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2015-08-05: We are superseding Airworthiness Directive (AD) 2013-26-05 for all Dassault Aviation Model FAN JET FALCON, FAN JET FALCON SERIES C, D, E, F, and G airplanes; Model MYSTERE-FALCON 200 airplanes; and Model MYSTERE-FALCON 20-C5, 20-D5, 20-E5, and 20-F5 airplanes. AD 2013-26-05 required repetitive weighing of fire extinguisher bottles having a certain part number, and eventual replacement of those bottles to terminate the repetitive weighing. This new AD continues to require repetitive weighing of fire extinguisher bottles having a certain part number, and eventual replacement of those bottles to terminate the repetitive weighing. This AD was prompted by our determination that certain text in the method of compliance language specified in AD 2013- 26-05 incorrectly refers to Airbus, instead of ``Dassault Aviation.'' We are issuing this AD to detect and correct a dormant failure in the fire suppression system, which could result in the inability to put out a fire in an engine, auxiliary power unit (APU), or rear compartment.
2000-09-08: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 747-100, -200, 747SP, and 747SR series airplanes, that requires one-time detailed visual and eddy current inspections to detect cracking of the nose cowl mounting flange; rework of the nose cowl mounting flange; eddy current inspection to detect cracking of the reworked nose cowl mounting flange; and corrective action, if necessary. This amendment is prompted by reports of the nose cowl separating from the engine and departing the airplane following severe engine vibration. The actions specified by this AD are intended to prevent separation of the nose cowl from the engine, which could cause collateral damage to the airplane, and, possibly, reduced controllability of the airplane.
57-19-02: 57-19-02 SIKORSKY: Applies to all Model S-58 Helicopters. Compliance required as soon as possible but not later than October 30, 1957. To avoid the possibility of slippage in S-58 hydromechanical clutch due to adverse tolerance conditions replace S1635-91046-1 rollers with S1635-91065 rollers. The new rollers are three-thousandths (0.003) larger in diameter and may be identified by their dulite finish. (Sikorsky telegraphic message SST-1-281 dated September 12, 1957, covers the same subject.)
86-07-12: 86-07-12 PRATT & WHITNEY: Amendment 39-5267. Applies to PW JT9D-7R4G2 engines. Compliance is required as indicated unless already accomplished. To prevent possible engine support clevis failure, accomplish the following: (a) Remove P/N 5006482-01 engine support clevis on PW JT9D-7R4G2 at or before 3,000 cycles in accordance with PW SB JT9D-7R4-72-119, Revision 3, dated November 5, 1985, or FAA approved equivalent. (b) Replace any engine support clevis with greater than 3,000 cycles prior to next flight. NOTES: (1) For the purpose of this AD, the number of flight cycles equals the number of flights that involve an engine operating sequence consisting of engine starting, takeoff operation, landing and engine shutdown. (2) The hourly life limit is not affected by this AD. Aircraft may be ferried in accordance with the provisions of FAR 21.197 and 21.199 to a base where the AD can be accomplished. SB JT9D-7R4-72-119, Revision 3, dated November 5,1985, identified and described in this document, is 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 this document from the manufacturer may obtain copies upon request to Pratt & Whitney, Commercial Products Division, 400 Main Street, East Hartford, Connecticut 06108. These documents also may be examined at the Office of the Regional Counsel, New England Region, Federal Aviation Administration, 12 New England Executive Park, Burlington, Massachusetts 01803. This amendment becomes effective on April 11, 1986.
2015-05-52: We are publishing a new airworthiness directive (AD) for Agusta S.p.A. (Agusta) Model A109, A109A, A109A II, A109C, A109K2, A109E, A119, A109S, AW119 MKII, and AW109SP helicopters, which was sent previously to all known U.S. owners and operators of these helicopters. This AD requires inspecting certain tail rotor (T/R) pitch control links (pitch links) for freedom of movement, corrosion, excessive friction of the spherical bearings, and cracks. This AD is prompted by a report of an in-flight failure of a pitch link on an Agusta Model AW119 MKII helicopter. These actions are intended to prevent loss of T/ R pitch control and subsequent loss of control of the helicopter.
