Airworthiness Directives; The Boeing Company Airplanes, 21648-21651 [2014-08726]

Download as PDF 21648 Proposed Rules Federal Register Vol. 79, No. 74 Thursday, April 17, 2014 This section of the FEDERAL REGISTER contains notices to the public of the proposed issuance of rules and regulations. The purpose of these notices is to give interested persons an opportunity to participate in the rule making prior to the adoption of the final rules. DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2014–0235; Directorate Identifier 2013–NM–249–AD] 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 DC–8–55, DC–8F–54, and DC–8F–55 airplanes, Model DC–8–60 series airplanes, Model DC–8–60F series airplanes, Model DC– 8–70 series airplanes, and Model DC–8– 70F series airplanes. This proposed AD was prompted by multiple reports of cracking of the upper aft skin panel of the fuselage. An evaluation by the design approval holder (DAH) indicates that the upper aft skin panel of the fuselage is subject to widespread fatigue damage (WFD). This proposed AD would require removing any previously installed local repairs; installing a fulllength improvement modification with finger doublers or a full-length repair with finger doublers; and repetitive inspections for cracking of the doublers, and repair if necessary. We are proposing this AD to detect and correct fatigue cracking of the upper aft skin panel of the fuselage, which could result in loss of structural integrity and consequent rapid decompression of the airplane. DATES: We must receive comments on this proposed AD by June 2, 2014. ADDRESSES: You may send comments, using the procedures found in 14 CFR 11.43 and 11.45, by any of the following methods: • Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments. wreier-aviles on DSK5TPTVN1PROD with PROPOSALS SUMMARY: VerDate Mar<15>2010 14:53 Apr 16, 2014 Jkt 232001 • 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, 3855 Lakewood Boulevard, MC D800–0019, Long Beach, CA 90846–0001; telephone 206–544–5000, extension 2; fax 206– 766–5683; 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. Examining the AD Docket You may examine the AD docket on the Internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2014– 0235; 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: Chandraduth Ramdoss, Aerospace Engineer, Airframe Branch, ANM–120L, FAA, Los Angeles Aircraft Certification Office (ACO), 3960 Paramount Blvd., Suite 100, Lakewood, CA 90712–4137, phone: 562–627–5239; fax: 562–627– 5210; email: chandraduth.ramdoss@ 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– 2014–0235; Directorate Identifier 2013– NM–249–AD’’ at the beginning of your PO 00000 Frm 00001 Fmt 4702 Sfmt 4702 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 Structural fatigue damage is progressive. It begins as minute cracks, and those cracks grow under the action of repeated stresses. This can happen because of normal operational conditions and design attributes, or because of isolated situations or incidents such as material defects, poor fabrication quality, or corrosion pits, dings, or scratches. Fatigue damage can occur locally, in small areas or structural design details, or globally. Global fatigue damage is general degradation of large areas of structure with similar structural details and stress levels. Multiple-site damage is global damage that occurs in a large structural element such as a single rivet line of a lap splice joining two large skin panels. Global damage can also occur in multiple elements such as adjacent frames or stringers. Multiple-sitedamage and multiple-element-damage cracks are typically too small initially to be reliably detected with normal inspection methods. Without intervention, these cracks will grow, and eventually compromise the structural integrity of the airplane, in a condition known as WFD. As an airplane ages, WFD will likely occur, and will certainly occur if the airplane is operated long enough without any intervention. The FAA’s WFD final rule (75 FR 69746, November 15, 2010) became effective on January 14, 2011. The WFD rule requires certain actions to prevent catastrophic failure due to WFD throughout the operational life of certain existing transport category airplanes and all of these airplanes that will be certificated in the future. For existing and future airplanes subject to the WFD rule, the rule requires that E:\FR\FM\17APP1.SGM 17APP1 Federal Register / Vol. 79, No. 74 / Thursday, April 17, 2014 / Proposed Rules DAHs establish a limit of validity (LOV) of the engineering data that support the structural maintenance program. Operators affected by the WFD rule may not fly an airplane beyond its LOV, unless an extended LOV is approved. The WFD rule (75 FR 69746, November 15, 2010) does not require identifying and developing maintenance actions if the DAHs can show that such actions are not necessary to prevent WFD before the airplane reaches the LOV. Many LOVs, however, do depend on