Airworthiness Directives; Airbus Model A318, A319, A320, and A321 Airplanes, 71101-71103 [E6-20852]

Download as PDF Federal Register / Vol. 71, No. 236 / Friday, December 8, 2006 / Proposed Rules Unsafe Condition (d) This AD results from loss of a number (No.) 3 window in-flight. We are issuing this AD to detect and correct cracking in the failsafe interlayer of certain No. 2 and No. 3 glass windows, which could result in loss of the window and consequent rapid loss of cabin pressure. Loss of the window could also result in crew communication difficulties or incapacitation of the crew. 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, Related Investigative Actions, and Corrective Action Exception to Compliance Times (g) Where Tables 1, 2, and 3 of paragraph 1.E. of Boeing Alert Service Bulletin 747– 56A2012, dated August 24, 2006, specify counting the compliance time from ‘‘* * * after the date on this service bulletin,’’ this AD requires counting the compliance time from the effective date of this AD. pwalker on PRODPC60 with PROPOSALS Alternative Methods of Compliance (AMOCs) (h)(1) The Manager, Seattle Aircraft Certification Office (ACO), 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. (3) An AMOC that provides an acceptable level of safety may be used for any repair required by this AD, if it is approved by an Authorized Representative for the Boeing Commercial Airplanes Delegation Option Authorization Organization who has been authorized by the Manager, Seattle ACO, to make those findings. For a repair method to be approved, the repair must meet the certification basis of the airplane, and the approval must specifically refer to this AD. 16:40 Dec 07, 2006 Jkt 211001 BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2006–26272; Directorate Identifier 2006–NM–153–AD] RIN 2120–AA64 (f) Inspect the No. 2 and No. 3 windows on the left and right sides of the airplane to determine their part numbers (P/Ns), and do all the applicable related investigative and corrective actions, by accomplishing all of the actions specified in Accomplishment Instructions of Boeing Alert Service Bulletin 747–56A2012, dated August 24, 2006, as applicable. Do all of these actions at the compliance times specified in Tables 1, 2, and 3 of paragraph 1.E. of the service bulletin, as applicable, except as provided by paragraph (g) of this AD. A review of airplane maintenance records is acceptable in lieu of the inspection if the part numbers of the windows can be conclusively determined from that review. Repeat the related investigative and corrective actions thereafter at the interval specified in Table 2 or 3 of the service bulletin, as applicable. VerDate Aug<31>2005 Issued in Renton, Washington, on November 20, 2006. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E6–20863 Filed 12–7–06; 8:45 am] Airworthiness Directives; Airbus Model A318, A319, A320, and A321 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 A318, A319, A320, and A321 airplanes. This proposed AD would require repetitive inspections of the operation of the main landing gear (MLG) door opening sequence to determine if a defective actuator is installed, and replacing any defective actuator with a new actuator. This proposed AD results from reports of slow operation of the MLG door opening/closing sequence due to a defective actuator. We are proposing this AD to detect and correct defective actuators of the MLG door, which could result in slow operation of the MLG door and consequent non-extension of the MLG during an emergency freefall operation. We must receive comments on this proposed AD by January 8, 2007. ADDRESSES: Use one of the following addresses to submit comments on this proposed AD. • DOT Docket Web site: Go to https://dms.dot.gov and follow the instructions for sending your comments electronically. • Government-wide rulemaking Web site: Go to https://www.regulations.gov and follow the instructions for sending your comments electronically. • Mail: Docket Management Facility, U.S. Department of Transportation, 400 Seventh Street, SW., Nassif Building, room PL–401, Washington, DC 20590. • Fax: (202) 493–2251. • Hand Delivery: Room PL–401 on the plaza level of the Nassif Building, 400 Seventh Street, SW., Washington, DATES: PO 00000 Frm 00027 Fmt 4702 Sfmt 4702 71101 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 Dulin, Aerospace Engineer, International Branch, ANM–116, FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, WA 98057– 3356; telephone (425) 227–2141; 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 in the ADDRESSES section. Include the docket number ‘‘FAA–2006–26272; Directorate Identifier 2006–NM–153–AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of the proposed AD. We will consider all comments received by the closing date and may amend the proposed AD in light of those comments. We will post all comments we receive, without change, to https:// dms.dot.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact with FAA personnel concerning this proposed AD. Using the search function of 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 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 European Aviation Safety Agency (EASA), which is the airworthiness E:\FR\FM\08DEP1.SGM 08DEP1 71102 Federal Register / Vol. 71, No. 236 / Friday, December 8, 2006 / Proposed Rules authority for the European Union, notified us that an unsafe condition may exist on all Airbus Model A318, A319, A320, and A321 airplanes. The EASA advises that there have been several reports of slow operation of the MLG door opening/closing sequence due to a defective actuator. This could lead to the generation of electronic centralized aircraft monitor warnings during the landing gear retraction or extension sequence. Investigation revealed that the affected MLG doors were difficult to open manually (unusually high pressure was required to extend the actuator to open the door) due to a problem with the door actuator. The damping ring and associated retaining ring were found broken, with subsequent damage to the damping housing from resulting debris. The resulting high friction delays the MLG extension/retraction sequence. This condition, if not corrected, could result in slow operation of the MLG door and consequent non-extension of the MLG during an emergency freefall operation. Relevant Service Information Airbus has issued Service Bulletin A320–32–1309, dated March 7, 2006. The service bulletin describes procedures for repetitive inspections of the operation of the main landing gear door (MLG) opening sequence to determine if a defective actuator is installed, and replacing any defective actuator with a new actuator. 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 2006–0112, dated May 15, 2006, to ensure the continued airworthiness of these airplanes in France. pwalker on PRODPC60 with PROPOSALS 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. 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 airplanes of this VerDate Aug<31>2005 16:40 Dec 07, 2006 Jkt 211001 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 Proposed AD and the Service Information.’’ Difference Between Proposed AD and the Service Information Although the Accomplishment Instructions of the service bulletin describe procedures for submitting certain information to the manufacturer and sending defective actuators back to the component manufacturer for investigation, this AD does not include those requirements. Interim Action We consider this proposed AD interim action. If final action is later identified, we may consider further rulemaking then. Clarification of Inspection Terminology In this proposed 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 This proposed AD would affect about 700 airplanes of U.S. registry. The proposed inspection 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 proposed AD for U.S. operators is $56,000, or $80 per airplane, per inspection cycle. Authority for This Rulemaking Title 49 of the United States Code specifies the FAA’s authority to issue rules on aviation safety. Subtitle I, section 106, describes the authority of the FAA Administrator. Subtitle VII, Aviation Programs, describes in more detail the scope of the Agency’s authority. We are issuing this rulemaking under the authority described in subtitle VII, part A, subpart III, section 44701, ‘‘General requirements.’’ Under that 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 PO 00000 Frm 00028 Fmt 4702 Sfmt 4702 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 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, 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. § 39.13 [Amended] 2. The Federal Aviation Administration (FAA) amends § 39.13 by adding the following new airworthiness directive (AD): Airbus: Docket No. FAA–2006–26272; Directorate Identifier 2006–NM–153–AD. Comments Due Date (a) The FAA must receive comments on this AD action by January 8, 2007. Affected ADs (b) None. Applicability (c) This AD applies to all Airbus Model A318, A319, A320, and A321 airplanes, certificated in any category. E:\FR\FM\08DEP1.SGM 08DEP1 Federal Register / Vol. 71, No. 236 / Friday, December 8, 2006 / Proposed Rules Unsafe Condition (d) This AD results from reports of slow operation of the main landing gear (MLG) door opening/closing sequence due to a defective actuator. We are issuing this AD to detect and correct defective actuators of the MLG door, which could result in slow operation of the MLG door and consequent non-extension of the MLG during an emergency freefall operation. 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. pwalker on PRODPC60 with PROPOSALS Repetitive Inspections/Replacement (f) At the time specified in paragraph (f)(1) or (f)(2) of this AD, as applicable: Do a general visual inspection of the operation of the MLG door opening sequence to determine if a defective actuator is installed by doing all the applicable actions, including replacing the door actuator, as applicable, specified in the Accomplishment Instructions of Airbus Service Bulletin A320– 32–1309, dated March 7, 2006. Do all applicable replacements before further flight. Repeat the inspection thereafter at intervals not to exceed 900 flight cycles. (1) For airplanes on which a record of the total number of flight cycles on the MLG door actuator is available: Before the accumulation of 3,000 total flight cycles on the MLG door actuator, or within 800 flight cycles after the effective date of this AD, whichever is later. (2) For airplanes on which a record of the total number of flight cycles on the MLG door actuator is not available: With 800 flight cycles after the effective date of this AD. 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.’’ (g) Although the Accomplishment Instructions of Airbus Service Bulletin A320– 32–1309, dated March 7, 2006, specifies submitting certain information to the manufacturer and sending defective actuators back to the component manufacturer for investigation; this AD does not include those requirements. Alternative Methods of Compliance (AMOCs) (h)(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 VerDate Aug<31>2005 16:40 Dec 07, 2006 Jkt 211001 appropriate principal inspector in the FAA Flight Standards Certificate Holding District Office. Related Information (i) EASA airworthiness directive 2006– 0112, dated May 15, 2006, also addresses the subject of this AD. Issued in Renton, Washington, on November 21, 2006. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E6–20852 Filed 12–7–06; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2006–26516; Directorate Identifier 2006–NM–173–AD] RIN 2120–AA64 Airworthiness Directives; Airbus Model A318, A319, A320, and A321 Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Notice of proposed rulemaking (NPRM). AGENCY: SUMMARY: The FAA proposes to supersede an existing airworthiness directive (AD) that applies to all Airbus Model A318–100 and A319–100 series airplanes, Model A320–111 airplanes, and Model A320–200, A321–100, and A321–200 series airplanes. The existing AD currently requires repetitive inspections of the upper and lower attachments of the trimmable horizontal stabilizer actuator (THSA) to measure for proper clearance and to detect cracks, damage, and metallic particles. The existing AD also requires corrective actions, if necessary, and reports of inspection findings. This proposed AD would shorten the repetitive interval for inspecting the upper THSA attachment. This proposed AD results from new test results on the secondary load path, which indicated the need to shorten the repetitive interval for inspecting the upper THSA attachment. We are proposing this AD to detect and correct failure of the THSA’s primary load path, which could result in latent (undetected) loading and eventual failure of the THSA’s secondary load path and consequent uncontrolled movement of the horizontal stabilizer and loss of control of the airplane. DATES: We must receive comments on this proposed AD by January 8, 2007. PO 00000 Frm 00029 Fmt 4702 Sfmt 4702 71103 Use one of the following addresses to submit comments on this proposed AD. • DOT Docket Web site: Go to https://dms.dot.gov and follow the instructions for sending your comments electronically. • Government-wide rulemaking Web site: Go to https://www.regulations.gov and follow the instructions for sending your comments electronically. • Mail: Docket Management Facility; U.S. Department of Transportation, 400 Seventh Street, SW., Nassif Building, Room PL–401, Washington, DC 20590. • 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 Dulin, Aerospace Engineer, International Branch, ANM–116, FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington 98057–3356; telephone (425) 227–2141; fax (425) 227–1149. SUPPLEMENTARY INFORMATION: ADDRESSES: 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 in the ADDRESSES section. Include the docket number ‘‘Docket No. FAA–2006–26516; Directorate Identifier 2006–NM–173– AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of the proposed AD. We will consider all comments received by the closing date and may amend the proposed AD in light of those comments. We will post all comments we receive, without change, to https:// dms.dot.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact with FAA personnel concerning this proposed AD. Using the search function of 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. E:\FR\FM\08DEP1.SGM 08DEP1

