Results
68-26-06: 68-26-06 BEECH: Amdt. 39-702 as amended by Amendment 39-712, 39-1040 and 39- 1469 is further amended by Amendment 39-1776. Applies to Models 95-55, 95-A55, B95A, D95A, E95, 95-B55, 95-B55A, 95-B55B, 95- C55, 95-C55A, D55 and D55A Airplanes. NOTE: Amendment 39-1776, effective February 5, 1974, removed the Model 95 and B95 airplanes from the applicability block of this AD. Placard and Flight Manual revisions previously required to be installed in these model airplanes by this AD may be removed. Compliance required as indicated unless already accomplished. To prevent engine power loss accomplish the following: (A) Effective immediately, turning type takeoffs or a takeoff immediately following a fast taxi turn is prohibited. (B) Within 10 hours' time in service after the effective date of this airworthiness directive, either install a permanent type placard on the lower portion of the pilot's shock mounted instrument panel utilizing a minimum of 1/8 inchhigh letters or at any equivalent location approved by the FAA with the following wording: "TAKE OFF AND LAND ON MAIN TANKS ONLY. TURNING TYPE TAKEOFFS OR TAKEOFFS IMMEDIATELY FOLLOWING FAST TAXI TURNS PROHIBITED. REFER TO FAA FLIGHT MANUAL FOR OTHER FUEL SYSTEM LIMITATIONS." and revise the Airplane Flight Manual to include Beech Part No. 130776 AFM Supplement dated November 27, 1968 with the exception that the portion a. and b. under "For Ground Operation" is to be deleted. (C) Airplanes in which fuel cells have been installed in both wings in accordance with Beech Service Instructions 0459-281 (Beech Kit Nos. 35-9009-1S, 35-9009-2S, 35-9009-3S or 35-9009-4S) or 365-281, Rev. 1 (Beech Kits 35-9009S or 35-9009-5S), or later revisions, or which have fuel reservoirs installed in both wings per Beech Kit 35-9012 or a fuel reservoir in one wing and a baffled cell in the other, are exempt from compliance with this AD. When either of these installations has been accomplished, the placard and the revisions to the Airplane Flight Manual required by Paragraph B of the AD may be removed. The limitations for baffled cells in Airplane Flight Manual Supplement, P/N 96-590011-7 dated February 11, 1972, or later revision, are applicable to installation of either baffled cells or fuel reservoirs. NOTE: The operator may make and install the above placard. 3/16 inch high letters must be used if the placard is installed at a location other than the pilot's shock mounted instrument panel. Amendment 39-702 became effective January 1, 1969. Amendment 39-712 became effective January 27, 1969. Amendment 39-1040 became effective July 24, 1970. Amendment 39-1469 became effective June 28, 1972. This amendment 39-1776 becomes effective February 5, 1974.
2015-26-07: We are adopting a new airworthiness directive (AD) for all The Boeing Company Model 767-200, -300, and -300F series airplanes. This AD was prompted by a finding that certain barrel nuts installed at the vertical fin may be subject to stress corrosion and cracking. This AD requires either repetitive inspections of vertical fin barrel nuts for corrosion or a magnetic check to identify certain barrel nuts, and corrective actions if necessary. We are issuing this AD to detect and correct corroded and loose barrel nuts that attach the vertical fin to body section 48; this condition could result in reduced structural integrity of the vertical fin attachment joint, loss of the vertical fin, and consequent loss of controllability of the airplane.
89-08-02: 89-08-02 GROB WERKE GMBH & COMPANY KG (BURKHART GROB): Amendment 39-6174. Applicability: Models G103 TWIN II and G103 A TWIN II ACRO (serial numbers 3501 through 3878, and 33879 through 34078) gliders. Compliance: As indicated in the body of the AD. To preclude failure of the flight control systems, accomplish the following: (a) Within the next 10 hours time-in-service after the effective date of this AD, inspect the control systems for weld cracks in accordance with the instructions contained in Grob Service Bulletin (S/B) TM315-37, dated July 22, 1988. (b) If weld cracks are found per the inspection specified in paragraph (a) of this AD, prior to further flight repair the cracks and modify the glider in accordance with the instructions in the above referenced S/B. (c) If weld cracks are not found per the inspection specified in paragraph (a) of this AD, within the next 100 hours time-in-service after the effective date of this AD, modify the gliderin accordance with the instructions in the above referenced S/B. (d) An equivalent means of compliance with this AD may be used if approved by the Manager, Brussels Aircraft Certification Staff, AEU-100, FAA, c/o American Embassy, 15 Rue de la Loi B1040, Brussels, Belgium. All persons affected by this directive may obtain copies of the documents referred to herein upon request to Grob Systems, Incorporated, Aircraft Division, I-75 and Airport Drive, Bluffton, Ohio 45817; or may examine these documents at the FAA, Office of the Assistant Chief Counsel, Room 1558, 601 East 12th Street, Kansas City, Missouri 64106. This amendment (39-6174, AD 89-08-02) becomes effective on April 27, 1989.
