Airworthiness Directives; Slingsby Aviation Ltd. Airplanes, 30136-30138 [2015-12448]

Download as PDF mstockstill on DSK4VPTVN1PROD with RULES 30136 Federal Register / Vol. 80, No. 101 / Wednesday, May 27, 2015 / Rules and Regulations ‘‘Adequate awareness’’ means warning information must be provided to alert the crew of unsafe operating conditions and to enable them to take appropriate corrective action. (c) The static directional stability (as shown by the tendency to recover from a skid with the rudder free) must be positive for any landing gear and flap position and symmetrical power condition, at speeds from 1.13 VSR1, up to VFE, VLE, or VFC/MFC (as appropriate). (d) The static lateral stability (as shown by the tendency to raise the low wing in a sideslip with the aileron controls free), for any landing-gear and wing-flap position and symmetricpower condition, may not be negative at any airspeed (except that speeds higher than VFE need not be considered for wing-flaps-extended configurations nor speeds higher than VLE for landing-gearextended configurations) in the following airspeed ranges: (i) From 1.13 VSR1 to VMO/MMO. (ii) From VMO/MMO to VFC/MFC, unless the divergence is— (1) Gradual; (2) Easily recognizable by the pilot; and (3) Easily controllable by the pilot. (e) In straight, steady sideslips over the range of sideslip angles appropriate to the operation of the airplane, but not less than those obtained with one half of the available rudder control movement (but not exceeding a rudder control force of 180 pounds), rudder control movements and forces must be substantially proportional to the angle of sideslip in a stable sense; and the factor of proportionality must lie between limits found necessary for safe operation. This requirement must be met for the configurations and speeds specified in paragraph (c) of this section. (f) For sideslip angles greater than those prescribed by paragraph (e) of this section, up to the angle at which full rudder control is used or a rudder control force of 180 pounds is obtained, the rudder control forces may not reverse, and increased rudder deflection must be needed for increased angles of sideslip. Compliance with this requirement must be shown using straight, steady sideslips, unless full lateral control input is achieved before reaching either full rudder control input or a rudder control force of 180 pounds; a straight, steady sideslip need not be maintained after achieving full lateral control input. This requirement must be met at all approved landing gear and wing-flap positions for the range of operating speeds and power conditions appropriate to each landing gear and VerDate Sep<11>2014 17:50 May 26, 2015 Jkt 235001 wing-flap position with all engines operating. Issued in Renton, Washington, on May 15, 2015. Michael Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2015–12699 Filed 5–26–15; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2015–1737; Directorate Identifier 2015–CE–014–AD; Amendment 39–18164; AD 2015–11–01] RIN 2120–AA64 Airworthiness Directives; Slingsby Aviation Ltd. Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Final rule; request for comments. AGENCY: We are adopting a new airworthiness directive (AD) for Slingsby Aviation Ltd. Models T67M260 and T67M260–T3A airplanes. This AD results from mandatory continuing airworthiness information (MCAI) issued by the aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as failure of a brake master cylinder pivot pin. We are issuing this AD to require actions to address the unsafe condition on these products. DATES: This AD is effective June 16, 2015. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of June 16, 2015. We must receive comments on this AD by July 13, 2015. ADDRESSES: You may send comments 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: U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC 20590, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. SUMMARY: PO 00000 Frm 00008 Fmt 4700 Sfmt 4700 For service information identified in this AD, contact Marshall Aerospace and Defence Group, The Airport, Newmarket Road, Cambridge, CB5 8RX, UK; telephone: +44 (0) 1223 399856; fax: +44 (0) 7825365617; email: mark.bright@marshalladg.com; Internet: www.marshalladg.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 http:// www.regulations.gov by searching for locating Docket No. FAA–2015–1737. 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– 1737; 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 street address for the Docket Office (telephone (800) 647– 5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: Jim Rutherford, Aerospace Engineer, FAA, Small Airplane Directorate, 901 Locust, Room 301, Kansas City, Missouri 64106; telephone: (816) 329–4165; fax: (816) 329–4090; email: jim.rutherford@ faa.gov. SUPPLEMENTARY INFORMATION: Discussion The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Community, has issued AD No.: 2015– 0065–E, dated April 24, 2015, to correct an unsafe condition for the specified products. The MCAI states: An occurrence was reported where pivot pin Part Number (P/N) T67M–45–539, of rudder pedal assembly #4, installed on the right hand (RH) side of the aeroplane (RH seat, RH pedal) failed during taxi. This caused the rudder pedal mechanism to detach from the brake master cylinder. This condition, if not detected and corrected, could cause the rudder linkages to rotate out of their normal orientation, possibly resulting in jammed rudder controls and consequent loss of control of the aeroplane. To address this potential