Airworthiness Directives; Bombardier Model CL-600-2B19 (Regional Jet Series 100 & 440) Airplanes, 52902-52903 [05-17405]

Download as PDF 52902 Federal Register / Vol. 70, No. 171 / Tuesday, September 6, 2005 / Rules and Regulations Issued in Renton, Washington, on August 24, 2005. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 05–17461 Filed 9–2–05; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. 2003–NM–163–AD; Amendment 39–14244; AD 2005–18–04] 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. AGENCY: SUMMARY: This amendment adopts a new airworthiness directive (AD), applicable to certain Bombardier Model CL–600–2B19 (Regional Jet Series 100& 440) airplanes, that requires performing an inspection of the electrical harnesses of the spoiler and the brake pressure sensor unit on both sides of the wing root to detect any chafing or wire damage, and repairing or replacing any damaged or chafed harness or wire with a new harness, as applicable. This action also provides/requires a terminating modification for the onetime inspection. The actions specified by this AD are intended to detect and correct chafing of the electrical cables of the spoiler and brake pressure sensor unit on both sides of the wing root, which could result in loss of the flight control system and consequent reduced controllability of the airplane. This action is intended to address the identified unsafe condition. DATES: Effective October 11, 2005. The incorporation by reference of a certain publication listed in the regulations is approved by the Director of the Federal Register as of October 11, 2005. ADDRESSES: The service information referenced in this AD may be obtained from Bombardier, Inc., Canadair, Aerospace Group, P.O. Box 6087, Station Centreville, Montreal, Quebec H3C 3G9, Canada. This information may be examined at the Federal Aviation Administration (FAA), Transport Airplane Directorate, Rules Docket, 1601 Lind Avenue, SW., Renton, Washington; or at the FAA, New York VerDate Aug<18>2005 11:56 Sep 02, 2005 Jkt 205001 Aircraft Certification Office, 1600 Stewart Avenue, Suite 410, Westbury, New York 11590; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. 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: A proposal to amend part 39 of the Federal Aviation Regulations (14 CFR part 39) to include an airworthiness directive (AD) that is applicable to certain Bombardier Model CL–600–2B19 (Regional Jet Series 100 & 440) airplanes was published as a supplemental notice of proposed rulemaking (NPRM) in the Federal Register on June 27, 2005 (70 FR 36862). That action proposed to require performing an inspection of the electrical harnesses of the spoiler and the brake pressure sensor unit on both sides of the wing root to detect any chafing or wire damage, and repairing or replacing any damaged or chafed harness or wire with a new harness, as applicable. The action also proposed to require performing a terminating modification for the one-time inspection. Comments Interested persons have been afforded an opportunity to participate in the making of this amendment. We received no comments on the proposed AD or on the determination of the cost to the public. Conclusion After careful review of the available data, the FAA has determined that air safety and the public interest require the adoption of the rule as proposed. Cost Impact The FAA estimates that 709 airplanes of U.S. registry will be affected by this AD. It will take approximately 1 work hour per airplane to accomplish the required inspection, at the average labor rate of $65 per work hour. Based on these figures, the cost impact of the inspection required by this AD on U.S. operators is estimated to be $46,085, or $65 per airplane. It will take approximately 5 work hours per airplane to accomplish the required modification, at the average labor rate of $65 per work hour. Required parts will be supplied by the airplane manufacturer at no cost to operators. Based on these figures, the PO 00000 Frm 00010 Fmt 4700 Sfmt 4700 cost impact of the modification required by this AD on U.S. operators is estimated to be $230,425, or $325 per airplane. The cost impact figures discussed above are based on assumptions that no operator has yet accomplished any of the requirements of this AD action, and that no operator would accomplish those actions in the future if thisAD were not adopted. The cost impact figures discussed in AD rulemaking actions represent only the time necessary to perform the specific actions actually required by the AD. These figures typically do not include incidental costs, such as the time required to gain access and close up, planning time, or time necessitated by other administrative actions. 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 Impact The regulations adopted herein 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. Therefore, it is determined that this final rule does not have federalism implications under Executive Order 13132. For the reasons discussed above, I certify that this action (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. A final evaluation has E:\FR\FM\06SER1.SGM 06SER1 Federal Register / Vol. 70, No. 171 / Tuesday, September 6, 2005 / Rules and Regulations been prepared for this action and it is contained in the Rules Docket. A copy of it may be obtained from the Rules Docket at the location provided under the caption ADDRESSES. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. Adoption of the Amendment Accordingly, pursuant to the authority delegated to me by the Administrator, the Federal Aviation Administration amends part 39 of the Federal Aviation Regulations (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. Section 39.13 is amended by adding the following new airworthiness directive: I 2005–18–04 Bombardier, Inc. (Formerly Canadair): Amendment 39–14244. Docket 2003–NM–163–AD. Applicability: Model CL–600–2B19 (Regional Jet Series 100 & 440) airplanes, serial numbers 7003 through 7067 inclusive, and 7069 through 7947 inclusive; certificated in any category. Compliance: Required as indicated, unless accomplished previously. To detect and correct chafing of the electrical cables of the spoiler and brake pressure sensor unit (BPSU) on both sides of the wing root, which could result in loss of the flight control system and consequent reduced controllability of the airplane, accomplish the following: Initial Inspections (a) Within 500 flight hours after the effective date of this AD, do a general visual inspection for chafing or wire damage of the electrical harnesses of the spoiler and the BPSU on both sides of the wing root, in accordance with Part A of the Accomplishment Instructions of Bombardier Alert Service Bulletin A601R–27–133, Revision ‘A,’ dated September 16, 2004. Note 1: For the purposes of this AD, a general visual inspection is defined as: ‘‘A visual examination of an interior or exterior area, installation, or assembly to detect obvious damage, failure, or irregularity. This level of inspection is made from within touching distance unless otherwise specified. A mirror may be necessary to enhance visual access to all exposed surfaces in the inspection area. This level of inspection is made under normally available lighting conditions such as daylight, hangar lighting, flashlight, or droplight and may require removal or opening of access panels or doors. Stands, ladders, or platforms may be required to gain proximity to the area being checked.’’ VerDate Aug<18>2005 11:56 Sep 02, 2005 Jkt 205001 Corrective Actions (b) If any damaged or chafed electrical harness or wire is found during any inspection required by paragraph (a) of this AD, before further flight, do either paragraph (b)(1) or (b)(2) of this AD. (1) Replace any damaged or chafed harness or wire with a new harness, in accordance with Part C or Part D of the Accomplishment Instructions of Bombardier Alert Service Bulletin A601R–27–133, Revision ‘A’, dated September 16, 2004, as applicable. (2) Repair any damaged or chafed electrical harness in accordance with Part B of the Accomplishment Instructions of Bombardier Alert ServiceBulletin A601R–27–133, Revision ‘A’, dated September 16, 2004. Within 3,500 flight hours after the repair is done, do paragraph (b)(1) of this AD. Credit for Earlier Service Bulletins (c) Inspections, replacements, and repairs accomplished before the effective date of this AD in accordance with Bombardier Alert ServiceBulletin A601R–27–101, dated April 17, 2000; or Revision ‘A,’ dated October 26, 2001; or Bombardier Alert Service Bulletin A601R–27–133, dated July 12, 2004; are acceptable for compliance with the corresponding requirements of this AD. Terminating Modification (d) Within 4,000 flight hours after the effective date of this AD, modify the routing and support of the electrical harnesses of the spoiler and the BPSU on both sides of the wing root by accomplishing all the actions specified in Part E or F, as applicable, of the AccomplishmentInstructions of Bombardier Alert Service Bulletin A601R–27–133, Revision ‘A’, dated September 16, 2004. Accomplishing the modification constitutes compliance with the requirements of this AD. Exception to Service Bulletin (e) Although Bombardier Alert Service Bulletin A601R–27–133, Revision‘A’, dated September 16, 2004, specifies to submit certain information to the manufacturer, this AD does not include that requirement. Alternative Methods of Compliance (f) In accordance with 14 CFR 39.19, the Manager, New York AircraftCertification Office, FAA, is authorized to approve alternative methods of compliance for this AD. Note 2: The subject of this AD is addressed in Canadiar airworthiness directive CF– 2003–14R1, effective February 26, 2005. Incorporation by Reference (g) Unless otherwise specified in this AD, the actions must be done in accordance with Bombardier Alert Service Bulletin A601R– 27–133, Revision ‘A’, dated September 16, 2004. This incorporation by reference was approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. To get copies of this service information, contact Bombardier, Inc., Canadair, Aerospace Group, P.O. Box 6087, Station Centre-ville, Montreal, Quebec H3C 3G9, Canada. To inspect copies of this service information, go to the FAA, TransportAirplane Directorate, 1601 Lind PO 00000 Frm 00011 Fmt 4700 Sfmt 4700 52903 Avenue, SW., Renton, Washington; or to the FAA, New York Aircraft Certification Office, 1600 Stewart Avenue, Suite 410, Westbury, New York 11590; or to the National Archives and RecordsAdministration (NARA). For information on the availability of this material at the NARA, call (202) 741–6030, or go to https://www.archives.gov/federalregister/cfr/ibr-locations.html. Effective Date (h) This amendment becomes effective on October 11, 2005. Issued in Renton, Washington, on August 24, 2005. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 05–17405 Filed 9–2–05; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 71 [Docket No. FAA–2005–21256; Airspace Docket No. 05–AGL–04] Establishment of Class D Airspace; Eau Claire, WI Federal Aviation Administration (FAA), DOT. ACTION: Direct final rule; request for comments. AGENCY: SUMMARY: This document establishes Class D airspace at Eau Clair, WI. A control tower is currently under construction at Chippewa Valley Regional Airport. Controlled airspace extending upward from the surface is required when the control tower is operational. This action establishes a radius of controlled airspace for Eau Clair, WI. DATES: Effective 0901 UTC, October 27, 2005. Comments must be received on or before October 10, 2005. ADDRESSES: Send comments on the proposal to the Docket Management System, U.S. Department of Transportation, Room Plaza 401, 400 Seventh Street, SW., Washington, DC 20590–0001. You must identify the docket Number FAA–2005–21256/ Airspace Docket No. 05–AGL–04, at the beginning of your comments. You may also submit comments on the internet at https://dms.dot.gov. You may review the public docket containing the proposal, any comments received, and any final disposition in person in the Dockets Office between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The Docket Office (telephone 1–800–647–5527) is on the plaza level E:\FR\FM\06SER1.SGM 06SER1

