80 FR 30391 - Airworthiness Directives; Lockheed Martin Corporation/Lockheed Martin Aeronautics Company Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 80, Issue 102 (May 28, 2015)
Federal Aviation Administration
Federal Register Volume 80, Issue 102 (May 28, 2015)
| Page Range | 30391-30394 | |
| FR Document | 2015-12859 |
[Federal Register Volume 80, Number 102 (Thursday, May 28, 2015)] [Proposed Rules] [Pages 30391-30394] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2015-12859] ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2015-1425; Directorate Identifier 2014-NM-185-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 certain 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 that a certain circumferential fuselage splice is subject to widespread fatigue damage (WFD). This proposed AD would require an inspection for corrosion and previous repairs, severed stringers, cracking, and loose or distressed fasteners of the forward and aft ends of the stringer splices of certain stringers, inspection for cracking and modification of certain fastener holes common to the stringer and splice member at the forward and aft ends of the splice, and related investigative and corrective actions if necessary. We are proposing this AD to prevent loss of residual strength of a certain circumferential fuselage splice, which could lead to rapid decompression of the cabin and potential loss of the airplane. DATES: We must receive comments on this proposed AD by July 13, 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; phone: 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- 1425; or in person at the Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, [[Page 30392]] 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-2015-1425; Directorate Identifier 2014-NM-185-AD'' at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this proposed AD. We will consider all comments received by the closing date and may amend this proposed AD because of those comments. We will post all comments we receive, without change, to http://www.regulations.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact we receive about this proposed AD. Discussion Structural fatigue damage is progressive. It begins as minute cracks, and those cracks grow under the action of repeated stresses. This can happen because of normal operational conditions and design attributes, or because of isolated situations or incidents such as material defects, poor fabrication quality, or corrosion pits, dings, or scratches. Fatigue damage can occur locally, in small areas or structural design details, or globally. Global fatigue damage is general degradation of large areas of structure with similar structural details and stress levels. Multiple-site damage is global damage that occurs in a large structural element such as a single rivet line of a lap splice joining two large skin panels. Global damage can also occur in multiple elements such as adjacent frames or stringers. Multiple- site-damage and multiple-element-damage cracks are typically too small initially to be reliably detected with normal inspection methods. Without intervention, these cracks will grow, and eventually compromise the structural integrity of the airplane, in a condition known as WFD. As an airplane ages, WFD will likely occur, and will certainly occur if the airplane is operated long enough without any intervention. The FAA's WFD final rule (75 FR 69746, November 15, 2010) became effective on January 14, 2011. The WFD rule requires certain actions to prevent 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 circumferential fuselage splice at fuselage-station (FS) 695 is subject to WFD. The root cause of this WFD is fatigue cracks manifesting and growing simultaneously at similar structural details and stress levels at the circumferential fuselage splice. Fatigue cracking is increasingly likely as the airplane is operated and aged, and without intervention, fatigue cracking could lead to loss of residual strength of the circumferential fuselage splice at FS 695, which could lead to rapid decompression of the cabin area and potential loss of the airplane. Related Service Information Under 1 CFR Part 51 We reviewed Lockheed Martin Electra Service Bulletin 88/SB-722, dated April 30, 2014. This service bulletin describes procedures for doing the following actions: A general visual inspection (GVI) for corrosion and previous repairs, severed stringers, cracking, and loose or distressed fasteners of the forward and aft ends of the stringer splices of stringers 1-7 and 66-72, and corrective actions if necessary. At stringers 1-7 and 66-72, removing the four rivets common to the stringer and splice member at the forward and aft ends of the splice and doing a bolt hole eddy current (BHEC) inspection or an equivalent inspection procedure for cracking in each of the fastener holes, and corrective actions if necessary. Corrective actions for cracked holes include reaming to the maximum permissible hole diameter of the next larger size rivet. If a crack indication remains after reaming, this service information specifies repairing the cracked stringer. If a severed stringer is found during the GVI, doing related investigative actions of an eddy current surface scan inspection for cracking of the fuselage skin at the skin-to-stringer attachments immediately forward and aft of the stringer break and confirming skin cracks with a dye penetrant inspection. Corrective actions include repairing the severed stringer or skin cracks. For holes without crack indications, other specified actions include modifying the fastener holes by reaming to a certain maximum permissible hole diameter of the same size rivet and installing replacement fasteners; or if original hole is larger than the maximum permissible diameter, installing the next rivet size and type. 