Airworthiness Directives; The Boeing Company Airplanes, 46540-46543 [2013-18564]

Download as PDF 46540 Federal Register / Vol. 78, No. 148 / Thursday, August 1, 2013 / Proposed Rules 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 (h) Maintenance Program Revision 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): ■ The Boeing Company: Docket No. FAA– 2013–0666; Directorate Identifier 2013– NM–060–AD. (a) Comments Due Date We must receive comments by September 16, 2013. (b) Affected ADs None. (c) Applicability This AD applies to all The Boeing Company Model 727, 727C, 727–100, 727 –100C, 727–200, and 727–200F series airplanes; certificated in any category. emcdonald on DSK67QTVN1PROD with PROPOSALS (e) Unsafe Condition This AD was prompted by reports indicating that a standard fuel tank access door was located where an impact-resistant access door was required, and stencils were missing from some impact-resistant access doors. We are issuing this AD to prevent foreign object penetration of the fuel tank, which could cause a fuel leak near an ignition source (e.g., hot brakes), consequently leading to a fuel-fed fire. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Inspections Within 72 months after the effective date of this AD, do the actions specified in 16:23 Jul 31, 2013 Jkt 229001 (k) Related Information (1) For more information about this AD, contact Suzanne Lucier, Aerospace Engineer, Propulsion Branch, ANM–140S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue SW., Renton, WA 98057–3356; phone: 425–917–6438; fax: 425–917–6590; email: suzanne.lucier@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 review copies of the 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 July 21, 2013. Stephen P. Boyd, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. Within 60 days after the effective date of this AD, revise the maintenance program to incorporate Critical Design Configuration Control Limitation (CDCCL) Task 57–AWL– 01, ‘‘Impact-Resistant Fuel Tank Access Door,’’ of Section 1, Airworthiness Limitations (AWLs) of Boeing 727–100/200 Airworthiness Limitations (AWLs) Document D6–8766–AWL, Revision September 2012. [FR Doc. 2013–18507 Filed 7–31–13; 8:45 am] (i) No Alternative CDCCLs [Docket No. FAA–2013–0667; Directorate Identifier 2013–NM–062–AD] After accomplishing the revision required by paragraph (h) of this AD, no alternative CDCCLs may be used unless the CDCCLs are approved as an alternative method of compliance in accordance with the procedures specified in paragraph (j) of this AD. (j) Alternative Methods of Compliance (AMOCs) (d) Subject Joint Aircraft System Component (JASC)/ Air Transport Association (ATA) of America Code 28, Fuel. VerDate Mar<15>2010 paragraphs (g)(1) and (g)(2) of this AD, in accordance with the Accomplishment Instructions of Boeing Service Bulletin 727– 28–0134, dated January 12, 2012. (1) Do either a general visual inspection or ultrasonic non-destructive test of the left- and right-hand wing fuel tank access doors to determine whether impact-resistant access doors are installed in the correct locations. If any standard access door is found, before further flight, replace with an impactresistant access door, in accordance with the Accomplishment Instructions of Boeing Service Bulletin 727–28–0134, dated January 12, 2012. (2) Do a general visual inspection of the left- and right-hand wing fuel tank impactresistant access doors to verify stencils and index markers are applied. If a stencil or index marker is missing, before further flight, apply stencil or index marker, as applicable, in accordance with the Accomplishment Instructions of Boeing Service Bulletin 727– 28–0134, dated January 12, 2012. (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 the Related Information section of this AD. Information may be emailed to: 9-ANMSeattle-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 the Boeing Commercial Airplanes Organization Designation Authorization (ODA) that has been authorized by the Manager, Seattle ACO to make those findings. For a repair method to be approved, the repair must meet the certification basis of the airplane, and the approval must specifically refer to this AD. PO 00000 Frm 00013 Fmt 4702 Sfmt 4702 BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 RIN 2120–AA64 Airworthiness Directives; The Boeing Company Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: We propose to adopt a new airworthiness directive (AD) for certain The Boeing Company Model 747–400 airplanes. This proposed AD was prompted by reports of fasteners missing on an airplane undergoing a passenger-to-freighter conversion. This proposed AD would require doing a general visual inspection of the station 1920 splice clip for correct fastener