Results
85-15-51: 85-15-51 GENERAL ELECTRIC COMPANY: Amendment 39-5180. Applies to General Electric CF6- 80A/A2 model turbofan engines. Compliance is required as indicated unless already accomplished. To prevent rupture of the fuel manifold supply tube which could lead to a rejected takeoff, accomplish the following: (a) Remove from service fuel manifold supply tube, GE P/N 9327M46G01 or G02, with 2,500 or more total cycles within the next 100 operating cycles. (b) Remove from service fuel manifold supply tube, GE P/N 9327M46G01 or G02, with less than 2,500 total cycles, prior to accumulating 2,500 total cycles, or within the next 100 operating cycles, whichever occurs later. (c) Replace fuel manifold supply tube, GE P/N 9327M46G01 or G02, removed in accordance with (a) or (b) above, with a serviceable part. NOTE: This AD establishes a life limit of 2,500 cycles for fuel manifold supply tube, GE P/N 9327M46G01 or G02. Aircraft may be ferried in accordance with the provisions of FAR 21.197 and 21.199 to a base where the AD can be accomplished. Upon request, an equivalent means of compliance with the requirements of this AD may be approved by the Manager, Engine Certification Office, ANE-140, 12 New England Executive Park, Burlington, Massachusetts 01803, telephone (617) 273-7080. Upon submission of substantiating data by an owner or operator through an FAA maintenance inspector, the Manager, Engine Certification Office, New England Region, may adjust the compliance time specified in this AD. This amendment becomes effective December 23, 1985, to all persons except those persons to whom it was made immediately effective by T85-15-51 issued July 26, 1985, which contained this amendment.
72-02-06: 72-02-06 MITCHELL INDUSTRIES, INC., doing business as EDO-AIRE MITCHELL: Amdt. 39-1383. Applies to Mitchell automatic pilot instruments installed in various Cessna aircraft in accordance with the following Supplemental Type Certificates: AUTOPILOT MODEL STC NUMBER AIRCRAFT MAKE AND MODE AK086 SA20SW Cessna 210B and C AK086R SA20SW Cessna 210B and C AK086E SA20SW Cessna 210B and C AK088 SA27SW Cessna 182E and F AK088R SA27SW Cessna 182E and F AK088E SA27SW Cessna 182E and F AK110 SA101SW Cessna 182E, F and G AK110E SA101SW Cessna 182E, F and G AK110E-3 SA101SW Cessna 182E, F and G AK112 SA89SW Cessna 210B and C AK120 SA149SW (Cessna 210-5, 210-5A,) AK120E SA149SW ( 206, P206, ) AK120E-3 SA149SW ( and U206, ) AK126 SA330SW Cessna 210D and E AK126E SA330SW Cessna 210D and E AK126E-3 SA330SW Cessna 210D and E AK154 SA489SW Cessna 182H AK154E SA489SW Cessna 182H AK154E-3 SA489SW Cessna 182HAK155 SA491SW Cessna 337 AK155E SA491SW Cessna 337 AK155E-3 SA491SW Cessna 337 Compliance required within the next ten (10) hours' time in service after the effective date of this AD, unless already accomplished. To prevent fatigue failure of the control wheel shaft with possible resultant loss of aileron and elevator control, accomplish the following: Remove the Mitchell automatic pilot instrument servo, inspect the control wheel shaft, take corrective action as necessary, and reassemble in accordance with Edo-Aire Mitchell Service Bulletin No. MB-6 dated October 29, 1971, or later FAA approved revision, or any other method approved by the Chief, Engineering and Manufacturing Branch, Southwest Region, Federal Aviation Administration, Fort Worth, Texas. NOTE: The Mitchell automatic pilot instrument servo may be reinstalled in accordance with Edo-Aire Mitchell Service Letter ML-32 dated December 22, 1971, or later FAA approved revision, or any other methodapproved by the Chief, Engineering and Manufacturing Branch, Southwest Region, Federal Aviation Administration, Fort Worth, Texas. The bulletin and letter mentioned herein may be obtained from Edo-Aire Mitchell, P. O. Box 610, Mineral Wells, Texas 76067. This amendment becomes effective January 31, 1972.