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. FAA's Determination We are proposing this AD because we evaluated all the relevant information and determined the unsafe condition described previously is likely to exist or develop in other products of the same type design. Proposed AD Requirements This proposed AD would require accomplishing the actions specified in the service information described [[Page 30393]] previously, except as discussed under ``Differences Between this Proposed AD and the Service Information.'' Differences Between This Proposed AD and the Service Information Although Lockheed Martin Electra Service Bulletin 88/SB-722, dated April 30, 2014, specifies that crack indications should be confirmed by an alternate inspection method, this proposed AD would not require that action. Operators should note that, although the Accomplishment Instructions of Lockheed Martin Electra Service Bulletin 88/SB-722, dated April 30, 2014, describe procedures for submitting a report of damage, this proposed AD would not require that action. Lockheed Martin Electra Service Bulletin 88/SB-722, dated April 30, 2014, does not describe corrective actions if any corrosion or previous repair is found, and if any loose or distressed fastener is found. This proposed AD would require repair. Explanation of Proposed 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 per Cost on U.S. Action Labor cost Parts cost product operators ---------------------------------------------------------------------------------------------------------------- Inspections and Modification........ 18 work-hours x $85 per $5,000 $6,530 $26,120 hour = $1,530. ---------------------------------------------------------------------------------------------------------------- We have received no definitive data that would enable us to provide cost estimates for the on-condition actions specified in this proposed AD. Authority for This Rulemaking Title 49 of the United States Code specifies the FAA's authority to issue rules on aviation safety. Subtitle I, section 106, describes the authority of the FAA Administrator. Subtitle VII: Aviation Programs, describes in more detail the scope of the Agency's authority. We are issuing this rulemaking under the authority described in Subtitle VII, Part A, Subpart III, Section 44701: ``General requirements.'' Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action. Regulatory Findings We determined that this proposed AD would not have federalism implications under Executive Order 13132. This proposed AD would not have a substantial direct effect on the States, on the relationship between the national Government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify this proposed regulation: (1) Is not a ``significant regulatory action'' under Executive Order 12866, (2) Is not a ``significant rule'' under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979), (3) Will not affect intrastate aviation in Alaska, and (4) Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. The Proposed Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 14 CFR part 39 as follows: PART 39--AIRWORTHINESS DIRECTIVES 0 1. The authority citation for part 39 continues to read as follows: Authority: 49 U.S.C. 106(g), 40113, 44701. Sec. 39.13 [Amended] 0 2. The FAA amends Sec. 39.13 by adding the following new airworthiness directive (AD): Lockheed Martin Corporation/Lockheed Martin Aeronautics Company: Docket No. FAA-2015-1425; Directorate Identifier 2014-NM-185-AD. (a) Comments Due Date We must receive comments by July 13, 2015. (b) Affected ADs None. (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 53, Fuselage. (e) Unsafe Condition This AD was prompted by an evaluation by the design approval holder (DAH) indicating that the circumferential fuselage splice at fuselage-station (FS) 695 is subject to widespread fatigue damage (WFD). We are issuing this AD to prevent loss of residual strength of the circumferential fuselage splice at FS 695, which could lead to rapid decompression of the cabin and potential loss of the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Inspections, Modification, Related Investigative Actions, and Corrective Actions Before the accumulation of 38,200 total flight hours or within 30 days after the effective date of this AD, whichever occurs later: Do a general visual inspection for corrosion and previous repairs, severed stringers, cracking, and loose or distressed fasteners of the forward and aft ends of the stringer splices of stringers 1-7 and 66-72; remove the four rivets common to the stringer and splice member at the forward and aft ends of the splice and do a bolt hole eddy current inspection or an equivalent inspection procedure