installation, and related investigative and corrective actions if necessary. We are proposing this AD to detect and correct missing or incorrect fasteners, which can lead to cracking and loss of load carrying capacity, resulting in a possible decompression event. DATES: We must receive comments on this proposed AD by September 16, 2013. ADDRESSES: You may send comments, using the procedures found in 14 CFR 11.43 and 11.45, by any of the following methods: SUMMARY: E:\FR\FM\01AUP1.SGM 01AUP1 46541 Federal Register / Vol. 78, No. 148 / Thursday, August 1, 2013 / Proposed Rules • 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 review copies of the referenced service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425–227–1221. Examining the AD Docket You may examine the AD docket on the Internet at http:// www.regulations.gov; or in person at the Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this proposed AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Office (phone: 800–647–5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: Bill Ashforth, Aerospace Engineer, Airframe Branch, ANM–120S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue SW., Renton, WA 98057–3356; phone: 425–917–6432; fax: 425–917– 6590; email: bill.ashforth@faa.gov. SUPPLEMENTARY INFORMATION: Comments Invited We invite you to send any written relevant data, views, or arguments about this proposal. Send your comments to an address listed under the ADDRESSES section. Include ‘‘Docket No. FAA– 2013–0667; Directorate Identifier 2013– NM–062–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 We have received a report of an airplane, while undergoing a passengerto-freighter conversion, missing fasteners on the station 1920 splice clip. The possibility of this discrepancy exists on airplanes already delivered. This condition, if not corrected, could result in cracking and loss of load carrying capacity, resulting in a possible decompression event. Relevant Service Information We reviewed Boeing Alert Service Bulletin 747–53A2844, Revision 1, dated July 30, 2012. For information on the procedures and compliance times, see this service information at http:// www.regulations.gov by searching for Docket No. FAA–2013–0667. 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 require accomplishing the actions specified in the service information described previously, except as discussed under ‘‘Differences Between the Proposed AD and the Service Information.’’ The phrase ‘‘related investigative actions’’ might be used in this proposed AD. ‘‘Related investigative actions’’ are follow-on actions that: (1) Are related to the primary actions, and (2) further investigate the nature of any condition found. Related investigative actions in an AD could include, for example, inspections. In addition, the phrase ‘‘corrective actions’’ might be used in this proposed AD. ‘‘Corrective actions’’ are actions that correct or address any condition found. Corrective actions in an AD could include, for example, repairs. Differences Between the Proposed AD and the Service Information Although the service bulletin specifies that operators may contact the manufacturer for disposition of certain repair conditions, this proposed AD would require operators to repair those conditions in accordance with a method approved by the FAA. Costs of Compliance We estimate that this proposed AD affects 3 airplanes of U.S. registry. We estimate the following costs to comply with this proposed AD: ESTIMATED COSTS Action Labor cost Inspection for correct fastener installation ............ 2 work-hours × $85 per hour = $170 ................... emcdonald on DSK67QTVN1PROD with PROPOSALS We estimate the following costs to do any necessary repairs that would be Parts cost required based on the results of the proposed inspection. We have no way of $0 Cost per product $170 Cost on U.S. operators $510 determining the number of aircraft that might need these repairs: ON-CONDITION COSTS Action Labor cost Inspections for cracking .................................................... Fastener installation .......................................................... Repair ................................................................................ 3 work-hours × $85 per hour = $255 ............................... 2 work-hours × $85 per hour = $170 ............................... 2 work-hours × $85 per hour = $170 ............................... VerDate Mar<15>2010 16:23 Jul 31, 2013 Jkt 229001 PO 00000 Frm 00014 Fmt 4702 Sfmt 4702 E:\FR\FM\01AUP1.SGM Parts cost 01AUP1 $0 0 0 Cost per product $255 170 170 46542 Federal Register / Vol. 78, No. 148 / Thursday, August 1, 2013 / Proposed Rules 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. 