Airworthiness Directives; Pratt & Whitney JT8D Series Turbofan Engines, 73361-73364 [05-23897]

Download as PDF 73361 Federal Register / Vol. 70, No. 237 / Monday, December 12, 2005 / Rules and Regulations Part nomenclature Part number Stage 6 LPT Disk ..................................................................... Stage 7 LPT Disk ..................................................................... CIR manual section ALL .............. ALL .............. 72–53–16 72–53–61 CIR manual inspection CIR manual Insp/Check–02 ........................ Insp/Check–02 ........................ 51A357 51A357 For Engine Manual 51A345, add the following table data: Part nomenclature Stage Stage Stage Stage Stage Stage Stage 3 4 5 6 7 8 9 LPT LPT LPT LPT LPT LPT LPT Disk Disk Disk Disk Disk Disk Disk Part number ..................................................................... ..................................................................... ..................................................................... ..................................................................... ..................................................................... ..................................................................... ..................................................................... ALL ALL ALL ALL ALL ALL ALL CIR manual section .............. .............. .............. .............. .............. .............. .............. 72–53–13 72–53–14 72–53–60 72–53–16 72–53–72 72–53–62 72–53–63 CIR manual inspection CIR manual Insp/Check–02, Config–1 ....... Insp/Check–02 ........................ Insp/Check–02 ........................ Insp/Check–02, Config–1 ....... Insp/Check–02 ........................ Insp/Check–02, Config–1 ....... Insp/Check–02 ........................ 51A750 51A750 51A750 51A750 51A750 51A750 51A750 For Engine Manual 51A751, add the following table data: CIR manual section Part nomenclature Part number Stage 3 LPT Disk ..................................................................... ALL .............. 72–53–13 Stage 4 LPT Disk ..................................................................... Stage 5 LPT Disk ..................................................................... Stage 6 LPT Disk ..................................................................... ALL .............. ALL .............. ALL .............. 72–53–14 72–53–60 72–53–16 Stage 7 LPT Disk ..................................................................... Stage 8 LPT Disk ..................................................................... ALL .............. ALL .............. 72–53–72 72–53–62 Stage 9 LPT Disk ..................................................................... ALL .............. 72–53–63 CIR manual inspection CIR manual Insp/Check–02, Config–2. See Note (1). Insp/Check–02 ........................ Insp/Check–02 ........................ Insp/Check–02, Config–2. See Note (1). Insp/Check–02 ........................ Insp/Check–02, Config–2. See Note (1). Insp/Check–02 ........................ 51A750 51A750 51A750 51A750 51A750 51A750 51A750 (1) FPI method only. (2) For the purposes of these mandatory inspections, piece-part opportunity means: (i) The part is considered completely disassembled when done in accordance with the disassembly instructions in the manufacturer’s engine manual to either part number level listed in the table above, and (ii) The part has accumulated more than 100 cycles in service since the last piece-part opportunity inspection, provided that the part was not damaged or related to the cause for its removal from the engine.’’ Alternative Methods of Compliance (g) You must perform these mandatory inspections using the TLS and the applicable Engine Manual unless you receive approval to use an alternative method of compliance under paragraph (h) of this AD. Section 43.16 of the Federal Aviation Regulations (14 CFR 43.16) may not be used to approve alternative methods of compliance or adjustments to the times in which these inspections must be performed. (h) 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. Maintaining Records of the Mandatory Inspections (i) You have met the requirements of this AD by using a TLS of the manufacturer’s VerDate Aug<31>2005 15:45 Dec 09, 2005 Jkt 208001 engine manual changed as specified in paragraph (f) of this AD, and, for air carriers operating under part 121 of the Federal Aviation Regulations (14 CFR part 121), by modifying your continuous airworthiness maintenance plan to reflect those changes. You must maintain records of the mandatory inspections that result from those changes to the TLS according to the regulations governing your operation. You do not need to record each piece-part inspection as compliance to this AD. For air carriers operating under part 121, you may use either the system established to comply with section 121.369 or use an alternative system that your principal