for cracking in each of the fastener holes; modify the fastener holes; [[Page 30394]] and do all applicable related investigative and corrective actions and other specified actions; in accordance with the Accomplishment Instructions of Lockheed Martin Electra Service Bulletin 88/SB-722, dated April 30, 2014, except as specified in paragraph (h) of this AD. Do all applicable related investigative and corrective actions and other specified actions before further flight. If any repairs exceed the repair limits specified in Lockheed Martin Electra Service Bulletin 88/SB-722, dated April 30, 2014, before further flight, repair using a method approved in accordance with the procedures specified in paragraph (j) of this AD. (h) Corrective Action (1) If, during any inspection required by paragraph (g) of this AD, any corrosion or previous repair is found, before further flight, repair using a method approved in accordance with the procedures specified in paragraph (j) of this AD. (2) If, during any inspection required by paragraph (g) of this AD, any loose or distressed fastener is found, before further flight, repair using a method approved in accordance with the procedures specified in paragraph (j) of this AD. (i) Exception Although Lockheed Martin Electra Service Bulletin 88/SB-722, dated April 30, 2014, specifies to submit certain information to the manufacturer, this AD does not include that requirement. (j) Alternative Methods of Compliance (AMOCs) (1) The Manager, Atlanta 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 (j)(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. (k) Related Information (1) For more information about this AD, 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; phone: 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 19, 2015. Dionne Palermo, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2015-12859 Filed 5-27-15; 8:45 am] BILLING CODE 4910-13-P
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List of Subjects in 14 CFR Part 33 of 33.29(c) the PW210A must 188 series airplanes. This proposed AD
Air Transportation, Aircraft, Aviation, incorporate a means or a provision for was prompted by an evaluation by the
Aviation safety, Safety. a means to: design approval holder (DAH)
(1) Alert the pilot when the engine is indicating that a certain circumferential
The authority citation for these
at the Flat 30-second and 2-minute OEI fuselage splice is subject to widespread
special conditions is as follows:
Power level, when the event begins, and fatigue damage (WFD). This proposed
Authority: 49 U.S.C. 106(g), 40113, 44701, when the time interval expires; AD would require an inspection for
44702, 44704. (2) Automatically record each usage corrosion and previous repairs, severed
The Proposed Special Conditions and duration of power at the Flat 30- stringers, cracking, and loose or
Accordingly, the Federal Aviation second and 2-minute OEI Power rating; distressed fasteners of the forward and
Administration (FAA) proposes the (3) Following each flight when the aft ends of the stringer splices of certain
following special conditions as part of Flat 30-second and 2-minute OEI Power stringers, inspection for cracking and
the type certification basis for Pratt and rating is used, alert maintenance modification of certain fastener holes
Whitney Canada PW210A engine personnel in a positive manner that the common to the stringer and splice
model. engine has been operated at the Flat 30- member at the forward and aft ends of
second and 2-minute OEI Power level, the splice, and related investigative and
Flat 30-Second and 2-Minute OEI and permit retrieval of the recorded corrective actions if necessary. We are
1. Part 1.1 Definitions data; and proposing this AD to prevent loss of
(4) Enable routine verification of the residual strength of a certain
‘‘Rated Flat 30-second and 2-minute proper operation of the above means. circumferential fuselage splice, which
One Engine Inoperative (OEI) Power,’’ (f) Section 33.87 Endurance test. The could lead to rapid decompression of
with respect to rotorcraft turbine requirements applicable to 30-second the cabin and potential loss of the
engines, means (1) a single rating for and 2-minute OEI ratings, except for: airplane.
which the shaft horsepower and (1) The test of § 33.87(a)(7) for the
associated operating limitations of the DATES: We must receive comments on
purposes of temperature stabilization, this proposed AD by July 13, 2015.
30-second OEI and 2-minute OEI ratings must be run with a test period time of
are equal, and (2) the shaft horsepower ADDRESSES: You may send comments,
2.5 minutes.
is that developed under static (2) The tests in § 33.87(f)(2) and (3) using the procedures found in 14 CFR
conditions at the altitude and must be run continuously for the 11.43 and 11.45, by any of the following
temperature for the hot day, and within duration of 2.5 minutes, and methods:
the operating limitations established • Federal eRulemaking Portal: Go to
(3) The tests in § 33.87(f)(6) and (7)
under Part 33. The rating is for http://www.regulations.gov. Follow the
must be run continuously for the
continuation of flight operation after the instructions for submitting comments.
duration of 2.5 minutes.
failure or shutdown of one engine in • Fax: 202–493–2251.
