Results
95-26-05 R1: This amendment rescinds an existing Airworthiness Directive (AD) for Robinson Helicopter Company (Robinson) Model R44 helicopters, which currently requires revisions to the R44 Rotorcraft Flight Manual (RFM). The RFM revisions limit operations in high winds and turbulence. The RFM revisions also provide information about main rotor stall and mast bumping with recommendations for avoiding these situations and additional emergency procedures for use in certain conditions. This amendment is prompted by the FAA's determination that the limitations and the procedures required by that AD are no longer necessary to correct an unsafe condition. The actions specified by this AD rescind all the requirements of AD 95-26-05, Amendment 39-9463, Docket 95-SW- 30-AD.
2004-12-14: This amendment adopts a new airworthiness directive (AD), applicable to certain Dornier Model 328-100 series airplanes, that requires an inspection of the alternating current (AC) power cables, realignment of the AC power cable retaining clamp, and corrective actions if necessary. This action is necessary to prevent chafing of the AC power cables against the alternator, which could result in a short circuit and impaired performance of AC-powered components, possibly leading to loss of flight-critical information to the flight deck and reduced controllability of the airplane. This action is intended to address the identified unsafe condition.
88-12-12: 88-12-12 CESSNA: Amendment 39-5941. Applies to all serial numbers of Models 177RG and F177RG airplanes certificated in any category. \n\n\tCompliance: Required within the next 75 hours time in service after the effective date of this AD, unless already accomplished. \n\n\tTo prevent power loss or engine stoppage due to water contamination of the fuel system, accomplish the following: \n\n\t(a)\tModify the airplane fuel system using one of the options in subparagraphs (a)(1), (a)(2), or (a)(3) below: \n\n\t\t(1)\tInstall a fuel strainer quick drain control in accordance with STC SA2344CE or SA2345CE. \n\tNOTE 1: These STCs are owned by Air Plains, Inc., P.O. Box 541, Wellington, Kansas 67152, telephone (316) 326-8581. \n\n\t\t(2)\tInstall a fuel strainer quick drain control in accordance with STC SA2335CE or SA2336CE. \n\tNOTE 2: These STCs are owned by Cessna Pilots Association, Inc., Wichita Mid- Continent Airport, 2120 Airport Road, P.O. Box 12948, Wichita, Kansas 67277, telephone (316)946-4777. \n\n\t\t(3)\tInstall a fuel strainer quick drain control by using equivalent aircraft standard hardware. \n\tNOTE 3: The FAA has received reports of corrosion inside the fuel strainer bowl caused by undrained water. A check of the condition of the fuel strainer and bowl can be made during installation of the fuel strainer quick drain control. \n\n\t(b)\tAirplanes may be flown in accordance with FAR 21.197 to a location where this AD may be accomplished. \n\n\t(c)\tAn equivalent means of compliance with this AD may be used, if approved by the Manager, Wichita Aircraft Certification Office, Federal Aviation Administration, 1801 Airport Road, Room 100, Mid-Continent Airport, Wichita, Kansas 67209. \n\n\tAll persons affected by this AD may obtain copies of the document(s) referred to herein upon request to: Cessna Pilots Association Supplemental Type Certificates (STCs) SA2335CE and SA2336CE information may be obtained from Mr. John Frank, Editor Cessna Pilots Association, Wichita Mid-Continent Airport, 2120 Airport Road, P.O. Box 12948, Wichita, Kansas 67277, telephone (316) 946-4777. Air Plains Inc. STCs SA2344CE and SA2345CE information may be obtained from Mr. Kent McIntyre, Vice President, Air Plains, Inc., P.O. Box 541, Wellington, Kansas 67152, telephone (316) 326-8581. These documents may also be examined at FAA, Office of the Regional Counsel, Room 1558, 601 East 12th Street, Kansas City, Missouri 64106. \n\n\tThis amendment, 39-5941, becomes effective on July 5, 1988.
2016-25-11: We are adopting a new airworthiness directive (AD) for certain International Aero Engines AG (IAE) V2522-A5, V2524-A5, V2527-A5, V2527E-A5, V2527M-A5, V2530-A5, V2533-A5, V2525-D5, V2528-D5, and V2531-E5 turbofan engines. This AD was prompted by nine in-flight shutdowns (IFSDs) that resulted from premature failure of the No. 3 bearing. This AD requires inspections and corrective actions for bearing damage. This AD also requires removal of the No. 3 bearing from service at the next engine shop visit. We are issuing this AD to correct the unsafe condition on these products.