accomplishment of future maintenance actions. As stated in the WFD rule, any maintenance actions necessary to reach the LOV will be mandated by airworthiness directives through separate rulemaking actions. In the context of WFD, this approach is necessary to enable DAHs to propose LOVs that allow operators the longest operational lives for their airplanes, and still ensure that WFD will not occur. This approach allows for an implementation strategy that provides flexibility to DAHs in determining the timing of service information development (with FAA approval), while providing operators with certainty regarding the LOV applicable to their airplanes. During routine maintenance inspections, three operators reported finding cracks in the upper aft skin panel. The cracks were located along the upper row of rivets common to the longeron 28 skin splice, near the flat aft pressure bulkhead. Cracks were detected on airplanes that had accumulated between 27,072 and 46,176 total flight cycles. This cracking, if not corrected, could result in fatigue cracking of the upper aft skin panel of the fuselage, which could result in loss of structural integrity and consequent rapid decompression of the airplane. Relevant Service Information We reviewed Boeing Alert Service Bulletin DC8–53A080, Revision 2, dated September 18, 2013. For information on the procedures and compliance times, see this service information at http:// www.regulations.gov by searching for Docket No. FAA–2014–0235. 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 21649 the requirements of paragraphs (g) and (h) of this proposed AD. Differences Between This Proposed AD and the Service Information Boeing Alert Service Bulletin DC8– 53A080, Revision 2, dated September 18, 2013, specifies to contact the manufacturer for instructions on how to repair certain conditions, but this proposed AD would require repairing those conditions in one of the following ways: • In accordance with a method that we approve; or • Using data that meet the certification basis of the airplane, and that have been approved by the Boeing Commercial Airplanes Organization Designation Authorization (ODA) whom we have authorized to make those findings. Explanation of Compliance Time This proposed AD would require removing previously installed local repairs; installing a full-length improvement modification with finger doublers, or a full-length repair with finger doublers; and doing repetitive detailed inspections or repetitive low frequency eddy current inspections for cracking along all four edges of the doublers, and corrective action if necessary. Related Rulemaking On March 9, 2008, we issued AD 2008–06–23, Amendment 39–15435 (73 FR 14378, March 18, 2008). AD 2008– 06–23 provides an option to install fulllength preventive modifications or fulllength repairs, and requires repetitive inspections. Accomplishing these actions is a method of compliance with The compliance time for the modification specified in this proposed AD for addressing WFD was established to ensure that discrepant structure is modified before WFD develops in airplanes. Standard inspection techniques cannot be relied on to detect WFD before it becomes a hazard to flight. We will not grant any extensions of the compliance time to complete any AD-mandated service bulletin related to WFD without extensive new data that would substantiate and clearly warrant such an extension. Costs of Compliance We estimate that this proposed AD affects 18 airplanes of U.S. registry. We estimate the following costs to comply with this proposed AD: ESTIMATED COSTS Labor cost Parts cost Cost per product Full-length modification or repair. Inspection .......................... wreier-aviles on DSK5TPTVN1PROD with PROPOSALS Action Up to 184 work-hours × $85 per hour = $15,640. 9 work-hours × $85 per hour = $765 per inspection cycle. Up to $14,720 ................... Up to $30,360 ................... Up to $546,480. $0 ...................................... $765 per inspection cycle $13,770 per inspection cycle. We have received no definitive data that would enable us to provide cost estimates for the on-condition actions specified in this proposed AD. 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 VerDate Mar<15>2010 14:53 Apr 16, 2014 Jkt 232001 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 PO 00000 Frm 00002 Fmt 4702 Sfmt 4702 Cost on U.S. operators 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 E:\FR\FM\17APP1.SGM 17APP1 21650 Federal Register / Vol. 79, No. 74 / Thursday, April 17, 2014 / Proposed Rules 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 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– 2014–0235; Directorate Identifier 2013– NM–249–AD. (a) Comments Due Date We must receive comments by June 2, 2014. wreier-aviles on DSK5TPTVN1PROD with PROPOSALS (b) Affected ADs This AD affects AD 2008–06–23, Amendment 39–15435 (73 FR 14378, March 18, 2008). (c) Applicability This AD applies to The Boeing Company