Federal Register / Vol. 79, No. 64 / Thursday, April 3, 2014 / Rules and Regulations 18617 

(2) You must use this service information 

as applicable to do the actions required by 

this AD, unless the AD specifies otherwise. 

(i) Alexander Schleicher, Segelflugzeugbau 

Alexander Schleicher GmbH & Co. 

Segelflugzeugbau ASK 21 Technical Note Nr. 

4b, Issue for US registered gliders, dated 

October 31, 2013. 

(ii) Reserved. 

(3) For Alexander Schleicher, 

Segelflugzeugbau service information 

identified in this AD, contact Alexander 

Schleicher GmbH & Co. Segelflugzeugbau, 

Alexander-Schleicher-Str. 1, D–36163 

Poppenhausen, Germany; phone: +49 (0) 

06658 89–0; fax: +49 (0) 06658 89–40; 

Internet: http://www.alexanderschleicher.de/; email: info@alexanderschleicher.de. 

(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. 

(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 March 

19, 2014. 

James E. Jackson, 

Acting Manager, Small Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2014–06627 Filed 4–2–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2006–24777; Directorate 

Identifier 2006–NE–19–AD; Amendment 39– 

17809; AD 2014–06–05] 

RIN 2120–AA64 

Airworthiness Directives; Rolls-Royce 

Deutschland Ltd & Co KG Turbofan 

Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are superseding 

airworthiness directive (AD) 2007–03– 

02 for all Rolls-Royce Deutschland 

(RRD) Tay 620–15, Tay 650–15, and Tay 

651–54 turbofan engines. AD 2007–03– 

02 required an ultrasonic inspection 

(UI) of low-pressure (LP) compressor fan 

blades for cracks on certain serial 

number (S/N) Tay 650–15 engines. AD 

2007–03–02 also required, for all Tay 

611–8, 620–15, Tay 650–15, and Tay 

651–54 engines, initial and repetitive 

UIs of LP compressor fan blades. AD 

2007–03–02 also required, for Tay 650– 

15 and Tay 651–54 engines, UIs of LP 

compressor fan blades whenever the 

blade set is removed from one engine 

and installed on a different engine. This 

AD requires additional inspections for 

the affected engines and removal of the 

Tay 611–8 engine from the applicability. 

This AD was prompted by a report of an 

additional engine failure due to 

multiple fan blade separation. We are 

issuing this AD to prevent failure of the 

LP compressor fan blade, engine failure, 

and damage to the airplane. 

DATES: This AD is effective May 8, 2014. 

Federal Register approved the 

incorporation by reference of a certain 

publication listed in this AD as of May 

8, 2014. 

ADDRESSES: For service information 

identified in this AD, contact RollsRoyce Deutschland Ltd & Co KG, 

Eschenweg 11, D–15827 Blankenfelde— 

Mahlow, Germany; phone: 49 0 33 7086 

1200; fax: 49 0 33 7086 1212. 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. 

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–2006– 

24777; 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 mandatory 

continuing airworthiness information 

(MCAI), the regulatory evaluation, any 

comments received, and other 

information. The address for the Docket 

Office (phone: 800–647–5527) is 

Document Management Facility, U.S. 

Department of Transportation, Docket 

Operations, M–30, West Building 

Ground Floor, Room W12–140, 1200 

New Jersey Avenue SE., Washington, 

DC 20590. 

FOR FURTHER INFORMATION CONTACT: 

Anthony W. Cerra Jr., Aerospace 

Engineer, Engine & Propeller 

Directorate, FAA, 12 New England 

Executive Park, Burlington, MA 01803; 

phone: 781–238–7128; fax: 781–238– 

7199; email: anthony.cerra@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to supersede AD 2007–03–02, 

Amendment 39–14913 (72 FR 3936, 

January 29, 2007), (‘‘AD 2007–03–02’’). 

AD 2007–03–02 applied to all RRD Tay 

611–8 and Tay 620–15 turbofan engines 

with LP compressor module, part 

number (P/N) M01100AA or P/N 

M01100AB, installed, and Tay 650–15 

and Tay 651–54 turbofan engines with 

LP compressor module, P/N M01300AA 

or P/N M01300AB, installed. The NPRM 

published in the Federal Register on 

November 29, 2013 (78 FR 71532). The 

NPRM proposed to require a UI of LP 

compressor fan blades for cracks on 

certain S/N Tay 650–15 engines; initial 

and repetitive UIs of LP compressor fan 

blades for all Tay 620–15, Tay 650–15, 

and Tay 651–54 engines; and UIs of LP 

compressor fan blades whenever the 

blade set is removed from one engine 

and installed on a different engine for 

Tay 650–15 and Tay 651–54 engines. 

