Results
2000-02-22: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 747-400 series airplanes. This action requires installation of a modification of the thrust reverser control and indication system and wiring on each engine; and repetitive operational checks of that installation to detect discrepancies, and repair, if necessary. This amendment is prompted by the results of a safety review, which revealed that in-flight deployment of a thrust reverser could result in a significant reduction in airplane controllability. The actions specified in this AD are intended to ensure the integrity of the fail-safe features of the thrust reverser system by preventing possible failure modes, which could result in inadvertent deployment of a thrust reverser during flight, and consequent reduced controllability of the airplane.
2019-18-02: The FAA is adopting a new airworthiness directive (AD) for certain Leonardo S.p.A. (Leonardo) Model AW169 helicopters. This AD requires replacing the seals, filler wedges, and handles of each emergency exit window. This AD was prompted by a report that a high level of pushing force was required to jettison some windows. The actions of this AD are intended to address an unsafe condition on these products.
95-20-04: This amendment adopts a new airworthiness directive (AD), applicable to all Lockheed Model L-1011-385-1 series airplanes, that requires implementation of a Supplemental Inspection Document (SID) program of structural inspections to detect fatigue cracking, and repair, if necessary, to ensure continued airworthiness of these airplanes as they approach the manufacturer's original fatigue design life goal. This amendment is prompted by a structural re-evaluation by the manufacturer that identified certain structural details where fatigue damage is likely to occur. The actions specified by this AD are intended to prevent fatigue cracking that could compromise the structural integrity of these airplanes.
87-02-07: 87-02-07 BOEING: Amendment 39-5506. Applies to all Model 737-100 and 737-200 series airplanes, certificated in any category. To minimize the hazard of lower wing surface fuel tank access cover penetration due to impact from low energy engine debris, accomplish the following, unless already accomplished. \n\n\tA.\tWithin the next year after the effective date of this AD, replace the lower wing surface fuel tank access covers located immediately inboard and outboard of each engine (total of four per airplane), with covers having impact resistance equivalent to that of 2024-T3 aluminum 0.140-inch thick, as approved by the Manager, Seattle Aircraft Certification Office, FAA, Northwest Mountain Region. The replacement covers must also be fire resistant, as defined in the Federal Aviation Regulations, Part 1. \n\n\tB.\tAn 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, Seattle Aircraft Certification Office, FAA, Northwest Mountain Region. \n\n\tC.\tSpecial 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. \n\n\tThis amendment becomes effective February 9, 1987.
93-06-01: 93-06-01 BOEING: Amendment 39-8526. Docket 92-NM-148-AD. Supersedes AD 84-21-02 R1, Amendment 39-6430.\n\n\tApplicability: Model 747 series airplanes, as listed in Section 3.0 of Boeing Document No. D6-35022, "Supplemental Structural Inspection Document" (SSID), Revision D, dated February 1992, certificated in any category.\n\n\tCompliance: Required as indicated, unless accomplished previously.\n\n\tTo ensure the continuing structural integrity of the total Boeing Model 747 fleet, accomplish the following:\n\n\t(a)\tFor airplanes listed in Boeing Document No. D6-35022, Revision C, dated April 1989: Within 3 months after February 12, 1990 (the effective date of AD 84-21-02 R1, Amendment 39-6430), incorporate a revision into the FAA-approved maintenance inspection program which provides no less than the required Damage Tolerance Rating (DTR) for each Structural Significant Item (SSI) listed in Boeing Document No. D6-35022, Revision C, dated April 1989. (The required DTR value for eachSSI is listed in the document.) The revision to the maintenance program shall include and be implemented in accordance with the procedures in Sections 5.0 and 6.0 of the SSID.\n\n\t(b)\tFor airplanes listed in Boeing Document No. D6-35022, Revision D, dated February 1992: Within 12 months after the effective date of this AD, replace the revision of the FAA-approved maintenance inspection program required by paragraph (a) of this AD with a revision that provides no less than the required DTR for each SSI listed in Boeing Document No. D6-35022, Revision D, dated February 1992. (The required DTR value for each SSI is listed in the document.) The revision to the maintenance program shall include and be implemented in accordance with the procedures in Sections 5.0 and 6.0 of the SSID.\n\n\t(c)\tCracked structure must be repaired, prior to further flight, in accordance with an FAA-approved method.\n\n\t(d)\tAn alternative method of compliance or adjustment of the compliance time that providesan acceptable level of safety may be used if approved by the Manager, Seattle Aircraft Certification Office (ACO), 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, Seattle ACO.\n\n\tNOTE: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Seattle ACO.\n\n\t(e)\tSpecial 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.\n\n\t(f)\tThe inspections shall be done in accordance with Boeing Document No. D6-35022, "Supplemental Structural Inspection Document (SSID)", Revision C, dated April 1989, and Boeing Document No. D6-35022, "Supplemental Structural Inspection Document (SSID)", Revision D, dated February 1992, comprised of Volumes I and II, which includes the following list of effective pages:\n\n\nPage Number\nRevision Ltr.\n\n\nList of Active Pages\nD\nPages 1 thru 21.1\n\n\n(NOTE: The issue date of Revision D is indicated only on the title page; no other page of the document is dated.) The incorporation by reference of Revision D was approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR Part 51. The incorporation by reference of Revision C was approved previously by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR Part 51 as of February 12, 1990 (55 FR 1005, January 11, 1990). Copies may be obtained from Boeing Commercial Airplane Group, P.O. Box 3707, Seattle, Washington 98124-2207. 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.\n\n\t(g)\tThis amendment becomes effective on May 17, 1993.
2000-24-19: This amendment adopts a new airworthiness directive (AD), applicable to all Learjet Model 35, 35A, 36, and 36A series airplanes, that requires revision of the Airplane Flight Manual (AFM) to add procedures for donning the flightcrew oxygen masks when the cabin altitude warning horn is activated. This amendment is intended to prevent incapacitation of the flightcrew due to lack of oxygen and consequent loss of control of the airplane due to absence of AFM procedures for donning the flightcrew oxygen masks when the cabin altitude warning horn is activated.
