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48-13-06: 48-13-06 BELLANCA: Applies to Models 14-13, 14-13-2 Serial Numbers 1060 Through 1310. Compliance required after each 25 hours of operation. To prevent failure of the four engine-cowl-support brackets, Bellanca P/N 9892-13, mounted on the firewall and possible cowl loss in flight, the brackets should be closely examined for cracks. If cracks are noted, heavier brackets available from the factory should be installed, in which case inspection is no longer required. (Bellanca Service Bulletin No. 16 dated December 8, 1947, covers this same subject.)
68-20-08: 68-20-08 SIKORSKY: Amdt. 39-633 as amended by Amendment 39-665 is further amended by Amendment 39-1141. Applies to S-61A, S-61L and S-61N Type Helicopters. To assure proper adjustment of the Automatic Flight Control System (AFCS) accomplish the following: A. Prior to next AFCS flight inspect all AFCS electrical connectors for electrical integrity, pin alignment and perform a functional test of the AFCS system including amplifier and amplifier rack connectors Cannon Part No. DPJ-98-33S-B or DPJM-98-33S-B and box mating connectors Part No. DPJ-98-34P-A. B. Prior to the first AFCS flight each day accomplish the following checks: 1. A pitch stick sensor check on the ground with electrical and hydraulic power "ON" as follows (a) engage the AFCS (b) place C.G. trim knob to center of its travel (c) select "P" on null indicator switch (d) move pitch cyclic stick to center the null indicator (e) verify that forward stick motion deflects the needle to the right. 2. A roll stick sensor check on the ground with electrical and hydraulic power "ON" as follows: (a) Engage AFCS (B) select "R" on null indicator (c) move roll cyclic stick to center the null indicator (d) verify that left stick motion deflects the needle to the left. 3. A pitch and roll AFCS hard-over check on the ground in accordance with Sikorsky Service Bulletin No. 61B65-1 Paragraphs B-1 thru B-4 dated April 12, 1967, or later FAA approved revision or alternate check approved by the Chief, Engineering & Manufacturing Branch, Eastern Region. 4. Yaw Hard-over check on the ground as follows: (a) position null indicator switch to position "Y" and position pedals to full right position (b) position yaw channel disengage switch to "ON" and yaw hard-over switch to "LEFT". Verify that pointer on null indicator also moves hard-over and pedals start motion to the left (c) verify that it is possible to push right pedal to override hard-over condition (d) position hard-over switch to "RIGHT" and pedals to the full left position. Verify that the pointer on null indicator moves hard-over and pedals start motion to the right. (e) Verify that it is possible to push left pedal to override hard- over condition. C. After the effective date of this AD as amended and prior to the next AFCS Flight, if not already accomplished, with AFCS "OFF" measure the adjustment of the auxiliary servo linkage, by placing dial indicators at the output of the servo and at the bolt located in the sloppy link to ascertain that the adjustment of the linkage is .010" or less in the "AUX-ON" and "AUX- OFF" positions. Perform stick jump test to further verify these measurements. Perform these checks in the roll attitude, pitch and yaw functions. D. Within the next 1200 hours time in service and thereafter at 1200 hour intervals of time in service, accomplish the following: 1. Perform AFCS hard-over check according to Sikorsky Service Bulletin No. 61B65-1 dated April 12, 1967 paragraph B-5, or alternate check approved by the Chief, Engineering and Manufacturing Branch, Eastern Region. E. Compliance with this AD is not required if the AFCS installation is disconnected. Amendment 39-633 was effective August 17, 1968. Amendment 39-665 was effective October 10, 1968. This Amendment, 39-1141, is effective January 14, 1971.
