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88-14-02: 88-14-02 GLASER-DIRKS FLUGZEUGBAU GMBH: Amendment 39-5945. Applies to DG-100, all gliders with single piece canopy, up to Serial Number E195; DG-200 all gliders with single piece canopy; DG-300, Serial Numbers 3E1 through 3E175, certificated in any category. Compliance is required within the next 25 hours time-in-service after the effective date of this AD, unless already accomplished. To prevent failure of the canopy to release during an inflight emergency procedure, comply with the requirements of the Glaser-Dirks Technical Notes (TN's) as indicated below: (a) DG-100, must comply with Glaser-Dirks TN 301/14, dated June 24, 1986, paragraphs 1, 2, 3 and 5 ("Measures:"). (b) DG-200, must comply with Glaser-Dirks TN 323/6, dated June 24, 1986, paragraphs 1, 2, 3 and 5 ("Measures:"). (c) DG-300, must comply with Glaser-Dirks TN 359/9, dated June 24, 1986, paragraphs 1, 2, 3 and 5 ("Measures:"). (d) Upon request, an equivalent means of compliancewith the requirements of this AD may be approved by the Manager, Brussels Aircraft Certification Office, AEU-100, Europe, and Middle East Office, Federal Aviation Administration, c/o American Embassy, 15 Rue de La Loi B-1040 Brussels, Belgium; telephone 513.38.30 ext. 2710; or the Manager, New York Aircraft Certification Office, Federal Aviation Administration, New England Region, 181 South Franklin Avenue, Room 202, Valley Stream, New York 11581; telephone (516) 791-6680. (e) Upon submission of substantiating data by an owner or operator through an FAA Airworthiness Inspector, the Manager, Brussels Aircraft Certification Office, or the Manager, New York Aircraft Certification Office, may adjust the compliance time specified in this AD. Glaser-Dirks TN's No. 301/14, 323/6, and 359/9, all dated June 24, 1986, 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 havenot already received these documents may obtain copies from Glaser-Dirks Flugzeugbau GmbH, Im Schollengarten 19-20, D-7520 Bruchsal 4, Federal Republic of Germany. These documents may also 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 No. 88-ANE-24, between the hours of 8:00 a.m. and 4:30 p.m., Monday through Friday, except federal holidays. This amendment, 39-5945, becomes effective on June 30, 1988.
85-23-07: 85-23-07 KING RADIO CORPORATION: Amendment 39-5217. Applies to Models KFC 150, KAP 150 and KAP 100 autopilot systems which use the following flight computers and are certificated to the applicable requirements of Technical Standard Orders C9c and C52a (): \n\n\nMODEL\nPART NO.\nSERIAL NO. \nKC 190\n065-0055-00\nall serial numbers \n\n065-0055-01\nall serial numbers \n\n065-0055-02\n1474 and below \n\n065-0055-03\n10095 and below \nKC 191\n065-0054-00\nall serial numbers \n\n065-0054-01\nall serial numbers \n\n065-0054-02\n20754 and below \n\n065-0054-03\n30227 and below \n\n065-0054-04\n20754 and below \n\n065-0054-05\n30227 and below \nKC 192\n065-0042-00\nall serial numbers \n\n065-0042-01\nall serial numbers \n\n065-0042-02\n40614 and below \n\n065-0042-03\n50464 and below \n\n065-0042-04\n40614 and below \n\n065-0042-05\n50464 and below \n\n\t()\tUnits with serial numbers above those stated comply with this AD at the time of shipment from King Radio Corporation. \n\n\tCompliance: Required as indicated unless already accomplished. \n\n\tTo prevent undetected trim malfunctions that may result in significant mistrim conditions, accomplish the following: \n\n\t(a)\tFor affected flight computers not installed in an aircraft, prior to further use, modify the computer in accordance with the instructions contained in King Radio Corporation Alert Service Bulletin KC 190/191/192-9 dated November 6, 1985. \n\n\t(b)\tFor affected flight computers installed in the following airplanes: \n\n\nAIRCRAFT MAKE AND MODEL\nSTC NUMBER\n\n\nMooney M20J, M20K\nSA1561CE-D\nPiper PA-28RT-201, PA-28RT-201T\nSA1563CE-D\nPiper PA-28-161, PA-28-181, PA-28-236\nSA1565CE-D\nPiper PA-32-301, PA-32-301T\nSA1567CE-D\nCessna 172RG\nSA1568CE-D\nCessna U206G, TU206G (Landplane, \n\n Seaplane, and Amphibian)\nSA1569CE-D\nCessna 172P\nSA1570CE-D\nCessna R182, TR182\nSA1571CE-D\nPiper