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67-07-05: 67-07-05 GENERAL DYNAMICS: Amdt. 39-353 Part 39 Federal Register February 25, 1967. Applies to General Dynamics Model 240 Airplanes Equipped with Rolls Royce Mk 542-4 Engines and Dowty Rotol (c)R245/4-40-4.5/13 Propellers in Accordance with General Dynamics Supplemental Type Certificate SA1054WE (hereinafter referred to as the CV-600), and General Dynamics Model 340 and 440 Airplanes Equipped with Rolls Royce MK542-4 Engines and Dowty Rotol (c)R245/4-40-4.5/13 or Dowty Rotol (c)R259/4-40-4.5/17 Propellers in Accordance with General Dynamics Supplemental Type Certificate SA1096WE (hereinafter referred to as the CV-640). Compliance required within 50 hours' time in service after the effective date of this AD unless already accomplished. To prevent unwanted withdrawal of the propeller flight fine pitch stops, de-activate the propeller-gust lock interlock system (P/N 2D3120907-1) on CV-600 and CV-640 airplanes in accordance with the following: (a) CV-600 (1) Disconnect the gust lock switches from the propeller control circuit in accordance with the instruction outlined in General Dynamics Alert Service Bulletin 600 (240D) S.B. No. A61-5 or an equivalent approved by the Chief, Aircraft Engineering Division, FAA Western Region. (2) Concurrently, with the modification described in (a) (1), incorporate an FAA approved revision to the Normal Procedures Section of the FAA approved Model 600- (240D) Airplane Flight Manual (General Dynamics Report CS-65-021) which deletes all reference to the gust lock handle control of the propeller flight fine pitch stops. (b) CV-640 (1) Disconnect the gust lock switches from the propeller control circuit in accordance with the instructions outlined in General Dynamics Alert Service Bulletin 640 (340D) S.B. No. A61-4 or an equivalent approved by the Chief, Aircraft Engineering Division, FAA Western Region. (2) Concurrently with the modification described in (b) (1), incorporate an FAA approved revision to the Normal Procedures Section of the FAA approved Model 640- (340D) Airplane Flight Manual (General Dynamics Report CS-65-024) which deletes all reference to the gust lock handle control of the propeller flight fine pitch stops. This directive effective February 25, 1967.
2016-08-15: We are superseding Airworthiness Directive (AD) 2014-17-51 for certain Bombardier, Inc. Model CL-600-2B16 airplanes. AD 2014-17-51 required inspecting the inboard flap fasteners of the hinge-box forward fitting at Wing Station (WS) 76.50 and WS 127.25 to determine the orientation and condition of the fasteners, as applicable, and replacement or repetitive inspections of the fasteners if necessary. AD 2014-17-51 also provided for optional terminating action for the requirements of that AD. This new AD requires accomplishment of the previously optional terminating action. This AD was prompted by a determination that that additional action is necessary. We are issuing this AD to detect and correct incorrectly oriented or fractured fasteners, that could result in premature failure of the fasteners attaching the inboard flap hinge-box forward fitting; failure of the fasteners could lead to the detachment of the flap hinge box and the flap surface, and consequent loss of control ofthe airplane.
47-21-07: 47-21-07 NAVION: (Was Mandatory Note of AD-782-3.) Applies to Serial Numbers NAV-4-10 Through 20, 22 Through 26, 28, 29, 31 Through 49, 51, 52, 55 Through 58, 60, 63, 73, 76, 79, 82 Through 84, 88 Through 95, 99 Through 104, 106, 108, 110, 112 Through 116, 120 Through 122, 124, 125, 130, 133, 141, 151, 153, 158, 163, 171. To be accomplished prior to August 1, 1947. Some airplanes were delivered with a cork or rubber filler strip cemented to the upper surface of the 145-42201-71 carburetor air intake scoop where the scoop fits over the flange of the air mixing chamber. This strip may becomes dislodged and drawn into the air induction system. To prevent this, replace the filler strip with a 3 1/8-inch x 5/8-inch dural strip of 0.093- inch thickness, flush-riveted to the scoop. (NAA Field Service Bulletin No. 15 covers this subject.)
47-25-07: 47-25-07 GLOBE: (Was Mandatory Note 11 of AD-766-5.) Applies to Models GC-1A and GC-1B Aircraft Serial Numbers 1001 to 1119 Inclusive. Compliance required prior to August 1, 1947. If an oil radiator is or has been installed, inspect the forward end of the engine's left oil galley outlet port and remove steel sleeve, Continental P/N 25206, if found to be installed. This is necessary to insure that positive lubrication is being provided the No. 6 cylinder connecting rod bearing. (Globe Customer Service Maintenance Bulletin No. 13 covers this same subject.)