86-20-01: 86-20-01 MITSUBISHI: Amendment 39-5428. Applies to Models MU-2B, -10, -15, -20, -25, -26, -26A, -30, -35, -36, -36A, -40, and -60 (Serial Numbers 1 through 753 inclusive, with or without the SA suffix) airplanes certificated in any category. NOTE: The serial numbers of airplanes manufactured in the United States by MAI under Type Certificate A10SW are suffixed by "SA". The serial numbers of airplanes manufactured in Japan by MHI under Type Certificate A2PC have no suffix. Compliance required as indicated unless already accomplished. To assure anti-ice capability of pitot system and proper electric load distribution of anti-ice/deice circuits, accomplish the following: (a) Before next flight after the effective date of this AD: (1) Modify the following in accordance with Mitsubishi Heavy Industries (MHI) Ltd., Service Recommendation (SR) 053, Revision A, dated October 23, 1984, or Mitsubishi Aircraft International, (MAI) Inc. SR 020/34-005, Revision B, dated May 24, 1985, as applicable: (i) The electrical circuitry of the pitot tube and anti-ice/deice systems and, (ii) The pitot tube system by installing higher heat capacity pitot tube, P/N PH1100. (2) As an alternate means of compliance: (i) Before further flight: (A) Fabricate and install a temporary placard(s) in full view of the pilot, using letters of minimum 0.10 inch in height which state: (I) "FLIGHT IN KNOWN ICING CONDITIONS IS PROHIBITED". (II) "TURN PITOT HEAT ON DURING FLIGHT IN VISIBLE MOISTURE". (III) "Pilot and copilot airspeed indicators may display erroneous data after: (a) Flight in visible moisture; (b) Outside storage in rain without pitot covers; or (c) Washing of airplane. Refer to AFM for corrective action", and (B) On the "TYPES OF OPERATION" placard located in the cockpit delete, using opaque tape, the words "ICING CONDITIONS", and (C) Add the following information to the "LIMITATIONS" section of the FAA Approved Airplane Flight Manual (AFM) which supersedes any other AFM information which may be contradictory: (I) "FLIGHT in known icing conditions is PROHIBITED", and (II) "TURN PITOT HEAD HEATER ON DURING FLIGHT IN VISIBLE MOISTURE", and (III) "The pilot and copilot airspeed indicator may display erroneous data after any: (a) Flight in visible moisture, or (b) Period of outside storage in rain with no pitot covers installed, or (c) Washing of airplane with no pitot covers installed. If erroneous airspeed indication(s) has (have) been observed, corrective action is required prior to next flight by draining the affected pitot line(s) and performing the 'OPERATIONAL CHECK OF PITOT LINE' in accordance with the applicable Mitsubishi MU-2 maintenance manual." (ii) Within the next 100 hours time-in-service after the effective date of this AD, modify the electrical circuitry of the pitot tube and anti-ice/deice systems in accordance with the applicable service information as follows: A. Mitsubishi Heavy Industries International (MAI) Ltd., Service Recommendation (SR) 053, Revision A, dated October 23, 1984, or B. Mitsubishi Aircraft International (MAI), Inc. SR 020/34-005, Revision B, dated May 24, 1985. (iii) Replacement of the existing pitot tube(s) with the high heat producing pitot tube(s) in accordance with paragraph (a)(1)(ii) of this AD may be delayed until September 1, 1988, if compliance with paragraph (a)(2)(i) of this AD is accomplished prior to further flight. (b) Insertion of a copy of this AD in the "LIMITATIONS" section of the AFM satisfies the requirements of paragraph (a)(2)(i)(C) of this AD. (c) The requirements of paragraphs (a)(2)(i)(A), (a)(2)(i)(B) and (b) of this AD may be accomplished by the holder of a pilot certificate issued under Part 61 of the Federal Aviation Regulations on any airplane owned or operatedby him. The person accomplishing these actions must make the appropriate aircraft maintenance record entry as prescribed by FAR 91.173. (d) Remove the temporary placard(s) and AFM textual addition required by paragraph (a)(2)(i) of this AD when the requirements of paragraph (a)(1) of this AD are accomplished. (e) Airplanes may be flown in accordance with FAR 21.197 to a location where this AD may be accomplished. (f) An equivalent method of compliance with this AD may be used on the MHI airplanes, if approved by the Manager, Western Aircraft Certification Office, ANM-170W, Federal Aviation Administration, P.O. Box 92007, Worldway Postal Center, Los Angeles, California, 90009-2007, and on the MAI airplanes, if approved by the Manager, Wichita Aircraft Certification Office, ACE-115W, 1801 Airport Road, Room 100, Mid-Continent Airport, Wichita, Kansas, 67209. All persons affected by this directive may obtain copies of the documents referred to herein upon request toBeech Aircraft Corporation (Licensee for Mitsubishi), 9709 East Central, P.O. Box 85, Wichita, Kansas 67201, or FAA, Office of the Regional Counsel, Room 1558, 601 East 12th Street, Kansas City, Missouri 64106. This amendment supersedes Amendment 39-5006 (50 FR 8321) as amended by Amendment 39-5328 (51 FR 21515), AD 85-04-03R1. This amendment becomes effective October 6, 1986.
2000-04-15: This amendment adopts a new airworthiness directive (AD) applicable to Bell Helicopter Textron Canada (BHTC) Model 222, 222B, 222U, and 230 helicopters. This action requires inspecting the swashplate assembly drive pin (drive pin) for damage or looseness, torque testing to determine if the interference fit between the drive pin and rotating ring (ring) is adequate, and replacing any unairworthy drive pin. This amendment is prompted by an accident investigation that revealed fatigue failure of a drive pin. The actions specified in this AD are intended to prevent fatigue failure of a drive pin and subsequent loss of control of the helicopter.