88-12-09: 88-12-09 BOEING HELICOPTER COMPANY (BOEING VERTOL; VERTOL) AND KAWASAKI HEAVY INDUSTRIES, LTD: Amendment 39-5919. Applies to Boeing Helicopter Company Model 107-II and Kawasaki Model KV107- IIA helicopters, certificated in any category (Airworthiness Docket 88-ASW-10). Compliance is required as indicated, unless already accomplished. To prevent possible hazards in flight associated with a cracked aft main rotor shaft slider guide, Part Number (P/N) 107R3574-1, accomplish the following: (a) Within the next 10 hours time in service from the effective date of this AD, or before the accumulation of 1,200 hours time in service, whichever comes later, perform a dye penetrant inspection of the two forward lug areas of the aft main rotor shaft slider guide for cracks in accordance with paragraph 2, "Accomplishment Instructions," Boeing Helicopter Co., Service Bulletin No. 107-370R1, dated September 21, 1987. (b) After the initial inspection of paragraph (a), repeat the dye penetrant inspection at intervals not to exceed 50 hours time in service from the last inspection. (c) Remove cracked slider guides from service and replace with a serviceable part prior to further flight. (d) Upon submission of substantiating data by an owner or operator through an FAA maintenance inspector, the Manager, New York Aircraft Certification Office, FAA, New England Region, may adjust the compliance times specified in this AD. (e) An alternate method of compliance which provides an equivalent level of safety may be used when approved by the Manager, New York Aircraft Certification Office, 181 South Franklin Avenue, Valley Stream, New York 11581. (f) In accordance with FAR sections 21.197, and 21.199, flight is permitted to a base where the requirements of this AD may be accomplished. The procedures shall be done in accordance with paragraph 2, "Accomplishment Instructions," Boeing Helicopter Co., Service Bulletin No. 107-370R1, dated September 21, 1987. This incorporation by reference was approved by the Director of the Federal Register in Accordance with 5 U.S.C. 552(a) and 1 CFR Part 51. Copies may be obtained from Boeing Helicopter Company, Boeing Center, P.O. Box 16858, Philadelphia, Pennsylvania 19141. These documents may be examined at the Office of the Regional Counsel, FAA, Southwest Region, 4400 Blue Mound Road, Fort Worth, Texas, or the Office of the Federal Register, 1100 L Street, N.W., Room 8401, Washington, D.C. This amendment, 39-5919, becomes effective June 2, 1988.
89-03-09: 89-03-09 AIRBUS INDUSTRIE: Amendment 39-6123. Applicability: Model A300 series airplanes, as listed in Airbus Industrie Service Bulletin A300-53-220, Revision 1, dated July 8, 1988. Compliance: Required as indicated, unless previously accomplished. To prevent separation of the rear passenger/crew door from the airplane and subsequent rapid decompression, accomplish the following: A. Prior to the accumulation of 8,000 landings or within the next 1,000 landings after the effective date of this AD, whichever occurs later, inspect frame 73A RH and LH between beams 5 and 7, in accordance with Airbus Industrie Service Bulletin A300-53-220, Revision 1, dated July 8, 1988. 1. If cracks are detected that are less than 0.4 inch, modify the frame within the next 2,500 landings, in accordance with Airbus Industrie Service Bulletin A300-53-221, Revision 2, dated October 13, 1988. The inspection must be repeated at intervals not to exceed 1,250 landings until the modification is accomplished. 2. If cracks are detected that are equal to or more than 0.4 inch but less than 0.8 inch, modify the frame within the next 1,500 landings, in accordance with Airbus Industrie Service Bulletin A300-53-221, Revision 2, dated October 13, 1988. The inspection must be repeated at intervals not to exceed 750 landings until the modification is accomplished. 3. If cracks are detected that are equal to or more than 0.8 inch, prior to further flight, modify the frame in accordance with Airbus Industrie Service Bulletin A300-53-221, Revision 2, dated October 13, 1988. 4. If no cracks are detected, repeat the inspection at intervals not to exceed 4,000 landings. B. The repetitive inspections required by paragraph A., above, may be terminated following completion of the modification of the door frame structure, in accordance with Airbus Service Bulletin A300-53-221, Revision 2, dated October 13, 1988. 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 Manger, 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 modifications required by 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 Airbus Industrie, Airbus Support Division, Avenue Didier Daurat, 31700 Blagnac, France. This document may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or the Seattle Aircraft Certification Office, 9010 East Marginal Way South, Seattle, Washington. This amendment (39-6123, AD 89-03-09) becomes effective March 7, 1989.