2021-09-03: The FAA is correcting an airworthiness directive (AD) that was \npublished in the Federal Register. That AD applies to certain Airbus \nCanada Limited Partnership Model BD-500-1A10 and BD-500-1A11 airplanes. \nAs published, two references to a Transport Canada Civil Aviation \n(TCCA) AD number specified in the regulatory text are incorrect. This \ndocument corrects those errors. In all other respects, the original \ndocument remains the same.
2003-17-02: This amendment adopts a new airworthiness directive (AD) that applies to all EXTRA Flugzeugbau GmbH (EXTRA) Models EA-300/200, EA- 300L, and EA-300S airplanes. This AD requires you to inspect the fuel selector valve for leakage and the wing for structural damage and correct any damage or leakage. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Germany. The actions specified by this AD are intended to detect and correct fuel leakage in the wings, which could lead to structural damage of the wings and possible reduced structural margins. Reduced structural margins could lead to eventual structural failure.
2016-08-19: We are adopting a new airworthiness directive (AD) for certain Mitsubishi Heavy Industries, Ltd. Models MU-2B-30, MU-2B-35, MU-2B-36, MU-2B-36A, and MU-2B-60 airplanes. This AD results from mandatory continuing airworthiness information (MCAI) issued by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as reports of cracks found in the attach fittings of the main landing gear oleo strut. We are issuing this AD to require actions to address the unsafe condition on these products.
75-11-03: 75-11-03 SEMCO BALLOONS: Amendment 39-2200. Applies to Model T, Model TC-4A and Model Challenger balloons certificated in the Balloon category. Compliance required as indicated. Improper owner/operator assembly of the deflation system has resulted in excessive force being required to operate the deflation cable and fraying of the deflation cable end. The frayed cable end may draw deflation sleeve material into the hole in the locking block and brass rod preventing proper operation of the deflation system. To prevent these occurrences, accomplish the following: (a) Prior to each flight after the effective date of this AD, and until Revision 1, dated April 18, 1975, or later equivalent FAA approved revision to the Balloon Flight Manual is incorporated, accomplish the following check procedures. The pilot may perform these check procedures. 1. Check the portion of the end of the deflation cable which protrudes from the side of the aluminum locking block stamped "out" for fraying or loose strands with the hand or a cloth. If not smooth and free of loose strands, repair or replace before further flight. 2. During inflation, check the routing of the deflation cable. The deflation cable should lead from the basket through the fairlead ring sewn to the inside of the envelope, then in a straight line to the side of the locking block marked "in" and then to the outside of the envelope. The cable should not wrap around the locking block. If cable routing is not correct, reassemble the deflation system properly prior to flight. (b) Within 20 hours time in service after the effective date of this AD, obtain and incorporate Revision 1, dated April 18, 1975, or later equivalent FAA approved revision in the applicable Balloon Flight Manual. NOTE: Revision 1, dated April 18, 1975, to the applicable Balloon Flight Manual may be obtained on request to Semco Balloons, Route 3, Box 514, Griffin, Georgia 30223. The model of the balloonfor which the revision is desired should be specified, also the name and address to which it is desired that the revision be sent. These revisions are also available for examination in Room 274, FAA Building, 3400 Whipple Avenue, East Point, Georgia 30344. This amendment becomes effective May 19, 1975.
73-26-04: 73-26-04 MCDONNELL DOUGLAS: Amdt. 39-1760. Applies to Model DC-10-10, DC-10-30, and DC-10-30F airplanes certificated in all categories. \n\n\tCompliance required within the next 10 hours' of flight for Model DC-10-10 airplanes and 50 hours' of flight for Model DC-10-30 and DC-10-30F airplanes after the effective date of this AD, unless already accomplished. \n\n\tTo determine that the correct nose cowl attach bolts are installed and to assure the proper installation of the bolts, conduct a one-time inspection of the wing mounted engine nose cowl attach bolts and take corrective action in accordance with the following: \n\n\t(a)\tRemove bolts P/N 71658-6 (identified by 71658-6 stamped on the bolt head), if installed, and replace with P/N EWB 22-6-14 bolts, or FAA Western Region approved equivalent bolts (see paragraph (f)), in accordance with the instructions in paragraph (b). \n\n\t(b)\tInstall bolts P/N EWB 22-6-14, identified by HI PSI EWB 22-6 stamped on the bolt head, or FAA WesternRegion approved equivalent. Bolts must protrude through the nut by .030 to .180 inch. Bolts protruding more than .180 inch must have washers P/N MS 20002-6, P/N WPL 22-6, or FAA Western Region approved equivalent washers added between the existing countersunk washer P/N WCL22-6 and the nose cowl attach fitting to meet the .030 to .180 inch protrusion range. The grip length, -14, is not indicated on the bolt head and numbers stamped on the bolt head other than EWB 22-6 should be disregarded. \n\n\t(c)\tInspect all engine flange nutplates and replace any that are cracked or have attach rivets sheared off. As an alternative, accomplish either (1) or (2) below. \n\n\t\t(1)\tRemove the nut from the nutplate by bending the tangs of the retainer and install a new nut from nutplate General Electric (G.E.) P/N 9698M80P01 and rebend the nutplate tangs to secure the nut. \n\n\t\t(2)\tRemove the nutplate by chisel or grinding the rivets. Modify washer P/N MS20002-5 by drilling I.D. to .378/.388 inch. Reidentify the washer as G.E. P/N 9146M8-4P01 and install under nut G.E. P/N 9629-M48P06. \n\n\t(d)\tBack all bolts out until clampup torque is removed and make a running torque check of nut retention. Nuts with less than 10-inch-pounds of locking torque must be replaced, or accomplish either (1) or (2) below. \n\n\t\t(1)\tThoroughly clean the nose cowl and mating engine flange holes, bolts and nut threads with a brush and 1, 1, 1 Trichloroethane (MIL-T-81533), Naptha, or MEK (FED TT-M-261). Allow to dry completely after cleaning. Apply primer MIL-S-22473, Grade T, Form R, to bolt threads and allow to dry completely. Apply locking sealant MIL-S-22473, Grade A or Grade AV, or Loctite 271 on the first three bolt threads. These instructions are per Douglas Process Standard (DPS) 3.51, except that Loctite is an acceptable material not covered by the DPS. \n\n\t\t(2)\tAfter the bolts have been torqued in accordance with paragraph (e), below, clean the exposed threads and nut end per (d) (1), above, and puddle PR1422 class B sealant with accelerator to fill bolt end exposed threads. Cap bolt end with PR1422 sealant and extend the sealant partially over the nut (Reference DPS 2.50). \n\n\t(e)\tLubricate nuts, bolt threads, and washers with MIL-L-25681 per DPS 1.22, or with an FAA Western Region approved equivalent lubricant. If the (D) (1) procedure is used, lubricate bolt shank and washers under the bolt head only (no lubricant on the bolt or nut threads). Torque bolts to 28 to 32 foot pounds. Reference: McDonnell Douglas Maintenance Manual Chapter 71-11-00, page 206. \n\n\t(f)\tBolts P/N R21T5B1-6F14, P/N VS200-3F6-14, P/N EWB TM9-6-14, or P/N BAC B30MT6T14 are, for the purpose of complying with this AD, FAA Western Region approved equivalents for bolt P/N EWB 22-6-14. When bolt P/N BAC B30MT6T14 is installed, the bolt must protrude through the nut by .030 to .130 inch and have washers installed per paragraph (b) if the bolt protrudes more than .130 inch. \n\n\tNOTE: McDonnell Douglaswires C1-SVC-DC10COM-167, C1-SVC-DC10COM-168, C1-SVC-DC10COM-170, C1-SVC-DC10COM-176 cover the procedures described above. \n\n\t(g)\tSpecial flight permits may be issued under FARs 21.197 and 21.199 for the purpose of moving the aircraft to a base to accomplish maintenance to comply with this AD. \n\n\t(h)\tPrior to installation of any quick engine change (QEC) unit, verify accomplishment of this AD. \n\n\tThis amendment is effective December 19, 1973, for all persons except those to whom it was made effective immediately by telegram dated November 7, 1973.
2003-14-18: This amendment adopts a new airworthiness directive (AD) for the specified Sikorsky Aircraft Corporation (Sikorsky) model helicopters that requires removing non-conforming main landing gear brake discs (discs) and replacing them with different part-numbered airworthy discs. It also requires revising the Rotorcraft Flight Manual (RFM) to adjust takeoff and landing distances until the discs are replaced. This amendment is prompted by the manufacture of some discs using inferior materials. The actions specified by this AD are intended to prevent reduced braking performance and subsequent loss of control of the helicopter.
2024-22-02: The FAA is superseding Airworthiness Directive (AD) 2023-21- 02, which applied to certain Airbus SAS Model A330-200 series, A330-200 Freighter series, A330-300 series, A330-800 series, and A330-900 series airplanes. AD 2023-21-02 required revising the existing maintenance or inspection program, as applicable, to incorporate new or more restrictive airworthiness limitations. This AD was prompted by a determination that new or more restrictive airworthiness limitations are necessary. This AD continues to require certain actions in AD 2023- 21-02 and requires revising the existing maintenance or inspection program, as applicable, to incorporate new or more restrictive airworthiness limitations, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
2016-08-09: We are adopting a new airworthiness directive (AD) for certain Pratt & Whitney Division (PW) PW4000-94 inch and PW4000-100 inch model turbofan engines. This AD was prompted by a report of a crack found in the high-pressure compressor (HPC) 10th stage disk. This AD requires performing an ultrasonic inspection (USI) or an eddy current inspection (ECI) of the HPC 10th stage disk. We are issuing this AD to prevent failure of the HPC 10th stage disk, uncontained disk release, damage to the engine, and damage to the airplane.