93-22-06: 93-22-06 AIRBUS: Amendment 39-8730. Docket 93-NM-99-AD. Applicability: Model A300 series airplanes, excluding Model A300-600 series airplanes and Model A310 series airplanes; on which Airbus Modification 10361 has not been installed; certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent liquid from entering the generator control unit (GCU) and causing internal short circuits, which could result in the failure of the GCU and subsequent loss of electrical generation capacity, accomplish the following: (a) Within 6 months after the effective date of this AD, install a protective cover over each GCU and install a drainage circuit, in accordance with Airbus Industrie Service Bulletin A300-24-0082, dated March 3, 1993. (b) An alternative method of compliance or adjustment of the compliance time that provides an acceptable level of safety may be used if approved by the Manager, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate. Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, Standardization Branch, ANM-113. NOTE: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Standardization Branch, ANM-113. (c) Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate the airplane to a location where the requirements of this AD can be accomplished. (d) The installations shall be done in accordance with Airbus Industrie Service Bulletin A300-24-0082, dated March 3, 1993. This incorporation by reference was approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR Part 51. Copies may be obtained from Airbus Industrie, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. (e) This amendment becomes effective on December 17, 1993.
75-12-09 R2: 75-12-09 R2 ROCKWELL: Amendment 39-2223 as amended by Amendment 39-4166 is further amended by Amendment 39-4246. Applies to Models 500, 500A, 500B, 500S, 500U, 520, 560, 560A, 560E, 560F, 680, 680E, 680F, 680F(P), and 720, through Serial Number 3323 airplanes certificated in all categories. Compliance is required as indicated. Within the next 300 hours' time in service after the effective date of this AD, to prevent inadvertent pilot induced structural failure, install "bob weights" in accordance with Rockwell International Service Bulletin No. 128, Revision 1, dated April 24, 1975, or No. 129, Revision 2, dated May 9, 1975, or No. 136, Revision 1, dated May 9, 1975 (or later FAA approved revision), or an equivalent procedure approved by the Chief, Engineering and Manufacturing Branch, Southwest Region, Federal Aviation Administration, Fort Worth, Texas, unless already accomplished in accordance with the above revised service bulletins. Aircraft that have complied with Service Bulletin No. 129 prior to Revision 2 or Service Bulletin No. 136 prior to Revision 1, must comply with Rockwell Service Bulletin No. 152 dated May 9, 1975, or an equivalent approved by the Chief, Engineering and Manufacturing Branch, Southwest Region, Federal Aviation Administration, Fort Worth, Texas, unless already accomplished. Compliance with Service Bulletin No. 152 is required within 300 hours' time in service after the effective date of this AD. Aircraft that have complied with the bob-weight installation in accordance with Service Bulletin No. 129, prior to Revision 4 dated January 26, 1981, or Service Bulletin No. 136 prior to Revision 3 dated January 26, 1981, must comply with Service Bulletin No. 179 dated January 26, 1981, or an equivalent approved by the Chief, Engineering and Manufacturing Branch, Southwest Region, Federal Aviation Administration, Fort Worth, Texas, unless already accomplished. Compliance with the inspection specified in Service Bulletin No. 179 is required as follows: a. Models 500, 500A, 500B, 500U, 520, 560, 560A, 560E, 560F, 680, 680E, 680F, 680F(P), 720, and 500S, through Serial Number 3246 aircraft certificated in all categories which have had the provisions of Service Bulletin No. 129 prior to Revision 4 dated January 26, 1981, or Service Bulletin No. 136 prior to Revision 3 dated January 26, 1981, and Service Bulletin No. 152 dated May 9, 1975, which required the bob-weight installation or an equivalent approved by the Chief, Engineering and Manufacturing Branch, Southwest Region, Federal Aviation Administration, Fort Worth, Texas, accomplished; within 25 hours' time in service after August 9, 1981. When compliance with the repair or strengthening of the supports in accordance with Service Bulletin No. 129, Revision 4, or Service Bulletin No. 136, Revision 3, has been accomplished, the repetitive 25-hour inspection of Service Bulletin No. 179 may be discontinued. b. Model 500S, Serial Numbers 3247 through 3323, aircraft certificated in all categories; within 25 hours' time in service after the effective inspection of Service Bulletin No. 179. This repetitive 25-hour inspection may be discontinued when the repair or strengthening of the supports is accomplished in accordance with Part II of Service Bulletin No. 179. In accordance with FAR 21.197, a ferry flight is permitted to a base where the inspection, repair or modification required by this AD may be accomplished. Copies of these bulletins may be obtained by contacting the Service Manager, Gulfstream American Corporation, 5001 North Rockwell Avenue, Bethany, Oklahoma 73008. Amendment 39-2223 became effective July 2, 1975. Amendment 39-4166 became effective August 9, 1981. This amendment 39-4246 becomes effective November 28, 1981.
