWER RIGHT SIDE,’’ is P6–11. (2) This paragraph restates the provisions of paragraph (j)(2) of AD 2013–26–08, Amendment 39–17717 (79 FR 545, January 6, 2014), with no changes. In paragraph 3.B. of the Work Instructions of Boeing Special Attention Service Bulletin 737–30–1058, Revision 5, dated April 24, 2013, the description for Part 3 of the Work Instructions is identified as ‘‘PART 3: RECEPTACLE CONNECTOR POSITION CHANGE,’’ which is incorrect. The correct description for Part 3 of the Work Instructions is ‘‘PART 3: COIL CORD INSPECTION AND REPLACEMENT IF DAMAGE IS FOUND.’’ (3) This paragraph restates the provisions of paragraph (j)(3) of AD 2013–26–08, Amendment 39–17717 (79 FR 545, January 6, 2014), with no changes. In Figures 13 and 14, in paragraph 3.B. of the Work Instructions of Boeing Special Attention Service Bulletin 737–30–1058, Revision 5, dated April 24, 2013, the note before the step tables misidentifies certain parts and airplane groups. The note should read: NOTE: Group 1 and Group 2 airplanes have the connector receptacle identified as D10572. Group 3 airplanes have the connector receptacle identified as D10560. Except for Group 1 airplanes, a wire diagram change is not necessary and not shown in this service bulletin. (l) Credit for Previous Actions This paragraph restates the provisions of paragraph (k) of AD 2013–26–08, Amendment 39–17717 (79 FR 545, January 6, 2014), with no changes. This paragraph provides credit for the replacement required by paragraph (g)(2) of this AD, if the replacement was performed before February 10, 2014 (the effective date of AD 2013–26– 08), using the service information specified in paragraph (l)(1), (l)(2), (l)(3), (l)(4), or (l)(5) of this AD, provided that the actions required by paragraph (h) of this AD are done in accordance with Boeing Special Attention Service Bulletin 737–30–1058, Revision 4, dated November 3, 2011; or Boeing Special Attention Service Bulletin 737–30–1058, Revision 5, dated April 24, 2013; for airplanes in Group 1, Configuration 2, and Group 2. (1) Boeing Service Bulletin 737–30–1058, dated July 27, 2006, which is not incorporated by reference in this AD. PO 00000 Frm 00033 Fmt 4702 Sfmt 9990 (2) Boeing Service Bulletin 737–30–1058, Revision 1, dated June 18, 2007, which is not incorporated by reference in this AD. (3) Boeing Service Bulletin 737–30–1058, Revision 2, dated February 13, 2009, which is not incorporated by reference in this AD. (4) Boeing Special Attention Service Bulletin 737–30–1058, Revision 3, dated July 7, 2010, which is not incorporated by reference in this AD. (5) Boeing Special Attention Service Bulletin 737–30–1058, Revision 4, dated November 3, 2011. (m) 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 (n)(1) of this AD. Information may be emailed to: 9-ANM-Seattle-ACO-AMOCRequests@faa.gov. (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) AMOCs approved for AD 2013–26–08, Amendment 39–17717 (79 FR 545, January 6, 2014), are approved as AMOCs for the corresponding provisions of this AD. (4) For airplanes identified as Group 3 in Boeing Special Attention Service Bulletin 737–30–1058, Revision 5, dated April 24, 2013, AMOCs approved for the actions required by paragraph (h) of AD 2013–26–08, Amendment 39–17717 (79 FR 545, January 6, 2014), are approved as AMOCs for the corresponding provisions of paragraph (j) of this AD. (n) Related Information (1) For more information about this AD, contact Frank Carreras, Aerospace Engineer, Systems and Equipment Branch, ANM–130S, FAA, Seattle Aircraft Certification Office (ACO), 1601 Lind Avenue SW., Renton, WA 98057–3356; phone: 425–917–6442; fax: 425– 917–6590; email: frank.carreras@faa.gov. (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. For information on the availability of this material at the FAA, call 425–227–1221. Issued in Renton, Washington, on January 14, 2015. John P. Piccola, Jr., Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2015–00962 Filed 1–22–15; 8:45 am] BILLING CODE 4910–13–P E:\FR\FM\23JAP1.SGM 23JAP1