airplanes identified in paragraphs (c)(1) through (c)(6) of this AD, certificated in any category, as identified in Boeing Alert Service Bulletin DC8–53A080, Revision 2, dated September 18, 2013. (1) The Boeing Company Model DC–8–55 airplanes. (2) The Boeing Company Model DC–8F–54 and DC–8F–55 airplanes. (3) The Boeing Company Model DC–8–61, DC–8–62, and DC–8–63 airplanes. (4) The Boeing Company Model DC–8–61F, DC–8–62F, and DC–8–63F airplanes. (5) The Boeing Company Model DC–8–71, DC–8–72, and DC–8–73 airplanes. (6) The Boeing Company Model DC–8–71F, DC–8–72F, and DC–8–73F airplanes. VerDate Mar<15>2010 14:53 Apr 16, 2014 Jkt 232001 (d) Subject Air Transport Association (ATA) of America Code 53, Fuselage. (e) Unsafe Condition This AD was prompted by multiple reports of cracking of the upper aft skin panel of the fuselage. An evaluation by the design approval holder indicates that the upper aft skin panel of the fuselage is subject to widespread fatigue damage. We are issuing this AD to detect and correct fatigue cracking of the upper aft skin panel of the fuselage, which could result in loss of structural integrity and consequent rapid decompression of the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Modification or Repair Before the accumulation of 45,400 total flight cycles, or within 72 months after the effective date of this AD, whichever occurs later: Remove any previously installed local repairs and install a full-length improvement modification with finger doublers or a fulllength repair with finger doublers, as applicable, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin DC8–53A080, Revision 2, dated September 18, 2013. Installation of the full-length improvement modification or fulllength repair with finger doublers, in accordance with paragraph (i) of AD 2008– 06–23, Amendment 39–15435 (73 FR 14378, March 18, 2008), is a method of compliance with the requirements of paragraph (g) of this AD. Installation of a local repair as specified in paragraph (i) of AD 2008–06–23, does not comply with the requirements of paragraph (g) of this AD. (h) Post-Modification or Post-Repair Repetitive Inspections After accomplishing the actions required by paragraph (g) of this AD, at the applicable time and intervals specified in paragraph (h)(1) or (h)(2) of this AD: Do an external visual inspection or low frequency eddy current (LFEC) inspection for cracking along all four edges of the finger doublers, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin DC8–53A080, Revision 2, dated September 18, 2013. Repeat the inspections thereafter at the applicable time and interval specified in paragraphs (h)(1) or (h)(2) of this AD. Accomplishment of the applicable repetitive inspection specified in paragraph (j)(1) or (j)(2)(ii) of AD 2008–06–23, Amendment 39– 15435 (73 FR 14378, March 18, 2008), is a method of compliance with the applicable inspection requirements of paragraph (h) of this AD. (1) For an external visual inspection, within 30,000 flight cycles after doing the actions specified in paragraph (g) of this AD. Repeat the external visual inspection thereafter at intervals not to exceed 5,000 flight cycles. (2) For an LFEC inspection, within 15,000 flight cycles after doing the actions specified in paragraph (g) of this AD. Repeat the LFEC PO 00000 Frm 00003 Fmt 4702 Sfmt 4702 inspection thereafter at intervals not to exceed 10,000 flight cycles. (i) Cracking Repair If any cracking is found during any inspection required by paragraph (h) of this AD: Before further flight, repair using a method approved in accordance with the procedures specified in paragraph (k) of this AD. (j) 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 DC8–53A080, dated June 22, 2004; or Boeing Alert Service Bulletin DC8– 53A080, Revision 1, dated May 3, 2013. Boeing Alert Service Bulletin DC8–53A080, dated June 22, 2004, was previously incorporated by reference in AD 2008–06–23, Amendment 39–15435 (73 FR 14378, March 18, 2008). Boeing Alert Service Bulletin DC8– 53A080, Revision 1, dated May 3, 2013, is not incorporated by reference in this AD. (k) Alternative Methods of Compliance (AMOCs) (1) The Manager, Los Angeles 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 (l)(1) of this AD. Information may be emailed to: 9-ANM-LAACO-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 the Boeing Commercial Airplanes Organization Designation Authorization (ODA) that has been authorized by the Manager, Los Angeles ACO, to make those findings. For a repair method to be approved, the repair must meet the certification basis of the airplane and 14 CFR 25.571, Amendment 45, and the approval must specifically refer to this AD. (l) Related Information (1) For more information about this AD, contact Chandraduth Ramdoss, Aerospace Engineer, Airframe Branch, ANM–120L, FAA, Los Angeles Aircraft Certification Office (ACO), 3960 Paramount Blvd., Suite 100, Lakewood, CA 90712–4137, phone: 562– 627–5239; fax: 562–627–5210; email: chandraduth.ramdoss@faa.gov. (2) For service information identified in this AD, contact Boeing Commercial Airplanes, Attention: Data & Services Management, 3855 Lakewood Boulevard, MC D800–0019, Long Beach, CA 90846–0001; telephone 206–544–5000, extension 2; fax 206–766–5683; Internet https:// www.myboeingfleet.com. You may view this service information at the FAA, Transport E:\FR\FM\17APP1.SGM 17APP1 Federal Register / Vol. 79, No. 74 / Thursday, April 17, 2014 / Proposed Rules 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 April 8, 2014. John P. Piccola, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2014–08726 Filed 4–16–14; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2014–0236; Directorate Identifier 2013–NM–184–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 A300 series airplanes. This proposed AD was prompted by our determination of the need to incorporate new life limits for the main landing gear (MLG) barrel assembly, retraction actuator assembly linkage, and flange duct. This proposed AD would require revising the maintenance or inspection program to include the new life limits. We are proposing this AD to prevent reduced structural integrity of the airplane and possible loss of controllability of the airplane. DATES: We must receive comments on this proposed AD by June 2, 2014. 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–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 service information identified in this proposed AD, contact Airbus SAS, Airworthiness Office—EAW, 1 Rond wreier-aviles on DSK5TPTVN1PROD with PROPOSALS SUMMARY: VerDate Mar<15>2010 14:53 Apr 16, 2014 Jkt 232001 Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 44 51; email account.airworth-eas@airbus.com; Internet http://www.airbus.com. You may view this service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425–227– 1221. Examining the AD Docket You may examine the AD docket on the Internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2014– 0236; 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 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: 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. 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–2014–0236; Directorate Identifier 2013–NM–184–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. 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 2013–0210, dated September 11, 2013 (referred to after this as the Mandatory Continuing PO 00000 Frm 00004 Fmt 4702 Sfmt 4702 21651 Airworthiness Information, or ‘‘the MCAI’’), to correct an unsafe condition for the specified products. The MCAI states: Some life limits previously defined in Revision 00 of A300 ALS [airworthiness limitations section] Part 1 have been removed [from] that document at Revision 01 and should normally be included in an ALS Part 4. At this time, there are no plans to issue an ALS Part 4 for A300 aeroplanes. Nevertheless, failure to comply with these life limits could result in an unsafe condition. For the reasons described above, it has been decided to require the application of these life limits through a separate [EASA] AD. Consequently, this [EASA] AD requires application of life limits applicable to Main Landing Gear (MLG) barrel assembly, retraction actuator assembly linkage assembly and flanged duct which were previously contained in Airbus ALS Part 1 Revision 00. EASA AD 2007–0293 [which corresponds with FAA AD 2009–18–15, Amendment 39– 16011 (74 FR 48143, September 22, 2009)], which required compliance with the actions specified in ALS Part 1, will be superseded by a new [EASA] AD, requiring compliance with ALS Part 1 at Revision 1. You may examine the MCAI in the AD docket on the Internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2014– 0236. FAA’s Determination and Requirements of This Proposed AD This product has been approved by the aviation authority of another country, and is approved for operation in the United States. Pursuant to our bilateral agreement with the State of Design Authority, we have been notified of the unsafe condition described in the MCAI and service information referenced above. We are proposing this AD because we evaluated all pertinent information and determined an unsafe condition exists and is likely to exist or develop on other products of the same type design. This AD requires revisions to certain operator maintenance documents to include new actions (e.g., inspections). Compliance with these actions is required by 14 CFR 91.403(c). For airplanes that have been previously modified, altered, or repaired in the areas addressed by this proposed AD, the operator may not be able to accomplish the actions described in the revisions. In this situation, to comply with 14 CFR 91.403(c), the operator must request approval for an alternative method of compliance according to the procedures specified in paragraph (i)(1) of this AD. The request should include a description of changes to the required E:\FR\FM\17APP1.SGM 17APP1

