Airworthiness Directives; Airbus Model A300 B4-600, B4-600R, and F4-600R Series Airplanes, and Model A300 C4-605R Variant F Airplanes (Collectively Called A300-600 Series Airplanes), 53559-53562 [E6-14942]

Download as PDF Federal Register / Vol. 71, No. 176 / Tuesday, September 12, 2006 / Rules and Regulations Credit for Original Issue of Service Bulletin (i) For Model DC–10–10 and DC–10–10F airplanes; Model DC–10–15 airplanes; Model DC–10–30 and DC–10–30F (KC–10A and KDC–10) airplanes; Model DC–10–40 and DC–10–40F airplanes; and Model MD–10– 10F and MD–10–30F airplanes: Actions done before the effective date of this AD in accordance with Boeing Alert Service Bulletin DC10–29A146, dated April 30, 2001, are acceptable for compliance with the corresponding requirements of this AD. Alternative Methods of Compliance (AMOCs) (j)(1) The Manager, Los Angeles 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 53559 which the AMOC applies, notify the appropriate principal inspector in the FAA Flight Standards Certificate Holding District Office. Material Incorporated by Reference (k) You must use the service information identified in Table 1 of this AD to perform the actions that are required by this AD, unless the AD specifies otherwise. TABLE 1—MATERIAL INCORPORATED BY REFERENCE Service bulletin Revision level Boeing Alert Service Bulletin DC10–29A146 ........................................................................................... Boeing Alert Service Bulletin MD11–29A060 ........................................................................................... McDonnell Douglas DC–10 Service Bulletin 29–135 ............................................................................... 1 ..................... Original ........... Original ........... The Director of the Federal Register approved the incorporation by reference of these documents in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Contact Boeing Commercial Airplanes, Long Beach Division, 3855 Lakewood Boulevard, Long Beach, California 90846, Attention: Data and Service Management, Dept. C1–L5A (D800–0024), for a copy of this service information. You may review copies at the Docket Management Facility, U.S. Department of Transportation, 400 Seventh Street, SW., Room PL–401, Nassif Building, Washington, DC; on the Internet at https://dms.dot.gov; or at the National Archives and Records Administration (NARA). For information on the availability of this material at the NARA, call (202) 741–6030, or go to https:// www.archives.gov/federal_register/ code_of_federal_regulations/ ibr_locations.html. Issued in Renton, Washington, on September 1, 2006. Kalene C. Yanamura, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E6–14939 Filed 9–11–06; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2006–25047; Directorate Identifier 2006–NM–028–AD; Amendment 39–14759; AD 2006–19–02] RIN 2120–AA64 jlentini on PROD1PC65 with RULES Airworthiness Directives; Airbus Model A300 B4–600, B4–600R, and F4–600R Series Airplanes, and Model A300 C4– 605R Variant F Airplanes (Collectively Called A300–600 Series Airplanes) Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: VerDate Aug<31>2005 15:49 Sep 11, 2006 Jkt 205001 SUMMARY: The FAA is superseding an existing airworthiness directive (AD), which applies to certain Airbus Model A300–600 series airplanes. That AD currently requires repetitive eddy current inspections to detect cracks of the outer skin of the fuselage at certain frames, and repair or reinforcement of the structure at the frames, if necessary. That AD also requires eventual reinforcement of the structure at certain frames, which, when accomplished, terminates the repetitive inspections. This new AD requires, for airplanes that were previously reinforced but not repaired in accordance with the existing AD, a one-time inspection for cracking of the fuselage outer skin at frames 28A and 30A above stringer 30, and repair if necessary. This AD results from a report that the previously required actions were not sufficient to correct cracking before the structural reinforcement was installed. We are issuing this AD to prevent such fatigue cracking, which could result in reduced structural integrity, and consequent rapid decompression of the airplane. This AD becomes effective October 17, 2006. The Director of the Federal Register approved the incorporation by reference of certain publications listed in the AD as of October 17, 2006. On August 4, 1997 (62 FR 35072, June 30, 1997), the Director of the Federal Register approved the incorporation by reference of Airbus Service