Airworthiness Directives; Airbus Model A319, A320, and A321 Series Airplanes, 34636-34638 [05-11707]

Download as PDF 34636 § 111.43 Federal Register / Vol. 70, No. 114 / Wednesday, June 15, 2005 / Rules and Regulations [Amended] 3. In § 111.43, paragraph (a)(2)(iii) is amended by removing ‘‘$50,000¥$549,999.99’’ and adding in its place ‘‘$450,000–549,999.99.’’ I 4. In § 111.44, paragraph (a)(1) is revised to read as follows: I § 111.44 What is the schedule of penalties for 48-hour notices that are not filed or are filed late? (a) * * * (1) Civil money penalty = $110 + (.10 × amount of the contribution(s) not timely reported). * * * * * Dated: June 9, 2005. Scott E. Thomas, Chairman, Federal Election Commission. [FR Doc. 05–11790 Filed 6–14–05; 8:45 am] BILLING CODE 6715–01–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2005–21433; Directorate Identifier 2005–NM–079–AD; Amendment 39–14123; AD 2005–12–07] RIN 2120–AA64 Airworthiness Directives; Airbus Model A319, A320, and A321 Series 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 A319, A320, and A321 series airplanes. This AD requires a onetime ultrasonic inspection for certain airplanes, and repetitive detailed inspections for all airplanes, for cracking in the forward lug of the support rib 5 fitting of both main landing gear (MLG), and repair if necessary. This AD also provides for optional terminating actions. This AD is prompted by a report of a crack found in the forward lug of the right-hand MLG rib 5 fitting during greasing of both MLG pintle bearings. We are issuing this AD to find and fix cracking in the forward lug of the MLG, which could result in failure of the lug and consequent collapse of the MLG during landing. DATES: Effective June 30, 2005. The incorporation by reference of a certain publication listed in the AD is approved by the Director of the Federal Register as of June 30, 2005. VerDate jul<14>2003 16:54 Jun 14, 2005 Jkt 205001 We must receive comments on this AD by August 15, 2005. 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. For service information identified in this AD, contact Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France. You can examine the contents of this AD docket on the Internet at https:// dms.dot.gov, or in person at the Docket Management Facility, U.S. Department of Transportation, 400 Seventh Street SW., room PL–401, on the plaza level of the Nassif Building, Washington, DC. This docket number is FAA–2005– 21433; the directorate identifier for this docket is 2005-NM–079–AD. Examining the Docket You can 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 (DMS) receives them. 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: The ´ ´ Direction Generale de l’Aviation Civile (DGAC), which is the airworthiness authority for France, notified the FAA that an unsafe condition may exist on certain Airbus Model A319, A320, and A321 series airplanes. The DGAC advises that, during greasing of the main FOR FURTHER INFORMATION CONTACT: PO 00000 Frm 00010 Fmt 4700 Sfmt 4700 landing gear (MLG) pintle bearings on a Model A320 series airplane, a crack was found in the forward lug of the righthand MLG rib 5 fitting. The airplane had accumulated 12,634 total flight cycles and 19,710 total flight hours at the time of the findings. Laboratory analysis of the damaged lug revealed that it was fitted with a bushing that had insufficient cadmium plating. Further investigation revealed that certain Airbus Model A319 and A320 series airplanes may have been equipped with bushings from a batch found to have insufficient cadmium plating. The forward lug of the left- and right-hand MLG rib 5 fitting of Airbus Model A319, A320, and A321 series airplanes that do not have Airbus Modification 32025 incorporated could also be susceptible to cracking. These conditions, if not corrected, could result in failure of the lug and consequent collapse of the MLG during landing. Relevant Service Information Airbus has issued Service Bulletin A320–57A1136, dated January 26, 2005 (for Model A319 and A320 series airplanes). The service bulletin describes procedures for a one-time ultrasonic inspection for cracking in the forward lug of the support rib 5 fitting of both MLG. The service bulletin recommends contacting the manufacturer for repair instructions if any cracking is found. The DGAC mandated Service Bulletin A320–57A1136, and a detailed visual inspection as defined in the visual procedures of Airbus A318/A319/A320/ A321 Nondestructive Testing Manual (NTM), Chapter 51–90–00, revision dated February 2003; and issued French airworthiness directive F–2005–035, dated March 2, 2005, to ensure the continued airworthiness of these airplanes in France. Airbus has also issued Service Bulletin A320–57–1118, dated September 5, 2002, and Revision 01, dated August 28, 2003 (for Model A319, A320, and A321 series airplanes). The service bulletins describe procedures for modification of the lugs of the support rib 5 fitting of the left- and right-hand MLG and related investigative and corrective actions if necessary. The modification includes installing new bushings on the lugs of the support rib 5 fitting of the MLG, and applying protective sealant to the bores and spotfaces of the lug. The related investigative and corrective actions include performing a visual inspection for corrosion/damage of the bores and spotfaces of the lug for the pintle pin bushings, and repair if corrosion/ damage is found. Accomplishing this E:\FR\FM\15JNR1.SGM 15JNR1 Federal Register / Vol. 70, No. 114 / Wednesday, June 15, 2005 / Rules and Regulations service bulletins eliminates the need to conduct the inspections described above. 