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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.