Airworthiness Directives; Airbus Model A300 B2 and B4 Series Airplanes; Model A300 B4-600, B4-600R, and F4-600R Series Airplanes, and Model C4-605R Variant F Airplanes (Collectively Called A300-600 Series Airplanes); and Model A310 Series Airplanes; Equipped With General Electric CF6-80A3 or CF6-80C2 Engines, 45595-45598 [05-15594]

Download as PDF Federal Register / Vol. 70, No. 151 / Monday, August 8, 2005 / Proposed Rules Related Information (m) French airworthiness directive F– 2003–457 R1, dated December 22, 2004, also addresses the subject of this AD. Issued in Renton, Washington, on August 2, 2005. Kevin Mullin, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 05–15593 Filed 8–5–05; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2005–22036; Directorate Identifier 2005–NM–009–AD] RIN 2120–AA64 Airworthiness Directives; Airbus Model A300 B2 and B4 Series Airplanes; Model A300 B4–600, B4–600R, and F4– 600R Series Airplanes, and Model C4– 605R Variant F Airplanes (Collectively Called A300–600 Series Airplanes); and Model A310 Series Airplanes; Equipped With General Electric CF6– 80A3 or CF6–80C2 Engines 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 certain Airbus airplane models, as specified above. This proposed AD would require installing electropneumatic locking bar devices (TRAS lock systems) in the engine nacelles, installing a dedicated and shielded electrical circuit that is segregated from the existing thrust reverser control system, and performing related investigative/corrective actions if necessary. This proposed AD is prompted by the manufacturer’s reassessment of the thrust reverser systems in the Airbus airplane models specified above, which showed that the thrust reverser could inadvertently deploy in flight under certain conditions. We are proposing this AD to prevent inadvertent deployment of thrust reversers in flight, which could result in reduced controllability of the airplane. We must receive comments on this proposed AD by September 7, 2005. ADDRESSES: Use one of the following addresses to submit comments on this proposed AD. DATES: VerDate jul<14>2003 20:26 Aug 05, 2005 Jkt 205001 • DOT Docket Web Site: Go to http:/ /dms.dot.gov and follow the instructions for sending your comments electronically. • Government-Wide Rulemaking Web Site: Go to http://www.regulations.gov and follow the instructions for sending your comments electronically. • Mail: Docket Management Facility, U.S. Department of Transportation, 400 Seventh Street SW., Nassif Building, room PL–401, Washington, DC 20590. • 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 http:// dms.dot.gov, or in person at the Docket Management Facility, U.S. Department of Transportation, 400 Seventh Street SW., room PL–401, on the plaza level of the Nassif Building, Washington, DC. This docket number is FAA–2005– 22036; the directorate identifier for this docket is 2005–NM–009–AD. FOR FURTHER INFORMATION CONTACT: Tim Backman, Aerospace Engineer, International Branch, ANM–116, FAA, 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– 2005–22036; Directorate Identifier 2005–NM–009–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 http:// 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 PO 00000 Frm 00025 Fmt 4702 Sfmt 4702 45595 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 http:// dms.dot.gov. Examining the Docket 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 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 certain Airbus Model A300 B2 and B4 series airplanes; Model A300 B4–600, B4–600R, and F4–600R series airplanes, and Model C4–605R Variant F airplanes (collectively called A300–600 series airplanes); and Model A310 series airplanes; equipped with General Electric CF6–80A3 or CF6–80C2 engines. The DGAC advises that the manufacturer has reassessed the thrust reverser systems of those airplanes and has determined that the thrust reverser could inadvertently deploy in flight. The manufacturer has developed a new, improved design of the thrust reversers, which provides an independent system to prevent deployment of the thrust reversers in flight. Inadvertent deployment of the thrust reversers in flight could result in reduced controllability of the airplane. Relevant Service Information Airbus has issued the following service bulletins (SBs), which describe procedures for installing electropneumatic locking bar devices (TRAS lock system) and a dedicated and shielded electrical circuit that is segregated from the existing thrust reverser control system. The new electrical circuit commands the locking bar devices (TRAS locks), which would be installed in the engine nacelles. Implementation