Results
2012-22-09: We are adopting a new airworthiness directive (AD) for the Sikorsky Aircraft Corporation (Sikorsky) Model S-92A helicopters. This AD requires inspecting the tail rotor (T/R) pylon for a loose or missing fastener, a crack, damage, or corrosion and adding an internal doubler to the aft shear deck tunnel assembly. This AD was prompted by the discovery of cracks in T/R pylons. The actions are intended to detect a loose or missing fastener, a crack, damage, or corrosion on the T/R pylon and, if present, to repair the T/R pylon and install a doubler on the aft shear deck tunnel assembly or to replace the T/R pylon and install a doubler on the aft shear deck tunnel assembly. The actions are intended to prevent failure of the T/R pylon or other T/R components, which could lead to the loss of control of the helicopter.
73-07-05: 73-07-05 McKINNON: Amdt. 39-1614. Applies to Model G-21 Series 73-07-05 McKinn Airplanes. Compliance required as indicated. Applicable to torque tube assemblies, Gruman Part Numbers 12755-1, 12756-1, 12757-1, and 12758-1, and the support tubes, Part Numbers 12725-1 and -2. A. Applicable to those torque tube and support tube assemblies having less than 6000 hours' time in service, or less than 7 years' life since re-manufacture: To prevent hazards in flight associated with the failure of the elevator or rudder torque tubes, unless already accomplished within the last eleven (11) months, visually inspect the external condition of the tubes within one (1) month after the effective date of this AD, and at intervals thereafter not to exceed twelve (12) months from last inspection. Tubes which are cracked or show evidence of corrosion must either be repaired or replaced in accordance with FAR Part 43 and Advisory Circular 43.13-1 prior to further flight. B. Applicable to those torque tube and support tube assemblies having more than 6000 hours' time in service, or more than 7 years since re-manufacture. Within the next year, unless already accomplished: (1) Visually inspect the support tubes, Part Numbers 12725-1 and -2 for corrosion. If corrosion is found, repair or replace in accordance with FAR Part 43 and Advisory Circular 43.13-1 before further flight. (2) Remove all bolted bellcranks, arms, and pedals from the torque tubes. Using visual and dye penetrant methods, or an FAA-approved equivalent inspection, inspect the parts removed from the torque tubes for corrosion and cracking. Repair and replace in accordance with FAR Part 43 and AC 43.13-1. (3) Discard elevator torque tube, Part Number 12755-1; rudder torque tube, Part Number 12756-1 and the L.H. and R.H. rudder pedal torque tubes, Part Numbers 12757-1 and 12758-1. Install new manufactured parts or fabricate replacement tubes in accordance with FAR 43 and AC 43.13-1 from new manufacture stock 2024-T3 (material specifications WW-T-700/3 or equivalent) in conformance with the above drawings taking special care to corrosion-proof the interior as well as the exterior surfaces of the tubes. (4) Re-assemble and re-initiate the visual inspection program per (A) until reaching the rebuild threshold per (B). C. Aircraft with badly corroded but uncracked torque tubes may be flown in accordance with FAR 21.197 to a base where a repair or replacement can be performed. D. Upon submission of substantiating data by an owner or operator through an FAA Maintenance Inspector, the Chief, Engineering and Manufacturing Branch, FAA Northwest Region, may adjust the repetitive inspection intervals specified in this AD. This supersedes Amendment 39-1525 (31 F.R. 13697), AD 72-20-04. This Amendment becomes effective on publication.
2012-22-11: We are adopting a new airworthiness directive (AD) for Bell Helicopter Textron (BHT) Model 412, 412EP, and 412CF helicopters. This AD requires a repetitive inspection of the collective lever for a crack, and if there is a crack, before further flight, replacing the collective lever with an airworthy collective lever. This AD was prompted by a reported failure of a collective lever. The actions are intended to detect a crack in the collective lever, which could lead to failure of the collective lever and subsequent loss of control of the helicopter.
99-20-12: This amendment adopts a new airworthiness directive (AD), applicable to MD Helicopters, Inc. Model 369D, 369E, 369FF, 500N, and 600N helicopters, that requires replacing the oil cooler blower bracket (bracket). This amendment is prompted by three reports of cracked brackets. The actions specified by this AD are intended to prevent failure of a bracket, loss of cooling of engine oil and transmission oil, and a subsequent forced landing.
