Results
2000-21-05: This amendment adopts a new airworthiness directive (AD), applicable to all British Aerospace BAe Model ATP airplanes. This action requires repetitive inspections to detect damage of the torque link apex joint of the left- and right-hand main landing gear (MLG); and replacement of nuts, pins, and bolts with new parts, if necessary. This action is necessary to prevent separation of the top and bottom torque links, and consequent loss of directional control of the MLG. This action is intended to address the identified unsafe condition.
47-40-02: 47-40-02 CONTINENTAL: (Was Mandatory Note of Airworthiness Directive Supplement Dated October 3, 1947.) Applies Only to the Following Models: Cessna 120 and 140, Commonwealth (Rearwin) 185, Superior (Culver) V and V2, Air Products (Erco) 415C, McClish (Funk) B85C, Universal (Globe) GC-1A, GC-1B, Silvaire (Luscombe) 8E, and Piper J3C-65, J4E, J5A Having Continental C75-12 or -12F Engines With Serial Numbers Below 1794-6-12 Except 1788-6-12: Airplanes Having Continental C85-12, -12F or -12FHJ Engines With Serial Numbers Below 20668-6-12 Except: 20656-6-12, 20658-6-12, 20659-6-12, 20661-6-12, and 20666- 6-12; Airplanes Having Continental C125-1 or -2 Engines With Serial Numbers Below 1046-6-12 Except: 1034- 6-12, 1037-6-12 Through 1042-6-12, and 1044-6-12. Compliance required immediately if engine has attained or passed 600-hour major overhaul period, but in any event not later than December 31, 1947, or 600 hours of operation, whichever occurs first. A certain percentage of piston pins installed in engines of the above numbers and distributed as replacement parts are subject to failure without warning. The weakness of these pins cannot be detected by normal inspection methods. Piston pin breakage can result in complete engine failure. It is the owner's responsibility to avoid this risk by making the following change at the earliest possible time. Replace piston pin assembly No. 22248-A1 (0.6875-inch inside diameter) with thick wall piston pin assembly No. 25121-A1 or 25262-A1 (0.5945-inch inside diameter). Supplies of the heavy wall pins are adequate so that immediate replacement can be effected. (Continental Service Bulletin No. M47-9 covers this same subject.)
2016-01-01: We are adopting a new airworthiness directive (AD) for certain Piper Aircraft, Inc. Model PA-46-500TP airplanes. This AD was prompted by a report of the wing upper skin joints being manufactured without sealant, which allows water to enter and stay in sealed, bonded stringers. This AD requires inspecting the upper wing surface for sealant; inspecting the wing stringers for water intrusion; inspecting for deformation and corrosion if evidence of water intrusion exists; and taking corrective actions as necessary. We are issuing this AD to correct the unsafe condition on these products.
2009-01-05: 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: Embraer has issued the Service Bulletin (SB) No. 145-00-0032 to provide instructions to modify the EMB-145 ( ) aircraft and allow operation with an increased Maximum Takeoff Weight (MTOW). Reassessment of the Damage Tolerance Analysis during development of the SB resulted in changes to the Airworthiness Limitation Items (ALI) for those modified aircraft to include new tasks and to revise some existing ones and its respective intervals. Failure to inspect some structural components, according to the new tasks and intervals for those modified aircraft, could prevent a timely detection of fatigue cracking. Undetected fatigue cracking in these componentscould adversely affect the structural integrity of these airplanes. * * * * * We are issuing this AD to require actions to correct the unsafe condition on these products.
93-24-06: 93-24-06 GENERAL DYNAMICS (CONVAIR): Amendment 39-8755. Docket 93-NM-44-AD. Applicability: All Model 340, 440, and C-131B through C-131H (military) series airplanes, certificated in any category, including those airplanes modified for turbo-propeller power. Compliance: Required as indicated, unless accomplished previously. To prevent the loss of an elevator or rudder, resulting from installation of a suspected unapproved part, accomplish the following: (a) Within 400 hours time-in-service or 180 days after the effective date of this AD, whichever occurs first, accomplish paragraphs (a)(1), (a)(2), and (a)(3) of this AD. (1) Remove the elevators and rudder in accordance with Parts 2.A.1. and 2.B.1., respectively, of the Accomplishment Instructions of General Dynamics, Convair Division, Alert Service Bulletin 640(340D) S. B. No. A55-7, dated March 22, 1993; perform a detailed visual inspection of the elevator and rudder hinge pins and bushings to detect wear in accordance with the procedures described in Part 2.B. of the Accomplishment Instructions of General Dynamics, Convair Division, Service Bulletin 640(340D)55-5, dated September 21, 1990; and perform a detailed visual inspection of the elevator and rudder bearing plate assemblies to detect cracks and of the elevator and rudder bearings to detect chattering, looseness, dryness, or binding in accordance with Parts 2.A. and 2.B. of the Accomplishment Instructions of General Dynamics, Convair Division, Alert Service Bulletin 640(340D) S. B. No. A55-7, dated March 22, 1993. (i) If any pin or bushing is worn, prior to further flight, replace the worn pin or bushing with a serviceable pin or bushing in accordance with the procedures described in Part 2.B. of the Accomplishment Instructions of General Dynamics, Convair Division, Service Bulletin 640(340D)55-5, dated September 21, 1990. (ii) If any cracked bearing plate assembly is found, prior to further flight, replace the cracked bearing plate assembly with a serviceable bearing plate assembly in accordance with Part 2.A. or 2.B. of the Accomplishment Instructions of General Dynamics, Convair Division, Alert Service Bulletin 640(340D) S. B. No. A55-7, dated March 22, 1993. (iii) If any