Airworthiness Directives; Airbus Model A300 B2 and B4 Series Airplanes, 45592-45595 [05-15593]

Download as PDF 45592 Federal Register / Vol. 70, No. 151 / Monday, August 8, 2005 / Proposed Rules electromechanical gust lock system to become unscrewed. We are proposing this AD to prevent unscrewing of the spring cartridge clevis from jamming the elevator, which could lead to 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. Restatement of Requirements of AD 2003– 09–03 Inspection (f) For Model EMB–135BJ airplanes: Within 30 days after May 14, 2003 (the effective date of AD 2003–09–03), perform a general visual inspection of each spring cartridge of the elevator gust lock system to determine if the lock washer projection correctly fits the slots in the cartridge flange, in accordance with EMBRAER Service Bulletin 145LEG–27–0006, dated December 9, 2002. Before further flight, replace any discrepant spring cartridge with a new part having the same part number, in accordance with the service bulletin; or replace the spring cartridge, part number (P/N) KDP2611, with a new, improved spring cartridge, P/N KDP4235, as specified in paragraph (h) of this AD. After the effective date of this AD, only the replacement specified in paragraph (h) may be accomplished. Repeat the inspection at intervals not to exceed 800 flight hours until the replacement of the spring cartridge is accomplished as required by paragraph (h). Although the service bulletin recommends that operators report inspection results to EMBRAER, this AD does not require such a report. Note 1: For the purposes of this AD, a general visual inspection is: ‘‘A visual examination of an interior or exterior area, installation, or assembly to detect obvious damage, failure, or irregularity. This level of inspection is made from within touching distance unless otherwise specified. A mirror may be necessary to ensure visual access to all surfaces in the inspection area. This level of inspection is made under normally available lighting conditions such as daylight, hangar lighting, flashlight, or droplight and may require removal or opening of access panels or doors. Stands, ladders, or platforms may be required to gain proximity to the area being checked.’’ (g) For airplanes not identified in paragraph (f) of this AD: At the applicable time specified in paragraph (g)(1) or (g)(2) of this AD, perform a general visual inspection of each spring cartridge of the elevator gust lock system to determine if the lock washer projection correctly fits the slots in the cartridge flange, in accordance with EMBRAER Service Bulletin 145–27–0098, dated December 9, 2002. Repeat the inspection at intervals not to exceed 800 flight hours after the initial inspection until the replacement of the spring cartridge, P/N KDP2611, with a new, improved spring cartridge, P/N KDP4235, is done as specified in paragraph (h) of this AD. Although the service bulletin recommends that operators report inspection results to EMBRAER, this AD does not require such a report. VerDate jul<14>2003 20:26 Aug 05, 2005 Jkt 205001 (1) For airplanes equipped with an operational electromechanical gust lock system on the elevator: Inspect within 30 days after May 14, 2003, in accordance with PART I of the service bulletin. Before further flight, replace any discrepant spring cartridge with a new part having the same part number, in accordance with PART I of the service bulletin; or do the replacement specified in paragraph (h) of this AD. After the effective date of this AD, only the replacement specified in paragraph (h) may be accomplished. (2) For airplanes that are not equipped with an operational electromechanical gust lock system on the elevator, but that are equipped with provisions for the system: Inspect within 60 days after May 14, 2003, in accordance with PART II of the service bulletin. Before further flight, replace any discrepant spring cartridge with a new part having the same part number, in accordance with PART II of the service bulletin; or do the replacement specified in paragraph (h) of this AD. After the effective date of this AD, only the replacement specified in paragraph (h) may be accomplished. Alternatively, removal of the spring cartridges terminates the repetitive inspection requirement of this AD during the time the cartridges are removed. New Requirements of This AD Replacement of Spring Cartridge (h) Within 5,500 flight hours or 36 months after the effective date of this AD, whichever comes first, replace the spring cartridge, P/N KPD2611, with a new, improved spring cartridge, P/N KDP4235, in accordance with the Accomplishment Instructions of EMBRAER Service Bulletin 145LEG–27– 0012, Revision 01, dated April 12, 2004 (for Model EMB–135BJ airplanes); or Service Bulletin 145–27–0102, Revision 02, dated January 20, 2005 (for Model EMB–135ER, –135KE, –135KL, –135LR, –145, –145ER, –145MR, –145LR, –145XR, –145MP, and –145EP airplanes); as applicable. Accomplishing this replacement terminates the repetitive inspections required by paragraphs (f) and (g) of this AD. Parts Installation (i) As of the effective date of this AD, no person may install a spring cartridge, P/N KPD2611, on any airplane. Cartridge Replacement According to Previous Issue of Service Bulletin (j) Spring cartridge replacements accomplished before the effective date of this AD in accordance with EMBRAER Service Bulletin 145LEG–27–0012, dated March 2, 2004; or Service Bulletin 145–27–0102, dated December 23, 2003, or Revision 01, dated April 12, 2004; are considered acceptable for compliance with the corresponding action required by this AD. Alternative Methods of Compliance (AMOCs) (k)(1) 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. PO 00000 Frm 00022 Fmt 4702 Sfmt 4702 (2) AMOCs approved previously according to AD 2003–09–03, amendment 39–13132, are approved as AMOCs for the corresponding provisions of this AD. Related Information (l) Brazilian airworthiness directive 2003– 01–03R1, dated July 26, 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. 05–15592 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–2005–22035; Directorate Identifier 2005–NM–016–AD] RIN 2120–AA64 Airworthiness Directives; Airbus Model A300 B2 and B4 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 Airbus Model A300 B2 and B4 series airplanes. This proposed AD would require an inspection to determine the part number of all angle of attack (AOA) sensors, and repetitive replacement of the AOA sensors with new or overhauled AOA sensors if necessary. This proposed AD would also provide an optional terminating action for the repetitive replacements. This proposed AD is prompted by reports of several false stall warnings associated with stick-shaker activation, occurring during take-off. We are proposing this AD to prevent false stall warnings associated with stick-shaker activation, which could result in increased pilot workload as the pilot tries to determine the cause of the stall warning and possible reduction in the pilot’s ability to control 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. E:\FR\FM\08AUP1.SGM 08AUP1 45593 Federal Register / Vol. 70, No. 151 / Monday, August 8, 2005 / Proposed Rules • 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. • 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. Contact Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France, for service information identified in this proposed 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. Include the docket number ‘‘FAA–2005–22035; Directorate Identifier 2005-NM–016AD’’ 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 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 that 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 may review the DOT’s complete Privacy Act Statement in the Federal Register published on April 11, 2000 (65 FR 19477–78), or you may visit http:// dms.dot.gov. dated November 2, 2004. Service Bulletin A300–34–0092 describes the following procedures: • Replacing Honeywell ‘‘pencil’’ AOA sensors having P/N 965–4020–007 with ‘‘vane’’ AOA sensors between frame (FR)18 and FR19. • Replacing the current detectors in relay boxes 252VU and 107VU with new current detectors. Airbus Service Bulletin A300–34– 0092 also specifies that accomplishing the modification in that service bulletin cancels the actions specified in Airbus Service Bulletin A300–34–0176. Examining the Docket You may 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 Docket Management System receives them. FAA’s Determination and Requirements of the Proposed AD 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. The DGAC advises that it has received reports of several false stall warnings associated with stick-shaker activation, occurring during take-off. Investigation revealed that defective angle of attack (AOA) sensors caused the false stall warnings. This condition, if not corrected, could result in increased pilot workload as the pilot tries to determine the cause of the stall warning and possible reduction in the pilot’s ability to control the airplane. 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, except as discussed under ‘‘Difference Between the Proposed AD and Service Bulletin.’’ Relevant Service Information Airbus has issued Service Bulletin A300–34–0176, Revision 01, dated February 3, 2004, which describes the following procedures: • Inspecting zone 120 to determine the part number (P/N) of all three AOA sensors. • Repetitively replacing any Honeywell AOA sensor having P/N 965–4020–007 with a new or overhauled AOA sensor. 