Airworthiness Directives; Airbus Model A319-131, -132, and -133; A320-232 and -233; and A321-131 and -231 Airplanes, 72088-72090 [05-23513]

Download as PDF 72088 Federal Register / Vol. 70, No. 230 / Thursday, December 1, 2005 / Proposed Rules A320–211, –212, –214, –231, –232, and –233 airplanes; and Model A321–111, –112, and –131 airplanes. lenses, etc., may be necessary. Surface cleaning and elaborate procedures may be required.’’ Unsafe Condition (d) This AD results from reports of wear damage to the inboard flap trunnions after incorporation of the terminating modification. We are issuing this AD to detect and correct wear of the inboard flap trunnions, which could lead to loss of flap surface control and consequently result in the flap detaching from the airplane. A detached flap could result in damage to the tail of the airplane. (1) Before accumulating 4,000 total flight hours on the inboard flap trunnion since new. (2) Within 4,000 flight hours after accomplishing paragraph (f) of this AD. (3) Within 600 flight hours after the effective date of this AD. 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 Certain Requirements of AD 2000–24–02 Modification (f) For Model A319–111, –112, –113, –114, –115, –131, –132, and –133 airplanes; Model A320–111 airplanes; Model A320–211, –212, –214, –231, –232, and –233 airplanes; and Model A321–111, –112, and –131 airplanes; except those on which Airbus Modification 26495 has been accomplished in production: Within 18 months after January 8, 2001 (the effective date of AD 2000–24–02), modify the sliding panel driving mechanism of the flap drive trunnions, in accordance with Airbus Service Bulletin A320–27–1117, Revision 02, dated January 18, 2000. Note 1: Accomplishment of the modification required by paragraph (f) of this AD before January 8, 2001, in accordance with Airbus Service Bulletin A320–27–1117, dated July 31, 1997; or Revision 01, dated June 25, 1999, is acceptable for compliance with that paragraph. Requirements of this AD Detailed Inspections (g) For all airplanes: At the latest of the applicable compliance times specified in paragraphs (g)(1), (g)(2), and (g)(3) of this AD, do a detailed inspection of the inboard flap trunnions for any wear marks and of the sliding panels for any cracking at the long edges, and do any corrective actions as applicable, by accomplishing all of the applicable actions specified in the Accomplishment Instructions of Airbus Service Bulletin A320–57–1133, dated July 28, 2005; except as provided by paragraph (h) of this AD. Any corrective actions must be done at the compliance times specified in Figures 5 and 6, as applicable, of the service bulletin; except as provided by paragraph (i) of this AD. Repeat the detailed inspections thereafter at intervals not to exceed 4,000 flight hours. Note 2: For the purposes of this AD, a detailed inspection is: ‘‘An intensive examination of a specific item, installation, or assembly to detect damage, failure, or irregularity. Available lighting is normally supplemented with a direct source of good lighting at an intensity deemed appropriate. Inspection aids such as mirror, magnifying VerDate Aug<31>2005 14:46 Nov 30, 2005 Jkt 208001 DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2005–23142; Directorate Identifier 2005–NM–154–AD] RIN 2120–AA64 No Reporting Requirement (h) Although Airbus Service Bulletin A320–57–1133, dated July 28, 2005, specifies to submit certain information to the manufacturer, this AD does not include that requirement. Airworthiness Directives; Airbus Model A319–131, –132, and –133; A320–232 and –233; and A321–131 and –231 Airplanes AGENCY: Compliance Times (i) Where Airbus Service Bulletin A320– 57–1133, dated July 28, 2005, specifies replacing the sliding panel at the next opportunity, replace it within 600 flight hours after the inspection required by paragraph (g) of this AD. If the trunnion is found damaged during any inspection required by paragraph (g) of this AD, do the corrective actions specified in the service bulletin before further flight. Where the service bulletin specifies contacting the manufacturer for a grace period assessment after replacing the trunnion or flap, contact ´ ´ the FAA or Direction Generale de l′Aviation Civile (DGAC) for the grace period assessment. Alternative Methods of Compliance (AMOCs) (j)(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 14 CFR 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 (k) French airworthiness directive F–2005– 139, dated August 3, 2005, also addresses the subject of this AD. Issued in Renton, Washington, on November 18, 2005. Kalene C. Yanamura, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 05–23514 Filed 11–30–05; 8:45 am] BILLING CODE 4910–13–P PO 00000 Frm 00006 Fmt 4702 Sfmt 4702 Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Notice of proposed rulemaking (NPRM). SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD) for certain Airbus Model A319–131, –132, and –133; A320–232 and –233; and A321–131 and –231 