Airworthiness Directives; Airbus Model A300 B2 and A300 B4 Series Airplanes; Model A300 B4-600, B4-600R and F4-600R Series Airplanes, and Model A300 C4-605R Variant F Airplanes (Collectively Called A300-600); and Model A310 Series Airplanes, 16981-16984 [05-6578]

Download as PDF Federal Register / Vol. 70, No. 63 / Monday, April 4, 2005 / Proposed Rules Compliance DEPARTMENT OF TRANSPORTATION (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. Inspection for Float Switches (f) Within 48 months after the effective date of this AD, inspect the wing and auxiliary fuel tanks to determine if any float switches are present. Instead of an inspection of the fuel tanks, a review of airplane maintenance records is acceptable if the presence of any float switch can be conclusively determined from that review. (1) If no float switches are present: No further work is required by this paragraph. (2) If any float switch is present: Before further flight, inspect to identify the float switch models. Instead of an inspection of the fuel tanks, a review of airplane maintenance records is acceptable if the identity of the float switch can be conclusively determined from that review. (i) If a float switch other than an Ametek Model F8300–146 float switch is installed: Before further flight, install a liner system inside the float switch electrical cable conduit in the fuel tanks by doing all applicable actions specified in the Accomplishment Instructions of Boeing Alert Service Bulletin 727–28A0127, dated August 26, 2004. (ii) If any Ametek Model F8300–146 float switch is installed: Before further flight, replace it with a new switch and install a liner system inside the float switch electrical cable conduit in the fuel tanks, by doing all applicable actions specified in the Accomplishment Instructions of Boeing Alert Service Bulletin 727–28A0127, dated August 26, 2004. Note 1: Boeing Alert Service Bulletin 727– 28A0127 segregates the work into nine work packages for the six fuel tank configurations identified in the service bulletin. The work packages do not have to be completed sequentially. Each work package can be done independently or simultaneously. However, all work packages, as applicable for each fuel tank configuration, must be done to complete the requirements of this AD. Parts Installation (g) As of the effective date of this AD, no person may install an Ametek Model F8300– 146 float switch in a fuel tank on any airplane. Alternative Methods of Compliance (AMOCs) (h) The Manager, Seattle Aircraft Certification Office, FAA, has the authority to approve AMOCs for this AD, if requested in accordance with the procedures found in 14 CFR 39.19. Issued in Renton, Washington, on March 28, 2005. Kalene C. Yanamura, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 05–6577 Filed 4–1–05; 8:45 am] BILLING CODE 4910–13–P VerDate jul<14>2003 15:01 Apr 01, 2005 Jkt 205001 Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2005–20796; Directorate Identifier 2004–NM–160–AD] RIN 2120–AA64 Airworthiness Directives; Airbus Model A300 B2 and A300 B4 Series Airplanes; Model A300 B4–600, B4–600R and F4– 600R Series Airplanes, and Model A300 C4–605R Variant F Airplanes (Collectively Called A300–600); and Model A310 Series Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Notice of proposed rulemaking (NPRM). AGENCY: SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD) for all the Airbus models identified above. This proposed AD would require modifying the electrical power supply logic for the integral lighting of the standby horizon indicator in the cockpit; accomplishing repetitive operational tests of the integral lighting logic system, and corrective action if necessary. This proposed AD is prompted by a report of temporary loss of six cathode ray tube flight displays and the integral lighting of the standby horizon indicator in the cockpit during takeoff, due to failure of the normal electrical power circuit. We are proposing this AD to prevent loss of that integral lighting due to such failure, which could result in inability of the pilot to read the backup attitude information during takeoff, and possible deviation from the intended flight path. DATES: We must receive comments on this proposed AD by May 4, 2005. ADDRESSES: Use one of the following addresses to submit comments on this proposed AD. • DOT Docket Web site: Go to https://dms.dot.gov and follow the instructions for sending your comments electronically. • Government-wide rulemaking Web site: Go to https://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. • By fax: (202) 493–2251. • Hand Delivery: Room