Bulletin A300–53–6045, dated March 21, 1995, as revised by Change Notice No. O.A., dated June 1, 1995; and Airbus Service Bulletin A300–53–6037, dated March 21, 1995. ADDRESSES: You may examine the 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, DATES: PO 00000 Frm 00015 Fmt 4700 Sfmt 4700 Date April 6, 2005. April 30, 2001. September 8, 1993. SW., Nassif Building, Room PL–401, Washington, DC. Contact Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France, for service information identified in this AD. FOR FURTHER INFORMATION CONTACT: Tom Stafford, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue, SW., Renton, Washington 98057–3356; telephone (425) 227–1622; fax (425) 227–1149. SUPPLEMENTARY INFORMATION: Examining the Docket You may examine the airworthiness directive (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 street address stated in the ADDRESSES section. Discussion The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to include an AD that supersedes AD 97–14–02, amendment 39–10059 (62 FR 35072, June 30, 1997). The existing AD applies to certain Airbus Model A300–600 series airplanes. That NPRM was published in the Federal Register on June 15, 2006 (71 FR 34563). That NPRM proposed to continue to require repetitive eddy current inspections to detect cracks of the outer skin of the fuselage at certain frames, and repair or reinforcement of the structure at the frames, if necessary. That NPRM also proposed to continue to require eventual reinforcement of the structure at certain frames, which, when accomplished, terminates the repetitive inspections. That NPRM also proposed E:\FR\FM\12SER1.SGM 12SER1 53560 Federal Register / Vol. 71, No. 176 / Tuesday, September 12, 2006 / Rules and Regulations to require, for airplanes that were previously reinforced but not repaired in accordance with the existing AD, a one-time inspection for cracking of the fuselage outer skin at frames 28A and 30A above stringer 30, and repair if necessary. Comments We provided the public the opportunity to participate in the development of this AD. No comments have been received on the NPRM or on the determination of the cost to the public. Conclusion We have carefully reviewed the available data and determined that air safety and the public interest require adopting the AD as proposed. Costs of Compliance This AD will affect about 53 airplanes of U.S. registry. The following table provides the estimated costs for U.S. operators to comply with this AD. The average labor rate is $80 per work hour. ESTIMATED COSTS Work hours Action Inspection (required by AD 97–14–02) ................ Reinforcement (required by AD 97–14–02) ......... Inspection (new required action) ......................... 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. jlentini on PROD1PC65 with RULES We have determined that this AD will not have federalism implications under Executive Order 13132. This AD will not have a substantial direct effect on the States, on the relationship between the national government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify that this AD: (1) Is not a ‘‘significant regulatory action’’ under Executive Order 12866; (2) Is not a ‘‘significant rule’’ under 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. 15:49 Sep 11, 2006 None $7,200 None Cost per airplane We prepared a regulatory evaluation of the estimated costs to comply with this AD and placed it in the AD docket. See the ADDRESSES section for a location to examine the regulatory evaluation. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. Jkt 205001 Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: I PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: I Authority: 49 U.S.C. 106(g), 40113, 44701. [Amended] 2. The Federal Aviation Administration (FAA) amends § 39.13 by removing amendment 39–10059 (62 FR 35072, June 30, 1997) and by adding the following new airworthiness directive (AD): 2006–19–02 Airbus: Amendment 39–14759. Docket No. FAA–2006–25047; Directorate Identifier 2006–NM–028–AD. Effective Date (a) This AD becomes effective October 17, 2006. Affected ADs (b) This AD supersedes AD 97–14–02. Applicability (c) This AD applies to Airbus Model A300 B4–601, B4–603, B4–620, B4–622, B4–605R, B4–622R, F4–605R, F4–622R, and C4–605R Variant F airplanes, certificated in any category, except those on which Airbus Modification 8683 has been done. PO 00000 Frm 00016 Fmt 4700 Sfmt 4700 $4,240, per inspection cycle. $775,920. $4,240. Unsafe Condition (d) This AD results from a report that the previously required actions were not sufficient to correct cracking before the structural reinforcement was installed. We are issuing this AD to prevent fatigue cracking of the outer skin of the fuselage at certain frames, which could result in reduced structural integrity, and consequent rapid decompression of the airplane. Compliance Adoption of the Amendment § 39.13 Fleet cost $80, per inspection cycle ............ $14,640 ....................................... $80 .............................................. I Regulatory Findings VerDate Aug<31>2005 1 93 1 Parts (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 the Requirements of AD 97– 14–02 (f) Prior to the accumulation of 14,100 total flight cycles, or within 12 months after August 4, 1997 (the effective date of AD 97– 14–02), whichever occurs later, conduct an eddy current inspection to detect cracking of the fuselage outer skin at frames 28A and 30A above stringer 30, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300–53–6045, dated March 21, 1995, as revised by Change Notice No. O.A., dated June 1, 1995; or Airbus Service Bulletin A300–53–6045, Revision 03, dated October 28, 2004. After the effective date of this AD, only Revision 03 may be used. After the effective date of this AD, the initial eddy current inspection and all applicable repairs required by this paragraph must be done before doing the reinforcement specified in paragraph (g) of this AD. (1) If no cracking is found, repeat the eddy current inspection thereafter at intervals not to exceed 4,500 flight cycles. (2) If any cracking is found that is within the limits specified in the service bulletin: Prior to further flight do the actions in paragraph (f)(2)(i) or (f)(2)(ii) of this AD. After the effective date of this AD, only Airbus Service Bulletin A300–53–6045, Revision 03, dated October 28, 2004, may be used for the repair specified in paragraph (f)(2)(i) of this AD; and the reinforcement option specified in paragraph (f)(2)(ii) of this AD is not allowed in accordance with this paragraph. E:\FR\FM\12SER1.SGM 12SER1 Federal Register / Vol. 71, No. 176 / Tuesday, September 12, 2006 / Rules and Regulations (i) Repair in accordance with paragraph 2.D. of the Accomplishment Instructions of Airbus Service Bulletin A300–53–6045, dated March 21, 1995, as revised by Change Notice No. O.A., dated June 1, 1995; or paragraph 3.C. of the Accomplishment Instructions of Airbus Service Bulletin A300– 53–6045, Revision 03, dated October 28, 2004. After the repair, repeat the eddy current inspection thereafter at intervals not to exceed 4,500 flight cycles. (ii) Reinforce the structure at frames 28 and 29, and at frames 30 and 31, between stringers 29 and 30, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300–53–6037, dated March 21, 1995; or Airbus Service Bulletin A300– 53–6037, Revision 02, dated October 28, 2004. Such reinforcement constitutes terminating action for the repetitive inspections required by this AD. (3) If any cracking is found that is outside the limits specified in the service bulletin: Prior to further flight, reinforce the structure at frames 28 and 29, and at frames 30 and 31, between stringers 29 and 30, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300– 53–6037, dated March 21, 1995; or Airbus Service Bulletin A300–53–6037, Revision 02, dated October 28, 2004. After the effective date of this AD, only Revision 02 may be used. Such reinforcement constitutes terminating action for the repetitive inspections required by this AD. (g) Within 5 years after August 4, 1997: Reinforce the structure at frames 28 and 29, and at frames 30 and 31, between stringers 29 and 30, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300–53–6037, dated March 21, 1995; or Airbus Service Bulletin A300– 53–6037, Revision 02, dated October 28, 2004. After the effective date of this AD, only Revision 02 may be used. Such reinforcement constitutes terminating action for the repetitive inspections required by this AD. After the effective date of this AD, the initial eddy current inspection and all applicable repairs required by paragraph (f) of this AD must be done before doing the reinforcement. 53561 New Requirements of This AD Inspection and Corrective Action (h) For airplanes that meet the conditions of both paragraphs (h)(1) and (h)(2) of this AD: Within 2,400 flight cycles or 18 months after the effective date of this AD, whichever occurs first, conduct an eddy current inspection to detect cracking of the fuselage outer skin at frames 28A and 30A above stringer 30, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300–53–6045, Revision 03, dated October 28, 2004. If no cracking is found: No further action is required by this paragraph. If any cracking is found: Before further flight, repair the cracking using 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) Airplanes that were reinforced before the effective date of this AD in accordance with any service bulletin specified in Table 1 of this AD. TABLE 1.