Results
2018-15-01: We are adopting a new airworthiness directive (AD) for certain Rolls-Royce plc (RR) Trent 1000-A, Trent 1000-C, Trent 1000-D, Trent 1000-E, Trent 1000-G, Trent 1000-H, Trent 1000-A2, Trent 1000-C2, Trent 1000-D2, Trent 1000-E2, Trent 1000-G2, Trent 1000-H2, Trent 1000-J2, Trent 1000-K2, and Trent 1000-L2 engine models. This AD requires certain engines susceptible to intermediate-pressure turbine (IPT) blade failure not be installed on an airplane together with other engines with IPT blades of the same age. This AD was prompted by new operating restrictions for engines with IPT blades susceptible to shank corrosion and possible blade separation. We are issuing this AD to address the unsafe condition on these products.
48-33-01: 48-33-01 LOCKHEED: Applies to All 49-46, 149-46, 649-79 and 749-79 Models, Through Serial Number 2588. Compliance with new placard restrictions required immediately. Placards to be installed not later than December 1, 1948. Remove existing fuel placards and install three new placards covering fuel system operational procedure. A. The placard to be removed from the 49-46 airplane is located on the Flight Engineer's lower instrument panel and reads: "CAUTION: Do Not Land With More Than 900 Gallons of Fuel in Each Outer Tank". B. The placard to be removed from the 649 airplane is located on the Flight Engineer's uppermost panel and reads: "Fuel Load Restrictions Model 749. Takeoff: Do not Takeoff with Less Than the Following Fuel Loads": The placards to be added read as follows: 1. "This Airplane Must be Fueled, and Fuel Used, in Accordance With the Charts in the Approved Operating Manual." (LAC, Part M302166). 2. "At All Times, Fuel in Tanks 2 and 3 Must Not Exceed Fuel in Tanks 1 and 4, Respectively." (LAC, Part M302163.) 3. "Fuel Transfer from one Tank to Another is not Permitted. When Operating the Fuel System on Crossfeed, the Tanks not Being Used Must be Turned Off." (LAC, Part M302109.) (On Models 49-46, 149, 649, and 749 install placard 1 on Pilot's instrument panel and placards 1, 2, and 3, on Flight Engineer's uppermost instrument panel. Placard 3 has been installed on airplane Serial Number 2577 and subsequent, prior to delivery. (LAC Service Bulletin 49/SB-439, dated March 23, 1948 covers this same subject.)
2005-01-15 R1: The FAA is revising an existing airworthiness directive (AD) for Rolls-Royce plc (RR) RB211 Trent 875, 877, 884, 884B, 892, 892B, and 895 series turbofan engines with certain part number (P/N) low pressure compressor (LPC) fan blades installed. That AD currently requires initial and repetitive ultrasonic inspections of the fan blade dovetail roots and defines a specific terminating action to the repetitive blade inspection requirements. This AD requires the same actions but clarifies the terminating action. We are issuing this AD to prevent multiple LPC fan blade failures due to cracks, which could result in uncontained engine failure and possible damage to the airplane. DATES: This AD becomes effective October 17, 2005. The Director of the Federal Register previously approved the incorporation by reference of certain publications listed in the regulations as of January 28, 2005 (70 FR 2336, January 13, 2005).
2018-15-05: We are adopting a new airworthiness directive (AD) for certain Airbus SAS Model A319-115, -132, and -133 airplanes; and Model A320- 214, -216, -232, -233, -251N, and -271N airplanes. This AD was prompted by reports of safety pins that had been installed on the inflation reservoirs of escape slides/slide rafts during production, but had not been removed. This AD requires inspecting each passenger escape slide/ slide raft to determine whether the safety pin is installed on the slide inflation reservoir, and removing any installed safety pin. We are issuing this AD to address the unsafe condition on these products.
2018-14-09: We are adopting a new airworthiness directive (AD) for certain Airbus Model A318 series airplanes; Model A319 series airplanes; Model A320-211, -212, -214, -216, -231, -232, and -233 airplanes; and Model A321-111, -112, -131, -211, -212, -213, -231, and -232 airplanes. This AD was prompted by reports of early cracking on certain holes of the crossbeam splicing at certain fuselage frames. This AD requires repetitive inspections for cracking of the fastener holes in certain fuselage frames, and depending on airplane configuration, provides an optional terminating action to the repetitive inspections. We are issuing this AD to address the unsafe condition on these products.