93-03-02: 93-03-02 BEECH AIRCRAFT CORPORATION: Amendment 39-8501; Docket No. 93-CE-09-AD. Applicability: The following model and serial number airplanes equipped with a Bendix/King KLN-88 Loran receiver system, certificated in any category: Models Serial Numbers F33A CE-1620, CE-1640, CE-1655, CE-1659, CE-1662, CE-1680, CE-1682, and CE-1693 A36 E-2563, E-2564, E-2575, E-2582, E-2599, E-2604, E-2614, E-2631, E-2633, E-2643, E-2645, E-2650, E-2660, E-2664, E-2673, E-2675, E-2680, E-2681, E-2688, E-2690, E-2693, E-2695, E-2698, E-2711, E-2727, E-2728, E-2737, E-2738, E-2743, E-2746, and E-2752. B36TC EA-515, EA-516, EA-519, EA-522, EA-524, and EA-529. 58 TH-1581, TH-1588, TH-1592, TH-1597, TH-1598, TH-1599, TH-1600, TH-1602, TH-1612, TH-1616, TH-1621, TH-1623, TH-1627, TH-1628, TH-1632, TH-1633, TH-1640, TH-1642, TH-1646, TH-1650, TH-1651, TH-1653, TH-1661, TH-1663, TH-1668, TH-1672, and TH-1673. Compliance: Required within the next 50 hourstime-in-service after the effective date of this AD, unless already accomplished. To prevent the display of a Loran lateral deviation signal when the instrument landing system localizer frequency is selected, which could result in navigational errors, accomplish the following: (a) Modify the wiring configuration of the switching system between the Bendix/King KLN-88 Loran receiver system and the instrument landing system localizer in accordance with the ACCOMPLISHMENT INSTRUCTIONS section of Beech Service Bulletin No. 2496, dated January 1993. (b) 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. (c) An alternative method of compliance or adjustment of the compliance time that provides an equivalent level of safety may be approved by the Manager, Wichita Aircraft Certification Office, FAA, 1801 Airport Road, Room 100, Wichita, Kansas 67209. The request shall be forwarded through an appropriate FAA Maintenance Inspector, who may add comments and send it to the Manager, Wichita Aircraft Certification Office. NOTE: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Wichita Aircraft Certification Office. (d) The modification required by this AD shall be done in accordance with Beech Service Bulletin No. 2496, dated January 1993. 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 the Beech Aircraft Corporation, P.O. Box 85, Wichita, Kansas 67201-0085. Copies may be inspected at the FAA, Central Region, Office of the Assistant Chief Counsel, Room 1558, 601 E. 12th Street, Kansas City, Missouri, or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. (e) This amendment (39-8501) becomes effective on March 12, 1993.
53-24-02: 53-24-02 HILLER: Applies to All Model UH-12, UH-12A and UH-12B Helicopters. Compliance required as indicated below. There have been several recent failures of the tail rotor pitch change rod on UH-12B helicopters, resulting in loss of directional control. This pitch change rod, P/N 25036 or 25009, must be reinforced and/or inspected as follows on all UH-12 Series helicopters. (1) Prior to the next flight and thereafter at periods not to exceed 10 hours operating time, remove the tail rotor pitch change arm and inspect the pitch change rod, P/N 25036 or 25009, in the shoulder area by dye penetrant method. If cracks are found the rod must be removed from service. If no cracks are found, the pitch change rod is considered satisfactory for an additional 10 hours operating time. On reassembling the parts determine that chamfer of hole in arm does not interfere with radius on rod. If interference is noted, enlarge chamfer on arm to clear. Reinstall arm on pitch change rod, making sure woodruff key or bolt properly locates arm and that arm bottoms on shoulder. Install washer and nut on rod and torque to 50-75 inch-pounds (UH-12 and -12A Models) or 100-150 inch-pounds (UH-12B Models). This periodic inspection must be continued until such time as the rod is reinforced as set forth in part (2). (2) When the pitch change rod is reinforced by the addition of bracket, Hiller P/N 25104, the 10-hour inspections may be discontinued. Installation of this bracket is described in Hiller Service Bulletin No. 41. The service life of this installation is limited to 300 hours from time of modification. This bracket, P/N 25104, should be installed as soon as possible but not later than January 31, 1954.
2014-20-16: We are adopting a new airworthiness directive (AD) for Brantly International, Inc. (Brantly) Model B-2, Model B-2A, and Model B-2B helicopters with certain main rotor blades. This AD requires inspecting each main rotor (M/R) blade for a crack or delamination and removing the blade if a crack exists or if the delamination exceeds certain thresholds. This AD was prompted by multiple reports of M/R blade cracks and an incident in which a crack that originated near the M/R blade trailing edge resulted in the loss of a large section of the M/R blade. The actions of this AD are intended to prevent loss of the M/R blade and subsequent loss of control of the helicopter.
