Airworthiness Directives; Airbus Model A300 B4-601, A300 B4-603, A300 B4-605R, A300 C4-605R Variant F, A310-204, and A310-304 Airplanes Equipped With General Electric CF6-80C2 Engines, 17376-17379 [E7-6450]

Download as PDF rwilkins on PROD1PC63 with RULES 17376 Federal Register / Vol. 72, No. 67 / Monday, April 9, 2007 / Rules and Regulations during the year, for continued justification for such disclosures; (4) At the instruction of OMB, compile a report to be submitted to the Administrator and OMB, and made available to the public on request, describing the matching activities of SBA, including, (i) Matching programs in which SBA has participated; (ii) Matching agreements proposed that were disapproved by the Board; (iii) Any changes in membership or structure of the Board in the preceding year; (iv) The reasons for any waiver of the requirement described below for completion and submission of a costbenefit analysis prior to the approval of a matching program; (v) Any violations of matching agreements that have been alleged or identified and any corrective action taken; and (vi) Any other information required by OMB to be included in such report; (5) Serve as clearinghouse for receiving and providing information on the accuracy, completeness, and reliability of records used in matching programs; (6) Provide interpretation and guidance to SBA offices and personnel on the requirements for matching programs; (7) Review Agency recordkeeping and disposal policies and practices for matching programs to assure compliance with the Privacy Act; and (8) May review and report on any SBA matching activities that are not matching programs. (g) Cost-benefit analysis. Except as provided in paragraphs (e)(2) and (3) of this section, the Data Integrity Board shall not approve any written agreement for a matching program unless SBA has completed and submitted to such Board a cost-benefit analysis of the proposed program and such analysis demonstrates that the program is likely to be cost effective. The Board may waive these requirements if it determines, in writing, and in accordance with OMB guidelines, that a cost-benefit analysis is not required. Such an analysis also shall not be required prior to the initial approval of a written agreement for a matching program that is specifically required by statute. (h) Disapproval of matching agreements. If a matching agreement is disapproved by the Data Integrity Board, any party to such agreement may appeal to OMB. Timely notice of the filing of such an appeal shall be provided by OMB to the Committee on Governmental Affairs of the Senate and the Committee on Government VerDate Aug<31>2005 16:25 Apr 06, 2007 Jkt 211001 Operations of the House of Representatives. (1) OMB may approve a matching agreement despite the disapproval of the Data Integrity Board if OMB determines that: (i) The matching program will be consistent with all applicable legal, regulatory, and policy requirements; (ii) There is adequate evidence that the matching agreement will be costeffective; and (iii) The matching program is in the public interest. (2) The decision of OMB to approve a matching agreement shall not take effect until 30 days after it is reported to the committees described in paragraph (h) of this section. (3) If the Data Integrity Board and the OMB disapprove a matching program proposed by the Inspector General, the Inspector General may report the disapproval to the Administrator and to the Congress. § 102.41 Other provisions. (a) Personnel Records. All SBA personnel records and files, as prescribed by OPM, shall be maintained in such a way that the privacy of all individuals concerned is protected in accordance with regulations of OPM (5 CFR parts 293 and 297). (b) Mailing Lists. The SBA will not sell or rent an individual’s name or address. This provision shall not be construed to require the withholding of names or addresses otherwise permitted to be made public. (c) Changes in Systems. The SBA shall provide adequate advance notice to Congress and OMB of any proposal to establish or alter any system of records in order to permit an evaluation of the probable or potential effect of such proposal on the privacy and other personal or property rights of individuals or the disclosure of information relating to such individuals, and its effect on the preservation of the constitutional principles of federalism and separation of powers. (d) Medical Records. Medical records shall be disclosed to the individual to whom they pertain. SBA may, however, transmit such information to a medical