2015-07-03: We are adopting a new airworthiness directive (AD) for certain Cessna Aircraft Company (Cessna) Model 402C and 414A airplanes. This AD requires repetitively inspecting the engine mount beams for cracks and contacting Cessna for FAA-approved corrective action if cracks are found. This AD also requires sending an inspection report to the FAA and to Cessna. This AD was prompted by reports of cracks found across the engine mount beams. We are issuing this AD to correct the unsafe condition on these products.
97-26-13: This amendment adopts a new airworthiness directive (AD) that applies to all Empresa Brasileira de Aeronautica S.A. (EMBRAER) Models EMB-110P1 and EMB-110P2 airplanes. This AD requires amending the Limitations Section of the airplane flight manual (AFM) to prohibit the positioning of the power levers below the flight idle stop while the airplane is in flight. This AFM amendment will include a statement of consequences if the limitation is not followed. This AD results from numerous incidents and five documented accidents involving airplanes equipped with turboprop engines where the propeller beta was improperly utilized during flight. The actions specified by this AD are intended to prevent increased propeller drag beyond the certificated limits caused by the power levers being positioned below the flight idle stop while the airplane is in flight, which could result in loss of airplane control or engine overspeed with consequent loss of engine power.
86-07-08: 86-07-08 DEHAVILLAND: Amendment 39-5279. Applies to all Model DHC-7 series airplanes, certificated in any category. Compliance is required as indicated, unless already accomplished. To ensure observation of wet starts, detection of heat-damaged wing upper surface structure behind the engine, and protection against wet starts of the engine resulting in external combustion of fuel, accomplish the following: A. Except as provided in paragraph C., below, within the next 25 hours time-in- service after the effective date of this AD, insert a copy of this AD following Page 2-2-4B of the DHC-7 Airplane Flight Manual (AFM). After every aborted engine start in conjunction with either flight or other operations, follow AFM limitations and applicable procedures for starter cranking cycles, proper fuel draining, and dry motoring/clearing of the engine. An appropriately stationed observer must witness the subsequent starting attempt to determine whether external flames from the exhaust stacks and any burning of residual fuel on wing surfaces occurs. 1. If no external flame or external flame lasting for less than 5 seconds is observed, the airplane may be dispatched. 2. If external flame lasting 5 seconds or more is observed, a visual inspection of the affected wing area must be performed before further flight, in accordance with the Accomplishment Instructions, Paragraph 1, of DeHavilland Service Bulletin No. 7-57-25, Revision B, dated November 22, 1985. a. If distortion or buckling of the skin is evident during the visual inspection, perform an internal conductivity survey of the affected area, and repair, as necessary, before further flight, in accordance with the Accomplishment Instructions of DeHavilland Service Bulletin No. 7-57-25, Revision B, dated November 22, 1985. Details of any damage discovered and data obtained from conductivity surveys must be transmitted to DeHavilland Aircraft of Canada, Ltd., immediately for processing.b. If blistering or charring of the paint due to engine exhaust heat is evident during the visual inspection, before further flight, perform an external conductivity survey and, as necessary, an internal conductivity survey, and make repairs, as necessary, in accordance with the Accomplishment Instructions of DeHavilland Service Bulletin No. 7-57-25, Revision B, dated November 22, 1985. Details of any damage discovered and data obtained from conductivity surveys must be transmitted to DeHavilland Aircraft of Canada, Ltd., immediately for processing. c. If no visible damage (i.e., no blistering or charring of paint or buckling of the wing skin) is apparent, within 100 flight hours perform an external conductivity survey and, as necessary, an internal conductivity survey, and make repairs, as necessary, of the affected area in accordance with the Accomplishment Instructions of DeHavilland Service Bulletin No. 7-57-25, Revision B, dated November 22, 1985. Details of any damage discovered and data obtained from conductivity surveys must be transmitted to DeHavilland Aircraft of Canada, Ltd., immediately for processing. B. Except as provided in paragraph C., below, within the next 25 hours time-in- service after the effective date of this AD, visually inspect the upper wing skin behind each engine nacelle in accordance with the Accomplishment Instructions, Paragraph 1, of DeHavilland Service Bulletin No. 7-57-25, Revision B, dated November 22, 1985. 