4650 Federal Register / Vol. 77, No. 20 / Tuesday, January 31, 2012 / Rules and Regulations 

that it would require operators to inspect 

more often than required to ensure safety. We 

are issuing this AD to revise the definition of 

shop visit and to detect cracks in the lowpressure (LP) turbine stage 1, 2, and 3 discs, 

which could result in an uncontained release 

of LP turbine blades and damage to the 

airplane. 

(e) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(1) Initial Inspection Requirements 

At the next engine shop visit after the 

effective date of this AD, perform a visual 

and a fluorescent penetrant inspection of the 

LP turbine stage 1, 2, and 3 discs. 

(2) Repeat Inspection Requirements 

At each engine shop visit after 

accumulating 1,500 cycles since the last 

inspection of the LP turbine stage 1, 2 and 

3 discs, repeat the inspections specified in 

paragraph (e)(1) of this AD. 

(3) Remove Cracked Discs 

If you find cracks, remove the disc from 

service. 

(f) Definitions 

For the purpose of this AD, an ‘‘engine 

shop visit’’ is induction of an engine into the 

shop for any purpose where: 

(1) All the blades are removed from the 

high-pressure (HP) compressor discs and the 

HP turbine disc, or 

(2) All the blades are removed from the 

intermediate pressure turbine disc. 

(g) Alternative Methods of Compliance 

(AMOCs) 

The Manager, Engine Certification Office, 

FAA may approve AMOCs for this AD. Use 

the procedures found in 14 CFR 39.19 to 

make your request. 

(h) Related Information 

(1) Contact Alan Strom, Aerospace 

Engineer, Engine Certification Office, FAA, 

Engine & Propeller Directorate, 12 New 

England Executive Park, Burlington, MA 

01803; phone: (781) 238–7143; fax: (781) 

238–7199; email: alan.strom@faa.gov, for 

more information about this AD. 

(2) Refer to MCAI European Aviation 

Safety Agency Airworthiness Directive 2009– 

0244, dated November 9, 2009, and RollsRoyce plc Alert Service Bulletin No. RB.211– 

72–AG272 for related information. Contact 

Rolls-Royce plc, P.O. Box 31, Derby, DE24 

8BJ, United Kingdom; phone: 011 44 1332 

242424, fax: 011 44 1332 249936; or email: 

http://www.rollsroyce.com/contact/ 

civil_team.jsp, for a copy of this service 

information or download the publication 

from https://www.aeromanager.com. 

(i) Material Incorporated by Reference 

None. 

Issued in Burlington, Massachusetts, on 

January 25, 2012. 

Peter A. White, 

Manager, Engine & Propeller Directorate, 

Aircraft Certification Service. 

[FR Doc. 2012–1954 Filed 1–30–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–0068; Directorate 

Identifier 2010–NE–05–AD; Amendment 39– 

16930; AD 2012–02–07] 

RIN 2120–AA64 

Airworthiness Directives; General 

Electric Company Turbofan Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are superseding two 

existing airworthiness directives (ADs) 

for General Electric Company (GE) CF6– 

45 and CF6–50 series turbofan engines 

with certain low-pressure turbine (LPT) 

rotor stage 3 disks installed. The 

existing ADs currently require 

inspections of high-pressure turbine 

(HPT) and LPT rotors, engine checks, 

and vibration surveys. This new AD 

retains the requirements of the two ADs 

being superseded, adds an optional LPT 

rotor stage 3 disk removal after a failed 

HPT blade borescope inspection (BSI) or 

a failed engine core vibration survey, 

establishes a new lower life limit for the 

affected LPT rotor stage 3 disks, and 

requires removing these disks from 

service at times determined by a 

drawdown plan. This AD was prompted 

by the determination that a new lower 

life limit for the LPT rotor stage 3 disks 

is necessary. We are issuing this AD to 

prevent critical life-limited rotating 

engine part failure, which could result 

in an uncontained engine failure and 

damage to the airplane. 

DATES: This AD is effective March 6, 

2012. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of February 22, 2011 (76 FR 6323, 

February 4, 2011). 

