Airworthiness Directives; Pratt & Whitney JT8D-7, -7A, -7B, -9, -9A, -11, -15, and -17 Turbofan Engines, 62229-62231 [E9-27518]

Download as PDF Federal Register / Vol. 74, No. 227 / Friday, November 27, 2009 / Rules and Regulations the Instructions for Continued Airworthiness, as required by paragraph (f) of this AD, do not need to be reworked in accordance with the CDCCLs. However, once the ALS of the Instructions for Continued Airworthiness has been revised, future maintenance actions on these components must be done in accordance with the CDCCLs. FAA AD Differences Note 3: This AD differs from the MCAI and/or service information as follows: No differences. Other FAA AD Provisions (g) The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, New York ACO, ANE–170, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. Send information to ATTN: Program Manager, Continuing Operational Safety, FAA, New York ACO, 1600 Stewart Avenue, Suite 410, Westbury, New York, 11590; telephone 516– 228–7300; fax 516–794–5531. Before using any approved AMOC on any airplane to which the AMOC applies, notify your principal maintenance inspector (PMI) or principal avionics inspector (PAI), as appropriate, or lacking a principal inspector, your local Flight Standards District Office. The AMOC approval letter must specifically reference this AD. (2) Airworthy Product: For any requirement in this AD to obtain corrective actions from a manufacturer or other source, use these actions if they are FAA-approved. Corrective actions are considered FAA-approved if they are approved by the State of Design Authority (or their delegated agent). You are required to ensure the product is airworthy before it is returned to service. (3) Reporting Requirements: For any reporting requirement in this AD, under the provisions of the Paperwork Reduction Act (44 U.S.C. 3502 et seq.), the Office of Management and Budget (OMB) has approved the information collection requirements and has assigned OMB Control Number 2120–0056. srobinson on DSKHWCL6B1PROD with RULES Related Information (h) Refer to MCAI Canadian Airworthiness Directive CF–2008–07, dated January 25, 2008; and CRJ 700/900 Series Regional Jet (Bombardier) Temporary Revision 2–222, dated March 30, 2006; for related information. Material Incorporated by Reference (i) You must use CRJ 700/900 Series Regional Jet (Bombardier) Temporary Revision 2–222, dated March 30, 2006, to Section 3, ‘‘Fuel System Limitations,’’ of Part 2 of Bombardier CL–600–2C10, CL–600– 2D15 and CL–600–2D24 Maintenance Requirements Manual CSP B–053, 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 CRJ 700/900 Series Regional Jet (Bombardier) Temporary Revision 2–222, dated March 30, 2006, to Section 3, ‘‘Fuel VerDate Nov<24>2008 16:26 Nov 25, 2009 Jkt 220001 System Limitations,’’ of Part 2 of Bombardier CL–600–2C10, CL–600–2D15, and CL–600– 2D24 Maintenance Requirements Manual CSP B–053, on June 6, 2008 (73 FR 24145, May 2, 2008). (2) For service information identified in ˆ this AD, contact Bombardier, Inc., 400 Cote´ Vertu Road West, Dorval, Quebec H4S 1Y9, Canada; telephone 514–855–5000; fax 514– 855–7401; e-mail thd.crj@aero.bombardier.com; Internet http:// www.bombardier.com. (3) You may review copies of the service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington. For information on the availability of this material at the FAA, call 425–227–1221 or 425–227–1152. (4) You may also review copies of the service information that is incorporated by reference 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/ code_of_federal_regulations/ ibr_locations.html. Issued in Renton, Washington, on November 18, 2009. Stephen P. Boyd, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E9–28297 Filed 11–25–09; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2009–0317; Directorate Identifier 79–ANE–18; Amendment 39– 16087; AD 2009–24–01] RIN 2120–AA64 Airworthiness Directives; Pratt & Whitney JT8D–7, –7A, –7B, –9, –9A, –11, –15, and –17 Turbofan Engines AGENCY: Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. SUMMARY: The FAA is superseding an existing airworthiness directive (AD) for Pratt & Whitney JT8D–1, –1A, –1B, –7, –7A, –7B, –9, –9A, –11, –15, and –17 turbofan engines with 2nd stage fan blades, part number (P/N) 433802, 645902, 759902, 695932, 678102, or 746402, installed. That AD currently requires initial and repetitive ultrasonic inspection (UI) and fluorescent penetrant inspection (FPI) of those P/N 2nd stage fan blades. This AD replaces the required FPI with eddy current