(g) Section 33.88 Engine • Mail: U.S. Department of
multiengine rotorcraft, for up to three overtemperature test. The requirements
periods of use no longer than 2.5 Transportation, Docket Operations, M–
of § 33.88(b) except that the test time is 30, West Building Ground Floor, Room
minutes each in any one flight, and 5 minutes instead of 4 minutes.
followed by mandatory inspection and W12–140, 1200 New Jersey Avenue SE.,
Issued in Burlington, Massachusetts, on Washington, DC 20590.
prescribed maintenance action.
May 18, 2015. • Hand Delivery: Deliver to Mail
2. Part 33 Requirements Carlos Pestana, address above between 9 a.m. and 5
(a) The airworthiness standards in Acting Manager, Engine & Propeller p.m., Monday through Friday, except
Part 33 Amendment 30 for the 30- Directorate, Aircraft Certification Service. Federal holidays.
second OEI and 2-minute OEI ratings [FR Doc. 2015–12986 Filed 5–27–15; 8:45 am] For service information identified in
are applicable to the Flat 30-second and BILLING CODE 4910–13–P this proposed AD, contact Lockheed
2-minute OEI Power rating. In addition Martin Corporation/Lockheed Martin
the following special conditions apply; Aeronautics Company, Airworthiness
(b) Section 33.7 Engine ratings and DEPARTMENT OF TRANSPORTATION Office, Dept. 6A0M, Zone 0252, Column
operating limitations. Flat 30-second P–58, 86 S. Cobb Drive, Marietta, GA
and 2-minute OEI Power rating and Federal Aviation Administration 30063; phone: 770–494–5444; fax: 770–
operating limitations are established for 494–5445; email: ams.portal@lmco.com;
power, torque, rotational speed, gas 14 CFR Part 39 Internet http://
temperature, and time duration. [Docket No. FAA–2015–1425; Directorate www.lockheedmartin.com/ams/tools/
(c) Section 33.27 Turbine, Identifier 2014–NM–185–AD] TechPubs.html. You may view this
compressor, fan, and turbosupercharger referenced service information at the
RIN 2120–AA64
rotor overspeed. The requirements of FAA, Transport Airplane Directorate,
§ 33.27, except that following the test, Airworthiness Directives; Lockheed 1601 Lind Avenue SW., Renton, WA.
the rotor may not exhibit conditions Martin Corporation/Lockheed Martin For information on the availability of
such as cracking or distortion which Aeronautics Company Airplanes this material at the FAA, call 425–227–
preclude continued safe operation. 1221.
wreier-aviles on DSK5TPTVN1PROD with PROPOSALS
(d) Section 33.28 Engine controls AGENCY: Federal Aviation
systems. Must incorporate a means, or a Administration (FAA), DOT. Examining the AD Docket
provision for a means, for automatic ACTION: Notice of proposed rulemaking You may examine the AD docket on
availability and automatic control of the (NPRM). the Internet at http://
Flat 30-second and 2-minute OEI Power www.regulations.gov by searching for
within the declared operating SUMMARY: We propose to adopt a new and locating Docket No. FAA–2015–
limitations. airworthiness directive (AD) for certain 1425; or in person at the Docket
(e) Section 33.29 Instrument Lockheed Martin Corporation/Lockheed Management Facility between 9 a.m.
