47534 Federal Register / Vol. 78, No. 151 / Tuesday, August 6, 2013 / Rules and Regulations 

TABLE 1 TO PARAGRAPH (e)—Continued 

UT inspect grip, P/N 

Within 30 days, 

for a grip with 

the following or 

more hours TIS: 

Thereafter, at intervals not to exceed the following number of hours 

TIS or the engine start/stop cycles, 

whichever occurs first: 

Hours TIS Engine start/stop 

cycles 

204–011–121–005 or –113, if the grip was EVER installed on a Model 205B or Model 

UH–1N helicopter ......................................................................................................... 4,000 400 1,600 

204–011–121–117, if the grip was EVER installed on a Model 205B helicopter ........... 500 150 600 

(3) At intervals not to exceed 1,200 hours 

TIS or 24 months, whichever occurs first: 

(i) Remove each main rotor blade, and 

(ii) Inspect each grip buffer pad on the 

inner surfaces of each grip tang for 

delamination as depicted in Figure 5–7, 

Inspection of Main Rotor Hub Grip (1200 

Hours), Revision 9, dated August 8, 2008, of 

Chapter 5, Inspections and Component 

Overhaul Schedule, Revision 11, dated April 

30, 2010, of Bell Helicopter Textron, Inc., 

BHT–212–MM–1, Revision 13, dated 

September 16, 2010. If there is any 

delamination, remove the buffer pad and 

inspect the grip surface for corrosion or other 

damage. 

(4) Within 2,400 hours TIS or at the next 

overhaul of the main rotor hub, whichever 

occurs first, and then at intervals not to 

exceed 2,400 hours TIS: 

(i) Remove each main rotor blade. 

(ii) Remove each grip buffer pad (if 

installed) from the inner surfaces of each grip 

tang. 

(iii) Visually inspect the grip surfaces for 

corrosion or other damage. 

(iv) Fluorescent-penetrant inspect (FPI) the 

grip for a crack, paying particular attention 

to the upper and lower grip tangs. When 

inspecting a grip, P/N 204–011–121–005, 

204–011–121–009, or 204–011–121–113, or 

ASI–4011–121–9, pay particular attention to 

the leading and trailing edges of the grip 

barrel. 

(5) Before further flight: 

(i) Replace any cracked grip with an 

airworthy grip. 

(ii) Replace any grip with any corrosion or 

other damage with an airworthy grip, or 

repair the grip if the corrosion or other 

damage is within the maximum repair 

limitations. 

(iii) Remove any grip, P/N 204–011–121– 

009 or ASI–4011–121–9, that has been in 

service for 15,000 or more hours TIS. 

(iv) Remove any grip, P/N 204–011–121– 

121, that has been in service for 25,000 or 

more hours TIS. 

(6) Revise the Airworthiness Limitations 

section of the applicable maintenance 

manual or the Instructions for Continued 

Airworthiness (ICA) by establishing a new 

retirement life of 15,000 hours TIS for grip, 

P/N 204–011–121–009 or ASI–4011–121–9, 

and 25,000 hours TIS for grip, P/N 204–011– 

121–121, by marking pen and ink changes or 

inserting a copy of this AD into the 

maintenance manual or ICA. 

(7) Record a 15,000 hour TIS life limit for 

each grip, P/N 204–011–121–009 or ASI– 

4011–121–9, and a 25,000 hour life limit for 

each grip, P/N 204–011–121–121, on the 

applicable component history card or 

equivalent record. 

(f) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Rotorcraft Certification 

Office, FAA, may approve AMOCs for this 

AD. Send your proposal to: Michael Kohner, 

Aviation Safety Engineer, Rotorcraft 

Certification Office, Rotorcraft Directorate, 

FAA, 2601 Meacham Blvd., Fort Worth, 

Texas 76137; telephone (817) 222–5170; 

email 7-avs-asw-170@faa.gov. 

(2) For operations conducted under a 14 

CFR part 119 operating certificate or under 

14 CFR part 91, subpart K, we suggest that 

you notify your principal inspector, or 

lacking a principal inspector, the manager of 

the local flight standards district office or 

certificate holding district office before 

operating any aircraft complying with this 

AD through an AMOC. 

(g) Additional Information 

BHTI Alert Service Bulletin (ASB) 212–94– 

92, Revision A, dated March 13, 1995; BHTI 

Operations Safety Notice (OSN) 204–85–6, 

OSN 205–85–9, and OSN 212–85–13, all 

dated November 14, 1985 and co-published 

as one document; BHTI ASB 205B–02–39, 

Revision B, dated November 22, 2002; and 

BHTI ASB 212–02–116, Revision A, dated 

October 30, 2002, which are not incorporated 

by reference, contain additional information 

about the subject of this AD. 