chattering, loose, dry, or seized bearing is found, prior to further flight, replace the discrepant bearing with a serviceable bearing in accordance with Part 2.A. or 2.B. of the Accomplishment Instructions of General Dynamics, Convair Division, Alert Service Bulletin 640(340D) S. B. No. A55-7, dated March 22, 1993. (2) Perform a hardness test to determine the equivalent strength of the elevator and rudder hinge pins and bushings in accordance with normal maintenance procedures. If the equivalent strength of any pin or bushing does not meet the type design strength specified in paragraph (a)(2)(i) or (a)(2)(ii) of this AD, as applicable, prior to further flight, replace the discrepant pin or bushing with a serviceable pin or bushing in accordance with Part 2.A. or 2.B. of the Accomplishment Instructions of General Dynamics, Convair Division, Alert Service Bulletin 640(340D) S. B. No. A55-7, dated March 22, 1993. Elevator and rudder hinge pins and bushings received directly from Convair that bear the Convair mark are excluded from the requirements of this paragraph. The Convair mark is an etched mark, which appears as follows: CV SD The Convair mark is located on the top of the hinge pin and on the top of the bushing. (i) For airplanes having pin assembly 240-2010908-1, the pins and bushings must meet type design strengths specified as follows: Part Part No. Type Design Strength Pin GD/Convair 240-2010904 170-195 ksi Bushing GD/Convair 240-2010903-7 120-145 ksi (ii) For airplanes having pin assembly 240-2010908-3, the pins and bushings must meet type design strengths specified as follows: Part Part No. Type Design StrengthPin GD/Convair 240-2010904 170-195 ksi Bushing GD/Convair 340-2015903 125-145 ksi Bushing Allison 9015192 120-145 ksi (3) Reinstall the elevator and rudder, and ensure that proper mating of the pin and bushing tapered surfaces exists in accordance with Parts 2.A.5. and 2.B.5. of the Accomplishment Instructions of General Dynamics, Convair Division, Alert Service Bulletin 640(340D) S. B. No. A55-7, dated March 22, 1993. (b) Repeat the requirements of paragraphs (a)(1) and (a)(3) of this AD at intervals not to exceed 2,000 hours time-in-service or 2 years, whichever occurs first, in accordance with Item 55-2-9 of General Dynamics, Convair Division, "Supplemental Inspection Document (SID), Model 340/440," Report No. ZS-34-1000, Revision 1, dated April 15, 1991, including Addenda I, II, and III, all dated April 15, 1991. NOTE 1: Paragraph (b) of this AD restates a requirement for repetitive actions contained in AD 92-06-06, Amendment 39-8186. Accomplishment of paragraphs (a)(1) and (a)(3) of this AD satisfies the corresponding requirements contained in AD 92-06-06. (c) In accordance with the schedules specified in paragraphs (c)(1) and (c)(2) of this AD, report inspection results to the Manager, Los Angeles Aircraft Certification Office (ACO), FAA, Transport Airplane Directorate, 3229 East Spring Street, Long Beach, California 90806-2425; fax (310) 988-5210. Information collection requirements contained in this regulation have been approved by the Office of Management and Budget (OMB) under the provisions of the Paperwork Reduction Act of 1980 (44 U.S.C. 3501 et seq.) and have been assigned OMB Control Number 2120-0056. (1) Within 72 hours after accomplishing the initial inspection required by paragraph (a) of this AD, report inspection results, positive or negative. A "positive" inspection result is defined as any finding of a discrepant part in the pin, bushing, or support structure. (2) Within 72 hours after accomplishingany repetitive inspection required by paragraph (b) of this AD, report any positive inspection result. (d) As of the effective date of this AD, no person shall install an elevator or rudder hinge pin or bushing on any airplane unless, prior to installation, the pin or bushing has been tested for hardness and meets the specified type design strength in accordance with paragraph (a)(2) of this AD, or unless the pin or bushing bears the Convair mark described in that paragraph. (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, Los Angeles Aircraft Certification Office (ACO), 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, Los Angeles ACO. NOTE 2: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Los Angeles ACO. (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 elevator/rudder removal and reinstallation, replacements, and inspections shall be done in accordance with General Dynamics, Convair Division, Service Bulletin 640(340D)55-5, dated September 21,1990; General Dynamics, Convair Division, Alert Service Bulletin 640(340D) S. B. No. A55-7, dated March 22, 1993; and General Dynamics, Convair Division, "Supplemental Inspection Document (SID), Model 340/440," Report No. ZS-34-1000, Revision 1, dated April 15, 1991, including Addenda I, II, and III, all dated April 15, 1991; as applicable. The incorporation by reference of General Dynamics, Convair Division, Service Bulletin 640(340D)55-5, dated September 21, 1990; and General Dynamics, Convair Division, Alert Service Bulletin 640(340D)S. B. No. A55-7, dated March 22, 1993; was approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR Part 51. The incorporation by reference of General Dynamics, Convair Division, "Supplemental Inspection Document (SID), Model 340/440," Report No. ZS-34-1000, Revision 1, dated April 15, 1991, including Addenda I, II, and III, all dated April 15, 1991, was approved previously by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR Part 51 as of April 22, 1992 (57 FR 9382, March 18, 1992). Copies may be obtained from General Dynamics, Convair Division, P.O. Box 85377, San Diego, California 92186-5377. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the FAA, Los Angeles Aircraft Certification Office, 3229 East Spring Street, Long Beach, California; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. (h) This amendment becomes effective on January 18, 1994.
