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2002-03-04: This amendment adopts a new airworthiness directive (AD) that applies to all Pilatus Britten-Norman Limited (Pilatus Britten-Norman) BN-2, BN-2A,BN-2B, BN-2T, and BN2A MK. III series airplanes. This AD requires you to replace the emergency exit window sealant. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for the United Kingdom. The actions specified by this AD are intended to correct the problems with emergency exit windows failing to open. Such failure could lead to the inability to exit the airplane in an emergency.
2002-03-10: This amendment adopts a new airworthiness directive (AD), applicable to certain BAE Systems (Operations) Limited Model BAe 146 and Avro 146-RJ series airplanes, that requires repetitive inspections to detect cracking of the oleo strut of the nose landing gear (NLG), and corrective actions if necessary. This AD also provides for optional terminating action for the repetitive inspections. This action is necessary to detect and correct fatigue cracking of the oleo strut of the NLG, which could result in failure of the NLG. This action is intended to address the identified unsafe condition.
93-05-09: 93-05-09 ALLIED-SIGNAL INC., GARRETT ENGINE DIVISION: Amendment 39-8560. Docket No. 93-ANE-05. Supersedes AD 87-19-02, Amendment 39-5707, and priority letter AD 91-04-02, issued February 8, 1991. Applicability: Allied-Signal Inc., Garrett Engine Division, Model TPE331-1, -2, -2UA, -3U, -3UW, -5, -5A, -5AB, -5B, -6, and -6A turboprop and Model TSE331-3U turboshaft engines containing third stage turbine stator assemblies Part Number (P/N) 868379-1, -3, or -5. These engines are installed on but not limited to: Mitsubishi MU-2B series (MU-2 series); Construcciones Aeronauticas, S.A. (CASA) C-212 series; Fairchild SA226 series (Swearingen Merlin and Metro series); Prop-Jets, Inc. Model 400; Twin Commander 680 and 690 (Jetprop Commander); Rockwell Commander S-2R; Shorts Brothers and Harland, Ltd. SC7 (Skyvan); Dornier 228 series; Beech 18 and 45 series and Models JRB-6, 3N, 3NM, 3TM, and B100; Pilatus PC-6 series (Fairchild Porter and Peacemaker); De Havilland DH 104 series 7AXC (Dove); Ayres S-2R series; Grumman American G- 164 series; and Schweizer G-164 series airplanes; and Sikorsky S-55 series (Helitec Corp. S55T) helicopters. Compliance: Required as indicated, unless accomplished previously. To prevent an uncontained failure of the third stage turbine wheel, accomplish the following: (a) If the cycles in service (CIS) since new or rework of third stage turbine stator assemblies, P/N 868379-1 and -3, are unknown, convert hours time in service (TIS) to CIS by multiplying the hours TIS since new or rework upon receipt of this AD by 1.5 to get CIS since new or rework on the effective date of this AD. (b) Replace third stage turbine stator assemblies, P/N 868379-1 and -3, with new or reworked assemblies in accordance with the applicable Allied-Signal Inc., Garrett Engine Division, Engine Maintenance Manual, and the following schedule, based upon CIS: CIS since New or Rework on the effective date of this AD Replacement Schedule CIS unknown Replace within 50 CIS after the effective date of this AD. 5500 or more CIS Replace within 50 CIS after the effective date of this AD. 4000 to 5499 CIS Replace within 200 CIS after the effective date of this AD, but not more than 5550 CIS since new or rework, whichever occurs first. 3200 to 3999 CIS Replace within 400 CIS after the effective date of this AD, but not more than 4200 CIS since new or rework, whichever occurs first. Less than 3200 CIS Replace prior to accumulating 3600 CIS since new or rework. (c) During access to the third stage turbine stator assembly as required in paragraph (b) of this AD, remark all third stage turbine stator assemblies P/N 868379-1 as third stage turbine stator assemblies P/N 868379- 3, in accordance with the Accomplishment Instructions of Garrett Turbine Engine Company Alert Service Bulletin (ASB) No. TPE/TSE-331-A72-0384, Revision 3, dated July 1, 1987, or ASB No. TPE/TSE-331-A72- 0384, Revision 4, dated September 4, 1987.