Results
99-06-04: This amendment adopts a new airworthiness directive (AD), applicable to Eurocopter France Model AS 332C, L, L1, and L2 helicopters that requires replacing certain circuit breakers. This amendment is prompted by the manufacturer discovering, upon testing a circuit breaker installed in a helicopter, the loss of electrical continuity between the terminals of the installed circuit breaker. The actions specified by this AD are intended to prevent loss of electrical power caused by improper installation of certain circuit breakers, loss of electrical power to instrumentation, and subsequent loss of control of the helicopter.
2022-12-08: The FAA is adopting a new airworthiness directive (AD) for certain Robinson Helicopter Company Model R22 BETA, R44, and R44 II helicopters. This AD was prompted by reports of intermittent or abnormal operation of the engine revolutions per minute (RPM) governor (governor). This AD requires inspecting the engine RPM sensor wiring and installing a wiring kit. The FAA is issuing this AD to address the unsafe condition on these products.
2022-11-15: The FAA is adopting a new airworthiness directive (AD) for all Rolls-Royce Deutschland Ltd & Co KG (RRD) Trent 7000-72 and Trent 7000- 72C model turbofan engines. This AD was prompted by in-service experience showing that certain high-pressure turbine (HPT) blades may prematurely deteriorate to an unacceptable condition when managed in accordance with the inspection intervals in the Time Limits Manual (TLM). This AD requires initial and repetitive on-wing borescope inspections (BSIs) of the HPT blades to detect axial cracking and, depending on the results of the inspections, replacement of the HPT blade set, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference (IBR). The FAA is issuing this AD to address the unsafe condition on these products.
99-06-03: This amendment adopts a new airworthiness directive (AD), applicable to Eurocopter France Model AS-365N, N1, and N2 helicopters, that requires inspecting the helicopter to determine if a certain main rotor head frequency adapter (frequency adapter) is installed and, if so, replacing it with an airworthy frequency adapter. This amendment is prompted by a report of disbonding of the metal center section of a frequency adapter from the elastomer on a main rotor head caused by a lack of adherence during the production process. The actions specified by this AD are intended to prevent increased vibrations caused by disbonding of the center section of a frequency adapter from the elastomer and subsequent reduced controllability of the helicopter.
99-05-06: This amendment supersedes an existing airworthiness directive (AD), applicable to certain Boeing Model 747 series airplanes, that currently requires a one-time inspection to detect cracking and corrosion of various areas at all four nacelle struts; and repair, if necessary. This amendment requires new repetitive inspections to detect fatigue cracking or loose or missing fasteners of the aft torque bulkheads of the outboard nacelle struts; and repair, if necessary. In addition, this action expands the applicability of the existing AD to include additional airplanes. This amendment is prompted by a report indicating that cracking was found in the aft torque bulkheads of the outboard nacelle struts, and by the availability of new service instructions for detecting fatigue cracking that would not have been detected by the required actions of the existing AD. The actions specified in this AD are intended to detect and correct such fatigue cracking and loose or missing fasteners, which could result in failure of an outboard nacelle strut diagonal brace load path and possible separation of the nacelle from the wing.
