Airworthiness Directives; Construcciones Aeronauticas, S.A., (CASA) Model C-212 Airplanes, 80-84 [E7-25481]

Download as PDF 80 Federal Register / Vol. 73, No. 1 / Wednesday, January 2, 2008 / Proposed Rules Costs of Compliance List of Subjects in 14 CFR Part 39 We estimate that this proposed AD would affect 379 GE CF6–45 and CF6– 50 series turbofan engines installed on airplanes of U.S. registry. We also estimate that it would take about 44 work hours per engine to perform the proposed actions, and that the average labor rate is $80 per work hour. Required parts would cost about $11,000 per engine. Based on these figures, we estimate the total cost of the proposed AD to U.S. operators to be $2,802,360. Air transportation, Aircraft, Aviation safety, Safety. 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. mstockstill on PROD1PC66 with PROPOSALS Regulatory Findings We have determined that this proposed AD would not have federalism implications under Executive Order 13132. This proposed AD would not have a substantial direct effect on the States, on the relationship between the national Government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify that the proposed regulation: 1. Is not a ‘‘significant regulatory action’’ under Executive Order 12866; 2. Is not a ‘‘significant rule’’ under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); and 3. Would not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. We prepared a regulatory evaluation of the estimated costs to comply with this proposed AD. See the ADDRESSES section for a location to examine the regulatory evaluation. VerDate Aug<31>2005 16:49 Dec 31, 2007 Jkt 214001 The Proposed Amendment Under the authority delegated to me by the Administrator, the Federal Aviation Administration proposes to amend 14 CFR part 39 as follows: PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The FAA amends § 39.13 by adding the following new airworthiness directive: General Electric Company: Docket No. FAA– 2006–24145; Directorate Identifier 2006– NE–06–AD. Alternative Methods of Compliance (g) The Manager, Engine Certification Office, has the authority to approve alternative methods of compliance for this AD if requested using the procedures found in 14 CFR 39.19. Related Information (h) Contact Robert Green, Aerospace Engineer, Engine Certification Office, FAA, Engine & Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803; e-mail: robert.green@faa.gov; telephone (781) 238–7754; fax (781) 238– 7199, for more information about this AD. Issued in Burlington, Massachusetts, on December 17, 2007. Peter A. White, Assistant Manager, Engine and Propeller Directorate, Aircraft Certification Service. [FR Doc. E7–25458 Filed 12–31–07; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Comments Due Date (a) The Federal Aviation Administration (FAA) must receive comments on this airworthiness directive (AD) action by February 19, 2008. Federal Aviation Administration Affected ADs (b) None. RIN 2120–AA64 Applicability (c) This AD applies to General Electric Company (GE) CF6–45A, CF6–45A2, CF6– 50A, CF6–50C, CF6–50CA, CF6–50C1, CF6– 50C2, CF6–50C2B, CF6–50C2D, CF6–50E, CF6–50E1, CF6–50E2, and CF6–50E2B series turbofan engines with long fixed core exhaust nozzle (LFCEN) assembly forward centerbody, part number (P/N) 1313M55G01 or G02, P/N 9076M28G09 or G10, and aft centerbody P/N 1313M56G01 or 9076M46G05, installed. These engines are installed on, but not limited to, Airbus A300 series, Boeing 747 series, McDonnell Douglas DC–10 series, and DC–10–30F (KC–10A, KDC–10) airplanes. Unsafe Condition (d) This AD results from reports of separation of LFCEN assembly forward and aft centerbodies, due to high imbalance engine conditions. We are issuing this AD to prevent the forward and aft centerbody of the LFCEN assembly from separating, leading to additional damage to the airplane. Compliance (e) You are responsible for having the actions required by this AD performed within 42 months after the effective date of this AD, unless the actions have already been done. (f) Replace the forward centerbody, P/N 1313M55G01 or G02, P/N 9076M28G09 or G10, and aft centerbody, P/N 1313M56G01 or 9076M46G05 with a forward and aft centerbody that have been modified using with the Accomplishment Instructions, Section 3, of GE service bulletin No. CF6–50 S/B 78–0244, dated July 30, 2007. PO 00000 Frm 00008 Fmt 4702 Sfmt 4702 14 CFR Part 39 [Docket No. FAA–2007–0372; Directorate Identifier 2007–NM–164–AD] Airworthiness Directives; Construcciones Aeronauticas, S.A., (CASA) Model C–212 Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: SUMMARY: We propose to adopt a new airworthiness directive (AD) for the products listed above that would supersede an existing AD. This proposed AD results from mandatory continuing airworthiness information (MCAI) originated by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as: On 23 November 2006, Emergency Airworthiness Directive (EAD) Nr. (number) 2006–0351–E was published requiring an inspection to be performed on C–212 aeroplanes having been used for Maritime Patrol or other similar low altitude operations, due to the fact that, after initial examination of the evidences of a recent C– 212 Maritime Patrol aircraft accident, cracks had been found in the centre wing lower skin at STA Y=1030. At the time of the accident, the aircraft had accumulated 17,000 flight hours and 7,300 flight cycles. The cracks were suspected to be caused by fatigue. A more detailed examination in the laboratory, led to think that the initiation of the fatigue cracks was produced by fretting, and EAD 2006–0365–E, superseding EAD E:\FR\FM\02JAP1.SGM 02JAP1 Federal Register / Vol. 73, No. 1 / Wednesday, January 2, 2008 / Proposed Rules 2006–0351–E, was published on 4 December 2006 to address the new situation. Further examination in the laboratory has allowed to establish that crack initiation was due to fatigue and the fretting was posterior. The above mentioned cracks, if not timely detected, could lead to reduced structural integrity of the aircraft. The proposed AD would require actions that are intended to address the unsafe condition described in the MCAI. DATES: We must receive comments on this proposed AD by February 1, 2008. ADDRESSES: You may send comments by any of the following methods: • Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments. • Fax: (202) 493–2251. • Mail: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC 20590. • Hand Delivery: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–40, 1200 New Jersey Avenue SE., Washington, DC, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. Examining the AD Docket You may examine the AD docket on the Internet at https:// www.regulations.gov; or in person at the Docket Operations office between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this proposed AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Operations office (telephone (800) 647–5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: Shahram Daneshmandi, Aerospace Engineer, International Branch, ANM– 116, FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, Washington 98057–3356; telephone (425) 227–1112; fax (425) 227–1149. SUPPLEMENTARY INFORMATION: mstockstill on PROD1PC66 with PROPOSALS Comments Invited We invite you to send any written relevant data, views, or arguments about this proposed AD. Send your comments to an address listed under the ADDRESSES section. Include ‘‘Docket No. FAA–2007–0372; Directorate Identifier 2007–NM–164–AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy VerDate Aug<31>2005 16:49 Dec 31, 2007 Jkt 214001 aspects of this proposed AD. We will consider all comments received by the closing date and may amend this proposed AD based on those comments. We will post all comments we receive, without change, to https:// www.regulations.gov including any personal information you provide. We will also post a report summarizing each substantive verbal contact we receive about this proposed AD. Discussion On February 16, 2007, we issued AD 2007–05–01, Amendment 39–14962 (72 FR 8610, February 27, 2007). That AD required actions intended to address an unsafe condition on the products listed above. The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Community, has issued EASA Emergency Airworthiness Directive (EAD) 2007–0108-E, dated April 18, 2007 (referred to after this as ‘‘the MCAI’’), to correct an unsafe condition for the specified products. The MCAI states: On 23 November 2006, Emergency Airworthiness Directive Nr. (number) 2006– 0351-E was published, requiring an inspection to be performed on C–212 aeroplanes having been used for Maritime Patrol or other