2004-03-26: This amendment adopts a new airworthiness directive (AD), applicable to certain Dassault Model Falcon 900EX series airplanes, that requires modification of the front attachment area of the No. 2 engine. This action is necessary to prevent failure of the fail-safe lugs of the hoisting plate of the forward engine mount, and subsequent cracking of the pick-up folded sheet of the pylon forward rib. Such cracking could rupture the mast case box, which could result in loss of the two forward engine mounts and consequent separation of the engine from the airplane. This action is intended to address the identified unsafe condition.
75-04-05: 75-04-05 ROCKWELL INTERNATIONAL: Amendment 39-2087. Applies to all NA- 265 Series Airplanes certificated in all categories. Compliance as indicated, unless already accomplished. To provide protection in the event of an unknown incipient failure condition in the engine fuel pressure switch, Hydra-Electric Co. P/N 12251, accomplish the following: (a) Within 10 hours' time in service after the effective date of this AD, inspect the engine fuel pressure switches for fuel seepage or leakage. (1) If seepage or leakage is found, replace the failed switch before further flight, in accordance with Sabreliner Service Bulletin 74-34, dated January 15, 1975, revised January 24, 1975, or later FAA-approved revisions. (2) If seepage or leakage is not found, repeat the inspection at intervals not to exceed 10 hours' time in service until the inspection and installation described in (b) are accomplished. (b) Within 90 days after the effective date of this AD, conductan inspection to determine the part number of the engine fuel pressure switch installed in accordance with steps 1 through 3 of Sabreliner Service Bulletin 74-34, dated January 15, 1975, revised January 24, 1975, or later FAA-approved revisions. (1) If Hydra-Electric Co. P/N 12251 is found installed, either (i) Accomplish the installation described in steps 4 through 10 of Sabreliner Service Bulletin 74-34, dated January 15, 1975, revised January 24, 1975, or later FAA-approved revisions, prior to further flight; or (ii) Repeat (a) above, until the installation described in (b)(1)(i) is accomplished. The installation required by (b)(1)(i) is to be performed within 90 days after the effective date of this AD. (c) If P/N 1B2522-25 (Aero Instruments Co., or Century Electronics and Instrument Inc., or Hathaway Industries, or Electro Controls Inc.), or P/N 685-1, Value Engineering Products, is installed, proceed with steps 8 through 10 of Sabreliner Service Bulletin74-34, dated January 15, 1975, revised January 24, 1975, or later FAA-approved revisions. (d) Airplanes may be flown to a base for the performance of the inspections and installations required by this AD, per FAR's 21.197 and 21.199, except when seepage or leakage is known to exist. (e) Return P/N 12251 switches removed from service to Rockwell International, Aviation Services Division, Lambert Field, St. Louis, Mo. 63145. (f) Equivalent inspections and installations may be approved by the Chief, Aircraft Engineering Division, FAA Western Region, upon submission of adequate substantiating data. This amendment becomes effective February 18, 1975.
2016-15-06: We are adopting a new airworthiness directive (AD) for certain Bombardier, Inc. Model BD-700-1A10 and BD-700-1A11 airplanes. This AD was prompted by a design review, which found that the burst pressure of the flexible hose used to vent oxygen from the high-pressure relief valve of the oxygen cylinder overboard is lower than the opening pressure of the high-pressure relief valve. This AD requires replacement of flexible relief hoses for the crew oxygen bottles with new metal design relief hoses. We are issuing this AD to prevent the accumulation of excess oxygen in an enclosed space, which could, if near a source of ignition, cause an uncontrolled oxygen-fed fire.
70-26-05: 70-26-05 PRATT & WHITNEY AIRCRAFT: Amdt. 39-1131. Applies to all model JT8D series turbofan engines. Compliance required as indicated. To prevent failure of the first stage compressor rotor blades as the result of improperly machined blade roots, accomplish the following: (a) Within the next 900 hours in service after the effective date of this AD, unless already accomplished, visually inspect all P/N 487801, 511901 change letter L or earlier, 594601 and 616601 change letter B or earlier first stage compressor rotor blades, for tool marks within the radius of the Z plane platform on both sides of the blade root area. If tool marks are observed, replace the blade. (b) Upon submission of substantiating data through an FAA Maintenance Inspector by an owner or operator to the Chief, Engineering and Manufacturing Branch, FAA Eastern Region, compliance time may be adjusted. (Pratt & Whitney letter PSE:HHB:0-4-6-1-33 dated April 6, 1970, pertains to this subject.) This amendment is effective December 29, 1970.