airplanes. This proposed AD would require inspecting for cracks or failure of the primary load path components of the engine forward mount, and corrective action if necessary. This proposed AD also would require removing, re-installing, and re-torquing the attachment bolts for the secondary load path. This proposed AD results from a report that, during modification of certain engine forward mount assemblies of the left and right engines done at an engine shop visit, an incorrect torque was applied to the attachment bolts. We are proposing this AD to prevent structural failure of the secondary load path of the forward engine mount, which, if combined with failure of the primary load path, could result in separation of the engine from the airplane. DATES: We must receive comments on this proposed AD by January 3, 2006. ADDRESSES: Use one of the following addresses to submit comments on this proposed AD. • DOT Docket Web site: Go to http:// dms.dot.gov and follow the instructions for sending your comments electronically. • Government-wide rulemaking Web site: Go to http://www.regulations.gov and follow the instructions for sending your comments electronically. • Mail: Docket Management Facility, U.S. Department of Transportation, 400 Seventh Street, SW., Nassif Building, room PL–401, Washington, DC 20590. • 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. E:\FR\FM\01DEP1.SGM 01DEP1 Federal Register / Vol. 70, No. 230 / Thursday, December 1, 2005 / Proposed Rules 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 98055–4056; 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–2005–23142; Directorate Identifier 2005–NM–154–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 Generale de l’Aviation Civile (DGAC), which is the airworthiness authority for France, notified us that an unsafe condition may VerDate Aug<31>2005 14:46 Nov 30, 2005 Jkt 208001 exist on certain Airbus Model A319– 131, –132, and –133 airplanes; Model A320–232 and –233 airplanes; and Model A321–131 and –231 airplanes. The DGAC advises that, during modification of certain forward engine mount assemblies of the left and right engines done at an engine shop visit, an incorrect torque was applied to the attachment bolts. Lower torque values used on the bolts reduce the bolt fatigue life. The bolts are part of a secondary thrust load path that is only active upon failure of the primary thrust load path. These conditions, if not corrected, could result in separation of the engine from the airplane. Other Relevant Rulemaking On November 30, 1999, we issued AD 99–25–10, amendment 39–11453 (64 FR 68623, December 8, 1999), for certain Airbus Model A319, A320, and A321 series airplanes. That AD requires a onetime inspection of the forward engine mount assembly of the left and right engines to verify that the part number on each assembly is correct; reidentification of the forward engine mount assembly; and follow-on actions, if necessary. That AD was prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. We issued that AD to prevent structural failure of the secondary load path of the forward engine mount, which, if combined with failure of the primary load path, could result in separation of the engine from the airplane. When accomplishing the actions required by that AD during an engine shop visit, an incorrect torque was applied to the attachment bolts. Relevant Service Information Airbus has issued All Operators Telex (AOT) A320–71A1036, Revision 1, dated June 28, 2005. The AOT describes procedures for accomplishing a detailed inspection for cracks or failure of the primary load path components of the engine forward mount, and performing corrective action if necessary. The corrective action involves replacing defective components with new components. The AOT also describes procedures for removing, re-installing, and re-torquing the attachment bolts for the secondary load path. The AOT recommends reporting inspection results to the manufacturer. The DGAC mandated the service information and issued French emergency airworthiness directive UF– 2005–117, dated June 29, 2005, to ensure the continued airworthiness of these airplanes in France. PO 00000 Frm 00007 Fmt 4702 Sfmt 4702 72089 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 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 Among French Airworthiness Directive, Proposed AD, and AOT.’’ Differences Among French Emergency Airworthiness Directive, Proposed AD, and AOT Although the DGAC issued an emergency airworthiness directive to address the unsafe condition of incorrect torque applied to the attachment bolts, we have determined that issuing an immediately adopted rule is not necessary. We have received confirmation that the affected U.S. fleet has accomplished the inspection of the primary load path in accordance with the AOT specified in the proposed AD. Therefore, we have determined that issuing a notice of proposed rulemaking will ensure that the identified unsafe condition is properly addressed. Although the AOT referenced in this proposed AD recommends that inspection results be reported to the manufacturer, this proposed AD does not include that requirement. Costs of Compliance This proposed AD would affect about 131 airplanes of U.S. registry. The proposed inspection would take about 2 work hours per airplane (1 work hour per engine), at an average labor rate of $65 per work hour. Based on these figures, the estimated cost of the proposed inspection for U.S. operators is $17,030, or $130 per airplane. The proposed removal, re-installation, and re-torquing would take about 8 work hours per airplane (4 work hours per engine), at an average labor rate of $65 per work hour. Based on these figures, the estimated cost of the proposed adjustments for U.S. operators is $68,120, or $520 per airplane. E:\FR\FM\01DEP1.SGM 01DEP1 72090 Federal Register / Vol. 70, No. 230 / Thursday, December 1, 2005 / Proposed Rules 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: VerDate Aug<31>2005 14:46 Nov 30, 2005 Jkt 208001 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–2005–23142; Directorate Identifier 2005–NM–154–AD. Comments Due Date (a) The FAA must receive comments on this AD action by January 3, 2006. Affected ADs (b) None. Applicability (c) This AD applies to Airbus Model A319– 131, –132, and –133 airplanes; Model A320– 232 and –233 airplanes; and Model A321– 131 and –231 airplanes; certificated in any category; as identified in Airbus All Operators Telex (AOT) A320–71A1036, Revision 1, dated June 28, 2005. Unsafe Condition (d) This AD results from a report that, during modification of certain engine forward mount assemblies of the left and right engines done at an engine shop visit, an incorrect torque was applied to the attachment bolts. We are issuing this AD to prevent structural failure of the secondary load path of the forward engine mount, which, if combined with failure of the primary load path, could result in separation of the engine from 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. Note 1: For the purposes of this AD, a detailed inspection is: ‘‘An intensive examination of a specific item, installation, or assembly to detect damage, failure, or irregularity. Available lighting is normally supplemented with a direct source of good lighting at an intensity deemed appropriate. Inspection aids such as mirror, magnifying lenses, etc., may be necessary. Surface cleaning and elaborate procedures may be required.’’ Inspection and Corrective Action (f) Perform a detailed inspection for cracks or failure of the primary load path components of the engine forward mount by doing all the applicable actions in accordance with the procedures in AOT A320–71A1036, Revision 1, dated June 28, 2005. Do any corrective action before further flight in accordance with the procedures in the AOT. Perform the actions at the time specified in paragraph (f)(1) or (f)(2) of this AD, as applicable. (1) For Model A321–131 and –231 airplanes: Do the inspection within 5 days after the effective date of this AD. (2) For Model A319–131, –132, and –133 airplanes: Do the inspection within 10 days after the effective date of this AD. (g) For all airplanes: At the applicable time specified in paragraph (g)(1) or (g)(2) of this PO 00000 Frm 00008 Fmt 4702 Sfmt 4702 AD, remove, re-install, and re-torque each of the attachment bolts of the engine forward mount assembly in accordance with the procedures in AOT A320–71A1036, Revision 1, dated June 28, 2005. (1) If the inspection specified in paragraph (f) of this AD was accomplished after the effective date of this AD: Do the actions within 2,250 flight cycles after accomplishing the inspection. (2) If the inspection specified in paragraph (f) of this AD was accomplished before the effective date of this AD: Do the actions within 2,250 flight cycles after the effective date of this AD. Actions Accomplished Previously (h) Inspections, adjustments or repairs done before the effective date of this AD in accordance with the procedures in AOT A320–71A1036, dated June 27, 2005, are acceptable for compliance with the corresponding actions required by this AD. No Reporting Required (i) Although AOT A320–71A1036, Revision 1, dated June 28, 2005, recommends that inspection results be reported to the manufacturer, this AD does not include that requirement. Alternative Methods of Compliance (AMOCs) (j)(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 (k) French emergency airworthiness directive UF–2005–117, dated June 29, 2005, also addresses the subject of this AD. Issued in Renton, Washington, on November 18, 2005. Kalene C. Yanamura, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 05–23513 Filed 11–30–05; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF ENERGY Federal Energy Regulatory Commission 18 CFR Part 284 [Docket No. RM06–5–000] Amendments to Codes of Conduct for Unbundled Sales Service and for Persons Holding Blanket Marketing Certificates November 21, 2005. Federal Energy Regulatory Commission, DOE. AGENCY: E:\FR\FM\01DEP1.SGM 01DEP1