89-15-08: 89-15-08 BOEING: Amendment 39-6269. \n\tApplicability: All Model 737 series airplanes through line number 1581, equipped with a second observer's seat, certificated in any category. \n\n\tCompliance: Required as indicated, unless previously accomplished. \n\n\tTo ensure structural integrity of the second observer's seat, accomplish the following: \n\n\tA.\tWithin 30 days after the effective date of this AD, install a placard above the second observer's seat, stating: "NO OCCUPANCY." This placard may be removed once the terminating action of paragraph B., below, has been accomplished. \n\n\tB.\tWithin 6 months after the effective date of this AD, inspect the second observer's seat installation for missing fasteners, in accordance with Boeing Service Letter 737-SL-25-41, dated October 14, 1988, or Boeing Service Letter 737-SL-25-41-A, dated April 20, 1989. If fasteners are found to be missing, repair prior to further flight, in accordance with the service letter. \n\n\tC.\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\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, Seattle Aircraft Certification Office. \n\n\tD.\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 this directive who have not already received the appropriate service documents from the manufacturer may obtain copies upon request to Boeing Commercial Airplanes, P.O. Box 3707, Seattle, Washington 98124. These documents may be examined at the FAA, Transport Airplane Directorate, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or Seattle Aircraft Certification Office, FAA, Northwest Mountain Region, 9010 East Marginal Way South, Seattle, Washington. \n\n\tThis amendment (39-6269, AD 89-15-08) becomes effective on August 24, 1989.
47-10-27: 47-10-27 LOCKHEED: (Was Mandatory Note 30 of AD-763-3.) Applies to All Model 49 Serials Up to and Including 2078. Compliance required prior to July 1, 1947. Install new type fuel tank vent outlets and add extension to fuel dump chutes. (LAC Service Bulletin 49/SB-201 covers this same subject.)
65-14-01: 65-14-01 BEECH: Amdt. 39-96 Part 39 Federal Register June 26, 1965. Applies to Models H35, J35, K35, and 35-33 Series Aircraft Equipped with Ellingsworth Products Co., Inc. Alternator Kit Number 195860 Installed Under STC SA1-377. Compliance required within the next 25 hours' time in service after the effective date of this AD, and thereafter at intervals not to exceed 50 hours' time in service from the last inspection. To prevent further failures of the alternator support bracket, accomplish the following: (a) Remove alternator supporting brackets, P/N's 195814, 195820, 195836, 195838, 195840 and 626131, thoroughly clean and inspect for elongated bolt holes. (b) Inspect brackets not having elongated bolt holes, for cracks using dye penetrant or magnetic particle method or FAA-approved equivalent. (c) Replace brackets having elongated bolt holes or cracks with unused parts of the same part number or FAA-approved equivalent before further flight. (d) Upon request of the operator, and FAA maintenance inspector, subject to prior approval of the Chief, Engineering and Manufacturing Branch, FAA Eastern Region, may adjust the repetitive inspection intervals specified in this AD to permit compliance at an established inspection period of the operator if the request contains substantiating data to justify the increase for such operator. This directive effective June 26, 1965.
2018-12-08: We are superseding Airworthiness Directive (AD) 2017-07-07, which applied to certain Airbus Model A330-200, A330-300, A340-200, and A340-300 series airplanes. AD 2017-07-07 required repetitive inspections of certain fastener holes, and related investigative and corrective actions if necessary. This AD retains the requirements of AD 2017-07-07 and expands the applicability. This AD was prompted by a report of cracking at fastener holes located at frame (FR) 40 on the lower shell panel junction. We are issuing this AD to address the unsafe condition on these products.
