Federal Register / Vol. 75, No. 186 / Monday, September 27, 2010 / Rules and Regulations 59067 

FAA–2007–28077; Directorate Identifier 

2007–NE–20–AD. 

Effective Date 

(a) This airworthiness directive (AD) 

becomes effective November 1, 2010. 

Affected ADs 

(b) This AD revises AD 2009–09–03, 

Amendment 39–15889. 

Applicability 

(c) This AD applies to Turbome ́ca S.A. 

ARRIEL 2B and 2B1 turboshaft engines that 

don’t incorporate modification TU166. These 

engines are installed on, but not limited to, 

Eurocopter AS 350 B3 and EC 130 B4 

helicopters. 

Reason 

(d) This AD results from: 

Since issuance of AD 2007–0109, 

Turbome ́ca has released modification TU166 

which consists in inserting HP blade 

dampers between the HP disc and the HP 

blade platform. Introduction of these 

dampers has demonstrated to limit axial 

displacement of the HP blade relative to the 

disk in case of blade lock rupture or opening, 

therefore eliminating the need for inspection 

and replacement. 

We are issuing this AD to prevent an 

uncommanded in-flight engine shutdown 

which could result in an emergency 

autorotation landing or an accident. 

Actions and Compliance 

(e) Unless already done, do the following 

actions: 

Initial Inspection 

(1) Perform an initial high-pressure (HP) 

turbine borescope inspection according to 

Turbome ́ca S.A. Mandatory Service Bulletin 

(MSB) No. 292 72 2825, Version B, dated 

September 21, 2009, or earlier version as 

follows: 

(i) For engines with fewer than 500 hours 

and 450 cycles since new or since the last HP 

turbine borescope inspection, inspect before 

reaching 600 hours or 500 cycles whichever 

occurs first. Replace HP turbine modules 

with rearward turbine blade displacement 

greater than 0.5 mm. 

(ii) For the remaining engines, inspect 

within the next 100 hours. Replace HP 

turbine modules with rearward turbine blade 

displacement greater than 0.5 mm. 

Repetitive Inspections 

(2) Perform repetitive HP turbine borescope 

inspections according to Turbome ́ca S.A. 

MSB No. 292 72 2825, Version B, dated 

September 21, 2009 or earlier version: 

(i) Within 600 hours or 500 cycles from the 

previous inspection, whichever occurs first, 

if the rearward displacement of the turbine 

blades was less than 0.2 mm. Replace HP 

turbine modules with rearward turbine blade 

displacement greater than 0.5 mm. 

(ii) Within 100 hours of the previous 

inspection if the rearward displacement of 

the turbine blades was between 0.2 mm and 

0.5 mm. Replace HP turbine modules with 

rearward turbine blade displacement greater 

than 0.5 mm. 

Optional Terminating Action 

(f) Incorporating modification TU166 

terminates the repetitive inspection 

requirements of paragraphs (e)(2)(i) and 

(e)(2)(ii) of this AD. 

FAA AD Differences 

(g) For clarification, we restructured the 

actions and compliance wording of this AD. 

(h) We deleted the Turbome ́ca reporting 

requirement from the AD. 

(i) Although EASA Airworthiness Directive 

2007–0109R1, dated November 9, 2009, 

applies to the ARRIEL 2B1A engine, this AD 

does not apply to that model because it has 

no U.S. type certificate. 

Alternative Methods of Compliance 

(AMOCs) 

(j) The Manager, Engine Certification 

Office, FAA, has the authority to approve 

AMOCs for this AD, if requested using the 

procedures found in 14 CFR 39.19. 

Related Information 

(k) Refer to EASA Airworthiness Directive 

2007–0109R1, dated November 9, 2009, and 

Turbome ́ca S.A. MSB No. 292 72 2825, 

Version B, dated September 21, 2009, or 

earlier version, for related information. 

(l) Contact Richard Woldan, Aerospace 

Engineer, Engine Certification Office, FAA, 

Engine and Propeller Directorate, 12 New 

England Executive Park, Burlington, MA 

01803–5299; telephone (781) 238–7136; fax 

(781) 238–7199, for more information about 

this AD. 

