Results
2019-18-07: The FAA is superseding Airworthiness Directive (AD) 2015-17- 14, which applied to all Airbus SAS Model A319 series airplanes; Model A320-211, -212, -214, -231, -232, and -233 airplanes, and Model A321- 111, -112, -131, -211, -212, -213, -231, and -232 airplanes. AD 2015- 17-14 required repetitive rototest inspections of the open tack holes and rivet holes at the cargo floor support fittings of the fuselage, including doing all applicable related investigative actions, and repair if necessary. This AD continues to require the actions of AD 2015-17-14, adds actions for certain airplanes, and reduces the compliance times for certain airplanes, as specified in an European Aviation Safety Agency (EASA) AD, which is incorporated by reference. This AD also reduces the applicability. This AD was prompted by further analysis and widespread fatigue damage (WFD) evaluations which identified the need to reduce the initial compliance times and repetitive intervals for the inspections for certain airplanes, and to add work for certain airplanes. The FAA is issuing this AD to address the unsafe condition on these products.
99-06-13: This amendment supersedes an existing airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-9-80 series airplanes and Model MD-88 airplanes, that currently requires inspection(s) to detect fatigue cracking of the shock strut cylinder of the main landing gear (MLG), and replacement of any cracked shock strut cylinder with a serviceable part. That AD also provides for installation of brake line hydraulic restrictors on the MLG brake systems, which, if accomplished, terminates the repetitive inspections. This amendment requires that the subject inspection be accomplished repetitively following installation of brake line hydraulic restrictors. This amendment is prompted by an additional report of fatigue cracking and subsequent fracturing of the shock strut cylinder of the MLG. The actions specified by this AD are intended to prevent collapse of the MLG due to fracturing of the shock strut cylinder.
83-11-03: 83-11-03 PACIFIC SCIENTIFIC COMPANY, KIN-TECH DIVISION: Amendment 39-4662. Applies to Pacific Scientific flight attendant restraint system rotary buckle assemblies, Part Numbers 1107261-01, -05 and -09, manufactured prior to 1982. Compliance required within 180 days from the effective date of this AD, unless previously accomplished. To prevent the entrapment of occupants caused by the inability to release the restraint system assembly, accomplish the following: a. Inspect flight attendant restraint systems to determine if Pacific Scientific rotary buckle as identified in Figure 1 of Pacific Scientific Service Bulletin 1107261-25-01 is installed. b. If installed, determine if the old lower cover 1107270-01 or the new cover assembly 1107525-01 is installed. The cover is not identified with a part number; however, with the old cover only the two (2) attachment screw heads will be seen. The new cover assembly also has two (2) rivet upsets on the outside of the cover assembly and, in addition, the lap belt and/or inertia reel nameplate should be identified with the letter "M" after the assembly part number. c. If the new cover assembly 1107525-01 is installed, no further action is required per this AD. d. If the old cover 1107270-01 is installed, replace the old cover with the new 1107525-01 cover assembly and stamp or mark a suffix letter "M" next to part number on each lap belt and on inertia reel nameplate. NOTE: Pacific Scientific Service Bulletin 1107261-25-01, Revision 1, dated June 1, 1982, pertains to this subject. e. Alternate inspections, modifications or other actions which provide an equivalent level of safety may be used when approved by the Manager, Western Aircraft Certification Field Office, FAA, Northwest Mountain Region. This amendment becomes effective July 18, 1983.
2006-01-08: The FAA is adopting a new airworthiness directive (AD) for all BAE Systems (Operations) Limited Model Avro 146-RJ airplanes. This AD requires reviewing the airplane's maintenance records to determine if certain tasks of the BAE Systems (Operations) Limited BAe146/Avro RJ Maintenance Planning Document issued May 15, 2004, have been accomplished. This AD also requires doing repetitive detailed inspections of the external fuselage skin adjacent to the longeron at rib 0 from frame 29 to frame 31, and repairing any damage. This AD results from issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. We are issuing this AD to detect and correct cracking of the fuselage skin, which could result in structural failure of the fuselage.
