Airworthiness Directives; Lockheed Martin Corporation/Lockheed Martin Aeronautics Company Airplanes, 32069-32072 [2015-13339]

Download as PDF Federal Register / Vol. 80, No. 108 / Friday, June 5, 2015 / Proposed Rules 4, 2014, specifies a compliance time ‘‘after the initial issue date on this service bulletin,’’ this AD requires compliance within the specified compliance time after the effective date of this AD. (2) Where Aviation Partners Boeing Service Bulletin AP767–57–010, Revision 7, dated November 4, 2014, specifies to contact Boeing for repair instructions: Before further flight, repair the cracking using a method approved in accordance with the procedures specified in paragraph (k) of this AD. (k) Alternative Methods of Compliance (AMOCs) asabaliauskas on DSK5VPTVN1PROD with PROPOSALS (l) Related Information (1) For more information about this AD, contact Allen Rauschendorfer, Aerospace Engineer, Airframe Branch, ANM–120S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue SW., Renton, WA 98057– 3356; phone: 425–917–6487; fax: 425–917– 6590; email: Allen.Rauschendorfer@faa.gov. (2) For service information identified in this AD, contact Aviation Partners Boeing, 2811 S. 102nd Street, Suite 200, Seattle, WA 98168; telephone 206–762–1171; Internet https://www.aviationpartnersboeing.com. You may view this referenced service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425–227–1221. Issued in Renton, Washington, on May 13, 2015. Jeffrey E. Duven, Manager, Transport Airplane Directorate, Aircraft Certification Service. BILLING CODE 4910–13–P VerDate Sep<11>2014 17:42 Jun 04, 2015 Jkt 235001 Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2015–1419; Directorate Identifier 2014–NM–183–AD] RIN 2120–AA64 Airworthiness Directives; Lockheed Martin Corporation/Lockheed Martin Aeronautics Company Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: (1) The Manager, Seattle Aircraft Certification Office (ACO), FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the manager of the ACO, send it to the attention of the person identified in paragraph (l)(1) of this AD. Information may be emailed to: 9-ANM-Seattle-ACO-AMOCRequests@faa.gov. (2) Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/ certificate holding district office. (3) An AMOC that provides an acceptable level of safety may be used for any repair required by this AD if it is approved by 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. [FR Doc. 2015–13328 Filed 6–4–15; 8:45 am] DEPARTMENT OF TRANSPORTATION We propose to adopt a new airworthiness directive (AD) for all Lockheed Martin Corporation/Lockheed Martin Aeronautics Company Model 188 series airplanes. This proposed AD was prompted by an evaluation by the design approval holder (DAH) indicating the left and right lower surface panels of the wings are subject to widespread fatigue damage (WFD). This proposed AD would require repetitive inspections for cracking at these panels, and repair if necessary. The proposed AD would also require a one-time bolt-hole eddy current inspection of all open holes for cracking, repair if necessary, and modification. We are proposing this AD to prevent fatigue cracking of the left and right lower surface panels of the wings, which could result in reduced structural integrity of the airplane. DATES: We must receive comments on this proposed AD by July 20, 2015. ADDRESSES: You may send comments, using the procedures found in 14 CFR 11.43 and 11.45, by any of the following methods: • Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments. • Fax: 202–493–2251. • Mail: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC 20590. • Hand Delivery: Deliver to Mail address above between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For service information identified in this proposed AD, contact Lockheed Martin Corporation/Lockheed Martin Aeronautics Company, Airworthiness Office, Dept. 6A0M, Zone 0252, Column P–58, 86 S. Cobb Drive, Marietta, GA 30063; telephone 770–494–5444; fax 770–494–5445; email ams.portal@ lmco.com; Internet https:// SUMMARY: PO 00000 Frm 00028 Fmt 4702 Sfmt 4702 32069 www.lockheedmartin.com/ams/tools/ TechPubs.html. 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 https:// www.regulations.gov by searching for and locating Docket No. FAA–2015– 1419; 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: Carl Gray, Aerospace Engineer, Airframe Branch, ACE–117A, FAA, Atlanta Aircraft Certification Office (ACO), 1701 Columbia Avenue, College Park, GA 30337; phone: 404–474–5554; fax: 404– 474–5605; email: carl.w.gray@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– 2015–1419; Directorate Identifier 2014– NM–183–AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this proposed AD. We will consider all comments received by the closing date and may amend this proposed AD because of those comments. We will post all comments we receive, without change, to https:// www.regulations.