Results
79-26-04: 79-26-04 PIPER AIRCRAFT CORPORATION: Amendment 39-3642. Applies to the following Model PA-32RT-300 and PA-32RT-300T series airplanes, certificated in all categories: PA-32RT-300 Lance II 32R-7885001 to 32R-7885025 Inclusive 32R-7885027 to 32R-7885261 Inclusive 32R-7885263 to 32R-7885285 Inclusive 32R-7985001 to 32R-7985035 Inclusive 32R-7985037 to 32R-7985045 Inclusive 32R-7985047 to 32R-7985059 Inclusive 32R-7985062, 32R-7985064, 32R-7985066, 32R-7985067, 32R-7985069 to 32R-7985076 Inclusive 32R-7985078, 32R-7985083 to 32R-7985085 Inclusive 32R-7985088 to 32R-7985090 Inclusive 32R-7985092 to 32R-7985097 Inclusive 32R-7985101, 32R-7985103 to 32R-7985105 PA-32RT-300T Turbo Lance lI 32R-7887001 to 32R-7887222 Inclusive 32R-7887224 to 32R-7887226 Inclusive 32R-7887228 to 32R-7887237 Inclusive 32R-7887239 to 32R-7887243 Inclusive 32R-7887245 to 32R-7887254 Inclusive 32R-7887256 to 32R-7887261 Inclusive32R-7887263, 32R-7887265 to 32R-7887289 Inclusive 32R-7987001, 32R-7987002 32R-7987004 to 32R-7987011 Inclusive 32R-7987013, 32R-7987014, 32R-7987016, 32R-7987017, 32R-7987019, 32R-7987020, 32R-7987024 to 32R-7987028 Inclusive 32R-7987029, 32R-7987030, 32R-7987032, 32R-7987034, 32R-7987035, 32R-7987038, 32R-7987039, 32R-7987041, 32R-7987042, 32R-7987044, 32R-7987046, 32R-7987049 to 32R-7987051 Inclusive 32R-7987054 to 32R-7987058 Inclusive 32R-7987060, 32R-7987066, 32R-7987068 to 32R-7987070 Inclusive 32R-7987072, 32R-7987073, 32R-7987075, 32R-7987076, 32R-7987078 to 32R-7987080 Inclusive 32R-7987082 to 32R-7987086 Inclusive 32R-7987088, 32R-7987089, 32R-7987091, 32R-7987094, 32R-7987096 to 32R-7987099 Inclusive 32R-7987101, 32R-7987102, 32R-7987104, 32R-7987107 to 32R-7987115 Inclusive 32R-7987117, 32R-7987119, 32R-7987122, 32R-7987124, 32R-7987125, 32R-7987126.Compliance as prescribed in the body of the AD. To prevent initiation and/or growth of rudder skin cracks, with resulting possible weakening of rudder structural integrity, accomplish the following, unless already accomplished: a. Within the next 25 hours time-in-service after the effective date of this AD, and at intervals not to exceed 25 hours time in service, visually check the area along the skin beads at the trailing edge of the rudder for cracks. This check may be accomplished by the pilot. NOTE: A maintenance record entry showing compliance with these repetitive visual checks is required. b. If crack(s) are found, repair within the next 10 hours time in service in accordance with the instructions contained in Piper Kit Part Number 763 940V, or in an equivalent manner approved by the Chief, Engineering and Manufacturing Branch, FAA Southern Region. c. If no crack(s) are found during the checks required by paragraph a, modify the rudder within thenext 100 hours time in service after the effective date of this AD in accordance with the instructions contained in Piper Kit Part Number 763 936V, or in an equivalent manner approved by the Chief, Engineering and Manufacturing Branch, FAA Southern Region. d. Verify that the rudder balance, after repair or modification, is within the limits established in the Piper Lance II Service Manual. e. Compliance with paragraphs b or c, and d, above terminates the repetitive checks required in paragraph a above. f. Upon submission of substantiating data through an FAA Aviation Safety Inspector, the Chief, Engineering and Manufacturing Branch, FAA Southern Region, may adjust the repair or modification compliance time. Piper Service Letter No. 882 also deals with this subject. This amendment is effective January 7, 1980.