62-21-04: 62-21-04 LOCKHEED: Amdt. 489 Part 507 Federal Register October 3, 1962. Applies to All Model 1649A Aircraft. Compliance required as indicated. As a result of chordwise cracks on the wing lower milled skin at wing Station 590, the following shall be accomplished: (a) Within the next 400 hours' time in service after the effective date of this AD, unless already accomplished within the past 600 hours' time in service, and at periods thereafter not exceeding 1,000 hours' time in service following that initial inspection, inspect from wing Station 580 through wing Station 600, the external lower surface of the aft skin panels, P/N 472066, for any evidence of cracks emanating from the aft edge of the panel through the rear beam attachment holes. Inspection shall be by close visual or dye penetrant means. (b) Any cracks shall be repaired prior to further flight in accordance with Lockheed 1649 Service Bulletin No. 73, Section 1, "Modification Data," and Lockheed Drawing SED61- 9004, or an equivalent method approved by the Chief, Engineering and Manufacturing Branch, FAA Western Region. (c) The periodic inspections may be discontinued following repair per (b) or when an uncracked skin panel has been reinforced in accordance with Lockheed 1649 Service Bulletin No. 73. (d) Upon request of the operator, an FAA maintenance inspector, subject to prior approval of the Chief, Engineering and Manufacturing Branch, FAA Western Region, may adjust the repetitive inspection intervals specified in this AD to permit compliance at an established inspection period of the operator if the request contains substantiating data to justify the increase for such operator. (Lockheed Field Service Letter FS/240893L, dated April 14, 1960, and Lockheed 1649 Service Bulletin No. 73 cover this same subject.) This directive effective November 2, 1962.
99-06-01: This amendment supersedes Airworthiness Directive (AD) 81-15-04 R1, which currently requires repetitively inspecting for cracks at the elevator outboard hinge attachment on the horizontal stabilizer rear spar on certain The New Piper Aircraft, Inc. (Piper) Models PA-31, PA-31-300, PA-31-325, PA-31-350, and PA-31P-350 airplanes, and if cracks are found, incorporating a spar and hinge bracket assembly kit. This AD requires repetitively inspecting the horizontal rear spar in the area of the outboard hinge attachment and the outboard hinge attach bracket for cracks. When cracks are found or at a certain accumulation of time-in-service (TIS), this AD also requires modifying the horizontal stabilizer spar by incorporating an improved stabilizer spar and hinge bracket assembly kit that will terminate the repetitive inspections. This AD is prompted by several field reports of cracks found during routine inspections on airplanes already in compliance with AD 81-15-04 R1. The actions specified by this AD are intended to prevent failure of the horizontal stabilizer rear spar caused by cracks at the elevator outboard hinge attachment, which could result in loss of control of the airplane.
88-18-03: 88-18-03 GARRETT ENGINE DIVISION, ALLIED-SIGNAL, INC. (formerly Garrett Turbine Engine Company, GTEC): Amendment 39-6248. Final copy of priority letter AD issued August 30, 1988. Applicability: Garrett TFE731-3 turbofan engine models installed in airplane models as follows: GARRETT MODEL NO. AIRPLANE MODEL TFE731-3-1C FALCON 50 TFE731-3-1E 731 JETSTAR TFE731-3-1F JETSTAR II TFE731-3-1G WESTWIND 1124 TFE731-3-1H BAe HS125-SERIES TFE731-3-1J CASA 101 TFE731-3-1K JETSTAR II (SPRINGFIELD) TFE731-3A-2B LEARJET 55 TFE731-3A-2B1 LEARJET 55 TFE731-3A-200G WESTWIND 1125 TFE731-3AR-2B LEARJET 55 TFE731-3AR-2B1 LEARJET 55 TFE731-3AR-200G WESTWIND 1125 TFE731-3R-1D SABERLINER 65/65A TFE731-3R-1G WESTWIND 1124 TFE731-3R-1H BAe HS125-SERIES Compliance: Required as indicated, unless already accomplished. To prevent uncontained engine failures, accomplish the following within 25 cycles in service, after the effective date of this AD. (a) Review the engine maintenance records on the above listed engine models to determine if part number 3072316-2 or -3, or 3073110-1 or -2, high pressure turbine rotor (HPTR) disc with one of the following serial numbers is installed. Spare discs must also be checked for applicable part number and serial number. 