94-01-10: 94-01-10 BOEING: Amendment 39-8792. Docket 92-NM-173-AD. Supersedes AD 91-20-09, Amendment 39-8043.\n \n\tApplicability: Model 757 series airplanes equipped with Pratt and Whitney PW2000 series engines, certificated in any category. \n\n\tCompliance: Required as indicated, unless accomplished previously. \n\n\tNOTE 1: Paragraphs (a) and (b) of this AD restate the requirements of AD 91-20-09, Amendment 39-8043, paragraphs (a) and (b). As allowed by the phrase, "unless accomplished previously," if the requirements of AD 91-20-09 have been accomplished previously, paragraphs (a) and (b) of this AD do not require those actions to be repeated. \n\n\tNOTE 2: Paragraph (c) of this AD restates the requirement for repetitive inspections contained in paragraph (d) of AD 91-20-09, Amendment 39-8043. Paragraph (c) of this AD requires that the first inspection required by this AD must be performed within the specified repetitive inspection interval after the last inspection performed in accordance with paragraph (d) of AD 91-20-09. \n\n\tTo prevent deployment of a thrust reverser in flight and subsequent reduced controllability of the airplane, accomplish the following: \n\n\t(a)\tWithin 14 days after September 16, 1991 (the effective date of AD 91-20-09, Amendment 39-8043), accomplish either paragraph (a)(1) or (a)(2) of this AD. \n\n\t\t(1)\tAccomplish both paragraphs (a)(1)(i) and (a)(1)(ii) of this AD: \n\t\t\t(i)\tInspect the thrust reverser Directional Control Valve (DCV) assemblies of both engines to determine the solenoid-driven pilot valve's part number, in accordance with Boeing Alert Service Bulletin 757-78A0027, dated September 9, 1991.\n \n\t\t\t\t(A)\tIf any DCV has a suspect pilot valve as specified in the service bulletin, prior to further flight, replace the DCV with a DCV that has a part number of a non-suspect solenoid-driven pilot valve, in accordance with the service bulletin. \n\n\t\t\t\t(B)\tIf a DCV has a non-suspect solenoid-driven pilot valve as specified in the service bulletin, that pilot valve does not need to be replaced. \n\n\t\t\t(ii)\tPerform all tests and inspections of the engine thrust reverser control and indication system on both engines in accordance with Boeing Service Bulletin 757- 78-0025, dated September 9, 1991. Prior to further flight, correct any discrepancy found in accordance with the service bulletin. \n\n\t\t(2)\tAccomplish paragraph (a)(1) of this AD on one engine's thrust reverser and deactivate the other engine's thrust reverser, in accordance with Section 78-31-1 of Boeing Document D630N002, "Boeing 757 Dispatch Deviation Guide," Revision 8, dated January 15, 1991.\n \n\t(b)\tWithin 24 days after September 16, 1991 (the effective date of AD 91-20-09, Amendment 39-8043), the requirements of paragraph (a)(1) of this AD must be accomplished on both engines' thrust reverser systems. \n\n\t(c)\tRepeat the tests and inspections specified in paragraph (a)(1)(ii) at intervals not to exceed 3,000 flight hours, and prior to further flight following any maintenance that disturbs the thrust reverser control system. Prior to further flight, correct any discrepancy found in accordance with Boeing Service Bulletin 757-78-0025, dated September 9, 1991. \n\n\t(d)\tWithin 5 years after the effective date of this AD, install an additional thrust reverser system locking feature (sync lock installation), in accordance with Boeing Service Bulletin 757-78-0028, Revision 1, dated October 29, 1992, or Revision 2, dated January 14, 1993. \n\n\t(e)\tWithin 1,000 hours time-in-service after installing the sync lock required by paragraph (d) of this AD (either in production or by retrofit), or within 1,000 hours time-in- service after the effective date of this AD, whichever occurs later; and thereafter at intervals not to exceed 1,000 hours time-in-service: Perform functional tests of the sync lock in accordance with the "Thrust Reverser Sync Lock Integrity Test" procedures specified below. If any discrepancy is found during any test, prior to further flight, correct it in accordance with procedures described in the Boeing 757 Maintenance Manual. \n\n\t\t"THRUST REVERSER SYNC LOCK INTEGRITY TEST \n\n1.\tGeneral \n\tA.\tUse this procedure to test the integrity of the thrust reverser sync locks. \n\n2.\tThrust Reverser Sync Lock Test \n\tA.\tPrepare for the Thrust Reverser Sync Lock Test. \n\n\t\t(1)\tOpen the AUTO SPEEDBRAKE circuit breaker on the overhead \t\t\t\tcircuit breaker panel, P11. \n\n\t\t(2)\tDo the steps that follow to supply power to the thrust reverser system: \n\t\t\t(a)\tMake sure the thrust levers are in the idle position. \n\n\t\t\tCAUTION:\tDO NOT EXTEND THE THRUST REVERSER \t\t\t\t\t\tWHILE THE CORE COWL PANELS ARE OPEN. \t\t\t\t\tDAMAGE TO THE THRUST REVERSER AND \t\t\t\t\t\tCORE COWL PANELS CAN OCCUR. \n\n\t\t\t(b)\tMake sure the thrust reverser halves are closed. \n\t\t\t(c)\tMake sure the core cowl panels are closed. \t\t\t\t\t(d)\tPut the EEC MAINT POWER switch or the EEC POWER L \t\t\t\tand EEC POWER R switches to the ALTN position. \n\n\t\t\t(e)\tFor the left engine: \n\n\t\t\t\t1)\tPut the EEC MAINT CHANNEL SEL L switch to the \n\t\t\t\t\tAUTO position. \n\t\t\t\t2)\tPut the L ENG fire switch to the NORM position. \n\n\t\t\t(f)\tFor the right engine: \n\n\t\t\t\t1)\tPut the EEC MAINT CHANNEL SEL R switch to the \n\t\t\t\t\tAUTO position. \n\t\t\t\t2)\tPut the R ENG fire switch to the NORM position. \n\n\t\t\t(g)\tMake sure the EICAS circuit breakers (6 locations) are \t\t\t\t\tclosed. \n\n\t\t\tWARNING:\tTHE THRUST REVERSER WILL AUTOMATICALLY \n\t\t\t\t\tRETRACT IF THE ELECTRICAL POWER TO THE \n\t\t\t\t\tEEC/THRUST REVERSER CONTROL SYSTEM IS \n\t\t\t\t\tTURNED OFF OR IF THE EEC MAINT POWER \n\t\t\t\t\tSWITCH IS MOVED TO THE NORM POSITION. \t\t\t\t\tTHE ACCIDENTAL OPERATION OF THE THRUST \n\t\t\t\t\tREVERSER CAN CAUSE INJURY TO PERSONS \t\t\t\t\tOR DAMAGE TO EQUIPMENT CAN OCCUR. \n\n\t\t\t(h)\tMake sure these circuit breakers on the main power \t\t\t\t\tdistribution panel, P6, are closed: \n\n\t\t\t\t1)\tFUEL COND CONT L \n\t\t\t\t2)\tFUEL COND CONT R \n\t\t\t\t3)\tT/L INTERLOCK L \n\t\t\t\t4)\tT/L INTERLOCK R \n\t\t\t\t5)\tLEFT T/R SYNC LOCK6)\tRIGHT T/R SYNC LOCK \n\t\t\t\t7)\tL ENG ELECTRONIC ENGINE CONTROL ALTN \t\t\t\t\tPWR \n\t\t\t\t\t(if installed) \n\t\t\t\t8)\tR ENG ELECTRONIC ENGINE CONTROL ALTN \t\t\t\t\tPWR \n\t\t\t\t\t(if installed) \n\n\t\t\t(i)\tMake sure these circuit breakers on the overhead circuit \n\t\t\t\tbreaker panel, P11, are closed: \n\n\t\t\t\t1)\tAIR/GND SYS 1 \n\t\t\t\t2)\tAIR/GND SYS 2 \n\t\t\t\t3)\tLANDING GEAR POS SYS 1 \n\t\t\t\t4)\tLANDING GEAR POS SYS 2 \n\n\t\t\t(j)\tFor the left engine, make sure these circuit breakers on the \t\t\t\tP11 panel are closed: \n\n\t\t\t\t1)\tLEFT ENGINE PDIU \n\t\t\t\t2)\tLEFT ENGINE THRUST REVERSER CONT/SCAV \n\t\t\t\t\tPRESS \n\t\t\t\t3)\tLEFT ENGINE ELECTRONIC ENGINE CONTROL \n\t\t\t\t\tALTN PWR (if installed) \n\t\t\t\t4)\tLEFT ENGINE THRUST REVERSER PRI CONT 5)\n\t\t\t\t\tLEFT ENGINE THRUST REVERSER SEC CONT \n\n\t\t\t(k)\tFor the right engine, make sure these circuit breakers on the \n\t\t\t\tP11 panel are closed: \n\n\t\t\t\t1)\tRIGHT ENGINE PDIU \n\t\t\t\t2)\tRIGHT ENGINE THRUST REVERSER CONT/SCAV \n\t\t\t\t\tPRESS \n\t\t\t\t3)\tRIGHT ENGINE ELECTRONIC ENGINE CONTROLALTN PWR (if installed) \n\t\t\t\t4)\tRIGHT ENGINE THRUST REVERSER PRI CONT \n\t\t\t\t5)\tRIGHT ENGINE THRUST REVERSER SEC CONT \n\n\t\t\t(l)\tSupply electrical power. \n\n\t\t\t(m)\tRemove the pressure from the left (right) hydraulic system. \n\n\tB.