—REINFORCEMENT SERVICE BULLETINS Airbus service bulletin Revision level A300–53–6037 .............................................................................................................................................. Original ...... 1 ................. 02 ............... Date March 21, 1995. February 3, 1999. October 28, 2004. (2) Airplanes that were not inspected and repaired in accordance with any service bulletin specified in Table 2 of this AD. TABLE 2.—INSPECTION AND REPAIR SERVICE BULLETINS Airbus service bulletin Revision level A300–53–6045 .............................................................................................................................................. Original ...... 01 ............... 02 ............... 03 ............... Alternative Methods of Compliance (AMOCs) (i)(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 Date March 21, 1995. August 25, 1997. May 2, 1999. October 28, 2004. Material Incorporated by Reference (k) You must use the service information identified in Table 3 of this AD to perform the actions that are required by this AD, unless the AD specifies otherwise. (j) French airworthiness directive F–2005– 002, dated January 5, 2005, also addresses the subject of this AD. TABLE 3.—MATERIAL INCORPORATED BY REFERENCE jlentini on PROD1PC65 with RULES Airbus service bulletin Revision level A300–53–6037 .............................................................................................................................................. A300–53–6037 .............................................................................................................................................. A300–53–6045 .............................................................................................................................................. A300–53–6045, as revised by Change Notice No. O.A., dated June 1, 1995 ............................................ Original ...... 02 ............... 03 ............... Original ...... VerDate Aug<31>2005 15:49 Sep 11, 2006 Jkt 205001 PO 00000 Frm 00017 Fmt 4700 Sfmt 4700 E:\FR\FM\12SER1.SGM 12SER1 Date March 21, 1995. October 28, 2004. October 28, 2004. March 21, 1995. 53562 Federal Register / Vol. 71, No. 176 / Tuesday, September 12, 2006 / Rules and Regulations (1) The Director of the Federal Register approved the incorporation by reference of Airbus Service Bulletin A300–53–6037, Revision 02, dated October 28, 2004; and Airbus Service Bulletin A300–53–6045, Revision 03, dated October 28, 2004; in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. (2) On August 4, 1997 (62 FR 35072, June 30, 1997), the Director of the Federal Register approved the incorporation by reference of Airbus Service Bulletin A300–53–6045, dated March 21, 1995, as revised by Change Notice No. O.A., dated June 1, 1995; and Airbus Service Bulletin A300–53–6037, dated March 21, 1995. (3) Contact Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France, for a copy of this service information. You may review copies at the Docket Management Facility, U.S. Department of Transportation, 400 Seventh Street, SW., Room PL–401, Nassif Building, Washington, DC; on the Internet at https://dms.dot.gov; or at the National Archives and Records Administration (NARA). For information on the availability of this material at the NARA, call (202) 741–6030, or go to https:// www.archives.gov/federal_register/ code_of_federal_regulations/ ibr_locations.html. Issued in Renton, Washington, on September 1, 2006. Kalene C. Yanamura, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E6–14942 Filed 9–11–06; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2006–25746; Directorate Identifier 2006–NM–151–AD; Amendment 39–14750; AD 2006–18–11] RIN 2120–AA64 Airworthiness Directives; Boeing Model 737–200, –300, –400, and –500 Series Airplanes Equipped With an Auxiliary Fuel System Installed in Accordance With Supplemental Type Certificate (STC) SA83NE, SA1078NE, SA725NE, ST00040NY, or ST01337NY Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule; request for comments. jlentini on PROD1PC65 with RULES AGENCY: SUMMARY: The FAA is adopting a new airworthiness directive (AD) for certain Boeing Model 737–200, –300, –400, and –500 series airplanes equipped with an VerDate Aug<31>2005 15:49 Sep 11, 2006 Jkt 205001 auxiliary fuel system installed in accordance with STC SA83NE, SA1078NE, SA725NE, ST00040NY, or ST01337NY. This AD requires a onetime deactivation of the auxiliary fuel system, repetitive venting of the auxiliary fuel tanks, and revising the Limitations section of the airplane flight manual to limit the maximum cargo weight. This AD results from a reevaluation of the floor structure and cargo barriers conducted by the STC holder. We are issuing this AD to prevent structural overload of the auxiliary fuel tank support structure, which could cause the floor beams to fail and resultant damage to the primary flight controls and the auxiliary power unit fuel lines that pass through the floor beams, and consequent loss of control of the airplane. We are also issuing this AD to prevent structural overload of the cargo barriers, which could cause the barriers to fail, allowing the cargo to shift, resulting in possible damage to the auxiliary fuel tanks, residual fuel leakage, and consequent increased risk of a fire. DATES: This AD becomes effective September 27, 2006. The Director of the Federal Register approved the incorporation by reference of certain publications listed in the AD as of September 27, 2006. We must receive comments on this AD by November 13, 2006. ADDRESSES: Use one of the following addresses to submit comments on this AD. • DOT Docket Web site: Go to https://dms.dot.gov and follow the instructions for sending your comments electronically. • Government-wide rulemaking Web site: Go to https://www.regulations.gov and follow the instructions for sending your comments electronically. • Mail: Docket Management Facility; U.S. Department of Transportation, 400 Seventh Street, SW., Nassif Building, room PL–401, Washington, DC 20590. • Fax: (202) 493–2251. • Hand Delivery: Room PL–401 on the plaza level of the Nassif Building, 400 Seventh Street, SW., Washington, DC, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. Contact PATS Aircraft, LLC, Product Support, 21652 Nanticoke Avenue, Georgetown, Delaware 19947, for service information identified in this AD. Jon Hjelm, Aerospace Engineer, Airframe and Propulsion Branch, ANE–171, FAA, FOR FURTHER INFORMATION CONTACT: PO 00000 Frm 00018 Fmt 4700 Sfmt 4700 New York Aircraft Certification Office, 1600 Stewart Avenue, Suite 410, Westbury, New York 11590; telephone (516) 228–7323; fax (516) 794–5531. SUPPLEMENTARY INFORMATION: Discussion PATS Aircraft (holder of Supplemental Type Certificates (STC) SA83NE, SA1078NE, SA725NE, ST00040NY, and ST01337NY) notified us that it has determined that Boeing Model 737–200, –300, –400, and –500 series airplanes equipped with an auxiliary fuel tank system installed by STC SA83NE, SA1078NE, SA725NE, ST00040NY, or ST01337NY, have insufficient structural strength in the auxiliary fuel tank support structure. The STC holder has also determined that the cargo barriers have insufficient structural strength if subjected to emergency landing loads with the cargo load weights listed in the existing airplane flight manual (AFM) supplements. These determinations were based on a new structural analysis resulting from a re-evaluation of the floor structure and cargo barriers conducted by the STC holder. Structural overload of the auxiliary fuel tank support structure could cause the floor beams to fail, resulting in damage to the primary flight controls and the auxiliary power unit (APU) fuel lines that pass through the floor beams, and consequent loss of control of the airplane. Structural overload of the cargo barriers could cause the barriers to fail, allowing the cargo to shift, resulting in possible damage to the auxiliary fuel tanks, residual fuel leakage, and consequent increased risk of a fire. Relevant Service Information We have reviewed the PATS Aircraft service bulletins listed in the table below. These service bulletins describe procedures for deactivating the auxiliary fuel system, which, for certain airplanes, includes installing new cargo loading weight limit and ‘‘INOP’’ placards, depending on the airplane configuration. The service bulletins also describe procedures for venting any residual air pressure from the auxiliary fuel tanks following each flight. For certain airplanes, paragraph I.D. (‘‘Description’’) of the service bulletins describes limiting the maximum cargo weight (as specified on the new cargo weight placards) in the forward and aft cargo compartments, as applicable, depending on the STC configuration of the airplane. E:\FR\FM\12SER1.SGM 12SER1

