Results
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 The rescinded AD resulted from mandatory continuing airworthiness information (MCAI) originated by an aviation authority of another country to identify and correct an unsafe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 Since issuance of the rescinded AD, we have determined that the unsafe condition does not exist or is not likely to develop on affected type design airplanes.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.
86-22-07: 86-22-07 PARA-FLITE, INCORPORATED: Amendment 39-5486. Applies to Swift Reserve Canopy P/N 82700, Serial Numbers R3-2750 through R3-3471. Compliance is required before further use after the effective date of this AD, unless already accomplished. To prevent the possibility of the applicable canopies performing below their standards on rate of descent, forward speed and flare capability perform the following: (a) Inspect and modify the canopies in accordance with Para-Flite, Incorporated Drawing 886028 dated January 17, 1986. (b) Do not use or repack the affected canopies unless paragraph (a) has been accomplished. NOTE: Para-Flite, Incorporated recall notice dated January 17, 1986, is applicable. Upon request, an equivalent means of compliance with the requirements of this AD may be approved by the Manager, New York Aircraft Certification Office, Aircraft Certification Division, Federal Aviation Administration, 181 South Franklin Avenue, Room 202, Valley Stream, New York 11581. Para-Flite, Incorporated Drawing 886028 dated January 17, 1986, identified and described in this document, is 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 this document from the manufacturer may obtain copies upon request to Para-Flite, Incorporated, 5800 Magnolia Avenue, Pennsauken, New Jersey 08109-1399. This document also may 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, Docket Number 86-ANE-16, between the hours of 8:00 a.m. and 4:30 p.m., Monday through Friday, except Federal holidays. Upon request, an equivalent means of compliance with the requirements of this AD may be approved by the Manager, Aircraft Certification Office, AEU-100, Europe, Africa, and Middle East Office, FAA, c/o American Embassy, Brussels, Belgium 09667-1011; telephone 513.38.30 Ext 2710, or the Manager, New York Aircraft Certification Office, Aircraft Certification Division, FAA, New England Region, 181 South Franklin Avenue, Room 202, Valley Stream, New York 11581, telephone (516) 791-6220. Aircraft may be ferried in accordance with the provisions of Federal Aviation Regulations 21.197 and 21.199 to a base where the AD can be accomplished. This amendment becomes effective December 29, 1986.
2012-25-04: We are superseding an existing emergency airworthiness directive (EAD) for Eurocopter France (Eurocopter) Model AS350B3 helicopters with certain part-numbered laminated half-bearings (bearings) and tail rotor (T/R) blades installed. The existing EAD currently requires installing two placards and revising the Rotorcraft Flight Manual (RFM). The EAD also requires certain checks and inspecting and replacing, if necessary, all four bearings. Finally, the EAD requires a one-time removal and inspection of the bearings, and replacing the bearings if necessary. Since we issued that EAD, we have determined that newly-designed helicopters with other part-numbered T/R blades may be affected by this unsafe condition and that the requirements should allow the bearing removal and inspection to be performed before the last flight of the day. This superseding AD removes the bearing and T/R blade part numbers (P/N) from the applicability paragraph and clarifies when the bearing removal and inspection is required. The actions are intended to prevent vibration due to a failed bearing, failure of the T/R, and subsequent loss of control of the helicopter.
2012-11-02: We are adopting a new airworthiness directive (AD) that supersedes an existing Emergency Airworthiness Directive (EAD) for certain Eurocopter Deutschland GmbH (ECD) Model EC135 helicopters. The existing EAD, which was previously sent to all known U.S. owners and operators of ECD Model EC135 helicopters and not made generally effective by publication in the Federal Register, currently requires inspecting the ring frame between the rear structure tube (tailboom) and the tail rotor fenestron housing (fenestron housing) for a crack before the first flight of each day and replacing any cracked ring frame with an airworthy ring frame. Since we issued that EAD, we have determined that a pre-flight pilot check in conjunction with a recurring 25-hour inspection is sufficient for determining the airworthiness of the ring frame. Additionally, ECD has developed a modification that is terminating action for the requirements of that EAD. This superseding AD revises the inspection requirements of the EAD to allow an owner/operator to perform the pre-flight pilot check, adds a recurring inspection of the ring frame, and allows for installation of a ring frame reinforcement as an optional terminating action for the AD requirements. The actions are intended to detect a crack in the ring frame which could result in loss of the fenestron structure and subsequent loss of control of the helicopter.
