80 FR 58354 - Airworthiness Directives; M7 Aerospace LLC Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 80, Issue 188 (September 29, 2015)
Federal Aviation Administration
Federal Register Volume 80, Issue 188 (September 29, 2015)
| Page Range | 58354-58357 | |
| FR Document | 2015-24249 |
[Federal Register Volume 80, Number 188 (Tuesday, September 29, 2015)] [Rules and Regulations] [Pages 58354-58357] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2015-24249] ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2015-2207; Directorate Identifier 2015-CE-003-AD; Amendment 39-18272; AD 2015-19-10] RIN 2120-AA64 Airworthiness Directives; M7 Aerospace LLC Airplanes AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Final rule. ----------------------------------------------------------------------- SUMMARY: We are superseding Airworthiness Directive (AD) 97-02-02 for certain Models SA26-AT, SA26-T, 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. AD 97-02-02 required applying torque to the control column pitch bearing attaching nuts, inspecting the bearing assembly, inspecting the elevator control rod end bearing retainer/dust seals, and replacing or installing new parts as necessary. This new AD requires inspecting for movement and correct torque of the elevator control pivot bearing, inspecting the elevator control rod for damage and correct configuration, and replacing parts as necessary. This AD also requires a 10,000-hour time-in-service (TIS) repetitive replacement of the control column pivot bearing and elevator control rod bolt and requires replacement of the control column pivot bearing with the improved design by 35,000 hours TIS. This AD was prompted by loss of elevator control due to failure of the bolt attaching the elevator control rod to the elevator walking beam under the cockpit floor. We are issuing this AD to correct the unsafe condition on these products. DATES: This AD is effective November 3, 2015. The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of November 3, 2015. ADDRESSES: 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]. 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 Docket No. FAA-2015-2207. Examining the AD Docket You may examine the AD docket on the Internet at http://www.regulations.govby searching for and locating Docket No. FAA-2015- 2207; 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: 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: [email protected]. SUPPLEMENTARY INFORMATION: Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to supersede AD 97-02-02, Amendment 39-9886 (62 FR 2552, January 17, 1997), (``AD 97-02-02''). AD 97-02-02 applied to certain M7 Aerospace LLC Models SA26-AT, SA26-T, 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 June 16, 2015 (80 FR 34326). The NPRM was prompted by an operator experiencing complete loss of elevator control due to failure of the bolt attaching the elevator control rod to the elevator walking beam under the cockpit floor. A follow-on inspection of the operator's fleet revealed a variety of hardware installed. Some hardware matched the illustrated parts catalog (IPC), some matched the AD 97-02-02 configuration, and some matched neither of those configurations. When AD 97-02-02 was issued, the IPC was never revised to match the hardware configuration called out in AD 97-02-02 or in the service information associated with that AD. Because of the conflict between the AD and the IPC configurations, an airplane that was in compliance with the requirements of AD 97-02-02 could have had an incorrect hardware configuration installed during routine maintenance after complying with the AD. The IPC has been updated and corrected by M7 Aerospace, LLC. Also, since we issued AD 97-02-02, the manufacturer developed an improved design for the control column pivot bearing and support structure that terminates the repetitive torque check and replacement of control column pivot bearings. The manufacturer also issued new service information that adds the 10,000-hour TIS repetitive replacement of the control column pivot bearing that is in the airworthiness limitations section (ALS) of the airplane maintenance manual (AMM) and (if this revision is mandated) requires the replacement of the pivot bearing with the improved design by 35,000 hours TIS that is in the supplemental inspections document (SID). Issuance of [[Page 58355]] the new service information, the revised IPC, and this AD will eliminate the conflicts between AD 97-02-02, the service information, the IPC, the ALS, and the SID. The NPRM (80 FR 34326, June 16, 2015) proposed to require inspecting for movement and correct torque of the elevator control pivot bearing, inspecting the elevator control rod for damage and correct configuration, and replacing parts as necessary. The NPRM also proposed to require a 10,000-hour TIS repetitive replacement of the control column pivot bearing and elevator control rod bolt and require replacement of the control column pivot bearing with the improved design by 35,000 hours TIS. Replacing the original control column pivot bearing with the improved design terminates the requirement to repetitively replace the original control column pivot bearing every 10,000 hours. 