The NPRM also proposed to require 

additional inspections for the affected 

engines and removal of the Tay 611–8 

engine from the applicability of this AD. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

received no comments on the NPRM (78 

FR 71532, November 29, 2013). 

Conclusion 

We reviewed the relevant data and 

determined that air safety and the 

public interest require adopting this AD 

as proposed. 

Costs of Compliance 

We estimate that this AD affects about 

52 engines installed on airplanes of U.S. 

registry. We also estimate that it will 

take about 4 hours per engine to remove 

and inspect an LP compressor blade set. 

The average labor rate is $85 per hour. 

Prorated parts life will cost about 

$11,750 per engine. Based on these 

figures, we estimate that the cost of this 

AD on U.S. operators is $628,680. 

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 


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18618 Federal Register / Vol. 79, No. 64 / Thursday, April 3, 2014 / Rules and Regulations 

is within the scope of that authority 

because it addresses an unsafe condition 

that is likely to exist or develop on 

products identified in this rulemaking 

action. 

Regulatory Findings 

This AD will not have federalism 

implications under Executive Order 

13132. This AD will not have a 

substantial direct effect on the States, on 

the relationship between the national 

government and the States, or on the 

distribution of power and 

responsibilities among the various 

levels of government. 

For the reasons discussed above, I 

certify that this AD: 

(1) Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866, 

(2) Is not a ‘‘significant rule’’ under 

DOT Regulatory Policies and Procedures 

(44 FR 11034, February 26, 1979), 

(3) Will not affect intrastate aviation 

in Alaska to the extent that it justifies 

making a regulatory distinction, 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 part 39 of the Federal 

Aviation Regulations (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 

removing airworthiness directive (AD) 

2007–03–02, Amendment 39–14913 (72 

FR 3936, January 29, 2007) and adding 

the following new AD: 

2014–06–05 Rolls-Royce Deutschland Ltd & 

Co KG: (Type Certificate previously held 

by Rolls-Royce plc) Amendment 39– 

17809; Docket No. FAA–2006–24777; 

Directorate Identifier 2006–NE–19–AD. 

(a) Effective Date 

This AD is effective May 8, 2014. 

(b) Affected ADs 

This AD supersedes AD 2007–03–02, 

Amendment 39–14913 (72 FR 3936, January 

29, 2007). 

(c) Applicability 

This AD applies to Rolls-Royce 

Deutschland Ltd & Co KG (RRD) Tay 620–15 

turbofan engines with low-pressure (LP) 

compressor module, part number (P/N) 

M01100AA or P/N M01100AB, installed, and 

Tay 650–15 and Tay 651–54 turbofan engines 

with LP compressor module, P/N M01300AA 

or P/N M01300AB, installed. 

(d) Unsafe Condition 

This AD was prompted by a report of an 

additional engine failure due to multiple fan 

blade separation. We are issuing this AD to 

prevent failure of the LP compressor fan 

blade, engine failure, and damage to the 

airplane. 

(e) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(1) For Tay 650–15 and Tay 651–54 engine 

LP compressor fan blade ultrasonic 

inspection (UI): 

(i) After the effective date of this AD, 

whenever LP compressor fan blades are 

removed from an engine, before reinstallation on a different engine, inspect the 

LP compressor fan blades and accomplish a 

UI of the LP compressor fan blades in 

accordance with Instruction I of paragraph 3 

of RRD Alert Non-Modification Service 

Bulletin (NMSB) TAY–72–A1442, Revision 6, 

dated August 26, 2013. 

(ii) After the effective date of this AD, 

during each engine shop visit, before return 

to service of the engine, inspect the LP 

compressor fan blades and accomplish a UI 

of the LP compressor fan blades in 

accordance with Instruction II of paragraph 3 

of RRD Alert NMSB TAY–72–A1442, 

Revision 6, dated August 26, 2013. 

(2) For Tay 620–15 engine LP compressor 

fan blade UI, after the effective date of this 

AD, before return to service of an engine after 

every mid-life, or every calendar-life, or 

every overhaul shop visit, inspect the LP 

compressor fan blades and accomplish a UI 

of the LP compressor fan blades in 

accordance with Instruction II of paragraph 3 

of RRD Alert NMSB TAY–72–A1442, 

Revision 6, dated August 26, 2013. 

(3) For Tay 620–15, Tay 650–15, and Tay 

651–54 engine LP compressor fan blade and 

rotor disk replacement, if during any 

inspection required by paragraph (e)(1) or 

(e)(2) of this AD, any LP compressor fan 

blade is found cracked, before next flight or 

return to service of the engine, replace the 

complete set of the LP compressor fan blades 

and the LP compressor rotor disk. 