93-13-11: 93-13-11 TEXTRON LYCOMING: Amendment 39-8624. Docket 91-ANE-46. Applicability: Textron Lycoming LTS 101 series turboshaft engines and LTP 101 series turboprop engines installed on but not limited to Aerospatiale AS 350 and SA366G, Bell 222, and Messerschmitt-Bolkow-Blohm (MBB) BK117 helicopters; or Piaggio P166-DL3 and Airtractor AT302 airplanes. Compliance: Required as indicated, unless accomplished previously. To prevent gas generator turbine rotor disk failure, uncontained engine failure, and possible damage to the aircraft, accomplish the following: (a) Remove from service and replace with a serviceable part, gas generator turbine rotor disks in accordance with the following schedule based on disk cycles since new (CSN) on the effective date of this AD, but not to exceed the total operating hour service life limits established in Textron Lycoming Service Bulletin (SB) No. LT 101-71-00-0002, Revision 12, dated May 31, 1991: (1) For Model LTS 101 series turboshaft engines with gas generator turbine rotor disks identified by Part Numbers (P/N) 4-111-015-04 or 4-111-015-09: (i) Replace disks with 6,800 or more CSN within 100 cycles in service (CIS) or 1 month after the effective date of this AD, whichever occurs first, but not to exceed 7,500 CSN. (ii) Replace disks with 6,500 or more CSN but less than 6,800 CSN within 200 CIS, or 3 months after the effective date of this AD, whichever occurs first. (iii) Replace disks with 6,000 or more CSN but less than 6,500 CSN, within 400 CIS, or 6 months after the effective date of this AD, whichever occurs first. (iv) Replace disks with 5,500 or more CSN but less than 6,000 CSN, within 600 CIS, or 9 months after the effective date of this AD, whichever occurs first. (v) Replace disks with 5,000 or more CSN but less than 5,500 CSN, within 800 CIS, or 12 months after the effective date of this AD, whichever occurs first. (vi) Replace disks with 4,000 or more CSN but less than 5,000 CSN, within 1,000 CIS, or 15 months after the effective date of this AD, whichever occurs first. (vii) Replace disks with less than 4,000 CSN before exceeding 5,000 CSN. (2) For Textron Lycoming Model LTP 101 series turboprop engines with gas generator turbine rotor disks identified by P/N 4-111-015-04 or P/N 4-111-015-09: (i) Replace disks with 5,000 or more CSN within 100 CIS, or 3 months after the effective date of this AD, whichever occurs first, but not to exceed 5,500 CIS. (ii) Replace disks with 4,000 or more CSN but less than 5,000 CSN, within 200 CIS, or 6 months after the effective date of this AD, whichever occurs first. (iii) Replace disks with 3,400 or more CSN but less than 4,000 CSN, within 300 CIS, or 9 months after the effective date of this AD, whichever occurs first. (iv) Replace disks with 3,000 or more CSN but less than 3,400 CSN, within 400 CIS, or 12 months after the effective date of this AD, whichever occurs first. (v) Replace disks with less than 3,000 CSN before exceeding 3,400 CSN. (3) For Textron Lycoming Model LTS 101 series turboshaft engines with gas generator turbine rotor disks identified by P/N 4-111-015-14, replace disks before exceeding 6,300 CSN. (b) An alternative method of compliance or adjustment of the compliance time that provides an acceptable level of safety, may be used if approved by the Manager, Engine Certification Office. The request should be forwarded through an FAA Maintenance Inspector, who may add comments and then send it to the Manager, Engine Certification Office. NOTE: Information concerning the existence of approved alternative methods of compliance with this airworthiness directive, if any, may be obtained from the Engine Certification Office. (c) Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate the aircraft to a location where the requirements of this AD can be accomplished. (d) The total operating hour servicelife limit shall be established in accordance with the following Textron Lycoming service bulletin: Document No. Pages Revision Date LT 101-71-00-0002 1-16 12 May 31, 1991 Total Pages: 16. This incorporation by reference was approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Copies may be obtained from Textron Lycoming, 550 Main Street, Stratford, CT 06497. Copies may be inspected at the FAA, New England Region, Office of the Assistant Chief Counsel, 12 New England Executive Park, Burlington, MA; or at the Office of the Federal Register, 800 North Capitol Street NW., suite 700, Washington, DC. (e) This amendment becomes effective on November 8, 1993.