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. 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. emcdonald on DSK67QTVN1PROD with PROPOSALS Regulatory Findings We 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 this 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, VerDate Mar<15>2010 16:23 Jul 31, 2013 Jkt 229001 § 39.13 [Amended] 2. The FAA amends § 39.13 by adding the following new airworthiness directive (AD): ■ The Boeing Company: Docket No. FAA– 2013–0667; Directorate Identifier 2013– NM–062–AD. (a) Comments Due Date We must receive comments by September 16, 2013. (b) Affected ADs None. (c) Applicability This AD applies to The Boeing Company Model 747–400 series airplanes, certificated in any category, as identified in Boeing Alert Service Bulletin 747–53A2844, Revision 1, dated July 30, 2012. (d) Subject Joint Aircraft System Component (JASC)/ Air Transport Association (ATA) of America Code 53, Fuselage. (e) Unsafe Condition This AD was prompted by reports of fasteners missing on an airplane undergoing a passenger-to-freighter conversion. We are issuing this AD to detect and correct missing or incorrect fasteners, which can lead to cracking and loss of load carrying capacity, resulting in a possible decompression event. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Inspection Except as required by paragraph (h)(1) of this AD, at the times specified in paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 747–53A2844, Revision 1, dated July 30, 2012: Do a general visual inspection for correct installation of the station 1920 splice clip common to the auxiliary sill web and the tie clip, and do all applicable related investigative and corrective actions in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 747–53A2844, Revision 1, dated July 30, 2012, except as required by paragraph (h)(2) of this AD. Do all applicable related investigative and corrective actions before further flight. (h) Exceptions to the Service Information (1) Where Boeing Alert Service Bulletin 747–53A2844, Revision 1, dated July 30, 2012, specifies a compliance time ‘‘after the original issue date of the service bulletin,’’ this AD requires compliance within the PO 00000 Frm 00015 Fmt 4702 Sfmt 4702 specified compliance time after the effective date of this AD. (2) If any cracking is found during any inspection required by this AD, and Boeing Alert Service Bulletin 747–53A2844, Revision 1, dated July 30, 2012, specifies contacting Boeing for appropriate action: Before further flight, repair using a method approved in accordance with the procedures specified in paragraph (j) of this AD. (i) Credit for Previous Actions This paragraph provides credit for actions required by paragraph (g) of this AD, if those actions were performed before the effective date of this AD using Boeing Alert Service Bulletin 747–53A2844, dated September 15, 2011, except the detailed inspection for cracking of the auxiliary sill outer chord tee and attached parts and all applicable related investigative and corrective actions must be done in accordance with Boeing Alert Service Bulletin 747–53A2844, Revision 1, dated July 30, 2012, at the times specified in paragraph (g) of this AD. Boeing Alert Service Bulletin 747–53A2844, dated September 15, 2011, is not incorporated by reference in this AD. (j) 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 the Related Information section of this AD. Information may be emailed to: 9-ANMSeattle-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 the Boeing Commercial Airplanes Organization Designation Authorization (ODA) that has been authorized by the Manager, Seattle ACO to make those findings. For a repair method to be approved, the repair must meet the certification basis of the airplane, and the approval must specifically refer to this AD. (k) Related Information (1) For more information about this AD, contact Bill Ashforth, Aerospace Engineer, Airframe Branch, ANM–120S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue SW., Renton, WA 98057–3356; phone: 425–917–6432; fax: 425–917–6590; email: bill.ashforth@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 review copies of the referenced service information at the FAA, Transport Airplane E:\FR\FM\01AUP1.SGM 01AUP1 Federal Register / Vol. 78, No. 148 / Thursday, August 1, 2013 / Proposed Rules 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 July 21, 2013. Stephen P. Boyd, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2013–18564 Filed 7–31–13; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2013–0665; Directorate Identifier 2012–NM–082–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 Airbus Model A330–300 series airplanes and Model A340–200 and –300 series airplanes. This proposed AD was prompted by