Agencies

[Federal Register Volume 70, Number 171 (Tuesday, September 6, 2005)]
[Rules and Regulations]
[Pages 52902-52903]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 05-17405]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2003-NM-163-AD; Amendment 39-14244; AD 2005-18-04]
RIN 2120-AA64


Airworthiness Directives; Bombardier Model CL-600-2B19 (Regional 
Jet Series 100 & 440) Airplanes

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

ACTION: Final rule.

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

SUMMARY: This amendment adopts a new airworthiness directive (AD), 
applicable to certain Bombardier Model CL-600-2B19 (Regional Jet Series 
100& 440) airplanes, that requires performing an inspection of the 
electrical harnesses of the spoiler and the brake pressure sensor unit 
on both sides of the wing root to detect any chafing or wire damage, 
and repairing or replacing any damaged or chafed harness or wire with a 
new harness, as applicable. This action also provides/requires a 
terminating modification for the one-time inspection. The actions 
specified by this AD are intended to detect and correct chafing of the 
electrical cables of the spoiler and brake pressure sensor unit on both 
sides of the wing root, which could result in loss of the flight 
control system and consequent reduced controllability of the airplane. 
This action is intended to address the identified unsafe condition.

DATES: Effective October 11, 2005.
    The incorporation by reference of a certain publication listed in 
the regulations is approved by the Director of the Federal Register as 
of October 11, 2005.

ADDRESSES: The service information referenced in this AD may be 
obtained from Bombardier, Inc., Canadair, Aerospace Group, P.O. Box 
6087, Station Centreville, Montreal, Quebec H3C 3G9, Canada. This 
information may be examined at the Federal Aviation Administration 
(FAA), Transport Airplane Directorate, Rules Docket, 1601 Lind Avenue, 
SW., Renton, Washington; or at the FAA, New York Aircraft Certification 
Office, 1600 Stewart Avenue, Suite 410, Westbury, New York 11590; or at 
the Office of the Federal Register, 800 North Capitol Street, NW., 
suite 700, Washington, DC.

