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2010-13-12: We are adopting a new airworthiness directive (AD) for certain Model 747 series airplanes. This AD requires replacing the power control relays for the main tank fuel boost pumps and jettison pumps, and the center tank scavenge pump, as applicable, with new relays having a ground fault interrupt (GFI) feature. This AD also requires revising the maintenance program to incorporate Airworthiness Limitations (AWLs) 28-AWL-23 (for Model 747-100, 747-100B, 747-100B SUD, 747-200B, 747-200C, 747-200F, 747-300, 747SP, and 747SR series airplanes), and AWLs 28-AWL-28 and 28-AWL-29 (for Model 747-400, 747- 400D, and 747-400F series airplanes). This AD results from fuel system reviews conducted by the manufacturer. We are issuing this AD to prevent damage to the fuel pumps caused by electrical arcing that could introduce an ignition source in the fuel tank, which, in combination with flammable fuel vapors, could result in a fuel tank explosion and consequent loss of the airplane.
98-26-06: This document publishes in the Federal Register an amendment adopting Airworthiness Directive (AD) 98-26-06 which was sent previously to all known U.S. owners and operators of Schweizer Aircraft Corporation (Schweizer) Model 269D helicopters by individual letters. This AD requires removing the main rotor drive shaft (shaft) and inspecting it for cracks. If a crack is found, replacing the shaft with an airworthy shaft is required. This AD also requires periodically verifying the torque of the main rotor hub (hub) bolts. This amendment is prompted by four reports of cracking in the shaft of helicopters with a large diameter hub. Wear patterns indicate cracking was caused by loss of clamping torque on the hub and shaft assembly due to the use of grease between the hub and shaft. This condition, if not corrected, could result in failure of the shaft and subsequent loss of control of the helicopter.
2022-11-19: The FAA is adopting a new airworthiness directive (AD) for certain Bell Textron Inc. Model 212, 412, 412CF, and 412EP helicopters. This AD was prompted by a report of a cracked check valve. This AD requires inspecting certain engine oil and fuel check valves, and depending on the results, repetitively inspecting and removing the check valve from service. This AD also prohibits installing affected engine oil and fuel check valves on any helicopter. The FAA is issuing this AD to address the unsafe condition on these products.
81-17-01: 81-17-01 BENDIX: Amendment 39-4183. Applies to Bendix Starting Vibrator Assemblies, Part Numbers 10-176485-121, -122, -241, -242; 10-382780-12, -24 installed in but not limited to the following aircraft powered by reciprocating engines. Bell (Textron) Model 47 series helicopters Brantley (Hynes) Model B2 series helicopters Enstrom Model F28, F28A, F28F; 280, 280F helicopters, Model F28C and 280C helicopters equipped with Avco Lycoming HIO-360-E1BD engines Hughes (Summa Corp.) Model 269 series helicopters Hiller (Fairchild Industries) Model UH12 series helicopters Robinson Model R-22 series helicopters To preclude the loss of ignition due to the grounding of both "P" (Primary) leads within the starting vibrator, accomplish the alteration and identification shown in the Detailed Instruction of Bendix Engine Products Division Service Bulletin No. 614 or an FAA approved equivalent within the next 25 hours time in service after the effective date of this ADunless previously accomplished. Equivalent inspections and Procedures must be approved by the Chief of the Engineering and Manufacturing Branch, AEA-210, Federal Aviation Administration (FAA) Eastern Region. As permitted by FAR 21.197, aircraft may be flown to a base where maintenance required by this airworthiness directive can be accomplished. This amendment becomes effective August 13, 1981.
2021-03-01: The FAA is superseding Airworthiness Directive (AD) 2018-05- 09, which applied to all Airbus Helicopters Model AS332C, AS332C1, AS332L, and AS332L1 helicopters. AD 2018-05-09 required inspecting the tail rotor (T/R) flapping hinge link (hinge) and reporting the results. This AD requires repetitive inspections of the spindle bolts and the inner ring and needle bearings of each flapping hinge, corrective actions if necessary, and repetitive replacements of affected flapping hinge components, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. Replacement of all affected flapping hinge components on each flapping hinge is terminating action for the repetitive inspections. This AD also expands the applicability. This AD was prompted by a report of a damaged flapping hinge on a T/R blade. The FAA is issuing this AD to address the unsafe condition on these products.
99-02-07: This amendment adopts a new airworthiness directive (AD), applicable to certain Fokker Model F.28 Mark 0070 series airplanes, that requires modification of the power supply system of the horizontal stabilizer control unit. 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 loss of primary hydraulic stabilizer control during use of certain emergency procedures, which could result in the inability of the flight crew to control the airplane.