2018-13-08: We are superseding Airworthiness Directive (AD) 2016-01-11, which applied to certain Airbus Model A320-211, -212, and -231 airplanes. AD 2016-01-11 required repetitive inspections for cracking of the radius of the front spar vertical stringers and the horizontal floor beam on frame (FR) 36, repetitive inspections for cracking of the fastener holes of the front spar vertical stringers on FR 36, and repair if necessary. This AD adds new thresholds and intervals for the repetitive inspections; requires, for certain airplanes, a potential terminating action modification of the center wing box area; and expands the applicability. This AD was prompted by a report that, during a center fuselage certification full-scale fatigue test, cracks were found on the front spar vertical stringer at a certain frame. This AD was also prompted by a determination that, during further investigations of the frame as part of the widespread fatigue damage (WFD) campaign, certain inspection compliancetimes have to be revised and new inspections and a new potential terminating action modification have to be introduced. We are issuing this AD to address the unsafe condition on these products.
84-23-01: 84-23-01 LOCKHEED: Amendment 39-4955. Applies to Lockheed Models 1329-23A, -23D, - 23E, and -25 series airplanes, serial numbers 5001 through 5162 and 5201 through 5240, certificated in all categories. Compliance is required as indicated, unless already accomplished. To detect cracks which could lead to failure of the empennage and loss of the airplane, accomplish the following: A. Within the next 25 hours flying time or within 20 days after the effective date of this airworthiness directive (AD), inspect for cracks, proper hardware, proper installation of hardware, and loose fasteners in the JE24-1 empennage pivot fitting at the point where the fitting attaches to the flange of the JE22-1 rear beam of the vertical stabilizer in accordance with Lockheed Alert Service Bulletins A329II-55-3 and A329-299, dated October 19, 1984. If loose fasteners or cracks are found, before further flight, repair or replace with new or serviceable parts, as necessary, in accordance with a method acceptable to or approved by the FAA. B. Alternate means of compliance with this AD which provide an equivalent level of safety may be used when approved by the Manager, Atlanta Aircraft Certification Office, FAA, Central Region. This amendment becomes effective November 26, 1984.
69-07-01: 69-07-01 BRITISH AIRCRAFT CORPORATION: Amdt. 39-741. Applies to Model BAC 1-11, 200, and 400 Series Airplanes. Compliance required as indicated, unless already accomplished. To prevent interference between the flap rear pick up fitting and the flap link assembly, accomplish the following: (a) For BAC 1-11, 200, and 400 Series Airplanes with flap links P/N AB09A3697 installed, accomplish the following: (1) Within the next 160 hours' time in service after the effective date of this AD, inspect in accordance with paragraph (3) of this section to determine if a minimum clearance of 0.075 inches is provided between the flap rear pick up fitting and the flap link assembly. (2) If the inspection reveals a clearance of less than 0.075 inches, before further flight (except that the airplane may be flown in accordance with Section 21.197 of the Federal Aviation Regulations to a base where the repair can be performed), incorporate BAC Modification PM 2868, as specifiedin paragraph (3) of this section. (3) Perform the inspection and modification required in paragraphs (1) and (2) of this section, in accordance with British Aircraft Corporation BAC 1-11, Alert Service Bulletin No. 27-A-PM 2245, Issue 6, dated September 16, 1968, or later ARB-approved issue, or an FAA approved equivalent. (b) For BAC 1-11, 200, and 400 Series Airplanes with flap links P/N AB09A3657 or P/N AB09A3697 installed, accomplish the following: (1) Within the next 1000 hours' time in service after the effective date of this AD, inspect in accordance with paragraph (3) of this section, the outer link positions at No. 2 and No. 3 flaps, left and right sides, for interference between the flap link and flap rear pick up fitting fork. (2) If the inspection reveals an interference, before further flight (except that the airplane may be flown in accordance with Section 21.197 of the Federal Aviation Regulations to a base where the repair can be performed), incorporate BAC Modification PM 3691, as specified in paragraph (3) of this section. (3) Perform the inspection and modification required in paragraphs (1) and (2) of this section in accordance with British Aircraft Corporation BAC 1-11, Alert Service Bulletin No. 27-A-PM 2245, Issue 6, dated September 16, 1968, or later ARB-approved issue or an FAA-approved equivalent. This amendment effective March 27, 1969.
