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89-03-06: 89-03-06 FOKKER: Amendment 39-6122. Applicability: Model F-27 series airplanes, Serial Numbers 10623 through 10692, in Mark 500 configuration, certificated in any category. Compliance: Required as indicated, unless previously accomplished. To prevent loss of electrical power and eliminate a potential fire hazard, due to chafing wire bundles, accomplish the following: A. Within 60 days after the effective date of this AD, perform a one-time inspection of the upper fuselage cableloom for chafing and insufficient clamping, and repair, if necessary, in accordance with Fokker Service Bulletin F27/24-77, dated June 7, 1988. B. An alternate means of compliance or adjustment of the compliance time, which provides an acceptable level of safety, may be used when approved by the Manager, Standardization Branch, ANM-113, FAA, Northwest Mountain Region. NOTE: The request should be forwarded through an FAA Principal Maintenance Inspector (PMI), who may add any comments and then send it to the Manager, Standardization Branch, ANM-113. C. 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. All persons affected by this directive who have not already received the appropriate service documents from the manufacturer may obtain copies upon request to Fokker Aircraft USA, Inc., 1199 N. Fairfax Street, Alexandria, Virginia 22314. These documents may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or at the Seattle Aircraft Certification Office, 9010 East Marginal Way South, Seattle, Washington. This amendment (39-6122, AD 89-03-06) becomes effective March 6, 1989.
2022-23-10: The FAA is superseding Airworthiness Directive (AD) 2021-06- 03, which applied to all The Boeing Company Model 777F series airplanes. AD 2021-06-03 required deactivating the potable water system. This AD was prompted by a report of a water supply line that detached at a certain joint located above an electronic equipment (EE) cooling filter, leading to water intrusion into the forward EE bay. This AD retains the actions required by AD 2021-06-03 and requires installing a shroud to the water supply line in the forward cargo compartment, and performing a leak test of the potable water system. For certain airplanes, this AD also requires replacing tubes and hoses from the water supply line and installing a shroud to the water return line. The FAA is issuing this AD to address the unsafe condition on these products.
2010-21-13: We are adopting a new airworthiness directive (AD) for the products listed above. This AD requires installing a support bracket and coupler on the left and right wing-to-fuselage transition, and metallic overbraid on the left and right leading edge wire assembly. This AD was prompted by fuel system reviews conducted by the manufacturer, as well as reports that the fuel quantity system was affected by lightning-induced transients. We are issuing this AD to prevent lightning-induced transients to the fuel quantity indication system, which could cause voltage levels to go beyond original design levels between fuel tank probes and structure, and become a potential ignition source at the fuel tank, which, in combination with flammable fuel vapors, could result in a fuel tank explosion and consequent loss of the airplane.
83-04-02: 83-04-02 FOKKER-VFW B.V.: Amendment 39-4569. Applies to Model F28 airplanes serial number 11003 and on. To prevent loss of aileron control, accomplish the following, unless already accomplished within the last three months prior to the effective date of this AD: 1. Within the next 50 hours time in service or one month, whichever occurs first after the effective date of this AD, perform a one time inspection of the aileron control cables in both the R.H. and L.H. wings for airplanes with more than one year's time from the date of manufacture in accordance with the following instructions: a. Open the main landing gear doors and flap shroud doors 81j, 81k, 82j, and 82k. b. Rotate the aileron control wheel in the cockpit to the full left-hand position. c. With the control wheel in this position, inspect the four aileron input cables at location of cable pulleys between stations 3100 and 3600 (illustrated parts catalog, chapter 27-10-01-05). Inspection must be performed with the aid of a mirror and a very strong light otherwise corrosion may remain undetected. d. If wires are broken or there are definite signs of corrosion in the cables, accomplish the actions of paragraph 2. e. Rotate the aileron control wheel in the cockpit to the full right-hand position and repeat the inspections described in paragraphs (c) and (d). 2. If corrosion on the cables is evident from the inspections of paragraph 1, above, accomplish the following: a. Disconnect the cable at the turnbuckle in the wheelwell per the F28 Maintenance Manual, chapter 27-11. b. Pull out the cable at the cable pulleys between stations 3100 and 3600. c. Carefully bend the cable one time at the location of the corrosion over a radius of one inch. If any wire breaks while being bent, replace the cable prior to further flight. d. If no wires failed during the bending test of paragraph 2(c), repeat the test by bending the cable in the opposite direction. If any wire breaks, replace the cable before further flight. e. If the cable is not rejected by the bending tests of paragraphs 2(c) or 2(d), inspect the cable for interior corrosion in accordance with the F28 Maintenance Manual, chapter 20-30-9. f. If interior corrosion is found, replace the cable before further flight. g. Remove any exterior corrosion and treat the cable in accordance with F28 Maintenance Manual, Chapter 20-30-9. h. Reconnect the turnbuckles in the L.H. and R.H. wheelwells and adjust the cable system in accordance with F28 Maintenance Manual, Chapter 27-11-00, and check the aileron for free and smooth operation. 3. Alternate means of compliance which provide an equivalent level of safety may be used when approved by the Manager, Seattle Aircraft Certification Office, FAA, Northwest Mountain Region. 4. 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. 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). This amendment becomes effective March 7, 1983.
