Airworthiness Directives; Pratt & Whitney Canada Corp. (P&WC) Models PW305A and PW305B Turbofan Engines, 7836-7838 [E9-3622]

Download as PDF 7836 Federal Register / Vol. 74, No. 33 / Friday, February 20, 2009 / Proposed Rules 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 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 this proposed regulation: 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. You can find our regulatory evaluation and the estimated costs of compliance in the AD Docket. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. The Proposed Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA 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 AD: Boeing: Docket No. FAA–2008–0612; Directorate Identifier 2008–NM–059–AD. Comments Due Date (a) We must receive comments by March 17, 2009. Affected ADs (b) None. VerDate Nov<24>2008 17:28 Feb 19, 2009 Jkt 217001 Applicability (c) This AD applies to all Boeing Model 747–100, 747–100B, 747–100B SUD, 747– 200B, 747–200C, 747–200F, 747–300, 747– 400, 747–400D, 747–400F, 747SR, and 747SP series airplanes, certificated in any category. Subject (d) Air Transport Association (ATA) of America Code 53: Fuselage. Unsafe Condition (e) This AD results from a report of a crack found in the right-side Stringer 11 longeron horizontal flange, adjacent to the horizontal stabilizer pivot bulkhead, during a routine maintenance inspection. We are issuing this AD to detect and correct fatigue cracking of the longeron, which can propagate and cause damage to the adjacent horizontal stabilizer pivot bulkhead. This damage could result in loss of structural integrity and consequent inability of the bulkhead to carry flight loads, which could adversely affect controllability of the airplane. Compliance (f) Comply with this AD within the compliance times specified, unless already done. Inspection/Related Investigative and Corrective Actions (g) Except as provided by paragraph (h) of this AD: At the applicable times specified in paragraph 1.E. of Boeing Service Bulletin 747–53A2703, Revision 1, dated September 16, 2008, do a surface high frequency eddy current (HFEC) inspection for cracks in the left- and right-side Stringer 11 longeron exposed surfaces and edges between Station 2598 and 2607 adjacent to the horizontal stabilizer pivot bulkhead; and do all applicable related investigative and corrective actions before further flight, in accordance with the Accomplishment Instructions of Boeing Service Bulletin 747– 53A2703, Revision 1, dated September 16, 2008, except as provided by paragraph (h) of this AD. Exception to Compliance Times (h) Where Boeing Service Bulletin 747– 53A2703, Revision 1, dated September 16, 2008, specifies counting the compliance time from ‘‘* * * the date on this service bulletin,’’ this AD requires counting the compliance time from the effective date of this AD. Exception to Corrective Actions (i) If any crack is found during any inspection required by this AD, and Boeing Service Bulletin 747–53A2703, Revision 1, dated September 16, 2008, specifies to contact Boeing for appropriate action: Before further flight, repair using a method approved in accordance with the procedures specified in paragraph (j) of this AD. Alternative Methods of Compliance (AMOCs) (j)(1) The Manager, Seattle Aircraft Certification Office (ACO), FAA, ATTN: Ivan Li, Aerospace Engineer, Airframe Branch, ANM–120S, FAA, Seattle ACO, 1601 Lind Avenue, SW., Renton, Washington 98057– PO 00000 Frm 00007 Fmt 4702 Sfmt 4702 3356; telephone (425) 917–6437; fax (425) 917–6590 has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. (2) To request a different method of compliance or a different compliance time for this AD, follow the procedures in 14 CFR 39.19. Before using any approved AMOC on any airplane to which the AMOC applies, notify your principal maintenance inspector (PMI) or principal avionics inspector (PAI), or lacking a principal inspector, your local Flight Standards District Office. The AMOC approval letter must specifically reference this AD. (3) An AMOC that provides an acceptable level of safety may be used for any repair required by this AD, if it is approved by an Authorized Representative for the Boeing Commercial Airplanes Delegation Option Authorization Organization who has been authorized by the Manager, Seattle ACO, to make those findings. For a repair method to be approved, the repair must meet the certification basis of the airplane, and the approval must specifically refer to this AD. Issued in Renton, Washington, on January 30, 2009. Stephen P. Boyd, Assistant Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E9–3614 Filed 2–19–09; 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] RIN 2120–AA64 Airworthiness Directives; Pratt & Whitney Canada Corp. (P&WC) Models PW305A and PW305B Turbofan Engines 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) 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. E:\FR\FM\20FEP1.SGM 20FEP1 Federal Register / Vol. 74, No. 33 / Friday, February 20, 2009 / Proposed Rules We are proposing 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: We must receive comments on this proposed AD by March 23, 2009. ADDRESSES: You may send comments by any of the following methods: • 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. 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. 