Airworthiness Directives; Lockheed Martin Corporation/Lockheed Martin Aeronautics Company Airplanes, 26370-26373 [2021-10262]

Download as PDF 26370 Federal Register / Vol. 86, No. 92 / Friday, May 14, 2021 / Rules and Regulations Note 2 to paragraph (h)(1): For obtaining the procedures for Bombardier Challenger 300 Airplane Flight Manual (Imperial Version), Publication No. CSP 100–1, use Document Identification No. CH 300 AFM–I. (2) Challenger 300 Airplane Flight Manual (Imperial Version), Publication No. CSP 100– 1, Revision 61, dated September 25, 2020. (3) Challenger 300 Airplane Flight Manual (Imperial Version), Publication No. CSP 100– 1, Revision 62, dated December 22, 2020. (i) Other FAA AD Provisions The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, New York ACO Branch, 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 responsible Flight Standards Office, as appropriate. If sending information directly to the manager of the certification office, send it to ATTN: Program Manager, Continuing Operational Safety, FAA, New York ACO Branch, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; telephone 516–228–7300; fax 516–794–5531. Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the responsible Flight Standards Office. (2) Contacting the Manufacturer: For any requirement in this AD to obtain instructions from a manufacturer, the instructions must be accomplished using a method approved by the Manager, New York ACO Branch, FAA; or Transport Canada Civil Aviation (TCCA); or Bombardier, Inc.’s TCCA Design Approval Organization (DAO). If approved by the DAO, the approval must include the DAO-authorized signature. khammond on DSKJM1Z7X2PROD with RULES (j) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) TCCA AD CF–2020–47, dated November 18, 2020, for related information. This MCAI may be found in the AD docket on the internet at https://www.regulations.gov by searching for and locating Docket No. FAA–2021–0342. (2) For more information about this AD, contact Jiwan Karunatilake, Aerospace Engineer, Airframe and Propulsion Section, FAA, New York ACO Branch, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; telephone 516–228–7300; fax 516–794–5531; email 9-avs-nyaco-cos@faa.gov. (3) Service information identified in this AD that is not incorporated by reference is available at the addresses specified in paragraphs (k)(3) and (4) of this AD. (k) Material Incorporated by Reference (1) The Director of the Federal Register approved the incorporation by reference (IBR) of the service information listed in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51. (2) You must use this service information as applicable to do the actions required by this AD, unless this AD specifies otherwise. (i) Section 02–04, ‘‘Systems Limitations,’’ of Chapter 02, ‘‘LIMITATIONS,’’ of the VerDate Sep<11>2014 16:17 May 13, 2021 Jkt 253001 Bombardier Challenger 300 Airplane Flight Manual (Imperial Version), Publication No. CSP 100–1, Revision 63, dated April 1, 2021. (ii) Section 04–03 of Chapter 04, ‘‘NORMAL PROCEDURES,’’ of the Bombardier Challenger 300 Airplane Flight Manual (Imperial Version), Publication No. CSP 100–1, Revision 63, dated April 1, 2021. (3) For service information identified in this AD, contact Bombardier, Inc., 200 Coˆte Vertu Road West, Dorval, Que´bec H4S 2A3, Canada; North America toll-free telephone 1– 866–538–1247 or direct-dial telephone 1– 514–855–2999; email ac.yul@ aero.bombardier.com; internet https:// www.bombardier.com. Note 2 to paragraph (j)(3): For obtaining the procedures for Bombardier Challenger 300 Airplane Flight Manual (Imperial Version), Publication No. CSP 100–1, use Document Identification No. CH 300 AFM– I. (4) You may view this service information at the FAA, Airworthiness Products Section, Operational Safety Branch, 2200 South 216th St., Des Moines, WA. For information on the availability of this material at the FAA, call 206–231–3195. (5) You may view this service information that is incorporated by reference at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, email fedreg.legal@nara.gov, or go to: https:// www.archives.gov/federal-register/cfr/ibrlocations.html. Issued on April 23, 2021. Lance T. Gant, Director, Compliance & Airworthiness Division, Aircraft Certification Service. [FR Doc. 2021–10259 Filed 5–11–21; 4:15 pm] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2021–0341; Project Identifier AD–2021–00325–T; Amendment 39–21529; AD 2021–09–15] RIN 2120–AA64 Airworthiness Directives; Lockheed Martin Corporation/Lockheed Martin Aeronautics Company Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Final rule; request for comments. AGENCY: The FAA is adopting a new airworthiness directive (AD) for all Lockheed Martin Corporation/Lockheed Martin Aeronautics Company Model 382, 382B, 382E, 382F, and 382G airplanes, type certificated in any category; and Model C–130A, C–130B, C–130BL, C–130E, C–130H, C–130H–30, SUMMARY: PO 00000 Frm 00024 Fmt 4700 Sfmt 4700 C–130J, C–130J–30, EC–130Q, HC– 130H, KC–130H, NC–130B, NC–130, and WC–130H airplanes, type certificated in the restricted or amateur category. This AD was prompted by a crack found on the web attachment flange of the center wing upper forward corner fitting. This AD requires an eddy current surface scan for cracks of the center wing upper and lower forward corner fittings and fasteners, a torque check of the left and right outer-wingto-center-wing front-beam-web-jointsplice-angle fasteners, and repair, retorqueing, or replacement if necessary. The FAA is issuing this AD to address the unsafe condition on these products. DATES: This AD is effective June 1, 2021. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of June 1, 2021. The FAA must receive comments on this AD by June 28, 2021. 