81-10-05: 81-10-05 McDONNELL DOUGLAS: Amendment 39-4104. Applies to McDonnell Douglas Model DC-10 series airplanes, fuselage numbers 1 through 98, except fuselage number 2, certificated in all categories. See McDonnell Douglas Service Bulletin identified below for the applicable aircraft serial numbers. Compliance is required as indicated, unless already accomplished. \n\n\tTo prevent electrical arcing and burning in the electrical connector in the Hydro-Aire fuel pump housing, accomplish the following: \n\n\t(a)\tWithin 300 hours' additional time in service after the effective date of this AD, replace the electrical connectors in the fuel boost/transfer pump housings in those fuel tanks specified, in accordance with paragraph 2, Accomplishment Instructions, McDonnell Douglas Service Bulletin, DC-10 SB 28-17, Revision 2, dated July 27, 1973. \n\n\t(b)\tSpecial flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base for the accomplishment of modifications required by this AD. \n\n\t(c)\tAlternative modifications 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. \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 these documents from the manufacturer may obtain copies upon request to the McDonnell Douglas Corporation, 3855 Lakewood Boulevard, Long Beach, California 90846, Attention: Director, Publications and Training, C1-750 (54-60). These documents also may be examined at FAA Northwest Region, 9010 East Marginal Way South, Seattle, Washington 98108, or 15000 Aviation Boulevard, Hawthorne, California 90261, Room 6W14. \n\n\tThis amendment becomes effective July 22, 1981.
2004-03-04: This amendment adopts a new airworthiness directive (AD), applicable to all BAE Systems (Operations) Limited (Jetstream) Model 4101 airplanes. This AD requires repetitive inspections for cracking in the casing of the nose landing gear (NLG), and corrective action if necessary. This action is necessary to find and fix cracking of the NLG casing, which could result in failure of the NLG, and consequent reduced controllability of the airplane during takeoff and landing. This action is intended to address the identified unsafe condition.
2002-09-03: This amendment adopts a new airworthiness directive (AD) for Eurocopter France (ECF) Model AS332L2 helicopters. This action requires, before further flight, verifying that the air vent is installed on the inflation cylinder of each life raft assembly. If the air vent is missing, this AD also requires replacing the cylinder head with an airworthy part before further flight. This amendment is prompted by the discovery that an inflation cylinder in the life raft did not have an air vent installed. This condition, if not corrected, could result in inadvertent life raft inflation, loss of the life raft, contact with the main or tail rotor, and subsequent loss of control of the helicopter.
81-16-04: 81-16-04 BELLANCA AIRCRAFT CORPORATION: Amendment 39-4172. Applies to Models 8KCAB, 7ECA, 7GCAA, 7GCBC and 7KCAB airplanes certificated in Acrobatic category. \n\n\tTo insure that the competition harness (also referred to as the ACRO harness) is installed properly, accomplish the following before further flight: \n\n\t1.\tUnless previously accomplished, insert figure I of this AD into all applicable aircraft having approved flight manuals. \n\n\t2.\tAttach figure I of this AD to all "Operating Limitation Instructions" (yellow card) for those applicable aircraft where a flight manual is not required (Model 7 Series airplanes). \n\n\t3.\tInspect all competition harness installations to insure that the shoulder straps are installed in accordance with figure I of this AD. Insure that the shoulder straps of the added harness pass on the forward side of the seat back. \n\n\tThis amendment becomes effective July 28, 1981.