\tDo the Thrust Reverser Sync Lock Test. \n\n\t\t(1)\tMove and hold the manual unlock lever on the center actuator on both \t\t\tthrust reverser sleeves to the unlock position. \n\t\t(2)\tMake sure the thrust reverser sleeves did not move. \n\t\t(3)\tMove the left (right) reverser thrust lever up and rearward to the idle \n\t\t\tdetent position. \n\t\t(4)\tMake sure both thrust reverser sleeves move aft (approximately 0.15 \t\t\tto 0.25 inch). \n\t\t(5)\tRelease the manual unlock lever on the center actuators. \n\n\n\t\tWARNING:\tMAKE SURE ALL PERSONS AND EQUIPMENT ARE \t\t\tCLEAR OF THE AREA AROUND THE THRUST REVERSER. WHEN YOU \t\tAPPLY \tHYDRAULIC PRESSURE THE THRUST REVERSER WILL EXTEND \t\tAND CAN CAUSE INJURIES TO PERSONS OR DAMAGE TO EQUIPMENT. \n\n\t\t(6)\tPressurize the left (right) hydraulic system. \n\t\t(7)\tMake sure the thrust reverser extends. \n\t\t(8)\tMove the left (right) reverser thrust lever to the fully forward and down \n\t\t\tposition to retract the thrust reverser.\n \n\tC.\tPut the Airplane Back to its Usual Condition. \n\n\t\t(1)\tRemove hydraulic pressure. \n\t\t(2)\tClose the left and right fan cowls. \n\t\t(3)\tClose the AUTO SPEEDBRAKE circuit breaker on the P11 panel. \n\t\t(4)\tRemove electrical power if it is not necessary. \n\n\tD.\tRepeat the Thrust Reverser Sync Lock Test on the other engine." \n\n\t(f)\tInstallation of the sync lock, as required by paragraph (d) of this AD, constitutes terminating action for the requirements of paragraphs (a) through (c) of this AD. \n\n\t(g)\tAn 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, Seattle Aircraft Certification Office (ACO), 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, Seattle ACO. \n\n\tNOTE 3: Approvals of alternative methods of compliance issued for AD 91-20-09 constitute valid approvals for compliance with the requirements of paragraphs (a) through (c) of this AD. \n\n\tNOTE 4: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Seattle ACO. \n\n\t(h)\tSpecial 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. \n\n\t(i)\tThe actions shall be done in accordance with Boeing Alert Service Bulletin 757- 78A0027, dated September 9, 1991; Boeing Service Bulletin 757-78-0025, dated September 9, 1991; Boeing Document D630N002, "Boeing 757 Dispatch Deviation Guide," Revision 8, dated January 15, 1991; Boeing Service Bulletin 757-78-0028, Revision 1, dated October 29, 1992; andBoeing Service Bulletin 757-78-0028, Revision 2, dated January 14, 1993. The incorporation by reference of Boeing Alert Service Bulletin 757-78A0027, dated September 9, 1991; Boeing Service Bulletin 757-78-0025, dated September 9, 1991; Boeing Document D630N002, "Boeing 757 Dispatch Deviation Guide," Revision 8, dated January 15, 1991; was approved previously by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR Part 51 as of September 16, 1991 (56 FR 46725, September 16, 1991). The incorporation by reference of the remainder of the service documents listed above is 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 Boeing Commercial Airplane Group, P.O. Box 3707, Seattle, Washington 98124-2207. 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. \n\n\t(j)\tThis amendment becomes effective on March 3, 1994.
2019-18-01: The FAA is adopting a new airworthiness directive (AD) for certain International Aero Engines AG (IAE) V2500 model turbofan engines. This AD was prompted by an inspection that determined that material anomalies exist in certain low-pressure turbine (LPT) stage 6 disks. This AD requires removal from service of the affected LPT stage 6 disks and their replacement with a part eligible for installation. The FAA is issuing this AD to address the unsafe condition on these products.
97-11-01: This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A320 series airplanes, that requires an initial inspection of fastener holes on certain outer frames of the fuselage to detect fatigue cracking, and modification of this area by cold expanding these holes and installing oversized fasteners. This amendment is prompted by a report from the manufacturer indicating that, during full-scale fatigue testing of the test article, fatigue cracking was detected in the area where the center fuselage joins the wing. The actions specified by this AD are intended to prevent fatigue cracking and consequent reduced structural integrity of this area, which could lead to rapid depressurization of the fuselage.
2007-05-16: This action supersedes emergency airworthiness directive (AD) 2007-04-51 that was sent previously to all known U.S. owners and operators of GE CF34-3A1/-3B/-3B1 turbofan engines. That action required a onetime visual and tactile inspection of certain areas of certain serial number (SN) fan disks for an arc-out defect, within 20 engine flight hours after the effective date of that AD. This AD supersedes AD 2007-04-51 and adds eight SNs to the list of suspect fan disks. This AD results from GE discovering eight additional SNs of fan disks suspected of having an arc-out defect, and from the original report that a GE CF34-3B1 turbofan engine experienced an uncontained fan disk failure during flight operation. We are issuing this AD to prevent an uncontained fan disk failure and airplane damage.
80-17-11: 80-17-11 GATES LEARJET: Amendment 39-3888. Applies to the following model and serial number airplanes: Model 35 Series Serial Number 35-050 through 35-339 except 35-054 and 35-065 Model 36 Series Serial Number 36-017 through 36-045 COMPLIANCE: Required as indicated unless already accomplished. To prevent encountering a possible overload flight condition that could fail the forward engine mount, accomplish the following: A) Within the next 75 hours time-in-service after the effective date of this AD, in accordance with Gates Learjet Corporation Service Bulletin 35/36-11-3, dated July 28, 1980: 1. Install airspeed warning placards and modify the Mach/overspeed switch circuit to effect a reduced maximum operating airspeed (VMO) of 307 KIAS, from sea level to 31,100 feet altitude. 2. Insert in the existing Airplane Flight Manual the temporary Airplane Flight Manual Supplement included in Service Bulletin 35/36-11-3. B) Within the next 600 hours' time-in-service after the effective date of this AD, replace or re-age both forward engine mounts in accordance with Gates Learjet Corporation Airplane Modification Kit AMK 80-6. Accomplish the removal and installation of the engine mounts at authorized Gates Learjet Service Centers and the nondestructive testing and heat treating at appropriately rated FAA certified repair stations. C) Upon compliance with Paragraph B above, the requirements of Paragraph A of this AD are no longer applicable. D) Issuance of a Special Flight Permit in accordance with FAR 21.197 is permitted for the purpose of moving the affected airplanes to a location where the modifications required by this AD can be accomplished. E) Any equivalent means of compliance with this AD must be approved by the Chief, Aircraft Certification Program, Federal Aviation Administration, Room 238, Terminal Building No. 2299, Mid-Continent Airport, Wichita, Kansas 67209. This amendment becomes effective August 28, 1980.
2019-16-12: The FAA is superseding Airworthiness Directive (AD) 2005-20- 01, which applied to all The Boeing Company Model 737-100, -200, -200C, -300, -400, and -500 series airplanes. AD 2005-20-01 required repetitive inspections of the vertical stiffeners at left buttock line (LBL) and right buttock line (RBL) 6.15 for cracks; and replacement of both stiffeners with new, improved stiffeners if any stiffener is found cracked. This new AD requires, depending on airplane configuration, replacing the vertical stiffeners at LBL and RBL 6.15 on the rear spar of the wing center section, installing angle and bonding jumpers, installing brackets, applying sealant, and applying paint. This AD was prompted by reports of cracks found in the left and right side keel beam upper chords when replacing vertical stiffeners. This AD was also prompted by possible degradation of the fault current bonding path that could introduce an ignition source in the fuel tank in the event of a fault current being imparted onto the fuel tank structure. The FAA is issuing this AD to address the unsafe condition on these products.