67-19-04: 67-19-04 MARTIN: Amdt. 39-432, Part 39, Federal Register June 15, 1967. Applies to Type 202, 202A and 404 Airplanes Incorporating Engine Mount, P/N's A10100, A10100-9, 2021C11039-9, A16647-81, 404-5000004, 404-5000004-59, 404-5000005, or 404-5000005-29. Compliance required as indicated. To detect cracks and corrosion in the engine mounts, accomplish the following: (a) Within the next 100 hours' time in service after the effective date of this AD, unless already accomplished within the last 100 hours' time in service, and thereafter at intervals not to exceed 200 hours' time in service from the last inspection; visually inspect the engine mount tubular members and welds for cracks, using a glass of at least 10-power, or use an FAA- approved equivalent inspection. If a crack is found comply with (c) before further flight. (b) Within the next 250 hours' time in service after the effective date of this AD, unless already accomplished within the last 750 hours' time in service, and thereafter at intervals not to exceed 1000 hours' time in service from the last inspection, or one (1) year whichever occurs first, inspect the engine mount tubular members and welds for external and internal cracks and corrosion, using both Magnaflux and X-ray or FAA-approved equivalent inspections. Remove paint and sandblast the engine mount prior to inspecting, or use an FAA-approved equivalent method. The sandblasting operation should be limited to the removal of any light rust or other superficial discolorations as necessary to give a clean surface to conduct Magnaflux inspection. If a crack is found comply with (c) before further flight. Engine mounts inspected within the last 750 hours' time in service using Magnaflux and X-ray, or FAA-approved equivalent inspections, but without sandblasting need not be reinspected before 1000 hours' of time in service from such inspection. (c) If a crack is found in the weld metal or in any tube between welds, and the crack is parallel to the tube axis, repair or replace the cracked part in accordance with the procedures outlined in the latest FAA-approved revision of the applicable Martin structural repair manual, or with an FAA-approved equivalent repair, or replace the cracked part with a part of the same part number that has been inspected in accordance with (b) and found free of cracks and corrosion, or with an FAA-approved equivalent part. If a crack is found in any tube wall, and the crack is transverse to the tube axis, replace the entire engine mount with a part of the same part number that has been inspected in accordance with (b) and found free of cracks and corrosion, or with an FAA-approved equivalent part. If a crack is found which is not identified above, approval for continued use of the engine mount must be obtained from the Chief, Engineering and Manufacturing Branch, FAA Eastern Region. Substantiating data must be submitted along with the request. (d) The repetitive inspection interval specified in paragraph (a) may be increased to 350 hours' time in service, and the repetitive inspection interval specified in paragraph (b) may be increased to 2500 hours' time in service or two (2) years, whichever occurs first, on aircraft whose engine mounts are treated internally at the next required inspection with hot linseed oil. The liquid shall be applied through holes drilled therein, or by immersing the part in a bath of the liquid, or FAA-approved equivalent method. All excess holes must be closed with cadmium- plated or zinc-plated self-tapping screws. (e) Equivalent inspections and repairs may be approved by an FAA maintenance inspector. Equivalent parts, Structural Repair Manual revisions, and internal treatment methods specified in paragraph (d), must be approved by the Chief, Engineering and Manufacturing Branch, FAA Eastern Region. (f) Upon request with substantiating data submitted through an FAA Maintenance Inspector, the compliance timesspecified in this AD may be increased by the Chief, Engineering and Manufacturing Branch, FAA Eastern Region. This supersedes AD 66-12-01. This amendment effective June 20, 1967.
47-32-15: 47-32-15 SIKORSKY: (Was Mandatory Note 1 of AD-2H-1.) Applies to Model S-51 Helicopters. Compliance required prior to next flight. Inspect the chain and sprockets of the control system for an accumulation of excessive grease and foreign matter. Excessive grease and any foreign matter adhering to the chain and sprockets should be removed prior to the next flight in order to prevent possible malfunctioning of the flight control system. The recommended procedure as contained in the Sikorsky Service Information Circular No. 17 dated June 2, 1947, should be followed at the first disassembly of these parts.
