Document ID: FAA-2019-0581-0001
Agency: faa
Document Type: Proposed Rule
Title: Airworthiness Directives: Lockheed Martin Corporation/Lockheed Martin Aeronautics Company Airplanes
Posted Date: 2019-07-31T04:00Z

[Federal Register Volume 84, Number 147 (Wednesday, July 31, 2019)]
[Proposed Rules]
[Pages 37165-37167]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2019-16130]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2019-0581; Product Identifier 2019-NM-067-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).

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SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD) 
for all Lockheed Martin Corporation/Lockheed Martin Aeronautics Company 
Model 382, 382B, 382E, 382F, 382G, C-130A, C-130B, C-130BL, C130E, C-
130H, C 130H 30, C130J, C130J-30, EC130Q, HC130H, KC 130H, NC-130B, 
NC130, and WC-130H airplanes. This proposed AD was prompted by a report 
indicating that two elevator booster assemblies experienced significant 
hydraulic fluid leaks, caused by fatigue cracks in the actuator 
cylinder. This proposed AD would require an inspection to determine the 
part number of the elevator booster actuator, repetitive ultrasonic 
inspections of the actuator to detect cracking, and replacement of 
cracked elevator booster assemblies. The FAA is proposing this AD to 
address the unsafe condition on these products.

DATES: The FAA must receive comments on this proposed AD by September 
16, 2019.

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 NPRM, contact Lockheed 
Martin Corporation/Lockheed Martin Aeronautics Company, Customer 
Support Center, Dept. 3E1M, Zone 0591, 86 S. Cobb Drive, Marietta, GA 
30063; telephone 770-494-9131; email hercules.support@lmco.com; 
internet http://www.lockheedmartin.com/en-us/who-we-are/business-areas/aeronautics/mmro/customer-support-center.html. You may view this 
service information at the FAA, Transport Standards Branch, 2200 South 
216th St., Des Moines, WA. For information on the availability of this 
material at the FAA, call 206-231-3195.

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-2019-
0581; or in person at Docket Operations between 9 a.m. and 5 p.m., 
Monday through Friday, except Federal holidays. The AD docket contains 
this NPRM, the regulatory evaluation, any comments received, and other 
information. The street address for Docket Operations is listed above. 
Comments will be available in the AD docket shortly after receipt.

FOR FURTHER INFORMATION CONTACT: Hector Hernandez, Aerospace Engineer, 
Systems and Equipment Section, FAA, Atlanta ACO Branch, 1701 Columbia 
Avenue, College Park, GA 30337; phone: 404-474-5587; fax: 404-474-5606; 
email: hector.hernandez@faa.gov.

SUPPLEMENTARY INFORMATION: 

Comments Invited

    The FAA invites 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-2019-0581; 
Product Identifier 2019-NM-067-AD'' at the beginning of your comments. 
The FAA specifically invites comments on the overall regulatory, 
economic, environmental, and energy aspects of this NPRM. The FAA will 
consider all comments received by the closing date and may amend this 
NPRM because of those comments.
    The FAA will post all comments received, without change, to http://www.regulations.gov, including any personal information you provide. 
The FAA will also post a report summarizing each substantive verbal 
contact received about this NPRM.

Discussion

    The FAA has received a report indicating that two elevator booster 
assemblies experienced significant hydraulic fluid leaks, caused by 
fatigue cracks in the actuator cylinder. Laboratory analysis of the 
cracked elevator booster actuators revealed an internal area in the 
cylinder body that is prone to fatigue crack initiation. The fatigue 
crack propagates unseen within the cylinder under normal operational 
loading until either a minor fluid leak becomes evident or the cylinder 
ruptures, creating a major leak. This condition, if not addressed, 
could result in a dual failure of the left and right actuator cylinders 
in the elevator booster assembly, which could lead to a significant 
reduction in controllability of the airplane.

Related Service Information Under 1 CFR Part 51

    The FAA reviewed Lockheed Martin Aeronautics Company Service 
Bulletin 382-27-51, Revision 1, dated January 17, 2018; and Lockheed 
Martin Aeronautics Company Service Bulletin 82-833, Revision 1, dated 
January 17, 2018. This service information describes procedures for an 
inspection to determine the part number of the elevator booster 
actuator, repetitive ultrasonic inspections of the elevator booster 
actuator at the forward-most end to detect cracking along the fluid 
transfer bore, left and right cylinders, and replacement of cracked 
elevator

[[Page 37166]]

booster assemblies. These documents are distinct since they apply to 
different airplane models.
    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.