PA-32R-301, PA-32R-301T\nSA1572CE-D\nBeech A36, A36TC, B36TC\nSA1574CE-D\nPiper PA-34-200T, PA-34-220T\nSA1575CE-D\nCessna 182P, 182Q, 182R, T182\nSA1770CE-D\nCessna 172L S/N 17256631\nSA1772CE-D\nPiper PA-46-310P\nSA1778CE-D\nReims-Cessna FR182\nSA1783CE-D\nPartenavia AP68TP 300\nSA1784CE-D\nSOCATA TB20\nSA1785CE-D\nBeech F33A\nSA1789CE-D\nPartenavia P68C, P68C-TC\nSA1791CE-D\nReims-Cessna F182P, F182Q\nSA1794CE-D\nCessna 210R, T210R\nSA2050CE-D\n\n\t\t(1)\tWithin the next 10 hours time-in-service (TIS) after the effective date of this AD, deactivate the autopilot and electric trim by pulling the respective circuit breakers and banding by placing a tie wrap equivalent around the circuit breaker stem. \n\n\t\t(2)\tFabricate and install on the instrument panel in clear view of the pilot the following placard using letters of a minimum 0.10 inch in height: "AP AND ELECTRIC TRIM INOPERATIVE PER AD 85-23-07" and operate the aircraft accordingly. \n\n\t\t(3)\tWithin 50 hours TIS or 120 calendar days, whichever comes first, after the effective date of this AD, modify the flight computer in accordance with the instructions contained in King Radio Corporation Alert Service Bulletin KC 190/191/192-9 dated November 6, 1985. \n\n\t\t(4)\tThe requirements of paragraphs (b)(1) and (b)(2) of this AD may be accomplished by the holder of a pilot certificate issued under Part 61 of the Federal Aviation Regulations (FARs) on any airplane owned or operated by him. The person accomplishing these actions must make the appropriate aircraft maintenance record entry as prescribed by FAR 91.173. \n\n\t\t(5)\tThe requirements of paragraphs (b)(1) and (b)(2) of this AD are no longer required when paragraph (b)(3) of this AD has been accomplished. \n\n\t(c)\tFor affected flight computers installed in the following airplanes: \n\n\nAIRCRAFT MAKE AND MODEL\nSTC NUMBER \nPiper PA-60-700P\nSA1777CE-D \n\t\t(1)\tWithin the next 10 hours TIS after the effective date of this AD, deactivate the autopilot by pulling the respective circuit breaker and banding open by placing a tie wrap or equivalent around the circuit breaker stem.(2)\tFabricate and install on the instrument panel in clear view of the pilot the following placard using letters of a minimum 0.10 inch in height: "AP INOPERATIVE PER AD 85-23-07", and operate the aircraft accordingly. \n\n\t\t(3)\tWithin 50 hours TIS or 120 calendar days, whichever comes first, following the effective date of this AD, modify the flight computer in accordance with the instructions contained in King Radio Corporation Alert Service Bulletin KC190/191/192-9 dated November 6, 1985. \n\n\t\t(4)\tThe requirements of paragraphs (c)(1) and (c)(2) of this AD may be accomplished by the holder of a pilot certificate issued under Part 61 of the Federal Aviation Regulations (FARs) on any airplane owned or operated by him. The person accomplishing these actions must make the appropriate aircraft maintenance record entry as prescribed by FAR 91.173. \n\n\t\t(5)\tThe requirements of paragraphs (c)(1) and (c)(2) of this AD are no longer required when paragraph (c)(3) of this AD has been accomplished. \n\n\t(d)\tThe modification requirements of paragraphs (b)(3) and (c)(3) of this AD must be accomplished by an appropriate FAA certified radio repair station. \n\n\t(e)\tAircraft may be flown in accordance with Federal Aviation Regulation 21.197 to a location where this AD can be accomplished. \n\n\t(f)\tAn equivalent method of compliance with this AD, if used, must be approved by the Manager, Wichita Aircraft Certification Office, 1801 Airport Road, Room 100, Mid-Continent Airport, Wichita, Kansas 67209. \n\n\tAll persons affected by this directive may obtain copies of the documents referred to herein upon request to King Radio Corporation, 400 North Rogers Road, Olathe, Kansas 66062, or the FAA, Rules Docket, Office of the Regional Counsel, Room 1558, 601 East 12th Street, Kansas City, Missouri 64106. \n\n\tThis amendment becomes effective January 27, 1986, as to all persons except those persons to whom it was made immediately effective by priority letter AD 85-23-07, issued November 20, 1985, which contained this amendment.
