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47-47-10: 47-47-10 REPUBLIC: (Was Mandatory Note 13 of AD-769-2.) Applies to Model RC-3 Aircraft. Compliance required prior to February 1, 1948. To prevent possible float strut failures during rough water landings, install wing reinforcing angles 17W21028, float strut brace assemblies 17W22013, spacers 17W22011 and lugs 17W22010. (Republic Service Bulletin No. 19 dated September 9, 1947, covers this same subject.)
60-17-03 R1: 60-17-03 R1 SIKORSKY: Amendment 191 as amended by Amendment 495, Amendment 747, Amendment 199, Amendment 39-1552, Amendment 39-2212, and Amendment 39-2743 is further amended by Amendment 39-6097. Applicability: All S-58 series helicopters. (Docket No. 88-ASW-49) Compliance: Required as indicated unless already accomplished. As a result of a fatigue failure of the main rotor blade spar the following must be accomplished: (a) All main rotor blade assemblies (less cuff) P/N's S1615-20100, -2, -4, -5, -6, S1615-20201-1, -2, -7, -8, -13 and -14, with 1,330 or more hours' time in service shall be removed from service before further flight. (b) An X-ray inspection covering the complete cross sectional area of the spar from the root section to the tip of the blade must be conducted for cracks, internal flaws on inclusions in the material of the spar on all main rotor blade assemblies P/N'S S1615-20100, -2, -4, -5, -6, S1615-20201-1, -2, -7, -8, -13, -14, within the following time specified: (1) All main rotor blades with 800 or more hours' time in service, prior to the next flight. (2) All main rotor blades with less than 800 hours' time in service, within the next 100 hours' time in service except no rotor blade shall exceed 800 hours' time in service before X-ray inspection is conducted. (c) Pending completion of the X-ray inspection in paragraph (b)(2), a daily visual inspection must be conducted on the spar of all blades with 500 or more hours' time in service as follows: (1) Using a magnifying glass of not less than 8-power, inspect the external surface of the spar from the root section to the tip of the blade for cracks. (2) Inspection of the upper surface of the spar must be conducted with the blade in normal static position. (3) Inspection of the lower surface of the spar must be conducted by disconnecting the pitch controls and rotating the blade 180 degrees in pitch so that the surface beinginspected is in tension due to the blades own dead weight. (d) If any cracks, internal flaws or inclusions are found in the spar material the blade must be replaced prior to further flight. (e) The service life limit specified in (a) may be extended to 3,200 hours' total time in service for S1615-20201-7, -8, and -14 main rotor blade assemblies (less cuff) and S1615-20100, -2, -4, -5, -6, S1615-20201-1, -2, and -13 main rotor blade assemblies modified to S1615-20201-7, -8, or -14 assemblies, provided the blade assemblies are inspected at the times and in the manner set forth in Sikorsky Service Bulletin No. 58B15-4K, dated July 16, 1976 or later FAA approved revisions and, if low pressure is indicated, the cause is determined and corrected before further flight in accordance with that service bulletin. NOTE: The check for black or red color indication on the pressure indicator for the main rotor blades, as specified in Part IV (Items 1 and 2) of the accomplishment instructions of Sikorsky Service Bulletin No. 58B15-4, may be accomplished by a properly trained pilot. Results of the requirements of checks must be recorded in accordance with the requirements of FAR Section 43.9. (f) Upon request an alternate means of compliance which provides an equivalent level of safety with the requirements of this AD may be used when approved by the Manager, Rotorcraft Standards Staff, Aircraft Certification Service, ASW-110, FAA, Fort Worth, Texas 76193-0110. (g) In accordance with Sections 21.197 and 21.199, the helicopter may be flown to a base where compliance may be accomplished. This amendment amends Amendment 191 (25 FR 8026), AD 60-17-03, as amended by Amendment 495 (27 FR 10117), Amendment 747 (29 FR 7668), Amendment 199 (31 FR 3064), and Amendment 39-1552 (37 FR 23711), Amendment 39-2212 (40 FR 22249), and Amendment 39-2743 (41 FR 44998) which was effective October 26, 1976. This amendment (39-6097, AD 60-17-03 R1) becomes effective February 2, 1989.