(f) Credit for Previous Actions 

If, before the effective date of this AD, you 

inspected or replaced any Tay 620–15, Tay 

650–15, or Tay 651–54 turbofan engine LP 

compressor fan blade or rotor disk assembly 

using RRD Alert NMSB TAY–72–A1442, 

Revision 5, dated May 31, 2013, or earlier, 

you have satisfied the requirements of 

paragraphs (e)(1) through (e)(3) of this AD. 

(g) Definitions 

For the purposes of this AD for Tay 620– 

15 engines: 

(1) A mid-life shop visit is an engine shop 

visit accomplished before accumulating 

12,000 engine flight cycles since new (FCSN) 

or flight cycles (FC) since last engine mid-life 

shop visit; 

(2) A calendar-life shop visit is an engine 

shop visit accomplished within 10 years 

since new or since the last engine calendarlife shop visit; and 

(3) An overhaul shop visit is an engine 

shop visit accomplished before accumulating 

22,000 engine FCSN or FC since the last 

engine overhaul shop visit. 

(h) Alternative Methods of Compliance 

(AMOCs) 

The Manager, Engine Certification Office, 

may approve AMOCs for this AD. Use the 

procedures found in 14 CFR 39.19 to make 

your request. 

(i) Related Information 

(1) For more information about this AD, 

contact Anthony W. Cerra Jr., Aerospace 

Engineer, Engine & Propeller Directorate, 

FAA, 12 New England Executive Park, 

Burlington, MA 01803; phone: 781–238– 

7128; fax: 781–238–7199; email: 

anthony.cerra@faa.gov. 

(2) Refer to MCAI European Aviation 

Safety Agency, AD 2013–151R2, dated 

September 2, 2013, for more information. 

You may examine the MCAI in the AD 

docket on the Internet at http://

www.regulations.gov/

#!documentDetail;D=FAA-2006-24777-0012. 

(3) 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. 

(j) 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) Rolls-Royce Deutschland Ltd & Co KG 

Alert Non-Modification Service Bulletin No. 

TAY–72–A1442, Revision 6, dated August 

26, 2013. 

(ii) Reserved. 

(3) For RRD service information identified 

in this AD, contact Rolls-Royce Deutschland 

Ltd & Co KG, Eschenweg 11, D–15827 

Blankenfelde-Mahlow, Germany; phone: 49 0 

33 7086 1200; fax: 49 0 33 7086 1212. 

(4) You may view this service information 

at 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. 

(5) You may view this service information 

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. 


pmangrum on DSK3VPTVN1PROD with RULES
Federal Register / Vol. 79, No. 64 / Thursday, April 3, 2014 / Rules and Regulations 18619 

Issued in Burlington, Massachusetts, on 

March 18, 2014. 

Ann C. Mollica, 

Acting Assistant Directorate Manager, Engine 

& Propeller Directorate, Aircraft Certification 

Service. 

[FR Doc. 2014–06632 Filed 4–2–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0975; Directorate 

Identifier 2013–NM–082–AD; Amendment 

39–17813; AD 2014–06–09] 

RIN 2120–AA64 

Airworthiness Directives; ATR—GIE 

Avions de Transport Re ́gional 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are superseding 

Airworthiness Directive (AD) 2009–18– 

18 for certain ATR—GIE Avions de 

Transport Re ́gional Model ATR42 and 

ATR72 airplanes. AD 2009–18–18 

required repetitive inspections for 

damage and absence of repair of the 

cockpit forward side windows, and 

replacement if necessary. This new AD 

requires repetitive detailed inspections 

of the cockpit forward side window for 

damage and discrepancies; and 

replacement if necessary. Replacing 

both cockpit forward side windows with 

approved windows terminates the 

repetitive detailed inspections. This 

new AD also expands the applicability 

of AD 2009–18–18. The actions required 

by AD 2009–18–18 are not required by 

this AD. This AD was prompted by 

reports of a cockpit forward right-hand 

side blow out during flight. We are 

issuing this AD to detect and correct air/ 

water leakage of the cockpit forward 

side window, which could lead to rapid 

cabin decompression, resulting in loss 

of control of the airplane. 

DATES: This AD becomes effective May 

8, 2014. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of May 8, 2014. 

ADDRESSES: You may examine the AD 

docket on the Internet at http://

www.regulations.gov/

#!docketDetail;D=FAA-2013-0975; or in 

person at the Docket Management 

Facility, U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE., 

Washington, DC. 

For PPG Aerospace service 

information identified in this AD, 

contact PPG Aerospace, 12780 San 

Fernando Road, Sylmar, CA 91342; 

phone: 818–362–6711; fax: 818–362– 

0603; Internet: http://

corporateportal.ppg.com/na/aerospace. 

