Airworthiness Directives; Airbus Model A340-541 and -642 Airplanes, 52410-52412 [E6-14624]

Download as PDF 52410 Federal Register / Vol. 71, No. 172 / Wednesday, September 6, 2006 / Rules and Regulations Citation control of the airplane or cause an unsafe condition (or hazard to the airplane). In addition, a deployed inflatable restraint must be at least as strong as a Technical Standard Order (C114) certificated belt and shoulder harness. 6. It must be shown that deployment of the inflatable restraint system is not hazardous to the occupant or will not result in injuries that could impede rapid egress. This assessment should include occupants whose restraint is loosely fastened. 7. It must be shown that an inadvertent deployment that could cause injury to a standing or sitting person is improbable. In addition, the restraint must also provide suitable visual warnings that would alert rescue personnel to the presence of an inflatable restraint system. 8. It must be shown that the inflatable restraint will not impede rapid egress of the occupants 10 seconds after its deployment. 9. To comply with HIRF and lightning requirements, the inflatable restraint system is considered a critical system since its deployment could have a hazardous effect on the airplane. 10. It must be shown that the inflatable restraints will not release hazardous quantities of gas or particulate matter into the cabin. 11. The inflatable restraint system installation must be protected from the effects of fire such that no hazard to occupants will result. 12. There must be a means to verify the integrity of the inflatable restraint activation system before each flight or it must be demonstrated to reliably operate between inspection intervals. 13. A life limit must be established for appropriate system components. 14. Qualification testing of the internal firing mechanism must be performed at vibration levels appropriate for a general aviation airplane. The authority citation for these special conditions is as follows: I jlentini on PROD1PC65 with RULES Authority: 49 U.S.C. 106(g), 40113 and 44701; 14 CFR 21.16 and 21.101; and 14 CFR 11.38 and 11.19. The Special Conditions I The FAA has determined that this project will be accomplished on the basis of not lowering the current level of safety of the Diamond Aircraft Industries, Inc., models DA40 and DA42 occupant restraint system. Accordingly, pursuant to the authority delegated to me by the Administrator, the following special conditions are issued as part of the type certification basis for these models, as modified by AmSafe, Incorporated. Inflatable Three-Point Restraint Safety Belt with an Integrated Airbag Device on the Pilot, Co-pilot, and Passenger Seats of the Diamond Aircraft Industries, Inc., Models DA40 and DA42. 1. It must be shown that the inflatable restraint will deploy and provide protection under emergency landing conditions. Compliance will be demonstrated using the dynamic test condition specified in 14 CFR, part 23, § 23.562(b)(2). It is not necessary to account for floor warpage, as required by § 23.562(b)(3), or vertical dynamic loads, as required by § 23.562(b)(1). The means of protection must take into consideration a range of stature from a 5th percentile female to a 95th percentile male. The inflatable restraint must provide a consistent approach to energy absorption throughout that range. 2. The inflatable restraint must provide adequate protection for each occupant. In addition, unoccupied seats that have an active restraint must not constitute a hazard to any occupant. 3. The design must prevent the inflatable restraint from being incorrectly buckled and/or incorrectly installed such that the airbag would not properly deploy. Alternatively, it must be shown that such deployment is not hazardous to the occupant and will provide the required protection. 4. It must be shown that the inflatable restraint system is not susceptible to inadvertent deployment as a result of wear and tear or the inertial loads resulting from in-flight or ground maneuvers (including gusts and hard landings) that are likely to be experienced in service. 5. It must be extremely improbable for an inadvertent deployment of the restraint system to occur, or an inadvertent deployment must not impede the pilot’s ability to maintain VerDate Aug<31>2005 16:42 Sep 05, 2006 Jkt 205001 Issued in Kansas City, Missouri on August 29, 2006. James E. Jackson, Acting Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. E6–14750 Filed 9–5–06; 8:45 am] BILLING CODE 4910–13–P PO 00000 Frm 00008 Fmt 4700 Sfmt 4700 DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2006–25722; Directorate Identifier 2006–NM–141–AD; Amendment 39–14749; AD 2006–18–10] RIN 2120–AA64 Airworthiness Directives; Airbus Model A340–541 and –642 Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule; request for comments. AGENCY: SUMMARY: The FAA is adopting a new airworthiness directive (AD) for certain Airbus Model A340–541 and –642 airplanes. This AD requires a one-time inspection of the anti-stall valve sleeve of the ram air turbine (RAT) for proper installation, determining the part number of the modification plate on the hydraulic pump of the RAT, and followon corrective actions if necessary. This AD results from reports of failure of the anti-stall valve on the hydraulic pump of the RAT during scheduled ground tests. We are issuing this AD to prevent failure of the RAT hydraulic pump to supply adequate pressure to activate the RAT, and consequent loss of the RAT as a source of hydraulic and electrical power in an emergency situation. DATES: This AD becomes effective September 21, 2006. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in the AD as of September 21, 2006. We must receive comments on this AD by November 6, 2006. ADDRESSES: Use one of the following addresses to submit comments on this 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. • 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, E:\FR\FM\06SER1.SGM 06SER1 Federal Register / Vol. 71, No. 172 / Wednesday, September 6, 2006 / Rules and Regulations for service information identified in this AD. Tim Backman, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue, SW., Renton, Washington 98057–3356; telephone (425) 227–2797; fax (425) 227–1149. FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: Discussion The European Aviation Safety Agency (EASA), which is the airworthiness authority for the European Union, notified us that an unsafe condition may exist on certain Airbus Model A340–541 and –642 airplanes. The EASA advises that operators have reported failure of the anti-stall valve on the hydraulic pump of the ram air turbine (RAT) during scheduled ground tests. Investigation revealed that this failure was due to poor installation of the antistall valve sleeve, causing a shift in the anti-stall speed setting and leading to inability to supply adequate pressure to activate the RAT. These conditions, if not corrected, could result in loss of the RAT as a source of hydraulic and electrical power in an emergency situation. jlentini on PROD1PC65 with RULES Relevant Service Information Airbus has issued Service Bulletin A340–29–5010, including Appendix 01, dated October 10, 2005. The service bulletin describes procedures for determining the part number of the modification plate on the hydraulic pump of the ram air turbine (RAT), and follow-on corrective actions. The follow-on corrective actions include a one-time inspection of the anti-stall valve sleeve of the RAT for proper installation after determining the part number of the modification plate on the hydraulic pump of the RAT, reworking the anti-stall valve or replacing the RAT with a new RAT, and doing an operational test of the new RAT. Accomplishing the actions specified in the service information is intended to adequately address the unsafe condition. The EASA mandated the service information and issued airworthiness directive 2006–0046, dated February 16, 2006, to ensure the continued airworthiness of these airplanes in the European Union. The Airbus service bulletin refers to Hamilton Sundstrand Service Bulletin ERPS33T–29–3, dated August 1, 2005, as an additional source of service information for accomplishing the actions. VerDate Aug<31>2005 16:42 Sep 05, 2006 Jkt 205001 FAA’s Determination and Requirements of This 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. As described in FAA Order 8100.14A, ‘‘Interim Procedures for Working with the European Community on Airworthiness Certification and Continued Airworthiness,’’ dated August 12, 2005, the EASA has kept the FAA informed of the situation described above. We have examined the EASA’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 issuing this AD to prevent failure of the RAT hydraulic pump to supply adequate pressure to activate the RAT, and consequent loss of the RAT as a source of hydraulic and electrical power in an emergency situation. This AD requires accomplishing the actions specified in the Airbus service information described previously, except as discussed under ‘‘Differences Between the AD and the Airbus Service Bulletin.’’ Differences Between the AD and the Airbus Service Bulletin Unlike the procedures described in the service bulletin, the intent of the EASA airworthiness directive referenced in this AD is to mandate the one-time inspection of the anti-stall valve sleeve of the RAT for proper installation before determining the part number of the modification plate on the hydraulic pump of the RAT. If, after beginning the inspection, it is determined that the modification plate is already marked with a ’B’ showing that the inspection was accomplished previously, no further action is required by this AD. The service bulletin specifies returning any removed RAT to Hamilton Sundstrand; however, this AD does not require that action. Clarification of Inspection Terminology In this AD, the ‘‘inspection’’ specified in the service bulletin is referred to as a ‘‘general visual inspection.’’ We have included the definition for a general visual inspection in a note in the proposed AD. Costs of Compliance None of the airplanes affected by this action are on the U.S. Register. All PO 00000 Frm 00009 Fmt 4700 Sfmt 4700 52411 airplanes affected by this AD are currently operated by non-U.S. operators under foreign registry; therefore, they are not directly affected by this AD action. However, we consider this AD necessary to ensure that the unsafe condition is addressed if any affected airplane is imported and placed on the U.S. Register in the future. If an affected airplane is imported and placed on the U.S. Register in the future, the required actions would take about 1 work hour per airplane, at an average labor rate of $80 per work hour. Based on these figures, the estimated cost of the AD would be $80 per airplane. FAA’s Determination of the Effective Date No airplane affected by this AD is currently on the U.S. Register. Therefore, providing notice and opportunity for public comment is unnecessary before this AD is issued, and this AD may be made effective in less than 30 days after it is published in the Federal Register. Comments Invited This AD is a final rule that involves requirements that affect flight safety and was not preceded by notice and an opportunity for public comment; however, we invite you to submit any relevant written data, views, or arguments regarding this AD. Send your comments to an address listed in the ADDRESSES section. Include ‘‘Docket No. FAA–2006–25722; Directorate Identifier 2006–NM–141–AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of the AD that might suggest a need to modify it. 