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact we receive about this proposed AD. Discussion 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, E:\FR\FM\05JNP1.SGM 05JNP1 32070 Federal Register / Vol. 80, No. 108 / Friday, June 5, 2015 / Proposed Rules 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 rule (75 FR 69746, November 15, 2010) became effective on January 14, 2011. The WFD rule requires certain actions to prevent structural 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 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 action 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. This proposed AD was prompted by an evaluation by the DAH indicating that the left and right lower surface panels of the wings are subject to WFD. The root cause of WFD is fatigue cracks manifesting and growing simultaneously at similar structural details and stress levels on the outer wings. Fatigue cracking is increasingly likely as the airplane is being operated and is aging; without intervention, fatigue cracking of the left and right lower surface panels of the wings on the inboard and outboard sides of the buttock line (BL) 65 splice joint could result in reduced structural integrity of the airplane. Related Service Information Under 1 CFR part 51 We reviewed Lockheed Martin Electra Service Bulletin 88/SB–707C, Revision C, dated April 30, 2014. The service information describes procedures for repetitive inspections for cracking of the left and right lower surface panels of the wings on the inboard and outboard sides of the BL 65 splice joint, and repair if necessary. This service information also describes procedures for a one-time bolt-hole eddy current inspection of all open holes for cracking, repair if necessary, and modification of the BL 65 wing root joint. This service information is reasonably available because the interested parties have access to it through their normal course of business or by the means identified in the section of this NPRM. ADDRESSES Related ADs This proposed AD is related to AD 81–03–53, Amendment 39–4243 (Docket No. 81–NW–7–AD) (46 FR 52090, October 26, 1981); and AD 81–03–53R1, Amendment 39–4301 (Docket No. 81– NW–97–AD) (47 FR 3347, January 25, 1982); for all Lockheed Model L–188 series airplanes. AD 81–03–53R1 requires inspecting for fuel leakage and fatigue cracks, and replacement, as necessary, of defective parts on the wing lower BL 65 splice joints. 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 designs. Proposed AD Requirements This proposed AD would require accomplishing the actions specified in the service information described previously. 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 replaced 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 4 airplanes of U.S. registry. We estimate the following costs to comply with this proposed AD: ESTIMATED COSTS asabaliauskas on DSK5VPTVN1PROD with PROPOSALS Action Labor cost X-ray or ultrasonic inspections. Bolt hole inspections .............. Modification ............................ We estimate the following costs to do any necessary repairs that would be VerDate Sep<11>2014 17:42 Jun 04, 2015 Jkt 235001 required based on the results of the proposed inspections. We have no way PO 00000 Frm 00029 Fmt 4702 Up to $3,400 ... Up to $13,600. 0 5,000 60 work-hours × $85 per hour = $5,100 ............................... 400 work-hours × $85 per hour = $ 34,000 ......................... Cost on U.S. operators $0 Up to 40 work-hours × $85 per hour = up to $3,400 ........... Cost per product $5,100 ............. $39,000 ........... $20,400. $156,000. Parts cost Sfmt 4702 of determining the number of aircraft that might need these repairs. E:\FR\FM\05JNP1.SGM 05JNP1 Federal Register / Vol. 80, No. 108 / Friday, June 5, 2015 / Proposed Rules 32071 ON-CONDITION COSTS Action Labor cost Parts cost Cost per product Repair .............................................. 