2015-23-08: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 737-100,-200,-200C,-300,-400, and -500 series airplanes. This AD was prompted by reports of cracks in fuselage frames, and a report of a missing strap that was not installed on a fuselage frame during production. This AD requires an inspection to determine if the strap adjacent to a certain stringer is installed, and repair if it is missing; repetitive inspections of the frame for cracking or a severed frame web; and related investigative and corrective actions if necessary. This AD also provides optional actions to terminate certain repetitive inspections. We are issuing this AD to detect and correct missing fuselage frame straps and frame cracking that can result in severed frames which, with multiple adjacent severed frames, or the combination of a severed frame and fuselage skin chemical mill cracks, can result in uncontrolled decompression of the airplane.
2010-20-14: We are adopting a new airworthiness directive (AD) for certain Model DC-10-10, DC-10-10F, DC-10-15, DC-10-30, DC-10-30F (KC-10A and KDC-10), DC-10-40, DC-10-40F, MD-10-10F, MD-10-30F, MD-11, and MD-11F airplanes. This AD requires installing an in-line fuse in certain float level switches and sleeving the wires between the fuel tank and the in- line fuse. For certain airplanes, this AD also requires installing an in-line fuse in certain fuel pump pressure switches. This AD results from fuel system reviews conducted by the manufacturer. We are issuing this AD to prevent fuel tank explosions and consequent loss of the airplane.
2000-19-03: 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 a one-time inspection of the coupling hinge and locking fastener of the Gamah couplings of the fuel system tubing located in the wing dry bay to detect discrepancies, and follow-on corrective actions. This action is necessary to prevent failure of the rivets of the Gamah couplings and consequent separation of a Gamah coupling, which could result in fuel leakage and consequent fire in or around the wing. This action is intended to address the identified unsafe condition.
80-19-09 R1: 80-19-09 R1 GATES LEARJET: Amendment 39-3913 as amended by Amendment 39-3998. Applies to the following Model 23, 24, 25, 28, 29, 35 and 36 series airplanes certificated in all categories: Model Serial Numbers *23 (equipped with jet pumps) 23-003 thru 23-099 24 24-100 thru 24-357 25 25-003 thru 25-319 28 28-001 thru 28-005 29 29-001 and 29-002 35 35-001 thru 35-348 36 36-001 thru 36-045 *NOTE: Model 23 airplanes were not equipped with jet pumps when manufactured. Model 23 airplanes which have been retrofitted with jet pumps in the field will be so identified on the title page of the Airplane Flight Manual. COMPLIANCE: Required as indicated unless already accomplished. To reduce the possibility of fuel contamination and/or the presence of ignition sources in the tailcone service area, accomplish the following: A) Within the next 25 hours time-in-service after May 8, 1980: 1. Run each engine to takeoff thrust momentarily, shut downand immediately open the access cover under the tailcone service area and make the following visual inspections: a. Inspect the fuel and hydraulic system components for deterioration or damage, leakage and stains indicating leakage, paying particular attention to the exterior of the P/N AV16E1182 motive flow shutoff valves. b. Inspect the batteries and electrical equipment for deterioration or damage and conditions which may cause arcing. c. Inspect all vents and drains for obstruction or blockage. d. Before further flight, correct any of the above-noted unsatisfactory conditions. Do not disassemble or reassemble motive flow shutoff valves in the field. Replace leaking valves with a new or factory rebuilt part. 2. Remove the Temporary Airplane Flight Manual Supplement, included in AD 80-09-06 as Figure 1, in the existing Airplane Flight Manual and in place thereof, install Temporary Airplane Flight Manual Supplement, included in this AD as Figure 1A, and comply with its instructions. B) On or before February 13, 1981, install Gates Learjet motive flow valve shrouds and drain lines per Modification Kit No. AMK 80-7. After accomplishing this modification, remove the Temporary Airplane Flight Manual Supplement required by Paragraph A)2. C) Airplanes may be flown in accordance with FAR 21.197 to a location where the provisions of this AD can be accomplished. D) Any equivalent method of compliance with this AD must be approved by the Chief, Aircraft Certification Program Office, Room 238, Terminal Building 2299, Mid-Continent Airport, Wichita, Kansas 67209; Telephone (316) 942-4285. This AD supersedes AD 80-09-06, Amendment 39-3764. Amendment 39-3913 became effective September 15, 1980. This amendment 39-3998 becomes effective December 11, 1980. FIGURE 1A TEMPORARY AIRPLANE FLIGHT MANUAL SUPPLEMENT FOR GATES LEARJET MODELS 23, 24, 25 , 28, 29, 35 AND 36 SERIES AIRPLANES (AD 80-19-09 requires this supplement to remain in the below designated Airplane Flight Manual until replaced by an equivalent Gates Learjet Company Flight Manual Supplement.) Model ________ N ________ S/N ________ In addition to the presently specified post-flight procedures, immediately after the engines are shut down, open the access cover under the tailcone service area and accomplish the following, using a flashlight or supplemental light as necessary for adequate illumination. 1. Check the motive flow valves for leaks or stains indicating leaks. 2. Check all vents and drains to assure that they are clean and free from obstruction. 3. Any leaking motive flow valve must be replaced with a new or factory rebuilt part prior to further flight. 4. Secure access cover.
