Results
2022-03-15: The FAA is adopting a new airworthiness directive (AD) for various airplanes modified with certain configurations of Garmin G3X Touch Electronic Flight Instrument System installed per Supplemental Type Certificate (STC) No. SA01899WI or Garmin GI 275 Multi-Function Display (MFD) installed per STC No. SA02658SE. This AD was prompted by a report of a fuel quantity disparity between the amount of fuel indicated and the actual amount of fuel. This AD requires modifying the resistive fuel probe interface. The FAA is issuing this AD to address the unsafe condition on these products.
75-01-02: 75-01-02 PIPER: Amendment 39-2058. Applies to Piper PA-36-285 airplanes serial numbers 36-7360001 through 36-7460026 and 36-7460034 certificated in all categories. Compliance required within the next 50 hours' time in service after the effective date of this AD, unless already accomplished. To prevent possible undesirable elevator control forces accomplish the following: Install Piper Flap Travel Modification Kit No. 760-903V in accordance with Piper Service Bulletin No. 439 or an equivalent approved by the Chief, Engineering and Manufacturing Branch, FAA Southern Region. This amendment becomes effective January 6, 1975.
2004-10-13: This amendment adopts a new airworthiness directive (AD), that applies to CFM International, S.A., CFM56-2-C, -3 series, and -5 series turbofan engines. This amendment requires removing from service main fuel pumps with bronze gear-stage bearings and installing main fuel pumps with bi-metal, aluminum/bronze bearings. This amendment results from several reports of main fuel pump bronze bearing failures. We are issuing this AD to prevent main fuel pump bearing failures resulting in fuel nozzle clogging, low pressure turbine (LPT) case burn-through, and damage to the airplane.
2016-21-08: We are superseding Airworthiness Directive (AD) 2013-25-08 for all Airbus Model A330-200, -200 Freighter, and -300 series airplanes; and Model A340-200 and -300 series airplanes. AD 2013-25-08 required a repetitive inspection program on certain check valves in the hydraulic systems that includes, among other things, inspections for lock wire presence and integrity, traces of seepage or black deposits, proper torque, alignment of the check valve and manifold, installation of new lock wire, and corrective actions if needed. This new AD removes airplanes from the applicability, and requires modifying the green, blue, and yellow high pressure hydraulic manifolds by replacing certain check valves with improved check valves, which terminates the repetitive inspections required by this AD. This AD was prompted by multiple reports of hydraulic line check valves loosening. We are issuing this AD to address the unsafe condition on these products.
2016-22-17: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 787-8 airplanes. This AD was prompted by a report that the grounding jumpers between the environmental control system (ECS) bracket and the current return network (CRN) straps near certain passenger entry doors were not bonded correctly during manufacturing. This AD requires changing the configuration of the grounding jumpers connecting the ECS brackets and CRN straps; measuring the bond resistance; and doing related investigative and corrective actions if necessary. We are issuing this AD to address the unsafe condition on these products.
89-19-05: 89-19-05 CASA: Amendment 39-6320. (Docket No. 89-NM-29-AD) Applicability: All Model C-212 series airplanes, certificated in any category. Compliance: Required within the next 180 days after the effective date of this AD, unless previously accomplished. To prevent hindered egress of passengers in the event of an emergency evacuation, accomplish the following: A. Remove the right rear passenger seats adjacent to the emergency exit or modify the seat installation so that the projected opening of the exit is not obstructed by any part of the seat, including the seat back or armrests, in any position, in a manner approved by the Manager, Standardization Branch, ANM-113, FAA, Northwest Mountain Region. B. Ensure that the left forward seat is installed in a position that provides clearance from the intersection of the plane of the seat cushion and the front of the seat back to hard structure, such as the bulkhead, of 35 inches or greater. C. 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, Standardization Branch, ANM-113, FAA, Northwest Mountain Region. NOTE: The request should be forwarded through an FAA Principal Maintenance Inspector (PMI), who may add any comments and then send it to the Manager, Standardization Branch, ANM-113. D. Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base for the accomplishment of the requirements of this AD. This amendment (39-6320, AD 89-19-05) becomes effective on October 14, 1989.