92-14-05: 92-14-05 AEROSPATIALE: Amendment 39-8287. Docket No. 92-NM-05-AD. Supersedes AD 85-12-04, Amendment 39-5076. Applicability: Model Nord 262A airplanes, certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent corrosion of the rudder hinge support assembly, that could lead to loss of rudder control, accomplish the following: (a) Within 100 hours time-in-service or three months, whichever occurs first after July 5, 1985 (the effective date of AD 85-12-04, Amendment 39-5076), inspect and protect against corrosion, or replace components if necessary, in accordance with paragraph II, Accomplishment Instructions, of Aerospatiale N262 Fregate Service Bulletin No. 55-10, Revision 2, dated January 31, 1984. Repeat the inspection at intervals not to exceed 6 years. (b) Within 6 years after the most recent inspection performed in accordance with paragraph (a) of this AD, perform a visual and X-ray inspection of therudder hinge support assembly for corrosion and apply corrosion protection treatments, in accordance with Aerospatiale 262-Fregate Service Bulletin No. 55-10, Revision 3, dated May 25, 1991. Compliance with this paragraph constitutes terminating action for the inspection requirements of paragraph (a) of this AD. (c) As a result of the visual inspection required by paragraph (b) of this AD, accomplish either paragraph (c)(1) or (c)(2) of this AD, as applicable: (1) If no corrosion is detected, repeat the visual inspection at intervals not to exceed 6 years. (2) If corrosion is detected, accomplish either paragraph (c)(2)(i) or (c)(2)(ii) of this AD, as applicable: (i) If internal corrosion is penetrating tube walls, or if deformation or buckling is evidenced, or if external corrosion is outside the tolerance limits specified in Aerospatiale 262-Fregate Service Bulletin No. 55-10, Revision 3, dated May 25, 1991: Prior to further flight, replace corroded components in accordance with Aerospatiale 262-Fregate Service Bulletin No. 55-11, Revision 2, dated May 25, 1991. Thereafter, at intervals not to exceed 6 years, repeat the visual inspection of tubes not replaced, as well as tubes replaced as a result of accomplishing Modification 861 described in the Service Bulletin 55-11, Revision 2, dated May 25, 1991. (ii) If internal corrosion is not penetrating tube walls, or if external corrosion is within the tolerance limits specified in Aerospatiale 262-Fregate Service Bulletin No. 55-10, Revision 3, dated May 25, 1991: Prior to further flight, apply external protective treatment in accordance with that Aerospatiale service bulletin. Thereafter, repeat the visual inspection at intervals not to exceed 6 years. (d) As a result of the X-ray inspection required by paragraph (b) of this AD, accomplish either paragraph (d)(1) or (d)(2) of this AD, as applicable: (1) If no corrosion or buckling is detected: Prior to further flight apply internal protective treatment, in accordance with Aerospatiale 262-Fregate Service Bulletin No. 55-10, Revision 3, dated May 25, 1991. (2) If any corrosion is detected, accomplish either paragraph (d)(2)(i) or (d)(2)(ii) of this AD, as applicable: (i) If corrosion is detected on both tubes of the upper support tube section, or on the lower support tube section, or on the support tube assembly: Prior to further flight, replace corroded components in accordance with Aerospatiale 262-Fregate Service Bulletin No. 55-10, Revision 3, dated May 25, 1991. (ii) If corrosion is detected on only one tube of the upper or lower support tube sections: Within 3 months or 600 landings of the discovery of corrosion, whichever occurs first, replace corroded components in accordance with Aerospatiale 262-Fregate Service Bulletin No. 55-10, Revision 3, dated May 25, 1991. (e) Accomplishment of Modification 866, in accordance with Aerospatiale 262-Fregate Service Bulletin No. 55-11, Revision 2, dated May 25, 1991, constitutes terminating action for the inspections required by this AD for the component replaced. (f) 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. The request shall be forwarded through an FAA Principal Maintenance Inspector, who may concur or comment and then send it to the Manager, Standardization Branch. NOTE: Information concerning the existence of approved alternative methods of compliance with this airworthiness directive, if any, may be obtained from the Standardization Branch. (g) 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. (h) The inspections, corrosion protection treatments, and replacement shall be donein accordance with Aerospatiale N262 Fregate Service Bulletin No. 55-10, Revision 3, dated May 25, 1991; or Aerospatiale N262 Fregate Service Bulletin No. 55-10, Revision 2, dated January 31, 1984, which contains the following list of effective pages: Page Number Revision Level Date 1, 10-12 2 January 31, 1984 2-9, 13-18 1 December 29, 1981 The modification shall be done in accordance with Aerospatiale 262-Fregate Service Bulletin No. 55-11, Revision 2, dated May 25, 1991, which contains the following list of effective pages: Page Number Revision Level Date 1-6 2 May 25, 1991 7-13 Original December 29, 1981 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 Aerospatiale, 316 Route de Bayonne, 31060 Toulouse, Cedex 03, 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., 7th Floor, Suite 700, Washington, DC. (i) This amendment becomes effective on September 8, 1992.
