16526 Federal Register / Vol. 76, No. 57 / Thursday, March 24, 2011 / Rules and Regulations 

an annual effect on the economy of $100 

million or more; a major increase in 

costs or prices; or significant adverse 

effects on competition, employment, 

investment, productivity, innovation, or 

on the ability of United States-based 

companies to compete with foreignbased companies in domestic and 

export markets. 

Congressional Review Act 

This action pertains to agency 

organization, procedures, and practices 

and does not substantially affect the 

rights or obligations of non-agency 

parties. Accordingly, it is not a ‘‘rule’’ as 

that term is used by the Congressional 

Review Act (Subtitle E, SBREFA). 

Therefore, the reporting requirement of 

5 U.S.C. 801 does not apply. 

Executive Order 12866 

This rule has been drafted and 

reviewed in accordance with Executive 

Order 12866, section 1(b), Principles of 

Regulation. The Department of Justice 

has determined that this rule is not a 

‘‘significant regulatory action’’ under 

section 3(f) of Executive Order 12866, 

Regulatory Planning and Review. 

Accordingly, this rule has not been 

reviewed by the Office of Management 

and Budget (OMB). 

Executive Order 13132 

This rule will not have substantial 

direct effects 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. Therefore, in 

accordance with section 6 of Executive 

Order 13132, the Department of Justice 

has determined that this rule does not 

have sufficient federalism implications 

to warrant a federalism summary impact 

statement. 

Executive Order 12988 

This rule meets the applicable 

standards set forth in sections 3(a) and 

3(b)(2) of Executive Order 12988, Civil 

Justice Reform. 

List of Subjects in Part 1274a 

Administrative practice and 

procedure, Immigration. 

PART 1247a—[AMENDED] 

■ Accordingly, the interim rule 

amending 8 CFR part 1274a that was 

published at 74 FR 2337 on January 15, 

2009, is adopted as a final rule without 

change. 

Dated: March 18, 2011. 

Eric H. Holder, Jr., 

Attorney General. 

[FR Doc. 2011–6961 Filed 3–23–11; 8:45 am] 

BILLING CODE 4410–30–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–0452; Directorate 

Identifier 98–ANE–80–AD; Amendment 39– 

16639; AD 2011–07–02] 

RIN 2120–AA64 

Airworthiness Directives; Pratt & 

Whitney JT8D–209, –217, –217A, 

–217C, and –219 Series Turbofan 

Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are superseding an 

existing airworthiness directive (AD) for 

the products listed above. That AD 

currently requires initial and repetitive 

torque inspections of the 3rd stage and 

4th stage low-pressure turbine (LPT) 

blades for shroud notch wear and 

replacement of the blade if wear limits 

are exceeded. That AD also requires 

replacing LPT-to-exhaust case bolts and 

nuts with bolts and nuts made of 

Tinidur material. This new AD requires 

the same torque inspection, blade, and 

Tinidur nut replacement actions, but 

requires replacement of the LPT-toexhaust case bolts with longer bolts 

made of Tinidur material. This AD also 

requires installation of crushable sleeve 

spacers on the bolts. This AD was 

prompted by nine reports of failure of 

Tinidur material LPT-to-exhaust case 

bolts, as a result of blade failure, since 

AD 2005–02–03 became effective. We 

are issuing this AD to prevent turbine 

blade failures that could result in 

uncontained engine debris and damage 

to the airplane. 

DATES: This AD is effective April 28, 

2011. The Director of the Federal 

Register approved the incorporation by 

reference of certain publications listed 

in the AD as of April 28, 2011. 