PL–401 on the plaza level of the Nassif Building, 400 Seventh Street SW., Washington, DC, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. PO 00000 Frm 00015 Fmt 4702 Sfmt 4702 16981 For service information identified in this proposed AD, contact Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France. You can examine the contents of this AD docket on the Internet at https:// 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–2005– 20796; the directorate identifier for this docket is 2004–NM–160–AD. FOR FURTHER INFORMATION CONTACT: Tim Backman, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington 98055–4056; telephone (425) 227–2797; fax (425) 227–1149. SUPPLEMENTARY INFORMATION: Comments Invited We invite you to submit any relevant written data, views, or arguments regarding this proposed AD. Send your comments to an address listed under ADDRESSES. Include ‘‘Docket No. FAA– 2005–20796; Directorate Identifier 2004–NM–160–AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of the proposed AD. We will consider all comments submitted by the closing date and may amend the proposed AD in light of those comments. We will post all comments we receive, without change, to https:// dms.dot.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact with FAA personnel concerning this proposed AD. Using the search function of our docket website, anyone can find and read the comments in any of our dockets, including the name of the individual who sent the comment (or signed the comment on behalf of an association, business, labor union, etc.). You can review the DOT’s complete Privacy Act Statement in the Federal Register published on April 11, 2000 (65 FR 19477–78), or you can visit https:// dms.dot.gov. Examining the Docket You can examine the AD docket on the Internet at https://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 E:\FR\FM\04APP1.SGM 04APP1 16982 Federal Register / Vol. 70, No. 63 / Monday, April 4, 2005 / Proposed Rules level of the Nassif Building at the DOT street address stated in the ADDRESSES section. Comments will be available in the AD docket shortly after the DMS receives them. Discussion ´ ´ The Direction Generale de l’Aviation Civile (DGAC), which is the airworthiness authority for France, notified us that an unsafe condition may exist on all Airbus Model A300 B2 and A300 B4 series airplanes; Model A300 B4–600, B4–600R and F4–600R series airplanes, and Model A300 C4–605R Variant F airplanes (collectively called A300–600); and Model A310 series airplanes. The DGAC advises that, during takeoff on a Model A300 B2 series airplane, an operator reported the temporary loss of six cathode ray tube (CRT) flight displays and the integral lighting of the standby horizon indicator in the cockpit due to failure of the normal electrical power circuit. The temporary loss of the CRTs is still under investigation. Power for the integral lighting of the standby horizon indicator is supplied through the normal electrical power circuit. In the event of failure of the normal electrical power circuit, modifying the logic for the integral lighting of the standby horizon will allow automatic switching from the normal to the essential electrical power circuit. Loss of the integral lighting due to such failure could result in loss of the backup source of attitude data, consequent inability of the pilot to access attitude information during takeoff, and possible deviation from the intended flight path. The integral lighting logic system on Model A300 B4 series airplanes; Model A300 B4–600, B4–600R and F4–600R series airplanes, and Model A300 C4– 605R Variant F airplanes; and Model A310 series airplanes is identical to the integral lighting logic system on the affected Model A300 B2 series airplane. Therefore, those airplanes may be subject to the same unsafe condition identified on Model A300 B2 series airplanes. Relevant Service Information We have reviewed the following Airbus service bulletins: REFERENCED SERVICE BULLETINS For model— Service bulletin/date— A300 B2 and A300 B4 series airplanes ............................................................................ A300–31–0077, dated March 2, 2004 . A300–33–0126, dated April 5, 2004. A300–31–6105, Revision 02, dated May 27, 2003. A300 B4–600, B4–600R and F4–600R series airplanes; A300 C4–605R Variant F airplanes. A310 series airplanes ........................................................................................................ Service Bulletins A300–31–0077, A300–31–6105, and A310–31–2120 describe procedures for modifying the electrical power supply for the standby horizon indicator. Service Bulletins A300–33–0126, A300–33–6049, and A310–33–2047 describe procedures for accomplishing repetitive operational tests (inspections) of the integral lighting logic system. The service bulletins also recommend sending an inspection report to Airbus. Accomplishing the actions specified in the service information is intended to adequately address the unsafe condition. The DGAC mandated the service information and issued French airworthiness directive F–2004–098, dated July 7, 2004, to ensure the continued airworthiness of these airplanes in France. FAA’s Determination and Requirements of the Proposed AD These airplane models are manufactured in France and are 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, the DGAC has kept us informed of the situation described above. We have examined the DGACs findings, evaluated all pertinent VerDate jul<14>2003 15:01 Apr 01, 2005 Jkt 205001 A300–33–6049, Revision 01, dated May 28, 2004. A310–31–2120, Revision 01, dated May 27, 2003. A310–33–2047, dated April 5, 2004. information, and determined that we need to issue an AD for products of this type design that are certificated for operation in the United States. Therefore, we are proposing this AD, which would require accomplishing the actions specified in the service information described previously, except as discussed under ‘‘Differences Between the Proposed AD and Service Information.’’ Differences Between the Proposed AD and Service Information Service Bulletins A300–33–0126, A300–33–6049, and A310–33–2047 recommend sending an inspection report to Airbus, but this proposed AD does not contain that requirement. Service Bulletins A300–33–0126, A300–33–6049, and A310–33–2047 do not specify repair procedures for failure of the operational test, but this proposed AD would require you to repair those conditions using a method that we or the DGAC (or its delegated agent) approve. In light of the type of repair that would be required to address the unsafe condition, and consistent with existing bilateral airworthiness agreements, we have determined that, for this proposed AD, a repair we or the DGAC approve would be acceptable for compliance with this proposed AD. PO 00000 Frm 00016 Fmt 4702 Sfmt 4702 Costs of Compliance This proposed AD would affect about 189 airplanes of U.S. registry. It would take between approximately 10 and 36 work hours per airplane to accomplish the proposed modification (depending on the number of kits needed), at an average labor rate of $65 per work hour. Required parts would cost approximately between $310 and $4,880 per airplane. Based on these figures, the estimated cost of the proposed modification is between $960 and $7,220 per airplane. It would take about 1 work hour per airplane to accomplish the proposed operational test, at an average labor rate of $65 per work hour. Based on these figures, the estimated cost of the proposed test is $12,285, or $65 per airplane, per test cycle. 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 E:\FR\FM\04APP1.SGM 04APP1 Federal Register / Vol. 70, No. 63 / Monday, April 4, 2005 / Proposed Rules 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 prepared a regulatory evaluation of the estimated costs to comply with this proposed AD. See the ADDRESSES section for a location to examine the regulatory evaluation. Regulatory Findings Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 14 CFR part 39 as follows: We have determined that this proposed AD will not have federalism implications under Executive Order 13132. This proposed 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 the proposed regulation: 1. Is not a ‘‘significant regulatory action’’ under Executive Order 12866; 2. Is not a ‘‘significant rule’’ under the 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. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Safety. The Proposed Amendment PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: 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): Airbus: Docket No. FAA–2005–20796; Directorate Identifier 2004–NM–160–AD. Comments Due Date (a) The Federal Aviation Administration must receive comments on this AD action by May 4, 2005. Affected ADs (b) None. 16983 Applicability (c) This AD applies to all Airbus Model A300 B2 and A300 B4 series airplanes; Model A300 B4–600, A300 B4–600R, and A300 F4–600R series airplanes, and Model A300 C4–605R Variant F airplanes (collectively called A300–600); and Model A310 series airplanes; certificated in any category. Unsafe Condition (d) This AD was prompted by a report of temporary loss of six cathode ray tube flight displays and the integral lighting of the standby horizon indicator in the cockpit during takeoff, due to failure of the normal electrical power circuit. We are issuing this AD to prevent loss of that integral lighting due to such failure, which could result in inability of the pilot to read the backup attitude information during takeoff, and possible deviation from the intended flight path. 