2016-01-08: We are superseding Airworthiness Directive (AD) 2013-13-04, for certain Airbus Model A318, A319, A320, and A321 series airplanes. AD 2013-13-04 required installing a power interruption protection circuit for the landing gear control interface unit (LGCIU). This new AD requires a new modification of any previously modified LGCIU. This new AD also requires revising the maintenance or inspection program to reduce a certain functional check interval. This new AD also adds airplanes to the applicability. This AD was prompted by a determination that additional work is necessary to adequately address the identified unsafe condition. We are issuing this AD to prevent untimely unlocking and/or retraction of the nose landing gear (NLG), which, while on the ground, could result in injury to ground personnel and damage to the airplane.
2016-01-02: We are adopting a new airworthiness directive (AD) for certain Bombardier, Inc. Model CL-600-2B19 (Regional Jet Series 100 & 440) airplanes. This AD was prompted by reports that the horizontal stabilizer trim actuator (HSTA) spur gear bolts inside the gearbox were found loose, broken, or backed out due to incorrect bending of the anti-rotation tab washer and the improper application of Loctite glue during installation. This AD requires replacing certain HSTAs with a new HSTA. This AD also requires revising the airplane flight manual (AFM) and the maintenance or inspection program, as applicable. We are issuing this AD to prevent failure of the HSTA and subsequent loss of control of the airplane.
2000-20-17: This amendment adopts a new airworthiness directive (AD) for Eurocopter France (ECF) Model AS332C, L, and L1 helicopters. This AD requires inspecting the horizontal stabilizer spar tube (spar tube) for corrosion, hardness, cracks, and scratches, and if necessary, replacing any unairworthy spar tube and bushing with an airworthy spar tube and bushing. This amendment is prompted by the loss of a horizontal stabilizer in flight due to a spar tube failure. The actions specified by this AD are intended to prevent failure of the spar tube, separation of the horizontal stabilizer and impact with the main or tail rotor, and subsequent loss of control of the helicopter.
84-13-01: 84-13-01 FAIRCHILD (SWEARINGEN): Amendment 39-4885. Applies to Models SA226- TC, (S/N 398 and up); SA227-AC; SA227-AT and SA227-TT (all serial numbers) airplanes certificated in any category. NOTE: The model prefix has been omitted from serial numbers listed in this AD to simplify the AD. Use the sequential number to determine AD applicability. Compliance: Required as indicated, unless already accomplished. To prevent cockpit fires, accomplish the following: (a) On all applicable models and serial numbers, within the next 50 hours time-in- service after the effective date of this AD, modify and inspect the generator control junction box (J- box) and wire terminations in accordance with Fairchild SB's 24-003 (SA227 series) dated March 21, 1983, or 24-021 (SA226-TC) dated March 21, 1983. (b) Within 200 hours time-in-service since new or the last inspection per AD 84-05-01 or 50 hours time-in-service after the effective date of this AD, whichever occurs later, and within each 200 hours time-in-service thereafter. (1) On Models SA226-TC (S/N 398 and up) and SA227-AC, -AT, -TT (S/Ns 406, 415, 416 and 420 through 583) airplanes; (i) Verify that all 3 flammable fluid external drains are open. (ii) Feel the bottom of flammable fluid bag for pockets of oil. If oil is detected, push up lower spot in bag toward either the right or left drain. Verify that oil comes out of one or all of the drains. Temporarily place rags in lower left bag just forward of the open area to prevent fluid from draining into belly of aircraft. Remove instruments as necessary to allow access to the bag. Unzip a small portion of the bag to determine cause of leak. Correct cause of leak. Clean bag with rags using Brulin Super 816 detergent in 3 parts water to 1 part detergent or an equivalent industrial cleaner (detergent) per AMS 1526 or 1547 or 1550. Use rags to clean out any residue that may havecollected in the lower left bag. Close all opened flammable fluid protection bags and handshape the bags to encourage flow of leakage toward the bag drains. (iii) The inspections required by paragraph (b)(1)(i) and (ii) above are not required when improved brake master cylinders are incorporated per Fairchild Service Bulletins 226-32-046 applicable to the Models 226 series airplanes or 32-013, Option 2, applicable to the Model 227 series airplanes. (2) On Models SA226-TC (S/N TC-398 thru TC-419) and SA227-AC, -AT, and -TT (S/N 406, 415, 416 and 420 thru 609 except AC-580, AC-582 and AC-583) airplanes; (i) Visually check oxygen lines for separation from moving components and for leakage using MIL-L-25567B leak detector solution or equivalent as specified in Fairchild Maintenance Manual. Minimum clearance between oxygen lines and all moving parts must be at least 2 inches. Give particular attention to the fittings in the vicinity of the cockpit side panelsand instrument panel area and the fittings on the oxygen supply line from the oxygen bottle to the cockpit. If leaks are found, prior to further flight, correct as necessary. See Fairchild Maintenance Manual Section 35-00-06 (SA226) and Section 35-00-05 (SA227) for proper maintenance of lines and fittings. NOTE: FAA Advisory Circular 43.13-1A, Chapter 10, paragraph 393, Chapter 8, paragraph 363, contains