Agencies

[Federal Register Volume 70, Number 230 (Thursday, December 1, 2005)]
[Proposed Rules]
[Pages 72088-72090]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 05-23513]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2005-23142; Directorate Identifier 2005-NM-154-AD]
RIN 2120-AA64


Airworthiness Directives; Airbus Model A319-131, -132, and -133; 
A320-232 and -233; and A321-131 and -231 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 certain Airbus Model A319-131, -132, and -133; A320-232 and -233; 
and A321-131 and -231 airplanes. This proposed AD would require 
inspecting for cracks or failure of the primary load path components of 
the engine forward mount, and corrective action if necessary. This 
proposed AD also would require removing, re-installing, and re-torquing 
the attachment bolts for the secondary load path. This proposed AD 
results from a report that, during modification of certain engine 
forward mount assemblies of the left and right engines done at an 
engine shop visit, an incorrect torque was applied to the attachment 
bolts. We are proposing this AD to prevent structural failure of the 
secondary load path of the forward engine mount, which, if combined 
with failure of the primary load path, could result in separation of 
the engine from the airplane.

DATES: We must receive comments on this proposed AD by January 3, 2006.

ADDRESSES: Use one of the following addresses to submit comments on 
this proposed AD.
     DOT Docket Web site: Go to http://dms.dot.gov and follow 
the instructions for sending your comments electronically.
     Government-wide rulemaking Web site: Go to http://
www.regulations.gov and follow the instructions for sending your 
comments electronically.
     Mail: Docket Management Facility, U.S. Department of 
Transportation, 400 Seventh Street, SW., Nassif Building, room PL-401, 
Washington, DC 20590.
     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.

[[Page 72089]]

    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 98055-4056; 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-2005-
23142; Directorate Identifier 2005-NM-154-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 A319-131, -132, and 
-133 airplanes; Model A320-232 and -233 airplanes; and Model A321-131 
and -231 airplanes. The DGAC advises that, during modification of 
certain forward engine mount assemblies of the left and right engines 
done at an engine shop visit, an incorrect torque was applied to the 
attachment bolts. Lower torque values used on the bolts reduce the bolt 
fatigue life. The bolts are part of a secondary thrust load path that 
is only active upon failure of the primary thrust load path. These 
conditions, if not corrected, could result in separation of the engine 
from the airplane.

Other Relevant Rulemaking

    On November 30, 1999, we issued AD 99-25-10, amendment 39-11453 (64 
FR 68623, December 8, 1999), for certain Airbus Model A319, A320, and 
A321 series airplanes. That AD requires a one-time inspection of the 
forward engine mount assembly of the left and right engines to verify 
that the part number on each assembly is correct; re-identification of 
the forward engine mount assembly; and follow-on actions, if necessary. 
That AD was prompted by issuance of mandatory continuing airworthiness 
information by a foreign civil airworthiness authority. We issued that 
AD to prevent structural failure of the secondary load path of the 
forward engine mount, which, if combined with failure of the primary 
load path, could result in separation of the engine from the airplane. 
When accomplishing the actions required by that AD during an engine 
shop visit, an incorrect torque was applied to the attachment bolts.

Relevant Service Information

    Airbus has issued All Operators Telex (AOT) A320-71A1036, Revision 
1, dated June 28, 2005. The AOT describes procedures for accomplishing 
a detailed inspection for cracks or failure of the primary load path 
components of the engine forward mount, and performing corrective 
action if necessary. The corrective action involves replacing defective 
components with new components. The AOT also describes procedures for 
removing, re-installing, and re-torquing the attachment bolts for the 
secondary load path. The AOT recommends reporting inspection results to 
the manufacturer.
    The DGAC mandated the service information and issued French 
emergency airworthiness directive UF-2005-117, dated June 29, 2005, to 
ensure the continued airworthiness of these airplanes in France.

FAA's Determination and Requirements of the Proposed AD

    These airplane models are manufactured in France and are type 
certificated for operation in the United States under the provisions of 
section 21.29 of the Federal Aviation Regulations (14 CFR 21.29) and 
the applicable bilateral airworthiness agreement. Pursuant to this 
bilateral airworthiness agreement, the DGAC has kept the FAA informed 
of the situation described above. We have examined the DGAC's findings, 
evaluated all pertinent information, and determined that we need to 
issue an AD for 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 Among 
French Airworthiness Directive, Proposed AD, and AOT.''