doctor named by the requesting individual. In regard to medical records in personnel files, see also 5 CFR 297.205. Steven C. Preston, Administrator. [FR Doc. 07–1651 Filed 4–6–07; 8:45 am] BILLING CODE 8025–01–P PO 00000 Frm 00024 Fmt 4700 Sfmt 4700 DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2007–27012; Directorate Identifier 2006–NM–188–AD; Amendment 39–15017; AD 2007–07–15] RIN 2120–AA64 Airworthiness Directives; Airbus Model A300 B4–601, A300 B4–603, A300 B4– 605R, A300 C4–605R Variant F, A310– 204, and A310–304 Airplanes Equipped With General Electric CF6–80C2 Engines Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: SUMMARY: The FAA is superseding an existing airworthiness directive (AD), which applies to certain Airbus Model A300 B4–600, B4–600R, C4–605R Variant F, and F4–600R (collectively called A300–600) series airplanes; and Model A310 series airplanes. That AD currently requires a one-time inspection for damage of the integrated drive generator (IDG) electrical harness and pyramid arm, and repair if necessary. This new AD adds new repetitive inspections, which, when initiated, terminate the inspection required by the existing AD. This new AD also requires repairing damage and protecting the harness. This new AD also provides for optional terminating action for the repetitive inspections. This new AD also removes certain airplanes from the applicability of the existing AD. This AD results from a report of structural damage on the forward pyramid arm of an engine pylon due to chafing of the IDG electrical harness against the structure of the pyramid arm. We are issuing this AD to prevent electrical arcing in the engine pylon, which could result in loss of the relevant alternating current (AC) bus bar, reduced structural integrity of the engine pylon, and possible loss of control of the airplane. DATES: This AD becomes effective May 14, 2007. The Director of the Federal Register approved the incorporation by reference of certain publications listed in the AD as of May 14, 2007. On May 13, 2004 (69 FR 23090, April 28, 2004), the Director of the Federal Register approved the incorporation by reference of Airbus All Operators Telex A310–54A2038, dated February 19, 2004; and Airbus All Operators Telex A300–54A6037, dated February 19, 2004. E:\FR\FM\09APR1.SGM 09APR1 17377 Federal Register / Vol. 72, No. 67 / Monday, April 9, 2007 / Rules and Regulations 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, FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington 98057–3356; telephone (425) 227–1622; fax (425) 227–1149. SUPPLEMENTARY INFORMATION: ADDRESSES: Discussion 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. 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. The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to include an AD that supersedes AD 2004–09–01, amendment 39–13590 (69 FR 23090, April 28, 2004). The existing AD applies to certain Airbus Model A300 B4–600, B4–600R, C4–605R Variant F, and F4–600R (collectively called A300–600) series airplanes; and Model A310 series airplanes. That NPRM was published in the Federal Register on January 26, 2007 (72 FR 3764). That NPRM proposed to require a one-time inspection for damage of the integrated drive generator (IDG) electrical harness and pyramid arm, and repair if necessary. That NPRM proposed to add new repetitive inspections, which, when initiated, would terminate the inspection required by the existing AD. That NPRM also proposed to require repairing damage and protecting the harness. That NPRM also proposed to provide for optional terminating action for the repetitive inspections. That NPRM also proposed to remove certain airplanes from the applicability of the existing AD. Change to Applicability We have removed Airbus Model A310–308 airplanes from the applicability of this AD. That model is not listed as an FAA-certified model in our type certificate data sheets. Conclusion We have carefully reviewed the available data and determined that air safety and the public interest require adopting the AD with the change described previously. We have determined that this change will neither increase the economic burden on any operator nor increase the scope of the AD. Costs of Compliance The following table provides the estimated costs for U.S. operators to comply with this AD. ESTIMATED COSTS Action Average labor rate per hour Work hours One-time inspection (from AD 2004–09–01). Repetitive inspections and harness protection (new requirement). New optional modification $80 $0 4 80 0 8 80 2,460 rwilkins on PROD1PC63 with RULES 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 16:25 Apr 06, 2007 Cost per airplane 2 Authority for This Rulemaking VerDate Aug<31>2005 Cost of parts Jkt 211001 Number of U.S.registered airplanes $160 ............................... 