2000-19-04: This amendment adopts a new airworthiness directive (AD) that applies to certain Raytheon Aircraft Company (Raytheon) Beech Models 1900C, 1900C (C-12J), and 1900D airplanes. This AD requires you to install a spiral wrap around the wing fuel quantity wiring harness and apply an adhesive sealant to the Wiggins couplings on the internal fuel tank wiring carry-through conduit. This AD is the result of reports of chafed or shorted wing fuel quantity harness wires on the affected airplanes. These occurrences were found during regular maintenance inspections. The actions specified by this AD are intended to prevent chafing between the wing fuel quantity wiring harness and the internal wing harness supports at each wing rib location, which could cause the fuel quantity indication to become unreliable. This could leave the flight crew without an indication of the amount of fuel the airplane has during flight. The actions are also intended to prevent fuel from leaking through the wiring carry-through conduit and into the wing tip or wheel well area, which could lead to a fire or explosion.
2015-23-05: We are adopting a new airworthiness directive (AD) for all Airbus Model A330-200, A330-200 Freighter, and A330-300 series airplanes; and Model A340-200 and A340-300 series airplanes. This AD was prompted by reports of cracked support strut body ends at a certain frame location of the trimmable horizontal stabilizer (THS). This AD requires repetitive inspections for cracking of the strut ends of the THS support located at a certain frame in the tail cone, and replacement if necessary; and reinstallation or installation of reinforcing clamps on certain strut ends. We are issuing this AD to detect and correct cracked support strut body ends of the THS, which could lead to the loss of all four THS support struts, making the remaining structure unable to carry limit loads, resulting in the loss of the horizontal tail plane.
2010-20-19: 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: Two cases of a crack on a "dry'' ADG [air driven generator] (Hamilton Sundstrand part number in the 761339 series), in the aft area of the strut and generator housing assembly, have been reported on CL-600-2B19 aircraft. The same part is also installed on CL-600- 2C10, -2D15 and -2D24 aircraft. Investigation determined that the crack was in an area of the strut where the wall thickness of the casting was below specification, due to a manufacturing anomaly in a specific batch of ADGs. Structural failure and departure of the ADG during deployment could possibly result in damage to the aircraft structure. If deployment was activated by a dual engine shutdown, ADG structural failure would also result in loss of hydraulics for the flight controls. * * * * * We are issuing this AD to require actions to correct the unsafe condition on these products.
2000-18-12: This amendment adopts a new airworthiness directive (AD) that applies to all Polskie Zaklady Lotnicze Spolka zo.o. (PZL-Mielac) Models PZL M18, PZL M18A, and PZL M18B airplanes. This AD requires you to repetitively inspect the centerwing-to-outboard wing attach joints for cracks in the lugs, corrosion in the main holes, and ovalization of the main holes; repair corrosion and apply anti-corrosion protection; replace the wing attach joints, as necessary; and eliminate any ovalization of the wing main joint holes. This AD is the result two instances of in-flight wing separation on Model PZL M18A airplanes where severe corrosion and pitting led to high stress concentrations on the wing attachment joints. The actions specified by this AD are intended to detect and correct cracks in the lugs, corrosion in the main holes, and ovalization of the main holes, in the centerwing-to-outboard wing attach joints. Such damage could result in failure of the joints with consequent in-flight wing separation.
2000-18-11: This amendment adopts a new airworthiness directive (AD) that is applicable to certain Israel Aircraft Industries, Ltd., Model 1125 Westwind Astra series airplanes. This action requires revising the Airplane Flight Manual to provide the flight crew with operational guidance under certain failure conditions and a limitation not to engage the long-range navigation system during takeoff, approach, or landing. This action is necessary to prevent the loss of primary attitude and directional gyros, which relate position information to the flight crew. This action is intended to address the identified unsafe condition.