inspection (ECI) on all affected 2nd stage fan blades and maintains the requirement of UI of the blade root PO 00000 Frm 00023 Fmt 4700 Sfmt 4700 62229 attachment on some of the affected 2nd stage fan blades. This AD also introduces an optional terminating action to the repetitive blade inspections for certain engine models. This AD results from reports of 10 fractures of 2nd stage fan blades since AD 87–14–01R1 became effective. We are issuing this AD to prevent uncontained failure of 2nd stage fan blades, which could result in damage to the airplane. DATES: This AD becomes effective January 4, 2010. The Director of the Federal Register approved the incorporation by reference of certain publications listed in the regulations as of January 4, 2010. ADDRESSES: You can get the service information identified in this AD from Pratt & Whitney, 400 Main St., East Hartford, CT 06108; telephone (860) 565–8770; fax (860) 565–4503. 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: 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: The FAA proposed to amend 14 CFR part 39 by superseding AD 87–14–01 R1, Amendment 39–6359 (54 FR 43954, October 30, 1989), with a proposed AD. The proposed AD applies to JT8D–7, –7A, –7B, –9, –9A, –11, –15, and –17 turbofan engines with 2nd stage fan blades, P/N 433802, 645902, 759902, 695932, 678102, or 746402 installed. We published the proposed AD in the Federal Register on August 7, 2009 (74 FR 39582). That action proposed to replace the required FPI with ECI on all affected 2nd stage fan blades and would maintain the requirement of UI of the blade root attachment on some of the affected 2nd stage fan blades. That action also proposed to introduce an optional terminating action to the repetitive blade inspections for certain engine models. 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 E:\FR\FM\27NOR1.SGM 27NOR1 62230 Federal Register / Vol. 74, No. 227 / Friday, November 27, 2009 / Rules and Regulations 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 comment received. One commenter, FedEx Express, requests that we add a requirement to the AD to mandate the inspections to be performed at a repair agency having engine overhaul capabilities. We do not agree. Code of Federal Regulations, 14 Part 43 (Maintenance, Preventative Maintenance, Rebuilding, and Alteration) establish the requirements as to who can perform these types of actions on typecertificated products, including the actions specified in this AD. Restating these requirements in the AD is unnecessary. We did not change the AD. Conclusion We have carefully reviewed the available data, including the comment received, and determined that air safety and the public interest require adopting the AD as proposed. srobinson on DSKHWCL6B1PROD with RULES Costs of Compliance We estimate that this AD will affect 1,380 engines installed on airplanes of U.S. registry. We also estimate that it will take about 25 work-hours per engine to perform one inspection cycle, and that the average labor rate is $80 per work-hour. Based on these figures, we estimate the total cost of the AD to U.S. operators to be $2,760,000. 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 VerDate Nov<24>2008 16:26 Nov 25, 2009 Jkt 220001 products identified in this rulemaking action. Regulatory Findings We have determined that this AD will not have federalism implications under Executive Order 13132. This AD will not have a substantial direct effect on the States, on the relationship between the national government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify that this AD: (1) Is not a ‘‘significant regulatory action’’ under Executive Order 12866; (2) Is not a ‘‘significant rule’’ under DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); and (3) Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. We prepared a summary of the costs to comply with this AD and placed it in the AD Docket. You may get a copy of this summary at the address listed under ADDRESSES. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, the Federal Aviation Administration amends 14 CFR part 39 as follows: ■ PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: ■ Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The FAA amends § 39.13 by removing Amendment 39–6359 (54 FR 43954, October 30, 1989), and by adding a new airworthiness directive, Amendment 39–16087, to read as follows: ■ 2009–24–01 Pratt & Whitney: Amendment 39–16087. Docket No. FAA–2009–0317; Directorate Identifier 79–ANE–18. Effective Date (a) This airworthiness directive (AD) becomes effective January 4, 2010. Affected ADs (b) This AD supersedes AD 87–14–01 R1, Amendment 39–6359. Applicability (c) This AD applies to Pratt & Whitney JT8D–7, –7A, –7B, –9, –9A, –11, –15, and –17 PO 00000 Frm 00024 Fmt 4700 Sfmt 4700 turbofan engines, with 2nd stage fan blades, part number (P/N) 433802, 645902, 759902, 695932, 678102, or 746402, installed. These engines are installed on, but not limited to, Boeing 727, 737, and McDonnell Douglas DC–9 series airplanes. Unsafe Condition (d) This AD results from reports of 10 fractures of 2nd stage fan blades since AD 87–14–01R1 became effective. We are issuing this AD to prevent uncontained failure of 2nd stage fan blades, 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. 2nd Stage Fan Blade Inspections (f) For 2nd stage fan blades, P/N 678102 and P/N 746402, perform an eddy current inspection (ECI) of the blade pin-root holes for cracks, and for 2nd stage fan blades, P/Ns 433802, 645902, 759902, and 695932, perform an ECI of the blade pin-root holes and perform an ultrasonic inspection (UI) of the blade root attachment for cracks, as follows: (1) Perform an inspection at the first disassembly of the 2nd stage fan rotor from the low-pressure (LP) compressor after accumulation of 3,000 cycles-in-service (CIS) since the last inspection of the blade root attachment, not to exceed 10,000 CIS since last inspection. (2) If the 2nd stage fan blades were new at their last installation onto the 2nd stage fan disk, inspect at the first disassembly of the 2nd stage fan rotor from the LP compressor after accumulating 3,000 cycles-since-new (CSN), not to exceed 10,000 CSN. (3) Thereafter, inspect the 2nd stage fan blades at each disassembly of the 2nd stage fan rotor from the LP compressor after accumulating 3,000 CIS, not to exceed 10,000 CIS since the last inspection. (4) Guidance on performing ECIs and UIs of the 2nd stage fan blade pin-root holes and blade root attachments can be found in Pratt & Whitney Maintenance Advisory Notice MAN–JT8D–1–08. Contact Pratt & Whitney, 400 Main St., East Hartford, CT 06108; telephone (860) 565–8770; fax (860) 565– 4503, for a copy of this service information. (5) Remove from service before further flight any 2nd stage fan blades that are found cracked. Optional Terminating Action (g) For JT8D–9, –9A, –11, –15, and –17 engines, as optional terminating action to the repetitive inspections required by this AD, replace the affected 2nd stage fan blades with redesigned 2nd stage fan blades using Pratt & Whitney Service Bulletin No. 5866, Revision 2, dated October 20, 1998. Alternative Methods of Compliance (h) The Manager, Engine Certification Office, FAA, has the authority to approve alternative methods of compliance for this AD, if requested using the procedures found in 14 CFR 39.19. E:\FR\FM\27NOR1.SGM 27NOR1 Federal Register / Vol. 74, No. 227 / Friday, November 27, 2009 / Rules and Regulations Related Information (i) 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. Material Incorporated by Reference (j) You must use Pratt & Whitney Service Bulletin No. 5866, Revision 2, dated October 20, 1998, to perform the optional terminating action in this AD. The Director of the Federal Register approved the incorporation by reference of this service bulletin in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Contact Pratt & Whitney, 400 Main St., East Hartford, CT 06108; telephone (860) 565–8770; fax (860) 565–4503, for a copy of this service information. You may review copies at the FAA, New England Region, 12 New England Executive Park, Burlington, MA; or at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202–741–6030, or go to: http:// www.archives.gov/federal-register/cfr/ibrlocations.html. Issued in Burlington, Massachusetts, on November 9, 2009. Peter A. White, Assistant Manager, Engine and Propeller Directorate, Aircraft Certification Service. [FR Doc. E9–27518 Filed 11–25–09; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2009–0411; Directorate Identifier 2008–NM–190–AD; Amendment 39–16095; AD 2009–24–07] RIN 2120–AA64 Airworthiness Directives; Boeing 737– 600, –700, –700C, and –800 Series Airplanes srobinson on DSKHWCL6B1PROD with RULES AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Final rule. SUMMARY: We are adopting a new airworthiness directive (AD) for certain Boeing Model 737–600, –700, –700C, and –800 series airplanes. This AD requires repetitive lubrications of the right and left main landing gear (MLG) forward trunnion pins. This AD also requires an inspection for