Results
2016-18-03: 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 two in-service incidents of a loss of all air data information in the flight deck. This AD requires a revision of the airplane flight manual (AFM) emergency procedures section to provide procedures to guide the crew on how to stabilize the airplane airspeed and attitude for continued safe flight when a loss of all air data information has occurred in the flight deck. We are issuing this AD to prevent loss of control when a loss of all air data information has occurred in the flight deck.
70-25-03: 70-25-03 BOEING: Boeing 747 and PRATT AND WHITNEY JT9D. Amdt. 39-1116 as amended by Amendment 39-1149. Applies to Boeing Model 747 Series Airplanes and Pratt and Whitney Aircraft Model JT9D Series Engines. \n\n\tCompliance required within the next 600 hours' time in service after the effective date of this AD, unless previously accomplished. \n\n\tTo reduce the possibility of engine surge during thrust reversal, accomplish the following: \n\n\t(a)\tModify the engine Air-Automatic Deceleration System in accordance with Pratt and Whitney Aircraft Service Bulletin Number 2841, dated August 21, 1970, or later FAA approved revision or an equivalent method approved by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region.\n \n\t(b)\tModify the engine controls mixing box, airplane electrical wiring system, engine cowl panel, bleed duct bracket and pressure regulator vent line in accordance with the Boeing Company Service Bulletin Number 75-2002, dated September 25, 1970, or later FAA approved revision or an equivalent method approved by the Chief, Aircraft Engineering Division, FAA, Western Region. \n\n\t(c)\tUpon completion of the work described in (a) and (b) on all four engines, reverse thrust may be used to landing roll speeds as noted in the FAA approved Boeing 747 Airplane Flight Manual Normal Operating Procedures entitled RABS PROCEDURE (OPTIONAL), or an alternate procedure approved by the Chief, Aircraft Engineering Division, FAA, Western Region. \n\n\tUntil such time as the modification of all four engines on an aircraft is accomplished, install the placard described in Boeing Service Bulletin Number 78-2016, dated November 10, 1970, and referenced at Paragraph C(iv), of Boeing Service Bulletin Number 75-2002, dated September 25, 1970, or later FAA approved revisions or an equivalent placard approved by the Chief, Aircraft Engineering Division, FAA, Western Region. The placard may be removed after the modifications in (a) and (b) are accomplished. Theplacard need not be installed if RABS PROCEDURES (OPTIONAL) is not used as an optional procedure by the operator. \n\n\tAmendment 39-1116 effective January 5, 1971. \n\n\tThis amendment 39-1149 becomes effective January 29, 1971.
86-06-05: 86-06-05 BRITISH AEROSPACE AIRCRAFT GROUP: Amendment 39-5263. Applies to all BAe Model HS 748 airplanes, certificated in any category. Compliance is required within 60 days after the effective date of this AD. To prevent the detachment of the windshield wiper actuating arm, accomplish the following, unless already accomplished: A. Inspect and modify, as necessary, the windshield actuating arm in accordance with Dunlap Limited Aviation Division Service Bulletin 30-92, dated March 7, 1985. B. Alternate means of compliance which provide an acceptable level of safety 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 accomplishment of inspections and/or 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 British Aerospace, Inc., Librarian, Box 17414, Dulles International Airport, Washington, D.C. 20041. 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 becomes effective May 2, 1986.
2024-17-09: The FAA is adopting a new airworthiness directive (AD) for certain Embraer S.A. (Embraer) Model EMB-505 airplanes. This AD was prompted by analysis of the left-hand (LH) refreshment center and LH forward cabinet that identified the need for installing structural reinforcements. This AD requires installing structural reinforcements as specified in an Ag[ecirc]ncia Nacional de Avia[ccedil][atilde]o Civil (ANAC) AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
2016-18-01: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 737-600, -700, -700C, -800, -900, and -900ER series airplanes. This AD was prompted by reports of heavy corrosion and chrome damage on the forward and aft trunnion pin assemblies of the right and left main landing gears (MLGs). This AD requires repetitive lubrication of the forward and aft trunnion pin assemblies of the right and left MLGs; repetitive inspections of these assemblies for corrosion and chrome damage, and related investigative and corrective actions if necessary; and installation of new or modified trunnion pin assembly components, which will terminate the repetitive lubrication and repetitive inspections. We are issuing this AD to detect and correct heavy corrosion and chrome damage on the forward and aft trunnion pin assemblies of the right and left MLGs, which could result in cracking of these assemblies and collapse of the MLGs.