Material Incorporated by Reference 

(m) You must use Turbome ́ca S.A. 

Mandatory Service Bulletin No. 292 72 2825, 

Version B, dated September 21, 2009, to do 

the actions required by this AD, unless the 

AD specifies otherwise. 

(1) The Director of the Federal Register 

previously approved the incorporation by 

reference of Turbome ́ca S.A. Mandatory 

Service Bulletin No. 292 72 2825, dated April 

5, 2007, on June 1, 2009 (74 FR 18981, April 

27, 2009). 

(2) For service information identified in 

this AD, contact Turbome ́ca, 40220 Tarnos, 

France; telephone 33 05 59 74 40 00, fax 33 

05 59 74 45 15. 

(3) 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. 

Issued in Burlington, Massachusetts, on 

September 17, 2010. 

Robert J. Ganley, 

Acting Manager, Engine and Propeller 

Directorate, Aircraft Certification Service. 

[FR Doc. 2010–23833 Filed 9–24–10; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2009–1100; Directorate 

Identifier 2009–NE–37–AD; Amendment 39– 

16441; AD 2010–20–07] 

RIN 2120–AA64 

Airworthiness Directives; International 

Aero Engines AG V2500–A1, V2522– 

A5, V2524–A5, V2525–D5, V2527–A5, 

V2527E–A5, V2527M–A5, V2528–D5, 

V2530–A5, and V2533–A5 Turbofan 

Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: The FAA is adopting a new 

airworthiness directive (AD) for all 

International Aero Engines AG (IAE) 

V2500–A1, V2525–D5 and V2528–D5 

turbofan engines and certain serial 

numbers (S/Ns) of IAE V2522–A5, 

V2524–A5, V2527–A5, V2527E–A5, 

V2527M–A5, V2530–A5, and V2533–A5 

turbofan engines. For certain S/Ns of 

V2500–A1, V2522–A5, V2524–A5, 

V2527–A5, V2527E–A5, V2527M–A5, 

V2530–A5, and V2533–A5 series 

turbofan engines, this AD requires 

initial and repetitive on-wing ultrasonic 

inspections of the high-pressure 

compressor (HPC) stage 3 to 8 drum for 

cracks. As mandatory terminating action 

to the repetitive inspections, this AD 

requires removal from service of the 

fully silver plated nuts attaching the 

HPC stage 3 to 8 drum to the HPC stage 

9 to 12 drum, removal of silver residue 

from the HPC stage 3 to 8 drum, and 

fluorescent penetrant inspection (FPI) of 

the stage 3 to 8 drum within a specified 

time. For all other engines, this AD 

requires removal from service of the 

fully silver plated nuts attaching the 

HPC stage 3 to 8 drum to the HPC stage 

9 to 12 drum, removal of silver residue 

from the HPC stage 3 to 8 drum, and FPI 

of the HPC stage 3 to 8 drum at the next 

drum piece-part exposure. This AD 

results from reports of 39 HPC stage 3 

to 8 drums found cracked since March 

2009. We are issuing this AD to prevent 

uncontained failure of the HPC stage 3 

to 8 drum, which could result in 

damage to the airplane. 

DATES: This AD becomes effective 

November 1, 2010. The Director of the 

Federal Register approved the 

incorporation by reference of certain 

publications listed in the regulations as 

of November 1, 2010. 

ADDRESSES: You can get the service 

information identified in this AD from 

mstockstill on DSKH9S0YB1PROD with RULES

59068 Federal Register / Vol. 75, No. 186 / Monday, September 27, 2010 / Rules and Regulations 

International Aero Engines AG, 400 

Main Street, East Hartford, CT 06108; 

telephone: (860) 565–5515; fax: (860) 

565–5510. 

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: 

Mark Riley, Aerospace Engineer, Engine 

Certification Office, FAA, Engine and 

Propeller Directorate, 12 New England 

Executive Park, Burlington, MA 01803; 

e-mail: mark.riley@faa.gov; telephone 

(781) 238–7758, fax (781) 238–7199. 