1. If distortion or buckling of the skin is evident during the visual inspection, repairs must be effected before further flight. In order to determine the extent of repairs, perform an internal conductivity survey of the affected area in accordance with the Accomplishment Instructions of DeHavilland Service Bulletin No. 7-57-25, Revision B, dated November 22, 1985. Details of any damage discovered and data obtained from conductivity surveys must be transmitted to DeHavilland Aircraft of Canada, Ltd., immediately for processing. 2. If blistering or charring of the paint due to engine exhaust heat is evident during the visual inspection, before further flight, perform an external conductivity survey and, as necessary, an internal conductivity survey, and make repair, as necessary, of the affected area in accordance with the Accomplishment Instructions of DeHavilland Service Bulletin No. 7-57-25, Revision B, dated November 22, 1985. Details of any damage discovered and data obtained from conductivity surveys must be transmitted to DeHavilland Aircraft of Canada, Ltd., immediately for processing. C. Accomplishment of DeHavilland Modification No. 7/2414 - "Wing - Upper Skin Structure - Special Inspection and Installation of Heat Shields," described in DeHavilland Service Bulletin No. 7-57-25 constitutes terminating action for the visual inspection and conductivity surveys required by paragraphs A. and B., above. When that modification has been accomplished, this AD may then be removed from the Airplane Flight Manual. 1. Prior to installation of Modification No. 7/2414, the following must be accomplished: a. Perform an external conductivity survey and, as necessary, an internal conductivity survey, and make repairs, as necessary before further flight, of the upper wing skin behind each engine nacelle, in accordance with the Accomplishment Instructions of DeHavilland Service Bulletin No. 7-57-25, Revision B, dated November 22, 1985. Details of any damage discovered and data obtained from conductivity surveys must be transmitted to DeHavilland Aircraft of Canada, Ltd., immediately for processing. b. For airplanes, serial numbers 1 through 27, Modification Nos. 7/2377 and 7/2378 - "Fuel Tank Access Panel Replacement," described in DeHavilland Service Bulletin No. 7-57-17 (originally issued October 12, 1983), must be accomplished. D. Alternate means of compliance which provide an acceptable level of safety may be used when approved bythe Manager, New York Aircraft Certification Office, FAA, New England Region. E. Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base for the accomplishment of inspections and/or modifications required by this AD. All persons affected by this directive who have not already received the appropriate service documents from the manufacturer may obtain copies upon request to DeHavilland Aircraft of Canada, Ltd., Downsview, Ontario M3K 1Y5, Canada. These documents may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or FAA, New England Region, New York Aircraft Certification Office, 181 South Franklin Avenue, Room 202, Valley Stream, New York. This amendment becomes effective April 22, 1986.
2015-07-01: We are adopting a new airworthiness directive (AD) for certain Rolls-Royce plc (RR) RB211-524 turbofan engines with certain part number (P/N) low-pressure turbine (LPT) stage 3 turbine blades installed. This AD requires implementation of a life limit for certain P/N LPT stage 3 turbine blades and replacement of affected blades that reach or exceed the life limit. This AD was prompted by reports of LPT stage 3 turbine blade failures, release of blades, and subsequent in- flight shutdowns. We are issuing this AD to prevent failure of LPT stage 3 turbine blades and subsequent release of blade debris, which could lead to failure of one or more engines, loss of thrust control, and damage to the airplane.