77-07-05: 77-07-05 HILLER AVIATION: Amendment 39-2862 as amended by Amendment 39-2917. Applies to Hiller Model UH-12, UH-12A, UH-12B, UH-12C, UH-12D, UH-12E UH-12E (4- place), (including military Models H-23A, H-23B, H-23C, H-23D, H-23F, OH-23G, HTE-1, HTE-2, and CH112) helicopters, certificated in all categories. Compliance required as indicated, unless already accomplished. To detect cracks in the control rotor blade spar tube and cuff and to establish a service life of 6860 hours for Hiller P/N 36124 cuff used with unfaired paddles accomplish the following: (a) Within the next 100 hours time in service after the effective date this AD, unless already accomplished within the last 100 hours time in service and thereafter at intervals not to exceed 100 hours time in service from the last inspection, inspect, replace or repair the control rotor blade spar tube and cuff in accordance with Hiller Aviation Service Bulletin No. 36-1, Revision 2, dated June 19, 1974, or later FAA-approved revisions. (b) After any repair is accomplished in accordance with Hiller Aviation Service Bulletin No. 36-1, Revision 2, dated June 19, 1974 or later FAA-approved revisions, the control rotor blade spar tube (faired and unfaired) and cuff must be retired before 2500 additional hours time in service after rework or when the current approved total service life (total service life before repair plus service life after repair) is reached, whichever comes first. (c) Fabric covered, metal covered, faired and unfaired control rotor blades are not interchangeable and must not be intermixed. (d) For Hiller P/N 36124 cuffs used with unfaired paddles (1) Cuffs with more than 6660 hours time in service, remove and replace with a serviceable part within 200 hours time in service after the effective date of this AD. (2) Cuffs with less than 6660 hours time in service, remove and replace with a serviceable part prior to 6860 hours time in service. (3) For cuffs for which the prior service history cannot be documented, within the next 25 hours time in service, unless already accomplished within the last 25 hours time in service prior to the effective date of this AD and at intervals not to exceed 50 hours time in service, perform a dye penetrant inspection of the cuff per Hiller Aviation Service Bulletin, No. 36-1, Revision 2, dated June 19, 1974, or later FAA approved revisions. Remove cracked cuffs from service prior to further flight. Cuffs for which the prior service history cannot be documented cannot be used as a replacement part. Remove from service all cuffs prior to the accumulation of 225 hours total time in service since April 7, 1977. (e) Equivalent inspection procedures and repair procedures for Hiller P/N 36124 cuff when used only with unfaired paddles may be approved by the Chief,Aircraft Engineering Division, FAA Western Region. (f) Special flight permits may be issued in accordance with FAR's 21.197 and 21.199 tooperate helicopters to a base for accomplishment of the inspections required by this AD. Amendment 39-2862 superseded Amendment 39-1990 (39 F.R. 36855), AD 74-21-05. Amendment 39-2862 became effective April 7, 1977. This amendment 39-2917 becomes effective June 20, 1977.
97-04-02: This document publishes in the Federal Register an amendment adopting Airworthiness Directive (AD) 97-04-02, which was sent previously to known U.S. owners and operators of certain Raytheon Aircraft Company (Raytheon) Models 1900, 1900C, and 1900D airplanes (formerly referred to as Beech Models 1900, 1900C, and 1900D airplanes). This AD requires installing new exterior operating instruction placards for the airstair door, cargo door, and emergency exits, as applicable. This AD results from an accident involving a Raytheon Model 1900C airplane that collided with another airplane while completing its landing roll. The ensuing fire destroyed both airplanes. The actions specified by this AD are intended to assure complete instructions are visible for opening the airstair door, cargo door, or emergency exits, which, if not visible or understandable, could result in the inability to open the airstair door, cargo door, or emergency exits during an emergency situation.
80-19-08: 80-19-08 CESSNA: Amendment 39-3902. Applies to Model 172RG (S/N 172RG0001 through 172RG0573) airplanes certificated in all categories. COMPLIANCE: Required as indicated unless already accomplished. To preclude slippage of the mixture control wire at the carburetor fuel mixture control arm and resultant power loss due to a lean fuel/air mixture, within the next 25 hours time-in-service after the effective date of this AD, accomplish the following: A) Visually inspect the mixture control connection on the right side of the carburetor for correct assembly. Assure that (1) Cessna Part Number (P/N) 9862010-9 mixture control assembly wire is secured to the Cessna P/N S2323-11 clamp at the carburetor mixture control arm with an AN960-10 (approximately .063 inch thick) washer installed between the mixture control wire and the MS20365-1032C nut and (2) an AN960-10L (approximately .032 inch thick) washer is installed between the mixture control wire and the mixture controlarm. B) If the parts are assembled per Paragraph A), check to assure that the minimum torque on the MS20365-1032C nut is 15 inch-pounds and that the Cessna P/N S2323-11 clamp will swivel in the mixture control arm. Make the prescribed entry in the aircraft maintenance records indicating compliance with this AD and no further action is required. C) If the parts are not assembled per Paragraph A) remove and discard the MS20365-1032C nut. Install washers in the positions specified by Paragraph A) and install a new MS20365-1032C nut. Torque the nut to 15 inch-pounds minimum and assure that the Cessna P/N S2323-11 clamp will swivel in the mixture control arm. D) Airplanes may be flown in accordance with FAR 21.197 to a location where the inspection required by Paragraph A) may be accomplished. E) Any equivalent method of compliance with this AD must be approved by the Chief, Aircraft Certification Program, Federal Aviation Administration, Room 238, Terminal Building No. 2299, Mid-Continent Airport, Wichita, Kansas 67209; Telephone (316) 942-4285. This amendment becomes effective September 15, 1980.
90-26-10: 90-26-10 BOEING: Amendment 39-6836. Docket No. 90-NM-132-AD. \n\n\tApplicability: Model 747 series airplanes, line numbers 001 through 430, certificated in any category. \n\n\tCompliance: Required as indicated, unless previously accomplished. \n\n\tTo prevent rapid decompression of the airplane, accomplish the following: \n\n\tA.\tPrior to the accumulation of 12,000 flight cycles or within the next 1,000 flight cycles after the effective date of this AD, whichever occurs later, unless previously accomplished within the last 1,000 flight cycles, conduct an external detailed visual and external high frequency eddy current inspection for cracks of the fuselage skin from body station (BS) BS 220 to BS 520, left and right hand side of the airplane between stringers (S) S-6 and S-14, excluding the skin lap joints, in accordance with Boeing Alert Service Bulletin 747-53A2321, dated October 31, 1989. Repeat the inspections thereafter at intervals not to exceed 2,000 flight cycles. \n\n\tB.\tIfcracks are detected, repair prior to further flight, in accordance with the Boeing Alert Service Bulletin 747-53A2321, dated October 31, 1989.\n \n\tC.\tFor airplanes line numbers 001 through 200, prior to the accumulation of 20,000 flight cycles, or within the next 4 years after the effective date of this AD, whichever occurs later, perform the terminating modification of the skin panel from BS 340 to BS 520, S-6 to S-14, in accordance with Boeing Alert Service Bulletin 747-53A2321, dated October 31, 1989. (The modification consists of replacing the skin panel with a new skin panel which was manufactured utilizing the improved hot phosphoric anodize bonding process.) \n\n\tD.\tReplacement of the skin panel required by paragraph C. of this AD constitutes terminating action for the inspections from BS 340 to BS 520 required by paragraph A. of this AD. The inspections from BS 220 to BS 340 required by paragraph A. of this AD are to be continued. \n\n\tE.\tFlight cycles conducted at 2.0 PSIor less cabin differential pressure need not be counted for the purpose of this airworthiness directive. \n\n\tF.\tFor Model 747SR airplanes only, the threshold and repetitive inspection intervals specified herein may be multiplied by the 1.2 adjustment factor based on continued mixed operation at lower cabin pressure differentials. \n\n\tG.\tAn 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, Seattle Aircraft Certification Office (ACO), FAA, Transport Airplane Directorate. \n\n\tNOTE: The request should be submitted directly to the Manager, Seattle ACO, and a copy sent to the cognizant FAA Principal Inspector (PI). The PI will then forward comments or concurrence to the Seattle ACO. \n\n\tH.\tSpecial 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. \n\n\tAll persons affected by thisdirective who have not already received the appropriate service documents from the manufacturer may obtain copies upon request to Boeing Commercial Airplane Group, P.O. Box 3707, Seattle, Washington 98124. These documents may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, Washington. \n\n\tAirworthiness Directive 90-26-10 supersedes AD 89-23-53, Amendment 39-6524. \n\tThis amendment (39-6836, AD 90-26-10) becomes effective on January 22, 1991.
