Results
2006-02-12: The FAA adopts a new airworthiness directive (AD) for all Glaser-Dirks Flugzeugbau GmbH Models DG-100 and DG-400 sailplanes and certain DG Flugzeugbau GmbH Models DG-500 Elan Series and DG-500M sailplanes. This AD requires you to modify or replace the complete rudder mount assembly and ensure that the securing washer, castellated nut, and new split pins are installed. This AD results from mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Germany. We are issuing this AD to prevent the universal bearing of the lower rudder mounting from slipping out of the bearing support. The universal bearing slipping out could result in the rudder separating from its support. This failure could lead to loss of sailplane control during flight operations.
64-16-01: 64-16-01\tBOEING: Amdt. 760 Part 507 Federal Register July 8, 1964. Applies to Model 720 Series Aircraft. \n\n\tCompliance required as indicated. \n\n\tSeveral failures of bolts attaching the main landing gear centering cylinder and snubber assembly to the inner cylinder assembly and to the truck assembly have occurred. To preclude further failures, the following or an equivalent approved by the Chief, Aircraft Engineering Division, FAA Western Region, shall be accomplished: \n\n\t(a)\tWithin the next 500 hours' time in service after the effective date of this AD, unless already accomplished: \n\n\t\t(1)\tReplace the existing bolts attaching the main landing gear centering cylinder and snubber assembly to the inner cylinder assembly and to the truck assembly with larger diameter bolts specified in step (e) and in accordance with the provisions of the note following step (e) of paragraph 3, Modification Data of Boeing Service Bulletin No. 1570. The provisions of Boeing Service Bulletin No. 1570A shall also be accomplished; or \n\n\t\t(2)\tAs an alternative, remove the existing 9/16 inch-diameter bolts, P/N's 63-9663 and 66-26031, and replace with 9/16 inch-diameter Standard Press Steel (SPS), P/N's 63425-9-24 and 63425-9-28 (H.T. 220,000 p.s.i. MIN.) respectively. The new bolts are to be reworked in accordance with the instructions on Figure 1 of Boeing Service Bulletin No. 1570, or later approved revisions to Boeing Service Bulletin No. 1570. \n\n\t(b)\tWithin the next 3,000 hours' time in service after the effective date of this AD, accomplish the following, unless already accomplished: \n\n\t\t(1)\tRemove existing bolts, P/N's 63-9663 and 66-26031, or P/N's 63425-9-24 and 63425-9-28. \n\n\t\t(2)\tRework terminal and inner cylinder lug per Figures 3 and 5 and steps 3b and 3c of Boeing Service Bulletins Nos. 1570 and 1570A respectively. \n\n\t\t(3)\tRework truck assembly lug per Figure 4 and step 3d of Boeing Service Bulletins Nos. 1570 and 1570A. \n\n\t\t(4)\tReinstall centering cylinder and snubber assembly using bolts 66-15739-1 and 66-15739-2 as shown in Figure 2 of Boeing Service Bulletin No. 1570. \n\n\t(c)\tThe modifications in (a)(1) or (a)(2) need not be accomplished if the provisions of (b) are accomplished prior to the next 500 hours' time in service following the effective date of this AD. \n\n\t(d)\tCompliance with paragraph (b) may be extended to the next main landing gear overhaul or to 6,000 hours' time in service after the effective date of this AD, whichever occurs first, if the following is accomplished: \n\n\t\t(1)\tOperators who have complied with (a)(1) shall replace the bushings prior to 3,000 hours' time in service after the bushing has been reworked.\n \n\t\t(2)\tOperators who have complied with (a)(2) shall replace the bolts at periods not to exceed 2,000 hours' time in service until (b) is accomplished. \n\n\t(Boeing Service Bulletins Nos. 1570 and 1570A cover this same subject.) \n\n\tThis directive effective August 7, 1964.