2000-09-06: This amendment adopts a new airworthiness directive (AD) that applies to certain Maule Aerospace Technology, Inc. (Maule) M-4, M-5, M-6, M-7, MX-7, and MXT-7 series airplanes and Models MT-7-235 and M-8-235 airplanes. This AD requires you to inspect all NicopressTM sleeve terminal ends for correct size compression, with adjustment or replacement, as necessary. This AD results from a report of the rudder cable slipping out of the NicopressTM sleeve while one of the affected airplanes was landing. The actions specified by this AD are intended to detect and correct improper crimping of the NicopressTM sleeve, which could cause a control cable to slip from the sleeve. This could result in loss of rudder, elevator, aileron, or flap control.
90-15-08: 90-15-08 HOFFMANN AIRCRAFT GmbH: Amendment 39-6655. Docket No. 90-CE-08. Applicability: Model H-36 DIMONA (all serial numbers) gliders, certificated in any category. Compliance: Required within the next 50 hours time-in-service after the effective date of this AD, unless already accomplished. To insure the continued structural integrity of the wing attachments, accomplish the following: (a) Visually inspect and measure the distance between the main bolt heads, the bulkhead bushings, and the back face of the main bulkhead in the wing spar tunnel in accordance with the instructions and criteria specified in Hoffmann Aircraft GmbH Service Bulletin Number 24, dated May 4, 1988. If any discrepancies are noted, prior to further flight repair the discrepancies in accordance with the instructions contained in the above Service Bulletin. (b) An alternate method of compliance or adjustment of the compliance time which provides an equivalent level of safety, maybe approved by the Manager, Brussels Aircraft Certification Office, FAA, c/o American Embassy, B-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 Office. All persons affected by this directive may obtain copies of the documents referred to herein upon request to Hoffmann Aircraft GmbH, Richard-Neutra-Gasse 5, 1210 Wein, Austria; or may examine these documents at the FAA, Central Region, Office of the Assistant Chief Counsel, Room 1558, 601 E. 12th Street, Kansas City, Missouri 64106. This amendment (39-6655, AD 90-15-08) becomes effective on August 20, 1990.
83-07-04 R1: 83-07-04 R1 SHORT BROTHERS LTD.: Amendment 39-4604 as amended by Amendment 39-4665. Applies to Model SC-7 Series 3 (all serial numbers) airplanes certificated in any category. Compliance: Required as indicated, unless already accomplished. To preclude failure of the primary flight control systems, accomplish the following: a) Within the next 100 hours time-in-service after the effective date of this AD and at intervals not to exceed 500 hours time-in-service thereafter: 1) Visually inspect the control system linkage connections listed in paragraph a)3) of this AD in accordance with Short Brothers Service Bulletin (SB) No. 27-66, dated November 18, 1977. Each connection typically consists of a clevis (control rod) and rod- end bearing joined by a pin as shown on Figure 1 of SB No. 27-66. Each end of the pin must be secured by a retaining plate bonded to the clevis and one end must have a locking rivet through the pin and clevis. 2) If a retaining plate or locking rivet are found to be loose or detached from the clevis, prior to further flight, repair the connection in accordance with instructions in SB No. 27-66.z. 3) The locations of the control system linkage connections to be inspected are as follows (refer to page 3 of SB No. 27-66): i) One location in each wing on the aileron control rod. ii) Twenty-four locations in control rods along the upper fuselage between Stations 96 and 410. b) The intervals between the repetitive inspections required by this AD may be adjusted up to 10 percent of the specified interval to allow accomplishing these inspections concurrent with other scheduled maintenance of the airplanes. c) The repetitive inspections required by this AD may be discontinued upon incorporation of Modification 1674 as described in Revision 1 to Short Brothers SB No. 27-66, dated March 31, 1978, and SB No. 27-68, dated January 19, 1979. d) Aircraft may be flown in accordance with Federal Aviation Regulation 21.197 to a location where this AD can be accomplished. e) An equivalent method of compliance with this AD, if used, must be approved by the Manager, Aircraft Certification Staff, AEU-100, Europe, Africa or Middle East Office, FAA, c/o American Embassy, 1000 Brussels, Belgium. Amendment 39-4604 became effective on April 11, 1983. This Amendment 39-4665 becomes effective June 23, 1983.