90-16-04: 90-16-04 McDONNELL DOUGLAS: Amendment 39-6613. Docket No. 89-NM-198-AD.\n\n\tApplicability: Model DC-10 and KC-10 series airplanes, certificated in any category. \n\n\tCompliance: Required as indicated, unless previously accomplished. \n\n\tTo prevent structural failure, accomplish the following: \n\n\tA.\tExcept as provided in paragraph C., below, within the threshold for inspections specified in the service bulletins listed in Table 2.1 of "DC-10/KC-10 Aging Aircraft Service Action Requirements Document," McDonnell Douglas Report No. MDC-K1571, Revision A, dated February 28, 1990 (hereafter referred to as "The Document"), or within one repetitive inspection period specified in those service bulletins after the effective date of this AD, whichever is later, inspect for cracks in accordance with those service bulletins. Repeat these inspections at intervals specified in the service bulletins listed in Table 2.1 of The Document. \n\n\t\t1.\tIf cracks are found during any inspection,prior to further flight, either accomplish the terminating modification in accordance with the applicable service bulletin, or repair in accordance with data approved by the Manager, Los Angeles Aircraft Certification Office, FAA, Northwest Mountain Region.\n\n\tNOTE: Detection of discrepancies other than cracking necessitates appropriate corrective action in accordance with the provisions of Part 43 of the Federal Aviation Regulations (FAR). \n\n\t2.\tModification in accordance with paragraph B. of this AD terminates individual inspection requirements of the applicable service bulletin.\n\n\tB.\tExcept as provided in paragraph C., below, prior to reaching the incorporation thresholds listed in The Document or within the next 4 years after the effective date of this AD, whichever occurs later, accomplish the structural modifications specified in the service bulletins listed in Table 2.1 of The Document. \n\n\tNOTE: The modifications required by this paragraph do not terminate the inspection requirements of any other AD unless that AD specifies that any such modification constitutes terminating action for the inspection requirements.\n\n\tC.\tFor McDonnell Douglas Service Bulletins A30-37, 30-38, 53-16, 53-19, 53-25, 54-11, 54-27, 54-33, 55-2, and 57-7, listed in Table 2.1 of The Document, within the threshold for inspections listed in Table 2.1 of The Document under "S/B Change Required" or within one repetitive inspection period specified in Table 2.1 of The Document under "S/B Change Required" after the effective date of this AD, whichever is later, inspect for cracks in a manner approved by the Manager, Los Angeles Aircraft Certification Office. Repeat these inspections at intervals specified in Table 2.1 of The Document under "S/B Change Required."\n\n\t\t1.\tIf cracks are found during any inspection, prior to further flight, either accomplish the terminating modification in accordance with the applicable service bulletin, or repair in accordance with data approved by the Manager, Los Angeles Aircraft Certification Office, FAA, Northwest Mountain Region.\t\n\n\t\t2.\tModification in accordance with paragraph D., of this AD terminates individual inspection requirements of the applicable service bulletin.\n\n\tD.\tWithin 4 years after the effective date of this AD accomplish the structural modifications stipulated in the service bulletins specified in paragraph C., above.\n\n\tE.\tAn 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, Los Angeles Aircraft Certification Office, FAA, Northwest Mountain Region.\n\n\tNOTE: 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, Los Angeles Aircraft Certification Office.\n\n\tF.\tSpecial 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.\n\n\tThe inspections and modifications shall be done in accordance with the "DC-10/KC-10 Aging Aircraft Service Action Requirements Document," McDonnell Douglas Report No. MDC-K1571, dated February 28, 1990, which incorporates the following list of effective pages:\n\n\nPage Number\nRevision Number\nDate\nPage i (Cover)\nRevision A\nFebruary 28, 1990\nPage ii\n(Original)\nSeptember 12, 1989\nPages iii - vi\nRevision A\nFebruary 28, 1990\nPages vii - viii\nRevision A\nFebruary 28, 1990\nPage 1\n(Original)\nSeptember 12, 1989\nPage 2\nRevision A\nFebruary 28, 1990\nPage 3\n(Original)\nSeptember 12, 1989\nPages 4 - 15\nRevision A\nFebruary 28, 1990\nPage 16\n(Original)\nSeptember 12, 1989\nPages 17-20\nRevision A\nFebruary 28, 1990\nPages 21-22\n(Original)\nSeptember 12, 1989\nPage 23\nRevision A\nFebruary 28, 1990\n\nThis 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 maybe obtained from McDonnell Douglas Corporation, 3855 Lakewood Boulevard, Long Beach, California 90806, Attention: Director, Publication and Training, C1-750 (54-60). Copies may be inspected at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 17900 Pacific Highway South, Seattle, Washington; at the Los Angeles Aircraft Certification Office, 3229 East Spring Street, Long Beach, California; or at the Office of the Federal Register, 1100 L Street, N.W., Room 8301, Washington, D.C.\n\n\tThis amendment (39-6613, AD 90-16-04) becomes effective on September 10, 1990.
2019-16-09: The FAA is adopting a new airworthiness directive (AD) for certain Bombardier, Inc., Model DHC-8-400 series airplanes. This AD was prompted by reports of cracked elevator power control unit (PCU) brackets on the horizontal stabilizer rear spar and cracking on the elevator front spar. This AD requires one-time inspections for cracks and damage of the elevator PCU brackets and surrounding area, horizontal stabilizer rear spar, and elevator front spar, and related investigative and corrective actions if necessary. The FAA is issuing this AD to address the unsafe condition on these products.
96-01-09: This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-9-80 series airplanes and Model MD-88 airplanes, that requires installation of hydraulic line restrictors in the main landing gear (MLG), and modification of the hydraulic damper assembly of the MLG. This amendment is prompted by reports of vibration occurring in the MLG during landing; in some cases, such vibration has led to the collapse of the MLG. The actions specified by this AD are intended to prevent incidents of vibration in the MLG, which can adversely affect the integrity of the MLG.
2007-05-08: The FAA is adopting a new airworthiness directive (AD) for all Airbus Model A330 and A340 airplanes. This AD requires revising the Airworthiness Limitations section of the Instructions for Continued Airworthiness by incorporating new and revised certification maintenance requirements (CMRs). This AD results from the manufacturer's determination that additional and revised CMRs are necessary in order to ensure continued operational safety of the affected airplanes. We are issuing this AD to prevent safety- significant latent failures that would, in combination with one or more other specific failures or events, result in a hazardous or catastrophic failure condition.
2019-10-51: The FAA is publishing a new airworthiness directive (AD) for all Airbus Helicopters Deutschland GmbH Helicopters (Airbus) Model MBB- BK 117 C-2 helicopters. Emergency AD 2019-10-51 was sent previously to all known U.S. owners and operators of these helicopters. This AD requires, for certain helicopters, inspecting the fuselage frame and providing certain information to the FAA. This AD also prohibits installing certain components as part of Supplemental Type Certificate (STC) SR00592DE on any helicopter. This AD was prompted by reports of fatigue cracks in the fuselage frame. The FAA is issuing this AD to address the unsafe condition on these products.