69-18-05: 69-18-05 CONTINENTAL: Amdt. 39-835. Applies to Models TSIO-520-B (Serial Numbers 145001 through 145618), TSIO-520-D (Serial Numbers 156001 through 156103), and TSIO-520-E (Serial Numbers 165001 through 165493, 165496, and 165497) engines having 300 hours' or more time-in-service, except those engines having turbocharger oil scavenge pumps with P/N 635327 Shaft Gear-Starter, P/N 635328 Body- Scavenge Pump and P/N 635330 Gear-Scavenge Pump, or those engines equipped with P/N 635061-A1 Starter Adaptor and Scavenge Pump Assembly. Compliance: Unless already accomplished, within the next 100 hours' time-in-service after the effective date of this airworthiness directive, on engines having 300 or more hours' time-in-service, or at or before 400 hours' time-in-service on engines that have less than 300 hours' time-in-service at the effective date of this airworthiness directive, accomplish the following: To prevent failure of the turbocharger lubricating oil scavenge pump: Remove P/N 632597 scavenge pump drive gear and P/N MS 35756-3 Woodruff Key and replace with a P/N 636251 scavenge pump drive gear and a new P/N MS35756-3 Woodruff Key. In the P/N 632602 scavenge body assembly drill a .093 inch (3/32) diameter hole to a depth of .31 inch (5/16) in the floor of the gear cavity midway between the center of the gears. Continental Service Bulletin No. M69-8 dated June 11, 1969, refers to the above and provides additional instructions on this modification. This amendment becomes effective September 4, 1969.
2009-01-01: The FAA is adopting a new airworthiness directive (AD) for CFM International, S. A. CFM56-5B series turbofan engines. This AD requires reviewing exhaust gas temperature (EGT) monitoring records to determine EGT deterioration margin, and for airplanes where both engines have greater than 80[deg] centigrade (C) deterioration of EGT margin, borescope-inspecting the high-pressure compressor (HPC) of both engines. This AD also requires removing from service any engine that does not pass the borescope inspection, and if both engines pass, removing and replacing one of the engines with an engine that has 80 [deg]C or less deterioration of EGT margin. This AD also requires continuous monitoring of EGT margin on engines in service, to prevent two engines on an airplane from having greater than 80 [deg]C of deterioration of EGT margin. This AD results from an Airbus A321 airplane powered by CFM56-5B1/P turbofan engines experiencing HPC stalls during climb out after takeoff. We are issuing this AD to prevent HPC stalls, which could prevent continued safe flight or landing.
2016-08-17: We are superseding Airworthiness Directive (AD) 2010-19-51 for Bell Helicopter Textron Canada (Bell) Model 222, 222B, 222U, 230, and 430 helicopters. AD 2010-19-51 required inspecting parts of the main rotor hydraulic servo actuator (servo actuator) for certain conditions and replacing any unairworthy parts before further flight. This new AD requires installing a servo actuator with a new stainless steel piston rod. This AD was prompted by a collective servo actuator malfunction. We are issuing this AD to detect corrosion on a piston rod, which could result in failure of the servo actuator and consequent loss of helicopter control.