(h) Subject 

Joint Aircraft Service Component (JASC) 

Code: 6220, Main rotor head. 

(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) Bell Helicopter Textron, Inc. 

Nondestructive Inspection Procedure, Log 

No. 00–340, Revision E, dated April 9, 2002. 

(ii) Figure 5–7, Inspection of Main Rotor 

Hub Grip (1200 Hours), Revision 9, dated 

August 8, 2008, of Chapter 5, Inspections and 

Component Overhaul Schedule, Revision 11, 

dated April 30, 2010, of Bell Helicopter 

Textron, Inc., BHT–212–MM–1, Revision 13, 

dated September 16, 2010. 

(3) For BHTI service information identified 

in this AD, contact Bell Helicopter Textron, 

Inc., P.O. Box 482, Fort Worth, TX 76101; 

telephone (817) 280–3391; fax (817) 280– 

6466; or at http://www.bellcustomer.com/ 

files/. 

(4) You may review a copy of this service 

information at the FAA, Office of the 

Regional Counsel, Southwest Region, 2601 

Meacham Blvd., Room 663, Fort Worth, 

Texas 76137. 

(5) You may also review a copy of 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/ibr-locations.html. 

Issued in Fort Worth, Texas, on June 18, 

2013. 

Kim Smith, 

Directorate Manager, Rotorcraft Directorate, 

Aircraft Certification Service. 

[FR Doc. 2013–18570 Filed 8–5–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0447; Directorate 

Identifier 2013–NE–17–AD; Amendment 39– 

17536; AD 2013–15–20] 

RIN 2120–AA64 

Airworthiness Directives; General 

Electric Company Turbofan Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule; request for 

comments. 

SUMMARY: We are superseding 

emergency airworthiness directive (AD) 

2013–14–51 for General Electric 

Company (GE) GE90–110B1 and GE90– 

115B turbofan engines with affected 

transfer gearbox assembly (TGB) radial 

gearshafts installed. AD 2013–14–51 

was sent previously to all known U.S. 

owners and operators of GE90–110B1 

and GE90–115B turbofan engines. AD 

2013–14–51 prohibited operation of an 

airplane if more than one installed 

engine has an affected TGB radial 


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Federal Register / Vol. 78, No. 151 / Tuesday, August 6, 2013 / Rules and Regulations 47535 

gearshaft. This AD contains the same 

prohibition as AD 2013–14–51 and also 

prohibits operation of any airplane 60 

days after the effective date of this new 

AD if any installed engine has an 

affected TGB radial gearshaft. This new 

AD also revises the applicability by 

adding GE90–76B, GE90–77B, GE90– 

85B, GE90–90B, GE90–94B, and GE90– 

113B turbofan engine models and adds 

a mandatory terminating action. This 

new AD was prompted by reports of 

three failures of TGB radial gearshafts 

which resulted in in-flight shutdowns 

(IFSDs). We are issuing this new AD to 

prevent failure of the TGB radial 

gearshaft, which could result in IFSD of 

one or more engines, loss of thrust 

control, and damage to the airplane. 

DATES: This AD is effective August 21, 

2013. 

We must receive any comments on 

this AD by September 20, 2013. 

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 General Electric 

Company, One Neumann Way, Room 

285, Cincinnati, OH; phone: 513–552– 

3272; email: geae.aoc@ge.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. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http:// 

www.regulations.gov; 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 (phone: 800–647– 

5527) is in the ADDRESSES section. 

Comments will be available in the AD 

docket shortly after receipt. 

FOR FURTHER INFORMATION CONTACT: 

Carlos Fernandes, Aerospace Engineer, 

Engine Certification Office, FAA, Engine 

& Propeller Directorate, 12 New England 

Executive Park, Burlington, MA 01803; 

phone: 781–238–7189; fax: 781–238– 

7199; email: carlos.fernandes@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

On May 16, 2013, we issued 

emergency AD 2013–10–52 (issued on 

June 16, 2013, as a Final Rule, Request 

for Comments (78 FR 38195, June 26, 

2013)), which was immediately effective 

to owners and operators of GE GE90– 

110B1 and GE90–115B turbofan 

engines. That AD resulted from reports 

of two failures of TGB radial gearshafts 

that resulted in IFSDs. That AD 

prohibited operation of an airplane with 

affected TGBs installed on both engines. 

