80 FR 32069 - Airworthiness Directives; Lockheed Martin Corporation/Lockheed Martin Aeronautics Company Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 80, Issue 108 (June 5, 2015)
Federal Aviation Administration
Federal Register Volume 80, Issue 108 (June 5, 2015)
| Page Range | 32069-32072 | |
| FR Document | 2015-13339 |
[Federal Register Volume 80, Number 108 (Friday, June 5, 2015)] [Proposed Rules] [Pages 32069-32072] From the Federal Register Online [www.thefederalregister.org] [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 http://www.regulations.gov. Follow the instructions for submitting comments. Fax: 202-493-2251. Mail: U.S. Department of Transportation, Docket Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue SE., Washington, DC 20590. Hand Delivery: Deliver to Mail address above between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For service information identified in this proposed AD, contact 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 http://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 http://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 http://www.regulations.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact we receive about this proposed AD. Discussion Structural fatigue damage is progressive. It begins as minute cracks, and those cracks grow under the action of repeated stresses. This can happen because of normal operational conditions and design attributes, or because of isolated situations or incidents such as material defects, poor fabrication quality, or corrosion pits, [[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 http://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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4, 2014, specifies a compliance time ‘‘after DEPARTMENT OF TRANSPORTATION www.lockheedmartin.com/ams/tools/
the initial issue date on this service bulletin,’’ TechPubs.html. You may view this
this AD requires compliance within the Federal Aviation Administration referenced service information at the
specified compliance time after the effective FAA, Transport Airplane Directorate,
date of this AD. 14 CFR Part 39 1601 Lind Avenue SW., Renton, WA.
(2) Where Aviation Partners Boeing Service For information on the availability of
[Docket No. FAA–2015–1419; Directorate
Bulletin AP767–57–010, Revision 7, dated this material at the FAA, call 425–227–
Identifier 2014–NM–183–AD]
November 4, 2014, specifies to contact 1221.
Boeing for repair instructions: Before further RIN 2120–AA64
flight, repair the cracking using a method Examining the AD Docket
approved in accordance with the procedures Airworthiness Directives; Lockheed You may examine the AD docket on
specified in paragraph (k) of this AD. Martin Corporation/Lockheed Martin the Internet at http://
Aeronautics Company Airplanes www.regulations.gov by searching for
(k) Alternative Methods of Compliance
(AMOCs) AGENCY: Federal Aviation and locating Docket No. FAA–2015–
Administration (FAA), DOT. 1419; or in person at the Docket
(1) The Manager, Seattle Aircraft Management Facility between 9 a.m.
Certification Office (ACO), FAA, has the ACTION: Notice of proposed rulemaking
and 5 p.m., Monday through Friday,
authority to approve AMOCs for this AD, if (NPRM). except Federal holidays. The AD docket
requested using the procedures found in 14 contains this proposed AD, the
CFR 39.19. In accordance with 14 CFR 39.19, SUMMARY: We propose to adopt a new
airworthiness directive (AD) for all regulatory evaluation, any comments
send your request to your principal inspector received, and other information. The
or local Flight Standards District Office, as Lockheed Martin Corporation/Lockheed
Martin Aeronautics Company Model street address for the Docket Office
appropriate. If sending information directly (phone: 800–647–5527) is in the
to the manager of the ACO, send it to the 188 series airplanes. This proposed AD
was prompted by an evaluation by the ADDRESSES section. Comments will be
attention of the person identified in available in the AD docket shortly after
paragraph (l)(1) of this AD. Information may design approval holder (DAH)
indicating the left and right lower receipt.
be emailed to: 9-ANM-Seattle-ACO-AMOC-
surface panels of the wings are subject FOR FURTHER INFORMATION CONTACT: Carl
Requests@faa.gov.