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. Pursuant to this bilateral airworthiness agreement, the DGAC has kept the FAA informed of the situation described above. We have examined the DGAC’s findings, evaluated all pertinent information, and determined that we need to issue an AD for products of this type design that are certificated for operation in the United States. Therefore, we are issuing this AD to require accomplishing the actions specified in Service Bulletin A320– 57A1136 (for Model A319 and A320 series airplanes), described previously, except as discussed under ‘‘Difference Between the AD and Service Bulletin A320–57A1136.’’ This AD also requires repetitive detailed inspections for all airplanes for cracking in the forward lug of the support rib 5 fitting of the MLG, and repair if necessary. This AD also provides for optional terminating actions. Difference Between the AD and Service Bulletin A320–57A1136 The service bulletin specifies that you may contact the manufacturer for repair instructions if cracks are found, but this AD requires you to repair any cracking by using a method that we or the DGAC (or its delegated agent) approve. In light of the type of repair required to address the unsafe condition, and consistent with existing bilateral airworthiness agreements, we have determined that, for this AD, a repair we or the DGAC approve is acceptable for compliance with this AD. Clarification of Inspection Terminology In this AD, the ‘‘detailed visual inspection’’ specified in the French airworthiness directive is referred to as a ‘‘detailed inspection.’’ We have included the definition for a detailed inspection in a note in the AD. Interim Action We consider this AD interim action. We are currently considering requiring the optional modification of the lugs of the support rib 5 fitting of the left- and right-hand MLG, which would constitute terminating action for the repetitive inspections required by this VerDate jul<14>2003 16:54 Jun 14, 2005 Jkt 205001 AD action. However, the planned compliance time for the modification would require us to provide notice and opportunity for prior public comment on the merits of the modification. FAA’s Determination of the Effective Date An unsafe condition exists that requires the immediate adoption of this AD; therefore, providing notice and opportunity for public comment before the AD is issued is impracticable, and good cause exists to make this AD effective in less than 30 days. 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 under ADDRESSES. Include ‘‘Docket No. FAA– 2005–21433; Directorate Identifier 2005NM–079-AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of the AD. We will consider all comments received by the closing date and may amend the 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 AD. Using the search function of our docket Web site, anyone can find and read the comments in any of our dockets, including the name of the individual who sent the comment (or signed the comment on behalf of an association, business, labor union, etc.). You can review the DOT’s complete Privacy Act Statement in the Federal Register published on April 11, 2000 (65 FR 19477–78), or you can visit https://dms.dot.gov. 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 PO 00000 Frm 00011 Fmt 4700 Sfmt 4700 34637 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. 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 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: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The FAA amends § 39.13 by adding the following new airworthiness directive (AD): I 2005–12–07 Airbus: Amendment 39–14123. Docket No. FAA–2005–21433; Directorate Identifier 2005–NM–079–AD. (b) None. (b) None. Effective Date (a) This AD becomes effective June 30, 2005. E:\FR\FM\15JNR1.SGM 15JNR1 34638 Federal Register / Vol. 70, No. 114 / Wednesday, June 15, 2005 / Rules and Regulations Affected ADs (b) None. Applicability (c) This AD applies to Airbus Model A319, A320, and A321 series airplanes, certificated in any category; except those on which Airbus Modification 32025 was done during production. Unsafe Condition (d) This AD was prompted by a report of a crack found in the forward lug of the righthand main landing gear (MLG) rib 5 fitting during greasing of the MLG pintle bearings. The FAA is issuing this AD to find and fix cracking in the forward lug of the MLG, which could result in failure of the lug and consequent collapse of the MLG during landing. 