99-04-01: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 747 series airplanes, that requires repetitive inspections of the outboard nacelle struts to detect fatigue cracking of the strut skin and spring beam support fittings, and to detect cracked or loose fasteners of the support fittings; and corrective actions, if necessary. This amendment also provides for optional terminating action for the repetitive inspection requirements. This amendment is prompted by reports indicating that several cracked or broken spring beam support fittings were found on the outboard nacelle struts. The actions specified by this AD are intended to detect and correct such fatigue cracking and loose fasteners, which could result in failure of the outboard nacelle struts and consequent separation of the engine.
57-10-01: 57-10-01 MOONEY: Applies to Model M-20 Aircraft Serial Numbers 1002 Through 1126 Incorporating Main Landing Gear Retracting Bellcrank Bracket P/N 5035. To be accomplished as soon as practicable but not later than July 1, 1957. Cracks have been reported in the main landing gear retracting bellcrank bracket P/N 5035. In one case complete failure of the bracket resulted in jamming the elevator control system. Therefore, it is required that bracket PN 5035 be replaced by new redesigned brackets P/N 5101 which have a 0.095 inch wall tubing. The revised retracting bellcrank bracket P/N 5101 incorporated a reinforcing angle at the lower front corner and a cross member between the gear bungee fittings. (Mooney Service Letter 20-22 covers this same subject.)
87-23-04 R1: 87-23-04 R1 ROLLS-ROYCE plc: Amendment 39-5753 as amended by amendment 39-6180. Applicability: Rolls-Royce plc (R-R) RB211-22B, -524, -524B, -524B2, -524B3, and -524C2 turbofan engines. Compliance: Required as indicated, unless already accomplished. To prevent low pressure turbine (LPT) stage 1 disk uncontained failure, accomplish the following: (a) Modify LPT stage 2 vane nozzle assemblies, Part Numbers (P/N) LK63392, LK63331, LK63333, LK59046, LK59816, LK59853, LK59818, LK59038, LK55447, LK55420, LK54278, LK55452, and LK59002, in accordance with the Accomplishment Instructions of R-R Service Bulletin (SB) RB.211-72-8301, Revision 5, dated May 13, 1988, at the next shop visit of the LPT module, but not later than June 30, 1989. NOTE: For the purpose of this AD, an LPT module shop visit is defined as separation of the LPT rotor assembly from the LPT case/vane nozzle assembly as necessitated by (1) its condition or (2) a requirement for scheduled maintenance. (b) Aircraft may be ferried in accordance with the provisions of FAR 21.197 and 21.199 to a base where the AD may be accomplished. (c) Upon submission of substantiating data by an owner or operator through an FAA Airworthiness Inspector, and alternative method of compliance with the requirements of this AD or adjustments to the compliance times specified in this AD, may be approved by the Manager, Engine Certification Office, ANE-140, Engine and Propeller Directorate, Aircraft Certification Service. The LPT stage 2 vane nozzle assembly modification shall be done in accordance with Rolls-Royce SB RB.211-72-8301, Revision 5, dated May 13, 1988. 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 Rolls-Royce plc, Technical Publications Department, P.O. Box 31, Derby DE2 8BJ, England. Copies may be inspected at the Regional Rules Docket, Office of the Assistant Chief Counsel, Federal Aviation Administration, New England Region, 12 New England Executive Park, Room 311, Burlington, Massachusetts 01803, or at the Office of the Federal Register, 1100 L Street, N.W., Room 8301, Washington, DC. Amendment 39-5753, AD 87-23-04 became effective on December 11, 1987. This amendment (39-6180, AD 87-23-04 R1) becomes effective on May 31, 1989.