71-01-05: 71-01-05 MCDONNELL DOUGLAS: Amdt. 39-1140. Applies to DC-9 series airplanes certificated in all categories. \n\n\tCompliance required within the next 500 hours time in service after the effective date of this AD, unless already accomplished. \n\n\tTo prevent failures in the deployment of the emergency evacuation slide, accomplish the following: \n\n\t(a)\tModify the Douglas Aircraft Company P/N 3753213-39 latch clip in accordance with Douglas Aircraft Company All Operators Letter (AOL) 9-370, dated November 17, 1969, or Revision A thereto, dated November 19, 1970, or later FAA approved revisions, to provide a notch in the latch clip at the point of interference with the clevis pin in the swaged head of the emergency evacuation slide deployment cable assembly, or \n\n\t(b)\tReplace Douglas P/N 3753213-39 latch clip with Douglas P/N 3753213-99 latch clip, or \n\n\t(c)\tAn equivalent modification approved by the Chief, Aircraft Engineering Division, FAA Western Region. \n\n\tThis amendment becomes effective February 17, 1971.
84-25-06: 84-25-06 HAMILTON STANDARD: Amendment 39-4970. Applies to Hamilton Standard Model 23LF-335 and -371 variable pitch propellers installed on, but not limited, to British Aerospace HP137 aircraft certificated in any category. Compliance is required within the next 20 hours time in service or before the next propeller landing reversal, whichever occurs first, following the effective date of this AD, unless already accomplished, and at every 50 propeller landing reversals thereafter. To detect cracks in the blades/counterweights which could cause possible propeller failure, accomplish the following: (a) Clean and inspect for cracks in the propeller blades and counterweights in accordance with section 2, paragraphs A and B of Hamilton Standard ASB No. A27, Revision 1, November 1, 1984, or FAA approved equivalent. (b) Blades and counterweights found to have evidence of cracks must be removed from service and replaced with a serviceable assembly prior to further flight.Aircraft may be ferried in accordance with the provisions of Federal Aviation Regulations (FARs) 21.197 and 21.199 to a base where the AD can be accomplished. Upon request, an equivalent means of compliance with the requirements of this AD may be approved by the Manager, Engine and Propeller Standards Staff, ANE-110, FAA, 12 New England Executive Park, Burlington, Massachusetts 01803. 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 this document from the manufacturer may obtain copies upon request to Hamilton Standard, Division of United Technologies Corporation, Windsor Locks, Connecticut 06096. These documents also may be examined at the Office of the Regional Counsel, FAA, Attn: Rule Docket No. 84-ANE-22, 12 New England Executive Park, Burlington, Massachusetts 01803. This amendment becomes effective on January 3, 1985.
52-23-01: 52-23-01 EDISON FIRE DETECTORS: Applies to All Aircraft Equipped With Edison P/N 35534, Fire Detectors Installed in Junction Boxes. To be accomplished not later than next engine change after January 1, 1953. In order to prevent grounding of either or both terminals of Edison P/N 35534 fire detectors due to inadequate clearance between the detector terminals and the structure to which the junction box and detector assembly are mounted, or the junction box cover in some instances, the following corrective action must be accomplished. The dimensions of the P/N 35534 Edison fire detector should be compared with the dimensions of the junction box employed by each operator to assure that there is sufficient clearance between the detector terminals and the structure to which it is mounted, or the cover. Sufficient clearance will depend on the construction of the junction box, but 3/16 of an inch may be used as a general guide. If such clearance does not exist an appropriate modification should be made, or appropriate insulation provided between the terminals and the structure or the junction box cover, as the case may be. (Douglas General Service Letter DC-6 No. 115, dated January 29, 1952, covers this same subject.)