88-09-02: 88-09-02 CASA: Amendment 39-5899. Applies to Model C-212 series airplanes, serial numbers as listed in CASA Service Bulletin 212-28-15, dated April 11, 1983, certificated in any category. Compliance is required within 5 months after the effective date of this AD, unless previously accomplished. To prevent inability to close fuel shut-off valves in the event of a fire, accomplish the following: A. Replace the fuel shut-off valves with new modified valves, in accordance with CASA C-212 Service Bulletin 212-28-15, dated April 11, 1983. B. An alternate means of compliance or adjustment of the compliance time, which provides an acceptable level of safety and which has the concurrence of an FAA Principal Maintenance Inspector, may be used when approved by the Manager, Standardization Branch, ANM-113, FAA, Northwest Mountain Region. C. Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base for the accomplishmentof the modifications required by this AD. All persons affected by this directive who have not already received the appropriate service document from the manufacturer may obtain copies upon request to Contrucciones Aeronauticas S.A., Getafe, Madrid, Spain. This document 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 39-5899 becomes effective June 1, 1988.
2022-10-09: The FAA is adopting a new airworthiness directive (AD) for Airbus Helicopters Model SA-365C1 and SA-365C2 helicopters. This AD was prompted by a Model EC225 helicopter accident and subsequent investigation that determined that the level of particles in certain main gearboxes (MGB) could lead to a planet gear seizure. This AD requires inspecting the MGB magnetic plugs and oil filter for particles and, depending on the outcome of the inspections, further inspections and replacing certain parts, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
93-13-03: 93-13-03 BRITISH AEROSPACE (COMMERCIAL AIRCRAFT), LIMITED: Amendment 39-8616. Docket 93-NM-89-AD. Applicability: Model ATP series airplanes; serial numbers 2001 through 2055, inclusive; certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent operational failure of the fire extinguisher systems for the left- and right-hand engines, accomplish the following: (a) Within 14 days after the effective date of this AD, perform a safety ohmmeter inspection to verify the electrical conductivity of the firing circuits at the cartridge connectors of the fire extinguisher bottles of the left- and right-hand engines in accordance with Jetstream Aircraft, Ltd., Service Bulletin ATP-26-9, dated May 12, 1993. (1) If an out-of-tolerance condition is not detected: No further action is required by this paragraph. NOTE: An "out-of-tolerance condition" is defined as having an electrical resistance reading of less than 5.5 ohms or greater than 7 ohms. (2) If an out-of-tolerance condition is detected: Prior to further flight, perform a full electrical inspection of the fire extinguisher systems of the left- and right-hand engines and repeat the safety ohmmeter inspection in accordance with the service bulletin. (i) If an out-of-tolerance condition is no longer detected: No further action is required by this paragraph. (ii) If an out-of-tolerance condition is still detected: Prior to further flight, replace the cartridge firing unit with a new or serviceable cartridge firing unit and/or replace the cartridge connector with a new or serviceable cartridge connector in accordance with the service bulletin. (b) Within 10 days after accomplishing the inspection(s) required by paragraph (a) of this AD, submit a report of any inspection findings, to Jetstream Aircraft, Ltd., in accordance with Jetstream Aircraft, Ltd., Service Bulletin ATP-26-9, dated May 12, 1993. Report all findings, including nil defects, to: Service Support Manager, Customer Support Department, Jetstream Aircraft, Ltd., Woodford Aerodrome, Chester Road, Cheshire SK7 1QR, England. 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. (c) An alternative method of compliance or adjustment of the compliance time that provides an acceptable level of safety may be used if approved by the Manager, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate. Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, Standardization Branch, ANM-113. NOTE: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Standardization Branch, ANM-113. (d) 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. (e) The inspections and replacement shall be done in accordance with Jetstream Aircraft, Ltd., Service Bulletin ATP-26-9, dated May 12, 1993. 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 Jetstream Aircraft, Inc., P.O. Box 16029, Dulles International Airport, Washington, DC 20041-6029. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. (f) This amendment becomes effective on July 19, 1993.
99-02-06: This amendment adopts a new airworthiness directive (AD), applicable to certain Fokker Model F.28 Mark 0100 series airplanes, that requires modification of the aft cabin sidewall area to improve decompression venting and, for certain airplanes, modification of the aft wardrobe/stowage area door and installation of decompression panels to improve decompression venting. 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 damage to the cabin floor in the event of sudden decompression in the cargo compartment, which could result in injury to passengers, reduced structural integrity of the airplane, and the loss of airplane systems.