Agencies

[Federal Register Volume 71, Number 236 (Friday, December 8, 2006)]
[Proposed Rules]
[Pages 71101-71103]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E6-20852]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2006-26272; Directorate Identifier 2006-NM-153-AD]
RIN 2120-AA64


Airworthiness Directives; Airbus Model A318, A319, A320, and A321 
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 A318, A319, A320, and A321 airplanes. This 
proposed AD would require repetitive inspections of the operation of 
the main landing gear (MLG) door opening sequence to determine if a 
defective actuator is installed, and replacing any defective actuator 
with a new actuator. This proposed AD results from reports of slow 
operation of the MLG door opening/closing sequence due to a defective 
actuator. We are proposing this AD to detect and correct defective 
actuators of the MLG door, which could result in slow operation of the 
MLG door and consequent non-extension of the MLG during an emergency 
freefall operation.

DATES: We must receive comments on this proposed AD by January 8, 2007.

ADDRESSES: Use one of the following addresses to submit comments on 
this proposed AD.
     DOT Docket Web site: Go to https://dms.dot.gov and follow 
the instructions for sending your comments electronically.
     Government-wide rulemaking Web site: Go to https://
www.regulations.gov and follow the instructions for sending your 
comments electronically.
     Mail: Docket Management Facility, U.S. Department of 
Transportation, 400 Seventh Street, SW., Nassif Building, room PL-401, 
Washington, DC 20590.
     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 Dulin, Aerospace Engineer, 
International Branch, ANM-116, FAA, Transport Airplane Directorate, 
1601 Lind Avenue, SW., Renton, WA 98057-3356; telephone (425) 227-2141; 
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 in the ADDRESSES section. Include the docket number ``FAA-2006-
26272; Directorate Identifier 2006-NM-153-AD'' at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of the proposed AD. We will 
consider all comments received by the closing date and may amend the 
proposed AD in light of those comments.
    We will post all comments we receive, without change, to https://
dms.dot.gov, including any personal information you provide. We will 
also post a report summarizing each substantive verbal contact with FAA 
personnel concerning this proposed AD. Using the search function of 
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 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 European Aviation Safety Agency (EASA), which is the 
airworthiness

