Federal Register / Vol. 74, No. 57 / Thursday, March 26, 2009 / Rules and Regulations 13089 

FAA AD Differences 

Note 2: This AD differs from the MCAI 

and/or service information as follows: No 

differences. 

Other FAA AD Provisions 

(g) The following provisions also apply to 

this AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, New York Aircraft 

Certification Office, FAA, has the authority to 

approve AMOCs for this AD, if requested 

using the procedures found in 14 CFR 39.19. 

Send information to ATTN: Fabio Buttitta, 

Aerospace Engineer, Airframe & Propulsion 

Branch, ANE–171, FAA, New York Aircraft 

Certification Office, 1600 Stewart Avenue, 

Suite 410, Westbury, New York 11590; 

telephone (516) 228–7303; fax (516) 794– 

5531. Before using any approved AMOC on 

any airplane to which the AMOC applies, 

notify your appropriate principal inspector 

(PI) in the FAA Flight Standards District 

Office (FSDO), or lacking a PI, your local 

FSDO. 

(2) Airworthy Product: For any 

requirement in this AD to obtain corrective 

actions from a manufacturer or other source, 

use these actions if they are FAA-approved. 

Corrective actions are considered FAAapproved if they are approved by the State 

of Design Authority (or their delegated 

agent). You are required to assure the product 

is airworthy before it is returned to service. 

(3) Reporting Requirements: For any 

reporting requirement in this AD, under the 

provisions of the Paperwork Reduction Act, 

the Office of Management and Budget (OMB) 

has approved the information collection 

requirements and has assigned OMB Control 

Number 2120–0056. 

Related Information 

(h) Refer to MCAI Canadian Airworthiness 

Directive CF–2008–09, dated February 5, 

2008; and Bombardier Service Bulletin 601R– 

24–113, Revision A, dated August 11, 2005; 

for related information. 

Material Incorporated by Reference 

(i) You must use Bombardier Service 

Bulletin 601R–24–113, Revision A, dated 

August 11, 2005, to do the actions required 

by this AD, unless the AD specifies 

otherwise. 

(1) The Director of the Federal Register 

approved the incorporation by reference of 

this service information under 5 U.S.C. 

552(a) and 1 CFR part 51. 

(2) For service information identified in 

this AD, contact Bombardier, Inc., 400 CoˆteVertu Road West, Dorval, Qubec H4S 1Y9, 

Canada; telephone 514–855–5000; fax 514– 

855–7401; e-mail 

thd.crj@aero.bombardier.com; Internet http:// 

www.bombardier.com. 

(3) You may review copies of the service 

information at the FAA, Transport Airplane 

Directorate, 1601 Lind Avenue, SW., Renton, 

Washington. For information on the 

availability of this material at the FAA, call 

425–227–1221 or 425–227–1152. 

(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/ 

code_of_federal_regulations/ 

ibr_locations.html. 

Issued in Renton, Washington, on March 6, 

2009. 

Linda Navarro, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. E9–6221 Filed 3–25–09; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2008–0888; Directorate 

Identifier 2008–NM–084–AD; Amendment 

39–15840; AD 2009–06–04] 

RIN 2120–AA64 

Airworthiness Directives; Bombardier 

Model CL–600–2B19 (Regional Jet 

Series 100 & 440) Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for the 

products listed above. This AD results 

from mandatory continuing 

airworthiness information (MCAI) 

originated by an aviation authority of 

another country to identify and correct 

an unsafe condition on an aviation 

product. The MCAI describes the unsafe 

condition as: 

Bombardier Aerospace has completed a 

system safety review of the CL–600–2B19 

aircraft fuel system against new fuel tank 

safety standards * * *. 

This assessment showed that there is 

insufficient electrical bonding for lightning 

protection at certain locations inside the fuel 

tanks. In addition, the assessment also 

revealed that existing bonding jumpers across 

self-bonded couplings are not required. 

Insufficient electrical bonding, if not 

corrected, could result in arcing and 

potential ignition source inside the fuel tank 

during lightning strikes and consequent fuel 

tank explosion. 

We are issuing this AD to require 

actions to correct the unsafe condition 

on these products. 

DATES: This AD becomes effective April 

30, 2009. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of April 30, 2009. 