Connection. In lieu of the requirements Martin Aeronautics Company Model and 5 p.m., Monday through Friday,
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previously, except as discussed under submitting a report of damage, this replaced before WFD develops in
‘‘Differences Between this Proposed AD proposed AD would not require that airplanes. Standard inspection
and the Service Information.’’ action. techniques cannot be relied on to detect
Lockheed Martin Electra Service WFD before it becomes a hazard to
Differences Between This Proposed AD Bulletin 88/SB–722, dated April 30,
and the Service Information flight. We will not grant any extensions
2014, does not describe corrective of the compliance time to complete any
Although Lockheed Martin Electra actions if any corrosion or previous AD-mandated service bulletin related to
Service Bulletin 88/SB–722, dated April repair is found, and if any loose or WFD without extensive new data that
30, 2014, specifies that crack indications distressed fastener is found. This would substantiate and clearly warrant
should be confirmed by an alternate proposed AD would require repair. such an extension.
inspection method, this proposed AD
would not require that action. Explanation of Proposed Compliance Costs of Compliance
Operators should note that, although Time
the Accomplishment Instructions of The compliance time for the We estimate that this proposed AD
Lockheed Martin Electra Service modification specified in this proposed affects 4 airplanes of U.S. registry.
Bulletin 88/SB–722, dated April 30, AD for addressing WFD was established We estimate the following costs to
2014, describe procedures for to ensure that discrepant structure is comply with this proposed AD:
ESTIMATED COSTS
Cost per Cost on U.S.
Action Labor cost Parts cost product operators
Inspections and Modification .......................... 18 work-hours × $85 per hour = $1,530 ........ $5,000 $6,530 $26,120
We have received no definitive data (1) Is not a ‘‘significant regulatory (b) Affected ADs
that would enable us to provide cost action’’ under Executive Order 12866, None.
estimates for the on-condition actions (2) Is not a ‘‘significant rule’’ under
(c) Applicability
specified in this proposed AD. the DOT Regulatory Policies and
Procedures (44 FR 11034, February 26, This AD applies to Lockheed Martin
Authority for This Rulemaking Corporation/Lockheed Martin Aeronautics
1979),
Company Model 188A and 188C airplanes,
Title 49 of the United States Code (3) Will not affect intrastate aviation certificated in any category, serial numbers
specifies the FAA’s authority to issue in Alaska, and 1001 and subsequent.
rules on aviation safety. Subtitle I, (4) Will not have a significant
section 106, describes the authority of economic impact, positive or negative, (d) Subject
the FAA Administrator. Subtitle VII: on a substantial number of small entities Air Transport Association (ATA) of
Aviation Programs, describes in more under the criteria of the Regulatory America Code 53, Fuselage.
detail the scope of the Agency’s Flexibility Act. (e) Unsafe Condition
authority.
List of Subjects in 14 CFR Part 39 This AD was prompted by an evaluation by
We are issuing this rulemaking under the design approval holder (DAH) indicating
the authority described in Subtitle VII, Air transportation, Aircraft, Aviation that the circumferential fuselage splice at
Part A, Subpart III, Section 44701: safety, Incorporation by reference, fuselage-station (FS) 695 is subject to
‘‘General requirements.’’ Under that Safety. widespread fatigue damage (WFD). We are
section, Congress charges the FAA with issuing this AD to prevent loss of residual
The Proposed Amendment strength of the circumferential fuselage splice
promoting safe flight of civil aircraft in
air commerce by prescribing regulations Accordingly, under the authority at FS 695, which could lead to rapid
for practices, methods, and procedures delegated to me by the Administrator, decompression of the cabin and potential
the FAA proposes to amend 14 CFR part loss of the airplane.
the Administrator finds necessary for
safety in air commerce. This regulation 39 as follows: (f) Compliance
is within the scope of that authority Comply with this AD within the
because it addresses an unsafe condition PART 39—AIRWORTHINESS compliance times specified, unless already
that is likely to exist or develop on DIRECTIVES done.
products identified in this rulemaking ■ 1. The authority citation for part 39 (g) Inspections, Modification, Related
action. continues to read as follows: Investigative Actions, and Corrective
Regulatory Findings Actions
Authority: 49 U.S.C. 106(g), 40113, 44701.