2019-17-01: The FAA is superseding Airworthiness Directive (AD) 2017-11-09 for certain Learjet, Inc. (Learjet), Model 60 airplanes. AD 2017-11-09 required a one-time fluorescent dye penetrant inspection of the fuselage skin for corrosion, additional related inspections and corrective actions as necessary, and reporting the inspection results to the FAA. This AD clarifies the compliance time for the inspection and corrects an error in the inspection area of the fuselage skin. This AD was prompted by the identification of an error in the fluorescent dye penetrant inspection of the fuselage skin and an ambiguity in the compliance time for the fluorescent dye penetrant inspection. The FAA is issuing this AD to address the unsafe condition on these products.
95-07-05: This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A300-600 series airplanes, that requires repetitive ultrasonic inspections to detect cracks in the bolt holes inboard and outboard of rib 9 on the bottom booms of the front and rear wing spars, and repair, if necessary. This amendment is prompted by the discovery of fatigue cracks that emanated from the bolt holes inboard and outboard of rib 9 in the bottom booms of the front and rear wing spars. The actions specified by this AD are intended to prevent reduced structural integrity of a wing spar as a result of fatigue cracks in the bolt holes.
93-17-09: 93-17-09 MCDONNELL DOUGLAS: Amendment 39-8680. Docket 92-NM-221-AD. Supersedes AD 92-02-08, Amendment 39-8144 which superseded AD 89-22-10, Amendment 39-6330.\n\n\tApplicability: Model DC-10 series airplanes and KC-10A (military) airplanes, certificated in any category.\n\n\tCompliance: Required as indicated, unless accomplished previously. \n\n\tTo ensure the continuing structural integrity of these airplanes, accomplish the following: \n\n\t(a)\tWithin 6 months after March 9, 1992 (the effective date of AD 92-02-08, Amendment 39-8144), incorporate a revision into the FAA-approved maintenance inspection program which provides for inspection(s) of the Principal Structural Elements (PSE's) defined in Section 2 of Volume I of McDonnell Douglas Report No. L26-012, "DC-10 Supplemental Inspection Document (SID)," Revision 1, dated May 1990, in accordance with Section 2 of Volume III-90, dated May 1990, or Section 2 of Volume III-91, dated December 1991, of the SID. The non-destructiveinspection (NDI) techniques set forth in Section 2 and Section 4 of Volume II, Revision 1, dated May 1990, of the SID provide acceptable methods for accomplishing the inspections required by this paragraph. All inspection results (negative or positive) must be reported to McDonnell Douglas, in accordance with the instructions contained in Section 2 of Volume III-90, dated May 1990; or Section 2 of Volume III-91, dated December 1991, of the SID. Information collection requirements contained in this regulation have been approved by the Office of Management and Budget (OMB) under the provisions of the Paperwork Reduction Act of 1980 (44 U.S.C. 3501 et seq.) and have been assigned OMB Control Number 2120-0056. \n\n\t(b)\tWithin 6 months after the effective date of this AD, replace the revision of the FAA-approved maintenance inspection program required by paragraph (a) of this AD, with a revision that provides for inspection(s) of the PSE's defined in Section 2 of Volume I of McDonnell Douglas Report No. L26-012, "DC-10 Supplemental Inspection Document (SID)," Revision 3, dated December 1992, in accordance with Section 2 of Volume III-92, dated October 1992, of the SID. The NDI techniques set forth in Section 2 and Section 4 of Volume II, Revision 3, dated December 1992, of the SID provide acceptable methods for accomplishing the inspections required by this paragraph. All inspection results (negative or positive) must be reported to McDonnell Douglas, in accordance with the instructions contained in Section 2 of Volume III-92, dated October 1992, of the SID. Information collection requirements contained in this regulation have been approved by the OMB under the provisions of the Paperwork Reduction Act of 1980 (44 U.S.C. 3501 et seq.) and have been assigned OMB Control Number 2120-0056.\n\n\t\t(1)\tFor those Fleet Leader Operator Sampling (FLOS) PSE's which do not have a Normal Maintenance Visual Inspection specified in Section 4 of Volume II, Revision 3, dated December 1992, of the SID, the procedure for general visual inspection is as follows: Perform an inspection of the general PSE area for cleanliness, presence of foreign objects, security of parts, cracks, corrosion, and damage.\n\n\t\t(2)\tFor PSE's 53.10.031E/.032E, 53.10.047E/.048E, and 57.10.029E/.030E: The ENDDATE for these PSE's is October 1993. (For these PSE's disregard the June 1993 ENDDATE specified in Section 2 of Volume III-92, dated October 1992, of the SID.)\n\n\t(c)\tAny cracked structure detected during the inspections required by paragraph (a) or (b) of this AD must be repaired before further flight, in accordance with a method approved by the Manager, Los Angeles Aircraft Certification Office (ACO), FAA, Transport Airplane Directorate.\n\n\tNOTE 1: Requests for approval of any PSE repair that would affect the FAA-approved maintenance inspection program that is required by this AD should include a damage tolerance assessment for that PSE repair.\n\n\t(d)\tAn alternative method ofcompliance or adjustment of the compliance time that provides an acceptable level of safety may be used if approved by the Manager, Los Angeles ACO, 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, Los Angeles ACO.\n\n\tNOTE 2: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Los Angeles ACO.\n\n\t(e)\tSpecial 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. \n\n\t(f)\tThe incorporation of the revision and reporting requirements shall be done in accordance with McDonnell Douglas Report No. L26-012, "DC-10 Supplemental Inspection Document (SID)," Volumes I, II, and III, Revision 1, dated May 1990; and McDonnell Douglas Report No. L26-012, "DC-10 Supplemental Inspection Document (SID)," Volume I, Revision 3, dated December 1992, Volume II, Revision 3, dated December 1992, and Volume III-92, dated October 1992; which contains the following list of effective pages:\n\n\nVolume Number\nReferenced and Date\n\nPage Number\nRevision Level\nShown on Page\nDate\nShown on Page\n\n\n\n\nI - All Series, \nRevision 3,\nDecember 1992\n\nList of Effective Pages \nA, B, C, D,\nE, and F\n\n3\nDecember 1992\n\n\n\n\nII - All Series,\nRevision 3,\nDecember 1992\nList of Effective Pages \nA, B, C, D, E, F, G, H, I, J,\nK, L, M, N, O, and P\n3\nDecember 1992\n\n\n\n\nIII-92 - All Series,\nOriginal\nOctober 1992\nEntire Document \nOriginal \nOctober 1992\n\n(NOTE: The issue/publish date of Volumes I, II, III is indicated on the Record of Revisions page.) The incorporation by reference of McDonnell Douglas Report No. L26-012, "DC-10 Supplemental Inspection Document (SID)," Volume I, Revision 3, dated December 1992, Volume II, Revision 3, dated December 1992, and Volume III-92, dated October 1992; is approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR Part 51. The incorporation by reference of McDonnell Douglas Report No. L26-012, "DC-10 Supplemental Inspection Document (SID)," Volumes I, II, and III, Revision 1, dated May 1990, was approved previously by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR Part 51 as of March 9, 1992 (57 FR 3931, February 3, 1992). Copies may be obtained from McDonnell Douglas Corporation, P.O. Box 1771, Long Beach, California 90846-1771, Attention: Business Unit Manager, Technical Publications - Technical Administrative Support, C1-L5B. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at FAA, Transport Airplane Directorate, Los Angeles Aircraft Certification Office, 3229 East Spring Street, Long Beach, California 90806-2425; or at the Office of the Federal Register,800 North Capitol Street, NW., suite 700, Washington, DC.\n\n\t(g)\tThis amendment becomes effective on November 24, 1993.