similar low altitude operations, due to the fact that, after initial examination of the evidences of a recent C– 212 Maritime Patrol aircraft accident, cracks had been found in the centre wing lower skin at STA Y=1030. At the time of the accident, the aircraft had accumulated 17,000 flight hours and 7,300 flight cycles. The cracks were suspected to be caused by fatigue. A more detailed examination in the laboratory, led to think that the initiation of the fatigue cracks was produced by fretting, and EAD 2006–0365-E, superseding EAD 2006–0351-E, was published on 4 December 2006 to address the new situation. Further examination in the laboratory has allowed to establish that crack initiation was due to fatigue and the fretting was posterior. Additionally, given that some operators were reporting difficulties in performing the required inspections, a new procedure has been defined using High Frequency Eddy Currents. Finally, an inspection interval has been established to make the required inspections repetitive in the interim until a definitive solution is available. The subject element is identified in Ref. 1 (CASA C–212 Supplemental Inspection Document (SID) C–212–PV–02–SID) as a Principal Structural Element (PSE) with No. 57.212.06 and requested to be inspected at a threshold of 20,000 landings (subject to some operational constraints defined in Ref. 1) in accordance with the inspection method and sequence described in Ref. 2 (CASA C–212 Supplemental Inspection Procedures (SIP) C– 212–PV–02–SIP), Section 57–10–03. Ref. 1 document was made mandatory by DGAC-Spain Airworthiness directive Nr. 02/ PO 00000 Frm 00009 Fmt 4702 Sfmt 4702 81 88 (current status of that AD is revision 3, dated 4 February 2004). Inspection threshold as per AD 02/88 Rev. 3 remains valid and relevant inspections have to be performed in addition to the requirements of this Emergency Airworthiness Directive (EAD). The above mentioned cracks, if not timely detected, could lead to reduced structural integrity of the aircraft. This EAD [which supersedes EASA EAD 2006–0365–E], is intended to ensure that no other C–212 aircraft could be affected by this problem, by mandating a one time inspection of the subject area and a repetitive inspection thereafter, until the moment a definitive design solution will be available, in accordance with the requirements under the paragraph ‘‘Compliance’’ of this EAD. An additional inspection procedure, by using High Frequency Eddy Currents, has been introduced, which should be able to detect cracks with higher reliability. The corrective action includes repetitive inspections for cracks, and repair if necessary. We clarified the compliance times specified in paragraphs (f)(1)(i) and (f)(2)(i) of the existing AD to specify those times in terms of a threshold (e.g., 5,600 total flight hours, 2,400 total landings) and a grace period (e.g., within 6 months), whichever is latest. You may obtain further information by examining the MCAI in the AD docket. Relevant Service Information EADS–CASA has issued All Operator Letter 212–018, Revision 2, dated March 20, 2007. The actions described in this service information are intended to correct the unsafe condition identified in the MCAI. FAA’s Determination and Requirements of This Proposed AD This product has been approved by the aviation authority of another country, and is approved for operation in the United States. Pursuant to our bilateral agreement with the State of Design Authority, we have been notified of the unsafe condition described in the MCAI and service information referenced above. We are proposing this AD because we evaluated all pertinent information and determined an unsafe condition exists and is likely to exist or develop on other products of the same type design. Differences Between This AD and the MCAI or Service Information We have reviewed the MCAI and related service information and, in general, agree with their substance. But we might have found it necessary to use different words from those in the MCAI to ensure the AD is clear for U.S. operators and is enforceable. In making E:\FR\FM\02JAP1.SGM 02JAP1 82 Federal Register / Vol. 73, No. 1 / Wednesday, January 2, 2008 / Proposed Rules these changes, we do not intend to differ substantively from the information provided in the MCAI and related service information. We might also have proposed different actions in this AD from those in the MCAI in order to follow FAA policies. Any such differences are highlighted in a NOTE within the proposed AD. Costs of Compliance Based on the service information, we estimate that this proposed AD would affect about 33 products of U.S. registry. We also estimate that it would take about 8 work-hours per product to comply with the basic requirements of this proposed AD. The average labor rate is $80 per work-hour. Based on these figures, we estimate the cost of the proposed AD on U.S. operators to be $21,120, or $640 per product. mstockstill on PROD1PC66 with PROPOSALS 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 determined that this proposed AD would not have federalism implications under Executive Order 13132. This proposed AD would not have a substantial direct effect on the States, on the relationship between the national Government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify this proposed regulation: 1. Is not a ‘‘significant regulatory action’’ under Executive Order 12866; 2. Is not a ‘‘significant rule’’ under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); and 3. Will not have a significant economic impact, positive or negative, VerDate Aug<31>2005 16:49 Dec 31, 2007 Jkt 214001 on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. We prepared a regulatory evaluation of the estimated costs to comply with this proposed AD and placed it in the AD docket. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Safety. The Proposed Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 14 CFR part 39 as follows: PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The FAA amends § 39.13 by removing Amendment 39–14962 (72 FR 8610, February 27, 2007) and adding the following new AD: Construcciones Aeronauticas, S.A. (CASA): Docket No. FAA–2007–0372; Directorate Identifier 2007–NM–164–AD. Comments Due Date (a) We must receive comments by February 1, 2008. Affected ADs (b) The proposed AD supersedes AD 2007– 05–01, Amendment 39–14962. Applicability (c) This AD applies to Construcciones Aeronauticas, S.A., (CASA) Model C–212 airplanes; all series, all serial numbers; certificated in any category. Subject (d) Air Transport Association (ATA) of America Code 57: Wings. Reason (e) The mandatory continuing airworthiness information (MCAI) states: On 23 November 2006, Emergency Airworthiness Directive Nr. (number) 2006– 0351–E was published, requiring an inspection to be performed on C–212 aeroplanes having been used for Maritime Patrol or other similar low altitude operations, due to the fact that, after initial examination of the evidences of a recent C– 212 Maritime Patrol aircraft accident, cracks had been found in the centre wing lower skin at STA Y=1030. At the time of the accident, the aircraft had accumulated 17,000 flight hours and 7,300 flight cycles. The cracks were suspected to be caused by fatigue. A more detailed examination in the laboratory, led to think that the initiation of the fatigue cracks was produced by fretting, and EAD 2006–0365–E, superseding EAD PO 00000 Frm 00010 Fmt 4702 Sfmt 4702 2006–0351–E, was published on 4 December 2006 to address the new situation. Further examination in the laboratory has allowed to establish that crack initiation was due to fatigue and the fretting was posterior. Additionally, given that some operators were reporting difficulties in performing the required inspections, a new procedure has been defined using High Frequency Eddy Currents. Finally, an inspection interval has been established to make the required inspections repetitive in the interim until a definitive solution is available. The subject element is identified in Ref. 1 (CASA C–212 Supplemental Inspection Document (SID) C–212–PV–02–SID) as a Principal Structural Element (PSE) with No. 57.212.06 and requested to be inspected at a threshold of 20,000 landings (subject to some operational constraints defined in Ref. 1) in accordance with the inspection method and sequence described in Ref. 2 (CASA C–212 Supplemental Inspection Procedures (SIP) C– 212–PV–02–SIP), Section 57–10–03. Ref. 1 document was made mandatory by DGAC-Spain Airworthiness directive Nr. 02/ 88 (current status of that AD is revision 3, dated 4 February 2004). Inspection threshold as per AD 02/88 Rev. 3 remains valid and relevant