74-10-07: 74-10-07 DETROIT DIESEL ALLISON AEROPRODUCTS: Amendment 39-1839. Applies to Detroit Diesel Allison Aeroproducts Model A6441FN-606 and -606A propellers. Compliance required as indicated, unless already accomplished: (a) For propeller blades and hubs, installed on an aircraft prior to the effective date of this Airworthiness Directive, that have been stripped, inspected for corrosion, and replated per Detroit Diesel Allison Overhaul Manual 1AC3 or an equivalent procedure approved by the Chief, Engineering and Manufacturing Branch, FAA, Great Lakes Region, within the preceding 27 months prior to the effective date of this AD, remove from service before 36 months since date of initial installation on an aircraft following stripping, inspecting for corrosion and replating. (b) For propeller blades and hubs, installed on an aircraft prior to the effective date of this AD, that have been stripped, inspected for corrosion and replated per Detroit Diesel Overhaul Manual 1AC3or equivalent, but this work has not been accomplished within the preceding 27 months prior to the effective date of this AD, remove from service in accordance with the following schedule: On the effective date of this AD, the number of months since the date of initial installation on an aircraft after being stripped, inspected for corrosion, and replated as described above: Over 55 months - Remove from service by: 25 flight hours after effective date of this AD. 55 months - Remove from service by: May 11, 1974 53-54 months - Remove from service by: June 11, 1974 48-52 months - Remove from service by: July 11, 1974 42-47 months - Remove from service by: October 11, 1974 27-41 months - Remove from service by: January 11, 1975 (c) New propeller blades and hubs may continue in service 40 months since initial installation on aircraft. However, those in service, at the effective date of this AD, more than 31 months since initial installation on aircraft shall be removed from service at or before the time or dates specified in the schedule under paragraph (b). (d) Propeller blades and hubs removed from service pursuant to paragraphs (a), (b), or (c), stripped, inspected for corrosion and replated as set forth above, and installed on an aircraft shall thereafter be removed from service, stripped, inspected for corrosion, and replated as described above at intervals not to exceed 36 months. (e) Propeller blades and hubs initially installed on an aircraft on or after the effective date of this AD shall be stripped, inspected for corrosion and replated, as described above, at intervals no greater than 36 months from date of initial installation; provided however, that new propeller blades and hubs may continue in service for 40 months since initial installation. (f) Extensions of compliance times or date may be obtained from the Chief, Engineering and Manufacturing Branch, Federal Aviation Administration, Great Lakes Region, upon submission of acceptable substantiating data to support the extension. This amendment is effective May 17, 1974, and was effective April 11, 1974, for all recipients of the telegram dated April 11, 1974, which contained this amendment.
2024-25-12: The FAA is adopting a new airworthiness directive (AD) for all Airbus SAS Model A319-111, -112, -113, -114, -115, -131, -132, -133, - 151N, and -153N airplanes; A320 series airplanes; and A321-211, -212, - 213, -231, -232, -251N, -252N, -253N, -271N, -272N, -251NX, -252NX, - 253NX, -271NX, and -272NX airplanes. This AD was prompted by a determination that a damage-tolerance and fatigue reassessment of nose landing gear (NLG) repairs is necessary for certain parts fitted on airplanes approved for operation in the Commonwealth of Independent States (CIS). This AD requires repair and replacement of all affected parts, and introduces restrictions for the installation of affected parts, 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.
2009-02-05: We are adopting a new airworthiness directive (AD) for certain Boeing Model 777 airplanes. This AD requires installing software upgrades to the airplane information management system (AIMS) located in the flight compartment. This AD results from an investigation that revealed that detrimental effects could occur on certain AIMS software during flight. We are issuing this AD to prevent an unannunciated loss of cabin pressure. If an undetected loss of pressure event were to cause an unsafe pressure in the cabin, the flight crew could become incapacitated.
87-16-13: 87-16-13 BOEING: Amendment 39-5702. Applies to Model 747 series airplanes, as listed in Boeing Alert Service Bulletin 747-53A2279, dated January 15, 1987, certificated in any category. Compliance required as indicated, unless previously accomplished. \n\n\tTo detect disbonding of the upper body tear straps in body section 46, accomplish the following, unless already accomplished: \n\n\tA.\tWithin 250 landings after the effective date of this AD for airplanes line number 1 through 230, and within 750 landings after the effective date of this AD, for airplanes line number 231 through 349, perform an ultrasonic inspection of tear straps for disbonding in accordance with Boeing Alert Service Bulletin 747-53A2279, Revision 1, dated May 7, 1987, or later FAA-approved revisions. \n\n\tB.\tIf no evidence of unbonded areas are found, reinspect those areas at intervals not to exceed 6 years. \n\n\tC.\tIf evidence of unbonded areas is found, and the unbonded area between any two adjacent stringersdoes not exceed 60 percent of the total tear strap area between these stringers, reinspect those areas at intervals not to exceed the limits allowed by the chart in Figure 2 or 4, as appropriate, of Boeing Alert Service Bulletin 747-53A2279, Revision 1, dated May 7, 1987, or later FAA-approved revisions. \n\n\tD.\tIf evidence of unbonded areas is found, and the unbonded area between any two adjacent stringers exceeds 60 percent of the total tear strap area between these stringers, repair those areas prior to further flight in accordance with Boeing Alert Service Bulletin 747-53A2279, Revision 1, dated May 7, 1987, or later FAA-approved revisions. If blind fasteners are used, visually reinspect installation at intervals not to exceed 1,000 landings for loose or missing fasteners, cracks, or corrosion. \n\n\tE.\tTerminating action for the inspections required by this AD is the installation of solid fasteners at all affected tear strap locations in accordance with Boeing Alert Service Bulletin 747-53A2279, Revision 1, dated May 7, 1987, or later FAA-approved revisions. \n\n\tF.\tFor the purpose of complying with this AD, the number of landings may be determined to equal the number of pressurization cycles where the cabin pressure differential was greater than 2.0 PSI. \n\n\tG.\tAn alternate means of compliance or adjustment of the compliance time, which provide 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\tH.\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. Box3707, Seattle, Washington 98124. These documents may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or Seattle Aircraft Certification Office, 9010 East Marginal Way South, Seattle, Washington. \n\n\tThis amendment, 39-5702, becomes effective September 13, 1987.