ADDRESSES: For service information 

identified in this AD, contact General 

Electric Company, GE-Aviation, Room 

285, 1 Neumann Way, Cincinnati, OH 

45215, phone: (513) 552–3272; email: 

geae.aoc@ge.com. You may review 

copies of the referenced 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 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: 

Tomasz Rakowski, Aerospace Engineer, 

Engine Certification Office, FAA, Engine 

& Propeller Directorate, 12 New England 

Executive Park, Burlington, MA 01803; 

phone: (781) 238–7735; fax: (781) 238– 

7199; email: tomasz.rakowski@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to supersede AD 2011–02–07, 

Amendment 39–16580 (76 FR 6323, 

February 4, 2011) and AD 2011–18–01, 

Amendment 39–16783 (76 FR 52213, 

August 22, 2011). Those ADs apply to 

the specified products. The NPRM 

published in the Federal Register on 

October 19, 2011 (76 FR 64844). That 

NPRM proposed to retain the 

requirements of AD 2011–02–07 and AD 

2011–18–01, except that reporting to the 

FAA would no longer be required and 

there would be an optional LPT rotor 

stage 3 disk removal after a failed HPT 

blade BSI or a failed engine core 

vibration survey. That NPRM also 

proposed to establish a new lower life 

limit for the LPT rotor stage 3 disk part 

numbers listed in Table 1 of the 

proposed AD, and proposed to require 

removing these disks from service at 

times determined by a drawdown plan. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. The 

following presents the comments 

received on the proposal and the FAA’s 

response to each comment. 

Support for the NPRM as Written 

One commenter, The Boeing 

Company, supports the NPRM (76 FR 

64844, October 19, 2011) as written. 


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Request To Allow Credit for Vibration 

Surveys Performed in a Test Cell 

One commenter, MTU Maintenance 

Hannover GmbH, requested that we add 

a paragraph that allows credit for 

performing vibration surveys in a test 

cell, as meeting the AD vibration survey 

requirements. 

We agree. We added paragraph (k)(8) 

to the AD, which states ‘‘Vibration 

surveys carried out in an engine test cell 

as part of an engine manual 

performance run fulfill the vibration 

survey requirements of paragraphs (k)(2) 

through (k)(3) of this AD.’’ 

Request To Add a Requirement for Raw 

Exhaust Gas Temperature (EGT) Trend 

Data Point Exceedance 

One commenter, Evergreen 

International Airlines, requested that we 

add a requirement that two consecutive 

raw EGT trend data point exceedances 

must be confirmed by a corresponding 

shift of other engine parameters to 

trigger the HPT blade BSI. 

We partially agree. We agree that EGT 

system error should not force a BSI of 

turbine blades. But we disagree with 

troubleshooting the EGT raw data points 

once the EGT system error was ruled 

out. We added paragraph (o)(4) to the 

AD to state that, for the purposes of this 

AD, a raw EGT trend data point above 

the smoothed average is a confirmed 

temperature reading over the rolling 

average of EGT readings that is not a 

result of EGT system error. We also 

rearranged the wording in paragraph (iv) 

in Table 2 of the AD for clarification. 

Correction to Engine Model CF6–50– 

E2D 

Since we issued the NPRM (76 FR 

67844, October 19, 2011), we discovered 

that, in applicability paragraph (c), 

engine model CF6–50–E2D was 

incorrect. We corrected it to read CF6– 

50E2B in the AD. 

Conclusion 

We reviewed the relevant data, 

considered the comments received, and 

determined that air safety and the 

public interest require adopting the AD 

with the changes described previously. 

We have determined that these minor 

changes: 

• Are consistent with the intent that 

was proposed in the NPRM (76 FR 

64844, October 19, 2011) for correcting 

the unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the NPRM. 

We also determined that these 

changes will not increase the economic 

burden on any operator or increase the 

scope of the AD. 

Costs of Compliance 

We estimate that this AD will affect 

387 CF6–45 and CF6–50 series turbofan 

engines installed on airplanes of U.S. 

registry. We also estimate that it will 

take about 8 work-hours to perform the 

HPT blade inspection, 6 work-hours to 

perform a vibration survey, 4 workhours to perform an ultrasonic 

inspection, 2 work-hours to perform an 

EGT resistance check, 1 work-hour to 

perform an EGT thermocouple 

inspection, and 7 work-hours to clean 

and perform an fluorescent-penetrant 

inspection of the LPT rotor stage 3 disk 

for each engine. The average labor rate 

is $85 per work-hour. The cost estimate 

for the work just described was covered 

in the two ADs we are superseding. For 

this AD, we estimate that a replacement 

LPT rotor stage 3 disk prorated part cost 

is $75,000. Based on these figures, we 

estimate the total cost of this AD to U.S. 

operators to be $29,025,000. 

