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2001-07-07: This amendment supersedes an existing airworthiness directive (AD), applicable to all Fokker Model F.28 Mark 0070 and Mark 0100 series airplanes, that currently requires revising the Airplane Flight Manual (AFM) to provide the flightcrew with instructions not to arm the liftdumper system prior to commanding the landing gear to extend. For Model F.28 Mark 0100 series airplanes, the existing AD also requires modification of the grounds of the shielding of the wheelspeed sensor wiring of the main landing gear (MLG) and installation of new electrical grounds for the wheelspeed sensor channel of the anti-skid control box of the MLG. This amendment removes the previous revision of the AFM and requires a new limitation and a new warning. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to prevent inadvertent deployment of the liftdumpers during approach for landing or reduced brake pressure during low speed taxiing, and consequent reduced controllability and performance of the airplane.
2001-07-08: This amendment adopts a new airworthiness directive (AD) that is applicable to all McDonnell Douglas Model MD-11 series airplanes equipped with Pratt & Whitney Model PW4400 series engines. This action requires revising the Airplane Flight Manual (AFM) to advise the flight crew of applicable operational limits. This action is necessary to ensure that the flight crew is informed of applicable limitations in airplane performance, and to prevent reduced acceleration and climb performance relative to performance data in the AFM, which could result in the airplane overrunning the end of the runway during takeoff or landing, or impacting obstacles or terrain. This action is intended to address the identified unsafe condition.
93-01-10: 93-01-10 BRITISH AEROSPACE: Amendment 39-8464. Docket 92-NM-90-AD. Applicability: Model DH/HS/BAe 125 series airplanes equipped with Garrett engines; as listed in British Aerospace Service Bulletin SB.24-289-3267A,B,C,D,E, F & G, Revision 1, dated April 10, 1992; certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent battery overheating and/or damage of voltage sensitive avionics equipment, accomplish the following: (a) Within 180 days after the effective date of this AD, modify the Generator Control Circuit (GCU) circuitry in accordance with British Aerospace Service Bulletin SB.24-289-3267A,B,C,D,E,F & G, Revision 1, dated April 10, 1992. (b) An alternative method of compliance or adjustment of the compliance time that provides an acceptable level of safety may be used if approved by the Manager, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate. Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, Standardization Branch, ANM-113. NOTE: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Standardization Branch, ANM-113. (c) Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate the airplane to a location where the requirements of this AD can be accomplished. (d) The modification shall be done in accordance with British Aerospace Service Bulletin SB.24-289-3267A,B,C,D,E,F & G, Revision 1, dated April 10, 1992. (NOTE: The issue date of this British Aerospace Service Bulletin SB.24-289-326-7A,B,C,D,E,F & G is indicated only on "page 1 of 57"; no other page of this document is dated.) 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 British Aerospace, PLC, Librarian for Service Bulletins, P.O. Box 17414, Dulles International Airport, Washington, DC. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. (e) This amendment becomes effective on March 2, 1993.
47-10-22: 47-10-22 LOCKHEED: (Was Mandatory Note 24 of AD-763-3.) Applies to Model 49 Serials 1975, 1976, 1977, and 2021 Through 2065. Compliance required prior to March 1, 1947. Install steel retainer washer (American LaFranch P/N 2CD-3054C) in place of existing aluminum alloy retainer washer on fire extinguisher selector valve. (LAC Service Bulletin 49/SB-27 covers this same subject.)
2016-11-21: We are adopting a new airworthiness directive (AD) for Airbus Helicopters Model EC135P1, EC135P2, EC135P2+, EC135T1, EC135T2, and EC135T2+ helicopters. This AD requires reducing the life limit of certain parts and removing each part that has reached its life limit. The actions of this AD are intended to reduce the life limits of certain critical parts to prevent failure of a part and subsequent loss of control of the helicopter.