2024-20-05: The FAA is adopting a new airworthiness directive (AD) for Columbia Helicopters, Inc., Model 234 helicopters and restricted category Model CH-47D helicopters. This AD was prompted by two reports of a flight control rigid connecting link (link) failure, due to a manufacturing defect. This AD requires removing certain links from service and prohibits installing those links. The FAA is issuing this AD to address the unsafe condition on these products.
2016-17-15: 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 the need for more stringent inspection requirements for certain affected components. This AD requires revising the maintenance or inspection program to incorporate certain revised airworthiness limitations (AWL) and require repairs of affected components. We are issuing this AD to detect and correct fatigue cracking in the affected components; such cracking could result in loss of structural integrity.
69-25-03: 69-25-03\tBOEING: Amdt. 39-884. Applies to Model 727 series airplanes listed in Boeing Service Bulletin 71-43 dated 10 November 1969, or later FAA approved revisions. \n\n\tCompliance required within the next 500 hours time in service after the effective date of this AD, unless already accomplished. \n\n\tTo prevent engine cone bolt failures, accomplish the inspections and bolt replacement in accordance with the instructions in Boeing Service Bulletin 71-43, dated 10 November 1969, Section II, Pages 4, 5, and 6, Steps A through F, or later FAA approved revisions, or an equivalent inspection and replacement procedure approved by the Chief, Aircraft Engineering Division, FAA Western Region. \n\n\tThis amendment becomes effective December 5, 1969.
2016-17-06: We are adopting a new airworthiness directive (AD) for all The Boeing Company Model 767-200 and -300 series airplanes. This AD was prompted by an evaluation by the design approval holder (DAH) indicating that the aft pressure bulkhead web to pressure chord joint is subject to widespread fatigue damage (WFD). This AD requires repetitive high frequency eddy current (HFEC) inspections of the aft pressure bulkhead web at fasteners common to the bulkhead web and pressure chord, around the entire circumference of the pressure chord, for any crack, and repair of cracks. We are issuing this AD to detect and correct cracks in the aft pressure bulkhead web. Such cracking could result in the loss of structural integrity of the airplane.
70-14-02: 70-14-02 BELL: Amendment 39-1023. Applies to all Bell Model 47D, 47D-1, 47G, 47G-2 and 47H-1 helicopters certificated in all categories, and to any other helicopters equipped with tail rotor hub assembly bolt (also called a blade grip retaining bolt or a bearing retaining bolt), P/N 47-641-052-3. Compliance required as indicated. To detect and prevent possible failure of the tail rotor hub assembly bolt due to a fatigue crack and to correct any improper installation of the hub bolt, accomplish the following: (a) Within the next 50 hours time in service, remove and replace bolts with 550 hours or more total time in service on the effective date of this AD. (b) Within the next 50 hours time in service, inspect, one time, bolts with less than 550 hours total time in service on the effective date of this AD as follows: (1) Remove and disassemble the tail rotor assembly and remove the hub assembly bolts. (2) Inspect the bolt head to shank radius for cracks using a magnetic particle or equivalent inspection method. (3) Replace cracked bolts before further flight as specified in paragraph (e). (c) Remove and replace bolts with less than 550 hours total time in service on the effective date of this AD at or prior to accumulating 600 hours total time in service. (d) Remove and replace all replacement bolts at or prior to accumulating 600 hours total time in service. (e) Install bolts in accordance with paragraph 6-16.e., Section VI, Model 47D-1, 47G and 47G-2 Maintenance and Overhaul Instruction Manual, as revised August 15, 1961, or in accordance with equivalent FAA approved procedures. This amendment becomes effective August 10, 1970.
50-42-01: 50-42-01 BEECH: Applies to Model A35 Aircraft, Serial Numbers D-1501 to D-2200 Inclusive Not Having the Cambered Elevator Tabs Installed. Compliance required at next 100 hours inspection but not later than November 15, 1950. All aircraft should be modified as follows: (1) Replace the elevator tabs (noncambered) with cambered tabs (lower surface cambered) P/N 35-660040-52 and -53 or, (2) Restrict rear c.g. limit by appropriate revisions to loading schedules and Airplane Flight Manual to comply with the following c.g. limits: (plus 83.7) to (plus 84.4) at 2,650 pounds (plus 75.9) to (plus 84.4) at 2,140 pounds or less Straight line variation between forward c.g. limits. (Beech Service Bulletin No. A35-8 dated April 3, 1950, covers this same subject.)