2016-15-07: We are adopting a new airworthiness directive (AD) for certain Bombardier, Inc. Model CL-600-2C10 (Regional Jet Series 700, 701, & 702), Model CL-600-2D15 (Regional Jet Series 705), Model CL-600-2D24 (Regional Jet Series 900), and Model CL-600-2E25 (Regional Jet Series 1000) airplanes. This AD was prompted by reports of corrosion found on the slat and flap torque tubes in the slat and flap control system. This AD requires replacement of the slat and flap torque tubes in the slat and flap control system. We are issuing this AD to prevent rupture of a corroded slat or flap torque tube. This condition could result in an inoperative slat or flap system and consequent reduced controllability of the airplane.
2016-15-04: We are adopting a new airworthiness directive (AD) for all The Boeing Company Model 757-200 and -200CB series airplanes. This AD was prompted by an evaluation by the design approval holder (DAH) indicating that the lap splices at stringer S-14R, lower fastener row, are subject to widespread fatigue damage (WFD). This AD requires external dual frequency eddy current (DFEC) or internal high frequency eddy current (HFEC) inspections of the lap splice, inner skin \n\n((Page 49874)) \n\nfasteners, at stringer S-14R, station (STA) 440 through STA 540, and corrective action if necessary. We are issuing this AD to detect and correct cracking of the fuselage skin lap splice. Such cracking could result in reduced structural integrity of the airplane.
2001-22-07: This amendment adopts a new airworthiness directive (AD), that is applicable to certain Honeywell International, Inc. (formerly AlliedSignal, Inc. and Textron Lycoming) LTP 101 series turboprop and LTS101 series turboshaft engines. This amendment requires a new life limitation and removal of rigid tube fuel manifold assemblies and replacement with serviceable assemblies. This amendment is prompted by reports of cracking and fuel leakage of rigid tube fuel manifolds. The actions specified by this AD are intended to prevent engine fuel leakage due to low-cycle fatigue (LCF) cracking of the rigid tube fuel manifold, which could result in an in-flight fire.
2009-04-17: The FAA is adopting a new airworthiness directive (AD) for General Electric Company (GE) CF6-45 and CF6-50 series turbofan engines. This AD requires replacing certain forward and aft centerbodies of the long fixed core exhaust nozzle (LFCEN) assembly. This AD results from the engine manufacturer issuing new service information. We are issuing this AD to prevent the forward and aft centerbody of the LFCEN assembly from separating due to high imbalance engine conditions, leading to damage to the airplane.
2004-03-11: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 747-200C and -200F series airplanes, that requires repetitive inspections to find fatigue cracking in the upper chord of the upper deck floor beams, and repair if necessary. For certain airplanes, this amendment also provides an optional repair/ modification, which extends certain repetitive inspection intervals. This action is necessary to find and fix cracking in certain upper deck floor beams. Such cracking could extend and sever floor beams at a floor panel attachment hole location and could result in rapid decompression and consequent loss of controllability of the airplane. This action is intended to address the identified unsafe condition.
2016-15-01: We are adopting a new airworthiness directive (AD) for all Airbus Model A300 series airplanes; Model A300 B4-600, B4-600R, F4-600R series airplanes, and Model A300 C4-605R Variant F airplanes (collectively called Model A300-600 series airplanes); and Model A310 series airplanes. This AD was prompted by reports of partial loss of no-back brake (NBB) efficiency on the trimmable horizontal stabilizer actuator (THSA). This AD requires an inspection to determine THSA part numbers, serial numbers, and flight cycles on certain THSAs; and repetitive replacement of certain THSAs. We are issuing this AD to prevent loss of THSA NBB efficiency, which, in conjunction with the inability of the power gear to keep the ball screw in its last commanded position, could lead to an uncommanded movement of the horizontal stabilizer, possibly resulting in loss of control of the airplane.
70-06-05: 70-06-05 BRITTEN-NORMAN, LTD: Amdt. 39-956. Applies to BN-2 and BN-2A airplanes. To prevent failure of the elevator trim system final drive lever attachment lugs, accomplish the following: (a) Within the next 10 hours' time in service after the effective date of this AD, unless already accomplished, and thereafter at intervals not to exceed 25 hours' time in service since the last inspection until the modifications of paragraph (b) have been accomplished, visually inspect the elevator trim system final drive lever (P/N NB-45-D-1823) for cracks in accordance with Britten-Norman Service Bulletin No. BN-2/SB.24 dated January 8, 1969, or later ARB-approved issue or an FAA-approved equivalent. (b) If cracks are found on the drive lever during the inspections required by paragraph (a), before further flight replace the affected lever (P/N NB-45-D-1823) with a new lever (P/N NB-45-D-2165) by incorporating Modification NB/M/394 in accordance with Britten- Norman Service Bulletin BN-2/SB.24 dated January 8, 1969, or later ARB-approved issue or an FAA-approved equivalent. (c) The repetitive inspections required by paragraph (a) may be discontinued after compliance with paragraph (b) has been accomplished. This amendment becomes effective March 17, 1970.