of the following SBs is intended to provide an independent system to prevent inadvertent deployment of thrust reversers during flight. E:\FR\FM\08AUP1.SGM 08AUP1 45596 Federal Register / Vol. 70, No. 151 / Monday, August 8, 2005 / Proposed Rules Airbus SB A310–78–2023, dated October 7, 2003 (for Model A310 series airplanes equipped with General Electric CF6–80C2 engines and not equipped with Full Authority Digital Engine Control (FADEC)), specifies previous or concurrent accomplishment of Airbus SB A310–78–2022, and describes modifying/retrofitting the electrical harness routine from each lock to the pylon interfaces of the engine/ nacelle, and the existing monitoring wire; and activating the electrical system of the aircraft. Airbus SB A310–78–2022, dated January 7, 2003 (for Airbus Model 310 series airplanes equipped with General Electric CF6–80C2 engines and not equipped with FADEC), describes modifying/retrofitting a new electrical circuit between the forward cargo compartment and the wing/pylon interfaces, a new electrical circuit in the engine pylons, and a new electrical circuit in the avionics compartment and the forward cargo compartment; and connecting the new electrical circuit. The SB indicates that Parts 1 and 2 of the SB can be accomplished independently and in any sequence, but Part 3 must be accomplished after the first two parts. Full function can be assured once Airbus SB A310–78–2023 has been accomplished. Airbus SB A310–78–2025, dated July 23, 2004 (for Model A310 series airplanes equipped with General Electric CF6–80A3 engines), specifies previous or concurrent accomplishment of Airbus SB A310–78–2024, and references Goodrich Service Bulletin 71–065 as an additional source of service information. (After the issuance of Airbus SB A310–78–2025, dated July 23, 2004, the Goodrich Service Bulletin was reissued as Rohr Service Bulletin CF6–80A3, dated April 28, 2005.) Airbus SB A310–78–2025 also describes the following procedures: • Modifying/retrofitting the existing monitoring wire and activating the electrical system of the aircraft. • Modifying/retrofitting the electrical harness routine from each lock to the pylon interfaces of the engine/nacelle. • Installing the support bracket for the electrical harness of the engine/ nacelle. • Modifying the stowed position of the hold-open rod bracket of the engine/ nacelle. • Replacing the lower end actuator gearbox with a gearbox that integrates the locking bar. • Replacing the pneumatic tubing situated upstream from the pressure regulated shut-off valve (PRSOV) with a new PRSOV having a third line of defense (TLOD) tubing connector. VerDate jul<14>2003 20:26 Aug 05, 2005 Jkt 205001 • Modifying the hold-open rod bracket of the fan cowl. • Accomplishing the test job set-up, extended operational test of the circuit breaker monitoring system, and the test for the stow and deploy switches included in the thrust reverser functional and indicating/warning sensors test. Airbus Service Bulletin A310–78– 2024, dated October 15, 2003 (for Model A310 series airplanes equipped with CF6–80A3 engines), describes procedures for the airplane and the engine/nacelle that include the following: • Modifying the hold-open rod bracket of the fan cowl. • Installing the actuation system lock. • Modifying the wiring in a certain circuit breaker panel. Airbus Service Bulletin A300–78– 6024, dated October 7, 2003 (for Model A300–600 series airplanes equipped with General Electric CF6–80C2 engines and equipped with FADEC), specifies previous or concurrent accomplishment of Airbus SB A300–78–6021, Revision 1, dated October 7, 2003, and describes procedures for the following: • Installing an actuation system lock. • Modifying the wiring in a certain circuit breaker panel. • Accomplishing the test job set-up, extended operational test of the circuit breaker monitoring system, and the test for the stow and deploy switches included in the thrust reverser functional and indicating/warning sensors test. Airbus SB A300–78–6021, Revision 1, dated October 7, 2003 (for Model A300– 600 series airplanes equipped with General Electric CF6–80C2 engines and equipped with FADEC), describes procedures for the following: • Part 1—Modifying/retrofitting a new electrical circuit between the forward cargo compartment and the wing/pylon interfaces. • Part 2—Modifying/retrofitting a new electrical circuit in the engine pylons. • Part 3—Modifying/retrofitting a new electrical circuit in the avionics compartment; modifying/retrofitting a new electrical circuit between the avionics compartment and the forward cargo compartment; and modifying/ retrofitting a new electrical circuit. Airbus SB