2015-23-10: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 747-8 series airplanes. This AD was prompted by a report of improperly installed outboard stowage bin modules in the passenger compartment found during maintenance. Further investigation revealed that certain attachment bracket bushings were missing or had moved out of the holes. This AD requires installing a spacer on the end of each quick-release pin that attaches the outboard stowage bin module to the lateral support tie rods of the main deck passenger compartment. We are issuing this AD to prevent detachment of the quick-release pin, which could result in separation of the lateral support tie rod and subsequent detachment of the module and consequent injuries to passengers or flightcrew.
2000-18-08: This amendment adopts a new airworthiness directive (AD) for MD Helicopters, Inc. (MDHI) Model MD-900 helicopters that requires modifying the non-rotating swashplate assembly and re-identifying it and the swashplate assembly with new part numbers. This AD also requires creating a component history card or equivalent record to track the life of the newly identified non-rotating swashplate assembly and establishing a life limit of 1800 hours time-in-service (TIS). Additionally, this AD requires inspecting and modifying, if necessary, the longitudinal drive link assembly. This AD is prompted by reports of damage to the longitudinal drive link assembly caused by the sharp inner edge of the bushing in the non-rotating swashplate assembly. The actions specified by this AD are intended to prevent damage to the longitudinal drive link, loss of control of the main rotor system, and subsequent loss of control of the helicopter.
92-23-05: 92-23-05 AIRBUS INDUSTRIE: Amendment 39-8405. Docket No. 91-NM-244-AD. Supersedes AD 90-14-05, Amendment 39-6648. Applicability: Model A300 series airplanes equipped with General Electric engines; up to and including airplane serial number 153 and serial number 157; on which Airbus Industrie Modification 8430 has not been installed; certificated in any category. Compliance: Required as indicated, unless accomplished previously. To ensure proper operation of the fire extinguishing system, accomplish the following: (a) Within 400 hours time-in-service after July 23, 1990 (the effective date of Amendment 39-6648, AD 90-14-05), perform an inspection of the engine fire extinguishing pipe in the pylon area at rib 12, in accordance with Airbus Industrie All Operators Telex (AOT) 26/90/01, dated February 9, 1990, and Correction, dated February 9, 1990. If chafing is found, prior to further flight, repair in accordance with the AOT. (b) If no evidence of chafing is found as a result of the inspection required by paragraph (a) of this AD, perform repetitive visual inspections of the engine fire extinguishing pipe in the pylon area at rib 12 at intervals not to exceed 8,000 hours time-in-service, in accordance with Airbus Industrie Service Bulletin A300-26-055, Revision 1, dated September 4, 1991, or Revision 2, dated December 18, 1991. If wear is found that exceeds 0.6 mm (0.023 inch), prior to further flight, repair or replace the worn pipe in accordance with the service bulletin. (c) Within 18 months after the effective date of this AD, modify the engine fire extinguishing pipe, and test the fire extinguishing bottles, in accordance with Airbus Industrie Service Bulletin A300-26-055, Revision 1, dated September 4, 1991, or Revision 2, dated December 18, 1991. (d) Modification of the engine fire extinguishing pipe, in accordance with Airbus Industrie Service Bulletin A300-26-055, Revision 1, dated September 4, 1991, or Revision 2, dated December 18, 1991, constitutes terminating action for the repetitive visual inspections required by paragraph (b) of this AD. (e) 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, Standardization Branch, ANM-113, FAA, Transport 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, Standardization Branch. NOTE: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Standardization Branch. (f) 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. (g) The inspections, repair, replacement, modification, and test shall be done in accordance with the following Airbus Industrie service bulletins, as applicable, which contain the specified effective pages: Service Bulletin Referenced and Date Page Number Revision Level Shown on Page Date Shown on Page All Operators Telex (AOT) 26/90/01, February 9, 1990 1-2 (Original) February 9, 1990 Correction to All Operators Telex (AOT) 26/90/01, February 9, 1990 1 (Original) February 9, 1990 A300-26-055, Revision 1, September 4, 1991 1-22 1 September 4, 1991 A300-26-055, Revision 2, December 18, 1991 1, 5-6, 8-28 2-4, 7 2 1 December 18, 1991 September 4, 1991 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 Airbus Industrie, Airbus Support Division, Avenue Didier Daurat, 31700 Blagnac, France. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. (h) This amendment becomes effective on December 14, 1992.