ADDRESSES: For service information 

identified in this AD, contact Pratt & 

Whitney, 400 Main St., East Hartford, 

CT 06108; phone: (860) 565–8770, fax: 

(860) 565–4503. 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: Ian 

Dargin, Aerospace Engineer, Engine 

Certification Office, FAA, Engine and 

Propeller Directorate, 12 New England 

Executive Park; Burlington, MA 01803; 

phone: 781–238–7178; fax: 781–238– 

7199; e-mail: ian.dargin@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to supersede AD 2005–02–03, 

Amendment 39–13948 (70 FR 3867, 

January 27, 2005). That AD applies to 

the specified products. The NPRM 

published in the Federal Register on 

July 1, 2010 (75 FR 38052). That NPRM 

proposed the same torque inspection, 

blade, and LPT-to-exhaust case retaining 

nut replacement actions as the 

superseded AD, but would also require 

replacement of the LPT-to-exhaust case 

bolts with longer bolts made of Tinidur 

material. That NPRM also proposed to 

require installation of crushable sleeve 

spacers on the LPT-to-exhaust case 

bolts. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

have considered the comments received. 

Request to Include Other FAAApproved Methods 

One commenter, American Airlines, 

requested that paragraph (s) of the 

proposed AD be revised to include other 

FAA-approved methods not published 

in the OEM’s engine manual. 

We agree and changed paragraph (t) to 

state: ‘‘For the purpose of this AD, 

‘‘refurbished’’ is defined as restoration of 

the shrouds and/or blade re-twist per 

the JT8D–200 Engine Manual, Part No. 

773128, or per an operator’s approved 

manual system.’’ 


jdjones on DSK8KYBLC1PROD with RULES
Federal Register / Vol. 76, No. 57 / Thursday, March 24, 2011 / Rules and Regulations 16527 

Request To Allow Compliance to Alert 

Service Bulletin (ASB) Revision 5 or 

Revision 6 

One commenter, Delta Airlines, 

requested that we allow compliance 

using either PW ASB No. JT8D A6224, 

Revision 5, dated June 11, 2004, or 

Revision 6, dated May 3, 2007. They 

stated that their experience with backto-back testing both with and without 

notch gauge support did not show any 

measurable differences. Revision 6 

introduced the notch gauge support. 

We do not agree. Revision 6 of the 

ASB provides an improved method of 

inspection that ensures that the arm of 

the inspection tool is parallel to the 

engine center line during the inspection. 

This yields more accurate inspection 

results. We do allow previous credit 

using Revision 5 of the ASB for 

performing an initial inspection before 

the effective date of the AD. We did not 

change the AD. 

Request To Change ‘‘Modified’’ to ‘‘AsCast’’ 

One commenter, Turborreactores S.A. 

de C.V., stated that in Table 4, item 5, 

the term ‘‘Modified’’ should be changed 

to ‘‘As-Cast’’ to correctly identify the 

blades. 

We do not agree. PW Service Bulletin 

No. JT8D 6090 is referenced in ASB No. 

JT8D A6224. PW Service Bulletin No. 

JT8D 6090 released both a new ‘‘as-cast’’ 

blade and instructions for a field 

modification of existing blades, which 

could result in ‘‘modified’’ blades in the 

field. We did not change the AD. 

Suggestion That Proposed AD Does Not 

Address Root Cause 

One commenter, Scandinavian 

Airlines System, suggested that the 

proposed AD does not address the root 

cause of LPT failures, which they state 

is stage 3/stage 4 LPT turbine blades 

shroud wear and subsequent high-cycle 

fatigue. They suggested that the 

proposed AD will probably improve 

containment with the new design of 

longer case bolts with crushable sleeves, 

but they will not eliminate the root 

cause of LPT failures. 

We do not agree. This AD addresses 

the stage 3 and stage 4 turbine blade 

shroud notch wear with initial and 

repetitive torque inspections. The longer 

Tinidur material LPT case bolts with 

crushable spacers will prevent bolt 

fractures and/or case ripping near the 

flange, and will result in only a 2.02 

pound weight increase. We did not 

change 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 change described previously. 

We have determined that this change 

will neither increase the economic 

burden on any operator nor increase the 

scope of the AD. 

