This section of the FEDERAL REGISTER

contains notices to the public of the proposed

issuance of rules and regulations. The

purpose of these notices is to give interested

persons an opportunity to participate in the

rule making prior to the adoption of the final

rules.

Proposed Rules Federal Register

6860 

Vol. 75, No. 29 

Friday, February 12, 2010 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2009–0544; Directorate 

Identifier 2009–NE–37–AD] 

RIN 2120–AA64 

Airworthiness Directives; International 

Aero Engines AG (IAE) 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: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: The FAA proposes to adopt 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 proposed AD 

would require initial and repetitive onwing ultrasonic inspections (UIs) of the 

high-pressure compressor (HPC) stage 3 

to 8 drum for cracks. As mandatory 

terminating action to the repetitive 

inspections, this proposed AD would 

require 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 

proposed AD would require 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 proposed AD 

results from reports of 39 HPC stage 3 

to 8 drums found cracked since March 

2009. We are proposing this AD to 

prevent uncontained failure of the HPC 

stage 3 to 8 drum, which could result in 

damage to the airplane. 

DATES: We must receive any comments 

on this proposed AD by April 13, 2010. 

ADDRESSES: Use one of the following 

addresses to comment on this proposed 

AD. 

• Federal eRulemaking Portal: Go to 

http://www.regulations.gov and follow 

the instructions for sending your 

comments electronically. 

• Mail: Docket Management Facility, 

U.S. Department of Transportation, 1200 

New Jersey Avenue, SE., West Building 

Ground Floor, Room W12–140, 

Washington, DC 20590–0001. 

• Hand Delivery: Deliver to Mail 

address above between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

• Fax: (202) 493–2251. 

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 identified in this proposed 

AD. 

FOR FURTHER INFORMATION CONTACT: 

Kevin Dickert, Aerospace Engineer, 

Engine Certification Office, FAA, Engine 

and Propeller Directorate, 12 New 

England Executive Park, Burlington, MA 

01803; e-mail: kevin.dickert@faa.gov; 

telephone (781) 238–7117, fax (781) 

238–7199. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to send us any written 

relevant data, views, or arguments 

regarding this proposal. Send your 

comments to an address listed under 

ADDRESSES. Include ‘‘Docket No. FAA– 

2009–0544; Directorate Identifier 2009– 

NE–37–AD’’ in the subject line of your 

comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of the proposed AD. We will 

consider all comments received by the 

closing date and may amend the 

proposed AD in light of those 

comments. 

We will post all comments we 

receive, without change, to http:// 

www.regulations.gov, including any 

personal information you provide. We 

will also post a report summarizing each 

substantive verbal contact with FAA 

personnel concerning this proposed AD. 

Using the search function of the Web 

site, anyone can find and read the 

comments in any of our dockets, 

including, if provided, the name of the 

individual who sent the comment (or 

signed the comment on behalf of an 

association, business, labor union, etc.). 

You may review the DOT’s complete 

Privacy Act Statement in the Federal 

Register published on April 11, 2000 

(65 FR 19477–78). 

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 proposed AD, the 

regulatory evaluation, any comments 

received, and other information. The 

street address for the Docket Operations 

office (telephone (800) 647–5527) is the 

same as the Mail address provided in 

the ADDRESSES section. Comments will 

be available in the AD docket shortly 

after receipt. 

Discussion 

Since March 2009, we received 

reports of 12 V2500–A5 series HPC stage 

3 to 8 drums found cracked during shop 

visit inspections, and reports of 24 

V2500–A5 series HPC stage 3 to 8 drums 

found cracked during on-wing 

inspections. We also received reports of 

3 V2500–A1 stage 3 to 8 drums found 

cracked during shop visits. Analysis 

revealed that high levels of chlorine in 

the engine, combined with engine 

operation in high temperature and high 

humidity environments, led to 

depletion of the silver plating on the 

exterior of the nuts that attach the HPC 

stage 3 to 8 drum to the HPC stage 9 to 

12 drum. The depletion of the silver 

plating led to deposits of silver chloride 

on the HPC stage 3 to 8 drum, causing 

stress corrosion and cracking. This 

condition, if not corrected, could result 

in uncontained failure of the HPC stage 

3 to 8 drum, which could result in 

damage to the airplane. 

Relevant Service Information 

We have reviewed and approved the 

technical contents of IAE Service 

Bulletin (SB) No. V2500–ENG–72–0594, 


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Federal Register / Vol. 75, No. 29 / Friday, February 12, 2010 / Proposed Rules 6861 

Revision 5, dated November 23, 2009, 

and IAE SB No. V2500–ENG–0603, 

Revision 1, dated December 18, 2009, 

which describe procedures for 

performing initial and repetitive onwing UIs of HPC stage 3 to 8 drums for 

cracks. We have also reviewed and 

approved the technical contents of IAE 

SB No. V2500–ENG–72–0601, Revision 

1, dated December 18, 2009, which 

describes procedures for removal of 

silver residue from the HPC stage 3 to 

8 drum. Although SB No. V2500–ENG– 

72–0601, Revision 1, dated December 

18, 2009, only specifies certain S/N 

engines in the effectivity section, we are 

proposing to require accomplishing this 

bulletin on all engines affected by this 

AD. 