unsafe condition, Slingsby Advanced Composites Ltd, trading as Marshall Aerospace and Defence Group (hereafter called ‘Marshall’ in this AD) issued Service Bulletin (SB) SBM200 to provide inspection instructions. E:\FR\FM\27MYR1.SGM 27MYR1 Federal Register / Vol. 80, No. 101 / Wednesday, May 27, 2015 / Rules and Regulations For the reason described above, this AD requires repetitive inspections of the brake master cylinder pivot pins of rudder pedal assemblies #1 and #4 and, depending on findings, replacement of the affected pivot pins(s). You may examine the MCAI on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA–2015–1737. Relevant Service Information Under 1 CFR Part 51 Marshall Aerospace and Defence Group Service Bulletin SBM 200, Revision 1, dated April 2015. The transmittal letter for Marshall Aerospace and Defence Group SBM 200, Revision 1, incorrectly states it transmits the Initial Issue; page 1 of this service bulletin is dated April 2015; pages 2 through 8 are dated March 2015. The actions described in this service information are intended to correct the unsafe condition identified in the MCAI. The service bulletin describes procedures for inspecting the brake master cylinder pivot pins, part number (P/N) T67M–45–539, that are installed on rudder pedal assemblies #1 and #4 for cracks and distortion and replacing any damaged pivot pins. 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 AD. mstockstill on DSK4VPTVN1PROD with RULES FAA’s Determination and Requirements of the AD This product has been approved by the aviation authority of another country, and is approved for operation in the United States. Pursuant to our bilateral agreement with this State of Design Authority, they have notified us of the unsafe condition described in the MCAI and service information referenced above. We are issuing this AD because we evaluated all information provided by the State of Design Authority and determined the unsafe condition exists and is likely to exist or develop on other products of the same type design. FAA’s Determination of the Effective Date An unsafe condition exists that requires the immediate adoption of this AD. The FAA has found that the risk to the flying public justifies waiving notice and comment prior to adoption of this rule because failure of a brake master cylinder pivot pin could cause the rudder pedal mechanism to detach from the brake master cylinder, which could result in jammed rudder controls and consequent loss of control. Therefore, VerDate Sep<11>2014 17:50 May 26, 2015 Jkt 235001 we determined that notice and opportunity for public comment before issuing this AD are impracticable and that good cause exists for making this amendment effective in fewer than 30 days. Comments Invited This AD is a final rule that involves requirements affecting flight safety, and we did not precede it by notice and opportunity for public comment. We invite you to send any written relevant data, views, or arguments about this AD. Send your comments to an address listed under the ADDRESSES section. Include ‘‘Docket No. FAA–2015–1737; Directorate Identifier 2015–CE–014– AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this AD. We will consider all comments received by the closing date and may amend this 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 AD. Costs of Compliance We estimate that this AD will affect 2 products of U.S. registry. We also estimate that it will take about 6 workhours per product to comply with the basic requirements of this AD. The average labor rate is $85 per work-hour. Required parts would cost about $50 per product. Based on these figures, we estimate the cost of the AD on U.S. operators to be $1,120, or $560 per product. In addition, we estimate that any necessary follow-on actions will take about .5 work-hours and require parts costing $100, for a cost of $142.50 per product. We have no way of determining the number of products that may need these actions. 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 PO 00000 Frm 00009 Fmt 4700 Sfmt 4700 30137 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 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 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. 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 AD: ■ 2015–11–01 Slingsby Aviation Ltd.: Amendment 39–18164; Docket No. FAA–2015–1737; Directorate Identifier 2015–CE–014–AD. (a) Effective Date This airworthiness directive (AD) becomes effective June 16, 2015. (b) Affected ADs None. E:\FR\FM\27MYR1.SGM 27MYR1 30138 Federal Register / Vol. 80, No. 101 / Wednesday, May 27, 2015 / Rules and Regulations (c) Applicability This AD applies to Slingsby Aviation Ltd. Models T67M260 and T67M260–T3A airplanes, all serial numbers, certificated in any category. (d) Subject Air Transport Association of America (ATA) Code 27: Flight Controls. (e) Reason This AD was prompted by mandatory continuing airworthiness information (MCAI) issued by the aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as failure of a brake master cylinder pivot pin. We are issuing this AD to prevent failure of a brake master cylinder pivot pin, which could cause the rudder pedal mechanism to detach from the brake master cylinder. This failure could result in jammed rudder controls and consequent loss of control. mstockstill on DSK4VPTVN1PROD with RULES (f) Actions and Compliance Unless already done, do the actions in paragraphs (f)(1) and (f)(2) of this AD. (1) Before further flight after June 16, 2015 (the effective date of this AD) and repetitively thereafter every 300 hours time-in-service or 12 months, whichever occurs first, inspect the brake master cylinder pivot pins, part number T67M–45–539, installed on rudder pedal assemblies #1 and #4. Do the inspections following the Accomplishment Instructions in Marshall Aerospace and Defence Group Service Bulletin SBM 200, Revision 1, dated April 2015. This AD does not require the retention and reporting requirements of paragraph (2) of F. COMPLETION in the Accomplishment Instructions of this service bulletin. (2) If, during any inspection required in paragraph (f)(1) of this AD, any crack or distortion to a brake master cylinder pivot pin is found, or a pivot pin fails the dimensional check, before further flight, replace the affected pivot pin with a serviceable part. Do the replacement as specified in paragraph C.