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 have 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 

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] 

The FAA amends § 39.13 by removing 

airworthiness directive (AD) 2011–02– 

07, Amendment 39–16580 (76 FR 6323, 

February 4, 2011) and AD 2011–18–01, 

Amendment 39–16783 (76 FR 52213, 

August 22, 2011), and adding the 

following new AD: 

2012–02–07 General Electric Company: 

Amendment 39–16930; Docket No. 

FAA–2010–0068; Directorate Identifier 

2010–NE–05–AD. 

(a) Effective Date 

This airworthiness directive (AD) is 

effective March 6, 2012. 

(b) Affected ADs 

This AD supersedes AD 2011–02–07, 

Amendment 39–16580 (76 FR 6323, February 

4, 2011) and AD 2011–18–01, Amendment 

39–16783 (76 FR 52213, August 22, 2011). 

(c) Applicability 

This AD applies to General Electric 

Company (GE) CF6–45A, CF6–45A2, CF6– 

50A, CF6–50C, CF6–50CA, CF6–50C1, CF6– 

50C2, CF6–50C2B, CF6–50C2D, CF6–50E, 

CF6–50E1, CF6–50E2, and CF6–50E2B 

turbofan engines, including engines marked 

on the engine data plate as CF6–50C2–F and 

CF6–50C2–R, with any of the low-pressure 

turbine (LPT) rotor stage 3 disk part numbers 

listed in Table 1 of this AD installed. 


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TABLE 1—APPLICABLE LPT ROTOR STAGE 3 DISK PART NUMBERS

9061M23P06 9061M23P07 9061M23P08 9061M23P09 9224M75P01 

9061M23P10 1473M90P01 1473M90P02 1473M90P03 1473M90P04 

9061M23P12 9061M23P14 9061M23P15 9061M23P16 1479M75P01 

1479M75P02 1479M75P03 1479M75P04 1479M75P05 1479M75P06 

1479M75P07 1479M75P08 1479M75P09 1479M75P11 1479M75P13 

1479M75P14 N/A N/A N/A N/A 

(d) Unsafe Condition 

This AD was prompted by the 

determination that a new lower life limit for 

the LPT rotor stage 3 disks listed in Table 1 

of this AD is necessary. We are issuing this 

AD to prevent critical life-limited rotating 

engine part failure, which could result in an 

uncontained engine failure and damage to 

the airplane. 

(e) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(f) Borescope Inspections (BSI) of HighPressure Turbine (HPT) Rotor Stage 1 and 

Stage 2 Blades 

For the BSIs required by paragraphs (f)(1), 

(f)(2), and (f)(3) of this AD, inspect the blades 

from the forward and aft directions. Inspect 

all areas of the blade airfoil. Your inspection 

must include blade leading and trailing edges 

and their convex and concave airfoil 

surfaces. Inspect for signs of impact, 

cracking, burning, damage, or distress. 

(1) Perform an initial BSI of the HPT rotor 

stage 1 and stage 2 blades within 10 cycles 

after the effective date of this AD. 

(2) Thereafter, repeat the BSI of the HPT 

rotor stage 1 and stage 2 blades within every 

75 cycles since last inspection (CSLI). 

(3) Borescope-inspect the HPT rotor stage 

1 and stage 2 blades within the cycle limits 

after the engine has experienced any of the 

events specified in Table 2 of this AD. 

(4) Remove any engine from service before 

further flight if the engine fails any of the 

BSIs required by this AD. 

TABLE 2—CONDITIONAL BSI CRITERIA

If the engine has experienced: Then borescope-inspect: 

(i) An exhaust gas temperature (EGT) above redline. ................................................................................. Within 10 cycles. 

(ii) A shift in the smoothed EGT trending data that exceeds 18 °F (10 °C), but is less than or equal to 

36 °F (20 °C).