99-09-14: This amendment supersedes an existing airworthiness directive (AD), applicable to all Lockheed Model L-1011-385 series airplanes, that currently requires inspections to detect cracking of fuselage station (FS) 983 main frame (left and right sides), and repair, if necessary. That AD was prompted by reports of cracks found in the left and right sides of the FS 983 main frame, below the level of the cabin floor. This amendment adds a new requirement to review the airplane maintenance records to determine if a crack within the FS 983 main frame web was detected previously, and if repair of any such crack was deferred; and repetitive inspections, if necessary, until accomplishment of a repair. This amendment also adds terminating action for the repetitive inspections. The actions specified by this AD are intended to prevent cracking of the FS 983 frame, which could result in reduced structural integrity of the fuselage.
62-06-03: 62-06-03 HILLER: Amdt. 411 Part 507 Federal Register March 22, 1962. Applies to All Model UH-12D Helicopters and Model UH-12E Serial Numbers 942, 954, 2001 Through 2198 Inclusive. Compliance required as indicated. (a) Prior to next flight install placard in cockpit in full view of pilot to read as follows: "Oil Warmup Procedure: 1. After Start Idle at 1,450 r.p.m. in Flat Pitch. A. If Oil Temperature is Less Than 20 degrees C. Idle Engine For a Minimum of Four Minutes. Continue Idle As Necessary Until Oil Temperature Reaches 20 degrees C. B. If Oil Temperature is Greater Than 20 degrees C. Idle Engine For Two Minutes. 2. Complete Warmup at 2,350 r.p.m. Until Oil Temperature Reaches 40 degrees C. ShutDown Procedure. After Main Rotor Blades Come to Rest Crank Engine 20-25 Seconds With Magneto Switch Off." (b) Within 10 hours' time in service after effective date of this directive and every 25 hours' time in service thereafter until accomplishment ofparagraph (d), inspect the first and second stage planetary system in the transmission in accordance with Hiller Service Information Letter 3028 and at time of first inspection install ring gear spacer baffle P/N 23652 as described therein. Replace parts showing evidence of overheating or abnormal wear prior to further flight. (c) Within 10 hours' time in service after effective date of this directive install placard in cockpit in full view of pilot to read as follows: "Operation of Helicopter in Ambient Temperatures of -10 degrees F., -23 degrees C., or Colder is Prohibited." This placard may be removed upon accomplishment of paragraph (d). (d) Within 100 hours' time in service after effective date of this directive modify transmission and lubrication system to incorporate additional lubrication provisions for the transmission. Conduct modification in accordance with Hiller Service Bulletin 2026. NOTE: The inspection and baffle installation specified in paragraph (b), are included in and required as part of Service Bulletin 2026. (Hiller Service Information Letters 3027 dated January 19, 1962, 3028 dated February 2, 1962, 3029 dated February 14, 1962, and Service Bulletin 2026 dated February 26, 1962, cover this same subject.) This directive effective upon publication in the Federal Register for all persons except those to whom it was made effective immediately by telegram dated March 2, 1962.
2006-03-17: The FAA is adopting a new airworthiness directive (AD) for certain Polskie Zaklady Lotnicze Spolka zo.o. Model PZL M26 01 airplanes. This AD requires you to repetitively inspect fuselage frame No. XI for cracks and to replace fuselage frame No. XI and install reinforcement modifications if any cracks are found. The installation of reinforcement modifications is terminating action for the repetitive inspection requirement. This AD results from mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for the European Union. We are issuing this AD to detect and correct cracks in fuselage frame No. XI, which could result in failure of this frame. This failure could lead to failure of the tail section of the airplane.