2001-07-05: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 767 series airplanes powered by General Electric or Pratt & Whitney engines, that requires repetitive inspections to detect discrepancies of the aft-most fastener holes in the horizontal tangs of the midspar fitting of the strut, and corrective actions, if necessary. This AD also provides an optional terminating action for the repetitive inspections. These actions are necessary to prevent fatigue cracking in primary strut structure and reduced structural integrity of the strut, which could result in separation of the strut and engine. This action is intended to address the identified unsafe condition.
68-01-01 R1: 68-01-01 R1 BRITISH AEROSPACE: Amendment 39-998 as amended by Amendment 39-5956. Applies to Model BAC 1-11 200 and 400 series airplanes. Compliance required within the next 50 hours time-in-service after the effective date of this AD, unless already accomplished. To prevent heat damage or fire in the airframe plenum of the auxiliary power unit (APU) installation, accomplish the following: A. For use of the APU on the ground, accomplish the following: 1. Visually check the fiberglass surround of the APU intake of the fuselage immediately behind the intake grill for evidence of heat discoloration. If evidence of heat is present, remove the non-return valve located in the APU air delivery duct, Part No. 525180, and replace with a serviceable Part No. 525180 or modified Part No. 1398B000, 1398B000/1398B999, or 3031B000. 2. Install a placard adjacent to the APU control panel in clear view of the pilot and amend the airplane flight manual limitations Section 2,to read as follows: "Close APU air delivery valve when starting an engine from an external supply or by cross-feeding air from an operating engine. Close APU air delivery valve and shut down APU for takeoff and flight operations." When all actions required by paragraph B., below, are accomplished, the placard may be removed or the foregoing amendment to the airplane flight manual should be deleted, as appropriate. 3. Remove all APU plenum chamber sound proofing. B. For operational use of the APU in flight, accomplish the following: 1. Remove non-return valve, Part No. 525180, located in the APU air delivery duct and replace with non-return valve, Part No. 1398B000, 1398B000/1398B999, or 3031B000, in accordance with British Aerospace BAC 1-11 Service Bulletins 36-PM3254 or 36-PM4912. 2. Perform the following modifications in accordance with British Aerospace BAC 1-11 Service Bulletin 53-PM3148: a. Install additional fire-proof, stainless steel skin overexisting light alloy outer skin on top of the fuselage, between Stations 936 and 958 to isolate the APU plenum chamber from the fin structure. b. Replace the light alloy wall separating the APU plenum chamber from the hydraulic compensator unit compartment by installing a stainless steel wall enlarging the hydraulic compensator box and replacing light alloy structural parts with stainless steel. c. Install revised spring loaded door in the bulkhead at Station 936 and modify the hydraulic compensator drain box and drain outlet. 3. Install sealing plates around the control guard, located above the rudder power control units, and over the hole in the fin rear spar, to provide restriction to the airflow into the fin, in accordance with British Aerospace BAC 1-11 Service Bulletin 55-PM3177. 4. Install an additional bi-metallic temperature sensor in parallel with the existing mercury sensor in circuitry for controlling the electrically actuated primary temperaturevalve located in the low pressure bleed flow duct to the heat exchanger, in accordance with British Aerospace BAC 1-11 Service Bulletin 21-PM 2780A, or install Graviner bi-metallic sensor in accordance with BAC 1-11 Modification 21-PM-2545 Part A. 5. Perform a magnetic check to identify "felt metal" jet pipe installed on the APU manufactured from type "430" stainless steel post PM 209 in accordance with British Aerospace BAC 1-11 Service Bulletin 49-A-PM3313. Thoroughly inspect the jet pipes thus identified for cracks adjacent to the weld. Replace cracked pipes with serviceable pipes manufactured from 430 or 347 material. Jet pipes identified as manufactured from "430" stainless steel and found by inspection to be in a serviceable condition, may continue in operation provided that the inspection is performed thereafter at intervals not to exceed 160 hours time in service. Type "430" jet pipes must be removed from service upon accumulating 3,000 hours time in service. 6.Add a new paragraph at the end of Section 2, Page 15, of the BAC 1-11 airplane flight manual entitled "APU Supply and Air Conditioning," to read as follows: "The following limitations on the use of the APU air supply and integrated air system shall be observed to limit the time of exposure of the common duct to the simultaneous delivery of air from the engines and the APU. a. Whenever an engine is being started by air from an external supply or by cross-feeding air from the other engine, the APU air delivery valve shall be closed. b. When one or both engines are running and the APU is supplying air for both air conditioning systems, the master valve switch for each system must be set to APU. If the APU is only supplying air for one system, the master valve switch for that system must be set to APU and, for the system not in use, the master valve switch must be set to CLOSE and isolation valve switch must be set to CLOSE. c. After take-off and whenchanging the source of supply from the APU to the engines, the APU air delivery valve switch must be set to CLOSE immediately on completion of the change-over drill. Refer to Section 4." 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 may add any comments 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 for the accomplishment of the modifications required by 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, Inc., 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 Seattle Aircraft Certification Office, 9010 East Marginal Way South, Seattle, Washington. This Amendment, 39-5956, revises AD 68-01-01, Amendment 39-998. This Amendment, 39-5956, becomes effective July 18, 1988.