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. Required Service Information (f) Unless otherwise specified in this AD, the term ‘‘service bulletin,’’ as used in this AD, means the Accomplishment Instructions of the applicable service bulletin identified in Table 1 of this AD. Service Bulletins A300–33–0126, A300–33–6049, and A310– 33–2047 specify to submit certain information to the manufacturer, but this AD does not include that requirement. TABLE 1.—SERVICE BULLETINS For Airbus models— Use Airbus service bulletin(s)— Revision— Dated— And, for actions done before the effective date of this AD, credit is given for prior accomplishing of— A300 B2 and A300 B4 series ...... A300–31–0077 (Airbus Modification 12513). A300–33–0126 ............................ A300–31–6105 (Airbus Modifications 12513 and 12730). Original ............. March 2, 2004 .... N/A. Original ............. 02 ..................... April 5, 2004 ....... May 27, 2003 ..... N/A. None. A300–33–6049 ............................ A310–31–2120 (Airbus Modification 12513). A310–33–2047 ............................ 01 ..................... 01 ..................... May 28, 2004 ..... May 27, 2003 ..... Original ............. April 5, 2004 ....... Original, dated April 5, 2004. Original, dated November 19, 2002. N/A. A300 B4–600; A300 B4–600R and F4–600R series; and A300 C4–605R Variant F airplanes. A310 series .................................. Modification (g) For airplanes on which Airbus Modifications 12513 and 12730 have not been accomplished: Within 12 months after the effective date of this AD, modify the electrical power supply logic of the integral lighting for the standby horizon indicator in the cockpit in accordance with the service bulletin. Repetitive Operational Tests (h) For all airplanes: Within 600 flight hours after accomplishing the modification required by paragraph (g) of this AD, or within 600 flight hours after the effective date of this AD, whichever is later, VerDate jul<14>2003 15:01 Apr 01, 2005 Jkt 205001 accomplish the operational test of the integral lighting logic system in accordance with the service bulletin. Repeat the test thereafter at intervals not to exceed 600 flight hours. Corrective Action (i) If any operational test required by paragraph (h) of this AD fails: Before further flight, accomplish any applicable repair per a method approved by either the Manager, International Branch, ANM–116, FAA, Transport Airplane Directorate; or the ´ ´ Direction Generale de l’Aviation Civile (or its delegated agent). PO 00000 Frm 00017 Fmt 4702 Sfmt 4702 Alternative Methods of Compliance (AMOCs) (j) The Manager, International Branch, ANM–116, has the authority to approve AMOCs for this AD, if requested in accordance with the procedures found in 14 CFR 39.19. Related Information (k) French airworthiness directive F–2004– 098, dated July 7, 2004, also addresses the subject of this AD. E:\FR\FM\04APP1.SGM 04APP1 16984 Federal Register / Vol. 70, No. 63 / Monday, April 4, 2005 / Proposed Rules Issued in Renton, Washington, on March 23, 2005. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 05–6578 Filed 4–1–05; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2005–20798; Directorate Identifier 2004–NM–257–AD] RIN 2120–AA64 Airworthiness Directives; Learjet Model 23, 24, 25, 35, and 36 Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Notice of proposed rulemaking (NPRM). AGENCY: SUMMARY: The FAA proposes to supersede an existing airworthiness directive (AD) that applies to certain Learjet Model 23, 24, 25, 35, and 36 airplanes. The existing AD currently requires repetitive inspections to detect deterioration of both flappers of the tip tank in each wing of the airplane, and various follow-on actions. The existing AD also requires replacing the flappers with new flappers, and repetitively performing certain other follow-on actions. This proposed AD would require an inspection of the flappers and flapper assemblies of the tip tank in each wing or a review of the airplane maintenance records to determine the part numbers, and replacement of certain flappers or flapper assemblies if necessary, which would end the existing repetitive inspections. This proposed AD is prompted by the results of