inspections have to be performed in addition to the requirements of this Emergency Airworthiness Directive (EAD). The above mentioned cracks, if not timely detected, could lead to reduced structural integrity of the aircraft. This EAD [which supersedes EASA EAD 2006–0365–E], is intended to ensure that no other C–212 aircraft could be affected by this problem, by mandating a one time inspection of the subject area and a repetitive inspection thereafter, until the moment a definitive design solution will be available, in accordance with the requirements under the paragraph ‘‘Compliance’’ of this EAD. An additional inspection procedure, by using High Frequency Eddy Currents, has been introduced, which should be able to detect cracks with higher reliability. The corrective action includes repetitive inspections for cracks, and repair if necessary. Restatement of Requirements of AD 2007– 05–01: (f) Unless already done, do the following actions. (1) For airplanes used for maritime operations and all other airplanes on which the operator cannot positively determine that the airplanes have not been flown more than ten percent of flights at altitudes below 3,000 feet as of March 14, 2007 (the effective date of AD 2007–05–01): Perform a NonDestructive Inspection (NDI) and a complementary NDI for cracks at the applicable time specified in paragraph (f)(1)(i), (f)(1)(ii), or (f)(1)(iii) of this AD. Do the inspections as defined in EADS–CASA All Operator Letter 212–018, Revision 1, dated December 1, 2006; or Revision 2, dated March 20, 2007. As of the effective date of this AD, only Revision 2 may be used. – Note 1: For the purposes of this AD, the term ‘‘maritime operations’’ is defined as airplanes which are used for monitoring certain areas of water. E:\FR\FM\02JAP1.SGM 02JAP1 Federal Register / Vol. 73, No. 1 / Wednesday, January 2, 2008 / Proposed Rules mstockstill on PROD1PC66 with PROPOSALS (i) For airplanes having accumulated 5,600 flight hours or less, and 2,400 landings or less as of March 14, 2007: Perform the inspections before the accumulation of 5,600 total flight hours, or before the accumulation of 2,400 total landings, or within 6 months after March 14, 2007, whichever occurs latest. (ii) For airplanes having accumulated more than 5,600 flight hours but less than or equal to 8,000 flight hours, or more than 2,400 landings but less than or equal to 3,600 landings, as of March 14, 2007: Perform the inspections before the accumulation of 200 flight hours or 100 landings after March 14, 2007, whichever occurs first. (iii) For airplanes having accumulated more than 8,000 flight hours or more than 3,600 landings as of March 14, 2007: Perform the inspections within 14 days after March 14, 2007. (2) For airplanes other than those identified in paragraph (f)(1) of this AD: Perform the NDIs at the applicable time specified in paragraph (f)(2)(i), (f)(2)(ii), or (f)(2)(iii) of this AD. Do the inspections as defined in EADS–CASA All Operator Letter 212–018, Revision 1, dated December 1, 2006; or Revision 2, dated March 20, 2007. As of the effective date of this AD, only Revision 2 may be used. (i) For airplanes having accumulated 10,000 total flight hours or less, and 10,000 total landings or less as of March 14, 2007: Perform the inspections before the accumulation of 10,000 total flight hours, or before the accumulation of 10,000 total landings, or within 6 months after March 14, 2007, whichever occurs latest. (ii) For airplanes having accumulated more than 10,000 flight hours but less than or equal to 15,000 flight hours, or more than 10,000 landings but less than or equal to 15,000 landings, as of March 14, 2007: Perform the inspections before the accumulation of 200 flight hours or 100 landings after March 14, 2007, whichever occurs first. (iii) For airplanes having accumulated more than 15,000 flight hours or more than 15,000 landings as of March 14, 2007: Perform the inspections within 14 days after March 14, 2007. New Requirements of This AD: Actions and Compliance (g) Unless already done, do the following actions. (1) For airplanes identified in paragraph (f)(1) of this AD that have accumulated 5,600 flight hours or less, and 2,400 landings or less as of the effective date of this AD: Perform the inspections at the times specified in paragraphs (g)(1)(i) and (g)(1)(ii) of this AD. Do the inspections as defined in EADS– CASA All Operator Letter 212–018, Revision 2, dated March 20, 2007. (i) At the later of the times specified in paragraphs (g)(1)(i)(A) and (g)(1)(i)(B) of this AD: Perform a high frequency eddy current (HFEC) NDI for cracks. (A) Within 200 flight hours or 100 landings after the effective date of this AD, whichever occurs first. (B) Before the accumulation of 5,600 total flight hours or 2,400 total landings, whichever occurs first. VerDate Aug<31>2005 16:49 Dec 31, 2007 Jkt 214001 (ii) Repeat the inspections required by paragraphs (f)(1) and (g)(1)(i) of this AD before the accumulation of 8,000 total flight hours or 3,600 total landings, whichever occurs first, and thereafter at intervals not to exceed 600 flight hours or 250 landings, whichever occurs first. (2) For airplanes identified in paragraph (f)(1) of this AD that have accumulated more than 5,600 flight hours but less than or equal to 8,000 flight hours, or more than 2,400 landings but less than or equal to 3,600 landings, as of the effective date of this AD: Perform the inspections at the times specified in paragraphs (g)(2)(i) and (g)(2)(ii) of this AD. Do the inspections as defined in EADS– CASA All Operator Letter 212–018, Revision 2, dated March 20, 2007. (i) Within 200 flight hours or 100 landings after the effective date of this AD, whichever occurs first: Perform a HFEC NDI for cracks. (ii) Within 600 flight hours or 250 landings, whichever occurs first, after doing the inspection required by paragraph (g)(2)(i) of this AD: Perform the inspections required by paragraphs (f)(1) and (g)(2)(i) of this AD and repeat the inspections thereafter at intervals not to exceed 600 flight hours or 250 landings, whichever occurs first. (3) For airplanes identified in paragraph (f)(1) of this AD that are not subject to paragraph (g)(1) or (g)(2) of this AD: Perform the inspections at the times specified in paragraphs (g)(3)(i) and (g)(3)(ii) of this AD. Do the inspections as defined in EADS– CASA All Operator Letter 212–018, Revision 2, dated March 20, 2007. (i) Within 14 days after the effective date of this AD: Perform a HFEC NDI for cracks. (ii) Within 600 flight hours or 250 landings, whichever occurs first, after doing the inspection required by paragraph (g)(3)(i) of this AD: Perform the inspections required by paragraphs (f)(1) and (g)(3)(i) of this AD and repeat the inspections thereafter at intervals not to exceed 600 flight hours or 250 landings, whichever occurs first. (4) For airplanes identified in paragraph (f)(2) of this AD that have accumulated 10,000 flight hours or less, and 10,000 landings or less, as of the effective date of this AD: Perform the inspections at the times specified in paragraphs (g)(4)(i) and (g)(4)(ii) of this AD. Do the inspections as defined in EADS–CASA All Operator Letter 212–018, Revision 2, dated March 20, 2007. (i) Within 200 flight hours or 100 landings after the effective date of this AD, whichever occurs first: Perform a HFEC NDI for cracks. (ii) Repeat the inspections required by paragraphs (f)(2) and (g)(4)(i) of this AD before the accumulation of 15,000 total flight hours or 15,000 total landings, whichever occurs first, and thereafter at intervals not to exceed 4,500 flight hours or 4,500 landings, whichever occurs first. (5) For airplanes identified in paragraph (f)(2) of this AD that have accumulated more than 10,000 flight hours but less than or equal to 15,000 flight hours, or more than 10,000 landings but less than or equal to 15,000 landings, as of the effective date of this AD: Perform the inspections at the time specified in paragraphs (g)(5)(i) and (g)(5)(ii) of this AD. Do the inspections as defined in EADS–CASA All Operator Letter 212–018, Revision 2, dated March 20, 2007. PO 00000 Frm 00011 Fmt 4702 Sfmt 4702 83 (i) Within 200 flight hours or 100 landings after the effective date of this AD, whichever occurs first: Perform a HFEC NDI for cracks. (ii) Within 4,500 flight hours or 4,500 landings, whichever occurs first, after doing the inspection required by paragraph (g)(5)(i) of this AD: Perform the inspections required by paragraphs (f)(2) and (g)(5)(i) of this AD. Repeat the inspections thereafter at intervals not to exceed 4,500 flight hours or 4,500 landings, whichever occurs first. (6) For airplanes identified in paragraph (f)(2) of this