2016-17-12: We are adopting a new airworthiness directive (AD) for all Airbus Model A318 and A319 series airplanes, Model A320-211, -212, - 214, -231, -232, and -233 airplanes, and Model A321 series airplanes. This AD was prompted by a report of a partial loss of the no-back brake (NBB) efficiency during endurance qualification tests on the trimmable horizontal stabilizer actuator (THSA). This AD requires inspecting certain THSAs to determine the number of total flight cycles the THSA has accumulated, and replacing the THSA if necessary. We are issuing this AD to prevent premature wear of the carbon friction disks on the NBB of the THSA, which could lead to reduced braking efficiency in certain load conditions, and, in conjunction with the inability of the power gear train to keep the ball screw in its last commanded position, could result in uncommanded movements of the trimmable horizontal stabilizer and loss of control of the airplane.
81-19-07: 81-19-07 BOEING: Amendment 39-4212. Applies to Boeing Model 727 airplanes certificated in all categories with the Air Flow Multiplier installed, through line number 1264, on which AiResearch Service Bulletin 21-2291 has not been incorporated. \n\n\tWithin 300 hours time-in-service after the effective date of this AD, accomplish one of the following, unless already accomplished: \n\n\tA.\tBegin performing the repetitive inspections of the Air Flow Multiplier in accordance with Boeing Alert Service Bulletin 727-21A95, dated May 29, 1981. This inspection must be repeated at intervals not to exceed 1000 hours time-in-service. Step B or C below may be used for terminating action for these repetitive inspections. \n\n\tB.\tAccomplish the modification to the air flow multiplier in accordance with AiResearch Service Bulletin 21-2291.\n \n\tC.\tAlternative inspections, repairs, or other action which provide an equivalent level of safety may be used when approved by the Chief, Seattle Area Aircraft Certification Office, FAA Northwest Region.\n \n\tThe 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). \n\n\tAll persons affected by this directive who have not already received the above specified alert service bulletin from the manufacturer may obtain copies upon request to Boeing Commercial Airplane Company, P.O. Box 3707, Seattle, Washington 98124, or it may be examined at FAA Northwest Region, 9010 East Marginal Way South, Seattle, Washington 98108. \n\n\tThis amendment becomes effective September 20, 1981.
81-15-52 R1: 81-15-52 R1 BRITISH AEROSPACE CORPORATION: Amendment 39-4201. Applies to all operators of HS-748 airplanes certified in all categories. To ensure all entry and cargo doors are properly secured, accomplish the following unless already accomplished: 1. Within 2 days after the receipt of this AD, accomplish a preflight check procedure including log book entry in accordance with paragraph 2A of British Aerospace Corporation Alert Service Bulletin A52/90 dated July 10, 1981, or a later FAA approved revision. 2. Within 14 days after the receipt of this AD, remove external markings and indicators in accordance with paragraph 2B of British Aerospace Corporation Alert Service Bulletin A52/90 dated July 10, 1981, or a later FAA approved revision. 3. Within 14 days after the receipt of this AD, perform checks of the mechanical locking system in accordance with paragraph 2C1 of British Aerospace Corporation Alert Service Bulletin A52/90 dated July 10, 1981, or a later FAA approved revision. 4. At the next "A" check or within 14 days, whichever comes first, and at each "A" check thereafter or 14 day-period, perform electrical indication system checks in accordance with paragraph 2C2 of British Aerospace Corporation Alert Service Bulletin A52/90 dated July 10, 1981, or a later FAA approved revision. 5. Airplanes may be flown to a maintenance base for repairs or replacement in accordance with FAR 21.197 and FAR 21.199. 6. Alternate means of compliance or other actions which provide an equivalent level of safety may be used when approved by the Chief, Seattle Area Aircraft Certification Office, FAA Northwest Region. 7. Within ten days after the effective date of this AD, unless already accomplished, inspect the windows adjacent to indicator drums for correct installation in accordance with British Aerospace Corporation Alert Service Bulletin A52/90 dated August 3, 1981, or a later FAA approved revision. If windows are found improperly installed, they must be removed and refitted correctly. 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 the addresses listed above. These documents may also be examined at FAA Northwest Region, 9010 East Marginal Way South, Seattle, Washington 98108. This amendment becomes effective September 9, 1981, and was effective earlier to those recipients of Telegraphic AD T81-15-52 dated July 10, 1981.