ADDRESSES: You may examine the AD 

docket on the Internet at http:// 

www.regulations.gov or in person at the 

U.S. Department of Transportation, 

Docket Operations, M–30, West 

Building Ground Floor, Room W12–140, 

1200 New Jersey Avenue, SE., 

Washington, DC. 

FOR FURTHER INFORMATION CONTACT: 

Mazdak Hobbi, Aerospace Engineer, 

Airframe and Propulsion Branch, ANE– 

171, FAA, New York Aircraft 

Certification Office, 1600 Stewart 

Avenue, Suite 410, Westbury, New York 

11590; telephone (516) 228–7330; fax 

(516) 794–5531. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to include an AD that would 

apply to the specified products. That 

NPRM was published in the Federal 

Register on August 19, 2008 (73 FR 

48312). That NPRM proposed to correct 

an unsafe condition for the specified 

products. The MCAI states: 

Bombardier Aerospace has completed a 

system safety review of the CL–600–2B19 

aircraft fuel system against new fuel tank 

safety standards, introduced in Chapter 525 

of the Airworthiness Manual through Notice 

of Proposed Amendment (NPA) 2002–043. 

The identified non-compliances were 

assessed using Transport Canada Policy 

Letter No. 525–001 to determine if mandatory 

corrective action is required. 

This assessment showed that there is 

insufficient electrical bonding for lightning 

protection at certain locations inside the fuel 

tanks. In addition, the assessment also 

revealed that existing bonding jumpers across 

self-bonded couplings are not required. 

Insufficient electrical bonding, if not 

corrected, could result in arcing and 

potential ignition source inside the fuel tank 

during lightning strikes and consequent fuel 

tank explosion. 

To correct the unsafe condition, this 

directive mandates the modification of 

certain bonding jumpers inside the fuel 

tanks. 

Corrective actions include, for certain 

airplanes, a general visual inspection to 

determine if the modification has been 

done on both sides of the airplane. You 

may obtain further information by 

examining the MCAI in the AD docket. 

Revision to Service Bulletin 

Information 

Since the NPRM was issued, we have 

received Revision F of Bombardier 

Service Bulletin 601R–28–055, dated 

May 27, 2008. We referred to 

Bombardier Service Bulletin 601R–28– 

055, Revision E, dated March 17, 2008, 

as the appropriate source of service 

information for accomplishing the 

actions proposed in the NPRM. Revision 

F of Bombardier Service Bulletin 601R– 

13090 Federal Register / Vol. 74, No. 57 / Thursday, March 26, 2009 / Rules and Regulations 

28–055 changes Figure 7 in the 

Accomplishment Instructions and also 

includes small editorial changes that do 

not affect the technical content of the 

service bulletin. We have revised 

paragraphs (f)(1) and (f)(2) of this AD to 

refer to Revision F of Bombardier 

Service Bulletin 601R–28–055, and we 

have added paragraph (f)(3) of this AD 

to give credit for actions done before the 

effective date of this AD in accordance 

with Revision E of Bombardier Service 

Bulletin 601R–28–055. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

considered the comments received. 

Request To Revise the Costs of 

Compliance Section 

Air Wisconsin states that the service 

information does not discuss warranty 

consideration for parts needed to do the 

modification proposed in the NPRM, 

and requests that we amend the Costs of 

Compliance section of the NPRM to 

reflect the cost of kits at $427 per 

airplane. 

We agree to revise the Costs of 

Compliance section to reflect the parts 

cost. The cost per product and fleet cost 

have increased accordingly. 

Request To Allow Credit for Prior 

Service Bulletin Revision 

Air Wisconsin states that Revision D 

of Bombardier Service Bulletin 601R– 

28–055, dated July 17, 2006, added a 

statement to modify both sides of the 

airplane, and requests that we revise the 

NPRM to give credit for actions 

performed according to Revision D of 

the service bulletin. Air Wisconsin 

notes that Canadian Airworthiness 

Directive CF–2007–34 allows 

compliance with Bombardier Service 

Bulletin 601R–28–055, Revision D. 