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 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 https://dms.dot.gov. Examining the Docket You may 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 E:\FR\FM\06SER1.SGM 06SER1 52412 Federal Register / Vol. 71, No. 172 / Wednesday, September 6, 2006 / Rules and Regulations 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. 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 jlentini on PROD1PC65 with RULES We have determined that this AD will not have federalism implications under Executive Order 13132. This AD will not have a substantial direct effect on the States, on the relationship between the national government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify that the 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 AD and placed it in the AD docket. See the ADDRESSES section for a location to examine the regulatory evaluation. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. 16:42 Sep 05, 2006 Jkt 205001 Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: I PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: I Authority for This Rulemaking VerDate Aug<31>2005 Adoption of the Amendment Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The Federal Aviation Administration (FAA) amends § 39.13 by adding the following new airworthiness directive (AD): I 2006–18–10 Airbus: Amendment 39–14749. Docket No. FAA–2006–25722; Directorate Identifier 2006–NM–141–AD. Effective Date (a) This AD becomes effective September 21, 2006. Affected ADs (b) None. Applicability (c) This AD applies to Airbus Model A340– 541 and –642 airplanes, certificated in any category; equipped with a ram air turbine (RAT) module, Model ERPS33T, part number (P/N) 772722D or 772722E; serial numbers 0001 through 0024 inclusive, and 0101 through 0166 inclusive, having a Parker hydraulic pump with P/N 4217701 or 4217702. Unsafe Condition (d) This AD results from reports of failure of the anti-stall valve on the hydraulic pump of the RAT during scheduled ground tests. We are issuing this AD to prevent failure of the RAT hydraulic pump to supply adequate pressure to activate the RAT, and consequent loss of the RAT as a source of hydraulic and electrical power in an emergency situation. 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/Follow-on Corrective Actions if Necessary (f) Within 11 months after the effective date of this AD: Do a one-time general visual inspection of the anti-stall valve sleeve of the RAT for proper installation, and determine the P/N of the modification plate on the hydraulic pump of the RAT, by doing all applicable actions, including all applicable follow-on corrective actions, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A340–29–5010, dated October 10, 2005. All corrective actions must be done before further flight. Although the service bulletin specifies returning any removed RAT to Hamilton Sundstrand, this AD does not require that action. PO 00000 Frm 00010 Fmt 4700 Sfmt 4700 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 enhance visual access to all exposed surfaces in the inspection area. This level of inspection is made under normally available lighting conditions such as daylight, hangar lighting, flashlight, or droplight and may require removal or opening of access panels or doors. Stands, ladders, or platforms may be required to gain proximity to the area being checked.’’ Note 2: The Airbus service bulletin refers to Hamilton Sundstrand Service Bulletin ERPS33T–29–3, dated August 1, 2005, as an additional source of service information for accomplishing the actions required by paragraph (f) of this AD. Alternative Methods of Compliance (AMOCs) (g)(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. (2) Before using any AMOC approved in accordance with § 39.19 on any airplane to which the AMOC applies, notify the appropriate principal inspector in the FAA Flight Standards Certificate Holding District Office. Related Information (h) European Aviation Safety Agency (EASA) airworthiness directive 2006–0046, dated February 16, 2006, also addresses the subject of this AD. Material Incorporated by Reference (i) You must use Airbus Service Bulletin A340–29–5010, excluding Appendix 01, dated October 10, 2005, to perform the actions that are required by this AD, unless the AD specifies otherwise. The Director of the Federal Register approved the incorporation by reference of this document in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Contact Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France, for a copy of this service information. You may review copies at the Docket Management Facility, U.S. Department of Transportation, 400 Seventh Street, SW., Room PL–401, Nassif Building, Washington, DC; on the Internet at https://dms.dot.gov; or at the National Archives and Records Administration (NARA). For information on the availability of this material at the NARA, call (202) 741–6030, or go to https:// www.archives.gov/federal_register/ code_of_federal_regulations/ ibr_locations.html. Issued in Renton, Washington, on August 23, 2006. Kalene C. Yanamura, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E6–14624 Filed 9–5–06; 8:45 am] BILLING CODE 4910–13–P E:\FR\FM\06SER1.SGM 06SER1