Within 10 cycles. 

(iii) A shift in the smoothed EGT trending data that exceeds 36 °F (20 °C) ............................................... Before further flight. 

(iv) Two consecutive raw EGT trend data points that exceed 18 °F (10 °C), but is less than or equal to 

36 °F (20 °C), above the smoothed average.

Within 10 cycles. 

(v) Two consecutive raw EGT trend data points that exceed 36 °F (20 °C) above the smoothed average Before further flight. 

(g) Actions Required for Engines With 

Damaged HPT Rotor Blades 

For those engines that fail any BSI 

requirements of this AD, before returning the 

engine to service: 

(1) Remove the LPT rotor stage 3 disk from 

service; or 

(2) Perform a fluorescent-penetrant 

inspection (FPI) of the inner diameter surface 

forward cone body (forward spacer arm) of 

the LPT rotor stage 3 disk as specified in 

paragraphs (l)(1)(i) through (l)(1)(iii) of this 

AD. 

(h) EGT Thermocouple Probe Inspections 

(1) Inspect the EGT thermocouple probe for 

damage within 50 cycles after the effective 

date of this AD or before accumulating 750 

CSLI, whichever occurs later. 

(2) Thereafter, re-inspect the EGT 

thermocouple probe for damage within every 

750 CSLI. 

(3) If any EGT thermocouple probe shows 

wear through the thermocouple guide sleeve, 

remove and replace the EGT thermocouple 

probe before further flight, and ensure the 

turbine mid-frame liner does not contact the 

EGT thermocouple probe. 

(i) EGT System Resistance Check Inspections 

(1) Perform an EGT system resistance 

check within 50 cycles from the effective 

date of this AD or before accumulating 750 

cycles since the last resistance check on the 

EGT system, whichever occurs later. 

(2) Thereafter, repeat the EGT system 

resistance check within every 750 cycles 

since the last resistance check. 

(3) Remove and replace, or repair any EGT 

system component that fails the resistance 

system check before further flight. 

(j) Ultrasonic Inspection (UI) of the LPT 

Rotor Stage 3 Disk Forward Spacer Arm 

Within 75 cycles after the effective date of 

this AD, perform a UI of the forward spacer 

arm of the LPT rotor stage 3 disk. Use 

Appendix A of GE Service Bulletin (SB) No. 

CF6–50 S/B 72–1312, Revision 1, dated 

October 18, 2010, paragraph 4. except for 

paragraph 4.(12), to do the UI. 

(k) Engine Core Vibration Survey 

(1) Within 75 cycles after the effective date 

of this AD, perform an initial engine core 

vibration survey. 

(2) Use about a one-minute acceleration 

and a one-minute deceleration of the engine 

between ground idle and 84% N2 (about 

8,250 rpm) to perform the engine core 

vibration survey. 

(3) Use a spectral/trim balance analyzer or 

equivalent to measure the N2 rotor vibration. 

(4) If the vibration level is above 5 mils 

Double Amplitude then, before further flight, 

remove the engine from service. 

(5) For those engines that fail any engine 

core vibration survey requirements of this 

AD, then before returning the engine to 

service: 

(i) Remove the LPT rotor stage 3 disk from 

service; or 

(ii) Perform an FPI of the inner diameter 

surface forward spacer arm of the LPT rotor 

stage 3 disk as specified in paragraphs 

(l)(1)(i) through (l)(1)(iii) of this AD. 

(6) Thereafter, within every 350 cycles 

since the last engine core vibration survey, 

perform the engine core vibration survey as 

required in paragraphs (k)(1) through (k)(5) of 

this AD. 

(7) If the engine has experienced any 

vibration reported by maintenance or flight 

crew that is suspected to be caused by the 

engine core (N2), perform the engine core 

vibration survey as required in paragraphs 

(k)(1) through (k)(5) of this AD within 10 

cycles after the report. 

(8) Vibration surveys carried out in an 

engine test cell as part of an engine manual 

performance run fulfill the vibration survey 

requirements of paragraphs (k)(2) through 

(k)(3) of this AD. 

(l) Initial and Repetitive FPI of LPT Rotor 

Stage 3 Disks 

(1) At the next shop visit after the effective 

date of this AD: 

(i) Clean the LPT rotor stage 3 disk forward 

spacer arm, including the use of a wetabrasive blast, to eliminate residual or 

background fluorescence. 