numerous continual inspections, and the approval of a new, improved flapper and flapper assembly. We are proposing this AD to prevent significant reduction in the lateral control of the airplane due to imbalance of the fuel loads in the wings of the airplane. DATES: We must receive comments on this proposed AD by May 19, 2005. ADDRESSES: Use one of the following addresses to submit comments on this proposed AD. • DOT Docket Web site: Go to https://dms.dot.gov and follow the instructions for sending your comments electronically. • Government-wide rulemaking Web site: Go to https://www.regulations.gov and follow the instructions for sending your comments electronically. VerDate jul<14>2003 15:01 Apr 01, 2005 Jkt 205001 • 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, DC, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For service information identified in this proposed AD, contact Learjet, Inc., One Learjet Way, Wichita, Kansas 67209–2942. You can examine the contents of this AD docket on the Internet at https:// 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–2005– 20798; the directorate identifier for this docket is 2004–NM–257–AD. FOR FURTHER INFORMATION CONTACT: Jeffrey Janusz, Aerospace Engineer, Systems and Propulsion Branch, ACE– 116W, FAA, Wichita Aircraft Certification Office, 1801 Airport Road, Room 100, Mid-Continent Airport, Wichita, Kansas 67209; telephone (316) 946–4148; fax (316) 946–4107. SUPPLEMENTARY INFORMATION: Comments Invited We invite you to submit any relevant written data, views, or arguments regarding this proposed AD. Send your comments to an address listed under ADDRESSES. Include ‘‘Docket No. FAA– 2005–20798; Directorate Identifier 2004–NM–257–AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of the proposed AD. We will consider all comments received by the closing date and may amend the proposed AD in light of those comments. We will post all comments we receive, without change, to https:// dms.dot.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact with FAA personnel concerning this proposed AD. Using the search function of our docket Web site, anyone can find and read the comments in any of our dockets, including the name of the individual who sent the comment (or signed the comment on behalf of an association, business, labor union, etc.). You can review the DOT’s complete Privacy Act Statement in the Federal Register published on April 11, 2000 (65 FR 19477–78), or you can visit https:// dms.dot.gov. PO 00000 Frm 00018 Fmt 4702 Sfmt 4702 Examining the Docket You can examine the AD docket on the Internet at https://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 DOT street address stated in the ADDRESSES section. Comments will be available in the AD docket shortly after the DMS receives them. Discussion On November 27, 1995, we issued AD 95–25–03, amendment 39–9447 (60 FR 63617, December 12, 1995), for certain Learjet Model 23, 24, 25, 35, and 36 airplanes. That AD requires repetitive inspections to detect deterioration of both flappers of the tip tank in each wing of the airplane, and various follow-on actions. That AD also requires replacing the flappers with new flappers, and repetitively performing certain other follow-on actions. That AD was prompted by reports of imbalance of the fuel loads in the wings of the airplane due to failed or cracked flappers. We issued that AD to prevent significant reduction in the lateral control of the airplane due to imbalance of the fuel loads in the wings of the airplane. Actions Since Existing AD Was Issued Since we issued AD 95–25–03, we have reviewed Learjet Service Bulletin 23/24/25–28–7, Revision 2, dated May 9, 2001 (for Model 23, 24, and 25 airplanes); and Learjet Service Bulletin 35/36–28–14, Revision 2, dated May 9, 2001 (for Model 35 and 36 airplanes). The service bulletins describe procedures for replacing flappers with new flappers or replacing the flapper assemblies with new or modified and reidentified assemblies, which eliminates the need for the repetitive inspections required by AD 95–25–03. Accomplishing the actions specified in the service information is intended to adequately address the unsafe condition. FAA’s Determination and Requirements of the Proposed AD The unsafe condition described previously is likely to exist or develop on other airplanes of the same type design that may be registered in the U.S. at some time in the future. We can better ensure long-term continued operational safety by design changes to remove the source of the problem, rather than by repetitive inspections. Long-term inspections, as E:\FR\FM\04APP1.SGM 04APP1