FAA's Determination

    The FAA is proposing this AD because the agency 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 previously, except as discussed 
under ``Differences Between this Proposed AD and the Service 
Information.''

Impact on Intrastate Aviation in Alaska

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

Differences Between This Proposed AD and the Service Information

    Lockheed Martin Aeronautics Company Service Bulletin 382-27-51, 
Revision 1, dated January 17, 2018; and Lockheed Martin Aeronautics 
Company Service Bulletin 82-833, Revision 1, dated January 17, 2018; 
specify to return parts to the manufacturer. This proposed AD would not 
include that requirement.

Costs of Compliance

    The FAA estimates that this proposed AD affects 7 airplanes of U.S. 
registry. The FAA estimates the following costs to comply with this 
proposed AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                 Cost on U.S.
              Action                    Labor cost        Parts cost      Cost per product        operators
----------------------------------------------------------------------------------------------------------------
Part number inspection...........  1 work-hour x $85                $0  $85................  $595.
                                    per hour = $85.
Ultrasonic inspections...........  5 work-hours x $85                0  425 per inspection   2,975 per
                                    per hour = $425                      cycle.               inspection cycle.
                                    per inspection
                                    cycle.
----------------------------------------------------------------------------------------------------------------

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

                                               On-Condition Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                     Cost per
                    Action                                 Labor cost               Parts cost        product
----------------------------------------------------------------------------------------------------------------
Replacement...................................  10 work-hours x $85 per hour =           $43,000         $43,850
                                                 $850.
----------------------------------------------------------------------------------------------------------------

Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to 
issue rules on aviation safety. Subtitle I, section 106, describes the 
authority of the FAA Administrator. Subtitle VII: Aviation Programs, 
describes in more detail the scope of the Agency's authority.
    The FAA is issuing this rulemaking under the authority described in 
Subtitle VII, Part A, Subpart III, Section 44701: ``General 
requirements.'' Under that section, Congress charges the FAA with 
promoting safe flight of civil aircraft in air commerce by prescribing 
regulations for practices, methods, and procedures the Administrator 
finds necessary for safety in air commerce. This regulation is within 
the scope of that authority because it addresses an unsafe condition 
that is likely to exist or develop on products identified in this 
rulemaking action.
    This proposed AD is issued in accordance with authority delegated 
by the Executive Director, Aircraft Certification Service, as 
authorized by FAA Order 8000.51C. In accordance with that order, 
issuance of ADs is normally a function of the Compliance and 
Airworthiness Division, but during this transition period, the 
Executive Director has delegated the authority to issue ADs applicable 
to transport category airplanes and associated appliances to the 
Director of the System Oversight Division.

Regulatory Findings

    The FAA 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) 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:

[[Page 37167]]

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-2019-0581; Product Identifier 2019-NM-067-AD.

(a) Comments Due Date

    The FAA must receive comments by September 16, 2019.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to all Lockheed Martin Corporation/Lockheed 
Martin Aeronautics Company Model 382, 382B, 382E, 382F, 382G, C-
130A, C-130B, C-130BL, C130E, C-130H, C 130H 30, C130J, C130J-30, 
EC130Q, HC130H, KC 130H, NC-130B, NC130, and WC-130H airplanes, 
certificated in any category.

(d) Subject

    Air Transport Association (ATA) of America Code 27, Flight 
controls.

(e) Unsafe Condition

    This AD was prompted by a report indicating that two elevator 
booster assemblies experienced significant hydraulic fluid leaks, 
caused by fatigue cracks in the actuator cylinder. The FAA is 
issuing this AD to address the possibility of a dual failure of the 
left and right actuator cylinders in the elevator booster assembly, 
which could lead to a significant reduction in controllability of 
the airplane.

