Results
96-12-12: This amendment supersedes Airworthiness Directive (AD) 80-22-04, which currently requires the following on The New Piper Aircraft, Inc. (Piper) Models PA31, PA31-300, PA31-325, and PA31-350 airplanes: repetitively inspecting the upper section of Fuselage Station (FS) 317.75 bulkhead for cracks, and incorporating a certain reinforcement kit if any crack is found. This action requires inspecting (one-time) the upper section of the FS 317.75 bulkhead for cracks, and incorporating one of two reinforcement kits depending on whether cracks are found in the FS 317.75 bulkhead area. Cracks found on airplanes in compliance with the inspection requirements of AD 80-22-04 and the Federal Aviation Administration's policy on aging commuter-class aircraft prompted this action. The actions specified in this AD are intended to prevent structural failure of the vertical fin forward spar caused by cracks in the FS 317.75 bulkhead, which, if not detected and corrected, could result in lossof control of the airplane.
93-10-11: 93-10-11 AVIONS MUDRY & CIE: Amendment 39-8592. Docket 92-CE-20-AD. Supersedes AD 80-24-51, Amendment 39-4119 which superseded AD T80-17-51. Applicability: Model CAP 10B airplanes (all serial numbers), certificated in any category. Compliance: Required as indicated, unless already accomplished. To prevent fatigue failure of the wing spar, which could lead to loss of control of the airplane, accomplish the following: (a) For airplanes having a serial number of 263 or lower, within the next 100 hours TIS, install a permanent inspection opening in the wing in accordance with the Technical Instructions section of Avions Mudry & Cie Service Bulletin (SB) CAP10B No. 16 (ATA 57-004), dated April 27, 1992. NOTE 1: The installation specified in paragraph (a) of this AD is incorporated during production for airplanes having a serial number of 264 or higher. (b) For all serial number airplanes, within the next 100 hours TIS and thereafter at intervals not to exceed1,000 hours TIS, inspect the upper and lower wing spar caps for cracks in accordance with the Technical Instructions section of Avions Mudry & Cie SB CAP10B No. 15 (ATA 57-003), dated April 14, 1992. If cracks are found, prior to further flight, obtain a repair scheme from the manufacturer through the Manager, Brussels Aircraft Certification Office, at the address specified in paragraph (d) of this AD, and incorporate this repair scheme. (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) An alternative method of compliance or adjustment of the initial or repetitive compliance times that provides an equivalent level of safety may be approved by the Manager, Brussels Aircraft Certification Office, FAA, Europe, Africa, and Middle East Office, c/o American Embassy, B-1000 Brussels, Belgium. The request shall be forwarded through an appropriate FAA Maintenance Inspector, who may add comments and then send it to the Manager, Brussels Aircraft Certification Office. NOTE 2: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Brussels Aircraft Certification Office. (e) The inspections and installation required by this AD shall be done in accordance with Avions Mudry & Cie Service Bulletin CAP10B No. 15 (ATA 57-003), dated April 14, 1992, and Avions Mudry & Cie Service Bulletin CAP10B No. 16 (ATA 57-004), dated April 27, 1992. 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 Avions Mudry & Cie, B.P. 214, 27300 Bernay, France. Copies may be inspected at the FAA, Office of the Assistant Chief Counsel, Room 1558, 601 E. 12th Street, Kansas City, Missouri, or at the Office of the Federal Register, 800 North Capitol Street, NW, suite 700, Washington, DC. (f) This amendment (39-8592) supersedes AD 80-24-51, Amendment 39-4119 which superseded AD T80-17-51. (g) This amendment becomes effective on July 23, 1993.
2000-22-08: This amendment adopts a new airworthiness directive (AD), applicable to certain EMBRAER Model EMB-120 series airplanes, that requires inspections of certain components, and corrective action, if necessary. The actions specified by this AD are intended to prevent deterioration and deformation of the mass-balance weights of the aileron, which could affect the surface balance of the aileron and result in loss of aileron control and consequent reduced controllability of the airplane. This action is intended to address the identified unsafe condition.