Agencies

[Federal Register Volume 71, Number 172 (Wednesday, September 6, 2006)]
[Rules and Regulations]
[Pages 52410-52412]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E6-14624]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2006-25722; Directorate Identifier 2006-NM-141-AD; 
Amendment 39-14749; AD 2006-18-10]
RIN 2120-AA64


Airworthiness Directives; Airbus Model A340-541 and -642 
Airplanes

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

ACTION: Final rule; request for comments.

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

SUMMARY: The FAA is adopting a new airworthiness directive (AD) for 
certain Airbus Model A340-541 and -642 airplanes. This AD requires a 
one-time inspection of the anti-stall valve sleeve of the ram air 
turbine (RAT) for proper installation, determining the part number of 
the modification plate on the hydraulic pump of the RAT, and follow-on 
corrective actions if necessary. This AD results from reports of 
failure of the anti-stall valve on the hydraulic pump of the RAT during 
scheduled ground tests. We are issuing this AD to prevent failure of 
the RAT hydraulic pump to supply adequate pressure to activate the RAT, 
and consequent loss of the RAT as a source of hydraulic and electrical 
power in an emergency situation.

DATES: This AD becomes effective September 21, 2006.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in the AD as of September 21, 
2006.
    We must receive comments on this AD by November 6, 2006.

ADDRESSES: Use one of the following addresses to submit comments on 
this 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.
     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,

[[Page 52411]]

for service information identified in this AD.

FOR FURTHER INFORMATION CONTACT: Tim Backman, Aerospace Engineer, 
International Branch, ANM-116, Transport Airplane Directorate, FAA, 
1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425) 
227-2797; fax (425) 227-1149.

SUPPLEMENTARY INFORMATION: 

Discussion

    The European Aviation Safety Agency (EASA), which is the 
airworthiness authority for the European Union, notified us that an 
unsafe condition may exist on certain Airbus Model A340-541 and -642 
airplanes. The EASA advises that operators have reported failure of the 
anti-stall valve on the hydraulic pump of the ram air turbine (RAT) 
during scheduled ground tests. Investigation revealed that this failure 
was due to poor installation of the anti-stall valve sleeve, causing a 
shift in the anti-stall speed setting and leading to inability to 
supply adequate pressure to activate the RAT. These conditions, if not 
corrected, could result in loss of the RAT as a source of hydraulic and 
electrical power in an emergency situation.

Relevant Service Information

    Airbus has issued Service Bulletin A340-29-5010, including Appendix 
01, dated October 10, 2005. The service bulletin describes procedures 
for determining the part number of the modification plate on the 
hydraulic pump of the ram air turbine (RAT), and follow-on corrective 
actions. The follow-on corrective actions include a one-time inspection 
of the anti-stall valve sleeve of the RAT for proper installation after 
determining the part number of the modification plate on the hydraulic 
pump of the RAT, reworking the anti-stall valve or replacing the RAT 
with a new RAT, and doing an operational test of the new RAT. 
Accomplishing the actions specified in the service information is 
intended to adequately address the unsafe condition. The EASA mandated 
the service information and issued airworthiness directive 2006-0046, 
dated February 16, 2006, to ensure the continued airworthiness of these 
airplanes in the European Union.
    The Airbus service bulletin refers to Hamilton Sundstrand Service 
Bulletin ERPS33T-29-3, dated August 1, 2005, as an additional source of 
service information for accomplishing the actions.