500 work-hours × $85 per hour = $42,500 ............................................... $0 $42,500 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. asabaliauskas on DSK5VPTVN1PROD 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 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 Sep<11>2014 17:42 Jun 04, 2015 Jkt 235001 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): ■ Lockheed Martin Corporation/Lockheed Martin Aeronautics Company: Docket No. FAA–2015–1419; Directorate Identifier 2014–NM–183–AD. (a) Comments Due Date We must receive comments by July 20, 2015. (b) Affected ADs This AD affects AD 81–03–53, Amendment 39–4243 (Docket No. 81–NW–7–AD) (46 FR 52090, October 26, 1981); and AD 81–03– 53R1, Amendment 39–4301 (Docket No. 81– NW–97–AD) (47 FR 3347, January 25, 1982). (c) Applicability This AD applies to Lockheed Martin Corporation/Lockheed Martin Aeronautics Company Model 188A and 188C airplanes, certificated in any category, serial numbers 1001 and subsequent. (d) Subject Air Transport Association (ATA) of America Code 57, Wings. (e) Unsafe Condition This AD was prompted by an evaluation by the design approval holder indicating the left and right lower surface panels of the wings are subject to widespread fatigue damage. We are issuing this AD to prevent fatigue cracking of the left and right lower surface panels of the wings on the inboard and outboard sides of the buttock line (BL) 65 splice joint, which could result in reduced structural integrity of the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Inspections and Repair At the later of the times specified in paragraphs (g)(1) and (g)(2) of this AD: Inspect for cracking of the inboard and outboard sides of the lower splice joint at BL 65, using X-ray, ultrasonic, and bolt-hole eddy current inspection techniques, as applicable, and repair any cracking found, in PO 00000 Frm 00030 Fmt 4702 Sfmt 4702 accordance with the Accomplishment Instructions of Lockheed Martin Electra Service Bulletin 88/SB–707C, Revision C, dated April 30, 2014. All applicable repairs must be done before further flight. Repeat the inspections at intervals not to exceed 2,000 flight hours, until the modification required by paragraph (h) of this AD has been done. Accomplishing the inspections required by this paragraph terminates the inspections required by paragraphs A. and B. of AD 81– 03–53, Amendment 39–4243 (Docket No. 81– NW–7–AD) (46 FR 52090, October 26, 1981); and AD 81–03–53R1, Amendment 39–4301 (Docket No. 81–NW–97–AD) (47 FR 3347–01, January 25, 1982). (1) Before the accumulation of 19,000 total flight hours. (2) Within 600 flight hours or 365 days after the effective date of this AD, whichever occurs first. (h) Modification At the later of the times specified in paragraphs (h)(1) and (h)(2) of this AD: Do a bolt-hole eddy current inspection of all open holes for cracking, repair any cracking found before further flight, and modify the BL 65 wing root lower joint, in accordance with the Accomplishment Instructions of Lockheed Martin Electra Service Bulletin 88/SB–707C, Revision C, dated April 30, 2014. Accomplishing this modification terminates the inspections required by paragraph (g) of this AD. (1) Before the accumulation of 29,000 total flight hours. (2) Within 600 flight hours or 365 days after the effective date of this AD, whichever occurs first. (i) No Reporting Required Although Lockheed Martin Electra Service Bulletin 88/SB–707C, Revision C, dated April 30, 2014, specifies to submit a report of crack findings, this AD does not include that requirement. (j) Alternative Methods of Compliance (AMOCs) (1) The Manager, Atlanta 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 (k)(1) of this AD. (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. E:\FR\FM\05JNP1.SGM 05JNP1 32072 Federal Register / Vol. 80, No. 108 / Friday, June 5, 2015 / Proposed Rules (k) Related Information (1) For more information about this AD, contact Carl Gray, Aerospace Engineer, Airframe Branch, ACE–117A, FAA, Atlanta ACO, 1701 Columbia Avenue, College Park, GA 30337; phone: 404–474–5554; fax: 404– 474–5605; email: carl.w.gray@faa.gov. (2) For service information identified in this AD, contact Lockheed Martin Corporation/Lockheed Martin Aeronautics Company, Airworthiness Office, Dept. 6A0M, Zone 0252, Column P–58, 86 S. Cobb Drive, Marietta, GA 30063; telephone 770–494– 5444; fax 770–494–5445; email ams.portal@ lmco.com; Internet https:// www.lockheedmartin.com/ams/tools/ TechPubs.html. You may view this service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425–227–1221. Issued in Renton, Washington, on May 14, 2015. Jeffrey E. Duven, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2015–13339 Filed 6–4–15; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2015–1935; Directorate Identifier 2014–SW–008–AD] RIN 2120–AA64 Airworthiness Directives; Agusta S.p.A. Helicopters Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: We propose to adopt a new airworthiness directive (AD) for Agusta S.p.A. (Agusta) Model AB139 and AW139 helicopters. This proposed AD would require visually inspecting certain subfloor frames for a crack. This proposed AD is prompted by reports of cracks on in-service