2002-20-03: This amendment adopts a new airworthiness directive (AD) for the specified Eurocopter France (ECF) model helicopters that requires a one-time measurement of the electrical resistance between the ferry fuel tank (tank) electrostatic ground connector and the tank filler neck before the next refueling of an installed tank or before the first fueling after installing a tank. If the electrical resistance has a value more than 1.5 milliohms, this AD prohibits refueling the tank. This amendment is prompted by reports of an inadequate electrical bond between the electrostatic ground connector and its support on several tank installations. The actions specified by this AD are intended to prevent refueling a tank that is not adequately electrically bonded, which could generate an electric arc between the refueling nozzle and the tank, causing an explosion.
89-20-04: 89-20-04 BOEING: Amendment 39-6326. (Docket No. 89-NM-152-AD) \n\tApplicability: Model 727 series airplanes, line numbers 001 through 047, certificated in any category. \n\n\tCompliance: Required as indicated, unless previously accomplished. \n\n\tTo prevent rapid decompression of the airplane, accomplish the following: \n\n\tA.\tWithin the next 15 days after receipt of AD T89-14-51, dated June 30, 1989, conduct an internal detailed visual inspection for cracks of the fuselage skin at lap joints located at stringer (S) 14L from body station (BS) 440 to BS 720, and at S-14R from BS 440 to BS 540, in accordance with the following instructions: \n\n\t\t1.\tRemove seats, sidewall lining, and insulation as required to gain access to the internal portion of the fuselage skin at lap joints S-14L from BS 440 to BS 720, and at S-14R from BS 440 to BS 540. \n\n\t\t2.\tAccomplish a detailed visual inspection of the fuselage skin along the bottom fastener row of the lap joint. \n\n\tNOTE: The fastenerrow is immediately below the stringer. \n\n\t\t3.\tConfirm all cracks with dye penetrant inspection or high frequency eddy current inspection. \n\n\t\t4.\tIf any cracks are detected, repair prior to further flight, in accordance with Boeing Drawing Number 65C35368 or 65C35369. \n\n\tB.\tWithin the next 500 landings after conducting the inspection required by paragraph A., above, or ten days after the effective date of this AD, whichever occurs later, accomplish the inspection specified in either paragraph B.1. or B.2., below: \n\n\t\t1.\tConduct a high frequency eddy current (HFEC) inspection as follows: \n\n\t\t\ta.\tRemove seats, sidewall lining, and insulation as required to gain access to the internal portion of the fuselage skin at lap joints S-14L from BS 440 to BS 720, and at S-14R from BS 440 to BS 540. \n\n\t\t\tb.\tConduct an HFEC inspection of the lap joints, in accordance with the Accomplishment Instructions in Boeing Alert Service Bulletin 727-53A0200, Revision 1, dated July 20, 1989.2.\tConduct a low frequency eddy current (LFEC) inspection of the lap joints, in accordance with the Accomplishment Instructions in Boeing Alert Service Bulletin 727-53A0200, Revision 1, dated July 20, 1989. \n\n\tC.\tRepeat the inspections required by paragraph B., above, at the following intervals: \n\n\t\t1.\tIf the immediately preceding inspection was conducted using HFEC techniques, conduct the next inspection within 2,000 landings. \n\n\t\t2.\tIf the immediately preceding inspection was conducted using LFEC techniques, conduct the next inspection within 1,000 landings. \n\n\tD.\tIf any cracks are detected, repair prior to further flight, in accordance with Boeing Drawing 65C35368 or 65C35369. This repair constitutes terminating action for the inspections required by paragraph B.2. or C., above, in the areas repaired. \n\n\tE.\tModification of the lap joints at S-14L from BS 440 to BS 720, and at S-14R from BS 440 to BS 540, in accordance with Boeing Drawing 65C35402 constitutes terminating action for the repetitive inspections required by paragraphs C.1. and C.2., above. \n\n\tF.\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. \n\n\tNOTE: The request should be forwarded through an FAA Principal Maintenance Inspector (PMI), who will either concur or comment and then send it to the Manager, Seattle Aircraft Certification Office. \n\n\tG.\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 information from the manufacturer may obtain copies upon request to Boeing Commercial Airplanes, P.O. Box 3707, Seattle, Washington 98124. This information may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 17900 Pacific Highway South, Seattle, Washington, or Seattle Aircraft Certification Office 9010 East Marginal Way South, Seattle, Washington. \n\n\tThis AD supersedes Telegraphic Airworthiness Directive T89-14-51, issued on June 30, 1989. \n\tThis amendment (39-6326, AD 89-20-04) becomes effective on October 6, 1989.
2024-26-02: The FAA is superseding Airworthiness Directive (AD) 2021-07-13 for certain Pacific Scientific Company rotary buckle assemblies (buckles). AD 2021-07-13 required inspecting each specified buckle including its buckle handle vane and prohibited installing affected buckles. This AD was prompted by the publication of an updated service bulletin, which revises the applicability based on date of manufacture of the affected buckles. This AD retains certain requirements of AD 2021-07-13, reduces the applicability, and requires performing corrective actions by complying with certain portions of the updated service bulletin. The FAA is issuing this AD to address the unsafe condition on these products.