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 final rule, contact Lockheed Martin Corporation/Lockheed Martin Aeronautics Company, Customer Support Center, Dept. 3E1M, Zone 0591, 86 S Cobb Drive, Marietta, GA 30063; telephone 770–494–9131; email hercules.support@lmco.com; internet https://www.lockheedmartin.com. You may view this service information at the FAA, Airworthiness Products Section, Operational Safety Branch, 2200 South 216th St., Des Moines, WA. For information on the availability of this material at the FAA, call 206–231–3195. It is also available at https:// www.regulations.gov by searching for and locating Docket No. FAA–2021– 0341. Examining the AD Docket You may examine the AD docket at https://www.regulations.gov by searching for and locating Docket No. FAA–2021–0341; or in person at Docket Operations between 9 a.m. and 5 p.m., Monday through Friday, except Federal E:\FR\FM\14MYR1.SGM 14MYR1 Federal Register / Vol. 86, No. 92 / Friday, May 14, 2021 / Rules and Regulations holidays. The AD docket contains this final rule, any comments received, and other information. The street address for the Docket Operations is listed above. Fred Caplan, Aerospace Engineer, Airframe Section, FAA, Atlanta ACO Branch, 1701 Columbia Avenue, College Park, GA 30337; phone: 404–474–5507; fax: 404–474–5606; email: Frederick.N.Caplan@faa.gov. FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: Background The FAA has received a report indicating that a crack was found on the web attachment flange of the center wing upper forward corner fitting. Loose fasteners in the wing station 220 wing joint at the front beam web can cause internal load redistribution and consequent cracked center wing upper and lower corner fittings and failed fasteners in those fittings. This condition, if not addressed, could result in reduced structural integrity of the airplane and loss of control of the airplane. The FAA is issuing this AD to address the unsafe condition on these products. FAA’s Determination The FAA is issuing this AD because the agency has determined the unsafe condition described previously is likely to exist or develop in other products of the same type design. khammond on DSKJM1Z7X2PROD with RULES Related Service Information Under 1 CFR Part 51 The FAA reviewed Lockheed Martin Aeronautics Company Alert Service Bulletin A382–57–99, Revision 1, dated February 17, 2021. This service information specifies procedures for an eddy current surface scan for cracks of the center wing upper and lower forward corner fittings and fasteners (including the exterior of the vertical flange of the corner fitting common to the front beam web and interior surfaces of the corner fitting horizontal and vertical flanges common to the beam cap), a torque check of left and right outer-wing-to-center-wing front-beamweb-joint-splice-angle fasteners (including checking for any loose, sheared, broken, or missing fasteners), retorqueing the outer-wing-to-centerwing front-beam-web-joint-splice-angle fasteners, and repair or replacement. 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. VerDate Sep<11>2014 16:17 May 13, 2021 Jkt 253001 AD Requirements This AD requires accomplishing the actions specified in the service information already described, except as discussed under ‘‘Differences Between this AD and the Service Information.’’ Differences Between This AD and the Service Information Lockheed Martin Aeronautics Company Alert Service Bulletin A382– 57–99, Revision 1, dated February 17, 2021, applies to Model 382, 382B, 382E, 382F, and 382G airplanes. This AD applies to Model C–130A, C–130B, C– 130BL, C–130E, C–130H, C–130H–30, C–130J, C–130J–30, EC–130Q, HC– 130H, KC–130H, NC–130B, NC–130, and WC–130H airplanes as well as the airplanes specified in Lockheed Martin Aeronautics Company Alert Service Bulletin A382–57–99, Revision 1, dated February 17, 2021. The FAA has confirmed that all airplanes identified in paragraph (c) of this AD can comply with the actions specified in Lockheed Martin Aeronautics Company Alert Service Bulletin A382–57–99, Revision 1, dated February 17, 2021. Impact on Intrastate Aviation in Alaska In light of the heavy reliance on aviation for intrastate transportation in Alaska, the FAA has fully considered the effects of this AD (including costs to be borne by affected operators) from the earliest possible stages of AD development. This AD is based on those considerations, and was developed with regard to minimizing the economic impact on operators to the extent possible, consistent with the safety objectives of this AD. In any event, the Federal Aviation Regulations require operators to correct an unsafe condition identified on an airplane to ensure operation of that airplane in an airworthy condition. The FAA has determined in this case that the requirements are necessary and the indirect costs would be outweighed by the safety benefits of the AD. Justification for Immediate Adoption and Determination of the Effective Date Section 553(b)(3)(B) of the Administrative Procedure Act (APA) (5 U.S.C. 551 et seq.) authorizes agencies to dispense with notice and comment procedures for rules when the agency, for ‘‘good cause,’’ finds that those procedures are ‘‘impracticable, unnecessary, or contrary to the public interest.’’ Under this section, an agency, upon finding good cause, may issue a final rule without providing notice and seeking comment prior to issuance. Further, section 553(d) of the APA authorizes agencies to make rules PO 00000 Frm 00025 Fmt 4700 Sfmt 4700 26371 effective in less than thirty days, upon a finding of good cause. An unsafe condition exists that requires the immediate adoption of this AD without providing an opportunity for public comments prior to adoption. The FAA has found that the risk to the flying public justifies forgoing notice and comment prior to adoption of this rule because loose fasteners in the wing station 220 wing joint at the front beam web can cause internal load redistribution, and consequent cracked center wing upper and lower corner fittings and failed fasteners in those fittings, resulting in reduced structural integrity of the airplane and loss of control of the airplane. Accordingly, notice and opportunity for prior public comment are impracticable and contrary to the public interest pursuant to 5 U.S.C. 553(b)(3)(B). In addition, the FAA finds that good cause exists pursuant to 5 U.S.C. 553(d) for making this amendment effective in less than 30 days, for the same reasons the FAA found good cause to forgo notice and comment. Comments Invited The FAA invites you to send any written data, views, or arguments