2001-07-01: This amendment adopts a new airworthiness directive (AD) that applies to certain DG Flugzeugbau GmbH (DG Flugzeugbau) Model DG-800B sailplanes. This AD requires you to install an additional filter for the primer valve; inspect and align the exhaust system; modify the placement of the fuel lines if the fuel filter is installed at the front mounting point of the spindle drive; and secure the gas strut piston rod end using Loctite if the piston rod does rotate. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Germany. The actions specified by this AD are intended to prevent failure of the fuel line, exhaust system, and piston rod of the gas strut, which could result in failure of the engine. Such failure could lead to loss of power during critical stages of flight.
90-23-15: 90-23-15 GENERAL ELECTRIC COMPANY: Amendment 39-6754. Docket No. 89-ANE-06. Applicability: General Electric Company (GE) CF6-50/-45 series turbofan engines installed on, but not limited to, McDonnell-Douglas DC-10, Boeing 747, and Airbus A300 type aircraft. Compliance: Required as indicated, unless previously accomplished. To prevent turbine mid-frame (TMF) cracks which can cause the release of hot gas, increased nacelle temperature, activation of the fire warning system, and an inflight shutdown, accomplish the following: (a) Inspect the TMF, Part Numbers (P/N) 9128M52 and 9137M92 that do not incorporate GE CF6-50/- 45 Service Bulletin (SB) 72-973 or 72-975, in accordance with GE CF6-50/-45 SB 72-957, Revision 2, dated January 9, 1990, as follows: (1) Inspect TMF cases with 1,050 or greater cycles since new (CSN) on the effective date of this AD, at the next shop visit or prior to accumulating the next 450 cycles in service (CIS) after the effective date of this AD, whichever occurs first. (2) Inspect TMF cases with less than 1,050 CSN on the effective date of this AD, prior to accumulating 1,500 CSN. (3) Remove from service, prior to further flight, TMF cases which exceed the serviceable limits specified in Tables 1-4 inclusive of GE SB 72-957, Revision 2, dated January 9, 1990. (4) Thereafter, for TMF cases used in CF6-50 engines, reinspect cases with no cracks or indications at intervals not to exceed 600 CIS since previous inspection. Reinspect TMF cases with cracks or indications in accordance with the schedules and limits specified in Tables 1-4 inclusive of GE SB 72-957, Revision 2, dated January 9, 1990. (5) Thereafter, for TMF cases used exclusively in CF6-45 engines, reinspect cases with no cracks or indications at intervals not to exceed 750 CIS since previous inspection. Reinspect TMF cases with cracks or indications in accordance with the schedules and limits specified in Tables 1-4 inclusive of GE SB 72-957, Revision 2, dated January 9, 1990. (b) Inspect the TMF, P/N 9128M52 and 9137M92 that incorporate GE CF6-50/-45 SB 72-973, Revision 1, dated April 20, 1990, in accordance with GE CF6-50/-45 SB 72-957, Revision 2, dated January 9, 1990, as follows: (1) Inspect TMF cases prior to accumulating 6,000 CIS since incorporation of GE SB 72-973, Revision 1, dated April 20, 1990. (2) Remove from service, prior to further flight, TMF cases which exceed the serviceable