maintenance inspector has accepted if that alternative system: (1) Includes a method for preserving and retrieving the records of the inspections resulting from this AD; and (2) Meets the requirements of section 121.369(c); and (3) Maintains the records either indefinitely or until the work is repeated. (j) These record keeping requirements apply only to the records used to document the mandatory inspections required as a result of revising the TLS as specified in paragraph (f) of this AD, and do not alter or amend the record keeping requirements for any other AD or regulatory requirement. PO 00000 Frm 00015 Fmt 4700 Sfmt 4700 Related Information (k) None. Issued in Burlington, Massachusetts, on December 5, 2005. Carlos Pestana, Acting Manager, Engine and Propeller Directorate, Aircraft Certification Service. [FR Doc. 05–23828 Filed 12–9–05; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. 98–ANE–48–AD; Amendment 39–14398; AD 2005–25–05] RIN 2120–AA64 Airworthiness Directives; Pratt & Whitney JT8D Series Turbofan Engines Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: SUMMARY: The FAA is superseding an existing airworthiness directive (AD) for E:\FR\FM\12DER1.SGM 12DER1 73362 Federal Register / Vol. 70, No. 237 / Monday, December 12, 2005 / Rules and Regulations Pratt & Whitney (PW) JT8D–1, –1A, –1B, –7, –7A, –7B, –9, –9A, –11, –15, –15A, –17, –17A, –17R, and –17AR series turbofan engines. That AD currently requires revisions to the engine manufacturer’s time limits section (TLS) to include enhanced inspection of selected critical life-limited parts at each piece-part opportunity. This AD modifies the airworthiness limitations section of the manufacturer’s manual and an air carrier’s approved continuous airworthiness maintenance program to add an eddy current inspection. An FAA study of in-service events involving uncontained failures of critical rotating engine parts has indicated the need for mandatory inspections. The mandatory inspections are needed to identify those critical rotating parts with conditions, which if allowed to continue in service, could result in uncontained failures. We are issuing this AD to prevent critical lifelimited rotating engine part failure, which could result in an uncontained engine failure and damage to the airplane. This AD becomes effective June 12, 2006. DATES: You may examine the AD docket at the FAA, New England Region, Office of the Regional Counsel, 12 New England Executive Park, Burlington, MA. ADDRESSES: FOR FURTHER INFORMATION CONTACT: Keith Lardie, Aerospace Engineer, Engine Certification Office, FAA, Engine and Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803–5299; telephone (781) 238–7189, fax (781) 238–7199. The FAA proposed to amend 14 CFR Part 39 with a proposed airworthiness directive (AD). The proposed AD applies to PW JT8D– 1, –1A, –1B, –7, –7A, –7B, –9, –9A, –11, –15, –15A, –17, –17A, –17R, and –17AR series turbofan engines. We published the proposed AD in the Federal Register on August 18, 2004 (69 FR 51203). That action proposed to require modifying the time limitations section of the manufacturer’s manual and an air carrier’s approved continuous airworthiness maintenance program to incorporate additional inspection requirements. SUPPLEMENTARY INFORMATION: Examining the AD Docket You may examine the AD Docket (including any comments and service information), by appointment, between 8 a.m. and 4:30 p.m., Monday through Friday, except Federal holidays. See ADDRESSES for the location. VerDate Aug<31>2005 15:45 Dec 09, 2005 Jkt 208001 Comments We provided the public the opportunity to participate in the development of this AD. We have considered the comments received. Request To Change the Effective Date One commenter asks us to change the effective date to six to eight months. The commenter states the change will allow additional time to order, fabricate, and install automated inspection equipment. It will also allow more time to train employees on using the new equipment. We agree. We have extended the effective date 180 days to allow operators to set up their inspection process. Concern the Costs To Comply Are Too Low One commenter suggests the NPRM fails to recognize the substantial upfront investment to get the equipment needed for the eddy current inspection (ECI). In addition, the commenter states we should increase the Costs of Compliance because the complex inspections will require several fulltime, specially trained operators. We don’t agree. The AD doesn’t require air carriers to invest in tooling and equipment or hire more personnel to comply with the proposed AD. The AD requires adding the new ECI to the TLS of the engine manufacturer’s manual, and to the air carriers’ approved maintenance manuals. Operators can choose to buy equipment to perform the inspection, or they may send the disk to an approved service provider. We have not changed the AD. Request To Change the ECI for