Agencies

[Federal Register Volume 79, Number 74 (Thursday, April 17, 2014)]
[Proposed Rules]
[Pages 21648-21651]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2014-08726]


========================================================================
Proposed Rules
                                                Federal Register
________________________________________________________________________

This section of the FEDERAL REGISTER contains notices to the public of 
the proposed issuance of rules and regulations. The purpose of these 
notices is to give interested persons an opportunity to participate in 
the rule making prior to the adoption of the final rules.

========================================================================


Federal Register / Vol. 79, No. 74 / Thursday, April 17, 2014 / 
Proposed Rules

[[Page 21648]]



DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2014-0235; Directorate Identifier 2013-NM-249-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 DC-8-55, DC-8F-54, and DC-8F-55 
airplanes, Model DC-8-60 series airplanes, Model DC-8-60F series 
airplanes, Model DC-8-70 series airplanes, and Model DC-8-70F series 
airplanes. This proposed AD was prompted by multiple reports of 
cracking of the upper aft skin panel of the fuselage. An evaluation by 
the design approval holder (DAH) indicates that the upper aft skin 
panel of the fuselage is subject to widespread fatigue damage (WFD). 
This proposed AD would require removing any previously installed local 
repairs; installing a full-length improvement modification with finger 
doublers or a full-length repair with finger doublers; and repetitive 
inspections for cracking of the doublers, and repair if necessary. We 
are proposing this AD to detect and correct fatigue cracking of the 
upper aft skin panel of the fuselage, which could result in loss of 
structural integrity and consequent rapid decompression of the 
airplane.

DATES: We must receive comments on this proposed AD by June 2, 2014.

ADDRESSES: You may send comments, using the procedures found in 14 CFR 
11.43 and 11.45, by any of the following methods:
     Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.
     Fax: 202-493-2251.
     Mail: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE., Washington, DC 20590.
     Hand Delivery: Deliver to Mail address above between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
    For service information identified in this proposed AD, contact 
Boeing Commercial Airplanes, Attention: Data & Services Management, 
3855 Lakewood Boulevard, MC D800-0019, Long Beach, CA 90846-0001; 
telephone 206-544-5000, extension 2; fax 206-766-5683; 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.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2014-
0235; 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: Chandraduth Ramdoss, Aerospace 
Engineer, Airframe Branch, ANM-120L, FAA, Los Angeles Aircraft 
Certification Office (ACO), 3960 Paramount Blvd., Suite 100, Lakewood, 
CA 90712-4137, phone: 562-627-5239; fax: 562-627-5210; email: 
chandraduth.ramdoss@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-2014-0235; 
Directorate Identifier 2013-NM-249-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