91-14-02: 91-14-02 SAAB-SCANIA: Amendment 39-7044. Docket No. 91-NM-28-AD. Supersedes AD 90-16-02. Applicability: Model SF-340A series airplanes, Serial Numbers 031 through 159; and SAAB 340B series airplanes, Serial Numbers 160 through 186; certificated in any category. Compliance: Required as indicated, unless previously accomplished. To prevent inhibited airplane rudder control due to cracking in the vertical stabilizer top closure rib, accomplish the following: A. Prior to the accumulation of 500 hours time-in-service since new or within 100 hours time- in-service after August 30, 1990 (the effective date of Amendment 39-6676, AD 90-16-02), whichever occurs later, inspect the vertical stabilizer top closure rib for evidence of cracking, in accordance with SAAB Service Bulletin 340-55-022, Revision 1, dated February 27, 1990. B. If no evidence of cracking is found, reinspect the vertical stabilizer top closure rib for cracking at intervals not to exceed 500 flight hours time-in-service. C. If cracking is found, prior to further flight, stop drill the ends of the cracks, blend, clean, and apply aluminum tape, as specified in SAAB Service Bulletin 340-55-022, Revision 1, dated February 27, 1990. Reinspect for additional cracking and the condition of the aluminum tape at intervals not to exceed 100 hours time-in-service. D. Within one year after the effective date of this amendment, either replace the rib with a new thicker rib with a larger radius, or reinforce the rib and replace the attachment angle, in accordance with SAAB Service Bulletin 340-55-023, dated October 1, 1990. Accomplishment of either of these modifications constitutes terminating action for repetitive inspections required by paragraphs B. and C. of this AD. E. 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. F. 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 SAAB-Scania AB, Product Support, S-581.88, Linkoping, Sweden. These documents may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 1601 Lind Avenue S.W., Renton, Washington. Airworthiness Directive 39-7044 supersedes AD 90-16-02, Amendment 39-6676 which superseded AD 88-13-10, Amendment 39-5963. This amendment (39-7044, AD 91-14-02) becomes effective on July 29, 1991.
2000-03-09: This amendment supersedes an existing airworthiness directive (AD), applicable to certain Cessna Model 560 series airplanes, that currently requires revising the FAA-approved Airplane Flight Manual (AFM) to provide the flightcrew with limitations, operational procedures, and performance information to be used during approach and landing when residual ice is present or can be expected. This amendment is prompted by reports indicating that, while operating in icing conditions or when ice is on the wings, some of these airplanes have experienced uncommanded roll at (or slightly higher than) the speed at which the stall warning system is activated. This amendment requires revising the AFM and revises the applicability of the existing AD. This amendment also requires modification of the stall warning system of the angle-of-attack computer. The actions specified by this AD are intended to prevent uncommanded roll of the airplane during approach and landing when residual ice ispresent or can be expected.
2014-20-01: We are adopting a new airworthiness directive (AD) for certain Bombardier, Inc. Model CL-600-2B16 (CL-601-3A, CL-601-3R, and CL-604 Variants) airplanes. This AD requires repetitive inspections for any fuel leak in the right-hand landing lights compartment, and related investigative and corrective actions if necessary. This AD also provides for an optional replacement of the connector of the fuel boost pump canister of the auxiliary power unit (APU), which terminates the repetitive inspections. This AD was prompted by a report of fuel leaks in the connector cavity of the APU fuel boost pump canister and at the electrical conduit connection of the APU fuel boost pump in the right- hand landing lights compartment. We are issuing this AD to detect and correct fuel leaks in the right-hand landing lights compartment, which, in combination with the heat generated by the taxi lights and landing lights on the ground reaching the auto-ignition temperature of the fuel, could result in ignition of any fuel or fumes present in the right-hand landing lights compartment.
2004-14-06: This amendment supersedes an existing airworthiness directive (AD), applicable to certain Airbus Model A310 series airplanes, that currently requires repetitive inspections of the fuselage skin to detect corrosion or fatigue cracking around and under the chafing plates of the wing root; and corrective actions, if necessary. That AD also provides an optional terminating action for the repetitive inspections. This amendment reinstates repetitive inspections in certain areas where corrosion was detected and reworked as required by the existing AD. The actions specified by this AD are intended to detect and correct fatigue cracks and corrosion around and under the chafing plates of the wing root, which could result in reduced structural integrity of the airplane. This action is intended to address the identified unsafe condition. DATES: Effective August 13, 2004. The incorporation by reference of certain publications listed in the regulations is approved by the Director of the Federal Register as of August 13, 2004. The incorporation by reference of certain other publications, as listed in the regulations, was approved previously by the Director of the Federal Register as of June 3, 1998 (63 FR 23377, April 29, 1998).