99-03-04: This amendment adopts a new airworthiness directive (AD), applicable to all Boeing Model 737-100, -200, -300, -400, and -500 series airplanes, that requires installation of components to provide shielding and separation of the fuel system wiring (that is routed to the fuel tanks) from adjacent wiring. This amendment also requires installation of flame arrestors and pressure relief valves in the fuel vent system. This amendment is prompted by testing results, obtained in support of an accident investigation, and by re-examination of possible causes of a similar accident. The actions specified by this AD are intended to prevent possible ignition of fuel vapors in the fuel tanks, and external ignition of fuel vapor exiting the fuel vent system and consequent propagation of a flame front into the fuel tanks.
91-02-04: 91-02-04 GROB WERKE GMBH & CO. KG (GROB): Amendment 39-6823; Docket No. 90-CE-29-AD. Applicability: Models G103 "Twin Astir" (including "Trainer") gliders (Serial Numbers (S/N) 3000 through 3291) and G103 "Twin II" (including "ACRO") gliders (S/N 3501 through 3729), 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 preclude the incorrect installation of the aileron system connecting bolt, accomplish the following: (a) Modify the aileron control system by installing a GROB forkhead nut (GROB part number 103B-4229) and removing the placard that cautions against incorrect installation of the connecting bolts located on the aileron control lever adjacent to the connecting bolt, if installed, as described in GROB Service Bulletin No. TM 315-38/1, dated December 12, 1989. (b) An alternate method of compliance or adjustment of the compliance time thatprovides an equivalent level of safety may be approved by the Manager, Brussels Aircraft Certification Staff, Europe, Africa, and Middle East Office, FAA, c/o American Embassy, B-1000 Brussels, Belgium; Telephone (322) 513.38.30 ext. 2718; Facsimile (322) 230.68.99. The request should be forwarded through an appropriate FAA Maintenance Inspector, who may add comments and then send it to the Manager, Brussels Aircraft Certification Staff. (c) All persons affected by this directive may obtain copies of the document referred to herein upon request to GROB Systems, Incorporated; Aircraft Division, I-75 and Airport Drive, Bluffton, Ohio 45817; Telephone (419) 358-9015; or may examine this document at the FAA, Central Region, Office of the Assistant Chief Counsel, Room 1558, 601 E. 12th Street, Kansas City, Missouri 64106. This amendment (39-6823, AD 91-02-04) becomes effective on February 8, 1991.
2013-16-16: We are adopting a new airworthiness directive (AD) for Agusta S.p.A. (Agusta) Model AB412 and AB412 EP, and Bell Helicopter Textron (Bell) Model 412, 412CF, and 412EP helicopters with certain DART Aerospace Ltd. (Dart) high gear aft crosstubes (crosstube) installed. This AD requires adding a life limit of 10,000 landings to the crosstube and removing from service any crosstubes with more than 10,000 accumulated landings. This AD is prompted by five separate reports of crosstube failures. The actions in this AD are intended to prevent failure of the crosstube and subsequent collapse of the landing gear.
2010-14-06: The FAA is superseding an existing airworthiness directive (AD), which applies to certain Model 737-300, -400, and -500 series airplanes. That AD currently requires an inspection to determine the manufacturer and manufacture date of the oxygen masks in the passenger service unit and the lavatory and attendant box assemblies, corrective action if necessary, and other specified action. This new AD expands the applicability in the existing AD. This AD results from a determination indicating that additional airplanes may be subject to the identified unsafe condition. We are issuing this AD to prevent the in-line flow indicators of the passenger oxygen masks from fracturing and separating, which could inhibit oxygen flow to the masks and consequently result in exposure of the passengers and cabin attendants to hypoxia following a depressurization event.
2013-16-09: We are adopting a new airworthiness directive (AD) for all Airbus Model A318, A319, A320, and [[Page 48287]] A321 series airplanes. This AD requires an inspection to determine airplane configuration and part numbers of the landing gear control interface unit and main landing gear (MLG) door actuators; and, for affected airplanes, repetitive inspections of the opening sequence of the MLG door actuator, and replacement of the MLG door actuator if necessary. This AD also provides optional terminating action for the repetitive inspections. This AD was prompted by a report of a MLG failing to extend during landing, and a determination that a certain configuration of landing gear control interface unit and actuators may result in masking of centralized fault display system messages that are necessary to mitigate risks associated with failure of MLG extension or down-locking. We are issuing this AD to detect and correct such a configuration, which could prevent the full extension or down-locking of the MLG, possibly resulting in MLG collapse during landing and consequent damage to the airplane and injury to occupants.