additional guidance pertaining to these inspections and corrective action. (ii) The inspections required by paragraph (b)(2)(i) above are not required when Fairchild Service Bulletin SB 226-35-002, 227-35-003 or 227-35-004 as applicable to the Models 226 or 227 series airplanes are incorporated. (3) On Models SA226-TC (S/Ns 398 and up) and SA227 (all models and S/Ns) airplanes not equipped with optional antiskid system; (i) Visually inspect the brake reservoir vent area located on the forward pressure bulkhead in front of the pilot for signs of hydraulic fluid contamination. (ii) Before further flight, clean or replace as necessary any hydraulic fluid-contaminated structure, insulation, or soundproofing. (c) On Models SA226-TC (S/N TC398 and up) and Models SA227-AC, -AT, -TT (S/Ns 415, 416, and 420 thru 599) airplanes, within 200 hours time since new or within 50 hours time-in-service after the effective date of this AD whichever occurs later, visually inspect the electrical wires and their supports in the vicinity of the cockpit side panels and behind the instrument panel on both sides of the aircraft for contact or inadequate clearance between the wires and adjacent components including hydraulic and oxygen lines or structure. It is desirable to maintain a 6-inch clearance between oxygen tubing and electrical wires. If this is not possible, fasten all electrical wires securely so that they cannot come to within 2 inches of oxygen tubing. If 2 inches cannot be maintained, reroute oxygen line or wires as necessary to get the maximum possible clearance and then add additional support and/or "butterfly" clamp as necessary to prevent contact between oxygen lines and electrical wires bundles. Accomplishment of paragraph (a)(4) of AD 84-05-01 satisfies this requirement. (d) Airplanes may be flown in accordance with FAR 21.197 to a location where this AD may be accomplished. (e) The intervals between repetitive inspections required by this AD may be adjusted up to 10 percent of the specified interval to allow accomplishing these inspections concurrent with other scheduled maintenance of the airplane. (f) An equivalent method of compliance with this AD may be used if approved by the Manager, Airplane Certification Branch, ASW-150, Southwest Region, FAA, Fort Worth, Texas 76101; telephone (817) 877-2070. This AD supersedes AD 84-05-01, Amendment 39-4822. This Amendment 39-4885 becomes effective on July 5, 1984.
89-22-14: 89-22-14 BEECH: Amendment 39-6357. Applicability: 90, 200, and 300 series airplanes (all serial numbers) certificated in any category. Compliance: Required within the next 100 hours time-in-service after the effective date of this AD, unless already accomplished. To prevent possible aileron flutter, accomplish the following: (a) For Models C90A (S/N LJ-1132 through LJ-1167), B200 (S/N BB-1246 through BB-1285 except BB-1272), 300 (S/N FA-91 through FA-140 except FA-120 and FA-128), A200CT (S/N BP-59 through BP-63), and B200C (S/N BP-64 through BP-66 and BV-1 through BV-8), inspect each aileron using the tap procedure in Beech Service Bulletin No. 2256, dated November 1988. If this inspection shows the presence of foam, prior to further flight remove the foam in accordance with the procedures in the above Service Bulletin. (b) For all other affected airplanes, check the airplane records to determine if any aileron has been replaced for any reason subsequent toJanuary 1, 1985. If so, inspect the aileron using the tap procedure in Beech Service Bulletin No. 2256. If this inspection shows the presence of foam, prior to further flight remove the foam in accordance with the procedures in the above Service Bulletin. NOTE 1: If the applicability of paragraph (b) is uncertain, perform a "tap test" on each area between the rivet rows along the aft 8.0 inches of the aileron skins. Use care in tapping to reduce the possibility of chipping the paint. (1) A tinny, hollow sound indicates an acceptable area. (2) A solid, heavy sound indicates that Scotch foam is present and must be removed. (c) Airplanes may be flown in accordance with FAR 21.197 to a location where this AD may be accomplished. (d) An alternate method of compliance or adjustment of the compliance time, which 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; Telephone (316) 946-4400. NOTE 2: The request should be forwarded through an FAA Maintenance Inspector, who may add comments and then send it to the Manager, Wichita Aircraft Certification Office. All persons affected by this directive may obtain copies of the document referred to herein upon request to the Beech Aircraft Corporation, Commercial Service, Department 52, Wichita, KS 67201-0085; or may examine these documents at the FAA, Office of the Assistant Chief Counsel, Room 1558, 601 East 12th Street, Kansas City, Missouri 64106. This amendment (39-6357, AD 89-22-14) becomes effective on November 17, 1989.
2015-27-01: We are adopting a new airworthiness directive (AD) for all General Electric Company (GE) GE90-76B, -77B, -85B, -90B, and -94B turbofan engines. This AD requires performing an eddy current inspection (ECI) or ultrasonic inspection (USI) of the high-pressure compressor (HPC) stage 8-10 spool and removing from service those parts that fail inspection. This AD was prompted by an uncontained failure of the HPC stage 8-10 spool, leading to an airplane fire. We are issuing this AD to prevent failure of the HPC stage 8-10 spool, uncontained rotor release, damage to the engine, and damage to the airplane.