2007-19-16: The FAA is superseding an existing airworthiness directive (AD), which applies to certain Boeing Model 747 series airplanes. That AD requires a one-time inspection for discrepancies of the potable water and drain lines in the cargo compartments, and corrective action if necessary. This new AD requires that the inspection be repetitively performed using new service information, until terminating action is done. This AD also removes certain airplanes from the applicability. This AD results from a report of a fire in the aft cargo compartment started by a potable water line heater tape. We are issuing this AD to prevent overheating of the heater tape on potable water fill and drain lines, which could ignite accumulated debris or contaminants on or near the potable water fill and drain lines, resulting in a fire in the airplane.
2001-07-09: This amendment supersedes an existing emergency airworthiness directive (AD) that applies to MD Helicopters Inc. (MDHI) Model MD-900 helicopters. That emergency AD requires, within 6 hours time-in-service (TIS), or before further flight after January 31, 2000, whichever occurs first, inspecting the main rotor upper hub assembly drive plate attachment flange (flange) and determining the torque of each flange nut (nut). If a crack is found, the hub assembly must be replaced before further flight. The emergency AD also requires, within 25 hours TIS or before further flight after January 31, 2000, whichever occurs first, inspecting the hub assembly and verifying that the torque on the nuts is correct. Replacing a cracked hub assembly with an airworthy hub assembly is required before further flight. This amendment requires the same actions as the existing emergency AD but removes the January compliance dates and corrects errors in the existing emergency AD. This amendment isprompted by the discovery that there are several errors in the emergency AD. The actions specified by this AD are intended to prevent failure of the hub assembly, loss of drive to the main rotor, and subsequent loss of control of the helicopter.
86-20-11: 86-20-11 PIPER AIRCRAFT CORPORATION: Amendment 39-5441. Applies to Model PA-44-180T (Serial Numbers 44-8107001 through 44-8207020) airplanes certificated in any category. Compliance: Required as indicated after the effective date of this AD, unless already accomplished. To prevent smoke in the cockpit and possibly complete electrical failure resulting from shorting of ammeter terminal posts, accomplish the following: (a) Within the next 50 hours time-in-service (TIS) after the effective date of this AD, replace both ammeters with Ammeter Replacement Kits, Piper Part No. 765-302: in accordance with the instructions contained in Piper Service Bulletin No. 847, dated August 28, 1986. (b) Airplanes may be flown in accordance with FAR 21.197 to a location where this AD can be accomplished. (c) An equivalent method of compliance if used, must be approved by the Manager, Atlanta Aircraft Certification Office, FAA, 1075 Inner Loop Road, College Park, Georgia 30337. All persons affected by this directive may obtain copies of the document(s) referred to herein upon request to Piper Aircraft Corp., 2926 Piper Drive, Vero Beach, Florida 32960; or the FAA, Rules Docket, Office of Regional Counsel, Room 1558, 601 East 12th Street, Kansas City, Missouri 64106. This amendment becomes effective on October 17, 1986.
