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2017-12-14: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 757-200 and -200PF series airplanes. This AD was prompted by an evaluation by the design approval holder (DAH) indicating that certain areas of the frame webs are subject to widespread fatigue damage (WFD). This AD requires inspections of the frame webs for any crack of any open coordinating holes, tooling holes, and insulation blanket attachment holes; repair if necessary; and modification of the frame webs at all open hole locations, which would terminate the repetitive inspections. We are issuing this AD to address the unsafe condition on these products.
2017-12-12: We are adopting a new airworthiness directive (AD) for all The Boeing Company Model 757-200, -200PF, and -200CB series airplanes. This AD was prompted by an evaluation by the design approval holder (DAH) indicating that certain fuselage circumferential splice plates are subject to widespread fatigue damage (WFD). This AD requires repetitive low frequency eddy current (LFEC) inspections for cracks of certain circumferential splice plates, and repairs if necessary. We are issuing this AD to address the unsafe condition on these products.
62-21-02: 62-21-02 GENERAL DYNAMICS/CONVAIR: Amdt. 487 Part 507 Federal Register September 25, 1962. Applies to All Models 22 and 22M Series Aircraft. Compliance required within the next 350 hours' time in service after the effective date of this AD, unless already accomplished. With the rudder pedals adjusted to the full forward position and the rudder fully deflected, mechanical interference can make it impossible to apply brakes on the side with the deflected rudder. To correct this interference problem, P/N's 22-41202-1 LH and 22-41202-2 RH located at fuselage Station 192 shall be reworked in accordance with General Dynamics/Convair Service Bulletin A27-53 for the Model 22 and A27-22 for the Model 22M or in accordance with an FAA engineering approved equivalent modification. (General Dynamics/Convair Alert Service Bulletin A27-53 for the Model 22 and A27-22 for the Model 22M cover this same subject.) This directive effective October 25, 1962.
79-21-02: 79-21-02 AVIONS MARCEL DASSAULT (A.M.D.): Amendment 39-3587. Applies to all models of the Fan Jet Falcon series airplanes, Serial Numbers 1 through 376, 378 through 380, 382, and 385 through 388, certificated in all categories. Compliance required as specified in the body of this AD, unless already accomplished. To prevent inadvertent opening of the passenger door due to incomplete manual engagement in closing, worn components, or poor adjustment of the latching mechanism, accomplish the following: (a) For aircraft serial numbers 371 and 386, comply only with paragraph (e) of this AD. All other aircraft must comply with paragraphs (b) through (g) of this AD. (b) Within the next 50 hours in service after the effective date of this AD, unless already accomplished, inspect the passenger door outer control handle and its catch for evidence of wear or inadequate mating of the engaging surfaces in accordance with Avions Marcel Dassault (A.M.D.) Service Bulletin (SB)No. 604 dated May 17, 1978, with Revision 1 dated June 8, 1978, or equivalent approved by the Chief, Aircraft Certification Staff, FAA, AEU-100, Europe, Africa, and Middle East Region. (c) If during any inspection required by this AD, inadequate mating of the door outer control handle and its catch is found, before further flight, except that the airplane may be flown in accordance with FAR 21.197 and 21.199 to a base where repairs can be made, modify the door outer control handle assembly and its catch and install new steel lock bolts in accordance with AMD - SB No. 615, dated May 17, 1978, or an equivalent approved by Chief, Aircraft Certification Staff, FAA, Europe, Africa, and Middle East Region, or if wear is localized on the door outer handle, replace it with a door outer handle of the same part number in accordance with the Falcon 20 service manuals referenced in paragraph "J" of AMD-SB No. 615 or equivalent approved by Chief, Aircraft Certification Staff, AEU-100, FAA, Europe, Africa, and Middle East Region. (d) If during any inspection required by this AD, inadequate mating of the door outer control handle and its catch is found or if a new door outer control handle has been installed in accordance with paragraph (c) of this AD, inspect the door outer control handle and its catch in accordance with the method specified in paragraph (b) of this AD at intervals not to exceed 500 hours time in service from the last inspection until the door outer control handle assembly and its catch are modified and steel lock bolts are installed in accordance with AMD - SB No. 615, dated May 17, 1978, or equivalent approved by the Chief, Aircraft Certification Staff, AEU-100, FAA, Europe, Africa, and Middle East Region. (e) Within the next 500 hours time in service after the effective date of this AD, install passenger door closing instruction placards and symbols in accordance with the Accomplishment Instructions, paragraph 2.k. of AMD - SB No. 616, dated May 17, 1978 or FAA-approved equivalent. (f) Within the next 1000 hours time in service after the effective date of this AD, install a microswitch and associated electrical circuitry to the passenger door handle mechanism and accomplish associated modifications, in accordance with AMD - SB 616, dated May 17, 1978, or equivalent approved by the Chief, Aircraft Certification Staff, AEU-100, Federal Aviation Administration, Europe, Africa, and Middle East Region, c/o American Embassy, Brussels, Belgium. (g) Upon accomplishment of each modification specified in this AD, incorporate appropriate revisions to the Aircraft Parts, Maintenance and Repair Manuals, and Wiring Diagrams related to AMD service bulletins referenced in this AD. This amendment becomes effective November 12, 1979.
