Results
2005-14-08: The FAA is superseding an existing airworthiness directive (AD), which applies to certain Boeing Model 747-100, -200, -300, and 747SP series airplanes. That AD currently requires certain inspections to find missing or alloy-steel taperlock fasteners (bolts) in the diagonal brace underwing fittings, and corrective actions if necessary. For airplanes with missing or alloy-steel fasteners, that AD also mandates replacement of certain fasteners with new fasteners, which constitutes terminating action for certain inspections. This new AD expands the applicability to include additional airplane models and requires a new inspection to determine fastener material and to find missing or broken fasteners, and related investigative/corrective actions if necessary. This AD is prompted by reports indicating that cracked fasteners made of A286 material were found on airplanes that had only fasteners made of A286 material installed in the area common to the diagonal brace underwing fittings.We are issuing this AD to prevent loss of the underwing fitting load path due to missing or damaged alloy-steel or A286 taperlock fasteners, which could result in separation of the engine and strut from the airplane. \n\n\nDATES: This AD becomes effective August 15, 2005. \n\n\tThe incorporation by reference of Boeing Alert Service Bulletin 747-57A2312, Revision 1, dated April 29, 2004, is approved by the Director of the Federal Register as of August 15, 2005. \n\n\tOn August 1, 2001 (66 FR 34094, June 27, 2001), the Director of the Federal Register approved the incorporation by reference of Boeing Alert Service Bulletin 747-57A2312, dated June 15, 2000.
75-12-05: 75-12-05 MCCLISH (Funk): Amendment 39-2225: Applies to all McClish (Funk) Model B, B75L, B85C and Funk C Aircraft. 1. Affects wing forward external support struts and rear fuselage lower longerons at the tail post. a. Within the next ten hours' time in service or one month, whichever occurs first, after the effective date of this Airworthiness Directive, unless accomplished within the last 90 hours in service or 11 months, accomplish the following: b. Inspect the wing forward external support struts at the lower end where the aileron cable enters the strut, for corrosion and cracks. c. Inspect the lower fuselage longerons at the tail post and weldments in the rudder hinge post area, for corrosion and cracks. 2. The inspection specified in paragraph (1) must be repeated at intervals not to exceed 100 hours' time in service or 12 months, whichever occurs first. 3. Before further flight, all corroded or cracked parts must be replaced with the same partnumber or with approved equivalent parts, or repaired in accordance with an approved repair procedure. 4. Upon submission of substantiating data by an owner or operator through an FAA Maintenance Inspector, the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region may adjust the inspection time in this Airworthiness Directive. Repairs and equivalent parts must be approved by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region. Substantiating data for repairs and equivalent parts must be submitted by an owner or operator through an FAA Maintenance Inspector. This amendment is effective June 5, 1975.
84-12-02: 84-12-02 BELL HELICOPTER TEXTRON, INC: Amendment 39-4876. Applies to Bell Model 222 helicopters, certificated in all categories, that have nodal beam support fitting P/N 222-031-520-105 installed. (Airworthiness Docket 83-ASW-41.) Compliance is required as indicated, unless already accomplished. To prevent possible failure of the nodal beam left side aft support fitting, P/N 222-031- 520-105, accomplish the following: (a) For those aircraft that have support fitting P/N 222-031-520-105 installed with 1,100 or more hours time in service on the effective date of this AD, remove the fitting within the next 100 hours time in service. (b) For those aircraft that have support fitting P/N 222-031-520-105 with fewer than 1,100 hours time in service on the effective date of this AD, remove the fitting upon reaching 1,200 hours time in service. NOTE: Fitting P/N 222-031-520-105 may be replaced by a serviceable fitting of the same part number, or by P/N 222-031-592-103. (c) This AD establishes a 1,200 hour retirement life for all nodal beam left side aft support fittings P/N 222-031-520-105. (d) Any equivalent method of compliance with this AD must be approved by the Manager, Helicopter Certification Branch, Federal Aviation Administration, 4400 Blue Mound Road, Fort Worth, Texas 76106. (e) In accordance with Section 21.197, flight is permitted to a base where the actions required by this AD may be accomplished. NOTE: The following is provided as information only: Bell Helicopter Textron, Inc., Alert Service Bulletin 222-83-20 is the manufacturer's notification of the 1,200-hour life assignment to the nodal beam left side aft support fitting, P/N 222-031-520-105. Bell Helicopter Textron, Inc., Technical Bulletin 222-83-53 provides instructions for replacement of the P/N 222-031-520-105 aluminum fitting with a stainless steel fitting, P/N 222- 031-592-103, that has no retirement life. This amendment becomes effective July 11, 1984.
