Airworthiness Directives; Pratt & Whitney PW4077D, PW4084D, PW4090, and PW4090-3 Turbofan Engines, 49335-49337 [E6-13909]

Download as PDF Federal Register / Vol. 71, No. 163 / Wednesday, August 23, 2006 / Rules and Regulations Note 1: For the purposes of this AD, a detailed inspection is: ‘‘An intensive examination of a specific item, installation, or assembly to detect damage, failure, or irregularity. Available lighting is normally supplemented with a direct source of good lighting at an intensity deemed appropriate. Inspection aids such as mirror, magnifying lenses, etc., may be necessary. Surface cleaning and elaborate procedures may be required.’’ Terminating Action (g) The repetitive inspections required by this AD may be terminated if all ballasts installed on the airplane have P/N BR9000– 21, installed in accordance with the Accomplishment Instructions of Bombardier Service Bulletin 8–33–51, Revision ‘A,’ dated 49335 April 20, 2005 (to replace ballast P/N BA08006–1), or 8–33–52, dated April 15, 2005 (to replace ballast P/N BA08006–28–1). Ballasts installed before the effective date of this AD are also acceptable if done in accordance with Bombardier Service Bulletin 8–33–51, dated August 16, 2002. (2) Before using any AMOC approved in accordance with § 39.19 on any airplane to which the AMOC applies, notify the appropriate principal inspector in the FAA Flight Standards Certificate Holding District Office. Parts Installation (h) As of the effective date of this AD: No person may install a ballast P/N BA08006–1 or BA08006–28–1 on any airplane. Related Information Alternative Methods of Compliance (AMOCs) (i)(1) The Manager, New York ACO, FAA, has the authority to approve AMOCs for this AD, if requested in accordance with the procedures found in 14 CFR 39.19. (j) Canadian airworthiness directive CF– 2004–26R1, dated September 28, 2005, also addresses the subject of this AD. Material Incorporated by Reference (k) You must use the service information identified in Table 2 of this AD to perform the actions that are required by this AD, unless the AD specifies otherwise. TABLE 2.—MATERIAL INCORPORATED BY REFERENCE de Havilland Temporary Revision— To the de Havilland DASH 8 Series— MRB–146, dated August 31, 2004 ........................................................... MRB–147, dated May 3, 2005 ................................................................. MRB 2–24, dated August 31, 2004 .......................................................... MRB 2–25, dated May 3, 2005 ................................................................ MRB 3–155, dated August 31, 2004 ........................................................ MRB 3–156, dated May 3, 2005 .............................................................. sroberts on PROD1PC70 with RULES (Page 2 of de Havilland Temporary Revision MRB–147, dated May 3, 2005, incorrectly refers to Series 300 airplanes; that reference should be to Series 100.) If the terminating action is accomplished, you must use Bombardier Service Bulletin 8–33–51, Revision ‘A,’ dated April 20, 2005; or Bombardier Service Bulletin 8–33–52, dated April 15, 2005, as applicable, to perform the optional terminating action specified in this AD. The Director of the Federal Register approved the incorporation by reference of these documents in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Contact Bombardier, Inc., Bombardier Regional Aircraft Division, 123 Garratt Boulevard, Downsview, Ontario M3K 1Y5, Canada, for a copy of this service information. You may review copies at the Docket Management Facility, U.S. Department of Transportation, 400 Seventh Street, SW., Room PL–401, Nassif Building, Washington, DC; on the Internet at http://dms.dot.gov; or at the National Archives and Records Administration (NARA). For information on the availability of this material at the 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 August 14, 2006. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E6–13829 Filed 8–22–06; 8:45 am] BILLING CODE 4910–13–P VerDate Aug<31>2005 15:49 Aug 22, 2006 Jkt 208001 100 100 200 200 300 300 Maintenance Maintenance Maintenance Maintenance Maintenance Maintenance Program Program Program Program Program Program DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2006–24034; Directorate Identifier 2006–NE–05–AD; Amendment 39– 14729; AD 2006–17–08] RIN 2120–AA64 Airworthiness Directives; Pratt & Whitney PW4077D, PW4084D, PW4090, and PW4090–3 Turbofan Engines Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: SUMMARY: The FAA is adopting a new airworthiness directive (AD) for Pratt & Whitney (PW) PW4077D, PW4084D, PW4090, and PW4090–3 turbofan engines that were reassembled with certain previously used high pressure compressor (HPC) exit brush seal assembly parts and certain new or refurbished HPC exit diffuser air seal inner lands. This AD requires replacing the HPC exit inner and outer brush seal packs with new brush seal packs, or replacing the HPC exit brush seal assembly with a new HPC exit brush seal assembly. This AD results from a report of oil leaking into the high pressure turbine (HPT) interstage cavity and igniting, leading to an engine case penetration and engine in-flight shutdown. Although liberated engine PO 00000 Frm 00027 Fmt 4700 Sfmt 4700 Manual Manual Manual Manual Manual Manual PSM PSM PSM PSM PSM PSM 1–8–7. 1–8–7. 1–82–7. 1–82–7. 1–83–7. 1–83–7. parts did not penetrate the engine nacelle, we are issuing this AD to prevent uncontained engine failure, damage to the airplane, and injury to passengers. This AD becomes effective September 27, 2006. The Director of the Federal Register approved the incorporation by reference of certain publications listed in the regulations as of September 27, 2006. 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. You may examine the AD docket on the Internet at http://dms.dot.gov or in Room PL–401 on the plaza level of the Nassif Building, 400 Seventh Street, SW., Washington, DC. FOR FURTHER INFORMATION CONTACT: Antonio Cancelliere, Aerospace Engineer, Engine Certification Office, FAA, Engine and Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803; telephone (781) 238–7751; 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 Pratt & Whitney (PW) PW4077D, PW4084D, PW4090, and PW4090–3 turbofan engines that were reassembled with certain previously used HPC exit brush seal assembly parts and certain new or refurbished HPC exit diffuser air seal DATES: E:\FR\FM\23AUR1.SGM 23AUR1 49336 Federal Register / Vol. 71, No. 163 / Wednesday, August 23, 2006 / Rules and Regulations inner lands. We published the proposed AD in the Federal Register on April 19, 2006 (71 FR 20042). That action proposed to require replacing the HPC exit inner and outer brush seal packs with new brush seal packs, or replacing the HPC exit brush seal assembly with a new HPC exit brush seal assembly. Examining the AD Docket You may examine the docket that contains the AD, any comments received, and any final disposition in person at the Docket Management Facility Docket Office between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The Docket Office (telephone (800) 647–5227) is located on the plaza level of the Department of Transportation Nassif Building at the street address stated in ADDRESSES. Comments will be available in the AD docket shortly after the DMS receives them. Comments We provided the public the opportunity to participate in the development of this AD. We have considered the comments received. sroberts on PROD1PC70 with RULES Request to More Accurately Describe the Unsafe Condition The Boeing Company requests that we more accurately describe the unsafe condition. They propose that we state the unsafe condition as ‘‘This AD results from a report of oil leaking into the high pressure turbine (HPT) interstage cavity and igniting, leading to an engine case penetration and engine in-flight shutdown. Although liberated engine parts did not penetrate the engine nacelle, we are proposing this AD to prevent uncontained engine failure, damage to the airplane, and injury to passengers.’’ We agree and adopted the suggested language. Request for Clarification Japan Airlines requests clarification of the compliance on whether ‘‘cyclessince-last-overhaul (CSLO)’’ applies to the engine’s last shop visit or if it applies to overhaul of the HPC diffuser assembly only. We agree we need to clarify the compliance. The CSLO applies to overhaul of the HPC diffuser assembly only. As a result of the comment, we reworded compliance paragraphs (g)(1) and (g)(2) to read as follows: ‘‘(1) By 3,000 cycles-in-service (CIS) since a used HPC exit inner brush seal pack and a new or refurbished HPC exit diffuser air seal land were installed in the engine, or by March 31, 2007, whichever occurs later; however VerDate Aug<31>2005 17:06 Aug 22, 2006 Jkt 208001 (2) If on March 31, 2007, the used HPC exit inner brush seal pack coupled with a new or refurbished HPC exit diffuser air seal inner land assembly has not accumulated 3,000 CIS, then by 3,000 CIS, or December 31, 2008, whichever occurs first.’’ 