A300–78–6025, dated October 7, 2003 (for Model A300–600 series airplanes equipped with General Electric CF6–80C2 engines not equipped with FADEC), specifies previous or concurrent accomplishment of Airbus SB A300–78–6022, and describes procedures for the following: • Installing an actuation system lock. PO 00000 Frm 00026 Fmt 4702 Sfmt 4702 • Modifying the wiring in a certain circuit breaker panel. • Accomplishing the test job set-up, extended operational test of the circuit breaker monitoring system, and the test for the stow and deploy switches included in the thrust reverser functional and indicating/warning sensors test. Airbus SB A300–78–6022, Revision 1, dated January 7, 2003 (for Model A300– 600 airplanes equipped with General Electric CF6 80C2 engines and not equipped with FADEC), describes procedures for the following: • Part 1—Modifying/retrofitting a new electrical circuit between the forward cargo-compartment and the wing/pylon interfaces. • Part 2—Modifying/retrofitting a new electrical circuit in the engine pylons. • Part 3—Modifying/retrofitting a new electrical circuit in the avionics compartment; modifying/retrofitting a new electrical circuit between the avionics compartment and the forward cargo compartment; and modifying/ retrofitting a new electrical circuit. Accomplishing the actions specified in the service information is intended to adequately address the unsafe condition. The DGAC mandated the above service bulletins and issued French airworthiness directive F–2004– 165, dated October 13, 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 the FAA informed of the situation described above. We have examined the DGAC’s 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. Costs of Compliance This AD affects about 101 airplanes of U.S. registry. (The total number of airplanes in the following table totals more than 101 airplanes because most of the airplanes would be required to accomplish two of the specified service E:\FR\FM\08AUP1.SGM 08AUP1 45597 Federal Register / Vol. 70, No. 151 / Monday, August 8, 2005 / Proposed Rules bulletins.) The following table provides the estimated costs for U.S. operators to comply with this proposed AD at an average labor rate per hour of $65. ESTIMATED COSTS FOR MODIFICATIONS (LISTED BY APPLICABLE SERVICE BULLETIN) Airbus service bulletin (SB) Work hours A300–78–6021, Revision 1 ...................................................................... A300–78–6022, Revision 1 ...................................................................... A300–78–6024 ......................................................................................... A300–78–6025 ......................................................................................... A310–78–2024 ......................................................................................... A310–78–2025 ......................................................................................... 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 proposed AD would not have federalism implications under Executive Order 13132. This proposed AD would not 257 289 4 4 4 4 Cost per airplane Parts $15,185 18,198 150 150 18,009 150 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. Number of airplanes $31,890 36,983 410 410 35,884 410 36 34 36 34 27 31 General Electric engine model A300 B2 and B4; A300 B4–600, B4– 600R, and F4–600R, C4–605R Variant F airplanes (collectively called A300– 600 series airplanes). A300 B2 and B4; A300 B4–600, B4– 600R, and F4–600R, C4–605R Variant F airplanes (collectively called A300– 600). A300 B2 and B4; A300 B4–600, B4– 600R, and F4–600R, C4–605R Variant F airplanes (collectively called A300– 600). A300 B2 and B4; A300 B4–600, B4– 600R, and F4–600R, C4–605R Variant F airplanes (collectively called A300– 600). A310 ......................................................... A310 ......................................................... A310 ......................................................... VerDate jul<14>2003 20:26 Aug 05, 2005 Jkt 205001 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. § 39.13 [Amended] 2. The FAA amends § 39.13 by adding the following new airworthiness directive (AD): Airbus: Docket No. FAA–2005–22036; Directorate Identifier 2005–NM–009–AD. Comments Due Date (a) The Federal Aviation Administration must receive comments on this AD action by September 7, 2005. Affected ADs (b) None. Applicability: (c) This AD applies to Airbus series airplanes, certificated in any category, as identified in the service bulletins listed in Table 1 of this AD. Airbus service bulletin Date CF6–80C2 A300–78–6024 ......................................... October 7, 2003. CF6–80C2 A300–78–6021, Revision 1 ...................... October 7, 2003. CF6–80C2 A300–78–6025 ......................................... October 7, 2003. CF6–80C2 A300–78–6022, Revision 1 ...................... January 7, 2003. CF6–80C2 CF6–80C2 CF6–80A3 A310–78–2023 ......................................... A310–78–2022 ......................................... A310–78–2025 ......................................... October 7, 2003. January 7, 2003. July 23, 2004. PO 00000 Frm 00027 Fmt 4702 Sfmt 4702 $1,148,040 1,257,422 14,760 13,940 968,868 12,710 The Proposed Amendment TABLE 1.