100 ................................. $16,000. $320, per inspection cycle. 100 ................................. $32,000, per inspection cycle. $3,100 ............................ Up to 100 ....................... Up to $310,000. 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 PO 00000 Frm 00025 Fmt 4700 Sfmt 4700 Fleet cost 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 Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: I E:\FR\FM\09APR1.SGM 09APR1 17378 Federal Register / Vol. 72, No. 67 / Monday, April 9, 2007 / Rules and Regulations 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 Federal Aviation Administration (FAA) amends § 39.13 by removing amendment 39–13590 (69 FR 23090, April 28, 2004) and by adding the following new airworthiness directive (AD): I 2007–07–15 Airbus: Amendment 39–15017. Docket No. FAA–2007–27012; Directorate Identifier 2006–NM–188–AD. Effective Date (a) This AD becomes effective May 14, 2007. Affected ADs (b) This AD supersedes AD 2004–09–01. Applicability (c) This AD applies to Airbus Model A300 B4–601, A300 B4–603, A300 B4–605R, A300 C4–605R Variant F, A310–204, and A310– 304 airplanes; certificated in any category; equipped with General Electric CF6–80C2 engines without full-authority digital electronic control (FADEC); excluding airplanes on which Airbus Modification 13184 was done in production. Unsafe Condition (d) This AD results from a report of structural damage on the forward pyramid arm of an engine pylon due to chafing of the integrated drive generator (IDG) electrical harness against the structure of the pyramid arm. We are issuing this AD to prevent electrical arcing in the engine pylon, which could result in loss of the relevant alternating current (AC) bus bar, reduced structural integrity of the engine pylon, and possible loss of control 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 Certain Requirements of AD 2004–09–01 rwilkins on PROD1PC63 with RULES All Operators Telex Reference (f) The term ‘‘All Operators Telex,’’ or ‘‘AOT,’’ as used in paragraphs (g), (h), and (j) of this AD, means the following AOTs, as applicable: (1) For Model A300 B4–601, A300 B4–603, A300 B4–605R, and A300 C4–605R Variant F airplanes: Airbus AOT A300–54A6037, dated February 19, 2004; and (2) For Model A310–204, and A310–304 airplanes: Airbus AOT A310–54A2038, dated February 19, 2004. Inspection (g) At the applicable time in paragraph (g)(1) or (g)(2) of this AD, do a one-time detailed inspection for discrepancies of the IDG harness, harness bracket, retaining VerDate Aug<31>2005 16:25 Apr 06, 2007 Jkt 211001 fasteners, and pyramid arm, in accordance with the applicable AOT. (1) For airplanes on which Airbus Modification 07591 has not been incorporated as of May 13, 2004 (the effective date of AD 2004–09–01): Within 10 days after May 13, 2004. (2) For airplanes on which Airbus Modification 07591 has been incorporated as of May 13, 2004: Within 600 flight hours after May 13, 2004. Note 1: For the purposes of this AD, a detailed inspection is defined as: ‘‘An intensive visual examination of a specific structural area, system, installation, or assembly to detect damage, failure, or irregularity. Available lighting is normally supplemented with a direct source of good lighting at intensity deemed appropriate by the inspector. Inspection aids such as mirror, magnifying lenses, etc., may be used. Surface cleaning and elaborate access procedures may be required.’’ Related Investigative and Corrective Actions for Damaged Electrical Harness (h) If any discrepancy in the IDG electrical harness, fretting at the convoluted conduits, or contact between the IDG electrical harness and the pyramid arms is found during the inspection required by paragraph (g) of this AD: Before further flight, do the applicable related investigative actions and corrective actions in accordance with the applicable AOT. Corrective Action for Damaged Electrical Harness Bracket, Retaining Fasteners, or Pyramid Arm (i) If any discrepancy in the electrical harness bracket, retaining fasteners, or pyramid arm is found during the inspection required by paragraph (g) of this AD: Before further flight, repair in accordance with a method approved by the Manager, International Branch, ANM–116, Transport Airplane Directorate, FAA; the Direction ´ ´ Generale de l’Aviation Civile (DGAC) (or its delegated agent); or the European Aviation Safety Agency (EASA) (or its delegated agent). After the effective date of this AD, repair in accordance with a method approved by the FAA or the EASA. No Reporting Requirement for Paragraph (g) of this AD (j) Although the referenced AOTs describe procedures for submitting certain information to the manufacturer, no report is required for the inspection required by paragraph (g) of this AD. New Requirements of this AD Repetitive Inspections (k) Within 6 months after the effective date of this AD, and thereafter at intervals not to exceed 12 months: Do a detailed inspection for damage of the IDG harness and the pylon pyramid arms, and protect the harness. Do the actions in accordance with Airbus Service Bulletin A300–24–6097, dated March 3, 2006 (for Model A300 B4–601, A300 B4– 603, A300 B4–605R, and A300 C4–605R Variant F airplanes); or A310–24–2100, dated March 3, 2006 (for Model A310–204, and A310–304 airplanes). The initial inspection PO 00000 Frm 00026 Fmt 4700 Sfmt 4700 terminates the requirements of paragraph (g) of this AD. If any discrepancy is found: Before further flight, repair in accordance with the applicable service bulletin; except, where the service bulletin specifies to contact the manufacturer for repair instructions, this AD requires repair using a method approved by either the Manager, International Branch, ANM–116; or the EASA (or its delegated agent). Report (l) At the applicable times specified in paragraphs (l)(1) and (l)(2) of this AD, submit a report of the findings (both positive and negative) of each inspection required by paragraph (k) of this AD. Send the report to Airbus Customer Services Directorate, Department AI/SE–E43, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France. The report must include the information specified in Appendix 01 of Airbus Service Bulletin A300–24–6097 or A310–24–2100, both dated March 3, 2006, as applicable. Under the provisions of the Paperwork Reduction Act (44 U.S.C. 3501 et seq.), the Office of Management and Budget (OMB) has approved the information collection requirements contained in this AD and has assigned OMB Control Number 2120–0056. (1) For each inspection done after the effective date of this AD: Send the report within 30 days after the inspection. (2) If an inspection was done before the effective date of this AD: Send the report within 30 days after the effective date of this AD. Optional Terminating Action (m) Replacement of the bracket feeder on the pylons terminates the requirements of this AD if the bracket feeder is replaced in accordance with Airbus Service Bulletin A300–54–6038, dated May 12, 2006 (for Model A300 B4–601, A300 B4–603, A300 B4–605R, and A300 C4–605R Variant F airplanes); or A310–54–2039, dated May 12, 2006 (for Model A310–204, and A310–304 airplanes); as applicable. Alternative Methods of Compliance (AMOCs) (n)(1) 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. (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 (o) EASA airworthiness directive 2006– 0155, dated June 1, 2006, also addresses the subject of this AD. Material Incorporated by Reference (p) 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. E:\FR\FM\09APR1.SGM 09APR1 Federal Register / Vol. 72, No. 67 / Monday, April 9, 2007 / Rules and Regulations Issued in Renton, Washington, on March 28, 2007. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E7–6450 Filed 4–6–07; 8:45 am] TABLE 1.—REQUIRED MATERIAL INCORPORATED BY REFERENCE Airbus Service information Date All Operators Telex A300–54A6037. All Operators Telex A310–54A2038. Service Bulletin A300– 24–6097, including Appendix 01. Service Bulletin A310– 24–2100, including Appendix 01. February 19, 2004. February 19, 2004. DEPARTMENT OF TRANSPORTATION March 3, 2006. Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2005–20944; Directorate Identifier 2003–NE–64–AD; Amendment 39– 15018; AD 2007–08–01] RIN 2120–AA64 Airworthiness Directives; General Electric Company CT7–5, –7, and –9 Series Turboprop Engines TABLE 2.—OPTIONAL MATERIAL INCORPORATED BY REFERENCE Airbus Service information Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: Date May 12, 2006. May 12, 2006. (1) The Director of the Federal Register approved the incorporation by reference of the service information identified in Table 3 of this AD in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. TABLE 3.