93-08-18: 93-08-18 PRATT & WHITNEY: Amendment 39-8566. Docket 92-ANE-16. Supersedes AD 91-05-20, Amendment 39-6919. Applicability: Pratt & Whitney Model PW4152, PW4156, and PW4158 model turbofan engines equipped with electronic engine control (EEC) Part Numbers 50D436, 50D791, 50D824, 51D037, and 51D053, installed on but not limited to Airbus A310 and Airbus A300 series aircraft. Compliance: Required within 30 days after the effective date of this airworthiness directive (AD), unless accomplished previously. To prevent a high pressure compressor failure that can be caused by excessive blade tip to airseal interference, which can result in total loss of engine thrust, accomplish the following: (a) The ENGINE ANTI ICE must be switched to "ON" prior to takeoff and must be in the "ON" position for any flight operation below 15,000 feet. (b) Install placards in the cockpit of Airbus A310-300 and A300-600 aircraft, just above the Captain and the First Officer Primary Flight Displays, indicating the following: "BEFORE TAKE OFF, SET ENG. ANTI ICE ON. KEEP ENG. ANTI ICE ON FOR ANY OPERATION BELOW 15,000 FT." NOTE: Further information on the placards may be obtained from Airbus Industrie Service Information Letter 72-001, Revision 1, dated September 18, 1990. (c) 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 appropriate FAA Principal 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. (d) 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. (e) This amendment becomes effective on July 6, 1993.
2015-06-09: We are adopting a new airworthiness directive (AD) for Pacific Aerospace Limited (PAL) Model 750XL 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 PAL Model 750XL airplanes manufactured with only one attitude indicator. A second attitude indicator is required for flights under instrument flight rules. We are issuing this AD to require actions to address the unsafe condition on these products.
2000-08-18: This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-9 series airplanes, and Model MD-88 and MD-90-30 airplanes, that requires replacement of the lanyard assembly pins of the evacuation slides with solid corrosion-resistant pins. This amendment is prompted by a report that, due to stress corrosion on the lanyard pins, the arms of the lanyard assembly of the evacuation slide were found to be frozen. The actions specified by this AD are intended to prevent the improper deployment of the evacuation slide due to stress corrosion, which could delay or impede evacuation of passengers during an emergency.
2000-09-05: This amendment adopts a new airworthiness directive (AD) that is applicable to certain Allison Engine Company AE 3007 series turbofan engines. This AD would require removal of certain cone shafts from service before exceeding new cyclic life limits and replacement with serviceable parts. This amendment is prompted by additional testing and low cycle fatigue (LCF) life analysis that substantiate lower cyclic lives than originally determined. The actions specified by this AD are intended to prevent LCF failure of cone shafts, which could result in an uncontained engine failure and damage to the aircraft.
81-24-04: 81-24-04 SWEARINGEN: Amendment 39-4261. Applies to the following airplane models approved for flight into known icing: Model SA226-T (Serial Numbers T-205E; T-215E, T-201 through T-275 and T-277 through T-291); Model SA226-T(B) (Serial Numbers T-276; T-303E; and T-292 through T-419); Model SA226-AT (Serial Numbers AT-003E, AT-038E, AT-062E, AT-064E, and AT-001 through AT-419); and Model SA-226-TC (Serial Numbers TC-211E, TC-211EE, TC-211EEE, TC-211EEEE, TC-202E, TC-208E, TC-215E, TC-222E, TC-222EE, TC-227E, TC-228E, TC-229E, TC-234E, TC-237E, TC-238E, TC-239E, TC-255E, TC-246E, and TC-201 through TC-419) airplanes. (Airworthiness Directive Docket No. 81-ASW-37.) Compliance is required within the next 10 hours' time in service after the effective date of this AD unless already accomplished. To prevent operation in icing conditions wherein ice shed from the propeller spinner could be ingested into the engine inlet, resulting in flameout and subsequent total loss of engine power, accomplish the following: (a) Strike from the Type of Operations paragraph in the Operation Limitations Section of the FAA approved Airplane Flight Manual the words, "and icing conditions." (b) Install a placard, minimum 1/4 inch lettering, on the instrument panel in plain view of the pilot stating, "Flight into known icing conditions prohibited." NOTE: Installation of an auto ignition system in accordance with Fairchild Swearingen Corporation Service Bulletin SB 74-002 dated October 22, 1981, removes the limitations in (a) and (b) above. (c) Any alternate equivalent method of compliance with this airworthiness directive must be approved by the Chief, Engineering and Manufacturing Branch, Flight Standards Division, Southwest Region, Federal Aviation Administration. 