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 (80 FR 34326, June 16, 2015) 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 (80 FR 34326, June 16, 2015) for correcting the unsafe condition; and Do not add any additional burden upon the public than was already proposed in the NPRM (80 FR 34326, June 16, 2015). Relevant Service Information Under 1 CFR 51 We reviewed M7 Aerospace SA26 Series Service Bulletin No. 26-27-30- 046 R2, dated December 5, 2014; Fairchild Aircraft SA26 Series Service Bulletin No. 26-27-30-047, dated June 16, 1997; M7 Aerospace SA226 Series Service Bulletin No. 226-27-060 R2, dated December 5, 2014; Fairchild Aerospace SA226 Series Service Bulletin No. 226-27-061, dated June 16, 1997; M7 Aerospace SA227 Series Service Bulletin, No. 227-27- 041 R2, dated December 5, 2014; Fairchild Aircraft SA227 Series Service Bulletin No. 227-27-042, dated June 16, 1997; M7 Aerospace LLC SA227 Series Commuter Category Service Bulletin No. CC7-27-010 R2, dated December 5, 2014; and Fairchild Aircraft SA227 Series Commuter Category Service Bulletin No. CC7-27-011, dated June 16, 1997. The service information describes procedures for inspecting for movement and correct torque of the elevator control pivot bearing, inspecting the elevator control rod for damage, and replacing parts as necessary. The service information also adds a repetitive replacement of the control column pivot bearings at 10,000 hours TIS and requires replacement of the control column pivot bearing with the improved design within 35,000 hours TIS. This 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 AD. 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 ---------------------------------------------------------------------------------------------------------------- Inspection of torque on the 2 work-hours x $85 Not applicable......... $170 $61,200 control column pivot bearing. per hour = $170. Control column pivot bearing 8 work-hours x $85 $300................... 980 352,800 replacement. per hour = $680. New designed control column pivot 20 work-hours x $85 $2,450................. 4,150 1,494,000 bearing replacement. per hour = $1,700. Elevator rod end bolt replacement 4 work-hours x $85 $10.................... 350 126,000 per hour = $340. ---------------------------------------------------------------------------------------------------------------- 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 have determined that 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. 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. [[Page 58356]] Sec. 39.13 [Amended] 0 2. The FAA amends Sec. 39.13 by removing Airworthiness Directive (AD) 97-02-02, Amendment 39-9886 (62 FR 2552, January 17, 1997), and adding the following new AD: 2015-19-10 M7 Aerospace: Amendment 39-18272; Docket No. FAA-2015- 2207; Directorate Identifier 2015-CE-003-AD. (a) Effective Date This AD is effective November 3, 2015. (b) Affected ADs This AD supersedes AD 97-02-02, Amendment 39-9886 (62 FR 2552, January 17, 1997). (c) Applicability This AD applies to M7 Aerospace LLC Models SA26-AT, SA26-T, 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), SA227-TT, all serial numbers, certificated in any category. (d) Subject Joint Aircraft System Component (JASC)/Air Transport Association (ATA) of America Code 27, Flight Controls. (e) Unsafe Condition AD 97-02-02 (62 FR 2552, January 17, 1997) (``AD 97-02-02'') resulted from reports of Fairchild SA227 series airplanes losing pitch control in-flight. This supersedure was prompted by an operator experiencing complete loss of elevator control because of failure of the bolt attaching the elevator control rod to the elevator walking beam under the cockpit floor. We are issuing this AD to prevent loss of pitch control, which if not corrected, could result in loss of airplane control. (f) Compliance Comply with this AD within the compliance times specified, unless already done. Models SA227-CC and SA227-DC, serial numbers 892, 893, and 895 and up, have the revised (modified) configuration. Since those airplanes are already in compliance, they do not have to do the actions in paragraphs (h) or (i) of this AD, including all subparagraphs. Those airplanes must still do the actions required in paragraph (j) of this AD, including all subparagraphs. (g) Credit for Actions Accomplished in Accordance With Previous Service Information This AD allows credit for the control column pivot bearing torque check and initial replacement required in paragraph (i)(2) of this AD and the elevator rod bolt inspection and initial replacement required in paragraphs (j)(1) and (j)(3)(i) of this AD, if done before November 3, 2015 (the effective date of this AD), following the procedures specified in the Accomplishment Instructions of the applicable service information listed in paragraphs (g)(1) through (g)(4) of this AD: (1) M7 Aerospace SA227 Commuter Category Service Bulletin No. CC7-27-010, original issue or revision 1. (2) M7 Aerospace SA227 Series Service Bulletin No. 227-27-041, original issue or revision 1. (3) M7 Aerospace SA226 Series Service Bulletin No. 226-27-060, original issue or revision 1. (4) M7 Aerospace SA26 Series Service Bulletin No. 26-27-30-046, original issue or revision 1. (h) Control Column Pivot Bearing Revised (Modified) Configuration (1) On or before the airplane accumulates a total of 35,000 hours time-in-service (TIS) or within the next 1,000 hours TIS after November 3, 2015 (the effective date of this AD), whichever occurs later, you must revise (modify) the control column pivot bearing configuration with the improved design. Use the applicable service information listed in paragraphs (h)(1)(i) through (h)(1)(iv) of this AD. Revising (modifying) the configuration of the control column pivot bearing with the improved design terminates the actions for paragraph (i) of this AD, including all subparagraphs, but you must still complete the required actions in paragraph (j) of this AD, including all subparagraphs. (i) Fairchild