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 

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 

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. 

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Federal Register / Vol. 80, No. 101 / Wednesday, May 27, 2015 / Rules and Regulations 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 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 

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. 

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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. 

(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 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. 

(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/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 

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 

Airworthiness Directives; International 

Aero Engines AG Turbofan Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: 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:// 

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