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–2003–457 R1, dated December 22, 2004, to ensure the continued airworthiness of these airplanes in France. Airbus has also issued Service Bulletin A300–34–0092, Revision 03, Difference Between the Proposed AD and Service Bulletin Operators should note that, although the Accomplishment Instructions of the Airbus Service Bulletin A300–34–0176, Revision 01, dated February 3,2004, describe procedures for reporting inspection findings, this proposed AD would not require that action. We do not need this information from operators. Costs of Compliance The following table provides the estimated costs for U.S. operators to comply with this proposed AD. ESTIMATED COSTS Action Inspection ............................ VerDate jul<14>2003 20:26 Aug 05, 2005 Average labor rate per hour Work hours 1 Jkt 205001 $65 PO 00000 Cost per airplane Parts None .................................. Frm 00023 Fmt 4702 Sfmt 4702 Number of U.S.registered airplanes $65 E:\FR\FM\08AUP1.SGM 20 08AUP1 Fleet cost $1,300. 45594 Federal Register / Vol. 70, No. 151 / Monday, August 8, 2005 / Proposed Rules ESTIMATED COSTS—Continued Action Average labor rate per hour Work hours Replacement if necessary, per replacement cycle. Optional terminating action 2 65 $3,300 ($1,100 per sensor) 3,430 20 7 65 $8,780 ................................ 9,235 20 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. VerDate jul<14>2003 20:26 Aug 05, 2005 Number of U.S.registered airplanes Cost per airplane Parts Jkt 205001 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. § 39.13 [Amended] 2. The FAA amends § 39.13 by adding the following new airworthiness directive (AD): Airbus: Docket No. FAA–2005–22035; Directorate Identifier 2005–NM–016–AD. Comments Due Date (a) The Federal Aviation Administration must receive comments on this AD action by September 7, 2005. Fleet cost $68,600 per replacement cycle. $184,700. required by this paragraph. If any Honeywell AOA sensor having P/N 965–4020–007 is found, before further flight, replace the AOA sensor with a new or overhauled AOA sensor having P/N 965–4020–007, in accordance with the service bulletin. Repeat the replacement thereafter at intervals not to exceed 8,000 flight hours or 96 months, whichever is first. Accomplishing the actions specified in paragraph (g) of this AD terminates the repetitive replacements. Optional Terminating Action (g) Replacement of all Honeywell AOA sensors having P/N 965–4020–007 between frame (FR)18 and FR19 with ‘‘vane type’’ AOA sensors; and replacement of the current detectors in relay boxes 252VU and 107VU with new current detectors; in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300–34–0092, Revision 03, dated November 2, 2004; terminate the repetitive replacements required by paragraph (f) of this AD. No Reporting Requirement Affected ADs (b) None. Applicability: (c) This AD applies to all Airbus Model A300 B2–1A, B2–1C, B2K–3C, and B2–203 airplanes; and Model A300 B4– 2C, B4–103, and B4–203 airplanes; certificated in any category. (h) Although Airbus Service Bulletin A300–34–0176, Revision 01, dated February 3, 2004, specifies to submit certain information to the manufacturer, this AD does not include that requirement. Unsafe Condition (d) This AD was prompted by reports of several false stall warnings associated with stick-shaker activation, occurring during take-off. We are issuing this AD to prevent false stall warnings associated with stickshaker activation, which could result in increased pilot workload as the pilot tries to determine the cause of the stall warning and possible reduction in the pilot’s ability to control 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. (i) As of the effective date of this AD, no person may install an AOA sensor having P/N 965–4020–007 on any airplane, unless it is new or overhauled and is repetitively inspected as required by paragraph (f) of this AD. Inspection and Repetitive Replacement, if Necessary (f) Within 4,500 flight hours or 36 months after the effective date of this AD, whichever is first: Inspect zone 120 to determine the part number of all three angle of attack (AOA) sensors, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300–34–0176, Revision 01, dated February 3, 2004. If no Honeywell AOA sensor having part number (P/N) 965– 4020–007 is found, then no further action is PO 00000 Frm 00024 Fmt 4702 Sfmt 4702 Parts Installation Credit for Previously Accomplished Actions (j) Actions done before the effective date of this AD in accordance with Airbus Service Bulletin A300–34–0176, dated July 9, 2003, are acceptable for compliance with the corresponding requirements of paragraph (f) of this AD. Credit for Optional Terminating Action (k) Actions done before the effective date of this AD in accordance with Airbus Service Bulletin A300–34–092, Revision 2, dated July 18, 1985, are acceptable for compliance with the requirements of paragraph (g) of this AD. Alternative Methods of Compliance (AMOCs) (l) 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. E:\FR\FM\08AUP1.SGM 08AUP1 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