FAA's Determination and Requirements of This 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. As described in FAA 
Order 8100.14A, ``Interim Procedures for Working with the European 
Community on Airworthiness Certification and Continued Airworthiness,'' 
dated August 12, 2005, the EASA has kept the FAA informed of the 
situation described above. We have examined the EASA'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 issuing this AD to prevent failure of the RAT 
hydraulic pump to supply adequate pressure to activate the RAT, and 
consequent loss of the RAT as a source of hydraulic and electrical 
power in an emergency situation. This AD requires accomplishing the 
actions specified in the Airbus service information described 
previously, except as discussed under ``Differences Between the AD and 
the Airbus Service Bulletin.''

Differences Between the AD and the Airbus Service Bulletin

    Unlike the procedures described in the service bulletin, the intent 
of the EASA airworthiness directive referenced in this AD is to mandate 
the one-time inspection of the anti-stall valve sleeve of the RAT for 
proper installation before determining the part number of the 
modification plate on the hydraulic pump of the RAT. If, after 
beginning the inspection, it is determined that the modification plate 
is already marked with a 'B' showing that the inspection was 
accomplished previously, no further action is required by this AD.
    The service bulletin specifies returning any removed RAT to 
Hamilton Sundstrand; however, this AD does not require that action.

Clarification of Inspection Terminology

    In this AD, the ``inspection'' specified in the service bulletin is 
referred to as a ``general visual inspection.'' We have included the 
definition for a general visual inspection in a note in the proposed 
AD.

Costs of Compliance

    None of the airplanes affected by this action are on the U.S. 
Register. All airplanes affected by this AD are currently operated by 
non-U.S. operators under foreign registry; therefore, they are not 
directly affected by this AD action. However, we consider this AD 
necessary to ensure that the unsafe condition is addressed if any 
affected airplane is imported and placed on the U.S. Register in the 
future.
    If an affected airplane is imported and placed on the U.S. Register 
in the future, the required actions would take about 1 work hour per 
airplane, at an average labor rate of $80 per work hour. Based on these 
figures, the estimated cost of the AD would be $80 per airplane.

FAA's Determination of the Effective Date

    No airplane affected by this AD is currently on the U.S. Register. 
Therefore, providing notice and opportunity for public comment is 
unnecessary before this AD is issued, and this AD may be made effective 
in less than 30 days after it is published in the Federal Register.

Comments Invited

    This AD is a final rule that involves requirements that affect 
flight safety and was not preceded by notice and an opportunity for 
public comment; however, we invite you to submit any relevant written 
data, views, or arguments regarding this AD. Send your comments to an 
address listed in the ADDRESSES section. Include ``Docket No. FAA-2006-
25722; Directorate Identifier 2006-NM-141-AD'' at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of the AD that might 
suggest a need to modify it.
    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 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 
https://dms.dot.gov.

Examining the Docket

    You may 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

[[Page 52412]]

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.

Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to 
issue rules on aviation safety. Subtitle I, section 106, describes the 
authority of the FAA Administrator. Subtitle VII, Aviation Programs, 
describes in more detail the scope of the Agency's authority.
    We are issuing this rulemaking under the authority described in 
subtitle VII, part A, subpart III, section 44701, ``General 
requirements.'' Under that section, Congress charges the FAA with 
promoting safe flight of civil aircraft in air commerce by prescribing 
regulations for practices, methods, and procedures the Administrator 
finds necessary for safety in air commerce. This regulation is within 
the scope of that authority because it addresses an unsafe condition 
that is likely to exist or develop on products identified in this 
rulemaking action.

Regulatory Findings

    We have determined that this AD will not have federalism 
implications under Executive Order 13132. This AD will not have a 
substantial direct effect on the States, on the relationship between 
the national government and the States, or on the distribution of power 
and responsibilities among the various levels of government.
    For the reasons discussed above, I certify that the 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 AD and placed it in the AD docket. See the ADDRESSES 
section for a location to examine the regulatory evaluation.

