80_FR_30237 80 FR 30136 - Airworthiness Directives; Slingsby Aviation Ltd. Airplanes

80 FR 30136 - Airworthiness Directives; Slingsby Aviation Ltd. Airplanes

DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration

Federal Register Volume 80, Issue 101 (May 27, 2015)

Page Range30136-30138
FR Document2015-12448

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.

Federal Register, Volume 80 Issue 101 (Wednesday, May 27, 2015) 
[Federal Register Volume 80, Number 101 (Wednesday, May 27, 2015)]
[Rules and Regulations]
[Pages 30136-30138]
From the Federal Register Online  [www.thefederalregister.org]
[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: [email protected]; 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: 
[email protected].

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: 
[email protected]. 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: [email protected]; 
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

30136 Federal Register / Vol. 80, No. 101 / Wednesday, May 27, 2015 / Rules and Regulations ‘‘Adequate awareness’’ means warning wing-flap position with all engines For service information identified in information must be provided to alert operating. this AD, contact Marshall Aerospace the crew of unsafe operating conditions Issued in Renton, Washington, on May 15, and Defence Group, The Airport, and to enable them to take appropriate 2015. Newmarket Road, Cambridge, CB5 8RX, corrective action. Michael Kaszycki, UK; telephone: +44 (0) 1223 399856; (c) The static directional stability (as Acting Manager, Transport Airplane fax: +44 (0) 7825365617; email: shown by the tendency to recover from Directorate, Aircraft Certification Service. mark.bright@marshalladg.com; Internet: a skid with the rudder free) must be [FR Doc. 2015–12699 Filed 5–26–15; 8:45 am] www.marshalladg.com. You may view positive for any landing gear and flap BILLING CODE 4910–13–P this referenced service information at position and symmetrical power the FAA, Small Airplane Directorate, condition, at speeds from 1.13 VSR1, up 901 Locust, Kansas City, Missouri to VFE, VLE, or VFC/MFC (as appropriate). DEPARTMENT OF TRANSPORTATION 64106. For information on the (d) The static lateral stability (as availability of this material at the FAA, shown by the tendency to raise the low Federal Aviation Administration call (816) 329–4148. It is also available wing in a sideslip with the aileron on the Internet at http:// controls free), for any landing-gear and 14 CFR Part 39 www.regulations.gov by searching for wing-flap position and symmetric- [Docket No. FAA–2015–1737; Directorate locating Docket No. FAA–2015–1737. power condition, may not be negative at Identifier 2015–CE–014–AD; Amendment Examining the AD Docket any airspeed (except that speeds higher 39–18164; AD 2015–11–01] than VFE need not be considered for You may examine the AD docket on RIN 2120–AA64 the Internet at http:// wing-flaps-extended configurations nor speeds higher than VLE for landing-gear- www.regulations.gov by searching for Airworthiness Directives; Slingsby and locating Docket No. FAA–2015– extended configurations) in the Aviation Ltd. Airplanes following airspeed ranges: 1737; or in person at the Docket (i) From 1.13 VSR1 to VMO/MMO. AGENCY: Federal Aviation Management Facility between 9 a.m. (ii) From VMO/MMO to VFC/MFC, Administration (FAA), DOT. and 5 p.m., Monday through Friday, unless the divergence is— ACTION: Final rule; request for except Federal holidays. The AD docket (1) Gradual; comments. contains this AD, the regulatory (2) Easily recognizable by the pilot; evaluation, any comments received, and SUMMARY: We are adopting a new other information. The street address for and airworthiness directive (AD) for the Docket Office (telephone (800) 647– (3) Easily controllable by the pilot. Slingsby Aviation Ltd. Models T67M260 (e) In straight, steady sideslips over 5527) is in the ADDRESSES section. and T67M260–T3A airplanes. This AD Comments will be