87-20-04: 87-20-04 CESSNA: Amendment 39-5733. Applies to Model 185, 185A, 185B, 185C, 185D, 185E, A185E and A185F (Serial Numbers 185-0001 thru 18503153) airplanes certificated in any category. Compliance: Within the next 50 hours of operation or before completion of the next annual inspection, whichever comes first, after the effective date of this AD, unless already accomplished per AD 84-10-01. To prevent power loss or engine stoppage due to water contamination of the fuel system, accomplish the following: (a) Modify the aircraft fuel system using one of the options on the following subparagraphs (a)(1), (a)(2), or (a)(3). (1) Install fuel reservoir (accumulator) quick drains in accordance with STC SA2272CE. This STC is owned by Mike Kelley Aircraft Inc., P.O. Box 541, Wellington, Kansas 67152, telephone (316) 326-8581. This STC is applicable to Cessna 185 and 185A thru 185E, A185E and A185F Serial Numbers 185-0001 thru 18503153. (2) Install fuel reservoir (accumulator) quick drains in accordance with STC SA2245CE. This STC is owned by Safe Air Repair, Inc., 3325 Bridge Avenue, Albert Lea, Minnesota 56007, telephone (507) 373-5408. This STC is applicable to Cessna 185A thru 185E, A185E and A185F, Serial Numbers 185-0414 thru 18503153. (3) Install quick drains in the fuel reservoir (accumulator) outlet line by using equivalent aircraft standard hardware. NOTE: A one-time inspection of the Cessna fuel line Part Number 0500106-329 which is used on Serial Number 185-0001 thru 185-0413 should be performed during installation of the fuel reservoir quick drains. This fuel line requires careful attention to routing in order to insure adequate clearance from moving control components located immediately adjacent to this fuel line. (b) Airplanes may be flown in accordance with FAR 21.197 to a location where this AD may be accomplished if it is determined that no water is present in the fuel reservoir (accumulator) or any other part of the fuel system from which fuel will be used. (c) An equivalent means of compliance with this AD may be used, if approved by the Manager, Aircraft Certification Office, Federal Aviation Administration, 1801 Airport Road, Room 100, Mid-Continent Airport, Wichita, Kansas 67209. All persons affected by this AD may obtain copies of the document(s) referred to herein upon request to FAA, Office of the Regional Counsel, Room 1558, 601 East 12th Street, Kansas City, Missouri 64106. This amendment becomes effective on September 30, 1987.
89-19-02: 89-19-02 BOEING OF CANADA, LTD., DE HAVILLAND DIVISION: Amendment 39- 6314. Applicability: Model DHC-8-100 series airplanes, and Model DHC-8-300 series airplanes, serial numbers 001 through 149, certificated in any category. Compliance: Required as indicated, unless previously accomplished. To ensure that the engine fire extinguishing system bottle squibs are connected to the proper actuating switch, accomplish the following: A. Within the next 70 hours time-in-service after the effective date of this AD, perform an inspection to verify proper installation of the fire bottle squib wiring in the engine fire extinguishing system, in accordance with the Accomplishment Instructions of de Havilland Alert Service Bulletin A8-26-8, dated March 20, 1989. If the connector identification sleeves are difficult to read or are damaged, or if it has not been confirmed that the installation is correct, prior to further flight, correct the wiring installation and verify properwiring in accordance with the service bulletin. NOTE: Airplanes on which this inspection and/or repair has previously been performed, as required by paragraphs A. and B. of Telegraphic AD T89-05-51, in accordance with Items 1 through 26 of de Havilland Alert Service Bulletin A8-26-7, dated February 24, 1989, are considered to have complied with the requirements of this paragraph. B. Within the next 120 hours time-in-service or 30 days after the effective date of this AD, whichever occurs first, install de Havilland Modification Number 8/1336, "Fire Protection - Fire Extinguisher Squib Electrical Connector Positioning," in accordance with the Accomplishment Instructions of de Havilland Service Bulletin 8-26-9, dated March 23, 1989. C. 