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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).