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 

Federal Register / Vol. 74, No. 57 / Thursday, March 26, 2009 / Rules and Regulations 13093 

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 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 summary of the costs 

to comply with this AD and placed it in 

the AD Docket. You may get a copy of 

this summary at the address listed 

under ADDRESSES. 

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 Federal Aviation Administration 

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 airworthiness 

directive: 

2009–07–03 General Electric Company: 

Amendment 39–15862. Docket No. 

FAA–2008–1025; Directorate Identifier 

2008–NE–31–AD. 

Effective Date 

(a) This airworthiness directive (AD) 

becomes effective April 30, 2009. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to 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. 

These engines are installed on, but not 

limited to, Airbus A300–600R/F, A310–200/ 

300, and A330–200/300, and Boeing 747– 

200B/300/400/400D/400F, 767–200/300/ 

400F/400ER, and MD–11 airplanes. 

Unsafe Condition 

(d) This AD results from reports of 12 

cracked HPCR spool shaft stage 14 disk webs 

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. 

Compliance 

(e) You are responsible for having the 

actions required by this AD performed at the 

next engine shop visit where the separation 

of a major engine flange will occur after the 

effective date of this AD, unless the actions 

have already been done. 

(f) For the purpose of this AD, introduction 

of an engine into a shop solely for the 

following maintenance actions is not 

considered an engine shop visit: 

(1) Removal of a compressor case for airfoil 

or variable stator vane bushing maintenance. 

(2) Removal or replacement of the stage 1 

fan disk. 

(3) Replacement of the turbine rear frame. 

(4) Removal or replacement of the 

accessory and/or transfer gearbox. 

(5) Removal or replacement of the fan 

forward case. 

(6) Any combination of the maintenance 

actions listed above. 

One-Time Eddy Current Inspection (ECI) 

(g) Using the following Alert Service 

Bulletin (ASB) instructions, perform a onetime ECI of the HPCR spool shaft stage 14 

disk web for crack indications, and remove 

from service those parts found to be cracked. 

(1) Use paragraphs 3.B.(1) through 3.B.(5) 

of the Accomplishment Instructions of GE 

ASB No. CF6–80C2 S/B 72–A1122, Revision 

1, dated June 19, 2006, to ECI the CF6–80C2 

series engine HPCR spool shaft stage 14 disk 

web at the module level. 

(2) Use paragraph 3.C.(1) of the 

Accomplishment Instructions of GE ASB No. 

CF6–80C2 S/B 72–A1122, Revision 1, dated 

June 19, 2006, to ECI the CF6–80C2 series 

engine HPCR spool shaft stage 14 disk web 

at the piece-part level. 

(3) Use paragraphs 3.B.(1) through 3.B.(5) 

of the Accomplishment Instructions of GE 

ASB No. CF6–80E1 S/B 72–A0258, Revision 

1, dated June 15, 2006, to ECI the CF6–80E1 

series engine HPCR spool shaft stage 14 disk 

web at the module level. 

(4) Use paragraph 3.C.(1) of the 

Accomplishment Instructions of GE ASB No. 

CF6–80E1 S/B 72–A0258, Revision 1, dated 

June 15, 2006, to ECI the HPCR spool shaft 

stage 14 disk web at the piece-part level. 

Previous Credit 

(h) Performance of a one-time ECI of the 

HPCR spool shaft stage 14 disk web for crack 

indications, done before the effective date of 

this AD and following the procedures 

defined in GE ASB No. CF6 80C2 S/B 72– 

A1122, dated January 19, 2004, for CF6–80C2 

series engines or GE ASB No. CF6 80E1 S/ 

B 72–A0258, dated January 19, 2004, for 

CF6–80E1 series engines satisfies the 

compliance requirements specified in this 

AD. 

Alternative Methods of Compliance 

(i) The Manager, Engine Certification 

Office, has the authority to approve 

alternative methods of compliance for this 

AD, if requested using the procedures found 

in 14 CFR 39.19. 

Related Information 

(j) 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, for more 

information about this AD. 

Material Incorporated by Reference 

(k) You must use the service information 

specified in the following Table 1 to perform 

the one-time ECI required by this AD. The 

Director of the Federal Register approved the 

incorporation by reference of the documents 

listed in the following Table 1 in accordance 

with 5 U.S.C. 552(a) and 1 CFR part 51. 

Contact General Electric Company via 

Lockheed Martin Technology Services, 10525 

Chester Road, Suite C, Cincinnati, Ohio 

45215, telephone (513) 672–8400, fax (513) 

672–8422, for a copy of this service 

information. You may review copies at the 

FAA, New England Region, 12 New England 

Executive Park, Burlington, MA; or at the 

National Archives and Records 

Administration (NARA). For information on 

the availability of this material at NARA, call 

202–741–6030, or go to: http:// 

www.archives.gov/federal-register/cfr/ibrlocations.html. 

TABLE 1—INCORPORATION BY REFERENCE

GE Alert Service Bulletin No. Page Revision Date 

CF6–80C2 S/B 72–A1122 Total Pages: 57 ................................................................................. ALL ...... 1 June 19, 2006. 

