
[Federal Register Volume 81, Number 177 (Tuesday, September 13, 2016)]
[Proposed Rules]
[Pages 62845-62847]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2016-21704]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2016-9120; Directorate Identifier 2016-CE-024-AD]
RIN 2120-AA64


Airworthiness Directives; M7 Aerospace LLC

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: We propose to adopt a new airworthiness directive (AD) for all 
M7 Aerospace LLC Models SA226-AT, SA226-T, SA226-T(B), SA226-TC, SA227-
AC (C-26A), SA227-AT, SA227-BC (C-26A), SA227-CC, SA227-DC (C-26B), and 
SA227-TT airplanes. This proposed AD was prompted by corrosion and 
stress corrosion cracking of the pitch trim actuator upper attach 
fittings of the horizontal stabilizer front spar. This proposed AD 
would require repetitive inspections of the pitch trim actuator upper 
attach fittings for corrosion and/or cracking in the bolt holes and the 
web/flange radius with replacement of fittings as necessary. We are 
proposing this AD to prevent jamming and/or loss of control of the 
horizontal stabilizer, which could result in partial or complete loss 
of airplane pitch control.

DATES: We must receive comments on this proposed AD by October 28, 
2016.

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 M7 
Aerospace LLC, 10823 NE Entrance Road, San Antonio, Texas 78216; phone: 
(210) 824-9421; fax: (210) 804-7766; Internet: http://www.elbitsystems-us.com; email: MetroTech@M7Aerospace.com. You may view this referenced 
service information at the FAA, Small Airplane Directorate, 901 Locust, 
Kansas City, Missouri 64106. For information on the availability of 
this material at the FAA, call 816-329-4148.

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-2016-
9120; 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: Andrew McAnaul, Aerospace Engineer, 
FAA, ASW-143 (c/o San Antonio MIDO), 10100 Reunion Place, Suite 650, 
San Antonio, Texas 78216; phone: (210) 308-3365; fax: (210) 308-3370; 
email: andrew.mcanaul@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-2016-9120; 
Directorate Identifier 2016-CE-024-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

    We received reports of multiple SA226 and SA227 airplanes with 
corrosion and/or stress corrosion cracks in the pitch trim actuator 
upper attach fittings of the horizontal stabilizer front spar. This 
condition, if not corrected, could result in jamming and/or loss of 
control of the horizontal stabilizer with consequent partial or 
complete loss of airplane pitch control.

Related Service Information Under 1 CFR Part 51

    We reviewed M7 Aerospace LLC Service Bulletin (SB) 226-27-081 R1, 
M7 Aerospace LLC SB 227-27-061 R1, and M7 Aerospace LLC SB CC7-27-033 
R1, all Issued: April 13, 2016 and Revised: June 27, 2016. The service 
information describes procedures for detailed visual, liquid penetrant, 
ultrasound and high frequency eddy current inspections of the pitch 
trim actuator upper attach fittings for corrosion and cracking in the 
bolt holes and the web/flange radius, and replacement if necessary. 
This service information is reasonably available

[[Page 62846]]

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 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.

Costs of Compliance

    We estimate that this proposed AD affects 300 airplanes of U.S. 
registry.
    We estimate the following costs to comply with this proposed AD:

                                                 Estimated Costs
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                                                                                    Cost per       Cost on U.S.
            Action                    Labor cost              Parts cost            product         operators
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Inspect pitch trim actuator     16 work-hours x $85     Not Applicable........          $1,360         $408,000
 upper attach fittings.          per hour = $1,360.
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    We estimate the following costs to do any necessary replacements 
that would be required based on the results of the proposed inspection. 
We have no way of determining the number of aircraft that might need 
these replacements:

                                               On-Condition Costs
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                                                                                                     Cost per
                  Action                                Labor cost                 Parts cost        product
----------------------------------------------------------------------------------------------------------------
Replace 2 fittings........................  8 work-hours x $85 per hour = $680          $4,900           $5,580
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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):

M7 Aerospace LLC: Docket No. FAA-2016-9120; Directorate Identifier 
2016-CE-024-AD.

(a) Comments Due Date

    We must receive comments by October 28, 2016.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to M7 Aerospace LLC Models SA226-AT, SA226-T, 
SA226-T(B), SA226-TC, SA227-AC (C-26A), SA227-AT, SA227-BC (C-26A), 
SA227-CC, SA227-DC (C-26B), and SA227-TT airplanes, all serial 
numbers, certificated in any category.