2017-12-15: We are adopting a new airworthiness directive (AD) for all Bombardier, Inc., Model CL-600-2E25 (Regional Jet Series 1000) airplanes. This AD requires revising the airplane flight manual (AFM) to provide procedures to stabilize the airplane's airspeed and attitude. This AD was prompted by two in-service incidents of loss of all air data information in the flight deck. We are issuing this AD to address the unsafe condition on these products.
2017-12-07: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 737-800, -900, and -900ER series airplanes. This AD was prompted by reports of in-flight failure of the left temperature control valve and control cabin trim air modulating valve. This AD requires replacing the left temperature control valve and control cabin trim air modulating valve. We are issuing this AD to address the unsafe condition on these products.
2024-16-01: The FAA is superseding Airworthiness Directive (AD) 2000-18- 09, which applied to certain Bell Helicopter Textron, Inc. (now Bell Textron Inc.), Model 412, 412CF, and 412EP helicopters. AD 2000-18-09 required repetitively inspecting the upper left-hand cap angle (cap angle) and adjacent structure for a crack and, depending on the results, replacing any cracked cap angle and repairing any crack in the adjacent structure. This AD was prompted by a report of a fatigue crack in a tail boom attachment cap angle. This AD retains the requirements of AD 2000-18-09, expands the applicability by adding models and an additional part-numbered cap angle, reduces the inspection intervals, and requires using updated procedures. This AD also updates the reporting requirement. The FAA is issuing this AD to address the unsafe condition on these products.
86-24-06: 86-24-06 BRITISH AEROSPACE: Amendment 39-5472. Applies to Models HP-137 MK 1 and Jetstream 200 Series (all serial numbers), and Model Jetstream 3101 (S/N 601-633, 635-646 and 648-654 inclusive) airplanes certificated in any category. Compliance: Required within 600 hours time-in-service (TIS) after the effective date of this AD, unless already accomplished. To prevent unacceptable aileron control vibration and aileron jamming, accomplish the following: (a) Inspect the special stud BAe P/N 13705E29 and nut BAe P/N A103-JT for tightness, visible thread length and punch marks, in accordance with Section 2. "Accomplishment Instructions" in BAe Mandatory S/B No. 27-JM-5257, dated June 6, 1986. (1) If the special stud and nut are secure, and the special stud end protrudes 1-1/2 to 2 threads beyond the nut and all three punch marks are visible, no further action is necessary. (2) If the special stud and nut are loose, or the special stud end does not protrude 1-1/2 to 2 threads beyond the nut, or all three punch marks are not visible, prior to further flight, remove aileron quadrant in accordance with Section 2. "Accomplishment Instructions," Paragraph B. "Removal/Installation" in BAe Mandatory S/B No. 27-JM-5257, dated June 6, 1986, and check the security of the nut P/N A103-JT securing the special stud P/N 13705E29 to the quadrant, and determine that peening of the stud is in accordance with the above BAe Service Bulletin. (i) If security and locking are satisfactory, prior to further flight, reinstall aileron control quadrant using steps (13) to (20) inclusive of the above Service Bulletin, and no further action is required. (ii) If the securing nut P/N A103-JT or special stud P/N 13705E29 is loose or the peening of the stud is not in accordance with the above BAe Service Bulletin, prior to further flight, remove and replace nut BAe P/N A103-JT with new nut BAe P/N RMTE 9868-6, install new stud BAe P/N 13705E91 and add splitpin SP90-C7 to lock the nut on, according to the instructions in BAe Mandatory S/B 27-JM-5257, dated June 6, 1986. (b) Airplanes may be flown in accordance with FAR 21.197 to a location where this AD may be accomplished. (c) An equivalent means of compliance with this AD may be used if approved by the Manager, Aircraft Certification Staff, AEU-100, Europe, Africa and Middle East Office, FAA, c/o American Embassy, B-1000 Brussels, Belgium. All persons affected by this directive may obtain copies of the document referred to herein upon request to British Aerospace PLC., Manager, Product Support Civil Aircraft Division, Prestwick Airport, Ayrshire, KA9 2RW, Scotland; or British Aerospace, Inc., Librarian, Box 17414, Dulles International Airport, Washington, D.C. 20041; or FAA, Office of the Regional Counsel, Room 1558, 601 East 12th Street, Kansas City, Missouri 64106. This amendment becomes effective on January 2, 1987.
2024-16-06: The FAA is superseding Airworthiness Directive (AD) 2023-15- 07, which applied to all Air Tractor, Inc. (Air Tractor) Model AT-802 and AT-802A airplanes with Wipaire, Inc. Supplemental Type Certificate (STC) No. SA01795CH installed. AD 2023-15-07 required repetitively inspecting the left and right forward horizontal stabilizer spars for cracks, replacing any forward horizontal stabilizer spar found cracked, and reporting inspection results to the FAA. This AD requires repetitively inspecting the left and right, forward and rear, horizontal stabilizer spars for cracks at shorter intervals than those required by AD 2023-15-07, replacing any horizontal stabilizer spar found cracked or damaged, installing bathtub fittings, and reporting inspection results to the FAA. This AD was prompted by additional reports of cracks in the horizontal stabilizer spars and the need to incorporate a new finlet attach design on the horizontal stabilizer spars to reduce the cracking. The FAA is issuing this AD to address the unsafe condition on these products.