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, New York Aircraft Certification Office, FAA, Engine and Propeller Directorate.NOTE: The request should be forwarded through an FAA Principal Maintenance Inspector (PMI), who may add any comments and then send it to the Manager, New York Aircraft Certification Office. D. Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base in order to comply with the requirements of this AD. All persons affected by this directive who have not already received the appropriate service information from the manufacturer may obtain copies upon request to Boeing of Canada, Ltd., de Havilland Division, Garatt Boulevard, Downsview, Ontario M3K 1Y5, Canada. This information may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 17900 Pacific Highway South, Seattle, Washington, or the New York Aircraft Certification Office, Engine and Propeller Directorate, 181 South Franklin Avenue, Room 202, Valley Stream, New York. This amendment (39-6314) supersedes Telegraphic AD T89-05-51, issued February 28, 1989. This amendment (39-6314, AD 89-19-02) becomes effective on September 19, 1989.
90-25-15: 90-25-15 FOKKER: Amendment 39-6826. Docket No. 90-NM-247-AD. Applicability: All Model F-28 Mark 0100 series airplanes, equipped with main wheel assemblies Part Nos. 5008131-2 and 5008131-3, certificated in any category. Compliance: Required as indicated, unless previously accomplished. To prevent wheel failure, reduced steering capability, loss of braking performance, structural damage and possible injury to people, accomplish the following: A. Within 6 days after the effective date of this AD, and thereafter prior to each flight, perform a visual inspection of the main landing gear (MLG) wheel assemblies for missing or cracked tie bolts. If any bolt is broken or missing, prior to further flight, replace the wheel with a serviceable wheel. B. Upon removal of any wheel in accordance with paragraph A. of this AD or for a tire change, accomplish the following: 1. After thorough cleaning, perform a magnetic particle inspection of all main wheel tie bolts for cracks. a. If a bolt is cracked, prior to further flight replace the cracked bolt. b. If a bolt is broken or missing, prior to further flight, replace the bolt and the two adjacent bolts (one on each side). c. If more than one bolt is broken or missing, prior to further flight, replace all bolts. 2. Inspect all bolts and nuts for crossed threads, and the self-locking feature for a minimum torque of 18 inch-pounds (2.0 Nm). If defective parts are found, prior to further flight, replace all defective parts. C. Within 60 days after the effective date of this AD, replace the MLG wheel assemblies, having Part Nos. 5008131-2 or 5008131-3, with modified wheel assemblies, Part Number 5008131-4, in accordance with Fokker Service Bulletin F100-32-044, dated October 24, 1990. Installation of the modified wheel assemblies constitutes terminating action for the repetitive inspections required by paragraphs A. and B. of this AD. NOTE: The Fokker servicebulletin references Aircraft Braking System Corporation Service Bulletin Fo-100-32-24, dated June 30, 1990, for additional instructions. D. 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, Standardization Branch, ANM- 113, FAA, Transport Airplane Directorate. NOTE: The request should be submitted directly to the Manager, Standardization Branch, ANM- 113, and a copy sent to the cognizant FAA Principal Inspector (PI). The PI will then forward comments or concurrence to the Manager, Standardization Branch, ANM-113. E. Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base in order to comply with the requirements of this AD. All persons affected by this directive who have not already received the appropriate service information from the manufacturer may obtain copies upon request to Fokker Aircraft USA, Inc., 1199 N. Fairfax Street, Alexandria, Virginia 22314 or Aircraft Braking Systems Corporation, 1204 Massillon Road, Akron, Ohio 44306-4186. This information may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 1601 Lind Avenue S.W., Renton, Washington. This amendment (39-6826, AD 90-25-15) becomes effective on December 24, 1990.