Agencies

[Federal Register Volume 70, Number 151 (Monday, August 8, 2005)]
[Proposed Rules]
[Pages 45592-45595]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 05-15593]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2005-22035; Directorate Identifier 2005-NM-016-AD]
RIN 2120-AA64


Airworthiness Directives; Airbus Model A300 B2 and B4 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 Airbus Model A300 B2 and B4 series airplanes. This proposed AD 
would require an inspection to determine the part number of all angle 
of attack (AOA) sensors, and repetitive replacement of the AOA sensors 
with new or overhauled AOA sensors if necessary. This proposed AD would 
also provide an optional terminating action for the repetitive 
replacements. This proposed AD is prompted by reports of several false 
stall warnings associated with stick-shaker activation, occurring 
during take-off. We are proposing this AD to prevent false stall 
warnings associated with stick-shaker activation, which could result in 
increased pilot workload as the pilot tries to determine the cause of 
the stall warning and possible reduction in the pilot's ability to 
control 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.

[[Page 45593]]

     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.
     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.
    Contact Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, 
France, for service information identified in this proposed 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. Include the docket number ``FAA-
2005-22035; Directorate Identifier 2005-NM-016-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 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 
that 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 may review the DOT's complete Privacy Act Statement in the 
Federal Register published on April 11, 2000 (65 FR 19477-78), or you 
may visit http://dms.dot.gov.

Examining the Docket

    You may 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 Docket Management System 
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. The DGAC advises that it has received reports of 
several false stall warnings associated with stick-shaker activation, 
occurring during take-off. Investigation revealed that defective angle 
of attack (AOA) sensors caused the false stall warnings. This 
condition, if not corrected, could result in increased pilot workload 
as the pilot tries to determine the cause of the stall warning and 
possible reduction in the pilot's ability to control the airplane.

Relevant Service Information

    Airbus has issued Service Bulletin A300-34-0176, Revision 01, dated 
February 3, 2004, which describes the following procedures:
     Inspecting zone 120 to determine the part number (P/N) of 
all three AOA sensors.
     Repetitively replacing any Honeywell AOA sensor having P/N 
965-4020-007 with a new or overhauled AOA sensor.
    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-
2003-457 R1, dated December 22, 2004, to ensure the continued 
airworthiness of these airplanes in France.
    Airbus has also issued Service Bulletin A300-34-0092, Revision 03, 
dated November 2, 2004. Service Bulletin A300-34-0092 describes the 
following procedures:
     Replacing Honeywell ``pencil'' AOA sensors having P/N 965-
4020-007 with ``vane'' AOA sensors between frame (FR)18 and FR19.
     Replacing the current detectors in relay boxes 252VU and 
107VU with new current detectors.
    Airbus Service Bulletin A300-34-0092 also specifies that 
accomplishing the modification in that service bulletin cancels the 
actions specified in Airbus Service Bulletin A300-34-0176.

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, except as discussed under ``Difference Between 
the Proposed AD and Service Bulletin.''

Difference Between the Proposed AD and Service Bulletin

    Operators should note that, although the Accomplishment 
Instructions of the Airbus Service Bulletin A300-34-0176, Revision 01, 
dated February 3,2004, describe procedures for reporting inspection 
findings, this proposed AD would not require that action. We do not 
need this information from operators.

