[Federal Register Volume 82, Number 61 (Friday, March 31, 2017)]
[Rules and Regulations]
[Pages 15982-15985]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2017-05857]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2016-9531; Directorate Identifier 2015-CE-011-AD; 
Amendment 39-18839; AD 2017-07-01]
RIN 2120-AA64


Airworthiness Directives; M7 Aerospace LLC Models Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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SUMMARY: We are adopting a new airworthiness directive (AD) for certain 
M7 Aerospace LLC Models SA226-T, SA226-AT, 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 detachment of the power 
lever linkage to the TPE331 engine propeller pitch control. This AD 
requires repetitively inspecting the propeller pitch control for proper 
torque, with corrections as necessary until required replacement or 
rework of the PPC assembly to have a threaded hole in the splined end 
of the shouldered shaft and installation of a secondary retention 
device is done. We are issuing this AD to correct the unsafe condition 
on these products.

DATES: This AD is effective May 5, 2017.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in this AD as of May 5, 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: [email protected]; or Honeywell 
International Inc. 111 S. 34th Street, Phoenix, Arizona 85034-2802; 
phone: (855) 808-6500; email: [email protected]; Internet: 
https://aerospace.honeywell.com/en/services/maintenance-and-monitoring. 
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-
9531.

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-
9531; 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 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 ONE OF THE FOLLOWING: 
     Justin Carter, ASW-142, Aerospace Engineer, Fort Worth 
Airplane Certification Office (ACO), FAA, 10101 Hillwood Parkway, Fort 
Worth, Texas 76177-1524; telephone: (817) 222-5146; fax: (817) 222-
5960; email: [email protected]; or
     Kristin Bradley, ASW-143, Aerospace Engineer, Fort Worth 
ACO, FAA, 10101 Hillwood Parkway, Fort Worth, Texas 76177-1524; 
telephone: (817) 222-5485; fax: (817) 222-5960; email: 
[email protected].

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 certain M7 Aerospace LLC 
Models SA226-T, SA226-AT, 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 December 28, 
2016 (81 FR 95528). The NPRM was prompted by reports of the airplane 
power lever linkage detaching from the TPE331 engine propeller pitch 
control (PPC) shaft. In flight operations, detachment may result in 
fuel flow to the engine remaining constant regardless of the power 
lever movement by the pilot. The orientation of the engine on certain 
M7 Aerospace airplanes increases the vulnerability of detachment. The 
PPC lever is an airplane part and its detachment from

[[Page 15983]]

the TPE311 has been the subject of previous ADs on other airplane type 
designs. The NPRM proposed to require repetitive inspections of the PPC 
lever with corrective action as necessary until required replacement or 
rework of the PPC assembly to have a threaded hole in the splined end 
of the shouldered shaft and installation of a secondary retention 
feature for the airplane control linkage interface is done. 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. 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 SA226 Series Service Bulletin 226-76-
012, dated March 17, 2015; M7 Aerospace LLC SA227 Series Service 
Bulletin 227-76-007, dated March 17, 2015; and M7 Aerospace LLC SA227 
Series Commuter Category Service Bulletin CC7-76-004, dated March 17, 
2015; that, in combination with the temporary revisions and service 
bulletin listed below, describes the actions that must be done for the 
applicable models to comply with this AD.
    We also reviewed M7 Aerospace SA226 Series Maintenance Manual 
Temporary Revision 71-02, dated March 15, 2016; M7 Aerospace SA227 
Series Maintenance Manual Temporary Revision 71-03, dated March 15, 
2016; and M7 Aerospace SA227 Series Commuter Category Maintenance 
Manual Temporary Revision 71-02, dated March 15, 2016; that describes 
procedures for installing the secondary retention device on the PPC 
assembly and doing a visual inspection of the PPC lever for the 
applicable models.
    We also reviewed Honeywell International Inc. Service Bulletin 
TPE331-72-2190, dated December 21, 2011, that describes procedures for 
replacing or reworking the propeller pitch control assembly, 
incorporating a threaded hole in the splined end of the shouldered 
shaft, and reassembling the propeller pitch control assembly.
    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 of this 
document.