79-05-09: 79-05-09\tTELEDYNE CONTINENTAL MOTORS: Amendment 39-3426. Applies to: \n\nNEW ENGINES \n\nModel\t\t\tSerial Numbers \n\nO-470R\t\t\t466555, 466556, 466561, 466562, 466566 thru 466574 \n\nO-470S\t\t\t464570 \nO-470U\t\t\t467230 thru 467237, 467250 thru 467261, 467263 thru 467271, 467273 \nthru 467313, 467315 thru 467373, 467375, 467377 thru 467397, 467399 thru 467406, 467408 thru 467417, 467419 thru 467448, 467450, 467451, 467453 thru 467464, 467466 thru 467487, 467489 thru 467520, 467523, 567524, 467526 thru 467531, 467533 thru 467539, 467541, 467544 thru 467547, 467550 thru 467558 \nIO-470F\t\t\t453049, 453050 \n\nIO-470L\t\t\t465350 thru 465352, 465354, 465355, 465357 thru 465359, 465361 thru \n465363, 465370 thru 465378, 465380, 465382, 465385, 465388, 465392, 465393, 465395 thru 465399, 465402, 465406, 465408, 465412, 465414, 465415, 465418 thru 465420, 465431 thru 465433, 465437, 465438, 465440, 465441, 465446, 465449 thru 465459 \nIO-470N\t\t458085, 458087 thru 458125, 458127 \n\nIO-520BA & BB\t\t569432, 569447, 569448, 569451 thru 569456, 569458, 569461, 569463 \nthru 569468, 569485, 569507, 569512, 569527, 569566 thru 569593, 569609, 569612, 569619, 569622, 569629, 569637 thru 569659, 569675, 569691, 569713, 569720, 569721, 569723, 569724, 569725 thru 569731, 569734 \n\nIO-520C & CB\t\t561981, 561990, 561991, 561993, 561998, 571001, 571011, 571015, \n571016, 571018, 571025, 571027, 571031, 571033, 571034, 571037, 571041, 571043 thru 571047, 571052, 571065, 571067, 571070, 571071, 71074 thru 571077, 571082, 571089 thru 571093, 571112, 571114, 571123, 571125, 571127 thru 571129, 571133, 571137, 571139 thru 571143, 571149, 571166 thru 571172, 571178, 571180, 571181, 571184, 571185, 571187, 571223 thru 571228 \n\nIO-520D\t\t566792 thru 566794, 566812 thru 566819, 566821, 566840, 566852, \n566856, 566869, 566873 thru 566877, 566880 thru 566884, 566886 thru 566893, 566895 thru 566899, 566900 thru 566929, 566931, 566933, 566934, 566937, 566939, 566941, 566943 thru 566948, 566952 thru 566958, 566962 thru 566965, 566982 thru 566989, 566991 thru 566999, 572001 thru 572003, 572005 thru 572019, 572022 thru 572024, 572026 thru 572032, 572035 thru 572041, 572043 thru 572055, 572057 thru 572062, 572070, 572077 \n\nIO-520E\t\t\t556389, 556391, 556395, 556396, 556397, 556407 thru 556441 \n\nIO-520F\t\t\t570043 thru 570046, 570066 thru 570266, 570268 thru 570275, \n570277 thru 570281, 570284, 570285, 570290 thru 570292, 570300 thru 570312 \n\nIO-520K\t\t\t557360 thru 557367, 557369, 557371, 557373 thru 557405 \n\nIO-520L\t\t\t567255, 567256, 567264, 567266, 567270 thru 567280, 567282 thru \n567293, 567295, 567296, 567299 thru 567312, 567314 thru 567316, 567318, 567320 thru 567325, 567327 thru 567336, 567338, 567339, 567342 thru 567350, 567352 thru 567355, 567359 thru 567363 \n\nIO-520M & MB\t\t565506 thru 565509, 565511, 565512, 565514 thru 565529, 565532 thru \n565546, 565548 thru 565552, 565554, 565557, 565560 thru 565563, 565565 thru 565587, 565589, 565592, 565593, 565596, 565598 thru 565600, 565602, 565603, 565607 thru 565627, 565629, 565631, 565632, 565634, 565635, 565636 thru 565641, 565649, 565651 thru 565653, 565657, 565658, 565662, 565667, 565668, 565671, 565672, 565678, 565692, 565698 \n\nTSIO-520B & BB\t500639, 500644, 500650, 500651 thru 500654, 500660 thru 500665, \n500667 thru 500672, 500674, 500675, 500679, 500680, 500682 thru 500700, 500703, 500704, 500707 thru 500721, 500723 thru 500726, 500728, 500729, 500733 thru 500738, 500740, 500742, 500744, 500747, 500749, 500751, 500752, 500755, 500758 thru 500760, 500771, 500772, 500775, 500776, 500790, 500792, 500794 \n\nTSIO-520C\t\t501540, 501541, 501543 thru 501545 \n\nTSIO-520D & DB\t505009 \n\nTSIO-520E & EB\t501408 thru 501413, 501421 thru 501427, 501430 thru 501470 \n\nTSIO-520H\t\t506865 thru 506868 \n\nTSIO-520J & JB\t\t503605, 503607 thru 503611 \n\nTSIO-520K & KB\t504314 \n\nTSIO-520L & LB\t\t508546, 508549, 508551 thru 508553, 508557, 508559 thru 508573, \n508576, 508579, 508580, 508583 thru 508601, 508603 thru 508607, 508609, 508611 thru 508614, 508618 thru 508626, 508628 thru 508630, 508633, 508681 thru 508693, 508695 thru 508697, 508706 \n\nTSIO-520M\t\t511379 thru 511408, 511410 thru 511420, 511423 thru 511425, 511426 \nthru 511438, 511440 thru 511448, 511451 thru 511459, 511461 thru 511463, 511465 thru 511474, 511476 thru 511480, 511482 thru 511484, 511486 thru 511491, 511493, 511495 thru 511497, 511499, 511503 thru 511505, 511507 thru 511521, 511523 thru 511532, 511535, 511537 thru 511554, 511589 \n\nTSIO-520N & NB\t514303, 514313, 514315 thru 514318, 514327, 514330 thru 514332, \n514334 thru 514407, 514409 thru 514412, 514414 thru 514418, 514420 thru 514434, 514436 thru 514440, 514442 thru 514464, 514467 thru 514491, 514495 thru 514497, 514499, 514501, 514503 thru 514525, 514529 thru 514531, 514534 thru 514537, 514541 thru 514543, 514547 thru 514550, 514552, 514553, 514555 thru 514558, 514560 thru 514571, 514575 thru 514582, 514584 thru 514591, 514593, 514595, 514597, 514598, 514601 thru 514604, 514606 thru 514609, 514618 thru 514623, 514630 thru 514634, 514640, 514642, 514645, 514650, 514651, 514657, 514658, 514662, 514664, 514665, 514671, 514679, 514681, 514691, 514698, 514701, 514728, 514763, 514766 thru 514768, 514771, 514792 thru 514794, 514797, 514815 \n\nTSIO-520P\t\t513028, 513031, 513048 thru 513081, 513083 thru 513125, 513127 thru \n513129, 513133 thru 513140, 513142, 513143, 513146, 513150 thru 513161, 513164, 513166, 513168 thru 513177, 513181, 513185, 513190, 513191, 513193 thru 513195 \n\nTSIO-520R\t\t512759, 512779, 512790 thru 512811, 512813 thru 512833, 512835 thru \n512842, 512844 thru 512909, 512911 thru 512976, 512978 thru 512986, 512988 thru 512991, 512993 thru 512995, 512997, 512998, 517000 thru 517030, 517032 thru 517035, 517037 thru 517043, 517045 thru 517054, 517056 thru 517065, 517067 thru 517074, 517077, 517078, 517080 thru 517082, 517084 thru 517086, 517088 thru 517102, 517104, 517107, 517108, 517109, 517111 \n\nTSIO-520T\t\t515008, 515009, 515014,515016, 515017, 515022, 515023, 515026, \n515027, 515030 thru 515032, 515039 thru 515044, 515046, 515047, 515051, 515053, 515055, 