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 We estimate that this AD will affect 76 PW PW4077D, PW4084D, PW4090, and PW4090–3 turbofan engines installed on airplanes of U.S. registry. We also estimate that it will take about 9 work-hours per engine to perform the parts replacement, and that the average labor rate is $80 per work-hour. Required parts will cost about $100,017 per engine. Based on these figures, we estimate the total cost of the AD to U.S. operators to be $7,656,012. 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. PO 00000 Frm 00028 Fmt 4700 Sfmt 4700 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: 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 adding the following new airworthiness directive: I 2006–17–08 Pratt & Whitney: Amendment 39–14729. Docket No. FAA–2006–24034; Directorate Identifier 2006–NE–05–AD. Effective Date (a) This airworthiness directive (AD) becomes effective September 27, 2006. Affected ADs (b) None. Applicability (c) This AD applies to Pratt & Whitney (PW) PW4077D, PW4084D, PW4090, and PW4090–3 turbofan engines that were: (1) Reassembled with a previously used high pressure compressor (HPC) exit inner brush seal pack, part number (P/N) 50J894– 01; and (2) Reassembled with a new or refurbished HPC exit diffuser air seal inner land, P/N 55H869. (d) These engines are installed on, but not limited to, Boeing 777 airplanes. Unsafe Condition (e) This AD results from a report of oil leaking into the high pressure turbine (HPT) interstage cavity and igniting, leading to an engine case penetration and engine in-flight shutdown. Although liberated engine parts did not penetrate the engine nacelle, we are E:\FR\FM\23AUR1.SGM 23AUR1 Federal Register / Vol. 71, No. 163 / Wednesday, August 23, 2006 / Rules and Regulations issuing this AD to prevent uncontained engine failure, damage to the airplane, and injury to passengers. DEPARTMENT OF TRANSPORTATION Federal Aviation Administration Compliance (f) You are responsible for having the actions required by this AD performed at the following compliance times, unless the actions have already been done. (g) Replace the HPC exit inner and outer brush seal packs with new HPC exit inner and outer brush seal packs, or replace the HPC exit brush seal assembly with a new HPC exit brush seal assembly as follows: (1) By 3,000 cycles-in-service (CIS) since a used HPC exit inner brush seal pack and a new or refurbished HPC exit diffuser air seal land were installed in the engine, or by March 31, 2007, whichever occurs later; however, (2) If on March 31, 2007, the used HPC exit inner brush seal pack coupled with a new or refurbished HPC exit diffuser air seal inner land assembly has not accumulated 3,000 CIS, then by 3,000 CIS, or December 31, 2008, whichever occurs first. (h) Use the Accomplishment Instructions of PW Service Bulletin No. PW4G–112-A72– 280, Revision 1, dated March 21, 2006, to do the inner and outer brush pack replacements. Alternative Methods of Compliance (i) The Manager, Engine Certification Office, has the authority to approve alternative methods of compliance for this AD if requested using the procedures found in 14 CFR 39.19. Related Information (j) None. Material Incorporated by Reference sroberts on PROD1PC70 with RULES (k) You must use Pratt & Whitney Service Bulletin No. PW4G–112–A72–280, Revision 1, dated March 21, 2006, to perform the replacements required by 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 for a copy of this service information. You may review copies at the FAA, New England Region, Office of the Regional Counsel, 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 August 14, 2006. Thomas A. Boudreau, Acting Manager, Engine and Propeller Directorate, Aircraft Certification Service. [FR Doc. E6–13909 Filed 8–22–06; 8:45 am] BILLING