about this final rule. Send your comments to an address listed under ADDRESSES. Include Docket No. FAA–2021–0341 and Project Identifier AD–2021–00325– T at the beginning of your comments. The most helpful comments reference a specific portion of the final rule, explain the reason for any recommended change, and include supporting data. The FAA will consider all comments received by the closing date and may amend this final rule because of those comments. Except for Confidential Business Information (CBI) as described in the following paragraph, and other information as described in 14 CFR 11.35, the FAA will post all comments received, without change, to https:// www.regulations.gov, including any personal information you provide. The agency will also post a report summarizing each substantive verbal contact received about this final rule. Confidential Business Information CBI is commercial or financial information that is both customarily and actually treated as private by its owner. Under the Freedom of Information Act (FOIA) (5 U.S.C. 552), CBI is exempt from public disclosure. If your comments responsive to this AD contain commercial or financial information that is customarily treated as private, that you actually treat as private, and that is relevant or responsive to this AD, E:\FR\FM\14MYR1.SGM 14MYR1 26372 Federal Register / Vol. 86, No. 92 / Friday, May 14, 2021 / Rules and Regulations it is important that you clearly designate the submitted comments as CBI. Please mark each page of your submission containing CBI as ‘‘PROPIN.’’ The FAA will treat such marked submissions as confidential under the FOIA, and they will not be placed in the public docket of this AD. Submissions containing CBI should be sent to Fred Caplan, Aerospace Engineer, Airframe Section, FAA, Atlanta ACO Branch, 1701 Columbia Avenue, College Park, GA 30337; phone: 404–474–5507; fax: 404– 474–5606; email: Frederick.N.Caplan@ faa.gov. Any commentary that the FAA receives that is not specifically designated as CBI will be placed in the public docket for this rulemaking. Regulatory Flexibility Act The requirements of the Regulatory Flexibility Act (RFA) do not apply when an agency finds good cause pursuant to 5 U.S.C. 553 to adopt a rule without prior notice and comment. Because the FAA has determined that it has good cause to adopt this rule without notice and comment, RFA analysis is not required. Costs of Compliance The FAA estimates that this AD affects 20 airplanes of U.S. registry. The FAA estimates the following costs to comply with this AD: ESTIMATED COSTS Action Labor cost Inspection, torque check, and retorque .......... 40 work-hours × $85 per hour = $3,400 ........ The FAA estimates the following costs to do any necessary replacements that would be required based on the results of the inspection. The FAA has no way of determining the number of Cost per product Parts cost $0 Cost on U.S. operators $3,400 $68,000 aircraft that might need these replacements: ON-CONDITION COSTS Action Labor cost Parts cost Replacement ............................ Up to 120 work-hours × $85 per hour = Up to $10,200 ........... Up to $100 ................ The FAA has received no definitive data on which to base the cost estimates for the on-condition repairs specified in this AD. Authority for This Rulemaking khammond on DSKJM1Z7X2PROD with RULES 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. The FAA is 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. This AD will not have federalism implications under Executive Order 13132. This AD will not have a substantial direct effect on the States, on the relationship between the national government and the States, or on the 16:17 May 13, 2021 List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA amends 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: ■ Regulatory Findings VerDate Sep<11>2014 distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify that this AD: Is not a ‘‘significant regulatory action’’ under Executive Order 12866. Jkt 253001 2021–09–15 Lockheed Martin Corporation/ Lockheed Martin Aeronautics Company: Amendment 39–21529; Docket No. FAA–2021–0341; Project Identifier AD– 2021–00325–T. PO 00000 Frm 00026 Fmt 4700 Sfmt 4700 Cost per product Up to $10,300. (a) Effective Date This airworthiness directive (AD) is effective June 1, 2021. (b) Affected ADs None. (c) Applicability This AD applies to all Lockheed Martin Corporation/Lockheed Martin Aeronautics Company Model 382, 382B, 382E, 382F, and 382G airplanes, type certificated in any category; and Model C–130A, C–130B, C– 130BL, C–130E, C–130H, C–130H–30, C– 130J, C–130J–30, EC–130Q, HC–130H, KC– 130H, NC–130B, NC–130, and WC–130H airplanes, type certificated in the restricted or amateur category. The restricted and amateur category airplanes were originally manufactured by Lockheed Martin Corporation/Lockheed Martin Aeronautics Company; current type certificate holders include, but are not limited to, those specified in paragraphs (c)(1) through (9) of this AD. (1) LeSEA Model C–130A airplanes, Type Certificate Data Sheet (TCDS) A34SO, Revision 1. (2) T.B.M, Inc. (transferred from Central Air Services, Inc.), Model C–130A airplanes, TCDS A39CE, Revision 3. (3) Western International Aviation, Inc., Model C–130A airplanes, TCDS A33NM. (4) USDA Forest Service Model C–130A airplanes, TCDS A15NM, Revision 4. (5) Snow Aviation International, Inc., Model C–130A airplanes, TCDS TQ3CH, Revision 1. (6) Heavylift Helicopter, Inc. (transferred from Hemet Valley Flying Service), Model C– 130A, TCDS A31NM airplanes, Revision 1. E:\FR\FM\14MYR1.SGM 14MYR1 Federal Register / Vol. 86, No. 92 / Friday, May 14, 2021 / Rules and Regulations (7) Heavylift Helicopters, Inc., Model C– 130B airplanes, TCDS A35NM, Revision 1. (8) Hawkins & Powers Aviation, Inc., Model HP–C–130A airplanes, TCDS A30NM, Revision 1. (9) Coulson Aviation (USA), Inc., Model EC–130Q airplanes, TCDS T00019LA, Revision 2. (d) Subject Air Transport Association (ATA) of America Code 57, Wings. (e) Unsafe Condition This AD was prompted by a report of a crack found on the web attachment flange of the center wing upper forward corner fitting. The FAA is issuing this AD to address loose