Airworthiness Directives; Honeywell International Inc. (Formerly AlliedSignal Inc. and Garrett Turbine Engine Co.) TFE731-2 and -3 Series Turbofan Engines, 35992-35993 [05-12080]

Download as PDF 35992 Federal Register / Vol. 70, No. 119 / Wednesday, June 22, 2005 / Rules and Regulations DEPARTMENT OF TRANSPORTATION Federal Aviation Administration [Docket No. FAA–2004–18496; Directorate Identifier 2004–NE–04–AD; Amendment 39– 14143; AD 2005–13–07] RIN 2120–AA64 Airworthiness Directives; Honeywell International Inc. (Formerly AlliedSignal Inc. and Garrett Turbine Engine Co.) TFE731–2 and –3 Series Turbofan Engines Federal Aviation Administration (FAA), DOT. ACTION: Final rule. AGENCY: SUMMARY: The FAA is adopting a new airworthiness directive (AD) for Honeywell International Inc. (formerly AlliedSignal Inc. and Garrett Turbine Engine Co.) TFE731–2 and –3 series turbofan engines with certain part numbers (P/Ns) and serial numbers (SNs) of low pressure (LP) 1st and 2nd stage turbine rotor discs initially installed. This AD requires replacement of those LP 1st and 2nd stage turbine rotor discs. This AD results from a report of an uncontained failure of an LP 2nd stage turbine rotor disc that resulted in an in-flight engine shutdown. We are issuing this AD to prevent LP turbine rotor disk separation, which could result in an uncontained engine failure and damage to the airplane. This AD becomes effective July 27, 2005. The Director of the Federal Register approved the incorporation by reference of certain publications listed in the regulations as of July 27, 2005. ADDRESSES: You can get the service information identified in this AD from Honeywell Engines and Systems (formerly AlliedSignal Inc. and Garrett Turbine Engine Co.) Technical Publications and Distribution, M/S 2101–201, P.O. Box 52170, Phoenix, AZ 85072–2170; telephone: (602) 365–2493 (General Aviation), (602) 365–5535 (Commercial Aviation), fax: (602) 365– 5577 (General Aviation), (602) 365–2832 (Commercial Aviation). You may examine the AD docket on the Internet at https://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: Joseph Costa, Aerospace Engineer, Los Angeles Aircraft Certification Office, FAA, Transport Airplane Directorate, 3960 Paramount Blvd., Lakewood CA VerDate jul<14>2003 15:52 Jun 21, 2005 Jkt 205001 The FAA proposed to amend 14 CFR part 39 with a proposed AD. The proposed AD applies to Honeywell International Inc. (formerly AlliedSignal Inc. and Garrett Turbine Engine Co.) TFE731–2 and –3 series turbofan engines with certain P/ Ns and SNs of LP 1st and 2nd stage turbine rotor discs initially installed as new parts before April 1, 1991. These discs were heat treated with a process that may have resulted in disk material with a non-uniform microstructure that is susceptible to creep fatigue, which may lead to cracking or separation. We published the proposed AD in the Federal Register on July 1, 2004 (69 FR 39875). That action proposed to require replacement of those LP 1st and 2nd stage turbine rotor discs. SUPPLEMENTARY INFORMATION: 14 CFR Part 39 DATES: 90712–4137; telephone: (562) 627–5246; fax: (562) 627–5210. Examining the AD Docket 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. We have carefully reviewed the available data and determined that air safety and the public interest require adopting the AD as proposed. 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. Costs of Compliance List of Subjects in 14 CFR Part 39 There are about 56 Honeywell International Inc. TFE731–2 and –3 series turbofan engines of the affected design in the worldwide fleet. We estimate that 24 engines installed on airplanes of U.S. registry will be affected by this AD. We also estimate that it will take about 4 work hours per engine to perform these actions, and that the average labor rate is $65 per work hour. Required parts cost about $30,000 per engine. Based on these figures, we estimate the total cost of this AD to U.S. operators to be $726,240. Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. You may examine the docket that contains the AD, any comments received, and any final disposition in person at the DMS Docket Offices 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 received no comments on the proposal or on the determination of the cost to the public. Conclusion PO 00000 Frm 00008 Fmt 4700 Sfmt 4700 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 E:\FR\FM\22JNR1.SGM 22JNR1 Federal Register / Vol. 70, No. 119 / Wednesday, June 22, 2005 / Rules and Regulations 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 2005–13–07 Honeywell International Inc. (formerly AlliedSignal Inc. and Garrett Turbine Engine Co.): Amendment 39– 14143. Docket No. FAA–2004–18496; Directorate Identifier. 2004–NE–04–AD. Effective Date (a) This airworthiness directive (AD) becomes effective July 27, 2005. Affected ADs (b) None. Applicability (c) This AD applies to Honeywell International Inc. (formerly AlliedSignal Inc. and Garrett Turbine Engine Co.) TFE731–2 and –3 series turbofan engines with the following low pressure (LP) 1st and 2nd stage turbine rotor disc part numbers (P/Ns), with serial numbers (SNs) listed in Tables 1, 2, and 3 of Honeywell International Inc. SB No. TFE731–72–3682, dated November 26, 2002, initially installed as new parts before April 1, 1991: PART NUMBERS 3072069-All 3072070-All 3072351-All 3072542-All 3073013-All ............................. ............................. ............................. ............................. ............................. 