Aircraft SA26 Series Service Bulletin No. 26-27- 30-047, dated June 16, 1997; (ii) Fairchild Aircraft SA226 Series Service Bulletin No. 226- 27-061, dated June 16, 1997; (iii) Fairchild Aircraft SA227 Series Service Bulletin No. 227- 27-042, dated June 16, 1997; or (iv) Fairchild Aircraft SA227 Series Commuter Category No. CC7- 27-011, dated June 16, 1997. (2) You may at any time before 35,000 hours TIS revise (modify) the control column pivot bearing configuration with the improved design to terminate the repetitive replacement of the original control column pivot bearing using the applicable service information listed in paragraphs (h)(1)(i) through (h)(1)(iv) of this AD. This action terminates the requirements of paragraph (i) of this AD, including all subparagraphs, but you must still complete the required actions in paragraph (j) of this AD, including all subparagraphs. (i) Torque Check or Replacement of the Control Column Pivot Bearing (1) Use the service information, as applicable, listed in paragraphs (i)(1)(i) through (i)(1)(iv) of this AD to do a control column pivot bearing torque check or replacement at the applicable compliance times in paragraph (i)(2) or (i)(3) of this AD, including all subparagraphs: (i) M7 Aerospace LLC SA26 Series Service Bulletin No. 26-27-30- 046 R2, dated December 5, 2014; (ii) M7 Aerospace LLC SA226 Series Service Bulletin No. 226-27- 060 R2, dated December 5, 2014; (iii) M7 Aerospace LLC SA227 Series Service Bulletin No. 227-27- 041 R2, dated December 5, 2014; or (iv) M7 Aerospace LLC SA227 Series Commuter Category Service Bulletin No. CC7-27-010 R2, December 5, 2014. (2) For airplanes where the control column pivot bearing has been torque checked or replaced within the last 10,000 hours TIS before November 3, 2015 (the effective date of this AD) using the applicable service information listed in paragraph (g)(1) through (g)(4) or (i)(1)(i) through (i)(1)(iv) of this AD, do one of the following actions: (i) Within the next 10,000 hours TIS after the last control column pivot bearing replacement or within the next 1,000 hours TIS after November 3, 2015 (the effective date of this AD), whichever occurs later, and repetitively thereafter every 10,000 hours TIS, replace the control column pivot bearing following paragraph 2.B. of the Accomplishment Instructions of the applicable service information listed in paragraphs (i)(1)(i) through (i)(1)(iv) of this AD; or (ii) Within the next 10,000 hours TIS after the last control column pivot bearing replacement or within the next 1,000 hours TIS after November 3, 2015 (the effective date of this AD), whichever occurs later, revise (modify) the control column pivot bearing configuration with the improved design using the applicable service information listed in paragraphs (h)(1)(i) through (h)(1)(iv) of this AD. Revising (modifying) the configuration of the control column pivot bearing with the improved design terminates the repetitive replacement of the original control column pivot bearing. No other actions are required for paragraph (i) of this AD, including all subparagraphs, but you must still complete the actions in paragraph (j) of this AD, including all subparagraphs. (3) For airplanes where the control column pivot bearing has not been torque checked or replaced within the last 10,000 hours TIS before November 3, 2015 (the effective date of this AD) using the applicable service information listed in paragraphs (g)(1) through (g)(4) or (i)(1)(i) through (i)(1)(iv) of this AD, within the next 200 hours TIS after November 3, 2015 (the effective date of this AD), torque check the control column pivot bearing following paragraph 2.A. of the service information listed in paragraphs (i)(1)(i) through (i)(1)(iv) of this AD. (4) If nut movement occurs during the torque check required in paragraph (i)(3) of this AD, do one of the following actions: (i) Before further flight and repetitively thereafter at intervals not to exceed every 10,000 hours TIS, replace the control column pivot bearing following paragraph 2.B. of the Accomplishment Instructions of the applicable service information listed in paragraphs (i)(1)(i) through (i)(1)(iv) of this AD; or (ii) Before further flight, revise (modify) the control column pivot bearing configuration with the improved design using the applicable service information listed in paragraphs (h)(1)(i) through (h)(1)(iv) of this AD. Revising (modifying) the configuration of the control column pivot bearing with the improved design terminates the repetitive replacement of the original control column pivot bearing. No other actions are required for paragraph (i) of this AD, including all [[Page 58357]] subparagraphs, but you must still complete the actions in paragraph (j) of this AD, including all subparagraphs. (5) If no nut movement occurs during the torque check required in paragraph (i)(3) of this AD, do one of the following actions: (i) Within the next 1,000 hours TIS after November 3, 2015 (the effective date of this AD), replace the control column pivot bearing following paragraph 2.B. of the Accomplishment Instructions of the applicable service information listed in paragraphs (i)(1)(i) through (i)(1)(iv) of this AD; or (ii) Within the next 1,000 hours TIS after November 3, 2015 (the effective date of this AD), revise (modify) the control column pivot bearing configuration with the improved design using the applicable service information listed in paragraphs (h)(1)(i) through (h)(1)(iv) of this AD. Revising (modifying) the configuration of the control column pivot bearing with the improved design terminates the repetitive replacement