CF6–80E1 S/B 72–A0258 Total Pages: 57 ................................................................................. ALL ...... 1 June 15, 2006. 

13094 Federal Register / Vol. 74, No. 57 / Thursday, March 26, 2009 / Rules and Regulations 

Issued in Burlington, Massachusetts, on 

March 18, 2009. 

Thomas A. Boudreau, 

Acting Manager, Engine and Propeller 

Directorate, Aircraft Certification Service. 

[FR Doc. E9–6387 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–2008–0522; Directorate 

Identifier 2008–NM–041–AD; Amendment 

39–15855; AD 2009–06–18] 

RIN 2120–AA64 

Airworthiness Directives; Bombardier 

Model CL–600–2C10 (Regional Jet 

Series 700, 701, & 702) Airplanes, 

Model CL–600–2D15 (Regional Jet 

Series 705) Airplanes, and Model CL– 

600–2D24 (Regional Jet Series 900) 

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: 

Following in-flight test deployments on 

CL–600–2B19 aircraft, several Air-Driven 

generators (ADGs) failed to come on-line. 

Investigation revealed that, as a result of a 

wiring anomaly that had not been detected 

during ADG manufacture, a short circuit was 

possible between certain internal wires and 

their metallic over-braided shields, which 

could result in the ADG not providing power 

when deployed. 

The unsafe condition is that failure of 

the ADG could lead to loss of several 

functions essential for safe flight. 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: 

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. 

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 May 8, 2008 (73 FR 26045). 

That NPRM proposed to correct an 

unsafe condition for the specified 

products. The MCAI states: 

Following in-flight test deployments on 

CL–600–2B19 aircraft, several Air-Driven 

generators (ADGs) failed to come on-line. 

Investigation revealed that, as a result of a 

wiring anomaly that had not been detected 

during ADG manufacture, a short circuit was 

possible between certain internal wires and 

their metallic over-braided shields, which 

could result in the ADG not providing power 

when deployed. This directive mandates 

checking of the ADG and modification of the 

ADG internal wiring, if required. It also 

prohibits future installation of unmodified 

ADGs. 

The unsafe condition is that failure of 

the ADG could lead to loss of several 

functions essential for safe flight. You 

may obtain further information by 

examining the MCAI in the AD docket. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

considered the comments received. 

Request To Extend Compliance Time 

for Inspecting the Identification Plate 

Comair requests that we change the 

compliance time specified in paragraph 

(f)(1)(ii) of the NPRM to remove the 

‘‘before further flight’’ phrase. Comair 

states that it has already reviewed their 

maintenance records and found that 

affected ADGs are installed on its fleet. 

Since the review was performed before 

the effective date of the AD, it is not 

clear when Comair would be required to 

inspect the ADG identification plate. 

Comair suggests a compliance time of 12 

months after the effective date of the 

AD. 

We agree to change the compliance 

time. The intent of the AD is to inspect 

and modify the ADG wiring within 12 

months after the effective date of the 

AD. We have revised the compliance 

time of paragraph (f)(1)(ii) of this AD 

accordingly. 

Request To Shorten Compliance Time 

and Restrict Dispatch Conditions 

Air Line Pilots Association, 

International (ALPA), requests that the 

compliance time be shortened from 12 

months to 3 months. ALPA states that 

although its review did not reveal any 

incidents of full electrical failures in 

Bombardier airplanes, the ADG is the 

only remaining source of electrical 

power sustaining the batteries and flight 

critical electrical systems if all other 

generators fail or are unavailable. In 

addition, ALPA states there are 

procedures for deferring an enginedriven or APU generator under certain 

circumstances, but the ADG is a nondeferrable item. ALPA recommends 

that, given the potential consequences 

of a full electrical system failure, 

particularly in low visibility weather 

conditions in which these airplanes 

routinely operate, we shorten the 

compliance time to 3 months. ALPA 

also recommends that no flights be 

allowed with a non-operating enginedriven or APU generator unless this AD 

has been complied with. 

We do not agree to shorten the 

compliance time. We have considered 

the risks (probability of dual engine 

shutdown due to a common cause and 

total loss of electrical power, including 

the emergency battery power) and have 

determined that a 12-month compliance 

time is appropriate. The issue of not 

allowing flights to be dispatched 

without an operational engine-driven or 

APU generator would be better 

addressed in the applicable Master 

Minimum Equipment List (MMEL). We 

are considering a revision to the MMEL 

for that issue. No change to the AD was 

made in this regard. 

Clarification 

We have revised paragraphs (f)(1)(i) 

and (f)(1)(ii)(A) of this AD from ‘‘* * * 

by this AD.’’ to ‘‘* * * by this 

paragraph.’’ to clarify that if the criteria 

in those paragraphs are met, no further 

actions are required by those 

paragraphs. The requirements of 

paragraph (f)(2) of this AD would still be 

in effect. 

We have removed reference to 

Hamilton Sundstrand Service Bulletin 

ERPS10AG–24–2, dated February 19, 

2004, from paragraph (f)(2) of this AD. 

Instead we have added Note 1 of this 

AD to include this information. 

Conclusion 

We reviewed the available data, 

including the comments received, and