3073014-All 3073113-All 3071114-All 3074103-All 3074105-All (All denotes all dash numbers installed) These engines are installed on, but not limited to, the following airplanes: Avions Marcel Dassault Mystere-Falcon 10 and 50 series Cessna Model 650, Citation III, and Citation VI Gulfstream Aerospace LP (formerly IAI) 1125 Westwind Astra series Israel Aircraft Industries (IAI) 1124 series Learjet 31, 35, 36, and 55 series Lockheed-Georgia 1329–25 series (731 Jetstar, Jetstar II) Raytheon Corporate Jets (formerly British Aerospace) DH/HS/BH–125 series; Sabreliner NA–265–65 (Sabreliner 65) Unsafe Condition (d) This AD results from a report of an uncontained failure of an LP 2nd stage turbine rotor disc that resulted in an in-flight engine shutdown. We are issuing this AD to prevent LP turbine rotor disk separation, 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. VerDate jul<14>2003 15:52 Jun 21, 2005 Jkt 205001 Removal From Service of LP 1st and 2nd Stage Turbine Rotor Discs (f) For TFE731–2–2J, TFE731–2–2N, TFE731–2A–2A, and TFE731–3–1J engines, replace discs that are listed by SN in Tables 1 and 3 of SB No. TFE731–72–3682, dated November 26, 2002, within 100 hours timein-service (TIS) after the effective date of this AD. (g) For TFE731–2 series engines except TFE731–2–2J, TFE731–2–2N, and TFE731– 2A–2A engines, replace discs that are listed by SN in Tables 1 and 2 of SB No. TFE731– 72–3682, dated November 26, 2002, at the next Major Periodic Inspection (MPI) or next access to the turbine discs after the effective date of this AD, but within 2,200 hours TIS since the last disc inspection, whichever occurs first. (h) For TFE731–3 series engines except TFE731–3–1J, replace discs that are listed by SN in Table 3 of SB No. TFE731–72–3682, dated November 26, 2002, at the next MPI or next access to the turbine discs after the effective date of this AD, but within 1,500 hours TIS since the last disc inspection, whichever occurs first. (i) Information on replacing affected discs can be found in Honeywell International Inc. SB No. TFE731–72–3682, dated November 26, 2002. (j) After the effective date of this AD, do not install any LP 1st and 2nd stage turbine rotor disc that has a SN listed in Table 1, 2, or 3 of SB No. TFE731–72–3682, dated November 26, 2002, and determined to be manufactured before April 1, 1991. Definitions (k) For the purposes of this AD, access to the turbine discs is the level of disassembly that has removed the tie-shaft nut. Alternative Methods of Compliance (l) The Manager, Los Angeles Aircraft 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. Material Incorporated by Reference (m) You must use Honeywell International, Inc. Service Bulletin No. TFE731–72–3682, dated November 26, 2002, 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 Honeywell Engines and Systems Technical Publications and Distribution, M/S 2101–201, P.O. Box 52170, Phoenix, AZ 85072–2170; telephone: (602) 365–2493 (General Aviation), (602) 365–5535 (Commercial Aviation), fax: (602) 365–5577 (General Aviation), (602) 365–2832 (Commercial Aviation) 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., Nassif Building, Room PL–401, Washington, DC 20590–0001, on the internet at https://dms.dot.gov, 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: https://www.archives.gov/ PO 00000 Frm 00009 Fmt 4700 Sfmt 4700 35993 federal_register/code_of_federal_regulations/ ibr_locations.html. Related Information (n) None. Issued in Burlington, Massachusetts, on June 13, 2005. Francis A. Favara, Acting Manager, Engine and Propeller Directorate, Aircraft Certification Service. [FR Doc. 05–12080 Filed 6–21–05; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–05–19473; Directorate Identifier 2004–CE–35–AD; Amendment 39– 14146; AD 2005–13–09] RIN 2120–AA64 Airworthiness Directives; GROB– WERKE Model G120A Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Final rule; request for comments. AGENCY: SUMMARY: The FAA adopts a new airworthiness directive (AD) for certain GROB–WERKE Model G120A airplanes. This AD requires you to replace the main landing gear (MLG) up-lock hook assembly. This AD results from mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Germany. We are issuing this AD to prevent the MLG from becoming jammed and not extending, which could result in loss of control of the airplane during landing. During the comment period for the notice of proposed rulemaking (NPRM) regarding this action, we received a comment recommending the incorporation of service information to install connecting bolts secured with cotter pins instead of connecting bolts secured with snap rings. All U.S.registered airplanes currently have these actions incorporated so these actions do not impose an additional burden over that proposed in the NPRM and prior public comment is not necessary. However, we are reopening the comment period to allow the public the chance to comment on these additional actions. DATES: This AD becomes effective on July 26, 2005. As of July 26, 2005, the Director of the Federal Register approved the incorporation by reference of certain publications listed in the regulation. E:\FR\FM\22JNR1.SGM 22JNR1