65-26-01: 65-26-01 FAIRCHILD: Amdt. 39-157 Part 39 Federal Register November 17, 1965. Applies to Model F-27 Series Airplanes. Compliance required as indicated. To prevent further corrosion of the magnesium aileron control sectors, accomplish the following: (a) For airplanes with aileron sectors, P/N's 27-727207-21, 27-727208-21, 27-727209-21, 27-727300-21, and 27-727381-21, with two or more years installed time on the effective date of this AD, comply with (c) within the next four weeks after the effective date of this AD, unless already accomplished within the last twelve weeks. (b) For airplanes with aileron sectors specified in (a), with less than two years installed time on the effective date of this AD, comply with (c) before the accumulation of two years and four weeks installed time, unless already accomplished within the last twelve weeks. (c) Visually inspect all surfaces of each aileron sector for corrosion. NOTE. - Aileron sectors, P/N's 27-727207-21, 27-727208-21, and 27-727209-21 are located under the cockpit floor, on the auxiliary shaft at Fuselage Station 129.917, approximately 20 inches to the left and right of the center of fuselage. Aileron sector, P/N 27-727300-21, is located in the left wing center section at Wing Station 54.135, and is mounted on the aft face of the wing rear spar. Aileron sector, P/N 27-727381-21, is located in both the left and right wing outer panel, at Wing Station 398.320 and is mounted on the aft face of the wing rear spar. During the inspection required by (c), particular attention should be given to the cable groove, ball socket and ball sleeve. (1) If corrosion is found, before further flight except that the airplane may be flown in accordance with FAR 21.197 to a base where the repair can be made: (i) Replace the part with an unused part of the same part number or an equivalent approved by the Chief, Engineering and Manufacturing Branch, FAA Eastern Region, and comply with (c) within two years from the inspection; (ii) Replace the part with Fairchild Hiller aluminum aileron sector P/N 27-727207-23, 27-727208-23, 27-727209-23, 27-727300-23, or 27-727381-23 as applicable, or an equivalent approved by the Chief, Engineering and Manufacturing Branch, FAA Eastern Region; or (iii) Remove the corrosion in accordance with (d) and reinspect in accordance with (c) at intervals not to exceed 16 weeks from the last inspection. If corrosion is found, comply with (c)(1). (2) If no corrosion is found, comply with (c) within one year from the inspection. (d) Remove corrosion from aileron sectors, P/N's 27-727207-21, 27-727208-21, and 27-727209-21, in accordance with Fairchild Service Letter No. 311, dated April 12, 1965, or later FAA-approved revision or an FAA-approved equivalent; from aileron sector, P/N 27-727300-21, in accordance with Fairchild Service Letter No. 307 dated September 17, 1963, or later FAA-approved revision or an FAA-approved equivalent; from aileron sector P/N 27-727381-21, in accordance with Fairchild Service Letter No. 306, dated August 22, 1963, or later FAA-approved revision or an FAA-approved equivalent. (e) Upon request of the operator, an FAA maintenance inspector, subject to prior approval of the Chief, Engineering and Manufacturing Branch, FAA Eastern 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. This directive effective December 17, 1965.
2022-11-12: The FAA is adopting a new airworthiness directive (AD) for certain Viking Air Limited (type certificate previously held by Bombardier Inc. and de Havilland, Inc.) Model DHC-6-1, DHC-6-100, DHC- 6-200, DHC-6-300, and DHC-6-400 airplanes. This AD was prompted by mandatory continuing airworthiness information (MCAI) originated by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI identifies the unsafe condition as binding of the rod end bearing connecting the lower fuel control unit (FCU) push rod assembly to the FCU power lever. This AD requires performing tests, inspections, and lubrication of the FCU push rod assemblies, and replacing them with improved parts as necessary. The FAA is issuing this AD to address the unsafe condition on these products.
2013-16-17: We are adopting a new airworthiness directive (AD) for all The Boeing Company Model 727, 727C, 727-100, 727-100C, 727-200, and 727- 200F series airplanes. This AD was prompted by a structural re- evaluation by the manufacturer, which identified elements within the wing trailing edge flap area that qualify as structural significant items (SSIs). This AD requires revising the maintenance inspection program to include inspections that will give no less than the required damage tolerance rating (DTR) for certain SSIs, and repairing any cracked structure. We are issuing this AD to detect and correct fatigue cracking of the wing trailing edge structure, which could result in compromised structural integrity of the airplane.
99-05-09: This amendment adopts a new airworthiness directive (AD) that applies to certain The New Piper Aircraft, Inc. (Piper) PA-23, PA-24, PA-28, PA-32, and PA-34 series airplanes that incorporate certain Facet (manufactured by the Purolator Products Company) induction air filters. This AD requires replacing these induction air filters. This AD results from reports of cracking, splitting, crumbling, and deterioration (referred to as damage hereon) of Facet/Purolator induction air filters manufactured between a certain time period. The actions specified by this AD are intended to prevent pieces of a damaged induction air filter from being ingested into the engine, which could result in reduced or loss of engine power. Comments for inclusion in the Rules Docket must be received on or before April 28, 1999.
2022-11-18: The FAA is adopting a new airworthiness directive (AD) for all Airbus Helicopters Model AS355E, AS355F, AS355F1, AS355F2, AS-365N2, AS 365 N3, SA-365N, SA-365N1, EC 155B, and EC155B1 helicopters. This AD was prompted by investigation results from an engine compartment fire, which determined some of the internal parts of the engine upper fixed cowling (engine cowling) were painted with finish paint on top of the primer layer. This AD requires a one-time inspection of certain part- numbered engine cowlings, and corrective actions if necessary, 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.