2016-17-11: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 787-8 airplanes. This AD requires a one-time inspection of the engine pylon wiring bracket on the left wing for the presence of an existing corner relief fillet, and corrective action if necessary. This AD was prompted by a report indicating that the engine pylon wiring bracket on certain airplanes was missing a corner relief fillet, which could result in stress concentration and cracking in the engine pylon wiring bracket. We are issuing this AD to detect and correct cracking in the engine pylon wiring bracket. Such cracking could result in damage to adjacent power feeders, subsequent electrical arcing in a flammable leakage zone, and consequent uncontrollable fire.
66-22-03: 66-22-03 HAWKER SIDDELEY: Amdt. 39-281 Part 39 Federal Register September 3, 1966. Applies to Model DH.125-1A Airplanes Equipped With Aileron and Elevator Systems Gust Lock, P/N 25CF-1793AB. Compliance required within the next 300 hours' time in service after the effective date of this AD, unless already accomplished. To prevent operation with the elevator and aileron gust lock engaged, accomplish the following: (a) Remove gust lock assembly, P/N 25CF-1793AB, located on left side of cockpit. (b) Modify pilot's control wheel and seat rail, and install gust lock stowage box assembly, P/N 25.MM. 333, in accordance with Hawker Siddeley Aviation Ltd. Service Bulletin No. 27-34-(1716), dated May 18, 1966, or later ARB-approved issue. (c) Equip airplane with aileron and elevator gust lock assembly P/N 25.MM. 2583. This directive effective September 3, 1966.
81-21-51 R1: 81-21-51 R1 LOCKHEED-CALIFORNIA COMPANY: Amendment 39-4329 as amended by Amendment 39-4533. Applies to Lockheed Model L-1011-385 series airplanes, certificated in all categories. To alert the flight crew to conditions which may precede engine failure, perform the following, unless previously accomplished: A. Within 25 hours time in service after the receipt of this AD or within 3 calendar days, whichever occurs later, revise the Lockheed L-1011 FAA approved Airplane Flight Manual LR-25925 to add the following and provide to flight crews: NOTE: FAA approved Lockheed L-1011 Airplane Flight Manual revision dated September 29, 1981, is considered an acceptable means of compliance for paragraph A. SECTION 1 - LIMITATIONS POWERPLANT LIMITATIONS Airborne Vibration Monitor (AVM) System o At least one channel (A or B) (FAN or TURB) of the AVM System must be operative for each engine for all flight operations. o The operative AVM channel (A or B) (FAN orTURB) must be the same for all engines and must be latched in. o When both channels of the AVM System are operative, channel A or FAN must be latched in. If this channel becomes inoperative (indication goes to zero) inflight, select B or TURB. o For single or dual channel operation, the AVM filter selector must be set to the NORM position. SECTION 2 - EMERGENCIES ENGINE ABNORMAL VIBRATION INDICATION. During steady running conditions, if an Airborne Vibration Monitor (AVM) System channel indicates a sudden increase of 1 unit or more, or exceeds 2.5 units (warning light setting) for more than 2 seconds, even if the indication returns to normal: IMMEDIATE ACTION THROTTLE Close FUEL AND IGNITION SWITCH Off NOTE During takeoff roll, a momentary fluctuation of the AVM indication with no other indication of engine malfunction is not cause for engine shutdown. REFERENCE HYDRAULIC POWER Check ELECTRICAL LOADS Monitor AC ESSENTIALPOWER Check Do not attempt a relight unless a greater emergency exists. NOTE When holding or descending in heavy icing conditions, the AVM indication may gradually increase to above 2.5 units (warning light setting). No action is required unless other indications of engine malfunction are observed. This condition can be alleviated by increasing N1 to 90 percent for 5 seconds when ice accumulation (gradual vibration increase) is first detected. SECTION 2 - EMERGENCIES ENGINE OIL FILTER PRESSURE LIGHT ILLUMINATED If the engine oil FILTER PRESSURE light illuminates steadily: IMMEDIATE ACTION THROTTLE Close FUEL AND IGNITION SWITCH Off REFERENCE HYDRAULIC POWER Check ELECTRICAL LOADS Monitor AC ESSENTIAL POWER Check Do not attempt a relight unless a greater emergency exists. B. Within 25 hours time in service after the receipt of this AD, reactivate the AVM input to the ENG/APU STATUS light in accordance with the Accomplishment Instructions in Lockheed L-1011 Alert Service Bulletin 093-77-A044, Revision 2, dated September 29, 1981, or later revisions approved by the Manager, Los Angeles Aircraft Certification Office, FAA Northwest Mountain Region. C. Within 75 days calendar time after receipt of this AD, comply with paragraphs A and B (Parts I and II) of the Accomplishment Instructions in Lockheed L-1011 Alert Service Bulletin 093-77-A049 dated September 29, 1981, or Revision 1, dated October 13, 1981, or later revisions approved by the Manager, Los Angeles Aircraft Certification Office, FAA Northwest Mountain Region. D. When the indications specified in paragraph A above occur, engines must undergo the following appropriate maintenance actions prior to further engine operation for flight: 1. Rolls Royce Alert Service Bulletin RB.211-77-A6422 dated September 4, 1981, paragraph D.