Agencies

[Federal Register Volume 70, Number 119 (Wednesday, June 22, 2005)]
[Rules and Regulations]
[Pages 35992-35993]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 05-12080]



[[Page 35992]]

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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2004-18496; Directorate Identifier 2004-NE-04-AD; 
Amendment 39-14143; AD 2005-13-07]
RIN 2120-AA64


Airworthiness Directives; Honeywell International Inc. (Formerly 
AlliedSignal Inc. and Garrett Turbine Engine Co.) TFE731-2 and -3 
Series Turbofan Engines

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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

SUMMARY: The FAA is adopting a new airworthiness directive (AD) for 
Honeywell International Inc. (formerly AlliedSignal Inc. and Garrett 
Turbine Engine Co.) TFE731-2 and -3 series turbofan engines with 
certain part numbers (P/Ns) and serial numbers (SNs) of low pressure 
(LP) 1st and 2nd stage turbine rotor discs initially installed. This AD 
requires replacement of those LP 1st and 2nd stage turbine rotor discs. 
This AD results from a report of an uncontained failure of an LP 2nd 
stage turbine rotor disc that resulted in an in-flight engine shutdown. 
We are issuing this AD to prevent LP turbine rotor disk separation, 
which could result in an uncontained engine failure and damage to the 
airplane.

DATES: This AD becomes effective July 27, 2005. The Director of the 
Federal Register approved the incorporation by reference of certain 
publications listed in the regulations as of July 27, 2005.

ADDRESSES: You can get the service information identified in this AD 
from Honeywell Engines and Systems (formerly AlliedSignal Inc. and 
Garrett Turbine Engine Co.) Technical Publications and Distribution, M/
S 2101-201, P.O. Box 52170, Phoenix, AZ 85072-2170; telephone: (602) 
365-2493 (General Aviation), (602) 365-5535 (Commercial Aviation), fax: 
(602) 365-5577 (General Aviation), (602) 365-2832 (Commercial 
Aviation).
    You may examine the AD docket on the Internet at https://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: Joseph Costa, Aerospace Engineer, Los 
Angeles Aircraft Certification Office, FAA, Transport Airplane 
Directorate, 3960 Paramount Blvd., Lakewood CA 90712-4137; telephone: 
(562) 627-5246; fax: (562) 627-5210.

SUPPLEMENTARY INFORMATION: The FAA proposed to amend 14 CFR part 39 
with a proposed AD. The proposed AD applies to Honeywell International 
Inc. (formerly AlliedSignal Inc. and Garrett Turbine Engine Co.) 
TFE731-2 and -3 series turbofan engines with certain P/Ns and SNs of LP 
1st and 2nd stage turbine rotor discs initially installed as new parts 
before April 1, 1991. These discs were heat treated with a process that 
may have resulted in disk material with a non-uniform microstructure 
that is susceptible to creep fatigue, which may lead to cracking or 
separation. We published the proposed AD in the Federal Register on 
July 1, 2004 (69 FR 39875). That action proposed to require replacement 
of those LP 1st and 2nd stage turbine rotor discs.

Examining the AD Docket

    You may examine the docket that contains the AD, any comments 
received, and any final disposition in person at the DMS Docket Offices 
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 received no comments on the proposal or on 
the determination of the cost to the public.

Conclusion

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

Costs of Compliance

    There are about 56 Honeywell International Inc. TFE731-2 and -3 
series turbofan engines of the affected design in the worldwide fleet. 
We estimate that 24 engines installed on airplanes of U.S. registry 
will be affected by this AD. We also estimate that it will take about 4 
work hours per engine to perform these actions, and that the average 
labor rate is $65 per work hour. Required parts cost about $30,000 per 
engine. Based on these figures, we estimate the total cost of this AD 
to U.S. operators to be $726,240.

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:


[[Page 35993]]


    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:

2005-13-07 Honeywell International Inc. (formerly AlliedSignal Inc. 
and Garrett Turbine Engine Co.): Amendment 39-14143. Docket No. FAA-
2004-18496; Directorate Identifier. 2004-NE-04-AD.