82-06-10: 82-06-10 CESSNA: Amendment 39-4363. Applies to Models 210L/T210L (S/Ns 21059810, 21059819 thru 21061573), 210M/T210M (S/Ns 21061574 thru 21062954), 210N/T210N (S/Ns 21062955 thru 21064535) and P210N (S/Ns P21000001 thru P21000760) airplanes equipped with Airborne Model 442CW-8 (Cessna P/N C431004-0102) vacuum pump, pneumatic deicer boots and vacuum operated attitude indicator. COMPLIANCE: Required as indicated, unless already accomplished. To prevent loss of vacuum-driven-attitude instruments resulting from failure of the single Airborne Model 442CW-8 (Cessna P/N C431004-0102) vacuum pump during flight in IFR conditions, before further flight, accomplish the following: A) Remove approval for IFR operations by: 1. Installing a temporary placard on the instrument panel in full view of the pilot, which reads in letters at least 1/8-inch high "APPROVED FOR DAY-NIGHT-VFR OPERATIONS" and operate the airplane in accordance with this limitation. 2. Covering theabbreviation "IFR" on the types of operation placard and on the facsimile of this placard in the applicable Airplane Manual, Pilot's Operating Handbook or Information Manual with opaque tape or equivalent. B) The requirements of Paragraph A) of this AD are no longer applicable when: 1. An attitude indicator powered by an independent power source is installed, or 2. Cessna Service Alert Letter SE82-13 has been incorporated or, 3. Cessna P/N C431003-0102 (Airborne) or C431003-0302 (Edo-Aire, P/N 1U128-001 or -003) pump is installed replacing the C431004-0102 (Airborne Model 442CW-8) pump. The PN C4310O3-0102 or -0302 pump may be installed as follows: a. Bolt the pump on the pad vacated by the P/N C431004-0102 pump. b. Remove fittings from P/N C431004-0102 pump and install fittings in the P/N C431003-0l02 or -0302 pump. c. Reconnect the vacuum hose to the pump suction port. d. Remove the pressure hose from the pump leading to the deicepressure valve mounted on the firewall. (Cover the valve inlet to exclude foreign objects.) e. On those aircraft approved for flight into known icing, cover the words, "This airplane is approved for flight into icing conditions if the proper optional equipment is installed and operational," on the types of operation placard and on the facsimile of this placard in the applicable Airplane Flight Manual, Pilots Operating Handbook or Information Manual with opaque tape or equivalent. f. Install a temporary placard on the instrument panel in the vicinity of the De-Ice Press switch in full view of the pilot which reads in letters at least 1/8-inch high "WING/TAIL BOOTS INOP." C) Paragraph A) of this AD may be accomplished by the holder of at least a private pilot certificate issued under Part 61 of the Federal Aviation Regulations on any airplane owned or operated by that person. This person must make the prescribed entry in the aircraft maintenance records, including those airplanes on which it has already been accomplished, indicating compliance with this AD. D) Any equivalent method of compliance with this Airworthiness Directive, if used, must be approved by the Chief, Wichita Aircraft Certification Office, FAA, Room 238, Terminal Building 2299, Mid-Continent Airport, Wichita, Kansas, telephone (316) 269-7000. This Amendment 39-4363 becomes effective on April 15, 1982, to all persons except those to whom it has already been made effective by an airmail letter from the FAA dated March 12, 1982, and is identified as AD 82-06-10.
99-09-01: This amendment adopts a new airworthiness directive (AD) that is applicable to certain McDonnell Douglas Model MD-11 series airplanes. This action requires a visual inspection to verify that the channel flanges of the bracket installations are facing forward and to detect chafing or damage of the wire bundles of the center accessory compartment (CAC), and corrective actions, if necessary. This amendment also requires that operators submit a report of the inspection results to the FAA. This amendment is prompted by an incident in which sparks and smoke came out of the CAC during a functional test due to a wire bundle that had chafed against a support bracket installation, which was installed improperly during production of the airplane. The actions specified in this AD are intended to ensure that such bracket installations are installed properly. Improper installation of the brackets of the CAC could cause chafing of the wire bundles, which could result in sparks, smoke,and possible fire in the CAC.
97-15-13 R2: This amendment revises Airworthiness Directive (AD) 97-15-13 R1, which currently requires installing lubrication fittings in the airstair door handle and latch housing mechanisms on certain Raytheon Aircraft Company (Raytheon) Beech Models 1900, 1900C, and 1900D airplanes. Since issuance of AD 97-15-13 R1, Raytheon has revised the applicable service information to correct the reference to the number of parts each owner/operator of the affected airplanes should order and to change an incorrect reference to a maintenance manual. This AD retains the actions of AD 97-15-13 R1, and incorporates the revised service bulletin into the AD. The actions specified by this AD are intended to continue to prevent moisture from accumulating and freezing in the airstair door handle and latch housing, which could result in the door freezing shut and passengers not being able to evacuate the airplane in an emergency situation.
