Document ID: FAA-2016-9120-0003
Agency: faa
Document Type: Rule
Title: Airworthiness Directives: M7 Aerospace LLC
Posted Date: 2016-12-08T05:00Z

[Federal Register Volume 81, Number 236 (Thursday, December 8, 2016)]
[Rules and Regulations]
[Pages 88621-88623]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2016-29242]

-----------------------------------------------------------------------

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2016-9120; Directorate Identifier 2016-CE-024-AD; 
Amendment 39-18738; AD 2016-25-12]
RIN 2120-AA64

Airworthiness Directives; M7 Aerospace LLC

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

-----------------------------------------------------------------------

SUMMARY: We are adopting 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 AD was prompted by corrosion and stress 
corrosion cracking of the pitch trim actuator upper attach fittings of 
the horizontal stabilizer front spar. This AD requires repetitive 
inspections with replacement of fittings as necessary. We are issuing 
this AD to correct the unsafe condition on these products.

DATES: This AD is effective January 12, 2017.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in this AD as of January 12, 
2017.

ADDRESSES: For service information identified in this final rule, 
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. It 
is also available on the internet at http://www.regulations.gov by 
searching for and locating Docket No. FAA-2016-9120.

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 AD, the regulatory evaluation, any comments received, and 
other information. The address for the

[[Page 88622]]

Docket Office (phone: 800-647-5527) is Document Management Facility, 
U.S. Department of Transportation, Docket Operations, M-30, West 
Building Ground Floor, Room W12-140, 1200 New Jersey Avenue SE., 
Washington, DC 20590.

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: 

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 by adding an AD that would apply to 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. 
The NPRM published in the Federal Register on September 13, 2016 (81 FR 
62845). The NPRM was prompted by 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. The NPRM proposed to 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. This condition, if not corrected, could cause jamming 
and/or loss of control of the horizontal stabilizer, which could result 
in partial or complete loss of airplane pitch control. We are issuing 
this AD to correct the unsafe condition on these products.

Comments

    We gave the public the opportunity to participate in developing 
this AD. We received no comments on the NPRM or on the determination of 
the cost to the public.

Conclusion

    We reviewed the relevant data and determined that air safety and 
the public interest require adopting this AD as proposed except for 
minor editorial changes. We have determined that these minor changes:
     Are consistent with the intent that was proposed in the 
NPRM for correcting the unsafe condition; and
     Do not add any additional burden upon the public than was 
already proposed in the NPRM.

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 revised June 27, 2016. In combination for the different 
applicable models, 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 for applicable 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.

Costs of Compliance

    We estimate that this AD affects 300 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
----------------------------------------------------------------------------------------------------------------
Inspect pitch trim actuator upper   16 work-hours x $85    Not applicable.......          $1,360        $408,000
 attach fittings.                    per hour = $1,360.
----------------------------------------------------------------------------------------------------------------

    We estimate the following costs to do any necessary replacements 
that would be required based on the results of the inspection. We have 
no way of determining the number of aircraft that might need these 
replacements:

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

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

    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

[[Page 88623]]

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):

2016-25-12 M7 Aerospace LLC: Amendment 39-18738; Docket No. FAA-
2016-9120; Directorate Identifier 2016-CE-024-AD.

(a) Effective Date

    This AD is effective January 12, 2017.

(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, 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, revised June 27, 2016; 
or
    (3) For Models SA227-CC and SA227-DC (C-26B): M7 Aerospace LLC 
SB CC7-27-033 R1, revised June 27, 2016.

(g) Actions

    (1) Within the next 600 hours time-in-service (TIS) after 
January 12, 2017 (the effective date of this AD) or within the next 
12 months after January 12, 2017 (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 paragraph (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 paragraph (f)(1), (2), or (3) of 
this AD, as applicable.

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

    This 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 January 12, 2017 (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

    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.

(k) 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) M7 Aerospace LLC Service Bulletin (SB) 226-27-081 R1, 
revised June 27, 2016.
    (ii) M7 Aerospace LLC SB 227-27-061 R1, revised June 27, 2016.
    (iii) M7 Aerospace LLC SB CC7-27-033 R1, revised June 27, 2016.
    (3) For M7 Aerospace LLC 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.
    (4) 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.
    (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 Kansas City, Missouri, on November 30, 2016.
Melvin Johnson,
Acting Manager, Small Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2016-29242 Filed 12-7-16; 8:45 am]
BILLING CODE 4910-13-P