Before the accumulation of 38,200 total
We determined that this proposed AD § 39.13 [Amended] flight hours or within 30 days after the
would not have federalism implications effective date of this AD, whichever occurs
under Executive Order 13132. This ■ 2. The FAA amends § 39.13 by adding
later: Do a general visual inspection for
the following new airworthiness
wreier-aviles on DSK5TPTVN1PROD with PROPOSALS
proposed AD would not have a corrosion and previous repairs, severed
substantial direct effect on the States, on directive (AD): stringers, cracking, and loose or distressed
the relationship between the national Lockheed Martin Corporation/Lockheed fasteners of the forward and aft ends of the
Government and the States, or on the Martin Aeronautics Company: Docket stringer splices of stringers 1–7 and 66–72;
No. FAA–2015–1425; Directorate remove the four rivets common to the
distribution of power and
Identifier 2014–NM–185–AD. stringer and splice member at the forward
responsibilities among the various and aft ends of the splice and do a bolt hole
levels of government. (a) Comments Due Date eddy current inspection or an equivalent
For the reasons discussed above, I We must receive comments by July 13, inspection procedure for cracking in each of
certify this proposed regulation: 2015. the fastener holes; modify the fastener holes;
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and do all applicable related investigative Issued in Renton, Washington, on May 19, • Fax: Fax comments to Docket
and corrective actions and other specified 2015. Operations at 202–493–2251.
actions; in accordance with the Dionne Palermo, Privacy: In accordance with 5 U.S.C.
Accomplishment Instructions of Lockheed Acting Manager, Transport Airplane 553(c), DOT solicits comments from the
Martin Electra Service Bulletin 88/SB–722, Directorate, Aircraft Certification Service. public to better inform its rulemaking
dated April 30, 2014, except as specified in
paragraph (h) of this AD. Do all applicable
[FR Doc. 2015–12859 Filed 5–27–15; 8:45 am] process. DOT posts these comments,
related investigative and corrective actions BILLING CODE 4910–13–P without edit, including any personal
and other specified actions before further information the commenter provides, to
flight. If any repairs exceed the repair limits www.regulations.gov, as described in
specified in Lockheed Martin Electra Service DEPARTMENT OF TRANSPORTATION the system of records notice (DOT/ALL–
Bulletin 88/SB–722, dated April 30, 2014, 14 FDMS), which can be reviewed at
before further flight, repair using a method Federal Aviation Administration www.dot.gov/privacy.
approved in accordance with the procedures Docket: Background documents or
specified in paragraph (j) of this AD. 14 CFR Part 91 comments received may be read at
(h) Corrective Action [Docket No.: FAA–2015–1746; Notice No. http://www.regulations.gov at any time.
(1) If, during any inspection required by 15–05] Follow the online instructions for
paragraph (g) of this AD, any corrosion or accessing the docket or go to Docket
RIN 2120–AK54
previous repair is found, before further flight, Operations in Room W12–140 of the
repair using a method approved in Changes to the Application West Building Ground Floor at 1200
accordance with the procedures specified in Requirements for Authorization to New Jersey Avenue SE., Washington,
paragraph (j) of this AD. Operate in Reduced Vertical DC, between 9 a.m. and 5 p.m., Monday
(2) If, during any inspection required by Separation Minimum Airspace through Friday, except Federal holidays.
paragraph (g) of this AD, any loose or FOR FURTHER INFORMATION CONTACT: For
distressed fastener is found, before further AGENCY: Federal Aviation
flight, repair using a method approved in
technical questions concerning this
Administration (FAA), DOT. action, contact Charles Fellows,
accordance with the procedures specified in
ACTION: Notice of proposed rulemaking Aviation Safety Inspector, Avionics
paragraph (j) of this AD.
(NPRM). Branch, Aircraft Maintenance Division,
(i) Exception Flight Standards Services, AFS–360,
SUMMARY: This action would revise the
Although Lockheed Martin Electra Service Federal Aviation Administration, 950
Bulletin 88/SB–722, dated April 30, 2014, FAA’s requirements for an application
to operate in Reduced Vertical L’Enfant Plaza North SW., Washington,
specifies to submit certain information to the DC 20024; telephone (202) 267–1706;
manufacturer, this AD does not include that Separation Minimum (RVSM) airspace.
requirement. This proposal would eliminate the email Charles.Fellows@faa.gov.