99-08-22: This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-10 series airplanes and KC-10 (military) airplanes, that requires repetitive inspections to detect fatigue cracking of the rear spar cap of the horizontal stabilizer; and repair, if necessary. The amendment also would require a preventive modification of the rear spar cap of the horizontal stabilizer, which would constitute terminating action for the repetitive inspections. This amendment is prompted by reports of fatigue cracking of the rear spar cap of the horizontal stabilizer. The actions specified by this amendment are intended to prevent fatigue cracking of the rear spar cap of the horizontal stabilizer, which could result in reduced structural integrity of the horizontal stabilizer, and consequent reduced controllability of the airplane.
2006-03-14: The FAA is adopting a new airworthiness directive (AD) for Rolls Royce plc (RR) RB211 Trent 500 series turbofan engines. This AD requires initial and repetitive borescope inspections of the high pressure-and-intermediate pressure (HP-IP) turbine oil vent tubes and bearing chambers for coking and carbon buildup and replacing the vent tubes if necessary. This AD results from a report of an RB211 Trent 700 series engine that experienced a disk shaft separation, overspeed of the IP turbine rotor, and multiple blade release of IP turbine blades. Since the design arrangement in the Trent 500 series engines is similar to that of the Trent 700 series engines, the same failure could occur in the Trent 500 series engines. We are issuing this AD to prevent internal oil fires caused by coking and carbon buildup, that could result in uncontained engine failure and damage to the airplane.
52-25-02: 52-25-02 ERCOUPE: Applies to Models 415-C and -CD Aircraft Having a 5.00x4 Nose Wheel and Using Federal Skis. To be accomplished not later than December 1, 1952. To eliminate instances of the nose ski coming off when operating on Federal Aircraft Works Model A-1500 skis, a supplementary safety device should be installed. A simple and suitable device is a rectangular plate (approximately 1/8-inch thick and 1/2-inch longer than axle diameter) installed to end of axle stub so that ends of plate will prevent retaining nut from backing off if lock washer fails. This plate, which will also provide for visual inspection of retaining nut, to be held in place by a safetied through bolt. This modification can easily be made and installed in the field. Drawing (No. ES-B-203) describing such an installation is available from Federal Aircraft Works, Minneapolis, Minn. (Federal Service Bulletin No. 100 also covers this subject.)
2019-23-02: The FAA is adopting a new airworthiness directive (AD) for certain Airbus SAS Model A330-200 Freighter, A330-200, and A330-300 series airplanes. This AD was prompted by a determination that new or more restrictive airworthiness limitations are necessary. This AD requires revising the existing maintenance or inspection program, as applicable, to incorporate new or more restrictive airworthiness limitations. The FAA is issuing this AD to address the unsafe condition on these products.
2008-18-08: We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) issued by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as: This action is necessary following the discovery of IP Compressor Rotor rear balance land cracking on an in-service Trent 800 engine. Stress analysis of the damaged rotor has shown a possible threat to the rotor integrity, the cracking therefore presents a potential unsafe condition. We are issuing this AD to detect cracking on the intermediate pressure (IP) compressor rotor rear balance land. IP compressor rotor rear balance land cracking can lead to uncontained failure of the rotor and damage to the airplane.
