Results
82-23-05: 82-23-05 GULFSTREAM AMERICAN: Amendment 39-4492. Applies to Model 685 (S/Ns 12000 through 12043, and 12045 through 12066) airplanes certificated in any category. COMPLIANCE: Required within 25 hours after the effective date of this AD, unless already accomplished. To prevent possible contamination of cabin air by engine exhaust, accomplish the following: (a) Replace the existing induction air elbow with an improved P/N 610597-501 elbow and inspect the exhaust system in accordance with Gulfstream American Corporation Service Bulletin No. 192 dated August 20, 1982. (b) Airplanes may be flown in accordance with FAR 21.197 to a location where this AD may be accomplished. (c) An equivalent method of compliance with this AD may be used if approved by the Manager, Aircraft Certification Division, ASW-100, Southwest Regional Office, FAA, Fort Worth, Texas 76101; telephone (817) 624-4911, extension 511. This amendment becomes effective on November 15, 1982.
84-02-07: 84-02-07 AVCO LYCOMING WILLIAMSPORT DIVISION: Amendment 39-4856. Applies to Avco Lycoming Model LTS101-600A-2 gas turbine engines. Compliance is required as indicated (unless already accomplished). To prevent power loss and power turbine overspeed, accomplish the following: 1. Replace, concurrently, the output gear assembly and torquemeter gear assembly with a new output gear assembly, part numbers (P/Ns) 4-081-120-10, -15, -16, or -17, and a new torquemeter gear assembly, P/Ns 4-081-070-12, -15, -19, -25, or -26, for those engines which have had the torquemeter gear assembly replaced without concurrent replacement of the output gear assembly, and which presently have output gear assembly P/Ns 4-081-120-11, -12, -13, or -14 installed, within the next 25 operating hours. 2. Replace, concurrently, the output gear assembly and torquemeter gear assembly with a new output gear assembly, P/Ns 4-081-120-10, -15, -16, or -17, and a new torquemeter gear assembly, P/Ns 4-081-070-12, -15, -19, -25, or -26, for those engines which have had the output gear assembly replaced without concurrent replacement of the torquemeter gear assembly, and which presently have output gear assembly P/Ns 4-081-120- 11, -12, -13, or -14 installed, within the next 25 operating hours. 3. Replace, concurrently, the output gear assembly and torquemeter gear assembly with a new output gear assembly, P/Ns 4-081-120-10, -15, -16, or -17, and a new torquemeter gear assembly, P/Ns 4-081-070-12, -15, -19, -25, or -26, for those engines having output gear assembly P/Ns 4-081-120-11, -12, -13, or -14 installed, within the next 100 operating hours or before reaching 1,000 operating hours, whichever occurs later. Aircraft may be ferried in accordance with the provisions of Federal Aviation Regulation (FAR) 21.197 and 21.199 to a base where the AD can be accomplished. Upon request of an operator, an equivalent means of compliance with the requirements of this AD may be approved by the Manager, Engine Certification Office, FAA, New England Region. This amendment becomes effective May 7, 1984, as to all persons except those persons to whom it was made immediately effective by priority letter AD 84-02-07, issued January 27, 1984, which contained this amendment.
2019-23-15: 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 a determination that new or more restrictive airworthiness limitations are necessary. This AD requires revising the existing maintenance or inspection program, as applicable, to incorporate new or more restrictive airworthiness limitations. The FAA is issuing this AD to address the unsafe condition on these products.
72-24-02: 72-24-02 PIPER: Amendment 39-1557. Applies to Model PA-28-140, PA-28-150, PA- 28-160, PA-28-S-160, PA-25 (150 HP) airplanes, equipped with Lycoming O-320 engines and Marvel Schebler carburetors Model MA-4SPA, Part Number 10-3678-32 certificated in all categories. Compliance required within the next 10 hours' time in service after the effective date of this airworthiness directive, unless already accomplished: To prevent power interruption as a result of abrupt throttle movement, accomplish the following: (a) Attach the following operating limitation placard to the instrument panel near the throttle control in full view of the pilot using 1/8" minimum size type: "DO NOT OPEN THE THROTTLE RAPIDLY. (IDLE TO FULL THROTTLE IN 2 SECONDS MINIMUM.)" The placard may be fabricated by the owner/operator. This amendment becomes effective November 17, 1972.
