Results
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.
79-25-03: 79-25-03 DETROIT DIESEL ALLISON: Amendment 39-3625. Applies to Model 501-D13, 501-D13A, 501-D13D, 501-D13E, and 501-D13H engines equipped with second, third, and fourth stage turbine wheels P/N's 6829072, 6847112, 6788833, 6842143, 6841223, 6846553, 6738424, and 6843014. Compliance required as follows unless previously accomplished: (a) For second stage turbine wheels, remove from service in accordance with FAA approved revision of 501-D13 CSL-235 dated December 13, 1979. (b) For third and fourth stage turbine wheels, remove from service in accordance with FAA approved revision of 501-D13 CSL-253 dated December 13, 1979. Detroit Diesel Allison Commercial Service Letters 501-D13 CSL-235, 501-D13 CSL-253, and Commercial Overhaul Information Letter 501-D13 COIL-349 revised as of December 13, 1979 are incorporated herein and made a part hereof pursuant to 5 U.S.C. 552(a)(1). The incorporated service documents may be obtained from Detroit Diesel Allison, Division ofGeneral Motors Corporation, Indianapolis, Indiana 46206. This amendment becomes effective on December 13, 1979.
64-04-05: 64-04-05 NAVION: Amdt. 684 Part 507 Federal Register February 11, 1964. Applies to All Navion D, E, F, and G Aircraft, Serial Numbers NAV-4-2 and up. Compliance required within 10 hours' time in service after the effective date of this AD and thereafter within every 100 hours'-time in service. (a) Visually inspect wing panel outboard of Wing Stations 130 (outboard edge of flap) for loose rivets. Replace loose rivets with the next larger size. Where this is impractical due to edge distance, interference, etc., install a protruding head rivet of the same diameter located between the loose rivet and the next adjacent rivet. (b) Install 4 AD 4 protruding head rivets both top and bottom skin equally spaced between the last 5 rivets in stringer No. 3. This is at the front tip tank attachment. (c) This inspection is no longer necessary if the skin with flush rivets is replaced with new skin of equivalent strength and protruding head rivets of the original size are used. Other modifications must be approved by a Regional FAA Engineering and Manufacturing Branch. (Navion Service Letter No. 85 covers this same subject.) This directive effective February 17, 1964.
2006-02-11: The FAA is adopting a new airworthiness directive (AD) for certain McDonnell Douglas transport category airplanes. This AD requires doing repetitive detailed inspections for accumulation of debris (blockage) in the drain holes of the pitot tubes, and cleaning the hole if any evidence of debris is found. This AD results from reports of blocked drain holes of the pitot tubes. We are issuing this AD to prevent blocked drain holes of the pitot tubes, which could result in the accumulation of water in the pitot-static system and consequent failure of that system. Failure of the pitot-static system could result in erroneous airspeed indications in the cockpit and consequent loss of airspeed control.
78-24-03: 78-24-03 SOCIETE NATIONALE INDUSTRIELLE AEROSPATIALE: Amendment 39- 3347. Applies to Model SA 330 Puma helicopters, certificated in all categories, that have accumulated less than 500 hours total time in service on their main gear boxes and have not incorporated Puma Modification AMS 07.51.103. Compliance required before further flight, unless already accomplished, but helicopter may be flown in accordance with FAR 21.197 and 21.199 to a base where the required work can be performed. To prevent failure of the main gear box input reduction gears due to excessive vibration, replace the main gear box with a gear box incorporating Puma Modification AMS 07.51.103 or accomplish the following: (a) Determine the acceleration spectral level of the input reduction gears in accordance with the accomplishment instructions of Puma SA 330 Service Bulletin No. 01.21, dated July 12, 1977, or an FAA-approved equivalent. (b) If the acceleration spectral level found during the test required by paragraph (a) of this AD measures 52db or more, replace the forward input reduction gears with gears incorporating Puma Modification AMS 07.51.103, or an FAA-approved equivalent. (c) If the acceleration spectral level found during the test required by paragraph (a) of this AD measures less than 52db, the input reduction gears may remain in service if the operator receives written information from Aerospatiale that a spectral analysis shows the gears to be acceptable. (d) Continue to comply with paragraphs (a) through (c) of this AD at intervals not to exceed 20 hours time in service until the gears have been replaced with gears incorporating Puma Modification AMS 07.51.103, or an FAA-approved equivalent. This amendment is effective November 24, 1978, as to all persons except those persons to whom it was made immediately effective by the telegram dated May 19, 1978, which contained this amendment.