2013-15-05: We are adopting a new airworthiness directive (AD) for certain Bombardier, Inc. Model CL-600-2B19 (Regional Jet Series 100 & 440) airplanes. This AD was prompted by a determination that certain flap actuators require restoration by installing a redesigned flap actuator inboard pinion seal. This AD requires revising the maintenance program by incorporating new airworthiness limitation tasks. We are issuing this AD to prevent flap system failure, and consequent reduced control of the airplane.
98-26-51: This document publishes in the Federal Register an amendment adopting Airworthiness Directive (AD) 98-26-51 that was sent previously to all known U.S. owners and operators of certain McDonnell Douglas Model DC-8 series airplanes by individual telegrams. This AD requires a revision to the Airplane Flight Manual to specify restrictions on operating if any pressurization anomaly is detected. This AD also requires a one-time inspection to detect discrepancies and cracking of the main deck cargo door in the immediate area of the bolts attaching the latch fittings, and repair, if necessary. This action is prompted by a report that a cabin pressurization anomaly was detected on a McDonnell Douglas Model DC-8 series airplane, and by subsequent investigation, which revealed fatigue cracking in the structure of the main deck cargo door. The actions specified by this AD are intended to detect and correct fatigue cracking in the structure of the main deck cargo door, which could result in cabin decompression of the airplane and loss of the main deck cargo door, and consequent reduced controllability of the airplane.\n\n\tEffective February 3, 1999, to all persons except those persons to whom it was made immediately effective by telegraphic AD T98-26-51, issued December 18, 1998, which contained the requirements of this amendment. \n\n\tComments for inclusion in the Rules Docket must be received on or before March 30, 1999.
81-10-02: 81-10-02 HILLER AVIATION: Amendment 39-4103. Applies to all Models FH 1100 Series Helicopter, certified in all categories, Serial Nos. 001 through 254. Compliance required as indicated, unless already accomplished. To prevent the upper controls support column from contacting and damaging the main rotor mast accomplish the following: (a) Within the next ten (10) calendar days from the effective date of this AD (1) Accomplish a one time visual inspection of the support column P/N 24-30208 to determine whether or not the base flange P/N 24-30210 is undersized. Inspection is to be performed in accordance with Hiller Service Bulletin SB 30-9, Part 2, Subpart B, dated April 3, 1981. (2) If the inspection (a) (1) determines that the flange thickness is in accordance with type design (specifically 0.090 0.010 inches), no further AD action is required. (b) After inspection of paragraph (a) (1) and a determination that the flange thickness is undersized, prior to further flight (1) Replace the support column P/N 24-30208 with a like serviceable part which is in compliance with type design; and (2) Inspect the main rotor mast for damage (nicks, scratches or dents) at the top of the support column location, approximately 12.375 inches from top of upper housing of transmission. Replace each damaged main rotor mast with a like serviceable part. NOTE: The main rotor mast cannot be inspected until the upper controls and support column are disassembled. NOTE: Hiller kits P/N SBK-FH-1100-23-2 and spares stock may contain undersize flight control system support columns. (c) Verify that any replacement support column is in compliance with type design as noted in paragraph (a) (2) prior to return to service. Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate helicopters to a base for the accomplishment of inspections and maintenance required by this AD. 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. 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 Hiller Aviation, 2075 West Scranton Avenue, Porterville, California 93275. These documents may also be examined at FAA Western Region Office, Room 6W14, 15000 Aviation Boulevard, Hawthorne, California 92061; and at FAA Headquarters, 800 Independence Avenue, S.W., Washington, D.C. 20591. 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 May 11, 1981.
