Results
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.
2000-20-02: This amendment adopts a new airworthiness directive (AD) that is applicable to General Electric Company (GE) CF6-50 series turbofan engines. This action requires inspection of the low pressure turbine nozzle lock assemblies, and replacement of the borescope plug with a new design plug. This amendment is prompted by three uncontained engine failures. The actions specified in this AD are intended to detect loose or missing LPT nozzle lock assembly studs that could lead to failure of the locks and subsequent uncontained failure of the engine.
81-09-08: 81-09-08 HILLER AVIATION: Amendment 39-4137. Applies to Models UH-12D, UH-12E, UH-12E4 Series Helicopters, including military Models H-23F, OH-23G, and all models converted by STC SH178WE and STC SH177WE, equipped with main rotor blades Part No. 53200-03, certified in all categories. Compliance is required as indicated, unless already accomplished. To prevent possible main rotor blade failure due to the delamination of the skin at the blade tip, accomplish the following: (a) Prior to further flight, after the effective date of this AD or receipt of the priority mail AD 81-09-08, issued April 27, 1981, whichever occurs first: (1) Remove blade tip cap and visually inspect for skin bond separation in the tip cap area, in accordance with Para. II.D of Hiller Aviation Service Bulletin No. 51-8 dated March 25, 1981. (2) If the skin bond separation is detected, replace blade with like serviceable item or repair in a manner approved by the Chief, Engineering and Manufacturing Branch, FAA Western Region. Submit data defining exact areas of delamination when requesting repair approval. (3) If no skin bond separation is detected, replace the tip cap and seal, in accordance with Para. II.F of Hiller Aviation Service Bulletin No. 51-8, dated March 25, 1981. (b) Upon the effective date or upon receipt of the priority mail AD 81-09-08, issued April 27, 1981, whichever occurs first, whenever the rotor blade tip cap is removed for whatever reason, comply with the inspection requirements and tip cap reinstallation requirements of Para. (a) of this AD prior to return to service. Special flight permits may be issued in accordance with FARs 21.197 and 21.199 to operate helicopters to a base for the accomplishment of inspections or modifications required by this AD. Alternative inspections, modifications, or other actions which provide an equivalent level of safety may be used when approved by the Chief, Engineering and ManufacturingBranch, FAA Western Region. 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. 553(a)(1). All persons affected by this directive, who have not already received these documents from the manufacturer, may obtain copies upon request to Hiller Aviation, 2075 West Scranton Avenue, Porterville, California 93275. These documents may also be examined at FAA Western Region Office, Rules Docket, Room 6W14, 15000 Aviation Boulevard, Hawthorne, California 90261 and at FAA Headquarters, Rules Docket, Room 916, 800 Independence Avenue, S.W., Washington, D.C. 20591. A historical file on this AD, which includes the incorporated material in full, is maintained by the FAA Headquarters in Washington, D.C. and the FAA Western Region Office. This amendment becomes effective June 25, 1981 to all persons, except those to whom it was made immediately effective by priority mail AD 81-09-08, issued April 27, 1981.
2015-25-09: We are adopting a new airworthiness directive (AD) for certain Airbus Model A330-200, A330-200 Freighter, and A330-300 series airplanes; and all Model A340-200 and A340-300 series airplanes. This AD was prompted by reports that a bracket that attaches the cockpit instrument panel to the airplane structure does not sustain the fatigue loads of the design service goal. This AD requires repetitive inspections of that bracket for cracking and to determine if both lugs are fully broken, an inspection for cracking of an adjacent bracket if necessary, and corrective actions if necessary. This AD also provides an optional modification, which terminates the repetitive inspections. We are issuing this AD to detect and correct cracking on a bracket of the cockpit instrument panel, which, combined with failure of the horizontal beam, could lead to collapse of the cockpit panel, and reduced controllability of the airplane.
2000-20-06: This amendment adopts a new airworthiness directive (AD) for Agusta S.p.A. (Agusta) Model A109K2 and A109E helicopters. This AD requires replacing a certain main transmission aft support fitting (aft support fitting) with an airworthy aft support fitting within specified time intervals and establishes a retirement life for certain aft support fittings. This AD is prompted by three failures of the engine to main gearbox drive shaft due to fatigue cracks on the aft support fittings. This condition, if not corrected, could result in excessive displacement of the main gearbox, failure of an engine to main gearbox drive shaft, loss of power to the main rotor, and a subsequent forced landing.