available in the AD the range of sideslip angles appropriate results from mandatory continuing to the operation of the airplane, but not docket shortly after receipt. airworthiness information (MCAI) FOR FURTHER INFORMATION CONTACT: Jim less than those obtained with one half issued by the aviation authority of of the available rudder control Rutherford, Aerospace Engineer, FAA, another country to identify and correct Small Airplane Directorate, 901 Locust, movement (but not exceeding a rudder an unsafe condition on an aviation control force of 180 pounds), rudder Room 301, Kansas City, Missouri 64106; product. The MCAI describes the unsafe telephone: (816) 329–4165; fax: (816) control movements and forces must be condition as failure of a brake master substantially proportional to the angle 329–4090; email: jim.rutherford@ cylinder pivot pin. We are issuing this faa.gov. of sideslip in a stable sense; and the AD to require actions to address the factor of proportionality must lie unsafe condition on these products. SUPPLEMENTARY INFORMATION: between limits found necessary for safe DATES: This AD is effective June 16, Discussion operation. This requirement must be 2015. met for the configurations and speeds The European Aviation Safety Agency The Director of the Federal Register specified in paragraph (c) of this (EASA), which is the Technical Agent approved the incorporation by reference section. for the Member States of the European of a certain publication listed in this AD (f) For sideslip angles greater than as of June 16, 2015. Community, has issued AD No.: 2015– those prescribed by paragraph (e) of this We must receive comments on this 0065–E, dated April 24, 2015, to correct section, up to the angle at which full AD by July 13, 2015. an unsafe condition for the specified rudder control is used or a rudder products. The MCAI states: ADDRESSES: You may send comments by control force of 180 pounds is obtained, any of the following methods: An occurrence was reported where pivot the rudder control forces may not • Federal eRulemaking Portal: Go to pin Part Number (P/N) T67M–45–539, of reverse, and increased rudder deflection http://www.regulations.gov. Follow the rudder pedal assembly #4, installed on the must be needed for increased angles of right hand (RH) side of the aeroplane (RH instructions for submitting comments. seat, RH pedal) failed during taxi. This sideslip. Compliance with this • Fax: (202) 493–2251. caused the rudder pedal mechanism to requirement must be shown using • Mail: U.S. Department of detach from the brake master cylinder. straight, steady sideslips, unless full Transportation, Docket Operations, This condition, if not detected and lateral control input is achieved before M–30, West Building Ground Floor, corrected, could cause the rudder linkages to reaching either full rudder control input Room W12–140, 1200 New Jersey rotate out of their normal orientation, or a rudder control force of 180 pounds; Avenue SE., Washington, DC 20590. possibly resulting in jammed rudder controls mstockstill on DSK4VPTVN1PROD with RULES a straight, steady sideslip need not be • Hand Delivery: U.S. Department of and consequent loss of control of the maintained after achieving full lateral Transportation, Docket Operations, aeroplane. To address this potential unsafe condition, control input. This requirement must be M–30, West Building Ground Floor, Slingsby Advanced Composites Ltd, trading met at all approved landing gear and Room W12–140, 1200 New Jersey as Marshall Aerospace and Defence Group wing-flap positions for the range of Avenue SE., Washington, DC 20590, (hereafter called ‘Marshall’ in this AD) issued operating speeds and power conditions between 9 a.m. and 5 p.m., Monday Service Bulletin (SB) SBM200 to provide appropriate to each landing gear and through Friday, except Federal holidays. inspection instructions. VerDate Sep<11>2014 17:50 May 26, 2015 Jkt 235001 PO 00000 Frm 00008 Fmt 4700 Sfmt 4700 E:\FR\FM\27MYR1.SGM 27MYR1