reports of corrosion found on certain trimmable horizontal stabilizer actuators (THSA), affecting the ballscrew lower splines between the tie bar and the screw-jack. This proposed AD would require repetitive detailed inspections for corrosion of certain THSAs, ballscrew integrity tests if necessary; and replacing any affected THSA with a serviceable or new and improved THSA, if necessary. We are proposing this AD to detect and correct corrosion of the THSAs, which could lead, in the case of ballscrew rupture, to the loss of transmission of THSA torque loads from the ballscrew to the tie-bar, prompting THSA blowback, and possibly resulting in loss of control of the airplane. DATES: We must receive comments on this proposed AD by September 16, 2013. ADDRESSES: You may send comments 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: U.S. Department of Transportation, Docket Operations, M– emcdonald on DSK67QTVN1PROD with PROPOSALS SUMMARY: VerDate Mar<15>2010 16:23 Jul 31, 2013 Jkt 229001 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For Airbus service information identified in this proposed AD, contact Airbus SAS—Airworthiness Office— EAL, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 45 80; email airworthiness.A330A340@airbus.com; Internet http:// www.airbus.com. For Goodrich service information identified in this proposed AD, contact Goodrich Corporation, Actuation Systems, Product Support Department 13, Avenue de L’Eguillette—Saint-Ouen L’Aumone Boite Postale 7186 95056, Cergy Pontoise Cedex, France; fax: 33–1– 34326310. You may review copies of the referenced service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425–227– 1221. Examining the AD Docket You may examine the AD docket on the Internet at http:// www.regulations.gov; or in person at the Docket Operations office 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 Operations office (telephone (800) 647–5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: Vladimir Ulyanov, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057–3356; telephone (425) 227–1138; fax (425) 227–1149. 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–2013–0665; Directorate Identifier 2012–NM–082–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 based on those comments. PO 00000 Frm 00016 Fmt 4702 Sfmt 4702 46543 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 The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Community, has issued EASA Airworthiness Directive 2012–0061R1, dated November 30, 2012 (referred to after this as ‘‘the MCAI’’), to correct an unsafe condition for the specified products. The MCAI states: Some Trimmable Horizontal Stabilizer Actuators (THSA), Part Number (P/N) 47147– 500, have been found with corrosion, affecting the ballscrew lower splines between the tie bar and the screw-jack. The results of the technical investigations have identified that the corrosion was caused by a combination of: —Contact/friction between the tie bar and the inner surface of the ballscrew leading to the removal of Molykote (corrosion protection) at the level of the tie bar splines, —Humidity ingress initiating surface oxidation starting from areas where Molykote is removed, and —Water retention in THSA lower part leading to corrosion spread out and to the creation of a brown deposit (iron oxide). The results of the technical investigations have also concluded that THSA P/N 47147– 500 and P/N 47147–700 ballscrews might be affected by this corrosion issue. THSA P/N 47147–400 ballscrews might be affected as well, but should no longer be in service, and modified into P/N 47147–500, as required by EASA AD 2010–0192 and EASA AD 2010–0193 [and as required by FAA AD 2005–07–04, Amendment 39–14028 (70 FR 16104, March 30, 2005)]. This condition, if not detected and corrected, may lead, in case of ballscrew rupture, to loss of transmission of THSA torque loads from the ballscrew to the tie-bar, prompting THSA blowback, possibly resulting in loss of control of the aeroplane. To correct this potential unsafe condition, EASA issued AD 2012–0061 to require repetitive [detailed] visual inspections of the ballscrew lower splines of THSA having P/N 47147–500 or P/N 47147–700 to detect corrosion and, depending on findings [ballscrew integrity tests], the accomplishment of applicable corrective actions [replacing the affected THSA with a serviceable or improved THSA]. Since that [EASA] AD [2012–0061] was issued, Airbus published new Service Bulletin (SB) A330–27–3194 or Airbus SB A340–27–4187 (Airbus modification 202802), which allow installation in service of an improved THSA P/N 47172–530. For the reasons described above, this [EASA] AD [2012–0061R1] is revised to specify that installation of THSA P/N 47172– E:\FR\FM\01AUP1.SGM 01AUP1