(1)(j) of the Inspection section of the Accomplishment Instructions in Marshall Aerospace and Defence Group Service Bulletin SBM 200, Revision 1, dated April 2015. After doing this replacement, continue with the repetitive inspection requirement in paragraph (f)(1) of this AD. (g) Other FAA AD Provisions The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, Standards Office, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. Send information to ATTN: Jim Rutherford, Aerospace Engineer, FAA, Small Airplane Directorate, 901 Locust, Room 301, Kansas City, Missouri 64106; telephone: (816) 329–4165; fax: (816) 329– 4090; email: jim.rutherford@faa.gov. Before using any approved AMOC on any airplane to which the AMOC applies, notify your appropriate principal inspector (PI) in the FAA Flight Standards District Office (FSDO), or lacking a PI, your local FSDO. VerDate Sep<11>2014 17:50 May 26, 2015 Jkt 235001 (2) Airworthy Product: For any requirement in this AD to obtain corrective actions from a manufacturer or other source, use these actions if they are FAA-approved. Corrective actions are considered FAAapproved if they are approved by the State of Design Authority (or their delegated agent). You are required to assure the product is airworthy before it is returned to service. DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2009–1100; Directorate Identifier 2009–NE–37–AD; Amendment 39– 18159; AD 2015–10–04] RIN 2120–AA64 (h) Related Information Refer to MCAI European Aviation Safety Agency (EASA) AD No.: 2015–0065–E, dated April 24, 2015, for related information. You may examine the MCAI on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA–2015–1737. Airworthiness Directives; International Aero Engines AG Turbofan Engines (i) Material Incorporated by Reference SUMMARY: (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) Marshall Aerospace and Defence Group Service Bulletin SBM 200, Revision 1, dated April 2015. Note 1 to paragraph (i)(2)(i): The transmittal letter for Marshall Aerospace and Defence Group SBM 200, Revision 1, dated April 2015, incorrectly states it transmits the Initial Issue; page 1 is dated April 2015; pages 2 through 8 are dated March 2015. (ii) Reserved. (3) For Slingsby Aviation Ltd. service information identified in this AD, contact Marshall Aerospace and Defence Group, The Airport, Newmarket Road, Cambridge, CB5 8RX, UK; telephone: +44 (0) 1223 399856; fax: +44 (0) 7825365617; email: mark.bright@ marshalladg.com; Internet: www.marshalladg.com. (4) You may view this 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 locating Docket No. FAA–2015–1737. (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/ibrlocations.html. Issued in Kansas City, Missouri, on May 18, 2015. Earl Lawrence, Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. 2015–12448 Filed 5–26–15; 8:45 am] BILLING CODE 4910–13–P PO 00000 Frm 00010 Fmt 4700 Sfmt 4700 Federal Aviation Administration (FAA), DOT. ACTION: Final rule. AGENCY: We are superseding Airworthiness Directive (AD) 2012–09– 09 for all International Aero Engines AG (IAE) V2500–A1, V2525–D5, and V2528–D5 turbofan engines, and certain serial numbers (S/Ns) of IAE V2522–A5, V2524–A5, V2527–A5, V2527E–A5, V2527M–A5, V2530–A5, and V2533–A5 turbofan engines. AD 2012–09–09 required cleaning, eddy current inspection (ECI) or fluorescent penetrant inspection (FPI), and initial and repetitive ultrasonic inspections (USIs) of certain high-pressure compressor (HPC) stage 3 to 8 drums, as well as replacement of the drum attachment nuts. This new AD expands the affected population for initial and repetitive USIs of the HPC stage 3 to 8 drum, revises the inspection intervals, requires performing ECI or FPI, requires removal of the affected attachment nuts and any HPC stage 3 to 8 drum found cracked, and adds a mandatory terminating action. This AD was prompted by the discovery that additional attachment nuts for certain HPC stage 3 to 8 drums are affected. We are issuing this AD to prevent failure of the HPC stage 3 to 8 drum, which could result in uncontained drum failure, damage to the engine, and damage to the airplane. DATES: This AD is effective July 1, 2015. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of July 1, 2015. ADDRESSES: For service information identified in this AD, contact International Aero Engines AG, 400 Main Street, East Hartford, CT 06118; phone: 860–368–3700; fax: 860–368– 4600; email: iaeinfo@iaev2500.com; Internet: https://www.iaeworld.com. You may view this service information at the FAA, Engine & Propeller Directorate, 12 New England Executive Park, Burlington, MA. For information on the availability of this material at the FAA, call 781–238–7125. It is also available on the Internet at http:// E:\FR\FM\27MYR1.SGM 27MYR1