We agree with Air Wisconsin to give 

credit for Revision D of Bombardier 

Service Bulletin 601R–28–055, and have 

revised paragraph (f)(3) of this AD 

accordingly. We have also revised Table 

1 of this AD to remove the restriction on 

Revision D of Bombardier Service 

Bulletin 601R–28–055. In addition, we 

have removed Note (1) from the NPRM 

and therefore Note (2) of the NPRM 

becomes Note 1 of this AD. Note (2) is 

also revised to remove the difference for 

Revision D of Bombardier Service 

Bulletin 601R–28–055. 

Conclusion 

We reviewed the available data, 

including the comments received, and 

determined that air safety and the 

public interest require adopting the AD 

with the changes described previously. 

We determined that these changes will 

not increase the economic burden on 

any operator or increase the scope of the 

AD. 

Differences Between This AD and the 

MCAI or Service Information 

We have reviewed the MCAI and 

related service information and, in 

general, agree with their substance. But 

we might have found it necessary to use 

different words from those in the MCAI 

to ensure the AD is clear for U.S. 

operators and is enforceable. In making 

these changes, we do not intend to differ 

substantively from the information 

provided in the MCAI and related 

service information. 

We might also have required different 

actions in this AD from those in the 

MCAI in order to follow our FAA 

policies. Any such differences are 

highlighted in a NOTE within the AD. 

Costs of Compliance 

We estimate that this AD will affect 

about 686 products of U.S. registry. We 

also estimate that it will take about 18 

work-hours per product to comply with 

the basic requirements of this AD. The 

average labor rate is $80 per work-hour. 

Required parts will cost about $427 per 

product. Where the service information 

lists required parts costs that are 

covered under warranty, we have 

assumed that there will be no charge for 

these parts. As we do not control 

warranty coverage for affected parties, 

some parties may incur costs higher 

than estimated here. Based on these 

figures, we estimate the cost of this AD 

to the U.S. operators to be $1,280,762, 

or $1,867 per product. 

Authority for This Rulemaking 

Title 49 of the United States Code 

specifies the FAA’s authority to issue 

rules on aviation safety. Subtitle I, 

section 106, describes the authority of 

the FAA Administrator. ‘‘Subtitle VII: 

Aviation Programs,’’ describes in more 

detail the scope of the Agency’s 

authority. 

We are issuing this rulemaking under 

the authority described in ‘‘Subtitle VII, 

Part A, Subpart III, Section 44701: 

General requirements.’’ Under that 

section, Congress charges the FAA with 

promoting safe flight of civil aircraft in 

air commerce by prescribing regulations 

for practices, methods, and procedures 

the Administrator finds necessary for 

safety in air commerce. This regulation 

is within the scope of that authority 

because it addresses an unsafe condition 

that is likely to exist or develop on 

products identified in this rulemaking 

action. 

Regulatory Findings 

We determined that this AD will not 

have federalism implications under 

Executive Order 13132. This AD will 

not have a substantial direct effect on 

the States, on the relationship between 

the national government and the States, 

or on the distribution of power and 

responsibilities among the various 

levels of government. 

For the reasons discussed above, I 

certify this AD: 

1. Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866; 

2. Is not a ‘‘significant rule’’ under the 

DOT Regulatory Policies and Procedures 

(44 FR 11034, February 26, 1979); and 

3. 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. 

We prepared a regulatory evaluation 

of the estimated costs to comply with 

this AD and placed it in the AD docket. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http:// 

www.regulations.gov; or in person at the 

Docket Operations office between 9 a.m. 

and 5 p.m., Monday through Friday, 

except Federal holidays. The AD docket 

contains the NPRM, the regulatory 

evaluation, any comments received, and 

other information. The street address for 

the Docket Operations office (telephone 

(800) 647–5527) is in the ADDRESSES

section. Comments will be available in 

the AD docket shortly after receipt. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

Adoption of the Amendment 

■ Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA amends 14 CFR part 39 as 

follows: 

PART 39—AIRWORTHINESS 

DIRECTIVES 

■ 1. The authority citation for part 39 

continues to read as follows: 

Authority: 49 U.S.C. 106(g), 40113, 44701. 

§ 39.13 [Amended] 

■ 2. The FAA amends § 39.13 by adding 

the following new AD: 

2009–06–04 Bombardier, Inc. (Formerly 

Canadair): Amendment 39–15840. 

Docket No. FAA–2008–0888; Directorate 

Identifier 2008–NM–084–AD. 