73-10-02: 73-10-02 BENDIX: Amendment 39-1634. Applies to Bendix Fuel Injectors Models RSA-5AD1, RSA-51B1 and RSA-10AD1 installed on Lycoming Engines Models: IO540-C1B5, -C1C5, -C2C, -C4B5, -C4C5, -D4A5, -D4B5, -J4A5, -L1A5, -M1A5, -M2A5D, -N1A5, -R1A5; IO360-A1A, -A1B, -A1B6, -A1B6D, -A1C, -A1D, -A1D6, -A2A, -A2B, -A2C, -B1B, -B1C, -B1D, -B1E, -B1F, -B2E, -B2F, -B4A, -C1A, -C1B, -C1C, -C1D6, -C1E6, -C1F, -D1A, -E1A, -F1A; IO-320-A1A, -A2A, -E2A, -B1A, -B1B, -B1C, -B1D, -B2A, -C1A, -D1A, -D1B, -E2B; AIO-320-A1A, -A1B, -A2A, -A2B, -B1B, -C1B; LIO-320-B1A, -C1A; IGO-480-A1A6; IVO-360-A1A; HIO-360-A1A, -B1A, -B1B, -C1A, -C1B; AIO-360-A1A, -A2A, -A1B, -A2B, -B1B; LIO-360-C1E6; IO-720-A1A, -B1A; IVO-540-A1A; TIO-540-A1A, -A1B, -A1C, -A2A, -A2C, -A2B, -A1A, -B1A, -C1A, -E1A, -G1A, -H1A; TIO-360-A1A, -A1B, -A3B6; and IO-720-A1B, -C1B. Compliance required within the next 25 hours time in service after the effective date of this Airworthiness Directive, and at each subsequent installation of the subject Fuel Injectors. To detect defective diaphragm assemblies, Bendix P/N 2529470, in Bendix Fuel Injectors, accomplish the following: a) Determine from the airplane and engine logbooks whether the fuel injector has been repaired and/or overhauled between September 30, 1972, and February 28, 1973. If it is established that the fuel injector has not been repaired and/or overhauled between September 30, 1972, and February 28, 1973 record compliance with Paragraph "a" of this Airworthiness Directive in the engine logbook. b) If the fuel injector has been repaired and/or overhauled between September 30, 1972, and February 28, 1973, unless already accomplished, inspect the fuel injector in accordance with Bendix Service Bulletin No. RS-41 dated February 13, 1973, Bendix Service Bulletin No. RS-41 revised April 7, 1973, or subsequent FAA approved revisions; or by any other method approved by the Chief, Engineering and Manufacturing Branch, Great Lakes Region. Indicate compliance on airworthy parts by stamping a "T" after the fuel injector serial number, and record compliance in the engine logbook or return to service statement. Replace or repair fuel injectors having defective diaphragms with airworthy fuel injector units. NOTE: Only appropriately rated FAA approved repair stations are authorized to perform the inspection in "b" above. This amendment is effective May 16, 1973.
99-04-24: This amendment adopts a new airworthiness directive (AD), applicable to certain Aerospatiale Model ATR72 series airplanes, that requires a one-time inspection to detect damage of certain anchor nuts located on the upper surface of the wings, and replacement of the anchor nuts with new or serviceable nuts, 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 failure of anchor nuts on the upper surface of the wings, which could result in reduced structural integrity of the airplane.