Federal Register / Vol. 80, No. 101 / Wednesday, May 27, 2015 / Rules and Regulations 30137 For the reason described above, this AD we determined that notice and air commerce by prescribing regulations requires repetitive inspections of the brake opportunity for public comment before for practices, methods, and procedures master cylinder pivot pins of rudder pedal issuing this AD are impracticable and the Administrator finds necessary for assemblies #1 and #4 and, depending on that good cause exists for making this safety in air commerce. This regulation findings, replacement of the affected pivot pins(s). amendment effective in fewer than 30 is within the scope of that authority days. because it addresses an unsafe condition You may examine the MCAI on the that is likely to exist or develop on Internet at http://www.regulations.gov Comments Invited products identified in this rulemaking by searching for and locating Docket No. This AD is a final rule that involves action. FAA–2015–1737. requirements affecting flight safety, and we did not precede it by notice and Regulatory Findings Relevant Service Information Under 1 CFR Part 51 opportunity for public comment. We We determined that this AD will not invite you to send any written relevant have federalism implications under Marshall Aerospace and Defence data, views, or arguments about this AD. Executive Order 13132. This AD will Group Service Bulletin SBM 200, Send your comments to an address not have a substantial direct effect on Revision 1, dated April 2015. The listed under the ADDRESSES section. the States, on the relationship between transmittal letter for Marshall Aerospace Include ‘‘Docket No. FAA–2015–1737; the national government and the States, and Defence Group SBM 200, Revision Directorate Identifier 2015–CE–014– or on the distribution of power and 1, incorrectly states it transmits the AD’’ at the beginning of your comments. responsibilities among the various Initial Issue; page 1 of this service We specifically invite comments on the levels of government. bulletin is dated April 2015; pages 2 overall regulatory, economic, through 8 are dated March 2015. The For the reasons discussed above, I environmental, and energy aspects of certify that this AD: actions described in this service this AD. We will consider all comments information are intended to correct the (1) Is not a ‘‘significant regulatory received by the closing date and may unsafe condition identified in the action’’ under Executive Order 12866, amend this AD because of those MCAI. The service bulletin describes comments. (2) Is not a ‘‘significant rule’’ under procedures for inspecting the brake We will post all comments we the DOT Regulatory Policies and master cylinder pivot pins, part number receive, without change, to http:// Procedures (44 FR 11034, February 26, (P/N) T67M–45–539, that are installed www.regulations.gov, including any 1979), on rudder pedal assemblies #1 and #4 personal information you provide. We (3) Will not affect intrastate aviation for cracks and distortion and replacing will also post a report summarizing each in Alaska, and any damaged pivot pins. This service substantive verbal contact we receive (4) Will not have a significant information is reasonably available about this AD. economic impact, positive or negative, because the interested parties have on a substantial number of small entities access to it through their normal course Costs of Compliance under the criteria of the Regulatory of business or by the means identified We estimate that this AD will affect 2 Flexibility Act. in the ADDRESSES section of this AD. products of U.S. registry. We also estimate that it will take about 6 work- List of Subjects in 14 CFR Part 39 FAA’s Determination and Requirements hours per product to comply with the Air transportation, Aircraft, Aviation of the AD basic requirements of this AD. The safety, Incorporation by reference, This product has been approved by average labor rate is $85 per work-hour. Safety. the aviation authority of another Required parts would cost about $50 per country, and is approved for operation product. Adoption of the Amendment in the United States. Pursuant to our Based on these figures, we estimate Accordingly, under the authority bilateral agreement with this State of the cost of the AD on U.S. operators to delegated to me by the Administrator, Design Authority, they have notified us be $1,120, or $560 per product. the FAA amends 14 CFR part 39 as of the unsafe condition described in the In addition, we estimate that any follows: MCAI and service information necessary follow-on actions will take referenced above. We are issuing this about .5 work-hours and require parts PART 39—AIRWORTHINESS AD because we evaluated all costing $100, for a cost of $142.50 per DIRECTIVES information provided by the State of product. We have no way of Design Authority and determined the determining the number of products ■ 1. The authority citation for part 39 unsafe condition exists and is likely to that may need these actions. continues to read as follows: exist or develop on other products of the same type design. Authority for This Rulemaking Authority: 49 U.S.C. 106(g), 40113, 44701. Title 49 of the United States Code § 39.13 [Amended] FAA’s Determination of the Effective specifies the FAA’s authority to issue Date rules on aviation safety. Subtitle I, ■ 2. The FAA amends § 39.13 by adding An unsafe condition exists that section 106, describes the authority of the following new AD: requires the immediate adoption of this the FAA Administrator. ‘‘Subtitle VII: 2015–11–01 Slingsby Aviation Ltd.: AD. The FAA has found that the risk to Aviation Programs,’’ describes in more Amendment 39–18164; Docket No. the flying public justifies waiving notice detail the scope of the Agency’s FAA–2015–1737; Directorate Identifier mstockstill on DSK4VPTVN1PROD with RULES and comment prior to adoption of this authority. 2015–CE–014–AD. rule because failure of a brake master We are issuing this rulemaking under (a) Effective Date cylinder pivot pin could cause the the authority described in ‘‘Subtitle VII, This airworthiness directive (AD) becomes rudder pedal mechanism to detach from Part A, Subpart III, section 44701: effective June 16, 2015. the brake master cylinder, which could General requirements.’’ Under that result in jammed rudder controls and section, Congress charges the FAA with (b) Affected ADs consequent loss of control. Therefore, promoting safe flight of civil aircraft in None. VerDate Sep<11>2014 17:50 May 26, 2015 Jkt 235001 PO 00000 Frm 00009 Fmt 4700 Sfmt 4700 E:\FR\FM\27MYR1.SGM 27MYR1