(2) Before using any approved AMOC, to widespread fatigue damage (WFD). Gray, Aerospace Engineer, Airframe
notify your appropriate principal inspector, This proposed AD would require Branch, ACE–117A, FAA, Atlanta
or lacking a principal inspector, the manager repetitive inspections for cracking at Aircraft Certification Office (ACO), 1701
of the local flight standards district office/ these panels, and repair if necessary. Columbia Avenue, College Park, GA
certificate holding district office. The proposed AD would also require a 30337; phone: 404–474–5554; fax: 404–
(3) An AMOC that provides an acceptable one-time bolt-hole eddy current 474–5605; email: carl.w.gray@faa.gov.
level of safety may be used for any repair inspection of all open holes for SUPPLEMENTARY INFORMATION:
required by this AD if it is approved by the cracking, repair if necessary, and Comments Invited
Boeing Commercial Airplanes Organization modification. We are proposing this AD
Designation Authorization (ODA) that has to prevent fatigue cracking of the left We invite you to send any written
been authorized by the Manager, Seattle and right lower surface panels of the relevant data, views, or arguments about
ACO, to make those findings. For a repair wings, which could result in reduced this proposal. Send your comments to
method to be approved the repair must meet structural integrity of the airplane. an address listed under the ADDRESSES
the certification basis of the airplane and the section. Include ‘‘Docket No. FAA–
DATES: We must receive comments on
approval must specifically refer to this AD. 2015–1419; Directorate Identifier 2014–
this proposed AD by July 20, 2015. NM–183–AD’’ at the beginning of your
(l) Related Information ADDRESSES: You may send comments, comments. We specifically invite
(1) For more information about this AD, using the procedures found in 14 CFR comments on the overall regulatory,
contact Allen Rauschendorfer, Aerospace 11.43 and 11.45, by any of the following economic, environmental, and energy
Engineer, Airframe Branch, ANM–120S, methods: aspects of this proposed AD. We will
FAA, Seattle Aircraft Certification Office, • Federal eRulemaking Portal: Go to consider all comments received by the
1601 Lind Avenue SW., Renton, WA 98057– http://www.regulations.gov. Follow the closing date and may amend this
3356; phone: 425–917–6487; fax: 425–917– instructions for submitting comments. proposed AD because of those
6590; email: Allen.Rauschendorfer@faa.gov. • Fax: 202–493–2251. comments.
(2) For service information identified in • Mail: U.S. Department of We will post all comments we
this AD, contact Aviation Partners Boeing, Transportation, Docket Operations, M– receive, without change, to http://
2811 S. 102nd Street, Suite 200, Seattle, WA 30, West Building Ground Floor, Room www.regulations.gov, including any
98168; telephone 206–762–1171; Internet W12–140, 1200 New Jersey Avenue SE., personal information you provide. We
https://www.aviationpartnersboeing.com. Washington, DC 20590. will also post a report summarizing each
You may view this referenced service • Hand Delivery: Deliver to Mail substantive verbal contact we receive
information at the FAA, Transport Airplane address above between 9 a.m. and 5 about this proposed AD.
Directorate, 1601 Lind Avenue SW., Renton, p.m., Monday through Friday, except
WA. For information on the availability of Federal holidays. Discussion
asabaliauskas on DSK5VPTVN1PROD with PROPOSALS
this material at the FAA, call 425–227–1221. For service information identified in Structural fatigue damage is
this proposed AD, contact Lockheed progressive. It begins as minute cracks,
Issued in Renton, Washington, on May 13,
2015.
Martin Corporation/Lockheed Martin and those cracks grow under the action
Aeronautics Company, Airworthiness of repeated stresses. This can happen
Jeffrey E. Duven, Office, Dept. 6A0M, Zone 0252, Column because of normal operational
Manager, Transport Airplane Directorate, P–58, 86 S. Cobb Drive, Marietta, GA conditions and design attributes, or
Aircraft Certification Service. 30063; telephone 770–494–5444; fax because of isolated situations or
[FR Doc. 2015–13328 Filed 6–4–15; 8:45 am] 770–494–5445; email ams.portal@ incidents such as material defects, poor
BILLING CODE 4910–13–P lmco.com; Internet http:// fabrication quality, or corrosion pits,
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ON-CONDITION COSTS
Cost per
Action Labor cost Parts cost product
Repair .............................................. 500 work-hours × $85 per hour = $42,500 ............................................... $0 $42,500
Authority for This Rulemaking the FAA proposes to amend 14 CFR part accordance with the Accomplishment
39 as follows: Instructions of Lockheed Martin Electra
Title 49 of the United States Code Service Bulletin 88/SB–707C, Revision C,
specifies the FAA’s authority to issue PART 39—AIRWORTHINESS dated April 30, 2014. All applicable repairs
rules on aviation safety. Subtitle I, DIRECTIVES must be done before further flight. Repeat the
section 106, describes the authority of inspections at intervals not to exceed 2,000
the FAA Administrator. Subtitle VII: ■ 1. The authority citation for part 39 flight hours, until the modification required
Aviation Programs, describes in more continues to read as follows: by paragraph (h) of this AD has been done.