2022-14-06: The FAA is adopting a new airworthiness directive (AD) for all Airbus SAS Model A300 B4-600, B4-600R, and F4-600R series airplanes, and Model A300 C4-605R Variant F airplanes (collectively called Model A300-600 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, 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.
2016-25-24: We are adopting a new airworthiness directive (AD) for certain Airbus Model A319, A320, and A321 series airplanes. This AD requires repetitive general visual inspections for broken battery retaining rods and replacement if necessary. We are issuing this AD to address the unsafe condition on these products.
2021-14-07: The FAA is superseding Airworthiness Directive (AD) 2003-25-01 which applied to certain Eurocopter France (now Airbus Helicopters) Models AS332C, AS332C1, AS332L, AS332L1, AS350B, AS350BA, AS350B1, AS350B2, AS350B3, AS350D, AS355E, AS355F, AS355F1, AS355F2, and AS355N helicopters. AD 2003-25-01 required modifying and re-identifying the hoist operator control unit and replacing certain fuses. This AD was prompted by the identification of multiple errors in the applicable service information for the AS350-series and AS355-series helicopters and of other needed changes. This AD retains certain requirements of AD 2003-25-01, revises the applicability, and requires using corrected service information. This AD also requires reporting certain information and prohibits the installation of an affected hoist until the required actions are accomplished. The FAA is issuing this AD to address the unsafe condition on these products.
76-09-07: 76-09-07 LOCKHEED-CALIFORNIA COMPANY: Amendment 39-2596. Applies to Lockheed-California Company Model L-1011-385 series airplanes, certificated in all categories, that have a Part I configuration center engine S-duct installed (See NOTE). Compliance required as indicated. To prevent possible separation of the center engine S-duct assembly due to failure of the articulating joints, accomplish the following: (a) For airplanes with 4,500 or more hours' time in service on July 14, 1975, comply with paragraphs (c) and (d) within the next 250 hours' time in service after July 14, 1975 unless already accomplished. (b) For airplanes with less than 4,500 hours' time in service on July 14, 1975, comply with paragraphs (c) and (d) within the next 250 hours' time in service after July 14, 1975 or before the accumulation of 4,500 hours' time in service, whichever occurs later, unless already accomplished. (c) Accomplish the following actions in accordance with paragraphs 2A(1) and 2A(2) of Lockheed Alert Service Bulletin 093-54-A019, Revision 2, dated April 20, 1976, or later FAA- approved revision, or an FAA-approved equivalent. (1) Visually inspect all alignments units (leaf springs and spring cartridges) installed at the forward articulating joint of the S-duct assembly for damaged units or worn attachment holes; and, if damage is found, repair, as necessary. (2) Visually inspect the forward ring of S-duct assembly articulating joint, for cracks at all alignment unit locations. If cracks are found, either accomplish the modifications described in paragraph (f), below, or repair, as necessary, before further flight. (d) Accomplish the following actions in accordance with paragraphs 2A(3) or 2A(4) or 2A(5) of Lockheed Alert Service Bulletin 093-54-A019, Revision 2, dated April 20, 1976, or later FAA-approved revision, or an FAA-approved equivalent. (1) Inspect the upper half of the forward ring on the aft side of the S-duct assembly articulating joint for cracks using a dye penetrant method. (2) If cracks are found, either accomplish the modifications described in paragraph (f), below, or repair, as necessary, before further flight. (e) Until the center engine S-duct modifications of paragraph (f) have been accomplished, repeat compliance with the inspection and repair requirements of paragraphs (c) and (d) at intervals not to exceed 800 or 1600 or 2400 hours' time in service since the last inspection, whichever is appropriate, in accordance with the conditions and repetitive inspection interval criteria established by paragraphs 2A(1), 2A(2), and 2A(3) or 2A(4) or 2A(5) of Lockheed Alert Service Bulletin 093-54-A019, Revision 2, dated April 20, 1976, or later FAA-approved revision or an FAA-approved equivalent. (f) The repetitive inspections required by paragraph (e) may be discontinued after the center engine S-duct forward articulating joint is modified in accordance with Part I of Lockheed ServiceBulletin 093-54-019, dated November 4, 1975, or later FAA-approved revision, or an equivalent approved by the Chief, Aircraft Engineering Division, FAA Western Region. (g) Special flight permits may be issued in accordance with FAR's 21.197 and 21.199 to operate airplanes to a base where the