80-01-02: 80-01-02 BRITISH AEROSPACE/SOCIETE NATIONALE INDUSTRIELLE AEROSPATIALE: Amendment 39-3644. Applies to Concorde Type I airplanes. To prevent failure of the main landing gear tires or wheels or both resulting from underinflated tire conditions, accomplish the following, or an FAA-approved equivalent: (a) Before each flight after the effective date of this AD check the tire pressure of each main landing gear tire in accordance with the instructions of Chapter 12.14.32 of the Maintenance Manual as follows: (1) When the gate stop time is more than 4 hours, verify the tire pressure within 2 hours preceding start of engines. (2) When the gate stop time is between 3 and 4 hours, verify the tire pressure within the hour preceding the start of engines. (3) When the gate stop time is 2 to 3 hours verify the tire pressure within 30 minutes preceding the start of engines. (4) When the gate stop time is less than 2 hours verify the tire pressure within 30 minutes preceding the start of engines and comply with paragraph (c) of this AD. (b) If as a result of the tire pressure verifications required by paragraph (a)(1), (a)(2) or (a)(3) of this AD, the tire pressure was found to be - (1) Between 14.6 bars/212 psi and 15 bars/218 psi, no further action required; (2) From 14.2 bars/206 psi to 14.6 bars/212 psi, reinflate to 15 bars/218 psi; (3) From 13.4 bars/195 psi to 14.2 bars/206 psi, reinflate to 15 bars/218 psi and record this action for future reference; (4) From 12.6 bars/183 psi to 13.4 bars/195 psi, replace that wheel and tire and comply with paragraph (e) of this AD; or (5) Below 12.6 bars/183 psi, replace that wheel and tire and also replace the adjoining wheel and tire and comply with paragraph (e) of this AD. (c) If as a result of the tire pressure verification required by paragraph (a)(4) of this AD the pressure was found to be - (1) Above 14.6 bars/212 psi - nofurther action is required; (2) From 14.2 bars/206 psi to 14.6 bars/212 psi, reinflate the tire to 15 bars/218 psi; (3) From 12.6 bars/183 psi to 14.2 bars/206 psi, replace that tire and wheel and comply with paragraph (e) of this AD; or (4) Below 12.6 bars/183 psi, replace that wheel and tire and also replace the adjoining wheel and tire and comply with paragraph (e) of this AD. (d) Prior to further flight, replace the wheel and tire, and accomplish the "push-in" fuse plug check in accordance with Aerospatiale Campaign Wire 32CW076, Issue 4, if - (1) The cockpit brake temperature indicator records a temperature above 510C/950F; (2) A rejected takeoff is executed from a speed over 100 knots, with a brake cooling fan inoperative and the corresponding brake was not deactivated; or (3) A landing was accomplished with a brake cooling fan inoperative and the corresponding brake was not deactivated. (e) Perform the non-destructive test, and the "push-in" fuse plug check on any wheel removed from the aircraft as required in paragraph (b), (c), or (d) of this AD, in accordance with Aerospatiale Campaign Wire 32CW076, Issue 4. (f) Any discrepancies found on the wheels, tires, brakes or on the fuse plugs during the inspections defined above must be reported to the Chief, Aircraft Certification Staff, AEU-100, Federal Aviation Administration, c/o American Embassy, Brussels, Belgium. (Reporting approved by the Office of Management and Budget under OMB No. 04-R0174.) (g) An equivalent means of compliance with the requirements of this AD may be used if approved by the Chief, Aircraft Certification Staff, AEU-100, Federal Aviation Administration, c/o American Embassy, Brussels, Belgium. This supersedes telegraphic AD T79EU11, dated September 10, 1979. This amendment becomes effective December 26, 1979.
