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[Federal Register Volume 80, Number 164 (Tuesday, August 25, 2015)]
[Proposed Rules]
[Pages 51495-51498]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2015-20977]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2015-3607; Directorate Identifier 2015-CE-010-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 all 
M7 Aerospace LLC Models SA26-AT, SA226-T, SA226-AT, SA226-T(B), SA226-
TC, SA227-AT, SA227-TT, SA227-AC (C-26A), SA227-BC (C-26A), SA227-CC, 
and SA227-DC (C-26B) airplanes. This proposed AD was prompted by 
information that the airplane flight manual (AFM) does not provide 
adequate guidance in the handling of engine failures, which may lead to 
reliance on the negative torque system (NTS) for reducing drag. This 
condition could lead the pilot to not fully feather the propeller with 
consequent loss of control. This proposed AD would require inserting 
updates into the airplane flight manual (AFM) and/or the pilot 
operating handbook (POH) that will clearly establish that the NTS is 
not designed to automatically feather the propeller but only to provide 
drag protection. We are proposing this AD to correct the unsafe 
condition on these products.

DATES: We must receive comments on this proposed AD by October 9, 2015.

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-2015-
3607; 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: Michael Heusser, Aerospace Engineer, 
FAA, Fort Worth Aircraft Certification Office, 2601 Meacham Blvd., Fort 
Worth, Texas 76137; telephone: (817) 222-5038; fax: (817) 222-5960; 
email: Michael.A.Heusser@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-2015-3607; 
Directorate Identifier 2015-CE-010-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

    The FAA received a report of an accident where an M7 Aerospace LLC 
Model SA227-AC airplane experienced left engine power loss and 
consequent loss of control. Training manuals provide descriptions of 
the negative torque system (NTS), which provides partial anti-drag 
protection if a negative torque condition is sensed. This feature might 
cause pilots to assume the system automatically provides full anti-drag 
protection in the event of an engine failure or power loss. The pilot 
must also take prompt action to fully feather the propeller on the 
failed engine to reduce drag. A pilot's sole reliance on the NTS for 
reducing drag in the event of engine power loss may result in the 
pilot's failure to initiate the Engine Failure Inflight checklist and 
feather the propellers in time.
    This condition, if not corrected, could result in loss of control 
of the aircraft due to excessive asymmetric drag.

Related Service Information Under 1 CFR Part 51

    We reviewed the following M7 Aerospace LLC AFM revisions:
     AFM revision dated May 14, 2015, section III, SA26-AT Dash 
One;
     AFM revision dated May 14, 2015, section III, SA26-AT Dash 
Two;
     AFM revision B-33, sections i and III, SA226-AT, dated 
November 14, 2014;
     AFM revision A-29, sections i and III, SA226-T, dated 
November 14, 2014;
     AFM revision B-29, sections i and 3, SA226-T(B), dated 
November 14, 2014;
     AFM revision A-43, sections i and III, SA226-TC, dated 
November 14, 2014;

[[Page 51496]]

     AFM (4AC) revision B-11, sections 0 and 3, SA227-AC, dated 
November 14, 2014;
     AFM (4MC) revision A-12, sections 0 and 3, SA227-AC, dated 
November 14, 2014;
     AFM (6AC) revision A-16, sections 0 and 3, SA227-AC, dated 
November 14, 2014;
     AFM (7AC) revision B-19, sections 0 and 3, SA227-AC, dated 
November 14, 2014;
     AFM (7MC) revision A-13, sections 0 and 3, SA227-AC, dated 
November 14, 2014;
     AFM (8AC) revision A-15, sections 0 and 3, SA227-AC, dated 
November 14, 2014;
     Pilot operating handbook (POH)/AFM (4AT) revision A-12, 
sections 0 and 3, SA227-AT, dated November 14, 2014;
     POH/AFM (6AT) revision 13, sections 0 and 3, SA227-AT, 
dated November 14, 2014;
     POH/AFM (6AT), section 7, revision 7, SA227-AT, dated 
November 14, 2014;
     POH/AFM (7AT) revision B-12, sections 0 and 3, SA227-AT, 
dated November 14, 2014;
     POH/AFM (8AT) revision 13, sections 0 and 3, SA227-AT, 
dated November 14, 2014;
     AFM (6BC) revision 21, sections 0 and 3, SA227-BC, dated 
November 14, 2014;
     AFM (6CC) revision 17, sections 0 and 3, SA227-CC, dated 
November 14, 2014;
     AFM (6DC) revision 34, sections 0 and 3, SA227-DC, dated 
November 14, 2014;
     AFM (8DC) revision 8, sections 0 and 3, SA227-DC, dated 
November 14, 2014;
     POH/AFM revision 15, sections 0 and 3, SA227-TT Fairchild 
300, dated November 14, 2014;
     POH/AFM revision 13, sections 0 and 3, SA227-TT Fairchild 
312, dated November 14, 2014;
     POH/AFM revision 29, sections 0 and 3, SA227-TT, dated 
November 14, 2014.
    The M7 Aerospace LP service information describes procedures for 
inflight engine shutdown procedures. 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.
    In addition, minimum controllable airspeed for single engine 
landing is being investigated for possible future action.

