80 FR 15525 - Airworthiness Directives; Lockheed Martin Corporation/Lockheed Martin Aeronautics Company Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 80, Issue 56 (March 24, 2015)
Federal Aviation Administration
Federal Register Volume 80, Issue 56 (March 24, 2015)
| Page Range | 15525-15528 | |
| FR Document | 2015-06576 |
[Federal Register Volume 80, Number 56 (Tuesday, March 24, 2015)] [Proposed Rules] [Pages 15525-15528] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2015-06576] ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2015-0493; Directorate Identifier 2014-NM-184-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 the upper and lower wing skin planks at the attachment of the main landing gear (MLG) ribs at certain wing-stations are subject to widespread fatigue damage (WFD). This proposed AD would require an inspection (for cracking) and modification of the chordwise fastener rows of the upper and lower wing planks at the attachments to the MLG ribs at certain wing-stations. We are proposing this AD to prevent fatigue cracking of the upper and lower wing skin planks at the attachment of the MLG ribs, which could result in failure of the wing. DATES: We must receive comments on this proposed AD by May 8, 2015. ADDRESSES: You may send comments, using the procedures found in 14 CFR 11.43 and 11.45, by any of the following methods: [[Page 15526]]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 [email protected]; 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- 0493; 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: [email protected]. 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-2015-0493; Directorate Identifier 2014-NM-184-AD'' at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this proposed AD. We will consider all comments received by the closing date and may amend this proposed AD 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 upper and lower wing skin planks at the attachment of the MLG ribs are subject to WFD. The root cause of WFD is fatigue cracks manifesting and growing simultaneously at similar structural details and stress levels of the upper and lower wing skin planks at the attachment of the MLG ribs. Fatigue cracking is increasingly likely as the airplane is operated and aged, and without intervention, fatigue cracking of the upper and lower wing skin planks at the attachment of the MLG ribs could result in failure of the wing. Related Service Information Under 1 CFR Part 51 We reviewed Lockheed Martin Electra 88 Service Bulletin 721, dated April 30, 2014. This service bulletin describes procedures to do a bolt hole eddy current (BHEC) inspection for cracking and modification of the chordwise fastener rows of the upper and lower wing planks at the attachments to the MLG ribs at wing-station (WS) 167 and WS 209 by removing the original fasteners and replacing them with new first oversize fasteners of the same type or approved substitute type for original fasteners. Corrective actions include repairing any cracking before further flight. The compliance times for the inspection and modification are specified at the following times. For WS 167 lower: Before the accumulation of 33,300 total flight hours. For WS 167 upper: Before the accumulation of 23,200 total flight hours. For WS 209 lower: Before the accumulation of 31,500 total flight hours. [[Page 15527]] For WS 209 upper: Before the accumulation of 35,400 total flight hours. This service information is reasonably available; see ADDRESSES for ways to access this service information. 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 these same type designs. Proposed AD Requirements This proposed AD would require accomplishing the actions specified in the service information described previously, except as discussed under ``Differences Between this Proposed AD and the Service Information.'' Differences Between This Proposed AD and the Service Information Operators should note that, although the Accomplishment Instructions of Lockheed Martin Electra 88 Service Bulletin 721, dated April 30, 2014, describe procedures for reporting any damage detected to the manufacturer, this proposed AD would not require those actions. Although Lockheed Martin Electra Service Bulletin 88/721, dated April 30, 2014, specifies that operators may contact the manufacturer for disposition of certain repair conditions, this proposed AD would require operators to repair those conditions in accordance with a method approved by the FAA. Explanation of Compliance Time The compliance time for the modification specified in this proposed AD for addressing WFD was established to ensure that discrepant structure is modified before WFD develops in airplanes. Standard inspection techniques cannot be relied on to detect WFD before it becomes a hazard to flight. We will not grant any extensions of the compliance time to complete any AD-mandated service bulletin related to WFD without extensive new data that would substantiate and clearly warrant such an extension. Costs of Compliance We estimate that this proposed AD affects 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 ---------------------------------------------------------------------------------------------------------------- Inspection and Modification......... 