Agencies

[Federal Register Volume 70, Number 63 (Monday, April 4, 2005)]
[Proposed Rules]
[Pages 16981-16984]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 05-6578]

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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2005-20796; Directorate Identifier 2004-NM-160-AD]
RIN 2120-AA64

Airworthiness Directives; Airbus Model A300 B2 and A300 B4 Series
Airplanes; Model A300 B4-600, B4-600R and F4-600R Series Airplanes, and
Model A300 C4-605R Variant F Airplanes (Collectively Called A300-600);
and Model A310 Series Airplanes

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

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD)
for all the Airbus models identified above. This proposed AD would
require modifying the electrical power supply logic for the integral
lighting of the standby horizon indicator in the cockpit; accomplishing
repetitive operational tests of the integral lighting logic system, and
corrective action if necessary. This proposed AD is prompted by a
report of temporary loss of six cathode ray tube flight displays and
the integral lighting of the standby horizon indicator in the cockpit
during takeoff, due to failure of the normal electrical power circuit.
We are proposing this AD to prevent loss of that integral lighting due
to such failure, which could result in inability of the pilot to read
the backup attitude information during takeoff, and possible deviation
from the intended flight path.

DATES: We must receive comments on this proposed AD by May 4, 2005.

ADDRESSES: Use one of the following addresses to submit comments on
this proposed AD.
DOT Docket Web site: Go to https://dms.dot.gov and follow
the instructions for sending your comments electronically.
Government-wide rulemaking Web site: Go to https://
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.
By fax: (202) 493-2251.
Hand Delivery: Room PL-401 on the plaza level of the
Nassif Building, 400 Seventh Street SW., Washington, DC, between 9 a.m.
and 5 p.m., Monday through Friday, except Federal holidays.
For service information identified in this proposed AD, contact
Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France.
You can examine the contents of this AD docket on the Internet at
https://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-2005-20796; the directorate identifier for this
docket is 2004-NM-160-AD.

FOR FURTHER INFORMATION CONTACT: Tim Backman, Aerospace Engineer,
International Branch, ANM-116, Transport Airplane Directorate, 1601
Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425) 227-
2797; fax (425) 227-1149.

SUPPLEMENTARY INFORMATION:

Comments Invited

We invite you to submit any relevant written data, views, or
arguments regarding this proposed AD. Send your comments to an address
listed under ADDRESSES. Include ``Docket No. FAA-2005-20796;
Directorate Identifier 2004-NM-160-AD'' at the beginning of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of the proposed AD. We will
consider all comments submitted by the closing date and may amend the
proposed AD in light of those comments.
We will post all comments we receive, without change, to https://
dms.dot.gov, including any personal information you provide. We will
also post a report summarizing each substantive verbal contact with FAA
personnel concerning this proposed AD. Using the search function of our
docket website, anyone can find and read the comments in any of our
dockets, including the name of the individual who sent the comment (or
signed the comment on behalf of an association, business, labor union,
etc.). You can review the DOT's complete Privacy Act Statement in the
Federal Register published on April 11, 2000 (65 FR 19477-78), or you
can visit https://dms.dot.gov.

Examining the Docket

You can examine the AD docket on the Internet at https://
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

[[Page 16982]]

level of the Nassif Building at the DOT street address stated in the
ADDRESSES section. Comments will be available in the AD docket shortly
after the DMS receives them.

Discussion

The Direction Generale de l'Aviation Civile (DGAC), which is the
airworthiness authority for France, notified us that an unsafe
condition may exist on all Airbus Model A300 B2 and A300 B4 series
airplanes; Model A300 B4-600, B4-600R and F4-600R series airplanes, and
Model A300 C4-605R Variant F airplanes (collectively called A300-600);
and Model A310 series airplanes. The DGAC advises that, during takeoff
on a Model A300 B2 series airplane, an operator reported the temporary
loss of six cathode ray tube (CRT) flight displays and the integral
lighting of the standby horizon indicator in the cockpit due to failure
of the normal electrical power circuit. The temporary loss of the CRTs
is still under investigation. Power for the integral lighting of the
standby horizon indicator is supplied through the normal electrical
power circuit. In the event of failure of the normal electrical power
circuit, modifying the logic for the integral lighting of the standby
horizon will allow automatic switching from the normal to the essential
electrical power circuit. Loss of the integral lighting due to such
failure could result in loss of the backup source of attitude data,
consequent inability of the pilot to access attitude information during
takeoff, and possible deviation from the intended flight path.
The integral lighting logic system on Model A300 B4 series
airplanes; Model A300 B4-600, B4-600R and F4-600R series airplanes, and
Model A300 C4-605R Variant F airplanes; and Model A310 series airplanes
is identical to the integral lighting logic system on the affected
Model A300 B2 series airplane. Therefore, those airplanes may be
subject to the same unsafe condition identified on Model A300 B2 series
airplanes.