Costs of Compliance

    We estimate that this AD affects 360 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
----------------------------------------------------------------------------------------------------------------
Replacement or rework of the PPC   19 work-hours x $85   $1,000.................          $2,615        $941,400
 assembly.                          per hour = $1,615.
Install secondary retention        1 work-hour x $85     10.....................              95          34,200
 device.                            per hour = $85.
Visual inspection of PPC lever...  .5 work-hour x $85    Not applicable.........           42.50          15,300
                                    per hour = $42.50.
----------------------------------------------------------------------------------------------------------------

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

                                               On-Condition Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                     Cost per
                 Action                          Labor cost                  Parts cost               product
----------------------------------------------------------------------------------------------------------------
Correct attachment of the PPC lever....  .5 work-hour x $85 per     Not applicable..............          $42.50
                                          hour = $42.50.
----------------------------------------------------------------------------------------------------------------

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 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.

[[Page 15984]]

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):

2017-07-01 M7 Aerospace LLC: Amendment 39-18839; Docket No. FAA-
2016-9531; Directorate Identifier 2015-CE-011-AD.

(a) Effective Date

    This AD is effective May 5, 2017.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to M7 Aerospace LLC SA226-T, SA226-AT, 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 61, Propellers/Propulsors.

(e) Unsafe Condition

    This AD was prompted by detachment of the power lever linkage to 
the TPE331 engine propeller pitch control (PPC). We are issuing this 
AD to prevent detachment of the power lever linkage to the TPE331 
engine PPC, which could result in uncommanded change to the engine 
power settings with consequent loss of control.

(f) Compliance

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

(g) Applicable M7 Aerospace LLC Service Bulletins

    Use the applicable service bulletins as listed in paragraph 
(g)(1), (2), or (3) of this AD as reference to complete the actions 
in paragraph (i)(1) or (2) of this AD:
    (1) M7 Aerospace LLC SA226 Series Service Bulletin 226-76-012, 
dated March 17, 2015;
    (2) M7 Aerospace LLC SA227 Series Service Bulletin 227-76-007, 
dated March 17, 2015; or
    (3) M7Aerospace LLC SA227 Series Commuter Category Service 
Bulletin CC7-76-004, dated March 17, 2015.

(h) PPC Lever Installation

    (1) Within 100 hours time-in-service (TIS) after May 5, 2017 
(the effective date of this AD) and repetitively thereafter at 
intervals not to exceed 100 hours TIS, visually inspect the PPC 
lever to assure the attachment is properly installed following the 
applicable service information listed in paragraph (h)(1)(i), (ii), 
or (iii) of this AD, as applicable.
    (i) For Models SA226 Series: M7 Aerospace SA226 Series 
Maintenance Manual Temporary Revision 71-02, dated March 15, 2016.
    (ii) For Models SA227 Series: M7 Aerospace SA227 Series 
Maintenance Manual Temporary Revision 71-03, dated March 15, 2016.
    (iii) For Models SA227 Series Commuter Category: M7 Aerospace 
SA227 Series Commuter Category Maintenance Manual Temporary Revision 
71-02, dated March 15, 2016.
    (2) The rework/replacement required by paragraph (i) of the AD 
and the installation of the secondary retention device required in 
paragraph (j) of this AD terminate the repetitive visual inspections 
of the PPC lever attachment required by paragraph (h)(1) of this AD.

(i) Replace or Rework the Propeller Pitch Assembly

    Within the next 600 hours TIS after May 5, 2017 (the effective 
date of this AD) or within the next 12 months after May 5, 2017 (the 
effective date of this AD), whichever occurs first, do the actions 
in either paragraph (i)(1) or (2) of this AD following the 
Accomplishment Instructions in Honeywell International Inc. Service 
Bulletin TPE331-72-2190, dated December 21, 2011, as referenced in 
the applicable service information listed in paragraph (g)(1), (2), 
or (3) this AD.
    (1) Replace the PPC. Remove the PPC assembly and replace with 
the applicable new design PPC using the part numbers listed in table 
1 to paragraph (i)(1) of this AD.

