Results
91-22-01: 91-22-01 CESSNA: Amendment 39-8061. Docket No. 91-CE-64-AD. Applicability: Model 210 airplanes (serial numbers (S/N) 21059062 through 21064535, S/N T210-0393 through T210-0454, and S/N P21000001 through P21000760), certificated in any category. Compliance: Required within the next 50 hours time-in-service, unless already accomplished. To prevent fuel leakage caused by damaged fuel lines, which could result in an in-flight fire, accomplish the following: (a) Inspect the electrical wires in the nose gear tunnel area and the fuel line to the engine-driven fuel pump for cracks or chafing. (1) If any cracked or chafed electrical wire or fuel line is found, prior to further flight, replace with a new electrical wire or fuel line. Ensure that the electrical wires are bundled and route or clamp the wire bundle so there is a clearance of .25 inches between the wire bundle and fuel line to the engine-driven fuel pump. (2) If no cracked or chafed electrical wire or fuel line is found, ensure that the electrical wires are bundled and route or clamp the wire bundle so there is a clearance of .25 inches between the wire bundle and fuel line to the engine-driven fuel pump. NOTE: Cessna Service Information Letter SE82-32, dated July 23, 1982, includes a photo that highlights the inspection areas and clearance area that is referenced in this AD. This service information may be obtained from the Cessna Aircraft Company, P.O. Box 7704, Wichita, Kansas 67277. (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, Mid-Continent Airport, Wichita, Kansas 67209. The request should be forwarded throughan appropriate FAA Maintenance Inspector, who may add comments and then send it to the Manager, Wichita Aircraft Certification Office. (d) Information that is related to this AD may be obtained from the FAA, Central Region, Office of the Assistant Chief Counsel, Room 1558, 601 E. 12th Street, Kansas City, Missouri. This amendment (39-8061, AD 91-22-01) becomes effective on November 4, 1991.
2001-25-06: This amendment adopts a new airworthiness directive (AD) for Sikorsky Aircraft Corporation (Sikorsky) Model S-76B and S-76C helicopters. This action requires modifying the electrical power distribution system to change the source of the 28 volts supplied to Nos. 1 and 2 attitude and heading reference (AHRS) WARN circuits. This amendment is prompted by a ground test simulating loss of the essential bus by pulling both bus tie circuit breakers and switching off both batteries. As a result of this action, both autopilots went off-line. The actions specified in this AD are intended to prevent an AHRS fail signal to both autopilots due to a failure of the essential bus, loss of autopilot functions, and subsequent loss of control of the helicopter.
47-41-03: 47-41-03 BELL: (Was Mandatory Note 15 of AD-1H-2.) Applies to Models 47B and 47B3 Helicopters. Compliance required not later than next 50-hour inspection after December 1, 1947. To prevent failure of the fuel line connecting the fuel shutoff valve and auxiliary fuel pump, replace the rigid aluminum line with a flexible hose line. On Serial Numbers 2 through 5, 7 through 11, 13 and 14, replace P/N 47-686-001-37 with P/N AN 856A6A or AN 6270-6-14. (Bell Service Bulletin 47C46 dated June 19, 1947, covers the above installation.)
2017-14-14: We are adopting a new airworthiness directive (AD) for all Airbus Model A321 series airplanes. This AD was prompted by a determination from fatigue testing that cracks could develop in the cabin floor beam junction at certain fuselage frame locations. This AD requires repetitive inspections for cracking in the cabin floor beam junction at certain fuselage frame locations, and repair if necessary. We are issuing this AD to address the unsafe condition on these products.
2010-26-10: The FAA is superseding an existing airworthiness directive (AD), which applies to certain Model 747-200C, -200F, -400, -400D, and -400F series airplanes. That AD currently requires repetitive inspections for cracks in the overlapping (upper) skin of the upper fastener row of the lap joints of the fuselage skin in sections 41, 42, and 46; and related investigative and corrective actions, if necessary. This new AD expands the inspection area in the existing AD, and adds a modification of certain lap joints and certain post-repair inspections of the lap joints. Accomplishing the modification would end the repetitive inspections required by the existing AD for the length of lap joint that is modified. This AD results from a structural review of affected skin lap joints for widespread fatigue damage. We are issuing this AD to prevent fatigue cracking in certain lap joints, which could result in rapid depressurization of the airplane.