96-01-01: This amendment adopts a new airworthiness directive (AD) that is applicable to Hamilton Standard Propeller Models 14RF-9, 14RF-19, 14RF-21; and 14SF-5, 14SF-7, 14SF-11, 14SFL11, 14SF-15, 14SF-17, 14SF-19, and 14SF-23; and Hamilton Standard/British Aerospace 6/5500/F. This action supersedes priority letter AD 95-18-06 R1, that was issued on August 30, 1995, that currently requires ultrasonic shear wave inspection on all Hamilton Standard 14RF-9 propeller blades, and ultrasonic shear wave inspection on certain Hamilton Standard Propeller Models 14RF-19, 14RF-21; and 14SF-5, 14SF-7, 14SF-11, 14SFL11, 14SF-15, 14SF-17, 14SF-19, and 14SF-23; and Hamilton Standard/British Aerospace 6/5500/F propeller blades. This action requires that all blades of applicable Hamilton Standard propellers be calibrated for ultrasonic transmissibility before conducting the ultrasonic shear wave inspection. This action improves the crack detection capability of the ultrasonic shear wave inspection.This action also decreases the repetitive inspection interval for the 14RF-9, 14SF-5, -7, -11, -15, -17, -19, and -23 from 1,250 flight cycles to 500 flight cycles. This action also establishes a new ultrasonic shear wave inspection interval of 1,000 flight cycles for the 14RF-19 and 2,500 flight cycles for the 14RF-21 and the 6/5500/F. This AD also removes 14SFL11 propellers from service. This AD is prompted by reports that the existing ultrasonic shear wave inspection may not detect cracks as originally determined with some blades due to geometric differences. The actions specified by this AD are intended to prevent separation of a propeller blade due to cracks initiating in the blade taper bore, that can result in aircraft damage, and possible loss of the aircraft.
97-08-04: 97-08-04 AIRBUS INDUSTRIE: Amendment 39-9992. Docket 96-NM-93-AD. Applicability: Model A320-111, -211, -212, and -231 series airplanes, as listed in Airbus Service Bulletin A320-53-1110, dated August 28, 1995; certificated in any category. NOTE 1: This AD applies to each airplane identified in the preceding applicability provision, regardless of whether it has been otherwise modified, altered, or repaired in the area subject to the requirements of this AD. For airplanes that have been modified, altered, or repaired so that the performance of the requirements of this AD is affected, the owner/operator must request approval for an alternative method of compliance in accordance with paragraph (b) of this AD. The request should include an assessment of the effect of the modification, alteration, or repair on the unsafe condition addressed by this AD; and, if the unsafe condition has not been eliminated, the request should include specific proposed actions to address it.Compliance: Required as indicated, unless accomplished previously. To prevent structural damage to the tail section of the airplane when it strikes the runway which, if undetected, could result in depressurization of the fuselage during flight, accomplish the following: (a) Within 6 years after the effective date of this AD, modify the fuselage by reinforcing frames 68 and 69 in accordance with Airbus Service Bulletin A320-53-1110, dated August 28, 1995. (b) 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, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate. Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, Standardization Branch, ANM-113. NOTE 2: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Standardization Branch, ANM-113. (c) Special flight permits may be issued in accordance with sections 21.197 and 21.199 of the Federal Aviation Regulations (14 CFR 21.197 and 21.199) to operate the airplane to a location where the requirements of this AD can be accomplished. (d) The actions shall be done in accordance with Airbus Service Bulletin A320-53-1110, dated August 28, 1995. 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 Airbus Industrie, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. (e) This amendment becomes effective on May 15, 1997.
82-27-01: 82-27-01 McCAULEY ACCESSORY DIVISION: Amendment 39-4520. Applies to all McCauley Accessory Division Model 1A170/FFA fixed pitch propellers installed on, but not limited to, Gulfstream Aerospace Model AA-5B aircraft certificated in all categories. Compliance is required as indicated, unless already accomplished. To prevent propeller failure, accomplish the following: (a) For propellers with 190 or more hours time in service since new or since last dye penetrant type inspection, inspect in accordance with paragraph (c) within the next 10 hours time in service and every 200 hours time in service thereafter. (b) For propellers with less than 190 hours time in service since new or since last dye penetrant type inspection, inspect in accordance with paragraph (c) prior to the accumulation of 200 hours time in service and every 200 hours time in service thereafter. (c) Inspection procedure: (1) Remove propeller from the aircraft and remove spacer from the propeller. (2) Thoroughly remove and clean all paint material down to the anodize surface and inspect the center relief bore (hole), all mounting bolt holes, and all external surfaces in the entire propeller hub area (faces and sides) for cracks using dye penetrant inspection methods. (3) If a crack is found, replace the propeller with a serviceable propeller before further flight. (d) A special flight permit may be issued in accordance with Federal Aviation Regulations (FARs) 21.197 and 21.199 to operate the aircraft to a base where this AD can be accomplished. (e) Upon request of the operator, an equivalent means of compliance with the requirements of this AD may be approved by the Manager, Chicago Aircraft Certification Office, FAA, 2300 East Devon Avenue, Des Plaines, Illinois 60018. This AD supersedes Amendment 39-3689 (45 FR 8947), AD 80-04-05. This amendment becomes effective December 30, 1982.