85-06-04: 85-06-04 PIPER: Amendment 39-5021. Applies to all Models of J-3, J-4, J-5, PA-11, PA-12, PA-14, PA-15, PA-16, PA-17, PA-18, PA-18A, PA-20, and PA-22 series airplanes (all serial numbers) certificated in any category. \n\n\tCompliance: Required within the next 100 hours time-in-service after the effective date of this AD or at the next annual inspection, whichever occurs first, unless fuel tank quick drain valves have previously been installed except that the placard described in paragraph (e) must be installed in these airplanes. \n\n\tTo prevent engine stoppage or malfunction due to the accumulation of water or other contaminants in the fuel system, accomplish the following: \n\t\n\t(a)\tFor Models J-3, J-4 (S/N 4-1 through 4-1377, 4-1379 through 4-1384), PA-15 and PA-17 series airplanes with fuselage fuel tanks and 3/8 National Pipe Thread (NPT) drain boss: \n\n\t\t(1)\tDrain fuel tank. \n\n\t\t(2)\tRemove fuel tank drain plug, Piper Part Number 70151, from the lower aft portion of the fuel tank. \n\n\t\t(3)\tInstall elbow, Piper Part Number 458-883, (AN915-3D) reducer/adapter, Piper Part Number 453-618, (AN912-3D) and drain valve, Piper Part Number 22179-00 or FAA approved equivalents per Figure 1 of this AD. \n\n\t\t(4)\tInstall clear plastic tube 1/4 inch I.D. x 3/8 inch O.D. (Available from Piper Aircraft Corporation as P/N 189543 in one foot length increments.) The tubing shall be long enough to extend from the drain valve to a minimum of 1 inch below the lower fuselage skin. \n\n\t\t(5)\tAdd appropriate clamp to the tube at the drain valve and secure plastic tube to the existing fuel feed line and/or adjacent airplane structure. \n\n\t\t(6)\tRoute the tube clear of the rudder pedals or pilots feet and drill a 5/8 inch hole in the fuselage bottom skin near the centerline if the engine has two exhaust tailpipes or on the side opposite the engine exhaust tailpipe if it has only one. \n\n\t\t(7)\tInstall 3/8 inch I.D. grommet (AN931-6-10 or equivalent) in the lower fuselage skin where the clear plastic drain tube exits the fuselage. \n\n\t\t(8)\tAdd fuel, check for leaks and assure that the fuel drains clear of the airplane. \n\n\t(b)\tFor Model PA-16 series airplanes which have a wing tank with a 1/4 NPT drain boss and a fuselage tank with a 3/8 NPT drain boss, install quick drain valves, Piper P/Ns 22179-00 and 491-806 or FAA approved equivalents in accordance with the following procedure: \n\n\t\t(1)\tInstall fuselage quick drain Piper P/N 22179-00 by repeating the procedure set forth in paragraph (a) steps (1) through (8). \n\n\t\t(2)\tDrain wing fuel tank. \n\n\t\t(3)\tRemove the inspection cover located approximately 4 inches outboard of the butt rib and approximately 5 inches forward of the rear spar. \n\n\t\t(4)\tRemove the fuel tank drain plug, Piper Part Number 70151. \n\n\t\t(5)\tInstall reducer adapter Piper P/N 453-616 (AN912-1D) and fuel drain valve 491-806 or FAA approved equivalent per Figure 2 of this AD. \n\n\t\t(6)\tAdd a 3/4 inch diameter hole in the inspection cover at the quick drain location. \n\n\t\t(7)\tAdd fuel, check for leaks, check for proper quick drain operation and install inspection cover. \n\n\t(c)\tFor Models J-4 (S/N 4-1378, 4-1385 and up), J-5, PA-12 and PA-14 series airplanes with wing tanks incorporating a 3/8 NPT drain boss inside the wing, install drain valve, Piper P/N 491-806 or FAA approved equivalent in accordance with the following procedure: \n\n\t\t(1)\tDrain fuel tank. \n\n\t\t(2)\tRemove the inspection cover located approximately 4 inches outboard of the butt rib and approximately 5 inches forward of the rear spar. \n\n\t\t(3)\tRemove the fuel tank drain plug. \n\n\t\t(4)\tInstall special Piper adapter, Piper P/N 453-618 (AN9I2-3D) and fuel drain valve P/N 491-806 or FAA approved equivalents per Figure 2 of this AD. \n\n\t\t(5)\tAdd 3/4 inch diameter hole in the inspection cover at the quick drain location. \n\n\t\t(6)\tAdd fuel, check for leaks, check for proper operation of the quick drain valves and install inspection cover. \n\n\t(d)\tFor Models PA-11, PA-16, PA-18, PA-18A, PA-20 and PA-22 series airplanes which have wing fuel tanks incorporating a 1/4 NPT drain boss, install drain valve Piper P/N 491-806 or FAA approved equivalent in accordance with the following procedures: \n\n\t\t(1)\tDrain fuel tank. \n\n\t\t(2)\tRemove the inspection cover located approximately 4 inches outboard of