74-26-08: 74-26-08 ROCKWELL INTERNATIONAL: Amendment 39-2051. Applies to NA265- 40, NA265-60, NA265-70 (CT-39E, CT-39G) series airplanes certificated in all categories. Compliance required as indicated. To preclude inflight engine shutdown due to loss of oil quantity because of an unknown incipient failure condition in the engine oil low pressure switch, (Hydra-electric, P/N 12252), accomplish the following: (1) Within ten flight hours after receipt of this AD, unless already accomplished, inspect each engine installation to determine if Hydra-electric P/N 12252, is installed. If found installed remove Hydra-electric P/N 12252 and; (a) Replace with Hydra-electric P/N 12252-1, or, (b) Install Aero Instruments Co. P/N 1B2522-230, or Century Electronics and Instrument Inc. P/N 1B2522-230; or (c) Install O-ring NAS 617-4 and plug MS 9015-04 or an 814-4L. Safety wire with proper lockwire. Disconnect the electric connector cap, and stow in accordance with good maintenance practice. See (d)(ii) and (e) below for placard installation. (d) If both engine oil low pressure switches are removed and plugged; (i) The amber "OIL PRESS LOW" caution light must be modified by either removing the light cover and replacing with a blank cover or installing an "INOPERATIVE" placard over the light cover, and, (ii) Install, in front of and in full view of the crew, a placard which reads: "ENGINE LOW OIL PRESSURE WARNING SYSTEM INOPERATIVE. MONITOR OIL PRESSURE GAGES." (e) If one engine oil low pressure switch is removed and plugged, install in front of and in full view of the crew, a placard which reads: "(LEFT OR RIGHT) ENGINE LOW OIL PRESSURE WARNING SYSTEM INOPERATIVE. MONITOR (LEFT OR RIGHT) OIL PRESSURE GAGE." Note: Sabre Gram, dated November 15, 1974, covers this subject. (2) Within sixty days after receipt of this AD, install new engine oil low pressure switch, Hydra-electric P/N 12252-1 or Aero Instruments Co. or Century Electronics and Instrument Inc. P/N 1B2522-230, in those positions where Hydra-electric P/N 12252 was removed, and plugs have been installed. Reconnect the electrical connector and accomplish functional check before return to service. (3) Remove placards and reactivate "OIL PRESS LOW" caution light when (2), above, has been accomplished. (4) Airplanes may be flown to a base for the performance of the inspections and installations required by paragraph one of this AD, per FAR's 21.197 and 21.199. (5) Return P/N 12252 switches removed from service to Rockwell-International, Aviation Service Division, Lambert Field, St. Louis, Mo. 63l45 (6) Equivalent inspections and installations may be approved by the Chief, Aircraft Engineering Division, FAA Western Region, upon submission of adequate substantiating data." This amendment is effective December 24, 1974, for all persons except those to whom it was made effective immediately by airmail letter dated November 27, 1974.
2013-16-12: We are adopting a new airworthiness directive (AD) for certain Bombardier, Inc. Model DHC-8-102, -103, and -106 airplanes. This AD was prompted by a report of cracking in a lower longeron in a nacelle. This AD requires repetitive inspections for cracking of the lower longerons in the nacelles, and replacement with new longerons or repair if necessary. [[Page 51051]] Additionally, this AD specifies an optional terminating action. We are issuing this AD to detect and correct such cracking, which could result in degradation of the structural integrity of the nacelle and possible collapse of the main landing gear (MLG).
2013-16-15: We are adopting a new airworthiness directive (AD) for all General Electric Company (GE) model GEnx-2B67B turbofan engines with booster anti-ice (BAI) air duct, part number (P/N) 2469M32G01, and support bracket, P/N 2469M46G01, installed. This AD was prompted by reports of cracks in the BAI air duct. This AD requires initial and repetitive visual inspections of the BAI air duct, removal from service of the BAI air duct if it fails inspection and, as a mandatory terminating action, the installation of new BAI air duct support brackets. We are issuing this AD to prevent failure of the BAI air duct, resulting in an in-flight shutdown of one or more engines, loss of thrust control, and damage to the airplane.
99-04-22: This amendment adopts a new airworthiness directive (AD) that is applicable to all Boeing Model 727, 727-100, 727-200, 727C, 727-100C, and 727-200F series airplanes. This action requires repetitive inspections to detect cracking of the lower skin panel at the lower row of fasteners in certain lap joints of the fuselage, and repair, if necessary. This amendment also provides for optional terminating action for certain repetitive inspections. This amendment is prompted by a report of fatigue cracking in the lower skin panel at the lower row of fasteners of the fuselage lap joints. The actions specified in this AD are intended to detect and correct such fatigue cracking, which could result in sudden fracture and failure of the lower skin lap joints, and rapid decompression of the airplane.