AD that are not subject to paragraph (g)(4) or (g)(5) of this AD: Perform the inspections at the time specified in paragraphs (g)(6)(i) and (g)(6)(ii) of this AD. Do the inspections as defined in EADS– CASA All Operator Letter 212–018, Revision 2, dated March 20, 2007. (i) Within 14 days after the effective date of this AD: Perform a HFEC NDI for cracks. (ii) Within 4,500 flight hours or 4,500 landings, whichever occurs first, after doing the inspection required by paragraph (g)(6)(i) of this AD: Perform the inspections required by paragraphs (f)(2) and (g)(6)(i) of this AD, and repeat the inspection thereafter at intervals not to exceed 4,500 flight hours or 4,500 landings, whichever occurs first. (7) If any crack or loose rivet is detected during any inspection required by this AD, before further flight, repair using a method approved by either the Manager, International Branch, ANM–116, Transport Airplane Directorate, FAA; or the European Aviation Safety Agency (EASA) (or its delegated agent). Within 30 days after cracks are detected, or within 30 days after the effective date of this AD, whichever occurs later, send a detailed report of the first inspection findings (both positive and negative) of the inspections required by paragraph (f) of this AD to EADS–CASA for evaluation at the following address: EADS– CASA, Military Transport Aircraft Division, Integrated Customer Services, Technical Services, Avenida de Aragon 404, 28022Madrid, Spain; telephone 34–91–624–6306; fax 34–91–585–5505; E-mail: MTA, TechnicalService@casa.eads.net. In any case, a confirmation of the accomplishment of this inspection is required to be sent to EADS– CASA. FAA AD Differences Note 2: This AD differs from the MCAI and/or service information as follows: (1) Compliance Time: For certain airplanes, the compliance time required by the MCAI or service information for performing the HFEC inspections is before further flight; however, to avoid inadvertently grounding airplanes, this AD requires performing those inspections within 14 days after the effective date of this AD. (2) Repair: Although the MCAI or service information does not include a repair procedure for cracking, this AD requires the repair of any cracking per the FAA or EASA (or its delegated agent). Other FAA AD Provisions (h) The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, International E:\FR\FM\02JAP1.SGM 02JAP1 84 Federal Register / Vol. 73, No. 1 / Wednesday, January 2, 2008 / Proposed Rules Branch, ANM–116, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. Send information to ATTN: Shahram Daneshmandi, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, Washington 98057– 3356; telephone (425) 227–1112; fax (425) 227–1149. Before using any approved AMOC on any airplane to which the AMOC applies, notify your appropriate principal inspector (PI) in the FAA Flight Standards District Office (FSDO), or lacking a PI, your local FSDO. (2) Airworthy Product: For any requirement in this AD to obtain corrective actions from a manufacturer or other source, use these actions if they are FAA-approved. Corrective actions are considered FAA-approved if they are approved by the State of Design Authority (or their delegated agent). You are required to assure the product is airworthy before it is returned to service. (3) Reporting Requirements: For any reporting requirement in this AD, under the provisions of the Paperwork Reduction Act, the Office of Management and Budget (OMB) has approved the information collection requirements and has assigned OMB Control Number 2120–0056. Related Information (i) Refer to MCAI EASA Emergency Airworthiness Directive 2007–0108–E, dated April 18, 2007, and EADS–CASA All Operator Letter 212–018, Revision 2, dated March 20, 2007, for related information. Issued in Renton, Washington, on December 19, 2007. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E7–25481 Filed 12–31–07; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2007–0389; Directorate Identifier 2007–NM–222–AD] RIN 2120–AA64 Airworthiness Directives; Various Transport Category Airplanes Equipped With Auxiliary Fuel Tanks Installed in Accordance With Certain Supplemental Type Certificates Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Notice of proposed rulemaking (NPRM). mstockstill on PROD1PC66 with PROPOSALS AGENCY: SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD) for various transport category airplanes. This proposed AD would require VerDate Aug<31>2005 16:49 Dec 31, 2007 Jkt 214001 deactivation of Southeast Aero-Tek, Inc., auxiliary fuel tanks. This proposed AD results from fuel system reviews conducted by the manufacturer, which identified potential unsafe conditions for which the manufacturer has not provided corrective actions. We are proposing this AD to prevent the potential of ignition sources inside fuel tanks, which, in combination with flammable fuel vapors, could result in fuel tank explosions and consequent loss of the airplane. DATES: We must receive comments on this proposed AD by February 19, 2008. ADDRESSES: You may send comments by any of the following methods: • Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments. • Fax: 202–493–2251. • Mail: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue, SE., Washington, DC 20590. • Hand Delivery: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue, SE., Washington, DC 20590, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. Examining the AD Docket You may examine the AD docket on the Internet at https:// www.regulations.gov; or in person at the Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this proposed AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Office (telephone 800–647–5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: Robert Bosak, Aerospace Engineer, Propulsion and Services Branch, ACE– 118A, FAA, Atlanta Aircraft Certification Office, One Crown Center, 1895 Phoenix Boulevard, Suite 460, Atlanta, Georgia 30349; telephone (770) 703–6094; fax (770) 703–6097. SUPPLEMENTARY INFORMATION: Comments Invited We invite you to send any written relevant data, views, or arguments about this proposed AD. Send your comments to an address listed under the ADDRESSES section. Include ‘‘Docket No. FAA–2007–0389; Directorate Identifier 2007–NM–222–AD’’ at the beginning of your comments. We specifically invite PO 00000 Frm 00012 Fmt 4702 Sfmt 4702 comments on the overall regulatory, economic, environmental, and energy aspects of this proposed AD. We will consider all comments received by the closing date and may amend this proposed AD because of those comments. We will post all comments we receive, without change, to https:// www.regulations.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact we receive about this proposed AD. Discussion The FAA has examined the underlying safety issues involved in fuel tank explosions on several large transport airplanes, including the adequacy of existing regulations, the service history of airplanes subject to those regulations, and existing maintenance practices for fuel tank systems. As a result of those findings, we issued a regulation titled ‘‘Transport Airplane Fuel Tank System Design Review, Flammability Reduction and Maintenance and Inspection Requirements’’ (66 FR 23086, May 7, 2001). In addition to new airworthiness standards for transport airplanes and new maintenance requirements, this rule included Special Federal Aviation Regulation No. 88 (‘‘SFAR 88,’’ Amendment 21–78, and subsequent Amendments 21–82 and 21–83). Among other actions, SFAR 88 requires certain type design (i.e., type certificate (TC) and supplemental type certificate (STC) design approval) holders to substantiate that their fuel tank systems can prevent ignition sources in the fuel tanks. This requirement applies to design approval holders for large turbine-powered transport airplanes and for subsequent modifications to those airplanes. It requires them to perform design reviews and to develop design changes and maintenance procedures if their designs do not meet the new fuel tank safety standards. As explained in the preamble to the rule, we intended to adopt airworthiness directives to mandate any changes found necessary to address unsafe conditions identified as a result of these reviews. In evaluating these design reviews, we have established four criteria intended to define the unsafe conditions associated with fuel tank systems that require corrective actions. The percentage of operating time during which fuel tanks are exposed to flammable conditions is one of these criteria. The other three criteria address the failure types under evaluation: Single failures, single failures in E:\FR\FM\02JAP1.SGM 02JAP1