limits specified in Tables 1-4 inclusive of GE SB 72-957, Revision 2, dated January 9, 1990. (3) Thereafter, for CF6-50/-45 engines, reinspect TMF cases with no cracks or indications at each engine shop visit, not to exceed 2,400 CIS since last inspection. Reinspect TMF cases with cracks or indications, in accordance with the schedules and limits specified in Tables 1-4 inclusive of GE SB 72-957, Revision 2, dated January 9, 1990. (c) Inspect the TMF, P/N 9128M52 and 9137M92 that incorporate GE CF6-50/-45 SB 72-975, dated December 11, 1989, in accordance with GE CF6-50/-45 SB 72-957, Revision 2, dated January 9, 1990, as follows: (1) For TMF cases used in CF6-50 engines, inspect cases prior to accumulating 1,200 CIS since incorporation of GE SB 72-975, dated December 11, 1989. Thereafter, reinspect TMF cases with no cracks or indications at each engine shop visit, not to exceed 1,200 CIS since last inspection. (2) For TMF cases used exclusively in CF6-45 engines, inspect cases prior to accumulating 1,500 CIS since incorporation of GE SB 72-975, dated December 11, 1989. Thereafter, reinspect TMF cases with no cracks or indications at each engine shop visit, not to exceed 1,500 CIS since last inspection. (3) Remove from service, prior to further flight, TMF cases which exceed the serviceable limits specified in Tables 1-4 inclusive of GE SB 72-957, Revision 2, dated January 9, 1990. (4) For CF6-50/-45 engines, reinspect TMF cases with cracks or indication in accordance with the schedules and limits specified in Tables 1-4 inclusive of GE SB 72-957, Revision 2, dated January 9, 1990. (d) Inspections previously performed in accordance with AD 90-06-07, are considered to be in compliance with the corresponding requirements of this AD. (e) For the purpose of this AD, shop visit is defined as the introduction of an engine into a shop for the conduct of engine maintenance. (f) For the purpose of this AD, applicable limits are those limits associated with the highest engine rating under which the TMF case has operated. (g) 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. (h) 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, Engine Certification Office, ANE-140, Engineand Propeller Directorate, Aircraft Certification Service, Federal Aviation Administration, New England Region, 12 New England Executive Park, Burlington, Massachusetts 01803. The initial and repetitive inspection program shall be done in accordance with the following GE documents: DOCUMENT PAGE REVISION DATE GE SB 72-957 All 2 Jan. 9, 1990 GE SB 72-973 All 1 April 20, 1990 GE SB 72-975 All Original Dec. 11, 1990 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 the General Electric Company, Technical Publications Department, 1 Neumann Way, Cincinnati, Ohio 45215. Copies may be inspected at the Regional Rules Docket, Office of the Assistant Chief Counsel, New England Region, 12 New England Executive Park, Room 311, Burlington, Massachusetts 01803, or at the office of the Federal Register, 1100 L Street, NW, Room 8301, Washington, D.C.20591. Airworthiness Directive 90-23-15 supersedes AD 90-06-07, Amendment 39-6449. This amendment (39-6754, AD 90-23-15) becomes effective on December 6, 1990.