Costs of Compliance 

We estimate that this AD will affect 

1,143 engines installed on airplanes of 

U.S. registry. We also estimate that it 

will take about 1 work-hour per engine 

to perform the 3rd and 4th stage LPT 

blade inspection, and 1.5 work-hours 

per engine to replace the LPT-to-exhaust 

case bolts and nuts and install the 

crushable sleeve spacers. Required 

bolts, nuts, and sleeve spacers will cost 

about $4,576 per engine. We anticipate 

that 61 engines will also require blade 

replacement each year. Required blades 

will cost about $131,560 per engine. The 

average labor rate is $85 per work-hour. 

Based on these figures, we estimate the 

total cost of the AD to U.S. operators to 

be $13,617,671. 

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); and 

(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 

removing airworthiness directive (AD) 

2005–02–03, Amendment 39–13948 (70 

FR 3867, January 27, 2005), and adding 

the following new AD: 

2011–07–02 Pratt & Whitney: Amendment 

39–16639. Docket No. FAA–2010–0452; 

Directorate Identifier 98–ANE–80–AD. 

Effective Date 

(a) This airworthiness directive (AD) is 

effective April 28, 2011. 

Affected ADs 

(b) This AD supersedes AD 2005–02–03, 

Amendment 39–13948. 

Applicability 

(c) This AD applies to Pratt & Whitney 

(PW) JT8D–209, –217, –217A, –217C, and 

–219 series turbofan engines. These engines 

are installed on, but not limited to, Boeing 

727 series and McDonnell Douglas MD–80 

series airplanes. 

Unsafe Condition 

(d) This AD results from nine reports of 

failure of Tinidur material LPT-to-exhaust 

case bolts, as a result of blade failure, since 

AD 2005–02–03 became effective. We are 

issuing this AD to prevent turbine blade 

failures that could result in uncontained 

engine debris and damage to the airplane. 

Compliance 

(e) You are responsible for having the 

actions required by this AD performed within 

the compliance times specified unless the 

actions have already been done. 


jdjones on DSK8KYBLC1PROD with RULES
16528 Federal Register / Vol. 76, No. 57 / Thursday, March 24, 2011 / Rules and Regulations 

Requirements of AD 2005–02–03 

Initial Torque Inspection for JT8D–209, 

–217, and –217A Engines 

(f) For JT8D–209, –217, and –217A engines, 

perform the initial torque inspection of 3rd 

and 4th stage LPT blades for shroud notch 

wear. Use the procedures described in 

Accomplishment Instructions, Part 1, 

Paragraphs 1 through 3, of PW Alert Service 

Bulletin (ASB) No. JT8D A6224, Revision 6, 

dated May 3, 2007, at the applicable 

threshold in the following Table 1: 

TABLE 1—INITIAL TORQUE INSPECTION THRESHOLD FOR JT8D–209, –217, AND –217A ENGINES

Blade type 

Hours time-in-service 

(TIS) as of March 3, 2005 

(the effective date of AD 

2005–02–03) 

Inspection threshold 

(1) New pre-Service Bulletin (SB) No. 5867 (small notch) 

3rd stage turbine blades.

Any number ........................ Within 6,000 hours TIS. 

(2) Refurbished pre-SB No. 5867 (small notch) 3rd stage 

turbine blades.

(i) Fewer than 3,000 ........... Within 4,000 hours TIS. 

(ii) 3,000 or more ................ Within 6,000 hours TIS, or within 1,000 hours TIS from 

March 3, 2005, whichever occurs first. 

(3) New post-SB No. 5867 (large notch) 3rd stage turbine blades.Any number ........................ Within 10,000 hours TIS. 

(4) Refurbished post-SB No. 5867 (large notch) 3rd 

stage turbine blades.

(i) Fewer than 6,000 ........... Within 7,000 hours TIS. 

(ii) 6,000 or more ................ Within 8,000 hours TIS, or within 1,000 hours TIS from 

March 3, 2005, whichever occurs first. 

(5) New pre-SB No. 6029 (small notch) 4th stage turbine 

blades.

Any number ........................ Within 6,000 hours TIS. 

(6) Refurbished pre-SB No. 6029 (small notch) 4th stage 

turbine blades.

(i) Fewer than 3,000 ........... Within 4,000 hours TIS. 