88-10-05: 88-10-05 LOCKHEED AERONAUTICAL SYSTEMS COMPANY-GEORGIA: Amendment 39-5913. Applies to Model 382 series airplanes, Serial Numbers 3946 through 4250, and 4299 through 4303, except those having outer wings installed to a configuration equivalent to Serial Number 4542 or subsequent; certificated in any category. Compliance required as indicated, unless previously accomplished. To prevent severe damage to the lower surface panels of the outer wings, accomplish the following: A. Within the next 50 hours time-in-service after the effective date of this AD; or upon the accumulation of 11,000 flight hours total time-in-service for airplanes Serial Numbers 3946 through 4250, or 18,000 flight hours total time-in-service for airplanes Serial Numbers 4299 through 4303; whichever occurs later, perform an inspection of the outer wing lower surface panels 1, 2, 3, and 4, in accordance with Lockheed Service Bulletin A382-57-71, dated November 30, 1987, to determine the existence of doublers on those panels between outer wing stations 161 and 195. B. If doublers have been installed on panels 1, 2, 3, and 4, left and right, in accordance with Northwest Industries (NWI) Drawing 3609103, the airplane may be returned to normal service. C. If doublers have been installed on panels 1 and 2 in accordance with Lockheed Service Bulletin 382-152 (382-57-35), dated September 2, 1987, or later FAA-approved revisions, prior to further flight, accomplish either of the following: 1. Inspect the heat shield and nacelle fairing attachment fastener holes from outer wing station 161 to 195, in accordance with Lockheed Service Bulletin A382-57-71, dated November 30, 1987. a. If no cracks are found, repeat this inspection at intervals not to exceed 300 flight hours. b. If cracks are found, prior to further flight, repair in accordance with an FAA-approved method. 2. Modify the wing in accordance with Lockheed Service Bulletin 382-57- 73, dated January 28,1988. Installation of this modification constitutes terminating action for the repetitive inspections required by paragraph C.1.a., above. D. If doublers have not been installed on panels 1, 2, 3, and 4, prior to further flight, accomplish either of the following: 1. Inspect the heat shield and nacelle fairing attachment fastener from outer wing station 161 to 195, in accordance with Lockheed Service Bulletin A382-57-71, dated November 30, 1987. a. If no cracks are found, repeat this inspection at intervals not to exceed 300 flight hours. b. If cracks are found, prior to further flight, repair in accordance with an FAA approved method. 2. Modify the wing in accordance with Northwest Industries (NWI) Drawing 3609103. Installation of this modification constitutes terminating action for the repetitive inspections required by paragraph D.1.a., above. E. Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes toa base in order to comply with the requirements of this AD. F. An alternate means of compliance or adjustment of the compliance time, which provides an acceptable level of safety, may be used when approved by the Manager, Atlanta Aircraft Certification Office, FAA, Central Region. NOTE: The request for alternate means of compliance should be forwarded through an FAA Principal Maintenance Inspector (PMI), who may add any comments and then send it to the Atlanta Aircraft Certification Office. All persons affected by this directive who have not already received the applicable service information from the manufacturer may obtain copies upon request to Lockheed Aeronautical Systems Company-Georgia, Attn: Commercial and Customer Support, Department 72-05, Zone 80, 86 South Cobb Drive, Marietta, Georgia 30063. This information may be examined at FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or FAA, Central Region, Atlanta Aircraft Certification Office, 1669 Phoenix Parkway, Suite 210, Atlanta, Georgia. This amendment becomes effective May 25, 1988.