1-18040-9514 6-12112-960 4-12112-167 6-12112-1938 4-12112-1536 7-12112-875 4-12112-1564 8-12112-199 6-12112-938 9-12112-3862 6-12112-954 9-12112-3878 (b) Inspect and remove from service, if necessary, suspect serial number disc installed in engines in accordance with the accomplishment instructions of Garrett Alert Service Bulletin TFE731-A72-3376, dated August 19, 1988, and replace with serviceable HPTR disc. (c) Inspection of the disc is required per paragraph (b) above, before further flight operation, if a suspect serial number disc is located in a spare engine or as a spare part. (d) 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. (e) Upon submission of substantiating data by an owner or operator through an FAA Airworthiness Inspector, the Manager, Los Angeles Aircraft Certification Office, Transport Airplane Directorate, Aircraft Certification Service, Federal Aviation Administration, 3229 East Spring Street, Long Beach, California 90806- 2425, may approve an equivalent means of compliance or an adjustment of the compliance schedule which provides an equivalent level of safety. The HPTR disc inspection shall be done in accordance with Garrett SB TFE731-A72-3376, dated August 19, 1988. This incorporation by reference was approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR Part 51. Copies may be obtained from Garrett General Aviation Services Division, Distribution Center, 2340 East University, Phoenix, Arizona 85034; telephone (602) 225-2548. Copies may be inspected at the Regional Rules Docket, Office of the Assistant Chief Counsel, Federal Aviation Administration, New England Region, 12 New England Executive Park, Room 311, Burlington, Massachusetts 01803, or at the Office of the Federal Register, 1100 L Street, Room 8301, Washington, DC 20591. This amendment (39-6248) becomes effective on July 21, 1989, as to all persons except those persons to whom it was made immediately effective by Priority Letter AD 88-18-03 issued August 30, 1988, which contained this amendment.
60-23-05: 60-23-05 VERTOL: Amdt. 218 Part 507 Federal Register November 8, 1960. Applies to All 42 and 44 Series Helicopters. Compliance required as indicated. As a result of a recent fatigue failure of the lower directional bellcrank assembly, P/N 22C1611-13, all Vertol parts P/N 22C1611-13 must be retired upon the accumulation of 2,500 hours of time in service. This directive effective November 8, 1960.
2006-01-05: The FAA is adopting a new airworthiness directive (AD) for certain Honeywell International Inc., (formerly AlliedSignal, Inc., formerly Textron Lycoming, formerly Avco Lycoming) T53 turboshaft engines, installed on, but not limited to, Bell 204, Bell 205, Kaman K- 1200 series, Bell AH-1, and Bell UH-1 helicopters, certified under 14 CFR 21.25 or 14 CFR 21.27. This AD requires implementing reduced life limits for certain parts, using cycle counting methods, and using draw- down schedules to replace components that exceed the new limits. This AD results from the manufacturer informing us of test and analysis showing lower calculated service life limits for certain parts, than previously published. We are issuing this AD to prevent failure of certain compressor, gas producer, and power turbine rotating components, which could result in failure of the engine and possible damage to the helicopter.
99-05-15: This amendment adopts a new airworthiness directive (AD) that is applicable to certain Boeing Model 737-100, -200, -200C, -300, -400, and -500 series airplanes. This action requires a one-time inspection of the attachment nuts at each end attachment of the elevator tab push rods to measure run-on torque values, and corrective actions, if necessary. This amendment is prompted by reports of excessive high-frequency airframe vibration during flight, with consequent structural damage to the elevator tab, elevator, and stabilizer. The actions specified in this AD are intended to prevent detachment of an elevator tab push rod due to a detached nut at either end attachment of a push rod, which could result in excessive high-frequency airframe vibration during flight; consequent structural damage to the elevator tab, elevator, and horizontal stabilizer; and reduced controllability of the airplane.