—NEW MATERIAL INCORPORATED BY REFERENCE Airbus Service Bulletin rwilkins on PROD1PC63 with RULES A300–24–6097, including Appendix 01. A300–54–6038 ............. A310–24–2100, including Appendix 01. A310–54–2039 ............. Date March 3, 2006. May 12, 2006. March 3, 2006. May 12, 2006. (2) On May 13, 2004 (69 FR 23090, April 28, 2004), the Director of the Federal Register approved the incorporation by reference of Airbus All Operators Telex A310–54A2038, dated February 19, 2004; and Airbus All Operators Telex A300–54A6037, dated February 19, 2004. (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 FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202–741–6030, or go to: https://www.archives.gov/federal-register/ cfr/ibr-locations.html. VerDate Aug<31>2005 16:25 Apr 06, 2007 Jkt 211001 You may examine the AD docket on the Internet at https://dms.dot.gov or in Room PL–401 on the plaza level of the Nassif Building, 400 Seventh Street, SW., Washington, DC. FOR FURTHER INFORMATION CONTACT: Mark Bouyer, Engine Certification Office, FAA, Engine and Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803; telephone (781) 238–7755; fax (781) 238–7199. The FAA proposed to amend 14 CFR part 39 with a proposed AD. The proposed AD applies to GE CT7–5A2, –5A3, –7A, –7A1, –9B, –9B1, and –9B2 turboprop engines, with certain P/N and serial number stage 2 turbine aft cooling plates installed. We published the proposed AD in the Federal Register on March 31, 2006 (71 FR 16248). That action proposed to expand the population of affected CT7 turboprop engine models required to undergo a onetime ECI of boltholes in certain P/N stage 2 turbine aft cooling plates. That action also proposed to reduce the number of cooling plates affected by identifying the serial numbers. SUPPLEMENTARY INFORMATION: March 3, 2006. You must use the service information identified in Table 2 of this AD to perform the optional terminating action, if accomplished, unless the AD specifies otherwise. Service Bulletin A300– 54–6038. Service Bulletin A310– 54–2039. BILLING CODE 4910–13–P 17379 SUMMARY: The FAA is superseding an existing airworthiness directive (AD) for General Electric Company (GE) CT7– 5A2, –5A3, –7A, –7A1, –9B, –9B1, and –9B2, –9C, –9C3, –9D, and –9D2 turboprop engines, with certain part number (P/N) and serial number stage 2 turbine aft cooling plates installed. That AD currently requires a onetime eddy current inspection (ECI) of boltholes in certain P/N stage 2 turbine aft cooling plates. This AD expands the population of affected CT7 turboprop engine models, but reduces the number of cooling plates affected. It also requires a onetime ECI of boltholes in certain P/ N stage 2 turbine aft cooling plates with specific serial numbers. This AD results from the manufacturer expanding the list of affected engine models and identifying the affected stage 2 turbine aft cooling plates by serial number. We are issuing this AD to prevent separation of the stage 2 turbine aft cooling plate, resulting in uncontained engine failure and damage to the airplane. This AD becomes effective May 14, 2007. The Director of the Federal Register approved the incorporation by reference of certain publications listed in the regulations as of May 14, 2007. ADDRESSES: You can get the service information identified in this AD from General Electric Aircraft Engines CT7 Series Turboprop Engines, 1000 Western Ave, Lynn, MA 01910; telephone (781) 594–3140, fax (781) 594–4805. DATES: PO 00000 Frm 00027 Fmt 4700 Sfmt 4700 Examining the AD Docket You may examine the docket that contains the AD, any comments received, and any final disposition in person at the Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The Docket Office (telephone (800) 647–5227) is located on the plaza level of the Department of Transportation Nassif Building at the street address stated in ADDRESSES. Comments will be available in the AD docket shortly after the DMS receives them. Comments We provided the public the opportunity to participate in the development of this AD. We have considered the comments received. Clarification of ECI Requirements GE suggests that we clarify paragraph (f) of this AD to limit the required ECI to stage 2 turbine aft cooling plates that are being returned to service. This change would eliminate any requirement to ECI cooling plates that are not going to be reused. We agree. If the cooling plate is not going to be reused, there is no need to ECI it immediately after it is removed. Paragraph (h) of this AD requires an ECI of all cooling plates affected by this AD before they are returned to service. We made the clarification to paragraph (f). E:\FR\FM\09APR1.SGM 09APR1