Agencies

[Federal Register Volume 80, Number 101 (Wednesday, May 27, 2015)]
[Rules and Regulations]
[Pages 30136-30138]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2015-12448]


-----------------------------------------------------------------------

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2015-1737; Directorate Identifier 2015-CE-014-AD; 
Amendment 39-18164; AD 2015-11-01]
RIN 2120-AA64


Airworthiness Directives; Slingsby Aviation Ltd. Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule; request for comments.

-----------------------------------------------------------------------

SUMMARY: We are adopting a new airworthiness directive (AD) for 
Slingsby Aviation Ltd. Models T67M260 and T67M260-T3A airplanes. This 
AD results from mandatory continuing airworthiness information (MCAI) 
issued by the aviation authority of another country to identify and 
correct an unsafe condition on an aviation product. The MCAI describes 
the unsafe condition as failure of a brake master cylinder pivot pin. 
We are issuing this AD to require actions to address the unsafe 
condition on these products.

DATES: This AD is effective June 16, 2015.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of June 16, 
2015.
    We must receive comments on this AD by July 13, 2015.

ADDRESSES: You may send comments 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: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE., Washington, DC 20590, between 9 a.m. and 5 p.m., 
Monday through Friday, except Federal holidays.
    For service information identified in this AD, contact Marshall 
Aerospace and Defence Group, The Airport, Newmarket Road, Cambridge, 
CB5 8RX, UK; telephone: +44 (0) 1223 399856; fax: +44 (0) 7825365617; 
email: mark.bright@marshalladg.com; Internet: www.marshalladg.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 http://www.regulations.gov by 
searching for locating Docket No. FAA-2015-1737.

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-
1737; 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 street address for the Docket Office (telephone 
(800) 647-5527) is in the ADDRESSES section. Comments will be available 
in the AD docket shortly after receipt.

FOR FURTHER INFORMATION CONTACT: Jim Rutherford, Aerospace Engineer, 
FAA, Small Airplane Directorate, 901 Locust, Room 301, Kansas City, 
Missouri 64106; telephone: (816) 329-4165; fax: (816) 329-4090; email: 
jim.rutherford@faa.gov.