Agencies

[Federal Register Volume 71, Number 176 (Tuesday, September 12, 2006)]
[Rules and Regulations]
[Pages 53559-53562]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E6-14942]

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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2006-25047; Directorate Identifier 2006-NM-028-AD;
Amendment 39-14759; AD 2006-19-02]
RIN 2120-AA64

Airworthiness Directives; Airbus Model A300 B4-600, B4-600R, and
F4-600R Series Airplanes, and Model A300 C4-605R Variant F Airplanes
(Collectively Called A300-600 Series Airplanes)

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

ACTION: Final rule.

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

SUMMARY: The FAA is superseding an existing airworthiness directive
(AD), which applies to certain Airbus Model A300-600 series airplanes.
That AD currently requires repetitive eddy current inspections to
detect cracks of the outer skin of the fuselage at certain frames, and
repair or reinforcement of the structure at the frames, if necessary.
That AD also requires eventual reinforcement of the structure at
certain frames, which, when accomplished, terminates the repetitive
inspections. This new AD requires, for airplanes that were previously
reinforced but not repaired in accordance with the existing AD, a one-
time inspection for cracking of the fuselage outer skin at frames 28A
and 30A above stringer 30, and repair if necessary. This AD results
from a report that the previously required actions were not sufficient
to correct cracking before the structural reinforcement was installed.
We are issuing this AD to prevent such fatigue cracking, which could
result in reduced structural integrity, and consequent rapid
decompression of the airplane.

DATES: This AD becomes effective October 17, 2006.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in the AD as of October 17,
2006.
On August 4, 1997 (62 FR 35072, June 30, 1997), the Director of the
Federal Register approved the incorporation by reference of Airbus
Service Bulletin A300-53-6045, dated March 21, 1995, as revised by
Change Notice No. O.A., dated June 1, 1995; and Airbus Service Bulletin
A300-53-6037, dated March 21, 1995.

ADDRESSES: You may examine the 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., Nassif Building,
Room PL-401, Washington, DC.
Contact Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex,
France, for service information identified in this AD.

FOR FURTHER INFORMATION CONTACT: Tom Stafford, Aerospace Engineer,
International Branch, ANM-116, Transport Airplane Directorate, FAA,
1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425)
227-1622; fax (425) 227-1149.

SUPPLEMENTARY INFORMATION:

Examining the Docket

You may examine the airworthiness directive (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 street address stated in the ADDRESSES section.

Discussion

The FAA issued a notice of proposed rulemaking (NPRM) to amend 14
CFR part 39 to include an AD that supersedes AD 97-14-02, amendment 39-
10059 (62 FR 35072, June 30, 1997). The existing AD applies to certain
Airbus Model A300-600 series airplanes. That NPRM was published in the
Federal Register on June 15, 2006 (71 FR 34563). That NPRM proposed to
continue to require repetitive eddy current inspections to detect
cracks of the outer skin of the fuselage at certain frames, and repair
or reinforcement of the structure at the frames, if necessary. That
NPRM also proposed to continue to require eventual reinforcement of the
structure at certain frames, which, when accomplished, terminates the
repetitive inspections. That NPRM also proposed

[[Page 53560]]

to require, for airplanes that were previously reinforced but not
repaired in accordance with the existing AD, a one-time inspection for
cracking of the fuselage outer skin at frames 28A and 30A above
stringer 30, and repair if necessary.

Comments

We provided the public the opportunity to participate in the
development of this AD. No comments have been received on the NPRM or
on the determination of the cost to the public.

Conclusion

We have carefully reviewed the available data and determined that
air safety and the public interest require adopting the AD as proposed.

Costs of Compliance

This AD will affect about 53 airplanes of U.S. registry. The
following table provides the estimated costs for U.S. operators to
comply with this AD. The average labor rate is $80 per work hour.

Estimated Costs
--------------------------------------------------------------------------------------------------------------------------------------------------------
Work
Action hours Parts Cost per airplane Fleet cost
--------------------------------------------------------------------------------------------------------------------------------------------------------
Inspection (required by AD 97-14- 1 None $80, per inspection cycle..................... $4,240, per inspection cycle.
02).
Reinforcement (required by AD 97- 93 $7,200 $14,640....................................... $775,920.
14-02).
Inspection (new required action).. 1 None $80........................................... $4,240.
--------------------------------------------------------------------------------------------------------------------------------------------------------

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 this AD:
(1) Is not a ``significant regulatory action'' under Executive
Order 12866;
(2) Is not a ``significant rule'' under DOT Regulatory Policies and
Procedures (44 FR 11034, February 26, 1979); and
(3) Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
We prepared a regulatory evaluation of the estimated costs to
comply with this AD and placed it in the AD docket. See the ADDRESSES
section for a location to examine the regulatory evaluation.

List of Subjects in 14 CFR Part 39

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

Adoption of the Amendment

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

PART 39--AIRWORTHINESS DIRECTIVES

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

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

Sec. 39.13 [Amended]

0
2. The Federal Aviation Administration (FAA) amends Sec. 39.13 by
removing amendment 39-10059 (62 FR 35072, June 30, 1997) and by adding
the following new airworthiness directive (AD):

2006-19-02 Airbus: Amendment 39-14759. Docket No. FAA-2006-25047;
Directorate Identifier 2006-NM-028-AD.