List of Subjects in 14 CFR Part 39

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

Adoption of the Amendment

0
Accordingly, under the authority delegated to me by the Administrator, 
the FAA amends 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

0
1. The authority citation for part 39 continues to read as follows:

    Authority: 49 U.S.C. 106(g), 40113, 44701.


Sec.  39.13  [Amended]

0
2. The Federal Aviation Administration (FAA) amends Sec.  39.13 by 
adding the following new airworthiness directive (AD):

2006-18-10 Airbus: Amendment 39-14749. Docket No. FAA-2006-25722; 
Directorate Identifier 2006-NM-141-AD.

Effective Date

    (a) This AD becomes effective September 21, 2006.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to Airbus Model A340-541 and -642 airplanes, 
certificated in any category; equipped with a ram air turbine (RAT) 
module, Model ERPS33T, part number (P/N) 772722D or 772722E; serial 
numbers 0001 through 0024 inclusive, and 0101 through 0166 
inclusive, having a Parker hydraulic pump with P/N 4217701 or 
4217702.

Unsafe Condition

    (d) This AD results from reports of failure of the anti-stall 
valve on the hydraulic pump of the RAT during scheduled ground 
tests. We are issuing this AD to prevent failure of the RAT 
hydraulic pump to supply adequate pressure to activate the RAT, and 
consequent loss of the RAT as a source of hydraulic and electrical 
power in an emergency situation.

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/Follow-on Corrective Actions if Necessary

    (f) Within 11 months after the effective date of this AD: Do a 
one-time general visual inspection of the anti-stall valve sleeve of 
the RAT for proper installation, and determine the P/N of the 
modification plate on the hydraulic pump of the RAT, by doing all 
applicable actions, including all applicable follow-on corrective 
actions, in accordance with the Accomplishment Instructions of 
Airbus Service Bulletin A340-29-5010, dated October 10, 2005. All 
corrective actions must be done before further flight. Although the 
service bulletin specifies returning any removed RAT to Hamilton 
Sundstrand, this AD does not require that action.

    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 
enhance visual access to all exposed surfaces in the inspection 
area. This level of inspection is made under normally available 
lighting conditions such as daylight, hangar lighting, flashlight, 
or droplight and may require removal or opening of access panels or 
doors. Stands, ladders, or platforms may be required to gain 
proximity to the area being checked.''


    Note 2: The Airbus service bulletin refers to Hamilton 
Sundstrand Service Bulletin ERPS33T-29-3, dated August 1, 2005, as 
an additional source of service information for accomplishing the 
actions required by paragraph (f) of this AD.

Alternative Methods of Compliance (AMOCs)

    (g)(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.
    (2) Before using any AMOC approved in accordance with Sec.  
39.19 on any airplane to which the AMOC applies, notify the 
appropriate principal inspector in the FAA Flight Standards 
Certificate Holding District Office.

Related Information

    (h) European Aviation Safety Agency (EASA) airworthiness 
directive 2006-0046, dated February 16, 2006, also addresses the 
subject of this AD.

Material Incorporated by Reference

    (i) You must use Airbus Service Bulletin A340-29-5010, excluding 
Appendix 01, dated October 10, 2005, to perform the actions that are 
required by this AD, unless the AD specifies otherwise. The Director 
of the Federal Register approved the incorporation by reference of 
this document in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. 
Contact Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, 
France, for a copy of this service information. You may review 
copies at the Docket Management Facility, U.S. Department of 
Transportation, 400 Seventh Street, SW., Room PL-401, Nassif 
Building, Washington, DC; on the Internet at https://dms.dot.gov; or 
at the National Archives and Records Administration (NARA). For 
information on the availability of this material at the NARA, call 
(202) 741-6030, or go to https://www.archives.gov/federal_
register/code_of_federal_regulations/ibr_
locations.html.

    Issued in Renton, Washington, on August 23, 2006.
Kalene C. Yanamura,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
 [FR Doc. E6-14624 Filed 9-5-06; 8:45 am]
BILLING CODE 4910-13-P

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