of the original control column pivot bearing. (j) Inspect the Elevator Control Rod Ends and Hardware (1) Within the next 200 hours TIS after November 3, 2015 (the effective date of this AD), inspect the elevator control rod ends and hardware for wear, creasing, or other damage and verify the elevator rod bolt and attachment hardware for correct configuration following paragraph 2.D. of the Accomplishment Instructions of the applicable service information listed in paragraphs (i)(1)(i) through (i)(1)(iv) of this AD. (2) If any damage is found during the inspection required in paragraph (j)(1) of this AD or the elevator rod bolt and attachment hardware does not match the correct configuration, before further flight, replace the elevator rod bolt, rod ends, and associated hardware following paragraph 2.D. of the Accomplishment Instructions of the applicable service information listed in paragraphs (i)(1)(i) through (i)(1)(iv) of this AD. (3) Replace the elevator rod end bolt and associated hardware following paragraph 2.D. of the Accomplishment Instructions of the applicable service information listed in paragraphs (i)(1)(i) through (i)(1)(iv) of this AD at whichever of the following compliance times applies and repetitively thereafter at intervals not to exceed 10,000 hours TIS: (i) For airplanes where the elevator rod bolt has been replaced: Within the next 10,000 hours TIS after the last elevator rod bolt replacement or within the next 1,000 hours TIS after November 3, 2015 (the effective date of this AD), whichever occurs later; or (ii) For airplanes where the elevator rod bolt has never been replaced: Within the next 200 hours TIS after November 3, 2015 (the effective date of this AD). (k) 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 (l)(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. (l) Related Information (1) 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: [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. (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 SA26 Series Service Bulletin No. 26-27-30- 046 R2, dated December 5, 2014. (ii) M7 Aerospace LLC SA226 Series Service Bulletin No. 226-27- 060 R2, dated December 5, 2014. (iii) M7 Aerospace LLC SA227 Series Service Bulletin No. 227-27- 041 R2, dated December 5, 2014. (iv) M7 Aerospace LLC SA227 Series Commuter Category Service Bulletin No. CC7-27-010 R2, December 5, 2014. (v) Fairchild Aircraft SA26 Series Service Bulletin No. 26-27- 30-047, dated June 16, 1997. (vi) Fairchild Aircraft SA226 Series Service Bulletin No. 226- 27-061, dated June 16, 1997. (vii) Fairchild Aircraft SA227 Series Service Bulletin No. 227- 27-042, dated June 16, 1997. (viii) Fairchild Aircraft SA227 Series Commuter Category No. CC7-27-011, dated June 16, 1997. (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]. (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 September 17, 2015. Melvin Johnson, Acting Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. 2015-24249 Filed 9-28-15; 8:45 am] BILLING CODE 4910-13-P
![58354 Federal Register / Vol. 80, No. 188 / Tuesday, September 29, 2015 / Rules and Regulations
14 CFR part 91, subpart K, we suggest that column pitch bearing attaching nuts, FOR FURTHER INFORMATION CONTACT:
you notify your principal inspector, or inspecting the bearing assembly, Andrew McAnaul, Aerospace Engineer,
lacking a principal inspector, the manager of inspecting the elevator control rod end FAA, ASW–143 (c/o San Antonio
the local flight standards district office or bearing retainer/dust seals, and MIDO), 10100 Reunion Place, Suite 650,
certificate holding district office before
operating any aircraft complying with this
replacing or installing new parts as San Antonio, Texas 78216; phone: (210)
AD through an AMOC. necessary. This new AD requires 308–3365; fax: (210) 308–3370; email:
inspecting for movement and correct andrew.mcanaul@faa.gov.
(h) Additional Information torque of the elevator control pivot SUPPLEMENTARY INFORMATION:
(1) Airbus Helicopters Alert Service bearing, inspecting the elevator control
Bulletin No. ASB BO105–10–125, Revision 3, Discussion
rod for damage and correct
dated May 27, 2014, and Eurocopter Service configuration, and replacing parts as We issued a notice of proposed
Bulletin B0105–10–126, Revision 1, dated necessary. This AD also requires a rulemaking (NPRM) to amend 14 CFR
August 6, 2013, which are not incorporated part 39 to supersede AD 97–02–02,
by reference, contain additional information
10,000-hour time-in-service (TIS)
repetitive replacement of the control Amendment 39–9886 (62 FR 2552,
about the subject of this AD. For service
information identified in this AD, contact column pivot bearing and elevator January 17, 1997), (‘‘AD 97–02–02’’). AD
Airbus Helicopters, 2701 N. Forum Drive, control rod bolt and requires 97–02–02 applied to certain M7
Grand Prairie, TX 75052; telephone (972) replacement of the control column pivot Aerospace LLC Models SA26–AT,
641–0000 or (800) 232–0323; fax (972) 641– bearing with the improved design by SA26–T, SA226–AT, SA226–T, SA226–
3775; or at http:// 35,000 hours TIS. This AD was T(B), SA226–TC, SA227–AC (C–26A),
www.airbushelicopters.com/techpub.You prompted by loss of elevator control due SA227–AT, SA227–BC (C–26A),
may review a copy of the service information to failure of the bolt attaching the SA227–CC, SA227–DC (C–26B), and
at the FAA, Office of the Regional Counsel, SA227–TT airplanes. The NPRM
Southwest Region, 10101 Hillwood Pkwy.,
elevator control rod to the elevator
walking beam under the cockpit floor. published in the Federal Register on
Room 6N–321, Fort Worth, Texas 76177.