2005-14-02: The FAA is adopting a new airworthiness directive (AD) for all Empresa Brasileira de Aeronautica S.A. (EMBRAER) Model EMB-135 and Model EMB-145, -145ER, -145MR, -145LR, -145XR, -145MP, and -145EP airplanes. This AD requires inspecting to determine the part number of the left and right engine fire handles; and replacing the engine fire handles with engine fire handles having different part numbers if necessary. This AD is prompted by cases of the internal circuit of the engine fire handle failing. We are issuing this AD to prevent failure of the internal circuit of the engine fire handle that could disable the fuel shut-off valves and the discharge of the fire extinguishing agent, which, in the event of a fire, could result in the inability to extinguish a fire.
75-16-19: 75-16-19 FLUG-und FAHRZEUGWERKE A.G.: Amendment 39-2293. Applies to Diamant HBV gliders, all serial numbers, and Diamant 16.5 gliders, S/N 011 through 069, except 030, 031, 036, 058, 067, and 068, certificated in all categories. Compliance is required within 25 hours' time in service after the effective date of this AD, unless already accomplished. To prevent jamming of the rudder, accomplish the following: (a) Visually inspect and measure the fin fairing overlap of the rudder nose for right full rudder to assure an overlap of more than 0.4 inc. (10 mm) in accordance with Flug-und Fahrzeugwerke A.G. Service Bulletin No.2, dated May 15, 1970, or an FAA-approved equivalent. (b) If fin fairing overlap measured in accordance with paragraph (a) of this AD is less than 0.4 in. (10 mm), modify (lengthen) the rudder nose by bonding fiberglass strips to the nose in accordance with Flug-und Fahrzeugwerke A.G. Service Bulletin No.2, dated May 15, 1970, or an FAA-approvedequivalent. This amendment becomes effective August 12, 1975.
97-16-02: This amendment adopts a new airworthiness directive (AD) that is applicable to Robinson Helicopter Company (Robinson) Model R44 helicopters. This action requires inspections of the belt tension actuator switches (up-limit switches) for proper operation, and replacement if necessary; and replacement of a certain part-numbered clutch assembly. This amendment is prompted by six occurrences of prematurely worn sprag clutches. The actions specified in this AD are intended to prevent failure of the sprag clutch to lock in the driving direction, which would result in loss of power to the main rotor system and a subsequent forced landing; or failure of the sprag clutch to unlock in the overrunning direction, which, if combined with engine failure, would result in an inability to autorotate and a subsequent loss of control of the helicopter.
2005-14-01: The FAA is adopting a new airworthiness directive (AD) for certain Airbus transport category airplanes. This AD requires an inspection to determine if suspect part numbers (P/Ns) and serial numbers of certain Thales Avionics equipment are installed, and replacement of any suspect part with a modified part having a new P/N. This AD is prompted by reports of loss of the digital distance radio magnetic indicator and subsequent loss of both very high frequency omnidirectional range indicators, both distance measuring equipment, and one centralized maintenance computer. We are issuing this AD to prevent loss of navigation indications on the primary flight display requiring continuation of the flight on emergency instruments, which could lead to reduced ability to control the airplane in adverse conditions.
75-16-13: 75-16-13 MITSUBISHI HEAVY INDUSTRIES, LIMITED: Amendment 39-2286. Applies to Mitsubishi MU-2B-20/-25 (serial numbers 201 through 311 except 285, 291, 301, 305, and 309), and MU-2B-30/-35 (serial numbers 541 through 650 except 559, 612, 632, 645, and 648) airplanes certificated in all categories. Compliance is required within the next 100 hours time in service after the effective date of this AD, unless already accomplished. To prevent fatigue failure of the wing flap main actuator jack screw, accomplish the following: (a) Irrespective of the airplane total hours time in service, inspect the left and right wing flap main actuator jack screws for cracks, replace the jack screws that are found cracked, and realign all the main actuator gear box housing units in accordance with the instructions contained in Mitsubishi MU-2 Service Bulletin No. 167 as revised January 9, 1975 (hereinafter MU-2 Service Bulletin 167), or an equivalent approved by the Chief, Engineering and Manufacturing District Office, FAA, Pacific-Asia Region. (b) During the realignment process, ensure there is a nominal clearance of 2.0 mm (.080 inch), and under no circumstances less than 0.5 mm (.020 inch), between the main actuator gear box housings and wing rear spar. (c) For airplanes equipped with a rubber bearing pad between a main actuator gear box housing and the wing rear spar, accomplish the modification of the main gear box and removal of the rubber pad, as described in paragraph 3.l(7) or paragraph 3.2 1(b) of MU-2 Service Bulletin 167, as applicable, prior to realignment of the main gear box housings. NOTE: MU-2 Service Bulletin 167, paragraphs 4 and 5, and the appropriate Mitsubishi MU-2 Maintenance Manuals contain information on adjustment and operational check of the flap system. This amendment becomes effective August 5, 1975.