85-19-51 R1: 85-19-51 R1 PRATT & WHITNEY AIRCRAFT: Amendment 39-5168. Applies to Pratt and Whitney Aircraft JT8D-15, -17, and -17R turbofan engines. Compliance is required as indicated unless already accomplished. To prevent possible failure of the second stage turbine disk, inspect second stage turbine disk, Part Numbers 676802, 770602, 780502, 786802, and 787302 details, and Part Numbers 676822, 769722, 769832, 786822, and 787232 assemblies for wear and cracking of the snap diameter and at the bottom of the disk airseal groove, repair the disk, and modify the mating third stage turbine inner airseal in accordance with the Accomplishment Instructions (Paragraph 2) of PWA Alert SB 5541, Revision 1, dated May 4, 1984, and PWA SB 5510, Revision 1, dated February 13, 1984, or FAA approved equivalents, per the following schedule: (a) For disks which have not had the airseal groove previously repaired: (1) With 14,000 hours or more time in service since new - inspect, repair andmodify prior to reaching 17,000 hours time in service since new or within the next 2,000 hours time in service, whichever occurs first. (2) With less than 14,000 hours time in service since new - inspect, repair and modify by 14,000 hours time in service since new or within the next 2,000 hours time in service, whichever occurs later. (b) For disks which have had the airseal groove previously repaired: (1) With 2,000 hours or more time in service since repair - inspect, repair, and modify within the next 400 hours time in service. (2) With less than 2,000 hours time in service since repair, inspect, repair and modify by 2,000 hours time in service since repair or within the next 400 hours time in service, whichever occurs later. Disks worn beyond the repair limits of the applicable SB's must be removed from service. Aircraft may be ferried in accordance with the provisions of FAR 21.197 and 21.199 to a base where the AD can be accomplished. Upon request of an owner or operator, an equivalent means of compliance with the requirements of this AD may be approved by the Manager, Engine Certification Office, Federal Aviation Administration, New England Region, 12 New England Executive Park, Burlington, Massachusetts 01803. Upon submission of substantiating data by an owner or operator, through an FAA maintenance inspector, the Manager, Engine Certification Office, New England Region, may adjust the compliance schedule specified in this AD. PWA SB Number 5510, Revision 1, dated February 13, 1984, and the Accomplishment Instructions of (Paragraph 2) PWA Alert SB 5541, Revision 1, dated May 4, 1984, 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 Pratt & Whitney Aircraft Group, Commercial Products Division, 400 Main Street, East Hartford, Connecticut 06108.These documents also may be examined at the Office of Regional Counsel, New England Region, FAA, Room No. 311, between the hours of 8:00 a.m. and 4:30 p.m., Monday though Friday except Federal holidays. This amendment supersedes Amendment 39-4879 (49 FR 37568) AD 84-16-03. Those provisions of this amendment which apply to unrepaired disks become effective on December 26, 1985. The remaining provisions of this amendment become effective December 26, 1985, except to those persons to whom they were made immediately effective by individual telegrams issued September 25, 1985.
68-23-06: 68-23-06 BEECH: Amendment 39-684. Applies to Models D18C, D18S, E18S, E18S- 9700, G18S, H18, C45G, TC45G, C45H, TC45H, TC-45J (SNB-5), and JRB-6 with Volpar Tri- Gears, Serial Numbers 1 through 368, installed in accordance with STC SA111-WE or SA4- 1531. Compliance is required within the next six calendar months after the effective date of this AD, unless already accomplished. Repetition thereafter is not necessary. To determine the possible presence of corrosion and to provide a moisture barrier for the internal portion of the Beech center section wing truss assembly, accomplish the following: (a) Remove two bolts at each attachment point where the Volpar truss in each nacelle is secured to the center section wing truss as shown in Figure Nos. 1 and 2 of Volpar Service Bulletin no. 14. Dry and seal tubes from which bolts were removed in accordance with paragraphs 1 and 2 of Volpar Service Bulletin No. 14 or later FAA approved revision. (b) Remove the bolt which passes through the lower sparcap just inboard of each outer wing attach point as shown in Figure 3 of Volpar Service Bulletin No. 14. Inspect the bolts for corrosion and pitting, and the edges of the bolt hole through the elliptical spar tube for indications of moisture and/or corrosion. If pitting of the bolts exceeds .005 inches in depth or if evidence of moisture or corrosion exists, further inspections outlined under (c), below, must be accomplished. Otherwise dry and seal the lower spar cap in accordance with paragraphs 1 and 2 of Volpar Service Bulletin No. 14, or later FAA approved revision. (c) Conduct an x-ray inspection of the elliptical lower spar cap outboard of the wing to fuselage intersection for evidence of internal corrosion in accordance with Volpar Service Bulletin No. 14 and Report No. 34 or latter FAA approved revisions. If corrosion is indicated by this inspection, before further flight, the part must be replaced or the extent of corrosion and the corrective action to be taken must be evaluated by Volpar, Inc., and concurred in by the Chief, Aircraft Engineering Division, FAA Western Region. (d) Upon satisfactory completion of (c), dry and seal the lower spar cap as specified in (b), above. (e) Modify the Volpar Part No. 299-2 drag strut by cutting off the lug for the bolt in accordance with Figure 3 of Volpar Service Bulletin No. 14. Install Volpar Part No. 873 strap installation and Volpar Part No. 873-2 strap or an equivalent approved by the Chief Aircraft Engineering Division, FAA Western Region. (f) Aircraft with corrosion found pursuant to (c) of this AD may be flown in accordance with FAR 21.197 to a base where further evaluation or repair may be accomplished. This amendment becomes effective December 19, 1968.