68-26-01: 68-26-01 HUGHES: Amendment 39-696. Applies to Model 269A Helicopter Serial Nos. 0011 through 0893 (except TH-55A helicopters), 269A-1 Helicopter Serial Nos. 0001 through 0041, 269A-2 Helicopters Serial Nos. 0001 and 0002, 269B Helicopter Series Nos. 0001 through 0359 with P/N 269A5504-3 Lower Coupling Drive Shaft or Hughes P/N 80-269A5504-5 or P/N 269A5504-5 Lower Coupling Drive Shaft assembly installed. Compliance required within 25 hours of helicopter operation after the effective date of this airworthiness directive, unless previously accomplished. To prevent failures of the lower coupling drive shaft (Hughes P/N 269A5504-3) or lower coupling drive shaft assembly (Hughes P/N 80-269A5504-5 or 269A5504-5) by assuring the physical integrity of the shaft, including freedom from cracks: (a) Inspect the entire shaft per Hughes Service Information Notice No. N-55.1, dated December 9, 1968, or later FAA approved revisions, or any equivalent inspection approved by the Chief, Aircraft Engineering Division, Western Region. (1) If cracks are found during this inspection, retire shaft from service and replace with a new shaft. (2) If no cracks are found, identify the shaft per Item "m" of Hughes Service Information Notice No. N-55.1, or later FAA approved revisions, or equivalent identification approved by the Chief, Aircraft Engineering Division, Western Region. The shaft may continue to be used in accordance with service life limitations. (b) Determine that the inspection or identification, as appropriate, specified in paragraph (a) has been accomplished, prior to installing replacement lower coupling drive shafts (P/N 269A5504-3). This supersedes Amendment 39-661 (33 F.R. 14636), AD 68-20-03. This amendment becomes effective December 21, 1968.
79-26-01: 79-26-01 PIPER: Amendment 39-3639. Applies to Piper PA-23-250 Model airplanes, Serial Nos. 27-7654001 thru 27-7954044 certificated in all categories, which incorporate the following stabilators. Serial Nos.: 0336-L thru 0340-L 0401-L thru 0607-L 0337-R thru 0341-R 0402-R thru 0609-R To prevent possible loosening and relative motion between the stabilator bottom skins and the stabilator frame - structure, accomplish the following: a. Within the next 50 hours in service after the effective date of this AD, unless already accomplished within the past 50 hours and at intervals not to exceed 100 hours in service thereafter, inspect and repair or alter the left and right stabilator in accordance with the "INSTRUCTIONS" section on page 3 of 3 in Piper Service Bulletin No. 606 dated July 12, 1979, or approved equivalent. b. When the stabilator assemblies are altered in accordance with paragraph B.4. of the "INSTRUCTIONS" section or equivalent, compliance with this AD is no longer required. c. Equivalent inspections, repairs or alterations must be approved by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region. d. Upon submission of substantiating data through an FAA Maintenance Inspector, the compliance time specified in this AD may be adjusted by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region. This amendment is effective December 24, 1979.
2020-20-01: The FAA is adopting a new airworthiness directive (AD) for certain Dassault Aviation Model FALCON 7X, FALCON 900EX, and FALCON 2000EX airplanes. This AD was prompted by reports of primary display unit (PDU) data flickering on airplanes equipped with EASy software. This AD requires amending the applicable Dassault airplane flight manual (AFM) to incorporate the applicable AFM change project (CP), 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.
2009-07-05: We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) originated 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: Incomplete accomplishment instructions in SB [service bulletin] ATR72-27-1059 original issue and Revision 1, failed to mention installation of cotter pins to secure the self locking nuts after re-installation of the modified Pitch Uncoupling Mechanism (PUM), when connecting the elevator control linkage rods to the PUM input levers and the PUM output rods to the elevator bellcranks (on both sides). Because of the non-installation of these four cotter pins, the fail-safe criteria of the design requirements on the pitch control are no longer met. Such a failure could cause the loss of one self locking nut and would result in the loss of pitch control onone side--Captain or First Officer--or the loss of control of one elevator surface. The symmetrical loss of two concerned self-locking nuts could lead to a complete loss of the pitch control. * * * * * We are issuing this AD to require actions to correct the unsafe condition on these products.
2020-20-07: The FAA is adopting a new airworthiness directive (AD) for all Rolls-Royce Deutschland Ltd & Co KG (RRD) Trent 1000-AE3, Trent 1000- CE3, Trent 1000-D3, Trent 1000-G3, Trent 1000-H3, Trent 1000-J3, Trent 1000-K3, Trent 1000-L3, Trent 1000-M3, Trent 1000-N3, Trent 1000-P3, Trent 1000-Q3, Trent 1000-R3, Trent 7000-72, and Trent 7000-72C model turbofan engines. This AD was prompted by a report of crack findings in the front air seal on the intermediate-pressure compressor (IPC) shaft assembly during the stripping of a flight test engine. This AD requires initial and repetitive borescope inspections (BSIs) or visual inspections of the IPC shaft assembly and, depending on the results of the inspection, replacement of the IPC shaft assembly with a part eligible for installation. The FAA is issuing this AD to address the unsafe condition on these products.
