32802 Federal Register / Vol. 74, No. 130 / Thursday, July 9, 2009 / Rules and Regulations 

(2) For airplanes manufactured after 

August 18, 2000, each flight data 

recorder system required by this section 

must be installed in accordance with the 

requirements of § 23.1459(a) (except 

paragraphs (a)(3)(ii) and (6)), (b), (d) and 

(e), or § 25.1459(a) (except paragraphs 

(a)(3)(ii) and (7)), (b), (d) and (e) of this 

chapter. A correlation must be 

established between the values recorded 

by the flight data recorder and the 

corresponding values being measured. 

The correlation must contain a 

sufficient number of correlation points 

to accurately establish the conversion 

from the recorded values to engineering 

units or discrete state over the full 

operating range of the parameter. Except 

for airplanes having separate altitude 

and airspeed sensors that are an integral 

part of the flight data recorder system, 

a single correlation may be established 

for any group of airplanes— 

* * * * * 

Issued in Washington, DC, on July 2, 2009. 

Pamela Hamilton-Powell, 

Director, Office of Rulemaking. 

[FR Doc. E9–16056 Filed 7–8–09; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2009–0046; Directorate 

Identifier 2008–NE–05–AD; Amendment 39– 

15962; AD 2009–14–12] 

RIN 2120–AA64 

Airworthiness Directives; Pratt & 

Whitney Canada Corp. (P&WC) Models 

PW305A and PW305B Turbofan 

Engines 

AGENCY: Federal Aviation 

Administration (FAA), 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) 

issued 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: 

P&WC has determined that the PostService Bulletin (SB) PW300–72–24287 High 

Pressure Compressor (HPC) drum rotor 

assemblies P/N 30B2478 and 30B2542 on PW 

305A and 305B engines with single stage 

coated labyrinth seals, are susceptible to 

developing significant cracks in the region of 

the labyrinth seal. 

We are issuing this AD to detect cracks 

in the HPC drum rotor assembly, which 

could lead to an uncontained failure of 

the drum rotor assembly and damage to 

the airplane. 

DATES: This AD becomes effective 

August 13, 2009. 

ADDRESSES: 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: Ian 

Dargin, Aerospace Engineer, Engine 

Certification Office, FAA, Engine & 

Propeller Directorate, 12 New England 

Executive Park, Burlington, MA 01803; 

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

(781) 238–7178; fax (781) 238–7199. 

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 February 20, 2009 (74 FR 

7836). That NPRM proposed to correct 

an unsafe condition for the specified 

products. The MCAI states: 

P&WC has determined that the PostService Bulletin (SB) PW300–72–24287 High 

Pressure Compressor (HPC) drum rotor 

assemblies P/N 30B2478 and 30B2542 on PW 

305A and 305B engines with single stage 

coated labyrinth seals, are susceptible to 

developing significant cracks in the region of 

the labyrinth seal. 

P&WC issued SB PW300–72–24462 for 

initial inspection of affected HPC drum rotor 

assemblies for cracks. In addition, the PW305 

Maintenance Manual (MM) 05–20–00 was 

revised (Revision No. 26) accordingly, to add 

requirement for repeat inspection interval. A 

new P/N 31B6325–01, HPC drum rotor 

assembly, which is not susceptible to subject 

cracking, is made available through SB 

PW300–72–24376, as terminating action for 

the required repeat inspection. 

Recent data (Ref: SIL: PW300–093) indicate 

that a number of high-time Pre-SB–PW300– 

72–24376 HPC drum rotor assemblies (P/N 

30B2478 and 30B2542), with potential for a 

hazardous disk failure in consequence of 

non-compliance with the inspection 

requirements, are still in-service. This AD is 

issued to mandate the inspection of the 

affected P/N 30B2478 and 30B2542 HPC 

drum rotor assemblies in accordance with 

PW305–MM–05–20–00 requirements. 

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. 

Costs of Compliance 

Based on the service information, we 

estimate that this AD will affect about 

540 products of U.S. registry. We also 

estimate that it will take about 10 workhours per product to comply with this 

AD. The average labor rate is $80 per 

work-hour. Required parts will cost 

about $5,000 per product. Based on 

these figures, we estimate the cost of the 

AD on U.S. operators to be $3,132,000. 

Our cost estimate is exclusive of 

possible warranty coverage. 

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. 


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Federal Register / Vol. 74, No. 130 / Thursday, July 9, 2009 / Rules and Regulations 32803 

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 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. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, 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: 

2009–14–12 Pratt & Whitney Canada Corp: 

Amendment 39–15962. Docket No. 

FAA–2009–0046; Directorate Identifier 

2008–NE–05–AD. 

Effective Date 

(a) This airworthiness directive (AD) 

becomes effective August 13, 2009. 

Affected ADs 

(b) None. 

(c) This AD applies to Pratt & Whitney 

Canada Corp. (P&WC) Models PW305A and 

PW305B turbofan engines with high pressure 

compressor (HPC) drum rotor assemblies, 

post P&WC Service Bulletin (SB) PW300–72– 

24287 but without P&WC SB PW300–72– 

24376, installed. These engines are installed 

on, but not limited to, Bombardier Learjet 

M60 and Hawker Beechcraft 1000 series 

airplanes. 