    Structural fatigue damage is progressive. It begins as minute 
cracks, and those cracks grow under the action of repeated stresses. 
This can happen because of normal operational conditions and design 
attributes, or because of isolated situations or incidents such as 
material defects, poor fabrication quality, or corrosion pits, dings, 
or scratches. Fatigue damage can occur locally, in small areas or 
structural design details, or globally. Global fatigue damage is 
general degradation of large areas of structure with similar structural 
details and stress levels. Multiple-site damage is global damage that 
occurs in a large structural element such as a single rivet line of a 
lap splice joining two large skin panels. Global damage can also occur 
in multiple elements such as adjacent frames or stringers. Multiple-
site-damage and multiple-element-damage cracks are typically too small 
initially to be reliably detected with normal inspection methods. 
Without intervention, these cracks will grow, and eventually compromise 
the structural integrity of the airplane, in a condition known as WFD. 
As an airplane ages, WFD will likely occur, and will certainly occur if 
the airplane is operated long enough without any intervention.
    The FAA's WFD final rule (75 FR 69746, November 15, 2010) became 
effective on January 14, 2011. The WFD rule requires certain actions to 
prevent catastrophic failure due to WFD throughout the operational life 
of certain existing transport category airplanes and all of these 
airplanes that will be certificated in the future. For existing and 
future airplanes subject to the WFD rule, the rule requires that

[[Page 21649]]

DAHs establish a limit of validity (LOV) of the engineering data that 
support the structural maintenance program. Operators affected by the 
WFD rule may not fly an airplane beyond its LOV, unless an extended LOV 
is approved.
    The WFD rule (75 FR 69746, November 15, 2010) does not require 
identifying and developing maintenance actions if the DAHs can show 
that such actions are not necessary to prevent WFD before the airplane 
reaches the LOV. Many LOVs, however, do depend on accomplishment of 
future maintenance actions. As stated in the WFD rule, any maintenance 
actions necessary to reach the LOV will be mandated by airworthiness 
directives through separate rulemaking actions.
    In the context of WFD, this approach is necessary to enable DAHs to 
propose LOVs that allow operators the longest operational lives for 
their airplanes, and still ensure that WFD will not occur. This 
approach allows for an implementation strategy that provides 
flexibility to DAHs in determining the timing of service information 
development (with FAA approval), while providing operators with 
certainty regarding the LOV applicable to their airplanes.
    During routine maintenance inspections, three operators reported 
finding cracks in the upper aft skin panel. The cracks were located 
along the upper row of rivets common to the longeron 28 skin splice, 
near the flat aft pressure bulkhead. Cracks were detected on airplanes 
that had accumulated between 27,072 and 46,176 total flight cycles. 
This cracking, if not corrected, could result in fatigue cracking of 
the upper aft skin panel of the fuselage, which could result in loss of 
structural integrity and consequent rapid decompression of the 
airplane.

Relevant Service Information

    We reviewed Boeing Alert Service Bulletin DC8-53A080, Revision 2, 
dated September 18, 2013. For information on the procedures and 
compliance times, see this service information at http://www.regulations.gov by searching for Docket No. FAA-2014-0235.

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 removing previously installed local 
repairs; installing a full-length improvement modification with finger 
doublers, or a full-length repair with finger doublers; and doing 
repetitive detailed inspections or repetitive low frequency eddy 
current inspections for cracking along all four edges of the doublers, 
and corrective action if necessary.

Related Rulemaking

    On March 9, 2008, we issued AD 2008-06-23, Amendment 39-15435 (73 
FR 14378, March 18, 2008). AD 2008-06-23 provides an option to install 
full-length preventive modifications or full-length repairs, and 
requires repetitive inspections. Accomplishing these actions is a 
method of compliance with the requirements of paragraphs (g) and (h) of 
this proposed AD.