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. One-Time Ultrasonic Inspection/Repair (f) For Model A319 and A320 series airplanes having serial numbers 537 through 625 inclusive: At the earliest of the times specified in paragraphs (f)(1), (f)(2), and (f)(3) of this AD; perform a one-time ultrasonic inspection for cracking in the forward lug of the support rib 5 fitting of the left- and righthand MLG by doing all the actions specified in the Accomplishment Instructions of Airbus Service Bulletin A320–57A1136, dated January 26, 2005. Repair any cracking before further flight, according to a method approved by either the Manager, International Branch, ANM–116, Transport Airplane Directorate, FAA; or the Direction ´ ´ Generale de l’Aviation Civile (DGAC) (or its delegated agent). (1) Within 750 flight cycles after the effective date of this AD. (2) Within 600 flight hours after the effective date of this AD. (3) Within 100 days after the effective date of this AD. Repetitive Detailed Inspections (g) Perform a detailed inspection for cracking in the forward lug of the support rib 5 fitting of the left- and right-hand MLG at the time specified in paragraph (g)(1) or (g)(2) of this AD, as applicable, and repair any cracking before further flight, according to a method approved by either the Manager, International Branch, ANM–116; or the DGAC (or its delegated agent). Accomplishing the actions specified in the Airbus A318/A319/A320/A321 Nondestructive Testing Manual, Chapter 51–90– 00, revision dated February 2003, is one approved method for performing the detailed inspection. Repeat the inspection thereafter at intervals not to exceed 750 flight cycles, 600 flight hours, or 100 days, whichever occurs earliest. (1) For Model A319 and A320 series airplanes having serial numbers 537 through 625 inclusive: Do the detailed inspection within 100 days after the effective date of this AD or at the earliest of the times specified VerDate jul<14>2003 16:54 Jun 14, 2005 Jkt 205001 in paragraphs (g)(1)(i), (g)(1)(ii), and (g)(1)(iii) of this AD, whichever is later. (i) Within 750 flight cycles after accomplishing the ultrasonic inspection. (ii) Within 600 flight hours after accomplishing the ultrasonic inspection. (iii) Within 100 days after accomplishing the ultrasonic inspection. (2) For all other airplanes: Do the detailed inspection at the earliest of the times specified in paragraphs (g)(2)(i), (g)(2)(ii), and (g)(2)(iii) of this AD. (i) Within 750 flight cycles after the effective date of this AD. (ii) Within 600 flight hours after the effective date of this AD. (iii) Within 100 days after the effective date of this AD. 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.’’ Optional Terminating Action (h) Modification of the lugs of the support rib 5 fitting of the left- and right-hand MLG and accomplishment of all related investigative actions and all applicable corrective actions in accordance with Airbus Service Bulletin A320–57–1118, dated September 5, 2002; or Revision 01, dated August 28, 2003; constitutes compliance with the requirements of this AD. (i) Repair of the forward lugs of the support rib 5 fitting of the left- and right-hand MLG in accordance with Airbus A319 Structural Repair Manual, Chapter 5.C., 57–26–13: Airbus A320 Structural Repair Manual, Chapter 5.D., 57–26–13; and Airbus A321 Structural Repair Manual, Chapter 5.D., all revisions dated November 1, 2004, constitutes compliance with the requirements of this AD. Alternative Methods of Compliance (AMOCs) (j) The Manager, International Branch, ANM–116, has the authority to approve AMOCs for this AD, if requested in accordance with the procedures found in 14 CFR 39.19. Related Information (k) French airworthiness directive F–2005– 035, dated March 2, 2005, also addresses the subject of this AD. Material Incorporated by Reference (l) You must use Airbus Service Bulletin A320–57A1136, dated January 26, 2005, to perform the actions that are required by this AD, unless the AD specifies otherwise. The Director of the Federal Register approves the incorporation by reference of this document in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. To get copies of the service information, contact Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France. To view the AD docket, go to the PO 00000 Frm 00012 Fmt 4700 Sfmt 4700 Docket Management Facility, U.S. Department of Transportation, 400 Seventh Street SW., room PL–401, Nassif Building, Washington, DC. To review copies of the service information, go to 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 June 6, 2005. Michael J. Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 05–11707 Filed 6–14–05; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2005–21240; Directorate Identifier 2005–NM–104–AD; Amendment 39–14130; AD 2005–12–14] RIN 2120–AA64 Airworthiness Directives; Boeing Model 767–200, –300, and –400ER Series Airplanes Equipped With DoorMounted Escape Slides 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 Boeing Model 767–200, –300, and –400ER series airplanes. This AD requires an inspection to determine if the door-mounted escape slide/rafts have certain part numbers. For those door-mounted escape slide/rafts having certain part numbers, this AD requires an inspection for excessive tension of the firing cable, and procedures for providing slack in the firing cable or rerouting the firing cable if necessary. This AD is prompted by reports of uncommanded inflation inside the airplane of a door-mounted escape slide/raft located in the passenger compartment. We are issuing this AD to prevent injury to maintenance personnel, passengers, and crew during otherwise normal operating conditions and to prevent interference with evacuation of the airplane during an emergency, due to uncommanded inflation of a door-mounted escape slide/raft. DATES: Effective June 30, 2005. The incorporation by reference of certain publications listed in the AD is E:\FR\FM\15JNR1.SGM 15JNR1