99-08-01: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 747 series airplanes, that requires repetitive detailed visual inspections for corrosion, and repetitive high frequency eddy current (HFEC) inspections for cracks, of the upper link assembly on the number 2 and number 3 engine struts, and corrective actions, if necessary. This amendment is prompted by reports of corrosion and cracks located at the four fasteners that attach to the aft end to the upper link assembly on the number 2 and number 3 engine struts. The actions specified by this AD are intended to prevent failure of the upper link due to cracking or corrosion, subsequent damage to other strut support structure, and in-flight separation of an engine from the airplane.
79-19-13: 79-19-13 CESSNA: Amendment 39-3578 as amended by Amendment 39-3651. Applies to Model 441 (Serial Numbers 441-0001 through 441-0106 and 441-0109) airplanes certificated in all categories. COMPLIANCE: Required as indicated unless already accomplished in accordance with (1) Cessna Propjet Service Information Letter Number PJ79-15, Revision #1 and information applicable thereto on the errata sheet dated October 17, 1979, issued by Cessna, (2) Cessna Service Kit Instructions Number SK441-27 dated September 18, 1979, and information applicable thereto on the errata sheets, dated October 5, 17, 22 and November 5, 1979, issued by Cessna, and (3) applicable dispositions approved by Cessna and issued on Conquest Return to Service (RTS) call report forms. To preclude failure of the elevator trim tab actuator jack screws, accomplish the following: A) At least 24 hours prior to initiating compliance with this AD, each owner/operator shall contact his local FAA GADO/FSDO/EMDO (whichever is applicable) and advise them of the following: 1. Registration number and serial number of each of their Cessna Model 441 airplanes, and 2. When and where each of the airplanes is to have this AD accomplished. NOTE: GADO stands for General Aviation District Office FSDO stands for Flight Standards District Office EMDO stands for Engineering and Manufacturing District Office B) Prior to the next flight install, (1) a new horizontal stabilizer assembly, left and right elevator assemblies, elevator trim tab control system and, (2) inspect and modify or, if necessary, replace the tailcone shelf assembly, all in accordance with Cessna Propjet Service Information Letter Number PJ79-15, Revision #2, Cessna Service Kit Instructions Number SK441-27A, dated November 14, 1979, and any applicable dispositions approved by Cessna and issued on Conquest Return to Service (RTS) call report forms. NOTE: Cessna has issued errata sheets dated November 20, 1979, which includes some general information items and several items showing special modification procedures to be used if certain problems occur during compliance with Paragraph B) of this AD. The November 20, 1979 errata sheets may not be used as the approval document for any modifications necessary to correct the subject problems. Such approval will be dispositioned by Cessna on Conquest Return to Service (RTS) call report forms issued for the specific airplane involved. C) Prior to approving the airplane for return to service, revise airplane weight and balance report to reflect the change in weight, moment and center of gravity location, as outlined in Federal Aviation Regulations (FAR) 43.5 and 91.31, resulting from these modifications. D) An appropriately rated Repair Station or the Authorized Inspector who inspected the work must make an entry in the airplane maintenance records, that are to be transferred with the airplane, showing that this AD has been complied with and approving the airplane for return to service. E) Prior to carrying any person in the airplane other than a crew member, perform a flight check of the airplane in accordance with FAR 91.167 and instructions in Cessna Propjet Service Information Letter Number PJ79-15, Revision #2. F) Return to Cessna and/or destroy components removed from the airplane during compliance with this AD in accordance with instructions in Cessna Propjet Service Information Letter PJ79-15, Revision #2. G) Any equivalent method of compliance with this AD must be approved by the Chief, Engineering and Manufacturing Branch, FAA, Central Region. Amendment 39-3578 became effective September 19, 1979. This Amendment 39-3651 becomes effective December 26, 1979.
