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88-17-05: 88-17-05 SCHEMPP-HIRTH GMBH: Amendment 39-5982. Applies to Models Nimbus-2B, Janus B, and Mini-Nimbus B gliders certificated in any category. Compliance is required as indicated, unless already accomplished. To prevent failure of the elevator drive bracket and loss of pitch control accomplish the following: (a) Within the next 10 hours time in service (TIS) after the effective date of this AD unless already accomplished, and thereafter at intervals not to exceed 50 hours TIS from the last inspection, visually inspect the elevator drive bracket, P/N 30.055, using a 5-power or greater magnifying glass for cracks in the area adjacent to the welds on both sides of the bracket as shown in Sketch 1 or Sketch 3 of Schempp-Hirth Flugzeugbau GmbH Technical Note (TN) No. 286-24, dated August 14, 1987, for Nimbus-2B gliders, TN No. 295-19, dated August 14, 1987, for Janus B gliders, and TN No. 328-8, dated August 14, 1987, for Mini-Nimbus B gliders. (b) If cracks are found in the elevator drive bracket, replace the elevator drive bracket with elevator drive bracket, Part Number (P/N) 30.055, modification "a", dated August 24, 1987, before further flight. (c) Prior to November 30, 1988, unless already accomplished, replace elevator drive bracket P/N 30.055 with elevator drive bracket P/N 30.055, modification "a", dated August 24, 1987. NOTE: Installation of P/N 30.055, modification "a" is shown in Schempp-Hirth drawing HS5-30.055/1 Elevator-to-Stabilizer Assembly. (d) Upon request an equivalent means of compliance with the requirements of this AD may be approved by the Manager, Brussels Aircraft Certification Office, AEU-100, Europe, Africa, and Middle East Office, FAA, c/o American Embassy, 15 Rue de la Loi B-1040 Brussels, Belgium; telephone 513.38.30, Ext. 2710; or the Manager, New York Aircraft Certification Office, Aircraft Certification Division, Federal Aviation Administration, New England Region, 181 South Franklin Avenue, Room 202, Valley Stream, New York 11581; telephone (516) 791- 6680. (e) Upon submission of substantiating data by an owner or operator through an FAA Airworthiness Inspector, the Manager, Brussels Aircraft Certification Office, or the Manager, New York Aircraft Certification Office may adjust the compliance times specified in this AD. Schempp-Hirth GmbH TN No. 286-24 with 4 attached sketches, TN No. 295-19 with 4 attached sketches, and TN No. 328-8 with 4 attached sketches and 1 attached drawing, all dated August 14, 1987, identified and described in this document, 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 Messrs. Schempp-Hirth, Flugzeugbau GmbH, Krebenstr 25, PostFach 14 43, D-7312 Kircheim/Teck, Federal Republic of Germany. These documents may also be examined at the Office of the Regional Counsel, Federal Aviation Administration, New England Region, 12 New England Executive Park, Burlington, Massachusetts 01803, Room 311, Rules Docket 88-ANE-27, between the hours of 8:00 a.m. and 4:30 p.m., Monday through Friday, except federal holidays. This amendment, 39-5982, becomes effective on August 19, 1988.