2005-13-36: The FAA is adopting a new airworthiness directive (AD) for certain Learjet Model 23, 24, 24A, 24B, 24B-A, 24C, 24D, 24D-A, 24E, 24F, 24F-A, 25, 25A, 25B, 25C, 25D, 25F, 28, 29, 31, 31A, 35, 35A (C- 21A), and 36 airplanes. This AD requires a one-time inspection of the center ball of the aileron control cable or cables for a defective swage, and corrective actions if necessary. This AD is prompted by a report indicating that an aileron cable failed on one affected airplane when the cable underwent a tension check. We are issuing this AD to prevent severe weakening of the aileron cable, and consequent reduced controllability of the airplane.
97-15-10: This amendment adopts a new airworthiness directive (AD), applicable to AlliedSignal Inc. (formerly Garrett Engine Division and Garrett Turbine Engine Company) TPE331 series turboprop engines equipped with Woodward fuel controls, that requires revising the applicable Emergency Procedures or Abnormal Procedures Section of the applicable Federal Aviation Administration (FAA)-approved Airplane Flight Manual (AFM) or Pilot's Operating Handbook (POH) to include a paragraph relating to a non-responsive power lever. In addition, this AD requires replacing or reworking orifice fittings and restrictors, which would constitute terminating action to the requirement to revise the applicable AFM. This amendment is prompted by reports of occasional icing of the inlet Pt2 sensor, which can produce an erroneous (high) pressure signal to the fuel control, causing little or no response to power lever movement. The actions specified by this AD are intended to prevent a non-responsive power lever and lack of control of engine power.
82-18-10: 82-18-10 FLIGHT EQUIPMENT AND ENGINEERING CORPORATION: Amendment 39-4450. Applies to 639 and 675 series seats of the model and serial numbers listed below manufactured in accordance with FAA Technical Standard Order (TSO) C-39a, Aircraft Seats and Berths, and installed in aircraft certificated in any category. These seats are believed to be installed in, but not necessarily limited to, Douglas Model DC-9 Series and Boeing Model 737 Series airplanes. \n\n\nModel No.\nSerial No. \n639NL\n19654 thru 19661 \n639-3WL\n19476 thru 19499, 19940, 22273 \n639-3WR\n19500 thru 19523, 19941, 22274 \n639-3XL\n19524, 19525 \n639-3XR\n19526, 19527 \n639-3ZR\n19530, 19531 \n639-3AAL\n19532, 19533 \n639-3AAR\n19534, 19535 \n639-3ABL\n19536, 19537 \n639-3ABR\n19538, 19539 \n639-3ACL\n19540, 19541 \n639-3ACR\n19542, 19543 \n639-3AER\n19662, 19663 \n639-3AQL\n21050 thru 21063 \n639-3AQR\n21064 thru 21077 \n639-3ASL\n21078 \n639-3ASR\n21079 \n639-3ATL\n21080 \n639-3ATR\n21081 \n639-3AUR\n21082 \n639-3AVL\n21083 \n639-3AVR\n21084 \n639-3AWL\n21085 \n639-3AWR\n21086 \n639-3AXR\n21087 \n639-3AZL\n21090 \n639-3AZR\n21091 \n639-3BBL\n21289 thru 21299, 21332 thru 21342 \n639-3BBR\n21300 thru 21310, 21343 thru 21353 \n639-3BCL\n21311, 21354 \n639-3BCR\n21312, 21355 \n639-3BDL\n21313, 21356 \n639-3BDR\n21314, 21357 \n639-3BEL\n21315, 21325 \n639-3BER\n21316, 21326 \n639-3BFL\n21317, 21327 \n639-3BGR\n21318, 21328 \n639-3BHL\n21319, 21358 \n639-3BHR\n21320, 21331 \n639-3BKR\n21323, 21331 \n675-3AR\n21494 thru 21526, 21680 thru 21707, 21766 thru 21793, 22152 thru 22172, 22233 thru 22238, 22873 thru 22883, 23025 thru 23029 \n675-3BL\n21527 thru 21529, 21708, 21709, 21794, 21795, 22173, 22174, 22884, 23030 \n675-3BR\n21530 thru 21532, 21710, 21711, 21796, 21797, 22175, 22176, 