V2500–A5 series engines with S/Ns 

listed in Groups ‘‘A’’ and ‘‘D’’ of IAE SB 

No. V2500–ENG–72–0594, Revision 5, 

dated November 23, 2009, and V2500– 

A1 series engines with S/Ns listed in 

‘‘Group A’’ of IAE SB No. V2500–ENG– 

72–0603, Revision 1, dated December 

18, 2009, are those engines suspect of 

having been exposed to excessive levels 

of chlorine contamination. These 

engines require initial and repetitive 

inspection of the HPC stage 3 to 8 drum 

for cracks, and removal from service of 

the fully silver plated nuts joining the 

HPC stage 3 to 8 drum to the HPC stage 

9 to 12 drum within 27 months from the 

effective date of the proposed AD. 

FAA’s Determination and Requirements 

of the Proposed AD 

We have evaluated all pertinent 

information and identified an unsafe 

condition that is likely to exist or 

develop on other products of this same 

type design. We are proposing this AD, 

which would 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 UIs of 

HPC stage 3 to 8 drums for cracks; 

and 

Æ As mandatory terminating action to 

the repetitive UIs, 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. 

The proposed AD would require you to 

use the service information described 

previously to perform the inspections 

and removal of silver residue. 

Costs of Compliance 

We estimate that this proposed AD 

would 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 would require UIs, and 

that it would take about 3 work-hours 

per engine to perform one UI. We 

estimate that it would 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 would cost about $2,600 per 

engine. Required parts would cost about 

$795 per engine. Based on these figures, 

we estimate the total cost of the 

proposed 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 

proposed AD would not have federalism 

implications under Executive Order 

13132. This proposed AD would 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 the proposed 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. Would 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 proposed AD. 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. 

The Proposed Amendment 

Under the authority delegated to me 

by the Administrator, the Federal 

Aviation Administration proposes to 

amend 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: 

International Aero Engines AG: Docket No. 

FAA–2009–0544; Directorate Identifier 

2009–NE–37–AD. 

Comments Due Date 

(a) The Federal Aviation Administration 

(FAA) must receive comments on this 

airworthiness directive (AD) action by April 

13, 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 


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6862 Federal Register / Vol. 75, No. 29 / Friday, February 12, 2010 / Proposed Rules 

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 

(UI) 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 5, dated November 23, 2009, and for 

V2500–A1 turbofan engines with S/Ns in 

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

0603, Revision 1, dated December 18, 2009, 

do the following: 

(1) Perform an initial UI of the HPC stage 

3 to 8 drum using paragraph 3 of the 

Accomplishment Instructions of IAE SB No. 

V2500–ENG–72–0594, Revision 5, dated 

November 23, 2009, or IAE SB No. V2500– 

ENG–72–0603, Revision 1, dated December 

18, 2009, as applicable, 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 UIs of the 

HPC stage 3 to 8 drum for cracks within 

every 500 cycles-since-last-inspection. 

(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 8 to 12 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 paragraph 3 of the 

Accomplishment Instructions of IAE SB No. 

V2500–ENG–72–0601, Revision 1, dated 

December 18, 2009. 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 paragraph 3 of the 

Accomplishment Instructions of IAE SB No. 

V2500–ENG–72–0601, Revision 1, dated 

December 18, 2009. 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 does not constitute an engine 

shop visit. 

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

exposure of the HPC stage 3 to 8 drum is 

removal of the 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, 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, 

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 

(l) 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 

(m) Contact Kevin Dickert, Aerospace 

Engineer, Engine Certification Office, FAA, 

Engine and Propeller Directorate, 12 New 

England Executive Park, Burlington, MA 

01803; e-mail: kevin.dickert@faa.gov; 

telephone (781) 238–7117, 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. 

Issued in Burlington, Massachusetts, on 

February 8, 2010. 

Peter A. White, 

Assistant Manager, Engine and Propeller 

Directorate, Aircraft Certification Service. 

[FR Doc. 2010–2999 Filed 2–11–10; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–0039; Directorate 

Identifier 2009–NM–239–AD] 

RIN 2120–AA64 

Airworthiness Directives; Bombardier, 

Inc. Model CL–600–1A11 (CL–600), CL– 

600–2A12 (CL–601), CL–600–2B16 (CL– 

601–3A, CL–601–3R, and CL–604 

Variants (Including CL–605 Marketing 

Variant)) Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for the 

products listed above. This proposed 

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: 

Seven cases of on-ground hydraulic 

accumulator screw cap or end cap failure 

have been experienced on CL–600–2B19 

(CRJ) aircraft, resulting in loss of the 

associated hydraulic system and high-energy 

impact damage to adjacent systems and 

structure. * * * 

* * * * * 

A detailed analysis of the systems and 

structure in the potential line of trajectory of 

a failed screw cap/end cap for each 

accumulator * * * has been conducted. It 

has been identified that the worst case 

scenario would be failure of one of the brake 

accumulator screw caps/end caps, resulting 

in impact damage causing loss of both 

hydraulic systems No. 2 and No. 3, with 

consequent loss of both braking and nose 

wheel steering and the potential for a runway 

excursion [resulting in damage to the 

airplane and hazards to persons or property 

on the ground]. 

* * * * * 

The proposed AD would require actions 

that are intended to address the unsafe 

condition described in the MCAI. 


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