69-25-08: 69-25-08 LYCOMING ENGINES: Amdt. 39-892 as amended by Amendment 39-938. Applies to Lycoming GO-435-C2A, GO-480, GSO-480 and IGSO-480 type engines using spline type reduction gear assemblies 72875 and 72879, GO-480 and GSO-480 type engines using flange type reduction gear assemblies 69346, 70412 and 71803 and IGO-540 and IGSO-540 type engines using reduction gear assemblies 72782, 74900, 75679, 76494 and 77731. Compliance required unless already accomplished prior to the accumulation of six hundred (600) hours in service or 100 hours after the effective date of this AD whichever comes later for the GO-435, IGO-540 and IGSO-540 type engines and prior to the accumulation of seven hundred (700) hours in service or 100 hours after the effective date of this AD whichever comes later for GO-480, GSO-480 and IGSO-480 type engines. To prevent failure of the reduction gear assembly a one time inspection is to be accomplished as follows: a. Check torque on reduction gearing pinioncage attaching nut. 1. If found to be in excess of 50 ft.-lbs. remove, inspect for damage and replace the oil retaining housing if necessary. During assembly comply with part (b) using a new lockplate and a pinion cage attaching nut torque of 400 ft.-lbs. When the assembly is disassembled replace thrust bearing oil slinger P/N 68319 with P/N 77454. 2. If found to be less than 50 ft.-lbs. disassemble the assembly and insure that all components meet approved specifications and replace the thrust bearing oil slinger P/N 68319 and P/N 77454 and the oil retaining housing. During assembly comply with part (b) using a new lockplate and a pinion cage attaching nut torque of 400 ft.-lbs. b. If the pinion cage is secured with a spline nut it must be replaced with an approved hexagonal nut. c. If the assembly has been rebuilt using thrust bearing oil slinger P/N 77454, stamp the suffix (-1) to the part number on the reduction gear housing. Lycoming Service BulletinNo. 319A and Lycoming Service Instruction No. 1210A pertain to this subject. Amendment 39-892 effective December 17, 1969. This Amendment (39-938) is effective February 19, 1970.
81-19-04: 81-19-04 RAJAY INDUSTRIES, INC.: Amendment 39-4214. Applies to all affected aircraft, certificated in all categories modified per Rajay Supplemental Type Certificates Aircraft Model Rajay STC No. Aerocommander 500-A STC SA683WE Aerocommander 500-B, 500-S & 500-U STC SA529WE Beech H35, J, K, M, N & P, and 35-33, 35-A33, 35-B33, 35-C33, E33 & F33 STC SA1252WE Beech S35, V35, V35A, V35B, 35-C33A, E33A, E33C, F33A, F33C STC SA2556WE Beech 95, B95, B95A, D95A & E95 STC SA153SO Britten Norman Islander, BN-2, BN-2A, BN-2A-6, BN-2A-8, BN-2A-9 STC SA2243WE Cessna 180-A, B, C, D, E, F, G, H & J STC SA1157WE Cessna 182-A, B, C, D, E, F, G, H, J, K, L, M, N & P STC SA1032WE Cessna 210-A, B, C, 210-5(205), 210-5A(205A) STC SA1098WE Cessna 310-C, D, E, F & G STC SA2383SO Cessna 310-I and J STC SA181SO Evangel 4500-300 Evangel 4500-300, Series II STC SA2657WE Helio Courier H-295 STC SA156SO Helio Courier H-395 STC SA125SO Lake 4 and 4A STC SA2270WE Lake 4-200 STC SA2990WE Mooney 20A, M20B, M20C, M20D & M20G STC SA1156WE Mooney 20E & M20F STC SA1411WE Mooney 20J STC SA3555WE Piper PA-23-160, Apache STC SA1260WE Piper PA-23-160, Apache STC SA4-1637-WE Piper PA-23-235, -250, Aztec "B" STC SA539WE Piper PA-23-250, Aztec "C" STC SA840WE Piper PA-24-250, Comanche STC SA811WE Piper PA-24-400, Comanche STC SA2359WE Piper PA-30 & 39, Twin Comanche STC SA787WE Piper PA-32-260, Cherokee STC SA1557WE Piper PA-32R-300, Lance STC SA3513WE Piper PA-34-200, Seneca STC SA2937WE Compliance required as indicated, unless already accomplished. To prevent failure of the powerplant hoses carrying air, fuel and/or oil and resultant fire hazard, accomplish the following: (a) Within 100 hours' time in service from the effective date of this AD, or prior to return to service after the next annual inspection, whichever occurs first, visually inspect the powerplant fuel, air and oil hose assemblies listed in RajayService Letter No. 28 dated August 3, 1981 to determine the general condition and age of the hose assemblies based upon the metal plate attached to the hose, and; 1) If the hose assembly is five years old or older, replace with like serviceable part prior to further flight. 2) If the hose assembly does not have a metal tag and the age cannot be determined, replace with like serviceable part prior to further flight. 3) Record hose ages in the aircraft engine log book and establish a replacement schedule for affected hoses such that a five year life will not be exceeded. 4) If the hose assembly is deteriorated (regardless of age), replace with like serviceable part prior to further flight. (b) Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate aircraft to a base for the accomplishment of inspections or modifications required by this AD. (c) Alternative inspections, modifications or other actions which provide an equivalent level of safety may be used when approved by the Chief, Engineering and Manufacturing Branch, FAA Western Region. 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. 553(a)(1). All persons affected by this directive, who have not already received these documents from the manufacturer, may obtain copies upon request to Rajay Industries, Inc., 2600 East Wardlow Road, P.O. Box 207, Long Beach, California 90801, telephone (213) 426-0346. 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 FAA Western Region Office. This amendment becomes effective September 17, 1981.