Differences Between This Proposed AD and the Service Information

    Boeing Alert Service Bulletin DC8-53A080, Revision 2, dated 
September 18, 2013, specifies to contact the manufacturer for 
instructions on how to repair certain conditions, but this proposed AD 
would require repairing those conditions in one of the following ways:
     In accordance with a method that we approve; or
     Using data that meet the certification basis of the 
airplane, and that have been approved by the Boeing Commercial 
Airplanes Organization Designation Authorization (ODA) whom we have 
authorized to make those findings.

Explanation of Compliance Time

    The compliance time for the modification specified in this proposed 
AD for addressing WFD was established to ensure that discrepant 
structure is modified before WFD develops in airplanes. Standard 
inspection techniques cannot be relied on to detect WFD before it 
becomes a hazard to flight. We will not grant any extensions of the 
compliance time to complete any AD-mandated service bulletin related to 
WFD without extensive new data that would substantiate and clearly 
warrant such an extension.

Costs of Compliance

    We estimate that this proposed AD affects 18 airplanes of U.S. 
registry.
    We estimate the following costs to comply with this proposed AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                 Cost on U.S.
             Action                   Labor cost          Parts cost       Cost per product        operators
----------------------------------------------------------------------------------------------------------------
Full-length modification or       Up to 184           Up to $14,720.....  Up to $30,360.....  Up to $546,480.
 repair.                           work[dash]hours x
                                   $85 per hour =
                                   $15,640.
Inspection......................  9 work-hours x $85  $0................  $765 per            $13,770 per
                                   per hour = $765                         inspection cycle.   inspection cycle.
                                   per inspection
                                   cycle.
----------------------------------------------------------------------------------------------------------------

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

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

[[Page 21650]]

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-2014-0235; Directorate Identifier 
2013-NM-249-AD.

(a) Comments Due Date

    We must receive comments by June 2, 2014.

(b) Affected ADs

    This AD affects AD 2008-06-23, Amendment 39-15435 (73 FR 14378, 
March 18, 2008).

(c) Applicability

    This AD applies to The Boeing Company airplanes identified in 
paragraphs (c)(1) through (c)(6) of this AD, certificated in any 
category, as identified in Boeing Alert Service Bulletin DC8-53A080, 
Revision 2, dated September 18, 2013.
    (1) The Boeing Company Model DC-8-55 airplanes.
    (2) The Boeing Company Model DC-8F-54 and DC-8F-55 airplanes.
    (3) The Boeing Company Model DC-8-61, DC-8-62, and DC-8-63 
airplanes.
    (4) The Boeing Company Model DC-8-61F, DC-8-62F, and DC-8-63F 
airplanes.
    (5) The Boeing Company Model DC-8-71, DC-8-72, and DC-8-73 
airplanes.
    (6) The Boeing Company Model DC-8-71F, DC-8-72F, and DC-8-73F 
airplanes.

(d) Subject

    Air Transport Association (ATA) of America Code 53, Fuselage.

(e) Unsafe Condition

    This AD was prompted by multiple reports of cracking of the 
upper aft skin panel of the fuselage. An evaluation by the design 
approval holder indicates that the upper aft skin panel of the 
fuselage is subject to widespread fatigue damage. We are issuing 
this AD to detect and correct fatigue cracking of the upper aft skin 
panel of the fuselage, which could result in loss of structural 
integrity and consequent rapid decompression of the airplane.