91-13-02: 91-13-02 AIRBUS INDUSTRIE: Amendment 39-7033. Docket No. 90-NM-227-AD. Applicability: Model A310-200 series airplanes, serial numbers 162 through 378, inclusive; on which Modification 4942 has not been incorporated (reference Airbus Industrie Service Bulletin A310-53-2013, Revision 1, dated April 17, 1986); certificated in any category. Compliance: Required as indicated, unless previously accomplished. To prevent reduced structural integrity of the fuselage, accomplish the following: A. Prior to the accumulation of 12,000 landings, or within 6 months after the effective date of this AD, whichever occurs later, and thereafter at intervals not to exceed 3,000 landings, perform a visual inspection of the cabin floor structure between Frame 40 and Frame 46, in accordance with Airbus Industrie Service Bulletin A310-53-2056, dated April 18, 1990. B. If cracks are found, prior to further flight, replace the affected part or modify the corresponding area in accordance with Airbus Industrie Service Bulletin A310-53-2013, Revision 1, dated April 17, 1986. The modified area no longer needs to be inspected in accordance with paragraph A. of this AD. Unmodified areas must be inspected at intervals not to exceed 3,000 landings. C. Modification of the cabin floor structure between Frame 40 and Frame 46, in accordance with Airbus Industrie Service Bulletin A310-53-2013, Revision 1, dated April 17, 1986, constitutes terminating action for the repetitive visual inspections required by paragraphs A. and B. of this AD. D. 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. E. 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 Airbus Industrie, Airbus Support Division, Avenue Didier Daurat, 31700 Blagnac, France. These documents may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 1601 Lind Avenue S.W., Renton, Washington. This amendment (39-7033, AD 91-13-02) becomes effective on July 15, 1991.
2015-16-07 R1: We are adopting a new airworthiness directive (AD) for REIMS AVIATION S.A. Model F406 airplanes. This AD revises AD 2015-16-07, which required inspection of the left-hand and right-hand rudder control pedal torque tubes, and, depending on findings, replacement with a serviceable part. This AD retains the actions of AD 2015-16-07 and adds additional acceptable serviceable replacement parts. The AD was prompted by reports of detachment of the pilot's rudder control pedal in flight. We are issuing this AD to require actions to address the unsafe condition on these products.
76-10-04: 76-10-04 START & FLUG: Amendment 39-2612. Applies to H101 "Salto" gliders, certificated in all categories. Compliance is required as indicated unless already accomplished. To prevent possible failure of the cockpit canopy locking device and the consequent inability of the pilot to use his parachute, accomplish the following: (a) Within the next 10 hours time in service after the effective date of this AD, either (1) Install an operating limitations placard on the instrument panel in full view of the pilot to read as follows: "ACROBATIC MANEUVERS PROHIBITED;" or (2) Modify the cockpit canopy fastening mechanism by installing polyamide stop blocks on both canopy fastening mechanisms in accordance with Start & Flug GmbH Technical Note No. 101-8, dated May 1, 1974 and Drawing No. 101-14-34, undated, or FAA-approved equivalents. (b) The placard specified in paragraph (a)(1) of this AD, if installed, may be removed upon the incorporation of the modification described in paragraph (a)(2) of this AD. This amendment becomes effective May 27, 1976.
2000-18-13: This amendment supersedes an existing airworthiness directive (AD) that applies to Eurocopter Canada Ltd. Model BO 105 LS A-3 helicopters. That AD currently requires, before further flight, creating a component log card or equivalent record and determining the calendar age and number of flights on each tension-torsion (TT) strap, and inspecting and removing, as necessary, certain unairworthy TT straps. This amendment establishes a life limit for certain main rotor TT straps. This amendment is prompted by an accident in which a main rotor blade (blade) separated from a Eurocopter Deutschland GMBH (ECD) Model MBB-BK 117 helicopter due to fatigue failure of a TT strap. The same part-numbered TT strap is used on the Model BO 105 LS A-3 helicopters. The actions specified by this AD are intended to prevent fatigue failure of a TT strap, loss of a blade, and subsequent loss of control of the helicopter.