(f) Compliance

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

(g) Part Number Inspection, Repetitive Ultrasonic Inspections, and 
Replacement

    (1) On any elevator booster assembly having a part number 
374461-5, 374461-7, or 374461-11, before the accumulation of 4,000 
total flight hours on the elevator booster assembly, or within 180 
days after the effective date of this AD, whichever occurs later, 
except as required by paragraph (h) of this AD: Do an inspection of 
the elevator booster assembly to determine the part number of the 
elevator booster actuator. If the elevator booster actuator has a 
part number other than 5C5803, no further action is required by this 
AD.
    (2) If, during the inspection required by paragraph (g)(1) of 
this AD, any elevator booster actuator having part number 5C5803 is 
found, before the accumulation of 4,000 total flight hours on the 
elevator booster assembly, or within 180 days after the effective 
date of this AD, whichever occurs later, except as required by 
paragraph (h) of this AD: Do an ultrasonic inspection of the 
elevator booster actuator at the forward-most end to detect cracking 
along the fluid transfer bore, left and right cylinders, in 
accordance with the Accomplishment Instructions of Lockheed Martin 
Aeronautics Company Service Bulletin 382-27-51, Revision 1, dated 
January 17, 2018; or Lockheed Martin Aeronautics Company Service 
Bulletin 82-833, Revision 1, dated January 17, 2018; as applicable. 
Repeat the inspection thereafter at intervals not to exceed 1,400 
flight hours.
    (3) If, during any inspection required by paragraph (g)(2) of 
this AD, any cracking is found, before further flight: Replace the 
elevator booster assembly, in accordance with the Accomplishment 
Instructions of Lockheed Martin Aeronautics Company Service Bulletin 
382-27-51, Revision 1, dated January 17, 2018; or Lockheed Martin 
Aeronautics Company Service Bulletin 82-833, Revision 1, dated 
January 17, 2018; as applicable.

(h) Compliance Time Exception

    For any elevator booster assembly having part number 374461-5, 
374461-7, or 374461-11 on which the total flight cycles are unknown, 
do the inspections required by paragraphs (g)(1) and (g)(2) of this 
AD, as applicable, within 180 days after the effective date of this 
AD.

(i) No Reporting and No Return of Parts

    (1) Although Lockheed Martin Aeronautics Company Service 
Bulletin 382-27-51, Revision 1, dated January 17, 2018; and Lockheed 
Martin Aeronautics Company Service Bulletin 82-833, Revision 1, 
dated January 17, 2018; specify to report submit certain information 
to the manufacturer, this AD does not include that requirement.
    (2) Although Lockheed Martin Aeronautics Company Service 
Bulletin 382-27-51, Revision 1, dated January 17, 2018; and Lockheed 
Martin Aeronautics Company Service Bulletin 82-833, Revision 1, 
dated January 17, 2018; specify to return parts to the manufacturer, 
this AD does not require the return of the parts to the 
manufacturer.

(j) Credit for Previous Actions

    This paragraph provides credit for the actions specified in 
paragraph (g) of this AD, if those actions were performed before the 
effective date of this AD using Lockheed Martin Aeronautics Company 
Service Bulletin 382-27-51, dated July 17, 2017; or Lockheed Martin 
Aeronautics Company Service Bulletin 82-833, dated April 28, 2017; 
as applicable.

(k) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, Atlanta ACO Branch, FAA, has the authority to 
approve AMOCs for this AD, if requested using the procedures found 
in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request 
to your principal inspector or local Flight Standards District 
Office, as appropriate. If sending information directly to the 
manager of the certification office, send it to the attention of the 
person identified in paragraph (l)(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.
    (3) An AMOC that provides an acceptable level of safety may be 
used for any repair, modification, or alteration required by this AD 
if it is approved by a Lockheed Martin Corporation/Lockheed Martin 
Aeronautics Company Designated Engineering Representative (DER) that 
has been authorized by the Manager, Atlanta ACO Branch, FAA, to make 
those findings. To be approved, the repair, modification deviation, 
or alteration deviation must meet the certification basis of the 
airplane, and the approval must specifically refer to this AD.

(l) Related Information

    (1) For more information about this AD, contact Hector 
Hernandez, Aerospace Engineer, Systems and Equipment Section, FAA, 
Atlanta ACO Branch, 1701 Columbia Avenue, College Park, GA 30337; 
phone: 404-474-5587; fax: 404-474-5606; email: 
hector.hernandez@faa.gov.
    (2) For service information identified in this AD, contact 
Lockheed Martin Corporation/Lockheed Martin Aeronautics Company, 
Customer Support Center, Dept. 3E1M, Zone 0591, 86 S Cobb Drive, 
Marietta, GA 30063; telephone 770-494-9131; email 
hercules.support@lmco.com; internet http://www.lockheedmartin.com/en-us/who-we-are/business-areas/aeronautics/mmro/customer-support-center.html. You may view this service information at the FAA, 
Transport Standards Branch, 2200 South 216th St., Des Moines, WA. 
For information on the availability of this material at the FAA, 
call 206-231-3195.

    Issued in Des Moines, Washington, on July 24, 2019.
Dionne Palermo,
Acting Director, System Oversight Division, Aircraft Certification 
Service.
[FR Doc. 2019-16130 Filed 7-30-19; 8:45 am]
 BILLING CODE 4910-13-P