2013-15-20: We are superseding emergency airworthiness directive (AD) 2013-14-51 for General Electric Company (GE) GE90-110B1 and GE90-115B turbofan engines with affected transfer gearbox assembly (TGB) radial gearshafts installed. AD 2013-14-51 was sent previously to all known U.S. owners and operators of GE90-110B1 and GE90-115B turbofan engines. AD 2013-14-51 prohibited operation of an airplane if more than one installed engine has an affected TGB radial [[Page 47535]] gearshaft. This AD contains the same prohibition as AD 2013-14-51 and also prohibits operation of any airplane 60 days after the effective date of this new AD if any installed engine has an affected TGB radial gearshaft. This new AD also revises the applicability by adding GE90- 76B, GE90-77B, GE90-85B, GE90-90B, GE90-94B, and GE90-113B turbofan engine models and adds a mandatory terminating action. This new AD was prompted by reports of three failures of TGB radial gearshafts which resulted in in-flight shutdowns (IFSDs). We are issuing this new AD to prevent failure of the TGB radial gearshaft, which could result in IFSD of one or more engines, loss of thrust control, and damage to the airplane.
75-08-11: 75-08-11 ROCKWELL INTERNATIONAL: Amendment 39-2161 as amended by Amendment 39-2681. Applies to NA-265, T-39A, NA-265-20, T-39B, NA-265-30, T-39D, NA- 265-40, NA-265-60 and NA-265-70 Airplanes, certificated in all categories. For paragraphs (a) through (f), compliance required within the next 50 hours time in service or 30 days, whichever is sooner, after April 14, 1975 (the effective date of Amendment 39-2161, AD 75-08-11), unless already accomplished. For paragraphs (g) through (i), compliance is required as indicated. To prevent loss of electrical power in flight, accomplish the following: (a) Perform an inspection of the electrical cable system at fuselage stations #143 and #333 as follows: (1) Examine cable lugs for looseness on cable or Essential Bus circuit breakers; if readily movable by hand applied force, replace that particular circuit breaker, and cable terminal, if applicable. (2) Examine circuit breakers for cracked cases. Application ofexcess torque on lug attaching bolt may cause cracks emanating from area adjacent to breaker terminal. Replace units having such cracks. (3) Determine by inspection that the cable lug is attached to the circuit breaker by not less than 50 inch-pounds torque; if below 50 inch-pounds, adjust to 50-60 inch- pounds. (b) For airplane Model NA-265-40 Serial Numbers 282-98 through 282-137 and Model NA-265-60 Serial Numbers 306-64 through 306-93: (1) Test the circuit breakers and replace, if necessary, as specified in Sabreliner Service Bulletin 74-28, as issued on September 20, 1974, or as revised January 15, 1975, or later FAA-approved revisions; or (2) Replace the 10 Essential Bus circuit breakers with Rockwell International supplied replacements which have been tested. (These are date stamped with black ink by Rockwell International, and must be dated either prior to January 1, 1970, or after July 7, 1974. During the interval between these dates, tests were conducted only on selected samples, and such units must not be used, unless tested as specified in Service Bulletin 74-28.) (c) Revise AFM Limitations Section as follows: ESSENTIAL BUS CIRCUIT BREAKERS. All 28V DC, 100 AMP Essential Bus circuit breakers (cockpit and cabin) must be checked and engaged (pushed in) during the pre-flight (prior to first flight of the day) inspection. (d) Install a placard in full view of the crew: "PRIOR TO FIRST FLIGHT OF DAY - DETERMINE THAT COCKPIT AND CABIN ESSENTIAL BUS CIRCUIT BREAKERS ARE PUSHED IN." (e) Install a placard on or immediately adjacent to the aft cabin circuit breaker panel: "CIRCUIT BREAKERS ON THIS PANEL ARE ESSENTIAL TO SAFETY AND MUST BE READILY ACCESSIBLE TO THE CREW IN FLIGHT - DO NOT OBSTRUCT." (f) Examine circuit breakers in spares stock. Either remove those date stamped by Rockwell International during interval of January 1, 1970, through July 7, 1974, and identify in a manner to preclude installation in NA-265 series airplanes, or perform the one hour functional test specified in Service Bulletin 74-28 prior to returning to spares. (g) After August 5, 1976 (the effective date of Amendment 39-2681) the placard specified in paragraph (e), above, may be removed when: (1) A placard is installed on or immediately adjacent to the circuit breaker access cover: 'CIRCUIT BREAKER ACCESS', and (2) A placard is installed on or immediately adjacent to the circuit breaker panel so that it is visible when the circuit breaker access cover is opened: 'CIRCUIT BREAKERS ON THIS PANEL ARE ESSENTIAL TO SAFETY AND MUST BE ACCESSIBLE FOR INSPECTION ON THE GROUND AND IN FLIGHT' (h) Before September 1, 1976, unless already accomplished, revise the FAA- approved Airplane Flight Manual (AFM) appropriate to the airplane model as listed below, by incorporating the AFM revision as dated, or later FAA-approved revision. (This revised manual material incorporates revised Certificate Limitations pertaining to the circuit breaker preflight check, and new Emergency Procedures covering the failure of the 28V DC Essential Bus system.) Model AFM Date of AFM Revision NA-265(T-39A) NA-61-3 July 19, 1976 NA-265-20 (T-39B) NA-61-3 July 19, 1976 NA-265-30 (T-39D) NA-61-3 July 19, 1976 NA-265-40 (S/N 1-97) NA-62-1300 July 19, 1976 (S/N 98-137) NA-72-25 July 19, 1976 NA-265-60 NA-66-1030 July 19, 1976 NA-265-70 NA-69-422 July 19, 1976 Concurrently with incorporating this AFM