2003-17-03 R1: We are revising an existing airworthiness directive (AD) for certain Piaggio Aero Industries S.p.A. Model P-180 airplanes. That AD currently requires replacement of any firewall shutoff or crossfeed valve with a serial number in a certain range even if it has been previously modified. The way the applicability was written includes valves that should not be affected and are not included in the referenced service information. This AD requires [[Page 67765]] the same actions as the current AD, but only affects those firewall shutoff valves referenced in the referenced service information. We are issuing this AD to clarify the affected parts required to correct the unsafe condition on these products.
97-21-08: This amendment adopts a new airworthiness directive (AD), applicable to General Electric Company CT58 series turboshaft engines, that requires removal from service of certain stage 1 and 2 forward cooling plates, and stage 2 aft cooling plates, and replacement with serviceable parts. This amendment is prompted by reports of certain cooling plates forged with contaminated alloy that could reduce the lives of the parts. The actions specified by this AD are intended to prevent cooling plate fracture, which could result in a contained engine failure, and an inflight engine shutdown.
2011-21-07 R1: We are revising an existing airworthiness directive (AD) for certain Bombardier Model CL-600-2B19 (Regional Jet Series 100 & 440) airplanes; all Model CL-600-2C10 (Regional Jet Series 700, 701, & 702) airplanes; all Model CL-600-2D15 (Regional Jet Series 705) airplanes; and all Model CL-600-2D24 (Regional Jet Series 900) airplanes. That AD currently requires replacing certain water accumulator assemblies having a certain part installed on the pitot and static lines of the air data computer (ADC). This new AD corrects an erroneous service document number and removes the other erroneously cited service document from that AD. This new AD was prompted by an error that was discovered in one service document number, and a determination that credit for accomplishing actions in another erroneously cited service document should be removed from that AD. We are issuing this AD to prevent pitot-static tubing from becoming partially or completely blocked by water, which could result in erroneous airspeed and altitude indications and consequent loss of control of the airplane.
75-17-36: 75-17-36 BALLOON WORKS, HOT AIR BALLOONS: Amendment 39-2326. Applies to Models Firefly 6, 6B, and 7 with burner S/N 510 through 562. Before next flight, accomplish the following or an equivalent approved by the Chief, Engineering and Manufacturing Branch, Southern Region. To avoid separation due to a possible brass nipple failure, install safety wire extending from each of the three corners of the bottom plate to the lower portion of the upper Rego valve body. Assure wires are uniformly tightened. Within the next five hours of time in service from the effective date of this AD, accomplish the following: 1. Disconnect main burner tubes from manifold. 2. Drill out nine rivets holding pan to the bottom plate. 3. Unhook three burner support springs. 4. Remove upper burner assembly from lower burner assembly. 5. Unscrew nuts to remove pilot light tubes. 6. Clamp square section of Rego valve in vise. 7. Unscrew and remove burner manifold. 8. Inspect nipple. If nipple is steel, reassemble the burner,* if nipple is brass, proceed through the following steps. 9. Unscrew nipple with pipe wrench. 10. Replace brass nipple with steel nipple, Balloon Works P/N A4032B. 11. Reassemble in the reverse order. Safety wire is not required after steel nipple is installed. *Use teflon tape or pipe dope type sealant on nipple threads. This amendment is effective August 13, 1975, and was effective on receipt for all recipients of the air mail letter dated July 24, 1975 which contained this amendment.
2012-22-06: We are adopting a new airworthiness directive (AD) for Aeronautical Accessories, Inc. (AAI) high landing gear forward crosstube assemblies (crosstubes) installed on Agusta S.p.A. (Agusta) Model AB412 and AB412EP; and Bell Helicopter Textron, Inc. (Bell) Model 205A, 205A-1, 205B, 212, 412, 412CF, and 412EP helicopters during production or based on a supplemental type certificate (STC). This AD requires counting and recording the total number of landings for the crosstubes, and inspecting the crosstubes and replacing them if a crack or other damage exists. This AD was prompted by two reports from the field of failed crosstubes. The actions are intended to prevent failure of a crosstube, collapse of the landing gear, and subsequent loss of control of the helicopter.