94-07-05: 94-07-05 GENERAL ELECTRIC COMPANY: Amendment 39-8863. Docket No. 94-ANE-03. This amendment supersedes priority letter AD 93-10-09. Applicability: General Electric Company (GE) CT58-110 and -140 series turboshaft engines installed on but not limited to Boeing Vertol 107 series, and Sikorsky S61 and S62 series aircraft. Compliance: Required as indicated, unless accomplished previously. To prevent an uncontained engine failure and damage to the aircraft, accomplish the following: (a) For stage 1 turbine wheels, Part Number (P/N) 4002T17P01 and 4002T17P02, and stage 2 turbine wheels, P/N 4002T96P01 and 4002T96P02, that have not previously accomplished GE CT58 Service Bulletin (SB) No. A72-126 (CEB-206), Revision 1, dated December 5, 1969, inspect the wheels in accordance with paragraphs 2.A or 2.B; and 2.D, 2.E, and 2.F of GE CT58 SB No. A72-126 (CEB-206), Revision 2, dated August 31, 1993, as follows, or remove the wheels from service prior to August 1, 1994, andreplace with a serviceable part, whichever occurs earlier: (1) For wheels utilized in repetitive heavy lift (RHL) or external lift operation: (i) For wheels that have accumulated less than 500 hours time since new (TSN) on the effective date of this airworthiness directive (AD), inspect the wheels prior to accumulating 900 hours TSN. (ii) For wheels that have accumulated 500 hours TSN or more on the effective date of this AD, inspect the wheels at the next engine shop visit, or prior to accumulating 400 hours time in service (TIS) after the effective date of this AD, whichever occurs earlier. (2) For wheels utilized in non-RHL operation: (i) For wheels that have accumulated less than 1,500 hours TSN on the effective date of this AD, inspect the wheels prior to accumulating 2,000 hours TSN. (ii) For wheels that have accumulated 1,500 hours TSN or more on the effective date of this AD, inspect the wheels at the next engine shop visit, or prior toaccumulating 600 hours TIS after the effective date of this AD, whichever occurs earlier. (b) For stage 1 turbine wheel, P/N 4002T17P04, and stage 2 turbine wheel, P/N 4002T96P04, inspect the wheels in accordance with paragraphs 2.D and 2.E of GE CT58 SB No. A72-126 (CEB-206), Revision 2, dated August 31, 1993, and the inspection schedule outlined in paragraph (a)(1) and (a)(2) of this AD, as applicable, or remove the wheels from service prior to August 1, 1994, and replace with a serviceable part, whichever occurs earlier. (c) For wheels inspected in accordance with paragraph (a) of this AD, accomplish the following: (1) Prior to further flight, remove from service cracked wheels, wheels that do not meet the required web thickness limits, or wheels that have a cooling plate locating groove or channel (rabbet groove) radius less than 0.006 inches, and replace with a serviceable part. (2) Prior to further flight, mark wheels that have a rabbet groove radius of 0.006 inches or greater, by marking the part with the number "CEB 206, REV 2" in accordance with paragraph 2.H of GE CT58 SB No. A72-126 (CEB-206), Revision 2, dated August 31, 1993. (d) For wheels inspected in accordance with paragraph (b) of this AD, accomplish the following: (1) Prior to further flight, remove from service cracked wheels, and replace with a serviceable part. (2) Prior to further flight, mark wheels with the number "CEB 206, REV 2" in accordance with paragraph 2.H of GE CT58 SB No. A72-126 (CEB-206), Revision 2, dated August 31, 1993. (e) For stage 1 turbine wheels, P/N 4002T17P02 and 4002T17P04, and stage 2 turbine wheels, P/N 4002T96P02 and 4002T96P04, that have previously accomplished GE CT58 SB No. A72-126 (CEB-206), Revision 1, dated December 5, 1969, eddy current inspect (ECI) and fluorescent penetrant inspect (FPI) the wheels in accordance with GE CT58 SB No. A72-126 (CEB-206), Revision 2, dated August 31, 1993, as follows, or remove the wheels from service and replace with a serviceable part in accordance with paragraph (g)(1) or (g)(2) of this AD, as applicable, whichever occurs earlier: (1) For wheels utilized in RHL or external lift operation, inspect wheels in accordance with the inspection limits