revision, remove AFM material specified in paragraph (c) and the placard specified in paragraph (d). (i) For models NA-265-40, NA-265-60 and NA-265-70 (1) Before October 15, 1976, unless already accomplished, comply with Part I of Rockwell International Service Bulletin No. 11 as revised May 14, 1976 or later FAA- approved revision, to provide improved circuit breaker cooling at Station 333. (2) Before April 25, 1977, unless already accomplished: (i) Comply with Part II (replacement of five 100 ampere circuit breakers with five 140 ampere circuit breakers at Station 333 and providing additional circuit breaker cooling), of Rockwell International Service Bulletin No. 11 as revised May 14, 1976, or later FAA-approved revision, and (ii) Install an 'Essential Bus Circuit Breaker Out' caution light and test circuit system in accordance with Rockwell International Service Bulletin No. 75-20 as revised May 24, 1976 or later FAA-approved revision. (iii) When the replacement of the five circuit breakers in accordance with subparagraph (i)(2)(i) is accomplished the requirements of Paragraph (b) no longer apply to the five circuit breakers located at station 333. Equivalent procedures may be approved by the Chief, Aircraft Engineering Division, FAA Western Region, upon submission of adequate substantiation data. Aircraft may be flown to a base for performance of work required by this AD per FAR's 21.197 and 21.199. Amendment 39-2161 became effective April 14, 1975. This amendment 39-2681 becomes effective August 5, 1976.
90-01-06: 90-01-06 ENSTROM HELICOPTER CORPORATION: Amendment 39-6457. Docket No. 89-ASW-59. Applicability: Enstrom Model F-28, F-28A, F-28C, F-28C-2, F-28F, 280, 280C, 280F and 280FX Series Helicopters, equipped with tail rotor gearboxes, P/N 28-13500-1, 28-13525-1, -3, and -5, containing spiral miter gear-set "Boston Gear XR-137-2YR" and "Boston Gear XR- 137-2YL." Compliance: Required as indicated, unless already accomplished. To prevent the loss of tail rotor thrust and directional control, which could result in loss of the helicopter, accomplish the following: (a) Within the next five hours' time in service-- (1) Determine from the aircraft log book if tail rotor gearbox, P/N 28-13500- 1, 28-13525-1, -3, or -5, is installed in the helicopter; (2) Remove all -1, -3 or -5 tail rotor gearboxes containing spiral miter gear- set "Boston Gear XR-137-2YR" and "Boston Gear XR-137-2YL", with 1,200 or more hours' time in service since the last overhaul, and replace with an airworthy gearbox; and (3) For tail rotor gearboxes with less than 1,200-hours' time in service since the last overhaul, remove the magnetic chip detector (plug), drain the oil from the tail rotor gearbox, filter the oil using a white filter paper, and inspect the magnetic plug and the filter paper with a ten-power magnifying glass-- (i) If no metal contaminants are found, return the tail rotor gearbox to service; (ii) If the inspection required by paragraph (a)(3) above reveals the presence of more than 15 thin metal flakes, splinters, or granular-shaped steel particles greater than 0.005-inches thick or longer than 0.015 inches, remove and replace the tail rotor gearbox with an airworthy gearbox; and (iii) If metal contaminants are found that are fewer in number and smaller than those described in paragraph (ii) above, conduct further servicing and inspection in accordance with paragraph (a)(4). (4) Flush the gearbox with clean oil and clean the magnetic plug with a cotton swab and/or an air gun. NOTE: Do not clean the magnetic plug with a strong magnet. This weakens the magnet on the chip detector. (i) Refill the tail rotor gearbox with Mil-L-6082B Shell SAE10W, Mil-L-6082B Texaco SAE 10W, or Mil-L-22851B Phillips SAE 20W-50W lubricant. If any of these lubricants are not available, consult Enstrom Helicopter Corporation, Customer Service Department, for a possible alternative. (ii) Conduct a serviceability check by flying the helicopter for one hour at various power settings up to full power, and then repeat the inspection required by paragraphs (a)(3) above. (A) If no metal contaminants are found, return the tail rotor gearbox to service. (B) If the repeat inspection reveals the presence of any metal contaminants, regardless of size or number, remove and replace the tail rotor gearbox with an airworthy gearbox. (b) At intervals not to exceed 100 hours' time in service on all gearboxes returned to service after passing the inspections of paragraph (a), remove the magnetic chip detector (plug), drain the oil from the tail rotor gearbox, filter the oil using a white filter paper, and inspect the magnetic plug and the filter paper with a ten-power magnifying glass. (1) If the inspection reveals the presence of any metal contaminants, regardless of size or number, remove and replace the tail rotor gearbox with an airworthy gearbox. (2) If no metal contaminants are found return the tail rotor gearbox to service. (c) Within 1,200 hours' time in service since the last overhaul, remove and replace the tail rotor gearbox with an airworthy gearbox. (d) An alternate method of compliance with this AD, which provides an equivalent level of safety, may be used when approved by the Manager, Chicago Aircraft Certification Office, FAA, 2300 East Devon Avenue, Room 232, Des Plaines, Illinois 60018. (e) In accordance with Sections 21.197 and 21.199,flight is permitted to a base where the maintenance required by this AD may be accomplished. This amendment (39-6457, AD 90-01-06) becomes effective on February 1, 1990.