We are issuing this AD to correct the June 16, 2015 (80 FR 34326). The NPRM
(2) The subject of this AD is addressed in
European Aviation Safety Agency (EASA) AD unsafe condition on these products. was prompted by an operator
2014–0230, dated October 21, 2014. You may experiencing complete loss of elevator
DATES: This AD is effective November 3,
view the EASA AD on the Internet at http:// control due to failure of the bolt
2015.
www.regulations.gov by searching for and attaching the elevator control rod to the
The Director of the Federal Register
locating Docket No. FAA–2012–0503. elevator walking beam under the
approved the incorporation by reference
cockpit floor. A follow-on inspection of
(i) Subject of certain publications listed in this AD
the operator’s fleet revealed a variety of
Joint Aircraft Service Component (JASC) as of November 3, 2015.
hardware installed. Some hardware
Code: 6320 Main Gear Box. ADDRESSES: For service information matched the illustrated parts catalog
Issued in Fort Worth, Texas, on September identified in this AD, contact M7 (IPC), some matched the AD 97–02–02
17, 2015. Aerospace LLC, 10823 NE Entrance configuration, and some matched
James A. Grigg, Road, San Antonio, Texas 78216; phone: neither of those configurations.
Acting Manager, Rotorcraft Directorate, (210) 824–9421; fax: (210) 804–7766; When AD 97–02–02 was issued, the
Aircraft Certification Service. Internet: http://www.elbitsystems- IPC was never revised to match the
[FR Doc. 2015–24256 Filed 9–28–15; 8:45 am] us.com; email: MetroTech@ hardware configuration called out in AD
BILLING CODE 4910–13–P
M7Aerospace.com. You may view this 97–02–02 or in the service information
referenced service information at the associated with that AD. Because of the
FAA, Small Airplane Directorate, 901 conflict between the AD and the IPC
DEPARTMENT OF TRANSPORTATION Locust, Kansas City, Missouri 64106. configurations, an airplane that was in
For information on the availability of compliance with the requirements of
Federal Aviation Administration this material at the FAA, call 816–329– AD 97–02–02 could have had an
4148. It is also available on the Internet incorrect hardware configuration
14 CFR Part 39 at http://www.regulations.gov by installed during routine maintenance
searching for Docket No. FAA–2015– after complying with the AD. The IPC
[Docket No. FAA–2015–2207; Directorate
Identifier 2015–CE–003–AD; Amendment 2207. has been updated and corrected by M7
39–18272; AD 2015–19–10] Examining the AD Docket Aerospace, LLC.
Also, since we issued AD 97–02–02,
RIN 2120–AA64 You may examine the AD docket on the manufacturer developed an
the Internet at http:// improved design for the control column
Airworthiness Directives; M7 www.regulations.govby searching for pivot bearing and support structure that
Aerospace LLC Airplanes and locating Docket No. FAA–2015– terminates the repetitive torque check
AGENCY: Federal Aviation 2207; or in person at the Docket and replacement of control column
Administration (FAA), DOT. Management Facility between 9 a.m. pivot bearings.
ACTION: Final rule.
and 5 p.m., Monday through Friday, The manufacturer also issued new
except Federal holidays. The AD docket service information that adds the
SUMMARY: We are superseding contains this AD, the regulatory 10,000-hour TIS repetitive replacement
Airworthiness Directive (AD) 97–02–02 evaluation, any comments received, and of the control column pivot bearing that
asabaliauskas on DSK5VPTVN1PROD with RULES
for certain Models SA26–AT, SA26–T, other information. The address for the is in the airworthiness limitations
SA226–AT, SA226–T, SA226–T(B), Docket Office (phone: 800–647–5527) is section (ALS) of the airplane
SA226–TC, SA227–AC (C–26A), Document Management Facility, U.S. maintenance manual (AMM) and (if this
SA227–AT, SA227–BC (C–26A), Department of Transportation, Docket revision is mandated) requires the
SA227–CC, SA227–DC (C–26B), and Operations, M–30, West Building replacement of the pivot bearing with
SA227–TT airplanes. AD 97–02–02 Ground Floor, Room W12–140, 1200 the improved design by 35,000 hours
required applying torque to the control New Jersey Avenue SE., Washington, TIS that is in the supplemental
DC 20590. inspections document (SID). Issuance of
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![58356 Federal Register / Vol. 80, No. 188 / Tuesday, September 29, 2015 / Rules and Regulations
§ 39.13 [Amended] (1) M7 Aerospace SA227 Commuter (iv) M7 Aerospace LLC SA227 Series
Category Service Bulletin No. CC7–27–010, Commuter Category Service Bulletin No.
■ 2. The FAA amends § 39.13 by original issue or revision 1. CC7–27–010 R2, December 5, 2014.
removing Airworthiness Directive (AD) (2) M7 Aerospace SA227 Series Service (2) For airplanes where the control column
97–02–02, Amendment 39–9886 (62 FR Bulletin No. 227–27–041, original issue or pivot bearing has been torque checked or
2552, January 17, 1997), and adding the revision 1. replaced within the last 10,000 hours TIS
following new AD: (3) M7 Aerospace SA226 Series Service before November 3, 2015 (the effective date
Bulletin No. 226–27–060, original issue or of this AD) using the applicable service
2015–19–10 M7 Aerospace: Amendment information listed in paragraph (g)(1) through
39–18272; Docket No. FAA–2015–2207; revision 1.