59-26-07: 59-26-07 LOCKHEED: Amdt. 73 Part 507 Federal Register December 19, 1959. Applies to Models 649 and 749 Aircraft, Serial Numbers 2518 Through 2524, 2529 Through 2535, 2548, 2549, 2554 Through 2556, 2610, 2611, 2614 Through 2618, 2642, 2653, 2659, 2660, 2662 Through 2673, Model 1049-54 Serial Numbers 4001 Through 4024 and Model 1049C, Serial Numbers 4523 Through 4538. Compliance required as indicated. As a result of cracks discovered in forward passenger door latch brackets the following shall be accomplished on the above serial numbered aircraft which have accumulated flight time of 10,000 hours or more. Unless already accomplished, within the next 200 hours of service time and at each succeeding 1,000 hours of service time the following inspections are required: (a) Models 649 and 749 aircraft. (1) Remove and inspect by the dye penetrant method the top and bottom P/N 291924-2 and -3 brackets of the P/N 291941-2 and -3 top and bottom latch assemblies of the P/N 290809 forward passenger door assembly for cracks in the fillet radius of attach flanges of the brackets. (Lockheed Field Service Letters FS/222746 and FS/220393-W pertain to this subject.) Cracked latch brackets must be replaced. The replacement part may be either a new bracket of the same part number, the improved latch assembly P/N 554278-1, P/N 554389-1 or P/N 554289-3, whichever is applicable, or an equivalent item. (2) Check door rigging and condition of safety bar and hooks. (b) Models 1049-54 and 1049C aircraft. (1) Remove and inspect by the dye penetrant method the upper lower aft P/N 291925 and/or P/N 308236 brackets of the P/N 291940 and P/N 338239 upper and lower aft latch assemblies of the P/N 308269 and P/N 308269-600 forward passenger door assemblies for cracks in the fillet radius of the attach flanges of the brackets. (Lockheed Field Service Letters FS/222746 and FS/220393-W pertain to this subject.) Cracked latch brackets must be replaced.The replacement part may be either a new bracket of the same part number, the improved latch assembly P/N 554278-3, P/N 554289-1, or P/N 554289-3, whichever is applicable, or an equivalent item. (2) Check door rigging and condition of safety bar and hooks. When the improved latch assemblies (identified above by part number) are installed, this inspection procedure may be terminated. When the replacement bracket is identical to the originally installed bracket, this inspection procedure is to be reestablished upon accumulation of 10,000 flight-hours on the replacement brackets. (Lockheed Service Bulletins 49/SB-882 and 1049/SB-3052 describe the installation of the improved latch assemblies mentioned above.)
2006-03-11: The FAA is adopting a new airworthiness directive (AD) for all British Aerospace Model HS 748 airplanes. This AD requires installing a baulking actuator system for the elevator gust lock; doing a functional test and an inspection of any previously installed baulking actuator system for wiring errors; doing repetitive inspections of the gust lock baulk lever for correct operation; and corrective action, if necessary. This AD results from incidents where an elevator gust lock re-engaged without input from the flightcrew, and may have caused a flight control restriction. We are issuing this AD to prevent uncommanded re- engagement of the elevator gust lock, which could result in restriction of the elevator's movement and consequent reduced controllability of the airplane.
99-08-14: This amendment adopts a new airworthiness directive (AD), applicable to Pratt & Whitney (PW) PW2000 series turbofan engines, that requires revisions to the engine manufacturers time limits section (TLS) to include enhanced inspection of selected critical life-limited parts at each piece-part exposure. This amendment will also require an air carrier's approved continuous airworthiness maintenance program to incorporate these inspection procedures. This amendment is prompted by a Federal Aviation Administration (FAA) study of in-service events involving uncontained failures of critical rotating engine parts that indicated the need for improved inspections. The improved inspections are needed to identify those critical rotating parts with conditions that if allowed to continue in service, could result in uncontained failures. The actions specified by this AD are intended to prevent critical life-limited rotating engine part failure, which could result in an uncontained engine failure and damage to the airplane.
99-08-15: This amendment adopts a new airworthiness directive (AD), that requires revisions to the Time Limits Section (TLS) of the manufacturer's Engine Manuals (EMs) for Pratt & Whitney (PW) PW4000 series turbofan engines to include required enhanced inspection of selected critical life-limited parts at each piece-part exposure. This amendment will also require an air carrier's approved continuous airworthiness maintenance program to incorporate these inspection procedures. This amendment is prompted by a Federal Aviation Administration (FAA) study of in-service events involving uncontained failures of critical rotating engine parts that indicated the need for improved inspections. The improved inspections are needed to identify those critical rotating parts with conditions that if allowed to continue in service, could result in uncontained failures. The actions specified by this AD are intended to prevent critical life-limited rotating engine part failure, which could result in an uncontained engine failure and damage to the airplane.