2019-19-01: The FAA is adopting a new airworthiness directive (AD) for all Airbus SAS Model A320-251N and -271N airplanes, and Model A321-251N, - 253N, -271N, and -272N airplanes. This AD was prompted by reports that the regulated bleed temperature was measured above the design target with a temperature regulation shift phenomenon, and investigation results show that incorrect temperature regulation can degrade pneumatic system components located downstream of the pre-cooler. This AD requires uploading improved bleed monitoring computer (BMC) software (SW), 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.
2006-03-01: The FAA is adopting a new airworthiness directive (AD) for all Empresa Brasileira de Aeronautica S.A. (EMBRAER) Model ERJ 170 airplanes. This AD requires, when certain SmartProbes are installed, revising the Limitations section of the airplane flight manual to limit the maximum take-off weight of the airplane and increase the reference speed during certain landing conditions. This AD results from reports of variable calibration values of certain sensors of the SmartProbes, which could result in the transmission of erroneous information to the air data system. We are issuing this AD to prevent reduced controllability of the airplane.
2019-21-04: The FAA is adopting a new airworthiness directive (AD) for certain Saab AB, Saab Aeronautics Model SAAB 2000 airplanes. This AD was prompted by reports of loose and irregular fasteners at the forward end of the nacelle upper longeron, where the bulkhead frame and struts are attached to the engine mounting structure (EMS). This AD requires modification of the EMS and structural attachments. The FAA is issuing this AD to address the unsafe condition on these products.
2019-21-12: The FAA is adopting a new airworthiness directive (AD) for certain BRP-Rotax GmbH & Co KG (Rotax) 914 F2, 914 F3, and 914 F4 model engines. This AD requires removal of a certain exhaust valve and its replacement with a part eligible for installation. This AD was prompted by a report of a broken exhaust valve installed on a Rotax 914 model engine. The FAA is issuing this AD to address the unsafe condition on these products.
2019-21-02: The FAA is adopting a new airworthiness directive (AD) for all Airbus SAS Model A330-200, -200F, and -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.
2006-02-09: The FAA is adopting a new airworthiness directive (AD) for all Airbus Model Airbus Model A330-200, A330-300, A340-200, and A340-300 series airplanes. This AD requires inspecting for damage to certain actuators of the low-pressure shut-off valve (LPSOV), and related investigative and corrective actions if necessary. This AD results from a report of damage to the LPSOV pedestal. We are issuing this AD to ensure that, in the event of an engine fire, the LPSOV actuator functions properly to delay or block the fuel flow to the engine and prevent an uncontrollable fire.
78-23-03: 78-23-03 SOCIETE NATIONALE INDUSTRIELLE AEROSPATIALE (SNIAS): Amendment 39-3337. Applies to Model SA 316C and 319 Alouette III helicopters, certificated in all categories, that do not incorporate SNIAS Modification AMS 07.2109 (covered in Service Bulletin No. 65.108). Compliance is required as indicated, unless already accomplished. To prevent a possible loss of helicopter control, accomplish the following: (a) Within the next 50 hours time in service after the effective date of this AD, and, thereafter, at intervals not to exceed 50 hours time in service since the previous inspection, inspect the left-hand and right-hand upper flight control bellcrack support attachment fittings, P/Ns 319A.84.10.118 and 319A.84.10.119, in accordance with Alouette SA316C and 319 Service Bulletin No. 05.57, dated September 29, 1975, or an FAA-approved equivalent (hereinafter referred to as Service Bulletin). (b) If a crack is found during an inspection required by paragraph (a)of this AD, replace the affected part with a new fitting, P/N 319A.84.10.120 or 319A.84.10.121, as appropriate, in accordance with the Service Bulletin before further flight, except that the helicopter may be flown in accordance with FAR 21.197 and 21.199 to a base where the work can be performed. (c) The inspections required by paragraph (a) of this AD may be discontinued upon the installation of new fittings, P/Ns 319A.84.10.120 and 319A.84.10.121, in accordance with the Service Bulletin. This amendment becomes effective December 4, 1978.