91-10-10: 91-10-10 BRITISH AEROSPACE: Amendment 39-6995. Docket No. 91-NM-09-AD. Applicability: All Model BAe 125-800A series airplanes, certificated in any category. Compliance: Required as indicated, unless previously accomplished. To prevent a wheel loosening from the axle and the possible loss of a wheel, accomplish the following: A. Within 30 days after the effective date of this AD, inspect all nose wheels for nose wheel serial numbers, listed in paragraph 2.A.(2) of Dunlop Service Bulletin AH52339-A32-1046, dated July 27, 1990. B. If the serial number on the nose wheel coincides with any of the serial numbers listed in paragraph 2.A.(2) of Dunlop Service Bulletin AH52339-A32-1046, dated July 27, 1990, retorque the location plate retaining nuts to 8 foot-pounds in accordance with the service bulletin. NOTE: If the airplane maintenance records indicate that the nose wheel assembly has had the wheel halves disassembled and reassembled since the airplane was new, the required retorquing will have been accomplished at that time, and no further action is required. WARNING: DO NOT ADJUST THE TORQUE TIGHTENED MAIN HUB TIE BOLTS WITH THE TIRE INFLATED. C. An alternative method 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 forwarded through an FAA Principal Maintenance Inspector, who may concur or comment and then send it to the Manager, Standardization Branch, ANM-113. D. 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 British Aerospace, PLC, Librarian for Service Bulletins, P.O. Box 17414, Dulles International Airport, Washington, D.C. 20041. These documents may be examined at the FAA, Transport Airplane Directorate, 1601 Lind Avenue S.W., Renton, Washington. This amendment (39-6995, AD 91-10-10) becomes effective on June 18, 1991.
62-17-03: 62-17-03 DOUGLAS: Amdt. 468 Part 507 Federal Register July 28, 1962. Applies to DC-8 Aircraft, Serial Numbers 45253-45289, 45291-45306, 45376-45382, 45384-45393, 45408-45413, 45416-45419, 45421-45431, 45433, 45442-45445, 45526, 45565-45570, 45588-45606, 45609-45614, 45617-45618, 45620-45622, 45624-45627. \n\n\tCompliance required within 300 hours' time in service after the effective date of this AD. \n\n\tInvestigation has shown that the overwing emergency exits cannot, under all necessary circumstances, be opened from outside the airplane, as required by Civil Air Regulations Sections 4b.362(e)(2) and 4b.362(e)(3). To eliminate this condition, one of the following modifications shall be accomplished with respect to each aft overwing exit which is not deactivated per Note 7 of Type Certificate Data Sheet 4A25 and with respect to each forward overwing exit: \n\n\t(a)\tThe outboard seat in the row of seats forward of each overwing exit shall be permanently blocked to prevent the seat from being reclined across any portion of the exit opening. The outboard seat in the row of seats aft of each overwing exit shall be permanently blocked to prevent the seat from being moved forward across any portion of the exit opening. \n\n\t(b)\tEach row of seats forward and aft of each overwing exit shall be relocated in an approved manner that will permit the exit door to be readily opened from the outside and removed when the back of the outboard seat in each such row of seats is in any of its possible positions. The seat track or other seat positioning means shall be clearly marked or blocked in a manner which will assure that these rows of seats are continuously retained in this position during service. \n\n\t(c)\tCombinations of the modifications specified in (a) and (b) may be used provided that fore and aft outboard seat backs are restricted from being placed in a position which will prevent opening of the exit from the outside. \n\n\t(d)\tRework each overwing exit door assembly,door jamb and lower stop, install a handle on the exterior of each of those door assemblies, and restrict the forward movement of the outboard seat in each row of seats just aft of an overwing exit. This total modification shall be such as to permit the exit door to be readily opened and removed from the outside when the backs of both adjacent outboard seats are in any of their possible positions. \n\n\t(Douglas DC-8 Service Bulletin No. 52-21 pertains to this same subject and describes an FAA approved means of complying with modification method (d).) \n\n\tThis directive effective August 27, 1962.