detail the scope of the Agency’s Accomplishing the inspections required by
Authority: 49 U.S.C. 106(g), 40113, 44701.
authority. this paragraph terminates the inspections
We are issuing this rulemaking under required by paragraphs A. and B. of AD 81–
§ 39.13 [Amended]
the authority described in Subtitle VII, 03–53, Amendment 39–4243 (Docket No. 81–
■ 2. The FAA amends § 39.13 by adding NW–7–AD) (46 FR 52090, October 26, 1981);
Part A, Subpart III, Section 44701: the following new airworthiness and AD 81–03–53R1, Amendment 39–4301
‘‘General requirements.’’ Under that directive (AD): (Docket No. 81–NW–97–AD) (47 FR 3347–01,
section, Congress charges the FAA with January 25, 1982).
Lockheed Martin Corporation/Lockheed
promoting safe flight of civil aircraft in Martin Aeronautics Company: Docket (1) Before the accumulation of 19,000 total
air commerce by prescribing regulations No. FAA–2015–1419; Directorate flight hours.
for practices, methods, and procedures Identifier 2014–NM–183–AD. (2) Within 600 flight hours or 365 days
the Administrator finds necessary for after the effective date of this AD, whichever
safety in air commerce. This regulation (a) Comments Due Date occurs first.
is within the scope of that authority We must receive comments by July 20, (h) Modification
because it addresses an unsafe condition 2015.
At the later of the times specified in
that is likely to exist or develop on
(b) Affected ADs paragraphs (h)(1) and (h)(2) of this AD: Do a
products identified in this rulemaking bolt-hole eddy current inspection of all open
action. This AD affects AD 81–03–53, Amendment
39–4243 (Docket No. 81–NW–7–AD) (46 FR holes for cracking, repair any cracking found
Regulatory Findings 52090, October 26, 1981); and AD 81–03– before further flight, and modify the BL 65
53R1, Amendment 39–4301 (Docket No. 81– wing root lower joint, in accordance with the
We determined that this proposed AD NW–97–AD) (47 FR 3347, January 25, 1982). Accomplishment Instructions of Lockheed
would not have federalism implications Martin Electra Service Bulletin 88/SB–707C,
under Executive Order 13132. This (c) Applicability Revision C, dated April 30, 2014.
proposed AD would not have a This AD applies to Lockheed Martin Accomplishing this modification terminates
substantial direct effect on the States, on Corporation/Lockheed Martin Aeronautics the inspections required by paragraph (g) of
the relationship between the national Company Model 188A and 188C airplanes, this AD.
certificated in any category, serial numbers (1) Before the accumulation of 29,000 total
Government and the States, or on the 1001 and subsequent. flight hours.
distribution of power and
(d) Subject (2) Within 600 flight hours or 365 days
responsibilities among the various after the effective date of this AD, whichever
levels of government. Air Transport Association (ATA) of occurs first.
For the reasons discussed above, I America Code 57, Wings.
certify this proposed regulation: (i) No Reporting Required
(e) Unsafe Condition
(1) Is not a ‘‘significant regulatory Although Lockheed Martin Electra Service
This AD was prompted by an evaluation by
action’’ under Executive Order 12866, Bulletin 88/SB–707C, Revision C, dated April
the design approval holder indicating the left
(2) Is not a ‘‘significant rule’’ under 30, 2014, specifies to submit a report of crack
and right lower surface panels of the wings
the DOT Regulatory Policies and findings, this AD does not include that
are subject to widespread fatigue damage. We
requirement.
Procedures (44 FR 11034, February 26, are issuing this AD to prevent fatigue
1979), cracking of the left and right lower surface (j) Alternative Methods of Compliance
(3) Will not affect intrastate aviation panels of the wings on the inboard and (AMOCs)
in Alaska, and outboard sides of the buttock line (BL) 65
(1) The Manager, Atlanta Aircraft
splice joint, which could result in reduced
(4) Will have a significant economic structural integrity of the airplane.