(ii) Perform an FPI of the LPT rotor stage 

3 disk forward spacer arm for cracks and for 

a band of fluorescence. Include all areas of 

the disk forward spacer arm and the inner 

diameter surface forward spacer arm of the 

LPT rotor stage 3 disk. 


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(iii) Remove the disk from service before 

further flight if a crack or a band of 

fluorescence is present. 

(2) Thereafter, clean and perform an FPI of 

the LPT rotor stage 3 disk forward spacer 

arm, as specified in paragraphs (l)(1)(i) 

through (l)(1)(iii) of this AD, at each engine 

shop visit that occurs after 1,000 cycles since 

the last FPI of the LPT rotor stage 3 disk 

forward spacer arm. 

(m) Removal of LPT Rotor Stage 3 Disks 

Remove LPT rotor stage 3 disks listed in 

Table 1 from service as follows: 

(1) For disks that have fewer than 3,200 

flight cycles since new (CSN) on the effective 

date of this AD, remove the disk from service 

before exceeding 6,200 CSN. 

(2) For disks that have 3,200 CSN or more 

on the effective date of this AD, do the 

following: 

(i) If the engine has a shop visit before the 

disk exceeds 6,200 CSN, remove the disk 

from service before exceeding 6,200 CSN. 

(ii) If the engine does not have a shop visit 

before the disk exceeds 6,200 CSN, remove 

the disk from service at the next shop visit 

after 6,200 CSN, not to exceed 3,000 cycles 

from the effective date of this AD. 

(n) Installation Prohibition 

(1) After the effective date of this AD, do 

not install or reinstall in any engine any LPT 

rotor stage 3 disk that exceeds the new life 

limit of 6,200 CSN. 

(2) Remove from service any LPT rotor 

stage 3 disk that is installed or re-installed 

after the effective date of this AD, before the 

disk exceeds the new life limit of 6,200 CSN. 

(o) Definitions 

(1) For the purposes of this AD, an EGT 

above redline is a confirmed overtemperature indication that is not a result of 

EGT system error. 

(2) For the purposes of this AD, a shift in 

the smoothed EGT trending data is a shift in 

a rolling average of EGT readings that can be 

confirmed by a corresponding shift in the 

trending of fuel flow or fan speed/core speed 

(N1/N2) relationship. You can find further 

guidance about evaluating EGT trend data in 

GE Company Service Rep Tip 373 

’’Guidelines For Parameter Trend 

Monitoring.’’ 

(3) For the purposes of this AD, an engine 

shop visit is the induction of an engine into 

the shop after the effective date of this AD, 

where the separation of a major engine flange 

occurs; except the following maintenance 

actions, or any combination, are not 

considered engine shop visits: 

(i) Induction of an engine into a shop 

solely for removal of the compressor top or 

bottom case for airfoil maintenance or 

variable stator vane bushing replacement. 

(ii) Induction of an engine into a shop 

solely for removal or replacement of the stage 

1 fan disk. 

(iii) Induction of an engine into a shop 

solely for replacement of the turbine rear 

frame. 

(iv) Induction of an engine into a shop 

solely for replacement of the accessory 

gearbox or transfer gearbox, or both. 

(v) Induction of an engine into a shop 

solely for replacement of the fan forward 

case. 

(4) For the purposes of this AD, a raw EGT 

trend data point above the smoothed average 

is a confirmed temperature reading over the 

rolling average of EGT readings that is not a 

result of EGT system error. 

(p) Previous Credit 

(1) A BSI performed before the effective 

date of this AD using AD 2010–06–15, 

Amendment 39–16240 (75 FR 12661, March 

17, 2010) or AD 2010–12–10, Amendment 

39–16331 (75 FR 32649, June 9, 2010) or AD 

2011–02–07, Amendment 39–16580 (76 FR 

6323, February 4, 2011) within the last 75 

cycles, satisfies the initial BSI requirement in 

paragraph (f)(1) of this AD. 