fasteners in a certain wing joint at the front beam web, which can cause internal load redistribution, and consequent cracked center wing upper and lower corner fittings and failed fasteners in those fittings, resulting in reduced structural integrity of the airplane and loss of control of the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. khammond on DSKJM1Z7X2PROD with RULES (g) Inspection, Torque Check, and Corrective Actions At the applicable compliance time specified in paragraph (g)(1) or (2) of this AD, do an eddy current surface scan for cracks of the center wing upper and lower forward corner fittings and fasteners, and do a torque check of the left and right outer-wing-tocenter-wing front-beam-web-joint-spliceangle fasteners (including checking for any loose, sheared, broken, or missing fasteners), in accordance with the Accomplishment Instructions of Lockheed Martin Aeronautics Company Alert Service Bulletin A382–57–99, Revision 1, dated February 17, 2021. If any cracking is found during the inspection, repair before further flight using a method approved in accordance with the procedures specified in paragraph (j) of this AD. If any loose fastener is found during the torque check, retorque the fastener before further flight, in accordance with the Accomplishment Instructions of Lockheed Martin Aeronautics Company Alert Service Bulletin A382–57–99, Revision 1, dated February 17, 2021. If any sheared, broken, or missing fastener is found during the torque check, replace the fastener before further flight. (1) For airplanes that have accumulated 2,500 or more flight hours as of the effective date of this AD: Within 90 days after the effective date of this AD. (2) For airplanes that have accumulated less than 2,500 flight hours as of the effective date of this AD: Within 270 days after the effective date of this AD. (h) No Reporting Although Lockheed Martin Aeronautics Company Alert Service Bulletin A382–57–99, Revision 1, dated February 17, 2021, specifies to report inspection findings, this AD does not require any report. VerDate Sep<11>2014 16:17 May 13, 2021 Jkt 253001 (i) Special Flight Permit Special flight permits, as described in 14 CFR 21.197 and 21.199, are not allowed. (j) Alternative Methods of Compliance (AMOCs) (1) The Manager, Atlanta ACO Branch, 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 responsible Flight Standards Office, as appropriate. If sending information directly to the manager of the certification office, send it to the attention of the person identified in Related Information. (2) Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the responsible Flight Standards Office. (3) An AMOC that provides an acceptable level of safety may be used for any repair, modification, or alteration required by this AD if it is approved by a Lockheed Martin Corporation/Lockheed Martin Aeronautics Company Designated Engineering Representative (DER) that has been authorized by the Manager, Atlanta ACO Branch, FAA, to make those findings. To be approved, the repair, modification deviation, or alteration deviation must meet the certification basis of the airplane, and the approval must specifically refer to this AD. (k) Related Information For more information about this AD, contact Fred Caplan, Aerospace Engineer, Airframe Section, FAA, Atlanta ACO Branch, 1701 Columbia Avenue, College Park, GA 30337; phone: 404–474–5507; fax: 404–474– 5606; email: Frederick.N.Caplan@faa.gov. (l) Material Incorporated by Reference (1) The Director of the Federal Register approved the incorporation by reference (IBR) of the service information listed in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51. (2) You must use this service information as applicable to do the actions required by this AD, unless the AD specifies otherwise. (i) Lockheed Martin Aeronautics Company Alert Service Bulletin A382–57–99, Revision 1, dated February 17, 2021. (ii) [Reserved] (3) For service information identified in this AD, contact Lockheed Martin Corporation/Lockheed Martin Aeronautics Company, Customer Support Center, Dept. 3E1M, Zone 0591, 86 S Cobb Drive, Marietta, GA 30063; telephone 770–494–9131; email hercules.support@lmco.com; internet https:// www.lockheedmartin.com. (4) You may view this service information at the FAA, Airworthiness Products Section, Operational Safety Branch, 2200 South 216th St., Des Moines, WA. For information on the availability of this material at the FAA, call 206–231–3195. (5) You may view this service information that is incorporated by reference at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, email fedreg.legal@nara.gov, or go to: https:// www.archives.gov/federal-register/cfr/ibrlocations.html. PO 00000 Frm 00027 Fmt 4700 Sfmt 4700 26373 Issued on April 23, 2021. Gaetano A. Sciortino, Deputy Director for Strategic Initiatives, Compliance & Airworthiness Division, Aircraft Certification Service. [FR Doc. 2021–10262 Filed 5–11–21; 4:15 pm] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2021–0365; Project Identifier MCAI–2021–00527–T; Amendment 39–21553; AD 2021–10–20] RIN 2120–AA64 Airworthiness Directives; ATR—GIE Avions de Transport Re´gional Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Final rule; request for comments. AGENCY: The FAA is adopting a new airworthiness directive (AD) for certain ATR—GIE Avions de Transport Re´gional Model ATR42–500 and ATR72–212A airplanes. This AD was prompted by reports of temporary loss of all display units and the integrated electronic standby instrument (IESI). This AD requires revising the existing aircraft flight manual (AFM) and applicable corresponding operational procedures to update a systems limitation, limiting dispatch with certain equipment inoperative, performing an operational test of a certain contactor and an electrical test of a certain battery toggle switch, and corrective actions if necessary, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products. DATES: This AD becomes effective May 14, 2021. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of May 14, 2021. The FAA must receive comments on this AD by June 28, 2021. 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– SUMMARY: E:\FR\FM\14MYR1.SGM 14MYR1