560 work-hours x $85 $5,000 $52,600 $210,400 per hour = $47,600. ---------------------------------------------------------------------------------------------------------------- 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-2015-0493; Directorate Identifier 2014-NM-184-AD. (a) Comments Due Date We must receive comments by May 8, 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 57, Wings. (e) Unsafe Condition This AD was prompted by an evaluation by the design approval holder (DAH) indicating that the upper and lower wing skin planks at the attachment of the main landing gear (MLG) ribs at certain wing- stations are subject to widespread fatigue damage (WFD). We are issuing this AD to prevent fatigue cracking of the upper and lower wing skin planks at the attachment of the MLG ribs, which could result in failure of the wing. (f) Compliance Comply with this AD within the compliance times specified, unless already done. [[Page 15528]] (g) Inspection, Modification, and Corrective Action At the later of the times specified in paragraphs (g)(1) and (g)(2) of this AD: Remove the chordwise fastener rows of the upper and lower wing planks at the attachments to the MLG ribs at wing- station (WS) 167 and WS 209; do a bolt hole eddy current (BHEC) inspection to detect cracking of the fastener rows; and replace the original fasteners with new, first oversize fasteners; in accordance with the Accomplishment Instructions of Lockheed Martin Electra 88 Service Bulletin 721, dated April 30, 2014. If any cracking is found during any inspection required by this paragraph: Before further flight, repair the cracking, in accordance with the Accomplishment Instructions of Lockheed Martin Electra 88 Service Bulletin 721, dated April 30, 2014. (1) At the applicable time specified in table 1 of paragraph 1.E., ``Compliance,'' of Lockheed Martin Electra 88 Service Bulletin 721, dated April 30, 2014. Where table 1 of paragraph 1.E., ``Compliance,'' of Lockheed Martin Electra 88 Service Bulletin 721, dated April 30, 2014, specifies ``Flt. Hrs,'' this AD specifies ``total flight hours.'' (2) Within 365 days or 600 flight hours after the effective date of this AD, whichever occurs first. (h) No Reporting Although Lockheed Martin Electra 88 Service Bulletin 721, dated April 30, 2014, specifies to submit certain information to the manufacturer, this AD does not include that requirement. (i) 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. (j) 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: [email protected]. (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 [email protected]; 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 March 12, 2015. Jeffrey E. Duven, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2015-06576 Filed 3-23-15; 8:45 am] BILLING CODE 4910-13-P
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The Boeing Company: Docket No. FAA– and corrective actions, must be done in 98057–3356; phone: 425–917–6447; fax: 425–
2015–0495; Directorate Identifier 2014– accordance with Part 3 of the 917–6590; email: haytham.alaidy@faa.gov.
NM–172–AD. Accomplishment Instructions of Boeing Alert (2) For service information identified in
Service Bulletin 737–53A1328, dated July 22, this AD, contact Boeing Commercial
(a) Comments Due Date Airplanes, Attention: Data & Services
2014, except as required by paragraph (i)(2)
We must receive comments by May 8, of this AD. Management, P.O. Box 3707, MC 2H–65,
2015. Seattle, WA 98124–2207; telephone 206–
(i) Exceptions to the Service Bulletin 544–5000, extension 1; fax 206–766–5680;
(b) Affected ADs Specifications Internet https://www.myboeingfleet.com. You
None. (1) Where Boeing Alert Service Bulletin may view the referenced service information
737–53A1328, dated July 22, 2014, specifies at the FAA, Transport Airplane Directorate,
(c) Applicability
a compliance time ‘‘after the original issue 1601 Lind Avenue SW., Renton, WA. For
This AD applies to The Boeing Company date of this service bulletin,’’ this AD information on the availability of this
Model 737–300, –400, and –500 series requires compliance within the specified material at the FAA, call 425–227–1221.
airplanes, certificated in any category, as compliance time after the effective date of
identified in Boeing Alert Service Bulletin Issued in Renton, Washington, on March
this AD. 13, 2015.
737–53A1328, dated July 22, 2014.
(2) Where Boeing Alert Service Bulletin Jeffrey E. Duven,
(d) Subject 737–53A1328, dated July 22, 2014, specifies
Manager, Transport Airplane Directorate,
Air Transport Association (ATA) of to contact Boeing for repair instructions:
Aircraft Certification Service.