the butt rib and approximately 5 inches forward of the rear spar. \n\n\t\t(3)\tRemove the fuel tank drain plug. \n\n\t\t(4)\tInstall reducer/adapter Piper P/N 453-616 (AN912-1D) and fuel drain valve P/N 491-806 or FAA approved equivalents per Figure 2 of this AD. \n\n\t\t(5)\tAdd a 3/4 inch diameter hole in the inspection cover at the quick drain location. \n\n\t\t(6)\tAdd fuel, check for leaks, check for proper operation of the quick drain valve and install inspection cover. \n\n\tNOTE: Drain valve, Piper P/N 491-806, is designed for use with sample cup, Piper P/N 67728-00. Piper Service Spares Letter SP-6 dated February 5, 1960, pertains to this subject. \n\n\t(e)\tFor all aircraft models affected by this AD, after complying with paragraphs (a) through (d) above, install a permanent placard in the cockpit in a location visible to the pilot, using letters 1/8 inch minimum height. The placard must read as follows: \n\n\t\t\t"DRAIN ALL FUEL SUMPS BEFORE FIRST FLIGHT OF EACH DAY" \n\n\t(f)\tAirplanes may be flown in accordance with FAR 21.197 to a location where this AD may be accomplished. \n\n\t(g)\tAn equivalent method of compliance with this AD may be used when approved by the Manager, Atlanta Aircraft Certification Office, ACE-115A, FAA, Central Region, 1075 Inner Loop Road, College Park, Georgia 30337; telephone (404) 763-7428. \n\n\tThis amendment becomes effective on May 4, 1985. \n\n\n\nFigure 1 \nAD 85-06-04
85-05-01: 85-05-01 PIPER: Amendment 39-5011. Applies to Model PA-31P (Serial Numbers 31P-3 through 31P-7730012) airplanes certificated in any category. Compliance: Required as indicated, unless already accomplished. To prevent the propagation of cracks in the fuselage bulkhead at station 332.0, and loss of stabilizer front spar structural support, accomplish paragraph (a) as follows: (a) Within the next 25 hours time-in-service after the effective date of this AD, and thereafter at intervals not exceeding 200 hours time-in-service, inspect, using a dye-penetrant method, the fuselage station 332.0 bulkhead in accordance with Piper S/B No. 802 dated December 12, 1984. (1) If no cracks are found to exist, make appropriate maintenance record entry of compliance. (2) If cracks are found that do not exceed the acceptable limitations given in Piper S/B No. 802, prior to further flight stop drill the crack(s), and install Reinforcement Kit, Piper Part Number 764-983, orreinforced bulkhead assembly, Piper Part Number 45583-16. (3) If cracks are found that exceed the acceptable limitations given in Piper S/B No. 802, prior to further flight replace the bulkhead assembly with Reinforced Bulkhead Assembly, Piper Part Number 45583-16. (b) The repetitive inspections required by paragraph (a) of this AD may be discontinued when Reinforcement Kit Piper Part Number 764-983, or Replacement Bulkhead Piper Part No. 45583-16 is installed. (c) The intervals between repetitive inspections required by this AD may be adjusted up to 10 percent of the specified interval to allow accomplishing these inspections concurrent with other scheduled maintenance of the airplane. (d) The airplanes may be flown, in accordance with FAR 21.197 to a location where the AD may be accomplished. (e) An equivalent method of compliance with this AD may be used if approved by the Manager, Atlanta Aircraft Certification Office, ACE-115A, FAA, Central Region, 1075 Inner Loop Road, College Park, Georgia 30337; Telephone (404) 763-7428. This amendment becomes effective on March 15, 1985.
2007-19-12: We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from Mandatory Continuing Airworthiness Information (MCAI) provided by the aviation authority of France to identify and correct an unsafe condition on SICMA Aero Seat 50XXX Passenger Seats. The MCAI states the following: \n\n\tA release of smoke was experienced in the passenger compartment during flight after an overheating of a reading lights power box of a PN 5039201-4T SICMA seat. An analysis put into evidence that this overheating was caused by a short-circuit produced by the rupture of an electrical power supply component (PN 78147-B). It has been noticed that this power supply is not in compliance with DO 160 environmental standard. \n\n\tThe short-circuiting could result in arcing and consequent smoke or fire. We are proposing this AD to prevent a short-circuit in the power box, which could result in smoke or fire in the airplane cabin.