2000-20-12: This amendment adopts a new airworthiness directive (AD) that applies to all Aerotechnik s.r.o. (Aerotechnik) Model L 13 SEH VIVAT sailplanes. This AD requires you to inspect the tail-fuselage hinge for strength requirements and damage, and also requires you to replace any hinge with damage or that does not meet strength requirements. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for the Czech Republic. The actions specified by this AD are intended to detect and correct any tail-fuselage hinge that is damaged or has inadequate material characteristics. Any tail-fuselage hinge with damage or inadequate material characteristics could fail and result in loss of controlled flight.
80-19-02: 80-19-02 HILLER AVIATION: Amendment 39-3910. Applies to Hiller UH-12D and UH-12E (including 4-place) helicopters certificated in all categories which have been converted to turbine power under Soloy Conversions, Ltd. Supplemental Type Certificates SH177WE or SH178WE. Compliance required within 500-hours operating time or 180 days, whichever occurs first, after the effective date of this AD. To prevent engine, transmission, or driveline failure and the resultant loss of power, replace Soloy Part Number 560-2408-2 engine output coupling shaft with Soloy Part Number 660-2408-3 shaft in accordance with Soloy Service Bulletin Number 12-560 dated May, 21, 1980, or later FAA approved revisions. Equivalent methods of compliance may be used when approved by the Chief, Engineering and Manufacturing Branch, FAA Northwest Region, 9010 East Marginal Way South, Seattle, Washington 98108. The manufacturer's specifications and procedures identified and described in this directive are incorporated herein and made a part hereof pursuant to 5 U.S.C. 552(a)(1). All persons affected by this directive who have not already received these documents from the manufacturer, may obtain copies upon request to Soloy Conversions, Ltd., Post Office Box 60, Chehalis, Washington 98532. These documents may also be examined at FAA Northwest Region, 9010 East Marginal Way South, Seattle, Washington 98108. This amendment becomes effective October 11, 1980.
2000-20-11: This amendment adopts a new airworthiness directive (AD) that applies to all LET Aeronautical Works (LET) Model L-13 "Blanik" sailplanes. This AD requires you to inspect the tail- fuselage hinge for strength requirements and damage, and also requires you to replace any hinge with damage or that does not meet strength requirements. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for the Czech Republic. The actions specified by this AD are intended to detect and correct any tail-fuselage hinge that is damaged or has inadequate material characteristics. Any tail-fuselage hinge with damage or inadequate material characteristics could fail and result in loss of controlled flight.
71-19-04: 71-19-04 BRITISH AIRCRAFT CORPORATION: Amdt. 39-1286. Applies to Viscount Models 744 and 745D airplanes. Compliance is required as indicated. To prevent cabin depressurization due to leakage through cracks in the rear pressure bulkhead boundary member accomplish the following: (a) For airplanes that have accumulated 25,000 or more landings on the effective date of this AD - (1) Before further flight install an operating limitation placard in the pilot's compartment in clear view of the pilot prohibiting further flight at a cabin pressure differential exceeding 3.5 p.s.i. and (2) Within the next 25 landings after the effective date of this AD comply with paragraph (d). (b) For airplanes that have accumulated 20,000 or more landings but less than 25,000 landings on the effective date of this AD - (1) Before further flight install an operating limitation placard in the pilot's compartment in clear view of the pilot prohibiting further flight at a cabin pressure differential exceeding 4.5 p.s.i. and (2) Within the next 50 landings after the effective date of this AD comply with paragraph (d). (c) For airplanes that have accumulated less than 20,000 landings on the effective date of this AD, before the accumulation of 20,000 landings or before the accumulation of 100 landings after the effective date of this AD, whichever occurs later, comply with paragraph (d). (d) Inspect the rear pressure bulkhead boundary member around the complete circumference of the boundary member for cracks - (1) Using the eddy current method, with a standard pencil non ferrous probe, along the forward inside bend radius of the boundary member, or (2) Visually inspect using a magnifying lens of at least 10 powers. (e) If any cracks in the boundary member are found during the inspection required by paragraph (d), before further flight repair the cracked boundary member - (1) By reinforcing the cracked portion of the boundary memberwith a length of serviceable boundary member section which extends at least three inches beyond the extremities of any crack; or (2) By replacing the cracked portion with a length of serviceable boundary member section; connecting the replacement section by typical type joint plates. (f) The placard required by paragraph (a) or (b) may be removed after paragraph (d) and paragraph (e), if applicable, have been accomplished. (g) For the purpose of complying with this AD, subject to acceptance by the assigned FAA maintenance inspector, the number of landings may be determined by dividing each airplane's hours' time in service by the operator's fleet average time from takeoff to landing for the airplane type. (BAC campaign wire SS1073V refers to this subject.) This amendment is effective upon publication in the Federal Register as to all persons except those persons to whom it was made immediately effective upon receipt of the airmail letter dated August 6, 1971, which contained this amendment.
2000-20-14: This amendment adopts a new airworthiness directive (AD) that applies to certain Raytheon Aircraft Corporation (Raytheon) Beech Models A36 and B36TC airplanes. This AD requires you to inspect for the installation of firewall sealant and install firewall sealant if not present. This AD is the result of a report that firewall sealant was not found during a routine production inspection. The actions specified by this AD are intended to correct the absence of sealant and prevent the consequent entry of smoke or fire into the flight compartment or cabin in the event of an engine compartment fire.