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 personsaffected by this directive who have not already received these documents from the manufacturer may obtain copies upon request to Director of Product Support, Fairchild Swearingen Corporation, P.O. Box 32486, San Antonio, Texas 78284. These documents may also be examined at the Office of the Regional Counsel, Southwest Region, Federal Aviation Administration, 4400 Blue Mound Road, Fort Worth, Texas, and at the FAA Headquarters, 800 Independence Avenue, SW., Washington, D.C. A historical file on this AD, which includes the incorporated material in full, is maintained by the FAA at their headquarters in Washington, D.C., and at the Southwest Regional Office in Fort Worth, Texas. This amendment becomes effective November 19, 1981.
2015-06-04: We are superseding Airworthiness Directive (AD) 2011-13-07 for all Dassault Aviation Model FALCON 7X airplanes. AD 2011-13-07 requires revising the airplane flight manual (AFM) to include a procedure to power off a radio-altimeter or revert to the correct radio-altimeter output. This new AD requires revising the AFM to include a simpler procedure to revert to the correct radio-altimeter output. This AD was prompted by an analysis which showed that AFM procedures could be simplified. We are issuing this AD to ensure that the flightcrew has procedures in the event of a radio-altimeter lock-up, which inhibits the display of warnings along with certain abnormal conditions, during the switch into landing mode during altitude cruise. If not corrected, this could result in the flightcrew being unaware of possible system failures that require immediate action by the flightcrew, leading to possible loss of control of the airplane.
2000-07-51: This document publishes in the Federal Register an amendment adopting airworthiness directive (AD) 2000-07-51 that was sent previously to all known U.S. owners and operators of McDonnell Douglas Model 717-200 series airplanes by individual notices. This AD requires coiling and stowing of electrical wires between the glareshield control panel and the Integrated Standby Instrument System; and revising the abnormal procedures of the Procedures section of the Airplane Flight Manual to include procedures for identifying and pulling certain circuit breakers if the altimeter Captain's Primary Flight Display (PFD) data become unreliable. This action is prompted by a report of two incidents in which an intermittent loss of altitude data occurred simultaneously on the Captain's PFD, First Officer's PFD, and the Integrated Standby Instrument System (ISIS) altitude display due to a voltage drop in the power distribution control unit. The actions specified by this AD are intended to prevent loss of all altitude information and subsequent essential navigation data for continued safe flight and landing.
2000-09-03: This amendment supersedes an existing airworthiness directive (AD), applicable to certain Boeing Model 747-400 series airplanes, that currently requires various inspections and functional tests to detect discrepancies of the thrust reverser control and indication system, and correction of any discrepancy found. This amendment adds an appendix and revises certain actions in the existing AD. This amendment is prompted by a report indicating that completion of the cone brake test of the center drive unit is ineffective for certain airplanes. The actions specified in this AD are intended to ensure the integrity of the fail safe features of the thrust reverser system by preventing possible failure modes in the thrust reverser control system that can result in inadvertent deployment of a thrust reverser during flight.