Certification Office (ACO), FAA, has the
impact, positive or negative, on a authority to approve AMOCs for this AD, if
substantial number of small entities (f) Compliance requested using the procedures found in 14
under the criteria of the Regulatory Comply with this AD within the CFR 39.19. In accordance with 14 CFR 39.19,
Flexibility Act. compliance times specified, unless already send your request to your principal inspector
asabaliauskas on DSK5VPTVN1PROD with PROPOSALS
done. or local Flight Standards District Office, as
List of Subjects in 14 CFR Part 39 appropriate. If sending information directly
(g) Inspections and Repair to the manager of the ACO, send it to the
Air transportation, Aircraft, Aviation attention of the person identified in
At the later of the times specified in
safety, Incorporation by reference, paragraphs (g)(1) and (g)(2) of this AD: paragraph (k)(1) of this AD.
Safety. Inspect for cracking of the inboard and (2) Before using any approved AMOC,
The Proposed Amendment outboard sides of the lower splice joint at BL notify your appropriate principal inspector,
65, using X-ray, ultrasonic, and bolt-hole or lacking a principal inspector, the manager
Accordingly, under the authority eddy current inspection techniques, as of the local flight standards district office/
delegated to me by the Administrator, applicable, and repair any cracking found, in certificate holding district office.
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(k) Related Information • Fax: 202–493–2251. We will file in the docket all
(1) For more information about this AD, • Mail: Send comments to the U.S. comments that we receive, as well as a
contact Carl Gray, Aerospace Engineer, Department of Transportation, Docket report summarizing each substantive
Airframe Branch, ACE–117A, FAA, Atlanta Operations, M–30, West Building public contact with FAA personnel
ACO, 1701 Columbia Avenue, College Park, Ground Floor, Room W12–140, 1200 concerning this proposed rulemaking.
GA 30337; phone: 404–474–5554; fax: 404– New Jersey Avenue SE., Washington, Before acting on this proposal, we will
474–5605; email: carl.w.gray@faa.gov. DC 20590–0001. consider all comments we receive on or
(2) For service information identified in
• Hand Delivery: Deliver to the before the closing date for comments.
this AD, contact Lockheed Martin
Corporation/Lockheed Martin Aeronautics ‘‘Mail’’ address between 9 a.m. and 5 We will consider comments filed after
Company, Airworthiness Office, Dept. 6A0M, p.m., Monday through Friday, except the comment period has closed if it is
Zone 0252, Column P–58, 86 S. Cobb Drive, Federal holidays. possible to do so without incurring
Marietta, GA 30063; telephone 770–494– expense or delay. We may change this
Examining the AD Docket proposal in light of the comments we
5444; fax 770–494–5445; email ams.portal@
lmco.com; Internet http:// You may examine the AD docket on receive.
www.lockheedmartin.com/ams/tools/ the Internet at http://
TechPubs.html. You may view this service Discussion
www.regulations.gov or in person at the
information at the FAA, Transport Airplane Docket Operations Office between 9 EASA, which is the Technical Agent
Directorate, 1601 Lind Avenue SW., Renton, for the Member States of the European
a.m. and 5 p.m., Monday through
WA. For information on the availability of Union, has issued EASA AD No. 2014–
this material at the FAA, call 425–227–1221. Friday, except Federal holidays. The AD
docket contains this proposed AD, the 0048, dated March 4, 2014, to correct an
Issued in Renton, Washington, on May 14, European Aviation Safety Agency unsafe condition for Agusta Model
2015. AB139 and AW139 helicopters with a
(EASA) AD, the economic evaluation,
Jeffrey E. Duven, any comments received, and other serial number (S/N) 31005 through
Manager, Transport Airplane Directorate, information. The street address for the 31517 (except S/N 31007, 31415, 31431,
Aircraft Certification Service. Docket Operations Office (telephone 31491, 31500, 31508, and 31516) and S/
[FR Doc. 2015–13339 Filed 6–4–15; 8:45 am] 800–647–5527) is in the ADDRESSES N 41001 through 41356 (except S/N
BILLING CODE 4910–13–P section. Comments will be available in 41355). EASA advises that cracks have
the AD docket shortly after receipt. been reported in the subfloor frame at
For service information identified in station (STA) 2105 on in-service
DEPARTMENT OF TRANSPORTATION this proposed AD, contact helicopters. This condition, if not
AgustaWestland, Product Support detected and corrected, could lead to
Federal Aviation Administration Engineering, Via del Gregge, 100, 21015 failure of the pedals supporting the
Lonate Pozzolo (VA) Italy, ATTN: frame, which in turn could lead to the
14 CFR Part 39 Maurizio D’Angelo; telephone 39–0331– pedals being inoperative and
[Docket No. FAA–2015–1935; Directorate 664757; fax 39–0331–664680; or at subsequent loss of control of the
Identifier 2014–SW–008–AD] http://www.agustawestland.com/ helicopter, EASA advises.