64-06-02: 64-06-02\tBOEING: Amdt 707 Part 507 Federal Register March 17, 1964. Applies to All Model 720 Series Aircraft with Pratt and Whitney JT3C-7 and JT3C-12 Turbojet Engines Installed. \n\n\tCompliance required as indicated. \n\n\tAs the result of the failure of the second and third stage compressor rotor disc spacer assemblies, P/N's 359411 and 359412, respectively, and resultant serious engine damage together with possible aircraft damage, accomplish the following: \n\n\t(a)\tFor spacer assemblies previously inspected by the procedure described in (c), reinspect in accordance with (c) as follows: \n\n\t\t(1)\tInspect spacer assemblies having 200 or more hours' time in service since the last inspection within 50 hours' time in service after the effective date of this AD, and within each 250 hours' time in service thereafter. \n\n\t\t(2)\tInspect spacer assemblies having less than 200 hours' time in service since last inspection prior to the accumulation of 250 hours' time in service and within each 250 hours' time in service thereafter. \n\n\t(b)\tFor spacer assemblies not previously inspected by the procedure described in (c), inspect in accordance with (c) as follows: \n\n\t\t(1)\tInspect spacer assemblies with 950 or more hours' time in service since last overhaul within the next 50 hours' time in service after the effective date of this AD, and every 250 hours' time in service thereafter. \n\n\t\t(2)\tInspect spacer assemblies with less than 950 hours' time in service since last overhaul prior to the accumulation of 1,000 hours' time in service since last overhaul and every 250 hours' time in service from the last inspection. \n\n\t(c)\tIncorporate an inspection hole and plug in the compressor case and second stage vane and shroud assembly and in the compressor case and third stage vane and shroud assembly in accordance with Pratt and Whitney Aircraft letter dated November 22, 1963, and its two enclosed sketches. Using an American Systoscope Markers Incorporated Model B-175-AS-15 or FAA approved equivalent viewing instrument inserted through these holes, inspect the second and third stage compressor rotor disc spacer assemblies for possible cracks in all the visible areas of each spacer. Give particular attention to the front and rear seal edges. If any cracks are found, remove the engine before further flight and disassemble for confirmation of the cracks. Replace any cracked spacer assemblies. \n\n\t(d)\tWhen P/N's 420145 and 429175 second and third stage compressor rotor disc spacer assemblies, respectively, are incorporated, the inspections prescribed by this AD are no longer required. \n\n\t(e)\tUpon request of the operator, an 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. \n\n\t(Pratt and Whitney Aircraft telegraphic message dated November 20, 1963, to Eastern Air Lines and Pratt and Whitney Aircraft letter dated November 22, 1963, and enclosed two sketches to all operators of JT3C-7 turbojet engines cover the same subject.) \n\n\tThis supersedes AD 63-26-01. \n\n\tThis directive effective March 17, 1964.
2017-12-09: We are adopting a new airworthiness directive (AD) for certain Empresa Brasileira de Aeronautica S.A. (Embraer) Model EMB-135 airplanes and Model EMB-145, -145ER, -145MR, -145LR, -145MP, -145EP, and -145XR airplanes. This AD was prompted by a report of chafing found between the fuel pump electrical harness and the fuel pump tubing during scheduled maintenance. This AD requires a detailed inspection for chafing on the electrical harness of each electrical fuel pump in the fuel tanks, replacement of the affected electrical fuel pump with a new or serviceable pump if necessary, and installation of clamps on the fuel pump electrical harnesses. We are issuing this AD to address the unsafe condition on these products.
2017-12-08: We are superseding Airworthiness Directive (AD) 2011-24-06 for all BAE Systems (Operations) Limited Model BAe 146-100A, -200A, and - 300A airplanes; and Model Avro 146-RJ70A, 146-RJ85A, and 146-RJ100A airplanes. AD 2011-24-06 required revising the maintenance program to incorporate life limits for certain items, adding new and more restrictive inspections to detect fatigue cracking in certain structures, and adding fuel system critical design configuration control limitations (CDCCLs) to prevent ignition sources in the fuel tanks. AD 2011-24-06 also required modifying the main fittings of the main landing gear (MLG) and revising the maintenance program to incorporate new life limits on MLG up-locks and door up-locks and other MLG components. This new AD requires revising the maintenance or inspection program, as applicable, to incorporate new or revised structural inspection requirements. This AD was prompted by a determination that new or revised structural inspection requirements are necessary. We are issuing this AD to address the unsafe condition on these products.