2001-24-21: This amendment supersedes an existing airworthiness directive (AD), applicable to all McDonnell Douglas Model DC-10 series airplanes, that currently requires a one-time detailed visual inspection to determine if wire segments of the wire bundle routed through the feed through on the aft side of the flight engineer's station are damaged or chafed, and corrective actions, if necessary. This amendment also requires revising the wire bundle support clamp installation at the flight engineer's station. This action is necessary to prevent chafing of the wire bundle located behind the flight engineer's panel caused by the wire bundle coming in contact with the lower edge of the feed through and consequent electrical arcing, which could result in smoke and fire in the cockpit. This action is intended to address the identified unsafe condition.
85-07-07: 85-07-07 SOCIETE NATIONALE INDUSTRIELLE AEROSPATIALE (SNIAS): Amendment 39-5020. Applies to Model SE3130, SE313B, SA3180, SA318B, SA318C, and SA315B helicopters, certificated in all categories, that are equipped with a tail rotor pitch change control rod that has been modified in accordance with AMS2178. Compliance is required within 50 hours time in service after the effective date of the AD or before the accumulation of 750 hours total time in service for tail rotor gearboxes, whichever occurs later, unless already accomplished. To ensure that proper shot peening of the control rod has been accomplished and thereby prevent possible cracks in the control rod, accomplish the following: (a) Comply with paragraph C of Aerospatiale Service Bulletin No. 01.19 or No. 01.50, dated May 2, 1984, for the appropriate helicopter model. Paragraph C of each bulletin contains disassembly, inspection, and assembly information. (b) Equivalent means of complying with this AD must be approved by the Manager, Aircraft Certification Office, FAA, Europe, Africa, and Middle East Office, c/o American Embassy, Brussels, Belgium. (c) Aircraft may be flown in accordance with FAR Sections 21.197 and 21.199 to a base where compliance may be accomplished. (d) The Director of the Federal Register approved the incorporation by reference of the manufacturer's specifications and procedures identified and described in this directive pursuant to 5 U.S.C. 552(a)(1). Persons may obtain copies of the service bulletins upon request to Aerospatiale Helicopter Corporation, 2701 Forum Drive, Grand Prairie, Texas 75051, Attention: Customer Support. The documents may be examined at the Office of the Regional Counsel, Southwest Region, Federal Aviation Administration, 4400 Blue Mound Road, Fort Worth, Texas. This amendment becomes effective April 19, 1985.
2017-14-07: We are adopting a new airworthiness directive (AD) for certain International Aero Engines AG (IAE) V2522-A5, V2524-A5, V2527-A5, V2527E-A5, V2527M-A5, V2530-A5, V2533-A5, V2525-D5, V2528-D5, and V2531-E5 turbofan engines. This AD was prompted following a self- disclosure by IAE regarding manufacturing quality escapes. This AD requires replacing the affected and suspect parts within the time limits specified in the compliance section. We are issuing this AD to address the unsafe condition on these products.
76-21-06: 76-21-06 CESSNA: Amendment 39-2750. Applies to Models 172M (Serial Numbers 17266981 thru 17267584); 172N (Serial Numbers 17267585 thru 67610, 612 thru 621, 623 thru 626, 628 thru 634, 636, 638 thru 648, 651 thru 655, 657, 658, 660 thru 666, 669, 670, 673 thru 679, 681, 682, 684 thru 687, 689, 691 thru 698, 700, 701, 703 thru 706, 708 thru 713, 715, 718, 722 thru 724, 727 thru 729, 732, 736, 738, 739, 74l thru 744, 746 thru 749, 752, 754, 756, 757, 759, 760, 763, 764, 770, 772, 776, 785, 791 and 800); 177B (Serial Numbers 17702450 thru 17702536, 17702538 thru 17702544); and 177RG (Serial Numbers 177RG0875 thru 177RG0990, 177RG0992 thru 177RG0995, 0997 thru 1000, 1002 and 1004) airplanes. Compliance: Required as indicated, unless already accomplished. To prevent loss of engine oil, accomplish the following: A) Before next flight of the affected airplanes, remove the lower engine cowl and visually inspect the engine oil cooler fluid fitting side to determine whetherit is a Model 8406J (S/N 101 thru 1500) or Model 10599A (S/N 101 thru 700). 1. If the oil cooler is not of the model and serial number listed above, make an entry in the aircraft maintenance records indicating that this AD has been accomplished and the airplane may be returned to service. 2. If the oil cooler is of a model and serial number listed above, prior to further flight, replace this cooler with a serviceable oil cooler not of the above model and serial numbers. B. The inspection and maintenance record entry required by Paragraph A(l) may be accomplished by holder of a pilot's certificate issued under Part 61 of the Federal Aviation Regulations on any aircraft owned or operated by him. C. Any equivalent method of compliance with this AD must be approved by the Chief, Engineering and Manufacturing Branch, FAA, Central Region. Cessna Service Letter SE76-17 pertains to this subject. NOTE: A ferry permit to accomplish a needed oil cooler replacementmay be issued under the provisions of FAR 21.197 by FAA District Offices, with appropriate limitations, in coordination with the Chief, Engineering and Manufacturing Branch, FAA. Central Region. This amendment becomes effective October 26, 1976, to all persons except those to whom it was made effective earlier by air mail letters issued September 21, 1976, and October 1, 1976, respectively.