22885, 23031\n675-3CL\n21533 thru 21535, 21712, 21713, 21798, 21799, 22177, 22178, 22886, 23032 \n675-3CR\n21536 thru 21538, 21714, 21715, 21800, 21801, 22179, 22180, 22887, 23033 \n675-3DL\n21539 thru 21541, 22888, 23034675-3DR\n21542 thru 21544, 22889, 23035 \n675-3EL\n21545 thru 21547, 22890, 23036 \n675-3FR\n21548 thru 21550, 22891, 23037 \n675-3GL\n21551 thru 21553, 21716, 21717, 21802, 21803, 22892, 23038 \n675-3GR\n21554 thru 21556, 21718, 21719, 21804, 21805, 22893, 23039 \n675-3JR\n21563 thru 21565, 22896, 23042 \n675-3KR\n21724, 21725, 22333, 23043, 23197 \n675-3MR\n21726, 21727, 22239, 22240, 23044 \n675-3NL\n21728, 21729, 22241, 22242, 22334, 23045, 23197 \n675-3NR\n21730, 21731, 21810, 21811, 22243, 22244, 23046 \n675-3PL\n21732, 21733, 22245, 22246, 23047 \n675-3PR\n21734, 21735, 22247, 22248, 23048 \n675-3QL\n22181 \n675-3QR\n22182 \n675-3SR\n22183 \n675-3TR\n22184 \n675-3UL\n21812, 21813, 23049 \n675-3UR\n21814, 21815, 23050 \n675-3AL\n21461 thru 21493, 21652 thru 21679, 21738 thru 21765, 22128 thru 22151, 22227 thru 22232, 22862 thru 22872, 23020 thru 23024\n\n\tCOMPLIANCE: Required within 60 calendar days after the effective date of this AD, unless already accomplished. \n\n\tTo assure the seat attachment meets strength requirements of TSO C-39a, accomplish the following: \n\n\t(a)\tReplace existing P/N 31620 track lock fittings with P/N 33667 fittings having increased strength. \n\n\t(b)\tAirplanes may be flown in accordance with FAR 21.197 to a location where this AD may be accomplished. \n\n\t(c)\tAn alternate means of compliance with this AD may be used if approved by the Chief, Atlanta Certification Office, FAA, P.O. Box 20639, Atlanta, Georgia 30320. \n\n\tFlight Equipment Service Bulletin No. 675-25-63 dated April 6, 1982, Subject: Replacement of Leg Frame Rear Floor Track Fitting - Replacement of, pertains to the subject matter of this AD. \n\n\tThis amendment becomes effective October 4, 1982.
69-06-01: 69-06-01 FAIRCHILD-HILLER: Amdt. 39-734. Applies to Type F-27 Airplanes Serial Numbers 1 through 124 inclusive. Incorporating Cutler Hammer P/N 6046 H46 Relay in Flap Control System. Compliance required as follows: To prevent hazards associated with flap drive system failure whereby the flaps are driven off the drive screw jacks, accomplish the following: (a) Within the next 200 hours time in service after the effective date of this AD, and thereafter at 200 hour intervals from the date of the last inspection, open cover of wing flap system motor relay and visually inspect all contacts. Any finding of contact pitting or discoloration of contacts requires replacement of the relay with an unused part. The inspection may be terminated upon completion of the requirement of paragraph (b) of this AD. (b) Within the next 500 hours time in service after the effective date of the AD, unless already accomplished, rewire the flap drive circuit in accordance with Fairchild Hiller F- 27 Service Bulletin F-27-27-67 dated February 1, 1969, for F-27 aircraft, or later revisions approved by the Chief, Engineering and Manufacturing Branch, FAA Eastern Region, or perform an equivalent modification approved by the Chief, Engineering and Manufacturing Branch, FAA Eastern Region. (c) Upon request with substantiating data submitted through an FAA Maintenance Inspector, compliance time may be increased by the Chief, Engineering and Manufacturing Branch, FAA Eastern Region. This amendment is effective March 26, 1969.