helicopters. The proposed actions are intended to detect or prevent a crack in the subfloor frame, which could result in failure of the pilot and co-pilot pedal support frame and subsequent loss of control of the helicopter. asabaliauskas on DSK5VPTVN1PROD with PROPOSALS SUMMARY: We must receive comments on this proposed AD by August 4, 2015. ADDRESSES: You may send comments by any of the following methods: • Federal eRulemaking Docket: Go to https://www.regulations.gov. Follow the online instructions for sending your comments electronically. DATES: VerDate Sep<11>2014 17:42 Jun 04, 2015 Jkt 235001 • Fax: 202–493–2251. • Mail: Send comments to the U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC 20590–0001. • Hand Delivery: Deliver to the ‘‘Mail’’ address between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. Examining the AD Docket You may examine the AD docket on the Internet at https:// 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 European Aviation Safety Agency (EASA) AD, the economic 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 service information identified in this proposed AD, contact AgustaWestland, Product Support Engineering, Via del Gregge, 100, 21015 Lonate Pozzolo (VA) Italy, ATTN: Maurizio D’Angelo; telephone 39–0331– 664757; fax 39–0331–664680; or at https://www.agustawestland.com/ technical-bulletins. You may review the referenced service information at the FAA, Office of the Regional Counsel, Southwest Region, 2601 Meacham Blvd., Room 663, Fort Worth, Texas 76137. FOR FURTHER INFORMATION CONTACT: Robert Grant, Aviation Safety Engineer, Safety Management Group, FAA, 2601 Meacham Blvd., Fort Worth, Texas 76137; telephone (817) 222–5110; email robert.grant@faa.gov. SUPPLEMENTARY INFORMATION: Comments Invited We invite you to participate in this rulemaking by submitting written comments, data, or views. We also invite comments relating to the economic, environmental, energy, or federalism impacts that might result from adopting the proposals in this document. The most helpful comments reference a specific portion of the proposal, explain the reason for any recommended change, and include supporting data. To ensure the docket does not contain duplicate comments, commenters should send only one copy of written comments, or if comments are filed electronically, commenters should submit only one time. PO 00000 Frm 00031 Fmt 4702 Sfmt 4702 We will file in the docket all comments that we receive, as well as a report summarizing each substantive public contact with FAA personnel concerning this proposed rulemaking. Before acting on this proposal, we will consider all comments we receive on or before the closing date for comments. We will consider comments filed after the comment period has closed if it is possible to do so without incurring expense or delay. We may change this proposal in light of the comments we receive. Discussion EASA, which is the Technical Agent for the Member States of the European Union, has issued EASA AD No. 2014– 0048, dated March 4, 2014, to correct an unsafe condition for Agusta Model AB139 and AW139 helicopters with a serial number (S/N) 31005 through 31517 (except S/N 31007, 31415, 31431, 31491, 31500, 31508, and 31516) and S/ N 41001 through 41356 (except S/N 41355). EASA advises that cracks have been reported in the subfloor frame at station (STA) 2105 on in-service helicopters. This condition, if not detected and corrected, could lead to failure of the pedals supporting the frame, which in turn could lead to the pedals being inoperative and subsequent loss of control of the helicopter, EASA advises. The EASA AD requires repetitive inspections of the subfloor frame at STA 2105 for a crack. The EASA AD also requires installation of frame reinforcements before further flight if there is a crack or within 1,200 flight hours if there is no crack. The EASA AD provides that installation of the frame reinforcements constitutes terminating action for the repetitive inspections required by the AD. FAA’s Determination These helicopters have been approved by the aviation authority of Italy and are approved for operation in the United States. Pursuant to our bilateral agreement with Italy, EASA, its technical representative, has notified us of the unsafe condition described in its AD. We are proposing this AD because we evaluated all known relevant information and determined that an unsafe condition is likely to exist or develop on other products of the same type design. Related Service Information Under 1 CFR Part 51 We reviewed AgustaWestland Bolletino Tecnico No. 139–311, Revision B, dated June 4, 2014 (BT), for certain serial-numbered Agusta Model E:\FR\FM\05JNP1.SGM 05JNP1