80-06-02: 80-06-02 GATES LEARJET: Amendment 39-3715. Applies to Models 35 (Serial Numbers 35-001 thru 35-066); 36 (Serial Numbers 36-001 thru 36-017); 35A (Serial Numbers 35-067 thru 35-288); and 36A (Serial Numbers 36-018 thru 36-044) airplanes. COMPLIANCE: Required as indicated, unless previously accomplished. To preclude takeoff, or continued flight after a starter assist air start, with an unannunciated failure in the electrical system, accomplish the following: A) Within the next 10 hours time-in-service after the effective date of this AD, insert the following information in the FAA Approved Airplane Flight Manual and operate the airplane in accordance with these insertions: 1) In Section 1, LIMITATIONS, add the following: ELECTRICAL SYSTEM The battery charging bus current limiter and starter disengagement checks, as outlined in STARTING ENGINES, STARTER ASSIST AIRSTART, and/or BEFORE TAKEOFF procedures in Sections II and III of this manual, must be accomplished whenever an engine start using a starter has been performed. These checks require that both engines be operating to perform the check. 2) In Section 2, NORMAL OPERATING PROCEDURES, under the heading STARTING ENGINES, add the following: (a) Starter Disengagement Check - After both engines are started, perform check as follows: 1. Air Conditioner and Auxiliary Heater - OFF. 2. Both Battery Switches - OFF. 3. Ammeters - Check total current indication less than 100 amps. 4. If total current indication is greater than 100 amps, shut down engines. NOTE: A total ammeter indication greater than 100 amps indicates that a starter has not disengaged. Subsequent starter and/or engine damage may occur. If total current indication is less than 100 amps, set both Battery Switches ON. (b) Battery Charging Bus Current Limiter Check (Serials 35-001 thru 35-147 and 36-001 thru 36-035): 1. Pull MAIN DC BUS TIE circuit breaker. 2. One Generator Switch - OFF. Check ammeter reading on opposite generator, approximately doubles, then switch back to GEN. 3. Opposite Generator Switch - OFF. Check ammeter reading on opposite generator, approximately doubles, then switch back to GEN. 4. Reset MAIN DC BUS TIE circuit breaker. CAUTION: Failure to meet the above check indicates a malfunction. Replace 275A Current Limiter prior to takeoff. Loss of 275A Current Limiters can lead to loss of essential DC power. Battery Charging Bus Current Limiter Check (Serials 35-148 thru 35-288 and 36-036 thru 36-044): 1. Test Switch - L CUR LIM. 2. Test Button - Press. Green current limiter light will illuminate and remain on while button is held. The light indicates continuity through the left current limiter. Also the L GEN light will come on and the right generator voltage may be reduced by approximately 2 VDC. 3. Test switch - R CUR LIM. 4. Test Button - Press. Green current limiter light will illuminate and remain on while button is held. The light indicates continuity through the right Current Limiter. Also the R GEN light will come on and the left generator voltage may be reduced by approximately 2 VDC. CAUTION: Failure of light to remain illuminated indicates a malfunction. Replace 275A Current Limiter prior to takeoff. Loss of 275A Current Limiters can lead to loss of essential DC power. 3) In Section 3, EMERGENCY PROCEDURES, under the headings, ENGINE FAILURE DURING CRUISE and OPERATIONS WITH ONE FUEL COMPUTER INOPERATIVE, add the following after all starter assist engine starts: (a) Starter Disengagement Check 1. Air Conditioner and Auxiliary Heater - OFF. 2. Both Battery Switches - OFF. 3. Ammeter - Check total current indication less than 100 amps. 4. If total current indication is greater than 100 amps: a. Both Battery Switches - ON. b. and as soon as practical. c. Do not attempt further flights until trouble has been corrected. NOTE: A total ammeter indication greater than 100 amps indicates that a starter has not disengaged and subsequent starter and/or engine damage may occur. If total current indication is less than 100 amps, set both Battery Switches ON. (b) Battery Charging Bus Current Limiter Check (Serials 35-001 thru 35-147 and 36-001 thru 36-035): 1. Pull MAIN DC BUS TIE circuit breaker. 