Airworthiness Directives; The Boeing Company Airplanes, 8568-8571 [2015-02925]

Download as PDF 8568 Federal Register / Vol. 80, No. 32 / Wednesday, February 18, 2015 / Proposed Rules 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] 2. The FAA amends § 39.13 by adding the following new airworthiness directive (AD): ■ Airbus: Docket No. FAA–2015–0242; Directorate Identifier 2014–NM–100–AD. (a) Comments Due Date We must receive comments by April 6, 2015. (b) Affected ADs None. (c) Applicability This AD applies to the Airbus airplanes identified in paragraphs (c)(1), (c)(2), and (c)(3) of this AD, certificated in any category. (1) Model A300 B4–603, B4–605R, B4–620, B4–622, and B4–622R airplanes, all manufacturer serial numbers. (2) Model A300 C4–605R Variant F airplanes, all manufacturer serial numbers. (3) Model A300F4–605R airplanes, all manufacturer serial numbers, except those on which Airbus Modification 12699 was embodied in production. (d) Subject Air Transport Association (ATA) of America Code 53, Fuselage. (e) Reason This AD was prompted by the manufacturer’s review of all repairs accomplished using the structural repair manual. This review was done using revised fatigue and damage tolerance calculations. We are issuing this AD to detect and correct previous incomplete or inadequate repairs to the surrounding panels of the left and right forward passenger doors and the fail-safe ring, which could negatively affect the structural integrity of the airplane. mstockstill on DSK4VPTVN1PROD with PROPOSALS (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Inspection At the time specified in paragraph (g)(1) or (g)(2) of this AD, whichever is later: Do a detailed inspection of the surrounding panels of the left and right forward passenger doors to determine if any repairs have been done, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300– 53–6173, Revision 01, dated February 28, 2014. (1) Prior to the accumulation of 30,000 total flight cycles or 67,500 total flight hours, whichever occurs first. (2) Within 28 months after the effective date of this AD. VerDate Sep<11>2014 17:51 Feb 17, 2015 Jkt 235001 (h) Identification of Repairs If any affected repair is found during the inspection required by paragraph (g) of this AD: Before further flight, identify the reworked area(s), the percentage of the rework, and the limits of the rework, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300– 53–6173, Revision 01, dated February 28, 2014. (i) Corrective Actions During the repair identification required by paragraph (h) of this AD, if any rework is found that is outside the allowable damage limits specified in Airbus Service Bulletin A300–53–6173, Revision 01, dated February 28, 2014: Before further flight, rework or repair, as applicable, using a method approved by the Manager, International Branch, ANM–116, Transport Airplane Directorate, FAA; the European Aviation Safety Agency (EASA); or Airbus’s EASA Design Organization Approval (DOA). (j) Exception to Service Information Specifications Although Airbus Service Bulletin A300– 53–6173, Revision 01, dated February 28, 2014, specifies to contact Airbus for repair instructions, and specifies that action as ‘‘RC’’ (Required for Compliance), this AD requires repair before further flight using a method approved by the Manager, International Branch, ANM–116, Transport Airplane Directorate, FAA; EASA; or Airbus’s EASA DOA. (k) Credit for Previous Actions This paragraph provides credit for the actions required by paragraphs (g) and (h) of this AD, if those actions were performed before the effective date of this AD using Airbus Service Bulletin A300–53–6173, dated August 1, 2013, which is not incorporated by reference in this AD. (l) 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–116– AMOC–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. The AMOC approval letter must specifically reference this AD. (2) Required for Compliance (RC): Except as required by paragraph (j) of this AD, if the PO 00000 Frm 00008 Fmt 4702 Sfmt 4702 service information contains procedures or tests that are identified as RC, those procedures and tests must be done to comply with this AD; any procedures and tests that are not identified as RC are recommended. Those procedures and tests that are not identified as RC may be deviated from using accepted methods in accordance with the operator’s maintenance or inspection program without obtaining approval of an AMOC, provided the procedures and tests identified as RC can be done and the airplane can be put back in a serviceable condition. Any substitutions or changes to procedures or tests identified as RC require approval of an AMOC. (3) 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; the EASA; or Airbus’s EASA DOA. If approved by the DOA, the approval must include the DOA-authorized signature. (m) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA Airworthiness Directive 2014–0101, dated May 2, 2014, for related information. This MCAI may be found in the AD docket on the Internet at https://www.regulations.gov by searching for and locating Docket No. FAA– 2015–0242. (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 https://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 February 2, 2015. Dionne