2016-23-04: We are adopting a new airworthiness directive (AD) for certain BRP-Powertrain GmbH & Co KG Rotax 912 F2, 912 F3, 912 F4, 912 S2, 912 S3, 912 S4, 914 F2, 914 F3, and 914 F4 reciprocating engines. This AD requires replacement of any affected carburetor float with a float that is eligible for installation. This AD was prompted by a report of a quality escape in the manufacturing of the affected floats. We are issuing this AD to prevent failure of the carburetor float, failure of the engine, in-flight shutdown, and loss of the airplane.
88-15-07: 88-15-07 BRITISH AEROSPACE: Amendment 39-5981. Applies to all British Aerospace (BAe) Model 146 series airplanes as listed in BAe 146 Service Bulletin 32-73, dated March 13, 1987, certificated in all categories. Compliance required as indicated, unless previously accomplished. To prevent collapse of the main landing gear (MLG) due to defective main fittings, accomplish the following: A. Prior to the accumulation of 12,000 landings or within the next 1,000 landings after the effective date of this AD, whichever occurs later, inspect the main fitting and barrel section of the main fitting in accordance with British Aerospace BAe 146 Service Bulletin 32-73, dated March 13, 1987. If defective parts are identified during the inspection, repair, prior to further flight, in accordance with Dowty Rotol Service Bulletin number 146-32-23. NOTE: British Aerospace BAe Service Bulletin 32-73 references Dowty Rotol Service Bulletin 146-32-23 for specific procedures for identification, inspection, and repair of the affected MLG parts. The modification of MLG fittings in accordance with Dowty Rotol Service Bulletin 146-32-56 (as recommended in Dowty Rotol Service Bulletin 146-32-23) is not made mandatory by this airworthiness directive. B. 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, Standardization Branch, ANM-113, FAA, Northwest Mountain Region. NOTE: The request should be forwarded through an FAA Principal Maintenance Inspector (PMI), who may add any comments and then send it to the Manager, Standardization Branch, ANM-113. C. Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base for the accomplishment of the modifications required by this AD. All persons affected by this directive who have not already received the appropriate service documents from the manufacturer may obtain copies upon request to British Aerospace, Librarian for Service Bulletins, P.O. Box 17414, Dulles International Airport, Washington, D.C. 20041. These documents may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or at the Seattle Aircraft Certification Office, 9010 East Marginal Way South, Seattle, Washington. This amendment, 39-5981, becomes effective August 22, 1988.
87-08-03: 87-08-03 LOCKHEED-CALIFORNIA COMPANY: Amendment 39-5595. Applies to Lockheed Model L-188A and L-188C airplanes, certificated in any category. Compliance required as indicated, unless previously accomplished. To prevent airframe vibration from an open wing air start access door, accomplish the following: A. Within 500 hours time-in-service after the effective date of this AD, modify the air start door in accordance with Lockheed Drawing 842715, dated February 18, 1986, or later revision approved by the Manager, Los Angeles Aircraft Certification Office, FAA, Northwest Mountain Region. B. Alternate means of compliance which provide an acceptable level of safety may be used when approved by the Manager, Los Angeles Aircraft Certification Office, FAA, Northwest Mountain Region. C. Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate the airplane to a base to accomplish the modification required by this AD. All persons affected by this directive who have not already received the appropriate service documents from the manufacturer may obtain copies upon request to Lockheed-California Company, P.O. Box 551, Burbank, California 91520, Attention: L-188, Commercial Support Contracts, Dept. 63-11 Unit 33. These documents may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or the Los Angeles Aircraft Certification Office, 4344 Donald Douglas Drive, Long Beach, California. This Amendment becomes effective May 5, 1987.