2. One Generator Switch - OFF. Check ammeter reading on opposite generator, approximately doubles, then switch back to GEN. 3. Opposite Generator Switch - OFF. Check ammeter readings on opposite generator, approximately doubles, then switch back to GEN. 4. Reset MAIN DC BUS TIE circuit breaker. CAUTION: Failure to meet the above check indicates a malfunction. Loss of both 275A Current Limiters can lead to loss of essential DC power. Battery Charging Bus Current Limiter Check (Serials 35-148 thru 35-288 and 36-036 thru 36-044): 1. Test Switch - L CUR LIM. 2. Test Button - Press. Green current limiter light will illuminate and remain on while button is held. The light indicates continuity through the left current limiter. Also the L GEN light will come on and the right generator voltage may be reduced by approximately 2 VDC. 3. Test Switch - R CUR LIM. 4. Test Button - Press. Green current limiter light will illuminate and remain on while button is held. The light indicates continuity through the right current limiter. Also the R GEN light will come on and the left generator voltage may be reduced by approximately 2 VDC. CAUTION: Failure of light to remain illuminated indicates a malfunction. Loss of both 275A Current Limiters can lead to loss of essential DC power. B) Use Paragraph A of this AD, or a duplicate thereof, as an amendment to the FAA Approved Airplane Flight Manual until replaced by Change 9 or 10 to Gates Learjet 35/36 or 35A/36A FAA Approved Airplane Flight Manual, as applicable, both FAA approved February 15, 1980. C) This AD may be accomplished by the holder of a pilot certificate issued under Part 61 of the Federal Aviation Regulations on any airplane owned or operated by that person, who must make an entry in the airplane maintenance records indicating prescribed compliance with this AD. D) Any equivalent method of compliance with this Airworthiness Directive must be approved by the Chief, Wichita Engineering and Manufacturing District Office, Federal Aviation Administration, Room 238, Terminal Building No. 2299, Mid-Continent Airport, Wichita, Kansas 67209. This amendment becomes effective March 24, 1980.
64-11-03: 64-11-03 LOCKHEED: Amdt. 729 Part 507 Federal Register May 15, 1964. Applies to All Models 188A and 188C Series Aircraft. Compliance required as indicated. Cracks have been detected in the upper wing planks on both the inboard and outboard sides of the nacelle where the inboard nacelle skate angles attach to the wing planks. As a result of these cracks, accomplish the following: (a) Within the next 450 hours' time in service after the effective date of this AD, and thereafter at intervals not to exceed 450 hours' time in service, externally inspect the wing planks in accordance with Section 2.A. of Lockheed Service Bulletin 88/SB-600 or FAA approved equivalent. The external inspections may be discontinued when the internal inspection program prescribed by (b) is initiated. (b) Within the next 900 hours' time in service after the effective date of this AD, unless accomplished within 2,100 hours' time in service prior to the effective date of this AD, and thereafter atintervals not to exceed 3,000 hours' time in service, internally inspect the wing planks by X-ray or visual means in accordance with Section 2.B. of Lockheed Service Bulletin 88/SB-600 or FAA approved equivalent. (c) Any cracks found during the accomplishment of (a) or (b) shall be repaired before further flight (except that the aircraft may be ferried in accordance with the provisions of CAR 1.76 to the base at which the repairs are to be accomplished) in accordance with the Lockheed Electra Structural Repair Manual, Section 57-2-1, or an equivalent approved by the Chief, Aircraft Engineering Division, FAA Western Region. (d) The repetitive inspections of (b) may be discontinued for those aircraft which exhibit no signs of cracks 6,000 hours' time in service after the initial internal inspection is accomplished. (e) For aircraft on which cracks are detected and repaired in accordance with (c), the repetitive inspections of (b) may be discontinued if no cracks are detected6,000 hours' time in service after the repair is accomplished. (f) Upon request of the operator, an FAA maintenance inspector, subject to prior approval of the Chief, Aircraft Engineering Division, FAA Western 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 such operator. (Lockheed Alert Bulletin 88/SB-600 dated June 24, 1963, covers this same subject.) This directive effective June 15, 1964.