Agencies

[Federal Register Volume 70, Number 114 (Wednesday, June 15, 2005)]
[Rules and Regulations]
[Pages 34636-34638]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 05-117]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2005-21433; Directorate Identifier 2005-NM-079-AD; 
Amendment 39-14123; AD 2005-12-07]
RIN 2120-AA64


Airworthiness Directives; Airbus Model A319, A320, and A321 
Series 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 A319, A320, and A321 series airplanes. This AD 
requires a one-time ultrasonic inspection for certain airplanes, and 
repetitive detailed inspections for all airplanes, for cracking in the 
forward lug of the support rib 5 fitting of both main landing gear 
(MLG), and repair if necessary. This AD also provides for optional 
terminating actions. This AD is prompted by a report of a crack found 
in the forward lug of the right-hand MLG rib 5 fitting during greasing 
of both MLG pintle bearings. We are issuing this AD to find and fix 
cracking in the forward lug of the MLG, which could result in failure 
of the lug and consequent collapse of the MLG during landing.

DATES: Effective June 30, 2005.
    The incorporation by reference of a certain publication listed in 
the AD is approved by the Director of the Federal Register as of June 
30, 2005.
    We must receive comments on this AD by August 15, 2005.

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.
    For service information identified in this AD, contact Airbus, 1 
Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France.
    You can examine the contents of this AD docket on the Internet at 
https://dms.dot.gov, or in person at the Docket Management Facility, 
U.S. Department of Transportation, 400 Seventh Street SW., room PL-401, 
on the plaza level of the Nassif Building, Washington, DC. This docket 
number is FAA-2005-21433; the directorate identifier for this docket is 
2005-NM-079-AD.

Examining the Docket

    You can 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 
(DMS) receives them.

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: The Direction G[eacute]n[eacute]rale de 
l'Aviation Civile (DGAC), which is the airworthiness authority for 
France, notified the FAA that an unsafe condition may exist on certain 
Airbus Model A319, A320, and A321 series airplanes. The DGAC advises 
that, during greasing of the main landing gear (MLG) pintle bearings on 
a Model A320 series airplane, a crack was found in the forward lug of 
the right-hand MLG rib 5 fitting. The airplane had accumulated 12,634 
total flight cycles and 19,710 total flight hours at the time of the 
findings. Laboratory analysis of the damaged lug revealed that it was 
fitted with a bushing that had insufficient cadmium plating. Further 
investigation revealed that certain Airbus Model A319 and A320 series 
airplanes may have been equipped with bushings from a batch found to 
have insufficient cadmium plating. The forward lug of the left- and 
right-hand MLG rib 5 fitting of Airbus Model A319, A320, and A321 
series airplanes that do not have Airbus Modification 32025 
incorporated could also be susceptible to cracking. These conditions, 
if not corrected, could result in failure of the lug and consequent 
collapse of the MLG during landing.

Relevant Service Information

    Airbus has issued Service Bulletin A320-57A1136, dated January 26, 
2005 (for Model A319 and A320 series airplanes). The service bulletin 
describes procedures for a one-time ultrasonic inspection for cracking 
in the forward lug of the support rib 5 fitting of both MLG. The 
service bulletin recommends contacting the manufacturer for repair 
instructions if any cracking is found.
    The DGAC mandated Service Bulletin A320-57A1136, and a detailed 
visual inspection as defined in the visual procedures of Airbus A318/
A319/A320/A321 Nondestructive Testing Manual (NTM), Chapter 51-90-00, 
revision dated February 2003; and issued French airworthiness directive 
F-2005-035, dated March 2, 2005, to ensure the continued airworthiness 
of these airplanes in France.
    Airbus has also issued Service Bulletin A320-57-1118, dated 
September 5, 2002, and Revision 01, dated August 28, 2003 (for Model 
A319, A320, and A321 series airplanes). The service bulletins describe 
procedures for modification of the lugs of the support rib 5 fitting of 
the left- and right-hand MLG and related investigative and corrective 
actions if necessary. The modification includes installing new bushings 
on the lugs of the support rib 5 fitting of the MLG, and applying 
protective sealant to the bores and spotfaces of the lug. The related 
investigative and corrective actions include performing a visual 
inspection for corrosion/damage of the bores and spotfaces of the lug 
for the pintle pin bushings, and repair if corrosion/damage is found. 
Accomplishing this