72-15-02: 72-15-02 PRESTOLITE: Amendment 39-1487 as amended by amendment 39-1508. Applies to Prestolite alternator cooling fans, P/N's PU1605 and PU1605A installed on Prestolite Models ALE6406, ALE 6406R, ALE 8105A, ALE 8105S, ALE 8406, ALE 8406R, ALE 8408, ALE 8408R, ALH 5105, ALH 5105S, ALH 5106S, ALT 5101A, ALT 5101R, ALT 5102S, ALT 8403, ALT 8404, ALT 8404R, ALT 8404RS, ALT 8404LS, ALU 8403, ALU 8403R, ALU 8403RS, ALU 8403LS, ALX 6406, ALX 8403, ALX 8403R, ALX 8403RS, ALX 8403LS, ALY 6406, ALY 6406R, ALY 6407, ALY 6408, ALY 8402, ALY 8403, ALY 8403R, ALY 8403RS, ALY 8403LS, ALY 8405, ALY 8405R, ALY 8410, ALY 8410R, ALZ 8401, ALZ 8401R, alternators utilized in various makes and models of aircraft engines. Compliance: Required as indicated, unless already accomplished. To preclude in-service failures of alternator cooling fans accomplish the following: A) On all aircraft with more than 100 hours' time in service, within the next 25 hours' time in service, unless already accomplished within the previous 75 hours' time in service and thereafter at intervals not to exceed 100 hours' time in service from the last inspection, remove and visually inspect the alternator cooling fan for damage, distortion, cracks, or breaks. Replace all alternator cooling fans found damaged, distorted, cracked or broken with an airworthy fan prior to return to service. Replacement and/or reinstallation of the fan should be accomplished in accordance with the directions set forth in Prestolite Service Bulletin No. ASM-4 revised December 27, 1971. NOTE: When removing and replacing the pulley retaining nut do not use the cooling fan to prevent rotation of the alternator shaft. Use of the fan to prevent shaft rotation can result in bending and distortion of the fan that will require it to be replaced. B) No later than January 1, 1973, replace PU1605 and PU1605A Prestolite alternator cooling fan as applicable with 90-2241 Prestolite alternator cooling fan (consisting oftwo plates - Part Nos. PU604A and PU605A) in accordance with Prestolite Service Bulletin ASM-8, dated May 30, 1972, or any alternate replacement approved by Chief, Engineering and Manufacturing Branch, Great Lakes Region. This AD 72-15-2 amendment 39-1487 superseded AD 72-1-5. Amendment 39-1487 became effective July 27, 1972. This amendment 39-1508 becomes effective September 1, 1972.
2016-21-05: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 777-200, -200LR, -300, and -300ER series airplanes. This AD was prompted by a report indicating that the manufacturer discovered locations where the control components and wiring of the left and right engine fuel spar valves do not have adequate physical separation to meet the redundant system separation requirements. This AD requires modifying the wiring, and installing a new relay bracket and new location for the relay on the left and right engine fuel spar valves. This AD also requires an inspection to identify the part number of the motor operated valve (MOV) actuators for the left and right engine fuel spar valves; replacement of specified MOV actuators with new MOV actuators; certain bonding resistance measurements; and applicable corrective actions. We are issuing this AD to prevent loss of control of both the left and right engine fuel spar valves during a single event, such as local wire bundle damage or a wire bundle fire, which could cause both engines to shut down or result in the inability to control an engine fire.
2000-15-07: This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-10 series airplanes, that requires a one-time detailed visual inspection of the galley power feeder cables and fuselage structure at a certain station to detect chafing or arcing damage to the cables and structure or to detect arcing damage to the insulation blankets; and corrective actions, if necessary. This AD also requires installation of spacers between the galley power feeder cable clamps and fuselage structure. This amendment is prompted by reports indicating that the galley power feeder cables chafed against a certain fuselage frame in the forward lower cargo compartment, which resulted in electrical arcing. The actions specified by this AD are intended to prevent such chafing and arcing due to insufficient clearance between the cables and the airplane structure, which could result in smoke and fire in the forward lower cargo compartment.