2018-23-14: We are adopting a new airworthiness directive (AD) for certain Airbus SAS Model A330-200 series airplanes; Model A330-200 Freighter series airplanes; and Model A330-300 series airplanes. This AD was prompted by revisions to certain airworthiness limitation item (ALI) documents, which specify more restrictive instructions and/or airworthiness limitations. This AD requires revising the existing maintenance or inspection program, as applicable, to incorporate new or more restrictive instructions and/or airworthiness limitation requirements. We are issuing this AD to address the unsafe condition on these products.
T91-11-51:
2018-24-02: We are adopting a new airworthiness directive (AD) for certain Dassault Aviation Model MYSTERE-FALCON 50, MYSTERE-FALCON 900, and FALCON 900EX airplanes. This AD was prompted by reports of cracked reinforcing straps (doublers) on the ailerons of airplanes equipped with blended winglets. This AD requires repetitive detailed inspections for cracking of the upper and lower reinforcing straps on the ailerons, and replacement if necessary. We are issuing this AD to address the unsafe condition on these products.
98-14-13: This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A300, A310, and A300-600 series airplanes. This amendment requires a one-time operational test and repetitive functional tests of the free fall control mechanism of the landing gear to ensure proper release of the main landing gear (MLG), and corrective action, if necessary. This amendment also requires eventual modification of the free fall control mechanism of the landing gear, which constitutes terminating action for the repetitive functional tests. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to prevent malfunction of the free fall control mechanism of the landing gear, which could result in the inability to extend the MLG in the event of failure of the hydraulic extension system. DATES: Effective August 12, 1998. The incorporation by reference of certain publications listed in the regulations is approved by the Director of the Federal Register as of August 12, 1998.
98-12-18: This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A320-111, -211, and -231 series airplanes, that requires repetitive inspections for cracking in the transition and pick-up angles in the lower part of the center fuselage area, and corrective action, if necessary. This amendment also provides for an optional terminating modification for the repetitive inspection requirements. This amendment is prompted by the issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to detect and correct fatigue cracking in the transition and pick-up angles of the lower part of the center fuselage, which could result in reduced structural integrity of the wing-fuselage support and fuselage pressure vessel.
2000-15-09: This amendment adopts a new airworthiness directive (AD), applicable to Honeywell International, Inc. (formerly AlliedSignal Inc. and Garrett Turbine Engine Company) high pressure compressor (HPC) impellers installed on TFE731-2, -3, -4, and -5 series turbofan engines. This AD requires the removal and inspection of the HPC impeller and, if necessary, replacement of the HPC impeller with a serviceable impeller. This amendment is prompted by an incident of an uncontained impeller failure due to cracking in the seal relief area of the HPC impeller. The actions specified by this AD are intended to prevent HPC impeller failure due to fatigue cracking.
2000-01-01: This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A300 B2-1A, B2-1C, B2-203, B2K-3C, B4-103, B4-2C, and B4-203 series airplanes, that requires modification of the wire harness routing next to the pitch artificial feel unit, and removal of the green and yellow colors from various connectors. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to prevent the electrical connections of the actuators of the green and yellow hydraulic systems for the pitch artificial feel unit from being cross connected due to the design of the wire harness routing, which could result in a stiff elevator control at takeoff, and consequent reduced controllability of the airplane.
2006-04-04: The FAA is adopting a new airworthiness directive (AD) for certain smoke detectors installed on various transport category airplanes. This AD requires replacing the affected smoke detectors with modified smoke detectors. This AD results from a report indicating that the affected smoke detectors can "lock up" during electrical power transfer from the auxiliary power unit to the engines. We are issuing this AD to identify and provide corrective action for a potentially inoperative smoke detector and to ensure that the flightcrew is alerted in the event of a fire.
