[Federal Register Volume 83, Number 100 (Wednesday, May 23, 2018)]
[Rules and Regulations]
[Pages 23788-23791]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2018-11133]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2018-0447; Product Identifier 2018-NM-080-AD; Amendment 
39-19290; AD 2018-11-02]
RIN 2120-AA64


Airworthiness Directives; Lockheed Martin Corporation/Lockheed 
Martin Aeronautics Company

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule; request for comments.

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SUMMARY: We are adopting a new airworthiness directive (AD) for all 
Lockheed Martin Corporation/Lockheed Martin Aeronautics Company Model 
188A and 188C airplanes; and Model P3A, P-3A, and P3B airplanes type 
certificated under various other type certificate holders. Certain 
variants of Model 188A and 188C airplanes are known as ``P-3'' series 
airplanes. P-3 series airplanes include but are not limited to Model 
CP-140, NP-3A, P3A, P-3A, P3B, P-3B, P-3C, P-3P, and WP-3D airplanes. 
This AD requires a borescope inspection of the aileron

[[Page 23789]]

control rod assembly to determine if threads exist on the aileron 
control rod body, and corrective actions if necessary. This AD was 
prompted by a report indicating that certain aileron control rod bodies 
were incorrectly machined so that they did not include the load-
carrying threads in the bore of the aileron control rod body. As a 
result, aileron control rod assemblies, which contain the discrepant 
part, do not provide adequate load carrying capabilities. We are 
issuing this AD to address the unsafe condition on these products.

DATES: This AD is effective May 23, 2018.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of May 23, 
2018.
    We must receive comments on this AD by July 9, 2018.

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 final rule, contact 
Lockheed Martin Corporation/Lockheed Martin Aeronautics Company, 
Customer Support Center, Dept. 3E1M, Zone 0591, 86 S Cobb Drive, 
Marietta, GA 30063; telephone 770-494-9131; email 
[email protected]; internet https://www.lockheedmartin.com/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. It is also available on the internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2018-
0447.

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-2018-
0447; 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 final rule, the regulatory evaluation, any comments received, and 
other information. The street address for Docket Operations (phone: 
800-647-5527) is in the ADDRESSES section. 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: [email protected].

SUPPLEMENTARY INFORMATION: 

Discussion

    We have received a report indicating that certain aileron control 
rod bodies, part number (P/N) 826999-3, were incorrectly machined so 
that they did not include the load-carrying threads in the bore of the 
aileron control rod body. As a result, aileron control rod assemblies, 
P/N 826998-3, which contain the discrepant part, do not provide 
adequate load carrying capabilities. A number of these discrepant parts 
have been found installed on operational airplanes.
    The discrepant aileron control rod bodies, P/N 826999-3, were 
machined with a smooth internal bore rather than with \7/8\-inch 
internal threads to engage the mating part. The missing \7/8\-inch 
internal threads are intended to transmit the aileron control loads. 
The incorrectly machined aileron control rod assemblies, P/N 826998-3, 
are held together with a single threaded #10 (0.190-inch diameter) 
screw that is not intended to carry aileron control forces.
    Failure of the aileron control rod assembly, or loss or failure of 
the #10 (0.190-inch diameter) screw holding the left (or right) aileron 
control rod assembly together, if not addressed, will result in loss of 
aileron authority, and could result in the jamming of both left and 
right ailerons, and loss of control of the airplane.

Related Service Information Under 1 CFR Part 51

    We reviewed Lockheed Martin Aeronautics Company Aircraft 
Maintenance Bulletin M0017R2, Revision 2, dated May 10, 2018. This 
service information describes procedures for a borescope inspection of 
the aileron control rod assembly to determine if threads exist on the 
aileron control rod body. 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

    We are issuing 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.

AD Requirements

    This AD requires accomplishing the actions specified in the service 
information described previously, and replacement of the aileron 
control rod assembly with a serviceable assembly.

