Results
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.
2016-11-13: We are superseding airworthiness directive (AD) 99-19-33 for BLANIK LIMITED Models L-13 Blanik and L-13 AC Blanik gliders (type certificate previously held by LET Aeronautical Works). 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 lack of distinct color marking of the elevator drive. We are issuing this AD to require actions to address the unsafe condition on these products.
71-14-02: 71-14-02 GOODRICH: Amdt. 39-1236. Applies to B. F. Goodrich 26 x 6.6, 14 PR; tubeless, 200 m.p.h. tire, S/N's 0318 AK 0000 through and including 0365 AK 9999. (a) Prior to next flight, visually inspect the tire, particularly on sidewall and shoulders, for bumps, blisters, or peeling. (b) Replace defective tires with tire or tires having S/N's outside of the subject group, or with an equivalent tire approved by the Chief, Engineering & Manufacturing Branch, FAA, Eastern Region. (c) If a tire within the subject group reveals no specified deficiency, it may be used for a maximum of five (5) landings thereafter, provided the tire is inspected prior to each flight in accordance with paragraph (a). Replace tires after five (5) landings in accordance with paragraph (b). This amendment is effective July 2, 1971, and was effective upon receipt for all recipients of the airmail letter, dated May 22, 1971, which contained this amendment.
76-02-02: 76-02-02 SOCIETE NATIONALE INDUSTRIELLE AEROSPATIALE: Amendment 39- 2495. Applies to Model SA341G "Gazelle" helicopters, certificated in all categories, equipped with horizontal transmission shafts P/N's 341A.34.1106.00, .01, .02, or .03, or coupling shafts P/N's 341A.34.1114.00, .01, or .02, or bearing attachment straps P/N 341A.34.1033.00. Compliance is required as indicated, unless already accomplished. To prevent possible failure of tail rotor drive system components and possible loss of control of the helicopter, accomplish the following: (a) Within the next 10 hours' time in service after the effective date of this AD, paint an alignment index line on bushings of the horizontal transmission shafts, P/N's 341A.34.1106.00, .01, or .03, and coupling shafts, P/N's 341A.34.1114.00, .01, or .02, to enable detection of relative rotation between bushings and shaft. (b) Upon the accomplishment of paragraph (a) of this AD and thereafter at intervals not to exceed 10 hours' time in service since the last inspection, inspect the bushings on both the horizontal transmission shaft and the coupling shaft for relative rotation between the bushings and the shaft, and rectify, as necessary, in accordance with subparagraph 1C(2) or Gazelle Service Bulletin No. 05.07, as revised June 18, 1975, or an FAA-approved equivalent. (c) Within the next 10 hours' time in service after the effective date of this AD and thereafter at intervals not to exceed 10 hours' time in service, since the last inspection, inspect the bearings on the coupling shaft and horizontal transmission shaft for grease leaks, rust run-outs, or seal damage and rectify, as necessary, in accordance with subparagraph 1C(3) of Gazelle Service Bulletin No. 05.07, as revised June 18, 1975, or an FAA-approved equivalent. (d) Within the next 10 hours' time in service after the effective date of this AD, and thereafter at intervals not to exceed 50 hours' time in service since the last inspection for assemblies 341A.34.1106.00, .01, and 341A.34.1114.00, or at intervals not to exceed 100 hours' time in service since the last inspection for assemblies 341A.34.1106.02, .03, and 341A.34.1114.01, .02, inspect bearings and attachment straps, and rectify, as necessary, in accordance with subparagraph 1C(4) of Gazelle Service Bulletin No. 05.07, as revised June 18, 1975, or an FAA-approved equivalent. This amendment becomes effective on January 30, 1976.