49-34-02: 49-34-02 BELL: Applies to All Model 47D1 Helicopters. Compliance required as soon as possible but not later than September 2, 1949, and daily thereafter. As a result of several fatigue failures of the attaching clamps on the ventral fin and at the attaching bolt holes of the fixed tab, these parts should be visually inspected daily until a permanent fix is available. If cracks are detected, either in the AN 735 clamps, the ventral fin, or the fixed tab, the effected part should be replaced prior to the next flight. (Bell Service Bulletin No. 70 covers the same subject.)
89-22-11: 89-22-11 AIRBUS INDUSTRIE: Amendment 39-6364. Docket No. 89-NM-115-AD. Applicability: Model A300 B4-103 and B4-203 series airplanes, equipped with main landing gear (MLG) barrel hinge arms, Messier Part Number C65381-4 or -6, certificated in any category. Compliance: Required within 12 months after the effective date of this AD, unless previously accomplished. To prevent collapse of one main landing gear, accomplish the following: A. Except as provided in paragraph B., below, replace all main landing gear (MLG) hinge arms having a pad cadmium coating, with either hinge arms that do not have a pad cadmium coating or hinge arms that have been reconditioned in accordance with MHB Service Bulletin 470- 32-652, dated December 30, 1988. Replacement is required in accordance with the procedures specified in Airbus Industrie Service Bulletin A300-32-390, Revision 1, dated December 20, 1988. NOTE: Airbus Service Bulletin A300-32-390 references Messier-Hispano-Bugatti (MHB) Service Bulletin 470-32-651 for additional replacement procedures. B. The following airplanes are not subject to the requirements of this AD: 1. Airplanes equipped with MLG hinge arms to which a pad cadmium coating has been applied in accordance with Airbus Industrie Service Bulletin A300-26-356, dated May 15, 1985 (which references MHB Service Bulletin 470-32-422), and have since undergone a main workshop overhaul and have been subjected to an electrolytic cadmium stripping and replating in a bath. 2. Airplanes equipped with MLG hinge arms that have been reconditioned in accordance with MHB Service Bulletin 470-32-652. C. 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. NOTE: The request should be forwarded through an FAA Principal Maintenance Inspector (PMI), who will either concur or comment and then send it to the Manager, Standardization Branch, ANM-113. D. 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, 17900 Pacific Highway South, Seattle, Washington, or the Standardization Branch, 9010 East Marginal Way South, Seattle, Washington. This amendment (39-6364, AD 89-22-11) becomes effective on November 20, 1989.
2001-24-15: This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-9-10, -30, and -40 series airplanes and C-9 airplanes, that requires an inspection to detect chafing of the wiring of the attendants' work light of the aft cabin, and repair of chafed wiring. This AD also requires modification and reidentification of the attendants' work light assemblies of the aft cabin. This action is necessary to prevent chafing of the ground wire against the positive contact of the lamp of the attendants' work light of the aft cabin, and consequent arcing or arcing damage to the wiring of the attendants' work light and transformer of the aft cabin. Such arcing or arcing damage could result in short circuits and consequent smoke and fire in the aft cabin area. This action is intended to address the identified unsafe condition.