America Code 53, Fuselage. Before further flight, repair the cracking
using a method approved in accordance with [FR Doc. 2015–06574 Filed 3–23–15; 8:45 am]
(e) Unsafe Condition the procedures specified in paragraph (j) of BILLING CODE 4910–13–P
This AD was prompted by reports of this AD.
fatigue cracking at certain fastener locations (j) Alternative Methods of Compliance
in the window corners of the window belt (AMOCs)
DEPARTMENT OF TRANSPORTATION
area. We are issuing this AD to detect and
correct fatigue cracking around the fastener (1) The Manager, Seattle Aircraft Federal Aviation Administration
locations that could cause multiple window Certification Office (ACO), FAA, has the
corner skin cracks, which could result in authority to approve AMOCs for this AD, if 14 CFR Part 39
rapid decompression and loss of structural requested using the procedures found in 14
integrity of the airplane. CFR 39.19. In accordance with 14 CFR 39.19, [Docket No. FAA–2015–0493; Directorate
send your request to your principal inspector Identifier 2014–NM–184–AD]
(f) Compliance or local Flight Standards District Office, as
RIN 2120–AA64
Comply with this AD within the appropriate. If sending information directly
compliance times specified, unless already to the manager of the ACO, send it to the
attention of the person identified in
Airworthiness Directives; Lockheed
done.
paragraph (k)(1) of this AD. Information may Martin Corporation/Lockheed Martin
(g) Inspections be emailed to: 9-ANM-Seattle-ACO-AMOC- Aeronautics Company Airplanes
At the applicable time specified in tables Requests@faa.gov. AGENCY: Federal Aviation
1 and 2 of paragraph 1.E., ‘‘Compliance,’’ of (2) Before using any approved AMOC,
Administration (FAA), DOT.
Boeing Alert Service Bulletin 737–53A1328, notify your appropriate principal inspector,
dated July 22, 2014, except as required by or lacking a principal inspector, the manager ACTION: Notice of proposed rulemaking
paragraph (i)(1) of this AD: Do external of the local flight standards district office/ (NPRM).
surface high frequency eddy current (HFEC) certificate holding district office.
inspections for cracking of the skin at the 12 (3) If any service information contains SUMMARY: We propose to adopt a new
fastener locations at the upper forward and steps that are identified as RC (Required for airworthiness directive (AD) for certain
lower aft corners of each window between Compliance), those steps must be done to Lockheed Martin Corporation/Lockheed
station (STA) 360 and STA 540 and between comply with this AD; any steps that are not Martin Aeronautics Company Model
STA 727 and STA 908, left-side and right- identified as RC are recommended. Those 188 series airplanes. This proposed AD
side of the fuselage, at and between stringers steps that are not identified as RC may be was prompted by an evaluation by the
S–11 and S–13, and all applicable related deviated from using accepted methods in design approval holder (DAH)
investigative and corrective actions, in accordance with the operator’s maintenance indicating that the upper and lower
accordance with the Accomplishment or inspection program without obtaining
wing skin planks at the attachment of
Instructions of Boeing Alert Service Bulletin approval of an AMOC, provided the steps
737–53A1328, dated July 22, 2014, except as identified as RC can be done and the airplane
the main landing gear (MLG) ribs at
required by paragraph (i)(2) of this AD. Do all can be put back in a serviceable condition. certain wing-stations are subject to
applicable related investigative and Any substitutions or changes to steps widespread fatigue damage (WFD). This
corrective actions before further flight. identified as RC require approval of an proposed AD would require an
Repeat the inspections at the applicable AMOC. inspection (for cracking) and
times specified in tables 1 and 2 of paragraph (4) An AMOC that provides an acceptable modification of the chordwise fastener
1.E., ‘‘Compliance,’’ of Boeing Alert Service level of safety may be used for any repair rows of the upper and lower wing
Bulletin 737–53A1328, dated July 22, 2014, required by this AD if it is approved by the planks at the attachments to the MLG
until the terminating action specified in Boeing Commercial Airplanes Organization ribs at certain wing-stations. We are
paragraph (h) of this AD is done. Designation Authorization (ODA) that has
been authorized by the Manager, Seattle
proposing this AD to prevent fatigue
(h) Optional Preventive Modification ACO, to make those findings. For a repair cracking of the upper and lower wing
Accomplishment of a preventive method to be approved, the repair must meet skin planks at the attachment of the
TKELLEY on DSK3SPTVN1PROD with PROPOSALS
modification in the fastener locations in the the certification basis of the airplane, and the MLG ribs, which could result in failure
window corners of the window belt area approval must specifically refer to this AD. of the wing.
between station (STA) 360 and STA 540 and DATES: We must receive comments on
between STA 727 and STA 908, left-side and (k) Related Information
this proposed AD by May 8, 2015.
right-side fuselage, at and between stringers (1) For more information about this AD,
S–11 and S–13, terminates the inspections contact Haytham Alaidy, Aerospace ADDRESSES: You may send comments,
required by paragraph (g) of this AD at the Engineer, Airframe Branch, ANM–120S, using the procedures found in 14 CFR
modified location only. The modification, FAA, Seattle Aircraft Certification Office 11.43 and 11.45, by any of the following
including all applicable related investigative (ACO), 1601 Lind Avenue SW., Renton, WA methods:
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• For WS 209 upper: Before the Differences Between This Proposed AD Explanation of Compliance Time
accumulation of 35,400 total flight and the Service Information The compliance time for the
hours.