2005-13-37: The FAA is adopting a new airworthiness directive (AD) for all Fokker Model F.28 Mark 0070 and 0100 airplanes. This AD requires repetitive inspections for damage of the drive rod assembly of the aileron tab on each aileron actuator; repetitive measurements of the clearance between the aileron hydraulic lines and the drive rod; and related investigative and corrective actions if necessary. This AD is prompted by a report of an aileron 2 fault caused by severe wear of the polyamide washer that is part of an anti-rotation bush assembly in the aileron attachment lug. We are issuing this AD to prevent excessive wear of the polyamide washer of the aileron actuator bush assembly, which could result in aileron flutter and loss of control of the airplane.
2010-23-12: We are adopting a new airworthiness directive (AD) for the products listed above. This AD results 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: * * * * * Investigation conducted by Thales on * * * probes revealed oil residue between the stator and the rotor parts of the AoA [angle of attack] vane position resolvers. This oil residue was due to incorrect cleaning of the machining oil during the manufacturing process of the AoA resolvers. At low temperatures, this oil residue becomes viscous (typically in cruise) causing lag of AoA vane movement. Such condition could lead to discrepant AoA measurement. If not corrected, and if two or three AoA probes were simultaneously affected and provided wrong indications of the AoA to a similar extent, it could lead to a late activation of the angle ofattack protection, which in combination with flight at high angle of attack would constitute an unsafe condition. * * * * * We are issuing this AD to require actions to correct the unsafe condition on these products.
70-14-05: 70-14-05 BELL: Amendment 39-1025. Applies to all Model 206A helicopters certificated in all categories equipped with voltage regulator P/N 206-075-027-3. Compliance is required within 300 hours time in service after the effective date of this airworthiness directive, unless already accomplished. Replace the voltage regulator, Bell Part No. 206-075-027-3, in accordance with the instructions in paragraphs 1 through 11, as applicable, of Bell Helicopter Company Service Letter No. 206A-139, Revision "A", dated October 14, 1969, or later FAA approved revision. Alternate means of compliance or equivalent replacement parts may be acceptable if approved by the Chief, Engineering and Manufacturing Branch, Flight Standards Division, Southwest Region, Federal Aviation Administration. This amendment becomes effective August 15, 1970.
2005-13-38: The FAA is adopting a new airworthiness directive (AD) for certain Bombardier Model DHC-8-100, DHC-8-200, and DHC-8-300 series airplanes. This AD requires revising the airworthiness limitations section of the Instructions for Continued Airworthiness by incorporating new and revised structural inspection procedures and new and revised inspection intervals for the longitudinal skin joints in the fuselage pressure shell. This proposed AD also requires phase-in inspections and repair of any crack found during any phase-in inspection. This AD is prompted by a report indicating that visual inspections were not adequate for detecting fatigue cracking in portions of the longitudinal skin joints in the fuselage pressure shell. We are issuing this AD to detect and correct fatigue cracking of the longitudinal skin joints in the fuselage pressure shell, which could affect the structural integrity of the airplane, and result in loss of cabin pressurization during flight.
97-15-08: This amendment adopts a new airworthiness directive (AD) that is applicable to McDonnell Douglas Helicopter Systems (MDHS) Model 369D, E, F, FF, 500N, AH-6, and MH-6 helicopters. This action requires replacement of certain transmission output drive gears (gears). This amendment is prompted by several reports of spalled or fractured gear teeth, most of which occurred during high-power or external-lift operations. The actions specified in this AD are intended to prevent failure of the gear, which could result in loss of main rotor control and subsequent loss of control of the helicopter.
59-17-06: 59-17-06 HELIO: Applies to All Model H-391B Aircraft and Model H-395, Serial Number 075 and 502 Through 509 Inclusive. Compliance required within next 100 hours or by November 1, 1959, whichever occurs first. Install additional pulley guards at three 3-inch stabilator control system pulleys located at: (a) The upper left-hand corner of the fuselage truss just aft of the firewall. (b) Just forward of the lower left-hand side of the instrument panel. (c) Directly under the forward attach point of the vertical stabilizer in the aft portion of the tail cone. (The cable makes a 180 degree turn around this pulley.) (Helio Service Bulletin No. 20 covers this subject.)