Repaired Parts to Fluorescent Penetrant Inspection (FPI) The same commenter asks us to change the inspection method for parts previously repaired with bushings from an automated eddy current method to a fluorescent penetrant method. The commenter states that one cannot perform an automated ECI with the bushings installed. The commenter states that removing the bushings to perform the automated ECI would leave score marks because of the tight fit. We don’t agree. The operators don’t need to remove the bushings. The instructions for Section 72–33–31, Inspection –05, and Section 72–33–33, Inspection –03, state that holes with bushings installed are not subject to the ECI. Holes with bushings installed are subject to FPI and an additional visual inspection within the ECI instructions. We have not changed the AD. PO 00000 Frm 00016 Fmt 4700 Sfmt 4700 Request To Perform an FPI If the Part Fails the ECI The same commenter suggests that service-run parts that fail the automated ECI should be subjected to an FPI. If the part fails the FPI, then the part is scrap. If the part passes the FPI, then it would be acceptable to perform the bushing repair. The commenter states that there is a possibility of false readings due to worn or oblong, but not cracked, holes that cause ‘‘liftoff’’ of the probe. We don’t agree. The inspection instructions provide an opportunity to clean and reinspect the part. If the part fails again, the operator may return the disk to the manufacturer for a third opinion before determining if the part is acceptable or if it is scrap. The operator may propose other alternatives through the Alternative Method of Compliance process. We have not changed the AD. Request for Clear Direction for Preparing the Surface of a Hole The same commenter asks us to provide clear direction for preparing the surface of a hole that is worn, oblong, or scored from removing a bushing. The commenter states the automated ECI equipment is extremely sensitive to surface finish. It might be necessary to machine the surface to provide an acceptable surface finish for the inspection. The commenter further states this is not desirable since the machining operation might mask or remove crack indications. We do not agree that we need to provide clearer instructions. The manufacturer has provided instructions to prepare the part for ECI. This AD does not allow any machining operations, although it does allow certain cleaning operations. Bushings are not subject to the ECI and must not be removed. We have not changed the AD. Conclusion We have carefully reviewed the available data, including the comments received, and determined that air safety and the public interest require adopting the AD with the changes described previously. We have determined that these changes will neither increase the economic burden on any operator nor increase the scope of the AD. Costs of Compliance There are about 6,085 Pratt & Whitney JT8D–1, –1A, –1B, –7, –7A, –7B, –9, –9A, –11, –15, –15A, –17, –17A, –17R, and –17AR series turbofan engines of the affected design in the worldwide fleet. We estimate that this AD will affect 3,236 engines installed on airplanes of U.S. registry. We also estimate that it will take about 8 work E:\FR\FM\12DER1.SGM 12DER1 Federal Register / Vol. 70, No. 237 / Monday, December 12, 2005 / Rules and Regulations hours per engine to perform the proposed inspections, and that the average labor rate is $65 per work hour. Since this is an added inspection requirement, included as part of the normal maintenance cycle, no additional part costs are involved. Based on these figures, we estimate the total cost of the AD to U.S. operators to be $1,682,720. 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 by sending a request to us at the address listed under ADDRESSES. Include ‘‘AD Docket No. 98–ANE–48– AD’’ in your request. 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 Federal Aviation Administration amends 14 CFR part 39 as follows: I PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: I Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The FAA amends § 39.13 by removing Amendment 39–12867, (67 FR 55108 August 28, 2002), and by adding a new airworthiness directive, Amendment 39–14398, to read as follows: I 2005–25–05 Pratt & Whitney: Amendment 39–14398. Docket No. 98–ANE–48–AD. Effective Date (a) This AD becomes effective June 12, 2006. Affected ADs (b) This AD supersedes AD 2002–17–02. Applicability (c) This AD applies to Pratt & Whitney (PW) JT8D–1, –1A, –1B, –7, –7A, –7B, –9, –9A, –11, –15, –15A, –17, –17A, –17R, and Description VerDate Aug<31>2005 15:45 Dec 09, 2005 Jkt 208001 PO 00000 Frm 00017 –17AR series turbofan engines. These engines are installed on, but not limited to Boeing 727 and 737 series, and McDonnell Douglas DC–9 series airplanes. Unsafe Condition (d) This AD results from the need to require enhanced inspection of selected critical life-limited parts of