discrepancies of the transition radius of the MLG forward trunnion pins, and corrective actions if necessary. For certain airplanes, this AD also requires repetitive detailed inspections for discrepancies (including finish damage, corrosion, pitting, and base metal VerDate Nov<24>2008 16:26 Nov 25, 2009 Jkt 220001 scratches) of the transition radius of the left and right MLG trunnion pins, and corrective action if necessary. Replacing or overhauling the trunnion pins terminates the actions required by this AD. This AD results from a report that the protective finishes on the forward trunnion pins for the left and right MLG might have been damaged during final assembly. We are issuing this AD to prevent stress corrosion cracking of the forward trunnion pins, which could result in fracture of the pins and consequent collapse of the MLG. DATES: This AD is effective January 4, 2010. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in the AD as of January 4, 2010. ADDRESSES: For service information identified in this AD, contact Boeing Commercial Airplanes, Attention: Data & Services Management, P.O. Box 3707, MC 2H–65, Seattle, Washington 98124– 2207; telephone 206–544–5000, extension 1; fax 206–766–5680; e-mail me.boecom@boeing.com; Internet https://www.myboeingfleet.com. Examining the AD Docket You may examine the AD docket on the Internet at http:// www.regulations.gov; or in person at the Docket Management Facility 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 address for the Docket Office (telephone 800–647–5527) is the Document Management Facility, U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue, SE., Washington, DC 20590. FOR FURTHER INFORMATION CONTACT: Nancy Marsh, Aerospace Engineer, Airframe Branch, ANM–120S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue, SW., Renton, Washington 98057–3356; telephone (425) 917–6440; fax (425) 917–6590. SUPPLEMENTARY INFORMATION: Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to include an airworthiness directive (AD) that would apply to certain Boeing Model 737–600, –700, –700C, and –800 series airplanes. That NPRM was published in the Federal Register on May 5, 2009 (74 FR 20661). That NPRM proposed to require repetitive lubrications of the right and left main landing gear (MLG) forward PO 00000 Frm 00025 Fmt 4700 Sfmt 4700 62231 trunnion pins. That NPRM also proposed to require an inspection for discrepancies of the transition radius of the MLG forward trunnion pins, and corrective actions if necessary. For certain airplanes, that NPRM also proposed to require repetitive detailed inspections for discrepancies (including finish damage, corrosion, pitting, and base metal scratches) of the transition radius of the left and right MLG trunnion pins, and corrective action if necessary. Replacing or overhauling the trunnion pins would terminate the actions proposed by that NPRM. Comments We gave the public the opportunity to participate in developing this AD. We considered the comments received from the commenters. Support for the NPRM Boeing and Alaska Airlines support the NPRM. Request To Change Reference to Terminating Action in Paragraph (h) of the Final Rule Air Transport Association (ATA), on behalf of its member AirTran, states that paragraph (h) of the NPRM should refer to paragraph (j) of the NPRM instead of paragraph (i) of the NPRM as the optional terminating action. We agree that paragraph (h) of the NPRM should reference paragraph (j) of the NPRM. We have changed this final rule accordingly. Request To Clarify Service Information ATA, on behalf of its member AirTran, states that Boeing Special Attention Service Bulletin 737–32– 1402, dated August 6, 2008 (the source of service information cited in the NPRM), contains two errors. AirTran notes a discrepancy between the part number cited in the materials section of the service bulletin and the Work Instructions. AirTran states that the section titled ‘‘Parts and Materials Supplied by the Operator’’ of the service bulletin identifies BMS3–26 as ‘‘grease—aircraft general purpose.’’ However, AirTran notes that BMS3–26 is a corrosion-inhibiting compound, and the work instructions for the lubrication requirement identify Boeing specification BMS3–33 for the grease. In addition, the materials section of the service bulletin identifies MS20995NC32 (corrosion-resistant steel). AirTran requests that we provide clarification regarding the correct safety wire to be used for the trunnion pin installation to ensure consistent fleet compliance. E:\FR\FM\27NOR1.SGM 27NOR1