Palermo, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2015–02920 Filed 2–17–15; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2015–0245; Directorate Identifier 2014–NM–135–AD] RIN 2120–AA64 Airworthiness Directives; The Boeing Company Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: E:\FR\FM\18FEP1.SGM 18FEP1 Federal Register / Vol. 80, No. 32 / Wednesday, February 18, 2015 / Proposed Rules We propose to supersede Airworthiness Directive (AD) 2012–24– 10, which applies to certain The Boeing Company Model 747–400 and -400F series airplanes. AD 2012–24–10 currently requires installing new software, replacing the duct assembly with a new duct assembly, making wiring changes, and routing certain wire bundles. Since we issued AD 2012–24– 10, we have received new reports of intermittent or blank displays of a certain integrated display unit (IDU) that were due to an intermittent false ground not addressed by the software installation or wiring changes required by AD 2012–24–10. This proposed AD would retain the requirements of AD 2012–24–10 and would require installing a new or serviceable pressure switch bracket and altitude pressure switch, and add an airplane to the applicability of the existing AD. We are proposing this AD to prevent IDU malfunctions, which could affect the ability of the flightcrew to read primary displays for airplane attitude, altitude, or airspeed, and consequently reduce the ability of the flightcrew to maintain control of the airplane. DATES: We must receive comments on this proposed AD by April 6, 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 https://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 referenced service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425–227–1221. It is also available on the Internet at https:// www.regulations.gov by searching for and locating Docket No. FAA–2015– 0245. mstockstill on DSK4VPTVN1PROD with PROPOSALS SUMMARY: VerDate Sep<11>2014 17:51 Feb 17, 2015 Jkt 235001 Examining the AD Docket You may examine the AD docket on the Internet at https:// www.regulations.gov by searching for and locating Docket No. FAA–2015– 0245; 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: Ana Martinez Hueto, Aerospace Engineer, Cabin Safety and Environmental Systems Branch, ANM–150S, FAA, Seattle Aircraft Certification Office (ACO), 1601 Lind Avenue SW., Renton, WA 98057–3356; phone: 425–917–6592; fax: 425–917–6591; email: ana.m.hueto@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–2015–0245; Directorate Identifier 2014–NM–135–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 https:// 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 November 30, 2012, we issued AD 2012–24–10, Amendment 39–17280 (77 FR 73908, December 12, 2012), for certain The Boeing Company Model 747–400 and -400F series airplanes. AD 2012–24–10 requires installing new software, replacing the duct assembly with a new duct assembly, making wiring changes, and routing certain wire bundles. AD 2012–24–10 resulted from multiple reports of integrated display unit (IDU) malfunctions and mode control panel (MCP) malfunctions. We issued AD 2012–24–10 to prevent IDU malfunctions, which could affect the PO 00000 Frm 00009 Fmt 4702 Sfmt 4702 8569 ability of the flightcrew to read primary displays for airplane attitude, altitude, or airspeed, and consequently reduce the ability of the flightcrew to maintain control of the airplane. Actions Since AD 2012–24–10, Amendment 39–17280 (77 FR 73908, December 12, 2012), Was Issued Since we issued AD 2012–24–10, Amendment 39–17280 (77 FR 73908, December 12, 2012), we have received reports of intermittent or blank displays of a certain IDU in the flight deck that were due to an intermittent false ground not addressed by the software installation or wiring changes required by AD 2012–24–10. The false ground exists on the 25,000 foot altitude analog/ discrete signal of the environmental control systems miscellaneous card, which is a signal that is transmitted to the pack temperature controller. This false ground creates a potential to circumvent the control logic by allowing the 3-way valve to switch air sources before an aircraft reaches an altitude of 25,000 feet, defeating the intent of the corrective actions of AD 2012–24–10. We have determined that the installation of a pressure switch bracket and an altitude pressure switch is needed on the forward side of the station 400 bulkhead to achieve an adequate level of safety. The installation of the altitude pressure switch would change the operating logic for the threeway valve, so that the source for equipment cooling air is changed as the airplane transitions through an altitude of 25,000 feet. Since we issued AD 2012–24–10, Boeing issued Special Attention Service Bulletin 747–21– 2532; and Special Attention Service Bulletin 747–21–2533; both dated February 13, 2014; which contain procedures for installing the pressure switch bracket and altitude pressure switch discussed previously. Since we issued AD 2012–24–10, Amendment 39–17280 (77 FR 73908, December 12, 2012), Boeing also issued a revision to Boeing Alert Service Bulletin 747–21A2523, Revision 1, dated October 3, 2011 (which was referenced as a source of service information in AD 2012–24–10). Boeing Alert Service Bulletin 747–21A2523, Revision 2, dated June 7, 2013, was