Airworthiness Directives; M7 Aerospace LLC, 88621-88623 [2016-29242]

Download as PDF Federal Register / Vol. 81, No. 236 / Thursday, December 8, 2016 / Rules and Regulations § 39.13 [Amended] 2. The FAA amends § 39.13 by adding the following new airworthiness directive (AD): ■ 2016–24–06 Bombardier, Inc.: Amendment 39–18723; Docket No. FAA–2016–7267; Directorate Identifier 2016–NM–015–AD. (a) Effective Date This AD is effective January 12, 2017. (b) Affected ADs None. (c) Applicability This AD applies to Bombardier, Inc. Model DHC–8–102, –103, –106, –201, –202, –301, –311, and –315 airplanes, certificated in any category, serial numbers 003 through 672 inclusive. (d) Subject Air Transport Association (ATA) of America Code 30, Ice and rain protection. (j) Related Information (e) Reason This AD was prompted by several occurrences of loss of airspeed data on both pilot and co-pilot air speed indicators due to the accumulation of ice on the pitot probes. An investigation revealed that the accumulation of ice was due to inoperative pitot probe heaters. We are issuing this AD to prevent circuit breakers from tripping and cutting power supply to the pitot probe heater, which could cause loss of airspeed data and result in the flight crew not being able to control the airspeed of the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Replacement Except as provided by paragraph (h) of this AD, within 5,000 flight hours or 60 months after the effective date of this AD, whichever occurs first: Replace the existing circuit breakers in both the left and right side of the pitot heater system with circuit breakers that have higher trip points, in accordance with the Accomplishment Instructions of Bombardier Service Bulletin 8–30–39, dated November 11, 2015 (for the right side), and Bombardier Service Bulletin 8–30–40, dated November 11, 2015 (for the left side). sradovich on DSK3GMQ082PROD with RULES (h) Airplanes That Meet the Requirements of Paragraph (g) of This AD For airplanes on which Bombardier ModSum IS8Q3000004 has been incorporated, no action is required by paragraph (g) of this AD. (i) Other FAA AD Provisions The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, New York Aircraft Certification Office (ACO), ANE–170, 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 VerDate Sep<11>2014 16:11 Dec 07, 2016 Jkt 241001 Office, as appropriate. If sending information directly to the New York ACO, send it to ATTN: Program Manager, Continuing Operational Safety, FAA, New York ACO, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; telephone: 516–228–7300; fax: 516–794–5531. 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. The AMOC approval letter must specifically reference this AD. (2) Contacting the Manufacturer: For any requirement in this AD to obtain corrective actions from a manufacturer, the action must be accomplished using a method approved by the Manager, New York ACO, ANE–170, FAA; or Transport Canada Civil Aviation (TCCA); or Bombardier, Inc.’s TCCA Design Approval Organization (DAO). If approved by the DAO, the approval must include the DAO-authorized signature. Refer to Mandatory Continuing Airworthiness Information (MCAI) Canadian AD CF–2016–04, dated February 1, 2016, for related information. This MCAI may be found in the AD docket on the Internet at https://www.regulations.gov by searching for and locating Docket No. FAA–2016–7267. (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 this AD specifies otherwise. (i) Bombardier Service Bulletin 8–30–39, dated November 11, 2015. (ii) Bombardier Service Bulletin 8–30–40, dated November 11, 2015. (3) For service information identified in this AD, contact Bombardier, Inc., Q-Series Technical Help Desk, 123 Garratt Boulevard, Toronto, Ontario M3K 1Y5, Canada; telephone: 416–375–4000; fax: 416–375– 4539; email: thd.qseries@ aero.bombardier.com; Internet: https:// www.bombardier.com. (4) You may view this service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425–227–1221. (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: https:// www.archives.gov/federal-register/cfr/ibrlocations.html. Issued in Renton, Washington, on November 16, 2016. Phil Forde, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2016–28602 Filed 12–7–16; 8:45 am] BILLING CODE 4910–13–P PO 00000 Frm 00007 Fmt 4700 Sfmt 4700 88621 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 Federal Aviation Administration (FAA), DOT. ACTION: Final rule. AGENCY: 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: https://www.elbitsystemsus.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 https://www.regulations.gov by searching for and locating Docket No. FAA–2016–9120. SUMMARY: Examining the AD Docket You may examine the AD docket on the Internet at https:// 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 E:\FR\FM\08DER1.SGM 08DER1 88622 Federal Register / Vol. 81, No. 236 / Thursday, December 8, 2016 / Rules and Regulations 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: 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. 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 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. Comments 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 product Action Labor cost Parts cost Inspect pitch trim actuator upper attach fittings. 16 work-hours × $85 per hour = $1,360 ... Not applicable ......... 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 $1,360 Cost on U.S. operators $408,000 determining the number of aircraft that might need these replacements: ON-CONDITION COSTS Action Labor cost Replace 2 fittings ............................. 8 work-hours × $85 per hour = $680 ........................................................ sradovich on DSK3GMQ082PROD with RULES 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 VerDate Sep<11>2014 16:11 Dec 07, 2016 Jkt 241001 Parts cost 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 PO 00000 Frm 00008 Fmt 4700 Sfmt 4700 $4,900 Cost per product $5,580 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 E:\FR\FM\08DER1.SGM 08DER1 Federal Register / Vol. 81, No. 236 / Thursday, December 8, 2016 / Rules and Regulations (g) Actions 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 1. The authority citation for part 39 continues to read as follows: ■ Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The FAA amends § 39.13 by adding the following new airworthiness directive (AD): (1) Within the next 600 hours time-inservice (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 2016–25–12 M7 Aerospace LLC: Amendment 39–18738; Docket No. FAA–2016–9120; Directorate Identifier 2016–CE–024–AD. 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. (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. sradovich on DSK3GMQ082PROD with RULES (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. VerDate Sep<11>2014 17:30 Dec 07, 2016 Jkt 241001 88623 (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: https:// 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: https:// www.archives.gov/federal-register/cfr/ibrlocations.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 DEPARTMENT OF TRANSPORTATION (i) Alternative Methods of Compliance (AMOCs) Federal Aviation Administration (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. 14 CFR Part 39 (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. PO 00000 Frm 00009 Fmt 4700 Sfmt 4700 [Docket No. FAA–2016–4224; Directorate Identifier 2015–NM–170–AD; Amendment 39–18720; AD 2016–24–03] RIN 2120–AA64 Airworthiness Directives; Bombardier, Inc. Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: We are adopting a new airworthiness directive (AD) for certain Bombardier, Inc. Model DHC–8–400 series airplanes. This AD was prompted by reports of cracked and corroded barrel nuts found at the mid-spar location of the horizontal-stabilizer-tovertical-stabilizer attachment joint. This AD requires repetitive detailed SUMMARY: E:\FR\FM\08DER1.SGM 08DER1

Agencies

[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: https://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 https://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 https://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: 
https://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: https://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