Agencies

[Federal Register Volume 86, Number 92 (Friday, May 14, 2021)]
[Rules and Regulations]
[Pages 26370-26373]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2021-10262]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2021-0341; Project Identifier AD-2021-00325-T; 
Amendment 39-21529; AD 2021-09-15]
RIN 2120-AA64


Airworthiness Directives; Lockheed Martin Corporation/Lockheed 
Martin Aeronautics Company Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule; request for comments.

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

SUMMARY: The FAA is adopting a new airworthiness directive (AD) for all 
Lockheed Martin Corporation/Lockheed Martin Aeronautics Company Model 
382, 382B, 382E, 382F, and 382G airplanes, type certificated in any 
category; and Model C-130A, C-130B, C-130BL, C-130E, C-130H, C-130H-30, 
C-130J, C-130J-30, EC-130Q, HC-130H, KC-130H, NC-130B, NC-130, and WC-
130H airplanes, type certificated in the restricted or amateur 
category. This AD was prompted by a crack found on the web attachment 
flange of the center wing upper forward corner fitting. This AD 
requires an eddy current surface scan for cracks of the center wing 
upper and lower forward corner fittings and fasteners, a torque check 
of the left and right outer-wing-to-center-wing front-beam-web-joint-
splice-angle fasteners, and repair, retorqueing, or replacement if 
necessary. The FAA is issuing this AD to address the unsafe condition 
on these products.

DATES: This AD is effective June 1, 2021.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of June 1, 
2021.
    The FAA must receive comments on this AD by June 28, 2021.

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 final rule, contact 
Lockheed Martin Corporation/Lockheed Martin Aeronautics Company, 
Customer Support Center, Dept. 3E1M, Zone 0591, 86 S Cobb Drive, 
Marietta, GA 30063; telephone 770-494-9131; email 
[email protected]; internet https://www.lockheedmartin.com. You 
may view this service information at the FAA, Airworthiness Products 
Section, Operational Safety Branch, 2200 South 216th St., Des Moines, 
WA. For information on the availability of this material at the FAA, 
call 206-231-3195. It is also available at https://www.regulations.gov 
by searching for and locating Docket No. FAA-2021-0341.

Examining the AD Docket

    You may examine the AD docket at https://www.regulations.gov by 
searching for and locating Docket No. FAA-2021-0341; or in person at 
Docket Operations between 9 a.m. and 5 p.m., Monday through Friday, 
except Federal

[[Page 26371]]

holidays. The AD docket contains this final rule, any comments 
received, and other information. The street address for the Docket 
Operations is listed above.

FOR FURTHER INFORMATION CONTACT: Fred Caplan, Aerospace Engineer, 
Airframe Section, FAA, Atlanta ACO Branch, 1701 Columbia Avenue, 
College Park, GA 30337; phone: 404-474-5507; fax: 404-474-5606; email: 
[email protected].