inspections required by this AD can be performed. NOTE: For the purpose of determining applicability, Part I configuration center engine S- ducts are identified as those utilizing two leaf spring and twelve spring cartridge type alighment units around the forward articulating joint as described by Lockheed Alert Service Bulletin 093-54- A019. Part I configuration S-duct may be found on, but not necessarily limited to, aircraft serials 1002 through 1037. This supersedes Amendment 39-2256, AD 75-14-07, as amended by Amendments 39- 2299 and 39-2360. Compliance with AD 75-14-07 may be credited for compliance with either the initial inspection requirements of paragraph (a) or (b) and the repetitive inspection requirements of paragraph (e). This amendment becomes effective May 10, 1976.
2016-25-09: We are superseding Airworthiness Directive (AD) 2012-22-02 for certain The Boeing Company Model 747-400, -400D, and -400F series airplanes. AD 2012-22-02 required measuring the web at station (STA) 320 and, depending on findings, various inspections for cracks and missing fasteners, web and fastener replacement, and related investigative and corrective actions if necessary. This new AD requires, for certain airplanes, replacement of the web, including related investigative and corrective actions if necessary. This AD was prompted by a determination that there were no inspection or repair procedures included in AD 2012-22-02 for airplanes with a certain crown frame web thickness. We are issuing this AD to address the unsafe condition on these products.
2004-13-14: This amendment adopts a new airworthiness directive (AD), applicable to all Airbus Model A300 B2 series airplanes; Model A300 B4 series airplanes; and Model A300 B4-600, B4-600R, C4 605R Variant F, and F4-600R (collectively called A300-600) series airplanes; that requires inspection of the label of certain slat friction brakes for correct label wording, and corrective actions if necessary. This AD also provides for optional terminating actions for certain repetitive corrective actions. These actions are necessary to find and fix incorrect labels on the housings of the slat friction brakes, which may lead to the use of unapproved oil in the brakes. Use of unapproved oil could affect the efficiency of the brakes and lead to failure of the brakes to maintain proper slat orientation in the event of a rupture of the slat drive shaft, consequent uncommanded retraction of the slat, and reduced controllability of the airplane. This action is intended to address the identified unsafe condition.
87-25-09: 87-25-09 BOEING: Amendment 39-5791. Applies to Model 767 series airplanes listed in Boeing Alert Service Bulletin 767-25A0092, dated June 18, 1987, certificated in any category. \n\n\tCompliance required as indicated, unless previously accomplished. \n\n\tTo ensure that the entry and service doors cannot become jammed due to a loose mid liner dust cover, accomplish the following: \n\n\tA.\tWithin the next 30 days after the effective date of this AD, and thereafter at intervals not to exceed 90 days, visually inspect the door mid liner for evidence of dust cover disbonding. Disbonding is identified by the dust cover moving away from edges of the reveal. If the dust cover shows evidence of disbonding, prior to further flight, modify the dust cover in accordance with Boeing Alert Service Bulletin 767-25A0092, dated June 18, 1987, or later FAA- approved revisions. \n\n\tB.\tModification of the dust cover in accordance with Boeing Service Bulletin 767- 25A0092, dated June 18, 1987, or later FAA-approved revisions, constitutes terminating action for the repetitive inspection requirements of paragraph A., above. \n\n\tC.\tWithin the next 18 months after the effective date of this AD, modify all dust covers in accordance with Boeing Service Bulletin 767-25A0092, dated June 18, 1987, or later FAA-approved revisions. \n\n\tD.\tAn alternate means of compliance or adjustment of the compliance time, which provides an acceptable level of safety and which has the concurrence of an FAA Principal Maintenance Inspector, may be used when approved by the Manager, Seattle Aircraft Certification Office, FAA, Northwest Mountain Region. \n\n\tE.\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 inspections and/or modifications required by this AD. \n\n\tAll persons affected by this directive who have not already received the appropriate service documents from the manufacturer may obtain copies upon request to the Boeing Commercial Airplane Company, P.O. Box 3707, Seattle, Washington 98124-2207. These documents may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or Seattle Aircraft Certification Office, FAA, Northwest Mountain Region, 9010 East Marginal Way South, Seattle, Washington. \n\n\tThis amendment becomes effective January 19, 1988.