86-01-06: 86-01-06 AIRBORNE DIVISION, PARKER HANNIFIN CORPORATION: Amendment 39-5206. Applies to the following Airborne Dry Air Pumps and Auxiliary Dry Air Pumps installed on piston engine airplanes certificated in any category: AIRBORNE PART NUMBER SERIAL NUMBERS Dry Air Pumps 241CC-13 10AA30 thru 10AA36 and 10AA38 242CW 10AA281 thru 10AA293 441CC 9AA260 thru 9AA288 9AA291, 9AA294, 9AA295 441CC-7 9AA929 thru 9AA-949 9AA953, 9AA954, 9AA956, 9AA957, 9AA959 442CW 9AA850 thru 9AA875, 9AA880 thru 9AA886, 9AA888 thru 9AA903, 9AA905 thru 9AA921, 9AA928, 9AA934, 9AA936, 9AA939, 9AA940, 9AA945 thru 9AA952, 9AA955 thru 9AA958, 9AA962 thru 9AA967 442CW-4 10AA173 thru 10AA179 10AA182 thru 10AA199 10AA201, 10AA202 442CW-12 10AA356, 10AA357, 10AA386, 10AA389 Auxiliary Dry Air Pumps 4A2-1 9AA44 thru 9AA46 4A3-1 9AA56, 9AA59 thru 9AA66, 9AA73, 9AA79 thru 9AA82, 10AA83 thru 10AA88, 10AA90 thru 10AA94, 10AA96, 10AA114, 10AA126, 10AA130, 10AA131, 10AA132, 10AA138, 10AA150, 10AA154, 10AA155, 10AA159, 10AA161 NOTE: These pumps were not available for installation before September 1, 1985. Therefore, new Airborne Dry Air Pumps or Auxiliary Dry Air Pumps installed previous to that date are exempt from this AD. Pumps that have been reworked by Airborne will have a white date code stamped on the pump housing near the discharge port. This will indicate that the pump complies with this AD. COMPLIANCE: Required as indicated, unless previously accomplished. To prevent premature failure of the Airborne Dry Air and Auxiliary Dry Air Pumps, accomplish the following: (a) For Dry Air Pumps P/N's 241CC-13, 242CW, 441CC, 441CC-7, 442CW, 442CW-4, and 442CW-12, prior to further flight in IFR conditions, inspect installed dry air pump(s) to determine if one of the subject pumps is installed. (1) If one of these pumps is installed, and if the airplane is equipped for IFR flight, fabricate using minimum 0.10 inch letters, and install a placard in full view of the pilot which states; "FLIGHT IN IFR CONDITIONS PROHIBITED", and operate in accordance with this limitation. (2) And within 15 days of the effective date of this AD, replace the subject pump and remove the placard. Return pump to Airborne as described in Airborne Service Letter No. 30, dated November 11, 1985. (b) For Airborne Auxiliary Dry Air Pump P/N 4A2-1 or 4A3-1, prior to further flight in IFR conditions, inspect the auxiliary dry air pump if installed, to determine if one of the subject pumps is installed. (1) If one of these pumps is installed, fabricate using a minimum of 0.10 inch letters and install a placard in full view of the pilot which states; "STANDBY VACUUM SYSTEM MAY BE INOPERATIVE DUE TO VACUUM PUMP MALFUNCTION". (2) And within 30 days of the effective date of this AD, replace the subject pump and remove the placard. Return pump to Airborne as described in Airborne Service Letter No. 30, dated November 11, 1985. (c) Aircraft may be flown in accordance with FAR 21.197 to a location where this AD can be accomplished. (d) An equivalent method of compliance with this AD, if used, must be approved by the Manager, Chicago Aircraft Certification Office, 2300 East Devon Avenue, Room 232, Des Plaines, Illinois 60018, Telephone (312) 694-7357. All persons affected by this directive may obtain copies of the documents referred to herein upon request to Betty Annable, Parker Hannifin Corp., Airborne Division, 711 Taylor Street, Elyria, Ohio 44036 or the FAA, Rules Docket, Office of the Regional Counsel, Room 1558, 601 East 12th Street, Kansas City, Missouri 64106. This amendment becomes effective on January 31, 1986.