Agencies

[Federal Register Volume 80, Number 15 (Friday, January 23, 2015)]
[Proposed Rules]
[Pages 3527-3530]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2015-00962]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2015-0075; Directorate Identifier 2014-NM-202-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) 2013-26-
08, which applies to certain The Boeing Company Model 737-600, -700, -
700C, -800, -900, and -900ER series airplanes. AD 2013-26-08 currently 
requires inspecting the orientation of both sides of the coil cord 
connector keyways of the number 2 windows on the flight deck; re-
clocking the connector keyways, if necessary; and replacing the coil 
cord assemblies on both number 2 windows on the flight deck. Since we 
issued AD 2013-26-08, we have determined that additional airplanes are 
subject to the identified unsafe condition. This proposed AD would add 
airplanes to the applicability. We are proposing this AD

[[Page 3528]]

to prevent arcing, smoke, and fire in the flight deck, which could lead 
to injuries to or incapacitation of the flightcrew.

DATES: We must receive comments on this proposed AD by March 9, 2015.

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 proposed AD, contact 
Boeing Commercial Airplanes, Attention: Data & Services Management, 
P.O. Box 3707, MC 2H-65, Seattle, WA 98124-2207; telephone 206-544-
5000, extension 1; fax 206-766-5680; Internet https://www.myboeingfleet.com. You may view this service information at the 
FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. 
For information on the availability of this material at the FAA, call 
425-227-1221.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2015-
0075; 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: Frank Carreras, Aerospace Engineer, 
Systems and Equipment Branch, ANM-130S, FAA, Seattle Aircraft 
Certification Office (ACO), 1601 Lind Avenue SW., Renton, WA 98057-
3356; phone: 425-917-6442; fax: 425-917-6590; email: 
frank.carreras@faa.gov.

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-2015-0075; 
Directorate Identifier 2014-NM-202-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 December 20, 2013, we issued AD 2013-26-08, Amendment 39-17717 
(79 FR 545, January 6, 2014), for certain The Boeing Company Model 737-
600, -700, -700C, -800, -900, and -900ER series airplanes. AD 2013-26-
08 requires inspecting the orientation of both sides of the coil cord 
connector keyways of the number 2 windows on the flight deck; re-
clocking the connector keyways, if necessary; and replacing the coil 
cord assemblies on both number 2 windows on the flight deck. AD 2013-
26-08 resulted from reports of arcing and smoke at the left number 2 
window in the flight deck. We issued AD 2013-26-08 to prevent arcing, 
smoke, and fire in the flight deck, which could lead to injuries to or 
incapacitation of the flightcrew.

Actions Since AD 2013-26-08, Amendment 39-17717 (79 FR 545, January 6, 
2014) Was Issued

    In AD 2013-26-08, Amendment 39-17717 (79 FR 545, January 6, 2014), 
a commenter to the SNPRM (77 FR 41931, July 17, 2012) requested that we 
add additional airplanes to the applicability. We determined that 
further delay of AD 2013-26-08 was not appropriate in light of the 
identified unsafe condition that existed on the airplanes specified in 
the applicability of AD 2013-26-08. We stated that we might consider 
additional rulemaking in the future. We now have determined that 
further rulemaking is indeed necessary, and this proposed AD follows 
from that determination.

FAA's Determination

    We are proposing this AD because we evaluated all the relevant 
information and determined the unsafe condition described previously is 
likely to exist or develop in other products of the same type design.

Proposed AD Requirements

    This proposed AD would retain all requirements of AD 2013-26-08, 
Amendment 39-17717 (79 FR 545, January 6, 2014). This proposed AD would 
add Group 3 airplanes, as identified in Boeing Special Attention 
Service Bulletin 737-30-1058, Revision 5, dated April 24, 2013, to the 
applicability.