2016-25-12: We are adopting a new airworthiness directive (AD) for all M7 Aerospace LLC Models SA226-AT, SA226-T, SA226-T(B), SA226-TC, SA227-AC (C-26A), SA227-AT, SA227-BC (C-26A), SA227-CC, SA227-DC (C-26B), and SA227-TT airplanes. This AD was prompted by corrosion and stress corrosion cracking of the pitch trim actuator upper attach fittings of the horizontal stabilizer front spar. This AD requires repetitive inspections with replacement of fittings as necessary. We are issuing this AD to correct the unsafe condition on these products.
96-18-12: This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A320 series airplanes, that requires an inspection to detect damage to the electrical wiring of the fuel tank of the wings and to verify if the proper P-clip is installed in the electrical wiring. This amendment also requires re-fitting any proper P-clip, replacing any improper P-clip with a new P-clip, and repairing damaged electrical wiring. This amendment is prompted by a report that incorrect P-clips were found installed in the electrical wiring of the fuel system on these airplanes. The actions specified by this AD are intended to ensure that the proper P-clips are installed. Improper P-clips could fail to adequately safeguard the fuel tank of the wing against a lightning strike, which could result in electrical arcing and resultant fire.
2021-26-20: The FAA is adopting a new airworthiness directive (AD) for all Airbus SAS Model A300 B4-600, B4-600R, and F4-600R series airplanes, and Model A300 C4-605R Variant F airplanes (collectively called Model A300-600 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, 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.
2016-24-07: We are adopting a new airworthiness directive (AD) for certain Dassault Aviation Model FALCON 7X airplanes. This AD was prompted by investigation results that determined that a certain thickness of the fuel tank panels is insufficient to meet the certification requirements. This AD requires inspecting the thickness of the fuel tank panels, and repair if necessary. We are issuing this AD to address the unsafe condition on these products.
85-21-03: 85-21-03 McDONNELL DOUGLAS: Amendment 39-5143. Applies to McDonnell Douglas Model DC-8-71, -72, and -73 series airplanes certificated in any category. To minimize inflight shutdowns due to oil loss, accomplish the following unless previously accomplished: \n\n\tA.\tWithin eighteen (18) months, or three thousand (3,000) landings, whichever occurs earlier, after the effective date of this AD, modify at least one engine on each side of the airplane in accordance with paragraph B., below, and complete the modifications on all engines within thirty-six (36) months, or six thousand (6,000) landings, whichever occurs earlier after the effective date of this AD. \n\n\tB.\tAccomplish the modification described in paragraph A., above, in accordance with McDonnell Douglas Service Bulletin 71-96, dated February 12, 1985, or later revisions approved by the Manager, Los Angeles Aircraft Certification Office, FAA, Northwest Mountain Region. \n\n\tC.\tSpecial flight permits may be issued in accordancewith FAR 21.197 and 21.199 to operate airplanes to a base in order to comply with the requirements of this AD. \n\n\tD.\tAlternate 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. \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 the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or at 4344 Donald Douglas Drive, Long Beach, California. \n\n\tThis amendment becomes effective November 4, 1985.