81-09-02: 81-09-02 PICCARD BALLOON: Amendment 39-4091. Applies to Model Ax-6 Series Balloon, certified in all categories. Compliance is required as indicated, unless already accomplished. To prevent inadvertent deflation panel opening in flight, accomplish the following: (a) Prior to the next inflation, and during each subsequent preflight inspection, after the effective date of this AD: (1) Check the synthetic fastener tape, known as hook and pile (Velcro), of the deflation panel system for broken hook and pile, or deterioration caused by heat, in accordance with paragraph A of General Balloon Corporation Service Letter Number 7, dated March 17, 1981, (hereafter referred to as General Balloon Letter No. 7). (2) Repair all areas of hook and pile found to be unserviceable during check (a)(1), in accordance with paragraph G of General Balloon Letter No. 7. (3) After accomplishment of (a)(1) and (a)(2), conduct a side shear load transfer capability check of thehook and pile, in accordance with paragraph B of General Balloon Letter No. 7. If hook and pile separate, accomplish either (i) or (ii) as follows: (i) Have the side shear load transfer capability of the hook and pile retested by a rated mechanic or certified repair station, in accordance with paragraph E of General Balloon Letter No. 7, and replace all areas of hook and pile unable to sustain the side shear load with like serviceable fastener tape. (ii) Have a rated mechanic or certified repair station replace areas of hook and pile that did not pass the side shear load transfer capability check conducted in paragraph (a)(3) with like serviceable fastener tape. (4) Preflight checks conducted in accordance with Piccard Balloon Ax-6 Balloon Flight Manual (BFM) Revision No. 9, dated April 2, 1981, deletes the requirements for subsequent preflight checks specified in paragraph (a) of this AD. (b) Prior to next inflation, after the effective date of this AD, install an approved mechanical latch (i.e., a Capewell) at the apex of the balloon envelope, in accordance with the balloon manufacturer's instructions as approved by the FAA. (c) At intervals not to exceed 100 hours time in service or at each annual inspection after the effective date of this AD, whichever comes first, accomplish side shear load transfer capability test of the hook and pile fastener tape, in accordance with paragraph E of General Balloon Letter No. 7. Replace areas of degraded hook and pile fastener tape with like serviceable fastener tape. NOTE: The General Balloon Corporation Service Letter Number 7, dated March 17, 1981, is applicable to Piccard Balloon Model Ax-6, since General Balloon Corporation produces the Piccard Balloon Ax-6 under a licensing arrangement with Don Piccard Balloons, Inc., the type certificate holder. NOTE: Revision 9 to the Piccard Balloon Ax-6 Balloon Flight Manual (BFM), dated April 2, 1981, is being distributed with General Balloon Corporation Service Letter Number 7, dated March 17, 1981, or may be obtained from General Balloon Corporation, P.O. Box 1902, Newport Beach, California 92663. All repairs, modifications, and inspections stipulated in this AD must be accomplished by a rated mechanic or an FAA certified repair station. The checks required by this AD constitute preventative maintenance and may be performed by persons authorized to perform preventative maintenance under FAR 43. The checks required by this AD may be performed by a pilot with a free balloon rating. Accomplishment of the checks required by this AD are to be recorded in the balloon maintenance records. Alternative inspections, modifications, or other actions which provide an equivalent level of safety may be used when approved by the Chief, Engineering and Manufacturing Branch, FAA Western Region. 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. 553(a)(1). All persons affected by this directive who have not already received these documents from the manufacturer may obtain copies upon request to General Balloon Corporation, P.O. Box 1902, Newport Beach, California 92663. These documents may also be examined at Room 6W14, FAA Western Region, 15000 Aviation Boulevard, Hawthorne, California, and at FAA Headquarters, 800 Independence Avenue, S.W., Washington, D.C. A historical file on this AD, which includes the incorporated material in full, is maintained by the FAA at its Headquarters in Washington, D.C., and at FAA Western Region Office, Room 6W14. This amendment becomes effective April 23, 1981.