On July 12, 2013, we issued 

emergency AD 2013–14–51, superseding 

AD 2013–10–52 (78 FR 38195, June 26, 

2013). AD 2013–14–51 also prohibits 

operation of an airplane with affected 

TGB radial gearshafts installed on both 

engines. AD 2013–14–51 resulted from 

a report of an additional failure of a TGB 

radial gearshaft, outside the population 

identified in AD 2013–10–52. We issued 

ADs 2013–10–52 and 2013–14–51 to 

prevent failure and separation of the 

TGB radial gearshaft, which could result 

in IFSD of one or more engines, loss of 

thrust control, and damage to the 

airplane. 

Actions Since AD 2013–14–51 Was 

Issued 

Since we issued emergency AD 2013– 

14–51, dated July 12, 2013, we 

determined that airplanes with an 

installed engine with an affected TGB 

radial gearshaft should not be allowed 

to operate more than 60 days after the 

effective date of this new AD. We also 

revised the Applicability of this new AD 

since we determined that the affected 

TGB radial gearshafts are installed on 

additional GE90 engine models besides 

the GE90–110B1 and GE90–115B. We 

also determined the need to add a 

mandatory terminating action. 

Relevant Service Information 

We reviewed GE GE90–100 Series 

Alert Service Bulletin (ASB) No. GE90– 

100 S/B 72–A0568, dated July 10, 2013; 

GE GE90–100 Series Service Bulletin 

(SB) No. GE90–100 S/B 72–0569, 

Revision 0, dated July 19, 2013; and GE 

GE90 SB No. GE90 S/B 72–1091, 

Revision 0, dated June 11, 2013, which 

provide additional information 

regarding the affected TGB radial 

gearshafts. We also reviewed GE GE90– 

100 Series SB No. GE90–100 S/B 72– 

0563, Revision 0, dated June 21, 2013, 

and Revision 1, dated July 10, 2013; and 

GE GE90 SB No. GE90 S/B 72–1066, 

Revision 0, dated June 21, 2013; which 

provide information regarding the 

mandatory terminating action. 

FAA’s Determination 

We are issuing this AD because we 

evaluated all the relevant information 

and determined the unsafe condition 

described previously is likely to exist or 

develop in other products of the same 

type design. 

AD Requirements 

This AD prohibits operation of an 

airplane with affected TGB radial 

gearshafts installed on both engines 

after the effective date of this AD. This 

AD also prohibits operation of an 

airplane with affected TGB radial 

gearshafts installed on any engine 60 

days after the effective date of this AD. 

This AD also adds a mandatory 

terminating action, namely, to install a 

TGB radial gearshaft that is eligible for 

installation. 

FAA’s Justification and 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 of the before further flight 

compliance time. Therefore, we find 

that notice and opportunity for prior 

public comment are impracticable and 

that good cause exists for making this 

amendment effective in less than 30 

days. 

Comments Invited 

This AD is a final rule that involves 

requirements affecting flight safety, and 

we did not provide you with notice and 

an opportunity to provide your 

comments before it becomes effective. 

However, we invite you to send any 

written data, views, or arguments about 

this AD. Send your comments to an 

address listed under the ADDRESSES

section. Include the docket number 

FAA–2013–0447 and directorate 

identifier 2013–NE–17–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 


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47536 Federal Register / Vol. 78, No. 151 / Tuesday, August 6, 2013 / Rules and Regulations 

substantive verbal contact we receive 

about this AD. 

Costs of Compliance 

We estimate that this AD will affect 

about 16 GE90 engines installed on 

airplanes of U.S. registry. We also 

estimate that it will take about eight 

hours per engine to replace the TGB 

radial gearshaft. The average labor rate 

is $85 per hour. The cost of this part is 

about $16,700. Based on these figures, 

we estimate the total cost of this AD to 

U.S. operators to be $278,080. 

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 

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: 

■ a. Removing AD 2013–10–52 (78 FR 

38195, June 26, 2013); and 

■ b. Adding the following new AD: 

2013–15–20: Amendment 39–17536; 

Docket No. FAA–2013–0447; Directorate 

Identifier 2013–NE–17–AD. 

(a) Effective Date 

This AD is effective August 21, 2013. 

(b) Affected ADs 

This AD supersedes Emergency AD 

2013–14–51, Directorate ID 2013–NE– 

17–AD, dated July 12, 2013. This AD 

also removes AD 2013–10–52 (78 FR 

38195, June 26, 2013) from the Code of 

Federal Regulations. 