Agencies

[Federal Register Volume 78, Number 148 (Thursday, August 1, 2013)]
[Proposed Rules]
[Pages 46540-46543]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2013-18564]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2013-0667; Directorate Identifier 2013-NM-062-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 adopt a new airworthiness directive (AD) for 
certain The Boeing Company Model 747-400 airplanes. This proposed AD 
was prompted by reports of fasteners missing on an airplane undergoing 
a passenger-to-freighter conversion. This proposed AD would require 
doing a general visual inspection of the station 1920 splice clip for 
correct fastener installation, and related investigative and corrective 
actions if necessary. We are proposing this AD to detect and correct 
missing or incorrect fasteners, which can lead to cracking and loss of 
load carrying capacity, resulting in a possible decompression event.

DATES: We must receive comments on this proposed AD by September 16, 
2013.

ADDRESSES: You may send comments, using the procedures found in 14 CFR 
11.43 and 11.45, by any of the following methods:

[[Page 46541]]

     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 review copies of the referenced service 
information at the FAA, Transport Airplane Directorate, 1601 Lind 
Avenue SW., Renton, WA. For information on the availability of this 
material at the FAA, call 425-227-1221.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://www.regulations.gov; or in person at the Docket Management Facility 
between 9 a.m. and 5 p.m., Monday through Friday, except Federal 
holidays. The AD docket contains this proposed AD, the regulatory 
evaluation, any comments received, and other information. The street 
address for the Docket Office (phone: 800-647-5527) is in the ADDRESSES 
section. Comments will be available in the AD docket shortly after 
receipt.

FOR FURTHER INFORMATION CONTACT: Bill Ashforth, Aerospace Engineer, 
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office, 
1601 Lind Avenue SW., Renton, WA 98057-3356; phone: 425-917-6432; fax: 
425-917-6590; email: bill.ashforth@faa.gov.

SUPPLEMENTARY INFORMATION:

Comments Invited

    We invite you to send any written relevant data, views, or 
arguments about this proposal. Send your comments to an address listed 
under the ADDRESSES section. Include ``Docket No. FAA-2013-0667; 
Directorate Identifier 2013-NM-062-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

    We have received a report of an airplane, while undergoing a 
passenger-to-freighter conversion, missing fasteners on the station 
1920 splice clip. The possibility of this discrepancy exists on 
airplanes already delivered. This condition, if not corrected, could 
result in cracking and loss of load carrying capacity, resulting in a 
possible decompression event.

Relevant Service Information

    We reviewed Boeing Alert Service Bulletin 747-53A2844, Revision 1, 
dated July 30, 2012. For information on the procedures and compliance 
times, see this service information at http://www.regulations.gov by 
searching for Docket No. FAA-2013-0667.

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 require accomplishing the actions specified 
in the service information described previously, except as discussed 
under ``Differences Between the Proposed AD and the Service 
Information.''
    The phrase ``related investigative actions'' might be used in this 
proposed AD. ``Related investigative actions'' are follow-on actions 
that: (1) Are related to the primary actions, and (2) further 
investigate the nature of any condition found. Related investigative 
actions in an AD could include, for example, inspections.
    In addition, the phrase ``corrective actions'' might be used in 
this proposed AD. ``Corrective actions'' are actions that correct or 
address any condition found. Corrective actions in an AD could include, 
for example, repairs.

Differences Between the Proposed AD and the Service Information

    Although the service bulletin specifies that operators may contact 
the manufacturer for disposition of certain repair conditions, this 
proposed AD would require operators to repair those conditions in 
accordance with a method approved by the FAA.

Costs of Compliance

    We estimate that this proposed AD affects 3 airplanes of U.S. 
registry.
    We estimate the following costs to comply with this proposed AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                       Cost on
                 Action                              Labor cost             Parts cost    Cost per       U.S.
                                                                                          product     operators
----------------------------------------------------------------------------------------------------------------
Inspection for correct fastener           2 work-hours x $85 per hour =             $0         $170         $510
 installation.                             $170.
----------------------------------------------------------------------------------------------------------------

    We estimate the following costs to do any necessary repairs that 
would be required based on the results of the proposed inspection. We 
have no way of determining the number of aircraft that might need these 
repairs:

                                               On-Condition Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                       Cost per
                    Action                                    Labor cost                 Parts cost    product
----------------------------------------------------------------------------------------------------------------
Inspections for cracking......................  3 work-hours x $85 per hour = $255....           $0         $255
Fastener installation.........................  2 work-hours x $85 per hour = $170....            0          170
Repair........................................  2 work-hours x $85 per hour = $170....            0          170
----------------------------------------------------------------------------------------------------------------


[[Page 46542]]

    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 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 this 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 adding the following new airworthiness 
directive (AD):

The Boeing Company: Docket No. FAA-2013-0667; Directorate Identifier 
2013-NM-062-AD.