85-17-07: 85-17-07 CESSNA: Amendment 39-5125. Applies to the following Cessna airplanes certificated in any category: MODEL SERIAL NUMBER U206F/TU206F S/N U20601071 thru U20603521 U206G/TU206G S/N U20603522 thru U20604649 207/T207 S/N 20700001 thru 20700315 207A/T207A S/N 20700363 thru 20700767 Compliance: Required within the next 100 hours time-in-service after the effective date of this AD unless already accomplished. To prevent a possible failure in the wing rear spar on airplanes that have had the full spar or inboard end of the spar replaced, accomplish the following: (a) Visually inspect the airplane in accordance with Cessna Single Engine Service Bulletin SEB85-9 dated May 3, 1985. If the P/N 1222111-1 doubler is missing, prior to further flight repair the spar in accordance with SEB85-9. (b) Airplanes may be flown in accordance with FAR 21.197 to a location where this AD may be accomplished. (c) An equivalent method of compliance with this AD may be used if approved by Manager, Wichita Aircraft Certification Office, Federal Aviation Administration, 1801 Airport Road, Room 100, Wichita, Kansas 67209; Telephone (316) 946-4400. All persons affected by this directive may obtain copies of the document referred to herein upon request to Cessna Aircraft Company, Post Office Box 1521, Wichita, Kansas 67201 or FAA, Office of the Regional Counsel, Room 1558, 601 East 12th Street, Kansas City, Missouri 64106. This amendment becomes effective on September 30, 1985.
2000-18-09: This amendment adopts a new airworthiness directive (AD) for Bell Helicopter Textron, Inc. (BHTI) Model 412, 412EP, and 412CF helicopters. This AD requires inspecting the upper left-hand cap angle (cap angle) and adjacent structure for a crack and, before further flight, replacing any cracked cap angle and repairing any crack in the adjacent structure. This AD is prompted by a report of a fatigue crack in a tailboom attachment cap angle. The actions specified in this AD are intended to prevent failure of a cap angle, loss of the tailboom, and subsequent loss of control of the helicopter.
2000-18-10: This amendment adopts a new airworthiness directive (AD) for Kaman Model K-1200 helicopters. This action requires replacing certain unairworthy sprag clutches with airworthy sprag clutches. This amendment is prompted by two incidents of sprag clutch failure during external load operations. The actions specified in this AD are intended to prevent a malfunctioning transmission clutch, loss of drive to the main rotor system, and subsequent loss of control of the helicopter.
79-20-04: 79-20-04 LOCKHEED-CALIFORNIA COMPANY: Amendment 39-3576. Applies to all L-1011-385-1, L-1011-385-1-14, and L-1011-385-1-15 series airplanes certificated in all categories. Compliance required as indicated. To provide a warning to the flight crew of an occurrence of a potentially hazardous jam in the elevator drive system prior to takeoff, and thus prevent takeoff with a possible jammed elevator drive system on the horizontal stabilizer of the primary pitch control system which can result in degradation of the airplane controllability, accomplish the following: (a) Within the next ten (10) days after the effective date of this AD, unless the elevator drive system jam warning system of paragraph (b) is installed and is operational on all aircraft of each operator's fleet, initiate the following check program: (1) Prior to each takeoff, conduct an exterior visual check of the elevator/stabilizer surface positions after the full aft controls check and with the control column full forward to assure there is no obvious discrepancy between elevator positions. The pilot-in- command shall be informed of the results of this check. NOTE: This check can be accomplished with any one single hydraulic system pressurized by any main hydraulic system pump. (2) If obvious discrepancy is noted, correct prior to further flight. (3) No further full aft control column movement may be performed prior to takeoff. A placard must be installed in the flight station in full view of the pilot to inform the pilot of the requirements of this subparagraph. (b) On or before July 1, 1981, unless already accomplished, install the elevator drive system jam warning system in accordance with FAA approved Lockheed-California Company Service Bulletin 093-27-174, dated August 3, 1979. The visual exterior checks of paragraph (a), above, may be discontinued upon installation and operation of the warning system on all aircraft of each operator's L-1011 fleet. (c) All elevator surface jam conditions indicated by the warning system of paragraph (b) must be corrected prior to further flight. (d) If the elevator drive system jam warning system is not fully operative prior to initiation of flight operations, the aircraft may be allowed to dispatch provided the visual exterior check of paragraph (a) is accomplished. (e) Alternative checks, installations or other actions which provide an equivalent level of safety may be used when approved by the Chief, Aircraft Engineering Division, FAA Western Region. This amendment becomes effective October 11, 1979.