(ii) 3,000 or more ................ Within 6,000 hours TIS, or within 1,000 hours TIS from 

March 3, 2005, whichever occurs first. 

(7) New post-SB No. 6029 or new post-SB No. 6308 

(large notch) 4th stage turbine blades.

Any number ........................ Within 10,000 hours TIS. 

(8) Refurbished post-SB No. 6029 or refurbished postSB No. 6308 (large notch) 4th stage turbine blades.(i) Fewer than 6,000 ........... Within 7,000 hours TIS. 

(ii) 6,000 or more ................ Within 8,000 hours TIS, or within 1,000 hours TIS from 

March 3, 2005, whichever occurs first. 

Repetitive Torque Inspections for JT8D–209, 

–217, and –217A Engines 

(g) For JT8D–209, –217, and –217A 

engines, perform repetitive torque 

inspections of 3rd and 4th stage LPT blades 

for shroud notch wear. Use the procedures 

described in Accomplishment Instructions, 

Part 1, Paragraph 1 of PW ASB No. JT8D 

A6224, Revision 6, dated May 3, 2007, at the 

applicable intervals in the following Table 2 

and Table 3: 

TABLE 2—3RD STAGE REPETITIVE TORQUE INSPECTION INTERVALS FOR JT8D–209, –217, AND –217A ENGINES

Inspection torque readings Number of readings Disposition 

Greater than or equal to 15 LB–IN (1.695 N.m) .............. All ....................................... Repeat torque inspection within 1,000 hours TIS since 

last inspection. 

Less than 15 LB–IN (1.695 N.m) but greater than or 

equal to 10 LB–IN (1.130 N.m).

One or more ....................... Repeat torque inspection within 500 hours TIS since 

last inspection. 

Less than 10 LB–IN (1.130 N.m) but greater than or 

equal to 5 LB–IN (0.565 N.m).

One to three ....................... Repeat torque inspection within 125 hours TIS since 

last inspection. 

Less than 10 LB–IN (1.130 N.m) but greater than or 

equal to 5 LB–IN (0.565 N.m).

Four or more ...................... Remove engine from service within 20 hours TIS since 

last inspection. 

Less than 5 LB–IN (0.565 N.m) ....................................... One or more ....................... Remove engine from service within 20 hours TIS since 

last inspection. 

TABLE 3—4TH STAGE REPETITIVE TORQUE INSPECTION INTERVALS FOR JT8D–209, –217, AND –217A ENGINES

Inspection torque readings Number of readings Disposition 

Greater than or equal to 15 LB–IN (1.695 N.m) .............. All ....................................... Repeat torque inspection within 1,000 hours TIS since 

last inspection. 

Less than 15 LB–IN (1.695 N.m) but greater than or 

equal to 10 LB–IN (1.130 N.m).

One or more ....................... Repeat torque inspection within 500 hours TIS since 

last inspection. 

Less than 10 LB–IN (1.130 N.m) but greater than or 

equal to 5 LB–IN (0.565 N.m).

One to six ........................... Repeat torque inspection within 125 hours TIS since 

last inspection. 

Less than 10 LB–IN (1.130 N.m) but greater than or 

equal to 5 LB–IN (0.565 N.m).

Seven or more ................... Remove engine from service within 20 hours TIS since 

last inspection. 

Less than 5 LB–IN (0.565 N.m) ....................................... One or more ....................... Remove engine from service within 20 hours TIS since 

last inspection. 


jdjones on DSK8KYBLC1PROD with RULES
Federal Register / Vol. 76, No. 57 / Thursday, March 24, 2011 / Rules and Regulations 16529 

(h) Subsequent repeat inspection intervals 

must not exceed the previous inspection 

interval. 

JT8D–209, –217, and –217A Engines 

Removed From Service 

(i) JT8D–209, –217, and –217A engines 

removed from service may be returned to 

service after a detailed inspection and repair 

or replacement of all blades of the failed 

stage, that exceed Engine Manual limits, is 

done. Information on repairing or replacing 

turbine blades can be found in Sections 72– 

53–12 through 72–53–13 of the JT8D–200 

Engine Manual, Part No. 773128. 