71-20-08: 71-20-08 BRITISH AIRCRAFT CORPORATION: Amdt. 39-1297. Applies to Model Viscount 810 airplanes. Compliance is required as indicated. (a) For airplanes that have accumulated 25,000 or more landings on the effective date of this AD - (1) Before further flight install an operating limitation placard in the pilot's compartment in clear view of the pilot prohibiting further flight at a cabin pressure differential exceeding 3.5 p.s.i.; and (2) Within the next 50 landings after the effective date of this AD, comply with paragraph (d). (b) For airplanes that have accumulated 20,000 or more landings, but less than 25,000 landings on the effective date of this AD - (1) Before further flight install an operating limitation placard in the pilot's compartment in clear view of the pilot prohibiting further flight at a cabin pressure differential exceeding 4.5 p.s.i.; and- (2) Within the next 100 landings after the effective date of this AD, comply with paragraph (d). (c) For airplanes that have accumulated less than 20,000 landings on the effective date of this AD, before the accumulation of 20,000 landings or before the accumulation of 100 landings after the effective date of this AD, whichever occurs later, comply with paragraph (d). (d) Inspect the rear pressure bulkhead boundary member around the complete circumference of the boundary member for cracks, by an x-ray radiographic method which uses approximately 80 KV perpendicular to the forward inside bend radius of the boundary member. (e) If any cracks in the boundary member are found during the inspection required by paragraph (d), before further flight repair the cracked boundary member - (1) By reinforcing the cracked portion of the boundary member with a length of serviceable boundary member section which extends at least three inches beyond the extremities of any crack; or - (2) By replacing the cracked portion with a length of serviceable boundary member section;connecting the replacement section by typical type joint plates. (f) The placard required by paragraph (a) or (b) may be removed after paragraph (d) and paragraph (e), if applicable, have been accomplished. (g) For purposes of complying with this AD, subject to acceptance by the assigned FAA maintenance inspector, the number of landings may be determined by dividing each airplane's hours' time in service by the operator's fleet average time from takeoff to landing for the airplane type. (BAC campaign wire SS 1093V refers to this subject). This amendment is effective upon publication in the Federal Register as to all persons except those persons to whom it was made effective immediately upon receipt of the airmail letter dated August 13, 1971, which contained this amendment.
99-04-12: This amendment adopts a new airworthiness directive (AD), applicable to McDonnell Douglas Helicopter Systems (MDHS) Model 369D, 369E, 369FF, 369H, MD500N, and MD600N helicopters, that requires a one-time visual inspection of certain input shaft coupling assemblies for pitting. This amendment is prompted by three operators' reports of discovering pitting on the internal spline teeth. The actions specified by this AD are intended to prevent failure of the spline teeth in the input shaft coupling assembly, loss of drive to the main rotor system, and subsequent loss of control of the helicopter.
2013-15-16: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 737-600, -700, -700C, -800, -900, and -900ER series airplanes. This AD was prompted by a report of an inboard main landing gear (MLG) door assembly departure due to premature fatigue cracking in the inboard MLG door hinge fittings. This AD requires repetitive inspections for cracking of the inboard MLG door hinge fittings; and replacement or modification of cracked fittings. This AD also provides an option to remove the affected MLG door. We are issuing this AD to detect and correct fatigue cracking in the inboard MLG door hinge fittings, which could result in loss of the MLG door assembly from the airplane, and the MLG door assembly could impact the flight control surfaces and result in reduced controllability of the airplane.
99-07-10 R1: We are rescinding an airworthiness directive (AD) for PIAGGIO AERO INDUSTRIES S.p.A. Model P-180 airplanes. The rescinded AD resulted from mandatory continuing airworthiness information (MCAI) originated by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as partial detachment of the inner protective film of the composite nacelles. Since issuance of the rescinded AD, we have determined that the unsafe condition does not exist or is not likely to develop on affected type design airplanes.
99-04-10: This amendment adopts a new airworthiness directive (AD), applicable to any transport category airplane that is equipped with certain Day-Ray fluorescent light ballasts installed in the upper and/or lower cabin sidewall, that requires a visual inspection to determine the type of fluorescent light ballasts installed in the cabin sidewall, and the replacement of suspect ballasts with new or serviceable ballasts. This amendment is prompted by reports of smoke, fumes, and/or electrical fire emitting from the baggage bin of the aft passenger compartment due to the failure of the fluorescent light ballasts. The actions specified by this AD are intended to prevent fire in the passenger compartment resulting from failure of the fluorescent light ballast of the cabin sidewall.