issued to correct wiring instructions for 747–400BCF airplanes that provide crew rest heat below a 25,000 foot altitude, and to add an airplane configuration having variable number RT061 as Group 21 to the effectivity. The airplane that was added was recently converted from a passenger to a freighter configuration, which this proposed AD addresses. Since this E:\FR\FM\18FEP1.SGM 18FEP1 8570 Federal Register / Vol. 80, No. 32 / Wednesday, February 18, 2015 / Proposed Rules proposed AD adds this new airplane group to the applicability, we have added paragraph (j) to this proposed AD, which provides new compliance times for Group 21 airplanes. Related Service Information Under 1 CFR Part 51 Boeing issued Boeing Alert Service Bulletin 747–21A2523, Revision 2, dated June 7, 2013. This service information describes procedures for changing the wiring and operating logic of the equipment cooling three-way valve and replacing the existing duct assembly with a new duct assembly on the main distribution manifold of the air conditioning system. Boeing also issued Boeing Special Attention Service Bulletin 747–21– 2532, dated February 13, 2014. This service information describes procedures for installing an altitude pressure switch on the forward side of the station 400 bulkhead for the threeway valve of the equipment cooling system. Boeing also issued Boeing Special Attention Service Bulletin 747– 21–2533, dated February 13, 2014. This service information describes procedures for adding a second altitude signal to the switching logic for the three-way valve to provide a second, independent, altitude signal for the equipment cooling system. For information on the procedures and compliance times, see this service information. This service information is reasonably available; see ADDRESSES for ways to access this service information. 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 these same type designs. Proposed AD Requirements This proposed AD would retain all of the requirements of AD 2012–24–10, Amendment 39–17280 (77 FR 73908, December 12, 2012.) This proposed AD would also require installing a pressure switch bracket and altitude pressure switch, and would add an airplane to the applicability. Costs of Compliance We estimate that this proposed AD affects 33 airplanes of U.S. registry. We estimate the following costs to comply with this proposed AD: ESTIMATED COSTS Cost per product Labor cost Duct assembly and replacement wiring changes (retained actions from AD 2012– 24–10, Amendment 39–17280 (77 FR 73908, December 12, 2012). Software changes (retained actions from AD 2012–24–10, Amendment 39–17280 (77 FR 73908, December 12, 2012). Altitude pressure switch installation (new proposed action). 44 work-hours × $85 per hour = $3,740 ........ $20,121 $23,861 $787,413 3 work-hours × $85 per hour = $255 ............. 0 255 8,415 13 work-hours × $85 per hour = $1,105 ........ 5,230 6,335 209,055 According to the manufacturer, some of the costs of this proposed AD may be covered under warranty, thereby reducing the cost impact on affected individuals. We do not control warranty coverage for affected individuals. As a result, we have included all costs in our cost estimate. products identified in this rulemaking action. mstockstill on DSK4VPTVN1PROD with PROPOSALS 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 VerDate Sep<11>2014 17:51 Feb 17, 2015 Jkt 235001 Parts cost Cost on U.S. operators 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. PO 00000 Frm 00010 Fmt 4702 Sfmt 4702 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 1. The authority citation for part 39 continues to read as follows: ■ Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The FAA amends § 39.13 by removing Airworthiness Directive (AD) 2012–24–10, Amendment 39–17280 (77 FR 73908, December 12, 2012), and adding the following new AD: ■ The Boeing Company: Docket No. FAA– 2015–0245; Directorate Identifier 2014– NM–135–AD. (a) Comments Due Date The FAA must receive comments on this AD action by April 6, 2015. E:\FR\FM\18FEP1.SGM 18FEP1 Federal Register / Vol. 80, No. 32 / Wednesday, February 18, 2015 / Proposed Rules (b) Affected ADs This AD replaces AD 2012–24–10, Amendment 39–17280 (77 FR 73908, December 12, 2012). (c) Applicability This AD applies to The Boeing Company Model 747–400 and –400F series airplanes, certificated in any category, as identified in Boeing Alert Service Bulletin 747–21A2523, Revision 2, dated June 7, 2013. (d) Subject Air Transport Association (ATA) of America Code 21, Air Conditioning; 31, Instruments. (e) Unsafe Condition This AD was prompted by reports of intermittent or blank displays of a certain integrated display unit (IDU) in the flight deck. We are issuing this AD to prevent IDU malfunctions, which could affect the ability of the flightcrew to read primary displays for airplane attitude, altitude, or airspeed, and consequently reduce the ability of the flightcrew to maintain control of the airplane. mstockstill on DSK4VPTVN1PROD with PROPOSALS (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Retained Software Update This paragraph restates the requirements of paragraph (g) of AD 2012–24–10, Amendment 39–17280 (77 FR 73908, December 12, 2012), with revised service information. Within 12 months after January 16, 2013 (the effective date of AD 2012–24– 10), except as provided by paragraph (j) of this AD: Install integrated display system software, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 747–21A2523, Revision 1, dated October 3, 2011; or Boeing Alert Service Bulletin 747–21A2523, Revision 2, dated June 7, 2013. As of the effective date of this AD, only Boeing Alert Service Bulletin 747–21A2523, Revision 2, dated June 7, 2013, may be used to accomplish the actions required by this paragraph. Note 1 to paragraph (g) and (j) of this AD: Boeing Alert Service Bulletin 747–21A2523, Revision 1, dated October 3, 2011; and Boeing Alert Service Bulletin 747–21A2523, Revision 2, dated June 7, 2013; refer to Boeing Service Bulletin 747–31–2426, dated July 29, 2010 (for airplanes with Rolls-Royce engines); Boeing Service Bulletin 747–31– 2427, dated July 29, 2010 (for airplanes with General Electric engines); and Boeing Service Bulletin 747–31–2428, dated July 29, 2010 (for airplanes with Pratt & Whitney engines); as additional sources of guidance for the software installation specified by paragraph (g) of this AD. Boeing Service Bulletin 747– 31–2426, dated July 29, 2010; Boeing Service Bulletin 747–31–2427, dated July 29, 2010; and Boeing Service Bulletin 747–31–2428, dated July 29, 2010; are not incorporated by reference in this AD. (h) Retained Duct Assembly Replacement and Wiring Changes This paragraph restates the requirements of paragraph (h) of AD 2012–24–10, VerDate Sep<11>2014 17:51 Feb 17, 2015 Jkt 235001 Amendment 39–17280 (77 FR 73908, December 12, 2012), with revised service information. Within 60 months after January 16, 2013 (the effective date of AD 2012–24– 10), except as provided by paragraph (j) of this AD: Replace the duct assembly with a new duct assembly, do wiring changes, and route certain wire bundles, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 747–21A2523, Revision 1, dated October 3, 2011; or Boeing Alert Service Bulletin 747–21A2523, Revision 2, dated June 7, 2013. As of the effective date of this AD, only Boeing Alert Service Bulletin 747–21A2523, Revision 2, dated June 7, 2013, may be used to accomplish the actions required by this paragraph. (i) New Installation of Pressure Switch Bracket and Altitude Pressure Switch Within 60 months after the effective date of this AD: Install a new or serviceable pressure switch bracket and a new or serviceable altitude pressure switch on the forward side of the station 400 bulkhead, do wiring changes, route certain wire bundles, install a new hose assembly, and perform a leak check and a functional logic test, in accordance with the Accomplishment Instructions of the service information specified in paragraph (i)(1) or (i)(2) of this AD, as applicable. (1) For Model 747–400F series airplanes: Boeing Alert Service Bulletin 747–21–2532, dated February 13, 2014. (2) For Model 747–400BCF series airplanes: Boeing Alert Service Bulletin 747– 21–2533, dated February 13, 2014. (j) Actions for Group 21 Airplanes For Group 21 airplanes, as identified in Boeing Alert Service Bulletin 747–21A2523, Revision 2, dated June 7, 2013, do the actions specified in paragraphs (j)(1) and (j)(2) of this AD, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 747–21A2523, Revision 2, dated June 7, 2013. (1) Within 12 months after the effective date of this AD, install integrated display system software. (2) Within 60 months after the effective date of this AD, replace the duct assembly with a new duct assembly, do wiring changes, and route certain wire bundles. (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 Boeing Alert Service Bulletin 747–21A2523, Revision 1, dated October 3, 2011. (l) Alternative Methods of Compliance (AMOCs) (1) The Manager, Seattle Aircraft Certification Office (ACO), FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the manager of the ACO, send it to the attention of the person identified in PO 00000 Frm 00011 Fmt 4702 Sfmt 4702 8571 paragraph (m)(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) An AMOC that provides an acceptable level of safety may be used for any repair required by this AD if it is approved by 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. (4) AMOCs approved for AD 2012–24–10, Amendment 39–17280 (77 FR 73908, December 12, 2012), are approved as AMOCs for the corresponding provisions of paragraphs (g) and (h) of this AD. (m) Related Information (1) For more information about this AD, contact Ana Martinez Hueto, Aerospace Engineer, Cabin Safety and Environmental Systems Branch, ANM–150S, FAA, Seattle Aircraft Certification Office (ACO), 1601 Lind Avenue SW., Renton, WA 98057–3356; phone: 425–917–6592; fax: 425–917–6591; email: ana.m.hueto@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, Washington. For information on the availability of this material at the FAA, call 425–227–1221. Issued in Renton, Washington, on February 2, 2015. Dionne Palermo, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2015–02925 Filed 2–17–15; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2015–0243; Directorate Identifier 2014–NM–114–AD] RIN 2120–AA64 Airworthiness Directives; Airbus Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: We propose to adopt a new airworthiness directive (AD) for all SUMMARY: E:\FR\FM\18FEP1.SGM 18FEP1