2022-27-09: The FAA is adopting a new airworthiness directive (AD) for certain Airbus Helicopters Model EC130T2 helicopters. This AD was prompted by a crack in the tailboom. This AD requires repetitively inspecting the vibration level on the tail rotor drive shaft and, depending on the results, taking corrective action. This AD also requires reporting information and prohibits installing certain rotor drive shafts unless the inspection is done, 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.
2010-24-03: This amendment adopts a new airworthiness directive (AD) for Robinson Model R22, R22 Alpha, R22 Beta, and R22 Mariner helicopters, and Model R44 and R44 II helicopters. This AD requires visually inspecting each tail rotor (T/R) control pedal bearing block support (support) for a crack, measuring the thickness of each support, installing support safety tabs on certain supports, and replacing supports of a certain thickness during the next 2,200 hour overhaul. This amendment is prompted by two reports of Model R22 helicopters experiencing broken supports during flight, which resulted in the T/R control pedals becoming jammed. The actions specified by this AD are intended to prevent the supports from breaking, which can bind the T/R control pedals, resulting in a reduction of yaw control and subsequent loss of control of the helicopter.
2001-17-09 R1: This amendment rescinds Airworthiness Directive (AD) 2000-17-09, which is applicable to certain McDonnell Douglas Model MD-11 series airplanes. That AD requires an inspection of the upper avionics circuit breaker panel at the main observer's station to detect damage of the wires and to verify the correct routing of the wire bundles; corrective actions, if necessary; and installation of a new clamp, spacer, and sta-straps. The requirements of that AD were intended to prevent chafing in the upper avionics circuit breaker panel of the main observer's station, which could result in arcing and consequent smoke and/or fire in the cockpit. Since the issuance of that AD, the FAA has determined that the improper procedures specified by the service bulletin referenced in that AD could lead to wiring pre-load conditions and consequent wire damage, and arcing in the upper avionics circuit breaker panel. Such conditions could result in arcing and consequent smoke and/or fire in the cockpit.
2001-19-02: This amendment adopts a new airworthiness directive (AD) that is applicable to GE CF34-3A1, -3B, and -3B1 turbofan engines with scavenge screens part numbers (P/N's) 4047T95P01 and 5054T86G02 installed in the B-sump oil scavenge system. This action requires initial and repetitive visual inspections and cleaning of the B-sump scavenge screens. This amendment is prompted by five reports of B-sump oil scavenge system failure causing engine in-flight shutdowns. The actions specified in this AD are intended 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.
2017-04-15: We are adopting a new airworthiness directive (AD) for certain Learjet Inc. Model 36A airplanes. This AD was prompted by a report indicating that an aileron cable failed on an airplane during a tension check and a determination that Model 36A airplanes were not included in AD 2005-13-36, which addresses this issue for other Learjet Inc. airplanes. This AD requires a one-time inspection of the center ball of the aileron control cables for a defective swage, and corrective actions if necessary. We are issuing this AD to address the unsafe condition on these products.