SUPPLEMENTARY INFORMATION: The FAA 

proposed to amend 14 CFR part 39 with 

a proposed AD. The proposed AD 

applies to all IAE V2500–A1, V2525–D5 

and V2528–D5 turbofan engines and 

certain S/Ns of IAE V2522–A5, V2524– 

A5, V2527–A5, V2527E–A5, V2527M– 

A5, V2530–A5, and V2533–A5 turbofan 

engines. We published the proposed AD 

in the Federal Register on February 12, 

2010 (75 FR 6860). That action proposed 

to require: 

• For certain S/Ns of IAE V2500–A1, 

V2522–A5, V2524–A5, V2527–A5, 

V2527E–A5, V2527M–A5, V2530–A5, 

and V2533–A5 turbofan engines: 

Æ Initial and repetitive on-wing 

ultrasonic inspections of HPC stage 3 to 

8 drums for cracks; and 

Æ As mandatory terminating action to 

the repetitive ultrasonic inspections, 

within 27 months from the effective 

date of this AD, removal from service of 

the fully silver plated nuts attaching the 

HPC stage 3 to 8 drum to the HPC stage 

9 to 12 drum, removal of silver residue 

from the HPC stage 3 to 8 drums, and 

FPI of the HPC stage 3 to 8 drums. 

• For all other engines, at the next 

piece-part exposure of the HPC stage 3 

to 8 drum, removal from service of the 

fully silver plated nuts attaching the 

HPC stage 3 to 8 drum to the HPC stage 

9 to 12 drum, removal of silver residue 

from the HPC stage 3 to 8 drums, and 

FPI of the HPC stage 3 to 8 drums. 

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. 

Request To Mandate Inspection of 

Group B and Group C Engines 

One commenter, Airbus, requests that 

we mandate inspection for the S/N 

engines identified in Group B and 

Group C of IAE Service Bulletin (SB) 

No. V2500–ENG–72–0594, Revision 5, 

as these engines may have operated in 

a similar environment as the Group A 

engines. 

We do not agree. Engines identified in 

Groups B and C have not exhibited 

cracking similar to that seen in engines 

listed in Groups A and D. Therefore, it 

is not appropriate to mandate 

inspections on Group B or C engines at 

this time. We did not change the AD. 

Claim That Root Cause Is Not Yet 

Determined 

Airbus claims that the proposed AD 

would mandate the inspection only on 

engines identified in IAE SB No. 

V2500–ENG–72–0594 (Groups A and D) 

and IAE SB No. V2500–ENG–72–0603 

(Group A) without determining root 

cause. To properly identify the suspect 

population, determining the root cause 

of the HPC stage 3–8 drum cracking is 

required. 

We do not agree. While we do not yet 

know the specific root cause of the 

contamination causing the corrosion 

cracking of the HPC stage 3–8 drum, we 

do know that engines specified in IAE 

SB No. V2500–ENG–72–0594 (Groups A 

and D) and IAE SB No. V2500–ENG–72– 

0603 (Group A) may exhibit HPC stage 

3–8 drum corrosion cracking. We did 

not change the AD. 

Request To Include a Fleetwide 

Introduction of a Final Fix 

Airbus requests that the proposed AD 

should include a fleet-wide introduction 

of the final fix (nuts modification), and 

in the interim, the ultrasonic inspection, 

to correct the cause of HPC stage 3–8 

drum cracking for the entire V2500 fleet. 

We partially agree. Paragraph (f)(4)(i) 

of this AD requires that all operators of 

engines requiring these repetitive 

ultrasonic inspections remove the fully 

silver plated nuts, P/N AS44862, or 

equivalent, that attach the HPC stage 3 

to 8 drum to the HPC stage 9 to 12 

drum, within 27 months after the 

effective date of the AD. Paragraph (g) 

of this AD also requires those operators 

of all other affected engines to remove 

the fully silver plated nuts at the next 

piece-part exposure of the HPC stage 3– 

8 drum after the effective date of the 

AD. Ultrasonic inspection(s) per IAE SB 

No. V2500–ENG–72–0594 (Groups A 

and D) and IAE SB No. V2500–ENG–72– 

0603 only affect certain engines and are 

not required for the entire fleet. We did 

not change the AD. 