technical-bulletins. You may review the The EASA AD requires repetitive
RIN 2120–AA64 inspections of the subfloor frame at STA
referenced service information at the
FAA, Office of the Regional Counsel, 2105 for a crack. The EASA AD also
Airworthiness Directives; Agusta
Southwest Region, 2601 Meacham requires installation of frame
S.p.A. Helicopters
Blvd., Room 663, Fort Worth, Texas reinforcements before further flight if
AGENCY: Federal Aviation 76137. there is a crack or within 1,200 flight
Administration (FAA), DOT. hours if there is no crack. The EASA AD
FOR FURTHER INFORMATION CONTACT:
ACTION: Notice of proposed rulemaking provides that installation of the frame
Robert Grant, Aviation Safety Engineer, reinforcements constitutes terminating
(NPRM). Safety Management Group, FAA, 2601 action for the repetitive inspections
Meacham Blvd., Fort Worth, Texas required by the AD.
SUMMARY: We propose to adopt a new
76137; telephone (817) 222–5110; email
airworthiness directive (AD) for Agusta
robert.grant@faa.gov. FAA’s Determination
S.p.A. (Agusta) Model AB139 and
AW139 helicopters. This proposed AD SUPPLEMENTARY INFORMATION: These helicopters have been approved
would require visually inspecting Comments Invited by the aviation authority of Italy and are
certain subfloor frames for a crack. This approved for operation in the United
proposed AD is prompted by reports of We invite you to participate in this States. Pursuant to our bilateral
cracks on in-service helicopters. The rulemaking by submitting written agreement with Italy, EASA, its
proposed actions are intended to detect comments, data, or views. We also technical representative, has notified us
or prevent a crack in the subfloor frame, invite comments relating to the of the unsafe condition described in its
which could result in failure of the pilot economic, environmental, energy, or AD. We are proposing this AD because
and co-pilot pedal support frame and federalism impacts that might result we evaluated all known relevant
subsequent loss of control of the from adopting the proposals in this information and determined that an
document. The most helpful comments unsafe condition is likely to exist or
asabaliauskas on DSK5VPTVN1PROD with PROPOSALS
helicopter.
reference a specific portion of the develop on other products of the same
DATES: We must receive comments on proposal, explain the reason for any type design.
this proposed AD by August 4, 2015. recommended change, and include
ADDRESSES: You may send comments by supporting data. To ensure the docket Related Service Information Under 1
any of the following methods: does not contain duplicate comments, CFR Part 51
• Federal eRulemaking Docket: Go to commenters should send only one copy We reviewed AgustaWestland
http://www.regulations.gov. Follow the of written comments, or if comments are Bolletino Tecnico No. 139–311,
online instructions for sending your filed electronically, commenters should Revision B, dated June 4, 2014 (BT), for
comments electronically. submit only one time. certain serial-numbered Agusta Model
VerDate Sep<11>2014 17:42 Jun 04, 2015 Jkt 235001 PO 00000 Frm 00031 Fmt 4702 Sfmt 4702 E:\FR\FM\05JNP1.SGM 05JNP1](https://thefederalregister.org/doc/80_FR_32177/page/4.svg)
Document Created: 2015-12-15 15:20:46
Document Modified: 2015-12-15 15:20:46
| Category | Regulatory Information | |
| Collection | Federal Register | |
| sudoc Class | AE 2.7: GS 4.107: AE 2.106: | |
| Publisher | Office of the Federal Register, National Archives and Records Administration | |
| Section | Proposed Rules | |
| Action | Notice of proposed rulemaking (NPRM). | |
| Dates | We must receive comments on this proposed AD by July 20, 2015. | |
| 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: [email protected] | |
| FR Citation | 80 FR 32069 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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