Difference Between Service Information and AD

    Lockheed Martin Aeronautics Company Aircraft Maintenance Bulletin 
M0017R2, Revision 2, dated May 10, 2018, recommends that the inspection 
be performed before the next flight. This AD, however, allows 3 days 
after the effective date of the AD to do this inspection. We have 
determined that 3 days will allow affected operators time for an 
orderly inspection of their fleet and still provide an acceptable level 
of safety.

FAA's Justification and Determination of the Effective Date

    An unsafe condition exists that requires the immediate adoption of 
this AD without providing an opportunity for public comments prior to 
adoption. The FAA has found that the risk to the flying public 
justifies waiving notice and comment prior to adoption of this rule 
because failure of the aileron control rod assembly, or loss or failure 
of the #10 (0.190-inch diameter) screw holding the left (or right) 
aileron control rod assembly together, will result in loss of aileron 
authority, and could result in the jamming of both left and right 
ailerons, and loss of control of the airplane. Therefore, we find good 
cause that notice and opportunity for prior public comment are 
impracticable. In addition, for the reasons stated above, we find that 
good cause exists for making this amendment effective in less than 30 
days.

Comments Invited

    This AD is a final rule that involves requirements affecting flight 
safety and was not preceded by notice and an opportunity for public 
comment. However, we invite you to send any written data, views, or 
arguments about this final rule. Send your comments to an address 
listed under the ADDRESSES section. Include the docket number

[[Page 23790]]

FAA-2018-0447 and Product Identifier 2018-NM-080-AD at the beginning of 
your comments. We specifically invite comments on the overall 
regulatory, economic, environmental, and energy aspects of this final 
rule. We will consider all comments received by the closing date and 
may amend this final rule 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 final rule.

Costs of Compliance

    We estimate that this AD affects 25 airplanes of U.S. registry. We 
estimate the following costs to comply with this AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                     Cost per      Cost on U.S.
                Action                         Labor cost           Parts cost        product        operators
----------------------------------------------------------------------------------------------------------------
Inspection............................  4 work-hours x $85 per                $0            $340          $8,500
                                         hour = $340.
----------------------------------------------------------------------------------------------------------------

    We estimate the following costs to replace any aileron control rod 
assembly that would be required based on the results of the inspection. 
We have no way of determining the number of aircraft that might need 
this replacement:

                                               On-Condition Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                     Cost per
                    Action                                 Labor cost               Parts cost        product
----------------------------------------------------------------------------------------------------------------
Replacement...................................  9 work-hours x $85 per hour =             $1,600          $2,365
                                                 $765.
----------------------------------------------------------------------------------------------------------------

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.
    This 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

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

Adoption of the Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA amends 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

0
1. The authority citation for part 39 continues to read as follows:

    Authority:  49 U.S.C. 106(g), 40113, 44701.


Sec.  39.13  [Amended]

0
2. The FAA amends Sec.  39.13 by adding the following new airworthiness 
directive (AD):

2018-11-02 Lockheed Martin Corporation/Lockheed Martin Aeronautics 
Company and various other type certificate holders: Amendment 39-
19290; Docket No. FAA-2018-0447; Product Identifier 2018-NM-080-AD.

(a) Effective Date

    This AD is effective May 23, 2018.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to all Lockheed Martin Corporation/Lockheed 
Martin Aeronautics Company Model 188A and 188C airplanes; and Model 
P3A, P-3A, and P3B airplanes type certificated under various other 
type certificate holders; certificated in any category.

    Note 1 to paragraph (c) of this AD: Certain variants of Model 
188A and 188C airplanes are known as ``P-3'' series airplanes. P-3 
series airplanes include but are not limited to Model CP-140, NP-3A, 
P3A, P-3A, P3B, P-3B, P-3C, P-3P, and WP-3D airplanes.