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: Comments Invited We invite you to send any written relevant data, views, or arguments about this proposed AD. Send your comments to an address listed under the ADDRESSES section. Include ‘‘Docket No. FAA–2009–0046; Directorate Identifier 2008–NE–05–AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this proposed AD. We will consider all comments received by the closing date and may amend this proposed AD based on those comments. We will post all comments we receive, without change, to http:// www.regulations.gov, including any personal information you provide. We VerDate Nov<24>2008 17:28 Feb 19, 2009 Jkt 217001 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). Discussion Transport Canada, which is the aviation authority for Canada, has issued Canadian Airworthiness Directive CF–2007–25R1, dated February 13, 2008 (referred to after this as ‘‘the MCAI’’), 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. You may obtain further information by examining the MCAI in the AD docket. Relevant Service Information Pratt & Whitney Canada Corp. has issued Service Bulletin PW300–72– 24462, dated December 13, 1999. The actions described in this service information are intended to correct the unsafe condition identified in the MCAI. FAA’s Determination and Requirements of This Proposed AD This product has been approved by the aviation authority of Canada, and is PO 00000 Frm 00008 Fmt 4702 Sfmt 4702 7837 approved for operation in the United States. Pursuant to our bilateral agreement with Canada, they have notified us of the unsafe condition described in the MCAI and service information referenced above. We are issuing this AD because we evaluated all the information provided by Canada and determined the unsafe condition exists and is likely to exist or develop on other products of the same type design. Costs of Compliance Based on the service information, we estimate that this proposed AD would affect about 540 products of U.S. registry. We also estimate that it would take about 10 work-hours per product to comply with this proposed AD. The average labor rate is $80 per work-hour. Required parts would cost about $5,000 per product. Based on these figures, we estimate the cost of the proposed 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 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 this proposed regulation: 1. Is not a ‘‘significant regulatory action’’ under Executive Order 12866; E:\FR\FM\20FEP1.SGM 20FEP1 7838 Federal Register / Vol. 74, No. 33 / Friday, February 20, 2009 / Proposed Rules 2. Is not a ‘‘significant rule’’ under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); and 3. Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. We prepared a regulatory evaluation of the estimated costs to comply with this proposed AD and placed it in the AD docket. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Safety. The Proposed Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA 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 AD: Pratt & Whitney Canada Corp.: Docket No. FAA–2009–0046; Directorate Identifier 2008–NE–05–AD. Comments Due Date (a) We must receive comments by March 23, 2009. Affected Airworthiness Directives (ADs) (b) None. Applicability (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. VerDate Nov<24>2008 17:28 Feb 19, 2009 Jkt 217001 (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 information about 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. Issued in Burlington, Massachusetts, on February 13, 2009. Peter A. White, Assistant Manager, Engine and Propeller Directorate, Aircraft Certification Service. [FR Doc. E9–3622 Filed 2–19–09; 8:45 am] BILLING CODE 4910–13–P COMMODITY FUTURES TRADING COMMISSION 17 CFR Parts 1, 30, and 140 RIN 3038–AC72 Acknowledgment Letters for Customer Funds and Secured Amount Funds Commodity Futures Trading Commission. AGENCY: PO 00000 Frm 00009 Fmt 4702 Sfmt 4702 ACTION: Notice of proposed rulemaking. SUMMARY: The Commodity Futures Trading Commission (‘‘Commission’’ or ‘‘CFTC’’) is proposing to amend its regulations regarding the required content of the acknowledgment letter that a registrant must obtain from any depository holding its segregated customer funds or funds of foreign futures or foreign options customers, and certain technical changes. DATES: Submit comments on or before March 23, 2009. ADDRESSES: You may submit comments, identified by RIN number, by any of the following methods: • Federal eRulemaking Portal: http:// www.regulations.gov. Follow the instructions for submitting comments. • Agency Web Site: http:// www.cftc.gov. Follow the instructions for submitting comments on the Web site. • E-mail: secretary@cftc.gov. Include the RIN number in the subject line of the message. • Fax: 202–418–5521. • Mail: David A. Stawick, Secretary of the Commission, Commodity Futures Trading Commission, Three Lafayette Centre, 1155 21st Street, NW., Washington, DC 20581. • Hand Delivery/Courier: Same as mail above. FOR FURTHER INFORMATION CONTACT: Eileen A. Donovan, Special Counsel, 202–418–5096, edonovan@cftc.gov; Division of Clearing and Intermediary Oversight, Commodity Futures Trading Commission, Three Lafayette Centre, 1155 21st Street, NW., Washington, DC 20581. SUPPLEMENTARY INFORMATION: I. Background Regulation 1.20 (17 CFR 1.20) requires futures commission merchants (FCMs) that accept customer funds and derivatives clearing organizations (DCOs) that accept customer funds from FCMs to segregate and separately account for those funds.1 Currently, Regulation 1.20 requires such FCMs and DCOs to obtain from the bank, trust company, FCM or DCO holding customer funds in the capacity of a depository (each, a ‘‘Depository’’) a written acknowledgment that the Depository was informed that the customer funds deposited therein are those of commodity or option customers and are being held in accordance with the provisions of the Commodity Exchange Act (Act) 2 and CFTC 1 See 17 CFR 1.3(gg) (defining the term ‘‘customer funds’’). 2 7 U.S.C. 1 et seq. E:\FR\FM\20FEP1.SGM 20FEP1