2024-13-05: The FAA is adopting a new airworthiness directive (AD) for all The Boeing Company Model 787-8, 787-9, and 787-10 airplanes. This AD was prompted by a report of heat damage on multiple engine inlets around the engine anti-ice (EAI) duct within the inlet aft compartment. This AD requires doing a records check and updating the operator's existing minimum equipment list (MEL), inspecting the left and right engine inlet cowl assembly for signs of heat damage around the EAI duct, installing or replacing the EAI duct seals, repairing any damage, and replacing the engine inlet if necessary. This AD also prohibits the installation of engine inlets under certain conditions. The FAA is issuing this AD to address the unsafe condition on these products.
91-13-10 R1: 91-13-10 R1 BOEING: Amendment 39-8158. Docket No. 91-NM-241-AD. Revises AD 91-13-10, Amendment 39- 7041. \n\n\tApplicability: Model 747 series airplanes equipped with Pratt and Whitney PW4000 engines; and Model 767 series airplanes equipped with Pratt and Whitney PW4000, General Electric CF6-80C2-B2F, or General Electric CF6- 80C2-B6F series engines; certificated in any category. \n\n\tCompliance: Required as indicated, unless previously accomplished. \n\tTo prevent overspeed or uncommanded shutdown of an engine, accomplish the following:\n\n\t(a)\tFor Model 747 series airplanes equipped with Pratt and Whitney PW4000 engines, and Model 767 series airplanes equipped with Pratt and Whitney PW4000 or General Electric CF6-80C2-B6F engines: Within 3 days after May 22, 1989 (the effective date of Amendment 39-6210), add the following to the Limitations Section of the FAA- approved Airplane Flight Manual (AFM). This may be accomplished by inserting a copy of this AD in the AFM. \n\n\t"Prior to each departure, with all engines running, refer to the EICAS status page and determine the dispatch capability of the aircraft." \n\n\t(b)\tWithin the next 24 months after August 12, 1991 (the effective date of this Amendment 39-7041), replace the EICAS computers in accordance with the appropriate service bulletin listed below. After replacement of the EICAS computers in accordance with the specified service bulletins, the AFM limitation required by paragraph (a) of this AD may be removed. \n\n\t\t(1)\tFor Model 747 series airplanes listed in Boeing Service Bulletin 747-31-2151, dated March 29, 1990. \n\n\t\t(2)\tFor Model 767 series airplanes equipped with Pratt and Whitney PW4000 engines listed in Boeing Service Bulletin 767-31-0033, Revision 1, dated September 27, 1990. \n\n\t\t(3)\tFor Model 767 series airplanes equipped with General Electric CF6-80C2-B6F engines listed in Boeing Service Bulletin 767-31-0038, dated April 12, 1990. \n\n\t(c)\tFor Model 767 series airplanes equipped with General Electric CF6-80C2-B2F engines: \n\n\t\t(1)\tWithin the next 3 days after the effective date of this AD, add the following to the Limitations Section of the FAA-approved Airplane Flight Manual (AFM). This may be accomplished by inserting a copy of this AD in the AFM. \n\n\t"Prior to each departure, with all engines running, refer to the EICAS status page and determine the dispatch capability of the aircraft." \n\n\t\t(2)\tWithin the next 24 months after the effective date of this AD, replace the EICAS computers in accordance with Boeing Service Bulletin 767-31-0038, dated April 12, 1990. After incorporation of the EICAS computers, the AFM limitation required by paragraph (c)(1) may be removed. \n\n\t(d)\tFor airplanes not subject to paragraph (b) or (c) of this AD, within the next 30 days after the effective date of this AD, remove the AFM limitation required by paragraph (a) of this AD. \n\n\t(e)\tAn alternative method of compliance or adjustment of the compliance time, which provides anacceptable level of safety, may be used when approved by the Manager, Seattle Aircraft Certification Office (ACO), FAA, Transport Airplane Directorate. \n\n\tNOTE: The request should be forwarded through an FAA Principal Maintenance Inspector, who may concur or comment and then send it to the Manager, Seattle ACO. \n\n\t(f)\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\t(g)\tThe replacement requirements shall be done in accordance with the following Boeing Service Bulletins, which incorporate the following list of affected pages: \n\nService Bulletin\tRevision Level\t\tDate\t\t\tPages \n\n747-31-2151\nOriginal\t\nMarch 29, 1990\n1 - 10 \n767-31-0033\n1\nOriginal\t\nSeptember 27, 1990 May 31, 1990\n1, 2, 4, 5 \n3, 6, 7, 8, \n9, 10 \n767-31-0038\nOriginal\t\nApril 12, 1990\n1 - 8 \n\n\n\n\n\t\nThis incorporation by reference was approved by the Director of the Federal Register inaccordance with 5 U.S.C. 552(a) and 1 CFR Part 51. Copies may be obtained from Boeing Commercial Airplane Group, P.O. Box 3707, Seattle, Washington 98124. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, Washington; or at the Office of the Federal Register, 1100 L Street NW., Room 8401, Washington, D.C.\n\n\t(h)\tAirworthiness Directive 91-13-10 superseded AD 89-10-06, Amendment 39-6210. \n\t(i)\tThis Airworthiness Directive 91-13-10 R1 revises AD 91-13-10, Amendment 39-7041.\n \t(j)\tThis amendment (39-8158, AD 91-13-10 R1) becomes effective on February 26, 1992.