PW JT8D series turbofan engines. We are issuing this AD to prevent critical life-limited rotating engine part failure, which could result in an uncontained engine failure and 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. (f) Within the next 30 days after the effective date of this AD, (1) revise the Time Limits Section (TLS) of the manufacturer’s Engine Manual, Part Number 481672, as appropriate for PW JT8D–1, –1A, –1B, –7, –7A, –7B, –9, –9A, –11, –15, –15A, –17, –17A, –17R, and –17AR series turbofan engines, and (2) for air carriers, revise the approved mandatory inspections section of the continuous airworthiness maintenance program, by adding the following: ‘‘Critical Life Limited Part Inspection A. Inspection Requirements: (1) This section has the definitions for individual engine piece parts and the inspection procedures which are necessary when these parts are removed from the engine. (2) It is necessary to do the inspection procedures of the piece parts in paragraph B when: (a) The part is removed from the engine and disassembled to the level specified in paragraph B and (b) The part has accumulated more than 100 cycles since the last piece part inspection, provided that the part was not damaged or related to the cause for its removal from the engine. (3) The inspections specified in this paragraph do not replace or make not necessary other recommended inspections for these parts or other parts. B. Parts Requiring Inspection: Note: Piece part is defined as any of the listed parts with all the blades removed. Section Hub (Disk), 1st Stage Compressor: Hub Detail—All P/Ns .................................................................................................................. Hub Assembly—All P/Ns ............................................................................................................ 2nd Stage Compressor: Disk—All P/Ns ............................................................................................................................ Disk Assembly—All P/Ns ............................................................................................................ Disk, 13th Stage Compressor—All P/Ns ........................................................................................... HP Turbine Disk, First Stage w/integral Shaft—All P/Ns .................................................................. HP Turbine, First Stage, w/separable Shaft: Rotor Assembly—All P/Ns .......................................................................................................... Disk—All P/Ns ............................................................................................................................ Disk, 2nd Stage Turbine—All P/Ns ................................................................................................... Disk, 3rd Stage Turbine—All P/Ns .................................................................................................... Disk (Separable), 4th Stage Turbine—All P/Ns ................................................................................. Disk (Integral Disk/Hub), 4th Stage Turbine—All P/Ns ..................................................................... Fmt 4700 Sfmt 4700 73363 Inspection Number 72–33–31 72–33–31 –02, –03, –04, –05 –02, –03, –04, –05 72–33–33 72–33–33 72–36–47 72–52–04 –02, –03 –02, –03 –02 –03 72–52–02 72–52–02 72–53–16 72–53–17 72–53–15 72–53–18 –04 –03 –02 –02 –02 –02’’ E:\FR\FM\12DER1.SGM 12DER1 73364 Federal Register / Vol. 70, No. 237 / Monday, December 12, 2005 / Rules and Regulations Alternative Methods of Compliance DEPARTMENT OF TRANSPORTATION (g) You must perform these mandatory inspections using the TLS and the applicable Engine Manual unless you receive approval to use an alternative method of compliance under paragraph (h) of this AD. Section 43.16 of the Federal Aviation Regulations (14 CFR 43.16) may not be used to approve alternative methods of compliance or adjustments to the times in which these inspections must be performed. (h) 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. Maintaining Records of the Mandatory Inspections (i) You have met the requirements of this AD by using a TLS of the manufacturer’s engine manual changed as specified in paragraph (f) of this AD, and, for air carriers operating under part 121 of the Federal Aviation Regulations (14 CFR part 121), by modifying your continuous airworthiness maintenance plan to reflect those changes. You must maintain records of the mandatory inspections that result from those changes to the TLS according to the regulations governing your operation. You do not need to record each piece-part inspection as compliance to this AD. For air carriers operating under part 121, you may use either the system established to comply with section 121.369 or use an alternative system that your principal maintenance inspector has accepted if that alternative system: (1) Includes a method for preserving and retrieving the records of the inspections resulting from this AD; and (2) Meets the requirements of section 121.369(c); and (3) Maintains the records either indefinitely or until the work is repeated. (j) These recordkeeping requirements apply only to the records used to document the mandatory inspections required as a result of revising the TLS as specified in paragraph (f) of this AD, and do not alter or amend the recordkeeping requirements for any other AD or regulatory requirement. Related Information (k) None. Issued in Burlington, Massachusetts, on December 1, 2005. Peter A. White, Acting Manager, Engine and Propeller Directorate, Aircraft Certification Service. [FR Doc. 05–23897 Filed 12–9–05; 8:45 am] BILLING CODE 4910–13–P VerDate Aug<31>2005 15:45 Dec 09, 2005 Jkt 208001 Federal Aviation Administration 14 CFR Part 39 [Docket No. 2001–NE–50–AD; Amendment 39–14403; AD 2005–25–10] RIN 2120–AA64 Airworthiness Directives; Dowty Propellers Type R321/4–82–F/8, R324/ 4–82–F/9, R333/4–82–F/12, and R334/4– 82–F/13 Propeller Assemblies Federal Aviation Administration (FAA), DOT. ACTION: Final rule; request for comments. AGENCY: SUMMARY: The FAA is superseding an existing airworthiness directive (AD) for Dowty Propellers Type R321/4–82–F/8, R324/4–82–F/9, R333/4–82–F/12, and R334/4–82–F/13 propeller assemblies. That AD currently requires initial and repetitive ultrasonic inspections of propeller hubs, part number (P/N) 660709201. This AD requires the same initial and repetitive ultrasonic inspections, but makes some needed corrections. This AD results from comments received on AD 2005–20–12. We are issuing this AD to prevent propeller hub failure due to cracks in the hub, which could result in loss of control of the airplane. DATES: Effective December 27, 2005. The Director of the Federal Register previously approved the incorporation by reference of certain publications listed in the regulations as of July 27, 2004 (69 FR 34560, June 22, 2004) and October 28, 2005 (70 FR 59647, October 13, 2005). We must receive any comments on this AD by February 10, 2006. ADDRESSES: Use one of the following addresses to submit comments on this AD: • By mail: Federal Aviation Administration (FAA), New England Region, Office of the Regional Counsel, Attention: Rules Docket No. 2001–NE– 50–AD, 12 New England Executive Park, Burlington, MA 01803–5299. • By fax: (781) 238–7055. • By e-mail: 9-aneadcomment@faa.gov. Contact Dowty Propellers, Anson Business Park, Cheltenham Road East, Gloucester GL 29QN, UK; telephone 44 (0) 1452 716000; fax 44 (0) 1452 716001, for the service information referenced in this AD. You may examine the AD docket, by appointment, at the FAA, New England Region, Office of the Regional Counsel, 12 New England Executive Park, Burlington, MA. PO 00000 Frm 00018 Fmt 4700 Sfmt 4700 FOR FURTHER INFORMATION CONTACT: Terry Fahr, Aerospace Engineer, Boston Aircraft Certification Office, FAA, Engine and Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803–5299; telephone (781) 238–7155; fax (781) 238–7170. SUPPLEMENTARY INFORMATION: On September 26, 2005, we issued AD 2005–20–12, Amendment 39–14306 (70 FR 59647, October 13, 2005). That AD requires initial and repetitive ultrasonic inspections of propeller hubs, P/N 660709201. That AD was the result of a report of a hub separation on a CASA 212 airplane. That condition, if not corrected, could result in propeller hub failure due to cracks in the hub, which could result in loss of control of the airplane. Comments We provided the public the opportunity to comment on AD 2005– 20–12. We have considered the comments received. Allow Use of Appendix D One commenter, the manufacturer, requests we allow operators and inspectors to also use Appendix D of the referenced service bulletins. We agree and added the use of Appendix D to this AD. Request To Include Flight Cycle Limit The same commenter requests we include a flight cycle limit in the repetitive inspection compliance for R334/4–82–F/13 propeller assemblies, to be consistent with the service bulletin. We agree and changed the repetitive ultrasonic inspection compliance to ‘‘within 300 flight hours time-since-last-inspection or 300 flight cycles-since-last inspection, whichever occurs sooner’’. Request To Correct the Manufacturer’s Name The same commenter requests we correct their former name of Dowty Aerospace Propellers, to their current name of Dowty Propellers. We agree and made the name change. Request To Clarify Initial Inspection Compliance The same commenter requests we revise paragraph (h) of AD 2005–20–12 to clarify that operators that previously complied with the initial inspection in paragraph (f) do not have to comply a second time to that initial inspection. We agree. For clarification, we revised the paragraph, moved it closer to the Compliance heading, and codified it as paragraph (f). E:\FR\FM\12DER1.SGM 12DER1