83-17-05: 83-17-05 BEECH: Amendment 39-4715. Applies to Model E33C (Serial Numbers CJ-1 through CJ-25) and Model F33C (Serial Numbers CJ-26 through CJ-155) airplanes certificated in acrobatic and utility categories. \n\n\tCOMPLIANCE: Required as indicated, unless previously accomplished. \n\n\tTo prevent maneuvers which may develop into an unrecoverable spin, within the next 100 hours time-in-service after the effective date of this AD, accomplish paragraph a) or b) below. \n\n\ta)\tInstall Beech Spin Improvement Kit 33-4002-3 (E33C Serial Numbers CJ-1 through CJ-25 airplanes and F33C Serial Numbers CJ-26 through CJ-38 and CJ-40 through CJ-51 airplanes) or 33-4002-1 (F33C Serial Number CJ-39 and Serial Numbers CJ-52 through CJ-155 airplanes) in accordance with instructions contained in Beechcraft Class I Service Instruction No. 1249. \n\n\tb)\tRemove approval for operation of the airplane in acrobatic category in accordance with the following: \n\n\t\t1.\tPlace a copy of this AD in the limitations section of the Pilot's Operating Manual and FAA Approved Airplane Flight Manual. \n\n\t\t2.\tRemove the Airplane Flight Manual Supplement (Beech Part Number 33-590006-11, -13, or -17) pertaining to operation in the Acrobatic Category. \n\n\t\t3.\tCut both electrical leads to the acrobatic category fuel boost pump P/N 4140-00-191 (E33C Serial Numbers CJ-1 through CJ-25 and F33C Serial Numbers CJ-26 through CJ-148 airplanes) or P/N 1297-00-1 (F33C Serial Numbers CJ-149 through CJ-155 (airplanes) at a point near the pump motor housing. Cap and stow these leads per AC 43-13. \n\n\t\t4.\tReplace existing 3-position fuel boost pump switch P/N 35-380053-27 with 2-position switch P/N 35-380053-21, restoring electrical connections for correct operation of the auxiliary fuel boost pump P/N 4140-00-39 (E33C Serial Numbers CJ-1 through CJ-25 and F33C Serial Numbers CJ-25 through CJ-148 airplanes) or P/N 1296-00-1 (F33C Serial Numbers CJ-149 through CJ-155 airplanes). Cap and stow the unused electrical leadper AC 43-13. Secure knob P/N 96-384050-9 to the installed switch with LOCTITE 222 or equivalent bonding agent. \n\n\t\t5.\tModify the auxiliary fuel pump operation placard (including switch position placarding) to read as follows: \n\n\n\n\n\n\n\t\t6.\tObliterate the words "Remove door hold open rod prior to operation in Acrobatic Category" from the placard on the cabin door side panel. \n\n\t\t7.\tRemove the following placards on the left hand sidewall: \n\n\nDURING ACROBATIC CATEGORY \nOPERATION OCCUPANCY \nLIMITED TO PILOT'S OR PILOT'S \nAND COPILOT'S SEAT \n\n\t\tand, if installed, \n\nREMOVE THIRD & FOURTH \nPASSENGER SEATS \nPRIOR TO OPERATION \nIN ACROBATIC CATEGORY \n\n\t\t8.\tObliterate from the airplane operation limitations placards on the left side panel the heading "Acrobatic Category Airplane" and all portions of the placard under that heading. \n\n\t\t9.\tObliterate the word "AEROBATIC" located below the pilot's and co-pilot's window on the exterior of the airplane. \n\n\t\t10.\tOn ModelE33C (Serial Numbers CJ-1 through CJ-25) airplanes, obliterate from P/N 33-590003-7 Pilot's Operating Handbook and FAA Approved Airplane Flight Manual: \n\n\t\t\ti)\tOn the cover page, the words "ACROBATIC See Flight Manual Supplement" after "E33C." \n\n\t\t\tii)\tOn page 9-3, "33-590006-17 Acrobatic Bonanza E33C." \n\n\t\t11.