—APPLICABILITY Series airplane Cost per SB E:\FR\FM\08AUP1.SGM 08AUP1 45598 Federal Register / Vol. 70, No. 151 / Monday, August 8, 2005 / Proposed Rules TABLE 1.—APPLICABILITY—Continued General Electric engine model Series airplane Airbus service bulletin A310 ......................................................... CF6–80A3 Unsafe Condition (d) This AD was prompted by the manufacturer’s reassessment of the thrust reverser systems in the Airbus airplane models specified in Table 1 of this AD, which showed that the thrust reverser could deploy in flight under certain conditions. We are issuing this AD to prevent inadvertent deployment of thrust reversers in flight, which could result in reduced controllability 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. Date A310–78–2024 ......................................... Installing TRAS Locks System and Accomplishing Modifications October 15, 2003. this AD, install the electro-pneumatic locking bar devices (TRAS Lock Systems) in the thrust reverser system of the nacelles, in accordance with the Accomplishment Instructions of the applicable service bulletin. (f) For airplanes identified in the service bulletins specified in Table 2 of this AD: Within 36 months after the effective date of TABLE 2.—INSTALLING TRAS LOCK SYSTEMS General Electric engine model Series airplane A300 B2 and B4; A300 B4–600, B4– 600R, and F4–600R, C4–605R Variant F airplanes (collectively called A300– 600 series airplanes). A300 B2 and B4; A300 B4–600, B4600R, and F4–600R, C4–605R Variant F airplanes (collectively called A300– 600). A310 ......................................................... A310 ......................................................... Airbus service bulletin Date CF6–80C2 October 7, 2003. CF6–80C2 A300–78–6025 ......................................... October 7, 2003. CF6–80C2 CF6–80A3 Note 1: Airbus SB A310–78–2025, dated July 23, 2004, references draft Goodrich Service Bulletin 71–065 as an additional source of service information. After the issuance of Airbus A310–78–2025, the Goodrich SB was reissued as Rohr Service Bulletin CF6–80A3, dated April 28, 2005. A300–78–6024 ......................................... A310–78–2023 ......................................... A310–78–2025 ......................................... October 7, 2003. July 23, 2004. (g) For airplanes identified in the service bulletins specified in Table 3 of this AD: Prior to or concurrent with the accomplishment of the applicable service bulletin specified in paragraph (f) of this AD, accomplish all the modifications and actions related to an independent third line of defense on the thrust reversers, in accordance with the Accomplishment Instructions of the applicable service bulletin specified in Table 3 of this AD. TABLE 3.—PRIOR OR CONCURRENT ACCOMPLISHMENT General Electric engine model Series airplane A300 B2 and B4; A300 B4–600, B4– 600R, and F4–600R, C4–605R Variant F airplanes (collectively called A300– 600). A300 B2 and B4; A300 B4–600, B4– 600R, and F4–600R, C4–605R Variant F airplanes (collectively called A300– 600). A310 ......................................................... A310 ......................................................... Jkt 205001 A300–78–6021, Revision 1 ...................... October 7, 2003. CF6–80C2 A300–78–6022, Revision 1 ...................... January 7, 2003. CF6–80C2 CF6–80A3 A310–78–2022 ......................................... A310–78–2024 ......................................... January 7, 2003. October 15, 2003. Related Information (h) 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. 20:26 Aug 05, 2005 Date CF6–80C2 Alternative Methods of Compliance (AMOCs) VerDate jul<14>2003 Airbus service bulletin (i) French airworthiness directive F–2004– 165, dated October 13, 2004, also addresses the subject of this AD. PO 00000 Issued in Renton, Washington, on August 2, 2005. Kevin Mullin, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 05–15594 Filed 8–5–05; 8:45 am] BILLING CODE 4910–13–P Frm 00028 Fmt 4702 Sfmt 4702 E:\FR\FM\08AUP1.SGM 08AUP1