87-14-05: 87-14-05 DEHAVILLAND AIRCRAFT COMPANY OF CANADA, A DIVISION OF BOEING OF CANADA, LTD.: Amendment 39-5676. Applies to Models DHC-8-101 and DHC-8-102 series airplanes, serial numbers 3 through 83, certificated in any category. Compliance required as indicated, unless previously accomplished. To prevent failure of the main landing gear yoke pin, accomplish the following: A. Within 25 landings after the effective date of this AD: 1. Inspect both main landing gears to determine the yoke pin part number, in accordance with Paragraph 1, Accomplishment Instructions of de Havilland Aircraft Company of Canada Service Bulletin 8-32-56, dated May 8, 1987. 2. Reidentify the shock strut, as necessary, in accordance with Paragraph 1, Accomplishment Instructions of de Havilland Aircraft Company of Canada Service Bulletin 8-32- 56, dated May 8, 1987. B. If yoke pin P/N 10150-3 is installed, replace it with yoke pin P/N 10150-5, in accordance with the following schedule:1. For Model DHC-8-101 airplanes (33,000 lb. airplane): prior to the accumulation of 5,500 flights since installation of the yoke pin. 2. For Model DHC-8-102 airplanes (34,500 lb. airplane): prior to the accumulation of 4,700 flights since installation of the yoke pin. C. 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. 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, New York Aircraft Certification Office, FAA, New England Region. All persons affected by this directive who have not already received the appropriate service information from the manufacturer may obtain copies upon request to The de Havilland Aircraft Company of Canada, A Division of Boeing of Canada, Ltd., Garratt Boulevard, Downsview, Ontario M3K 1Y5, Canada. This information may be examined at FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or FAA, New England Region, New York Aircraft Certification Office, 181 South Franklin Avenue, Valley Stream, New York. This amendment becomes effective August 1, 1987.
91-06-03: 91-06-03 BOEING: Amendment 39-6923. Docket No. 90-NM-152-AD. \n\n\tApplicability: Model 747 series airplanes, line numbers 001 through 045, certificated in any category. \n\n\tCompliance: Required as indicated, unless previously accomplished. \n\n\tTo prevent sudden cabin pressure loss, accomplish the following: \n\n\tA.\tWithin the next 500 flight cycles after the effective date of this AD, or prior to the accumulation of 12,000 total flight cycles, whichever occurs later, perform a detailed visual inspection for cracks of the Section 42 fuselage frame web at the stringer cutout from body station (BS) 540 to BS 920, Stringer (S) 8L to S-8R. Repeat this inspection thereafter at intervals not to exceed 3,000 flight cycles. \n\n\tB.\tIf cracking is found as the result of the inspections required by paragraph A. of this AD, prior to further flight, repair the fuselage frame web in accordance with the Boeing 747 Structural Repair Manual (SRM), Section 53-10-04, Figure 4 or Figure 35; or in a manner approved by the Manager, Seattle Aircraft Certification Office, FAA, Transport Airplane Directorate. \n\n\tC.\tAn 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, Seattle Aircraft Certification Office (ACO), Transport Airplane Directorate. \n\n\tNOTE: The request should be submitted directly to the Manager, Seattle ACO, and a copy sent to the cognizant FAA Principal Inspector (PI). The PI will then forward comments or concurrence to the Seattle ACO. \n\n\tD.\tSpecial 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. \n\n\tAll persons affected by this directive who have not already received the appropriate service documents from the manufacturer may obtain copies upon request to Boeing Commercial Airplane Group, P.O. Box 3707, Seattle, Washington 98124. These documents may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, Washington. \n\n\tThis amendment (39-6923, AD 91-06-03) becomes effective on April 8, 1991.
2016-20-09: We are adopting a new airworthiness directive (AD) for certain Bombardier, Inc. Model CL-600-2A12 (CL-601 Variant), and CL-600-2B16 (CL-601-3A, CL-601-3R, and CL-604 Variants) airplanes. This AD was prompted by a report that a potential chafing condition exists between the negative-G fuel feed drain line of the auxiliary power unit (APU) and its surrounding structure and components. This AD requires, for certain airplanes, a detailed inspection for chafing conditions of the negative-G fuel feed drain line of the APU, and corrective actions if necessary. For certain other airplanes, this AD requires replacement of the APU negative-G fuel feed tube assembly and the drain line. We are issuing this AD to address the unsafe condition on these products.