\tOn Model F33C (Serial Numbers CJ-26 through CJ-128) airplanes: \n\n\t\t\ti)\tIn P/N 33-590009-9 Pilot's Operating Manual and FAA Approved Airplane Flight Manual: \n\n\t\t\t\tA)\tObliterate the following: \n\n\t\t\t\t\t1)\tOn Page 5-8, all information pertaining to F33C Acrobatic Category limits. \n\n\t\t\t\t\t2)\tOn Page 8-1, "Pilot's Operating Manual Acrobatic Supplement P/N 33-590006-9." \n\n\t\t\t\t\t3)\tOn Page 8-3, "33-590006-11 Acrobatic Supplement for the F33C 11/3/72." \n\n\t\t\t\tB)\tRemove P/N 33-590006-9 Pilot's Operating Manual Supplement or \n\n\t\t12.\tIn P/N 33-590009-15A1 Pilot's Operating Handbook and FAA Approved Airplane Flight Manual: \n\n\t\t\ti)\tObliterate the following: \n\n\t\t\t\tA)\tOn the cover page, the word "Acrobatic" after F33C and the words "See Flight Manual Supplement" after CJ-128. \n\n\t\t\t\tB)\tOn page 6-1: \n\n\t\t\t\t\t1)\t"Sample Weight and Balance Load Form (Acrobatic Category) - 6-17." \n\n\t\t\t\t\t2)\t"Weight and Balance Loading Form (Acrobatic Category) - 6-18." \n\n\t\t\t\tC)\tOn page 6-12, all information pertaining to F33C Acrobatic Category limits. \n\n\t\t\t\tD)\tOn page 9-3, "33-590006-11 Acrobatic Supplement for the F33C, Rev. No. 2/11/77." \n\n\t\t\t\t\tii)\tRemove pages 6-17 and 6-18. \n\n\t\t13.\tOn Model F33C (Serial Numbers CJ-129 through CJ-155) airplanes, obliterate from P/N 33-590009-13A3 Pilot's Operating Handbook and FAA Approved Airplane Flight Manual the following: \n\n\t\t\ti)\tOn page 6-10, all information pertaining to F33C Acrobatic Category limits. \n\n\t\t\tii)\tOn cover page: \n\n\t\t\t\tThe word "Acrobatic" before F33C and the words "(See Flight Manual Supplement)" after "CJ-129 and after." \n\n\t\t\tiii)\tOn page 9-3, "33-590006-13 Acrobatic Supplement for the F33C Rev. No. 2/9/78." \n\n\t\t14.\tRemove the existing Utility/Acrobatic Category Airworthiness Certificate and replace it with a new Utility Category Airworthiness Certificate as provided in Paragraph b 15 of this AD. \n\n\t\t15.\tObtain a new Utility Category Airworthiness Certificate from any FAA General Aviation District Office or Flight Standards District Office by presenting a completed FAA Form 8130-6, Application for Airworthiness Certificate, together with the removed Utility/Acrobatic Category Airworthiness Certificate, citing compliance with this AD as reason for the replacement. \n\n\tc)\tAn equivalent method of compliance with this AD may be used if approved by the Manager, Wichita Aircraft Certification Office, FAA, Room 238, Terminal Building 2299, Mid-Continent Airport, Wichita, Kansas 67209; telephone (316) 269-7000. \n\t\n\tThis amendment becomes effective October 1, 1983.
97-01-07: This amendment adopts a new airworthiness directive (AD), applicable to all British Aerospace Model BAe 146 and Avro 146-RJ series airplanes, that requires modification of the left and right elevators, and replacement of the elevator spring with a stiffer spring. This amendment is prompted by reports indicating that water and ice have accumulated at the trailing edge of the left and right elevators; this accumulation can cause the elevators to become unbalanced, and oscillate or flutter. The actions specified by this AD are intended to prevent this oscillation or flutter. Elevator oscillation, if not corrected, could result in reduced controllability of the airplane. Elevator flutter, if not corrected, could couple with the natural vibrations of the airplane, and result in loss of the airplane s structural integrity.