   Table 1 to Paragraph (i)(1) of This AD--Part Number PPC Assemblies
------------------------------------------------------------------------
                                                           Part No. PPC
             Part No. PPC assembly to remove                assembly to
                                                              install
------------------------------------------------------------------------
869130-11...............................................     70000295-11
869130-12...............................................     70000295-12
869130-13...............................................     70000295-13
869130-14...............................................     70000295-14
869130-16...............................................     70000295-16
869130-17...............................................     70000295-17
869130-18...............................................     70000295-18
869130-19...............................................     70000295-19
869130-30...............................................     70000295-30
895481-1................................................      70000298-1
895481-2................................................      70000298-2
895481-4................................................      70000298-4
895481-5................................................      70000298-5
895481-6................................................      70000298-6
895481-7................................................      70000298-7
895481-17...............................................     70000298-17
895481-18...............................................     70000298-18
895481-19...............................................     70000298-19
895481-20...............................................     70000298-20
895481-22...............................................     70000298-22
------------------------------------------------------------------------

    (2) Rework the PPC assembly. Inspect the splined end of the 
shouldered shaft for the presence and good condition of a threaded 
hole, repairing or replacing the cam assembly, and reworking the PPC 
assembly as necessary.

(j) Secondary Retention Feature

    (1) Before further flight after the replacement or rework of the 
PPC assembly required in paragraph (i)(1) or (2) of this AD, install 
the secondary retention feature on the PPC assembly following the 
applicable service information listed in paragraph (j)(1)(i), (ii), 
or (iii) of this AD.
    (i) For Models SA226 Series: M7 Aerospace SA226 Series 
Maintenance Manual Temporary Revision 71-02, dated March 15, 2016.
    (ii) For Models SA227 Series: M7 Aerospace SA227 Series 
Maintenance Manual Temporary Revision 71-03, dated March 15, 2016.
    (iii) For Models SA227 Series Commuter Category: M7 Aerospace 
SA227 Series Commuter Category Maintenance Manual Temporary Revision 
71-02, dated March 15, 2016.
    (2) The rework/replacement required by paragraph (i) of this AD 
and the installation of the secondary retention device required by 
paragraph (j) of this AD terminate the requirement for the 
repetitive inspections of the PPC lever torque required in paragraph 
(h) of this AD.

(k) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, Fort Worth Airplane Certification Office (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, mail it to the 
attention of one of the people identified in paragraph (l), Related 
Information, of this AD or email the request to [email protected].
    (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 one of the following 
people:
    (1) Justin Carter, ASW-142, Aerospace Engineer, Fort Worth 
Airplane Certification Office (ACO), FAA, 10101 Hillwood Parkway, 
Fort Worth, Texas 76177-1524; telephone: (817) 222-5146; fax: (817) 
222-5960; email: [email protected]; or
    (2) Kristin Bradley, ASW-143, Aerospace Engineer, Fort Worth 
ACO, FAA, 10101 Hillwood Parkway, Fort Worth, Texas 76177-1524; 
telephone: (817) 222-5485; fax: (817) 222-5960; 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.

[[Page 15985]]

    (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 SA226 Series Service Bulletin 226-76-012, 
dated March 17, 2015.
    (ii) M7 Aerospace LLC SA227 Series Service Bulletin 227-76-007, 
dated March 17, 2015.
    (iii) M7Aerospace LLC SA227 Series Commuter Category Service 
Bulletin CC7-76-004, dated March 17, 2015.
    (iv) M7 Aerospace SA226 Series Maintenance Manual Temporary 
Revision 71-02, dated March 15, 2016.
    (v) M7 Aerospace SA227 Series Maintenance Manual Temporary 
Revision 71-03, dated March 15, 2016.
    (vi) M7 Aerospace SA227 Series Commuter Category Maintenance 
Manual Temporary Revision 71-02, dated March 15, 2016.
    (vii) Honeywell International Inc. Service Bulletin TPE331-72-
2190, dated December 21, 2011.
    (3) 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: [email protected]; or 
Honeywell International Inc. 111 S. 34th Street, Phoenix, Arizona 
85034-2802; phone: (855) 808-6500; email: 
[email protected]; Internet: https://aerospace.honeywell.com/en/services/maintenance-and-monitoring.
    (4) You may view this service information at 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 March 17, 2017.
William Schinstock,
Acting Manager, Small Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2017-05857 Filed 3-30-17; 8:45 am]
 BILLING CODE 4910-13-P