97-19-17: This amendment adopts a new airworthiness directive (AD), applicable to General Electric Company CT58 series turboshaft engines, that requires removal from service of certain compressor rear shafts, initial and repetitive inspections of specific critical rotating parts, and replacement if found cracked, until those parts are removed from service and replaced with improved design parts. This amendment is prompted by a stage 2 turbine wheel incident in 1993 which resulted in an increased awareness of small features on critical rotating parts which could affect part life. The actions specified by this AD are intended to prevent fatigue cracking on specific critical rotating parts, which could result in failure of the part, causing an uncontained engine failure and damage to the aircraft.
2012-16-13: We are adopting a new airworthiness directive (AD) for BRP- Powertrain GmbH & Co KG Rotax 912 F2; 912 F3; 912 F4; 912 S2; 912 S3; and 912 S4 reciprocating engines. This AD requires replacing the pressure side fuel hose on certain fuel pumps and inspecting the carburetors connected to those fuel pumps for contamination within 5 flight hours after the effective date of this AD. This AD was prompted by reports of fuel pumps having pressure side fuel hoses not meeting the design specification. We are issuing this AD to prevent pressure side fuel hose deterioration and contamination of the carburetor, which could result in an in-flight engine shutdown, forced landing and damage to the airplane.
69-02-02: 69-02-02 GENERAL ELECTRIC: Amendment 39-710. Applies to Type CJ805-3, -3A, -3B, -23, -23B, and -23C Turbojet Engines. Compliance required as indicated. Within the next 6,000 hours' time in service after the effective date of this AD or at the next compressor disassembly, whichever occurs first, unless already accomplished, replace the 12th, 13th, and 14th stage compressor discs with new ones as indicated below: Disc Stage G.E. P/N'S to be replaced New P/N 12 106R686P1 or 108R627P1 111R232P2 13 106R687P1 or 108R628P1 111R233P2 14 106R688P1 or 108R629P1 111R234P2 The information in this AD is similar to that contained in General Electric Service Bulletins (880) 72-253 and (990) 72-260 and Revisions Nos. 1 and 2. This amendment is effective February 14, 1969.
2012-21-16: We are adopting a new airworthiness directive (AD) for certain BAE SYSTEMS (OPERATIONS) LIMITED Model BAe 146 series airplanes and Model Avro 146-RJ series airplanes. This AD was prompted by hydraulic pipe ruptures in the center of the cabin resulting in passengers being contaminated with hydraulic fluid. This AD requires installing a hydraulic fluid containment system. We are issuing this AD to prevent harmful or hazardous concentrations of hydraulic fluid or hydraulic vapor from entering the passenger compartment, possibly resulting in injury to the passengers.
2012-21-17: We are adopting a new airworthiness directive (AD) for certain Airbus Model A320-214 and -232 airplanes. This AD was prompted by reports that medium-head fasteners were installed in lieu of shear-head fasteners on a certain upper panel, which manufacturer fatigue and damage tolerance analyses demonstrated could have an effect on panel fatigue life. This AD requires repetitive inspections for cracking of certain fasteners, and repairs if necessary. We are issuing this AD to detect and correct such cracking, which could result in the loss of structural integrity of the airplane.
2012-21-18: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model MD-90-30 airplanes. This AD was prompted by reports of fatigue cracks found in Stringer 11 at the outboard flap, inboard drive hinge at Station Xrs=164.000. This AD requires repetitive inspections for cracks in Stringer 11, and a splice repair if necessary; and repetitive post-repair inspections, and repair if necessary. We are issuing this AD to detect and correct such cracking, which could result in the wing structure not supporting the limit load condition, which could lead to loss of the structural integrity of the wing.
48-28-01: 48-28-01 TEMCO: Applies to All Models GC-1A and GC-1B Aircraft. I. Inspection required at each 20 hours operation until compliance with item II is made. Cracks are occurring in the last bulkhead (Station 185) of the fuselage at the bottom rudder hinge and stop fitting, and the bulkhead must be inspected for such cracks. If cracks are found, a repair must be made in accordance with item II. II. Compliance required not later than September 1, 1948. To preclude the possibility of a structural failure in the rear bulkhead of the fuselage, at the bottom rudder hinge and stop, a steel reinforcement must be made as follows: 1. If cracks are found in the bulkhead drill No. 50 (0.07 diameter) check holes at end of each crack. 2. Fabricate and install a steel reinforcement fitting as defined in TEMCO Drawing 11-213-5074. The Texas Engineering and Manufacturing Co., Inc., will furnish free of charge the steel reinforcement fitting described in item 2. (TEMCO Customer Service Maintenance Bulletin No. 26 covers this same subject.)