Effective Date 

(a) This airworthiness directive (AD) 

becomes effective April 30, 2009. 

Federal Register / Vol. 74, No. 57 / Thursday, March 26, 2009 / Rules and Regulations 13091 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to Bombardier Model 

CL–600–2B19 (Regional Jet Series 100 & 440) 

airplanes, serial numbers 7003 through 7067, 

and 7069 through 7929, certificated in any 

category. 

Subject 

(d) Air Transport Association (ATA) of 

America Code 28: Fuel. 

Reason 

(e) The mandatory continuing 

airworthiness information (MCAI) states: 

Bombardier Aerospace has completed a 

system safety review of the CL–600–2B19 

aircraft fuel system against new fuel tank 

safety standards, introduced in Chapter 525 

of the Airworthiness Manual through Notice 

of Proposed Amendment (NPA) 2002–043. 

The identified non-compliances were 

assessed using Transport Canada Policy 

Letter No. 525–001 to determine if mandatory 

corrective action is required. 

This assessment showed that there is 

insufficient electrical bonding for lightning 

protection at certain locations inside the fuel 

tanks. In addition, the assessment also 

revealed that existing bonding jumpers across 

self-bonded couplings are not required. 

Insufficient electrical bonding, if not 

corrected, could result in arcing and 

potential ignition source inside the fuel tank 

during lightning strikes and consequent fuel 

tank explosion. 

To correct the unsafe condition, this 

directive mandates the modification of 

certain bonding jumpers inside the fuel 

tanks. 

Corrective actions include, for certain 

airplanes, a general visual inspection to 

determine if the modification has been done 

on both sides of the airplane. 

Actions and Compliance 

(f) Unless already done: Within 5,000 flight 

hours after the effective date of this AD, do 

the following actions. 

(1) For airplanes on which none of the 

Bombardier service bulletins identified in 

Table 1 of this AD have been incorporated as 

of the effective date of this AD: Modify the 

fuel tank bonding jumpers inside the wing 

and center fuel tanks in accordance with Part 

A of the Accomplishment Instructions of 

Bombardier Service Bulletin 601R–28–055, 

Revision F, dated May 27, 2008. 

TABLE 1—SERVICE BULLETINS

Bombardier service bulletin— Revision— Dated— 

601R–28–055 ............................................................................................................................................... Original ........ May 4, 2004. 

601R–28–055 ............................................................................................................................................... A .................. February 14, 2005. 

601R–28–055 ............................................................................................................................................... B .................. September 14, 2005. 

601R–28–055 ............................................................................................................................................... C ................. January 9, 2006. 

(2) For airplanes on which any Bombardier 

service bulletin identified in Table 1 of this 

AD has been incorporated as of the effective 

date of this AD: Do a general visual 

inspection of the inside of the wing and 

center fuel tanks to determine if the actions 

in Part A of the Accomplishment Instructions 

of Bombardier Service Bulletin 601R–28–055, 

Revision F, dated May 27, 2008, have been 

done on both sides of the airplane. If Part A 

of Bombardier Service Bulletin 601R–28–055, 

Revision F, dated May 27, 2008, has not been 

done on either side of the airplane, before 

further flight, do the actions specified in Part 

A of the Accomplishment Instructions of 

Bombardier Service Bulletin 601R–28–055, 

Revision F, dated May 27, 2008; for the side 

of the airplane on which Part A of 

Bombardier Service Bulletin 601R–28–055, 

Revision F, dated May 27, 2008, has not been 

done. 

(3) Actions done before the effective date 

of this AD in accordance with Bombardier 

Service Bulletin 601R–28–055, Revision D, 

dated July 17, 2006; or Bombardier Service 

Bulletin 601R–28–055, Revision E, dated 

March 17, 2008; is acceptable for compliance 

with the corresponding requirements of this 

AD. 

FAA AD Differences 

Note 1: This AD differs from the MCAI 

and/or service information as follows: 

The MCAI specifies that the modification 

must be done on all airplanes in accordance 

with Bombardier Service Bulletin 601R–28– 

055, Revision D, dated July 17, 2006, and that 

accomplishing Bombardier Service Bulletin 

601R–28–055, dated May 4, 2004; 

Bombardier Service Bulletin 601R–28–055, 

Revision A, dated February 14, 2005; or 

Bombardier Service Bulletin 601R–28–055, 

Revision B, dated September 14, 2005; does 

not satisfy the requirements of the MCAI. 