Costs of Compliance

    The following table provides the estimated costs for U.S. operators 
to comply with this proposed AD.

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                     Number of
                                 Work      Average                       Cost per      U.S.-
           Action               hours     labor rate       Parts         airplane    registered     Fleet cost
                                           per hour                                  airplanes
----------------------------------------------------------------------------------------------------------------
Inspection..................          1          $65  None...........          $65           20  $1,300.

[[Page 45594]]

 
Replacement if necessary,             2           65  $3,300 ($1,100         3,430           20  $68,600 per
 per replacement cycle.                                per sensor).                               replacement
                                                                                                  cycle.
Optional terminating action.          7           65  $8,780.........        9,235           20  $184,700.
----------------------------------------------------------------------------------------------------------------

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-2005-22035; Directorate Identifier 2005-NM-
016-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 all Airbus Model A300 B2-
1A, B2-1C, B2K-3C, and B2-203 airplanes; and Model A300 B4-2C, B4-
103, and B4-203 airplanes; certificated in any category.

Unsafe Condition

    (d) This AD was prompted by reports of several false stall 
warnings associated with stick-shaker activation, occurring during 
take-off. We are issuing this AD to prevent false stall warnings 
associated with stick-shaker activation, which could result in 
increased pilot workload as the pilot tries to determine the cause 
of the stall warning and possible reduction in the pilot's ability 
to control 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.

Inspection and Repetitive Replacement, if Necessary

    (f) Within 4,500 flight hours or 36 months after the effective 
date of this AD, whichever is first: Inspect zone 120 to determine 
the part number of all three angle of attack (AOA) sensors, in 
accordance with the Accomplishment Instructions of Airbus Service 
Bulletin A300-34-0176, Revision 01, dated February 3, 2004. If no 
Honeywell AOA sensor having part number (P/N) 965-4020-007 is found, 
then no further action is required by this paragraph. If any 
Honeywell AOA sensor having P/N 965-4020-007 is found, before 
further flight, replace the AOA sensor with a new or overhauled AOA 
sensor having P/N 965-4020-007, in accordance with the service 
bulletin. Repeat the replacement thereafter at intervals not to 
exceed 8,000 flight hours or 96 months, whichever is first. 
Accomplishing the actions specified in paragraph (g) of this AD 
terminates the repetitive replacements.

Optional Terminating Action

    (g) Replacement of all Honeywell AOA sensors having P/N 965-
4020-007 between frame (FR)18 and FR19 with ``vane type'' AOA 
sensors; and replacement of the current detectors in relay boxes 
252VU and 107VU with new current detectors; in accordance with the 
Accomplishment Instructions of Airbus Service Bulletin A300-34-0092, 
Revision 03, dated November 2, 2004; terminate the repetitive 
replacements required by paragraph (f) of this AD.

No Reporting Requirement

    (h) Although Airbus Service Bulletin A300-34-0176, Revision 01, 
dated February 3, 2004, specifies to submit certain information to 
the manufacturer, this AD does not include that requirement.

Parts Installation

    (i) As of the effective date of this AD, no person may install 
an AOA sensor having P/N 965-4020-007 on any airplane, unless it is 
new or overhauled and is repetitively inspected as required by 
paragraph (f) of this AD.

Credit for Previously Accomplished Actions

    (j) Actions done before the effective date of this AD in 
accordance with Airbus Service Bulletin A300-34-0176, dated July 9, 
2003, are acceptable for compliance with the corresponding 
requirements of paragraph (f) of this AD.

Credit for Optional Terminating Action

    (k) Actions done before the effective date of this AD in 
accordance with Airbus Service Bulletin A300-34-092, Revision 2, 
dated July 18, 1985, are acceptable for compliance with the 
requirements of paragraph (g) of this AD.

Alternative Methods of Compliance (AMOCs)

    (l) 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.

[[Page 45595]]

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