Airworthiness Directives; Airbus Model A300 B2 and B4 Series Airplanes, 36833-36834 [05-12505]

Download as PDF Federal Register / Vol. 70, No. 122 / Monday, June 27, 2005 / Rules and Regulations Vennep, the Netherlands. To view the AD docket, go to the Docket Management Facility, U.S. Department of Transportation, 400 Seventh Street SW, room PL–401, Nassif Building, Washington, DC. To review copies of the service information, go to 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. TABLE 1.—MATERIAL INCORPORATED BY REFERENCE Fokker Service Bulletin Revision level F28/57–93 F28/57–96 Original ..... Original ..... Date Dec. 22, 2003. Dec. 22, 2003. Issued in Renton, Washington, on June 14, 2005. Kevin M. Mullin, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 05–12504 Filed 6–24–05; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2005–20861; Directorate Identifier 2005–NM–020–AD; Amendment 39–14170; AD 2005–13–33] RIN 2120–AA64 Airworthiness Directives; Airbus Model A300 B2 and B4 Series Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: The FAA is adopting a new airworthiness directive (AD) for certain Airbus Model A300 B2 and B4 series airplanes. This AD requires modifying the wiring of the autopilot pitch torque limiter switch. This AD is prompted by several reports of pitch trim disconnect caused by insufficient length in the wiring to the pitch torque limiter lever. We are issuing this AD to prevent possible trim loss when the flightcrew tries to override the autopilot pitch control, which could result in uncontrolled flight of the airplane. DATES: This AD becomes effective August 1, 2005. The incorporation by reference of a certain publication listed in the AD is approved by the Director of the Federal Register as of August 1, 2005. SUMMARY: VerDate jul<14>2003 16:46 Jun 24, 2005 Jkt 205001 For service information identified in this AD, contact Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France. Docket: The AD docket contains the proposed AD, comments, and any final disposition. You can examine the AD docket on the Internet at http:// dms.dot.gov, or in person at the Docket Management Facility office between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The Docket Management Facility office (telephone (800) 647–5227) is located on the plaza level of the Nassif Building at the U.S. Department of Transportation, 400 Seventh Street SW., room PL–401, Washington, DC. This docket number is FAA–2005–20861; the directorate identifier for this docket is 2005–NM– 020–AD. FOR FURTHER INFORMATION CONTACT: Rosanne Ryburn, Aerospace Engineer, International Branch, ANM–116, FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington 98055–4056; telephone (425) 227–2139; fax (425) 227–1149. SUPPLEMENTARY INFORMATION: The FAA proposed to amend 14 CFR part 39 with an AD for certain Airbus Model A300 B2 and B4 series airplanes. That action, published in the Federal Register on April 6, 2005 (70 FR 17347), proposed to require modifying the wiring of the autopilot pitch torque limiter switch. ADDRESSES: Comments We provided the public the opportunity to participate in the development of this AD. We have considered the one comment that has been submitted on the proposed AD. Support for the Proposed AD The commenter supports the proposed AD. Change to This AD We have updated reference to Airbus Model A300 B2 and B4 series airplanes in paragraph (c) of this AD to match the common model designation identified in the latest revision of the type certificate data sheet. Conclusion We have carefully reviewed the available data, including the comment that has been submitted, and determined that air safety and the public interest require adopting the AD as proposed. Costs of Compliance This AD affects about 20 airplanes of U.S. registry. The actions take between 8 and 11 work hours per airplane, depending on airplane configuration, at PO 00000 Frm 00025 Fmt 4700 Sfmt 4700 36833 an average labor rate of $65 per work hour. Required parts cost between $1,840 and $4,280 per airplane, depending on airplane configuration. Based on these figures, the estimated cost of the AD for U.S. operators is between $47,200 and $99,900, or between $2,360 and $4,995 per airplane. 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 regulatory evaluation of the estimated costs to comply with this AD. See the ADDRESSES section for a location to examine the regulatory evaluation. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. E:\FR\FM\27JNR1.SGM 27JNR1 36834 Federal Register / Vol. 70, No. 122 / Monday, June 27, 2005 / Rules and Regulations Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA 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 (AD): I 2005–13–33 Airbus: Amendment 39–14170. Docket No. FAA–2005–20861; Directorate Identifier 2005–NM–020–AD. Effective Date (a) This AD becomes effective August 1, 2005. Issued in Renton, Washington, on June 14, 2005. Kevin M. Mullin, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 05–12505 Filed 6–24–05; 8:45 am] BILLING CODE 4910–13–P Affected ADs (b) None. Applicability (c) This AD applies to Airbus Model A300 B2–1A, B2–1C, B2K–3C, and B2–203 airplanes; and Model A300 B4–2C, B4–103, and B4–203 airplanes; certificated in any category; as identified in Airbus Service Bulletin A300–22–0117, dated September 7, 2004. Unsafe Condition (d) This AD was prompted by several reports of pitch trim disconnect caused by insufficient length in the wiring to the pitch torque limiter lever. We are issuing this AD to prevent possible trim loss when the flightcrew tries to override the autopilot pitch control, which could result in uncontrolled flight of 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. Modification (f) Within 20 months after the effective date of this AD, modify the wiring of the autopilot pitch torque limiter switch, by doing all of the applicable actions specified in the Accomplishment Instructions of Airbus Service Bulletin A300–22–0117, dated September 7, 2004. Alternative Methods of Compliance (AMOCs) (g) The Manager, International Branch, ANM–116, Transport Airplane Directorate, FAA, has the authority to approve AMOCs for this AD, if requested in accordance with the procedures found in 14 CFR 39.19. Material Incorporated by Reference (h) You must use Airbus Service Bulletin A300–22–0117, dated September 7, 2004, to perform the actions that are required by this VerDate jul<14>2003 AD, unless the AD specifies otherwise. The Director of the Federal Register approves the incorporation by reference of this document in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. To get copies of the service information, contact Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France. To view the AD docket, go to the Docket Management Facility, U.S. Department of Transportation, 400 Seventh Street SW., room PL–401, Nassif Building, Washington, DC. To review copies of the service information, go to 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. 16:46 Jun 24, 2005 Jkt 205001 DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2005–20660; Directorate Identifier 2004–NM–242–AD; Amendment 39–14166; AD 2005–13–29] RIN 2120–AA64 Airworthiness Directives; Boeing Model 777–200 and –300 Series Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: SUMMARY: The FAA is adopting a new airworthiness directive (AD) for certain Boeing Model 777–200 and -300 series airplanes. This AD requires inspecting for the installation of the tie plate for the wire bundles routed from lower section 41 into the center control stand in the flight deck; inspecting for any wire chafing or damage and repair if necessary; and installing a tie plate if necessary. This AD is prompted by a report of missing tie plates for the wire bundles. We are issuing this AD to prevent wire chafing, which could result in the loss of flight control, communication, navigation, and engine fire control systems. Loss of these systems could consequently result in a significant reduction of safety margins, an increase in flight crew workload, and in the case where loss of engine fire control is combined with an engine fire, could result in an uncontrollable fire. PO 00000 Frm 00026 Fmt 4700 Sfmt 4700 This AD becomes effective August 1, 2005. The incorporation by reference of a certain publication listed in the AD is approved by the Director of the Federal Register as of August 1, 2005. ADDRESSES: For service information identified in this AD, contact Boeing Commercial Airplanes, P.O. Box 3707, Seattle, Washington 98124–2207. Docket: The AD docket contains the proposed AD, comments, and any final disposition. You can examine the AD docket on the Internet at http:// dms.dot.gov, or in person at the Docket Management Facility office between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The Docket Management Facility office (telephone (800) 647–5227) is located on the plaza level of the Nassif Building at the U.S. Department of Transportation, 400 Seventh Street SW., room PL–401, Washington, DC. This docket number is FAA–2005–20660; the directorate identifier for this docket is 2004–NM– 242–AD. FOR FURTHER INFORMATION CONTACT: Georgios Roussos, Aerospace Engineer, Systems and Equipment Branch, ANM– 130S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue, SW., Renton, Washington 98055–4056; telephone (425) 917–6482; fax (425) 917–6590. SUPPLEMENTARY INFORMATION: The FAA proposed to amend 14 CFR part 39 with an AD for certain Boeing Model 777– 200 and –300 series airplanes. That action, published in the Federal Register on March 22, 2005 (70 FR 14430), proposed to require inspecting for the installation of the tie plate for the wire bundles routed from lower section 41 into the center control stand in the flight deck; inspecting for any wire chafing or damage and repair if necessary; and installing a tie plate if necessary. DATES: Comment We provided the public the opportunity to participate in the development of this AD. We have considered the comment that has been submitted on the proposed AD. The commenter supports the proposed AD. Conclusion We have carefully reviewed the available data, including the comment that has been submitted, and determined that air safety and the public interest require adopting the AD as proposed. Costs of Compliance There are about 289 airplanes of the affected design in the worldwide fleet. E:\FR\FM\27JNR1.SGM 27JNR1