(a) Comments Due Date

    We must receive comments by September 16, 2013.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to The Boeing Company Model 747-400 series 
airplanes, certificated in any category, as identified in Boeing 
Alert Service Bulletin 747-53A2844, Revision 1, dated July 30, 2012.

(d) Subject

    Joint Aircraft System Component (JASC)/Air Transport Association 
(ATA) of America Code 53, Fuselage.

(e) Unsafe Condition

    This AD was prompted by reports of fasteners missing on an 
airplane undergoing a passenger-to-freighter conversion. We are 
issuing this AD to detect and correct missing or incorrect 
fasteners, which can lead to cracking and loss of load carrying 
capacity, resulting in a possible decompression event.

(f) Compliance

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

(g) Inspection

    Except as required by paragraph (h)(1) of this AD, at the times 
specified in paragraph 1.E., ``Compliance,'' of Boeing Alert Service 
Bulletin 747-53A2844, Revision 1, dated July 30, 2012: Do a general 
visual inspection for correct installation of the station 1920 
splice clip common to the auxiliary sill web and the tie clip, and 
do all applicable related investigative and corrective actions in 
accordance with the Accomplishment Instructions of Boeing Alert 
Service Bulletin 747-53A2844, Revision 1, dated July 30, 2012, 
except as required by paragraph (h)(2) of this AD. Do all applicable 
related investigative and corrective actions before further flight.

(h) Exceptions to the Service Information

    (1) Where Boeing Alert Service Bulletin 747-53A2844, Revision 1, 
dated July 30, 2012, specifies a compliance time ``after the 
original issue date of the service bulletin,'' this AD requires 
compliance within the specified compliance time after the effective 
date of this AD.
    (2) If any cracking is found during any inspection required by 
this AD, and Boeing Alert Service Bulletin 747-53A2844, Revision 1, 
dated July 30, 2012, specifies contacting Boeing for appropriate 
action: Before further flight, repair using a method approved in 
accordance with the procedures specified in paragraph (j) of this 
AD.

(i) Credit for Previous Actions

    This paragraph provides credit for actions required by paragraph 
(g) of this AD, if those actions were performed before the effective 
date of this AD using Boeing Alert Service Bulletin 747-53A2844, 
dated September 15, 2011, except the detailed inspection for 
cracking of the auxiliary sill outer chord tee and attached parts 
and all applicable related investigative and corrective actions must 
be done in accordance with Boeing Alert Service Bulletin 747-
53A2844, Revision 1, dated July 30, 2012, at the times specified in 
paragraph (g) of this AD. Boeing Alert Service Bulletin 747-53A2844, 
dated September 15, 2011, is not incorporated by reference in this 
AD.

(j) 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 the Related Information 
section 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 the 
Boeing Commercial Airplanes Organization Designation Authorization 
(ODA) that has been authorized by the Manager, Seattle ACO to make 
those findings. For a repair method to be approved, the repair must 
meet the certification basis of the airplane, and the approval must 
specifically refer to this AD.

(k) Related Information

    (1) For more information about this AD, contact Bill Ashforth, 
Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle Aircraft 
Certification Office, 1601 Lind Avenue SW., Renton, WA 98057-3356; 
phone: 425-917-6432; fax: 425-917-6590; email: 
bill.ashforth@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 review copies of the referenced 
service information at the FAA, Transport Airplane

[[Page 46543]]

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 July 21, 2013.
Stephen P. Boyd,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2013-18564 Filed 7-31-13; 8:45 am]
BILLING CODE 4910-13-P