SUPPLEMENTARY INFORMATION:

Background

    The FAA has received a report indicating that a crack was found on 
the web attachment flange of the center wing upper forward corner 
fitting. Loose fasteners in the wing station 220 wing joint at the 
front beam web can cause internal load redistribution and consequent 
cracked center wing upper and lower corner fittings and failed 
fasteners in those fittings. This condition, if not addressed, could 
result in reduced structural integrity of the airplane and loss of 
control of the airplane. The FAA is issuing this AD to address the 
unsafe condition on these products.

FAA's Determination

    The FAA is issuing this AD because the agency has determined the 
unsafe condition described previously is likely to exist or develop in 
other products of the same type design.

Related Service Information Under 1 CFR Part 51

    The FAA reviewed Lockheed Martin Aeronautics Company Alert Service 
Bulletin A382-57-99, Revision 1, dated February 17, 2021. This service 
information specifies procedures for an eddy current surface scan for 
cracks of the center wing upper and lower forward corner fittings and 
fasteners (including the exterior of the vertical flange of the corner 
fitting common to the front beam web and interior surfaces of the 
corner fitting horizontal and vertical flanges common to the beam cap), 
a torque check of left and right outer-wing-to-center-wing front-beam-
web-joint-splice-angle fasteners (including checking for any loose, 
sheared, broken, or missing fasteners), retorqueing the outer-wing-to-
center-wing front-beam-web-joint-splice-angle fasteners, and repair or 
replacement. 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.

AD Requirements

    This AD requires accomplishing the actions specified in the service 
information already described, except as discussed under ``Differences 
Between this AD and the Service Information.''

Differences Between This AD and the Service Information

    Lockheed Martin Aeronautics Company Alert Service Bulletin A382-57-
99, Revision 1, dated February 17, 2021, applies to Model 382, 382B, 
382E, 382F, and 382G airplanes. This AD applies to Model C-130A, C-
130B, C-130BL, C-130E, C-130H, C-130H-30, C-130J, C-130J-30, EC-130Q, 
HC-130H, KC-130H, NC-130B, NC-130, and WC-130H airplanes as well as the 
airplanes specified in Lockheed Martin Aeronautics Company Alert 
Service Bulletin A382-57-99, Revision 1, dated February 17, 2021. The 
FAA has confirmed that all airplanes identified in paragraph (c) of 
this AD can comply with the actions specified in Lockheed Martin 
Aeronautics Company Alert Service Bulletin A382-57-99, Revision 1, 
dated February 17, 2021.

Impact on Intrastate Aviation in Alaska

    In light of the heavy reliance on aviation for intrastate 
transportation in Alaska, the FAA has fully considered the effects of 
this AD (including costs to be borne by affected operators) from the 
earliest possible stages of AD development. This AD is based on those 
considerations, and was developed with regard to minimizing the 
economic impact on operators to the extent possible, consistent with 
the safety objectives of this AD. In any event, the Federal Aviation 
Regulations require operators to correct an unsafe condition identified 
on an airplane to ensure operation of that airplane in an airworthy 
condition. The FAA has determined in this case that the requirements 
are necessary and the indirect costs would be outweighed by the safety 
benefits of the AD.

Justification for Immediate Adoption and Determination of the Effective 
Date

    Section 553(b)(3)(B) of the Administrative Procedure Act (APA) (5 
U.S.C. 551 et seq.) authorizes agencies to dispense with notice and 
comment procedures for rules when the agency, for ``good cause,'' finds 
that those procedures are ``impracticable, unnecessary, or contrary to 
the public interest.'' Under this section, an agency, upon finding good 
cause, may issue a final rule without providing notice and seeking 
comment prior to issuance. Further, section 553(d) of the APA 
authorizes agencies to make rules effective in less than thirty days, 
upon a finding of good cause.
    An unsafe condition exists that requires the immediate adoption of 
this AD without providing an opportunity for public comments prior to 
adoption. The FAA has found that the risk to the flying public 
justifies forgoing notice and comment prior to adoption of this rule 
because loose fasteners in the wing station 220 wing joint at the front 
beam web can cause internal load redistribution, and consequent cracked 
center wing upper and lower corner fittings and failed fasteners in 
those fittings, resulting in reduced structural integrity of the 
airplane and loss of control of the airplane. Accordingly, notice and 
opportunity for prior public comment are impracticable and contrary to 
the public interest pursuant to 5 U.S.C. 553(b)(3)(B).
    In addition, the FAA finds that good cause exists pursuant to 5 
U.S.C. 553(d) for making this amendment effective in less than 30 days, 
for the same reasons the FAA found good cause to forgo notice and 
comment.

Comments Invited

    The FAA invites you to send any written data, views, or arguments 
about this final rule. Send your comments to an address listed under 
ADDRESSES. Include Docket No. FAA-2021-0341 and Project Identifier AD-
2021-00325-T at the beginning of your comments. The most helpful 
comments reference a specific portion of the final rule, explain the 
reason for any recommended change, and include supporting data. The FAA 
will consider all comments received by the closing date and may amend 
this final rule because of those comments.
    Except for Confidential Business Information (CBI) as described in 
the following paragraph, and other information as described in 14 CFR 
11.35, the FAA will post all comments received, without change, to 
https://www.regulations.gov, including any personal information you 
provide. The agency will also post a report summarizing each 
substantive verbal contact received about this final rule.