80-04-03 R2: 80-04-03 R2 AVCO LYCOMING: Amendment 39-3692 as amended by Amendment 39-3977 is further amended by Amendment 39-5893. Applies to O-320-H series engines and O-360-E, LO-360-E, TO-360-E and LTO-360-E series engines; (all serial numbers and hydraulic lifter (tappet) configurations). Compliance required as indicated, unless already accomplished. a. To prevent hazards in flight associated with bent push rods on Model O-320-H series engines, accomplish the following: Within the next 50 hours in service after the effective date of this AD, replace the upper exhaust valve spring seats with P/N LW-16475-KLI and the exhaust hydraulic lifters with P/N LW-16586 in accordance with AVCO Lycoming Service Bulletin No. 435 dated March 17, 1979, or FAA-approved equivalent, on all O- 320-H series engines with serial numbers up to and including L-6182-76 and on all O-320-H series engines overhauled (remanufactured by Lycoming) before March 19, 1979. b. To prevent excessive wear and oil system contamination associated with hydraulic lifters spalling on O-320-H, and O-360-E, LO-360-E, TO-360-E and LTO-360-E series engines, accomplish the following: 1. At the next engine oil change but no later than 50 hours in service after the effective date of this AD, and at each subsequent oil change or 50-hour interval, whichever occurs earlier, add one 6-ounce can of Lycoming P/N LW-16702 oil additive in accordance with Lycoming Service Bulletin No. 446B. 2. Within the next 50 hours in service after the effective date of this AD and at every subsequent oil change thereafter, not to exceed 100-hour intervals, inspect lubrication system for metal contaminants. Inspection of the lubrication system consists of visual examination for minute particles of metal suspended in the oil, examination of the engine oil suction screen for presence of metal particles and the inspection of the external full flow oil filter for metal particles by cutting it open so that the pleated element can be unfolded and examined. If ferrous metal contaminants are detected during the above inspections, the camshaft lobes and all hydraulic lifters must be inspected for wear or loss of metal. Replace the camshaft and hydraulic lifters found to have such indications. 3. If contaminants are detected, engine maintenance entries shall be made. If the engine is one of the affected Textron Lycoming engine models with the 'T mod' modification (larger diameter hydraulic lifters), notification in writing must be sent to the Manager, New York Aircraft Certification Office, 181 South Franklin Avenue, Room 202, Valley Stream, New York 11581, specifying the following information: 1. Engine Model and Serial Number. 2. Total time and time since overhaul. 3. Total time on cam and hydraulic lifters. 4. Total time since oil additive first used. 5. Visual condition of cam lobe and lifter contact surfaces. (Information collection requirements contained in this regulation (Section 39.13) have been approved by the Office of Management and Budget under the provisions of the Paperwork Reduction Act of 1980 (Pub. L. 96- 511) and have been assigned OMB control number 2120-0056). NOTE: The 'T mod' is the latest design crankcase that incorporates large diameter hydraulic lifters and wide lobe camshafts and is described in Textron Lycoming Service Instruction No. 1406B. Engines incorporating this configuration are identified by the letter 'T' stamped as a suffix to the engine serial number which appears on the engine nameplate for overhaul modified, remanufactured, and new production engines (e.g., L-6005-76T). c. Equivalent methods of compliance may be approved by the Manager, New York Aircraft Certification Office, FAA, New England Region. d. Upon submission of substantiating data by an owner or operator through an FAA Maintenance Inspector, the Manager, New York Aircraft Certification Office, FAA, may adjust the compliance time specified in this AD. e. Special Flight Permits may be issued per FAR's 21.197 and 21.199 to authorize operation of aircraft to a base where the modification and inspection required by this AD may be performed. Amendment 39-3692 was effective February 8, 1980. Amendment 39-3977 was effective November 24, 1980. This amendment 39-5893, becomes effective on April 25, 1988.