78-07-03: 78-07-03 GENERAL ELECTRIC: Amendment 39-3164 as amended by Amendment 39-3211. Applies to CF6-6D and CF6-6D1 engines installed in aircraft certificated in all categories. To prevent failure of the 11-13 Stage Compressor Spool, P/N 9021M66 (all assembly part numbers), thirteenth stage rim compliance is required, unless previously accomplished, as follows: (a) Modify the 11-13 spool in accordance with General Electric Service Bulletin 72-682 not later than December 31, 1979. (b) Pending modification per (a) above inspect the following 11-13 spool serials in accordance with General Electric Service Bulletin 72-673 or 72-700 within the next 500 cycles in service after the effective date of this AD and thereafter each 700 cycles in service if previously inspected in accordance with General Electric Service Bulletin 72-700 or 1800 cycles in service if previously inspected in accordance with General Electric Service Bulletin 72-673. MP31293A MP021392 MP022819 MP023561 MP024432 MP024433 MP025458 MP025463 MP025472 MP027903 MP027906 MP028163 MP028175 MP028176 MP028574 MP028711 MP029244 MP029245 MP029246 MP031291 MP031292 MP031304 MP031736 MP032456 MP033570 MP034332 MP034468 MP034648 MP034649 MP034808 MP034810 MP034821 MP034822 MP034823 MP035315 MP035343 MP035344 MP035350 MP035351 MP035353 MP035816 MP035821 MP035823 MP035836 MP035844 MP035847 MP035848 MP036810 MP036814 MP036829 MP037135 MP0A0123 MP0A0129 MP0A0134 MP0A0138 MP0A0140 MP0A0161 MP0A0273 MP0A0277 MP0A0278 MP0A0280 MP0A0281 MP0A0286 MP0A0287 MP0A0292 MP0A0293 MP0A0354 MP0A0379 MP0A0383 MP0A0396 MP0A0400 MP0A0402 MP0A0404 MP0A0411 MP0A0430 MP0A0446 MP0A0450 MP0A0458 MP0A0571 MP0A0579 MP0A0587 MP0A0589 MP0A0591 MP0A0600 MP0A0604 MP0A0643 MP0A0644 MP0A0645 MP0A0648 MP0A0652 MP0A0659 MP0A0660 MP0A0744 MP0A0751 MP0A0755 MP0A0797 MP0A0811 MP0A0813 MP0A0816 MP0A0819 MP0A0820 MP0A0822 MP0A0830 MP0A0831 MP0A0875 MP0A0876 MP0A0882 MP0C0889 MP0C3154 MPX32453 RP021891 RP022426 RP023605 RP023614 RP024401 The manufacturer's specifications and procedures identified in this directive are incorporated herein and made part hereof pursuant to 5 U.S.C. 553(a)(1). All persons affected by this directive who have not already received these documents from the manufacturer may obtain copies upon request to General Electric Company, Cincinnati, Ohio 45215. These documents may also be examined at the Great Lakes Regional Office, 2300 East Devon Avenue, Des Plaines, Illinois 60018, and at FAA Headquarters, 800 Independence Avenue, S.W., Washington, D.C. 20591. A historical file on this airworthiness directive which includes incorporated material in full is maintained by the FAA at its headquarters in Washington, D.C., and the Great Lakes Region. Amendment 39-3164 became effective April 6, 1978. This amendment 39-3211 becomes effective May 22, 1978.