Claim That Proposed AD Is Less 

Restrictive Than IAE SB 

Airbus claims that the proposed AD is 

less restrictive than the IAE service 

bulletins, and it does not recommend 

immediate action for V2500–A5 drums 

above 7,545 cycles-since-new and for 

V2500–A1 drums above 10,305 cyclessince-new. It therefore does not meet the 

criteria for maximum allowable 

individual risk per flight. 

We do not agree. All ‘‘high cycle’’ HPC 

stage 3 to 8 drums in the field that 

required inspections at reduced 

thresholds, as referenced in the IAE SBs, 

have already been inspected. Therefore, 

an equivalent level of fleet risk is 

maintained for the AD action, and meets 

FAA criteria. We did not change the AD. 

FAA Should Mandate the Nut Removal 

for the Complete V2500 Fleet 

Airbus states that the proposed AD 

does not put a compliance date for 

removal of the fully plated silver nuts 

for the complete V2500 fleet. Removal 

of the fully silver plated nuts should be 

mandated for the complete V2500 fleet. 

We agree that the fully silver plated 

nuts should be removed from service for 

the entire V2500 fleet. However, all 

engines do not need to be retrofitted 

before a specific compliance date. 

V2500 engines that have been 

determined to require repetitive 

ultrasonic inspections are at an elevated 

risk level, and therefore require removal 

of the fully silver plated nuts within a 

specified time period to prevent 

corrosion and potential failure of the 

HPC 3–8 drum. The remaining V2500 

engines that do not require repetitive 

ultrasonic inspections have been 

determined to be at a much lower risk 

level, and therefore, are only required to 

have the fully silver plated nuts 

removed at the next piece part exposure. 

We did not change the AD. 

Request To Reference the Latest Service 

Bulletins 

IAE and Japan Airlines request that 

we reference the latest revisions of the 

service bulletins, which are IAE SB No. 

V2500–ENG–72–0594, Revision 6, IAE 

SB No. V2500–ENG–72–0603, Revision 

2, and V2500–ENG–72–0601, Revision 

2, as they have been updated to include 

additional engine S/Ns and other 

clarification changes. 

We agree. We changed the AD to 

reference the revised service bulletins. 

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Federal Register / Vol. 75, No. 186 / Monday, September 27, 2010 / Rules and Regulations 59069 

Request To Correct Typos in the 

Proposed AD 

Two commenters request that we 

change the following: 

Paragraph (f)(4) should be revised 

from ‘‘HPC Stage 8 to 12 drum’’ to ‘‘HPC 

Stage 3 to 8 drum’’. 

Paragraphs (f)(1), (f)(4)(ii), and (g)(2) 

should be revised from ‘‘using paragraph 

3 of the Accomplishment Instructions 

of’’ to ‘‘using the paragraph 3 

Accomplishment Instructions of’’. 

We partially agree. We agree that 

paragraph (f)(4) should be revised from 

‘‘HPC Stage 8 to 12 drum’’ to ‘‘HPC Stage 

3 to 8 drum,’’ We changed the AD. 

We also agree that our reference in 

paragraphs (f)(1), (f)(4)(ii), and (g)(2) 

should be revised, but not as 

recommended. We changed paragraphs 

(f)(1), (f)(4)(ii), and (g)(2) from ‘‘using 

paragraph 3 of the Accomplishment 

Instructions of’’ to ‘‘use IAE SB No. 

V2500–ENG–72–0601, Revision 2, dated 

April 12, 2010, Accomplishment 

Instructions, paragraph 3.’’ 

Material Incorporated by Reference 

Section Missing From Proposed AD 

One commenter states that paragraphs 

(f)(1), (f)(4)(ii), and (g)(2) require 

ultrasonic inspection and cleaning to be 

performed using the Accomplishment 

Instructions of specified revisions of 

IAE SBs V2500–ENG–72–0594, V2500– 

ENG–603, and V2500–ENG–72–0601. 