Agencies

[Federal Register Volume 80, Number 32 (Wednesday, February 18, 2015)]
[Proposed Rules]
[Pages 8568-8571]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2015-02925]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2015-0245; Directorate Identifier 2014-NM-135-AD]
RIN 2120-AA64


Airworthiness Directives; The Boeing Company Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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[[Page 8569]]

SUMMARY: We propose to supersede Airworthiness Directive (AD) 2012-24-
10, which applies to certain The Boeing Company Model 747-400 and -400F 
series airplanes. AD 2012-24-10 currently requires installing new 
software, replacing the duct assembly with a new duct assembly, making 
wiring changes, and routing certain wire bundles. Since we issued AD 
2012-24-10, we have received new reports of intermittent or blank 
displays of a certain integrated display unit (IDU) that were due to an 
intermittent false ground not addressed by the software installation or 
wiring changes required by AD 2012-24-10. This proposed AD would retain 
the requirements of AD 2012-24-10 and would require installing a new or 
serviceable pressure switch bracket and altitude pressure switch, and 
add an airplane to the applicability of the existing AD. We are 
proposing this AD to prevent IDU malfunctions, which could affect the 
ability of the flightcrew to read primary displays for airplane 
attitude, altitude, or airspeed, and consequently reduce the ability of 
the flightcrew to maintain control of the airplane.

DATES: We must receive comments on this proposed AD by April 6, 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 https://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 referenced service information 
at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., 
Renton, WA. For information on the availability of this material at the 
FAA, call 425-227-1221. It is also available on the Internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2015-
0245.

Examining the AD Docket

    You may examine the AD docket on the Internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2015-
0245; 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: Ana Martinez Hueto, Aerospace 
Engineer, Cabin Safety and Environmental Systems Branch, ANM-150S, FAA, 
Seattle Aircraft Certification Office (ACO), 1601 Lind Avenue SW., 
Renton, WA 98057-3356; phone: 425-917-6592; fax: 425-917-6591; email: 
ana.m.hueto@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-2015-0245; 
Directorate Identifier 2014-NM-135-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 https://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 November 30, 2012, we issued AD 2012-24-10, Amendment 39-17280 
(77 FR 73908, December 12, 2012), for certain The Boeing Company Model 
747-400 and -400F series airplanes. AD 2012-24-10 requires installing 
new software, replacing the duct assembly with a new duct assembly, 
making wiring changes, and routing certain wire bundles. AD 2012-24-10 
resulted from multiple reports of integrated display unit (IDU) 
malfunctions and mode control panel (MCP) malfunctions. We issued AD 
2012-24-10 to prevent IDU malfunctions, which could affect the ability 
of the flightcrew to read primary displays for airplane attitude, 
altitude, or airspeed, and consequently reduce the ability of the 
flightcrew to maintain control of the airplane.