2024-14-03: The FAA is adopting a new airworthiness directive (AD) for various airplanes modified with a certain configuration of the Garmin GFC 500 Autopilot System installed per Supplemental Type Certificate (STC) No. SA01866WI. This AD was prompted by a report of an un- commanded automatic pitch trim runaway when the autopilot was first engaged. This AD requires updating the applicable Garmin GFC 500 Autopilot System software for your airplane and prohibits installing earlier versions of that software. The FAA is issuing this AD to address the unsafe condition on these products.
2017-12-04: We are superseding airworthiness directive (AD) 2016-20-04 for Airbus Helicopters Model SA341G and SA342J helicopters. AD 2016-20-04 prohibited autorotation training flights until the landing gear rear crosstube (crosstube) was inspected. This new AD adds additional part- numbered crosstubes to the applicability and revises the hardness criteria for the inspection. This AD is prompted by a determination that an additional part-numbered crosstube may have the same unsafe condition. The actions of this AD are intended to detect and prevent an unsafe condition on these helicopters.
2017-11-04: We are adopting a new airworthiness directive (AD) for all The Boeing Company Model 767-200, -300, and -400ER series airplanes. This AD was prompted by an evaluation by the design approval holder (DAH) indicating that the fuselage skin lap splices are subject to widespread fatigue damage (WFD). This AD requires repetitive inspections to detect any crack in the fuselage skin at the skin lap splices, and corrective actions if necessary. We are issuing this AD to address the unsafe condition on these products.
91-05-09: 91-05-09 PILATUS BRITTEN-NORMAN (PBN): Amendment 39-6892; Docket No. 90-CE-33-AD. Applicability: Model BN-2T Turbine Islander airplanes (all serial numbers), certificated in any category, that do not have PBN Modification Number NB/M/1429 incorporated. Compliance: Required within the next 200 hours time-in-service after the effective date of this AD, unless already accomplished. To prevent the loss of engine power on both engines simultaneously, accomplish the following: (a) Modify the airplane engine ignition system as described in PBN Service Bulletin BN-2/SB 193, dated April 11, 1990. (b) Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a location where the requirements of this AD can be accomplished. (c) An alternate method of compliance or adjustment of the compliance time that provides an equivalent level of safety may be approved by the Manager, Brussels Aircraft Certification Staff, FAA, Europe, Africa, and Middle East Office, c/o American Embassy, B-1000 Brussels, Belgium. The request should be forwarded through an appropriate FAA Maintenance Inspector, who may add comments and then send it to the Manager, Brussels Aircraft Certification Staff. (d) All persons affected by this directive may obtain copies of the document referred to herein upon request to Pilatus Britten-Norman Limited, Bembridge Airport, Isle of Wight, PO36 5PR, England; or may examine this document at the FAA, Central Region, Office of the Assistant Chief Counsel, Room 1558, 601 E. 12th Street, Kansas City, Missouri 64106. This amendment (39-6892, AD 91-05-09) becomes effective on March 25, 1991.
77-22-05: 77-22-05 BELLANCA (CHAMPION): Amendment 39-3069. Applies to models 7ECA S/Nos. 1 thru 722, 725, 723-70 thru 1238-78 7GC S/Nos. All 7GCA S/Nos. All 7GCAA S/Nos. 1 thru 198, 200 thru 204, 276, 205-70 thru 355- 78 7GCB S/Nos. All 7GCBC S/Nos. 1 thru 201, 205, 207, 202-70 thru 1024-78 7HC S/Nos. All 7KCAB S/Nos. 1 thru 208, 210 thru 226, 270, 271, 209-70 thru 617-77 Certificated in all categories. Compliance is required as indicated unless already accomplished. Part I Airspeed Restriction/Front Strut Replacement a. Effective immediately, unless already accomplished, attach the following operating limitation placard near the airspeed indicator in full view of the pilot: "DO NOT EXCEED 153 MPH CAS MAXIMUM OPERATING SPEED" The letters on this placard must be at least 1/8 inch in height and on suitable material which can be expected to remain affixed in position and resist deterioration. This placard may be installed by the pilot.b. Within three (3) months after the effective date of this airworthiness directive, accomplish either: 1. Remove red radial marking on airspeed indicator at 162 MPH (141 KTS). Remark indicator with red radial line at 153 MPH (133 KTS). Change Operations Limitations Card as follows: Replace Airspeed Limitations "GLIDE or DIVE-----162 MPH CAS" with "MAXIMUM OPERATING SPEED----153 MPH