defined in Table 1 of GE CT58 SB No. A72-126 (CEB-206), Revision 2, dated August 31, 1993, or prior to 400 hours TIS after the effective date of this AD, whichever occurs later. (2) For wheels utilized in non-RHL operation, inspect wheels in accordance with the inspection limits defined in Table 1 of GE CT58 SB No. A72-126 (CEB-206), Revision 2, dated August 31, 1993, or prior to 600 hours TIS after the effective date of this AD, whichever occurs later. (f) For wheels inspected in accordance with paragraph (e) of this AD, accomplish the following: (1) Prior to further flight, remove from service cracked wheels, and replace with a serviceable part. (2) Prior to further flight, mark wheels with thenumber "CEB 206, REV 2" in accordance with paragraph 2.H of GE CT58 SB No. A72-126 (CEB-206), Revision 2, dated August 31, 1993. (g) For wheels marked in accordance with paragraph (c)(2), (d)(2), or (f)(2) of this AD: (1) For wheels that have a rabbet groove radius less than 0.013 inches, remove from service prior to August 1, 1994, and replace with a serviceable part. (2) For wheels that have a rabbet groove radius of 0.013 inches or greater, remove from service in accordance with the inspection limits defined in Table 1 of GE CT58 SB No. A72-126 (CEB-206), Revision 2, dated August 31, 1993, or prior to August 1, 1994, whichever occurs later, and replace with a serviceable part. (3) ECI and FPI wheels in accordance with GE CT58 SB No. A72-126 (CEB-206), Revision 2, dated August 31, 1993, as follows: (i) For wheels utilized in RHL or external lift operation, reinspect wheels at intervals not to exceed 1,000 hours TIS since the last inspection. (ii)For wheels utilized in non-RHL operation, reinspect wheels at intervals not to exceed 2,000 hours TIS since the last inspection. (iii) Prior to further flight, remove from service cracked wheels, and replace with a serviceable part. (h) Remove from service within 400 hours TIS after the effective date of this AD, stage 1 turbine wheels, P/N 278D978P002, 37D400498P101, 37D400307P101, 37D400010P101, 37D400227P101, 3018T97P02, 3018T97P03, and 3018T97P04; and stage 2 turbine wheels, P/N 278D979P002, 37D400499P101, 37D400228P102, 37D400004P102, 3018T98P01, 3018T98P02, 3018T98P03, and 3018T98P04, and replace with serviceable parts. (i) For the purpose of this AD, the following definitions apply: (1) An engine shop visit is defined as the induction of an engine into a shop for maintenance involving the separation of any major flange. (2) RHL operation is defined as more than ten lift-carry-drop cycles per hour TIS without landing, or more than ten takeoffs and landings per hour TIS. (3) External lift operation is defined as up to ten lift-carry-drop cycles per hour TIS without landing, or up to ten takeoffs and landings per hour TIS. (4) Non-RHL operation is defined as carrying passengers or internal cargo. (5) A serviceable part is defined as stage 1 turbine wheel, P/N 4002T17P02 TF3, and stage 2 turbine wheel, P/N 4002T96P02 TF3. (j) An alternative method of compliance or adjustment of the compliance time that provides an acceptable level of safety may be used if approved by the Manager, Engine 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, Engine Certification Office. NOTE: Information concerning the existence of approved alternative methods of compliance with this airworthiness directive, if any, may be obtained from the Engine Certification Office. (k) 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. (l) The inspection and replacement shall be done in accordance with the following service bulletin: DOCUMENT NO. PAGE REVISION DATE GE CT58 SB No. A72-126 (CEB-206) 1-28 2 August 31, 1993 Total Pages: 28. 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 General Electric Company, 1000 Western Ave., Lynn, MA 01910. Copies may be inspected at the FAA, New England Region, Office of the Assistant Chief Counsel, 12 New England Executive Park, Burlington, MA; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. (m) This amendment supersedes priority letter AD 93-10-09, issued May 20, 1993. (n) This amendment becomes effective on April 19, 1994.