Operators should note that, although modification specified in this proposed
This service information is reasonably
available; see ADDRESSES for ways to the Accomplishment Instructions of AD for addressing WFD was established
access this service information. Lockheed Martin Electra 88 Service to ensure that discrepant structure is
Bulletin 721, dated April 30, 2014, modified before WFD develops in
FAA’s Determination airplanes. Standard inspection
describe procedures for reporting any
We are proposing this AD because we techniques cannot be relied on to detect
damage detected to the manufacturer,
evaluated all the relevant information WFD before it becomes a hazard to
this proposed AD would not require flight. We will not grant any extensions
and determined the unsafe condition those actions.
described previously is likely to exist or of the compliance time to complete any
develop in other products of these same Although Lockheed Martin Electra AD-mandated service bulletin related to
type designs. Service Bulletin 88/721, dated April 30, WFD without extensive new data that
2014, specifies that operators may would substantiate and clearly warrant
Proposed AD Requirements contact the manufacturer for disposition such an extension.
This proposed AD would require of certain repair conditions, this Costs of Compliance
accomplishing the actions specified in proposed AD would require operators to
the service information described repair those conditions in accordance We estimate that this proposed AD
previously, except as discussed under with a method approved by the FAA. affects 4 airplanes of U.S. registry.
‘‘Differences Between this Proposed AD We estimate the following costs to
and the Service Information.’’ comply with this proposed AD:
ESTIMATED COSTS
Cost per Cost on U.S.
Action Labor cost Parts cost product operators
Inspection and Modification ............................ 560 work-hours × $85 per hour = $47,600 .... $5,000 $52,600 $210,400
We have received no definitive data responsibilities among the various § 39.13 [Amended]
that would enable us to provide cost levels of government. ■ 2. The FAA amends § 39.13 by adding
estimates for the on-condition actions For the reasons discussed above, I the following new airworthiness
specified in this proposed AD. certify this proposed regulation: directive (AD):
Authority for This Rulemaking Lockheed Martin Corporation/Lockheed
(1) Is not a ‘‘significant regulatory
Martin Aeronautics Company: Docket
Title 49 of the United States Code action’’ under Executive Order 12866, No. FAA–2015–0493; Directorate
specifies the FAA’s authority to issue (2) Is not a ‘‘significant rule’’ under Identifier 2014–NM–184–AD.
rules on aviation safety. Subtitle I, the DOT Regulatory Policies and (a) Comments Due Date
section 106, describes the authority of Procedures (44 FR 11034, February 26,
the FAA Administrator. Subtitle VII: We must receive comments by May 8,
1979), 2015.
Aviation Programs, describes in more
detail the scope of the Agency’s (3) Will not affect intrastate aviation (b) Affected ADs
authority. in Alaska, and None.
We are issuing this rulemaking under (4) Will not have a significant
the authority described in Subtitle VII, (c) Applicability
economic impact, positive or negative,
Part A, Subpart III, Section 44701: This AD applies to Lockheed Martin
on a substantial number of small entities Corporation/Lockheed Martin Aeronautics
‘‘General requirements.’’ Under that under the criteria of the Regulatory
section, Congress charges the FAA with Company Model 188A and 188C airplanes,
Flexibility Act. certificated in any category, serial numbers
promoting safe flight of civil aircraft in
1001 and subsequent.
air commerce by prescribing regulations List of Subjects in 14 CFR Part 39
for practices, methods, and procedures (d) Subject
the Administrator finds necessary for Air transportation, Aircraft, Aviation Air Transport Association (ATA) of
safety in air commerce. This regulation safety, Incorporation by reference, America Code 57, Wings.
is within the scope of that authority Safety. (e) Unsafe Condition
because it addresses an unsafe condition
The Proposed Amendment This AD was prompted by an evaluation by
that is likely to exist or develop on the design approval holder (DAH) indicating
products identified in this rulemaking Accordingly, under the authority that the upper and lower wing skin planks
action. delegated to me by the Administrator, at the attachment of the main landing gear
the FAA proposes to amend 14 CFR part (MLG) ribs at certain wing-stations are
Regulatory Findings
TKELLEY on DSK3SPTVN1PROD with PROPOSALS
subject to widespread fatigue damage (WFD).