These SBs should be listed in the 

Material Incorporated by Reference 

section, which is missing from the 

NPRM. 

We agree. This Final Rule AD 

includes the Material Incorporated by 

Reference section, which includes those 

SBs. 

Request To Revise the Relevant Service 

Information 

IAE commented to revise the last 

sentence of the ‘‘Relevant Service 

Information’’ in the preamble of the AD 

to change: ‘‘* * * 27 months from the 

effective date of the proposed AD’’ to ‘‘27 

months after the effective date of this 

AD’’. The commenter states that this 

could be interpreted incorrectly as 27 

months from February 12, 2010 (date of 

the NPRM). 

We do not agree that the compliance 

date could be misinterpreted. Paragraph 

(4) of this AD correctly states ‘‘27 

months after the effective date of this 

AD.’’ We did not change the AD. 

Request To Revise the Mandatory 

Terminating Action Compliance Time 

IAE requests that we revise the 

mandatory terminating action 

compliance time of ‘‘27 months after the 

effective date of this AD’’ to a calendar 

end date of October 31, 2012, to be 

consistent with the IAE risk assessment. 

We do not agree. Due to the 

uncertainty of the actual publication 

date of the AD, revising the mandatory 

terminating action from 27 months after 

the effective date of this AD to a 

calendar date of October 31, 2012, may 

result in a compliance time that is more 

restrictive than what was proposed in 

the NPRM. We did not change the AD. 

Request To Revise the Definition of 

Piece-Part Exposure 

IAE requests that we revise the AD to 

change paragraph (i) of the definition of 

piece-part exposure for the HPC stage 3 

to 8 drum from ‘‘removal of the drum 

from the engine and removal of all 

blades from the drum’’ to ‘‘separation of 

the rotating drum hardware from the 

static cases and removal of all blades 

from the HPC stage 3 to 8 drum’’. IAE 

is concerned that confusion could occur 

with the current statement. 

We do not agree. The current 

description is accurate. We did not 

change the AD. 

Request To Eliminate the Mandatory 

Terminating Action 

One commenter requests that we 

revise paragraph (f)(4) of the AD to 

eliminate the 27-month mandatory 

terminating action requirement to 

remove the fully silver plated nuts that 

attach the HPC stage 3 to 8 drum to the 

HPC stage 9 to 12 drum. The commenter 

states that performing repetitive 

ultrasonic inspections will provide an 

acceptable level of safety, and that 

incorporation of the 27-month 

mandatory terminating action 

requirement is an unacceptable cost 

burden to operators. 

We do not agree. We have determined 

that removal of the fully silver plated 

nuts within 27 months from the 

effective date of the AD is required to 

maintain an acceptable level of safety. 

We did not change the 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 

848 IAE V2500–A1, V2522–A5, V2524– 

A5, V2525–D5, V2527–A5, V2527E–A5, 

V2527M–A5, V2528–D5, V2530–A5, 

and V2533–A5 turbofan engines 

installed on airplanes of U.S. registry. 

We estimate that 29 of these engines 

will require ultrasonic inspections, and 

that it will take about 3 work-hours per 

engine to perform one ultrasonic 

inspection. We estimate that it will take 

about 2 work-hours per engine to 

perform the FPI of the HPC stage 3 to 

8 drum, and that the average labor rate 

is $85 per work-hour. We also estimate 

that removal of silver residue from the 

engine will cost about $2,600 per 

engine. Required parts will cost about 

$795 per engine. Based on these figures, 

we estimate the total cost of the AD to 

U.S. operators to be $3,030,515. 

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 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. 

mstockstill on DSKH9S0YB1PROD with RULES

59070 Federal Register / Vol. 75, No. 186 / Monday, September 27, 2010 / Rules and Regulations 

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: 

2010–20–07 International Aero Engines 

AG: Amendment 39–16441. Docket No. 