65-11-01: 65-11-01 BEECH: Amdt. 39-67 Part 39 Federal Register May 20, 1965. Applies to Model 23 Aircraft Serial Numbers M-1 through M-334 except M-62. Compliance required within 100 hours' time in service after the effective date of this AD, unless already accomplished. To prevent water from entering the static lines through the fuselage static air ports and causing a system malfunction, accomplish the following or an FAA-approved equivalent: (a) Remove the tee fitting from the static line connection just aft of the rear cabin bulkhead. (b) Connect a 52-inch length of 0.25-inch O.D. by 0.040-inch wall polyethylene tubing to the static line running under the floorboard with a 262-P-1/4 union. (c) Place the pack nut and plastic ferrule not used with the union on the other end of the tubing and connect the tee fitting. (d) Remove the clips which originally secured the static lines to the cabin bulkhead and use one to attach the static line to the top of the bulkhead just aft of the cabin bulkhead Station 239.00. (e) Shorten the tubing from each static port to provide gentle curves and to prevent any low places in the line that could trap water between the static ports and the tee. Reconnect the two shortened static port lines to the tee fitting using either the original plastic ferrules and pack nuts or new like parts. (Beech Service Bulletin No. 7 covers this same subject.) This directive effective June 19, 1965.
2018-13-01: We are adopting a new airworthiness directive (AD) for certain Rolls-Royce Corporation (RRC) model 250-C turboshaft engines. This AD was prompted by several reports of engine power loss, one of which resulted in a fatal helicopter accident. This AD requires removal of the power turbine governor (PTG) bearing assembly, part number (P/N) 2544198, and its replacement with a bearing assembly eligible for installation. We are issuing this AD to address the unsafe condition on these products.
89-07-13: 89-07-13 BOEING: Amendment 39-6165. \n\tApplicability: Model 737 series airplanes, certificated in any category. \n\n\tCompliance: Required within the next 18 months after the effective date of this AD, unless previously accomplished. \n\n\tTo prevent smoke in the cockpit and partial loss of electrical power caused by the failures of the Generator Control Unit (GCU) filter modules, accomplish the following: \n\n\tA.\tReplace or modify the GCU filter modules, in Westinghouse GCU P/N 915F212- 5 and GCU P/N 948F458-1, in accordance with Westinghouse Service Bulletin 87-101, dated March 1987, or Westinghouse Service Bulletin 87-102, dated August 1987. \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\tNOTE: The request should be forwarded through an FAA Principal Maintenance Inspector (PMI), who mayadd any comments and then send it to the Manager, Seattle Aircraft Certification Office. \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 modification by this AD. \n\n\tAll persons affected by this directive who have not already received the appropriate service documents from the manufacturer may obtain copies upon request to Westinghouse, Electrical Systems Division, P.O. Box 989, Lima, Ohio 45802. These documents may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or the Seattle Aircraft Certification Office, FAA, 9010 East Marginal Way South, Seattle, Washington. \n\n\tThis amendment (39-6165, 89-07-13) becomes effective on April 28, 1989.
47-42-08: 47-42-08 DOUGLAS: (Was Mandatory Note 5 of AD-781-1.) Applies to DC-6 Airplane Serial Numbers 42854, 42855, 42857, 42858, 42860 to 42865, Inclusive; 42867, 42869 to 42880, Inclusive; 42882 to 42891, Inclusive; 43000, 43001, 43003 to 43009, Inclusive; 43055 and 43056. \n\nTo be accomplished not later than next No. 3 inspection (or not later than next 150 hours for non-air-carrier operations). \n\nCertain cases have been found wherein the 5240452 horizontal stabilizers do not have the rivet pattern specified on Drawings Nos. 5248752 and 5249045. The following specific cases should be inspected and rivets should be added if the numbers are less than the following: \n\nReferring to Drawing 5248752 "Horizontal Stabilizer Rear Spar Assembly", zone 4, directly outboard of Station 63: \n1.\tThere should be at least 12 AD5 rivets top and bottom through the web and cap between the -14 and -12 stiffeners, not counting those through the stiffeners. \n2.\tThere should be at least 4 AD5 rivets through the -68 doubler, spar web and spar cap. \n3.\tThere should be at least 6 AD5 rivets top and bottom between the -12 stiffener and the -68 doubler through web and cap. \n\nWith reference to Drawing No. 5249045 "Horizontal Stabilizer Panel and Spar Structure Assembly" zone 3, section L-L, directly inboard of Station 69.5 both top and bottom, the existing rivet pattern of either 1/8 or 5/32 rivets should be continued inboard with AD5 rivets using the present pattern of 3/4 inch O.C. to within 3 1/16 inches from the end of the spar cap. Existing 1/8-inch rivets are satisfactory. \n\nIt should be noted that the foregoing inspections and riveting can be accomplished without removing the elevators. \n\n(Douglas Service Letter A-214-529.010/RLT, and attached sketches, dated July 14, 1947, covers the same subject.)