84-02-01: 84-02-01 AIRBUS INDUSTRIE: Amendment 39-4794. Applies to Model A300 B2-1A, B2- 1C, B4-2C, B2K-3C, B4-103, B2-203, and B4-203 series airplanes, certificated in all categories with serial numbers specified in paragraph 1, Planning Information, of Airbus Industrie Service Bulletin A300-32-310, dated February 12, 1981. To prevent potential loss of braking, accomplish the following, unless previously accomplished: A. Within the next 500 flight hours after the effective date of this AD, inspect the hydraulic hose end fitting collars on Titeflex Type 3/8-inch diameter hoses SC641060266 of the brake hydraulic system in accordance with paragraph 2, Accomplishment Instructions, of the service bulletin. 1. End fittings with batch reference number 06K672C,06L039C, or 06M330C on the sleeve or other fittings which are cracked must be replaced with end fittings manufactured after January 1976 and having identification mark "U", within 50 flight hours from the date of inspection.2. Uncracked end fittings with date of manufacture later than January 1976 and no identification mark or identification mark "X" must be replaced with the end fittings types specified in subparagraph A.1, above, within 250 flight hours from the date of inspection. B. Alternate means of compliance which provide an equivalent level of safety may be used when approved by the Manager, Seattle Aircraft Certification Office, FAA, Northwest Mountain Region. C. 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. This amendment becomes effective February 27, 1984.
2003-21-01: The FAA supersedes Airworthiness Directive (AD) 94-18-04 R1, which currently applies to all Univair Aircraft Corporation (Univair) Models Alon A-2 and A2-A; ERCO 415-C, 415-CD, 415-D, 415-E, and 415-G; Forney F-1 and F-1A; and Mooney M10 airplanes. AD 94-18-04 R1 requires installing inspection openings in the outer wing panels, inspecting (one-time) the wing outer panel structural components for corrosion, and repairing any corroded wing outer panel structural component. Several reports of corrosion in the outer wing panels of the affected airplanes prompted that AD. This AD is the result of additional reports of corrosion on airplanes in compliance with AD 94- 18-04 R1. This AD makes the inspection required in AD 94-18-04 R1 repetitive. We are issuing this AD to prevent wing damage caused by a corroded wing outer panel structural component, which, if not detected and corrected, could progress to the point of structural failure. DATES: This AD becomes effective on December1, 2003. The Director of the Federal Register previously approved the incorporation by reference of Univair Aircraft Corporation Service Bulletin No. 29, Revision B, dated January 2, 1995, as of March 24, 1995 (60 FR 13626, March 14, 1995). The Director of the Federal Register approved the incorporation by reference of Univair Aircraft Corporation Mandatory Service Bulletin No. 29, Revision C, dated July 8, 1999, as of December 1, 2003.
79-20-07: 79-20-07 PIPER AIRCRAFT CORPORATION: Amendment 39-3573. Applies to the following Piper Models of airplanes, equipped with three 12 volt cigar lighters powered through a triplet of voltage dropping resistors, certificated in all categories; PA-31 and PA-31-325, S/N 31- 7712074 through 31-7912098 and PA-31-350, S/N 31-7752096 through 31-7952197. Compliance is required within the next 25 hours time in service or 30 days, whichever occurs first, after the effective date of this AD unless already accomplished. To prevent smoke in the cockpit, accomplish the following: a. For Models PA-31 and PA-31-325, S/N 31-7712074 to, but not including, 31- 7912001, and PA-31-350, S/N 31-7752096 to, but not including, 31-7952001; disconnect wire CIG-1 from the 7 amp circuit breaker located at the voltage dropping resistor assembly under the instrument panel or disconnect wire CIG-1A from the 15 amp "Heater and Cigar Lighter" circuit breaker located on the pilot's circuit breaker panel. b. For Models PA-31 and PA-31-325, S/N 31-7912001 through 31-7912098, and PA-31-350, S/N 31-7952001 through 31-7952197, except 31-7952191, 31-7952193, 31- 7952195; disconnect wire CIG-1 from the 7 amp "Lighter" circuit breaker located on the pilot's circuit breaker panel. c. After disconnection, protect the wire by insulating its disconnected end and fold the wire end back against itself or the bundle in which it is routed and secure it. Compliance with the provisions of this Airworthiness Directive may be accomplished in an equivalent manner approved by the Chief, Engineering and Manufacturing Branch, FAA, Southern region. This amendment is effective October 2, 1979.