86-10-01: 86-10-01 PRATT & WHITNEY: Amendment 39-5292. Applies to Pratt & Whitney (PW) JT9D-3A series turbofan engines. Compliance is required as indicated, unless already accomplished. To preclude second stage turbine disk failures resulting from rearward deflection of the second stage turbine nozzle guide vane inner shroud, inspect second stage nozzle guide vanes, Part Number (P/N) 770372, in accordance with the Accomplishment Instructions of PW Alert Service Bulletin (ASB) 5619, dated July 31, 1985, or FAA approved equivalent, per the following schedule: (a) Inspect vanes for rearward deflection prior to accumulating 4,000 hours in service since new or since the vanes were refurbished, and reinspect thereafter per paragraph (b). (b) Reinspect at the following intervals and until such time as the engine incorporates a complete set of new or refurbished vanes with zero time in service, at which time the requirements of paragraph (a) become applicable. (1) Within the next 1,000 hours in service since last inspection, if the vane deflection is greater than 0.050 inches but not greater than 0.070 inches. (2) Within the next 2,000 hours in service since last inspection, if the vane deflection is less than or equal to 0.050 inches. (c) Remove from service, prior to further flight, vanes that have a rearward deflection greater than 0.070 inches. NOTES: 1. Refurbished vanes are defined as vanes which have been operated in service and have subsequently been inspected and repaired to the specifications in Pratt & Whitney Engine Manual, P/N 646028. 2. Engine Manuals P/N 646028 and 770407 are identical for the JT9D-3A engine model and are both FAA approved. Upon request, an equivalent means of compliance may be approved by the Manager, Engine Certification Office, Aircraft Certification Division, New England Region, Federal Aviation Administration, 12 New England Executive Park, Burlington, Massachusetts 01803. Aircraft may be ferried in accordance with the provisions of FAR Sections 21.197 and 21.199 to a base where the AD can be accomplished. Upon submission of substantiating data by an owner or operator through the FAA maintenance inspector, the Manager, Engine Certification Office, New England Region, may adjust the compliance time specified in this AD. PW ASB 5619, dated July 31, 1985, 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 Pratt & Whitney, Publication Department, P.O. Box 611, Middletown, Connecticut 06457. This document also may be examined at the Office of the Regional Counsel, New England Region, Federal Aviation Administration, 12 New England Executive Park, Burlington, Massachusetts 01803, Rules Docket Number 85-ANE-22, Room Number 311, between the hours of 8:00 a.m. and 4:30 p.m., Monday though Fridayexcept Federal holidays. This amendment becomes effective on June 5, 1986.
84-19-05: 84-19-05 GULFSTREAM AEROSPACE CORPORATION: Amendment 39-4925. Applies to Models 690 and 690A, (S/Ns 11001 through 11284 which have had engine isolator assemblies replaced after July 28, 1975); 690A (S/Ns 11285 through 11344); 690B (S/Ns 11350 through 11566); 690C (S/Ns 11600 through 11732); 690D (S/Ns 15001 through 15033 and 15037); 695 (S/Ns 95000 through 95084); 695A (S/Ns 96001 through 96061, 96063 through 96072, 96075, 96078, 96085, and 96088) airplanes certificated in any category. Compliance: Required as indicated, unless already accomplished. To prevent failure of the engine mount systems accomplish the following: (a) Within 50 hours time-in-service after the effective date of this AD, inspect and modify, if required, the engine mount systems in accordance with Gulfstream Aerospace Corporation Service Bulletin SB201 issued May 11, 1984. (b) Airplanes may be flown in accordance with FAR 21.197 to a location where this AD may be accomplished. (c) An equivalentmethod of compliance with this AD may be used if approved by the Manager, Airplane Certification Branch, ASW-150, FAA, Southwest Region, Post Office Box 1689, Fort Worth, Texas 76101; telephone (817) 877-2070. This amendment becomes effective on October 8, 1984.
2005-13-34: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 777-200 and -300 series airplanes, that requires replacing existing ceiling and sidewall light connectors in the passenger cabin with new connectors, and follow-on actions. This action is necessary to prevent overheating of the light connectors, which could result in smoke and a possible fire in the passenger cabin. This action is intended to address the identified unsafe condition.