FAA–2009–1100; Directorate Identifier 

2009–NE–37–AD. 

Effective Date 

(a) This airworthiness directive (AD) 

becomes effective November 1, 2010. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to: 

(1) All International Aero Engines AG (IAE) 

V2500–A1 turbofan engines; and 

(2) All IAE V2525–D5 and V2528–D5 

turbofan engines; and 

(3) IAE V2522–A5, V2524–A5, V2527–A5, 

V2527E–A5, V2527M–A5, V2530–A5, and 

V2533–A5 turbofan engines with serial 

numbers (S/Ns) up to and including V13181, 

and with S/Ns from V15000 up to and 

including V15245. 

(4) These engines are installed on, but not 

limited to, Airbus A319, A320, and A321, 

and McDonnell Douglas MD–90 airplanes. 

Unsafe Condition 

(d) This AD results from reports of 39 highpressure compressor (HPC) stage 3 to 8 

drums found cracked since March 2009. We 

are issuing this AD to prevent uncontained 

failure of the HPC stage 3 to 8 drum, which 

could result in 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. 

Engines Requiring Ultrasonic Inspections of 

the HPC Stage 3 to 8 Drum 

(f) For IAE V2522–A5, V2524–A5, V2527– 

A5, V2527E–A5, V2527M–A5, V2530–A5, 

and V2533–A5 turbofan engines with S/Ns in 

‘‘Group A’’ or ‘‘Group D’’ in IAE Service 

Bulletin (SB) No. V2500–ENG–72–0594, 

Revision 6, dated April 12, 2010, and for 

V2500–A1 turbofan engines with S/Ns in 

‘‘Group A’’ in IAE SB No. V2500–ENG–72– 

0603, Revision 2, dated March 17, 2010, do 

the following: 

(1) Perform an initial ultrasonic inspection 

of the HPC stage 3 to 8 drum using IAE SB 

No. V2500–ENG–72–0594, Revision 6, dated 

April 12, 2010, Accomplishment 

Instructions, paragraph 3, or IAE SB No. 

V2500–ENG–72–0603, Revision 2, dated 

March 17, 2010, Accomplishment 

Instructions, paragraph 3, before 

accumulating 5,200 cycles-since-new (CSN) 

or within 500 cycles from the effective date 

of this AD, whichever occurs later. 

(2) Thereafter, perform repetitive ultrasonic 

inspections of the HPC stage 3 to 8 drum for 

cracks within every 500 cycles-since-lastinspection. 

(3) If cracks or crack indications are 

identified, remove the drum from service 

before further flight. 

Mandatory Terminating Action 

(4) As mandatory terminating action to the 

repetitive inspections required by this AD, at 

the next engine shop visit, but no later than 

27 months after the effective date of this AD, 

do the following before returning any HPC 

stage 3 to 8 drum to service: 

(i) Remove from service fully silver plated 

nuts, part number (P/N) AS44862 or 

equivalent, that attach the HPC stage 3 to 8 

drum to the HPC stage 9 to 12 drum. 

(ii) Remove the silver residue from the HPC 

stage 3 to 8 drum using the IAE SB No. 

V2500–ENG–72–0601, Revision 2, dated 

April 12, 2010, Accomplishment 

Instructions, paragraph 3. Drums cleaned 

before the effective date of this AD using 

engine manual task 72–41–11–110–001 

satisfy this requirement. 

(iii) Fluorescent penetrant inspect (FPI) the 

HPC stage 3 to 8 drum for cracks, and remove 

from service any drum found cracked. You 

can find guidance on performing an FPI of 

the HPC stage 3 to 8 drum in IAE engine 

manual task 72–41–11–200–001. 

(iv) Installation of a zero-time HPC stage 3 

to 8 drum or a drum that has never operated 

with fully silver plated nuts, P/N AS44862 or 

equivalent, that attach the HPC stage 3 to 8 

drum to the HPC stage 9 to 12 drum 

eliminates the need for the cleaning and FPI 

required by paragraphs (f)(4)(ii) and (f)(4)(iii) 

of this AD. 