(d) Thereafter, replace third stage turbine stator assemblies, P/N 868379-1 and -3, with new or reworked assemblies in accordance with the applicable Allied-Signal Inc., Garrett Engine Division, Engine Maintenance Manual, at intervals not to exceed 3600 CIS since new or rework. (e) Replace third stage turbine stator assemblies, P/N 868379-5, with new or reworked assemblies in accordance with the applicable Allied-Signal Inc., Garrett Engine Division, Engine Maintenance Manual, and the following schedule: CIS since New or Rework on the effective date of this AD Replacement Schedule CIS unknown Replace within 50 CIS after the effective date of this AD. 900 or more CIS Replace within 50 CIS after the effective date of this AD. 450 to 899 CIS Replace within 150 CIS after the effective date of this AD, but not more than 950 CIS since new or rework, whichever occurs first. Less than 450 CIS Replace prior to accumulating 600 CIS since new or rework. (f) Thereafter, replace third stage turbine stator assemblies, P/N 868379-5, with new or reworked assemblies in accordance with the applicable Allied-Signal Inc., Garrett Engine Division, Engine Maintenance Manual, at intervals not to exceed 600 CIS since new or rework. NOTE: Additional information regarding the replacement of the stator assembly can be obtained from Allied- Signal, Inc., Garrett Engine Division, ASB No. TPE331-A72-0861, dated November 19, 1992. (g) For the purposes of this AD, rework of the third stage turbine stator assembly must include installation of a new inner seal support. (h) Perform a one-time X-ray inspection of all third stage turbine stator assemblies, P/N 868379-1 and -3, for weld penetration in accordance with the following schedule and replace, if necessary, in accordance with the Accomplishment Instructions of Garrett Turbine Engine Company ASB No. TPE331-A72-0559, dated July 1, 1987, ASB No. TPE331-A72-0559, Revision 1, dated September 4, 1987, or ASB No. TPE331-A72-0559, Revision 2, dated January 15, 1988, except those third stage turbine stator assemblies listed by serial number in Table 1 of those ASB's: Hours TIS since New on September 14, 1987 Inspection Schedule Unknown hours TIS Inspect within 200 hours TIS after September 14, 1987. 5001 or more hours TIS Inspect within 200 hours TIS after September 14, 1987. 4000 to 5000 hours TIS Inspect within 500 hours TIS after September 14, 1987, or prior to accumulating 5200 hours TIS since new, whichever occurs first. Less than 4000 hours TIS Inspect prior to accumulating 4500 hours TIS since new. NOTE: September 14, 1987, is the effective date of AD 87-19-02. (i) An alternative method of compliance or adjustment of the initial compliance time that provides an acceptable level of safety may be used if approved by the Manager, Los Angeles Aircraft Certification Office. The request should be forwarded through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, Los Angeles Aircraft Certification Office. NOTE: Information concerning the existence of approved alternative methods of compliance with this airworthiness directive, if any, may be obtained from the Los Angeles Aircraft Certification Office. (j) Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate the aircraft to a location where the requirements of this AD can be accomplished. (k) The remarking and one-time x-ray inspection shall be done in accordance with the following Garrett Turbine Engine Company Alert Service Bulletins: Document No. Pages Revision Date TPE/TSE331-A72-0384 total pages: 12 1-12 3 July 1, 1987 TPE/TSE331-A72-0384 1 4 September 4, 1987 2 3 July 1, 1987 3 4 September 4, 1987 total pages: 12 4-12 3 July 1, 1987 TPE331-A72-0559 total pages: 16 1-16 Original July 1, 1987 TPE331-A72-0559 1 1 September 4, 19872 Original July 1, 1987 3-4 1 September 4, 1987 5-6 Original July 1, 1987 7-14 1 September 4, 1987 total pages: 16 15-16 Original July 1, 1987 TPE331-A72-0559 1 2 January 15, 1988 2 Original July 1, 1987 3 1 September 4, 1987 4 2 January 15, 1988 5-6 Original July 1, 1987 total pages: 20 7-20 2 January 15, 1988 This incorporation by reference was approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR Part 51. Copies may be obtained from Garrett General Aviation Services Division, Distribution Center, 1944 East Sky Harbor Circle, Phoenix, Arizona 85034; telephone (602) 365-2548. Copies may be inspected at the FAA, New England Region, Office of the Assistant Chief Counsel, 12 New England Executive Park, Burlington, Massachusetts; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. (1) This amendment becomes effective on June 28, 1993, to all persons except those persons to whom it was made immediately effective by priority letter AD 93-05-09, issued March 8, 1993, which contained the requirements of this amendment.