Effective Date

(a) This AD becomes effective October 17, 2006.

Affected ADs

(b) This AD supersedes AD 97-14-02.

Applicability

(c) This AD applies to Airbus Model A300 B4-601, B4-603, B4-620,
B4-622, B4-605R, B4-622R, F4-605R, F4-622R, and C4-605R Variant F
airplanes, certificated in any category, except those on which
Airbus Modification 8683 has been done.

Unsafe Condition

(d) This AD results from a report that the previously required
actions were not sufficient to correct cracking before the
structural reinforcement was installed. We are issuing this AD to
prevent fatigue cracking of the outer skin of the fuselage at
certain frames, which could result in reduced structural integrity,
and consequent rapid decompression of the airplane.

Compliance

(e) You are responsible for having the actions required by this
AD performed within the compliance times specified, unless the
actions have already been done.

Restatement of the Requirements of AD 97-14-02

(f) Prior to the accumulation of 14,100 total flight cycles, or
within 12 months after August 4, 1997 (the effective date of AD 97-
14-02), whichever occurs later, conduct an eddy current inspection
to detect cracking of the fuselage outer skin at frames 28A and 30A
above stringer 30, in accordance with the Accomplishment
Instructions of Airbus Service Bulletin A300-53-6045, dated March
21, 1995, as revised by Change Notice No. O.A., dated June 1, 1995;
or Airbus Service Bulletin A300-53-6045, Revision 03, dated October
28, 2004. After the effective date of this AD, only Revision 03 may
be used. After the effective date of this AD, the initial eddy
current inspection and all applicable repairs required by this
paragraph must be done before doing the reinforcement specified in
paragraph (g) of this AD.
(1) If no cracking is found, repeat the eddy current inspection
thereafter at intervals not to exceed 4,500 flight cycles.
(2) If any cracking is found that is within the limits specified
in the service bulletin: Prior to further flight do the actions in
paragraph (f)(2)(i) or (f)(2)(ii) of this AD. After the effective
date of this AD, only Airbus Service Bulletin A300-53-6045, Revision
03, dated October 28, 2004, may be used for the repair specified in
paragraph (f)(2)(i) of this AD; and the reinforcement option
specified in paragraph (f)(2)(ii) of this AD is not allowed in
accordance with this paragraph.

[[Page 53561]]

(i) Repair in accordance with paragraph 2.D. of the
Accomplishment Instructions of Airbus Service Bulletin A300-53-6045,
dated March 21, 1995, as revised by Change Notice No. O.A., dated
June 1, 1995; or paragraph 3.C. of the Accomplishment Instructions
of Airbus Service Bulletin A300-53-6045, Revision 03, dated October
28, 2004. After the repair, repeat the eddy current inspection
thereafter at intervals not to exceed 4,500 flight cycles.
(ii) Reinforce the structure at frames 28 and 29, and at frames
30 and 31, between stringers 29 and 30, in accordance with the
Accomplishment Instructions of Airbus Service Bulletin A300-53-6037,
dated March 21, 1995; or Airbus Service Bulletin A300-53-6037,
Revision 02, dated October 28, 2004. Such reinforcement constitutes
terminating action for the repetitive inspections required by this
AD.
(3) If any cracking is found that is outside the limits
specified in the service bulletin: Prior to further flight,
reinforce the structure at frames 28 and 29, and at frames 30 and
31, between stringers 29 and 30, in accordance with the
Accomplishment Instructions of Airbus Service Bulletin A300-53-6037,
dated March 21, 1995; or Airbus Service Bulletin A300-53-6037,
Revision 02, dated October 28, 2004. After the effective date of
this AD, only Revision 02 may be used. Such reinforcement
constitutes terminating action for the repetitive inspections
required by this AD.
(g) Within 5 years after August 4, 1997: Reinforce the structure
at frames 28 and 29, and at frames 30 and 31, between stringers 29
and 30, in accordance with the Accomplishment Instructions of Airbus
Service Bulletin A300-53-6037, dated March 21, 1995; or Airbus
Service Bulletin A300-53-6037, Revision 02, dated October 28, 2004.
After the effective date of this AD, only Revision 02 may be used.
Such reinforcement constitutes terminating action for the repetitive
inspections required by this AD. After the effective date of this
AD, the initial eddy current inspection and all applicable repairs
required by paragraph (f) of this AD must be done before doing the
reinforcement.