(c) Applicability 

General Electric Company (GE) GE90– 

76B, GE90–77B, GE90–85B, GE90–90B, 

GE90–94B, GE90–110B1, GE90–113B 

and GE90–115B turbofan engines with a 

transfer gearbox assembly (TGB) radial 

gearshaft, part number (P/N) 

1995M24P02, serial number (S/N) listed 

in Figure 1 to paragraph (c) of this AD, 

installed. 

FIGURE 1 TO PARAGRAPH (c)—TGB RADIAL GEARSHAFT P/N 1995M24P02 S/N’S

FIA0KCYG FIA0JETA FIA0H0VJ FIA0HL0C 

FIA0K63F FIA0J7V2 FIA0K62R FIA0HLY9 

FIA0K3A3 FIA0KCYM FIA0K63C FIA0HL0E 

FIA0JVRE FIA0JJ6E FIA0K89H FIA0HL0F 

FIA0H0VM FIA0JNJH FIA0KCYK FIA0HL0G 

FIA0K3A4 FIA0K62W FIA0K3A5 FIA0HLY7 

FIA0K62T FIA0K89P FIA0HWKA FIA0HJTE 

FIA0JJ53 FIA0JJ57 FIA0KCYR FIA0HJTJ 

FIA0K89W FIA0JJ56 FIA0HWKE FIA0HJTG 

FIA0KCW8 FIA0KH9Y FIA0J7WH FIA0HJTC 

FIA0K3A6 FIA0KCYP FIA0JER9 FIA0HJTF 

FIA0HY8C FIA0JJ55 FIA0JNJJ FIA0HJTH 

FIA0K3AP FIA0KH9G FIA0JVRR FIA0HJTA 

FIA0J7WG FIA0KH9H FIA0JNJM FIA0HJR9 

FIA0JVRL FIA0KH9K FIA0KH9R FIA0HWJ7 

FIA0J7V1 FIA0KH9C FIA0KH9P FIA0HY76 

FIA0JVRM FIA0K63H FIA0K89C FIA0HY8F 

FIA0K3AV FIA0K63M FIA0JVRH FIA0H0VK 

FIA0J7V8 FIA0K62Y FIA0K89L FIA0J7VR 

FIA0J7WE FIA0JVP9 FIA0JER6 FIA0JJ58 

FIA0K3A2 FIA0K63E FIA0JETH FIA0JJ6C 

FIA0K3A1 FIA0K3AY FIA0H0VC FIA0JNJF 

FIA0K3AN FIA0JVRT FIA0K3AL FIA0JNJK 

FIA0JVRP FIA0HY8E FIA0J7VV FIA0JVRC 

FIA0JJ6F FIA0HY8N FIA0J7VP FIA0J7V4 

FIA0JJ6J FIA0J7V0 FIA0J7V9 FIA0JETF 

FIA0JVRV FIA0J7V3 FIA0HWJ8 FIA0HEG4 

FIA0H0VL FIA0J7V5 FIA0H0VA FIA0HWJ9 

FIA0K89T FIA0HY8H FIA0KCYL FIA0HWJ5 

FIA0K89Y FIA0HEG2 FIA0HY79 FIA0HWJ6 


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Federal Register / Vol. 78, No. 151 / Tuesday, August 6, 2013 / Rules and Regulations 47537 

FIGURE 1 TO PARAGRAPH (c)—TGB RADIAL GEARSHAFT P/N 1995M24P02 S/N’S—Continued 

FIA0JETL FIA0K62V FIA0KH9J FIA0J7VW 

FIA0JER8 FIA0HEGY FIA0HY8G FIA0J7VY 

FIA0J7WC FIA0HWKC FIA0HY8M FIA0J7VT 

FIA0JETE FIA0K3A0 FIA0HY8A FIA0J7WF 

FIA0K3AT FIA0JVRJ FIA0H0VG FIA0J7V6 

FIA0JJ59 FIA0K8AA FIA0K3AR FIA0K89G 

FIA0K3AW FIA0KCYT FIA0JETC FIA0K89K 

FIA0JVRN FIA0KH9T FIA0KH9W FIA0K89R 

FIA0JNH8 FIA0HEG1 FIA0JNJC FIA0KCYJ 

FIA0JETN FIA0HEG3 FIA0K63L FIA0JJ6G 

FIA0HY78 FIA0J7WJ FIA0KCYN FIA0JJ6A 

FIA0HY75 FIA0JER7 FIA0JVRG FIA0HY8K 

FIA0HEG0 FIA0JVRF FIA0HY8L FIA0HLY6 

FIA0KH9E FIA0K63K FIA0HY8J FIA0HLY0 

FIA0KH9F FIA0J7WK FIA0H0VH FIA0HLY1 

FIA0H0T9 FIA0JER5 FIA0H0VF FIA0HLY4 

FIA0HLY3 FIA0JETM 

(d) Unsafe Condition 

This AD was prompted by reports of 

three failures of TGB radial gearshafts 

which resulted in in-flight shutdowns 

(IFSDs). We are issuing this AD to 

prevent failure of the TGB radial 

gearshaft, which could result in IFSD of 

one or more engines, loss of thrust 

control, and damage to the airplane. 