CAS". Bellanca Service Kit 256 may be used to accomplish this. (Bellanca Service Letter C-127 pertains to this subject.) After marking indicator, the placard required per paragraph (a) above may be removed, or 2. Remove wing front lift struts Bellanca P/N 5-144 and install replacement wing front lift struts Bellanca P/N 5-392 (Bellanca Service Letter C-127 and Service Kit 257 pertain to this subject). After the struts are replaced, the placard per paragraph (a) above may be removed and the airspeed markings and Operations Limitations Card per paragraph (b.1) above may be returned to theiroriginal 162 MPH CAS markings. NOTE: The Bellanca P/N 5-392 strut may be identified by a square tube fitting at the wing end. Part II Acrobatic Maneuvers Placard/Accelerometer Markings/Operating Limitations Card Change. Applies to All Bellanca (Champion) Acrobatic Models As Indicated. (Bellanca Service Letter C-128 pertains to this subject.) a. Effective immediately, flight operations shall be conducted in accordance with the limitations specified below. b. Within three (3) months after the effective date of this airworthiness directive unless already accomplished, replace the acrobatic maneuvers placard and remark the accelerometer if applicable as indicated below. 1. For Model 7ECA - S/Nos. 1 thru 722, 725, 723-70 thru 1238-78 7GCAA - S/Nos. 1 thru 198, 200 thru 204, 276, 205-70 thru 355-78 Install Bellanca placard (Bellanca Service Kit 258) or facsimile on suitable material which can be expected to remain affixed in position and resist deterioration as shown below. LANDPLANE APPROVED FOR ONLY FOLLOWING ACROBATIC MANEUVERS MANEUVER ENTRY SPEED IAS MPH KNOTS CHANDELLE, LAZY EIGHT 120 104 BARREL OR SLOW ROLL 120 104 IMMELMANN 145 126 LOOP OR CLOVER LEAF 140 122 SPLITS 80 70 SNAP ROLL 85 74 HAMMERHEAD TURN 140 122 CUBAN EIGHT 145 126 SPIN SLOW DECELERATION DO NOT EXCEED +5.0 OR -2.0 G LOAD FACTOR. DO NOT EXCEED 135 MPH IAS DURING NEGATIVE G CONDITIONS. DO NOT PERFORM ACROBATICS IN TURBULENT AIR. CAUTION: NEGATIVE G FLIGHT WILL CAUSE LOSS OF OIL AND OIL PRESSURE. TO RECOVER FROM SPIN USE FULL OPPOSITE RUDDER AND NEUTRALIZE ELEVATOR. 2. For Model 7GCBC - S/NOS. 1 THRU 201, 205, 207, 202-70 thru 1024- 78 7GCB - Aircraft approved in acrobatic category only Install Bellanca placard (Bellanca Service Kit 259) or facsimile on suitable material which can be expected to remain affixed in position and resist deterioration as shown below. LANDPLANE APPROVED FOR ONLY FOLLOWING ACROBATIC MANEUVERS MANEUVER ENTRY SPEED IAS MPH KNOTS CHANDELLE, LAZY EIGHT 120 104 BARREL OR SLOW ROLL 120 104 IMMELMANN 145 126 LOOP OR CLOVER LEAF 140 122 SPLITS 80 70 SNAP ROLL 85 74 HAMMERHEAD TURN 140 122 CUBAN EIGHT 145 126 SPIN SLOW DECELERATION DO NOT EXCEED +5.0 OR -2.0 G LOAD FACTOR. DO NOT EXCEED 135 MPH IAS DURING NEGATIVE G CONDITION. DO NOT PERFORM ACROBATICS IN TURBULENT AIR. CAUTION: NEGATIVE G FLIGHT WILL CAUSE LOSS OF OIL AND OIL PRESSURE. USE OF FLAPS DURING ACROBATICS PROHIBITED. TO RECOVER FROM SPIN USE FULL OPPOSITE RUDDER AND NEUTRALIZE ELEVATOR. 3. For Model 7KCAB - S/Nos. 1 thru 208, 210 thru 226, 270, 271, 209-70 thru 404-73, 405-74 thru 458-74, 460-74 thru 508-75 Install Bellanca placard (Bellanca Service Kit 260) or facsimile on suitable material which can be expected to remain affixed in position and resist deterioration as shown below: LANDPLANE APPROVED FOR ONLY FOLLOWING ACROBATIC MANEUVERS MANEUVER ENTRY SPEED IAS MPH KNOTS CHANDELLE, LAZY EIGHT 120 104 BARREL OR SLOW ROLL 120 104 IMMELMANN 145 126 LOOP OR CLOVER LEAF 140 122 SPLITS 80 70 SNAP ROLL 85 74 HAMMERHEAD TURN 140 122 CUBAN EIGHT 145 126 SPIN SLOW DECELERATION LEVEL INVERTED FLIGHT 120 104 135 MPH (117 KTS) IAS MAX DO NOT EXCEED +5.0 or -2.0 G LOAD FACTOR. DO NOT EXCEED 135 MPH IAS DURING NEGATIVE G CONDITION. DO NOT PERFORM ACROBATICS IN TURBULENT AIR. INVERTED FLIGHT LIMITED TO 2 MIN - MONITOR OIL PRESS WHILE INVERTED TO INSURE MINIMUM OF 60 PSI. TO RECOVER FROM SPIN USE FULL OPPOSITE RUDDER AND NEUTRALIZE ELEVATOR. 4. For Model 7KCAB - S/Nos. 459-74, 509-75 thru 617-77 Install Bellanca placard (Bellanca Service Kit 261) or facsimile on suitable material which can be expected to remain affixed in position and resist deterioration as shown below LANDPLANE APPROVED FOR ONLY FOLLOWING ACROBATIC MANEUVERS MANEUVER ENTRY SPEED IAS MPH KNOTS CHANDELLE, LAZY EIGHT 120 104 BARREL OR SLOW ROLL 120 104 IMMELMANN 145 126 LOOP OR CLOVER LEAF 140 122 SPLITS 80 70 SNAP ROLL 85 74 HAMMERHEAD TURN 140 122 CUBAN EIGHT 145 126 SPIN SLOW DECELERATION LEVEL INVERTED FLIGHT 120 104 135 MPH (117 KTS) IAS MAX DO NOT EXCEED +5.0 OR -2.0 G FACTOR. DO NOT EXCEED 135 MPH IAS DURING NEGATIVE G CONDITION. DO NOT PERFORM ACROBATICS IN TURBULENT AIR. 2 MIN OF INVERTED FUEL NORMALLY AVAILABLE. MOMENTARY OIL PRESSURE INTERRUPTIONS ARE NORMAL. TO RECOVER FROM SPIN USE FULL OPPOSITE RUDDER AND NEUTRALIZE ELEVATOR. 