(4) M7 Aerospace SA26 Series Service (g)(4) or (i)(1)(i) through (i)(1)(iv) of this AD,
Directorate Identifier 2015–CE–003–AD. do one of the following actions:
Bulletin No. 26–27–30–046, original issue or
(a) Effective Date revision 1. (i) Within the next 10,000 hours TIS after
the last control column pivot bearing
This AD is effective November 3, 2015. (h) Control Column Pivot Bearing Revised replacement or within the next 1,000 hours
(b) Affected ADs (Modified) Configuration TIS after November 3, 2015 (the effective date
(1) On or before the airplane accumulates of this AD), whichever occurs later, and
This AD supersedes AD 97–02–02,
a total of 35,000 hours time-in-service (TIS) repetitively thereafter every 10,000 hours
Amendment 39–9886 (62 FR 2552, January
or within the next 1,000 hours TIS after TIS, replace the control column pivot bearing
17, 1997). following paragraph 2.B. of the
November 3, 2015 (the effective date of this
(c) Applicability Accomplishment Instructions of the
AD), whichever occurs later, you must revise
applicable service information listed in
This AD applies to M7 Aerospace LLC (modify) the control column pivot bearing
paragraphs (i)(1)(i) through (i)(1)(iv) of this
Models SA26–AT, SA26–T, SA226–AT, configuration with the improved design. Use AD; or
SA226–T, SA226–T(B), SA226–TC, SA227– the applicable service information listed in (ii) Within the next 10,000 hours TIS after
AC (C–26A), SA227–AT, SA227–BC (C–26A), paragraphs (h)(1)(i) through (h)(1)(iv) of this the last control column pivot bearing
SA227–CC, SA227–DC (C–26B), SA227–TT, AD. Revising (modifying) the configuration of replacement or within the next 1,000 hours
all serial numbers, certificated in any the control column pivot bearing with the TIS after November 3, 2015 (the effective date
category. improved design terminates the actions for of this AD), whichever occurs later, revise
(d) Subject paragraph (i) of this AD, including all (modify) the control column pivot bearing
subparagraphs, but you must still complete configuration with the improved design
Joint Aircraft System Component (JASC)/ the required actions in paragraph (j) of this
Air Transport Association (ATA) of America using the applicable service information
AD, including all subparagraphs. listed in paragraphs (h)(1)(i) through
Code 27, Flight Controls. (i) Fairchild Aircraft SA26 Series Service (h)(1)(iv) of this AD. Revising (modifying) the
(e) Unsafe Condition Bulletin No. 26–27–30–047, dated June 16, configuration of the control column pivot
1997; bearing with the improved design terminates
AD 97–02–02 (62 FR 2552, January 17,
(ii) Fairchild Aircraft SA226 Series Service the repetitive replacement of the original
1997) (‘‘AD 97–02–02’’) resulted from reports
Bulletin No. 226–27–061, dated June 16, control column pivot bearing. No other
of Fairchild SA227 series airplanes losing
1997; actions are required for paragraph (i) of this
pitch control in-flight. This supersedure was
(iii) Fairchild Aircraft SA227 Series AD, including all subparagraphs, but you
prompted by an operator experiencing
Service Bulletin No. 227–27–042, dated June must still complete the actions in paragraph
complete loss of elevator control because of
16, 1997; or (j) of this AD, including all subparagraphs.
failure of the bolt attaching the elevator
(iv) Fairchild Aircraft SA227 Series (3) For airplanes where the control column
control rod to the elevator walking beam
Commuter Category No. CC7–27–011, dated pivot bearing has not been torque checked or
under the cockpit floor. We are issuing this
June 16, 1997. replaced within the last 10,000 hours TIS
AD to prevent loss of pitch control, which if
not corrected, could result in loss of airplane (2) You may at any time before 35,000 before November 3, 2015 (the effective date
control. hours TIS revise (modify) the control column of this AD) using the applicable service
pivot bearing configuration with the information listed in paragraphs (g)(1)
(f) Compliance improved design to terminate the repetitive through (g)(4) or (i)(1)(i) through (i)(1)(iv) of
Comply with this AD within the replacement of the original control column this AD, within the next 200 hours TIS after
compliance times specified, unless already pivot bearing using the applicable service November 3, 2015 (the effective date of this
done. Models SA227–CC and SA227–DC, information listed in paragraphs (h)(1)(i) AD), torque check the control column pivot
serial numbers 892, 893, and 895 and up, through (h)(1)(iv) of this AD. This action bearing following paragraph 2.A. of the
have the revised (modified) configuration. terminates the requirements of paragraph (i) service information listed in paragraphs
Since those airplanes are already in of this AD, including all subparagraphs, but (i)(1)(i) through (i)(1)(iv) of this AD.