Agencies

[Federal Register Volume 80, Number 108 (Friday, June 5, 2015)]
[Proposed Rules]
[Pages 32069-32072]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2015-13339]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2015-1419; Directorate Identifier 2014-NM-183-AD]
RIN 2120-AA64


Airworthiness Directives; Lockheed Martin Corporation/Lockheed 
Martin Aeronautics 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 all 
Lockheed Martin Corporation/Lockheed Martin Aeronautics Company Model 
188 series airplanes. This proposed AD was prompted by an evaluation by 
the design approval holder (DAH) indicating the left and right lower 
surface panels of the wings are subject to widespread fatigue damage 
(WFD). This proposed AD would require repetitive inspections for 
cracking at these panels, and repair if necessary. The proposed AD 
would also require a one-time bolt-hole eddy current inspection of all 
open holes for cracking, repair if necessary, and modification. We are 
proposing this AD to prevent fatigue cracking of the left and right 
lower surface panels of the wings, which could result in reduced 
structural integrity of the airplane.

DATES: We must receive comments on this proposed AD by July 20, 2015.

ADDRESSES: You may send comments, using the procedures found in 14 CFR 
11.43 and 11.45, by any of the following methods:
     Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments.
     Fax: 202-493-2251.
     Mail: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE., Washington, DC 20590.
     Hand Delivery: Deliver to Mail address above between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
    For service information identified in this proposed AD, contact 
Lockheed Martin Corporation/Lockheed Martin Aeronautics Company, 
Airworthiness Office, Dept. 6A0M, Zone 0252, Column P-58, 86 S. Cobb 
Drive, Marietta, GA 30063; telephone 770-494-5444; fax 770-494-5445; 
email ams.portal@lmco.com; Internet https://www.lockheedmartin.com/ams/tools/TechPubs.html. 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 https://www.regulations.gov by searching for and locating Docket No. FAA-2015-
1419; 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: Carl Gray, Aerospace Engineer, 
Airframe Branch, ACE-117A, FAA, Atlanta Aircraft Certification Office 
(ACO), 1701 Columbia Avenue, College Park, GA 30337; phone: 404-474-
5554; fax: 404-474-5605; email: carl.w.gray@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-2015-1419; 
Directorate Identifier 2014-NM-183-AD'' at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of this proposed AD. We 
will consider all comments received by the closing date and may amend 
this proposed AD because of those comments.
    We will post all comments we receive, without change, to https://www.regulations.gov, including any personal information you provide. We 
will also post a report summarizing each substantive verbal contact we 
receive about this proposed AD.