65-11-04: 65-11-04 PIPER: Amdt. 39-66 Part 39 Federal Register May 14, 1965. Applies to Models PA-24-250, PA-24-260, PA-24-400, and PA-30 Aircraft Equipped with a Mitchell Altimatic II Autopilot. Compliance required within the next 25 hours' time in service after the effective date of this AD, unless already accomplished. To prevent further jamming of the stabilator control system by the autopilot pitch servo breakaway ball link, accomplish the following: (a) On autopilots with pitch servos, Mitchell P/N 1X312C, having serial numbers listed on page 2 of Mitchell Service Information Bulletin No. A55, dated March 23, 1965, install pitch servo rack, Mitchell P/N 44A75-1, and spacer, Mitchell P/N 43A284 or Piper P/N 25422, in accordance with the accomplishment instructions in that Service Bulletin, or later FAA-approved revision, or an FAA-approved equivalent. Attach spacer using AN510-10R16 screws, AN960-10 washers, and MS20365-1032C nuts, or FAA-approved equivalents. (b) Install a fairlead in the fuselage in accordance with the sketch in Piper Service Bulletin No. 224, dated April 7, 1965, or later FAA-approved revision, or an FAA-approved equivalent. This directive effective May 15, 1965.
49-30-01: 49-30-01 DOUGLAS AND CONVAIR: Applies to All DC-6 and 240 Aircraft Equipped With Curtiss Model C632S-A Propellers. \n\n\tCompliance required as soon as possible but not later than August 15, 1949. \n\n\tBecause of a number of cracks having been discovered in the threaded portion of the hub barrels of the C632S-A propellers, preflight visual inspections must be made in accordance with Curtiss Instructions to all owners dated May 12, 1949. \n\n\tIt is strongly recommended that wherever the necessary equipment is available, magnetic inspections be made in accordance with Curtiss Instructions entitled, "Field Magnetic Inspection of C632S-A Hubs". \n\n\tAny hubs revealing cracks must be retired from service immediately. \n\n\tThe above inspections are to remain in effect as long as these propellers are in service regardless of any rework accomplished. \n\n\tOperational procedures for the Douglas DC-6 during ground run, takeoff and climb, as recommended by the Douglas Co. telegram of May 25, 1949, must also be complied with.
47-16-02: 47-16-02 DOUGLAS: (Was Mandatory Note 17 of AD-762-7.) Applies to C-54 and DC-4 Aircraft. \n\n\tTo be accomplished not later than June 1, 1947. \n\n\tIn case of leakage of the oil dilution solenoid, fuel may flow down the flexible conduit between the solenoid and the firewall junction box and into the junction box, thus creating a fire hazard. To correct this condition, remove the existing flexible conduit and wire between the solenoid and junction box and install new 18-gage wire. Support wire with AN 755-4-4-8 clamps spaced approximately 10-inches apart. \n\n\tThis change is similar to the removal of the flexible conduit for the primer solenoid as covered in item 25 of Douglas Service Bulletin 266 in accordance with Note 47-02-04. \n\t(Part 2A, item 4 of Douglas Service Bulletin DC-4, No. 66, dated June 18, 1947, covers this same subject.)
2005-19-22: The FAA is adopting a new airworthiness directive (AD) for certain Airbus Model A330-322, -341, and -342 airplanes, and Model A340-200 and -300 series airplanes. This AD requires modifying the left and right ram air outlets of the two air conditioning packs. The modification includes replacing the old air outlet assembly with a new air outlet assembly, and modifying the web. This AD results from a report of fatigue cracks that initiated in the duct structure of the ram air outlet, which is adjacent to the hydraulics compartment. We are issuing this AD to prevent fatigue cracks in the duct structure of the ram air outlet, which could lead to hot air damage and consequent loss of function of the hydraulics systems.