87-06-09: 87-06-09 MECHANICAL PRODUCTS, INC.: Amendment 39-5585. Applies to the following 4001, 4200, 4310, and 8500 Series circuit breakers: Mechanical Products Designation Military Designation Ampere Rating Date Code 4001 Series MS22073 1 thru 5 8501 thru 8636 4200 Series MS26574 1/2 thru 5 8430 thru 8636 4310-001, -019 Series MS3320 1 thru 5 8605 thru 8636 8500 Series (None) 1 thru 5 8514 thru 8636 This AD does not apply to circuit breakers produced or installed prior to July 23, 1984, (the thirtieth week of 1984), or to circuit breakers which have been inspected by the manufacturer, found free of defect, marked with a white inverted Z or a T painted on the terminal end, and have an additional date code with an "R" prefix. NOTE 1: As an aid in identification, the bodies of these circuit breakers are blue or black in color. NOTE 2: The date codes listed above are used to identify the year and week of manufacture; i.e., 8430 indicates the thirtieth week of 1984, and 8636 indicates the thirty-sixth week of 1986. These date codes may be found on the top, side, or bottom of the circuit breakers. NOTE 3: As an example, the unit may have the additional date code of R8642, where "R" designates a retest by Mechanical Products, 86 indicates the year 1986, and 42 indicates the 42nd week of 1986. Compliance: Required as indicated after the effective date of this AD. To prevent possible loss of essential equipment, electrical fire, or electrical shock hazard on aircraft, accomplish the following: (a) Within six months after the effective date of this AD, accomplish the following: (1) Visually inspect for installation in aircraft of any of the applicable circuit breakers and prior to further flight remove all units from service, or (2) Visually inspect for installation in aircraft of any of the applicable circuit breakers in accordance with the instructions contained in Mechanical Products Service Instruction (identification on the back page with the date 10/86) and, prior to further flight, remove all units from service, or (3) Determine that none of the applicable circuit breakers are installed in aircraft by an examination of maintenance and/or purchasing records. NOTE: Return of all affected circuit breakers to Mechanical Products, Inc., 1824 River Street, P.O. Box 729, Jackson, Michigan 49204, is recommend and may enhance replacement part availability. (b) Aircraft may be flown in accordance with FAR 21.197 to a location where the AD may be accomplished. (c) An adjustment to the compliance time or an equivalent means of compliance with this AD may be used if approved by the Manager, Chicago Aircraft Certification Office, ACE-115C, 2300 East Devon Avenue, Des Plaines, Illinois 60018. All persons affected by this directive may obtain copies of the document(s) referred to herein upon request to Mechanical Products, Inc., 1824 River Street, P.O. Box 729, Jackson, Michigan 49204; or may examine the document(s) referred to herein at FAA, Office of the Regional Counsel, Room 1558, 601 East 12th Street, Kansas City, Missouri 64106. This amendment becomes effective on April 27, 1987.
57-08-06: 57-08-06 VICKERS: Applies to Viscount 744 and 745 Type Aircraft. Compliance required as indicated. In view of a recent horizontal stabilizer buckling incident compliance with the following is required: 1. Effective immediately the following placard must be installed in full view of the pilot: "TURBULENT AIR PENETRATION-165-KNOTS-FLAPS UP-LANDING GEAR UP." (This placard required regardless of compliance with item 2.) 2. Compliance required by August 31, 1957, with Vickers Modification D.1906. This modification introduces new horizontal stabilizer skin panels of 18 gage, Specification L.73 material between Stations 34.36 and 99.13 in lieu of the 20-gage panels of Specification L.72.
85-14-11: 85-14-11 BELL HELICOPTER TEXTRON, INC,: Amendment 39-5812. Applies to Model 222 helicopters, serial numbers 47008 through 47089; Model 222B helicopters, serial numbers 47131 through 47143; Model 222U helicopters, serial numbers 47501 through 47537, and 47539. Compliance is required prior to next flight after the effective date of this AD unless previously accomplished in accordance with BHTI ASB 222-85-33, dated August 13, 1985, or ASB 222U-85-8, dated August 13, 1985. To prevent the loss of a rivet and ultimate disconnection of the control linkage on tail rotor control servo 222-382-002-101, accomplish the following: (a) Prior to next flight, after the effective date of this AD, visually inspect installation of linkage rivets (3) for shop-formed head in accordance with BHTI ASB No. 222-85- 33, dated August 13, 1985, or 222U-85-8, dated August 13, 1985. NOTE: Parts are identified in BHTI Model 222 Component Repair and Overhaul Vol. 2, Chapter 29-00-1 pp. 1009and 1010, Fig. 1, Index Number 46, 54, and 156 rivets, March 16, 1981. b. If the shop-formed head on each rivet is not evident, or if either rivet is loose or missing, the tail rotor control servo must be replaced prior to further flight. c. An alternate method of compliance which provides an equivalent level of safety, may be used when approved by the Manager, Helicopter Certification Branch, Aircraft Certification Division, FAA, Southwest Region. The above procedures shall be done in accordance with BHTI ASB No. 222-85-33, dated August 13, 1985, or 222U-85-8, dated August 13, 1985, as appropriate. This incorporation by reference was approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a)(1) and 1 CFR Part 51. Copies may be obtained from BHTI, P.O. Box 482, Fort Worth, Texas 76101. Copies may be inspected at the Office of the Regional Counsel, FAA, Southwest Region, 4400 Blue Moune Road, Fort Worth, Texas, or at the Office of the Federal Register, 1100 L Street, N.W., Room 8401, Washington, D.C. This amendment 39-5812 becomes effective February 9, 1988, as to all persons except those persons to whom it was made immediately effective by priority letter AD 85-14-11, issued July 26, 1985, which contained this amendment.