95-04-12: 95-04-12 AIRBUS INDUSTRIE: Amendment 39-9164. Docket 95-NM-14-AD. Applicability: Model A310 and A300-600 series airplanes on which Airbus Modification 10156 has not been accomplished, and Model A320 series airplanes on which Airbus Modification 22561 or Airbus Service Bulletin A320-26-1017 has not been accomplished; certificated in any category. This AD is not applicable to airplanes on which the air extraction system is not configured to detect smoke in the extracted air. (That is, airplanes that do not have standard air extraction systems are not subject to the requirements of this AD.) NOTE 1: This AD applies to each airplane identified in the preceding applicability provision, regardless of whether it has been modified, altered, or repaired in the area subject to the requirements of this AD. For airplanes that have been modified, altered, or repaired so that the performance of the requirements of this AD is affected, the owner/operator must use the authority provided in paragraph (b) to request approval from the FAA. This approval may address either no action, if the current configuration eliminates the unsafe condition; or different actions necessary to address the unsafe condition described in this AD. Such a request should include an assessment of the effect of the changed configuration on the unsafe condition addressed by this AD. In no case does the presence of any modification, alteration, or repair remove any airplane from the applicability of this AD. Compliance: Required as indicated, unless accomplished previously. To prevent failure of the lavatory smoke detection system to detect smoke in the lavatory, accomplish the following: (a) Within 450 flight hours after the effective date of this AD, perform an inspection of each lavatory to verify proper installation of the grille over the air extraction duct of the lavatories, and to detect blockage in the air extraction duct of the lavatories, in accordance with Airbus All Operators Telex (AOT) 26-12, Revision 1, dated July 4, 1994. (1) If the grille is found to be properly installed and if no blockage is found, repeat the inspection thereafter whenever the cover over the air extraction duct of the lavatories or any ceiling louver (grille) of the ceiling light in the lavatory is removed or replaced for any reason. (2) If the grille is found to be improperly installed and/or if blockage is found, prior to further flight, correct any discrepancies found, in accordance with Airbus AOT 26-12, Revision 1, dated July 4, 1994. Repeat the inspection thereafter whenever the cover over the air extraction duct of the lavatories or any ceiling louver (grille) of the ceiling light in the lavatory is removed or replaced for any reason. (b) 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, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate. Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, Standardization Branch, ANM-113. NOTE 2: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Standardization Branch, ANM-113. (c) Special flight permits may be issued in accordance with sections 21.197 and 21.199 of the Federal Aviation Regulations (14 CFR 21.197 and 21.199) to operate the airplane to a location where the requirements of this AD can be accomplished. (d) The inspections and correction of discrepancies shall be done in accordance with Airbus AOT 26-12, Revision 1, dated July 4, 1994. 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 Airbus Industrie, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. (e) This amendment becomes effective on March 17, 1995.
2019-23-13: The FAA is adopting a new airworthiness directive (AD) for certain Airbus SAS Model A320-251N and A321-253N airplanes. This AD was prompted by reports of cracks on the pylon block seals. This AD requires replacement of the pylon block seals, 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.
72-21-03: 72-21-03 PIPER: Amdt. 39-1533. Applies to all PA-20 type aircraft S/N 20-1 and up and PA-22 type aircraft S/N 22-1 to 22-9393 inclusive. Compliance required within 100 hours in service or at next annual inspection, whichever occurs first, after the effective date of this AD unless already accomplished. To prevent potential in-flight fire due to fuel line failure, accomplish the following: Identify the flexible fuel line assembly routed from fuel strainer to the carburetor. A metal identification band permanently affixed to each line may be used for this purpose. Replace any P/N 70322-32 hose assembly with P/N 17766-66 hose assembly or an equivalent part approved by the Chief, Engineering and Manufacturing Branch, FAA Eastern Region. If the fuel line cannot be identified, it shall also be replaced with P/N 17766-66. Installation and routing of replacement hose assemblies shall be accomplished so as to prevent abrasion, interference chafing, and heat damage.Upon request, and submission of substantiating data through an FAA Maintenance Inspector, the Chief, Engineering and Manufacturing Branch, FAA Eastern Region, may adjust the compliance time specified in this AD. (Piper Service Bulletin No. 351 dated 3 May 1972 pertains to this subject.) This amendment is effective October 13, 1972.