Initial Inspection for JT8D–217C and –219 

Engines 

(j) For JT8D–217C and –219 engines, 

perform the initial torque inspection of 4th 

stage LPT blades for shroud notch wear. Use 

the procedures described in Accomplishment 

Instructions, Part 2, Paragraphs 1 through 3 

of PW ASB No. JT8D A6224, Revision 6, 

dated May 3, 2007, at the applicable 

threshold in the following Table 4: 

TABLE 4—INITIAL TORQUE INSPECTION THRESHOLD FOR JT8D–217C AND –219 ENGINES

Blade type TIS as of March 3, 2005 Inspection threshold 

(1) New pre-SB No. 6090 (small notch) 4th stage turbine 

blades.

Any number ........................ Within 5,000 hours TIS. 

(2) Refurbished pre-SB No. 6090 (small notch) 4th stage 

turbine blades.

(i) Fewer than 3,000 ........... Within 4,000 hours TIS. 

(ii) 3,000 or more ................ Within 5,000 hours TIS, or within 1,000 hours TIS from 

March 3, 2005, whichever occurs first. 

(3) New post-SB No. 6090, new post-SB No. 6402, or 

new post-SB No. 6412 (large notch) 4th stage turbine 

blades.

Any number ........................ Within 10,000 hours TIS. 

(4) Refurbished ‘‘As-Cast’’ post-SB No. 6090, post-SB 

No. 6402, or post-SB No. 6412 (large notch) 4th stage 

turbine blades.

Any number ........................ Within 7,000 hours TIS. 

(5) Refurbished ‘‘Modified’’ post-SB No. 6090, post-SB 

No. 6402, or post-SB No. 6412 (large notch) 4th stage 

turbine blades.

(i) Fewer than 3,000 ........... Within 4,000 hours TIS. 

(ii) 3,000 or more ................ Within 7,000 hours TIS, or within 1,000 hours TIS from 

March 3, 2005, whichever occurs first. 

Repetitive Torque Inspections for JT8D–217C 

and –219 Engines 

(k) For JT8D–217C and –219 engines, 

perform repetitive torque inspections of 4th 

stage LPT blades for shroud notch wear. Use 

the procedures described in Accomplishment 

Instructions, Part 2, Paragraph 1 of PW ASB 

No. JT8D A6224, Revision 6, dated May 3, 

2007, at the applicable intervals in the 

following Table 5: 

TABLE 5—REPETITIVE TORQUE INSPECTION INTERVALS FOR JT8D–217C AND –219 ENGINES

Inspection torque readings Number of readings Disposition 

Greater than or equal to 15 LB–IN (1.695 N.m) .............. All ....................................... Repeat torque inspection within 1,000 hours TIS since 

last inspection. 

Less than 15 LB–IN (1.695 N.m) but greater than or 

equal to 10 LB–IN (1.130 N.m).

One or more ....................... Repeat torque inspection within 500 hours TIS since 

last inspection. 

Less than 10 LB–IN (1.130 N.m) but greater than or 

equal to 5 LB–IN (0.565 N.m).

One to six ........................... Repeat torque inspection within 125 hours TIS since 

last inspection. 

Less than 10 LB–IN (1.130 N.m) but greater than or 

equal to 5 LB–IN (0.565 N.m).

Seven or more ................... Remove engine from service within 20 hours TIS since 

last inspection. 

Less than 5 LB–IN (0.565 N.m) ....................................... One or more ....................... Remove engine from service within 20 hours TIS since 

last inspection. 

(l) Subsequent repeat inspection intervals 

must not exceed the previous inspection 

interval. 

JT8D–217C and –219 Engines Removed From 

Service 

(m) JT8D–217C and –219 engines removed 

from service may be returned to service after 

a detailed inspection and repair or 

replacement of all blades of the failed stage, 

that exceed Engine Manual limits, is done. 

Information on repairing or replacing turbine 

blades can be found in Sections 72–53–12 

through 72–53–13 of the JT8D–200 Engine 

Manual, Part No. 773128. 