74-03-02: 74-03-02 BEECH: Amendment 39-1777. Applies to Model F33A (Serial Numbers CE- 436 thru CE-463 except CE-439 and CE-462); Model V35B (Serial Numbers D-9469 thru D- 9536 except D-9481, D-9532 and D-9533); Model A36 (Serial Numbers E-425 thru E-475 except E-431); Models 95-B55 and 95-B55A (Serial Numbers TC-1552 thru TC-1607 except TC-1557, TC-1558, TC-1599 and TC-1604); Models E55 and E55A (Serial Numbers TE-914 through TE-940 except TE-919, TE-920 and TE-938); and Models 58 and 58A (Serial Numbers TH-325 thru TH-383 except TH-336, TH-337, TH-363 and TH-382) airplanes. Compliance: Required as indicated, unless already accomplished per Beechcraft Service Instructions 0612-200 or later FAA-approved revisions. To check landing gear shock strut pistons for proper hardness, within the next 100 hours' time in service after the effective date of this AD, accomplish the following. A) Using a portable hardness tester, measure the hardness of the nose gear shock strut piston in an area from 1 inch to 4 inches above the nose wheel fork. The allowable hardness range is from Rockwell Scale C38 to C46 1/2. If during the hardness measuring process a reading appears unreliable, make additional measurements at other spots but within the 1 inch to 4 inch area specified herein until an accurate measurement is obtained. B) Using a portable hardness tester, measure the hardness of both main gear shock strut pistons in an area 1 inch to 4 inches above the axle socket. The allowable hardness range is from Rockwell Scale C43 1/2 to C50 1/2. If during the hardness measuring process a reading appears unreliable, make additional measurements at other spots but within the 1 inch to 4 inch area specified herein until an accurate measurement is obtained. C) If a hardness measurement is outside of the hardness range specified in Paragraphs A and/or B of this AD, prior to further flight, replace any defective landing gear shock strut piston with an airworthy piston, except that the airplane may be flown in accordance with FAR 21.197 to a base where the replacement can be performed, provided the landing gear remains down and locked. This amendment becomes effective February 5, 1974.
75-22-10: 75-22-10 ENSTROM: Amendment 39-2403. Applies to Enstrom Models F-28A and 280 helicopters certified in all categories, with the following serial numbers: F-28A - S/N's 4 through 275, 277, 278, 280 through 283. 280 - S/N's 1001 through 1006. Note: Helicopters equipped with a 'tang' hub lock washer, Enstrom P/N 28-14263, are exempt from compliance with this Airworthiness Directive. Compliance required as indicated unless already accomplished. Within the next 25 hours time in service after the effective date of this Airworthiness Directive: (a) Remove the main rotor retention nut, Enstrom P/N 28-14004, and hub nut washer, Enstrom P/N 28-14005; (b) Replace hub nut washer, Enstrom P/N 28-14005, with a new retention washer, Enstrom P/N 28-14008, or an equivalent approved by the Chief, FAA Engineering and Manufacturing Branch, Great Lakes Region. The chamfer on the new washer must be installed parallel with the main rotor spline chamfer; and, (c) Install main rotor hub retention nut, Enstrom P/N 28-14004, and torque nut to a value of 400 ft. lbs. Re-safety with .040" diameter stainless steel safety wire in three (3) places to the hub adapter plate bolt heads. Enstrom Service Notes 0025 and 0025A pertain to this same subject. This amendment becomes effective October 28, 1975.
2018-23-15: We are adopting a new airworthiness directive (AD) for all Airbus SAS Model A330-200 Freighter series airplanes, Model A330-200 and -300 series airplanes, and Model A340-200 and -300 series airplanes. This AD was prompted by defects found during production tests of ram air turbine (RAT) units; investigation revealed that the defects were due to certain RAT hydraulic pumps having an alternative manufacturing process of the pump pistons. This AD requires replacing any defective RAT hydraulic pump with a serviceable part and re- identifying the RAT module part number. We are issuing this AD to address the unsafe condition on these products. [[Page 59286]]
2006-03-10: The FAA is adopting a new airworthiness directive (AD) for certain Airbus Model A318-100 and A319-100 series airplanes; A320-111 airplanes; A320-200 series airplanes; and A321-100 and A321-200 series airplanes. This AD requires a one-time inspection of the horizontal hinge pin of the 103VU electrical panel in the avionics compartment to determine if the hinge pin can move out of the hinge, and related investigative and corrective actions if necessary. This AD results from a report indicating that electrical wire damage was found in the 103VU electrical panel due to contact between the hinge pin and the adjacent electrical wire harness. We are issuing this AD to prevent contact between the horizontal hinge pin and the adjacent electrical wire harness, which could result in damage to electrical wires, and consequent arcing and/or failure of associated systems.