47-10-31: 47-10-31 LOCKHEED: (Was Service Note 1 of AD-763-3.) Applies to All Model 49 Serials Up to and Including 2088. At periods not to exceed 100 hours the webs of all landing gear torque arms should be examined closely at the knee bolt ends for the presence of cracks. When a nose gear arm is found to be cracked, it should be replaced with a new part. When either main gear arm is found to be cracked, the 283557 or 292132 aluminum alloy torque link assemblies on both main gears should be replaced with 293882 steel torque link assemblies. When Note 47-10-21 is complied with, this periodic inspection procedure for the main gear may be discontinued.
67-01-02: 67-01-02 GENERAL ELECTRIC: Amendment 39-332 as amended by Amendment 39-536 and Amendment 39-1085 is further amended by Amendment 39-2688. Applies to Model CT58-100-1, CT58-100-2, CT58-110-1, CT58-110-2, CT58-140-1, CT58-140-2, T58-GE-1 and T58-GE-5 Engines. Compliance required as indicated. To ensure adequate life limit margin for first stage compressor rotor discs, remove from service G.E. P/N's 37D400218P101, 37D400218P101 CEB #148, 37D400218P102, 37D400359P101, 37D400359P102, 3920T11P01, 3920T11P02, 5013T06P01, 5001T20P01, and 5001T20P02 as follows: (a) Discs with more than 9,700 cycles on October 15, 1970, prior to the accumulation of 200 additional cycles. (b) Discs with 9,700 cycles or less on October 15, 1970, before 9,900 cycles. For the purposes of this AD a cycle is considered as any engine operating sequence involving engine start, at least one acceleration to a power required for take off, and shutdown. Amendment 39-332 became effective December 29, 1966. Amendment 39-536 became effective January 9, 1968. Amendment 39-1085 became effective October 15, 1970. This amendment 39-2688 becomes effective August 24, 1976.
2012-21-19: We are adopting a new airworthiness directive (AD) for all Airbus Model A330-200 freighter series airplanes; Model A330-200 and - 300 [[Page 65813]] series airplanes; and Model A340-200 and -300 series airplanes. This AD was prompted by reports of ram air turbine (RAT) pump failure. This AD requires inspecting the RAT pump anti-stall valve for correct setting, re-identifying the RAT pump, performing a functional ground test of the RAT, and replacing the RAT pump or the RAT assembly with a serviceable part if necessary. We are issuing this AD to detect and correct malfunction of the RAT pump, which could lead to in-flight loss of the RAT-pump pressurization, possibly resulting in reduced control of the airplane.
2012-21-11: We are adopting a new airworthiness directive (AD) for certain Bombardier, Inc. Model CL-600-2B16 (CL-601-3A, CL-601-3R, and CL-604 Variants) airplanes. This AD was prompted by reports of deformation at the neck of the pressure regulator body on the oxygen cylinder and regulator assemblies (CRAs), and an electrical wiring harness in the area of the oxygen cylinder with no protective conduit sleeving. This AD requires inspecting to determine if certain oxygen pressure regulators are installed and replacing oxygen CRAs containing pressure regulators that do not meet the required material properties. This AD also requires inspecting for damaged wiring, and repairing or replacing wiring if necessary. We are issuing this AD to prevent rupture of the oxygen cylinder, which in the case of cabin depressurization, would lead to oxygen not being available when required; and to detect and correct unprotected wiring that could chafe against the oxygen system components or surrounding structure in the area, and lead to electrical arcing and an oxygen-fed fire.