89-17-06: 89-17-06 BRITISH AEROSPACE (BAE), PLC: Amendment 39-6294. Applicability: Model BAe/DH/BH/HS 125 series airplanes equipped with Garrett TFE731 engines, certificated in any category. Compliance: Required as indicated, unless previously accomplished. To prevent an electrical fire caused by grounding of certain electrical contractors, accomplish the following: A. Within 120 days after the effective date of this AD, inspect and modify Hartman electrical contractor components, in accordance with paragraph 2.A. of British Aerospace Service Bulletin 24-268-3223A&B, Revision 2, dated February 28, 1989. B. After the effective date of this AD, Hartman contractors which have Part Numbers A848MAS, A848KHS, or A848KSS shall not be installed on any airplane unless modified in accordance with paragraph 2.B. of British Aerospace Service Bulletin 24-268-3223A&B, Revision 2, dated February 28, 1989. C. An alternate means of compliance or adjustment of the compliance time,which provides an acceptable level of safety, may be used when approved by the Manager, Standardization Branch, ANM-113, FAA, Northwest Mountain Region. NOTE: The request should be forwarded through an FAA Principal Maintenance Inspector (PMI), who will either concur or comment and then send it to the Manager, Standardization Branch, ANM-113. D. Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base in order to comply with the requirements of this AD. All persons affected by this directive who have not already received the appropriate service documents from the manufacturer may obtain copies upon request to British Aerospace, PLC, Librarian for Service Bulletins, P.O. Box 17414, Dulles International Airport, Washington, D.C. 20041. These documents may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or at the Seattle Aircraft Certification Office, 9010 East Marginal Way South, Seattle, Washington. This amendment (39-6294, AD 89-17-06) becomes effective on September 15, 1989.
76-04-06: 76-04-06 BRITISH AIRCRAFT CORPORATION: Amendment 39-2523. Applies to BAC 1- 11 200 and 400 Series airplanes certificated in all categories. Compliance is required as indicated. To detect cracks in the horizontal stabilizer structure and prevent possible horizontal stabilizer failure, accomplish the following: (a) For airplanes equipped with horizontal stabilizers that do not incorporate the modification contained in Part (d) of British Aircraft Corporation Service Bulletin 55-PM3485, comply with paragraph (c) of this AD as follows: (1) If the horizontal stabilizer has accumulated less than 28,000 total landings on the effective date of this AD - (i) Prior to the accumulation of 30,000 total landings, inspect in accordance with paragraph (c) of this AD; (ii) Prior to the accumulation of 35,000 total landings, reinspect in accordance with paragraph (c) of this AD; and (iii) Thereafter, continue to inspect in accordance with paragraph (c) of this AD at intervals not to exceed 2500 landings since the last inspection. (2) If the horizontal stabilizer has accumulated 28,000 or more total landings but less than 30,000 total landings on the effective date of this AD - (i) Prior to the accumulation of an additional 1000 landings or 30,501 total landings, whichever occurs earlier, unless already accomplished within the preceding 1000 landings, inspect in accordance with paragraph (c) of this AD; (ii) Prior to the accumulation of 35,000 total landings, reinspect in accordance with paragraph (c) of this AD; and (iii) Thereafter, continue to inspect in accordance with paragraph (c) of this AD at intervals not to exceed 2500 landings since the last inspection. (3) If the horizontal stabilizer has accumulated 30,000 or more total landings but less than 32,000 total landings on the effective date of this AD - (i) Prior to the accumulation of an additional 500 landings or 32,101 total landings whichever occurs earlier, unless already accomplished within the preceding 2500 landings, inspect in accordance with paragraph (c) of this AD; (ii) Prior to the accumulation of 35,000 total landings reinspect in accordance with paragraph (c) of this AD; and (iii) Thereafter, continue to inspect in accordance with paragraph (c) of this AD at intervals not to exceed 2500 landings since the last inspection. (4) If the horizontal stabilizer has accumulated 32,000 or more total landings but less than 35,000 total landings on the effective date of this AD - (i) Prior to the accumulation of an additional 100 landings, unless already accomplished within the preceding 5000 landings, inspect in accordance