Costs of Compliance

    We estimate that this proposed AD affects 718 airplanes of U.S. 
registry.
    We estimate the following costs to comply with this proposed AD:

                                                                     Estimated Costs
--------------------------------------------------------------------------------------------------------------------------------------------------------
                                                                                                                   Number of
                Action                           Labor cost             Parts cost        Cost per product         airplanes     Cost on U.S. operators
--------------------------------------------------------------------------------------------------------------------------------------------------------
Keyway inspection and installation     6 work[dash]hours x $85 per            $1,608  $2,118..................             712  $1,508,016.
 (Group1, Configuration 1 airplanes)    hour = $510.
 [actions retained from AD
 2013[dash]26[dash]08, Amendment
 39[dash]17717 (79 FR 545, January 6,
 2014)].
Adjustment of receptacles (Group 1,    4 work-hours x $85 per hour =              $0  $340....................             410  $139,400.
 Configuration 2, Group 2, and Group    $340.
 3 airplanes) [actions retained from
 AD 2013[dash]26[dash]08, Amendment
 39[dash]17717 (79 FR 545, January 6,
 2014)].

[[Page 3529]]

 
Coil cord inspection (Group 1,         1 work-hour x $85 per hour =               $0  $85 per coil cord.......             404  $34,340 per coil cord.
 Configuration 3, and Group 2           $85 per coil cord.
 airplanes) [actions retained from AD
 2013[dash]26[dash]08, Amendment
 39[dash]17717 (79 FR 545, January 6,
 2014)].
--------------------------------------------------------------------------------------------------------------------------------------------------------

    We estimate the following costs to do any necessary replacements 
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 replacements:

                                               On-Condition Costs
----------------------------------------------------------------------------------------------------------------
               Action                         Labor cost                Parts cost           Cost per product
----------------------------------------------------------------------------------------------------------------
Replacement........................  3 work-hours x $85 per hour  $1,735 per coil cord    $1,990 per coil cord
                                      = $255 per coil cord         assembly.               assembly.
                                      assembly.
----------------------------------------------------------------------------------------------------------------

    According to the manufacturer, some of the costs of this 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.

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) 
2013-26-08, Amendment 39-17717 (79 FR 545, January 6, 2014), and adding 
the following new AD:

The Boeing Company: Docket No. FAA-2015-0075; Directorate Identifier 
2014-NM-202-AD.

(a) Comments Due Date

    The FAA must receive comments on this AD action by March 9, 
2015.

(b) Affected ADs

    This AD replaces AD 2013-26-08, Amendment 39-17717 (79 FR 545, 
January 6, 2014).

(c) Applicability

    This AD applies to The Boeing Company Model 737-600, -700, -
700C, -800, -900, and -900ER series airplanes, certificated in any 
category, as identified in Boeing Special Attention Service Bulletin 
737-30-1058, Revision 5, dated April 24, 2013.

 (d) Subject

    Air Transport Association (ATA) of America Code 30, Ice and Rain 
Protection.

(e) Unsafe Condition

    This AD was prompted by reports of arcing and smoke at the left 
number 2 window in the flight deck. We are issuing this AD to 
prevent arcing, smoke, and fire in the flight deck, which could lead 
to injuries to or incapacitation of the flightcrew.

(f) Compliance

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

(g) Retained Inspection and Replacement for Group 1, Configuration 1, 
Airplanes

    This paragraph restates the requirements of paragraph (g) of AD 
2013-26-08, Amendment 39-17717 (79 FR 545, January 6, 2014), with no 
changes. For airplanes identified as Group 1, Configuration 1, in 
Boeing Special Attention Service Bulletin 737-30-1058, Revision 5, 
dated April 24, 2013: Within 48 months after February 10, 2014 (the 
effective date of AD 2013-26-08), do the actions specified in 
paragraphs (g)(1) and (g)(2) of this AD.
    (1) Do a general visual inspection of the orientation of the 
coil cord connector keyways on the captain's and first officer's 
sides of the flight compartment, in accordance with the 
Accomplishment Instructions of Boeing Special Attention Service 
Bulletin 737-30-1058, Revision 5, dated April 24, 2013, except as 
specified in

[[Page 3530]]

paragraph (k) of this AD. If the orientation is not at the specified 
position, before further flight, turn the receptacle connector to 
the correct position, in accordance with the Accomplishment 
Instructions of Boeing Special Attention Service Bulletin 737-30-
1058, Revision 5, dated April 24, 2013, except as specified in 
paragraph (k) of this AD.
    (2) Replace the coil cords with new coil cords on both sides of 
the flight deck, in accordance with the Accomplishment Instructions 
of Boeing Special Attention Service Bulletin 737-30-1058, Revision 
5, dated April 24, 2013, except as specified in paragraph (k) of 
this AD.

