Results
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.
2009-07-12: The FAA is adopting a new airworthiness directive (AD) for General Electric Company (GE) CF34-1A, -3A, -3A1, -3A2, -3B, and -3B1 turbofan engines with high-pressure (HP) rotor 4-step air balance piston stationary seals (4-step seals), part numbers (P/Ns) 4923T54G01, 6019T90G03, 6037T99G01, 6037T99G02, and 6037T99G03, installed. This AD requires removing the 4-step seals and incorporating an 8-step seal at the next piece-part exposure. This AD results from the investigation of an airplane accident. Both engines experienced high-altitude flameout. Rotation of the HP rotors was not maintained during descent and the engines could not be restarted. We are issuing this AD to prevent the inability to restart both engines after flameout due to excessive friction of the 4-step seal, which could result in subsequent forced landing of the airplane.
64-19-04: 64-19-04 GENERAL DYNAMICS: Amdt. 783 Part 507 Federal Register August 7, 1964. Applies to Model 240 Series Aircraft. Compliance required within 1,000 hours' time in service after the effective date of this AD, unless already accomplished. A fault in an unprotected cabin supercharger disconnect circuit caused an electrical fire in the cabin pressurization console on the copilot's side. To prevent recurrence of this incident provide the following circuit protection: Modify the aircraft fire extinguisher circuits, cabin pressure dump solenoid circuit and emergency compressor shutoff valve circuit to provide circuit protection and incorporate an alternate emergency power circuit and a normally-off test light in accordance with Convair Service Engineering Report No. 240-24 dated January 3, 1964, with revision "A" dated March 9, 1964, or an FAA Western Region Engineering approved equivalent. (Convair Service Engineering Report No. 240-24 pertains to this same subject.) This directive effective September 7, 1964.
2020-19-05: The FAA is adopting a new airworthiness directive (AD) for certain Bell Helicopter Textron Canada Limited (Bell) Model 505 helicopters. This AD requires inspecting each swashplate assembly bearing (bearing), and depending on the inspection results, removing the bearing from service. This AD was prompted by a report of a bearing that migrated out of the swashplate inner ring. The actions of this AD are intended to address an unsafe condition on these products.
79-06-03: 79-06-03 GULFSTREAM AMERICAN (formerly Grumman American Aviation Corporation): Amendment 39-3437. Applies to Model G-159, all serial numbers; and to Model G-1159, serial numbers 1 through 238 and 775, certificated in all categories. Compliance is required prior to further flight, unless already accomplished. To prevent a potential hazard caused by inability to discharge the engine or APU fire extinguisher bottles, accomplish the following: (1) Inspect the cartridge terminals on each aircraft engine and APU fire extinguisher bottle (container) for the presence of electrical shunts. Shunts are installed for safety in shipping and handling and inadvertently may have been left installed. (2) Remove any electrical shunts found on the cartridge terminals, using procedures in the applicable aircraft maintenance manual. Gulfstream American Alert Customer Bulletins No. 11 for Model G-159, and No. 17 for Model G-1159, both dated February 16, 1979, pertain to this subject. This amendment is effective April 2, 1979.
2003-20-14: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 727-200 series airplanes, that requires installation of four lanyards on the forward access panel/ door. This action is necessary to prevent the forward ceiling access panel/door from falling down and blocking the aisle, which would impede evacuation in an emergency. This action is intended to address the identified unsafe condition.
78-26-05: 78-26-05 PIPER: Amendment 39-3377. Applies to Piper Model PA-36-285 and PA-36-300, Serial Nos. 36-7360001 thru 36-7760123, 36-7760125 thru 36-7860001, 36-7860003, 36-7860007, 36-7860010 thru 36-7860015 36-7860017 thru 36-7860019, 36-7860021 thru 36- 7860024, 36-7860027 thru 36-7860031, 36-7860034, 36-7860036, 36-7860041, 36-7860043 thru 36-7860045, 36-7860047, 36-7860049 thru 36-7860051, 36-7860061 thru 36-7860063, 36- 7860069, 36-7860071, 36-7860073 thru 36-7860079, 36-7860081 thru 36-7860083, 36-7860086 thru 36-7860114 and 36-7860116 and Model PA-36-375, Serial Nos. 36-7802002 thru 36-7802019, 36-7802021 thru 36-7802023, 36-7802025 thru 36-7802029, 36-7802031, 36-7802040 thru 36-7802042 and 36-7802049 certificated in all categories. To prevent hazards in flight associated with the seizing of rod end bearings in the elevator and aileron control systems, accomplish the following: (a) Within the next ten hours in service from the effective date of this AD or upon the attainment of 50 hours total time in service whichever is later, unless previously accomplished within the previous 50 hours, and at intervals not to exceed 50 hours in service from the last inspection, inspect and replace the rod end bearings in the elevator and aileron system controls in accordance with the "Instructions Section - Paragraphs 1 thru 5" of Piper Service Bulletin No. 608 dated July 11, 1975, or equivalent. (b) Equivalent inspections and parts must be approved by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region. (c) Upon the installation of Heim MSS-3D, -4D and -5D rod end bearings for Piper part numbers 452633, 452590 and 452645, respectively, compliance with the inspection requirements of (a) may be canceled. (d) Upon submission of substantiating data by an owner or operator through an FAA Maintenance Inspector, the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region may adjust the inspection intervals specified in this AD.This amendment is effective December 26, 1978.