with paragraph (c) of this AD; (ii) Prior to the accumulation of 35,000 total landings or 2500 landings from the last inspection, whichever occurs later, reinspect in accordance with paragraph (c) of this AD; and (iii) Thereafter,continue to inspect in accordance with paragraph (c) of this AD at intervals not to exceed 2500 landings since the last inspection. (5) If the horizontal stabilizer has accumulated 35,000 or more total landings on the effective date of this AD - (i) Prior to the accumulation of an additional 50 landings unless already accomplished within the preceding 2500 landings, inspect in accordance with paragraph (c) of this AD; and (ii) Thereafter, continue to inspect in accordance with paragraph (c) of this AD at intervals not to exceed 2500 landings since the last inspection. (b) For airplanes equipped with horizontal stabilizers that incorporate the modification contained in Part (d) of British Aircraft Corporation Service Bulletin 55-PM3485 comply with paragraph (c) of this AD as follows: (1) If the horizontal stabilizer has accumulated less than 39,000 total landings on the effective date of this AD - (i) Prior to the accumulation of 40,000 total landings, inspect in accordance with paragraph (c) of this AD. (ii) Thereafter, continue to inspect in accordance with paragraph (c) at intervals not to exceed 6000 landings since the last inspection. (2) If the horizontal stabilizer has accumulated 39,000 or more total landings on the effective date of this AD - (i) Prior to the accumulation of 1000 additional landings, unless already accomplished within the last 6000 landings, inspect in accordance with paragraph (c) of this AD. (ii) Thereafter, continue to inspect in accordance with paragraph (c) at intervals not to exceed 6000 landings since the last inspection. (c) Inspect the horizontal stabilizer structure for cracks in accordance with paragraphs 2.3.1, 2.3.2, and 2.3.3 of British Aircraft Corporation Alert Service Bulletin 55-A-PM 5208, Issue No. 1, dated November 14, 1974, or an FAA-approved equivalent. (d) If any cracks are found during an inspection required by paragraph (a) or (b) of this AD, before further flight, conduct the detailed inspection of the horizontal stabilizer structure in accordance with the applicable provisions of paragraphs 2.5 through 2.5.2 of British Aircraft Corporation Alert Service Bulletin 55-A-PM 5208, Issue No. 1, dated November 14, 1974, or an FAA-approved equivalent. (e) If, during an inspection required by paragraphs (a), (b), (d), or (e) of this AD, cracks are found only in the outboard channel brackets, accomplish the following: (1) Measure the cracks in accordance with the criteria specified in paragraphs 2.6.1. and 2.6.2. of British Aircraft Corporation Alert Service Bulletin 55-A-PM 5208, Issue No. 1, dated November 14, 1974. (2) If cracks measure, in length - (i) Less than 0.3 inches, reinspect the crack for crack propagation at intervals not to exceed 500 landings since the last inspection; (ii) 0.3 inches or more but less than 0.4 inches, reinspect the crack for crack propagation at intervals not to exceed 200 landings since the last inspection; and (iii) 0.4 inches or more but less than 0.5 inches, reinspect the crack for crack propagation at intervals not to exceed 100 landings since the last inspection. (3) Continue performing the inspections required by paragraphs (a), (b), and (d) of this AD. (f) If a crack if found in an outboard channel bracket that measures 0.5 inches or more in length or a crack of any length is found in any other component of the horizontal stabilizer during any of the inspections required by this AD, before further flight, except as provided in paragraph (g) of this AD, replace the component with a new part of the same part number or an FAA-approved equivalent. (g) Upon the request of an operator, the Chief, Aircraft Certification Staff, Europe, Africa and Middle East Region may adjust crack length limitations, approve alternate repetitive inspection intervals, or approve rework procedures to provide for continued operations by an operator, without the replacement of parts, as required under paragraph (f) of this AD, if data substantiating such action is submitted by the operator. (h) For the purpose of complying with this AD, subject to acceptance by the assigned FAA maintenance inspector, the number of landings may be determined by dividing each airplane's total hours' time in service by the operator's fleet average time from takeoff to landing for the airplane type. This amendment becomes effective March 4, 1976.