95-20-04 R1: This amendment revises an existing airworthiness directive (AD), applicable to all Lockheed Model L-1011-385-1 series airplanes, that currently 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. That AD originally was prompted by a structural re-evaluation by the manufacturer that identified certain structural details where fatigue damage is likely to occur. The actions specified in that AD are intended to prevent fatigue cracking that could compromise the structural integrity of these airplanes. This amendment corrects the compliance time for the initial inspection of each structurally significant detail (SSD). The incorporation by reference of certain publications listed in the regulations was approved previously by the Director of the Federal Register as of November 2, 1995 (60 FR 51713, October 3, 1995).
2006-02-06: The FAA is adopting a new airworthiness directive (AD) for certain Airbus Model A310-203, -204, and -222 airplanes, and Model A310-300 series airplanes. This AD requires a one-time rototest inspection for cracking of the frame foot and adjacent frames and skin in the area surrounding the frame foot run-outs from fuselage frames (FR) 43 through FR 46, and repair if necessary. This AD also requires modification of certain fastener holes. This AD results from a structural evaluation of Model A310 airplanes for widespread fatigue damage of the frame foot run-outs from FR 43 through FR 46. The evaluation revealed that, on in-service airplanes, undetected cracking in this area can lead to the rupture of the frame foot and subsequent cracking of the adjacent frames and fuselage skin. We are issuing this AD to prevent fatigue cracking of the frame foot run-outs, which could lead to rupture of the frame foot and cracking in adjacent frames and skin, and result in reduced structural integrity of the fuselage.
99-21-16: This amendment adopts a new airworthiness directive (AD), applicable to certain British Aerospace BAe Model ATP airplanes, that requires repetitive replacements of the weight on wheels microswitch harness subassembly with a new microswitch harness subassembly. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to prevent a nose wheel shimmy, which could result in the collapse of the nose landing gear during takeoff or landing and possible injury to the flightcrew and passengers.
96-08-08: This amendment supersedes an existing airworthiness directive (AD), applicable to all Airbus Model A300 series airplanes (excluding Model A300 B4-600 series airplanes), that currently requires certain structural inspections and modifications. This amendment requires additional structural inspections and modifications that have been identified as necessary to ensure the structural integrity of these airplanes as they approach their economic design goal. This amendment also excludes additional airplanes from the applicability of the AD. The actions specified by this AD are intended to prevent degradation of the structural capability of the affected airplanes.
2018-23-01: We are adopting a new airworthiness directive (AD) for certain Zodiac Seats France 536 Series Cabin Attendant Seats. This AD was prompted by cracks found in a highly concentrated stress area of the seat pan hinges. This AD requires repetitive inspections and replacement of the seat pan. We are issuing this AD to address the unsafe condition on these products.