Actions Since AD 2012-24-10, Amendment 39-17280 (77 FR 73908, December 
12, 2012), Was Issued

    Since we issued AD 2012-24-10, Amendment 39-17280 (77 FR 73908, 
December 12, 2012), we have received reports of intermittent or blank 
displays of a certain IDU in the flight deck that were due to an 
intermittent false ground not addressed by the software installation or 
wiring changes required by AD 2012-24-10. The false ground exists on 
the 25,000 foot altitude analog/discrete signal of the environmental 
control systems miscellaneous card, which is a signal that is 
transmitted to the pack temperature controller. This false ground 
creates a potential to circumvent the control logic by allowing the 3-
way valve to switch air sources before an aircraft reaches an altitude 
of 25,000 feet, defeating the intent of the corrective actions of AD 
2012-24-10.
    We have determined that the installation of a pressure switch 
bracket and an altitude pressure switch is needed on the forward side 
of the station 400 bulkhead to achieve an adequate level of safety. The 
installation of the altitude pressure switch would change the operating 
logic for the three-way valve, so that the source for equipment cooling 
air is changed as the airplane transitions through an altitude of 
25,000 feet. Since we issued AD 2012-24-10, Boeing issued Special 
Attention Service Bulletin 747-21-2532; and Special Attention Service 
Bulletin 747-21-2533; both dated February 13, 2014; which contain 
procedures for installing the pressure switch bracket and altitude 
pressure switch discussed previously.
    Since we issued AD 2012-24-10, Amendment 39-17280 (77 FR 73908, 
December 12, 2012), Boeing also issued a revision to Boeing Alert 
Service Bulletin 747-21A2523, Revision 1, dated October 3, 2011 (which 
was referenced as a source of service information in AD 2012-24-10). 
Boeing Alert Service Bulletin 747-21A2523, Revision 2, dated June 7, 
2013, was issued to correct wiring instructions for 747-400BCF 
airplanes that provide crew rest heat below a 25,000 foot altitude, and 
to add an airplane configuration having variable number RT061 as Group 
21 to the effectivity. The airplane that was added was recently 
converted from a passenger to a freighter configuration, which this 
proposed AD addresses. Since this

[[Page 8570]]

proposed AD adds this new airplane group to the applicability, we have 
added paragraph (j) to this proposed AD, which provides new compliance 
times for Group 21 airplanes.

Related Service Information Under 1 CFR Part 51

    Boeing issued Boeing Alert Service Bulletin 747-21A2523, Revision 
2, dated June 7, 2013. This service information describes procedures 
for changing the wiring and operating logic of the equipment cooling 
three-way valve and replacing the existing duct assembly with a new 
duct assembly on the main distribution manifold of the air conditioning 
system.
    Boeing also issued Boeing Special Attention Service Bulletin 747-
21-2532, dated February 13, 2014. This service information describes 
procedures for installing an altitude pressure switch on the forward 
side of the station 400 bulkhead for the three-way valve of the 
equipment cooling system. Boeing also issued Boeing Special Attention 
Service Bulletin 747-21-2533, dated February 13, 2014. This service 
information describes procedures for adding a second altitude signal to 
the switching logic for the three-way valve to provide a second, 
independent, altitude signal for the equipment cooling system.
    For information on the procedures and compliance times, see this 
service information. This service information is reasonably available; 
see ADDRESSES for ways to access this service information.

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 these same type 
designs.

Proposed AD Requirements

    This proposed AD would retain all of the requirements of AD 2012-
24-10, Amendment 39-17280 (77 FR 73908, December 12, 2012.) This 
proposed AD would also require installing a pressure switch bracket and 
altitude pressure switch, and would add an airplane to the 
applicability.

Costs of Compliance

    We estimate that this proposed AD affects 33 airplanes of U.S. 
registry.
    We estimate the following costs to comply with this proposed AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                     Cost per      Cost on U.S.
                Action                         Labor cost           Parts cost        product        operators
----------------------------------------------------------------------------------------------------------------
Duct assembly and replacement wiring    44 work-hours x $85 per          $20,121         $23,861        $787,413
 changes (retained actions from AD       hour = $3,740.
 2012-24-10, Amendment 39-17280 (77 FR
 73908, December 12, 2012).
Software changes (retained actions      3 work-hours x $85 per                 0             255           8,415
 from AD 2012-24-10, Amendment 39-       hour = $255.
 17280 (77 FR 73908, December 12,
 2012).
Altitude pressure switch installation   13 work-hours x $85 per            5,230           6,335         209,055
 (new proposed action).                  hour = $1,105.
----------------------------------------------------------------------------------------------------------------

    According to the manufacturer, some of the costs of this proposed 
AD may be covered under warranty, thereby reducing the cost impact on 
affected individuals. We do not control warranty coverage for affected 
individuals. As a result, we have included all costs in our cost 
estimate.

Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to 
issue rules on aviation safety. Subtitle I, Section 106, describes the 
authority of the FAA Administrator. Subtitle VII, Aviation Programs, 
describes in more detail the scope of the Agency's authority.
    We are issuing this rulemaking under the authority described in 
Subtitle VII, Part A, Subpart III, Section 44701, ``General 
requirements.'' Under that section, Congress charges the FAA with 
promoting safe flight of civil aircraft in air commerce by prescribing 
regulations for practices, methods, and procedures the Administrator 
finds necessary for safety in air commerce. This regulation is within 
the scope of that authority because it addresses an unsafe condition 
that is likely to exist or develop on products identified in this 
rulemaking action.

Regulatory Findings

    We have determined that this proposed AD would not have federalism 
implications under Executive Order 13132. This proposed AD would not 
have a substantial direct effect on the States, on the relationship 
between the national Government and the States, or on the distribution 
of power and responsibilities among the various levels of government.
    For the reasons discussed above, I certify that the proposed 
regulation:
    (1) Is not a ``significant regulatory action'' under Executive 
Order 12866,
    (2) Is not a ``significant rule'' under the DOT Regulatory Policies 
and Procedures (44 FR 11034, February 26, 1979),
    (3) Will not affect intrastate aviation in Alaska, and
    (4) Will not have a significant economic impact, positive or 
negative, on a substantial number of small entities under the criteria 
of the Regulatory Flexibility Act.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

The Proposed Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA proposes to amend 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

0
1. The authority citation for part 39 continues to read as follows:

    Authority:  49 U.S.C. 106(g), 40113, 44701.


Sec.  39.13  [Amended]

0
2. The FAA amends Sec.  39.13 by removing Airworthiness Directive (AD) 
2012-24-10, Amendment 39-17280 (77 FR 73908, December 12, 2012), and 
adding the following new AD:

The Boeing Company: Docket No. FAA-2015-0245; Directorate Identifier 
2014-NM-135-AD.

(a) Comments Due Date

    The FAA must receive comments on this AD action by April 6, 
2015.

[[Page 8571]]

(b) Affected ADs

    This AD replaces AD 2012-24-10, Amendment 39-17280 (77 FR 73908, 
December 12, 2012).

(c) Applicability

    This AD applies to The Boeing Company Model 747-400 and -400F 
series airplanes, certificated in any category, as identified in 
Boeing Alert Service Bulletin 747-21A2523, Revision 2, dated June 7, 
2013.

(d) Subject

    Air Transport Association (ATA) of America Code 21, Air 
Conditioning; 31, Instruments.

(e) Unsafe Condition

    This AD was prompted by reports of intermittent or blank 
displays of a certain integrated display unit (IDU) in the flight 
deck. We are issuing this AD to prevent IDU malfunctions, which 
could affect the ability of the flightcrew to read primary displays 
for airplane attitude, altitude, or airspeed, and consequently 
reduce the ability of the flightcrew to maintain control of the 
airplane.

(f) Compliance

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

(g) Retained Software Update

    This paragraph restates the requirements of paragraph (g) of AD 
2012-24-10, Amendment 39-17280 (77 FR 73908, December 12, 2012), 
with revised service information. Within 12 months after January 16, 
2013 (the effective date of AD 2012-24-10), except as provided by 
paragraph (j) of this AD: Install integrated display system 
software, in accordance with the Accomplishment Instructions of 
Boeing Alert Service Bulletin 747-21A2523, Revision 1, dated October 
3, 2011; or Boeing Alert Service Bulletin 747-21A2523, Revision 2, 
dated June 7, 2013. As of the effective date of this AD, only Boeing 
Alert Service Bulletin 747-21A2523, Revision 2, dated June 7, 2013, 
may be used to accomplish the actions required by this paragraph.
    Note 1 to paragraph (g) and (j) of this AD: Boeing Alert Service 
Bulletin 747-21A2523, Revision 1, dated October 3, 2011; and Boeing 
Alert Service Bulletin 747-21A2523, Revision 2, dated June 7, 2013; 
refer to Boeing Service Bulletin 747-31-2426, dated July 29, 2010 
(for airplanes with Rolls-Royce engines); Boeing Service Bulletin 
747-31-2427, dated July 29, 2010 (for airplanes with General 
Electric engines); and Boeing Service Bulletin 747-31-2428, dated 
July 29, 2010 (for airplanes with Pratt & Whitney engines); as 
additional sources of guidance for the software installation 
specified by paragraph (g) of this AD. Boeing Service Bulletin 747-
31-2426, dated July 29, 2010; Boeing Service Bulletin 747-31-2427, 
dated July 29, 2010; and Boeing Service Bulletin 747-31-2428, dated 
July 29, 2010; are not incorporated by reference in this AD.