73-23-01: 73-23-01 AVCO LYCOMING: Amendment 39-1738 as amended by Amendment 39-1825, 39-1984 and 39-2188 is further amended by Amendment 39-2804. Applies to all Lycoming series engines and all engines overhauled by Lycoming (also known as remanufactured) listed below and in Lycoming Service Bulletin No. 367F and in Supplement No. 1 for Lycoming Service Bulletin No. 367F. O-320 Series L-6798-39A thru L-6815-39A IO-320 Series L-4952-55 O-360 Series L-17389-36A thru L-17408-36A, L-17410-36A thru L-17427-36A, L-17429-36A thru L-17452-36A, L-17454-36A thru L-17479-36A, L-17481-36A thru L-17495-36A, L-17497-36A thru L-17500-36A, L-17503-36A thru L-17505-36A, L-17516-36A thru L-17518-36A RL-523-36A, RL-2030-36A, RL-3933-36A, RL-7173-36A, RL-11169-36A, RL-16937-36A IO & HIO-360 Series L-9409-51A, L-9410-51A, L-9415-51A thru L-9417-51A, L-9419-51A thru L-9427-51A, L-9438-51A thru L-9453-51A, L-9455-51A, L-9457-51A thru L-9498-51A, L-9500-51A thru L-9517-51A, L-9519-51A thru L-9564-51A, L-9566-51A thru L-9616-51A, L-9618-51A, L-9620-51A thru L-9640-51A, L-9642-51A thru L-9651-51A, L-9653-51A thru L-9713-51A, L-9715-51A, L-9716-51A, L-9718-51A thru L-9768-51A, L-9770-51A thru L-9774-51A, L-9776-51A thru L-9826-51A, L-9828-51A thru 9848-51A, L-9850-51A thru L-9930-51A, L-9932-51A thru L-9962-51A, L-9964-51A thru L-9995-51A, L-9997-51A thru L-10090-51A, L-10092-51A thru L-10113-51A, L-10115-51A thru L-10249-51A, L-10257-51A thru L-10261-51A, L-10263-51A thru L-10273-51A, L-10279-51A thru L-10281-51A, L-10284-51A thru L-10290-51A RL-191-51A, RL-591-51A, RL-595-51A, RL-702-51A, RL-776-51A, RL-778-51A, RL-955-51A, RL-993-51A, RL-1267-51A, RL-1272-51A, RL-1435-51A, RL-1481-51A, RL-1515-51A, RL-1642-51A, RL-1769-51A, RL-1845-51A, RL-1847-51A, RL-2143-51A, RL-2227-51A, RL-2249-51A, RL-2464-51A, RL-2476-51A, RL-2508-51A, RL-2562-51A, RL-2629-51A, RL-2672-51A, RL-2923-51A, RL-3048-51A, RL-3113-51A, RL-3195-51A, RL-3235-51A, RL-3318-51A, RL-3344-51A, RL-3392-51A, RL-3427-51A, RL-3464-51A, RL-3540-51A, RL-3573-51A, RL-3738-51A, RL-3832-51A, RL-3868-51A, RL-3974-51A, RL-4787-51A, RL-4960-51A, RL-5082-51A, RL-5085-51A, RL-5652-51A, RL-5685-51A, RL-5751-51A, RL-5824-51A, RL-6331-51A, RL-6345-51A, RL-6350-51A, RL-6417-51A, RL-6469-51A, RL-6623-51A, RL-6652-51A, RL-6693-51A, RL-6724-51A, RL-6744-51A, RL-6950-51A, RL-7043-51A, RL-7201-51A, RL-7357-51A, RL-7422-51A, RL-7475-51A, RL-7806-51A, RL-7852-51A, RL-7886-51A, RL-8000-51A, RL-8354-51A, RL-8872-51A, RL-9611-51A, RL-9812-51A AIO-360 Series L-165-63A thru L-171-63A TIO-360 Series L-112-64A thru L-115-64A LIO-360 Series L-440-67A thru L-480-67A, L-487-67A thru L-512-67A, L-514-67A thru L-537-67A, L-545-67A thru L-591-67A, L-593-67A thru L-632-67A, L-634-67A thru L-648-67A, L-650-67A thru L-655-67A, L-660-67A GO-480-G1D6 Series RL-288-37, RL-482-37 IGSO-480-A1E6 Series RL-829-44, RL-1258-44, RL-1508-44, RL-1509-44, RL-1518-44, RL-1586-44 IGO-540 Series L-320-49 VO-540 Series L-2280-43, L-2281-43 RL-343-43, RL-376-43, RL-456-43, RL-485-43, RL-522-43, RL-564-43, RL-691-43, RL-694-43, RL-846-43, RL-849-43, RL-1125-43, RL-1148-43, RL-1186-43, RL-1333-43, RL-1452-43, RL-1571-43, RL-1700-43, RL-1731-43, RL-1828-43, RL-1900-43, RL-1913-43, RL-1929-43, RL-1931-43, RL-2041-43, RL-2125-43, RL-2142-43, RL-2208-43, RL-2224-43, RL-2245-43, RL-2269-43, RL-2275-43 thru RL-2279-43 O-540-A1C5, -A1D5, -B1A5, -B2B5, -B4B5, -B2C5, -E4A5, -E4B5, -E4C5, G1A5 Series L-15062-40, L-15063-40, L-15108-40, L-15117-40, L-15132-40, L-15133-40, L-15161-40, L-15221-40, L-15222-40, L-15225-40 thru L-15227-40, L-15242-40 thru L-15249-40, L-15297-40, L-15300-40, L-15304-40 thru L-15320-40, L-15322-40 thru L-15367-40, L-15372-40 RL-1040-40, RL-1207-40, RL-3330-40, RL-6768-40, RL-7670-40, RL-9416-40, RL-10859-40, RL-11312-40, RL-11377-40, RL-11420-40, RL-11862-40, RL-13058-40, RL-13637-40, RL-14194-40 IO-540-A1A5, -B1A5, -C1A5, -C4B5, -D4A5, -E1A5, -E1B5, -G1D5, J4A5, -K1A5, -K1B5, -K1C5, -K1E5, -K1E5D Series L-10118-48 thru L-10122-48, L-10124-48 thru