Reason 

(d) P&WC has determined that the PostService Bulletin (SB) PW300–72–24287 High 

Pressure Compressor (HPC) drum rotor 

assemblies P/N 30B2478 and 30B2542 on 

PW305A and 305B engines with single stage 

coated labyrinth seals, are susceptible to 

developing significant cracks in the region of 

the labyrinth seal. 

We are issuing this AD to detect cracks in the 

HPC drum rotor assembly, which could lead 

to an uncontained failure of the drum rotor 

assembly and damage to the airplane. 

Actions and Compliance 

(e) Unless already done, do the following 

actions. 

(1) Within 500 flight hours after effective 

date of this directive, borescope-inspect the 

interiors of affected HPC rotor assemblies for 

cracks. If a crack is found, remove the engine 

before next flight for HPC drum rotor 

replacement. Pratt & Whitney Maintenance 

Manual, Chapter 72–00–00, contains 

guidance on borescope inspection. 

Credit for Previous Inspections 

(2) Inspection of affected HPC drum rotor 

assembly per P&WC SB PW300–72–24462 

and or SB PW305 MM 05–20–00 inspection 

requirements prior to the effective date of 

this directive satisfies the requirements of 

paragraph (e)(1) of this AD. 

(3) Repeat borescope inspection per 

paragraph (e)(1) of this AD, at intervals not 

exceeding 1,350 flight cycles. If a crack is 

found, remove the engine before next flight 

for HPC rotor drum replacement. 

Optional Terminating Action 

(4) Replacement of the affected HPC rotor 

assembly P/N 30B2478 or 30B2542 with PostSB PW300–72–24376 assembly P/N 

31B6325–01 or later superseding P/N, will 

constitute terminating action for the 

inspection requirements of the above 

paragraphs (e)(1) and (e)(2) of the corrective 

action requirements of this AD. 

Other FAA AD Provisions 

(f) Alternative Methods of Compliance 

(AMOCs): 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 

(g) Refer to Canadian Airworthiness 

Directive CF–2007–25R1, dated February 13, 

2008, and P&WC SB PW300–72–24462, dated 

December 13, 1999, for related information. 

Contact Pratt & Whitney Canada Corp., 1000 

Marie-Victorin, Longueuil, Quebec, Canada 

J4G 1A1, telephone: (800) 268–8000, for a 

copy of this service information. 

(h) Contact Ian Dargin, Aerospace 

Engineer, Engine Certification Office, FAA, 

Engine & Propeller Directorate, 12 New 

England Executive Park, Burlington, MA 

01803; e-mail: ian.dargin@faa.gov; telephone 

(781) 238–7178; fax (781) 238–7199, for more 

information about this AD. 

Material Incorporated by Reference 

(i) None. 

Issued in Burlington, Massachusetts, on 

June 30, 2009. 

Francis A. Favara, 

Manager, Engine and Propeller Directorate, 

Aircraft Certification Service. 

[FR Doc. E9–16111 Filed 7–8–09; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 91 

[Docket No. FAA–2008–0937; Amendment 

No. 91–308] 

RIN 2120–AJ37 

Drug and Alcohol Testing Program; 

Technical Amendment 

AGENCY: Federal Aviation 

Administration, DOT. 

ACTION: Final rule; technical 

amendment. 

SUMMARY: The Federal Aviation 

Administration (FAA) is making minor 

technical changes to a final rule 

published in the Federal Register on 

May 14, 2009. That final rule amended 

the FAA’s drug and alcohol regulations 

to place them in a new part. In that final 

rule the FAA inadvertently did not 

include an instruction to amend a crossreference to two appendices. 

DATES: Effective Dates: Effective on July 

13, 2009. 

FOR FURTHER INFORMATION CONTACT: 

Rafael Ramos, Office of Aerospace 

Medicine, Drug Abatement Division, 

AAM–800, Federal Aviation 

Administration, 800 Independence 

Avenue, SW., Washington, DC 20591; 

telephone (202) 267–8442; facsimile 

(202) 267–5200; e-mail 

drugabatement@faa.gov. 

SUPPLEMENTARY INFORMATION: The 

Federal Aviation Administration (FAA) 

published a document in the Federal 

Register May 14, 2009, in 74 FR 22649 

that amended the regulations governing 

FAA-required drug and alcohol testing 

requirements. The FAA inadvertently 

did not include an instruction to revise 

language in § 91.146 to change the 

reference to the drug and alcohol testing 

program regulation title from the old (14 

CFR part 121, appendices I and J) to 

new, 14 CFR part 120. This amendment 

will not impose any additional 

restrictions on operators affected by 

these regulations. 

Technical Amendment 

The technical amendment will further 

amend part 91 by updating a crossreference in § 91.146(b). 

List of Subjects in 14 CFR Part 91 

Aircraft, Airmen, Aviation safety. 

■ Accordingly, Title 14 of the Code of 

Federal Regulations (CFR) part 91 is 

amended as follows: 


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