Agencies

[Federal Register Volume 70, Number 151 (Monday, August 8, 2005)]
[Proposed Rules]
[Pages 45595-45598]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 05-15594]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2005-22036; Directorate Identifier 2005-NM-009-AD]
RIN 2120-AA64


Airworthiness Directives; Airbus Model A300 B2 and B4 Series 
Airplanes; Model A300 B4-600, B4-600R, and F4-600R Series Airplanes, 
and Model C4-605R Variant F Airplanes (Collectively Called A300-600 
Series Airplanes); and Model A310 Series Airplanes; Equipped With 
General Electric CF6-80A3 or CF6-80C2 Engines

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 certain Airbus airplane models, as specified above. This proposed 
AD would require installing electro-pneumatic locking bar devices (TRAS 
lock systems) in the engine nacelles, installing a dedicated and 
shielded electrical circuit that is segregated from the existing thrust 
reverser control system, and performing related investigative/
corrective actions if necessary. This proposed AD is prompted by the 
manufacturer's reassessment of the thrust reverser systems in the 
Airbus airplane models specified above, which showed that the thrust 
reverser could inadvertently deploy in flight under certain conditions. 
We are proposing this AD to prevent inadvertent deployment of thrust 
reversers in flight, which could result in reduced controllability of 
the airplane.

DATES: We must receive comments on this proposed AD by September 7, 
2005.

ADDRESSES: Use one of the following addresses to submit comments on 
this proposed AD.
     DOT Docket Web Site: Go to http://dms.dot.gov and follow 
the instructions for sending your comments electronically.
     Government-Wide Rulemaking Web Site: Go to http://
www.regulations.gov and follow the instructions for sending your 
comments electronically.
     Mail: Docket Management Facility, U.S. Department of 
Transportation, 400 Seventh Street SW., Nassif Building, room PL-401, 
Washington, DC 20590.
     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 
http://dms.dot.gov, or in person at the Docket Management Facility, 
U.S. Department of Transportation, 400 Seventh Street SW., room PL-401, 
on the plaza level of the Nassif Building, Washington, DC. This docket 
number is FAA-2005-22036; the directorate identifier for this docket is 
2005-NM-009-AD.

FOR FURTHER INFORMATION CONTACT: Tim Backman, Aerospace Engineer, 
International Branch, ANM-116, FAA, 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-2005-22036; 
Directorate Identifier 2005-NM-009-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 http://
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 http://dms.dot.gov.

Examining the Docket

    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 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 G[eacute]n[eacute]rale de l'Aviation Civile (DGAC), 
which is the airworthiness authority for France, notified us that an 
unsafe condition may exist on certain Airbus Model A300 B2 and B4 
series airplanes; Model A300 B4-600, B4-600R, and F4-600R series 
airplanes, and Model C4-605R Variant F airplanes (collectively called 
A300-600 series airplanes); and Model A310 series airplanes; equipped 
with General Electric CF6-80A3 or CF6-80C2 engines. The DGAC advises 
that the manufacturer has reassessed the thrust reverser systems of 
those airplanes and has determined that the thrust reverser could 
inadvertently deploy in flight. The manufacturer has developed a new, 
improved design of the thrust reversers, which provides an independent 
system to prevent deployment of the thrust reversers in flight. 
Inadvertent deployment of the thrust reversers in flight could result 
in reduced controllability of the airplane.

Relevant Service Information

    Airbus has issued the following service bulletins (SBs), which 
describe procedures for installing electro-pneumatic locking bar 
devices (TRAS lock system) and a dedicated and shielded electrical 
circuit that is segregated from the existing thrust reverser control 
system. The new electrical circuit commands the locking bar devices 
(TRAS locks), which would be installed in the engine nacelles. 
Implementation of the following SBs is intended to provide an 
independent system to prevent inadvertent deployment of thrust 
reversers during flight.