Agencies

[Federal Register Volume 74, Number 227 (Friday, November 27, 2009)]
[Rules and Regulations]
[Pages 62229-62231]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E9-27518]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2009-0317; Directorate Identifier 79-ANE-18; Amendment 
39-16087; AD 2009-24-01]
RIN 2120-AA64


Airworthiness Directives; Pratt & Whitney JT8D-7, -7A, -7B, -9, -
9A, -11, -15, and -17 Turbofan Engines

AGENCY: Federal Aviation Administration (FAA), Department of 
Transportation (DOT).

ACTION: Final rule.

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

SUMMARY: The FAA is superseding an existing airworthiness directive 
(AD) for Pratt & Whitney JT8D-1, -1A, -1B, -7, -7A, -7B, -9, -9A, -11, 
-15, and -17 turbofan engines with 2nd stage fan blades, part number 
(P/N) 433802, 645902, 759902, 695932, 678102, or 746402, installed. 
That AD currently requires initial and repetitive ultrasonic inspection 
(UI) and fluorescent penetrant inspection (FPI) of those P/N 2nd stage 
fan blades. This AD replaces the required FPI with eddy current 
inspection (ECI) on all affected 2nd stage fan blades and maintains the 
requirement of UI of the blade root attachment on some of the affected 
2nd stage fan blades. This AD also introduces an optional terminating 
action to the repetitive blade inspections for certain engine models. 
This AD results from reports of 10 fractures of 2nd stage fan blades 
since AD 87-14-01R1 became effective. We are issuing this AD to prevent 
uncontained failure of 2nd stage fan blades, which could result in 
damage to the airplane.

DATES: This AD becomes effective January 4, 2010. The Director of the 
Federal Register approved the incorporation by reference of certain 
publications listed in the regulations as of January 4, 2010.

ADDRESSES: You can get the service information identified in this AD 
from Pratt & Whitney, 400 Main St., East Hartford, CT 06108; telephone 
(860) 565-8770; fax (860) 565-4503.
    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: 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: The FAA proposed to amend 14 CFR part 39 by 
superseding AD 87-14-01 R1, Amendment 39-6359 (54 FR 43954, October 30, 
1989), with a proposed AD. The proposed AD applies to JT8D-7, -7A, -7B, 
-9, -9A, -11, -15, and -17 turbofan engines with 2nd stage fan blades, 
P/N 433802, 645902, 759902, 695932, 678102, or 746402 installed. We 
published the proposed AD in the Federal Register on August 7, 2009 (74 
FR 39582). That action proposed to replace the required FPI with ECI on 
all affected 2nd stage fan blades and would maintain the requirement of 
UI of the blade root attachment on some of the affected 2nd stage fan 
blades. That action also proposed to introduce an optional terminating 
action to the repetitive blade inspections for certain engine models.

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

[[Page 62230]]

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 comment received.
    One commenter, FedEx Express, requests that we add a requirement to 
the AD to mandate the inspections to be performed at a repair agency 
having engine overhaul capabilities.
    We do not agree. Code of Federal Regulations, 14 Part 43 
(Maintenance, Preventative Maintenance, Rebuilding, and Alteration) 
establish the requirements as to who can perform these types of actions 
on type-certificated products, including the actions specified in this 
AD. Restating these requirements in the AD is unnecessary. We did not 
change the AD.

Conclusion

    We have carefully reviewed the available data, including the 
comment received, and determined that air safety and the public 
interest require adopting the AD as proposed.

Costs of Compliance

    We estimate that this AD will affect 1,380 engines installed on 
airplanes of U.S. registry. We also estimate that it will take about 25 
work-hours per engine to perform one inspection cycle, and that the 
average labor rate is $80 per work-hour. Based on these figures, we 
estimate the total cost of the AD to U.S. operators to be $2,760,000.