Agencies

[Federal Register Volume 70, Number 237 (Monday, December 12, 2005)]
[Rules and Regulations]
[Pages 73361-73364]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 05-23897]

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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 98-ANE-48-AD; Amendment 39-14398; AD 2005-25-05]
RIN 2120-AA64

Airworthiness Directives; Pratt & Whitney JT8D Series 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

[[Page 73362]]

Pratt & Whitney (PW) JT8D-1, -1A, -1B, -7, -7A, -7B, -9, -9A, -11, -15,
-15A, -17, -17A, -17R, and -17AR series turbofan engines. That AD
currently requires revisions to the engine manufacturer's time limits
section (TLS) to include enhanced inspection of selected critical life-
limited parts at each piece-part opportunity. This AD modifies the
airworthiness limitations section of the manufacturer's manual and an
air carrier's approved continuous airworthiness maintenance program to
add an eddy current inspection. An FAA study of in-service events
involving uncontained failures of critical rotating engine parts has
indicated the need for mandatory inspections. The mandatory inspections
are needed to identify those critical rotating parts with conditions,
which if allowed to continue in service, could result in uncontained
failures. We are issuing this AD to prevent critical life-limited
rotating engine part failure, which could result in an uncontained
engine failure and damage to the airplane.

DATES: This AD becomes effective June 12, 2006.

ADDRESSES: You may examine the AD docket at the FAA, New England
Region, Office of the Regional Counsel, 12 New England Executive Park,
Burlington, MA.

FOR FURTHER INFORMATION CONTACT: Keith Lardie, Aerospace Engineer,
Engine Certification Office, FAA, Engine and Propeller Directorate, 12
New England Executive Park, Burlington, MA 01803-5299; telephone (781)
238-7189, fax (781) 238-7199.

SUPPLEMENTARY INFORMATION: The FAA proposed to amend 14 CFR Part 39
with a proposed airworthiness directive (AD). The proposed AD applies
to PW JT8D-1, -1A, -1B, -7, -7A, -7B, -9, -9A, -11, -15, -15A, -17, -
17A, -17R, and -17AR series turbofan engines. We published the proposed
AD in the Federal Register on August 18, 2004 (69 FR 51203). That
action proposed to require modifying the time limitations section of
the manufacturer's manual and an air carrier's approved continuous
airworthiness maintenance program to incorporate additional inspection
requirements.

Examining the AD Docket

You may examine the AD Docket (including any comments and service
information), by appointment, between 8 a.m. and 4:30 p.m., Monday
through Friday, except Federal holidays. See ADDRESSES for the
location.

Comments

We provided the public the opportunity to participate in the
development of this AD. We have considered the comments received.

Request To Change the Effective Date

One commenter asks us to change the effective date to six to eight
months. The commenter states the change will allow additional time to
order, fabricate, and install automated inspection equipment. It will
also allow more time to train employees on using the new equipment. We
agree. We have extended the effective date 180 days to allow operators
to set up their inspection process.

Concern the Costs To Comply Are Too Low

One commenter suggests the NPRM fails to recognize the substantial
up-front investment to get the equipment needed for the eddy current
inspection (ECI). In addition, the commenter states we should increase
the Costs of Compliance because the complex inspections will require
several full-time, specially trained operators. We don't agree. The AD
doesn't require air carriers to invest in tooling and equipment or hire
more personnel to comply with the proposed AD. The AD requires adding
the new ECI to the TLS of the engine manufacturer's manual, and to the
air carriers' approved maintenance manuals. Operators can choose to buy
equipment to perform the inspection, or they may send the disk to an
approved service provider. We have not changed the AD.