2000-15-52: This document publishes in the Federal Register an amendment adopting superseding Airworthiness Directive (AD) 2000-15-52, which was sent previously to all known U.S. owners and operators of Bell Helicopter Textron, Inc. Model (BHTI) Model 204B, 205A, 205A-1, 205B, and 212 helicopters by individual letters. This AD reduces the retirement index number (RIN) life limit for the main rotor mast (mast); increases the RIN factor for masts and main rotor trunnions (trunnions); applies standard RIN factors for all external load lifts; and requires a one-time inspection of the snap ring groove area of the mast. This AD also establishes RIN factors for masts and trunnions that have been previously installed on military or restricted category helicopters and removes from service those masts that have been previously installed with a hub spring. This amendment is prompted by an occurrence of a cracked mast at a lower value than the established RIN life limit. The actions specified by thisAD are intended to preclude the occurrence of fatigue cracks in the damper clamp splined area of a mast. A crack in the damper clamp splined area could result in failure of a mast or trunnion, separation of the main rotor system, and subsequent loss of control of the helicopter.
2016-05-01: We are superseding Airworthiness Directive (AD) 96-12-12, which applies to certain Piper Aircraft, Inc. Models PA-31, PA-31-300, PA-31-325, and PA-31-350 airplanes. AD 96-12-12 requires a one-time inspection of the bulkhead assembly at fuselage station (FS) 317.75 for cracks and the installation of one of two reinforcement kits determined by whether cracks were found during the inspection. This new AD requires repetitive inspections of the bulkhead assembly at FS 317.75 for cracks, repair of cracks as necessary, and the installation of a reinforcement modification. This AD was prompted by cracks found in the FS 317.75 upper bulkhead. We are issuing this AD to correct the unsafe condition on these products.
67-08-04: 67-08-04 FAIRCHILD-HILLER: Amdt. 39-364 Part 39 Federal Register March 7, 1967. Applies to Models F-27 and FH-227 Series Airplanes. Compliance required as indicated. To detect cracks in the elevator torque tube and supporting rings, accomplish the following: (a) Within the next 10 hours' time in service after the effective date of this AD, unless already accomplished, visually inspect the inside area of the elevator torque tube P/N 27-223002-3 between Elevator Stations 11.811 (inboard end rib) and 15.748 (next rib outboard) and the elevator end (inboard) rib and internal elevator structure adjacent to the elevator torque tube for cracks using a mirror and light or an equivalent inspection approved by an FAA maintenance inspector. If a crack is found, comply with (c) before further flight. (b) Within the next 75 hours' time in service after the effective date of this AD, unless already accomplished, inspect the elevator torque tube P/N 27-223002-3 between Elevator Stations 11.811 and 15.748 and the torque tube supporting rings P/N 27-223006-9 (inboard end rib) and P/N 27-223006-3 (next rib outboard) for cracks using X-ray or dye-penetrant with a glass of at least 10-power or an equivalent inspection approved by an FAA maintenance inspector. If a crack is found comply with (c) before further flight. (c) Replace any part found cracked with a part of the same part number that has been inspected for cracks in accordance with (b) or with an equivalent part approved by the Chief, Engineering and Manufacturing Branch, FAA Eastern Region. (d) Upon request of the operator an FAA maintenance inspector may, subject to prior approval of the Chief, Engineering and Manufacturing Branch, FAA Eastern Region, increase the initial compliance times specified in this AD by not more than 5 hours' time in service if the request contains substantiating data to justify the increase for that operator. (Fairchild-Hiller Alert Service Bulletins No. F-27-55-13A and FH-227-55-2A dated February 21, 1967, pertain to this subject.) This directive effective upon publication in the Federal Register for all persons except those to whom it was made effective immediately by telegram dated March 1, 1967.
2000-25-04: This amendment adopts a new airworthiness directive (AD), applicable to certain Raytheon (Beech) Model MU-300, MU-300-10, 400, 400A, and 400T series airplanes, that requires a one-time inspection to detect hydraulic fluid leakage from the B-nut area, which attaches a hydraulic tube to the anti-skid valve assembly, and corrective actions, if necessary; and installation of an additional support for the hydraulic tube. This amendment is intended to prevent an asymmetric braking condition and a longer stopping distance due to sudden loss of normal braking to the left wheel. Such loss of normal braking could result in the airplane overrunning the runway surface. This action is intended to address the identified unsafe condition.