[[Page 45596]]

    Airbus SB A310-78-2023, dated October 7, 2003 (for Model A310 
series airplanes equipped with General Electric CF6-80C2 engines and 
not equipped with Full Authority Digital Engine Control (FADEC)), 
specifies previous or concurrent accomplishment of Airbus SB A310-78-
2022, and describes modifying/retrofitting the electrical harness 
routine from each lock to the pylon interfaces of the engine/nacelle, 
and the existing monitoring wire; and activating the electrical system 
of the aircraft.
    Airbus SB A310-78-2022, dated January 7, 2003 (for Airbus Model 310 
series airplanes equipped with General Electric CF6-80C2 engines and 
not equipped with FADEC), describes modifying/retrofitting a new 
electrical circuit between the forward cargo compartment and the wing/
pylon interfaces, a new electrical circuit in the engine pylons, and a 
new electrical circuit in the avionics compartment and the forward 
cargo compartment; and connecting the new electrical circuit. The SB 
indicates that Parts 1 and 2 of the SB can be accomplished 
independently and in any sequence, but Part 3 must be accomplished 
after the first two parts. Full function can be assured once Airbus SB 
A310-78-2023 has been accomplished.
    Airbus SB A310-78-2025, dated July 23, 2004 (for Model A310 series 
airplanes equipped with General Electric CF6-80A3 engines), specifies 
previous or concurrent accomplishment of Airbus SB A310-78-2024, and 
references Goodrich Service Bulletin 71-065 as an additional source of 
service information. (After the issuance of Airbus SB A310-78-2025, 
dated July 23, 2004, the Goodrich Service Bulletin was reissued as Rohr 
Service Bulletin CF6-80A3, dated April 28, 2005.) Airbus SB A310-78-
2025 also describes the following procedures:
     Modifying/retrofitting the existing monitoring wire and 
activating the electrical system of the aircraft.
     Modifying/retrofitting the electrical harness routine from 
each lock to the pylon interfaces of the engine/nacelle.
     Installing the support bracket for the electrical harness 
of the engine/nacelle.
     Modifying the stowed position of the hold-open rod bracket 
of the engine/nacelle.
     Replacing the lower end actuator gearbox with a gearbox 
that integrates the locking bar.
     Replacing the pneumatic tubing situated upstream from the 
pressure regulated shut-off valve (PRSOV) with a new PRSOV having a 
third line of defense (TLOD) tubing connector.
     Modifying the hold-open rod bracket of the fan cowl.
     Accomplishing the test job set-up, extended operational 
test of the circuit breaker monitoring system, and the test for the 
stow and deploy switches included in the thrust reverser functional and 
indicating/warning sensors test.
    Airbus Service Bulletin A310-78-2024, dated October 15, 2003 (for 
Model A310 series airplanes equipped with CF6-80A3 engines), describes 
procedures for the airplane and the engine/nacelle that include the 
following:
     Modifying the hold-open rod bracket of the fan cowl.
     Installing the actuation system lock.
     Modifying the wiring in a certain circuit breaker panel.
    Airbus Service Bulletin A300-78-6024, dated October 7, 2003 (for 
Model A300-600 series airplanes equipped with General Electric CF6-80C2 
engines and equipped with FADEC), specifies previous or concurrent 
accomplishment of Airbus SB A300-78-6021, Revision 1, dated October 7, 
2003, and describes procedures for the following:
     Installing an actuation system lock.
     Modifying the wiring in a certain circuit breaker panel.
     Accomplishing the test job set-up, extended operational 
test of the circuit breaker monitoring system, and the test for the 
stow and deploy switches included in the thrust reverser functional and 
indicating/warning sensors test.
    Airbus SB A300-78-6021, Revision 1, dated October 7, 2003 (for 
Model A300-600 series airplanes equipped with General Electric CF6-80C2 
engines and equipped with FADEC), describes procedures for the 
following:
     Part 1--Modifying/retrofitting a new electrical circuit 
between the forward cargo compartment and the wing/pylon interfaces.
     Part 2--Modifying/retrofitting a new electrical circuit in 
the engine pylons.
     Part 3--Modifying/retrofitting a new electrical circuit in 
the avionics compartment; modifying/retrofitting a new electrical 
circuit between the avionics compartment and the forward cargo 
compartment; and modifying/retrofitting a new electrical circuit.
    Airbus SB A300-78-6025, dated October 7, 2003 (for Model A300-600 
series airplanes equipped with General Electric CF6-80C2 engines not 
equipped with FADEC), specifies previous or concurrent accomplishment 
of Airbus SB A300-78-6022, and describes procedures for the following:
     Installing an actuation system lock.
     Modifying the wiring in a certain circuit breaker panel.
     Accomplishing the test job set-up, extended operational 
test of the circuit breaker monitoring system, and the test for the 
stow and deploy switches included in the thrust reverser functional and 
indicating/warning sensors test.
    Airbus SB A300-78-6022, Revision 1, dated January 7, 2003 (for 
Model A300-600 airplanes equipped with General Electric CF6 80C2 
engines and not equipped with FADEC), describes procedures for the 
following:
     Part 1--Modifying/retrofitting a new electrical circuit 
between the forward cargo-compartment and the wing/pylon interfaces.
     Part 2--Modifying/retrofitting a new electrical circuit in 
the engine pylons.
     Part 3--Modifying/retrofitting a new electrical circuit in 
the avionics compartment; modifying/retrofitting a new electrical 
circuit between the avionics compartment and the forward cargo 
compartment; and modifying/retrofitting a new electrical circuit.
    Accomplishing the actions specified in the service information is 
intended to adequately address the unsafe condition. The DGAC mandated 
the above service bulletins and issued French airworthiness directive 
F-2004-165, dated October 13, 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 the FAA informed 
of the situation described above. We have examined the DGAC's 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.