This AD requires doing the modification on 

airplanes on which any Bombardier service 

bulletin identified in Table 1 of this AD, has 

not been done. For airplanes on which any 

Bombardier service bulletin identified in 

Table 1 of this AD has been done, this AD 

requires inspecting to determine if the 

modification is done on both sides of the 

airplane and modifying the airplane if the 

modification was not done on both sides. 

Other FAA AD Provisions 

(g) The following provisions also apply to 

this AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, New York Aircraft 

Certification Office, FAA, has the authority to 

approve AMOCs for this AD, if requested 

using the procedures found in 14 CFR 39.19. 

Send information to ATTN: Mazdak Hobbi, 

Aerospace Engineer, Airframe and 

Propulsion Branch, ANE–171, FAA, New 

York Aircraft Certification Office, 1600 

Stewart Avenue, Suite 410, Westbury, New 

York 11590; telephone (516) 228–7330; fax 

(516) 794–5531. Before using any approved 

AMOC on any airplane to which the AMOC 

applies, notify your appropriate principal 

inspector (PI) in the FAA Flight Standards 

District Office (FSDO), or lacking a PI, your 

local FSDO. 

(2) Airworthy Product: For any 

requirement in this AD to obtain corrective 

actions from a manufacturer or other source, 

use these actions if they are FAA-approved. 

Corrective actions are considered FAAapproved if they are approved by the State 

of Design Authority (or their delegated 

agent). You are required to assure the product 

is airworthy before it is returned to service. 

(3) Reporting Requirements: For any 

reporting requirement in this AD, under the 

provisions of the Paperwork Reduction Act, 

the Office of Management and Budget (OMB) 

has approved the information collection 

requirements and has assigned OMB Control 

Number 2120–0056. 

Related Information 

(h) Refer to MCAI Canadian Airworthiness 

Directive CF–2007–34, dated December 21, 

2007; and Bombardier Service Bulletin 601R– 

28–055, Revision F, dated May 27, 2008; for 

related information. 

Material Incorporated by Reference 

(i) You must use Bombardier Service 

Bulletin 601R–28–055, Revision F, dated 

May 27, 2008, to do the actions required by 

this AD, unless the AD specifies otherwise. 

(1) The Director of the Federal Register 

approved the incorporation by reference of 

this service information under 5 U.S.C. 

552(a) and 1 CFR part 51. 

(2) For service information identified in 

this AD, contact Bombardier, Inc., 400 CoˆteVertu Road West, Dorval, Que ́bec H4S 1Y9, 

Canada; telephone 514–855–5000; fax 514– 

855–7401; e-mail 

thd.crj@aero.bombardier.com; Internet http:// 

www.bombardier.com. 

(3) You may review copies of the service 

information at the FAA, Transport Airplane 

Directorate, 1601 Lind Avenue, SW., Renton, 

Washington. For information on the 

availability of this material at the FAA, call 

425–227–1221 or 425–227–1152. 

(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/ 

code_of_federal_regulations/ 

ibr_locations.html. 

13092 Federal Register / Vol. 74, No. 57 / Thursday, March 26, 2009 / Rules and Regulations 

Issued in Renton, Washington, on February 

27, 2009. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. E9–6569 Filed 3–25–09; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2008–1025; Directorate 

Identifier 2008–NE–31–AD; Amendment 39– 

15862; AD 2009–07–03] 

RIN 2120–AA64 

Airworthiness Directives; General 

Electric Company CF6–80C2 and CF6– 

80E1 Series Turbofan Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: The FAA is adopting a new 

airworthiness directive (AD) for General 

Electric Company (GE) CF6–80C2 and 

CF6–80E1 series turbofan engines with 

high-pressure compressor rotor (HPCR) 

spool shaft stage 14 disks, part number 

(P/N) 1703M49G02, 1703M49G03, or 

1509M71G10 installed. This AD 

requires a one-time eddy current 

inspection (ECI) of the HPCR spool shaft 

stage 14 disk web for crack indications, 

and removing from service any parts 

with web cracks. This AD results from 

reports of 12 HPCR spool shaft stage 14 

disks with web cracks discovered to 

date. We are issuing this AD to prevent 

cracks from propagating to an 

uncontained failure of the disk and 

damage to the airplane. 