80-09-08 R2: 80-09-08 R2 FAIRCHILD AIRCRAFT CORP. (Swearingen): Amendment 39-3758 as amended by amendment 39-3883 is further amended by amendment 39-5821. Applies to Models SA 226-TC (S/N TC201 through TC419) and SA 226-AT (S/N AT001 through AT074) certificated in any category. Compliance required before pressurized flight or prior to obtaining 250 unpressurized flight hours after compliance with emergency telegraphic AD T80SW14 dated March 15, 1980, amended. To assure proper adjustment, operation, and structural integrity of the cargo door latching mechanism, accomplish the following: (a) With the cargo door open, conduct the following inspection to assure full expansion of the click-clack latch jaws. Move the door handle to the door closed position. Using a "go, no-go" type of gage, determine that the distance from the inside of the click-clack plunger face to the edge of the click-clack jaws is not less than 0.34 inches. Adjust each latch as necessary to gain a minimum of 0.34 inches by varying the length of its connecting push-pull rod. (b) To assure proper engagement of the click-clack jaws into the door frame receptacle, three measurements are necessary. The first measurement (door open) is the dimension from the door face plate surface to the undercut on the click-clack jaws. The second measurement (door open) is the dimension from the door frame receptacle face plate surface to the jaws seating surface. The third measurement (door closed) is the gap (taken with a feeler gage) between the surface of the door frame receptacle and the door face plate surface. The first dimension must be at least the sum of the second and third dimensions to assure proper engagement of the click-clack jaws in the door frame receptacle. Adjust each latch as necessary to gain the proper click-clack engagement by varying the length of its connecting push-pull rod. (c) Inspect each door face plate and receptacle face plate for evidence of deformation. If deformed, also inspect door frame and door latch assembly for evidence of cracks or deformation. If such defects are detected, replace with airworthy part. (d) Using an inside micrometer, or equivalent, measure the inside diameter of each receptacle. Measure across the hole in at least three directions to check for roundness. The widest dimension must be used to compare with the following allowables. (1) Receptacles on side of cargo door, one piece type, limit 0.690 inches. (2) Receptacles on side of cargo door, eccentric type, limit 0.700 inches. (3) Receptacles on bottom of cargo door, one piece type, limit 0.670 inches. (4) If any receptacle is oversized, replace with an airworthy part. (e) Check the cargo door warning system as follows: (1) With the door in the open position, manually depress all door warning switches. Check to see that the cargo door warning light in the annunciator panel is extinguished. (2) Selectively release and depress each warning switch. Check that with all other switches depressed, releasing any individual switch causes illumination of the cargo door warning light. Actuate each switch several times while checking for any tendency for the switch to stick in the depressed position. (3) Any switches that show any tendency to stick in the depressed position should be replaced. (f) After the inspections and adjustments required by paragraphs (a) through (e) have been satisfactorily completed, open and close the cargo door a minimum of three cycles. (1) Operate the door handle to the closed position during each door closed cycle. (2) Door open light on annunciator panel must be out when door is closed. (Reference Swearingen SA226 series maintenance manual for proper switch adjustment.) (3) If the door mechanism or warning light system does not function properly during the three open and close cycles, reconduct inspections and adjustments as described above. (g) Repeat the steps as necessary until the cargo door operates properly. (h) Repeat the inspections and adjustments required by paragraph (a) through (g) of this AD as follows: (1) Each 1,200 flight hours for airplanes which have been modified per Fairchild SB 226-52-008 revised April 6, 1984, or (2) Each 250 flight hours for airplanes that have not been modified per the above SB. (i) Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes unpressurized to a base where the inspections and adjustments can be accomplished. (j) An equivalent means of compliance with this AD may be used if approved by the Manager, Airplane Certification Branch, Southwest Regional Office, FAA, Fort Worth, Texas 76193-0150; Telephone (817) 624-5150. All persons affected by this AD may obtain copies of the document(s) referred to herein upon request to Fairchild Aircraft Corporation, P.O. Box 790490, San Antonio, Texas 78279- 0490; or mayexamine the document(s) referred to herein at FAA, Office of the Regional Counsel, Room 1558, 601 East 12th Street, Kansas City, Missouri 64106. Amendment 39-3758 became effective May 14, 1980 and was effective to all recipients of telegraphic AD T80-SW-15 dated March 20, 1980. Amendment 39-3883 became effective August 26, 1980. This amendment 39-5821 revises AD 80-09-08 R1, Amendment 39-3883 (45 FR 56333; August 25, 1980). This amendment 39-5821 becomes effective on February 5, 1988.