2016-13-09: We are adopting a new airworthiness directive (AD) for certain Bombardier, Inc. Model CL-600-2B16 (CL-604 Variant) airplanes. This AD was prompted by a determination that certain maintenance tasks for the horizontal stabilizer trim actuator (HSTA) are inadequate. This AD requires revising the maintenance or inspection program, as applicable, to incorporate new airworthiness limitations for the HSTA. We are issuing this AD to detect and correct premature wear and cracking of the HSTA, which could result in failure of the HSTA and consequent loss of control of the airplane.
2016-14-08: We are superseding Airworthiness Directive (AD) 2015-10-03 for certain Airbus Model A330-200 and -300 series airplanes, and Model A340-200 and -300 series airplanes. AD 2015-10-03 required a detailed inspection for visible chrome of each affected main landing gear (MLG) sidestay upper cardan pin, associated nuts, and retainer assembly; pin replacement if needed; measurement of cardan pin clearance dimensions (gap check); corrective actions if necessary; and a report of all findings. This new AD requires a detailed inspection of the upper cardan pin and nut threads for any corrosion, pitting, or thread damage, and if necessary, replacement of the cardan pin and nut. This new AD also revises the applicability to include additional airplane models. This AD was prompted by a report that an MLG sidestay upper cardan pin migration event had been caused by corrosion due to lack of jointing compound and inadequate sealant application during the MLG installation. We are issuing this ADto detect and correct migration of the sidestay upper cardan pin, which could result in disconnection of the sidestay upper arm from the airplane structure, and could result in a landing gear collapse and consequent damage to the airplane and injury to occupants.
58-09-02: 58-09-02 HARTZELL: Applies to HC-82XF-1 and -1A Propellers Installed on Cessna 180 Aircraft. Compliance required as outlined. There have been several reported instances of the piston guide rod P/N A-811 used in jack assembly B-804 breaking at the point where it is pinned to the A-96A fork. Failure of a guide rod will allow the particular blade to become uncontrollable. In view of the possible serious consequences resulting from vibration and the loss of control of the propeller, the following steps must be taken: 1. Inspection within 25 hours. If item 2 will not be complied with within 25 hours of operation, remove fork pin P/N A- 522 and slide the pitch change fork P/N A-96 sufficiently to completely expose the hole in push rod P/N A-811 used in jack assembly B-804. Visually inspect the exposed rod for cracks. If a crack is found, the rod should be removed from the propeller and replaced. 2. Replacement. Prior to September 1, 1958, replace jack assembly B-804 with jack assembly B-828. (Hartzell Service Bulletin No. 39 dated January 16, 1957, covers this same subject, and Hartzell Service Bulletin No. 47 also applies.)
82-09-01: 82-09-01 TELEDYNE CONTINENTAL MOTORS: Amendment 39-4412. Applies to the following engines installed in, but not limited to, Cessna Models 340 and 414 series airplanes: NEW ENGINES: TSIO-520-NB serial numbers 519735 thru 519738, 519781 thru 519785, 519885 thru 519890, 519893 thru 519897, 519899 through 519915, 519929 thru 519933, 519935 thru 519937, 519939 thru 519962, 521026 thru 521045, 521049 thru 521074, 521085 thru 521088, 521097, 521141 thru 521168, 521170 thru 521183, 521187 thru 521237, 521239 thru 521247, 521249 thru 521255, 521257, 521258, 521260 thru 521281, 521284 thru 521305, 521307 thru 521335, 521339, 521340, 521342 thru 521345, 521347, 521349, 521351, 521353, 521354, 521357, 521358, 521362, 521365, 521366, 521371, 521378, 521384, 521385, 521393, 521395, 521398, 521413 thru 521418, 521441, 521442, 521455, 521461. REBUILT ENGINES: TSIO-520-J serial numbers 218830, 218831, 218836, 218838 thru 218873; TSIO- 520-K serial numbers 224563, 224565 thru 224573; TSIO-520-N serial numbers 228231, 228243, 228248 thru 228250, 228255, 228262 thru 228363, 228365 thru 228368, 228373; TSIO-520-NB serial numbers 233976, 233982, 233986, 233987, 233989 thru 234058, 234060 thru 234069, 234071 thru 234074, 234077, 234078. Compliance is required as indicated unless already