81-12-06 R1: 81-12-06 R1 BENDIX: Amendment 39-4249. Applies to Bendix Engine Products Division D-3000 and D-3200 (Blue) series magnetos identified as follows, unless previously identified by the letter "X", on the upper left area of magneto data plate: a. D-3000 series (see models specified under "MAGNETO IDENTIFICATION") pressurized (dark blue) magnetos with serial numbers below 1423, installed on AVCO Lycoming TIO, LTIO-540-J2BD engines. MAGNETO IDENTIFICATION MODEL PART NO. D6LN-3200 10-682910-13 D6RN-3200 10-682910-18 These magnetos are installed on but not limited to the following aircraft engines or aircraft engine/aircraft combinations: AVCO LYCOMING ENGINES AIRCRAFT INSTALLATIONS TIO-540-J2BD Piper PA-31-350; LTIO-540-J2BD STC SA1151SO and SA970SO Colemill conversion of Piper PA-31, PA-31-325 and PA-31-350; STC SA980NW Machen Industries conversion of Piper Aerostar 600 STC SA762NW Machen Industries conversion of Beechcraft Bonanza B35 and A36 series.To detect loose distributor gear rotating electrodes on magnetos having 100 hours or more in service since new or overhaul, accomplish paragraph c, before further flight, unless previously accomplished, and every 50 hours in service thereafter until the gears are replaced with laser welded gear assemblies identified by the presence of the letter "Z" or the letters "XO" on the retaining ring end of the gear axle. b. All D-3000 and D-3200 series (blue) magnetos with serial numbers 100 through 1968 not covered by paragraph a, unless previously accomplished. To detect loose distributor gear rotating electrodes on magnetos having 100 hours or more in service since new or overhaul, accomplish paragraph c, before the expiration of 50 hours in service since new or overhaul after the effective date of this AD unless previously accomplished and every 50 hours in service thereafter until the gears are replaced with laser welded gear assemblies identified by the presence of the letter"Z" or the letters "XO" on the retaining ring end of the gear axle or the letter "L", stamped on the distributor gear electrode. c. 1. Remove the distributor block from the magneto and the gears from the block. 2. (A). Inspect distributor gears and block for the presence of bronze colored particles and for indications of metal to metal contact of electrodes. (B). Inspect rotating electrode for looseness by holding the gear in one hand while attempting to move the distributor gear electrode relative to the axle, clock-wise and vertically. Any looseness of the rotating electrode is reason for rejection of distributor gear. 3. If the distributor block is contaminated with brass filings or bronze colored dust, inspect the engine as follows: (A). Observe engine pistons through spark plug hole for evidence of burning. (B). Check valve dry tappet clearance per engine manufacturer's instructions. If piston damage or lower than specified dry tappet clearance is present, the engine must be inspected, in accordance with the engine manufacturer's instructions, for continued airworthiness. 4. Reinstall serviceable distributor gears into a clean serviceable distributor block. Reassemble the magneto and check timing as appropriate. 5. (A). Make an engine log entry of compliance, including magneto serial number. (B). When the laser beam welded distributor gear has been installed in a D-3000 or D-3200 series magneto, identify that magneto by metal stamping the letter "X", on the upper left area of magneto data plate and make the appropriate log entry. Equivalent inspections and procedures must be approved by the Chief of the Engineering and Manufacturing Branch, AEA-210, Federal Aviation Administration (FAA) Eastern Region. As permitted by FAR 21.197, aircraft may be flown to a base where maintenance required by this AD can be accomplished. (Bendix Service Bulletins 618 and 619 pertain to paragraphs a and b respectively.) This Airworthiness Directive is effective November 12, 1981, and paragraph a. was effective upon receipt for all recipients of airmail letter dated June 5, 1981, which covered that subject.
2021-04-08: The FAA is adopting a new airworthiness directive (AD) for Airbus Helicopters Model AS350B3 helicopters. This AD requires modifying the electrical system of the throttle twist grip, inspecting the routing of a microswitch electrical harness, and correcting the electrical harness routing if it is incorrect. This AD was prompted by reports of the engine remaining in idle when the twist grip was turned from the ''forced idle'' position to the ''flight'' position. The actions of this AD are intended to address an unsafe condition on these products.