2016-04-12: We are adopting a new airworthiness directive (AD) for certain Turbomeca S.A. Arriel 2B, 2B1, 2C, 2C1, 2C2, 2D, 2E, 2S1, and 2S2 turboshaft engines. This AD requires inspection, and, depending on the results, removal of the engine accessory gearbox (AGB). This AD was prompted by a report of an uncommanded in-flight shutdown (IFSD) of an Arriel 2 engine caused by rupture of the 41-tooth gear, which forms part of the bevel gear in the engine AGB. We are issuing this AD to prevent failure of the engine AGB, which could lead to in-flight shutdown, damage to the engine, and damage to the aircraft.
91-05-14: 91-05-14 AIRBUS INDUSTRIE: Amendment 39-6912. Docket No. 90-NM-92-AD. Applicability: Model A300 B2 and B4 series airplanes, certificated in any category, equipped with the flap ball screwjack no-back mechanisms, as listed in Airbus Industrie Service Bulletin A300-27-172, dated April 10, 1984, which have not been modified in accordance with Modification AI 5240, as described in Airbus Industrie Service Bulletin A300-27-173, dated May 2, 1984. Compliance: Required as indicated, unless previously accomplished. To prevent excessive wear of the carbon friction disc of the no-back assemblies, which could lead to an asymmetric flap condition in the event of flap transmission shaft failure, accomplish the following: A. For airplanes on which flap jamming with one or more affected flap screwjacks has occurred, perform a jackhead axial backlash measurement on the affected flap ball screwjacks in accordance with Airbus Industrie Service Bulletin A300-27-172, dated April 10, 1984, at the earlier of the following: 1. Prior to 13,000 landings; or 2. Within 1,000 landings after November 3, 1987 (the effective date of Amendment 39-5736, AD 87-21-03). B. For airplanes on which flap jamming with any of the affected flap screwjacks has not occurred, perform a jackhead axial backlash measurement on the affected flap ball screwjacks in accordance with Airbus Industrie Service Bulletin A300-27-172, dated April 10, 1984, at the earlier of the following: 1. Prior to 13,000 landings; or 2. Whichever is the later of the following: a. Within 1,000 landings after the effective date of this AD; or b. Within the next "N" number of landings after the effective date of this AD, as determined by the following formula: N = 3,600 - 0.2 x (number of accumulated landings). C. If backlash is found, repeat the measurement required by paragraph A. or B., of this AD, at the following intervals: 1. If the backlash is less than or equalto 0.33 mm, prior to the accumulation of 3,600 landings after the last measurement. 2. If the backlash is more than 0.33 mm but less than or equal to 0.40 mm, prior to the accumulation of 2,000 landings after the last measurement. 3. If the backlash is more than 0.40 mm, but less than or equal to 0.56 mm, prior to the accumulation of 1,000 landings after the last measurement. D. Replace the flap ball screwjack within the next 250 landings when a measurement required by paragraph A. or B. of this AD indicates that the backlash is greater than 0.56 mm. E. Within 18 months after the effective date of this AD, modify the flap ball screwjack assemblies by installing a new carbon friction disc, a modified drive shaft, and a collar to the no-back mechanism, in accordance with Airbus Industrie Service Bulletin A300-27-173, dated May 2, 1984. Installation of this modification constitutes terminating action for the repetitive measurements required by paragraph C. of this AD.NOTE: This Airbus Service Bulletin references Lucas Aerospace Service Bulletin No. 1058-27-1100 for additional modification instructions. F. An alternate means of compliance or adjustment of the compliance time, which provides an acceptable level of safety, may be used when approved by the Manager, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate. NOTE: The request should be submitted directly to the Manager, Standardization Branch, ANM-113, and a copy sent to the cognizant Principal Inspector (PI). The PI will then forward comments or concurrence to the Manager, Standardization Branch, ANM-113. G. Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base in order to comply with the requirements of this AD. All persons affected by this directive who have not already received the appropriate service documents from the manufacturer may obtain copies upon request to Airbus Industrie, AirbusSupport Division, Avenue Didier Daurat, 31700 Blagnac, France. These documents may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 1601 Lind Avenue S.W., Renton, Washington. Airworthiness Directive 91-05-14 supersedes AD 87-21-03, Amendment 39-5736. This amendment (39-6912, AD 91-05-14) becomes effective on April 1, 1991.