For ATR service information 

identified in this AD, contact ATR—GIE 

Avions de Transport Re ́gional, 1, Alle ́e 

Pierre Nadot, 31712 Blagnac Cedex, 

France; telephone +33 (0) 5 62 21 62 21; 

fax +33 (0) 5 62 21 67 18; email 

continued.airworthiness@atr.fr; Internet 

http://www.aerochain.com. 

You may view this referenced service 

information at the FAA, Transport 

Airplane Directorate, 1601 Lind Avenue 

SW., Renton, WA. For information on 

the availability of this material at the 

FAA, call 425–227–1221. 

FOR FURTHER INFORMATION CONTACT: Tom 

Rodriguez, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA 

1601 Lind Avenue SW., Renton, WA 

98057–3356; telephone (425) 227–1137; 

fax (425) 227–1149. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to supersede AD 2009–18–18, 

Amendment 39–16014 (74 FR 46336, 

September 9, 2009). AD 2009–18–18 

applied to certain ATR—GIE Avions de 

Transport Re ́gional Model ATR42 and 

ATR72 airplanes. The NPRM published 

in the Federal Register on November 27, 

2013 (78 FR 70892). The NPRM was 

prompted by reports of a cockpit 

forward right-hand side blow out during 

flight. The NPRM proposed to require 

repetitive detailed inspections of the 

cockpit forward side window for 

damage and discrepancies; and 

replacement if necessary. Replacing 

both cockpit forward side windows with 

approved windows would terminate the 

repetitive detailed inspections. The 

NPRM also proposed to expand the 

applicability of AD 2009–18–18. The 

actions required by AD 2009–18–18 are 

not required by the NPRM. We are 

issuing this AD to detect and correct air/ 

water leakage of the cockpit forward 

side window, which could lead to rapid 

cabin decompression, resulting in loss 

of control of the airplane. 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Community, has issued EASA 

Airworthiness Directive 2013–0087, 

dated April 9, 2013 (referred to after this 

as the Mandatory Continuing 

Airworthiness Information, or ‘‘the 

MCAI’’), to correct an unsafe condition 

for all ATR—GIE Avions de Transport 

Re ́gional Model ATR42–200, –300, 

–320, and –500 airplanes; and Model 

ATR72–101, –201, –102, –202, –211, 

–212, and –212A airplanes; all 

manufacturer serial numbers. The MCAI 

states: 

In 2009, a Left-Hand (LH) forward side 

glass window of an ATR 72–212 aeroplane 

blew out while performing a ground pressure 

test. The investigation results revealed some 

anomalies on the forward side window at the 

level of the z-bar on the windows external 

side and at the level of the inner retainer on 

the windows internal side. Such anomalies 

are considered as precursors of this kind of 

failure. Air or water leakages between the zbar and the outer glass ply, or between the 

inner retainer and inner glass ply indicate the 

presence of deteriorating structural 

components in the window. 

Neither ATR nor PPG Aerospace have 

authorized repairs on the window z-bar or zbar sealant. Any attempted repairs on these 

forward side window z-bars and/or z-bar 

sealants could lead to a similar event as 

described above. 

In-flight loss of a forward side window 

would cause rapid cabin decompression, 

possibly resulting in flight crew 

incapacitation and consequent reduced 

control, or loss of control of the aeroplane, 

and cause the risk of injury to persons on the 

ground. The loss of a forward side window 

while the aeroplane is on the ground, due to 

differential cabin pressure, could result in 

injury to aeroplane occupants or to persons 

outside the aeroplane. 

To address this potential unsafe condition, 

EASA issued AD 2009–0159–E [dated July 

20, 2009] (http://ad.easa.europa.eu/blob/

easa_ad_2009_0159E_superseded.pdf/EAD_

2009-0159-E_1) [which corresponds to FAA 

AD 2009–18–18, Amendment 39–116014 (74 

FR 46336, September 9, 2009)] to require 

repetitive inspections of the affected LH and 

right-hand (RH) cockpit forward side glass 

windows and, in case discrepancies are 

found as defined in PPG Aerospace Service 

Bulletin (SB) NP–158862–001, the 

replacement of the window(s). 

Since that [EASA] AD was issued, a 

cockpit forward RH-side window blew out 

during flight on an ATR72–212 aeroplane. 

Degradation of the window is considered to 

have been the cause for this failure. 

* * * [T]his [EASA] AD * * * requires to 

accomplish the [detailed] inspections in 

accordance with the instructions of Revision 

1 of PPG Aerospace SB NP–158862–001, 

which provides more information on 

examples of [damaged and] discrepant 

conditions. 

This [EASA] AD also requires the removal 

from service of the affected Part Number (P/ 

N) NP158862–1 and P/N NP158862–2 

cockpit forward side windows, which 

constitutes terminating action for the 

repetitive inspections required by this AD. 


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