99-02-05: This amendment adopts a new airworthiness directive (AD), applicable to certain Lockheed Model L-1011-385-1 series airplanes, that requires modification of the power drive units and the lower drive sprocket assemblies of the galley lift system. This amendment is prompted by a report indicating that, due to fatigue cracking, the primary and secondary drive shafts of the galley lift failed and caused the galley lift to drop to the lower level, injuring a flight attendant. The actions specified by this AD are intended to prevent such fatigue cracking of the primary and secondary drive shafts, which could result in complete fracturing of the secondary shaft; such fracturing could allow the galley lift to drop to the bottom of the shaft, and could result in possible injury to crewmembers.
83-07-09 R1: 83-07-09 R1 CANADAIR: Amendment 39-8675. Docket 92-NM-231-AD. Revises AD 83-07-09, Amendment 39-4609. Applicability: All Model CL-600-1A11 and CL-600-2A12 series airplanes, certificated in any category. Compliance: Required as indicated, unless accomplished previously. NOTE 1: This AD requires the same actions as required by AD 83-07-09, Amendment 39-4609, but is applicable to fewer airplanes. Operators affected by this AD who have accomplished these actions previously in accordance with AD 83-07-09 are considered to be in compliance with this revised AD. To prevent possible wire overheating, which could result in a cabin fire, accomplish the following: (a) Within 300 hours time-in-service or within 3 calendar months after April 13, 1983 (the effective date of AD 83-07-09, Amendment 39-4609), whichever occurs earlier, perform an inspection to verify proper installation of the 8 gage feeder wires from generators 1 and 2 and the auxiliary power unit (APU), in accordance with Canadair Drawings 600-58001, Note 17, or 600-58031, Note 14; and CL-600 Completion Centre Handbook Section 6. Prior to further flight, correct any discrepant wires in accordance with the drawings or handbook. (b) Replacement of the 8 gage generator 1, generator 2, and APU feeder wires with 4 gage feeder wires of the same type constitutes an approved alternative method of compliance for the requirements of this AD. (c) 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, New York Aircraft Certification Office (ACO), FAA, Engine and Propeller Directorate. Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, New York ACO. NOTE 2: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the New York ACO. (d) 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. (e) This amendment becomes effective on November 12, 1993.
90-02-09: 90-02-09 GROB WERKE GmbH & COMPANY KG (BURKHART GROB): Amendment 39-6447. Applicability: Models TWIN ASTIR and TWIN ASTIR TRAINER (Serial Numbers (S/N) 3000 through 3291); G103 TWIN II (S/N 3501 through 3878, and 33879 through 34078); and G103A TWIN II ACRO (S/N 3544 through 34078) gliders certificated in any category. Compliance: Required as indicated after the effective date of this AD, unless already accomplished. To preclude failure of the wing spar spigots, accomplish the following: (a) Within the next 500 takeoffs after the effective date of this AD, inspect the wing spar spigots for damage in accordance with the ultrasonic inspection procedures specified in GROB WERKE GmbH Technical Information TM 315-36, dated June 23, 1988. (1) If damage is found, prior to further flight remove and replace the spigot with a Fail-Safe Spigot using the procedures specified in the above-referenced service information. (2) If no damage is found, within the next 500 takeoffs remove and replace the spigots with Fail-Safe Spigots using the procedures specified in the above-referenced service information. NOTE 1: Note 5 in the Type Certificate Data Sheet G39EU Burkhart Grob Model G103 Twin Astir, Model G103 Twin II, and Model G103A Twin II Acro, Revision 3, dated April 2, 1984, states: "Major airframe repairs must be accomplished at FAA certified repair stations rated for composite construction of small aircraft, using Grob Werke repair methods for the model of interest, approved by the FAA." The replacement of the wing spigots is considered major airframe repair. (b) An alternate method of compliance or adjustment of the compliance times which provides an equivalent level of safety may be approved by the Manager, Brussels Aircraft Certification Staff, FAA, c/o American Embassy, 15 Rue de la Loi B1040, Brussels, Belgium. NOTE 2: The request should be forwarded through an FAA Maintenance Inspector, who may add comments and send it to the Manager, Brussels Aircraft Certification Staff. All persons affected by this directive may obtain copies of the document referred to herein upon request to Grob Systems, Incorporated; Aircraft Division; I-75 and Airport Drive, Bluffton, Ohio 45817; or may examine this document at the FAA, Central Region, Office of the Assistant Chief Counsel, Room 1558, 601 East 12th Street, Kansas City, Missouri 64106. This amendment (39-6447, AD 90-02-09) becomes effective on February 5, 1990.