Agencies

[Federal Register Volume 72, Number 67 (Monday, April 9, 2007)]
[Rules and Regulations]
[Pages 17376-17379]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E7-6450]


=======================================================================
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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2007-27012; Directorate Identifier 2006-NM-188-AD; 
Amendment 39-15017; AD 2007-07-15]
RIN 2120-AA64


Airworthiness Directives; Airbus Model A300 B4-601, A300 B4-603, 
A300 B4-605R, A300 C4-605R Variant F, A310-204, and A310-304 Airplanes 
Equipped With General Electric CF6-80C2 Engines

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 B4-600, B4-600R, C4-
605R Variant F, and F4-600R (collectively called A300-600) series 
airplanes; and Model A310 series airplanes. That AD currently requires 
a one-time inspection for damage of the integrated drive generator 
(IDG) electrical harness and pyramid arm, and repair if necessary. This 
new AD adds new repetitive inspections, which, when initiated, 
terminate the inspection required by the existing AD. This new AD also 
requires repairing damage and protecting the harness. This new AD also 
provides for optional terminating action for the repetitive 
inspections. This new AD also removes certain airplanes from the 
applicability of the existing AD. This AD results from a report of 
structural damage on the forward pyramid arm of an engine pylon due to 
chafing of the IDG electrical harness against the structure of the 
pyramid arm. We are issuing this AD to prevent electrical arcing in the 
engine pylon, which could result in loss of the relevant alternating 
current (AC) bus bar, reduced structural integrity of the engine pylon, 
and possible loss of control of the airplane.

DATES: This AD becomes effective May 14, 2007.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in the AD as of May 14, 2007.
    On May 13, 2004 (69 FR 23090, April 28, 2004), the Director of the 
Federal Register approved the incorporation by reference of Airbus All 
Operators Telex A310-54A2038, dated February 19, 2004; and Airbus All 
Operators Telex A300-54A6037, dated February 19, 2004.

[[Page 17377]]


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, FAA, Transport Airplane Directorate, 
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 2004-09-01, amendment 
39-13590 (69 FR 23090, April 28, 2004). The existing AD applies to 
certain Airbus Model A300 B4-600, B4-600R, C4-605R Variant F, and F4-
600R (collectively called A300-600) series airplanes; and Model A310 
series airplanes. That NPRM was published in the Federal Register on 
January 26, 2007 (72 FR 3764). That NPRM proposed to require a one-time 
inspection for damage of the integrated drive generator (IDG) 
electrical harness and pyramid arm, and repair if necessary. That NPRM 
proposed to add new repetitive inspections, which, when initiated, 
would terminate the inspection required by the existing AD. That NPRM 
also proposed to require repairing damage and protecting the harness. 
That NPRM also proposed to provide for optional terminating action for 
the repetitive inspections. That NPRM also proposed to remove certain 
airplanes from the applicability of the existing AD.

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.

Change to Applicability

    We have removed Airbus Model A310-308 airplanes from the 
applicability of this AD. That model is not listed as an FAA-certified 
model in our type certificate data sheets.

Conclusion

    We have carefully reviewed the available data and determined that 
air safety and the public interest require adopting the AD with the 
change described previously. We have determined that this change will 
neither increase the economic burden on any operator nor increase the 
scope of the AD.

Costs of Compliance

    The following table provides the estimated costs for U.S. operators 
to comply with this AD.

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                          Average
                                 Work      labor     Cost of       Cost per     Number of U.S.-
           Action               hours     rate per    parts        airplane        registered       Fleet cost
                                            hour                                   airplanes
----------------------------------------------------------------------------------------------------------------
One-time inspection (from AD          2        $80         $0  $160...........  100............  $16,000.
 2004-09-01).
Repetitive inspections and            4         80          0  $320, per        100............  $32,000, per
 harness protection (new                                        inspection                        inspection
 requirement).                                                  cycle.                            cycle.
New optional modification...          8         80      2,460  $3,100.........  Up to 100......  Up to $310,000.
----------------------------------------------------------------------------------------------------------------

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:

[[Page 17378]]

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 39-13590 (69 FR 23090, April 28, 2004) and by adding 
the following new airworthiness directive (AD):

2007-07-15 Airbus: Amendment 39-15017. Docket No. FAA-2007-27012; 
Directorate Identifier 2006-NM-188-AD.

Effective Date

    (a) This AD becomes effective May 14, 2007.