(2) A UI performed before the effective date 

of this AD using AD 2011–02–07, 

Amendment 39–16580 (76 FR 6323, February 

4, 2011) or GE SB No. CF6–50 S/B 72–1312, 

dated August 9, 2010 or GE SB No. CF6–50 

S/B 72–1312 Revision 1, dated October 18, 

2010, satisfies the inspection requirement in 

paragraph (j) of this AD. 

(3) An engine core vibration survey 

performed before the effective date of this AD 

using AD 2011–02–07, Amendment 39– 

16580 (76 FR 6323, February 4, 2011) or GE 

SB No. CF6–50 S/B 72–1313, dated August 

9, 2010 or GE SB No. CF6–50 S/B 72–1313 

Revision 1, dated October 18, 2010, within 

the last 350 cycles, satisfies the initial survey 

requirement in paragraphs (k)(1) through 

(k)(5) of this AD. 

(4) An FPI of the LPT rotor stage 3 disk 

forward spacer arm performed before the 

effective date of this AD using AD 2011–18– 

01, Amendment 39–16783 (75 FR 52213, 

August 22, 2011), within the last 1,000 flight 

cycles of the LPT rotor stage 3 disk, satisfies 

the initial inspection requirements in 

paragraphs (l)(1)(i) through (l)(1)(iii) of this 

AD. 

(q) Alternative Methods of Compliance 

(AMOCs) 

(1) AMOCs previously approved for AD 

2010–06–15, Amendment 39–16240 (75 FR 

12661, March 17, 2010) are not approved for 

this AD. However, AMOCs previously 

approved for AD 2010–12–10, Amendment 

39–16331 (75 FR 32649, June 9, 2010), AD 

2011–02–07, Amendment 39–16580 (76 FR 

6323, February 4, 2011), or AD 2011–18–01, 

Amendment 39–16783 (76 FR 52213, August 

22, 2011) are approved for this AD. 

(2) The Manager, Engine Certification 

Office, may approve alternative methods of 

compliance for this AD. Use the procedures 

found in 14 CFR 39.19 to make your request. 

(r) Related Information 

(1) For more information about this AD, 

contact Tomasz Rakowski, Aerospace 

Engineer, Engine Certification Office, FAA, 

Engine & Propeller Directorate, 12 New 

England Executive Park, Burlington, MA 

01803; phone: (781) 238–7735; fax: (781) 

238–7199; email: tomasz.rakowski@faa.gov. 

(2) For service information identified in 

this AD, contact General Electric Company, 

GE–Aviation, Room 285, 1 Neumann Way, 

Cincinnati, OH 45215, phone: (513) 552– 

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

review copies of the referenced 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. 

(s) Material Incorporated by Reference 

(1) You must use the following service 

information to do the UIs required by this 

AD, unless the AD specifies otherwise. The 

Director of the Federal Register approved the 

incorporation by reference (IBR) under 5 

U.S.C. 552(a) and 1 CFR part 51 of the 

following service information on July 22, 

2011: General Electric Company Service 

Bulletin No. CF6–50 S/B 72–1312 Revision 1, 

dated October 18, 2010. 

(2) For service information identified in 

this AD, contact General Electric Company, 

GE–Aviation, Room 285, 1 Neumann Way, 

Cincinnati, OH 45215, phone: (513) 552– 

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

(3) You may review copies of the 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. 

(4) You may also review copies of the 

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 Burlington, Massachusetts, on 

January 20, 2012. 

Peter A. White, 

Manager, Engine & Propeller Directorate, 

Aircraft Certification Service. 

[FR Doc. 2012–1953 Filed 1–30–12; 8:45 am] 

BILLING CODE 4910–13–P 

SOCIAL SECURITY ADMINISTRATION 

20 CFR Parts 404 and 416 

[Docket No. SSA–2011–0094] 

Requiring Electronic Filing of Select 

Appeals by Certain Claimant 

Representatives 

AGENCY: Social Security Administration. 

ACTION: Notification of implementation 

of requirement. 

SUMMARY: We are announcing the 

requirement that appointed 

representatives file certain appeals 

using our electronic systems in matters 

for which the representatives request 

direct fee payment. This is the first 

service required under the regulation we 

published on September 12, 2011 (76 FR 

56107), Requiring Use of Electronic 

Services. 

DATES: The effective date of this 

notification of implementation of 

requirement is March 16, 2012. 


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