Results
96-11-02: This amendment adopts a new airworthiness directive (AD) that applies to Jetstream Aircraft Limited (JAL) HP137 Mk1, Jetstream series 200, and Jetstream Model 3101 airplanes. This action requires repetitively inspecting the spigot housing plate for cracks at the wing/fuselage forward attachment sliding joint, replacing any cracked housing plate, repetitively inspecting the spigots and spigot posts for corrosion and installing improved spigots if corrosion is found that exceeds certain limits, and eventually installing improved spigots if corrosion that does not exceed certain limits is found. For certain affected airplanes, this action requires repetitively inspecting the spigot bushes for migration gaps, replacing the bushes with modified bushes if gaps are found that exceed 0.5 inch, and eventually replacing the bushes with modified bushes if migration gaps are not found. Reports of bush migration gaps found on three of the affected airplanes and another report of corrosion and several cracks found on the spigot housing plate on a Jetstream Model 3101 airplane prompted this action. The actions specified by this AD are intended to prevent structural failure of the wing/fuselage area caused by a cracked or corroded spigot housing assembly.
99-04-20: This amendment adopts a new airworthiness directive (AD) that is applicable to Agusta S.p.A. Model A109K2 helicopters. This action requires replacing a certain Breeze-Eastern rescue hoist (rescue hoist) with a different part-numbered airworthy rescue hoist. This amendment is prompted by an incident in which a rescue hoist cable broke due to cable damage, resulting in one fatality. The actions specified in this AD are intended to prevent the breaking of the rescue hoist cable, personal injury, or entanglement of the rescue hoist cable in the helicopter s main or tail rotor blades, and subsequent loss of control of the helicopter.
97-07-11: This amendment supersedes Airworthiness Directive (AD) 81-20-01, which currently requires repetitively inspecting the nose landing gear (NLG) actuator support structure and the front pressure bulkhead for cracks on Jetstream Aircraft Limited (JAL) HP137 Mk1 and Jetstream series 200 airplanes, and replacing any cracked part. This AD retains the repetitive inspections required by AD 81-20-01; requires repetitively inspecting the NLG retraction jack upper mounting fitting and attachment hardware for security bolt failure and for bolts with improper torque levels on the HP137 Mk1, Jetstream series 200, and Jetstream Model 3101 airplanes, and requires replacing any failed security bolts and adjusting any bolt with an improper torque level; and requires modifying the NLG retraction jack on all affected airplanes, as terminating action for the repetitive inspections. This AD results from reports of NLG jack mounting fitting failures on several of the affected airplanes, and the Federal Aviation Administration's policy on aging commuter-class aircraft. The actions specified by this AD are intended to prevent failure of the NLG caused by a cracked NLG actuator support structure or cracked front pressure bulkhead, which, if not detected and corrected, could lead to nose gear collapse and damage to the airplane.
97-11-08: This amendment adopts a new airworthiness directive (AD), applicable to all Bombardier Model CL-415 series airplanes. This action requires revising the Airplane Flight Manual (AFM) to modify the limitation that prohibits positioning the power levers below the flight idle stop during flight, and to provide a statement of the consequences of positioning the power levers below the flight idle stop during flight. This amendment is prompted by incidents and accidents involving airplanes equipped with turboprop engines in which the propeller ground beta range was used improperly during flight. The actions specified in this AD are intended to prevent loss of airplane controllability, or engine overspeed and consequent loss of engine power caused by the power levers being positioned below the flight idle stop while the airplane is in flight.
97-23-12: This amendment adopts a new airworthiness directive (AD), applicable to certain Fokker Model F28 Mark 0100 and 0070 series airplanes, that requires replacement of the fusible pin in the upper torque link of the main landing gear with an improved pin. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to prevent reduced structural integrity and potential collapse of the main landing gear.