90-21-05: 90-21-05 AEROSPATIALE: Amendment 39-6757. Docket No. 90-NM-68-AD. Applicability: All Model ATR42-300 and ATR42-320 series airplanes, certificated in any category. Compliance: Required as indicated, unless previously accomplished. To prevent the propeller brake from overheating and causing damage to the engine, accomplish the following: A. Within 100 hours time-in-service after May 29, 1989 (the effective date of AD 88- 14-06 R1) for airplanes listed in Aerospatiale Service Bulletin ATR42-61-0013, Revision 1, dated December 8, 1987, modify the propeller brake electronic control wiring, in accordance with this service bulletin. B. Within 100 hours time-in-service after May 29, 1989 (the effective date of AD 88- 14-06 R1), for the airplanes listed in Aerospatiale Service Bulletin ATR42-61-0014, Revision 2, dated November 15, 1988, modify the propeller brake control unit, in accordance with this service bulletin. C. Within 100 hours time-in-service after May 29, 1989 (the effective date of AD 88- 14-06 R1), for the airplanes listed in Aerospatiale Service Bulletin ATR42-61-0010, Revision 3, dated December 19, 1988, replace the pushbutton switch with a two-position mechanical switch, in accordance with this service bulletin. D. Within 180 days after the effective date of this AD, install a new brake control unit in accordance with Aerospatiale Service Bulletin ATR42-61-0005, Revision 2, dated January 2, 1990; Revision 3, dated March 15, 1990; or Revision 4, dated June 19, 1990. E. Within 180 days after the effective date of this AD, install a modified propeller brake in accordance with Aerospatiale Service Bulletin ATR42-61-0022, Revision 1, dated September 25, 1989, or Revision 2, dated March 15, 1990. F. Within 180 days after the effective date of this AD, modify the propeller brake indicating logic, in accordance with Aerospatiale Service Bulletin ATR42-61-0023, Revision 1, dated December 1, 1989; or Revision 2, dated March 15, 1990. G. As an alternative to paragraphs A. through F. of this AD, operators may remove the propeller brake from the airplane in accordance with Aerospatiale Service Bulletin ATR42-61- 0016, Revision 1, dated September 1, 1988. H. An alternate means of compliance or adjustment of the compliance time, which provides an acceptable level of safety, may be used when approved by the Manager, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate. NOTE: The request should be submitted directly to the Manager, Standardization Branch, ANM-113, and a copy sent to the cognizant FAA Principal Inspector (PI). The PI will then forward comments or concurrence to the Manager, Standardization Branch, ANM-113. I. 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 Aerospatiale, 316 Route de Bayonne, 31060 Toulouse, Cedex 03, France. These documents may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 1601 Lind Avenue S.W., Renton, Washington. Airworthiness Directive 90-21-05 supersedes AD 88-14-06 (Amendment 39-5967) as revised by AD 88-14-06 R1 (Amendment 39-6202). This amendment (39-6757, AD 90-21-05) becomes effective on October 30, 1990.
2022-17-10: The FAA is superseding Airworthiness Directive (AD) 2021-19- 20, which applied to all Dassault Aviation Model FALCON 7X airplanes. AD 2021-19-20 required amending the existing airplane flight manual (AFM) to incorporate a check and an operating limitation regarding the O<INF>2</INF> saver function. This AD was prompted by reports of defects that may prevent efficient deactivation of the O<INF>2</INF> saver function of crew oxygen masks and a determination that the AFM amendment required by AD 2021-19-20 may not be sufficient to mitigate the risk. This AD retains the requirements of AD 2021-19-20 and also requires physical deactivation of the O<INF>2</INF> saver function, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. This AD also limits the installation of affected parts under certain conditions. The FAA is issuing this AD to address the unsafe condition on these products.
2000-04-09: This amendment adopts a new airworthiness directive (AD) that is applicable to certain EMBRAER Model EMB-135 and EMB-145 series airplanes. This action requires various inspections to detect discrepancies of the elevator servo tab and spring tab hinge fittings of the horizontal stabilizer, and follow-on corrective actions, if necessary. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified in this AD are intended to prevent the linkage of the elevator servo tab or spring tab hinge fittings from separating from the horizontal stabilizer, which could result in loss of control of the airplane.
2000-04-11: This amendment adopts a new airworthiness directive (AD) that is applicable to certain Airbus Model A319, A320, and A321 series airplanes. This action requires a revision to the Limitations and Normal Procedures Sections of the FAA-approved Airplane Flight Manual (AFM) to limit the use of the radio altimeter of the flight management guidance system (FMGS) during the approach phase of flight. This action also provides for an optional terminating modification, which, if accomplished, would terminate the requirement for the AFM revision. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified in this AD are intended to prevent erroneous display of decision height information to the flight crew during final approach, which could result in an increased risk of collision with the terrain.
2000-04-04: This amendment adopts a new airworthiness directive (AD), applicable to all Fokker Model F.28 Mark 0070 and 0100 series airplanes, that requires a measurement of the resistance of the electrical connectors of the auxiliary power unit (APU) to detect a short circuit; an inspection to determine if the grommets or shrink sleeves are present; and modification, if necessary. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to detect and prevent a short circuit of a fire extinguisher electrical system due to a lack of shrink sleeves or grommets, and consequent disabling of the affected fire extinguisher system.
86-21-06: 86-21-06 BRITISH AEROSPACE: Amendment 39-5417. Applies to BAe Model 125- 800A airplanes, serial numbers as listed in BAe Service Bulletin 24-251-(3014A), dated April 8, 1985, certificated in any category. Compliance is required within 60 days after the effective date of this AD, unless previously accomplished. To provide dedicated AC and DC ground terminals, accomplish the following: 1. Modify electrical wiring in accordance with BAe Service Bulletin 24-251- (3014A), dated April 8, 1985. 2. 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. 3. 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 document from the manufacturer, may obtain copies upon request to British Aerospace, Inc., Librarian, Box 17414, Dulles International Airport, Washington, D.C. 20041. This document may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or at the Seattle Aircraft Certification Office, 9010 East Marginal Way South, Seattle, Washington. This Amendment becomes effective October 20, 1986.