(h) Retained Receptacle Replacement for Group 1, Configuration 2, and 
Group 2, Configuration 1 Airplanes

    This paragraph restates the requirements of paragraph (h) of AD 
2013-26-08, Amendment 39-17717 (79 FR 545, January 6, 2014), with no 
changes. For airplanes identified as Group 1, Configuration 2, and 
Group 2, Configuration 1, in Boeing Special Attention Service 
Bulletin 737-30-1058, Revision 5, dated April 24, 2013: Within 48 
months after February 10, 2014 (the effective date of AD 2013-26-
08), install the receptacle connector with changed keyway position 
on both sides of the flight deck, in accordance with the 
Accomplishment Instructions of Boeing Special Attention Service 
Bulletin 737-30-1058, Revision 5, dated April 24, 2013, except as 
specified in paragraph (k) of this AD.

(i) Retained Coil Cord Inspection and Corrective Action

    This paragraph restates the requirements of paragraph (i) of AD 
2013-26-08, Amendment 39-17717 (79 FR 545, January 6, 2014), with no 
changes. For airplanes identified as Group 1, Configuration 3, and 
Group 2, Configuration 2, in Boeing Special Attention Service 
Bulletin 737-30-1058, Revision 5, dated April 24, 2013: Within 48 
months after February 10, 2014 (the effective date of AD 2013-26-
08), do a general visual inspection for rubbing damage of the coil 
cord on the captain's and first officer's sides of the flight 
compartment, in accordance with the Accomplishment Instructions of 
Boeing Special Attention Service Bulletin 737-30-1058, Revision 5, 
dated April 24, 2013, except as specified in paragraph (k) of this 
AD. If any rubbing damage is found: Before further flight, replace 
the coil cord with a new coil cord, in accordance with the 
Accomplishment Instructions of Boeing Special Attention Service 
Bulletin 737-30-1058, Revision 5, dated April 24, 2013, except as 
specified in paragraph (k) of this AD.

(j) New Requirements of This AD: Receptacle Replacement for Group 3 
Airplanes

    For airplanes identified as Group 3 in Boeing Special Attention 
Service Bulletin 737-30-1058, Revision 5, dated April 24, 2013: 
Within 48 months after the effective date of this AD, install the 
receptacle connector with changed keyway position on both sides of 
the flight deck, in accordance with the Accomplishment Instructions 
of Boeing Special Attention Service Bulletin 737-30-1058, Revision 
5, dated April 24, 2013, except as specified in paragraph (k) of 
this AD.

(k) Exceptions to Boeing Special Attention Service Bulletin 737-30-
1058, Revision 5, Dated April 24, 2013