(f) Compliance

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

(g) Modification or Repair

    Before the accumulation of 45,400 total flight cycles, or within 
72 months after the effective date of this AD, whichever occurs 
later: Remove any previously installed local repairs and install a 
full-length improvement modification with finger doublers or a full-
length repair with finger doublers, as applicable, in accordance 
with the Accomplishment Instructions of Boeing Alert Service 
Bulletin DC8-53A080, Revision 2, dated September 18, 2013. 
Installation of the full-length improvement modification or full-
length repair with finger doublers, in accordance with paragraph (i) 
of AD 2008-06-23, Amendment 39-15435 (73 FR 14378, March 18, 2008), 
is a method of compliance with the requirements of paragraph (g) of 
this AD. Installation of a local repair as specified in paragraph 
(i) of AD 2008-06-23, does not comply with the requirements of 
paragraph (g) of this AD.

(h) Post-Modification or Post-Repair Repetitive Inspections

    After accomplishing the actions required by paragraph (g) of 
this AD, at the applicable time and intervals specified in paragraph 
(h)(1) or (h)(2) of this AD: Do an external visual inspection or low 
frequency eddy current (LFEC) inspection for cracking along all four 
edges of the finger doublers, in accordance with the Accomplishment 
Instructions of Boeing Alert Service Bulletin DC8-53A080, Revision 
2, dated September 18, 2013. Repeat the inspections thereafter at 
the applicable time and interval specified in paragraphs (h)(1) or 
(h)(2) of this AD. Accomplishment of the applicable repetitive 
inspection specified in paragraph (j)(1) or (j)(2)(ii) of AD 2008-
06-23, Amendment 39-15435 (73 FR 14378, March 18, 2008), is a method 
of compliance with the applicable inspection requirements of 
paragraph (h) of this AD.
    (1) For an external visual inspection, within 30,000 flight 
cycles after doing the actions specified in paragraph (g) of this 
AD. Repeat the external visual inspection thereafter at intervals 
not to exceed 5,000 flight cycles.
    (2) For an LFEC inspection, within 15,000 flight cycles after 
doing the actions specified in paragraph (g) of this AD. Repeat the 
LFEC inspection thereafter at intervals not to exceed 10,000 flight 
cycles.

(i) Cracking Repair

    If any cracking is found during any inspection required by 
paragraph (h) of this AD: Before further flight, repair using a 
method approved in accordance with the procedures specified in 
paragraph (k) of this AD.

(j) 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 DC8-53A080, dated June 22, 2004; or Boeing Alert Service 
Bulletin DC8-53A080, Revision 1, dated May 3, 2013. Boeing Alert 
Service Bulletin DC8-53A080, dated June 22, 2004, was previously 
incorporated by reference in AD 2008-06-23, Amendment 39-15435 (73 
FR 14378, March 18, 2008). Boeing Alert Service Bulletin DC8-53A080, 
Revision 1, dated May 3, 2013, is not incorporated by reference in 
this AD.

(k) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, Los Angeles 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 (l)(1) of this AD. 
Information may be emailed to: 9-ANM-LAACO-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, Los Angeles ACO, to 
make those findings. For a repair method to be approved, the repair 
must meet the certification basis of the airplane and 14 CFR 25.571, 
Amendment 45, and the approval must specifically refer to this AD.

(l) Related Information

    (1) For more information about this AD, contact Chandraduth 
Ramdoss, Aerospace Engineer, Airframe Branch, ANM-120L, FAA, Los 
Angeles Aircraft Certification Office (ACO), 3960 Paramount Blvd., 
Suite 100, Lakewood, CA 90712-4137, phone: 562-627-5239; fax: 562-
627-5210; email: chandraduth.ramdoss@faa.gov.
    (2) For service information identified in this AD, contact 
Boeing Commercial Airplanes, Attention: Data & Services Management, 
3855 Lakewood Boulevard, MC D800-0019, Long Beach, CA 90846-0001; 
telephone 206-544-5000, extension 2; fax 206-766-5683; Internet 
https://www.myboeingfleet.com. You may view this service information 
at the FAA, Transport

[[Page 21651]]

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 April 8, 2014.
John P. Piccola,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2014-08726 Filed 4-16-14; 8:45 am]
BILLING CODE 4910-13-P