Proposed AD Requirements

    This proposed AD would require updates be inserted into the AFM 
that will clearly establish that the NTS is not designed to 
automatically feather the propeller but only to provide drag 
protection.
    The proposed requirements do not address anything on the above-
referenced minimum controllable airspeed for single engine landing.

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
----------------------------------------------------------------------------------------------------------------
                                                                                    Cost per       Cost on U.S.
              Action                     Labor cost            Parts cost           product         operators
----------------------------------------------------------------------------------------------------------------
Insert revision into the            .5 work-hour x $85    Not applicable......          $42.50         $15,300.
 appropriate AFM describing action   per hour = $42.50.
 to take when feathering
 propellers in the event of engine
 failure.
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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 LP: Docket No. FAA-2015-3607; Directorate 
Identifier 2015-CE-010-AD.

[[Page 51497]]

(a) Comments Due Date

    We must receive comments by October 9, 2015.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to M7 Aerospace LLC Models SA26-AT, SA226-T, 
SA226-AT, SA226-T(B), SA226-TC, SA227-AT, SA227-TT, SA227-AC (C-
26A), SA227-BC (C-26A), SA227-CC, and SA227-DC (C-26B) airplanes, 
all serial numbers, certificated in any category.

(d) Subject

    Air Transport Association of America (ATA) Code 01, Operations 
Information.

(e) Unsafe Condition

    This AD was prompted by information that a pilot's sole reliance 
on the NTS for reducing drag in the event of engine power loss may 
result in the pilot's failure to initiate the Engine Failure 
Inflight checklist and feather the propellers in time. This could 
lead the pilot to not fully feather the propeller with consequent 
loss of control. We are issuing this AD to add information to the 
AFM and/or POH that reliance on the NTS to reduce drag during an 
engine failure could lead the pilot to not fully feather the 
propeller with consequent loss of control.

(f) Compliance

    Comply with this AD within 30 days after the effective date of 
this AD, unless already done.