65-03-03: 65-03-03 LYCOMING: Amdt. 39-460, Part 39- Federal Register February 2, 1965. Applies to Model IO- 320-BIA Engines Equipped with Hartzell HC-E2YL-2/7663-4 Propellers and Installed in Piper Model PA-30 Aircraft. Compliance required as indicated. To prevent crankshaft flange failure with a possible loss of propeller accomplish the following: (a) Add the following operating limitation to the airplane flight manual: Do not exceed 2,100 r.p.m. engine speed when demonstrating or practicing power-on-stalls. (b) Inspect engines in accordance with the procedure described in 2(a) and 2(b) of Lycoming Service Bulletin No. 300A before further flight following any flight involving acrobatic maneuvers (including spins) which are prohibited by the airplane placard and flight manual or any flight during which the limitation specified in (a) has been exceeded. If cracks are found in the crankshaft flange remove the crankshaft from service before further flight. NOTE: It is requested that any cracks found as the result of the inspections required by this AD be reported to the Engineering and Manufacturing Branch, FAA Eastern Region, John F. Kennedy International Airport, Jamaica, New York. This supersedes AD 64-15-05. This directive effective January 30, 1965. Revised August 5, 1967.
2003-05-10R1: This amendment revises an existing airworthiness directive (AD), that applies to General Electric Company (GE) CF34-3A1, -3B, and -3B1 turbofan engines with scavenge screens part numbers (P/Ns) 4047T95P01 and 5054T86G02 installed in the B-sump oil scavenge system. That AD currently requires initial and repetitive visual inspections and cleaning of the B-sump scavenge screens until a screenless fitting is installed. This amendment requires the same initial and repetitive visual inspections and cleaning of the B-sump scavenge screens until a screenless fitting is installed. This amendment also corrects a typographical error, and introduces a less restrictive terminating action schedule. This amendment is prompted by the need to correct a typographical error and by the need to introduce a less restrictive terminating action schedule. We are issuing this AD to prevent B-sump scavenge screen blockage due to coking which could result in ignition of B-sump oil in the secondary air system, fan drive shaft separation, and uncontained engine failure.
79-19-09: 79-19-09 PIPER: Amendment 39-3560. Applies to Model PA-31T1, Serial Nos. 31T-7804001 to 31T-7904016 inclusive, and PA-31T, Serial Nos. 31T-7400002 to 31T-7920036, inclusive. To prevent possible hazards in flight caused by a shorting of the electroluminescent panel inverters creating smoke in the cockpit: (a) Within the next 100 hours in service or at the next scheduled inspection, whichever occurs first, comply with the instructions of Piper Service Bulletin No. 640 dated June 22, 1979, for the replacement and/or relocation of the electroluminescent panel power supply inverter. (b) Upon request with substantiating data submitted through an FAA Maintenance Inspector, the compliance time specified in this AD may be adjusted by the Chief, Engineering and Manufacturing Branch, FAA Eastern Region. This amendment is effective September 25, 1979.
2020-18-16: The FAA is adopting a new airworthiness directive (AD) for certain The Boeing Company Model 767-200, -300, -300F, and -400ER series airplanes. This AD was prompted by the FAA's analysis of the Model 767 fuel system reviews conducted by the manufacturer. This AD requires modifying the fuel quantity indicating system (FQIS) to prevent development of an ignition source inside the center fuel tank due to electrical fault conditions. This AD also provides optional actions for cargo airplanes. The FAA is issuing this AD to address the unsafe condition on these products.
2020-20-12: The FAA is adopting a new airworthiness directive (AD) for all General Electric Company (GE) GEnx-1B64, -1B64/P1, -1B64/P2, -1B67, - 1B67/P1, -1B67P2, -1B70, -1B70/75/P1, -1B70/75/P2, -1B70/P1, -1B70/P2, -1B70C/P1, -1B70C/P2, -1B74/75/P1, -1B74/75/P2, -1B76/P2, and -1B76A/P2 model turbofan engines. This AD was prompted by reports of combustor case burn-through. This AD requires installation of electronic engine control (EEC) software, version B205 or later. The FAA is issuing this AD to address the unsafe condition on these products.