81-03-04: 81-03-04 SOCIETE NATIONALE INDUSTRIELLE AEROSPATIALE: Amendment 39- 4058. Applies to Models SA315, SA316B, SA316C, and SA319 helicopters certificated in all categories. Compliance required as follows, unless already accomplished: 1. Within 10 hours' time in service after the effective date of this AD for helicopters with transmissions which have 390 hours' or more total time in service, or, 2. Before accumulation of 400 hours' total time in service for helicopters with transmissions which have less than 390 hours' time in service on the effective date of this AD, and, 3. Thereafter at intervals not to exceed 400 hours' time in service. Inspect transmission components for possible excessive wear at the coupling splines of the rear output bevel pinion-to-vertical gearshaft of the main gearbox in accordance with instructions in Aerospatiale Service Bulletin No. 05.68 dated October 3, 1980, or FAA-approved equivalent for the Aerospatiale Model SA316 and SA319 series helicopters, or Aerospatiale Service Bulletin No. 05.16 dated October 3, 1980, or FAA-approved equivalent, for the Aerospatiale Model SA315 helicopter. (Except for model designation these bulletins are identical.) If the total displacement found by this inspection exceeds 1.00 millimeter (0.04 inches) before further flight replace the transmission with a serviceable like transmission. Equivalent means of compliance must be approved by the Chief, Aircraft Certification Staff, FAA, Europe, Africa, and Middle East Office, c/o American Embassy, Brussels, Belgium. This amendment becomes effective March 12, 1981, for all persons except those to whom it was made effective immediately by priority mail letter AD No. 81-03-04 dated January 22, 1981 (priority letter superseded telegraphic AD 80-19-51).
2006-03-08: The FAA adopts a new airworthiness directive (AD) for all airplanes equipped with Aero Advantage ADV200 series (part numbers ADV211CC and ADV212CW) vacuum pumps installed under supplemental type certificate number SA10126SC, through field approval, or other methods. This AD requires you to remove from service any affected vacuum pump and install an FAA-approved vacuum pump other than the affected part numbers. This AD results from several reports of pump chamber failure. We are issuing this AD to prevent vacuum pump failure or malfunction during instrument flight rules (IFR) flight that could lead to loss of flight instruments critical for flight. The loss of flight instruments could cause pilot disorientation and loss of control of the aircraft.
99-08-12: This amendment adopts a new airworthiness directive (AD), that requires revisions to the Engine Time Limits section in the Engine Manual (EM) for Pratt & Whitney (PW) JT9D series turbofan engines to include required enhanced inspection of selected critical life-limited parts at each piece-part exposure. This amendment will also require an air carrier's approved continuous airworthiness maintenance program to incorporate these inspection procedures. This amendment is prompted by a Federal Aviation Administration (FAA) study of in-service events involving uncontained failures of critical rotating engine parts which indicated the need for improved inspections. The improved inspections are needed to identify those critical rotating parts with conditions, that if allowed to continue in service, could result in uncontained failures. The actions specified by this proposed AD are intended to prevent critical life-limited rotating engine part failure, which could result in an uncontained engine failure and damage to the airplane.
99-08-13: This amendment adopts a new airworthiness directive (AD), that requires revisions to the Life Limits Section of the manufacturer's Instructions for Continued Airworthiness (ICA) for General Electric Company (GE) CF6-80A, CF6-80C2 and CF6-80E1 series turbofan engines to include required enhanced inspection of selected critical life-limited parts at each piece-part exposure. This AD also requires that an air carrier's approved continuous airworthiness maintenance program incorporate these inspection procedures. This amendment is prompted by a Federal Aviation Administration (FAA) study of in-service events involving uncontained failures of critical rotating engine parts that indicated the need for improved inspections. The improved inspections are needed to identify those critical rotating parts with conditions, which if allowed to continue in service, could result in uncontained failures. The actions specified by this AD are intended to prevent critical life-limited rotating engine part failure, which could result in an uncontained engine failure and damage to the airplane.