Affected ADs

    (b) This AD supersedes AD 2004-09-01.

Applicability

    (c) This AD applies to Airbus Model A300 B4-601, A300 B4-603, 
A300 B4-605R, A300 C4-605R Variant F, A310-204, and A310-304 
airplanes; certificated in any category; equipped with General 
Electric CF6-80C2 engines without full-authority digital electronic 
control (FADEC); excluding airplanes on which Airbus Modification 
13184 was done in production.

Unsafe Condition

    (d) This AD results from a report of structural damage on the 
forward pyramid arm of an engine pylon due to chafing of the 
integrated drive generator (IDG) electrical harness against the 
structure of the pyramid arm. We are issuing this AD to prevent 
electrical arcing in the engine pylon, which could result in loss of 
the relevant alternating current (AC) bus bar, reduced structural 
integrity of the engine pylon, and possible loss of control 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 Certain Requirements of AD 2004-09-01

All Operators Telex Reference

    (f) The term ``All Operators Telex,'' or ``AOT,'' as used in 
paragraphs (g), (h), and (j) of this AD, means the following AOTs, 
as applicable:
    (1) For Model A300 B4-601, A300 B4-603, A300 B4-605R, and A300 
C4-605R Variant F airplanes: Airbus AOT A300-54A6037, dated February 
19, 2004; and
    (2) For Model A310-204, and A310-304 airplanes: Airbus AOT A310-
54A2038, dated February 19, 2004.

Inspection

    (g) At the applicable time in paragraph (g)(1) or (g)(2) of this 
AD, do a one-time detailed inspection for discrepancies of the IDG 
harness, harness bracket, retaining fasteners, and pyramid arm, in 
accordance with the applicable AOT.
    (1) For airplanes on which Airbus Modification 07591 has not 
been incorporated as of May 13, 2004 (the effective date of AD 2004-
09-01): Within 10 days after May 13, 2004.
    (2) For airplanes on which Airbus Modification 07591 has been 
incorporated as of May 13, 2004: Within 600 flight hours after May 
13, 2004.

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

Related Investigative and Corrective Actions for Damaged Electrical 
Harness

    (h) If any discrepancy in the IDG electrical harness, fretting 
at the convoluted conduits, or contact between the IDG electrical 
harness and the pyramid arms is found during the inspection required 
by paragraph (g) of this AD: Before further flight, do the 
applicable related investigative actions and corrective actions in 
accordance with the applicable AOT.

Corrective Action for Damaged Electrical Harness Bracket, Retaining 
Fasteners, or Pyramid Arm

    (i) If any discrepancy in the electrical harness bracket, 
retaining fasteners, or pyramid arm is found during the inspection 
required by paragraph (g) of this AD: Before further flight, repair 
in accordance with a method approved by the Manager, International 
Branch, ANM-116, Transport Airplane Directorate, FAA; the Direction 
G[eacute]n[eacute]rale de l'Aviation Civile (DGAC) (or its delegated 
agent); or the European Aviation Safety Agency (EASA) (or its 
delegated agent). After the effective date of this AD, repair in 
accordance with a method approved by the FAA or the EASA.

No Reporting Requirement for Paragraph (g) of this AD

    (j) Although the referenced AOTs describe procedures for 
submitting certain information to the manufacturer, no report is 
required for the inspection required by paragraph (g) of this AD.

New Requirements of this AD

Repetitive Inspections

    (k) Within 6 months after the effective date of this AD, and 
thereafter at intervals not to exceed 12 months: Do a detailed 
inspection for damage of the IDG harness and the pylon pyramid arms, 
and protect the harness. Do the actions in accordance with Airbus 
Service Bulletin A300-24-6097, dated March 3, 2006 (for Model A300 
B4-601, A300 B4-603, A300 B4-605R, and A300 C4-605R Variant F 
airplanes); or A310-24-2100, dated March 3, 2006 (for Model A310-
204, and A310-304 airplanes). The initial inspection terminates the 
requirements of paragraph (g) of this AD. If any discrepancy is 
found: Before further flight, repair in accordance with the 
applicable service bulletin; except, where the service bulletin 
specifies to contact the manufacturer for repair instructions, this 
AD requires repair using a method approved by either the Manager, 
International Branch, ANM-116; or the EASA (or its delegated agent).