2017-24-06: We are adopting a new airworthiness directive (AD) for certain CFM International S.A. (CFM) LEAP-1A turbofan engines. This AD requires removal, inspection, rework, and re-identification of the high-pressure turbine (HPT) stage 2 disk, part number (P/N) 2466M52G03. This AD was prompted by a quality escape at the manufacturer that resulted in cracks appearing during forging of the HPT stage 2 disks. We are issuing this AD to address the unsafe condition on these products.
2002-03-06: This amendment supersedes an existing airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-9-81, -82, -83, and -87 series airplanes, Model MD-88 airplanes, and Model MD-90-30 series airplanes, that currently requires a revision to the applicable Airplane Flight Manual (AFM) to provide the flightcrew with the appropriate landing distance and flap positions, if applicable, for wet or icy runways. That AD also provides for an optional terminating action for the applicable AFM revision. For certain airplanes, this action requires accomplishment of the previously optional terminating action. The actions specified by this AD are intended to prevent the flightcrew from performing a scheduled landing on a runway of potentially insufficient length due to failure of the weight-on-wheels spoiler lockout mechanism system and possible inactivation of the autospoiler actuator, which could result in the airplane overrunning the end of the runway during landing on awet or icy runway.
89-23-12: 89-23-12 ALLISON GAS TURBINE DIVISION, GENERAL MOTORS CORPORATION (Allison, formerly Detroit Diesel Allison): Amendment 39-6345. Applicability: Allison Model 250-C28B and -C28C engines, with P/N 6898952 second stage turbine nozzle assembly, installed in aircraft certificated in any category except those with the following turbine assembly serial numbers: Engine Model Turbine Serial Number 250-C28B CAT 70498, CAT 70499 CAT 70502, CAT 70513 and subsequent 250-C28C CAT 28010 and subsequent Compliance: Required as indicated, unless already accomplished. To prevent failure of the second stage turbine nozzle which can lead to rubbing contact between the nozzle diaphragm and the second stage turbine wheel possibly resulting in an uncontained turbine wheel failure, accomplish the following: (a) Within the next 100 hours time-in-service after the effective date of this AD, or at the next turbine repair or overhaul, whichever occurs first, but not later thanNovember 30, 1989, perform the following: Modify and reidentify second stage turbine nozzle, P/N 6898952, into P/N 23001942, in accordance with Allison Commercial Engine Alert Bulletin CEB-A-72-2044, Revision 4, dated May 1, 1989. NOTE: Existing Model 250-C28B and -28C engines which have incorporated Allison Commercial Engine Alert Bulletin CEB-A-72-2044, Revision 4, dated May 1, 1989, or prior issues of CEB-72-2044, or engines which have incorporated P/N 23001942 are already in compliance with this AD. (b) Aircraft may be ferried in accordance with the provisions of FAR 21.197 and 21.199 to a base where the AD can be accomplished. (c) Upon submission of substantiating data by an owner or operator through an FAA Airworthiness Inspector, an alternate method of compliance with the requirements of this AD or adjustments to the compliance schedule specified in this AD may be approved by the Manager, Chicago Aircraft Certification Office, Federal Aviation Administration, 2300 East Devon Avenue, Des Plaines, Illinois 60018. The second stage turbine nozzle modification shall be done in accordance with Allison Commercial Engine Alert Bulletin CEB-A-72-2044, Revision 4, dated May 1, 1989. This incorporation by reference was approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR Part 51. Copies may be obtained from Allison Gas Turbine Division, General Motors Corporation, P.O. Box 420, Indianapolis, Indiana 46206-0420. Copies may be inspected at the Regional Rules Docket, Office of the Assistant Chief Counsel, Federal Aviation Administration, New England Region, 12 New England Executive Park, Room 311, Burlington, Massachusetts 01803, or at the Office of the Federal Register, 1100 L Street, N.W., Room 8301, Washington, D.C. 20591. This amendment (39-6345, AD 89-23-12) becomes effective on October 29, 1989.