2015-26-02: We are adopting a new airworthiness directive (AD) for all Airbus Model A330-200, A330-200 Freighter, and A330-300 series airplanes; and Airbus Model A340-200, A340-300, A340-500, and A340-600 series airplanes. This AD was prompted by a report that, during a production flight test, the ram air turbine (RAT) did not pressurize the green hydraulic system. For certain airplanes, this AD requires identification of the part number, serial number, and standard of the RAT pump, RAT module, RAT actuator, and RAT lower gearbox assembly; replacement of the balance weight screw, modification of the actuator coil spring, modification of the actuator, an inspection of the anti- stall valve for correct installation in the RAT pump housing; and corrective actions if necessary. For certain other airplanes, this AD requires re-identification or replacement of the RAT module. We are issuing this AD to prevent loss of the impeller function and RAT pump pressurization capability, which, if preceded by a total engine flame- out, could result in the loss of control of the airplane.
88-19-06: 88-19-06 CESSNA: Amendment 39-6014. Applies to Model 208B (Serial Numbers 208B0001 through 208B0106) airplanes certificated in any category. Compliance: Required within the next 50 hours time-in-service after effective date of this AD, unless already accomplished. To prevent possible elevator flutter, accomplish the following: (a) Check both elevators for correct balance in accordance with the procedures given in Cessna Service Bulletin CAB 88-27, dated August 19, 1988. If any elevator is out of balance, prior to further flight rebalance the elevator in accordance with the instructions and the criteria contained in the above Service Bulletin. NOTE: The elevator balance limits currently shown in the Maintenance Manual for the 208 series airplane are not applicable to the 208B. (b) Airplanes may be flown in accordance with FAR 21.197 to a location where this AD may be accomplished. (c) An equivalent means of compliance with this AD may be used if approved by the Manager, Wichita Aircraft Certification Office, FAA, 1801 Airport Road, Room 100, Wichita, Kansas 67208; telephone (316) 946-4400. All persons affected by this directive may obtain copies of the document(s) referred to herein upon request to Cessna Aircraft Co., Customer Services, P.O. Box 7704, Wichita, Kansas 67277; telephone number (316) 946-7550; or may examine the document(s) referred to herein at FAA, Office of the Regional Counsel, Room 1558, 601 East 12th Street, Kansas City, Missouri 64106. This amendment, 39-6014, becomes effective on September 30, 1988.
2024-25-11: The FAA is superseding Airworthiness Directive (AD) 2022-19- 02, which applied to certain Airbus SAS Model A330-200, -200 Freighter, and -300 series airplanes; and Model A330-841 and A330-941 airplanes. AD 2022-19-02 required revising the existing maintenance or inspection program, as applicable, to incorporate new or more restrictive airworthiness limitations. This AD was prompted by a determination that new or more restrictive airworthiness limitations are necessary. This AD continues to require certain actions in AD-2022-19-02, and 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.
87-11-01 R1: 87-11-01 R1 BELLANCA: Amendment 39-5624 as amended by Amendment 39-5684. Applies to Models 17- 30, 17-30A, 17-31, 17-31A, 17-31TC, and 17-31ATC (all serial numbers) airplanes certificated in any category. Compliance: Required as indicated, unless already accomplished. To preclude engine power loss due to either the accumulation of water or other contaminants in the fuel system or due to mismanagement of available fuel resources caused by lack of pilot familiarity with the airplane fuel system design and operating procedures, accomplish the following: (a) For all airplanes, within the next 30 days after the effective date of this AD or at the next annual inspection, whichever occurs later, and thereafter at each annual inspection, inspect the fuel filler caps and fuel filler well (scupper) drains in accordance with the instructions contained in Section II of Bellanca Service Letter No. B-105, dated February 2, 1987. (b) For Bellanca Models and Serials identifiedin Table 1., within the next 30 days after the effective date of this AD, accomplish the following: (1) Install the appropriate AFM revision, as specified in Table 1. (2) Install permanent placards which state the following at the specified airplane locations: (i) For Models 17-30 and 17-30A, on the instrument panel adjacent to the auxiliary fuel pump switch: "USE TO RESTORE FUEL PRESSURE AND RELEASE TO PREVENT ENGINE FLOODING." (ii) On the instrument panel adjacent to the fuel quantity gauges: "FUEL GAUGES READ QUANTITY IN TANK SELECTED, MAIN FUEL TANK GAUGE INOPERATIVE WHEN AUXILIARY TANK SELECTED. FUEL REMAINING IN SELECTED TANK CANNOT BE USED SAFELY IN FLIGHT WHEN GAUGE READS ZERO." (iii) On the console adjacent to the fuel selector valve (on airplanes with a 58 gallon capacity fuel system): "LEFT TANK: 15.5 GALLONS RIGHT TANK: 15.5 GALLONS AUXILIARY TANK: 20 GALLONS USE AUX. TANK IN LEVEL FLIGHT ONLY." (3) Placards specified in (b)(2)(i), (b)(2)(ii), and (b)(2)(iii) may