L-10127-48, L-10144-48, L-10145-48, L-10209-48, L-10213-48, L-10221-48 thru L-10260-48, L-10263-48 thru L-10267-48, L-10303-48, L-10304-48, L-10306-48 thru L-10308-48, L-10317-48 thru L-10320-48, L-10398-48, L-10459-48, L-10487-48 thru L-10546-48, L-10548-48 thru L-10562-48, L-10564-48 thru L-10569-48, L-10571-48 thru L-10584-48 RL-113-48, RL-622-48, RL-918-48, RL-1170-48, RL-1606-48, RL-1640-48, RL-2015-48, RL-2050-48, RL-2210-48, RL-2271-48, RL-2276-48, RL-3610-48, RL-3614-48, RL-3732-48, RL-4057-48, RL-4103-48, RL-4506-48, RL-5778-48, RL-7116-48 TIO-540-A2B, -A2C, -C1A, TIO-540-J2BD Series L-2412-61 thru L-2414-61, L-2416-61 thru L-2419-61, L-2489-61 thru L-2498-61, L-2501-61 thru L-2503-61, L-2550-61, L-2557-61, L-2562-61, L-2566-61, L-2567-61, L-2572-61 thru L-2583-61, L-2585-61 thru L-2588-61, L-2590-61, L-2591-61, L-2595-61 thru L-2597-61 RL-122-61, RL-226-61, RL-759-61, RL-771-61, RL-1263-61,RL-1268-61, RL-1346-61, RL-1488-61, RL-1679-61, RL-1683-61, RL-2189-61 LIO-540 Series L-102-68, L-105-68, L-109-68, L-113-68 thru L-117-68, L-125-68, L-128-68 thru L-130-68, L-147-68 thru L-152-68, L-154-68, L-155-68 RL-106-68 IGSO-540 Series L-3060-50, L-3061-50, L-3070-50, L-3071-50, L-3074-50, L-3085-50 thru L-3087-50, L-3090-50, L-3093-50, L-3094-50 RL-315-50, RL-518-50, RL-528-50, RL-821-50, RL-1014-50, RL-1100-50, RL-1151-50, RL-1174-50, RL-1216-50, RL-1517-50, RL-1558-50, RL-1591-50, RL-1682-50, RL-1694-50, RL-1700-50, RL-1773-50, RL-1788-50, RL-1821-50, RL-2003-50, RL-2157-50, RL-2187-50, RL-2385-50, RL-2479-50, RL-2543-50, RL-2604-50, RL-2907-50 TIO-541 Series L-866-59 thru L-873-59 TIGO-541 Series L-343-62 thru L-352-62 RL-161-62 IO-720-A, -B and -C Series L-505-54, L-506-54, L-508-54 thru L-529-54, L-532-54 thru L-538-54, L-540-54, L-541-54, L-546-54 thru L-549-54, L-551-54 thru L-554-54 Compliance required within 50 hours in service after the effective date of this AD, unless already accomplished. To prevent piston pin failures resulting from grinding cracks which occurred during manufacture, comply with Lycoming Service Bulletin No. 367F or equivalent procedure approved by Chief, Engineering and Manufacturing Branch, FAA, Eastern 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. 552(a)(1). All persons affected by this directive who have not already received these documents from the manufacturer, may obtain copies upon request to Avco Lycoming Division, Service Department, Williamsport Pennsylvania 17701. These documents may also be examined at the Engineering and Manufacturing Branch, Federal Aviation Administration, Eastern Region, Federal Building, John F. Kennedy International Airport, Jamaica, New York 11430. A historical file on this AD which includes the incorporated material in full is maintained by the FAA at its Eastern Region Headquarters. Amendment 39-1738 was effective November 1, 1973. Amendment 39-1825 was effective May 1, 1974. Amendment 39-1984 was effective October 10, 1974. Amendment 39-2188 was effective April 30, 1975. This amendment 39-2804 is effective January 13, 1977.
2003-14-23: The FAA is adopting a new airworthiness directive (AD) for Rolls-Royce plc (RR) RB211-524G2, -524G2-T, -524G3, -524G3-T, -524H, - 524H-T, -524H2, and -524H2-T series turbofan engines with high pressure compressor (HPC) rotor stage 1 through stage 6 drums, part numbers (P/Ns) FK25502 and FW20195 installed. This AD is prompted by reports of cracks found in loading slots of HPC rotor stage 1 through stage 6 drums. We are issuing this AD to prevent crack initiation and propagation leading to uncontained failure of the HPC rotor stage 1 through stage 6 drum, and damage to the airplane.