All Other Engines 

(g) For all other engines, at the next piecepart exposure of the HPC stage 3 to 8 drum 

after the effective date of this AD, do the 

following before returning the drum to 

service: 

(1) Remove from service fully silver plated 

nuts, P/N AS44862 or equivalent, that attach 

the HPC stage 3 to 8 drum to the HPC stage 

9 to 12 drum. 

(2) Remove the silver residue from the HPC 

stage 3 to 8 drum using IAE SB No. V2500– 

ENG–72–0601, Revision 2, dated April 12, 

2010, Accomplishment Instructions, 

paragraph 3. Drums cleaned before the 

effective date of this AD using engine manual 

task 72–41–11–110–001 satisfy this 

requirement. 

(3) FPI the HPC stage 3 to 8 drum for 

cracks, and remove from service any drum 

found cracked. You can find guidance on 

performing an FPI of the HPC stage 3 to 8 

drum in IAE engine manual task 72–41–11– 

200–001. 

(4) Installation of a zero-time HPC stage 3 

to 8 drum or a drum that has never operated 

with fully silver plated nuts, P/N AS44862 or 

equivalent, that attach the HPC stage 3 to 8 

drum to the HPC stage 9 to 12 drum 

eliminates the need for the cleaning and FPI 

required by paragraphs (g)(2) and (g)(3) of 

this AD. 

Definitions 

(h) For the purpose of this AD, an engine 

shop visit is the induction of an engine into 

the shop for maintenance involving the 

separation of a pair of major mating engine 

flanges, except that the separation of engine 

flanges solely for the purposes of 

transportation without subsequent engine 

maintenance is not an engine shop visit. 

(i) For the purpose of this AD, piece-part 

exposure is removal of the HPC stage 3 to 8 

drum from the engine and removal of all 

blades from the drum. 

Previous Credit 

(j) Initial or repetitive ultrasonic 

inspections of the HPC stage 3 to 8 drum 

using IAE SB No. V2500–ENG–72–0594, 

Revision 3, dated August 7, 2009, or Revision 

4, dated October 13, 2009, or Revision 5, 

dated November 23, 2009, before the effective 

date of this AD, meets the inspection 

requirements of paragraphs (f)(1) through 

(f)(3) of this AD. 

(k) Initial or repetitive ultrasonic 

inspections of the HPC stage 3 to 8 drum 

using IAE SB No. V2500–ENG–72–0603, 

Original Issue, dated November 24 2009, or 

Revision 1, dated December 18, 2009, before 

the effective date of this AD, meets the 

inspection requirements of paragraphs (f)(1) 

through (f)(3) of this AD. 

Alternative Methods of Compliance 

(AMOCS) 

(l) The Manager, Engine Certification 

Office, has the authority to approve AMOCs 

for this AD if requested using the procedures 

found in 14 CFR 39.19. 

Related Information 

(m) Contact Mark Riley, Aerospace 

Engineer, Engine Certification Office, FAA, 

Engine and Propeller Directorate, 12 New 

England Executive Park, Burlington, MA 

01803; e-mail: mark.riley@faa.gov; telephone 

(781) 238–7758, fax (781) 238–7199, for more 

information about this AD. 

(n) Contact International Aero Engines AG, 

400 Main Street, East Hartford, CT 06108; 

telephone: (860) 565–5515; fax: (860) 565– 

5510, for a copy of the service information 

referenced in this AD. 

Material Incorporated by Reference 

(o) You must use the service information 

specified in the following Table 1 to perform 

the inspections and silver residue removal 

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 

International Aero Engines AG, 400 Main 

Street, East Hartford, CT 06108; telephone: 

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Federal Register / Vol. 75, No. 186 / Monday, September 27, 2010 / Rules and Regulations 59071 

(860) 565–5515; fax: (860) 565–5510, 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/ibr-locations.html. 

TABLE 1—INCORPORATION BY REFERENCE

International Aero Engines Service Bulletin No. Page Revision Date 

V2500–ENG–72–0594 ...................................................................................................................... ALL ...... 6 April 12, 2010. 