99-16-09: 99-16-09 BELL HELICOPTER TEXTRON CANADA: Amendment 39-11244; Docket No. 98-SW-52-AD. Issued July 28 1999. Applicability: Model 230 helicopters, serial numbers 23001 through 23038, certificated in any category. NOTE 1: This AD applies to each helicopter 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 helicopters 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 (e) 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: Requiredas indicated, unless accomplished previously. To prevent loss of torque of the vertical fin attachment bolts (bolts), which could lead to fracture of the bolts, separation of the vertical fin from the helicopter, and subsequent loss of control of the helicopter accomplish the following: (a) Within 25 hours time-in-service (TIS), verify the torque on the bolts in accordance with Part I of the Accomplishment Instructions of Bell Helicopter Textron Alert Service Bulletin No. 230-98-14, Revision A, dated June 9, 1998 (ASB). (b) On or before the next 150 hour TIS inspection, inspect the vertical fin fitting and tail boom fitting for cracks, elongated bolt holes, distortion, and corrosion in accordance with Part II of the Accomplishment Instructions in the ASB. If elongation of a bolt hole is detected, incorporate the modifications specified in Bell Helicopter Textron Technical Bulletin No. 230- 98-23, Revision A, dated July 1, 1998. (c) After the inspection required by paragraph (b) and after at least 5 hours TIS but within 10 hours TIS, re-verify the torque on the bolts in accordance with Part III, Special Inspections, Step 1 of the Accomplishment Instructions in the ASB. (d) Thereafter, at intervals not to exceed 150 hours TIS, verify the torque of the vertical fin attachment bolts in accordance with the 150 flight hour scheduled inspections, Part III, of the Accomplishment Instructions in the ASB. (e) 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, Rotorcraft Certification Office, Rotorcraft Directorate, FAA. Operators shall submit their requests through an FAA Principal Maintenance Inspector, who may concur or comment and then send it to the Manager, Rotorcraft Certification Office. NOTE 2: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Rotorcraft Certification Office. (f) 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 helicopter to a location where the requirements of this AD can be accomplished. (g) The inspections shall be done in accordance with Bell Helicopter Textron Alert Service Bulletin No. 230-98-14, Revision A, dated June 9, 1998 and Bell Helicopter Textron Technical Bulletin No. 230-98-23, Revision A, dated July 1, 1998. These incorporations by reference were 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 Bell Helicopter Textron Canada, 12,800 Rue de l'Avenir, Mirabel, Quebec JON1LO, telephone (800) 463-3036, fax (514) 433-0272. Copies may be inspected at the FAA, Office of the Regional Counsel, Southwest Region, 2601 Meacham Blvd., Room 663, Fort Worth, Texas; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. (h) This amendment becomes effective on August 24, 1999. NOTE 3: The subject of this AD is addressed in Transport Canada (Canada) AD CF-98- 22, dated August 7, 1998.
98-13-18: This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A319 and A321-100 series airplanes, that requires adjustment of the landing gear unlocked-stop screw; replacement of the shear pins in the reduction gear box and the landing gear pulley assembly with new or serviceable shear pins; a one-time inspection to detect discrepancies of the landing gear cut-out valve; an operational test of the uplock mechanical control system; and follow-on corrective actions, if necessary. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to prevent non-extension of one or more landing gears, consequent damage to the airplane structure, and possible injury to passengers and crewmembers.
97-16-03: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 767 series airplanes, that requires a one-time inspection of the main landing gear (MLG) retaining bolt to ensure that it is installed correctly, and adjustments or repairs, if necessary. This amendment is prompted by a report indicating that a disconnected retaining bolt was found in the MLG forward trunnion joint of a Model 767 series airplane. The actions specified by this AD are intended to prevent aft-acting trunnion loads from being transferred to the MLG beam, and consequent fracture and collapse of the MLG; this condition could result in the loss of control of the airplane on the ground.
98-13-29: This amendment adopts a new airworthiness directive (AD), applicable to all EMBRAER Model EMB-120 series airplanes, that requires revising the Airplane Flight Manual (AFM) to prohibit positioning the power levers below the flight idle stop. This amendment is prompted by incidents and accidents involving airplanes equipped with turboprop engines in which the ground propeller beta range was used improperly during flight. The actions specified by this AD are intended to prevent loss of airplane controllability or engine overspeed with consequent loss of engine power caused by the power levers being positioned below the flight idle stop while the airplane is in flight.
97-18-10: This amendment adopts a new airworthiness directive (AD), applicable to certain Bombardier Model CL-600-2B19 (Regional Jet Series 100) airplanes that requires a one-time inspection of the direct current (DC) power distribution system for reliability, and correction or repair, of any fuse holders and associated electrical wiring, if necessary. This amendment is prompted by a report indicating that a loose fuse holder caused the DC power distribution system to short circuit on one of the affected airplanes, which resulted in a burnt wire between circuit breaker panel CBP-2 and junction box JB7. The actions specified by this AD are intended to prevent such short circuiting, which could result in a burnt wire, smoke entering the cockpit area, and consequent passenger injury due to smoke inhalation.