(3) for oil pressure and/or AVM indications. 2. Lockheed L-1011 Maintenance Manual Chapter 71-91-00, High Indicated Vibration. E. For aircraft incorporating engines which are in compliance with AD 82-12-05, Amendment 39-4398, and which have engine indicating systems modified in accordance with the Accomplishment Instructions in Lockheed L-1011 Service Bulletin 093-77-052, dated December 17, 1982, the Powerplant Limitations and Emergency Procedures contained in FAA approved Lockheed L-1011 Airplane Flight Manual No. LR-25925 revision dated December 20, 1982, may be used in lieu of those specified in paragraph A. above. F. Special flight permits for a two-engine ferry flight 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. G. Alternate methods of compliance with this AD which provide an equivalent level of safety may be used when approved by the Manager, Los Angeles Aircraft Certification Office, FAA Northwest Mountain 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. 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 Lockheed-California Company, P.O. Box 551, Burbank, California 91520, Attention: Commercial Support Contracts, Dept. 63-11, U-33, B-1. These documents also may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or Los Angeles Aircraft Certification Office, 4344 Donald Douglas Drive, Long Beach, California. Amendment 39-4329 became effective March 11, 1982, to all persons, except those to whom it was made immediately effective by Telegraphic AD T81-21-51, dated October 1, 1981. This Amendment 39-4533 becomes effective January 17, 1983.
66-16-06: 66-16-06 PRATT & WHITNEY: Amdt. 39-256 Part 39 Federal Register July 2, 1966. Applies to Models JT3C-7 and JT3C-12 Turbojet Engines. Compliance required as indicated. To prevent further failures of fourth stage compressor rotor disc spacer assemblies, accomplish the following: (a) For fourth stage compressor rotor disc spacer assemblies, P/N 359413, with 1,000 or more hours' time in service since last overhaul, comply with (c) within the next 50 hours' time in service after the effective date of this AD, unless already accomplished within the last 575 hours' time in service, and thereafter at intervals not to exceed 625 hours' time in service from the last inspection until installation of assembly, P/N 429177. (b) For fourth stage compressor rotor disc spacer assemblies, P/N 359413, with less than 1,000 hours' time in service since last overhaul, comply with (c) before the accumulation of 1,050 hours' time in service since last overhaul, unless already accomplished after the accumulation of 425 hours' time in service since last overhaul, and thereafter at intervals not to exceed 625 hours' time in service from the last inspection until installation of assembly, P/N 429177. (c) Drill an inspection hole and install a plug in the compressor case and fourth stage vane and shroud assembly in accordance with Pratt & Whitney Aircraft letter dated April 15, 1966, and sketches PWA 15814 and SL61447. Using an American Cystoscope Makers Incorporated Model B-175-AS-15, B-110-AS-15 instrument (or FAA-approved equivalent) inserted through this hole, inspect the fourth stage compressor rotor disc spacer assembly for indication of cracks in visible areas of the spacer. If any indications of cracks are found, remove the engine before further flight, disassemble, and reinspect. If, after disassembly, no cracks are found, the engine may be returned to service. Replace any cracked spacer assemblies before further flight with an assembly of the same partnumber or P/N 429177. NOTE: During the inspection required by (c), particular attention should be directed to the front and rear seal edges. (d) Upon request of the operator, an FAA maintenance inspector, subject to prior approval of the Chief, Engineering and Manufacturing Branch, FAA Eastern Region, may adjust the repetitive inspection intervals specified in this AD to permit compliance at an established inspection period of the operator if the request contains substantiating data to justify the increase for that operator. This directive effective July 2, 1966.