SUPPLEMENTARY INFORMATION:

Discussion

    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Community, has issued AD 
No.: 2015-0065-E, dated April 24, 2015, to correct an unsafe condition 
for the specified products. The MCAI states:

    An occurrence was reported where pivot pin Part Number (P/N) 
T67M-45-539, of rudder pedal assembly #4, installed on the right 
hand (RH) side of the aeroplane (RH seat, RH pedal) failed during 
taxi. This caused the rudder pedal mechanism to detach from the 
brake master cylinder.
    This condition, if not detected and corrected, could cause the 
rudder linkages to rotate out of their normal orientation, possibly 
resulting in jammed rudder controls and consequent loss of control 
of the aeroplane.
    To address this potential unsafe condition, Slingsby Advanced 
Composites Ltd, trading as Marshall Aerospace and Defence Group 
(hereafter called `Marshall' in this AD) issued Service Bulletin 
(SB) SBM200 to provide inspection instructions.

[[Page 30137]]

    For the reason described above, this AD requires repetitive 
inspections of the brake master cylinder pivot pins of rudder pedal 
assemblies #1 and #4 and, depending on findings, replacement of the 
affected pivot pins(s).

You may examine the MCAI on the Internet at http://www.regulations.gov 
by searching for and locating Docket No. FAA-2015-1737.

Relevant Service Information Under 1 CFR Part 51

    Marshall Aerospace and Defence Group Service Bulletin SBM 200, 
Revision 1, dated April 2015. The transmittal letter for Marshall 
Aerospace and Defence Group SBM 200, Revision 1, incorrectly states it 
transmits the Initial Issue; page 1 of this service bulletin is dated 
April 2015; pages 2 through 8 are dated March 2015. The actions 
described in this service information are intended to correct the 
unsafe condition identified in the MCAI. The service bulletin describes 
procedures for inspecting the brake master cylinder pivot pins, part 
number (P/N) T67M-45-539, that are installed on rudder pedal assemblies 
#1 and #4 for cracks and distortion and replacing any damaged pivot 
pins. 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 
AD.

FAA's Determination and Requirements of the AD

    This product has been approved by the aviation authority of another 
country, and is approved for operation in the United States. Pursuant 
to our bilateral agreement with this State of Design Authority, they 
have notified us of the unsafe condition described in the MCAI and 
service information referenced above. We are issuing this AD because we 
evaluated all information provided by the State of Design Authority and 
determined the unsafe condition exists and is likely to exist or 
develop on other products of the same type design.

FAA's Determination of the Effective Date

    An unsafe condition exists that requires the immediate adoption of 
this AD. The FAA has found that the risk to the flying public justifies 
waiving notice and comment prior to adoption of this rule because 
failure of a brake master cylinder pivot pin could cause the rudder 
pedal mechanism to detach from the brake master cylinder, which could 
result in jammed rudder controls and consequent loss of control. 
Therefore, we determined that notice and opportunity for public comment 
before issuing this AD are impracticable and that good cause exists for 
making this amendment effective in fewer than 30 days.

Comments Invited

    This AD is a final rule that involves requirements affecting flight 
safety, and we did not precede it by notice and opportunity for public 
comment. We invite you to send any written relevant data, views, or 
arguments about this AD. Send your comments to an address listed under 
the ADDRESSES section. Include ``Docket No. FAA-2015-1737; Directorate 
Identifier 2015-CE-014-AD'' at the beginning of your comments. We 
specifically invite comments on the overall regulatory, economic, 
environmental, and energy aspects of this AD. We will consider all 
comments received by the closing date and may amend this 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 AD.

Costs of Compliance

    We estimate that this AD will affect 2 products of U.S. registry. 
We also estimate that it will take about 6 work-hours per product to 
comply with the basic requirements of this AD. The average labor rate 
is $85 per work-hour. Required parts would cost about $50 per product.
    Based on these figures, we estimate the cost of the AD on U.S. 
operators to be $1,120, or $560 per product.
    In addition, we estimate that any necessary follow-on actions will 
take about .5 work-hours and require parts costing $100, for a cost of 
$142.50 per product. We have no way of determining the number of 
products that may need these actions.

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 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 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.

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 AD:

2015-11-01 Slingsby Aviation Ltd.: Amendment 39-18164; Docket No. 
FAA-2015-1737; Directorate Identifier 2015-CE-014-AD.

(a) Effective Date

    This airworthiness directive (AD) becomes effective June 16, 
2015.

(b) Affected ADs

    None.

[[Page 30138]]

(c) Applicability

    This AD applies to Slingsby Aviation Ltd. Models T67M260 and 
T67M260-T3A airplanes, all serial numbers, certificated in any 
category.

(d) Subject

    Air Transport Association of America (ATA) Code 27: Flight 
Controls.