74-12-10: 74-12-10 NIHON AEROPLANE MANUFACTURING COMPANY LIMITED: Amendment 39-1866. Applies to NAMC Model YS-11/11A series airplanes (S/N's 2050 through 2053, 2056, 2057, 2061, 2062, 2072, 2073, 2075, 2077, 2079, 2084, 2086 through 2089, 2091, 2100, 2118 through 2123, 2126, 2128, 2129, 2132, 2140, 2148, 2159, 2169, 2172, 2173, and 2179 through 2181) equipped with AiResearch APU's. Compliance required within the next 25 hours' time in service after the effective date of this AD unless already accomplished. To prevent possible malfunction in the auxiliary power unit (APU) wiring harness that could result in a fire, inspect and modify the installation of the APU electrical wiring harnesses in accordance with the Japan Civil Aviation Bureau approved NAMC YS-11 Service Bulletin No. A49-13, dated February 25, 1974 or an equivalent approved by the Chief, Engineering and Manufacturing District Office, FAA, Pacific-Asia Region. This amendment becomes effective June 12, 1974.
2016-23-01: We are superseding Airworthiness Directive (AD) 2010-04-03 for all Airbus Model A310 series airplanes. AD 2010-04-03 required accomplishing repetitive detailed inspections for cracking around the fastener holes in certain wing top skin panels between the front and rear spars on the left- and right-hand sides of the fuselage, and repair if necessary. This new AD continues to require the repetitive detailed inspections, and also requires supplemental repetitive ultrasonic inspections for cracking around the fastener holes in wing top skin panels 1 and 2 at ribs 2 and 3, and repair if necessary. This AD was prompted by development of an ultrasonic inspection program to allow for earlier crack detection and extended repetitive inspection intervals. We are issuing this AD to detect and correct fatigue cracking around the fastener holes, which could result in reduced structural integrity of the airplane.
96-09-24: This amendment adopts a new airworthiness directive (AD), applicable to all EMBRAER Model EMB-120 series airplanes, that requires revising the Airplane Flight Manual (AFM) to provide the flight crew with recognition cues for, and procedures for exiting from, severe icing conditions, and to limit or prohibit the use of various flight control devices. This amendment is prompted by results of a review of the requirements for certification of the airplane in icing conditions, new information on the icing environment, and icing data provided currently to the flight crews. The actions specified by this AD are intended to minimize the potential hazards associated with operating the airplane in severe icing conditions by providing more clearly defined procedures and limitations associated with such conditions.
2016-22-09: We are superseding Airworthiness Directive (AD) 2006-20-11 for certain The Boeing Company Model 757-200, -200CB, and -200PF series airplanes. AD 2006-20-11 required initial and repetitive detailed or high frequency eddy current (HFEC) inspections for cracks around the rivets at the upper fastener row of the skin lap splice of the fuselage, and repair of any crack found. This new AD no longer allows the detailed inspections and instead requires repetitive external HFEC inspections for cracking of the skin lap splices of the fuselage, and repair if necessary. This AD was prompted by an evaluation done by the design approval holder (DAH) indicating that the fuselage skin lap splice is subject to widespread fatigue damage (WFD). We are issuing this AD to detect and correct fatigue cracking at certain skin lap splice locations of the fuselage, which could result in reduced structural integrity and rapid decompression of the airplane.