[[Page 71102]]

authority for the European Union, notified us that an unsafe condition 
may exist on all Airbus Model A318, A319, A320, and A321 airplanes. The 
EASA advises that there have been several reports of slow operation of 
the MLG door opening/closing sequence due to a defective actuator. This 
could lead to the generation of electronic centralized aircraft monitor 
warnings during the landing gear retraction or extension sequence. 
Investigation revealed that the affected MLG doors were difficult to 
open manually (unusually high pressure was required to extend the 
actuator to open the door) due to a problem with the door actuator. The 
damping ring and associated retaining ring were found broken, with 
subsequent damage to the damping housing from resulting debris. The 
resulting high friction delays the MLG extension/retraction sequence. 
This condition, if not corrected, could result in slow operation of the 
MLG door and consequent non-extension of the MLG during an emergency 
freefall operation.

Relevant Service Information

    Airbus has issued Service Bulletin A320-32-1309, dated March 7, 
2006. The service bulletin describes procedures for repetitive 
inspections of the operation of the main landing gear door (MLG) 
opening sequence to determine if a defective actuator is installed, and 
replacing any defective actuator with a new actuator. 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 2006-0112, dated May 15, 2006, 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. 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 airplanes 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 
Proposed AD and the Service Information.''

Difference Between Proposed AD and the Service Information

    Although the Accomplishment Instructions of the service bulletin 
describe procedures for submitting certain information to the 
manufacturer and sending defective actuators back to the component 
manufacturer for investigation, this AD does not include those 
requirements.

Interim Action

    We consider this proposed AD interim action. If final action is 
later identified, we may consider further rulemaking then.

Clarification of Inspection Terminology

    In this proposed 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

    This proposed AD would affect about 700 airplanes of U.S. registry. 
The proposed inspection 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 proposed AD for U.S. operators is $56,000, or $80 
per airplane, per inspection cycle.

Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to 
issue rules on aviation safety. Subtitle I, section 106, describes the 
authority of the FAA Administrator. Subtitle VII, Aviation Programs, 
describes in more detail the scope of the Agency's authority.
    We are issuing this rulemaking under the authority described in 
subtitle VII, part A, subpart III, section 44701, ``General 
requirements.'' Under that 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 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, 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 Federal Aviation Administration (FAA) amends Sec.  39.13 by 
adding the following new airworthiness directive (AD):

Airbus: Docket No. FAA-2006-26272; Directorate Identifier 2006-NM-
153-AD.

Comments Due Date

    (a) The FAA must receive comments on this AD action by January 
8, 2007.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to all Airbus Model A318, A319, A320, and 
A321 airplanes, certificated in any category.

[[Page 71103]]

Unsafe Condition

    (d) This AD results from reports of slow operation of the main 
landing gear (MLG) door opening/closing sequence due to a defective 
actuator. We are issuing this AD to detect and correct defective 
actuators of the MLG door, which could result in slow operation of 
the MLG door and consequent non-extension of the MLG during an 
emergency freefall operation.

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.

Repetitive Inspections/Replacement

    (f) At the time specified in paragraph (f)(1) or (f)(2) of this 
AD, as applicable: Do a general visual inspection of the operation 
of the MLG door opening sequence to determine if a defective 
actuator is installed by doing all the applicable actions, including 
replacing the door actuator, as applicable, specified in the 
Accomplishment Instructions of Airbus Service Bulletin A320-32-1309, 
dated March 7, 2006. Do all applicable replacements before further 
flight. Repeat the inspection thereafter at intervals not to exceed 
900 flight cycles.
    (1) For airplanes on which a record of the total number of 
flight cycles on the MLG door actuator is available: Before the 
accumulation of 3,000 total flight cycles on the MLG door actuator, 
or within 800 flight cycles after the effective date of this AD, 
whichever is later.
    (2) For airplanes on which a record of the total number of 
flight cycles on the MLG door actuator is not available: With 800 
flight cycles after the effective date of this AD.

    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.''

    (g) Although the Accomplishment Instructions of Airbus Service 
Bulletin A320-32-1309, dated March 7, 2006, specifies submitting 
certain information to the manufacturer and sending defective 
actuators back to the component manufacturer for investigation; this 
AD does not include those requirements.

Alternative Methods of Compliance (AMOCs)

    (h)(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

    (i) EASA airworthiness directive 2006-0112, dated May 15, 2006, 
also addresses the subject of this AD.

    Issued in Renton, Washington, on November 21, 2006.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. E6-20852 Filed 12-7-06; 8:45 am]
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