86-07-07: 86-07-07 GARLICK HELICOPTERS, HAWKINS AND POWERS AVIATION, INC.. INTERNATIONAL HELICOPTERS, INC., PILOT PERSONNEL INTERNATIONAL, INC., WILCO AVIATION: Amendment 39-5274. Applies to Model UH-1B helicopters modified by Garlick Helicopters, Hawkins and Powers Aviation, Inc., International Helicopters, Inc., Pilot Personnel International, Inc., and Wilco Aviation certified in any category that have a Bell Helicopter Textron, Inc., Part Number (P/N) 204-011-128-1 universal on the main rotor pitch change link. Unless already accomplished, compliance is required within 15 days after the effective date of this AD or the next 10 hours time in service, whichever occurs first. To prevent loss of main rotor control, accomplish the following: (a) Inspect the P/N 204-011-128-1 universal assembly on the pitch change control link of the main rotor for Arko Precision Machinists' supplier P/N "DW-6ZZ." If found, replace before further flight with a serviceable assembly. (b) If the P/N "DW-6ZZ" is missing or cannot be seen, apply MIL-G-81322 grease to each of the two grease fittings on the universal. If the grease does not purge past the seals, replace the P/N 204-011-128-1 universal before further flight with a serviceable assembly. (c) P/N 212-010-412-1 universal is an acceptable alternate replacement for P/N 204-011-128-1 and may be considered interchangeable. (d) Any alternate method of compliance which provides an equivalent level of safety with this AD may be used when approved by the Manager, Helicopter Certification Branch, Federal Aviation Administration, 4400 Blue Mound Road, Fort Worth, Texas 76106. This amendment becomes effective April 25, 1986.
2004-13-04: This amendment adopts a new airworthiness directive (AD), applicable to certain Short Brothers Model SD3-SHERPA series airplanes, that requires a repetitive detailed inspection of the stub wing shear decks for corrosion and abnormal wear on and around the retaining pin in the main landing gear (MLG) forward pintle pin; and corrective action, if necessary. This AD also provides an optional terminating action. These actions are necessary to detect and correct corrosion and abnormal wear to the top and bottom shear decks, which could result in damage to the MLG and consequent reduced controllability of the airplane on landing. This action is intended to address the identified unsafe condition.
87-15-51: 87-15-51 LOCKHEED-CALIFORNIA COMPANY: Amendment 39-5701. Applies to Lockheed-California Model L-1011-385 series airplanes, certificated in any category, which have stainless steel bushings installed in the retract lugs of the left and/or the right main landing gear (MLG) shock strut cylinder. Compliance required as indicated, unless previously accomplished. To detect cracks and prevent structural failure of the MLG shock strut cylinder, accomplish the following: A. Within 10 days after the effective date of this AD, unless previously accomplished within the last 400 landings, and thereafter at intervals not to exceed 400 landings, perform an ultrasonic inspection of the inboard retract lugs of both the left and right MLG shock strut cylinder, following the procedure specified in Section 2, Accomplishment Instructions, of Lockheed-California L-1011 Service Bulletin 093-32-A211, Revision 1, dated October 26, 1982, or later revisions approved by the Manager, Los Angeles Aircraft Certification Office, FAA, Northwest Mountain Region. B. Any MLG shock strut cylinders that are found cracked must be repaired or replaced prior to further flight, in a manner approved by the Manager, Los Angeles Aircraft Certification Office, FAA, Northwest Mountain Region. C. 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. 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 inspection requirements of this AD. All persons affected by this directive who have not already received the appropriate service document from the manufacturer, may obtain copies upon request to Lockheed-California Company, P.O. Box 551, Burbank, California 91520, Attention: Commercial Order Administration, Dept, 65-33, U-33, B-1. This document may be examined at theFAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or 4344 Donald Douglas Drive, Long Beach, California. This amendment, 39-5701, becomes effective August 24, 1987, as to all persons, except those persons to whom it was made immediately effective by telegraphic AD T87-15-51 issued July 22, 1987.
2022-02-10: The FAA is adopting a new airworthiness directive (AD) for certain Dassault Aviation Model FALCON 7X, FALCON 900EX, and FALCON 2000EX airplanes. This AD was prompted by a report of an improper heat treatment process applied during the manufacturing of certain titanium screws. This AD requires replacement of certain titanium screws, 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.