61-26-02: 61-26-02 CANADAIR: Amdt. 379 Part 507 Federal Register December 21, 1961. Applies to all CL-44D4 aircraft. Compliance required as indicated. As a result of a fuel leak found in the line to the upper heater, the following inspection must be accomplished within the next 25 hours' time in service after the effective date of this AD unless already accomplished within the last 40 hours' time in service and at intervals of 65 hours' time in service thereafter. With full fuel pressure in the tail heater fuel lines, inspect all fuel lines and fittings in the tail heater compartment for leaks and security of attachment. Loose lines shall be properly secured, and defective lines and fittings replaced prior to further flight. The special inspections required by this airworthiness directive may be discontinued after incorporation of the Canadian Department of Transport and FAA approved modification. Upon request of the operator an FAA maintenance inspector subject to priorapproval of the Chief, Engineering and Manufacturing Branch, International Division, Washington 25, D.C., may adjust the repetitive inspection intervals specified in this AD to permit compliance at an established inspection period of the operator if the request contains substantiating data to justify the increase for such operator. This directive effective December 21, 1961.
2003-20-11: This amendment supersedes an existing airworthiness directive (AD) for Eurocopter Deutschland GmbH (ECD) Model EC135 P1 and EC135 T1 helicopters. That AD currently requires adding the AD or a statement to the Rotorcraft Flight Manual (RFM) informing the pilot to reduce power and land as soon as practicable if a thump-like sound followed by unusual vibration occurs during flight. That AD also requires visually inspecting the main rotor drive torque strut assembly (strut) for a crack or a break, recording the inspections in the historical or equivalent record, and re-marking and relocating the strut, as appropriate, and replacing any unairworthy strut with an airworthy strut. Also, that AD establishes life limits for certain struts and revises the life limit for other struts. This amendment retains the same requirements but adds the ECD Model EC135 P2 and EC135 T2 helicopters to the applicability and requires replacing certain life-limited struts with titanium struts. This amendment is prompted by the manufacture of a titanium strut that provides a permanent correction to the unsafe condition that led to limiting the life of other struts that have failed. The actions specified by this AD are intended to prevent failure of a strut and subsequent loss of control of the helicopter.
94-17-16: This amendment supersedes an existing airworthiness directive (AD), applicable to General Electric Aircraft Engines (GEAE) CT7 series turboprop engines, that currently requires a one-time ultrasonic inspection of a suspect population of propeller shafts for metallurgical defects, and if necessary, replacement with a serviceable part. This amendment extends the compliance time for the required ultrasonic inspection on certain propeller shafts. This amendment is prompted by information indicating that the equipment necessary to perform the ultrasonic inspection is less available than originally assumed. The actions specified by this AD are intended to prevent failure of the propeller shaft, which can result in separation of the propeller from the propeller shaft and possible damage to the aircraft.
2003-20-10: The FAA is adopting a new airworthiness directive (AD) that applies to all Raytheon Aircraft Company (Raytheon) Beech Models 1900, 1900C, and 1900D airplanes. This AD requires you to make a correction to the elevator trim system maintenance procedures, incorporate a temporary revision to the applicable maintenance manual, and incorporate procedures that will enhance the existing elevator trim operational check every time you have maintenance done on the elevator trim system. This AD is the result of an analysis of the maintenance procedures of the elevator trim system. We are issuing this AD to detect and correct any maintenance-induced problems with the elevator trim system installation before problems occur during operation. Such a condition could lead to difficulties in controlling the airplane or a total loss of pitch control.
2020-20-02: The FAA is adopting a new airworthiness directive (AD) for Leonardo S.p.a. (Leonardo) Model A109E, A109S, and AW109SP helicopters. This AD requires inspecting each fire extinguisher bottle for a crack. This AD was prompted by a report of a cracked fire extinguisher bottle. The actions of this AD are intended to address an unsafe condition on these products.