Other Criteria for All Engine Models Listed 

in This AD 

(n) Whenever a refurbished or used blade 

is intermixed with new blades in a rotor, use 

the lowest initial inspection threshold that is 

applicable. 

(o) The initial torque inspection or the 

repetitive inspection intervals for a particular 

stage may not be reset, unless the blades for 

that stage are refurbished or replaced. 

(p) Whenever a used (service run) blade is 

reinstalled in a rotor, the previous used time 

should be subtracted from the initial torque 

inspection threshold. 

What This AD Changes 

LPT-to-Exhaust Case Bolts and Nuts 

Replacement, and Crushable Sleeve Spacer 

Installation 

(q) At next accessibility to the LPT-toExhaust Case bolts and nuts, do the 

following: 

(1) Replace the bolts with part number 

(P/N) MS9557–26 bolts; and 

(2) Replace the nuts with P/N 375095 nuts 

or P/N 490270 nuts; and 

(3) Install crushable sleeve spacers, P/N 

822903, under the head of the bolts. 

(r) Guidance on replacing the bolts and 

nuts and installing the crushable sleeve 

spacers can be found in PW ASB No. JT8D 

A6494, Revision 1, dated January 26, 2010. 

Previous Credit 

(s) Initial inspections performed before the 

effective date of this AD using PW ASB No. 

JT8D A6224, Revision 5, dated June 11, 2004, 

or Revision 6, dated May 3, 2007, satisfy the 

initial inspection requirements of this AD. 


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16530 Federal Register / Vol. 76, No. 57 / Thursday, March 24, 2011 / Rules and Regulations 

Definitions 

(t) For the purpose of this AD, 

‘‘refurbished’’ is defined as restoration of the 

shrouds and/or blade re-twist per the JT8D– 

200 Engine Manual, Part No. 773128, or per 

an operator’s approved manual system. 

(u) For the purpose of this AD, ‘‘As-Cast’’ 

refers to blades that were machined from new 

castings, and ‘‘Modified’’ refers to blades that 

were derived from the pre-SB No. 6090 

configuration. 

(v) For the purpose of this AD, 

‘‘accessibility to the LPT-to-exhaust case 

bolts’’ refers to when the inner turbine fan 

ducts are removed. 

Alternative Methods of Compliance 

(w) The Manager, Engine Certification 

Office, has the authority to approve 

alternative methods of compliance (AMOCs) 

for this AD if requested using the procedures 

found in 14 CFR 39.19. AMOCs approved for 

the initial and repetitive inspection 

requirements of AD 2005–02–03 are 

approved as AMOCs for this AD. 

Related Information 

(x) For information about this AD, contact 

Ian Dargin, Aerospace Engineer, Engine 

Certification Office, FAA, Engine and 

Propeller Directorate, 12 New England 

Executive Park; Burlington, MA 01803; 

phone: 781–238–7178; fax: 781–238–7199; email: ian.dargin@faa.gov. 

Material Incorporated by Reference 

(y) You must use Pratt & Whitney Alert 

Service Bulletin No. JT8D A6224, Revision 6, 

dated May 3, 2007, to perform the torque 

inspections required by this AD. 

(1) The Director of the Federal Register 

approved the incorporation by reference of 

this service bulletin in accordance with 5 

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

(2) For service information identified in 

this AD, contact Pratt & Whitney, 400 Main 

St., East Hartford, CT 06108; phone: 860– 

565–8770, fax: 860–565–4503, for a copy of 

this service information. 

(3) You may review copies of the service 

information at the FAA, New England 

Region, 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 an NARA facility, call 202–741– 

6030, or go to http://www.archives.gov/ 

federal_register/code_of 

_federal_regulations/ibr_locations.html. 

Issued in Burlington, Massachusetts on 

March 14, 2011. 

Peter A. White, 

Acting Manager, Engine and Propeller 

Directorate, Aircraft Certification Service. 