89-07-06: 89-07-06 BRITISH AEROSPACE (BAe) PLC: Amendment 39-6161. Applicability: Model 3101 Jetstream (serial numbers 601 through 619) airplanes certificated in any category. Compliance: Required within the next 50 hours time-in-service after the effective date of this AD, unless already accomplished. To prevent loss of the airplane due to failure of the engine fire protection system, accomplish the following: (a) Inspect the right and left hand engine fire extinguisher systems to ensure that existing electrical connections to the fire extinguisher cartridges are correct in accordance with PART A-INSPECTION, under the Section 2 ACCOMPLISHMENT INSTRUCTIONS of British Aerospace Civil Aircraft Division (BAe) Alert Service Bulletin (ASB) Jetstream 26-A- JA881142, Rev 1, dated January 10, 1989. Prior to further flight, modify electrical connections that are not correct in accordance with Part B of the above referenced ASB. (b) Inspect the engine fire extinguisher cartridges in accordance with PART B- REPLACEMENT OF TERMINAL TAGS, under the ACCOMPLISHMENT INSTRUCTIONS of BAe ASB Jetstream 26-A-JA881142, Rev 1, dated January 10, 1989. Prior to further flight, replace any Part Number 13085-5 fire extinguisher cartridges with Part Number 30903819 cartridges. (c) Airplanes may be flown in accordance with FAR 21.197 to a location where this AD may be accomplished. (d) An equivalent means of compliance with this AD may be used if approved by the Manager, Brussels Aircraft Certification Staff, FAA, AEU-100, Europe, Africa, and Middle East Office, c/o American Embassy, B-1000 Brussels, Belgium. All persons affected by this directive may obtain copies of the documents referred to herein upon request to British Aerospace Inc., Technical Librarian, P.O. Box 17414, Dulles International Airport, Washington D.C. 20041; Telephone (703) 435-9100; or British Aerospace PLC, Aircraft Group, Scottish Division, Prestwick Airport, Ayrshire KA9 2RW U.K. (0292)79888; or may examine these documents at the FAA, Office of the Assistant Chief Counsel, Room 1558, 601 East 12th Street, Kansas City, Missouri 64106. This amendment (39-6161, AD 89-07-06) becomes effective on April 20, 1989.
2022-10-11: The FAA is adopting a new airworthiness directive (AD) for certain The Boeing Company Model 747-100B SUD, 747-200B, 747-200C, 747- 200F, 747-300, 747SP, 747-400, 747-400D, and 747-400F series airplanes. This AD was prompted by a determination that a certain fastener type that penetrates the fuel tank walls has insufficient bond to the structure, and energy from a lightning strike or high-powered short circuit could cause arcing to occur at the ends of fasteners in the fuel tanks. This AD requires, for certain airplanes, reconfiguring the clamps of certain wire bundles, applying sealant to certain fasteners that penetrate the fuel tank walls, installing cushion clamps and polytetrafluoroethylene (TFE) sleeves, inspecting to determine if sealant was applied to certain fasteners, and applying sealant if necessary. This AD also requires, for all airplanes, revising the maintenance or inspection program, as applicable, to incorporate new, more restrictive airworthiness limitations (AWLs). The FAA is issuing this AD to address the unsafe condition on these products.
99-04-06: This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model MD-90-30 series airplanes, that requires modification of the right and left main landing gear (MLG) hydraulic damper assemblies or replacement of the MLG hydraulic damper assemblies with modified and re-identified hydraulic damper assemblies. This amendment is prompted by reports indicating that, during overhauls, the MLG hydraulic dampers assemblies failed or had damaged spring retainers due to insufficient material thickness of the spring retainers. The actions specified by this AD are intended to prevent failure of the hydraulic damper assemblies of the MLG, which could result in vibration damage and collapse of the MLG.