30138 Federal Register / Vol. 80, No. 101 / Wednesday, May 27, 2015 / Rules and Regulations (c) Applicability (2) Airworthy Product: For any DEPARTMENT OF TRANSPORTATION This AD applies to Slingsby Aviation Ltd. requirement in this AD to obtain corrective Models T67M260 and T67M260–T3A actions from a manufacturer or other source, Federal Aviation Administration airplanes, all serial numbers, certificated in use these actions if they are FAA-approved. any category. Corrective actions are considered FAA- 14 CFR Part 39 (d) Subject approved if they are approved by the State [Docket No. FAA–2009–1100; Directorate of Design Authority (or their delegated Air Transport Association of America Identifier 2009–NE–37–AD; Amendment 39– agent). You are required to assure the product (ATA) Code 27: Flight Controls. 18159; AD 2015–10–04] is airworthy before it is returned to service. (e) Reason RIN 2120–AA64 (h) Related Information This AD was prompted by mandatory continuing airworthiness information (MCAI) Refer to MCAI European Aviation Safety Airworthiness Directives; International issued by the aviation authority of another Agency (EASA) AD No.: 2015–0065–E, dated Aero Engines AG Turbofan Engines country to identify and correct an unsafe April 24, 2015, for related information. You condition on an aviation product. The MCAI AGENCY: Federal Aviation may examine the MCAI on the Internet at describes the unsafe condition as failure of a http://www.regulations.gov by searching for Administration (FAA), DOT. brake master cylinder pivot pin. We are and locating Docket No. FAA–2015–1737. ACTION: Final rule. issuing this AD to prevent failure of a brake master cylinder pivot pin, which could cause (i) Material Incorporated by Reference SUMMARY: We are superseding the rudder pedal mechanism to detach from Airworthiness Directive (AD) 2012–09– the brake master cylinder. This failure could (1) The Director of the Federal Register approved the incorporation by reference 09 for all International Aero Engines AG result in jammed rudder controls and consequent loss of control. (IBR) of the service information listed in this (IAE) V2500–A1, V2525–D5, and paragraph under 5 U.S.C. 552(a) and 1 CFR V2528–D5 turbofan engines, and certain (f) Actions and Compliance serial numbers (S/Ns) of IAE V2522–A5, part 51. Unless already done, do the actions in (2) You must use this service information V2524–A5, V2527–A5, V2527E–A5, paragraphs (f)(1) and (f)(2) of this AD. as applicable to do the actions required by V2527M–A5, V2530–A5, and V2533–A5 (1) Before further flight after June 16, 2015 turbofan engines. AD 2012–09–09 this AD, unless the AD specifies otherwise. (the effective date of this AD) and repetitively required cleaning, eddy current thereafter every 300 hours time-in-service or (i) Marshall Aerospace and Defence Group 12 months, whichever occurs first, inspect Service Bulletin SBM 200, Revision 1, dated inspection (ECI) or fluorescent penetrant the brake master cylinder pivot pins, part April 2015. inspection (FPI), and initial and number T67M–45–539, installed on rudder Note 1 to paragraph (i)(2)(i): The repetitive ultrasonic inspections (USIs) pedal assemblies #1 and #4. Do the transmittal letter for Marshall Aerospace and of certain high-pressure compressor inspections following the Accomplishment Defence Group SBM 200, Revision 1, dated (HPC) stage 3 to 8 drums, as well as Instructions in Marshall Aerospace and April 2015, incorrectly states it transmits the replacement of the drum attachment Defence Group Service Bulletin SBM 200, Initial Issue; page 1 is dated April 2015; nuts. This new AD expands the affected Revision 1, dated April 2015. This AD does pages 2 through 8 are dated March 2015. population for initial and repetitive not require the retention and reporting requirements of paragraph (2) of F. (ii) Reserved. USIs of the HPC stage 3 to 8 drum, COMPLETION in the Accomplishment (3) For Slingsby Aviation Ltd. service revises the inspection intervals, requires Instructions of this service bulletin. information identified in this AD, contact performing ECI or FPI, requires removal (2) If, during any inspection required in Marshall Aerospace and Defence Group, The of the affected