Request To Change the ECI for Repaired Parts to Fluorescent Penetrant
Inspection (FPI)

The same commenter asks us to change the inspection method for
parts previously repaired with bushings from an automated eddy current
method to a fluorescent penetrant method. The commenter states that one
cannot perform an automated ECI with the bushings installed. The
commenter states that removing the bushings to perform the automated
ECI would leave score marks because of the tight fit. We don't agree.
The operators don't need to remove the bushings. The instructions for
Section 72-33-31, Inspection -05, and Section 72-33-33, Inspection -03,
state that holes with bushings installed are not subject to the ECI.
Holes with bushings installed are subject to FPI and an additional
visual inspection within the ECI instructions. We have not changed the
AD.

Request To Perform an FPI If the Part Fails the ECI

The same commenter suggests that service-run parts that fail the
automated ECI should be subjected to an FPI. If the part fails the FPI,
then the part is scrap. If the part passes the FPI, then it would be
acceptable to perform the bushing repair. The commenter states that
there is a possibility of false readings due to worn or oblong, but not
cracked, holes that cause ``liftoff'' of the probe. We don't agree. The
inspection instructions provide an opportunity to clean and reinspect
the part. If the part fails again, the operator may return the disk to
the manufacturer for a third opinion before determining if the part is
acceptable or if it is scrap. The operator may propose other
alternatives through the Alternative Method of Compliance process. We
have not changed the AD.

Request for Clear Direction for Preparing the Surface of a Hole

The same commenter asks us to provide clear direction for preparing
the surface of a hole that is worn, oblong, or scored from removing a
bushing. The commenter states the automated ECI equipment is extremely
sensitive to surface finish. It might be necessary to machine the
surface to provide an acceptable surface finish for the inspection. The
commenter further states this is not desirable since the machining
operation might mask or remove crack indications. We do not agree that
we need to provide clearer instructions. The manufacturer has provided
instructions to prepare the part for ECI. This AD does not allow any
machining operations, although it does allow certain cleaning
operations. Bushings are not subject to the ECI and must not be
removed. We have not changed the AD.

Conclusion

We have carefully reviewed the available data, including the
comments received, and determined that air safety and the public
interest require adopting the AD with the changes described previously.
We have determined that these changes will neither increase the
economic burden on any operator nor increase the scope of the AD.

Costs of Compliance

There are about 6,085 Pratt & Whitney JT8D-1, -1A, -1B, -7, -7A, -
7B, -9, -9A, -11, -15, -15A, -17, -17A, -17R, and -17AR series turbofan
engines of the affected design in the worldwide fleet. We estimate that
this AD will affect 3,236 engines installed on airplanes of U.S.
registry. We also estimate that it will take about 8 work

[[Page 73363]]

hours per engine to perform the proposed inspections, and that the
average labor rate is $65 per work hour. Since this is an added
inspection requirement, included as part of the normal maintenance
cycle, no additional part costs are involved. Based on these figures,
we estimate the total cost of the AD to U.S. operators to be
$1,682,720.

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 by
sending a request to us at the address listed under ADDRESSES. Include
``AD Docket No. 98-ANE-48-AD'' in your request.

List of Subjects in 14 CFR Part 39

Air transportation, Aircraft, Aviation safety, 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 39-12867, (67 FR
55108 August 28, 2002), and by adding a new airworthiness directive,
Amendment 39-14398, to read as follows:

2005-25-05 Pratt & Whitney: Amendment 39-14398. Docket No. 98-ANE-
48-AD.

Effective Date

(a) This AD becomes effective June 12, 2006.

Affected ADs

(b) This AD supersedes AD 2002-17-02.

Applicability

(c) This AD applies to Pratt & Whitney (PW) JT8D-1, -1A, -1B, -
7, -7A, -7B, -9, -9A, -11, -15, -15A, -17, -17A, -17R, and -17AR
series turbofan engines. These engines are installed on, but not
limited to Boeing 727 and 737 series, and McDonnell Douglas DC-9
series airplanes.