Confidential Business Information

    CBI is commercial or financial information that is both customarily 
and actually treated as private by its owner. Under the Freedom of 
Information Act (FOIA) (5 U.S.C. 552), CBI is exempt from public 
disclosure. If your comments responsive to this AD contain commercial 
or financial information that is customarily treated as private, that 
you actually treat as private, and that is relevant or responsive to 
this AD,

[[Page 26372]]

it is important that you clearly designate the submitted comments as 
CBI. Please mark each page of your submission containing CBI as 
``PROPIN.'' The FAA will treat such marked submissions as confidential 
under the FOIA, and they will not be placed in the public docket of 
this AD. Submissions containing CBI should be sent to Fred Caplan, 
Aerospace Engineer, Airframe Section, FAA, Atlanta ACO Branch, 1701 
Columbia Avenue, College Park, GA 30337; phone: 404-474-5507; fax: 404-
474-5606; email: [email protected]. Any commentary that the 
FAA receives that is not specifically designated as CBI will be placed 
in the public docket for this rulemaking.

Regulatory Flexibility Act

    The requirements of the Regulatory Flexibility Act (RFA) do not 
apply when an agency finds good cause pursuant to 5 U.S.C. 553 to adopt 
a rule without prior notice and comment. Because the FAA has determined 
that it has good cause to adopt this rule without notice and comment, 
RFA analysis is not required.

Costs of Compliance

    The FAA estimates that this AD affects 20 airplanes of U.S. 
registry. The FAA estimates the following costs to comply with this AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                     Cost per      Cost on U.S.
                Action                         Labor cost           Parts cost        product        operators
----------------------------------------------------------------------------------------------------------------
Inspection, torque check, and retorque  40 work-hours x $85 per               $0          $3,400         $68,000
                                         hour = $3,400.
----------------------------------------------------------------------------------------------------------------

    The FAA estimates the following costs to do any necessary 
replacements that would be required based on the results of the 
inspection. The FAA has no way of determining the number of aircraft 
that might need these replacements:

                                               On-Condition Costs
----------------------------------------------------------------------------------------------------------------
            Action                    Labor cost                 Parts cost                Cost per product
----------------------------------------------------------------------------------------------------------------
Replacement...................  Up to 120 work-hours x  Up to $100.................  Up to $10,300.
                                 $85 per hour = Up to
                                 $10,200.
----------------------------------------------------------------------------------------------------------------

    The FAA has received no definitive data on which to base the cost 
estimates for the on-condition repairs specified in this 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.
    The FAA is 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

    This AD will not have federalism implications under Executive Order 
13132. This AD will not have a substantial direct effect on the States, 
on the relationship between the national government and the States, or 
on the distribution of power and responsibilities among the various 
levels of government.
    For the reasons discussed above, I certify that this AD:
    Is not a ``significant regulatory action'' under Executive Order 
12866.

List of Subjects in 14 CFR Part 39

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

Adoption of the Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA amends 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:

2021-09-15 Lockheed Martin Corporation/Lockheed Martin Aeronautics 
Company: Amendment 39-21529; Docket No. FAA-2021-0341; Project 
Identifier AD-2021-00325-T.

(a) Effective Date

    This airworthiness directive (AD) is effective June 1, 2021.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to all Lockheed Martin Corporation/Lockheed 
Martin Aeronautics Company Model 382, 382B, 382E, 382F, and 382G 
airplanes, type certificated in any category; and Model C-130A, C-
130B, C-130BL, C-130E, C-130H, C-130H-30, C-130J, C-130J-30, EC-
130Q, HC-130H, KC-130H, NC-130B, NC-130, and WC-130H airplanes, type 
certificated in the restricted or amateur category. The restricted 
and amateur category airplanes were originally manufactured by 
Lockheed Martin Corporation/Lockheed Martin Aeronautics Company; 
current type certificate holders include, but are not limited to, 
those specified in paragraphs (c)(1) through (9) of this AD.
    (1) LeSEA Model C-130A airplanes, Type Certificate Data Sheet 
(TCDS) A34SO, Revision 1.
    (2) T.B.M, Inc. (transferred from Central Air Services, Inc.), 
Model C-130A airplanes, TCDS A39CE, Revision 3.
    (3) Western International Aviation, Inc., Model C-130A 
airplanes, TCDS A33NM.
    (4) USDA Forest Service Model C-130A airplanes, TCDS A15NM, 
Revision 4.
    (5) Snow Aviation International, Inc., Model C-130A airplanes, 
TCDS TQ3CH, Revision 1.
    (6) Heavylift Helicopter, Inc. (transferred from Hemet Valley 
Flying Service), Model C-130A, TCDS A31NM airplanes, Revision 1.