compliance, they do not have to do the you must still complete the required actions (4) If nut movement occurs during the
actions in paragraphs (h) or (i) of this AD, in paragraph (j) of this AD, including all torque check required in paragraph (i)(3) of
including all subparagraphs. Those airplanes subparagraphs. this AD, do one of the following actions:
must still do the actions required in (i) Before further flight and repetitively
(i) Torque Check or Replacement of the
paragraph (j) of this AD, including all thereafter at intervals not to exceed every
Control Column Pivot Bearing
subparagraphs. 10,000 hours TIS, replace the control column
(1) Use the service information, as pivot bearing following paragraph 2.B. of the
(g) Credit for Actions Accomplished in applicable, listed in paragraphs (i)(1)(i) Accomplishment Instructions of the
Accordance With Previous Service through (i)(1)(iv) of this AD to do a control applicable service information listed in
Information column pivot bearing torque check or paragraphs (i)(1)(i) through (i)(1)(iv) of this
This AD allows credit for the control replacement at the applicable compliance AD; or
column pivot bearing torque check and times in paragraph (i)(2) or (i)(3) of this AD, (ii) Before further flight, revise (modify) the
initial replacement required in paragraph including all subparagraphs: control column pivot bearing configuration
asabaliauskas on DSK5VPTVN1PROD with RULES
(i)(2) of this AD and the elevator rod bolt (i) M7 Aerospace LLC SA26 Series Service with the improved design using the
inspection and initial replacement required Bulletin No. 26–27–30–046 R2, dated applicable service information listed in
in paragraphs (j)(1) and (j)(3)(i) of this AD, if December 5, 2014; paragraphs (h)(1)(i) through (h)(1)(iv) of this
done before November 3, 2015 (the effective (ii) M7 Aerospace LLC SA226 Series AD. Revising (modifying) the configuration of
date of this AD), following the procedures Service Bulletin No. 226–27–060 R2, dated the control column pivot bearing with the
specified in the Accomplishment December 5, 2014; improved design terminates the repetitive
Instructions of the applicable service (iii) M7 Aerospace LLC SA227 Series replacement of the original control column
information listed in paragraphs (g)(1) Service Bulletin No. 227–27–041 R2, dated pivot bearing. No other actions are required
through (g)(4) of this AD: December 5, 2014; or for paragraph (i) of this AD, including all
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![Federal Register / Vol. 80, No. 188 / Tuesday, September 29, 2015 / Rules and Regulations 58357
subparagraphs, but you must still complete request to your principal inspector or local Issued in Kansas City, Missouri, on
the actions in paragraph (j) of this AD, Flight Standards District Office, as September 17, 2015.
including all subparagraphs. appropriate. If sending information directly Melvin Johnson,
(5) If no nut movement occurs during the to the manager of the ACO, send it to the Acting Manager, Small Airplane Directorate,
torque check required in paragraph (i)(3) of attention of the person identified in Aircraft Certification Service.
this AD, do one of the following actions: paragraph (l)(1) of this AD.
(i) Within the next 1,000 hours TIS after [FR Doc. 2015–24249 Filed 9–28–15; 8:45 am]
(2) Before using any approved AMOC,
November 3, 2015 (the effective date of this notify your appropriate principal inspector, BILLING CODE 4910–13–P
AD), replace the control column pivot or lacking a principal inspector, the manager
bearing following paragraph 2.B. of the of the local flight standards district office/
Accomplishment Instructions of the certificate holding district office. DEPARTMENT OF TRANSPORTATION
applicable service information listed in
paragraphs (i)(1)(i) through (i)(1)(iv) of this (l) Related Information Federal Aviation Administration
AD; or (1) For more information about this AD,
(ii) Within the next 1,000 hours TIS after contact Andrew McAnaul, Aerospace 14 CFR Part 39
November 3, 2015 (the effective date of this Engineer, FAA, ASW–143 (c/o San Antonio
AD), revise (modify) the control column [Docket No. FAA–2014–0773; Directorate
MIDO), 10100 Reunion Place, Suite 650, San
pivot bearing configuration with the Identifier 2014–NM–068–AD; Amendment
Antonio, Texas 78216; phone: (210) 308–
improved design using the applicable service 39–18271; AD 2015–19–09]
3365; fax: (210) 308–3370; email:
information listed in paragraphs (h)(1)(i)
andrew.mcanaul@faa.gov. RIN 2120–AA64
through (h)(1)(iv) of this AD. Revising
(modifying) the configuration of the control (m) Material Incorporated by Reference
column pivot bearing with the improved
Airworthiness Directives; The Boeing
(1) The Director of the Federal Register Company Airplanes
design terminates the repetitive replacement
approved the incorporation by reference
of the original control column pivot bearing. AGENCY: Federal Aviation
(IBR) of the service information listed in this
(j) Inspect the Elevator Control Rod Ends paragraph under 5 U.S.C. 552(a) and 1 CFR Administration (FAA), DOT.
and Hardware part 51. ACTION: Final rule.