Agencies

[Federal Register Volume 73, Number 1 (Wednesday, January 2, 2008)]
[Proposed Rules]
[Pages 80-84]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E7-25481]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2007-0372; Directorate Identifier 2007-NM-164-AD]
RIN 2120-AA64


Airworthiness Directives; Construcciones Aeronauticas, S.A., 
(CASA) Model C-212 Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: We propose to adopt a new airworthiness directive (AD) for the 
products listed above that would supersede an existing AD. This 
proposed AD results from mandatory continuing airworthiness information 
(MCAI) originated by an aviation authority of another country to 
identify and correct an unsafe condition on an aviation product. The 
MCAI describes the unsafe condition as:

    On 23 November 2006, Emergency Airworthiness Directive (EAD) Nr. 
(number) 2006-0351-E was published requiring an inspection to be 
performed on C-212 aeroplanes having been used for Maritime Patrol 
or other similar low altitude operations, due to the fact that, 
after initial examination of the evidences of a recent C-212 
Maritime Patrol aircraft accident, cracks had been found in the 
centre wing lower skin at STA Y=1030. At the time of the accident, 
the aircraft had accumulated 17,000 flight hours and 7,300 flight 
cycles. The cracks were suspected to be caused by fatigue.
    A more detailed examination in the laboratory, led to think that 
the initiation of the fatigue cracks was produced by fretting, and 
EAD 2006-0365-E, superseding EAD

[[Page 81]]

2006-0351-E, was published on 4 December 2006 to address the new 
situation.
    Further examination in the laboratory has allowed to establish 
that crack initiation was due to fatigue and the fretting was 
posterior.
    The above mentioned cracks, if not timely detected, could lead 
to reduced structural integrity of the aircraft.

The proposed AD would require actions that are intended to address the 
unsafe condition described in the MCAI.

DATES: We must receive comments on this proposed AD by February 1, 
2008.

ADDRESSES: You may send comments by any of the following methods:
     Federal eRulemaking Portal: Go to https://
www.regulations.gov. Follow the instructions for submitting comments.
     Fax: (202) 493-2251.
     Mail: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE., Washington, DC 20590.
     Hand Delivery: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-40, 1200 New 
Jersey Avenue SE., Washington, DC, between 9 a.m. and 5 p.m., Monday 
through Friday, except Federal holidays.

Examining the AD Docket

    You may examine the AD docket on the Internet at https://
www.regulations.gov; or in person at the Docket Operations office 
between 9 a.m. and 5 p.m., Monday through Friday, except Federal 
holidays. The AD docket contains this proposed AD, the regulatory 
evaluation, any comments received, and other information. The street 
address for the Docket Operations office (telephone (800) 647-5527) is 
in the ADDRESSES section. Comments will be available in the AD docket 
shortly after receipt.

FOR FURTHER INFORMATION CONTACT: Shahram Daneshmandi, Aerospace 
Engineer, International Branch, ANM-116, FAA, Transport Airplane 
Directorate, 1601 Lind Avenue SW., Renton, Washington 98057-3356; 
telephone (425) 227-1112; fax (425) 227-1149.

SUPPLEMENTARY INFORMATION:

Comments Invited

    We invite you to send any written relevant data, views, or 
arguments about this proposed AD. Send your comments to an address 
listed under the ADDRESSES section. Include ``Docket No. FAA-2007-0372; 
Directorate Identifier 2007-NM-164-AD'' at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of this proposed AD. We 
will consider all comments received by the closing date and may amend 
this proposed AD based on those comments.
    We will post all comments we receive, without change, to https://
www.regulations.gov including any personal information you provide. We 
will also post a report summarizing each substantive verbal contact we 
receive about this proposed AD.