Costs of Compliance

    This AD affects about 101 airplanes of U.S. registry. (The total 
number of airplanes in the following table totals more than 101 
airplanes because most of the airplanes would be required to accomplish 
two of the specified service

[[Page 45597]]

bulletins.) The following table provides the estimated costs for U.S. 
operators to comply with this proposed AD at an average labor rate per 
hour of $65.

                    Estimated Costs for Modifications (Listed by Applicable Service Bulletin)
----------------------------------------------------------------------------------------------------------------
                                                                             Cost per    Number of
          Airbus service bulletin (SB)            Work hours     Parts       airplane    airplanes   Cost per SB
----------------------------------------------------------------------------------------------------------------
A300-78-6021, Revision 1.......................          257      $15,185      $31,890           36   $1,148,040
A300-78-6022, Revision 1.......................          289       18,198       36,983           34    1,257,422
A300-78-6024...................................            4          150          410           36       14,760
A300-78-6025...................................            4          150          410           34       13,940
A310-78-2024...................................            4       18,009       35,884           27      968,868
A310-78-2025...................................            4          150          410           31       12,710
----------------------------------------------------------------------------------------------------------------

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 proposed AD would not have federalism 
implications under Executive Order 13132. This proposed AD would 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-2005-22036; Directorate Identifier 2005-NM-
009-AD.

Comments Due Date

    (a) The Federal Aviation Administration must receive comments on 
this AD action by September 7, 2005.

Affected ADs

    (b) None.
    Applicability: (c) This AD applies to Airbus series airplanes, 
certificated in any category, as identified in the service bulletins 
listed in Table 1 of this AD.

                                             Table 1.--Applicability
----------------------------------------------------------------------------------------------------------------
                                              General
             Series airplane                 Electric       Airbus service bulletin              Date
                                           engine model
----------------------------------------------------------------------------------------------------------------
A300 B2 and B4; A300 B4-600, B4-600R,           CF6-80C2  A300-78-6024..............  October 7, 2003.
 and F4-600R, C4-605R Variant F
 airplanes (collectively called A300-600
 series airplanes).
A300 B2 and B4; A300 B4-600, B4-600R,           CF6-80C2  A300-78-6021, Revision 1..  October 7, 2003.
 and F4-600R, C4-605R Variant F
 airplanes (collectively called A300-
 600).
A300 B2 and B4; A300 B4-600, B4-600R,           CF6-80C2  A300-78-6025..............  October 7, 2003.
 and F4-600R, C4-605R Variant F
 airplanes (collectively called A300-
 600).
A300 B2 and B4; A300 B4-600, B4-600R,           CF6-80C2   A300-78-6022, Revision 1.  January 7, 2003.
 and F4-600R, C4-605R Variant F
 airplanes (collectively called A300-
 600).
A310....................................        CF6-80C2  A310-78-2023..............  October 7, 2003.
A310....................................        CF6-80C2  A310-78-2022..............  January 7, 2003.
A310....................................        CF6-80A3  A310-78-2025..............  July 23, 2004.