90-17-16: 90-17-16 AIRBUS INDUSTRIE: Amendment 39-6703. Docket No. 90-NM-52-AD. Applicability: Model A300, A310, and A300-600 series airplanes, on which Modification 6240 has not been incorporated, certificated in any category. Compliance: Required as indicated, unless previously accomplished. To detect corrosion in the passenger/crew door emergency operation cylinders, accomplish the following: A. Within 180 days after the effective date of this AD, and thereafter at intervals not to exceed 18 months, inspect the dampers and emergency operation cylinder strikers, in accordance with Airbus Industrie Service Bulletins A300-52-130, or A310-52-2018, or A300-52-6008, all dated December 12, 1985, as applicable. NOTE: The above-referenced service bulletins reference Ratier-Figeac Service Bulletin No. 701-2650-52-3 for additional instructions. B. If corrosion is found, repair, prior to further flight, in accordance with Ratier- Figeac Service Bulletin No. 701-2650-52-3. C. Incorporation of Modification 6240, in accordance with Airbus Industrie Service Bulletins A300-52-132, Revision 2, dated October 9, 1987; or A300-52-6010, Revision 3, dated July 15, 1989; or A310-52-2020, Revision 4, dated July 15, 1989; as applicable, constitutes terminating action for the repetitive inspection required by paragraph A., of this AD. NOTE: The above referenced service bulletins reference Ratier-Figeac Service Bulletin No. 701-5000-52-5 and 701-5000-52-7 for additional modification instructions. D. 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. 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, 17900 Pacific Highway South, Seattle, Washington, or the Standardization Branch, 9010 East Marginal Way South, Seattle, Washington. This amendment (39-6703, AD 90-17-16) becomes effective on September 21, 1990.
83-08-05: 83-08-05 BEECH: Amendment 39-4637. Applies to Models 60, A60, and B60 (S/Ns P-4 through P-577, P-579 through P-587, P-589, and P-592) airplanes, having optional air conditioning systems installed, certificated in any category. Compliance: Required within the next 50 hours time-in-service after the effective date of this AD unless already accomplished. To prevent loss of power or inflight fires caused by a loose air conditioner compressor clutch pulley contacting an adjacent fuel line, accomplish the following: a) Modify the air conditioner compressor installation by incorporating the appropriate Beech Kit No. 60-5026-1S or No. 60-5026-3S as identified by criteria in Beechcraft Class I Service Instructions No. 1236 or; b) Deactivate the air conditioner system in accordance with the following: (1) Remove the air conditioner compressor belt. (2) Pull and block the air conditioning circuit breaker so that it cannot be inadvertently reset. (3) Install a permanent placard in full view of the pilot near the cabin comfort control which reads as follows: "AIR CONDITIONER DEACTIVATED." c) Airplanes may be flown in accordance with FAR 21.197 to a location where the AD may be accomplished. d) An equivalent means of compliance with this AD may be used, if approved, by the Manager, Wichita Aircraft Certification Office, Room 238, Terminal Building 2299, Mid- Continent Airport, Wichita, Kansas 67209; telephone (316) 269-7000. This amendment becomes effective on May 3, 1983.
2000-20-05: This amendment adopts a new airworthiness directive (AD), applicable to certain EMBRAER Model EMB-120 series airplanes, that requires revising the Airplane Flight Manual (AFM), and either installing hydraulic tube assemblies incorporating a check valve, or visually inspecting the check valve if already installed and corrective action, 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 the landing gear doors from becoming blocked from opening during application of emergency procedures in the event of a loss of hydraulics.
86-20-02: 86-20-02 AEROSPATIALE: Amendment 39-5429. Applies to Model ATR-42 airplanes, certificated in any category. Compliance is required as indicated, unless previously accomplished. To prevent uncommanded pitch excursions from occurring during flight in icing conditions at a flap setting of 45 degrees, accomplish the following: A. Within seven days after effective date of this AD, incorporate the following into the Limitations Section of the Airplane Flight Manual (AFM). This may be accomplished by including a copy of this AD in the AFM. "Flap extension in excess of 30 degrees is not authorized during any normal or abnormal flight conditions. During an emergency landing or ditching, as required by the flight crew, flap 45 degrees may be used." B. Within 21 days after effective date of AD, apply temporary Scotchcal adhesive labels to the speed limits placard and to the flaps control sector markings, to provide VFE and approach/landing settings consistent with the limitations required in paragraph A., above, in accordance with Aerospatiale (ATR) Service Bulletin ATR42-27-0004, dated September 3, 1986. C. No later than December 1, 1986, replace previously installed temporary adhesive labels with permanent engraved labels with the same markings, and install a stop on the flaps control in accordance with Aerospatiale (ATR) Service Bulletin ATR42-27-0004, dated September 3, 1986. NOTE: The mechanical stop which precludes the normal use of flaps 45 degree operations may be removed in case of emergency ditching or emergency landing, when, at the discretion of the flight crew, additional safety would be provided by using flaps 45 degrees. D. 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. E. 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 the requirements of this AD. All persons affected by this directive who have not already received the appropriate service information from the manufacturer, may obtain copies upon request to Aerospatiale, 316 Route de Bayonne, 31060 Toulouse Cedex 03, France. This information may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or the Seattle Aircraft Certification Office, 9010 East Marginal Way South, Seattle, Washington. This amendment becomes effective October 15, 1986.