2004-20-05: The FAA is adopting a new airworthiness directive (AD) for certain Airbus Model A318, A319, A320, and A321 series airplanes. This AD requires revising the airplane flight manual to provide procedures for the flightcrew to follow in the event of the loss of all liquid crystal display (LCD) units on airplanes equipped with a certain EIS2 standard of electronic instrument system. This AD is prompted by reports of the brief but total loss of all LCD units during cruise on airplanes equipped with that standard of electronic instrument system. We are issuing this AD to provide procedures to the flightcrew to restore operation of these LCD units and prevent prolonged loss of critical flight information to the flightcrew and the consequent reduced ability of the flightcrew to control the airplane during adverse flight conditions.
84-10-06 R1: 84-10-06 R1 GARRETT TURBINE ENGINE COMPANY (GTEC, formerly AIRESEARCH MANUFACTURING COMPANY OF ARIZONA): Amendment 39-4867 as amended by Amendment 39-4964. Applicable to all series of engine models TPE331-25, -43, -47, -55, -1, -2, -3, -5, -6, -10 (except -10A), and -11 equipped with the following fuel pump assemblies: P/N S/N 868531-7/-8 All. 869151-1/-3/-4/-5 All. 893573-1 through -7 All. 895413-1/-9 All. 897380-1/-2/-3 Series 1 & 2. 897380-4/-5 Series 1, 2, & 3. 897390-1/-2/-3/-4 Series 1 & 2. 897400-1/-2 Series 1 & 2. 897400-4 Series 1. Compliance is required as indicated unless already accomplished. To prevent possible engine failure, accomplish the following: (a) Inspect low-time engine fuel control/pump assembly to determine drive shaft running torque as specified in Section 2.A.(2), "Accomplishment Instructions," of GTEC SB TPE331-73-0121, Revision 2 dated April 18, 1984, or equivalent approved by the Manager, Western Aircraft Certification Office, in accordance with the schedule below: Fuel pump assembly time: since new or since last assembled; or engine total time: since new or since last overhauled; whichever is known to be least, Hours Inspect not later than Less than 200 the next 100 hours in service 200 or more, and less than 1,000 the next 200 hours in service 1,000 or more next fuel pump disassembly NOTE: Engine Logbook Records should indicate if a new or reassembled fuel pump assembly has been installed on the engine since new or returned from overhaul. Remove from further service fuel pump assemblies having unsatisfactory running torque inspection results unless modified as specified in Section 2, "Accomplishment Instructions," in SB TPE331-73-0121, Revision 2, or equivalent approved by the Manager, Western Aircraft Certification Office. Fuel control/pump assemblies having satisfactory inspection results may be continued in service until fuel pump disassembly per Paragraph (b) below. (b) Upon disassembly of fuel pump for any reason, reassemble to an approved parts configuration as specified in Section 2, "Accomplishment Instructions," in SB TPE331-73-0121, Revision 2, or equivalent approved by the Manager, Western Aircraft Certification Office. (c) Special flight permits may be issued in accordance with Federal Aviation Regulation FAR 21.197 and FAR 21.199 to ferry aircraft to a maintenance base in order to comply with the requirements of this AD. (d) Alternative means of compliance providing an equivalent level of safety may be used when approved by the Manager, Western Aircraft Certification Office, FAA, Northwest Mountain Region. (e) Upon request of the operator, an FAA Maintenance Inspector, subject to prior approval of the Manager, Western Aircraft Certification Office, FAA, Northwest Mountain Region, may adjust the compliance schedule specified in this AD to permit compliance at an established inspection period of the operator if the request contains substantiating data to justify the adjustment for that operator. (f) The Manager, Western Aircraft Certification Office has found GTEC SB TPE331-73-0121 Revision 3, dated November 5, 1984, to be equivalent to GTEC SB TPE331-73-0121 Revision 2 dated April 18, 1984. This revision only adds the fuel pump assembly P/N. There are no changes in inspections or accomplishment instructions. The manufacturer's specifications and procedures identified and described in this directive 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 this document from the manufacturer may obtain copies upon request to Garrett Turbine Engine Company, 111 South 34th St., P.O. Box 5217, Phoenix, Arizona 85010; telephone (602) 231-1000. This document also may be examined at FAA Rules Docket 83-ANE-29, New England Region, Office of the Regional Counsel, 12 New England Executive Park, Burlington, Massachusetts 01803. This amendment supersedes Amendment 39-4840 (49 FR 13487), AD 84-07-08. Amendment 39-4867 became effective May 30, 1984. This Amendment 39-4964 becomes effective on December 26, 1984.