attachment nuts and any paragraph (f)(1) of this AD, any crack or Airport, Newmarket Road, Cambridge, CB5 HPC stage 3 to 8 drum found cracked, distortion to a brake master cylinder pivot 8RX, UK; telephone: +44 (0) 1223 399856; and adds a mandatory terminating pin is found, or a pivot pin fails the fax: +44 (0) 7825365617; email: mark.bright@ action. This AD was prompted by the dimensional check, before further flight, marshalladg.com; Internet: discovery that additional attachment replace the affected pivot pin with a www.marshalladg.com. serviceable part. Do the replacement as nuts for certain HPC stage 3 to 8 drums (4) You may view this service information are affected. We are issuing this AD to specified in paragraph C.(1)(j) of the at the FAA, Small Airplane Directorate, 901 prevent failure of the HPC stage 3 to 8 Inspection section of the Accomplishment Instructions in Marshall Aerospace and Locust, Kansas City, Missouri 64106. For drum, which could result in Defence Group Service Bulletin SBM 200, information on the availability of this uncontained drum failure, damage to Revision 1, dated April 2015. After doing this material at the FAA, call (816) 329–4148. It the engine, and damage to the airplane. replacement, continue with the repetitive is also available on the Internet at http:// DATES: This AD is effective July 1, 2015. inspection requirement in paragraph (f)(1) of www.regulations.gov by searching for this AD. The Director of the Federal Register locating Docket No. FAA–2015–1737. approved the incorporation by reference (g) Other FAA AD Provisions (5) You may view this service information that is incorporated by reference at the of a certain publication listed in this AD The following provisions also apply to this National Archives and Records as of July 1, 2015. AD: ADDRESSES: For service information (1) Alternative Methods of Compliance Administration (NARA). For information on (AMOCs): The Manager, Standards Office, the availability of this material at NARA, call identified in this AD, contact FAA, has the authority to approve AMOCs 202–741–6030, or go to: http:// International Aero Engines AG, 400 for this AD, if requested using the procedures www.archives.gov/federal-register/cfr/ibr- Main Street, East Hartford, CT 06118; found in 14 CFR 39.19. Send information to locations.html. phone: 860–368–3700; fax: 860–368– ATTN: Jim Rutherford, Aerospace Engineer, 4600; email: iaeinfo@iaev2500.com; FAA, Small Airplane Directorate, 901 Locust, Issued in Kansas City, Missouri, on May Internet: https://www.iaeworld.com. mstockstill on DSK4VPTVN1PROD with RULES Room 301, Kansas City, Missouri 64106; 18, 2015. You may view this service information telephone: (816) 329–4165; fax: (816) 329– Earl Lawrence, at the FAA, Engine & Propeller 4090; email: jim.rutherford@faa.gov. Before Manager, Small Airplane Directorate, Aircraft using any approved AMOC on any airplane Directorate, 12 New England Executive Certification Service. Park, Burlington, MA. For information to which the AMOC applies, notify your appropriate principal inspector (PI) in the [FR Doc. 2015–12448 Filed 5–26–15; 8:45 am] on the availability of this material at the FAA Flight Standards District Office (FSDO), BILLING CODE 4910–13–P FAA, call 781–238–7125. It is also or lacking a PI, your local FSDO. available on the Internet at http:// VerDate Sep<11>2014 17:50 May 26, 2015 Jkt 235001 PO 00000 Frm 00010 Fmt 4700 Sfmt 4700 E:\FR\FM\27MYR1.SGM 27MYR1


Document Created: 2015-12-15 15:35:28
Document Modified: 2015-12-15 15:35:28
CategoryRegulatory Information
CollectionFederal Register
sudoc ClassAE 2.7:
GS 4.107:
AE 2.106:
PublisherOffice of the Federal Register, National Archives and Records Administration
SectionRules and Regulations
ActionFinal rule; request for comments.
DatesThis AD is effective June 16, 2015.
ContactJim Rutherford, Aerospace Engineer, FAA, Small Airplane Directorate, 901 Locust, Room 301, Kansas City, Missouri 64106; telephone: (816) 329-4165; fax: (816) 329-4090; email: [email protected]
FR Citation80 FR 30136 
RIN Number2120-AA64
CFR AssociatedAir Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety
2025 Federal Register | Disclaimer | Privacy Policy
USC | CFR | eCFR