(e) Reason

    This AD was prompted by mandatory continuing airworthiness 
information (MCAI) issued by the aviation authority of another 
country to identify and correct an unsafe condition on an aviation 
product. The MCAI describes the unsafe condition as failure of a 
brake master cylinder pivot pin. We are issuing this AD to prevent 
failure of a brake master cylinder pivot pin, which could cause the 
rudder pedal mechanism to detach from the brake master cylinder. 
This failure could result in jammed rudder controls and consequent 
loss of control.

 (f) Actions and Compliance

    Unless already done, do the actions in paragraphs (f)(1) and 
(f)(2) of this AD.
    (1) Before further flight after June 16, 2015 (the effective 
date of this AD) and repetitively thereafter every 300 hours time-
in-service or 12 months, whichever occurs first, inspect the brake 
master cylinder pivot pins, part number T67M-45-539, installed on 
rudder pedal assemblies #1 and #4. Do the inspections following the 
Accomplishment Instructions in Marshall Aerospace and Defence Group 
Service Bulletin SBM 200, Revision 1, dated April 2015. This AD does 
not require the retention and reporting requirements of paragraph 
(2) of F. COMPLETION in the Accomplishment Instructions of this 
service bulletin.
    (2) If, during any inspection required in paragraph (f)(1) of 
this AD, any crack or distortion to a brake master cylinder pivot 
pin is found, or a pivot pin fails the dimensional check, before 
further flight, replace the affected pivot pin with a serviceable 
part. Do the replacement as specified in paragraph C.(1)(j) of the 
Inspection section of the Accomplishment Instructions in Marshall 
Aerospace and Defence Group Service Bulletin SBM 200, Revision 1, 
dated April 2015. After doing this replacement, continue with the 
repetitive inspection requirement in paragraph (f)(1) of this AD.

(g) Other FAA AD Provisions

    The following provisions also apply to this AD:
    (1) Alternative Methods of Compliance (AMOCs): The Manager, 
Standards Office, FAA, has the authority to approve AMOCs for this 
AD, if requested using the procedures found in 14 CFR 39.19. Send 
information to ATTN: Jim Rutherford, Aerospace Engineer, FAA, Small 
Airplane Directorate, 901 Locust, Room 301, Kansas City, Missouri 
64106; telephone: (816) 329-4165; fax: (816) 329-4090; email: 
jim.rutherford@faa.gov. Before using any approved AMOC on any 
airplane to which the AMOC applies, notify your appropriate 
principal inspector (PI) in the FAA Flight Standards District Office 
(FSDO), or lacking a PI, your local FSDO.
    (2) Airworthy Product: For any requirement in this AD to obtain 
corrective actions from a manufacturer or other source, use these 
actions if they are FAA-approved. Corrective actions are considered 
FAA-approved if they are approved by the State of Design Authority 
(or their delegated agent). You are required to assure the product 
is airworthy before it is returned to service.

 (h) Related Information

    Refer to MCAI European Aviation Safety Agency (EASA) AD No.: 
2015-0065-E, dated April 24, 2015, for related information. You may 
examine the MCAI on the Internet at http://www.regulations.gov by 
searching for and locating Docket No. FAA-2015-1737.

(i) 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) Marshall Aerospace and Defence Group Service Bulletin SBM 
200, Revision 1, dated April 2015.
    Note 1 to paragraph (i)(2)(i): The transmittal letter for 
Marshall Aerospace and Defence Group SBM 200, Revision 1, dated 
April 2015, incorrectly states it transmits the Initial Issue; page 
1 is dated April 2015; pages 2 through 8 are dated March 2015.
    (ii) Reserved.
    (3) For Slingsby Aviation Ltd. service information identified in 
this AD, contact Marshall Aerospace and Defence Group, The Airport, 
Newmarket Road, Cambridge, CB5 8RX, UK; telephone: +44 (0) 1223 
399856; fax: +44 (0) 7825365617; email: mark.bright@marshalladg.com; 
Internet: www.marshalladg.com.
    (4) You may view this 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 locating Docket No. FAA-2015-
1737.
    (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 May 18, 2015.
Earl Lawrence,
Manager, Small Airplane Directorate, Aircraft Certification Service.
[FR Doc. 2015-12448 Filed 5-26-15; 8:45 am]
 BILLING CODE 4910-13-P