(d) Subject

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

(e) Unsafe Condition

    This AD was prompted by a report indicating that certain aileron 
control rod bodies, part number (P/N) 826999-3, were incorrectly 
machined so that they did not include the load-carrying threads in 
the bore

[[Page 23791]]

of the aileron control rod body. As a result, aileron control rod 
assemblies, P/N 826998-3, which contain the discrepant part, do not 
provide adequate load carrying capabilities. We are issuing this AD 
to address failure of the aileron control rod assembly, or loss or 
failure of the #10 (0.190-inch diameter) screw holding the left (or 
right) aileron control rod assembly together, which will result in 
loss of aileron authority, and could result in the jamming of both 
left and right ailerons, and loss of control of the airplane.

(f) Compliance

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

(g) Inspection

    Within 3 days after the effective date of this AD, perform a 
borescope inspection of the aileron control rod assembly, P/N 
826998-3, to determine if threads exist on the aileron control rod 
body, P/N 826999-3, in accordance with Lockheed Martin Aeronautics 
Company Aircraft Maintenance Bulletin M0017R2, Revision 2, dated May 
10, 2018. If the inspection indicates missing threads on the aileron 
control rod body, before further flight, replace the aileron control 
rod assembly with a serviceable part. A serviceable aileron control 
rod assembly is one that has been inspected in accordance with the 
requirements of this paragraph and found to have internal threads on 
the aileron control rod body.

    Note 2 to paragraph (g) of this AD: Guidance on replacing the 
aileron control rod assembly can be found in Lockheed Martin 
Aircraft Maintenance Manual Sections 27-2-2 AILERON PRIMARY CONTROL 
CABLES, Maintenance Practices, Rigging of Aileron Primary Control 
Cable System; 27-2-3 AILERON PUSH-PULL TUBES, BRACKETS AND 
BELLCRANKS, Maintenance Practices, Aileron Push-Pull Tubes, Brackets 
and Bellcranks, Remove/Replace/Adjust/Rig; and 27-2-4 AILERON, 
Maintenance Practices, Removal/Installation/Adjustment/Lubrication 
aileron.

(h) Parts Installation Limitation

    As of the effective date of this AD, no person may install an 
aileron control rod assembly, P/N 826998-3, on any airplane, unless 
the aileron control rod assembly is serviceable as defined in 
paragraph (g) of this AD.

(i) Reporting Provisions

    Although Lockheed Martin Aeronautics Company Aircraft 
Maintenance Bulletin M0017R2, Revision 2, dated May 10, 2018, 
recommends that inspection reports be submitted to Lockheed, this AD 
does not require that action.

(j) Special Flight Permit

    Special flight permits, as described in Section 21.197 and 
Section 21.199 of the Federal Aviation Regulations (14 CFR 21.197 
and 21.199), are not allowed.

(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) 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.

(l) Related Information

    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: [email protected].

(m) Material Incorporated by Reference

    (1) The Director of the Federal Register approved the 
incorporation by reference (IBR) of the service information listed 
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
    (2) You must use this service information as applicable to do 
the actions required by this AD, unless the AD specifies otherwise.
    (i) Lockheed Martin Aeronautics Company Aircraft Maintenance 
Bulletin M0017R2, Revision 2, dated May 10, 2018 (only the first 
page contains the date).
    (ii) Reserved.
    (3) For service information identified in this AD, contact 
Lockheed Martin Corporation/Lockheed Martin Aeronautics Company, 
Customer Support Center, Dept. 3E1M, Zone 0591, 86 S Cobb Drive, 
Marietta, GA 30063; telephone 770-494-9131; email 
[email protected]; internet https://www.lockheedmartin.com/en-us/who-we-are/business-areas/aeronautics/mmro/customer-support-center.html.
    (4) 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.
    (5) You may view this service information that is incorporated 
by reference at the National Archives and Records Administration 
(NARA). For information on the availability of this material at 
NARA, call 202-741-6030, or go to http://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued in Des Moines, Washington, on May 17, 2018.
Jeffrey E. Duven,
Director, System Oversight Division, Aircraft Certification Service.
[FR Doc. 2018-11133 Filed 5-22-18; 8:45 am]
 BILLING CODE 4910-13-P