We determined that this proposed AD 39 as follows:
We are issuing this AD to prevent fatigue
would not have federalism implications cracking of the upper and lower wing skin
PART 39—AIRWORTHINESS planks at the attachment of the MLG ribs,
under Executive Order 13132. This
DIRECTIVES which could result in failure of the wing.
proposed AD would not have a
substantial direct effect on the States, on (f) Compliance
the relationship between the national ■ 1. The authority citation for part 39
continues to read as follows: Comply with this AD within the
Government and the States, or on the compliance times specified, unless already
distribution of power and Authority: 49 U.S.C. 106(g), 40113, 44701. done.
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(g) Inspection, Modification, and Corrective WA. For information on the availability of • Hand Delivery: U.S. Department of
Action this material at the FAA, call 425–227–1221. Transportation, Docket Operations,
At the later of the times specified in Issued in Renton, Washington, on March M–30, West Building Ground Floor,
paragraphs (g)(1) and (g)(2) of this AD: 12, 2015. Room W12–140, 1200 New Jersey
Remove the chordwise fastener rows of the Avenue SE., Washington, DC, between 9
upper and lower wing planks at the Jeffrey E. Duven,
Manager, Transport Airplane Directorate, a.m. and 5 p.m., Monday through
attachments to the MLG ribs at wing-station
(WS) 167 and WS 209; do a bolt hole eddy Aircraft Certification Service. Friday, except Federal holidays.
current (BHEC) inspection to detect cracking [FR Doc. 2015–06576 Filed 3–23–15; 8:45 am]
For service information identified in
of the fastener rows; and replace the original this proposed AD, contact Bombardier,
BILLING CODE 4910–13–P
fasteners with new, first oversize fasteners; in Inc., 400 Côte Vertu Road West, Dorval,
accordance with the Accomplishment Québec H4S 1Y9, Canada; telephone
Instructions of Lockheed Martin Electra 88 514–855–5000; fax 514–855–7401; email
Service Bulletin 721, dated April 30, 2014. If
DEPARTMENT OF TRANSPORTATION
thd.crj@aero.bombardier.com; Internet
any cracking is found during any inspection http://www.bombardier.com. You may
required by this paragraph: Before further
Federal Aviation Administration
flight, repair the cracking, in accordance with
view this referenced service information
the Accomplishment Instructions of 14 CFR Part 39 at the FAA, Transport Airplane
Lockheed Martin Electra 88 Service Bulletin Directorate, 1601 Lind Avenue SW.,
721, dated April 30, 2014. [Docket No. FAA–2015–0492; Directorate Renton, WA. For information on the
(1) At the applicable time specified in table Identifier 2014–NM–232–AD] availability of this material at the FAA,
1 of paragraph 1.E., ‘‘Compliance,’’ of call 425–227–1221.
Lockheed Martin Electra 88 Service Bulletin RIN 2120–AA64
721, dated April 30, 2014. Where table 1 of Examining the AD Docket
paragraph 1.E., ‘‘Compliance,’’ of Lockheed Airworthiness Directives; Bombardier,
Inc. Airplanes You may examine the AD docket on
Martin Electra 88 Service Bulletin 721, dated
the Internet at http://
April 30, 2014, specifies ‘‘Flt. Hrs,’’ this AD
specifies ‘‘total flight hours.’’