89-10-07: 89-10-07 PRATT & WHITNEY: Amendment 39-6181. Applicability: Pratt & Whitney (PW) JT9D-3A, -7, -7A, -7AH, -7H, -7F, -7J, and -20 turbofan engines. Compliance: Required as indicated, unless already accomplished. To prevent a diffuser case Number 4 or Number 7 strut failure that can cause a Number 3 bearing compartment fire and subsequent nacelle fire, accomplish the following: (a) Install strut insert assembly Part Number 804698-01 into both the Number 4 and Number 7 diffuser case struts, in accordance with the Accomplishment Instructions of PW Service Bulletin (SB) 5730, dated February 4, 1987, at the next engine shop visit after the effective date of this AD, but not later than August 31, 1991. NOTE: For the purpose of this AD, engine shop visit is defined as maintenance entailing a separation of the high pressure compressor case and diffuser case "K" flange. (b) Aircraft may be ferried in accordance with the provisions of FAR 21.197 and 21.199 toa base where the AD may be accomplished. (c) Upon submission of substantiating data by an owner or operator through an FAA Airworthiness Inspector, an alternative method of compliance with the requirements of this AD or adjustment to the compliance times specified in this AD may be approved by the Manager, Engine Certification Office, ANE-140, Engine and Propeller Directorate, Aircraft Certification Service, Federal Aviation Administration, 12 New England Executive Park, Burlington, Massachusetts 01803. The diffuser case strut insert incorporation shall be done in accordance with PW SB 5730, dated February 4, 1987. 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 Pratt & Whitney, Publication Department, P.O. Box 611, Middletown, Connecticut 06457. Copies may be inspected at the Regional Rules Docket, Office of the Assistant Chief Counsel, Federal AviationAdministration, New England Region, 12 New England Executive Park, Room 311, Burlington, Massachusetts 01803, or at the Office of the Federal Register, 1100 L Street, N.W., Room 8301, Washington, DC. This amendment (39-6181, AD 89-10-07) becomes effective on May 30, 1989.
2006-02-51: The FAA is adopting a new airworthiness directive (AD) for certain Raytheon Aircraft Company Model 390 airplanes. This AD contains the same information as emergency AD 2006-02-51 and publishes the action in the Federal Register. This AD requires you to visually inspect the hydraulic tube assembly (P/N 390-580035-0001 or P/N 390- 580035-0005) and the clamp (P/N MS21919WCJ6 or P/N MS21919WCJ7) (or FAA-approved equivalent part numbers), as specified in the service information; replace the clamp at each inspection; replace the hydraulic tube assembly immediately if any of the problems identified in the service bulletin are found; and report the results of each inspection or replacement to the FAA. This AD results from failure of the hydraulic tube assembly, which caused in-flight loss of hydraulic fluid. We are issuing this AD to prevent failure of the hydraulic tube assembly and consequent leaking of hydraulic fluid. This failure could result in loss of hydraulic system functionsand risk of fire because of flammable fluid leakage in the engine nacelle and lead to loss of control of the airplane.
99-08-10: This amendment adopts a new airworthiness directive (AD) that is applicable to all Boeing Model 747-100, -200, -300, -SP, and -400F series airplanes. Among other things, this amendment requires repetitive leak tests of the lavatory drain system and repair, if necessary; installation of a cap or flush/fill line ball valve on the flush/fill line; periodic seal changes; and replacement of any "donut" type valves installed in the waste drain system. This amendment is prompted by continuing reports of damage to airframes and damage to property on the ground, caused by "blue ice" that forms from leaking lavatory drain systems on transport category airplanes and subsequently dislodges from the airplane fuselage. The actions specified by this AD are intended to prevent damage to airframes and property on the ground that is associated with the problems of "blue ice" that forms from leaking lavatory drain systems on transport category airplanes and subsequently dislodges from theairplane fuselage.
99-08-09: This amendment supersedes an existing airworthiness directive (AD), applicable to certain Aerospatiale Model ATR42-300 and -320 series airplanes, that currently requires a one-time inspection of the main landing gear (MLG) actuator fitting bolt holes for correct alignment, and rework of the fitting surface and bolt replacement, if necessary. This amendment requires replacement of the MLG actuator fitting bolts with new, improved bolts. This amendment also revises the applicability of the existing AD. 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 failure of the MLG actuator fitting bolts, which could result in the inability to retract the MLG and attain an adequate climb gradient.