Agencies

[Federal Register Volume 70, Number 122 (Monday, June 27, 2005)]
[Rules and Regulations]
[Pages 36833-36834]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 05-12505]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2005-20861; Directorate Identifier 2005-NM-020-AD; 
Amendment 39-14170; AD 2005-13-33]
RIN 2120-AA64


Airworthiness Directives; Airbus Model A300 B2 and B4 Series 
Airplanes

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

ACTION: Final rule.

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

SUMMARY: The FAA is adopting a new airworthiness directive (AD) for 
certain Airbus Model A300 B2 and B4 series airplanes. This AD requires 
modifying the wiring of the autopilot pitch torque limiter switch. This 
AD is prompted by several reports of pitch trim disconnect caused by 
insufficient length in the wiring to the pitch torque limiter lever. We 
are issuing this AD to prevent possible trim loss when the flightcrew 
tries to override the autopilot pitch control, which could result in 
uncontrolled flight of the airplane.

DATES: This AD becomes effective August 1, 2005.
    The incorporation by reference of a certain publication listed in 
the AD is approved by the Director of the Federal Register as of August 
1, 2005.

ADDRESSES: For service information identified in this AD, contact 
Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France.
    Docket: The AD docket contains the proposed AD, comments, and any 
final disposition. You can examine the AD docket on the Internet at 
http://dms.dot.gov, or in person at the Docket Management Facility 
office between 9 a.m. and 5 p.m., Monday through Friday, except Federal 
holidays. The Docket Management Facility office (telephone (800) 647-
5227) is located on the plaza level of the Nassif Building at the U.S. 
Department of Transportation, 400 Seventh Street SW., room PL-401, 
Washington, DC. This docket number is FAA-2005-20861; the directorate 
identifier for this docket is 2005-NM-020-AD.

FOR FURTHER INFORMATION CONTACT: Rosanne Ryburn, Aerospace Engineer, 
International Branch, ANM-116, FAA, Transport Airplane Directorate, 
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425) 
227-2139; fax (425) 227-1149.

SUPPLEMENTARY INFORMATION: The FAA proposed to amend 14 CFR part 39 
with an AD for certain Airbus Model A300 B2 and B4 series airplanes. 
That action, published in the Federal Register on April 6, 2005 (70 FR 
17347), proposed to require modifying the wiring of the autopilot pitch 
torque limiter switch.

Comments

    We provided the public the opportunity to participate in the 
development of this AD. We have considered the one comment that has 
been submitted on the proposed AD.

Support for the Proposed AD

    The commenter supports the proposed AD.

Change to This AD

    We have updated reference to Airbus Model A300 B2 and B4 series 
airplanes in paragraph (c) of this AD to match the common model 
designation identified in the latest revision of the type certificate 
data sheet.

Conclusion

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

Costs of Compliance

    This AD affects about 20 airplanes of U.S. registry. The actions 
take between 8 and 11 work hours per airplane, depending on airplane 
configuration, at an average labor rate of $65 per work hour. Required 
parts cost between $1,840 and $4,280 per airplane, depending on 
airplane configuration. Based on these figures, the estimated cost of 
the AD for U.S. operators is between $47,200 and $99,900, or between 
$2,360 and $4,995 per airplane.

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 regulatory evaluation of the estimated costs to 
comply with this AD. See the ADDRESSES section for a location to 
examine the regulatory evaluation.

List of Subjects in 14 CFR Part 39

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

[[Page 36834]]

Adoption of the Amendment

0
Accordingly, under the authority delegated to me by the Administrator, 
the FAA 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 (AD):

2005-13-33 Airbus: Amendment 39-14170. Docket No. FAA-2005-20861; 
Directorate Identifier 2005-NM-020-AD.

Effective Date

    (a) This AD becomes effective August 1, 2005.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to Airbus Model A300 B2-1A, B2-1C, B2K-3C, 
and B2-203 airplanes; and Model A300 B4-2C, B4-103, and B4-203 
airplanes; certificated in any category; as identified in Airbus 
Service Bulletin A300-22-0117, dated September 7, 2004.

Unsafe Condition

    (d) This AD was prompted by several reports of pitch trim 
disconnect caused by insufficient length in the wiring to the pitch 
torque limiter lever. We are issuing this AD to prevent possible 
trim loss when the flightcrew tries to override the autopilot pitch 
control, which could result in uncontrolled flight of 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.

Modification

    (f) Within 20 months after the effective date of this AD, modify 
the wiring of the autopilot pitch torque limiter switch, by doing 
all of the applicable actions specified in the Accomplishment 
Instructions of Airbus Service Bulletin A300-22-0117, dated 
September 7, 2004.

Alternative Methods of Compliance (AMOCs)

    (g) The Manager, International Branch, ANM-116, Transport 
Airplane Directorate, FAA, has the authority to approve AMOCs for 
this AD, if requested in accordance with the procedures found in 14 
CFR 39.19.

Material Incorporated by Reference

    (h) You must use Airbus Service Bulletin A300-22-0117, dated 
September 7, 2004, to perform the actions that are required by this 
AD, unless the AD specifies otherwise. The Director of the Federal 
Register approves the incorporation by reference of this document in 
accordance with 5 U.S.C. 552(a) and 1 CFR part 51. To get copies of 
the service information, contact Airbus, 1 Rond Point Maurice 
Bellonte, 31707 Blagnac Cedex, France. To view the AD docket, go to 
the Docket Management Facility, U.S. Department of Transportation, 
400 Seventh Street SW., room PL-401, Nassif Building, Washington, 
DC. To review copies of the service information, go to 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 June 14, 2005.
Kevin M. Mullin,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 05-12505 Filed 6-24-05; 8:45 am]
BILLING CODE 4910-13-P