[[Page 26373]]

    (7) Heavylift Helicopters, Inc., Model C-130B airplanes, TCDS 
A35NM, Revision 1.
    (8) Hawkins & Powers Aviation, Inc., Model HP-C-130A airplanes, 
TCDS A30NM, Revision 1.
    (9) Coulson Aviation (USA), Inc., Model EC-130Q airplanes, TCDS 
T00019LA, Revision 2.

(d) Subject

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

(e) Unsafe Condition

    This AD was prompted by a report of a crack found on the web 
attachment flange of the center wing upper forward corner fitting. 
The FAA is issuing this AD to address loose fasteners in a certain 
wing joint at the front beam web, which can cause internal load 
redistribution, and consequent cracked center wing upper and lower 
corner fittings and failed fasteners in those fittings, resulting in 
reduced structural integrity of the airplane and loss of control of 
the airplane.

(f) Compliance

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

(g) Inspection, Torque Check, and Corrective Actions

    At the applicable compliance time specified in paragraph (g)(1) 
or (2) of this AD, do an eddy current surface scan for cracks of the 
center wing upper and lower forward corner fittings and fasteners, 
and do a torque check of the left and right outer-wing-to-center-
wing front-beam-web-joint-splice-angle fasteners (including checking 
for any loose, sheared, broken, or missing fasteners), in accordance 
with the Accomplishment Instructions of Lockheed Martin Aeronautics 
Company Alert Service Bulletin A382-57-99, Revision 1, dated 
February 17, 2021. If any cracking is found during the inspection, 
repair before further flight using a method approved in accordance 
with the procedures specified in paragraph (j) of this AD. If any 
loose fastener is found during the torque check, retorque the 
fastener before further flight, in accordance with the 
Accomplishment Instructions of Lockheed Martin Aeronautics Company 
Alert Service Bulletin A382-57-99, Revision 1, dated February 17, 
2021. If any sheared, broken, or missing fastener is found during 
the torque check, replace the fastener before further flight.
    (1) For airplanes that have accumulated 2,500 or more flight 
hours as of the effective date of this AD: Within 90 days after the 
effective date of this AD.
    (2) For airplanes that have accumulated less than 2,500 flight 
hours as of the effective date of this AD: Within 270 days after the 
effective date of this AD.

(h) No Reporting

    Although Lockheed Martin Aeronautics Company Alert Service 
Bulletin A382-57-99, Revision 1, dated February 17, 2021, specifies 
to report inspection findings, this AD does not require any report.

(i) Special Flight Permit

    Special flight permits, as described in 14 CFR 21.197 and 
21.199, are not allowed.

(j) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, Atlanta ACO Branch, 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 responsible Flight Standards Office, 
as appropriate. If sending information directly to the manager of 
the certification office, send it to the attention of the person 
identified in Related Information.
    (2) Before using any approved AMOC, notify your appropriate 
principal inspector, or lacking a principal inspector, the manager 
of the responsible Flight Standards Office.
    (3) An AMOC that provides an acceptable level of safety may be 
used for any repair, modification, or alteration required by this AD 
if it is approved by a Lockheed Martin Corporation/Lockheed Martin 
Aeronautics Company Designated Engineering Representative (DER) that 
has been authorized by the Manager, Atlanta ACO Branch, FAA, to make 
those findings. To be approved, the repair, modification deviation, 
or alteration deviation must meet the certification basis of the 
airplane, and the approval must specifically refer to this AD.

(k) Related Information

    For more information about this AD, contact Fred Caplan, 
Aerospace Engineer, Airframe Section, FAA, Atlanta ACO Branch, 1701 
Columbia Avenue, College Park, GA 30337; phone: 404-474-5507; fax: 
404-474-5606; email: [email protected].

(l) Material Incorporated by Reference

    (1) The Director of the Federal Register approved the 
incorporation by reference (IBR) of the service information listed 
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
    (2) You must use this service information as applicable to do 
the actions required by this AD, unless the AD specifies otherwise.
    (i) Lockheed Martin Aeronautics Company Alert Service Bulletin 
A382-57-99, Revision 1, dated February 17, 2021.
    (ii) [Reserved]
    (3) For service information identified in this AD, contact 
Lockheed Martin Corporation/Lockheed Martin Aeronautics Company, 
Customer Support Center, Dept. 3E1M, Zone 0591, 86 S Cobb Drive, 
Marietta, GA 30063; telephone 770-494-9131; email 
[email protected]; internet https://www.lockheedmartin.com.
    (4) You may view this service information at the FAA, 
Airworthiness Products Section, Operational Safety Branch, 2200 
South 216th St., Des Moines, WA. For information on the availability 
of this material at the FAA, call 206-231-3195.
    (5) You may view this service information that is incorporated 
by reference at the National Archives and Records Administration 
(NARA). For information on the availability of this material at 
NARA, email [email protected], or go to: https://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued on April 23, 2021.
Gaetano A. Sciortino,
Deputy Director for Strategic Initiatives, Compliance & Airworthiness 
Division, Aircraft Certification Service.
[FR Doc. 2021-10262 Filed 5-11-21; 4:15 pm]
BILLING CODE 4910-13-P
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