76-08-02 R2: 76-08-02 R2 CESSNA: Amendment 39-2582 as amended by Amendment 39-2608 is further amended by Amendment 39-4540. Applies to the following models of airplanes if equipped with strobe lights installed in the wing tip fuel tank nose cap, except those airplanes having Symbolic Displays P/Ns 30-0005, 30-0199-1, 30-0199-2, 30-0199-3, 30-0329, 31-0725-1, and 701133-1, Whelen Engineering Company, Inc., P/N A430, and Grimes Manufacturing Company (Grimes) P/Ns 30-0515-5, 30-1172-1, 30-1172-5, 30-0531-1, and 30-0467-5 strobe lights: Models 310, 310A, Military U-3A, 310B, 310C, 310D, 310E, Military U-3B, 310F, 310G, 310H, E310H, 310I, 310J, 310J-1, E310J, 310K, 310L, 310N, 310P, T310P, 310Q, T310Q, 310R, T310R; 320, 320-1, 320A, 320B, 320C, 320D, 320E, 320F; 340; 401, 401A, 401B; 402, 402A, 402B; 411, 411A; 414; and 421, 421A, and 421B airplanes. Compliance: Required as indicated, unless already accomplished. To preclude wing fuel tip tank nose cap explosions, within the next 100hours' time in service after the effective date of this AD, accomplish the following: A) Visually inspect the strobe lights in the tip tank nose cap area to determine whether Grimes P/N 30-0515-1 strobe light or any other strobe lights other than those excepted above are installed. On those airplanes where Grimes P/N 30-0515-1 strobe lights are installed, determine if the strobe lights have been modified by installing Grimes P/Ns 31-1723-5 or 30-1171-1 cover plates. These cover plates may be identified by the presence of two quench tubes protruding into the light assembly from the end plate. B) On those airplanes having unmodified Grimes P/N 30-0515-1 strobe lights, or strobe lights other than those excepted above, deactivate the strobe light system by installing a guard over the switch and/or by pulling and blocking the circuit breaker so that it cannot be inadvertently reset or by any other suitable means. C) Systems having unmodified Grimes P/N 30-0515-1 strobe lights may be reactivated upon the installation of Grimes P/Ns 31-1723-5 or 30-1171-1 cover plates in accordance with Cessna Service Letter ME75-16, dated July 11, 1975, or later approved revisions. D) Do not reactivate strobe light assemblies, other than Grimes P/N 30-0515-1 strobe lights modified per Paragraph C, until data showing the strobe lights are explosion proof have been submitted to and approved by the Chief, Engineering and Manufacturing Branch, or Division of the FAA Region issuing the original light approval. Amendment 39-2582 became effective April 23, 1976, and superseded Amendment 39-2103, AD 75-05-08. Amendment 39-2608 became effective May 20, 1976. This Amendment 39-4540 becomes effective January 31, 1983.
2015-25-01: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 757-200, 757-200CB, and 757-200PF airplanes. This AD was prompted by a report that a forward-most cam latch of the forward center cam latch pair on a main cargo door (MCD) broke during flight. This AD requires doing a general visual inspection for broken or missing cam latches, latch pins, and latch pin cross bolts; torqueing the cross bolts in the latch pins; measuring the extension of \n\n((Page 79462)) \n\nthe latch pins; replacing all alloy steel cross bolts through the latch pins with corrosion resistant steel (CRES) cross bolts; doing a general visual inspection of all cam latches for lip deformation; doing an inspection of cam latch 1 and cam latch 2 for cracks and replacing all cracked or broken parts; checking the rig of the MCD and re-rigging as applicable; and doing related investigative and corrective actions, if necessary. This AD also requires doing certain repetitive inspections until MCD rigging is done. This AD also requires repetitive MCD post- rigging inspections and corrective actions if necessary. We are issuing this AD to detect and correct discrepancies of the cam latches, latch pins, and latch pin cross bolts, which could reduce the structural integrity of the MCD, and result in potential loss of the cargo door and rapid decompression of the airplane.
2000-20-03: This amendment adopts a new airworthiness directive (AD) that is applicable to certain Bombardier Model CL-600-2B19 series airplanes. This action requires installation of shields for the aileron quadrants in the wheel bay of the main landing gear (MLG). This action is necessary to prevent the accumulation of water, ice, or slush on the aileron quadrants and control cable pulleys in the wheel bay of the MLG, which could freeze and result in reduced controllability of the airplane. This action is intended to address the identified unsafe condition.
2015-25-04: We are adopting a new airworthiness directive (AD) for Agusta S.p.A. (Agusta) Model A109A and A109A II helicopters. This AD requires inspecting the slider assembly pitch control (slider) for play and replacing the slider if the play exceeds certain limits. This AD is prompted by a report of excessive slider play and wear that was detected during a scheduled inspection of a Model A109A II helicopter. These actions are intended to detect and prevent excessive wear and play on a slider, which could lead to loss of tail rotor pitch control and consequently loss of helicopter control.