83-21-06 R1: 83-21-06 R1 AMI INDUSTRIES, INC.: Amendment 39-4752 as amended by Amendment 39-4859. Applies to AMI crew seats Model 716-1, -2, -11, -12, -21, and -22 and Model 865-1 through -9 and -11 typically found on but not limited to Beech Aircraft Corporation Model 18 series and Model 65/90 series airplanes certificated in all categories. Compliance required on or before July 31, 1984, unless previously accomplished. To prevent the possible failure of crew seats, reinforce the crew seat frame assembly P/N 865J10005-1 by installation of AMI Industries, Inc., seat frame brace kit P/Ns 865K90000-1 or 865K90000-3 in accordance with AMI Industries, Inc., Service Bulletin No. 25-10-865-01, Revision B, dated February 22, 1984, or later FAA approved revision. An alternate means of compliance which provides an equivalent level of safety may be used when approved by the Manager, Denver Aircraft Certification Office, FAA, Northwest Mountain Region. 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. Amendment 39-4752 became effective November 28, 1983. This Amendment 39-4859 becomes effective April 26, 1984.
2020-20-11: The FAA is adopting a new airworthiness directive (AD) for certain General Electric Company (GE) GEnx-1B64/P2, -1B67/P2, -1B70/P2, -1B70C/P2, -1B70/75/P2, -1B74/75/P2, -1B76/P2, -1B76A/P2, and GEnx- 2B67/P model turbofan engines. This AD was prompted by the detection of melt-related freckles in the billet, which may reduce the life limits of certain high-pressure turbine (HPT) rotor stage 2 disks and a certain stages 6-10 compressor rotor spool. This AD requires the removal of certain HPT rotor stage 2 disk and the removal of a certain stages 6-10 compressor rotor spool before reaching their new life limits. The FAA is issuing this AD to address the unsafe condition on these products.
2020-18-20: The FAA is adopting a new airworthiness directive (AD) for certain MD Helicopters Inc. (MDHI) Model 369A, 369D, 369E, 369FF, 369H, 369HE, 369HM, 369HS, 500N, and 600N helicopters. This AD was prompted by reports of abrasion strips departing the main rotor (MR) blade in- flight. This AD requires tap inspecting each MR blade leading edge abrasion strip. The FAA is issuing this AD to address the unsafe condition on these products.
94-17-08: This amendment adopts a new airworthiness directive (AD), applicable to all de Havilland Model DHC-7 series airplanes, that requires removal of the aluminum or brass hardware in the firewall terminal block assembly and replacement with steel hardware. This amendment is prompted by the results of an investigation, which revealed that corroded aluminum washers in the DC firewall terminal block assembly may loosen the electrical connections. The actions specified by this AD are intended to prevent interruption of DC electrical power due to connections that may have loosened from corrosion.
81-02-05: 81-02-05 MCDONNELL DOUGLAS: Amendment 39-4022. Applies to all Model DC-8 series airplanes equipped with upper main cargo door, certificated in all categories. Compliance required as indicated unless already accomplished. To prevent stress corrosion cracking of the upper cargo door spool fitting attach bolts accomplish the following: \n\n\tA.\tFor airplanes not modified per Douglas Aircraft Company Service Bulletin DC-8 SB 52-78, dated May 5, 1975, within 12 months after the effective date of this AD, inspect, lubricate, replace as necessary, and seal the cargo door latch spool fitting attach bolts in accordance with a method approved by the Chief, Los Angeles Area Aircraft Certification Office. (NOTE: Accomplishment of the instructions in Figure 1 of Douglas Aircraft Company Service Bulletin DC-8 SB 52-82, dated October 28, 1980, has been approved as a means of compliance with this requirement.) \n\n\tB.\tFor airplanes modified per Douglas Aircraft Company Service Bulletin DC-8 SB52-78, within 24 months after the effective date of this AD, inspect, lubricate, replace as necessary, and seal the cargo door latch spool fitting attach bolts in accordance with a method approved by the Chief, Los Angeles Area Aircraft Certification Office. (NOTE: Accomplishment of the instructions in Part II, Group II, Paragraph C of DC-8 SB 52-82 has been approved as a means of compliance with this requirement.) \n\n\tC.\tSpecial flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes unpressurized to a base for the accomplishment of inspections/modifications required by this AD. \n\n\tD.\tAlternative inspections, modifications, or other actions which provide an equivalent level of safety may be used when approved by the Chief, Los Angeles Area Aircraft Certification Office, FAA Northwest Region. \n\n\tThis amendment becomes effective April 1, 1981.