2022-16-02: The FAA is adopting a new airworthiness directive (AD) for certain Airbus Canada Limited Partnership Model BD-500-1A10 and BD-500- 1A11 airplanes. This AD was prompted by the discovery that overwing emergency exit door (OWEED) handle covers were difficult to open on some airplanes. This AD requires replacing the existing OWEED handle cover brackets with newly designed OWEED handle cover brackets and installing placards regarding this replacement, as specified in a Transport Canada Civil Aviation (TCCA) AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
97-11-04: This amendment adopts a new airworthiness directive (AD), applicable to Bell Helicopter Textron, Inc. (BHTI) Model 412 and 412EP helicopters, that requires creation of a component history card or equivalent record using a Retirement Index Number (RIN) system; establishes a system for tracking increases to the accumulated RIN; and establishes a maximum accumulated RIN for certain main rotor masts (masts) and main rotor spline plates (spline plates). This amendment is prompted by fatigue analyses and tests that show certain masts and spline plates fail earlier than originally anticipated because of an unanticipated high number of takeoffs and external load lifts utilizing high power settings, in addition to the time-in-service (TIS) accrued under normal operating conditions. The actions specified by this AD are intended to prevent fatigue failure of the mast or spline plate, which could result in failure of the main rotor system and subsequent loss of control of the helicopter.
2000-09-04: This amendment supersedes an existing airworthiness directive (AD), applicable to certain Boeing Model 767 series airplanes, that currently requires tests, inspections, and adjustments of the thrust reverser system. That AD also requires installation of a terminating modification, and repetitive follow-on actions. This amendment revises certain actions in the existing AD. This amendment is prompted by a report indicating that certain instructions referenced in the existing AD for accomplishment of the cone brake test of the center drive unit are not accurate for certain airplanes. The actions specified in this AD are intended to ensure the integrity of the fail safe features of the thrust reverser system by preventing possible failure modes in the thrust reverser control system that can result in inadvertent deployment of a thrust reverser during flight.
82-16-02: 82-16-02 FOKKER B.V.: Amendment 39-4424. Applies to Model F28 Series 1000 and 4000 airplanes certificated in all categories, serial numbers as indicated below. Note: Some serial numbers listed may actually be 2000, 3000, 5000, or 6000 airplanes that are not presently eligible for U.S. certification. Those serial numbers may be disregarded insofar as this AD is concerned. 1. Unless already accomplished, accomplish the following within the time specified in each paragraph below after the effective date of this AD. A. Applies to airplanes with serial numbers (S/N's) 11004 through 11016. Compliance required within the next 750 hours time in service. To prevent inadvertent cross connection of the engine fire extinguishing bottle electrical wiring, install placards and inspect and rework the wiring in accordance with the Accomplishment Instructions of Fokker Service Bulletin F28/26-2, Revision 1, dated March 19, 1970. B. Applies to airplanes with S/N's 11003, 11004, 11006, and 11009 through 11012. Compliance required within the next 900 hours time in service. To preclude inadvertent fuel transfer, install a 1.0 p.s.i. check valve and rework the defueling control valve wiring in accordance with the Accomplishment Instructions of Fokker Service Bulletin F28/28-3 dated January 6, 1970. C. Applies to airplanes with S/N's 11004 through 11016, 11021 through 11052, 11054 through 11061, 11063 through 11066, and 11991 through 11993. Compliance required within the next 100 hours time in service. To preclude fuel leakage, inspect fuel supply tubes for chafing damage, repair or replace such tubes as necessary, and provide adequate chafing protection in accordance with the Accomplishment Instructions of Fokker Service Bulletin F28/28- 8 dated December 24, 1969 (S/N's 11004 through 11016), or Service Bulletin F28/28-22, Revision 1, dated December 18, 1972 (S/N's 11021 through 11052, 11054 through 11061, 11063 through 11066, and 11991 through 11993). D. Applies to airplanes with S/N's 11053, 11062, 11077, 11080, 11081, 11090 through 11093, 11108 through 11112, 11114 through 11116, 11118, 11120 through 11124, 11126 through 11128, 11130, 11133, 11135, 11138 through 11142, and 11144. Compliance required within the next 100 hours time in service. To preclude a fuselage fire, perform both of the following: (1) Inspect the APU fuel supply line for interference with electrical wiring and replace as necessary; and (2) Modify the fuel supply line installation and electrical wiring to provide adequate clearance in accordance with the Accomplishment Instructions of Fokker Service Bulletin F28/28-32, Revision 1, dated September 3, 1979. E. Applies to all airplanes having check valve Part No. 123312-2-1 installed in the Auxiliary Power Unit (APU) bleed air duct. Compliance required within the next 100 hours time in service and at no greater than 3000 hour intervals time in service thereafter. To preclude damage to the APU, inspect the check valve for wear and replace, as necessary, in accordance with the Accomplishment Instructions of Fokker Service Bulletin F28/36-9, Revision 1, dated February 16, 1973. F. Applies to airplanes with S/N's 11003 through 11056 and 11991 through 11993. Compliance required within the next 100 hours time in service. To ensure proper functioning of the fire seal, inspect the seventh stage bleed air duct fire seal and modify, as necessary, in accordance with the Accomplishment Instructions of Fokker Service Bulletin F28/36- 10 dated February 12, 1973. G. Applies to airplanes with S/N's 11003 through 11101, and 11991 through 11993. Initial compliance required within the next 100 hours time in service and on a daily basis thereafter. To detect failure of the APU extension silencer and thereby preclude failure of APU exhaust jet pipe, inspect the extension silencer in accordance with the Accomplishment Instructions of Fokker Service Bulletin F28/49-24 dated February 23, 1976. These inspections may be discontinued upon installation of an improved APU extension silencer in accordance with Fokker Service Bulletin F28/49-21, Revision 1, dated May 10, 1976. H. Applies to airplanes with S/N's 11003 through 11131, and 11991 through 11993. Compliance required within the next 1500 hours time in service. To ensure adequate drainage of fuel leakage from the APU compartment, modify the APU enclosure drain system in accordance with the Accomplishment Instructions of Fokker Service Bulletin F28/49-25 dated July 18, 1977. I. Applies to airplanes with S/N's 11003 through 11013. Compliance required within the next 750 hours time in service. To maintain the integrity of the firewall, close the unused holes in the left hand and right hand engine nacelle firewalls in accordance with the Accomplishment Instructions of Fokker Service Bulletin F28/54-2, Revision 1, dated June 15, 1970. J. Applies to airplanes with S/N's 11003 through 11073, 11075, and 11991 through 11993. Compliance required within the next 150 hours time in service. To prevent control cable failure due to corrosion, inspect, replace as necessary, and treat HPC and RPM control cables in accordance with the Accomplishment Instructions of Fokker Service Bulletin F28/76-16, Revision 1, dated October 6, 1975. K. Applies to airplanes with S/N's 11003 through 11124, 11126 through 11132, 11134, 11991, and 11992. Compliance required within the next 100 hours time in service. To preclude inadvertent closure of the fire shutoff valves, inspect and correct microswitch adjustment, as necessary, and install seal wire (safety wire) on fire switch guards in accordance with the Accomplishment Instructions of Fokker Service Bulletin F28/76-20 dated January 1, 1979. 2. Alternate means of compliance with this AD which provide an equivalent level of safety may be used when approved by the Chief, Seattle Area Aircraft Certification Office, FAA Northwest Mountain Region. 3. Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base for the accomplishment of inspections and/or modifications required by this AD. 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). This amendment becomes effective August 30, 1982.
2015-05-08: We are adopting a new airworthiness directive (AD) for certain Lockheed Martin Corporation/Lockheed Martin Aeronautics Company Model 382, 382B, 382E, 382F, and 382G airplanes. This AD was prompted by an evaluation by the design approval holder (DAH) indicating that the upper and lower rainbow fittings on the outer wing are subject to widespread fatigue damage (WFD). This AD requires repetitive inspections of the upper and lower rainbow fittings on the outer wing to detect cracks propagating from fasteners attaching the fittings to skin panels, and related investigative and corrective actions if necessary; and replacement of the upper and lower rainbow fittings on the outer wing. We are issuing this AD to prevent fatigue cracking of the upper and lower rainbow fittings on the outer wing and skin-panel- to-fitting fastener holes, which could result in reduced structural integrity of the airplane and possible separation of the wing from the airplane.