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.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

Adoption of the Amendment

0
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

0
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]

0
2. The FAA amends Sec.  39.13 by removing Amendment 39-6359 (54 FR 
43954, October 30, 1989), and by adding a new airworthiness directive, 
Amendment 39-16087, to read as follows:

2009-24-01 Pratt & Whitney: Amendment 39-16087. Docket No. FAA-2009-
0317; Directorate Identifier 79-ANE-18.

Effective Date

    (a) This airworthiness directive (AD) becomes effective January 
4, 2010.

Affected ADs

    (b) This AD supersedes AD 87-14-01 R1, Amendment 39-6359.

Applicability

    (c) This AD applies to Pratt & Whitney JT8D-7, -7A, -7B, -9, -
9A, -11, -15, and -17 turbofan engines, with 2nd stage fan blades, 
part number (P/N) 433802, 645902, 759902, 695932, 678102, or 746402, 
installed. These engines are installed on, but not limited to, 
Boeing 727, 737, and McDonnell Douglas DC-9 series airplanes.

Unsafe Condition

    (d) This AD results from reports of 10 fractures of 2nd stage 
fan blades since AD 87-14-01R1 became effective. We are issuing this 
AD to prevent uncontained failure of 2nd stage fan blades, 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.

2nd Stage Fan Blade Inspections

    (f) For 2nd stage fan blades, P/N 678102 and P/N 746402, perform 
an eddy current inspection (ECI) of the blade pin-root holes for 
cracks, and for 2nd stage fan blades, P/Ns 433802, 645902, 759902, 
and 695932, perform an ECI of the blade pin-root holes and perform 
an ultrasonic inspection (UI) of the blade root attachment for 
cracks, as follows:
    (1) Perform an inspection at the first disassembly of the 2nd 
stage fan rotor from the low-pressure (LP) compressor after 
accumulation of 3,000 cycles-in-service (CIS) since the last 
inspection of the blade root attachment, not to exceed 10,000 CIS 
since last inspection.
    (2) If the 2nd stage fan blades were new at their last 
installation onto the 2nd stage fan disk, inspect at the first 
disassembly of the 2nd stage fan rotor from the LP compressor after 
accumulating 3,000 cycles-since-new (CSN), not to exceed 10,000 CSN.
    (3) Thereafter, inspect the 2nd stage fan blades at each 
disassembly of the 2nd stage fan rotor from the LP compressor after 
accumulating 3,000 CIS, not to exceed 10,000 CIS since the last 
inspection.
    (4) Guidance on performing ECIs and UIs of the 2nd stage fan 
blade pin-root holes and blade root attachments can be found in 
Pratt & Whitney Maintenance Advisory Notice MAN-JT8D-1-08. Contact 
Pratt & Whitney, 400 Main St., East Hartford, CT 06108; telephone 
(860) 565-8770; fax (860) 565-4503, for a copy of this service 
information.
    (5) Remove from service before further flight any 2nd stage fan 
blades that are found cracked.

Optional Terminating Action

    (g) For JT8D-9, -9A, -11, -15, and -17 engines, as optional 
terminating action to the repetitive inspections required by this 
AD, replace the affected 2nd stage fan blades with redesigned 2nd 
stage fan blades using Pratt & Whitney Service Bulletin No. 5866, 
Revision 2, dated October 20, 1998.

Alternative Methods of Compliance

    (h) The Manager, Engine Certification Office, FAA, has the 
authority to approve alternative methods of compliance for this AD, 
if requested using the procedures found in 14 CFR 39.19.

[[Page 62231]]

Related Information

    (i) 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.

Material Incorporated by Reference

    (j) You must use Pratt & Whitney Service Bulletin No. 5866, 
Revision 2, dated October 20, 1998, to perform the optional 
terminating action in this AD. The Director of the Federal Register 
approved the incorporation by reference of this service bulletin in 
accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Contact Pratt & 
Whitney, 400 Main St., East Hartford, CT 06108; telephone (860) 565-
8770; fax (860) 565-4503, 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.

    Issued in Burlington, Massachusetts, on November 9, 2009.
Peter A. White,
Assistant Manager, Engine and Propeller Directorate, Aircraft 
Certification Service.
[FR Doc. E9-27518 Filed 11-25-09; 8:45 am]
BILLING CODE 4910-13-P