Effective Date

    (a) This airworthiness directive (AD) becomes effective July 27, 
2005.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to Honeywell International Inc. (formerly 
AlliedSignal Inc. and Garrett Turbine Engine Co.) TFE731-2 and -3 
series turbofan engines with the following low pressure (LP) 1st and 
2nd stage turbine rotor disc part numbers (P/Ns), with serial 
numbers (SNs) listed in Tables 1, 2, and 3 of Honeywell 
International Inc. SB No. TFE731-72-3682, dated November 26, 2002, 
initially installed as new parts before April 1, 1991:

                              Part Numbers
------------------------------------------------------------------------
 
------------------------------------------------------------------------
3072069-All..............................  3073014-All
3072070-All..............................  3073113-All
3072351-All..............................  3071114-All
3072542-All..............................  3074103-All
3073013-All..............................  3074105-All
------------------------------------------------------------------------
(All denotes all dash numbers installed)

    These engines are installed on, but not limited to, the 
following airplanes:

Avions Marcel Dassault Mystere-Falcon 10 and 50 series
Cessna Model 650, Citation III, and Citation VI
Gulfstream Aerospace LP (formerly IAI) 1125 Westwind Astra series
Israel Aircraft Industries (IAI) 1124 series
Learjet 31, 35, 36, and 55 series
Lockheed-Georgia 1329-25 series (731 Jetstar, Jetstar II)
Raytheon Corporate Jets (formerly British Aerospace) DH/HS/BH-125
 series;
Sabreliner NA-265-65 (Sabreliner 65)
 

Unsafe Condition

    (d) This AD results from a report of an uncontained failure of 
an LP 2nd stage turbine rotor disc that resulted in an in-flight 
engine shutdown. We are issuing this AD to prevent LP turbine rotor 
disk separation, 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.

Removal From Service of LP 1st and 2nd Stage Turbine Rotor Discs

    (f) For TFE731-2-2J, TFE731-2-2N, TFE731-2A-2A, and TFE731-3-1J 
engines, replace discs that are listed by SN in Tables 1 and 3 of SB 
No. TFE731-72-3682, dated November 26, 2002, within 100 hours time-
in-service (TIS) after the effective date of this AD.
    (g) For TFE731-2 series engines except TFE731-2-2J, TFE731-2-2N, 
and TFE731-2A-2A engines, replace discs that are listed by SN in 
Tables 1 and 2 of SB No. TFE731-72-3682, dated November 26, 2002, at 
the next Major Periodic Inspection (MPI) or next access to the 
turbine discs after the effective date of this AD, but within 2,200 
hours TIS since the last disc inspection, whichever occurs first.
    (h) For TFE731-3 series engines except TFE731-3-1J, replace 
discs that are listed by SN in Table 3 of SB No. TFE731-72-3682, 
dated November 26, 2002, at the next MPI or next access to the 
turbine discs after the effective date of this AD, but within 1,500 
hours TIS since the last disc inspection, whichever occurs first.
    (i) Information on replacing affected discs can be found in 
Honeywell International Inc. SB No. TFE731-72-3682, dated November 
26, 2002.
    (j) After the effective date of this AD, do not install any LP 
1st and 2nd stage turbine rotor disc that has a SN listed in Table 
1, 2, or 3 of SB No. TFE731-72-3682, dated November 26, 2002, and 
determined to be manufactured before April 1, 1991.

Definitions

    (k) For the purposes of this AD, access to the turbine discs is 
the level of disassembly that has removed the tie-shaft nut.

Alternative Methods of Compliance

    (l) The Manager, Los Angeles Aircraft 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.

Material Incorporated by Reference

    (m) You must use Honeywell International, Inc. Service Bulletin 
No. TFE731-72-3682, dated November 26, 2002, 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 Honeywell Engines and Systems Technical Publications and 
Distribution, M/S 2101-201, P.O. Box 52170, Phoenix, AZ 85072-2170; 
telephone: (602) 365-2493 (General Aviation), (602) 365-5535 
(Commercial Aviation), fax: (602) 365-5577 (General Aviation), (602) 
365-2832 (Commercial Aviation) 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., Nassif Building, Room PL-401, Washington, DC 20590-0001, on the 
internet at https://dms.dot.gov, 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: https://
www.archives.gov/federal_register/code_of_federal_regulations/
ibr_locations.html.

Related Information

    (n) None.

    Issued in Burlington, Massachusetts, on June 13, 2005.
Francis A. Favara,
Acting Manager, Engine and Propeller Directorate, Aircraft 
Certification Service.
[FR Doc. 05-12080 Filed 6-21-05; 8:45 am]
BILLING CODE 4910-13-P

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