2016-17-04: We are adopting a new airworthiness directive (AD) for all hot air balloons to determine if BAL[Oacute]NY KUB[Iacute][Ccaron]EK spol. s r.o. Model Kub[iacute][ccaron]ek burners equipped with fuel hoses made of ``EGEFLEX'' material are installed. This AD results from mandatory continuing airworthiness information (MCAI) issued by the aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as propane leaks found on burners equipped with fuel hoses made of EGEFLEX material. We are issuing this AD to require actions to address the unsafe condition on these products.
69-05-05: 69-05-05 PILATUS: Amdt. 39-732. Applies to Model PC-6/B-H2 and PC-6/B1-H2 airplanes. Compliance required within the next 25 hours' time in service after the effective date of this AD, unless already accomplished. Check the travel of the knurled friction nut on the power control lever assembly to determine if it exceeds 3/4 of a turn. If travel exceeds 3/4 of a turn, install shim(s) of adequate thickness, or drill a new hole and insert a new cotter pin, in accordance with Pilatus Service Bulletin No. 85 dated July 1968 or later Swiss Federal Air Office-approved issue or an FAA- approved equivalent. This amendment becomes effective March 12, 1969.
86-07-13: 86-07-13 AVCO LYCOMING DIVISION: Amendment 39-5265. Applies to Avco Lycoming ALF502L series turbofan engines. Compliance is required within the next 50 hours time in service after the effective date of this AD unless already accomplished within the last 50 hours time in service, and thereafter at intervals not to exceed 100 hours time in service from the last inspection. To prevent engine power loss due to release of fourth stage compressor vane airfoils into the compressor flow path, accomplish the following: (a) Inspect the fourth stage compressor vane assemblies, identified by Avco Lycoming Part Number (P/N) 2-100-040-27, for vane cracking at the outer shroud in accordance with Avco Lycoming Service Bulletin (SB) Number ALF502L-72-0137, dated March 27, 1986. (b) Remove from service, prior to further flight, those fourth stage compressor vane assemblies found with vane airfoils missing, or cracked or separated at the outer shroud. Aircraft may be ferriedin accordance with the provisions of FAR 21.197 and 21.199 to a base where the AD can be accomplished. Upon request, an equivalent means of compliance with the requirements of this AD may be approved by the Manager, Engine Certification Office, Aircraft Certification Division, New England Region, Federal Aviation Administration, 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, Burlington, Massachusetts, may adjust the compliance time specified in this AD. Avco Lycoming SB Number ALF502L-72-0137, dated March 27, 1986, identified and described in this document, is 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 this document from the manufacturer may obtain copies upon request to Avco Lycoming Division, 550 South Main Street, Stratford, Connecticut 06497. These documents also may be examined at the Office of the Regional Counsel, New England Region, Federal Aviation Administration, 12 New England Executive Park, Burlington, Massachusetts 01803. This amendment becomes effective on April 11, 1986.
2023-12-03: The FAA is correcting an airworthiness directive (AD) that was published in the Federal Register. That AD applies to certain Airbus SAS Model A350-941 and -1041 airplanes. As published, a European Union Aviation Safety Agency (EASA) AD number specified in the regulatory text is incorrect. This document corrects that error. In all other respects, the original document remains the same.