91-15-23: 91-15-23 AEROSPATIALE: Amendment 39-7088. Docket No. 91-NM-29-AD. Applicability: Model Nord 262A series airplanes, certificated in any category. Compliance: Required as indicated, unless previously accomplished. To prevent reduced structural integrity of the fuselage, accomplish the following: A. For airplanes which are 20 years old or more since new as of the effective date of this AD: Within 2 years after the effective date of this AD, perform internal and external detailed visual inspections and a low frequency eddy current inspection of the fuselage skin panel junctions, in accordance with Aerospatiale N262-Fregate Service Bulletin 53-34, Revision 1, dated March 24, 1991. B. For airplanes which are less than 20 years old since new as of the effective date of this AD: Within 4 years after the effective date of this AD, perform internal and external detailed visual inspections and a low frequency eddy current inspection of the fuselage skin panel junctions, in accordance with Aerospatiale N262-Fregate Service Bulletin 53-34, Revision 1, dated March 24, 1991. C. If no corrosion is found as a result of the inspections required by paragraph A. or B. of this AD, accomplish the following: 1. At intervals not to exceed one year, perform an EXTERNAL visual inspection of the fuselage from Frame N to Frame 27, in accordance with Aerospatiale N262- Fregate Service Bulletin 53-34, Revision 1, dated March 24, 1991. 2. At intervals not to exceed 2 years, perform an INTERNAL visual inspection from Frame N to Frame 27, in accordance with Aerospatiale N262-Fregate Service Bulletin 53-34, Revision 1, dated March 24, 1991. 3. At intervals not to exceed 6 years, accomplish the following: a. NON-PRESSURIZED AREA: Perform internal and external detailed visual inspections of the circumferential and longitudinal skin panel junction from Frame N to Frame J and from Frame 21 to Frame 27, in accordance with the AccomplishmentInstructions, paragraph 2C(3)A of Aerospatiale N262-Fregate Service Bulletin 53-34, Revision 1, dated March 24, 1991. b. PRESSURIZED AREA: Perform internal and external detailed visual inspections of the circumferential and longitudinal fuselage skin panel junctions in accordance with the Accomplishment Instructions, paragraph 2C(3)A of Aerospatiale N262-Fregate Service Bulletin 53-34, Revision 1, dated March 24, 1991. D. If corrosion is found as a result of the inspections required by paragraph A., B., or C. of this AD, and the corrosion depth is equal to or less than 30 microns, accomplish one of the following: 1. Perform external visual inspections at intervals not to exceed one year, and low frequency eddy current inspections at intervals not to exceed 2 years, in accordance with Aerospatiale N262-Fregate Service Bulletin 53-34, Revision 1, dated March 24, 1991; or 2. Prior to further flight, repair in accordance with Scheme No. 1 (Preventative Measure Procedure without Removal of Panels) specified in Aerospatiale N262- Fregate Service Bulletin 53-35, Revision 1, dated March 24, 1991. Thereafter, repeat the visual and low frequency eddy current inspections at intervals not to exceed 6 years, in accordance with Aerospatiale N262-Fregate Service Bulletin 53-34, Revision 1, dated March 24, 1991; or 3. Prior to further flight, repair in accordance with Scheme No. 2 (Curative Measures Procedures with Removal of Panels) specified in Aerospatiale N262-Fregate Service Bulletin 53-35, Revision 1, dated March 24, 1991. This constitutes terminating action for the repetitive inspections of that area required by this AD. E. If corrosion is found as a result of the inspections required by paragraph A., B., or C. of this AD, and the corrosion depth is more than 30 microns but less than or equal to 100 microns, accomplish one of the following: 1. Prior to further flight, repair in accordance with Scheme No. 1 (Preventative Measure Procedure without Removal of Panels) specified in Aerospatiale N262- Fregate Service Bulletin 53-35, Revision 1, dated March 24, 1991. Thereafter, repeat the visual and low frequency eddy current inspections at intervals not to exceed 2 years, in accordance with Aerospatiale N262-Fregate Service Bulletin 53-34, Revision 1, dated March 24, 1991. 