75-26-09: 75-26-09 MORANE SAULNIER (SOCATA): Amendment 39-2460. Applies to MS892.A-150, MS893-A, and MS894-A airplanes, serial numbers 1873 and below, certificated in all categories. Compliance is required as indicated, unless already accomplished. To detect a distorted or bent elevator bellcrank and prevent loss of pitch-up control, accomplish the following: (a) Within the next 10 hours' time in service after the effective date of this Ad, and thereafter at intervals not to exceed 100 hours' time in service from the last inspection, visually inspect the elevator bellcrank (pitch control crank lever) in accordance with Socata Service Bulletin No. 89 GR 27.07, dated June 1971, or an FAA-approved equivalent. (b) If a bent or distorted elevator bellcrank is found as a result of an inspection required by paragraph (a) of this AD, before further flight, replace the elevator bellcrank, No. 880-27.0.261.0, with a reinforced elevator bellcrank, No. 880-27.0.371.0, in accordance with the "Description" paragraph of Socata Service Bulletin No. 92 Gr:27-08, dated October 1971, or an FAA-approved equivalent. (c) The inspections required by paragraph (a) of this AD may be discontinued after installation of a reinforced bellcrank, No. 880-27.0.371.0, in accordance with the Socata Service Bulletin No. 92 Gr:27-08, dated October 1971, or an FAA-approved equivalent. This amendment becomes effective December 29, 1975.
92-15-02: 92-15-02 BEECH AIRCRAFT CORPORATION: Amendment 39-8295. Docket No. 92-NM-04-AD. Applicability: Beech Model 400 airplanes, serial numbers RJ-1 through RJ-65, inclusive; Mitsubishi Model MU-300 airplanes, serial numbers A003SA through A091SA, inclusive; and Mitsubishi Model MU-300-10 airplanes, serial numbers A1001SA through A1011SA, inclusive; certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent reduced structural integrity of the engine mounting system, accomplish the following: (a) Within 200 hours time-in-service after the effective date of this AD, or at the next scheduled inspection interval, whichever occurs first, replace each engine mount nut and bolt with nuts and bolts that have been inspected using magnetic particle techniques (identified by green dye), in accordance with Beechcraft Service Bulletin 2408, dated June 1991 (for Beech Model 400 and Mitsubishi Model MU- 300-10 airplanes); or Mitsubishi Service Bulletin 71-004, dated January 8, 1992 (for Mitsubishi Model MU-300 airplanes); as applicable. (b) An alternative method of compliance or adjustment of the compliance time that provides an acceptable level of safety may be used if approved by the Manager, Wichita Aircraft Certification Office (ACO), ACE-115W, FAA, Small Airplane Directorate. Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, Wichita ACO. NOTE: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Wichita ACO. (c) Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate the airplane to a location where the requirements of this AD can be accomplished. (d) The replacement shall be done in accordance with Beechcraft Service Bulletin 2408, dated June 1991 (for Beech Model 400 and Mitsubishi Model MU-300-10 airplanes); or Mitsubishi Service Bulletin 71-004, dated January 8, 1992 (for Mitsubishi Model MU-300 airplanes); as applicable. 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 Beech Aircraft Corporation, P.O. Box 85, Wichita, Kansas 67201-0085. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, Washington; or at FAA, Wichita Aircraft Certification Office, 1801 Airport Road, Room 100, Mid-Continent Airport, Wichita, Kansas; or at the Office of the Federal Register, 1100 L Street NW., Room 8401, Washington, DC. (e) This amendment becomes effective on August 18, 1992.
2005-12-12: The FAA is adopting a new airworthiness directive (AD) to supersede AD 79-10-15, which applies to all Cessna Aircraft Company (Cessna) Models 401, 401A, 401B, 402, 402A, 402B, 411, and 411A airplanes. AD 79-10-15 currently requires repetitive inspections of the right and left wing spar lower cap areas for fatigue cracks and requires wing spar cap repair or replacement as necessary. This AD is the result of fatigue and crack growth analyses of the wings of these airplanes, recent cracks found on similar design Model 402C airplanes, and the FAA's determination that repetitive inspections and a wing spar modification are necessary to address the unsafe condition. Consequently, this AD would require repetitive inspections and a spar strap modification on each wing. The actions specified by this AD are intended to prevent wing spar cap failure caused by undetected fatigue cracks. Such failure could result in loss of a wing with consequent loss of airplane control. FAA is also issuing AD 2005-12-13 to require the spar strap modification and long-term inspections on Models 402C and 414A airplanes.