83-16-01 R1: 83-16-01 R1 SUNDSTRAND DATA CONTROL, INC.: Amendment 39-4705 as amended by Amendment 39-4857. Applies to Sundstrand Model AV-557B, and AV-557C Cockpit Voice Recorders. To prevent loss of recorded data, accomplish the following within the next 4,000 hours time in service (on the cockpit voice recorder (CVR)) after the effective date of this AD, unless already accomplished: A. Inspect the CVR's for the type of tape deck housing connector sockets used in accordance with Sundstrand Service Bulletin 012-0296-109 dated January 25, 1982, or a later FAA approved revision. Remove CVR's from service that have incorrect connectors for repair to be accomplished at the factory. Return to service CVR's that have correct connectors and have met the requirements of this AD. B. Alternate means of compliance which provide an equivalent level of safety may be used when approved by the Manager, Seattle Aircraft Certification Office, FAA, Northwest Mountain Region. Amendment 39-4705became effective September 12, 1983. This Amendment 39-4857 becomes effective May 15, 1984.
98-25-11 R1: This amendment corrects and clarifies information in an existing airworthiness directive (AD), applicable to all McDonnell Douglas Model MD-11 series airplanes, that currently requires a one-time inspection to detect discrepancies at certain areas around the entry light connector of the sliding ceiling panel above the forward passenger doors, and repair, if necessary. The actions specified in that AD are intended to prevent chafing of the electrical wire assemblies, which could result in an electrical fire in the passenger compartment. This amendment corrects and clarifies the requirements of the current AD by specifying the specific area in which the subject inspection must be conducted and by correcting the part number of the ramp deflector assembly. This amendment is prompted by communication received from the manufacturer that the current requirements of the AD are unclear.
99-01-11: This amendment adopts a new airworthiness directive (AD) that applies to all The Uninsured Relative Workshop Inc. (doing business as and referred to herein as Relative Workshop) vector parachute systems that were manufactured between January 1, 1996, and September 10, 1998. This AD requires inspecting the amp fittings on the end of the breakaway housing for proper swaging, and re-swaging any incorrectly swaged fittings using the Nicopress or Swage-It swaging tool. This AD is the result of a quality control problem on Relative Workshop vector parachute systems. In particular, a loose amp fitting was found on the breakaway housing during packing of one of these vector parachute systems. Further analysis reveals that the amp fittings on the end of the stainless steel breakaway housing were improperly swaged, and that this condition could exist on any of the 2,127 parachute systems that were manufactured during the above-referenced time period. The actions specified by thisAD are intended to prevent the amp fittings from coming off the stainless steel breakaway housing, which could result in an unintentional partial breakaway of the main chute and interference with the deployment of the reserve parachute.
98-26-24: This amendment supersedes an existing airworthiness directive (AD), applicable to certain Boeing Model 737-100 and -200 series airplanes, that currently requires replacement of certain outboard and inboard wheel halves with improved wheel halves; cleaning and inspecting certain outboard and inboard wheel halves for corrosion, missing paint in large areas, and cracks; and repair or replacement of the wheel halves with serviceable wheel halves, if necessary. That AD was prompted by a review of the design of the flight control systems on Model 737 series airplanes. This amendment requires that the actions be accomplished in accordance with revised service information. The actions specified by this AD are intended to prevent failure of the wheel flanges, which could result in damage to the hydraulics systems, jammed flight controls, loss of electrical power, or other combinations of failures; and consequent reduced controllability of the airplane.
99-01-08: This amendment adopts a new airworthiness directive (AD) that is applicable to Pratt & Whitney (PW) JT8D and JT3D series turbofan engines. This action requires operators to remove and replace with serviceable parts, certain stage 7 through stage 15 high-pressure compressor (HPC) disks identified by part number and serial number. This amendment is prompted by a report of an uncontained failure of a stage 8 HPC disk during a takeoff roll that resulted in damage to the airplane. The actions specified in this AD are intended to prevent the failure of a high-pressure compressor disk due to Cadmium embrittlement, resulting in uncontained engine failure and damage to the airplane. Comments for inclusion in the Rules Docket must be received on or before March 1, 1999.
92-17-12: 92-17-12 BRITISH AEROSPACE: Amendment 39-8341. Docket No. 92-NM-64-AD. Applicability: Model HS/BH 125-600A, HS 125-700A, and BAe 125-800A series airplanes; as listed in British Aerospace Service Bulletin 33-45-25A027A&B, dated December 23, 1991; certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent electrical arcing and a resultant fire, accomplish the following: (a) Within 180 days after the effective date of this AD, modify the cabin and toilet fluorescent lighting systems, in accordance with British Aerospace Service Bulletin 33-45-25A027A&B, dated December 23, 1991. (b) An alternative method of compliance or adjustment of the compliance time that provides an acceptable level of safety may be used if approved by the Manager, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate. Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who mayadd comments and then send it to the Manager, Standardization Branch, ANM-113. NOTE: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Standardization Branch. (c) 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. (d) The modification shall be done in accordance with British Aerospace Service Bulletin 33-45-25A027A&B, dated December 23, 1991. This incorporation by reference was approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR Part 51. Copies may be obtained from British Aerospace, PLC, Librarian for Service Bulletins, P.O. Box 17414, Dulles International Airport, Washington, DC 20041-0414. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, Washington; or at the Office of the Federal Register, 800 North Capitol Street NW., suite 700, Washington, DC. (e) This amendment becomes effective on September 28, 1992.