AGENCY: Federal Aviation www.regulations.gov by searching for
(2) Within 365 days or 600 flight hours Administration (FAA), DOT. and locating Docket No. FAA–2015–
after the effective date of this AD, whichever ACTION: Notice of proposed rulemaking 0492; or in person at the Docket
occurs first. (NPRM). Management Facility between 9 a.m.
and 5 p.m., Monday through Friday,
(h) No Reporting
SUMMARY: We propose to adopt a new except Federal holidays. The AD docket
Although Lockheed Martin Electra 88 airworthiness directive (AD) for certain contains this proposed AD, the
Service Bulletin 721, dated April 30, 2014, Bombardier, Inc. Model CL–600–2C10 regulatory evaluation, any comments
specifies to submit certain information to the
(Regional Jet Series 700, 701, & 702), received, and other information. The
manufacturer, this AD does not include that
requirement. CL–600–2D15 (Regional Jet Series 705), street address for the Docket Operations
and CL–600–2D24 (Regional Jet Series office (telephone 800–647–5527) is in
(i) Alternative Methods of Compliance 900) airplanes. This proposed AD was the ADDRESSES section. Comments will
(AMOCs) prompted by reports of a disconnect be available in the AD docket shortly
(1) The Manager, Atlanta ACO, FAA, has between the elevator lever and control after receipt.
the authority to approve AMOCs for this AD, rod. This proposed AD would require FOR FURTHER INFORMATION CONTACT:
if requested using the procedures found in 14 replacement of left and right fixed
CFR 39.19. In accordance with 14 CFR 39.19, Cesar Gomez, Aerospace Engineer,
control rods and lever assemblies of the Airframe and Mechanical Systems
send your request to your principal inspector
or local Flight Standards District Office, as elevator control system. We are Branch, ANE–171, FAA, New York
appropriate. If sending information directly proposing this AD to prevent a Aircraft Certification Office (ACO), 1600
to the manager of the ACO, send it to the disconnect between the elevator lever Stewart Avenue, Suite 410, Westbury,
attention of the person identified in and control rod, which could lead to un- NY 11590; telephone 516–228–7318; fax
paragraph (j)(1) of this AD. commanded elevator movement of the 516–794–5531.
(2) Before using any approved AMOC, associated control surface, a large
notify your appropriate principal inspector, SUPPLEMENTARY INFORMATION:
difference between the position of the
or lacking a principal inspector, the manager left and the right elevator control Comments Invited
of the local flight standards district office/
surface, and consequent reduced We invite you to send any written
certificate holding district office.
controllability of the airplane and relevant data, views, or arguments about
(j) Related Information degradation of the structural integrity of this proposed AD. Send your comments
(1) For more information about this AD, the horizontal stabilizer. to an address listed under the
Carl Gray, Aerospace Engineer, Airframe DATES: We must receive comments on ADDRESSES section. Include ‘‘Docket No.
Branch, ACE–117A, FAA, Atlanta ACO, 1701 this proposed AD by May 8, 2015.
Columbia Avenue, College Park, GA 30337; FAA–2015–0492; Directorate Identifier
phone: 404–474–5554; fax: 404–474–5605; ADDRESSES: You may send comments, 2014–NM–232–AD’’ at the beginning of
email: carl.w.gray@faa.gov. using the procedures found in 14 CFR your comments. We specifically invite
(2) For service information identified in 11.43 and 11.45, by any of the following comments on the overall regulatory,
this AD, contact Lockheed Martin methods: economic, environmental, and energy
Corporation/Lockheed Martin Aeronautics • Federal eRulemaking Portal: Go to aspects of this proposed AD. We will
TKELLEY on DSK3SPTVN1PROD with PROPOSALS
Company, Airworthiness Office, Dept. 6A0M, http://www.regulations.gov. Follow the consider all comments received by the
Zone 0252, Column P–58, 86 S. Cobb Drive, instructions for submitting comments. closing date and may amend this
Marietta, GA 30063; telephone 770–494–
• Fax: 202–493–2251. proposed AD based on those comments.
5444; fax 770–494–5445; email
ams.portal@lmco.com; Internet http:// • Mail: U.S. Department of We will post all comments we
www.lockheedmartin.com/ams/tools/ Transportation, Docket Operations, receive, without change, to http://
TechPubs.html. You may view this service M–30, West Building Ground Floor, www.regulations.gov, including any
information at the FAA, Transport Airplane Room W12–140, 1200 New Jersey personal information you provide. We
Directorate, 1601 Lind Avenue SW., Renton, Avenue SE., Washington, DC 20590. will also post a report summarizing each
VerDate Sep<11>2014 18:30 Mar 23, 2015 Jkt 235001 PO 00000 Frm 00008 Fmt 4702 Sfmt 4702 E:\FR\FM\24MRP1.SGM 24MRP1](https://thefederalregister.org/doc/80_FR_15581/page/4.svg)
Document Created: 2015-12-18 11:45:15
Document Modified: 2015-12-18 11:45:15
| 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 May 8, 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 15525 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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