2000-18-02: This amendment adopts a new airworthiness directive (AD) that applies to certain Raytheon Aircraft Company (Raytheon) Models A65, A65-8200, 65-B80, 70, 95-A55, 95-B55, 95-C55, D55, E55, 56TC, A56TC, 58, 58P, 58TC, 95-B55B (T42A) airplanes. This AD requires replacement of certain elevator skin assemblies that Raytheon shipped from January 1, 1999, through December 31, 1999, and prevents the future installation of these elevator skin assemblies. This AD authorizes the pilot to check the logbooks to determine whether one of these elevator skin assemblies is installed. This AD is the result of reports that certain elevator skin assemblies did not receive a 250-degree Fahrenheit bake operation after corrosion treatment, thus making the skin susceptible to separation from the elevator assembly. The actions specified by this AD are intended to detect and correct potential elevator skin separation, which would lead to a reduction in static strength capability with continued operation. This could then result in potential airplane flutter with consequent loss of control of the airplane. The Federal Aviation Administration (FAA) must receive any comments on this rule on or before October 27, 2000.
2000-18-06: This amendment adopts a new airworthiness directive (AD), that is applicable to Allison Engine Company AE 3007A and AE 3007C series turbofan engines with certain full authority digital electronic controls (FADEC's), listed by hardware serial number (SN), installed. This action requires inspections of installed FADEC's before further flight to be sure that no more than one engine with suspect FADEC's is installed on the same airplane, and eventual replacement of all of the suspect FADEC's with serviceable FADEC's. This amendment is prompted by reports of uncommanded in-flight shutdowns of engines. The actions specified in this AD are intended to prevent an uncommanded in-flight engine shutdown and the potential for an in-flight dual-engine shutdown caused by a potential hardware failure mode in some AE 3007 series FADEC's.
97-12-01: 97-12-01 CESSNA AIRCRAFT COMPANY: Amendment 39-10044. Docket 97-NM-101-AD. Applicability: Model 650 airplanes, having serial numbers 650-0174 through 650-0241 inclusive, 650-7001 through 650-7006 inclusive, and 650-7008 through 650-7076 inclusive, certificated in any category. NOTE 1: This AD applies to each airplane identified in the preceding applicability provision, regardless of whether it has been otherwise modified, altered, or repaired in the area subject to the requirements of this AD. For airplanes that have been otherwise modified, altered, or repaired so that the performance of the requirements of this AD is affected, the owner/operator must request approval for an alternative method of compliance in accordance with paragraph (b) of this AD. The request should include an assessment of the effect of the modification, alteration, or repair on the unsafe condition addressed by this AD; and, if the unsafe condition has not been eliminated, the request should include specific proposed actions to address it. Compliance: Required as indicated, unless accomplished previously. To prevent electrical arcing of the alternating current wire and consequent fire hazard, accomplish the following: (a) Within 25 hours time-in-service after the effective date of this AD, accomplish paragraphs (a)(1), (a)(2), and (a)(3) of this AD, in accordance with the Accomplishment Instructions of Cessna Service Bulletin SB650-24-57, dated May 15, 1997. (1) Perform a visual inspection to detect discrepancies (i.e., improper clearance, wear, and damage) of the wire bundle assembly from point 1 to point 2, in accordance with the service bulletin. If any discrepancy is detected, prior to further flight, replace the wire bundle assembly with a new wire bundle assembly or install a spiral wrap, as applicable, in accordance with the service bulletin. (2) Perform a visual inspection to detect discrepancies (i.e., chafing, rubbing, nicks, scratches, and burn marks) of the hydraulic pump suction line in the area above the baggage compartment, in accordance with the service bulletin. If any discrepancy is detected, prior to further flight, repair it in accordance with the service bulletin. (3) Modify the supports for the wire bundle cable assembly and the supports for the hydraulic pump suction line in accordance with the service bulletin. (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), 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 2: 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 sections 21.197 and 21.199 of the Federal Aviation Regulations (14 CFR 21.197 and 21.199) to operate the airplane to a location where the requirements of this AD can be accomplished. (d) The inspections and modification shall be done in accordance with Cessna Service Bulletin SB650-24-57, dated May 15, 1997. 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 Cessna Aircraft Co., P.O. Box 7706, Wichita, Kansas 67277. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the FAA, Wichita Aircraft Certification Office, Small Airplane Directorate, 1801 Airport Road, Room 100, Mid-Continent Airport, Wichita, Kansas; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. (e) This amendment becomes effective on June 19, 1997.