5. If aircraft is equipped with accelerometer, verify that the red radial marks are installed at +5.0 G and -2.0 G. If markings are incorrect, remark indicator. c. Within the next 30 days after the effective date of this airworthiness directive, unless already accomplished, attach the following placard near the airspeed indicator in full view of the pilot. The placard will be a facsimile of the following on suitable material which can be expected to remain affixed in position and resist deterioration as shown below: "DO NOT EXCEED 135 MPH IAS DURING NEGATIVE G CONDITION" This placard is available as a part of the Service Kits described in parts (1) through (4) above. d. For Model 7KCAB, within three (3) months after the effective date of this airworthiness directive, verify that the Operating Limitations Card presents the following information. If markings are incorrect, remark Operating Limitations Card. Replacement Operating Limitations Cards are available in Bellanca Service Kit 262. Maneuvering Flight Limit Load Factors Positive ------------------ 5.0 g Negative ---------------- 2.0 g DO NOT EXCEED 135 MPH IAS DURING NEGATIVE G CONDITION. This amendment becomes effective November 7, 1977.
91-26-07: 91-26-07 BRITISH AEROSPACE: Amendment 39-8118. Docket No. 91-NM-245-AD. Applicability: British Aerospace Model BAe 146-100A, -200A, and -300A series airplanes equipped with G.E.C. Plessey generator control units (GCU); as listed in British Aerospace Alert Service Bulletin 24-A97, dated November 12, 1991; certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent inaccurate flight instrument readings, accomplish the following: (a) Within 10 days after the effective date of this AD, replace G.E.C. Plessey GCU's having part number 700-1-22490-410 or 700-1-22490-510, with G.E.C. Plessey GCU's having part number 700-1-22490-400 or 700-1-22490-500, in accordance with British Aerospace Alert Service Bulletin 24-A97, dated November 12, 1991. (b) An alternative method of compliance or adjustment of the compliance time, which provides an acceptable level of safety, may be used when approved by the Manager, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate. The request shall be forwarded through an FAA Principal Maintenance Inspector, who may concur or comment and then send it to the Manager, Standardization Branch, ANM-113. NOTE: Information concerning the existence of approved alternative methods of compliance with this airworthiness directive, if any, may be obtained from the Standardization Branch, ANM-113. (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) The replacement shall be done in accordance with British Aerospace Alert Service Bulletin 24-A97, dated November 12, 1991. 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 British Aerospace, PLC, Librarian for Service Bulletins, P.O. Box 17414, Dulles InternationalAirport, Washington, DC. 20041-0414. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, Washington; or at the Office of the Federal Register, 1100 L Street NW., Room 8401, Washington, DC. (e) This amendment becomes effective June 16, 1992.
2017-12-02: We are adopting a new airworthiness directive (AD) for certain General Electric Company (GE) GEnx-1B64, -1B64/P1, -1B64/P2, -1B67, - 1B67/P1, -1B67/P2, -1B70, -1B70/P1, -1B70/P2, -1B70/75/P1, -1B70/75/P2, -1B70C/P1, -1B70C/P2, -1B74/75/P1, -1B74/75/P2, -1B76A/P2 turbofan engines. This AD was prompted by a fracture of the fuel manifold which led to an in-flight shutdown of the engine. This AD requires replacement of the outer left side signal fuel manifold with a part eligible for installation. We are issuing this AD to address the unsafe condition on these products.
2023-15-07: The FAA is adopting a new airworthiness directive (AD) for all Air Tractor, Inc. (Air Tractor) Model AT-802 and AT-802A airplanes that have Wipaire Supplemental Type Certificate (STC) No. SA01795CH installed. This AD was prompted by reports of cracks found in the forward horizontal stabilizer spar where the vertical finlets tie to the horizontal tail forward spar. This AD requires repetitively inspecting both the left and right forward horizontal stabilizer spars for cracks and replacing any forward horizontal stabilizer spar found cracked. This AD also requires reporting inspection results to the FAA. The FAA is issuing this AD to address the unsafe condition on these products.