Discussion

    On February 16, 2007, we issued AD 2007-05-01, Amendment 39-14962 
(72 FR 8610, February 27, 2007). That AD required actions intended to 
address an unsafe condition on the products listed above.
    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Community, has issued EASA 
Emergency Airworthiness Directive (EAD) 2007-0108-E, dated April 18, 
2007 (referred to after this as ``the MCAI''), to correct an unsafe 
condition for the specified products. The MCAI states:

    On 23 November 2006, Emergency Airworthiness Directive Nr. 
(number) 2006-0351-E was published, requiring an inspection to be 
performed on C-212 aeroplanes having been used for Maritime Patrol 
or other similar low altitude operations, due to the fact that, 
after initial examination of the evidences of a recent C-212 
Maritime Patrol aircraft accident, cracks had been found in the 
centre wing lower skin at STA Y=1030. At the time of the accident, 
the aircraft had accumulated 17,000 flight hours and 7,300 flight 
cycles. The cracks were suspected to be caused by fatigue.
    A more detailed examination in the laboratory, led to think that 
the initiation of the fatigue cracks was produced by fretting, and 
EAD 2006-0365-E, superseding EAD 2006-0351-E, was published on 4 
December 2006 to address the new situation.
    Further examination in the laboratory has allowed to establish 
that crack initiation was due to fatigue and the fretting was 
posterior. Additionally, given that some operators were reporting 
difficulties in performing the required inspections, a new procedure 
has been defined using High Frequency Eddy Currents. Finally, an 
inspection interval has been established to make the required 
inspections repetitive in the interim until a definitive solution is 
available.
    The subject element is identified in Ref. 1 (CASA C-212 
Supplemental Inspection Document (SID) C-212-PV-02-SID) as a 
Principal Structural Element (PSE) with No. 57.212.06 and requested 
to be inspected at a threshold of 20,000 landings (subject to some 
operational constraints defined in Ref. 1) in accordance with the 
inspection method and sequence described in Ref. 2 (CASA C-212 
Supplemental Inspection Procedures (SIP) C-212-PV-02-SIP), Section 
57-10-03.
    Ref. 1 document was made mandatory by DGAC-Spain Airworthiness 
directive Nr. 02/88 (current status of that AD is revision 3, dated 
4 February 2004).
    Inspection threshold as per AD 02/88 Rev. 3 remains valid and 
relevant inspections have to be performed in addition to the 
requirements of this Emergency Airworthiness Directive (EAD).
    The above mentioned cracks, if not timely detected, could lead 
to reduced structural integrity of the aircraft. This EAD [which 
supersedes EASA EAD 2006-0365-E], is intended to ensure that no 
other C-212 aircraft could be affected by this problem, by mandating 
a one time inspection of the subject area and a repetitive 
inspection thereafter, until the moment a definitive design solution 
will be available, in accordance with the requirements under the 
paragraph ``Compliance'' of this EAD.
    An additional inspection procedure, by using High Frequency Eddy 
Currents, has been introduced, which should be able to detect cracks 
with higher reliability.

The corrective action includes repetitive inspections for cracks, and 
repair if necessary.

    We clarified the compliance times specified in paragraphs (f)(1)(i) 
and (f)(2)(i) of the existing AD to specify those times in terms of a 
threshold (e.g., 5,600 total flight hours, 2,400 total landings) and a 
grace period (e.g., within 6 months), whichever is latest. You may 
obtain further information by examining the MCAI in the AD docket.

Relevant Service Information

    EADS-CASA has issued All Operator Letter 212-018, Revision 2, dated 
March 20, 2007. The actions described in this service information are 
intended to correct the unsafe condition identified in the MCAI.

FAA's Determination and Requirements of This Proposed AD

    This product has been approved by the aviation authority of another 
country, and is approved for operation in the United States. Pursuant 
to our bilateral agreement with the State of Design Authority, we have 
been notified of the unsafe condition described in the MCAI and service 
information referenced above. We are proposing this AD because we 
evaluated all pertinent information and determined an unsafe condition 
exists and is likely to exist or develop on other products of the same 
type design.

Differences Between This AD and the MCAI or Service Information

    We have reviewed the MCAI and related service information and, in 
general, agree with their substance. But we might have found it 
necessary to use different words from those in the MCAI to ensure the 
AD is clear for U.S. operators and is enforceable. In making

[[Page 82]]

these changes, we do not intend to differ substantively from the 
information provided in the MCAI and related service information.
    We might also have proposed different actions in this AD from those 
in the MCAI in order to follow FAA policies. Any such differences are 
highlighted in a NOTE within the proposed AD.

Costs of Compliance

    Based on the service information, we estimate that this proposed AD 
would affect about 33 products of U.S. registry. We also estimate that 
it would take about 8 work-hours per product to comply with the basic 
requirements of this proposed AD. The average labor rate is $80 per 
work-hour. Based on these figures, we estimate the cost of the proposed 
AD on U.S. operators to be $21,120, or $640 per product.

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 determined that this proposed AD would not have federalism 
implications under Executive Order 13132. This proposed AD would not 
have a substantial direct effect on the States, on the relationship 
between the national Government and the States, or on the distribution 
of power and responsibilities among the various levels of government.
    For the reasons discussed above, I certify this proposed 
regulation:
    1. Is not a ``significant regulatory action'' under Executive Order 
12866;
    2. Is not a ``significant rule'' under the DOT Regulatory Policies 
and Procedures (44 FR 11034, February 26, 1979); and
    3. Will not have a significant economic impact, positive or 
negative, on a substantial number of small entities under the criteria 
of the Regulatory Flexibility Act.
    We prepared a regulatory evaluation of the estimated costs to 
comply with this proposed AD and placed it in the AD docket.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Safety.

The Proposed Amendment

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

PART 39--AIRWORTHINESS DIRECTIVES

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

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


Sec.  39.13  [Amended]

    2. The FAA amends Sec.  39.13 by removing Amendment 39-14962 (72 FR 
8610, February 27, 2007) and adding the following new AD:

Construcciones Aeronauticas, S.A. (CASA): Docket No. FAA-2007-0372; 
Directorate Identifier 2007-NM-164-AD.

Comments Due Date

    (a) We must receive comments by February 1, 2008.

Affected ADs

    (b) The proposed AD supersedes AD 2007-05-01, Amendment 39-
14962.

Applicability

    (c) This AD applies to Construcciones Aeronauticas, S.A., (CASA) 
Model C-212 airplanes; all series, all serial numbers; certificated 
in any category.

Subject

    (d) Air Transport Association (ATA) of America Code 57: Wings.