65-08-01: 65-08-01 HAWKER SIDDELEY: Amdt. 39-52 Part 39 Federal Register April 2, 1965. Applies to de Havilland Model 114 "Heron" Aircraft. Compliance required as indicated. To prevent further cases of overheating of electric cables in the cockpit and fuselage nose area, accomplish the following: Within the next 25 hours' time in service after the effective date of this AD, unless already accomplished, dismantle, clean, inspect, replace and modify as required, the main ground (earth) assembly in the forward fuselage in accordance with Hawker Siddeley Technical News Sheet Heron (114) No. N.4, Issue 1, dated July 20, 1964. (Hawker Siddeley Aviation, de Havilland Division, Technical News Sheet Heron (114) No. N.4, Issue 1, dated July 20, 1964, covers this same subject.) This directive effective May 3, 1965.
2018-14-01: We are adopting a new airworthiness directive (AD) for certain Piper Aircraft, Inc. (Piper) Models PA-46-600TP (M600) airplanes. This AD requires inserting temporary airspeed limitations into the pilot's operating handbook, installing a temporary placard, inspecting rivets on the cockpit canopy above the left and right cockpit side windows, and installing a repair kit based on the findings of the rivet inspection. This AD was prompted by a report of undersized fasteners installed during manufacturing. We are issuing this AD to address the unsafe condition on these products.
65-06-04: 65-06-04 EUREKA WILLIAMS: Amdt. 39-44 Part 39 Federal Register March 6, 1965. Applies to All Aircraft with Life Preservers or Liferafts Equipped with Eureka Williams Survivor Locator Light Model EW-101-WL-( )-8 with a Yellow Polyethylene Lower Battery End Cap. Compliance required within 30 days after the effective date of this AD unless already accomplished. To prevent further damage to life preservers or liferafts from acid emitted from survivor locator light batteries, accomplish the following: (a) Inspect life preservers and liferafts for acid damage from survivor locator light batteries. Repair or replace damaged life preservers and liferafts before further service. (b) Replace survivor locator light with FAA-approved lights other than Eureka Williams EW-101-WL-( )-8 lights with a yellow polyethylene lower battery end cap before further service. NOTE: Number denoted by empty brackets varies with lead length. All lights with yellow caps were manufactured after December 9, 1964, and are stamped with manufacturer codes 1-65, 2-65, or 12-64. (Eureka Williams Service Bulletin No. ADV SCI 101-1 dated February 19, 1965, covers this subject.) This directive effective March 6, 1965.
47-10-17: 47-10-17 LOCKHEED: (Was Mandatory Note 19 of AD-763-3.) Applies to All Model 49 Serials Up to and Including 2075. Compliance required prior to resumption of cabin supercharger operation. Prior to resumption of cabin supercharger operation, the following Lockheed Service Bulletins must be complied with: 49/SB-107, revised November 22, 1946 - Replacement of Cabin Supercharger Drive Shafts. 49/SB-141, revised August 7, 1946 - Replacement of Cabin Supercharger. 49/SB-156, revised September 17, 1946 - Installation of Supercharger Oil Temperature Indicator. The revision dates given for these three Bulletins are later than those listed in the Supplement to AD-763 (Special) dated September 25, 1946. Aircraft on which the cabin supercharging equipment was rendered operative in accordance with that Supplement should be checked for compliance with these later revisions dates within the next 150 hours of operation.
2003-16-11: This amendment adopts a new airworthiness directive (AD) for the specified MD Helicopters, Inc. (MDHI) model helicopters that requires reducing the life limit of the main rotor drive shaft (drive shaft) and changing the life limit on the component history card or equivalent record. This amendment is prompted by the review of final fatigue test data, which indicates that the life limit of the drive shaft should be reduced by 2000 hours time-in-service (TIS). The actions specified by this AD are intended to prevent failure of the drive shaft, loss of drive of the main rotor system, and subsequent loss of control of the helicopter.