CODE 4910–13–P VerDate Aug<31>2005 15:49 Aug 22, 2006 Jkt 208001 14 CFR Part 39 [Docket No. FAA–2006–25657; Directorate Identifier 2006–NM–187–AD; Amendment 39–14735; AD 2006–17–14] RIN 2120–AA64 Airworthiness Directives; Bombardier Model CL–600–2B19 (Regional Jet Series 100 & 440) Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule; request for comments. AGENCY: SUMMARY: The FAA is superseding an existing airworthiness directive (AD) that applies to certain Bombardier Model CL–600–2B19 (Regional Jet Series 100 & 440) airplanes. The existing AD currently requires inspecting contactors 1K4XD, 2K4XD, and K4XA to determine the type of terminal base plate, and applying sealant on the terminal base plates, if necessary. This new AD revises the effective date of the existing AD. This AD results from incidents of short circuit failures of certain alternating current (AC) contactors located in the avionics bay. We are issuing this AD to prevent short circuit failures of certain AC contactors, which could result in arcing and consequent smoke or fire. DATES: This AD becomes effective September 7, 2006. On August 9, 2006 (71 FR 45364, August 9, 2006), the Director of the Federal Register approved the incorporation by reference of Bombardier Service Bulletin 601R–24– 122, Revision A, dated July 13, 2006. We must receive any comments on this AD by October 23, 2006. ADDRESSES: Use one of the following addresses to submit comments on this AD. • DOT Docket Web site: Go to http://dms.dot.gov and follow the instructions for sending your comments electronically. • Government-wide rulemaking Web site: Go to http://www.regulations.gov and follow the instructions for sending your comments electronically. • Mail: Docket Management Facility, U.S. Department of Transportation, 400 Seventh Street, SW., Nassif Building, Room PL–401, Washington, DC 20590. • Fax: (202) 493–2251. • Hand Delivery: Room PL–401 on the plaza level of the Nassif Building, 400 Seventh Street, SW., Washington, PO 00000 Frm 00029 Fmt 4700 Sfmt 4700 49337 DC, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. Contact Bombardier, Inc., Canadair, Aerospace Group, P.O. Box 6087, Station Centre-ville, Montreal, Quebec H3C 3G9, Canada, for service information identified in this AD. You may examine the contents of the AD docket on the Internet at http:// dms.dot.gov, or in person at the Docket Management Facility, U.S. Department of Transportation, 400 Seventh Street, SW., Room PL–401, on the plaza level of the Nassif Building, Washington, DC. This docket number is FAA–2006– 25657; the directorate identifier for this docket is 2006–NM–187–AD. FOR FURTHER INFORMATION CONTACT: Wing Chan, Aerospace Engineer, Systems and Flight Test Branch, ANE– 172, FAA, New York Aircraft Certification Office, 1600 Stewart Avenue, suite 410, Westbury, New York 11590; telephone (516) 228–7311; fax (516) 794–5531. SUPPLEMENTARY INFORMATION: Discussion On July 31, 2006, the FAA issued AD 2006–16–07, amendment 39–14707 (71 FR 45364, August 9, 2006). That AD applies to certain Bombardier Model CL–600–2B19 (Regional Jet Series 100 & 440) airplanes. That AD requires inspecting contactors 1K4XD, 2K4XD, and K4XA to determine the type of terminal base plate, and applying sealant on the terminal base plates, if necessary. That AD resulted from incidents of short circuit failures of certain alternating current (AC) contactors located in the avionics bay. The actions specified in that AD are intended to prevent short circuit failures of certain AC contactors, which could result in arcing and consequent smoke or fire. Actions Since AD Was Issued Since we issued that AD, we have determined that the effective date of that AD was inadvertently specified as the same date as the publication date. The effective date of the AD should be 15 days after the date of publication in the Federal Register FAA’s Determination and Requirements of This AD This airplane model is manufactured in Canada and is type certificated for operation in the United States under the provisions of section 21.29 of the Federal Aviation Regulations (14 CFR 21.29) and the applicable bilateral airworthiness agreement. Pursuant to this bilateral airworthiness agreement, Transport Canada Civil Aviation (TCCA), which is the airworthiness E:\FR\FM\23AUR1.SGM 23AUR1