Reason

    (e) The mandatory continuing airworthiness information (MCAI) 
states:

    On 23 November 2006, Emergency Airworthiness Directive Nr. 
(number) 2006-0351-E was published, requiring an inspection to be 
performed on C-212 aeroplanes having been used for Maritime Patrol 
or other similar low altitude operations, due to the fact that, 
after initial examination of the evidences of a recent C-212 
Maritime Patrol aircraft accident, cracks had been found in the 
centre wing lower skin at STA Y=1030. At the time of the accident, 
the aircraft had accumulated 17,000 flight hours and 7,300 flight 
cycles. The cracks were suspected to be caused by fatigue.
    A more detailed examination in the laboratory, led to think that 
the initiation of the fatigue cracks was produced by fretting, and 
EAD 2006-0365-E, superseding EAD 2006-0351-E, was published on 4 
December 2006 to address the new situation.
    Further examination in the laboratory has allowed to establish 
that crack initiation was due to fatigue and the fretting was 
posterior. Additionally, given that some operators were reporting 
difficulties in performing the required inspections, a new procedure 
has been defined using High Frequency Eddy Currents. Finally, an 
inspection interval has been established to make the required 
inspections repetitive in the interim until a definitive solution is 
available.
    The subject element is identified in Ref. 1 (CASA C-212 
Supplemental Inspection Document (SID) C-212-PV-02-SID) as a 
Principal Structural Element (PSE) with No. 57.212.06 and requested 
to be inspected at a threshold of 20,000 landings (subject to some 
operational constraints defined in Ref. 1) in accordance with the 
inspection method and sequence described in Ref. 2 (CASA C-212 
Supplemental Inspection Procedures (SIP) C-212-PV-02-SIP), Section 
57-10-03.
    Ref. 1 document was made mandatory by DGAC-Spain Airworthiness 
directive Nr. 02/88 (current status of that AD is revision 3, dated 
4 February 2004).
    Inspection threshold as per AD 02/88 Rev. 3 remains valid and 
relevant inspections have to be performed in addition to the 
requirements of this Emergency Airworthiness Directive (EAD).
    The above mentioned cracks, if not timely detected, could lead 
to reduced structural integrity of the aircraft. This EAD [which 
supersedes EASA EAD 2006-0365-E], is intended to ensure that no 
other C-212 aircraft could be affected by this problem, by mandating 
a one time inspection of the subject area and a repetitive 
inspection thereafter, until the moment a definitive design solution 
will be available, in accordance with the requirements under the 
paragraph ``Compliance'' of this EAD.
    An additional inspection procedure, by using High Frequency Eddy 
Currents, has been introduced, which should be able to detect cracks 
with higher reliability.
The corrective action includes repetitive inspections for cracks, 
and repair if necessary.

Restatement of Requirements of AD 2007-05-01:

    (f) Unless already done, do the following actions.
    (1) For airplanes used for maritime operations and all other 
airplanes on which the operator cannot positively determine that the 
airplanes have not been flown more than ten percent of flights at 
altitudes below 3,000 feet as of March 14, 2007 (the effective date 
of AD 2007-05-01): Perform a Non-Destructive Inspection (NDI) and a 
complementary NDI for cracks at the applicable time specified in 
paragraph (f)(1)(i), (f)(1)(ii), or (f)(1)(iii) of this AD. Do the 
inspections as defined in EADS-CASA All Operator Letter 212-018, 
Revision 1, dated December 1, 2006; or Revision 2, dated March 20, 
2007. As of the effective date of this AD, only Revision 2 may be 
used. -

    Note 1: For the purposes of this AD, the term ``maritime 
operations'' is defined as airplanes which are used for monitoring 
certain areas of water.


[[Page 83]]


    (i) For airplanes having accumulated 5,600 flight hours or less, 
and 2,400 landings or less as of March 14, 2007: Perform the 
inspections before the accumulation of 5,600 total flight hours, or 
before the accumulation of 2,400 total landings, or within 6 months 
after March 14, 2007, whichever occurs latest.
    (ii) For airplanes having accumulated more than 5,600 flight 
hours but less than or equal to 8,000 flight hours, or more than 
2,400 landings but less than or equal to 3,600 landings, as of March 
14, 2007: Perform the inspections before the accumulation of 200 
flight hours or 100 landings after March 14, 2007, whichever occurs 
first.
    (iii) For airplanes having accumulated more than 8,000 flight 
hours or more than 3,600 landings as of March 14, 2007: Perform the 
inspections within 14 days after March 14, 2007.
    (2) For airplanes other than those identified in paragraph 
(f)(1) of this AD: Perform the NDIs at the applicable time specified 
in paragraph (f)(2)(i), (f)(2)(ii), or (f)(2)(iii) of this AD. Do 
the inspections as defined in EADS-CASA All Operator Letter 212-018, 
Revision 1, dated December 1, 2006; or Revision 2, dated March 20, 
2007. As of the effective date of this AD, only Revision 2 may be 
used.
    (i) For airplanes having accumulated 10,000 total flight hours 
or less, and 10,000 total landings or less as of March 14, 2007: 
Perform the inspections before the accumulation of 10,000 total 
flight hours, or before the accumulation of 10,000 total landings, 
or within 6 months after March 14, 2007, whichever occurs latest.
    (ii) For airplanes having accumulated more than 10,000 flight 
hours but less than or equal to 15,000 flight hours, or more than 
10,000 landings but less than or equal to 15,000 landings, as of 
March 14, 2007: Perform the inspections before the accumulation of 
200 flight hours or 100 landings after March 14, 2007, whichever 
occurs first.
    (iii) For airplanes having accumulated more than 15,000 flight 
hours or more than 15,000 landings as of March 14, 2007: Perform the 
inspections within 14 days after March 14, 2007.