67-25-02 R3: 67-25-02 R3 BRITISH AEROSPACE: Amendment 39-477 as amended by Amendments 39- 485 and Amendment 39-909 is further amended by Amendment 39-5059. Applies to BAC 1-11 200 and 400 series airplanes, certificated in all categories. Compliance required as indicated unless previously accomplished. To prevent serious deterioration and failure of the flap drive screwjacks, accomplish the following: A. Perform a visual inspection of the flap drive screwjacks for evidence of unusual wear in accordance with paragraph 2.1.1 of British Aerospace BAC 1-11 Alert Service Bulletin 27-A-PM2992, Issue 4, dated November 30, 1979, prior to the accumulation of 750 landings or 800 hours time in service from the last inspection, whichever occurs earlier. Repeat the inspection at intervals not to exceed 800 hours time in service thereafter. B. Measure the nut-to-screw backlash in accordance with paragraph 2.2 of the service bulletin prior to the accumulation of 3,000 landings or 4,800 hours time inservice from the last check, whichever occurs earlier, and thereafter at intervals not to exceed 4800 hours time in service or 3000 landings, whichever occurs first. If the nut-to-screw backlash exceeds 0.03- inch, the screwjack assembly must be replaced with serviceable parts. C. Incorporation of modification PM2992, which introduces a new seal for the ball nut, constitutes terminating action for this AD. D. Alternate means of compliance which provide an acceptable level of safety may be used when approved by the Manager, Seattle Aircraft Certification Office, FAA, Northwest Mountain Region. E. Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base for the accomplishment of inspections and/or modifications required by this AD. F. Upon request of an operator, an FAA Maintenance Inspector, subject to prior approval of the Manager, Seattle Aircraft Certification Office, FAA, Northwest Mountain Region, may adjust the inspection times specified in this AD to permit compliance at an established inspection period of that operator, if the request contains substantiating data to justify the increase for that operator. Amendment 39-477 became effective September 9, 1967. Amendment 39-485 became effective September 20, 1967. Amendment 39-909 became effective January 11, 1970. This Amendment 39-5059 becomes effective June 17, 1985.
2016-22-05: We are adopting a new airworthiness directive (AD) for certain Pratt & Whitney (PW) PW4164, PW4164-1D, PW4168, PW4168-1D, PW4168A, PW4168A-1D, and PW4170 turbofan engines. This AD was prompted by several instances of fuel leaks on PW engines installed with the Talon IIB combustion chamber configuration. This AD requires initial and repetitive inspections of the affected fuel nozzles and their replacement with parts eligible for installation. We are issuing this AD to prevent failure of the fuel nozzles, which could lead to engine fire and damage to the airplane.
2004-09-33: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 747-400 and 747-400D series airplanes, that requires a detailed inspection of the fire extinguishing system tube and clamp for correct installation or a repetitive pressure test of the fire extinguishing system tube for leakage, and corrective action, if necessary. This action is necessary to prevent a chafed hole in the fire extinguishing system tube of the aft cargo compartment, which could result in a lack of fire extinguishing agent and consequent uncontained fire in the aft cargo compartment. This action is intended to address the identified unsafe condition.
2016-22-11: We are superseding airworthiness directive (AD) 2013-02-06 for all Engine Alliance (EA) GP7270 and GP7277 turbofan engines with certain part number (P/N) high-pressure turbine (HPT) stage 2 nozzle segments installed. AD 2013-02-06 required initial and repetitive borescope inspections (BSI) and removal from service of these nozzles before further flight if one or more burn holes were detected in any HPT stage 2 nozzle segment. AD 2013-02-06 also required removal from service of these HPT stage 2 nozzle segments at the next engine shop visit. This AD requires the same inspections as AD-2013-02-06, requires removal of affected HPT stage 2 nozzles at next piece-part exposure, and adds certain P/Ns to the applicability. This AD was prompted by another report of inadequate cooling of the HPT stage 1 shroud and stage 2 nozzle, leading to damage to the HPT stage 2 nozzle, burn- through of the turbine case, and in-flight shutdown. We are issuing this AD to prevent HPT stage 2 nozzle failure, uncontrolled fire, in- flight shutdown, and damage to the airplane.
51-22-01: 51-22-01 SIKORSKY: Applies to All Model S-51 Helicopters. Compliance required within the next 25 hours of operation, but not later than November 1, 1951. Due to the reported failures of Gear Shaft (Generator Drive-Tail Drive Transmission System) P/N S-10-35-1004, all shafts in service shall be replaced by shafts which have been jig drilled (i.e., the taper pin hole is located squarely with respect to the splines) and which have been stoned and polished to deburr and remove any sharp radii where the taper pin hole intersects the splines. (Sikorsky Service Information Circular No. 172, dated August 30, 1951, covers this same subject.)