[[Page 34637]]

service bulletins eliminates the need to conduct the inspections 
described above.

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. Pursuant to this 
bilateral airworthiness agreement, the DGAC has kept the FAA informed 
of the situation described above. We have examined the DGAC's findings, 
evaluated all pertinent information, and determined that we need to 
issue an AD for products of this type design that are certificated for 
operation in the United States.
    Therefore, we are issuing this AD to require accomplishing the 
actions specified in Service Bulletin A320-57A1136 (for Model A319 and 
A320 series airplanes), described previously, except as discussed under 
``Difference Between the AD and Service Bulletin A320-57A1136.'' This 
AD also requires repetitive detailed inspections for all airplanes for 
cracking in the forward lug of the support rib 5 fitting of the MLG, 
and repair if necessary. This AD also provides for optional terminating 
actions.

Difference Between the AD and Service Bulletin A320-57A1136

    The service bulletin specifies that you may contact the 
manufacturer for repair instructions if cracks are found, but this AD 
requires you to repair any cracking by using a method that we or the 
DGAC (or its delegated agent) approve. In light of the type of repair 
required to address the unsafe condition, and consistent with existing 
bilateral airworthiness agreements, we have determined that, for this 
AD, a repair we or the DGAC approve is acceptable for compliance with 
this AD.

Clarification of Inspection Terminology

    In this AD, the ``detailed visual inspection'' specified in the 
French airworthiness directive is referred to as a ``detailed 
inspection.'' We have included the definition for a detailed inspection 
in a note in the AD.

Interim Action

    We consider this AD interim action. We are currently considering 
requiring the optional modification of the lugs of the support rib 5 
fitting of the left- and right-hand MLG, which would constitute 
terminating action for the repetitive inspections required by this AD 
action. However, the planned compliance time for the modification would 
require us to provide notice and opportunity for prior public comment 
on the merits of the modification.

FAA's Determination of the Effective Date

    An unsafe condition exists that requires the immediate adoption of 
this AD; therefore, providing notice and opportunity for public comment 
before the AD is issued is impracticable, and good cause exists to make 
this AD effective in less than 30 days.

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 under ADDRESSES. Include ``Docket No. FAA-2005-21433; 
Directorate Identifier 2005-NM-079-AD'' at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of the AD. We will consider 
all comments received by the closing date and may amend the 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 AD. Using the search function of our docket 
Web site, anyone can find and read the comments in any of our dockets, 
including the name of the individual who sent the comment (or signed 
the comment on behalf of an association, business, labor union, etc.). 
You can review the DOT's complete Privacy Act Statement in the Federal 
Register published on April 11, 2000 (65 FR 19477-78), or you can visit 
https://dms.dot.gov.

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. 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 FAA amends Sec.  39.13 by adding the following new airworthiness 
directive (AD):

2005-12-07 Airbus: Amendment 39-14123. Docket No. FAA-2005-21433; 
Directorate Identifier 2005-NM-079-AD.
    (b) None.
    (b) None.

Effective Date

    (a) This AD becomes effective June 30, 2005.

[[Page 34638]]

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to Airbus Model A319, A320, and A321 series 
airplanes, certificated in any category; except those on which 
Airbus Modification 32025 was done during production.

Unsafe Condition

    (d) This AD was prompted by a report of a crack found in the 
forward lug of the right-hand main landing gear (MLG) rib 5 fitting 
during greasing of the MLG pintle bearings. The FAA is issuing this 
AD to find and fix cracking in the forward lug of the MLG, which 
could result in failure of the lug and consequent collapse of the 
MLG during landing.

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.