2014-20-08: We are adopting a new airworthiness directive (AD) for certain Lockheed Martin Corporation/Lockheed Martin Aeronautics Company Model L-1011 series airplanes. This AD was prompted by reports of cracked rib cap castellations. This AD requires repetitive inspections for castellation and skin clips cracked or damaged between stringers and cracked stringer clips of the wing box pylon back-up structure, and front spar to rear spar; repetitive inspections for cracking, damage, or failure of the pylon back-up torque box structure; repetitive inspections for cracking or damage of the wing box external areas at the drag brace aft wing fitting; repetitive inspections of the outer surface of the wing upper and lower skins for cracks or damage along the rib attachment at the fastener holes and between the two rows of attachment; and corrective actions if necessary. We are issuing this AD to detect and correct cracked or damaged rib cap castellations, which could degrade the structural capabilities of the airplane.
2000-04-05: This amendment adopts a new airworthiness directive (AD), applicable to certain Israel Aircraft Industries Model Astra SPX series airplanes, that requires a one-time inspection to measure the countersink angle of the bolt holes in the lower scissors fitting of the horizontal stabilizer, and corrective actions, if necessary. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to prevent cracks in the lower scissors fitting and fitting attachment bolts of the horizontal stabilizer, which could result in possible in-flight loss of the horizontal stabilizer and consequent reduced controllability of the airplane.
2014-19-05: We are adopting a new airworthiness directive (AD) for all Turbomeca S.A. Arriel 1A1, 1A2, 1B, 1C, 1C1, 1C2, 1D, 1D1, 1E2, 1K1, 1S, 1S1, 2B, 2B1, 2C, 2C1, 2C2, 2S1, and 2S2 turboshaft engines. This AD requires an initial one-time vibration check of the engine accessory gearbox (AGB) on certain higher risk Arriel 1 and Arriel 2 model engines. This AD also requires repetitive vibration checks of the engine AGB for all Arriel 1 and Arriel 2 engines at every engine shop visit. This AD was prompted by reports of uncommanded in-flight shutdowns on Turbomeca S.A. Arriel 1 and Arriel 2 engines following rupture of the 41-tooth gear forming part of the 41/23-tooth bevel gear located in the engine AGB. We are issuing this AD to prevent failure of the engine AGB, which could lead to in-flight shutdown and damage to the engine, which may result in damage to the aircraft.
2014-20-02: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 767-200, -300, -300F, and -400ER airplanes. This AD was prompted by reports indicating that a standard access door was located where an impact-resistant access door was required, and stencils were missing from some impact-resistant access doors. This AD requires an inspection of the wing fuel tank access doors to determine whether impact-resistant access doors are installed in the correct locations, and to replace incorrectly installed doors with impact- resistant access doors. This AD also requires an inspection for stencils and index markers on impact-resistant access doors, and application of new stencils or index markers if necessary. In addition, this AD requires revising the maintenance program to incorporate changes to the airworthiness limitations section. We are issuing this AD to correct the unsafe condition on these products.
2010-18-07: 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: A special detailed inspection of A318/A319/A320/A321 elevators pre-modification 35515 was introduced under ALI (Airworthiness Limitations Items) task 552007 in the ALS (Airworthiness Limitations Section) part 2 * * * This ALI task has been introduced with an applicability defined at aeroplane modification level. * * * * * It has been reported that some elevators may have been moved from the aeroplane on which they were originally fitted to another aeroplane, * * *. Consequently, those elevators might not have been inspected within the applicable required time frame as per ALI task 552007 requirements. * * * * * The unsafe condition is structural failure of the elevators and consequent loss of control of the airplane. This AD requires actions that are intended to address the unsafe condition described in the MCAI.
2000-04-02: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 737-100, -200, -300, -400, and -500 series airplanes, that requires repetitive testing of certain main tank fuel boost pumps to identify those with degraded performance, and replacement of degraded pumps with new or serviceable pumps. This AD also requires eventual replacement of the existing low pressure switches for boost pumps located in the main fuel tanks with higher threshold low pressure switches, which, when accomplished, terminates the repetitive testing. This amendment is prompted by reports of engine power loss caused by unsatisfactory performance of the fuel boost pumps. The actions specified by this AD are intended to prevent fuel suction feed operation on both engines without flight crew indication, and possible consequent multiple engine power loss.