(d) Subject

    Joint Aircraft System Component (JASC)/Air Transport Association 
(ATA) of America Code 5510, Horizontal Stabilizer Structure.

(e) Unsafe Condition

    This AD was prompted by corrosion and stress corrosion cracking 
of the pitch trim actuator upper attach fittings of the horizontal 
stabilizer front spar. We are issuing this AD to prevent jamming 
and/or loss of control of the horizontal stabilizer, which could 
result in partial or complete loss of airplane pitch control.

(f) Compliance

    Comply with paragraphs (g)(1) and (2) of this AD using the 
following service bulletins and within the compliance times 
specified, unless already done:
    (1) For Models SA226-AT, SA226-T, SA226-T(B), and SA226-TC: M7 
Aerospace LLC Service Bulletin (SB) 226-27-081 R1, Issued: April 13, 
2016 and Revised: June 27, 2016; or
    (2) For Models SA227-AC (C-26A), SA227-AT, SA227-BC (C-26A), and 
SA227-TT: M7 Aerospace LLC SB 227-27-061 R1, Issued: April 13, 2016 
and Revised: June 27, 2016; or
    (3) For Models SA227-CC and SA227-DC (C-26B): M7 Aerospace LLC 
SB CC7-27-033 R1, Issued: April 13, 2016 and Revised: June 27, 2016.

[[Page 62847]]

(g) Actions

    (1) Within the next 600 hours time-in-service (TIS) after the 
effective date of this AD or within the next 12 months after the 
effective date of this AD, whichever occurs first, and repetitively 
thereafter at intervals not to exceed every 5,000 hours TIS or 5 
years, whichever occurs first, perform the inspection of the pitch 
trim actuator upper attach fittings following section 2.A. and 
return to service following section 2.C. of the Accomplishment 
Instructions of the service bulletins identified in paragraphs 
(f)(1), (2), or (3) of this AD, as applicable.
    (2) If any corrosion or cracks are found as a result of any 
inspection in paragraph (g)(1) of this AD, before further flight, 
replace the fitting following section 2.B. and return to service 
following section 2.C. of the Accomplishment Instructions of the 
service bulletins identified in paragraphs (f)(1), (2), or (3) of 
this AD, as applicable.

(h) Credit for Actions Accomplished in Accordance With Previous Service 
Information

    This proposed AD allows credit for inspection or replacement of 
the pitch trim actuator upper attach fittings required in paragraph 
(g)(1) and (2) of the AD, if done before the effective date of this 
AD, following the procedures in the Accomplishment Instructions of 
the applicable service information listed in paragraphs (h)(1) 
through (3) of this AD:
    (1) For Models SA226-AT, SA226-T, SA226-T(B), and SA226-TC: M7 
Aerospace LLC Service Bulletin (SB) 226-27-081, Issued: April 13, 
2016; or
    (2) For Models SA227-AC (C-26A), SA227-AT, SA227-BC (C-26A), and 
SA227-TT: M7 Aerospace LLC SB 227-27-061, Issued: April 13, 2016; or
    (3) For Models SA227-CC and SA227-DC (C-26B): M7 Aerospace LLC 
SB CC7-27-033, Issued: April 13, 2016.

(i) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, Fort Worth Airplane Certification Office, 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 (i) 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, contact Andrew McAnaul, 
Aerospace Engineer, FAA, ASW-143 (c/o San Antonio MIDO), 10100 
Reunion Place, Suite 650, San Antonio, Texas 78216; phone: (210) 
308-3365; fax: (210) 308-3370; email: andrew.mcanaul@faa.gov.
    (2) For service information identified in this AD, contact M7 
Aerospace LLC, 10823 NE Entrance Road, San Antonio, Texas 78216; 
phone: (210) 824-9421; fax: (210) 804-7766; Internet: http://www.elbitsystems-us.com; email: MetroTech@M7Aerospace.com. You may 
view this referenced service information at the FAA, Small Airplane 
Directorate, 901 Locust, Kansas City, Missouri 64106. For 
information on the availability of this material at the FAA, call 
816-329-4148.

    Issued in Kansas City, Missouri, on September 1, 2016.
Pat Mullen,
Acting Manager, Small Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2016-21704 Filed 9-12-16; 8:45 am]
BILLING CODE 4910-13-P