DATES: This AD becomes effective April 

30, 2009. The Director of the Federal 

Register approved the incorporation by 

reference of certain publications listed 

in the regulations as of April 30, 2009. 

ADDRESSES: You can get the service 

information identified in this AD from 

General Electric Company via Lockheed 

Martin Technology Services, 10525 

Chester Road, Suite C, Cincinnati, Ohio 

45215, telephone (513) 672–8400, fax 

(513) 672–8422. 

The Docket Operations office is 

located at Docket Management Facility, 

U.S. Department of Transportation, 1200 

New Jersey Avenue, SE., West Building 

Ground Floor, Room W12–140, 

Washington, DC 20590–0001. 

FOR FURTHER INFORMATION CONTACT: 

Christopher Richards, Aerospace 

Engineer, Engine Certification Office, 

FAA, Engine & Propeller Directorate, 12 

New England Executive Park, 

Burlington, MA 01803; e-mail: 

christopher.j.richards@faa.gov; 

telephone (781) 238–7133; fax (781) 

238–7199. 

SUPPLEMENTARY INFORMATION: The FAA 

proposed to amend 14 CFR part 39 with 

a proposed AD. The proposed AD 

applies to GE CF6–80C2 and CF6–80E1 

series turbofan engines with HPCR 

spool shaft stage 14 disks, P/N 

1703M49G02, 1703M49G03, or 

1509M71G10 installed. We published 

the proposed AD in the Federal Register 

on November 26, 2008 (73 FR 71949). 

That action proposed to require a onetime ECI of the HPCR spool shaft stage 

14 disk web for crack indications, and 

removing from service any parts with 

web cracks. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http:// 

www.regulations.gov; or in person at the 

Docket Operations office 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 Operations office (telephone 

(800) 647–5527) is provided in the 

ADDRESSES section. Comments will be 

available in the AD docket shortly after 

receipt. 

Comments 

We provided the public the 

opportunity to participate in the 

development of this AD. We have 

considered the comments received. 

Compliance Should Be at Next Engine 

Shop Visit 

One commenter, Amiri Flight, states 

that the compliance should be at next 

engine shop visit and should not have 

a calendar time limit, which may 

require forced removal/shop visit of 

low-utilization engines. 

We agree. The compliance in the 

proposed AD, and the AD, require 

inspection at next engine shop visit 

only. We did not change the AD. 

Request To Correct the Boeing Airplane 

Models 

One commenter, The Boeing 

Company, requests that we correct some 

of the minor models listed in the 

applicability section, and add a missing 

model. They state that for their 

airplanes, the AD should only list 747 

and 767 models as-listed in the type 

certificate data sheet. We agree. We 

changed the AD to state ‘‘Boeing 747– 

200B/300/400/400D/400F, 767–200/ 

300/400F/400ER and MD–11 airplanes’’. 

Costs of Compliance Is the Cost of a 

Single Spool Replacement 

One commenter, FedEx Express, 

states that it appears that the proposed 

AD costs of compliance total to U.S. 

operators of $594,500, is inaccurate and 

might be the cost of a single spool 

replacement, rather than the 

accumulated total of the proposed 

action, if the estimate of 10 affected 

units is accurate. 

We agree that the proposed AD total 

is inaccurate. We had a typo in the 

proposed AD costs of compliance. The 

total cost should have been $5,594,500. 

We corrected the total in the final rule 

AD. 

Conclusion 

We have carefully reviewed the 

available data, including 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 changes 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 

126 CF6–80C2 and CF6–80E1 series 

turbofan engines installed on airplanes 

of U.S. registry. We also estimate that it 

will take about 10 work-hours per 

engine to perform the inspection, and 

about 281 hours to complete the actions 

if done at module level, and that the 

average labor rate is $80 per work-hour. 

The pro-rated cost of a HPCR stage 10– 

14 spool shaft, based on average life 

remaining on disks found cracked, is 

$526,890. Using data on the percentage 

of the affected fleet already in 

compliance with the corrective actions, 

we estimate there will be 10 disks found 

cracked as a result of these inspections. 

Based on these figures, we estimate the 

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

be $5,594,500. 

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