be fabricated and installed using letters with minimum 1/10 inch height. NOTE: The AFM revisions specified above (and associated placards) are available at a nominal cost from Bellanca, Inc., P.O. Box 964, Alexandria, Minnesota 56308; Telephone (612) 762-1501. The placards are revised versions of existing placards. The existing placards may either be removed and discarded or overlaid by the corresponding revised placard. The placard specified in paragraph (2)(iii) deletes information which was contained in the placard being replaced. This information, however, is presented more clearly in the placard of paragraph (2)(ii) which is a new placard for the airplanes to which paragraph (2)(iii) applies. (c) The requirements of paragraph (b) of this AD may be accomplished by the holder of a pilot certificate issued under Part 61 of the Federal Aviation Regulations (FAR) on any airplane owned or operated by him, provided the airplanes are not used in air taxi operations. The person accomplishing these actions must make the appropriate aircraft maintenance record entry as prescribed by FAR 91.173. (d) Airplanes may be flown in accordance with FAR 21.197 to a location where this AD may be accomplished. (e) An equivalent means of compliance with this AD may be used if approved by the Manager, Chicago Aircraft Certification Office, FAA, 2300 East Devon Ave., Des Plaines, Illinois 60018; Telephone (312) 694-7357. All persons affected by this directive may obtain copies of the document(s) referred to herein upon request to Bellanca, Inc., P.O. Box 964, Alexandria, Minnesota 56308; or may examine the document(s) referred to herein at FAA, Office of the Regional Counsel, Room 1558, 601 East 12th Street, Kansas City, Missouri 64106. Amendment 39-5624 became effective June 22, 1987. This amendment, 39-5684, becomes effective on August 28, 1987. Table 1. Serial Numbers (may be AFMRevision Model prefixed with year of manufacture) to be installed. 17-30 30001 - 30262 Rev. 15, dtd. 2/2/87 -30A 30263 - 30514 (except 30498) Rev. 6, dtd. 2/2/87 -31 32-1 - 32-14 Rev. 2, dtd. 2/2/87 -31A 32-15 - 32-102 Rev. 8, dtd. 2/2/87 -31TC 31001 - 31003 Rev. 2, dtd. 2/2/87 -31ATC 31004 - 31046 Rev. 8, dtd. 2/2/87
87-04-16: 87-04-16 LOCKHEED-CALIFORNIA COMPANY: Amendment 39-5539. Applies to Lockheed Model L-1011 series airplanes equipped with carbon fibre cowls, certificated in any category. Compliance is required within 12 months after the effective date of this AD, unless already accomplished. To prevent loss of throttle control caused by an unstowed left rear fan cowl door support on carbon fibre cowls, accomplish the following: A. Modify the fan cowl support strut stowage mechanism in accordance with Rolls- Royce Service Bulletin RB211-71-8220, dated May 23, 1986, or later revisions approved by the Manager, Los Angeles Aircraft Certification Office, FAA, Northwest Mountain Region. B. Alternate means of compliance which provides 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 airplanes toa base for the accomplishment of 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 Rolls-Royce PLC, P.O. Box 31, Derby DE 2 8BJ, England, Attention: Technical Publications Department. 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 March 9, 1987.
75-17-23 R2: 75-17-23 R2 SIAI-MARCHETTI: Amendment 39-2328 as amended by Amendment 39-4612 is further amended by Amendment 39-5139. Applies to Models S205-18F, S205-18R, S205-20F, S205-20R, S205-22R, S208, and S208A airplanes certificated in any category. Compliance is required as indicated. To detect cracks which could result in the possible failure of the landing gear operating mechanism, accomplish the following: (a) Within the next 25 hours time in service after the effective date of this AD, unless already accomplished within the last 75 hours time in service, and thereafter at intervals not to exceed 100 hours time in service from the last inspection, inspect the internal wing rib brackets, P/N's 205-3-033-18 and 205-3-034-18 for cracks in accordance with Instructions Paragraph (a) of SIAI Marchetti Service Bulletin No. 205B37D, dated March 15, 1985, or an FAA-approved equivalent. (b) If cracks are found during an inspection required by Paragraph (a) of this AD that are in excess of 10 mm (0.394 inch) in length, before further flight comply with the following: (1) Replace the affected brackets with new brackets of the same part number. (2) Unless already accomplished replace the associated washers, P/N AN960-516L, with new design countersunk washers, P/N 205-3-053-16, in accordance with Instructions Paragraph (b) of SIAI Marchetti Service Bulletin No. 205B37D, dated March 15, 1985, or an FAA-approved equivalent. (c) Following accomplishment of Paragraph (b) of this AD continue to inspect in accordance with Paragraph (a) of this AD until brackets P/N 205-3-033-18 and 205-3-034-18 are replaced by new brackets P/N 205-3-313-11 and P/N 205-3-313-12 in accordance with Instructions Paragraph (b) of SIAI-Marchetti Service Bulletin S/B No. 205B37D, dated March 15, 1985. Amendment 39-2328 became effective August 20, 1975. Amendment 39-4612 became effective April 14, 1983. This Amendment 39-5139 becomes effective September 27, 1985.