89-21-08: 89-21-08 CASA: Amendment 39-6348. Docket No. 89-NM-125-AD. Applicability: All Model C-212 series airplanes, certificated in any category. Compliance: Required within 60 days after the effective date of this AD, unless previously accomplished. To prevent airframe damage due to flutter caused by certain single failure conditions of the trim control system components, accomplish the following: A. Replace elevator, rudder, and aileron trim control system components, in accordance with CASA Service Bulletin 212-27-25, Revision 6, dated February 24, 1989. B. An alternate means of compliance or adjustment of the compliance time, which provides an acceptable level of safety, may be used when approved by the Manager, Standardization Branch, ANM-113, FAA, Northwest Mountain Region. NOTE: The request should be forwarded through an FAA Principal Maintenance Inspector (PMI), who will either concur or comment and then send it to the Manager, Standardization Branch, ANM-113. C. 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 Construcciones Aeronatuicas S.A. (CASA) Getafe, Madrid, Spain. These documents may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 17900 Pacific Highway South, Seattle, Washington, or the Standardization Branch, 9010 East Marginal Way South, Seattle, Washington. This AD supersedes AD 87-18-08 (Amendment 39-5724) as revised by AD 87-18-08 R1 (Amendment 39-6013) which became effective on October 11, 1988. This amendment (39-6348, AD 89-21-08) becomes effective on October 5, 1989.
2017-14-16: We are adopting a new airworthiness directive (AD) for certain Bombardier, Inc., Model BD-100-1A10 airplanes. This AD requires removing the fasteners attaching the machined center fitting to the rear spar frame lower flange splice, inspecting the fasteners and fastener holes for damage, reworking and repairing the fastener holes, as applicable, and replacing the fasteners. This AD was prompted by a report indicating that certain fasteners attaching the machined rear spar center fitting to the frame were installed with a gap between the fastener head and the structure, or were installed tilted. We are issuing this AD to address the unsafe condition on these products.
2017-14-08: We are adopting a new airworthiness directive (AD) for certain CFM International S.A. (CFM) CFM56-3, -3B, and -3C turbofan engines. This AD was prompted by a report of dual-engine loss of thrust control (LOTC) that resulted in an air turn back. This AD requires initial and repetitive checks of the variable stator vane (VSV) actuation system in the high-pressure compressor (HPC). We are issuing this AD to address the unsafe condition on these products.
2001-24-20: This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-10-10, -15, -30, -30F (KC-10A and KDC-10 military), and -40 series airplanes; and Model MD-10-10F series airplanes, that requires an inspection to verify that the wire connections at circuit breakers are properly connected, and correction of any incorrect wire connection at the circuit breakers. This amendment is necessary to prevent loss of protection by the circuit breakers in the flight engineer's equipment panel due to improperly wired connections at the circuit breakers, which could result in wire damage and could lead to smoke and/or fire in the cockpit. This action is intended to address the identified unsafe condition.
2001-24-28: This amendment supersedes an existing airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-8 series airplanes, that currently requires repetitive visual and eddy current inspections to detect cracking of the rudder pedals adjuster hub assembly, and replacement of the assembly with a new assembly, if necessary. This amendment requires accomplishment of a terminating action for the repetitive inspections. This amendment also adds airplanes to the applicability of the existing AD. This amendment is prompted by the FAA's determination that further rulemaking is necessary. The actions specified by this AD are intended to prevent loss of rudder pedals control and reduction of braking capability.
2001-24-13: This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-9-10, -20, -30, and - 40 series airplanes, that requires rework and reidentification of certain reflector assemblies of the passenger ceiling lights; and installation of a support channel above the reflector, as applicable. This amendment is prompted by reports of heat damaged lamp reflectors and scorched insulation blankets in the main cabin due to the lamps inside the reflectors creating high temperatures. The actions specified by this AD are intended to prevent overheating of the lamp reflectors, which could result in smoke and fire in the main cabin.
2017-14-01: We are superseding Airworthiness Directive (AD) 2013-10-03, which applied to all Airbus Model A330-200, -200 Freighter, and -300 series airplanes; and Model A340-200, -300, -500, and -600 series airplanes. AD 2013-10-03 required one-time inspections for deformation and damage of the bogie beams of the main landing gear (MLG); repetitive inspections for damage and corrosion of the sliding piston sub-assembly on certain airplanes; and related investigative and corrective actions if necessary. This new AD removes Model A340-500 and 600 series airplanes from the applicability; removes certain one-time inspections of the MLG bogie beams and the sliding piston sub-assembly; revises certain compliance times; and requires replacement of certain MLGs with MLGs having an improved bogie beam, which constitutes terminating action for the repetitive inspections on the modified MLG. This AD was prompted by reports of corroded and cracked bogie beams under the bogie stop pad. We are issuingthis AD to address the unsafe condition on these products.