New Requirements of This AD

Inspection and Corrective Action

(h) For airplanes that meet the conditions of both paragraphs
(h)(1) and (h)(2) of this AD: Within 2,400 flight cycles or 18
months after the effective date of this AD, whichever occurs first,
conduct an eddy current inspection to detect cracking of the
fuselage outer skin at frames 28A and 30A above stringer 30, in
accordance with the Accomplishment Instructions of Airbus Service
Bulletin A300-53-6045, Revision 03, dated October 28, 2004. If no
cracking is found: No further action is required by this paragraph.
If any cracking is found: Before further flight, repair the cracking
using 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) Airplanes that were reinforced before the effective date of
this AD in accordance with any service bulletin specified in Table 1
of this AD.

Table 1.--Reinforcement Service Bulletins
----------------------------------------------------------------------------------------------------------------
Airbus service bulletin Revision level Date
----------------------------------------------------------------------------------------------------------------
A300-53-6037.............................. Original................... March 21, 1995.
1.......................... February 3, 1999.
02......................... October 28, 2004.
----------------------------------------------------------------------------------------------------------------

(2) Airplanes that were not inspected and repaired in accordance
with any service bulletin specified in Table 2 of this AD.

Table 2.--Inspection and Repair Service Bulletins
----------------------------------------------------------------------------------------------------------------
Airbus service bulletin Revision level Date
----------------------------------------------------------------------------------------------------------------
A300-53-6045.............................. Original................... March 21, 1995.
01......................... August 25, 1997.
02......................... May 2, 1999.
03......................... October 28, 2004.
----------------------------------------------------------------------------------------------------------------

Alternative Methods of Compliance (AMOCs)

(i)(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

(j) French airworthiness directive F-2005-002, dated January 5,
2005, also addresses the subject of this AD.

Material Incorporated by Reference

(k) You must use the service information identified in Table 3
of this AD to perform the actions that are required by this AD,
unless the AD specifies otherwise.

Table 3.--Material Incorporated by Reference
----------------------------------------------------------------------------------------------------------------
Airbus service bulletin Revision level Date
----------------------------------------------------------------------------------------------------------------
A300-53-6037.............................. Original................... March 21, 1995.
A300-53-6037.............................. 02......................... October 28, 2004.
A300-53-6045.............................. 03......................... October 28, 2004.
A300-53-6045, as revised by Change Notice Original................... March 21, 1995.
No. O.A., dated June 1, 1995.
----------------------------------------------------------------------------------------------------------------

[[Page 53562]]

(1) The Director of the Federal Register approved the
incorporation by reference of Airbus Service Bulletin A300-53-6037,
Revision 02, dated October 28, 2004; and Airbus Service Bulletin
A300-53-6045, Revision 03, dated October 28, 2004; in accordance
with 5 U.S.C. 552(a) and 1 CFR part 51.
(2) On August 4, 1997 (62 FR 35072, June 30, 1997), the Director
of the Federal Register approved the incorporation by reference of
Airbus Service Bulletin A300-53-6045, dated March 21, 1995, as
revised by Change Notice No. O.A., dated June 1, 1995; and Airbus
Service Bulletin A300-53-6037, dated March 21, 1995.
(3) Contact Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac
Cedex, France, for a copy of this service information. You may
review copies at the Docket Management Facility, U.S. Department of
Transportation, 400 Seventh Street, SW., Room PL-401, Nassif
Building, Washington, DC; on the Internet at https://dms.dot.gov; or
at the National Archives and Records Administration (NARA). For
information on the availability of this material at the NARA, call
(202) 741-6030, or go to https://www.archives.gov/federal_register/
code_of_federal_regulations/ibr_locations.html.

Issued in Renton, Washington, on September 1, 2006.
Kalene C. Yanamura,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E6-14942 Filed 9-11-06; 8:45 am]
BILLING CODE 4910-13-P

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