90-04-08: 90-04-08 BOEING: Amendment 39-6507. Docket No. 89-NM-190-AD. \n\n\tApplicability: Model 727 series airplanes, line numbers 048 through 453, certificated in any category. \n\n\tCompliance: Required within the next 600 landings after the effective date of this AD, unless previously accomplished. \n\n\tTo detect cracking and prevent rapid depressurization, accomplish the following: \n\n\tA.\tConduct an eddy current inspection in accordance with the 727 Non-Destructive Testing Manual (NDT), D6-48875, Part 6, 53-30-27, Figure 8; or an ultrasonic inspection in accordance with the 727 NDT Manual, D6-48875, Part 4, 53-30-27, Figure 2; to determine the configuration of the fuselage skins located between stringer (S) 14 and S-19. If the skin has the .020 inch bonded doubler added to the .040 inch skin, conduct the inspection described in paragraph B., below; otherwise, no further action is required. \n\n\tB.\tIf the fuselage skins are determined to have the .040 inch skin with the .020 inch bonded doubler, conduct a one-time eddy current inspection for cracks of the over-lapped skin in accordance with the 727 NDT Manual D6-48875, Part 6, 53-30-27, Figure 9 or 10, near the bottom row of fasteners in the lower skin of the longitudinal lap splices located at S-14L from body station (BS) 440 to BS 720, and at S-14R from BS 440 to BS 540. Prior to further flight, repair any cracks found, in accordance with a method approved by the Manager, Seattle Aircraft Certification Office, FAA, Northwest Mountain Region. \n\n\tC.\tWithin 10 days after completion of the inspections required by paragraph B., above, submit a report of positive findings of cracks on airplanes with the bonded doubler to the Manager, Seattle Aircraft Certification Office, ANM-100S, FAA, Northwest Mountain Region, 17900 Pacific Highway South, C-68966, Seattle, Washington 98168. The report must include the line number of the airplane inspected, the number of cycles, and the size and locations of the cracks. \n\n\tD.An 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\tE.\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, Northwest Mountain Region, Transport Airplane Directorate, 17900 Pacific Highway South, Seattle, Washington, or at the Seattle Aircraft Certification Office, 9010 East Marginal Way South, Seattle, Washington.\n \n\tThis amendment (39-6507, AD 90-04-08) becomes effective on March 19, 1990.
90-21-06: 90-21-06 DORNIER: Amendment 39-6755. Docket No. 90-CE-24-AD. Applicability: Models Do28D and Do28D-1 (all serial numbers) airplanes, certificated in any category. Compliance: Required as indicated in the body of the AD, unless already accomplished. To prevent engine mount failure, accomplish the following: (a) Within the next 50 hours time-in-service (TIS) after the effective date of this AD visually inspect the riveted connections between the L-section and formed sheet of the right-hand and left-hand engine mounts. (1) If no loose or damaged rivets are found, reinspect the connections at intervals of 100 hours TIS thereafter. (2) If any loose or damaged rivets are found, prior to further flight remove and replace any damaged rivets, and replace all universal and Huck blind rivets having a diameter of 3.2mm (.126 in) with steel blind rivets having a diameter of 4.0mm in accordance with the instructions contained in Dornier Service Bulletin No. 1131-1613, dated August 2, 1989. Reinspect the connections at intervals of 100 hours TIS thereafter. (b) Airplanes may be flown in accordance with FAR 21.197 to a location were this AD may be accomplished. (c) An alternate method of compliance or adjustment of the initial or repetitive compliance times, which provides an equivalent level of safety, may be approved by the Manager, Aircraft Certification Staff, Europe, Africa, and Middle East Office, FAA, c/o American Embassy, 1000 Brussels, Belgium. NOTE: The request should be forwarded through an FAA Maintenance Inspector, who may add comments and then send it to the Manager, Brussels Aircraft Certification Staff. All persons affected by this directive may obtain copies of the document referred to herein upon request to Dornier Luftfahrt GmbH, P.O. Box D-8031 Wessling, Federal Republic of Germany; or may examine this document at the FAA, Central Region, Office of the Assistant Chief Counsel, Room 1558, 601 E. 12th Street, Kansas City, Missouri 64106. This amendment (39-6755, AD 90-21-06) becomes effective on November 13, 1990.
78-21-02: 78-21-02 BELL: Amendment 39-3317. Applies to all Bell Helicopter Models 204B, 205A, 205A-1, and 212 modified by Chadwick, Inc., STC's SH149WE or SH17NW. Prior to further flight involving external-load operations over congested or densely populated areas, replace Chadwick, Inc., load cell link assembly P/N 47-40200-19 with parts approved by the Chief, Engineering and Manufacturing Branch, Federal Aviation Administration, Northwest Region. This amendment is effective October 12, 1978, and was effective earlier for all recipients of the airmail letter dated September 18, 1978, which contained this amendment.