2001-24-16: This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-9-10, -20, -30, -40, and -50 series airplanes and C-9 airplanes. This AD requires an inspection to detect chafing or damage at the conduit and support bracket interface in the forward electrical power center (EPC); and repair or replacement of wires with new wires, if necessary. For certain airplanes, this AD also requires installation of grommets on the conduits of the forward EPC. These actions are necessary to prevent chafing of electrical cables in the forward EPC and a possible short within a conduit, which could result in smoke and fire in the cockpit. These actions are intended to address the identified unsafe condition.
2023-03-10: The FAA is adopting a new airworthiness directive (AD) for all Schempp-Hirth Flugzeugbau GmbH Model Duo Discus and Duo Discus T gliders. This AD was prompted by 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 identifies the unsafe condition as cracks in the connecting tube of the elevator U-bracket of the horizontal tail, which could compromise the stiffness of the elevator control system and of the attachment of the horizontal tail. This AD requires repetitively inspecting the elevator U-bracket for cracks and broken weld seams, the rear connection between the horizontal tail and the rear attachment on the fuselage for play and softness, and the foam support for compression between the vertical and horizontal tail, and replacing or repairing damaged parts as applicable. The FAA is issuing this AD to address the unsafe condition on these products.
2001-24-22: This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-10-10, -10F, -30, -30F (KC-10A and KDC-10), -40, and -40F series airplanes; and Model MD-10-10F series airplanes. This AD requires an inspection of the power feeder cable assembly of the auxiliary power unit (APU) for chafing, correct type of clamps, and proper clamp installation; and corrective actions, if necessary. The actions specified by this AD are intended to prevent loss of the APU generator due to chafing of the generator power feeder cables, and consequent electrical arcing and smoke/fire in the APU compartment. This action is intended to address the identified unsafe condition.
2001-24-26: This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A300 B2 and B4, A300 B4-600 and B4-600R, and A310 series airplanes, that requires modification of the terminal blocks of the starter feeder line of the auxiliary power unit (APU). This action is necessary to prevent slackness and subsequent overheat and arcing of certain wiring connections. This action is intended to address the identified unsafe condition.
92-21-02: 92-21-02 FOKKER: Amendment 39-8382. Docket No. 92-NM-107-AD. Applicability: Model F28 Mark 0100 series airplanes; serial numbers 11262 through 11267, inclusive, and 11270 through 11376, inclusive; certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent an incorrect rudder deflection, accomplish the following: (a) Within 30 days after the effective date of this AD, revise the Limitations Section of the FAA-approved Airplane Flight Manual (AFM) as follows. Paragraph (a)(1) of this AD may be accomplished by inserting a copy of this AD into the AFM. (1) Add the following to Section 2.04.01, SPEED LIMITATIONS: "MINIMUM V1 ON DRY OR WET RUNWAY IS 110 KNOTS. MINIMUM V1 ON ICY RUNWAY IS 117 KNOTS." (2) Amend Section 2.05.01, WEATHER LIMITATIONS, as follows: "MAXIMUM ALLOWABLE CROSS-WIND COMPONENT FOR TAKEOFF AND LANDING. . . . . . . . . . 25 KNOTS" (3) Amend Section 2.08.01, AFCAS LIMITATIONS, as follows: "DO NOT ENGAGE AP WHILE AFCAS IS IN TAKEOFF MODE. APPROACH/LANDING IN LAND MODE (GS/LOC IN FMA) DISENGAGE AP AT 1,500 FEET AGL AND CONTINUE APPROACH ON FLIGHT DIRECTOR." (b) Within 45 days after the effective date of this AD, inspect to determine the dimensions of the autopilot rudder servo input brackets of the rudder post assembly, part numbers 77938-003 and 77939- 003, in accordance with Fokker Service Bulletin SBF100-027-041, dated February 24, 1992. If brackets with incorrect dimensions are found, prior to further flight, replace those brackets in accordance with the service bulletin. (c) After accomplishment of paragraph (b) of this AD, the limitations required by paragraphs (a)(1), (a)(2), and (a)(3) of this AD may be removed from the FAA-approved Airplane Flight Manual. (d) 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, ANM-113. NOTE: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Standardization Branch, ANM-113. (e) 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. (f) The inspection and replacement shall be done in accordance with Fokker Service Bulletin SBF100-027-041, dated February 24, 1992. 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 Fokker Aircraft USA, Inc., 1199 North Fairfax Street, Alexandria, Virginia 22314. 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. (g) This amendment becomes effective on November 24, 1992.