Differences Among French Emergency Airworthiness Directive, Proposed 
AD, and AOT

    Although the DGAC issued an emergency airworthiness directive to 
address the unsafe condition of incorrect torque applied to the 
attachment bolts, we have determined that issuing an immediately 
adopted rule is not necessary. We have received confirmation that the 
affected U.S. fleet has accomplished the inspection of the primary load 
path in accordance with the AOT specified in the proposed AD. 
Therefore, we have determined that issuing a notice of proposed 
rulemaking will ensure that the identified unsafe condition is properly 
addressed.
    Although the AOT referenced in this proposed AD recommends that 
inspection results be reported to the manufacturer, this proposed AD 
does not include that requirement.

Costs of Compliance

    This proposed AD would affect about 131 airplanes of U.S. registry.
    The proposed inspection would take about 2 work hours per airplane 
(1 work hour per engine), at an average labor rate of $65 per work 
hour. Based on these figures, the estimated cost of the proposed 
inspection for U.S. operators is $17,030, or $130 per airplane.
    The proposed removal, re-installation, and re-torquing would take 
about 8 work hours per airplane (4 work hours per engine), at an 
average labor rate of $65 per work hour. Based on these figures, the 
estimated cost of the proposed adjustments for U.S. operators is 
$68,120, or $520 per airplane.

[[Page 72090]]

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-2005-23142; Directorate Identifier 2005-NM-
154-AD.

Comments Due Date

    (a) The FAA must receive comments on this AD action by January 
3, 2006.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to Airbus Model A319-131, -132, and -133 
airplanes; Model A320-232 and -233 airplanes; and Model A321-131 and 
-231 airplanes; certificated in any category; as identified in 
Airbus All Operators Telex (AOT) A320-71A1036, Revision 1, dated 
June 28, 2005.

Unsafe Condition

    (d) This AD results from a report that, during modification of 
certain engine forward mount assemblies of the left and right 
engines done at an engine shop visit, an incorrect torque was 
applied to the attachment bolts. We are issuing this AD to prevent 
structural failure of the secondary load path of the forward engine 
mount, which, if combined with failure of the primary load path, 
could result in separation of the engine from 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.

    Note 1: For the purposes of this AD, a detailed inspection is: 
``An intensive examination of a specific item, installation, or 
assembly to detect damage, failure, or irregularity. Available 
lighting is normally supplemented with a direct source of good 
lighting at an intensity deemed appropriate. Inspection aids such as 
mirror, magnifying lenses, etc., may be necessary. Surface cleaning 
and elaborate procedures may be required.''

Inspection and Corrective Action

    (f) Perform a detailed inspection for cracks or failure of the 
primary load path components of the engine forward mount by doing 
all the applicable actions in accordance with the procedures in AOT 
A320-71A1036, Revision 1, dated June 28, 2005. Do any corrective 
action before further flight in accordance with the procedures in 
the AOT. Perform the actions at the time specified in paragraph 
(f)(1) or (f)(2) of this AD, as applicable.
    (1) For Model A321-131 and -231 airplanes: Do the inspection 
within 5 days after the effective date of this AD.
    (2) For Model A319-131, -132, and -133 airplanes: Do the 
inspection within 10 days after the effective date of this AD.
    (g) For all airplanes: At the applicable time specified in 
paragraph (g)(1) or (g)(2) of this AD, remove, re-install, and re-
torque each of the attachment bolts of the engine forward mount 
assembly in accordance with the procedures in AOT A320-71A1036, 
Revision 1, dated June 28, 2005.
    (1) If the inspection specified in paragraph (f) of this AD was 
accomplished after the effective date of this AD: Do the actions 
within 2,250 flight cycles after accomplishing the inspection.
    (2) If the inspection specified in paragraph (f) of this AD was 
accomplished before the effective date of this AD: Do the actions 
within 2,250 flight cycles after the effective date of this AD.

Actions Accomplished Previously

    (h) Inspections, adjustments or repairs done before the 
effective date of this AD in accordance with the procedures in AOT 
A320-71A1036, dated June 27, 2005, are acceptable for compliance 
with the corresponding actions required by this AD.

No Reporting Required

    (i) Although AOT A320-71A1036, Revision 1, dated June 28, 2005, 
recommends that inspection results be reported to the manufacturer, 
this AD does not include that requirement.

Alternative Methods of Compliance (AMOCs)

    (j)(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

    (k) French emergency airworthiness directive UF-2005-117, dated 
June 29, 2005, also addresses the subject of this AD.

    Issued in Renton, Washington, on November 18, 2005.
Kalene C. Yanamura,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 05-23513 Filed 11-30-05; 8:45 am]
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