accomplished. To prevent the possibility of a fuel leak which could result in an engine compartment fire, accomplish the following: A. Prior to next flight, activate the boost pump to static check the fuel pressure regulator inlet and outlet for leaks. Visually inspect in the area of the fuel pressure regulator for the presence of fuel stains. If either inspection indicates a leak or stains, comply with Paragraph B before further flight. If no leak or stain is evident, comply with Paragraph B within the next 10 hours of operation. B. Remove the fuel fittings from the regulator and inspect the thread bores in the regulator and the threads of the fittings. If the threads in the regulator appear damaged, cut, or chipped (when compared to a normal pipe thread), replace the fuel pressure regulator with a serviceable regulator of a like part number. Replace any damaged fittings. Prior to installing the fittings, clean the threads with clean degreaser, Loctite "LOQUIC PRIMER T" or equivalent, to be sure all oil and dirt is removed. Blow dry with dry compressed air. Apply Loctite Hydraulic Sealant 69 or 569 or equivalent sparingly 3/4 of the way around on the fitting threads only. To avoid contamination of the fuel cavity, do not apply sealant to the first thread. Install the fittings until tight (at least 3-5 threads engagement). Allow sealant to cure for 30 minutes before pressure testing. NOTE: Teledyne Continental Motors Service Bulletin No. M82-5, dated April 26, 1982, pertains to this subject. An equivalent method of compliance may be approved by the Chief, Atlanta Aircraft Certification Office, Federal Aviation Administration, ACE-115A, P.O. Box 20636, Atlanta, Georgia 30320. This amendment becomes effective July 8, 1982, as to all persons except those to whom it was made immediately effective by priority mail, issued April 16, 1982.
65-12-03: 65-12-03 MOONEY: Amdt. 39-74 Part 39 Federal Register May 28, 1965. Applies to Model M20E Aircraft, Serial Numbers 101 through 722 Equipped with Hartzell Propeller, HC-C2YK/7666-2 or CHC-C2YK/7666-2. Compliance required within the next 25 hours' time in service after the effective date of this AD unless already accomplished. To avoid continuous propeller operation in the speed range where vibration stresses are high, accomplish the following: (a) Add the following operating limitation to the Airplane Flight Manual: "Avoid continuous operation between 2,100 and 2,350 r.p.m." (b) Mark engine tachometer with a red arc from 2,100 to 2,350 r.p.m., install Mooney decal P/N 150010-65, on tachometer bezel glass in accordance with Mooney Service Letter No. 21-127, dated April 15, 1965. This directive effective May 28, 1965.
2016-14-02: We are superseding Airworthiness Directive (AD) 2012-18-12 for certain Airbus Model A318, A319, and A320 series airplanes. AD 2012-18- 12 required modifying the off-wing escape slide (OWS) enclosures on the left-hand (LH) side and right-hand (RH) side of the fuselage. This new AD retains the requirements of AD 2012-18-12 and expands the applicability to all Airbus Model A318, A319, and A320 series airplanes. This AD was prompted by reports that additional OWS part numbers have been affected. We are issuing this AD to prevent off-wing exits on the LH and RH sides of the fuselage from becoming inoperative. During an emergency, inoperative off-wing exits could impair the safe evacuation of occupants, possibly resulting in personal injuries.
71-05-01: 71-05-01 SIKORSKY: Amdt. 39-1157. Applies to S-61 Type Helicopters Certified in all Categories. Compliance required as follows: To preclude the possibility of failure of the S-61 Main Landing Gear Axle, P/N 6125-50115-0, unless already accomplished, inspect and replace the axle in accordance with paragraph 2, Accomplishment Instructions of Sikorsky Service Bulletin 61B25-3 dated 15 January 1971 or later FAA-approved revision or an alternate method approved by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region. Report results of above inspection in compliance with this AD to Chief, Engineering and Manufacturing Branch, FAA, Eastern Region (Reporting Approved by Bureau of the Budget under BOB No. 04-R0174.) Replacement axle P/N S6125-50115-2 has a service life of 242,550 landings. This amendment is effective February 23, 1971.