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: A proposal to amend part 39 of the Federal 
Aviation Regulations (14 CFR part 39) to include an airworthiness 
directive (AD) that is applicable to certain Bombardier Model CL-600-
2B19 (Regional Jet Series 100 & 440) airplanes was published as a 
supplemental notice of proposed rulemaking (NPRM) in the Federal 
Register on June 27, 2005 (70 FR 36862). That action proposed to 
require performing an inspection of the electrical harnesses of the 
spoiler and the brake pressure sensor unit on both sides of the wing 
root to detect any chafing or wire damage, and repairing or replacing 
any damaged or chafed harness or wire with a new harness, as 
applicable. The action also proposed to require performing a 
terminating modification for the one-time inspection.

Comments

    Interested persons have been afforded an opportunity to participate 
in the making of this amendment. We received no comments on the 
proposed AD or on the determination of the cost to the public.

Conclusion

    After careful review of the available data, the FAA has determined 
that air safety and the public interest require the adoption of the 
rule as proposed.

Cost Impact

    The FAA estimates that 709 airplanes of U.S. registry will be 
affected by this AD.
    It will take approximately 1 work hour per airplane to accomplish 
the required inspection, at the average labor rate of $65 per work 
hour. Based on these figures, the cost impact of the inspection 
required by this AD on U.S. operators is estimated to be $46,085, or 
$65 per airplane.
    It will take approximately 5 work hours per airplane to accomplish 
the required modification, at the average labor rate of $65 per work 
hour. Required parts will be supplied by the airplane manufacturer at 
no cost to operators. Based on these figures, the cost impact of the 
modification required by this AD on U.S. operators is estimated to be 
$230,425, or $325 per airplane.
    The cost impact figures discussed above are based on assumptions 
that no operator has yet accomplished any of the requirements of this 
AD action, and that no operator would accomplish those actions in the 
future if thisAD were not adopted. The cost impact figures discussed in 
AD rulemaking actions represent only the time necessary to perform the 
specific actions actually required by the AD. These figures typically 
do not include incidental costs, such as the time required to gain 
access and close up, planning time, or time necessitated by other 
administrative actions.

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 Impact

    The regulations adopted herein 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. Therefore, it 
is determined that this final rule does not have federalism 
implications under Executive Order 13132.
    For the reasons discussed above, I certify that this action (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. A final evaluation has

[[Page 52903]]

been prepared for this action and it is contained in the Rules Docket. 
A copy of it may be obtained from the Rules Docket at the location 
provided under the caption ADDRESSES.

List of Subjects in 14 CFR Part 39

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

Adoption of the Amendment

0
Accordingly, pursuant to the authority delegated to me by the 
Administrator, the Federal Aviation Administration amends part 39 of 
the Federal Aviation Regulations (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. Section 39.13 is amended by adding the following new airworthiness 
directive:

2005-18-04 Bombardier, Inc. (Formerly Canadair): Amendment 39-14244. 
Docket 2003-NM-163-AD.
    Applicability: Model CL-600-2B19 (Regional Jet Series 100 & 440) 
airplanes, serial numbers 7003 through 7067 inclusive, and 7069 
through 7947 inclusive; certificated in any category.
    Compliance: Required as indicated, unless accomplished 
previously.
    To detect and correct chafing of the electrical cables of the 
spoiler and brake pressure sensor unit (BPSU) on both sides of the 
wing root, which could result in loss of the flight control system 
and consequent reduced controllability of the airplane, accomplish 
the following:

Initial Inspections

    (a) Within 500 flight hours after the effective date of this AD, 
do a general visual inspection for chafing or wire damage of the 
electrical harnesses of the spoiler and the BPSU on both sides of 
the wing root, in accordance with Part A of the Accomplishment 
Instructions of Bombardier Alert Service Bulletin A601R-27-133, 
Revision `A,' dated September 16, 2004.