Relevant Service Information

We have reviewed the following Airbus service bulletins:

Referenced Service Bulletins
----------------------------------------------------------------------------------------------------------------
For model-- Service bulletin/date--
----------------------------------------------------------------------------------------------------------------
A300 B2 and A300 B4 series airplanes A300-31-0077, dated March 2, 2004 .
A300-33-0126, dated April 5, 2004.
A300 B4-600, B4-600R and F4-600R A300-31-6105, Revision 02, dated May 27, 2003.
series airplanes; A300 C4-605R
Variant F airplanes.
A300-33-6049, Revision 01, dated May 28, 2004.
A310 series airplanes............... A310-31-2120, Revision 01, dated May 27, 2003.
A310-33-2047, dated April 5, 2004.
----------------------------------------------------------------------------------------------------------------

Service Bulletins A300-31-0077, A300-31-6105, and A310-31-2120
describe procedures for modifying the electrical power supply for the
standby horizon indicator.
Service Bulletins A300-33-0126, A300-33-6049, and A310-33-2047
describe procedures for accomplishing repetitive operational tests
(inspections) of the integral lighting logic system. The service
bulletins also recommend sending an inspection report to Airbus.
Accomplishing the actions specified in the service information is
intended to adequately address the unsafe condition. The DGAC mandated
the service information and issued French airworthiness directive F-
2004-098, dated July 7, 2004, to ensure the continued airworthiness of
these airplanes in France.

FAA's Determination and Requirements of the Proposed AD

These airplane models are manufactured in France and are 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, the DGAC has kept us informed of the
situation described above. We have examined the DGACs findings,
evaluated all pertinent information, and determined that we need to
issue an AD for products of this type design that are certificated for
operation in the United States.
Therefore, we are proposing this AD, which would require
accomplishing the actions specified in the service information
described previously, except as discussed under ``Differences Between
the Proposed AD and Service Information.''

Differences Between the Proposed AD and Service Information

Service Bulletins A300-33-0126, A300-33-6049, and A310-33-2047
recommend sending an inspection report to Airbus, but this proposed AD
does not contain that requirement.
Service Bulletins A300-33-0126, A300-33-6049, and A310-33-2047 do
not specify repair procedures for failure of the operational test, but
this proposed AD would require you to repair those conditions using a
method that we or the DGAC (or its delegated agent) approve. In light
of the type of repair that would be required to address the unsafe
condition, and consistent with existing bilateral airworthiness
agreements, we have determined that, for this proposed AD, a repair we
or the DGAC approve would be acceptable for compliance with this
proposed AD.

Costs of Compliance

This proposed AD would affect about 189 airplanes of U.S. registry.
It would take between approximately 10 and 36 work hours per
airplane to accomplish the proposed modification (depending on the
number of kits needed), at an average labor rate of $65 per work hour.
Required parts would cost approximately between $310 and $4,880 per
airplane. Based on these figures, the estimated cost of the proposed
modification is between $960 and $7,220 per airplane.
It would take about 1 work hour per airplane to accomplish the
proposed operational test, at an average labor rate of $65 per work
hour. Based on these figures, the estimated cost of the proposed test
is $12,285, or $65 per airplane, per test cycle.

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

[[Page 16983]]

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 proposed AD will not have federalism
implications under Executive Order 13132. This proposed 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 the proposed
regulation:
1. Is not a ``significant regulatory action'' under Executive Order
12866;
2. Is not a ``significant rule'' under the 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 proposed 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, Safety.