515056 \n\nTSIO-520U\t\t515501 thru 515506 \n\nTSIO-520VB\t\t516001 thru 516024, 516026 thru 516030, 516033, 516035, 516037, \n516039, 516041, 516043 thru 516045, 516050, 516053, 516057, 516060 thru 516064, 516080 thru 516083, 516091, 516114 thru 516117 \n\nGTSIO-520C\t\t602228 \n\nGTSIO-520H\t\t600993, 600995, 607000, 607002, 607003 \n\t\nGTSIO-520K\t\t605149, 605150, 605152 thru 605154 \n\nGTSIO-520L\t\t604797, 604932, 604937, 604938, 604942 thru 604953, 604955 thru \n604966, 604968 thru 604975, 604978, 604981 thru 604983, 604985, 604986, 604988, 604989, 604991 thru 604994, 604996 thru 604999, 608000 thru 608002, 608004 thru 608011, 608014, 608018, 608020, 608023 thru 608029, 608034, 608040, 608043 thru 608048, 608050 thru 608053, 608064, 608066 \n\nGTSIO-520M\t\t606363, 606366, 606400 thru 606439, 606441, 606443, 606444, 606452 \nthru 606454, 606456, 606459, 606460, 606475 \n\nREBUILT ENGINE \n\nModel\t\t\tSerial Numbers \n\nIO-346A\t\t\t230102R, 230103R \n\n6-285CA\t\t227150R thru 227152R, 227154R thru 227162R, 227173R, 227175R, \n227176R \n\nO-470G\t\t\t70671R thru 70673R \n\nO-470J\t\t\t202093R, 202094R, 202096R thru 202102R \n\nO-470K\t\t\t49345R thru 49350R \n\nO-470L\t\t\t69571R, 69572R, 69575R thru 69584R, 69586R thru 69588R \n\nO-470M\t\t\t54081R thru 54085R, 54088R thru 54100R \n\nO-470R\t\t\t226839R, 226858R, 226863R, 226865R, 226868R thru 226907R, \n226909R thru 226914R, 226916R thru 226944R, 226946R, 226949R thru 226954R, 226956R, 226958R, 226962R \n\nO-470S\t\t\t226259R, 226261R thru 226270R, 226272R thru 226281R \n\nO-470U\t\t\t230351R, 230352R, 230354R \n\nIO-470C\t\t\t227245R thru 227264R \n\nIO-470D\t\t105517R thru 105523R, 105525R thru 105527R, 105529R \n\nIO-470E\t\t\t88716R thru 88719R \n\nIO-470F\t\t\t89762R thru 89766R \n\nIO-470H\t\t87327R \n\nIO-470J\t\t\t89100R thru 89102R \n\nIO-470K\t\t\t92767R thru 92779R \n\nIO-470L\t\t\t230033R, 230035R, 230038R thru 230069R, 230071R thru 230077R, \n230079R thru 230082R, 230084R, 230085R, 230088R, 230089R, 230094R, 230095R \n\nIO-470N\t\t96343R thru 96350R, 96352R, 96358R \n\nIO-470S\t\t\t109282R thru 109287R \n\nIO-470U\t\t118389R thru 118390R \n\nIO-470V\t\t\t170628R thru 170652R, 170654R THRU 170665R, 170670R, 170671R \n\nIO-520A\t\t\t112401R thru 112427R, 112429R thru 112431R \n\nIO-520BA\t\t122813R, 122819R, 122836R thru 122841R, 122843R thru 122858R, \n122860R thru 122872R, 122926R, 122931R thru 122934R, 122937R thru 122942R, 122944R thru 122953R, 122956R thru 122958R, 122960R, 122962R, 122964R thru 122966R, 122969R, 122973R thru 122975R, 122978R \n\nIO-520C\t\t\t17325OR, 173259R, 173277R, 173282R, 173284R thru 173289R, \n173294R, 173297R thru 173354R, 173356R thru 173376R, 173379R thru 173396R, 173398R, 173399R, 231553R thru 231601R, 231604R, 231606R, 231609R, 231610R, 231612R, 231615R, 231620R \n\nIO-520D\t\t179564R, 179571R, 179577R thru 179583R, 179585R thru 179613R, \n179615R thru 179628R, 179630R thru 179644R, 179646R, 179647R,179651R, 179654R thru 179658R, 179660R, 179664R \n\nIO-520E\t\t\t215537R \n\nIO-520F\t\t\t195764R, 195767R, 195768R, 195771R, 195774R, 195779R thru \n195797R, 195799R, 195801R, 195802R, 195804R thru 195810R, 195812R thru 195814R, 195818R thru 195829R \n\nIO-520K\t\t\t224010R, 224011R, 224013R \n\nIO-520L\t\t\t220560R thru 220580R \n\nIO-520M\t\t227369R thru 227396R, 227398R thru 227404R \n\nTSIO-520B\t\t176277R, 176281R thru 176283R, 176285R thru 176301R, 176303R \n\nTSIO-520C\t\t178168R thru 178175R, 178178R \n\nTSIO-520E\t\t182930R, 182932R, 182934R thru 182942R, 182944R thru 182998R, \n183000R thru 183017R, 183020R thru 183024R, 183026R thru 183051R, 183054R, 183056R, 183057R \n\nTSIO-520G\t\t216008R \n\nTSIO-520H\t\t217055R thru 217067R \n\nTSIO-520J\t\t218738R thru 218759R, 218761R, 218762R, 218768R thru 218770R \n\nTSIO-520K\t\t224545R \n\nTSIO-520L\t\t227621R, 227622R, 227624R thru 227626R, 227629R \n\nTSIO-520M\t\t230128R, 230129R \n\nTSIO-520N\t\t228091R thru 228114R, 228117R thru 228120R, 228122R \n\nTSIO-520R\t\t230228R, 230230R thru 230233R \n\nGTSIO-520C\t\t155451R thru 155473R, 155479R \n\nGTSIO-520D\t\t219302R thru 219312R, 219314R, 219315R, 219318R \n\nGTSIO-520H\t\t218429R, 218431R thru 218448R, 182450R thru 218465R, 218467R thru \n218493R, 218500R, 231351R thru 231386R, 231388R, 231389R, 231397R \n\nGTSIO-520K\t\t226041R thru 226052R \n\nGTSIO-520L\t\t227825R thru 227829R, 227831R thru 227833R, 227858R, 227860R thru \n227862R \n\nGTSIO-520M\t\t227914R, 227915R, 227917R thru 227922R, 227924R thru 227929R, \n227931R thru 227937R, 227939R, 227940R \n\n\tIn addition, all Teledyne Continental Motors engines of the above listed models, regardless of serial number, which have had the oil pump assembly or oil pressure relief valve screw and/or plunger changed in service during the period April 1, 1978 through January 5, 1979, must comply with this AD. \n\tCompliance is required within the next 50 hours' time in service after the effective date of this AD, unless already accomplished. \n\tTo prevent the possible loss of oil pressure indication, accomplish the following: \n\t(1)\tInspect the oil pressure relief valve housing. If a yellow paint dot is evident, no further action is required. If the paint dot is not evident, remove the relief valve assembly, inspect the screw and plunger and compare their dimensions to the illustrations in paragraph (3). \n\t(2)\tThose screws and plungers which conform dimensionally to Figure 2, "Intermediate Design," must be replaced with components conforming to Figure 3, "Current Design." The "Current Design" is contained in TCM Kit 642335KA1. Screws and plungers conforming to Figure 1, "Original Design," may be continued in service. \n\t(3) \n\n\n\t(4)\tIdentify the oil pressure relief valve housing with a yellow dot on those valves with plungers installed in accordance with Figures 1 and 3. \n\t(5)\tAn alternate method of compliance may be approved by the Chief, Engineering and Manufacturing Branch, Federal Aviation Administration, Southern Region. \n\t\tNOTE:Teledyne Continental Motors (TCM) Service Bulletin M79-2, Rev. 1, dated February 12, 1979, also pertains to this subject. \n\tThis amendment becomes effective March 12, 1979.