    Note 1: For the purposes of this AD, a general visual inspection 
is defined as: ``A visual examination of an interior or exterior 
area, installation, or assembly to detect obvious damage, failure, 
or irregularity. This level of inspection is made from within 
touching distance unless otherwise specified. A mirror may be 
necessary to enhance visual access to all exposed surfaces in the 
inspection area. This level of inspection is made under normally 
available lighting conditions such as daylight, hangar lighting, 
flashlight, or droplight and may require removal or opening of 
access panels or doors. Stands, ladders, or platforms may be 
required to gain proximity to the area being checked.''

Corrective Actions

    (b) If any damaged or chafed electrical harness or wire is found 
during any inspection required by paragraph (a) of this AD, before 
further flight, do either paragraph (b)(1) or (b)(2) of this AD.
    (1) Replace any damaged or chafed harness or wire with a new 
harness, in accordance with Part C or Part D of the Accomplishment 
Instructions of Bombardier Alert Service Bulletin A601R-27-133, 
Revision `A', dated September 16, 2004, as applicable.
    (2) Repair any damaged or chafed electrical harness in 
accordance with Part B of the Accomplishment Instructions of 
Bombardier Alert ServiceBulletin A601R-27-133, Revision `A', dated 
September 16, 2004. Within 3,500 flight hours after the repair is 
done, do paragraph (b)(1) of this AD.

Credit for Earlier Service Bulletins

    (c) Inspections, replacements, and repairs accomplished before 
the effective date of this AD in accordance with Bombardier Alert 
ServiceBulletin A601R-27-101, dated April 17, 2000; or Revision `A,' 
dated October 26, 2001; or Bombardier Alert Service Bulletin A601R-
27-133, dated July 12, 2004; are acceptable for compliance with the 
corresponding requirements of this AD.

Terminating Modification

    (d) Within 4,000 flight hours after the effective date of this 
AD, modify the routing and support of the electrical harnesses of 
the spoiler and the BPSU on both sides of the wing root by 
accomplishing all the actions specified in Part E or F, as 
applicable, of the AccomplishmentInstructions of Bombardier Alert 
Service Bulletin A601R-27-133, Revision `A', dated September 16, 
2004. Accomplishing the modification constitutes compliance with the 
requirements of this AD.

Exception to Service Bulletin

    (e) Although Bombardier Alert Service Bulletin A601R-27-133, 
Revision`A', dated September 16, 2004, specifies to submit certain 
information to the manufacturer, this AD does not include that 
requirement.

Alternative Methods of Compliance

    (f) In accordance with 14 CFR 39.19, the Manager, New York 
AircraftCertification Office, FAA, is authorized to approve 
alternative methods of compliance for this AD.

    Note 2: The subject of this AD is addressed in Canadiar 
airworthiness directive CF-2003-14R1, effective February 26, 2005.

Incorporation by Reference

    (g) Unless otherwise specified in this AD, the actions must be 
done in accordance with Bombardier Alert Service Bulletin A601R-27-
133, Revision `A', dated September 16, 2004. This incorporation by 
reference was approved by the Director of the Federal Register in 
accordance with 5 U.S.C. 552(a) and 1 CFR part 51. To get copies of 
this service information, contact Bombardier, Inc., Canadair, 
Aerospace Group, P.O. Box 6087, Station Centre-ville, Montreal, 
Quebec H3C 3G9, Canada. To inspect copies of this service 
information, go to the FAA, TransportAirplane Directorate, 1601 Lind 
Avenue, SW., Renton, Washington; or to the FAA, New York Aircraft 
Certification Office, 1600 Stewart Avenue, Suite 410, Westbury, New 
York 11590; or to the National Archives and RecordsAdministration 
(NARA). For information on the availability of this material at the 
NARA, call (202) 741-6030, or go to https://www.archives.gov/federal-
register/cfr/ibr-locations.html.

Effective Date

    (h) This amendment becomes effective on October 11, 2005.

    Issued in Renton, Washington, on August 24, 2005.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 05-17405 Filed 9-2-05; 8:45 am]
BILLING CODE 4910-13-P

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