    (1) This paragraph restates the provisions of paragraph (j)(1) 
of AD 2013-26-08, Amendment 39-17717 (79 FR 545, January 6, 2014), 
with no changes. In the circuit breaker tables of the Work 
Instructions of Boeing Special Attention Service Bulletin 737-30-
1058, Revision 5, dated April 24, 2013, the panel number for circuit 
breaker C00393 is incorrectly identified as ``P6-12.'' The correct 
panel number reference for circuit breaker C00393, ``WINDOW HEAT 
POWER RIGHT SIDE,'' is P6-11.
    (2) This paragraph restates the provisions of paragraph (j)(2) 
of AD 2013-26-08, Amendment 39-17717 (79 FR 545, January 6, 2014), 
with no changes. In paragraph 3.B. of the Work Instructions of 
Boeing Special Attention Service Bulletin 737-30-1058, Revision 5, 
dated April 24, 2013, the description for Part 3 of the Work 
Instructions is identified as ``PART 3: RECEPTACLE CONNECTOR 
POSITION CHANGE,'' which is incorrect. The correct description for 
Part 3 of the Work Instructions is ``PART 3: COIL CORD INSPECTION 
AND REPLACEMENT IF DAMAGE IS FOUND.''
    (3) This paragraph restates the provisions of paragraph (j)(3) 
of AD 2013-26-08, Amendment 39-17717 (79 FR 545, January 6, 2014), 
with no changes. In Figures 13 and 14, in paragraph 3.B. of the Work 
Instructions of Boeing Special Attention Service Bulletin 737-30-
1058, Revision 5, dated April 24, 2013, the note before the step 
tables misidentifies certain parts and airplane groups. The note 
should read:
    NOTE: Group 1 and Group 2 airplanes have the connector 
receptacle identified as D10572. Group 3 airplanes have the 
connector receptacle identified as D10560. Except for Group 1 
airplanes, a wire diagram change is not necessary and not shown in 
this service bulletin.

(l) Credit for Previous Actions

    This paragraph restates the provisions of paragraph (k) of AD 
2013-26-08, Amendment 39-17717 (79 FR 545, January 6, 2014), with no 
changes. This paragraph provides credit for the replacement required 
by paragraph (g)(2) of this AD, if the replacement was performed 
before February 10, 2014 (the effective date of AD 2013-26-08), 
using the service information specified in paragraph (l)(1), (l)(2), 
(l)(3), (l)(4), or (l)(5) of this AD, provided that the actions 
required by paragraph (h) of this AD are done in accordance with 
Boeing Special Attention Service Bulletin 737-30-1058, Revision 4, 
dated November 3, 2011; or Boeing Special Attention Service Bulletin 
737-30-1058, Revision 5, dated April 24, 2013; for airplanes in 
Group 1, Configuration 2, and Group 2.
    (1) Boeing Service Bulletin 737-30-1058, dated July 27, 2006, 
which is not incorporated by reference in this AD.
    (2) Boeing Service Bulletin 737-30-1058, Revision 1, dated June 
18, 2007, which is not incorporated by reference in this AD.
    (3) Boeing Service Bulletin 737-30-1058, Revision 2, dated 
February 13, 2009, which is not incorporated by reference in this 
AD.
    (4) Boeing Special Attention Service Bulletin 737-30-1058, 
Revision 3, dated July 7, 2010, which is not incorporated by 
reference in this AD.
    (5) Boeing Special Attention Service Bulletin 737-30-1058, 
Revision 4, dated November 3, 2011.

 (m) 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 (n)(1) of this AD. 
Information may be emailed to: 9-ANM-Seattle-ACO-AMOC-Requests@faa.gov.
    (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) AMOCs approved for AD 2013-26-08, Amendment 39-17717 (79 FR 
545, January 6, 2014), are approved as AMOCs for the corresponding 
provisions of this AD.
    (4) For airplanes identified as Group 3 in Boeing Special 
Attention Service Bulletin 737-30-1058, Revision 5, dated April 24, 
2013, AMOCs approved for the actions required by paragraph (h) of AD 
2013-26-08, Amendment 39-17717 (79 FR 545, January 6, 2014), are 
approved as AMOCs for the corresponding provisions of paragraph (j) 
of this AD.

(n) Related Information

    (1) For more information about this AD, contact Frank Carreras, 
Aerospace Engineer, Systems and Equipment Branch, ANM-130S, FAA, 
Seattle Aircraft Certification Office (ACO), 1601 Lind Avenue SW., 
Renton, WA 98057-3356; phone: 425-917-6442; fax: 425-917-6590; 
email: frank.carreras@faa.gov.
    (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. For information on the availability of this 
material at the FAA, call 425-227-1221.

    Issued in Renton, Washington, on January 14, 2015.
John P. Piccola, Jr.,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2015-00962 Filed 1-22-15; 8:45 am]
BILLING CODE 4910-13-P