(e) Compliance 

(1) Comply with this AD within the 

compliance times specified, unless 

already done. 

(2) Before further flight after the 

effective date of this AD, do not operate 

the airplane if more than one installed 

engine has a TGB radial gearshaft P/N 

and S/N listed in Figure 1 to paragraph 

(c) of this AD. 

(f) Mandatory Terminating Action 

No later than 60 days after the 

effective date of this AD, as terminating 

action to the requirements of paragraph 

(e) of this AD, replace all TGB radial 

gearshafts identified in Figure 1 to 

paragraph (c) of this AD that are 

installed on an airplane with TGB radial 

gearshafts that are eligible for 

installation. 

(g) Prohibition on Operation 

Sixty days after the effective date of 

this AD, do not operate any airplane 

that has an engine installed that has a 

TGB radial gearshaft P/N and S/N listed 

in Figure 1 to paragraph (c) of this AD. 

(h) Definition 

For the purposes of this AD, a TGB 

radial gearshaft eligible for installation 

is: 

(1) A TGB radial gearshaft P/N and S/ 

N, not listed in this AD or 

(2) A TGB radial gearshaft with an S/ 

N listed in paragraph (c) of this AD with 

part number 1995M24P04, 2205M61P01 

or 2205M61P02. 

(i) Alternative Methods of Compliance 

(AMOCs) 

The Manager, Engine Certification 

Office, FAA, may approve AMOCs for 

this AD. Use the procedures in 14 CFR 

39.19 to make your request. 

(j) Related Information 

(1) For more information about this 

AD, contact Carlos Fernandes, 

Aerospace Engineer, Engine 

Certification Office, FAA, 12 New 

England Executive Park, Burlington, MA 

01803; phone: 781–238–7189; fax: 781– 

238–7199; email: 

carlos.fernandes@faa.gov. 

(2) GE GE90–100 Series Alert Service 

Bulletin No. GE90–100 S/B 72–A0568, 

Revision 0, dated July 10, 2013; GE 

GE90–100 Series Service Bulletin (SB) 

No. GE90–100 S/B 72–0569, Revision 0, 

dated July 19, 2013; GE GE90–100 

Series SB No. GE90–100 S/B 72–0563, 

Revision 0, dated June 21, 2013, and 

Revision 1, dated July 10, 2013; GE 

GE90 SB No. GE90 S/B 72–1066, 

Revision 0, dated June 21, 2013; and GE 

GE90 SB No. GE90 S/B 72–1091, 

Revision 0, dated June 11, 2013, can be 

obtained from GE using the contact 

information in paragraph (j)(3) of this 

AD. 

(3) For service information identified 

in this AD, contact General Electric 

Company, One Neumann Way, Room 

285, Cincinnati, OH; phone: 513–552– 

3272; email: geae.aoc@ge.com. 

(4) 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. 

(k) Material Incorporated by Reference 

None. 

Issued in Burlington, Massachusetts, on 

July 25, 2013. 

Frank P. Paskiewicz, 

Acting Director, Aircraft Certification Service. 

[FR Doc. 2013–18840 Filed 8–5–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–1033; Directorate 

Identifier 2010–NM–266–AD; Amendment 

39–17504; AD 2013–13–16] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are superseding 

airworthiness directive (AD) 2005–07– 

04 for all Airbus Model A330–200 and 

–300 series airplanes, and Model A340– 

200 and –300 series airplanes. AD 2005– 

07–04 required repetitive inspections to 

detect discrepancies of the transfer 

tubes and the collar of the ball nut of the 

trimmable horizontal stabilizer actuator 

(THSA), and corrective action if 

necessary; repetitive inspections for 

discrepancies of the ball screw 

assembly, and corrective action if 

necessary; repetitive greasing of the 

THSA ball nut, and replacement of the 

THSA if necessary; and modification or 

replacement (as applicable) of the ball 

nut assembly, which ends certain 

repetitive inspections. This new AD 

removes certain inspections, revises 

certain actions, and adds airplanes to 

the applicability. This AD was 

prompted by several reports of 


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