Agencies

[Federal Register Volume 74, Number 33 (Friday, February 20, 2009)]
[Proposed Rules]
[Pages 7836-7838]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E9-3622]


-----------------------------------------------------------------------

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2009-0046; Directorate Identifier 2008-NE-05-AD]
RIN 2120-AA64


Airworthiness Directives; Pratt & Whitney Canada Corp. (P&WC) 
Models PW305A and PW305B Turbofan Engines

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) 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 Post-Service 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.


[[Page 7837]]


We are proposing 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: We must receive comments on this proposed AD by March 23, 2009.

ADDRESSES: You may send comments by any of the following methods:
     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.

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.

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:

Comments Invited

    We invite you to send any written relevant data, views, or 
arguments about this proposed AD. Send your comments to an address 
listed under the ADDRESSES section. Include ``Docket No. FAA-2009-0046; 
Directorate Identifier 2008-NE-05-AD'' at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of this proposed AD. We 
will consider all comments received by the closing date and may amend 
this proposed AD based on 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).

Discussion

    Transport Canada, which is the aviation authority for Canada, has 
issued Canadian Airworthiness Directive CF-2007-25R1, dated February 
13, 2008 (referred to after this as ``the MCAI''), to correct an unsafe 
condition for the specified products. The MCAI states:

    P&WC has determined that the Post-Service 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.

    You may obtain further information by examining the MCAI in the AD 
docket.

Relevant Service Information

    Pratt & Whitney Canada Corp. has issued Service Bulletin PW300-72-
24462, dated December 13, 1999. The actions described in this service 
information are intended to correct the unsafe condition identified in 
the MCAI.

FAA's Determination and Requirements of This Proposed AD

    This product has been approved by the aviation authority of Canada, 
and is approved for operation in the United States. Pursuant to our 
bilateral agreement with Canada, they have notified us of the unsafe 
condition described in the MCAI and service information referenced 
above. We are issuing this AD because we evaluated all the information 
provided by Canada and determined the unsafe condition exists and is 
likely to exist or develop on other products of the same type design.

Costs of Compliance

    Based on the service information, we estimate that this proposed AD 
would affect about 540 products of U.S. registry. We also estimate that 
it would take about 10 work-hours per product to comply with this 
proposed AD. The average labor rate is $80 per work-hour. Required 
parts would cost about $5,000 per product. Based on these figures, we 
estimate the cost of the proposed 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 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 this proposed 
regulation:
    1. Is not a ``significant regulatory action'' under Executive Order 
12866;

[[Page 7838]]

    2. Is not a ``significant rule'' under the DOT Regulatory Policies 
and Procedures (44 FR 11034, February 26, 1979); and
    3. Will not have a significant economic impact, positive or 
negative, on a substantial number of small entities under the criteria 
of the Regulatory Flexibility Act.
    We prepared a regulatory evaluation of the estimated costs to 
comply with this proposed AD and placed it in the AD docket.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Safety.

The Proposed Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA 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.


Sec.  39.13  [Amended]

    2. The FAA amends Sec.  39.13 by adding the following new AD:

Pratt & Whitney Canada Corp.: Docket No. FAA-2009-0046; Directorate 
Identifier 2008-NE-05-AD.

Comments Due Date

    (a) We must receive comments by March 23, 2009.

Affected Airworthiness Directives (ADs)

    (b) None.

Applicability

    (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 Post-Service 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 information about 
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 Post-SB 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.

    Issued in Burlington, Massachusetts, on February 13, 2009.
Peter A. White,
Assistant Manager, Engine and Propeller Directorate, Aircraft 
Certification Service.
 [FR Doc. E9-3622 Filed 2-19-09; 8:45 am]
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