Agencies

[Federal Register Volume 71, Number 163 (Wednesday, August 23, 2006)]
[Rules and Regulations]
[Pages 49335-49337]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E6-13909]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2006-24034; Directorate Identifier 2006-NE-05-AD; 
Amendment 39-14729; AD 2006-17-08]
RIN 2120-AA64


Airworthiness Directives; Pratt & Whitney PW4077D, PW4084D, 
PW4090, and PW4090-3 Turbofan Engines

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

ACTION: Final rule.

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

SUMMARY: The FAA is adopting a new airworthiness directive (AD) for 
Pratt & Whitney (PW) PW4077D, PW4084D, PW4090, and PW4090-3 turbofan 
engines that were reassembled with certain previously used high 
pressure compressor (HPC) exit brush seal assembly parts and certain 
new or refurbished HPC exit diffuser air seal inner lands. This AD 
requires replacing the HPC exit inner and outer brush seal packs with 
new brush seal packs, or replacing the HPC exit brush seal assembly 
with a new HPC exit brush seal assembly. This AD results from a report 
of oil leaking into the high pressure turbine (HPT) interstage cavity 
and igniting, leading to an engine case penetration and engine in-
flight shutdown. Although liberated engine parts did not penetrate the 
engine nacelle, we are issuing this AD to prevent uncontained engine 
failure, damage to the airplane, and injury to passengers.

DATES: This AD becomes effective September 27, 2006. The Director of 
the Federal Register approved the incorporation by reference of certain 
publications listed in the regulations as of September 27, 2006.

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.
    You may examine the AD docket on the Internet at http://dms.dot.gov 
or in Room PL-401 on the plaza level of the Nassif Building, 400 
Seventh Street, SW., Washington, DC.

FOR FURTHER INFORMATION CONTACT: Antonio Cancelliere, Aerospace 
Engineer, Engine Certification Office, FAA, Engine and Propeller 
Directorate, 12 New England Executive Park, Burlington, MA 01803; 
telephone (781) 238-7751; 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 Pratt & Whitney (PW) PW4077D, PW4084D, PW4090, and PW4090-3 turbofan 
engines that were reassembled with certain previously used HPC exit 
brush seal assembly parts and certain new or refurbished HPC exit 
diffuser air seal

[[Page 49336]]

inner lands. We published the proposed AD in the Federal Register on 
April 19, 2006 (71 FR 20042). That action proposed to require replacing 
the HPC exit inner and outer brush seal packs with new brush seal 
packs, or replacing the HPC exit brush seal assembly with a new HPC 
exit brush seal assembly.

Examining the AD Docket

    You may examine the docket that contains the AD, any comments 
received, and any final disposition in person at the Docket Management 
Facility Docket Office between 9 a.m. and 5 p.m., Monday through 
Friday, except Federal holidays. The Docket Office (telephone (800) 
647-5227) is located on the plaza level of the Department of 
Transportation Nassif Building at the street address stated in 
ADDRESSES. Comments will be available in the AD docket shortly after 
the DMS receives them.

Comments

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

Request to More Accurately Describe the Unsafe Condition

    The Boeing Company requests that we more accurately describe the 
unsafe condition. They propose that we state the unsafe condition as 
``This AD results from a report of oil leaking into the high pressure 
turbine (HPT) interstage cavity and igniting, leading to an engine case 
penetration and engine in-flight shutdown. Although liberated engine 
parts did not penetrate the engine nacelle, we are proposing this AD to 
prevent uncontained engine failure, damage to the airplane, and injury 
to passengers.''
    We agree and adopted the suggested language.