2. Prior to further flight, repair in accordance with Scheme No. 2 (Curative Measures Procedures with Removal of Panels) specified in Aerospatiale N262-Fregate Service Bulletin 53-35, Revision 1, dated March 24, 1991. This constitutes terminating action for the repetitive inspections for that area required by this AD. F. If corrosion is found as a result of the inspections required by paragraph A., B., or C. of this AD, and the corrosion depth is more than 100 microns, prior to further flight, repair in accordance with Scheme No. 2 (Curative Measures Procedures with Removal of Panels) specified in Aerospatiale N262-Fregate Service Bulletin 53-35, Revision 1, dated March 24, 1991. This constitutes terminating action for the repetitive inspections of that area required by this AD. G. An alternative method of compliance or adjustment of the compliance time, which provides an acceptable level of safety, may be used when approved by the Manager, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate. NOTE: The request should be forwarded through an FAA Principal Maintenance Inspector, who may concur or comment and then send it to the Manager, Standardization Branch, ANM-113. H. Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base in order to comply with the requirements of this AD. All persons affected by this directive who have not already received the appropriate service documents from the manufacturer may obtain copies upon request to Aerospatiale, 316 Route de Bayonne, 31060 Toulouse, Cedex 03, France. These documents may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 1601 Lind Avenue S.W., Renton, Washington. This amendment (39-7088, AD 91-15-23) becomes effective on August 26, 1991.
88-06-07: 88-06-07 GENERAL ELECTRIC: Amendment 39-5866. Applies to General Electric (GE) CF34-1A and -3A turbofan engines installed in the Canadair Limited Model CL-600-2A12 and CL-600-2B16 aircraft. Compliance is required as indicated, unless already accomplished. To prevent an engine flameout or uncommanded power roll-back and subsequent inflight shutdown due to contamination of the fuel control, accomplish the following: (a) For the engines not operated in accordance with Canadair Airplane Flight Manual (AFM) Temporary Revision Numbers 601/10-1 and 601/11 for Model CL-600-2B16, or Temporary Revision Numbers 601/17-1 and 601/18 for Model CL-600-2A12, accomplish the following prior to further flight after the effective date of this AD: (1) For engines with fuel controls identified in GE Service Bulletin (SB) Number (CF34) 73-5, dated January 22, 1988, replace the fuel control with a reworked unit which has a redesigned bypass valve piston installed and cleaned internally by the improved process, in accordance with this SB. (2) For engines with fuel controls identified in GE SB Number 73-6, dated January 22, 1988, replace the bypass valve piston with redesigned hardware in accordance with this SB. (b) For the engines operated in accordance with Canadair AFM Temporary Revisions Numbers 601/10-1 and 601/11 for Model CL-600-2B16, or Temporary Revision Numbers 601/17-1 and 601/18 for Model CL-600-2A12, accomplish paragraphs (a)(1) and (a)(2) above within 500 hours in service from the effective date of this AD, or prior to September 30, 1988, whichever occurs sooner. (c) Aircraft may be ferried in accordance with the provision of FAR 21.197 and 21.199 to a base where the AD can be accomplished. (d) Upon request, an equivalent means of compliance with the requirements of the AD may be approved by the Manager, Engine Certification Office, Aircraft Certification Division, Federal Aviation Administration, New England Region, 12 New England Executive Park, Burlington, Massachusetts 01803. (e) Upon submission of substantiating data by an owner or operator through an FAA maintenance inspector, the Manager, Engine Certification Office, New England Region, may adjust the compliance times specified in this AD. The GE SB's identified and described in this document are incorporated herein and made a part hereof pursuant to 5 U.S.C. 552(a)(1). All persons affected by this directive who have not already received the engine manufacturer's SB's may obtain copies upon request to General Electric Company, 1000 Western Avenue, Lynn, Massachusetts 01910. These documents also may be examined at the Office of the Regional Counsel, Federal Aviation Administration, New England Region, 12 New England Executive Park, Burlington, Massachusetts 01803, Room 311, Rules Docket Number 88-ANE-08, between the hours of 8:00 a.m. and 4:30 p.m., Monday through Friday, except federal holidays. This amendment becomes effective on March 23, 1988.