Unsafe Condition

(d) This AD results from the need to require enhanced inspection
of selected critical life-limited parts of PW JT8D series turbofan
engines. We are issuing this AD to prevent critical life-limited
rotating engine part failure, which could result in an uncontained
engine failure and 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.
(f) Within the next 30 days after the effective date of this AD,
(1) revise the Time Limits Section (TLS) of the manufacturer's
Engine Manual, Part Number 481672, as appropriate for PW JT8D-1, -
1A, -1B, -7, -7A, -7B, -9, -9A, -11, -15, -15A, -17, -17A, -17R, and
-17AR series turbofan engines, and
(2) for air carriers, revise the approved mandatory inspections
section of the continuous airworthiness maintenance program, by
adding the following:
``Critical Life Limited Part Inspection
A. Inspection Requirements:
(1) This section has the definitions for individual engine piece
parts and the inspection procedures which are necessary when these
parts are removed from the engine.
(2) It is necessary to do the inspection procedures of the piece
parts in paragraph B when:
(a) The part is removed from the engine and disassembled to the
level specified in paragraph B and
(b) The part has accumulated more than 100 cycles since the last
piece part inspection, provided that the part was not damaged or
related to the cause for its removal from the engine.
(3) The inspections specified in this paragraph do not replace
or make not necessary other recommended inspections for these parts
or other parts.
B. Parts Requiring Inspection:

Note: Piece part is defined as any of the listed parts with all
the blades removed.

----------------------------------------------------------------------------------------------------------------
Description Section Inspection Number
----------------------------------------------------------------------------------------------------------------
Hub (Disk), 1st Stage Compressor:
Hub Detail--All P/Ns.............. 72-33-31 -02, -03, -04, -05
Hub Assembly--All P/Ns............ 72-33-31 -02, -03, -04, -05
2nd Stage Compressor:
Disk--All P/Ns.................... 72-33-33 -02, -03
Disk Assembly--All P/Ns........... 72-33-33 -02, -03
Disk, 13th Stage Compressor--All P/Ns. 72-36-47 -02
HP Turbine Disk, First Stage w/ 72-52-04 -03
integral Shaft--All P/Ns.
HP Turbine, First Stage, w/separable
Shaft:
Rotor Assembly--All P/Ns.......... 72-52-02 -04
Disk--All P/Ns.................... 72-52-02 -03
Disk, 2nd Stage Turbine--All P/Ns..... 72-53-16 -02
Disk, 3rd Stage Turbine--All P/Ns..... 72-53-17 -02
Disk (Separable), 4th Stage Turbine-- 72-53-15 -02
All P/Ns.
Disk (Integral Disk/Hub), 4th Stage 72-53-18 -02''
Turbine--All P/Ns.
----------------------------------------------------------------------------------------------------------------

[[Page 73364]]

Alternative Methods of Compliance

(g) You must perform these mandatory inspections using the TLS
and the applicable Engine Manual unless you receive approval to use
an alternative method of compliance under paragraph (h) of this AD.
Section 43.16 of the Federal Aviation Regulations (14 CFR 43.16) may
not be used to approve alternative methods of compliance or
adjustments to the times in which these inspections must be
performed.
(h) 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.

Maintaining Records of the Mandatory Inspections

(i) You have met the requirements of this AD by using a TLS of
the manufacturer's engine manual changed as specified in paragraph
(f) of this AD, and, for air carriers operating under part 121 of
the Federal Aviation Regulations (14 CFR part 121), by modifying
your continuous airworthiness maintenance plan to reflect those
changes. You must maintain records of the mandatory inspections that
result from those changes to the TLS according to the regulations
governing your operation. You do not need to record each piece-part
inspection as compliance to this AD. For air carriers operating
under part 121, you may use either the system established to comply
with section 121.369 or use an alternative system that your
principal maintenance inspector has accepted if that alternative
system:
(1) Includes a method for preserving and retrieving the records
of the inspections resulting from this AD; and
(2) Meets the requirements of section 121.369(c); and
(3) Maintains the records either indefinitely or until the work
is repeated.
(j) These recordkeeping requirements apply only to the records
used to document the mandatory inspections required as a result of
revising the TLS as specified in paragraph (f) of this AD, and do
not alter or amend the recordkeeping requirements for any other AD
or regulatory requirement.

Related Information

(k) None.

Issued in Burlington, Massachusetts, on December 1, 2005.
Peter A. White,
Acting Manager, Engine and Propeller Directorate, Aircraft
Certification Service.
[FR Doc. 05-23897 Filed 12-9-05; 8:45 am]
BILLING CODE 4910-13-P

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