Report

    (l) At the applicable times specified in paragraphs (l)(1) and 
(l)(2) of this AD, submit a report of the findings (both positive 
and negative) of each inspection required by paragraph (k) of this 
AD. Send the report to Airbus Customer Services Directorate, 
Department AI/SE-E43, 1 Rond Point Maurice Bellonte, 31707 Blagnac 
Cedex, France. The report must include the information specified in 
Appendix 01 of Airbus Service Bulletin A300-24-6097 or A310-24-2100, 
both dated March 3, 2006, as applicable. Under the provisions of the 
Paperwork Reduction Act (44 U.S.C. 3501 et seq.), the Office of 
Management and Budget (OMB) has approved the information collection 
requirements contained in this AD and has assigned OMB Control 
Number 2120-0056.
    (1) For each inspection done after the effective date of this 
AD: Send the report within 30 days after the inspection.
    (2) If an inspection was done before the effective date of this 
AD: Send the report within 30 days after the effective date of this 
AD.

Optional Terminating Action

    (m) Replacement of the bracket feeder on the pylons terminates 
the requirements of this AD if the bracket feeder is replaced in 
accordance with Airbus Service Bulletin A300-54-6038, dated May 12, 
2006 (for Model A300 B4-601, A300 B4-603, A300 B4-605R, and A300 C4-
605R Variant F airplanes); or A310-54-2039, dated May 12, 2006 (for 
Model A310-204, and A310-304 airplanes); as applicable.

Alternative Methods of Compliance (AMOCs)

    (n)(1) 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.
    (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

    (o) EASA airworthiness directive 2006-0155, dated June 1, 2006, 
also addresses the subject of this AD.

Material Incorporated by Reference

    (p) 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.

[[Page 17379]]



          Table 1.--Required Material Incorporated by Reference
------------------------------------------------------------------------
      Airbus Service information                      Date
------------------------------------------------------------------------
All Operators Telex A300-54A6037.....  February 19, 2004.
All Operators Telex A310-54A2038.....  February 19, 2004.
Service Bulletin A300-24-6097,         March 3, 2006.
 including Appendix 01.
Service Bulletin A310-24-2100,         March 3, 2006.
 including Appendix 01.
------------------------------------------------------------------------

    You must use the service information identified in Table 2 of 
this AD to perform the optional terminating action, if accomplished, 
unless the AD specifies otherwise.

          Table 2.--Optional Material Incorporated by Reference
------------------------------------------------------------------------
      Airbus Service information                      Date
------------------------------------------------------------------------
Service Bulletin A300-54-6038........  May 12, 2006.
Service Bulletin A310-54-2039........  May 12, 2006.
------------------------------------------------------------------------

    (1) The Director of the Federal Register approved the 
incorporation by reference of the service information identified in 
Table 3 of this AD in accordance with 5 U.S.C. 552(a) and 1 CFR part 
51.

            Table 3.--New Material Incorporated by Reference
------------------------------------------------------------------------
       Airbus Service Bulletin                        Date
------------------------------------------------------------------------
A300-24-6097, including Appendix 01..  March 3, 2006.
A300-54-6038.........................  May 12, 2006.
A310-24-2100, including Appendix 01..  March 3, 2006.
A310-54-2039.........................  May 12, 2006.
------------------------------------------------------------------------

    (2) On May 13, 2004 (69 FR 23090, April 28, 2004), the Director 
of the Federal Register approved the incorporation by reference of 
Airbus All Operators Telex A310-54A2038, dated February 19, 2004; 
and Airbus All Operators Telex A300-54A6037, dated February 19, 
2004.
    (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 FAA, Transport Airplane Directorate, 1601 Lind 
Avenue, SW., Renton, Washington; or at the National Archives and 
Records Administration (NARA). For information on the availability 
of this material at NARA, call 202-741-6030, or go to: https://
www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued in Renton, Washington, on March 28, 2007.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
 [FR Doc. E7-6450 Filed 4-6-07; 8:45 am]
BILLING CODE 4910-13-P
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