2006-02-03: The FAA is adopting a new airworthiness directive (AD) for certain Raytheon Model Hawker 800XP airplanes. This AD requires inspecting to determine if the correct fuse is installed on the hydraulic over-temperature switch on panel ZK in the rear equipment bay, and replacing the existing fuse if necessary. This AD results from a report of the installation of an incorrect fuse on the over- temperature switch on panel ZK in the rear equipment bay during airplane maintenance. We are issuing this AD to prevent a short circuit in the fuse and consequent heat damage to associated wiring and surrounding equipment, which could result in smoke or fire on the airplane.
2008-18-03: We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) originated 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: During manufacturing of A330/A340 aircraft framework, cracks have been found on Frame (FR) 12, left (LH) and right (RH) sides. It has been confirmed that a defect of the FR12 forming tool press is the root cause of the cracks. If undetected such damage could affect, after propagation, the structural integrity of the aircraft. * * * * * * * We are issuing this AD to require actions to correct the unsafe condition on these products.
81-02-08: 81-02-08 LOCKHEED-CALIFORNIA: Amendment 39-4023. Applies to all Model L-1011 series airplanes certificated in all categories. Compliance required within 300 hours time-in-service after the effective date of this AD. To assure availability of emergency passenger oxygen, accomplish the following: A. Replace all one-man fixed chemical oxygen generators, Scott Aviation P/N 801462-01 with Scott Aviation P/N 801462-04 oxygen generators, in accordance with a method approved by the Chief, Los Angeles Area Aircraft Certification Office. (NOTE: Accomplishment of Lockheed Service Bulletin 093-35-030, dated September 15, 1980, has been approved as a means of compliance with this requirement.) B. Alternative means of compliance or other actions which provide an equivalent level of safety may be used when approved by the Chief, Los Angeles Area Aircraft Certification Office, FAA Northwest Region. C. Special flight permits may be issued in accordance with FAR 21.197 and 21.199to operate airplanes to a base in order to comply with the requirements of this AD. This amendment becomes effective January 27, 1981.
81-20-04 R1: 81-20-04 R1 BOEING: Amendment 39-4225 as amended by Amendment 39-4250. Applies to Boeing Model 727-200 series and 737 airplanes, certificated in all categories, using the following Hamilton Standard electronic pressurization controllers that have not been previously modified to HS reference number P57: \n\n\nHS Part Number\nBoeing Part Number \n710204-7\n10-61209-13 \n710204-8\n10-61209-14 \n761260-7\n10-61209-19 \n761260-8\n10-61209-18 \n\n\tTo prevent inflight fires, on or before May 12, 1982, accomplish the following, unless already accomplished: Modify the Hamilton Standard pressurization controllers listed above in accordance with Boeing Service Bulletins 727-21 A96 and 737-21 A1064, published August 28, 1981, or later FAA approved revision, or in a manner approved by the Chief, Seattle Area Aircraft Certification Office. \n\tThe Assurance of Serviceability testing described in Paragraph B(16) of Hamilton Standard Service Bulletin 21-88, Revision 1, dated October 13, 1981, may be used in lieu of the complete functional test specified in the Boeing Service Bulletins listed above.\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). All 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 also be examined at FAA Northwest Region, 9010 East Marginal Way South, Seattle, Washington 98108. \n\n\tAmendment 39-4225 became effective October 13, 1981. \n\tThis amendment 39-4250 becomes effective November 13, 1981.