58-14-01: 58-14-01 SUD AVIATION: Applies to All Alouette II SE 3130 Helicopters Equipped With Tail Rotor Blade Model Numbers 34.20.000, 34.20.000.50, 34.20.000.51, and 34.30.000. Compliance required prior to next flight and each 5 hours of operation thereafter. Two cases of defective bonding at the outboard end of the root end side plates of the tail rotor blades have been found. In order to preclude any possible fatigue failures of the blade, Sud Aviation has issued the following corrective measures which the French SGACC considers mandatory: Inspection A. Blades with rigid flapping restrainer. (Aircraft Numbers 1137 and above or aircraft incorporating modification V.14.) 1. Saturate with turbine oil (Spec. AIR 3512 or DED 2479/6, Shell turbine oil No. 9 or Esso aviation oil No. 57) the edge of the side plate and the bead of adhesive at the outboard end of the side plate. 2. Move blade to and from by pushing and pulling blade tip alternately four or five timesrespectively, applying a load of approximately 13 lb. (check with spring balance). 3. In the case of a defective blade, the oil will flow in and out and, at the same time, air bubbles may be produced. 4. If in doubt, wipe the side plate and repeat the above loading procedure. B. Blades with earlier type flapping restrainer. (Aircraft Numbers 1136 and below which do not incorporate modification V.14.) The previously described inspection procedure cannot be applied without risking distortion of the flapping restrainers. The procedure may, however, be applied if the blades are removed and are clamped in a vise over the two inboard blade-cuff retaining bolts (bolts nearest root end of blade). To avoid blade removal and inspection in a vise, the tools may be fabricated in order to rigidly support the blade root on the helicopter. The tools can simply consist of a wood block cut to proper length so as to rest at one end against the two tail gearbox nutsand at the other end against the blade-cuff bolts. To hold the blade in the other direction, strap the blade and the tail gearbox housing as shown in the sketch in the referenced Service Bulletin, using a cable cut to the proper length or, alternatively, a non-elastic strap. The inspection procedure is the same as previously described. C. Defective blades shall be retired from service immediately. Others may be left in service as long as the bonding is satisfactory up to a maximum of 300 hours. The FAA concurs with this action and considers compliance there with mandatory. (Sud Aviation Helicopter Service Bulletin No. AL 34.11.131/A covers the same subject.) This supersedes AD 58-13-04.
55-16-02: 55-16-02 MARTIN: Applies to Models 202, 202A, and 404 Aircraft Equipped With Hamilton Standard Propellers. Compliance required by first scheduled engine change after November 1, 1955, but not later than November 1, 1956. To increase the fire-resistance integrity of the propeller feathering system against damage by a powerplant fire, all flexible hose components of propeller feathering lines forward of the firewall must be replaced with lines and fittings which will meet current fire-resistant requirements. The following hose assemblies are considered acceptable for this application: (a) Aeroquip 680-12S hose assemblies with Aeroquip 304 protective sleeves over end fittings (Aeroquip assembly P/N 304000-12S). (b) Resistoflex SSFR-3800-10 hose assemblies utilizing -12 connections. (c) Aeroquip 309009-12S hose assemblies.
99-26-14: This amendment adopts a new airworthiness directive (AD) applicable to Agusta S.p.A. Model AB412 helicopters. This action requires removing and replacing certain main rotor yokes with airworthy main rotor yokes before further flight. This amendment is prompted by the fatigue failure of a main rotor yoke (yoke). Fatigue analysis indicates that certain yokes are on the low end of the manufacturer s tolerance for thickness and do not have the desired margin of safety. This condition, if not corrected, could result in fatigue failure of the yoke, loss of a main rotor blade, and subsequent loss of control of the helicopter.