2001-18-13: This amendment adopts a new airworthiness directive (AD) for Eurocopter Deutschland GmbH (Eurocopter) Model EC135 P1 and EC135 T1 helicopters. This action requires, before further flight, adding a copy of this AD or a statement to the Emergency Procedures section of the Rotorcraft Flight Manual (RFM) to inform the pilot to reduce power and land as soon as practicable if a thump-like sound followed by unusual vibration occurs during flight. This action also requires visually inspecting for a crack or a break in certain main rotor drive torque strut (strut) assemblies at specified time intervals and recording details of the inspections in the historical or equivalent record. This AD also requires re-marking and relocating the strut as appropriate and replacing any unairworthy strut assembly with an airworthy strut assembly before further flight. Also, this AD establishes a life limit of 1000 hours time-in-service (TIS) for certain struts with an additional 1000 hours TIS for struts re-marked right-hand (RH) or left-hand (LH) before installing in the new location. This amendment is prompted by a report of a thump-like sound heard during flight followed by unusual vibrations due to failure of the RH strut between the main transmission and the fuselage. The actions specified in this AD are intended to prevent failure of a strut, failure of a worn or ineffective back-up emergency stop, and subsequent loss of control of the helicopter.
82-03-04 R1: 82-03-04 R1 LOCKHEED-CALIFORNIA COMPANY: Amendment 39-4310 as amended by Amendment 39-4810. Applies to Lockheed Model L-1011-385 series airplanes, prior to Serial No. 1239, certificated in all categories. Compliance required as indicated, unless previously accomplished. A. To detect leakage of flammable fluids in areas from which fluids or vapors could reach the auxiliary power unit exhaust shroud, accomplish the following: 1. Within 400 hours time in service from the effective date of this AD, and at repetitive intervals not to exceed 400 hours time in service thereafter, perform leak tests and visual inspections as specified in the Accomplishment Instructions of Lockheed Service Bulletin 093-49- 058 dated July 31, 1981, or later revisions approved by the Manager, Los Angeles Aircraft Certification Office, FAA Northwest Mountain Region. 2. If fuel or hydraulic fluid leakage is detected, repair or replace defective parts or components with serviceable units beforefurther flight. 3. Upon request of an operator, an FAA maintenance inspector, subject to prior approval by the Manager, Los Angeles Aircraft Certification Office, FAA Northwest Mountain Region, may adjust the repetitive inspection intervals specified in this AD to permit compliance at an established inspection period of that operator if the request contains substantiating data to justify the change for that operator. B. To reduce the APU exhaust shroud skin temperature to a safe level, within 5000 flight hours or two (2) calendar years after the effective date of this amendment, whichever occurs first, install the APU Exhaust Duct and Shroud Insulation as specified in Part II, Accomplishment Instructions of Lockheed L-1011 Service Bulletin 093-49-058, Revision 3, dated October 28, 1982, or later revisions approved by the Manager, Los Angeles Aircraft Certification Office, FAA, Northwest Mountain Region. This action terminates the requirements for repetitive inspections required by paragraph A., above. C. Alternate means of compliance with this AD, which provide an equivalent level of safety, may be used when approved by the Manager, Los Angeles Aircraft Certification Office, FAA Northwest Mountain Region. D. 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 required by this AD. All persons affected by this directive who have not already received these documents from the manufacturer may obtain copies upon request to: Lockheed-California Company, P.O. Box 551, Burbank, California 91520, Attention: Commercial Support Contracts, Dept. 63-11, U-33, B-1. These documents also may be examined at FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington 98168, or 4344 Donald Douglas Drive, Long Beach, California 90808. Amendment 39-4310 became effective March 11, 1982. his Amendment 39-4810 becomes effective March 19,1984.