2024-22-04: The FAA is superseding Airworthiness Directive (AD) 2021-09- 03, which applied to certain Airbus Canada Limited Partnership Model BD-500-1A10 and BD-500-1A11 airplanes. AD 2021-09-03 required repetitive replacements of the emergency locator transmitter (ELT) antenna and repetitive inspections of the exterior fuselage skin around the ELT antenna attachment area. This AD was prompted by a report that there was an in-service failure of an ELT antenna that occurred before the repetitive replacement interval required by AD 2021-09-03, and that a terminating action was developed. This AD continues to require the actions in AD 2021-09-03 and requires replacement of the ELT antenna with a new ELT antenna, inspection of the exterior fuselage skin around the ELT antenna attachment holes, and repair if necessary; as specified in a Transport Canada AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
66-06-01: 66-06-01\tBOEING: Amdt. 39-197 Part 39 Federal Register February 22, 1966. Applies to Model 707-200 and -300 Series Airplanes Equipped with Pratt & Whitney JT4 Engines.\n \n\tCompliance required as indicated, unless already accomplished. \n\n\tTo prevent loose B-nut on the thrust reverser P(s4) lines, accomplish one of the following or an equivalent approved by the Chief, Aircraft Engineering Division, FAA Western Region.\n\n\t(a)\tWithin the next 1,200 hours' time in service after the effective date of this AD, replace P(s4) tube assemblies (located between the P(s4) engine bleed port and the thrust reverser directional control valve) that incorporate stainless steel 17-4 PH CRES sleeves with tube assemblies that incorporate case-hardened 316 CRES sleeves in accordance with Boeing Service Bulletin 2228, dated August 9, 1965, or later FAA-approved revision; or \n\n\t(b)\tWithin the next 1,200 hours' time in service after the effective date of this AD, replace P(s4) tube assemblies (locatedbetween the P(s4) engine bleed port and the thrust reverse directional control valve) that incorporate stainless steel 17-4 PH CRES sleeves with tube assemblies that incorporate nickel plated carbon steel sleeves or silver plated carbon steel sleeves in accordance with Boeing Service Letter 6-7161-4-8966, dated May 11, 1965, and within the next 3,000 hours' time in service after the effective date of this AD, replace the assemblies that incorporate nickel or silver plated carbon steel sleeves with tube assemblies that incorporate case- hardened 316 CRES sleeves in accordance with Boeing Service Bulletin 2228, dated August 9, 1965, or later FAA-approved revision.\n \n\tThis supersedes AD 65-25-01. \n\n\tThis directive effective February 22, 1966.
67-29-07: 67-29-07 SIKORSKY: Amdt. 39-504 Part 39 Federal Register November 3, 1967. Applies to Type S-55 Helicopters equipped with Wright R-1300 engines (Restricted and Normal Category). Compliance required as indicated. To prevent fatigue failure of the azimuth control rod assembly, P/N S1440-2105-1, accomplish the following: (a) Remove from service all control rod assemblies, P/N S1440-2105-1, with 725 or more hours' time in service on the effective date of this AD within the next 25 hours' time in service. (b) Remove from service all other control rod assemblies P/N S1440-2105-1, before the accumulation of 750 hours' time in service. (c) Within the next 15 hours' time in service after the effective date of this AD, unless already accomplished, and thereafter at intervals not to exceed 50 hours' time in service from the last inspection, inspect the control rod assembly in accordance with paragraph B of Sikorsky Service Bulletin No. 55B40-5, dated October 18, 1967, or later revisions approved by the Chief, Engineering and Manufacturing Branch, Federal Aviation Administration, Eastern Region. Equivalent inspections may be approved by an FAA maintenance inspector. This amendment effective November 3, 1967.
2024-14-05: The FAA is adopting a new airworthiness directive (AD) for certain Bombardier, Inc., Model BD-700-2A12 airplanes. This AD was prompted by reports that the baggage bay discharge push-button annunciator (PBA) switch was making contact but was not fully engaged, and the tabs were not fully locked. This AD requires a verification of the baggage bay discharge PBA functionality and tab installation. The FAA is issuing this AD to address the unsafe condition on these products.
2003-14-11: This amendment adopts a new airworthiness directive (AD), applicable to all Airbus Model A330 and A340 series airplanes, that requires revising the Airworthiness Limitations Section of the Instructions for Continued Airworthiness to incorporate life limits for the servo-controls located on the ailerons and replacement of the servo-controls with new servo-controls when they have reached their operational life limits. This action is necessary to prevent hydraulic leakage and failure of the servo-controls due to cracks in the end caps and along the barrel, which could result in loss of the ailerons and consequent reduced controllability of the airplane. This action is intended to address the identified unsafe condition.
2016-08-16: We are adopting a new airworthiness directive (AD) for all Turbomeca S.A. Arriel 2E turboshaft engines. This AD requires removing the pre-TU 193 adjusted high-pressure/low-pressure pump and metering valve assembly and replacing it with a part that is eligible for installation. This AD also requires replacing the constant delta- pressure (delta-P) diaphragm of the fuel metering valve. This AD was prompted by reports of fuel flow non-conformities found during acceptance tests of Arriel 2E hydro-mechanical metering units (HMUs). We are issuing this AD to prevent failure of the delta-P diaphragm, which could result in an uncommanded in-flight shutdown and damage to the helicopter.
2016-08-05: We are adopting a new airworthiness directive (AD) for certain Bombardier, Inc. Model CL-600-2C10 (Regional Jet Series 700, 701, & 702) airplanes, Model CL-600-2D15 (Regional Jet Series 705) airplanes, Model CL-600-2D24 (Regional Jet Series 900) airplanes, and Model CL- 600-2E25 (Regional Jet Series 1000) airplanes. This AD was prompted by the discovery of a number of incorrectly calibrated angle of attack (AOA) transducers installed in the stall protection system. This AD requires replacement of affected AOA transducers. We are issuing this AD to detect and replace incorrectly calibrated AOA transducers; incorrect calibration of the transducers could result in late activation of the stick pusher.