Discussion

    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,

[[Page 32070]]

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 rule (75 FR 69746, November 15, 2010) became 
effective on January 14, 2011. The WFD rule requires certain actions to 
prevent structural 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 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 action 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.
    This proposed AD was prompted by an evaluation by the DAH 
indicating that the left and right lower surface panels of the wings 
are subject to WFD. The root cause of WFD is fatigue cracks manifesting 
and growing simultaneously at similar structural details and stress 
levels on the outer wings. Fatigue cracking is increasingly likely as 
the airplane is being operated and is aging; without intervention, 
fatigue cracking of the left and right lower surface panels of the 
wings on the inboard and outboard sides of the buttock line (BL) 65 
splice joint could result in reduced structural integrity of the 
airplane.

Related Service Information Under 1 CFR part 51

    We reviewed Lockheed Martin Electra Service Bulletin 88/SB-707C, 
Revision C, dated April 30, 2014. The service information describes 
procedures for repetitive inspections for cracking of the left and 
right lower surface panels of the wings on the inboard and outboard 
sides of the BL 65 splice joint, and repair if necessary. This service 
information also describes procedures for a one-time bolt-hole eddy 
current inspection of all open holes for cracking, repair if necessary, 
and modification of the BL 65 wing root joint. This service information 
is reasonably available because the interested parties have access to 
it through their normal course of business or by the means identified 
in the ADDRESSES section of this NPRM.

Related ADs

    This proposed AD is related to AD 81-03-53, Amendment 39-4243 
(Docket No. 81-NW-7-AD) (46 FR 52090, October 26, 1981); and AD 81-03-
53R1, Amendment 39-4301 (Docket No. 81-NW-97-AD) (47 FR 3347, January 
25, 1982); for all Lockheed Model L-188 series airplanes. AD 81-03-53R1 
requires inspecting for fuel leakage and fatigue cracks, and 
replacement, as necessary, of defective parts on the wing lower BL 65 
splice joints.

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 designs.

Proposed AD Requirements

    This proposed AD would require accomplishing the actions specified 
in the service information described previously.

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 replaced 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 4 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
----------------------------------------------------------------------------------------------------------------
X-ray or ultrasonic inspections  Up to 40                        $0  Up to $3,400.........  Up to $13,600.
                                  work[dash]hours x
                                  $85 per hour = up
                                  to $3,400.
Bolt hole inspections..........  60 work-hours x                  0  $5,100...............  $20,400.
                                  $85 per hour =
                                  $5,100.
Modification...................  400 work-hours x             5,000  $39,000..............  $156,000.
                                  $85 per hour = $
                                  34,000.
----------------------------------------------------------------------------------------------------------------

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

[[Page 32071]]



                                               On-Condition Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                     Cost per
                  Action                                Labor cost                 Parts cost        product
----------------------------------------------------------------------------------------------------------------
Repair....................................  500 work-hours x $85 per hour =                 $0          $42,500
                                             $42,500.
----------------------------------------------------------------------------------------------------------------

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 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):

Lockheed Martin Corporation/Lockheed Martin Aeronautics Company: 
Docket No. FAA-2015-1419; Directorate Identifier 2014-NM-183-AD.

(a) Comments Due Date

    We must receive comments by July 20, 2015.

(b) Affected ADs

    This AD affects AD 81-03-53, Amendment 39-4243 (Docket No. 81-
NW-7-AD) (46 FR 52090, October 26, 1981); and AD 81-03-53R1, 
Amendment 39-4301 (Docket No. 81-NW-97-AD) (47 FR 3347, January 25, 
1982).

