[Federal Register Volume 81, Number 249 (Wednesday, December 28, 2016)]
[Proposed Rules]
[Pages 95528-95531]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2016-30292]


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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]
RIN 2120-AA64


Airworthiness Directives; M7 Aerospace LLC Airplanes

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 
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 proposed AD was prompted by 
detachment of the power lever linkage to the TPE331 engine propeller 
pitch control. This proposed AD would require installing a secondary 
retention device and repetitively inspecting the propeller pitch 
control for proper torque, with corrections as necessary. We are 
proposing this AD to correct the unsafe condition on these products.

DATES: We must receive comments on this proposed AD by February 13, 
2017.

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.

[[Page 95529]]

     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 
information 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.

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 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 ONE OF THE FOLLOWING: 
     Justin Carter, ASW-142, Aerospace Engineer, Fort Worth 
Airplane Certification Office (ACO), FAA, 2601 Meacham Blvd., Fort 
Worth, Texas 76137-4298; telephone: (817) 222-5146; fax: (817) 222-
5960; email: [email protected]; or
     Kristin Bradley, ASW-143, Aerospace Engineer, Fort Worth 
ACO, FAA, 2601 Meacham Blvd., Fort Worth, Texas 76137-4298; telephone: 
(817) 222-5485; fax: (817) 222-5960; email: [email protected].

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-2016-9531; 
Directorate Identifier 2015-CE-011-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 the airplane power lever linkage detaching 
from the TPE331 engine propeller pitch control (PPC) shaft on M7 
Aircraft SA226 and SA227 airplanes. 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 
the TPE311 has been the subject of previous ADs on other airplane type 
designs. This condition, if not corrected, could result in uncommanded 
change to the engine power settings with consequent loss of control.

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 for the applicable models describes the 
actions that must be done to comply with this NPRM.
    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 in 
combination for the applicable models describes procedures for 
installing the secondary retention device on the PPC assembly and doing 
a visual inspection of the PPC lever.
    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 
NPRM.

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 the same type design.

Proposed AD Requirements

    This proposed AD would require replacement or rework of the PPC 
assembly to have a threaded hole in the splined end of the shouldered 
shaft, installation of a secondary retention feature for the airplane 
control linkage interface, and a repetitive inspection of the PPC lever 
torque with corrective action as necessary.

Costs of Compliance

    We estimate that this proposed AD affects 360 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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Replacement or rework of the PPC    19 work-hours x $85    $1,000...............          $2,615        $941,400
 assembly.                           per hour = 1,615.

[[Page 95530]]

 
Install secondary retention device  1 work-hour x $85 per  10...................              95          34,200
                                     hour = $85.
Visual inspection of propeller      .5 work-hour x $85     Not applicable.......           42.50          15,300
 pitch control lever.                per hour = $42.50.
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    We estimate the following costs to do any necessary adjustments 
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 adjustments:

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

    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-2016-9531; Directorate 
Identifier 2015-CE-011-AD.

(a) Comments Due Date

    We must receive comments by February 13, 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 propeller pitch control, 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 pargraph (h)(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 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: Pages TR-224 through TR-228 from M7 
Aerospace SA226 Series Maintenance Manual Temporary Revision 71-02, 
dated March 15, 2016.
    (ii) For Models SA227 Series: Pages 206 and 207 from M7 
Aerospace SA227 Series

[[Page 95531]]

Maintenance Manual Temporary Revision 71-03, dated March 15, 2016.
    (iii) For Models SA227 Series Commuter Category: Pages 206 and 
206A from M7 Aerospace SA227 Series Commuter Category Maintenance 
Manual Temporary Revision 71-02, dated March 15, 2016.
    (2) Installation of the secondary retention device required in 
paragraph (j) of this AD terminates the repetitive visual 
inspections of the PPC lever attachment required in paragraph (h)(1) 
of this AD.

(i) Replace or Rework the Propeller Pitch Assembly

    Within the next 600 hours TIS after the effective date of this 
AD or within the next 12 months after 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 assembly to
     Part No. PPC assembly to remove                  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) 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: Pages TR-224 through TR-228 from M7 
Aerospace SA226 Series Maintenance Manual Temporary Revision 71-02, 
dated March 15, 2016.
    (ii) For Models SA227 Series: Pages 206 and 207 from M7 
Aerospace SA227 Series Maintenance Manual Temporary Revision 71-03, 
dated March 15, 2016.
    (iii) For Models SA227 Series Commuter Category: Pages 206 and 
206A from M7 Aerospace SA227 Series Commuter Category Maintenance 
Manual Temporary Revision 71-02, dated March 15, 2016.
    (2) Installation of the secondary retention device terminates 
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, send it to the 
attention of the person identified in paragraph (l)(1), Related 
Information, 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

    (1) For more information about this AD, contact one of the 
following individuals:
    (i) Justin Carter, ASW-142, Aerospace Engineer, Fort Worth 
Airplane Certification Office (ACO), FAA, 2601 Meacham Blvd., Fort 
Worth, Texas 76137-4298; telephone: (817) 222-5146; fax: (817) 222-
5960; email: [email protected]; or
    (ii) Kristin Bradley, ASW-143, Aerospace Engineer, Fort Worth 
ACO, FAA, 2601 Meacham Blvd., Fort Worth, Texas 76137-4298; 
telephone: (817) 222-5485; fax: (817) 222-5960; email: 
[email protected].
    (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: [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.

    Issued in Kansas City, Missouri on December 8, 2016.
Pat Mullen,
Acting Manager, Small Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2016-30292 Filed 12-27-16; 8:45 am]
 BILLING CODE 4910-13-P