69-17-03: 69-17-03 GENERAL ELECTRIC: Amdt. 39-824. Applies to General Electric Models CT58-100-1, CT58- 100-2, CT58-110-1, CT58-110-2, CT58-140-1, CT58-140-2, T58-GE-1 and T58-GE-5 engines, installed in Boeing Vertol 107 and Sikorsky S61 and S62 aircraft. To prevent failures of first and second stage turbine rotor discs remove from service General Electric part numbers listed below with more than 10,100 cycles at the time of receipt of this telegram, unless already accomplished. STAGE 1 DISCS STAGE 2 DISCS 278D978P002 278D979P002 37D400498P101 37D400499P101 37D400010P101 37D400004P102 37D400227P101 37D400228P102 37D400307P101 4002T96P01 4002T17P01 For the purposes of this airworthiness directive a cycle is considered as any engine operating sequence involving engine start, at least one acceleration to a power required for takeoff and shutdown. Since it was found that immediate corrective action was required, notice and public procedure thereon was impracticable and contrary to the public interest and good cause existed for making the airworthiness directive effective immediately as to all known U.S. operators of Boeing Vertol 107 and Sikorsky S61 and S62 aircraft with General Electric Engine Models CT58-100-1, CT58-100-2, CT58-110-1, CT58-110-2, CT58-140-1, CT58- 140-2, T58-GE-1 and T58-GE-5, by individual telegrams dated August 12, 1969. These conditions still exist and the airworthiness directive is hereby published in the FEDERAL REGISTER as an amendment to Section 39.13 of Part 39 of the Federal Aviation Regulations to make it effective as to all persons. This amendment becomes effective upon publication in the FEDERAL REGISTER for all persons except those to whom it was made effective immediately by telegram dated August 12, 1969.
76-03-07: 76-03-07 BEECH: Amendment 39-2515. Applies to Models 200 and A100-1 (Serial Numbers BB-2 through BB-58) airplanes. Compliance: Required as indicated, unless already accomplished. To preclude loss of rudder control, within the next 50 hours' time in service after the effective date of this AD, accomplish the following: A) Inspect the P/N 101-524062-1 aft rudder push rod assembly for loose rivets securing the adapters to the aluminum tube in accordance with Beechcraft Service Instruction 0778-153, dated January, 1976, or later approved revisions. Replace any aft rudder push rod assembly having this condition with airworthy P/N 101-524062-1 aft rudder push rod assembly or P/N 101-524265-1 aft rudder push rod assembly. B) If a loose rivet or other defect is found as a result of the inspection required herein provide the FAA with written notification thereof utilizing Malfunction and Defect Report (FAA Form 8330-2) describing the condition and giving the total operating time on the airplane or part at the time of discovery (Reporting approved by the Office Management and Budget under OMB No. 04-R0174). C) Aircraft may be flown in accordance with FAR 21.197 to a location where this AD may be accomplished. D) Any equivalent method of compliance with this AD must be approved by the Chief, Engineering and Manufacturing Branch, FAA, Central Region. This amendment becomes effective February 20, 1976.
93-10-07: 93-10-07 TEXTRON LYCOMING: Amendment 39-8587. Docket 91-ANE-53. Applicability: Textron Lycoming ALF502R and ALF502L series turbofan engines installed on but not limited to British Aerospace BAe-146 and Canadair Challenger CL-600 aircraft. Compliance: Required as indicated, unless accomplished previously. To prevent corrosion and cracking of the third stage compressor disks, that could result in engine failure, accomplish the following: (a) Repair and mark, or replace, third stage compressor disks, Part Number (P/N) 2-101-263-02, P/N 2-101-263-05, P/N 2-101-263-09, P/N 2-101-263-R10, or third stage disk assemblies P/N 2-101-630-04, P/N 2-101-630-05, P/N 2-101-630-08; at the next part exposure, after the effective date of this AD, but no later than, 7,500 cycles since new, in accordance with Textron Lycoming Service Bulletin No. ALF502R 72-259, dated August 13, 1991, or Service Bulletin No. ALF502L 72-259, dated August 13, 1991, as applicable. (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, 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. (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 repairing and marking, or replacement shall be done in accordance with the following Textron Lycoming service bulletins: Document No. Pages Date ALF502R 72-259 1-5 August 13, 1991 Total pages: 5 ALF502L 72-259 1-5 August 13, 1991 Total Pages: 5 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 Textron Lycoming, Stratford Division, 550 Main Street, Stratford, CT 06497-7593. 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. (e) This amendment becomes effective on August 10, 1993.