Request for Clarification

    Japan Airlines requests clarification of the compliance on whether 
``cycles-since-last-overhaul (CSLO)'' applies to the engine's last shop 
visit or if it applies to overhaul of the HPC diffuser assembly only.
    We agree we need to clarify the compliance. The CSLO applies to 
overhaul of the HPC diffuser assembly only. As a result of the comment, 
we reworded compliance paragraphs (g)(1) and (g)(2) to read as follows:
    ``(1) By 3,000 cycles-in-service (CIS) since a used HPC exit inner 
brush seal pack and a new or refurbished HPC exit diffuser air seal 
land were installed in the engine, or by March 31, 2007, whichever 
occurs later; however
    (2) If on March 31, 2007, the used HPC exit inner brush seal pack 
coupled with a new or refurbished HPC exit diffuser air seal inner land 
assembly has not accumulated 3,000 CIS, then by 3,000 CIS, or December 
31, 2008, whichever occurs first.''

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

    We estimate that this AD will affect 76 PW PW4077D, PW4084D, 
PW4090, and PW4090-3 turbofan engines installed on airplanes of U.S. 
registry. We also estimate that it will take about 9 work-hours per 
engine to perform the parts replacement, and that the average labor 
rate is $80 per work-hour. Required parts will cost about $100,017 per 
engine. Based on these figures, we estimate the total cost of the AD to 
U.S. operators to be $7,656,012.

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 adding the following new airworthiness 
directive:

2006-17-08 Pratt & Whitney: Amendment 39-14729. Docket No. FAA-2006-
24034; Directorate Identifier 2006-NE-05-AD.

Effective Date

    (a) This airworthiness directive (AD) becomes effective 
September 27, 2006.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to Pratt & Whitney (PW) PW4077D, PW4084D, 
PW4090, and PW4090-3 turbofan engines that were:
    (1) Reassembled with a previously used high pressure compressor 
(HPC) exit inner brush seal pack, part number (P/N) 50J894-01; and
    (2) Reassembled with a new or refurbished HPC exit diffuser air 
seal inner land, P/N 55H869.
    (d) These engines are installed on, but not limited to, Boeing 
777 airplanes.

Unsafe Condition

    (e) This AD results from a report of oil leaking into the high 
pressure turbine (HPT) interstage cavity and igniting, leading to an 
engine case penetration and engine in-flight shutdown. Although 
liberated engine parts did not penetrate the engine nacelle, we are

[[Page 49337]]

issuing this AD to prevent uncontained engine failure, damage to the 
airplane, and injury to passengers.

Compliance

    (f) You are responsible for having the actions required by this 
AD performed at the following compliance times, unless the actions 
have already been done.
    (g) Replace the HPC exit inner and outer brush seal packs with 
new HPC exit inner and outer brush seal packs, or replace the HPC 
exit brush seal assembly with a new HPC exit brush seal assembly as 
follows:
    (1) By 3,000 cycles-in-service (CIS) since a used HPC exit inner 
brush seal pack and a new or refurbished HPC exit diffuser air seal 
land were installed in the engine, or by March 31, 2007, whichever 
occurs later; however,
    (2) If on March 31, 2007, the used HPC exit inner brush seal 
pack coupled with a new or refurbished HPC exit diffuser air seal 
inner land assembly has not accumulated 3,000 CIS, then by 3,000 
CIS, or December 31, 2008, whichever occurs first.
    (h) Use the Accomplishment Instructions of PW Service Bulletin 
No. PW4G-112-A72-280, Revision 1, dated March 21, 2006, to do the 
inner and outer brush pack replacements.

Alternative Methods of Compliance

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

Related Information

    (j) None.

Material Incorporated by Reference

    (k) You must use Pratt & Whitney Service Bulletin No. PW4G-112-
A72-280, Revision 1, dated March 21, 2006, to perform the 
replacements required by 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 for a copy of this service information. You may 
review copies at the FAA, New England Region, Office of the Regional 
Counsel, 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 August 14, 2006.
Thomas A. Boudreau,
Acting Manager, Engine and Propeller Directorate, Aircraft 
Certification Service.
 [FR Doc. E6-13909 Filed 8-22-06; 8:45 am]
BILLING CODE 4910-13-P