74-23-09: 74-23-09 BEECH: Amendment 39-2006. Applies to those Model 23 (Serial Numbers M- 1, M-2, M-4 through M-554), Model A23-19 (Serial Numbers MB-1 through MB-288), Model 19A (Serial Number MB-289 through MB-460), Model M19A (Serial Numbers MB-461 through MB-480), and Model B23 (Serial Numbers M-1095 through M-1284) airplanes which were originally approved in the Acrobatic Category and intentional spins in the Utility and Acrobatic Categories. Compliance: Required as indicated, unless already accomplished. To prevent inflight situations in which prompt spin recovery may not be assured, accomplish the following: A) Effective immediately intentional spins in the Utility and Acrobatic Categories are prohibited. B) Within the next 20 hours' time in service or ten (10) calendar days, whichever comes first, after the effective date of this AD, remove all placards pertaining to intentional spins and acrobatic flight and install in place thereof a placard to be conspicuouslylocated on the instrument panel which reads as follows: "THIS AIRPLANE MUST BE OPERATED AS A NORMAL OR UTILITY CATEGORY AIRPLANE. INTENTIONAL SPINS ARE PROHIBITED. NO ACROBATIC MANEUVERS APPROVED EXCEPT: CHANDELLES, LAZY EIGHTS, STEEP TURNS, AND STALLS (EXCEPT WHIP STALLS)." C) To reinstate the acrobatic category for those airplanes originally approved in the Acrobatic Category and intentional spins in Utility and Acrobatic Categories, install Beech spin improvement Kit No. 23-4007-1 or 23-4007-5 or subsequent revisions in accordance with instructions contained therein. Kit 23-4007-1 is applicable to the Models A23-19, 19A, M19A and B23 airplanes. Kit 23-4007-5 is applicable to the Model 23 serial numbers M1, M2, M4 thru M-554 airplanes. Any equivalent method must be approved by the Chief, Engineering and Manufacturing Branch, FAA, Central Region. Upon installation of the appropriate kit, the requirements of Paragraphs A and B of this AD are no longer applicable.NOTE: Kits from the manufacturer may not be available for some models until after December 15, 1974. This amendment becomes effective November 14, 1974.
97-14-14: This amendment adopts a new airworthiness directive (AD) that applies to certain Industrie Aeronautiche E Meccaniche (I.A.M.) Model Piaggio P-180 airplanes that are equipped with a certain freon air conditioning system. This AD requires inspecting the baggage compartment for stringer or air cycle machine (ACM) by-pass duct damage, repairing any damage found, and modifying the freon air inlet duct and electrical wiring. This AD results from trim system malfunction on one of the affected airplanes, resulting from contact between the freon air inlet duct and the electrical wiring. The actions specified by this AD are intended to prevent trim system malfunction caused by contact between the freon air inlet duct and electrical wiring, which could result in loss of control of the airplane.
70-02-06: 70-02-06 BRITTEN-NORMAN, LTD: Amdt. 39-914. Applies to Britten-Norman Models BN.2 and BN.2A airplanes. Compliance is required within the next 50 hours' time in service, unless already accomplished. To reduce the possibility of failure of the elevator trim tab attachment structure due to cracking, accomplish the following: (a) Visually inspect the elevator trim tab hinge attachment structure for cracks in the angle of the elevator trailing edge member and elevator skin forward of the trim tab. (b) If cracks are found during the inspection required by paragraph (a) which do not exceed four inches in length, repair the cracks in accordance with Britten-Norman Service Bulletin No. BN-2/SB.1, Issue 5, dated 23 June 1969, or an FAA-approved equivalent, before reinforcing the elevator structure as required by paragraph (d). (c) If cracks are found during the inspection required by paragraph (a) which exceed four inches in length, replace the cracked member before reinforcingthe elevator structure as required by paragraph (d). (d) Reinforce the elevator structure by modifying the elevator trailing edge structure at the trim tab outboard hinge in accordance with Britten-Norman Modification Leaflet No. BN.2/NB/M/339, Issue 1, dated 23 July 1969, or an FAA-approved equivalent. This amendment becomes effective January 11, 1970.