2006-02-05: The FAA is adopting a new airworthiness directive (AD) for certain Bombardier Model CL-600-2B19 (Regional Jet Series 100 & 440) airplanes. This AD requires replacing the Camloc fasteners on the sidewall of the center pedestal. This AD results from reports of the Camloc fasteners on the sidewall of the center pedestal disengaging and interfering with an inboard rudder pedal. We are issuing this AD to prevent these fasteners from disengaging and interfering with an inboard rudder pedal, which could reduce directional controllability of the airplane.
2002-26-10: This amendment supersedes an existing airworthiness directive (AD), applicable to certain McDonnell Douglas DC-9-10, -20, -30, -40, and -50 series airplanes, that currently requires a one-time visual inspection to determine the modification status of the corners of the forward lower cargo doorjamb; low-frequency eddy current or X-ray inspections to detect cracks of the fuselage skin and doubler at all corners of the forward lower cargo doorjamb; various follow-on repetitive inspections; and modification, if necessary. This amendment retains those requirements but requires certain high-frequency, rather than low-frequency, eddy current inspections for certain conditions. The actions specified by this AD are intended to detect and correct cracking, which could result in rapid decompression of the fuselage and consequent reduced structural integrity of the airplane. This action is intended to address the identified unsafe condition.
64-02-06 R1: 64-02-06 R1 SIKORSKY AIRCRAFT: Amendment 674 as amended by Amendment 39-6090. Applies to all Sikorsky Model S-58 series helicopters. Compliance is required as indicated unless already accomplished. Fatigue cracks have been found in the area of the rear three bolt holes of upper pylon folding hinge fitting P/N S1620-63130-2, the forward bolt holes of mating fitting P/N S1620-64127, the forward bolt hole of the lower pylon hinge fitting P/N S1620-64131, and the lug through which the hinge bolt passes of fittings P/N's S1620-64127 and S1620-64127-7. In order to preclude propagation of fatigue cracks in these areas and subsequent serious weakening of the pylon attachment, accomplish the following: (a) As of the effective date of this AD, conduct daily visual inspections of the area around the fitting bolt holes of all pylon and tail cone folding hinge fittings for cracks. Replace any cracked fittings before further flight. (b) Unless already accomplished, accomplish the following in accordance with Sikorsky Service Bulletin No. 58B20-11A within 100 hours' time in service after the effective date of this AD on all upper pylon hinge fittings P/N S1620-64127 with 1,900 hours' or more time in service, or prior to the accumulation of 2,000 hours' time in service on all fittings having less than 1,900 hours' time in service as of the effective date of this AD: (1) Remove all bushings from the hinges. (2) Rework and inspect the bore of each hole. (3) Install oversized replacement bushings P/N S1620-63129-7. (c) Upon request, an alternate means of compliance which provides an equivalent level of safety with the requirements of this AD may be used when approved by the Manager, Rotorcraft Standards Staff, Rotorcraft Directorate, Aircraft Certification Service, ASW-110, FAA, Fort Worth, Texas 76193-0110. (d) In accordance with Sections 21.197 and 21.199, the helicopter may be flown to a base where compliance may be accomplished. Airworthiness Directive 63-09-02 was superseded by AD 64-02-06 (Amendment 674; 29 FR 559; January 21, 1964) which was effective January 31, 1964. This amendment (39-6090, AD 64-02-06 R1) revises AD 64-02-06 and becomes effective December 27, 1988.
2001-08-14 R1: The FAA is revising an existing airworthiness directive (AD) for Turbomeca S.A. Arrius Models 2B, 2B1, and 2F turboshaft engines. That AD currently requires replacing the right injector half manifold, left injector half manifold, and privilege injector pipe. This AD requires the same actions, but relaxes the compliance time for the repetitive replacements on Arrius 2F engines. This AD results from Turbomeca relaxing the repetitive replacement interval for Arrius 2F engine fuel nozzles based on review of returned fuel nozzles to Turbomeca. We are issuing this AD to prevent engine flameout during rapid deceleration, or the inability to maintain the 2.5 minutes one engine inoperative (OEI) rating, and to prevent air path cracks due to blockage of the fuel injection manifolds.