93-14-18: 93-14-18 GENERAL ELECTRIC COMPANY: Amendment 39-8643. Docket 92-ANE-10. Applicability: General Electric Company (GE) CF6-6/-45/-50/-80A/-80C2 series turbofan engines that contain high pressure turbine (HPT) thermal shields as listed in the applicable service bulletins that are referenced in this AD, installed on but not limited to Airbus A300 and A310 series, Boeing 747 and 767 series, and McDonnell Douglas DC-10 and MD-11 series aircraft. Compliance: Required as indicated, unless accomplished previously. To prevent an uncontained engine failure, accomplish the following: (a) Perform either an impression and optical comparitor inspection or an ultrasonic inspection of the HPT thermal shield at the next HPT shop visit, or by December 12, 1995, whichever occurs first, as follows: (1) For GE CF6-6 engines, in accordance with GE CF6-6 Service Bulletin (SB) No. 72-983, Revision 1, dated October 10, 1991. (2) For CF6-45/-50 engines, in accordance with GECF6-50 SB No. 72-1021, Revision 1, dated October 10, 1991. (3) For CF6-80A engines, in accordance with GE CF6-80A SB No. 72-596, Revision 1, dated October 10, 1991. (4) For CF6-80C2 engines, in accordance with GE CF6-80C2 SB No. 72-565, Revision 1, dated October 10, 1991. (b) Remove from service prior to further flight, and replace with a serviceable part, HPT thermal shields that do not meet the service criteria contained in the applicable service bulletins as specified in paragraph (a) of this AD. (c) For the purpose of this AD, a shop visit is defined as the removal of the HPT module from the engine for any reason. (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, Engine Certification Office. The request should be forwarded through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, Engine Certification Office. NOTE: Information concerning the existence of approved alternative methods of compliance with this airworthiness directive, if any, may be obtained from the Engine Certification Office. (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 inspections shall be done in accordance with the following service bulletins: Document No. Pages Revision Date GE CF6-6 SB 1-3 1 October 10, 1991 No. 72-983 4-30 Original September 19, 1991 Total Pages: 30 GE CF6-50 SB 1-3 1 October 10, 1991 No. 72-1021 4-30 Original September 19, 1991 Total Pages: 30 GE CF6-80A SB 1-3 1 October 10, 1991 No. 72-596 4-31 Original September 19, 1991 Total Pages: 31 This incorporation by reference was approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFRpart 51. Copies may be obtained from General Electric Aircraft Engines, CF6 Distribution Clerk, Room 132, 111 Merchant Street, Cincinnati, OH 45246. Copies may be inspected at the FAA, New England Region, Office of the Assistant Chief Counsel, 12 New England Executive Park, Burlington, MA; or at the Office of the Federal Register, 800 North Capitol Street NW., suite 700, Washington, DC. (g) This amendment becomes effective on October 4, 1993.
2000-20-04: This document supersedes an existing airworthiness directive (AD) that applies to certain McDonnell Douglas Model MD-90-30 series airplanes. That AD currently requires replacement of certain ground block screws with new screws; and retermination of the circuit ground wires of the electrical power control unit (EPCU) to separate grounding points. The actions specified in that AD are intended to prevent a loose electrical ground block of the circuit ground wires of the EPCU, which could result in complete loss of the primary electrical power of an airplane during flight. This amendment is prompted by the Federal Aviation Administration's determination that the existing AD must be revised to ensure that the requirements apply to the appropriate airplane groups. \n\n\tThe incorporation by reference of McDonnell Douglas Service Bulletin MD90-24-062, dated February 3, 2000, as listed in the regulations, is approved by the Director of the Federal Register as of November 13, 2000.The incorporation by reference of McDonnell Douglas Alert Service Bulletin MD90-24A060, Revision 01, dated September 2, 1999, as listed in the regulations, was approved previously by the Director of the Federal Register as of September 19, 2000 (65 FR 49728, August 15, 2000).
2015-26-04: We are superseding airworthiness directive (AD) 2002-13-11 for Eurocopter France (now Airbus Helicopters) Model EC120B helicopters. AD 2002-13-11 required installing front and side covers on the cabin floor to protect the yaw control at both the pilot and co-pilot stations. Since we issued AD 2002-13-11, we have determined that the required actions should apply only to the cabin's right-hand pilot station. This AD retains the requirements of AD 2002-13-11 but for only the pilot station. These actions are intended to prevent an object from sliding between the canopy and the cabin floor, loss of yaw control, and subsequent loss of helicopter control.
2000-20-08: This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-8 series airplanes, that requires, for certain airplanes, inspection(s) to detect cracks of the doorjamb corners and follow-on actions. For certain other airplanes, this AD requires installation of a preventative modification; an inspection to detect cracks at the corners of the doorjambs of the passenger and service doors; and follow-on actions. This amendment is prompted by reports indicating that fatigue cracks were found in the fuselage skin and doublers at the corners of the doorjambs of the passenger and service doors. The actions specified by this AD are intended to detect and correct such fatigue cracking, which could result in rapid decompression of the fuselage and consequent reduced structural integrity of the airplane.