(1) Within the next 200 hours TIS after (2) You must use this service information
November 3, 2015 (the effective date of this as applicable to do the actions required by SUMMARY: We are adopting a new
AD), inspect the elevator control rod ends this AD, unless the AD specifies otherwise. airworthiness directive (AD) for all The
and hardware for wear, creasing, or other (i) M7 Aerospace LLC SA26 Series Service Boeing Company Model 787–8
damage and verify the elevator rod bolt and Bulletin No. 26–27–30–046 R2, dated airplanes. This AD was prompted by
attachment hardware for correct December 5, 2014. reports of a potential latent failure of the
configuration following paragraph 2.D. of the (ii) M7 Aerospace LLC SA226 Series
fuel shutoff valve actuator circuitry,
Accomplishment Instructions of the Service Bulletin No. 226–27–060 R2, dated
applicable service information listed in December 5, 2014.
which was not identified during
paragraphs (i)(1)(i) through (i)(1)(iv) of this (iii) M7 Aerospace LLC SA227 Series actuator development. This AD requires
AD. Service Bulletin No. 227–27–041 R2, dated replacing certain engine and auxiliary
(2) If any damage is found during the December 5, 2014. power unit (APU) fuel shutoff valve
inspection required in paragraph (j)(1) of this (iv) M7 Aerospace LLC SA227 Series actuators with new actuators, and also
AD or the elevator rod bolt and attachment Commuter Category Service Bulletin No. requires revising the maintenance or
hardware does not match the correct CC7–27–010 R2, December 5, 2014. inspection program to include a new
configuration, before further flight, replace (v) Fairchild Aircraft SA26 Series Service airworthiness limitation into the
the elevator rod bolt, rod ends, and Bulletin No. 26–27–30–047, dated June 16, Airworthiness Limitations Section
associated hardware following paragraph 2.D. 1997.
of the Accomplishment Instructions of the
(ALS) of the Instructions for Continued
(vi) Fairchild Aircraft SA226 Series Service Airworthiness (ICA). We are issuing this
applicable service information listed in Bulletin No. 226–27–061, dated June 16,
paragraphs (i)(1)(i) through (i)(1)(iv) of this AD to detect and correct latent failures
1997.
AD. (vii) Fairchild Aircraft SA227 Series
of the fuel shutoff valve to the engine
(3) Replace the elevator rod end bolt and Service Bulletin No. 227–27–042, dated June and auxiliary power unit (APU), which
associated hardware following paragraph 2.D. 16, 1997. could result in the inability to shut off
of the Accomplishment Instructions of the (viii) Fairchild Aircraft SA227 Series fuel to the engine and APU and, in case
applicable service information listed in Commuter Category No. CC7–27–011, dated of certain fires, an uncontrollable fire
paragraphs (i)(1)(i) through (i)(1)(iv) of this that could lead to structural failure.
June 16, 1997.
AD at whichever of the following compliance
(3) For service information identified in DATES: This AD is effective November 3,
times applies and repetitively thereafter at
this AD, contact M7 Aerospace LLC, 10823 2015.
intervals not to exceed 10,000 hours TIS:
NE Entrance Road, San Antonio, Texas
(i) For airplanes where the elevator rod bolt The Director of the Federal Register
78216; phone: (210) 824–9421; fax: (210)
has been replaced: Within the next 10,000 approved the incorporation by reference
hours TIS after the last elevator rod bolt 804–7766; Internet: http://www.elbitsystems-
us.com; email: MetroTech@ of a certain publication listed in this AD
replacement or within the next 1,000 hours as of November 3, 2015.
TIS after November 3, 2015 (the effective date M7Aerospace.com.
of this AD), whichever occurs later; or (4) You may view this service information ADDRESSES: For service information
(ii) For airplanes where the elevator rod at FAA, Small Airplane Directorate, 901 identified in this AD, contact Boeing
bolt has never been replaced: Within the next Locust, Kansas City, Missouri 64106. For Commercial Airplanes, Attention: Data
200 hours TIS after November 3, 2015 (the information on the availability of this & Services Management, P.O. Box 3707,
asabaliauskas on DSK5VPTVN1PROD with RULES
effective date of this AD). material at the FAA, call 816–329–4148. MC 2H–65, Seattle, WA 98124–2207;
(5) You may view this service information
(k) Alternative Methods of Compliance telephone 206–544–5000, extension 1;
that is incorporated by reference at the
(AMOCs) National Archives and Records
fax 206–766–5680; Internet https://
(1) The Manager, Fort Worth Airplane Administration (NARA). For information on www.myboeingfleet.com. You may view
Certification Office, FAA, has the authority to the availability of this material at NARA, call this referenced service information at
approve AMOCs for this AD, if requested 202–741–6030, or go to: http:// the FAA, Transport Airplane
using the procedures found in 14 CFR 39.19. www.archives.gov/federal-register/cfr/ibr- Directorate, 1601 Lind Avenue SW.,
In accordance with 14 CFR 39.19, send your locations.html. Renton, WA. For information on the
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Document Created: 2015-12-15 09:47:13
Document Modified: 2015-12-15 09:47:13
| Category | Regulatory Information | |
| Collection | Federal Register | |
| sudoc Class | AE 2.7: GS 4.107: AE 2.106: | |
| Publisher | Office of the Federal Register, National Archives and Records Administration | |
| Section | Rules and Regulations | |
| Action | Final rule. | |
| Dates | This AD is effective November 3, 2015. | |
| 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: [email protected] | |
| FR Citation | 80 FR 58354 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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