86-18-08: 86-18-08 SHORT BROTHERS PLC: Amendment 39-5388. Applies to Models SD3-30 and SD3-60 airplanes listed in Short Brothers PLC Service Bulletins SD3-28-22, Revision 2, dated July 1985 (for Model SD3-30 airplanes), and SD360-28-06, Revision 2, dated July 1985 (for Model SD3-60 airplanes), certificated in any category. Compliance is required within 90 days after the effective date of this AD. To prevent erroneous or erratic fuel quantity indications caused by moisture ingress into the fuel tank gauging system co-axial connectors, accomplish the following, unless previously accomplished: A. Seal the affected co-axial connectors in accordance with Short Brothers PLC, Service Bulletins SD3-28-22, Revision 2, dated July 1985, for Model SD3-30 airplanes, and SD360-28-06, Revision 2, dated July 1985, for Model SD3-60 airplanes. 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. 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 Shorts Aircraft, 1725 Jefferson Davis Highway, Suite 510, Arlington, Virginia 22202. These documents may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or the Seattle Aircraft Certification Office, 9010 East Marginal Way South, Seattle, Washington. This amendment becomes effective September 11, 1986.
67-28-05: 67-28-05 PRATT & WHITNEY: Amdt. 39-495 Part 39 Federal Register October 21, 1967. Applies to Models JT3D-1, JT3D-1-MC6, JT3D-1-MC7, JT3D-3, and JT3D-3B Turbofan Engines with First Stage Fan Hubs, P/N 431001, that have not been inspected in accordance with Pratt & Whitney Aircraft Turbojet Engine Service Bulletin No. 1219, dated June 3, 1966, or later FAA-approved revision, and reworked in accordance with Pratt & Whitney Aircraft turbojet engine Service Bulletin No. 1066; dated October 25, 1965, or Service Bulletin No. 1219, dated June 3, 1966, or later FAA-approved revisions of these bulletins. Compliance required as indicated. (a) Before further flight, unless already accomplished within the last four cycles and thereafter at intervals not to exceed four cycles from the last inspection, visually inspect front of first stage fan hub, P/N 431001, with 6000 or more cycles since new for the JT3D-1, JT3D-1-MC6, JT3D-1-MC7, or JT3D-3 and JT3D- 3B turbofan engine models operated at JT3D-1 engine power ratings, or 4000 or more cycles since new for turbofan engine models operated at JT3D-3 or JT3D-3B engine power ratings, for indications of cracks emanating from root of fan blade slots, using a glass of at least 3-power. (b) If indications of cracks are found, remove hub from service before further flight, except that the airplane may be flown in accordance with FAR 21-197 to a base where the hub can be removed. (c) For the purposes of this AD, the number of cycles equals the number of landings (including touch- and-go landings). (d) Upon submission of substantiating data through an FAA maintenance inspector, the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region, may adjust the repetitive inspection period of the operator. This amendment effective October 24, 1967. This Supersedes AD 66-17-03.
73-13-07: 73-13-07 GRUMMAN AMERICAN AVIATION CORPORATION: Amdt. 39-1669. Applies to all Model AA-1, Model AA-1A, and Model AA-1B airplanes through Serial Numbers AA-1B-0177 certificated in all categories. Compliance required within the next 10 hours time in service or 30 calendar days, whichever comes first, after the effective date of this airworthiness directive. To clearly indicate to the pilot that spins are prohibited in this make and model airplane, and to provide information to assist in preventing conditions that might lead to accidental spin entry, install the new placards as provided by Grumman American Aviation Corporation Service Bulletin No. 138 or by a suitable alternate procedure as approved by the Chief, Engineering and Manufacturing Branch, Great Lakes Region. This Amendment becomes effective June 25, 1973.
2016-12-02: We are adopting a new airworthiness directive (AD) for various aircraft equipped with a BRP-Powertrain GmbH & Co KG (formerly Rotax Aircraft Engines) 912 A series engine. This AD results from mandatory continuing airworthiness information (MCAI) issued 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 a design change of the engine cylinder head temperature sensor without a concurrent revision of the engine model designation, the engine part number, or the cockpit indication to the pilot. We are issuing this AD to require actions to address the unsafe condition on these products.