(h) Retained Duct Assembly Replacement and Wiring Changes

    This paragraph restates the requirements of paragraph (h) of AD 
2012-24-10, Amendment 39-17280 (77 FR 73908, December 12, 2012), 
with revised service information. Within 60 months after January 16, 
2013 (the effective date of AD 2012-24-10), except as provided by 
paragraph (j) of this AD: Replace the duct assembly with a new duct 
assembly, do wiring changes, and route certain wire bundles, in 
accordance with the Accomplishment Instructions of Boeing Alert 
Service Bulletin 747-21A2523, Revision 1, dated October 3, 2011; or 
Boeing Alert Service Bulletin 747-21A2523, Revision 2, dated June 7, 
2013. As of the effective date of this AD, only Boeing Alert Service 
Bulletin 747-21A2523, Revision 2, dated June 7, 2013, may be used to 
accomplish the actions required by this paragraph.

(i) New Installation of Pressure Switch Bracket and Altitude Pressure 
Switch

    Within 60 months after the effective date of this AD: Install a 
new or serviceable pressure switch bracket and a new or serviceable 
altitude pressure switch on the forward side of the station 400 
bulkhead, do wiring changes, route certain wire bundles, install a 
new hose assembly, and perform a leak check and a functional logic 
test, in accordance with the Accomplishment Instructions of the 
service information specified in paragraph (i)(1) or (i)(2) of this 
AD, as applicable.
    (1) For Model 747-400F series airplanes: Boeing Alert Service 
Bulletin 747-21-2532, dated February 13, 2014.
    (2) For Model 747-400BCF series airplanes: Boeing Alert Service 
Bulletin 747-21-2533, dated February 13, 2014.

(j) Actions for Group 21 Airplanes

    For Group 21 airplanes, as identified in Boeing Alert Service 
Bulletin 747-21A2523, Revision 2, dated June 7, 2013, do the actions 
specified in paragraphs (j)(1) and (j)(2) of this AD, in accordance 
with the Accomplishment Instructions of Boeing Alert Service 
Bulletin 747-21A2523, Revision 2, dated June 7, 2013.
    (1) Within 12 months after the effective date of this AD, 
install integrated display system software.
    (2) Within 60 months after the effective date of this AD, 
replace the duct assembly with a new duct assembly, do wiring 
changes, and route certain wire bundles.

(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 Boeing Alert Service 
Bulletin 747-21A2523, Revision 1, dated October 3, 2011.

(l) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, Seattle Aircraft Certification Office (ACO), 
FAA, has the authority to approve AMOCs for this AD, if requested 
using the procedures found in 14 CFR 39.19. In accordance with 14 
CFR 39.19, send your request to your principal inspector or local 
Flight Standards District Office, as appropriate. If sending 
information directly to the manager of the ACO, send it to the 
attention of the person identified in paragraph (m)(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) An AMOC that provides an acceptable level of safety may be 
used for any repair required by this AD if it is approved by 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.
    (4) AMOCs approved for AD 2012-24-10, Amendment 39-17280 (77 FR 
73908, December 12, 2012), are approved as AMOCs for the 
corresponding provisions of paragraphs (g) and (h) of this AD.

(m) Related Information

    (1) For more information about this AD, contact Ana Martinez 
Hueto, Aerospace Engineer, Cabin Safety and Environmental Systems 
Branch, ANM-150S, FAA, Seattle Aircraft Certification Office (ACO), 
1601 Lind Avenue SW., Renton, WA 98057-3356; phone: 425-917-6592; 
fax: 425-917-6591; email: ana.m.hueto@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, Washington. For information on the availability 
of this material at the FAA, call 425-227-1221.

    Issued in Renton, Washington, on February 2, 2015.
Dionne Palermo,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2015-02925 Filed 2-17-15; 8:45 am]
BILLING CODE 4910-13-P
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