(g) Actions

    Incorporate the applicable M7 Aerospace LLC AFM revisions as 
listed in paragraphs (g)(1) through (g)(12) of this AD:
    (1) For Model SA26-AT Dash One airplanes: Insert pages III-1 
through III-6, revised May 14, 2015; and pages III-7 through III-8, 
FAA Approved May 14, 2015; into the Merlin Model SA-26AT Dash One 
AFM.
    (2) For Model SA26-AT Dash Two airplanes: Insert pages III-1 
through III-6, revised May 14, 2015; and pages III-7 through III-8, 
FAA Approved May 14, 2015; into the Merlin Model SA-26AT Dash Two 
AFM.
    (3) For Model SA226-T airplanes: Insert pages III-2 though III-
26, revised November 14, 2014, into the Swearingen Merlin SA226-T 
AFM, Reissue A, dated June 28, 1976.
    (4) For Model SA226-AT airplanes: Insert pages III-2 through 
III-30, revised November 14, 2014, into the Merlin SA226-AT AFM, 
Reissue B, dated May 6, 1977.
    (5) For Model SA226-T(B) airplanes: Insert pages 3-2, Emergency 
Procedures, through page 3-20, Emergency Procedures, revised 
November 14, 2014; and pages 3-21 through 3-24, Emergency 
Procedures, issued November 14, 2014; into the Merlin SA226-T(B) 
AFM, Reissue B, dated November 2, 1979.
    (6) For Model SA226-TC airplanes: Insert pages III-2 through 
page III-24, revised November 24, 2014; and pages III-25 through 
III-32, FAA Approved November 14, 2014; into the Metro SA226-TC AFM, 
Reissue A, dated December 1, 1976.
    (7) For Model SA227-AT airplanes:
    (i) Model 4AT: Insert pages 3-4 through 3-30, Emergency 
Procedures, revised November 14, 2014; and pages 3-31 through 3-34, 
Emergency Procedures, FAA Approved November 14, 2014; into the 
SA227-AT (4AT) pilot operating handbook (POH)/AFM, Reissue A, dated 
November 30, 1988;
    (ii) Model 6AT: Insert pages 3-4 through 3-36, FAA Approved, 
Emergency Procedures, revised November 14, 2014, into the SA227-AT 
(6AT) POH/AFM, dated May 13, 1987.
    (iii) Model 7AT: Insert pages 3-4 through 3-30, Emergency 
Procedures, revised December 9, 2014, and pages 3-31 through 3-34, 
FAA Approved December 9, 2014, into the SA227-AT (7AT) POH/AFM, 
Reissue B, dated November 30, 1988.
    (iv) Model 8AT: Insert pages 3-4 through 3-30, Emergency 
Procedures, revised December 9, 2014; and pages 3-31 through 3-34, 
FAA Approved December 9, 2014; into the SA227-AT (8AT) POH/AFM, 
dated May 13, 1987.
    (8) For Model SA227-TT Fairchild 300 airplanes: Insert page 3-3 
through 3-30, Emergency Procedures, revised December 9, 2014; and 
pages 3-31 through 3-34, Emergency Procedures, FAA Approved December 
9, 2014; into the SA227-TT Fairchild 300 POH/AFM, Reissue A, dated 
August 7, 1981.
    (9) For Model SA227-TT Fairchild 312 airplanes: Insert page 3-3, 
Emergency Procedures, revised December 9, 2014; pages 3-5 through 3-
30, Emergency Procedures, revised December 9, 2014; and pages 3-31 
through 3-32, Emergency Procedures, FAA Approved December 9, 2014; 
into the Model SA227-TT Fairchild 300 (312) 12,500 LBS POH/AFM, 
dated October 4, 1981.
    (10) For Model SA227-TT Fairchild Merlin IIIC airplanes: Insert 
pages 3-3 through 3-24, revised December 9, 2014, and pages 3-25 
through 3-32, issued December 9, 2014; into the SA227-TT Merlin IIIC 
POH/AFM, Reissue A, dated August 7, 1981.
    (11) For Model SA227-AC (4AC) airplanes: Insert pages 3-3 
through 3-30, Emergency Procedures, revised November 14, 2014; into 
the SA227-AC AFM, Reissue B, dated November 7, 1990.
    (12) For Model SA227-AC (4MC) airplanes: Insert pages 3-3 
through 3-30, Emergency Procedures, revised November 14, 2014; and 
pages 3-31 through 3-36, Emergency Procedures, FAA Approved November 
14, 2014, into the SA227-AC AFM, Reissue A, dated May 22, 1989.
    (13) For Model SA227-AC (7AC) airplanes: Insert pages 3-3 
through 3-30, Emergency Procedures, revised December 9, 2014; and 
pages 3-31 through 3-34, Emergency Procedures, FAA Approved December 
9, 2014, into the SA227-AC AFM, Reissue B, dated April 2, 1986.
    (14) For Model SA227-AC (7MC) airplanes: Insert pages 3-3 
through 3-30, Emergency Procedures, revised December 9, 2014; and 
pages 3-31 through 3-34, Emergency Procedures, FAA Approved December 
9, 2014, into the SA227-AC AFM, Reissue A, dated May 22, 1989.
    (15) For Model SA227-AC (8AC) airplanes: Insert pages 3-3 
through 3-30, Emergency Procedures, revised December 9, 2014; and 
pages 3-31 through 3-34, Emergency Procedures, FAA Approved December 
9, 2014, into the SA227-AC AFM, Reissue A, dated May 22, 1989
    (16) For Model SA227-AC (6AC) airplanes: Insert pages 3-3 
through 3-20, Emergency Procedures, revised November 14, 2014; into 
the SA227-AC AFM, Reissue A, dated May 22, 1989.
    (17) For Model SA227-AC (6BC) airplanes: Insert pages 3-3 
through 3-30, Emergency Procedures, revised November 14, 2014; and 
pages 3-31 through 3-36, Emergency Procedures, FAA Approved November 
14, 2014, into the SA227-BC AFM, dated September 25, 1989.
    (18) For Model SA227-DC (6DC) airplanes: Insert pages 3-3 
through 3-26, Emergency Procedures, revised December 9, 2014; and 
pages 3-27 through 3-32, Emergency Procedures, FAA Approved December 
9, 2014, into the SA227-DC AFM, dated August 23, 1991.
    (19) For Model SA227-BC (C-26A) airplanes: Insert pages 3-4 
through 3-30, Emergency Procedures, revised December 9, 2014; and 
pages 3-31 through 3-36, Emergency Procedures, FAA Approved December 
9, 2014; into the SA227-BC AFM, dated September 25, 1989.
    (20) For Model SA227-CC (6CC) airplanes: Insert pages 3-3 
through 3-24, Emergency Procedures, revised December 9, 2014; and 
pages 3-25 through 3-30, Emergency Procedures, FAA Approved December 
9, 2014; into the SA227-CC AFM, dated December 11, 1992.
    (21) For Model SA227-DC (8DC) airplanes: Insert pages 3-3 
through 3-26, Emergency Procedures, revised December 9, 2014; and 
pages 3-27 through 3-32, Emergency Procedures, FAA Approved December 
9, 2014; into the SA227-DC AFM.

(h) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, Fort Worth Aircraft 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)(1) 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.

(i) Related Information

    (1) For more information about this AD, contact Michael Heusser, 
Aerospace Engineer, FAA, Fort Worth Aircraft Certification Office, 
2601 Meacham Blvd., Fort Worth, Texas 76137; telephone: (817) 222-
5038; fax: (817) 222-5960; email: Michael.A.Heusser@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)

[[Page 51498]]

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 August 19, 2015.
Earl Lawrence,
Manager, Small Airplane Directorate, Aircraft Certification Service.
[FR Doc. 2015-20977 Filed 8-24-15; 8:45 am]
 BILLING CODE 4910-13-P
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