The Proposed Amendment

Accordingly, under the authority delegated to me by the
Administrator, the FAA proposes to amend 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

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]

2. The FAA amends Sec. 39.13 by adding the following new
airworthiness directive (AD):

Airbus: Docket No. FAA-2005-20796; Directorate Identifier 2004-NM-
160-AD.

Comments Due Date

(a) The Federal Aviation Administration must receive comments on
this AD action by May 4, 2005.

Affected ADs

(b) None.

Applicability

(c) This AD applies to all Airbus Model A300 B2 and A300 B4
series airplanes; Model A300 B4-600, A300 B4-600R, and A300 F4-600R
series airplanes, and Model A300 C4-605R Variant F airplanes
(collectively called A300-600); and Model A310 series airplanes;
certificated in any category.

Unsafe Condition

(d) This AD was prompted by a report of temporary loss of six
cathode ray tube flight displays and the integral lighting of the
standby horizon indicator in the cockpit during takeoff, due to
failure of the normal electrical power circuit. We are issuing this
AD to prevent loss of that integral lighting due to such failure,
which could result in inability of the pilot to read the backup
attitude information during takeoff, and possible deviation from the
intended flight path.

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.

Required Service Information

(f) Unless otherwise specified in this AD, the term ``service
bulletin,'' as used in this AD, means the Accomplishment
Instructions of the applicable service bulletin identified in Table
1 of this AD. Service Bulletins A300-33-0126, A300-33-6049, and
A310-33-2047 specify to submit certain information to the
manufacturer, but this AD does not include that requirement.

Table 1.--Service Bulletins
----------------------------------------------------------------------------------------------------------------
And, for actions
done before the
Use Airbus service effective date of
For Airbus models-- bulletin(s)-- Revision-- Dated-- this AD, credit is
given for prior
accomplishing of--
----------------------------------------------------------------------------------------------------------------
A300 B2 and A300 B4 series...... A300-31-0077 Original.......... March 2, 2004..... N/A.
(Airbus
Modification
12513).
A300-33-0126...... Original.......... April 5, 2004..... N/A.
A300 B4-600; A300 B4-600R and F4- A300-31-6105 02................ May 27, 2003...... None.
600R series; and A300 C4-605R (Airbus
Variant F airplanes. Modifications
12513 and 12730).
A300-33-6049...... 01................ May 28, 2004...... Original, dated
April 5, 2004.
A310 series..................... A310-31-2120 01................ May 27, 2003...... Original, dated
(Airbus November 19,
Modification 2002.
12513).
A310-33-2047...... Original.......... April 5, 2004..... N/A.
----------------------------------------------------------------------------------------------------------------

Modification

(g) For airplanes on which Airbus Modifications 12513 and 12730
have not been accomplished: Within 12 months after the effective
date of this AD, modify the electrical power supply logic of the
integral lighting for the standby horizon indicator in the cockpit
in accordance with the service bulletin.

Repetitive Operational Tests

(h) For all airplanes: Within 600 flight hours after
accomplishing the modification required by paragraph (g) of this AD,
or within 600 flight hours after the effective date of this AD,
whichever is later, accomplish the operational test of the integral
lighting logic system in accordance with the service bulletin.
Repeat the test thereafter at intervals not to exceed 600 flight
hours.

Corrective Action

(i) If any operational test required by paragraph (h) of this AD
fails: Before further flight, accomplish any applicable repair per a
method approved by either the Manager, International Branch, ANM-
116, FAA, Transport Airplane Directorate; or the Direction
G[eacute]n[eacute]rale de l'Aviation Civile (or its delegated
agent).

Alternative Methods of Compliance (AMOCs)

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

Related Information

(k) French airworthiness directive F-2004-098, dated July 7,
2004, also addresses the subject of this AD.

[[Page 16984]]

Issued in Renton, Washington, on March 23, 2005.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 05-6578 Filed 4-1-05; 8:45 am]
BILLING CODE 4910-13-P

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