2015-26-03: We are superseding Airworthiness Directive (AD) 2011-07-10 for certain Bombardier, Inc. Model BD-100-1A10 (Challenger 300) airplanes. AD 2011-07-10 required revising the Airworthiness Limitations section of the Instructions for Continued Airworthiness; doing detailed visual inspections; removing discrepant material; cleaning the surfaces of the valves, the plug of the sensing port, and the cabin pressure-sensing port plug; securing the insulation; installing a new safety valve, and replacing certain cabin pressure-sensing port plugs. This new AD retains all requirements of AD 2011-07-10, and requires a detailed visual inspection of both safety valves and the surrounding area for foreign material, room temperature vulcanizing (RTV) silicone, contamination, foam on the bulkhead structure, tape or insulation, and loose material; and corrective actions if necessary. This AD was prompted by reports of in-flight loss of cabin pressurization that was attributed to partial blockage ofa safety valve cabin pressure-sensing port in conjunction with a failed safety valve manometric capsule. We are issuing this AD to detect and correct blockage of a safety valve cabin pressure-sensing port, which could result in loss of cabin pressure.
88-25-03: 88-25-03 BOEING: Amendment 39-6072. Applies to all Model 707-300, -300B, -300C, and -400 series airplanes, certificated in any category. Compliance required as indicated, unless previously accomplished.\n\n\tNOTE: The inspections required by AD 85-12-01 are not changed by this action.\n\n\tTo prevent the separation of the horizontal stabilizer, accomplish the following:\n\n\tA.\tFor airplanes on which the modification required by AD 79-01-06 has not been accomplished: Prior to the accumulation of 8,000 total landings, install structural improvement kits on the horizontal stabilizer outer panels and center section in accordance with Boeing Alert Service Bulletin A3313, Revision 9, dated February 25, 1988, Boeing Service Bulletin 3253, Revision 3, dated February 25, 1988, and Boeing Service Bulletin 3331, Revision 3, dated June 15, 1979.\n\n\tB.\tFor airplanes which have been modified in accordance with Boeing Service Bulletin A3313, Revision 8, or earlier revisions, or Boeing ServiceBulletin 3253, Revision 2, or earlier revisions, in compliance with AD 79-01-06: Within one year after the effective date of this AD, rework the clevis fittings in accordance with Boeing Alert Service Bulletin A3313, Revision 9, dated February 25, 1988, and Boeing Service Bulletin 3253, Revision 3, dated February 25, 1988.\n\n\tC.\tAccomplishment of the modification requirements of this AD, constitutes terminating action for this AD and AD's 77-16-11 and 78-01-04.\n\n\tD.\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, FAA, Northwest Mountain Region.\n\n\tNOTE: The request should be forwarded through an FAA Principal Maintenance Inspector (PMI), who may add any comments and then send it to the Manager, Seattle Aircraft Certification Office.\n\n\tE.\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 Airplanes, P.O. Box 3707, Seattle, Washington 98124. 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 supersedes AD 79-01-06, Amendment 39-3388, effective February 10, 1979.\n\tThis amendment, 39-6072, becomes effective December 30, 1988.
59-25-03: 59-25-03 HILLER: Applies to Hiller UH Series Helicopters As Follows: (a) UH-12 and UH-12A - incorporating both P/N 34126 wobble plate shield and P/N 34158 forged lower cyclic scissors. (b) UH-12B and UH-12C - incorporating the P/N 34158 forged lower cyclic scissors. (c) UH-12D - all Serial Numbers. (d) UH-12E - Serials 942, 954, and 2001 through 2018. Compliance required as indicated. To prevent contact between the lower cyclic scissors and the filister head screws attaching the wobble plate shield, which can result in damage to the lower scissors and subsequent loss of cyclic control, the following inspection and rework are required. (1) Daily inspect the lower cyclic scissors P/N 34158 on all models, or P/N 34141 on Models UH-12D and UH-12E for damage due to striking the wobble plate shield attachment screws. Damaged scissors must be replaced prior to next flight. (2) Not later than January 1, 1960, replace the filister head screws attaching thewobble plate shield with AN 509-8R4 flush head screws in accordance with the procedures in Hiller Service Bulletins No. 87 or No. 2004. (3) Upon accomplished of item (2) the inspections of item (1) may be discontinued.
2024-25-10: The FAA is adopting a new airworthiness directive (AD) for certain Rolls-Royce Deutschland Ltd & Co KG (RRD) Model Trent XWB-97 engines. This AD was prompted by a report of damage to the main fuel hose assembly of the fuel manifold, which resulted an in-flight shut down. This AD requires a one-time set of visual and dimensional inspections of the main fuel hose assembly of the fuel manifold to confirm softness, compliance, and lack of resistance, and for shrinkage, cracks, chafing, dents, kinks, necking, and degradation of the hose braid wire; and, if necessary, replacement of the main fuel hose assembly of the fuel manifold, 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.