[[Page 45598]]

 
A310....................................        CF6-80A3  A310-78-2024..............  October 15, 2003.
----------------------------------------------------------------------------------------------------------------

Unsafe Condition

    (d) This AD was prompted by the manufacturer's reassessment of 
the thrust reverser systems in the Airbus airplane models specified 
in Table 1 of this AD, which showed that the thrust reverser could 
deploy in flight under certain conditions. We are issuing this AD to 
prevent inadvertent deployment of thrust reversers in flight, which 
could result in reduced controllability 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.

Installing TRAS Locks System and Accomplishing Modifications

    (f) For airplanes identified in the service bulletins specified 
in Table 2 of this AD: Within 36 months after the effective date of 
this AD, install the electro-pneumatic locking bar devices (TRAS 
Lock Systems) in the thrust reverser system of the nacelles, in 
accordance with the Accomplishment Instructions of the applicable 
service bulletin.

                                     Table 2.--Installing TRAS Lock Systems
----------------------------------------------------------------------------------------------------------------
                                              General
             Series airplane                 Electric       Airbus service bulletin              Date
                                           engine model
----------------------------------------------------------------------------------------------------------------
A300 B2 and B4; A300 B4-600, B4-600R,           CF6-80C2  A300-78-6024..............  October 7, 2003.
 and F4-600R, C4-605R Variant F
 airplanes (collectively called A300-600
 series airplanes).
A300 B2 and B4; A300 B4-600, B4-600R,           CF6-80C2  A300-78-6025..............  October 7, 2003.
 and F4-600R, C4-605R Variant F
 airplanes (collectively called A300-
 600).
A310....................................        CF6-80C2  A310-78-2023..............  October 7, 2003.
A310....................................        CF6-80A3  A310-78-2025..............  July 23, 2004.
----------------------------------------------------------------------------------------------------------------


    Note 1: Airbus SB A310-78-2025, dated July 23, 2004, references 
draft Goodrich Service Bulletin 71-065 as an additional source of 
service information. After the issuance of Airbus A310-78-2025, the 
Goodrich SB was reissued as Rohr Service Bulletin CF6-80A3, dated 
April 28, 2005.

    (g) For airplanes identified in the service bulletins specified 
in Table 3 of this AD: Prior to or concurrent with the 
accomplishment of the applicable service bulletin specified in 
paragraph (f) of this AD, accomplish all the modifications and 
actions related to an independent third line of defense on the 
thrust reversers, in accordance with the Accomplishment Instructions 
of the applicable service bulletin specified in Table 3 of this AD.

                                  Table 3.--Prior or Concurrent Accomplishment
----------------------------------------------------------------------------------------------------------------
                                              General
             Series airplane                 Electric       Airbus service bulletin              Date
                                           engine model
----------------------------------------------------------------------------------------------------------------
A300 B2 and B4; A300 B4-600, B4-600R,           CF6-80C2  A300-78-6021, Revision 1..  October 7, 2003.
 and F4-600R, C4-605R Variant F
 airplanes (collectively called A300-
 600).
A300 B2 and B4; A300 B4-600, B4-600R,           CF6-80C2  A300-78-6022, Revision 1..  January 7, 2003.
 and F4-600R, C4-605R Variant F
 airplanes (collectively called A300-
 600).
A310....................................        CF6-80C2  A310-78-2022..............  January 7, 2003.
A310....................................        CF6-80A3  A310-78-2024..............  October 15, 2003.
----------------------------------------------------------------------------------------------------------------

Alternative Methods of Compliance (AMOCs)

    (h) 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.

Related Information

    (i) French airworthiness directive F-2004-165, dated October 13, 
2004, also addresses the subject of this AD.

    Issued in Renton, Washington, on August 2, 2005.
Kevin Mullin,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 05-15594 Filed 8-5-05; 8:45 am]
BILLING CODE 4910-13-P