(c) Applicability

    This AD applies to Lockheed Martin Corporation/Lockheed Martin 
Aeronautics Company Model 188A and 188C airplanes, certificated in 
any category, serial numbers 1001 and subsequent.

(d) Subject

    Air Transport Association (ATA) of America Code 57, Wings.

(e) Unsafe Condition

    This AD was prompted by an evaluation by the design approval 
holder indicating the left and right lower surface panels of the 
wings are subject to widespread fatigue damage. We are issuing this 
AD to prevent fatigue cracking of the left and right lower surface 
panels of the wings on the inboard and outboard sides of the buttock 
line (BL) 65 splice joint, which could result in reduced structural 
integrity of the airplane.

(f) Compliance

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

(g) Inspections and Repair

    At the later of the times specified in paragraphs (g)(1) and 
(g)(2) of this AD: Inspect for cracking of the inboard and outboard 
sides of the lower splice joint at BL 65, using X-ray, ultrasonic, 
and bolt-hole eddy current inspection techniques, as applicable, and 
repair any cracking found, in accordance with the Accomplishment 
Instructions of Lockheed Martin Electra Service Bulletin 88/SB-707C, 
Revision C, dated April 30, 2014. All applicable repairs must be 
done before further flight. Repeat the inspections at intervals not 
to exceed 2,000 flight hours, until the modification required by 
paragraph (h) of this AD has been done. Accomplishing the 
inspections required by this paragraph terminates the inspections 
required by paragraphs A. and B. of AD 81-03-53, Amendment 39-4243 
(Docket No. 81-NW-7-AD) (46 FR 52090, October 26, 1981); and AD 81-
03-53R1, Amendment 39-4301 (Docket No. 81-NW-97-AD) (47 FR 3347-01, 
January 25, 1982).
    (1) Before the accumulation of 19,000 total flight hours.
    (2) Within 600 flight hours or 365 days after the effective date 
of this AD, whichever occurs first.

(h) Modification

    At the later of the times specified in paragraphs (h)(1) and 
(h)(2) of this AD: Do a bolt-hole eddy current inspection of all 
open holes for cracking, repair any cracking found before further 
flight, and modify the BL 65 wing root lower joint, in accordance 
with the Accomplishment Instructions of Lockheed Martin Electra 
Service Bulletin 88/SB-707C, Revision C, dated April 30, 2014. 
Accomplishing this modification terminates the inspections required 
by paragraph (g) of this AD.
    (1) Before the accumulation of 29,000 total flight hours.
    (2) Within 600 flight hours or 365 days after the effective date 
of this AD, whichever occurs first.

(i) No Reporting Required

    Although Lockheed Martin Electra Service Bulletin 88/SB-707C, 
Revision C, dated April 30, 2014, specifies to submit a report of 
crack findings, this AD does not include that requirement.

(j) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, Atlanta 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 (k)(1) of this AD.
    (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.

[[Page 32072]]

(k) Related Information

    (1) For more information about this AD, contact Carl Gray, 
Aerospace Engineer, Airframe Branch, ACE-117A, FAA, Atlanta ACO, 
1701 Columbia Avenue, College Park, GA 30337; phone: 404-474-5554; 
fax: 404-474-5605; email: carl.w.gray@faa.gov.
    (2) For service information identified in this AD, contact 
Lockheed Martin Corporation/Lockheed Martin Aeronautics Company, 
Airworthiness Office, Dept. 6A0M, Zone 0252, Column P-58, 86 S. Cobb 
Drive, Marietta, GA 30063; telephone 770-494-5444; fax 770-494-5445; 
email ams.portal@lmco.com; Internet https://www.lockheedmartin.com/ams/tools/TechPubs.html. You may view this service information at 
the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., 
Renton, WA. For information on the availability of this material at 
the FAA, call 425-227-1221.

    Issued in Renton, Washington, on May 14, 2015.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2015-13339 Filed 6-4-15; 8:45 am]
 BILLING CODE 4910-13-P
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