burden and expense of developing, For legal questions concerning this
(j) Alternative Methods of Compliance action, contact Benjamin Jacobs,
(AMOCs)
processing, and approving RVSM
maintenance programs. As a result of Attorney-Advisor, Office of Chief
(1) The Manager, Atlanta ACO, FAA, has this proposed revision, an applicant to Counsel, AGC–200, Federal Aviation
the authority to approve AMOCs for this AD, Administration, 800 Independence Ave.
if requested using the procedures found in 14
operate in RVSM airspace would no
longer be required to develop and SW., Washington, DC 20591; telephone
CFR 39.19. In accordance with 14 CFR 39.19, (202) 267–7240; email
send your request to your principal inspector submit an RVSM maintenance program
solely for the purpose of an RVSM Benjamin.Jacobs@faa.gov.
or local Flight Standards District Office, as
appropriate. If sending information directly authorization. Because of other, SUPPLEMENTARY INFORMATION:
to the manager of the ACO, send it to the independent FAA airworthiness Authority for This Rulemaking
attention of the person identified in regulations, all aircraft operators would
paragraph (j)(1) of this AD. nevertheless continue to be required to The FAA’s authority to issue rules
(2) Before using any approved AMOC, maintain RVSM equipment in an regarding aviation safety is found in
notify your appropriate principal inspector, Title 49 of the United States Code.
airworthy condition.
or lacking a principal inspector, the manager Sections 106(f), 40113, and 44701
of the local flight standards district office/ DATES: Send comments on or before July
27, 2015. authorize the FAA Administrator to
certificate holding district office. prescribe regulations necessary for
ADDRESSES: Send comments identified
(k) Related Information aviation safety. Section 40103
by docket number FAA–2015–1746 authorizes the Administrator to
(1) For more information about this AD, using any of the following methods:
Carl Gray, Aerospace Engineer, Airframe prescribe regulations to enhance the
• Federal eRulemaking Portal: Go to
Branch, ACE–117A, FAA, Atlanta ACO, 1701 efficiency of the national airspace. This
Columbia Avenue, College Park, GA 30337;
http://www.regulations.gov and follow
rulemaking is within the scope of these
phone: 404–474–5554; fax: 404–474–5605; the online instructions for sending your
authorities because it would remove
email: carl.w.gray@faa.gov. comments electronically.
• Mail: Send comments to Docket existing safety and airspace-related
(2) For service information identified in regulations that the FAA no longer finds
this AD, contact Lockheed Martin Operations, M–30; U.S. Department of
Corporation/Lockheed Martin Aeronautics Transportation (DOT), 1200 New Jersey necessary to protect aviation safety.
Company, Airworthiness Office, Dept. 6A0M, Avenue SE., Room W12–140, West I. Executive Summary
wreier-aviles on DSK5TPTVN1PROD with PROPOSALS
Zone 0252, Column P–58, 86 S. Cobb Drive, Building Ground Floor, Washington, DC
Marietta, GA 30063; phone: 770–494–5444; 20590–0001. A. Summary of Proposed Rule
fax: 770–494–5445; email: ams.portal@ • Hand Delivery or Courier: Take This Notice of Proposed Rulemaking
lmco.com; Internet http://
comments to Docket Operations in (NPRM) proposes to remove the
www.lockheedmartin.com/ams/tools/
TechPubs.html. You may view this service Room W12–140 of the West Building requirement in Appendix G of part 91
information at the FAA, Transport Airplane Ground Floor at 1200 New Jersey of Title 14 of the Code of Federal
Directorate, 1601 Lind Avenue SW., Renton, Avenue SE., Washington, DC, between 9 Regulations (14 CFR) that any operator
WA. For information on the availability of a.m. and 5 p.m., Monday through seeking Reduced Vertical Separation
this material at the FAA, call 425–227–1221. Friday, except Federal holidays. Minimum (RVSM) authorization must
VerDate Sep<11>2014 15:12 May 27, 2015 Jkt 235001 PO 00000 Frm 00012 Fmt 4702 Sfmt 4702 E:\FR\FM\28MYP1.SGM 28MYP1](https://thefederalregister.org/doc/80_FR_30493/page/4.svg)
Document Created: 2018-02-21 10:32:54
Document Modified: 2018-02-21 10:32:54
| 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 13, 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 30391 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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