Total Pages: 61.

V2500–ENG–72–0601 ...................................................................................................................... ALL ...... 2 April 12, 2010. 

Total Pages: 9.

V2500–ENG–72–0603 ...................................................................................................................... ALL ...... 2 March 17, 2010. 

Total pages: 46.

Issued in Burlington, Massachusetts, on 

September 15, 2010. 

Robert J. Ganley, 

Acting Manager, Engine and Propeller 

Directorate, Aircraft Certification Service. 

[FR Doc. 2010–23832 Filed 9–24–10; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–0439; Directorate 

Identifier 2010–NM–029–AD; Amendment 

39–16437; AD 2010–20–03] 

RIN 2120–AA64 

Airworthiness Directives; Bombardier, 

Inc. Model CL–600–2B16 (CL–604 

Variants (Including CL–605 Marketing 

Variant)) 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 five reported cases of * * * 

balance washer screw failure on similar 

ADGs [air-driven generators]/ram air turbines 

installed on other aircraft types, investigation 

by Hamilton Sundstrand determined that a 

specific batch of the screws had a 

metallographic non-conformity that 

increased their susceptibility to brittle 

fracture. * * * 

Failure of a balance washer screw can 

result in loss of the related balance washer, 

with consequent turbine imbalance. Such 

imbalance could potentially result in ADG 

structural failure (including blade failure), 

loss of ADG electrical power and structural 

damage to the aircraft and, if deployment was 

activated by a dual engine shutdown, could 

also result in loss of hydraulic power for the 

flight controls [and consequent reduced 

ability of the flightcrew to maintain the safe 

flight and landing of the airplane]. 

* * * * * 

We are issuing this AD to require 

actions to correct the unsafe condition 

on these products. 

DATES: This AD becomes effective 

November 1, 2010. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of November 1, 2010. 

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: 

Christopher Alfano, Aerospace 

Engineer, Airframe and Mechanical 

Systems Branch, ANE–171, FAA, New 

York Aircraft Certification Office, 1600 

Stewart Avenue, Suite 410, Westbury, 

New York 11590; telephone (516) 228– 

7340; 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 June 2, 2010 (75 FR 30740). 

That NPRM proposed to correct an 

unsafe condition for the specified 

products. The MCAI states: 

Following five reported cases of * * * 

balance washer screw failure on similar 

ADGs [air-driven generators]/ram air turbines 

installed on other aircraft types, investigation 

by Hamilton Sundstrand determined that a 

specific batch of the screws had a 

metallographic non-conformity that 

increased their susceptibility to brittle 

fracture. Subsequently, it was established 

that 152 ‘‘dry’’ ADGs [Hamilton Sundstrand 

Part Numbers (P/Ns) in the 761339 series and 

1711405; see Note] either had nonconforming screws installed during 

production or possibly during maintenance 

or repair at Hamilton Sundstrand repair 

stations. 

Failure of a balance washer screw can 

result in loss of the related balance washer, 

with consequent turbine imbalance. Such 

imbalance could potentially result in ADG 

structural failure (including blade failure), 

loss of ADG electrical power and structural 

damage to the aircraft and, if deployment was 

activated by a dual engine shutdown, could 

also result in loss of hydraulic power for the 

flight controls [and consequent reduced 

ability of the flightcrew to maintain the safe 

flight and landing of the airplane]. 

This [Canadian] directive mandates 

checking of the ADG and replacing the 

balance washer screws, if required. It also 

prohibits future installation of unmodified 

ADGs. 

Note: ADGs with Hamilton Sundstrand 

P/Ns in the 761339 series and 1711405 are 

installed on the aircraft model listed in the 

Applicability section above in addition to 

Bombardier Inc. Models CL–600–2B19, CL– 

600–2C10 and CL–600–2D24. The latter three 

models are covered in a separate directive. 

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 

received no comments on the NPRM or 

on the determination of the cost to the 

public. 

Conclusion 

We reviewed the available data and 

determined that air safety and the 

public interest require adopting the AD 

as proposed. 

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. 

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