New Requirements of This AD: Actions and Compliance

    (g) Unless already done, do the following actions.
    (1) For airplanes identified in paragraph (f)(1) of this AD that 
have accumulated 5,600 flight hours or less, and 2,400 landings or 
less as of the effective date of this AD: Perform the inspections at 
the times specified in paragraphs (g)(1)(i) and (g)(1)(ii) of this 
AD. Do the inspections as defined in EADS-CASA All Operator Letter 
212-018, Revision 2, dated March 20, 2007.
    (i) At the later of the times specified in paragraphs 
(g)(1)(i)(A) and (g)(1)(i)(B) of this AD: Perform a high frequency 
eddy current (HFEC) NDI for cracks.
    (A) Within 200 flight hours or 100 landings after the effective 
date of this AD, whichever occurs first.
    (B) Before the accumulation of 5,600 total flight hours or 2,400 
total landings, whichever occurs first.
    (ii) Repeat the inspections required by paragraphs (f)(1) and 
(g)(1)(i) of this AD before the accumulation of 8,000 total flight 
hours or 3,600 total landings, whichever occurs first, and 
thereafter at intervals not to exceed 600 flight hours or 250 
landings, whichever occurs first.
    (2) For airplanes identified in paragraph (f)(1) of this AD that 
have accumulated more than 5,600 flight hours but less than or equal 
to 8,000 flight hours, or more than 2,400 landings but less than or 
equal to 3,600 landings, as of the effective date of this AD: 
Perform the inspections at the times specified in paragraphs 
(g)(2)(i) and (g)(2)(ii) of this AD. Do the inspections as defined 
in EADS-CASA All Operator Letter 212-018, Revision 2, dated March 
20, 2007.
    (i) Within 200 flight hours or 100 landings after the effective 
date of this AD, whichever occurs first: Perform a HFEC NDI for 
cracks.
    (ii) Within 600 flight hours or 250 landings, whichever occurs 
first, after doing the inspection required by paragraph (g)(2)(i) of 
this AD: Perform the inspections required by paragraphs (f)(1) and 
(g)(2)(i) of this AD and repeat the inspections thereafter at 
intervals not to exceed 600 flight hours or 250 landings, whichever 
occurs first.
    (3) For airplanes identified in paragraph (f)(1) of this AD that 
are not subject to paragraph (g)(1) or (g)(2) of this AD: Perform 
the inspections at the times specified in paragraphs (g)(3)(i) and 
(g)(3)(ii) of this AD. Do the inspections as defined in EADS-CASA 
All Operator Letter 212-018, Revision 2, dated March 20, 2007.
    (i) Within 14 days after the effective date of this AD: Perform 
a HFEC NDI for cracks.
    (ii) Within 600 flight hours or 250 landings, whichever occurs 
first, after doing the inspection required by paragraph (g)(3)(i) of 
this AD: Perform the inspections required by paragraphs (f)(1) and 
(g)(3)(i) of this AD and repeat the inspections thereafter at 
intervals not to exceed 600 flight hours or 250 landings, whichever 
occurs first.
    (4) For airplanes identified in paragraph (f)(2) of this AD that 
have accumulated 10,000 flight hours or less, and 10,000 landings or 
less, as of the effective date of this AD: Perform the inspections 
at the times specified in paragraphs (g)(4)(i) and (g)(4)(ii) of 
this AD. Do the inspections as defined in EADS-CASA All Operator 
Letter 212-018, Revision 2, dated March 20, 2007.
    (i) Within 200 flight hours or 100 landings after the effective 
date of this AD, whichever occurs first: Perform a HFEC NDI for 
cracks.
    (ii) Repeat the inspections required by paragraphs (f)(2) and 
(g)(4)(i) of this AD before the accumulation of 15,000 total flight 
hours or 15,000 total landings, whichever occurs first, and 
thereafter at intervals not to exceed 4,500 flight hours or 4,500 
landings, whichever occurs first.
    (5) For airplanes identified in paragraph (f)(2) of this AD that 
have accumulated more than 10,000 flight hours but less than or 
equal to 15,000 flight hours, or more than 10,000 landings but less 
than or equal to 15,000 landings, as of the effective date of this 
AD: Perform the inspections at the time specified in paragraphs 
(g)(5)(i) and (g)(5)(ii) of this AD. Do the inspections as defined 
in EADS-CASA All Operator Letter 212-018, Revision 2, dated March 
20, 2007.
    (i) Within 200 flight hours or 100 landings after the effective 
date of this AD, whichever occurs first: Perform a HFEC NDI for 
cracks.
    (ii) Within 4,500 flight hours or 4,500 landings, whichever 
occurs first, after doing the inspection required by paragraph 
(g)(5)(i) of this AD: Perform the inspections required by paragraphs 
(f)(2) and (g)(5)(i) of this AD. Repeat the inspections thereafter 
at intervals not to exceed 4,500 flight hours or 4,500 landings, 
whichever occurs first.
    (6) For airplanes identified in paragraph (f)(2) of this AD that 
are not subject to paragraph (g)(4) or (g)(5) of this AD: Perform 
the inspections at the time specified in paragraphs (g)(6)(i) and 
(g)(6)(ii) of this AD. Do the inspections as defined in EADS-CASA 
All Operator Letter 212-018, Revision 2, dated March 20, 2007.
    (i) Within 14 days after the effective date of this AD: Perform 
a HFEC NDI for cracks.
    (ii) Within 4,500 flight hours or 4,500 landings, whichever 
occurs first, after doing the inspection required by paragraph 
(g)(6)(i) of this AD: Perform the inspections required by paragraphs 
(f)(2) and (g)(6)(i) of this AD, and repeat the inspection 
thereafter at intervals not to exceed 4,500 flight hours or 4,500 
landings, whichever occurs first.
    (7) If any crack or loose rivet is detected during any 
inspection required by this AD, before further flight, repair using 
a method approved by either the Manager, International Branch, ANM-
116, Transport Airplane Directorate, FAA; or the European Aviation 
Safety Agency (EASA) (or its delegated agent). Within 30 days after 
cracks are detected, or within 30 days after the effective date of 
this AD, whichever occurs later, send a detailed report of the first 
inspection findings (both positive and negative) of the inspections 
required by paragraph (f) of this AD to EADS-CASA for evaluation at 
the following address: EADS-CASA, Military Transport Aircraft 
Division, Integrated Customer Services, Technical Services, Avenida 
de Aragon 404, 28022-Madrid, Spain; telephone 34-91-624-6306; fax 
34-91-585-5505; E-mail: MTA, TechnicalService@casa.eads.net. In any 
case, a confirmation of the accomplishment of this inspection is 
required to be sent to EADS-CASA.

FAA AD Differences

    Note 2: This AD differs from the MCAI and/or service information 
as follows:
    (1) Compliance Time: For certain airplanes, the compliance time 
required by the MCAI or service information for performing the HFEC 
inspections is before further flight; however, to avoid 
inadvertently grounding airplanes, this AD requires performing those 
inspections within 14 days after the effective date of this AD.
    (2) Repair: Although the MCAI or service information does not 
include a repair procedure for cracking, this AD requires the repair 
of any cracking per the FAA or EASA (or its delegated agent).

Other FAA AD Provisions

    (h) The following provisions also apply to this AD:
    (1) Alternative Methods of Compliance (AMOCs): The Manager, 
International

[[Page 84]]

Branch, ANM-116, has the authority to approve AMOCs for this AD, if 
requested using the procedures found in 14 CFR 39.19. Send 
information to ATTN: Shahram Daneshmandi, Aerospace Engineer, 
International Branch, ANM-116, Transport Airplane Directorate, FAA, 
1601 Lind Avenue SW., Renton, Washington 98057-3356; telephone (425) 
227-1112; fax (425) 227-1149. Before using any approved AMOC on any 
airplane to which the AMOC applies, notify your appropriate 
principal inspector (PI) in the FAA Flight Standards District Office 
(FSDO), or lacking a PI, your local FSDO.
    (2) Airworthy Product: For any requirement in this AD to obtain 
corrective actions from a manufacturer or other source, use these 
actions if they are FAA-approved. Corrective actions are considered 
FAA-approved if they are approved by the State of Design Authority 
(or their delegated agent). You are required to assure the product 
is airworthy before it is returned to service.
    (3) Reporting Requirements: For any reporting requirement in 
this AD, under the provisions of the Paperwork Reduction Act, the 
Office of Management and Budget (OMB) has approved the information 
collection requirements and has assigned OMB Control Number 2120-
0056.

Related Information

    (i) Refer to MCAI EASA Emergency Airworthiness Directive 2007-
0108-E, dated April 18, 2007, and EADS-CASA All Operator Letter 212-
018, Revision 2, dated March 20, 2007, for related information.

    Issued in Renton, Washington, on December 19, 2007.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. E7-25481 Filed 12-31-07; 8:45 am]
BILLING CODE 4910-13-P
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