One-Time Ultrasonic Inspection/Repair

    (f) For Model A319 and A320 series airplanes having serial 
numbers 537 through 625 inclusive: At the earliest of the times 
specified in paragraphs (f)(1), (f)(2), and (f)(3) of this AD; 
perform a one-time ultrasonic inspection for cracking in the forward 
lug of the support rib 5 fitting of the left- and right-hand MLG by 
doing all the actions specified in the Accomplishment Instructions 
of Airbus Service Bulletin A320-57A1136, dated January 26, 2005. 
Repair any cracking before further flight, according to a method 
approved by either the Manager, International Branch, ANM-116, 
Transport Airplane Directorate, FAA; or the Direction 
G[eacute]n[eacute]rale de l'Aviation Civile (DGAC) (or its delegated 
agent).
    (1) Within 750 flight cycles after the effective date of this 
AD.
    (2) Within 600 flight hours after the effective date of this AD.
    (3) Within 100 days after the effective date of this AD.

Repetitive Detailed Inspections

    (g) Perform a detailed inspection for cracking in the forward 
lug of the support rib 5 fitting of the left- and right-hand MLG at 
the time specified in paragraph (g)(1) or (g)(2) of this AD, as 
applicable, and repair any cracking before further flight, according 
to a method approved by either the Manager, International Branch, 
ANM-116; or the DGAC (or its delegated agent). Accomplishing the 
actions specified in the Airbus A318/A319/A320/A321 Non-destructive 
Testing Manual, Chapter 51-90-00, revision dated February 2003, is 
one approved method for performing the detailed inspection. Repeat 
the inspection thereafter at intervals not to exceed 750 flight 
cycles, 600 flight hours, or 100 days, whichever occurs earliest.
    (1) For Model A319 and A320 series airplanes having serial 
numbers 537 through 625 inclusive: Do the detailed inspection within 
100 days after the effective date of this AD or at the earliest of 
the times specified in paragraphs (g)(1)(i), (g)(1)(ii), and 
(g)(1)(iii) of this AD, whichever is later.
    (i) Within 750 flight cycles after accomplishing the ultrasonic 
inspection.
    (ii) Within 600 flight hours after accomplishing the ultrasonic 
inspection.
    (iii) Within 100 days after accomplishing the ultrasonic 
inspection.
    (2) For all other airplanes: Do the detailed inspection at the 
earliest of the times specified in paragraphs (g)(2)(i), (g)(2)(ii), 
and (g)(2)(iii) of this AD.
    (i) Within 750 flight cycles after the effective date of this 
AD.
    (ii) Within 600 flight hours after the effective date of this 
AD.
    (iii) Within 100 days after the effective date of this AD.

    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.''

Optional Terminating Action

    (h) Modification of the lugs of the support rib 5 fitting of the 
left- and right-hand MLG and accomplishment of all related 
investigative actions and all applicable corrective actions in 
accordance with Airbus Service Bulletin A320-57-1118, dated 
September 5, 2002; or Revision 01, dated August 28, 2003; 
constitutes compliance with the requirements of this AD.
    (i) Repair of the forward lugs of the support rib 5 fitting of 
the left- and right-hand MLG in accordance with Airbus A319 
Structural Repair Manual, Chapter 5.C., 57-26-13: Airbus A320 
Structural Repair Manual, Chapter 5.D., 57-26-13; and Airbus A321 
Structural Repair Manual, Chapter 5.D., all revisions dated November 
1, 2004, constitutes compliance with the requirements of this AD.

Alternative Methods of Compliance (AMOCs)

    (j) The Manager, International Branch, ANM-116, has the 
authority to approve AMOCs for this AD, if requested in accordance 
with the procedures found in 14 CFR 39.19.

Related Information

    (k) French airworthiness directive F-2005-035, dated March 2, 
2005, also addresses the subject of this AD.

Material Incorporated by Reference

    (l) You must use Airbus Service Bulletin A320-57A1136, dated 
January 26, 2005, to perform the actions that are required by this 
AD, unless the AD specifies otherwise. The Director of the Federal 
Register approves the incorporation by reference of this document in 
accordance with 5 U.S.C. 552(a) and 1 CFR part 51. To get copies of 
the service information, contact Airbus, 1 Rond Point Maurice 
Bellonte, 31707 Blagnac Cedex, France. To view the AD docket, go to 
the Docket Management Facility, U.S. Department of Transportation, 
400 Seventh Street SW., room PL-401, Nassif Building, Washington, 
DC. To review copies of the service information, go to 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 June 6, 2005.
Michael J. Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 05-11707 Filed 6-14-05; 8:45 am]
BILLING CODE 4910-13-P

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