[FR Doc. 2011–6719 Filed 3–23–11; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 71 

[Docket No. FAA–2010–1170; Airspace 

Docket No. 10–ACE–13] 

Establishment of Class E Airspace; 

Creighton, NE 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: This action establishes Class 

E airspace at Creighton, NE, to 

accommodate new Area Navigation 

(RNAV) Standard Instrument Approach 

Procedures (SIAP) at Creighton 

Municipal Airport, Creighton, NE. The 

FAA is taking this action to enhance the 

safety and management of Instrument 

Flight Rule (IFR) operations at the 

airport. 

DATES: Effective date: 0901 UTC, June 

30, 2011. The Director of the Federal 

Register approves this incorporation by 

reference action under 1 CFR part 51, 

subject to the annual revision of FAA 

Order 7400.9 and publication of 

conforming amendments. 

FOR FURTHER INFORMATION CONTACT: 

Scott Enander, Central Service Center, 

Operations Support Group, Federal 

Aviation Administration, Southwest 

Region, 2601 Meacham Blvd., Fort 

Worth, TX 76137; telephone (817) 321– 

7716. 

SUPPLEMENTARY INFORMATION: 

History 

On January 10, 2011, the FAA 

published in the Federal Register a 

notice of proposed rulemaking to 

establish Class E airspace for Creighton, 

NE, creating controlled airspace at 

Creighton Municipal Airport (76 FR 

1380) Docket No. FAA–2010–1170. 

Interested parties were invited to 

participate in this rulemaking effort by 

submitting written comments on the 

proposal to the FAA. No comments 

were received. Class E airspace 

designations are published in paragraph 

6005 of FAA Order 7400.9U dated 

August 18, 2010, and effective 

September 15, 2010, which is 

incorporated by reference in 14 CFR 

part 71.1. The Class E airspace 

designations listed in this document 

will be published subsequently in the 

Order. 

The Rule 

This action amends Title 14 Code of 

Federal Regulations (14 CFR) part 71 by 

creating Class E airspace extending 

upward from 700 feet above the surface 

to accommodate new standard 

instrument approach procedures at 

Creighton Municipal Airport, Creighton, 

NE. This action is necessary for the 

safety and management of IFR 

operations at the airport. 

The FAA has determined that this 

regulation only involves an established 

body of technical regulations for which 

frequent and routine amendments are 

necessary to keep them operationally 

current. Therefore, this regulation: (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); and 

(3) does not warrant preparation of a 

regulatory evaluation as the anticipated 

impact is so minimal. Since this is a 

routine matter that will only affect air 

traffic procedures and air navigation, it 

is certified that this rule, when 

promulgated, will not have a significant 

economic impact on a substantial 

number of small entities under the 

criteria of the Regulatory Flexibility Act. 

The FAA’s authority to issue rules 

regarding aviation safety is found in 

Title 49 of the U.S. Code. Subtitle 1, 

Section 106, describes the authority of 

the FAA Administrator. Subtitle VII, 

Aviation Programs, describes in more 

detail the scope of the agency’s 

authority. This rulemaking is 

promulgated under the authority 

described in Subtitle VII, part A, subpart 

I, Section 40103. Under that section, the 

FAA is charged with prescribing 

regulations to assign the use of airspace 

necessary to ensure the safety of aircraft 

and the efficient use of airspace. This 

regulation is within the scope of that 

authority as it creates controlled 

airspace at Creighton Municipal Airport, 

Creighton, NE. 

List of Subjects in 14 CFR Part 71 

Airspace, Incorporation by reference, 

Navigation (Air). 

Adoption of the Amendment 

In consideration of the foregoing, the 

Federal Aviation Administration 

amends 14 CFR part 71 as follows: 

PART 71—DESIGNATION OF CLASS A, 

B, C, D, AND E AIRSPACE AREAS; AIR 

TRAFFIC SERVICE ROUTES; AND 

REPORTING POINTS 

■ 1. The authority citation for 14 CFR 

part 71 continues to read as follows: 

Authority: 49 U.S.C. 106(g), 40103, 40113, 

40120; E. O. 10854, 24 FR 9565, 3 CFR, 1959– 

1963 Comp., p. 389. 


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