77-23-09: 77-23-09 PIPER: Amendment 39-3077 as amended by amendment 39-3368. Applies to Models PA-23-250 and PA-E23-250 Serial Numbers 27-2000 to 27-2504 (fuel injected only) and 27-2505 to 27-7754044. Compliance required within 10 hours in service after the effective date of this AD unless already accomplished. In order to prevent fuel flow interruption and engine power loss due to possible adverse fuel vaporization during crossfeed operation, accomplish the following: a. Incorporate the applicable flight manual revision, as listed below, into the FAA-DOA Approved Airplane Flight Manual in accordance with Piper Service Bulletin No. 530: Airplane Flight Manual Revisions No. Model PA-23-250: 27-2000 to 27-2504 Incl. Fuel Injected Only 1204 27-2505 to 27-3943 Incl. 4800# Gross Weight Only 1308 27-2505 to 27-3943 Incl. 5200# Gross Weight Only 1360 27-3837, 27-3944 to 27-4573 Incl. 5200# Gross Weight Only 1520 27-4426, 27-4574 to 27-7554168 Incl. 5200# Gross Weight Only 1630 27-7654001 to 27-7754044 Incl. 5200# Gross Weight Only 1948 Model PA-E23-250: 27-2505 to 27-3943 Incl. 4995# Gross Weight Only 1378 27-3837, 27-3944 to 27-4573 Incl. 4995# Gross Weight Only 1521 27-4574 to 27-7554168 Incl. 4995# Gross Weight Only 1631 b. The Chief, Engineering & Manufacturing Branch, AEA-210, FAA Eastern Region, may adjust the inspection interval specified in this airworthiness directive upon request of an owner or operator submitted with substantiating data through an FAA maintenance inspector. c. The manufacturer's specifications and procedures identified and described in this directive are incorporated herein and made a part hereof pursuant to 5 U.S.C. 552(a)(1). All persons affected by this directive who have not already received these documents from the manufacturer may obtain copies upon request to Piper Aircraft Corp., 820 East Bald Eagle Street, Lock Haven, Pennsylvania 17745. These documents may also be examined at FAA Eastern Region Federal Building, JFK International Airport, Jamaica, New York 11430 and at FAA Headquarters, 800 Independence Avenue, S.W., Washington, D.C. A historical file on this AD which includes the incorporated material in full is maintained by the FAA at its headquarters in Washington, D.C. and at the Federal Aviation Administration, Eastern Region. (Piper Service Bulletin No. 530, dated December 10, 1976, pertains to this subject.) Amendment 39-3077 was effective November 18, 1977. This amendment 39-3368 is effective December 19, 1978.
2020-19-02: The FAA is superseding Airworthiness Directive (AD) 2000-22-19 for Eurocopter France (now Airbus Helicopters) Model SA330F, G, and J helicopters. AD 2000-22-19 required repetitively inspecting certain tail rotor (T/R) blades for skin debonding and a crack. Since the FAA issued AD 2000-22-19, the inspection procedures have been revised. Additionally, the FAA is adding an affected part-numbered T/R blade and the FAA-validation for Model SA330F and G helicopters has been cancelled. This new AD revises the applicability, requires repetitively inspecting affected T/R blades with the new inspection procedures, and depending on the inspection results, repairing or replacing the T/R blade. This new AD also prohibits installing an affected T/R blade unless it has passed the inspections. The actions of this AD are intended to address an unsafe condition on these products.
79-26-02: 79-26-02 BOEING: Amendment 39-3638. Applies to all Model 737-200 (advanced) airplanes with GPWS flap position switches sensing less than 30 degrees as landing flaps, certificated in all categories. Compliance required as indicated. Accomplish the following: \n\tWithin the next 1,200 hours time-in-service or six (6) months, whichever comes first, after the effective date of this AD, change the ground proximity warning system flap position switch to sense flaps 30 degrees and 40 degrees as the landing flap positions, and provide a flap override switch for landings that must proceed with flap position of 25 degrees or less. This modification may be accomplished in accordance with modifications approved by the Chief, Engineering and Manufacturing Branch, FAA Northwest Region, 9010 East Marginal Way South, Seattle, Washington 98108. \n\n\tThis amendment becomes effective December 31, 1979.