2000-08-51: 2000-08-51 TELEDYNE CONTINENTAL MOTORS: Docket No. 2000-NE-16-AD. Applicability: This Airworthiness Directive (AD) is applicable to Teledyne Continental Motors (TCM) IO-360, TSIO-360, LTSIO-360, O-470, IO-470, TSIO-470, IO-520, TSIO-520, LTSIO-520, IO-550, TSIO-550 and TSIOL-550 series engines that were assembled, rebuilt, or overhauled using a crankshaft that was manufactured between April 1, 1998, and March 31, 2000, listed by engine and crankshaft serial number (SN) in TCM Mandatory Service Bulletin (MSB) 00-5A, dated April 28, 2000. NOTE 1: The engines and crankshafts that are the subject of this AD were manufactured by TCM from April 1, 1998 through March 31, 2000. However the dates that the engines and crankshafts were delivered may not coincide with their dates of manufacture. For crankshafts identified in paragraph (a) of this AD, TCM has already determined which engines have a new suspect crankshaft installed and have identified those engines by engine SN. The crankshaft SN is only used to determine the need for taking a core sample for those crankshafts identified in paragraph (a) and (b) of this AD. NOTE 2: The engine SN can be found in logbooks or other maintenance records. For those engines that were overhauled in the field with factory new crankshafts, the crankshaft SN should be shown in work orders, log books or other maintenance records. If the engine was assembled new, rebuilt, or overhauled on or before March 31, 1998, or on or after April 1, 2000, no action is required. NOTE 3: This AD applies to each engine identified in the preceding applicability provision, regardless of whether it has been modified, altered, or repaired in the area subject to the requirements of this AD. For engines that have been modified, altered, or repaired so that the performance of the requirements of this AD is affected, the owner/operator must request approval for an alternative method of compliance in accordance with paragraph (d) ofthis AD. The request should include an assessment of the effect of the modification, alteration, or repair on the unsafe condition addressed by this AD; and, if the unsafe condition has not been eliminated, the request should include specific proposed actions to address it. Compliance: Compliance with the following instructions is required within the next 10 hours time-in-service from the receipt of this Emergency AD, unless already accomplished. To prevent crankshaft failure due to crankshaft connecting rod journal fracture, which could result in total engine power loss, in-flight engine failure and possible forced landing, do the following: NOTE 4: TCM supplies an instructional video in the tool kit for MSB 00-5A. It is recommended that the technician views and understands "Instructional Video for Compliance with Teledyne Continental Motors Mandatory Service Bulletin MSB 00-5A" before performing these procedures. Crankshaft Material Inspection (a) For thoseengines and crankshafts listed by SN in TCM MSB 00-5A, dated April 28, 2000, perform the crankshaft material inspection (crankshaft propeller flange core sample) as follows: NOTE 5: The engine SN's listed in TCM MSB 00-5A contain only the numerical portion of the SN. Engines that have been rebuilt by TCM will have a letter "R" at the end of the six digit numerical portion. Disregard the letter "R." (1) Perform the crankshaft material inspection (crankshaft propeller flange core sample) in accordance with sections A through J of TCM MSB 00-5A, dated April 28, 2000, as follows: (i) Use the specialized tools and equipment provided by TCM as listed in section A of TCM MSB 00-5A, dated April 28, 2000. (ii) You may use each rotobroach bit to obtain up to six core samples. Replace the rotobroach after the sixth core sample, or before if the rotobroach does not cut with the maximum torque applied. (iii) Maintain a record of each core sample obtained with eachrotobroach bit used. Contact TCM to obtain additional rotobroach bits. (iv) Do not exceed the torque limits specified in TCM MSB 00-5A, dated April 28, 2000, when obtaining the core sample. (2) After obtaining the core sample, disposition the crankshaft as follows: (i) If TCM notifies you that the crankshaft is not serviceable, replace the crankshaft with a serviceable crankshaft of the same part number prior to further flight. (ii) If TCM notifies you that the crankshaft is serviceable, the propeller assembly may be reinstalled. Installation of Crankshafts (b) After the effective date of this AD, installation of a crankshaft with a SN that is listed in MSB 00-5A, dated April 28, 2000, is prohibited, unless core samples have been taken and TCM approval for return to service has been received. (c) Crankshaft material inspections (crankshaft propeller flange core samples) performed in accordance with TCM MSB 00-5, dated April 14, 2000, comply with this AD and must not be repeated. Alternative Methods of Compliance (d) 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, Atlanta Aircraft Certification Office (ACO). Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, Atlanta ACO. NOTE 6: Information concerning the existence of approved alternative methods of compliance with this airworthiness directive, if any, may be obtained from the Atlanta ACO. (e) Copies of the applicable service information may be obtained from Teledyne Continental Motors, PO Box 90, Mobile, AL 36601; telephone toll free 1-888-200-7565, or on the TCM internet site "www.tcmlink.com." This information may also be examined at the FAA, New England Region, Office of the Regional Counsel, 12 New England Executive Park, Burlington, MA 01803. (f) Emergency AD 2000-08-51, issued April 28, 2000, becomes effective upon receipt.